Aeronautical NASA SP-7037(219) November 1987 Engineering A Continuing Bibliography with Indexes

National Aeronautics and Space Administration

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ACCESSION NUMBER RANGES

Accession numbers cited in this Supplement fall within the following ranges.

STAR (N-10000 Series) N87-25267 -- N87-26853

IAA (A-10000 Series) A87-42685 -- A87-47019

This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by RMS Associates. NASA SP-7037(219)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 219)

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientificand technical informationsystem and announced in October 1987 in

• Scientific and Technical Reports (STAR) • International Aerospace Abstracts (IAA).

Scientific and Technical Information Division 1987 National Aeronautics and Space Administration Washington, DC Thissupplementis availablefromthe NationalTechnicalInformationService(NTIS),Springfield, Virginia22161,pricecodeA08. INTRODUCTION

This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 586 reports, journal articles and other documents originally announced in October 1987 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construc- tion, evaluation, testing, operation, and performance of (including aircraft ) and as- sociated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical . Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged by the first nine STAR specific categories and the remaining STAR major categories. This arrangement offers the user the most advantageous breakdown for individual objectives. The citations include the original accession numbers from the respective announcement journals.The IAA items will precede the STAR items within each category Seven indexes -- subject, personal author, corporate source, foreign technology, contract number, report number, and accession number -- are included. An annual cummulative index will be published.

Information on the availability of cited publications including addresses of organizations and NTIS price schedules is located at the back of this bibliography. TABLE OF CONTENTS

Page Category 01 Aeronautics (General) 623

Category 02 Aerodynamics 625 Includes aerodynamics of bodies, combinations,wings, rotors,and controlsurfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 646 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 648 Includes digital and voice communication withaircraft; air navigation systems (satel- lite and ground based); and air traffic control.

Category 05 Aircraft Design, Testing and Performance 650 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 660 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 663 Includes prime propulsion systems and systems components, e.g., engines and compressors; and onboard auxiliary power plants for aircraft.

Category 08 Aircraft Stability and Control 678 Includes aircraft handling qualities; piloting;flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 683 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and test stands.

Category 10 Astronautics 688 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; space communications, spacecraft communications, command and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft pro- pulsion and power.

Category 11 Chemistry and Materials 688 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallicmaterials; propellants and fuels; and materials processing.

v PAGE [ _ !._IT.r_.!,TZO!.I_LI..YBLkNK 692 Category 12 Engineering Includes engineering (general); communications and radar; electronics and electri- cal engineering; fluid mechanics and heat transfer; instrumentation and photo- graphy; lasers and masers; mechanical engineering; quality assurance and relia- bility;and structural mechanics.

702 Category 13 Geosciences Includes geosciences (general); earth resources and remote sensing; energy pro- duction and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.

Category 14 Life Sciences NoA, Includes life sciences (general); aerospace medicine; behavioral sciences; man/ system technology and life support; and space biology.

704 Category 15 Mathematical and Computer Sciences Includes mathematical and computer sciences (general); computer operations and hardware; computer programming and software; computer systems; cybernetics; numerical analysis; statistics and probability; systems analysis; and theoretical mathematics.

707 Category 16 Physics Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and ther- modynamics and statistical physics.

708 Category 17 Social Sciences Includes social sciences (general); administration and management; documenta- tion and information science; economics and cost analysis; law, political science, and space policy; and urban technology and transportation.

Category 18 Space Sciences NoA, Includes space sciences (general); astronomy; astrophysics; lunar and planetary exploration; solar physics; and space radiation.

709 Category 19 General

Subject Index ...... A-1 Personal Author Index ...... B-1 Corporate Source Index ...... C-1 Foreign Technology Index ...... _...... D-1 Contract Number Index ...... E-1 Report Number Index ...... F-1 Accession Number Index ...... G-1

vi TYPICAL REPORT CITATION AND ABSTRACT

NASA SPONSORED

[ _--_ON MICROFICHE

ACCESSION NUMBER------,- N87-I0039"# National Aeronautics and Space Administration-._.---CORPORATE SOURCE Langley Research Center, Hampton, Va TITLE WIND-TUNNEL INVESTIGATION OF THE FLIGHT CHARACTERISTICS OF A GENERAL-AVIATION -PUBLICATION DATE AIRPLANE CONFIGURATION AUTHOR D. R. SATRAN Oct. 1986_'_p j .AVAILABILITY SOURCE REPORT NUMBERS-_--_ (NASA-TP-2623; L-15929; NAS 1.60:2623) Avail: NTIS HC PRICE CODE -_-_ A04/MF A01 CSCL 01A -.,- COSATI CODE A 0.36-scale model of a canard general-aviation airplane with a single pusher and winglets was tested in the Langley 30- by 60-Foot Wind Tunnel to determine the static and dynamic stability and control and free-flight behavior of the configuration. Model vanables made testing of the model possible with the canard in hiqh and low positions, with increased winglet area, with outboard winy leading-edge droop, with fuselage-mounted vertical fin and , with enlarged , with dual deflecting rudders, and with mounted closer to the wing tips. The basic model exhibited generally good longitudinal and lateral stability and control characteristics. The removal of an outboard leading-edge droop degraded roll damping and produced lightly damped roll (wing rock) oscillations. In general, the model exhibited very stable dihedral effect but weak directional stability. Rudder and control power were sufficiently adequate for control of most flight conditions, but appeared to be relatively weak for maneuvering compared with those of more conventionally configure d models. Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED

ACCESSION NUMBER-----,-A87-11487" National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. COMPUTATION OF TURBULENT SUPERSONIC FLOWS -,,_-----TITLE AROUND POINTED BODIES HAVING CROSSFLOW SEPARATION AUTHORS_D. DEGANI and L. B. SCHIFF (NASA, Ames Research Center,-.,,_--AUTHOR'S AFFILIATION JOURNAL TITLE Moffett Field_ CA)_._. Journal of Computational Physics (ISSN 0021-9991), vol. 66, Sept. 1986, p. 173-196. refs The numerical method developed by Schiff and Sturek (1980) on the basis of the thin-layer parabolized Navier-Stokes equations of Schiff and Steger (1980) is extended to the case of turbulent supersonic flows on pointed bodies at high angles of attack. The governing equations, the numerical scheme, and modifications to the algebraic eddy-viscosity turbulence model are described; and results for three cones and one ogive-cylinder body (obtained using grids of 50 nonuniformly spaced points in the radial direction between the body and the outer boundary) are presented graphically and compared with published experimental data. The grids employed are found to provide sufficient spatial resolution of the leeward-side vortices; when combined with the modified turbulence model, they are shown 1o permit accurate treatment of flows with large regions of crossflow separation. T.K. AERONAUTICAL

ENGINEERING A Continuing Bibliography (Suppl. 219)

NOVEMBER 1987

01 Cierva. The autogiro, an antecedent of the helicopter, employs a vertical-axis rotor with slight positive pitch which turns freely to AERONAUTICS(GENERAL) generate lift when the aircraft suspended to which the rotor is attached moves under the power of a conventional propulsion system. Attention is given to the Da Vinci, Cornu, Brequet, and Pascara designs that preceded de la Cierva's work, and to the Flettner, Focke, Sikorsky and Fairey designs that derived some measure of inspiration from the de la Cierva autogiro after his A87-42857 death in 1936. O.C. AIRCRAFT STRUCTURAL MAINTENANCE RECOMMENOA- TIONS BASED ON FRACTURE MECHANICS ANALYSIS A87-43723# ANTHONY G. DENYER (Rockwell International Corp., Los Angeles, TECHNOLOGICAL CHANGE AND SKILL REQUIREMENTS - A CA) IN: Case histories involving fatigue and fracture mechanics; CASE STUDY OF NUMERICALLY CONTROLLED RIVETING IN Proceedings of the Symposium, Chadeston, SC, Mar. 21, 22, 1985 COMMERCIAL AIRCRAFT MANUFACTURE . Philadelphia, PA, American Society for Testing and Materials, ERIC BASQUES and BRADLEY T. SHAW (U.S. Congress, Office 1986, p. 291-310. refs of Technology Assessment, Washington, DC) ASME, Winter The implementation of the Force Management phase of the Annual Meeting, Anaheim, CA, Dec. 7-12, 1986. 6 p. refs Aircraft Structural Integrity program for a USAF aircraft is discussed. (ASME PAPER 86-WA/TS-2) The case study considered demonstrates use of linear elastic fracture mechanics to show that the T-39 wing performs to the structural criteria defined by the MIL-STD-1530 and MIL-A-83444. A87-44228# The initial task of the fracture mechanics analysis was the durability THE RUDDER - AN EXAMPLE OF NEW FABRICATION and damage tolerance assessment (DATA) of the structure, based TECHNOLOGIES [DAS AIRBUS-SEITENLEITWERK EIN on the current service usage, the result of which were used to BEISPIEL NEUER FERTIGUNGSTECHNOLOGIEN] make structural life-enhancement recommendations. The DATA GO'I-rHARD MENZE (Messerschmitt-Boelkow-Blohm GmbH, Werk was followed by the individual aircraft tracking program the purpose Stade, West Germany) Luft- und Raumfahrt (ISSN 0173-6264), of which is to compute the rate at which the available structural vol. 8, 1st Quarter 1987, p. 14-18. In German. life of an individual aircraft is being used and to estimate the New technologies used to fabricate the A320 rudder are remaining structural life. The economic crack growth procedure described. It was determined that in order to develop an Airbus used, both to ascertain the accumulated damage based on the rudder with maximum strength and long life it was necessary to flight records and to estimate the remaining structural life, is utilize lightweight materials. The use of carbon-fiber-reinforced described. I.S. plastics as the construction material for the rudder is examined. The basic principles of the double-T construction method used to develop the grid structure for the rudder are reviewed. The A87-43401 # production and assembly procedures and equipment used to HELICOPTER ACTIVITIES IN GERMANY fabricate the rudder are discussed. Particular attention is given to VOLKER VON TEIN (Messerschmitt-Boelkow-Blohm GmbH, the prepreg blank, tape layering machine, wrapping and rigging Munich, West Germany) DGLR, European Rotorcraft Forum, machine, autoclave, machine processing, and ultrasound testing. 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, I.F. Paper. 22 p. After a short presentation of the history of helicopter technology in Germany, the current activities are described. In this context A87-44265 Operations Research, Inc., Rockville, Md. an update on the BO 105 and BK 117 programs is given. Next, ROTORCRAFT RESEARCH - A NATIONAL EFFORT (THE 1988 statistical information about all types of helicopters operating in ALEXANDER NIKOLSKY HONORARY LECTURESHIP) Germany and the related infrastructure is presented. Then the JOHN F. WARD (ORI, Inc., Aeronautics and Space Technology most important technology programs covering rotor technology, Div., Rockville, MD) American Helicopter Society, Journal (ISSN vibration suppression, advanced composite , 0002-8711), vol. 32, April 1987, p. 3-20. Research supported by avionics/cockpits, and flight controls are presented. A further main the American Helicopter Society, ORI, Inc., U.S. Army, and NASA. topic is the description of the most important future helicopter refs projects with German participation, such as the PAH 2, NH 90, The present history of rotary-wing and v'rOL aircraft and the Advanced Light Helicopter. Author development initiatives in the U.S. notes that most such R&D efforts have tended to be 'threat-driven'; the threat has in recent A87-43426# years passed from one of a primarily military character to one of SPANISH CONTRIBUTION TO ROTORCRAFT DEVELOPMENT global civilian market growth competition. Recommendations are - HOMAGE TO DE LA CIERVA made concerning remaining research requirements in rotorcraft ANGEL GARCIA-FRAILE (Guardia Civil, Madrid, Spain) DGLR, fluid dynamics, structural mechanics, and human factors European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West engineering. Next-generation configurations to be intensively Germany, Sept. 22-25, 1986, Paper. 28 p. refs developed encompass tilt-rotors, advancing blade concept A development history and historical influence evaluation are helicopters, convertible X-wings, and folding-blade tilt-rotors. presented for the autogiros designed and built by Juan de la O.C.

623 01 AERONAUTICS(GENERAL)

A87-44731 A87-46177"# National Aeronautics and Space Administration, MATERIALS IN HELICOPTERS - A REVIEW Washington, D.C. D. HOLT (Westland, PLC, Yeovil, England) IN: Materials in CIVIL PROPULSION TECHNOLOGY FOR THE NEXT aerospace; Proceedings of the First International Conference, TWENTY-FIVE YEARS London, England, Apr. 2-4, 1966. Volume 1 . London, Royal ROBERT ROSEN and JOHN R. FACEY (NASA, Washington, DC) Aeronautical Society, 1986, p. 17-28. IN: International Symposium on Air Breathing Engines, 8th, The application of advanced materials to the construction of Cincinnati, OH, June 14-19, 1987, Proceedings . New York, helicopter structures and mechanical components is motivated by American Institute of Aeronautics and Astronautics, 1987, p. 3-13. the desire to improve airworthiness and safety, reduce empty weight The next twenty-five years will see major advances in civil fraction, reduce purchase and operating costs, and improve propulsion technology that will result in completely new aircraft operational performance capability. In introducing a novel material, systems for domestic, international, commuter and high-speed attention must be given to intrinsic variability in basic material transports. These aircraft will include advanced aerodynamic, properties and variability due to manufacturing processes, as well structural, and avionic technologies resulting in major new system as to the behavior to be expected from the material in the course capabilities and economic improvements. Propulsion technologies of use throughout its operational environment and service life. An will include high-speed in the near term, very high examination is presently made of glass and carbon fiber-reinforced , high efficiency small engines and advanced plastics, thermoplastic matrices, welded titanium alloy, gearbox cycles utilizing high temperature materials for high-speed case magnesium alloy castings, and superplastically formed propulsion. Key fundamental enabling technologies include structures. O.C. increased temperature capability and advanced design methods. Increased temperature capability will be based on improved A87-44733 composite materials such as metal matrix, intermetallics, ceramics, HELICOPTER LUBRICATION and carbon/carbon as well as advanced heat transfer techniques. Advanced design methods will make use of advances in internal H. A. SPIKES (Imperial College of Science and Technology, computational fluid mechanics, reacting flow computation, London, England) IN: Materials in aerospace; Proceedings of computational structural mechanics and computational chemistry. the First International Conference, London, England, Apr. 2-4, 1986. The combination of advanced enabling technologies, new Volume 1 . London, Royal Aeronautical Society, 1986, p. 59-74. refs propulsion concepts and advanced control approaches will provide major improvements in civil aircraft. Author After discussing those characteristics of helicopters that render them generally difficult to satisfactorily lubricate, attention is given to the role specifically played bycurrent lubricants in such helicopter mechanical systems as the transmission, and to the present development status of materials for the fabrication of such mechanical systems. Because helicopter gas turbine engines are likely to become hotter and faster in operation in future years, A87-46182# lubricants with both thermal stability and higher viscosity will be U.S. AERONAUTICAL R&D GOALS - SST: BRIDGE TO THE required and may lead to the development of nonester-based NEXT CENTURY synthetic lubricants whose thermal stability is maintained into the JOHN M. SWIHART ( Co., Seattle, WA) IN: International 350-370 C range. O.C. Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . New York, American Institute of Aeronautics and Astronautics, 1987, p. 55-65. A87-44750 The present technology development status evaluation of CORROSION PROTECTION SST-related research trends in the past 15 years of R. G. MITCHELL and B. BELL (British Airways, PLC, Hounslow, NASA-sponsored efforts gives initial attention to the comparative England) IN: Materials in aerospace; Proceedings of the First advantages obtainable through next-generation subsonic transport International Conference, London, England, Apr. 2-4, 1986. Volume technology. An assessment is then made of the gains over 2. London, Royal Aeronautical Society, 1986, p. 440-449. first-generation SST performance that would be obtainable through A comprehensive consideration is undertaken of the factors incorporation of supersonic flow laminarization to improve lift/drag affecting the corrosion of civil aircraft structural components, giving and thereby reduce gross weight and sonic boom, the use of attention to the most effective methods for the prevention and thermoplastic matrix resin composites and superplastically formed solution of corrosion problems. Base structural materials become titanium alloy matrix structures, novel flight management systems, susceptible to corrosion whenever paints, platings and other and advanced variable cycle engines employing supersonic fans protective finishes are damaged. While most common forms of and generating more acceptable noise levels. The further range corrosion associated with metallic structures are electrolytic, of design options available for hypersonic transport design is composite materials' joining to metallic ones also leads to discussed. O.C. battery-like situations. Numerous other possible problem areas are presently identified, and recommendations are made. O.C.

A87-45159# ENGINE MAINTENANCE IMPROVEMENT CONSIDERATIONS C. L. CALLIS and C. E. CURRY (General Motors Corp., Allison A87-46708# Gas Turbine Div., Indianapolis, IN) AIAA, SAE, ASME, and ASEE, THE REAL WORLD - A MAINTAINER'S VIEW Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July CHARLES M. WORM (USAF, Coordinating Office for Logistics 2,1987.8p. refs Research, Wright-Patterson AFB, OH) IN: 1987 Annual Reliability (AIAA PAPER 87-1716) and Maintainability Symposium, Philadelphia, PA, Jan. 27-29, 1987, Major considerations used to improve engine maintainability in Proceedings . New York, Institute of Electrical and Electronics military and commercial applications are identified. In particular, Engineers, Inc., 1987,--p. 86-90. reliability and maintainability factors are developed through logistics Military aircraft maintainers believe that aircraft designers do support analysis, and the concept of reliability-centered not fully understand what it really takes to keep the aircraft flying. maintenance is discussed. Five different systems are This paper discusses that perception and presents several analyzed to show how reliability and maintainability methodology examples of problems caused by poor accessibility and design. can be used to achieve the largest improvement in operational Examples of design improvements to facilitate easier and faster capability for the least cost. V.L. field servicing and repair are also described. Author

624 02 AERODYNAMICS

A87-46716 airplanes and reported in NASA-TM-84660, and together they SPARING TO OPTIMIZE NAVAL AIRSHIP AVAILABILITY provide a data base for the design and analysis of general aviation LARRY S. MICKEL and EUGENE E. NEWMAN (Westinghouse airplane operations. Author Electric Corp., Baltimore, MD) IN: 1987 Annual Reliability and Maintainability Symposium, Philadelphia, PA, Jan. 27-29, 1987, N87-25990# Rand Graduate Inst. for Policies Study, Santa Proceedings . New York, Institute of Electrical and Electronics Monica, Calif. Engineers, Inc., 1987, p. 264-267. refs NATIONAL AEROSPACE PLANE PROGRAM: PRINCIPAL Long relegated to the status of airborne bulletin boards, current ASSUMPTIONS, FINDINGS AND POLICY OPTIONS technological advances in Lighter-Than-Air (LTA) craft have SCOTT PACE Dec. 1986 24 p Presented at a course on the renewed interest in airships for both commercial and military Uses of History in Public Policy, Santa Monica, Calif., Fall 1986 applications. The proposed use of these long endurance patrol (RAND/P-7288-RGS) Avail: NTIS HC A02/MF A01 craft to support Naval Surface Action Groups has triggered Top-level issues raised by the National Aerospace Plane maintenance planning for airship support above the world's oceans. Program (NASP) are examined. Its principle points are: major This paper describes a logistically optimal spares distribution uncertainties in the rate of NASP technical progress, cost technique for maximizing naval airship operational availability. projections, and potential applications of NASP technology. NASP Author development costs and possible increases may force tradeoffs with other research and development efforts in subsonic aircraft N87-25267"# National Aeronautics and Space Administration. and launch technology. The FY88-89 budget will require Langley Research Center, Hampton, Va. decisions on major funding increases for flying technology WIND SHEAR/TURBULENCE INPUTS TO FLIGHT SIMULATION demonstrators. The high classification of some NASP technologies AND SYSTEMS CERTIFICATION is limiting independent evaluation and may reduce commercial ROLAND L. BOWLES, ed. and WALTER FROST, ed. (FWG spinoffs. Major policy options that should be examined further Associates, Inc., Tullahoma, Tenn.) Jul. 1987 272 p Workshop are: maintain NASP research efforts, but deemphasize operational held in Hampton, Va., 30 May - 1 Jun. 1984 applications; hedge NASP research by expanding efforts in other (NASA-CP-2474; L-16329; NAS 1.55:2474) Avail: NTIS HC space and aeronautical transport programs; and increase NASA A12/MF A01 CSCL 01B responsibility for NASP work and ease classification restrictions. The purpose of the workshop was to provide a forum for NASP is a promising technical effort that has made significant industry, universities, and government to assess current status progress in the last year. The need for routine access to space and likely future requirements for application of flight simulators and aeronautical leadership makes NASP a national priority. The to aviation safety concerns and system certification issues costs and uncertainties of NASP, however, make it imperative to associated with wind shear and atmospheric turbulence. Research examine strategies for reducing its risks. Author findings presented included characterization of wind shear and turbulence hazards based on modeling efforts and quantitative results obtained from field measurement programs. Future research thrusts needed to maximally exploit flight simulators for aviation 02 safety application involving wind shear and turbulence were identified. The conference contained sessions on: Existing wind shear data and simulator implementation initiatives; Invited papers AERODYNAMICS regarding wind shear and turbulence simulation requirements; and Committee working session reports. Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery. N87-25291# Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn (West Germany). Untemehmensbereich Apparate. AIRCRAFT TECHNOLOGIES OF THE NINETIES IN MBB A87-43009"# North Carolina State Univ., Raleigh. PASSENGER AIRCRAFT PROJECTS [FLUGZEUG-TECHNO- AN INTERACTIVE APPROACH TO SURFACE-FITrlNG LOGIE DER 90ER JAHRE IN VERKEHRSFLUGZEUG-PROJEK- COMPLEX GEOMETRIES FOR FLOWFIELD APPLICATIONS TEN VON MBB] FRED R. DEJARNETTE (North Carolina State University, Raleigh), UWE GANZER 1986 40 p In GERMAN; ENGLISH summary H. HARRIS HAMILTON, II (NASA, Langley Research Center, Presented at the DGLR-Jahrestagung, Munich, West Germany, 8-10 Hampton, VA), and F. MCNEIL CHEATWOOD AIAA, Oct. 1986 Thermophysics Conference, 22nd, Honolulu, HI, June 8-10, 1987. (MBB-UT-21/86; DGLR-86-108; ETN-87-99962) Avail: Issuing 10 p. refs Activity (Contract NCC1-22; NCCI-100) Technologies for passenger aircraft in the nineties are treated. (AIAA PAPER 87-1476) The impact of new technologies on the economics of an aircraft Numerical flowfield methods require a geometry subprogram is considered. The propulsion concept, laminar and carbon which can calculate body coordinates, slopes, and radii of curvature fiber reinforced airfoils, as well as cockpit and flight control for typical aircraft and spacecraft configurations. The objective of techniques are reviewed, in order to identify problems involved in this paper is to develop a new surface-fitting technique which the development of these techniques. ESA addresses two major problems with existing geometry packages: computer storage requirements and the time required of the user N87-25293"# National Aeronautics and Space Administration. for the initial set-up of the geometry model. In the present method, coordinates of cross sections are fit in a least-squares sense Langley Research Center, Hampton, Va. FLIGHT DURATION, AIRSPEED PRACTICES AND ALTITUDE using segments of general conic sections. After fitting each cross MANAGEMENT OF AIRPLANES INVOLVED IN THE NASA VGH section, the next step is to blend the cross-sectional curve-fits in GENERAL AVIATION PROGRAM the longitudinal direction using general conics to fit specific JOSEPH W. JEWEL, JR. Aug. 1987 180 p meridional half-planes. For the initial setup of the geometry model, (NASA-TM-89074; L-16236; NAS 1.15:89074) Avail: NTIS HC an interactive, completely menu-driven computer code has been A09/MF A01 CSCL 01B developed to allow the user to make modifications to the initial fit Flight duration, airspeed, and altitude information obtained from for a given cross section or meridional cut. Graphic displays are NASA velocity gravity height (VGH) recorders is presented for provided to assist the user in the visualization of the effect of each of 95 general aviation airplanes flown in twin- and each modification. The completed model may be viewed from any single-engine executive, personal, instructional, commercial survey, angle using the code's three-dimensional graphics package. aerial application, aerobatic, commuter, and float operations. These Geometry results for the modeling of the Space Shuttle and a data complement normal acceleration data obtained from the same proposed Aeroassist Flight Experiment (AFE) geometry are

625 02 AERODYNAMICS presented, in addition to calculated heat-transfer rates based on been used. The perfect-gas flows were computed at two different these models. Author Reynolds numbers, including a flight trajectory point at maximum dynamic pressure, and on two different grids. Procedures for A87-43038"# National Aeronautics and Space Administration. coupling the solution of the species continuity equations with the Ames Research Center, Moffett Field, Calif. Navier-Stokes equations in the presence of chemical nonequilibrium THE THERMAL ENVIRONMENT OF TRANSATMOSPHERIC are reviewed and tested on the forebody of the AFE and on the VEHICLES complete flowfield assuming noncatalytic wall and no species MICHAEL E. TAUBER (NASA, Ames Research Center, Moffett diffusion. Problems with the STVD algorithm unique to flows with Field, CA) and HENRY G. ADELMAN (Eloret Institute, Sunnyvale, variable thermodynamic properties (real gas) are identified and CA) AIAA, Thermophysics Conference, 22nd, Honolulu, HI, June algorithm modifications are suggested. A potential heating problem 8-10, 1987. 15 p. refs caused by strong flow impingement on the nozzle lip in the near (AIAA PAPER 87-1514) wake at 0-deg angle of attack has been identified. Author A transatmospheric vehicle using primarily air-breathing propulsion must fly in the denser part of the atmosphere to achieve A87-43299 adequate acceleration to reach orbital speed. The potentially long VISCOUS-INVISCID INTERACTIONS IN EXTERNAL AERODY- ascent times, combined with the need for a low-drag configuration, NAMICS result in a severe aerothermodynamics environment. To achieve R. C. LOCK (City University, London, England) and B. R. WILLIAMS low drag, the vehicle must have a relatively sharp nose and wing (Royal Aircraft Establishment, Farnborough, England) Progress leading edges. The ascent peak stagnation point and equilibrium in Aerospace Sciences (ISSN 0376-0421), vol. 24, no. 2, 1987, p. wall temperatures for the wing leading edge can reach values of 51-171. refs 4000 K and 3000 K, respectively, for high dynamic pressure Interactive methods for the numerical modeling of viscous flows trajectories, making some form of mass addition cooling mandatory. are examined in an extensive analytical review, and typical results The corresponding temperatures during entry are about 1500 K are presented in graphs. The fundamental physics of lower. The vehicle windward centerline temperatures are more viscous-inviscid interactions is reviewed, and consideration is given moderate, however, with values peaking around 1500 K. Therefore, to three-dimensional interactive flows, coupling methods, methods radiative cooling should be effective over large areas of the vehicle. for two-dimensional incompressible and transonic flows, methods The windward, centerline heat loads are relatively insensitive to for axisymmetric transonic flows, and three-dimensional methods. the dynamic pressure of the ascent trajectory, in contrast to the The limitations of currently available techniques are indicated, and stagnation point and wing leading edge. The windward surface the potential for extending their applicability is assessed. T.K. entry heat loads are much lower, but depend strongly on the flightpath. Author A87-43376# FLOW OVER A TRAILING AND ITS ASYMMETRIC A87-43063"# Vigyan Research Associates, Inc., Hampton, Va. WAKE DIRECT SIMULATION OF AEROTHERMAL LOADS FOR AN S. ACHARYA, D. ADAIR, and J. H. WHITELAW (Imperial College AEROASSlST FLIGHT EXPERIMENT VEHICLE of Science and Technology, London, England) AIAA Journal VIRENDRA K. DOGRA (Vigyan Research Associates, Inc., (ISSN 0001-1452), vol. 25, July 1987, p. 897-904. rels Hampton, VA), JAMES N. MOSS, and ANN L. SlMMONDS (NASA, Detailed measurements of pressure and velocity characteristics Langley Research Center, Hampton, VA) AIAA, Thermophysics are reported for the attached flow on a trailing flap and in its Conference, 22nd, Honolulu, HI, June 8-10, 1987. 12 p. refs downstream asymmetric wake. The results indicate that the flow (AIAA PAPER 87-1546) over the flap is subjected to an adverse pressure gradient. Near Results of a numerical study using the direct simulation Monte the trailing edge, an inflection point develops in the streamwise Carlo (DSMC) method are presented for the hypersonic flow about velocity profile and the flow approaches intermittent separation. an elliptically blunted cone. The flow conditions are those for a The wake is asymmetric with a destabilizing curvature on the proposed Aeroassist Flight Experiment (AFE) vehicle. The altitude suction side and a stabilizing curvature on the pressure side. range considered is that from 130 to 90 km which encompasses Streamwise variations in the near wake are primarily confined to most of the transitional flow regime for the AFE vehicle, that is, the inner layer, and further downstream the mean velocity and the region bounded by free molecular and continuum flow. turbulence quantities attain self-similar profiles. Nonequilibrium Freestream velocities of 9.9 to 7.5 km/sec are considered. The effects are present in the near wake and imply that mixing length numerical simulations show that noncontinuum effects are evident models are not appropriate. Both the pressure gradient term and for all cases considered. The onset of chemical dissociation occurs the cross-stream gradient of the turbulent stresses are found to at a simulated altitude of about 130 km. Results presented highlight be important. Streamwise gradients of the turbulent stresses are, the thermal and chemical nonequilibrium nature of the flowfield however, small. Author and the impact of these effects on the surface heating and body drag. A calculation which included the additional effects of ionization A87-43377# and thermal radiation demonstrates that the inclusion of such efects TIME-CONSISTENT PRESSURE RELAXATION PROCEDURE would not significantly alter the surface quantities calculated in FOR COMPRESSIBLE REDUCED NAVIER-STOKES EQUA- the present study. The radiative heating is negligible when TIONS compared with the convective heating, and the same would be S. V. RAMAKRISHNAN and S. G. RUBIN (Cincinnati, University, true for the other conditions considered. Author OH) AIAA Journal (ISSN 0001-1452), vol. 25, July 1987, p. 905-913. refs A87-43084"# National Aeronautics and Space Administration. (Contract N00014-79-C-0849; F49620-85-C-0027) Langley Research Center, Hampton, Va. A time-consistent global pressure relaxation procedure for the A COMPUTATIONAL STUDY OF THE FLOWFIELD unsteady, compressible, reduced Navier-Stokes equations is SURROUNDING THE AEROASSIST FLIGHT EXPERIMENT presented. The shock-capturing capability of the procedure is VEHICLE investigated with different forms of pressure gradient splitting. An PETER A. GNOFFO and FRANCIS A. GREENE (NASA, Langley efficient conservative method for capturing shocks is detailed. The Research Center, Hampton, VA) AIAA, Thermophysics transient behavior of laminar, high Reynolds number, low subsonic Conference, 22nd, Honolulu, HI, June 8-10, 1987. 13 p. refs flow past a sine-wave airfoil geometry is analyzed using the new (AIAA PAPER 87-1575) reduced Navier-Stokes-based algorithm. These solutions are A symmetric total variation diminishing (STVD) algorithm has compared with steady and unsteady results previously obtained been applied to the solution of the three-dimensional hypersonic with a modified interacting boundary-layer procedure. The strong flowfield surrounding the Aeroassist Flight Experiment (AFE) influence of grid refinement and the type of differencing of the vehicle. Both perfect-gas and chemical nonequilibrium models have streamwise convection term on the existence or stability of

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separated laminar solutions is reaffirmed. More stable turbulent the wake geometry given by the code shows good agreement flow results are also presented. Finally, an unsteady solution for with experiments. Author the flow past a finite flat plate at incidence is described in order to demonstrate the time accuracy of the algorithm. Author

A87-43415# A87-43392"# Arizona Univ., Tucson. COMPUTATION OF UNSTEADY TRANSONIC AERODYNAMICS INVESTIGATION OF BLADE-VORTICES IN THE WITH TRUNCATION ERROR INJECTION ROTOR-DOWNWASH K.-Y. FUNG and J.-K. FU (Arizona, University, Tucson) AIAA B. JUNKER (DFVLR, Institut fuer Flugmechanik, Brunswick, West Journal (ISSN 0001-1452), vol. 25, July 1987, p. 1018-1020. Germany) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. Previously cited in issue 19, p. 2740, Accession no. A85-40744. refs 25 p. The flow field of a rotor consists of induced downwash, the (Contract AF-AFOSR-83-0071; NGT-03-002-800) fuselage wake, and strong rotor-blade vortices. This paper deals with the investigation of those vortices. The trace and the diameter A87-43412# of the vortex were identified by a simple measuring method (Junker, A UNIFIED APPROACH FOR POTENTIAL AND VISCOUS 1985). Results of different wind-tunnel investigations, such as level FREE-WAKE ANALYSIS OF HELICOPTER ROTORS flight, descend, climb, and transition are presented and discussed. L. MORINO and B. K. BHARADVAJ (Boston University, MA) The tests were conducted in the DNW wind tunnel using the DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, closed 8 x 6-m test section. The test results provide a better West Germany, Sept. 22-25, 1986, Paper. 12 p. refs understanding of the rotor downwash structure. Author (Contract DAAG29-83-K-0050) A unified formulation for the potential and viscous free-wake analysis of helicopter rotors in incompressible flows is presented. The wake is treated as a vortex layer (with zero thickness for A87-43416# potential flows and finite thickness for viscous flows). The numerical THE USE OF DISCRETE VORTICES TO PREDICT LIFT OF A algorithm for the discretization is outlined. Numerical results are CIRCULATION CONTROL ROTOR SECTION WITH A TRAILING in good agreement with the numerical results of Rao and Schatzle EDGE BLOWING SLOT and the experimental ones of Landgrebe and of Shivananda. Author C. W. HUSTAD (Kongsberg Vapenfabrikk A/S, Norway) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 19 p. refs A87-43413# This paper describes a method which applies discrete vortices A PARAMETRIC INVESTIGATION OF A FREE WAKE ANALYSIS to predict the flow around the trailing edge ('rE) of a OF HOVERING ROTORS circulation-control rotor (CCR) section. The vortices are shed from A. ROSEN (Technion - Israel Institute of Technology, Haifa) and the blowing lip with a frequency and strength determined by the A. GRABER DGLR, European Rotorcraft Forum, 12th, blowing parameters and lip geometry. As the vortices develop Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. downstream, viscosity and entrainment cause vortex growth, with 23 p. refs eventual overlapping resulting in a pairing process. Once initiated A recently developed free-wake model of a hovering rotor this process breaks down the discrete vortex structure, resulting (Rosen and Graber, 1985) is used to study the influence of different in a large-scale eddy flow representative of the flow in the wake parameters on the accuracy and efficiency of the calculations. of the CCR section. The proposed model shows distinct similarities The parameters investigated include: the spanwise and chordwise with the observed flow field, and it is suggested that discrete distribution of cells over the blade, the length of the near wake, vortex modeling may offer an alternative, or at the very least the length of the straight vortex elements of which the near wake suggest improvements, to the finite-difference methods which have is assembled, the vortex core size, relaxation factors, and the been used to predict the TE Coanda flow. Author influence of including a correction for the self-induction in the near wake due to the curvature of the real trailing vortex elements. This parametric investigation is aimed at giving future users of free-wake analysis guidelines on how to arrive at a numerical A87-43417"# National Aeronautics and Space Administration. model which is accurate and still efficient. A free-wake analysis of Ames Research Center, Moffett Field, Calif. a rotor having swept blades is included in order to learn about FULL POTENTIAL MODELING OF BLADE-VORTEX the influence of the sweep-back ont he aerodynamic behavior. INTERACTIONS Author H. E. JONES and F. X. CARADONNA (NASA, Ames Research Center; U.S. Army, Aeroflightdynamics Directorate, Moffett Field, A87-43414# CA) DGLR, European Rotorcraft Forum, 12th, A PRESCRIBED RADIAL DISTRIBUTION CIRCULATION OF A Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986. Paper. HOVERING ROTOR BLADE 28 p. Previously announced in STAR as N87-18532. refs C. MARESCA, D. FAVIER, and M. NSI MBA (Aix-Marseille II, A comparison is made of four different models for predicting Universite, Marseille, France) DGLR, European Rotorcraft Forum, the unsteady loading induced by a vortex passing close to an 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, airfoil. (1) The first model approximates the vortex effect as a Paper. 24 p. refs change in the airfoil angle of attack. (2) The second model is (Contract DRET-84-009) related to the first but, instead of imposing only a constant velocity A prescribed radial-distribution circulation has been deduced on the airfoil, the distributed effect of the vortex is computed and from new experimental results obtained on hovering rotor blades. used. This is analogous to a lifting surface method. (3) The third A synthetic empirical law of circulation is used as input data of an model is to specify a branch cut discontinuity in the potential iterative numerical code predicting the wake geometry, the rotor field. The vortex is modeled as a jump in potential across the flow, and airloads. Compared to a previous code using a prescribed branch cut, the edge of which represents the center of the vortex. distribution of induced velocities (Pouradier and Horowitz, 1980), (4) The fourth method models the vortex expressing the potential improvements concerning running time and precision on wake as the sum of as known potential due to the vortex and an unknown characteristics have been obtained. Moreover, it has been shown perturbation due to the airfoil. The purpose of the current study is that, in the case of a highly nonlinear twisted blade, the code to investigate the four vortex models described above and to becomes efficient when introducing the experimental values of determine their relative merits and suitability for use in large the bound circulation along the blade as input data. Particularly, three-dimensional codes. Author

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A87-43418# strategies are pursued: a coupling of the inviscid panel method COMPUTATION OF THE FLOW FIELDS OF PROPELLERS AND with the boundary layer code, and a strong coupling of the inviscid HOVERING ROTORS USING EULER EQUATIONS panel method with the boundary layer code. Attention is given to N. KROLL (DFVLR, Institut fuer Entwurfs-Aerodynamik, Brunswick, the main features of the unsteady time-marching panel method West Germany) DGLR, European Rotorcraft Forum, 12th, and boundary layer codes, as well as to numerical stability and Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. the phenomenon of unsteady separation. O.C. 16 p. refs A numerical procedure for the calculation of the flow fields of A87-43422# propellers and hovering rotors is described. The method solves THE INFLUENCE OF WINGLETS ON ROTOR AERODYNAMICS the three-dimensional Euler equations, which are formulated in R. MUELLER (Aachen, Rheinisch-Westfaelische Technische terms of the flow variables in a blade-attached Cartesian reference Hochschule, West Germany) DGLR, European Rotorcraft Forum, frame. The solution algorithm is based on the finite-volume method 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, originated by Jameson et al. (1981), using explicit Runge-Kutta Paper. 16 p. refs time-stepping schemes. Calculations are presented for subsonic Impulsive noise emission and dynamic blade loads of helicopters and transonic flows around a two-bladed propeller and a two-bladed are to some extent caused by Blade Vortex Interactions (BVI). In model in hover. The theoretical results show good this paper, a winglet arrangement is described which reduces the agreement with the experimental data. Author influence of BVl by increasing the distance between tip vortices and rotor blades at their first encounter. For hover flight, a free-wake A87-43419# analysis method has been developed to calculate the influence of APPLICATION OF A 3D EULER CODE TO TRANSONIC BLADE the winglet. It is shown that a winglet can produce a smaller TIP FLOW gradient of the spanwise load distribution, leading to a higher H. STAHL (Messerschmitt-Boelkow-Blohm GmbH, Munich, West spreading of the vorticity. Although it is expected that the winglet Germany) DGLR, European Rotorcraft Forum, 12th, in forward flight could have an adverse influence due to large Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. azimuthal variations of its incidence, the measured pressure 19 p. refs variations are smaller. Calculations, based on the theory of The unsteady three-dimensional rotational transonic flow on Naumann and Yeh (1972), show a favorable influence of a winglet the rotor blade of a helicopter in fast forward flight is investigated on the unsteady forces under certain flight conditions. Author analytically by means of numerical computations with the EUFLEX code (Eberle, 1984). The computational grid, boundary conditions, A87-43424# and numerical procedure are described, and the results obtained THE USE OF COMPUTER MODELS IN HELICOPTER DRAG for Psi = 90 deg with different grid refinements and dimensions PREDICTION and with grid lines attracted to the surface, are presented DAVID R. CLARK and BRIAN MASKEW (Analytical Methods, Inc., graphically. It is shown that best results are obtained with maximum Redmond, WA) DGLR, European Rotorcraft Forum, 12th, resolution of the body surface, with attracted grid lines, and with Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. grid boundaries far enough from the body to assure far-field 25 p. refs conditions. The overall pressure distribution on the blade is lowered The paper presents a brief review of the developments in by decaying velocity outboard of the blade tip. T.K. drag prediction capability in the last decade. In particular, it details the inability of the first generation panel methods to A87-43420# more than adequately calculate the flow about helicopter fuselages THE EFFECT OF PITCH RATE ON THE DYNAMIC OR and their failure, despite early promise to be able to predict absolute A MODIFIED NACA 23012 AEROFOIL AND COMPARISON WITH levels of drag. The development of a second generation of panel THE UNMODIFIED CASE methods led the way to an improved flow modeling capability ANDREW J. NIVEN and A. MCD. GALBRAITH (Glasgow, University, and, in particular, to the ability to model the behavior of viscous Scotland) DGLR, European Rotorcraft Forum, 12th, flow and to predict and track the development of regions of Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. separate flow. The paper shows, however, that even these models 15 p. Sponsorship: Ministry of Defence of England. refs fall short in their ability to accurately predict drag. They do, however, (Contract MOD-2048/026)XR/STR) provide the jumping off point for the development of a new An investigation into the effects of trailing-edge separation on generation of panel methods which take full account of the dynamic stall was carried out by modifying and re-testing a NACA unsteady motion of the large-scale separated flow. These methods 23012 aerofoil. An enhancement in rear separation was obtained are discussed and early results on a series of bluff bodies and by modifying the trailing-edge geometry. To maintain similar flow typical helicopter tail boom cross sections are presented. In most conditions at the leading-edge, the original aerofoil geometry within cases the correlation between predicted and measured drag is this area was left unaltered. The paper presents data obtained excellent. Author from oscillatory and ramp tests and shows the modified aerofoil to have an earlier dynamic stall initiation. It is suggested that this A87-43438# initiation was triggered, at the lower angle of incidence, by the INVESTIGATION OF HELICOPTER TWIN-ROTOR CHARAC- enhanced rear separation. Author TERISTICS H. AZZAM and P. TAYLOR (Southampton, University, England) A87-43421"# Deutsche Forschungs- und Versuchsanstalt fuer DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, Luft- und Raumfahrt, Goettingen (West Germany). West Germany, Sept. 22-25, 1986, Paper. 11 p. Research UNSTEADY SEPARATION CHARACTERISTICS OF AIRFOILS supported by the Ministry of Defence (Procurement Executive). OPERATING UNDER DYNAMIC STALL CONDITIONS refs WOLFGANG GEISSLER (DFVLR, Institut fuer Aeroelastik, The general application of the reported wake models to the Goettingen, West Germany), LAWRENCE W. CARR (NASA, Ames interference problems between two rotors is restricted. The free Research Center; U.S. Army, Aeromechanics Laboratory, Moffett convection of a limited number of revolutions of the tip vortex Field, CA), and TUNCER CEBECI (California State University, Long trajectory is only considered in the free wake models to reduce Beach) DGLR, European Rotorcraft Forum, 12th, the computational costs. Meanwhile, the far wake is either ignored Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. or prescribed by using a vortex ring or a helical wake of constant 16 p. refs radius. The objective of this paper is to demonstrate the important Unsteady viscous/inviscid interaction phenomena are effects of the far wake structure on the twin-rotor behavior. This investigated for airfoils operating under dynamic stall conditions, leads to the proposed prescribed wake model. This model is found using coupling procedures between a time-dependent inviscid panel to describe the performance of coaxial, nonoverlapped tandem method and two-dimensional unsteady boundary layer codes. Two and twin-tail rotors adequately. The flapping angles of the

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nonoverlapped tandem were found to be reasonably predicted. A87-43704# Author EFFECT OF SWIRL ON THE PERFORMANCE OF A RADIAL VANELESS DIFFUSER WITH COMPRESSIBLE FLOW AT MACH A87-43603 NUMBERS OF 0.7 AND 0.8 EFFECT OF FABRICATION-RELATED DEVIATIONS OF THE S. M. YAHYA, D. P. AGRAWAL (Indian Institute of Technology, GEOMETRICAL PARAMETERS OF BLADE PROFILES ON FLOW New Delhi, India), and D. N. REDDY (Osmania University, IN A COMPRESSOR [VLIIANIE TEKHNOLOGICHESKIKH Hyderabad, India) ASME, Winter Annual Meeting, Anaheim, CA, OTKLONENII GEOMETRICHESKIKH PARAMETROV PROFILEI Dec. 7-12, 1986. 6 p. refs LOPATOK NA TECHENIE V KOMPRESSORE] (ASME PAPER 86-WA/FE-6) L. G. BOIKO, V. N. ERSHOV, and V. N. IANEVICH The present investigation deals with the flow development and Samoletostroenie - Tekhnika Vozdushnogo Flota (ISSN 0581-4634), performance characteristics of a parallel wall radial vaneless no. 53, 1986, p. 10-14. In Russian. diffuser for varying degree of swirl (24 deg to 35 deg) at entry A two-dimensional mathematical model for the investigation of Mach numbers of 0.7 and 0.8. Test results are presented for the flow in a multistage is examined. It is constant passage width (b/D1 of 0.138) and at various radius demonstrated that this model can be used to study the effect of ratios (1.0 to 2.9) of the diffuser. The results show that the pressure fabrication-related deviations of the geometrical characteristics of recovery decreases with the increase in swirl angle, and that for the blade profiles on flow in the compressor. An assessment is the given swirl, performance of the diffuser deteriorates with the made of the effects of the chord, the maximum thickness of the increase in entry Mach number. It is further observed that the profile, and the setting angle on the flow characteristics in an swirl plays an important role in the velocity distortion at the inlet individual stage and in a six-stage compressor. B.J. of diffuser. Author

A87-43604 INVESTIGATION OF FLOW STRUCTURE IN A COMPRESSOR WITH TWO TYPES OF GUIDES [ISSLEDOVANIE STRUKTURY POTOKA V KOMPRESSORE S NAPRAVLIAIUSHCHIMI APPARATAMI DVUKH SKHEM ISPOLNENIIA] A. F. BREKHOV, L. N. BUSKIK, and A. V. SKLIAR A87-44019 Samoletostroenie - Tekhnika Vozdushnogo Flota (ISSN 0581-4634), THE EFFECT OF TRIP WIRE ROUGHNESS ON THE no. 53, 1986, p. 14-17. In Russian. PERFORMANCE OF THE WORTMANN FX 63-137 AIRFOIL AT The effects of two types of guides on the aerodynamic LOW REYNOLDS NUMBERS characteristics of a two-stage axial compressor are evaluated: (1) A. F. HUBER, tl and T. J. MUELLER (Notre Dame, University, IN) •a shrouded guide and (2) a cantilever guide with a radial clearance Experiments in Fluids (ISSN 0723-4864), vol. 5, no. 4, 1987, p. at the hub equal to 1.5 percent of the blade height. In the case 263-272. Research supported by the University of Notre Dame. of the second design, flow through the clearance localizes the refs vortex flow in the hub region, leading to an increase in the total (Contract N00014-83-K-0239) pressure behind the guide. Since the compressor in the experiment An experimental investigation was conducted on the had relatively short blades, the localization of the near-hub vortex performance and boundary layer characteristics of the Wortmann flows had a favorable effect on the flow structure over the entire FX 63-137 airfoil with and without trip wire roughness. Data were height of the guide blades in both stages of the compressor. B.J. obtained through use of a three-component strain gage force balance and static pressure measurement equipment at a test Reynolds number (based on chord c) of 100,000. Prediction of A87-43608 transition location by the criterion due to Tani (1964) and Gibbings CALCULATION OF THE BOUNDARY LAYER AT THE INLET (1959) was found to have limited application. Most trip wire SECTION OF A COMPRESSOR CASCADE [K RASCHETU locations resulted in degraded performance, but for some locations, POGRANICHNOGO SLOIA NA VKHODNOM UCHASTKE minimum drag was reduced, maximum lift to drag ratio was KOMPRESSORNOI RESHETKI] increased, and hysteresis was averted. Author N. M. ZUBOV Samoletostroenie - Tekhnika Vozdushnogo Flota (ISSN 0581-4634), no. 53, 1986, p. 26-28. In Russian. The application of a simple integral method to the calculation of a turbulent boundary layer at the inlet section of a transonic compressor cascade is considered. Calculated parameters of the boundary layer are compared with experimental data for transonic flow past a half-profile in a channel. It is concluded that the proposed method can be effectively used to calculate the A87-44902"# Boeing Co., Seattle, Wash. conditional thicknesses of the boundary layer at the inlet section NAVIER-STOKES SIMULATION OF A HYPERSONIC GENERIC of a compressor cascade. B.J. WING/FUSELAGE JOHN C. WAI, SAMUEL C. DAO (Boeing Military Airplane Co., A87-43618 Seattle, WA), and DENNY S. CHAUSSEE (NASA, Ames Research INVESTIGATION OF ROTATING ADDITIONAL BLADES ON THE Center, Moffett Field, CA) AIAA, Fluid Dynamics, Plasma PERIPHERY OF AN AXlAL-COMPRESSSOR ROTOR [OB Dynamics, and Lasers Conference, 19th, Honolulu, HI, June 8-10, ISSLEDOVANII POVOROTNYKH DOPOLNITEL'NYKH LOPATOK 1987. 13p. refs NA PERIFERII RABOCHEGO KOLESA OSEVOGO (AIAA PAPER 87-1192) KOMPRESSORA] An unsteady thin-layer Navier-Stokes code is used to calculate V. IU. NEZYM and V. G. PROKOPOVICH Samoletostroenie - a generic wing/fuselage configuration at a Mach number of 25 Tekhnika Vozdushnogo Flota (ISSN 0581-4634), no. 53, 1986, p. and freestream conditions corresponding to an altitude of 220,000 71-74. In Russian. feet. Calculations were performed with the assumptions of a perfect Experimental results on rotating additional blades in the inlet gas and with chemical equilibrium, and the boundary layer was region of an axial-compressor rotor confirm that the peripheral assumed to be turbulent and to have a surface temperature inlet region plays an important role in the occurrence of rotating prescribed at 1255 K. Results for the two different gas assumptions stall. The additional blades can be used to control the flow in the were compared in terms of distributions of pressure, density, peripheral zone. While practically preserving the level of efficiency, temperature, Mach number, ratio of specific heat, and heat transfer. it is possible to move the rotating-stall boundary toward lower air Numerical problems arising in the calculations were identified. flow rates. B.J. R.R.

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A87-44904"# Sterling Software, Palo Alto, Calif. A87-44913"# National Aeronautics and Space Administration. ADVANCES IN THE COMPUTATION OF TRANSONIC Ames Research Center, Moffett Field, Calif. SEPARATED FLOWS OVER FINITE WINGS NUMERICAL SIMULATION OF VORTICAL FLOWS OVER A UNVER KAYNAK (Sterling Software, Palo Alto, CA) and JOLEN -DELTA WING FLORES (NASA, Ames Research Center, Moffett Field, CA) AIAA, KOZO FUJII and LEWIS B. SCHIFF (NASA, Ames Research Center, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, 19th, Moffett Field, CA) AIAA, Fluid Dynamics, Plasma Dynamics, and Honolulu, HI, June 8-10, 1987. 20 p. refs Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 15 p. (Contract NCA2-OR-745-309) refs (AIAA PAPER 87-1195) (AIAA PAPER 87-1229) The transonic flow around a low-aspect-ratio infinite wing in a The vortical flow fields over a double-delta wing with sweep wind tunnel is investigated by means of numerical simulations, angles 80 and 60 deg are investigated by means of numerical with a focus on shock-induced separated flows. A coarse global simulations based on the LU-ADI code of Fujii and Obayashi (1986) grid with far-field boundaries matching those of the test section is for the three-dimensional thin-layer Navier-Stokes equations. The subdivided into zones: the flow in the clustered zones near the results obtained using an 850,000-point grid at angle of attack wing is analyzed by solving the Reynolds-averaged Navier-Stokes alpha = 6-40 deg are presented graphically, compared with equations, while that farther from the wing is modeled with the experimental data, and characterized in detail. Qualitatively Euler equations. The results are presented graphically, and it is accurate simulations are obtained for transition phenomena such shown that a mushroomlike separated flow with two counterrotating as strake/wing-vortex interaction at alpha = 12 deg, bubble-type vortices can be simulated when the correct shock strength is vortex breakdown near the trailing edge at alpha = 30 deg, and imposed (by careful selection of the artificial dissipation, the spiral-type breakdown at alpha = 35 deg. It is suggested that boundary conditions, the grid refinement, the algebraic turbulence quantitative simulations can be achieved at higher grid resolution. model, and the geometry representation). T.K. T.K.

A87-44905"# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. A87-44914"# National Aeronautics and Space Administration. TRANSONIC ANALYSIS OF THE F-16A WITH UNDER-WING Ames Research Center, Moffett Field, Calif. FUEL TANKS AN APPLICATION OF THE TRANAIR AN EXPERIMENTAL INVESTIGATION OF A SUPERCRITICAL FULL-POTENTIAL CODE AIRFOIL AT TRANSONIC SPEEDS MICHAEL D. MADSON (NASA, Ames Research Center, Moffett GEORGE C. MATEER, H. LEE SEEGMILLER, THOMAS J. Field, CA) AIAAI Fluid Dynamics, Plasma Dynamics, and Lasers COAKLEY, LAWRENCE A. HAND (NASA, Ames Research Center, Conference, 19th, Honolulu, HI, June 9-10, 1987. 14 p. refs Moffett Field, CA), and JOACHIM SZODRUCH (Contract NAS2-12513) (Messerschmitt-Boelkow-Blohm GmbH, Bremen, West Germany) (AIAA PAPER 87-1198) AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, Initial results obtained using the TranAir transonic full-potential 19th, Honolulu, HI, June 8-10, 1987. 11 p. refs code are presented for a fully configured F-16A geometry, including (AIAA PAPER 87-1241) two 370-gal under-wing fuel tanks, at freestream Mach numbers Benchmark experimental data obtained in the two-dimensional, of 0.6 and 0.9 and angle of attack of 4 deg. The geometry is transonic flow field surrounding a supercritical airfoil are presented. modeled using surface panels, and the flow field is defined by a Airfoil surface and tunnel wall pressure and LDV measurements rectangular array of flow-field grid points. The paneled geometry are used to describe the flow on the model, above the wing and is embedded within this rectangular flow field. By avoiding the in the wake. Comparisons are made with calculations using the use of surface-conforming flow-field grids, the modeling generality Reynolds-averaged Navier-Stokes equations. The results illustrate afforded by surface panels can be utilized to analyze very complex the performance of two turbulence models in both separated and configurations in the transonic flow regime. Author attached flows. The largest differences between theory and experiment occurred in separated flows with the Johnson and King turbulence model providing the best estimates. Author

A87-44906"# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. SIMULATION OF TRANSONIC VISCOUS FLOW OVER A FIGHTER-LIKE CONFIGURATION INCLUDING INLET A87-44915# JOLEN FLORES, NEAL M. CHADERJIAN, and REESE L. A NEW SIMULATION OF AIRFOIL DYNAMIC STALL DUE TO SORENSON (NASA, Ames Research Center, Moffett Field, CA) VELOCITY AND INCIDENCE FLUCTUATIONS AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, D. FAVIER, A. AGNES, C. BARBI, and C. MARESCA (Aix-Marseille 19th, Honolulu, HI, June 8-10, 1987. 15 p. refs II, Universite, France) AIAA, Fluid Dynamics, Plasma Dynamics, (AIAA PAPER 87-1199) and Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 20 The simulation of transonic viscous flow over a modified F-16A p. Research supported by the Ministere de la Defense Armee de including inlet is presented. A zonal approach is utilized which I'Air. refs allows appropriate clustering suitable for viscous calculations on (AIAA PAPER 87-1242) all solid surfaces. Computational efficiency is enhanced by solving The effects of simultaneous velocity and incidence fluctuations the thin-layer Navier-St0kes equations in viscous zones adjacent on the 2D aerodynamic behavior of a NACA0012 airfoil are to the aircraft and the Euler equations on those coarse zones investigated in this paper. A new mechanical system allows to away from the aircraft. The flow conditions for this transonic case drive the airfoil in pitching and in for and aft motions, as well as are freestream Mach number of 0.9, angle of attack of 4.12 deg, in a simultaneous combination of these two basic unsteady motions. and a Reynolds number (based on root chord) of 4.5 million. A In response of the simultaneous velocity and incidence variations, total of 19 zones are utilized yielding a total of 350,000 grid points. the time-dependent lift and drag fluctuations are measured for This case required about 3000 iterations to reduce the residual increasing values of the reduced frequency and amplitude by three orders, which takes about 10 hr of CPU time on the parameters including dynamic stall conditions. Complementary Cray X-MP/48 computer. Pressure distributions on the wing and informations on the dynamic stall occurring in combined motion on cross sections through the inlet region compare favorably with are provided by skin friction and pressure measurements along the experimental data for this transonic case. Author the airfoil surface. Author

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A87-44920"# National Aeronautics and Space Administration. A87-44931 # Ames Research Center, Moffett Field, Calif. FORCED UNSTEADY VORTEX FLOWS DRIVEN BY PITCHING EXPERIMENTAL STUDY OF THE VORTEX FLOW BEHAVIOR AIRFOILS ON A GENERIC FIGHTER WING AT SUBSONIC AND JOHN M. WALKER (USAF, Frank J. Seller Research Laboratory, TRANSONIC SPEEDS Colorado Springs, CO) and DAVID C. CHOU (New Mexico, GARY E. ERICKSON (NASA, Ames Research Center, Moffett Field, University, Albuquerque) AIAA, Fluid Dynamics, Plasma Dynamics, CA) and LAWRENCE W. ROGERS (USAF, Wright Aeronautical and Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 14 Laboratories, Wright-Patterson AFB, OH) AIAA, Fluid Dynamics, p. refs Plasma Dynamics, and Lasers Conference, 19th, Honolulu, HI, (AIAA PAPER 87-1331) June 8-10, 1987. 23 p. refs Experiments were conducted with a NACA 0015 airfoil pitching (AIAA PAPER 87-1262) rapidly to high angles of attack to study the initiation, development, A subsonic and transonic investigation of the vortex flow and evolution of dynamic stall vortex flows. The airfoil was pitched behavior of a generic fighter configuration with 55-deg cropped about its quarter-chord axis from zero to sixty degrees geometric delta wing has been conducted in order to improve current angle of attack at rates .from 115 deg/sec to 1380 deg/sec and understanding of vortical motions on a wing with deflected leading at flow speeds from 10 to 80 ft/sec (chord Reynolds numbers edge flap at moderate and high angles-of-attack. The leading edge from 25,000 to 200,000). Smoke-wire flow visualization, dynamic vortex strength was reduced, and the vortex was flatter and closer surface pressure measurement, and near-surface hot-film velocity to the wing surface, as the Mach number increased. Transonically, magnitude measurement experiments were performed and at high angles-of-attack, the test data suggested the development correlated to determine the nature of the elicited time dependent of a cross-flow shock wave above the vortex sheet which coexisted vortex flows. Lift, pressure drag, and moment coefficients were with a rear shock wave. Subsonically, a deflected leading edge calculated to be far in excess of the maximum steady flow values flap was able to sustain a concentrated vortex on the forward-facing and were shown to be functions of the non-dimensional pitch surface. O.C. rate. Author

A87-44921"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. A87-44932# A UNIQUE MEASUREMENT TECHNIQUE TO STUDY COMPARISONS OF UNSTEADY FLOW FIELDS ABOUT LAMINAR-SEPARATION BUBBLE CHARACTERISTICS ON AN STRAIGHT AND SWEPT WINGS USING FLOW VISUALIZATION AIRFOIL AND HOTWIRE ANEMOMETRY J. P. STACK (NASA, Langley Research Center, Hampton, VA), S. J. ASHWORTH, S. HUYER, and M. LUTTGES (Colorado, University, M. MANGALAM, and S. A. BERRY (Analytical Services and Boulder) AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Materials, Inc., Hampton, VA) AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, 19th, Honolulu, HI, June 8-10, Conference, 19th, Honolulu, HI, June 8-10, 1987. 13 p. refs (Contract F49620-83-K-0009) 1987.9p. refs (AIAA PAPER 87-1334) (Contract NAS1-18235) (AIAA PAPER 87-1271) The dynamic spatial and temporal differences in the unsteady A 'nonintrusive', multielement heat-transfer sensor was flow fields produced about three sinusoidally oscillating wings designed to study laminar-separation bubble characteristics on a differing in sweep angle are verified using flow visualization and NASA LRN (1)-1010 low-Reynolds number airfoil. The sensor hot-wire anemometry techniques. The measured local velocity fluctuations showed the position, size, and relative velocities of consists of 30 individual nickel films, vacuum-deposited on a thin substrate (0.05 mm) that was bonded to the airfoil model with the the flow-field structures. Chordwise anemometric investigations performed over the complete pitching cycle verified the formation, sensor array placed streamwise on the airfoil upper surface. Experiments were conducted on a 15-cm chord model in the development, and convection of the visualized leading-edge vortex structure. From a spanwise comparison of flow-visualization and 50,000-300,000 chord Reynolds number range. Time history as well as spectral analysis of signals from surface film gauges were anemometry data, it is found that wing sweep angles produced major changes in vortex initiation, development, and convection simultaneously obtained to determine the location of laminar velocity. R.R. separation and the subsequent behavior of the separated shear layer. In addition to the successful determination of laminar separation, a new phenomenon involving a large phase shift in dynamic shear stresses across the separation and reattachment points was observed. Author A87-44933"# Kansas Univ., Lawrence. INCOMPRESSIBLE NAVIER-STOKES COMPUTATIONS OF VORTICAL FLOWS OVER DOUBLE-DELTA WINGS A87-44929# CHUNG-HAO HSU (Kansas, University, Lawrence), VISUALIZATION OF THREE-DIMENSIONAL STRUCTURES PETER-MICHAEL HARTWlCH (Vigyan Research Associates, Inc., ABOUT A PITCHING FORWARD SWEPT WING Hampton, VA), and C. H. LIU (NASA, Langley Research Center, J. B. WISSLER, F. T. GILLIAM (U.S. Air Force Academy, Colorado Hampton, VA) AIAA, Fluid Dynamics, Plasma Dynamics, and Springs, CO), M. C. ROBINSON (Colorado, University, Boulder), Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 10 p. and J. M. WALKER (USAF, Frank J. Seller Research Laboratory, refs Colorado Springs, CO) AIAA, Fluid Dynamics, Plasma Dynamics, (Contract NAG1-455; NAS1-17919) and Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 10 (AIAA PAPER 87-1341) p. refs An implicit flux-difference splitting scheme is used to compute (AIAA PAPER 87-1322) incompressible laminar vortical flows about a thin round-edged Three-dimensional forced unsteady flow separation about a 30 double-delta wing with 80 deg and 60 deg leeding-edged sweep deg forward swept wing was visualized for a constant pitch rate for the strake and the main wing respectively. The numerical motion from 0 to 60 deg. The development of both wing tip and scheme combines approximate factorization in crossflow planes inboard leading edge vortices were observed with characteristics with a symmetric planar Gauss-Seidel relaxation in the remaining similar to those found in straight wing tests. The off-axis pitch spatial direction. It is second-order accurate spatially by applying geometry appeared to delay the initiation of the wing tip vortex to TVD-like upwind discretization to the inviscid fluxes and central large angles at attack, indicative of a delayed lift response. The differencing to the viscous shear fluxes. The interaction between results are contrasted with previous straight wing findings using the two primary vortices emanating from the apex and kink similar pitch motions and swept wing results obtained using leading-edges is successfully simulated. The computed trajectories sinusoidal motion histories. Author of vortical cores compare well with experimental data. Author

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A87-44934"# California Univ., Davis. A87-44945"# High Technology Corp., Hampton, Va. VORTEX BREAKDOWN SIMULATION STATIONARY DISTURBANCES IN THREE-DIMENSIONAL M. HAFEZ, J. AHMAD (California, University, Davis), G. KURUVILA, BOUNDARY LAYERS OVER CONCAVE SURFACES and M. D. SALAS (NASA, Langley Research Center, Hampton, F. S. COLLIER, JR. and M. R. MALIK (High Technology Corp., VA) AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Hampton, VA) AIAA, Fluid Dynamics, Plasma Dynamics, and Conference, 19th, Honolulu, HI, June 8-10, 1987. 20 p. refs Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 15 p. (AIAA PAPER 87-1343) refs In this paper, steady, axisymmetric inviscid, and viscous (Contract NAS1-18240) (laminar) swirling flows representing vortex breakdown phenomena (AIAA PAPER 87-1412) are simulated using a stream function-vorticity-circulation A two-dimensional boundary layer on a concave surface is formulation and two numerical methods. The first is based on an known to be susceptible to centrifugal instability which manifests inverse iteration, where a norm of the solution is prescribed and itself in the form of stationary streamwise counter-rotating vortices the swirling parameter is calculated as a part of the output. The commonly known as Goertler vortices. In this paper, the problem second is based on direct Newton iterations, where the linearized of the stability of a three-dimensional boundary layer on a concave equations, for all the unknowns, are solved simultaneously by an surface is considered. Linear stability equations, including efficient banded Gaussian elimination procedure. Several numerical streamline and surface curvature effects, are solved for an infinitely solutions for inviscid and viscous flows are demonstrated, followed swept wing. The results indicate that the Goetler vortex structure by a discussion of the results. Some improvements on previous begins to transform into co-rotating vortices when the crossflow work have been achieved: first order upwind differences are Reynolds number is increased. This transition is almost complete replaced by second order schemes, line relaxation procedure (with when the crossflow Reynolds number is in excess of 45. It is linear convergence rate) is replaced by Newton's iterations (which shown that the centrifugal effects destabilize the crossflow vortices. converge quadratically), and Reynolds numbers are extended from Some comparisons with available experimental results are made. 200 up to 1000. Author Author

A87-44938"# Toledo Univ., Ohio. AN LDA INVESTIGATION OF THREE-DIMENSIONAL NORMAL SHOCK-BOUNDARY LAYER INTERACTIONS IN A CORNER A87-44946"# High Technology Corp., Hampton, Va. R. M. CHRISS, T. G. KEITH, JR. (Toledo, University, OH), W. R. PREDICTION AND CONTROL OF TRANSITION IN HYPERSONIC HINGST, A. J. STRAZISAR, and A. R. PORRO (NASA, Lewis BOUNDARY LAYERS Research Center, Cleveland, OH) AIAA, Fluid Dynamics, Plasma MUJEEB R. MALIK (High Technology Corp., Hampton, VA) AIAA, Dynamics, and Lasers Conference, 19th, Honolulu, HI, June 8-10, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, 19th, 1987. 12p. refs Honolulu, HI, June 8-10, 1987. 13 p. refs (Contract NAG3-309) (Contract NAS1-18240) (AIAA PAPER 87-1369) (AIAA PAPER 87-1414) Nonintrusive, three-dimensional, measurements have been In this paper, the role of compressible linear stability theory in made of a normal shock wave-turbulent boundary layer interaction. prediction of boundary layer transition at supersonic and hypersonic The measurements were made in the corner of the test section speeds is investigated. Computations for sharp cones, using the of a continuous supersonic wind tunnel in which a normal shock e exp N method with N = 10, show that the first oblique wave had been stabilized. LDA, surface pressure measurement Tollmien-Schlichting mode is responsible for transition at adiabatic and flow visualization techniques were employed for two freestream wall conditions for freestream Mach numbers up to 7. For cold Mach number test cases: 1.6 and 1.3. The former contained walls, the two-dimensional second mode dominates the transition separated flow regions and a system of shock waves. The latter process at lower hypersonic Mach numbers due to the well-known was found to be far less complicated. The reported results are destabilizing effect of cooling on the second mode. It is shown believed to accurately define the flow physics of each case and that pressure gradient and suction may be used to stabilize this may be used as benchmark data to verify three-dimensional mode. Some results on the real gas effects on hypersonic computer codes. Author boundary-layer stability are presented. Author

A87-44943# AERO-OPTICAL ANALYSIS OF COMPRESSIBLE FLOW OVER AN OPEN CAVITY A87-44947"# National Aeronautics and Space Administration. PHILIP E. CASSADY, STANLEY F. BIRCH, and P. JOHN TERRY Langley Research Center, Hampton, Va. (Boeing Aerospace Co., Seattle, WA) AIAA, Fluid Dynamics, STABILITY AND TRANSITION IN SUPERSONIC BOUNDARY Plasma Dynamics, and Lasers Conference, 19th, Honolulu, HI, LAYERS June 8-10, 1987. 13 p. Research supported by the Boeing GORDON ERLEBACHER (NASA, Langley Research Center, Aerospace Co. and Boeing Commercial Airplane Co. refs Hampton, VA) and M. YOUSUFF HUSSAINI (NASA, Langley (AIAA PAPER 87-1399) Research Center; Institute for Computer Applications in Science The propagation of light from a distant point source to an and Engineering, Hamp AIAA, Fluid Dynamics, Plasma Dynamics, idealized optical detector mounted above an open hole in the and Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 13 body of an aircraft in transonic high-altitude flight is investigated p. refs theoretically, with a focus on the effects of the compressible (AIAA PAPER 87-1416) turbulent shear layer forming between the hole and the ambient The full three-dimensional time-dependent compressible air. The flow is simulated numerically (using codes based on the Navier-Stokes equations are numerically solved by a two-dimensional time-dependent Navier-Stokes equations) for Fourier-Chebyshev collocation algorithm to study the stability of altitudes 40,000-50,000 ft and Mach numbers 0.6-0.8; the optical supersonic flows over a flat plate. Several non-linear numerical effects are evaluated (using FFT ray-tracing and image-formation experiments suggest the existence of a secondary instability which codes) for look angles from -60 to +60 deg; and the results are might provide a possible route to transition. The interaction of the presented graphically. Image distortion is found to comprise mainly modes involved in this secondary instability is possibly amenable wavefront tilt (with little higher-order distortion), while image blur to a Floquet theory. Pertinent differences between this instability is attributed to coherent structures in the turbulent shear layer. and the more common incompressible K-type instabilities are T.K. pointed out. Author

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A87-44948# A87-44951# LINEARINSTABILITYWAVESINSUPERSONICTURBULENT NUMERICAL INVESTIGATION OF THE FLOW STRUCTURE MIXINGLAYERS AROUND A RAPIDLY PITCHING AIRFOIL SAADA.RAGAB(VirginiaPolytechnic Institute and State University, MIGUEL R. VISBAL and JOSEPH J. S. SHANG (USAF, Wright Blacksburg) and J. L. WU AIAA, Fluid Dynamics, Plasma Aeronautical Laboratories, Wright-Patterson AFB, OH) AIAA, Fluid Dynamics, and Lasers Conference, 19th, Honolulu, HI, June 8-10, Dynamics, Plasma Dynamics, and Lasers Conference, 19th, 1987. 17p. refs Honolulu, HI, June 8-10, 1987. 19 p. refs (Contract N00014-87-K-0168) (AIAA PAPER 87-1424) (AIAA PAPER 87-1418) A numerical study is presented for unsteady laminar flow past The structures of supersonic turbulent mixing layers are a NACA 0015 airfoil which is pitched, at a nominally constant presumed to be spatially growing instability waves superimposed rate, from zero incidence to a very high angle of attack. The flow on mean flows which are also spatially diverging. The objective of field simulation is obtained by solving the full two-dimensional the work presented here is to determine these waves, and to compressible Navier-Stokes equations on a moving grid employing evaluate the effect of certain parameters such as mean velocity an implicit approximate-factorization algorithm. An assessment of and temperature profiles on the stability characteristics (growth the accuracy of the computed solutions is presented, and the rate, most amplified frequency, etc.). Linear stability theory of numerical results are shown to be of sufficient quality to merit nonparallel mean flow has been used. Three-dimensional waves physical interpretation. The highly unsteady flow field structure is in the form of axisymmetric as well as helical modes interacting described and is found to be in qualitative agreement with available with axisymmetric basic state are considered. The basic state is experimental observations. A discussion is provided for the effects determined by solving the axisymmetric turbulent boundary-layer of pitch rate and pitch axis location on the induced vortical equations for the configuration of unconfined coaxial mixing. A structures and on the airfoil aerodynamic forces. Author mixing length model is used for turbulence closure. Increasing the Mach number of the outer stream or increasing the temperature of the inner stream (gas generator) significantly reduces the growth A87-44952"# National Aeronautics and Space Administration. rate and gain along the mixing layer length. Author Langley Research Center, Hampton, Va. THE NUMERICAL SIMULATION OF SUBSONIC FLUTTER THOMAS W. STRGANAC, MARIA V. MITCHUM (NASA, Langley Research Center, Hampton, VA), and DEAN T. MOOK (Virginia Polytechnic Institute and State University, Blacksburg) AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, 19th, Honolulu, HI, June 8-10, 1987. 11 p. A87-44949# (AIAA PAPER 87-1428) SIMULATIONS OF FLOW FIELDS. I - The present paper describes a numerical simulation of NUMERICAL MODEL, LARGE-SCALE AND MEAN MOTIONS unsteady, subsonic aeroelastic responses. The technique accounts SURESH MENON and WEN-HUEI JOU (Flow Research Co., Kent, for aerodynamic nonlinearities associated with angles of attack, WA) AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers vortex-dominated flow, static deformations, and unsteady behavior. Conference, 19th, Honolulu, HI, June 8-10, 1987. 20 p. refs The fluid and the wing together are treated as a single dynamic (Contract N00014-84-C-0359) system, and the equations of motion for the structure and flowfield (AIAA PAPER 87-1421) are integrated simultaneously and interactively in the time domain. An account is given of the results of a research effort using The method employs an iterative scheme based on a large-eddy numerical simulation to understand the flow pressure predictor-corrector technique. The aerodynamic loads are oscillations in a ramjet combustor. The numerical technique used computed by the general unsteady vortex-lattice method and are in solving the compressible Navier-Stokes equations and the determined simultaneously with the motion of the wing. Two models implementation of the proper boundary conditions are presented, are used to demonstrate the technique: a rigid wing on an elastic together with simulations ensuring that the calculated flow field is support experiencing plunge and pitch about the elastic axis, and independent of grid resolution. The separated shear layer is shown a continuous wing rigidly supported at the root chord experiencing to be unstable, so that concentrated vortices are formed by the spanwise bending and twisting. The time domain solution coupled growth of instability waves. Where the separated shear layer with the unsteady vortex-lattice method provides the capabUity of reattaches on the nozzle wall, strong counter-rotating vortices are graphically depicting wing and wake motion. Several graphs that produced which may be the primary acoustic sources. O.C. illustrate the time domain behavior of the wing and wake are presented. Author

A87-44953"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. A87-44950# TRANSONIC WALL INTERFERENCE ASSESSMENT AND SIMULATIONS OF RAMJET COMBUSTOR FLOW FIELDS. II - CORRECTIONS FOR AIRFOIL DATA FROM THE 0.3-METER ORIGIN OF PRESSURE OSCILLATIONS TCT ADAPTIVE WALL TEST SECTION WEN-HUEI JOU and SURESH MENON (Flow Research Co., Kent, LAWRENCE L. GREEN and PERRY A. NEWMAN (NASA, Langley WA) AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Research Center, Hampton, VA) AIAA, Fluid Dynamics, Plasma Conference, 19th, Honolulu, HI, June 8-10, 1987. 14 p. refs Dynamics, and Lasers Conference, 19th, Honolulu, HI, June 8-10, (Contract N00014-84-C-0359) 1987. 25 p. refs (AIAA PAPER 87-1422) (AIAA PAPER 87-1431) The vorticity fluctuations and pressure fluctuations present in The wall interference assessment/correction code presented the flow inside a ramjet combustor appear to be coherent; an is nonlinear, involves four walls, and is applicable to transonic attempt is presently made to identify the mechanism leading to airfoil data from wind tunnels with shaped, solid top and bottom the observed fluctuations, extracting acoustic information from walls. Attention is given to its application to data from the NASA computed results by visualization of the instantaneous dilatation 0.3-m Transonic Cryogenic Tunnel Adaptive Test Section, for two field. The dilatation field near the impingement point of the shear sizes of a NACA 0012 airfoil and to simulated data for an inviscid layer on the nozzle wall is analyzed by multipole expansion of the two-dimensional full-potential code. This study indicates that while computed dilatation field. The spectra of pressure and vorticity adaptive wall wind tunnels significantly reduce some aspects of fluctuations are analyzed to reveal the existence of two types of wall-interference effects (by comparison to straight solid and slotted fluctuation: the resonant acoustic mode and the coupled mode. A wall wind tunnels), residual wall and other interference effects are simple model is proposed for the coupled mode. O.C. present. O.C.

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A87-44955# A87-45183# FLOW-FIELD MEASUREMENTS OF AN AIRFOIL WITH A FLOW BEHIND SINGLE- AND DUAL-ROTATION PROPELLERS DEFLECTED SPOILER USING AN LDV SYSTEM AT ANGLE OF ATTACK S. BODAPATI, M. J. FOREMAN (U.S. Naval Postgraduate School, THOMAS TENEROWICZ (Boeing Commercial Airplane Co., Seattle, Monterey, CA), and C. S. LEE (Stanford University, CA) AIAA, WA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, 19th, 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. refs Honolulu, HI, June 8-10, 1987. 11 p. Research supported by the (AIAA PAPER 87-1750) Boeing Airplane Co. and U.S. Army. refs The results from two wind tunnel tests, which were conducted (AIAA PAPER 87-1438) to establish a data base to definee the local flowfield downstream Typical experiments were carried out in a small, low-speed of both single- and dual-rotation propellers, are presented here. wind tunnel to obtain the mean and fluctuating flow fields of an The model used for both tests consisted of a nacelle containing airfoil with a deflected spoiler using a two-component laser Doppler a gearbox and a 29-hp that was used to drive an velocimetry (LDV) system. The mean wake profiles and turbulent eight-bladed SR-2 propeller in the first and two counterrotating, shear stresses were evaluated and compared with the available four-bladed SR-2 propellers in the second test. The data were hot-wire and predicted results. Velocity and turbulent stress contour collected at two circumferential and four radial positions by using plots are also presented. Hot-wire results were not available close two split-film flow angularity probes attached to a rake slightly aft to the trailing edge because of the reverse flow. The predicted of the propellers. The data for both tests were collected at simulated results were evaluated using a two dimensional vortex tracing takeoff conditions. The test results show that the top inlet location method. The hot-wire anemometer gives reasonably accurate is best for a single-rotation configuration and that either top or results where there is no reverse flow and the flow is not highly bottom inlet location is appropriate for a dual-rotation configuration. turbulent. The LDV gives accurate results close to the trailing The data also show that the dual-rotation propellers produce lower edge where other methods fail. In general the LDV results are in levels of swirl and radial flow angles at all locations. Author better agreement with the calculated results. Author

A87-45094# STUDY ON THE INTERFERENCE BETWEEN THE LOCAL SEPARATION ON A WING SURFACE AND OUTER FLOW-FIELD A87-45184# KENJI YOSHIDA Japan Society for Aeronautical and Space TWO-DIMENSIONAL NUMERICAL ANALYSIS FOR INLETS AT Sciences, Journal (ISSN 0021-4663), vol. 35, no. 399, 1987, p. SUBSONIC THROUGH HYPERSONIC SPEEDS 197-203. In Japanese, with abstract in English. refs R. H. BUSH, P. G. VOGEL, W. P. NORBY, and B. A. HAEFFELE This paper presents a theoretical consideration on the (McDonnell Aircraft Co., St. Louis, MO) AIAA, SAE, ASME, and interference between the local separated region and its outer flow. ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June To simplify the analysis, a straight wing with an infinite span is 29-July 2, 1987. 12 p. refs assumed to have locally nonuniform distribution of transition points. (AIAA PAPER 87-1751) Using the boundary-layer theory and lifting-line theory, the influence FANSl (factored algorithm for Navier-Stokes, inlets) is a of such local disturbances on the boundary layer and its outer two-dimensional flowfield analysis code for inlet flowfield studies flow is investigated in detail. From this, three-dimensional which is valid for subsonic through hypersonic speeds. Examples characteristics of the local separation are deduced. Once the local are presented which reveal the code's applicability over a wide separation occurs, the thickness of separated region is increased range of conditions with attached and separated boundary layers. by the effect of trailing vortices, and the thickness of the boundary The code can accurately predict the loss mechanisms (flow layer near its region is decreased. The effect of three-dimensional separation shock formation) occurring at subsonic maneuver boundary layer is opposite to that of trailing vortices. Moreover, conditions for a traditional two-ramp external-compression outlet. the separated region is localized by the influence of induced cross In addition, it is capable of obtaining hypersonic separated solutions flow as well as trailing vortices. Author in high contraction ratio diffusers. K.K.

A87-45182"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. INVESTIGATION OF A DELTA-WING FIGHTER MODEL FLOW FIELD AT TRANSONIC SPEEDS E. ANN BARE, DAVID E. REUBUSH (NASA, Langley Research A87-45185# Center, Hampton, VA), RAYMOND HADDAD, ROSS W. NAVIER-STOKES SIMULATIONS OF SUPERSONIC FIGHTER HATHAWAY (McDonnell Aircraft Co., St. Louis, MO), and MIKE FLOWFIELDS COMPTON (USAF, Wright Aeronautical Laboratories, JOSEPH VADYAK, MARILYN J. SMITH, and DAVID M. SCHUSTER Wright-Patterson AFB, OH) AIAA, SAE, ASME, and ASEE, Joint (Lockheed-Georgia Co., Advanced Flight Sciences Dept., Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. Marietta) AIAA, SAE, ASME, and ASEE, Joint Propulsion 10 p. refs Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 17 p. (AIAA PAPER 87-1749) Research supported by Lockheed Independent Research and The paper reports a flow-field investigation on a 7.52-percent Development Programs. refs scale model of an advanced design conducted in (AIAA PAPER 87o1752) the NASA-Langley 16-ft Transonic Tunnel. The effects of An analysis is presented for calculating steady (or unsteady) free-stream Mach number, angle-of-attack, angle of sideslip, and three-dimensional supersonic fighter intake flowfields. This various vortex control devices on the local flow values were studied. algorithm can compute the flowfield about forebody, inlet, and The model was tested at Mach numbers of 0.6, 0.9, and 1.2 and diffuser configurations at zero or nonzero incidence. The algorithm the angles of sideslip of 0 and +/- 5 deg; the model angle-of-attack can solve either the Euler momentum equations for inviscid flow, was varied from -4 to 30 deg. Results are presented in terms of the thin- and shear-layer Navier-Stokes equations for viscous flow, contour plots of local total pressure recovery. The dominant or the full Navier-Stokes equations for viscous flow. The flowfield influence on the over-wing flow field was found to be the wing is determined on a body-fitted numerically-generated computational leading-edge vortex which first appears in the survey region at an grid. A fully-implicit alternating-direction-implicit algorithm is angle-of-attack of 8 deg and increases in strength and influence employed for solution of the finite-difference equations. Viscous with increasing angle-of-attack, finally dominating the entire survey flow results are presented to illustrate application of the analysis region at very high angles-of-attack. I.S. for cases at supersonic free-stream speeds. Author

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A87-45238"# National Aeronautics and Space Administration. A87-45281"# Lockheed-Georgia Co., Marietta. Langley Research Center, Hampton, Va. WIND TUNNEL TESTS ON A ONE-FOOT DIAMETER SR-7L PARAMETRIC STUDY OF SINGLE EXPANSION RAMP NOZZLES PROPFAN MODEL AT SUBSONIC/TRANSONIC SPEEDS ABDULLAH S. ALJABRI (Lockheed-Georgia Co., Marietta) AIAA, F. J. CAPONE, R. J. RE, E. A. BARE (NASA, Langley Research SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Center, Hampton, VA), and M. K. MACLEAN ( Diego, CA, June 29-July 2, 1987. 12 p. Co., Cincinnati, OH) AIAA, SAE, ASME, and ASEE, Joint (Contract NAS3-24339) Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, (AIAA PAPER 87-1892) 1987.--12 p. refs Wind tunnel tests have been conducted on a one-foot diameter (AIAA PAPER 87-1836) model of the SR-7L propfan in the Langley 16-Foot and 4 x 7 The Langley Research Center has conducted a parametric Meter Wind Tunnels as part of the Propfan Test Assessment (PTA) investigation to determine the aeropropulsive characteristics of Program. The model propfan was sized to be used on a 1/9-scale single expansion ramp nozzles (SERN). The SERN is a model of the PTA testbed aircraft. The model propeller was tested nonaxisymmetric, variable-area, internal/external expansion in isolation and wing-mounted on the aircraft configuration at exhaust nozzle. Internal nozzle parameters that were varied various Mach numbers and angles. Agreement between included upper ramp length, ramp chordal angle, lower flap length, data obtained from these tests and data from Hamilton Standard flap angle and the axial and vertical locations of nozzle throat. validate that the 1/9-scale propeller accurately simulates the Convergent-divergent and convergent nozzles were included in aerodynamics of the SR-7L propfan. Predictions from an analytical this investigation which was conducted in the Langley 16-Foot computer program are presented and show good agreement with Transonic Tunnel at Mach numbers from 0.6 to 1.2 and at nozzle the experimental data. Author pressure ratios up to 12.0. Author

A87-45278# PERFORMANCE CALCULATION OF COUNTER ROTATION A87-45283# PROPELLER NUMERICAL ANALYSIS OF PEAK HEAT TRANSFER RATES S. SAITO, H. KOBAYASHI (National Aerospace Laboratory, Tokyo, FOR HYPERSONIC FLOW OVER A COWL LEADING EDGE Japan), K. NASU (Ishikawajima-Harima Heavy Industries Co., Ltd., JEFFREY A. WHITE (Pratt and Whitney, West Palm Beach, FL) Tokyo, Japan), and Y. NAKAMURA AIAA, SAE, ASME, and and CHEA M. RHIE (Pratt and Whitney, East Hartford, CT) AIAA, ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San 29-July 2, 1987. 9 p. refs Diego, CA, June 29-July 2, 1987. 10 p. refs (AIAA PAPER 87-1889) (AIAA PAPER 87-1895) A newly developed aerodynamic code, named Local Circulation The complex viscous shock interaction phenomenon present Method (LCM), was applied to high-speed counterrotation when an oblique shock impinges on a blunt body bow shock, and propellers (CRPs) to investigate the potentials of these highly the peak heat transfer rates representative of the flow field near skewed/swept blade systems operating in high subsonic or the inlet cowl leading edge of a hypersonic vehicle are computed. transonic range. The calculations of CRP performance in a wide A pressure based implicit finite volume method is used to solve range of geometrical and operational rotor variables provided the the steady state Reynolds averaged Navier-Stokes equations for design data base for CRPs, including efficiency maps parametered the flow field. Steady state solutions are obtained for the complete by blade pitch angles of front and rear rotor. It was shown that, bow-oblique shock flow field with all shocks, shear layers, jets, compared with SRP, the CRP has a potential of higher efficiency and boundary layers being captured by the computational with several percentage points. I.S. procedure. Computed results are presented for two dimensional blunt body flows with and without shock impingement and are compared with data. Computed peak heat transfer and stagnation pressure augmentation are presented and compared with experimental data. Author A87-45280# EXTENSION OF LOCAL CIRCULATION METHOD TO COUNTER ROTATION PROPELLER SHIGERU SAITO, HORISHI KOBAYASHI (National Aerospace Laboratory, Tokyo, Japan), YOSHIYA NAKAMURA (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan), and KENICHI NASU AIAA, SAE, ASME, and ASEE, Joint A87-45284"# PEDA Corp., Palo Alto, Calif. Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. AERODYNAMIC DESIGN MODIFICATION OF A HYPERSONIC 10 p. refs WIND TUNNEL NOZZLE BY CSCM WITH HIGH ORDER (AIAA PAPER 87-1891) ACCURACY A computational method for rotary wing airloading calculation J. Y. YANG, C. K. LOMBARD, R. C.-C. LUH, N. NAGARAJ, and called the local circulation method (LCM) has been extended to a W. H. CODDING (PEDA Corp., Palo Alto, CA) AIAA, SAE, ASME, counter rotation propeller (CRP). The new method is a combination and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, of LCM for single rotor and a coaxial helicopter rotor model used June 29-July 2, 1987. 10 p. refs in the local momentum theory (LMT) with some modifications. (Contract NAS2-12243) The interaction of two rotors via swirl velocity is introduced in (AIAA PAPER 87-1896) addition to axial induced velocity. Results are compared with those An improved version of the CSCM implicit Navier-Stokes solver of experiment for subsonic CRP performance and showed a good with a flexible data structure has been applied, in conjunction agreement. It is applied to transonic propeller employing with a sophisticated patched grid system, to the aerodynamic experimental two-dimensional lift slope data at high Mach number. analysis of hypersonic axisymmetric contoured nozzles of the It also resulted in a good agreement with Euler calculation in NASA-Ames 3.5-foot hypersonic wind tunnel. The results obtained single rotation advanced turbo-prop (ATP). Some results of are found to be in good agreement with experiment. Based on calculation are given both for performance and time dependent the analysis, a newly designed throat contour for the Mach 14 airloading. Author nozzle has been recommended. V.L.

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A87-45332"#National Aeronautics and Space Administration. A87-45394# Langley Research Center, Hampton, Va. THE INFLUENCE OF FLOW NON-UNIFORMITIES IN THREE-DIMENSIONAL NUMERICAL PREDICTIONS OF THE AIR-BREATHING HYPERSONIC PROPULSION SYSTEMS FLOW BEHIND A REARWARD-FACING-STEP IN A MARK J. LEWIS and DANIEL E. HASTINGS (MIT, Cambridge, SUPERSONIC COMBUSTOR MA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, K. UENISHI (NASA, Langley Research Center; Vigyan Research 23rd, San Diego, CA, June 29-July 2, 1987. 15 p. Research Associates, Inc., Hampton, VA), R. C. ROGERS, and G. B. supported by the Charles Stark Draper Laboratory. refs NORTHAM (NASA, Langley Research Center, Hampton, VA) (AIAA PAPER 87-2079) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, The generation of inlet nonuniformities and their influence on San Diego, CA, June 29-July 2, 1987. 12 p. refs the flowfield of a supersonic combustion ramjet, or , is (AIAA PAPER 87-1962) examined. In particular, the problem of inlet Mach number and A CFD code was developed to compute the mixing and mass flux stratification through the formation of a thick forebody combustion of hydrogen fuel in the turbulent flow fields of . boundary layer is considered, along with the effect that the The code is based on the complete Reynold's time-averaged boundary layer flow will have on the inviscid core region inside three-dimensional Navier-Stokes equations, and chemical species the scramjet. Estimates are made of the expected thickness of equations. The code includes a global finite rate hydrogen-air the hypersonic boundary layer at various flight conditions that are chemical reaction model and the Baldwin-Lomax (1976) turbulence applicable to a trans-atmospheric vehicle trajectory, and these are model. The validity of this CFD code was demonstrated by related to the position of the vehicle bow shock. It is found that comparing computed results from the code with existing data for an engine designed for uniform flow cannot tolerate large inlet three configurations, each containing an important feature of the gradients in Mach number and mass flux. It is suggested that, in scramjet combustor flow. The code was then applied to the reacting order to reduce the thickness of the forebody boundary layer, an flow field in a complex combustor model in which hydrogen fuel aerospace plane may operate more effectively at lower altitudes was injected transversely into a supersonic hot airstream through than those which optimize lift-to-drag. Such a vehicle would also several fuel injectors. I.S. be restricted to a narrow range of angles of attack because of the sensitivity of the hypersonic boundary layer thickness to deflection angle. Author A87-45334# FORCE ACCOUNTING FOR AIRFRAME INTEGRATED A87-45397# ENGINES A STAGE-BY-STAGE POST-STALL COMPRESSION SYSTEM GARY A. SULLINS and FREDERICK S. BILLIG (Johns Hopkins MODELING TECHNIQUE University, Laurel, MD) AIAA, SAE, ASME, and ASEE, Joint M. W. DAVIS, JR. (Sverdrup Technology, Inc., Arnold Air Force Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. Station, TN) and W. F. O'BRIEN (Virginia Polytechnic Institute 10p. and State University, Blacksburg) AIAA, SAE, ASME, and ASEE, (AIAA PAPER 87-1965) Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July This paper is intended to clarify some of the issues concerning 2,1987.15p. refs force accounting methods for systems employing air breathing (AIAA PAPER 87-2088) propulsion. A detailed derivation of the thrust equation is presented A one-dimensional, stage-by-stage axial compression system for a somewhat simplified vehicle configuration using the freestream mathematical model has been constructed which can describe as the upstream reference plane. In doing so, forces on the system behavior during post-stall events such as surge and rotating forebody were considered as aerodynamic forces. The method stall. The model uses a numerical technique to solve the nonlinear was then extended to a more complicated vehicle in which the conservation equations of mass, momentum, and energy. Inputs engine is integrated into a vehicle airframe. Since this is but one for blade forces and shaft work are provided by a set of of the possible methods of force accounting, it was compared to quasi-steady stage characteristics modified by a first-order lagging another in which the inlet cowl plane is used as the upstream equation to simulate dynamic stage characteristics. The model reference plane. Whereas, this alternative method and others are was validated with experimental results for a three-stage, low-speed valid, as long as all forces are properly accounted for, to obtain compressor and a nine-stage, high-pressure compressor. Using the same degree of accuracy requires considerably more rigor. the model, a parametric study was conducted to determine the Author effect on post-stall system behavior of inlet resistance, combustor performance, heat transfer, and stage characteristic changes. Results demonstrate a new capability for the analysis of design A87-45386"# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. options and operating conditions on compression system post-stall behavior. Author UNSTEADY THREE-DIMENSIONAL NAVIER-STOKES SIMULA- TIONS OF TURBINE ROTOR-STATOR INTERACTION MAN MOHAN RAI (NASA, Ames Research Center, Moffett Field, A87-45413"# National Aeronautics and Space Administration. CA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, Lewis Research Center, Cleveland, Ohio. 23rd, San Diego, CA, June 29-July 2, 1987. 29 p. NASA-supported TWO-DIMENSIONAL NOZZLE PLUME CHARACTERISTICS research, refs UWE H. VON GLAHN (NASA, Lewis Research Center, Cleveland, (AIAA PAPER 87-2058) OH) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, Fluid flows within turbomachinery tend to be extremely complex. 23rd, San Diego, CA, June 29-July 2, 1987. 20 p. Previously Understanding such flows is crucial to efforts to improve current announced in STAR as N87-18540. refs turbomachinery designs, and the computational approach can be (AIAA PAPER 87-2111) used to great advantage in this regard. This study presents a Future high performance aircraft will likely feature asymmetric finite-difference, unsteady, thin-layer Navier-Stokes approach to or two-dimensional nozzles with or without ejectors. In order to calculating the flow within an axial turbine stage. The relative motion design two-dimensional nozzle/ejector systems of minimum size between the stator and rotor airfoils is made possible with the and weight, the plume decay and spreading characteristics of basic use of patched grids that move relative to each other. The two-dimensional nozzles must first be established. The present calculation includes end-wall and tip-leakage effects. Results in work deals with the experimental analyses of these plume the form of time-averaged surface pressures, pressure amplitudes characteristics and includes the effects of nozzle aspect ratio and (corresponding to the pressure fluctuation in time), near-surface flow conditions (jet Mach number and temperature) on the plume velocity vectors, and pressure contours in the passage areas are decay and spreading of two-dimensional nozzles. Correlations presented. The numerical results are compared with experimental including these variables are developed in a manner similar to data wherever possible, and the agreement between the two is those previously developed successfully for conic and dual-flow found to be good. Author plumes. Author

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A87-46414"# National Aeronautics and Space Administration. anemometry and flow visualization. Measurements are performed Lewis Research Center, Cleveland, Ohio. at 0 deg mean incidence angle with oscillation amplitude of 7.4 SECONDARY STREAM AND EXCITATION EFFECTS ON deg, for three values of reduced frequency K = 0.09, 0.13 and TWO-DIMENSIONAL NOZZLE PLUME CHARACTERISTICS 0.20. Velocity and turbulence intensity profiles, determined by UWE H. VON GLAHN (NASA, Lewis Research Center, Cleveland, ensemble average technique, are reported and compared. A OH) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, peculiar flow pattern with 'turbulent blobs' is observed during the 23rd, San Diego, CA, June 29-July 2, 1987. 12 p. Previously period of oscillation, of which the visualization picture is included. announced in STAR as N87-18539. refs Author (AIAA PAPER 87-2112) In order to design two-dimensional nozzle/ejector systems for future high performance aircraft, the basic engine exhaust plume velocity and temperature decay as effected by the secondary stream (ejector) and decay augmentation means must be assessed. A87-45792 Included in the assessment of the plume decay characteristics UNSTEADY VISCOUS FLOWS ROUND MOVING CIRCULAR are the effects of nozzle aspect ratio and nozzle/ejector flow CYLINDERS AND AIRFOILS. II conditions. Nozzle/ejector plume decay can be enhanced by Y. LECOINTE and J. PIQUET (Ecole Nationale Superieure de suitable excitation of the plume shear layers. Correlations of these Mecanique, Nantes, France) IN: Turbulence measurements and factors are developed in a manner similar to those previously flow modeling; Proceedings of the International Symposium, Iowa developed for conic and dual-flow nozzle plumes. Author City, IA, Sept. 16-18, 1985 . Washington, DC, Hemisphere Publishing Corp., 1987, p. 675-684. refs A87-45435# (Contract DRET-83/215) DEVELOPMENT OF A VISCOUS CASCADE CODE BASED ON High Reynolds number laminar flow around circular cylinders SCALAR IMPLICIT FACTORIZATION and airfoils, with or without superimposed motions of high reduced C. J. KNIGHT and D. CHOI (Avco Everett Research Laboratory, amplitude, are presently addressed by the solution of unsteady, Inc., MA) AIAA, SAE, ASME, and ASEE, Joint Propulsion two-dimensional Navier-Stokes equations that are written in their Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 18 p. vorticity streamfunction formulation and then solved numerically Research sponsored by the Avco Lycoming Independent Research by means of compact schemes. The procedure presented for the and Development Program. refs interpretation of harmonic results is shown to be useful. Attention (AIAA PAPER 87-2150) is given to the cases of a pitching elliptic cylinder and a surging A viscous cascade code has been developed, first for 2D NACA 0012 airfoil. O.C. configurations and then extended to 3D linear cascades with flat, parallel endwalls. It employs scalar implicit approximate factorization, a finite volume formulation, second order upwind differencing, and a two-equation q-omega turbulence model based on integration to the wall. A special form of the thin layer A87-46094 approximation for the compressible Navier-Stokes equations is used AERODYNAMIC CHARACTERISTICS OF WAVE RIDERS which gives accurate skin friction predictions on highly skewed [AERODINAMICHESKIE KHARAKTERISTIKI VOLNOLETOV] meshes, now based on sheared H-grids. The 2D code has been A. I. SHVETS PMTF - Zhurnal Prikladnoi Mekhaniki i Tekhnicheskoi validated by considering testcases for NASA Energy Efficient Fiziki (ISSN 0044-4626), Mar.-Apr. 1987, p. 62-68. In Russian. Engine blade and vane cascade geometries. The turbulence model refs displays proper boundary layer transition behavior. The 3D E(3) The lifting force, aerodynamic efficiency, and shock wave forms vane cascade has also been considered with straight endwalls. are investigated for several lifting configurations with a sharp bend Agreement with experiment is quite good. Author in the transverse profile, including caret wings, triangular wings with a conical bend, winged pyramidal bodies, and A87-45436# rectangular-planform caret wings. In the Mach number range 2-6, NAVIER-STOKES SOLUTIONS FOR HIGHLY LOADED TURBINE the triangular-planform wings with a bend in the transverse profile CASCADES investigated here are shown to have a higher aerodynamic B. N. SRIVASTAVA (Avco Everett Research Laboratory, Inc., efficiency than equivalent plane triangular wings. V.L. Everett, MA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 11 p. Research supported by the Avco Everett Research Laboratory Independent Research and Development Funds. refs (AIAA PAPER 87-2151) A87-46184# This paper deals with computation of 2-D turbulent thin-layer A COMPUTATIONAL METHOD FOR DETERMINING FLOWFIELD Navier-Stokes equations in a highly loaded turbine cascade PROPERTIES WHEN THE PITOT PRESSURE IS THE ONLY geometry at subsonic and transonic conditions. MacCormack's MEASURED INSTREAM PROPERTY explicit scheme has been utilized for overall cascade flow R. D. STOCKBRIDGE (Johns Hopkins University, Laurel, MD) IN: predictions which have been favorably compared with flow International Symposium on Air Breathing Engines, 8th, Cincinnati, visualizations for bulk flow behavior and with surface pressure OH, June 14-19, 1987, Proceedings. New York, American Institute data, outflow angles and outflow Mach numbers for both C- and of Aeronautics and Astronautics, 1987, p. 77-83. refs H-grid topologies. Author A computational procedure has been developed for the calculation of all in-stream flow properties in a ducted supersonic A87-45779 flow where viscous effects are important. Experimental WAKE MEASUREMENTS OF AN OSCILLATING AIRFOIL measurements of pitot pressures, wall pressures and temperature, S. O. PARK and J. S. KIM (Korea Advanced Institute of Science and upstream plenum conditions are the input data. The method and Technology, Seoul, Republic of Korea) IN: Turbulence has been designed for use when reliable measurements for a measurements and flow modeling; Proceedings of the International second instream flowfield property are unavailable. The Symposium, Iowa City, IA, Sept. 16-18, 1985 . Washington, DC, experimental flowfields for which the procedure was developed Hemisphere Publishing Corp., 1987, p. 127-136. Research were Mach 1.66, 2.35 and 2.89 flows through an annular duct supported by the Korea Advanced Institute of Science and with a length to height ratio of 18.6. The computational procedure Technology and Korea Science Foundation. refs divides the annular cross section into five zones and applies various Wake flow fields of NACA 0012 airfoil oscillating sinusoidally standard theoretical constraints to the measured data to solve for about 25 percent chord axis are investigated using hot wire deg the instream flow properties. Author

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A87-46189# stream surface of a centrifugal impeller. The problem of mixed EFFICIENCYPARAMETERSFORINLETSOPERATINGAT flow can be solved by the use of artificial compressibility method, HYPERSONICSPEEDS and the shock within the inducer can be captured automatically. FREDERICK S. BILLIG and DAVID M. VAN WlE (Johns Hopkins The distribution of the fluid velocity from hub to shroud can be University, Laurel, MD) IN: International Symposium on Air obtained directly by integrating the velocity gradient equation, after Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, knowing the streamline pattern. A computer program has been Proceedings . New York, American Institute of Aeronautics and coded which can be used in the S(1)-S(2) iteration procedure in Astronautics, 1987, p. 118-130. refs order to get the three-dimensional analysis solution for a high A variety of parameters have been introduced to define the pressure ratio . It can also be used as a efficiency of the compression process in the intake of an component in a transonic means of CAD method, by which the airbreathing engine. In some regard, each of the previously designer can design a transonic centrifugal compressor more introduced efficiency parameters is deficient when applied to the efficiently. The transonic flow field on a mean S(2) stream surface case of an inlet operating at high hypersonic speed with a of an 8:1 pressure ratio centrifugal compressor impeller has been compressed gas comprised of nonuniform flow. This paper will computed using this computer program. A comparison of computed delineate these deficiencies and will introduce a new parameter results with experimental data shows fairly good agreement. that avoids most of the previous limitations and provides a simplified Author tool for indexing complex inlet flows. Author A87-46204# A87-46191# APPLICATION OF A 3D INVISCID ROTATIONAL DESIGN 3-D VISCOUS FLOW CALCULATIONS AT DESIGN AND PROCEDURE FOR TURBOMACHINERY BLADINGS OFF-DESIGN CONDITIONS FOR THE NACA 48-INCH MAURO VARETTI and FRANCESCO LAROCCA (FIAT Aviazione RADIAL-INLET CENTRIFUGAL IMPELLER S.p.A., Turin, Italy) IN: International Symposium on Air Breathing JOHN MOORE and JOAN G. MOORE (Virginia Polytechnic Institute Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . and State University, Blacksburg) IN: International Symposium New York, American Institute of Aeronautics and Astronautics, on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, 1987, p. 246-252. refs Proceedings . New York, American Institute of Aeronautics and A method for solving cascade design problem for compressible Astronautics, 1987, p. 139-148. Research supported by the inviscid three-dimensional flow is considered. The Euler equations Rolls-Royce, PLC. refs are solved by using a time-marching procedure with one sided An elliptic flow calculation procedure has been used to model differences approximations. The method provides the geometry of three-dimensional flow in the NACA 48-inch centrifugal impeller. the cascade corresponding to a given pressure jump distribution The results demonstrate that fully elliptic steady turbulent flow across the blade surfaces. The closure condition is directly ensured calculations can be performed at design and off-design conditions. by prescribing blade thickness distribution. Examples are presented The calculations reproduce most of the features of the NACA for inviscid rotational transonic shockless stator blades and some study and they allow a quantitative assessemnt of the NACA results. checks on the accuracy of the computations are discussed. They show an ability to handle complex three-dimensional flow Author with leading-edge separation and tip leakage, and the losses due to these effects are in good agreement with the NACA A87-46206# measurements. Author NUMERICAL SIMULATION OF TRANSONIC THREE-DIMEN- SIONAL FLOWS IN PASSAGES A87-46192# M. IA. IVANOV IN: International Symposium on Air Breathing INVESTIGATION OF THE THREE DIMENSIONAL FLOW NEAR Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . THE EXIT OF TWO BACKSWEPT TRANSONIC CENTRIFUGAL New York, American Institute of Aeronautics and Astronautics, IMPELLERS 1987, p. 261-270. refs CH. FRADIN (ONERA, Chatillon-sous-Bagneux, France) IN: There are presented the modern numerical methods of the International Symposium on Air Breathing Engines, 8th, Cincinnati, transonic three-dimensional flow analysis widely used to turbine OH, June 14-19, 1987, Proceedings. New York, American Institute design of the airbreathing engines. Principal consideration is given of Aeronautics and Astronautics, 1987, p. 149-155. refs to effective flow calculation procedures for the approximation of By employing hot wire probes, a detailed analysis of the flow the ideal gas. Developed calculation methods are based on different field in the vicinity of the impeller outlet section for two transonic flow models including potential approximation and full centrifugal compressors with backward leaned blades has been multi-dimensional models for vortex flows. Characteristic calculation carded out. One of the rotors is equipped with splitter vanes. examples of the transonic flows past turbine blade passages are Using coordinates within the relative frames linked to the rotor, given. Author the test results give the velocity distribution at the impeller outlet. Effect of the splitter vanes on flow distribution is clearly shown. Tests were made at several radii at the outlet of the rotor in the A87-46208# vaneless diffuser. The increase in amplitude of the axial TIP CLEARANCE FLOWS. I - EXPERIMENTAL INVESTIGATION heterogeneities and the decay of the blade to blade ones are OF AN ISOLATED ROTOR. II - STUDY OF VARIOUS MODELS shown. Using mean values of the impeller outlet flow parameters, AND COMPARISON WITH TEST RESULTS the effect of rotor geometry on diffuser performance can be M. J. P. SCHMIDT (Instituto Tecnologico de AeronauUca, Sao Jose measured. Author dos Campos, Sao Paulo, Brazil), B. AGNEW (Newcastle-upon-Tyne, University, England), and R. L. ELDER (Cranfield Institute of A87-46195# Technology, Bedford, England) IN: International Symposium on TRANSONIC STREAM FUNCTION SOLUTION ON S(2) Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, STREAMSURFACE FOR A HIGH PRESSURE RATIO Proceedings . New York, American Institute of Aeronautics and CENTRIFUGAL COMPRESSOR Astronautics, 1987, p. 291-306. refs XIAOLU ZHAO (Chinese Academy of Sciences, Institute of Experiments have been undertaken to define the effect of tip Engineering Thermophysics, Beijing, People's Republic of IN: clearance on a low-speed, isolated rotor over a range of tip International Symposium on Air Breathing Engines, 8th, Cincinnati, clearances, with attention to the spanwise distribution of blade OH, June 14-19, 1987, Proceedings. New York, American Institute losses. The first part of this study notes that spanwise loss of Aeronautics and Astronautics, 1987, p. 168-174. refs distribution is strongly dependent on tip clearance and stage loading In this paper, the conservative stream function equation values. The second part compares these results to predictions of expressed with respect to a curvilinear stream surface coordinate various models, including those of Hesslegreaves (1969), Lewis system is used to calculate the transonic flow field along S(2) (1977), Lakshminarayana (1970), and Robinson (1982). This last

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model, which is the simplest one employed, also yielded the closest A87-46223# approximations to experimental results. O.C. FLOW PHENOMENA IN TRANSONIC TURBINE CASCADES DE- TAILED EXPERIMENTAL AND NUMERICAL INVESTIGATION H.-J. DIETRICHS, J. HOURMOUZIADIS, F. MALZACHER (MTU Motoren- und Turbine-Union Muenchen GmbH, Munich, West A87-46211 # Germany), and W. BRAEUNLING (DFVLR, Institut fuer A STUDY OF SOME FACTORS AFFECTING THE Experimentelle Stroemungsmechanik, Goettingen, West Germany) PERFORMANCE OF A CONTRA-ROTATING AXIAL IN: International Symposium on Air Breathing Engines, 8th, COMPRESSOR STAGE Cincinnati, OH, June 14-19, 1987, Proceedings . New York, P. B. SHARMA, Y. P. JAIN, and D. S. PUNDHIR (Indian Institute American Institute of Aeronautics and Astronautics, 1987, p. of Technology, New Delhi, India) IN: International Symposium 425-435. refs on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, The reduction of the number of turbine stages in order to Proceedings . New York, American Institute of Aeroanutics and reduce the weight, the complexity and the cooling air requirement Astronautics, 1987, p. 324-330. Research supported by the Aero of aircraft engines causes a considerable increase of the R&D Board of India. refs aerodynamic loading of the turbomachinery components. The An experimental investigation of the performance of a resulting transonic flow fields within the vanes and blades of highly contra-rotating stage is reported. The influence of factors such as loaded turbines is dominated by the intensity of compression speed ratio of the two rotors, rotor stagger, pitch-chord ratio and shocks and their interaction with the suction side boundary layer. axial spacing between the rotors is examined from tests on a The shock structures, their intensity and the interaction mechanism 0.66 hub-tip ratio compressor. The study reveals that the are discussed using schlieren photography, static pressures and performance of a contra-rotating stage is affected by all these wake measurements as well as numerical analysis. The contour factors. Axial spacing between the rotors and the speed ratio of of the separation bubble in the visious interaction zone could be the rotors both exhibit a strong influence on the stalling behavior modelled satisfactorily by means of the method of characteristics. of the stage. It has been found that in a stage with close axial An inviscid time marching computer code was used for the gap, rotating stall on the first rotor is suppressed if the second computation of the surface-Mach-number distributions and the rotor is contra-rotated at a speed 50 percent faster than the first transonic flow fields. Author rotor. This unique advantage of contra-rotation is not obtained if the axial gap is large. Measurements of sound pressure level are also reported to highlight the high noise problems associated with A87-46232# a contra-rotating stage. Author UNDEREXPANDED JET-FREE STREAM INTERACTIONS ON AN AXISYMMETRIC AFTERBODY CONFIGURATION N. B. MATHUR and K. S. YAJNIK (National Aeronautical Laboratory, Bangalore, India) IN: International Symposium on Air Breathing A87-46215# Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings. AN IMPROVED APPROACH FOR TRANSONIC FLOW New York, American Institute of Aeronautics and Astronautics, F. MARTELLI (Firenze, Universita, Florence, Italy) and A. 1987, p. 507-512. refs BORE'I-I'I IN: International Symposium on Air Breathing Engines, The exhaust jet-freestream interactions of an axisymmetric 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . New York, afterbody configuration have been studied experimentally, using American Institute of Aeronautics and Astronautics, 1987, p. an equivalent body-of-revolution representative of an actual combat 362-370. refs aircraft configuration. Attention is given to the effects of jet pressure An efficient explicit algorithm is presented for solving ratio and freestream Mach number on boattail, base, and afterbody compressible time-dependent Navier-Stokes equations for mass, pressure drag, for Mach numbers of 0.6-1.1 and Reynolds numbers momentum, and energy in the transonic flow field of plane turbine from 20 million/m to 35 million/m, at zero-dog incidence. Jet cascades. The flow equations are written in dimensionless integral pressure ratio was varied over 1-6. The underexpanded jet plume form, and then discretized by means of a classical explicit, primarily affects the afterbody pressure distribution, and therefore dissipative, pseudounsteady finite-area technique. A simple the afterbody pressure drag. O.C. algebraic eddy viscosity model is employed, and the results of coarse grid computations for two transonic turbine blade sections A87-46238# are found to be in good agreement with experimental data. O.C. A METHOD FOR THE CALCULATION OF THE INTERACTION OF A TURBULENT BOUNDARY LAYER WITH A SHOCK WAVE A87-46216# J. KALLAS and K. D. PAPAILIOU (National Technical University, IMPROVEMENT OF AERODYNAMIC CALCULATION ON S(2)M Athens, Greece) IN: International Symposium on Air Breathing STREAM SURFACE OF AXIAL COMPRESSOR BY USING OF Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . ANNULUS WALL BOUNDARY LAYER CALCULATION New York, American Institute of Aeronautics and Astronautics, WANG QINGHUAN and SU JIAN (Chinese Academy of Sciences, 1987, p. 551-560. refs Institute of Engineering Thermophysics, People's Republic of A two equation energy integral shear layer.method is presented China) IN: International Symposium on Air Breathing Engines, and used for the calculation of the normal shock/turbulent boundary 8th, Cincinnati, OH, June 14-19, 1987, Proceedings. New York, layer interaction. The effect of wall curvature and normal fluctuation American Institute of Aeronautics and Astronautics, 1987, p. terms is taken into account. The interaction is computed using 371-377. refs the approximate method of Mason, Inger and Panaras. This paper presents an approach to improve the aerodynamic Comparisons with experiment give good results, both for attached calculations on S(2)m (mean S(2) stream surface) by employing and detached situations. Author the annulus wall boundary layer (AWBL) calculation technique. A simplified formula of transforming the displacement thickness of A87-46264 AWBL into the mass flow blockage coefficient conventionally used THE AIR-INJECTION METHOD OF FIXING BOUNDARY-LAYER in S(2)m calculation has been proposed. The inviscid-viscid iterative TRANSITION AND INVESTIGATING SCALE EFFECTS calculations using three different schemes have been carried out P. R. ASHILL, J. L. FULKER, and D. J. WEEKS (Royal Aircraft to investigate the blockage effects of AWBL on the S(2)m Establishment, Bedford, England) Aeronautical Journal (ISSN calculation. The results of improved S(2) calculations for both of 0001-9240), vol. 91, May 1987, p. 214-224. refs a single-stage and a ten-stage axial compressor were compared The paper describes the air-injection method of fixing transition with that measured by laser two-focus velocimeter in the in wind-tunnel tests on a two-dimensional aerofoil and a swept compressor rotor. Author panel at high subsonic free-stream speeds. The method is shown

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toprovidea repeatablelevelof disturbancewhich,foragiven an incompressible two-dimensional strong interaction method for flow condition, may be generated without interrupting the test and multielement configurations. Improvements of the present which appears not to cause a significant excess drag. Examples calculation method are proposed, including the incorporation of a are given illustrating the effectiveness of the technique in two-equation integral transport model for the prediction of strongly demonstrating scale-sensitive features of flows, and a correlation separated flow regions. R.R. is presented which allows the minimum value of air-injection mass flow needed to fix transition to be estimated from a knowledge of the behavior of natural laminar flow on the wing. Author A87-46804" High Technology Corp., Hampton, Va. LINEAR STABILITY ANALYSIS OF THREE-DIMENSIONAL A87-46265 COMPRESSIBLE BOUNDARY LAYERS INVESTIGATION OF THE AERODYNAMIC PERFORMANCE AND MUJEEB R. MALIK (High Technology, Inc., Hampton, VA) and NOISE CHARACTERISTICS OF A II5TH SCALE MODEL OF STEVEN A. ORSZAG (Princeton University, NJ) Journal of THE DOWTY ROTOL R212 PROPELLER Scientific Computing (ISSN 0885-7474), vol. 2, March 1987, p. 77-97. refs W. J. G. TREBBLE Aeronautical Journal (ISSN 0001-9240), vol. 91, May 1987, p. 225-236. (Contract NAS1-15604; NAS1-16977; NAS1-16237) An investigation of the four-bladed Dowty Rotol R212 propeller A compressible stability analysis computer code is developed. (NACA 16 sections) has been made at l/5th scale (0.7 meter The code uses a matrix finite-difference method for local eigenvale diameter) in the RAE 1.5 meter acoustic tunnel. Propeller power solution when a good guess for the eigenvalue is available and is absorption and thrust have been measured over a range of significantly more computationally efficient than the commonly used rotational speeds up to 8000 rev/min at mainstream speeds fromm inital-value approach. The local eigenvalue search procedure also 15 m/s to 60 m/s for a range of blade settings. Slipstream wake results in eigenfunctions and, at little extra work, group velocities. surveys show outward movement of the position of the peak A globally convergent eigenvalue procedure is also developed that pressure as propeller loading is increased. Noise analysis may be used when no guess for the eigenvalue is available. The demonstrates the predominance of multiple tones whose number global problem is formulated in such a way that no unstable and intensity increase with helical-tip Mach number. An empirical spurious modes appear so that the method is suitable for use in formula shows that the fundamental tone SPL varies with tip speed a black-box stability code. Sample stability calculations are and power loading in an identical manner to that observed on a presented for the boundary layer profiles of an LFC swept wing. Author modern ARA-D section propeller. Author

A87-46328# A87-46759# AEROTHERMODYNAMIC COMPUTATIONS FOR SUPER-/ UNSTEADY VISCOUS-INVISCID INTERACTION METHOD AND HYPERSONIC FLIGHT COMPUTATION OF BUFFETING OVER AIRFOILS BERNHARD WAGNER and HERBERT RIEGER Dornier-Post P. GIRODROUX-LAVIGNE and J. C. LE BALLEUR (ONERA, (English Edition) (ISSN 0012-5563), no. 2, 1987, p. 28-30. Chatillon-sous-Bagneux, France) (Institute of Mathematics and Numerical methods for the aerodynamical evaluation of space its Applications and SMAI, Joint Conference on Computational transport and supersonic/hypersonic transport aircraft are Methods in Aeronautical Fluid Dynamics, University of Reading, described. Short and medium term problem sets for spaceflight England, Apr. 6-8, 1987) ONERA, TP, no. 1987-58, 1987, 28 p. aerodynamics for such vehicles as the Hermes/Ariane 5 are Research supported by the Service Technique des Programmes discussed. Typical flight regimes for reentry of spacecraft and Aeronautiques. refs transport aircraft are compared. The physical and mechanical (ONERA, TP NO. 1987-58) effects during the reentry on space transport vehicles, and the A time-consistent prediction of buffeting over airfoils is need to stabilize the heat balance and limit the heating of the performed here for viscous-inviscid interaction using the semiimplicit structure are studied. The solution of complete flow equations in numerical coupling technique where coupling is converged hypersonic aerodynamic evaluation is considered. An example iteraUvely at each time step, permitting the treatment of unsteady displaying the evaluation of a two-dimensional flow around a separation. Viscous marching calculations are used to solve integral deflected flap at hypersonic speed is presented. The flow around defect equations in a direct mode for attached flows and an inverse the Hermes configuration is also examined. I.F. mode for separated flows. As an example, the method is applied to study two-dimensional buffeting flows numerically in the case A87-46351 # of the RA16SC1 airfoil at lifting conditions. C.D. CHANGES IN THE FREE FLOW IN THE INTAKE OF A ENGINE DURING THE AIRCRAFT TAKEOFF RUN [PRZEMIANA SWOBODNEGO PRZEPLYWU WLOTOWEGO A87-46761 # SILNIKA ODRZUTOWEGO PODCZAS ROZBIEGU SAMOLOTU] STUDY OF THE AERODYNAMICS OF HIGH-SPEED TADEUSZ GAJEWSKI (Wyzsza Oficerska Szkola Lotnicza, Deblin, PROPELLERS [ETUDE DE L'AEROOYNAMIQUE DES HELICES Poland) Technika Lotnicza i Astronautyczna (ISSN 0040-1145), POUR AVIONS RAPIDES] vol. 42, Jan. 1987, p. 3-5, 10. In Polish. refs J. M. BOUSQUET (ONERA, Chatillon-sous-Bagneux, France) (NATO, AGARD, Symposium on Technology for Advanced Aero A87-46363 Engine Components, Paris, France, May 4-8, 1987) ONERA, TP, VALIDATION OF AERODYNAMIC MEASUREMENT TECH- no. 1987-61, 1987, 13 p. In French. NIQUES AND CALCULATION METHODS FOR HIGH-LIFT SYS- (ONERA, TP NO. 1987-61) TEMS [ELEMENTS DE VALIDATION DES TECHNIQUES DE ME- Calculation methods used in the development of the HT3 SURE ET DES METHODES DE CALCUL EN AERODYNAMIQUE propeller are discussed, and comparison with experimental DES SYSTEMES HYPERSUSTENTES] measurements shows the validity of the methods for the P. CAPBERN (Aerospatiale, Division Avions, Toulouse, France) aerodynamic analysis of simple-rotation high-speed propellers. L'Aeronautique et rAstronautique (ISSN 0001-9275), no. 122, 1987, Good agreement is found between results for the HT3 propeller p. 26-34. In French. refs obtained in the $1 Modane wind tunnel and those obtained using Problems in the prediction of the coefficients of maximum lift the LPC program global method. Comparison with experimental and drag for high-lift aircraft are discussed for the cases of single pressure measurements shows the development of the transonic slotted or double slotted flap systems. Following a treatment of flow on the propeller blades to be well modeled by the the purely two-dimensional problem, the subsonic problem, where three-dimensional Euler program. The present analysis is applied compressibility is negligible, is considered. Experimental drag to the case of counterrotating coaxial propellers, and the measurements, obtained by wake sounding with the Sl0 wind performance benefits of these propellers in comparison with single tunnel, are compared with theoretical calculations obtained using rotating propellers are considered. R.R.

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A87-46776# A87-46951 # NUMERICALSIMULATIONOFFLOWSINAXIALANDRADIAL A PANEL METHOD FOR PREDICITING THE DYNAMIC TURBOMACHINESUSINGEULERSOLVERS STABILITY DERIVATIVES OF AN OSCILLATING WING IN HIGH GEORGES MEAUZE and ANTOINE FOURMAUX (ONERA, SUBSONIC FLOW Chatillon-sous-Bagneux, France) (Institut von Karman de LIXIAN ZHUANG and BINGGANG TONG (University of Science Dynamique des Fluides, Cours, Rhode-Saint-Genese, Belgium, and Technology of China, Hefei, People's Republic of China) June 15-18, 1987) ONERA, TP, no. 1987-87, 1987, 57 p. refs 01Acta Aerodynamica Sinica (ISSN 0258-1825), vol. 5, June 1987, (ONERA, TP NO. 1987-87) p. 97-102. In Chinese, with abstract in English. refs State of the art numerical methods for transonic flow simulation In this paper, the pitching and rolling damping derivatives of in turbomachines, in particular high-pressure-ratio turbines, using several different shape wings in high subsonic flow are calculated Euler solvers, are presented. Phenomena related to supersonic by using the so-called 'Locally Linearization-Transonic-Panel- flows in turbomachines are described using one- or two-dimensional Method' developed in an earlier paper. The calculated results are analysis. Euler equations are considered, and the treatment of compared to the experimental data available and prove to be in the main boundary conditions in internal aerodynamics is good agreement with each other. The results of the present method addressed. The multidomain approach to treat complex problems are also compared to those of the purely linearized method, indicat- in computational fluid dyanmics is examined, as is the discretization ing that the nonlinear effect is not negligible in general for predicting of the three-dimensional Euler equations by means of an explicit the dynamic derivatives when the critical Mach number is ap- predictor-corrector scheme very similar to McCormack's scheme. proached. In this calculation, the necessary steady flow solutions Grid generation is discussed, and application examples are are obtained from the authors' 'lterative-PaneI-Method' which was considered, including steady flow numerical applications, developed for predicting the steady pressure distribution on the inverse-mode two-dimensional applications, viscous effects wing surface in transonicsubsonic flow. The present method proved simulation, and unsteady flows. C.D. to be very cost-effective. Author

A87-46777# A87-46956# ENTRAINMENT EFFECT OF A LEAOING-EDGE VORTEX AN EXPERIMENTAL INVESTIGATION OF DELTA WINGS WITH N. G. VERHAAGEN and A. C. H. KRUISBRINK (Delft, Technische LEADING-EDGE VORTEX SEPARATION Hogeschool, Netherlands) AIAA Journal (ISSN 0001-1452), vol. JINGBAI LI and MENGBU Ol (Nanjing Aeronautical Institute, 25, Aug. 1987, p. 1025-1032. Previously cited in issue 19, p. 2738, People's Republic of China) Acta Aerodynamica Sinica (ISSN Accession no. A85-40703. refs 0258-1825), vol. 5, June 1987, p. 141-147. In Chinese, with abstract in English. refs Low speed wind-tunnel tests have been carried out for five A87-46778"# Notre Dame Univ., Ind. delta wings with leading-edge vortex separation. The effects of LAMINAR SEPARATION BUBBLE CHARACTERISTICS ON AN variations in leading-edge sweptback angle on vortex core AIRFOIL AT LOW REYNOLDS NUMBERS trajectory, vortex burst point, vortex core circulation, and relative M. M. O'MEARA and T. J. MUELLER (Notre Dame, University, sink strength have been investigated using a seven-hole probe up IN) AIAA Journal (ISSN 0001-1452), vol. 25, Aug. 1987, p. to high angles of attack. The experimental results of the present 1033-1041. Research supported by the University of Notre Dame. paper have been compared with that of Mokry and Ohman (1980) Previously cited in issue 17, p. 2467, Accession no. A86-38433. by means of other measuring methods and showed fair agreement. refs Therefore, the seven-hole probe is a new, simple, convenient and (Contract NSG-1419) accurate measuring tool for flow studies of separated vortices. Author

A87-46779# A87-46962# CONTROL OF THE DISCRETE VORTICES FROM A DELTA FAST METHODS APPLIED TO THE CALCULATION OF WING TRANSONIC AIRFOILS MOHAMED GAD-EL-HAK (Notre Dame University, IN) and RON ZHENHUA XIAO and ZHONGYIN ZHANG (Northwestern F. BLACKWELDER (Southern California, University, Los Angeles, CA) AIAA Journal (ISSN 0001-1452), vol. 25, Aug. 1987, p. Polytechnical University, Xian, People's Republic of China) Acata Aerodynamica Sinica (ISSN 0258-1825), vol. 5, June 1987, p. 1042-1049. Previously cited in issue 22, p. 3219, Accession no. A86-45411. refs 193-196. In Chinese, with abstract in English. refs First, Bauer-Garabedian-Korn-Jameson's fast direct-solver/ (Contract F49620-85-C-0131) SLOR method and Hoist's implicit approximate factorization al- gorithm (AF2) are described. Next, the subsonic and supercritical A87-46922 flows around the airfoil NACA 0012 are calculated using these two COMPRESSIBLE FLOWS IN THE WAKES OF A SQUARE methods. Then, their convergent rates are compared. The result CYLINDER AND THICK SYMMETRICAL AIRFOIL ARRANGED shows that the convergent rate of BGKJ's method is faster than IN TANDEM AF2's. Author T. NAKAGAWA, G. E. A. MEIER, R. TIMM, and H.-M. LENT (Max-Planck-lnstitut fuer Stroemungsforschung, Goettingen, West A87-47014# Germany) Royal Society (London), Proceedings, Series A - AERODYNAMIC STUDY OF A HELICOPTER ROTOR IN Mathematical and Physical Sciences (ISSN 0080-4630), vol. 411, HOVERING FLIGHT - THEORY VS. EXPERIMENT no. 1841, June 8, 1987, p. 379-394. refs D. FAVIER, M. NSI MBA (Aix-Marseille II, Universite, Marseille, The two-dimensional compressible flow in the wake of a France), and A. VUILLET (Aerospatiale, Division Helicopteres, 20-mm-side square cylinder mounted 22.5-110 mm upstream of a Marignane, France) La Recherche Aerospatiale (English Edition) 20-mm-chord-length NACA 0018 airfoil at freestream Mach (ISSN 0379-380X), no. 1, 1987, p. 53-69. refs numbers M = 0.15-0.91 and Re = 70,000-420,000 is investigated (Contract DRET-82-432; DRET-84-009) experimentally using the setup and flow-visualization techniques The present work aims to check the range of validity of two described by Nakagawa (1986). The results are presented in aerodynamic rotor calculation models by direct comparison with extensive graphs and photographs and characterized in detail. The experiments performed in the hovering case. This hovering effects of the spacing between the cylinder and the airfoil at M configuration is a first and challenging step in code validation less than 0.63 are found to differ significantly from those in before considering models predicting more complex configurations higher-velocity flows, especially when local flow regions become in the forward flight case. The first model applies the classical supersonic (at M = 0.7 or higher). T.K. momentum theory to the rotating disk and the downstream wake.

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The second is a vortex theory application based on a lifting line N87-25297 Colorado Univ., Boulder. free wake analysis. In this second method, a new procedure for EXPERIMENTAL STUDIES ON THE DYNAMIC DEVELOPMENT free wake analysis (based on an initial prescribed blade circulation) AND CONTROL OF UNSTEADY SEPARATED FLOWS Ph.D. is proposed for the rotor performance prediction. To check the Thesis validity of these codes over a wide range, the calculation is HENRY ELMER HELIN 1986 196 p compared with experiment at different levels: rotor performance, Avail: Univ. Microfilms Order No. DA8706426 bounded circulation on the blade, tip vortex paths, induced velocity Current research in unsteady aerodynamics revolves around field, influence of the evolution blade tip geometry. These various the concept of enhancing aerodynamic performance through the comparisons provide a broad check of the code efficiency in energetic nature of vorticity dominated flowfields. It appears clear predicting overall and local aerodynamic quantities typical of the that substantial lift enhancement and stall delay are some of the hovering rotor cconfiguration. Author beneficial consequences of certain unsteady aerodynamic conditions. However, the work in unsteady aerodynamics remains in its infancy and we cannot fully predict what the area may yield in useful consequences: but the possibilities appear promising. N87-25294"# National Aeronautics and Space Administration. Before any useful scheme can be implemented a thorough Lewis Research Center, Cleveland, Ohio. understanding of the generation and control of unsteady WIND TUNNEL PERFORMANCE RESULTS OF AN phenomena must be obtained. Energetic vorticity dominated flows AEROELASTICALLY SCALED 2/9 MODEL OF THE PTA FLIGHT elicited through forced unsteady flow separation about a pitching TEST PROP-FAN airfoil were examined for a wide range of test conditions, including GEORGE L. STEFKO, GAYLE E. ROSE, and GARY G. PODBOY control oriented motion histories and model geometries. Phase Jul. 1987 50 p Presented at the 23rd Joint Propulsion Conference, locked high speed 16ram photography coupled with near-surface San Diego, Calif., 29 Jun. - 2 Jul. 1987; cosponsored by AIAA, hot-wire anemometry and multi-port surface pressure SAE, ASME, and ASEE Prepared in cooperation with Sverdrup measurements were used to quantify flowfield dynamics and the Technology, Inc., Cleveland, Ohio ensuing aerodynamic loading. The motion history employed as (NASA-TM-89917; E-3610; NAS 1.15:89917; AIAA-87-1893) well as the model geometry had significant influences on the Avail: NTIS HC A03/MF A01 CSCL 01A generation, coalescence, and convection of the vortical High speed wind tunnel aerodynamic performance tests of the structures. Dissert. Abstr. SR-7A advanced prop-fan have been completed in support of the Prop-Fan Test Assessment (PTA) flight test program. The test showed that the SR-7A model performed aerodynamically very well. At the cruise design condition, the SR-7A prop fan had a high measured net efficiency of 79.3 percent. R.J.F.

N87-25298# Aeronautical Research Inst. of Sweden, Stockholm. Aerodynamics Dept. THE AERONAUTICAL RESEARCH INSTITUE (FFA) WING BODY N87-25295"# National Aeronautics and Space Administration. 85 COMPUTER PROGRAM. A PANEL METHOD FOR Langley Research Center, Hampton, Va. DETERMINATION OF AEROELASTIC CHARACTERISTICS SUBSONIC WIND-TUNNEL MEASUREMENTS OF A SLENDER APPLYING DIRECT BLOCK ITERATIVE SOLUTION WING-BODY CONFIGURATION EMPLOYING A VORTEX FLAP TECHNIQUES NEAL T. FRINK Jul. 1987 313 p PER KRANTZ Apr. 1986 15 p (NASA-TM-89101; L-16265; NAS 1.15:89101) Avail: NTIS HC (Contract FMV-F-K-82260-84260) A14/MF A01 CSCL01A (FFA-TN-1986-28; ETN-87-99780) Avail: NTIS HC A02/MF A01 A wind tunnel study at Mach 0.4 was conducted for a slender A panel program for calculations of aerodynamic characteristics wing-body configuration with a leading edge vortex flap of curved of configurations with rigid or elastic wings was modified to handle planform that is deflectable about a 74 degree swept hinge line. a larger number of panels within a reasonable amount of computing The basic data consist of a unique combination of longitudinal time. A solution method for the equation systems is introduced aerodynamic, surface pressure, and vortex flap hinge-moment and the number of operations required for solution is compared measurements on a common model. The longitudinal aerodynamic, with the number needed for the old method. ESA pressure and hinge-moment data are presented without analysis in tabular format. Plots of the tabulated pressure data are also given. Author

N87-25296"# National Aeronautics and Space Administration. N87-25299# Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn Ames Research Center, Moffett Field, Calif. (West Germany). PERFORMANCE AND LOADS DATA FROM A HOVER TEST APPLICATION OF A THREE-DIMENSIONAL EULER CODE TO OF A 0.658-SCALE V-22 ROTOR AND WING TRANSONIC BLADE TIP FLOW FORT F. FELKER, DAVID B. SIGNOR, LARRY A. YOUNG, and HEIDEMARIE STAHL Sep. 1986 21 p Presented at the MARK D. BETZINA Apr. 1987 468 p Twelfth European Rotorcraft Forum, Garmisch-Partenkirchen, West (NASA-TM-89419; A-87058; NAS 1.15:89419) Avail: NTIS HC Germany, 22-25 Sep. 1986 Sponsored by DGLR, Bonn, West A20/MF A01 CSCL 01A Germany A hover test of a 0,658-scale model of a V-22 rotor and wing (MBB-UD-482/86; ETN-87-99927) Avail: Issuing Activity was conducted at the Outdoor Aerodynamic Research Facility at A three dimensional steady flow code for flows around fixed Ames Research Center. The primary objectives of the test were wings was modified for rotor flow. A method of step by step to obtain accurate measurements of the hover performance of mesh refinement starting from the coarsest grid reduces the the rotor system, and to measure the aerodynamic interactions computation time usually associated with Euler codes, without between the rotor and wing. Data were acquired for rotor tip Mach reducing accuracy. A strong dependency between grid resolution numbers ranging from 0.1 to 0.73. This report presents data on and resolution of aerodynamic coefficients is shown. The grid must rotor performance, rotor-wake downwash velocities, rotor system be large enough so that its outer boundaries can be considered loads, wing forces and moments, and wing surface pressures. to be in the undisturbed flow, so that far field conditions apply. Author ESA

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.N87-25300# Spectron Development Labs., Inc., Costa Mesa, vibration level from the rotor hub to the pilot's seat. The TRIS Calif. installation was designed with a decoupled control system and TOMOGRAPHIC RECONSTRUCTION OF THREE-DIMENSIONAL has shown a significant improvement in aircraft flying qualities, FLOW OVER AIRFOILS Final Report, 15 Mar. 1983 - 14 Nov. such that it permitted the trimmed aircraft to be flown hands-off 1986 for a significant period of time, over 90 seconds. The TRIS flight DARIUSH MODARRESS, HUNG TAN, and JAMES D. test program has demonstrated a system that greatly reduces TROLINGER 18 Mar. 1987 31 p vibration levels of a current-generation helicopter, while significantly (Contract DAAG29-83-C-0012) improving the flying qualities to a point where stability augmentation (AD-A179976; SDL-87-2284-13F; ARO-19471.4-EG) Avail: NTIS is no longer a requirement. Author HC A03/MF A01 CSCL 20D Application of holographic tomography to the flow around the tip of a revolving airfoil is investigated. Data in the form of interferograms obtained at forty different angles obtained by AVRADCOM at NASA Ames were used to reconstruct the three-dimensional density field. An automated fringe analysis capability was developed to digitize, filter and repair the fringe patterns. The binary images of the interferograms were used as the input data to the reconstruction code. A new ART code based N87-25304"# National Aeronautics and Space Administration. on the iterative refinement method of least squares solution was Langley Research Center, Hampton, Va. developed for tomographic reconstruction. Solutions were obtained EFFECT OF PLANFORM TAPER ON HOVER PERFORMANCE for the density and velocity field at various heights above the OF AN ADVANCED AH-64 MODEL ROTOR blade. An important feature of the technique was found to be that HENRY L. KELLEY Aug. 1987 13 p Prepared in cooperation with limited resolution (say 20 x 20), it was possible to repeatedly with Army Aviation Research and Development Command, use the same code and zoom into regions surrounding important Hampton, Va. features of the flow and, hence, reconstruct the flow field in greater (Contract DA PROJ. 1L1-61102-AH-45A) detail. This feature was used and the position of the shock wave (NASA-TM-89145; L-16267; NAS 1.15:89145; over the wing was determined. Author (GRA) AVSCOM-TM-87-B-10) Avail: NTIS HC A02/MF A01 CSCL 01A The hover performance of a 27 percent scale model baseline N87-25301"# National Aeronautics and Space Administration. rotor and advanced rotor with a 3:1 tapered tip (TR3) for the Langley Research Center, Hampton, Va. STUDY OF LEE-SIDE FLOWS OVER CONICALLY CAMBERED AH-64 attack helicopter was investigated and compared. Hover results from a previously tested advanced rotor with a 5:1 tapered DELTA WINGS AT SUPERSONIC SPEEDS, PART 2 RICHARD M. WOOD and CAROLYN B. WATSON Jul. 1987 tip (TR5) were also compared. Rotor thrust was varied over a range for two tip Mach numbers. The results indicated that the 404 p TR3 blades had improved performance compared with the TR5 (NASA-TP-2660-PT-2; L-16192; NAS 1.60:2660-PT-2) Avail: NTIS HC A18/MF A01 CSCL 01A blades, and both the TR3 and TR5 blades were superior to the baseline rotor. The additional margin in performance for the TR3 An experimental investigation was performed in which surface blades was likely due to an increase in blade area and Reynolds pressure data, flow visualization data, and force and moment data number in the tip region of the blades. Author were obtained on four conical delta wing models which differed in leading edge camber only. Wing leading edge camber was achieved through a deflection of the outboard 30% of the local wing semispan of a reference 75 deg swept flat delta wing. The four wing models have leading edge deflection angles delta sub F of 0, 5, 10, and 15 deg measured streamwise. Data for the wings with delta sub F = 10 and 15 deg showed that hinge line separation dominated the lee-side wing loading and prohibited the development of leading edge separation on the deflected portion N87-25305"# National Aeronautics and Space Administration. of wing leading edge. However, data for the wing with delta sub Ames Research Center, Moffett Field, Calif. F = 5 deg showed that at an angle of attack of 5 deg, a vortex ON THE NONLINEAR AERODYNAMIC AND STABILITY was positioned on the deflected leading edge with reattachment CHARACTERISTICS OF A GENERIC CHINE-FOREBODY at the hinge line. Flow visualization results were presented which SLENDER-WING FIGHTER CONFIGURATION detail the influence of Mach number, angle of attack, and camber GARY E. ERICKSON and JAY M. BRANDON Jun. 1987 38 p on the lee-side flow characteristics of conically cambered delta Prepared in cooperation with NASA- Langley Research Center, wings. Analysis of photographic data identified the existence of Hampton, Va. 12 distinctive lee-side flow types. Author (NASA-TM-89447; A-87174; NAS 1.15:89447) Avail: NTIS HC A03/MF A01 CSCL 01A N87-25302"# Textron Bell Helicopter, Fort Worth, Tex. An exploratory investigation was conducted of the nonlinear GROUND AND FLIGHT TEST RESULTS OF A TOTAL MAIN aerodynamic and stability characteristics of a tailless generic fighter ROTOR ISOLATION SYSTEM Final Report configuration featuring a chine-shaped forebody coupled to a DENNIS R. HALWES Washington NASA Jul. 1987 153 p slender cropped delta wing in the NASA Langley Research Center's Sponsored by Army Aerostructures Directorate 12-Foot Low-Speed Wind Tunnel. Forebody and wing vortex flow (Contract NAS1-16969) mechanisms were identified through off-body flow visualizations to (NASA-CR-4082; NAS 1.26:4082; REPT-699-099-055) Avail: explain the trends in the longitudinal and lateral-directional NTIS HC AO8/MF A01 CSCL 01B characteristics at extreme attitudes (angles of attack and sideslip). A six degree-of-freedom (DOF) isolation system using six LIVE The interactions of the vortical motions with centerline and units has been installed under an Army/NASA contract on a Bell wing-mounted vertical tail surfaces were studied and the flow 206LM helicopter. This system has been named the Total Rotor phenomena were correlated with the configuration forces and Isolation System, or TRIS. To determine the effectiveness of TRIS moments. Single degree of freedom, free-to-roll tests were used in reducing helicopter vibration, a flight verification study was to study the wing rock susceptibility of the generic fighter model. conducted at Bell's Flight Research Center in Arlington, Texas. Modifications to the nose region of the chine forebody were The flight test data indicate that the 4/rev vibration level at the examined and fluid mechanisms were established to account for pilot's seat were suppressed below the 0.04g level throughout the their ineffectiveness in modulating the highly interactive forebody transition envelope. Flight tests indicate over 95% suppression of and wing vortex systems. Author

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N87-25306"#NationalAeronauticsandSpace Administration, pressure, mean velocity, flow angularity, and vorticity distribution Washington, D.C. data at five chordwise stations of the near-wake ranging from RECENT PROGRESS IN THE MEASUREMENT OF THE DRAG 0.167 to 5.00 chord lengths aft of the trailing edge. The COEFFICIENTS OF MODELS OF TRANSPORT AIRCRAFT IN A experimental results were compared to the predicted results of a WIND TUNNEL 2-D Euler numerical method. The results predicted by an Euler C. ARMAND, P. HUGOUVIEUX, and R. SELVAGINNI Aug. 1987 method failed to accurately define the flowfield. Tangential 57 p Transl. into ENGLISH of conference paper Progres Recents velocities remained relatively constant over the range of X/C dans la Mesure en Soufflerie du Coefficient de Trainee de considered though increased in angle of attack and Reynolds Maquettes d'Avion de Transport presented at the 23rd Symposium number did bring about corresponding increases. Axial velocities of Applied Aerodynamics, 1980 p 1-47 Symposium held in Aussois, also increased with angle of attack and Reynolds number but France, 12-14 Nov. 1986 Original language document was showed greater sensitivity to increases in X/C. Graphic displays announced in IAA as A87-21070 Transl. by Kanner (Leo) and contours of the total pressure data indicate that roll-up of the Associates, Redwood City, Calif. wing tip vortex is essentially complete one and one half chords (Contract NASW-4005) downstream of the trailing edge. Author (NASA-TT-20096; NAS 1.77:20096; ONERA-TP-1986-170) Avail: NTIS HC A04/MF A01 CSCL 01A Techniques and apparatus employed by ONERA researchers at Mondane to obtain an accuracy of 0.0001 in drag measurements on scale models of transport aircraft are described. Emphasis is placed on cruise flight configurations for the Airbus, and on the computational methods applied to correct the data for scale models N87-25997"# Massachusetts Inst. of Tech., Cambridge. to account for wind tunnel effects, as opposed to aircraft in actual Aeronautical Systems Lab. flight. Model design, the mounts used, calibration of the balances AN EXPERIMENTAL LOW REYNOLDS NUMBER COMPARISON and the angle of attack, and the data acquisition and treatment OF A WORTMANN FX67-K170 AIRFOIL, A NACA 0012 AIRFOIL systems are summarized. Methods used to offset the thermal AND A NACA 64-210 AIRFOIL IN SIMULATED HEAVY RAIN friction, wall and support effects on the flowfield are discussed. Final Report Author ANTHONY P. CRAIG and R. JOHN HANSMAN Jun. 1987 106 p (Contract NAG1-568) N87-25307"# National Aeronautics and Space Administration, (NASA-CR-181119; NAS 1.26:181119; ASL-87-1) Avail: NTIS Washington, D.C. HC A06/MF A01 CSCL 01A THE INTERFERENCE OF THE MODEL SUPPORT MAST WITH Wind tunnel experiments were conducted on Wortmann MEASUREMENTS OF THE LONGITUDINAL AND LATERAL FX67-K170, NACA 0012, and NACA 64-210 airfoils at rain rates AERODYNAMIC COEFFICIENTS of 1000 mm/hr and Reynolds numbers of 310,000 to compare C. VANDEKREEKE, J. VERRIERE, and G. QUEMARD Aug. the aerodynamic performance degradation of the airfoils and to 1987 32 p Transl. into ENGLISH of conference paper Interaction attempt to identify the various mechanisms which affect d'un Mat Support de Maquette sur les Mesures des Coefficients performance in heavy rain conditions. Lift and drag were measured Aerodynamiques Longitudinaux presented at the 23rd Colloque in dry and wet conditions, a variety of flow visualization techniques d'Aerodynamique Appliquee, 1986 28 p Colloquium held in were employed, and a computational code which predicted airfoil Aussois, France, 12-14 Nov. 1986 Original language document boundary layer behavior was used. At low angles of attack, the was announced in IAA as A87-21080 Transl. by Kanner (Leo) lift degradation in wet conditions varied significantly between the Associates, Redwood City, Calif. airfoils. The Wortmann section had the greatest overall lift (Contract NASW-4005) degradation and the NACA 64-210 airfoil had the smallest. At (NASA-TT-20079; NAS 1.77:20079; ONERA-TP-1986-181) Avail: high angles of attack, the NACA 64-210 and 0012 airfoils had NTIS HC A03/MF A01 CSCL 01A improved aerodynamic performance in rain conditions due to an The effects the single-bottom support masts used in the ONERA apparent reduction of the boundry layer separation. Performance $1 and $4 wind tunnels have on aerodynamic data collected with degradation in heavy rain for all three airfoils at low angles of scale were examined experimentally and analytically. attack could be emulated by forced boundary layer transition near Systematic studies were performed on the flow characteristics the leading edge. The secondary effect occurs at time scales around different diameters for the mounts. Scaling methods used consistent with top surface water runback times. The runback layer to make data from one wind tunnel correspond to data from the is thought to effectively alter the airfoil geometry. The severity of other are described. Airbus 320 models were introduced into the the performance degradation for the airfoils varied. The relative tests and mast-body flow interactions were observed. A summary differences appeared to be related to the susceptibility of each is presented of restrictions on the mast diameters, relative to airfoil to premature boundary layer transition. Author cylindrical model diameters, which will minimize the effects the masts have on longitudinal and lateral aerodynamic stability data. Author

N87-25993"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. DETAILED NEAR-WAKE FLOWFIELD SURVEYS WITH COMPARISON TO AN EULER METHOD OF AN ASPECT RATIO N87-26005"# Lockheed-California Co., Burbank. 4 RECTANGULAR WING CFD APPLICATIONS: THE LOCKHEED PERSPECTIVE M. D. KLINGE, S. O. KJELGAARD, and J. N. PERKINS (North LUIS R. MIRANDA In NASA. Ames Research Center, Carolina State Univ., Raleigh.) 1986 29 p Supercomputing in Aerospace p 77-85 Mar. 1987 (NASAoTM-89357; NAS 1.15:89357) Avail: NTIS HC A01/MF Avail: NTIS HC A13/MF A01 CSCL 01A A01 CSCL 01A The Numerical Aerodynamic Simulator (NAS) epitomizes the An experimental investigation of the flowfield in the near-wake coming of age of supercomputing and opens exciting horizons in of an aspect ratio 4 rectangular wing was conducted, providing a the world of numerical simulation. An overview of supercomputing complete detailed set of data for use in the validation of at Lockheed Corporation in the area of Computational Fluid computational methods. An angle of attack of 8 degrees and two Dynamics (CFD) is presented. This overview will focus on Reynolds numbers 530,000 and 391,000 were investigated using developments and applications of CFD as an aircraft design tool pitot and six-hole probes. In addition, two types of flow visualization and will attempt to present an assessment, withing this context, were employed. The data presented includes contours of total of the state-of-the-art in CFD methodology. B.G.

