ACCESSION NUMBER RANGES

A.ccession numbers cited in this Supplement fall within the following ranges.

STAR (N-10000 Series) N87-10001 - N87-11683

IAA (A-10000 Series) A87- 10001 - A8743026

I I This bib!iography ?n.as prepared by :he NASA Scientific ana Tecnnicai Information Faciiity operated I for the National Aeronautics and Space Administration by RMS Associates. I NASA SP-7037(210)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 21 0)

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in January 1987 in

Scien tific and Technical Aerospace Reports (STAR) International Aerospace Abstracts (IAA).

Scientific and Technical Information Branch 1987 IW\S/\ National Aeronautics and Space Administration Washington, DC This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A06. INTRODUCTION

This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 409 reports, journal articles and other documents originally announced in January 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 engines) and as- sociated components, equipment, and systems. It also includes research and development in , aeronautics, and ground support equipment for aeronautical vehicles. 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 respectiveannouncement 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.

iii TABLE OF CONTENTS

Page Category 01 Aeronautics (General) 1

Category 02 Aerodynamics 3 Includes aerodynamics of bodies, combinations, , rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 16 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 18 Includes digital and voice communication with aircraft; air navigation systems (satel- lite and ground based); and air traffic control.

Category 05 Aircraft Design, Testing and Performance 22 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 28 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 34 Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and onboard auxiliary power plants for aircraft.

Category 08 Aircraft Stability and Control 35 Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 37 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 38 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 d~lsip,?ec!ing and Ferfnrmmce: spacecraft instrumentation; and spacecraft pro- pulsion and power.

Category 11 Chemistry and Materials 38 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.

V Category 12 Engineering 44 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.

Category 13 Geosciences 54 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 N.A. Includes life sciences (general); aerospace medicine; behavioral sciences; man/ system technology and life support; and space biology.

Category 15 Mathematical and Computer Sciences 56 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.

Category 16 Physics 57 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.

Category 17 Social Sciences 61 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 62 Includes space sciences (general); astronomy; astrophysics; lunar and planetary exploration; solar physics; and space radiation.

Category 19 General 62

Subject Index ...... A-1 Personal Author Index ...... 6-1 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 I FON MICROFICHE ACCESSION NUMBER -N87-10039'# National Aeronautics and Space Administration. -CORPORATE SOURCE Langley Research Center, Hampton. Va. TITLE -WINPTUNNEL INVESTIGATION OF THE FLIGHT CHARACTERISTICS OF A CANARD GENERAL-AVIATION DATE AIRPLANE CONFIGURATION AUTHOR- D. R. SATRAN Oct. 1986< /-,AVAILABILITY SOURCE REPORT NUMBERS- (NASA-TP-2623; L-15929; NAS 1.60:2623) Avail: NTIS HC PRICE CODE- A04/MF A01 CSCL OlA 4 COSATI CODE A 0.36-scale model of a canard general-aviation airplane with a single pusher propeller 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 variables made testing of the model possible with the canard in hiqh and low positions, with increased winglet area, with outboard leading-edge droop, with fuselage-mounted vertical fin and rudder, with enlarged rudders, with dual deflecting rudders, and with ailerons mounted closer to the wing tips. The basic model exhibited generally good longitudinaland 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 aileron control power were sufficiently adequate for control of most flight condiiions, bui appeared io be i&iiveiy wesk hi meneweiing compared with those of more conveniionaily configured models. Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED II 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. UtGANI and L. tl. SCHIFF (NASA, Ames Fiesearch &rlier. -&KHcR'S AFF:::X:c% Moffett Field CA Journal of Computational Physics (ISSN 0021-9991). .;I. 66: GDt. 1986. D. 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- 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

b~t~e~fithe bo&j and !k~C)C!?~ h~)un&y) are r.---.----nrecontori 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 to permit accurate treatment of flows with large regions of crossflow separation. T.K.

vii AERONAUTICAL A Continuing Bibliography (Suppl. 210)

FEBRUARY 1987

01 A87-13001 JOINT NATIONAL SYMPOSIUM ON THE INFLUENCE OF AVIATION ON ENGINEERING AND THE FUTURE OF AERONAUTICS (GENERAL) AERONAUTICS IN AUSTRALIA, MELBOURNE, AUSTRALIA, AUGUST 8, 9, 1985, PREPRINTS AND SUPPLEMENTARY PAPERS Symposium organized and sponsored by the Institution of Engineers, Australia and Royal Aeronautical Society. Barton, A87-11801 Australia/Brookfield, VT, Institution of EngineerdBrookfield RADIO TECHNICAL COMMISSION FOR AERONAUTICS, Publishing Co. (National Conference Publication 85/9), 1985. ANNUAL ASSEMBLY MEETING AND TECHNICAL SYMPOSIUM, Preprints, 106 p.; Supplementary Papers, 62 p. For individual items WASHINGTON, DC, NOVEMBER 19-21, 1985, PROCEEDINGS see A87-13002 to A87-13017. J. C. ALCORN, ED. (Radio Technical Commission for Aeronautics, The present conference considers computer-integrated Washington. DC) Washington, DC, Radio Technical Commission manufacturing, the manufacture of bonded composite assemblies for Aeronautics, 1985. 163 p. For individual items see A87-11802 for aircraft, advancements in the condition monitoring of gears to A87-11807. and rolling element bearings, condition monitoring of large !+egress in ?he re3!izrr?i~nnf the IUS National Airspace System comme:cia! !u:bc!an engines, C"VP! gas ?nrbine me?eria!s, and (NAS) Plan, the organizations established to accomplish ?he Plan advanced fiber-ieinforced composites for aierame applicatioos. goals, and the prospects for upgrading internationally standard Also discussed are the future of air power in the defense of aviation communications, navigation and surveillance systems are Australia, future procurement and operations of rotary wing aircraft described. Details of the management structure devised to in the Royal Australia Navy, the future balance between Australian coordinate, monitor and support the joint government-industry aerospace-related education, research and industry, and the partnership which is implementing the NAS Plan are provided. educational requirements for the Royal Melbourne Institute of Government and industry points of view are presented, noting Technology aeronautical engineering degree. O.C. benefits of the various program structures and cost and technical tracking mechanisms which have been emplaced to ensure that A87-13002# the Plan goals are met. Finally, the results of studies by the ICAO THE INFLUENCE OF AEROSPACE DEVELOPMENTS UPON Future Air Navigation Systems Committee to identify DEVELOPMENTS IN MANUFACTURING communications, navigation and surveillance technologies and R. S. DAVIE, L. M. GILLIN, and J. K. RUSSELL (Swinburne Institute systems which might meet the requirements for becoming of Technology, Hawthorn, Australia) IN: Joint National Symposium international standards are discussed. M.S.K. on the Influence of Aviation on Engineering and the Future of Aeronautics in Australia, Melbourne, Australia, August 8, 9, 1985, Preprints . Barton, Australia/Brookfield, VT, Institution of EngineersBrookfield Publishing Co., 1985, p. 1-4. An interpretive development history is presented for the ways in which growing demands for higher precision and extreme fabrication process condition resistances in the processes and materials of the aerospace industry have served as drivers in manufacturing engineering generally. Aerospace design complexity A87-11802# has notably led to the intensive development of computer aided THE NEED TO EXECUTE THE NATIONAL AIRSPACE SYSTEM aesign ana manuiaciuring iecnnoiogies iiiai iiave subsaquetiiiy PROGRAMANDFORR6DBEYOND undergone very general application in other industries. O.C. D. D. ENGEN (FAA, Washington, DC) IN: Radio Technical Commission for Aeronautics, Annual Assembly Meeting and A87-13005# Technical Symposium, Washington, DC, November 19-21, 1985, MANUFACTURE OF BONDED COMPOSITE ASSEMBLIES FOR Proceedings . Washington, DC, Radio Technical Commission for AIRCRAFT Aeronautics, 1985, p. 21 -26. I. M. CUCKSON (Government Aircraft Factories, Melbourne, The goals and progress in implementation of the National Australia) IN: Joint National Symposium on the Influence of Airspace System (NAS) Plan are summarized in a speech by the Aviation on Engineering and the Future of Aeronautics in Australia, FAA Administrator. Most of the contracts that will be issued for Melbourne, Australia, August 8, 9, 1985, Preprints . Barton, the 90-program Plan have been signed, including the host Australia/Brookfield, VT, Institution of Engineers/Brookfield _LI:-L:__ e.- .nor computer, the ASR-p radar. an advancea auromarion system -ruuiiaiiiiiy vu., IJU.+ p. :S-22. development, a flight service automation system, the MLS, Mode The F/A-18 Trailing Edge Flap, which is currently being S, etc. Current Federal budget difficulties have not yet seriously manufactured in Australia as part of that country's participation in hampered the progress of the Plan. The system is expected to the F/A-18 program, exemplifies the critical structural components double ATC productivity while reducing System operations and that can be manufactured by bonding carbon fiber-reinforced maintenance personnel and costs by 1/3 by the year 2000. Finally, composite materials. Attention is presently given to the flap's a short history of FAA participation in experimental aerospace subelement manufacture in the form of laminates, and their bonding technology and communications programs over the past decade to a honeycomb, as well as to the nondestructive testing to which is provided. M.S.K. the finished assembly is subjected. O.C.

1 01 AERONAUTICS (GENERAL)