644 02 AERODYNAMICS

N87-26019"#NationalAeronauticsandSpaceAdministration. trajectory in the near wake, in addition to supplying information LangleyResearchCenter,Hampton,Va. necessary to construct a grid for measurement of the three COMPUTATIONALANALYSISOFHYPERSONICAIRBREA- components of velocity in the vortex core. Dissert. Abstr. THINGAIRCRAFTFLOWFIELDS DOUGLAS L. DWOYER and AJAY KUMAR In NASA. Ames N87-26031"# National Aeronautics and Space Administration. Research Center, Supercomputing in Aerocomputing p 239-255 Langley Research Center, Hampton, Va. Mar. 1987 Previously announced in IAA as A87-22531 EFFECT OF REYNOLDS NUMBER VARIATION ON Avail: NTIS HC A13/MF A01 CSCL 01A AERODYNAMICS OF A HYDROGEN-FUELED TRANSPORT The general problem of calculating the flow fields associated CONCEPT AT MACH 6 with hypersonic airbreathing aircraft is presented. Unique aspects JIM A. PENLAND and DON C. MARCUM, JR. Aug. 1987 28 p of hypersonic aircraft aerodynamics are introduced and their (NASA-TP-2728; L-16286; NAS 1.60:2728) Avail: NTIS HC demands on computational fluid dynamics are outlined. Example A03/MF A01 CSCL 01A calculations associated with inlet/forebody integration and Two separate tests have been made on the same blended hypersonic nozzle design are presented to illustrate the nature of wing-body hydrogen-fueled transport model at a Mach number of the problems considered. Author about 6 and a range of Reynolds number (based on theoretical body length) of 1.577 to 55.36 X 10 to the 6th power. The results N87-26027# Royal Aircraft Establishment, Farnborough of these tests, made in a conventional hypersonic blowdown tunnel (England). and a hypersonic shock tunnel, are presented through a range of AERODYNAMICS OF UNMANNED AIRCRAFT AT FULL-SCALE angle of attack from -1 to 8 deg, with an extended study at a IN THE RAE 24FT WIND-TUNNEL constant angle of attack of 3 deg. The model boundary layer flow W.J.G. TREBBLE Ju1.1986 32p appeared to be predominately turbulent except for the low Reynolds (RAE-TM-AERO-2081; BR100296; ETN-87-90092) Avail: NTIS number shock tunnel tests. Model wall temperatures varied HC A03/MF A01 considerably; the blowdown tunnel varied from about 255 F to Wind tunnel tests were made on full-scale models of the X-RAE 340 F, whereas the shock tunnel had a constant 70 F model wall 1 and X-RAE 2 unmanned aircraft (UMA) over a Reynolds number temperature. The experimental normal-force coefficients were range from 500,000 to 1.2 million. The results show that substantial essentially independent of Reynolds number. A current theoretical increases in lifting capability could be achieved by choosing a computer program was used to study the effect of Reynolds wing section (Wortmann FX63-137) more appropriate to the range number. Theoretical predictions of normal-force coefficients were of Reynolds number associated with the required airspeed range good, particularly at anticipated cruise angles of attack, that is 2 from 20 to 50 m/sec. The UMA stalls from the root trailing-edge to 5 deg. Axial-force coefficients were generally underestimated so the 1 deg washout provided appears to be unnecessary. The for the turbulent skin friction conditions, and pitching-moment UMAs have adequate stability margins and both have powerful coefficients could not be predicted reliably. Author nose-down moments at the stall. Lift/drag ratio increases as the Reynolds number is raised. ESA N87-26032"# National Aeronautics and Space Administration. N87-26028 ESDU International Ltd., London (England). Langley Research Center, Hampton, Va. AEROFOIL MAXIMUM LIFT-COEFFICIENT FOR MACH STEADY AND UNSTEADY AERODYNAMIC FORCES FROM THE NUMBERS UP TO 0.4 SOUSSA SURFACE-PANEL METHOD FOR A FIGHTER WING Nov. 1984 16 p Supersedes ESDU-Aero-W.01.01.06 WITH TIP MISSILE AND COMPARISON WITH EXPERIMENT (ESDU-84026; ESDU-AERO-W.01.01.06; ISBN-0-85679-490-2; AND PANAIR ISSN-0141-397X) Avail: ESDU HERBERT J. CUNNINGHAM Aug. 1987 29 p ESDU 84026 provides a simple empirically derived method for (NASA-TP-2736; L-16262; NAS 1.60:2736) Avail: NTIS HC A03/MF A01 CSCL 01A estimating maximum lift coefficient. The method predicts the increment in lift coefficient by which the maximum exceeds the The body surface-panel method SOUSSA is applied to calculate value at zero incidence, and a prediction method for lift coefficient steady and unsteady lift and pitching moment coefficients on a at zero incidence is included. Graphs of the increment show its thin fighter-type wing model with and without a tip-mounted missile. variation with airfoil geometry and Reynolds nymber for airfoils Comparisons are presented with experimental results and with PANAIR and PANAIR-related calculations for Mach numbers from with smooth or rough leading edges; rough here would cover ice formation while smooth includes the level of roughness required 0.6 to 0.9. in general the SOUSSA program, the experiments, and just to fix transition. A further empirical factor is provided to extend the PANAIR (and related) programs give lift and pitching-moment the method to apply to modern airfoils with rear loading. The results which agree at least fairly well, except for the unsteady accuracy is assessed in terms of standard deviation of prediction clean-wing experimental moment and the unsteady moment on from experiment for nearly 500 points, subdivided by airfoil type, the wing tip body calculated by a PANAIR-predecessor program at a Mach number of 0.8. Author leading-edge condition and Reynolds number. The overall standard deviation was about 0.08. ESDU N87-26033"# National Aeronautics and Space Administration. N87-26030 Georgia Inst. of Tech., Atlanta. Langley Research Center, Hampton, Va. VELOCITY MEASUREMENTS NEAR THE BLADE TIP AND IN LOW-SPEED WIND-TUNNEL RESULTS FOR SYMMETRICAL THE TIP VORTEX CORE OF A HOVERING MODEL ROTOR NASA LS(1)-0013 AIRFOIL Ph.D. Thesis JAMES C. FERRIS, ROBERT J. MCGHEE, and RICHARD W. THOMAS LEE THOMPSON 1986 156 p BARNWELL Aug. 1987 38 p Avail: Univ. Microfilms Order No. DA8707864 (NASA-TM-4003; L-16279; NAS 1.15:4003) Avail: NTIS HC Detailed measurements with a laser Doppler velocimeter were A03/MF A01 CSCL 01A performed in the tip region and in the tip vortex core of a single A wind-tunnel test has been conducted in the Langley bladed model rotor, The rotor blade is untwisted and of constant Low-Turbulence Pressure Tunnel to evaluate the performance of chord with a NACA 0012 airfoil section and a square tip. The a symmetrical NASA LS(1)-0013 airfoil which is a 13-percent-thick, data from measurements near the blade tip were used to determine low-speed airfoil. The airfoil contour was obtained from the the tip vortex inception point and to study the subsequent growth thickness distribution of a 13-percent-thick, high-performance airfoil of vortex during its passage over the upper surface of the blade. developed for general aviation airplanes. The tests were conducted Velocity measurements at locations unaffected by a tip vortex at Mach numbers from 0.10 tp 0.37 over a Reynolds number passage were generally in good agreement with predictions from range from about 0.6 to 12.0 X 10 to the 6th power. The angle of a hovering rotor lifting surface code developed at Georgia Tech. attack varied from about -8 to 20 degrees. The results indicate A flow visualization study verified the steadiness of the tip vortex that the aerodynamic characteristics of the present airfoil are similar

645 03 AIRTRANSPORTATIONANDSAFETY to, but slightly better than, those of the NACA 0012 airfoil. accretion of ice on rotor blades for both the hover and forward Author flight cases. Theoretical results are compared with b6th icing wind tunnel and flight ice accretion measurements. Also described are both one- and two-dimensional models of an electrothermally 03 deiced rotor, and results are shown to illustrate their capabilities. The planned future application of these models in both design and certification of helicopters for flight in icing is described. AIR TRANSPORTATION AND SAFETY Author

A87-44707 Includes passenger and cargo air transport operations; and aircraft accidents. ICING CLEARANCES ON CIVIL HELICOPTERS - UNHEATED AND HEATED BLADES D. W. BLACKALL (Civil Aviation Authority, London, England) IN: A87-44701 Helicopter Rotor Icing Symposium, London, England, Jan. 14, 1986, HELICOPTER ROTOR ICING SYMPOSIUM, LONDON, ENGLAND, Proceedings . London, Royal Aeronautical Society, 1986, p. 98-103. JAN. 14, 1986, PROCEEDINGS Symposium sponsored by the Royal Aeronautical Society. London, The need for ice flying capabilities for civil helicopters is Royal Aeronautical Society, 1986, 111 p. For individual items see discussed. Commercial and technical problems of establishing icing A87-44702 to A87-44707. clearances for civil helicopters are studied. Examples of flight trials Papers are presented on when and where helicopter icing conductgd in order to gain icing clearance for certain aircraft are occurs, and the development of the Chinook helicopter fiberglass presented. I.F. rotor blade deicing system. Attention is given to icing clearance A87-44748 criteria for UK military helicopters, rotor icing research, and icing clearances on civil helicopters. I.F. FIRE, SMOKE, TOXICITY T. MADGWICK (British Aerospace, PLC, Civil Aircraft Div., A87-44703 Weybridge, England) IN: Materials in aerospace; Proceedings of ROTOR ICING EXPERIENCE AT WESTLAND AND ITS the First International Conference, London, England, Apr. 2-4, 1986. APPLICATION TO CURRENT AND FUTURE HELICOPTERS Volume 2 . London, Royal Aeronautical Society, 1986, p. 395-423. refs R. L. FROST (Westland, PLC, Yeovil, England) IN: Helicopter Rotor Icing Symposium, London, England, Jan. 14, 1986, An account is given of fires experienced in airliner operations Proceedings. London, Royal Aeronautical Society, 1986, p. 24-45. with a view to the characterization of the performance of the various materials used in airliner interiors. The results of these Research supported by the Ministry of Defence (Procurement Executive). considerations are compared with data that have been produced The effects of ice on the W30 helicopter are examined, and by the laboratory test methods devised by the airliner manufacturing an icing flight envelope for the helicopter is constructed. The industry for cabin interior materials selection. The impact of new equipment used to monitor icing during the flight testing of the and impending airworthiness regulations on fire safety-related helicopter is described. The flight tests were carried out at various materials specifications is discussed. The difficulties posed by the altitudes, temperatures, and icing conditions; the stresses, fire/smoke toxicity problem are considered in the cases of epoxy, performance, handling, and vibration of the helicopter were phenolic, polycarbonate, ABS, and PEEK-polyimide resins; of these, evaluated. It is observed that for the W30 the rotor performance only PEEK-polyimide is found to be acceptable. O.C. limitations dominate the aircraft flight envelope and therefore the flight envelope must be restricted to ensure that the limitations A87-45635"# Massachusetts Inst. of Tech., Cambridge. are avoided. The performance of a Sea King helicopter with COMPARISON OF WET AND DRY GROWTH IN ARTIFICIAL composite main rotor blades under icing conditions is analyzed. AND FLIGHT ICING CONDITIONS The data reveal that there is little difference in the operation of R. JOHN HANSMAN, JR. and MARK S. KIRBY (MIT, Cambridge, the helicopter with composite blades compared to one with metal MA) Journal of Thermophysics and Heat Transfer (ISSN blades. The design and development of an electrothermal rotor 0887-8722), vol. 1, July 1987, p. 215-221. FAA-supported research. blade deicing system are examined. I.F. Previously cited in issue 18, p. 2613, Accession no. A86-39948. refs A87-44705 (Contract NGL-22-009-640; NAG3-6662) ICING CLEARANCE CRITERIA FOR UK MILITARY HELICOPTERS A87-46317 M. G. MATTERSBY and P. A. KNOWLES (Aeroplane and Armament NUMERICAL SIMULATION OF CRUISER ON AIRCRAFT Experimental Establishment, Boscombe Down, England) IN: LIGHTNING Helicopter Rotor Icing Symposium, London, England, Jan. 14, 1986, M. MONAVON and M. LEROY (SEDACIP Sad, Les Ulis, France) Proceedings . London, Royal Aeronautical Society, 1986, p. Electronics Letters (ISSN 0013-5194), vol. 23, June 4, 1987, p. 64-76. 640-642. In French. The development of icing clearance criteria for UK military Ship and aircraft manufacture requires modern technologies helicopters is discussed. The basic requirements for the evaluation based on composite materials, which increases the vulnerability of the aircraft performance in icing conditions are described. Flight of electronic equipment subjected to an electromagnetic pulse testing techniques for the certification of a helicopter for flight in (EMP). The use of a 3D finite-difference method to simulate a icing conditions are examined. Rotor deicing clearance data for natural EMP, such as lightning, is limited by excessive CPU time. the Chinook helicopter, obtained from a number of trials, are Improvements are introduced to describe these phenomena using analyzed. I.F. large computation time windows with reduced CPU cost. Numerical results are given when the hull of a cruiser is subjected to A87-44706 lightning. Author ROTOR ICING RESEARCH AT RAE FARNBOROUGH R. W. GENT (Royal Aircraft Establishment, Farnborough, A87-46373 England) IN: Helicopter Rotor Icing Symposium, London, England, BURNING QUESTIONS Jan. 14, 1986, Proceedings. London, Royal Aeronautical Society, J. M. RAMSDEN Flight International (ISSN 0015-3710), vol. 131, 1986, p. 77-97. June 13, 1987, p. 121-125. Theoretical research at RAE into icing on helicopter rotors is A study of over 150 survivable airliner impacts has concluded reviewed. Mathematical models have been developed to predict that postcrash fires were set off in some two-thirds of these, and

646 03 AIR TRANSPORTATION AND SAFETY

that over one-third of the deaths in these fire-involving crashes N87-25288"# National Center for Atmospheric Research, Boulder, were due to fire-related rather than impact-related injuries. About Colo. 1300 people who might have survived the impacts are estimated WIND SHEAR INCIDENT OF MAY 31, 1984 to have burned to death. A broad evaluation is presently made of JOHN MCCARTHY In NASA. Langley Research Center Wind salient lessons to be learned from this and other studies bearing Shear/Turbulence Inputs to Flight Simulation and Systems on the causes and consequences of cabin fires, with attention to Certification p 235 Jul. 1987 the roles played by fuel characteristics, electrical wire insulation, Avail: NTIS HC A12/MF A01 CSCL 01C escape systems, cabin furniture upholstery, and the extensive use An incident involving wind shear which occured on 31 May of polymers in cabin structural elements. O.C. 1984 on a United Airlines aircraft is discussed by a member of the National Center for Atmospheric Research. The meteorological parameters important to this incident are detailed. E.R. A87-46724# THE AVSCOM FLIGHT SAFETY PART PROGRAM ANTHONY S. TORNATORE (U.S. Army, Aviation Systems Command, Saint Louis, MO) IN: 1987 Annual Reliability and Maintainability Symposium, Philadelphia, PA, Jan. 27-29, 1987, Proceedings . New York, Institute of Electrical and Electronics Engineers, Inc., 1987, p. 395-398. N87-25308# Lockheed-California Co., Burbank. This paper describes the procedural implementation of a KRASH ANALYSIS CORRELATION. TRANSPORT AIRPLANE management program designed to significantly curtail Army aviation CONTROLLED IMPACT DEMONSTRATION TEST Final Report, major accidents caused by equipment induced problems. The Feb. - Aug. 1985 program provides enhanced life cycle management, control, and GIL WI'I-ILIN Dec. 1986 125 p surveillance of parts that are critical to the safe operation of the (Contract DTFA03-84-C-00004) aircraft. Author (AD-A179906; LR-30916; DOT/FAA/CT-86-13) Avail: NTIS HC A06/MF A01 CSCL 01B N87-25282"# Princeton Univ., N. J. Dept. of Mechanical and The analyses results of a transport airplane Controlled Impact Aerospace Engineering. Demonstration (CID) test using programs KRASH are described. UNRESOLVED ISSUES IN WIND SHEAR ENCOUNTERS Pre-CID analyses, presented in FAA technical report ROBERT F. STENGEL /n NASA. Langley Research Center Wind DOT/FAA/CT-85/9, are provided in summary form. The KRASH Shear/Turbulence Inputs to Flight Simulation and Systems post CID correlation consists of modeling two sequences; a Certification p 197-204 Jul. 1987 symmetrical impact of the fuselage with the ground (after Avail: NTIS HC A12/MF A01 CSCL 01C engine-loss at initial air-to-ground impact) and the unsymmetrical Much remains to be learned about the hazards of low altitude air-to-ground including initial engine ground contact and subsequent wind shear to aviation. New research should be conducted on the fuselage impact with the ground. The analyses and test results nature of the atmospheric environment, on aircraft performance, are compared with regard to floor acceleration responses, fuselage and on guidance and control aids. In conducting this research, it shear and bending moment distribution, wing and engine is important to distinguish between near-term and far-term acceleration responses, wing bending moment distribution, objectives, between basic and applied research, and between uses structural failures, fuselage underside crush, and sequence of of results for aircraft design or for real-time implementation. events. GRA Advances in on-board electronics can be applied to assuring that aircraft of all classes have near optimal protection against wind shear hazards. Author

N87-25285"# National Transportation Safety Board, Washington, D.C. Bureau of Technology. ACCIDENT INVESTIGATION N87-25309# Kentucky Univ., Lexington. Dept. of Mechanical Engineering. WILLIAM G. BUD LAYNOR /n NASA. Langley Research Center DETERMINATION OF THE LOCAL HEAT TRANSFER Wind Shear/Turbulence Inputs to Flight Simulation and Systems CHARACTERISTICS ON GLAZE ICE ACCRETIONS ON A Certification p 217-220 Jul. 1987 Avail: NTIS HC A12/MF A01 CSCL 01C CYLINDER AND A NACA 0012 AIRFOIL Final Report, May 1983 - Sep. 1986 The National Transportation Safety Board (NTSB) has attributed M. R. PAlS and S. N. SINGH Apr. 1987 74 p wind shear as a cause or contributing factor in 15 accidents (Contract F33615-83-C-3013) involving transport-categroy airplanes since 1970. Nine of these were nonfatal; but the other six accounted for 440 lives. Five of (AD-A179931; AFWAL-TR-87-3001) Avail: NTIS HC A04/MF A01 CSCL 20D the fatal accidents and seven of the nonfatal accidents involved encounters with convective downbursts or microbursts. Of other In recent years, the problem of ice formation on aircraft has accidents, two which were nonfatal were encounters with a frontal received considerable attention because of its influence on military system shear, and one which was fatal was the result of a terrain aircraft capabilities. Military aircraft and helicopters may be required induced wind shear. These accidents are discussed with reference to operate under icing conditions which would effect their performance, maneuverability and impair the mechanical integrity to helping the aircraft to avoid the wind shear or if impossible to of unprotected engines. Ice formation poses a hazard to flight in help the pilot to get through the wind shear. E.R. that it alters the aerodynamic characteristics of lifting surfaces, reducing the maximum lift and sharply increasing the drag. In N87-25287"# United Air Lines, Inc., Denver, Colo. addition the ice formation may lead to control problems and, if it UNITED AIRLINES WIND SHEAR INCIDENT OF MAY 31, 1984 sloughs off, damage structures downstream. The above situations DAVID A. SIMMON In NASA. Langley Research Center Wind can cause serious problems for military aircraft or missiles flying Shear/Turbulence Inputs to Flight Simulation and Systems over the North Atlantic and North Sea. In Europe in winter it is Certification p 233-234 Jul. 1987 possible to have the proper weather conditions for ice formation Avail: NTIS HC A12/MF A01 CSCL 01C up to 30 percent of the time. The ice accretion process is of An incident involving wind shear on 31 May 1984 is discussed prime interest in aircraft design. In order to develop and then by an airline employee. The specs of the plane are given, the certify certain protection systems 11-16, it is necessary to be able weather conditions are listed, and the actions taken by the flight to test engine , aerofoils in simulated icing conditions. crew are discussed. E.R. GRA

647 03 AIR TRANSPORTATION AND SAFETY

N87-25310# National Transportation Safety Board, Washington, Finally a scheme is described to remove false data due to data-link D.C. corruption. Author AIRCRAFT ACCIDENT/INCIDENT SUMMARY REPORTS: UNALASKA, ALASKA, SEPTEMBER 25, 1985; JENKINSBURG, GEORGIA, SEPTEMBER 29, 1985; BOSTON, MASSACHUSETTS, DECEMBER 15, 1985; DEKALB, TEXAS, DECEMBER 31, 1985; ERIE, PENNSYLVANIA, FEBRUARY 21, 1986 A87-42786 30 Jun. 1987 48 p GEOSTATIONARY SATELLITE NAVIGATION SYSTEMS (PB87-910408; NTSB/AAR-87/O2/SUM) Avail: NTIS HC TRI T. HA and R. CLARK ROBERTSON (Virginia Polytechnic A03/MF A01 CSCL 01C Institute and State University, Blacksburg) IEEE Transactions on A compilation of reports of aviation accidents investigated by Aerospace and Electronic Systems (ISSN 0018-9251), vol. AES-23, the National Transportation Safety Board is presented. The accident March 1987, p. 247-254. refs locations and dates are: Unalaska, Alaska, September 25, 1985; The concept of position determination using geostationary Jenkinsburg, Georgia, September 29, 1985; Boston, satellites as an alternative to the global positioning system (GPS) Massachusetts, December 15, 1985; DeKalb, Texas, December is studied. The advantage of a geostationary system is that only 31, 1985; and Erie, Pennsylvania, February 21, 1986. Author three, or at most four, satellites are required to cover the continental United States. A total of twelve satellites are sufficient for global coverage (excluding polar regions), or eight if only longitude and N87-25311# National Transportation Safety Board, Washington, latitude, but not altitude, are measured. The system involves the D.C. Bureau of Safety Programs. ANNUAL REVIEW OF AIRCRAFT ACCIDENT DATA. US AIR determination of the range to either four geostationary satellites CARRIER OPERATIONS CALENDAR YEAR 1983 or, if the altitude is not measured, three geostationary satellites. The accuracy of the proposed systems are evaluated to obtain 13 Feb. 1987 112 p the rms error associated with position determination, and the (PB87-160628; NTSB/ARC-87-01) Avail: NTIS HC A06/MF A01 CSCL 01C concept for the implementation of measurements required by the systems is presented. The accuracy of the systems are adequate The record of aviation accidents involving revenue operations for civilian use in the continental United States; however, there is of U.S. air carriers and on demand air taxis for calendar year a degradation in accuracy as the location of the user approaches 1983 is given. Tables are presented to describe the losses and the equator. Author characteristics of the 1983 accidents to enable comparisons with prior years. GRA

N87-26034# Technische Hogeschool, Delft (Netherlands). Dept. of Aerospace Engineering. A87-43455# FUEL SAVING AND FUEL RELATED SUBJECTS WITHIN AN IRISH DAUPHIN HELICOPTER S.A.R. SYSTEM FLIGHT TESTS AIRLINE'S OPERATIONAL ENVIRONMENT B. FOUQUES (Aerospatiale, Division Helicopteres, Marignane, J. BRUEGGEN 1 Apr. 1986 213 p Prepared in cooperation France) DGLR, European Rotorcraff Forum, 12th, with KLM Royal Dutch Airlines, Amsterdam, Netherlands Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. (ETN-87-90148) Avail: NTIS HC A10/MF AOl 10p. Aircraft fuel level measuring magnetic sticks and their operation, A system description, together with an evaluation of the fuel used indicator and the corresponding fuel flow transmitter, development tests and their revealed difficulties, are presented the fuel quantity system, and the AIDS-equivalents of the fuel for the maritime search-and-rescue Dauphin helicopters developed used and fuel quantity indication are described. The layout and for the Irish Air Corps and equipped in order to enable their operation of the horizontal tail and the trim unit are shown, and quasi-autonomous operation in adverse weather conditions. the variation of the angle during flight, as a result of Attention is given to the functions and integration of an automatic weight reduction and center of gravity shift (fuel burn) is analyzed. flight control system, Doppler, Omega and VOR/DME navigation, A unit which characterizes the fuel consumption of a Boeing 747 and flight data display systems. D.C. is presented. ESA

04 A87-43469# AUTONOMOUS NAVIGATION SYSTEM FOR THE NEW GENERATION OF MILITARY HELICOPTERS AND ASSOCIATED AIRCRAFT COMMUNICATIONS AND NAVIGATION FLIGHT TESTS M. BAEUMKER and W. HASSENPFLUG (Litton Technische Werke, Includes digital and voice communication with aircraft; air navigation Freiburg im Breisgau, West Germany) DGLR, European Rotorcraft systems (satellite and ground based); and air traffic control. Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 22 p. refs The paper describes an integrated autonomous strapdown A87-42779 inertial navigator, augmented by a Doppler velocity sensor and a REAL-TIME WIND ESTIMATION AND TRACKING WITH magnetometer for helicopter application. To obtain height above TRANSPONDER DOWNLINKED AIRSPEED AND HEADING ground, a radar altimeter is integrated into the navigation system. DATA Accurate weapon delivery requirements and flight safety aspects C. C. LEFAS (Nuclear Research Center Democritos, Attiki, while operating the helicopter under adverse weather conditions Greece) IEEE Transactions on Aerospace and Electronic Systems and at night demand the accurate determination of TAS throughout (ISSN 0018-9251), vol. AES-23, March 1987, p. 169-174. the entire speed regime. Next to position, velocity and attitude, EUROCONTROL-supported research, refs the strapdown system provides all signals required for stability The use of magnetic heading and true air speed measurements augmentation and to support autopilot functions. The system made on board civil airplanes to assist in radar tracking is described. communicates with the other avionics on board the helicopter. The data are telemetered via the air-ground data link of the mode Flight trials using three different types of helicopters have been S radar system. A new filter, similar to the first-order Kalman performed to demonstrate the navigation capability and filter, is developed using velocity measurements to bias its performance of a hybrid strapdown navigator, a new analytical prediction equations. This filter follows satisfactorily maneuvers, true air speed system for the low speed regime, and the and estimates, in real time, the wind in the vicinity of the airplane. performance of a strapdown magnetometer. Author

648 04 AIRCRAFTCOMMUNICATIONSANDNAVIGATION

A87-44036 and the conflict detection and resolution algorithms. A graphic WORLDWIDENAVIGATIONINTOTHE21STCENTURY- AN interpretation of the algorithms is provided as well as a AIRLINEVIEW demonstration that it is not feasible to give the pilot an indication P. MOORE and D. M. PAGE (British Caledonian Airways, Ltd., of the headings of surrounding aircraft in addition to their Crawley, England) Journal of Navigation (ISSN 0020-3009), vol. positions. Author 40, May 1987, p. 158-163. The requirements for a future worldwide air navigation system, which combines navigation and air traffic control, are discussed. An integrated system of navigation and air traffic control is needed. The use of satellites for air navigation, control, and surveillance is A87-44312 examined. Consideration is given to the GPS, distance measuring ERRORS IN THE MEASUREMENT OF THE COURSE ANGLES equipment (DME)/DME fixing, and an automatic dependent OF RADAR REFERENCE POINTS DUE TO THE IMPRECISE surveillance system. Air traffic communications via data link STABILIZATION OF THE ANTENNA MOUNTING IN BANK AND transmission by satellites, operational control communications, and PITCH [OSHIBKI IZMERENIIA KURSOVYKH UGLOV passenger communications are studied. The cost effectiveness of RADIOLOKATSIONNYKH ORIENTIROV IZ-ZA NETOCHNOI a control, navigation, and surveillance system based on satellites STABILIZATSII OSNOVANIIA ANTENNY PO KRENU I is evaluated. I.F. TANGAZHU] S. D. SUBOCHEV (Leningradskii Institut Aviatsionnogo A87-44039 Priborostroeniia, Leningrad, USSR) Priborostroenie (ISSN INTEGRATED NAVIGATION, COMMUNICATION AND 0021-3454), vol. 30, April 1987, p. 49-52. In Russian. SURVEILLANCE SYSTEMS BASED ON STANDARD DISTANCE A first-approximation analysis is made of the measurement error MEASURING EQUIPMENT of the course angle of radar reference points according to the A. BECKER (DFVLR, Institut fuer Flugfuehrung, Brunswick, West indicator of an airborne panoramic radar. It is shown that the Germany) Journal of Navigation (ISSN 0020-3009), vol. 40, May error depends linearly on the stabilization errors of the antenna 1987, p. 194-205. refs mounting in bank and pitch. B.J. The use of standard distance measuring equipment (DME) to integrate communicationnavigationsurveillance systems is studied. DME growth capabilities include the use of additional pulses, and the ability to accurately measure the angle of incidence of the received DME RF carrier wave. Various equipment has A87-44845 been developed based on the DME concept; the functions of the TIME MODULATION. II - SCHEME CODES AVOIDANCE (1) three-way DME, (2) scanning three-way DME, (3) trilateration MANEUVERS FOR AIRCRAFT three-way DME, (4) ground azimuth direction finder, (5) ground EDMOND R. GUNNY Microwaves & RF (ISSN 0745-2993), vol. elevation direction finders, (6) air-to-ground and ground-to-air 26, June 1987, p. 86, 88-90, 92, 93. selective datalinks, and (7) ground-to-air broadcast datalinks. Four The operation of the reply encoder and decoder circuit and methods for integrating communication/navigation/surveillance the intent generation of time-effective modulation avoidance systems using DME elements are proposed. The bases of these scheme is described. In reply transmissions the reply message systems are (1) three-way DME, (2) scanning three-way DME, (3) elements are sent out in separate range periods; the first reply trilateration three-way DME, and (4) three-way DME with ground pulse transmission is sent immediately upon detection and signal azimuth direction finder. These four systems are compared in terms processing and the second is delayed by both the range listing of coverage, accuracy, integrity, frequency, utilization, installation, time and encoded reply time. Reply message-time spacing is and costs. It is noted that system 2 is most applicable followed achieved by a random access memory module. The replies are by systems 3, 1, and 4. I.F. then matched and sent to a computer to generate differential altitude data. The requirements for an air traffic control (ATC) A87-44040 transponder are examined. The limitations of the traffic alert and COLOUR DEPENDENCE AND SURPLUS INFORMATION IN collision avoidance systems currently utilized are discussed. A data AIRPORT VISUAL AIDS DURING VFR OPERATIONS link for pilots and ATC on a common radio spectrum needs to ROBERT K. MCKELVEY Journal of Navigation (ISSN 0020-3009), use a modulation system such as the one proposed. A diagram vol. 40, May 1987, p. 206-226. refs of the pulse-pair matching of signature modulation system is Airport visual aids are investigated for failure to transfer from presented. I.F. chromatic to achromatic viewing situations, and for their value during visual flight rule operations. Slide sequences of aircraft movements during taxi-out, take-off, approach, and landing operations under various meteorological conditions at night were prepared and evaluated by pilots. The responses of the 27 pilots A87-45722# are analyzed in terms of the proportions of color-linked response; AIRBORNE LASER COMMUNICATIONS SCINTILLATION the frequency of correct signal recognition responses within chroma MEASUREMENTS categories; and the frequency of correct response within visual ROBERT J. FELDMANN, LINDEN B. MERCER (USAF, Wright guidance categories. It is observed that only the signal light from Aeronautical Laboratories, Wright-Patterson AFB, OH), and the control tower is completely color dependent, and there is STEVEN K. ROGERS (USAF, Institute of Technology, some contradiction between the complexity of the display system Wright-Patterson AFB, OH) IN: MILCOM '86 Military and the guidance values. I.F. Communications Conference, Monterey, CA, Oct. 5-9, 1986, Conference Record. Volume 3 . New York, Institute of Electrical A87-44231 and Electronics Engineers, Inc., 1986, p. 45.5.1-45.5.5. refs AN AIRBORNE COLLISION AVOIDANCE SYSTEM - THE TCAS The effects of scintillation on air-to-air laser communication [UN SYSTEME ANTICOLLISION EMBARQUE - LE TCAS] performance are investigated using optical scintillation data JEAN LAMBERT (Direction Generale de I'Aviation Civile, Service collected during the Laser Airborne Communications Experiment Technique de la Navigation Aerienne, Paris, France Navigation (LACE). The objectives of and experimental procedures for LACE (Paris) (ISSN 0028-1530), vol. 35, April 1987, p. are described. The collected scintillation data are compared to TCAS is a totally airborne system which uses the secondary data derived from terrestrial atmospheric turbulence models. It is radar signal formats to detect surrounding aircraft. It indicates observed that the ground scintillation data correlate with this their positions to the pilot and computes vertical avoidance prediction, and the initial flight test results agree with a log normal maneuvers. This article describes the operation of the system distribution. I.F.

649 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

A87-45878 N87-25313# Test Wing (4950th), Wright-Patterson AFB, Ohio. THE QUALITY OF RADAR DATA AND ITS DETERMINATION TACAN/INS PERFORMANCE EVALUATION (TIPE) FLIGHT AT THE RADAR INSTALLATIONS OF THE BUNDESANSTALT TEST REPORT Report, 29 Apr. - 24 May 1986 FUER FLUGSICHERUNG [RADARDATENQUALITAET UND IHRE CHRISTOPHER J. MCCORMACK 22 Jan. 1987 43 p BESTIMMUNG AN DEN RADARANLAGEN DER (AD-A180138; REPT-4950/FTR-86-10) Avail: NTIS HC A03/MF BUNDESANSTALT FUER FLUGSICHERUNG] A01 CSCL 17G BOR B. CLOOS (Bundesanstalt fuer Flugsicherung, Frankfurt am The TACAN/INS Performance Evaluation test program Main, West Germany) IN: Radar Technology 1986; Symposium, investigated the feasibility of test missions requiring aircraft position 6th, Bremen, West Germany, Nov. 4-6, 1986, Reports. Duesseldorf, information without using dedicated ground based tracking radars. Deutsche Gesellschaft fuer Ortung und Navigation, 1986, p. This test examined the accuracy of the aircraft's TACAN receiver C2.1-C2.21. In German. refs and on board inertial navigation system by comparing data from The procedures used by the West German federal flight-safety these airborne systems with information from a ground based agency to evaluate the quality of radar data are reviewed. The precision laser tracker. Data analysis concentrated on the distance parameters used to define quality are introduced; the importance measuring equipment information from the TACAN transceiver. The of the interface between the radar sensor and the display is report contains a summary of the data collected as well as a indicated; problems related to target classification, reproducibility, description of the data reduction techniques, including dual DME and statistical significance are discussed; and the design concept position fixing and three dimensional coordinate transformations. of an integrated radar evaluation system is presented. Diagrams, The results indicate that a dual TACAN positioning system can drawings, graphs, and photographs are provided. T.K. provide accurate position fixing. GRA

A87-46415 TERRAIN MODELLING OF GLIDESLOPE FOR INSTRUMENT O5 LANDING SYSTEM M M. POULOSE, P. R. MAHAPATRA, and N. BALAKRISHNAN AIRCRAFT DESIGN, TESTING AND (Indian Institute of Science, Bangalore, India) IEE Proceedings, Part H - Microwaves, Antennas and Propagation (ISSN 0950-I07X), PERFORMANCE vol. 134, pt. H, no. 3, June 1987, p. 275-279. refs The paper makes a contribution to the evaluation of irregularities Includes aircraft simulation technology. introduced in electronically defined glideslopes of UHF instrument landing systems (ILS) by the unevenness of the terrain around the glideslope antenna. Various methods of physical and geometric A87-42855 optics have been applied in recent years to model and estimate FRACTURE OF AN AIRCRAFT HORIZONTAL STABILIZER the glideslope aberration at given locations prior to actual IAN C. HOWARD (Sheffield, University, England) IN: Case histories installation. A systematic study of various methods is made in the involving fatigue and fracture mechanics; Proceedings of the paper. A general treatment is evolved, which is capable of Symposium, Charleston, SC, Mar. 21, 22, 1985. Philadelphia, PA, exhaustively handling arbitrary ray order effects and topography. American Society for Testing and Materials, 1986, p. 259-276. The uniform asymptotic theory has been applied to the ILS problem An analysis is presented on the data of the accident report on and results compared with the uniform theory of diffraction. The a Boeing 707 crash, the origin of which was found to be a fatigue results of actual case studies are presented. Author failure of the top chord of the stabilizer. This fracture had eventually propagated, severing the stabilizer from the body of the aircraft during a flap maneuver. In the present study, linear elastic fracture mechanics (LEFM) is used to investigate the first static jump of A87-46861 the crack; in addition, use was made of published data on stress APPLICATION OF WEDGE DIFFRACTION THEORY TO intensity factor in a bar weakened by a corner crack. The results ESTIMATING POWER DENSITY AT AIRPORT HUMPED made it possible to predict the fracture toughness of the material RUNWAYS from which the cracked component was made and to estimate ALFRED R. LOPEZ (Hazeltine Corp., Commack, NY) IEEE the load transferred within the stabilizer by the arrest of this Transactions on Antennas and Propagation (ISSN 0018-926X), vol. crack. I.S. AP-35, June 1987, p. 708-714. refs Shadowing caused by humped runways at some airports significantly attenuates the guidance signals of the microwave A87-42856 landing system as the aircraft approaches the touchdown point. FATIGUE LIFE ANALYSIS OF FUEL TANK SKINS UNDER Application of wedge diffraction theory provides an estimate of COMBINED LOADS this effect. A wedge diffraction factor is presented which relates CHARLES R. SAFF and M. A. FERMAN (McDonnell Aircraft Co., the signal strength in the shadow to that for line-of-sight on a flat St.Louis, MO) IN: Case histories involving fatigue and fracture runway. Computations are confirmed by measurements at two mechanics; Proceedings of the Symposium, Charleston, SC, Mar. airports. Author 21, 22, 1985. Philadelphia, PA, American Society for Testing and Materials, 1986, p. 277-290. The superposition of high- and low-frequency Ioadings has caused numerous fatigue crack problems throughout the history of metal airframes. Fighter aircraft fuel tanks are subjected to the N87-25312# Federal Aviation Agency, Atlantic City, N.J. superposition of low-frequency (0.1 to 1 Hz) maneuver loads and HELIPORT VISUAL APPROACH SURFACE TESTING TEST high frequency (50 to 300 Hz) vibrations to panel flutter and fuel PLAN slosh. This loading can lead to cracks, and leaks, in shorter times ROSANNE M. WEISS and JOHN R. SACKETT Feb. 1987 31 p than can be predicted by using either load condition alone. This (AD-A179897; DOT/FAA/CT-TN86/61) Avail: NTIS HC A03/MF paper examines two methods for predicting fatigue lives under A0t CSCL 01D combined high- and low-frequency Ioadings. Tests of beam element This Technical Note identifies procedures to be used during specimens and a simulated fuel tank were used to examine tests to be conducted at the Federal Aviation Administration prediction accuracy of both techniques. Results show that both Technical Center. These tests are designed to test the applicability techniques accurately predict the effects of combined load of existing heliport approach and departure surface criteria. Three frequencies on life when adjusted to correlate predictions with the different types of aircraft will be used. GRA extreme (high- and low-) frequency data. Author

650 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE

A87-43402# high transonic and perhaps supersonic performance, provided that FEL - A NEW MAIN ROTOR SYSTEM suitable convertible engines become available. Author DIETER BRAUN, HUBERT FROMMLET, and ALOIS SCHWARZ (Messerschmitt-Boelkow-Blohm GmbH, Munich, West Germany) A87-43408"# National Aeronautics and Space Administration. DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, Ames Research Center, Moffett Field, Calif. West Germany, Sept. 22-25, 1986, Paper. 17 p. CALCULATED PERFORMANCE, STABILITY, AND MAN- A new hingeless main rotor system, the fiber-elastomeric bearing EUVERABILITY OF HIGH-SPEED TILTING-PROP-ROTOR AIR- rotor (FEL) for a 4-5-ton helicopter is under development. Its main CRAFT features are elastomeric bearings and composite materials for the WAYNE JOHNSON, BENTON H. LAU, and JEFFREY V. BOWLES blades and hub. Flapping and lead lag motions are made in the (NASA, Ames Research Center, Moffett Field, CA) DGLR, flexible neck of the blades; pitch change is accomplished by the European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West elastomeric bearings. The design goals for this new rotor type are Germany, Sept. 22-25, 1986, Paper. 43 p. Previously announced low weight, simple and robust construction, low parts count, minimal in STAR as N87-17695. refs maintenance, reduced vulnerability, and excellent maneuverability The feasability of operating tilting-prop-rotor aircraft at high by high control power. Stress calculations, stiffness optimization, speeds is examined by calculating the performance, stability, and and component testing have been performed, and the new rotor maneuverability of representative configurations. The rotor system has been verified on the whirl tower. Author performance is examined in high-speed cruise and in hover. The whirl-flutter stability of the coupled-wing and rotor motion is A87-43403# calculated in the cruise mode. Maneuverability is examined in terms NEW AERODYNAMIC DESIGN OF THE FENESTRON FOR of the rotor-thrust limit during turns in helicopter configuration. IMPROVED PERFORMANCE Rotor airfoils, rotor-hub configuration, wing airfoil, and airframe A. VUILLET and F. MORELLI (Aerospatiale, Division Helicopteres, structural weights representing demonstrated advanced technology Marignane, France) DGLR, European Rotorcraft Forum, 12th, are discussed. Key rotor and airframe parameters are optimized Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. for high-speed performance and stability. The basic aircraft-design 12 p. refs parameters are optimized for minimum gross weight. To provide a An evaluation is made of the performance advantages and focus for the calculations, two high-speed tilt-rotor aircraft are prospective design improvements for the 'fenestron' type of considered: a 46-passenger, civil transport and an helicopter tail rotor. Attention is given to the results of recent air-combat/escort fighter, both with design speeds of about 400 fenestron flow analyses conducted with both scale models and knots. It is concluded that such high-speed tilt-rotor aircraft are full scale aircraft, as well as to the methods employed to obtain quite practical. Author these experimental data. Tests of a fenestron incorporating stator blades behind the rotor, within the diffuser structure, have indicated A87-43409# significant efficiency and maximum thrust improvements for a given RSRA/X-WING - A STATUS REPORT rotor solidity. O.C. ARTHUR W. LINDEN ( Corp., Div., Stratford, CT) DGLR, European Rotorcraft Forum, 12th, A87-43406# Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. OPTIMUM DESIGN OF A HELICOPTER ROTOR BLADE 15p. S. HANAGUD, ADITI CHATTOPADHYAY, Y. K. YILLIKCI, D. A development history and status report is presented for the SCHRAGE (Georgia Institute of Technology, Atlanta), and G. Rotor System Research Aircraft; this is an 'X-wing' helicopter able REICHERT (Braunschweig, Technische Universitaet, Brunswick, to bring its main rotor to a full halt in order to employ it as a wing West Germany) DGLR, European Rotorcraft Forum, 12th, during high speed flight, and vice versa. Attention is given to this Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. rotary-to-fixed wing conversion mode. The flight test phase for 26 p. refs this experimental vehicle began in the Fall of 1986. Rotor The problem of minimum weight design of a helicopter rotor mechanical design details and control system organization are blade subject to a constraint on its coupled flap-lag-torsional natural discussed. O.C. frequency has been studied in this paper. Modern structural optimization technique based on optimality criteria approach has A87-43410"# National Aeronautics and Space Administration. been applied for optimizing the weight of the blade. Optimum Ames Research Center, Moffett Field, Calif. designs are presented for a typical soft-in-plane hingeless rotor MEASUREMENT OF SIDE FORCES OF A H-FORCE ROTOR configuration. The results indicate that the application of structural HENRY R. VELKOFF (NASA, Ames Research Center; U.S. Army, optimization techniques leads to benefits in rotor blade design not Advanced Research Technology Activity, Moffett Field, CA), only through substantial reduction in weight but a considerable CHRISTIAN PETERSILGE, and CURTIS COWAN (Ohio State reduction in the vibratory hub shears and moments at the blade University, Columbus) DGLR, European Rotorcraft Forum, 12th, root due to proper placement of blade natural frequency. Author Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 16 p. refs A87-43407# Study of the use of tip vanes has been underway to investigate EXPANDING TILT ROTOR CAPABILITIES both the impact of the vanes on hover performance and on their J. M. DREES (Bell Helicopter Textron, Fort Worth, TX) DGLR, potential use as force generators. It is the aim of this paper to European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West report on progress made to determine the forces that can be Germany, Sept. 22-25, 1986, Paper. 17 p. refs generated. Model tests were run using a 6-ft-diameter rotor with The XV-15 tilt-rotor aircraft is the culmination of over 50 years tip vanes pivoted below the blade tips. Data were taken on the of research, development, and testing. It has proven the practicality thrust, torque, and side force. The results obtained were in of the tilt rotor concept and led directly to implementation of the substantial agreement with the side force predicted by using a V-22 Osprey program. The time has now come to project the full simple wing model. Author potential of the tilt rotor in the future. In this paper, possibilities for weight reduction and performance improvement are discussed A87-43411 # that could lead to significant enhancements in payload and PREDICTION OF BLADE AIRLOADS IN HOVERING AND operational speeds. In particular, control system configurations, FORWARD FLIGHT USING FREE WAKES wing download reductions, wing forward sweep, and canard R. H. MILLER and S. C. ELLIS (MIT, Cambridge, MA) DGLR, concepts are suggested as candidates offering potential European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West improvements for the next generation of tilt-rotor aircraft. To Germany, Sept. 22-25, 1986, Paper. 11 p. refs achieve forward velocities beyond what is feasible with the tilt Recent advances in the determination of rotor airloads and rotor, its derivative, the tilt-fold rotor, could become attractive for performance in hovering and forward flight, including autorotation,

651 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE are discussed. The ability to predict the spatial and temporal A87-43434# variation of blade airloads in forward flight is particularly important, HELICOPTER MODELLING FOR PERFORMANCE since the higher harmonic components of these loads are the CALCULATION primary source of helicopter vibration. Flight regimes and rotor KARL LIESE (Braunschweig, Technische Universitaet, Brunswick, configurations are identified that require the use of free-wake West Germany) DGLR, European Rotorcraft Forum, 12th, analytical techniques, as opposed to those regimes for which the Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. simpler rigid wake or momentum balance techniques are 19 p. BMFT-sponsored research, refs adequate. Author Methods for helicopter performance calculations are brought into line with the specific job in each case. Modern calculation techniques used in science and industry generally include analytical, empirical, and experimental parts, computing exact results within short time. Essential parts of the helicopter physical model are A87-43423# studied (such as downwash, blade-tip loss, hub geometry, and MEASUREMENTS OF THE PERFORMANCE OF A HELICOPTER blade motions, as well as blade and fuselage aerodynamics), and SWEPT TIP ROTOR IN FLIGHT their influence on the power required and trim settings is described. M. J. RILEY (Royal Aircraft Establishment, Bedford, England) The high variety of results based on different modeling techniques DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, makes it possible to adapt existing calculation methods to a new West Germany, Sept. 22-25, 1986, Paper. 14 p. task or to bring about a new efficient method by combining suitable Swept and rectangular planforms have been flight tested parts. Author simultaneously on a single rotor. Surface pressure distributions have shown the swept tip to perform well on the retreating blade and in the highly loaded areas at the front and rear of the rotor A87-43442"# California Univ., Los Angeles. disk as well as on the advancing blade. Blade dynamic response RECENT TRENDS IN ROTARY-WING AEROELASTICITY measurements have demonstrated the effectiveness of the chosen PERETZ P. FRIEDMANN (California, University, Los Angeles) planform in controlling aerodynamic pitching moments and overall DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, power measurements indicate a reduction of the power required West Germany, Sept. 22-25, 1986, Paper. 46 p. refs by the swept tip rotor. Author (Contract NAG2-209; NAG2-226) The purpose of this paper is to survey the principal developments which have occurred in the field of rotary-wing aeroelasticity during the past five year period. This period has been one of considerable activity and approximately one hundred A87-43427# papers have been published on this topic. To facilitate this review AN ANALYSIS OF IN-FIN TAIL ROTOR NOISE the field has been divided into a number of areas in which M. ROGER and F. FOURNIER (Lyon, Ecole Centrale, Ecully, concentrated research activity has taken place. The main areas in which recent research is reviewed are: (1) structural modeling; France) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. (2) aerodynamic modeling; (3) aeroelastic problem formulation using 15 p. refs automated or computerized methods; (4) aeroelastic analyses in (Contract DRET-83-025; DRET-84-368) forward flight; (5) coupled rotor/fuselage analyses; (6) active This paper is concerned with some aspects of sound generation controls and their application to aeroelastic response and stability; and sound propagation from a fenestron in-fin tail rotor. The study (7) application of structural optimization to vibration reduction; and includes the three following parts: (1) a prediction of rotor-noise (8) aeroelastic analysis and testing of special configurations. These sources using calculations based on unsteady aerodynamics theory; areas are reviewed with different levels of detail and some useful (2) an experimental investigation of the diffraction caused by the observations regarding potentially rewarding areas of future casing; and (3) the definition of an acoustic testing procedure on research are made. Author a real complete version of a fenestron-type tail rotor. Each part was performed independently. All the results given here are therefore only preliminary results, which must be considered as a A87-43443# first attempt at understanding the noise generated by an in-fin tail AEROELASTIC STABILITY OF A BEARINGLESS CIRCULATION rotor. Author CONTROL ROTOR IN FORWARD FLIGHT INDERJIT CHOPRA and CHANG-HO HONG (Maryland, University, College Park) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 17 p. refs A87-43431"# National Aeronautics and Space Administration. The aeroelastic stability of flap bending, lag bending and torsion Langley Research Center, Hampton, Va. of a bearingless circulation control rotor blade in forward flight is ROTOR DESIGN FOR MANEUVER PERFORMANCE examined using a finite element formulation. The flexbeam, the JOHN D. BERRY (NASA, Langley Research Center; U.S. Army, torque tube and the outboard blade are all discretized into beam Aerostructures Directorate, Hampton, VA) and DANIEL SCHRAGE elements, and the displacement compatibility conditions are (Georgia Institute of Technology, Atlanta) DGLR, European introduced in assembled matrices. Quasisteady strip theory is used Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, to evaluate aerodynamic forces, and the airfoil characteristics are Sept. 22-25, 1986, Paper. 12 p. taken from data tables. The effects of pneumodynamics and A method of determining the sensitivity of helicopter maneuver centrifugal pumping in the pressure duct are included to calculate performance to changes in basic rotor design parameters is jet momentum coefficient as a radial station. Two types of vehicle developed. Maneuver performance is measured by the time trim, propulsive and auxiliary power, are calculated from vehicle required, based on a simplified rotor/helicopter performance model, and rotor equilibrium equations through numerical integration of to perform a series of specified maneuvers. This method identifies element forces in azimuth as well as in radial directions. The parameter values which result in minimum time quickly because nonlinear periodic blade response is calculated using a finite of the inherent simplicity of the rotor performance model used. element in time method in normal mode equations. The periodic For the specific case studied, this method predicts that the minimum linearized perturbation equations in modal space are analyzed for time required is obtained with a low disk loading and a relatively stability, using Floquet transition matrix theory. The effects of high rotor solidity. The method was developed as part of the several parameters on blade stability are examined, including winning design effort for the American Helicopter Society student advance ratio, collective pitch, shaft tilt, propulsive and auxiliary design competition for 1984/1985. Author power trim. Author

652 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE

A87-43444# A87-43450# INVESTIGATIONOFGROUNDANDAIRRESONANCEUSING DETERMINATION OF THE STRUCTURAL PROPERTIES OF A COMBINATIONOF MULTIBLADE COORDINATES AND HELICOPTER ROTOR BLADES BY THEORETICAL ANO FLOQUET THEORY EXPERIMENTAL METHODS J. EWALD (Braunschweig, Technische Universitaet, Brunswick, C. HATCH and A. R. LEE (Royal Aircraft Establishment, West Germany) DGLR, European Rotorcraft Forum, 12th, Farnborough, England) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 15 p. refs 20 p. (Contract BMFT-LFF-84318) The use of a theoretical method for determining equivalent The description of the dynamic behavior of helicopters often beam extensional, bending, and torsional stiffnesses for helicopter leads to differential equations with periodically varying coefficients. rotor blades fabricated from anisotropic material with arbitrary The solution of these differential equations can be obtained by cross-sectional geometry is discussed, and results presented. The different mathematical methods. An efficient procedure results from method, which uses the NASTRAN finite-element package, also the combination of multiblade coordinates and Floquet theory. determines all stiffness coupling terms and predicts the position Using this method, investigations of ground and air resonance are of the elastic axis and shear center. Experimental data, derived carried out. By plotting the eigensolutions and eigenvector functions from simple section beams and model rotor blades manufactured it is shown that the transformation using multiblade coordinates from composite materials, are used for comparison with the does not eliminate the periodicity of the coefficients. This is due theoretically derived stiffnesses. An experimental method used for not only to the different dynamic behavior of rotor blades, but determining the beam bending stiffness, torsional stiffness, and also to special frequencies contained in the system matrices. shear center is also presented. This technique uses a number of Author +/- 1 g servo accelerometers mounted on the blade and used as inclinometers to measure angular deflections for known loads. This method enables shear-center positions to be determined to an accuracy better than 1 percent of the blade chord, and bending A87-43445# and torsional stiffnesses to within 2 percent. Author AN IMPROVED ASSUMED MODE METHOD FOR ESTIMATING THE MOTION OF A NONUNIFORM ROTOR BLADE H. AZZAM and P. TAYLOR (Southampton, University, England) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 13 p. Research supported by the Ministry of Defence (Procurement Executive). A87-43451 # refs COMPOSITE VITAL PARTS OPTIMISATION FOR EH 101 ROTOR The uncoupled flapwise and torsional motion of a rotating blade HUB is considered in order to demonstrate that the Galerkin method is E. ANAMATEROS, L. CARONI, M. FARIOLI (Costruzioni also applicable to the case of a nonuniform blade whose structural Aeronautiche Giovanni Agusta S.p.A., Gollarate, Italy), and C. properties vary sharply along its length. Then, a finite ROTONDI DGLR, European Rotorcraft Forum, 12th, element-like-technique of the assumed modes is presented to Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. provide a consistent relation between the deflection and the 27 p. refs moment of the nonuniform blade. The concept of the equivalent This paper is aimed to present the optimization of the design, flapping hinge offset for hingeless blades is reassessed in an manufacturing, and controllability of composite loop-windings. attempt to make the flapping equation more representative. Finally, These loop-windings are parts of the EH 101 main rotor hub. The an equivalent elastic twist is proposed in order to partially material used for the construction of the loop-windings is compensate for the absence of the torsional analysis in the simple graphite-epoxy composite material. The target of the program was rotor programs. Author to optimize the manufacturing process, minimize defects, and choose the graphite-epoxy material with the characteristics more compatible with this application. To attain this target, manufacturing and structural tests were carried out, correlations with analytical A87-43449# models, and structural tests were performed. Research for the DAMAGE TOLERANCE CONCEPTS FOR MODERN nondestructive tests were done in order to assume the quality of HELICOPTERS the loop-windings. Author M. TAPAVICZA (Messerschmitt-Boelkow-Blohm GmbH, Munich, West Germany) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 21 p. refs Damage-tolerant methods have found much interest in the helicopter community in the past years. The aim of damage A87-43456"# National Aeronautics and Space Administration. tolerance is that structures may withstand reasonable static and Ames Research Center, Moffett Field, Calif. dynamic loads despite the occurrence of defects as a consequence CORRELATION OF SA349/2 HELICOPTER FLIGHT-TEST DATA of fatigue, wear, impact, etc. Damage tolerance may be achieved WITH A COMPREHENSIVE ROTORCRAFT MODEL by slow defect growth or fail-safe capability of the structure. In GLORIA K. YAMAUCHI, RUTH M. HEFFERNAN (NASA, Ames the first case, it is assured that defects propagate slowly and that Research Center, Moffett Field, CA), and MICHEL GAUBERT early detection is guaranteed. In the second case, defects are (Aerospatiale, Division Helicopteres, Marignane, France) DGLR, absorbed by redundant load paths or defect-arresting structures. European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Tolerating defects is necessarily connected with the availability of Germany, Sept. 22-25, 1986, Paper. 52 p. Previously announced adequate inspection methods and maintenance intervals, which in STAR as N87-17692. refs have to be approved during the certification procedure. Although A comprehensive rotorcraft analysis model was used to predict designed to the hitherto accepted safe-life philosophy, many blade aerodynamic and structural loads for comparison with flight helicopters already incorporate a bundle of damage-tolerant test data. The data were obtained from an SA349/2 helicopter features (e.g., the application of composite material or with an advanced geometry rotor. Sensitivity of the correlation to redundant-load-path design). The qualification of entire helicopters wake geometry, blade dynamics, and blade aerodynamic effects solely according to the damage-tolerant approach seems was investigated. Blade chordwise pressure coefficients were premature; rather, a combined safe-life/damage-tolerance predicted for the blade transonic regimes using the model coupled philosphy is adequate at the present time. Author with two finite-difference codes. Author

653 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE

A87-43459# and mission parameters; trade-offs involve choices among simple, EXPERIMENTALAPPLICATIONOF STRAINPATTERN 'bootstrap', and combined simple/bootstrap cycles in view of ANALYSIS(SPA)- WINDTUNNELANDFLIGHTTEST system weight-saving, energy-saving, overall dimensions, reliability, RESULTS and maintainability criteria. The behavior of complete ECSs A.R. WALKER and D. B. PAYEN (Royal Aircraft Establishment, encompassing heat exchangers, valves, water separators and pipes Farnborough, England) DGLR, European Rotorcraft Forum, 12th, is simulated by a well-tested computer program. The effects of Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. weight and power savings obtainable by the optimum configuration 25 p. are elaborated through evaluation of consequent fuel saving as a Further experimental application of Strain Pattern Analysis (SPA) function of mission length. The sample case of the EH 101 to derive rotor blade deformation is described. The SPA technique helicopter is presented. O.C. has now been extended to derive not only the vibration mode shapes of a rotating blade, but also the instantaneous deformation shape at consecutive azimuth stations around the rotor disc. This technique has been successfully applied to both a dynamically scaled rotor model tested in the RAE 24 ft Wind Tunnel, and a A87-43473# AIR CONDITIONING SYSTEMS FOR HELICOPTERS Puma helicopter used in flight research at RAE Bedford. Instantaneous blade deformations around the rotor disc are FRANCIS COUGNENC (Toulouse, Centre d'Essais Aeronautique, France) and MARCEL LESCAUDRON (ABG-Semca, S.A., presented for both the model and helicopter rotor blades. These results are compared with corresponding calculated deflections. Toulouse, France) DGLR, European Rotorcraft Forum, 12th, Author Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 11p. The cooling of helicopter avionics as well as cabins requires A87-43463# SUBSTANTIATION OF THE ANALYTICAL PREDICTION OF air conditioning systems whose basing on air or vapor cycles must GROUND AND AIR RESONANCE STABILITY OF A be evaluated in light of the full range of technological and economic BEARINGLESS ROTOR, USING MODEL SCALE TESTS criteria. Attention is presently given to the certification tests that must be undertaken for such air conditioning systems and the P. T. W. JUGGINS (Westland, PLC, Helicopter Div., Yeovil, facilities in which they can be conducted, with a view to plans for England) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. next-generation facility designs, lUustrative examples of the testing process are given for current helicopter cooling systems. O.C. 19 p. Research supported by the Ministry of Defence (Procurement Executive). refs Prediction of the ground and air resonance stability of a bearingless main rotor demands the use of analytical techniques which adequately address the particular characteristics associated A87-43474# with this type of rotor. The approach adopted in such an analytical THE TILT-ROTOR AIRCRAFT - A RESPONSE TO THE FUTURE? procedure is described and the substantiation of analysis by testing FROM EUROPEAN INTERROGATIONS TO EUROFAR of a scale model bearingless main rotor is reported. Substantiation ACTIONS is achieved, from generally good agreement between measured HELMUT HUBER (Messerschmitt-Boelkow-Blohm GmbH, Munich, and theoretical data, although parameters are identified which West Germany), J. ANDRES, and J. RENAUD (Aerospatiale, hindered clear evaluation of some stability margins by the Moving Division Helicopteres, Marignane, France) DGLR, European Block technique. The effects of pitch-lag coupling on stability are Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, discussed, from measured results and from a theoretical study. Sept. 22-25, 1986, Paper. 51 p. refs Implications for added damping requirements on a full scale rotor (MBB-UD-485-86-PUB) are identified. Author The European Future Advanced Rotorcraft (Eurofar) program, concerned with the development of a tilt-rotor aircraft by a group A87-43471 # of European aircraft manufacturers,, is examined. The advantages LIGHTNING PROTECTION ACTIVITY IN THE DEVELOPMENT and limitations of helicopters, and methods for extending these OF A NEW HELICOPTER limitations and increasing the operational efficiencies of the GIUSEPPE MESCHI (Costruzioni Aeronautiche Giovanni Agusta helicopter are discussed. The manufacturers propose to design a S.p.A., Cascina Costa, Italy) DGLR, European Rotorcraft Forum, 10-ton-class tilt-rotor aircraft that consists of an aircraft fuselage 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, with a fixed wing having a low aspect ratio and wing-tip mounted Paper. 17 p. tilting rotor. The aircraft is to weigh 10,200 kg, have a useful load The design and test procedures used to minimize the effects of 4,010 kg, an empty-to-gross weight ratio of 0.607, and a take-off of lightning on helicopters (especially those with many composite weight of 13,000 kg. Diagrams of the proposed tilt-rotor aircraft structures) are discussed. The division of an aircraft surface into and its operating modes, and graphs explaining the expected zones on the basis of lightning susceptibility called for by performance of the aimraft are presented. I.F. MIL-STD-1757 is reviewed and illustrated with a drawing; the peak, intermediate, continuing, and restrike currents to be survived are presented in tables; protective techniques against direct effects (metallic meshes, coatings, or laminae) and against indirect effects (shielding, terminal protection devices, and grounding) are A87-44256 described; and high-voltage and current-flow test procedures for HELICOPTER ROTOR ICING PROTECTION METHODS components and complete aircraft are outlined. T.K. H. J. COFFMAN, JR. (Bell Helicopter Textron, Inc., Fort Worth, TX) American Helicopter Society, Journal (ISSN 0002-8711), vol. A87-43472# 32, April 1987, p. 34-39. refs AIR CYCLE ENVIRONMENTAL CONTROL SYSTEM FOR Current production helicopter rotor icing protection systems and HELICOPTERS - A TRADE-OFF STUDY most systems now under development use electrothermal deicing. A. MANNINI, G. SARRI (-Torino, Turin, Italy), and V. This paper reviews other types of rotor icing protection systems MARCHIS (Torino, Politecnico, Turin, Italy) DGLR, European for which interest has been shown. In searching for icing protection Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, systems that weigh and cost less than the electrothermal deicing Sept. 22-25, 1986, Paper. 16 p. method, investigators have looked at fluid anti-icing, pneumatic In the present comparative analysis of air-cycle helicopter deicing, electro-impulse deicing, and electro-vibratory deicing environmental control systems (ECSs), an attempt is made to define methods. Several of these alternative blade icing protection the most suitable system configuration on the basis of aircraft systems show promise for future development. Author

654 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE

A87-44577 engine operability and integrated controls. It is noted that the PROSPECTSFORTHEUSEOFCOMPOSITESIN CIVIL selection of the preferred approach to engine/airframe integration AIRCRAFT depends largely on the installation to minimize supersonic drag A. W. KITCHENSlDE (British Aerospace, PLC, Weybridge, and on the achievement of reliable operation for required operating England) IN: High tech - The way into the nineties; Proceedings modes, including transition of engine and aircraft, ground effects, of the Seventh International SAMPE Conference, European and all flight maneuvers. V.L. Chapter, Munich, West Germany, June 10-12, 1986 . Amsterdam and New York, Elsevier Science Publishers, 1986, p. 15-28. A87-45237# The civil-aircraft primary-structure use of carbon-fiber-reinforced STOL CHARACTERISTICS OF A TACTICAL AIRCRAFT WITH composites is presently assessed on the basis of a technology NOZZLES demonstration program concerned with the production of a BAe ROBERT F. TAPE (Rolls-Royce, Inc., Atlanta, GA), RONALD J. 125 commuter-airliner wing structure. At the structural loading levels GLIDEWELL (USAF, Aero Propulsion Laboratory, Wright-Patterson that exist in small civil-aircraft wings and in empennage structures, AFB, OH), and DAVID E. BERNDT (Rockwell International Corp., which are of the order of 1.0 MN/m, these composites can furnish Los Angeles, CA) AIAA, SAE, ASME, and ASEE, Joint Propulsion worthwhile weight savings relative to aluminum alloys. At the higher Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 10 p. Ioadings that are characteristic of larger aircraft wing structures, (AIAA PAPER 87-1835) cost-effectiveness relative to emerging AI-Li alloy structures will An evaluation has been made of tactical aircraft exhaust system require the use of higher-modulus fibers. O.C. thrust vectoring concepts capable of improving short field operational capabilities in next-generation fighters. An advanced STOL combat aircraft, configured on the basis of study results, A87-44594 exhibits field length requirements of less than 1000 feet, using A310-300 CFRP FIN - DAMAGE TOLERANCE DEMONSTRATION the vectored bypass flow from an unmixed engine as a O. GOEKGOEL (Messerschmitt-Boelkow-Blohm GmbH, Munich, source of propulsive lift. The nozzles are located close to the West Germany) IN: High tech - The way into the nineties; center of gravity, minimizing the effect of thrust vectoring on pitch Proceedings of the Seventh International SAMPE Conference, characteristics. Two exhaust nozzle concepts are selected for European Chapter, Munich, West Germany, June 10-12, 1986 . detailed study in wind-tunnel tests. O.C. Amsterdam and New York, Elsevier Science Publishers, 1986, p. 273-286. refs A87-45300"# National Aeronautics and Space Administration. An account is given of the damage-tolerance philosophy applied Langley Research Center, Hampton, Va. to the certification process of an airliner's CFRP empennage INTEGRATION EFFECTS OF PYLON GEOMETRY AND structure box, with a view to general requirements encountered in REARWARD MOUNTED NACELLES FOR A HIGH-WING the A310-300 aircraft, design principles and allowables, structural TRANSPORT test methods, damage and defect types, and inspection and repair JOHN R. CARLSON and MILTON LAMB (NASA, Langley Research philosophies. Impact, bird-strike, APU-rotor-failure, and lightning- Center, Hampton, VA) AIAA, SAE, ASME, and ASEE, Joint strike damage consequences for the structure have been tested in Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. the course of certification. Four categories of defect and delamina- 11 p. refs tion size have been established for various elements of the struc- (AIAA PAPER 87-1920) ture. O.C. Results of a wind-tunnel study of the effect of pylon cross-sectional shape and tow angle on airplane drag and an A87-44704 aft-mounted nacelle are presented. The 1/24-scale wide-body DEVELOPMENT OF THE CHINOOK HELICOPTER ROTOR high-wing transport model was tested in the Langley 16-Foot BLADE DE-ICING SYSTEM Transonic Tunnel at free-stream Mach 0.7-0.8 and angles of attack KENNETH LUNN (Boeing Vertol Co., Philadelphia, PA) IN: from -3 to 4 degrees. A compression-type pylon is found to have Helicopter Rotor Icing Symposium, London, England, Jan. 14, 1986, the lowest drag at both Mach 0.7 and 0.8 and to be capable of Proceedings . London, Royal Aeronautical Society, 1986, p. suppressing the velocities in the inboard region of the pylon-wing 46-63. junction, reducing the extent of supersonic flow and the probability The design and development of a rotor deicing system for of flow separation. It is also shown that the D-shaped aft-mounted composite rotor blade equipped Chinook helicopters are described. nacelle has a low interference drag, as do previously tested circular Spanwise electrothermal deicing mats arranged in a 12-wire system nacelles in the same position. V.L. form the basis of the deicing system for the composite rotor blades. Diagrams of the location of the heaters on the rotor blade are A87-45302# presented. The system consists of an ice detector unit, the deicer ADVANCED FIGHTER THRUST REVERSER INTEGRATION FOR controller, two distributors, a pilot control panel, a development MINIMUM LANDING DISTANCE test panel, and an outside air temperature sensor; the operation CHRISTOPHER J. ANDERSON and MARTY K. BRADLEY of these components is discussed. A prototype of the deicing (Northrop Corp., Hawthorne, CA) AIAA, SAE, ASME, and ASEE, system was subjected to thermodynamic modeling, bench testing, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July flight and support tests, and thermal fatigue testing. The test data 2, 1987. 6 p. reveal that the electrothermal deicing system will allow composite (AIAA PAPER 87-1923) rotor blade helicopters to operate effectively in all levels of icing Thrust reversers are an effective means of reducing landing severity. I.F. groundroll distance, but their use and effectiveness are limited by the problem of exhaust plume reingestion into the inlet which A87-45158# causes undesirable thermal distortion for the engine. Canting the STOVL ENGINE/AIRFRAME INTEGRATION reverser discharge away from the inlet allows the reverser to be R. L. BUCKNELL (Pratt and Whitney, West Palm Beach, FL) AIAA, used longer before reingestion, but it also reduces the effective SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San reverse thrust. This paper investigates the effect of varying reverser Diego, CA, June 29-July 2, 1987. 6 p. discharge angles on landing groundroll distance for an advanced (AIAA PAPER 87-1711) fighter configuration in the 30,000-40,000 Ib landing weight class. Considerations for engine/airframe integration are examined Utilizing the results of water tunnel testing, along with full and with reference to four single-engine, advanced short takeoff, vertical partial reverse engine data, landing groundroll distances are landing supersonic aircraft concepts (vectored thrust, remote predicted for various reverser discharge angles. The analysis augmentor lift system, tandem fan, and ejector lift). In particular, indicates that uncanted thrust reversers can reduce the landing attention is given to typical propulsion considerations, engine cycle groundroll from 5,000 feet to approximately 2,000 feet and that selection trades, fore and aft combustor nozzle integration, and canting the reversers outboard away from the vertical axis allows

655 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE themto beusedfor a longer portion of the groundroll and can technologically advanced and powerful PW125B engines of 2500 further reduce the landing groundroll to distances as short as shp maximum power. Attention is presently given to the design 1,000 feet. Author features and flight handling qualities of the aircraft. Power increases with the throttle are noted to have greater effect on longitudinal A87-45335# stability with the more efficient propellers now used. For the same THRUST/DRAG ACCOUNTING FOR AEROSPACE PLANE fuel capacity as the F.27, the range of the Fokker 50 at economic VEHICLES cruise speed is more than 30 percent greater, due to the economy R. P. C. LEHRACH (United Technologies Research Center, East of the new engines. O.C. Hartford, CT) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 7 p. A87-45648 (AIAA PAPER 87-1966) SEASTAR - GLASS, PLASTIC, AND TRADITION Three approaches for representing the net axial force of highly ALAN POSTLETHWAITE and JANICE LOWE Flight International integrated hypersonic engine/vehicle configurations, such as the (ISSN 0015-3710), vol. 131, June 1987, p. 38-41. Aerospace Plane, in terms of engine thrust and vehicle drag are The traditional amphibious aircraft-design problems posed by discussed. Two approaches are found to be preferable, one in production start-up costs and airframe corrosion are addressed in which engine performance is generated from the local inlet flow the CD.2 aircraft presently discussed through the employment of field conditions and the entire vehicle forebody is treated as vehicle GFRP throughout the airframe. The primary structure is built up drag, and one in which engine performance is generated from the by means of simple and comparatively inexpensive hand lay-up free-stream conditions and the inlet-flow-wetted surface of the methods developed by the sailplane construction industry. The forebody is subtracted from vehicle drag considerations. Other result is a near-S5 million 13-passenger aircraft employing two than field forces, only the pressure-area and shear as applied to turboprop engines in tandem configuration above the fuselage, the surfaces of the system act to produce system motion. It is for which sales of 250 units over a 10-year period are projected. suggested that the two portions of the total system surface The fuselage features a flat belly for aquaplaning, in marked constituting the vehicle and propulsion system must be defined, contrast to the more conventional v-section hull of other amphibious and that the selected engine control volume should bound the designs. O.C. defined engine surface. R.R. A87-46312 A87-45400# THE NEW SOVIET FIGHTERS - HOW GOOD ARE THEY? FLIGHT TEST AND EVALUATION OF PROPULSION SYSTEM BILL SWEETMAN Interavia (ISSN 0020-5168), vol. 42, June OPERABILITY CHARACTERISTICS 1987, p. 577-580. GARY P. MOE, RONALD M. DAVINO (USAF, Flight Test Center, Performance capability projections, industrial production level Edwards AFB, CA), and ED GRAHAM (ED Graham and Associates, evaluations, and weapons effectiveness assessments are Lancaster, CA) AIAA, SAE, ASME, and ASEE, Joint Propulsion presented for the Soviet MiG-29, MiG-31, Su-27, and Su-25 fighter Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 12 p. aircraft. Twin-turbofan propulsion systems, large radar antennas, (AIAA PAPER 87-2092) and two-stage, long-range interception missiles, typified by the Propulsion system test methodologies are examined with AA-10 that will be used by both the Su-27 long-range escort/air emphasis on the testing of the afterburning turbofan engine. In superiority fighter and the MiG-29 frontal aviation/multirole fighter, particular, attention is given to instrumentation, data acquisition are characteristic of this entire generation of Soviet fighter design. and display, flight test maneuvers, analysis, and coordination with The MiG-31 is an interceptor capable of carrying four AA-9 missiles, other facilities. The discussion also covers investigations of which are comparable in size and range to the F-14's AIM-54 , gas generator aerodynamic instabilities, internal long-range radar-guided missiles. The AA-11, an In-guided acoustic disturbances, and digital control strategies. V.L. dogfighting missile comparable to the Sidewinder, will soon become available. Although unprecedented yearly production rate A87-45452# reductions have been observed for these aircraft, the MiG-29 is HALE THERMAL BALANCE expected to reach mass production rates of 300 aircraft/year in EDWARD P. PETKUS and ROGER W. GALLINGTON (Science the near future. O.C. Applications International Corp., Seattle, WA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, A87-46313 June 29-July 2, 1987. 8 p. FLYING THE CF-18 HORNET (AIAA PAPER 87-2172) MARK LAMBERT Interavia (ISSN 0020-5168), vol. 42, June This paper describes some of the unique challenges in balancing 1987, p. 595-598, 600. the thermal loads in High Altitude Long Endurance (HALE) aircraft. A cockpit-systems, flight-handling qualities, and maneuvering HALE aircraft operate in a low density and a low velocity performance evaluation is presented for the RCAF's CF-18 version environment making heat rejection difficult. HALE aircraft must of the F/A-18 U.S. Navy fighter. Attention is given to the fly-by-wire also operate through several diurnal cycles, each creating a unique control augmentation and stabilization system, which encompasses thermal environment. An optimal HALE aircraft's thermal system autopilot and autothrotUe functions. The fighter can be flown and requires several novel concepts to overcome these challenges. maneuvered in level flight at up to 35-deg angle-of-attack without The paper describes some concepts of minimizing heat loads and , and, although electronically limited to 7.33 g at low of rejecting waste heat effectively. Heat rejection concepts such weight conditions, has been flown at 11 g during an emergency as; surface heat exchangers, fuel tank heat sinks, and conventional maneuver. During air-to-air combat, sufficient flight-related radiators, are discussed relative to their respective merits and information appears on the radar screen to allow the pilot to handle weaknesses. Heat sources such as; reciprocating engines, the aircraft without additional reference to the HUD. O.C. turbochargers, and avionics, are discussed relative to their impact on vehicle performance. Some relative measures of performance A87-46314 are derived that allow HALE system designers to describe sensible PROVING THAT AVANTI STANDS FOR PROGRESS integrated concepts. Author MARC GRANGIER Interavia (ISSN 0020-5168), vol. 42, June 1987, p. 645-647. A87-45647 A large part of the P-180 Avanti twin-turboprop aircraft's flight FOKKER 50 - PEDIGREE WITH POWER envelope has been explored, and the prototype is currently flying HARRY HOPKINS Flight International (ISSN 0015-3710), vol. without weight restrictions in actual certification conditions. The 131, June 1987, p. 23-27. prototype is noted to have broken the 700 km/hr barrier, reaching The Fokker 50 commuter aircraft is a follow-on development 722 km/hr in level flight at 35,000 ft. Fuel consumption of the highly successful F.27-500, incorporating the more measurements have indicated that the Avanti will have a 3700-km

656 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

range when cruising at 590 km/hr at 41,000 ft with four passengers among the three versions extends to engines, transmissions, rotors, on the basis of 2510 Ib of fuel. On the strength of these encouraging most of the airframes, and numerous systems; the flight test program results, the manufacturer has decided to proceed engines are T700/CT7s. The main rotors employ wide-chord tips with the manufacture of an initial batch of 12 aircraft. O.C. in order to increase lift, reduce drag, and delay stall, on the basis of a combination of sweep, thickness, area, and vortex effects. A87-46326# The commercial version will accomodate 30 passengers. The CONCEPT FOR A NEW-GENERATION primary structure employed is almost entirely metallic. O.C. REGIONAL AIRLINER FRIEDHELM ZIMMER Dornier-Post (English Edition) (ISSN A87-46735 SOVIET HELICOPTER DEVELOPMENT 0012-5563), no. 2, 1987, p. 12-17. The design of the Do 328 is described. The requirements for ELFAN AP REES Aerospace (ISSN 0305-0831), vol. 14, June the aircraft include high operation economy and an optimum 1987, p. 9-18. price/performance ratio; the aircraft is in the 11-ton class and A development history and performance trend evaluation is has an engine performance requirement of about 2 x 1,700 shp. presented for Soviet helicopters produced by the Mil and Kamov The basic configuration of the aircraft is high wing, which has the design bureaus. Attention is given to the Mi-6 and Mi-26 cargo potential to increase the fuel capacity by about 500 kg, and the helicopters, the Mi-8 passenger helicopter, and the Mi-24 'Hind' tail unit has a T configuration. The pressurized fuselage consists troop transport/helicopter gunship, which has come to be of a cylindrical pipe in the cabin area, a conical fuselage front considered the most effective combat helicopter of the section with the cockpit, and a conical fuselage tail section with a counterinsurgency and antiarmor type. The Mi-24 will be stepped, large volume baggage compartment. Consideration is supplemented in current service by the smaller Mi-28 'Havoc'. given to reducing cabin noise, the use of CRFP composites and Kamov designs are of the contrarotating rotor type, which obviates AILi for aircraft parts, the avionics system of the aircraft, and the a tail rotor, and have appeared in both civil-aviation and naval cabin design. Diagrams of the aircraft are presented. I.F. variants. The gathering of Western helicopter design-related information, the development of Soviet helicopter turboshaft A87-46327# powerplant gearboxes, and the emphasis placed on attack TECHNOLOGICAL ASPECTS IN PREPARING THE helicopter development, are also discussed. O.C. DEVELOPMENT OF REGIONAL AIRLINERS KARL-HEINZ DOST Dornier-Post (English Edition) (ISSN A87-46870# FLYING WING COULD STEALTHILY REAPPEAR 0012-5563), no. 2, 1987, p. 18-21. The development of an optimum aerodynamic fuselage design WILLIAM R. SEARS (Arizona, University, Tucson) Aerospace and the application of the fiber composite construction method to America (ISSN 0740-722X), vol. 25, July 1987, p. 16-19. the development of the fuselage are examined during the new The development of the flying-wing aircraft, in particular the fuselage technology program for the Do 328. Two fuselage XB-35 bomber that needed to carry a 10,000 Ib bomb load and configurations, C2 and D2, were developed. The C2 has have a range of 10,000 miles, is discussed. The span-loading wing/fuselage transition section design and the D2 configuration theory for distributing the weight and inertia loading along the is wing and landing gear integrated into the pressurized fuselage; span, which is the major advantage of the flying wing, is described. these two configurations are analyzed, tested, and compared. It is The methods used to obtain high lift and momentum equilibrium determined that the D2 configuration is the better design. The during landing and takeoff of the XB-35 are examined. use of fiber composites in the primary structures of the pressurized Consideration is given to the testing of a flying-wing model and fuselage is studied, testing various fiber/resin (epoxy) systems. the XB-35. The testing revealed the good stability and controllability Configuration studies of trade-offs between aerodynamics and of a flying-wing aircraft. I.F. structure are discussed. Future research in the areas of acoustical efficiency, power plant configurations, and wing designs is A87-47009"# National Aeronautics and Space Administration. planned. I.F. Langley Research Center, Hampton, Va. INTERDISCIPLINARY OPTIMUM DESIGN A87-46362 JAROSLAW SOBIESZCZANSKI-SOBIESKI (NASA, Langley TRENDS IN THE AEROELASTIC ANALYSIS OF COMBAT Research Center, Hampton, VA) and RAPHAEL T. HAFTKA AIRCRAFT [TENDANCES ACTUELLES DE L'ANALYSE (Virginia Polytechnic Institute and State University, Blacksburg, AEROELASTIQUE DES AVlONS MILITAIRES] VA) NATO Advanced Study Institute on Computer Aided Optimal C. PETIAU and S. BRUN (Avions Marcel Dassault Breguet Aviation, Design, Troia, Portugal, June 29-July 11, 1986. 36 p. refs Saint-Cloud, France) L'Aeronautique et rAstronautique (ISSN Problems related to interdisciplinary interactions in the design 0001-9275), no. 122, 1987, p. 10-25. In French. refs of a complex engineering systems are examined with reference Following a discussion of the general principles of the structural to aerospace applications. The interdisciplinary optimization finite element analysis of aeroelastic coupling and the simplifying problems examined include those dealing with controls and assumptions leading to static aeroelasticity, the ELFINI program structures, materials and structures, control and stability, structure of aircraft structural analysis is considered. The data management and aerodynamics, and structure and thermodynamics. The approach relies on the load-basis and aerodynamic form basis discussion is illustrated by the following specific applications: principles, and permits computation of the finite element solutions integrated aerodynamic/structural optimization of glider wing; and the theoretical aerodynamic analysis independently of the less optimization of an antenna parabolic dish structure for minimum costly aeroelastic and flight maneuver computations. The present weight and prescribed emitted signal gain; and a multilevel approach deals effectively with flight-measurement model optimization study of a transport aircraft. V.L. adjustments and the optimization and differentiation of the aerodynamic coefficients, while it is less able to treat the static N87-25276"# National Aeronautics and Space Administration. and dynamic nonlinear effects. R.R. Marshall Space Flight Center, Huntsville, Ala. B-57B GUST GRADIENT PROGRAM A87-46371 DENNIS W. CAMP In NASA. Langley Research Center Wind EH.101 - THE HELICOPTER MATURES Shear/Turbulence Inputs to Flight Simulation and Systems GRAHAM WARWICK Flight International (ISSN 0015-3710), vol. Certification p 117-124 Jul. 1987 131, June 13, 1987, p. 83-86, 88, 90. Avail: NTIS HC A12/MF A01 CSCL 01C The three-engined EH-101 state-of-the-art helicopter is the The NASA B-57B Gust Gradient Program (GGP) is a NASA result of a British-Italian collaborative effort, and will be marketed multicenter program. The program objectives are presented. The in the forms of three distinct variants for troop transport, ASW, primary objective is to get wind gust data which can be used in and offshore oil rig-servicing/civilian commuting. Commonality new design criteria for aeronautical systems. The GGP data could

657 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

also be used to provide turbulence information for use in simulation N87-25316# Messerschmitt-Boelkow-Blohm G.m.b.H., Hamburg programs. This program is outlined. Author (West Germany). DESIGN OF A COMPOSITE TAIL FOR THE AIRBUS A-320 H. BRENNEIS 1986 24 p Presented at the 15th International N87-25281"# Calspan Corp., Buffalo, N. Y. Council of the Aeronautical Sciences (ICAS) Congress, London, MILITARY SPECIFICATIONS England, 7-12 Sep. 1986 PHILIP REYNOLDS In NASA. Langley Research Center Wind (MBB-UT-12-86; ICAS-86-4.3.5; ETN-87-99958) Avail: Issuing Shear/Turbulence Inputs to Flight Simulation and Systems Activity Certification p 181-195 Jul. 1987 A CFRP tail was built for the A-320 aircraft. The modular design Avail: NTIS HC A12/MF A01 CSCL 01C involves wrapping the CFRP fabric around metallic cores, pressed The current situation relative to the military specification is that together to obtain the desired geometry. The required thicknesses there is not one specific model of turbulence which people are are obtained by different thermal expansion between the metal using. Particular disagreement exists on how turbulence levels will cores and the bonding tool made from CFRP-prepreg during the vary with qualitative analysis. It does not tie one down to specifics. cure cycle at 125 C and 10 bar. No repairs caused by cracks or When it comes to flying quality specifications, many feel that one delaminations are reported after 120,000 life cycle tests, i.e., the should stay with the definitions of the Cooper-Harper rating scale equivalent of 3 aircraft life cycles. ESA but allow the levels to shift depending on the level of turbulence. There is a ride quality specification in the MIL-SPEC having to do with flight control systems design that is related to a turbulence N87-25317# Messerschmitt-Boelkow-Blohm G.m.b.H., Hamburg model. This spec (MIL-F8785C) and others are discussed. (West Germany). Author A310-300 CFRP FIN DAMAGE TOLERANCE DEMONSTRATION O. GOEKGOEL 1986 23 p Presented at the 7th International Conference SAMPE European Chapter, Munich, West Germany N87-25284"# Alabama Univ., University. Dept. of Aerospace (MBB-UT-015/86; ETN-87-99959) Avail: Issuing Activity Engineering. An approach for the determination of appropriate validation HELICOPTER-V/STOL DYNAMIC WIND AND TURBULENCE loads for given inspection intervals to demonstrate acceptable low DESIGN METHODOLOGY level of risk in service of CFRP fin is outlined. The inspection J. EARL BAILEY In NASA. Langley Research Center Wind intervals for metal fins are applied to the CFRP fin. ESA Shear/Turbulence Inputs to Flight Simulation and Systems Certification p 209-216 Jul. 1987 Avail: NTIS HC A12/MF A01 CSCL 01C N87-25318# Aeronautical Systems Div., Wright-Patterson AFB, Aircraft and helicopter accidents due to severe dynamic wind Ohio. and turbulence continue to present challenging design problems. CORRELATION OF B-1 FLIGHT TEST SUBJECTIVE The development of the current set of design analysis tools for a ASSESSMENTS AND SOME RIDE QUALITY/VIBRATION aircraft wind and turbulence design began in the 1940's and 1950's. EXPOSURE CRITERIA Final Report, Mar. 1982 - Jun. 1985 The areas of helicopter dynamic wind and turbulence modeling JOHN W. RUSTENBURG May 1986 103 p and vehicle response to severe dynamic wind inputs (microburst (AD-A179844; ASD-TR-85-5015) Avail: NTIS HC A06/MF A01 type phenomena) during takeoff and landing remain as major CSCL 01C unsolved design problems from a lack of both environmental data This study reviews several methods for describing the intensity and computational methodology. The development of helicopter of a vibration of ride-quality environment and its effect and comfort, and V/STOL dynamic wind and turbulence response computation proficiency and fatigue. These methods are applied to vibration methology is reviewed, the current state of the design art in industry environments encountered during B-1 low-altitude, high-speed flight is outlined, and comments on design methodology are made which tests. The resulting vibration environment/ride quality descriptions may serve to improve future flight vehicle design. Author are correlated with qualitative assessments of turbulence levels and impact on performance and discomfort obtained from the crew. This correlation provides an evaluation of the sensitivity of N87-25314 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn the methods in predicting the effects of variation in the vibration (West Germany). Space Div. environment. To evaluate the precision of the methods in predicting A MODEL TEST VEHICLE FOR HYPERSONIC AEROSPACE ride quality ratings for a high-speed low-altitude environment, the SYSTEMS DEVELOPMENT qualitative assessments of the crew are compared to ratings, H. GRALLERT, G. CUCINELLI, and M. RIGAULT 1986 13 p boundaries or limits established by the different methods. GRA Presented at the 37th International Astronautical Federation Congress on Space: New Opportunities for All People, Innsbruck, Austria, 4-11 Oct. 1986 Previously announced in IAA as N87-25320"# National Aeronautics and Space Administration. A87-15882 Submitted for publication Langley Research Center, Hampton, Va. (MBB-UR-875/86; IAF-86-125; ETN-87-99937) Avail: Issuing A MULTI-BODY AIRCRAFT WITH AN ALL-MOVABLE CENTER Activity FUSELAGE ACTIVELY CONTROLLING FUSELAGE PRESSURE The use of a hypersonic test vehicle in the Hermes space DRAG Patent Application shuttle development program is proposed. The technical, safety, RICHARD M. WOOD, inventor (to NASA) 12 Feb. 1987 16 p and cost justifications of such an approach are outlined. The MAIA (NASA-CASE-LAR-13511-1 ; US-PATENT-APPL-SN-013801 ) 1:3 scale model of Hermes is described. ESA Avail: NTIS HC A02/MF A01 CSCL 01C A multi-body aircraft with an all-movable center fuselage which translates relative to two side fuselages is described. At subsonic N87-25315# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich and transonic flight the center fuselage is in a forward position. (West Germany). Helicopter Div. At supersonic speeds the center fuselage moves aft so as to DESIGN FOR REPAIRABILITY OF HELICOPTER ROTOR ensure optimum aerodynamic interference at particular Mach BLADES numbers. This provides an increased shock strength and greater M. HAHN 1986 17 p Presented at the 62nd AGARD Meeting surface areas so the significant reductions in zero-lift wave drag of the Structures and Materials Panels Specialists' Meeting, Oslo, can be achieved. This concept allows for a significant increase in Norway, 14-18 Apr. 1986 the wing aspect ratio which would improve high-lift performance (MBB-UD-491/86; ETN-87-99931) Avail: Issuing Activity at all speeds without incurring a significant supersonic zero-lift Repairability criteria for helicopter main rotors are described, wave drag penalty. In additions, an improved low-fineness ratio, and repair procedures are outlined. Service experience with main high-speed performance is achieved at all speeds and for all flight and tail rotors is reviewed. ESA conditions. NASA

658 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

N87-25321"#National Aeronautics and Space Administration. N87-26037"# Virginia Polytechnic Inst. and State Univ., Langley Research Center, Hampton, Va. Blacksburg. Dept. of Chemistry. INTEGRALLY-STIFFENED CRASH ENERGY-ABSORBING FACTORS AFFECTING THE STICKING OF INSECTS ON SUBFLOOR BEAM STRUCTURE Patent Application MODIFIED AIRCRAFT WINGS Semiannual Report, 16 Jun. - 30 GARY L. FARLEY, inventor (to NASA) 19 May 1987 12 p Dec. 1986 (NASA-CASE-LAR-13697-1; US-PATENT-APPL-SN-051426) O. YI, M. R. CHITSAZ-Z, N. S. EISS, and J. P. WIGHTMAN 3 Avail: NTIS HC A02/MF A01 Jun. 1987 32 p An integrally-stiffened crash energy-absorbing subfloor beam (Contract NAG1-300) is disclosed which provides increased energy absorption efficiency (NASA-CR-180957; NAS 1.26:180957) Avail: NTIS HC A03/MF and ease of fabrication while uncoupling the design parameters A01 CSCL 01C for energy absorption and structural stiffness. The invention Past studies have shown that the surface energy of a polymer comprehends a beam web integrally stiffened by an assembly of coating has an important effect on the sticking of insects to the vertically oriented tubular stiffeners, interconnected by vertical flat surface. However, mechanical properties of polymer coatings such plates and top and bottom beam caps. The tubular stiffeners are as elasticity may also be important. A further study is suggested of arbitrary cross-sectional shape. Typical materials for the beam using polymer coatings of known surface energy and modulus so are any ductile metallic (aluminum) or non-metallic materials or that a better understanding of the mechanism of the sticking of fiber reinforced composite material (Graphite/Epoxy and insects to surfaces can be achieved. As the first step for the Kevlar/Epoxy). A subfloor structure is built by arranging the beams study, surface analysis and road tests were performed using into a grid or latticework configuration such that the flat plates elastomers having different energies and different moduli. The between the tubular stiffeners are oriented vertically. A rigid floor number of insects sticking to each elastomer was counted and surface is attached over this grid of beams to complete a lower compared from sample to sample and with a control (aluminum). fuselage structure. NASA An average height moment was also calculated and comparisons made between samples. Author

N87-26039# Deutsche Forschungs- und Versuchsanstalt fuer N87-26035"# Virginia Polytechnic Inst. and State Univ., Luft- und raumfahrt, Stuttgart (West Germany). Forschungs- Blacksburg. Dept. of Aerospace and Ocean Engineering. bereichs Werkstoffe und Bauweisen. SINGULAR TRAJECTORIES IN AIRPLANE CRUISE-DASH CANARD CONFIGURATIONS lENTEN - FLUGZEUGE] OPTIMIZATION M. MAILAENDER, M. DEGENER, H. DOEKER, H. HALD, H. P. KARL D. BILIMORIA and EUGENE M. CLIFF Jan. 1987 124 p SCHMIDT, and D. WETZEL 21 Feb. 1986 41 p In GERMAN (Contract NAG1-203) (ETN-87-99914) Avail: NTIS HC A03/MF A01 (NASA-CR-180636; NAS 1.26:180636) Avail: NTIS HC A06/MF Canard configurations were compared with conventional A01 CSCL 01C configurations. The static lateral stability and the directional stability The problem of determining cruise-dash trajectories is examined of canard and conventional configurations are summarized. for the case of time-fuel optimization using a linear combination Aerodynamic characteristics, such as the interactions between of time and fuel as the performance index. The trajectories consist control surfaces and wings, sweep, sideslip, profile, load of a transient arc followed by a steady-state arc. For cases where distribution, center-of-gravity range, trim, propulsion arrangement, the steady-state arc is flown with full throttle the associated skeletal and stalling behavior, are discussed for both configurations. The transient trajectories are also flow with full throttle, and the problems of a canard delta configuration are given. The cruise-dash points are approached monotonically in an asymptotic performances and maneuverability of the canard and conventional fashion. When the steady-state arc is flown at an intermediate configurations are compared. Development measures for military throttle setting, the transient trajectories follow a singular control aircraft in active control, aeroelastic tailoring, conformal stores law and exhibit a complex structure that is different from the carriage, mission adaptive wings, and thrust vectoring, are given. full-throttle transients. Addressing the question of optimality of the ESA steady-state arc, it was found that although steady-state cruise fails a Jacobi-type condition, steady-state cruise-dash can satisfy N87-26040 Stanford Univ., Calif. this condition if the emphasis on time is sufficiently large. The IDENTIFICATION OF A DYNAMIC MODEL OF A HELICOPTER outcome of the Jacobi test appears to be connected with the FROM FLIGHT TESTS Ph.D. Thesis eigenstructure of the linearized state-adjoint system. Author GARTH WILLIAM MILNE 1987 301 p Avail: Univ. Microfilms Order No. DA8707707 Techniques for identifying continuous models of dynamic systems were applied to the unstable longitudinal hover dynamics N67-26036"# Kansas Univ. Center for Research, Inc., Lawrence. of a CH-47B Chinook helicopter. The equation error method with Flight Research Lab. carefully filtered 7.18 Hz data produced good pitch transfer function AN EXPERIMENTAL INVESTIGATION OF DYNAMIC GROUND models. Frequency response plots for increasing order models EFFECT Final Report were used to determine the model order. The linear inter-sample PAl HUNG LEE, C. EDWARD LAN, and VINCENT U. MUIRHEAD equivalent produced better continuous models from identified Jan. 1987 83 p ARMA models than the zero order hold assumption. (Contract NAG1-616) Dissert. Abstr. (NASA-CR-180560; NAS 1.26:180560; CRINC-FRL-717-1) Avail: NTIS HC A05/MF A01 CSCL 01C N87-26041"# National Aeronautics and Space Administration. Sixty degree delta wing, F-106B, and XB-70 models with and Langley Research Center, Hampton, Va. without flap deflections were tested in static and dynamic ground EVALUATION OF INSTALLED PERFORMANCE OF A effect in the 36 by 51 inch subsonic wind tunnel at the University WING-TIP-MOUNTED PUSHER TURBOPROP ON A SEMISPAN of Kansas. Dynamic ground effect was measured with movable WING sting support. For flow visualization, a tufted wire grid was mounted JAMES C. PATTERSON, JR. and GLYNN R. BARTLEI-r Aug. on the movable sting behind the model. Tests results showed 1987 30 p that the lift and drag increments in dynamic ground effect were (NASA-TP-2739; L-16252; NAS 1.60:2739) Avail: NTIS HC always lower than the static values. Effect of the trailing-edge A03/MF A01 CSCL 01C flap deflections on lift increments was slight. The fuselage reduced An exploratory investigation has been conducted at the Langley the lift increments at a given ground height. From flow visualization Research Center to determine the effect of a wing-tip-mounted under static conditions, the vortex core was seen to enlarge as pusher turboprop on the aerodynamic characteristics of a semispan the ground approached. Author wing. Tests were conducted on a semispan model with an upswept,

659 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

untapered wing and an airdriven motor that powered an SR-2 N87-26834 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn high-speed propeller located on the tip of the wing as a pusher (West Germany). Unternehmensgruppe Transport- und propeller. All tests were conducted at a Mach number of 0.70 Verkehrsflugzeuge. over an angle-of-attack range from approximately -2 to 4 deg at a AIRCRAFT TECHNOLOGY OF THE NINETIES IN MBB Reynolds number of 3.82 x 10 to the 6th based on the wing PASSENGER AIRCRAFT PROJECTS [FLUGZEUGoTECHNOLO- reference chord of 13 in. The data indicate that, as a result of GIE DER 90ER JAHRE IN VERKEHRSFLUGZEUG-PROJEKTEN locating the propeller behind the wing trailing edge at the wing tip VON MBB] in the crossflow of the wing-tip vortex, it is possible to improve UWE GANZER In its Research and ueveiopment. propeller performance and simultaneously reduce the lift-induced Technical-Scientific Publications 1986 p 83-90 1986 In drag. Author GERMAN Presented at the DGLR-Jahrestagung, Munich, West Germany, 8-10 Oct. 1986 (MBB-UT-0021/86; DGLR-86-108) Avail: Issuing Activity N87-26042"# National Aeronautics and Space Administration. Problems arising in the application of propfan propulsion Langley Research Center, Hampton, Va. systems are treated. Methods for the design of laminar wings, OPTIMIZATION METHODS APPLIED TO THE AERODYNAMIC and the development of a wing made of carbon fiber reinforced DESIGN OF HELICOPTER ROTOR BLADES plastics are discussed. The research program for the development JOANNE L. WALSH, GENE J. BINGHAM, and MICHAEL F. RILEY of cockpits and flight control is presented. ESA (PRC Kentron, Inc., Hampton, Va.) May 1987 27 p Presented at the 26th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics and Materials Conference, Orlando, Fla., 15-17 Apr. 1985 Previously announced in IAA as A85-30245 (NASA-TM-89155; NAS 1.15:89155; AIAA-85-0644) Avail: NTIS 06 HC A03/MF A01 CSCL 01C Described is a formal optimization procedure for helicopter rotor blade design which minimizes hover horsepower while assuring AIRCRAFT INSTRUMENTATION satisfactory forward flight performance. The approach is to couple hover and forward flight analysis programs with a general-purpose Includes cockpit and cabin display devices; and flight instruments. optimization procedure. The resulting optimization system provides a systematic evaluation of the rotor blade design variables and their interaction, thus reducing the time and cost of designing A87-42812 advanced rotor blades. The paper discusses the basis for and SCAN STABILIZATION AND JITTER CONTROL FOR AN details of the overall procedure, describes the generation of AIRBORNE TELESCOPE advanced blade designs for representative Army helicopters, and M. A. FLOYD, C. A. LIN, and M. G. LYONS (Integrated Systems, compares design and design effort with those from the conventional Inc., Palo Alto, CA) IN: Acquisition, tracking, and pointing; approach which is based on parametric studies and extensive Proceedings of the Meeting, Orlando, FL, Apr. 3, 4, 1986 . cross-plots. Author Bellingham, WA, Society of Photo-Optical Instrumentation Engineers, 1987, p. 102-120. An evaluation is made of the primary considerations in the N87-26247# City Univ., London (England). Dept. of Mechanical development of high fidelity performance models for airborne Engineering. scanning telescopes, using a generic example to illustrate the HELICOPTER VIBRATION CONTROL: RECENT ADVANCES principles involved in such modeling. Due to the scan's ability to G. T. S. DONE In Vibration Inst., The Shock and Vibration reject low frequency sources of image jitter, the scan motion itself Digest, volume 18, no. 8 p 13-17 Aug. 1986 is rarely the cause of low system performance; instead, acoustic Avail: NTIS HC A05/MF A01 and base motion power spectra in an open aircraft cavity create Recent advances in the control of helicopter vibration are large image jitter amplitudes that are only partially attenuated by described and associated literature is reviewed. Vibration absorbers the scan and subsequent TDI signal processing. The modification and isolators, direct rotorcontrol, structural design and modification, of TDI intervals, or the number of pixels, can improve jitter rejection and vibration studies are considered. Author if changes in sensitivity and/or range can be accommodated. O.C.

N87-26833 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn (West Germany). EULER SOLUTION FOR A COMPLETE FIGHTER AIRCRAFT AT A87-43375 SUB- AND SUPERSONIC SPEED TESTING AUTOMATED GROUND COLLISION AVOIDANCE ALBRECHT EBERLE and KENT P. MISEGADES (Cray Research, SYSTEMS ON THE AFTIIF-16 Inc., Mendota Heights, Minn.) In its Research and Development. JOHN D. HOWARD and MARK A. SKOOG (USAF, Flight Test Technical-Scientific Publications 1986 p 73-82 1986 Presented Center, Edwards AFB, CA) Cockpit (ISSN 0742-1508), Jan.-Mar. at the AGARD Symposium on Applications of Computational Fluid 1987, p. 5-13. Dynamics in Aeronautics, Aix-en-Provence, France, 7-10 Apr. The testing of an automated ground collision avoidance (GCA) 1986 system, consisting of air-to-air and air-to-surface autorecovery, on (MBB-LKE-122-S/PUB/234) Avail: Issuing Activity the AFTI/F-16 is described. The AFTI/F-16 GCA system is A high resolution Euler code applied to air-flow calculations composed of a G-induced loss-of-consciousness and spatial-dis- behind a fighter-type aircraft is described. It features a orientation autorecovery system applicable to medium and high Godunov-type averaging procedure based on the eigenvalue altitudes and a low-altitude GCA system based on pilot selected analysis of the Euler equations, by means of which the fluxes are above ground-level-altitudes. The effects of dive angle, airspeed, evaluated at the finite volume faces separating constant sets of bank angle, roll rate, and load factor on the performance of the flow variables on either side. The procedure is third-order accurate systems are investigated. It is determined that sensor performance and locally preserve monotonic, thus avoiding the drawbacks of varies with altitude, and the best performance is possible at the global total-variation-diminishing schemes. The grid generation for lowest altitudes. Various uses of future GCA systems, such as complex configurations is performed from solutions of linear low-altitude manual maneuvering and an advanced automated biharmonic equations with only one parameter, prescribed by the maneuvering attack system are discussed. The use of incremental program user. The vector computer performance of the explicit run-by-run analysis, remotely piloted vehicles, or remote real-time and implicit program versions is discussed. ESA modeling for future testing of GCA systems is proposed. I.F.

660 06 AIRCRAFT INSTRUMENTATION

A87-43404# maintainability, system reliability, and testing) and costs (purchasing, EH101 COCKPIT DESIGN maintenance, spare parts, technical documentation, training, and G. BARTON, J. REVELL, and G. WEBSTER (Westland Helicopters, ground support equipment). After a short description of the status Ltd., Yeovil, England) DGLR, European Rotorcraft Forum, 12th, of technological integration, hardware, and software standardization Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. available to date on avionic systems, a demonstration of the 18p. effectiveness of the new maintenance philosophy and concepts This paper describes the work undertaken on the EH101 'all (elimination of the second maintenance level) is given. The results " CRT' cockpit design from initial conception through to system derived can be extended to naval and ground defense systems. design, detailed format development and proposed certification Author programme covering the approach to the many topical issues such as power systems formats, integrity, reversion, software certification and the problems of three engine instrumentation. Described are the trade-off studies on weight, screen size, configuration and A87-43470# flexibility. The resulting selected system is described, including EMI-FAULT PREVENTION AND SELF RECOVERY OF DIGITAL architecture, interfaces and modes of operation including reversion. FLIGHT CONTROL SYSTEMS The work undertaken on format development particularly the power MICHAEL STOCK (Messerschmitt-Boelkow-Blohm GmbH, Munich, system displays with the problems of instrumentation for three West Germany) DGLR, European Rotorcraft Forum, 12th, engines, torque margin and hover formats is covered. The proposed Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. certification programme is described before finally drawing 20 p. conclusions from the work undertaken to date and discussing It is the aim of this paper to show ways to achieve system possible future enhancements to the EH101 Cockpit Electronics reliability and survivability for microcomputers in complex flight Display System. Author critical applications. Microcomputer systems failures caused by EMI and their impact on flight control systems is addressed. Also A87-43437# addressed are ways to maintain system reliability in electromagnetic A PROMISING LOW SPEED AIR DATA SYSTEM FOR contaminated environment and ways to ensure self recovery after HELICOPTERS EMI-caused faults. In conclusion, a digital flight-control system, J. MANDLE (Crouzet, S.A., Division Aerospatiale, Valence, designed with respect to EMI problems and flight-tested on a BK France) DGLR, European Rotorcraft Forum, 12th, 117, is presented. Author Garmisch-Partenkirohen, West Germany, Sept. 22-25, 1986, Paper. 21 p. The principle of operation, instrumentation, and performance A87-44727 of CLASS, a set of algorithms and hardware developed for the ENGINEERING AND HUMAN VISUAL CONSIDERATIONS IN French defense department to calculate the (low) bidirectional DEVELOPMENT OF A FIBRE OPTIC HELMET MOUNTED airspeed of a helicopter using data from conventional pneumatic DISPLAY sensors, are discussed and illustrated with diagrams, drawings, B. L. WELCH and R. KRUK (CAE Electronics, Ltd., Montreal, and graphs. Calibration is performed using the truck-mounted Canada) IN: Advances in flight simulation - visual and motion anemometer scheme proposed by Mandle and Weiss. In flight systems; Proceedings of the International Conference, London, tests performed at Bretigny during 1984, the CLASS equipment England, Apr. 29-May I, 1986. London, Royal Aeronautical Society, was shown to give accurate results in stabilized flights (standard 1986, p. 295-313. deviation below 3 kts) and transient maneuvers. T.K. The design requirements and development of a fiber optic helmet-mounted display (FOHMD) are described. The FOHMD is A87-43439# applicable in ground-based and airborne operational and training A NEW METHOD OF ANALYTICAL EVALUATION OF devices. Methods for developing a helmet display that has a field HELICOPTER TRUE AIRSPEED of view of 100 deg horizontal x 60 deg vertical, with separate W. HASSENPFLUG (Litton Technische Werke, Freiburg, West eyepieces which have an overlap of 25-40 deg, and a resolution Germany) and R. SCHWAEBLE (Krupp Atlas Elektronik GmbH, of about 1 arcmin/pixel are discussed. The FOV and resolution West Germany) DGLR, European Rotorcraft Forum, 12th, requirements determine the hardware characteristics. Luminance Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. levels close to normal daylight levels are determined by combining 21 p. refs optical characteristics of display devices, relay optics between Due to rotor-induced downwash and limited resolution, the display and fiber optic cables, the transmission of fiber optic cables, classical air-data computation utilizing pressure-differential and and the transmission of helmet optics. Various devices for the temperature measurements is not applicable to the helicopter color CRTs are examined. Consideration is given to factors which low-airspeed range (below 20 m/s). In order to overcome this affect performance: the exit pupil, image stability, and eye tracking problem, several approaches have been made in the past resulting of the FOHMD. I.F. in systems with external sensors (like LASSIE and LORAS) and without external sensors (the so-called analytical systems like VIMI). As VIMI (Durand, 1974) was not designed to meet the accuracy requirement of 2 m/s, 95-percent probability, a new analytical A87-45115 method for the generation of military helicopters (Hassenpflug and FIBER OPTIC CONTROL OF ENGINES Schwaeble, 1985) has been developed using specific GLEN E. MILLER (Boeing Photonics Laboratory, Bellevue, WA) helicopter-control features. The validity and accuracy of this new IN: International Instrumentation Symposium, 32nd, Seattle, WA, analytical method has been verified by a series of flight trials. May 5-8, 1986, Proceedings . Research Triangle Park, NC, Author Instrument Society of America, 1986, p. 269-282. The paper describes an experimental drop-in fiber optic system A87-43468# developed to replace the primary electrical throttle level angle STANDARDIZATION AND LOGISTIC SUPPORT COST sensor and electrical wiring used for control and monitoring of a EFFECTIVENESS OF ADVANCED AVIONICS SYSTEMS commercial . The modification involved the replacement V. BUONTEMPO (Selenia S.p.A., Pomezia, Italy) DGLR, European of the electrical throttle control sensor with a functionally-equivalent Rotororaff Forum, 12th, Garmisch-Partenkirohen, West Germany, electrically-passive optical sensor. During the B 757 flight test, Sept. 22-25, 1986, Paper. 17 p. refs the fiber optic interfaces performed in a manner indistinguishable Modular standardization which has already been adopted within from that of the normal electrical interfaces, and the tracking and avionic systems can also be used to optimize the logistic support dynamic response of the optical throttle lever angle (TLA) were in terms of performance (such as operative availability, identical to those of the secondary electrical TLA resolver. K.K.

661 06 AIRCRAFT INSTRUMENTATION

A87-45126 A87-45879 ONBOARD INSTRUMENTATION FOR FLIGHT TEST TAKEOFF RADAR REQUIREMENTS FOR FUTURE AVIONICS SYSTEMS PERFORMANCE [ANFORDERUNGEN AN RADARGERAETE IN ZUKUENFTIGEN HAROLD K. CHENEY (Douglas Aircraft Co., Long Beach, CA) AVlONIKSYSTEMEN] IN: International Instrumentation Symposium, 32nd, Seattle, WA, W. HETZNER and W. KOHL (Messerschmitt-Boelkow-Blohm May 5-8, 1986, Proceedings . Research Triangle Park, NC, GmbH, Munich, West Germany) IN: Radar Technology 1986; Instrument Society of America, 1986, p. 539-543. Symposium, 6th, Bremen, West Germany, Nov. 4-6, 1986, Reports By using an inertial navigation system (INS) for space position • Duesseldorf, Deutsche Gesellschaft fuer Ortung und Navigation, data, a method has been developed to obtain velocity, distance, 1986, p. C3.-C3.15. In German. height, wind, and ambient temperature for takeoff performance The performance demands on radar equipment for future aircraft using only instrumentation on board a test aircraft. No external are reviewed. General requirements include integrability in instrumentation is required. The flight path component of wind at advanced avionics architectures with VHSIC components, the aircraft is determined using pitot total pressure, tracking altitude, high-speed data buses, speech-recognition and synthesis devices, and tracking velocity. Ambient runway temperature is determined and AI features; low probability of intercept; polarization agility; using measured total temperature prior to rotation. The only external advanced conformal or phased-array antennas; automatic information required is the runway slope. The resulting performance correction for radome-induced boresight errors; light weight; and data are equivalent or superior to similar data obtained using reduced cooling and power demands. These requirements are external systems. The recent improvement of INS height values discussed in detail for combat aircraft (air-air and air-ground obtained using the Litton LTN-96 INS with longer baro-inertial loop operation), early-warning aircraft, and maritime patrol aircraft• T.K. time constant values is presented. Author

A87-45732 AN AIRBORNE LASER AIR MOTION SENSING SYSTEM. I - CONCEPT AND PRELIMINARY EXPERIMENT A87-46727 R. J. KEELER, R. J. SERAFIN, R. L. SCHWlESOW, D. H. CULPRITS CAUSING AVIONIC EQUIPMENT FAILURES LENSCHOW (National Center for Atmospheric Research, Boulder, KAM L. WONG, IRVING QUART (Kambea Industries, Inc., CO), J. M. VAUGHAN (Royal Signals and Radar Establishment, Manhattan Beach, CA), JAMES M. KALLIS (Hughes Aircraft Co., Malvern, England) et al. Journal of Atmospheric and Oceanic El Segundo, CA), and ALAN H. BURKHARD (USAF, Flight Technology (ISSN 0739-0572), vol. 4, March 1987, p. 113-127. Dynamics Laboratory, Wright-Patterson AFB, OH) IN: 1987 Annual refs Reliability and Maintainability Symposium, Philadelphia, PA, Jan. This paper presents a concept for a laser air motion sensing 27-29, 1987, Proceedings. New York, Institute of Electrical and system using a conically scanned optical Doppler technique that Electronics Engineers, Inc., 1987, p. 416-421. senses air motions remote from the aircraft. The advantages of An examination of industrial and military failure data is performed the technique include calibration based on physical constants rather to determine the major locations and types of defects causing than experiment for an accurate measurement of mean wind, avionics field failures. Field failures were found to occur primarily freedom from flow distortion effects on turbulence measurements, in devices containing semiconductors, with discrete capacitors and all-weather performance, reduction in error from mechanical discrete resistors being less frequent locations of failures. vibrations, and ability to measure vertical wind shear. An experiment Connectors, relays, filters, and magnetic devices were found to comparing a single-component laser velocimeter and a differential be insignificant contributors to failures, while solder joints and pressure gust probe shows that the optical approach measures printed circuit boards are believed to have a significant number of the turbulence spectrum accurately at frequencies up to 10 Hz failures. More than a dozen types of defects, each contributing to and that the SNR is not a limiting factor. The effect of spectral a small fraction of the failures, have been identified. R.R. skewing caused by airflow distortion in cloud is observed. C.D.

A87-45733 AN AIRBORNE LASER AIR MOTION SENSING SYSTEM. II - DESIGN CRITERIA AND MEASUREMENT POSSIBILITIES N87-26838 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn LEIF KRISTENSEN (Forsoganlaeg Riso, Roskilde, Denmark) and DONALD H. LENSCHOW (National Center for Atmospheric (West Germany). Unternehmensgruppe Hubschrauber und Research, Boulder, CO) Journal of Atmospheric and Oceanic Flugzeuge. Technology (ISSN 0739-0572), vol. 4, March 1987, p. 128-138. AVIONICS SYSTEMS FOR FUTURE CIVIL HELICOPTERS [AV- refs IONIKSYSTEME FUER KUENFTIGE ZlVILHUBSCHRAUBER] A conically scanning Doppler lidar technique for measuring air ANTON INGELSPERGER In its Research and Development. motions from an aircraft is proposed in the companion paper (Keeler Technical-Scientific Publications 1986 p 167-174 1986 In et al.). A theoretical analysis of this technique shows that, assuming GERMAN Presented at the 4th BMFT-Statusseminar, Munich, isotropic turbulence, the technique is feasible for measuring air West Germany, 28-30 Apr. 1986 Original language document motions to scales small enough that the velocity spectra in a announced in IAA as A87-14005 convective atmospheric boundary layer can be resolved well into (MBB-UD-473/86) Avail: Issuing Activity the inertial subrange, and most of the turbulent motions that Civil helicopter cockpit instrumentation using color displays, and contribute to the vertical fluxes can be resolved. A scanning beam the testing of color displays are explained. The central control range of 10 m was selected to ensure that flow distortion induced unit principles are discussed. The main fields in cockpit by the aircraft will not significantly affect the velocity measurement. instrumentation and central control unit which need further Thus, the technique offers improved accuracy over presently used development for use in future helicopters are discussed. The use immersion air motion sensors. An additional feature is the possibility of development simulators, signal standardization and bus system, of measuring mean vertical wind shear. Author and software for display systems are presented. ESA

662 07 AIRCRAFT PROPULSION AND POWER

07 are described. A few significant results in the acoustic signature reduction are shown. Author AIRCRAFT PROPULSION AND POWER A87-43605 SELECTION OF ADMISSIBLE CONTACT STRESSES FOR Includes prime propulsion systems and systems components, e.g., TOOTHED GEARS OF AIRCRAFT ENGINES [K VOPROSU O gas turbine engines and compressors; and on-board auxiliary power VYBORE DOPUSKAEMYKH KONTAKTNYKH NAPRIAZHENII plants for aircraft. DLIA ZUBCHATYKHH PEREDACH AVIADVIGATELEI] IU. I. VOLOSHIN Samoletostroenie - Tekhnika Vozdushnogo A87-43464# Flota (ISSN 0581-4634), no. 53, 1986, p. 18-20. In Russian. The paper proposes a method for determining coefficients which T700/CT7 DERIVATIVE GROWTH ENGINE RELIABILITY - refine values of admissible stresses in the calculation of the contact CONSISTENT WITH LONGSTANDING INDUSTRY TRADITIONS endurance of the active surfaces of toothed gears in aircraft H. G. DONOHIE and W. W. ROSTRON (General Electric Co., engines. A calculation example confirms the effectiveness of the Aircraft Engine Business Group, Lynn, MA) DGLR, European proposed method. B.J. Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 25 p. refs A87-43606 The current family of T700/CT7 step 2 growth derivative APPROXIMATION OF THE CHARACTERISTICS OF THE engines, which encompass civil and military as well TURBINE OF A GAS TURBINE ENGINE IN A WIDE RANGE OF as a civil turboprop, has high commonality with predecessor OPERATING MODES [APPROKSIMATSIIA KHARAKTERISTIK engines; in addition, all technology improvements have undergone TURBINY GAZOTURBINNOGO DVIGATELIA V SHIROKOM demonstration in previous programs. A further development DIAPAZONE REZHIMOV RABOTY] program is underway which will conduct design verification tests V. P. GERASIMENKO Samoletostroenie - Tekhnika Vozdushnogo needed for the substantiation of engine level performance, as Flota (ISSN 0581-4634), no. 53, 1986, p. 20-24. In Russian. refs well as durability testing to achieve an early design maturity. Polynomial approximations of turbine characteristics have been O.C. obtained from factor planning of experiments, which makes it possible to refine them during turbine operation with a minimum A87-43465# of empirical data. The approximations can be included in various DEVELOPMENT PROGRAM OF A FULL AUTHORITY DIGITAL mathematical models of gas turbine engines, and are particularly ELECTRONIC CONTROL SYSTEM FOR THE T55-L-712E suitable for the development of adaptive models in connection TURBOSHAFT ENGINE with optimal engine control. B.J. DAVID PETRO (Textron, Inc., Avco Lycoming Textron Div., Stratford, CT) and ANTHONY J. GENTILE (Chandler Evans, Inc., A87-43607 West Hartford, CT) DGLR, European Rotorcraft Forum, 12th, THE LOW-ASPECT-RATIO PARAMETER OF BLADES Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. [PARAMETR MALOGO UDLINENIIA LOPATOK] 20 p. A. D. GRIGA Samoletostroenie - Tekhnika Vozdushnogo Flota An evaluation is made of the primary requirements for the (ISSN 0581-4634), no. 53, 1986, p. 24-26. In Russian. incorporation of a full authority digital electronic control system on It is proposed that the low-aspect-ratio parameter of turbine a twin-engine military helicopter; the component configuration blades be determined from the condition of the equality of profile employed is discussed in light of such criteria as maintainability, losses to the sum of end losses and secondary-vortex losses. It diagnostics, performance history recording, environmental is concluded that the characteristics of turbine stages with capabilities, engine installation, and aircraft integration. Closed-loop low-aspect-ratio blades can be improved by choosing values of computer simulations are used in order to evaluate and optimize kinematic and geometric characteristics in such a way as to obtain engine control modes. O.C. minimum values of the aspect ratio. B.J.

A87-43466# A87-43609 DEVELOPMENT OF A FLEXIBLE AND ECONOMIC HELICOPTER OPTIMIZATION OF THE DURATION OF ULTRASONICALLY ENGINE MONITORING SYSTEM ACTIVATED IMPACT SURFACE TREATMENT OF GAS-TURBINE- A. A. TEN HAVE (Nationaal Lucht- en Ruimtevaartlaboratorium, ENGINE BLADES [OPTIMIZATSIIA DLITEL'NOSTI UL'TRAZ- Emmeloord, Netherlands) and C. R. TJALSMA (Royal Netherlands VUKOVOGO UPROCHNENIIA LOPATOK GTD] Navy, The Hague, Netherlands) DGLR, European Rotorcraft V. G. KAZANSKII and V. M. ANISHCHENKO Samoletostroenie - Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, Tekhnika Vozdushnogo Flota (ISSN 0581-4634), no. 53, 1986, p. 1986, Paper. 12 p. refs 28-30. In Russian. Lynx helicopter engine loading is the subject of a research Consideration is given to the ultrasonically activated impact program aimed at investigating the possibility of continuous and surface treatment (via small steel balls) of turbine blades in the automated monitoring of engine fatigue damage accumulation finishing stage of treatment. Eddy-current monitoring was used in based on the Rolls-Royce Cycle Life Control concept. A pilot flight order to exclude the effect of the initial stage of the material on test program has been carried out, the results of which are being the final results of the treatment. Fatigue and nondestructive tests used for the development of a usable Lynx engine in-flight data were used to determine the optimal duration of the surface processor. Such a device will provide valuable information on Lynx treatment. B.J. engine service loading, and may be the basis of computerized Cyclic Life Control within the RNLN in the future. This paper will generally describe major topics of the above program. Author A87-43614 NUMERICAL STUDY OF THE GASDYNAMIC PROCESS IN A A87-43467# PULSEJET ENGINE [CHISLENNOE ISSLEDOVANIE GAZODIN- HELICOPTER TURBOSHAFT ENGINE ACOUSTIC AND AMICHESKOGO PROTSESSA V PUL'SIRUIUSHCHEM VOZ- INFRARED STUDIES AND TESTS DUSHNO-REAKTIVNOM DVIGATELE] A. FARRANDO (Turbomeca, S.A., Bordes, France) DGLR, V. M. LAPOTKO Samoletostroenie - Tekhnika Vozdushnogo Flota European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West (ISSN 0581-4634), no. 53, 1986, p. 51-56. In Russian. Germany, Sept. 22-25, 1986, Paper. 9 p. The effect of the combustion-chamber parameters on the The following statement concerns the field of the acoustic and gasdynamic process in a pulsejet engine is assessed using a infrared detection of helicopter turbushaft engines. Test facilities mathematical model based on the conservation laws of mass, in use and main research being carried out at present at Turbomeca momentum, and energy. It is found that the parameters of existing

663 07 AIRCRAFT PROPULSION AND POWER

pulsejet engines are far from optimal. It is concluded that the A87-43701# characteristics of these engines can be improved by increasing EVALUATING AND TESTING OF TURBOFAN ENGINES the amount of energy supplied to the gas, by increasing the rate THERESE M. MILLER (General Electric Co., Aircraft Engine of energy supply, by lengthening the zone of energy supply, and Business Group, Evendale, OH) ASME, Winter Annual Meeting, by optimizing the engine geometry. B.J. Anaheim, CA, Dec. 7-12, 1986. 7 p. (ASME PAPER 86-WA/DE-3) The tasks of the engineering evaluation specialist in planning, conducting, and interpreting ground tests of turbofan aircraft A87-43616 engines are reviewed. Consideration is given to the DOD and CALCULATION OF THE RELIABILITY OF AIRCRAFT-ENGINE FAA requirements for qualification and certification tests, the test PARTS UNDER REPEATED STATIC LOADING [RASCHET instrumentation, data acquisition procedures, endurance testing, NADEZHNOSTI DETALEI AVIATSIONNYKH DVIGATELEI PRI performance testing, ingestion testing, blade-out testing, verification POVTORNO-STATICHESKOM NAGRUZHENII] testing, and test interruptions. Photographs of test facilities and A. S. MOSKALENKO Samoletostroenie - Tekhnika Vozdushnogo test-damaged engine components and graphs of typical results Flota (ISSN 0581-4634), no. 53, 1986, p. 60-62. In Russian. are provided. T.K. The paper describes a mathematical model for the reliability of aircraft-engine parts which takes into account the gradual A87-43702# accumulation of damage. This model, based on the linear theory FINITE ELEMENT ANALYSIS AND REDESIGN OF JET ENGINE of damage accumulation, identifies the influence of structural, STARTER BREECH CHAMBER fabrication, and operational factors, and indicates ways to increase ALFRED G. STRIZ (Oklahoma, University, Norman) and FRANK reliability. B.J. P. BRUECKNER (Hughes Aircraft Co., Tucson, AZ) ASME, Winter Annual Meeting, Anaheim, CA, Dec. 7-12, 1986. 6 p. refs (Contract F34601-83-C-3448) A87-43620 (ASME PAPER 86-WA/DE-20) ENGINEERING AND COST PRINCIPLES FOR INCREASING THE A stress analysis by the finite element method of failure prone PRODUCTION EFFICIENCY AND MAINTAINABILITY OF jet engine starter breech chambers is presented. The chambers AIRCRAFT ENGINES [TEKHNIKO-EKONOMICHESKOE are modelled as axisymmetric and as three-dimensional structures. OBOSNOVANIE POVYSHENIIA UROVNIA TEKHNOLOGICH- The static analysis is performed by two finite element codes, SAP NOSTI AVIATSIONNYKH DVIGATELEI] IV and MSC/NASTRAN. The maximum stresses are found on the S. A. NIKITIN and V. V. DOBRIAKOV Samoletostroenie - Tekhnika inside surface of the chamber dome and are due to large bending Vozdushnogo Flota (ISSN 0581-4634), no. 53, 1986, p. 81-86. In stresses resulting from a considerable change in curvature and Russian. thickness in the merger region of the spherical chamber dome The problem of increasing the production efficiency and and the stiffer cylindrical side wall. Reductions of these high maintainability of aircraft engines is examined. A formula for the stresses are possible by decreasing the chamber wall thickness cost justification of the selection of a modular version of a structure just below the failure area and/or by increasing the dome wall is proposed on the basis of an engineering and cost analysis. A thickness by Atterbury and Bert's thin-shell reinforcement method. system of primary and secondary indices is presented for evaluating The effects of high burn temperatures on the chamber stresses the production efficiency and maintainability of engine designs. are presented as are those of a modelled corrosion pit. All results B.J. are compared to data obtained experimentally by Khan. Author

A87-44253 A87-43621 HEAT EXCHANGERS FOR TURBOSHAFT ENGINES OPTIMIZATION OF SYSTEMS FOR THE AUTOMATIC TESTING PETER PLETSCHACHER Interavia (ISSN 0020-5168), vol. 42, OF AIRCRAFT ENGINES ACCORDING TO COST CRITERIA May 1987, p. 503. [OPTIMIZATSIIA AVTOMATIZIROVANNYKH SISTEM ISPYTANII The decisive factor in the design of a heat exchanger for aircraft AVlATSIONNYKH DVIGATELEI PO EKONOMICHESKIM turboshaft and turboprop engines, in order to obtain fuel KRITERIIAM] consumption improvements through the recuperation of exhaust V. A. PIL'SHCHIKOV and IA. V. SAFRONOV Samoletostroenie - heat, is the ability to withstand high inlet temperatures and large Tekhnika Vozdushnogo Flota (ISSN 0581-4634), no. 53, 1986, p. pressure differentials while maintaining suitably small volume and 86-90. In Russian. weight increases to the powerplant installation. Attention is given Five optimization models for automatic test systems for aircraft to initial test results from a heat exchanger for a 1000 kW-class engines are described. All the models provide for minimization of turboshaft engine; exchanger inlet temperatures are of the order costs over the service life of the systems. B.J. of 1000 K at full load. Heat exchanger internal airflow patterns were investigated in detail for the case of subassemblies. A fuel saving of 25-35 percent is projected for airliners that cruise at 60-70 percent of rated power. O.C. A87-43640 A STUDY OF THE THERMAL-STRESS STATE OF GAS TURBINE ENGINE BLADES WITH PROTECTIVE COATINGS A87-44272 [ISSLEDOVANIE TERMONAPRIAZHENNOGO SOSTOIANIIA COUNTDOWN TO THE PROPFAN MODELEI LOPATOK GTD S ZASHCHITNYMI POKRYTIIAMI] KEN FULTON Air International (ISSN 0306-5634), vol. 32, June G. N. TERT'IACHENKO, K. P. BUISKIKH, L. V. KRAVCHUK, and 1987, p. 316-321. G. R. SEMENOV (AN USSR, Institut Problem Prochnosti, Kiev, A development history, current development status, and relative Ukrainian SSR) Problemy Prochnosti (ISSN 0556-171X), no. 5, performance advantage assessment is made of the candidate May 1987, p. 67-70. In Russian. refs turbomachine designs for 'propfan' propulsion systems that are to Thermal stress analysis is carried out for wedge-shaped blade be used by next-generation commercial aircraft in order to further models of ZhS6U nickel alloy of three different sizes with reduce specific fuel consumption. Attention is given to the progress heat-resistant electron-beam coatings of three different made by the Unducted Fan (UDF), which is currently undergoing compositions (Ni-Co-Cr-AI-Y, Co-Cr-AI-Y, and Ni-Cr-AI-Y). It is flight testing and appears to exhibit substantial intrinsic advantages shown that, in addition to protecting the blade surface against over both single-rotation and contrarotation propfan systems corrosion and erosion, the protective coatings are also capable of employing a gearbox (rather than the UDF's contrarotating low reducing thermal stresses in the surface layers of a structural pressure turbine stages) for transfer of engine bypass power. element. V.L. O.C.