A87-130 12# A87-130 17# THE FUTURE OPERATIONS AND PROCUREMENT OF ROTARY DEVELOPMENTS AT ARL TO MEET FUTURE AUSTRALIAN WING AIRCRAFT IN THE ROYAL AUSTRALIAN NAVY NEEDS IN AERONAUTICS N. RALPH (Royal Australian Navy, Canberra, Australia) IN: Joint G. L. BROWN (Department of Defence, Aeronautical Research National Symposium on the Influence of Aviation on Engineering Laboratories, Melbourne, Australia) IN: Joint National Symposium and the Future of Aeronautics in Australia, Melbourne, Australia, on the Influence of Aviation on Engineering and the Future of August 8. 9, 1985, Preprints . Barton. Australia/Brookfield, VT, Aeronautics in Australia, Melbourne, Australia, August 8, 9, 1985, Institution of EngineerdBrookfield Publishing Co., 1985, p. 53-58. Supplementary Papers . Barton, Australia/Brookfield, VT, Institution of EngineerdBrookfield Publishing Co., 1985, p. 59-62. Current Australian Aeronautical Research Laboratory (ARL) programs are discussed, illustrating a trend away from civil work and towards military aviation, and emphasizing the impact of A87-13013# computing, material sciences, and microelectronics on aeronautics FUTURE DEVELOPMENTS AND MANUFACTURING AT GAF development. Military aviation programs include the development W. M. KlDD (Government Aircraft Factories, Melbourne, Australia) of combat models to evaluate missile performance and other IN: Joint National Symposium on the Influence of Aviation on defense issues, airframe life assessment and extension, and Engineering and the Future of Aeronautics in Australia, Melbourne, assessment of aircraft performance and fatigue life. Future Australia, August 8, 9, 1985, Preprints . Barton, Australia/Brookfield, directions of expansion such as avionic systems, integrated control, VT, Institution of Engineers/Brookfield Publishing Co., 1985, p. systems analysis, and helicopter activities are envisioned at ARL. 59-65. R.R. An evaluation is made of ongoing R8D work at Australia's Government Aircraft Factories (GAF). whose integrated development and manufacturing capability extends from the ability to conduct feasibility design studies to in-service support of manufactured products. In addition to aircraft system and component design, GAF has accumulated expertise in the design of control systems, the application of composite and superplastic metallic materials, the use of CAD, flight testing, environmental N87-10002# Federal Aviation Administration, Atlantic City, N.J. testing, chemical milling, and the structural bonding of advanced Technical Center. composites. O.C. HELICOPTER MLS FLIGHT INSPECTION PROJECT Final Report S. B. SHOLLENBERGER and B. R. BILLMANN Apr. 1986 251 P (DOT/FAA/CT-86/14) Avail: NTlS HC A12/MF A01 A87-13014# The results of tests designed to formalize microwave landing FUTURE DEVELOPMENTS AND MANUFACTURING AT C.A.C system (MLS) heliport flight inspection procedures are described. J. A. C. KENTWELL (Commonwealth Aircraft Corp., Ltd., Melbourne, The tests, conducted in November 1985, demonstrated the Australia) IN: Joint National Symposium on the Influence of feasibility of using a helicopter to perform some portion of the Aviation on Engineering and the Future of Aeronautics in Australia, flight inspection of the MLS at heliports. Significant findings included Melbourne, Australia, August 8, 9. 1985, Preprints . Barton, the fact that radio theodolite techniques could be used for tracking Australia/Brookfield, VT, Institution of Engineers/Brookfield a helicopter not equipped with stability augmentation equipment. Publishing Co., 1985, p. 66-71. Constituent parts of a portable flight inspection package were also An evaluation is made of recent advancements in the aircraft identified and tested. Author development and manufacturing technology available to an Australian proprietary firm concerned with airframes, engines, and defense-related equipment. The company is currently involved in Australian coproduction of the F/A-18 aircraft and of its F404 engine's components. A strong trend toward manufacturing facilities' automation is being supported. O.C. N87-10003'# Nielsen Engineering and Research, Inc., Mountain View, Calif. DEVELOPMENT OF A TURBOMACHINERY DESIGN A87-13016# OPTIMIZATION PROCEDURE USING A MULTIPLE-PARAMETER THE FUTURE OF INTERNATIONAL AIR TRANSPORT NONLINEAR PERTURBATION METHOD Final Report R. J. YATES (Qantas Airways, Ltd., Sydney, Australia) IN: Joint S. S. STAHARA Sep. 1984 260 p National Symposium on the Influence of Aviation on Engineering (Contract NAS3-20836) and the Future of Aeronautics in Australia, Melbourne, Australia, (NASA-CR-3831; NAS 1.263831; NEAR-TR-295) Avail: NTlS August 8, 9, 1985, Supplementary Papers . Barton, HC A12/MF A01 CSCL 016 Australia/Brookfield, VT, Institution of Engineers/Brookfield An investigation was carried out to complete the preliminary Publishing Co., 1985, p. 14-52. development of a combined perturbation/optimization procedure Modern aircraft are discussed with respect to the commercial and associated computational code for designing optimized and regulatory environment and technological advances, and with blade-to-blade profiles of turbomachinery blades. The overall emphasis on their impact on Australia's economy and commercial purpose of the procedures developed is to provide demonstration airlines. Towards the goals of reducing aircraft weight and cost of a rapid nonlinear perturbation method for minimizing the while increasing range capability, projected 747 changes include computational requirements associated with parametric design application of more powerful fuel efficient engines such as the studies of turbomachineryflows. The method combines the multiple Rolls Royce RE211 52404, a fly-by-wire flight control system and parameter nonlinear perturbation method, successfully developed advanced avionics to reduce the number of flight crew from three in previous phases of this study, with the NASA TSONIC to two, and new lightweight materials to enhance payload range blade-to-blade turbomachinery flow solver, and the capability. Increased bypass ratios in advanced turbofans, COPES-CONMIN optimization procedure into a user's code for ultrabypass ratio contra fans, and propfans are considered, in designing optimized blade-to-blade surface profiles of addition to aluminum-lithium alloys, carbon fiber reinforced plastics, turbomachinery blades. Results of several design applications and and thermoplastic composites. Other avionics and aerodynamics a documented version of the code together with a user's manual issues are examined. R.R. are provided. Author

2 02 AERODYNAMICS

N87-10004# Air Force Systems Command, Wright-Patterson AFB, N87-10830# Air Force Test Pilot School, Edwards AFB, Calif. Ohio. Foreign Technology Div. PERFORMANCE AND QUALITY FLIGHT TEST TEXTBOOK. ACTA AERONAUTICA ET ASTRONAUTICA SlNlCA (SELECTED VOLUME 2 FLYING QUALITIES ARTICLES) Apr. 1986 1640 p H. ZHANG, S. CHEN, X. CHEN, H. YAN, and X. HUO 9 May (AD-A168124) Avail: NTlS HC A99/MF A06 CSCL 01B 1986 94 p Transl. into ENGLISH from Hangkong Xuebao Flying qualities is that discipline in the aeronautical sciences (China), v. 6, no. 4, 1985 p 301-312; 321-334; 362-370; 379-384; that is concerned with basic aircraft stability and pilot-in-the-loop 393-404 controllability. With the advent of sophisticated flight control (AD-A167918; FTD-ID(RS)T-0109-86) Avail: NTlS HC A05/MF systems, vectored thrust, forward-swept wings, and negative static A01 CSCL20D margins, the concept of flying qualities takes on added dimensions. The following articles are from Acta Aeronautica et Astronautica In aeronautical literature there are three terms bandied about which Sinica, vo1.6, no. 4, 1985: Advances in the Study of Separated are generally considered synonymous. These terms are flying Flows; Longitudinal Stability Analysis of Elastic Vehicles; Numerical qualities, stability and control, and handling qualities. Among others, Computation of Two Phase Turbulent Combustion Processes; Gust the textbook contains the following articles: Introduction to Flying Alleviation Using Combined Control Laws; Calculation of Supersonic Qualities; Vectors and Matrices; Differential Equations; Equations Flows around a Three-dimensional Wing and a Waisted Body with of Motion; Longitudinal Static Stability; Maneuvering Flight; Characteristic Method in Stream Surface Coordinates; and Lateral-DirectionalStatic Stability; Dynamic Stability; Roll Coupling; Thermodynamic Analysis of Turbofan Engines. GRA High ; Engine-Out Theory and Flight Testing; Aeroelasticity; Feedback Control Theory, and Flight Control Systems. GRA

N87-10828'# Old Dominion Univ., Norfolk, Va. Dept. of Mechanical Engineering and Mechanics. GRADUATE ENGINEERING RESEARCH PARTICIPATION IN AERONAUTICS Final Report, period ending 31 Aug. 1986 02 A. S. ROBERTS, JR. Aug. 1986 80 p (Contract NGR-47-003-052) (NASA-CR-179798; NAS 1.26:179798) Avail: NTIS HC A05/MF AERODYNAMICS AOi 232iOiB The Aeronautics Graduate Research Program commenced in Includes aeredynzmics of bodies, combinations. wings, rotors, and 1971, with the primary goal of engaging students who qualified control surfaces; and internal flow in ducts and turbomachinery. for regular admission to the Graduate School of Engineering at Old Dominion University in a graduate engineering research and study program in collaboration with NASA Langley Research AW-10409 Center, Hampton, Virginia. The format and purposes of this program A NUMERICAL ANALYSIS OF SUPERSONIC BOTTOM FLOW are discussed. Student selection and program statistics are WITH THERMAL MODIFICATION OF THE WAKE [CHISLENNYI summarized. Abstracts are presented in the folowing areas: aircraft ANALIZ SVERKHZVUKOVOGO DONNOGO TECHENllA V design, aerodynamics, / characteristics; avionics; fluid USLOVIIAKH TEPLOVOGO VOZDElSTVllA NA SLED] mechanics; solid mechanics; instrumentation and measurement V. I. GOLOVICHEV Fizika Goreniia i Vzryva (ISSN 0430-6228), techniques; thermophysical properties experiments; large space vol. 22, May-June 1986, p. 78-84. In Russian. refs structures; earth orbital dynamics; and environmental engineering. Numerical solutions to full nonstationary Navier-Stokes B.G. equations are used to analyze the structure of an axisymmetric wake flow behind a body in the case of supersonic homogeneous flow past the body. In particular, the effect of fuel injection in the bottom region or into an inviscid supersonic flow is investigated in order to evaluate the efficiency of various methods of increasing N87-10829'# Kentron International, Inc., Hampton, Va. bottom pressure through heat transfer to the near wake. It is NUMERICAL METHODS AND A COMPUTER PROGRAM FOR shown that a combined method of thermal modification of bottom SUBSONIC AND SUPERSONIC AERODYNAMIC DESIGN AND flow provides an efficient way to reduce the drag of bodies moving ANALYSIS OF WINGS WITH ATTAINABLE THRUST at supersonic velocities. V.L. CONSIDERATIONS H. W. CARLSON and K. B. WALKLEY Washington NASA Auy. is84 78 p (Contract NASl-16000) A87-105 17# (NASA-CR-3808; NAS 1.263808) Avail: NTlS HC AO5/MF A01 UNSTEADY AERODYNAMIC MODELING OF A FIGHTER WING CSCL 01 B IN FLOW This paper describes methodology and an associated computer J. B. MALONE (Lockheed-Georgia Co., Advanced Flight Sciences program for the design of wing lifting surfaces with attainable Dept., Marietta), L. N. SANKAR (Georgia Institute of Technology, thrust taken into consideration. The approach is based on the Atlanta), and W. A. SOTOMAYER (USAF, Wright Aeronautical determination of an optimum combination of a series of candidate Laboratories, Wright-Patterson AFB, OH) Journal of Aircraft surfaces rather than the more commonly used candidate loadings. (ISSN 0021-8669), vol. 23, Aug. 1986, p. 61 1-620. Previously cited Special leading-edge surfaces are selected to provide distributed in issue 17, p. 2425, Accession no. A84-37975. refs leading-edge thrust forces which compensate for any failure to (Contract F33615-83-C-3215) schietve !he !u!! !hen!e!!ci! !nrrrling-edgp !hruc!, 2nd a gncnnd series of general candidate surfaces is selected to minimize drag subject to constraints on the lift coefficient and, if desired, on the pitching A87-10520# moment coefficient. A primary purpose of the design approach is VORTEX-STRETCHED FLOW AROUND A CRANKED DELTA the introduction of attainable leading-edge thrust considerations WING so that relatively mild camber surfaces may be employed in the A. RlZZl (Flygtekniska Forsoksanstalten, Bromma, Sweden) and achievement of aerodynamic efficiencies comparable to those C. J. PURCELL (ETA Systems, Inc.. Saint Paul, MN) Journal of attainable if full theoretical leading-edge thrust could be achieved. Aircraft (ISSN 0021-8669), vol. 23, Aug. 1986, p. 636-640. The program provides an analysis as well as a design capability Previously cited in issue 01, p. 5, Accession no. A86-11043. and is applicable to both subsonic and supersonic flow. Author refs