664 07 AIRCRAFT PROPULSION AND POWER

A87-44582 gradient transport modeling. Due to the contribution of small-scale THE ART OF RETICULATION AND APPLICABLE ADHESIVES turbulent diffusion, turbulent flame in practical is thick, SID QUICK (Dexter Corp., Hysol Aerospace and Industrial Products and the mean reaction rate in such a thick flame is found to be Div., Pittsburg, CA) IN: High tech - The way into the nineties; at least 50 percent higher than that in a thin laboratory flame. Proceedings of the Seventh International SAMPE Conference, V.L. European Chapter, Munich, West Germany, June 10-12, 1986. Amsterdam and New York, Elsevier Science Publishers, 1986, p. 103-115. A87-45168# A development status evaluation is made of engine nacelles PROPFAN PROPULSION SYSTEMS FOR THE 1990'S that have been acoustically treated for compliance with FAA C. N. REYNOLDS (Pratt and Whitney, Engineering Div., East requirements and regulations; most of these nacelle designs in Hartford, CT), R. E. RIFFEL (General Motors Corp., Allison Gas some fashion employ a perforated aluminum face sheet that is Turbine Div., Indianapolis, IN), and S. LUDEMANN (United bonded to a reticulated honeycomb core. Attention is presently Technologies Corp., Hamilton Standard Div., Windsor Locks, CT) given to the unique properties required in reticulable adhesive AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, films, as well as the equipment and procedures required to perform San Diego, CA, June 29-July 2, 1987. 12 p. such film reticulations, as found in the state-of-the-art 'DynaRohr' (AIAA PAPER 87-1729) sound-attenuating hardware system. O.C. PW-Allison Engines with subcontractor Hamilton Standard are designing a Propfan Propulsion System for commercial and military A87-45156# transport aircraft. These companies are targeting for an early 1990's ADVANTAGES OF THRUST VECTORING FOR STOVL certification of a pusher system for the Douglas MD91X and the B. D. WARD (Rolls-Royce, Inc., Atlanta, GA) and W. J. LEWIS Boeing 7J7 airliners. The paper describes the Model 578 Propfan (Rolls-Royce, PLC, Bristol, England) AIAA, SAE, ASME, and Propulsion System design considerations. Included are discussions ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June on core engine selection, comparing new versus derivative; cycle 29-July 2, 1987. 8 p. definition; configuration and installation studies including gear (AIAA PAPER 87-1708) system concepts; and propfan propulsor configurations. Engine The advantages of concepts capable of full thrust vectoring selection studies will highlight fuel burn, economic, and acoustic over other STOVL and conventional aircraft concepts are examined criteria. Author in terms of the takeoff ground roll (as a function of the takeoff gross weight), efficiency of transition to fully wingborne flight, and A87-45169# overall aircraft safety. In particular, it is shown that full vectoring ENGINE DESIGN AND SYSTEMS INTEGRATION FOR PROPFAN concepts (advanced vector thrust and hybrid fan vectored thrust) AND HIGH BYPASS TURBOFAN ENGINES have two important advantages over part vectoring concepts (RALS, ejectors, lift, and lift/cruise): (1) for a given engine size, N. J. PEACOCK (Rolls-Royce, PLC, Derby, England) AIAA, SAE, the vectored thrust resultant is greater and (2) there are no changes ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. to the engine configuration or rating required during STO or transition to wingborne flight. V.L. (AIAA PAPER 87-1730) The effects of engine configuration geometry on alternative A87-45157# courses to the provision of such aircraft services as cabin IMPACT OF ENGINE TECHNOLOGY ON SUPERSONIC STOVL pressurization, air conditioning, and electricity (through engine air bleed and accessory power trains) are presently examined for a DONALD W. ELLIOTT and JOHN R. SIMMONS (General Electric Co., Technologies Dept., Cincinnati, OH) AIAA, SAE, ASME, propfan and a high bypass ratio turbofan employing the technology features anticipated for the next generation of high-speed, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, long-range airliner propulsion systems. The projected trends in June 29-July 2, 1987. 8 p. (AIAA PAPER 87-1709) cabin comfort level requirements lead, notwithstanding increasing engine efficiency, to specific fuel consumption penalties; where The effect of advanced engine technologies on the supersonic these are currently 1-2 percent, they will rise to over 4 percent STOVL aircraft is evaluated in terms of the takeoff gross weight for the best engine-offtake systems. By using the engine solely (TOGW) for a single-engine aircraft flying a typical STOVL as a provider of electrical power, this fuel consumption penalty supersonic mission. The far-term engine technology applied to may be reduced by up to 2 percent. O.C. the generic single-engine STOVL aircraft with 80-percent composite utilization is predicted to have a 30-percent improvement in TOGW for the STOVL mission. For the intermediate-term technology with A87-45170 60-percent utilization of composites, the predicted improvement in PREPARING A PROPFAN PROPULSION SYSTEM FOR FLIGHT TOGW is 22 percent. The SLIDE (short landing integrated deflected TEST exhaust) concept would have a 15-percent lower TOGW than the D. C. CHAPMAN (General Motors Corp., Allison Gas Turbine Div., same technology STOVL aircraft for the STOVL mission. V.L. Indianapolis, IN), G. J. SEVlCH (Pratt and Whitney, Engineering Div., East Hartford, CT), and D. E. SMITH (United Technologies A87-45161# Corp., Hamilton Standard Div., Windsor Locks, CT) AIAA, SAE, COMBUSTION-GENERATED TURBULENCE IN PRACTICAL ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, COMBUSTORS CA, June 29-July 2, 1987. 11 p. D. R. BALLAL (Dayton, University, OH) AIAA, SAE, ASME, and (AIAA PAPER 87-1731) ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June The PW-Ailison 578-DX Propfan Demonstrator Propulsion 29-July 2, 1987. 11 p. refs System is being prepared for flight test by the Pratt & Whitney, (Contract F33615-82-C-2255) Allison, and Hamilton Standard team. The demonstrator system (AIAA PAPER 87-1721) consists of an Allison Model 571 power section, which is currently Combustion-generated turbulence in practical combustors is in service in industrial and marine applications, a new low pressure examined with reference to experimental data for gas turbine compressor, a new gear reduction system developed from an combustors, dump combustors, bluff body stabilized combustors, Allison/NASA program, a new propfan module, a new nacelle, and flames stabilized by a rearward facing step. Four different and a full authority digital electronic control system. Preparation mechanisms that either affect or are affected by the for flight testing includes comprehensive testing of the major combustion-generated turbulence are identified: combustion zone components as 'building blocks,' leading to complete propulsion structure, reaction rates, recirculation and swirling motion, and system testing in an ambient test stand. Results of the test program two-phase combustion. Measurements indicate a dominating are presented. Flight testing will be conducted in late 1987 on a influence of small-scale random turbulence, consistent with mean McDonnell Douglas MD80 aircraft. Author

665 07 AIRCRAFT PROPULSION AND POWER

A87-45171# A87-45231# UDF/727 FLIGHT TEST PROGRAM DESIGN AND TEST VERIFICATION OF A COMBUSTION ROBERT W. HARRIS (General Electric Co., Cincinnati, OH) and SYSTEM FOR AN ADVANCED TURBOFAN ENGINE R. D. CUTHBERTSON (Boeing Commercial Airplane Co., Seattle, J. W. SANBORN, J. E. LENERTZ, and J. D. JOHNSON (Garrett WA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, Turbine Engine Co., Phoenix, AZ) AIAA, SAE, ASME, and ASEE, 23rd, San Diego, CA, June 29-July 2, 1987. 11 p. Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July (AIAA PAPER 87-1733) 2, 1987. 10 p. The Unducted Fan engine design concept, 'UDF', and (AIAA PAPER 87-1826) aircraft/engine configurations are presented as well as the Modeling has been conducted for both combustor internal and accomplishments of flight testing on a modified Boeing 727 aircraft. external flow fields in the case of a novel combustion system Cruise flight speeds up to 0.84 Mach at 36,000 ft were achieved configuration, evaluating various airflow split schemes and fuel together with system operability and safety, control stability, a good injection locations in order to arrive at the final design. A full-scale correlation between the model and full-scale data. In addition, annular plexiglass atmospheric test rig was used to measure the UDF acoustic acceptibility and predictability were confirmed. local pressure drops across the combustor dome and liners; K.K. measured pressure drops were compared to the predicted pressure drops. In addition, a full-scale annular high pressure test rig was employed to record all pertinent combustor performance data. A87-45180# Attention was given to combustion efficiency, pattern factor, ignition HIGHLY COMPACT INLET DIFFUSER TECHNOLOGY characteristics, lean blowout fuel/air ratios, and liner wall R. H. TINDELL (Grumman Corp., Bethpage, NY) AIAA, SAE, temperatures. O.C. ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 12 p. refs A87-45232# (AIAA PAPER 87-1747) THE INFLUENCE OF DILUTION HOLE AERODYNAMICS ON THE The desirable design characteristics of highly compact offset TEMPERATURE DISTRIBUTION IN A COMBUSTOR DILUTION diffuser systems are examined, with a goal of deriving inlet geometry ZONE parameters to achieve a separation-free flow. The experimental S. J. STEVENS and J. F. CARROTTE (Loughborough University work employed a diffuser test rig, designed to measure static and of Technology, England) AIAA, SAE, ASME, and ASEE, Joint total pressures throughout the diffuser and across the exit plane, to evaluate the effects of throat Mach number and active/passive Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 11 p. Sponsorship: Ministry of Defence. refs methods for BLC. The paper discusses passive and active BLC (Contract MOD-ER/2/1/7/0090-XR) methods for providing separation-free diffuser flow and compares (AIAA PAPER 87-1827) CFD methods with the experimental results to validate the An experimental investigation has been carried out to study applicability of the methods. I.S. circumferential irregularities in the temperature distribution downstream of a row of sixteen heated jets injected normally into A87-45181# a confined annular cross-flow at a momentum flux ratio of 4. The F-16 MODULAR COMMON INLET DESIGN CONCEPT heated air was fed to the plunged holes along a representative PAUL E. HAGSETH (General Dynamics Corp., Fort Worth, TX) approach annulus. Temperature distributions measured at a plane AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, 2 hole diameters downstream indicated, despite the uniformity of San Diego, CA, June 29-July 2, 1987. 12 p. the approach flow, a lack of symmetry between the dilution jets. (AIAA PAPER 87-1748) This has been shown to be due to an apparent twist of the The fixed geometry normal shock inlet of the F-16 fighter yields temperature contours associated with certain jets. Velocity efficient performance at both subsonic and low supersonic Mach distributions at the same location indicated a corresponding numbers while retaining the use of a simple and lightweight asymmetry in the double vortex structure that is formed in the structure. The modular common-inlet duct design which has been wake of each jet. Velocity measurements across the face of the developed to accomodate future engine changes without forfeiture dilution jets revealed non-uniformities in both flow direction and of the fixed inlet is presently discussed in light of wind tunnel distribution. Author data on pressure recovery, distortion, and turbulence. Although currently operating with the F100-PW-200 engine, the higher A87-45233# airflows of the larger and more powerful F-110 engine are HIGH DENSITY FUEL EFFECTS ON GAS TURBINE ENGINES accomodated by changing the forward inlet modules at the leading V. L. OECHSLE, P. T. ROSS, and H. C. MONGIA (General Motors 24 inches of the inlet, without disturbing the fuselage fuel tank Corp., Allison Gas Turbine Div., Indianapolis, IN) AIAA, SAE, and nose landing gear structures. O.C. ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 8 p. A87-45205# (Contract F33615-86-C-2604) TRANSIENT TEST SYSTEM DESIGN FOR THE T800-APW-800 (AIAA PAPER 87-1829) TURBOSHAFT ENGINE Four high density/high volumetric energy fuels are J. M. DAVIS (Pratt and Whitney, West Palm Beach, FL) AIAA, experimentally evaluated on the T56-A-15 combustion system. SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San These fuels represent an increase of up to 11.2 percent volumetric Diego, CA, June 29-July 2, 1987. 7 p. energy content over the baseline JP-4 fuel, and significant increases in the aromatic contents, fuel viscosity, surface tension, and initial (AIAA PAPER 87-1791) The U.S. Army has released contracts for development of the and final boiling points. Combustion system degradation is shown Light Helicopter Experimental (LHX). Part of the engine in regard to idle combustion efficiency, lean blowout, development requirements include simulation of engine 'droop' ignition/restart, smoke emissions, and wall temperature levels. Author condition following autorotation. This requirement necessitates the design of a high response transient test system. Requirements for the transient test system include performance collective A87-45234# pitch-induced load change from flight idle to 95-percent HIGH PERFORMANCE TURBOFAN AFTERBURNER SYSTEMS intermediate rated, ,wer(IRP) in one second, decoupling the power A. SOTHERAN (Rolls-Royce, PLC, Bristol, England) AIAA, SAE, absorber at zero torque and recoupling when load is applied, and ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, performance transients from no load to maximum power and CA, June 29-July 2, 1987. 11 p. maximum power to no load. This paper presents just such a design (AIAA PAPER 87-1830) of a transient test system for the turboshaft engine of the Army's An account is given of the design features and performance LHX Helicopter. Author capabilities of state-of-the-art, low bypass turbofan afterburner

666 07 AIRCRAFT PROPULSION AND POWER systems.A compact afterburner configuration is achieved by A87-45245# locating the flameholding baffles immediately downstream of the FLIGHT TEST OF THE F100-PW-220 ENGINE IN THE F-16 turbine exhaust plane at the confluence of the engine core and MARK T. CHILDRE and KEVIN D. MCCOY (General Dynamics fan bypass gas streams. are designed to be free of Corp., Fort Worth, TX) AIAA, SAE, ASME, and ASEE, Joint combustion-driven pressure oscillations that can occur either in Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. cross-stream modes, which can destroy engine hardware in 9 p. refs fractions of a second, or in longitudinal modes that can cause fan (AIAA PAPER 87-1845) surge. O.C. Results of a 106-flight two-phase test program of the F100-PW-220 engine for the F-16 aircraft are summarized. The A87-45235"# General Electric Co., Cincinnati, Ohio. program has demonstrated the overall capability and compatibility SCALE MODEL TEST RESULTS OF A THRUST REVERSER of the F100-PW-220 engine. The thrust produced by the CONCEPT FOR ADVANCED MULTI-FUNCTIONAL EXHAUST F100-PW-220 engine is comparable to that of its predecessor, SYSTEMS F100-PW200, with the response significantly improved. The new A. P. KUCHAR (General Electric Co., Cincinnati, OH) and L. D. engine has also demonstrated improved augmentor operability and LEAVITT (NASA, Langley Research Center, Hampton, VA) AIAA, start characteristics. Some minor problems and areas requiring SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San additional testing have been identified. V.L. Diego, CA, June 29-July 2, 1987. 11 p. refs (AIAA PAPER 87-1833) A87-45246# An evaluation is made of scale model test results for a F-15/F100 DIGITAL ELECTRONIC ENGINE CONTROL MAIN 'block-and-turn' thrust reverser design consisting of an internal FUEL GEAR PUMP FIELD SERVICE EVALUATION flow blocker, internal doors, two ports located on the top and J. E. TAYLOR and S. C. GERBER (Pratt and Whitney, West Palm bottom of the exhaust duct, cascade-turning vanes located at the Beach, FL) AIAA, SAE, ASME, and ASEE, Joint Propulsion port exit to turn the flow, and external doors which guide the Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 10 p. exhaust flow. Numerous geometric variations were incorporated in (AIAA PAPER 87-1846) order to obtain parametric aerodynamic design criteria. The baseline A two-year field service evaluation program is being conducted reverser configuration exceeded predicted levels of performance. on F-15 and F-16 aircraft with the purpose of assessing the Skewed vane cascade concepts can be as effective in turning operability, reliability, and supportability of the full authority digital the flow as the baseline vane concept. O.C. electronic engine control/gear pump (DP) system for the F100-PW-100 engine. In addition, the program is demonstrating A87-45236"# National Aeronautics and Space Administration. and evaluating the extensive engine monitoring diagnostic system. Langley Research Center, Hampton, Va. The operation and the main components of the digital electronic STATIC INVESTIGATION OF POST-EXIT VANES FOR engine control system and engine monitoring system are examined, MULTIAXlS THRUST VECTORING and results of the field evaluation are presented, with some possible BOBBY L. BERRIER and MARY L. MASON (NASA, Langley improvements identified. V.L. Research Center, Hampton, VA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July A87-45247"# National Aeronautics and Space Administration. 2, 1987. 13p. refs Flight Research Center, Edwards, Calif. (AIAA PAPER 87-1834) PRELIMINARY FLIGHT RESULTS OF AN ADAPTIVE ENGINE Transonic wind tunnel tests are conducted to determine the CONTROL SYSTEM OF AN F-15 AIRPLANE flow-turning capabilities and nozzle internal performance of LAWRENCE P. MYERS and KEVIN R. WALSH (NASA, Flight axisymmetric and nonaxisymmetric nozzles employing postexit Research Center, Edwards, CA) AIAA, SAE, ASME, and ASEE, vanes for multiaxis thrust-vectoring. The geometric parameters Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July investigated for the axisymmetric nozzle installation were number 2, 1987. 12 p. refs of vanes, vane curvature, vane location relative to nozzle exit, (AIAA PAPER 87-1847) and vane deflection angle; for the nonaxisymmetric cases, the Results of the flight demonstration of the adaptive engine control parameters were vane planform and curvature, nozzle type, and system (ADECS), an integrated flight and propulsion control system, nozzle exit aspect ratio. Nozzle pressure ratio was varied from are reported. The ADECS system provides additional engine thrust 1.5 to 6.0, using high pressure air. O.C. by increasing (EPR) at intermediate and afterburning power, with the amount of EPR uptrim modulated in A87-45240# accordance with the maneuver requirements, flight conditions, and DEVELOPMENT OF A LARGE, SPIRAL BEVEL GEAR engine information. As a result of EPR uptrimming, engine thrust ROTORCRAFT TRANSMISSION has increased by as much as 10.5 percent, rate of climb has RAYMOND J. DRAGO and JOHN C. MACK (Boeing Vertol Co., increased by 10 percent, and the time to climb from 10,000 to Philadelphia, PA) AIAA, SAE, ASME, and ASEE, Joint Propulsion 40,000 ft has been reduced by 12.5 percent. Increases in Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 7 p. acceleration of 9.3 and 13 percent have been obtained at (AIAA PAPER 87-1839) intermediate and maximum power, respectively. No engine This paper summarizes the results of testing on the U.S. Army anomalies have been detected for EPR increases up to 12 XCH-62 Heavy Lift Helicopter (HLH) combiner transmission. This percent. V.L. transmission is rated at 10,620 hp. Program elements included design and fabrication of new bevel gears, static and dynamic. A87-45248# strain surveys of the transmission gears, optimization of gear USE OF RPM TRIM TO AUTOMATE THE SUPERSONIC bending stresses following the first strain survey, correlation of ENGINE/INLET MATCH IN THE SR-71A FEM analysis with measured stresses, evaluation of a new lubricant J. R. WILSON and V. A. WRIGHT (Lockheed-California Co., to raise the scuffing/scoring load limitation, measurement of gear Burbank) AIAA, SAE, ASME, and ASEE, Joint Propulsion tooth temperatures under operation conditions, and load testing. Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 8 p. The findings establish that 100 percent of design loading was (AIAA PAPER 87-1848) attained within the permissible range of measured gear tooth In the design of an engine for a supercruise vehicle, the bending stress limits, AEO conditions; 95 percent of design loading capabilities of the anticipated inlet system must be very carefully was attained within the above limits, OEI conditions. Alternating integrated with the requirements of the engine. Analytical stresses on the collector gear set the load limits. Further analytical predictions are described that make it possible to achieve significant effort is required to accurately predict the stress levels in gears performance gains in the SR-71A Mach 3 + aircraft by incorporating loaded on both sides of the teeth as is the collector gear. a fairly simple change into the engine control system which allows Author the two systems to communicate. In particular, an RPM change is

667 07 AIRCRAFT PROPULSION AND POWER

added to the engine, which makes it possible to effect a match waves at the inlet shock, flame sheet, and exit nozzle along with between the engine and inlet airflows. The results of flight testing acoustic admittances at the inlet and exit are combined to verified the predicted improvements. I.S. determine the stability of the system as well as the acoustic modes. Since the acoustic and entropy waves travel at different velocities, A87-45263# the geometry is a critical factor in determining stability. Typical SIMULATION OF PERFORMANCE, BEHAVIOUR AND FAULTS values of the admittances will produce damped solutions when OF AIRCRAFT ENGINES the entropy is neglected, but, as the ratio of the entropy to acoustic G. TORELLA (Accademia Aeronautica, Pozzuoli, Italy) AIAA, fluctuations is increased, the coupling can either feed acoustic SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San energy into or out of different modes independently. This transfer of energy has a destabilizing or stabilizing effect on the acoustic Diego, CA, June 29-July 2, 1987. 12 p. refs modes of the system depending upon the phase of the energy (AIAA PAPER 87-1868) transfer. Author Italian Air Force Academy efforts to develop numerical codes for simulating aircraft engines are described. Consideration is given to codes for: (1) design point calculations, (2) calculations in A87-45275"# National Aeronautics and Space Administration. off-design conditions, and (3) simulation of faults in the Langley Research Center, Hampton, Va. components. These codes are used like 'paper engine test beds' A MIXING AUGMENTATIONTECHNIQUE FOR HYPERVELOCITY where the engineers and pilots can study the behavior of a SCRAMJETS particular engine in both steady- and unsteady-state flight A. KUMAR, D. M. BUSHNELL, and M. Y. HUSSAINI (NASA, Langley conditions. These codes are both reliable and flexible and have Research Center, Hampton, VA) AIAA, SAE, ASME, and ASEE, emerged as powerful tools in the learning process. K.K. Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 16p. refs A87-45264# (AIAA PAPER 87-1882) SYSTEM PERFORMANCE APPROACH TO AIR BREATHING The paper discusses mixing problems in hypervelocity scramjet PROPULSION DESIGN - A NEW UNDERGRADUATE OESIGN combustors. Techniques for providing turbulence and/or mixing COMPETITION enhancement are described. One such technique, the oscillating JACK D. MA'FTINGLY (USAF, Aero Propulsion Laboratory, shock interaction, is studied numerically and options for producing Wright-Patterson AFB, OH) AIAA, SAE, ASME, and ASEE, Joint oscillatory shock waves for mixing augmentation in scramjet Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. combustors are discussed. Author 7p. (AIAA PAPER 87-1869) A87-45279"# Purdue Univ., West Lafayette, Ind. This paper describes the Air-Breathing Propulsion Design A PANEL METHOD FOR COUNTER ROTATING Competition, a new undergraduate design competition sponsored M. H. WILLIAMS (Purdue University, West Lafayette, IN) and S. by AIAA through its Air-Breathing Propulsion Technical Committee H. CHEN AIAA, SAE, ASME, and ASEE, Joint Propulsion and Student Activities Committee. This new design program uses Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 12 p. the specification of the required aircraft system performance as refs identified by the customer as the starting point of the engine (Contract NAG3-499) design process. The design process for this new competition is (AIAA PAPER 87-1890) described in terms of its individual steps, including constraint A time domain source-doublet surface paneling method is analysis, mission analysis, cycle analysis, engine cycle selection, developed for analyzing the unsteady loads on counter rotating engine sizing and performance, component design, and integration and communications. C.D. propellers in incompressible irrotational flow. A scheme for treating the blade-wake interaction problem is described. Sample results for single rotation propellers are given, with comparisons to A87-45266# alternate theories and experiment. Finally, some preliminary results VORTEX-NOZZLE INTERACTIONS IN RAMJET COMBUSTORS for quasi-steady and fully unsteady loads on counter rotating K. YU, S. LEE, A. TROUVE, H. STEWART, and JOHN W. DAILY systems are presented. Author (California, University, Berkeley) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987.20p. refs (Contract N00014-84-K-0372) A87-45289"# National Aeronautics and Space Administration. (AIAA PAPER 87-1871) Lewis Research Center, Cleveland, Ohio. A facility designed to study the role of vortex-nozzle interactions CONTINGENCY POWER FOR SMALL TURBOSHAFT ENGINES in promoting low frequency instabilities in ramjet combustors is USING INTO TURBINE COOLING AIR described. The design issues are outlined, as are potential THOMAS J. BIESIADNY, BRETT BERGER (NASA, Lewis Research instabilities. Preliminary data are reported for both cold and Center, Cleveland, OH), GARY A. KLANN, and DAVID A. CLARK combusting flow. For the cold flow cases studied it appears that (NASA, Lewis Research Center; U.S. Army, Propulsion Directorate, there may be a flapping instability of the jet entering the combustor Cleveland, OH) AIAA, SAE, ASME, and ASEE, Joint Propulsion at the dump plane. For reacting flow, a pulsating, acoustically Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. coupled instability is important for the case studied. Author Previously announced in STAR as N87-20280. refs (AIAA PAPER 87-1906) A87-45267# Because of one engine inoperative requirements, together with PRESSURE OSCILLATIONS AND ACOUSTIC-ENTROPY hot-gas reingestion and hot day, high altitude takeoff situations, INTERACTIONS IN RAMJET COMBUSTION CHAMBERS power augmentation for multiengine rotorcraft has always been of JOSEPH W. HUMPHREY and F. E. C. CULICK (California Institute critical interest. However, power augmentation using overtempera- of Technology, Pasadena) AIAA, SAE, ASME, and ASEE, Joint ture at the turbine inlet will shorten turbine life unless a method of Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. limiting thermal and mechanical stresses is found. A possible sol- 11 p. refs ution involves allowing the turbine inlet temperature to rise to aug- (Contract N00014-84-K-0434) ment power while injecting water into the turbine cooling air to limit (AIAA PAPER 87-1872) hot-section metal temperatures. An experimental water injection A one-dimensional analytical model is presented for calculating device was installed in an engine and successfully tested. Although the longitudinal acoustic modes of idealized 'dump-type' ramjet concern for unprotected subcomponents in the engine hot section engines. The model contains the matching required to place an prevented demonstration of the technique's maximum potential, it oscillating flame sheet in the interior of a was still possible to demonstrate increases in power while maintain- with mean flow. The linear coupling of the acoustic and entropy ing nearly constant turbine rotor blade temperature. Author

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A87-45290# A87-45299# APU FUEL EFFICIENCY AND AFFORDABILITY FOR AN EXPERIMENTAL INVESTIGATION OF TURBINE CASE COMMERCIAL AIRCRAFT TREATMENTS C. RODGERS and D. C. JOHNSON (Sundstrand Corp., Turbomach L. S. OFFENBERG, J.D. FISCHER, and T. J. VANDER HOEK Div., San Diego, CA) AIAA, SAE, ASME, and ASEE, Joint (Garrett Turbine Engine Co., Phoenix, AZ) AIAA, SAE, ASME, Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, 13 p. refs June 29-July 2, 1987. 6 p. (AIAA PAPER 87-1907) (AIAA PAPER 87-1919) The fuel efficiency and life cycle cost of small gas turbine This paper presents the results of the Garrett Turbine Case auxiliary power units (APU) for commercial aircraft applications is Treatment Study Program carried out under the sponsorship of examined. Fuel efficiency has been improved through the use of the USAF Aero Propulsion Laboratory. The objective of this program higher cycle pressure ratios. However, a higher pressure ratio, was to develop an understanding of the effect of shroud trenching and associated increase in compressor discharge temperature, on axial turbine performance and the trenching parameters that results in an incompatibility with commercial aircraft most affect turbine efficiency. A test program that included 12 temperature and pressure limits. This has led to the introduction shroud configurations was completed. At nominal tip clearance, a of load compressor and dual spool APU's. Both of these smooth, untrenched shroud was found to be the most efficient. approaches have increased design sophistication, increased cost, As tip clearance increased, shroud trenching became more and reduced durability. A complex trade off arises between the advantageous. Author design constraints of fuel efficiency and total cost. The paper identifies the trade off parameters which must be addressed in A87-45301 # order to select an optimum APU design solution for future F-15 SMTD HOT GAS INGESTION WIND TUNNEL TEST commercial type aircraft applications. Author RESULTS WILLIAM B. BLAKE and JAMES A. LAUGHREY (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, A87-45292# CA, June 29-July 2, 1987. 8 p. refs A DERIVATIVE ENGINE BASED ON NEW TECHNOLOGY - LOW (AIAA PAPER 87-1922) RISK; COST EFFECTIVE Key results from a hot gas ingestion test conducted on a 0.075 W. P. PAINI (General Motors Corp., Allison Gas Turbine Div., scale model of the F-15 SMTD (STOL and Maneuver Technology Indianapolis, IN) AIAA, SAE, ASME, and ASEE, Joint Propulsion Demonstrator) are presented. Hot exhaust gases of 500 F are Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. used to simulate the reverser flow. Ingestion is determined by (AIAA PAPER 87-1910) temperature increases measured at the engine face. The The advantages of fulfilling new propulsion system requirements temperature data are correlated using the reverser jet to free-stream with the derivative engine approach are described using as a mass flux ratio. Reductions in the reverser vane angle and specific example the T406 engine, conceived and constructed as increases in the sideslip angle reduce the ingestion velocity. Ground a simple engine employing low-risk technology appropriate for the pressure data and exterior inlet wall temperature data are compared V-22 propulsion system. The V-22 propulsion system requirements as indicators of ingestion onset. Author are reviewed, and the T406 engine's physical features are described in some detail. The performance of the T406 is A87-45304# summarized, and its risk and cost effectiveness are evaluated, MICRO-COMPUTER/PARALLEL PROCESSING FOR REAL TIME individually studying the compressor, combustor, and gas generator TESTING OF GAS TURBINE CONTROL SYSTEMS turbine. Improvements that can be made in the basic engine are S. P. ROTH and L. A. CELIBERTI (Pratt and Whitney, West Palm discussed. C.D. Beach, FL) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. refs (AIAA PAPER 87-1926) A87-45295# An experimental multiprocessor real time engine simulation INFLUENCE OF VANE/BLADE SPACING AND COLD-GAS system, 'EMPRESS', for the verification of full authority digital INJECTION ON VANE AND BLADE HEAT-FLUX electronic controls for gas turbine engines is described. The DISTRIBUTIONS FOR THE TELEDYNE 702 HP TURBINE evolution, design, and use of these microprocessor based STAGE simulation benches, and their role in the development and testing M. G. DUNN (Calspan Advanced Technology Center, Buffalo, NY) of integrated flight and propulsion control systems for future aircraft, and R. E. CHUPP (Teledyne, Inc., Teledyne CAE, Toledo, OH) are discussed. Parallel processing in EMPRESS provides the fidelity AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, to accurately model engine performance, while offering simplicity San Diego, CA, June 29-July 2, 1987. 11 p. Research supported and ease of modification. The software verification steps (code by the Teledyne CAE Independent Research and Development read, module test, module integration test, and hardware/software Funds. refs integration test) for the module, software, electronic, and control (AIAA PAPER 87-1915) data acquisition verification benches, are discussed. R.R. The effects of the vane/blade spacing and the cold gas injection on the vane and blade time-averaged Stanton number distrubutions" A87-45305# were determined for the Teledyne CAE 702 HP full-stage rotating HIGHLY RELIABLE, MICROPROCESSOR-BASED ENGINE turbine for two different vane/blade axial spacings, 0.19 C(s) and CONTROL 0.50 C(s). The experimental technique used the short-duration TIMOTHY J. LEWIS (USAF, Aero Propulsion Laboratory, shock-tunnel approach for which a shock tube was used as a Wright-Patterson AFB, OH) AIAA, SAE, ASME, and ASEE, Joint short-duration source of heated and pressurized air directed into Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. the turbine stage. The cooling gas was injected through discrete 13p. circular holes on the vane pressure and suction surfaces, and in (AIAA PAPER 87-1927) one case, through holes in the nozzle guide vane ring near the Following a discussion of the evolution of engine controls, the tip region as well as through the vane holes. It was found that two-phase Integrated Reliable Fault Tolerant Control for Engines the values of the vane/blade spacing used had little effect on the (INTERFACE) program, and the fabrication of upgraded versions Stanton number distribution on both the vane and the blade. The of the redundant control systems, are considered. Requirements cold-gas injection influenced the vane (but not the blade) for the INTERFACE controllers are described which are based on Stanton-number distribution. I.S. engine configurations to be used in the next generation tactical

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fighters. The near complete absence of software penalty for A87-45348# redundancy managment implementation is a strength of both the ADVANCEMENTS IN HYDROGEN EXPANDER AIRBREATHING triplex and dual-dual architectures described. The requirement of ENGINES keeping nonapplication software to a minimum is fulfilled by both M. R. GLICKSTEIN and T. H. POWELL (Pratt and Whitney, controllers. The bench testing is also discusssed. R.R. Engineering Div., West Palm Beach, FL) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 6 p. A87-45308# (AIAA PAPER 87-2003) FUTURE ADVANCED CONTROL TECHNOLOGY STUDY Three aircraft propulsion system concepts based on variation (FACTS) - A LOOK AT EMERGING TECHNOLOGIES of the hydrogen expander cycle were examined to determine their S. J. PRZYBYLKO (USAF, Wright Aeronautical Laboratories, relative merits: a single-spool regenerative air-turboramjet (ATR), Wright-Patterson AFB, OH) AIAA, SAE, ASME, and ASME, Joint a preburning ATR, and a twin-spool hydrogen expander. These Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. concepts were compared with respect to their mechanical 9 p. refs arrangement, performance, and operational capabilities. The direct (AIAA PAPER 87-1930) use of heated hydrogen was shown to result in a heavy engine, Pertinent aspects, identified by the FACTS program, of six due to requirements for a heat exchanger, a gearbox, and a large number of turbine stages. The preburner ATR produced the lightest emerging technologies which are considered candidates for application to the control and accessory systems of future aircraft weight engine but exhibited a significant loss in (Isp) due to the requirement for an onboard oxidizer. On the other turbine engines are discussed. The technologies considered include fiber-optic sensors; VHSIC/GaAs technology; high-temperature hand, the twin-spool gas generator cycle exhibited a moderate electronics; parallel processing using VHSlC technology; electrical engine thrust-to-weight with high Isp, but did so with added power drive and actuation; and the use of composite materials in mechanical complexity. Thus, the choice of the best engine is electronics control housings, actuators, and pumps. Issues mission-dependent: missions with long cruise legs benefit from considered in the selection of these technologies include weight high Isp, while those with high thrust Ioadings demand high savings, improvement of material radiation tolerance, reduction of thrust-to-weight ratio. I.S. component operating temperatures, and extension of the operating temperature limits of hydraulic systems. R.R.

A87-45333# INTEGRATION OF PROPULSION/INTEGRATION TEST A87-45353# RESULTS THROUGH THE USE OF REFERENCE PLANE DIGITAL CONTROL DEVELOPMENT FOR THE T56-A-427 TRANSFERS J. V. DANILUCK (General Motors Corp., Allison Gas Turbine Div., JAMES NEELY (Sverdrup Technology, Inc., Arnold Air Force Indianapolis, IN) AIAA, SAE, ASME, and ASEE, Joint Propulsion Station, TN) and TRAVIS BINION (Calspan Corp., Arnold Air Force Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 13 p. Station, TN) AIAA, SAE, ASME, and ASEE, Joint Propulsion (Contract NAVAIR TASK AIR-536) Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. (AIAA PAPER 87-2013) (AIAA PAPER 87-1964) The T56-A-427 engine control system, with a unique software Use of the concept of reference plane transfers in designing a algorithm for horsepower control, has demonstated horsepower test methodology for determination of the various terms in a force and temperature control superior to previous T56 engines. This accounting system for a hypersonic vehicle is considered. The control should result in extended engine/gearbox life. The present role played by the technologies of diagnostics and computational control system provides bogdown/surge protection, far fewer fluid dynamics is discussed. It is noted that the effects of specific restrictions on power lever movement, and improved reliability and heat on the aerodynamic forces, and the effects of nonair on maintainability. Use of an in-circuit development system permitted combustion, must be quantified. Factors influencing the test on-line control development that significantly reduced time in objectives include forebody shaping, verification of the aerodynamic matching engine program goals. Favorable engine and flight tests results have been obtained. R.R. reference planes, replication of heat transfer effects on the forebody, and spurious reflected waves. Facility design must be driven by considerations of minimum scale, minimum run time, and measurement accuracy, in addition to the need to reproduce the required test conditions. R.R.

A87-45354# A87-45347# APPLICATION OF COMPUTATIONAL FLUID DYNAMICS TO STANDING OBLIQUE DETONATION WAVE ENGINE ANALYSIS OF EXHAUST GAS/DIFFUSER INTERACTIONS IN PERFORMANCE A TURBINE ENGINE ALTITUDE TEST CELL M. J. OSTRANDER, J. C. HYDE, M. F. YOUNG, R. D. KISSINGER M. A. CROSS (Sverdrup Technology, Inc., Arnold Air Force Station, (Aerojet TechSystems Co., Sacramento, CA), and D. T. PRATT TN) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, (Washington, University, Seattle) AIAA, SAE, ASME, and ASEE, 23rd, San Diego, CA, June 29-July 2,1987. 11 p. refs Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July (AIAA PAPER 87-2014) 2, 1987. 10 p. refs An experimental and computational fluid dynamics (CFD) study (Contract F04611-86oC-0095) of exhaust gas/diffuser interaction was performed to identify the (AIAA PAPER 87-2002) cause of excessive heating in a turbine engine altitude test cell. A ramjet propulsion system concept involving premixing of air The presence of exhaust gas recirculation indicated by CFD studies and fuel and combustion by means of a stabilized oblique was confirmed by experimental infrared scanner results. Increases detonation wave, rather than the scramjet's diffusive burning, is in temperature levels in the test cell were found to coincide with presently considered as a basis for hypersonic propulsion. Rapid the overexpansion of the jet and the exhaust gas recirculation. A chemical reactions in the fuel/air mixture downstream of the last Navier-Stokes model predicted no recirculation into the test cell shock are used to release energy into the flowing stream and when the nozzle was underexpanded, whereas simulation of the thereby couple with the shock wave to form a standing oblique overexpanded flow predicted unsteady recirculation into the test detonation wave. The propulsion system region exposed to the cell from within the diffuser. It is noted that modeling of the test high temperature, high pressure combustion gases is much smaller cell geometry and boundary conditions is necessary to realistically than for the diffusive burning scramjet. O.C. simulate the recirculation. R.R.

670 07 AIRCRAFT PROPULSION AND POWER

A87-45369"# General Electric Co., Evendale, Ohio. implications of his decision during the study phase of the aircraft. NASA/GE ADVANCED LOW EMISSIONS COMBUSTOR Author PROGRAM E. E. EKSTEDT (General Electric Co., Evendale, OH) and J. S. A87-45378# FEAR (NASA, Lewis Research Center, Cleveland, OH) AIAA, 0ESIGNING FOR FRETTING FATIGUE FREE JOINTS IN SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San TURBOPROP ENGINE GEARBOXES Diego, CA, June 29-July 2, 1987. 10 p. refs A. SMAILYS and C. BROWNRIDGE (Pratt and Whitney Canada, (AIAA PAPER 87-2035) Mississauga) AIAA, SAE, ASME, and ASEE, Joint Propulsion The Advanced Low Emissions Combustor Program consisted Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 10 p. of the design and testing of advanced combustor concepts utilizing refs lean, premixed, prevaporized fuel and variable geometry. The (AIAA PAPER 87-2046) objective was to evaluate the potential of these combustor systems Results from the analysis and testing of propeller shafts and to provide very low pollutant emissions levels, superior performance flanges were used to develop an empirical relationship for predicting and high durability relative to contemporary combustor designs. fretting fatigue based on three parameters: (1) the induced surface Four full annular combustor concepts were designed and fabricated stress in the parts; (2) the amount of slip between the contacting for a 30:1 pressure ratio high bypass turbofan engine. The four surfaces; and (3) the maximum localized contact pressure. full annular combustors with active variable geometry were tested Experimental data on a dedicated test rig simulating a propeller at pressures up to approximately 0.7 MPa with Jet A fuel. The hub and propshaft flange demonstrated fretting fatigue cracks, two most promising concepts were also tested in a high pressure and results were correlated with a three-dimensional finite element sector combustor test rig capable of operation at the maximum analysis of the hub/flange. The analysis is applied to the design engine pressures. The high pressure sector combustor tests were of press fitted joints between a bullgear and propshaft, also subject conducted with Jet A and a fuel with reduced hydrogen content. to potential fretting fatigue problems. R.R. Results of the sector combustor tests are presented in this paper. The potential for very low emissions with premixed fuel was A87-45392"# National Aeronautics and Space Administration. demonstrated. However, autoignition or flashback within the Langley Research Center, Hampton, Va. premixing systems was encountered at high pressures. Further AN OUTLOOK ON HYPERSONIC FLIGHT development effort is required to address this problem area. GRIFFIN Y. ANDERSON (NASA, Langley Research Center, Author Hampton, VA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. A87-45370# refs NO(X) REDUCTION AND COMBUSTION PHENOMENA IN THE (AIAA PAPER 87-2074) MULTI-ANNULAR GAS TURBINE SWIRL BURNER The NASA Langley Research Center has been active in A. K. GUPTA (Maryland, University, College Park), N. hypersonic research since the 1950's. A central part of the research MARCHIONNA (AVCO Lycoming Textron, Stratford, CT), and L. conducted since 1970 has focussed on high speed airbreathing H. ONG AIAA, SAE, ASME, and ASEE, Joint Propulsion propulsion - in particular on supersonic combustion or Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 14 p. scramjets. Renewed interest in very high speed flight in the 1980's Research supported by AVCO Lycoming Textron. refs has led to some expansion and broadening of this activity with (AIAA PAPER 87-2036) particular attention to extreme speeds approaching orbital velocity. Experimental studies on a multiannular gas-turbine swirl burner The purpose of this paper is to review the impact of extreme (MASB) were performed to determine the effects of the burner's speed on the potential of scramjet propulsion. The implications of geometry, swirl distribution, and strength in various annuli, as well system performance objectives on propulsion and vehicle as the fuel/air distribution, on the overall NO(x) emission levels. requirements will be explored. Some pertinent results from past The results obtained on an experimental variable-geometry facility, studies will be summarized along with examples of engineering with natural gas as the fuel at atmospheric conditions, facility, design and detailed analysis methods applied to typical scramjet indicate that significant changes in the NO(x) emission levels can components. Critical areas where fundamental knowledge is lacking be obtained by small changes in the input operational parameters will be highlighted, and some proposed studies to deal with these uncertainties will be outlined. Author to the burner. Extrapolation of the NO(x) data to practical operating conditions of a gas turbine revealed a potential of MASB for providing very low NO(x) emission levels from gas-turbine A87-45393# combustors. Preliminary results obtained with this combustor also AN IMPROVED COMPUTATIONAL MODEL FOR A SCRAMJET revealed high combustion efficiency and intensity as compared to PROPULSION SYSTEM conventional swirl burners. I.S. THOMAS R. A. BUSSING and GARY L. LIDSTONE (Boeing Military Airplane Co., Seattle, WA) AIAA, SAE, ASME, and ASEE, Joint A87-45376# Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. TRANSMISSION EFFICIENCY IN ADVANCED AEROSPACE 16 p. refs POWERPLANT (AIAA PAPER 87-2078) J. DOMINY (Rolls-Royce, PLC, Derby, England) AIAA, SAE, A mixing model representative of three-dimensional H2 fuel ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, injection into a scramjet combustor has been incorporated into CA, June 29-July 2, 1987.6 p. refs the SAIC scramjet propulsion program package. The model conserves mass, momentum and energy and uses the (AIAA PAPER 87-2043) The consideration of future aerospace powerplant requiring high experimentally generated H2 mass fraction correlations due to power reduction gearboxes has necessitated the development of Cohen, Coulter and Egan for closure. Computations preformed an analytical method of estimating the efficiency of candidate with this package have shown that fuel injection can increase transmissions. Efficiency becomes important not in terms of the combustor pressures substantially. Author cycle itself but to the installed efficiency of the engine. Inefficient gearboxes will require large cooling systems imposing penalties in A87-45404# bulk, weight and drag. The analysis has been calibrated against OPERATIONAL ENGINE USAGE AND MISSION ANALYSIS the existing Tyne transmission and then applied to gearboxes for MARK J. NIENHAUS (General Dynamics Corp., Fort Worth, TX) single and contra rotating propfans and larger Ultra-High-Bypass AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, Ratio engines. In all cases the predicted efficiencies are broadly San Diego, CA, June 29-July 2, 1987. 10 p. refs acceptable. The single most powerful influence is the gearbox (AIAA PAPER 87-2097) configuration which is generally imposed by airframe requirements. The use of a flight loads recorder (FLR) system to monitor It is important that the airframe manufacturer be aware of the engine usage and assess the impact of usage on the integrity of

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the aircraft is studied. Engine usage and mission analysis are A87-45409# concerned with the correlation of engine events that expend useful THREE STREAM TURBOFAN-VARIABLE CYCLE ENGINE WITH engine life with aircraft activity and operational usage mission types. INTEGRAL TURBOCOMPRESSOR The F-16/F100 FLR engine usage and mission analysis programs, GARY M. PERKINS (Pratt and Whitney, Engineering Div., West which are a series of four computer procedures that provide engine Palm Beach, FL) AIAA, SAE, ASME, and ASEE, Joint Propulsion use/fleet management data, are examined. The functions of the Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 6 p. four programs, power level angle (PLA)-I, ADDER, PLA-2, and (AIAA PAPER 87-2104) MIXER are described. The validity of the FLR data is evaluated. A variable cycle turbofan engine featuring an additional bypass Total accumulated life (TAC)/total operating time and TAC/engine stream has been conceptualized. In conjunction with the flight time ratio are calculated and compared with events history conventional thrust-producing duct and core streams, the concept recorder (EHR) data. It is observed that the FLR estimates are features an independent, coannular bypass stream to provide lower than the EHR data; however, the FRL data is valid and pressurized air for special application aircraft. This 'turbocompres- reliable. The engine structure integrity program for engine usage sor' stream can be sized to provide much more flow than possible data analysis is discussed. I.F. from core engine bleed and without the attendant debit on core performance. Maximum lift power can be developed at hover or low-speed approach with rapid thrust response for control, go- A87-45406# around, or maneuver. In the low-thrust mode, the engine functions ENGINE VARIABLE GEOMETRY EFFECTS ON COMMERCIAL mainly as a turbocompressor. The system can quickly transition to SUPERSONIC TRANSPORT DEVELOPMENT high thrust output while simultaneously supplying bleed power for RONALD B. STEINMETZ and BOB G. HINES (General Electric lift. Author Co., Cincinnati, OH) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. A87-45410# 5p. CYCLE SELECTION CONSIDERATIONS FOR HIGH MACH (AIAA PAPER 87-2101) APPLICATIONS The widely diversified requirements, such as reduced noise at RICHARD A. JOHNSON (General Motors Corp., Allison Gas Turbine takeoff and approach, efficient supersonic cruise, and significant Div., Indianapolis, IN) AIAA, SAE, ASME, and ASEE, Joint off-design usage of a commercial SST require a propulsion system Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. capable of efficient performance over a wide range of operation. 10p. The benefits to the propulsion/aircraft system accruing from engine (AIAA PAPER 87-2105) variable geometry in meeting the requirements can be quantified The paper utilizes propulsion system efficiency and Breguet in terms of aircraft Take Off Gross Weight (TOGW) and Fuel range as key relationships. Parametric performance is presented Burn (FB). These FB and TOGW improvements will be evaluated from Mach 1 to 6, showing the need for nozzle supercharging at by comparing a fixed-geometry, mixed-flow turbofan to a low speed and sufficiency of ram pressure at high speed. Propulsion variable-geometry/cycle engine at a 1990 IOC. Cycle and system efficiency fundamentally rises with velocity, justifying the configurational changes commensurate with Year 2000 IOC will choice of high flight speed. Turbomachinery-based cycles, be implemented for the variable geometry/cycle engine. Further, unconstrained by temperature limits, match ramjet performance at with this engine definition, a variable capture area inlet will be high speed. However, high inlet temperature will limit compressor employed so the engine variable geometry can be used to full and turbine operation to about Mach 4, necessitating conversion advantage in aircraft development. Author to ramjet mode above that speed. Mach 4 missions studied show the best performance with dry turbojet propulsion. Author A87-45407# DUAL CYCLE TURBOFAN ENGINE A87-45444"# National Aeronautics and Space Administration. F. A. SCHWEIGER (General Electric Co., Cincinnati, OH) AIAA, Langley Research Center, Hampton, Va. SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San EFFECTS OF SCALE ON SUPERSONIC COMBUSTOR Diego, CA, June 29-July 2, 1987. 9 p. PERFORMANCE (AIAA PAPER 87-2102) GLENN S. DISKIN and G. BURTON NORTHAM (NASA, Langley The subsonic Dual Cycle Turbofan Engine is a triple flow, dual Research Center, Hampton, VA) AIAA, SAE, ASME, and ASEE, shaft, double nozzle, partially-mixed turbofan where certain Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July variability has been employed to greatly enhance its flexibility and 2, 1987. 15p. refs performance. This engine utilizes a variable area core nozzle to (AIAA PAPER 87-2164) select nozzle thrust split, control shaft power split, control fan A series of tests has been carried out to investigate the effects operating line, increase takeoff thrust, and enhance performance. of various scale parameters on the direct connect scramjet This engine also employs a variable mixer area to give additional combustor performance. The calculated combustion efficiency performance improvement and to provide a significant amount of appears to be independent of scale for the same geometry, but reverse thrust with a simple reverser system. Author tests with more precise scaling of the entire combustor are required to verify this. Combustion, however, can be strongly dependent on geometry for the same scale. It is suggested that the beneficial A87-45408# aspects of certain geometric or scale variations can be combined VARIABLE CYCLE CONCEPTS FOR HIGH MACH to improve the overall performance. V.L. APPLICATIONS G. BLEVINS (USAF, Aero Propulsion Laboratory, Wright-Patterson A87-45453# AFB, OH), J. HARTSEL (General Electric Co., Evendale, OH), and PERFORMANCE ESTIMATION OF AN AIRCRAFT INTERNAL T. POWELL (Pratt and Whitney, West Palm Beach, FL) AIAA, COMBUSTION ENGINE SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San JOSEPH J. FRANZ (U.S. Navy, Naval Air Development Center, Diego, CA, June 29-July 2, 1987. 11 p. Warminster, PA) AIAA, SAE, ASME, and ASEE, Joint Propulsion (AIAA PAPER 87-2103) Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 5 p. Efforts made by the Air Force to identify advanced propulsion refs system candidates for high Mach cruise and acceleration (AIAA PAPER 87-2173) applications are described. Propulsion concepts under The NAVAIRDEVCEN has developed an analytical model of consideration include the turbojet, turboramjet, air turboramjet, and an aircraft internal combustion engine for performance estimation a variable cycle turbofan ramjet. An in-house study assessed the of an integrated propulsion system. The engine model is designed feasibility of advanced propulsion systems such as a turbo-scramjet to be integrated to a turbocharger and heat rejection system for or systems utilizing turbine bypass. K.K. performance design studies. The model accepts manifold air

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conditions, fuel/air ratio, engine delta pressure, crankshaft speed, A87-46176 and coolant temperature as inputs to provide output in the form INTERNATIONAL SYMPOSIUM ON AIR BREATHING ENGINES, of brake horsepower, fuel flow, exhaust gas temperature, and 8TH, CINCINNATI, OH, JUNE 14-19, 1987, PROCEEDINGS thermal flow rates. The analytical model has demonstrated good FREDERICK S. BILLIG, ED. (Johns Hopkins University, Laurel, correlation with test data throughout a range of engine MD) Symposium organized by General Electric Co. and U.S. performance. Author National Committee; Sponsored by General Electric Co. and International Society for Air Breathing Engines. New York, American Institute of Aeronautics and Astronautics, 1987, 785 p. For individual items see A87-46177 to A87-46262. A87-45454# The present conference on air-breathing aircraft engine WASTE HEAT RECOVERY SYSTEM FOR HIGH ALTITUDE technology considers topics in inlet design, radial-flow APPLICATION OF LIQUID COOLED, ENGINES turbomachinery, fuel injection and combustion systems, axial flow N. J. NAGURNY (U.S. Navy, Naval Air Development Center, compressor design and performance, ramjet configurations, turbine Warminster, PA) AIAA, SAE, ASME, and ASEE, Joint Propulsion flow phenomena, engine control and service life, fluid flow-related Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 7 p. problems, engine diagnostic methods, propfan design, combustor refs performance and pollutant chemistry, combustion dynamics, and (AIAA PAPER 87-2174) engine system analysis. Attention is given to thrust-vectoring A High Altitude Long Endurance Remotely Piloted Vehicle systems, supersonic missile air intakes, three-dimensional (HALE RPV) concept is currently being studied by the Naval Air centrifugal compressors, airblast atomizers, secondary flows in axial Development Center. Plans are for initial demonstrator vehicles to flow compressors, axial compressor blade tip clearance flows, be powered by two turbocharged, liquid cooled, piston engines. A hydrogen scramjets with sidewall injection, the performance of a major objective is to minimize fuel consumption so that the vehicle variable-geometry turbine, advanced tip clearance control systems, can stay aloft at greater than 60,000 feet for several days at a rotary jet mixing, fan blade aeroelastic behavior, flow dynamics in time. Waste heat from the engine coolant and turbochargers may combustion processes, and the technology of low cost drive a reverse Rankine cycle, producing electrical power for the turbomachinery. O.C. vehicle's radar and avionics. A nonazeotropic refrigerant mixture was selected as the working fluid for this study because it produces A87-46179# a higher cycle efficiency than single refrigerants. The Rankine FUTURE TRENDS - A EUROPEAN VIEW cycle, with its advantages and disadvantages, is compared with a S. C. MILLER (Rolls Royce, PLC, Derby, England) IN: International baseline, direct heat rejection system. When using the cycle during Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June a candidate mission, the vehicle endurance may be increased by 14-19, 1987, Proceedings . New York, American Institute of up to seven percent. While the waste heat recovery system in Aeronautics and Astronautics, 1987, p. 29-40. this paper is particularly geared for the Navy high altitude RPV, A comprehensive aerothermodynamic and economic evaluation the general principle would be applicable to other vehicles with of prospective development trends in both military and civilian critical endurance requirements and large heat sources. Author aircraft airbreathing propulsion systems is presented in view of West European requirements and technology base resources. While future trends in civil propulsion will be primarily determined by A87-45458# direct operating cost reduction criteria, those for military aircraft DEVELOPMENT OF DIGITAL ENGINE CONTROL SYSTEM FOR powerplants will be directed toward significant improvements in THE HARRIER II thrust/weight ratio and compatibility with multirole mission M. J. CAHILL, F. N. UNDERWOOD (McDonnell Aircraft Co., St. capabilities. Supersonic cruise without recourse to afterburners is Louis, MO), M. S. POPE (Rolls Royce, PLC, Bristol, England), and an attractive design goal for both military aircraft and civilian SSTs. J. A. CARVER (U.S. Navy, Naval Air Systems Command, V/STOL and hypersonic propulsion possibilities are also Washington, DC) AIAA, SAE, ASME, and ASEE, Joint Propulsion assessed. O.C. Conference, 23rd, San Diego, CA, June 29-July 2, 1987.9 p. (AIAA PAPER 87-2184) A87-46180# The development of a Digital Engine Control System (DECS) THRUST VECTORING - WHY AND HOW? for the Harrier II is reviewed. The program included the development W.-B. HERBST (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn, of DECS hardware and software, integration of the system into West Germany) IN: International Symposium on Air Breathing the Harrier II, and flight test evaluation of the system. Major goals Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . were to significantly reduce fuel control maintenance, improve New York, American Institute of Aeronautics and Astronautics, control capability, and maximize aircraft/engine compatibility. 1987, p. 41-46. Author A comprehensive presentation and development status evaluation is undertaken for thrust-vectoring nozzle research programs associated with the F-15 and F-14 fighters in the USA A87-45875# and the ND-102 and X-31A experimental aircraft in Germany. It is AIRCRAFT ENGINE DESIGN noted that the various applications of jet deflection differ JACK D. MA'r-IINGLY, WILLIAM H. HEISER, and DANIEL H. significantly; the essential criterion is the direction of jet deflection DALEY (U.S. Air Force Academy, Colorado Springs, CO) Research in either the pitch and/or yaw plane, or all-round. While supported by the General Electric Co. and USAF. New York, square-section nozzle configurations are restricted to deflection in American Institute of Aeronautics and Astronautics, Inc., 1987, only one plane, circular ones are suited to the all-round deflection 609 p. refs requirements of fighter aircraft 'supermaneuverability'. O.C. The present work, which is based on a design course offered at the U.S. Air Force Academy and serves as a companion text A87-46181# to Oates' (1984) 'Aerothermodynamics of Gas Turbine and IMPROVED AGILITY FOR MODERN FIGHTER AIRCRAFT. II - Propulsion', is broadly organized into considerations of engine cycle THRUST VECTORING ENGINE NOZZLES design and engine component design. Engine cycle design H. A. GEIDEL (MTU Motoren- und Turbinen-Union Muenchen encompasses aircraft/engine system constraint analysis, mission GmbH, Munich, West Germany) IN: International Symposium on analysis, on- and off-design condition cycle analyses, and the sizing Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, of the engine for a given installed performance. Engine component Proceedings . New York, American Institute of Aeronautics and design gives attention to global and interface qualities, rotating Astronautics, 1987, p. 47-54. refs turbomachine considerations, combustion systems, inlets, and A comparison is made of thrust-vectoring axisymmetric and exhaust nozzles. O.C. two-dimensional nozzles for different applications. The

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axisymmetricvectoringnozzlewillpermitvectoring with moderate A87-46218"# Virginia Polytechnic Inst. and State Univ., weight penalty; by contrast, the two-dimensional nozzle involves Blacksburg. extraordinary weight penalty and considerable construction DESIGN AND EVALUATION OF A NEW INJECTOR complexity. These difficulties are nevertheless offset by takeoff- CONFIGURATION FOR SUPERSONIC COMBUSTION and landing-improving thrust vectoring capabilities. Further nozzle TIMOTHY C. WAGNER, WALTER F. O'BRIEN (Virginia Polytechnic development efforts favor weight reduction by means of Institute and State University, Blacksburg), G. BURTON NORTHAM, nonmetallic, highly refractory composite materials. O.C. and JAMES M. EGGERS (NASA, Langley Research Center, Hampton, VA) IN: International Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . A87-46190# New York, American Institute of Aeronautics and Astronautics, PERFORMANCE PREDICTION IN A CENTRIFUGAL 1987, p. 390-397. refs COMPRESSOR IMPELLER Ignition and flameholding behavior data are presented from M. E. GILL (Cranfield Institute of Technology, Bedford, England) experiments with a novel scramjet injector configuration consisting and A. GOULAS (Salonika, University, Greece) IN: International of five small upstream pilot fuel injectors, a rearward-facing step, Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June and three primary fuel injectors downstream of the step; all injection 14-19, 1987, Proceedings . New York, American Institute of is perpendicular to the Mach 2 airflow, and the ignition source is Aeronautics and Astronautics, 1987, p. 133-138. refs located in the recirculation region downstream of the step. The The prediction of performance of a centrifugal impeller at design design attempts to minimize the amount of igniter energy required stage is increasingly important to produce more efficient machines for ignition, but without introduction of the large losses associated and to reduce development costs. The use of a with bluff bodies. Argon plasma, argon-hydrogen plasma, pyrophoric quasi-three-dimensional stream surface method, to provide both silane/hydrogen, and surface-discharge ignition sources are tested. velocity and entropy distributions and overall pressure ratio and The injector is found to be able to hold flames at 1400 R total efficiency, for a centrifugal impeller is described. A correction for temperatures without the use of large bluff bodies; the the effect of tip clearance losses is included. The predictions, argon-hydrogen plasma was the most effective igniter. O.C. with correction agree well with measured pressure ratio and efficiency, and the velocity profiles show the same features as A87-46226# those measured by laser anemometry. Author INTEGRATION OF ENGINE/AIRCRAFT CONTROL - 'HOW FAR IS IT SENSIBLE TO GO' A87-46212# V. A. FISHER (Rolls Royce, PLC, Bristol, England) IN: International EXPENDABLE TURBOJET COMPRESSOR DESIGN, TEST AND Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June DEVELOPMENT 14-19, 1987, Proceedings . New York, American Institute of T. W. VON BACKSTROM (Stellenbosch, University, Republic of Aeronautics and Astronautics, 1987, p. 453-458. Research South Africa) IN: International Symposium on Air Breathing supported by the Ministry of Defence (Procurement Executive). Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . A development history is presented for the propulsion control New York, American Institute of Aeronautics and Astronautics, systems of such high performance aircraft as Concorde, at the 1987, p. 331-338. refs outset, the 1970s Tornado, and most recently the European Fighter Two prototype compressors for a small, expendable, low cost Aircraft full authority digital engine controls. Engine control systems turbojet were designed, built and tested. The designs were of the modulate fuel flow for optimum performance; integration aspects axial transonic type, with double-circular-arc rotor blades machined of the operation of single and twin engine aircraft are discussed with a view to practical boundaries encountered in hardware that from solid 17-4 PH stainless steel, electron-beam welded integral rotor, externally inserted stator blades clamped by cables, and an must be marketable over a 10-20 year period. Integration methods unsplit aluminum compressor casing. The first prototype exhibited based on communications rather than physical joining are adequate surge margin for starting and running up to idle, and for recommended. O.C. slam acceleration from idle to full speed. Peak and full speed efficiencies were 80 and 71 percent. The second prototype had A87-46227# reduced first stage rotor blade camber, and tip clearance of all APPLICATION OF A FUZZY CONTROLLER IN FUEL SYSTEM rotor blades reduced to 0.35 mm instead of 0.5 mm. Peak and OF TURBOJET ENGINE full speed efficiencies increased to 0.84 and 0.75. In up to 75 CHI-HUA WU, YUN-HUA XU, and BEN-WEI LI (Northwestern percent design speed tests on a twice-full scale model, compressor Polytechnical University, Xian, People's Republic of China) IN: peak efficiencies of up to 0.87 were measured. Tests are International Symposium on Air Breathing Engines, 8th, Cincinnati, continuing. Author OH, June 14-19, 1987, Proceedings. New York, American Institute of Aeronautics and Astronautics, 1987, p. 459-464. A fuzzy control algorithm designed by the phase-plane method A87-46217"# Queensland Univ., St. Lucia (Australia). is presently used in the microprocessor-based control system of HYDROGEN SCRAMJET WITH SIDEWALL INJECTION - SHOCK a turbojet engine. Attention is given to the principles of fuzzy TUNNEL SIMULATIONS control, a comparison of the phase plane and membership degree R. G. MORGAN, A. PAULL, N. MORRIS, and R. J. STALKER fuzzy control system design methods, the microprocessor (Queensland, University, St. Lucia, Australia) IN: International program's flow chart, and the projected response of a given system Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June for different values of the adjustment parameter. O.C. 14-19, 1987. Proceedings . New York, American Institute of Aeronautics and Astronautics, 1987, p. 381-389. NASA-supported A87-46228"# National Aeronautics and Space Administration. research, refs Lewis Research Center, Cleveland, Ohio. A free-piston shock tunnel has been used to obtain test data INFLUENCE OF THIRD-DEGREE GEOMETRIC NON- on a scramjet combustion chamber with sidewall injection. The LINEARITIES ON THE VIBRATION AND STABILITY OF PRE- results obtained indicate that combustion was strongly influenced TWISTED, PRECONED, ROTATING BLADES by a region of fuel whose temperature was held below its ignition K. B. SUBRAHMANYAM and K. R. V. KAZA (NASA, Lewis temperature by wall-cooling effects; this increased the fraction of Research Center, Cleveland, OH) IN: International Symposium unburned fuel and resulted in a significant loss of specific impulse. on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, Aerodynamic heating would keep the walls above hydrogen ignition Proceedings . New York, American Institute of Aeronautics and temperature in an actual scramjet powerplant, however. Maximum Astronautics, 1987, p. 465-479. Previously announced in STAR as specific impulse was obtained with a combination of parallel and N86-31920. refs transverse injection in a long combustion chamber, followed by a The governing coupled flapwise bending, edgewise bending, dual stage expansion. O.C. and torsional equations are derived including third-degree goemetric

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nonlinear elastic terms by making use of the geometric nonlinear A87-46246# theory of elasticity in which the elongations and shears are EROSION PROBLEM OF AXIAL COMPRESSOR BLADES OF A negligible compared to unity. These equations are specialized for TURBOSHAFT ENGINE blades of doubly symmetric cross section with linear variation of R. V. NARAYANA MURTHY, V. UNNIKRISHNAN, B. G. Pretwist over the blade length. The nonlinear steady state equations AMARNATH (Defence Ministry, Resident Technical Office and the linearized perturbation equations are solved by using the /Engines/, Bangalore, India), and K. SRINIVASA IN: International Galerkin method, and by utilizing the nonrotating normal modes Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June for the shape functions. Parametric results obtained for various 14-19, 1987, Proceedings . New York, American Institute of cases of rotating blades from the present theoretical formulation Aeronautics and Astronautics, 1987, p. 619-626. refs are compared to those produced from the finite element code An account is given of the axial compressor blade erosion MSC/NASTRAN, and also to those produced from an in-house problem encountered during the operation of a single-engine experimental test rig. It is shown that the spurious instabilities, helicopter in a severe, sandy environment, with attention to cases observed for thin, rotating blades when second degree geometric of excessive sand erosion at the blade root which led to a reduction nonlinearities are used, can be eliminated by including the in natural frequency and an increase in fatigue damage due to third-degree elastic nonlinear terms. Furthermore, inclusion of third vibratory resonance. The sand ingestion test requirements in degree terms improves the correlation between the theory and airworthiness specifications emphasize the evaluation of experiment. M.G. performance loss and stability deterioration; more stringent precertification test requirements for the demonstration of sand erosion resistance are recommended. O.C.

A87-46239# INVESTIGATION ON THE STALL MARGIN OF A TURBOFAN ENGINE R. QUERZOLI and A. SBUTTONI (Aeritalia S.p.A., Gruppo Velivoli da Combattimento, Turin, Italy) IN: International Symposium on A87-46247# Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, PROPFAN PROPULSION SYSTEM DEVELOPMENT Proceedings . New York, American Institute of Aeronautics and A. S. NOVICK, R. E. RIFFEL (General Motors Corp., Allison Gas Astronautics, 1987, p. 561-567. Turbine Div., Indianapolis, IN), and C. N. REYNOLDS (Pratt and The stall margin of twin-spool, mixed flow turbofan engines, Whitney, East Hartford, CT) IN: International Symposium on Air and the effect exerted upon it by such factors as installation effects Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, and off-schedule engine controls, are presently assessed by ground Proceedings . New York, American Institute of Aeronautics and tests. High pressure stall lines were identified with the 'in-bleed' Astronautics, 1987, p. 629-634. method. Aircraft accessory loads are noted to influence the The Propfan propulsor provides the propulsive efficiency of steady-state working line, but do not significantly affect the surge contemporary propellers while achieving the 0.8 Mach cruise margin during transients. High pressure air bleeds are very effective capability of modern turbofan engines. Characteristics of Propfan in lowering both the steady state and the transient working line. propulsion systems present unique choices for designers. This The engine is virtually insensitive to inlet air distortion over the paper identifies advantages of the Propfan engine, assesses investigated speed range. O.C. configurations and their integration with commercial and military aircraft, and describes two Propfan flight test programs. Author

A87-46240# J85 SURGE TRANSIENT SIMULATION Y. SUGIYAMA (Japan Defense Agency, Technical Research and Development Institute, Tokyo), W. TABAKOFF, and A. HAMED A87-46248# (Cincinnati, University, OH) IN: International Symposium on Air MECHANICAL EVALUATION OF THE AEROELASTIC Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, BEHAVIOUR OF A FAN BLADE Proceedings . New York, American Institute of Aeronautics and J. L. LECORDIX (SNECMA, Villaroche, France), B. VINCENT, and Astronautics, 1987, p. 568-578. refs R. HENRY (Lyon, Institut National des Sciences Appliquees, Surge transient flow phenomena and unsteady compressor Villeurbanne, France) IN: International Symposium on Air Breathing operating-point excursion during surge in J85 turbojet engine, are Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . analyzed using a one-dimensional model which is capable of New York, American Institute of Aeronautics and Astronautics, simulating surge disturbance propagations throughout an entire 1987, p. 635-645. refs turbojet engine. Unknown stalled compressor stage characteristics This paper deals with the prediction of the aeroelastic stability are represented by parameters and predicted through the of bladed axisymmetric systems. All the aerodynamic/mechanical parametric study in such a way that the overall computed results couplings are taken into account over the full blade span. The must agree with surge data, such as hammer over-pressures at structure consists of twisted blades, modeled by special beam the compressor face and reduced burner-pressures. The prediction elements, including predominant effects such as bending - bending resulted in the stalled characteristics with faster responses and and bending - torsion coupling. The unsteady supersonic airflow larger pressure-ratio deterioration compared to low speed is determined at several airfoils sections along the span and the compressors. Surge hammer over-pressures are found to have a unsteady nodal forces are calculated. Modal reduction and solution triangle shape in time-space (engine axis) domain. Different stall of the aeroelastic system are established. The developed method methods result in different compressor operating-point excursion, and the associated computed program is applied to the analysis in which mass flows through compressor reduce to almost zero in of aeroelastic stability of a rotating advanced wide chord roughly 10 to 20 milliseconds, and thus affect surge transient unshrouded fan blade. The influence of the main aeroelastic flow phenomena such as levels of peak hammer over-pressures parameters are examined in order to find an efficient method at the intake duct and high temperatures in the compressor. capable of delivering accurate solutions at a reasonable price. Author Author

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A87-46249"# National Aeronautics and Space Administration. A87-46258"# Queensland Univ., Brisbane (Australia). Lewis Research Center, Cleveland, Ohio. PRESSURE SCALING EFFECTS IN A SCRAMJET COMBUSTION AEROELASTIC CONTROL OF STABILITY AND FORCED CHAMBER RESPONSE OF SUPERSONIC ROTORS BY AERODYNAMIC R. G. MORGAN and R. J. STALKER (Queensland, University, DETUNING Brisbane, Australia) IN: International Symposium on Air Breathing DANIEL HOYNIAK (NASA, Lewis Research Center, Cleveland, OH) Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . and SANFORD FLEETER (Purdue University, West Lafayette, IN) New York, American Institute of Aeronautics and Astronautics, IN: International Symposium on Air Breathing Engines, 8th, 1987, p. 730-736. NASA-supported research, refs Cincinnati, OH, June 14-19, 1987, Proceedings . New York, The test results obtained for a model scramjet over a range of American Institute of Aeronautics and Astronautics, 1987, p. pressure levels corresponding to different flight altitudes involve 646-658. refs enthalpies that vary from the ignition limit, at the low temperature Aerodynamic detuning, defined as designed passage-to-pass- end, to temperatures where the dissociation of combustion products age differences in the unsteady aerodynamic flow field of a rotor severely limits heat release. The minimum temperature is noted blade row, is a new approach to passive flutter and forced response to be highly pressure-sensitive; above the ignition limit, the amount control. Inthis paper, a mathematical model for aerodynamic detun- of heat release increased markedly with pressure and with ing is developed and utilized to demonstrate the aeroelastic stability combustion chamber length. A FEM computer code has been enhancement due to aerodynamic detuning of supersonic blade used to model the mixing and combustion processes. O.C. rows. In particular, a model is developed to analyze both the torsion mode and the coupled bending-torsion mode unstalled supersonic flutter and torsion mode aerodynamically forced response charac- A87-46261 # teristics of an aerodynamically detuned rotor operating in a super- ADVANCES IN TECHNOLOGY FOR LOW COST sonic inlet flow field with a subsonic leading edge locus. As smalll TURBOMACHINERY - A POTENTIAL TO ENHANCE THE solidity variations do not have a dominant effect on the steady-state ECONOMY OF FUTURE PROPULSION SYSTEM FOR GENERAL performance of a rotor, the aerodynamic detuning mechanism con- AND HELICOPTER AVIATION sidered is nonuniform circumferential spacing of adjacent blades. UWE DAMMEL (KHD Luftfahrttechnik GmbH, Oberursel, West Author Germany) IN: International Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings. New York, American Institute of Aeronautics and Astronautics, 1987, p. 753-757. The design criteria presently investigated for application to the A87-46253# small to medium-sized gas turbine engines used by general aviation EXHAUST CARBON - THE EFFECTS OF FUEL COMPOSITION aircraft and helicopters (as either primary powerplants or auxiliary D. KRETSCHMER and J. ODGERS (Universite Laval, Quebec, power units) are oriented toward cost reduction at optimal Canada) IN: International Symposium on Air Breathing Engines, performance levels. A number of advancements are achieved by 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . New York, this design process on the basis of improved aerodynamic, American Institute of Aeronautics and Astronautics, 1987, p. thermodynamic, and mechanical factors. Attention is given to 687-693. Research supported by the Federal Panel on Energy component-count minimization, short-length centrifugal compressor and DND. refs diffusers, simplified combustion chambers, air bearings, and Details are given of a series of experiments to determine the homopolar alternators. O.C. carbon (smoke) content of the exhaust of a small aircraft-type combustor tested with a range of commercially pure hydrocarbon compounds. The results are then correlated using a modified A87-46262# version of an equation developed some time ago within these A STUDY ON THE OPTIMIZATION OF JET ENGINES FOR laboratories. If a reference datum is supplied the correlation may COMBAT AIRCRAFTS be used to predict what happens as conditions and/or fuels are C. SANCHEZ TARIFA and E. MERA DIAZ (Escuela Tecnica changed within any given combustor but for general prediction Superior de Ingenieros Aeronauticos, Madrid, Spain) IN: purposes the correlation is not very satisfactory since the quantity International Symposium on Air Breathing Engines, 8th, Cincinnati, of exhaust carbon is also a function of combustor air distribution OH, June 14-19, 1987, Proceedings. New York, American Institute and geometry. Author of Aeronautics and Astronautics, 1987, p. 758-762. The optimization of jet engines for combat aircraft is discussed. This optimization is referred to the selection of the values of the engine fan pressure ratio or by-pass ratio, maximum turbine inlet temperature, overall pressure ratio, and maximum reheat A87-46255# temperature: which optimize the specific fuel consumption and NUMERICAL SIMULATION OF DIFFUSOR/COMBUSTOR DOME the ratio of the thrust to the nozzle throat area (assuming this INTERACTION last parameter to be an indicative of the thrust/weight ratio). The D. JEANDEL, G. BRUN (Lyon, Ecole Centrale, Ecully, France), S. selection is carried out taking into account the aircraft missions MEUNIER, and M. DESAULTY (SNECMA, Villaroche, France) IN: for which the engine design is optimized. Author International Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings. New York, American Institute of Aeronautics and Astronautics, 1987, p. 702-709. refs A87-46372 Precise knowledge of the aerodynamic field over the cowls on V.2500 - BACK ON COURSE? a combustor dome is essential to reach satisfactory performance. JULIAN MOXON Flight International (ISSN 0015-3710), vol. 131, A stairstep technique gives a poor description of the geometry. June 13, 1987, p. 101-105. To circumvent this drawback a finite-element method is described The V.2500 turbofan engine, a 25,000-1b thrust class powerplant in this paper. In addition of its ability to cope with fairly complex intended for the A320 airliner, is being developed by a configurations, a special treatment of the boundary conditions seven-company, five-nation consortium in order to compete with makes a two-dimensional calculation of the flow around a the CFM56-5 engine after its service entry date of April, 1989. combustor and prediction of the flow-split in the various orifices Consortium spokesmen maintain that the V.2500's fuel possible. Examples of calculated results for typical modern annular consumption will be 7-8 percent lower than that of the CFM56-5. combustors are given. Comparisons with experimental data show Attention is given to difficulties with the high pressure compressor good predictions of wall static pressures and aerodynamic flow that compelled the reduction of its pressure rise from 22:1 to split. Author 18:1. A cut-away drawing is included. O.C.

676 07 AIRCRAFT PROPULSION AND POWER

N87-25323"# Garrett Turbine Engine Co., Phoenix, Ariz. flow, parabolized Navier-Stokes, and Navier-Stokes codes. Likely COMPOUND CYCLE ENGINE FOR HELICOPTER future directions of CFD applied to engine flows are described, APPLICATION and current barriers to continued progress are highlighted. The JERE G. CASTOR 25 Apr. 1986 12 p potential importance of the Numerical Aerodynamic Simulator (NAS) (Contract NAS3-24346; DA PROJ. 1L1-61102-AH-45) to resolution of these difficulties is suggested. Author (NASA-CR-175110; NAS 1.26:175110; AD-A180007; USAAVSCOM-TR-86-C-15) Avail: NTIS HC A02/MF A01 CSCL 21E The Compound Cycle Engine (CCE) is a highly turbocharged, power compounded, ultra-high power density, light-weight . The turbomachinery is similar to a moderate pressure ratio, free power turbine engine and the diesel core is high speed and a low . This engine is considered a potential candidate for future military light helicopter applications. This executive summary presents cycle thermodynamic (SFC) and N87-26044"# Texas A&M Univ., College Station. Engineering engine weight analyses performed to establish general engine Experiment Station. operating parameters and configuration. An extensive performance MEASUREMENT OF THE EFFECT OF MANUFACTURING and weight analysis based on a typical two hour helicopter (+30 DEVIATIONS ON NATURAL LAMINAR FLOW FOR A SINGLE minute reserve) mission determined final conceptual engine design. ENGINE GENERAL AVIATION AIRPLANE Final Report With this mission, CCE performance was compared to that of a Feb. 1987 118p T-800 class gas turbine engine. The CCE had a 31% lower-fuel (Contract NAG1-309) consumption and resulted in a 16% reduction in engine plus fuel (NASA-CR-180671; NAS 1.26:180671; AERO-TR-87-2) Avail: and fuel tank weight. Design SFC of the CCE is 0.33 Ib-HP-HR NTIS HC A06/MF A01 CSCL 21G and installed wet weight is 0.43 Ibs/HP. The major technology Renewed interest in natural laminar flow (NLF) had rekindled development areas required for the CCE are identified and briefly designer concern that manufacuring deviations may destroy the discussed. GRA effectiveness of NLF for an operational aircraft. Experiments are summarized that attemtped to measure total drag changes N87-25326# Ecole Polytechnique Federale de Lausanne associated with three different wing surface conditions on an aircraft (Switzerland). Lab. de Thermique Appliquee. typical of current general aviation high performance singles. The AEROELASTIClTY IN TURBOMACHINES COMPARISON OF speed power technique was first used in an attempt to quantify THEORETICAL AND EXPERIMENTAL CASCADE RESULTS. the changes in total drag. Predicted and measured boundary layer APPENDIX AS: ALL EXPERIMENTAL AND THEORETICAL transition locations for three different wing surface conditions were RESULTS FOR THE 9 STANDARD CONFIGURATIONS Final also compared, using two different forms of flow visualization. Report, 2 May 1984 - 1 Nov. 1985 The three flight test phases included: assessment of an unpainted A. BOELCS and T. H. FRANSSON 1986 422 p airframe, flight tests of the same aircraft after painstakingly filling (Contract AF-AFOSR-0105-84) and sanding the wings to design contours, and similar measurement (AD-A180534; AFOSR-87-0605TR-APP-A-5) Avail: NTIS HC after this aricraft was painted. In each flight phase, transition A18/MF A01 CSCL 20D locations were monitored using with sublimating chemicals or Reliable, efficient methods are needed for calculating unsteady pigmented oil. Two-dimensional drag coefficients were estimated blade forces in turbomachines. The validity of such theoretical or using the Eppler-Somers code and measured with a wake rake in empirical prediction models can be established only if their flutter a method very similar to Jones' pitot travers method. The net and forced vibration predictions are applied to a number of well change in two-dimensional drag coefficient was approximately 20 documented experimental test cases. In this report, the geometrical counts between the unpainted aircraft and the hand-smoothed and time average flow conditions of nine two dimensional and aircraft for typical cruise flight conditions. Author quasi-three dimensional experimental (mainly) standard configurations for aeroelasticity in turbomachine cascades are given. Some aeroelastic test cases are defined for each configuration, comprising different incidence angles, Mach numbers, interblade phase angle, reduced frequencies, etc. The comparative investigation has shown that present theoretical models can predict accurately the aeroelastic behavior of certain cascade configurations in two dimensional flow. Other configurations cannot be predicted as well. It is concluded that, although present methods can predict stability limits in some cases, N87-26835 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn the physical reasons for flutter in cascades are not yet fully (West Germany). Unternehmensgruppe Transport- und understood. GRA Verkehrsflugzeuge. INTEGRATION OF THE PROPFAN CONCEPT IN AIRCRAFT N87-26009"# Pratt and Whitney Aircraft, East Hartford, Conn. DESIGN [PROPFAN-INTEGRATION IM FLUGZEUGENTWURF] Engineering Div. HANS GEORG SCHULZ In its Research and Development. APPLICATION OF CFD CODES TO THE DESIGN AND Technical-Scientific Publications 1986 p 99-106 1986 In DEVELOPMENT OF PROPULSION SYSTEMS GERMAN Presented at the 4th BMFT-Statusseminar, Munich, W. K. LORD, G. F. PICKETT, G. J. STURGESS, and H. D. West Germany, 28-30 Apr. 1986 WEINGOLD In NASA. Ames Research Center, Supercomputing (MBB-UT-0001/86) Avail: Issuing Activity in Aerospace p 139-148 Mar. 1987 The efforts and costs involved in the integration of the propfan Avail: NTIS HC A13/MF A01 CSCL 21E (free-rotating fans) concept in aircraft design are discussed. The The internal flows of aerospace propulsion engines have certain prospects of fuel saving due to the propfan integration are common features that are amenable to analysis through presented. The limitations of designs including propfan concepts, Computational Fluid Dynamics (CFD) computer codes. Although and the effects of propulsion systems parameters on the aircraft the application of CFD to engineering problems in engines was configuration are discussed. Two basic concepts, one with delayed by the complexities associated with internal flows, many contrarotating propfan propulsion systems at the airfoil, the second codes with different capabilities are now being used as routine with propulsion systems at the fuselage, were compared. An design tools. This is illustrated by examples taken from the aircraft economic analysis of propfan concepts as compared to turbofan gas turbine engine of flows calculated with potential flow, Euler concepts is presented. ESA

677 08 AIRCRAFTSTABILITYANDCONTROL

O8 change of the attitude of the helicopter depends on the flight conditions when the helicopter just hits the vortex core. Author AIRCRAFT STABILITY AND CONTROL A87-43430# Includes aircraft handling qualities; piloting; flight controls; and HELICOPTER RESPONSE TO AN AIRPLANES'S VORTEX autopilots. WAKE GUNJIT SlNGH BIR, INDERJIT CHOPRA (Maryland, University, College Park), and KI-CHUNG KIM DGLR, European Rotorcraft A87-43405# Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, SIMULATOR EVALUATIONS OF INCEPTORS FOR ACT 1986, Paper. 23 p. refs HELICOPTERS (Contract DOT-RS57-85-C-00105) C. P. MASSEY (Westland Helicopters, Ltd., Yeovil, England) An analytical formulation is developed for studying the DGLR, European Rot0rcraft Forum, 12th, Garmisch-Partenkirchen, rotor-fuselage system response to an airplane's trailing vortex field. West Germany, Sept. 22-25, 1986, Paper. 18 p. refs The blades are modeled as elastic beams undergoing flap bending, Two 3-axis inceptors have been used in ground simulation trials lag bending and torsional deflections. The fuselage is modelled at RAE Bedford during which approximately seventy hours of trials as a rigid body with five degrees of freedom: longitudinal, lateral, were flown by four primary evaluation pilots. Both inceptors were vertical, roll and pitch. Quasisteady strip theory is used to obtain used as 2-axis as well as 3-axis controllers and systematic aerodynamic forces, and a dynamic inflow model is used to include evaluations of inceptor forces and control signal shaping were the wake-induced unsteady effect. Dynamic stall and reverse flow performed. Objective measurements of performance and workload effects are also included. The coupled rotor-fuselage equations were taken and the pilots were asked to rate various aspects of are linearized about the vehicle trim state and the blade their task performance as well as rating the system in use. Statistical steady-state deflected position, and then solved by a numerical analysis of these results has shown the benefits of control signal time-integration technique. Dynamic response results are shaping and that the 2-axis configuration has performance determined in terms of blade deflections, blade stresses, rotor advantages but no subjective preference compared with the 3-axis disk tilts, and hub loads and moments. Results are calculated for configuration. Guidance towards preferred feel forces has also four cases of vortex encounters: hovering helicopter with vortex been gained. The trials procedure has proved successful in axis aligned with hub center: hovering helicopter with descending producing results in which a high degree of confidence can be vortex at 16 ft/sec; helicopter flies along vortex axis; and helicopter placed. Author flies across a two vortex system. For the vortex model, a fresh wake of a B-747 airplane is used and the response is calculated for typical helicopters including hingeless, articulated and teetering A87-43428"# Princeton Univ., N. J. rotors. Author STABILITY AND CONTROL MODELLING H. C. CURTISS, JR. (Princeton University, NJ) DGLR, European A87-43432# Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, AN ANALYTIC METHOD OF QUANTIFYING HELICOPTER Sept. 22-25, 1986, Paper. 18 p. refs AGILITY (Contract NAG2-244) D. G. THOMSON (Glasgow, University, Scotland) DGLR, European This paper discusses the influence of rotor dynamics and Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, dynamic inflow on the stability and control characteristics of single Sept. 22-25, 1986, Paper. 21 p. refs rotor helicopters in near hovering flight. Body attitude and rate This paper outlines a method of measuring the inherent agility feedback gain limitations which arise due to rotor dynamics and (i.e., the agility of the aircraft alone) of a helicopter configuration. dynamic inflow are discussed. It is shown that attitude feedback The method is based on inverse solutions of the equations of gain is limited primarily by body-flap coupling and rate gain is motion and standard performance-measurement techniques. limited by the lag degrees of freedom. Dynamic inflow is shown Inverse solutions can be found for a helicopter performing a family to produce significant changes in the modes of motion. Author of maneuvers within specified limits. An agility performance index is given for each maneuver, forming an agility surface covering A87-43429# this set of limits. An agility rating is then calculated as the volume STUDY OF THE DYNAMIC RESPONSE OF HELICOPTERS TO under the surface. This agility rating corresponds to a single A LARGE AIRPLANE WAKE configuration over a single class of maneuver. Other configurations SHIGERU SAITO (National Aerospace Laboratory, Tokyo, Japan), can then be tested over the same maneuvers for comparison. AKIRA AZUMA, KEIJI KAWACHI, and YOSHINORI OKUNO (Tokyo, The method is illustrated by comparing the agility of three helicopter University, Japan) DGLR, European Rotorcraft Forum, 12th, configurations (transport, battlefield, and agile) over a series of standard maneuvers. Author Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 23 p. refs A numerical simulation of helicopter flight dynamics is A87-43433# performed in order to get the dynamic characteristics of helicopters OBSERVATIONS OF PILOT CONTROL STRATEGY IN LOW which encounter a pair of trailing vortices from a large aircraft LEVEL HELICOPTER FLYING TASKS such as a jumbo jet. Two types of helicopter rotor (articulated G. D. PADFIELD, M. T. CHARLTON, S. S. HOUSTON (Royal and hingeless) are analyzed to make clear the effects of Aircraft Establishment, Bedford, England), H.-J. PAUSDER, and geometrical configuration of helicopter, rotorblade stiffness, and D. HUMMES (DFVLR, Institut fuer Flugmechanik, Brunswick, West flight condition on the helicopter dynamic responses. The rotor Germany) DGLR, European Rotorcraft Forum, 12th, aerodynamic forces, which are fully coupled to the body motion Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. with six degrees of freedom, are calculated by using the 27 p. refs local-momentum theory (Azuma and Kawachi, 1979). The time A series of task-oriented flight test techniques has been histories of the dynamic behavior of the helicopter and the blade developed for flying qualities research with highly augmented motion are presented for various parameters, such as the distance helicopters. These techniques encompass task definition, flight between helicopter and large aircraft, the type of helicopter rotor, testing, debriefing, and task analysis. The 'circle' maneuver has and the flight path angle with respect to the tip vortices of the been introduced as a task for the exploration of pilot control strategy large aircraft. The dynamic response of the helicopter is generally and hence of flying qualities associated with precise flight path moderate in comparison with that of the aircraft. The most severe control at high bank angles. Tests have been conducted with response is in the vertical direction, with almost 2 g load level, instrumented Puma and BO-105 aircraft involving tow level tracking and the flight path follows the shape of the vertical gust. The of ground-marked courses. The results presented are derived from

678 08 AIRCRAFT STABILITY AND CONTROL

the correlation of pilot opinion with the results of analyses of both The method is illustrated with an application to a BO 105 helicopter performance and pilot control activity. O.C. equipped with a digital FBW system. Results of flight tests are presented. Author A87-43435# AN ADVANCED MATHEMATICAL MODEL FOR HELICOPTER FLIGHT SIMULATION USING NONLINEAR UNSTEADY A87-43446"# Massachusetts Inst. of Tech., Cambridge. AERODYNAMICS HELICOPTER INDIVIDUAL-BLADE-CONTROL RESEARCH AT ULRICH LEISS and SIEGFRIED WAGNER (Muenchen, Universitaet MIT 1977-1985 der Bundeswehr, Munich, West Germany) DGLR, European NORMAN D. HAM (MIT, Cambridge, MA) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 18 p. refs Sept. 22-25, 1986, Paper. 10 p. NASA-sponsored research. (Contract BMFT-LFF-83408) Previously announced in STAR as N86-28954. refs A new mathematical model was formulated for application to a A new advanced system for active control of helicopters and wide variety of helicopter configurations. Quaternions and Euler its application to the solution of rotor aerodynamic and aeroelastic transformations describe the extended degrees of freedom. problems is described. Each blade is individually controlled in the Aerodynamic coefficients were expressed in analytical form. Thus, rotating frame over a wide range of frequencies. Application of blade elements were eliminated by analytical integration in the the system to gust alleviation, attitude stabilization, vibration radial direction. A new approach to inflow and three-dimensional alleviation, blade lag damping augmentation, stall flutter effects was included. Viscous and nonviscous unsteady effects suppression, blade flapping stabilization, stall alleviation, and were formulated separately for pitch, plunge, yaw, and fore-and-aft performance enhancement is outlined. The effectiveness of the motion. Separated and reverse flow can be evaluated at high system in achieving most of these applications is demonstrated advance ratios and heavily loaded rotors. The application of the by experimental results from wind tunnel tests of a model helicopter new model leads to improved numerical stability and accuracy. rotor with individual blade control. The feasibility of achieving many Computation time decreases significantly. New effects can be or all of the applications of individual blade control using the analyzed for isolated rotors or complete helicopters. Author conventional helicopter swash plate is demonstrated, and the necessary control laws are presented. Author A87-43436# THE INFLUENCE OF THE INDUCED VELOCITY DISTRIBUTION AND THE FLAPPING-LAGGING COUPLING ON THE A87-43447# DERIVATIVES OF THE ROTOR AND THE STABILITY OF THE DEVELOPMENT OF AN EXPERIMENTAL SYSTEM FOR ACTIVE HELICOPTER CONTROL OF VIBRATIONS ON HELICOPTERS XIN-YU XU and REN-LIANG CHANG (Nanjing Aeronautical MARC ACHACHE and MICHEL POLYCHRONIADIS (Aerospatiale, Institute, People's Republic of China) DGLR, European Rotorcraft Division Helicopteres, Marignane, France) DGLR, European Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, 1986, Paper. 25 p. refs Sept. 22-25, 1986, Paper. 11 p. refs The first-harmonic variation of the induced velocity distribution A research program sponsored by French government agencies derived by Wang's (1981) generalized vortex theory is invoked in has been conducted to develop an experimental system for active the present discussion of the coupling of the first control of vibrations through higher-harmonic controls applied to flapping-lagging-bending mode of helicopter rotor blade elasticity. the main rotor blades. All system-development phases are Sample calculations are presented for a generic helicopter, with presented within the framework of an airborne-system design and attention to the induced velocity distribution and the coupling development methodology. The various stages prior to flight flapping-lagging of the rotor derivatives and helicopter stability. All experiments are dealt with, from the theoretical modeling of the basic expressions of the mechanics of a hingeless rotor are helicopter vibratory behavior under higher-harmonic control up to given. O.C. the integration of the system on a rotor test rig. The flight-test campaign conducted at Marignane in 1985 on an SA 349 validated A87-43440# the concept for reducing vibrations through a closed-loop REALIZATION AND FLIGHT TESTING OF A MODEL self-adaptive system within the whole SA 349 helicopter flight FOLLOWING CONTROL SYSTEM FOR HELICOPTERS envelope. In addition to the very important reductions of vibrations G. BOUWER and M. ZOELLNER (DFVLR, Institut fuer obtained from three different algorithms (80 percent as an average Flugmechanik, Brunswick, West Germany) DGLR, European in the cabin at 250 km/h), this test campaign showed the efficiency Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, of a test methodology focused on the representativity of an off-line Sept. 22-25, 1986, Paper. 14 p. refs simulation. Author The realization of a designed model following-control system on a BO 105 fly-by-wire helicopter is described. A multi-computer system performs the numerous tasks of the in-flight simulation A87-43448"# Princeton Univ., N. J. facility. Different displays and flight-test parameters can be easily KINEMATIC OBSERVERS FOR ACTIVE CONTROL OF selected by the simulation pilot. High system capability is achieved HELICOPTER ROTOR VIBRATION by supporting simulation software for different applications. The ROBERT M. MCKILLIP, JR. (Princeton University, N J) DGLR, possibility of real-time ground simulation with the helicopter and European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West the flight test crew allows effective flight-test preparation. Extensive Germany, Sept. 22-25, 1986, Paper. 17 p. Research supported by test-data analysis software enables the user of the in-flight simulator the Engineering Foundation and NASA. refs to analyze the tests quickly. Flight-test results demonstrate the A simple scheme for estimating the state variables of a high effectiveness of the helicopter in-flight simulation. Author helicopter rotor is presented. The method incorporates the use of blade-mounted accelerometers and/or position transducers to A87-43441 # reconstruct modal displacements and velocities. The design of THE MODEL INVERSE AS AN ELEMENT OF A MANOEUVRE the observer structure and feedback gains is simplified by the DEMAND SYSTEM FOR HELICOPTERS fact that the method requires only knowledge of basic kinematic H. LEYENDECKER (DFVLR, Brunswick, West Germany) DGLR, relationships between the various modal quantities. The observer European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West structure described is particularly well-suited to control problems Germany, Sept. 22-25, 1986, Paper. 18 p. where the use of a traditional Katman Filter approach would be A method for the design of flight-control systems for plants too complex or costly. The technique can be viewed as decreasing with highly coupled dynamics is presented. It exploits the so-called the requirements on observer complexity while increasing the need integral inverse as an essential element of the control concept. for an enhanced sensor complement. Author

679 08 AIRCRAFT STABILITY AND CONTROL

A87-43457# A87-44328# EXPERIENCE WITH FREQUENCY-DOMAIN METHODS IN EXTREME ATMOSPHERIC TURBULENCE [PRESENTATION HELICOPTER SYSTEM IDENTIFICATION DES TURBULENCES ATMOSPHERIQUES EXTREMES] C. G. BLACK, D. J. MURRAY-SMITH (Glasgow, University, GABRIEL COUPRY (ONERA, Chatillon-sous-Bagneux, France) Scotland), and G. D. PADFIELD (Royal Aircraft Establishment, (NATO, AGARD, Meeting, 63rd, Athens, Greece, Sept. 28-Oct. 3, Bedford, England) DGLR, European Rotorcraft Forum, 12th, 1986) ONERA, TP, no. 1987-8, 1987, 9 p. In French. refs Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. (ONERA, TP NO. 1987-8) 27 p. refs A model of extreme atmospheric turbulence is proposed based (Contract MOD-2048/028/XR/STR) on five years of commercial flight data for events with load factors Most applications of system identification techniques to in excess of 0.5. The Pratt formula is found to lead to incoherent helicopters have involved time-domain methods using reduced- atmospheric descriptions, while the Hall formula, with appropriate order mathematical models representing six-degree-of-freedom choice of scale, is found to lead to a coherent turbulence rigid-body motion. Frequency-domain techniques provide an in- description which is relatively independent of the type of aircraft teresting alternative approacch in which data which lies outside considered. For strong turbulences, the average number of the frequency range of interest may be disregarded. This not only overshoots by a nautical mile are found to decrease exponentially provides a basis for establishing reduced order models which are with gust amplitude. The incidences of gusts exceeding a threshold valid over a defined range of frequencies but also results in a value are found to obey a Poisson distribution whose mean significant data reduction in comparison with time-domain methods. decreases exponentially with amplitude, indicating that the This paper presents a systematic approach to frequency-domain probability of the occurrence of big gusts can be represented by identification using both equation-error and output-error Gumbel's extreme value theory. R.R. techniques. Results are presented from flight data from the Puma helicopter to illustrate the application of the frequency-domain ap- A87-45096# proach to the estimation of parameters of the pitching moment and AN APPROACH TO THE SYNTHESIS OF AN ADAPTIVE FLIGHT normal force equations. These results are assessed both on a CONTROL SYSTEM WITH INCOMPLETE INFORMATION statistical basis and through comparisons with theoretical values. KIMIO KANAI and SlGERU UCHIKADO Japan Society for Author Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. 35, no. 399, 1987, p. 214-220. In Japanese, with abstract in English. refs The change of flight condition leads to variation in an aircraft's A87-43458# parameters. It can also vary the order of the numerator in the HELICOPTER MODEL IN FLIGHT IOENTIFICATION BY A REAL pulse-transfer function of such an aircraft. This means, in the TIME SELF ADAPTIVE DIGITAL PROCESS discrete-time case, a change in the time delay. It is difficult under A. DANESI and F. FELICIANI (Roma I, Universita, Rome, Italy) these circumstances to maintain the performance of an aircraft DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, with conventional control methods. Here, as an alternative scheme, West Germany, Sept. 22-25, 1986, Paper. 7 p. an adaptive flight control system is proposed which can be used A feasibility evaluation of an airborne electronic device that for aircraft with unknown time delay and parameters. By introducing automatically identifies helicopter transfer functions is presented. a polynomial identity based on the upper bound on time delay, The helicopter frequency response to the impulse response flight the control system can be synthesized simply, in spite of the test data is computed by a dedicated microprocessor. The software unknown time delay, as in standard model-reference implements an adaptive algorithm that matches a preselected adaptive-control systems. Simulation studies are carried out for helicopter frequency model with the computed frequency response. small high-performance aircraft to substantiate the analytical This yields the best linearized model approximation to the actual work. Author system transfer function. For the selected set of state and control variables, the corresponding numerator and denominator A87-45097# polynomial transfer functions are computed in real time. The basic DESIGN OF CCV FLIGHT CONTROL SYSTEM OF STOL FLYING theory of the adaptive strategy and identificator unit implementation BOAT are described in the paper. The simulation results prove the KIMIO KANAI, SlGERU UCHIKADO, and YOSHIKAZU MORITA feasibility of the inflight identification digital process as a useful Japan Society for Aeronautical and Space Sciences, Journal (ISSN tool in solving helicopter stability and control problems. Author 0021-4663), vol. 35, no. 399, 1987, p. 221-228. In Japanese, with abstract in English. refs A control-configured-vehicle (CCV) approach to the flight control of an STOL amphibian aircraft during approach and sea landing A87-44254" Rice Univ., Houston, Tex. (as in rescue operations) is developed analytically and MAX|MUM SURVIVAL CAPABILITY OF AN AIRCRAFT IN A demonstrated by means of numerical simulations. The problems SEVERE WlNDSHEAR imposed by low-speed approach and the inadequacy of simple A. MIELE, T. WANG (Rice University, Houston, TX), W. W. MELVIN automatic throttle control are discussed; the basic principles and (Delta Air Lines, Inc., Atlanta, GA), and R. L. BOWLES (NASA, implementation of the CCV system are outlined; and the simulation Langley Research Center, Hampton, VA) Journal of Optimization results are presented graphically. T.K. Theory and Applications (ISSN 0022-3239), vol. 53, May 1987, p. 181-217. Research supported by Boeing Commercial Airplane Co. A87-45306# refs VALIDATION OF AN INTEGRATED FLIGHT AND PROPULSION (Contract NAG1-516) CONTROL DESIGN FOR FIGHTER AIRCRAFT The performance of constant-alpha, maximum-alpha, constant- PETER D. SHAW, KARL R. HAIGES (Northrop Corp., Aircraft Div., velocity, constant-absolute-inclination, constant-climb-rate, and Hawthorne, CA), and CHARLES A. SKIRA (USAF, Wright constant-pitch (CP) vertical-plane guidance schemes for aircraft Aeronautical Laboratories, Wright-Patterson AFB, OH) AIAA, SAE, taking off under horizontal-windshear conditions with a downdraft ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, is compared by means of numerical simulations; the results are CA, June 29-July 2, 1987. 14 p. USAF-sponsored research, refs presented in tables and graphs, and it is found that CP guidance (AIAA PAPER 87-1928) gives the best aircraft survivability. Optimal, gamma-guidance, and An integrated control design methodology has been developed simplified-gamma trajectories are then evaluated to improve the for flight and propulsion control of a fighter aircraft. The approach performance of CP, and the correct selection of the feedback gain is one that emphasizes the practical design issues of integrated coefficient and the time delay for response to windshear onset is control. It involves partitioning of the problem into smaller, more shown to be of great importance for maximizing survivability. T.K. conventional design tasks, affording much greater physical insight.

680 08 AIRCRAFT STABILITY AND CONTROL

It provides a framework within which specialists in each discipline A87-46792# can apply their experience in the design process. Its structure ACTIVE CONTROL OF AEROFOIL FLU'n'ER also readily accommodates nonlinear effects that must be factored X. Y. HUANG AIAA Journal (ISSN 0001-1452), vol. 25, Aug. into any practical design. A thorough evaluation of the resulting 1987, p. 1126-1132. Research supported by Cambridge University control law has been conducted via digital and piloted simulation. and Academia Sinica. refs This paper focuses on the results of that evaluation, with particular This paper describes a novel method of eliminating aerofoil emphasis placed upon the highly coupled aspects of the flight flutter by an active control technique. The control is attained by and propulsion control systems. Performance payoffs are adding to the natural case a control-induced force of appropriate demonstrated in the landing phase of flight and at the limits of amplitude and phase to negate the natural destabilizing tendency the air combat regime. Author of the aerodynamic load. This control force may be induced on wings by actuating tabs or ailerons, however, the present paper A87-45307# concentrates on a scheme that may be more effective at high PERFORMANCE SEEKING CONTROL FOR CRUISE frequencies and which might, therefore, complement more OPTIMIZATION IN FIGHTER AIRCRAFT conventional methods. Acoustic equipment is used to carry out ERIC J. TICH, PETER D. SHAW (Northrop Corp., Aircraft Div., the techniques of active sound control that are known as Hawthorne, CA), DONALD F. BERG, SHRIDER ADIBHATLA, anti-sound. Although loudspeaker-induced pressures are small it JERRY A. SWAN (General Electric Co., Aircraft Engine Business is shown that they can actually induce significant and useful control Group, Cincinnati, OH) et al. AIAA, SAE, ASME, and ASEE, forces on an aerofoil. This technique offers new flexibility in system Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July design because the loudspeakers can be positioned at a convenient 2, 1987. 15 p. USAF-sponsored research, refs place, not necessarily on the aerofoil surface. This paper describes (AIAA PAPER 87-1929) the theory needed to assess the details of this idea and also An indirect adaptive control algorithm has been developed to contains the results of the experiments in which a fluttering aerofoil minimize fuel flow consumption for an integrated aircraft/engine was stabilized by switching on a loudspeaker. Author system in both subsonic and supersonic cruise operation. The algorithm utilizes onboard models of the aircraft and engine, with tracking logic to identify and account for any differences between N87-25279"# Sperry Flight Systems, Glendale, Ariz. Avionics the engine model and the true engine cycle. A constrained Div. numerical optimization technique is used with the onboard models AUTOMATIC SYSTEMS AND THE LOW-LEVEL WIND HAZARD to identify trim control sets that provide a fuel flow reduction. DWIGHT R. SCHAEFFER In NASA. Langley Research Center, Revised trim solutions are transmitted to the plant as incremental Wind Shear/Turbulence Inputs to Flight Simulation and Systems changes to the scheduled control positions, with the aircraft and Certification p 165-172 Jul. 1987 engine control systems responding to the adjustments through Avail: NTIS HC A12/MF A01 CSCL 01C normal control operation. The adaptive control algorithm is Automatic flight control systems provide means for significantly modelled within a high fidelity, six-degree-of-freedom enhancing survivability in severe wind hazards. The technology aircraft/engine simulation incorporating advanced fighter aircraft required to produce the necessary control algorithms is available features. This paper presents study results showing both potential and has been made technically feasible by the advent of digital and actual performance benefits from the adaptive algorithm, as flight control systems and accurate, low-noise sensors, especially well as its sensitivity to off-nominal variations. Author strap-down inertial sensors. The application of this technology and these means has not generally been enabled except for automatic A87-46315 landing systems, and even then the potential has not been fully DVI IN THE MILITARY COCKPIT - A THIRD HAND FOR THE exploited. To fully exploit the potential of automatic systems for COMBAT PILOT enhancing safety in wind hazards requires providing incentives, BRIAN WANSTALL Interavia (ISSN 0020-5168), vol. 42, June creating demand, inspiring competition, education, and eliminating 1987, p. 655, 656, 659, 660. prejudicial disincentitives to overcome the economic penalties Voice warning systems are already in service, and associated with the extensive and riskly development and advancements in both hardware and software development promise certification of these systems. If these changes will come about usable automatic speech recognition (ASR) systems for at all, it will likely be through changes in the regulations provided next-generation combat aircraft and battlefield helicopters. Direct by the certifying agencies. Author voice input (DVl) ASR systems have been specified for next-generation NATO fighters and combat helicopters, with the aim of reducing overall workload and stress levels. Noise, g-levels and pressurized breathing, however, militate against the easy N87-25330"# Manudyne Systems, Inc., Los Altos, Calif. incorporation of DVl; verification or feedback of the voice STUDY OF HELICOPTERROLL CONTROL EFFECTIVENESS commands in some yet to be defined form is noted to be vital for CRITERIA Final Report, Jul. 1983 - Jul. 1985 successful combat use. D.C. ROBERT K. HEFFLEY, SIMON M. BOURNE, HOWARD C. CURTISS, JR., WILLIAM S. HINDSON, and RONALD A. HESS A87-46767# Apr. 1986 267p BOUNDED RANOOM OSCILLATIONS MODEL AND (Contract NAS2-11665; DA PROJ. 1L1-62209-AH-76) NUMERICAL RESOLUTION FOR AN AIRFOIL (NASA-CR-177404; NAS 1.26:177404; AD-A172111; F. POIRION (ONERA, Chatillon-sous-Bagneux, France) (IUTAM, MANUDYNE-83-1; USAAVSCOM-TR-85-A-5) Avail: NTIS HC Symposium on Nonlinear Stochastic Dynamical Engineering' A12/MF A01 CSCL 01C Systems, Innsbruck, Austria, June 21-26, 1987) ONERA, TP, no. A study of helicopter roll control effectiveness based on 1987-73, 1987. 10 p. closed-loop task performance measurement and modeling is (ONERA, TP NO. 1987-73) presented. Roll control critieria are based on task margin, the A method of simulating bounded random oscillations arising in excess of vehicle task performance capability over the pilot's task a simple two-dimensional case of a flexible aircraft flying in a performance demand. Appropriate helicopter roll axis dynamic turbulent wind is demonstrated and compared to results from two models are defined for use with analytic models for task more elaborate numerical methods. These two methods are used performance. Both near-earth and up-and-away large-amplitude to calculate the stationary probability distribution and second order maneuvering phases are considered. The results of in-flight and statistics of the random oscillations by solving the generalized moving-base simulation measurements are presented to support Fokker-Planck equation using a finite difference scheme and the the roll control effectiveness criteria offered. This Volume contains Galerkin method, respectively. They provide results which are very the theoretical analysis, simulation results and criteria similar to those from the simple simulation. C.D. development. Author (GRA)

681 08 AIRCRAFT STABILITY AND CONTROL

N87-25331"# National Aeronautics and Space Administration. dynamic inflow modeling. A dynamic stall model is used to Lewis Research Center, Cleveland, Ohio. incorporate the unsteady stall effects. Corrections are introduced ADVANCED DETECTION, ISOLATION AND ACCOMMODATION for the reverse flow effects. The fuselage is allowed five degrees OF SENSOR FAILURES: REAL-TIME EVALUATION of freedom: vertical, longitudinal, lateral, pitch, and roll motions. WALTER C. MERRILL, JOHN C. DELAAT, and WILLIAM M. Finite element method based on the Hamilton principle is applied BRUTON Jul. 1987 30 p to discretize the equations of motion. Results were obtained for (NASA-TP-2740; E-3479; NAS 1.60:2740) Avail: NTIS HC the articulated and hingeless rotors in hover as well as forward A03/MF A01 CSCL 01C flight. Dissert. Abstr. The objective of the Advanced Detection, Isolation, and Accommodation (ADIA) Program is to improve the overall N87-26050 Stanford Univ., Calif. demonstrated reliability of digital electronic control systems for CONTROL OF AIRCRAFT UNDER SEVERE WIND SHEAR turbine engines by using analytical redundacy to detect sensor CONDITIONS Ph.D. Thesis failures. The results of a real time hybrid computer evaluation of PETER YAOHWA CHU 1987 187 p the ADIA algorithm are presented. Minimum detectable levels of Avail: Univ. Microfilms Order No. DA8707646 sensor failures for an F100 engine control system are determined. This research uses feedforward techniques to control a short Also included are details about the microprocessor implementation takeoff and landing transport during landing approach, assuming of the algorithm as well as a description of the algorithm itself. knowledge of wind states. At the same time, feedback is used to Author augment stability and handle modeling and estimation errors. Current and future wind states can be detected by ground based N87-26047"# Rice Univ., Houston, Tex. Dept. of Mechanical Doppler radars that scan the glide scope. Estimates of the current Engineering and Materials Science. wind states can also be derived from onboard sensors. Three OPTIMAL FLIGHT TRAJECTORIES IN THE PRESENCE OF different methods for designing a time-invariant feedforward WINDSHEAR, 1984-86 Final Report controller are discussed: asymptotic disturbance rejection, linear A. MIELE 1986 36 p quadratic disturbance rejection, and differential game. A wind shear (Contract NAG1-516) penetration index is proposed. It gives an indication of the ability (NASA-CR-180316; NAS 1.26:180316; of the aircraft to penetrate wind shear, and may establish a wind AERO-ASTRONAUTICS-203) Avail: NTIS HC A03/MF A01 threshold above which the aircraft should not attempt landing or CSCL 01C takeoff. Dissert. Abstr. Optimal flight trajectories were determined in the presence of windshear and guidance schemes were developed for near N87-26051 Georgia Inst. of Tech., Atlanta. optimum flight in a windshear. This is a wind characterized by AN INVESTIGATION OF HELICOPTER HIGHER HARMONIC sharp change in intensity and direction over a relatively small CONTROL USING A DYNAMIC SYSTEM COUPLER SIMULATION region of space. This problem is important in the takeoff and Ph.D. Thesis landing of both civilian airplanes and military airplanes and is key KIP PETER NYGREN 1986 188 p to aircraft saftey. The topics covered in reference to takeoff Avail: Univ. Microfilms Order No. DA8707859 problems are: equations of motion, problem formulation, algorithms, A free flight computer simulation of helicopter Higher Harmonic optimal flight trajectories, advanced guidance schemes, simplified Control (HHC) is developed by incorporation of an HHC solution guidance schemes, and piloting strategies. Author procedure in the Dynamic System Coupler (DYSCO) Program. The simulation can model almost any HHC control and identification N87-26048 ESDU International Ltd., London (England). scheme tested to date. The simulation is correlated with previous AN INTRODUCTION TO TIME-DEPENDENT AERODYNAMICS experiments and simulations, and the assumptions of the OF AIRCRAFT RESPONSE, GUSTS AND ACTIVE CONTROLS mathematical model are analyzed. Investigations are conducted Sep. 1984 65 p which compare fixed gain and adaptive control, local, and global (ESDU-84020; ISBN-0-85679-484-8; ISSN-0141-397X) Avail: formulations. The OH-6A helicopter with elastic rotor and fuselage ESDU is modeled using unsteady aerodynamics. Five baseline regulators ESDU 84020 explains the derivation and application of the are tested at flight velocities of 80, 100 and 120 knots, and the indicial (step-response) functions (also called Wagner and Kuessner simulation is verified by comparison with previous efforts. Variations functions) used to study aircraft response. The functions are in measurement noise, initial transfer matrix, and number of rotor introduced through the Fourier integration of the blades is considered. The model is also maneuvered from trimmed frequency-dependent generalized airforce coefficients associated flight at 80 knots to trimmed flight at 120 knots using large and with oscillatory motion. Indicial functions for use in predicting small step changes. The results indicate fixed gain, closed loop response in lift and pitching moment due to heave or pitch rate, control can adequately reduce vibration, though not as effectively or deflection of a 20 percent chord control, are tabulated for thin as adaptive control, except when initialized with an inappropriate airfoils in subsonic and supersonic flows. Results obtained for a transfer matrix. Dissert. Abstr. range of typical airframe two- and three-dimensional geometries, including wing/tailplane combinations, again through the speed N87-26836 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn range to supersonic, are illustrated graphically. They include the (West Germany). Unternehmensgruppe Transport- und effects of active controls. The results are discussed and various Verkehrsflugzeuge. aspects of the mathematical modeling of unsteady flows are CONCEPTUAL STUDIES OF CONTROL SYSTEMS FOR WINGS highlighted. ESDU WITH VARIABLE CAMBER [KONZEPTUNTERSUCHUNG ZU STEUERUNGSSYSTEMEN EINES TRAGFLUEGELS VARIABLE N87-26049 Maryland Univ., College Park. WOELBUNG] GUST RESPONSE OF HELICOPTERS Ph.D. Thesis JUERGEN RENKEN and UDO CARL In its Research and GUNJIT SINGH BIR 1985 254 p Development. Technical-Scientific Publications 1986 p 107-114 Avail: Univ. Microfilms Order No. DA8702145 1986 In GERMAN Presented at the 4th BMFT-Statusseminar, An analysis was developed for investigating the response of a Munich, West Germany, 28-30 Apr. 1986 rotor-fuselage system in a three-dimensional gust field wherein (MBB-UT-221/86) Avail: Issuing Activity the gust velocity components can have arbitrary variation in space Geometric-kinematic principles of camber variation, and the and time. Each rotor blade undergoes flap bending, lag bending, corresponding drive and control concepts were investigated, with and torsional deflections. The blades are divided into beam the restriction of camber variations of trailing edge of the wings. elements and each element consists of fifteen nodal degrees of The emphasis was on the control surfaces (spoiler, Fowler flaps, freedom. Quasisteady strip theory is used to obtain the aerodynamic aileron). The premise was that neither the original primary (roll loads. Unsteady aerodynamic effects are introduced through control) and secondary (high-lift) functions be reduced, nor that

682 09 RESEARCH AND SUPPORT FACILITIES (AIR)

complexity, weight and reliability endanger the global utility. The helicopter rotors. This data base could then be used in correlation flight-physical background of the camber concept, and the studies to establish the validity or deficiencies of available analytical geometric-kinematic-realization of camber variation (via profile methods for the prediction of structural dynamic and/or unsteady depth or wing span) are presented. A flap drive and control concept aerodynamic phenomena. This paper presents detailed description is explained. The effect of the elastic flap deformations on the of the facility, the testing philosophy behind its design and use, camber variation is discussed. The implementation of the function and current and future test programs conducted in the facility. camber variation into existing systems and functions is presented. Author ESA A87-43462# VALIDATION OF A METHOD FOR AIR RESONANCE TESTING O9 OF HELICOPTERS AT MODEL SCALE USING ACTIVE CONTROL OF PYLON DYNAMIC CHARACTERISTICS RICHARD L. BIELAWA (Rensselaer Polytechnic Institute, Troy, RESEARCH AND SUPPORT FACILITIES (AIR) NY) DGLR, European Rotorcraft Forum, 12th, Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. Includes airports, hangars and runways; aircraft repair and overhaul 32 p. Research supported by the United Technologies Corp. and facilities; wind tunnels; shock tube facilities; and engine test U.S. Army. refs blocks. A problem inherent in the testing for helicopter air resonance at mode scale is the design and fabrication of the pylon support structure to effect both a proper (Froude) scaling and adequate A87-43425"# Army Aviation Systems Command, Moffett Field, variability of the pylon parameters by using passive properties. Calif. One method of overcoming this difficulty is to provide for active A COMPARISON OF THE ACOUSTIC AND AERODYNAMIC control of the pylon properties using suitably controlled hydraulic MEASUREMENTS OF A MODEL ROTOR TESTED IN TWO feedback servo actuators acting in response tothe measured ANECHOIC WIND TUNNELS motion of the pylon. The objective of the study is to investigate D. A. BOXWELL (U.S. Army, Aeroflightdynamics Directorate, Moffett the validity of such an approach using analytical means. The results Field, CA), F. H. SCHMITZ (NASA, Ames Research Center, Moffett compare the air resonance eigensolutions obtained for various Field, CA), W. R. SPLETTSTOESSER, K. J. SCHULTZ (DFVLR, approximations inherent in such a method of model testing. Brunswick, West Germany), S. LEWY (ONERA, Chatillon-sous- Analytical formulations are presented describing the modifications Bagneux, France) et al. DGLR, European Rotorcraft Forum, 12th, required of a basic air-resonance theory to account for the dynamics Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. of the selected feedback control network. Author 54 p. Previously announced in STAR as N87-15178. refs Two aeroacoustic facilities - the CEPRA 19 in France and the A87-44714 DNW in the Netherlands - are compared. The two facilities have SOME FUNDAMENTALS OF SIMULATOR COCKPIT MOTION unique acoustic characteristics that make them appropriate for GENERATION acoustic testing of model-scale helicopter rotors. An identical M. BAARSPUL, R. J. A. W. HOSMAN, and J. C. VAN DER VAART pressure-instrumented model-scale rotor was tested in each facility (Delft, Technische Hogeschool, Netherlands) IN: Advances in and acoustic test results are compared with full-scale-rotor test flight simulation - visual and motion systems; Proceedings of the results. Blade surface pressures measured in both tunnels were International Conference, London, England, Apr. 29-May 1, 1986. used to correlated nominal rotor operating conditions in each tunnel, London, Royal Aeronautical Society, 1986, p. 81-100. refs and also used to assess the steadiness of the rotor in each Some aircraft simulator motion generation problems are tunnel's flow. In-the-flow rotor acoustic signatures at moderate discussed. The basic software and hardware elements for motion forward speeds (35-50 m/sec) are presented for each facility and generation are described. Examples of motion hardware quality discussed in relation to the differences in tunnel geometries and assessment are presented. A definition for motion cue, and a aeroacoustic characteristics. Both reports are presented in division of cues based on their functions and temporal properties appendices to this paper. Author are proposed. The interaction between visual and vestibular motion perception, and the relation between motion perception and aircraft control are investigated experimentally. Analysis of the A87-43460# stimulus-response data reveal that cockpit motion, if properly DESCRIPTION OF, AND PRELIMINARY RESULTS FROM, A NEW simulated without delays, decreases human operator time delays BLADE-VORTEX INTERACTION TEST FACILITY and improves control performance. The designing and tuning of A. KOKKALIS and R. A. MCD. GALBRAITH (Glasgow, University, drive motion laws are examined, and some examples of false Scotland) DGLR, European Rotorcraft Forum, 12th, transient cues due to motion filtering are provided. I.F. Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. 18 p. Research supported by the Ministry of Defence (Procurement A87-44715 Executive). refs A PROGRAM TO INVESTIGATE REQUIREMENTS FOR The paper describes the salient design features of a facility EFFECTIVE FLIGHT SIMULATOR DISPLAYS for the investigation of parallel blade-vortex interaction as may be E. A. MARTIN, G. R. MCMILLAN, R. WARREN, and G. E. RICCIO experienced by helicopter rotor blades. Preliminary results from (USAF, Harry G. Armstrong Aerospace Medical Research the test facility are presented and discussed. Author Laboratory, Wright-Patterson AFB, OH) IN: Advances in flight simulation - visual and motion systems; Proceedings of the A87-43461 # International Conference, London, England, Apr. 29-May 1, 1986. A UNIQUE APPROACH TO AEROELASTIC TESTING OF London, Royal Aeronautical Society, 1986, p. 101-126. refs SCALED ROTORS The effectiveness of flight simulator data is examined in terms G. ALVIN PIERCE and STEVENS. KLEIN (Georgia Institute of of inertial motion display fidelity, visual display dynamic fidelity, Technology, Atlanta) DGLR, European Rotorcraft Forum, 12th, and temporal fidelity. The experiments conducted to investigate Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. pilot performance and training transfer under conditions of: (1) 13p. dynamic seat roll-axis cuing; (2) visual perceptive transformation (Contract DAAG29-82-K-0094; DAAG29-85-G-0072) and flow field cuing; and (3) time delays in a visual display. Analysis In 1982 the U.S. Army Research Office commissioned the of the dynamic seat cuing data with respect to physical and Georgia Institute of Technology to design and construct a unique information fidelity, and the effect of experience on training transfer testing facility for the purpose of acquiring a comprehensive data reveal that the dynamic seat is useful for onset cuing. It is observed base of aeroelastic response characteristics for scaled model that it is necessary to have rich and reduced cue displays in

683 09 RESEARCHANDSUPPORTFACILITIES(AIR) simulationtraining; time-delay effects are greater under more A87-45203"# National Aeronautics and Space Administration. demanding situations; and training transfer is inhibited by long Lewis Research Center, Cleveland, Ohio. time delays. I.F. FULL-SCALE THRUST REVERSER TESTING IN AN ALTITUDE FACILITY CHARLES M. MEHALIC and ROY A. LOTTIG (NASA, Lewis Research Center, Cleveland, OH) AIAA, SAE, ASME, and ASEE, A87-44720 Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July THE INTEGRATION OF A SlX AXIS MOTION SYSTEM AND A 2, 1987. 14 p. Previously announced in STAR as N87-18575. WIDE ANGLE VISUAL SYSTEM INSIDE A DOME refs A. G. BARNES (British Aerospace, PLC, Military Aircraft Div., (AIAA PAPER 87-1788) Weybridge, England) IN: Advances in flight simulation - visual A two-dimensional convergent-divergent exhaust nozzle and motion systems; Proceedings of the International Conference, designed and fabricated by Pratt and Whitney Aircraft was installed London, England, Apr. 29-May 1, 1986. London, Royal Aeronautical on a PW1128 turbofan engine and tested during thrust reverser Society, 1986, p. 204-211. operation in an altitude facility at NASA Lewis Research Center. A proposal for integrating motion and visual systems is A unique collection system was used to capture the thrust reverser presented. The requirements for the simulator, which is to be exhaust gas and transport it to the primary exhaust collector. Tests integrated inside a single dome, are described. The visual system were conducted at three flight conditions with varying amounts of is composed of three new TV projectors, which cover a field-of-view thrust reverse at each condition. Some reverser exhaust gas of 150 x 40 deg, mounted on the gantry, and a sky-ground projector. spillage by the collection system was encountered but engine Methods for matching the horizon position and sky brightness of performance was unaffected at all flight conditions tested. Based the computer-generated-image projectors and the sky-ground on the results of this test program, the feasibility of altitude testing projector are examined. The size requirement for the motion system of advanced multifunction exhaust nozzle systems has been is considered in terms of translational and rotational performance. demonstrated. Author A diagram of the configuration for the motion/visual system, which is to be located on a platform in a 60-cm pit, is provided. The advantages and disadvantages of the selected configuration are discussed. I.F. A87-45204# STATE-OF-THE-ART TEST FACILITIES FOR DEVELOPMENT OF A87-44954"# National Aeronautics and Space Administration. THE ARMY'S T800-LHT-800 LHX HELICOPTER ENGINE WILLIAM R. STIEFEL (General Motors Corp., Allison Gas Turbine Langley Research Center, Hampton, Va. DESIGNING TRANSONIC WIND-TUNNEL TEST SECTIONS FOR Div., Indianapolis, IN) and ALBERT SELDER (Garrett Turbine FLOW DIAGNOSTICS AND LASER VELOCIMETER Engine Co., Phoenix, AZ) AIAA, SAE, ASME, and ASEE, Joint APPLICATIONS Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. G. S. JONES (NASA, Langley Research Center; Complere, Inc., 10p. Hampton, VA), L. R. GARTRELL, W. G. SEWALL, and P. C. (AIAA PAPER 87-1790) STAINBACK (NASA, Langley Research Center, Hampton, VA) The T800-LHT-800 helicopter engine is being developed for AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, the U.S. Army. The members of the development teams are in 19th, Honolulu, HI, June 8-10, 1987. 12 p. refs competition with another contractor for full-scale development and (AIAA PAPER 87-1434) ultimate production of the engine. One of the many aspects of The design, fabrication, and validation of the Basic Aerodynamic teaming is the requirement to test the engine at two separate test Facility (BARF), developed for the direct comparison of sites. This paper describes the coordination activities between the three-dimensional laser velocimetry (LV) and hot-wire techniques test organizations of two team members and the efforts to achieve at transonic speeds, are discussed. To accommodate the commonality or equivalence of test facilities, equipment, and installation of the three-dimensional orthogonal LV system in the procedures. It also describes the state-of-the-art engine test BARF, the transonic slots were redesigned to house windows, facilities, both general purpose and specialized, that the team and the test section mounting was redesigned to facilitate LV members have provided for development of the engine. Author transversing. Two-dimensional and three-dimensional code validation tests of the LV test section showed uniform mean flow through the test section to sonic speeds, and fluctuating pressure measurements at subsonic speeds which are consistent with facilities with good flow quality. R.R. A87-45276# GROUND TESTING FACILITIES REQUIREMENTS FOR HYPERSONIC PROPULSION DEVELOPMENT A87-45125# V. K. SMITH (Sverdrup Technology, Inc., Arnold Air Force Station, THE AIR FORCE FLIGHT TEST CENTER - NOW AND THE TN), L. C. KEEL, and A. H. BOUDREAU (USAF, Arnold Engineering FUTURE Development Center, Arnold Air Force Station, TN) AIAA, SAE, CHARLES E. ADOLPH (USAF, Flight Test Center, Edwards AFB, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA) IN: International Instrumentation Symposium, 32nd, Seattle, CA, June 29-July 2, 1987. 5 p. refs WA, May 5-8, 1986, Proceedings . Research Triangle Park, NC, (AIAA PAPER 87-1884) Instrument Society of America, 1986, p. 535-537. To meet the requirements of transatmospheric missions (TAVs), The Air Force Flight Test Center (AFFTC) conducts and revolutionary advances are needed in airbreathing propulsion supports manned and unmanned aircraft flight tests, development systems; high-strength high-temperature lightweight fully reusable testing of parachutes, operates the Edwards Flight Test Range, materials; super-computer-based aerodynamic, structural, and the USAF Test Pilot School, and the Utah Test and Training Range. propulsion design codes; high-efficiency energy management of This paper summarizes the evolutionary forces in the technical the hydrogen fuel; and advanced computers and adaptive-intelli- and management areas which gave impetus to today's methods gence control systems. In this paper, requirements of ground testing of operation. Current capabilities and procedures are then facilities, in terms of Mach number, altitude, and size, for hypersonic described, followed by a discussion of improvements planned to and TAV missions are analyzed and translated into the facility- meet the demands of the late 1980's. The largest single challenge oriented parameters of pressure, temperature, weight flow, and run facing the military flight test community in the next decade is the time. The current and near-term propulsion test capabilities are efficient evaluation of software-intensive avionics systems. evaluated, and the facility deficiencies, the propulsion ground test Author facility design issues, and enabling technologies are identified-I.S.

684 09 RESEARCH AND SUPPORT FACILITIES (AIR)

A87-45277"# National Aeronautics and Space Administration. A87-45445"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. Langley Research Center, Hampton, Va. MODIFICATION TO THE LANGLEY 8-FOOT HIGH TEST FLOW CALIBRATION STUDY OF THE LANGLEY TEMPERATURE TUNNEL FOR HYPERSONIC PROPULSION ARC-HEATED SCRAMJET TEST FACILITY TESTING SCOTT R. THOMAS, RANDALL T. VOLAND, and ROBERT W. DAVID E. REUBUSH, RICHARD L. PUSTER (NASA, Langley GUY (NASA, Langley Research Center, Hampton, VA) AIAA, Research Center, Hampton, VA), and H. NEALE KELLY (PRC SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Kentron, Inc., Hampton, VA) AIAA, SAE, ASME, and ASEE, Diego, CA, June 29-July 2, 1987. 12 p. refs Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July (AIAA PAPER 87-2165) 2, 1987. 12p. refs The test flow at the exits of two square cross-section contoured (AIAA PAPER 87-1887) nozzles with nominal exit Mach numbers of 4.7 and 6 has been This paper describes the modifications currently underway to studied as calibration data for the NASA-Langley Arc-Heated the Langley 8-Foot High Temperature Tunnel to produce a new, Scramjet Test Facility over simulated flight conditions from Mach unique national resource for testing of hypersonic air-breathing 5.5 (at altitudes from 98,600-128,000 ft) to Mach 7 (at altitudes propulsion systems. The current tunnel, which has been used for from 108,000-149,000 ft). Nozzle exit contour maps of measured aerothermal loads and structures research since its inception, is thermodynamic properties, calculated Mach number, and calculated being modified with the addition of a LOX system to bring the mass flow are used to determine the mass flow approaching the oxygen content of the test medium up to that of air, the addition inlets of various scramjet engines. Good agreement is found of alternate Mach number capability to augment the current M = between experimentally measured facility total mass flow and facility 7 capability, improvements to the tunnel hardware to reduce total mass flow determined by integration of the nozzle exit mass maintenance downtime, the addition of a hydrogen system to allow flow contours. R.R. the testing of hydrogen powered engines, and a new data system to increase both the quantity and quality of the data obtained. A87-46183"# Queensland Univ., Brisbane (Australia). The paper discusses both the modifications and the development SCRAMJET TESTING IN IMPULSE FACILITIES thereof. Author R. J. STALKER and R. G. MORGAN (Queensland, University, Brisbane, Australia) IN: International Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . New York, American Institute of Aeronautics and Astronautics, 1987, p. 66-74. refs (Contract NAGW-674) A87-45303"# National Aeronautics and Space Administration. The use of impulse facilities for gas dynamic experimentation Langley Research Center, Hampton, Va. on scramjets at high stagnation enthalpies is discussed. It is seen EXPLORATORY EVALUATION OF A MOVING-MODEL TECHNIQUE FOR MEASUREMENT OF DYNAMIC GROUND that, although such facilities will produce adequate stagnation enthalpies, it is necessary to compromise somewhat on the EFFECTS requirements for simulating test section densities, in order to allow GUY T. KEMMERLY, JOHN W. PAULSON, JR. (NASA, Langley realistic operating pressure levels. The shock tunnel and the Research Center, Hampton, VA), and MICHAEL COMPTON (USAF, expansion tube are briefly described, before focusing on operation Wright Aeronautical Laboratories, Wright-Patterson AFB) AIAA, of the reflected shock tunnel. It is shown that test times and flow SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San starting times are such as to allow testing with models of reasonable Diego, CA, June 29-July 2, 1987. 10 p. size, provided that large regions of flow recirculation do not exist. (AIAA PAPER 87-1924) Some examples of experimental scramjet studies, conducted in a An attempt is presently made to measure the dynamic or reflected shock tunnel, are presented, demonstrating that the time-dependent ground effects that may be encountered by aircraft reflected shock tunnel is suitable for basic studies of scramjet during approach and landing by means of a ground-based testing flow processes. Provided that the effective enhancement of fuel technique that employs a model moving horizontally over an calorific value by free stream 'freezing' of oxygen in the shock upwardly inclined ground plane to simulate the rate of descent. tunnel nozzle expansion does not prove to be an insuperable Results have been thus obtained for a 60-deg delta wing and for obstacle, the reflected shock tunnel may be expected to provide an F-18 full configuration, with and without , at realistic simulation of scramjet flows up to speeds approaching forward speeds of up to 100 ft/sec. An analysis of the results earth orbital velocity. Author gathered indicates that ground effects were reduced when the rate of descent was included in the test conditions. O.C. A87-46222# THE ROLE OF SHORT DURATION FACILITIES IN GAS TURBINE RESEARCH D. L. SCHULTZ, R. W. AINSWORTH (Oxford University, England), and C. T. J. SCRIVENER (Rolls-Royce, PLC, Derby, England) IN: A87-45381"# National Aeronautics and Space Administration. International Symposium on Air Breathing Engines, 8th, Cincinnati, Langley Research Center, Hampton, Va. OH, June 14-19, 1987, Proceedings. New York, American Institute A SUBSONIC TO MACH 5.8 SUBSCALE ENGINE TEST of Aeronautics and Astronautics, 1987, p. 417-424. Research FACILITY supported by the Ministry of Defence (Procurement Executive) and EARL H. ANDREWS, JR. (NASA, Langley Research Center, Rolls-Royce, PLC. refs Hampton, VA) AIAA, SAE, ASME, and ASEE, Joint Propulsion It is shown that, for certain classes of studies on gas turbines, Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 12 p. there is an advantage to be gained from the use of short duration refs testing. Not only are total power demands substantially reduced (AIAA PAPER 87-2052) whilst retaining the ability to carry out the required aerodynamic The NASA-Langley Mach 4 facility, in which air-hydrogen studies but short duration techniques are in many ways superior combustion is used to heat the test gas, was modified to make to steady state methods for the measurement of heat transfer the facility suitable for tests of ramjet-type models at subsonic rate to turbine blading. Comparisons between aerodynamic tests and transonic, as well as supersonic, Mach numbers. The in a short duration cascade show excellent agreement with those construction details and the instrumentation of this facility, carried out in a high power continuous cascade. The advantages designated the Combustion-Heated Scramjet Test Facility, are of short duration facilities for heat transfer rate studies are illustrated described, and modifications to enhance the test capability range by reference to comparative studies in a short duration facility from the subsonic/transonic and Mach 3.5 to 5.5 are discussed. and in a conventional high pressure high temperature sector Design diagrams and test result graphs are included. I.S. cascade. The effect of the scale of turbulence and of the turbulence

685 09 RESEARCHANDSUPPORTFACILITIES(AIR) levelontheheat transfer rate is identified and it is shown that A87-46354# the high turbulence level frequently associated with combustion CLASSIFICATION OF THE LOAD-CARRYING CAPACITY OF chamber flows may be due to large scale eddy structures which RUNWAY SURFACES BY THE ACN-PCN METHOD. II do not affect the blade surface momentum transfer and hence [KLASYFIKACJA NOSNOSCI NAWlERZCHNI LOTNISKOWYCH the heat transfer rate from the freestream to the blade. Author METODA ACN-PCN. II] KRZYSZTOF CZARNECKI Technika Lotnicza i Astronautyczna (ISSN 0040-1145), vol. 42, Feb. 1987, p. 19-21, 25. In Polish. refs A method for determining the ACN numbers of aircraft is A87-46241 # presented. This is followed by a method for the determination of MICROPROCESSOR BASED SURGE MONITORING SYSTEM the PCN numbers of runway surfaces. B.J. K. VENKATARAJU, A. G. SATHEERATNAM, and R. RAMANATHAN (Gas Turbine Research Establishment, Bangalore, A87-46438 India) IN: International Symposium on Air Breathing Engines, NEW STANDARDS ESTABLISHED FOR REALISM IN VISUAL 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . New York, SIMULATION American Institute of Aeronautics and Astronautics, 1987, p. KEITH W. FRAY (Singer Co., Link Flight Simulation Div., 579-581. Binghamton, NY) ICAO Bulletin, vol. 42, May 1987, p. 9-12. During the development phase of a gas turbine engine, it is The designs of the 200 deg field-of-view Aircraft Wide Angle highly desirable to have an indication of the operating condition Reflective Display System (AWARDS) and Image IV of the engine all the time to ensure its safety. Compressor is one computer-generated imagery (CGI) visual system for commercial of the most critical components of an air breathing gas turbine flight simulation are described. The AWARDS provides a engine. It has, as is well known, unstable regions of operation. continuous, panoramic, cross-cockpit view for pilots, copilots, and Instability in this component can lead to catastrophe. It is, therefore, other occupants of the simulated aircraft flight deck. The AWARDS necessary to monitor, wherever possible, the operating regions of uses a dome-segment display system, a forward-facing relay-optics the compressor during the development phase. A microprocessor CRT projector system, and an image surface of precision ground based system has been developed for online monitoring of the glass for the mirror assembly. The average brightness level of the operating region of a compressor during an engine test. Relevant system is 10.3 cd/sq m, with a high light brightness of 27.4 cd/sq parameters like inlet and outlet pressures and inlet temperatures m, a display resolution of greater than 3 arcmin, and a surface are fed as inputs to this processing system. A color graphic terminal contrast ratio of 30:1. The basis of the Image IV system is parallel, displays the operating line on the compressor map. It enables multiple microprocessors. The typical features of the Image IV one to know the surge margin at all the operating regions of the system, and the benefits it provides to pilot training are discussed. compressor. It is a very helpful tool during development testing of The Image IV architecture provides a large number of surfaces, the engine. Author and improves antialiasing, translucency, and full planar texture. I.F.

A87-46955# TWO-DIMENSIONAL SUBSONIC AND TRANSONIC WIND A87-46243# TUNNEL WALL INTERFERENCE CORRECTIONS FOR VARIED DIAGNOSTIC METHODS FOR AIR-BREATHING ENGINES WALLS D. LAREDO, Y. LEVY, and Y. M. TIMNAT (Technion - Israel Institute QIWEI ZHANG (Nanjing Aeronautical Institute, People's Republic of Technology, Haifa) IN: International Symposium on Air Breathing of China) Acta Aerodynamic Sinica (ISSN 0258-1825), vol. 5, Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . June 1987, p. 132-140. In Chinese, with abstract in English. refs New York, American Institute of Aeronautics and Astronautics, Two-dimensional subsonic and transonic wall interference 1987, p. 591-597. refs corrections are evaluated from experimental pressure distributions The process of combustion in a sudden-expansion chamber is near the tunnel walls and aerodynamic forces on a model. The presently studied experimentally using a modified LDA technique corrections can be used for both ventilated and solid walls. The to measure the local velocity distribution of the gas and fuel droplets knowledge of wall cross-flow properties is not required. Different of various diameters. Cold and hot flow results for kerosene fuel equations are used for different Mach number ranges. Two methods injected at 1-3 MPa are in good agreement with numerical are provided to suit different needs. One method is a fast computing predictions obtained from a modified TEACH computer code, which method which can be used while the flow near tunnel walls is takes into account chemical reactions and two-phase flow. The subcritical. Another is a finite difference method which can be reattachment length of the recirculation zone varies over 5-7 times used in both subsonic and transonic tests and can judge whether the step height, and is a function of the inlet Reynolds number the test data are correctable. Two practical examples are given. based on step height, chemical reaction, and the presence of the The effect of using different equations on the computing results liquid phase. O.C. is shown. Author

A87-46958# THE PITCHING DAMPING DERIVATIVES MEASURED BY FORCE-OSCILLATION METHOD AT TRANSONIC AND A87-46353# SUPERSONIC WIND TUNNEL CLASSIFICATION OF THE LOAD-CARRYING CAPACITY OF CHENGZENG WANG (China Aerodynamic Research and RUNWAY SURFACES BY THE ACN-PCN METHOD. I Development Center, Mianyang, People's Republic of China) Acta [KLASYFIKACJA NOSNOSCI NAWIERZCHNI LOTNISKOWYCH Aerodynamica Sinica (ISSN 0258-1825), vol. 5, June 1987, p. METODA ACN-PCN. I] 162-170. In Chinese, with abstract in English. refs KRZYSZTOF CZARNECKI (Instytut Techniczny Wojsk Lotniczych, A test mechanism for measuring pitching damping derivatives Warsaw, Poland) Technika Lotnicza i Astronautyczna (ISSN and data reduction equations for obtaining pitching dynamic 0040-1145), vol. 42, Jan. 1987, p. 19-21. In Polish. derivatives are outlined. The experimentally measured pitching The paper examines problems in the classification of the damping derivatives obtained in an FL-23 wind tunnel for AGARD load-carrying capacity of runway surfaces using the ACN-PCN Calibration Model C indicate that the variation trend of damping method. A definition of and general infromation about the ACN-PCN derivatives with Mach numbers is reasonable and the damping method are presented. Attention is given to examples of the derivatives of Model C at M = 2.5 is in good agreement with the determination of load classification numbers for aircraft and runway data obtained in AEDC 4-ft wind tunnel. The results obtained in surfaces with reference to various classification procedures. B.J. repeated tests show that this test mechanism can be used to

686 09 RESEARCH AND SUPPORT FACILITIES (AIR) measurethe pitching damping derivatives for vehicle models in N87-25283"# Flight Safety International, Inc., Tulsa, Okla. transonic and supersonic wind tunnels. Author SIMULATOR SYSTEMS INTEGRATION KEITH W. SHIPMAN In NASA. Langley Research Center, Wind Shear/Turbulence Inputs to Flight Simulation and Systems A87-46960# Certification p 205-207 Jul. 1987 DEVELOPMENT OF EXPERIMENTAL INVESTIGATION ON Avail: NTIS HC A12/MF A01 CSCL 14B TRANSONIC WIND TUNNEL WALL INTERFERENCE The implementation of available wind shear data into general YIYI HUANG (Nanjing Aeronautical Institute, People's Republic of aviation flight training simulators is discussed. Currently, there are China) Acta Aerodynamica Sinica (ISSN 0258-1825), vol. 5, June 11 simulators with wind shear models installed involving some 9 1987, p. 181-187. In Chinese, with abstract in English. refs different aircraft models. Retrofits to other systems that were put This paper introduces the development of experimental out earlier are currently underway, and all the new simulators will investigation on the transonic wind tunnel wall interference and have wind shear available for the instructors to use for provides some quantitative results. Some comments on the recently demonstrations and training. There are three types of computer developed wall interference correcting methods using measured systems involved, and two different types of instructor stations. wall pressure are given. The problems which should be noticed Most of the systems with wind shear are the CRT-type displays. and have not yet been solved are pointed out. A feasible program The integration of wind shear models in flight simulators is for reducing tunnel wall interference is discussed, and appropriate discussed in detail. Author technique for tunnel wall interference investigation is proposed. The conclusions are believed to be useful for improving the design of transonic wind tunnels and model tests. Author N87-25333# Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn (West Germany). Unternehmensbereich Apparate. N87-25275"# National Aeronautics and Space Administration. THE ROLE OF SIMULATION IN HELICOPTER DEVELOPMENT Ames Research Center, Moffett Field, Calif. [DIE ROLLE DER SIMULATION IN DER HUBSCHRAUBERENT- APPLICATION OF DATA TO PILOTED SIMULATORS WlCKLUNG] RICHARD S. BRAY In NASA. Langley Research Center Wind HUBER and KRAUSPE 1986 31 p In GERMAN Presented Shear/Turbulence Inputs to Flight Simulation and Systems at the 16th Internat. Hubschrauberforum Bueckeburg, Hanover, Certification p 97-115 Jul. 1987 West Germany, 11-12 Jun. 1986; and at the AGARD FMP Lecture Avail: NTIS HC A12/MF A01 CSCL 14B Series No. 139 on Helicopter Aeromechanics The application of a further developed analytical model and (MBB-UD-435/86; ETN-87-99925) Avail: Issuing Activity JAWS data to a piloted simulator is addressed. The Ames simulator Real time ground-based and flight simulation for helicopter provides a facility for the development of piloting procedures, and development are reviewed. Simulators are listed. ESA for the selection of training scenarios. The system is operational with the new wind shear models and comprehensive data output. The use of these models with the simulator is dicussed in detail. N87-25334" National Aeronautics and Space Administration. Author Langley Research Center, Hampton, Va. AIRFOIL FLU'I-FER MODEL SUSPENSION SYSTEM Patent WlLMER H. REED, inventor (to NASA) (DEI-Tech, Inc., Newport News, Va.) 28 Jul. 1987 9 p Filed 30 Jul. 1986 Supersedes N86- N87-25278"# Boeing Commercial Airplane Co., Seattle, Wash MICROBURST MODEL REQUIREMENTS FOR FLIGHT SIMULA- 31594 (24 - 23, p 3560) _NASA-CASE-LAR-13522-1-SB; US-PATENT-4,682,494; TION: AN AIRFRAME MANUFACTURER'S PERSPECTIVE US-PATENT-APPL-SN-890576; US-PATENT-CLASS-73-147; RICHARD L. SCHOENMAN In NASA. Langley Research Center US-PATENT-CLASS-73-856) Avail: Issuing Activity CSCL 14B Wind Shear/Turbulence Inputs to Flight Simulation and Systems A wind tunnel suspension system for testing flutter models Certification p 153-164 Jul. 1987 under various loads and at various angles of attack is described. Avail: NTIS HC A12/MF A01 CSCL 14B The invention comprises a mounting bracket assembly affixing the A brief outline is given of topics for presentation and discussion suspension system to the wind tunnel, a drag-link assembly and at the workshop. As manufacturers and certifiers of transport a compound spring arrangement comprises a plunge spring working airplanes and associated on-board systems, an interest in the in opposition to a compressive spring so as to provide a high prevention of wind shear related accidents and incidents is inherent. stiffness to trim out steady state loads and simultaneously a low The near term objectives are to provide the customers technical stiffness to dynamic loads. By this arrangement an airfoil may be support in the areas of training as well as to research existing tested for oscillatory response in both plunge and pitch modes and potentially improved on-board systems. In the future, many while being held under high lifting loads in a wind tunnel. improved systems should be implemented. This will require Official Gazette of the U.S. Patent and Trademark Office certification as well as further educational activity in the use of these new systems. A set of wind models is needed for design work which characterize a wide variety of real microbursts as N87-26053# Deutsche Forschungs- und Versuchsanstalt fuer measured during the JAWS project. The wind models should be Luft- und Raumfahrt, Cologne (West Germany). Hauptabteilung limited in both size and complexity to just those features which Windkanaele. degrade aircraft performance. Author THE 0.6 M X 0.6 M TRISONIC SECTION (TMK) OF DFVLR IN COLOGNE-PORZ, WEST GERMANY Status Report, 1966 N87-25280"# CAE Industries, Ltd., Montreal (Quebec). HELMUT ESCH Mar. 1986 82 p In GERMAN; ENGLISH SIMULATOR MANUFACTURERS' REQUIREMENTS summary Report will also be announced as translation DAVID R. REILLY In NASA. Langley Research Center Wind (ESA-TT-1052) Original contains color illustrations Shear/Turbulence Inputs to Flight Simulation and Systems (DFVLR-MI]-T-86-21; ISSN-0176-7739; ETN-87-99681) Avail: Certification p 173-180 JuL 1987 NTIS HC A05/MF A01; DFVLR, Cologne, West Germany DM Avail: NTIS HC A12/MF A01 CSCL 14B 46.50 Simulator manufacturers must continue to provide the customers Information for users of a blowdown wind tunnel is provided. It the latest wind shear models available for pilot training. The release has a Mach number range from 0.5 to 4.5, with Reynolds numbers, of the JAWS data package enabled the provision of a much more based on a reference length of 1 m, between 10 million and 90 realistic wind shear package to the customer rather than just the million. Typical running times are 60 sec. The Mach number range standard six SRI wind shear profiles currently in use. In this brief is extended by the neighboring hypersonic wind tunnel H2K, in presentation, the steps taken in implementing the JAWS data into which the same models can be tested at Mach numbers up to the FAA 727 simulator are highlighted. Author 11. ESA

687 09 RESEARCHANDSUPPORTFACILITIES(AIR)

N87-26054#Deutsche Forschungs- und Versuchsanstalt fuer 10 Luft- und Raumfahrt, Cologne (West Germany). Hauptabteilung Windkanaele. ASTRONAUTICS THE VERTICAL TEST SECTION (VMK) OF DFVLR IN COLOGNE-PORZ, WEST GERMANY Status Report, 1986 KLAUS TRIESCH and ERNST-OTTO KROHN May 1986 99 p Includes astronautics (general); astrodynamics; ground support In GERMAN; ENGLISH summary Report will also be announced systems and facilities (space); launch vehicles and space vehicles; as translation (ESA-TT-1053) space transportation; spacecraft communications, command and (DFVLR-MITT-86-22; ISSN-0176-7739; ETN-87-99682) Avail: tracking; spacecraft design, testing and performance; spacecraft NTIS HC A05/MF A01; DFVLR, Cologne, West Germany DM 38 instrumentation; and spacecraft propulsion and power. Information for users of a vertical test section blowdown wind tunnel with test section diameters from 150 to 340 mm is presented. A87-45443# The axisymmetric free jet has a Mach number range from 0.5 to STUDIES OF SCRAMJET FLOWFIELDS 0.95 at subsonic speeds, and from 1.57 to 3.23 at supersonic speeds, with Reynolds numbers, based on a reference length of J. A. SCHETZ (Virginia Polytechnic Institute and State University, 1 m, between 3 million and 300 million. Typical testing times are Blacksburg) and F. S. BILLIG (Johns Hopkins University, Laurel, between 30 and 60 sec. ESA MD) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 16 p. Navy-supported research, refs (AIAA PAPER 87-2161) The effective and efficient analytical/numerical treatment of the complex flows encountered in the combustors and nozzles of scramjet vehicles by a modular approach is considered in detail. The general modular approach and the specific methods that have been successfully applied to various separate flow modules are illustrated for representative configurations and conditions for both small, low hypersonic flight Mach number and large, high flight Mach number vehicles. Formulations of the equations of motion, numerical methods, grid arrangement, turbulence modeling, and chemistry are discussed. Author N87-26055# Royal Aircraft Establishment, Farnborough (England). FATIGUE-LIFE MONITORING OF THE 5 METRE WIND TUNNEL 11 D. E. LEAN Aug. 1986 20 p (RAE-TM-AERO-2084; BR100661; ETN-87-90093) Avail: NTIS CHEMISTRY AND MATERIALS HC A02/MF A01 The method used in the processing of fatigue-life data relating Includes chemistry and materials (general); composite materials; to the pressure shell of a 5 m wind tunnel is summarized. The inorganic a_d physical chemistry; metallic materials; nonmetallic processing of a typical set of data illustrates the method. ESA materials; and propellants and fuels.