3 A87-10521# A87-10609 AERODYNAMIC ANOMALIES - CAN CFD PREVENT OR METHOD OF MERIDIONAL SECTIONS IN PROBLEMS CORRECT THEM? INVOLVING A THREE-DIMENSIONAL BOUNDARY LAYER R. S. SHEVELL (Stanford University, CA) Journal of Aircraft [METOD MERIDIONAL'NYKH SECHENll V ZADACHAKH (ISSN 0021-8669). vol. 23, Aug. 1986, p. 641-649. Previously cited PROSTRANSTVENNOGO POGRANICHNOGO SLOIA] in issue 01, p. 4, Accession no. A86-11033. refs V. V. LUNEV and E. A. SENKEVICH Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), May-June 1986, p. 67-73. In Russian. refs A87-10522'# North Carolina State Univ., Raleigh. It is shown that the problem of calculating the heat-transfer EULER EQUATIONS ANALYSIS OF THE INITIAL ROLL-UP OF distribution on the surface of a body in three-dimensional flow AIRCRAFT WAKES can be simplified substantially when the effect of R. A. MITCHELTREE, H. A. HASSAN (North Carolina State three-dimensionality is small. The three-dimensional problem is University, Raleigh), and R. J. MARGASON (NASA, Langley reduced to a set of two-dimensional problems along the lines of Research Center, Hampton, VA) Journal of Aircraft (ISSN meridional sections of the body. The exact boundary layer equations 0021-8669), vol. 23, Aug. 1986, p. 650-655. Previously cited in can be solved independently along each meridional plane. B.J. issue 07, p. 829, Accession no. A86-19675. refs (Contract NCC1-84) A87-106 10 A87-10523# EXCITATION OF THE NATURAL OSCILLATIONS OF A FURTHER DEVELOPMENT OF THE INFLUENCE FUNCTION BOUNDARY LAYER BY AN EXTERNAL ACOUSTIC FIELD METHOD FOR STORE AERODYNAMIC ANALYSIS [VOZBUZHDENIE SOBSTVENNYKH KOLEBANll A. CENKO (Hofstra University, Hempstead, NY). R. MEYER, and POGRANICHNOGO SLOIA VNESHNIM AKUSTICHESKIM F. TESSITORE (Grumman Aerospace Corp., Bethpage, NY) POLEM] Journal of Aircraft (ISSN 0021-8669), vol. 23, Aug. 1986, p. 656-661. A. A. MASLOV and N. V. SEMENOV Akademiia Nauk SSSR, Previously cited in issue 05, p. 584, Accession no. A83-16622. Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), May-June refs 1986, p. 74-78. In Russian. refs (Contract F33615-82-C-3007) An electric-dischargeapparatus was used to study the excitation of natural oscillations in a laminar boundary layer by an external acoustic field. Experiments were carried out in a supersonic wind A87-10524'# Informatics General Corp., Palo Alto, Calif. tunnel at a of 2.0. Three regions were found where UNSTEADY TRANSONICS OF A WING WITH TIP STORE the external acoustic perturbations are most effectively converted G. P. GURUSWAMY (Informatics General Corp., Palo Alto, CA), to the natural oscillations of a supersonic boundary layer on a flat P. M. GOORJIAN (NASA, Ames Research Center, Moffett Field, plate: the leading edge of the plate, the acoustic branch of the CA), and E. L. TU Journal of Aircraft (ISSN 0021-8669), vol. neutral curve, and the lower branch of the neutral stability curve. 23. Aug. 1986. p. 662-668. USAF-supported research. Previously B.J. cited in issue 07. p. 828, Accession no. A86-19633. refs

A87- 10614 A87-10525# NUMERICAL INVESTIGATION OF SUPERSONIC FLOW PAST BODY OF REVOLUTION COMPARISONS FOR AXIAL- AND SPIKE-TIPPED BLUNT BODIES [CHISLENNOE ISSLEDOVANIE SURFACE-SINGULARITY DISTRIBUTIONS SVERKHZVUKOVOGO OBTEKANIIA ZATUPLENNYKH TEL S J. M. DSA and C. DALTON (Houston, University, TX) Journal of VYDVINUTOI VPERED IGLOI] Aircraft (ISSN 0021-8669), vol. 23, Aug. 1986, p. 669-672. refs V. N. KARLOVSKll and V. I. SAKHAROV Akademiia Nauk SSSR, A comparison is made between the surface velocities generated Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), May-June by two different singularity methods of representing an axisymmetric 1986, p. 119-127. In Russian. refs body in an incompressible uniform flow, Le., the method of axial A method is developed for calculating the supersonic flow of ,singularities and the method of surface-distributed singularities. In an ideal gas near axisymmetric spike-tipped blunt bodies. An particular, the two methods are compared by performing analysis is made of the flow past a truncated cone with a spherically calculations for an ellipsoid of revolution (finess ratio 7) and for blunted cylindrical spike as a function of the ratio (K) of the spike an afterbody. The surface-singularity method is found to be the length to the diameter of the end part of the body, and as a better of the two approaches. Although this method needs a function of the Mach number. Several steady flow regimes were relatively larger number of points to represent adequately the observed, including a regime involving the formation of circulation geometry of a body and requires more computing time, its ability zones and internal shock waves in the shock layer. It is shown to represent even complex body shapes makes it the superior that the mounting of the spike on the truncated cone can reduce method. V.L. the cone drag by 40-50 percent. The drag coefficient is studied as a function of K at M = 3. B.J. A87-10603 DENSITY FIELD OF A VISCOUS GAS JET ISSUING FROM A CONICAL NOZZLE INTO VACUUM [POLE PLOTNOSTI STRUI A87-10615 VIAZKOGO GAZA, ISTEKAIUSHCHEGO I2 KONICHESKOGO CONICAL WING OF MAXIMUM LIFT-TO-DRAG RATIO IN A SOPLA V VAKUUM] SUPERSONIC GAS FLOW [KONICHESKOE KRYLO E. N. BONDAREV, M. P. BURGASOV, I. A. VASILEV, and A. S. MAKSIMAL'NOGO AERODINAMICHESKOGO KACHESTVA V KOKOREV Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti SVERKHZVUKOVOM POTOKE GAZA] i Gaza (ISSN 0568-5281), May-June 1986, p. 25-30'. In Russian. V. 1. LAPYGIN and P. V. TRETIAKOV Akademiia Nauk SSSR, refs Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), May-June An approximation dependence for calculating the density field 1986, p. 128-133. In Russian. refs in a viscous gas jet issuing from a conical nozzle into vacuum is A theoretical analysis of conical wings at Mach numbers greater derived on the basis of experimental data and the numerical solution than 2 shows that maximum lift-to-drag ratio is possessed by wings of the full system of Navier-Stokes equations. The dependence of with a flat lower surface. Simple analytical relationships are obtained jet parameters on is given for the Re number determining the wing aerodynamic characteristics at angles of range of 500-5000. The results are found to agree well with findings attack up to the separation of the bow shock from the leading for supersonic ideal-gas jets. B.J. edges. B.J.

4 02 AERODYNAMICS

A87-10618 A87-11117# CALCULATION OF UNSTEADY SUPERSONIC FLOW PAST A VORTEX SIMULATION OF PROPAGATING IN A LINEAR PLANE BLADE ROW UNDER THE EFFECT OF VORTEX CASCADE OF INHOMOGENEITIES IN THE ONCOMING FLOW [RASCHET C. G. SPEZIALE (Georgia Institute of Technology, Atlanta), F. NESTATSIONARNOGO SVERKHZVUKOVOGO OBTEKANIIA SISTO. and S. JONNAVITHULA (Stevens Institute of Technology, PLOSKOI RESHETKI PLASTIN PRI VOZDEISTVII NA NEE Hoboken, NJ) ASME, Transactions, Journal of Fluids Engineering VIKHREVYKH NEODNORODNOSTEI NABEGAIUSHCHEGO (ISSN 0098-2202), vol. 108, Sept. 1986, p. 304-312. refs POTOKA] (Contract NO001 4-84-K-0741) K. K. BUTENKO and A. A. OSlPOV Akademiia Nauk SSSR, A vortex method developed by Spalart (1984) is used in the Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), May-June numerical simulation of propagating stall in a linear cascade of 1986, p. 152-160. In Russian. refs airfoils at high Reynolds numbers. Calculations are presented for Ni's (1979) approach is used to calculate the unsteady flow a variety of flow geometries and several different flow regimes past a plane blade row under the effect of vortex inhomogeneities are obtained for a given cascade of airfoils, disturbance wavelength, in the supersonic oncoming flow. Formulas are obtained for the and stagger angle. These include attached flow for lower angles intensity of unsteady pressure shocks and vortex wakes shedding of attack and a chaotic deep stall configuration at larger angles from the blade trailing edges. Calculation examples are presented of attack; there is a narrow intermediate range of such angles which illustrate the accuracy of the method and its capabilities. where propagating stall takes place. The physical traits of this B.J. propagating stall are parameterized and a quantative study of the effects of camber and imposed wavelength is performed. K.K.

A87-10619 MATHEMATICAL MODELING OF SEPARATED FLOW PAST A WING PROFILE AND AERODYNAMIC HYSTERESIS A87-11411 University Coll. of Swansea (Wales). [MATEMATICHESKOE MODELIROVANIE OTRYVNOGO RECENT DEVELOPMENTS IN FEM-CFD OBTEKANIIA KRY LOVOGO PROFILIA I R. LOEHNER, K. MORGAN, J. PERAIRE, and 0. C. ZlENKlEWlCZ AERODINAMICHESKOGO GISTEREZISA] (Swansea, University College, Wales) IN: The Free-Lagrange S. M. BELOTSERKOVSKII. V. N. KOTOVSKII, M. 1. NISHT, and method; Proceedings of the First International Conference, Hilton R. M. FEDOROV Akademiia Nauk SSSR, Izvestiia, Mekhanika Head Island. SC, March 4-6, 1985 . Berlin and New Yori, Zhidkosti i Gaza (ISSN 0568-5281), May-June 1986, p. 161-169. Springer-Verlag, 1985, p. 236-254. Research supported by the In Russian. refs Ministerio de Educacion y Ciencia of Spain. refs The unsteady-flow approaches of Kotovskii et al. (1982, 1983, (Contract NAGW-478) 1984). based on ideal-fluid and boundary-layer models, are The current status of CFD with regard to unstructured grids extended. This makes it possible to describe the separated flow employing finite element methods and Eulerian frames is reviewed. past a wing profile in a wide range of angles of attack with Algorithms suitable for the computation of large three-dimensional allowance for separation on the surface as well as the hysteresis problems involving flow past arbitrary geometries are developed. phenomenon. The proposed model allows a detailed investigation Adaptive mesh refinement strategy is reviewed, and domain splitting of unsteady processes in the boundary layer on the profile surface or local time-stepping are briefly addressed. The development of and in the near aerodynamic wake. B.J. search algorithms of optimal order, variable time-stepping Jacobi smoothers for elliptic problems, and transport concepts for hyperbolics to help achieve good performance for unstructured multigrid processes is discussed. As examples, transient supersonic flow in a channel, regular shock reflection of a wall, viscous flow A87-10620 past a protruberance, potential flow past a cylinder, and Burgers OPTIMAL CONTROL OF VISCOUS FLOW AT HIGH REYNOLDS equation are considered. C.D. NUMBERS [OPTIMAL'NOE UPRAVLENIE VlAZKlM POTOKOM PRI BOL'SHIKH CHISLAKH REINOL'DSA] M. A. BRUTIAN, P. L. KRAPIVSKII, and V. V. SYCHEV Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), May-June 1986, p. 174-176. In Russian. An effort is made to determine the theoretical minimum of A87-11487' National Aeronautics and Space Administration. dray UII a body iiiai itin be &~,hiev& ihiaugh boi~darjkje: Amee Resea:ch Cenk:, ?.!sffc!! Fio!d, CZ!!!. control via suction or blowing. This problem is investigated for the COMPUTATION OF TURBULENT SUPERSONIC FLOWS laminar flow of a viscous incompressible fluid past a body at high AROUND POINTED BODIES HAVING CROSSFLOW Reynolds numbers. Drag minimization is considered for a sphere SEPARATION and for planar bodies. B.J. D. DEGANI and L. B. SCHIFF (NASA, Ames Research Center, 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 A87-10675 of Schiff and Steger (1980) is extended to the case of turbulent MOTION OF A GAS IN A DUCT BEHIND A MOVING BODY supersonic flows on pointed bodies at high angles of attack. The :DV:ZHEH!E QAZA \' KAHALE z.4 PO"V!LHI?VU TELnuj Gnvnrning equations, the numerical scheme. and modifications to V. F. MAKSIMOV and IU. G. FlLlPPOV Moskovskii Universitet, the algebraic eddy-viscosity turbulence model are described; and Vestnik, Seriia 1 - Matematika, Mekhanika (ISSN 0579-9368), results for three cones and one ogive-cylinder body (obtained using May-June 1986, p. 111-1 13. In Russian. grids of 50 nonuniformly spaced points in the radial direction The nonstationary two-dimensional problem of gas flow behind between the body and the outer boundary) are presented an elongated body accelerating to supersonic velocities is solved graphically and compared with published experimental data. The numerically, and a computer simulation is carried out using a grids employed are found to provide sufficient spatial resolution program written in FORTRAN. A pattern of reverse flow in the of the leeward-side vortices; when combined with the modified bottom region developing with increasing body velocity is obtained. turbulence model, they are shown to permit accurate treatment of A comparison is made with the one-dimensional case. V.L. flows with large regions of crossflow separation. T.K.

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A87-11495# A87-11516 CALCULATION OF BOUNDARY LAYER OF A THREE APPLICATION OF A 2D TIME-MARCHING EULER CODE TO DIMENSIONAL SSHAPED INLET TRANSONIC TURBOMACHINERY FLOW Z. XING and S. ZEN Northwestern Polytechnical University, H.-W. HAPPEL (MTU, Motoren- und Turbinen-Union Muenchen Journal, vol. 4, July 1986, p. 361-370. In Chinese, with abstract in GmbH, Munich, West Germany) IN: Conference on Numerical English. refs Methods in Fluid Mechanics, 6th, Goettingen, West Germany, A simplified, fast-computation time method is presented for September 25-27, 1985, Proceedings . Brunswick, West Germany, modeling the three-dimensional boundary layer in an S-shaped jet Friedr. Vieweg und Sohn, 1986, p. 129-136. Research supported engine intake design. A streamline coordinate system is by the Bundesministerium der Verteidingung. refs implemented over the S-shaped geometry in order to reduce the This paper describes a time-marching finite area method to problem to that of an axisymmetric flow. A perturbation method is obtain the steady 2D blade-to-blade solution along an axisymmetric embedded in the flow calculations to accelerate identification of stream surface with changing radius and stream tube thickness. the streamline flow axes and the location of the edge of the The conservation laws are solved in a rotating frame. The numerical boundary layer. Sample calculations are provided for S-shaped scheme is explicit and first order accurate in time and space. To inlets with free stream Mach numbers ranging from 0.5-0.9 and achieve stability, explicit numerical viscosity is added. In order to varying mass ratios. The model outputs, which can be obtained increase the convergence speed, a sequential grid-refining with a personal computer, show reasonable agreement with procedure and a multiple-grid algorithmus are used in the code. experimental data on the variation of the boundary layer The accuracy and computational efficiency of the computer code parameters. M.S.K. are demonstrated for realistic blade geometries. The comparison with measurements shows good agreement for turbine and compressor cascades. Author A87-11509' National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. NUMERICAL SIMULATION OF VISCOUS SUPERSONIC FLOW OVER A GENERIC FIGHTER CONFIGURATION D. S. CHAUSSEE (NASA, Ames Research Center, Moffett Field, CA). G. BLOM (Boeing Co., Seattle, WA), and J. WAI IN: A87-11526 Conference on Numerical Methods in Fluid Mechanics, 6th. NUMERICAL EXPERIMENTS WITH A TOTAL VARIATION Goettingen, West Germany, September 25-27, 1985, Proceedings DIMINISHING (TVD) MACCORMACK SCHEME . Brunswick, West Germany, Friedr. Vieweg und Sohn, 1986, p. C. M. KWONG (Salford, University, England) IN: Conference on 63-69. Previously announced in STAR as N86-15627. refs Numerical Methods in Fluid Mechanics, 6th, Goettingen, West Germany, September 25-27, 1985, Proceedings . Brunswick, West Germany, Friedr. Vieweg und Sohn, 1986, p. 217-224. Research supported by the Ministry of Defence of England. refs A87-11510 The application of a TVD MacCormack scheme is outlined A PRE-PROCESSED IMPLICIT ALGORITHM FOR 3D VISCOUS and assessed. The scheme is seen to be robust, to resolve COMPRESSIBLE FLOW discontinuities well, to be free from oscillations typical of second W. N. DAWES (Central Electricity Generating Board, Whittle or higher order accurate schemes and to have no Laboratory, Cambridge, England) IN: Conference on Numerical problem-dependent parameters to be adjusted. Following the Methods in Fluid Mechanics, 6th. Goettingen, West Germany, numerical procedure outlined in this paper, many existing September 25-27, 1985, Proceedings . Brunswick, West Germany, MacCormack algorithms can be modified to good effect. The TVD Friedr. Vieweg und Sohn, 1986, p. 70-77. refs property of the scheme is demonstrated by the numerical The efficient numerical simulation by time marching methods computations relating to the 1-D linear wave equation and the of high Reynolds number compressible flow in turbomachine nonlinear inviscid Burger's equation. The scheme is further used geometries is considered. An algorithm is developed with to solve the inviscid Euler equations in one- and two-dimensions guaranteed diagonal dominance and low operation count by relating to practical transonic and supersonic flow problems. preprocessing the basic Beam-Warning implicit algorithm with a Comparisons between three schemes - MacCormack, suitable matrix operator. Results for the flow in a linear cascade Operator-Switching MacCormack-Upwind, and TVD MacCormack of turbine blades demonstrate the development of the passage schemes are also shown. Author vortex and associated strong three-dimensional effects. R.R.

A87-115 12 EULER SOLUTIONS ON 0-0 GRIDS AROUND WINGS USING LOCAL REFINEMENT A87-11528 L.-E. ERIKSSON (Flygtekniska Forsoksanstalten, Bromma, EFFICIENT NUMERICAL METHOD FOR TRANSONIC FLOW Sweden) IN: Conference on Numerical Methods in Fluid SIMULATIONS Mechanics, 6th, Goettingen, West Germany, September 25-27, E. VON LAVANTE (Old Dominion University, Norfolk, VA) and D. 1985, Proceedings . Brunswick, West Germany, Friedr. Vieweg CLAES (Bochum, Ruhr-Universitaet, West Germany) IN: und Sohn, 1986, p. 86-96. refs Conference on Numerical Methods in Fluid Mechanics, 6th, Local grid refinement as a means to improve the accuracy of Goettingen, West Germany, September 25-27, 1985, Proceedings finite-difference solutions to the Euler equations is here investigated . Brunswick, West Germany, Friedr. Vieweg und Sohn, 1986, p. in both two and three space dimensions. Two alternative 233-240. refs conservative interface conditions for the centered finite-volume A numerical method for solving the two-dimensional steady scheme with explicit multistage time-stepping are described and Euler equations using flux vector splitting is developed. The applied to the computation of steady Euler solutions on locally equations are expressed in curvilinear coordinates and the finite refined 0-type grids around wings. In 2D a comparison between volume approach is used. The energy equation is omitted since the two interface conditions shows that they perform equally well only steady state solutions are required. Depending on the Mach and are stable even when shocks intersect the interface. One of number levels in the flow two different implicit operators are the interface conditions is also investigated in 3D and several employed to enhance the stability properties of the present method. computed examples show that it performs equally well in this Present numerical results for several two-dimensional internal flow case also. Stability is achieved even when shocks or vortices configurations are compared with predictions obtained by other intersect the interface. Author authors. Author

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A87-11533 A87-11540 IMPLICIT FINITE-DIFFERENCE SIMULATION OF SEPARATED CALCULATION OF STRONG VISCOUS/INVISCID HYPERSONIC FLOW OVER AN INDENTED NOSETIP INTERACTIONS ON AIRFOILS BY ZONAL SOLUTIONS OF THE B. MUELLER and D. RUES (DFVLR. lnstitut fuer Theoretische NAVIER-STOKES EQUATIONS Stroemungsmechanik, Goettingen, West Germany) IN: Conference M. A. SCHMATZ (Messerschmitt-Boelkow-Blohm GmbH, Munich, on Numerical Methods in Fluid Mechanics, 6th, Goettingen. West West Germany) IN: Conference on Numerical Methods in Fluid Germany, September 25-27, 1985, Proceedings . Brunswick, West Mechanics, 6th. Goettingen, West Germany, September 25-27. Germany, Friedr. Vieweg und Sohn, 1986, p. 271-278. 1985, Proceedings . Brunswick, West Germany, Friedr. Vieweg DFG-supported research. refs und Sohn, 1986. p. 335-342. DFG-supported research. refs Laminar hypersonic flow over a severely indented blunt nosetip A method is presented to predict viscous/inviscid interacting at zero angle of attack is simulated by solving the axisymmetric flows by coupling iteratively zonal solutions of different fluid dynamic Navier-Stokes equations using an implicit finite-difference method. equations. Subdomains of weak interaction, where the Euler and New forms of convergence acceleration to the steady state are the boundary layer equations together yield the equivalent inviscid presented. The validity of the thin-layer approximation is confirmed flow, are coupled with domains of strong interactions. There the for flow with a large separation region at high Reynolds numbers. Navier-Stokes equations are solved. Characteristic boundary Author conditions are used at artificial boundaries of the overlapping computational grids due to the mathematical character of the A87-11536' National Aeronautics and Space Administration. equations. The two-dimensional calculations performed for Ames Research Center, Moffett Field, Calif. subsonic and transonic flow problems indicate that the method A SIMULATION OF ROTOR-STATOR INTERACTION USING THE should be an efficient aerodynamic tool in three-dimensional EULER EQUATIONS AND PATCHED GRIDS problems, too. Author M. M. RAI (NASA, Ames Research Center, Moffett Field, CA) IN: Conference on Numerical Methods in Fluid Mechanics, 6th, Goettingen, West Germany, September 25-27, 1985, Proceedings . Brunswick, West Germany, Friedr. Vieweg und Sohn. 1986, p. 295-301. Previously announced in STAR as N86-17014. refs