A87-43398" National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. THERMAL AND FLAMMABILITY CHARACTERIZATION OF GRAPHITE COMPOSITES D. A. KOURTIDES (NASA, Ames Research Center, Moffett Field, CA) Journal of Fire Sciences (ISSN 0734-9041), vol. 4, Nov.-Dec. 1986, p. 397-426. refs Thermal, mechanical, and flammability properties of graphite composites fabricated with XU71775/H795, a bismaleimide/vinyl- polystyrylpyridine formulation; H795, a bismaleimide; Cycom 6162, N87-26056 ESDU International Ltd., London (England). a phenolic; and PSP 6022M, a polystyrylpyridine and two types of FIRST APPROXIMATION TO LANDING FIELD LENGTH OF CIVIL graphite reinforcement were evaluated and compared with a com- TRANSPORT AEROPLANES (50 FT., 15.24 M SCREEN) posite made with an epoxy resin as a matrix. The measured prop- Dec. 1984 11 p erties included limiting-oxygen index, smoke evolution, thermal (ESDU-84040; ISBN-0-85679-504-6; ISSN-0141-4054) Avail: degradation products, total-heat release, heat-release rates, mass ESDU loss, flame spread, ignition resistance, thermogravimetric analysis, ESDU 84040 gives graphs from which quick first approximations and selected mechanical properties. It was found that the combina- can be obtained to the landing field lengths for all types of tion of XU71775/H795 with the graphite tape was the optimum conventional-landing civil transport aircraft. The estimation method design giving the lowest heat release rate. I.S. assumes the use of typical civil-transport-certification style landing maneuvers from the screen on to a hard, level, dry runway. The data are applicable over a wide range of ambient conditions and A87-43454# the effect of non-still-air conditions can be taken into account. THE MICROSTRUCTURE AND MECHANICAL PROPERTIES OF The method is intended for use in initial or project design work VARIOUS ALUMINIUM-LITHIUM ALLOY PRODUCT FORMS FOR but may also be of use in checking results of more detailed HELICOPTER STRUCTURES estimation methods. It is based on an analysis of landing data A. F. SMITH (Westland Helicopters, Ltd., Yeovil, England) DGLR, obtained from aircraft flight manuals and the use of true European Rotorcraff Forum, 12th, Garmisch-Partenkirchen, West groundspeed at the screen and mean brakes-on deceleration as Germany, Sept. 22-25, 1986, Paper. 16 p. Research supported by correlating parameters. A practical worked example illustrates the the Ministry of Defence (Procurement Executive). refs use of the data, and a table is included summarizing landing field This paper describes tests carried out and results obtained length factors from current civil certification requirements. ESDU from various aluminum-lithium alloy product forms, including

688 11 CHEMISTRY AND MATERIALS metallographicexamination,mechanicalpropertydeterminationand A87-44744 conclusionsdrawnfrom heat treatment and component DEVELOPMENTS IN TITANIUM ALLOYS manufacturing trials. Particular emphasis is placed upon aspects D. K. PEACOCK (Titanium Metal and Alloys, Ltd., Essex, of behavior and properties of aluminum-lithium which differ England) IN: Materials in aerospace; Proceedings of the First significantly from those of conventional aluminum alloys, together International Conference, London, England, Apr. 2-4, 1986. Volume with features unique to the new material. Finally, brief mention is 2. London, Royal Aeronautical Society, 1986, p. 290-302. refs made of disadvantages, limitations, and difficulties which may arise A comprehensive comparison is undertaken of the mechanical in the introduction of aluminum-lithium alloys for the manufacture properties of the novel aerospace Ti alloys Ti-10V-2Fe-3AI and of helicopter structures. Author Ti-15V-3Cr with such competitive materials as Ti-6AI-4V in aircraft applications. Ti-10-2-3 is an ideal candidate for isothermal forgings produced to near net shape. Ti-15-3 complements Ti-10-2-3 in providing meltable, fabricable alloys capable of heat treatments A87-44729 tailored for various uses. Both alloys are judged to yield a quantum MATERIALS IN AEROSPACE; PROCEEDINGS OF THE FIRST improvement in structural efficiency. O.C. INTERNATIONAL CONFERENCE, LONDON, ENGLAND, APR. 2-4, 1986. VOLUMES 1 & 2 Conference sponsored by the Royal Aeronautical Society. London, Royal Aeronautical Society, 1986. Vol. 1, 243 p.; vol. 2, 213 p. A87-44745 For individual items see A87-44730 to A87-44750. MATERIALS FOR STRUCTURES OF THE FUTURE The present conference on state-of-the-art applications of G. B. EVANS (British Aerospace, PLC, Haffield, England) IN: advanced materials in the aerospace industries considers topics Materials in aerospace; Proceedings of the First International in helicopter components, guided missiles, propulsion systems, Conference, London, England, Apr. 2-4, 1986. Volume 2. London, spacecraft, and airframe primary structures. Attention is given to Royal Aeronautical Society, 1986, p. 303-347. refs Ti alloy castings, thermoplastic matrix composites, microwavellR The present evaluation of aircraft structural material transparencies, self-reinforcing polymers, carbon/carbon development requirements and possibilities gives attention to the composites, engine hot component ceramics, and mechanical complex and consequential ways in which material property alloying of AI-Mg-Li alloys. Also discussed are superalloy advantages, material costs, and aircraft operation fuel costs, component durability enhancement methods, metal-matrix interact under pressures exerted by manufacturing costs, politics composites, the superplastic forming/diffusion bonding of Ti alloys, and the development time horizon for new aircraft designs. The and AI-Li alloys for aerospace applications. O.C. factors of environmental corrosion and protective measures, galvanic corrosion protection, sealants for fuel tanks, adhesively bonded aircraft structures, residual manufacturing stresses, and novel hydraulic systems are also discussed. O.C. A87-44739 HIGH TEMPERATURE TITANIUM ALLOYS P. A. BLENKINSOP (IMI Titanium, Ltd., Birmingham, England) IN: Materials in aerospace; Proceedings of the First International A87-44747 Conference, London, England, Apr. 2-4, 1966. Volume 1 . London, SUPERPLASTIC FORMING/DIFFUSION BONDING OF Royal Aeronautical Society, 1986, p. 189-208. refs TITANIUM A development history and current status evaluation is J. R. WILLIAMSON (USAF, Wright°Patterson AFB, OH) IN: presented for high temperature Ti alloys intended primarily for aircraft gas turbine engine applications. Since 1970, attention has Materials in aerospace; Proceedings of the First International primarily been given to the fatigue strength of the alloys as well Conference, London, England, Apr. 2-4, 1986. Volume 2. London, as their tensile and creep strength. Control of alloy composition Royal Aeronautical Society, 1986, p. 373-393. and thermomechanical processing has recently led to the An evaluation is made of the technology development maturity development of IMI 834; the alloy can be alpha + beta heat-treated and cost effectiveness of superplastically formed/diffusion bonded using 5-percent volume fractions of alpha phase to pin beta (SPF/DB) titanium alloy methods, as found in the cases of titanium boundaries, thereby restricting the grain growth of the 95-percent components for the B-1B, F-15, F-18, and AV-8B aircraft. SPF/DB beta matrix. Great creep and fatigue resistance characteristics are of F-18 environmental central system ducts is noted to result in a offered by this alloy. Prospective alloy and coating developments 40-percent fabrication labor cost reduction, an 11-fold reduction are projected. O.C. in the number of tools, and 90-percent reductions in tooling labor and materials costs. Tool fabrication time was reduced from 7-10 months to 6-10 weeks. A total of 77 B-1B structural components are produced by SPF/DB processing of Ti alloy. O.C. A87-44743 ADHESIVES IN AEROSPACE A. J. KINLOCH (Imperial College of Science and Technology, London, England) IN: Materials in aerospace; Proceedings of A87-44861 the First International Conference, London, England, Apr. 2-4, 1986. A DECADE OF COMPOSITE RUDDER SERVICE REVIEWED Volume 2 . London, Royal Aeronautical Society, 1986, p. L. J. HART-SMITH and ARTHUR V. HAWLEY (Douglas Aircraft 279-289. Co., Long Beach, CA) Aerospace Engineering (ISSN 0736-2536), A development history and current development status vol. 7, June 1987, p. 57-59. evaluation are presented for the use of structural adhesives in Carbon-epoxy upper aft rudders installed on 15 DC-10 jet aircraft manufacturing, with emphasis on these adhesives' essential transport aircraft have completed almost 350,000 hours of service role in honeycomb core sandwich airframe structure panels, with no significant failures. Installation of the composite rudders flooring, and control surfaces. Attention is given to the effect of resulted in a 33-percent weight savings, and the structures environmental corrosive attack on structural adhesive joints with a withstood over four times the design limit load. Design of these view to consequent mechanical performance, as well as to the rudders is unique in the use of a thin-skinned buckled multirib locus of joint failure, and the chemistry, temperature and humidity structure rather than the usual honeycomb sandwich structure, factors affecting joint durability. Joints to metallic surfaces are and in the out-of-autoclave cocuring of the structure as a one-piece noted to be the most susceptible to environmental degradation; assembly. In the postbuckled design, the spar and rib caps act to metallic substrate surface pretreatments are therefore prescribed. restrict the maximum strains which can develop within the skins. O.C. R.R.

689 11 CHEMISTRY AND MATERIALS

A87-45198# A87-45372"# Drexel Univ., Philadelphia, Pa. APPLICATION OF LOW-REYNOLDS-NUMBER K-EPSILON DEGRADATION MECHANISMS OF SULFUR AND NITROGEN MODEL TO SOLID FUEL TURBULENT BOUNDARY LAYER CONTAINING COMPOUNDS DURING THERMAL STABILITY COMBUSTION TESTING OF MODEL FUELS DAVID YU-YUNG SHAN and JAMES S. T'IEN (Case Western K. T. REDDY, N. P. CERNANSKY (Drexel University, Philadelphia, Reserve University, Cleveland, OH) AIAA, SAE, ASME, and ASEE, PA), and R. S. COHEN (Temple University, Philadelphia, PA) AIAA, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San 2, 1987. 13 p. refs Diego, CA, June 29-July 2, 1987. 10 p. Research supported by (Contract AF-AFOSR-85-0340) the Drexel University. refs (AIAA PAPER 87-1778) (Contract NAG3-183) In this study, turbulent combustion in a boundary layer adjacent (AIAA PAPER 87-2039) to a pyrolyzing solid fuel surface is analyzed. For the velocity field The degradation behavior of n-dodecane (singly or in and turbulence viscosity, the low-Reynolds-number two-equation combination with S- and N-containing dopants) was studied using model by Jones and Launder is adopted. Consistent with this a modified Thermal Oxidation Tester facility between 200 fluid mechanical treatment, the combustion model, which is and 400 C. The products were analyzed by gas chromatography modified from the mixing layer formulation using infinite fast and mass spectrometry. The soluble products consisted mainly of chemical kinetics and beta probability density function for the n-alkanes and 1-alkenes, aldehydes, tetrahydrofuran derivatives, mixture fraction, also consists of the same set of governing dodecanol and dodecanone isomers, C21-C24 alkane isomers, and equations and coefficients in the entire computational domain, dodecylhydroperoxide (ROOH) decomposition products. The major including the vicinity of the solid surface. The flame and flow field products were always the same, with and without dopants, but are solved numerically by a downstream marching scheme. At their distributions varied considerably. The 3,4-dimercaptotoluene the Reynolds number where the computation has been carried and dibutylsulfide dopants added individually to n-dodecane out, the flame structure predicted by this model shows that the interferred with the hydrocarbon oxidation at the alkylperoxy radical time averaged mass fractions of fuel and oxidizer overlap and the alkylhydroperoxide link, respectively, while the substantially. A rounded temperature profile is observed with the 2,5-dimethylpyrrole dopant inhibited ROOH formation. Pyridine, maximum mean temperature well below the adiabatic value. In pyrrole, and dibenzothiophene added individually showed few addition a comparison of the boundary layer structure with significant effects. I.S. incompressible cases is made. Author A87-45898"# Garrett Turbine Engine Co., Phoenix, Ariz. DURABILITY CHARACTERIZATION OF CERAMIC MATERIALS FOR GAS TURBINES W. D. CARRUTHERS and L. J. LINDBERG (Garrett Turbine Engine Co., Phoenix, AZ) International Committee for Advanced Materials Technology, Ceramic Workshop, 2nd, Nagoya, Japan, Mar. 9, 10, 1987, Paper. 15 p. NASA-supported research. A87-45202# The strength retention of ceramic materials during extended DIAGNOSTICS IN SUPERSONIC COMBUSTION high-temperature cyclic exposure is critical to their widespread Y. M. TIMNAT (Technion - Israel Institute of Technology, Haifa) application in gas turbine engines. During a continuing NASA funded AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, program initated in 1979, reaction bonded silicon nitride (RBSN), San Diego, CA, June 29-July 2, 1987. 10 p. refs sintered silicon carbide (SSC), reaction sintered silicon carbide (AIAA PAPER 87-1787) (RSSC), and sintered silicon nitride (SSN) materials were evaluated Diagnostic techniques which have shown promise in their following simulated gas turbine engine exposures. Exposures were application to supersonic combustion are discussed. Consideration performed by cycling specimens five times per hour between a is given to temperature measurements by thermocouple and high velocity burner discharge and a rapid air quench. The retained nonintrusive optical methods, velocity determination with lasers, flexural strengths were determined following up to 3500 hours of concentration measurements using probes, and regression rates exposure at temperatures up to 1370 C. Post-exposure strengths in solid propellants employing microwaves and ultrasonics. Different have been correlated with fractography and surface examination types of measurements of the same parameter are compared using SEM. Results illustrate excellent strength retention of SSC and it is concluded that the suitability of a particular technique materials after 3500 hours of exposure to 1370 C. At 1200 C, depends on the experimental conditions. K.K. RBSN and RSSC also demonstrate significant strength retention. Although SSN materials typically suffer significant strength losses during exposures at 1200 C, a new composition, which has improved high-temperature strength, also shows improved durability. In the majority of the materials, strength loss is typically associated with flaw formation in the protective SiO2 layer. Author A87-45274# PROGRESS TOWARD SHOCK ENHANCEMENT OF SUPER- A87-46221# SONIC COMBUSTION PROCESSES APPLICATION OF CERAMICS TO RAMJET ENGINE NOZZLES FRANK E. MARBLE, GAVIN J. HENDRICKES, and EDWARD E. SHIMON SHANI, JOSEPH BARTA, and ARIE PERETZ (Rafael ZUKOSKI (California Institute of Technology, Pasadena) AIAA, Armament Development Authority, Haifa, Israel) IN: International SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, San Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June Diego, CA, June 29-July 2, 1987. 9 p. refs 14-19, 1987, Proceedings . New York, American Institute of (AIAA PAPER 87-1880) Aeronautics and Astronautics, 1987, p. 408-414. refs A mechanism for enhancing the rate of mixing between air Several ceramic materials were evaluated experimentally for and hydrogen fuel over rates that are expected in shear layers application to ramjet nozzle throats under simulated ramjet and jets is investigated. Particular attention is given to the rapid configuration and operation conditions. The test nozzles were mixing induced by the interaction of a weak oblique shock with a mounted to a ramjet combustor, which burns JP-4/air/oxygen cylindrical jet of hydrogen embedded in air. It is concluded that mixture. The concepts mostly tested were sintered yttria-stabilized shock-induced mixing enhancement permits a significant reduction zirconia structures and zirconia coatings on porous graphites. in the time (length) required for the mixing process and that the Appropriate fabrication processes have been developed and test technique merits incorporation into engine development programs. survivability criteria were determined. Nozzle throat inserts made K.K. of sintered stabilized zirconia and zirconia-coated graphites (with

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intermediate molybdenum layer) sustained successfully (no N87-25436# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich disintegration and no measurable erosion) total temperature and (West Germany). pressure of 2450 K and 0.6MPa, respectively, for 100 sec. The EFFECTS OF IMPACT LOADING ON CARBON FIBER results of the study point out that these materials and concepts REINFORCED STRUCTURES [AUSWIRKUNGEN VON may be used successfully at nozzle throats, subjected to severe SCHLAGBEANSPRUCHUNGEN AUF CFX-STRUKTUREN] internal environment conditions, such as those encountered in J. BAUER and J. WARNECKE 1986 5 p In GERMAN high-performance ramjet engines. Author Presented at DGLR-Jahrestagung, Munich, West Germany, 9-10 Oct. 1986 (MBB-Z-83/86; ETN-87-99975) Avail: Issuing Activity A87-46772# The effects of impact loading on carbon fiber reinforced plastics CRACK GROWTH PREDICTION IN 3D STRUCTURES UNDER aircraft structures were investigated. Structures which are AERONAUTICAL-TYPE SPECTRUM LOADINGS damage-tolerant and light can only be realized if possible impact R. LABOURDETTE, G. BAUDIN, and M. ROBERT (ONERA, loading is already taken into account during the construction and Chatillon-sous-Bagneux, France) (International Conference on the static design. This requires an estimate of the impact energy Fatigue and Fatigue Thresholds, University of Virginia, and suitable comparative values for the dimensioning criterium Charlottesville, VA, June 28-July 2, 1987) ONERA, TP, no. 1987-79, (acceptable fiber extension). Another possibility of a 1987, 11 p. refs damage-tolerant construction is the optimization of the laminate (ONERA, TP NO. 1987-79) via the stacking sequence. ESA A model predicting the behavior of crack fronts in three-dimensional structures subjected to aeronautical spectrum Ioadings is presented. The model is based on the work of Baudin and Robert (1984) for two-dimensional structures, coupled to a description by Labourdette and Baudin (1981) of crack growth in three-dimensional structures subjected to constant-amplitude Ioadings. A comparison of predictions for 7075-T7351 alloy bending specimens undergoing FALSTAFF and mini-TWIST sequences with experimental results yielded reasonably good agreement. I.S. N87-25439"# Lockheed-California Co., Burbank. FLIGHT SERVICE EVALUATION OF ADVANCED COMPOSITE A87-46874# AILERONS ON THE L-1011 TRANSPORT AIRCRAFT Annual AIRCRAFT SKIN THAT BRUISES Flight Service Report No. 5 RICHARD DEMEIS Aerospace America (ISSN 0740-722X), vol. R. H. STONE Jun. 1987 14 p 25, July 1987, p. 33, 34. (Contract NASI-15069) The use of a microencapsulated dye system on aircraft to (NASA-CR-178321; NAS 1.26:178321) Avail: NTIS HC A02/MF indicate areas of damage and the severity is examined. The A01 CSCL 11D capsules, which are made from gelatine or polyurea materials, This report covers flight service evaluation of composite inboard and the indicators, which are enclosed inside the capsules and ailerons on the L-1011 under contract NAS1-15069 for a period remain liquid over the aircraft-skin operating temperature range, of five years. This is the fifth and final annual report of the bruise under impact. The inspection of impact damage using X-ray maintenance evaluation program, and covers the period from July or UV detection is described. The dye system has been tested on 1986 when the fourth yearly inspections were completed, through graphite-epoxy panel samples, and it is shown that it is effective May 1987. Four shipsets of graphite/epoxy composite inboard for passively assessing impact damage to aircraft parts. I.F. ailerons were installed on L-1011 aircraft for this maintenance evaluation program. These include two Delta and two TWA aircraft. A fifth shipset of composite ailerons was installed in 1980 on N87-25435"# National Aeronautics and Space Administration. Lockheed's flight test L-1011. The previous four annual inspections Langley Research Center, Hampton, Va. had been visual exterior inspections only. For this final inspection, PRELIMINARY STRUCTURAL DESIGN OF COMPOSITE MAIN the lower covers were removed for access and both interior and ROTOR BLADES FOR MINIMUM WEIGHT exterior surfaces, spars and ribs, and fastener holes were MARK W. NIXON Jul. 1987 28 p Prepared in cooperation inspected. No damage or defects were observed on any of the with Army Aviation Research and Development Command, composite ailerons, and no maintenance actions had occurred Hampton, Va. except for repainting of areas with paint loss. Flight hours on the (Contract DA PROJ. 1L1-62209-AH-76) airline components at the time of inspection ranged from 14,597 (NASA-TP-2730; L-16310; NAS 1.60:2730; AVSCOM-TM-87-B-6) to 17,180 hours, after approximately 5 years of service. Author Avail: NTIS HC A03/MF A01 CSCL 11D A methodology is developed to perform minimum weight structural design for composite or metallic main rotor blades subject to aerodynamic performance, material strength, autorotation, and frequency constraints. The constraints and load cases are developed such that the final preliminary rotor design will satisfy U.S. Army military specifications, as well as take advantage of the versatility of composite materials. A minimum weight design is first developed subject to satisfying the aerodynamic performance, strength, and autorotation constraints for all static load cases. N87-25988# Idaho Univ., Moscow. Dept. of Mechanical The minimum weight design is then dynamically tuned to avoid Engineering. resonant frequencies occurring at the design rotor speed. With DYNAMIC MECHANICAL PROPERTIES OF ADVANCED this methodology, three rotor blade designs were developed based COMPOSITE MATERIALS AND STRUCTURES: A REVIEW on the geometry of the UH-60A Black Hawk titanium-spar rotor R. F. GIBSON In Vibration Inst., The Shock and Vibration Digest, blade. The first design is of a single titanium-spar cross section, Volume 19, No. 7 p 13-22 Jul. 1987 which is compared with the UH-60A Black Hawk rotor blade. The Avail: NTIS HC A05/MF A01 second and third designs use single and multiple Progress is reviewed in the analytical and experimental graphite/epoxy-spar cross sections. These are compared with the characterization of dynamic properties of advanced composite titanium-spar design to demonstrate weight savings from use of materials and structures during the period 1983 to 1986. The this design methodology in conjunction with advanced composite implications of this research and the directions of continued materials. Author research are discussed. Author

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N87-26151# Messerschmitt-Boelkow-Blohm G.m.b.H., Hamburg A87-42852" National Aeronautics and Space Administration. (West Germany). Unternehmensbereich Transport- und Ames Research Center, Moffett Field, Calif. Verkehrsflugzeuge. FAILURE ANALYSIS OF A LARGE WIND TUNNEL DEVELOPMENT AND TESTING OF CRITICAL COMPONENTS COMPRESSOR BLADE FOR THE TECHNOLOGICAL PREPARATION ON AN AIRBUS ROY W. HAMPTON and HOWARD G. NELSON (NASA, Ames FUSELAGE MADE OF CARBON FIBER REINFORCED Research Center, Moffett Field, CA) IN: Case histories involving PLASTICS, PHASE 1 Final Report, Oct. 1985 fatigue and fracture mechanics; Proceedings of the Symposium, DIETER SCHULZ, WOLF-DIETRICH DOLZINSKI, UDO Charleston, SC, Mar. 21, 22, 1985 . Philadelphia, PA, American HERRMANN, SAMIR MALEK, KLAUS-HEINER SCHNEIDER, Society for Testing and Materials, 1986, p. 153-180. refs SIEGFRIED STENZEL, HANS-JUERGEN RIECKHOF, PETER A failure analysis was performed to establish the cause of a FORNELL, and MICHAEL KOLAX Bonn, West Germany BMFT 2014-T6 aluminum compressor rotor blade failure in a large Dec. 1986 141 p In GERMAN; ENGLISH summary Sponsored NASA-Ames wind tunnel. Metallurgical failure analysis by light by BMFT photography, fractographic SEM examinations, and fatigue (BMFT-FB-W-86-017; ISSN-0170-1339; ETN-87-99906) Avail: experiments showed that a 0.13-mm-deep scratch in the shank of NTIS HC A07/MF A01; Fachinformationszentrum, Karlsruhe, West the blade had acted as an initiation site for a fatigue crack, which Germany DM 29.50 subsequently grew by Stage II fatigue before occurrence of the Technological premises for the introduction of carbon fiber final fracture by unstable crack growth. Studies of modal reinforced plastics (CFRP) in wide-body fuselage structures of deformation plots and blade FEM analysis indicated that Mode-3 passenger aircraft were constituted. Design principles in was the most likely mode responsible for the resonance condition accordance with criteria of operating costs such as weight, which produced the vibration loading that effected crack growth. manufacturing costs, and in-service expenses, were evaluated. The Tunnel measurements data showed that the crack growth was specifications for a CFRP fuselage were prepared. A program controlled by both the tunnel resonance and the dampening from aiming at lower development risks for the critical components was the crack itself. I.S. defined, scheduled, and implemented. Critical components were manufactured. Materials for composite structures were selected and tested as to impact, hot/wet performance, and burning behavior. ESA

A87-42853 FATIGUE CRACK GROWTH PREDICTIONS OF WELDED AIRCRAFT STRUCTURES CONTAINING FLAWS IN THE RESIDUAL STRESS FIELD JAMES B. CHANG (Northrop University, Inglewood, CA) IN: Case histories involving fatigue and fracture mechanics; Proceedings of the Symposium, Charleston, SC, Mar. 21, 22, 1985 12 • Philadelphia, PA, American Society for Testing and Materials, 1986, p. 226-242. refs ENGINEERING This paper presents a procedure for fatigue crack analysis which makes it possible to predict the remaining crack life in a welded aircraft structure subjected to a fully reversed flight Includes engineering (general); communications; electronics and spectrum loading. The results of the analysis, which employed electrical engineering; fluid mechanics and heat transfer; the EFFRGO 111 computer code, showed good correlation when instrumentation and photography; lasers and masers; mechanical compared with test data. The results indicate that residual stresses engineering; quality assurance and reliability; and structural play a very important role for a flaw or a crack growing in the mechanics. welded structure and that the residual stress effect should be accounted for in the analysis of crack growth behavior. I.S.

A87-42851" National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. CASE HISTORIES INVOLVING FATIGUE AND FRACTURE MECHANICS; PROCEEDINGS OF THE SYMPOSIUM, CHARLESTON, SC, MAR. 21, 22, 1985 C. MICHAEL HUDSON, ED. (NASA, Langley Research Center, A87-42854 Hampton, VA) and THOMAS P. RICH, ED. (Bucknell University, FATIGUE AND FRACTURE MECHANICS ANALYSIS OF Lewisburg, PA) Symposium sponsored by ASTM. Philadelphia, COMPRESSION LOADED AIRCRAFT STRUCTURE PA, American Society for Testing and Materials , 1986, 435 p. DANIEL L. RICH, R. E. PINCKERT (McDonnell Aircraft Co., St. For individual items see A87-42852 to A87-42857. Louis, MO), and T. F. CHRISTIAN, JR. (USAF, Warner Robins Air Papers are presented on cracking at nozzle corners in the Logistics Center, Robins AFB, GA) IN: Case histories involving nuclear pressure vessel industry, applied fracture mechanics for fatigue and fracture mechanics; Proceedings of the Symposium, assessing defect significance in a crude oil pipeline, failure analysis Charleston, SC, Mar. 21, 22, 1985 . Philadelphia, PA, American of a large wind-tunnel compressor blade, analysis of a Society for Testing and Materials, 1986, p. 243-258. refs compressor-wheel failure, and preventing fracture by inspection Fatigue and fracture mechanical analysis was performed to and analysis. Consideration is also given to the fatigue crack growth determine exact nature of cracking discovered during inspection predictions of welded aircraft structures containing flaws in the of an F-15 fighter aircraft in the wing upper spar cap at the inboard residual stress field, the fatigue and fracture mechanics analysis end of the spar (which is a compression member during normal of a compression loaded aircraft structure, fracture of an aircraft flight). A detailed finite element model was developed to determine horizontal stabilizer, fatigue life analysis of fuel tank skins under the local stresses at the fastener holes in the seal groove, as combined loads, and aircraft structural maintenance well as the overall stresses in the flange. An experimental program recommendations based on fracture mechanics analysis. Additional was conducted in which element specimens were subjected to papers discuss an analysis of two metal-forming die failures, an spectrum loading to obtain crack initiation and crack growth analysis of a failed saw arbor, and the role of fracture mechanics characteristics. The analyses gave accurate predictions of in assessing the effect on fatigue life of design changes in welded in-service crack initiation and crack growth, provided the residual fabrications. I.S. stresses were included. I.S.

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A87-42905 discussions of the results are presented. The problem is important ELECTROCHEMICALMACHININGPROCESSESINAIRCRAFT in vacuum technology, astrophysics and new aircraft and rocket ENGINEBUILDING[TEKHNOLOGIIAELEKTROKHIMICHESKOI OBRABOTKIDETALEIVAVIADVlGATELESTROENII] technology. Author VASILII ALEKSANDROVl SHMANEV, VLADIMIR GEORGIEVICH FILIMOSHIN, AL'BERT KHAMZOVlCH KARIMOV, B. I. PETROV, A87-43053"# National Aeronautics and Space Administration. and N. D. PRONICHEV Moscow, Izdatel'stvo Mashinostroenie, Langley Research Center, Hampton, Va. MOLECULAR FLOW VELOCITY USING DOPPLER SHIFTED 1986, 168 p. In Russian. refs RAMAN SPECTROSCOPY Electrochemical machining processes used in the fabrication of the compressor and turbine blades of gas turbine engines and REGINALD J. EXTON, MERVIN E. HILLARD, JR., WALTER R. LEMPERT, PETER F. COVELL, and DAVID S. MILLER (NASA, the use of electrochemical methods for machining the surfaces of aircraft engine components made of high-temperature high-strength Langley Research Center, Hampton, VA) AIAA, Thermophysics Conference, 22nd, Honolulu, HI, June 8-10, 1987. 10 p. refs alloys and steels are examined. Methods for calculating the process variables and electrode parameters are presented. Attention is (AIAA PAPER 87-1531) also given to ways of increasing the efficiency of electrochemical Measurements of molecular flow velocity, static pressure, and machining. V.L. translational temperature in the free-stream of a supersonic wind tunnel and behind the shock of a simple model are reviewed. A87-42914 Based on the free-stream demonstration using inverse Raman HONEYCOMB STRUCTURES: PARAMETER SELECTION AND spectroscopy, an experiment is outlined to investigate the lee-side flow field above a swept delta wing and simulated spectra expected DESIGN [SOTOVYE KONSTRUKTSII: VYBOR PARAMETROV I for the leading-edge vortex are included. The extension of the PROEKTIROVANIE] technique to hypersonic wind tunnels is also explored through the ASKOL'D IVANOVlCH ENDOGUR, MARK VLADIMIROVICH use of simulated spectra. Author VAINBERG, and KONSTANTIN MOISEEVlC IERUSALIMSKII Moscow, Izdatel'stvo Mashinostroenie, 1986, 200 p. In Russian. refs A87-43381"# Naval Surface Weapons Center, Silver Spring, The book is concerned with the efficient design of aircraft Md. components using sandwich panels with a honeycomb core. In NUMERICAL SIMULATION AND COMPARISON WITH particular, attention is given to the mechanical characteristics of EXPERIMENT FOR SELF-EXCITED OSCILLATIONS IN A various honeycomb cores, including honeycomb structures of DIFFUSER FLOW aluminum and titanium alloys and Nomex polyamide paper; the T. HSIEH (U.S. Navy, Naval Surface Weapons Center, Silver load-bearing capacity of honeycomb panels and shells; fracture Springs, MD), T. J. BOGAR (McDonnell Douglas Research characteristics of honeycomb structures; and optimal parameters Laboratories, St. Louis, MO), and T. J. COAKLEY (NASA, Ames of honeycomb plates and shells under various kinds of loading. Research Center, Moffett Field, CA) AIAA Journal (ISSN The discussion also covers the design and performance 0001-1452), vol. 25, July 1987, p. 936-943. Research supported characteristics of bonded, welded, and soldered sandwich panels, by the U.S. Navy and McDonnell Douglas Independent Research typical joint configurations, and optimal design of some specific and Development Program. Previously cited in issue 18, p. 2662, aircraft components using honeycomb panels. V.L. Accession no. A85-39799. refs

A87-42916 A87-43453# THREE-DIMENSIONAL PROBLEMS IN COMPUTATIONAL FLUID RESEARCH ON THE STRESS ANALYSIS METHOD OF RUBBER DYNAMICS [PROSTRANSTVENNYE ZADACHI VYCHISLITEL- STRUCTURE - CALCULATION OF THE FREQUENCY ADAPTER 'NOI AEROGIDRODINAMIKI] STRESSES IURII DMITRIEVICH SHEVELEV Moscow, Izdaterstvo Nauka, YUQI LIU, ZHANGJIN, YONGKANG TU (Chinese Helicopter 1986, 368 p. In Russian. refs Research and Development Institute, People's Republic of China), Current approaches to the numerical solution of some and HEXlANG LU (Dalian Institute of Technology, People's three-dimensional problems in fluid dynamics are examined with Republic of China) DGLR, European Rotorcraft Forum, 12th, emphasis on finite difference methods. In particular, attention is Garmisch-Partenkirchen, West Germany, Sept. 22-25, 1986, Paper. given to the mathematical principles of the design of complex 10 p. refs geometries and construction of arbitrary systems of curvilinear In this paper, the incremental method and Newton-Raphson coordinates; three-dimensional flows in an incompressible fluid near iteration method are used for calculating the frequency adapter blunt bodies; and three-dimensional supersonic flow of an ideal stresses. The F.E. method is used to solve the stresses of the gas past blunt bodies. The discussion also covers three-dimensional rubber structure that can be simplified as the problem of plane laminar boundary layers in a compressible gas and numerical strain. All the formulations are based on the strain energy function, modeling of three-dimensional turbulent flows. V.L. considering nonlinear relation of the stress-strain of rubber materials, the nonlinear relation of displacement-strain, and A87-43046# incompressibility of the rubber materials. Author NATURAL CONVECTION FLOW OF A RADIATING RAREFIED GAS BETWEEN CONCENTRIC ROTATING SPHERES A. R. BESTMAN (International Centre for Theoretical Physics, Trieste, Italy) AIAA, Thermophysics Conference, 22nd, Honolulu, A87-43610 HI, June 8-10, 1987. 8 p. refs MATHEMATICAL MODEL FOR CALCULATING THE ATOMIZA- (AIAA PAPER 87-1523) TION OF A LIQUID JET BY AN ANNULAR GAS STREAM [RAS- The gasdynamics of a rarefied gas between two concentric CHETNO-TEORETICHESKAIA MODEL' DROBLENIIA STRUI rotating spheres is studied when the temperatures of the spheres ZHIDKOSTI KOL'TSEVYM GAZOVYM POTOKOM] are large enough for radiative heat transfer to be significant. IU. O. KAS'IANOV Samoletostroenie - Tekhnika Vozdushnogo Assuming the gas is slightly rarefied, the problem is modelled by Flota (ISSN 0581-4634), no. 53, 1986, p. 30-36. In Russian. the differential Navier Stokes equations and slip boundary The paper proposes a model for calculating the mixing of coaxial conditions. When the buoyancy parameter is small, asymptotic gas and liquid jets at interaction angles close to zero. The model approximation is adopted for the solution. On the assumption that makes it possible to determine the form of the spray flow field, the gas is optically thick and invoking the Rosseland differential the size of the droplets formed, the configuration of the unatomized approximation for radiation, the basic nonlinear approximation is part of the liquid jet, and other parameters of the two-phase flow. integrated in a close form. The higher approximations which are The results are of interest in connection with the development of linear are tackled by finite difference scheme. Quantitative gas-liquid mixing elements for use in aircraft engines. B.J.

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A87-43611 A87-45104"# National Aeronautics and Space Administration. EFFICIENCYOFTHEUTILIZATIONOF ROTOR BLADE SHROUD Langley Research Center, Hampton, Va. LABYRINTH SEALS IN AN AXIAL-COMPRESSOR STAGE WITH A MINIATURE REMOTE DEADWEIGHT CALIBRATOR LARGE RADIAL CLEARANCES [EFFEKTIVNOST' PRIMENENIIA FRANK H. SUPPLEE, JR. and PING TCHENG (NASA, Langley NADROTORNYKH USTROISTV LABIRINTNOGO TIPA V Research Center, Hampton, VA) IN: International Instrumentation STUPENI OSEVOGO KOMPRESSORA PRI UVELICHENNYKH Symposium, 32nd, Seattle, WA, May 5-8, 1986, Proceedings RADIAL'NYKH ZAZORAKH] Research Triangle Park, NC, Instrument Society of America, 1986, V. A. KOVAL', G. V. PAVLENKO, and S. N. SHILO p. 65-85. Samoletostroenie Tekhnika Vozdushnogo Flota (ISSN A miniature, computer-controlled, deadweight calibrator was 0581-4634) developed to remotely calibrate a force transducer mounted in a cryogenic chamber. This simple mechanism allows automatic loading and unloading of deadweights placed onto a skin friction A87-43622 balance during calibrations. Equipment for the calibrator includes PARAMETERS OF OPTIMAL PLANETARY GEARS OF AI TYPE a specially designed set of five interlocking 200-milligram weights, [PARAMETRY OPTIMAL'NYKH PLANETARNYKH PEREDACH a motorized lifting platform, and a controller box taking commands TIPA AI] from a microcomputer on an IEEE interface. The computer is also V. M. RYDCHENKO Samoletostroenie - Tekhnika Vozdushnogo used to record and reduce the calibration data and control other Flota (ISSN 0581-4634), no. 53, 1986, p. 90-93. In Russian. calibration parameters. The full-scale load for this device is 1,000 Computer calculations of the kinematic and geometric milligrams; however, the concept can be extended to accommodate characteristics of AI planetary gears (used in aircraft) are presented. other calibration ranges. Author Optimal solutions for various gear ratios and satellite numbers are sought according to a combination of five particular optimization criteria. B.J.

A87-44725 A87-45107 VISUAL SYSTEMS DEVELOPMENTS OPTICALLY INTERFACED SENSOR SYSTEM FOR AEROSPACE M. R. HASWELL (Singer Link-Miles, Ltd., Lancing, England) IN: APPLICATIONS Advances in flight simulation - visual and motion systems; DOUGLAS R. PATRIQUIN, FRED L. LICHTENFELS, and RICHARD Proceedings of the International Conference, London, England, P. ANDRESEN (Hercules, Inc., Instrument Systems Div., Apr. 29-May 1, 1986. London, Royal Aeronautical Society, 1986, Vergennes, VT) IN: International Instrumentation Symposium, p. 264-271. 32rid, Seattle, WA, May 5-8, 1986, Proceedings. Research Triangle Recent advances in visual system technology which fulfill the Park, NC, Instrument Society of America, 1986, p. 117-124. requirements of field of view (FOV) and resolution are examined. With the increasing use of composites in aircraft, emphasis The capabilities of modern visual systems are discussed in terms has been placed on reduction of the number of wired connections of an image generator that produces the visual scene and a display between various components. This concern is reflected in the system that presents the visual scene to the pilot. The improved development of fiberoptic systems for new aircraft. This paper training effectiveness achieved with area-of-interest techniques, in details a technique for fiberoptic interconnection of interfaces to particular the modular digital image generator, is evaluated. conventional sensors. The benefit of this technique is that wired Consideration is given to image generator requirements for training interconnections are eliminated while using proven sensor effectiveness and area-of-interest displays, and display system technology. The interfaces employ optical powering with power requirements for training effectiveness. A eye-slaved projected requirements compatible with solid state sources. Sensor data is raster inset visual system that provides a high-resolution display then converted to a modulated optical signal for transmission. An area within a wide FOV background of low resolution has been experimental system of several multiplexed optically interfaced developed. The visual system consists of a helmet-mounted sensors is described. The results of testing the system and potential occulometer system, a foveal projection system, peripheral aerospace applications are discussed. Author projectors, merge electronics, distortion correction electronics, and a high gain dome screen; the functions of these components are described. I.F.

A87-44726 AOI DISPLAYS USING LASER ILLUMINATION A87-45123"# National Aeronautics and Space Administration. B. BARBER (Rediffusion Simulation, Ltd., Crawley, England) IN: Langley Research Center, Hampton, Va. Advances in flight simulation - visual and motion systems; CRASH RESPONSE DATA SYSTEM FOR THE CONTROLLED Proceedings of the International Conference, London, England, IMPACT DEMONSTRATION (ClD) OF A FULL SCALE Apr. 29-May 1, 1986. London, Royal Aeronautical Society, 1986, TRANSPORT AIRCRAFT p. 272-294. refs RAYMOND S. CALLOWAY and VERNIE H. KNIGHT, JR. (NASA, The development and design of a helmet-mounted laser Langley Research Center, Hampton, VA) IN: International projector are described. The projector design features are: laser Instrumentation Symposium, 32nd, Seattle, WA, May 5-8, 1986, illumination, two channel eye-coupled area-of-interest (AOI) visual Proceedings. Research Triangle Park, NC, Instrument Society of display, close proximity, and exit pupil and eye point. The America, 1986, p. 409-427. helmet-mounted optics include galvanometer driven mirrors which NASA Langley's Crash Response Data System (CRDS) which perform vertical scanning and deflect the projected rasters vertically is designed to acquire aircraft structural and anthropomorphic and horizontally. The display system of the helmet-mounted laser dummy responses during the full-scale transport CID test is projector is coupled to the visual technology research simulator described. Included in the discussion are the system design flight computer and receives video from the two channels of the approach, details on key instrumentation subsystems and image generator. Consideration is given to the system's line image operations, overall instrumentation crash performance, and data generator, fiber optic links, head and eye trackers, computer-image recovery results. Two autonomous high-environment digital flight generation, and visual processor. The assembly of the helmet instrumentation systems, DAS 1 and DAS 2, were employed to and the calibration of the head and eye trackers are discussed. obtain research data from various strain gage, accelerometer, and The performance of the projector is evaluated, and it is observed tensiometric sensors installed in the B-720 test aircraft. The CRDS that the system performs well. An alternative design for an AOI successfully acquired 343 out of 352 measurements of dynamic projector requirement is proposed. I.F. crash data. K.K.

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A87-45124 frequencies, time and frequency dependent vibration amplitudes A RUGGED ELECTRONIC PRESSURE SCANNER DESIGNED and comparison of the optical noninterference results with strain FOR TURBINE TEST gage readings. Author TIMOTHY W. WORST and DOUGLAS B. JUANARENA (Pressure Systems, Inc., Hampton, VA) IN: International Instrumentation A87-45189# Symposium, 32rid, Seattle, WA, May 5-8, 1986, Proceedings . REAL-TIME NEUTRON IMAGING OF GAS TURBINES Research Triangle Park, NC, Instrument Society of America, 1986, P. A. E. STEWART (Rolls-Royce, PLC, Advanced Projects Dept., p. 429-444. Bristol, England) AIAA, SAE, ASME, and ASEE, Joint Propulsion This paper describes a rugged 16 channel electronic pressure Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 17 p. scanner capable of withstanding the extreme environmental Research supported by the Ministry of Defence (Procurement conditions associated wiith turbine test. It consists of a transducer Executive), Admiralty Weapons Research Establishment, and per port, internal multiplexing, amplification and an integral Atomic Energy Research Establishment. refs calibration valve permitting on-line calibrations. Its design also (AIAA PAPER 87-1762) includes a heater or cooling chamber to permit extreme cold or The current status of real-time neutron radiography imaging is hot applications. In addition to the benefits of past electronic briefly reviewed, and results of tests carried out on cold neutron pressure scanner instruments such as on-line calibration and scan sources are reported. In particular, attention is given to rates of up to 20,000 measurements per second, this type of demonstrations of neutron radiography on a running gas turbine scanner also can offer individual reference ports for true differential engine. The future role of real-time neutron imaging in engineering measurements and the ability to apply a separate calibration diagnostics is briefly discussed. V.L. reference pressure during calibration. This rugged electronic pressure scanner also offers the ability to field replace the pressure A87-45201# transduction modules in the event one should be destroyed or be MORPHOLOGY OF A STANDING OBLIQUE DETONATION rendered inoperative. This paper describes its design, performance WAVE and presents typical applications. Author DAVID T. PRAI-I', JOSEPH W. HUMPHREY, and DENNIS E. GLENN (Advanced Projects Research, Inc., Sacramento, CA) A87-45178# AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 23rd, ROTOR WAKE SEGMENT INFLUENCE ON STATOR-SURFACE San Diego, CA, June 29-July 2, 1987. 11 p. refs BOUNDARY LAYER DEVELOPMENT IN AN AXIAL-FLOW (AIAA PAPER 87-1785) COMPRESSOR STAGE The morphology of the standing oblique detonation wave (ODW) J. L. HANSEN (General Motors Corp., Allison Gas Turbine Div., is examined with particular reference to propulsion system Indianapolis, IN) and T. H. OKIISHI (Iowa State University of applications. It is shown that the maximum amount of heat that Science and Technology, Ames) AIAA, SAE, ASME, and ASEE, can be released in an overdriven weak ODW increases with Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July approach static temperature and Mach number and decreases 2, 1987. 6 p. USAF-sponsored research, refs with increasing wedge angle; it is insensitive to pressure and (AIAA PAPER 87-1741) considerably less than the Chapman-Juguet heat addition for The boundary layer development on blades in an axial-flow normal detonation. It is also shown that there are wide ranges of compressor is an important design consideration. The influence approach Mach number, temperature, and turning angles within of upstream-blade wake segments on downstream-blade boundary which overdriven weak ODW can be stabilized without variations layers is not yet satisfactorily modeled for design purposes. Surface of total pressure loss. V.L. hot-film gages were used to sense the influence of rotor wake segments on stator-surface boundary layers at midspan in a A87-45241# low-speed, axial-flow compressor stage. It was clear that rotor COMPLEX MODAL BALANCING OF FLEXIBLE ROTORS wake segments moved along the stator-blade pressure and suction INCLUDING RESIDUAL BOW surfaces much like a turbulent spot would; the region of influence W. L. MEACHAM, P. B. TALBERT (Garrett Turbine Engine Co., of each wake segment became larger further downstream. Phoenix, AZ), H. D. NELSON (Arizona State University, Tempe), Boundary layer transition was not expected on the low-speed stator and N. K. COOPERRIDER (Failure Analysis Associates, Phoenix, blade surface till about midchord. Nevertheless, the laminar AZ) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, boundary-layer flow on the forward portion of the stator blade 23rd, San Diego, CA, June 29-July 2, 1987. 10 p. refs appeared to be turbulent when a rotor wake segment was present. (AIAA PAPER 87-1840) This periodic alternating of the stator boundary-layer flow was A balancing procedure utilizing the Complex Modal Method is observed further aft on the blade also. Author presented for linear flexible rotor dynamic systems, including the effect of residual shaft bow. The method does not require trial A87-45186# runs; however, a valid mathematical model of the system dynamics A NONINTERFERENCE BLADE VIBRATION MEASUREMENT is required to obtain the system's modal parameters, which are SYSTEM FOR GAS TURBINE ENGINES used to relate the balance corrections to measured responses. WILLIAM B. WATKINS (Pratt and Whitney, Engineering Div., West Several balancing strategies, based on extension of previous work, Palm Beach, FL) and RAY M. CHI (United Technologies Research are suggested for single-speed balancing. Two applications are Center, East Hartford, CT) AIAA, SAE, ASME, and ASEE, Joint presented: (1) a gas turbine system with computer-generated Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. response data, and (2) an operating steam turbine-generatior 6p. system. Author (Contract F33657-79-C-0730) (AIAA PAPER 87-1758) A87-45243# A noninterfering blade vibration system has been demonstrated A BIDIRECTIONAL TAPERED ROLLER THRUST BEARING FOR in tests of a gas turbine first stage fan. Conceptual design of the GAS TURBINE ENGINES system, including its theory, design of case mounted probes, and R. LENGLADE, G. KREIDER (General Motors Corp., Allison Gas data acquisition and signal processing hardware was done in a Turbine Div., Indianapolis, IN), and R. PECH (Timken Co., Canton, previous effort. The current effort involved instrumentation of an OH) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, engine fan stage with strain gages; data acquisition using 23rd, San Diego, CA, June 29-July 2, 1987. 9 p. refs shaft-mounted reference and case-mounted optical probes; (Contract F33615-84-C-2409) recording of data on a wideband tape recorder; and posttest (AIAA PAPER 87-1842) processing using off-line analysis in a facility computer and a The paper iscusses a single row, bidirectional tapered roller minicomputer-based readout system designed for near- real-time thrust bearing, which will take the full range of forward thrust readout. Results are presented in terms of true blade vibration without thrust balance and, in addition, will take thrust in the reverse

695 12 ENGINEERING direction caused by compressor surge. The higher load capacity by both the three-dimensional multistage Euler and of a tapered roller bearing offers improved reliability over a ball three-dimensional Navier-Stokes codes. The vane airfoil surface bearing. To verify this concept, a tapered roller bearing was Stanton number distributions, however, are underpredicted by both designed, manufactured, and tested at speeds up to 24,000 rpm, two- and three-dimensional boundary value analysis. V.L. at loads up to 66.7 kN in the major thrust direction, and for reverse thrust up to 8.9 kN at 20,000 rpm. Bearing reliability was tested up to 10 times the calculated L(10) fatigue life. The bearing A87-45309# performed successfully in all phases of testing and the concept XMAN A TOOL FOR AUTOMATED JET ENGINE of reverse thrust load on a high speed tapered roller bearing was OIAGNOSTICS proved. The feasibility of a tapered roller bearing on a gas turbine T. G. JELLISON, J. A. FRENSTER, N. S. PRATT, and R. L. DEHOFF engine mainshaft was demonstrated at high speed as well as (Systems Control Technology, Inc., Palo Alto, CA) AIAA, SAE, heavy load. Author ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 6 p. A87-45273# (AIAA PAPER 87-1931) A SIMPLE MODEL FOR FINITE CHEMICAL KINETICS ANALYSIS The development and operation of XMAN, a knowledge-based OF SUPERSONIC TURBULENT SHEAR LAYER COMBUSTION software tool designed for automated jet engine diagnostics, is PAUL E. DIMOTAKIS (California Institute of Technology, Pasadena) presented. XMAN is an expert interface to the Comprehensive and JEFFERY L. HALL AIAA, SAE, ASME, and ASEE, Joint Engine Management System Increment IV (CEMS IV), which makes Propulsion Conference, 23rd, San Diego, CA, June 29-July 2, 1987. it possible to automate the diagnostic procedures. The application 13 p. refs of expert diagnostics to the TF-34 engine equipped with the Turbine (Contract AF-AFOSR-83-0213) Engine Monitoring System is described. As an integrated (AIAA PAPER 87-1879) diagnostics tool, the XMAN system allows an insight into actual A simple flow/thermodynamic model is proposed to describe troubleshooting performed and the evaluation of the results. finite chemical kinetic rate combustion in a turbulent supersonic Interactive user training and a feedback loop to improve the shear layer for the purposes of assessing Damkoehler number diagnostic process are discussed. I.S. effects in such flows. Sample calculations and comparisons for the H2/NO/F2 chemical system and the H2/air system are described for a set of initial flow and thermodynamic conditions A87-45349"# Avco-Everett Research Lab., Mass. of the entrained reactants. Author EXPERIMENTAL DATA CORRELATIONS FOR THE EFFECTS OF ROTATION ON IMPINGEMENT COOLING OF TURBINE A87-45293# BLADES DEVELOPMENT OF LOW-COST TEST TECHNIQUES FOR J. C. KREATSOULAS (Avco Everett Research Laboratory, Inc., ADVANCING FILM COOLING TECHNOLOGY MA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, F. O. SOECHTING, K. K. LANDIS (Pratt and Whitney, West Palm 23rd, San Diego, CA, June 29-July 2, 1987. 11 p. Research Beach, FL), and R. DOBROWOLSKI (U.S. Navy, Naval Air supported by Teledyne CAE, Avco Everett Research Laboratory, Propulsion Center, Trenton, NJ) AIAA, SAE, ASME, and ASEE, Inc., and NAS. refs Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July (AIAA PAPER 87-2008) 2, 1987.7p. refs The effects of rotation on impingement cooling have been (AIAA PAPER 87-1913) experimentally studied under simulated gas turbine operating A program for studying advanced film hole geometries that will conditions. A large scale model of a blade is spun in vacuum. provide improved film effectiveness levels relative to those reported External heating is simulated by resistve dissipation in the thin in the literature is described. A planar wind tunnel was used to wall of the model, which is impingement cooled. The local internal conduct flow visualization studies on different film hole shapes, Nu is measured by an IR radiometric technique with high spatial followed by film effectiveness measurements. The most promising resolution. At low rotational speeds the data agree well with geometries were then tested in a two-dimensional cascade to define published measurements taken under stationary conditions. At the film effectiveness distributions, while duplicating a turbine airfoil higher speeds, a decrease in the average Nu by up to 20-30 curvature, Mach number, and acceleration characteristics. The test percent is observed. Severe gradients are generated near the techniques are assessed and typical results are presented. It was hub region. Empirical correlations, which fit the data well and render shown that smoke flow visualization is an excellent low-cost it more useful for design purposes, are presented. Measurements technique for observing film coolant-to-mainstream characteristics and correlations suggest that rotational effects are very important and that reusable liquid crystal sheets provide an accurate low-cost and can cause premature blade failure. Author technique for measuring near-hole film effectiveness contours. Cascade airfoils constructed using specially developed precision fabrication techniques provided high-quality film effectiveness A87-45350# data. I.S. FRICTION FACTORS AND HEAT TRANSFER COEFFICIENTS IN TURBULATED COOLING PASSAGES OF DIFFERENT A87-45296# ASPECT RATIOS. I - EXPERIMENTAL RESULTS AERODYNAMIC AND HEAT TRANSFER ANALYSIS OF THE M. E. TASLIM (Northeastern University, Boston, MA) and S. D. LOW ASPECT RATIO TURBINE SPRING (General Electric Co., Aircraft Engine Business Group, O. P. SHARMA (Pratt and Whitney, East Hartford, CT), P. NGUYEN, Lynn, MA) AIAA, SAE, ASME, and ASEE, Joint Propulsion R. H. NI, C. M. RHIE, J. A. WHITE et al. AIAA, SAE, ASME, Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 8 p. and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, refs June 29-July 2, 1987. 12 p. refs (AIAA PAPER 87-2009) (Contract F33615-79-C-2050) In advanced turbine airfoil cooling designs where multiple-pass (AIAA PAPER 87-1916) cooling circuits are used, a range of cooling passage aspect ratios The available two- and three-dimensional codes are used to (height/width) are encountered. The objective of this experimental estimate external heat loads and aerodynamic characteristics of a investigation was to determine the effect that increasing aspect highly loaded turbine stage in order to demonstrate state-of-the-art ratios have on friction factors and Nusselt numbers in internal methodologies in turbine design. By using data for a low aspect cooling passages with rib-roughened (turbulated) surfaces. Aspect ratio turbine, it is found that a three-dimensional multistage Euler ratios ranging from 0.5 to 3.5 were tested over a Reynolds number code gives good averall predictions for the turbine stage, yielding range of 30,000 to 190,000. Each aspect ratio was tested at good estimates of the stage pressure ratio, mass flow, and exit three different turbulator-height/hydraulic-diameter ratios and at a gas angles. The nozzle vane loading distribution is well predicted constant turbulator-height/pitch ratio of 0.10. Author

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A87-45379# A87-45450# FINITE ELEMENT ANALYSIS OF LARGE SPUR AND HELICAL NAVIER-STOKES ANALYSIS OF A VERY-HIGH-BYPASS-RATIO GEAR SYSTEMS TURBOFAN ENGINE IN REVERSE THRUST S. SUNDARARAJAN and B. YOUNG (Pratt and Whitney Canada, JEFFREY J. BROWN (Boeing Commercial Airplane Co., Seattle, Longueuil) AIAA, SAE, ASME, and ASEE, Joint Propulsion WA) AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, Conference, 23rd, San Diego, CA, June 29-July 2, 1987. 5 p. 23rd, San Diego, CA, June 29-July 2, 1987. 10 p. refs (AIAA PAPER 87-2047) (AIAA PAPER 87-2170) The application of the 3D finite element sub-structure method An algorithm based upon MacCormack's implicit line has helped to improve the accuracy of calculation of gear tooth Gauss-Seidel Navier-Stokes scheme has been modified to model contact and fillet stresses in large spur and helical gear systems. the flowfield in very-high-bypass-ratio turbofan engines under The development of a dedicated preprocessor has significantly reverse-thrust conditions. It is assumed that reverse thrust is to reduced the manual effort involved in the analysis. The be achieved through fan blade pitch changes. The physics at the methodology is explained using the example analyses of the gear fan blade is modeled using an actuator disk to simulate the fan systems in the two stages of a typical speed reduction gearbox pumping characteristics. The algorithm, including boundary used in the Pratt and Whitney Canada PWl00 turbo propeller conditions, is described, and three different flowfields are presented engines. Author as illustrations of possible results. Author

A87-45457# ON THE EVOLUTION OF PARTICLE-LADEN JET FLOWS - A THEORETICAL AND EXPERIMENTAL STUDY A. A. MOSTAFA, H. C. MONGIA (General Motors Corp., Allison Gas Turbine Div., Indianapolis, IN), V. G. MCDONNELL, and G. S. A87-45398"# General Electric Co., Cincinnati, Ohio. SAMUELSEN (California, University, Irvine) AIAA, SAE, ASME, DYNAMIC DATA ACQUISITION, REDUCTION, AND ANALYSIS and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, FOR THE IDENTIFICATION OF HIGH-SPEED COMPRESSOR June 29-July 2, 1987. 14 p. refs COMPONENT POST-STABILITY CHARACTERISTICS (AIAA PAPER 87-2181) S. D. DVORAK, W. M. HOSNY, W. G. STEENKEN (General Electric A combined experimental/analytical investigation is being Co., Aircraft Engine Business Group, Cincinnati, OH), and J. H. conducted to study the interaction of a fuel nozzle spray with a TAYLOR (General Electric Co., Schenectady, NY) AIAA, SAE, swirler stabilized flow field. As a first step, the developing regions ASME, and ASEE, Joint Propulsion Conference, 23rd, San Diego, of an unconfined axisymmetric turbulent jet with and without glass CA, June 29-July 2, 1987. 14 p. refs beads of 105 micron diameter has been addressed for two mass (Contract NAS3-2483; NAS3-24211) loading ratios, LR = 0.2 and 1.0. Benchmark quality data were (AIAA PAPER 87-2089) obtained by using a two-component phase/Doppler technique. The A compressor test was conducted in which transient data were theoretical calculations based on a stochastic Lagrangian treatment obtained for the purpose of identifying the high-speed post-stability along with a two-equation turbulence model for two-phase flows characteristics. The transient, surge-cycle nature of high-speed yield reasonable and encouraging agreement with the post-stability operation precludes the possibility of obtaining the measurements. Author characteristics in a steady-state manner, as is possible during low-speed poststability operation, which is characterized by A87-45689 quasi-steady rotating-stall behavior. Specialized compressor CONFORMAL MICROSTRIP COMMUNICATION ANTENNA instrumentation was developed and was used to obtain the R. E. MUNSON (Ball Corp., Ball Aerospace Systems Div., Boulder, necessary surge-cycle performance data, which were then digitized, CO) IN: MILCOM '86 - Military Communications Conference, filtered, and analyzed. The high-speed post-stability characteristics Monterey, CA, Oct. 5-9, 1986, Conference Record. Volume 2 . were obtained through the use of a maximum likelihood-parameter New York, Institute of Electrical and Electronics Engineers, Inc., estimation technique. The estimated characteristics were found to 1986, p. 23.3.1-23.3.4. be insensitive to the presence of measurement noise and The characteristics and performance of four types of conformal unmodelled system dynamics, but the compressor time-response microstrip antennas are described. The four antennas are: (1) single constants, which were also estimated, were more sensitive to these same disturbances. Author element antennas with broad coverage; (2) wraparound omnidirectional, missile and satellite antennas; (3) fixed beam conformal microstrip antennas; and (4) electrically scanned microstrip arrays. The advantages associated with using microstrip antennas in communication systems are discussed. Various applications for these four conformal microwave antennas are considered. I.F. A87-45405# THE DESIGN OF LOW-STRESS/HIGH PERFORMANCE A87-45876 CENTRIFUGAL IMPELLERS RADAR TECHNOLOGY 1986; SYMPOSIUM, 6TH, BREMEN, P. S. KUO, M. B. FLATHERS, and P. J. ROONEY (Avco Corp., WEST GERMANY, NOV. 4-6, 1986, REPORTS [RADARTECHNIK Avco Lycoming Textron, Stratford, CT) AIAA, SAE, ASME, and 1986; SYMPOSIUM, 6TH, BREMEN, WEST GERMANY, NOV. 4-6, ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, June 1986, VORTRAEGE] 29-July 2, 1987. 10 p. Symposium sponsored by the Deutsche Gesellschaft fuer Ortung (AIAA PAPER 87-2099) und Navigation, Senatskansle, Bremen, Messerschmitt-Boelkow- The highly swept blades employed by state-of-the-art, high Blohm GmbH, et al. Duesseldorf, Deutsche Gesellschaft fuer Or- performance centrifugal impellers tend to exhibit high localized tung und Navigation, 1986, 558 p. In German. For individual items stresses that may prove detrimental to the structural service life see A87-45877 to A87-45895. of the component; this problem is exacerbated by the higher Advances in radar instrumentation, data processing, and operating speeds and elevated temperatures of modern gas turbine applications are discussed in reviews and reports of recent work engines. Attention is presently given to an interdisciplinary process in West Germany. Topics examined include GaAs ICs for active for impeller design and analysis which recent experience has shown phased arrays, the biophysics of low-level effects, a surveillance to accomodate structural integrity requirements. Localized blade and collision-avoidance system based on standard DME, radar stresses have been translated into local shape modifications which requirements for future avionics systems, rotating-antenna SARs, improve the overall tradeoff between aerodynamic performance and a CW radar for ranging with pseudonoise PSK modulation. and component durability. O.C. Consideration is given to a statistical analysis of the ground

697 12 ENGINEERING interference background in the mm band, ranging with a pulse A87-46230# Doppler radar, wind determination from data on aircraft movement, APPLICATION OF ENGINE COMPONENT LIFE METHODOLOGY and a frequency- and polarization-agile 94-GHz pulse Doppler TO LIFE ASSESSMENT radar. T.K. N. S. SWANSSON and J. D. CYRUS (U.S. Naval Material Command, Naval Air Development Center, Warminster, PA) IN: A87-45886 International Symposium on Air Breathing Engines, 8th, Cincinnati, AN AUTOMATED RADAR-SIGNATURE MEASUREMENT SYS- OH, June 14-19, 1987, Proceedings. New York, American Institute TEM [AUTOMATISIERTES RADAR-SIGNATUR-MESSSYSTEM] of Aeronautics and Astronautics, 1987, p. 486-493. refs JUERGEN KRUSE (Messerschmitt-Boelkow-Blohm GmbH, To provide an assurance that the life of aircraft engine Bremen, West Germany) IN: Radar Technology 1986; Symposium, components will meet requirements, a simple methodology has 6th, Bremen, West Germany, Nov. 4-6, 1986, Reports. Duesseldorf, been developed for independently assessing component life and Deutsche Gesellschaft fuer Ortung und Navigation, 1986, p. predicting its sensitivity to engine upgrades, material changes, or E5.1-E5.21. In German. modifications in usage. Techniques used for life estimation are The design and operation of an automated measurement facility outlined, and examples of applications given. The relative permitting determination of radar cross sections and location and magnitude of cyclic and hot section usage is of primary significance characterization of scattering centers on aircraft models up to 4.5 in predicting specific component failures and failure modes. m in length are described and illustrated with diagrams, drawings, Predictions based on comparative usage agree with available failure data. Author graphs, and photographs. The facility comprises a 15 x 5.8 x 3.8-m measurement chamber, a rotating platform with maximum load 270 kg and elevation range from -5 to +35 deg (precision A87-46231 # 0.1 deg), a tunable broadband 2-18-GHz transmitter, a THE MIXING OF JETS UNDER SIMULATED ENGINE-LIKE phase-sensitive receiver, and control and data-processing TURBULENCE computers. The analytical techniques employed to correct for T. FREUDENBERG and D. K. HENNECKE (Darmstadt, Technische measurement errors and to resolve scattering centers both Hochschule, West Germany) IN: International Symposium on Air longitudinally and transversely (two-dimensional representation) are Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, explained and demonstrated. The facility is currently being used Proceedings . New York, American Institute of Aeronautics and to develop and evaluate stealth-type aircraft designs. T.K. Astronautics, 1987, p. 497-506. Research supported by trhe Stiftung Volkswagenwerk. refs The effect of engine-like free-stream turbulence on mixing layers A87-46198# of jets in a duct was studied using hot-wire anemometry. The INFLUENCE OF FUEL TEMPERATURE ON ATOMIZATION kinetic energy and the length-scale of turbulence were varied. For PERFORMANCE OF PRESSURE-SWIRL ATOMIZERS this purpose a new type of turbulence generator was designed X. F. WANG and A. H. LEFEBVRE (Purdue University, West where the turbulence is generated by a large number of jets issuing Lafayette, IN) IN: International Symposium on Air Breathing perpendicular into the main stream. The influence of different length Engines, 8th, Cincinnati, OH, June 14-19, 1987, Proceedings. scales could be isolated while the mean velocity distribution and New York, American Institute of Aeronautics and Astronautics, the kinetic energy distribution at the entry of the mixing chamber 1987, p. 193-199. refs were kept constant. The experiments were backed up by The influence of fuel temperature on mean drop size and calculations using the k-epsilon-model. The results show that not drop-size distribution is examined for aviation gasoline and diesel only the turbulence intensity has a strong influence on the mixing oil, using three pressure-swirl simplex nozzles. Spray characteristics process but also its spectral distribution, characterized by a length are measured over wide ranges of fuel injection pressure and scale. Thus the turbulence scales should be included in more ambient air pressure using a Malvern spray analyzer. Fuel detailed flow calculations for the design of engines. Author temperatures are varied from -20 C to +50 C. Over this range of temperature, the overall effect of an increase in fuel temperature A87-46244# is to reduce the mean drop size and broaden the distribution of DEVELOPMENT OF A LASER INTERFEROMETRIC SYSTEM drop sizes in the spray. Generally, it is found that the influence of FOR VELOCITY MEASUREMENTS INSIDE A TRANSONIC AXIAL fuel temperature on mean drop size is far more pronounced for FLOW COMPRESSOR STAGE diesel oil than for gasoline. For both fuels the beneficial effect of D. ADLER, J. KRIMERMAN, R. SASSON, and M. KLEINER higher fuel temperatures on atomization quality is sensibly (Technion - Israel Institute of Technology, Haifa) IN: International independent of ambient air pressure. Author Symposium on Air Breathing Engines, 8th

A87-46229# A87-46245# A STUDY ON THE EFFECT OF NON-DIMENSIONAL SYSTEM OPTICAL FLOW DIAGNOSTIC MEASUREMENTS IN PARAMETERS ON SQUEEZE FILM DAMPER PERFORMANCE TURBOMACHINERY USING EXPERIMENTAL DATA D. G. JONES and R. J. PARKER (Rolls-Royce, PLC, Derby, V. ARUN KUMAR, B. S. PRABHU (National Aeronautical England) IN: International Symposium on Air Breathing Engines, Laboratory, Bangalore, India), and P. A. PARANJPE (Indian Institute 8th, Cincinnati, OH, June 14-19, 1987, Proceedings . New York, of Technology, Madras, India) IN: International Symposium on American Institute of Aeronautics and Astronautics, 1987, p. Air Breathing Engines, 8th, Cincinnati, OH, June 14-19, 1987, 607-618. Research supported by the Ministry of Defence Proceedings . New York, American Institute of Aeronautics and (Procurement Executive). refs Astronautics, 1987, p. 480-485. refs Detailed flow measurements within the passages of rotating An attempt is made to formulate guidelines for the design of model fans have been made using nonintrusive laser techniques airbreathing engines' squeeze film dampers, with emphasis on of holographic flow visualization and laser transit anemometry. dimensionless shaft amplitude and transmitted force in the The complementary nature of these two techniques uses the ability bearing-damper plane. Seven important nondimensional sets of of holography to provide a diagnostic identification in three variables, taken to be invariants, have been established with respect dimensions of some of the main features of the flow and the to various significant squeeze damper parameters. Attention is ability of laser anemometry to provide quantitative measurements given to the effects of different nondimensional system parameters of the flow velocity at selected spatial locations. The paper shows on two important nondimensional response parameters. The how these optical techniques, when suitably designed and nondimensional analysis indicates that good vibration attenuation ruggedized for a hostile environment, have provided quantitative can be obtained for larger values of a newly postulated information of the intra-passage flows for a sequence of tests on nondimensional number defined in terms of external oil supply wide chord fan blades which has aided the validation of their pressure, oil viscosity, and operating speed. O.C. design intent. Author

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A87-46250# predicted analytical failure rate, is also considered. Initial field tests STRESS ANALYSIS AND OPTIMISATION OF TURBINE ROTOR in both the commercial and military user environment demonstrate BLADE SHROUDS the high reliability performance of the engine controls. R.R. R. PADMANABHAN, K. RAMACHANDRA, M. CHANDRASEKA- RAN, R. V. MADHUSOODHANAN, and B. J. RAGHUNATH (Gas A87-46797# Turbine Research Establishment, Bangalore, India) IN: Interna- AEROELASTIC DERIVATIVES AS A SENSITIVITY ANALYSIS tional Symposium on Air Breathing Engines, 8th, Cincinnati, OH, OF NONLINEAR EQUATIONS June 14-19, 1987, Proceedings. New York, American Institute of PAOLO MANTEGAZZA (Milano, Politecnico, Milan, Italy) and Aeronautics and Astronautics, 1987, p. 659-665 GIAMPIERO BINDOLINO AIAA Journal (ISSN 0001-1452), vol. Shroud design and optimization of turbine rotor-blade is quite 25, Aug. 1987, p. 1145, 1146. refs an involved and important task which influences the mechanical It is noted that it is possible to use an appropriate adjoint and aerodynamic peeformance of modern aeroengines. This paper system of linear equations to reduce the operations required for deals with some aspects of shroud-failure mechanisms involved the calculation of aeroelastic eigensensitivities to O(n) operations, in turbine rotor-blades and discusses the results obtained from with a consequent substantial gain in efficiency; this is especially photoelastic and finite-element stress analysis. Author true where a large number of parameters is involved in the design process. The approach is useful if the divergence constraint is expressed by a minimum acceptable divergence speed for A87-46361 advanced altitudes or Mach numbers. O.C. CONTRIBUTION OF LASER ANEMOMETRY TO AIRCRAFT SAFETY [APPORT DE L'ANEMOMETRIE LASER A LA N87-25496"# National Aeronautics and Space Administration. SECURITE AERIENNE] Langley Research Center, Hampton, Va. JACQUES MANDLE (Crouzet, S.A., Division Aerospatiale, Valence, TRUSS-CORE CORRUGATION FOR COMPRESSION LOADS France) L'Aeronautique et I'Astronautique (ISSN 0001-9275), Patent Application no. 122, 1987, p. 2-9. In French. refs RANDALL C. DAVIS, inventor (to NASA) and L. ROBERT The contribution of laser anemometry to aircraft safety through JACKSON, inventor (to NASA) 5 Mar. 1987 15 p its use in the calibration of aircraft wind and pressure measurements (NASA-CASE-LAR-13438-1; NAS 1.71 :LAR-13438-1; and in wind shear detection is considered. Following a discussion US-PATENT-APPL-SN-022298) Avail: NTIS HC A02/MF A01 of the principles of laser anemometry and four standard pressure CSCL 13M error calibration methods, the application of laser anemometry to A corrugated panel structure for supporting compressive loads the calibration of aircraft incidence and sideslip is discussed. is described which includes curved cap strips separated by Calibration precisions of 0.2 deg at 100 kts and 0.1 deg at 200 truss-core web segments. The truss-core web segments are formed kts are possible. Ground-based laser anemometry systems for wind from first and second flat panels with a corrugated filler shear detection are considered, and a detection range of several therebetween. The corrugated filler extends in the direction of the dozen kilometers with an intrinsic precision of the order of 3 kts compressive load. As a result, all components of the panel structure should be possible. Airborne wind shear detection systems provide have a compressive load carrying capability resulting in a high 5-10 seconds of alert prior to the onset of the phenomenon. strength-to-weight ratio when the compressive load is limiting. R.R. Application to rocket and aircraft structures is suggested. NASA

A87-46715# N87-25534# Aeronautical Research Inst. of Sweden, Stockholm. THE F-15E R&M CHALLENGE Aerodynamics Dept. FREDRIC L. ABRAMS (USAF, Logistics Operations Center, DEVELOPMENT OF A GEOMETRY HANDLING PROGRAM FOR Wright-Patterson AFB, OH) IN: 1987 Annual Reliability and THE FFA SUBSONIC HIGHER ORDER PANEL METHOD Maintainability Symposium, Philadelphia, PA, Jan. 27-29, 1987, LARS G. TYSELL Oct. 1986 43 p Sponsored by the Swedish Proceedings . New York, Institute of Electrical and Electronics Board for Technical Development Engineers, Inc., 1987, p. 253-257. (Contract FFA-AU-PROJ-1731:1; FFA-AU-PROJ-1801:1; The reliability and maintainability drivers, actions taken, and FFA-AU-PROJ-1881:1; FFA-AU-PROJ-2041:1; initiatives pursued to meet the objectives for the F-15 Dual Role FFA-AU-PROJ-2240) Fighter program are discussed. Application of the R&M 2000 to (FFA-TN-1985-48; ETN-87-99778) Avail: NTIS HC A03/MF A01 both the F-15E and the Mobile Electronic Test Set (METS) will A program that simplifies the geometry input procedure to a result in increased warfighting capability, with increased F-15E subsonic higher order panel program, for a complete aircraft is sortie generation, and increased survivability, with the F-15E described. All necessary programs were coupled together to a containing additional systems to counter threats along with system. A fast equation solver was developed. A user's manual additional suppressant foam and more robust structures. The F-15E to the whole program system is given. Pressure distributions for a has conformal fuel tanks to increase its range, thus requiring less wing-fuselage configuration test case are presented. The tanker support. Better R&M will lead to lower Life Cycle Costs, agreement between the measurement and the calculation is very and changes brought about by METS will reduce intermediate good. ESA avionics manpower requirements. R.R. N87-25536# McDonnell Aircraft Co., St. Louis, Mo. A87-46728 VlSClD/INVISClD SEPARATED FLOWS Final Report, Sep. 1983 RELIABILITY, 'BETTER THAN THE BEST' - Mar. 1986 JOHN SIECZKOS and WILLIAM G. KINDIG (General Electric Co., T. CEBECI, K. C. CHANG, R. W. CLARK, D. P. MACK, and S. M. Binghamton, NY) IN: 1987 Annual Reliability and Maintainability SCHIMKE Jul. 1986 94 p Symposium, Philadelphia, PA, Jan. 27-29, 1987, Proceedings. New (Contract F33615-83-C-3026) York, Institute of Electrical and Electronics Engineers, Inc., 1987, (AD-A179858; MDC-J3968; AFWAL-TR-86-3048) Avail: NTIS HC p. 428-432. A05/MF A01 CSCL 20D The design, testing, and production of commercial and military A method has been developed for calculating subsonic engine controls are addressed, and the successful transfer of three-dimensional flows over fighter aircraft configurations at flow technology and program structure/discipline from the flight control conditions including separation. The method employs a viscid product line to engine controls is reported. Special considerations inviscid interaction approach, with a panel method used for the in the areas of operating environment, operating hours, cycle times, inviscid analysis and a finite difference boundary layer method for and technology changes from potted modules with hard wiring to the viscous analysis. The viscid and inviscid analyses are coupled printed circuit boards with interconnecting motherboards are using an interactive technique based on inverse boundary layer discussed. Hardware complexity, including the MIL-HDK-217 theory. This approach allows efficient calculation of flows with

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large separation regions, including both leading and trailing edge N87-25584"# National Aeronautics and Space Administration. separations. The method was validated on three fighter aircraft Langley Research Center, Hampton, Va. geometries and comparisons with test data are presented. GRA AUXILIARY DATA INPUT DEVICE Patent Application H. DOUGLAS GARNER, inventor (to NASA), ANTHONY M. BUSQUETS, inventor (to NASA), THOMAS W. HOGGE, inventor N87-25538# Sandia National Labs., Albuquerque, N. Mex. (to NASA), and RUSSELL V. PARRISH, inventor (to NASA) 18 INFLUENCE OF A HEATED LEADING EDGE ON BOUNDARY Jun. 1987 15p LAYER GROWTH, STABILITY AND TRANSITION (NASA-CASE-LAR-13626-1; US-PATENT-APPL-SN-063557) D. B. LANDRUM and J. M. MACHA 1987 11 p Presented at Avail: NTIS HC A02/MF A01 CSCL 131 the 19th Fluid Dynamics, Plasma Dynamics and Laser Conference, an object of this invention is to provide in a control lever, a Honolulu, Hawaii, 8 Jun. 1987 continuous, bi-coordinate, data entry device that can be (Contract DE-AC04-76DP-00789) manipulated by an operator's hand without the necessity of (DE87-008516; SAND-86-2718C; CONF-870622-3) Avail: NTIS removing the hand from the control lever. The improved data HC A02/MF A01 entry device is provided with a handle element having a finger This paper presents the results of a combined theoretical and portion. A ball element is rotatably disposed in the finger portion experimental study of the influence of a heated leading edge on and remains subject to manipulation by a single finger of the the growth, stability, and transition of a two-dimensional boundary human hand grasping the handle element. The combination of layer. The findings are directly applicable to aircraft wings and drive shafts, roller elements, disk elements, light sources, and nacelles that use surface heating for anti-icing protection. The photodetection elements provide continuous output signals that potential effects of the non-adiabatic condition are particularly describe the magnitide and direction of the ball element in two important for laminar-flow sections where even small perturbations dimensions. The output signals can then be utilized, for example, can result in significantly degraded aerodynamic performance. The to change the heading of an aircraft. NASA results of the study give new insight to the fundamental coupling between streamwise pressure gradient and surface heat flux in laminar and transitional boundary layers. DOE

N87-25550# Aerodyne Products Corp., Billerica, Mass. N87-25604# Messerschmitt-Boelkow-Blohm G.m.b.H., Bremen PORTABLE FUEL LEAK DETECTOR Final Report, 1 JuL 1986 (West Germany). - 1 Jan, 1987 ANALYTICAL DESCRIPTION OF CRACK RESISTANCE CURVES BURTON D. FIGLER Jan. 1987 37 p FOR ALUMINUM SHEETS USED IN AIRCRAFT (Contract F33615-86-C-2652) CONSTRUCTION (AD-A180095; AFWAL-TR-87-2021) Avail: NTIS HC A03/MF VUI NGUYEN-HOANG 1986 4 p Repr. from Aluminum, v. 62, A01 CSCL 01C no. 8, 1986 p 593-595 In GERMAN; ENGLISH summary Aerodyne Products Corp. successfully met the objective of (MBB-UT-133/85; ETN-87-99964) Avail: Issuing Activity this program by the development of a device for measurement of The R-curve concept was applied to predict the load-bearing fuel leaks in aircraft. This device satisfies the two requirements: capacity and the critical damage parameters for aluminum sheet (1) monitor enclosed bays for fuel leaks, and (2) measure the fuel aircraft components. The R-curves for the alloys 2024-T3, 7075-T6, leak rate. The first application requires a rugged, reliable and and 7475-T761 are given, and the materials constants for the inexpensive device that can be mounted in aircraft bays, R-curves were determined. It was assumed that the contants C1 continuously monitoring for fuel leaks. The second application uses to C4 are valid for various sheet widths, sheet thicknesses, and the same device with a battery attachment for ease in handling crack lengths. This assumption was justified by the agreement by personnel to measure fuel leak rates. In this Phase I SBIR found between predicted and experimental values of these program, tests were performed with a breadboard spectral constants. It is therefore justified to recommend the R-curve correlation device to determine detection sensitivity and to develop concept in the presented form for the prediction of residual strength techniques for fuel leak measurements. The device determines and critical crack length. ESA the presence of fuel vapor in air by measuring the absorption of infrared radiation by the vapor. Air to be analyzed is drawn into an absorption cell. The device was calibrated with decane and can observe vapor down to 1 part per million. Fuels have the same infrared absorption band. Measurements were made of the leak rate from an aluminum sheet with a 6 mil pinhole. An air N87-26004"# General Dynamics Corp., St. Louis, Mo. COMPUTATIONAL FLUID DYNAMICS: TRANSITION TO DESIGN sampling tube was placed above the leak, drawing air through the APPLICATIONS absorption cell. GRA R. G. BRADLEY, I. C. BHATELEY, and G. A. HOWELL In NASA. Ames Research Center, Supercomputing in Aerospace p 69-76 N87-25558"# National Aeronautics and Space Administration. Mar. 1987 Langley Research Center, Hampton, Va. Avail: NTIS HC A13/MF A01 CSCL 20D MINIATURE REMOTE DEAD WEIGHT CALIBRATOR Patent The development of aerospace vehicles, over the years, was Application an evolutionary process in which engineering progress in the FRANK H. SUPPLEE, JR., inventor (to NASA) and TCHENG PING, aerospace community was based, generally, on prior experience inventor (to NASA) 30 Apr. 1987 13 p and data bases obtained through wind tunnel and flight testing. (NASA-CASE-LAR-13564-1 ; US-PATENT-APPL-SN-044180) Advances in the fundamental understanding of flow physics, wind Avail: NTIS HC A02/MP A01 CSCL 14B tunnel and flight test capability, and mathematical insights into The invention is a miniature, remote, computer-controlled dead the governing flow equations were translated into improved air weight calibrator. This device which is comprised of an interlocking vehicle design. The modern day field of Computational Fluid rod and dead weight assembly, a motorized lifting mechanism, a Dynamics (CFD) is a continuation of the growth in analytical controller, and a microcomputer, allows automatic calibration of capability and the digital mathematics needed to solve the more force transducers needed for wind tunnel operations while the rigorous form of the flow equations. Some of the technical and transducers are located within a cryogenic chamber. The operation managerial challenges that result from rapidly developing CFD of a cryogenic transonic wind tunnel requires calibration of force capabilites, some of the steps being taken by the Fort Worth transducers at cryogenic operating temperatures. The invention Division of General Dynamics to meet these challenges, and some allows remote, automatic, and sequential loading and unloading of the specific areas of application for high performance air vehicles of preselected weights. NASA are presented. Author

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N87-26007"# McDonnell-Douglas Research Labs., St. Louis, N87-26259# Deutsche Forschungs- und Versuchsanstalt fuer Mo. Flight Sciences Dept. Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). Abteilung COMPUTATIONAL FLUID DYNAMICS APPLICATIONS AT HF-Physik. MCDONNEL DOUGLAS A CONFORMAL AIRCRAFT PHASED ARRAY ANTENNA FOR R. J. HAKKINEN In NASA. Ames Research Center, AIRPLANE-SATELLITE COMMUNICATION IN THE L BAND Supercomputing in Aerospace p 109-121 Mar. 1987 GEORG SPLITT and HANS FORSTER Sep. 1986 94 p In Avail: NTIS HC A13/MF A01 CSCL 20D GERMAN; ENGLISH summary Report will also be announced Representative examples are presented of applications and as translation (ESA-1-T-1057) development of advanced Computational Fluid Dynamics (CFD) (DFVLR-FB-86-47; ISSN-0171-1342; ETN-87-99688) Avail: codes for aerodynamic design at the McDonnell Douglas NTIS HC A05/MF A01; DFVLR, Cologne, West Germany DM 34 Corporation (MDC). Transonic potential and Euler codes, A medium gain antenna was developed for direct reception of interactively coupled with boundary layer computation, and solutions the MARECS satellite. The antenna system is conformal with the of slender-layer Navier-Stokes approximation are applied to aircraft outer skin of the airplane. It was designed as a phased-array wing/body calculations. An optimization procedure using evolution system consisting of six individual elements placed in a vertical theory is described in the context of transonic wing design. Euler row. The radiation pattern can be moved in elevation, and can methods are presented for analysis of hypersonic configurations, thus be pointed towards the satellite. The halfwidth in elevation and helicopter rotors in hover and forward flight. Several of these direction is 17 deg arc, and in azimuthal direction 120 deg arc. projects were accepted for access to the Numerical Aerodynamic The measurements show a gain between 9 and 10.8 dBi, depending Simulation (NAS) facility at the NASA-Ames Research Center. on the lobe, and an efficiency of 65%. The suppression of the Author mirror reflection by the antenna diagram is between -20 and -25 dB. ESA

N87-26301 ESDU International Ltd., London (England). N87-26011"# United Technologies Research Center, East ESTIMATION OF SPILLAGE DRAG FOR A WIDE RANGE OF Hartford, Conn. Aeromechanics Research. AXlSYMMETRIC INTAKES AT M 1 COMPUTATIONAL FLUID DYNAMICS RESEARCH AT THE Apr. 1984 42 p UNITED TECHNOLOGIES RESEARCH CENI'ER REQUIRING (ESDU-84004; ISBN-0-85679-466-X; ISSN-0141-4054) Avail: SUPERCOMPUTERS ESDU ANTON J. LANDGREBE In NASA. Ames Research Center, ESDU 84004 gives a correlation of experimental data drawn Supercomputing in Aerospace p 159-174 Mar. 1987 from a large number of sources that enables spillage drag to be Avail: NTIS HC A13/MF A01 CSCL 20D estimated for a wide range of configurations at incidences up to An overview of research activities at the United Technologies 20 degrees and for mass flow ratios from zero to unity. The method Research Center (UTRC) in the area of Computational Fluid is well suited to aircraft project studies and one particular application Dynamics (CFD) is presented. The requirement and use of various is providing spillage drag at low values of intake mass flow (i.e., levels of computers, including supercomputers, for the CFD 0.4) for use with the bare-engine windmilling drag and airflow data activities is described. Examples of CFD directed toward of ESDU 81009. That combined use of those two ESDU methods applications to helicopters, turbomachinery, heat exchangers, and to estimate the drag of an inoperative turbojet or turbofan engine the National Aerospace Plane are included. Helicopter rotor codes is described in ESDU 84005. Two comprehensive practical worked for the prediction of rotor and fuselage flow fields and airloads examples illustrate the use of the correlation. ESDU were developed with emphasis on rotor wake modeling. Airflow and airload predictions and comparisons with experimental data N87-26324 ESDU International Ltd., London (England). are presented. Examples are presented of recent parabolized THE TREATMENT OF CALIBRATIONS OF TOTAL AIR Navier-Stokes and full Navier-Stokes solutions for hypersonic TEMPERATURE PROBES FOR USE IN FLIGHT-TEST ANALYSIS shock-wave/boundary layer interaction, and hydrogen/air WORK supersonic combustion. In addition, other examples of CFD efforts Jul. 1984 20 p Supersedes ESDU-Perf-RG1/5 in turbomachinery Navier-Stokes methodology and separated flow (ESDU-84007; ESDU-PERF-RG1/5; ISBN-0-85679-469-4; modeling are presented. A brief discussion of the 3-tier scientific ISSN-0141-4054) Avail: ESDU computing environment is also presented, in which the researcher ESDU 84007 is concerned with the necessary further treatment has access to workstations, mid-size computers, and of data provided by the manufacturer of the total temperature supercomputers. Author probe to ensure that results obtained using it are correct under flight conditions. The systematic errors to probe temperature recovery treated are those due to radiation, self heating and, in the case of unsteady conditions, lag. Methods are given for deriving N87-26022"# National Aeronautics and Space Administration. true values of total and ambient temperature which include Ames Research Center, Moffett Field, Calif. consideration of the effects of both aircraft and probe-generated NUMERICAL SOLUTION OF THE NAVIER-STOKES EQUATIONS shock waves. A particular feature is the treatment of the lag ABOUT THREE-DIMENSIONAL CONFIGURATIONS: A SURVEY response of a probe having two terms in its response equation. A TERRY L. HOLST In its Supercomputing in Aerospace p 281-298 worked example illustrates the evaluation of true total temperature Mar. 1987 from flight tests data recorded in supersonic flight through an Avail: NTIS HC A13/MF A01 CSCL 20D area of changing temperature. ESDU The numerical solution of the Navier-Stokes equations about three-dimensional configurations is reviewed. Formulational and N87-26399"# National Aeronautics and Space Administration. computational requirements for the various Navier-Stokes Lewis Research Center, Cleveland, Ohio. approaches are examined for typical problems including the viscous A HIGH TEMPERATURE FATIGUE AND STRUCTURES TESTING flow field solution about a complete aerospace vehicle. Recent FACILITY computed results, with experimental comparisons when available, PAUL A. BARTOLOTTA and MICHAEL A. MCGAW Aug. 1987 are presented to highlight the presentation. The future of 24 p Navier-Stokes applications in three-dimensions is seen to be rapidly (NASA-TM-100151; E-3712; NAS 1.15:100151) Avail: NTIS HC expanding across a broad front including internal and external AO2/MF A01 CSCL 20K flows, and flows across the entire speed regime from As man strives for higher levels of sophistication in air and incompressible to hypersonic applications. Prospects for the future space transportation, awareness of the need for accurate life and are described and recommendations for areas of concentrated material behavior predictions for advanced propulsion system research are indicated. Author components is heightened. Such sophistication will require complex

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operating conditions and advanced materials to meet goals in precipitation, and the correlation between precipitation type and performance, thrust-to-weight ratio, and fuel efficiency. To temperature are studied. The need for improvement in observing accomplish these goals will require that components be designed LWC and for a numerical output model in order to improve icing using a high percentage of the material's ultimate capabilities. forecasts is discussed. I.F. This serves only to complicate matters dealing with life and material behavior predictions. An essential component of material behavior A87-45892 model development is the underlying experimentation which must WIND DETERMINATION FROM AIRCRAFT-MOVEMENT DATA occur to identify phenomena. To support experimentation, the [WlNDBERECHNUNG AUS DATEN VON FLUGZEUG- NASA Lewis Research Center's High Temperature Fatigue and BEWEGUNGEN] Structures Laboratory has been expanded significantly. Several H. J. HERMANNS (Eurocontrol, Maastricht, Netherlands) IN: new materials testing systems have been added, as well as an Radar Technology 1986; Symposium, 6th, Bremen, West Germany, extensive computer system. The intent of this paper is to present Nov. 4-6, 1986, Reports. Duesseldorf, Deutsche Gesellschaft fuer an overview of the laboratory, and to discuss specific aspects of Ortung und Navigation, 1986, p. G3.1-G3.55. In German. the test systems. A limited discussion of computer capabilities will The importance of accurate wind data for ATC is discussed; also be presented. Author the inadequacy of wind data based on global forecasts, airport measurements, and pilot reports is indicated; and techniques for N87-26837 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn estimating the prevailing upper winds by comparing the true (West Germany). Unternehmensgruppe Hubschrauber und airspeeds (TASs) of aircraft on particular routes with their Flugzeuge. radar-determined ground speeds are proposed and demonstrated. DEVELOPMENT OF NOVEL BEARINGLESS ROTOR SYSTEMS The theoretical basis of the TAS-based method (Ehrmanntraut [ENTWICKLUNG NEUARTIGER LAGERLOSER ROTORSYS- and Hermanns, 1985) and the steps required for its practical TEME] implementation are explained in detail and illustrated with extensive HENNING STREHLOW and HUBERT FROMMLET /n its Research diagrams, maps, flow charts, and graphs. T.K. and Development. Technical-Scientific Publications 1986 p 147-166 1986 In GERMAN Presented at the 4th BMFT-Statusseminar, A87-45962 Munich, West Germany, 28-30 Apr. 1986 ANALYSIS OF A MICROBURST IN THE FACE METEOROLOGI- (MBB-UD-471/86) Avail: Issuing Activity CAL MESONETWORK IN SOUTHERN FLORIDA An efficient bearingless main rotor system for a light FERNANDO CARACENA (NOAA, Boulder, CO) and MICHAEL W. multipurpose helicopter was developed. It concerns a further MAIER (Lightning Location and Protection, Inc., Tucson, AZ) development of the Boelkow fiber composite jointless rotor system. Monthly Weather Review (ISSN 0027-0644), vol. 115, May 1987, Two bearingless rotor systems with different systems design and p. 969-985. refs blade-angle control were tested on a rotor teststand and on the As a part of a study to produce a basis for forecasting all BO-105 helicopter. Experimental and theoretical investigation, microbursts, the multiscale environmental conditions which resulted including components testing were carried out. The test results in a wet microburst that occurred in the Florida Area Cumulus were successful, and can be used for the definition of the final Experiment meteorological mesonetwork at 1747 UTC on July 1, prototypes, especially with respect to the aerodynamic and 1975 were investigated. Several features were found: (1) a dry structural systems optimization. An optimized blade form and profile layer above 500 mb overlying a nearly moist adiabatic lower are proposed. Profile wind tunnel measurements and power tropospheric layer, (2) a short-wave trough approaching the area measurements on the rotor teststand show a 6% power increase from the north-northeast along the western side of a synoptic-scale compared to the BO-105 series blade. ESA trough, (3) an increased shear in the lower troposphere, and (4) a strong boundary-layer forcing, first by a lake breeze front off the Lake Okeechobee, then by convective gust fronts. The site of the 13 microburst itself was in the portion of the storm where a new cell was initiated by a strong gust front in the area where rain was still falling from an older, dissipating cell. I.S. GEOSClENCES A87-46481 Includes geosciences (general); earth resources; energy production LARGE-SCALE DISTRIBUTION OF PEROXYACETYLNITRATE and conversion; environment pollution; geophysics; meteorology RESULTS FROM THE STRATOZ III FLIGHTS and climatology; and oceanography. J. RUDOLPH, B. VIERKORN-RUDOLPH, and F. X. MEIXNER (Kernforschungsanlage Juelich, GmbH, Institut fuer Chemie, West Germany) Journal of Geophysical Research (ISSN 0148-0227), A87-44702 vol. 92, June 20, 1987, p. 6653-6661. BMFT-supported research. WHERE AND WHEN HELICOPTER ICING OCCURS refs DAVID A. FORRESTER (Meteorological Office, Bracknell, England) IN: Helicopter Rotor Icing Symposium, London, England, A87-46757# Jan. 14, 1986, Proceedings. London, Royal Aeronautical Society, STATISTICAL DISTRIBUTION OF EXTREME ATMOSPHERIC 1986, p. 1-23. TURBULENCES [DISTRIBUTION STATISTIQUE DES TURBU- The use of temperature and liquid water content (LWC) data LENCES ATMOSPHERIQUES EXTREMES] to accurately forecast icing conditions is considered. Hazardous G. COUPRY (ONERA, Chatillon-sous-Bagneux, France) (Canadian conditions are created by subzero temperatures, snow, and freezing Congress of Applied Mechanics, 11th, University of Alberta, rain. Estimating the adiabatic values of LWC for various cloud Edmonton, Canada, May 31-June 4, 1987) ONERA, TP, no. types, and the properties of clouds are examined. It is observed 1987-56, 1987, 3 p. In French. refs that there is no significant icing near the cloud base; precipitating (ONERA, TP NO. 1987-56) clouds have large LWC and often exceed the adiabatic values; Data from close to one million hours of flight obtained over a and cumulus, stratocumulus, low frontal clouds, and deep mature five year period, including 600 events corresponding to high fog approach the adiabatic limit. The effect of droplet size turbulence, have been analyzed to study the variations of loading distribution on icing and the relation between air mass origin and factors due to turbulence with an amplitude exceeding 0.5 g and LWC are investigated. Seasonal and annual vertical frequency cloud the corrresponding flight parameters. The Hall formula is used to profiles; the frequency of subzero clouds, clouds at 900 mb, and relate the acceleration data bank to the turbulence data bank. of encountering freezing rain; 0 C isotherm levels; and the ratio Results verify that the static distribution of these strong turbulences of convective to layer cloud are analyzed using flight is well represented by Gumbers extreme value theory, making reconnaissance data. The frequencies of various types of possible extrapolation of the data to exceptional events. R.R.

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N87-25268"#FederalAviationAdministration,Washington, D.C. analysis grid and how it was constructed. What the user actually CASE HISTORY OF FAA/SRI WIND SHEAR MODELS gets is discussed, followed by a discussion of the expected errors HERBERT SCHLICKENMAIER /n NASA. Langley Research Center in the three orthogonal wind components. Finally, a discussion is Wind Shear/Turbulence Inputs to Flight Simulation and Systems presented of why JAWS data are significant. Author Certification p 3-10 Jul. 1987 Avail: NTIS HC A12/MF A01 CSCL 04B N87-25272"# National Center for Atmospheric Research, Boulder, In order to understand the development of the FAA/SRI wind Colo. JAWS Project. fields, it is important to understand the operating philosophy of STATUS OF THE JAWS PROGRAM the FAA's Wind Shear Program Office. The goal of the office was JOHN MCCARTHY /n NASA. Langley Research Center Wind to ensure an integrated solution to the wind shear problem which Shear/Turbulence Inputs to Flight Simulation and Systems addressed three area: ground based equipment and coordination; Certification p 43-47 Jul. 1987 airborne systems and procedures; and weather prediction. This Avail: NTIS HC A12/MF A01 CSCL 04B triply addressed goal was central to the development of the wind Preliminary data description of the August 5, 1982, microburst fields. The primary user of the wind shear modeling during the case is available. Its use in simulation of microburst is discussed, FAA's program was airborne simulation. The project requirement excluding the turbulence part, since it is not available. Author was to use wind shear models that resulted from accidents so that effective procedures and/or equipment could be found for N87-25274"# National Aeronautics and Space Administration. hazardous wind shear encounters. The wind shear model Langley Research Center, Hampton, Va. development is discussed in detail. Author WIND SHEAR AND TURBULENCE SIMULATION ROLAND L. BOWLES In its Wind Shear/Turbulence Inputs to N87-25269"# Federal Aviation Administration, Washington, D.C. Flight Simulation and Systems Certification p 67-95 Jul. 1987 Office of Flight Operations. Avail: NTIS HC A12/MF A01 CSCL 04B HISTORY OF WIND SHEAR TURBULENCE MODELS The aviation community is increasing its reliance on flight LOU CUSIMANO /n NASA. Langley Research Center Wind simulators. This is true both in pilot training and in research and Shear/Turbulence Inputs to Flight Simulation and Systems development. In moving research concepts through the Certification p 11-12 Jul. 1987 development pipeline, there is a sequence of events which take Avail: NTIS HC A12/MF A01 CSCL 04B place: analysis, ground based simulation, inflight simulation, and The Office of Flight Operations, Flight Technical Programs Div., flight testing. Increasing fidelity as progress toward the flight testing at the FAA Headquarters, interfaces with industry, R&D arena is accompanied by increasing cost. The question that seems communities and air carriers during the introduction of new types to be posed in relation to the meteorological aspects of flight of equipment into operational services. A brief highlight of the simulation is, How much fidelity is enough and can it be quantified. need which FAA operations sees for new wind shear and turbulence As a part of the Langley Simulation Technology Program, there data sets from the viewpoint of equipment certification and are three principal areas of focus, one being improved simulation simulation is presented. Author of weather hazards. A close liaison with the JAWS project was established because of the Langley Simulation Technology interests N87-25270"# National Center for Atmospheric Research, Boulder, regarding reliable simulation of severe convective weather Colo. JAWS Project. phenomena and their impact on aviation systems. Simulation offers INTRODUCTION TO THE JAWS PROGRAM the only feasible approach for examining the utility of new JOHN MCCARTHY In NASA. Langley Research Center Wind technology and new procedures for coping with severe convective Shear/Turbulence Inputs to Flight Simulation and Systems weather phenomena such as wind shear. These simulation Certification p 13-27 JuL 1987 concepts are discussed in detail. Author Avail: NTIS HC A12/MF A01 CSCL 04B The JAWS Project is the Joint Airport Weather Studies project N87-25277"# FWG Associates, Inc., Tullahoma, Tenn. conceived in 1980 jointly between the National Center for TURBULENCE MODELS Atmospheric Research and the Univ. of Chicago. The objectives WALTER FROST In NASA. Langley Research Center Wind of the program are threefold: (1) Basic scientific characterization Shear/Turbulence Inputs to Flight Simulation and Systems of the microbursts and the statistics of microbursts occurrence; Certification p 125-151 JuL 1987 (2) Detection and warning, using the Low Level Wind Shear Alert Avail: NTIS HC A12/MF A01 CSCL 04B System (LLWSAS) operation and performance; and (3) Doppler The subject of modeling turbulence for use with the JAWS radar and airborne systems. These goals and the operation of the wind shear data sets is addressed. The present FAA AC 120-41 JAWS system in general are discussed in detail. Author wind shear models are quasisteady wind models. FAA recommends superimposing upon these winds a Dryden spectrum model of N87-25271"# National Center for Atmospheric Research, Boulder, turbulence. For the JAWS data, it must be decided whether this Colo. Joint Airport Weather Studies Project. approach is adequate or whether turbulence must be analyzed JAWS MULTIPLE DOPPLER DERIVED WINDS and modeled differently. This question is discussed in detail. KIMBERLY L. ELMORE In NASA. Langley Research Center Author Wind Shear/Turbulence Inputs to Flight Simulation and Systems Certification p 29-42 Jul. 1987 N87-25621"# Ohio State Univ., Columbus. Avail: NTIS HC A12/MF A01 CSCL 04B WIND TUNNEL EVALUATION OF A TRUNCATED NACA 64-621 An elementary working knowledge is given of the advantages AIRFOIL FOR WIND TURBINE APPLICATIONS Final Report and limitations of the multiple Doppler radar analyses that have S. P. LAW and G. M. GREGOREK Jul. 1987 37 p recently become available from the Joint Airport Weather Studies (Contract NAG3-330) (JAWS) project. What Doppler radar is and what it does is (NASA-CR-180803; DOE/NASA/0330-2; NAS 1.26:180803) addressed and the way Doppler radars were used in the JAWS Avail: NTIS HC A03/MF A01 CSCL 10A project to gather wind shear data is described. The working An experimental program to measure the aerodynamic definition of wind shear used is winds that affect aircraft flight performance of a NACA 64-621 airfoil with a truncated trailing over a span of 15 to 45 seconds and turbulence is defined as air edge for wind turbine applications has been conducted in the motion that cause abrupt aircraft motions. The JAWS data current Ohio State University Aeronautical and Astronautical Research available contain no turbulence data. The concept of multiple Laboratory 6 in. by 21 in. pressurized wind tunnel. The blunted or Doppler analysis and the geometry of how it works are described, trailing edge truncated (TET) airfoil has an advantage over similar followed by an explanation of how data gathered in radar space trailing edge airfoils because it is able to streamline a larger spar are interpolated to a common Cartesian coordinate system and structure, while also providing aerodynamic properties that are quite the limitations involved. A discussion is also presented of the good. Surface pressures were measured and integrated to

703 13 GEOSCIENCES

determine the lift, pressure drag, and moment coefficients over very accurate results after only one iteration. Indeed, convergence angles of attack ranging from -14 to +90 deg at Mach 0.2 and is shown to be significantly faster than in the standard subspace Reynolds numbers of 1,000,000 and 600,000. Results are iteration method. Author compared to the NACA 0025, 0030, and 0035 thick airfoils with sharp trailing edges. Comparison shows that the 30 percent thick A87-44241 NACA 64-621-TET airfoil has higher maximum lift, higher lift curve DESIGN OF AN AUTOMATED INFORMATION-PROCESSING slope, lower drag at higher lift coefficients, and higher chordwise SYSTEM [ENTWURF EINES AUTOMATISlERTEN INFORMA- force coefficient than similar thick airfoils with sharp trailing TIONSVERARBEITUNGSSYSTEMS] edges. Author MANFRED SCHUELER (Interflug Gesellschaft fuer Internationalen Flugverkehr mbH, Berlin, East Germany) Technisch-oekonomische N87-26476# Deutsche Forschungs- und Versuchsanstalt fuer Information der zivilen Luftfahrt (ISSN 0232-5012), vol. 23, no. 2, Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). Abteilung 1987, p. 59-62. In German. Wolkenphysik. The design concept of the information-processing system EXPERIENCES WITH HOT-WIRE INSTRUMENTS FOR THE developed for the aircraft-maintenance department of Interflug is MEASUREMENT OF THE LIQUID WATER CONTENT IN outlined, and the software for reliability analysis (RA) is described CLOUDS in detail, summarizing selected chapters of the author's dissertation HANS-EBERHARD HOFFMANN, JOHANN DEMMEL, and HEINZ (1985). The overall system is designed to optimize the way in LOEBEL Aug. 1986 47 p In GERMAN; ENGLISH summary which the maintenance capacity of the department is applied to (DFVLR-MITT-86; ISSN-0176-7739; ETN-87-99678) Avail: NTIS meet the demand for flight-ready aircraft. A functional model of HC A03/MF A01; DFVLR, Cologne, West Germany DM 16.50 department operations is broken down into objects and attributes Experiences with hot-wire instruments obtained in special which are used to divide the system into task complexes and calibrating flight, in research on icing, and in wind tunnel construct the appropriate data bases. The programs and calibrations, are discussed. The results of airborne measurement subprograms of the menu-based RA software framework, written of the liquid water content by the hot-wire instruments in BASIC, are listed and briefly characterized. Routine use of a Johnson-Williams (J-W) and Csiro-King (C-K) are in very good PC implementation of the RA program began in January 1987. T.K. agreement. This is valid for a liquid water content between 0.04 and 0.46 g/cum, and after a perfect calibration in dry air and an elimination of systematic errors. The values for dry air of the J-W A87-44712 instrument are not or very little affected by changes of flight velocity, DESIGN OF MOTION SIMULATION SOFTWARE WITH DIGITAL altitude and temperature; the values of the C-K instrument are FILTERING TECHNIQUES strongly affected. Radio signals have a large influence on the C-K R. A. R. ALMEIDA (ABC Teleinformatica, Brazil) IN: Advances in signals. Atmospheric turbulence and banking in flight cause output flight simulation - visual and motion systems; Proceedings of the signals similar to those due to the liquid water content. For the International Conference, London, England, Apr. 29-May 1, 1986. C-K instrument, the transfer of wind tunnel calibration data to London, Royal Aeronautical Society, 1986, p. 47-63. flight measurements is not possible with sufficient accuracy. The application of digital filtering techniques to the design of ESA motion simulation software for flight simulators is studied in this work. Some design criteria for three types of filters, used in classical washout schemes, are developed, taking into account the 15 performance specifications of the motion system and the acceleration envelope of the simulated aircraft. The utilization of the methodology is illustrated with the design of three filters, whose MATHEMATICAL AND COMPUTER SCIENCES responses simulated in a digital computer are presented. Author

Includes mathematical and computer sciences (general); computer A87-44713 operations and hardware; computer programming and software; MOTION SOFTWARE FOR A RESEARCH FLIGHT SIMULATOR computer systems; cybernetics; numerical analysis; statistics and B. N. TOMLINSON (Royal Aircraft Establishment, Farnborough, probability; systems analysis; and theoretical mathematics. England) IN: Advances in flight simulation - visual and motion systems; Proceedings of the International Conference, London, England, Apr. 29-May 1, 1986. London, Royal Aeronautical Society, A87-43388# 1986, p. 64-80. refs COMPONENT MODE ITERATION FOR FREQUENCY The motion software requirements for a flight simulator are CALCULATIONS discussed. The role of the research simulator at RAE, Bedford, JEFFREY K. BENNIGHOF (Texas, University, Austin) AIAA and its motion system are described. The motion software is a Journal (ISSN 0001-1452), vol. 25, July 1987, p. 996-1002. refs suite of complex computer programs which transform aircraft (AIAA PAPER 86-1023) response variables into commands to the motion hardware. The This paper presents component mode iteration, a new method software must (1) generate primary cue demands, (2) coordinate for carrying out a form of subspace iteration on the substructure cues, (3) produce special effects, (4) compute and transmit drive level, for structures composed of substructures. In component signals, and (5) monitor motion activity. The designing of the motion mode iteration, substructure displacement is in terms of 'component software to allow for alternative cue algorithms and versatility, modes' with the interface displacements as coefficients. and software packages for modeling and analyzing the data are Component modes are chosen such that exact compatibility is examined. I.F. assured throughout the structure. The reduced structure eigenvalue problem is assembled and solved for lower mode approximations. A87-45771" National Aeronautics and Space Administration. The resulting estimates of lower mode interface motion are used Langley Research Center, Hampton, Va. to refine the component modes by approximating the dynamic ANALYSIS OF TYPICAL FAULT-TOLERANT ARCHITECTURES response of substructures to interface motion with a vector iteration USING HARP process. For this step, the substructures are independent and SALVATORE J. BAVUSO (NASA, Langley Research Center, can be processed in parallel. Reassembly and solution of the Hampton, VA), JOANNE BECHTA DUGAN, KISHOR S. TRIVEDI, reduced structure yields improved lower mode estimates. Further ELIZABETH M. ROTHMANN, and W. EARL SMITH (Duke iterations of refinement and reassembly are performed until University, Durham, NC) IEEE Transactions on Reliability (ISSN convergence takes place. The initial component modes are 0018-9529), vol. R-36, June 1987, p. 176-185. refs generated automatically and at negligible expense and numerical Difficulties encountered in the modeling of fault-tolerant systems examples show that convergence with these is excellent, yielding are discussed. The Hybrid Automated Reliability Predictor (HARP)

704 15 MATHEMATICAL AND COMPUTER SCIENCES approachto modelingfault-tolerantsystemsisdescribed.The denominator correction terms. Analysis of the simulation runs has HARPiswrittenin FORTRAN,consistsofnearly30,000linesof shown that this dual control solution applied to a multi-input codesandcomments,andisbasedonbehavioraldecomposition. multi-output model improves over the cautious controller. The key Usingthebehavioraldecomposition,thedependabilitymodelis improvement is in the avoiding of situations like turnoff and slow dividedintofault-occurrence/repair and fault/error-handling convergences, typical of the cautious solution. Author models; the characteristics and combining of these two models are examined. Examples in which the HARP is applied to the N87-25806"# Information and Control Systems, Inc., Hampton, modeling of some typical fault-tolerant systems, including a Va. local-area network, two fault-tolerant computer systems, and a A COMBINED STOCHASTIC FEEDFORWARD AND FEEDBACK flight control system, are presented. I.F. CONTROL DESIGN METHODOLOGY WITH APPLICATION TO AUTOLAND DESIGN Final Report A87-46365 NESIM HALYO Washington NASA Jul. 1987 130 p PROJECT FOR AN INTELLIGENT SYSTEM FOR ON-LINE (Contract NAS1-16158) TROUBLE SHOOTING [UN PROJET DE SYSTEME (NASA-CR-4078; NAS 1.26:4078; FR-687102) Avail: NTIS HE; 'INTELLIGENT' POUR L'AIDE AU DEPANNAGE EN LIGNE] A07/MF A01 E;SE;L09B P. CHANET and J.-P. FOURNIER (Aerospatiale, Toulouse, A combined stochastic feedforward and feedback control France) L'Aeronautique et I'Astronautique (ISSN 0001-9275), design methodology was developed. The objective of the no. 122, 1987, p. 58-61. In French. feedforward control law is to track the commanded trajectory, The application of onboard artificial intelligence systems for whereas the feedback control law tries to maintain the plant state trouble shooting on commercial aircraft is considered. An ideal near the desired trajectory in the presence of disturbances and system should provide 'intelligent' reports, diagnostic information, uncertainties about the plant. The feedforward control law design and action proposals. Constraints imposed on the dialogue between is formulated as a stochastic optimization problem and is embedded the technician and the system are discussed. The manner of into the stochastic output feedback problem where the plant response of the system should be geared to the particular changing contains unstable and uncontrollable modes. An algorithm to situation of the aircraft, and the intelligent system should provide compute the optimal feedforward is developed. In this approach, a level of information and a dialogue strategy commensurate with the use of error integral feedback, dynamic compensation, control the needs of the technician. The possibilities of communication in rate command structures are an integral part of the methodology. natural language and via graphics are also discussed. R.R. An incremental implementation is recommended. Results on the eigenvalues of the implemented versus designed control laws are N87-25771"# National Aeronautics and Space Administration. presented. The stochastic feedforward/feedback control Langley Research Center, Hampton, Va. methodology is used to design a digital automatic landing system SURVEY OF CURRENTLY AVAILABLE HIGH-RESOLUTION for the ATOPS Research Vehicle, a Boeing 737-100 aircraft. The RASTER GRAPHICS SYSTEMS system control modes include Iocalizer and glideslope capture and DENISE R. JONES Jul. 1987 20 p track, and flare to touchdown. Results of a detailed nonlinear (NASA-TM-89139; L-16294; NAS 1.15:89139) Avail: NTIS HE; simulation of the digital control laws, actuator systems, and aircraft A02/MF A01 E;SE;L 09B aerodynamics are presented. Author Presented are data obtained on high-resolution raster graphics engines currently available on the market. The data were obtained N87-25807"# Purdue Univ., West Lafayette, Ind. School of through survey responses received from various vendors and also Aeronautics and Astronautics. from product literature. The questionnaire developed for this survey OPTIMAL COOPERATIVE CONTROL SYNTHESIS OF ACTIVE was basically a list of characteristics desired in a high performance DISPLAYS Final Contractor Report color raster graphics system which could perform real-time aircraft SAN JAY GARY and DAVID K. SE;HMIDT Washington NASA simulations. Several vendors responded to the survey, with most Jun. 1987 169 p reporting on their most advanced high-performance, high-resolution (Contract NAG2-228) raster graphics engine. Author (NASA-CR-4058; H-1378; NAS 1.26:4058) Avail: NTIS HC A08/MF A01 E;SE;L 09B N87-25786# Messerschmitt-Boelkow-Blohm G.m.b.H., Hamburg A technique is developed that is intended to provide a (West Germany). Transport Aircraft Div. systematic approach to synthesizing display augmentation for AUTOMATED SYSTEMS FOR THE MANUFACTURE OF AIRBUS optimal manual control in complex, closed-loop tasks. A cooperative VERTICAL STABILIZERS control synthesis technique, previously developed to design RUDOLF BERFRANZ 1986 6 p Presented at the 15th pilot-optimal control augmentation for the plant, is extended to International Council of the Aeronautical Sciences (IE;AS) Congress, incorporate the simultaneous design of performance enhancing London, England, 7-12 Sep. 1986 displays. The technique utilizes an optimal control model of the (MBB-UT-17-86; ETN-87-99960) Avail: Issuing Activity man in the loop. It is applied to the design of a quickening control A full series of Airbus vertical stabilizers with spar boxes in law for a display and a simple K/(s squared) plant, and then to E;FRP was produced using a module based production process, an F-15 type aircraft in a multichannel task. Utilizing the closed-loop intended to become fully automatic. With full mechanization and modeling and analysis procedures, the results from the display automation, production costs are expected to be similar to those design algorithm are evaluated and an analytical validation is for a comparable all-metal structure. ESA performed. Experimental validation is recommended for future efforts. Author N87-25804"# Univ., Storrs. Dept. of Electrical and Systems Engineering. N87-26006"# Rockwell International Science Center, Thousand DUAL ADAPTIVE CONTROL: DESIGN PRINCIPLES AND Oaks, Calif. APPLICATIONS DEVELOPMENT AND APPLICATION OF UNIFIED ALGORITHMS PURUSO'I-I'AM MOOKERJEE, YAAKOV BARSHALOM, and JOHN FOR PROBLEMS IN COMPUTATIONAL SCIENCE A. MOLUSIS Jun. 1987 118 p VIJAYA SHANKAR and SUKUMAR CHAKRAVARTHY In NASA. (Contract NAG2-318) Ames Research Center, Supercomputing in Aerospace p 87-107 (NASA-CR-181050; NAS 1.26:181050) Avail: NTIS HC A06/MF Mar. 1987 A01 E;SCL 09B Avail: NTIS HE; A13/MF A01 CSE;L 09B An adaptive dual control solution was developed for an ARMA A framework is presented for developing computationally unified MIMO system. This solution captures the dual effect by performing numerical algorithms for solving nonlinear equations that arise in a second order Taylor series expansion of the expected future modeling various problems in mathematical physics. The concept cost. It modifies the cautious solution by numerator and of computational unification is an attempt to encompass efficient

7O5 15 MATHEMATICAL AND COMPUTER SCIENCES

solution procedures for computing various nonlinear phenomena to a multiple-body configuration, a wind/body/tail configuration, that may occur in a given problem. For example, in Computational and an estimate of wind tunnel wall interference are described. Fluid Dynamics (CFD), a unified algorithm will be one that allows Applications to viscous flows include a 3-D cavity and another for solutions to subsonic (elliptic), transonic (mixed multi-body configuration. A variety of grid generators is used, and elliptic-hyperbolic), and supersonic (hyperbolic) flows for both several embedding strategies are described. Author steady and unsteady problems. The objectives are: development of superior unified algorithms emphasizing accuracy and efficiency aspects; development of codes based on selected algorithms leading to validation; application of mature codes to realistic problems; and extension/application of CFD-based algorithms to problems in other areas of mathematical physics. The ultimate objective is to achieve integration of multidisciplinary technologies to enhance synergism in the design process through computational N87-26023"# National Aeronautics and Space Administration. simulation. Specific unified algorithms for a hierarchy of gas Ames Research Center, Moffett Field, Calif. dynamics equations and their applications to two other areas: COMPUTATIONAL CHEMISTRY electromagnetic scattering, and laser-materials interaction accounting for melting. Author J. O. ARNOLD In its Supercomputing in Aerospace p 299-311 Mar. 1987 Avail: NTIS HC A13/MF A01 CSCL 09B N87-26008"# Northrop Corp., Hawthorne, Calif. Aircraft Div. APPLICATION OF COMPUTATIONAL PHYSICS WITHIN With the advent of supercomputers, modern computational NORTHROP chemistry algorithms and codes, a powerful tool was created to help fill NASA's continuing need for information on the properties M. W. GEORGE, R. T. LING, J. F. MANGUS, and W. T. of matter in hostile or unusual environments. Computational THOMPKINS (Northrop Research and Technology Center, Palos resources provided under the National Aerodynamics Simulator Verdes Peninsula, Calif.) In NASA. Ames Research Center, (NAS) program were a cornerstone for recent advancements in Supercomputing in Aerospace p 125-137 Mar. 1987 Avail: NTIS HC A13/MF A01 CSCL 09B this field. Properties of gases, materials, and their interactions can be determined from solutions of the governing equations. In An overview of Northrop programs in computational physics is the case of gases, for example, radiative transition probabilites presented. These programs depend on access to today's supercomputers, such as the Numerical Aerodynamical Simulator per particle, bond-dissociation energies, and rates of simple chemical reactions can be determined computationally as reliably (NAS), and future growth on the continuing evolution of computational engines. Descriptions here are concentrated on the as from experiment. The data are proving to be quite valuable in providing inputs to real-gas flow simulation codes used to compute following areas: computational fluid dynamics (CFD), computational aerothermodynamic loads on NASA's aeroassist orbital transfer electromagnetics (CEM), computer architectures, and expert vehicles and a host of problems related to the National Aerospace systems. Current efforts and future directions in these areas are Plane Program. Although more approximate, similar solutions can presented. The impact of advances in the CFD area is described, be obtained for ensembles of atoms simulating small particles of and parallels are drawn to analagous developments in CEM. The materials with and without the presence of gases. Computational relationship between advances in these areas and the development chemistry has application in studying catalysis, properties of of advances (parallel) architectures and expert systems is also polymers, all of interest to various NASA missions, including those presented. Author previously mentioned. In addition to discussing these applications of computational chemistry within NASA, the governing equations N87-26010"# General Electric Co., Cincinnati, Ohio. and the need for supercomputers for their solution is outlined. DESIGN APPLICATIONS FOR SUPERCOMPUTERS Author C. J. STUDERUS In NASA. Ames Research Center, Supercomputing in Aerospace p 149-158 Mar. 1987 Avail: NTIS HC A13/MF A01 CSCL 09B The complexity of codes for solutions of real aerodynamic problems has progressed from simple two-dimensional models to three-dimensional inviscid and viscous models. As the algorithms used in the codes increased in accuracy, speed and robustness, the codes were steadily incorporated into standard design processes. The highly sophisticated codes, which provide solutions N87-26523# Messerschmitt-Boelkow-Blohm G.m.b.H., Bremen to the truly complex flows, require computers with large memory (West Germany). and high computational speed. The advent of high-speed INDUSTRIAL APPLICATION OF COMPUTER AIDED supercomputers, such that the solutions of these complex flows STRUCTURAL OPTIMIZATION IN AIRCRAFT CONSTRUCTION become more practical, permits the introduction of the codes into [INDUSTRIELLER EINSATZ DER RECHNERGESTUETZTEN the design system at an earlier stage. The results of several codes STRUKTUROPTIMIERUNG IM FLUGZEUGBAU] which either were already introduced into the design process or HEINRICH WELLEN and KLAUS HERTEL 1986 11 p In are rapidly in the process of becoming so, are presented. The GERMAN Presented at the DGLR-Jahrestagung, Munich, West codes fall into the area of turbomachinery aerodynamics and Germany, 8-10 Oct. 1986 hypersonic propulsion. In the former category, results are presented (MBB-UT-273/86; DGLR-86-167; ETN-87-99968) Avail: Issuing for three-dimensional inviscid and viscous flows through nozzle Activity and unducted fan bladerows. In the latter category, results are The software package STARS was used for computer aided presented for two-dimensional inviscid and viscous flows for structural optimization with a view to a weight-optimized design of hypersonic vehicle forebodies and engine inlets. Author components with a minimum of time and cost effort. The iterative process of computer aided structural optimization of aircraft N87-26021"# Calspan Field Services, Inc., Arnold AFS, Tenn. components is outlined. The industrial use of STARS is explained EXPERIENCE WITH 3-D COMPOSITE GRIDS by examples of the stress, stiffness, and frequency optimization J. A. BENEK, T. L. DONEGAN, and N. E. SUHS In NASA. of components made of metal and composites and of a given Ames Research Center, Supercomputing in Aerospace p 271-277 geometry. The results show that large and complex components Mar. 1987 can be weight optimized, that the development costs can be Avail: NTIS HC A13/MF A01 CSCL 09B reduced, and that the optimization computer costs per iteration Experience with the three-dimensional (3-D), chimera grid step are one to three times higher than those of a statistical embedding scheme isdescribed. Applications of the inviscid version analysis. ESA

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N87-26831Messerschmitt-Boelkow-BlohmG.m.b.H., Ottobrunn accurate potential energy curves described by a set of discrete (West Germany). Unternehmensgruppe Hubschrauber und data points for a broad range of scattering conditions. This code Fleugzeuge. is based upon semiclassical approximations that properly account USE OF ARTIFICIAL INTELLIGENCE METHODS [EINSATZ VON for quantum mechanical behavior such as tunneling effects near METHODEN DER ARTIFICIAL INTELLIGENCE] a barrier maximum, resonance charge exchange, and nuclear KLAUS HOLLA In its Research and Development. symmetry effects. Transport collision integrals were determined Technical-Scientific Publications 1986 p 63-66 1986 In for N-N, O-O, N(+)-N, and O(+)-O interactions from complete GERMAN Presented at the DGLR-Jahrstagung 1986, Munich, sets of accurate potential functions derived from combined West Germany, 8-10 Oct. 1986 Original language document experimental and ab initio structure calculations. For the O-O case, announced in IAA as A87-36753 this includes results for excited states. The calculated values of (MBB-LKE-434-S/PUB/284; DGLR-86-100) Avail: Issuing the N(+)-N and O(+)-O resonance charge exchange cross section Activity Q(ex) agree well with measurements from beam experiment that Knowledge-based systems for military aircraft are described. are available at high energies where the diffusion cross section Onboard and ground-based diagnosis and maintenance systems, Q(d) satisfies Q(d) approximately equal to 2Q(ex)o Author multisensor systems, and systems development support are discussed. ESA A87-43383# COMPUTATIONAL AEROACOUSTICS AS APPLIED TO THE DIFFRACTION OF SOUND BY CYMNORICAL BODIES 16 M. M. S. KHAN, W. H. BROWN, and K. K. AHUJA (Lockheed-Georgia Co., Marietta) AIAA Journal (ISSN 0001-1452), vol. 25, July 1987, p. 949-956. Research sponsored PHYSICS by the Lockheed-Georgia Independent Research and Development Program. Previously cited in issue 22, p. 3338, Accession no. Includes physics (general); acoustics; atomic and molecular A86-45495. refs physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics. A87-45282"# Hamilton Standard, Windsor Locks, Conn. RESULTS OF ACOUSTIC TESTS OF A PROP-FAN MODEL F.B. METZGER and P. C. BROWN (United Technologies Corp., A87-42736 Hamilton Standard Div., Windsor Locks, CT) AIAA, SAE, ASME, MODEL-BASED KNOWLEDGE-BASED OPTICAL PROCESSORS and ASEE, Joint Propulsion Conference, 23rd, San Diego, CA, DAVID CASASENT and SUZANNE A. LIEBOWITZ (Carnegie- June 29-July 2, 1987. 8 p. Melon University, Pittsburgh, PA) Applied Optics (ISSN 0003-6935), (Contract NAS3-24222) vol. 26, May 15, 1987, p. 1935-1942. USAF-DARPA-supported-re- (AIAA PAPER 87-1894) search, refs Results of acoustic tests in a low speed open jet anechoic An efficient 3-D object-centered knowledge base is described. wind tunnel are presented for a counter rotation Prop-Fan model. The ability to on-line generate a 2-D image projection or range The model tested had 5 front and 5 rear rotor blades with swept image for any object/viewer orientation from this knowledge base planform. Noise spectra are presented showing the influence of is addressed. Applications of this knowledge base in associative operating and configuration variables such as: (1) power absorption, processors and symbolic correlators are then discussed. Initial (2) tip speed, (3) rotor-rotor spacing, (4) power split between the test results are presented for a multiple degree of freedom object front and rear blade rows, (5) variation of the RPM ratio between recognition problem. These include new techniques to achieve front and rear blade rows, (6) tractor versus pusher (pylon effects), object orientation information and two new associative memory and (7) angle of attack. In addition to model scale results, calculated matrix formulations. Author levels derived from test are presented showing the influence of the above variables on Effective Perceived Noise Level of a 13.1 A87-43044"# California Univ., Irvine. ft diameter Prop-Fan at a flyover distance of 1500 ft. It was found VOLUME INTERCHANGE FACTORS FOR HYPERSONIC that the strongest effects are caused by tip speed and power VEHICLE WAKE RADIATION absorption. A significant finding was that there is an optimum D. K. EDWARDS and D. S. BABIKIAN (California, University, operating tip speed for minimum noise for a given power absorption. Irvine) AIAA, Thermophysics Conference, 22nd, Honolulu, HI, Effects of other parametric variations are generally small but June 8-10, 1987. 10 p. refs measurable. In order to minimize noise to meet airplane certification (Contract NCA2-119) limits, operation at moderate tip speeds and power absorption is (AIAA PAPER 87-1520) shown to be desirable. Accuracy of predicted Effective Perceived Volume interchange factors are shown to be convenient in Noise Level is shown to be good with the best accuracy in the modeling the radiative processes in the wake of a hypersonic 590 to 670 ff/sec tip speed range. Author vehicle. Use of the factors facilitates calculating not just the radiative heating rates on afterbody surfaces but also the radiative A87-46753# de-excitation rates from stimulated emission and re-excitation rates WIND TUNNEL EXPERIMENTAL STUDY OF OPTICAL BEAM from absorption in rarefied nonequilibrium flows. Sample DEGRADATION THROUGH HETEROGENEOUS AERODYNAMIC calculations of volume interchange factors are presented for volume FLOWS configurations modeling wake elements, and the numerical results RUY DERON, MICHEL PHILBERT, JEAN-LOUIS SOLIGNAC, and are compared to limiting approximations to clarify the operation of JEAN-PIERRE FALENI (ONERA, Chatillon-sous-Bagneux, France) the emission, transmission, and absorption processes. Author (SPIE, Technical Symposium on Optics, Electro-Optics and Sensors, Orlando, FL, May 17-22, 1987) ONERA, TP, no. 1987-50, A87-43129"# National Aeronautics and Space Administration. 1987, 8 p. refs Ames Research Center, Moffett Field, Calif. (ONERA, TP NO. 1987-50) HIGH TEMPERATURE TRANSPORT PROPERTIES OF AIR This paper deals with the influence of aerodynamic disturbances E. LEVIN, HARRY PARTRIDGE, and J. R. STALLCOP (NASA, on the quality of images obtained by an airborne optical system. Ames Research Center, Moffett Field, CA) AIAA, Thermophysics A wind-tunnel experiment has been carried out in order to simulate Conference, 22nd, Honolulu, HI, June 8-10, 1987. 39 p. refs aerooptical phenomena in transsonic and supersonic flows. The (Contract NCC2-387) characterization of such effects is obtained by studying the (AIAA PAPER 87-1632) propagation of a laser beam (of 0.63-micron wavelength) through A general computer code was developed to allow calculation optical aerodynamic configurations. The influences of turbulent of atom-atom and ion-atom transport collision integrals from mixing zone and shock waves have been studied. Each

707 16 PHYSICS

aerodynamical configuration has been qualified by both Schlieren noise over a range of propeller rotational frequencies at a fixed visualization and wall pressure probing test. For each configuration, thrust. Author images are recorded and then processed to obtain point spread functions, optical transfer functions, modulation transfer function, and Wiener spectrum of the images. This study should lead to a match of optical and aerodynamical considerations in designing 17 future airborne imaging systems. Author SOCIAL SCIENCES N87-25824# Aeronautical Research Inst. of Sweden, Stockholm. Aerodynamics Dept. MEASUREMENT OF NOISE FROM AIRPLANES TRAVELING AT Includes social sciences (general); administration and management; 3500 TO 11000 M ALTITUDE documentation and information science; economics and cost MAGNUS LINDE and STAFFAN MEIJER Mar. 1986 34 p analysis; law and political science; and urban technology and Sponsored by the Swedish National Board for Technical transportation. Development (FFA-TN-1986-21; ETN-87-99779) Avail: NTIS HC A03/MF A01 The noise on the ground from jet and propeller airplanes at A87-42859# LIABILITY OF THE UNITED STATES GOVERNMENT IN CASES heights 3500 to 11000 m was measured. Results are presented as dBA-levels versus flight level. Equivalent noise levels were also OF AIR TRAFFIC CONTROLLER NEGLIGENCE calculated. Examples are given for how increased noise generation SETI K. HAMALIAN (McGill University, Montreal, Canada) IN: from airplanes affects the resulting Flight Noise Level (a Swedish Annals of air and space law. Volume 11 . Montreal, McGill noise rating for noise exposure forecast). It is found that Flight University, 1986, p. 55-85. refs Noise Level 55 dBA can easily be exceeded if it is assumed that The requirements for liability of the U.S. government and air a certain number of the flights is made with airplanes giving higher traffic controllers for aircraft accidents caused by air traffic controller equivalent noise level. ESA negligence are considered. The development and objectives of air traffic control, and the duties of air traffic controllers are described. The liability on the U.S. government for controller N87-25827"# National Aeronautics and Space Administration. negligence, and the use of the discretionary function for exclusion Langley Research Center, Hampton, Va. from liability are discussed. The liability of the air traffic controller EFFECT OF SIGNAL JITTER ON THE SPECTRUM OF ROTOR during various phases of the flight is examined. I.F. IMPULSIVE NOISE THOMAS F. BROOKS Jun. 1987 18 p Submitted for publication A87-42860# (NASA-TM-100477; NAS 1.15:100477) Avail: NTIS HC A02/MF THE NEW ANNEX 17 - THE LATEST CONTRIBUTION BY A01 CSCL 20A INTERNATIONAL CIVIL AVIATION TO THE BATTLE AGAINST The effect of randomness or jitter of the acoustic waveform TERRORISM [LA NOUVELLE ANNEXE 17 - LE DERNIER on the spectrum of rotor impulsive noise is studied because of its APPORT DE L'AVIATION CIVILE INTERNATIONALE POUR LA importance for data interpretation. An acoustic waveform train is LU'B'E CONTRE LE TERRORISME] modelled representing rotor impulsive noise. The amplitude, shape, JEAN-LOUIS MAGDELENAT (McGill University, Montreal, and period between occurrences of individual pulses are allowed Canada) IN: Annals of air and space law. Volume 11 . Montreal, to be randomized assuming normal probability distributions. Results, McGill University, 1986, p. 87-103. In French. refs in terms of the standard deviations of the variable quantities, are Following a review of the relatively unsuccessful post-facto given for the autospectrum as well as special processed spectra conventions previously adopted to counter terrorism, preventative designed to separate harmonic and broadband rotor noise security measures for international civil aviation which were added components. Consideration is given to the effect of accuracy in to the Annex 17 by the ICAO following the Air India tragedy in triggering or keying to a rotor one per revolution signal. An example 1985 are discussed. Additions to Annex 17 call for an increase in is given showing the resultant spectral smearing at the high the number of standards and recommended practices, requesting frequencies due to the pulse signal period variability. Author countries to intensify their procedures for passenger and baggage search, and aircraft inspection. Exchanges of information between the police services of Western Europe, the United States, and N87-26612"# Missouri Univ., Rolla. Dept. of Mechanical and Canada concerning international terrorist activity have been Aerospace Engineering. undertaken since 1986. Additional proposals are suggested A COMPARISON OF THE STRUCTUREBORNE AND AIRBORNE including an international criminal court and an international PATHS FOR PROPFAN INTERIOR NOISE Final Report prison. R.R. W. EVERSMAN, L. R. KOVAL, and J. V. RAMAKRISHNAN Oct. 1986 61 p (Contract NAG1-394) A87-42861 # (NASA-CR-180289; NAS 1.26:180289) Avail: NTIS HC A04/MF INTERCEPTION OF CIVIL AIRCRAFT VS. MISUSE OF CIVIL A01 CSCL 20A AVIATION A comparison is made between the relative levels of aircraft MICHAEL MILDE (International Civil Aviation Organization, interior noise related to structureborne and airborne paths for the Montreal, Canada) IN: Annals of air and space law. Volume 11 . same propeller source. A simple, but physically meaningful, model Montreal, McGill University, 1986, p. 105-130. refs of the structure treats the fuselage interior as a rectangular cavity The March 1986 ICAO Council amendment concerned with with five rigid walls. The sixth wall, the fuselage sidewall, is a the identification and interception of civil aircraft is discussed. The stiffened panel. The wing is modeled as a simple beam carried Council was concerned with ways to improve the coordination of into the fuselage by a large discrete stiffener representing the communications systems between military and civil aircraft and air carry-through structure. The fuselage interior is represented by traffic control services; to abstain from recourse to the use of analytically-derived acoustic cavity modes and the entire structure force against civil aircraft; and to improve procedures for the is represented by structural modes derived from a finite element identification and interception of civil aircraft. The recommendations model. The noise source for structureborne noise is the unsteady of the Air Navigation Commission for improving identification and lift generation on the wing due to the rotating trailing vortex system interception of civil aircraft are examined.The objections and of the propeller. The airborne noise source is the acoustic field alternatives proposed by various states, to the recommendations created by a propeller model consistent with the vortex of the Commission are described. The criminal use of civil aviation, representation. Comparisons are made on the basis of interior and its potential threat to the security of a state are studied. I.F.

708 19 GENERAL

A87-42862# changes by the FAA in the QAP/Snitch program and pilot certificate THEEFFECTOFEUROPEANLAWONAIRTRANSPORT actions related to pilot deviations detected by Snitch are identified [L'EFFETDU DROITEUROPEENSURLE TRANSPORT and analyzed. I.F. AERIEN] JACQUES NAVEAU (Bruxelles, Universite Libre, Brussels, Belgium) IN: Annals of air and space law. Volume 11 . Montreal, McGill University, 1986, p. 131-138. In French. refs A87-45265# A review of the impact of European law practices on air transport AIRBREATHING PROPULSION SYSTEM DESIGN AT THE is presented, with emphasis on the need for more regional UNITED STATES AIR FORCE ACADEMY - AN INTEGRATED intergovernmental air transport agreements. Competitive APPROACH regulations provided for in the 1956 Rome Treaty were stated to D. NEAL BARLOW and CHARLES W. WOOD (U.S. Air Force apply to air transport by the European Court of Justice in 1986. It Academy, Colorado Springs, CO) AIAA, SAE, ASME, and ASEE, is suggested that article 234 of the Rome Treaty, delegating to Joint Propulsion Conference, 23rd, San Diego, CA, June 29-July the Commission the powers of negotiating traffic rights with third 2, 1987. 11 p. parties on behalf of the community, could help establish a European (AIAA PAPER 87-1870) common market for air transport. Measures including the Council The philosophy and content of the propulsion curriculum at Directive of 1983, sponsored by the French Parliament president, the United States Air Force Academy are summarized, and a to authorize interregional regular air services for passengers, mail, detailed discussion is given of the capstone design course. The and freight, would result in a juxtaposition of interregional air course includes engine/aircraft system constraint analysis, services which would be approved automatically by the Commission preliminary engine/aircraft weight and mission analysis, preliminary and which would not be subject to governmental approval. R.R. aircraft configuration, fuselage design, drag and lift characteristics, engine design and point analysis, and engine off design parameters. A87-42863# The importance of the use of computers in the design sequence AIRLINES ARE EXEMPT FROM LAW ON RIGHTS OF THE is emphasized. V.L. DISABLED BARBARA REUKEMA (Southwestern University, Los Angeles, CA) IN: Annals of air and space law. Volume 11 . Montreal, McGill University, 1986, p. 139-150. refs N87-25273"# FWG Associates, Inc., Tullahoma, Tenn. The relation between airlines and the law prohibiting MODELING AND IMPLEMENTATION OF WIND SHEAR DATA discrimination against handicapped persons is examined. WALTER FROST In NASA. Langley Research Center Wind Consideration is given to airline deregulation, airline operating Shear/Turbulence Inputs to Flight Simulation and Systems certificates, and government assistance to airlines. Court of Appeals Certification p 49-66 Jul. 1987 and Supreme Court decisions on the Rehabilitation Act of 1973 Avail: NTIS HC A12/MF A01 CSCL 05B are discussed. The Supreme Court ruled that section 504 of the The problems of implementing the JAWS wind shear data are Rehabilitation Act of 1973 is not applicable to all commercial discussed. The data sets are described from the view of utilizing airlines; it is limited to those airlines which receive federal financial them in an aircraft performance computer program. Then, some assistance. I.F. of the problems of nonstandard procedures are described in terms of programming the equations of aircraft motion when the effects A87-42864# of temporal and spatially variable winds are included. Finally, some THE WARSAW CONVENTION SYSTEM REGARDING AIR of the computed effects of the various wind shear terms are CARRIER RESPONSIBILITY NEW OEVELOPMENTS IN shown. Author JURISPRUDENCE [LE SYSTEME DE LA CONVENTION DE VARSOVIE EN MATIERE DE RESPONSIBILITE DU TRANSPORTEUR AERIEN - NOUVEAUX DEVELOPPEMENTS JURISPRUDENTIELS] HAROLD ROUSSELLE (McGill University, Montreal, Canada) IN: Annals of air and space law. Volume 11 . Montreal, McGill University, 1986, p. 151-167. In French. refs 19 Recent developments in jurisprudence with respect to the interpretation of the Warsaw Convention in matters regarding air carrier responsibility are reviewed, highlighting the attitude adopted GENERAL recently by the United States of not wishing to modify the Warsaw Convention. In Darghouth vs. Swissair, it was concluded that a national law stipulating the nonapplicability of the prescription period to a minor is not compatible with Warsaw Convention article 29. In Rush vs. U.S. Air, it was specified that luggage and passengers A87-46178# can have a different destination for the purposes of calculating THE ORIGINS AND FUTURE POSSIBILITIES OF AIR the period provided for in article 29. In the Korean Airlines Disaster BREATHING SYSTEMS decision, a contractual link was found to exist between a state HANS VON OHAIN (Dayton, University, OH) IN: International which has solely ratified the Warsaw Convention and one which Symposium on Air Breathing Engines, 8th, Cincinnati, OH, June has only adhered to the Hague Protocol. R.R. 14-19, 1987, Proceedings . New York, American Institute of Aeronautics and Astronautics, 1987, p. 14-25. A87-44064 A development history is presented for airbreating jet aircraft AVIATION SAFETY AND THE FAA'S QUALITY ASSURANCE propulsion systems, together with a development status evaluation PROGRAM and prospective development projection. The various influences ALAN ARMSTRONG Air Law (ISSN 0165-2079), vol. 12, April which had a significant bearing on the major breakthoughs and 1987, p. 58-67. refs development trends, encompassing those of wartime economies The FAA Quality Assurance Program (QAP) aimed at identifying in Germany during WW II, the popular appeal of passenger jet problems in the national airspace system is examined. The travel at high subsonic speeds, etc. are assessed. The comparative implementation and operation of the Snitch program, conflict alert advantages of higher-bypass turbofans for subsonic flight and software connected to ATC computers to signal aircraft deviation low-bypass turbofans for supersonic flight are evaluated, and the from ATC clearance or if separation between aircraft is less than rationale for hydrogen-fueled supersonic combustion ramjet a percentage of the prescribed criteria, are described. Recent operating at hypersonic cruise speeds is presented. O.C.