A87-11537 A87-11542' Old Dominion Univ., Norfolk, Va. NUMERICAL EXPERIMENT WITH INVISCID FINITE ELEMENT COMPUTATIONS FOR HIGH SPEED 30 ..A__ Y ------..-- ...... --.- C. -... I vun I EA-~I nc I ~ntuFiUw AROUND A CRANKED DEiiA itvv1ac.w rLuwa WING, E. A. THORNTON and R. RAMAKRISHNAN (Old Dominion A. RlZZl (Flygtekniska Forsoksanstalten, Bromma, Sweden) and University, Norfolk, VA) IN: Conference on Numerical Methods C. J. PURCELL (ETA Systems, Inc., Saint Paul, MN) IN: in Fluid Mechanics, 6th, Goettingen, West Germany, September Conference on Numerical Methods in Fluid Mechanics, 6th, 25-27. 1985, Proceedings . Brunswick, West Germany, Friedr. Goettingen, West Germany, September 25-27, 1985, Proceedings Vieweg und Sohn, 1986, p. 359-366. NASA-supported research. . Brunswick, West Germany, Friedr. Vieweg und Sohn, 1986, p. Recent progress in the development of finite element 310-318. methodology for the prediction of aerothermal loads is described. A numerical method that solves the Euler equations for Three dimensional, inviscid computations are presented, but compressible flow is used to study vortex stretching. The particular emphasis is placed on development of an approach extendable case simulated is supersonic flow of freestream Mach number 1.2 to three dimensional viscous flows. Progress in key research areas and alpha of 10 deg around the twisted and cambered is described. Initial 30 results from the computational procedure cranked-and-cropped TKF of MBB. This geometry are described. Author induces multiple leading-edge vortices in a straining velocity field that brings about flow instabilities, but the result is a state of statistical equilibrium. The discretization contains over 600.000 cells and offers sufficient degrees of freedom in the solution to resolve the small-scale unstable modes that lead to disordered vortex flow. Author A87-11544 A87-11538 A SPLIT-MATRIX METHOD FOR THE INTEGRATION OF THE NUMERICAL SOLUTION OF THE EULER EQUATIONS USING QUASI-CONSERVATIVE EULER-EQUATIONS RATIONAL RUNGE-KUlTA METHOD C. WEILAND (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn, N. SATOFUKA. K. MORINISHI. and H. TOKUNAGA (Kyoto Institute West Germany! IN. Conference nn Niimerical Methods in Fleid of Technology, Japan) IN: Conference on Numerical Methods in Mechanics, 6th, Goettingen. West Germany, September 25-27, Fluid Mechanics, 6th. Goettingen, West Germany, September 1985, Proceedings , Brunswick, West Germany, Friedr. Vieweg 25-27, 1985, Proceedings . Brunswick, West Germany, Friedr. und Sohn, 1986, p. 383-390. refs Vieweg und Sohn, 1986, p. 319-326. refs A finite difference method based on the theory of characteristics A simple and efficient numerical method for solving the Euler is presented for the integration of the quasi-conservative equations is proposed which consists of a combination of the Euler-equations. The eigenvalues and the sets of left and right central finite difference approximation to the space variables with eigenvectors which diagonalize the coefficient matrices are the rational Runge-Kutta time integration scheme. Residual obtained from the nonconservative Euler-equations, and the averaging and multigriding are included into the basic scheme to coefficient matrices and the left and right eigenvectors for the improve the rate of convergence to the steady state solution. The conservative variables are derived from a simple similarity performance of the algorithm is demonstrated for two dimensional transformation. Special attention is paid to the boundary conditions transonic tlow past NAGA0012 and RAE2822 airfoils, and good at impermeable boundaries, and an algorithm utilizing the agreement is found between pressure distributions obtained with compatibility equations at a distance of a half cell width from the the present method and those derived from the Beam-Warming boundary where the sign of the eigenvalue is unique is introduced scheme. Though three times as many steps are required with the to overcome the failure, produced by the set of characteristic present method, only one-fourth of the CPU time/time step is compatibility equations which transmit the information from the needed in comparison with the Beam-Warming method. The field to the boundary, in the conservation of the total enthalpy. present method is easily vectorizable without additional Results are presented for supersonic blunt-body flow, transonic requirements such as extra memory, and extension to flow past airfoils, and transonic and supersonic flow past engine three-dimensional problems is straightforward. R.R. inlets. R.R.

7 02 AERODYNAMICS

A87-11782' Douglas Aircraft Co.. Inc., Long Beach, Calif. location of transition is crucial for accurate or detailed computations, NUMERICAL AND PHYSICAL ASPECTS OF AERODYNAMIC particularly at high angles of attack. When the upstream influence FLOWS Ill; PROCEEDINGS OF THE THIRD SYMPOSIUM, of pressure field through the shear layer is important, the thin-layer CALIFORNIA STATE UNIVERSITY, LONG BEACH, CA, Navier-Stokes procedure has an edge over the interactive JANUARY 21-24, 1985 procedure. Author T. CEBECI, ED. (Douglas Aircraft Co.; California State University, Long Beach) Symposium supported by NASA, US. Army, NSF, A87-11786 and U.S. Navy. New York, Springer-Verlag. 1986. 493 p. For COMPUTATIONS OF SEPARATED SUBSONIC AND TRANSONIC individual items see A87-11783 to A87-11786. FLOW ABOUT AIRFOILS IN UNSTEADY MOTION The present symposium considers hydrodynamic stability and R. HOUWINK (Nationaal Lucht- en Ruimtevaartlaboratorium, turbulent transition, transition calculations in three-dimensional Amsterdam, Netherlands) IN: Numerical and physical aspects of flows, a quasi-simultaneous finite difference approach for strongly aerodynamic flows 111; Proceedings of the Third Symposium, Long interacting flows, the significance of the thin layer Navier-Stokes Beach, CA, January 21-24, 1985 . New York, Springer-Verlag. approximation, unsteady airfoil boundary layers, predictions and 1986, p. 272-285. Research supported by the Nederlands lnstituut experiments on airfoils at low Reynolds numbers, and a comparison voor Vliegtuigontwikkelingen Ruimtevaart. of interactive boundary layer and thin layer Navier-Stokes An investigation is made of the applicability of the NASA-Ames procedures. Also discussed are a viscous-inviscid interaction code LTRAN2 for the unsteady aerodynamic and aeroelastic method for computing unsteady transonic separation, massive characteristics of airfoils, and an assessment is made of its separation and dynamic stall on a cusped trailing edge airfoil, the limitations through correlation of recent theoretical results with computation of turbulent separated flows over wings, an iterative experimental data. For a supercritical airfoil oscillating in pitch scheme for three-dimensional transonic flows, and the computation with shock-induced separation, computed results are compared of three-dimensional flows with shock wave/boundary layer with experimental data showing the effect of Mach number and interaction. Many of the papers in this symposium were abstracted reduced frequency. Results are presented for the RA.16.SCl and previously (cf., A85-42951). O.C. NACA 0012 airfoils. The aerodynamic resonance phenomena measured at higher frequency is not predicted; at low reduced A87-11783 frequency, however, the effect of Mach number on unsteady CALCULATION METHODS FOR AERODYNAMIC FLOWS - A airloads on an oscillating airfoil is attached and separated transonic REVIEW flow is well predicted. O.C. T. CEBECI (California State University, Long Beach) and J. H. WHITELAW (Imperial College of Science and Technology, London, A87-11890' National Aeronautics and Space Administration. England) IN: Numerical and physical aspects of aerodynamic Langley Research Center, Hampton, Va. flows 111; Proceedings of the Third Symposium, Long Beach, CA, DRAG REDUCING OUTER-LAYER DEVICES IN ROUGH WALL January 21 -24, 1985 . New York, Springer-Verlag, 1986, p. 1-19. TURBULENTBOUNDARY LAYERS (Contract NSF MEA-80-18565) P. R. BANDYOPADHYAY (NASA, Langley Research Center, The solution of inviscid flow equations for the design of Hampton, VA) Experiments in Fluids (ISSN 0723-4864), vol. 4, three-dimensional bodies is well established, and provides useful no. 5, 1986, p. 247-256. refs information on lift at lower angles-of-attack. As this angle increases, (Contract NASI-17296) so does the need to consider the influence of the viscous layer; The ability of outer-layer devices to reduce wall shear stress interactive methods developed for airfoil flows can be extended over a substantial streamwise distance in rough-wall turbulent to the cases of three-dimensional flow. At high angles of attack, boundary layers has been studied experimentally. The devices separation can occur, and the relative merits of interactive examined are a pair of thin flat ribbons placed in tandem as well inviscid-viscous procedures and the time-averaged Navier-Stokes as those having symmetric airfoil sections. The wall conditions equations become less certain. Unsteady two-dimensional flows examined are smooth, d- and k-type transverse-groove and also become increasingly difficult to deal with as the angle-of-attack sandgrain roughnesses. The wall drag is found to be reduced increases, so that they are influenced by the frequency of the from the respective normal levels in all rough walls. All k-type unsteadiness. O.C. rough walls exhibit a similar level of relative wall drag reduction which is also smaller than that in a smooth-wall. The d-type rough A87-11785' National Aeronautics and Space Administration. walls exhibit a transitional behaviour - the relative wall drag Ames Research Center, Moffett Field, Calif. reduction drops from the smooth wall level to that of the k-type A COMPARISON OF INTERACTIVE BOUNDARY-LAYER AND roughness with increasing roughness Reynolds number. However, THIN-LAYER NAVIER-STOKES PROCEDURES the absolute reductions in the local wall shear stress are similar U. MEHTA (NASA, Ames Research Center, Moffett Field, CA), K. in both the rough and smooth walls. On the other hand, the relative C. CHANG, and T. CEBECI (Douglas Aircraft Co., Long Beach, reductions are lower in the rough walls because of a higher CA) IN: Numerical and physical aspects of aerodynamic flows reference drag which is caused by the unique presence of a 111; Proceedings of the Third Symposium, Long Beach, CA, January pressure component on which the devices are not as effective. 21-24, 1985 . New York, Springer-Verlag. 1986, p. 198-215. Author Previously announced in STAR as N86-15244. Numerical procedures for solving the thin-shear-layer A87-12052 Navier-Stokes equations and for the interaction of solutions to ON THE LARGE-SCALE STRUCTURES IN TWO-DIMENSIONAL, inviscid and boundary-layer equations are described and evaluated. SMALL-DEFICIT, TURBULENT WAKES To allow appraisal of the numerical and fluid dynamic abilities of I. WYGNANSKI, F. CHAMPAGNE, and B. MARASLI (Arizona, the two schemes, they have been applied to one airfoil as a University, Tucson) Journal of Fluid Mechanics (ISSN 0022-1120), function of angle of attack at two slightly different Reynolds vol. 168, July 1986, p. 31-71. refs numbers. The NACA 0012 airfoil has been chosen because it (Contract F49620-79-C-0224) allows comparison with measured lift, drag, and moment and with Two-dimensional turbulent small-deficit wakes are studied using surface-pressure distributions. Calculations have been performed the University of Arizona wind tunnel facility in order to determine with algebraic eddy-viscosity formulations. and they include the structure of the waves and the universality of their consideration of transition. The results are presented in a form self-preserving states. Theoretical considerations are discussed and that allows easy appraisal of the accuracy of both procedures the experimental results are presented on a variety of wake and of the relative costs. The interactive procedure is generators, including circular cylinders, a symmetrical airfoil, a flat computationally efficient but restrictive relative to the thin-layer plate, and an assortment of screens of varying solidity, for a wide Navier-Stokes procedure. The latter procedure does a better job range of downstream distances. The results indicate that the of predicting drag than does the former. In both procedures, the normalized characteristic velocity and length scales depend on