709 19 GENERAL

N87-26826Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn (West Germany). Unternehmensbereich Apparate. RESEARCH AND DEVELOPMENT. TECHNICAL-SCIENTIFIC PUBLICATIONS 1986 [FORSCHUNG UND ENTWICKLUNG. TECHNISCH-WlSSENSCHAFTLICHE VEROEFFENTLICHUNGEN 1986] 1986 317 p Partly in GERMAN and ENGLISH (ETN-87-99713) Avail: Issuing Activity The evolution of microsystems techniques, the space transportation system SAENGER 2, strategic technology assessment, and the determination of the kinematic parameters of a moving imaging sensor are treated. Trends in intake pressure distortion measurements, artificial intelligence methods, recovery rates of optical fibers, and a Euler solution for air-flow calculations for fighter aircraft; technologies, camber control systems, and a propfan concept for transport aircraft; avionics systems and bearingless rotor systems for helicopters are presented. The TV-SAT antenna, combined spacecraft propulsion systems, the evolution of a serviceable EURECA, Columbus control engineering tasks, and life cycle costs are considered. Acoustics applications, active optics, adaptive preprocessing, streak techniques, and electronic packaging for defense systems are presented. ESA

N87-26853# Inter Nationes, Bonn 0Nest Germany). GOING BEYOND THE LIMITS. AVIATION IN GERMANY [DIE GRENZEN UEBERWINDEN. LUFTFAHRT IN DEUTSCHLAND] GOETZ WANGE, HANNS REDEMANN, and KLAUS MUELLER 1987 28 p In GERMAN (SO-1-87; ETN-87-99909) Avail: NTIS HC AO3/MF A01 The history of 175 years of aviation in Germany is depicted. The work of Hugo Junkers and Claude Domier is summarized. The beginning of world air traffic, and the evolution from propeller to jet aircraft are depicted. The new start of the German aviation industry after 1945, and the concentration and international cooperation in the aviation industry are presented. Military requirements as a motor for the technological development are treated. ESA

710 SUBJECT INDEX

AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 219) November 1987

Typical Subject Index Listing

I SUBJECT HEADING ! I Validation of a method for air resonance testing of Investigation of the aerodynamic performance and noise helicopters at model scale using active control of Pylon characteristics of a 1/5th scale model of the Dowry Rotol AERODYNAMIC BALANCE dynamic characteristics p 683 A87-43462 R212 propoller p640 A87-46265 Active control of aerofoil flutter p 681 A87-46792 Control of the discrete vortices from a delta wing rLowd_J ,pee_o_ad%aearng°dlYenafiaC_ta°fkF_e8tCr°en'siugltu_a_°d An introduction to time-dependent aerodynamics of p 641 A87-46779 nalysis aircraft response, gusts and active controls Computational fluid dynamics applications at McOonnel [ESDU-84020] p 682 N87-26048 Douglas p 701 N87-26007 ADAPTIVE CONTROL Aerodynamics of unmanned aircraft at full-scale in the An approach to the synthesis of an adaptive flight control RAE 24ft wind-tunnel ASA-CR_ p15 _ system with incomplete information p 680 A87-45096 [RAE-TM-AERO-208t ] p645 N87-26027 Preliminary flight results of an adaptive engine control An experimental investigation of dynamic ground system of an F-15 airl_ane effect [AIAA PAPER 87-1847] p 667 A87-45247 [NASA-CR-180560] p 659 N87-26036 Performance seeking control for cruise optimization in AERODYNAMIC COEFFICIENTS fighter aircraft [AIAA PAPER 87-1929] p 681 A87.45307 Helicopter modelling for performance calculation Dual adaptive control: Design principles and p 652 A87-43434 The subject heading is a key to the subject content applications Validation of aerodynamic measurement techniques and of the document. The title is used to provide a [NASA-CR-181050] p 705 N87.25804 calculation methods for high-lift systems An investigation of helicopter higher harmonic control p 640 A87-46363 description of the subject matter. When the title is using a dynamic system coupler simulation The interference of the model support mast with insufficiently descriptive of the document content, p 682 N87-26051 measurements of the longitudinal and lateral aerodynamic the title extension is added, separated from the title Conceptual studies Of control systems for wings with coefficients by three hyphens. The (NASA or AIAA) accession variable camber [NASA-TT-20079] p 644 N87-25307 [MBB-UT-221/86] p 682 N87o26836 number and the page number are included in each Aerofoil maximum lift-coefficient for Mach numbers up ADHESION to 0.4 entry to assist the user in locating the abstract in Factors affecting the sticking ot insects on modified [ESDU-84026} p 645 N87-26028 the abstract section. If applicable, a report number aircraft wings AERODYNAMIC CONFIGURATIONS is also included as an aid in identifying the [NASA-CR-180957] p 659 N87-26037 New aerodynamic design of the fenestron for improved ADHESIVE BONDING document. Under any one subject heading, the performance p 651 A87-43403 The art of reticulation and applicable adhesives --- for Investigation of helicopter twin-rotor characteristics accession numbers are arranged in sequence with acoustically treated engine nacelles p 665 A87-44582 p 628 A87-43438 the AIAA accession numbers appearing first. Adhesives in aerospace p 689 A87-44743 ADHESIVES Flying wing could stealthily reappear p 657 A87-46870 Adhesives in aerospace p 689 A87.44743 AERIAL RUDDERS On the nonlinear aerodynamic and stability The Airbus rudder - An example of new fabrication characteristics of a generic chine-forebody slender-wing technologies p 623 A87-44228 fighter configuration AEROACOUSTICS [NASA-TM-89447] p 643 N87-25305 Computational aeroacoustics asapplied to the diffraction A multi-body aimraff with an all-movable center fuselage of sound by cylindrical bodies p 707 A87.43383 actively controlling fuselage pressure drag A comparison of the acoustic and aerodynamic [ NASA-CASE-LAR-13511-1] p658 N87-25320 A measurements of a model rotor tested in two anechoic National Aerospace Plane Program: Principal wind tunnels p 683 A87o43425 assumptions, findings and policy options A-300 AIRCRAFT An analysis of in-fin tail rotor noise [RAND/P-7288-RGS] p 625 N87-25990 A310-300 CFRP fin Damage tolerance p 852 A87o43427 Computational fluid dynamics: Transition to design Results of acoustic tests of a Prop-Fan model demonstration p 655 A87-44594 applications p 700 N87-26004 [AIAA PAPER 87-1894] p 707 A87-45282 A-310 AIRCRAFT Experience with 3-D composite grids AEROASSlST p 706 N87-26021 A310-300 CFRP fin damage tolerance demonstration Direct simulation of aerothermal loads for an aeroassist [MBB-UT-015/86} p 658 N87-25317 Effect of Reynolds number variation on aerodynamics flight experiment vehicle A-320 AIRCRAFT of a hydrogen-fueled transport concept at Mach 8 [AIAA PAPER 87-1546] p626 A87-43063 [NASA*TP-2728] p 645 N87-26031 The Airbus rudder - An example of new fabrication A computational study of the flowtield surrounding the Gust response of helicopters p 682 N87-26049 technologies p 623 A87-44228 Aeroassist F|ight E_periment vehicta AERODYNAMIC DRAG V2500 - Back on course? p 676 A87-46372 [AIAA PAPER 87-1575] p 626 A87-43084 The use of computer models in helicopter drag Design of a composite tail for the Airbus A-320 AERODYNAMIC CHARACTERISTICS prediction p 628 A87-43424 [MBB-UT*12-86] p 658 N87-25316 Study of the dynamic response of helicopters to a large Thrust/drag accounting for aerospace plane vehicles ACCELERATED LIFE TESTS a=rplane wake p 678 A87-43429 [AIAA PAPER 87-1966] p 656 A87-45335 Operational engine usage and mission analysis Effect of fabrication-related deviations of the geometrical AERODYNAMIC FORCES [AIAA PAPER 87-2097] p 671 A87-45404 parameters of blade profiles on flow in a compressor Force accounting for airframe integrated engines ACCURACY p 629 A87-43603 [AIAA PAPER 87-1965] p 636 A87-45334 A program to investigate requirements for effective flight Investigation of flow structure in a compressor with two Two-dimensional subsonic and transonic wind tunnel wall interference corrections for varied walls simulator displays p683 A87-44715 typos of guides p 629 A87-43604 ACOUSTIC INSTABILITY p 686 A87-46955 Investigation of rotating additional blades on the Steady and unsteady aerodynamic forces from the Pressure oscillations and acoustic-entropy interactions periphery o( an axial-compresssur rotor in ramjet combustion chambers p 629 A87-43618 SOUSSA surface-panel method for a fighter wing with tip missile and comparison with experiment and PANAIR [AIAA PAPER 87-1872] p 668 A87-45267 An experimental investigation of a supercritical airfoil ACOUSTIC SCATTERING [NASA-TP-2736] p 645 N87-26032 at transonic speeds AERODYNAMIC HEAT TRANSFER Computational aeroacoust_cs as apt_ied to the diffraction [AIAA PAPER 87-1241] p 630 A87-44914 of sound by cylindrical bodies p 707 A87-43383 Aerodynamic and heat transfer analysis of the low aspect Two-dimensional numerical analysis for inlets at ratio turbine ACQUISITION subsonic through hypersonic speeds [AIAA PAPER 87-1916] p 696 A87-45296 The F-15E R&M challenge p 699 A87-46715 [AIAA PAPER 87-1751] p 634 A87-45184 AERODYNAMIC INTERFERENCE ACTIVE CONTROL Aerodynamic design modification of a hypersonic wind Two-dimensional subsonic and transonic wind tunnel Simulator evaluations of inceptors for ACT helicopters tunnel nozzle by CSCM with high order accuracy --- wall interference corrections for varied walls p 678 A87-43405 Conservative Supra-Characteristics Method p 686 A87.46955 Helicopter individual-blade-control research at MIT [AIAA PAPER 87.1896] p 635 A87-45284 Development of experimental investigation on transonic 1977-1985 p 679 A87-43446 Aerodynamic characteristics of wave riders wind tunnel wall interference p 687 A87-46960 Development of an experimental system for active p 637 A87-46094 The interference of the model support mast with control of vibrations on helicopters p 679 A87-43447 Underexpanded jet-free stream interactions on an measurements of the longitudinal and lateral aerodynamic Kinematic observers for active control of helicopter rotor axisymmetric afterbody contiguration coefficients vibration p 679 A87-43448 p 639 A87-46232 [NASA-TT-20079] p 644 N87-25307

A-1 AERODYNAMIC LOADS SUBJECT INDEX

A multi-body aircraft with an all-movable center fuselage Airbreathing propulsion system design at the United AIR CONDITIONING EQUIPMENT actively controlling fuselage pressure drag States Air Force Academy - An integrated approach Air conditioning systems for helicopters ]NASA-CASE-LAR-13511-t] p 658 N87-25320 [AIAA PAPER 87-1870] p 709 A87-45265 p 654 A87-43473 AERODYNAMIC LOADS AERONAUTICS AIR DATA SYSTEMS Calculated performance, stability, and maneuverability Going beyond the limits. Aviation in Germany A promising low speed air data system for helicopters of high-speed tilting-prop-rotor aircraft [SO-1-87] p 710 N87-26853 p 661 A87-43437 p 651 A87-43408 AEROSPACE ENGINEERING Contribution of laser anemometry to aircraft safety p 699 A87-46361 Prediction of blade airioads in hovenng and forward flight Interdisciplinary optimum design --- of aerospace using free wakes p 651 A87-43411 structures p 657 A87-47009 Statistical distribution of extreme atmospheric turbulences A prescribed radial distribution circulation of a hovering AEROSPACE INDUSTRY rotor blade p 627 A87-43414 [ONERA, TP NO. 1987-56] p 702 A87-46757 High temperature titanium alloys p 689 A87-44739 Correlation of SA349/2 helicopter flight-test data with AIR FLOW AEROSPACE VEHICLES a comprehensive rotorcraft model p 653 A87-43456 Flight test and evaluation of propulsion system Thrust/drag accounting for aerospace plane vehicles Performance and loads data from a hover test of a operability characteristics [AIAA PAPER 87-1966] p 656 A87-45335 0.658-scale V-22 rotor and wing [AIAA PAPER 87-2092] p 656 A87-45400 Transmission efficiency in advanced aerospace [NASA-TM-89419] p 642 N87-25296 AIR JETS Analytical description of crack resistance curves for powerplant The air-injection method of fixing boundary-layer aluminum sheets used in aircraft construction [AIAA PAPER 87-2043] p 671 A87-45376 transition and investigating scale effects AEROSPACEPLANES [MBB-UT-133/851 p 700 N87-25604 p 639 A87-46264 AERODYNAMIC NOISE A model test vehicle for hypersonic aerospace systems AIR LAW The influence of winglets on rotor aerodynamics development Liability of the United States government in cases of p 628 A87-43422 IMBB-UR-875/86] p 658 N87-25314 air traffic controller negligence p 708 A87-42859 AERODYNAMIC STABILITY National Aerospace Plane Program: Principal Interception of civil aircraft vs. misuse of civil aviation Helicopter individual-blade-control research at MIT assumptions, findings and policy options p 708 A87-42861 1977-1985 p 679 A87-43446 [RAND/P-7288-RGS] p 625 N87-25990 The effect of European law on air transport Aeroelastic control of stability and forced response of AEROTHERMODYNAMICS p 709 A87-42862 supersonic rotors by aerodynamic detuning The thermal environment of transatmospheric vehicles Airlines are exempt from law on rights of the disabled p 676 A87-46249 [AIAA PAPER 87-1514] p 626 A87-43038 p 709 A87-42863 On the nonlinear aerodynamic and stability Volume interchange factors for hypersonic vehicle wake The Warsaw Convention system regarding air carrier characteristics of a generic chine-forebody slender-wing radiation responsibility - New developments in jurisprudence fighter configuration [AIAA PAPER 87-15201 p 707 A87-43044 p 709 A87-42864 [NASA-TM-894471 p 643 N87-25305 AIR NAVIGATION Direct simulation of aerothermal loads for an aeroassist AERODYNAMIC STALLING Worldwide navigation into the 21st century - An airline flight experiment vehicle view p 649 A87-44036 The effect of pitch rate on the dynamic stall or a modified [AIAA PAPER 87-1546] p 626 A87-43063 NACA 23012 aerofoil and comparison with the unmodified Integrated navigation, communication and surveillance High temperature transport properties of air case p 628 A87-43420 systems based on standard distance measuring (AIAA PAPER 87-16321 p 707 A87-43129 Unsteady separation characteristics of airfoils operating equipment p 649 A87-44039 under dynamic stall conditions p 628 A87-43421 Integration of propulsion/integration test results through AIR PIRACY A new simulation of airfoil dynamic stall due to velocity the use of reference plane transfers The new Annex 17 - The latest contribution by and incidence fluctuations [AIAA PAPER 87-1964] p 670 A87-45333 international civil aviation to the battle against terrorism [AIAA PAPER 87-1242] p 630 A87-44915 Comparison of wet and dry growth in artificial and flight p 708 A87-42860 Investigation on the stall margin of a turbofan engine icing conditions p 646 A87-45635 AIR POLLUTION p 675 A87-46239 Aerothermodynamic computations for Large-scale distribution of peroxyacetylnitrate results J85 surge transient simulation p 675 A87-46240 super-/hypersonic flight p 640 A87-46328 from the STRATOZ III flights p 702 A87-46481 AERODYNAMICS AFTERBODIES AIR TRAFFIC Three-dimensional problems in computational fluid Underexpanded jet-free stream interactions on an The quality of radar data and its determination at the dynamics--- Russian book p 693 A87-42916 axisymmetric afterbody configuration radar installations of the Bundesanstalt fuer Correlation of SA349/2 helicopter flight-test data with p 639 A87-46232 Flugsicherung p 650 A87-45878 a comprehensive rotorcraff model p 653 A87-43456 AFTERBURNING AIR TRAFFIC CONTROL Designing transonic wind-tunnel test sections for flow High performance turbofan afterburner systems Real-time wind estimation and tracking with transponder diagnostics and laser velocimeter applications [AIAA PAPER 87-1830] p 666 A87-45234 downlinked airspeed and heading data [AIAA PAPER 87-14341 p 684 A87-44954 AH-64 HELICOPTER p 648 A87-42779 Experimental studies on the dynamic development and Effect of planform taper on hover performance of an Worldwide navigation into the 21st century - An airline control of unsteady separated flows p 642 N87-25297 advanced AH-64 model rotor view p 649 A87-44036 Aviation safety and the FAA's quality assurance An introduction to time-dependent aerodynamics of [NASA-TM-89145] p 643 N87-25304 program p 709 A87-44064 aircraft response, gusts and active controls AILERONS An airborne collision avoidance system - The TCAS [ESDU-84020] p 682 N87-26048 Flight service evaluation of advanced composite ailerons p 649 A87-44231 AEROELASTIClTY on the L-1011 transport aircraft Wind determination from aircraft-movement data The influence of the induced velocity distribution and INASA-CR-1783211 p 691 N87-25439 AIR BREATHING ENGINES p 702 A87-45892 the flapping-lagging coupling on the derivatives of the rotor Morphology of a standing oblique detonation wave --- AIR TRAFFIC CONTROLLERS (PERSONNEL) and the stability of the helicopter p 679 A87-43436 for hypersonic airbreathing propulsion Liability of the United States government in cases of Recent trends in rotary-wing aeroelasticity [AIAA PAPER 87-1785] p 695 A87-45201 air traffic controller negligence p 708 A87-42859 p 652 A87-43442 System performance approach to air breathing Aviation safety and the FAA's quality assurance Aeroelastic stability of a bearingless circulation contro_ propulsion design - A new undergraduate design program p 709 A87-44064 rotor in forward flight p 652 A87-43443 competition AIR TRANSPORTATION Helicopter individual-blade-control research at MIT [AIAA PAPER 87-1869] p 668 A87-45264 The effect of European law on air transport 1977-1985 p 679 A87-43446 Progress toward shock enhancement of supersonic p 709 A87-42862 A unique approach to aeroelastic testing of scaled combustion processes The Warsaw Convention system regarding air carrier rotors p 683 A87-43461 [AIAA PAPER 87-1880] p 690 A87-45274 responsibility - New developments in jurisprudence The numerical simulation of subsonic flutter Modification to the Langley 8-Foot High Temperature p 709 A87-42864 [AIAA PAPER 87-1428] p 633 A87-44952 Tunnel for hypersonic propulsion testing AIRBORNE EQUIPMENT Mechanical evaluation of the aeroelastic behaviour of [AIAA PAPER 87-1887] p 685 A87-45277 Scan stabilization and jitter control for an airborne telescope p 660 A87-42812 a fan blade p 675 A87-46248 Force accounting for airframe integrated engines Development of an experimental system for active Aeroetastic control of stability and forced response of [AIAA PAPER 87-1965] p 636 A87-45334 control of vibrations on helicopters p 679 A87-43447 supersonic rotors by aerodynamic detuning Thrust/drag accounting for aerospace plane vehicles Errors in the measurement of the course angles of radar p 676 A87-46249 [AIAA PAPER 87-1966] p 656 A87-45335 reference points due to the imprecise stabilization of the Trends in the aeroelastic analysis of combat aircraft Advancements in hydrogen expander airbreathing engines antenna mounting in bank and pitch p 657 A87-46362 [AIAA PAPER 87-20031 p 670 A87-45348 p 649 A87-44312 Aeroelastic derivatives as a sensitivity analysis of The influence of flow non-uniformities in air-breathing Wind tunnel experimental study of optical beam nonlinear equations p 699 A87-46797 hypersonic propulsion systems degradation through heterogeneous aerodynamic flows The Aeronautical Research Institue (FFA) wing body 85 [AIAA PAPER 87-2079] p 636 A87-45394 [ONERA, TP NO. 1987-50] p 707 A87-46753 computer program. A panel method for determination of International Symposium on Air Breathing Engines, 8th, History of wind shear turbulence models aeroelastic characteristics applying direct block iterative Cincinnati, OH, June 14-19, 1987, Proceedings p 703 N87-25269 solution techniques p 673 A87-46176 AIRBORNE LASERS [FFA-TN-1986-28] p 642 N87-25298 The origins and future possibilities of air breathing jet Airborne laser communications scintillation Aeroelasticity in turbomachines comparison of propulsion systems p 709 A87-46178 measurements p 649 A87-45722 theoretical and experimental cascade results. Appendix Future trends - A European view --- of air breathing An airborne laser air motion sensing system. I - Concept A5: All experimental and theoretical results for the 9 engines p 673 A87-46179 and preliminary experiment p 662 A87-45732 standard configurations Efficiency parameters for inlets operating at hypersonic An airborne laser air motion sensing system. II - Design [AD-A180534] p 677 N87-25326 speeds p 638 A87-46189 criteria and measurement possibilities AERONAUTICAL ENGINEERING Diagnostic methods for air-breathing engines p 662 A87-45733 Engineering and cost principles for increasing the p 686 A87-46243 AIRBORNE SURVEILLANCE RADAR production efficiency and maintainability of aircraft Computational analysis of hypersonic airbreathing An airborne collision avoidance system - The TCAS engines p 664 A87-43620 aircraft flow fields p 645 N87-26019 p 649 A87-44231

A-2 SUBJECT INDEX AIRCRAFT ENGINES

Radar requirements for future avionics systems Analytical description of crack resistance curves for A comparison of the structureborne and airborne paths p 662 A87-45879 aluminum sheets used in aircraft construction for propfan interior noise AIRCRAFT ACCIDENT INVESTIGATION [MBB-UT-133/85] p 700 N87-25604 [NASA-CR-180289] p 708 N87-26612 Burning questions --- fireworthiness of aircraft cabin Development and testing of cdtical components for the Research and development. Technical-scientific materials p 646 A67-46373 technological preparation on an Airbus fuselage made of publications 1986 Accident investigation p 647 N87-25285 carbon fiber reinforced plastics, phase 1 [ETN-87-99713] p 710 N87-26826 Aircraft accident/incident summary reports: Unalaska, [BMFT-FB-W-86-017] p 692 N87-26151 Aircraft technology of the nineties in MBB passenger Alaska, September 25, 1985; Jenkinsburg, Georgia, Industrial application of computer aided structural aircraft projects September 29, 1985; Boston, Massachusetts, December optimization in aircraft construction [MBB-UT-0021/86] p 660 N87-26834 [MBB-UT-273/86] p 706 N87*26523 15, 1985; DeKalb, Texas, December 31, 1985; Erie, Integration of the propfan concept in aircraft design AIRCRAFT CONTROL Pennsylvania, February 21, 1986 [MBB-UT-0001/86] p 677 N87-26835 An approach to the synthesis of an adaptive flight control [PB87-910408] p 648 N87-25310 AIRCRAFT DETECTION AIRCRAFT ACCIDENTS system with incomplete information p 680 ,6,87-45096 An automated radar-signature measurement system History of wind shear turbulence models Validation of an integrated flight and propulsion control p 698 A87-45886 p 703 N87-25269 design for fighter aircraft AIRCRAFT ENGINES Introduction to the JAWS Program [AIAA PAPER 87-1928] p 680 A87-45306 Electrochemical machining processes in aircraft engine p 703 N87-25270 Fokker 50 - Pedigree with poweT p 656 A87-45647 building --- Russian book p 693 A87-42905 JAWS multiple Doppler derived winds Integration of engine/aircraft control - 'How far is it T700/CT7 derivative growth engine reliability - p 703 N87-25271 sensible to go' p 674 A87-46226 Status of the JAWS Program p 703 N87-25272 DVI in the military cockpit - A third hand for the combat Consistent with longstanding industry traditions p 663 A87-43464 B-57B gust gradient program p 657 N87-25276 pilot --- Direct Voice Input p 681 AB7-46315 Microburst model requirements for flight simulation: An Turbulence models p 703 N87-25277 Effect of fabrication-related deviations of the gecmetrical airframe manufacturer's perspective Military specifications p 658 N87-25281 parameters of blade profiles on flow in a compressor p 687 N87-25278 Unresolved issues in wind shear encounters p 629 A87-43603 Military specifications p 658 N87-25281 p 647 N87-25282 Investigation of flow structure in a compressor with two Simulator systems integration p 687 N87-25283 Helicopter-V/STOL dynamic windand turbulence design typos of guides p 629 A87-43604 United Aidines wind shear incident of May 31, 1984 methodology p 658 N87-25284 Selection of admissible contact stresses for toothed p 647 N87-25287 Optimal cooperative control synthesis of active gears of aircraft engines p 663 A87-43605 United Airlines wind sheer incident of May 31, 1984 displays Approximation of the cbaracteristics of the turbine of a [NASA.CR-4058] p 705 N87-25807 p 647 N87-25288 gas turbine engine in a wide range of operating modes Control of aircraft under severe wind shear conditions KRASH analysis correlation. Transport airplane p 663 A87-43606 p 682 N87-26050 controlled impact demonstration test The low-aspect-ratio parameter of blades Conceptual studies of control systems for wings with lAD-A179906] p 647 N87-25308 p 663 A87-43607 Aircraft accident/incident summary reports: Unalaska, variable camber Optimization of the duration of ultrasonically activated Alaska, September 25, 1985; Jenkinsburg, Georgia, [MBB-UT-221/86] p 682 N87-26836 impact surface treatment of gas-turbine-engine blades September 29, 1985; Boston, Massachusetts, December AIRCRAFT DESIGN p 663 A87-43609 15, 1985; DeKalb, Texas, December 31, 1985; Erie, Honeycomb structures: Parameter selection and design Numerical study of the gasdynamic process in a pulsejet Pennsylvania, February 21, 1986 --- Russian book p 693 A87-42914 [PB87-910408] p 648 N87-25310 The tilt-rotor aircraft - A response to the future? From engine p 663 A87-43614 Annual revve_ of aircraft accident data. US air carder European interrogations to Eurefar actions Calculation of the reliability of aircraff-engino parts under operations calendar year 1983 ]MBB-UD-485-86-PUB] p 654 A87-43474 repeated static loading p 664 A87-43616 [PB87-160628] p 648 N87-25311 Validation of an integrated flight and propulsion control Engineering and cost principles for increasing the AIRCRAFT ANTENNAS design for fighter aircraft production efficiency and maintainability of aircraft A conformal aircraft phased away antenna for [AIAA PAPER 87-1928] p 680 A87-45306 engines p 664 A87-43620 airplane-satellite communication in the L bend Fokker 50 - Pedigree with power p 656 A87-45647 Optimization of systems for the automatic testing of [DFVLR-FB-86-47] p 701 N87-26259 Seastar - Glass, plastic, and tradition aircraft engines according to cost criteria AIRCRAFT APPROACH SPACING p 656 A87-45648 p 664 A87-43621 Application of wedge diftraction theory to estimating Technological aspects in preparing the development of Evaluating and testing of turbofan engines power density at airport humped runways regional airliners p 657 A87-46327 [ASME PAPER 86-WA/DE-3] p 664 A87-43701 p 650 A87-46861 The real world - A maintainer's view --. on military Heat exchangers for turboshaff engines AIRCRAFT COMMUNICATION aircraft p 624 A87-46708 p 664 A87-44253 Integrated navigation, communication end surveillance The F-15E R&M challenge p 699 A87-46715 Fiber optic control of _et aircraff engines systems based on standard distance measuring Study of the aerodynamics of high-speed propellers p 661 A87-45115 equipment p 649 A87-44039 [ONERA, TP NO. 1987-61] p 640 A87-46761 Engine maintenance improvement considerations AIRCRAFT COMPARTMENTS Interdisciplinary optimum design --- of aerospace [AIAA PAPER 87-1716] p 624 A87-45159 Fire, smoke, toxicity --- in airline operations structures p 657 A87-47009 Propfan propulsionsystems for the 1990's p 646 A87-44748 B-57B gust gradient program p 657 N87-25276 [AIAA PAPER 87-1729] p 665 A87-45168 AIRCRAFT CONFIGURATIONS Aircraft technologies of the nineties in MBB passenger Highly compact inlet diffuser technology An analytic method of quantifying helicopter agility aircraft projects [AIAA PAPER 87-1747] p 666 A87-45180 p 678 A87-43432 [MBB-UT-21/86] p 625 N87-25291 F-16 modular common iolet design concept [AIAA PAPER 87-1748] p 666 A87-45181 Transonic analysis of the F-16A with under-wing fuel Flight duration, airspeed practices and altitude Flight test of the F100-PW-220 engine in the F-16 tanks - An application of the TranAir full-potential code management of airplanes involved in the NASA VGH [AIAA PAPER 87-1845] p 667 A87-45245 [AIAA PAPER 87-1198] p 630 A87-44905 General Aviation Program F-15/F109 digital electronic engine control main fuel Simulation o1 transonic viscous flow over a fightar-like [NASA-TM-89074] p 625 N87-25293 configuration including inlet gear pump field service evaluation A multi-body aircraft with an all-movable center fuselage [AIAA PAPER 87-1199] p 630 A87-44906 [AIAA PAPER 87-1846] p 667 A87-45246 actively controlling fuselage pressure drag Simulation of performance, behaviour and faults of Uoderexpanded jet-free stream interactions on an [NASA-CASE-LAR-13511-1] p 658 N87-25320 axisymmetdc afterbody confKjuration aircraft engines Development of a geometry handling program for the p 639 A87.46232 [AIAA PAPER 87-1868] p 668 A87-45263 FFA subsonic higher order panel method Canard configurations Ground testing facilities requirements for hypersonic [FFA-TN-1985-48] p 699 N87-25534 [ETN-87-99914] p 659 N87-26039 propulsion development AIRCRAFT CONSTRUCTION MATERIALS National Aerospace Plane Program: PrkcipaI [AIAA PAPER 87-1884] p 684 A87-45276 Composite vital parts optimisation for EH 101 rotor assumptions, findings and policy options APU fuel efficiency and affordability for commercial hub p 653 A87-43451 [RAND/P-7288-RGS] p 625 N87-25990 aircraft The microstructure and mechanical properties of various Computational fluid dynamics: Transition to design [AIAA PAPER 87-1907] p 669 A87-45299 aluminium-lithium alloy product forms for helicopter applications 3 700 N87-26004 A derivative engine based on new technology - Low structures p 688 A87-43454 CFD applications: The Lockheed perspective risk; cost effective Prospects for the use of composites in civil aircraft 3 644 N87-26005 [AIAA PAPER 87.1910] p 669 A87-45292 p 655 A87-44577 Development and application of unified algorithms for Micro-computer/perallel processing for real time testing The art of reticulation and applicable adhesives --- for problems in computational science 3 705 N87.26006 of gas turbine control systems [AIAA PAPER 87-1926] p 669 A87-45304 acoustically treated engine nacelles p 665 A87-44582 Application of computational physics within Northrop A310-300 CFRP fin Damage tolerance 706 N87-26008 Transmission efficiency in advanced aerospace demonstration p 655 A87-44594 powerplant Design applications for supercornputers [AIAA PAPER 87-2043] p 671 A87-45376 Materials in aerospace; Proceedings of the First 706 N87-26010 International Conference, London, England, Apr. 2-4,1986. Flight test and evaluation of propulsion system Experience with 3-D composite grids operability characteristics Volumes 1 & 2 p 689 A87-44729 706 N87-26021 Materials in helicopters - A review [AIAA PAPER 87-2092] p 656 A87-45400 Numerical solution of the Navier-Stokes equations about p 624 A87-44731 Engine variable geometry effects on commercial Developments in titanium alloys p 689 A87-44744 three-dimensional configurations: A survey supersonic transport development Materials for structures of the future p 701 N87-26022 [AIAA PAPER 87-2101] p 672 A87-45406 p 669 A87-44745 Canard configurations Variable cycle concepts for high Mach applications Fire, smoke, toxicity --- in airline operations [ETN-67-99914] p 659 N87-26039 (AIAA PAPER 87-2103] p 672 A87-45408 p 646 A87-44748 Measurement of the effect of rnanufactudng deviations Performance estimation of an aircraft internal Effects of impact loading on carbon fiber reinforced on natural laminar flow for a single engine general aviation combustion engine structures air_ano [AIAA PAPER 87-2173] p 672 A87.45453 [MBB-Z-63/86] p 691 N87-25436 [NASA-CR-180671] p 677 N87-26044 Aircraft engine design --- Book p 673 A87-45875

A-3 AIRCRAFT EQUIPMENT SUBJECT INDEX

International Symposium on Air Breathing Engines, 8th, The F-15E R&M challenge p 699 A87-46715 Technological change and skill requirements - A case Cincinnati, OH, June 14-19, 1987, Proceedings Sparing to optimize naval airship availability study of numerically controlled riveting in commercial ) 673 A87-46176 p 625 A87-46716 aircraft manufacture Civil propulsion technology for the next twenty-five AIRCRAFT MANEUVERS [ASME PAPER 86-WA/TS-2] p 623 A87-43723 years ) 624 A87-46177 Rotor design for maneuver performance The Airbus rudder - An example of new fabrication Future trends - A European view --- of air breathing p 652 A87-43431 technologies p 623 A87-44228 engines ) 673 A87-46179 An analytic method of quantifying helicopter agility The new Soviet fighters - How good are they? Improved agility for modern fighter aircraft. II - Thrust p 678 A87-43432 p 656 A87-46312 vectoring engine nozzles ) 673 A87-46181 Observations of pilot control strategy in low level AIRCRAFT RELIABILITY Application of engine component life methodology to helicopter flying tasks p 678 A87-43433 Highly reliable, microprocessor-based engine control life assessment ) 698 A87-46230 Time modulation. II * Scheme cedes avoidance [AIAA PAPER 87-1927] p 669 A87-45305 Stress analysis and optimisation of turbine rotor blade maneuvers for aircraft p 649 A87-44845 The real wodd - A maintainer's view --- on military shrouds ) 699 A87-46250 Singular trajectories in airplane cruise-dash aircraft p 624 A87-46708 Exhaust carbon - The effects of fuel composition optimization AIRCRAFT SAFETY ) 676 A87-46253 [NASA-CR-f80636] p 659 N87-26035 Testing automated ground collision avoidance systems Numerical simulation of diffusor/combustor dome AIRCRAFT MODELS on the AFTI/F-16 p 660 A87-43375 interaction ) 676 A87-46255 Rotor design for maneuver performance Development of a flexible and economic helicopter AIRCRAFT EQUIPMENT p 652 A87-43431 engine monitoring system ) 663 A87-43466 TACAN/INS Performance Evaluation (TIPE) flight test Helicopter modelling for performance calculation Lightning protection activity in the development of a new report p 652 A87-43434 helicopter > 654 A87-43471 [AD-A180138] p 650 N87-25313 Helicopter model in flight identification by a real time Helicopter rotor icing protection methods Portable fuel leak detector self adaptive digital process p 680 A87-43458 } 654 A87-44256 lAD-A180095] p 700 N87-25550 Experimental study of the vortex flow behavior on a Development of the Chinook helicopter rotor blade AIRCRAFT FUEL SYSTEMS generic fighter wing at subsonic and transonic speeds de-icing system ) 655 A87-44704 Fuel saving and fuel related subjects within an airline's [AIAA PAPER 87-1262 p 631 A87-44920 Icing clearance criteria for UK militaw helicopters operational environment Investigation of a delta-wing fighter model flow field at ) 646 A87-44705 [ETN-87-90148] p 648 N87-26034 transonic speeds Contribution of laser anemometry to aircraft safety AIRCRAFT FUELS AIAA PAPER 87-1749 p 634 A87-45182 ) 699 A87-46361 Degradation mechanisms of sulfur and nitrogen Scale model test results of a thrust reverser concept Burning questions --- fireworthinesa of aircraft cabin containing compounds during thermal stability testing of for advanced multi-functional exhaust systems materials ) 646 A87-46373 model fuels AIAA PAPER 87-1833 p 667 A87-45235 Aircraft accident/incident summary reports: Unalaska, [AIAA PAPER 87-2039] p 690 A87-45372 Wind tunnel tests on a one-foot diameter SR-7L propfan Alaska, September 25, 1985; Jenkinsburg, Georgia, AIRCRAFT GUIDANCE model September 29, 1985; Boston, Massachusetts, December Maximum survival capability of an aircraft in a severe AIAA PAPER 87-1892 p 635 A87-45281 15, 1985; DeKalb, Texas, December 31, 1985; Erie, windshear p 680 A87-44254 F-t5 SMTD hot gas ingestion wind tunnel test results Pennsylvania, February 21, 1986 AIRCRAFT HAZARDS --- STOL and Maneuver Technology Demonstrator [PB87-910408] p 648 N87-25310 EMl-fault prevention and self recovery of digital flight AIAA PAPER 87-1922 p 669 A87-45301 Control of aircraft under severe wind shear conditions control systems p 661 A87-43470 Exploratory evaluation of a moving-model technique for p 682 N87-26050 Maximum survival capability of an aircraft in a severe measurement of dynamic ground effects AIRCRAFT SPECIFICATIONS windshear p 680 A87-44254 AIAA PAPER 87-1924 p 685 A87-45303 Proving that Avanti stands for progress Extreme atmospheric turbulence Recent progress in the measurement of the drag p 656 A87-46314 [ONERA, TP NO. 1987-8] p 680 A87-44328 coefficients of models of transport aircraft in a wind AIRCRAFT STABILITY Helicopter Rotor Icing Symposium, London, England, tunnel Calculated performance, stability, and maneuverability Jan. 14, 1986, Proceedings p 646 A87-44701 [NASA-TF-20096] p 644 N87-25306 of high-speed tilting-prop-rotor aircraft Where and when helicopter icing occurs The interference of the model support mast with p 651 A87-43408 p 702 A87-44702 measurements of the longitudinal and lateral aerodynamic Stability and control modelling --- helicopters in near Rotor icing experience at Westland and its application coefficients hovering flight p 678 A87-43428 to current and future helicopters p 646 A87-44703 [NASA-TF-20079] p 644 N87-25307 The influence of the induced velocity distribution and Comparison of wet and dry growth in artificial and flight AIRCRAFT NOISE the flapping-lagging coupling on the derivatives of the rotor icing conditions p 646 A87-45635 Measurement of noise from airplanes traveling at 3500 and the stability of the helicopter p 679 A87-43436 Numerical simulation of cruiser on aircraft lightning to 11000 m altitude AIRCRAFT STRUCTURES p 646 A87-46317 [FFA-TN-t986-21] p 708 N87-25824 Honeycomb structures: Parameter selection and design Burning questions --- fireworthiness of aircraft cabin Effect of signal jitter on the spectrum of rotor impulsive -.. Russian book p 693 A87-42914 materials p 646 A87-46373 noise Adhesives in aerospace p 689 A87-44743 AIRCRAFT INSTRUMENTS [NASA-TM-100477] p 708 N87-25827 Superplastic forming/diffusion bending of titanium Irish Dauphin helicopter S.A.R. system flight tests --- AIRCRAFT PARTS p 689 A87-44747 Search and Rescue p 648 A87-43455 Parameters of optimal planetary gears of AI type Corrosion protection --- in aircraft structures Optically interfaced sensor system for aerospace p 694 A87-43622 p 624 A87-44750 applications p 694 A87-45107 Analytical description of crack resistance curves for Crack growth prediction in 3D structures under Fiber optic control of jet aircraft engines aluminum sheets used in aircraft construction aeronautical-type spectrum Ioadings p 661 A87-45118 [MBB-UT-133/85] p 700 N87-25604 [ONERA, TP NO. 1987-79] p 691 A87-46772 Onboard instrumentation for flight test takeoff Industrial application of computer aided structural Aircraft skin that bruises p 691 A87-46874 performance p 662 A87-45126 optimization in aircraft construction A310-300 CFRP fin damage tolerance demonstration Contribution of laser anernometry to aircraft safety [MBB-UT-273/86] p 706 N87-26523 [MBB-UT-015/86] p 658 N87-25317 p 699 A87-46361 AIRCRAFT PERFORMANCE Effects of impact loading on carbon fiber reinforced Wind tunnel experimental study of optical beam Expanding tilt rotor capabilities p 651 A87-43407 structures degradation through heterogeneous aerodynamic flows Countdown to the propfan p 664 A87-44272 [MBB-Z-83/86] p 691 N87-25436 [ONERA, TP NO. 1987-50] p 707 A87-46753 Onboard instrumentation for flight test takeoff Statistical distribution of extreme atmospheric performance p 662 A87-45126 Automated systems for the manufacture of Airbus vertical stabilizers turbulences HALE thermal balance --- High Altitude Long Endurance [ONERA, TP NO. 1987-56] p 702 A87-46757 remotely piloted vehicles [MBB-UT-17-86] p 705 N87-25786 AIRCRAFT LANDING [AIAA PAPER 87-2172] p 656 A87-45452 Factors affecting the sticking of insects on modified Advanced fighter thrust reverser integration for minimum Fokker 50 - Pedigree with power p 656 A87-45647 aircraft wings landing distance Flying the CF-18 Hornet p 656 A87-46313 [NASA-CR-180957] p 659 N87-26037 [AIAA PAPER 87-1923] p 655 A87-45302 Flying wing could stealthily reappear Industrial application of computer aided structural Optimal flight trajectories in the presence of windshear, p 657 A87-46870 optimization in aircraft construction 1984-86 Wind Shear/Turbulence Inputs to Flight Simulation and [MSB-UT-273/86] p 706 N87-26523 [NASA-CR-180316] p 682 N87-26047 Systems Certification AIRCRAFT SURVIVABILITY AIRCRAFT MAINTENANCE [NASA-CP-2474] p 625 N87-25267 Maximum survival capability of an aircraft in a severe Aircraft structural maintenance recommendations based History of wind shear turbulence models windshear p 680 A87-44254 on fracture mechanics analysis p 623 A87-42857 p 703 N87-25269 AIRCRAFT WAKES Design of an automated information-processing Modeling and implementation of wind shear data Flow over a trailing flap and its asymmetric wake system p 704 A87-44241 p 709 N87-25273 p 626 A87-43376 Corrosion protection --- in aircraft structures Application of data to piloted simulators Investigation of blade-vortices in the rotor-downwash p 624 A87-44750 p 687 N87-25275 p 627 A87-43415 Engine maintenance improvement considerations Helicopter-V/STOL dynamic wind and turbulence design Study of the dynamic response of helicopters to a large [AIAA PAPER 87-1716] p 624 A87-45159 methodology p 658 N87-25284 airplane wake p 678 A87-43429 Real-time neutron imaging of gas turbines An introduction to time-dependent aerodynamics of [AIAA PAPER 87-1762] p 695 A87-45189 aircraft response, gusts and active controls Helicopter response to an airplanes's vortex wake p 678 A87-43430 Performance seeking control for cruise optimization in [ESDU-84020] p 682 N87-26048 fighter aircraft Estimation of spillage drag for a wide range of AIRFOIL OSCILLATIONS [AIAA PAPER 87-1929] p 681 A87-45307 axisymmetric intakes at M 1 Forced unsteady vortex flows driven by pitching Project for an intelligent system for on-line trouble [ESDU-84004] p 701 N87-26301 airfoils shooting p 705 A87-46365 AIRCRAFT PRODUCTION [AIAA PAPER 87-1331] p 631 A87-44931 The real world - A maintainer's view --- on military Electrochemical machining processes in aircraft engine Wake measurements of an oscillating airfoil aircraft p 624 A87-46708 building --- Russian book p 693 A87-42905 p 637 A87-45779

A-4 SUBJECT INDEX AVIONICS

Bounded random oscillations - Model and numerical Wind determination from aircraft-movement data ASPECT RATIO resolution for an airfoil p 702 A87-45892 Friction factors and heat transfer coefficients in [ONERA, TP NO. 1987-73] p 681 A87-46767 Flight duration, airspeed practices and altitude turbulated cooling passages of different aspect ratios. I - Active control of aerofoil flutter p 681 A87-46792 management of airplanes involved in the NASA VGH Experimental results AIRFOIL PROFILES General Aviation Program [AIAA PAPER 87-2009] p 696 A87-45350 Unsteady separation characteristics of airfoils operating [NASA-TM-89074] p 625 N87-25293 Detailed near-wake flowfield surveys with comparison under dynamic stall conditions p 628 A87-43421 ALGORITHMS to an Euler method of an aspect ratio 4 rectangular wing The effect of trip wire roughness on the performance Fast methods applied to the calculation of transonic [NASA-TM-89357] p 644 N87-25993 of the Wortmann FX 63-137 airfoil at low Reynolds airfoils p 641 A87-46962 ATMOSPHERIC ATTENUATION numbers p 629 A87-44019 Automatic systems and the low-level wind hazard Wind tunnel experimental study of Optical beam A new simulation of airfoil dynamic stall due to velocity p 681 N87-25279 degradation through heterogeneous aerodynamic flows and incidence fluctuations Development and application of unified algorithms for [ONERA, TP NO. 1987-50] p 707 A87-46753 [AIAA PAPER 87-1242] p 630 A87-44915 problems in computational science p 705 N87-26006 ATMOSPHERIC CIRCULATION Computational chemistry p 706 N87-26023 Low-speed wind-tunnel results for symmetrical NASA An airborne laser air motion sensing system. I - Concept ALTITUDE SIMULATION LS(1)-0013 airfoil and preliminary experiment p 662 A87-45732 [NASA-TM-4003] p 645 N87-26033 Full-scale thrust reverser testing in an altitude facility An airborne laser air motion sensing system, II - Design Optimization methods applied to the aerodynamic design [AIAA PAPER 87-t788] p 684 A87-45203 criteria and measurement possibilities of helicopter rotor blades ALTITUDE TESTS p 662 A87-45733 [NASA.TM-89155] p 660 N87-26042 Application of computational fluid dynamics to analysis ATMOSPHERIC COMPOSITION AIRFOILS of exhaust gas/diffuser interactions in a turbine engine Large-scale distribution of peroxyacetylnitrate results Flow over a trailing flap and its asymmetric wake altitude test cell from the STRATOZ III flights p 702 A87-46481 p 626 A87-43376 [AIAA PAPER 87-2014] p 670 A87-45354 Flow-field measurements of an airfoil with a deflected ALUMINUM ALLOYS ATMOSPHERIC MODELS spoiler using an LDV system Failure analysis of a large wind tunnel compressor Turbulence models p 703 N87-25277 [AIAA PAPER 87-1438] p 634 A87-44955 blade p 692 A87-42852 Microburst model requirements for flight simulation: An Development of low-cost test techniques for advancing The microstructure and mechanical properties of various airframe manufacturer's perspective film cooling technology aluminium-lithium alloy product forms for helicopter p 687 N87-25278 [AIAA PAPER 87-1913] p 696 A87-45293 structures p 688 A87-43454 ATMOSPHERIC MOISTURE Unsteady viscous flows round moving circular cylinders Analytical description of crack resistance curves for Where and when helicopter icing occurs and airfoils. II p 637 A87-45792 aluminum sheets used in aircraft construction p 702 A87-44702 Unsteady viscous-inviscid interaction method and [MBB-UT-133/85] p 700 N87-25604 Experiences with h0t-wiro instruments for the computation of buffeting over airfoils AMPHIBIOUS AIRCRAFT measurement of the liquid water content in clouds [ONERA, TP NO. 1987-58] p 640 A87-46759 Seastar - Glass, plastic, and tradition [DFVLR-MITI'-86] p 704 N87-26476 Laminar separation bubble characteristics on an airfoil p 656 A87-45648 ATMOSPHERIC TURBULENCE at low Reynolds numbers p 641 A87-46778 ANECHOIC CHAMBERS Extreme atmospheric turbulence Compressible flows in the wakes of a square cylinder A comparison of the acoustic and aerodynamic [ONERA, TP NO. 1987-8] p 680 A87-44328 and thick symmetrical airfoil arranged in tandem measurements of a model rotor tested in two anechoic Statistical distribution of extreme atmospheric p 641 A87-46922 wind tunnels p 683 A87-43425 turbulences Tomographic reconstruction of three-dimensional flow ANGLE OF ATTACK [ONERA, TP NO. 1987-56] p 702 A87-46757 over airfoils On the nonlinear aerodynamic and stability Status of the JAWS Program p 703 N87-25272 [AD-A179976] p 643 N87-25300 characteristics of a generic chine-forebody slender-wing Correlation of B*I flight test subjective assessments and Determination of the local heat transfer characteristics fighter configuration some ride quality/vibration exposure criteria on glaze ice accretions on a cylinder and a NACA 0012 [NASA-TM-89447] p 643 N87-25305 [AD-A179844] p 658 N87-25318 airfoil ANGULAR ACCELERATION ATOMIC INTERACTIONS [AD-A179931] p 647 N87-25309 Motion software for a research flight simulator High temperature transport properties of air Airfoil flutter model suspension system p 704 A87-44713 [AIAA PAPER 87-1632] p 707 A87-43129 [NASA-CASE-LAR-13522-1-SB] p 687 N87-25334 ANGULAR VELOCITY ATOMIZERS Influence of a heated leading edge on beundaw layer The influence of the induced velocity distribution and Influence of fuel temperature on atomization growth, stability and transition the flapping-lagging coupling on the derivatives of the rotor performance of pressure-swirl atomizers [DE87-008516] p 700 N87-25538 and the stability of the helicopter p 679 A87-43436 p 698 A87-46198 Wind tunnel evaluation of a truncated NACA 64-621 ANISOTROPIC MEDIA ATTACK AIRCRAFT airfoil for wind turbine applications Determination of the structural properties of helicopter Flying the CF-18 Hornet p 656 A87-46313 [NASA-CR-180803] p 703 N87-25621 rotor blades by theoretical and experimental methods Trends in the aeroelastic analysis of combat aircraft An experimental low Reynolds number comparison of p 653 A87-43450 p 657 A87-46362 a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil and ANNULAR FLOW ATrlTUDE CONTROL a NACA 64-210 airfoil in simulated heavy rain Mathematical model for calculating the atomization of Study of helicopterroll control effectiveness criteria [NASA-CR-181119] p 644 N87-25997 a liquid jet by an annular gas stream [NASA.CR-177404] p 681 N87-25330 Aerofoil maximum lift-coefficient for Math numbers up p 693 A87-43610 AUGMENTATION to 0.4 ANNULAR NOZZLES Optimal cooperative control synthesis of active [ESDU-84026] p 645 N87-26028 NO(x) reduction and combustion phenomena in the displays AIRFRAME MATERIALS multi-annular gas turbine swirl burner [NASA-CR-4058] p 705 N87-25807 Seastar - Glass, plastic, and tradition [AIAA PAPER 87-2036] p 671 A87-45370 AUTOGYROS p 656 A87-45648 ANTENNA ARRAYS Spanish contribution to rotorcraft development - AIRFRAMES A conformal aircraft phased array antenna for Homage to de la Cierva p 623 A87-43426 Helicopter activities in Germany p 623 A87-43401 airblase-satellite communication in the L band AUTOMATIC CONTROL Materials for structures of the future [DFVLR-FB-86-47] p 701 N87-26259 Design of CCV flight control system of STOL flying p 689 A87-44745 ANTENNA DESIGN beat p 680 A87-45097 AIRLINE OPERATIONS Conformal microstrip communication antenna AUTOMATIC FLIGHT CONTROL Airlines are exempt from law on rights of the disabled p 697 A87-45689 Automatic systems and the low-level wind hazard p 709 A87-42863 APPLICATIONS PROGRAMS (COMPUTERS) p 681 N87-25279 Worldwide navigation into the 21st century - An airline Development and application of unified algorithms for Accident investigation p 647 N87-25285 view p 649 A87.44036 problems in computational science p 705 N87-26006 AUTOMATIC LANDING CONTROL Fire, smoke, toxicity -- in airline operations Design applications for supercomputers A combined stochastic feedforward and feedback p 646 A87-44748 p 706 N87-26010 control design methodology with application to autoland AIRPORT BEACONS Computational fluid dynamics research at the United design Colour dependence and surplus information in airport Technologies Research Center requiring [NASA-CR-4078] p 705 N87-25806 visual aids during VFR operations p 649 A87-44040 supercomputers p 701 N87-26011 AUTOMATIC TEST EQUIPMENT AIRPORT LIGHTS APPROACH Optimization of systems for the automatic testing of Colour dependence and surplus information in airport Heliport visual approach surface testing test plan aircraft engines according to cost criteria visual aids during VFR operations p 649 A87-44040 [AD-A179897] p 650 N87-25312 p 664 A87-43621 AIRPORTS AUTOMATION ARC HEATING Classification of the load-carrying capacity of runway Testing automated ground collision avoidance systems Test flow calibration study of the Langley Arc-Heated surfaces by the ACN-PCN method. II on the AFTI/F-16 p 660 A87°43375 Scramjet Test Facility p 686 A87-46354 Design of an automated information-processing [AIAA PAPER 87-2165] p 685 A87-45445 AIRSHIPS system p 704 A87-44241 ARCHITECTURE (COMPUTERS) Spadng to optimize naval airship availability AUTONOMOUS NAVIGATION Application of computational physics within Northrop p 625 A87-46716 Autonomous navigation system for the new generation p 706 N87-26008 AIRSPACE of military helicopters and associated flight tests Heliport visual approach surface testing test plan ARMED FORCES (UNITED STATES) p 648 A87-43469 [AD-Af79897] p 650 N87-25312 The AVSCOM flight safety part program AUXILIARY POWER SOURCES AIRSPEED p 647 A87-46724 APU fuel efficiency and affordability for commercial Real-time wind estimation and tracking with transponder ARTIFICIAL INTELLIGENCE aircraft downlinked airspeed and heading data Project for an intelligent system for on-line trouble [AIAA PAPER 87-1907] p 669 A87-45290 p 648 A87-42779 shooting p 705 A87-46365 AVIONICS A new method of analytical evaluation of helicopter true Use of artificial intelligence methods A promising low speed air data system for helicopters airspeed p 661 A87-43439 [MBB-LKE-434-S/PUB/284] p 707 N87-26831 p 661 A87-43437

A-5 SUBJECT INDEX AXIAL FLOW

BUBBLES Standardization and logistic support cost effectiveness BODY CENTERED CUBIC LAI-rlCES A unique measurement technique to study of advanced avionics systems p 661 A87-43468 High temperature titanium alloys p 689 A87-44739 laminar-separation bubble charactenstics on an airfoil The Air Force Flight Test Center - Now and the future BODY-WING CONFIGURATIONS p 684 A87-45125 Navier-Stokes simulation of a hypersonic generic [AIAA PAPER 87-1271] p 631 A87-44921 Laminar separation bubble characteristics on an airfoil Radar requirements for future avionics systems wing/fuselage at low Reynolds numbers p 641 A87-46778 p 662 A87-45879 [AIAA PAPER 87-1192] p 629 A87-44902 BUFFETING Integration of engine/aircraft control - 'How far is it Subsonic wind-tunnel measurements of a slender Unsteady viscous-inviscid interaction method and sensible to go' p 674 A87-46226 wing-body configuration employing a vortex flap computation of buffeting over airfoils Culprits causing avionic equipment failures [NASA-TM-89101] p 642 N87-25295 p 662 A87-46727 [ONERA, TP NO, 1987-58] p 640 A87-46759 BOEING 707 AIRCRAFT BYPASS RATIO Wind Shear/Turbulence Inputs to Flight Simulation and Fracture of an aircraft horizontal stabilizer Engine design and systems integration for propfan and Systems Certification p 650 A87-42855 high bypass turbofan engines [NASA-CP-2474] p 625 N87-25267 BOEING 727 AIRCRAFT [AIAA PAPER 87-1730] p 665 A87-45169 Avionics systems for future civil helicopters UDF/727 flight test program Navier-Stokes analysis of a very-high-bypass-ratio [MBB.UD-473/86] p 662 N87-26838 [AIAA PAPER 87-1733] p 666 A87-45171 AXIAL FLOW turbofan engine in reverse thrust BOMBER AIRCRAFT Tip clearance flows. I - Experimental investigation of [AIAA PAPER 87-2170] p 697 A87-45450 Use of RPM trim to automate the supersonic engine/inlet an isolated rotor. II - Study of various models and match in the SR-71A comparison with test results p 638 A87-46208 [AIAA PAPER 87-1848] p 667 A87-45248 C AXIAL FLOW TURBINES BOUNDARY LAYER COMBUSTION An experimental investigation of turbine case CABIN ATMOSPHERES treatments Application of low-Reynolds-number K-epsilon model to solid fuel turbulent boundary layer combustion Air cycle environmental control system for helicopters [AIAA PAPER 87-1919] p 669 A87-45299 - A trade-oft study p 654 A87-43472 AX|SYMMETRIC FLOW [AIAA PAPER 87-1778] p 690 A87-45198 CABINS Estimation of spillage drag for a wide range of BOUNDARY LAYER CONTROL Prediction and control of transition in hypersonic Burning questions --- tiroworthiness of aircraft cabin axisymmetric intakes at M 1 materials p 646 A87-46373 boundary layers [ESDU-84004] p 701 N87-26301 CALIBRATING [AIAA PAPER 87-1414] p 632 A87-44946 A miniature remote deadweight calibrator BOUNDARY LAYER EQUATIONS p 694 A87-45104 B Improvement of aerodynamic calculation on S(2)m Miniature remote dead weight calibrator stream surface of axial compressor by using of annulus [NASA.CASE-LAR-13564-1] p 700 N87-25558 B-1 AIRCRAFT wall bounda W layer calculation p 639 A87-46216 The treatment of calibrations of total air temperature Correlation of B-1 flight test subjective assessments and BOUNDARY LAYER FLOW some ride quality/vibration exposure criteria probes for use in flight-test analysis work Rotor wake segment influence on stator-surface lAD-A179844] p 658 N87-25318 [ESDU-84007] p 701 N87-26324 boundary layer development in an axial-flow compressor B-7O AIRCRAFT CANADAIR AIRCRAFT stage An experimental investigation of dynamic ground Flying the CF-18 Hornet p 656 A87-46313 [AIAA PAPER 87-1741] p 695 A87-45178 effect CANARD CONFIGURATIONS Laminar separation bubble characteristics on an airfoil [NASA-CR-180560] p 659 N87-26036 Expanding tilt rotor capabilities p 651 A87-43407 BEARINGLESS ROTORS at low Reynolds numbers p 641 A87-46778 Canard configurations BOUNDARY LAYER SEPARATION Aeroalastic stability of a bearingless circulation control [ETN-87-99914] p 659 N87-26039 CARBON rotor in forward flight p 652 A87-43443 Unsteady separation characteristics of airfoils operating Substantiation of the analytical prediction of ground and under dynamic stall conditions p 628 A87-43421 Exhaust carbon - The effects of fuel composition p 676 A87-46253 air resonance stability of a bearingless rotor, using model Viscid/inviscid separated flows scale tests p 654 A87-43463 lAD-At79858] p 699 N87-25536 CARBON FIBER REINFORCED PLASTICS Development of novel bearingless rotor systems BOUNDARY LAYER STABILITY Prospects for the use of composites in civil aircraft p 655 A87-44577 [MBB-UD-471/86] p 702 N87-26837 Stationary disturbances in three-dimensional boundary A310-300 CFRP fin Damage tolerance BEARINGS layers over concave surfaces demonstration p 655 A87-44594 FEL - A new main rotor system p 651 A87-43402 [AIAA PAPER 87-1412] p 632 A87-44945 Design of a composite tail for the Airbus A-320 BENDING MOMENTS Stability and transition in supersonic boundary layers [MBB-UT-12-86] p 658 N87-25316 Determination of the structural properties of helicopter [AIAA PAPER 87-1416] p 632 A87-44947 A3t0-300 CFRP fin damage tolerance demonstration rotor blades by theoretical and experimental methods Linear stability analysis of three-dimensional p 653 A87-43450 [MBB-UT-015/86] p 658 N87-25317 compressible boundary layers p 640 A87-46504 BENDING VIBRATION Effects of impact loading on carbon fiber reinforced Influence of a heated leading edge on boundary layer The influence of the induced velocity distribution and structures growth, stability and transition the flapping-lagging coupling on the derivatives of the rotor [MBB-Z-83/86] p 691 N87-25436 [DE87-008516] p 700 N87-25538 and the stability of the helicopter p 679 A87-43436 Development and testing of critical components for the BOUNDARY LAYER TRANSITION Complex modal balancing of flexible rotors including technological preparation on an Airbus fuselage made of The effect of trip wire roughness on the performance residual bow carbon fiber reinforced plastics, phase 1 of the Wortmann FX 63-137 airfoil at low Reynolds [AIAA PAPER 87-1840] p 695 A87-45241 [BMFT-FB-W-86-017] p 692 N87-26151 numbers p629 A87-44019 BLADE TIPS CASCADE FLOW Application of a 3D Euler code to transonic blade tip Prediction and control of transition in hypersonic Calculation of the boundary layer at the inlet section flow p 628 A87-43419 boundary layers of a compressor cascade p 629 A87-43608 [AIAA PAPER 87-1414] p 632 A87-44946 An experimental investigation of turbine case Development of a viscous cascade code based on scalar treatments Stability and transition in supersonic boundary layers implicit factorization [AIAA PAPER 87-1919] p 669 A87-45299 [AIAA PAPER 87-1416] p 632 A87-44947 [AIAA PAPER 87-2150] p 637 A87-45435 Tip clearance flows. I - Experimental investigation of The air-injection method of fixing boundary-layer Navier-Stokes solutions for highly loaded turbine an isolated rotor. II - Study of various models and transition and investigating scale effects cascades comparison with test results p 638 A87-46208 p 639 A87-46264 [AIAA PAPER 87-2151] p 637 A87-45436 Application of a three-dimensional Euler code to Influence of a heated leading edge on boundary layer The role of short duration facilities in gas turbine transonic blade tip flow --- helicopter rotors growth, stability and transition research p 685 A87-46222 [MBB-UD-482/86] p 642 N87-25299 [DE87-008516] p 700 N87-25538 Flow phenomena in transonic turbine cascades detailed Effect of planform taper on hover performance of an An experimental low Reynolds number comparison of experimental and numerical investigation advanced AH*64 model rotor a Wortmann FX67-Kt70 airfoil, a NACA 0012 airfoil and p 639 A87-46223 [NASA-TM-89145] p 643 N87-25304 a NACA 64-210 airfoil in simulated heavy rain Aeroelasticity in turbomachines comparison of Velocity measurements near the blade tip and in the [NASA-CR-181119] p644 N87-25997 theoretical and experimental cascade results. Appendix tip vortex core of a hovering model rotor Measurement of the effect of manufacturing deviations A5: All experimental and theoretical results for the 9 p 645 N87.26030 on natural laminar flow for a single engine general aviation standard configurations BLADES airplane [AD-A180534] p 677 N87-25326 [NASA-CR-180671] p 677 N87-26044 Preliminary structural design of composite main rotor CAVITATION FLOW BOUNDARY LAYERS blades for minimum weight A unique measurement technique to study Study on the interference between the local separation [NASA-TP-2730] p 691 N87-25435 laminar-separation bubble characteristics on an airfoil on a wing surface and outer flow-field BLOWDOWN WIND TUNNELS [AIAA PAPER 87-1271] p 631 A87-44921 p 634 A87-45094 CAVITIES The role of short duration facilities in gas turbine BOUNDARY VALUE PROBLEMS Aero-optical analysis of compressible flow over an open research p 685 A87-46222 Numerical simulation of flows in axial and radial The 0.6 m x 0.6 m trisonic section (TMK) of DFVLR in cavity turbomachines using Euler solvers [AIAA PAPER 87-1399] p 632 A87-44943 Celogne-Porz, West Germany [ONERA, TP NO. 1987°87] p 641 A87-46776 [DFVLR-MITT-86-21 ] p 687 N87-26053 CENTERBODIES Computational fluid dynamics applications at McDonnel A multi-body aircraft with an all-movable center fuselage The vertical test section (VMK) of DFVLR in Douglas p 701 N87-26007 Celogne-Por-z, West Germany --- wind tunnel BRACKETS actively controlling fuselage pressure drag [DFVLR-MITT-86-22] p 688 N87-26054 Airfoil flutter model suspension system [NASA-CASE-LAR-13511-1] p 658 N87-25920 BLOWING [NASA-CASE*LAR-13522-1-SB] p 687 N87-25334 CENTRIFUGAL COMPRESSORS The use of discrete vortices to predict lift of a circulation BREADBOARD MODELS The design of low-stress/high performance centrifugal control rotor section with a trailing edge blowing slot Portable fuel leak detector impellers p 627 A87-43416 lAD-A180095] p 700 N87-25550 [AIAA PAPER 87-2099] p 697 A87-45405

A-6 SUBJECT iNDEX COMPRESSOR BLADES

Performance prediction in a centrifugal compressor COAXIAL FLOW APU fuel efficiency and affordability for commercial impeller p 674 A87-46190 Mathematical model for calculating the atomization of aircraft 3-D viscous flow calculations at design and oft-design a liquid jet by an annular gas stream [AIAA PAPER 87-1907] p 669 A87-45290 conditions for the NACA 48-inch radial-inlet centrifugal p 693 A87-43610 Engine variable geometry effects on commercial COCKPIT SIMULATORS impeller p 638 A87-46191 supersonic transport development Investigation of the three dimensional flow near the exit Some fundamentals of simulator cockpit motion [AIAA PAPER 87-2101] p 672 A87-45406 of two backswept transonic centrifugal impellers generation p 683 A87-44714 Fokker 50 - Pedigree with power p 656 A87-45647 COCKPITS p 638 A87-46192 Civil propulsion technology for the next twenty-five Transonic stream function solution on S(2) EH101 cockpit design p 661 A87-43404 years p 624 A87-46!77 CODES streamsurface for a high pressure ratio centrifugal Propfan propulsion system development Time modulation. II - Scheme codes avoidance compressor p 638 A87-46195 p 675 A87-46247 CERAMIC COATINGS maneuvers for aircraft p 649 A87-44845 Advances in technology for low cost turbomachine_ - Application of ceramics to ramjet engine nozzles COLD GAS A potential to enhance the economy of future propulsion p 690 A87-46221 Influence of vane/blade spacing and cold-gas injection system for general and helicopter aviation CERAMICS on vane and blade heat-flux distributions for the Teledyne p 676 A87-46261 Durability characterization of ceramic materials for gas 702 HP turbine stage Proving that Avanti stands for progress turbines p 690 A87-45898 [AIAA PAPER 87-1915] p 669 A87-45295 p 656 A87-46314 CERTIFICATION COLLISION AVOIDANCE Icing clearance criteria for UK military helicopters Testing automated ground collision avoidance systems Dornier 328 - Concept for a new-generation regional p 646 A87-44705 on the AFTI/F-16 p 660 A87-43375 airliner p 657 A87-46326 Icing clearances on civil helicopters - Unheated and An airborne collision avoidance system o The TCAS Technological aspects in preparing the development of heated blades p 646 A87-44707 p 649 A87-44231 regional airliners p 657 A87-46327 CH-47 HELICOPTER Time modulation. II - Scheme codes avoidance Project for an intelligent system for on-line trouble Development of the Chinook helicopter rotor blade maneuvers for aircraft p 649 A87-44845 shooting p 705 A87-46365 COLOR VISION de-icing system p 655 A87-44704 EH.101 - The helicopter matures p 657 A87-46371 Colour dependence and surplus information in airport Identification of a dynamic model of a helicopter from Burning questions --- fireworthiness of aircraft cabin visual aids during VFR operations p 649 A87-44040 flight tests p 659 N87-26040 materials p 646 A87-46373 CHEMICAL REACTIONS COMBUSTIBLE FLOW New standards established for realism in visual Computational chemistry p 706 N87-26023 Simulations of ramjet combustor flow fields. I - Numerical simulation --- for commercial aircraft flight CIRCUIT RELIABILITY model, large-scale and mean motions p 686 A87-46438 A rugged electronic pressure scanner designed for [AIAA PAPER 87-1421] p 633 A87-44949 Annual review of aircraft accident data. US air carder turbine test p 695 A87-45124 Combustion-genereted turbulence in practical CIRCULAR CYLINDERS combustors operations calendar year 1983 [PB87-160628] p 648 N87-25311 Unsteady viscous flows round moving circular cylinders [AIAA PAPER 87-1721] p 665 A87-45161 COMMUNICATION NETWORKS and airfoils. II p 637 A87-45792 A mixing augmentation technique for hypervelocity Determination of the local heat transfer characteristics scram jets Conformal microstrip communication antenna on glaze ice accretions on a cylinder and a NACA 0012 [AIAA PAPER 87-1882] p 668 A87-45275 p 697 A87-45689 airfoil Studies of scramjet flowfields COMPONENT RELIABILITY [AD-At79931] p 647 N87-25309 [AIAA PAPER 87-2161] p 688 A87-45443 Calculation of the reliability of aircraft-engine parts under CIRCULATION CONTROL ROTORS COMBUSTION CHAMBERS repeated static loading p 664 A87-43616 The use of discrete vortices to predict lift of a circulation Numerical study of the gasdynamic process in a pulsejet Application of engine component life methodology to control rotor section with a trailing edge blowing slot engine p 663 A87-43614 life assessment p 698 A87-46230 p 627 A87-43416 Simulations of ramjet combusior flow fields. I- Numerical COMPOSITE MATERIALS model, large-scale and mean motions Aeroelastic stability of a bearingless circulation control FEL - A new main rotor system p 651 A87-43402 rotor in forward flight p 652 A87-43443 [AIAA PAPER 87-1421] p 633 A87-44949 Materials in aerospace; Proceedings of the First Extension of local circulation method to counter rotation Simulations of ramjet combustor flow fields. II - Origin International Conference, London, England, Apr. 2-4,1986. of pressure oscillations propeller Volumes 1 & 2 p 689 A87-44729 [AIAA PAPER 87-1891] p 635 A87-45280 [AIAA PAPER 87-1422] p 633 A87-44950 Materials in helicopters - A review CIRCULATION DISTRIBUTION Combustion-genereted turbulence in practical p 624 A87*44731 A prescribed radial distribution circulation of a hovering combustors Preliminary structural design of composite main rotor rotor blade p 627 A87-43414 [AIAA PAPER 87-1721] p 665 A87-45161 CIVIL AVIATION Design and test verification of a combustion system for blades for minimum weight [NASA-TP-2730] p 691 N87-25435 The new Annex 17 - The latest contribution by an advanced turbolan engine international civil aviation to the battle against terrorism [AIAA PAPER 87-1826] p 666 A87-45231 Flight service evaluation of advanced composite ailerons p 708 A87-42860 The influence of dilution hole aerodynamics on the on the L-1011 transport aircraft Interception of civil aircraft vs. misuse of civil aviation temperature distribution in a combustor dilution zone [NASA-CR-178321] p 691 N87-25439 p 708 A87-42861 [AIAA PAPER 87-1827] p 666 A87-45232 COMPOSITE STRUCTURES Airlines are exempt from law on rights of the disabled Pressure oscillations and acoustic-entropy interactions Prospects for the use of composites in civil aircraft p 709 A87-42863 in ramjet combustion chambers p 655 A87-44577 Prospects for the use of composites in civil aircraft [AIAA PAPER 87-1872] p 668 A87-45267 A decade of composite rudder service reviewed p 655 A87-44577 NASA/GE advanced low emissions combustor p 689 A87-44861 Civil propulsion technology for the next twenty-five program Design for repairability of helicopter rotor blades years p 624 A87-46177 [AIAA PAPER 87-2035] p 671 A87-45369 [MBB-UD-491186] p 658 N87-25315 Annual review of aircraft accident data. US air carrier Diagnostic methods for air-breathing engines Dynamic mechanical properties of advanced composite operations calendar year 1983 p 686 A87-46243 materials and structures: A review p 691 N87-25988 [PB87-160628] p 648 N87-25311 Exhaust carbon - The effects of fuel composition COMPRESSIBLE BOUNDARY LAYER Measurement of the effect of manufacturing deviations p 676 A87-46253 Prediction and control of transition in hypersonic on natural laminar flow for a single engine general aviation Numerical simulation of diffusor/combuator dome boundary layers airplane interaction p 676 A87-46255 [AIAA PAPER 87-1414] p 632 A87-44946 [NASA-CR-180671] p 677 N87-26044 Pressure scaling effects in a scramjet combustion Linear stability analysis of three-dimensional First approximation to landing field length of civil chamber p 676 A87o46258 compressible boundary layers p 640 A87-46504 transport aeroplanes (50 ft., 15.24 m screen) COMBUSTION CHEMISTRY COMPRESSIBLE FLOW [ESDU-84040] p 688 N87-26056 NO(x) reduction and combustion phenomena in the Effect of swirl on the performance of a radial vaneless CLASSIFICATIONS multi-annular gas turbine swirl burner diffuser with compressible flow at Mech numbers of 0.7 Classification of the load-carrying capacity of runway [AIAA PAPER 87-2036] p 671 A87-45370 and 0.8 surfaces by the ACN-PCN method. I COMBUSTION EFFICIENCY [ASME PAPER 86-WA/FE-6] p 629 A87-43704 p 686 A87-46353 APU fuel efficiency and aflordability for commercial Aero-optical analysis of compressible flow over an open CLEAN FUELS aircraft cavity NASA/GE advanced low emissions combustor [AIAA PAPER 87-1907] p 669 A87-45290 [AIAA PAPER 87-1399] p 632 A87-44943 A method for the calculation of the interaction of a program Effects of scale on supersonic combustor turbulent boundary layer with a shock wave [AIAA PAPER 87-2035] p 671 A87-45369 performance CLEAR AIR TURBULENCE p 639 A87-46238 [AIAA PAPER 87-2164] p 672 A87-45444 Compressible flows in the wakes of a square cylinder History of wind shear turbulence models COMBUSTION STABILITY and thick symmetrical airfoil arranged in tandem p 703 N87-25269 Vortex-nozzle interactions inramjet combustors Wind shear and turbulence simulation p 641 A87-46922 [AIAA PAPER 87-1871] p 668 A87-45266 p 703 N87-25274 COMPRESSION LOADS COMMERCIAL AIRCRAFT Turbulence models p 703 N87-25277 Fatigue and fracture mechanics analysis of compression CLOSE PACKED LATTICES Interception of civil aircraft vs. misuse of civil aviation loaded aircraft structure p 692 A87-42854 p 708 A87-42861 High temperature titanium alloys p 689 A87-44739 COMPRESSIVE STRENGTH CLOUD GLACIATION Technological change and skill requirements - A case Truss-core corrugation for compression loads Comparison of wet and dry growth in artificial and flight study of numerically controlled riveting in commercial [NASA-CASEoLAR-13438-1] p 699 N87-25496 icing conditions p 646 A87-45635 aircraft manufacture COMPRESSOR BLADES CLOUDS (METEOROLOGY) [ASME PAPER 86-WA/TS-2] p 623 A87-43723 Failure analysis of a large wind tunnel compressor Experiences with hot-wire instruments for the Countdown to the propfan p 664 A87-44272 blade p 692 A87-42852 measurement of the liquid water content in clouds Icing clearances on civil helicopters - Unheated and Erosion problem of axial compressor blades of a [DFVLR-MITT-86] p 704 N87.26476 heated blades p 646 A87-44707 turboshaft engine p 675 A87-46246

A-7 SUBJECT INDEX COMPRESSOR ROTORS

COMPRESSOR ROTORS Unsteady viscous flows round moving circular cylinders COMPUTER AIDED MANUFACTURING A study of some factors affecting the performance of and airfoils. II p 637 A87-45792 Automated systems for the. manufacture of Airbus vertical stabilizers a contra-rotating axial compressor stage A computational method for determining flowfield p 639 A87-46211 properties when the pitot pressure is the only measured ]MBB-UT-17-86] p 705 N87-25786 COMPUTER GRAPHICS Expandable turbojet compressor design, test and instream property p 637 A87-46184 development p 674 A87-46212 3-D viscous flow calculations at design and off-design Survey of currently available high-resolution raster COMPRESSORS conditions for the NACA 48-inch radial-inlet centrifugal graphics systems Dynamic data acquisition, reduction, and analysis for impeller p 638 A87-46191 [NASA-TM-89139] p 705 N87-25771 COMPUTER PROGRAMS the identification of high-speed compressor component Transonic stream function solution on S(2) Operational engine usage and mission analysis pest-stability characteristics streamsorfaco for a high pressure ratio centrifugal [AIAA PAPER 87.2097] p 671 A87-45404 [AIAA PAPER 87-2089] p 697 A87-45398 compressor p 638 A87-46195 COMPUTATIONAL CHEMISTRY Improvement of aerodynamic calculation on S(2)m Modeling and implementation of wind shear data Computational chemistry p 706 N87-26023 stream surface of axial compressor by using of annulus p 709 N87-25273 COMPUTATIONAL FLUID DYNAMICS wall boundary layer calculation p 639 A87-46216 COMPUTER SYSTEMS PROGRAMS Three-dimensional problems in computational fluid Flow phenomena in transonic turbine cascades detailed Standardization and logistic support cost effectiveness of advanced avionics systems p 661 A87-43468 dynamics --- Russian book p 693 A87-42916 experimental and numerical investigation An interactive approach to surface-fitting complex p 639 A87-46223 Design of motion simulation software with digital filtering techniques p 704 A87-44712 geometries for flowfield applications Validation of aerodynamic measurement techniques and [AIAA PAPER 87-1476] p 625 A87-43009 calculation methods for high-lift systems Analysis of typical fault-tolerant architectures using A computational study of the flowfieid surrounding the p 640 A87-46363 HARP p 704 A87-45771 Aeroassist Flight Experiment vehicle Unear stability analysis of throe-dimensional The Aeronautical Research Institue (FFA) wing body 85 [AIAA PAPER 87-1575] p626 A87-43084 compressible boundary layers p 640 A87-46504 computer program. A panel method for determination of aeroelastic characteristics applying direct block iterative Time-consistent pressure relaxation procedure for Unsteady viscous-inviscid interaction method and compressible reduced Navier-Stokes equations computation of buffeting over airfoils solution techniques p 626 A87-43377 [ONERA, TP NO. 1987-58] p 640 A87-46759 [FFA-TN-1986-28] p 642 N87-25298 Computation of unsteady transonic aerodynamics with Numerical simulation of flows in axial and radial Development of a geometry handling program for the truncation error injection p 627 A87-43392 turbomschines using Euler solvers FFA subsonic higher order panel method Computation of the flow fields of propellers and hovering [ONERA, TP NO. 1987-87] p 641 A87-46776 [FFA.TN-1985-48] p 699 N87-25534 COMPUTERIZED SIMULATION rotors using Euler equations p 628 A87-43418 Entrainment effect of a leading-edge vortex Numerical simulation and comparison with experiment Unsteady separation characteristics of airfoils operating p 641 A87-46777 for self-excited oscillations in a diffuser flow under dynamic stall conditions p 628 A87-43421 Aerodynamic study of a helicopter rotor in hovering flight The use of computer models in helicopter drag - Theory vs. experiment p 641 A87-47014 p 693 A87-43381 prediction p 628 A87-43424 Viscid/inviscid separated flows The use of computer models in helicopter drag Navier-Stokes simulation of a hypersonic generic [AD-A179858] p 699 N87.25536 prediction p 628 A87-43424 Realization and flight testing of a model following control wing/fuselage Detailed near-wake flowfield surveys with comparison [AIAA PAPER 87-1192] p 629 A87-44902 to an Euler method of an aspect ratio 4 rectangular wing system for helicopters p 679 A87-43440 Advances in the computation of transonic separated [NASA-TM-89357] p 644 N87-25993 The numerical simulation of subsonic flutter flows over finite wings An experimental low Reynolds number comparison of [AIAA PAPER 87-1428] p 633 A87-44952 [AIAA PAPER 87-1195] p 630 A87-44904 a Wortmann FX67-Kt70 airfoil, a NACA 0012 airfoil and Complex medal balancing of flexible rotors including Simulation of transonic viscous flow over a fighter-like a NACA 64-210 airfoil in simulated heavy rain residual bow configuration including inlet [ NASA.CR-181 t 19 ] p 644 N87-25997 [AIAA PAPER 87-1840] p 695 A87-45241 [AIAA PAPER 87-1199] p 630 A87-44906 Computational fluid dynamics: Transition to design Simulation of performance, behaviour and faults of Numerical simulation of vortical flows over a strake-delta applications p 700 N87-26004 aircraft engines wing CFD applications: The Lockheed perspective [AIAA PAPER 87-1868] p 668 A87-45263 [AIAA PAPER 87-1229] p 630 A87-44913 p 644 N87-26005 Optimal cooperative control synthesis of active Incompressible Navier-Stokes computations of vortical Development and application of unified algorithms for displays flows over double-delta wings problems in computational science p 705 N87-26006 [NASA-CR-4058] p 705 N87-25807 [AIAA PAPER 87-1341] p 631 A87-44933 Computational fluid dynamics applications at McDonnel Computational chemistry p 706 N87-26023 Vor'tax breakdown simulation Douglas p 701 N87.26007 An investigation of helicopter higher harmonic control [AIAA PAPER 87-1349] p 632 A87-44934 Application of computational physics within Northrop using a dynamic system coupler simulation Prediction and control of transition in hypersonic p 706 N87-26008 p 682 N87-26051 boundary layers Application of CFD cedes to the design and development CONCENTRATION (COMPOSITION) [AIAA PAPER 87-1414] p 632 A87-44946 of propulsion systems p 677 N87-26009 Diagnostics in supersonic combustion [AIAA PAPER 87-1787] p 690 A87-45202 Stability and transition in supersonic boundary layers Computational fluid dynamics research at the United CONFERENCES [AIAA PAPER 87-1416] p 632 A87-44947 Technologies Research Center requiring Simulations of ramjet combustor flow fields. II - Origin supercomputers p 701 N87-26011 Case histories involving fatigue and fracture mechanics; of pressure oscillations Computational analysis of hypersonic airbreathing Proceedings of the Symposium, Charleston, SC, Mar. 21, [AIAA PAPER 87-1422] p 633 A87-44950 aircraft flow fields p 645 N87-260f 9 22, 1985 p 692 A87-4285t Helicopter Rotor Icing Symposium, London, England, Numerical investigation of the flow structure around a Experience with 3-D composite grids rapidly pitching airfoil p 706 N87-26021 Jan. 14, 1986, Proceedings p 646 A87-44701 [AIAA PAPER 87-1424] p 633 A87-44951 Numerical solution of the Navier.Stokes equations about Materials in aerospace; Proceedings of the First International Conference, London, England, Apr. 2-4,1986. The numerical simulation of subsonic flutter throe-dimensional configurations: A survey [AIAA PAPER 87-1428] p 633 A87-44952 p 701 N87.26022 Volumes 1 & 2 p 689 A87-44729 Two-dimensional numerical analysis for inlets at COMPUTATIONAL GRIDS Radar Technology 1986; Symposium, 6th, Bremen, West subsonic through hypersonic speeds An interactive approach to surface-fitting complex Germany, Nov. 4-6, 1986, Reports p 697 A87-45876 International Symposium on Air Breathing Engines, 8th, [AIAA PAPER 87-1751] p 634 A87-45184 geometries for flowtield applications Numerical analysis of peak heat transfer rates for [AIAA PAPER 87-1476] p 625 A87-43009 Cincinnati, OH, June t4-19, 1987, Proceedings hypersonic flow over a cowl leading edge Transonic analysis of the F.16A with under-wing fuel p 673 A87-46176 [AIAA PAPER 87-1895] p 635 A87-45283 tanks - An application of the TranAir full-potential code CONICAL CAMBER Aerodynamic and heat transfer analysis of the low aspect [AIAA PAPER 87-1198] 'p630 A87-44905 Study of lee-side flows over conically cambered Delta ratio turbine Development of a viscous cascade code based on scalar wings at supersonic spoeds, part 2 [AIAA PAPER 87-1916] p 696 A87-45296 implicit fectorization [NASA.TP-2660-PT-2] p 643 N87-25301 Three-dimensional numerical predictions of the flow [AIAA PAPER 87-2150] p 637 A87-45435 CONTACT LOADS behind a rearward-facing-step in a supersonic combustor Computational fluid dynamics applications at McDennel Selection of admissible contact stresses for toothed [AIAA PAPER 87-1962] p 636 A87-45332 Douglas p 701 N87.26007 gears of aircraft engines p 663 A87-43605 Application of computational fluid dynamics to analysis Experience with 3-D composite grids CONTINGENCY of exhaust gas/diffuser interactions in a turbine engine p 706 N87-26021 Contingency power for small turboshaft engines using altitude test cell COMPUTER AIDED DESIGN water injection into turbine cooling air [AIAA PAPER 87-2014] p 670 A87-45354 Parameters of optimal planetary gears of AI type [AIAA PAPER 87-1906] p 668 A87-45289 An improved computational model for a scramjet p 694 A87.43622 CONTRAROTATING PROPELLERS propulsion system Simulation of performance, behaviour and faults of UDF/727 flight test program [AIAA PAPER 87-2078] p 671 A87-45393 aircraft engines [AIAA PAPER 87-1733] p 666 A87-45171 A stage-by-stage pest.stall compression system [AIAA PAPER 87o1868] p 668 A87-45263 Flow behind single- and dual-rotation propellers at angle modeling technique Application of a 3D inviscid rotational design procedure of attack [AIAA PAPER 87-2088] p 636 A87-45397 for turbomachinery bladings p 638 A87-46204 [AIAA PAPER 87.1750] p 634 A87-45183 Development of a viscous cascade code based on scalar Trends in the aeroelastic analysis of combat aircraft A panel method for counter rotating propfans implicit tacterization p 657 A87-46362 [AIAA PAPER 87-1890] p 668 A87-45279 [AIAA PAPER 87-2150] p 637 A87-45435 CFD applications: The Lockheed perspective Extension of local circulation method to counter rotation Navier-Stokes solutions for highly loaded turbine p 644 N87-26005 cascades Development and application of unified algorithms for propeller [AIAA PAPER 87-1891] p635 A87-45280 [AIAA PAPER 87-2151] p 637 A87-45436 problems in computational science p 705 N87-26006 A study of some factors affecting the performance of Studies of scramjet flowfields Design applications for supercomputers [AIAA PAPER 87-2161] p 688 A87-45443 p 706 N87-26010 a contra-rotating axial compressor stage Performance estimation of an aircraft internal Industrial application of computer aided structural p 639 A87-46211 combustion engine optimization in aircraft construction Study of the aerodynamics of high-speed propellers [AIAA PAPER 87-2173] p 672 A87-45453 [MBB-UT-273/86] p 706 N87-26523 [ONERA, TP NO. 1987-61] p 640 A87-46761

A-8 SUBJECT INDEX DIAGNOSIS

CONTROL CONFIGURED VEHICLES National Aerospace Plane Program: Principal Dynamic data acquisition, reduction, and analysis for Design of CCV flight control system of STOL flying assumptions, findings and policy options the identification of high-speed compressor component beat p 680 A87-45097 [RAND/P-7288-RGS] p 625 N87-25990 post-stability characteristics CONTROL EQUIPMENT COSTS [AIAA PAPER 87-2089] p 697 A87-45398 Simulator evaluations of inceptors for ACT helicopters Materials for structures of the future DATA BASES p 678 A87-43405 p 689 A87-44745 Flight duration, airspeed practices and altitude COUNTER ROTATION Auxiliary data input device management of airplanes involved in the NASA VGH [NASA-CASE-LAR-13626-1] p 700 N87-25584 Performance calculation of counter rotation propeller General Aviation Program CONTROL STABILITY [AIAA PAPER 87-1889] p 635 A87-45278 [NASA-TM-89074] p 625 N87-25293 A panel method for counter rotating propfans Dual adaptive control: Design principles and DATA CORRELATION [AIAA PAPER 87-1890] p 668 A87-45279 applications Experimental data correlations for the effects of rotation Extension of local circulation method to counter rotation [NASA-CR-181050] p 705 N87.25804 on impingement cooling of turbine blades propeller CONTROL SYSTEMS DESIGN [AIAA PAPER 87-2008] p 696 A87-45349 [AIAA PAPER 87-1891] p 635 A87-45280 Scan stabilization and jitter control for an airborne Correlation of B-1 flight test subjective assessments and COWLINGS some ride quality/vibration exposure criteria telescope p 660 A87-42812 Numerical analysis of peak heat transfer rates for [AD-A179844] p 658 N87-25318 Expanding tilt rotor capabilities p 651 A87-43407 hypersonic flow over a cowl leading edge DATA PROCESSING Realization and flight testing of a model following control [AIAA PAPER 87-1895] p 635 A87-45283 Design of an automated information-processing system for helicopters p 679 A87-43440 CRACK ARREST system p 704 A87-44241 The model inverse as an element of a manoeuvre Fracture of an aircraft horizontal stabilizer Dynamic data acquisition, reduction, and analysis for demand system for helicopters p 679 A87-43441 p 650 A87-42855 the identification of high-speed compressor component Development of an experimental system for active CRACK PROPAGATION post*stability characteristics control of vibrations on helicopters p 679 A87-43447 Failure analysis of a large wind tunnel compressor blade p 692 A87-42852 [AIAA PAPER 87-2089] p 697 A87-45398 Development program of a full authority digital electronic Fatigue crack growth predictions of welded aircraft DATA PROCESSING EQUIPMENT control system for the T55.L-712E turboshaft engine Model-based knowledge-based optical processors p 663 A87-43465 structures containing flaws in the residual stress field p 692 A87-42853 p 707 A87-42736 Highly reliable, microprocessor-based engine control Fatigue and fracture mechanics analysis of compression DATA REDUCTION [AIAA PAPER 87-1927] p 669 A87-45305 loaded aircraft structure p 692 A87-42854 The pitching damping derivatives measured by Validation of an integrated flight and propulsion control Fracture of an aircraft horizontal stabilizer foroe-oscillation method at transonic and supersonic wind design for fighter aircraft p 650 A87.42855 tunnel p 686 A87-46958 [AIAA PAPER 87-1928] p 680 A87-45306 Aircraft structural maintenance recommendations based DATA TRANSMISSION Digital control development for the T56-A-427 on fracture mechanics analysis p 623 A87-42857 Auxiliary data input device [AIAA PAPER 87-2013] p 670 A87-45353 Crack growth prediction in 3D structures under [NASA-CASE-LAR.13626-1] p 700 N87-25584 CONTROL THEORY aeronautical-type spectrum Ioadings DC 10 AIRCRAFT A combined stochastic feedforward and feedback [ONERA, TP NO. 1987-79] p 691 A87-46772 A decade of composite rudder service reviewed control design methodology with application to autoland Analytical description of crack resistance curves for p 689 A87-44861 design aluminum sheets used in aircraft construction DEFECTS [NASA-CR.4078] p 705 N87-25806 [MBB-UT-133/85] p 700 N87-25604 Fatigue crack growth predictions of welded aircraft Optimal cooperative control synthesis of active CRASH LANDING structures containing flaws in the residual stress field displays KRASH analysis correlation. Transport airplane p 692 A87-42853 [NASA-CR-4058] p 705 N87-25807 controlled impact demonstration test DEGREES OF FREEDOM [AD-A179906] p 647 N87.25308 Singular trajectories in airplane cruise-dash Some fundamentals of simulator cockpit motion CRASHWORTHINESS optimization generation p 683 A87-44714 Crash response data system for the controlled impact [NASA-CR-180636] p 659 N87-26035 DEICING CONTROLLABILITY demonstration (CID) of a full scale transport aircraft Helicopter rotor icing protection methods Study of helioepterroll control effectiveness criteria p 694 A87-45123 p 654 A87-44256 [NASA-CR-177404] p 681 N87-25330 KRASH analysis correlation. Transport airplane Development of the Chinook helicopter rotor blade CONTROLLERS controlled impact demonstration test de-icing system p 655 A87-44704 Control of aircraft under severe wind shear conditions lAD-At79906] p 647 N87-25308 Influence of a heated leading edge on boundary layer p 682 N87-26050 Integrally-stiffened crash energy-absorbing subfloor CONVECTIVE HEAT TRANSFER beam structure growth, stability and transition Determination of the local heat transfer characteristics [DE87-008516] p 700 N87-25538 [NASA.CASE-LAR-13697-1] p 659 N87-25321 DELTA WINGS on glaze ice accretions on a cylinder and a NACA 0012 CROSS FLOW airfoil Numerical simulation of vortical flows over a strake-delta Study on the interference between the local separation [AD-A179931] p 647 N87-25309 wing on a wing surface and outer flow.tield CONVENTIONS [AIAA PAPER 87-1229] p 630 A87-44913 p 634 A87-45094 The Warsaw Convention system regarding air carrier Experimental study of the vortex flow behavior on a CRUISING FLIGHT responsibility - New developments in jurisprudence generic fighter wing at subsonic and transonic speeds Performance seeking control for cruise optimization in p 709 A87-42864 [AIAA PAPER 87-t262] p 631 A87-44920 CONVERGENT-DIVERGENT NOZZLES fighter aircraft Incompressible Navier-Stokes computations of vortical [AIAA PAPER 87-1929] p 681 A87-45307 Static investigation of post-exit vanes for multiaxis thrust flows over double-delta wings vectoring Singular trajectories in airplane cruise-dash [AIAA PAPER 87-1341] p 631 A87-44933 [AIAA PAPER 87-1834] p 667 A87-45236 optimization Investigation of a delta-wing fighter model flow field at COOLING [NASA-CR-t80636] p 659 N87-26035 transonic speeds Friction factors and heat transfer coefficients in CRYOGENIC EQUIPMENT [AIAA PAPER 87-1749] p 634 A87-45182 turbulated cooling passages of different aspect ratios. I - A miniature remote deadweight calibrator Entrainment effect of a leading-edge vortex Experimental results p 694 A87-45104 p 641 A87-46777 [AIAA PAPER 87.2009] p 696 A87-45350 CRYOGENIC WIND TUNNELS Control of the discrete vortices from a delta wing CORROSION PREVENTION Miniature remote dead weight calibrator p 641 A87-46779 A study of the thermal-stress state of gas turbine engine [NASA-CASE-LAR-13564-1] p 700 N87-25558 An experimental investigation of delta wings with blades with protective coatings p 664 A87-43640 CURVE FrrrlHG leading-edge vortex separation p 641 A87-46956 Corrosion protection --- in aircraft structures An interactive approach to surface-fitting complex Subsonic wind-tunnel measurements of a slender p 624 A87-44750 geometries for flowfield applications wing-body configuration employing a vortex flap CORRUGATED PLATES [AIAA PAPER 87-1476] p 625 A87-43009 [NASA-TM-89101] p 642 N87-25295 Truss-core corrugation for compression loads CYLINDERS Study of lee-side flows over conically cambered Delta [NASA-CASE-LAR-13438-1 ] p 699 N87-25496 Compressible flows in the wakes of a square cylinder wings at supersonic speeds, part 2 COST ANALYSIS and thick symmetrical airfoil arranged in tandem [NASA-TP-2660-PT-2] p 643 N87-25301 Engineering and cost principles for increasing the p 641 A87-46922 An experimental investigation of dynamic ground effect production efficiency and maintainability of aircraft CYLINDRICAL BODIES engines p 664 A87-43620 [NASA-CR-180560] p 659 N87-26036 Computational aeroacoustics as applied to the diffraction COST EFFECTIVENESS DESIGN ANALYSIS of sound by cylindrical bodies p 707 A87-43383 Standardization and logistic support cost effectiveness Aeroelastic derivatives as a sensitivity analysis of of advanced avionics systems p 661 A87-43468 nonlinear equations p 699 A87-46797 A derivative engine based on new technology - Low D DETECTION risk; cost effective Portable fuel leak detector [AIAA PAPER 87-1910] p 669 A87-45292 lAD-A180095] p 700 N87-25550 DAMAGE ASSESSMENT Reliability, 'better than the bast' p 699 A87-46728 DETONATION WAVES Damage tolerance concepts for modern helicopters COST ESTIMATES Morphology of a standing oblique detonation wave -- p 653 A87-43449 National Aerospace Plane Program: Principal for hypersonic airbreathing propulsion assumptions, findings and policy options A310.300 CFRP fin Damage tolerance [AIAA PAPER 87-1785] p 695 A87-45201 demonstration p 655 A87-44594 [RAND/P-7288-RGS] p 625 N87-25990 Standing oblique detonation wave engine performance COST REDUCTION Aircraft skin that bruises p 691 A87-46874 [AIAA PAPER 87-2002] p 670 A87-45347 Optimization of systems for the automatic testing of DATA ACQUISITION DIAGNOSIS aircraft engines according to cost criteria A unique approach to aeroelastic testing of scaled XMAN - A tool for automated jet engine diagnostics p 664 A87-43621 rotors p 683 A87-43461 [AIAA PAPER 87-1931] p 696 A87-45309

A-9 DIESEL ENGINES SUBJECT INDEX

DIESEL ENGINES DRAG MEASUREMENT ELECTROCHEMICAL MACHINING Compound cycle engine for helicopter application Exploratory evaluation of a moving-model technique for Electrochemical machining processes in aircraft engine [NASA-CR-175110] p 677 N87-25323 measurement of dynamic ground effects building --- Russian book p 693 A87-42905 DIFFERENTIAL EQUATIONS [AIAA PAPER 87-1924] p 685 A87-45303 ELECTROMAGNETIC INTERFERENCE Investigation of ground and air resonance using a DRAG REDUCTION Numerical simulation of cruiser on aircraft lightning combination of muitibtade coordinates and Floquet The thermal environment of transatmospheric vehicles p 646 A87-46317 theory p 653 A87-43444 [AIAA PAPER 87-1614] p 626 A87-43038 ELECTROMAGNETIC PULSES DIFFUSERS The use of computer models in helicopter drag Numerical simulation of cruiser on aircraft lightning Numerical simulation and comparison with experiment prediction p 628 A87-43424 p 646 A87-46317 for self-excited oscillations in a diffuser flow ELECTROMAGNETISM Recent progress in the measurement of the drag p 693 A87-43381 coefficients of models of transport aircraft in a wind Development and application of unified algorithms for Highly compact inlet diffuser technology tunnel problems in computational science p 705 N87-26006 ]AIAA PAPER 87-1747] p 666 A87-45180 ELECTRON BEAM WELDING ]NASA-3-1"-20096] p 644 N87-25306 DIGITAL COMMAND SYSTEMS DROP SIZE Expendable turbojet compressor design, test and Digital control development for the TS6-A-427 development p 674 A87-46212 Influence of fuel temperature on atomization [AIAA PAPER 67-2013] p 670 A87-45383 ELECTRONIC CONTROL DIGITAL COMPUTERS performance of pressure-swid atomizers p 698 A87-46198 Development program of a full authority digital electronic Design of motion simulation software with digital filtering control system for the T55-L-712E turboshaft engine DUAL THRUST NOZZLES techniques p 704 A87-44712 p 663 A87-43465 DIGITAL ELECTRONICS Dual cycle turbofan engine F-15/F100 digital electronic engine control main fuel [AIAA PAPER 87-2102] p 672 A87-45407 Development program of a full authority digital electronic gear pump field service evaluation control system for the T55-L-712E turboshaft engine DUCTED FLOW [AIAA PAPER 87-1846] p 667 A87-45246 p 663 A87-43465 A computational method for determining flowfield Preliminary flight results of an adaptive engine control F-t5/F100 digital electronic engine control main fuel properties when the pitot pressure is the only measured system of an F-15 airplane gear pump field service evaluation instream property p 637 A87-46184 [AIAA PAPER 87-1847] p 667 A87-45247 [AIAA PAPER 87-1846] p 667 A87-45246 DURABILITY Micro-computerparallel processing for real time testing Micro-computer/parallel processing for real time testing Aircraft structural maintenance recommendations based of gas turbine control systems of gas turbine control systems on fracture mechanics analysis p 623 A87-42857 [AIAA PAPER 87-t926] p 669 A87-45304 [AIAA PAPER 87-1926] p 669 A87-45304 DYNAMIC CHARACTERISTICS Highly reliable, microprocesser-baseq engine control DIGITAL FILTERS Validation of a method for air resonance testing of [AIAA PAPER 87-1927] p 669 A87-45305 Design of motion simulation software with digital filtering helicopters at model scale using active control of Pylon ENERGY ABSORPTION techniques p 704 A87-44712 dynamic characteristics p 683 A87-43462 Integrally-stiffened crash energy-absorbing subfloor DIGITAL SIMULATION DYNAMIC MODELS beam structure Study of the dynamic response of helicopters to a large An advanced mathematical model for helicopter flight [NASA-CASE-LAR-13697-1] p 659 N87-25321 airplane wake p 678 A87-43429 simulation using nonlinear unsteady aerodynamics ENERGY POLICY Numerical simulation of diffusor/combustor dome p 679 A87-43435 Research and development. Technical-scientific interaction p 676 A87-46255 publications 1986 DIGITAL SYSTEMS A stage-by-stage pest-stall compression system modeling technique [ETN-87-99713] p 710 N87-26826 Development of Digital Engine Control System for the [AIAA PAPER 87-2088] p 636 A87-45397 Integration of the propfan concept in aircraft design Harrier II [MBB-UT-0001/86] p 677 N87-26835 Dynamic data acquisition, reduction, and analysis for [AIAA PAPER 87-2184] p 673 A87-45458 ENGINE AIRFRAME INTEGRATION DIGITAL TECHNIQUES the identification of high-speed compressor component post-stability charactedstics STOVL engine/airframe integration EMI-fault prevention and self recovery of digital flight [AIAA PAPER 87-1711 ] p 655 A87-45158 [AIAA PAPER 87.2089] p 697 A87-45398 control systems p 66t A87-43470 Airbreathing propulsion system design at the United A combined stochastic feedforward and feedback Identification of a dynamic model of a helicopter from States Air Force Academy - An integrated approach control design methodology with application to autoland flight tests p 659 N87-26040 [AIAA PAPER 87-1870] p 709 A87-46265 DYNAMIC PROGRAMMING design Integration effects of pylon geometry and rearward [NASA-CR-4078] p 705 N87-25806 Dual adaptive control: Design principles and mounted nacelles for a high*wing transport DILUTION applications [AIAA PAPER 87-1920] p 655 A87.45300 The influence of dilution hole aerodynamics on the [NASA-CR-181050] p 705 N87-25804 Force accounting for airframe integrated engines temperature distribution in a combustor dilution zone DYNAMIC RESPONSE [AIAA PAPER 87-1965] p 636 A87-45334 [AIAA PAPER 87-1827] p 666 A87-45232 Study of the dynamic response of helicopters to a large Test flow calibration study of the Langley Arc-Heated DISPLAY DEVICES airplane wake p 678 A87-43429 Scramjet Test Facility EH101 cockpit design p 661 A87-43404 DYNAMIC STABILITY [AIAA PAPER 87-2165] p 685 A87-45445 A program to investigate requirements for effective flight Aeroelastic stability of a beadngless circulation control Computational analysis of hypersonic airbreathing simulator displays p 683 A87-44715 rotor in forward flight p 652 A87-43443 aircraft flow fields p 645 N87-26019 Visual systems developments p 694 A87-44725 A panel method for prediciting the dynamic stability ENGINE CONTROL New standards established for realism in visual derivatives of an oscillating wing in high subsonic flow Development program of a full authority digital electronic simulation --- for commerciai aircraft flight p 641 A87-46951 control system for the T55-L-712E turbosheft engine p 686 A87-46438 DYNAMIC STRUCTURAL ANALYSIS p 663 A87-43465 Optimal cooperative control synthesis of active Component mode iteration for frequency calculations Approximation of the characteristics of the turbine of a displays --- in analysis of structural vibration gas turbine engine in a wide range of operating modes [NASA-CR-4058] p 705 N87-25807 ]AIAA PAPER 86-1023] p 704 A87-43388 p 663 A87-43606 DISTANCE MEASURING EQUIPMENT Mechanical evaluation of the aeroelastic behaviour of Flight test of the F100-PW-220 engine in the F-16 Integrated navigation, communication and sunreillance a fan blade p 675 A87-46248 [AIAA PAPER 87-1845] p 667 A87-45245 Preliminary structural design of composite main rotor systems based on standard distance measuring F-15/F100 digital electronic engine control main fuel blades for minimum weight equipment p 649 A87-44039 gear pump field service evaluation [NASA.TP-2730] p 691 N87-25438 DOMES (STRUCTURAL FORMS) [AIAA PAPER 87-1846] p 667 A87-45246 DYNAMICAL SYSTEMS Numerical simulation of diffusor/combustor dome Preliminary flight results of an adaptive engine control An investigation of helicopter higher harmonic control interaction p 676 A87-46255 system of an F-16 airplane using a dynamic system coupler simulation DOPPLER RADAR [AIAA PAPER 87.1847] p 667 A87-45247 p 682 N87-26051 JAWS multiple Doppler derived winds Micro-computer/parallel processing for real time testing p 703 N87-25271 of gas turbine control systems United Airlines wind shear incident of May 31, 1984 E [AIAA PAPER 87-1926] p 669 A87-46304 p 647 N87-25288 Highly reliable, microprocesser-besed engine control DORNIER AIRCRAFT EDUCATION [AIAA PAPER 87-1927] p 669 A87-45305 Dornier 328 - Concept for a new-generation regional Simulation of performance, behaviour and faults of Development of Digital Engine Control System for the airliner p 657 A87-46326 aircraft engines Harrier II Technological aspects in preparing the development of [AIAA PAPER 87-1868] p 668 A87-45263 [AIAA PAPER 87-2184] p 673 A87-45458 Airbreathing propulsion system design at the United regional airliners p 657 A87-46327 Integration of engine/aircraft control - 'How far is it States Air Force Academy - An integrated approach DOWNWASH sensible to go' p 674 A87-46226 Investigation of blade-vortices in the rotor-downwash [AIAA PAPER 87-1870] p 709 A87-45265 EIGENVEGTORS Investigation on the stall margin of a turbofan engine p 627 A87-43415 p 675 A87-46239 Investigation of ground and air resonance using a Helicopter modelling for performance calculation combination of multiblade coordinates and Floquet Reliability, 'better than the best' p 699 A87-46728 p 652 A87-43434 theory p 653 A87-43444 Advanced detection, isolation and accommodation of DRAG EJECTORS sensor failures: Real-time evaluation Estimation of spillage drag for a wide range of Two-dimensional nozzle plume charactedstics [NASA-TP-2740] p 682 N87-25331 axisymmetric intakes at M 1 [AIAA PAPER 87-2111 ] p 636 A87-45413 ENGINE COOLANTS [ESDU-84004] p 701 N87-26301 ELASTIC BENDING Contingency power for small turboshaft engines using DRAG COEFFICIENTS Influence of third-degree geometric nonlinearities on the water injection into turbine cooling air Recent progress in the measurement of the drag vibration and stability of pretwisted, preconed, rotating [AIAA PAPER 87-1906] p 668 A87-45289 coefficients of models of transport aircraft in a wind blades p 674 A87-46228 Waste heat recovery system for high altitude application tunnel ELASTOMERS of liquid cooled, piston engines [ NASA-TT-20096 ] p 644 N87-25306 FEL - A new main rotor system p 651 A87-43402 [AIAA PAPER 87-2174] p 673 A87-45454 A-10 SUBJECT INDEX EXPERIENCE

ENGINE DESIGN ENGINE INLETS Modeling and implementation of wind shear data T700/CT7 derivative growth engine reliability - Highly compact inlet diffuser technology p 709 N87-25273 Consistent with longstanding industry traditions [AIAA PAPER 87-1747] p 666 A87-45180 Singular trajectories in airplane cruise-dash p 663 A87-43464 F-16 modular common inlet design concept optimization [AIAA PAPER 87-1748] p 666 A87-45181 Heat exchangers for turboshaft engines [NASA-CR-180636] p 659 N87-26035 p 664 A87-44253 Use of RPM trimto automate the supersonic engine/inlet Gust response of helicopters p 682 N87-26049 match in the SR-71A EROSION Countdown to the propfan p 664 A87-44272 [AIAA PAPER 87-1848] p 667 A87-45248 Erosion problem of axial compressor blades of a Engine design and systems integration for proplan and ENGINE MONITORING INSTRUMENTS turbeshaft engine p 675 A87-46246 high bypass turbofan engines Development of a flexible and economic helicopter ERROR ANALYSIS [AIAA PAPER 87-1730] p 665 A87-45169 engine monitoring system p 663 A87-43466 Errors in the measurement of the course angles of radar Highly compact inlet diffuser technology Helicopter turboshaft engine acoustic and infrared reference points due to the imprecise stabilization of the [AIAA PAPER 87-1747] p 666 A87-45180 studies and tests p 663 A87-43467 antenna mounting in bank and pitch Design and test verification of a combustion system for A noninterference blade vibration measurement system p 649 A87-44312 an advanced turbofan engine for gas turbine engines EULER EQUATIONS OF MOTION [AIAA PAPER 87-1826] p 666 A87-45231 [AIAA PAPER 87-1758] p 695 A87-45186 Computation of the flow fields of propellers and hovering Use of RPM tdm to automate the supersonic engine/inlet Microprocessor based surge monitoring system rotors using Euler equations p 628 A87-43418 match in the SR-71A p 686 A87-46241 Application of a 3D Euler cede to transonic blade tip [AIAA PAPER 87-1848] p 667 A87-45248 ENGINE NOISE flow p 628 A87-43419 Simulation of performance, behaviour and faults of Helicopter turboshaft engine acoustic and infrared Application of a 3D inviscid rotational design procedure aircraft engines studies and tests p 663 A87-43467 for turbomachinery bladings p 638 A87-46204 [AIAA PAPER 87-1868] p 668 A87-45263 ENGINE PARTS Numerical simulation of transonic three-dimensional System performance approach to air breathing Calculation of the reliability of aircraft-engine parts under flows in turbine blade passages p 638 A87-46206 Numerical simulation of flows in axial and radial propulsion design - A new undergraduate design repeated static loading p 664 A87-43616 competition Application of engine component life methodology to turbomachines using Euler solvers [AIAA PAPER 87-1869] p 668 A87-45264 life assessment p 698 A87-46230 [ONERA, TP NO. 1987-87] p 641 A87-46776 ENGINE STARTERS Application of a three-dimensional Euler code to Airbreathieg propulsion system design at the United Finite element analysis and redesign of jet engine starter transonic blade tip flow --- helicopter rotors States Air Force Academy - An integrated approach breech chamber [MBB-UD-482/86] p 642 N87-25299 [AIAA PAPER 87-1870] p 709 A87-45265 [ASME PAPER 86-WA/DE-20] p 664 A87-43702 Detailed near-wake flowfield surveys with comparison A derivative engine based on new technology - Low ENGINE TESTING LABORATORIES to an Euler method of an aspect ratio 4 rectangular wing risk; cost effective State-of-the-art test facilities for development of the [NASA-TM-89357] p 644 N87-25993 [AIAA PAPER 87-1910] p 669 A87-45292 Army's T800-LHT-800 LHX helicopter engine CFD applications: The Lockheed perspective NASA/GE advanced low emissions combustor [AIAA PAPER 87-1790] p 684 A87-45204 p 644 N87-26005 program ENGINE TESTS Application of CFD cedes to the design and development [AIAA PAPER 87-2035] p 671 A87-45369 Optimization of systems for the automatic testing of of propulsion systems p 677 N87-26009 Designing for fretting fatigue free joints in turboprop aircraft engines according to cost criteria Computational fluid dynamics research at the United engine gearboxes p 664 A87-43621 Technologies Research Center requiring [AIAA PAPER 87.2046] p 671 A87-45378 Evaluating and testing of turbofan engines supercomputers p 701 N87-26011 An improved computational model for a scramjet [ASME PAPER 86-WA/DE-3] p 664 A87-43701 Experience with 3-D composite grids propulsion system A rugged electronic pressure scanner designed for p 706 N87-26021 [AIAA PAPER 87-2078] p 671 A87-45393 turbine test p 695 A87-45124 Euler solution for a complete fighter aircraft at sub- and Dynamic data acquisition, reduction, and analysis for UDF/727 flight test Ixogram supersonic speed the identification of high-speed compressor component [AIAA PAPER 87-1733] p 666 A87-45171 [MBB-LKE-122-S/PUBI234] p 660 N87-26833 pest-stability characteristics Full-scale thrust reverser testing in an altitude facility EUROPEAN AIRBUS [AIAA PAPER 87-2089] p 697 A87-45398 [AIAA PAPER 87.1788] p 684 A87-45203 Automated systems for the manufacture of Airbus Flight test and evaluation of propulsion system State-of-the-art test facilities for development of the vertical stabilizers operability characteristics Army's T800-LHT-800 LHX helicopter engine [MBB-UT-17-86] p 705 N87-25786 [AIAA PAPER 87-2092] p 656 A87-45400 [AIAA PAPER 87-1790 p 684 A87-45204 Development and testing of critical components for the The design of Iow-stress/bigh performance centrifugal Transient test system design for the T800.APW-800 technological preparation on an Airbus fuselage made of impellers turbosheft engine carbon fiber reinforced plastics, phase 1 [AIAA PAPER 87-2099] p 697 A87-45405 [AIAA PAPER 87.1791 p 666 A87-45205 [BMFT-FB-W-86-017] p 692 N87-26151 EVALUATION Engine variable geometry effects on commercial Design and test verification of a combustion system for supersonic transport development an advanced turbofan engine Flight service evaluation of advanced composite ailerons [AIAA PAPER 87-2101] p 672 A87-45406 [AIAA PAPER 87-1826 p 666 A87-45231 on the L-1011 transport aircraft Scale model test results of a thrust reverser concept Deal cycle turbofan engine [NASA-CR.178321] p 691 N87-25439 [AIAA PAPER 87-2102] p 672 A87-45407 for advanced multi-functional exhaust systems EXCITATION Variable cycle concepts for high Mach applications [AIAA PAPER 87-18331 p 667 A87-45235 Secondary stream and excitation effects on [AIAA PAPER 87-2103] p 672 A87-45408 Ground testing facilities requirements for hypersonic two-dimensional nozzle plume characteristics Three stream turbofan-variable cycle engine with integral propulsion development [AIAA PAPER 87-2112] p 637 A87-45414 EXHAUST DIFFUSERS turbocompressor [AIAA PAPER 87-1884" p 684 A87-45276 [AIAA PAPER 87-2104] p 672 A87-45409 Modification to the Langley 8-Feot High Temperature Application of computational fluid dynamics to analysis Studies of scramjet flowfields Tunnel for hypersonic propulsion testing of exhaust gas/diffuser interactions in a turbine engine [AIAA PAPER 87-2161] p 688 A87-45443 [AIAA PAPER 87-1887] p 685 A87-45277 altitude test cell Aircraft engine design --- Book p 673 A87-45875 Results of acoustic tests of a Prop-Fan model [AIAA PAPER 87-2014] p 670 A87-45354 International Symposium on Air Breathing Engines, 8th, [AIAA PAPER 87-1894] p 707 A87-45282 EXHAUST EMISSION Cincinnati, OH, June 14.19, 1987, Proceedings Contingency power for small turboshaft engines using NASA/GE advanced low emissions combustor p 673 A87-46176 water injection into turbine cooling air program Future trends - A European v_=w --- of air breathing [AIAA PAPER 87-1906] p 668 A87-45289 [AIAA PAPER 87-2035] p 671 A87-45369 engines p 673 A87-46179 Integration of propulsion/integration test results through EXHAUST GASES 3-D viscous flow calculations at design and off.design the use of reference plane transfers Application of computational fluid dynamics to analysis conditions for the NACA 48-inch radial-inlet centrifugal [AIAA PAPER 87.1964] p 670 A87.45333 of exhaust gas/diffuser interactions in a turbine engine impeller p 638 A87-46191 A subsonic to Mach 5.5 subscale engine test facility altitude test cell Expendable turbojet compressor design, test and [AIAA PAPER 87-2052] p 685 A87-45381 [AIAA PAPER 87-2014] p 670 A87-45354 development p 674 A87-46212 Test flow calibration study of the Langley Arc-Heated Exhaust carbon - The effects of fuel composition Advances in technology for low cost turbomachinery - Scramjet Test Facility p 676 A87-46253 A potential to enhance the economy of future propulsion [AIAA PAPER 87-2165] p 685 A87-45445 EXHAUST NOZZLES STOL characteristics of a tactical aircraft with thrust system for general and helicopter aviation Scremlet testing in impulse facilities p 676 A87-46261 p 685 A87-46183 vectoring nozzles A study on the optimization of jet engines for combat The role of short duration facilities in gas turbine [AIAA PAPER 87-1835] p 655 A87-45237 aircrafts p 676 A87-46262 research p 685 A87-46222 Parametric study of single expansion ramp nozzles at subsonic/transonic speeds Reliability, 'better than the best' p 699 A87-46728 Investigation on the stall margin of a turbofan engine Compound cycle engine for helicopter application p 675 A87-46239 [AIAA PAPER 87-1836] p 635 A87-45238 Flight test and evaluation of propulsion system [NASA-CR-175110] p 677 N87-25323 V.2500 - Back on course? p 676 A87-46372 ENGINE FAILURE operability characteristics ENTRAINMENT Finite element analysis and redesign of jet engine starter [AIAA PAPER 87-2092] p 656 A87-45400 Entrainment effect of a leading-edge vortex breech chamber improved agility for modern fighter aircraft. II - Thrust p 641 A87-46777 [ASME PAPER 86-WA/DE-20] p 664 A87-43702 vectoring engine nozzles p 673 A87-46181 ENVIRONMENTAL CONTROL EXHAUST SYSTEMS A stege-by-stage pest-stall compression system Air cycle environmental control system for helicopters Scale model test results of a thrust reverser concept modeling technique [AIAA PAPER 87-2088] p 636 A87-45397 - A trade-off study p 654 A87-43472 for advanced multi-functional exhaust systems Erosion problem of axial compressor blades of a EQUATIONS OF MOTION [AIAA PAPER 87-1833] p 667 A87-45235 EXPERIENCE turboshaft engine p 675 A87-46246 An analytic method of quantifying helicopter agility Advanced detection, isolation and accommodation of p 678 A87-43432 Experiences with hot-wire instruments for the sensor failures: Real-time evaluation The integration of a six axis motion system and a wide measurement of the liquid water content in clouds [NASA-TP-2740] p 682 N87-25331 angle visual system inside a dome p 684 A87-44720 [DFVLR-MITT-86] p 704 N87-26476 A-11 EXPERIMENT DESIGN SUBJECT INDEX

EXPERIMENT DESIGN FEEDBACK CONTROL A comparison of the structureborne and airborne paths Transient test system design for the T800-APW-800 XMAN - A tool for automated jet engine diagnostics for propfan interior noise turboshaft engine [AIAA PAPER 87-1931] p 696 A87-45309 [NASA-CR-180289] p 708 N87-26612 [AIAA PAPER 87-1791] p 666 A87-45205 A combined stochastic feedforward and feedback FINITE VOLUME METHOD EXPERT SYSTEMS control design methodology with application to autoland Development of a viscous cascade code based on scalar XMAN - A tool for automated jet engine diagnostics design implicit factorization [AIAA PAPER 87-1931] p 696 A87-45309 [NASA-CR-4078] p 705 N87-25806 [AIAA PAPER 87-2150] p 637 A87-45435 Application of computational physics within Northrop FIBER OPTICS FINS p 706 N87-26008 Engineering and human visual considerations in A310-300 CFRP fin damage tolerance demonstration EXTREMUM VALUES development of a fibre optic helmet mounted display [MBB-UT-015/86] p 658 N87-25317 Extreme atmospheric turbulence p 661 A87-44727 FIRE PREVENTION [ONERA, TP NO. 1987-8] p 680 A87-44328 Optically interfaced sensor system for aerospace Fire, smoke, toxicity --- in airline operations applications p 694 A87-45107 p 646 A87-44748 F Fiber optic control of jet aircraft engines Burning questions --- fireworthiness of aircraft cabin p 661 A87-45115 materials p 646 A87-46373 FIELD OF VIEW FLAME PROPAGATION F-106 AIRCRAFT The integration of a six axis motion system and a wide Combustion*generated turbulence in practical An experimental investigation of dynamic ground angle visual system inside a dome p 684 A87-44720 combustors effect Visual systems developments p 694 A87-44725 [AIAA PAPER 87-1721] p 665 A87-45161 [NASA-CR-180560] p 659 N87-26036 AOI displays using laser illumination FLAME SPECTROSCOPY F-15 AIRCRAFT p 694 A87-44726 Diagnostics in supersonic combustion F-15/F100 digital electronic engine control main fuel Engineering and human visual considerations in [AIAA PAPER 87-1787] p 690 A87-45202 gear pump field service evaluation development of a fibre optic helmet mounted display FLAME STABILITY [AIAA PAPER 87-1646] p 667 A87-45246 p 661 A87-44727 Diagnostic methods for air-braathing engines Preliminary flight results of an adaptive engine control FIGHTER AIRCRAFT p 686 A87-46243 system of an F-15 airplane Simulation of transonic viscous flow over a fighter-like FLAME TEMPERATURE [AIAA PAPER 87-1847] p 667 A87-45247 configuration including inlet The influence of dilution hole aerodynamics on the F-15 SMTD hot gas ingestion wind tunnel test results [AIAA PAPER 87-1199] p 630 A87-44906 temperature distribution in a combustor dilution zone --- STOL and Maneuver Technology Demonstrator Experimental study of the vortex flow behavior on a [AIAA PAPER 87-1827] p 666 A87-45232 [AIAA PAPER 87-1922] p 669 A87-45301 generic fighter wing at subsonic and transonic speeds FLAMMABILITY The F-15E R&M challenge p699 A87-46715 [AIAA PAPER 87-1262] p 631 A87-44920 Thermal and flammability characterization of graphite F-16 AIRCRAFT STOVL engine/airframe integration composites p 688 A87-43398 Testing automated ground collision avoidance systems [AIAA PAPER 87-1711] p 655 A87-45158 FLAPS (CONTROL SURFACES) on the AFTI/F-16 p 660 A87-43375 Investigation of a delta-wing fighter model flow field at Conceptual studies of control systems for wings with Transonic analysis of the F-16A with under-wing fuel transonic speeds variable camber tanks - An application of the TranAir full-potential code [AIAA PAPER 87-1749] p 634 A87-45182 [MBB-UT-221/86] p 682 N87-26836 [AIAA PAPER 87-1198] p 630 A87-44905 Navier-Stokes simulations of supersonic fighter intake FLIGHT ALTITUDE F-16 modular common inlet design concept flowfields Flight duration, airspeed practices and altitude [AIAA PAPER 87-1748] p 666 A87-45181 [AIAA PAPER 87-1752] p 634 A87-45185 management of airplanes involved in the NASA VGH Flight test of the F100-PW-220 engine in the F-16 STOL characteristics Of a tactical aircraft with thrust General Aviation Program [AIAA PAPER 87-1845] p 667 A87-45245 vectoring nozzles [NASA-TM-89074] p 625 N87-25293 Operational engine usage and mission analysis [AIAA PAPER 87-1635] p 655 A87-45237 FLIGHT CHARACTERISTICS [AIAA PAPER 87-2097] p 671 A87-45404 Advanced fighter thrust reverser integration for minimum A new method of analytical evaluation of helicopter true FABRICATION landing distance airspeed p 661 A87-43439 The Airbus rudder - An example of new fabrication [AIAA PAPER 87-1923] p655 A87-45302 Advantages of thrust vectoring for STOVL technologies p 623 A87-44228 Highly reliable, microprocessor-based engine control [AIAA PAPER 87-1708] p 665 A87-45156 FACTORIZATION [AIAA PAPER 87-1927] p 669 A87-45305 Application of data to piloted simulators Fast methods applied to the calculation of transonic Performance seeking control for cruise optimization in p 687 N87-25275 airfoils p 641 A87-46962 fighter aircraft Flight duration, airspeed practices and altitude FAIL-SAFE SYSTEMS [AIAA PAPER 87-1929] p 681 A87-45307 management of airplanes involved in the NASA VGH Damage tolerance concepts for modern helicopters Thrust vectoring - Why and how? p 673 A87-46180 General Aviation Program p 653 A87-43449 Improved agility for modern fighter aircraft. II - Thrust [NASA-TM-89074] p 625 N87-25293 FAILURE ANALYSIS vectoring engine nozzles p 673 A87-46181 Optimization methods applied to the aerodynamic design Failure analysis of a large wind tunnel compressor A study on the optimization of jet engines for combat of helicopter rotor blades blade p 692 A87-42852 aircrafts p 676 A87-46262 [NASA-TM-89155] p 660 N87-26042 Culprits causing avionic equipment failures The new Soviet fighters - How good are they? FLIGHT CONDITIONS p 662 A87-46727 p 656 A87-46312 Comparison of wet and dry growth in artificial and flight FAILURE MODES On the nonlinear aerodynamic and stability icing conditions p 646 A87-45635 Stress analysis and optimisation of turbine rotor blade characteristics of a generic chine-forebedy slender-wing Measurement of the effect of manufacturing deviations shrouds p 699 A87-46250 fighter configuration on natural laminar flow for a single engine general aviation Culprits causing avionic equipment failures [NASA-TM-89447] p 643 N87-25305 airplane p 662 A87-46727 Application of computational physics within Northrop [NASA-CR-180671] p 677 N87-26044 FAN BLADES p 706 N87-26008 FLIGHT CONTROL Mechanical evaluation of the aeroelastic behaviour of Steady and unsteady aerodynamic forces from the The model inverse as an element of a manoeuvre a fan blade p 675 A87-46248 SOUSSA surfece-panel method for a fighter wing with tip FATIGUE (MATERIALS) demand system for helicopters p 679 A87-43441 missile and comparison with experiment and PANAIR Case histories involving fatigue and fracture mechanics; EMI-fault prevention and self recovery of digital flight [NASA-TP-2736] p 645 N87-26032 Proceedings of the Symposium, Charleston, SC, Mar. 21, control systems p 661 A87-43470 Euler solution for a complete fighter aircraft at sub- and 22, 1985 p 692 A87-42851 An approach to the synthesis of an adaptive flight control supersonic speed Fatigue crack growth predictions of welded aircraft system with incomplete information p 680 A87-45096 [MBB-LKE-122-S/PUB/234] p 660 N87-26833 structures containing flaws in the residual stress field FILM COOLING Design of CCV flight control system of STOL flying p 692 A87-42853 boat p 680 A87-45097 Development of low-cost test techniques for advancing Fatigue and fracture mechanics analysis of compression film cooling technology Validation of an integrated flight and propulsion control loaded aircraft structure p 692 A87-42854 [AIAA PAPER 87-1913] p 696 A87-45293 design for fighter aircraft Designing for fretting fatigue free joints in turboprop FINITE DIFFERENCE THEORY [AIAA PAPER 87-1928] p680 A87-45306 engine gearboxes Three-dimensional problems in computational fluid Analysis of typical fault-tolerant architectures using [AIAA PAPER 87-2046] p 671 A87-45378 HARP p 704 A87-45771 FATIGUE LIFE dynamics --- Russian book p 693 A87-42916 Correlation of SA349/2 helicopter flight-test data with Thrust vectoring- Why and how? p 673 A87-46180 Fatigue life analysis of fuel tank skins under combined a comprehensive rotorcraft model p 653 A87-43456 loads p 650 A87-42856 Reliability, 'better than the pest' p 699 A87-46728 Numerical simulation of transonic three-dimensional Development of a flexible and economic helicopter Military specifications p 658 N87-25281 flows in turbine blade passages p 638 A87-46206 engine monitoring system p 663 A87-43466 FLIGHT HAZARDS Linear stability analysis of three-dimensional Fatigue-life monitoring of the 5 metre wind tunnel Automatic systems and the low-level wind hazard compressible boundary layers p 640 A87-46504 [RAE-TM-AERO-2084] p 688 N87-26055 p 681 N87-25279 FINITE ELEMENT METHOD FATIGUE TESTS Unresolved issues in wind shear encounters Finite element analysis and redesign of jet engine starter A high temperature fatigue and structures testing p 647 N87-25282 breech chamber facility Determination of the local heat transfer characteristics [ASME PAPER 86-WA/DE-20] p 664 A87-43702 [NASA-TM-100151] p 701 N87-26399 Finite element analysis of large spur and helical gear on glaze ice accretions on a cylinder and a NACA 0012 FAULT TOLERANCE airfoil systems Damage tolerance concepts for modern helicopters [AD-At 79931 ] p 647 N87-25309 [AIAA PAPER 87-2047] p 697 A87-45379 p 653 A87-43449 Mechanical evaluation of the aeroelastic behaviour of Experiences with hot-wire instruments for the Analysis of typical fault-tolerant architectures using a fan blade p 675 A87-46248 measurement of the liquid water content in clouds HARP p 704 A87-45771 Numerical simulation of diffusor/combustor dome [DFVLR-MITI'-86] p 704 N87-26476 Advanced detection, isolation and accommodation of interaction p 676 A87-46255 FLIGHT LOAD RECORDERS sensor failures: Real-time evaluation Trends in the aeroelastic analysis of combat aircraft Operational engine usage and mission analysis [NASA-TP-2740] p 682 N87-25331 p 657 A87-46362 [AIAA PAPER 87-2097] p 671 A87-45404

A-12 SUBJECT INDEX FLOW MEASUREMENT

FLIGHT MANAGEMENT SYSTEMS Preparing a propfan propulsion system for flight test Advances in the computation of transonic separated The AVSCOM flight safety part program [AIAA PAPER 87-1731] p 665 A87-45170 flows over finite wings p 647 A87-46724 UDF/727 flight test program [AIAA PAPER 87-1195] p 630 A87-44904 FLIGHT PATHS [AIAA PAPER 87-1733] p 666 A87-45171 Transonic analysis of the F-16A with under-wing fuel Optimal flight trajectories in the presence of windshear, Flight test of the F100-PW-220 engine in the F-16 tanks - An application of the TranAir full-potential cede 1984-86 [AIAA PAPER 87-1845] p 667 A87-45245 [AIAA PAPER 87-1198] p 630 A87-44905 [NASA-CR-t80316] p 682 N87-26047 Preliminary flight results of an adaptive engine control Comparisons of unsteady flow fields about straight and FLIGHT RECORDERS system of an F-15 airplane swept wings using flow visualization and hotwire United Airlines wind shear incident of May 31, 1984 [AIAA PAPER 87-1847] p 667 A87-45247 anemometry p 647 N87-25287 Flight test and evaluation of propulsion system AIAA PAPER 87-1334] p 631 A87-44932 Flight duration, airspeed practices and altitude operability characteristics Simulations of ramjet eombustor flow fields. II - Origin management of airplanes involved in the NASA VGH [AIAA PAPER 87-2092] p 656 A87-45400 of pressure oscillations General Aviation Program Prepfan propulsion system development AIAA PAPER 87-1422] p 633 A87-44950 [NASA-TM-89074] p 625 N87-25293 p 675 A87-46247 Numerical investigation of the flow structure around a FLIGHT SAFETY Proving that Avanti stands for progress rapidly pitching airfoil The new Annex 17 . The latest contribution by p 656 A87-46314 AIAA PAPER 87-1424] p 633 A87-4495t international cMI aviation to the battle against terrorism Performance and loads data from a hover test of a p 708 A87-42860 0.658-scale V-22 rotor and wing Flow-field measurements of an airfoil with a deflected Aviation safety and the FAA's quality assurance [NASA-TM-89419] p 642 N87-25296 spoiler using an LDV system program p 709 A87-44064 Ground and flight test results of a total main rotor AIAA PAPER 87-1438] p 634 A87-44955 The quality of radar data and its determination at the isolation system Flow behind single- and dual-rotation propellers at angle radar installations of the Bundesanstalt fuer [NASA-CR-4082] p 643 N87-25302 of attack Flugsicherung p 650 A87-45878 Heliport visual approach surface testing test plan AIAA PAPER 87-1750] p 634 A87-45183 The AVSCOM flight safety part program [AD-A179897] p 650 N87-25312 Three-dimensional numerical predictions of the flow p 647 A87-46724 TACAN/INS Performance Evaluation (TIPE) flight test behind a rearward-faciog-step in a supersonic combustor Wind Shear/Turbulence Inputs to Flight Simulation and report AIAA PAPER 87-1962] p 636 A87-45332 Systems Certification [AD-A180138] p 650 N87-25313 Studies of scramjet flowfields [NASA.CP-2474] p 625 N87-25267 Correlation of B-t flight test subjective assessments and [AIAA PAPER 87-2161] p 688 A87-45443 Automatic systems and the low-level wind hazard some ride quality/vibration exposure criteria Test flow calibration study of the Langley Arc-Heated [AD-A179844] p 658 N87-25316 p 681 N87-25279 Scramjet Test Facility Unresolved issues in wind shear encounters Flight service evaluation of advanced composite ailerons [AIAA PAPER 87-2165] p 685 A87-45445 p 647 N87-25282 on the L-1011 transport aircraft An improved approach for transonic flow Aircraft accident/incident summary reports: Unalaska, [NASA-CR-178321] p 691 N87-25439 p 639 A87-46215 Alaska, September 25, 1985; Jenkinsburg, Georgia, Identification of a dynamic model of a helicopter from September 29, 1985; Boston, Massachusetts, December flight tests p 659 N87-26040 Experimental studies on the dynamic development and 15, 1985; DeKalb, Texas, December 31, 1985; Erie, The treatment of calibrations of total air temperature control of unsteady separated flows p 642 N87-25297 Pennsylvania, February 21, 1986 probes for use in flight-test analysis work Tomographic reconstruction of three-dimensional flow [PB87-910408] p 648 N87-25310 [ESDU-84007] p 701 N87-26324 over airfoils FLIGHT SIMULATION FLIGHT TIME [AD-A179976] p 643 N87-25300 Simulator evaluations of ioeeptors for ACT helicopters Flight duration, airspeed practices and altitude Study of lee-side flows over conically cambered Delta p 678 A87-43405 management of airplanes involved in the NASA VGH wings at supersonic speeds, part 2 An advanced mathematical model for helicopter flight General Aviation Program [NASA-TP-2660-PT-2] p 643 N87-25301 simulation using nonlinear unsteady aerodynamics [NASA-TM-89074] p 625 N87-25293 Detailed near-wake fiowfiold surveys with comparison p 679 A87-43435 FLIGHT TRAINING to an Euler method of an aspect ratio 4 rectangular wing The integration of a six axis motion system and a wide Simulator manufacturers' requirements [NASA-TM-89357] p 644 N87-25993 angle visual system inside a dome p 684 A87-44720 p 687 N87-25280 Computational fluid dynamics: Transition to design Engineering and human visual considerations in Simulator systems integration p 687 N87-25283 applications p 700 N87-26004 development of a fibre optic helmet mounted display FLIGHT VEHICLES Development and application of unified algorithms for p 661 A87-44727 A computational study of the flowfield surrounding the problems in computational science p 705 N87.26006 New standards established for realism in visual Aeroassist Flight Experiment vehicle Application of CFD codes to the design and development simulation --- for commercial aircraft flight [AIAA PAPER 87-1575] p 626 A87-43084 of propulsion systems p 677 N87-28009 p 686 A87.46438 FLOORS Computational fluid dynamics research at the United Wind Shear/Turbulence Inputs to Flight Simulation and Integrally-stiffened crash energy-absorbing subfloor Systems Certification Technologies Research Center requiring beam structure supercomputers p 701 N87-26011 [NASA-CP-2474] p 625 N87-25267 [NASA-CASE-LAR-13697-1] p 659 N87-2532t Wind shear and turbulence simulation Numerical solution of the Navier-Stokes equations about FLOQUET THEOREM p 703 N87-25274 three*dimensional configurations: A survey Investigation of ground and air resonance using a Microburst model requirements for flight simulation: An p 701 N87-26022 combination of multiblade coordinates and Floquet airframe manufacturer's perspective Velocity measurements near the blade tip and in the theory p 653 A87-43444 p 687 N87-25278 tip vortex core of a hovering model rotor FLOW CHARACTERISTICS The role of simulation in helicopter development p 645 N87-26030 Investigation of flow structure ina compressor with two [MSB-UD-435/86] p 687 N87-25333 FLOW EQUATIONS FLIGHT SIMULATORS types of guides p 629 A87-43604 Time-consistent pressure relaxation procedure for Realization and flight testing of a model following control Approximation of the characteristics of the turbine of a compressible reduced Navier-Stokes equations system for helicopters p 679 A87-43440 gas turbine engine in a wide range of operating modes p 626 A87-43377 p 663 A87-43606 Design of motion simulation software with digital filtering The influence of flow non-uniformities in air*breathing techniques p 704 A87-44712 Effect of swirl on the performance of a radial vaneless hypersonic propulsion systems Motion software for a research flight simulator diffuser with compressible flow at Mach numbers of 0.7 [AIAA PAPER 87-2079] p 636 A87-45394 p 704 A87-44713 and 0.8 An improved approach for transonic flow A program to investigate requirements for effective flight [ASME PAPER 86-WA/FE-6] p 629 A87-43704 p 639 A87-46215 simulator displays p 683 A87-44715 A computational method for determining flowfield FLOW GEOMETRY Visual systems developments p 694 A87-44725 properties when the pitot pressure is the only measured An interactive approach to surface-fitting complex AOI displays using laser illumination instream property p 637 A87-46184 geometries for flowfield applications p 694 A87-44726 FLOW DEFLECTION [AIAA PAPER 87-1476] p 625 A87-43009 Application of data to piloted simulators Simulation of transonic viscous flow over a fighter-like Effect of fabrication-related deviations of the geometrical p 687 N87-25275 configuration including inlet parameters of blade profiles on flow in a compressor Simulator manufacturers' requirements [AIAA PAPER 87-1199] p 630 A87-44906 p 629 A87-43603 p 687 N87-25280 Incompressible Navier-Stokes computations of vortical An LDA investigation of three-dimensional normal Simulator systems integration p 687 N87-25283 flows over double-delta wings shock-boundary layer interactions in a corner FLIGHT TESTS [AIAA PAPER 87-1341] p 631 A87-44933 [AIAA PAPER 87-1369] p 632 A87-44938 Observations of pilot control strategy in low level Flow-field measurements of an airfoil with a deflected Stationary disturbances in three-dimensional boundary helicopter flying tasks p 678 A87-43433 layers over concave surfaces spoiler using an LDV system Realization and flight testing of a model following control [AIAA PAPER 87-1412] p 632 A87-44945 [AIAA PAPER 87-1438] p 634 A87-44955 system for helicopters p 679 A87-43440 FLOW MEASUREMENT FLOW DISTORTION The model inverse as an element of a manoeuvre Flow over a trailing flap and its asymmetric wake Stationary disturbances in three-dimensional boundary demand system for helicopters p 679 A87-43441 p 626 A87-43376 layers over concave surfaces Irish Dauphin helicopter S.A.R. system flight tests ..- Designing transonic wind-tunnel test sections for flow [AIAA PAPER 87-1412] p 632 A87-44945 Search and Rescue p 648 A87-43455 diagnostics and laser velocimeter applications FLOW DISTRIBUTION Helicopter model in flight identification by a real time [AIAA PAPER 87-1434] p 684 A87-44954 A computational study of the flowfield surrounding the self adaptive digital process p 680 A87-43458 Wake measurements of an oscillating airfoil Aeroassist Flight Experiment vehicle Experimental application of strain pattern analysis (SPA) p 637 A87-45779 [AIAA PAPER 87-1575] p 626 A87-43084 - Wind tunnel and flight test results p 654 A87-43459 Optical flow diagnostic measurements in The Air Force Flight Test Center - Now and the future Investigation of blade-vortices inthe rotor-downwash turbomachinery p 698 A87-46245 p 684 A87-45125 p 627 A87-43415 Velocity measurements near the blade tip and in the Onboard instrumentation for flight test takeoff Computation of the flow fields ofpropellers and hovering tip vortex core of a hovering model rotor performance p 662 A87-45126 retors using Euler equations p628 A87-43418 p 645 N87-26030