8 02 AERODYNAMICS

the initial conditions, while the shape of the normalized mean basic relationships for the calculation of the flow parameters of velocity profile is independent of these conditions or the nature of coupled lifting surfaces in incompressible flow are presented. the generator. On the other hand, the normalized distributions of Results for both aerodynamic forces and the flow field are given. the longitudinal turbulence intensity are dependent on the initial Author conditions. IS. A87-12205 A87-12145 EXPERIMENTAL INVESTIGATION ON THE PERFORMANCES EXPERIMENTAL INVESTIGATIONS OF THREE-DIMENSIONAL OF A TRANSONIC TURBINE BLADE CASCADE FOR VARYING LAMINAR BOUNDARY LAYERS ON A SLENDER DELTA WING INCIDENCE ANGLES [EXPERIMENTELLE UNTERSUCHUNG DREIDIMENSIONALER G. BENVENUTO and F. PITTALUGA (Genova, Universita, Genoa, LAMINARER GRENZSCHICHTEN AN ElNEM SCHLANKEN Italy) IN: Measurement techniques in heat and mass transfer . DELTAFLUEGEL] Washington, DC, Hemisphere Publishing Corp., 1985, p. 179-191. D. HUMMEL (Braunschweig, Technische Universitaet, Brunswick, refs West Germany) Zeitschrift fuer Flugwissenschaften und The paper presents and discusses the experimental results Weltraumforschung (ISSN 0342-068X), vol. 10, May-June 1986, p. obtained in a transonic wind tunnel concerning a low-deflection 133-145. In German. refs turbine-blade cascade tested in correspondence with different The three-dimensional laminar boundary layers on the upper outlet Mach numbers and incidence angles. The flow-visualization and the lower surface of a lambda = 1.0 delta wing at an angle apparatus is described, indicating the peculiarities of the different of attack of alpha = 20.5 deg and a Reynolds number Re = techniques adopted (shadow, black and white or color schlieren). 900,000 have been investigated by means of pressure distribution Flow-visualization pictures are presented and correlated to the and boundary layer measurements and by surface oil flow patterns. aerodynamic analysis. Author The pressure distribution, the slope of the wall streamlines, the local flow direction at the wall and at the edge of the boundary layer, the boundary layer thickness and some characteristic velocity A87-12266 profiles are presented for both boundary layers. An accelerated THE PREDICTION OF THE DRAG OF AEROFOILS AND WINGS external flow acts on the pressure side of the wing whereas, on AT HIGH SUBSONIC SPEEDS the suction side downstream of the minimum pressure, a steep R. C. LOCK (Royal Aircraft Establishment, Farnborough, England) pressure rise is present and this leads to at 68 Aeronautical Journal (ISSN 0001-9240), vol. 90, June-July 1986, percent nf the Inca1 half span. Considerably skewed velocity profiles p. 207-226. refs were !wnd in bc?h becndary !ayers. .A comparison with theoretical After a brief discussion ot alternative ways in which rne drag results for the suction side by Cooke (1967) shows good agreement of an aircraft wing can be derived theoretically, attention is focused between a quasi-conical finite difference boundary layer calculation on a technique whereby the separate 'far-field' components of and the experimental data. Author drag - viscous, trailing-vortex (induced) and wave - are calculated separately. In particular, a new approximate method is described A87-12146 for estimating the wave drag. Based on an exact two-dimensional A LAMINAR BOUNDARY LAYER METHOD FOR FLOWS IN analysis involving the flow conditions just upstream of the shock PLANES OF SYMMETRY AND APPLICATION TO INCLINED wave, a simple formula is derived which, to first order, involves ELLIPSOIDS OF REVOLUTION [LAMINARES only a knowledge of the Mach number distribution on the surface GRENZSCHICHTVERFAHREN FUER STROEMUNGEN IN of the aerofoil ahead of the shock and of the surface geometry SYMMETRIEEBENEN UND ANWENDUNG AUF ANGESTELLTE at its foot. The accuracy of this formula is assessed for aerofoils ROTATIONSELLIPSOIDE] by comparison with more exact theoretical results and with H. W. STOCK (Dornier GmbH, Friedrichshafen, West Germany) experiment. A 'strip theory' extension to swept wings is proposed Zeitschrift fuer Flugwissenschaften und Weltraumforschung (ISSN and illustrated by applying it to a particular transport-type wing 0342-068X). vol. 10, May-June 1986, p. 146-157. In German. body combination. Using experimental pressure measurements as refs input, all three components of drag are estimated theoretically, An integral method for computing laminar, compressible and by adding their sum to separate balance measurements of boundary layer flow in planes of symmetry is presented. It is based the body drag comparisons between 'theory' and experiment for on a method for three-dimensional boundary layers. The flow on the overaii drag can be made. These show a satisfactory standard the windward- and leeward side of inclined ellipsoids of revolution of accuracy, the error varying between -5 pct and -1 pct of the is investigated. The analytical expression of the potential flow theory total drag over a wide range of Mach number and lift coefficient. is used to describe the inviscid outer flow. The results are compared Author with measurements, in regions of weak viscous interactions, and .a- wiin compuiaiions usiriy iiriiie riiiieieii~e iiieitiods. Speciai atteniiofi not- -...... -ILL~~ is paid to the leeside motion of the separation point, as influenced AN EXACT INTEGRAL (FIELD PANEL) METHOD FOR THE by changing the angle of attack and the axis ratio of the ellipsoid. CALCULATION OF TWO-DIMENSIONAL TRANSONIC It is shown that the separation point on the leeside suddenly POTENTIAL FLOW AROUND COMPLEX CONFIGURATIONS jumps from the rear part of the body to the nose region when the P. M. SlNCLAlR (British Aerospace, PLC, Military Aircraft Div., angle of attack is increased. The influence of the axis ratio on Brough, England) Aeronautical Journal (ISSN 0001-9240), vol. this critical angle of attack is described, and the axis ratio for 90, June-July 1986, p. 227-236. refs which the jump no longer occurs is determined. Author An integral formulation for the two-dimensional full potential equation is discussed. The basic principles of the standard panel A87-12148 and field methods are reviewed. The discretization of the equations THEORETICAL TREATMENT OF GUST SIMULATION IN THE and the iterative scheme for solving singularities. surface, and ..rahmn TI ILI~ICI r~uCnDCTiCt-uC "_,,_,._L1,._ EEP ..ll.Y I"I.I.LL L ,,,L",.bl IV1I.L m=uAUnl 'IUr! !ie!d of !he fie!d psnc! methnd are dnsarihnd The scheme is BOEENSIMULATION IM WINDKANAL] modified in order to be applied to the study of transonic flows. B. LASCHKA and W. WEGNER (Braunschweig. Technische The field panel method is applied to two single airfoils at subcritical Universitaet, Brunswick, West Germany) Zeitschrift fuer and supercritical Mach numbers and to three multielement airfoils. Flugwissenschaftenund Weltraumforschung (ISSN 0342-068X), vol. The results are compared to data obtained with the standard panel 10, May-June 1986, p. 168-173. In German. refs method based on the linear Prandtl-Glauert equation and the During the past years, gust generators consisting of a system Garabedian-Korn (1972) method; good correlation of the data is of oscillating lifting surfaces have been or are being prepared for detected. The application of the field panel method to transonic use in wind tunnels. The corresponding gust field can be assessed flow about complex three-dimensional geometries is proposed. by applying unsteady wing theories. In the present report, the I.F.

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A87-12586 A87-12805 ON THE OCCURRENCE OF REGULAR REFLECTION OF INDUCED DRAG OF A CURVED WING [INDUKTIVNOE SHOCKS IN CONCAVE CORNER FLOWS SOPROTIVLENIE IZOGNUTOGO KRYLA] R. NIEHUIS, H. SCHOELER, and H. HORNUNG (DFVLR, lnstitut G. I. MAIKAPAR PMTF - Zhurnal Prikladnoi Mekhaniki i fuer Experimentelle Stroemungsmechanik, Goettingen, West Tekhnicheskoi Fiziki (ISSN 0044-4626), May-June 1986, p. 38-40. Germany) IN: Shock waves and shock tubes; Proceedings of In Russian. the Fifteenth International Symposium, Berkeley, CA, July An equation is presented which provides a way to determine, 28-August 2, 1985 . Stanford, CA, Stanford University Press, 1986, from the wing shape, the cross-sectional shape of a free vortex p. 155-161. refs sheet at infinity behind the system wing-fuselage (in the Trefftz Results are reported from a theoretical and experimental study plane). The effect of the wing curvature on the minimal induced of regular reflection (RR) of shock waves from impingement of a drag is then estimated for the case where the cross-sectional three-dimensional supersonic flow on an internal corner. shape of the free vortex sheet is close to that of a circular arc. It Geometrical considerations which permitted modeling the problem is shown that the induced drag of the curved wing is less than in terms of plane flow are described. Consideration was restricted that of a straight wing and that the wing dihedral angle and the to corner flows with cross-flow Mach numbers larger than 2.4 and angles of the wing rotation axes should be selected with allowance the transition from RR to Mach reflection in this condition was for both the span and the curvature of the wing. V.L. numerically described. The analysis indicated that RR could occur in the corner flow. Two partially-glass plates were joined A87-12843 mechanically to control the corner angle and angle of attack when SIMILARITY LAW FOR THE SUPERSONIC FLOW PAST FLAT evaluating the theoretical predictions experimentally by means of SURFACES WITH INTENSE DISTRIBUTED INJECTION [ZAKON interferometry and Schlieren photography. The experiments were PODOBllA PRI SVERKHZVUKOVOM OBTEKANll PLOSKIKH run over 30 different angles of the wedge relative to the free POVERKHNOSTEI S SIL’NYM RASPREDELENNYM VDUVOM] stream. Fitting the wedge with a slit in the corner was found to I. I. VIGDOROVICH, IU. A. VINOGRADOV, V. A. LEVIN, and V. I. permit RR to occur. M.S.K. ROZHDESNENSKII (Moskovskii Gosudarstvennyi Universitet, Moscow, USSR) Akademiia Nauk SSSR. Doklady (ISSN 0002-3264), vol. 289, no. 3, 1986, p. 564-567. In Russian. refs The similarity law for the pressure distribution on a porous plate in supersonic flow (freestream Mach = 2 and 3) with intense distributed injection is formulated and experimentally confirmed. A87-12616 The experimental results are found to be described well by the QUANTITATIVE STUDY OF SHOCK-GENERATED law and to agree well with the theoretical calculation of Vigdorovich COMPRESSIBLE VORTEX FLOWS and Levin (1983) based on a thin-layer model where the mixing M. MANDELLA, Y. J. MOON, and D. BERSHADER (Stanford layer is replaced by a contact-discontinuity surface. The best University, CA) IN: Shock waves and shock tubes; Proceedings agreement is achieved when the lower bound of the j value for of the Fifteenth International Symposium, Berkeley, CA, July air is less than 1 percent and the upper bound (corresponding to 28-August 2, 1985 . Stanford, CA. Stanford University Press, 1986, k = 0.25) depends on the freestream Mach number. B.J. p. 471 -477. refs (Contract DAAG29-83-K-0146) The method of pulsed holographic interferometry has been A87-12956# applied to the study of the formation, transport and interaction TRANSONIC CASCADE FLOW SOLVED BY SHOCK-CAPTURE with a test surface of single two-dimensional shock-generated COMPUTATION FOLLOWED BY SEPARATE-REGION vortices. Radial density distributions have been determined, and COMPUTATION WITH SHOCK FllTlNG preliminary calculations of pressure and velocity distributions have C.-H. WU, Y. HUA, 6. WANG, Z. WANG. J. ZHANG (Chinese been obtained from the measured densities. Strong density and Academy of Sciences, Institute of Engineering Thermophysics. pressure drops are found to occur at the vortex center, verifying Beijing, People’s Republic of China) et al. Journal of Engineering Thermophysics, vol. 7, May 1986, p. 112-119. In Chinese, with the serious transient pressure loading which occurs when a vortex interacts with an airfoil. There is also some indication that these abstract in English. refs vortices have supersonic cores. Finite-difference calculation of the A new method is presented to solve the transonic flow past a density distribution shows a good agreement with experiment. compressor cascade, considering the effect of inlet bow wave Preliminary studies of interaction of vortices ’hurled’ at the leading and passage shock, the flow downstream of which can be either edge of a thin wedge show strong effects, featured by the rapid subsonic or transonic. The computation consists of two steps. In growth of secondary vortices. Author the first step, a shock capturing solution is obtained by the use of a potential equation or stream function. In the second step, separate algorithms are used, respectively, for the supersonic flow upstream of and the subsonic or transonic flow downstream of the passage shock. Calculations are made for a typical double-circular-arc cascade at inlet Mach number varying from A87-126 17 1.03 to 1.34. The effects of axial-velocity density ratio and entropy UNSTEADY DRAG OVER CYLINDERS AND AEROFOILS IN increase downstream of the passage shock are clearly shown. TRANSONIC SHOCK TUBE FLOWS The pressure distribution around the blade profile calculated with K. TAKAYAMA (Tohoku University, Sendai, Japan) and K. ITOH proper values of the axial-velocity density ratio and entropy increase IN: Shock waves and shock tubes; Proceedings of the Fifteenth compares favorably with experimental data. Author International Symposium, Berkeley, CA, July 28-August 2, 1985 . Stanford, CA, Stanford University Press, 1986, p. 479-485. refs A87-12957# The effectiveness of a transonic wind tunnel equipped with a AN EXPERIMENTAL STUDY ON LARGE NEGATIVE INCIDENCE holographic interferometer for collecting isopycnic data for deriving SEPARATED FLOW IN TWO-DIMENSIONAL TURBINE quantitative flow characteristics is described. Sample results are CASCADES provided in the form of interferometric fringes for transonic flows W. LIU and D. YE (Qinghua University, Beijing, People’s Republic past a cylinder and a NACA 0012 airfoil. Numerical techniques of China) Journal of Engineering Thermophysics, vol. 7, May are defined for using the isopycnic data to obtain the density 1986, p. 120-123. In Chinese, with abstract in English. refs distribution with the known stagnation condition, the pressure In order to investigate the characteristics of large negative distribution, the drag coefficient and the time variation of the drag incidence separated flow in turbine cascades, the separated region coefficient. Good agreement is found with PLM simulation data and its nature have been determined, and a separated flow model for the same flowfields. M.S.K. has been proposed by means of flow visualization and aerodynamic