A-13 FLOW STABILITY SUBJECT INDEX

FLOW STABILITY FRACTURE STRENGTH FULL SCALE TESTS Linear instability waves in supersonic turbulent mixing Analytical description of crack resistance curves for A310-300 CFRP fin Damage tolerance layers aluminum sheets used in aircraft construction demonstration p 655 A87-44594 [AIAA PAPER 87-1418] p 633 A87-44948 [MBB-UT-t 33/85] p 700 N87-25604 Crash response data system for the controlled impact FLOW THEORY FREE CONVECTION demonstration (CID) of a full scale transport aircraft On the evolution of particle-laden jet flows - A theoretical Natural convection flow of a radiating rarefied gas p 694 A87-45123 and experimental study between concentric rotating spheres FUSELAGES [AIAA PAPER 87-2181] p 697 A87-45457 [AIAA PAPER 87-t 523] p693 A87-43046 Investigation of blade-vortices in the rctor-downwash FLOW VELOCITY FREE FLOW p 627 A87-43415 Molecular flow velocity using Doppler shined Raman Changes in the free flow in the intake of a turbojet engine Navier-Stokes simulation of a hypersonic generic spectroscopy during the aircraft takeoff run p 640 A87-46351 wing/fuselage [AIAA PAPER 87-1531] p 693 A87-43053 FREE JETS [AIAA PAPER 87-1192] p 629 A87-44902 Optical flow diagnostic measurements in The vertical test section (VMK) of DFVLR in A multi-body aircraft with an all-movable center fuselage turbomachinery p 698 A87-46245 actively controlling fuselage pressure drag Cologne-Porz, West Germany --- wind tunnel FLOW VISUALIZATION [NASA-CASE-LAR-t3511-1] p 688 N87-25320 ]DFVLR-MITT-86-22] p 688 N87-26054 Visualization of three-dimensional structures about a Integragy-stiffened crash energy-absorbing subfloor FREQUENCY RESPONSE pitching forward swept wing beam structure Component mode iteration for frequency calculations [AIAA PAPER 87-1322] p 631 A87-44929 [NASA-CASE-LAR-13697-t ] p 659 N87-2532t --- in analysis of structural vibration Comparisons of unsteady flow fields about straight and Development and testing of critical components for the [AIAA PAPER 86-t023] p 704 A87-43388 swept wings using flow visualization and hotwire technological preparation on an Airbus fuselage made of anemometry Experience with frequency-domain methods in carbon fiber reinforced plastics, phase 1 [AIAA PAPER 87-1334] p 631 A87-44932 helicopter system identification p 680 A87-43457 [BMFT-FB-W-86-017] p 692 N87-26151 Wake measurements of an oscillating airfoil FRETTING FUZZY SYSTEMS p 637 A87-45779 Designing for fretting fatigue free joints in turboprop Application of a fuzzy controller in fuel system of turbojet Study of lee-side flows over conically cambered Delta engine gearboxes engine p 874 A87-46227 wings at supersonic speeds, part 2 [AIAA PAPER 87-2046] p 671 A87-45378 ]NASA-TP-2660-PT-2] p 643 N87-25301 FRICTION Detailed near-wake flowfield surveys with comparison Friction factors and heat transfer coefficients in G to an Euler method of an aspect ratio 4 rectangular wing turbulated cooling passages of different aspect ratios. I - [NASA-TM-89357] p 644 N87.25993 Experimental results GALERKIN METHOD An experimental low Reynolds number comparison of [AIAA PAPER 87-2009] p 696 A87-45350 An improved assumed mode method for estimating the a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil and FUEL COMBUSTION motion of a nonuniform rotor blade p 653 A87-43445 GAPS a NACA 64-210 airfoil in simulated heavy rain Application of low-Reynolds-number K-epsilon model to [NASA-CR-181119] p 644 N87-25997 solid fuel turbulent boundary layer combustion Efficiency of the utilization of rotor blade shroud labyrinth seals in an axial-compressor stage with large radial An experimental investigation of dynamic ground [AIAA PAPER 87-1778] p 690 A87-45198 effect clearances p 694 A87-43611 Pressure scaling effects in a scramjet combustion GAS COOLING [NASA-CR-180560] p 659 N87-26036 chamber p 676 A87-46258 FLUID DYNAMICS The influence of dilution hole aerodynamics on the FUEL CONSUMPTION Aeroelasticity in turbomachines comparison of temperature distribution in a combustor dilution zone APU fuel efficiency and affordability for commercial theoretical and experimental cascade results. Appendix [AIAA PAPER 87-1827] p 666 A87-45232 aircraft A5: All experimental and theoretical results for the 9 Experimental data correlations for the effects of rotation [AIAA PAPER 87-1907] p 669 A87-45290 standard configurations on impingement cooling of turbine blades [AD-A180534] p 677 N87-25326 A study of some factors affecting the performance of [AIAA PAPER 87-2008] p 696 A87-45349 a contra-rotating axial compressor stage GAS DYNAMICS Euler solution for a complete fighter aircraft at sub- and supersonic speed p 639 A87-46211 Numerical study of the gasdynamic process in a pulsajet [MBB-LKE-122-S/PUB/234] p 660 N87-26833 A study on the optimization of jet engines for combat engine p 663 A87-43614 FLUID FLOW aircrafts p 676 A87-46262 Scramjet testing in impulse facilities Portable fuel leak detector Fuel saving and fuel related subjects within an airline's p 685 A87-46183 [AD-At80095] p 700 N87-25550 operational environment GAS INJECTION FLUID JETS [ETN-87-90148] p 648 N87-26034 Influence of vane/blade spacing and cold-gas injection Mathematical model for calculating the atomization of FUEL CONTROL on vane and blade heat-flux distributions for the Teledyne a liquid jet by an annular gas stream Preliminary flight results of an adaptive engine control 702 HP turbine stage p 693 A87-43619 system of an F-15 airplane [AIAA PAPER 87-1915] p 669 A87-45295 FLU'R'ER [AIAA PAPER 87-1847] p 667 A87-45247 The air-injection method of fixing boundary-layer transition and investigating scale effects Active control of aerofoil flutter p 681 A87-46792 Application of a fuzzy controller in fuel system of turbojet p 639 A87-46264 Aercelasticity in turbomachinee comparison of engine p 674 A87-46227 GAS TURBINE ENGINES theoretical and experimental cascade results. Appendix FUEL GAGES Approximation of the characteristics of the turbine of a AS: All experimental and theoretical results for the 9 Fuel saving and fuel related subjects within an airline's gas turbine engine in a wide range of operating modes standard configurations operational environment p 663 A87-43606 [AD.A180534] p 677 N87-25326 [ETN-87-90148] p 648 N87-26034 Airfoil flutter model suspension system FUEL INJECTION The low-aspect-ratio parameter of blades p 663 A87-43807 [NASA-CASE-LAR-13522-1-SB] p 687 N87-25334 An improved computational model for a scramjet FLUTTER ANALYSIS Optimization of the duration of ultrasonically activated propulsion system impact surface treatment of gas-turbine-engine blades Aeroelastic derivatives as a sensitivity analysis of [AIAA PAPER 87-2078] p 671 A87-45393 p 663 A87-43609 nonlinear equations p 699 A87-46797 Influence of fuel temperature on atomization FLY BY WIRE CONTROL A study of the thermal-stress state of gas turbine engine performance of pressure-swirl atomizers blades with protective coatings p 664 A87-43640 Realization and flight testing of a model following control p 698 A87-46198 Heat exchangers for turboshaft engines system for helicopters p 679 A87-43440 Hydrogen scramjet with sidewall injection - Shock tunnel The model inverse as an element of a manoeuvre simulations p 674 A87-46217 p 664 A87-44253 demand system for helicopters p 679 A87-4344t Design and evaluation of a new injector configuration A rugged electronic pressure scanner designed for FOKKER AIRCRAFT for supersonic combustion p 674 A87-46218 turbine test p 698 A87-45124 Fokker 50 - Pedigree with power p 656 A87-45647 FUEL SPRAYS Impact of engine technology on supersonic STOVL FORCE DISTRIBUTION On the evolution of particle-laden jet flows - A theoretical [AIAA PAPER 87-1709] p 665 A87-45157 Measurement of side forces of a H-force rotor and experimental study Propfan propulsion systems for the 1990's p 651 A87-43410 [AIAA PAPER 87-2181] p 697 A87-45457 [AIAA PAPER 87-1729] p 665 A87-45168 FOREBODIES Influence of fuel temperature on atomization A noninterference blade vibration measurement system On the nonlinear aerodynamic and stability performance of pressure-swirl atomizers for gas turbine engines characteristics of a generic chine-forebody slender-wing p 698 A87-46198 [AIAA PAPER 87-1758] p 695 A87-45186 fighter configuration FUEL TANKS Real-time neutron imaging of gas turbines [NASA-TM-89447] p 643 N87-25305 Fatigue life analysis of fuel tank skins under combined FORMING TECHNIQUES [AIAA PAPER 87-1762] p 695 A87-45189 loads p 650 A87-42856 High density fuel effects on gas turbine engines Superplastic forming/diffusion bonding of titanium Transonic analysis of the F-t6A with under-wing fuel [AIAA PAPER 87-1829] p 666 A87o45233 p 689 A87-44747 tanks - An application of the TranAir full-potential code FRACTOGRAPHY A bidirectional tapered roller thrust bearing for gas [AIAA PAPER 87-1198] p 630 A87-44905 Failure analysis of a large wind tunnel compressor FUEL TESTS turbine engines [AIAA PAPER 87-1842] p 695 A87-45243 blade p 692 A87-42852 High density fuel effects on gas turbine engines FRACTURE MECHANICS [AIAA PAPER 87-1829] p 666 A87-45233 Aerodynamic and heat transfer analysis of the low aspect ratio turbine Case histories involving fatigue and fracture mechanics; Degradation mechanisms of sulfur and nitrogen Proceedings of the Symposium, Charleston, SC, Mar. 21, containing compounds during thermal stability testing of [AIAA PAPER 87-1916] p 696 A87-45296 22, 1985 p 692 A87-42851 model fuels Advancements in hydrogen expander airbreathing Fatigue and fracture mechanics analysis of compression [AIAA PAPER 87-2039] p 690 A87.45372 engines loaded aircraft structure p 692 A87-42854 FUEL-AIR RATIO [AIAA PAPER 87-2003] p 670 A87-45348 Fracture of an aircraft horizontal stabilizer Exhaust carbon - The effects of fuel composition Friction factors and heat transfer coefficients in p 650 A87-42855 p 676 A87-46253 turbulated cooling passages of different aspect ratios. I - Aircraft structural maintenance recommendations based Pressure scaling effects in a scramjet combustion Experimental results on fracture mechanics analysis p 623 A87-42857 chamber p 676 A87-46258 [AIAA PAPER 87-2009] p 696 A87-45350

A-14 SUBJECT INDEX HELICOPTER PERFORMANCE

NO(x) reduction and combustion phenomena in the Exploratory evaluation of a moving-model technique for Realization and flight testing of a model following control multi-annular gas turbine swirl burner measurement of dynamic ground effects system for helicopters ) 679 A87-43440 [AIAA PAPER 87-2036] p 671 A87-45370 [AIAA PAPER 87-1924] p 685 A87-45303 The model inverse as an element of a manoeuvre The design of low-stress/high performance centrifugal A subsonic to Mach 5.5 subscale engine test facility demand system for helicopters ) 679 A87-43441 impellers [AIAA PAPER 87-2052] p 685 A87-45381 Helicopter individual-blade-control research at MIT [AIAA PAPER 87-2099] p 697 A87-45405 Ground and flight test results of a total main rotor t977-1985 ) 679 A87-43446 isolation system Cycle selection considerations for high Mach Development of an experimental system for active [NASA-CR-4082] p 643 N87-25302 applications control of vibrations on helicopters ) 679 A87-43447 GUST LOADS [AIAA PAPER 87-2105] p 672 A87-45410 Extreme atmospheric turbulence Kinematic observers for active control of helicopter rotor Navier-Stokes solutions for highly loaded turbine vibration ) 679 A87-43448 cascades [ONERA, TP NO. 1987-8] p 680 A87-44328 Gust response of helicopters p 682 N87-26049 Helicopter model in flight identification by a real time [AIAA PAPER 87-2151] p 637 A87-45436 GUSTS self adaptive digital process ) 680 A87-43458 Durability characterization of ceramic materials for gas B-57B gust gradient program p 657 N87-25276 Autonomous navigation system for the new generation turbines p 690 A87-45898 Turbulence models p 703 N87-25277 of military helicopters and associated flight tests The role of short duration facilities in gas turbine An introduction to time-dependent aerodynamics of p 648 A87-43469 research p 685 A87o46222 aircraft response, gusts and active controls EMI-fault prevention and self recovery of digital flight A study on the effect of non-dimensional system [ESDU-84020] p 682 N87-26048 control systems p 661 A87-43470 parameters on squeeze film damper performance using Study of helicopterroll control effectiveness criteria experimental data p 698 A87-46229 H [NASA-CR-177404] p 681 N87-25330 Microprocessor based surge monitoring system An investigation of helicopter higher harmonic control p 686 A87-46241 HANDICAPS using a dynamic system coupler simulation Advances in technology for low cost turbomachinery - p 682 N87-26051 Airlines are exempt from law on rights of the disabled A potential to enhance the economy of future propulsion p 709 A87-42863 Helicopter vibration control: Recent advances system for general and helicopter aviation HARDWARE p 660 N87-26247 p 676 A87-46261 Standardization and logistic support cost effectiveness HELICOPTER DESIGN GAS TURBINES of advanced avionics systems p 661 A87-43468 New aerodynamic design of the fenestron for improved Compound cycle engine for helicopter application HARMONIC CONTROL performance p 651 A87-43403 [NASA-CR-175110] p677 N87-25323 An investigation of helicopter higher harmonic control EH101 cockpit design p 661 A87-43404 GEAR TEETH using a dynamic system coupler simulation Optimum design of a helicopter rotor blade Selection of admissible contact stresses for toothed p 682 N87-26051 p 651 A87-43406 gears of aircraft engines p 663 A87-43605 HARRIER AIRCRAFT Spanish contribution to rotororaft development - GEARS Development of Digital Engine Control System for the Homage to de la Cierva p 623 A87-43426 Parameters of optimal planetary gears of AI type Harrier It Rotor design for maneuver performance p 694 A87-43622 [AIAA PAPER 87-2184] p 673 A87-45458 p 652 A87-43431 Development of a large, spiral bevel gear rotororaft HEAT EXCHANGERS Investigation of ground and air resonance using a transmission Heat exchangers for turboshaft engines combination of multiblade coordinates and Floquet [AIAA PAPER 87-1839] p 667 A87-45240 p 664 A87-44253 theory p 653 A87-43444 HEAT FLUX Designing for fretting fatigue free joints in turboprop Damage tolerance concepts for modern helicopters Influence of vane/blade spacing and cold-gas injection engine gearboxes p 653 A87-43449 on vane and blade heat-flux distributions for the Teledyne [AIAA PAPER 87-2046] p 671 A87-45378 Composite vital parts optimisation for EH 101 rotor 702 HP turbine stage Finite element analysis of large spur and helical gear hub p 653 A87-43451 [AIAA PAPER 87-1915] p 669 A87-45295 systems Lightning protection activity in the development of a new HEAT RESISTANT ALLOYS [AIAA PAPER 87-2047] p 697 A87-45379 helicopter p 654 A87-43471 Materials in aerospace; Proceedings of the First GENERAL AVIATION AIRCRAFT Materials in helicopters - A review International Conference, London, England, Apr. 2-4, 1986. Flight duration, airspeed practices and altitude p 624 A87-44731 Volumes 1 & 2 p 689 A87-44729 management of airplanes involved in the NASA VGH EH.10t - The helicopter matures p 657 A87-46371 General Aviation Program High temperature titanium alloys p 689 A87-44739 Soviet helicopter development p 657 A87-46735 HEAT TRANSFER [NASA-TM-89074] p 625 N87-25293 Aerodynamic study of a helicopter rotor in hovering flight A unique measurement technique to study GEOMETRICAL THEORY OF DIFFRACTION - Theory vs. experiment p 641 A87-47014 laminar-separation bubble characteristics on an airfoil Application of wedge diffraction theory to estimating Helicopter-V/STOL dynamic wind and turbulence design [AIAA PAPER 87-1271] p 631 A87-44921 power density at airport humped runways methodology p 658 N87-25284 HEAT TRANSFER COEFFICIENTS p 650 A87-46861 Design for repairability of helicopter rotor blades Numerical analysis of peak heat transfer rates for GEOMETRY [MBB-UD-491/86] p 658 N87-25315 hypersonic flow over a cowl leading edge Numerical solution of the Navier-Stokes equations about The role of simulation in helicopter development [AIAA PAPER 87-1895] p 635 A87-45283 three-dimensional configurations: A survey [MBB-UD-435/86] p 687 N87-25333 Aerodynamic and heat transfer analysis of the low aspect p 701 N87-26022 Dual adaptive control: Design principles and ratio turbine GLASS FIBER REINFORCED PLASTICS applications [AIAA PAPER 87-1916] p 696 A87-45296 Seastar - Glass, plastic, and tradition [NASA-CR-181050] p 705 N87-25804 Friction factors and heat transfer coefficients in p 656 A87-45648 Optimization methods applied to the aerodynamic design turbulated cooling passages of different aspect ratios. I - GLIDE PATHS of helicopter rotor blades Experimental results Terrain modelling of glideslope for instrument landing [NASA-TM-89155] p 660 N87-26042 [AtAA PAPER 87-2009J p 696 A87-45350 system p 650 A87-46415 Gust response of helicopters p 682 N87-26049 GOERTLER INSTABILITY The role of short duration facilities in gas turbine HELICOPTER ENGINES research p 685 A87-46222 Stationary disturbances in three-dimensional boundary Development of a flexible and economic helicopter HEATING layers over concave surfaces engine monitoring system p 663 A87-43466 Application of computational fluid dynamics to analysis [AIAA PAPER 87-1412] p 632 A87-44945 Helicopter turboshaft engine acoustic and infrared of exhaust gas/diffuser interactions in a turbine engine GRAPHITE-EPOXY COMPOSITES studies and tests p 663 A87-43467 altitude test cell Thermal and flammability characterization of graphite Helicopter lubrication p 624 A87-44733 [AIAA PAPER 87-2014] p 670 A87-45354 composites p 688 A87-43398 State-of-the-art test facilities for development of the Composite vital parts optimisation for EH 101 rotor Influence of a heated leading edge on boundary layer Army's T800-LHT.800 LHX helicopter engine growth, stability and transition hub p 653 A87-43451 [AIAA PAPER 87-1790] p 684 A87-45204 [DE87-008516] p 700 N87-25538 Flight service evaluation of advanced composite ailerons Transient test system design for the T800-APW-800 HEAVY LIFT HELICOPTERS on the L-1011 transport aircraft turboshaft engine Development of a large, spiral bevel gear rotorcraft [NASA-CR-178321] p 691 N87-25439 [AIAA PAPER 87-1791] p 666 A87-45205 transmission GROUND EFFECT (AERODYNAMICS) Erosion problem of axial compressor blades of a [AIAA PAPER 87-1839] p 667 A87-45240 Exploratory evaluation of a moving-model technique for turboshaft engine p 675 A87-46246 HELICAL WINDINGS measurement of dynamic ground effects Advances in technology for low cost turbomachinery - Composite vital parts optimisation for EH 101 rotor [AIAA PAPER 87-1924] p 685 A87-45303 A potential to enhance the economy of future propulsion hub p 653 A87-43451 An experimental investigation of dynamic ground system for general and helicopter aviation Finite element analysis of large spur and helical gear effect p 676 A87-46261 [NASA-CR-180560] p 659 N87-26036 systems Compound cycle engine for helicopter application [AIAA PAPER 87-2047] p 697 A87-45379 GROUND RESONANCE [NASA-CR-175110] p 677 N87-25323 HELICOPTER CONTROL Investigation of ground and air resonance using a HELICOPTER PERFORMANCE Simulator evaluations of inceptors for ACT helicopters combination of multiblade coordinates and Floquet Helicopter activities in Germany p 623 A87-43401 p 678 A87-43405 theory p 653 A87-43444 New aerodynamic design of the fenestron for improved Stability and control modelling --- helicopters in near GROUND SUPPORT SYSTEMS performance p 651 A87-43403 Contribution of laser anemometry to aircraft safety hovering flight p 678 A87-43428 Prediction of blade airloads in hovering and forward flight p 699 A87-46361 Observations of pilot control strategy in low level using free wakes p 651 A87-43411 GROUND TESTS helicopter flying tasks p 678 A87-43433 Measurements of the performance of a helicopter swept Evaluating and testing of turbofan engines The influence of the induced velocity distribution and tip rotor in flight p 652 A87-43423 [ASME PAPER 86-WA/DE-3] p 664 A87-43701 the flapping-lagging coupling on the derivatives of the rotor An analytic method of quantifying helicopter agility Ground testing facilities requirements for hypersonic and the stability of the helicopter p 679 A87-43436 p 678 A87-43432 propulsion development A new method of analytical evaluation of helicopter true Helicopter modelling for performance calculation [AIAA PAPER 87-1884] p 684 A87-45276 airspeed p 661 A87-43439 p 652 A87.43434

A-15 HELICOPTER PROPELLER DRIVE SUBJECT INDEX

An advanced mathematical model for helicopter flight HIGH ALTITUDE ENVIRONMENTS Research on the stress analysis method of rubber simulation using nonlinear unsteady aerodynamics HALE thermal balance --- High Altitude Long Endurence structure - Calculation of the frequency adapter stresses p 679 A87-43435 remotely piloted vehicles p 693 A87-43453 Validation of a method for air resonance testing of [AIAA PAPER 87-2172] p 656 A87-45452 HUMAN FACTORS ENGINEERING helicopters at model scale using active control of Pylon HIGH ENERGY FUELS Engineering and human visual considerations in dynamic characteristics p 683 A87-43462 High density tual effects on gas turbine engines development of a fibre optic helmet mounted display Icing clearance criteria for UK military helicopters [AIAA PAPER 87-1829] p 666 A87-45233 p 661 A87-44727 p 646 A87-44705 HIGH PRESSURE HYDROCARBON COMBUSTION Effect of planform taper on hover performance of an Transonic stream function solution on S(2) Exhaust carbon. The effects of fuel composition advanced AH-64 model rotor streamsurface for a high pressure ratio centrifugal p 676 A87-46263 [NASA-TM-891451 p 643 N87-25304 compressor p 638 A87-46195 HYDROGEN FUELS Study of halicopterroll control effectiveness criteria HIGH RESOLUTION Three-dimensional numerical predictions of the flow [NASA-CR-177404] p 681 N87-25330 Survey of currently available high-resolution raster behind a rearward-facing-step in a supersonic combustor Optimization methods applied to the aerodynamic design graphics systems [AIAA PAPER 87-1962] p 636 A87-45332 of helicopter rotor blades [NASA-TM-89139] p 705 N87-25771 Advancements in hydrogen expander airbreathing [NASA-TM-89155] p 660 N67-26042 HIGH REYNOLDS NUMBER engines HELICOPTER PROPELLER DRIVE Aerodynamics of unmanned aircraft at full.scale in the [AIAA PAPER 87-2003] p 670 A87-45348 Development of a large, spiral bevel gear rotorcraft RAE 24ft wind-tunnel Hydrogen scr amjet with sidewall injection - Shock tunnel transmission [RAE-TM-AERO-2081] p 645 N87-26027 simulations p 674 A87-46217 [AIAA PAPER 87-1839] p 667 A87-45240 Fatigue-life monitoring of the 5 metre wind tunnel Effect of Reynolds number variation on aerodynamics HELICOPTER TAIL ROTORS [RAE-TM-AERO-2084] p 688 N87-26055 of a hydrogec-fueied transport concept at Mach 6 New aerodynamic design of the fenestron for improved HIGH SPEED [NASA.TP-27281 p 645 N87-26031 performance p 651 A87-43403 Variable cycle concepts for high Mech applications HYPERSONIC AIRCRAFT The use of computer models in helicopter drag [AIAA PAPER 87-2103] p 672 A87-45408 Ground testing facilities requirements for hypersonic prediction p 628 A87-43424 HIGH STRENGTH ALLOYS propulsion development HELICOPTER WAKES Developments in titanium alloys p 689 A87-44744 [AIAA PAPER 87-18841 p 684 A87.45276 Prediction of blade airloads in hovering and forward flight HIGH TEMPERATURE AIR A model test vehicle for hypersonic aerospace systems using free wakes p 651 A87-43411 High temperature transport properties of air development A unified approach for potential and viscous free-wake [AIAA PAPER 87-1632] p 707 A87-43129 [MBB-UR*875/86] p 658 N87-25314 analysis of helicopter rotors p 627 A67-43412 HIGH TEMPERATURE TESTS Computational analysis of hypersonic airbreathing A parametric investigation of a free wake analysis of Modification to the Langley 8-Foot High Temperature aircraft flow fields p 645 N87-26019 hovering rotors p 627 A87-43413 Tunnel for hypersonic propulsion testing Effect of Reynolds number variation on aerodynamics The influence of winglets on rotor aerodynamics [AIAA PAPER 87-1887] p 685 A87-45277 of a hydrOgen-fueled transport concept at Mach 6 p 628 A67-43422 A high temperature fatigue and structures testing [NASA-TP-2728] p 645 N87-26031 Correlation of SA349/2 helicopter flight-test data with facility HYPERSONIC BOUNDARY LAYER a comprehensive rotorcraft model p 653 A67-43456 [NASA-TM-t001511 p 701 N87-26399 Prediction and control of transition in hypersonic HELICOPTERS HISTORIES boundary layers Full potential modeling of blade-vortex interactions Going beyond the limits. Aviation in Germany [AIAA PAPER 87-1414] p 632 A87-44946 p 627 A87-43417 [SO-1-87] p 710 N87-26853 HYPERSONIC COMBUSTION A comparison of the acoustic and aerodynamic HOLOGRAPHIC INTERFEROMETRY An improved computational model for a scramlet measurements of a model rotor tested in two anechoic Tomographic reconstruction of three-dimensional flow wind tunnels p 683 A87-43425 over airfoils propulsion system [AIAA PAPER 87-2078] p 671 A87-45393 Spanish contribution to rotorcraft development - lAD-At79976] p 643 N87-25300 Homage to de la Cierva p 623 A87-43426 HOLOGRAPHY The influence of flow non-uniformities in air-breathing hypersonic propulsion systems Study of the dynamic response of helicopters to a large Optical flow diagnostic measurements in [AIAA PAPER 87-2079] p 636 A87-45394 airplane wake p 678 A87-43429 turbomachinery p 698 A87-46245 A promising low speed air data system for helicopters HONEYCOMB STRUCTURES HYPERSONIC FLIGHT p 661 A87-43437 Honeycomb structures: Parameter selection end design Morphology of a standing oblique detonation wave --- Correlation of SA34912 helicopter flight-test data with --- Russian book p 693 A87-42914 for hypersonic airbreathing propulsion a comprehensive rotorcraft model p 653 A87-43456 HORIZONTAL FLIGHT [AIAA PAPER 87-1785] p 695 A87-45201 Experience with frequency-domain methods in Application of a 3D Euier code to transonic blade tip A subsonic to Mach 5.5 subsoale engine test facility helicopter system identification p 680 A87-43457 flow p 628 A87-43419 [AIAA PAPER 87-2052] p 685 A87-45381 Air cycle environmental control system tot helicopters HORSEPOWER An outlook on hypersonic flight - A trade-off study p 654 A87-43472 Contingency power for small turboshaft engines using [AIAA PAPER 87-2074] p 671 A87-45392 Air conditioning systems for helicopters water injection into turbine cooling air Studies of scramjet flowfields p 654 A87-43473 [AIAA PAPER 87-1906] p668 A87-45289 [AIAA PAPER 87-2161] p 688 A67-45443 He4icopter rotor icing protection methods Digital control development for the T56-A-427 Aerothermodynamic computations for p 654 A87-44256 [AIAA PAPER 87-2013] p 670 A87-45353 super-/hypersonic flight p 640 A87-46328 Where and when helicopter icing occurs HOT-WIRE ANEMOMETERS HYPERSONIC FLOW p 702 A87-44702 Comparisons of unsteady flow fields about straight and Direct simulation of aerothermal loads for an aeroassist Rotor icing experience at Westiand and its application swept wings using flow visualization and hotwire flight experiment vehicle to current and future helicopters p 646 A87-44703 anemometry [AIAA PAPER 87-1546] p626 A87-43063 Icing clearances on civil helicopters - Unheated and [AIAA PAPER 87-1334] p 631 A87-44932 heated blades p 646 A87-44707 Wake measurements of an oscillating airfoil A computational study of the fiowfield surrounding the Performance and loads data from a hover test of a p 637 A87-45779 Aeroeesist Flight Experiment vehicle 0.658-scale V-22 rotor and wing HOT-WIRE FLOWMETERS [AIAA PAPER 87-15751 p 626 A87-43084 [NASA-TM-89419] p 642 N87-25296 Experiences with hot-wire instruments for the Navier-Stokes simulation of a hypersonic generic Ground and flight test results of a total main rotor measurement of the liquid water content in clouds wing/fuselage isolation system [DFVLR-MI'I-F-86] p 704 N87-26476 [AIAA PAPER 87-1192] p 629 A87-44902 [NASA-CR-4082] p 643 NS7-25302 HOVERING Numerical analysis of peak heat transfer rates for Preliminary structural design of composite main rotor Measurement of side forces of a H-force rotor hypersonic flow over a cowl leading edge blades for minimum weight p 651 A87-43410 [AIAA PAPER 87-1695] p 635 A87-45283 [NASA-TP-2730] p 691 NS7-25435 A parametric investigation of a free wake analysis of Computational analysis of hypersonic airbreathing Effect of signal jitter on the spectrum of rotor impulsive hovering rotors p 627 A87-43413 aircraft flow fields p 645 N87.26019 noise A prescribed radial distribution circulation of a hovering HYPERSONIC INLETS [NASA.TM-f00477] p 708 NS7-25827 rotor blade p 627 A87-43414 Two.dimeneional numerical analysis for inlets at Development of novel bearingless rotor systems Computation of the flow fields of propellers and hovering subsonic through hypersonic speeds [MBB-UD-471/86] p 702 NS7-26837 rotors using Euler equations p 628 A87-43418 [AIAA PAPER 87-1751] p 634 A87-45184 Stability and control modelling --- helicopters in near Avionics systems for future civil helicopters Efficiency parameters for inlets operating at hypersonic [MBB-UD-473/861 p 662 N87-26838 hovering flight p 678 A87-43428 speeds p 638 A87-46189 Aerodynamic study of a helicopter rotor in hovering flight HELIPORTS HYPERSONIC VEHICLES - Theory vs. experiment p 641 A87-47014 Heliport visual approach surface testing test plan Volume interchange factors for hypersonic vehicle wake Performance and loads data from a hover test of a [AD-A179897] p 650 NS7-25312 radiation 0.658-scale V-22 rotor and wing HELMET MOUNTED DISPLAYS [AIAA PAPER 87-1520] p 707 A87-43044 [NASA-TM-89419] p 642 N87-25296 AOI displays using laser illumination Morphology of a standing oblique detonation wave --- Effect of planform taper on hover performance of an p 694 AS7-44726 for hypersonic airbreathing propulsion advanced AH-64 model rotor [AIAA PAPER 87-1785] p 695 A87-45201 Engineering and human visual considerations in [NASA-TM-89145] p 643 N87-25304 development of a fibre optic helmet mounted display Identification of a dynamic model of a helicopter from HYPERSONIC WAKES p 661 AS7-44727 flight tests p 659 N87-26040 Volume interchange factors for hypersonic vehicle wake HERMES MANNED SPACEPLANE HUBS radiation A model test vehicle for hypersonic aerospace systems Calculated pedormance, stability, and maneuverability [AIAA PAPER 87-1520] p 707 A87-43044 development of high-speed tilting-prop-rotor aircraft HYPERSONIC WIND TUNNELS [MBB-UR-875/86] p 658 N87-25314 p 651 A87-43408 Modification to the Langley 8-Foot High Temperature HEXAGONAL CELLS Damage tolerance concepts for modern helicopters Tunnel for hypersonic propulsion testing High temperature titanium alloys p 689 A87-44739 p 653 A87-43449 [AtAA PAPER 87-18871 p 685 A87-45277

A-16 SUBJECT INDEX JET FLOW

Aerodynamic design modification of a hypersonic wind Development of a laser interferometric system for Influence of vaee/blede spacing and cold-gas injection tunnel nozzle by CSCM with high order accuracy --- velocity measurements inside a transonic axial flow on vane and blade heat-flux distributions for the Teledyne Conservative Supra-Characteristics Method compressor stage p 698 A87-46244 702 HP turbine stage [AIAA PAPER 87-1896] p 635 A87-45284 INCIDENCE [AIAA PAPER 87-1915] p 669 A87-45295 The 0.6 m x 0.6 m trisonic section (TMK) of DFVLR in A new simulation of airfoil dynamic stall due to velocity Unsteady three-dimensional Navier-Stokes simulations and incidence fluctuations Colegne-Porz, West Germany of turbine rotor-stator interaction [DFVLR-MITT-86.21] p 687 N87-26053 [AIAA PAPER 87-1242] p 630 A87-44915 [AIAA PAPER 87-2058] p 636 A87-45386 HYPERVELOCITY FLOW INCOMPRESSIBLE FLOW A method for the calculation of the interaction of a A unified approach for potential and viscous free-wake A mixing augmentation technique for hypervelocity turbulent boundary layer with a shock wave scram jets analysis of helicopter rotors p 627 A87-43412 p 639 A87-46238 [AIAA PAPER 87-1882] p 668 A87-45275 Incompressible Navier-Stokes computations of vortical flows over double-delta wings Compressible flows in the wakes of a square cylinder [AIAA PAPER 87-1341] p 631 A87-44933 and thick symmetrical airfoil arranged in tandem INDICATING INSTRUMENTS p 641 A87-46922 Portable fuel leak detector Computational fluid dynamics: Transition to design ICE FORMATION [AD-At80095] p 700 N87-25550 applications p 700 N87-26004 INERTIAL NAVIGATION Helicopter Rotor Icing Symposium, London, England, Development and application of unified algorithms for problems in computational science p 705 N87-26006 Jan. 14, 1986, Proceedings p 646 A87-44701 Autonomous navigation system for the new generation of military helicopters and associated flight tests Computational fluid dynamics applications at McDonnel Where and when helicopter icing occurs p 702 A87-44702 p 648 A87-43469 Douglas p 701 N87-26007 Onboard instrumentation for flight test takeoff Rotor icing expodence at Westland and its application Application of computational physics within Northrop performance p 662 A87-45126 to current and future helicopters p 646 A87-44703 p 706 N87-26008 TACAN/INS Performance Evaluation (TIPE) flight test Application of CFD codes to the design and development Development of the Chinook helicopter rotor blade report of propulsion systems p 677 N87-26009 de-icing system p 655 A87-44704 [AD-A180138] p 650 N87-25313 Icing clearance criteria for UK military helicopters INFORMATION SYSTEMS Experience with 3-D composite grids p 706 N87-26021 p 646 A87*44705 Design of an automated information-processing Rotor icing research at RAE Farnborough system p 704 A87-44241 Numerical solution of the Navier-Stokes equations about p 646 A87-44706 INFRARED DETECTORS three-dimensional configurations: A survey Icing clearances on civil helicopters - Unheated and Helicopter turboshaft engine acoustic and infrared p 701 N87-26022 INTERFERENCE DRAG heated blades p 646 A87-44707 studies and tests p 663 A87-43467 Comparison o1 wet and dry growth in artificial and flight INFRARED TELESCOPES Integration effects of pylon geometry and rearward icing conditions p 646 A87-45635 Scan stabilization and jitter control for an airborne mounted nacelles for a high-wing transport Determination of the local heat transfer characteristics telescope p 660 A87-42812 [AIAA PAPER 87-1920] p 655 A87-45300 on glaze ice accretions on a cylinder and a NACA 0012 INGESTION (ENGINES) INTERNAL COMBUSTION ENGINES airfoil F-15 SMTD hot gas ingestion wind tunnel test results Performance estimation of an aircraft internal [AD-A179931] p 647 N87-25309 --- STOL and Maneuver Technology Demonstrator combustion engine Experiences with hot-wire instruments for the [AIAA PAPER 87-1922] p 669 A87-45301 [AIAA PAPER 87-2173] p 672 A87-45453 measurement of the liquid water content in clouds INJECTORS INTERNATIONAL COOPERATION [DFVLR-MI]-[-86] p 704 N87-26476 Design and evaluation of a new injector configuration The new Annex 17 - The latest contribution by ICE PREVENTION for supersonic combustion p 674 A87-46218 international civil aviation to the battle against terrorism Helicopter rotor icing protection methods INLET AIRFRAME CONFIGURATIONS p 708 A87.42860 p 654 A87-44256 F-16 modular common inlet design concept Interception of civil aircraft vs. misuse of civil aviation IGNITION [AIAA PAPER 87-1748] p 666 A87-45181 p 708 A87-42861 Design and evaluation of a new injector configuration Force accounting for airframe integrated engines The effect of European law on air transport for supersonic combustion p 674 A87-46218 [AIAA PAPER 87-1965] p 636 A87-45334 p 709 A87-42862 IGNITION TEMPERATURE INLET FLOW EH.101 - The helicopter matures p 657 A87-46371 Pressure scaling effects in a scramjet combustion Two-dimensional numerical analysis for inlets at INVISClD FLOW chamber p 676 A87-46258 subsonic through hypersonic speeds Viscous-inviscid interactions in external aerodynamics IMAGE RECONSTRUCTION [AIAA PAPER 87-1751] p 634 A87-45184 p 626 A87-43299 Tomographic reconstruction of three-dimensional flow The influence of flow non-uniformities in air-breathing Unsteady viscous-inviscid interaction method and over airfoils hypersonic propulsion systems computation of buffeting over airfoils [AD-A179976] p 643 N87-25300 [AIAA PAPER 87-2079] p 636 A87-45394 [ONERA, TP NO. 1987-58] p 640 A87-46759 IMAGE RESOLUTION Efficiency parameters for inlets operating at hypersonic Viscid/inviscid separated flows Wind tunnel experimental study of optical beam speeds p 638 A87-46189 degradation through heterogeneous aerodynamic flows [AD-A179858] p 699 N87-25536 Changes inthe free flow inthe intake of a turbojet engine ITERATION [ONERA, TP NO. 1987-50] p 707 A87-46753 during the aircraft takeoff run p 640 A87-4635t IMAGES INLET TEMPERATURE Component mode iteration for frequency calculations --- in analysis of structural vibration Aero-optical analysis of compressible flow over an open A study on the optimization of jet engines for combat cavity aircrafts p 676 A87-46262 [AIAA PAPER 86-1023] p 704 A87-43388 ITERATIVE SOLUTION [AIAA PAPER 87-1399] p 632 A87-44943 INSECTS IMAGING TECHNIQUES Factors affecting the sticking of insects on modified A prescribed radial distribution circulation of a hovering rotor blade p 627 A87-43414 Visual systems developments p 694 A87-44725 aircraft wings IMPACT DAMAGE [NASA-CR-180957] p 659 N87-26037 The Aeronautical Research Institue (FFA) wing body 85 computer program. A panel method for determination of A310-300 CFRP fin Damage tolerance INSTALLING demonstration p 655 A87-44594 Evaluation of installed performance of a aeroelastic characteristics applying direct block iterative solution techniques IMPACT RESISTANCE wieg.tip-mounted pusher turboprop on a semispan wing KRASH analysis correlation. Transport airplane [NASA-TP-2739] p 659 N87-26041 [FFA-TN-1986-28] p 642 N87-25298 controlled impact demonstration test INSTRUMENT LANDING SYSTEMS [AD-A179906] p 647 N87-25308 Terrain modelling of glideslope for instrument landing J Integrally-stiffened crash energy-absorbing subfloor system p 650 A87-46415 beam structure INTAKE SYSTEMS J-85 ENGINE [NASA-CASE-LAR-t3697-1] p 659 N87-25321 F-16 modular common inlet design concept IMPACT STRENGTH J85 surge transient simulation p 675 A87-46240 [AIAA PAPER 87-1748] p 666 A87-45181 JET AIRCRAFT NOISE Effects of impact loading on carbon fiber reinforced Navier-Stokes simulations of supersonic fighter intake The art of reticulation and applicable adhesives --- for structures flowfields acoustically treated engine nacelles p 665 A87-44582 [MBB-Z-83/86] p 691 N87-25436 [AIAA PAPER 87-1752] p 634 A87-45185 JET ENGINE FUELS IMPACT TESTS Estimation of spillage drag for a wide range of High density fuel effects on gas turbine engines Crash response data system for the controlled impact axisymmetric intakes at M 1 [AIAA PAPER 87-1829] p 666 A87-45233 demonstration (CID) of a full scale transport aircraft [ESDU-84004] p 701 N87-26301 JET ENGINES p 694 A87-45123 INTERACTIONAL AERODYNAMICS XMAN ° A tool for automated jet engine diagnostics KRASH analysis correlation. Transport airplane Viscous-inviscid interactions inexternal aerodynamics [AIAA PAPER 87-1931] p 696 A87-45309 controlled impact demonstration test p 626 A87-43299 The origins and future possibilities of air breathing jet [AD-A179906] p 647 N87-25308 Unsteady separation characteristics of airfoils operating propulsion systems p 709 A87-46178 IMPELLERS under dynamic stall conditions p 628 A87-43421 The mixing of jets under simulated engine-like The design of low-stress/high performance centrifugal Description of, and preliminary results from, a now turbulence p 698 A87-46231 impellers blade-vortex interaction test facility p 683 A87-43460 Microprocessor based surge monitoring system [AIAA PAPER 87-2099] p 697 A87-45405 An LDA investigation of three-dimensional normal p 686 A87-4624t Performance prediction in a centrifugal compressor shock-boundary layer interactions in a corner A study on the optimization of jet engines for combat impeller p 674 A87-46190 [AIAA PAPER 87-1369] p 632 A87-44938 aircrafts p 676 A87-46262 3-D viscous flow calculations at design and off-design Numerical investigation of the flow structure around a JET FLOW conditions for the NACA 48-inch radial-inlet centrifugal rapidly pitching airfoil Two-dimensional nozzle plume characteristics impeller p 638 A87-46191 [AIAA PAPER 87-1424] p 633 A87-44951 [AIAA PAPER 87-2111] p 636 A87-45413 Investigation of the three dimensional flow near the exit Numerical analysis of peak heat transfer rates for Secondary stream and excitation effects on of two backswept transonic centrifugal impellers hypersonic flow over a cowl leading edge two-dimensional nozzle plume characteristics p 638 A87-46192 [AIAA PAPER 87-1895] p 635 A87-45283 [AIAA PAPER 87-2112] p 637 A87-45414

A-17 SUBJECT INDEX JET MIXING FLOW

Underexpanded jet-free stream interactions on an LATERAL STABILITY Classification of the load-carrying capacity of runway axisymmetric afferbody configuration On the nonlinear aerodynamic and stability surfaces by the ACN-PCN method. I p 639 A87-46232 characteristics of a generic chine-forebody slender-wing p 686 A87-46353 JET MIXING FLOW fighter configuration LOCKHEED AIRCRAFT Use of RPM trim to automate the supersonic engine/inlet Mathematical model for calculating the atomization of [NASA-TM-89447] p 643 N87-25305 match in the SR-71A a liquid jet by an annular gas stream The interference of the model support mast with p 693 A87-43610 measurements of the longitudinal and lateral aerodynamic [AIAA PAPER 87-1848] p 667 A87-45248 The influence of dilution hole aerodynamics on the coefficients LOGISTICS The F-t5E R&M challenge p 699 A87-46715 temperature distribution in a combustor dilution zone [NASA-TT-20079] p 644 N87-25307 LOGISTICS MANAGEMENT [AIAA PAPER 87-1827] p 666 A87-45232 LEADING EDGE FLAPS Standardization and logistic support cost effectiveness The mixing of jets under simulated engine-like Subsonic wind-tunnel measurements of a slender of advanced avionics systems p 661 A87-43468 turbulence p 698 A87-46231 wing-body configuration employing a vortex flap LONGITUDINAL STABILITY [NASA-TM-89101) p 642 N87-25295 On the nonlinear aerodynamic and stability LEADING EDGES K characteristics of a generic chine-forebody slender-wing Entrainment effect of a leading-edge vortex fighter configuration p 641 A87-48777 KINEMATICS [NASA-TM-89447] p 643 N87-25305 Kinematic observers for active control of helicopter rotor An experimental investigation of delta wings with The interference of the model support mast with vibration p 679 A87-43448 leading-edge vortex separation p 641 A87-46956 measurements of the longitudinal and lateral aerodynamic KNOWLEDGE Influence of a heated leading edge on boundary layer coefficients Use of artificial intelligence methods growth, stability and transition [NASA-TT-20079] p 644 N87-25307 [MBB-LKE-434-S/PUB/284] p 707 N87-26831 [DE87-008516] p 700 N87-25538 LOUDSPEAKERS LEAKAGE Active control of aerofoil flutter p 681 A87-46792 Portable fuel leak detector LOW ASPECT RATIO L [AD-A180095] p 700 N87-25550 The low-aspect-ratio parameter of blades LEGAL LIABILITY p 663 A87-43607 LABYRINTH SEALS Liability of the United States government in cases of Aerodynamic and heat transfer analysis of the low aspect Efficiency of the utilization of rotor blade shroud labyrinth air traffic controller negligence p 708 A87-42859 ratio turbine seals in an axial-compressor stage with large radial The Warsaw Convention system regarding air carrier [AIAA PAPER 87-1916] p 696 A87-45296 clearances p 694 A87-43611 responsibility - New developments in jurisprudence LOW COST LAMINAR FLOW p 709 A87-42864 Development of low-cost test techniques for advancing Laminar separation bubble characteristics on an airfoil LENGTH film cooling technology at low Reynolds numbers p 641 A87-46778 First approximation to landing field length of civil [AIAA PAPER 87-1913] p 696 A87-45293 Measurement of the effect of manufacturing deviations transport aeroplanes (50 ft., 15.24 m screen) Advances in technology for low cost turbomachinery - on natural laminar flow for a single engine general aviation [ESDU.84040] p 688 N87-26056 A potential to enhance the economy of future propulsion airplane LIFE (DURABILITY) system for general and helicopter aviation [NASA-CR-180671] p 677 N87-26044 p 676 A87-46261 Culprits causing avionic equipment failures LAMINAR FLOW AIRFOILS p 662 A87-46727 LOW LEVEL TURBULENCE Time-consistent pressure relaxation procedure for LIFE CYCLE COSTS Unresolved issues in wind shear encounters compressible reduced Navier-Stokes equations p 647 N87-25282 Engine maintenance improvement considerations p 626 A87-43377 [AIAA PAPER 87-1716] p 624 A87-45159 Helicopter-V/STOL dynamic wind and turbulence design A unique measurement technique to study The real world - A maintainer's view --- on military methodology p 658 N87-25284 laminar-separation bubble characteristics on an airfoil aircraft p 624 A87-46708 LOW REYNOLDS NUMBER [AtAA PAPER 87-1271 ] p 631 A87-44921 LIFT The effect of trip wire roughness on the performance Numerical investigation of the flow structure around a The use of discrete vortices to predict lift of a circulation of the Wortmann FX 63-137 airfoil at low Reynolds rapidly pitching airfoil control rotor section with a trailing edge blowing slot numbers p 629 A87-44019 [AIAA PAPER 87-1424] p 633 A87-44951 p 627 A87-43416 Application of low-Reynolds-number K-epsilon model to LANDING Validation of aerodynamic measurement techniques and solid fuel turbulent boundary layer combustion Control of aircraft under severe wind shear conditions calculation methods for high-lift systems [AIAA PAPER 87-1778] p 690 A87-45198 p 682 N87-26050 p 640 A87-46363 Laminar separation bubble characteristics on an airfoil First approximation to landing field length of civil Aerofoil maximum lift-coefficient for Mach numbers up at tow Reynolds numbers p 641 A87-46778 transport aeroplanes (50 ft., 15.24 m screen) to 0.4 LOW SPEED [ESDU-84040] p 688 N87-26056 [ESDU-84026] p 645 N87-26028 LANDING LOADS A promising low speed air data system for helicopters LIFTING BODIES Classification of the load-carrying capacity of runway p 661 A87-43437 Aerodynamic characteristics of wave riders surfaces by the ACN-PCN method. I Low-speed wind-tunnel results for symmetrical NASA p 637 A87-46094 p 686 A87-46353 LS(t)-O013 airfoil LIGHTNING Classification of the load-carrying capacity of runway [NASA-TM-4003] p 645 N87-26033 Lightning protection activity in the development of a new surfaces by the ACN-PCN method. II LOW SPEED WIND TUNNELS helicopter p 654 A87-43471 p 686 A87-46354 An experimental investigation of delta wings with Numerical simulation of cruiser on aircraft lightning LASER ANEMOMETERS leading-edge vortex separation p 641 A87-46956 p 646 A87-46317 An LDA investigation of three-dimensional normal LUBRICATING OILS LINEAR SYSTEMS shock-boundary layer interactions in a corner Aeroelastic derivatives as a sensitivity analysis of Helicopter lubrication p 624 A87-44733 [AIAA PAPER 87-1369] p 832 A87-44938 LUBRICATION SYSTEMS nonlinear equations p 699 A87-46797 Optical flow diagnostic measurements in LIQUID ATOMIZATION Helicopter lubrication p 624 A87-44733 turbomachinery p 698 A87-46245 Mathematical model for calculating the atomization of Contribution of laser anemometry to aircraft safety p 699 A87-46361 a liquid jet by an annular gas stream p 693 A87-43610 M LASER APPLICATIONS Influence of fuel temperature on atomization AOI displays using laser illumination MACH NUMBER p 694 A87-44726 performance of pressure-swirl atomizers p 698 A87-46198 Aero-optical analysis of compressible flow over an open LASER DOPPLER VELOCIMETERS LIQUID COOLING cavity Flow-field measurements of an airfoil with a deflected Waste heat recovery system for high altitude application [AIAA PAPER 87-1399] p 632 A87-44943 spoiler using an LDV system of liquid cooled, piston engines Cycle selection considerations for high Mach [AIAA PAPER 87-1438] p 634 A87-44955 [AIAA PAPER 87-2174] p 673 A87-45454 applications An airborne laser air motion sensing system. I - Concept LIQUID FUELS [AIAA PAPER 87-2105] p 672 A87-45410 and preliminary experiment p 662 A87-45732 Advancements in hydrogen expander airbreathing An airborne laser air motion sensing system. II - Design Recent progress in the measurement of the drag criteria and measurement possibilities engines coefficients of models of transport aircraft in a wind [AIAA PAPER 87-2003] p 670 A87-45348 p 662 A87-45733 tunnel Portable fuel leak detector [NASA-TT-20096] p 644 N87-25306 Development of a laser interferometric system for lAD-A180095) p 700 N87-25550 Aerofoil maximum lift-coefficient for Mach numbers up velocity measurements inside a transonic axial flow LIQUID-GAS MIXTURES to 0.4 compressor stage p 698 A87-46244 Mathematical model for calculating the atomization of [ESDU-84026] p 645 N87-26028 Velocity measurements near the blade tip and in the a liquid jet by an annular gas stream Effect of Reynolds number variation on aerodynamics tip vortex core of a hovering model rotor p 693 A87-43610 of a hydrogen-fueled transport concept at Mach 6 p 645 N87-26030 LITHIUM ALLOYS [NASA-TP-2728] p 645 N87-26031 LASER INTERFEROMETRY The microstructure and mechanical properties of various MAGNETOMETERS Development of a laser interferometric system for aluminium-lithium alloy product forms for helicopter Autonomous navigation system for the new generation velocity measurements inside a transonic axial flow structures p 688 A87-43454 of military helicopters and associated flight tests compressor stage p 698 A87-46244 LOAD DISTRIBUTION (FORCES) p 648 A87-43469 LASER MATERIALS Finite element analysis of large spur and helical gear MAINTAINABILITY Development and application of unified algorithms for systems Engine maintenance improvement considerations problems in computational science p 705 N87-26006 [AIAA PAPER 87-2047] p 697 A87-45379 [AIAA PAPER 87-1716] p 624 A87-45159 LATERAL CONTROL LOADS (FORCES) Study of helicopterroll control effectiveness criteria Fatigue life analysis of fuel tank skins under combined Design for repairability of helicopter rotor blades [ NASA-CR-t 77404] p 681 N87-25330 loads p 650 A87-42856 [MBB-UD-49t/86] p 658 N87-25315

A-18 SUBJECT INDEX NAVIER-STOKES EQUATION

MAINTENANCE METEOROLOGICAL RADAR Complex modal balancing of flexible rotors including T700/CT7 derivative growth engine reliability An airborne laser air motion sensing system. II - Design residual bow Consistent with longstanding industry traditions criteria and measurement possibilities [AIAA PAPER 87-1840] p 695 A87-45241 p 663 A87-43464 p 662 A87-45733 MODELS XMAN - A tool for automated jet engine diagnostics METEOROLOGY Model-based knowledge-based optical processors [AIAA PAPER 87-1931] p 696 A87-45309 Where and when helicopter icing occurs p 707 A87-42736 p 702 A87-44702 MAN MACHINE SYSTEMS Full potential modeling of blade-vortex interactions METHOD OF CHARACTERISTICS DVI in the military cockpit - A third hand for the combat p 627 A87-43417 Aerodynamic design modification of a hypersonic wind pilot --- Direct Voice input p 681 A87-46315 A comparison of the acoustic and aerodynamic tunnel nozzle by CSCM with high order accuracy --- Optimal cooperative control synthesis of active measurements of a model rotor tested in two anechoic Conservative Supra-Characteristics Method displays wind tunnels p 683 A87-43425 [AIAA PAPER 87-1896] p 635 A87-45284 MODULARITY [NASA-CR-4058] p 705 N87-25807 MICROBURSTS F-16 modular common inlet design concept MANEUVERABILITY Maximum survival capability of an aircraft in a severe [AIAA PAPER 87-1748] p 666 A87-45181 Calculated performance, stability, and maneuverability windshear p 680 A87-44254 MOLECULAR FLOW of high-speed tilting-prop-rotor aircraft Analysis of a microburst in the FACE meteorological p 651 A87-43408 Molecular flow velocity using Doppler shifted Raman mesonetwork in southern Florida p 702 A87-45962 spectroscopy Improved agility for modern fighter aircraft. II - Thrust Introduction tO the JAWS Program [AIAA PAPER 87-1531] p 693 A87-43053 vectoring engine nozzles p 673 A87-46181 p 703 N87-25270 MARECS MARITIME SATELLITES JAWS multiple Doppler derived winds MOMENTUM THEORY A conformal aircraft phased array antenna for p 703 N87-25271 Investigation of helicopter twin-rotor characteristics airplane-satellite communication in the L band Status of the JAWS Program p 703 N87-25272 p 628 A87-43438 [DFVLR-FB-86-47] p 701 N87-26259 Modeling and implementation of wind shear data MOMENTUM TRANSFER MATHEMATICAL MODELS p 709 N87-25273 An experimental low Reynolds number comparison of a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil and Rotor icing research at RAE Farnborough Microburst model requirements for flight simulation: An p 646 A87-44706 airframe manufacturer's perspective a NACA 64-210 airfoil in simulated heavy rain p 687 N87-25278 [NASA-CR-181119] p644 N87-25997 The integration o! a six axis motion system and a wide United Airlines wind shear incident of May 31, 1984 MONTE CARLO METHOD angle visual system inside a dome p 684 A87-44720 p 647 N87-25288 Simulations of ramjet combustor flow fields. I - Numerical Dual adaptive control: Design principles and MICROCOMPUTERS model, large-scale and mean motions applications [AIAA PAPER 87-1421] p 633 A87-44949 EMI.fault prevention and self recovery of digital flight [NASA-CR-181050] .p 705 N87-25804 control systems p 661 A87-43470 MOTION PERCEPTION Tip clearance flows. I - Experimental investigation o1 Micro-computer/parallel processing for real time testing an isolated rotor. II - Study of various models and Some fundamentals of simulator cockpit motion of gas turbine control systems comparison with test results p 638 A87-46208 generation p 683 A87-44714 [AIAA PAPER 87-1926] p 669 A87-45304 MOTION SIMULATION A study on the effect of non-dimensional system MICROMETEOROLOGY Exploratory evaluation of a moving-model technique for parameters on squeeze film damper performance using Analysis of a microburst in the FACE meteorological measurement of dynamic ground effects experimental data p 698 A87-46229 mesonetwork in southern Florida p 702 A87-45962 [AIAA PAPER 87-1924 p 685 A87-45303 Bounded random oscillations - Model and numerical MICROPROCESSORS MOTION SIMULATORS resolution for an airfoil Microprocessor based surge monitoring system Design of motion simulation software with digital filtering [ONERA, TP NO, 1987-73] p 681 A87-46767 p 686 A87-46241 techniques p 704 A87-44712 Numerical simulation of flows in axial and radial New standards established for realism in visual Motion software for a research flight simulator turbomachines using Euler solve{s simulation --- for commercial aircraft flight p 704 A87.44713 [ONERA, TP NO. 1987-87] p 641 A87-46776 p 686 A87-46438 Some fundamentals of simulator cockpit motion MICROSTRIP TRANSMISSION LINES Case history of FAA/SRI wind shear models generation p 683 A87-44714 Conformal microstrip communication antenna p 703 N87-25268 The integration of a s_x axis motion system and e wide p 697 A87-45689 Numerical solution of the Navier-Stokes equations about angle visual system inside a dome p 684 A87-44720 MICROSTRUCTURE three-dimensional configurations: A survey MOUNTING p 701 N87-26022 The microstructura and mechanical properties of various Airfoil flutter model suspension system A comparison of the structuraborne and airborne paths aluminium-lithium alloy product forms for helicopter [NASA-CASE.LAR-13522-1-SB] p 687 N87.25334 structures p 688 A87-43454 for propfan interior noise MTBF MICROWAVE LANDING SYSTEMS [NASA-CR-180289] p 708 N87-26612 Reliability, 'better than the best' p 699 A87.46728 Application of wedge diffraction theory to estimating MEASURING INSTRUMENTS power density at airport humped runways The treatment of calibrations of total air temperature p 650 A87-46861 N probes for use in flight-test analysis work MIG AIRCRAFT [ESDU-84007] p 701 N87-26324 The new Soviet lighters - How good are they? NACELLES MECHANICAL PROPERTIES p 656 A87-46312 The art of reticulation and applicable adhesives --- for Thermal and flammability characterization of graphite MIL AIRCRAFT acoustically treated engine nacelles p 665 A87-44582 composites p 688 A87-43398 Soviet helicopter development p 657 A87-46735 NASTRAN The microstructura and mechanical properties ot various MILITARY AIRCRAFT Determination of the structural properties of helicopter aluminium-lithium alloy product forms for helicopter The real world - A maintainer's view --- on military rotor blades by theoretical and experimental methods structures p 688 A87-43454 aircraft p 624 A87-46708 p 653 A87-43450 Developments in titanium alloys p 689 A87-44744 NAV|ER-STOKES EQUATION Research and development. Technical-scientific Superplastic forming/diffusion bonding of titanium Time-consistent pressure relaxation procedure for publications 1986 p 689 A87-44747 [ETN-87-99713] p 710 N87-26826 compressible reduced Navier-Stokes equations MESOMETEOROLOGY p 626 A87-43377 Use of artificial intelligence methods Analysis of a microburst in the FACE meteorological Navier-Stokes simulation of a hypersonic generic [MBB-LKE-434-S/PUB/284] p 707 N87-26831 mesonetwork in southern Florida p 702 A87-45962 wing/fuselage MILITARY HELICOPTERS METAL BONDING [AIAA PAPER 87-1192 p 629 A87.44902 An analytic method of quantifying helicopter agility The art ot reticulation and applicable adhesives --- ter Incompressible Nsvier-Stokes computations of vortical p 678 A87-43432 acoustically treated engine nacelles p 665 A87-44582 flows over double-delta wings Superplastic forming/diffusion bonding of titanium Irish Dauphin helicopter S.A.R, system flight tests --- [AIAA PAPER 87-1341 p 631 A87-44933 Search and Rescue p 648 A87-43455 p 689 A87-44747 Navier-Stokes simulations of supersonic fighter intake METAL COATINGS Development program of a full authority digital electronic flowfields A study of the thermal-stress state of gas turbine engine control system for the T55-L-712E turbosheff engine [AIAA PAPER 87.1752 p 634 A87.45185 blades with protective coatings p 664 A87-43640 p 663 A87.43465 Unsteady thrae-dimensional Navier-Stokes simulations METAL MATRIX COMPOSITES Icing clearance criteria 1or UK _litary hel4copters of turbine rotor-ststor interaction Dynamic mechanical properties of advanced composite p 646 A87-44705 [AIAA PAPER 87-2058 p 636 A87-45386 materials and structures: A review p 691 N87-25988 State-of-the-art test facilities for development of the Navier-Stokes solutions for highly loaded turbine cascades METAL SHEETS Army's T800-LHT-800 LHX helicopter engine Analytical description of crack resistance curves for [AIAA PAPER 87-1790] p 684 A87-45204 [AIAA PAPER 87-2151 p 637 A87.45436 aluminum sheets used in aircraft construction Navier-Stokes analysis of a very-high-bypass-ratio EH.101 - The helicopter matures p 657 A87-4637t turbofan engine in reverse thrust [MBS-UT-133/85] p 700 N87-25604 Soviet helicopter development p 657 A87-46735 METEOROLOGICAL FLIGHT [AIAA PAPER 87-2170 p 697 A87-45450 MILITARY TECHNOLOGY An airborne laser air motion sensing system. I - Concept Unsteady viscous flows round moving circular cylinders Military specifications p 658 N87-25281 and preliminary experiment p 662 A87-45732 and airfoils. II p 637 A87-45792 METEOROLOGICAL PARAMETERS MINIATURIZATION An improved approach for transonic flow A miniature remote deadweight calibrator Case history of FAA/SRI wind shear models p 639 A87-46215 p 694 A87-45104 p 703 N87-25268 Computational fluid dynamics: Transition to design Introduction to the JAWS Program MIXING LENGTH FLOW THEORY applications p 700 N87.26004 p 703 N87-25270 The mixing of iets under simulated engine-like Application of CFD codes to the design and development JAWS multiple Doppler derived winds lurbulence p 698 A87-46231 of propulsion systems p 677 N87-26009 p 703 N87-25271 MODAL RESPONSE Computational fluid dynamics research at the United Wind shear and turbulence simulation An improved assumed mode method for estimating the Technologies Research Center requiring p 709 N87-25274 motion of a nonuniform rotor blade p 653 A87-43445 supercomputers p 701 N87°26011

A-19 NAVY SUBJECT INDEX

Experience with 3-D composite grids NUMERICAL ANALYSIS Optimization methods applied to the aerodynamic design p 706 N87-26021 Bounded random oscillations - Model and numerical of helicopter rotor blades Numerical solution of the Navier-Stokes equations about resolution for an airfoil [NASA-TM-89155] p 660 N87-26042 throe-dimensional configurations: A survey [ONERA, TP NO. t987-73] p 681 A87-46767 Industrial application of computer aided structural p 701 N87-26022 NUMERICAL CONTROL optimization in aircraft construction NAVY Development of Digital Engine Control System for the [MBB-UT-273/86] p 706 N87-26523 Sparing to optimize navsi airship availability Harrier II OSCILLATING FLOW p 625 A87-46716 [AIAA PAPER 87-2184] p 673 A87-45458 Numerical simulation and comparison with experiment NEUTRON RADIOGRAPHY Dual adaptive control: Design principles and for self-excited oscillations in a diffuser flow p 693 A87-43381 Real-time neutron imaging of gas turbines applications The pitching damping derivatives measured by [AIAA PAPER 87-1762] p 695 A87-45189 [NASA-CR-tat050] p 705 N87-25804 force-oscillation method at transonic and supersonic wind NIGHT FLIGHTS (AIRCRAFT) NUMERICAL FLOW VISUALIZATION tunnel p 686 A87-46958 Colour dependence and surplus information in airport Direct simulation of aerothermal loads for an aeroassist visual aids during VFR operations p 649 A87-44040 OUTER SPACE TREATY flight experiment vehicle The Warsaw Convention system regarding air carrier NITROGEN COMPOUNDS [AIAA PAPER 87-1546] p 626 A87-43063 responsibility - New developments in jurisprudence Degradation mechanisms of sulfur and nitrogen Numerical simulation and comparison with experiment p 709 A87-42864 containing compounds during thermal stability testing of for self-excited oscillations in a diffuser flow model fuels OUTPUT p 693 A87-4338t Auxiliary data input device [AIAA PAPER 87-2039] p 690 A87-45372 Simulations of ramjet combustor flow fields. II - Origin NITROGEN OXIDES [NASA-CASE-LAR-13626-1] p 700 N87-25584 of pressure oscillations NO(x) reduction and combustion phenomena in the [AIAA PAPER 87-1422] p 633 A87-44950 multi-annular gas turbine swirl burner The numerical simulation of subsonic flutter P [AIAA PAPER 87-2036] p 671 A87-45370 [AIAA PAPER 87-1428] p 633 A87-44952 NOISE MEASUREMENT Two-dimensional numerical analysis for inlets at PAINTS Measurement of noise from airplanes traveling at 3500 subsonic through hypersonic speeds Aircraft skin that bruises p 691 A87-46874 to 11000 m altitude [AIAA PAPER 87-1751] p 634 A87-45184 Factors affecting the sticking of insects on modified [FFA-TN.t986-21] p 708 N87-25824 Numerical simulation of transonic throe-dimensional aircraft wings NOISE PREDICTION (AIRCRAFT) flows in turbine blade passages p 638 A87-46206 [NASA-CR-t80957] p 659 N87-26037 Investigation of the aerodynamic performance and noise Flow phenomena in transonic turbine cascades detailed PANEL METHOD (FLUID DYNAMICS) characteristics of a 1/Eth scale model of the Dowty Rotol experimental and numerical investigation A panel method for counter rotating propfans R212 propeller p 640 A87-46265 p 639 A87-46223 [AIAA PAPER 87-1890] p 668 A87-45279 Measurement of noise from airplanes traveling at 3500 A panel method for prediciting the dynamic stability to 11000 m altitude derivatives of an oscillating wing in high subsonic flow [FFA-TN-1986-21] p 708 N87-25824 0 p 641 A87-46951 NOISE REDUCTION The Aeronautical Research Institue (FFA) wing body 85 The art of reticulation and applicable adhesives --- for OBLIQUE SHOCK WAVES computer program. A panel method for determination of acoustically treated engine nacelles p 665 A87-44582 Morphology of a standing oblique detonation wave --- aeroelastic characteristics applying direct block iterative NONLINEAR EQUATIONS for hypersonic airbreathing propulsion solution techniques An advanced mathematical model for helicopter flight [AIAA PAPER 87-1785] p 695 A87-45201 [FFA-TN-1986-28] p 642 N87-25298 simulation using nonlinear unsteady aerodynamics Progress toward shock enhancement of supersonic Development of a geometry handling program for the p 679 A87.43435 combustion processes FFA subsonic higher order panel method Aeroelastic derivatives as a sensitivity analysis of [AIAA PAPER 87-1880] p 890 A87-45274 [FFA-TN-1985-48] p 699 N87-25534 nonlinear equations p 699 A87-46797 Standing oblique detonation wave engine performance Viscid/inviscid separated flows NONLINEAR SYSTEMS [AIAA PAPER 87-2002] p 670 A87-45347 [AD-A179858] p 699 N87-25536 ON-LINE SYSTEMS Influence of third-degree geometric nonlinearities on the Steady and unsteady aerodynamic forces from the Microprocessor based surge monitoring system vibration and stability of pretwisted, preconed, rotating SOUSSA surface-panel method for a fighter wing with tip blades p 674 A87-46228 p 686 A87-46241 missile and comparison with experiment and PANAIR OPERATING TEMPERATURE On the nonlinear aerodynamic and stability [NASA-TP-2736] p 645 N87-26032 Hydrogen scram jet with sidewall injection- Shock tunnel characteristics of a generic chine-forebedy slender-wing PANELS simulations p 674 A87-46217 fighter configuration Truss-core corrugation for compression loads [NASA-TM-89447] p 643 N87-25305 OPERATOR PERFORMANCE [NASA-CASE-EAR-13438-1] p 699 N87-25496 NONLINEARITY United Airlines wind shear incident of May 31, 1984 PARALLEL PROCESSING (COMPUTERS) Influence of third-degree geometric nonlinearities on the p 647 N87-25287 OPTICAL COMMUNICATION Micro-computer/parallel processing for real time testing vibration and stability of pretwisted, preconed, rotating Airborne laser communications scintillation of gas turbine control systems blades p 674 A87-46228 measurements p 649 A87-45722 [AIAA PAPER 87-1926] p669 A87-45304 NOSE CONES OPTICAL DATA PROCESSING Computational fluid dynamics research at the United Direct simulation of aerothermal loads for an aeroassist Model-based knowledge-based optical processors Technologies Research Center requiring flight experiment vehicle p 707 A87-42736 supercomputers p 701 N87-26011 [AIAA PAPER 87-t546] p 626 A87-43063 OPTICAL MEASURING INSTRUMENTS PARAMETER IDENTIFICATION NOZZLE DESIGN Optically interfaced sensor system for aerospace A parametric investigation of a free wake analysis of Aerodynamic design modification of a hypersonic wind applications p 694 A87-45107 hovering rotors p 627 A87-43413 tunnel nozzle by CSCM with high order accuracy --- Optical flow diagnostic measurements in Experience with frequency-domain methods in Conservative Supra-Characteristics Method turbomachinery p 698 A87-46245 helicopter system identification p 680 A87-43457 [AIAA PAPER 87-1896] p 635 A87-45284 OPTICAL RADAR Gust response of helicopters p 682 N87-26049 Application of ceramics to ramjet engine nozzles An airborne laser air motion sensing system. II - Design PARAMETERIZATION p 690 A87-46221 criteria and measurement possibilities Aeroelastic derivatives as a sensitivity analysis of NOZZLE FLOW p 662 A87-45733 nonlinear equations p 699 A87-46797 Static investigation of post-exit vanes for multiaxis thrust OPTICAL SCANNERS PARTICLE LADEN JETS vectodng Wind tunnel experimental study of optical beam On the evolution of particle-laden jet flows - A theoretical [AIAA PAPER 87-1834] p 667 A87-45236 degradation through heterogeneous aerodynamic flows and experimental study Aerodynamic and heat transfer analysis o1 the low aspect [ONERA, TP NO. 1987-50] p 707 A87-46753 [AIAA PAPER 87-2181] p 697 A87-45457 ratio turbine OPTIMAL CONTROL [AIAA PAPER 87-1916] p 696 A87-45296 A combined stochastic feedforward and feedback PASSENGER AIRCRAFT Fokker 50 - Pedigree with power p 656 A87-45647 Secondary stream and excitation effects on control design methodology with application to autoland two-dimensional nozzle plume characteristics design Seastar - Glass, plastic, and tradition [AIAA PAPER 87-2112] p 637 A87-45414 [NASA-CR-4078] p 705 N87-25806 p 656 A87-45648 Investigation on the stall margin of a turbofan engine Singular trajectories in airplane cruise-dash Dornier 328 - Concept for a new-geoeration regional p 675 A87-46239 optimization airliner p 657 A87-46326 [NASA-CR-180636] p 659 N87-26035 NOZZLE GEOMETRY Technological aspects in preparing the development of Optimal flight trajectories in the presence of windshear, Vortex-nozzle interactions in ramjet combustors regional airliners p 657 A87-46327 1984-86 [AIAA PAPER 87-1871] p 668 A87-45266 Burning questions --- tireworthiness of aircraft cabin [NASA-CR-t80316] p 682 N87-26047 materials p 646 A87-46373 Secondary stream and excitation effects on OPTIMIZATION two-dimensional nozzle plume characteristics Aircraft technologies of the nineties in MBB passenger Performance seeking control for cruise optimization in aircraft projects [AIAA PAPER 87-2112] p 637 A87-45414 fighter aircraft [MBB-UT-21/86] p 625 N87-25291 Computational fluid dynamics research at the United [AIAA PAPER 87-1929] p 681 A87-45307 Annual review of aircraft accident data. US air carder Technologies Research Center requiring HALE thermal balance --- High Altitude Long Endurance operations calendar year 1983 supercomputers p 701 N87-26011 remotely piloted vehicles [PB87-160628] p 648 N87-25311 NOZZLE INSERTS [AIAA PAPER 87-2172] p 656 A87-45452 Application of ceramics to ramjet engine nozzles Stress analysis and optimisation of turbine rotor blade Aircraft technology of the nineties in MBB passenger p 690 A87-46221 shrouds p 699 A87-46250 aircraft projects NOZZLE THRUST COEFFICIENTS Spadng to optimize naval airship availability [MBB-UT-0021/86] p 660 N87-26834 Secondary stream and excitation effects on p 625 A87.46716 PASSENGERS two-dimensional nozzle plume characteristics Interdisciplinary optimum design --- of aerospace Airlines are exempt from law on rights of the disabled [AIAA PAPER 87-2112] p 637 A87-45414 structures p 657 A87-47009 p 709 A87-42863

A-20 SUBJECT INDEX PROPULSION SYSTEM PERFORMANCE

PATTERN RECOGNITION PITCHING MOMENTS PRODUCTION ENGINEERING Model-based knowledge-based optical processors Numerical investigation Of the flow structure around a Engineering and cost principles for increasing the p 707 A87-42736 rapidly pitching airfoil production efficiency and maintainability of aircraft PAVEMENTS [AIAA PAPER 87-1424] p 633 A87-44951 engines p 664 A87-43620 Classification of the load-carrying capacity of runway The pitching damping derivatives measured by PROP-FAN TECHNOLOGY surfaces by the ACN-PCN method. I force-oscillation method at transonic and supersonic wind Countdown to the propfan p 664 A87-44272 p 686 A87-46353 tunnel p 686 A87-46958 Propfan propulsion systems for the 1990's PLASTIC AIRCRAFT STRUCTURES PERFORMANCE PREDICTION [AIAA PAPER 87-1729] p 665 A87-45168 Scan stabilization and jitter control for an airborne A decade of composite rudder service reviewed Engine design and systems integration for propfan and telescope p 660 A87-42812 p 689 A87-44861 PLUMES high bypass turbofan engines Substantiation of the analytical prediction of ground and [AIAA PAPER 87-1730] p 665 A87-45169 sir resonance stability of a bearingless rotor, using model Two-dimensional nozzle plume characteristics Preparing a propfan propulsion system for flight test scale tests p 654 A87-43463 [AIAA PAPER 87-2111 ] p 636 A87.45413 [AIAA PAPER 87-1731] p 665 A87-45170 Simulation of performance, behaviour and faults of Secondary stream and excitation effects on two-dimensional nozzle plume characteristics UDF/727 flight test program aircraft engines [AIAA PAPER 87-2112] p 637 A87-45414 [AIAA PAPER 87-1733] p 666 A87-45171 [AIAA PAPER 87-1866] p 668 A87.45263 POLLUTION TRANSPORT A panel method for counter rotating propfans An experimental investigation of turbine case Large-scale distribution of peroxyacetylnitrate results [AIAA PAPER 87-1890] p 668 A87-45279 treatments from the STRATOZ III flights p 702 A87-46481 [AIAA PAPER 67-1919] p 669 A87-45299 Wind tunnel tests on a one-foot diameter SR-7L propfan POLYMERIC FILMS model Performance estimation of an aircraft internal Factors affecting the sticking of insects on modified [AIAA PAPER 87-1892] p 635 A87-45281 combustion engine aircraft wings Results of acoustic tests of a Prop-Fan model [AIAA PAPER 87-2173] p 672 A87-45453 [NASA-CR-180957] p 659 N87-26037 [AIAA PAPER 87-1694] p 707 A87-45282 Performance prediction in a centrifugal compressor PORTABLE EQUIPMENT Transmission efficiency in advanced aerospace impeller p 674 A87-46190 Portable fuel leak detector powerplant Application of engine component life methodology to [AD-Af80095] p 700 N87-25550 [AIAA PAPER 87-2043] p 671 A87-45376 life assessment p 698 A87-46230 POSITION ERRORS Propfan propulsion system development An experimental low Reynolds number comparison of Geostationary satellite navigation systems p 675 A87-46247 a Wortmann FX67.K170 airfoil, a NACA 0012 airfoil and p 648 A87-42786 Aircraft technologies of the nineties in MBB passenger a NACA 64-210 airfoil in simulated heavy rain POTENTIAL FLOW aircraft projects [NASA-CR-181ff9] p 644 N87-25997 A unified approach for potential and viscous free-wake [MBB-UT-21/86] p 625 N87-25291 PERFORMANCE TESTS analysis of helicopter rotors p 627 A87-43412 Wind tunnel performance results of an aeroelastically Testing automated ground collision avoidance systems POTENTIAL GRADIENTS scaled 2/9 model of the PTA flight test prop-fan on the AFTI/F-16 p 660 A87-43375 Full potential modeling of blade-vortex interactions [NASA-TM.89917] p 642 N87-25294 A rugged electronic pressure scanner designed for p 627 A87-43417 A comparison of the structureborne and airborne paths turbine test p 695 A87-45124 POWER EFFICIENCY for propfan interior noise Effect of planform taper on hover performance of an A study on the effect of non-dimensional system [NASA-CR-180269] p 708 N87-26612 PROPELLER BLADES advanced AH-64 model rotor parameters on squeeze film damper performance using [NASA-TM-89145] p 643 N87-25304 experimental data p 698 A87-46229 Computation of the flow fields of propellers and hovedng rotors using Euler equations p 628 A87-43418 Development and testing of critical components for the PREDICTION ANALYSIS TECHNIQUES Influence of third-degree geometric nonlinearities on the technological preparation on an Airbus fuselage made of Fatigue crack growth predictions of welded aircraft carbon fiber reinforced plastics, phase 1 structures containing flaws in the residual stress field vibration and stability of pretwisted, preconed, rotating blades p 674 A87-46228 [BMFT-FB-W-86-017] p 692 N87-2615f p 692 A87-42853 Wind tunnel performance results of an aeroelastically PERIODIC VARIATIONS The use of discrete vortices to predict lift of a circulation scaled 219 model of the PTA flight test prop-fan A new simulation of airfoil dynamic stall due to velocity control rotor section with a trailing edge blowing slot and incidence fluctuations [NASA-TM-89917] p 642 N87-25294 p 627 A67-43416 PROPELLER EFFICIENCY [AIAA PAPER 87-1242] p 630 A87-44915 Dynamic data acquisition, reduction, and analysis for Extension of local circulation method to counter rotation PEROXIDES the identification of high-speed compressor component propeller Large.scale distribution of peroxyacetylnitrate results post.stability characteristics ]AIAA PAPER 87-1891] p 635 A87-45280 from the STRATOZ III flights p 702 A87-46481 [AIAA PAPER 87-2089] p 697 A87-45398 Investigation of the aerodynamic performance and noise PHASED ARRAYS Culprits causing avionic equipment failures characteristics of a 1/Sth scale model of the Dowry Rotol A conformal aircraft phased array antenna for p 662 A87-46727 R212 propeller p 640 A87-46265 airplane-satellite communication in the L band PRESSURE DISTRIBUTION Study of the aerodynamics of high-speed propellers [DFVLR.FB-86-47] p 701 N87-26259 A panel method for prediciting the dynamic stability [ONERA, TP NO. 1987-61] p 640 A87-46761 PILOT PERFORMANCE derivatives of an oscillating wing in high subsonic flow PROPELLER FANS Simulator evaluations of inceptors for ACT helicopters p 641 A87-46951 Wind tunnel performance results of an aeroelastically p 678 A87-43405 Two-dimensional subsonic and transonic wind tunnel scaled 2/9 model of the PTA flight test prop-fan Observations of pilot control strategy in low level wall interference corrections for varied walls [NASA-TM-89917] p 642 N87-25294 helicopter flying tasks p 678 A87-43433 p 686 A87-46955 Integration of the propfan concept in aircraft design Aviation safety and the FAA's quality assurance PRESSURE DRAG [MBB-UT-0001/86] p 677 N87-26835 PROPELLER SLIPSTREAMS program p 709 A87-44064 A multi-body aircraft with an all-movable center fuselage Flow behind single- and dual-rotation propellers at angle A program to investigate requirements for effective flight actively controlling fuselage pressure drag of attack simulator displays p 683 A87-44715 [NASA-CASE-LAR.13511-1] p 658 N87-25320 PRESSURE GRADIENTS [AIAA PAPER 87-1750] p 634 A87-45183 Wind Shear/Turbulence Inputs to Flight Simulation and PROPELLERS Systems Certification Flow over a trailing flap and its asymmetric wake Performance calculation of counter rotation propeller [NASA-CP-2474] p 625 N87-25267 p 626 A87-43376 [AIAA PAPER 87-1889] p 635 A87-45278 B-57B gust gradient program p 657 N87-25276 Optimal cooperative control synthesis of active Evaluation of installed performance of a displays PRESSURE MEASUREMENT wing-tip-mounted pusher turboprop on a semispan wing [NASA-CR-4058] p 705 N87-25807 A computational method for determining flowfield [NASA-TP-2739] p 659 N87-26041 PILOT TRAINING properties when the pitot pressure is the only measured A comparison of the structureborne and airborne paths Application of data to piloted simulators instream property p 637 A87-46184 for propfan interior noise p 687 N87-25275 PRESSURE OSCILLATIONS [NASA-CR-180289] p 708 N87-26612 Simulator manufacturers' requirements Simulations of ramjet combustor flow fields. II - Odgin PROPULSION SYSTEM CONFIGURATIONS p 687 N87-25280 of pressure oscillations Propfan propulsion systems for the 1990's Accident investigation p 647 N87-25285 [AIAA PAPER 87-1422] p 633 A87-44950 [AIAA PAPER 87-1729] p 665 A87-45168 PILOTLESS AIRCRAFT Pressure oscillations and acoustic-entropy interactions Propfan propulsion system development Aerodynamics of unmanned aircraft at full-scale in the in ramjet combustion chambers p 675 A87-46247 RAE 24ft wind-tunnel [AIAA PAPER 87-1872] p 668 A87-45267 Advances in technology for low cost turbomachinery - [RAE-TM-AERO-2081 ] p 645 N87-26027 PRESSURE SENSORS A potential to enhance the economy of future propulsion PISTON ENGINES A rugged electronic pressure scanner designed for system for general and helicopter aviation Waste heat recovery system for high altitude application turbine test p 695 A87-45124 p 676 A87-46261 of liquid cooled, piston engines Miniature remote dead weight calibrator Application of CFD codes to the design and development [AIAA PAPER 87-2174] p 673 A87-45454 of propulsion systems p 677 N87-26009 PITCH (INCLINATION) [NASA-CASE-LAR.13564-1] p 700 N87-25558 Design applications for supercomputers The effect of pitch rate on the dynamic stall or a modified PRINTED CIRCUITS p 706 N87-26010 Culprits causing avionic equipment failures NACA 23012 aerofoil and comparison with the unmodified PROPULSION SYSTEM PERFORMANCE p 662 A87-46727 case p 628 A87-43420 Impact of engine technology on supersonic STOVL PRODUCT DEVELOPMENT Errors in the measurement of the course angles of radar [AIAA PAPER 87-1709] p 665 A87-45157 reference points due to the imprecise stabilization of the The real world - A maintainer's view --- on military Preparing a propfan propulsion system for flight test antenna mounting in bank and pitch aircraft p 624 A87-46708 [AIAA PAPER 87-1731] p 665 A87-45170 p 649 A87-44312 Development of novel bearingless rotor systems High performance turbofan afterburner systems Visualization of three-dimensional structures about a [MBB-UD-471/86] p 702 N67-26837 [AIAA PAPER 87-1630] p 666 A87-45234 pitching forward swept wing Avionics systems for future civil helicopters Flight test of the F100-PW-220 engine in the F-16 [AIAA PAPER 67-1322] p 631 A87-44929 [MBB-UD-473/86] p 662 N87-26836 [AIAA PAPER 87-1845] p 667 A87-48245

A-21 PROPULSIVE EFFICIENCY SUBJECT INDEX

System performance approach to air breathing RADIAL FLOW REMOTELY PILOTED VEHICLES propulsion design - A new undergraduate design Effect of swirl on the performance of a radial vaneless HALE thermal balance --- High Altitude Long Endurance competition diffuser with compressible flow at Mach numbers of 0.7 remotely piloted vehicles ]AIAA PAPER 87-1869] p 668 A87-45264 and 0.8 [AIAA PAPER 87-2172] p 656 A87-45452 Integration of propulsion/integration test results through [ASME PAPER 86-WA/FE-6] p 629 A87-43704 Waste heat recovery system for high altitude application the use of reference plane transfers RADIATIVE HEAT TRANSFER of liquid cooled, piston engines [AIAA PAPER 87-1964] p670 A87-45333 Volume interchange factors for hypersonic vehicle wake [AIAA PAPER 87-2174] p 673 A87-45454 Thrust/drag accounting for aerospace plane vehicles radiation RESEARCH AND DEVELOPMENT [AIAA PAPER 87-1966] p 656 A87-45335 [AIAA PAPER 87-1520] p 707 A87-43044 T700/CT7 derivative growth engine reliability - Standing oblique detonation wave engine performance Natural convection flow of a radiating rarefied gas Consistent with longstanding industry traditions [AIAA PAPER 87-2002] p 670 A87-45347 between concentric rotating spheres p 663 A87-43464 Flight test and evaluation of propulsion system [AIAA PAPER 87-1523] p 693 A87-43046 The tilt-rotor aircraft - A response to the future? From Operability characteristics RAIN European interrogations to Eurofar actions [AIAA PAPER 87-2092] p 686 A87-45400 [MBB-UD-485-86-PUB] p 654 A67-43474 An experimental low Reynolds number comparison of Cycle selection considerations for high Mach Rotorcraft research - A national effort (The 1986 a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil and applications Alexander Nikolsky Honorary Lectureship) a NACA 64-210 airfoil in simulated heavy rain ]AIAA PAPER 87-2105] p 672 A87-454t0 p 623 A87-44255 [NASA-CR-181119] p644 N87-25997 A study of some factors affecting the performance of Rotor icing research at RAE Farnborough RAMAN SPECTROSCOPY a contra-rotating axial compressor stage p 646 A87-44706 Molecular flow velocity using Doppler shifted Raman p 639 A87-46211 U.S. aeronautical R&D goals - SST: bridge to the next spectroscopy Application of a fuzzy controller in fuel system of turbojet century p 624 A87-46182 [AIAA PAPER 87-1531] p 693 A87-43053 engine p 674 A87-46227 National Aerospace Plane Program: Principal RAMJET ENGINES Integration of the propfan concept in aircraft design assumptions, findings and policy options Simulations of ramjet combustor flow fields. I - Numerical ]MBB-UT-0001/86} p 677 N87-26835 {RAND/P-7288-RGS] p 625 N87-25990 model, large-scale and mean motions PROPULSIVE EFFICIENCY Research and development. Technical-scientific [AIAA PAPER 87-1421] p 633 A87-44949 A bidirectional tapered roller thrust bearing for gas publications 1986 turbine engines Simulations of ramjet combustor flow fields. II - Origin [ETN-87-99713] p 710 N87-26826 [AIAA PAPER 87-1842] p 695 A87-45243 of pressure oscillations RESIDUAL STRESS Propfan propulsion system development [AIAA PAPER 87-1422] p 633 A87-44950 Fatigue crack growth predictions of welded aircraft p 675 A87-46247 Vortex-nozzle interactions in ramjet combustors structures containing flaws in the residual stress field PROTECTIVE COATINGS [AIAA PAPER 87-1871} p 666 A87-45266 p 692 A87-42853 Corrosion protection -- in aircraft structures Pressure oscillations and acoustic-entropy interactions Fatigue and fracture meChanics analysis of compression p 624 A87-44750 in ramjet combustion chambers loaded aircraft structure p 692 A87-42854 Aircraft skin that bruises p 691 A87-46874 [AIAA PAPER 87-1872] p 668 A87-45267 RESONANCE TESTING Factors affecting the sticking of insects on modified Application of ceramics to ramjet engine nozzles Validation of a method for air resonance testing of aircraft wings p 690 A87-46221 helicopters at model scale using active control of Pylon [NASA-CR-180957] p 659 N87-26037 RANDOM VIBRATION dynamic characteristics p 683 A87-43462 PULSEJET ENGINES RESONANT FREQUENCIES Bounded random oscillations - Model and numerical Numerical study of the gasdynamic process in a pulse]el resolution for an airfoil Research on the stress analysis method of rubber engine p 663 A87-43614 structure - Calculation of the frequency adapter stresses [ONERA, TP NO. 1987-73] p 681 A87-46767 PYLON MOUNTING p 693 A87-43453 RANKINE CYCLE Integration effects of pylon geometry and rearward RESONANT VIBRATION Compound cycle engine for helicopter application mounted nacelles for a high-wing transport Substantiation of the analytical prediction of ground and [NASA-CR-175110] p 677 N87-25323 [AIAA PAPER 87-1920} p 655 A87-45300 air resonance stability of a bearingless rotor, using modal RAREFIED GAS DYNAMICS PYLONS scale tests p 654 A87-43463 Validation of a method for air resonance testing of Natural convection flow of a radiating rarefied gas REYNOLDS NUMBER helicopters at model scale using active control of Pylon between concentric rotating spheres Effect of Reynolds number variation on aerodynamics (AIAA PAPER 87-1523] p 693 A87-43046 dynamic characteristics p 683 A87-43462 of a hydrogen-fueled transport concept at Mach 6 REACTION KINETICS [NASA.TP-27281 p 845 N87-2603t A simple model for finite chemical kinetics analysis of RIDING QUALITY Q supersonic turbulent shear layer combustion Military specifications p 658 N87-25281 [AIAA PAPER 87-1879] p 696 A87-45273 Correlation of B-1 flight test subjective assessments and QUANTUM CHEMISTRY Computational chemistry p 706 N87-26023 some ride quality/vibration exposure criteria Computational chemistry p 706 N87-26023 REAL TIME OPERATION lAD-A179844) p 658 N87-25318 Real-time wind estimation and tracking with transponder RIGID ROTORS R downlinked airspeed and heading data FEL - A new main rotor system p 651 A87-43402 p 648 A87-42779 Optimum design of a helicopter rotor blade p 651 A87-43406 RADAR ANTENNAS Helicopter model in flight identification by a real time RIVETING Errors in the measurement of the course angles of radar self adaptive digital process p 680 A87-43458 Technological change and skill requirements - A case reference points due to the imprecise stabilization of the Real-time neutron imaging of gas turbines study Of numerically controlled riveting in commercial [AIAA PAPER 87-1762] p 695 A87-45189 antenna mounting in bank and pitch aircraft manufacture p 649 A87-44312 RECIRCULATIVE FLUID FLOW ]ASME PAPER 86-WAITS-2] p 623 A87-43723 RADAR CROSS SECTIONS Application of computational fluid dynamics to analysis ROLL of exhaust gas/diffuser interactions in a turbine engine An automated radar-signature measurement system Study of helicopterroU control effectiveness criteria altitude test cell p 698 A87-45886 [NASA-CR-177404] p 681 N87-25330 RADAR DATA [AIAA PAPER 87-2014] p 670 A87-45354 ROLLER BEARINGS RECTANGULAR WINGS The quality of radar data and its determination at the A bidirectional tapered roller thrust bearing for gas radar installations of the Bundesanstalt fuer Detailed near-wake flowfietd surveys with comparison turbine engines Flugsicherung p 650 A87-45878 to an Euler method of an aspect ratio 4 rectangular wing [AIAA PAPER 87-t842) p 695 A87-45243 RADAR DETECTION [NASA-TM-89357] p 644 N87-25993 ROTARY STABILITY An airborne collision avoidance system - The TCAS REDUCTION (CHEMISTRY) Influence of third-degree geometric nonlinearities on the p 649 A87-44231 NO(x) reduction and combustion phenomena in the vibration and stability of pretwisted, preconed, rotating An automated radar-signature measurement system multi-annular gas turbine swirl burner blades p 674 A87-46228 p 698 A87-45886 [AIAA PAPER 87-2036] p 671 A87-45370 ROTARY WING AIRCRAFT JAWS multiple Doppler derived winds REDUNDANCY ENCODING Full potential modeling Of blade-vortex interactions p 703 N87-25271 Advanced detection, isolation and accommodation of p 627 A87-43417 RADAR EQUIPMENT sensor failures: Real-time evaluation Contingency power for small turboshaft engines using [NASA-TP-2740] p 682 N87-25331 water injection into turbine cooling air Radar Technology 1986; Symposium, 6th, Bremen, West [AIAA PAPER 87-1906] p 668 A87-45289 Germany, Nov. 4-6, 1986, Reports p 697 A87-45876 RELAXATION METHOD (MATHEMATICS) Radar requirements for future avionics systems Time-consistent pressure relaxation procedure for Study of helicopterroll control effectiveness criteria compressible reduced Navier-Stokea equations [NASA-CR-177404] p 681 N87-25330 p 662 A87-45879 RADAR SCATTERING p 626 A87-43377 ROTARY WINGS RELIABILITY ANALYSIS Helicopter activities in Germany p 623 A87-4340t An automated radar-signature measurement system T700/CT7 derivative growth engine reliability - p 698 A87-45886 FEL - A new main rotor system p 651 A87-43402 Consistent with longstanding industry traditions RADAR SIGNATURES Optimum design of a helicopter rotor blade p 663 A87-43464 p 651 A87-43406 An automated radar-signature measurement system Application of engine component life methodology to p 698 A87-45886 Measurement of side forces of a H-force rotor life assessment p 698 A87-46230 RADAR TRACKING REMOTE SENSING p 651 A87-43410 Real-time wind estimation and tracking with transponder A miniature remote deadweight calibrator Prediction of blade airloads in hovering and forward flight downlinked airspeed and heading data p 694 A87-45104 using free wakes p 651 A87-43411 p 648 A87-42779 REMOTE SENSORS A unified approach for potential and viscous free-wake RADIAL DISTRIBUTION Advanced detection, isolation and accommodation of analysis of helicopter rotors p 627 A87-43412 A prescribed radial distribution circulation of a hovering sensor failures: Real-time evaluation A parametric investigation of a free wake analysis of rotor blade p 627 A87-43414 [NASA-TP.2740] p 682 N87-25331 hovering rotors p 627 A87-43413

A-22 SUBJECT INDEX SEPARATED FLOW

Computation of the flow fields of propellers and hovering Rotor wake segment influence on stator-surface RUBBER rotors using Euler equations p 628 A87-43418 boundary layer development in an axial-flow compressor Research on the stress analysis method of rubber The effect of pitch rate on the dynamic stall or a modified stage structure - Calculation of the frequency adapter stresses NACA 23012 aerofoil and comparison with the unmodified [AIAA PAPER 87-174t] p 695 A87-45178 p 693 A87-43453 case p 628 A87-43420 Performance calculation of counter rotation propeller RUDDERS The influence of winglets on rotor aerodynamics [AIAA PAPER 87-1889] p 635 A87.45278 A decade of composite rudder service reviewed Extension of local circulation method to counter rotation p 628 A87-43422 p 689 A87-44861 propeller Measurements of the performance of a helicopter swept RUNWAY CONDITIONS [AIAA PAPER 87-189t] p 635 A87-45280 tip rotor in flight p 652 A87-43423 Classification of the load-carrying capacity of runway Results of acoustic tests of a Prop-Fan model An analysis of in-fin tail rotor noise surfaces by the ACN-PCN method. II [AIAA PAPER 87-1894] p 707 A87-45282 p 652 A87-43427 p 686 A87-46354 Experimental data correlations for the effects of rotation RUNWAYS Stability and control modelling --- helicopters in near on impingement cooling of turbine blades hovering flight p 678 A87-43428 [AIAA PAPER 87-2008] p 696 A87-45349 Classification of the load-carrying capacity of runway surfaces by the ACN-PCN method. I Helicopter response to an airplanes's vortex wake Unsteady three-dimensional Navier-Stokes simulations p 678 A87.43430 of turbine rotor-stator interaction p 686 A87-46353 First approximation to landing field length of civil Rotor design for maneuver performance [AIAA PAPER 87-2058] p 636 A87-45386 transport aeroplanes (50 ft., 15.24 m screen) p 652 A87-43431 Application of a 3D inviscid rotational design procedure [ESDU-84040] p 688 N87-26056 The influence of the induced velocity distribution and for turbomachinery bladings p 638 A87-46204 the flapping-lagging coupling on the derivatives of the rotor Tip clearance flows. I . Experimental investigation of and the stability of the helicopter p 679 A87-43436 an isolated rotor. It - Study of various models and S Investigation of helicopter twin-rotor characteristics comparison with test results p 638 A87-46208 p 628 A87-43438 Aeroelastic control of stability and forced response of SAMPLING supersonic rotors by aerodynamic detuning Recent trends in rotary-wing aeroelasticity Portable fuel leak detector p 652 A87-43442 p 676 A87-46249 Study of the aerodynamics of high-speed propellers [AD-A180095] p 700 N87-25550 Helicopter individual-blade-control research at MIT [ONERA, TP NO. 1987-61] p 640 A87-46761 SATELLITE NAVIGATION SYSTEMS 1977-1965 p 679 A87-43446 Aerodynamic study of a helicopter rotor in hovering flight Geostaflonary satellite navigation systems Kinematic observers for active control of helicopter rotor - Theory vs. experiment p 641 A87-47014 p 648 A87-42786 vibration p 679 A87-43448 Performance and loads data from a hover test of a SCALE EFFECT Determination of the structural properties of helicopter 0.658-scale V-22 rotor and wing Effects of scale on supersonic combustor rotor blades by theoretical and experimental methods [NASA-TM-89419] p 642 N87-25296 performance p 653 A87-43450 Effect of signal jitter on the spectrum of rotor impulsive [AIAA PAPER 87-2164] p 672 A87-45444 Correlation of SA349/2 helicopter flight-test data with noise SCALE MODELS a comprehensive rotorcraft model p 653 A87-43456 [NASA-TM-100477] p 708 N87-25827 Validation of a method for air resonance testing of Experimental application of strain pattern analysis (SPA) Velocity measurements near the blade tip and in the helicopters at model scale using active control of Pylon - Wind tunnel and flight test results p 654 A87-43459 tip vortex core of a hovering model rotor dynamic characteristics p 683 A87-43462 Description of, and preliminary results from, a new p 645 N87-26030 Substantiation of the analytical prediction of ground and blade-vortex interaction test facility p 683 A87-43460 ROTOR BLADES air resonance stability of a bearingless rotor, using model Optimum design of a helicopter rotor blade A unique approach to aeroelastic testing of scaled scale tests p 654 A87-43463 rotors p 683 A87o43461 p 651 A87-43406 Scale model test results of a thrust reverser concept Helicopter rotor icing protection methods A prescribed radial distribution circulation of a hovering for advanced multi-functional exhaust systems p 654 A87-44256 rotor blade p 627 A87-43414 [AIAA PAPER 87-1833] p 667 A87-45235 Helicopter Rotor Icing Symposium, London, England, Investigation of blade-vortices in the rotor-downwash Jan. 14, 1986, Proceedings p 646 A87-44701 p 627 A87-43415 F-15 SMTD hot gas ingestion wind tunnel test results Where and when helicopter icing occurs Application of a 3D Euler code to transonic blade tip --- STOL and Maneuver Technology Demonstrator [AIAA PAPER 87-1922] p 669 A87-45301 p 702 A87-44702 flow p 628 A87-43419 Rotor icing experience at Westland and its application Determination of the structural properties of helicopter A model test vehicle for hypersonic aerospace systems to current and future helicopters p 646 A87-44703 rotor blades by theoretical and experimental methods development Development of the Chinook helicopter rotor blade p 653 A87-43450 [MBB-UR-875/86] p 658 N87-25314 de-icing system p 655 A87-44704 Experimental application of strain pattern analysis (SPA) SCANNING Rotor icing research at RAE Famborough - Wind tunnel and flight test results p 654 A87-43459 Scan stabilization and jitter control for an airborne p 646 A87-44706 Efficiency of the utilization of rotor blade shroud labyrinth telescope p 660 A87-42812 Icing clearances on civil helicopters - Unheated and seals in an axial-compressor stage with large radial SCATTERING heated blades p 646 A87-44707 clearances p 694 A87-43611 Development and application of unified algorithms for Application of a three-dimensional Euler code to A noninterference blade vibration measurement system problems in computational science p 705 N87-26006 transonic blade tip flow --- helicopter rotors for gas turbine engines SCHROEDINGER EQUATION [MBB-UD.482/86] p 642 N87-25299 [AIAA PAPER 87-1758] p 695 A87-45186 Computational chemistry p 706 N87-26023 Effect of planform taper on hover performance of an SCINTILLATION Expendable turbojet compressor design, test and advanced AH-64 model rotor development p 674 A87-46212 Airborne laser communications scintillation [NASA-TM-89145] p 643 N87-25304 Tomographic reconstruction of three-dimensional flow measurements p 649 A87-45722 Design for repairability of helicopter rotor blades SEAPLANES over airfoils [MBB-UD-49t/86] p 658 N87-25315 lAD-A179976] p 643 N87-25300 Design of CCV flight control system of STOL flying Optimization methods applied to the aerodynamic design boat p 680 A87-45097 ROTOR BLADES (TURBOMACHINERY) of helicopter rotor blades SEARCHING An improved assumed mode method for estimating the [NASA-TM-89155] p 660 N87-26042 Irish Dauphin helicopter S.A.R. system flight tests --- motion of a nonuniform rotor blade p 653 A87-43445 ROTATING SHAFTS Search and Rescue p 648 A87-43455 Complex modal balancing of flexible rotors including Stress analysis and optimisation of turbine rotor blade SECONDARY INJECTION residual bow shrouds p 699 A87-46250 Secondary stream and excitation effects on [AIAA PAPER 67-1840] p 695 A87-45241 Design applications for supercomputers two-dimensional nozzle plume characteristics ROTATING SPHERES p 706 N87-26010 [AIAA PAPER 87-2112] p 637 A87-45414 Natural convection flow of a radiating rarefied gas ROTOR BODY INTERACTIONS SELF ADAPTIVE CONTROL SYSTEMS between concentric rotating spheres Influence of vane/blade spacing and cold-gas injection Helicopter model in flight identification by a real time [AIAA PAPER 87-1523] p 693 A87-43046 on vane and blade heat-flux distributions for the Teledyne self adaptive digital process p 680 A87-43458 ROTOR AERODYNAMICS 702 HP turbine stage SELF OSCILLATION Prediction of blade airloads in hovering and forward flight [AIAA PAPER 87-1915] p 669 A87-45295 Numerical simulation and comparison with experiment using free wakes p 651 A87-43411 Gust response of helicopters p 682 N87-26049 for self-excited oscillations in a diffuser flow A unified approach for potential and viscous free-wake ROTOR SYSTEMS RESEARCH AIRCRAFT p 693 A87-43381 analysis of helicopter rotors p 627 A87-43412 RSRA/X-wing - A status report p 651 A87-43409 SEMISPAN MODELS The influence of winglets on rotor aerodynamics ROTORCRAFT AIRCRAFT Evaluation of installed performance of a p 628 A87-43422 Rotorcraft research - A national effort (The 1986 wing-tip-mounted pusher turboprop on a semiapan wing A comparison of the acoustic and aerodynamic Alexander Nikolsky Honorary Lectureship) [NASA-TP-2739] p 659 N87-26041 measurements of a model rotor tested in two anechoic SENSORS p 623 A87-44255 wind tunnels p 683 A87-43425 ROTORS A unique measurement technique to study Stability and control modelling --- helicopters in near laminar-separation bubble characteristics on an airfoil Full potential modeling of blade-vortex interactions hovering flight p 678 A87-43428 [AIAA PAPER 87-1271] p 631 A87-44921 p 627 A87-43417 Helicopter response to an airplanes's vortex wake SENSORY PERCEPTION Preliminary structural design of composite main rotor p 678 A87-43430 Motion software for a research flight simulator blades for minimum weight An advanced mathematical model for helicopter flight p 704 A87-44713 simulation using nonlinear unsteady aerodynamics [NASA-TP-2730] p 691 N87-25435 SEPARATED FLOW Wind tunnel evaluation of a truncated NACA 64-621 p 679 A87-43435 Advances in the computation of transonic separated Investigation of ground and air resonance using a airfoil for wind turbine applications flows over finite wings combination of multiblade coordinates and Floquet [NASA-CR-t808O3] p 703 N87-25621 [AIAA PAPER 87-1195] p 630 A87-44904 theory p 653 A87.43444 Velocity measurements near the blade tip and in the A unique measurement technique to study Description of, and preliminary results from, a new tip vortex core of a hovering model rotor laminar-separation bubble characteristics on an airfoil blade-vortex interaction test facility p 683 A87-43460 p 645 N87-26030 [AIAA PAPER 87-1271] p 631 A87-44921

A-23 SUBJECT INDEX SERVICE LIFE

Visualization of three-dimensional structures about a SIMULATION SQUEEZE FILMS pitching forward swept wing Study of helicopterroll control effectiveness criteria A study on the effect of non.dimensional system [AIAA PAPER 87-1322] p 631 A87-44929 [NASA-CR-177404] p 681 N87-25330 parameters on squeeze film damper performance using Study on the interference between the local separation A combined stochastic feedforward and feedback experimental data p 698 A87-46229 STABILIZERS (FLUID DYNAMICS) on a wing surface and outer flow-field control design methodology with application to autoland Fracture of an aircraft horizontal stabilizer p 634 A87-45094 design An improved approach for transonic flow [NASA-CR-4078] p 705 N87-25806 p 650 A87-42855 p 639 A87-46215 SKIN (STRUCTURAL MEMBER) On the nonlinear aerodynamic and stability Unsteady viscous-inviscid interaction method and Fatigue life analysis of fuel tank skins under combined characteristics of a generic chine-forebedy slender-wing computation of buffeting over airfoils loads p 650 A87-42856 fighter configuration [ONERA, TP NO, 1987-58] p 640 A87-46759 Adhesives in aerospace p 689 A87-44743 [NASA-TM-89447] p 643 N87-25305 Laminar separation bubble characteristics on an airfoil Aircraft skin that bruises p 691 A87-46874 Automated systems for the manufacture of Airbus at low Reynolds numbers p 641 A87-46778 SLENDER BODIES vertical stabilizers Experimental studies on the dynamic development and Subsonic wind-tunnel measurements of a slender [MBS-UT-17-86] p 705 N87-25786 control of unsteady separated flows p 642 N87-25297 wing-body configuration employing a vortex flap STANDARDIZATION Viscid/inviscid separated flows [NASA-TM-89101] p 642 N87-25295 Standardization and logistic support cost effectiveness [AD-At79858] p 699 N87-25536 SLENDER WINGS of advanced avionics systems p 661 A87-43468 STANDARDS SERVICE LIFE Entrainment effect of a leading-edge vortex New standards established for realism in visual Application of engine component life methodology to p 641 A87-46777 life assessment p 698 A87-46230 On the nonlinear aerodynamic and stability simulation --- for commercial aircraft flight p 686 A87-46438 The AVSCOM flight safety part program characteristics of a generic chine-forebody slender-wing STANDING WAVES p 647 A87-46724 fighter configuration SHEAR LAYERS [NASA-TM-89447] p 643 N87-25305 Morphology of a standing oblique detonation wave --- Aero-optical analysis of compressible flow over an open SMOG for hypersonic airbreathing propulsion cavity Large-scale distribution of peroxyacetylnitrate results [AIAA PAPER 87-1785] p 695 A87-45201 [AIAA PAPER 87-1399] p 632 A87-44943 from the STRATOZ III flights p 702 A87-46481 STANTON NUMBER A simple model for finite chemical kinetics analysis of SMOKE Influence of vane/blade spacing and cold-gas injection supersonic turbulent shear layer combustion Fire, smoke, toxicity --- in airline operations on vane and blade heat-flux distributions for the Teledyne [AIAA PAPER 87-1879] p 696 A87-45273 p 646 A87-44748 702 HP turbine stage A method for the calculation of the interaction of a SOFTWARE TOOLS [AIAA PAPER 87-1915] p 669 A87-45295 turbulent boundary layer with a shock wave Motion software for a research flight simulator STATIC LOADS p 639 A87-46238 p 704 A87-44713 Calculation of the reliability of aircraff-engine parts under SHOCK TUNNELS XMAN - A tool for automated jet engine diagnostics repeated static loading p 664 A87-43616 Hydrogen scramjet with sidewall injection - Shock tunnel [AIAA PAPER 87-1931] p 696 A87-45309 A miniature remote deadweight calibrator simulations p 674 A87-46217 SOLID PROPELLANT COMBUSTION p 694 A87-45104 STATIC TESTS Pressure scaling effects in a scramjet combustion Application of low-Reynolds-number K-epsilon model to chamber p 676 A87-46258 solid fuel turbulent boundary layer combustion Aerodynamic study of a helicopter rotor in hovering flight SHOCK WAVE INTERACTION [AIAA PAPER 87-1778] p 690 A87-45198 - Theon/vs. experiment p 641 A87-47014 STATISTICAL ANALYSIS Flow phenomena in transonic turbine cascades detailed Diagnostics in supersonic combustion experimental and numerical investigation [AIAA PAPER 87-1787] p 690 A87-45202 Helicopter activities in Germany p 623 A87-43401 p 639 A87-46223 SOLID STATE DEVICES STATISTICAL DISTRIBUTIONS Statistical distribution of extreme atmospheric A method for the calculation of the interaction of a Optically interfaced sensor system for aerospace turbulences turbulent boundary layer with a shock wave applications p 694 A87-45107 p 639 A87-46238 SOUND GENERATORS [ONERA, TP NO. 1987-56] p 702 A87-46757 STATOR BLADES SHOCK WAVE PROPAGATION An analysis of in-fin tail rotor noise Calculation of the boundary layer at the inlet section p 652 A87-43427 An analysis of in-fin tail rotor noise of a compressor cascade p 629 A87-43608 SOUND PROPAGATION p 652 A87-43427 SHOCK WAVES An analysis of in-fin tail rotor noise Rotor wake segment influence on stator-sorface Aerodynamic characteristics of wave riders p 652 A87-43427 boundary layer development in an axial-flow compressor p 637 A87.46094 SPACE COMMUNICATION stage SHORT TAKEOFF AIRCRAFT Airborne laser communications scintillation [AIAA PAPER 87-1741] p 695 A87-45178 Design of CCV flight control system of STOL flying measurements p 649 A87-45722 Application of a 30 inviscid rotational design procedure boat p 680 A87.45097 SPACE SURVEILLANCE (SPACEBORNE) for turbomachinery bladings p 638 A87-46204 STATORS Advantages of thrust vectoring for STOVL Sparing to optimize naval airship availability [AIAA PAPER 87-1708] p 665 A87-45156 p 625 A87-46716 Unsteady three-dimensional Navier-Stokes simulations Impact of engine technology on supersonic STOVL SPACECRAFT COMMUNICATION of turbine retor-stator interaction [AIAA PAPER 87-1709] p 665 A87-45157 A conformal aircraft phased array antenna for [AIAA PAPER 87-2058] p 636 A87-45386 STOVL engine/airframe integration airplane-satellite communication in the L band STEADY FLOW [AIAA PAPER 87-1711 ] p 655 A87-45158 [DFVLR-FB-86-47] p 701 N87-26259 A panel method for prediciting the dynamic stability STOL characteristics of a tactical aircraft with thrust SPACECRAFT COMPONENTS derivatives ol an oscillating wing in high subsonic flow p 641 A87-46951 vectoring nozzles A high temperature fatigue and structures testing STEEL STRUCTURES [AIAA PAPER 87-1835] p 655 A87-45237 facility F-15 SMTD hot gas ingestion wind tunnel test results [NASA-TM-100151] p 701 N87-26399 Fatigue-life monitoring of the 5 metre wind tunnel --- STOL and Maneuver Technology Demonstrator SPACECRAFT CONFIGURATIONS [RAE-TM-AERO-2084] p 688 N87-26055 [AIAA PAPER 87-1922] p 669 A87-45301 An interactive approach to surface-fitting complex STIFFENING Integrally-stiffened crash energy-absorbing subfloor Flying the CF-18 Hornet p 656 A87-46313 geometries for flowfield applications SHROUDED TURBINES [AIAA PAPER 87-1476] p 625 A87-43009 beam structure [NASA*CASE-LAR-13697-1] p 659 N87-25321 Efficiency of the utilization of rotor blade shroud labyrinth SPACECRAFT DESIGN STRAIN ENERGY METHODS seals in an axial-compressor stage with large radial Interdisciplinary optimum design --- of aerospace clearances p 694 A87-43611 structures p 657 A87.47009 Research on the stress analysis method of rubber SPACECRAFT RELIABILITY structure - Calculation of the frequency adapter stresses An experimental investigation of turbine case p 693 A87.43453 treatments Reliability, 'better than the best' p 699 A87-46728 STRAKES SPARE PARTS [AIAA PAPER 87-1919] p 669 A87-45299 Numerical simulation of vortical flows over a strake-delta The design of low-stress/high performance centrifugal Sparing to optimize naval airship availability wing impellers p 625 A87-46716 SPECTRAL METHODS [AIAA PAPER 87-1229] p 630 A87-44913 [AIAA PAPER 87-2099] p 697 A87-45405 STRAPDOWN INERTIAL GUIDANCE Effect of signal jitter on the spectrum of rotor impulsive SHROUDS noise Autonomous navigation system for the new generation Stress analysis and optimisation of turbine rotor blade of military helicopters and associated flight tests [NASA-TM-100477] p 708 N87-25827 shrouds p 699 A87-46250 SPEECH RECOGNITION p 648 A87°43469 SIDESLIP STRATEGY DVI in the military cockpit - A third hand for the combat On the nonlinear aerodynamic and stability Research and development. Technical-scientific pilot --- Direct Voice Input p 681 A87-46315 characteristics of a generic chine-forebody slender-wing SPILLING publications 1986 fighter configuration Estimation of spillage drag for a wide range of [ETN-87-99713] p 710 N87-26826 [NASA-TM-89447] p 643 N87-25305 STREAM FUNCTIONS (FLUIDS) axisymmetric intakes at M 1 Vortex breakdown simulation SIGNAL ANALYSIS [ESDU-84004] p 701 N87-26301 Effect of signal jitter on the spectrum of rotor impulsive SPOILERS [AIAA PAPER 87-1343] p 632 A87-44934 Transonic stream function solution on S(2) noise Flow-field measurements of an airfoil with a deflected [NASA-TM-100477] p 708 N87-25827 streamsurface for a high pressure ratio centrifugal spoiler using an LDV system SIGNAL FADING [AIAA PAPER 87-1438] p 634 A87-44955 compressor p 638 A87-46195 Improvement of aerodynamic calculation on S(2)m Application of wedge diffraction theory to estimating SPRAY CHARACTERISTICS stream surface of axial compressor by using of annulus power density at airport humped runways Influence of fuel temperature on atomization wall boundary layer calculation p 639 A87-46216 p 650 A87-46861 performance of pressure-swirl atomizers SIGNAL PROCESSING p 698 A87.46198 Underexpanded jet-free stream interactions on an Time modulation. II - Scheme codes avoidance Diagnostic methods for air-breathing engines axisymmetric afterbody configuration maneuvers for aircraft p 649 A87-44845 p 686 A87-46243 p 639 A87-46232

A-24 SUBJECT INDEX SWEPT WINGS

STRESS ANALYSIS The vertical test section (VMK) of DFVLR in SUPERSONIC FLIGHT Fatigue and fracture mechanics analysis of compression Cologne-Porz, West Germany --- wind tunnel Aerothermodynamic computations for loaded aircraft structure p 692 A87-42854 [DFVLR-MITF-86-22] p 688 N87-26054 super-/hypersonic flight p 640 A87-46328 FEL - A new main rotor system p 651 A87-43402 SULFUR COMPOUNDS SUPERSONIC FLOW Degradation mechanisms of sulfur and nitrogen Research on the stress analysis method of rubber A computational method for determining tlowtield containing compounds during thermal stability testing of structure - Calculation of the frequency adapter stresses properties when the pilot pressure is the only measured model fuels p 693 A87-43453 instream property p 637 A87-46184 [AIAA PAPER 87-2039] p 690 A87-45372 Mechanical evaluation of the aeroelastic behaviour of Selection of admissible contact stresses for toothed SUPERCOMPUTERS a fan blade p 675 A87-46248 gears of aircraft engines p 663 A87-43605 CFD applications: The Lockheed perspective Aeroelastic control of stability and forced response of Finite element analysis and redesign of jet engine starter p 644 N87-26005 supersonic rotors by aerodynamic detuning breech chamber Design applications for supercomputers p 676 A87-46249 [ASME PAPER 86-WA/DE-20] p 664 A87-43702 p 706 N87-26010 Wind tunnel experimental study of optical beam Designing for fretting fatigue free joints in turboprop Computational fluid dynamics research at the United degradation through heterogeneous aerodynamic flows engine gearboxes Technologies Research Center requiring [ONERA, TP NO. 1987-50] p 707 A87-46753 [AIAA PAPER 87-2046] p 671 A87-45378 supercomputers p 701 N87-26011 Numerical simulation of flows in axial and radial Stress analysis and optimisation of turbine rotor blade Computational chemistry p 706 N87-26023 shrouds p 699 A87-46250 SUPERCRITICAL AIRFOILS turbomachines using Euler solvers [ONERA, TP NO. t987-87] p 641 A87-46776 STRUCTURAL ANALYSIS Computation of unsteady transonic aerodynamics with Study of lee-side flows over conically cambered Delta Correlation of SA349/2 helicopter flight-test data with truncation error injection p 627 A87-43392 wings at supersonic speeds, part 2 a comprehensive rotorcraft model p 653 A87-43456 An experimental investigation of a supercriticai airfoil [NASA-TP-2660-PT-2] p 643 N87-25301 The design of low-stress/high performance centrifugal at transonic speeds A multi-body aircraft with an all-movable center fuselage impellers [AIAA PAPER 87-1241] p 630 A87-44914 SUPERCRITICAL FLOW actively controlling fuselage pressure drag ]AIAA PAPER 87-2099] p 697 A87-45405 [ NASA-CASE-LAR-13511-1 ] p 658 N87-25320 Trends in the aareelastic analysis of combat aircraft Fast methods applied to the calculation of transonic SUPERSONIC INLETS p 657 A87-46362 airfoils p 641 A87-46962 SUPERPLASTICITY Navior.Stokes simulations of supersonic fighter intake A high temperature fatigue and structures testing Superplastic forming/diffusion bonding of titanium flowfields facility p 689 A87-44747 [AIAA PAPER 87-1752] p 634 A87-45185 [NASA-TM-100151] p70t N87-26399 SUPERSONIC AIRCRAFT SUPERSONIC SPEED STRUCTURAL DESIGN Impact of engine technology on supersonic STOVL Euler solution for a complete fighter aircraft at sub- and Calculated performance, stability, and maneuverability [AIAA PAPER 87-1709] p 665 A87-45157 supersonic speed of high-speed tilting-prop-retor aircraft STOVL engine/airframe integration [MBB-LKE-122-SIPUB/234] p 660 N87-26833 p 651 A87-43408 [AIAA PAPER 87-1711] p 655 A87-45158 SUPERSONIC TRANSPORTS Interdisciplinary optimum design --- of aerospace Use of RPM trim to automate the supersonic eogine/inlet Engine variable geometry effects on commercial structures p 657 A87-47009 match in the SR-71A supersonic transport development Industrial application of computer aided structural [AIAA PAPER 87-1848] p 667 A87-45248 [AIAA PAPER 87-2101] p672 A87-45406 optimization in aircraft construction Variable cycle concepts tor high Mach applications U.S. aeronautical R&D goals - SST: bridge to the next [MBB-UT-273/86] p 706 N87-26523 [AIAA PAPER 87-2103] p 672 A87-45408 century p 624 A87-46182 STRUCTURAL DESIGN CRITERIA Flying the CF-18 Hornet p 656 A87-46313 Aerothermodynamic computations for Honeycomb structures: Parameter selection and design SUPERSONIC AIRFOILS super-/hypersonic flight p 640 A87-46328 --- Russian book p 693 A87.42914 Fast methods applied to the calculation of transonic SUPERSONIC TURBINES STRUCTURAL RELIABILITY airfoils p 641 A87-46962 Flow phenomena in transonic turbine cascades detailed A310-300 CFRP fin damage tolerance demonstration SUPERSONIC BOUNDARY LAYERS experimental and numerical investigation [MBB-UT.015/86] p 658 N87-25317 Stability and transition in supersonic boundary layers p 639 A87-46223 STRUCTURAL STABILITY [AIAA PAPER 87-1416] p 632 A87-44947 SUPERSONIC WIND TUNNELS Honeycomb structures: Parameter selection and design Linear instability waves in supersonic turbulent mixing The pitching damping derivatives measured by --- Russian book p 693 A87.42914 layers force-oscillation method at transonic and supersonic wind Substantiation of the analytical prediction of ground and [AIAA PAPER 87-1418] p 633 A87-44948 tunnel p 686 A87-46958 SUPERSONIC COMBUSTION air resonance stability of a bearingless rotor, using model The 0.6 m x 0.6 m trisonic section (TMK) of DFVLR in scale tests p 654 A87-43463 Diagnostics in supersonic combustion CoIogne-Porz, West Germany STRUCTURAL VIBRATION [AIAA PAPER 87-1787] p 690 A87-45202 [DFVLR-MITT-86-21 ] p 687 N87-26053 The vertical test section (VMK) of DFVLR in Fatigue life analysis of fuel tank skins under combined A simple model for finite chemical kinetics analysis of loads p 650 A87-42856 supersonic turbulent shear layer combustion CoIogne-Porz, West Germany --- wind tunnel Component mode iteration for frequency calculations [AIAA PAPER 87-1879] p 696 A87-45273 [DFVLR-MITT.86-22] p 688 N87-26054 SUPPORTS --- in analysis of structural vibration Progress toward shock enhancement of supersonic [AIAA PAPER 86-1023] p 704 A87-43388 combustion processes Airfoil flutter model suspension system Development of an experimental system for active [AIAA PAPER 87-1880] p 690 A87-45274 [NASA-CASE-LAR-13522-1-SB] p 687 N87-25334 control of vibrations on helicopters p 679 A87-43447 Design and evaluation of a new injector configuration SURFACE FINISHING Influence of third-degree geometric nonlinearities on the for supersonic combustion p 674 A87-46218 Optimization of the duration of ultrasonically activated vibration and stability of pretwisted, preconed, rotating SUPERSONIC COMBUSTION RAMJET ENGINES impact surface treatment of gas-turbine-engine blades blades p 674 A87-46228 A mixing augmentation technique for hypervelocity p 663 A87-43609 Correlation of B-1 flight test subjective assessments and scram jets SURFACE PROPERTIES some ride quality/vibration exposure cdteria [AIAA PAPER 87-1882] p 668 A87-45275 Classification of the load-carrying capacity of runway [AD-A179844] p 658 N87-25318 Three-dimensional numerical predictions of the flow surfaces by the ACN-PCN method. II Helicopter vibration control: Recent advances behind a rearward-tacing-step in a supersonic combustor p 686 A87-46354 SURFACE ROUGHNESS EFFECTS p 660 N87-26247 [AIAA PAPER 87-1962] p 636 A87-45332 A comparison of the struotureborne and airborne paths Standing oblique detonation wave engine performance The effect of trip wire roughness on the performance for propfan interior noise [AIAA PAPER 87-2002] p 670 A87-45347 of the Wortmann FX 63-137 airfoil at low Reynolds [NASA-CR-180289] p 708 N87-26612 A subsonic to Mach 5.5 subscale engine test facility numbers p 629 A87-44019 SUBSONIC FLOW [AIAA PAPER 87-2052] p 685 A87-45381 SURFACE TEMPERATURE Time-consistent pressure relaxation procedure for An outlook on hypersonic flight Influence of a heated leading edge on boundary layer compressible reduced Navier-Stokes equations [AIAA PAPER 87-2074] p 671 A87-45392 growth, stability and transition p 626 A87-43377 An improved computational model for a scramjet [DE87-008516] p 700 N87-25538 SURGES Highly compact inlet diffuser technology propulsion system [AIAA PAPER 87-1747] p 666 A87-45180 [AIAA PAPER 87-2078] p 671 A87-45393 J85 surge transient simulation p 675 A87-46240 Parametric study ol single expansion ramp nozzles at The influence of flow non-uniformities in air-breathing Microprocessor based surge monitoring system p 686 A87-46241 subsonic/transonic speeds hypersonic propulsion systems SURVEILLANCE [AIAA PAPER 87o1836] p 635 A87-45238 [AIAA PAPER 87°2079] p 636 A87-45394 A panel method for prediciting the dynamic stability Cycle selection considerations for high Mach Integrated navigation, communication and surveillance derivatives of an oscillating wing in high subsonic flow applications systems based on standard distance measuring p 641 A87-46951 [AIAA PAPER 87-2105] p 672 A87-45410 equipment p 649 A87-44039 SURVEYS Development of a geometry handling program for the Studies of scramjet tlowfields FFA subsonic higher order panel method [AIAA PAPER 87-2161] p 688 A87-45443 Survey of currently available high-resolution raster [FFA-TN-1985-48] p 699 N87-25534 Effects of scale on supersonic combustor graphics systems SUBSONIC FLUTTER performance [NASA-TM-89139] p 705 N87-25771 The numerical simulation of subsonic flutter [AIAA PAPER 87-2164] p 672 A87-45444 SUSPENDING (HANGING) [AIAA PAPER 87-1428] p 633 A87-44952 Test flow calibration study of the Langley Arc-Heated Airfoil flutter model suspension system SUBSONIC SPEED Scramjet Test Facility [NASA-CASE-LAR-t3522-1-SB] p 687 N87-25334 Euler solution for a complete fighter aircraft at sub- and [AIAA PAPER 87-2165] p 685 A87-45445 SWEPT FORWARD WINGS Visualization of three-dimensional structures about a supersonic speed Scramjet testing in impulse facilities [MBB-LKE-122-S/PUB/234] p 660 N87-26833 p 665 A87-46183 pitching forward swept wing SUBSONIC WIND TUNNELS Hydrogen scram jet with sidewall injection - Shock tunnel [AIAA PAPER 87-1322] p 631 A87-44929 Two-dimensional subsonic and transonic wind tunnel simulations p 674 A87-46217 SWEPT WINGS wall interference corrections for varied walls Pressure scaling effects in a scramjet combustion Measurements of the performance of a helicopter swept p 686 A87-46955 chamber p 676 A87-46258 tip rotor in flight p 652 A87-43423 A-25 SWIRLING SUBJECT INDEX

Comparisons of unsteady flow fields about straight and TAKEOFF TEST STANDS swept wings using flow visualization and hotwire Maximum survival capability of an aircraft in a severe An experimental investigation of turbine case anemometry windshear p 680 A87-44254 treatments [AIAA PAPER 87-1334] p 631 A87-44932 Onboard instrumentation for flight test takeoff [AIAA PAPER 87-1919] p 669 A87-45299 SWIRLING performance p 662 A87-45126 TESTING TIME Effect of swirl on the performance of a radial vaneless Control of aircraft under severe wind shear conditions The role of short duration facilities in gas turbine diffuser with compressible flow at Mach numbers of 0.7 p 682 N87-26050 research p 685 A87-46222 and 0.8 TAKEOFF RUNS THERMAL ANALYSIS [ASME PAPER 96-WA/FE-EJ p 629 A87-43704 Changes in the free flow in the intake of a turbojet engine HALE thermat balance --- High Altitude Long Endurance Influence of fuel temperature on atomization during the aircraft takeoff run p 640 A87-46351 remotely piloted vehicles performance of pressure-swirl atomizers TECHNOLOGICAL FORECASTING [AIAA PAPER 87-2172] p 656 A87-45452 p 698 A87.46198 Expanding tilt rotor capabilities p 651 A87-43407 THERMAL CONTROL COATINGS A study of some factors affecting the performance of Materials for structures of the future A study of the thermal-stress state of gas turbine engine a contra-rotating axial compressor stage p 689 A87-44745 blades with protective coatings p 664 A87-43640 p 639 A87-46211 Propfan propulsion systems for the 1990's THERMAL CYCLING TESTS SYMMETRICAL BODIES [AIAA PAPER 87-1729] p 665 A87-45168 Durability characterization of ceramic materials for gas Low-speed wind-tunnel results for symmetrical NASA Civil propulsion technology for the next twenty.five turbines p 690 A87-45898 LS(t)-0013 airfoil years p 624 A87-46177 THERMAL DEGRADATION {NASA-TM-4003] p 645 N87-26033 The origins and future possibilities of air breathing jet Degradation mechanisms of sulfur and nitrogen SYNCHRONOUS SATELLITES propulsion systems p 709 A87-46178 containing compounds during thermal stability testing of Geostationary satellite navigation systems Future trends - A European view --- of air breathing model fuels p 648 A87-42786 engines p 673 A87-46179 [AIAA PAPER 87-2039] p 690 A87-45372 SYSTEM FAILURES TECHNOLOGY ASSESSMENT THERMAL STABILITY EMI-fault prevention and self recovery of digital flight Helicopter activities in Germany p 623 A87-43401 Degradation mechanisms of sulfur and nitrogen control systems p 661 A87-43470 RSRA/X-wing - A status report p 651 A87-43409 containing compounds during thermal stability testing of Analysis of typical fault-tolerant architectures using Technological change and skill requirements - A case model fuels HARP p 704 A87-45771 study of numerically controlled riveting in commercial [AIAA PAPER 87-2039] p 690 A87-45372 SYSTEM IDENTIFICATION aircraft manufacture THERMAL STRESSES Experience with frequency-domain methods in [ASME PAPER 86-WA/TS-2] p 623 A87.43723 A study of the thermal-stress state of gas turbine engine helicopter system identilication p 680 A87-43457 Countdown to the propfan p 664 A87.44272 blades with protective coatings p 664 A87-43640 SYSTEMS ENGINEERING Radar Technology 1986; Symposium, 6th, Bremen, West Finite element analysis and redesign of jet engine starter The AVSCOM flight safety part program Germany, Nov. 4-6, 1986, Reports p 697 A87-45876 breech chamber p 647 A87-46724 U.S. aeronautical R&D goals - SST: bridge to the next [ASME PAPER 86-WA/DE-20] p 664 A87-43702 SYSTEMS INTEGRATION century p 624 A87-46182 THERMODYNAMIC CYCLES EH101 cockpit design p 661 A87-43404 Aircraft technologies of the nineties in MBB passenger Cycle selection considerations for high Mach Irish Dauphin helicopter S.A.R. system flight tests --- aircraft projects applications Search and Rescue p 648 A87-43455 [ MBB-UT-21/86] p625 N87-25291 [AIAA PAPER 87-2105] p 672 A87-45410 Engine design and systems integration for propfan and CFD applications: The Lockheed perspective Compound cycle engine for helicopter application high bypass turbofan engines p 644 N87-26005 [NASA-CR-175110] p677 N87-25323 THERMOPHYSICAL PROPERTIES [AIAA PAPER 87-1730] p 665 A87-45169 Aircraft technology of the nineties in MBB passenger Advanced fighter thrust reverser integration for minimum aircraft projects Thermal and flammability characterization of graphite landing distance [MBS-UT-0021/86] p 660 N67-26834 composites p 688 A87-43398 [AIAA PAPER 87-1923] p 655 A87-45302 TECHNOLOGY UTILIZATION THIN AIRFOILS Integration of propulsion/integration test results through Future advanced control technology study (FACTS) - The effect of pitch rate on the dynamic stall or a modified the use of reference plane transfers A look at emerging technologies --- for turbine engines NACA 23012 aerofoil and comparison with the unmodified [AIAA PAPER 87-1964] p 670 A87-45333 [AIAA PAPER 87-1930] p 670 A87-45308 case p 628 A87-43420 Integration of engine/aircraft control - 'How far is it TEMPERATURE CONTROL Transonic wall interference assessment and corrections sensible to go' p 674 A87-46226 Digital control development for the T56.A-427 for airfoil data from the 0.3-meter TCT adaptive wall test Simulator systems integration p 687 N87-25283 [AIAA PAPER 87-2013] p 670 A87-45353 section SYSTEMS SIMULATION TEMPERATURE DISTRIBUTION [AIAA PAPER 87-1431] p 633 A87-44953 The role of simulation in helicopter development The influence of dilution hole aerodynamics on the THREE DIMENSIONAL BODIES [MBBoUD-435/86] p 687 N87-25333 temperature distribution in a combustor dilution zone Crack growth prediction in 3D structures under Optimal cooperative control synthesis of active [AIAA PAPER 87-1827] p 666 A87-45232 aeronautical-type spectrum Ioadings displays TEMPERATURE MEASUREMENT [ONERA, TP NO, 1987-79] p 691 A87-46772 [NASA-CR-4058] p 705 N87-25807 Diagnostics in supersonic combustion THREE DIMENSIONAL BOUNDARY LAYER An investigation of helicopter higher harmonic control (AIAA PAPER 87.1787] p 690 A87-45202 Stationary disturbances in three-dimensional boundary using a dynamic system coupler simulation The treatment of calibrations of total air temperature layers over concave surfaces p 682 N87-26051 probes for use in flight-test analysis work [AIA.A PAPER 87.1412] p 632 A87-44945 [ESDU-84007] p 701 N87-28324 Linear stability analysis of three-dimensional T TERRAIN ANALYSIS compressible boundary layers p 640 A87-46504 Terrain modelling of glideslope for instrument landing THREE DIMENSIONAL FLOW system p 650 A87-46415 Three-dimensional problems in computational fluid T-,56 ENGINE TEST EQUIPMENT dynamics --- Russian book p 693 A87-42916 A derivative engine based on new technology - Low Transient test system design for the T800-APW-800 A computational study of the flowfield surrounding the risk; cost effective turboshaft engine Aeroassist Flight Experiment vehicle [AIAA PAPER 87-1910] p 669 A87-45292 [AIAA PAPER 87-1791] p 666 A87-45205 [AIAA PAPER 87-1575] p 626 A87-43084 Digital control development for the T56-A-427 TEST FACILITIES Application of a 3D Euler code to transonic blade tip [AIAA PAPER 87-2013] p 670 A87-45353 Description of, and preliminary results from, a new flow p 628 A87-43419 TACAN blade-vortex interaction test facility p 683 A87-43460 Visualization of three-dimensional structures about a TACAN/INS Performance Evaluation (TIPE) flight test A unique approach to aeroelastic testing of scaled pitching forward swept wing report rotors p 683 A87-43461 [AIAA PAPER 87-1322] p 631 A87-44929 [AD-A180138] p 650 N87-25313 The Air Force Flight Test Center - Now and the future An LDA investigation of three-dimensional normal TAIL ASSEMBLIES p 684 A67-45125 shock.boundary layer interactions in a corner New aerodynamic design of the fenestron for improved Full-scale thrust reverser testing in an altitude facility [AIAA PAPER 87.1369] p632 A87-44938 performance p 651 A87-43403 [AIAA PAPER 87-1788] p 684 A87-45203 Stability and transition in supersonic boundary layers The Airbus rudder - An example of new fabrication Ground testing facilities requirements for hypersonic [AIAA PAPER 87-1416] p 632 A87-44947 technologies p 623 A87-44228 propulsion development Three-dimensional numerical predictions o1 the flow On the nonlinear aerodynamic and stability [AIAA PAPER 87-1884] p 684 A87.45276 behind a rea_vard-facing-step in a supersonic combustor characteristics of a generic chine-forebody slender-wing Exploratory evaluation of a moving-model technique for [AIAA PAPER 87-1962] p 636 A87-45332 fighter configuration measurement of dynamic ground effects Unsteady three-dimensional Navier-Stokes simulations [NASA-TM-89447] p 643 N87-25305 [AtAA PAPER 87-1924] p 685 A87-45303 of turbine rotor-stator interaction Design of a composite tail for the Airbus A-320 A subsonic to Mach 5.5 subscale engine test facility [AIAA PAPER 87-2058] p 636 A87-45386 [MBB-UT-12-86] p 658 N87-25316 [AIAA PAPER 87-2052] p 685 A87-45381 3-O viscous flow calculations at design and off-design TAIL ROTORS Scramjet testing in impulse facilities conditions for the NACA 48-inch radial-inlet centrifugal p 685 A87-46163 An analysis of in-fin tail rotor noise impeller p 638 A87-46191 The role of short duration facilities in gas turbine p 652 A87-43427 Investigation of the three dimensional flow near the exit research p 685 A87-46222 Damage tolerance concepts for modern helicopters of two backswept transonic centrifugal impellers A high temperature fatigue and structures testing p 638 A87-46192 p 663 A87-43449 facility TAILLESS AIRCRAFT Application of a 3D inviscid rotational design procedure [NASA-TM-100151] p 701 N87-26399 Flying wing could stealthily reappear TEST FIRING for turbomachinery bladings p 638 A87-46204 Numerical simulation of transonic three-dimensional p 657 A87-46870 Application of ceramics to ramjet engine nozzles On the nonlinear aerodynamic and stability p 890 A87-46221 flows in turbine blade passages p 638 A87-46206 characteristics of a generic chine-forebody slender-wing TEST RANGES Application of a three-dimensional Euler code to fighter configuration The Air Force Flight Test Center - Now and the future transonic blade tip flow --- helicopter rotors [NASA-TM-89447] p 643 N87-25305 p 684 A87-45125 [MBB-UD-482/86] p 642 N87-25299

A-26 TRANSPORT AIRCRAFT SUBJECT INDEX

TRANSONIC FLOW Tomographic reconstruction of three-dimensional flow TOMOGRAPHY Computation of unsteady transonic aerodynamics with over airfoils Tomographic reconstruction of three-dimensional flow truncation error injection p 627 A87-43392 lAD-A179976] p 643 N87-25300 over airfoils Application of a 3D Euler code to transonic blade tip Viscid/inviscid separated flows [AD-A179976] p 643 N87-25300 TORQUE flow p 628 A87-43419 [AD-A179858] p 699 N87-25536 Measurement of side forces of a H-force rotor Advances in the computation of transonic separated Design applications for supercomputers p 651 A87-43410 p 706 N87-26010 flows over finite wings TORSION [AIAA PAPER 87-1195] p 630 A87-44904 Experience with 3-D composite grids Determination of the structural properties of helicopter p 706 N87-26021 Transonic analysis of the F-16A with under-wing fuel rotor blades by theoretical and experimental methods tanks - An application of the TranAir full-potential code Numerical solution of the Navier-Stokes equations about p 653 A87-43450 [AIAA PAPER 87-1198] p 630 A87-44905 three-dimensional configurations: A survey Influence of third-degree geometric nonlinearities on the Simulation of transonic viscous flow over a fighter-like p 701 N87-26022 vibration and stability of pretwisted, preconed, rotating configuration including inlet THROTTLING blades p 674 A87-46228 [AIAA PAPER 87-1199] p 630 A87-44906 Design of CCV flight control system of STOL flying TORSIONAL STRESS boat p 680 A87-45097 Mechanical evaluation of the aeroelastic behaviour of An experimental investigation of a supercritical airfoil at transonic speeds THRUST AUGMENTATION a fan blade p 675 A87-46248 [AIAA PAPER 87-1241] p 630 A87-44914 Progress toward shock enhancement of supersonic Aeroelastic control of stability and forced response of Transonic wall interference assessment and corrections combustion processes supersonic rotors by aerodynamic detuning for airfoil data from the 0.3-meter TCT adaptive wall test AIAA PAPER 87-1880] p 690 A87.45274 p 676 A87-46249 section United Airlines wind shear incident of May 31, 1984 TORSIONAL VIBRATION [AIAA PAPER 87-1431] p 633 A87-44953 p 647 N87-25287 An improved assumed mode method for estimating the motion of a nonuniform rotor blade p 653 A87-43445 Static investigation of pest-exit vanes for multiaxis thrust THRUST BEARINGS TOXICITY vectoring A bidirectional tapered roller thrust bearing for gas Fire, smoke, toxicity --- in airline operations [AIAA PAPER 87.1834] p 667 A87-45236 turbine engines p 646 A87-44748 Parametric study of single expansion ramp nozzles at [AIAA PAPER 87-1842] p 695 A87-45243 TRAILING EDGE FLAPS subsonic/transonic speeds THRUST DISTRIBUTION Flow over a trailing flap and its asymmetric wake [AIAA PAPER 87-1836] p 635 A87-45238 Measurement of side forces of a H-force rotor p 626 A87-43376 Transonic stream function solution on S(2) p 651 A87-43410 Helicopter response to an airplanes's vortex wake streamsurface for a high pressure ratio centrifugal THRUST REVERSAL p 678 A87-43430 compressor p 638 A87-46195 Full-scale thrust reverser testing in an altitude facility Validation of aerodynamic measurement techniques and Numerical simulation of transonic three-dimensional [AIAA PAPER 87-1788] p 684 A87-45203 calculation methods for high-lift systems flows in turbine blade passages p 638 A87-46206 Scale model test results of a thrust reverser concept p 640 A87-46363 An improved approach for transonic flow for advanced multi-functional exhaust systems TRAILING EDGES p 639 A87-46215 [AIAA PAPER 87-1833] p 667 A87-45235 The use of discrete vortices to predict lift of a circulation Flow phenomena in transonic turbine cascades detailed Advanced fighter thrust reverser integration for minimum control rotor section with a trailing edge blowing slot experimental and numerical investigation landing distance p 627 A87.43416 p 639 A87-46223 [AIAA PAPER 87-1923] p 655 A87-45302 Flow-field measurements of an airfoil with a deflected Development of a laser interferometric system for Navier-Stokes analysis of a very-high-bypass-ratio spoiler using an LDV system velocity measurements inside a transonic axial flow turbofan engine in reverse thrust [AIAA PAPER 87.1438] p 634 A87-44955 compressor stage p 698 A87-46244 [AIAA PAPER 87-2170] p 697 A87-45450 TRAJECTORIES Fast methods applied to the calculation of transonic THRUST VECTOR CONTROL Optimal flight trajectories in the presence of windshear, airfoils p 641 A87-46962 Advantages of thrust vectoring for STOVL 1984-86 Application of a three-dimensional Euler code to [AIAA PAPER 87-1708] p 665 A87-45156 [NASA.CR-180316] p 682 N87-26047 transonic blade tip flow --- helicopter rotors TRAJECTORY CONTROL [MBB-UD-482/86] p 642 N87-25299 Static investigation of post-exit vanes for multiaxis thrust Optimal cooperative control synthesis of active TRANSONIC SPEED vectoring Investigation _f a delta-wing fighter model flow field at [AIAA PAPER 87-1834] p 667 A87-45236 displays [NASA-CR-4058] p 705 N87-25807 transonic speeds STOL characteristics of a tactical aircraft with thrust Optimal flight trajectories in the presence of windshear, [AIAA PAPER 87-1749] p 634 A87-45182 vectoring nozzles 1984-86 TRANSONIC WIND TUNNELS [AIAA PAPER 87-1835] p 655 A87-45237 [NASA-CR-180316] p 682 N87-26047 Experimental study of the vortex flow behavior on a Thrust vectoring - Why and how? p 673 A87-46180 TRAJECTORY OPTIMIZATION generic fighter wing at subsonic and transonic speeds Improved agility for modern tighter aircraft. II - Thrust Singular trajectories in airplane cruise-dash [AlACk PAPER 87-1262] p 631 A87-44920 vectoring engine nozzles p 673 A87-46181 optimization Designing transonic wind-tunnel test sections for flow Singular trajectories in airplane cruise-dash [NASA-CR-180636] p 659 N87-26035 diagnostics and laser velocimeter applications optimization TRANSATMOSPHERIC VEHICLES [AIAA PAPER 87-1434] p 684 A87-44954 [NASA-CR-180636] p 659 N87-26035 The thermal environment of transatmospheric vehicles Integration effects of pylon geometry and rearward THRUST-WEIGHT RATIO [AIAA PAPER 87-1514] p 626 A87-43038 mounted nacelles for a high-wing transport Impact of engine technology on supersonic STOVL TRANSDUCERS [AIAA PAPER 87-1920] p 655 A87-45300 [AIAA PAPER 87-1709] p 665 A87-45157 A miniature remote deadweight calibrator Two-dimensional subsonic and transonic wind tunnel wall interference corrections for varied walls Thrust/drag accounting for aerospace plane vehicles p 694 A87-45104 p 686 A87-46955 [AIAA PAPER 87-1966] p 656 A87-45335 TRANSFER FUNCTIONS Helicopter model in flight identification by a real time The pitching damping derivatives measured by A study on the optimization of jet engines for combat force-oscillation method at transonic and supersonic wind aircrafts p 676 A87-46262 self adaptive digital process p 680 A87-43458 tunnel p 686 A87-46958 TILT ROTOR AIRCRAFT An approach to the synthesis of an adaptive flight control system with incomplete information p 680 A87-45096 Development of experimental investigation on transonic Expanding tilt rotor capabilities p 651 A87-43407 wind tunnel wall interference p 687 A87-46960 Calculated performance, stability, and maneuverability TRANSIENT RESPONSE Transient test system design for the T800-APW-80O Miniature remote dead weight calibrator of high-speod tilting-prop-rotor aircraft p 651 A87.43408 turboshaft engine [NASA-CASE-LAR-13564-1] p 700 N87-25558 The 0.6 m x 0.6 m trisonic section (TMK) of DFVLR in The tilt-rotor aircraft - A response to the future? From [AIAA PAPER 87-1791] p 666 A87-45205 TRANSITION POINTS Cologne-Porz, West Germany European interrogations to Eurofar actions [MBB-UD-485-86-PUB] p 654 A87-43474 Study on the interference between the local separation [DFVLR-MITT-86-21] p 687 N87-26053 TRANSPONDERS A derivative engine based on new technology - Low on a wing surface and outer flow-field p 634 A87.45094 Real-time wind estimation and tracking with transponder risk; cost effective [AIAA PAPER 87-1910] p 669 A87-45292 TRANSMISSION EFFICIENCY downlinked airspeed and heading data p 648 A87-42779 TIME DEPENDENCE Transmission efficiency in advanced aerospace TRANSPORT AIRCRAFT An introduction 1o time-dependent aerodynamics of powerplant Countdown to the propfan p 664 A87-44272 aircraft response, gusts and active controls [AIAA PAPER 87-2043] p 671 A87-45376 ]ESDU-84020] p 682 N87.26048 TRANSMISSIONS (MACHINE ELEMENTS) Crash response data system for the controlled impact demonstration (CID) of a full scale transport aircraft TIME LAG Parameters of optimal planetary gears of AI type p 694 A87-43622 p 694 A87-45123 Some fundamentals of simulator cockpit motion Development of a large, spiral bevel gear rotorcraft Integration effects of pylon geometry and rearward generation p 683 A87-44714 mounted nacelles for a high.wing transport TIP SPEED transmission [AIAA PAPER 87-1920] p 655 A87-45300 Tip clearance flows. I - Experimental investigation of [AIAA PAPER 87-1839] p 667 A87-45240 Transmission efficiency in advanced aerospace Dornier 328 - Concept for a new-generation regional an isolated rotor. II - Study of vanous models and airliner p 657 A87-46326 comparison with test results p 638 A87-46208 powerplant TIP VANES [AIAA PAPER 87-2043] p 671 A87-45376 Technological aspects in preparing the development of Measurement of side forces of a H-force rotor TRANSMrI'rER RECEIVERS regional airliners p 657 A87-46327 TACAN/INS Performance Evaluation (TIPE) flight test Soviet helicopter development p 657 A87.46735 p 651 A87-43410 TITANIUM report KRASH analysis correlation. Transport airplane controlled impact demonstration test Superplastic forming/diffusion bonding of titanium lAD-A180138] p 650 N87-25313 [AD-A179906] p 647 N87-25308 p 689 A87-44747 TRANSONIC COMPRESSORS TITANIUM ALLOYS Investigation of the three dimensional flow near the exit Flight service evaluation of advanced composite ailerons on the L-1011 transport aircraft High temperature titanium alloys p 689 A87-44739 of two backswept transonic centrifugal impellers [NASA-CR-178321] p 691 N87.25439 Developments in titanium alloys p 689 A87-44744 p 638 A87-46192