10 02 AERODYNAMICS measurements. Comparing the calculated values with experimental characteristics of plain and vortex flapped delta wings including results, the feasibility of the separated flow proposed by the authors the pressure distributions. Dissert. Abstr. can be demonstrated. Author N87-10007 Virginia Polytechnic Inst. and State Univ., A87-12958# Blacksburg. A QUASI-THREE-DIMENSIONAL METHOD FOR DIAGONAL THE EFFECT OF FREE STREAM DISTURBANCES AND FLOW FANS CONTROL SURFACE DEFLECTIONS ON THE PERFORMANCE K. WU, Z. CAI, and Y. OU (Huazhong University of Science and OF THE WORTMANN AIRFOIL AT LOW REYNOLDS NUMBERS Technology, People's Republic of China) Journal of Engineering Ph.D. Thesis Thermophysics, vol. 7. May 1986, p. 124-126. In Chinese, with V. SUMANTRAN 1985 249 p abstract in English. refs Avail: Univ. Microfilms Order No. DA8605467 A quasi-three-dimensional design method for diagonal flow A wing with a Wortmann FX-63-137-ESM airfoil section has impellers is introduced. A diagonal flow fan with downstream guide been used to study some unique problems encountered in wing vanes has been designed and manufactured. A greatly inclined aerodynamics in the range of Reynolds numbers between 50,000 stream surface and axial velocity variation are this fan's feature. and 500,000. The wind-tunnel testing conducted in the 6' x 6' The performance testing and applications of the fan show the Stability tunnel included strain-gauge data, pressure data and reliability of the design method. Author flow-visualization studies. The laminar separation bubble which frequently occurs on the upper surface of the wing is found to N87-10005 Georgia Inst. of Tech., Atlanta. dominate its performance and gives rise to a hysteresis loop for NUMERICAL SOLUTION OF THE 3-DIMENSIONAL BOUNDARY lift and drag. Changes in airfoil performance due to positive flap LAYER EQUATIONS IN THE INVERSE MODE USING FINITE or control surface deflections resemble changes witnessed at DIFFERENCES Ph.D. Thesis higher Reynolds numbers. Negative deflections are seen to S. F. RADWAN 1985 248 p considerably change the stall behavior and the flow over the airfoil. Avail: Univ. Microfilms Order No. DA8604015 This is due to the considerably greater effect on the separation A numerical formulation that uses a finite-difference method bubble for negative flap deflections. The structure and mechanism has been developed to solve the full three-dimensional boundary of the laminar separation bubble can also be altered by the layer equations in inverse and direct modes. It is a implicit scheme introduction of selected acoustic disturbances and increased and uses central differences in the direction normal to the wall. free-stream turbulence. The wind-tunnel test-section environment and wgigbied upwiii&iig .wZh :h;ee in !he para!!e! is, therefore, capable of considerablv alterina wing performance in the waii. The deveioped method has the following new featiires: !his regime. Dissert. Abstr. (1) the formulation is done for non-orthogonal curvilinear coordinates; and (2) the developed scheme uses variable grid N87-10009 Tennessee Univ., Knoxville. step size along all coordinates, and it preserves second-order A STUDY OF THE FLOW FIELD ABOUT AN UPPER SURFACE accuracy if needed. The accuracy in the marching direction parallel BLOWN WING AND ITS EFFECTS ON LONGITUDINAL STATIC to the wall can be of any order between first and second through STABILITY OF A SMALL JET AIRPLANE Ph.D. Thesis input control. This makes the scheme stable and robust in the U. P. SOLIES 1985 149 p reversed flow regions. These features make the present numerical Avail: Univ. Microfilms Order No. DAB608294 method more general and flexible than any of previous methods. The effects of powered lift technology on the longitudinal The capability of the method in the inverse mode to march into stability characteristics of an upper surface blown (USB) jet-flapped the flow regions inaccessible to the direct mode calculations has aircraft have been studied. Both theoretical and experimental been demonstrated for the following cases; (1) separated methods were employed to investigate the flow field in the vicinity two-dimensional turbulent flow; (2) separated turbulent flow over of the lifting wing and its influence on pitching moments of the an infinite swept wing and (3) laminar and turbulent flows over a aircraft in motion. A nonlinear vortex-lattice theory was used to prolate spheroid at low incidence. The principal achievement is model the lift induced airflow in the near flow field about the the demonstration of the validity of the developed numerical inverse wing. Comparison with literature data showed excellent agreement, mode method to march into the regions of reversed flow which giving confidence in the method used. Flight tests were conducted are inaccessible to !he direct mode procedures. Dissert. Abstr. with the Ball-Bartoe Jetwing technology demonstration aircraft to visualize flow angles on the fuselage surface and at selected N87-10006 Virginia Polytechnic Inst. and State Univ., points in the flow field near the horizontal tail. To save cost, Blacksburg. simple data acquiring techniques were used. Also, the theoretical ANALYSIS OF THE VORTICAL FLOW AROUND A 60 DEG flow computations were restricted to a simplified Jetwing model DELTA WING WITH VORTEX FLAP Ph.D. Thesis with a relatively small number of panels. Still, there was fair B. SUNG 1985 260 p agreemeni beiweeri ii iauiaiiuiiiiy aid eipeiiii;enZlly +Se;minec! Avail: Univ. Microfilms Order No. DA8605468 flow angles at the tail of the Jetwing aircraft. The vortex-lattice Subsonic wind tunnel investigations were conducted on a 60 routine was then used for a parametrical study of flow angles and deg. swept, flat plate, delta wing with a leading edge vortex flap. longitudinal stability parameters. The results show that the powered The pressure distributions were measured over a range of angles lift strongly affects the flow field about the wing. of attack starting from zero to 40 deg. to 5 deg. interval and flap deflection angles from zero to 45 deg. with 5 deg. increments at N87-10014# Mitsubishi Heavy-Industries Ltd., Tokyo (Japan). a Reynolds number of about 2.14 x 1 million based on the root A DESCRIPTION OF A TURBULENT FLOW PAST A CIRCULAR chord. The flow visualization experiments were performed from CYLINDER BY A DISCRETE VORTEX METHOD zero degree to the stall angle, with ten different flap defection H. NAKAJIMA and Y. YOSHIZAWA (Tsukuba Univ. (Japan).) ln angles at the same Reynolds number. The mean flow field was Tokyo Univ. Proceedings of the Symposium on Mechanics for e---- rI:^k., 4noc .In.-. measured at angies or ariack i0 aeg. ana i6 aeg. with iile iiap apabc I toynuy, laud ,, !985 deflection angles of 10 deg. and 30 deg. at a Reynolds number Avail: NTlS HC A12/MF A01 of about 1.50 x 1 million. The experimental results show that the Discrete vortex methods were often used to describe unsteady leading edge vortex flap is an effective means to control the vortex incompressible flows at high Reynolds numbers. Most studies flow over a delta wing. The optimimum flap deflection angles were already existing are concerned with large scale structures of the found where the primary vortex was confined to the leading edge interested flows and integrated properties, that is, lift and drag vortex flap, thus producing a thrust on the flap. It was found that coefficients of bodies. In order to examine potential abilities of flap deflection could be used to restore a vortex flow from burst the vortex methods in describing more detailed information, a vortex condition. A non-linear vortex lattice code with a new velocity correlation function in a wake of a circular cylinder is measured jump formula was developed to predict the aerodynamic by a discrete vortex method and also an experiment of an actual