A-27 TRANSPORTPROPERTIES SUBJECTINDEX

Effect of Reynolds number variation on aerodynamics Tip clearance flows. I - Experimental investigation of TURBOPROP ENGINES of a hydrogen-fueled transport concept at Mach 6 an isolated rotor. II - Study of various models and Engine maintenance improvement considerations [NASA-TP-2728] p 645 N87-26031 comparison with test results p 638 A87-46208 [AIAA PAPER 87-1716] p 624 A87-45159 Control of aircraft under severe wind shear conditions A study of some factors affecting the performance of Designing for fretting fatigue free joints in turboprop p 682 N87-26050 a contra-retating axial compressor stage engine gearboxes First approximation to landing field length of civil p 639 A87-46211 [AIAA PAPER 87-2046] p 671 A87-45378 transport aeroplanes (50 ft., 15.24 m screen) Expendable turbojet compressor design, test and Finite element analysis of large spur and helical gear [ESDU-84040] p 688 N87-26056 development p 674 A87-46212 systems TRANSPORT PROPERTIES Improvement of aerodynamic calculation on S(2)m [AIAA PAPER 87-2047] p 697 A87-45379 High temperature transport properties of air stream surface of axial compressor by using of annulus Wind tunnel performance results of an aeroelastically [AIAA PAPER 87-1632] p 707 A87-43129 wall boundary layer calculation p 639 A87-46216 scaled 2/9 model of the PTA flight test prop-tan TREES (MATHEMATICS) J85 surge transient simulation p 675 A87-46240 [NASA-TM-89917] p 642 N87-25294 Analysis of typical fault-tolerant architectures using Evaluation of installed performance of a HARP p 704 A87-45771 Development of a laser interferometric system for TRISONIC WIND TUNNELS velocity measurements inside a transonic axial flow wing-tip-mountad pusher turboprop on a semispan wing The 0.6 m x 0.6 m trisonic section (TMK) of DFVLR in compressor stage p 698 A87-46244 [NASA-TP-2739] p 659 N87-26041 Cologne-Porz, West Germany Erosion problem of axial compressor blades of a TURBOSHAFTS [DFVLR-MtTT-86-21] p 687 N87-26053 turboshaff engine p 675 A87-46246 Helicopter turboshaft engine acoustic and infrared TRUNCATION ERRORS TURBOFAN ENGINES studies and tests p 663 A87-43467 Computation of unsteady transonic aerodynamics with Evaluating and testing of turbofan engines Heat exchangers for turboshaft engines truncation error injection p 627 A87-43392 [ASME PAPER 86-WA/DE-3] p 664 A87-43701 p 664 A87-44253 TURBINE BLADES Engine design and systems integration for propfan and Transient test system design for the T800-APW-800 Electrochemical machining processes in aircraft engine high bypass turbofan engines turboshaft engine building --- Russian book p 693 A87-42905 [AIAA PAPER 87-1730] p 665 A87-46169 [AIAA PAPER 87-1791] p 666 A87-45205 The low-aspect-ratio parameter of blades UDF/727 flight test program Complex modal balancing of flexible rotors including p 663 A87-43607 [AIAA PAPER 87-1733] p 666 A87-45171 residual bow Optimization of the duration o1 ultrasonically activated Design and test verification of a combustion system for [AIAA PAPER 87-1840] p 695 A87-45241 impact surface treatment of gas-turbine-engine blades an advanced turbofan engine Contingency power for small turboshaft engines using p 663 A87-43609 [AIAA PAPER 87-1826] p 666 A87-45231 water injection into turbine cooling air A study of the thermal-stress state of gas turbine engine High performance turbofan afterburner systems [AIAA PAPER 87-1906] p 668 A87-45289 blades with protective coatings p 664 A87-43640 [AIAA PAPER 87-1830] p 666 A87-45234 Erosion problem of axial compressor blades of a Development of low-cost test techniques for advancing NASA/GE advanced low emissions combustor turboshaft engine p 675 A87-46246 film cooling technology program TURBULENT BOUNDARY LAYER [AIAA PAPER 87-1913] p 696 A87-45293 [AIAA PAPER 87-2035] p 671 A87-45369 Calculation of the boundary layer at the inlet section Experimental data correlations for the effects of rotation Operational engine usage and mission analysis of a compressor cascade p 629 A87-43608 on impingement cooling of turbine blades [AIAA PAPER 87-2097] p 671 A87-45404 A method for the calculation of the interaction of a [AIAA PAPER 87-2008] p 696 A87-45349 Dual cycle turbofan engine Friction factors and heat transfer coefficients in [AIAA PAPER 87-2102] p 672 A87-45407 turbulent boundary layer with a shock wave p 639 A87-46238 turbulated cooling passages of different aspect ratios. I - Three stream turbofan-variable cycle engine with integral Experimental results turbocompressor TURBULENT FLOW [AIAA PAPER 87-2009] p 696 A87-45350 [AIAA PAPER 87-2104] p 672 A87-45409 Aero-optical analysis of compressible flow over an open Application of a 3D inviscidrotational design procedure Navier-Stokes analysis of a very-high-bypass-ratio cavity for turbomachinery bladings p 638 A87-46204 turbofan engine in reverse thrust [AIAA PAPER 87-1399] p 632 A87-44943 Numerical simulation of transonic throe-dimensional [AIAA PAPER 87-2170] p 697 A87-45450 Combustion-generated turbulence in practical flows in turbine blade passages p 638 A87-46206 A study of some factors affecting the performance of combustors Aereelasticity in turbomachines comparison of a contra-retating axial compressor stage [AIAA PAPER 87-1721) p 665 A87-45161 theoretical and experimental cascade results. Appendix p 639 A87-46211 Three-dimensional numerical predictions of the flow A5: All experimental and theoretical results for the 9 Investigation on the stall margin of a turbofan engine behind a rearward-facing-step in a supersonic combustor standard configurations p 675 A87-46239 [AIAA PAPER 87-1962] p 636 A87-45332 lAD-A180534) p 677 N87-25326 V.2500 - Back on course? p 676 A87-46372 TURBINE ENGINES TURBULENT MIXING Evaluation of installed performance of a Linear instability waves in supersonic turbulent mixing Development program of a full authority digital electronic wing-tip-mounted pusher turboprop on a semispan wing layers control system for the T55-L-712E turboshaft engine ]NASA-TP-2739] p 659 N87-26041 p 663 A87-43465 TURBOJET ENGINE CONTROL [AIAA PAPER 87-1418] p 633 A87-44948 Full-scale thrust reverser testing in an altitude facility Fiber optic control of jet aircraft engines A simple model for finite chemical kinetics analysis of [AIAA PAPER 87-1788J p 684 A87-45203 p661 A87-45115 supersonic turbulent shear layer combustion Future advanced control technology study (FACTS) - Future advanced control technology study (FACTS) - [AIAA PAPER 87-1879] p 696 A87-45273 A look at emerging technologies --- for turbine engines A look at emerging technologies --- for turbine engines A mixing augmentation technique for hypervelocity [AIAA PAPER 87-1930] p 670 A87-45308 [AIAA PAPER 87-1930] p 670 A87-45308 scram jets Application of computational fluid dynamics to analysis Digital control development for the T56-A-427 [AIAA PAPER 87-1882] p 668 A87-45275 of exhaust gas/diffuser interactions in a turbine engine [AIAA PAPER 87-2013] p 670 A87-45353 altitude test cell TURBOJET ENGINES The mixing of jets under simulated engine-like [AIAA PAPER 87-2014] p 670 A87-45354 turbulence p 698 A87-46231 Use of RPM trim to automate the supersonic engine/inlet Advanced detection, isolation and accommodation of match in the SR-71A TURBULENT WAKES sensor failures: Real-time evaluation [AIAA PAPER 87-1848] p 667 A87-45248 Wake measurements of an oscillating airfoil [NASA-TP-2740] p 682 N87-25331 Expendable turbojet compressor design, test and p 637 A87-45779 TURBINE WHEELS development p 674 A87-46212 TWO DIMENSIONAL BODIES Experimental application of strain pattern analysis (SPA) Application of a fuzzy controller in fuel system of turbojet Secondary stream and excitation effects on - Wind tunnel and flight test results p 654 A87-43459 engine p 674 A87-46227 two-dimensional nozzle plume characteristics Investigation of rotating additional blades on the J85 surge transient simulation p 675 A87-46240 [AIAA PAPER 87-2112] p 637 A87-45414 periphery of an axial-compresssor rotor Prepfan propulsion system development TWO DIMENSIONAL BOUNDARY LAYER p 629 A87-43618 p 675 A87-46247 TURBOCOMPRESSORS Influence of a heated leading edge on boundary layer Changes in the free flow in the intake of a turbojet engine growth, stability and transition Effect of fabrication-related deviations of the geometrical during the aircraft takeoff run p 640 A87-46351 [DE87-008516] p 700 N87.25538 parameters of blade profiles on flow in a compressor TURBOMACHINE BLADES TWO DIMENSIONAL FLOW p 629 A87-43603 Investigation of rotating additional blades on the Investigation of flow structure in a compressor with two periphery of an axial-oompresssor rotor An experimental investigation of a superedtical airfoil types of guides p 629 A87-43604 p 629 A87-43618 at transonic speeds Calculation of the boundary layer at the inlet section TURBOMACHINERY [AIAA PAPER 87-1241] p 630 A87-44914 of a compressor cascade p 629 A87-43608 Application of a 3D inviscid rotational design procedure Two*dimensional numerical analysis for inlets at Efficiency of the utilization of rotor blade shroud labyrinth for turbomachinery bladings p 638 A87-46204 subsonic through hypersonic speeds seals in an axial-compressor stage with large radial An improved approach for transonic flow [AIAA PAPER 87-1751] p 634 A87-45184 clearances p 694 A87-43611 p 639 A87-46215 Numerical simulation of diffusor/combustor dome Investigation of rotating additional blades on the Optical flow diagnostic measurements in interaction p 676 A87-46255 periphery of an axial-comprssssor rotor turbomachinery p 698 A87-46245 Aereelasticity in turbomachines comparison of p 629 A87-43618 Numerical simulation of flows in axial and radial Rotor wake segment influence on stator-surface theoretical and experimental cascade results. Appendix turbomachines using Euler solvers boundary layer development in an axial-flow compressor A5: All experimental and theoretical results for the 9 [ONERA, TP NO. 1987-87] p 641 A87-46776 stage standard configurations Aeroelasticity in turbomachines comparison of [AIAA PAPER 87-1741] p 695 A87-45178 lAD-A180534] p 677 N87-25326 theoretical and experimental cascade results. Appendix A stage-by-stage pest-stall compression system TWO DIMENSIONAL JETS A5: All experimental and theoretical results for the 9 modeling technique standard configurations Two-dimensional nozzle plume characteristics [AIAA PAPER 87-2088] p 636 A87-45397 [AD-A180534] p 677 N87-25326 [AIAA PAPER 87-2111 ] p 636 A87-45413 Three stream turbofan-variable cycle engine with integral TURBOPROP AIRCRAFT TWO PHASE FLOW turbocompressor Proving that Avanti stands for progress Diagnostic methods for air-breathing engines [AIAA PAPER 87-2104] p 672 A87-45409 p 656 A87-46314 p 686 A87-46243

A-28 WAKES SUBJECT INDEX

U Diagnostics in supersonic combustion Viscid/inviscid separated flows [AIAA PAPER 87-1787] p 690 A87-45202 [AD-A179858] p 699 N87-25536 ULTRAHIGH FREQUENCIES Development of a laser interferometric system for Numerical solution of the Navier-Stokes equations about A conformal aircraft phased array antenna for velocity measurements inside a transonic axial flow three-dimensional configurations: A survey airplane-satellite communication in the L band compressor stage p 698 A87-46244 p 701 N87-26022 [DFVLR-FB-86-47] p 701 N87-26259 Velocity measurements near the blade tip and in the VISION ULTRASONICS tip vortex core of a hovering model rotor Engineering and human visual considerations in p 645 N87-26030 Optimization of the duration of ultrasonically actNated development of a fibre optic helmet mounted display VERTICAL LANDING impact surface treatment of gas-turbine-engine blades p 661 A87-44727 p 663 A87-43609 Advantages of thrust vectoring for STOVL VISUAL AIDS [AIAA PAPER 87-1708] p 665 A87-45158 UNSTEADY FLOW Colour dependence and surplus information in airport Impact of engine technology on supersonic STOVL visual aids during VFR operations p 649 A87-44040 Computation of unsteady transonic aerodynamics with [AIAA PAPER 87-1709] p 665 A87-45157 truncation error injection p 627 A87-43392 VISUAL FLIGHT STOVL engine/airframe integration Visual systems developments p 694 A87-44725 Unsteady separation characteristics of airfoils operating [AIAA PAPER 87-1711] p 655 A87-45158 VISUAL FLIGHT RULES under dynamic stall conditions p 628 A87-43421 VERTICAL TAKEOFF AIRCRAFT An advanced mathematical model for helicopter flight Rotorcraft research - A national effort (The 1986 Colour dependence and surplus information in airport simulation using nonlinear unsteady aerodynamics Alexander Nikolsky Honorary Lectureship) visual aids during VFR operations p 649 A87-44040 p 679 A87-43435 p 623 A87-44255 Heliport visual approach surface testing test plan Numerical study of the gasdynamic process in a pulsejet VIBRATION [AD-A179897] p 650 N87-25312 engine p 663 A87-43814 Aeroelasticity in turbomachines comparison of VISUAL SIGNALS Visualization of three-dimensional structures about a theoretical and experimental cascade results. Appendix New standards established for realism in visual pitching forward swept wing A5: All experimental and theoretical results for the 9 simulation --- for commercial aircraft flight [AIAA PAPER 87-1322] p 831 A87-44929 standard configurations p 686 A87-46438 Forced unsteady vortex flows driven by pitching [AD-A180534] p 677 N87-25326 VOICE CONTROL airfoils Effect of signal jitter on the spectrum of rotor impulsive DVI in the military cockpit - A third hand for the combat [AIAA PAPER 87-1331] p 631 A87-44931 noise pilot --- Direct Voice Input p 681 A87-46315 [NASA-TM-100477] p 708 N87-25827 Compadsons of unsteady flow fields about straight and VORTEX BREAKDOWN VIBRATION DAMPING swept wings using flow visualization and hotwire Vortex breakdown simulation Scan stabilization and jitter control for an airborne anemometry [AIAA PAPER 87-1343] p 632 A87-44934 telescope )660 A87-42812 [AIAA PAPER 87-1334] p 631 A87-44932 VORTEX FILAMENTS Helicopter activities in Germany ) 623 A87-43401 Unsteady three-dimensional Navier-Stokes simulations Prediction of blade airloads in hovering and forward flight Recent trends in rotary-wing aeroelasticity of turbine rotor-stator interaction using free wakes p 651 A87-43411 ) 652 A87-43442 [AIAA PAPER 87-2058] p 636 A87-45386 VORTEX FLAPS Development of an experimental system for active The influence of flow non-uniformities in air-breathing Subsonic wind-tunnel measurements of a slender control of vibrations on helicopters ) 679 A87-43447 hypersonic propulsion systems wing-body configuration employing a vortex flap Kinematic observers for active control of helicopter rotor [NASA-TM-89101] p 642 N87-25295 [AIAA PAPER 87-2079] p 638 A87-45394 vibration ) 679 A87-43448 Unsteady viscous flows round moving circular cylinders VORTEX RINGS A unique approach to aeroelastic testing of scaled and airfoils, II p 637 A87-45792 rotors ) 683 A87-43461 Investigation of helicopter twin-rotor characteristics J85 surge transient simulation p 675 A87-46240 p 628 A87-43438 A study on the effect of non-dimensional system Aeroelastic control of stability and forced response of parameters on squeeze film damper )erformance using VORTICES supersonic rotors by aerodynamic detuning experimental data 698 A87-46229 A parametric investigation of a free wake analysis of p 678 A87-46249 Ground and flight test results of total main rotor hovering rotors p 627 A87-43413 Experimental studies on the dynamic development and isolation system Investigation of blade-vortices in the rotor-downwash control of unsteady separated flows p 642 N87-25297 [NASA-CR-4082] p 643 N87-25302 p 627 A87-43415 Steady and unsteady aerodynamic forces from the Dual adaptive control: Design principles and The use of discrete vortices to predict lift of a circulation SOUSSA surface-panel method for a fighter wing with tip applications control rotor section with a trailing edge blowing slot missile and comparison with experiment and PANAIR [NASA-CR-181050] p 705 N87-25804 p 627 A87-43416 [NASA-TP-2736] p 645 N87-26032 Dynamic mechanical propedies of advanced composite UTILIZATION Full potential modeling of blade-vortex interactions materials and structures: A review p 691 N87-25988 p 627 A87-43417 Use of artificial intelligence methods Helicopter vibration control: Recent advances [MBB-LKE-434-S/PUB/284] p 707 N87-26831 Study of the dynamic response of helicopters to a large p 660 N87-26247 airplane wake p 678 A87-43429 VIBRATION ISOLATORS Helicopter response to an airplanes's vortex wake V Ground and flight test results of a total main rotor p 678 A87-43430 isolation system Investigation of flow structure in a compressor with two V/STOL AIRCRAFT [NASA-CR-4082] p 843 N87-25302 types of guides p 629 A87-43604 Helicopter-V/STOL dynamic wind and turbulence design Helicopter vibration control: Recent advances Numerical simulation of vortical flows over a strake-delta methodology p 658 N87-25284 p 660 N87-26247 wing VIBRATION MEASUREMENT VANELESS DIFFUSERS [AIAA PAPER 87-1229] p 630 A87-44913 A noninterference blade vibration measurement system Effect of swirl on the performance of a radial vaneless Experimental study of the vortex flow behavior on a diffuser with compressible flow at Mach numbers of 0.7 for gas turbine engines generic fighter wing at subsonic and transonic speeds and 0.8 [AIAA PAPER 87-1758] p 695 A87-45186 [AIAA PAPER 87-1262] p 631 A87-44920 VIBRATION MODE [ASME PAPER 86-WA/FE-6] p 629 A87-43704 Incompressible Navier-Stokes computations of vortical VANES Experimental application of strain pattern analysis (SPA) flows over double-delta wings Static investigation of post-exit vanes for multiaxis thrust - Wind tunnel and flight test results p 654 A87-43459 [AIAA PAPER 87-1341] p 631 A87-44933 VIBRATION SIMULATORS vectoring Study on the interference between the local separation Bounded random oscillations - Model and numerical [AIAA PAPER 87-1834] p 667 A87-45236 on a wing surface and outer flow-field VAPORS resolution for an airfoil p 634 A87-45094 Portable fuel leak detector [ONERA, TP NO. 1987-73] p 681 A87-46787 Vortex-nozzle interactions in ramjet combustors VIBRATION TESTS [AD-A180095] p 700 N87-25550 {AIAA PAPER 87-1871] p 668 A87-45266 VARIABLE CYCLE ENGINES Substantiation of the analytical prediction of ground and Entrainment effect of a leeding-edge vortex Dual cycle turbofan engine air resonance stability of a bearingless rotor, using model p 641 A87-46777 [AIAA PAPER 87-2102] p 672 A87-45407 scale tests p 654 A87-43463 Control of the discrete vortices from a delta wing Variable cycle concepts for high Mach applications VISCOUS FLOW p 641 A87-48779 Viscous-inviscid interactions inexternal aerodynamics [AIAA PAPER 87-2103] p 672 A87-45408 An experimental investigation of delta wings with p 626 A87-43299 Three stream turbofan-variable cycle engine with integral leading-edge vortex separation p 641 A87-46956 turbocompressor A unified approach for potential and viscous free-wake VORTICITY [AIAA PAPER 87-2104] p 672 A87-45409 analysis of helicopter rotors p 627 A87-43412 Forced unsteady vortex flows driven by pitching VARIABLE GEOMETRY STRUCTURES Simulation of transonic viscous flow over a fighter-like airfoils Engine variable geometry effects on commercial configuration including inlet [AIAA PAPER 87-1331] p 631 A87-44931 supersonic transport development ]AIAA PAPER 87-1199] p 630 A87-44906 The numerical simulation of subsonic flutter [AIAA PAPER 87-2101] p 672 A87-45406 Development of a viscous cascade code based on scalar [AIAA PAPER 87-1428] p 633 A87-44952 VELOCITY DISTRIBUTION implicit factorization Expedmental studies on the dynamic development and A new simulation of airfoil dynamic stall due to velocity [AIAA PAPER 87-2150] p 637 A87-45435 control of unsteady separated flows p 642 N87-25297 and incidence fluctuations Unsteady viscous flows round moving circular cylinders [AIAA PAPER 87-1242] p 830 A87-44915 and airfoils. II p 637 A87-45792 VELOCITY MEASUREMENT 3-D viscous flow calculations at design and off-design W Molecular flow velocity using Doppler shifted Raman conditions for the NACA 48-inch radial-inlet centrifugal spectroscopy impeller p 638 A87-46191 WAKES [AIAA PAPER 87-1531] p 693 A87-43053 A method for the calculation of the interaction of a Investigation of helicopter twin-rotor characteristics p 528 A87-43438 A new method of analytical evaluation of helicopter true turbulent boundary layer with a shock wave p 639 A87-46238 airspeed p 661 A87-43439 Rotor wake segment influence on stator-surface Autonomous navigation system for the new generation Unsteady viscous-inviscid interaction method and boundary layer development in an axial-flow compressor of military helicopters and associated flight tests computation of buffeting over airfoils stage p 648 A87-43469 [ONERA, TP NO. 1987-58] p 640 A87-46759 [AIAA PAPER 87-1741] p 695 A87-45178

A-29 WALL FLOW SUBJECT INDEX

Compressible flows in the wakes of a square cylinder Automatic systems and the low-level wind hazard The pitching damping derivatives measured by and thick symmetrical airfoil arranged in tandem p 681 N87-25279 fome-oscillation method at transonic and supersonic wind p 641 A87-46922 Simulator manufacturers' requirements tunnel p 686 A87-46958 WALL FLOW p 687 N87-25280 Wind tunnel performance results of an aeroelastically Transonic wall interference assessment and corrections Military specifications p 658 N87-25281 scaled 2/9 model of the PTA flight test prop-fan for airfoil data from the 0.3-rneter TCT adaptive wall test Unresolved issues in wind shear encounters [NASA-TM-89917] p 642 N87-25294 section Subsonic wind-tunnel measurements of a slender p 647 N87-25282 [AIAA PAPER 87-1431] p 633 A87-44953 wing-body configuration employing a vortex flap Simulator systems integration p 687 N87-25283 Improvement of aerodynamic calculation on S(2)m [NASA-TM-89101] p 642 N87-25295 Accident investigation p 647 N87-25285 stream surface of axial compressor by using of annulus Recent progress in the measurement of the drag United Airlines wind shear incident of May 31, 1984 wall boundary layer calculation p 639 A87-46216 coefficients of models of transport aircraft in a wind WALL PRESSURE p 647 N87-25287 tunnel

Development of experimental investigation on transonic United Airlines wind shear incident of May 31, 1984 [NASA-TT-20096] p 644 N87-25306 wind tunnel wall interference p 687 A87-46960 p 647 N87-25288 Determination of the local heat transfer characteristics WARNING SYSTEMS Optimal flight trajectories in the presence of windshear, on glaze ice accretions on a cylinder and a NACA 0012 History of wind shear turbulence models 1984-86 airfoil

p 703 N87-25269 [NASA-CR-180316] p 682 N87-26047 [AD-A179931] p 647 N87-25309 Accident investigation p 647 N87-25285 Control of aircraft under severe wind shear conditions Influence of a heated leading edge on boundary layer WASTE HEAT p 682 N87-26050 growth, stability and transition Waste heat recovery system for high altitude application WIND TUNNEL APPARATUS [DE87-008516] p 700 N87-25538 of liquid cooled, piston engines Airfoil flutter model suspension system Miniature remote dead weight calibrator {AIAA PAPER 87-2174] p 673 A87-45454 [NASA-CASE-LAR-13564-1] p 700 N87-25558 WATER INJECTION [NASA-CASE-LAR-t3522-1-SB] p 687 N87-25334 WIND TUNNEL CALIBRATION Wind tunnel evaluation of a truncated NACA 64-621 Contingency power for small turboshaft engines using airfoil for wind turbine applications Test flow calibration study of the Langley Arc-Heated water injection into turbine cooling air [NASA-CR-180803] p 703 N87-25621 Scramjet Test Facility [AIAA PAPER 87-1906] p 668 A87-45289 An experimental low Reynolds number comparison of WAVE DIFFRACTION [AIAA PAPER 87-2165] p 685 A87-45445 a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil and WIND TUNNEL MODELS Computational aeroacoustics as applied to the diffraction a NACA 64-210 airfoil in simulated heavy rain Airfoil flutter model suspension system of sound by cylindrical bodies p 707 A87-43383 [NASA-CR-181119] p 644 N87-25997 WEATHER [NASA-CASE-LAR-13522-1-SB] p 687 N87-25334 Aerodynamics of unmanned aircraft at full-scale in the Case history of FAA/SRI wind shear models An experimental investigation of dynamic ground RAE 24ft wind-tunnel effect p 703 N87-25268 [RAE-TM-AERO-2081] p 645 N87-26027 Introduction to the JAWS Program [NASA-CR-180560] p 659 N87-26036 Low-speed wind-tunnel results for symmetrical NASA p 703 N87-25270 WIND TUNNEL NOZZLES LS( 1)-0013 airfoil Wind shear and turbulence simulation Aerodynamic design modification of a hypersonic wind [NASA-TM-4003] p 645 N87-26033 p 703 N87-25274 tunnel nozzle by CSCM with high order accuracy --- An experimental investigation of dynamic ground WEIGHT INDICATORS Conservative Supra-Characteristics Method effect Miniature remote dead weight calibrator [AIAA PAPER 87-1896] p 635 A87-45284 [NASA-CR-180560] p 659 N87-26036 [NASA-CASE-LAR-13564-1] p 700 N87-25558 WIND TUNNEL TESTS WIND TUNNEL WALLS WEIGHT REDUCTION Molecular flow velocity using Doppler shifted Raman Transonic walt interference assessment and corrections Optimum design of a helicopter rotor blade spectroscopy for airfoil data from the 0.3-meter TCT adaptive wall test p 651 A87-43406 [AIAA PAPER 87-1531] p 693 A87-43053 section Expanding tilt rotor capabilities p 651 A87-43407 A comparison of the acoustic and aerodynamic [AIAA PAPER 87-1431] p 633 A67-44953 Preliminary structural design of composite main rotor measurements of a model rotor tested in two anechoic Two-dimensional subsonic and transonic wind tunnel blades for minimum weight wind tunnels p 683 A87-43425 wall interference corrections for varied walls [NASA-TP-2730] p 691 N87-25435 Experimental application of strain pattern analysis (SPA) p 686 A87-46955 WELDED STRUCTURES - Wind tunnel and flight test results p 654 A87-43459 Development of experimental investigation on transonic Fatigue crack growth predictions of welded aircraft The effect of trip wire roughness on the performance wind tunnel wall interference p 687 A87-46960 structures containing flaws in the residual stress field of the Wortmann FX 63-137 airfoil at low Reynolds WIND TUNNELS p 692 A87-42853 numbers p 629 A87-44019 Failure analysis of a large wind tunnel compressor WEST GERMANY Advances in the computation of transonic separated blade p 692 A87-42852 Going beyond the limits. Aviation in Germany flows over finite wings Fatigue-life monitoring of the 5 metre wind tunnel [SO-1-87] p 710 N87-26853 [AIAA PAPER 87-1195] p 630 A87-44904 [RAE-TM.AERO-2084] p 688 N87-26055 WIND EFFECTS Experimental study of the vortex flow behavior on a WIND TURBINES Introduction to the JAWS Program generic fighter wing at subsonic and transonic speeds Wind tunnel evaluation of a truncated NACA 64-62 f p 703 N87-25270 [AIAA PAPER 87-1262] p 631 A87-44920 airfoil for wind turbine applications Modeling and implementation of wind shear data Forced unsteady vortex flows driven by pitching [NASA-CR-180803] p 703 N87-25621 p 709 N87-25273 airfoils WIND VELOCITY MEASUREMENT WIND MEASUREMENT [AIAA PAPER 87-1331] p 631 A87-44931 Real-time wind estimation and tracking with transponder Wind determination from aircraft-movement data Designing transonic wind-tunnel test sections for flow downlinked airspeed and heading data p 702 A87-45892 diagnostics and laser vetocimeter applications p 648 A87-42779 Case history of FAA/SRI wind shear models [AIAA PAPER 87-1434] p 684 A87-44954 WlNDPOWER UTILIZATION p 703 N87-25268 Investigation of a delta-wing fighter model flow field at Wind tunnel evaluation of a truncated NACA 64-621 WIND PROFILES transonic speeds airfoil for wind turbine applications Turbulence models p 703 N87-25277 [AIAA PAPER 87-1749] p 634 A87-45182 [NASA-CR-180803] p 703 N87-25621 Simulator manufacturers' requirements Flow behind single- and dual-rotation propellers at angle WINDS ALOFT p 687 N87-25280 of attack United Airlines wind shear incident of May 31, 1984 WIND SHEAR [AIAA PAPER 87-1750] p 634 A87-45183 p 647 N87-25288 Maximum survival capability of an aircraft in a severe Static investigation of post-exit vanes for multiaxis thrust WING CAMBER windshear p 680 A87-44254 vectoring Conceptual studies of control systems for wings with Analysis of a microborst in the FACE meteorological [AIAA PAPER 87-1834] p 667 A87-45236 variable camber meeonetwork in southern Florida p 702 A87-45962 Parametric study of single expansion ramp nozzles at [MBB-UT-221/86] p 682 N87-26836 Wind Shear/Turbulence Inputs to Flight Simulation and subsonic/transonic speeds WING LOADING Systems Certification [AIAA PAPER 87-1836] p 635 A87-45238 Study of lee-side flows over conically cambered Delta [NASA-CP-2474] p 625 N87-25267 Wind tunnel tests on a one-foot diameter SR-7L propfan wings at supersonic speeds, part 2 Case history of FAA/SRI wind shear models model [NASA-TP-2660-PT-2] p 643 N87-25301 p 703 N87-25268 [AIAA PAPER 87-t892] p 635 A87-45281 WING NACELLE CONFIGURATIONS History of wind shear turbulence models Development of low-cost test techniques for advancing Integration effects of pylon geometry and rearward p 703 N87-25269 film cooling technology mounted nacelles for a high-wing transport Introduction to the JAWS Program [AIAA PAPER 87-1913] p 696 A87-45293 [AIAA PAPER 87-1920] p 655 A87-45300 p 703 N87-25270 F-15 SMTD hot gas ingestion wind tunnel test results WING OSCILLATIONS JAWS multiple Doppler derived winds --- STOL and Maneuver Technology Demonstrator Active control of aerofoil flutter p 681 A87-46792 p 703 N87-25271 [AIAA PAPER 87-1922] p 669 A87-45301 A panel method for prediciting the dynamic stability Status of the JAWS Program p 703 N87-25272 Design and evaluation of a new injector configuration derivatives of an oscillating wing in high subsonic flow Modeling and implementation of wind shear data for supersonic combustion p 674 A87-46218 p 641 A87-46951 p 709 N87-25273 Underexpanded jet-free stream interactions on an On the nonlinear aerodynamic and stability Wind shear and turbulence simulation axisymmetric afterbody configuration characteristics of a generic ohine-forebody slender-wing p 703 N87-25274 p 639 A87-46232 fighter configuration [NASA-TM-89447] p 643 N87-25305 Application of data to piloted simulators Validation of aerodynamic measurement techniques and WING PROFILES p 687 N87-25275 calculation methods for high-lift systems p 640 A87-46363 Advances in the computation of transonic separated B-57B gust gradient program p 657 N87-25276 Wind tunnel experimental study of optical beam flows over finite wings Turbulence models p 703 N87-25277 degradation through heterogeneous aerodynamic flows [AIAA PAPER 87-1195] p 630 A87-44904 Microburst model requirements for flight simulation: An [ONERA, TP NO. 1987-50] p 707 A87-46753 WING TIP VORTICES airframe manufacturer's perspective An experimental investigation of delta wings with The influence of winglets on rotor aerodynamics p 687 N87-25278 leading-edge vortex separation p 641 A87-46956 p 628 A87-43422

A-30 SUBJECT INDEX YIELD POINT

Description of, and preliminary results from, a new blade-vortex interaction test facility p 683 A87-43460 On the nonlinear aerodynamic and stability characteristics of a generic chine-forebody slender-wing fighter configuration [NASA-TM-89447] p 643 N87-25305 Evaluation of installed performance of a wing-tip-mounted pusher turboprop on a semispan wing [NASA-TP-2739] p 659 N87-26041 WING TIPS Measurements of the performance of a helicopter swept tip rotor in flight p 652 A87-43423 WINGLETS The influence of winglets on rotor aerodynamics p 628 A87-43422 WINGS Study on the interference between the local separation on a wing surface and outer flow-field p 634 A87-45094 Steady and unsteady aerodynamic forces from the SOUSSA surface-panel method for a fighter wing with tip missile and comparison with experiment and PANAIR [NASA-TP-2736] p 645 N87-26032 Factors affecting the sticking of insects on modified aircraft wings _NASA-CR-180957] p 659 N87-26037 Measurement of the effect Of manufacturing deviations on natural laminar flow for a single engine general aviation airplane [NASA-CR-180671] p 677 N87-26044 WIRE The effect of trip wire roughness on the performance of the Wortmann FX 63-137 airfoil at low Reynolds numbers p 629 A87-44019 WORKLOADS (PSYCHOPHYSlOLOGY) Optimal cooperative control synthesis of active displays [NASA-CR-4058] p 705 N87-25807 X

X WING ROTORS RSRA/X-wing - A status report p 651 A87-43409 Y

YIELD POINT A3t0-300 CFRP fin damage tolerance demonstration [MBB-UT-015/86] p 658 N87-25317

A-31 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 219) November 1987

Typical Personal Author Index Listing

AINSWORTH, R. W. BALAKRISHNAN, N. The role of short duration facilities in gas turbine Terrain modelling of glideslope for instrument landing -._ PERSONAL AUTHOR I research p 685 A87-46222 system p 650 A87-46415 AI.JABRI, ABDULLAH S. BALLAL, D. R. BERNER, W. E. Wind tunnel tests on a one-foot diameter SR-7L propfan Combustion-generated turbulence in practical model [---Air Force technical objective document fiscal year combustors [AIAA PAPER 87-1892] p 635 A87-45281 [AIAA PAPER 87-1721] p 665 A87-45161 1198-7 p62 N87-16779 ALMEIDA, R. A. R. BARBER, B. Design of motion simulation software with digital filtering AOI displays using laser illumination techniques p 704 A87-44712 p 694 A87-44726 AMARNATH, B. G. BARBI, C. Erosion problem of axial compressor blades of a A new simulation of airfoil dynamic stall due to velocity turboshaff engine p 675 A87-46246 and incidence fluctuations ANAMATEROS, E. [AIAA PAPER 87-1242] p 630 A87-44915 Composite vital parts optimisation for EH 101 rotor hub p 653 A87-43451 BARE, E. A. ANDERSON, CHRISTOPHER J. Parametric study of single expansion ramp nozzles at Advanced fighter thrust reverser integration for minimum subsonictransonic speeds landing distance [AIAA PAPER 87-1836] p 635 A87-45238 Listings in this index are arranged alphabetically by [AIAA PAPER 87-t923] p 655 A87-45302 BARE, E. ANN Investigation of a delta-wing fighter model flow field at personal author. The title of the document provides ANDERSON, GRIFFIN Y. An outlook on hypersonic flight transonic speeds the user with a brief description of the subject [AIAA PAPER 87-2074] p 671 A87-45392 [AIAA PAPER 87-1749] p 634 A87-45182 matter. The report number helps to indicate the ANDRES, J. BARLOW, D. NEAL type of document listed (e.g., NASA report, The tilt-rotor aircraft - A response to the future? From Airbreathing propulsion system design at the United European interrogations to Eurofar actions States Air Force Academy - An integrated approach translation, NASA contractor report). The page and [MBB-UD-485-86-PUB] p 654 A87-43474 [AIAA PAPER 87-1870] p 709 A87-45265 accession numbers are located beneath and to the ANDRESEN, RICHARD P. BARNES, A. G. right of the title. Under any one author's name the Optically interfaced sensor system for aerospace The integration of a six axis motion system and a wide accession numbers are arranged in sequence with applications p 694 A87-45107 angle visual system inside a dome p 684 A87-44720 ANDREWS, EARL H., JR. BARNWELL, RICHARD W. the AIAA accession numbers appearing first. A subsonic to Mach 5.6 subscale engine test facility Low-speed wind-tunnel results for symmetrical NASA [AIAA PAPER 87-2052] p 685 A87-45381 LS(1)-0013 airfoil ANISHCHENKO, V. M. [NASA-TM-4003] p 645 N87-26033 Optimization of the duration of ultrasonically activated BARSHALOM, YAAKOV A impact surface treatment of gas-turbine-engine blades Dual adaptive control: Design principles and p 663 A87-43609 applications ABRAMS, FREDRIC L. ARMAND, C. [NASA-CR-181050] p 705 N87-25804 The F-15E R&M challenge p 699 A87-46715 Recent progress in the measurement of the drag BARTA, JOSEPH ACHACHE, MARC coefficients of models of transport aircraft in a wind Application of ceramics to ramjet engine nozzles tunnel Development of an experimental system for active p 690 A87-46221 control of vibrations on helicopters p 679 A87-43447 [NASA-TT-20096] p 644 N87-25306 BARTLETT, GLYNN R. ARMSTRONG, ALAN Evaluation of installed performance of a ACHARYA, S. Aviation safety and the FAA's quality assurance wing-tip-mounted pusher turboprop on a semispan wing Flow over a trailing flap and its asymmetric wake program p 709 A87-44064 [NASA-TP-2739] p 659 N87-26041 p 626 A87-43376 ARNOLD, J. O. BARTOLOTTA, PAUL A. ADAIR, D. Computational chemistry p 706 N87-26023 A high temperature fatigue and structures testing Flow over a trailing flap and its asymmetric wake ASHILL, P. R. facility p 626 A87-43376 The air-injection method of fixing boundary-layer [NASA-TM-100151] p 701 N87-26399 ADELMAN, HENRY G. transition and investigating scale effects BARTON, G. The thermal environment of transatmospheric vehicles p 639 A87.46264 EH101 cockpit design p 661 A87-43404 [AIAA PAPER 87-1514] p 626 A87-43038 ASHWORTH, J. BASQUES, ERIC ADIBHATLA, SHRIDER Comparisons of unsteady flow fields about straight and Technological change and skill requirements - A case Performance seeking control for cruise optimization in swept wings using flow visualization and hotwire study of numerically controlled riveting in commercial fighter aircraft anemometry aircraft manufacture [AIAA PAPER 87-1929] p 681 A87.45397 [AIAA PAPER 87-1334] p 631 A87-44932 [ASME PAPER 86-WA/TS-2] p 623 A87-43723 ADLER, D. AZUMA, AKIRA BAUDIN, G. Development of a laser interferometric system for Study of the dynamic response of helicopters to a large Crack growth prediction in 3D structures under velocity measurements inside a transonic axial flow airplane wake p 678 A87-43429 aeronautical-type spectrum Ioadings compressor stage p 698 A87-46244 AZZAM, H. [ONERA, TP NO. 1987-79] p 691 A87-46772 ADOLPH, CHARLES E. Investigation of helicopter twin-rotor characteristics BAUER, J. The Air Force Flight Test Center - Now and the future p 628 A87-43438 Effects of impact loading on carbon fiber reinforced p 684 A87-45125 An improved assumed mode method for estimating the structures AGNES, A. motion of a nonuniform rotor blade p 653 A87-43445 [MBB-Z-83/86] p 691 N87-25436 A new simulation of airfoil dynamic stall due to velocity BAVUSO, SALVATORE J. and incidence fluctuations B Analysis of typical fault-tolerant architectures using [AIAA PAPER 87.1242] p 630 A87-44915 HARP p 704 A87-45771 AGNEW, B. BECHTA DUGAN, JOANNE BAARSPUL, M. Tip clearance flows. I - Experimental investigation of Analysis of typical fault-tolerant architectures using Some fundamentals of simulator cockpit motion an isolated rotor. II - Study of various models and HARP p 704 A87-45771 comparison with test results p 638 A87-46208 generation p 683 A87-44714 BECKER, A. AGRAWAL, D. P. BABIKIAN, D. S. Integrated navigation, communication and surveillance Effect of swirl on the performance of a radial vaneless Volume interchange factors for hypersonic vehicle wake systems based on standard distance measuring radiation diffuser with compressible flow at Mach numbers of 0.7 equipment p 649 A87-44039 [AIAA PAPER 87-1520] p 707 A87-43044 and 0.8 BELL, B. [ASME PAPER 86-WA/FE-6] p 629 A87-43704 BAEUMKER, M. Corrosion protection p 624 A87-44750 AHMAD, J. Autonomous navigation system for the new generation BENEK, J. A. Vortex breakdown simulation of military helicopters and associated flight tests Experience with 3-D composite grids [AIAA PAPER 87-1343] p 632 A87-44934 p 648 A87-43469 p 706 N87-26021 AHUJA, K. K. BAILEY, J. EARL BENNIGHOF, JEFFREY K. Computational aeroacoustics as applied to the diffraction Helicopter-V/STOL dynamic windand turbulence design Component mode iteration for frequency calculations of sound by cylindrical bodies p 707 A87-43383 methodology p 658 N87-25284 [AIAA PAPER 86-1023] p 704 A87-43388

B-1 BERFRANZ, RUDOLF PERSONAL AUTHOR INDEX

BERFRANZ, RUDOLF BLENKINSOP, P. A. BROWN, W. H. Automated systems for the manufacture of Airbus High temperature titanium alloys p 689 A87-44739 Computational aeroacoustics as applied to the diffraction vertical stabilizers BLEVlNS, G. of sound by cylindrical bodies p 707 A87-43383 [MBB-UT-17-86] p 705 N87-25786 Variable cycle concepts for high Mach applications BROWNRIDGE, C. BERG, DONALD F. [AIAA PAPER 87-2103] p 672 A87-45408 Designing for fretting fatigue free joints in turboprop Performance seeking control for cruise optimization in BODAPATI, S. engine gearboxes fighter aircraft Flow-field measurements of an airfoil with a deflected [AIAA PAPER 87-2046] p 671 A87-45378 ]AIAA PAPER 87-1929j p 681 A8/-45307 spoiler using an LDV system BRUECKNER, FRANK P. BERGEn, BRETT [AIAA PAPER 87-1438] p 634 A87-44955 Finite element analysis and redesign of jet engine starter Contingency power for small turboshaft engines using breech chamber BOELCS, A. [ASME PAPER 86-WA/DE-20] p 664 A87-43702 water injection into turbine cooling air Aeroetasticity in turbomachines comparison of BRUEGGEN, J. [AIAA PAPER 87-1906] p 668 A87-45289 theoretical and experimental cascade results. Appendix BERNDT, DAVID E. A5: All experimental and theoretical results for the 9 Fuel saving and fuel related subjects within an airline's STOL characteristics of a tactical aircraft with thrust standard configurations operational environment vectoring nozzles [AD-A180534] p 677 N87-25326 [ETN-87-90148] p 648 N87-26034 [AIAA PAPER 87-1835] p 655 A87-45237 BRUN, G. BOGAR, T. J. BERRIER, BOBBY L. Numerical simulation of diffusor/combustor dome Numerical simulation and comparison with experiment Static investigation of post-exit vanes for multiaxis thrust interaction p 676 A87-46255 for self-excited Oscillations in a diffuser flow vectoring BRUN, S. p 693 A87-43381 [AIAA PAPER 87-1834] p 667 A87-45236 Trends in the aeroelastic analysis of combat aircraft BERRY, JOHN D. BOIKO, L. G. p 657 A87-46362 Rotor design for maneuver performance Effect of fabrication-related deviations of the geometrical BRUTON, WILLIAM M. p 652 A87-43431 parameters of blade profiles on flow in a compressor Advanced detection, isolation and accommodation of BERRY, S. A. p 629 A87-43603 sensor failures: Real-time evaluation A unique measurement technique to study BOREI-rl, A. [NASA-TP-2740] p 682 N87-2533t laminar-separation bubble characteristics on an airfoil An improved approach for transonic flow BUCKNELL, R. L. [AIAA PAPER 87-t271] p 631 A87-44921 p 639 A87-46215 STOVL engine/airframe integration BESTMAN, A. R. BOUDREAU, A. H. [AIAA PAPER 87-1711] p 655 A87-45158 Natural convection flow of a radiating rarefied gas Ground testing facilities requirements for hypersonic BUlSKIKH, K. P. between concentric rotating spheres propulsion development A study of the thermal-strass state of gas turbine engine [AIAA PAPER 87-1523] p 693 A87-43046 [AIAA PAPER 87-1884] p 684 A87-45276 blades with protective coatings p 664 A87-43640 BETZlNA, MARK D. BOURNE, SIMON M. BUONTEMPO, V. Performance and loads data from a hover test of a Study of helicopterroll control effectiveness criteria Standardization and logistic support cost effectiveness 0.658-scale V-22 rotor and wing [NASA-CR-177404] p 681 N87-25330 of advanced avionics systems p 661 A87-43468 [NASA-TM-89419] p 642 N87-25296 BOUSQUET, J. M. BURKHARD, ALAN H. BHARADVAJ, B. K. Study of the aerodynamics of high-speed propellers Culprits causing avionic equipment failures A unified approach for potential and viscous free-wake [ONERA, TP NO. 1987-61] p 640 A87-46761 p 662 A87-46727 analysis of helicopter rotors p 627 A87-43412 BOUWER, G. BUSH, R. H. BHATELEY, I. C. Realization and flight testing of a model following control Two-dimensional numerical analysis for inlets at Computational fluid dynamics: Transition to design system for helicopters p 679 A87-43440 subsonic through hypersonic speeds applications p 700 N87-26004 [AIAA PAPER 87-1751] p 634 A87-45184 BOWLES, JEFFREY V. BIELAWA, RICHARD L. Calculated performance, stability, and maneuverability BUSHNELL, D. M. Validation of a method for air resonance testing of of high-speed tilting-prop-rotor aircraft A mixing augmentation technique for hypervelocity helicopters at model scale using active control of Pylon p 651 A87-43408 scram jets dynamic characteristics p 683 A87-43462 [AIAA PAPER 87-1882] p 668 A87-45275 BIESIADNY, THOMAS J. BOWLES, R. L. BUSKIK, L. N. Contingency power for small turboshaft engines using Maximum survival capability of an aircraft in a severe Investigation of flow structure in a compressor with two water injection into turbine cooling air windshear p 680 A87-44254 typos of guides p 629 A87-43604 [AIAA PAPER 87-1906] p 668 A87-45289 BOWLES, ROLAND L. BIMMORIA, KARL D. Wind Shear/Turbulence Inputs to Flight Simulation and BUSQUETS, ANTHONY M. Auxilian/data input device Singular trajectories in airplane cruise-dash Systems Certification [NASA-CASE-LAR-13626-1] p 700 N87-25584 optimization [NASA-CP-2474] p 625 N87-25267 [NASA-CR-180636] p 659 N87-26035 Wind shear and turbulence simulation BUSSING, THOMAS R. A. BILLIG, F. S. p 703 N87-25274 An improved computational model for a scramjet Studies of scramjet flowflelds BOXWELL, D. A. propulsion system [AIAA PAPER 87-2078] p 671 A87-45393 [AIAA PAPER 87-2161] p 688 A87-45443 A comparison of the acoustic and aerodynamic BILLIG, FREDERICK S. measurements of a model rotor tested in two anechoic Force accounting for airframe integrated engines wind tunnels p 683 A87-43425 C [AIAA PAPER 87-1965] p 636 A87-45334 BRADLEY, MARTY K. International Symposium on Air Breathing Engines, 8th, Advanced fighter thrust reverser integration for minimum Cincinnati, OH, June 14-19, 1987, Proceedings landing distance CAHILL, M. J. p 673 A87-46176 [AIAA PAPER 87-1923] p 655 A87-45302 Development of Digital Engine Control System for the Efficiency parameters for inlets operating at hypersonic BRADLEY, R. G. Harrier II speeds p 638 A87-46189 Computational fluid dynamics: Transition to design [AIAA PAPER 87-2184] p 673 A87-45458 BINDOLINO, GIAMPIERO applications p 700 N87-26004 CALMS, C. L. Aeroelastic derivatives as a sensitivity analysis of BRAEUNLING, W. Engine maintenance improvement considerations nonlinear equations p 699 A87-46797 Flow phenomena in transonic turbine cascades detailed [AIAA PAPER 87-1716] p 624 A87-45159 BINGHAM, GENE J. experimental and numerical investigation CALLOWAY, RAYMOND S. Optimization methods applied to the aerodynamic design p 639 A87-46223 Crash response data system for the controlled impact of helicopter rotor blades BRANDON, JAY M. demonstration (CID) of a full scale transport aircraft [NASA-TM-89155] p 660 N87-26042 On the nonlinear aerodynamic and stability p 694 A87-45123 BINION, TRAVIS characteristics of a generic chine-forebody slender-wing CAMP, DENNIS Wo Integration of propulsion/integration test results through fighter configuration R-57B gust gradient program p 657 N87-25276 the use of reference plane transfers [NASA-TM-89447] p 643 N87-25305 CAPBERN, Po ]AIAA PAPER 87-1964] p 670 A87-45333 BRAUN, DIETER Validation of aerodynamic measurement techniques and BIn, GUNJIT SlNGH FEL - A new main rotor system p 651 A67-43402 calculation methods for high-lift systems Helicopter response to an airplanes's vortex wake BRAY, RICHARD S. p 640 A87-46363 p 678 A87-43430 Application of data to piloted simulators CAPONE, F. J. p 687 N87-25275 Gust response of helicopters p 682 N87-26049 Parametric study of single expansion ramp nozzles at BREKHOV, A. F. BIRCH, STANLEY F. subsonic/transonic speeds Investigation of flow structure in a compressor with two Aero-optical analysis of compressible flow over an open [AIAA PAPER 87-1836] p 635 A87-45238 types of guides p 629 A87-43604 cavity CARACENA, FERNANDO BRENNEIS, H. [AIAA PAPER 87-1399] p 632 A87-44943 Analysis of a microburst in the FACE meteorological Design of a composite tail for the Airbus A-320 BLACK, C. G. mesonetwork in southern Florida p 702 A87-45962 [MBB-UT-12-86] p 658 N87-25316 Experience with frequency-domain methods in BROOKS, THOMAS F. CARADONNA, F. X. helicopter system identification p 680 A87-43457 Effect of signal jitter on the spectrum of rotor impulsive Full potential modeling of blade-vortex interactions BLACKALL, D. W. noise p 627 A87-43417 Icing clearances on civil helicopters - Unheated and [NASA-TM-100477] p 708 N87-25827 CARL, UDO heated blades p 646 A87-44707 BROWN, JEFFREY J. Conceptual studies of control systems for wings with BLACKWELDER, nON F. Navier-Stokes analysis of a very-high-bypass-ratio variable camber Control of the discrete vortices from a delta wing turbofan engine in reverse thrust [MBB-UT-221/86] p 682 N87-26836 p 641 A87-46779 [AIAA PAPER 87-2170] p 697 A87-45450 CARLSON, JOHN R. BLAKE, WILLIAM B. BROWN, P. C. Integration effects of pylon geometry and rearward F-t5 SMTD hot gas ingestion wind tunnel test results Results of acoustic tests of a Prop-Fan model mounted nacelles for a high-wing transport [AIAA PAPER 87-1922] p 669 A87-45301 ]AIAA PAPER 87-1894] p 707 A87-45282 [AIAA PAPER 87-1920] p 655 A87-45300

B-2 PERSONAL AUTHOR INDEX DEGENER, M.

CARONI, L CHITSAZ-Z, M. R. COVELL, PETER F. Composite vital parts optimisation for EH 101 rotor Factors affecting the sticking of insects on modified Molecular flow velocity using Doppler shifted Raman hub p 653 A87-43451 aircraft wings spectroscopy CARR, LAWRENCE W. [NASA-CR-180957] p 659 N87-26037 [AIAA PAPER 87-1531] p 693 A87-43053 Unsteady separation characteristics of airfoils operating CHOI, D. COWAN, CURTIS under dynamic stall conditions p 628 A87-43421 Development of a viscous cascade code based on scalar Measurement of side forces of a H-force rotor CARROTTE, J. F. implicit factorization p 651 A87-43410 The influence of dilution hole aerodynamics on the [AIAA PAPER 87-2150] p 637 A87-45435 CRAIG, ANTHONY P. temperature distribution in a combustor dilution zone CHOPRA, INDERJIT An experimental low Reynolds number comparison of [AIAA PAPER 87-1827] p 666 A87-45232 Helicopter response to an airplanes's vortex wake a Worfmann FX67-K170 airfoil, a NACA 0012 airfoil and CARRUTHERS, W. D. p 678 A87-43430 a NACA 64-210 airfoil in simulated heavy rain Durability characterization of ceramic materials for gas Aeroelastic stability of a bearingless circulation control [NASA-CR-181119] p 644 N87-25997 turbines p 690 A87-45898 rotor in forward flight p 652 A87-43443 CROSS, M. A. CHOU, DAVID C. CARVER, J. A. Application of computational fluid dynamics to analysis Forced unsteady vortex flows driven by pitching Development of Digital Engine Control System for the of exhaust gas/diffuser interactions in a turbine engine airfoils Harrier II altitude test cell [AIAA PAPER 87-1331] p 631 A87-44931 [AIAA PAPER 87-2184] p 673 A87*45458 [AIAA PAPER 57-2014] p 670 A87-45354 CHRISS, R. M. CASASENT, DAVID CUCINELLI, G. An LDA investigation of three-dimensional normal Model-based knowledge-based optical processors A model test vehicle for hypersonic aerospace systems shock-boundary layer interactions in a corner p 707 A87-42736 development [AIAA PAPER 87-1369] p 632 A87-44938 CASSADY, PHILIP E. [MBS-UR-875/86] p 658 N87-25314 CHRISTIAN, T. F., JR. Aero-optical analysis of compressible flow over an open CULICK, F. E. C. Fatigue and fracture mechanics analysis of compression cavity Pressure oscillations and acoustic-entropy interactions loaded aircraft structure p 692 A87-42554 [AIAA PAPER 57-1399] p 632 A87-44943 in ramjet combustion chambers CHU, PETER YAOHWA CASTOR, JERE G. [AIAA PAPER 57-1872] p 668 A87-45267 Control of aircraft under severe wind shear conditions Compound cycle engine for helicopter application CUNNINGHAM, HERBERT J. p 682 N87-26050 [NASA.CR-175110] p677 N87-25323 Steady and unsteady aerodynamic forces from the CHUPP, R. E. CEBECl, T. SOUSSA surface-panel method for a fighter wing with tip Influence of vane/blade spacing and cold.gas injection Viscid/inviscid separated flows missile and comparison with experiment and PANAIR on vane and blade heat-flux distributions for the Teledyne [AD-A179858] p 699 N87-25536 [NASA-TP-2736] p 645 N87-26032 702 HP turbine stage CEBECI, TUNCER CURRY, C. E. [AIAA PAPER 87-1915] p 669 A87-45295 Unsteady separation characteristics of airfoils operating Engine maintenance improvement considerations CLARK, DAVID A. under dynamic stall conditions p 628 A87-43421 [AIAA PAPER 57-1716] p 624 A87-45159 Contingency power for small turboshaft engines using CELIBERTI, L. A. CURTISS, H. C., JR. Micro-computer/parallel processing for real time testing water injection into turbine cooling air Stability and control modelling p 678 A87.43428 [AIAA PAPER 87-1906] p 668 A87-45289 of gas turbine control systems CURTISS, HOWARD C., JR. CLARK, DAVID R. [AIAA PAPER 87-1926] p 669 A87-45304 Study of helicopterroll control effectiveness criteria The use of computer models in helicopter drag CERNANSKY, N. P. [NASA-CR-177404] p 681 N87-25330 prediction p 628 A87-43424 Degradation mechanisms of sulfur and nitrogen CUSIMANO, Log CLARK, R. W. containing compounds during thermal stability testing of History of wind shear turbulence models Viscid/inviscid separated flows model fuels p 703 N87-25269 [AD-A179858] p 699 N87-25536 [AIAA PAPER 87-2039] p 690 A87-45372 CUTHBERTSON, R. D. CLIFF, EUGENE M. CHADERJIAN, HEAL M. UDF/727 flight test program Singular trajectories in airplane cruise-dash Simulation of transonic viscous flow over a fighter-like [AIAA PAPER 87-1733] p 666 A87-45171 optimization configuration including inlet CYRUS, J. D. [NASA-CR-180636] p 659 N87-26035 [AIAA PAPER 87-1199] p 630 A87-44906 Application of engine component life methodology to CLODS, BOR B. CHAKRAVARTHY, SUKUMAR life assessment p 698 A87-46230 The quality of radar data and its determination at the Development and application of unified algorithms for CZARNECKI, KRZYSZTOF radar installations of the Bundesenstalt fuer problems in computational science p 705 N87-26006 Classification of the load-carrying capacity of runway Flugsicherung p 650 A87-45878 CHANDRASEKARAN, M. surfaces by the ACN-PCN method. I COAKLEY, T. J. Stress analysis and optimisation of turbine rotor blade p 686 A87-46353 Numerical simulation and comparison with experiment shrouds p 699 A87-46250 Classification of the toad-carrying capacity of runway for self-excited Oscillations in a diffuser flow CHANET, P. surfaces by the ACN-PCN method. II p 693 A87-43381 Project for an intelligent system for on-line trouble p 686 A87-46354 shooting p 705 A87-46365 COAKLEY, THOMAS J. CHANG, JAMES B. An experimental investigation of a supercritical airfoil Fatigue crack growth predictions of welded aircraft at transonic speeds D structures containing flaws in the residual stress field [AIAA PAPER 87-1241] p 630 A87-44914 p 692 A87-42853 CODDING, W. H. DAILY, JOHN W. CHANG, K. C. Aerodynamic design modification of a hypersonic wind Vortex-nozzle interactions in ramjet combustors Viscid/inviscid separated flows tunnel nozzle by CSCM with high order accuracy (AIAA PAPER 87-1871} p 668 A87-45266 [AD-A179858] p 699 N87-25536 [AIAA PAPER 87-1896] p 635 A87-45284 DALEY, DANIEL H. CHANG, REH-LIANG COFFMAN, H. J., JR. Aircraft engine design p 673 A87-45875 The influence of the induced velocity distribution and Helicopter rotor icing protection methods DAMMEL, UWE the flapping-lagging coupling on the derivatives of the rotor p 654 A87-44256 Advances in technology for low cost turbomachinery - and the stability of the helicopter p 679 A87-43436 COHEN, R. S. A potential to enhance the economy of future propulsion CHAPMAN, D. C. Degradation mechanisms of sulfur and nitrogen system for general and helicopter aviation Preparing a propfan propulsion system for flight test containing compounds during thermal stability testing of p 676 A87-46261 [AIAA PAPER 87-1731 ] p 665 A87-45170 model fuels DANESI, A. CHARLTON, M. T. [AIAA PAPER 87-2039] p 690 A87-45372 Helicopter model in flight identification by a real time Observations of pilot control strategy in low level COLLIER, F. S., JR. self adaptive digital process p 680 A87-43458 helicopter flying tasks p 678 A87-43433 Stationary disturbances in three-dimensional boundary DANILUCK, J. V. CHATTOPADHYAY, ADITI layers over concave surfaces Digital control development for the T56-A-427 Optimum design of a helicopter rotor blade [AIAA PAPER 87-1412] p 632 A87-44945 [AIAA PAPER 87-2013] p 670 A87-45353 p 651 A87-43406 COMPTON, MICHAEL DAD, SAMUEL C. CHAUSSEE, DENNY S. Exploratory evaluation of a moving-model technique for Navier-Stokes simulation of a hypersonic generic Navier-Stokes simulation of a hypersonic generic measurement of dynamic ground effects wing/fuselage wing/fuselage [AIAA PAPER 87-1924] p 685 A87-45303 [AIAA PAPER 87-1192] p 629 A87-44902 [AIAA PAPER 87-1192] p 629 A87-44902 COMPTON, MIKE DAVlNO, RONALD M. CHEATWOOD, F. MCNEIL Investigation of a delta-wing fighter model flow field at Flight test and evaluation of propulsion system An interactive approach to surface-fitting complex transonic speeds operability characteristics geometries for flowfield applications [AIAA PAPER 87-1749] p 634 A87-45152 [AIAA PAPER 87-2092] p 656 A87-45400 [AIAA PAPER 87-1476] p 625 A87-43009 COOPERRIDER, N. K. DAVIS, J. M. CHEN, S. H. Complex modal balancing of flexible rotors including Transient test system design for the T800-APW-800 A panel method for counter rotating propfans residual bow turboshaft engine [AIAA PAPER 87-1890] p 668 A87-45279 [AIAA PAPER 87-1840] p 695 A87-45241 {AIAA PAPER 87-1791] p 666 A87-45205 CHENEY, HAROLD K. COUGNENC, FRANCIS DAVIS, M. W., JR. Onboard instrumentation for flight test takeoff Air conditioning systems for helicopters A stage-by-stage post-stall compression system performance p 662 A87-45126 p 654 A87-43473 modeling technique CHI, RAY M. COUPRY, G. [AIAA PAPER 87-2088] p 636 A87-45397 A noninterference blade vibration measurement system Statistical distribution of extreme atmospheric DAVIS, RANDALL C. for gas turbine engines turbulences Truss-core corrugation for compression loads [AIAA PAPER 57-1758] p 695 A87-45186 [ONERA, TP NO. 1987-56] p 702 A87-46757 [NASA-CASE-LAR-13438-1] p 699 N87-25496 CHILDRE, MARK T. COUPRY, GABRIEL DEGENER, M. Flight test of the FlO0-PW-220 engine in the F-16 Extreme atmospheric turbulence Canard configurations [AIAA PAPER 87-1845] p 667 A87-45245 [ONERA, TP NO. 1987-8] p 680 A87-44328 [ETN-87-99914] p 659 N87-26039

B-3 DEHOFF, R. L. PERSONAL AUTHOR INDEX

DEHOFF, R. L. E A new simulation of airfoil dynamic stall due to velocity XMAN - A tool for automated jet engine diagnostics and incidence fluctuations [AIAA PAPER 87-1931] p 696 A87-45309 EBERLE, ALBRECHT [AIAA PAPER 87-1242] p 630 A87-44915 DEJARNE'FTE, FRED R. Euler solution for a complete fighter aircraft at sub- and Aerodynamic study of a helicopter rotor in hovering flight An interactive approach to surface-fitting complex supersonic speed - Theory vs. experiment p 641 A87-47014 geometries for flowfield applications [MBB-LKE-122-S/PUB/234] p 660 N87-26833 FEAR, J. S. NASA/GE advanced low emissions combustor [AIAA PAPER 87-1476] p 625 A87-43009 EDWARDS, D. K. DELAAT, JOHN C. Volume interchange factors for hypersonic vehicle wake program Advanced detection, isolation and accommodation of radiation [AIAA PAPER 87-2035] p 671 A87-45369 sensor failures: Real-time evaluation [AIAA PAPER 87-1520] p 707 A87-43044 FELDMANN, ROBERT J. Airborne laser communications scintillation [NASA-TP-2740] p 682 N87-25331 EGGERS, JAMES M. DEMEIS, RICHARD measurements p 649 A87-45722 Design and evaluation of a new injector configuration Aircraft skin that bruises p 691 A87-46874 FELIClANI, F. for supersonic combustion p674 A87-46218 DEMMEL, JOHANN Helicopter model in flight identification by a real time EISS, N. S. Experiences with hot-wire instruments for the self adaptive digital process p 680 A87-43458 Factors affecting the sticking of insects on modified measurement of the liquid water content in clouds FELKER, FORT F. aircraft wings [DFVLR-MITT-86] p 704 N87-26476 Performance and loads data from a hover test of a [NASA-CR-t809571 p 659 N87-26037 DENYER, ANTHONY G. 0.658-scale V-22 rotor and wing Aircraft structural maintenance recommendations based EKSTEDT, E. E. [NASA-TM-894191 p 642 N87-25296 on fracture mechanics analysis p 623 A87-42857 NASA/GE advanced low emissions combustor FERMAN, M. A. DERON, RUY program Fatigue life analysis of fuel tank skins under combined Wind tunnel experimental study of optical beam [AIAA PAPER 87-2035] p 671 A87-45369 loads p 650 A87-42856 degradation through heterogeneous aerodynamic flows ELDER, R. L FERRIS, JAMES C. [ONERA, TP NO. 1987-50] p 707 A87-46753 Tip clearance flows. I - Experimental investigation of Low-speed wind-tunnel results for symmetrical NASA DESAULTY, M. an isolated rotor. II - Study of various models and LS( 1)-0013 airfoil Numerical simulation of diffusor/combustor dome comparison with test results p 638 A87-46208 [NASA-TM-4003] p 645 N87-26033 interaction p 676 A87-46255 ELLIOTT, DONALD W. FIGLER, BURTON D. DIETRICHS, H._. Impact of engine technology on supersonic STOVL Portable fuel leak detector Flow phenomena in transonic turbine cascades detailed [AIAA PAPER 87-17091 p 665 A87-45157 [AD-A180095] p 700 N87-25550 experimental and numerical investigation ELLIS, S. C. FILIMOSHIN, VLADIMIR GEORGIEVlCH p 639 A87-46223 Prediction of blade airloads in hovering and forward flight Electrochemical machining processes in aircraft engine DIMOTAKIS, PAUL E. using free wakes p 651 A87-43411 building p 693 A87-42905 A simple model for finite chemical kinetics analysis of ELMORE, KIMBERLY L FISCHER, J.D. supersonic turbulent shear layer combustion JAWS multiple Doppler derived winds An experimental investigation of turbine case [AIAA PAPER 87-18791 p 696 A87-45273 treatments p 703 N87-25271 DISKIN, GLENN S. ENDOGUR, ASKOL'D IVANOVICH [AIAA PAPER 87-1919] p 669 A87-45299 Effects of scale on supersonic combustor FISHER, V. A. Honeycomb structures: Parameter selection and performance design p 693 A87-42914 Integration of engine/aircraft control - 'How far is it [AIAA PAPER 87-2164] p 672 A87-45444 ERICKSON, GARY E. sensible to 9o' p 674 A87-46226 DOBRIAKOV, V. V. FLATHERS, M. B. Experimental study of the vortex flow behavior on a Engineering and cost principles for increasing the generic fighter wing at subsonic and transonic speeds The design of low-stress/high performance centrifugal production efficiency and maintainability of aircraft [AIAA PAPER 87-1262] p 631 A87-44920 impellers engines p 664 A87-43620 [AIAA PAPER 87-2099] p 697 A87-45405 On the nonlinear aerodynamic and stability DOBROWOLSKI, R. FLEETER, SANFORD characteristics of a generic chine-forebody slender-wing Development of low-cost test techniques for advancing Aaroelastic control of stability and forced response of fighter configuration film cooling technology supersonic rotors by aerodynamic detuning [NASA-TM-89447] p 643 N87-25305 [AIAA PAPER 87-1913] p 696 A87-45293 p 676 A87-46249 ERLEBACHER, GORDON DOEKER, H. FLORES, JOLEN Stability and transition in supersonic boundary layers Canard configurations Advances in the computation of transonic separated [AIAA PAPER 87-1416] p 632 A87-44947 [ETN-87-99914] p 659 N87-26039 flows over finite wings ERSHOV, V. N. DOGRA, VIRENDRA K. [AIAA PAPER 87-1195] p 630 A87-44904 Effect of fabrication-related deviations of the geometrical Direct simulation of aerothermal loads for an aeroassist Simulation of transonic viscous flow over a fighter-like parameters of blade profiles on flow in a compressor flight experiment vehicle configuration including inlet p 629 A87-43603 [AIAA PAPER 87-1546] p 626 A87-43063 [AIAA PAPER 87-1199] p 630 A87-44906 ESCH, HELMUT DOLZINSKI, WOLF-DIETRICH FLOYD, M. A. The 0.6 m x 0.6 m trisonic section (TMK) of DFVLR in Development and testing of critical components for the Scan stabilization and jitter control for an airborne Cologne-Porz, West Germany technological preparation on an Airbus fuselage made of telescope p 660 A87-42812 [DFVLR-MITT-86-21] p 687 N87-26053 carbon fiber reinforced plastics, phase 1 FOREMAN, M. J. EVANS, G. B. [BMFT-FB-W-86-017] p 692 N87-26151 Flow-field measurements of an airfoil with a deflected Materials for structures of the future DOMINY, J. spoiler using an LDV system p 689 A87-44745 Transmission efficiency in advanced aerospace [AIAA PAPER 87-1438] p 634 A87-44955 EVERSMAN, W. powerplant FORNELL, PETER A comparison of the structurebome and airborne paths [AIAA PAPER 87-20431 p 671 A87-45376 Development and testing of critical components for the for propfan interior noise DONE, G. T. S. technological preparation on an Airbus fuselage made of [NASA-CR-1802891 p 708 N87-26612 Helicopter vibration control: Recent advances EWALD, J. carbon fiber reinforced plastics, phase 1 p 660 N87-26247 Investigation of ground and air resonance using a [BMFT-FB-W-86-017] p 692 N87-26151 FORRESTER, DAVID A. DONEGAN, T. L combination of multiblade coordinates and Floquet Where and when helicopter icing occurs Experience with 3-D composite grids theory p 653 A87-43444 p 702 A87-44702 p 706 N87-26021 EXTON, REGINALD J. FORSTER, HANS DONOHIE, H. G. Molecular flow velocity using Doppler shifted Raman A conformal aircraft phased array antenna for T700/CT7 derivative growth engine reliability - spectroscopy airplane-satellite communication in the L band Consistent with longstanding industry traditions [AIAA PAPER 87-t531] p 693 A87-43053 p 663 A87-43464 [DFVLR-FB-86-47] p 701 N87-26259 FOUQUES, B. DOST, KARL-HEINZ F Irish Dauphin helicopter S.A.R. system flight tests Technological aspects in prepadng the development of p 648 A87-43455 regional airliners p 657 A87-46327 FOURMAUX, ANTOINE DRAGO, RAYMOND J. FACEY, JOHN R. Civil propulsion technology for the next twenty-five Numerical simulation of flows in axial and radial Development of a large, spiral bevel gear rotorcraft transmission years p 624 A87-46177 turbomachines using Euler solvers [ONERA, TP NO. 1987-87] p 641 A87-46776 [AIAA PAPER 87-1839] p 667 A87-45240 FALENI, JEAN-PIERRE Wind tunnel experimental study of optical beam FOURNIER, F. DREES, J. M. degradation through heterogeneous aerodynamic flows An analysis of in-fin tail rotor noise Expanding tilt rotor capabilities p 651 A87-43407 [ONERA, TP NO. 1987-50] p 707 A87-46753 p 652 A87-43427 DUNN, M. G. FARIOLI, M. FOURNIER, J.-P. Influence of vane/blade spacing and cold-gas injection Composite vital parts optimisation for EH 101 rotor Project for an intelligent system for on-line trouble on vane and blade heat-flux distributions for the Teledyne hub p 653 A87-43451 shooting p 705 A87-46365 702 HP turbine stage FARLEY, GARY L. FRADIN, CH. [AIAA PAPER 87-1915] p 669 A87-45295 Integrally-stiffened crash energy-absorbing subfloor Investigation of the three dimensional flow near the exit DVORAK, S. D. beam structure of two backswept transonic centrifugal impellers Dynamic data acquisition, reduction, and analysis for [NASA.CASE-LAR-13697-1] p 659 N87-25321 p 638 A97-46192 the identification of high-speed compressor component FARRANDO, A. FRANSSON, T. H. post-stability characteristics Helicopter turboshaft engine acoustic and infrared Aeroelasticity in turbomachines comparison of [AIAA PAPER 87-2089] p 697 A87-45398 studies and tests p 663 A87-43467 theoretical and experimental cascade results, Appendix DWOYER, DOUGLAS L FAVIER, D. A5: All experimental and theoretical results for the 9 Computational analysis of hypersonic airbreathing A prescribed radial distribution circulation of a hovering standard configurations aircraft flow fields p 645 N87-26019 rotor blade p 627 A87-43414 [AD-At80534] p 677 N87-25326

B-4 PERSONAL AUTHOR INDEX HARRIS, ROBERT W.

FRANZ, JOSEPH J. GEIDEL, H. A. GUPTA, A. K. Performance estimation of an aircraft internal Improved agility for modern fighter aircraft. II - Thrust NO(x) reduction and combustion phenomena in the combustion engine vectoring engine nozzles p 673 A87-46181 multi-annular gas turbine swirl burner [AIAA PAPER 67-2173] p 672 A87-45453 GEISSLER, WOLFGANG [AIAA PAPER 87-2036] p 671 A87-45370 FRAY, KEITH W. Unsteady separation characteristics of airfoils operating GUY, ROBERT W. New standards established for realism in visual under dynamic stall conditions p 628 A87-43421 Test flow calibration study of the Langley Arc-Heated GENT, R. W. simulation p 686 A87-46438 Scramjet Test Facility FRENSTER, J. A. Rotor icing research at RAE Farnborough [AIAA PAPER 87-2165] p 685 A87-45445 XMAN - A tool for automated jet engine diagnostics p 648 A87-44706 [AIAA PAPER 87-1931] p 696 A87-45309 GENTILE, ANTHONY J. FREUDENBERG, T. Development program of a full authority digital electronic H The mixing of jets under simulated engine-like control system for the T55-L-712E turboshaft engine p 663 A87-43465 turbulence p 698 A87-46231 HA, TRI T. GEORGE, M. W. FRIEDMANN, PERETZ P. Geostationary satellite navigation systems Application of computational physics within Northrop Recent trends in rotary-wing aeroelasticity p 648 A87-42786 p 652 A87-43442 p 706 N87-26008 GERASlMENKO, V. P. HADDAD, RAYMOND FRINK, NEAL 1". Approximation of the characteristics of the turbine of a Investigation of a delta-wing fighter model flow field at Subsonic wind-tunnel measurements of a slender transonic speeds gas turbine engine in a wide range of operating modes wing-body configuration employing a vortex flap [AIAA PAPER 87-1749] p 634 A87-45182 p 663 A87-43606 [NASA-TM-89101] p 642 N87-25295 GERBER, S. C. HAEFFELE, B. A. FROMMLET, HUBERT F-t5/F100 digital electronic engine control main fuel Two-dimensional numerical analysis for inlets at FEL - A new main rotor system p 651 A87-43402 gear pump field service evaluation subsonic through hypersonic speeds Development of novel bearingless rotor systems [AIAA PAPER 87-1846] p 667 A87.45246 [AIAA PAPER 87-1751] p 634 A87-45184 [MBB-UD-47t/86] p 702 N87-26837 GIBSON, R. F. HAFEZ, M. FROST, R. L. Dynamic mechanical properties of advanced composite Vortex breakdown simulation Rotor icing experience at Westland and its application materials and structures: A review p 691 N87-25988 [AIAA PAPER 87-1343] p 632 A87-44934 to current and future helicopters p 646 A87-44703 GILL, M. E. HAFTKA, RAPHAEL T. FROST, WALTER Performance prediction in a centrifugal compressor Interdisciplinary optimum design p 657 A87-47009 Wind Shear/Turbulence Inputs to Flight Simulation and impeller p 674 A87-46190 HAGSETH, PAUL E. Systems Certification GILLIAM, F. T. F-16 modular common inlet desigrl concept [NASA-CP-2474] p 625 N87-25267 Visualization of three-dimensional structures about a [AIAA PAPER 87-1748] p 666 A87-45181 Modeling and implementation of wind shear data pitching forward swept wing HAHN, M. p 709 N87-25273 [AIAA PAPER 87o1322] p 631 A87-44929 Design for repairability of helicopter rotor blades GIRODROUX-LAVIGNE, P. Turbulence models p 703 N87-25277 [MBB-UD-491/86] p 658 N87-25315 Unsteady viscous-inviscid interaction method and FU, J.-K. HAIGES, KARL R. computation of buffeting over airfoils Computation of unsteady transonic aerodynamics with Validation of an integrated flight and propulsion control [ONERA, TP NO. 1987-58] p 640 A87-46759 truncation error injection p 627 A87-43392 design for fighter aircraft GLENN, DENNIS E. FUJII, KOZO [AIAA PAPER 87-1928] p 680 A87-45306 Morphology of a standing oblique detonation wave Numerical simulation of vortical flows over a strake-delta HAKKINEN, R. J. [AIAA PAPER 87-1785] p 695 A87-45201 wing Computational fluid dynamics applications at McDonnel GLICKSTEIN, M. R. [AIAA PAPER 87-1229] p 630 A87-44913 Douglas p 701 N87-26007 Advancements in hydrogen expander airbreathing HALD, H. FULKER, J. L. engines Canard configurations The air-injection method of fixing boundary-layer [AIAA PAPER 87-2003] p 670 A87-45348 transition and investigating scale effects [ETN-87-99914] p 659 N87-26039 GLIDEWELL, RONALD J. HALL, JEFFERY L. p 639 A87-46264 STOL characteristics of a tactical aircraft with thrust A simple model for finite chemical kinetics analysis of FULTON, KEN vectoring nozzles supersonic turbulent shear layer combustion Countdown to the propfan p 664 A87-44272 [AIAA PAPER 87-1835] p 655 A87-45237 [AIAA PAPER 87-1879] p 696 A87-45273 FUNG, K.-Y. GNOFFO, PETER A. HALWES, DENNIS R. Computation of unsteady transonic aerodynamics with A computational study of the flowfield surrounding the Ground and flight test results of a total main rotor truncation error injection p 627 A87-43392 Aeroassist Flight Experiment vehicle isolation system [AIAA PAPER 87-1575] p 626 A87-43084 [NASA-CR-4082] p 643 N87-25302 G GOEKGOEL, O. HALYO, NESlM A310-300 CFRP fin Damage tolerance A combined stochastic feedforward and feedback control design methodology with application to autoland GAD-EL-HAK, MOHAMED demonstration p 655 A87-44594 design A310-300 CFRP fin damage tolerance demonstration Control of the discrete vortices from a delta wing [NASA-CR-4078] p 705 N87-25806 [MBB-UT-015/86] p 658 N87-25317 p 641 A87-46779 HAM, NORMAN D. GAJEWSKI, TADEUSZ GOULAS, A. Helicopter individual-blade-control research at MIT Changes in the free flow in the intake of a turbojet engine Performance prediction in a centrifugal compressor 1977-1985 p679 A87-43446 impeller p 674 A87.46190 during the aircraft takeoff run p 640 A87-46351 HAMALIAN, SETI K. GALBRAITH, A. MGD. GRABER, A. Liability of the United States government in cases of The effect of pitch rate on the dynamic stall or a modified A parametric investigation of a free wake analysis of air traffic controller negligence p 708 A87-42859 NACA 23012 aerofoil and comparison with the unmodified hovering rotors p 627 A87-43413 HAMED, A. case p 628 A87-43420 GRAHAM, ED J85 surge transient simulation p 675 A87-46240 GALBRAITH, R. A. MCD. Flight test and evaluation of propulsion system HAMILTON, H. HARRIS, II Description of, and preliminary results from, a new operability characteristics An interactive approach to surface-fitting complex blade-vortex interaction test facility p 683 A87-43460 [AIAA PAPER 87-2092] p 656 A87-45400 geometries for flowfield applications GALLINGTON, ROGER W. GRALLERT, H. [AIAA PAPER 87-1476] p 625 A87-43009 HALE thermal balance A model test vehicle for hypersonic aerospace systems HAMPTON, ROY W. [AIAA PAPER 87-2172] p 656 A87-45452 development Failure analysis of a large wind tunnel compressor GANZER, UWE [MBB-UR.875/86] p 658 N87-25314 blade p 692 A87-42852 Aircraft technologies of the nineties in MBB passenger GRANGIER, MARC HANAGUD, S. aircraft projects Proving that Avanti stands for progress Optimum design of a helicopter rotor blade [MBB-UT-21/86] p 625 N87-25291 p 656 A67-46314 p 651 A87-43406 Aircraft technology of the nineties in MBB passenger HAND, LAWRENCE A. aircraft projects GREEN, LAWRENCE L Transonic wall interference assessment and corrections An experimental investigation of a supercdtical airfoil [MBB-UT-0021/86] p 660 N87-26834 at transonic speeds GARClA-FRAILE, ANGEL for airfoil data from the 0.3-meter TCT adaptive wall test section [AIAA PAPER 87-1241] p 630 A87-44914 Spanish contribution to rotorcraft development - [AIAA PAPER 87-1431] p 633 A87-44953 HANSEN, J. L Homage to de la Cierva p 623 A87-43426 Rotor wake segment influence on stator-surface GARNER, H. DOUGLAS GREENE, FRANCIS A. boundary layer development in an axial*flow compressor Auxiliary data input device A computational study of the flowfield surrounding the stage [NASA-CASE-EAR-13626*1] p 700 N87-25584 Aeroassist Flight Experiment vehicle [AIAA PAPER 87-1741] p 695 A87-45178 GARTRELL, L R. [AIAA PAPER 87-1575] p626 A87-43084 HANSMAN, R. JOHN Designing transonic wind-tunnel test sections for flow GREGOREK, G. M. An experimental low Reynolds number comparison of Wind tunnel evaluation of a truncated NACA 64-621 diagnostics and laser velocimeter applications a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil and [AIAA PAPER 87-1434] p 684 A87-44954 air/oil for wind turbine applications a NACA 64-210 airfoil in simulated heavy rain GARY, SANJAY [NASA-CR.t80803] p 703 N87-25621 [NASA-CR-181119] p 644 N87-25997 Optimal cooperative control synthesis of active GRIGA, A. D. HANSMAN, R. JOHN, JR. displays The low-aspect-ratio parameter of blades Comparison of wet and dry growth in artificial and flight [NASA-CR-4058] p 705 N87-25807 p 663 A87-43607 icing conditions p 646 A87-45635 GAUBERT, MICHEL GUNNY, EDMOND R. HARRIS, ROBERT W. Correlation of SA349/2 helicopter flight-test data with Time modulation. II - Scheme codes avoidance UDF/727 flight test program a comprehensive rotorcraft model p 653 A87-43456 maneuvers for aircraft p 649 A87-44845 [AIAA PAPER 87-1733] p 666 A87-45171

B-5 PERSONAL AUTHOR INDEX HART-SMITH, L. J.

HART-SMITH, L. J. HOLLA, KLAUS HUYER, S. A decade of composite rudder service reviewed Use of artificial intelligence methods Comparisons of unsteady flow fields about straight and p 689 A87-44861 [MBB-LKE-434-S/PUB/284] p 707 N87-26831 swept wings using flow visualization and hotwire HARTSEL, J. HOLST, TERRY L. anemometry Variable cycle concepts for high Mach applications Numerical solution of the Navier-Stokes equations about [AIAA PAPER 87-1334] p 631 A87-44932 HYDE, J. C. [AIAA PAPER 87-2103] p 672 A87-45408 three-dimensional configurations: A survey HARTWlCH, PETER-MICHAEL p 701 N87-26022 Standing oblique detonation wave engine performance [AIAA PAPER 87-2002j p 670 A87-45347 Incompressible Navier-Stokes computations of vortical HOLT, D. flows over double-delta wings Materials in helicopters - A review [AIAA PAPER 87-1341 ] p 631 A87-44933 p 624 A87-44731 I HASSENPFLUG, W. HONG, CHANG-HO A new method of analytical evaluation of helicopter true Aeroelastic stability of a bearingless circulation control IANEVICH, V. N. airspeed p 661 A87-43439 rotor in forward flight p 652 A87-43443 Effect of fabrication-related deviations of the geometrical Autonomous navigation system for the new generation HOPKINS, HARRY parameters of blade profiles on flow in a compressor of military helicopters and associated flight tests Fokker 50 - Pedigree with power p 656 A87-45647 p 629 A87-43603 p 648 A87-43469 HOSMAN, R. J. A. W. IERUSALIMSKII, KONSTANTIN MOISEEVICH HASTINGS, DANIEL E. Some fundamentals of simulator cockpit motion Honeycomb structures: Parameter selection and The influence of flow n0n-uniformities in air-breathing generation p 683 A87-44714 design p 693 A87-42914 hypersonic propulsion systems HOSNY, W. M. INGELSPERGER, ANTON [AIAA PAPER 87-2079] p 636 A87-45394 Dynamic data acquisition, reduction, and analysis for Avionics systems for future civil helicopters HASWELL, M. R. the identification of high-speed compressor component [MBB-UD-473/86} p 662 N87-26838 Visual systems developments p 694 A87-44725 post-stability characteristics IVANOV, M. IA. HATCH, C. [AIAA PAPER 87-2089] p 697 A87-45398 Numerical simulation of transonic three-dimensional HOURMOUZlADIS, J. Determination of the structural properties of helicopter flows in turbine blade passages p 638 A87-46206 rotor blades by theoretical and experimental methods Flow phenomena in transonic turbine cascades detailed p 653 A87-43450 experimental and numerical investigation HATHAWAY, ROSS W. p 639 A87-46223 J Investigation of a delta-wing fighter model flow field at HOUSTON, S. S. transonic speeds Observations of pilot control strategy in low level JACKSON, L. ROBERT [AIAA PAPER 87-1749] p 634 A87-45182 helicopter flying tasks p 678 A87-43433 Truss-core corrugation for compression loads HAWLEY, ARTHUR V. HOWARD, IAN C. [NASA-CASE-LAR-13438-1] p 699 N87-25496 Fracture of an aircraft horizontal stabilizer A decade of composite rudder service reviewed JAIN, Y. P. p 689 A87-44861 p 650 A87-42855 A study o1 some factors affecting the performance of HEFFERNAN, RUTH M. HOWARD, JOHN D. a contra-rotating axial compressor stage Correlation of SA349/2 helicopter flight-test data with Testing automated ground collision avoidance systems p 639 A87-46211 a comprehensive rotorcraft model p 653 A87-43456 on the AFTI/F-16 p 660 A87-43375 JEANDEL, D. HEFFLEY, ROBERT K. HOWELL, G. A. Numerical simulation of diffusor/combustor dome Study of helicopterroll control effectiveness criteria Computational fluid dynamics: Transition to design interaction p 676 A87-46255 [NASA-CR-177404] p 681 N87-25330 applications p 700 N87-26004 JELLISON, T. G. HEISER, WILLIAM H. HOYNIAK, DANIEL XMAN - A tool for automated jet engine diagnostics Aircraft engine design p 673 A87-45875 Aeroelastic control of stability and forced response of [AIAA PAPER 87-1931] p 696 A87-45309 HELIN, HENRY ELMER supersonic rotors by aerodynamic detuning JEWEL JOSEPH W., JR. Experimental studies on the dynamic development and p 676 A87-46249 Flight duration, airspeed practices and altitude control of unsteady separated flows p 642 N87-25297 HSlEH, T. management of airplanes involved in the NASA VGH HENDRICKES, GAVIN J. Numerical simulation and comparison with experiment General Aviation Program Progress toward shock enhancement of supersonic for self-excited oscillations in a diffuser flow [NASA-TM-89074] p 625 N87-25293 combustion processes p 693 A87-43381 JIAN, SU [AIAA PAPER 87-1880] p 690 A87-45274 HSU, CHUNG-HAO Improvement of aerodynamic calculation on S(2]m HENNECKE, D. K. Incompressible Navier-Stokes computations of vortical stream surface of axial compressor by using of annulus The mixing of jets under simulated engine-like flows over double-delta wings wall boundary layer calculation p 639 A87-46216 turbulence p 698 A87-46231 [AIAA PAPER 87-1341] p 631 A87-44933 JOHNSON, D. C. HENRY, R. HUANG, X. Y. APU fuet efficiency and affordability for commercial Mechanical evaluation of the aeroelastic behaviour of Active control of aerofoil flutter p 681 A87-46792 aircraft a fan blade p 675 A87-46248 HUANG, YIYI [AIAA PAPER 87-1907] p 669 A87-45290 HERBST, W.-B. Development of experimental investigation on transonic JOHNSON, J. D. Thrust vectoring - Why and how? p 673 A87-46180 wind tunnel wall interference p 687 A87-46960 Design and test verification of a combustion system for HERMANNS, H. J. HUBER an advanced turbofan engine Wind determination from aircraft-movement data The role of simulation in helicopter development [AIAA PAPER 87-1826} p 666 A87-45231 p 702 A87-45892 [MBB-UD-435/86] p 687 N87-25333 JOHNSON, RICHARD A. HERRMANN, UDO HUBER, A. F., II Development and testing of critical components for the The effect of trip wire roughness on the performance Cycle selection considerations for high Mach technological preparation on an Airbus fuselage made of of the Wortmann FX 63-137 airfoil at low Reynolds applications [AIAA PAPER 87-2105] p 672 A87-45410 carbon fiber reinforced plastics, phase 1 numbers p 629 A87-44019 [BMFT-FB-W-86-017] p 692 N87-26151 HUBER, HELMUT JOHNSON, WAYNE HERTEL KLAUS The tilt-rotor aircraft - A response to the future? From Calculated performance, stability, and maneuverability Industrial application of computer aided structural European interrogations to Eurofar actions of high-speed tilting-prop-retor aircraft optimization in aircraft construction [MBB-UD-485-86-PUB] p 854 A87-43474 p 651 A87-43408 [MBB-UT-273/86] p 706 N87-26523 HUDSON, C. MICHAEL JONES, D. G. HESS, RONALD A. Case histories involving fatigue and fracture mechanics; Optical flow diagnostic measurements in Study of helicopterroII control effectiveness criteria Proceedings of the Symposium, Charleston, SC, Mar. 21, turbomachinery p 698 A87-46245 [NASA-CR-177404] p 681 N87-25330 22, 1985 p 692 A87-42851 JONES, DENISE R. HETZNER, W. HUGOUVIEUX, P. Survey of currently available high-resolution raster Radar requirements for future avionics systems Recent progress in the measurement of the drag graphics systems p 662 A87-45879 coefficients of models of transport aircraft in a wind [NASA-TM-89139] p 705 N87-25771 HILLARD, MERVIN E., JR. tunnel JONES, G. S. Molecular flow velocity using Doppler shifted Raman [NASA-TT-20096} p 644 N87-25306 Designing transonic wind-tunnel test sections for flow spectroscopy HUMMES, D. diagnostics and laser velocimeter applications [AIAA PAPER 87-1531] p 693 A87-43053 Observations ol pilot control strategy in low level [AIAA PAPER 87-1434] p 684 A87-44954 HINDSON, WILLIAM S. helicopter flying tasks p 678 A87-43433 JONES, H. E. Study of helicopterroII control effectiveness criteria HUMPHREY, JOSEPH W. Full potential modeling of blade-vortex interactions [NASA-CR-177404] p 681 N87-25330 Morphology o1 a standing oblique detonation wave p 627 A87-43417 HINES, SOB G. [AIAA PAPER 87-1785] p 695 A87-45201 JOg, WEN-HUEI Engine variable geometry effects on commercial Pressure oscillations and acoustic.entropy interactions Simulations of ramjet combustor flow fields. I - Numerical supersonic transport development in ramjet combustion chambers model, large-scale and mean motions [AIAA PAPER 87-2101] p 672 A87-45406 [AIAA PAPER 87-1872] p 668 A87-45267 [AIAA PAPER 87-1421] p 633 A87-44949 HINGST, W. R. HUSSAINI, M. Y. Simulations of ramjet combustor flow fields. II - Origin An LDA investigation of three-dimensional normal A mixing augmentation technique for hypervelocity of pressure oscillations shock-boundary layer interactions in a corner scram jets [AIAA PAPER 87-1422] p 633 A87-44950 [AIAA PAPER 87-1369] p 632 A87-44938 [AIAA PAPER 87-1882] p 668 A87-45275 HOFFMANN, HANS-EBERHARD HUSSAINI, M. YOUSUFF JUANARENA, DOUGLAS B. Experiences with hot-wire instruments for the Stability and transition in supersonic boundary layers A rugged electronic pressure scanner designed for turbine test p 895 A87-45124 measurement of the liquid water content in clouds [AIAA PAPER 87-1416] p 632 A87-44947 [DFVLR-MITT-86] p 704 N87-26476 HUSTAD, C. W. JUGGINS, P. T. W. HOGGE, THOMAS W. The use of discrete vortices to predict lift of a circulation Substantiation o1 the analytical prediction of ground and Auxiliary data input device control rotor section with a trailing edge blowing slot air resonance stability of a bearingless rotor, using model [ NASA-CASE-LAR-13626-1] p700 N87-25584 p 627 A87-43416 scale tests p 654 A87-43463

B-6 PERSONAL AUTHOR INDEX LECOINTE, Y.

JUNKER, B. KLEIN, STEVENS. KRUSE, JUERGEN Investigation of blade-vortices in the rotor-downwash A unique approach to aeroelastic testing of scaled An automated radar-signature measurement system p 627 A87-43415 rotors p 683 A87-43461 p 698 A87-45886 KLEINER, M. KUCHAR, A. P. Development of a laser interferometric system for Scale model test results ol a thrust reverser concept K velocity measurements inside a transonic axial flow for advanced multi-functional exhaust systems compressor stage p 698 A87-46244 [AIAA PAPER 87-1833] p 667 A87-45235 KALLAS, J. KLINGE, M. D. KUMAR, A. A method for the calculation of the interaclion of a Detaitod near-wake flowfield suweys with comparison A mixing augmentation technique for hypervelocity turbulent boundary layer with a shock wave to an Euler method of an aspect ratio 4 rectangular wing scramlets p 639 A87-46238 [NASA-TM-89357] p 644 N87-25993 [AIAA PAPER 87-1882] p 668 A87-45275 KNIGHT, C. J. KALLIS, JAMES M. KUMAR, AJAY Development of a viscous cascade code based on scalar Culprits causing avionic equipment failures Computational analysis of hypersonic airbreathing implicit factorization p 662 A87-46727 aircraft flow fields p 645 N87-26019 [AIAA PAPER 87-2150] p 637 A87-45435 KANAI, KIMIO KNIGHT, VERNIE H., JR, KUMAR, V. ARUN An approach to the synthesis of an adaptive flight control A study on the effect of non-dimensional system Crash response data system for the controlled impact system with incomplete information p 680 A87-45096 parameters on squeeze film damper performance using demonstration (CID) of a full scale transport aircraft Design of CCV flight control system of STOL flying experimental data p 698 A87-46229 p 694 A87-45123 boat p 680 A87-45097 KNOWLES, P. A. KUO, P. S. KARIMOV, AUBERT KHAMZOVICH Icing clearance criteria for UK military helicopters The design of low-stress/high performance centrifugal Electrochemical machining processes in aircraft engine p 646 A87-44705 impellers building p 693 A87-42905 KOBAYASHI, H. [AIAA PAPER 87-2099] p 697 A87-45405 KAS'IANOV, IU. O. Performance calculation of counter rotation propeller KURUVILA, G. Mathematical model for calculating the atomization of [AIAA PAPER 87-1889] p 635 A87-45278 Vortex breakdown simulation a liquid jet by an annular gas stream KOBAYASHI, HORISHI [AIAA PAPER 87-1343] p 632 A87-44934 p 693 A87-43610 Extension of local circulation method to counter rotation KAWACHI, KEIJI propeller Study of the dynamic response of helicopters to a large [AIAA PAPER 87-1891] p 635 A87-45280 L airplane wake p 678 A87-43429 KOHL, w. KAYNAK, UNVER Radar requirements for future avionics systems LABOURDETrE, R. Advances in the computation of transonic separated p 662 A87-45879 Crack growth prediction in 3D structures under flows over finite wings KOKKALIS, A. aeronautical-type spectrum Ioadings [AIAA PAPER 87-1195] p 630 A87-44904 Description of, and preliminary results from, a new [ONERA, TP NO. 1987-79] p 691 A87-46772 blade-vortex interaction test facility p 683 A87-43460 KAZA, K. R. V. LAMB, MILTON KOLAX, MICHAEL _nfluence ol third-degree geometric nonlinearities on the Integration effects of pylon geometry and rearward Development and testing of critical components for the vibration and stability of pretwisted, preconed, rotating mounted nacelles for a high-wing transport blades p 674 A87-46228 technological preparation on an Airbus fuselage made of [AIAA PAPER 87-1920] p 655 A87-45300 carbon fiber reinforced plastics, phase 1 KAZANSKII, V. G. LAMBERT, JEAN [BMFT-FB-W-86-017] p 692 N87-26151 Optimization of the duration ot ultrasonically activaled An airborne collision avoidance system - The TCAS KOURTIDES, D. A. impact surface treatment of gas-turbine-engine blades p 649 A87-44231 Thermal and flammability characterization of graphite p 663 A87-43609 LAMBERT, MARK composites p 688 A87-43398 KEEL, L C. Flying the CF-18 Hornet p 656 A87-46313 KOVAI.., L R. Ground testing facilities requirements for hypersonic LAN, C. EDWARD A comparison of the structureborne and airborne paths propulsion development An experimental investigation of dynamic ground for propfan interior noise [AIAA PAPER 87-1884] p 684 A87.45276 effect [NASA-CR-180289] p 708 N87-26612 [NASA-CR-180560] p 659 N87-26036 KEELER, R. J. KOVAL', V. A. An airborne laser air motion sensing system. I ° Concept Efficiency of the utilization of rotor blade shroud labyrinth LANDGREBE, ANTON J. and preliminary experiment p 662 A87-45732 seals in an axial-compressor stage with large radial Computational fluid dynamics research at the United KEITH, T. G., JR. clearances p 694 A87.43611 Technologies Research Center requiring An LDA investigation of three-dimensional normal KRANTZ, PER supercomputers p 701 N87-26011 shock-boundary layer interactions in a corner The Aeronautical Research Institue (FFA) wing body 85 LANDIS, K. K. [AIAA PAPER 87-1369] p 632 A87-44938 computer program. A panel method for determination of Development of low-cost test techniques for advancing KELLEY, HENRY L. aeroelastic characteristics applying direct block iterative film cooling technology Effect of planform taper on hover performance of an sotution technk:lues [AIAA PAPER 87-1913] p 696 A87-45293 advanced AH-64 model rotor [FFA-TN-1986-28] p 642 N87-25298 LANDRUM, D. B. [NASA-TM-89145] p 643 N87-25304 KRAUSPE Influence of a heated leading edge on boundary layer KELLY, H. NEALE The role of simulation in helicopter development growth, stability and transition Modification to the Langley 8-Foot High Temperature ]MBB-UD-435/86] p 687 N87-25333 [DE87-008516] p 700 N87-25538 Tunnel for hypersonic propulsion testing KRAVCHUK, L. V. LAPOTKO, V. M. [AIAA PAPER 87-1887] p 685 A87-45277 A study of the thermal-stress state of gas turbine engine Numerical study of the gasdynamic process in a pulsejet KEMMERLY, GUY T. blades with protective coatings p 664 A87°43640 engine p 663 A87-43614 Exploratory evaluation of a moving-model technique for KREATSOULAS, J. C. LAREDO, D. measurement of dynamic ground effects Experimental data correlations for the effects of rotation Diagnostic methods for air.breathing engines [AIAA PAPER 87-1924] p 685 A87-45303 on impingement cooling of tu_ne blades p 686 A87-46243 KHAN, M. M. S. [AIAA PAPER 87-2008] p 696 A87-45349 LAROCCA, FRANCESCO Computational aeroacoustics as applied to the diffraction KREIDER, G. Application of a 3D inviscid rotational design procedure of sound by cylindrical bodies p 707 A87-43383 A bidirectional tapered roller thrust bearing for gas for turbomachinery bladings p 638 A87-46204 KIM, J. S. turbine engines LAU, BENTON H. Wake measurements of an oscillating airfoil [AIAA PAPER 87.1842] p 695 A87-45243 Calculated performance, stability, and maneuverability p 637 A87-45779 KRETSCHMER, D. of high-speed tilting-prop-rotor aircraft KIM, KI-CHUNG Exhaust carbon - The effects of fuel composition p 651 A87-43408 Helicopter response to an airplanes's vortex wake p 676 A87-46253 LAUGHREY, JAMES A. p 678 A87-43430 KRIMERMAN, J. F-15 SMTD hot gas ingestion wind tunnel test results KINDIG, WILLIAM G. Development of a laser interferometric system for [AIAA PAPER 87-1922] p 669 A87*4530t Reliability, 'better than the best' p 699 A87-46728 velocity measurements inside a transonic axial flow LAW, S. P. KINLOCH, A. J. compressor stage p 698 A87-46244 Wind tunnel evaluation of a truncated NACA 64-621 Adhesives in aerospace p 689 A87-44743 KRISTENSEN, LEIF airfoil for wind turbine applications KIRBY, MARK S. An airborne laser air motion sensing system. II - Design [NASA-CR-t80803] p 703 N87-25621 Comparison of wet and dry growth in artificial and flight criteria and measurement possibilities LAYNOR, WILLIAM G. BUD icing conditions p 646 A87-45635 p 662 A87-45733 Accident investigation p 647 N87-25285 KlSSINGER, R. D. KROHN, ERNST-OTTO LE BALLIEUR, J. C. Standing oblique detonation wave engine performance The vertical test section (VMK) of DFVLR in Unsteady viscous-inviscid interaction method and [AIAA PAPER 87-2002] p 670 A87-45347 Cologne-Porz, West Germany computation of buffeting over airfoils KITCHENSlDE, A. W. [DFVLR-MITT-86-22] p 688 N87-26054 [ONERA, TP NO. 1987-58] p 640 A87-46759 Prospects for the use of composites in civil aircraft KNOLL, N. LEAN, O. E. p 655 A87-44577 Computation of the flow fields of propellers and hovering Fatigue-life monitoring of the 5 metre wind tunnel KJELGAARD, S. O. rotors using Euler equations p 628 A87-43418 [RAE-TM-AERO-2084] p 688 N87-26055 Detailed near-wake flowfield surveys with comparison KRUISBRINK, A. C. H. LEAVITT, L D. to an Euler method of an aspect ratio 4 rectangular wing Entrainment effect of a leading-edge vortex Scale model test results of a thrust reverser concept [NASA-TM-89357] p 644 N87-25993 p 641 A87-46777 for advanced multi-functional exhaust systems KLANN, GARY A. KRUK, R. [AIAA PAPER 87-1833] p 667 A87-45235 Contingency power for small turboshaft engines using Engineering and human visual considerations in LECOINTE, Y. water injection into turbine cooling air development ol a tibre optic helmet mounted display Unsteady viscous flows round moving circular cylinders [AIAA PAPER 87-1906] p 668 A87-45289 p 661 A87-44727 and airfoils. II p 637 A87-45792

B-7 PERSONAL AUTHOR INDEX LECORDIX, J. L.

LECORDIX, J. / LIDSTONE, GARY L MACLEAN, M. K. Mechanical evaluation of the aeroelastic behaviour of An improved computational model for a scramjet Parametric study of single expansion ramp nozzles at a fan blade p 675 A87-46248 propulsion system subsonic/transonic speeds LEE, A. R. [AIAA PAPER 87-2078] p 671 A87-45393 [AIAA PAPER 87-1836] p 635 A87-45238 Determination of the structural properties of helicopter LIEBOWITZ, SUZANNE A. MADGWlCK, T. rotor blades by theoretical and experimental methods Model-based knowledge-based optical processors Fire, smoke, toxicity p 646 A87-44748 p 653 A87-43450 p 707 A87-42736 MADHUSOODHANAN, R. V. Stress analysis and optimisation of turbine rotor blade LEE, C. S. LIESE, KARL shrouds p 699 A87-46250 Flow-field measurements of an airfoil with a deflected Helicopter modelling for performance calculation MADSON, MICHAEL D. spoiler using an LDV system p 652 A87-43434 Transonic analysis of the F-16A with under-wing fuel [AIAA PAPER 87-1438] p 634 A87-44955 LIN, C. A. tanks - An application of the TranAir full-potential code LEE, PAl HUNG Scan stabilization and jitter control for an airborne [AIAA PAPER 87-t198] p 630 A87-44905 An experimental investigation of dynamic ground telescope p 660 A87-42812 effect MAGDELENAT, JEAN-LOUIS LINDBERG, L. J. The new Annex 17 - The latest contribution by [NASA-CR-180560] p 659 N87-26036 Durability characterization of ceramic materials for gas international civil aviation to the battle against terrorism LEE, S. turbines p 690 A87-45898 p 708 A87-42860 Vorfex-nozzle interactions in ramjet combustors LINDE, MAGNUS [AIAA PAPER 87-1871] p 668 A87-45266 MAHAPATRA, P. R. Measurement of noise from airplanes traveling at 3500 LEFAS, C. C. Terrain modelling of glideslope for instrument landing to 11000 m altitude Real-time wind estimation and tracking with transponder system p650 A87-46415 [FFA-TN-1986-21] p 708 N87-25824 downlinked airspeed and heading data MAIER, MICHAEL W. p 648 A87-42779 LINDEN, ARTHUR W. Analysis of a microburst in the FACE meteorological RSRA/X-wing - A status report p 651 A87-43409 mesonetwork in southern Florida p 702 A87-45962 LEFEBVRE, A. H. Influence of fuel temperature on atomization LING, R. T. MAILAENDER, M. performance of pressure-swirl atomizers Application of computational physics within Northrop Canard configurations p 698 A87-46198 p 706 N87-26008 [ETN-87-99914] p 659 N87-26039 LEHRACH, R. P. C. LIU, C. H. MALEK, SAMIR Thrust/drag accounting for aerospace plane vehicles Incompressible Navier-Stokes computations of vortical Development and testing of critical components for the [AIAA PAPER 87-1966] p 656 A87-45335 flows over double-delta wings technological preparation on an Airbus fuselage made of LEISS, ULRICH [AIAA PAPER 87-1341] p 631 A87-44933 carbon fiber reinforced plastics, phase 1 [BMFT-FB-W-86-017] p 692 N87-26151 An advanced mathematical model for helicopter flight LIU, YUQI MALIK, M. R. simulation using nonlinear unsteady aerodynamics Research on the stress analysis method of rubber Stationary disturbances in three-dimensional boundary p 679 A87-43435 structure - Calculation of the frequency adapter stresses layers over concave surfaces LEMPERT, WALTER R. p 693 A87-43453 [AIAA PAPER 87-1412] p 632 A87-44945 Molecular flow velocity using Doppler shifted Raman LOCK, R. C. MALIK, MUJEEB R. spectroscopy Viscous-inviscid interactions in external aerodynamics Prediction and control of transition in hypersonic [AIAA PAPER 87-1531] p 693 A87-43053 p 626 A87-43299 LENERTZ, J. E. boundary layers LOEBEL, HEINZ Design and test verification of a combustion system for [AIAA PAPER 87-1414] p 632 A87-44946 Experiences with hot-wire instruments for the an advanced turbofan engine Linear stability analysis of three-dimensional measurement of the liquid water content in clouds [AIAA PAPER 87-1826] p 666 A87-45231 compressible boundary layers p 640 A87-46504 [DFVLR-MtTT-86] p 704 N87-26476 LENGLADE, R. MALZACHER, F. A bidirectional tapered roller thrust bearing for gas LOMBARD, C. K. Flow phenomena in transonic turbine cascades detailed turbine engines Aerodynamic design modification of a hypersonic wind experimental and numerical investigation tunnel nozzle by CSCM with high order accuracy [AIAA PAPER 87-1842] p 695 A87-45243 p 639 A87-46223 [AIAA PAPER 87.1896] p 635 A87-45284 LENSCHOW, D. H. MANDLE, J. LOPEZ, ALFRED R. An airborne laser air motion sensing system. I - Concept A promising low speed air data system for helicopters Application of wedge diffraction theory to estimating and preliminary experiment p 662 A87-45732 p 661 A87-43437 power density at airport humped runways LENSCHOW, DONALD H. MANDLE, JACQUES p 650 A87-46861 An airborne laser air motion sensing system. II - Design Contribution of laser anemometry to aircraft safety LORD, W. K. cdteria and measurement possibilities p 699 A87.46361 Application of CFD codes to the design and development p 662 A87-45733 MANGALAM, S. M. of propulsion systems p 677 N87-26009 LENT, H.-M. A unique measurement technique to study LO'I-rlG, ROY A. Compressible flows in the wakes of a square cylinder laminar-separation bubble characteristics on an airfoil Full-scale thrust reverser testing in an altitude facility and thick symmetrical airfoil arranged in tandem [AIAA PAPER 87-1271] p 631 A87-44921 [AIAA PAPER 87-1788] p 684 A87-45203 p 641 A87-46922 MANGUS, J. F. LOWE, JANICE LEROY, M. Application of computational physics within Northrop Seastar - Glass, plastic, and tradition Numerical simulation of cruiser on aircraft lightning p 706 N87-26008 p 646 A87-46317 p 656 A87-45648 MANNINI, A. LU, HEXlANG LESCAUDRON, MARCEL Air cycle environmental control system for helicopters Research on the stress analysis method of rubber Air conditioning systems for helicopters - A trade-off study p 654 A87-43472 structure - Calculation of the frequency adapter stresses p 654 A87-43473 MANTEGAZZA, PAOLO p 693 A87-43453 LEVIN, E. Aeroelastic derivatives as a sensitivity analysis of LUDEMANN, So High temperature transport properties of air nonlinear equations p 699 A87-46797 Propfan propulsion systems for the 1990's [AIAA PAPER 87-1632] p 707 A87-43129 MARBLE, FRANK E. [AIAA PAPER 87-1729] p 665 A87-45168 Progress toward shock enhancement of supersonic LEVY, Y. LUH, R. C.-C. combustion processes Diagnostic methods for air-breathing engines Aerodynamic design modification of a hypersonic wind p 686 A87-46243 [AIAA PAPER 87-1880] p 690 A87-45274 tunnel nozzle by CSCM with high order accuracy MARCHIONNA, N. LEWIS, MARK J. [AIAA PAPER 87-1896] p 635 A87-45284 NO(x) reduction and combustion phenomena in the The influence of flow non-uniformities in air-breathing LUNN, KENNETH multi-annular gas turbine swirl burner hypersonic propulsion systems Development of the Chinook helicopter rotor blade [AIAA PAPER 87-2036] p 671 A87-45370 [AIAA PAPER 87-2079] p 636 A87-45394 de-icing system p 655 A87-44704 LEWIS, TIMOTHY J. LUl-rGES, M. MARCHIS, V. Air cycle environmental control system for helicopters Highly reliable, microprocessor-based engine control Comparisons of unsteady flow fields about straight and - A trade-off study p 654 A87-43472 [AIAA PAPER 87-1927] p 669 A87-45305 swept wings using flow visualization and hotwire LEWIS, W. J. anemometry MARCUM, DON C., JR. Advantages of thrust vectoring for STOVL [AIAA PAPER 87-1334] p 631 A87-44932 Effect of Reynolds number variation on aerodynamics [AIAA PAPER 87-1708] p 665 A87-45156 LYONS, M. G. of a hydrogen-fueled transport concept at Math 6 LEWY, S. Scan stabilization and jitter control for an airborne [NASA-TP-2728] p 645 N87-26031 A comparison of the acoustic and aerodynamic telescope p 660 A87-42812 MARESCA, C. measurements of a model rotor tested in two anechoic A prescribed radial distribution circulation of a hovering wind tunnels p 683 A87-43425 M rotor blade p 827 A87-43414 LEYENDECKER, H. A new simulation of airfoil dynamic stall due to velocity The model inverse as an element of a manoeuvre and incidence fluctuations MACHA, J. M. demand system for helicopters p 679 A87-43441 [AIAA PAPER 87-1242] p 630 A87-44915 Influence of a heated leading edge on boundary layer MARTELLI, F. LI, BEN-WEI growth, stability and transition An improved approach for transonic flow Application of a fuzzy controller in fuel system of turbojet [DE87-008516] p 700 N87-25538 p 639 A87-46215 engine p 674 A87-46227 MACK, D. P. MARTIN, E. A. LI, JINGBAI Viscid/inviscid separated flows An experimental investigation of delta wings with lAD-A179858] p 699 N87-25536 A program to investigate requirements for effective flight simulator displays p 683 A87-44715 leading-edge vortex separation p 641 A87-46956 MACK, JOHN C. LICHTENFELS, FRED L. Development of a large, spiral bevel gear rotorcraft MASKEW, BRIAN Optically interfaced sensor system for aerospace transmission The use of computer models in helicopter drag applications p 694 A87-45107 [AIAA PAPER 87-1839] p 667 A87-45240 prediction p 628 A87-43424

B-8 NASU, K. PERSONAL AUTHOR INDEX

MOORE, JOHN MASON, MARY I- MERA DIAZ, E. 3-D viscous flow calculations at design and oft-design Static investigation of pest-exit vanes for multiaxis thrust A study on the optimization of jet engines for combat conditions for the NACA 48-inch radial-inlet centrifugal vectoring aircrafts p 676 A87-46262 impeller p 638 A87-46191 [AIAA PAPER 87-1834] p 667 A87-45236 MERCER, LINDEN B. Airborne laser communications scintillation MOORE, P. MASSEY, C. P. measurements p 649 A87-45722 Worldwide navigation into the 21st century - An airline Simulator evaluations of incepters for ACT helicopters view p 649 A87-44036 p 678 A87-43405 MERRILL, WALTER C. Advanced detection, isolation and accommodation of MORELLI, F. MATEER, GEORGE C. sensor failures: Real-time evaluation An experimental investigation of a supercritical airfoil New aerodynamic design of the fenestron for improved [NASA-TP-2740] p 682 N87-25331 performance p 651 A87-43403 at transonic speeds MESCHI, GIUSEPPE [AIAA PAPER 87-1241] p 630 A87-44914 MORGAN, R. G. Lightning protection activity in the development of a new MATHUR, N. B. Scramjet testing in impulse facilities Underexpanded jet-free stream interactions on an helicopter p 654 A87-43471 p 685 A87-46183 METZGER, F.B. axisymmetric afterbody configuration Hydrogen scramjet with sidewall injection - Shock tunnel Results of acoustic tests of a Prop-Fan model p 639 A87-46232 simulations p 674 A87-46217 [AIAA PAPER 87-1894] p 707 A87-45282 MATTERSBY, M, G. Pressure scaling effects in a soramjet combustion Icing clearance criteria for UK military helicopters MEUNIER, S. chamber p 676 A87-46258 Numerical simulation of diffusor/combustor dome p 646 A87-44705 interaction p 676 A87-46255 MORINO, / MATTINGLY, JACK D. MICKEL, LARRY S, A unified approach for potential and viscous free-wake System performance approach to air breathing analysis of helicopter rotors p 627 A87-43412 propulsion design - A new undergraduate design Sparing to optimize naval airship availability p 625 A87-46716 MORITA, YOSHIKAZU competition MIELE, A. Cosign of CCV flight control system of STOL flying [AIAA PAPER 87-1869] p 668 A87-45264 boat p 680 A87-45097 Aircraft engine design p 673 A87-45875 Maximum survival capability of an aircraft in a severe windshear p 680 A87-44254 MORRIS, N. MBA, M. NSl Hydrogen scramjet with sidewall injection - Shock tunnel A prescribed radial distribution circulation of a hovering Optimal flight trajectories in the presence of windshear, simulations p 674 A87-46217 rotor blade p 627 A87-43414 1984-86 MCCARTHY, JOHN [NASA-CR-180316] p 682 N87-26047 MOSKALENKO, A. S. Calculation of the reliability of aircraft-engine parts under Introduction to the JAWS Program MILDE, MICHAEL repeated static loading p 664 A87-43616 p 703 N87.25270 Interception of civil aircraft vs. misuse of civil aviation Status of the JAWS Program p 703 N87-25272 p 708 A87-42861 MOSS, JAMES N. Direct simulation of aerothermal loads for an aeroassist United Aidines wind shear incident of May 31, 1984 MILLER, DAVID S. p 647 N87-25288 Molecular flow velocity using Doppler shifted Raman flight experiment vehicle [AIAA PAPER 87°1546] p626 A87-43063 MCCORMACK, CHRISTOPHER J. spectroscopy TACAN/INS Performance Evaluation (TIPE) flight test ]AIAA PAPER 87-1531] p 693 A87-43053 MOSTAFA, A. A. On the evolution of particle.laden jet flows - A theoretical report MILLER, GLEN E. and experimental study [AD-A180138] p 650 N87-25313 Fiber optic control of jet aircraft engines MCCOY, KEVIN D. p 661 A87-45115 [AIAA PAPER 87-2181] p 697 A87-45457 Flight test of the F100-PW-220 engine in the F-16 MOXON, JULIAN MILLER, R. H. [AIAA PAPER 87-t845] p 667 A87-45245 Prediction of blade airloads in hovering and forward flight V.2500 - Back on course? p 676 A87-46372 MCDONNELL, V. G. using free wakes p 651 A87-43411 MUELLER, KLAUS On the evolution of particle-laden jet flows - A theoretical Going beyond the limits. Aviation in Germany MILLER, S. C. and experimental study Future trends - A European view p 673 A87-46179 [SO-1-87] p 710 N87-26853 [AIAA PAPER 87-2181] p 697 A87-45457 MUELLER, R. MILLER, THERESE M. MCGAW, MICHAEL A. The influence of winglets on rotor aerodynamics Evaluating and testing of turbofan engines A high temperature fatigue and structures testing p 628 A87-43422 facility [ASME PAPER 86-WA/DE-3] p 664 A87-43701 MUELLER, T. J. [NASA-TM-100151] p 701 N87-26399 MILNE, GARTH WILLIAM The effect of trip wire roughness on the performance MCGHEE, ROBERT J. Identification of a dynamic model of a helicopter from of the Wortmann FX 63-137 airfoil at low Reynolds Low-speed wind-tunnel results for symmetrical NASA flight tests p 659 N87-26040 numbers p 629 A87-44019 LS(1)-0013 airfoil MIRANDA, LUIS R. Laminar separation bubble characteristics on an airfoil [NASA-TM-4003] p 645 N87-26033 CFD applications: The Lockheed perspective MCKELVEY, ROBERT K. p 644 N87-26005 at low Reynolds numbers p 641 A87-46778 MUIRHEAD, VINCENT U. Colour dependence and surplus information in airport MISEGADES, KENT P. An experimental investigation of dynamic ground visual aids during VFR operations p 649 A87-44040 Euler solution for a complete fighter aircraft at sub- and effect MCKILLIP, ROBERT M. JR. supersonic speed [NASA-CR-180560] p 659 N87-26036 Kinematic observers for active control of helicopter rotor [MBB-LKE-122-S/PUB/234] p 660 N87-26833 vibration p 679 A87-43448 MUNSON, R. E. MITCHELL, R. G. Conformal microstrip communication antenna MCMILLAN, G. R. Corrosion protection p 624 A87-44750 A program to investigate requirements for effective flight p 697 A87-45689 MITCHUM, MARIA V. MURRAY-SMITH, D. J. simulator displays p 683 A87-44715 The numerical simulation of subsonic flutter MEACHAM, W. I- Experience with frequency-domain methods in [AIAA PAPER 87-1428] p 633 A87-44952 Complex modal balancing of flexible rotors including helicopter system identification p 680 A87-43457 residual bow MODARRESS, DARIUSH MYERS, LAWRENCE P. [AIAA PAPER 87-1840] p 695 A87-45241 Tomographic reconstruction of three-dimensional flow Preliminary flight results of an adaptive engine control MEAUZE, GEORGES over airfoils system of an F.15 airplane Numerical simulation of flows in axial and radial [AD-A179976] p 643 N87-25300 [AIAA PAPER 87-1847] p 667 A87-45247 turbomachiees using Euler solvers MOE, GARY P. [ONERA, TP NO. 1987-87] p 641 A87*46776 Flight test and evaluation of propulsion system N MERALIC, CHARLES M. operability characteristics Full-scale thrust reverser testing in an altitude facility [AIAA PAPER 87-2092] p 656 A87-45400 NAGARAJ, N. [AIAA PAPER 87-1788] p684 A87-45203 MOLUSlS, JOHN A. Aerodynamic design modification of a hypersonic wind MEIER, G. E. A. Dual adaptive control: Design principles and tunnel nozzle by CSCM with high order accuracy Compressible flows in the wakes of a square cylinder applications [AIAA PAPER 87-1896] p 635 A87-45284 and thick symmetrical airfoil arranged in tandem [NASA-CR-181050] p 705 N87-25804 NAGURNY, N. J. p 641 A87-46922 MONAVON, M. Waste heat recovery system for high altitude application MEIJER, STAFFAN Numerical simulation of cruiser on aircraft lightning of liquid cooled, piston engines Measurement of noise from airplanes traveling at 3500 p 646 A87-46317 [AIAA PAPER 87-2174] p 673 A87-45454 to 11000 m altitude MONGIA, H. C. NAKAGAWA, T. [FFA-TN-1986-21] p 708 N87-25824 High density fuel effects on gas turbine engines Compressible flows in the wakes of a square cylinder MEIXNER, F. X. [AIAA PAPER 87-1829] p 666 A87-45233 and thick symmetrical airfoil arranged in tandem Large-scale distribution of peroxyacetylnitrate results On the evolution of particle-laden jet flows - A theoretical p 641 A87-46922 from the STRATOZ III flights p 702 A87-46481 and experimental study NAKAMURA, Y. MELVIN, W. W. [AIAA PAPER 87-2181] p697 A87-45457 Performance calculation of counter rotation propeller Maximum survival capability of an aircraft in a severe MOOK, DEAN T. [AIAA PAPER 87-1889] p 635 A87-45278 windshear p 680 A87-44254 The numerical simulation of subsonic flutter NAKAMURA, YOSHIYA MENON, SURESH [AIAA PAPER 87-14281 p 633 A87-44952 Extension of local circulation method to counter rotation Simulations of ramjet combustor flow fields. I - Numerical MOOKERJEE, PURUSO'rTAM propeller model, large-scale and mean motions [AIAA PAPER 87-1891] p 635 A87-45280 [AIAA PAPER 87-1421] p 633 A87-44949 Dual adaptive control: Design principles and NARAYANA MURTHY, R. V. Simulations of ramjet combustor flow fields. II - Origin applications [NASA-CR-181050] p 705 N87-25804 Erosion problem of axial compressor blades of a of pressure oscillations turboshaft engine p 675 A87-46246 [AIAA PAPER 87-1422] p 633 A87.44950 MOORE, JOAN G. 3-D viscous flow calculations at design and oft-design NASU, K. MENZE, GOTTHARD Performance calculation of counter rotation propeller The Airbus rudder - An example of new fabrication conditions for the NACA 48-inch radial-inlet centrifugal [AIAA PAPER 87-1889] p 635 A87-45278 technologies p 623 A87-44228 impeller p 638 A87-46191 B-9 NASU, KENICHI PERSONAL AUTHOR INDEX

NASU, KENICHI ODGERS, J. PAVLENKO, G. V. Extension of local circulation method to counter rotation Exhaust carbon - The effects of fuel composition Efficiency of the utilization of rotor blade shroud labyrinth propeller p 676 A87-46253 seals in an axial-compressor stage with large radial [AIAA PAPER 87-1891] p 635 A67-45260 OECHSLE, V. L. clearances p 694 A87-43611 NAVEAU, JACOUES High density fuel effects on gas turbine engines PAYEN, D. B. The effect of European law on air transport [AIAA PAPER 87-1829] p 666 A67-45233 Experimental application of strain pattern analysis (SPA) p 709 A87-42862 OFFENBERG, I- S. - Wind tunnel and flight test results p 654 A87-43459 NEELY, JAMES An experimental investigation of turbine case PEACOCK, D. K. Integration of propulsion/integration test results through treatments Developments in titanium alloys p 689 A87-44744 the use of reference plane transfers [AIAA PAPER 87-1919] p 669 A87-45299 PEACOCK, N. J. Engine design and systems integration for propfan and [AIAA PAPER 87-1964] p 670 A87.45333 OKIISHI, T. H. NELSON, H. D. high bypass turbofan engines Rotor wake segment influence on stator-surface [AIAA PAPER 87-1730] p 665 A87-45169 Complex modal balancing of flexible rotors including boundary layer development in an axial-flow compressor residual bow PECH, R. stage A bidirectional tapered roller thrust bearing for gas [AIAA PAPER 87-1840] p 695 A87-45241 [AIAA PAPER 87-1741] p 695 A87-45178 NELSON, HOWARD G. turbine engines OKUNO, YOSHINORI Failure analysis Of a large wind tunnel compressor [AtAA PAPER 67-1642] p 695 A87-46243 Study of the dynamic response of helicopters to a large blade p 692 A87-42852 PENLAND, JIM A. airplane wake p 678 A67-43429 NEWMAN, EUGENE E. Effect of Reynolds number variation on aerodynamics Sparing to Optimize naval airship availability ONG, L. H. of a hydrogen-fueled transport concept at Mach 6 p 625 A87-46716 NO(x) reduction and combustion phenomena in the [NASA-TP-2728] p 645 N87-26031 NEWMAN, PERRY A. multi-annular gas turbine swirl burner PERETZ, ARIE Transonic wall interference assessment and corrections [AIAA PAPER 87-2036] p 671 A87-45370 Application of ceramics to ramjet engine nozzles for airfoil data from the 0.3-meter TCT adaptive wall test ORSZAG, STEVEN A. p 690 A87-46221 section Linear stability analysis of three-dimensional PERKINS, GARY M. [AIAA PAPER 87-1431] p 633 A87-44953 compressible boundary layers p 640 A87-46504 Three stream turbofan-variable cycle engine with integral NEZYM, V. IU. OSTRANDER, M. J. turbocompressor Investigation of rotating additional blades on the Standing oblique detonation wave engine performance [AIAA PAPER 87-2104] p 672 A87-45409 periphery of an axial-compresssor rotor [AIAA PAPER 87-2002] p 670 A87-45347 PERKINS, J. N. p 629 A87-43616 Detailed near.wake tiowtield surveys with comparison NGUYEN-HOANG, VUI to an Euler method of an aspect ratio 4 rectangular wing Analytical description of crack resistance curves for P [NASA-TM-69357] p 644 N87-25993 aluminum sheets used in akoraft construction PETERSILGE, CHRISTIAN [MBB-UT-133/65] p 700 N87-25604 PACE, SCOTT Measurement of side forces of a H-force rotor NGUYEN, P. National Aerospace Plane Program: Principal p 651 A87-43410 Aerodynamic and heat transfer analysis of the low aspect assumptions, findings and policy options PETIAU, C. ratio turbine [RAND/P-7288.RGS] p 625 N67-25990 Trends in the aeroelastic analysis of combat aircraft [AIAA PAPER 87-t916] p 696 A87-45296 PADFIELD, G. D. p 657 A87-46362 NI, R. H. Observations of pilot control strategy in low level PETKUS, EDWARD P. HALE thermal balance Aerodynamic and heat transfer analysis o1the low aspect helicopter flying tasks p 678 A87-43433 ratio turbine [AIAA PAPER 87-2172] p 656 A87-45452 Experience with frequency-domain methods in [AIAA PAPER 87-1916] p 696 A87-45296 PETRO, DAVID helicopter system identification p 680 A87-43457 NIENHAUS, MARK J. Development program of a full authority digital electronic PADMANABHAN, R. Operational engine usage and mission analysis control system for the T55-L-712E turboshaft engine Stress analysis and optimisation of turbine rotor blade [AIAA PAPER 87-2097] p 671 A87-45404 p 663 A87-43465 shrouds p 699 A87-46250 NIKITIN, S. A. PETROV, B. t. Engineering and c0st principles for increasing the PAGE, D. M. Electrochemical machining processes in aircraft engine production efficiency and maintainability of aircraft Worldwide nsvigation into the 21st century - An airline building p 693 A87-42905 engines p 664 A67-43620 view p 649 A87-44036 PHILBERT, MICHEL NIVEN, ANDREW J. PAINI, W. P. Wind tunnel experimental study of optical beam The effect of pitch rate on the dynamic stall or a modified A derivative engine based on new technology - Low degradation through heterogeneous aerodynamic flows NACA 23012 aerofoil and comparison with the unmodified risk; cost effective [ONERA, TP NO. 1987-50] p 707 A87-46753 case p 628 A87-43420 [AIAA PAPER 87-1910] p 669 A87-45292 PICKETT, G. F. NIXON, MARK W. PALS, M. R. Application of CFD codes to the design and development Preliminary structural design o1 composite main rotor Determination of the local heat transfer characteristics of propulsion systems p 677 N87-26009 blades for minimum weight on glaze ice accretions on a cylinder and a NACA 0012 PIERCE, G. ALVIN [NASA-TP.2730] p 691 N87-25435 airfoil A unique approach to aeroelastic testing of scaled NORBY, W. P. [AD-A179931] p 647 N87-25309 rotors p 683 A87-43461 Two-dimensional numerical analysis for inlets at PAPAIMOU, K. D. PIUSHCHIKOV, V. A. subsonic through hypersonic speeds A method for the calculation of the interaction of a Optimization of systems for the automatic testing of [AIAA PAPER 87-1751] p 634 A87-45184 turbulent boundary layer with a shock wave aircraft engines according to cost criteria NORTHAM, G. B. p 639 A87-46238 p 664 A67-43621 PINCKERT, R. E. Three-dimensional numerical predictions of the flow PARANJPE, P. A. behind a reanNard-facing-step in a supersonic combustor A study on the effect of non-dimensional system Fatigue and fracture mechanics analysis of compression loaded aircraft structure p 692 A87-42654 [AIAA PAPER 87-1962] p 636 A87-45332 parameters on squeeze film damper performance using NORTHAM, G. BURTON experimental data p 698 A87-46229 PING, TCHENG Miniature remote dead weight calibrator Effects of scale on supersonic combustor PARK, S. O. [NASA-CASE-LAR-13564-1] p 700 N87-25558 perfom'_.nce Wake measurements of an oscillating airfoil PIQUET, J. [AIAA PAPER 87-2164] p 672 A87.45444 p 637 A87-45779 Unsteady viscous flows round moving circular cylinders Design and evaluation of a new injector configuration PARKER, R. J. for supersonic combustion p 674 A87-46218 and airfoils. II p 637 A87-45792 Optical flow diagnostic measurements in PLETSCHACHER, PETER NOVICK, A. S. turbomachinery p 698 A87.46245 Heat exchangers for turboshaff engines Propfan propulsion system development PARRISH, RUSSELL V. p 664 A87-44253 p 675 A87-46247 Auxiliary data input device PODBOY, GARY G. NSl MBA, M. [NASA-CASE-LAR-13626-1] p 700 N87-25584 Wind tunnel performance results of an aeroeiestically Aerodynamic study of a helicopter rotor in hovering flight PARTRIDGE, HARRY scaled 2/9 model of the PTA flight test prop-fan - Theory vs. experiment p 641 A87-47014 High temperature transport properties o1 air [NASA-TM-69917] p 642 N87-25294 NYGREN, KIP PETER [AIAA PAPER 87-1632] p 707 A87-43129 POIRION, F. An investigation of helicopter higher harmonic control PATRIQMIN, DOUGLAS R. Sounded random oscillations - Model and numerical using a dynamic system coupler simulation Optioatty interfaced sensor system for aerospace resolution for an airfoil p 682 N87-26051 applications p 694 A87-45107 [ONERA, TP NO. 1987-73] p 681 A67-46767 PAI-rERSON, JAMES C., JR. POLYCHRONIADIS, MICHEL 0 Evaluation of installed performance of a Development of an experimental system for active wing.tip-mounted pusher turboprop on a semispan wing control of vibrations on helicopters p 679 A87-43447 [NASA-TP-2739] p 659 N87-26041 POPE, M. S. O'BRIEN, W. F. PAULL, A. Development of Digital Engine Control System for the A stage-by-stage post-stall compression system Hydrogen scram jet with sidewall injection - Shock tunnel Harrier II modeling technique simulations p 674 A87-46217 [AIAA PAPER 67-2184] p 673 A87-45458 [AIAA PAPER 87-2088] p 636 A87-45397 PAULSON, JOHN W., JR. PORRO, A. R. O'BRIEN, WALTER F. Exploratory evaluation of a moving-model technique for An LDA investigation of three-dimensional normal Design and evaluation of a new injector configuration measurement of dynamic ground effects shock-boundary layer interactions in a corner for supersonic combustion p 674 A87-46218 [AIAA PAPER 87-1924] p 685 A87-45303 [AIAA PAPER 87-1369] p 632 A87-44938 O'MEARA, M. M. PAUSDER, H.-J. POSTLETHWAITE, ALAN Laminar separation bubble characteristics on an airfoil Observations of pilot control strategy in low level Seestar - Glass, plastic, and tradition at low Reynolds numbers p 641 A87-46778 helicopter flying tasks p 678 A87-43433 p 656 A87-45648

B-10 SAFRONOV, IA. V. PERSONAL AUTHOR INDEX

RILEY, MICHAEL F. POULOSE, M. M. RAMSDEN, J. M. Optimization methods applied to the aerodynamic design Terrain modelling of glideslope for instrument landing Burning questions p 646 A87-46373 of helicopter rotor blades system p 650 A87-46415 RE, R. J. Parametric study of single expansion ramp nozzles at [NASA-TM-89155] p 660 N87-26042 POWELL, T. subsonic/transonic speeds ROBERT, M. Variable cycle concepts for high Mach applications [AIAA PAPER 87-1836] p 635 A87-45238 Crack growth prediction in 3D structures under [AIAA PAPER 87-2103] p 672 A87-45408 REDDY, D. N. aeronautical-type spectrum Ioadings POWELL, T. H. Effect of swirl on the performance of a radial vaneless [ONERA, TP NO. 1987-79] p 691 A87-46772 Advancements in hydrogen expander airbreathing diffuser with compressible flow at Mech numbers of 0.7 ROBERTSON, R. CLARK engines and 0.8 [AIAA PAPER 87-2003] p 670 A87-45348 Geostationary satellite navigation systems [ASME PAPER 86-WA/FE-6] p 629 A87-43704 p 648 A87-42786 PRASHU, B. S. REDDY, K. T. A study on the effect of non-dimensional system ROBINSON, M. C. Degradation mechanisms of sulfur and nitrogen Visualization of three-dimensional structures about a parameters on squeeze film damper performance using containing compounds during thermal stability testing of pitching forward swept wing experimental data p 698 A87-46229 model fuels [AIAA PAPER 87-1322] p 631 A87-44929 PRATT, D. T. [AIAA PAPER 87-2039] p 690 A87-45372 RODGERS, C. Standing oblique detonation wave engine performance REDEMANN, HANNS APU fuel efficiency and affordability for commercial [AIAA PAPER 87-2002] p 670 A87-45347 Going beyond the limits. Aviation in Germany aircraft PRATT, DAVID T. ]SO-1-87] p 710 N87-26853 [AIAA PAPER 87-1907] p 669 A87-45290 Morphology of a standing oblique detonation wave REED, WlLMER H. ROGER, M. [AIAA PAPER 87-1785] p 695 A87-4520t Airfoil flutter model suspension system An analysis of in-fin tail rotor noise PRATT, N. S. [NASA-CASE.LAR-13522-1-SB] p 687 N87-25334 p 652 A87-43427 XMAN - A tool for automated jet engine diagnostics REES, ELFAN AP ROGERS, LAWRENCE W. [AIAA PAPER 87-1931] p 696 A87-45309 Soviet helicopter development p 657 A87-46735 Experimental study of the vortex flow behavior on a PROKOPOVICH, V. G. REICHERT, G. generic fighter wing at subsonic and transonic speeds Investigation of rotating additional blades on the Optimum design of a helicopter rotor blade [AIAA PAPER 87-1262] p 631 A67-44920 periphery of an axial-compresssor rotor p 651 A87-43406 ROGERS, R. C. p 629 A87-43618 REILLY, DAVID R. Three-dimensional numerical predictions of the flow PRONICHEV, N. D. Simulator manufacturers' requirements behind a rearward-facing-step in a supersonic combustor Electrochemical machining processes in aircraft engine p 687 N87-25280 (AIAA PAPER 87-1962] p 636 A87-45332 building p 693 A87-42905 RENAUD, J. ROGERS, STEVEN K. PRZYBYLKO, S. J. The tilt-rotor aircraft - A response to the future? From Airborne laser communications scintillation Future advanced control technology study (FACTS) - European interrogations to Eurofar actions measurements p 649 A87-45722 A look at emerging technologies [MBB.UD-485-86-PUB] p 654 A87-43474 ROONEY, P. J. [AIAA PAPER 87-1930] p 670 A87-45308 RENKEN, JUERGEN The design of low-stress/high performance centrifugal PUNDHIR, D. S. Conceptual studies of control systems for wings with impellers A study of some factors affecting the performance of variable camber [AIAA PAPER 87-2099] p 697 A87-45405 a contra-rotating axial compressor stage [MBB-UT-221/86] p 682 N87-26836 ROSE, GAYLE E. p 639 A67-46211 REUSUSH, DAVID E. Wind tunnel performance results of an aeroelastically PUSTER, RICHARD L Investigation of a delta-wing fighter model flow field at scaled 2/9 model of the PTA flight test prop.fan Modification to the Langley 8-Foot High Temperature transonic speeds [NASA-TM-89917] p 642 N87-25294 Tunnel for hypersonic propulsion testing [AIAA PAPER 87-1749] p 634 A87-45182 ROSEN, A. [AIAA PAPER 87-1887] p 685 A87-45277 Modification to the Langley 8-Foot High Temperature A parametric investigation of a free wake analysis of Tunnel for hypersonic propulsion testing hovering rotors p 627 A87-43413 Q [AIAA PAPER 87-1887] p 685 A87-45277 ROSEN, ROBERT REUKEMA, BARBARA Civil propulsion technology for the next twenty-five Airlines are exempt from law on rights of the disabled years p 624 A87-46177 QI, MENGBU p 709 A87-42863 ROSS, P. T. An experimental investigation of delta wings with REVELI., J. leading-edge vortex separation p 641 A87-46956 High density fuel effects on gas turbine engines EH101 cockpit design p 661 A87-43404 [AIAA PAPER 87-1829] p 666 A87-45233 QINGHUAN, WANG REYNOLDS, C. N. ROSTRON, W. W. Improvement of aerodynamic calculation on S(2)m Propfan propulsion systems for the 1990's T700/CT7 derivative growth engine reliability - stream surface of axial compressor by using of annulus [AIAA PAPER 87-1729] p 665 A87-45168 Consistent with longstanding industry traditions wall boundary layer calculation p 639 A87-46216 Propfan propulsion system development p 663 A87-43464 QUART, IRVING p 675 A87-46247 ROTH, S. P. Culprits causing avionic equipment failures REYNOLDS, PHILIP p 662 A87-46727 Micro-computer/parallel processing for real time testing Military specifications p 658 N87-25281 of gas turbine control systems OUEMARD, G. RHIE, C. M. The interference of the model support mast with [AIAA PAPER 87-1926] p 669 A87-45304 Aerodynamic and heat transfer analysis of the low aspect measurements of the longitudinal and lateral aerodynamic ROTHMANN, ELIZABETH M. ratio turbine coefficients Analysis of typical fault-tolerant architectures using [AIAA PAPER 87-1916] p 696 A87-45296 HARP p 704 A87-45771 [NASA-TT-20079] p 644 N87.25307 RHIE, CHEA M. ROTONDI, C. QUERZOU, R. Numerical analysis of peak heat transfer rates for Investigation on the stall margin of a turbofan engine Composite vital parts optimisation for EH 101 rotor hypersonic flow over a cowl leading edge hub p 653 A87-43451 p 675 A87-46239 [AIAA PAPER 87-1895] p 635 A87-45283 QUICK, SID ROUSSELLE, HAROLD RlCClO, G. E. The Warsaw Convention system regarding air carrier The art of reticulation and applicable adhesives A program to investigate requirements for effective flight p 665 A87-44582 responsibility - New developments in jurisprudence simulator displays p 683 A87-44715 p 709 A87-42864 RICH, DANIEL L RUBIN, S. G. R Fatigue and fracture mechanics analysis of compression Time-consistent pressure relaxation procedure for loaded aircraft structure p 692 A87-42854 compressible reduced Navier-Stokes equations RAGAB, S/UkD A. RICH, THOMAS P. p 626 A87-43377 Linear instability waves in supersonic turbulent mixing Case histories involving fatigue and fracture mechanics; RUDOLPH, J. layers Proceedings of the Symposium, Charleston, SC, Mar. 21, Large-scale distribution of peroxyacetylnitrate results [AIAA PAPER 87-1418] p 633 A87-44948 22, 1985 p 692 A87-4285t from the STRATOZ III flights p 702 A87-46481 RAGHUNATH, B. J. RIECKHOF, HANS-JUERGEN RUSTENBURG, JOHN W. Stress analysis and optimisation of turbine rotor blade Development and testing of critical components for the Correlation of B-1 flight test subjective assessments and shrouds p 699 A87-46250 technological preparation on an Airbus fuselage made of some ride quality/vibration exposure criteria RAI, MAN MOHAN carbon fiber reinforced plastics, phase 1 [AD-A179844] p 658 N87-25318 Unsteady three-dimensional Navier-Stokes simulations [BMFT.FB-W.86-017] p 692 N87-26151 RYDCHENKO, V. M. of turbine rotor-stator interaction Parameters of optimal planetary gears of AI type RIEGER, HERBERT [AIAA PAPER 87-2058] p 636 A87-45386 Aerothermodynamic computations for p 694 A87-43622 RAMACHANDRA, K. super-/hypersonic flight p 640 A87-46328 Stress analysis and optimisation of turbine rotor blade RIFFEL, R. E. S shrouds p 699 A87-46250 Propfan propulsion systems for the t 990's RAMAKRISHNAN, J. V. [AIAA PAPER 87-1729] p 665 A87-45168 SACKETr, JOHN R. A comparison of the structurebeme and airborne paths Propfan propulsion system development Heliport visual approach surface testing test plan for propfan interior noise p 675 A87-46247 lAD-A179897] p 650 N87-25312 [NASA-CR-180289] p 708 N87-26612 RAMAKRISHNAN, S. V. RIGAULT, M. SAFF, CHARLES R. Time-consistent pressure relaxation procedure for A model test vehicle for hypersonic aerospace systems Fatigue life analysis of fuel tank skins under combined loads p 650 A87-42856 compressible reduced Navier-Stokes equations development p 626 A87.43377 [MBB-UR.875/86] p 658 N87-25314 SAFRONOV, IA. V. Optimization of systems for the automatic testing of RAMANATHAN, R. RILEY, M. J. aircraft engines according to cost criteria Microprocessor based surge monitoring system Measurements of the performance of a helicopter swept p 664 A87-43621 p 686 A87-46241 tip rotor in flight p 652 A87-43423

B-11 SAITO, S. PERSONAL AUTHOR INDEX

SAITO, S. SCHULZ, DIETER SHIPMAN, KEITH W. Performance calculation of counter rotation propeller Development and testing of critical components for the Simulator systems integration p 687 N87-25283 [AIAA PAPER 87-1889] p 635 A87-45278 technological preparation on an Airbus fuselage made of SHMANEV, VASILII ALEKSANDROVICH SAITO, SHIGERU carbon fiber reinforced plastics, phase 1 Electrochemical machining processes in aircraft engine Study ol the dynamic response of helicopters to a large [BMFT-FB-W-86-017] p 692 N87-26151 b_ilding p 693 A87-42905 airplane wake p 678 A87-43429 SCHULZ, HANS GEORG SHVETS, A. I. Extension of local circulation method to counter rotation Integration of the propfan concept in aircraft design Aerodynamic characteristics of wave riders p 637 A87-46094 propeller IMBB-UT-0001/86] p 677 N87-26835 SlECZKOS, JOHN [AIAA PAPER 87-1891] p 635 A87-45280 SCHUSTER, DAVID M. Navier-Stokes simulations of supersonic fighter intake Reliability, 'better than the best' p 699 A87-46728 SALAS, M. D. SIGNOR, DAVID B. Vortex breakdown simulation flowfields [AIAA PAPER 87-1752] p 634 A87-45185 Performance and loads data from a hover test of a [AIAA PAPER 87-1343] p 632 A87-44934 SCHWAEBLE, R. 0.658-scale V-22 rotor and wing SAMUELSEN, G. S. A new method of analytical evaluation of helicopter true [NASA-TM-89419] p 642 N87-25296 On the evolution of particle-laden jet flows - A theoretical airspeed p 661 A87-43439 SIMMON, DAVID A. and experimental study SCHWARZ, ALOIS United Airlines wind shear incident of May 31. 1984 [AIAA PAPER 87-2181] p 697 A87-45457 FEL - A new main rotor System p 651 A87-43402 p 647 N87-25287 SANBORN, J. W. SCHWEIGER, F. A. SlMMONDS, ANN L Design and test verification of a combustion system for Dual cycle turbofan engine Direct simulation of aerothermal loads for an aeroassist an advanced turbofan engine [AIAA PAPER 87-21021 p 672 A87-45407 flight experiment vehicle [AIAA PAPER 87-1826] p 666 A87-45231 SCHWIESOW, R. L [AIAA PAPER 87-1546] p626 A87-43063 SANCHEZ TARIFA, C. An airborne laser air motion sensing system. I - Concept SIMMONS, JOHN R. A study on the optimization of jet engines for combat and preliminary experiment p 662 A87-45732 Impact of engine technology on supersonic STOVL aircrafts p 676 A87-46262 SCRIVENER, C. T. J. [AIAA PAPER 87-1709] p 665 A87-45157 SARRI, G. The role of short duration facilities in gas turbine SINGH, S. N. Air cycle environmental control system for helicopters research p 685 A87-48222 Determination of the local heat transfer characteristics - A trade-off study p 654 A87-43472 SEARS, WILLIAM R. on glaze ice accretions on a cylinder and a NACA 0012 SASSON, R. Flying wing could stealthily reappear airfoil Development of a laser interferometric system for p 657 A87-45870 lAD-A179931} p 647 N87-25309 velocity measurements inside a transonic axial flow SEEGMILLER, H. LEE SKIRA, CHARLES A. compressor stage p 698 A87-46244 An experimental investigation of a aupercritical airfoil Validation of an integrated flight and propulsion control SATHEERATNAM, A. G. at transonic speeds design for fighter aircraft Microprocessor based surge monitoring system [AIAA PAPER 87-12411 p 630 A87-44914 [AIAA PAPER 87-19281 p 680 A87-45306 p 686 A87-4624t SELDEn, ALBERT SKUAR, A. V. Investigation of flow structure in a compressor with two SDUTt'OHI, A. State-of-the-art test facilities for development of the types of guides p 629 A87-43604 Investigation on the stall margin of a turbofan engine Army's T800-LHT-800 LHX helicopter engine SKOOG, MARK A. p 675 A87-46239 [AIAA PAPER 87-1790] p 684 A87-45204 SELVAGINNI, R. Testing automated ground collision avoidance systems SCHAEFFER, DWIGHT R. Recent progress in the measurement of the drag on the AFTI/F-16 p 660 A87-43375 Automatic systems and the low-level wind hazard coefficients of models of transport aircraft in a wind SMAILYS, A. p 681 N87-25279 tunnel Designing for fretting fatigue free joints in turboprop SCHETZ, J. A. [NASA-TT-20096] p 644 N87-25306 engine gearboxes Studies of scramjet flowfields SEMENOV, G. R. [AIAA PAPER 87-2046] p 671 A87-45378 ]AIAA PAPER 87-2161] p 688 A87-45443 A study of the thermal-stress state of gas turbine engine SMITH, A. F. SCHIFF, LEWIS B. blades with protective coatings p 664 A87-43640 The microstructure and mechanical properties of various Numerical simulation of vortical flows over a strake-deita SERAFIN, R. J. aluminium-lithium alloy product forms for helicopter wing An airborne laser air motion sensing system. I- Concept structures p 688 A87-43454 [AIAA PAPER 87-12291 p630 A87-44913 end preliminary experiment p 662 A87-45732 SMITH, D. E. SCHIMKE, S. M. SEVICH, G. J. Preparing a propfan propulsion system for flight test Viscid/inviScid separated flows Preparing a propfan propulsion system for flight test [AIAA PAPER 87-1731] p 665 A87-45170 lAD-A179858} p699 N87-25536 [AIAA PAPER 87-1731] p 665 A87-45170 SMITH, MARILYN J. SCHLICKENMAIER, HERBERT SEWALL, W. G. Navier-Stokes simulations of supersonic fighter intake Case history of FAA/SRI wind shear models Designing transonic wind-tunnel test sections for flow fiowtields p 703 N87-25268 diagnostics and laser velocimeter applications [AIAA PAPER 87-1752] p 634 A87-45185 SCHMIDT, DAVID K. [AIAA PAPER 87-1434] p 684 A87-44954 SMITH, V. K. Optimal cooperative control synthesis of active SHAN, DAVID YU-YUNG Ground testing facilities requirements for hypersonic displays Application of low-Reynolds-number K-epsilon model to propulsion development [NASA-CR-40581 p 705 N87-25807 solid fuel turbulent boundary layer combustion [A_AA PAPER 87-18841 p 684 A87-45276 SCHMIDT, H. P. [AIAA PAPER 87-1778] p 690 A87-45198 SMITH, W. EARL Analysis of typical fault-tolerant architectures using Canard configurations SHANG, JOSEPH J. S. [ETN-87-99914] p 659 N87-28039 Numerical investigation of the flow structure around a HARP p 704 A87-45771 SOBIESZCZANSKI-SOBIESKI, JAROSLAW SCHMIDT, M. J. P. rapidly pitching airfoil [AIAA PAPER 87-1424] p 633 A87-44951 Interdisciplinary optimum design p 857 A87-47009 Tip clearance flows. I - Experimental investigation of SOECHTING, F. O. an isolated rotor. II - Study of various models and SHANI, SHIMON Application of ceramics to ramjet engine nozzles Development of low-cost test techniques for advancing comparison with test results p 638 A87-46208 p 690 A87-4622t film cooling technology SCHMITZ, F. H. SHANKAR, VIJAYA [AIAA PAPER 87-1913] p 696 A87-45293 A comparison of the acoustic and aerodynamic Development and application of unified algorithms for SOLIGNAC, JEAN-LOUIS measurements of a model rotor tested in two anechoic problems in computational science p 705 N87-26006 Wind tunnel experimental study of optical beam wind tunnels p 683 A87-43425 SHARMA, O. P. degradation through heterogeneous aerodynamic flows SCHNEIDER, KLAUS-HEINER Aerodynamic and heat transfer analysis of the low aspect [ONERA, TP NO. t987-50] p 707 A87-46753 Development and testing of critical components for the ratio turbine SORENSON, REESE L technological preparation on an Airbus fuselage made of [AIAA PAPER 87-19161 p 696. A87-45296 Simulation of transonic viscous flow over a fighter-like carbon fiber reinforced plastics, phase 1 SHARMA, P. B. configuration including inlet [BMFT-FB-W-86-017] p 692 N87-26151 A study of some factors affecting the performance of [AIAA PAPER 87-1199] p 630 A87-44906 SCHOENMAN, RICHARD L • contra-rotatieg axial compressor stage SOTHERAN, A. Microburst model requirements for flight simulation: An p 639 A87-46211 High performance turbofan afterburner systems airframe manufacturer's perspective SHAW, BRADLEY T. [AIAA PAPER 87-18301 p 666 A87-45234 p 687 N87-25278 Technological change and skill requirements - A case SPIKES, H. A. SCHRAGE, D. study of numerically controlled riveting in commercial Helicopter lubrication p 624 A87-44733 Optimum design of a helicopter rotor blade aircraft manufacture SPLETTSTOESSER, W. R. p 651 A87-43406 [ASME PAPER 86-WA/TS.2] p 623 A87-43723 A comparison of the acoustic and aerodynamic SCHRAGE, DANIEL SHAW, PETER D. measurements of a model rotor tested in two anechoic Rotor design for maneuver performance Validation of an integrated flight and propulsion control wind tunnels p 683 A87-43425 p 652 A87-43431 design for fighter aircraft SPLI'rF, GEORG A conformal aircraft phased array antenna for SCHUELER, MANFRED [AIAA PAPER 87-1928] p 680 A87-45306 Performance seeking control for cruise optimization in airplane-satellite communication in the L band Design of an automated information.processing [DFVLR-FB-86-47] p 701 N87-26259 system p 704 A87-44241 fighter aircraft [AIAA PAPER 87-1929] p 681 A87-45307 SPRING, S. D. SCHULTZ, D. L SHEVELEV, IURII DMITRIEVICH Friction factors and heat transfer coefficients in The role of short duration facilities in gas turbine Three-dimensional problems in computational fluid turbulated cooling passages of different aspect ratios. I - research p 685 A87-46222 dynamics p 693 A87-42916 Experimental results SCHULTZ, K. J. SHILO, S. N. [AIAA PAPER 87-2009] p 696 A87-45350 A comparison of the acoustic and aerodynamic Efficiency of the utilization of rotor blade shroud labyrinth SRINIVASA, K. measurements of a model rotor tested in two anechoic seals in an axial-compressor stage with large radial Erosion problem of axial compressor blades of a wind tunnels p 683 A87-43425 clearances p 694 A87-43611 turboshaft engine p 675 A87-46246

B-12 PERSONAL AUTHOR INDEX UCHIKADO, SIGERU

SRIVASTAVA, B. N. SUBOCHEV, S. D. TENEROWICZ, THOMAS Navier-Stokes solutions for highly loaded turbine Errors in the measurement of the course angles of radar Flow behind single- and dual-rotation propellers at angle cascades reference points due to the imprecise stabilization of the of attack [AIAA PAPER 87-2151] p 637 A87-45436 antenna mounting in bank and pitch [AIAA PAPER 87-1750] p 634 A87-45183 STACK, J. P. p 649 A87-44312 TERRY, P. JOHN A unique measurement technique to study SUBRAHMANYAM, K. B. Aero-optical analysis of compressible flow over an open laminar-separation bubble characteristics on an airfoil Influence of third-degree geometric nonlinearities on the cavity [AIAA PAPER 87-1271] p 631 A87-44921 vibration and stability of pretwisted, praconed, rotating [AIAA PAPER 87-1399] p 632 A87-44943 blades p 674 A87-46228 STAHL, H. TERT'IACHENKO, G. N. Application of a 3D Euler code to transonic blade tip SUGIYAMA, Y. A study of the thermal-stress state of gas turbine engine flow p 628 A87-43419 J85 surge transient simulation p 675 A87-46240 blades with protectNe coatings p 664 A87-43640 SUHS, N. E. STAHL, HEIDEMARIE THOMAS, SCOTt" R. Experience with 3-D composite grids Application of a three-dimensional Euler code to Test flow calibration study of the Langley Arc-Heated p 706 N87-26021 transonic blade tip flow Scramjet Test Facility SULLINS, GARY A. [MSB-UD-482/86] p 642 N87-25299 [AIAA PAPER 87-2165] p 685 A87-45445 Force accounting for airframe integrated engines STAINBACK, P. C. THOMPKINS, W. T. [AIAA PAPER 87-1965] p 636 A87-45334 Designing transonic wind-tunnel test sections for flow Application of computational physics within Northrop SUNDARARAJAN, S. diagnostics and laser velocimeter applications p 706 N87-26008 Finite element analysis of large spur and helical gear [AIAA PAPER 87-1434] p 684 A87-44954 THOMPSON, THOMAS LEE systems Velocity measurements near the blade tip and in the STALKER, R. J. [AIAA PAPER 87-2047] p 697 A87-45379 tip vortex core of a hovering model rotor Scramjet testing in impulse facilities SUPPLEE, FRANK H., JR. p 685 A87-46183 p 645 N87-26030 A miniature remote deadweight calibrator THOMSON, D. G. Hydrogen scramjet with sidewall injection - Shock tunnel p 694 A87-45104 An analytic method of quantifying helicopter agility simulations p 674 A87-46217 Miniature remote dead weight calibrator p 678 A87-43432 Pressure scaling effects in a scramjet combustion [NASA-CASE-LAR-13564-1] p 700 N87-25558 TICH, ERIC J. chamber p 676 A87-46258 SWAN, JERRY A. Performance seeking control for cruise optimization in Performance seeking control for cruise optimization in STALLCOP, J. R. fighter aircraft High temperature transport properties of air fighter aircraft [AIAA PAPER 87-1929] p 681 A87-45307 [AIAA PAPER 87-1632] p 707 A87-43129 [AIAA PAPER 87-1929] p 681 A87-45307 TIMM, R. STEENKEN, W. O. SWANSSON, N. S. Compressible flows in the wakes of a square cylinder Application of engine component life methodology to Dynamic data acquisition, reduction, and analysis for and thick symmetrical airfoil arranged in tandem life assessment p 698 A87-46230 the identification of high-speed compressor component p 641 A87-46922 SWEETMAN, BILL post-stability characteristics TIMNAT, Y. M. [AIAA PAPER 87-2089] p 697 A87-45398 The new Soviet fighters - How good are they? Diagnostics in supersonic combustion STEFKO, GEORGE L. p 656 A87-46312 [AIAA PAPER 87-1787] p 690 A87-45202 Wind tunnel performance results of an aaroelastically SWIHART, JOHN M. Diagnostic methods for air-breathing engines US aeronautical R&D goals - SST: bridge to the next scaled 2/9 model of the PTA flight test prop-fan p 686 A87-46243 century p 624 A87-46182 [NASA-TM-89917] p 642 N87-25294 TINDELL, R. H. SZODRUCH, JOACHIM STEINMETZ, RONALD B. Highly compact inlet diffuser technology An experimental investigation of a suporcritical airfoil Engine variable geometry effects on commercial [AIAA PAPER 87-1747] p 666 A87-45180 supersonic transport development at transonic speeds TJALSMA, C. R. [AIAA PAPER 87-1241] p 630 A87-44914 [AIAA PAPER 87-2101] p 872 A87-45406 Development of a flexible and economic helicopter STENGEL, ROBERT F. engine monitoring system p 663 A87-43466 Unresolved issues in wind shear encounters T TOMLINSON, B. N. p 647 N87-25282 Motion software for a research flight simulator STENZEL, SIEGFRIED T'IEN, JAMES S. p 704 A87-44713 Development and testing of critical components for the Application of low-Reynolds-number K-epsilon model to TONG, BINGGAHG technological preparation on an Airbus fuselage made of solid fuel turbulent boundary layer combustion A panel method for prediciting the dynamic stability carbon fiber reinforced plastics, phase 1 [AIAA PAPER 87-1778] p 690 A87-45198 derivatives of an oscillating wing in high subsonic flow [BMFT-FB-W-86-017] p 692 N87-26151 TABAKOFF, W. p 641 A87-46951 STEVENS, SoJ. J85 surge transient simulation p 675 A87-46240 TORELLA, G. The influence of dilution hole aerodynamics on the TALBERT, P° S. Simulation of performance, behaviour and faults of temperature distribution in a combustor dilution zone Complex modal balancing of flexible rotors including aircraft engines [AIAA PAPER 87-1827] p 666 A87-45232 residual bow [AIAA PAPER 87-1868] p 668 A87-45263 STEWART, H. TORNATORE, ANTHONY S. [AIAA PAPER 87-1840] p 695 A87-45241 Vortex-nozzle interactions in ramjet combustors The AVSCOM flight safety part program TAN, HUNG [AIAA PAPER 87-1871 ] p 888 A87-45266 p 647 A87-46724 Tomographic reconstruction of three-dimensional flow STEWART, P. A. E. over airfoils TREBBLE, W. J. G. Real-time neutron imaging of gas turbines [AD-A179976] p 643 N87-25300 Investigation of the aerodynamic performance and noise [AIAA PAPER 87-1762] p 895 A87-45189 characteristics of a 1/Sth scale model of the Dowry Rotol TAPAVICZA, M. STIEFEL, WILLIAM R. R212 propeller p 640 A87-46265 Damage tolerance concepts for modern helicopters State-of-the-art test facilities for development of the p 653 A87-43449 Aerodynamics of unmanned aircraft at full-scale in the Army's T800-LHT-800 LHX helicopter engine RAE 24ff wind-tunnel TAPE, ROBERT F. [AIAA PAPER 87-1790] p 684 A87-45204 STOL characteristics of a tactical aircraft with thrust [RAE-TM-AERO-2081] p 645 N87-26027 STOCK, MICHAEL TRIESCH, KLAUS vectoring nozzles EMI-fault prevention and self recovery of digital flight [AIAA PAPER 87-1835] p 655 A87-45237 The vertical test section (VMK) of DFVLR in control systems p 661 A87-43470 Cologne-Porz, West Germany STOCKBRIDGE, R. D. TASLIM, M. E. Friction factors and heat transfer coefficients in [DFVLR-MITT-86-22] p 688 N87-26054 A computational method for determining flowfield turbulated cooling passages of different aspect ratios. I - TRIVEDI, KISHOR S. properties when the pitot pressure is the only measured Experimental results Analysis of typical fault-tolerant architectures using instream property p 637 A87-46184 [AIAA PAPER 87-2009] p 696 A87-45350 HARP p 704 A87-45771 STONE, R. H. TAUBER, MICHAEL E. TROLINGER, JAMES D. Flight service evaluation of advanced composite ailerons The thermal environment of transatmospheric vehicles Tomographic reconstruction of three-dimensional flow on the L-1011 transport aircraft over airfoils [AIAA PAPER 87-1514] p 626 A87-43038 [NASA-CR-178321 ] p 691 N87-25439 TAYLOR, J. E. [AD-A179976] p 643 N87-25300 STRAZlSAR, A. J. F-15/F100 digital electronic engine control main fuel TROUVE, A. An LDA investigation of three-dimensional normal gear pump field service evaluation Vortex-nozzle interactions in ramjet combustors shock-boundary layer interactions in a corner [AIAA PAPER 87-1871] p 668 A87-45266 [AIAA PAPER 87-1846] p 667 A87-45246 [AIAA PAPER 87-1369] p 632 A87-44938 TAYLOR, J. H. TU, YONGKANG STREHLOW, HENNING Research on the stress analysis method of rubber Dynamic data acquisition, reduction, and analysis for Development of novel bearingless rotor systems structure - Calculation of the frequency adapter stresses the identification of high-speed compressor component [MBB-UD-471/86] p 702 N87-26837 p 693 A87-43453 post-stability characteristics STRGANAC, THOMAS W. [AIAA PAPER 87-2089] p 697 A87-45398 TYSELL, LARS G. The numerical simulation of subsonic flutter Development of a geometry handling program for the TAYLOR, P. [AIAA PAPER 87-1428] p 633 A87-44952 FFA subsonic higher order panel method Investigation of helicopter twin-rotor characteristics STRIZ, ALFRED G. [FFA-TN-1985-48] p 699 N87-25534 p 628 A87-43438 Finite element analysis and redesign of jet engine starter breech chamber An improved assumed mode method for estimating the motion of a nonuniform rotor blade p 853 A87-43445 [ASME PAPER 86-WA/DE-20] p 664 A87-43702 U STUDERUS, C. J. TCHENG, PING Design applications for supercomputers A miniature remote deadweight calibrator UCHIKADO, SIGERU p 706 N87-26010 p 894 A87-45104 An approach to the synthesis of an adaptive flight control STURGESS, G. J. TEN HAVE, A. A. system with incomplete information p 680 A87-45096 Application of CFD codes to the design and development Development of a flexible and economic helicopter Design of CCV flight control system of STOL flying of propulsion systems p 677 N87-26009 engine monitoring system p 663 A87-43466 beat p 680 A87-45097

B-13 UENISHI, K. PERSONAL AUTHOR INDEX

UENISHI, K. Aerodynamic study of a helicopter rotor in hovering flight WELLEN, HEINRICH Three-dimensional numerical predictions of the flow * Theory vs. experiment p 641 A87-47014 Industrial application of computer aided structural behind a rearward-facing-step in a supersonic combustor optimization in aircraft construction [AIAA PAPER 87-1962] p 636 A87-45332 [MBB-UT-273/86] p 706 N87-26523 UNDERWOOD, F. N. W WETZEL, D. Development of Digital Engine Control System for the Canard configurations Harder II WAGNER, BERNHARD [ETN-87-99914] p 659 N87-26039 [AIAA PAPER 87-2184] p 673 A87-45458 Aerothermodynamic computations for WHITE, J. A. UNNIKRISHNAN, V. super-/hypersonic flight p 640 A87-46328 Aerodynamic and heat transfer analysis of the low aspect Erosion problem of axial compressor blades of a WAGNER, SIEGFRIED ratio turbine turboshaft engine p 675 A87-46246 An advanced mathematical model for helicopter flight [AIAA PAPER 87-1916] p 696 A87-45296 simulation using nonlinear unsteady serodynamics V p 679 A87-43435 WHITE, JEFFREY A. WAGNER, TIMOTHY C. Numerical analysis of peak heat transfer rates for Design and evaluation of a new injector configuration hypersonic flow over a cowl leading edge VADYAK, JOSEPH for supersonic combustion p 674 A87-46218 [AIAA PAPER 87-1895] p 635 A87-45283 Navier-Stokes simulations of supersonic fighter intake WAI, JOHN C. flowfields WHITELAW, J. H. Navier-Stokes simulation of a hypersonic generic Flow over a trailing flap and its asymmetric wake [AIAA PAPER 87-1752] p 634 A87-45185 VAINBERG, MARK VLADIMIROYICH wing/fuselage p 626 A87-43376 [AIAA PAPER 87-1192] p 629 A87-44902 Honeycomb structures: Parameter selection and WlGHTMAN, J. P. WALKER, A. R. design p 693 A87-42914 Factors affecting the sticking of insects on modified Experimental application of strain pattern analysis (SPA) VAN DEn VAART, J. C. aircraft wings - Wind tunnel and flight test results p 654 A87-43459 Some fundamentals of simulator cockpit motion [NASA-CR-180957] p 659 N87-26037 WALKER, J. M. generation p 683 A87-44714 Visualization of three*dimensional structures about a WILLIAMS, B. R. VAN WIE, DAVID M. pitching forward swept wing Viscous-inviscid interactions in external aerodynamics Efficiency parameters for inlets operating at hypersonic [AIAA PAPER 87-1322] p 631 A87-44929 p 626 A87-43299 speeds p 638 A87-46189 WALKER, JOHN M. WILLIAMS, M. H. VANDEKREEKE, C. Forced unsteady vortex flows driven by pitching A panel method for counter rotating propfans The interference of the model support mast with airfoils [AIAA PAPER 87-1890] p 668 A87-45279 measurements of the longitudinal and lateral aerodynamic coefficients [AIAA PAPER 87-1331] p 631 A87-44931 WlLLIAMSON, J. R. WALSH, JOANNE L. [NASA-Tr-20079] p 644 N87-25307 Superplastic forming/diffusion bonding of titanium Optimization methods applied to the aerodynamic design VANDER HOEK, T. J. p 689 A87-44747 of helicopter rotor blades An experimental investigation of turbine case WILSON, J. R. [NASA-TM-89155] p 660 N87-26042 treatments Use of RPM trim to automate the supersonic engine/inlet WALSH, KEVIN R. [AIAA PAPER 87-1919] p 669 A87-45299 match in the SR-71A Preliminary flight results of an adaptive engine control VARETTI, MAURO [AIAA PAPER 87-1848] p 667 A87-45248 system of an F-15 airplane Application of a 3D inviscid rotational design procedure [AtAA PAPER 87-1847] p 667 A87-45247 WlSSLER, J. B. for turbomachinery bladings p 638 A87-46204 WANG, CHENGZENG Visualization of three-dimensional structures about a VAUGHAN, J. M. The pitching damping derivatives measured by pitching forward swept wing An airborne laser air motion sensing system. I - Concept force-oscillation method at transonic and supersonic wind [AIAA PAPER 87-1322] p 631 A87-44929 and preliminary experiment p 662 A87-45732 tunnel p 686 A87-46958 VELKOFF, HENRY R. wrrruN, GIL WANG, T. Measurement of side forces of a H-force rotor KRASH analysis correlation. Transport airplane Maximum survival capability of an aircraft in a severe controlled impact demonstration test p 651 A87-43410 windshear p 660 A87-44254 VENKATARAJU, K. [AD-A179906] p 647 N87-25308 WANG, X. F. Microprocessor based surge monitoring system WONG, KAM L. Influence of fuel temperature on atomization p 686 A87-46241 Culprits causing avionic equipment failures performance of pressure-swirl atomizers VERHAAGEN, N. G. p 662 A87-46727 p 698 A87-46198 Entrainment effect of a leading-edge vortex WANGE, GOETZ WOOD, CHARLES W. p 641 A87-46777 Going beyond the limits, Aviation in Germany Airbreathing propulsion system design at the United VERRIERE, J. [SO-1-87] p 710 N87-26853 States Air Force Academy - An integrated approach The interference of the model support mast with WANSTALL, BRIAN [AIAA PAPER 87-1870] p 709 A87-45265 measurements of the longitudinal and lateral aerodynamic coefficients DVI in the military cockpit - A third hand for the combat WOOD, RICHARD M. pilot p 681 A87-46315 Study of lee-side flows over conically cambered Delta [NASA-TT-20079] p 644 N87-25307 WARD, B. 0. wings at supersonic speeds, part 2 VIERKORN-RUDOLPH, B. Advantages of thrust vectoring for STOVL [NASA-TP-2660-PT-2] p 643 N87-25301 Large-scale distribution of peroxyacetylnitrate results [AIAA PAPER 87-1708] p 665 A87-45156 from the STRATOZ III flights p 702 A87-46481 A multi-body aircraft with an all-movable center fuselage WARD, JOHN F. VINCENT, B. actively controlling fuselage pressure drag Rotorcraft research - A national effort (The 1986 Mechanical evaluation of the aeroelastic behaviour of [NASA-CASE-LAR-13511-1 ] p 658 N87-25320 Alexander Nikolsky Honorary Lectureship) a fan blade p 675 A87-46248 WORM, CHARLES M. p 623 A87-44255 VISBAL, MIGUEL R. The real world - A maintainers view WARNECKE, J. Numerical investigation of the flow structure around a p 624 A87-46708 Effects of impact loading on carbon fiber reinforced rapidly pitching airfoil structures WORST, TIMOTHY W. [AIAA PAPER 87-1424] p 633 A87-44951 [MBB-Z-83/86] p 691 N87-25436 A rugged electronic pressure scanner designed for VOGEL, P. G. WARREN, R. turbine test p 695 A87-45124 Two-dimensional numerical analysis for inlets at A program to investigate requirements for effective flight WRIGHT, V. A. subsonic through hypersonic speeds simulator displays p683 A87-44715 [AIAA PAPER 87-1751] p 634 A87-45184 Use of R PM trim to automate the supersonic engine/inlet WARWICK, GRAHAM match in the SR-71A VOLAND, RANDALL T. EH.101 - The helicopter matures p 657 A87-46371 [AIAA PAPER 87-1848] p 667 A87-45248 Test flow calibration study of the Langley Arc-Heated WATKINS, WILLIAM B. Scramjet Test Facility A noninterference blade vibration measurement system wg, CHI-HUA [AIAA PAPER 87-2165] p 685 A87-45445 for gas turbine engines Application of a fuzzy controller in fuel system of turbojet VOLOSHIN, lU. I. [AIAA PAPER 87-1758] p 695 A87-45186 engine p 674 A87-46227 Selection of admissible contact stresses for toothed WATSON, CAROLYN B. WU, J. L. gears of aircraft engines p 663 A87-43605 Study of lee-side flows over conically cambered Delta Linear instability waves in supersonic turbulent mixing YON BACKSTROM, T. W. wings at supersonic speeds, part 2 layers Expendable turbojet compressor design, test and [NASA-TP-2660-PT-2] p 643 N87-25301 [AIAA PAPER 87-1418] p 633 A87-44948 development p 674 A87-46212 WEBSTER, G. YON GLAHN, UWE H. EH101 cockpit design p 661 A87-43404 Two-dimensional nozzle plume characteristics WEEKS, D. J. X [AIAA PAPER 87o2111 ] p 636 A87-45413 The air*injection method of fixing boundary-layer Secondary stream and excitation effects on transition and investigating scale effects two-dimensional nozzle plume characteristics p 639 A87-46264 XIAO, ZHENHUA WEINGOLD, H. D. [AIAA PAPER 87-2112] p 637 A87-45414 Fast methods applied to the calculation of transonic Application of CFD codes to the design and development airfoils p 641 A87-46962 VON OHAIN, HANS of propulsion systems p 677 N87-26009 The origins and future possibilities of air breathing jet XU, XlN-YU WEISS, ROSANNE M. propulsion systems p 709 A87-46178 The influence of the induced velocity distribution and Heliport visual approach surface testing test plan YON TEIN, VOLKER the flapping-lagging coupling on the derivatives of the rotor {AD-A179897] p 650 N87-25312 and the stability of the helicopter p 679 A87-43436 Helicopter activities in Germany p 623 A87-43401 WELCH, B. L. VUILLET, A. Engineering and human visual considerations in XU, YUN-HUA New aerodynamic design of the fenestron for improved development of a fibre optic helmet mounted display Application of a fuzzy controller in fuel system of turbojet performance p 651 A87-43403 p 661 A87-44727 engine p 674 A87-46227

B-14 PERSONAL AUTHOR INDEX ZUKOSKI, EDWARD E. Y

YAHYA, S. M. Effect of swirl on the performance of a radial vaneless diffuser with compressible flow at Mach numbers of 0.7 and 0.8 [ASME PAPER 86-WA/FE-6] p 629 A87-43704 YAJNIK, K. S. Underexpanded jet-free stream interactions on an axisymmetric afferbody configuration p 639 A87-46232 YAMAUCHI, GLORIA K. Correlation of SA349/2 helicopter flight-test data with a comprehensive rotorcraft model p 653 A87-43456 YANG, J. Y. Aerodynamic design modification of a hypersonic wind tunnel nozzle by CSCM with high order accuracy [AIAA PAPER 87-1896] p 635 A87-45284 YI, O. Factors affecting the sticking of insects on modified aircraft wings [NASA-CR-180957] p 659 N87-26037 YILLIKCl, Y. K. Optimum design of a helicopter rotor blade p 651 A87-43406 YOSHIDA, KENJI Study on the interference between the local separation on a wing surface and outer flow-field p 634 A87-45094 YOUNG, B. Finite element analysis of large spur and helical gear systems [AIAA PAPER 87-2047] p 697 A87-45379 YOUNG, LARRY A. Performance and loads data from a hover test of a 0.658-scale V-22 rotor and wing [NASA-TM-89419] p 642 N87-25296 YOUNG, M. F. Standing oblique detonation wave engine performance [AIAA PAPER 87-2002] p 670 A87-45347 YU, K. Vortex-nozzle interactions in ramjet combustors [AIAA PAPER 87-1871] p 668 A87-45266 Z

ZHANG, QIWEI Two-dimensional subsonic and transonic wind tunnel wall interference corrections for varied walls p 686 A87-46955 ZHANG, ZHONGYIN Fast methods applied to the calculation of transonic airfoils p 641 A87-46962 ZHANGJIN Research on the stress analysis method of rubber structure - Calculation of the frequency adapter stresses p 693 A87-43453 ZHAO, XIAOLU Transonic stream function solution on S(2) streamsurface for a high pressure ratio centrifugal compressor p 638 A87-46195 ZHUANG, LlXlAN A panel method for prediciting the dynamic stability derivatives of an oscillating wing in high subsonic flow p 641 A87-4695t ZlMMER, FRIEDHELM Dornier 328 - Concept for a new-generation regional airliner p 657 A87-46326 ZOELLNER, M. Realization and flight testing of a model following control system for helicopters p 679 A87-43440 ZUBOV, N. M. Calculation of the boundary layer at the inlet section of a compressor cascade p 629 A87-43608 ZUKOSKI, EDWARD E. Progress toward shock enhancement of supersonic combustion processes [AIAA PAPER 87-1880] p 690 A87-45274

B-15 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 219) November 1987

Typical Corporate Source Index Listing Arizona Univ., Tucson. D Computation of unsteady transonic aerodynamics with truncation error injection p 627 A87-43392 Delta Air Lines, Inc., Atlanta, Ga. Army Aviation Research and Development Command, Maximum survival capability of an aircraft in a severe Hampton, Vs. windshear p 680 A87-44254 CORPORATE SOURCE I Rotor design for maneuver performance Deutsche Forschungs- und Versuchssnstalt fuer Luft- p 652 A87-43431 und Rsumfahrt, Brunswick (West Germany). Effect of planform taper on hover performance of an A comparison of the acoustic and aerodynamic advanced AH-64 model rotor measurements of a model rotor tested in two anechoic i [NASA-TM.89145] p 643 N87-25304 wind tunnels p 683 A87-43425 Army Aviation Systems Command, St. Louis, Mo. Preliminary structural design of composite main rotor Deutsche Forsohungs- und Versochunstalt fuer Luft- io Summary of artificial and natural icing tests conducted blades for minimum weight und Raumfahrt, Cologne (West Germany). n US Army aircraft from 1974 to 1985 [NASA-TP-2730] p 691 N87-25435 The 0.6 m x 0.6 m tdsonic section (TMK) of DFVLR in Army Aviation Systems Command, Moffett Field, Calif. Cologne-PoFz, West Germany Measurement of side forces of a H-force rotor [DFVLR-MITT-86-21 ] p 687 N87-26053 p 651 A87-43410 The vertical test section (VMK) of DFVLR in Full potential modeling of blade-vortex interactions Cologne-Porz, West Germany p 627 A87-43417 [DFVLR-MITT-86-22] .p 688 N87-26054 I _'_]_NASA_IFAA/CT-85/261 _1 p 25 N87-10064 Unsteady separation characteristics of airfoils operating under dynamic stall conditions p 628 A87-43421 Deutsche Forschungs- und Versuchssnstslt fuer Luft- A comparison of the acoustic and aerodynamic und Raumfahrt, Goettingen (West Germany). "-I TITLE I I n,,';;,_;_'l I ,,;,_'_='_1 I ACCESSION I measurements of a model rotor tested in two anechoic Unsteady separation characteristics of airfoils operating I "UMBERI wind tunnels p 683 A87-43425 under dynamic stall conditions p 628 A87-43421 Army Propulsion Lab., Cleveland, Ohio. Deutsche Forschungs- und Versuchssnstalt fuer Luft- Contingency power for small turboshaft engines using und Raumfshrt, Oberpfaffenhofsn (West Germany). water injection into turbine cooling air A conformal aircraft phased array antenna for Listings in this index are arranged alphabetically by [AIAA PAPER 87-1906] p 668 A87-45289 airplane-satellite communication in the L band [DFVLR-FB-86-47] p 701 N87-26259 corporate source. The title of the document is used Avco-Everstt Research Lab., Mass. Experimental data correlations for the effects of rotation Experiences with hot-wire instruments for the to provide a brief description of the subject matter. on impingement cooling of turbine blades measurement of the liquid water content in clouds The page number and the accession number are [AIAA PAPER 87-2008] p 696 A87-45349 [DFVLR-MITT-86] p 704 N87-26476 included in each entry to assist the user in locating Deutsche Forschungs- und Versuchssnstalt fuer Lutt- the abstract in the abstract section. If applicable, B und Rsumfshrt, Stuttgart (West Germany). Canard configurations a report number is also included as an aid in [ETN-87-99914] p 659 N87-26039 Boeing Co., Seattle, Wash. identifying the document. Drexel Univ., Philadelphia, PS. Navier-Stokes simulation of a hypersonic generic Degradation mechanisms of sulfur and nitrogen wing/fusolage containing compounds dudng thermal stability testing of [AIAA PAPER 87-1192] p 629 A87-44902 model fuels Boeing Commercial Airplane Co., Seattle, Wash. [AIAA PAPER 87-2039] p 690 A87-45372 Microburst model requirements for flight simulation: An Duke Univ., Durham, N. C. A aidrame manufacturer's perspective Analysis of typical fault-tolerant architectures using p 687 N87-25278 HARP p 704 A87-45771 Bucknell Univ., Lswiaburg, Pa. Aerodyns Products Corp., Billerlce, Mass. Case histories involving fatigue and fracture mechanics; Portable fuel leak detector Proceedings of the Symposium, Charleston, SC, Mar. 21, [AD-At80095] p 700 N87-25550 E 22, 1985 p 692 A87-42851 Aeronautical Research Inst. of Sweden, Stockholm. The Aeronautical Research Institue (FFA] wing body 85 Ecole Polytechnlque Foderale de Lausanne computer program. A panel method for determination of C (Switzerland). aeroelastic characteristics applying direct block iterative Aeroelasticity in turbomachines comparison of solution techniques CAE Industries, Ltd., Montreal (Quebec). theoretical and experimental cascade results. Appendix [FFA-TN-1986-28] p 642 N87-25298 Simulator manufacturers' requirements A5: All experimental and theoretical results for the 9 Development of a geometry handling program for the p 687 N87-25280 standard configurations FFA subsonic higher order panel method California State Univ. st Long Beach. (AD-A180534] p 677 N87-25326 [FFA-TN-1985-48] p 699 N87-25534 Unsteady separation characteristics of airfoils operating Eloret Corp., Sunnyvale, Calif. Measurement of noise from airplanes traveling at 3500 under dynamic stall conditions p 628 A87-43421 The thermal environment of transatmospheric vehicles to f 1000 m altitude California Univ., Davis. [AIAA PAPER 87-1514] p 626 A87-43038 [FFA-TN-1986-21] p 708 N87-25824 Vortex breakdown simulation ESDU Intsmstlonel Ltd., London (England). Aeronautical Systems DIv., Wright-Patterson AFB, [AIAA PAPER 87-1343] p 632 A87-44934 Aerofoil maximum lift-coefficient for Mach numbers up Ohio. California Univ., Irvlns. to 0.4 Correlation of B-1 flight test subjective assessments and Volume interchange factors for hypersonic vehicle wake [ESDU-84026] p 645 N87-26028 some ride quality/vibration exposure criteria radiation An introduction to time-dependent aerodynamics of ]AD-A179844] p 658 N87-25318 [AIAA PAPER 87-1520] p 707 A87.43044 aircraft response, gusts and active controls Air Force Wright Aeronautical Labs., Wright-Patterson California Univ., Los Angeles. [ESDU-84020] p 682 N87-26048 AFB, Ohio. Recent trends in rotary-wing aeroelasticity First approximation to landing field length of civil Experimental study of the vortex flow behavior on a p 652 A87-43442 transport aeroplanes (50 ft., 15.24 m screen) generic fighter wing at subsonic and transonic speeds Cslspsn Corp., Buffalo, N. Y. [ESDU-84040] p 688 N87-26056 [AIAA PAPER 87-1262] p 631 A87-44920 Military specifications p 658 N87-25281 Estimation of spillage drag for a wide range of axisymmetric intakes at M 1 Investigation of a delta.wing fighter model flow field at Caiapsn Field Services, Inc., Amold AFS, Tenn. [ESDU.84004] p 701 N87-26301 transonic speeds Experience with 3-D composite grids The treatment of calibrations of total air temperature [AIAA PAPER 87-1749] p 634 A87-45182 p 706 N87-26021 probes for use in flight-test analysis work Exploratory evaluation of a moving-model technique for City Univ., London (England). [ESDU-84007] p 701 N87-26324 measurement of dynamic ground effects Helicopter vibration control: Recent advances [AIAA PAPER 87-1924] p 685 A87-45303 p 660 N87-26247 Alabama Univ., University. Colorado Univ., Boulder. F Helicopter-V/STOL dynamic wind and turbulence design Experimental studies on the dynamic development and methodology p 658 N87-25284 control of unsteady separated flows p 642 N87-25297 Federal Aviation Administration, Washington, D.C. Analytical Services and Materials, Inc., Hampton, Vs. Connecticut Univ., Storrs. Case history of FAA/SRI wind shear models A unique measurement technique to study Dual adaptive control: Design principles and p 703 N87-25268 laminar-soparation bubble characteristics on an airfoil applications History of wind shear turbulence models [AIAA PAPER 87-1271] p 631 A87-44921 [NASA-CR.181050] p 705 N87-25804 p 703 N87-25269

C-1 Federal Aviation Agency, Atlantic City, N.J. CORPORA TE SOURCE

Federal Aviation Agency, Atlantic City, N.J. Kentucky Univ., Lexington. A model test vehicle for hypersonic aerospace systems Heliport visual approach surface testing test plan Determination of the local heat transfer characteristics development [AD-At79897] p 650 N87-25312 on glaze ice accretions on a cylinder and a NACA 0012 [MBB-UR-875/86] p 658 N87-25314 Flight Safety International, Inc., Tulsa, Okla. airfoil The role of simulation in helicopter development Simulator systems integration p 687 N87-25283 [AD-Af79931] p 647 N87-25309 [MBB-UD-435/86] : p 687 N87.25333 FWG Associates, Inc., Tullshome, Tenn. KLM Royal Dutch AIHInee, Amsterdam (Netherlands). Research and development. Technical-scientific Modeling and implementation of wind shear data Fuel saving and fuel related subjects within an airline's publications 1986 p 709 N87-25273 operational environment ]ETN-67-99713] p 710 N67-26626 Turbulence models p 703 N87-25277 [ETN-87-90148] p 648 N87-26034 Use of artificial intelligence methods [MBB-LKE-434-S/PUB/284] p 707 N87.26831 Euler solution for a complete fighter aircraft at sub- and G L supersonic speed [MBB-LKE-122-S/PUB/234] p 660 N87-26833 Gerrett Turbine Engine Co., Phoenix, Adz. Lockheed-California Co., Burbank. Aircraft technology of the nineties in MBB passenger Durability charactedzation of ceramic materials for gas KRASH analysis correlation. Transport airplane aircraft projects turbines p 690 A87.45898 controlled impact demonstration test [MBB-UT-0021/86] p 660 N87-26834 Compound cycle engine for helicopter application [AD-A179906] p 647 N87-25308 Integration of the propfan concept in aircraft design [NASA-CR-175110] p677 N87-25323 ]MBB-UT-0001/86] p 677 N87-26835 General Oynemlcs Corp., St. Louis, Mo. Flight service evaluation of advanced composite ailerons on the L.f0t 1 transport aircraft Conceptual studies of control systems for wings with Computational fluid dynamics: Transition to design variable camber [NASA-CR-178321] p 691 N87-25439 applications p 700 N87-26004 [MBB-UT-221/86] p 682 N87-26836 General Electric Co,, Cincinnati, Ohio. CFD applications: The Lockheed perspective p 644 N87-26005 Development of novel bearingless rotor systems Scale model test results of a thrust reverser concept [MBB-UD-471/86] p 702 N67-26837 Lockheed-Georgia Co., Marietta. for advanced multi-functional exhaust systems Avionics systems for future civil helicopters Wind tunnel tests on a one-foot diameter SR-7L propfan [AIAA PAPER 87-1833] p 667 A87-45235 [MBB-UD-473/86] p 662 N87-26838 model Parametric study of single expansion ramp nozzles at Mluourl Univ., Rolla. [AIAA PAPER 87-1892] p 635 A87-45281 subsonic/transonic speeds A comparison of the structurebome and airborne paths [AIAA PAPER 87-1836] p 635 A87-45238 for propfan interior noise Dynamic data acquisition, reduction, and analysis for M ]NASA.CR-180289] p 708 N87-26612 the identification of high-spesd compressor component pest.stability characteristics Manudyne Systems, Inc., Los Altos, Calif. [AIAA PAPER 87-2089] p 697 A87-45398 N Study of helicopterroll control effectiveness cdteria Design applications lor supercomputers [NASA.CR-177404] p 681 N87.25330 p 706 N87-26010 National Aeronautics and Space Administration, Maryland Univ., College Park. General Electric Co,, Evendale, Ohio. Washington, D.C. Gust response of helicopters p 682 N87-26049 NASA/GE advanced low emissions combustor Civil propulsion technology for the next twenty-five Massachusetts Inst. of Tech., Cambridge. program years p 624 A87-46177 Helicopter individual-blade-control research at MIT ]AIAA PAPER 87-2035] p 671 A87.45369 Recent progress in the measurement of the drag 1977-1985 p 679 A87-43446 General Electric Co., ScheneCtady, N.Y. coefficients of models of transport aircraft in a wind Compadson of wet and dry growth in artificial and flight Dynamic data acquisition, reduction, and analysis for tunnel icing conditions p 646 A87-45635 the identification of high-apeed compressor component [NASA.TT-20096] p 644 N87-25306 An experimental low Reynolds number comparison of pest-stability characteristics The interference of the model support mast with a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil and [AIAA PAPER 87-2089] p 697 A87-45398 measurements of the longitudinal and lateral aerodynamic a NACA 64-210 airfoil in simulated heavy rain Georgia Inst. of Tech., Atlanta. coefficients [NASA.CR-f81119] p 644 N87-25997 Rotor design for maneuver performance [NASA-TT-20079] p 644 N87-25307 McDonnell Aircraft Co., St. Louis, Mo. p 652 A87-43431 National Aeronautics and Space Administration. Ames investigation of a delta-wing fighter model flow field at Velocity measurements near the blade tip and in the Research Center, Moffett Field, Calif. transonic speeds tip vortex core of a hovering model rotor Failure analysis of a large wind tunnel compressor [AIAA PAPER 87-1749] p 634 A87-45182 p 645 N87-26030 blade p 692 A87-42652 Viscid/inviscid separated flows The thermal environment of transatmosphedc vehicles An investigation of helicopter higher harmonic control [AD-A179856] p 699 N87-25536 [AIAA PAPER 87-1514] p 626 A87-43038 using a dynamic system coupler simulation McDonnell-Douglas Corp., St. Louis, Mo. High temperature transport properties of air p 682 N87-26051 Numerical simulation and comparison with experiment for self-excited oscillations in a diffuser flow [AIAA PAPER 87-1632] p 707 A87-43129 Numerical simulation and comparison with expedment p 693 A87.4338t H for self-excited oscillations in a diffuser flow McDonnell-Douglas Research Labs., St. Louis, Mo. p 693 A87-43381 Computational fluid dynamics applications at McDonnel Thermal and flammability characterization of graphite Hamlhon Standard, Wl_r Locks, Conn. Douglas p 701 N87-26007 composites p 688 A87-43398 Results of acoustic tests of a Prop-Fan model Momrechmltt-Boelkow-Blohm G.m.b.H., Bremen [AIAA PAPER 87-1894] p 707 A87-45282 (Wast Germany). Calculated performance, stability, and maneuverability High Technology Corp., Hampton, Vs. An experimental investigation of a supercritical airfoil of high-speed tilting-prop-rotor aircraft Stationary disturbances in three-dimensional boundary at transonic speeds p 651 A87-43408 Measurement of side forces of a H-force rotor layers over concave surfaces [AIAA PAPER 87-1241] p 630 A87-44914 p 651 A87-43410 ]AIAA PAPER 87-1412] p 632 A87-44945 Analytical description of crack resistance curves for Full potential modeling of blade-vortex interactions Prediction and control of transition in hypersonic aluminum sheets used in aircraft construction p 627 A87-43417 boundary layers [MBB-UT-133/85] p 700 N87-25604 Unsteady separation characteristics of airfoils operating [AIAA PAPER 87-1414] p 632 A67-44946 Industrial application of computer aided structural under dynamic stall conditions p 628 A87-43421 optimization in aircraft construction Linear stability analysis of three-dimensional A comparison of the acoustic and aerodynamic [MBB-UT-273/86] p 706 N87-26523 compressible boundary layers p 640 A87-46504 measurements of a model rotor tested in two anechoic Meesarsehmltt-Boelkow-Blohm G.m.b,H., Hamburg wind tunnels p 669 A67-43425 (West Germany). Correlation of SA349/2 helicopter Sight-test data with I Design of a composite tail for the Airbus Ao320 a comprehensive rotorcraft model p 659 A87-43456 [MBB-UT-12-86] p 658 N87-25316 Navier-Stokes simulation of a hypersonic generic A310.300 CFRP fin damage teJlerance demonstration Idaho Univ., Moscow. wing/fuselage [MBB-UT-Ot5/86] p 658 N87-25317 Dynamic mechanical properties of advanced composite [AIAA PAPER 67-1192] p 629 A87-44902 Automated systems for the manufacture of Airbus materials and structures: A rewew p 691 N87-25988 vertical stabilizers Advances in the computation of transonic separated Info_tlon end Control Systems, Inc., Hampton, Vs. flows over finite wings [MBB-UT-17-86] p 705 N87-25786 A combined stochastic feedforward and feedback [AIAA PAPER 87-1195] p 630 A87-44904 Development and testing of critical components for the control design methodology with application to autotand Transonic analysis of the F-16A with under-wing fuel technological preparation on an Airbus fuselage made of design tanks - An application of the TranAir full.potential code carbon fiber reinforced plastics, phase 1 [NASA.CR-4078] p 705 N87-25806 [AIAA PAPER 87-1198] p 630 A87-44905 ]BMFT-FB-W-66-017] p 692 N87-26151 Simulation of transonic viscous flow over a fighter-like Inter Netlonos, Bonn (West Germany). Memmrechmltt-Boelkow-Blohm G.m.b,H., Munich (West Going beyond the limits. Aviation in Germany configuration including inlet Germany). [SO-1-67] p 710 N87-26653 [AIAA PAPER 87-1199] p 630 A87-44906 Design for repairability of helicopter rotor blades Numerical simulation of vortical flows over a strake-delta [MBB-UD-491/86] p 658 N87-25315 wing Effects of impact loading on carbon fiber reinforced K [AIAA PAPER 87-1229] p 630 A87-44913 structures [MBB-Z-83/86] p 691 N87-25436 An experimental investigation of a supercritical airfoil Kansas Univ., Lawrence. Mommrechmltt-Soelkow-Blohm G.m.b.H., Ottobrunn at transonic speeds Incompressible Navier-Stokes computations of vortical (Wast Germany). [AIAA PAPER 87-f241] p 630 A87-44914 flows over double-delta wings Aircraft technologies of the nineties in MBB passenger Experimental study of the vortex flow behavior on a [AIAA PAPER 87-1341] p 631 A87-44933 aircraft projects generic fighter wing at subsonic and transonic speeds Kansas Univ. Center for Research, Inc., Lawrence. [MBB-UT-21/86] p 625 N87-2529f [AIAA PAPER 87-1262] p 631 A87-44920 An experimental investigation of dynamic ground Application of a three-dimensional Euior code to Unsteady three-dimensional Navier-Stokes simulations effect transonic blade tip flow of turbine rotor-stator interaction [NASA-CR-180560] p 659 N87-26036 [MBB-UD-482/86] p 642 N87.25299 [AIAA PAPER 87-2058] p 636 A87-45386

C-2 Princeton Univ., N. J. CORPORA TE SOURCE

Influence of third-degree geometric nonlinearities on the Application of data to piloted simulators Effects of scale on supersonic combustor vibration and stability of pretwisted, preconed, rotating p 687 N87-25275 performance blades p 674 A87.46228 Performance and loads data from a hover test of a [AIAA PAPER 87-2164] p 672 A87-45444 Test flow calibration study of the Langley Arc.Heated Aeroelastic control of stability and forced response of 0.658-scale V-22 rotor and wing [NASA-TM-89419] p 642 N87-25296 Scramjet Test Facility supersonic rotors by aerodynamic detuning [AIAA PAPER 87.2165] p 685 A87-45445 p 676 A87-46249 On the nonlinear aerodynamic and stability Analysis of typical fault-tolerant architectures using Wind tunnel performance results of an aeroelastically characteristics of a generic chine-forebody slender-wing HARP p 704 A87.45771 scaled 2/9 model of the PTA flight test prop-fan fighter configuration Design and evaluation of a new injector configuration (NASA-TM-89917] p 642 N87-25294 [NASA-TM-89447] p 643 N87-25305 for supersonic combustion p 674 A87-46218 Numerical solution of the Navier-Stokes equations about Advanced detection, isolation and accommodation of Interdisciplinary optimum design p 657 A87-47009 sensor failures: Real-time evaluation three-dimensional configurations: A survey Wind Shear/Turbulence Inputs to Flight Simulation and p 701 N87-26022 [NASA-TP-2740] p 682 N87-25331 Systems Certification A high temperature fatigue and structures testing Computational chemistry p 706 N87-26023 [NASA-CP-2474] p 625 N87-25267 facility National Aeronautics and Space Administration. Flight Wind shear and turbulence simulation [NASA-TM-100151] p 701 N87-26399 Research Center, Edwards, CaiN. p 703 N87-25274 National Aeronautics and Space Administration. Preliminary flight results of an adaptive engine control Flight duration, airspeed practices and altitude Marshall Space Flight Center, Huntsville, Aia. system of an F-15 airplane management of airplanes involved in the NASA VGH B-57B gust gradient program p 657 N87-25276 [AIAA PAPER 87-1847] p 667 A87-45247 General Aviation Program National Center for Atmospheric Research, Boulder, National Aeronautics and Space Administration. [NASA-TM-89074] p 625 N87-25293 Colo. Langley Research Center, Hampton, Va. Subsonic wind-tunnel measurements of a slender Introduction to the JAWS Program Case histodes involving fatigue and fracture mechanics; wing-bedy configuration employing a vortex flap p 703 N87-25270 Proceedings of the Symposium, Chadeston, SC, Mar. 21, [NASA-TM-89101] p 642 N87-25295 22, 1985 p 692 A87-42851 Study of lee-side flows over conically cambered Delta JAWS multiple Doppler derived winds p 703 N87-25271 An interactive approach to surface-fitting complex wings at supersonic speeds, part 2 geometries for flowfield applications [NASA-TP.2660-PT-2] p 643 N87-25301 Status of the JAWS Program p 703 N87-25272 [AIAA PAPER 87-1476] p 625 A87-43009 Effect of planform taper on hover performance of an United Aidines wind shear incident of May 31, 1984 advanced AH-64 model rotor Molecular flow velocity using Doppler shifted Raman p 647 N87-25288 [NASA-TM-89145] p 643 N87-25304 spectroscopy National Transportation Safety Board, Washington, D. On the nonlinear aerodynamic and stability [AIAA PAPER 87-1531] p 693 A87-43053 C. characteristics of a generic chine-forebody sionder-wing Direct simulation of aerothermal loads for an aeroassist Accident investigation p 647 N87.25285 fighter configuration flight experiment vehicle Aircraft accioent/inoident summary reports: Unalaska, [NASA-TM-89447] p 643 N87.25305 [AIAA PAPER 87-1546] p 626 A87-43063 Alaska, September 25, 1985; Jenkinsburg, Georgia, A multi-body aircraft with an all-movable center fuselage September 29, 1985; Boston, Massachusetts, December A computational study of the flowfield surrounding the actively controlling fuselage pressure drag 15, 1985; DeKalb, Texas, December 31, 1985; Erie, Aeroassist Flight Experiment vehicle [ NASA-CASE.LAR-13511-1 ] p 658 N87-25320 [AIAA PAPER 87-1575] p 626 A87-43084 Pennsylvania, February 21, 1986 Integrally-stiffened crash energy-absorbing subfloor [PB87-910408] p 648 N87-253t0 Rotor design for maneuver performance beam structure Annual review of aircraft accident data. US air carrier p 652 A87-43431 [NASA-CASE.LAR-13697-1] p 659 N87-25321 operations calendar year 1983 Maximum survival capability of an aircraft in a severe Airfoil flutter model suspension system ]PB87-160628] p 648 N87-25311 windshear p 680 A87-44254 [NASA-CASE-LAR-13522-1-SB] p 687 N87-25334 Naval Surface Weapons Center, Silver Spring, Md. A unique measurement technique to study Preliminary structural design of composite main rotor Numerical simulation and comparison with experiment blades for minimum weight laminar-separation bubble characteristics on an airfoil for self-excited oscillations in a diffuser flow [AIAA PAPER 87.1271] p 631 A87-44921 [NASA-TP-2730] p 691 N87-25435 p 693 A87-43381 Incompressible Navier-Stokes computations of vortical Truss-core corrugation for compression loads North Carolina State Univ., Raleigh. flows over double-delta wings [NASA-CASE-LAR-13438-1] p 699 N87-25496 An interactive approach 1o surface-fitting complex [AIAA PAPER 87-1341] p 631 A87-44933 Miniature remote dead weight calibrator geometries for flowfield applications [NASA-CASE-LAR-13564-1] p 700 N87-25558 Vortex breakdown simulation [AIAA PAPER 87-1476] p 625 A87-43009 Auxiliary data input device [AIAA PAPER 87-1343] p 632 A87-44934 Northrop Corp., Hawthorne, Calif. [NASA-CASE-LAR-13626-1] p 700 N87-25584 Stability and transition in supersonic boundary layers Application of computational physics within Northrop Survey of currently available high-resolution raster [AIAA PAPER 87-1416] p 632 A87-44947 p 706 N87-26008 The numerical simulation of subsonic flutter graphics systems Notre Dame Univ., Ind. [NASA-TM-89139] p 705 N87-25771 [AIAA. PAPER 87-1428] p 633 A87-44952 Laminar separation bubble characteristics on an airfoil Transonic wall interference assessment and corrections Effect of signal jitter on the spectrum of rotor impulsive at low Reynolds numbers p 641 A87-46778 for airfoil data from the 0.3-meter TCT adaptive wall test noise section [NASA-TM-100477] p 708 N87-25827 [AIAA PAPER 87-1431] p 633 A87-44953 Detailed near-wake flowfield surveys with comparison 0 Designing transonic wind-tunnel test sections lor flow to an Euler method of an aspect ratio 4 rectangular wing diagnostics and laser velocimeter applications [NASA-TM-89357] p 644 N87-25993 Office National d'Etudes et de Recherches [AIAA PAPER 87-1434] p 684 A87-44954 Computational analysis of hypersonic airbreathing Aerospatlales, Leclerc (France). aircraft flow fields p 645 N87-26019 A miniature remote deadweight calibrator A comparison of the acoustic and aerodynamic p 694 A87-45104 Effect of Reynolds number variation on aerodynamics measurements of a model rotor tested in two anechoic Crash response data system for the controlled impact of a hydrogen-fueled transport concept at Mach 6 wind tunnels p 683 A87-43425 demonstration (CID) of a full scale transport aircraft [NASA-TP-2728] p 645 N87-26031 Ohio State Univ., Columbus. p 694 A87-45123 Steady and unsteady aerodynamic forces from the Measurement of side forces of a H-force rotor Investigation of a delta-wing fighter model flow field at SOUSSA surface.panel method for a fighter wing with tip p 651 A87-43410 transonic speeds missile and comparison with experiment and PANAIR Wind tunnel evaluation of a truncated NACA 64-621 [AIAA PAPER 87-1749] p 634 A87-45182 [NASA-TP-2736] p 645 N87.26032 airfoil for wind turbine applications Scale model test results of a thrust reverser concept Low-speed wind-tunnel results for symmetrical NASA [NASA-CR-180803] p 703 N87-25621 for advanced multi-functional exhaust systems LS(1)-0013 airfoil Operations Research, Inc., Rockvllle, Md. [AIAA PAPER 87-1833] p 667 A87-45235 [NASA-TM-4003] p 645 N87-26033 Rotorcraft research - A national effort (The 1986 Static investigation of post-exit vanes for multlaxis thrust Evaluation of installed performance of a Alexander Nikolsky Honorary Lectureship) vectoring wing.tip-mounted pusher turboprop on a semispan wing p 623 A87-44255 [AIAA PAPER 87-1834] p 667 A87-45236 [NASA.TP-2739] p 659 N87-26041 Parametric study of single expansion ramp nozzles at Optimization methods applied to the aerodynamic design P subsonic/traneenic speeds of helicopter rotor blades [AIAA PAPER 87-1836] p 635 A87-45238 [NASA-TM-89155] p 660 N87.26042 PEDA Corp., Palo Alto, Calif. A mixing augmentation technique for hypervelocity National Aeronautics and Space Administration. Lewis Aerodynamic design modification of a hypersonic wind scram jets Research Center, Cleveland, Ohio. tunnel nozzle by CSCM with high order accuracy [AIAA PAPER 87-1882] p 668 A87-45275 An LDA investigation of three-dimensional normal [AIAA PAPER 87-1896] p 635 A87-45284 Modification to the Langley 8-Foot High Temperature shock-boundary layer interactions in a corner Pratt and Whitney Aircraft, East Hartford, Conn. Tunnel for hypersonic propulsion testing [AIAA PAPER 87-1369] p 632 A87-44938 Application of CFD cedes to the design and development [AIAA PAPER 87-1887] p 685 A87-45277 Full-scale thrust reverser testing in an altitude facility Integration effects of pylon geometry and rearward of propulsion systems p 677 N87-26009 [AIAA PAPER 87-1788] p 684 A87-45203 PRC Kentron, Inc., Hampton, Va. mounted nacelles for a high-wing transport Contingency power for small turboshaft engines using [AIAA PAPER 87-1920] p 655 A87-45300 Modification to the Langley 8.Foot High Temperature water injection into turbine cooling air Exploratory evaluation of a moving-medel technique for Tunnel for hypersonic propulsion testing [AIAA PAPER 87-1906] p 668 A87-45289 measurement of dynamic ground effects [AIAA PAPER 87-1887] p 685 A87-45277 NASA/GE advanced low emissions combustor [AIAA PAPER 87-1924] p 685 A87-45303 Princeton Univ., N. J. program Three-dimensional numedcal predictions of the flow Stability and Control modelling p 678 A87-43428 ]AIAA PAPER 87-2035] p 671 A87-45369 Kinematic observers for active control of helicopter rotor behind a rearward-facing-step in a supersonic combustor vibration p 679 A87-43448 [AIAA PAPER 87-1962] p 636 A87-45332 Two-dimensional nozzle plume characteristics A subsonic to Mach 5.5 subscale engine test facility [AIAA PAPER 87-2111] p 636 A87-45413 Linear stability analysis of three-dimensional [AIAA PAPER 87-2052] p 685 A87-45381 Secondary stream and excitation effects on compressible boundary layers p 640 A87.46504 Unresolved issues in wind shear encounters An outlook on hypersonic flight two-dimensional nozzle plume characteristics p 647 N87-25282 [AIAA PAPER 87-2074] p 671 A87-45392 [AIAA PAPER 87-2112] p 637 A87-45414 C-3 Purdue Univ., West Lafayette, Ind. CORPORA TE SOURCE

Purdue Univ., West Lafayette, Ind. Taxis A&M Unlv., College Station. A panel method for counter rotating proplans Measurement of the effect of manufacturing deviations [AIAA PAPER 87-1890] p 668 A67-45279 on natural laminar flow for a single engine general aviation Aeroelastic control of stability and forced response of airplane supersonic rotors by aerodynamic detuning [NASA-CR-t80671] p 677 N87-26044 p 676 A87.46249 Textron Bell Helicopter, Fort Worth, "rex. Optimal cooperative control synthesis of active Ground and flight test results of a total main rotor displays isolation system [NASA-CR-4058] p 705 N87-25807 [NASA-CR-4082] p 643 N87-25302 Toledo Univ., Ohio. An LDA investigation of three-dimensional normal Q shock-boundary layer interactions in a corner [AIAA PAPER 87-1369] p 632 A87-44938 Qceemdand Univ., Brisbane (Australia). Scramjet testing in impulse facilities p 685 A87-46183 U Pressure scaling effects in a scramiet combustion chamber p 676 A87-46258 United Air Lines, Inc., Denver, Colo. Queensland Univ., St. Lucia (Australia). United Airlines wind shear incident of May 31, 1984 Hydrogen scramjet with sidewall injection - Shock tunnel p 647 N87-28287 simulations p 674 A87.46217 United Technologies Research Canter, East Hartford, Conn. Computational fluid dynamics research at the United R Technologies Research Center requiring supercomputers p 701 N87-26011 Rand Graduate Inst. for Policies Study, Santa Monlce, Calif. National Aerospace Plane Program: Principal V assumptions, findings and policy options [RAND/P.7288-RGS] p 625 N87-25990 Vlgyan Research Associates, Inc., Hampton, Va. Rice Univ., Houston, Tax. Direct simulation of aerothermal loads for an aeroassist Maximum survival capability of an aircraft in a severe flight experiment vehicle windshear p 680 A87-44254 [AIAA PAPER 87-1546] p 626 A87-43063 Optimal flight trajectories in the presence of windshear, Incompressible Navier-Stokes computations of vortical 1984-86 flows over double-delia wings [NASA-CR-180316] p 682 N87-26047 [AIAA PAPER 87-1341] p 631 A87.44933 Rockwell international Science Center, Thousand Three-dimensional numerical predictions of the flow Oaks, Calif. behind a rearward-facing-step in a supersonic combustor Development and application of unified algorithms for [AIAA PAPER 87-1962] p 636 A87-45332 problems in computational science p 705 N87-26006 Virginia Polytechnic Inst. and State Univ, Slecksburg. Royal Aircraft Establishment, Farnborough (England). The numerical simulation of subsonic flutter Aerodynamics of unmanned aircraft at full-scale in the [AIAA PAPER 87-1428] p 633 A87-44952 RAE 24It wind-tunnel Design and evaluation of a new injector configuration [RAE*TM-AERO-2081] p 645 N67-26027 for supersonic combustion p 674 A87-46218 Fatigue.life monitoring of the 5 metre wind tunnel Interdisciplinary optimum design p 657 A87-47009 [RAE-TM-AERO-2084] p 688 N87-26055 Singular trajectories in airplane cruise-dash optimization [NASA.CR-180636] p 659 N87-26035 S Factors affecting the sticking of insects on modified aircraft wings Sandia National Labs., Albuquerque, N. Max. [NASA-CR-180957] p 659 N67-26037 Influence of a heated leading edge on boundary layer growth, stability and transition [DE87-008516] p 700 N87-25538 Societe Nationals Industrlelle Aerospatlale, Marlgnane (France). Correlation of SA349/2 helicopter flight-test data with a comprehensive rotorcraft model p 653 A87-43456 Spectron Development Labs., inc., Costa Mesa, Calif. Tomographic reconstruction of three-dimensional flow over airfoils [AD-A179976] p 643 N87-25300 Sperry Flight Systems, Glendale, Adz. Automatic systems and the low-level wind hazard p 681 N87-25279 Stanford Univ., Calif. Identification of a dynamic model of a helicopter from flight tests p 659 N87-26040 Control of aircraft under severe wind shear conditions p 682 N87-26050 Stedlr_ Software, Paid Alto, Calif. Advances in the computation of transonic separated flows over finite wings [AIAA PAPER 87-1195] p 630 A87.44904 Sverdrup Technology, Inc., Cleveland, Ohio. Wind tunnel performance results of an aeroelastically scaled 2/9 model of the PTA flight test prop-fan [NASA-TM-89917] p 642 N87-25294 T

Technleche Hogeechool, Delft (Netherlands). Fuel saving and fuel related subjects within an aidine's operational environment [ETN-87-90148] p 648 N87-26034 Temple Univ., Philadelphia, Pa. Degradation mechanisms of sulfur and nitrogen containing compounds during thermal stability testing of model fuels [AIAA PAPER 87-2039] p 690 A87.45372 Test Wing (4950th), Wrlght-Pstteraon AFB, Ohio. TACAN/INS Performance Evalue.ticn (TIPE) flight test report [AD-A180138] p 650 N87-25313

C-4 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 219) November 1987

Numerical simulation of diffusor/combustor dome "lyplcal Foreign Technology Designing for fretting fatigue free joints in turboprop interaction p 676 A87-46255 Index Listing engine gearboxes [AIAA PAPER 87.2046] p 671 A87-45378 Numerical simulation of cruiser on aircraft lightning Finite element analysis of large spur and helical gear p 646 A87-46317 systems Contribution of laser anemometry to aircraft safety [AIAA PAPER 87-2047] p 697 A87-45379 p 699 A87-46361 Exhaust carbon - The effects of fuel composition Trends in the aeroeiastic analysis of combat aircraft p 676 A87-46253 p 657 A87-46362 Simulator manufacturers' requirements Validation of aerodynamic measurement techniques and p 687 N87-25280 calculation methods for high-lift systems CHINA, PEOPLE'S REPUBLIC OF p 640 A87-46363 ORIGIN The influence of the induced velocity distribution and Project for an intelligent system for on-line trouble the flapping-lagging coupling on the derivatives of the rotor AUSTRALIA shooting p 705 A87-46365 and the stability of the helicopter p 679 A87-43436 ,_ Reaction to aircrafl noise in res;denhal areas around Research on the stress analysis method of rubber Wind tunnel experimental study ot optical beam structure - Calculation of the frequency adapter stresses degradation through heterogeneous aerodynamic flows ustralian airports p 54 A87-10116 p 693 A87-43453 [ONERA, TP NO. 1987-50] p 707 A87-46753 Transonic stream function solution on S(2) Statistical distribution of extreme atmospheric streamsurface for a high pressure ratio centrifugal turbulences compressor p 638 A87-46195 [ONERA, TP NO. 1987o56] p 702 A87-46757 Improvement of aerodynamic calculation on S(2)m Unsteady viscous-inviscid interaction method and stream surface of axial compressor by using of annulus computation of buffeting over airfoils wall boundary layer calculation p 639 A87-46216 [ONERA, TP NO. 1987-58] p 640 A67-46759 Application of a fuzzy controller infuel system of turbojet Study of the aerodynamics of high-spesd propellers engine p 674 A87-46227 [ONERA, TP NO. 1987-61] p 640 A87-46761 A panel method for prediciting the dynamic stability Bounded random oscillations - Model and numerical derivatives of an oscillating wing in high subsonic flow resolution for an airfoil p 641 A87-46951 [ONERA, TP NO. 1987-73] p 681 A87-46767 Two-dimensional subsonic and transonic wind tunnel Crack growth prediction in 3D structures under wall interference corrections for varied walls Listings in this index are arranged alphabetically by aeronautical-type spectrum Ioadings p 686 A87-46955 country of intellectual origin. The title of the [ONERA, TP NO. 1987-79] p 691 A87-46772 An experimental investigation of delta wings with Numerical simulation of flows in axial and radial document is used to provide a brief description of leading-edge vortex separation p 641 A87.46956 turbomachioes using Euler solvers the subject matter. The page number and the The pitching damping derivatives measured by [ONERA, TP NO. 1987-87] p 641 A87-46776 force-oscillation method at transonic and supersonic wind accession number are included in each entry to tunnel p 686 A87-46958 Aerodynamic study of a helicopter rotor in hovering flight assist the user in locating the citation in the abstract Development of experimental investigation on transonic - Theory vs. experiment p 641 A87-47014 section. wind tunnel wall interference p 687 A87-46960 Recent progress in the measurement of the drag coefficients of models of transport aircraft in a wind Fast methods applied to the calculation of transonic tunnel airfoils p 641 A87-46962 [NASA-'I-1"-20096] p 644 N87-25306 The interference of the model support mast with A D measurements of the longitudinal and lateral aerodynamic coefficients DENMARK [NASA-l-1"-20079] p 644 N87-25307 AUSTRALIA An airborne laser air motion sensing system, II - Design Colour dependence and surplus information in airport criteria and measurement possibilities G visual aids during VFR operations p 649 A87-44040 p 662 A87-45733 Scramjet testing in impulse facilities p 685 A87-46183 GERMANY,FEDERAL REPUBLIC OF Hydrogen scramjet with sidewall injection - Shock tunnel F Helicopter activities in Germany p 623 A87-43401 simulations p 674 A87-46217 FEL - A new main rotor system p 651 A87-43402 Investigation of blede-vortices in the rotor.downwash Pressure scaling effects in a scramjet combustion FRANCE p 627 A87-43415 chamber p 676 A87-46258 New aerodynamic design of the fenestron for improved performance p 651 A87-43403 Computation of the flow fields of propellers and hovering A prescribed radial distribution circulation of a hovering rotors using Euler equations p 628 A87-43418 B rotor blade p 627 A87-43414 Application of a 3D Euior code to transonic blade tip An analysis of in-fin tail rotor noise flow p 628 A87-43419 p 652 A87-43427 Unsteady separation characteristics of airfoils operating BELGIUM A promising low speed air data system for helicopters under dynamic stall conditions p 628 A87-43421 The effect of European law on air transport p 661 A87-43437 The influence of winglets on rotor aerodynamics p 709 A87-42862 Development of an experimental system for active p 628 A87-43422 BRAZIL control of vibrations on helicopters p 679 A87-43447 Helicopter modelling for performance calculation Design of motion simulation software with digital filtering irish Dauphin helicopter S.A.R. system flight tests p 652 A87-43434 techniques p 704 A87-44712 p 648 A87-43455 An advanced mathematical model for helicopter flight Tip clearance flows. I - Experimental investigation of Helicopter turboshaft engine acoustic and infrared simulation using nonlinear unsteady aerodynamics an isolated rotor, n - Study of various models and studies and tests p 663 A87-43467 p 679 A87-43435 comparison with test results p 638 A87-46208 Air conditioning systems for helicopters A now method of analytical evaluation of helicopter true p 654 A87.43473 airspeed p 661 A87-43439 C An airborne collision avoidance system - The TCAS Realization and flight testing of a model following control p 649 A87-44231 system for helicopters p 679 A87-43440 The model inverse as an element of a manoeuvre CANADA Extreme atmospheric turbulence demand system for helicopters p 679 A87-43441 Liability of the United States government in cases of [ONERA, TP NO. 1987-8] p 680 A87-44328 Investigation of ground and air resonance using a air traffic controller negligence p 708 A87-42859 A new simulation of airfoil dynamic stall due to velocity and incidence fluctuations combination of multiblade coordinates and Floquet The now Annex 17 - The latest contribution by theory p 653 A87-43444 international civil aviation to the battle against terrorism [AIAA PAPER 87-1242] p 630 A87-44915 Damage tolerance concepts for modern helicopters p 708 A87.42860 Unsteady viscous flows round moving circular cylinders and airfoils. II p 637 A87-45792 p 653 A67-43449 The Warsaw Convention system regarding air carrier Autonomous navigation system for the new generation responsibility - New developments in jurisprudence Investigation of the three dimensional flow near the exit of military helicopters and associated flight tests p 709 A87-42864 of two backswept transonic centrifugal impellers p 638 A87-46192 p 648 A87-43469 Engineering and human visual considerations in EMI-fault prevention and self recovery of digital flight development of a fibre optic helmet mounted display Mechanical evaluation of the aeroelastic behaviour of control systems p 661 A87-43470 p 661 A87-44727 a fan blade p 675 A87.46248

D-1 GERMANY,PEOPLES DEMOCRATIC REPUBLIC OF FOREIGN TECHNOL OG Y INDEX

The tilt-rotor aircraft - A response to the future? From Euler solution for a complete fighter aircraft at sub- and J European interrogations to Eurofar actions supersonic speed [MBB-UD-485-86-PUB] p 654 A87-43474 [MBB-LKE-122-S/PUB/234] p 660 N87-26833 JAPAN Integrated navigation, communication and surveillance Aircraft technology of the nineties in MBB passenger Study of the dynamic response of helicopters to a large systems based on standard distance measuring aircraft projects airplane wake p 678 A87.43429 equipment p 649 A87-44039 [MBB-UT-0021/86 ] p660 N87-26834 Study on the interference between the local separation The Airbus rudder - An example of new fabrication Integration of the propfan concept in aircraft design on a wing surface and outer flow-field technologies p 623 A87-44228 ]MBB-UT-0001/86] p 677 N87-26835 p 634 A87-45094 A3t0-300 CFRP fin Damage tolerance Conceptual studies of control systems for wings with An approach to the synthesis of an adaptive flight control demonstration p 655 A87-44594 variable camber system with incomplete information p 680 A87°45096 Radar Technology 1986; Symposium, 6th, Bremen, West [MBB-UT-221/86] p 682 N87-26836 Design of CCV flight control system of STOL flying Germany, Nov, 4-6, 1986, Reports p 697 A87-45876 beat p 680 A87-45097 The quality of radar data and its determination at the Development of novel bearingless rotor systems Performance calculation of counter rotation propeller radar installations of the Bundesanstalt fuer [MBB-UD-471/86] p 702 N87-26837 [AIAA PAPER 87-1889] p 635 A87-45278 Avionics systems for future civil helicopters Flugsicherung p 650 A87.45878 Extension of local circulation method to counter rotation [MBB-UD-473/86] p 662 N87-26838 Radar requirements for future avionics systems propeller Going beyond the limits. Aviation in Germany p 662 A87-45879 [AIAA PAPER 87-1891] p 635 A87-45280 An automated radar-signature measurement system [SO-t-87] p 710 N87-26853 J86 surge transient simulation p 675 A87-46240 p 698 A87-45886 GERMANY,PEOPLES DEMOCRATIC REPUBLIC OF Thrust vectoring - Why and how? p 673 A87-46180 Design of an automated information-processing Improved agility for modern fighter aircraft, II - Thrust system p 704 A87-44241 K vectoring engine nozzles p 673 A87-46181 GREECE Flow phenomena in transonic turbine cascades detailed Real-time wind estimation and tracking with transponder KOREA,(SOUTH) experimental and numerical investigation downlinked airspeed and heading data Wake measurements of an oscillating airfoil p 639 A87-46223 p 648 A87.42779 p 637 A87-45779 The mixing of jets under simulated engine-like A method for the calculation of the interaction of a turbulence p 698 A87-46231 turbulent boundary layer with a shock wave N Advances in technology for low cost turbomachinery - p 639 A87-46238 A potential to enhance the economy of future propulsion system for general and helicopter aviation NETHERLANDS p 676 A87-46261 I Development of a flexible and economic helicopter Dornier 328 - Concept for a new-generation regional engine monitoring system p 663 A87-43466 airliner p 657 A87-46326 INDIA Some fundamentals of simulator cockpit motion generation p 683 A87-44714 Technological aspects in preparing the development of Effect of swirl on the performance of a radial vaneless Entrainment effect of a leading-edge vortex regional airliners p 657 A87-46327 diffuser with compressible flow at Mach numbers of 0.7 Aerothermodynamic computations for and 0.8 p 641 A87-46777 super-/hypersonic flight p 640 A87-46328 Fuel saving and fuel related subjects within an airline's [ASME PAPER 86-WA/FE-6] p 629 A87-43704 Large-scale distribution of peroxyacetylnitrate results operational environment A study of some factors affecting the performance of from the STRATOZ III flights p 702 A87.46481 [ETN-87-90148] p 648 N87-26034 a contra°rotating axial compressor stage NORWAY Compressible flows in the wakes of a square cylinder p 639 A87-46211 and thick symmetrical airfoil arranged in tandem The use of discrete vortices to predict lift of a circulation A study on the effect of non-dimensional system p 641 A87-46922 control rotor section with a trailing edge blowing slot parameters on squeeze film damper performance using p 627 A87-43416 Aircraft technologies of the nineties in MBB passenger experimental data p 698 A87-46229 aircraft projects Underexpanded jet-free stream interactions on an [MBS-UT-21/86] p 625 N87-25291 axisymmetric afterbody configuration P Application of a three-dimensional Euler code to p 639 A87-46232 transonic blade tip flow Microprocessor based surge monitoring system POLAND [MBB-UD-482/86] p 642 N87-25299 p 686 A87-4624t Changes inthe free flow in the intake of a turbojet engine A model test vehicle for hypersonic aerospace systems Erosion problem of axial compressor blades of a during the aircraft takeoff run p 640 A87-46351 development turboshaft engine p 675 A87-46246 [MBB-UR-875/86] p 658 N87-25314 Classification of the load-carrying capacity of runway Stress analysis and optimisation of turbine rotor blade surfaces by the ACN-PCN method, I Design for repairability of helicopter rotor blades shrouds p 699 A87-46250 p 686 A87-46353 [MBB-UD-491/86] p 658 N87-25315 Terrain modelling of glideslope for instrument landing Classification of the load-carrying capacity of runway Design of a composite tail for the Airbus A-320 system p 650 A87-46415 surfaces by the ACN-PCN method. II [MBB-UT-12-86] p 658 N87-25316 INTERNATIONAL ORGANIZATION p 686 A87-46354 A310-300 CFRP fin damage tolerance demonstration Interception of civil aircraft vs. misuse of civil aviation [MBB-UT-015/86] p 658 N87-25317 p 708 A87.42861 The role of simulation in helicopter development Natural convection flow of a radiating rarefied gas S [MBB-UD-435/86] p 687 N87-25333 between concentric rotating spheres [AIAA PAPER 87-1523] p 693 A67-43046 Effects of impact loading on carbon fiber reinforced SOUTH AFRICA, REPUBLIC OF structures Wind determination from aircraft-movement data Expendable turbojet compressor design, test and [MBB-Z-83/86] p 691 N87-25436 p 702 A87-45892 ISRAEL development p 674 A87-46212 Analytical description of crack resistance curves for SPAIN aluminum sheets used in aircraft construction A parametric investigation of a free wake analysis of hovering rotors p 627 A87-43413 Spanish contribution to rotorcraft development - [MBB-UT-133/85] p 700 N87-25604 Diagnostics in supersonic combustion Homage to de la Cierva p 623 A87-43426 Automated systems for the manufacture of Airbus A study on the optimization of jet engines for combat vertical stabilizers [AIAA PAPER 87-1787] p 690 A87-45202 Application of ceramics to ramjet engine nozzles aircrafts p 676 A87°46262 [MBB-UT-17-86] p 705 N87-25786 p 690 A87-46221 SWEDEN Canard configurations Diagnostic methods for air-breathing engines The Aeronautical Research Institue (FFA) wing body 85 [ETN-87-99914] p 659 N87-26039 p 686 A87-46243 computer program. A panel method for determination of The 0.6 m x 0.6 m trisonic section (TMK) of DFVLR in Development of a laser interferometric system for aeroelastic characteristics applying direct block iterative CoIogne-Porz, West Germany velocity measurements inside a transonic axial flow solution techniques [DFVLR-MITT-86.21] p 687 N87-26053 compressor stage p 698 A87-46244 [FFA*TN-1986-28] p 642 N87-25298 The vertical test section (VMK) of DFVLR in ITALY Development of a geometry handling program for the Cologne-Porz, West Germany Composite vital parts optimisation for EH 101 rotor FFA subsonic higher order panel method [DFVLR-MITT-86-22] p 688 N87-26054 hub p 653 A87-43451 [FFA-TN-1985-48] p 699 N87-25534 Development and testing of critical components for the Helicopter model in flight identification by a real time Measurement of noise from airplanes traveling at 3500 technological preparation on an Airbus fuselage made of self adaptive digital process p 680 A87-43458 to 11000 m altitude carbon fiber reinforced plastics, phase 1 Standardization and logistic support cost effectiveness [FFA.TN-1986-21] p 708 N87-25824 [BMFT-FB-W-86-017] p 692 N87.26151 of advanced avionics systems p 661 A87-43468 SWITZERLAND Lightning protection activity in the development of a new A conformal aircraft phased array antenna for Heat exchangers for turboshaft engines airplane.satellite communication in the L band helicopter p 654 A87-43471 p 664 A87-44253 [DFVLR-FB-86-47] p 701 N87-26259 Air cycle environmental control system for helicopters - A trade-off study p 654 A87-43472 The new Soviet fighters - How good are they?. Experiences with hot.wire instruments for the p 656 A87-46312 measurement of the liquid water content in clouds Simulation of performance, behaviour and faults of Flying the CF-18 Hornet p656 A87-46313 [DFVLR-MITT-86] p 704 N87-26476 aircraft engines [AIAA PAPER 87-1868] p 668 A87-45263 Proving that Avanti stands for progress Industrial application of computer aided structural p 656 A87-46314 optimization in aircraft construction Application of a 3D inviscid rotational design procedure for turbomachinery bladings p 638 A87-46204 DVI in the military cockpit - A third hand for the combat [MBB-UT-273/86] p 706 N87-26523 An improved approach for transonic flow pilot p 681 A87°46315 Research and development. Technical-scientific p 639 A87-46215 Aeroelasticity in turbomachines comparison of publications 1986 Investigation on the stall margin of a turbofan engine theoretical and experimental cascade results. Appendix [ETN-87°99713] p 710 N87-26826 p 675 A87-46239 A5: All experimental and theoretical results for the 9 Use of artificial intelligence methods Aeroelastic derivatives as a sensitivity analysis of standard configurations [MBB-LKE-434-S/PUB/284] p 707 N87-26831 nonlinear equations p 699 A87-46797 [AD-A180534] p 677 N87-25326 D-2 UNITED KINGDOM FOREIGN TECHNOLOG Y INDEX

U Worldwide navigation into the 21st century - An airline view p 649 A87-44036 U.S.S.R, Countdown to the propfan p 664 A87-44272 Electrochemical machining processes in aircraft engine Prospects for the use of composites in civil aircraft p 655 A87-44577 building p 693 A87-42905 Helicopter Rotor Icing Symposium, London, England, Honeycomb structures: Parameter selection and Jan. 14, 1986, Proceedings p 646 A87-44701 design p 693 A87-42914 Where and when helicopter icing occurs Three-dimensional problems in computational fluid p 702 A87-44702 dynamics p 693 A87-42916 Rotor icing experience at Wsstland and its application Effect of fabrication-related deviations of the geometrical to current and future helicopters p 646 A87-44703 parameters of blade profiles on flow in a compressor Icing clearance criteria for UK military helicopters p 629 A87-43603 p 646 A87-44705 Investigation of flow structure in a compressor with two Rotor icing research at RAE Farnborough types of guides p 629 A87.43604 p 646 A87-44706 Selection of admissible contact s_esses for toothed Icing clearances on civil helicopters - Unheated and gears of aircraft engines p 663 A87-43605 heated blades p 646 A87-44707 Approximation of the characteristics of the turbine of a Motion software for a research flight simulator gas turbine engine in a wide range of operating modes p 704 A87-44713 p 663 A87-43606 The integration of a six axis motion system and a wide The low-aspect.ratio parameter of blades angle visual system inside a dome p 684 A87-44720 p 663 A87-43607 Visual systems developments p 694 A87-44725 Calculation of the boundary layer at the inlet section AOI displays using laser illumination of a compressor cascade p 629 A87-43608 p 694 A87-44726 Optimization of the duration of ultrasonically activated Materials in aerospace; Pmcaedings of the First impact surface treatment of gas-turbine-engine blades International Conference, London, England, Apr. 2-4,1986. p 663 A87-43609 Volumes 1 & 2 p 689 A87-44729 Mathematical model for calculating the atomization of Materials in helicopters. A review a liquid jet by an annular gas stream p 624 A87-44731 p 693 A87.43610 Helicopter lubrication p 624 A87-44733 Efficiency of the utilization of rotor blade shroud labyrinth High temperature titanium alloys p 689 A87-44739 seals in an axial.compressor stage with large radial Adhesives in aerospace p 689 A87-44743 clearances p 694 A87-43611 Developments in titanium alloys p 689 A87-44744 Materials for structures of the future Numerical study of the gasdynamic process in a pulsejet engine p 663 A87-43614 p 689 A87-44745 Calculation of the reliability of aimraft-engine parts under Fire, smoke, toxicity p 646 A87-44748 repeated static loading p 664 A87-43616 Corrosion protection p 624 A87-44760 Investigation of rotating additional blades on the Engine design and systems integration for propfan and periphery of an axial-compresssor rotor high bypass turbofan engines p 629 A87-43618 [AIAA PAPER 87-1730] p 665 A87-45169 Engineering and cost principles for increasing the Real-time neutron imaging of gas turbines production efficiency and maintainability of aimraft [AIAA PAPER 87-1762] p 695 A87-45189 The influence of dilution hole aerodynamics on the engines p 664 A87-43620 Optimization of systems for the automatic testing of temperature distribution in a combustor dilution zone aircraft engines according to cost criteria [AIAA PAPER 87.1827] p 666 A87-45232 p 664 A87-4362t High performance turbofan afterburner systems Parameters of optimal planetary gears of AI type ]AIAA PAPER 87-1830] p 666 A87-45234 p 694 A87-43622 Transmission efficiency in advanced aerospace A study of the thermal-stress state of gas turbine engine powerplant blades with protective coatings p 664 A87-43640 [AIAA PAPER 87-2043] p 671 A87-45376 Errors in the measurement of the course angles of radar Fokker 50 - Pedigree with power p 656 A87-45647 reference points due to the imprecise stabilization of the Seastar - Glass, plastic, and tradition p 656 A87-45648 antenna mounting in bank and pitch p 649 A87-44312 Future trends - A European view p 673 A87-46179 Aerodynamic characteristics of wave riders Performance prediction in a centrifugal compressor p 637 A67.46094 impeller p 674 A87-46190 Numerical simulation of transonic three-dimensional The role of short duration facilities in gas turbine research p 685 A87-46222 flows in turbine blade passages p 638 A87-46206 UNITED KINGDOM Integration of engiee/aircraft control - 'How far is it Fracture of an aircraft horizontal stabilizer sensible to go' p 674 A87-46226 p 650 A87-42855 Optical flow diagnostic measurements in Viscous-inviscid interactions in external aerodynamics turbomachinery p 698 A87-46245 p 626 A87-43299 The air-injection method of fixing boundary-layer Flow over a trailing flap and its asymmetric wake transition and investigating scale effects p 626 A87.43376 p 639 A87-46264 EH1Ol cockpit design p 661 A87.43404 Investigation ol the aerodynamic performance and noise Simulator evaluations of inceptors for ACT helicopters characteristics of a 1/5th scale model of the Dowry Rotol p 678 A87-43405 R212 propeller p 640 A87-46265 EH.1Ol - The helicopter matures p 657 A87-46371 The effect of pitch rate on the dynamic stall or a modified V.2500 - Back on course? p 676 A87-46372 NACA 23012 aerofoil and comparison with the unmodified case p 628 A87-43420 Burning questions p 646 A87-46373 Measurements of the performance of a helicopter swept Soviet helicopter development p 657 A87-46735 tip rotor in flight p 652 A87-43423 Active control of aerofoil flutter p 681 A87-46792 An analytic method of quantifying helicopter agility Aerodynamics of unmanned aircraft at full-scale in the p 678 A87-43432 RAE 24ft wind-tunnel Observations of pilot control strategy in low level [RAE-TM-AERO-2081] p 645 N87-26027 helicopter flying tasks p 678 A87-43433 Aerofoil maximum lift-coefficient for Mach numbers up Investigation of helicopter twin-rotor characteristics to 0.4 p 628 A87-43438 [ESDU-84026] p 645 N87-26028 An improved assumed mode method for estimating the An introduction to time-dependent aerodynamics of motion of a nonuniform rotor blade p 653 A87-43445 aircraft response, gusts and active controls Determination of the structural properties of helicopter [ESDU-84020] p 682 N87-26048 rotor blades by theoretical and experimental methods Fatigue-life monitoring of the 5 metre wind tunnel p 653 A87-43450 [RAE.TM-AERO-2084] p 688 N87-26055 The microstructure and mechanical properties of various First approximation to landing field length of civil aluminium-lithium alloy product forms for helicopter transport aeroplanes (50 ft., 15.24 m screen) structures p 688 A87-43454 [ESDU-84040] p 688 N87-26056 Experience with froquency-domain methods in Helicopter vibration control: Recent advances helicopter system identification p 680 A87-43457 p 660 N87-26247 Experimental application of strain pattern analysis (SPA) Estimation of spillage drag for a wide range of - Wind tunnel and flight test results p 654 A87-43459 axisymmetric intakes at M 1 Description of, and preliminary results from, a new [ESDU-84004] p 701 N87-26301 The treatment of calibrations of total air temperature blade-vortex interaction test facility p 683 A87-43460 Substantiation of the analytical prediction of ground and probes for use in flight-test analysis work air resonance stability of a bearingiess rotor, using model ]ESDU-84007] p 701 N87-26324 scale tests p 654 A87-43463 D-3 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 219) November 1987

• jpical Contract Number Index Listing NAG1o516 ...... ) 680 A87-44254 )682 N87-26047 NAG1-568 ...... ) 644 N87-25997 NAG1-616 ...... )659 N87-26036 NAG1-472 ...... p 22 N87-10854 NAG2-209 ...... )652 A87-43442 NAG2-226 ...... )652 A87-43442 NAG2-228 ...... )705 N87-25807 NAG2-244 ...... )678 A87-43428 NAG2-318 ...... ) 705 N87-25804 -l- /T NAG3-183 ...... )690 A87-45372 NAG3-309 ...... )632 A87-44938 NAG3-330 ...... )703 N87-25621 NAG3-499 ...... )668 A87-45279 NAG3-6662 ...... )646 A87-45635 NASW-4005 ...... )644 N87-25306 )644 N87-25307 NAS1-15069 ...... )691 N87-25439 Listings in this index are arranged alpha- NAS1-15604 ...... )640 A87-46504 numerically by contract number. Under each NAS1-16158 ...... )705 N87-25806 NAS1-16237 ...... _640 A87-46504 contract number, the accession numbers denoting NAS1-16969 ...... J643 N87-25302 documents that have been produced as a result of NAS1-16977 ...... =640 A87-46504 research done under that contract are arranged in NAS1-17919 ...... 631 A87-44933 NAS1-18235 ...... ascending order with the AIAA accession numbers ) 631 A87-44921 NAS1-18240 ...... ) 632 A87-44945 appearing first. The accession number denotes the ) 632 A87-44946 number by which the citation is identified in the NAS2-11665 ...... ) 681 N87-25330 abstract section. Preceding the accession number NAS2-12243 ...... )635 A87-45284 NAS2-12513 ...... is the page number on which the citation may be )630 A87-44905 NAS3-24211 ...... )697 A87-45398 found. NAS3-24222 ...... )707 A87-45282 NAS3-24339 ...... )635 A87-45281 AF-AFOSR-0105-84 ...... 677 N87-25326 NAS3-24346 ...... )677 N87-25323 AF-AFOSR-83-0071 ...... 627 A87-43392 NAS3-2483 ...... )697 A87-45398 AF-AFOSR-83-0213 ...... 696 A87-45273 NAVAIR TASK AIR-536 ...... )670 A87-45353 AF-AFOSR-85-0340 ...... 690 A87-45198 NCA2-OR-745-309 ...... )630 A87-44904 BMFT-LFF-83408 ...... 679 A87-43435 NCA2-119 ...... _707 A87-43044 BMFT-LFF-84318 ...... 653 A87-43444 NCCI-100 ...... )625 A87-43009 DA PROJ. 1L1-61102-AH-45A ...... 643 N87-25304 NCC1-22 ...... _625 A87-43009 DA PROJ. 1L1-61102-AH-45 ...... 677 N87-25323 NCC2-387 ...... _707 A87-43129 DA PROJ. 1L1-62209-AH-76 ...... 681 N87-25330 NGL-22-009-640 ...... _646 A87-45635 691 N87-25435 NGT-03-002-800 ...... _627 A87-43392 DAAG29-82-K-0094 ...... 683 A87-43461 NSG-1419 ...... _641 A87-46778 DAAG29-83-C-0012 ...... 643 N87-25300 N00014-79-C-0849 ...... _826 A87-43377 DAAG29-83*K-0050 ...... 627 A87-43412 N00014-83-K-0239 ...... =629 A87-44019 DAAG29-85-G-0072 ...... 683 A87-43461 N00014-84-C-0359 ...... 1633 A87-44949 DE-AC04-76DP-00789 ...... 700 N87-25538 _633 A87-44950 DOT-RS57-85-C-00105 ...... 678 A87-43430 N00014-84-K-0372 ...... b668 A87-45266 DRET-82-432 ...... 641 A87-47014 N00014-84-K-0434 ...... _668 A87-45267 DRET-83-025 ...... 652 A87-43427 N00014-87-K-0168 ...... _833 A87-44948 DRET-83/215 ...... 637 A87-45792 482-58-13-01 ...... p705 N87-25771 DRET-84-009 ...... 627 A87-43414 505-60-21-01 ...... p645 N87-26033 641 A87-47014 505-60-21-02 ...... _642 N87-25295 DRET-84-368 ...... 652 A87-43427 505-61-51-01 ...... _660 N87-26042 DTFA03-84-C-00004 ...... 647 N87-25308 505-61-51-06 ...... _708 N87-25827 FFA-AU-PROJ-1731:l ...... 699 N87-25534 505-61o51 ...... _643 N87-25302 FFA-AU-PROJ-1801:1 ...... 699 N87-25534 505-61-71 ...... _643 N87-25305 FFAoAU-PROJ-1881:1 ...... 699 N87-25534 505-62-01 ...... _682 N87-25331 FFA-AU-PROJ-2041:1 ...... 699 N87-25534 505-62-81-01 ...... _645 N87-26031 FFA-AU-PROJ-2240 ...... 699 N87-25534 505-62-81-07 ...... _643 N87-25301 FMV-F-K-82260-84260 ...... 642 N87-25298 505-83-21-01 ...... _645 N87-26032 F04611-86-C-0095 ...... 670 A87-45347 505-63-51-01 ...... _691 N87-25435 F33615-79-C-2050 ...... 696 A87-45296 505-63-51 ...... _642 N87-25296 F33615-82-C°2255 ...... 665 A87-45161 505-66-11 ...... _705 N87-25807 F33615-83-C-3013 ...... 647 N87-25309 505-66-41-04 ...... p705 N87-25806 F33615-83-C-3026 ...... 699 N87-25536 505-67-41-03 ...... _825 N87-25267 F33615-84-C-2409 ...... 695 A87-45243 505-68-01-01 ...... _625 N87-25293 F33615-86-C-2604 ...... 666 A87-45233 533-04-11 ...... _701 N87-26399 F33615-86-C-2652 ...... 700 N87-25550 534-06-23-01 ...... _691 N87-25439 F33657-79-C-0730 ...... 695 A87-45186 535-03-01-01 ...... b659 N87-26041 F34601-83-C-3448 ...... 664 A87-43702 545-03-01 ...... ,642 N87-25294 F49620-83-K-0009 ...... 631 A87-44932 F49620-85-C-0027 ...... ) 626 A87-43377 F49620-85-C-0131 ...... ) 641 A87-46779 MOD-ER/2/1/7/0090-XR ...... 666 A87-45232 MOD-2048/026)XR/STR ...... ) 628 A87-43420 MOD-2048/028/XR/STR ...... ) 680 A87-43457 NAGW-674 ...... ) 685 A87-46183 NAG1-203 ...... 659 N87-26035 NAG1-300 ...... ) 659 N87-26037 NAG1-309 ...... ) 677 N87-26044 NAG1-394 ...... ) 708 N87-26612 NAG1-455 ...... ) 631 A87-44933

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 219) November 1987

l_plcal Report Number Index Listing

AIAA PAPER 87-1520 ...... ) 707 A87-43044 * # AIAA PAPER 87-2002 ...... ,670 A87-45347 # AIAA PAPER 87-1523 ...... ) 693 A87-43046 # AIAA PAPER 87-2003 ...... ,670 A87-45348 # AIAA PAPER 87-1531 ...... ) 693 A87-43053 * # AIAA PAPER 87-2008 ...... ,696 A87-45349 * # .ACCESS,O., o. AIAA PAPER 87-1546 ...... ) 626 A87-43063 * # AIAA PAPER 87-2009 ...... t 696 A87-45350 # AIAA PAPER 87-1575 ...... ) 626 A87-43084 * # I "U"BERI .,CRO_,C.E AIAA PAPER 87-2013 ...... 670 A87-45353 # AIAA PAPER 87-1632 ...... 707 A87-43129 * # 'I .ASA/ "I I AIAA PAPER 87-2014 ...... p670 A87-45354 # AIAA PAPER 87-1708 ...... )665 A87-45156 # AIAA PAPER 87-2035 ...... p671 A87-45369 * # A-9682 ...... p 15 N87-10641 ft AIAA PAPER 87-1709 ...... 665 A87-45157 # AIAA PAPER 87-2036 ...... 671 A87-45370 # AIAA PAPER 87-1711 ...... 655 A87-45158 # T AIAA PAPER 87-2039 ...... 890 A87-45372 * # AIAA PAPER 87-1716 ...... 624 A87-45159 # AIAA PAPER 87-2043 ...... 671 A87-45376 # AIAA PAPER 87-1721 ...... 665 A87-45161 # AIAA PAPER 87-2046 ...... 671 A87-45378 # I PAOEII .ASAAIAA PAPER 87-1729 ...... 665 A87-45168 # AIAA PAPER 87-2047 ...... ) 697 A87-45379 # AIAA PAPER 87-1730 ...... 665 A87-45169 # AIAA PAPER 87-2052 ...... ) 685 A87-45381 * # AIAA PAPER 87-1731 ...... 665 A87-45170 AIAA PAPER 87-2058 ...... 636 A87-45386 * # AIAA PAPER 87-1733 ...... 666 A87-45171 # AIAA PAPER 87-2074 ...... ) 671 A87-45392 * # AIAA PAPER 87-1741 ...... 695 A87-45178 # AIAA PAPER 87-2078 ...... ) 671 A87-45393 # Listings in this index are arranged alpha- AIAA PAPER 87-1747 ...... 666 A87-45180 # AIAA PAPER 87-2079 ...... ) 636 A87-45394 # numerically by report number. The page number AIAA PAPER 87-1748 ...... 666 A87-45181 # AIAA PAPER 87-2088 ...... )636 A87-45397 # AIAA PAPER 87-1749 ...... 634 A87-45182 * # indicates the page on which the citation is located. AIAA PAPER 87-2089 ...... ) 697 A87-45398 * # AIAA PAPER 87-1750 ...... 634 A87-45183 # The accession number denotes the number by AIAA PAPER 87-2092 ...... ) 656 A87-45400 # AIAA PAPER 87-1751 ...... 634 A87-45184 # AIAA PAPER 87-2097 ...... ) 671 A87-45404 # which the citation is identified. An asterisk (*) AIAA PAPER 87-1752 ...... 634 A87-45185 # AIAA PAPER 87-2099 ...... 697 A87-45405 # indicates that the item is a NASA report. A pound AIAA PAPER 87-1758 ...... ,695 A87-45186 # AIAA PAPER 87-2101 ...... 672 A87-45406 # AIAA PAPER 87-1762 ...... ,695 A87-45189 # sign (#) indicates that the item is available on AIAA PAPER 87-2102 ...... ) 672 A87-45407 # AIAA PAPER 87-1778 ...... ,690 A87-45198 # microfiche. AIAA PAPER 87-2103 ...... 672 A87-45408 # AIAA PAPER 87-1785 ...... b695 A87-45201 # AIAA PAPER 87-2104 ...... 672 A87-45409 # AIAA PAPER 87-1787 ...... 690 A87-45202 # AIAA PAPER 87-2105 ...... 672 A87-45410 # AIAA PAPER 87-1788 ...... 684 A87-45203 * # AIAA PAPER 87-2111 ...... 636 A87-45413 ° # A-87058 ...... p 642 N87-25296 * # AIAA PAPER 87-1790 ...... 684 A87-45204 # AIAA PAPER 87-2112 ...... 637 A87-45414 * # A-87174 ...... p 643 N87-25305 * # AIAA PAPER 87-1791 ...... 666 A87-45205 # AIAA PAPER 87-2150 ...... 637 A87-45435 # AIAA PAPER 87-1826 ...... 666 A87-45231 # AIAA PAPER 87-2151 ...... 637 A87-45436 # AIAA PAPER 87-1827 ...... 666 A87-45232 # AD-A172111 ...... p 681 N87-25330 * # AIAA PAPER 87-2161 ...... 688 A87-45443 # AIAA PAPER 87-1829 ...... 666 A87-45233 # AD-A179844 ...... p 658 N87-25318 # AIAA PAPER 87-2164 ...... 872 A87-45444 " # AIAA PAPER 87-1830 ...... 666 A87-45234 # AIAA PAPER 87-2165 ...... 685 A87-45445 * # AD-A179858 ...... p 699 N87-25536 # AIAA PAPER 87-1833 ...... 667 A87-45235 * # AIAA PAPER 87-2170 ...... 697 A87-45450 # AD-A179897 ...... p 650 N87-25312 # AIAA PAPER 87-1834 ...... _667 A87-45238 * # AIAA PAPER 87-2172 ...... 656 A87.45452 # AD-A179906 ...... p 647 N87-25308 # AIAA PAPER 87-1835 ...... p655 A87-45237 # AIAA PAPER 87-2173 ...... 672 A87-45453 # AD-A179931 ...... p 647 N87-25309 # AIAA PAPER 87-1836 ...... ) 635 A87-45238 * # AIAA PAPER 87-2174 ...... 873 A87-45454 # AD-A179976 ...... p 643 N87-25300 # AIAA PAPER 87-1839 ...... ) 667 A87-45240 # AIAA PAPER 87-2181 ...... 897 A87-45457 # AD-A180007 ...... p 677 N87-25323 * # AIAA PAPER 87-1840 ...... ) 695 A87-45241 # AIAA PAPER 87-2184 ...... :) 673 A87-45458 # AD-A180095 ...... p 700 N87-25550 # AIAA PAPER 87-1842 ...... ) 695 A87-45243 # AD-A180138 ...... p 650 N87-25313 # AIAA PAPER 87-1845 ...... ) 667 A87-45245 # AIAA-85-0644 ...... p 660 N87-26042 * # AD-A180534 ...... p 677 N87-25326 # AIAA PAPER 87-1846 ...... ) 667 A87-45246 # AIAA-87-1893 ...... p 642 N87-25294 * # AIAA PAPER 87-1847 ...... ) 667 A87-45247 * # AERO-ASTRONAUTICS-203 ...... p 682 N87-26047 * # AIAA PAPER 87-1848 ...... ) 667 A87-45248 # ARO-19471.4-EG ...... p 643 N87-25300 # AIAA PAPER 87-1868 ...... ) 668 A87-45263 # AERO-TR-87-2 ...... p 677 N87-26044 * # AIAA PAPER 97-1869 ...... ) 668 A87-45264 # ASD-TR-85-5015 ...... p 658 N87-25318 # AIAA PAPER 87-1870 ...... ) 709 A87-45265 # AFOSR-87-0605TR-APP-A-5 ...... p 677 N87-25326 # AIAA PAPER 87-1871 ...... ) 668 A87-45266 # ASL-87-1 ...... p 644 N87-25997 ° # AIAA PAPER 87-1872 ...... ) 668 A87-45267 # AFWAL-TR-86-3048 ...... p 699 N87-25536 # AIAA PAPER 87-1879 ...... ) 696 A87-45273 # ASME PAPER 86-WA/DE-20 ...... p 664 A87-43702 # AFWAL-TR-87-2021 ...... p 700 N87-25550 # AIAA PAPER 87-1880 ...... ) 690 A87-45274 # ASME PAPER 86-WA/DE-3 ...... p 664 A87-43701 # AFWAL-TR-87-3001 ...... p 647 N87-25309 # AIAA PAPER 87-1882 ...... 668 A87-45275 * # ASME PAPER 86-WA/FE-6 ...... p 629 A87-43704 # AIAA PAPER 87-1884 ...... 684 A87-45276 # AIAA PAPER 86-1023 ...... ,704 A87-43388 # ASME PAPER 86-WAITS-2 ...... p 623 A87-43723 # AIAA PAPER 87-1887 ...... 685 A87-45277 * # AIAA PAPER 87-1192 ...... 629 A87-44902 * # AIAA PAPER 87-1889 ...... 635 A87-45278 # AIAA PAPER 87-1195 ...... ,630 A87-44904 * # AVSCOM-TM-87-B-10 ...... p 643 N87-25304 * # AIAA PAPER 87-1890 ...... 668 A87-45279 * # AIAA PAPER 87-1198 ...... 830 A87-44905 ° # AVSCOM-TM-87-B-6 ...... p 691 N87-25435 * # AIAA PAPER 87-1891 ...... 635 A87-45280 # AIAA PAPER 87-1199 ...... 630 A87-44906 * # AIAA PAPER 87-1892 ...... 635 A87-45281 * # AIAA PAPER 87-1229 ...... 630 A87-44913 * # BMFT-FB-W-86-017 ...... p 692 N87-26151 # AIAA PAPER 87-1894 ...... 707 A87-45282 * # AIAA PAPER 87-1241 ...... ) 630 A87-44914 * # AIAA PAPER 87-1895 ...... 635 A87-45283 # BR100296 ...... p 645 N87-26027 # AIAA PAPER 87-1242 ...... ) 630 A87-44915 # AIAA PAPER 87-1896 ...... 635 A87-45284 * # AIAA PAPER 87-1262 ...... ) 831 A87-44920 * # BR100661 ...... p 688 N87-26055 # AIAA PAPER 87-1908 ...... 668 A87-45289 * # AIAA PAPER 87-1271 ...... ) 631 A87-44921 * # AIAA PAPER 87-1907 ...... 689 A87-45290 # AIAA PAPER 87-1322 ...... )631 A87-44929 # CONF-870622-3 ...... p 700 N87-25538 # AIAA PAPER 87-1910 ...... 669 A87-45292 # AIAA PAPER 87-1331 ...... ) 631 A87-44931 # AIAA PAPER 87-1913 ...... 696 A87-45293 # CRINC-FRL-717-1 ...... p 659 N87-26036 * # AIAA PAPER 87-1334 ...... ) 631 A87-44932 # AIAA PAPER 87-1915 ...... 669 A87-45295 # AIAA PAPER 87-1341 ...... ) 631 A87-44933 * # AIAA PAPER 87-1916 ...... 696 A87-45296 # AIAA PAPER 87-1343 ...... ) 632 A87-44934 * # DE87-008516 ...... p 700 N87-25538 # AIAA PAPER 87-1919 ...... 669 A87-45299 # AIAA PAPER 87-1369 ...... ) 632 A87-44938 * # AIAA PAPER 87-1920 ...... 655 A87-45300 * # AIAA PAPER 87-1399 ...... ) 632 A87-44943 # DFVLR-FB-86-47 ...... p 701 N87-26259 # AIAA PAPER 87-1922 ...... 669 A87-45301 # AIAA PAPER 87-1412 ...... ) 632 A87-44945 " # AIAA PAPER 87-1923 ...... 655 A87-45302 # DFVLR-MITT-86-21 ...... p 687 N87-26053 # AIAA PAPER 87-1414 ...... ) 632 A87-44946 * # AIAA PAPER 87-1924 ...... 685 A87-45303 * # DFVLR-MITT-86-22 ...... p 688 N87-26054 # AIAA PAPER 87-1416 ...... 632 A87-44947 * # AIAA PAPER 87-1926 ...... 669 A87-45304 # DFVLR-MITT-86 ...... p 704 N87-26476 # AIAA PAPER 87-1418 ...... 633 A87-44948 # AIAA PAPER 87-1927 ...... ,669 A87-45305 # AIAA PAPER 87-1421 ...... 633 A87-44949 # AIAA PAPER 87-1928 ...... 680 A87-45306 # AIAA PAPER 87-1422 ...... DGLR-86-100 ...... p 707 N87-26831 633 A87-44950 # AIAA PAPER 87-1929 ...... 681 A87-45307 # AIAA PAPER 87-1424 ...... DGLR-86-108 ...... p 625 N87-25291 # 633 A87-44951 # AIAA PAPER 87-1930 ...... 670 A87-45308 # AIAA PAPER 87-1428 ...... DGLR-86-108 ...... p 660 N87-26834 633 A87-44952 * # AIAA PAPER 87-1931 ...... 696 A87-45309 # AIAA PAPER 87-1431 ...... 633 A87-44953 * # DGLR-86-167 ...... p 706 N87-26523 # AIAA PAPER 87-1962 ...... 636 A87-45332 * # AIAA PAPER 87-1434 ...... 684 A87-44954 * # AIAA PAPER 87-1964 ...... 670 A87-45333 # AIAA PAPER 87-1438 ...... 634 A87-44955 # DOE/NASA/0330-2 ...... p 703 N87-25621 * # 636 A87-45334 # AIAA PAPER 87-1476 ...... 625 A87-43009 * # AIAA PAPER 87-1965 ...... AIAA PAPER 87-1514 ...... 626 A87-43038 * # AIAA PAPER 87-1966 ...... 656 A87-45335 # DOT/FAA/CT-TN86/61 ...... p 650 N87-25312 #

F-1 DOT/FAA/CT-86-13 REPORT NUMBER INDEX

OOT/FAA/CT-86-13 ...... p 647 N87-25308 # MBB-UR-875/86 ...... p 658 N87-25314 NASA-TP-2739 ...... p 659 N87-26041 * # NASA-TP-2740 ...... p 682 N87-25331 * # E-3479 ...... p 682 N87-25331 *# MBB-UT-0001/86 ...... p 677 N87-26835 E-3610 ...... p 642 N87-25294 * # MBB-UT-0021/86 ...... p 660 N87-26834 NASA-TT-20079 ...... p 644 N87-25307 ° # E-3712 ...... p 701 N87-26399 ° # MBB-UT-015/86 ...... p 658 N87-25317 # NASA-TT-20096 ...... p 644 N87-25306 * # MBB-UT-12-86 ...... p 658 N87-25316 # ESDU-AERO-W.01.01.06 ...... p 645 N87-26028 MBB-UT-133/85 ...... p 700 N87-25604 # NTSB/AAR-87/02/SUM ...... p 648 N87-25310 # MBB-UT-17-86 ...... p 705 N87-25786 # ESDU-PERF-RG1/5 ...... p 701 N87-26324 MBB-UT-21/86 ...... p 625 N87-25291 # NTSB/ARC-87-01 ...... p648 N87-25311 # MBB-UT-221/86 ...... p 682 N87-26836 ESDU-84004 ...... p 701 N87-26301 MBB-UT-273/86 ...... p 706 N87-26523 # ONERA-TP-1986-170 ...... p 644 N87o25306 ° # ESDU-84007 ...... p 701 N87-26324 ONERA-TP-1986-181 ...... p 644 N87-25307 * # ESDU-84020 ...... p 682 N87-26048 MBB-Z-83/86 ...... p 691 N87-25436 # ESDU-84026 ...... p 645 N87-26028 ONERA, TP NO. 1987-50 ...... p 707 A87-46753 # ESDU-84040 ...... p 688 N87-26056 MDC-J3968 ...... p 699 N87-25536 # ONERA, TP NO. 1987-56 ...... p 702 A87-46757 # ONERA, TP NO. 1987-58 ...... p 640 A87-46759 # ETN-87-90092 ...... p 645 N87-26027 # NAS 1.15:100151 ...... _ 701 N87-26399 * # ONERA, TP NO. 1987-61 ...... p 640 A87-46761 # ETN-87-90093 ...... p 688 N87-26055 # NAS 1.15:100477 ...... ) 708 N87-25827 * # ONERA, TP NO. 1987-73 ...... p 681 A87-46767 # ETN-87-90148 ...... p 648 N87-26034 # NAS 1.15:4003 ...... ) 645 N87-26033 * # ONERA, TP NO. 1987o79 ...... p 691 A87-46772 # ETN-87-99678 ...... p 704 N87-26476 # NAS 1.15:89074 ...... ) 625 N87-25293 * # ONERA, TP NO. 1987-87 ...... p 641 A87-46776 # ETN-87-99681 ...... p 687 N87-26053 # NAS 1.15:89101 ...... ) 642 N87-25295 * # ONERA, TP NO. 1987-8 ...... p 680 A87-44328 # ETNo87-99682 ...... p 688 N87-26054 # NAS 1.15:89139 ...... ) 705 N87-25771 * # ETN-87-99688 ...... p 701 N87-26259 # NAS 1.15:89145 ...... ) 643 N87-25304 * # PB87-160628 ...... p648 N87-25311 # ETN-87-99713 ...... p 710 N87-26826 NAS 1.15:89155 ...... ) 660 N87-26042 * # PB87-910408 ...... p 648 N87-25310 # ETN-87-99778 ...... p 699 N87-25534 # NAS 1.15:89357 ...... ) 644 N87-25993 * # ETN-87-99779 ...... p 708 N87-25824 # NAS 1.15:89419 ...... ) 642 N87-25296 * # RAE-TM-AERO-2081 ...... p 645 N87-26027 # ETN-87*99780 ...... p 642 N87-25298 # NAS 1.15:89447 ...... ) 643 N87-25305 * # RAE-TM-AERO-2084 ...... p 688 N87-26055 # ETN-87-99906 ...... p 692 N87-26151 # NAS 1.15:89917 ...... ) 642 N87-25294 o # ETN-87-99909 ...... p 710 N87-26853 # NAS 1.26:175110 ...... ) 677 N87°25323 * # RAND/P-7288-RGS ...... p 625 N87-25990 # ETN-87-99914 ...... p 659 N87-26039 # NAS 1.26:177404 ...... ) 681 N87-25330 " # ETN-87-99925 ...... p 687 N87-25333 # NAS 1.26:178321 ...... ) 691 N87-25439 * # REPT-4950/FTR-86-10 ...... p 650 N87-25313 # ETN-87-99927 ...... p 642 N87-25299 # NAS 1.26:180289 ...... ) 708 N87-26612 * # REPT-699-099-055 ...... p 643 N87-25302 * # ETN-87-99931 ...... p 658 N87-25315 # NAS 1.26:180316 ...... ) 682 N87-26047 * # ETN-87-99937 ...... p 658 N87-25314 NAS 1.26:180560 ...... ) 659 N87-26036 * # SAND-86-2718C ...... p 700 N87-25538 # ETNo87-99958 ...... p 658 N87-25316 # NAS 1.26:180636 ...... ) 659 N87-26035 * # ETNo87-99959 ...... p 658 N87-25317 # NAS 1.26:180671 ...... _ 677 N87-26044 * # SDL-87-2284-13F ...... p 643 N87-25300 # ETN-87-99960 ...... p 705 N87-25786 # NAS 1.26:180803 ...... ) 703 N87-25621 * # ETN-87-99962 ...... p 625 N87-25291 # NAS 1.26:180957 ...... ) 659 N87-26037 * # SO-1-87 ...... p 710 N87-26853 # ETN-87-99964 ...... p 700 N87-25604 # NAS 1.26:181050 ...... ) 705 N87-25804 * # ETN-87-99968 ...... p 706 N87-26523 # NAS 1.26:181119 ...... ) 644 N87-25997 * # US-PATENT-APPL-SN-013801 ..... p 658 N87-25320 * # ETN-87-99975 ...... p 691 N87o25436 # NAS 1.26:4058 ...... _ 705 N87-25807 * # US-PATENT-APPL-SN-022298 ..... p 699 N87-25496 * # NAS 1.26:4078 ...... ) 795 N87-25806 ° # US-PATENT-APPL-SN-044180 ..... p 700 N87-25558 * # FFA-TN-1985-48 ...... p 699 N87-25534 # NAS 1.26:4082 ...... ) 643 N87-25302 * # US-PATENT-APPL-SN-051426 ..... p 659 N87-25321 * # FFA-TN-1986-21 ...... p 708 N87-25824 # NAS 1.55:2474 ...... _ 625 N87-25267 * # US-PATENT-APPL-SN-063557 ..... p 700 N87-25584 * # FFA-TN-1986-28 ...... p 642 N87-25298 # NAS 1.60:2660-PT-2 ...... ) 643 N87-25301 * # US-PATENT-APPL-SN-890575 ..... p 687 N87-25334 * NAS 1.60:2728 ...... ) 645 N87-26031 * # FR-687102 ...... p 705 N87-25806 * # NAS 1.60:2730 ...... ) 691 N87-25435 * # US-PATENT-CLASS-73-147 ...... p 687 N87-25334 * NAS 1.60:2736 ...... ) 645 N87-26032 * # US-PATENT-CLASS-73-856 ...... p 687 N87-25334 * H-1378 ...... p 705 N87-25807 ° # NAS 1.60:2739 ...... ) 659 N87-26041 * # NAS 1.60:2740 ...... ) 682 N87-25331 ° # US-PATENT-4,682,494 ...... p 687 N87-25334 * IAF-86-125 ...... p 658 N87-25314 NAS 1.71:LAR-13438-1 ...... ) 699 N87-25496 ° # NAS 1.77:20079 ...... ) 644 N87-25307 ° # USAAVSCOM-TR-85-A-5 ...... p 681 N87-25330 * # ICAS-86-4.3.5 ...... p 658 N87-25316 # NAS 1.77:20096 ...... ) 644 N87-25306 * # USAAVSCOM-TR-86-C-15 ...... p 677 N87-25323 * #

ISBN-0-85679-466-X ...... p 701 N87-26301 NASA-CASE-LAR-13438-1 ...... p 699 N87-25496 * # ISBN-0-85679-469-4 ...... p 701 N87-26324 NASA-CASE-LAR-13511-1 ...... p 658 N87-25320 * # ISBN-0-85679-484-8 ...... p 682 N87-26048 NASA-CASE-LAR-13522-1-SB ..... p 687 N87-25334 * ISBN-0-85679-490-2 ...... p 645 N87-26028 NASA-CASE-LAR-13564-1 ...... p 700 N87-25558 * # ISBN-0-85679-504-6 ...... p 688 N87-26056 NASA-CASE-LAR-13626-1 ...... p 700 N87o25584 * # NASA-CASE-LAR-13697-1 ...... p 659 N87-25321 * # ISSN-0141-397X ...... p 645 N87-26028 ISSN-0141-397X ...... p 682 N87-26048 NASA-CP-2474 ...... p 625 N87-25267 * # ISSN-0141-4054 ...... p 688 N87-26056 ISSN-0141-4054 ...... p 701 N87-26301 NASA-CR-175110 ...... ) 677 N87-25323 # ISSN-0141-4054 ...... p 701 N87-26324 NASA-CR-177404 ...... ) 681 N87-25330 # ISSN-0170-1339 ...... p 692 N87-26151 # NASA-CR-178321 ...... ) 691 N87-25439 # ISSN-0171-1342 ...... p 701 N87-26259 # NASA-CR-180289 ...... ) 708 N87-26612 # ISSN-0176-7739 ...... p 687 N87-26053 # NASA-CR-180316 ...... ) 682 N87-26047 # ISSN-0176-7739 ...... p 688 N87-26054 # NASA-CR-180560 ...... ) 659 N87-28036 # ISSN-0176-7739 ...... p 704 N87-26476 # NASA-CR-180636 ...... ) 659 N87-26035 # NASA-CR-180671 ...... ) 877 N87-26044 # L-16192 ...... p 643 N87-25301 * # NASA-CR°180803 ...... ) 703 N87-25621 # L-16236 ...... p 625 N87-25293 * # NASA-CR-180957 ...... ) 659 N87-26037 # L-16252 ...... p 659 N87-28041 * # NASA-CR-181050 ...... ) 705 N87-25804 # L-16262 ...... p 645 N87-26032 " # NASA_R-181119 ...... ) 644 N87-25997 # L-16265 ...... p 642 N87-25295 " # NASA-CR-4058 ...... ) 705 N87-25807 # L-16267 ...... p 643 N87-25304 ° # NASA-CR-4078 ...... ) 705 N87-25806 # L-16279 ...... p 645 N87-26033 * # NASA-CR-4082 ...... ) 643 N87-25302 # L-16286 ...... p 645 N87-26031 ° # L-16294 ...... p 705 N87-25771 * # NASA-TM-100151 ...... ) 701 N87-26399 # L-16310 ...... p 691 N87-25435 * # NASA-TM-100477 ...... ) 708 N87-25827 # L-16329 ...... p 625 N87-25267 * # NASA-TM-4003 ...... ) 645 N87-26033 # NASA-TM-89074 ...... ) 625 N87-25293 # LR-30916 ...... p 647 N87-25308 # NASA-TM-89101 ...... ) 642 N87-25295 # NASA-TM-89139 ...... ) 705 N87-25771 # MANUDYNE-83-1 ...... p 681 N87-25330 * # NASA-TM-89145 ...... ) 643 N87-25304 # NASA-TM-89155 ...... }660 N87-26042 # MBB-LKE-122.S/PUB/234 ...... p 660 N87-26833 NASA-TM-89357 ...... ) 644 N87-25993 # MBB-LKE-434-S/PUB/284 ...... p 707 N87-26831 NASA-TM-89419 ...... ) 642 N87-25296 # NASA-TM-89447 ...... ) 643 N87-25305 # MBB-UD-435/86 ...... p 687 N87-25333 # NASA-TM-89917 ...... ) 642 N87-25294 # MBB-UD-471/86 ...... p 702 N87-26837 MBB-UD-473/86 ...... p 662 N87-26838 NASA-TP-2660-PT-2 ...... p 643 N87-25301 ° # MBB-UD-482/86 ...... p 642 N87-25299 # NASA-TP-2728 ...... p 645 N87-26031 ° # MBB-UD-485-86-PUB ...... p 654 A87-43474 # NASA-TP-2730 ...... p 691 N87-25435 ° # MBB-UD-491/86 ...... p 658 N87-25315 # NASA-TP-2736 ...... p 645 N87-26032 * #

F-2 ACCESSION NUMBER INDEX

I AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 219) November 1987

Typical Accession Number Index Listing

A87-43603 629 A67-44947 * # 632 A67-45301 # 669 A87.10524 # p4 A87-43604 629 A87-44948 # 633 A87-45302 # 655 A87-43605 663 A87-44949 # 633 A87-45303 *# 685 A87-43606 663 A67-45304 # 669 A87-44950 # 633 -I- A87-43607 663 A67-45305 # 669 A87-44951 # 633 A87-43608 629 A87-45306 # 680 A87-44952 * # 633 A87-43609 _ 663 A87-45307 # _ 681 A87-44953 *# 633 A87-43610 _ 693 A87-45308 # ) 670 A87-44954 *# ) 684 A87-43611 3 694 A57-45309 # 696 A67-44956 # ) 634 A67-43614 _663 A67-45332 ° # ) 636 MICROFICHE A87-45094 # 634 A87-43616 _664 A87-45333 # ) 670 A87-45096 # ) 680 J A87-43618 ,629 A87-45334 # ) 636 A87-45097 # 680 A87-43620 p664 A87-45335 # _ 656 A87-45104 °# 694 A87-43621 p664 A87-45347 # 3 670 A87-45107 694 A87-43622 =694 A87-45348 # ) 670 A67-45115 661 A87-43640 _664 A87-45349 *# =696 A87-45123 * # 694 Listings in this index are arranged alphanumerically A67-43701 # _664 A87-45350 # _696 A87-45124 ,695 A87-43702 # p664 A87-45353 # _670 by accession number. The page number listed to A87-45125 # 684 A87-43704 # _629 A87-45354 # _670 the right Indicates the page on which the citation A87-45126 662 A67-43723 # _623 A87-45369 *# _671 A87-45156 # 665 Is located, An asterisk (') indicates that the item is A67-44019 _629 A87-45370 # _671 A67-45157 # 665 a NASA report, A pound sign (#) indicates that the A67-44036 1649 A87-45372 *# =690 A87-45158 # i 655 A67-44039 )649 A87-45376 # _671 item is available on microfiche. A87-45159 # 624 A67-44040 _649 A87-45378 # _671 A87-45161 # ) 665 A87-44064 )709 A87-45379 # _697 A87-45168 # I 665 A87-44228 # )623 A87-45381 *# =685 A87-45169 # 1 665 A87-44231 )649 A87-45386 "# _636 A87-45170 ) 665 A67-44241 ) 704 A87-45392 * # 1671 A87-45171 # ) 666 A87-42736 ) 707 A87-43419 # o 628 A87-44253 )664 A87-45393 # 1671 A87-45175 # ) 695 A67-42779 )648 A87-44254 ° )680 A67-45394 # )636 A67-43420 # b626 A87-45180 # ) 666 A87-42786 ) 648 A87-44255 )623 A87-45397 # )636 A87-43421 *# ,628 A87-45181 # ) 666 A87-42812 ) 660 A87-44256 )654 A87-45398 "# )697 A87-43422 # _628 A87-45182 °# ) 634 A87-42651 ° ) 692 A87_4272 )664 A87-45400 # 1656 A87-43423 # _652 A87-45183 # ) 634 A87-42852 ° 692 A87-44312 649 A87-45404 # )671 A87-43424 # t628 A87-45184 # ) 634 A87-42853 ) 692 A87-44328 # ) 680 A87-45405 # )697 A87-43425 * # _683 A87-45185 # ) 634 A67-42654 ) 692 A87-44577 ) 656 A67-45406 # )672 A87-45186 # 695 A87-42855 650 A87-43426 # _623 A87-44552 665 A87-45407 # )672 A87-43427 # _652 A87-45189 # 695 A87-42856 650 A87-44594 655 A87-45408 # ) 672 A87-45198 # 690 A87-42657 623 A87-43428 * # _678 A87-44701 646 A67-45409 # ) 672 A87-43429 # _678 A87-45201 # 695 A87-42859 # 708 A87-44702 702 A87-45410 # ) 672 A87-45202 # 690 A87-42860 # 708 A87-43430 # _678 A87-44703 646 A87-45413 * # ) 636 A87-45203 *# 664 A87-42861 # 708 A87-43431 = # p652 A87-44704 655 A67-45414 * # ) 637 A87-45204 # 654 A87-42862 # 709 A87-43432 # )678 A87_4705 646 A87-45435 # 637 A87-45205 # 666 A87-42863 # 709 A87-43433 # )678 A87-44706 646 A87-45436 # )637 A57-45231 # 666 A87-42664 # ) 709 A67-43434 # )652 A87-44707 3 646 A67-45443 # )686 A87-45232 # 666 A87-42905 ) 693 A87o43435 # )679 A87-44712 ) 704 A87-45444 *# 672 A87-45233 # 666 A87-42914 693 A87-43436 # )679 A87-44713 704 A87-45445 * # 685 A67-43437 # )661 A87-45234 # 666 A87-42916 693 A97-44714 _ 663 A67-45450 # 697 A87-45235 * # 667 A87-43009 * # ) 625 A87-43438 # ) 628 A97-44715 3 683 A87-45452 # 656 A87-45236 * # 567 A87-43038 * # ) 626 A87-43439 # )661 A87-44720 3 684 A87-45453 # 672 A87-45237 # 655 A67-43044 * # ,707 A67-43440 # )679 A67-44725 _694 A67-45454 # 673 A87-45238 *# ) 635 A87-43046 # J 693 A87-43441 # 679 A87-44726 _694 A87-45457 # 697 A87-45240 # 667 A87-43053 * # 3 693 A87-43442 *# 652 A87-44727 ,661 A87-45458 # 673 A67-45241 # 695 A87-43063 * # ,626 A67-43443 # 652 A87-44729 =689 A87-45635 * # 646 A87-45243 # ) 695 A87-43084 * # ,626 A87-43444 # 653 A67-44731 p624 A87-45647 656 A87-45245 # ) 667 A87-43129 * # ,707 A87-43445 # 653 A87-44733 p624 A87-45648 656 A67-45246 # 667 A87-43299 626 A87-43446 * # 679 A87-44739 _689 A87-45669 p 697 A87-45247 *# 667 A87-43375 _660 A87-43447 # 679 A67-44743 _689 A87-45722 # p649 A87-45248 # ) 667 A87-43376 # 626 A87-43448 ° # 679 A87-44744 t689 A57-45732 p 662 A67-45263 # ,668 A87-43377 # p 626 A67-43449 # 653 A87-44745 _689 A87-45733 p 662 A87*45264 # 668 A87-43381 *# 693 A87-43450 # 653 A87-44747 _689 A87-45771 * p 704 A87-45265 # 709 A87-43383 # 707 A87-43451 # 653 A87-44748 _646 A87-45779 p 637 A67-45266 # 666 A87-43388 # 704 A87-43453 # ,693 A87-44750 1624 A87-45792 p 637 A87-45267 # 668 A87-43392 *# 627 A87-43454 # ) 688 A87-44845 1649 A87-45875 # p 673 A87-45273 # 696 A87-43398 o p 688 A87.43455 # )648 A87-44861 =689 A87-45876 p 697 A87.43456 °# _653 A87-45274 # 690 A87-43401 # I 623 A87-44902 *# 1629 A87-45878 p 650 A87.43457 # _680 A87-45275 * # 665 A87-43402 # 1 651 A87-44904 *# )630 A87-45879 p 662 A87-45276 # 684 A87-43403 # ) 651 A87-43458 # ,680 A87-44905 * # ) 630 A87-45886 p 695 A87-43459 # ,654 A87-45277 * # 685 A87-43404 # )661 A87-44906 * # ) 630 A87-45892 p 702 A87-45278 # 635 A87-43405 # 678 A87-43460 # p683 A87-44913 *# )630 A87-45898 *# p 690 A87-45279 * # 668 A87-43406 # i 651 A87-43461 # _683 A87-44914 * # ) 630 A87-45962 p 702 A87-43462 # _683 A87-45260 # I 635 A87-43407 # ) 651 A87-44915 # )630 A87-46094 p 637 A87-43463 # _654 A87-45281 "# 635 A87-43408 *# ) 651 A87-44920 * # ) 631 A87-46176 p 673 A87-43464 # p663 A87-45282 *# 707 A87-43409 # ) 651 A87-44921 * # ) 631 A87-46177 * # p 624 A87-43465 # p663 A87-45283 # ) 635 A87-43410 *# ) 651 A87-44929 # ) 631 A87-46178 # p 709 A87-43466 # p663 A87-45284 * # ) 635 A87-43411 # ) 651 A87-44931 # ) 631 A87-46179 # p 673 A87-45289 *# 668 A87-43412 # ) 627 A87-43467 # p663 A87-44932 # ) 631 A87-46180 # p 673 A87-45290 # ) 669 A87-43413 # ) 627 A87-43468 # _661 A87-44933 *# 631 A87-46181 # p 673 A87.43469 # _648 A87-45292 # ) 669 A87-43414 # ) 627 A87-44934 * # ) 632 A87-46182 # p 624 A87-43470 # _661 A87-45293 # ) 696 A87-43415 # ) 627 A67-44936"# )632 A67-46163 * # p685 A87-43471 # 1654 A87-45295 # ) 669 A87-44943 # 632 A87-46184 # p 637 A87-43416 # ) 627 A87.43472 # )654 A87-45296 # ) 696 A87-46189 # p 638 A87-43417 ° # ) 627 A87-43473 # )654 A87-44945 *# 632 A87-45299 # ) 669 A87°43418 # ) 628 A87-43474 # )654 A87-44946 *# 632 A87-45300 *# ) 655 A87-46190 # p 674

G-1 A87-46191 ACCESSION NUMBER INDEX

A87-46191 # b 638 N87-25267 ° # p 625 N87-26034 # ) 648 A87-46192 # p 638 N87-25268 * # p 703 N87-26035 * # ) 659 A87-46195 # 638 N87-25269 * # ,703 N87-26036 * # ) 659 N87-26037 * # ) 659 A87-46198 # 698 N87-25270 * # _ 703 N87-25271 * # _ 703 N87-26039 # ) 659 A87-46204 # b 638 N87-25272 * # _ 703 N87.26040 ) 659 A87-46206 # t 638 N87-25273 * # _ 709 N87.26041 * # ) 659 A87-46208 # 638 N87-25274 ° # b 703 N87-26042 * # ) 660 A87-46211 # p 639 N87-25275 * # b 687 N87-26044 * # 677 A87.46212 # p 674 N87-25276 ° # _ 657 N87-26047 * # ) 682 A87-46215 # p 639 N87-25277 ° # _ 703 N87-26048 682 N87-25278 ° # ,687 N87-26049 ) 682 A87-46216 # 639 N87-25279 * # D 681 N87-26050 682 A87-46217 * # p 674 N87-25280 * # _ 687 N87-26051 682 A87-46218 * # p 674 N87-25281 * # ,658 N87.26053 # 687 A87-46221 # p 690 N87-25282 * # ,647 N87o26054 # 688 A87-46222 # 685 N87-25283 * # ,687 N87-26055 # 688 A87.46223 # 639 N87-25284 * # ,658 N87-26056 688 A87-46226 # 674 N87-25285 * # _ 647 N87-26151 # 692 A87.46227 # 674 N87-25287 * # _ 647 N87-26247 # _660 A87.46228 * # 674 N87-25288 ° # ,647 N87-26259 # 701 A87-46229 # 698 N87-25291 # ,625 N87-26301 701 A87-46230 # 698 N87-25293 ° # ;) 625 N87-26324 701 A87-46231 # 698 N87-25294 * # 3 642 N87-26399 * # 701 A87-46232 # ,639 N87-25295 * # 3 642 N87-26476 # 704 A87-46238 # ,639 N87-25296 * # 3 642 N87-26523 # 706 A87-46239 # 675 N87-25297 3 642 N87-26612 * # 708 A87-46240 # ,675 N87-25298 # :_642 N87-26826 710 A87-46241 # ,686 N87-25299 # _ 642 N87-26831 707 A87-46243 # ,686 N87-25300 # ,643 N87-26833 _660 A87-46244 # 698 N87-25301 ° # ,643 N87-26834 _660 A87-46245 # ,698 N87-25302 * # ,643 N87-26835 677 A87-46246 # ,675 N87-25304 * # ,643 N87°26836 _682 A87-46247 # :3 675 N87-25305 ° # 3 643 N87.26837 702 A87-46248 # ;) 675 N87-25306 ° # _ 644 N87-26838 662 A87-46249 * # 3 676 N87-25307 ° # _ 644 N87-26853 # 710 A87-46250 # 699 N87-25308 # 3 647 A87-46253 # :) 676 N87-25309 # 3 647 A87-46255 # :) 676 N87-25310 # _ 648 A87-46258 * # 676 N87-25311 # _ 648 A87-46261 # 3 676 N87-25312 # _ 650 A87-46262 # :) 676 N87-25313 # 3 650 A87-46264 :) 639 N87-25314 _ 658 A87-46265 :) 640 N87-25315 # _ 658 A87.46312 :) 656 N87-25316 # _ 658 A87-46313 3 656 N87-25317 # _ 658 A87-46314 :) 656 N87-25318 # _ 658 A87-46315 3 681 N87-25320 * # _ 658 A87-46317 :) 646 N87-25321 * # _ 659 A87-46326 # :) 657 N87-25323 * # _ 677 A87-46327 # :} 657 N87-25326 # _ 677 A87.46328 # :} 640 N87-25330 * # _ 681 A87-46351 # :} 64O N87-25331 * # _ 682 A87-46353 # :) 686 N87-25333 # _ 687 A87-46354 # ,686 N87-25334 * _ 687 A87-46361 :_ 699 N87-25435 * # :_691 A87-46362 657 N87-25436 # :) 691 A87-46363 640 N87-25439 * # _ 691 A87-46365 ::, 705 N87-25496 " # _ 699 A87-46371 :) 657 N87-25534 # 699 A87-46372 ::, 676 N87-25536 # 699 A87-46373 646 N87-25538 # 700 A87-46415 650 N87-25550 # 700 A87-46438 686 N87-25558 ° # 700 A87-46481 702 N87-25584 ° # 700 A87-46504 ° :) 640 N87-25604 # 700 A87-46708 # 624 N87-25621 * # 703 A87-46715 # 699 N87-25771 * # 705 A87-46716 625 N87-25786 # 705 A87-46724 # 647 N87-25804 * # 705 A87-46727 662 N87-25806 * # 705 A87-46728 699 N87-25807 * # 705 A87-46735 657 N87-25824 # 708 A87-46753 # 707 N87-25827 * # 708 A87-46757 # 702 N87-25988 # 691 A87-46759 # 640 N87-25990 # 625 A87-46761 # 640 N87-25993 ° # 644 A87-46767 # 681 N87-25997 * # 644 A87-46772 # 691 N87-26004 * # 700 A87-46776 # 641 N87-26005 * # 644 A87-46777 # 641 N87-26006 * # 705 A87-46778 * # 641 N87-26007 * # 701 A87-46779 # 641 N87-26008 * # 706 A87-46792 # 681 N87-26009 * # 677 A87-46797 # 699 N87-26010 * # 706 A87-46861 650 N87-26011 *# 701 A87-46870 # 657 N87-26019 *# 645 A87-46874 # 691 N87-26021 * # 706 A87-46922 641 N87-26022 * # 701 A87-46951 # 641 N87-26023 * # 706 A87-46955 # 686 N87-26027 # ) 645 641 A87-46956 # N87-26028 :, 645 A87-46958 # 686 N87-26030 ) 645 A87-46960 # 687 A87-46962 # 641 N87o26031 * # ) 645 A87-47009 * # 657 N87-26032 * # ) 645 A87-47014 # 641 N87-26033 * # } 645

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NOTE: Each additional delivery address on an order requires a separate shipping and handling charge. 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (219)

4. Title and Subtitle 5. Report Date Aeronautical Engineering November, 1987

A Continuing Bibliography (Supplement 219) 6. Performing Organization Code

7. Author(s) 8. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Address National Aeronautics and Space Administration 11. Contract or Grant No. Washington, DC 20546

13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract This bibliography lists 586 reports, articles and other documents introduced into the NASA scientific and technical information system in October, 1987.

17. Key Words (Suggested by Authors(s)) 18. Distribution Statement Aeronautical Engineering Unclassified - Unlimited Aeronautics Bibliographies

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price * Unclassified Unclassified 164 AO8/HC

*For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Langley, 1987