11 02 AERODYNAMICS flow. Comparisons between them show that turbulent structures coordinates are used to analyze the flow structure of steady also could be well described by the discrete vortex method. separation and unsteady flow with massive separation. The Author numerical method solves the discretized equations using an ADI-BGE method. The method is applied to a symmetric 12 percent N87-10030# Academy of Sciences (USSR), Moscow. Computing thick Joukowski airfoil. A conformal clustered grid is generated; Center. several 1-D stretching transformations are used to obtain a grid COMPUTATIONAL AERODYNAMICS OF SUPERSONIC LIFTING that attempts to resolve many of the multiple scales of the unsteady VEHICLES flow with massive separation, while maintaining the transformation P. I. CHUSHKIN and G. P. VOSKRESENSKY ln Tokyo Univ. metrics to be smooth and continuous in the entire flow field. Proceedings of the Symposium on Mechanics for Space Flight. Detailed numerical results are obtained for three flow configurations 1985 13p 1985 (1) Re = 1000, alpha = 5 deg., (2) Re =1000, alpha = 15 Avail: NTIS HC A12/MF A01 deg., (3) Re = 10.000, alpha = 5 deg. No artificial dissipation A review of investigations on numerical modelling of supersonic was added; however, lack of a fine grid in the normal direction three dimensional steady flows about lifting vehicles and their has presently led to results which are considered qualitative, elements carried out in the Soviet Union during the last five years especially for case (3). Author is given. An inviscid gas, both perfect and high-temperature, is considered. A number of characteristic examples are presented. N87-10041'# National Aeronautics and Space Administration. Author Langley Research Center, Hampton, Va. SPIN-TUNNEL INVESTIGATION OF A 1/25-SCALE MODEL OF N87-10033# Academy of Sciences (USSR), Moscow. Inst. of THE GENERAL DYNAMICS F-16XL AIRPLANE Applied Mathematics. R. D. WHIPPLE and W. L. WHITE Oct. 1984 51 p SUPERSONIC FLOW AROUND TIP SIDES OF WINGS (NASA-TM-85660; L-15616; NAS 1.1585660) Avail: NTIS HC G. P. VOSKRESENSKY ln Tokyo Univ. Proceedings of the A04/MF A01 CSCL 01A Symposium on Mechanics for Space Flight, 1985 7 p 1985 A spin-tunnel investigation of the spin and recovery Avail: NTIS HC A12/MF A01 characteristics of a 1/25-scale model to the General Dynamics The problem of supersonic flow around the tip sides of wings F-16XL aircraft was conducted in the Langley Spin Tunnel. Tests with swept or unswept leading edges and an attached shock wave included erect and inverted spins at various symmetric and is presented. The solution of the problem is based on the asymmetric loading conditions. The required size of an emergency assumption that the surface of a rounded tip side of a wing is spin-recovery parachute was determined. Author conical and the flow around it is self-similar. This fact makes it possible to use the self-similar stationing principle for the solution N87-10042'# National Aeronautics and Space Administration. of the problem. The realization of this principle is carried out with Langley Research Center, Hampton, Va. the help of the finite-difference second-order algorithm. Author SUPERSONIC, NONLINEAR, AlTACHED-FLOW WING DESIGN FOR HIGH LIFT WITH EXPERIMENTAL VALIDATION N87-10039'# National Aeronautics and Space Administration. J. L. PITMAN, D. S. MILLER, and W. H. MASON (Grumman Langley Research Center, Hampton, Va. Aerospace Corp., Bethpage, N.Y.) Aug. 1984 221 p WIND-TUNNEL INVESTIGATION OF THE FLIGHT (NASA-TP-2336; L-15787; NAS 1.60:2336) Avail: NTIS HC CHARACTERISTICS OF A CANARD GENERAL-AVIATION AlO/MF A01 CSCL 01A AIRPLANE CONFIGURATION Results of the experimental validation are presented for the D. R. SATRAN Oct. 1986 60 p three dimensional cambered wing which was designed to achieve (NASA-TP-2623; L-15929; NAS 1.60:2623) Avail: NTlS HC attached supercritical cross flow for lifting conditions typical of A04/MF A01 CSCL 01A supersonic maneuver. The design point was a lift coefficient of A 0.36-scale model of a canard general-aviation airplane with 0.4 at Mach 1.62 and 12 deg angle of attack. Results from the a single pusher propeller and winglets was tested in the Langley nonlinear full potential method are presented to show the validity 30- by 60-Foot Wind Tunnel to determine the static and dynamic of the design process along with results from linear theory codes. stability and control and free-flight behavior of the configuration. Longitudinal force and moment data and static pressure data were Model variables made testing of the model possible with the canard obtained in the Langley Unitary Plan Wind Tunnel at Mach numbers in high and low positions, with increased winglet area, with outboard of 1.58, 1.62, 1.66, 1.70, and 2.00 over an angle of attack range wing leading-edge droop, with fuselage-mounted vertical fin and of 0 to 14 deg at a Reynolds number of 2.0 x 10 to the 6th rudder, with enlarged rudders, with dual deflecting rudders, and power per foot. Oil flow photographs of the upper surface were with ailerons mounted closer to the wing tips. The basic model obtained at M = 1.62 for alpha approx. = 8, 10, 12, and 14 deg. exhibited generally good longitudinal and lateral stability and control E.R. characteristics. The removal of an outboard leading-edge droop degraded roll damping and produced lightly damped roll (wing N87-10043'# Grumman Aerospace Corp., Bethpage, N.Y. rock) oscillations. In general, the model exhibited very stable VISCOUS WING THEORY DEVELOPMENT. VOLUME 1: dihedral effect but weak directional stability. Rudder and aileron ANALYSIS, METHOD AND RESULTS Final Report control power were sufficiently adequate for control of most flight R. R. CHOW, R. E. MELNIK, F. MARCONI, and J. STEINHOFF conditions, but appeared to be relatively weak for maneuvering Oct. 1986 127 p compared with those of more conventionally configured models. (Contract NASl-16858) Author (NASA-CR-178156; NAS 1.26:178156; RE-725-VOL-1) Avail: NTIS HC A07/MF A01 CSCL 01A N87-10040'# Cincinnati Univ., Ohio. Dept. of Aerospace Viscous transonic flows at large Reynolds numbers over 3-D Engineering and Engineering Mec wings were analyzed using a zonal viscid-inviscid interaction ANALYSIS OF TWO-DIMENSIONAL INCOMPRESSIBLE FLOW approach. A new numerical AFZ scheme was developed in PAST AIRFOILS USING UNSTEADY NAVIER-STOKES conjunction with the finite volume formulation for the solution of EQUATIONS the inviscid full-potential equation. A special far-field asymptotic K. N. GHIA, G. A. OSSWALD, and U. GHIA 1986 15 p boundary condition was developed and a second-order artificial Previously announced in IAA as A85-42975 viscosity included for an improved inviscid solution methodology. (Contract NAG1-465; AF-AFOSR-0160-80) The integral method was used for the laminar/turbulent boundary (NASA-CR-179823; NAS 1.26:179823) Avail: NTIS HC AO2/MF layer and 3-D viscous wake calculation. The interaction calculation A01 CSCL01A included the coupling conditions of the source flux due to the The conservative form of the unsteady Navier-Stokesequations wing surface boundary layer. the flux jump due to the viscous in terms of vorticity and stream function in generalized curvilinear wake, and the wake curvature effect. A method was also devised

12 02 AERODYNAMICS incorporating the 2-D trailing edge strong interaction solution for was found in the same fifth order model and verified by previous the normal pressure correction near the trailing edge region. A research. A mechanism for transfer of kinetic energy during the fully automated computer program was developed to perform the catastrophic behavior shown is hypothesized. A spin equilibrium proposed method with one scalar version to be used on an surface for the aircraft was determined from an eighth order model IBM-3081 and two vectorized versions on Cray-1 and Cyber-205 and, from that surface, possible control deflections for recovery c0 mp u t er s . from the spin were obtained. GRA

N87-10044'# Grumman Aerospace Corp., Bethpage, N.Y. N87-10047# Nielsen Engineering and Research, Inc., Mountain VISCOUS WING THEORY DEVELOPMENT. VOLUME 2 View, Calif. GRUMWING COMPUTER PROGRAM USER'S MANUAL Final PREDICTION OF GUST LOADINGS AND ALLEVIATION AT Report TRANSONIC SPEEDS Final Report, 20 Sep. 1983 - 20 Jul. R. R. CHOW and P. L. OGlLVlE Oct. 1986 117 p 1985 (Contract NAS1-16858) D. NIXON and K. L. TZU00 Mar. 1986 43 p (NASA-CR-178157; NAS 1.26:178157; RE-726-VOL-2) Avail: (Contract NO01 67-834-0114) NTlS HC AO6/MF A01 CSCL 01A (AD-A167748; NEAR-TR-352; DTNSRDC/ASED-CR-O1-86) This report is a user's manual which describes the operation Avail: NTlS HC A03/MF A01 CSCL 20D of the computer program, GRUMWING. The program computes The transonic indicial theory is used to predict the effect of a the viscous transonic flow over three-dimensional wings using a gust on an airfoil at transonic speeds. The effect of operating two boundary layer type viscid-inviscid interaction approach. The control surfaces is also modeled by the indicial method. The inviscid solution is obtained by an approximate factorization transonic indicial method is linear in a strained coordinate system (AF2)method for the full potential equation. The boundary layer and superposition can be used. This allows the effects of an solution is based on integral entrainment methods. Author arbitrary gust and control surface deflection to be modeled simply if the indicial responses for the gust and each control surface are N87-10045# Goldschmied (Fabio R.), Monroeville, Pa. known. The computation time is small and, therefore, an WIND TUNNEL TEST OF THE MODIFIED GOLDSCHMIED optimization technique can be used to determine the best control MODEL WITH PROPULSION AND EMPENNAGE ANALYSIS OF surface deflections to alleviate the gust loading. GRA TEST RESULTS Final Report, 3 Mar. 1981 - 30 Nov. 1982 F. R. GOLDSCHMIED 1 Feb. 1986 115 p N87-10048# Max-Planck-lnstitut fuer Stroernungsforschung. m--*---b hinni~7oi r.nn7m (uultuab, I"wwI",-"I-u V"..,, Goettingen (West Germany). (AD-Ai673600; FRG-82-i ; CTN§RDC/ASED-CR-02-86) Avail: VORTEX SHEDDING OF A SQUARE CYLINDER IN FRONT OF NTlS HC AO6/MF A01 CSCL 20D A SLENDER AIRFOIL AT HIGH REYNOLDS NUMBERS. PART An extensive test program was carried out in DTNSRDC's 8x10 1: SPACING EFFECT low-speed wind-tunnel for experimental verification of the integrated T. NAKAGAWA, G. E. A. MEIER. R. TIMM, and H. M. LENT hull boundary-layer controVpropulsion lighter-than-air design. The Oct. 1985 34 p Sponsored by Minna-James-Heinemann 1957 Goldschmied wind-tunnel model was overhauled with a new Foundation, Hannover, West Germany suction-slot inlet configuration, a suction/propulsion fan, a new (MPIS-23/1985; ISSN-0436-1199; ETN-86-98221) Avail: NTlS aftbody and a tailboom/empennage assembly. The fan air power HC A03/MF A01 ; Fachinformationszentrum,Karlsruhe, West coefficient of the operational model with empennage ranged in Germany DM 22 steady flight from 0.0130 (free transition) to 0.01 55 (transition The spacing effect on vortex shedding of a square cylinder in tripped at 10% length) at the volume Reynolds number of two front of a NACA 0018 airfoil at high Reynolds numbers was millions. Considerable excess thrust could be generated with an visualized in wind tunnel tests. When the free stream velocity is average incremental propulsive efficiency of 72%. As compared constant, the amplitude of the pressure fluctuations at a point in to wind-tunnel tests of conventional streamlined bodies with the test section is of comparable order irrespective of the spacing empennage at exactly the same volume Reynolds number, the between a square cylinder and an airfoil. When the separating integrated design offers 50% less equivalent drag for both free shear layers from the upstream square cylinder reattach to the and tripped transitions. The empennage provided neutral static downstream airfoil, the pressure signal is most regular and the stability over the complete test range of 8 degrees; the ratio of vortex shedding frequency is minimum. The airfoil can stabilize total fin planform over volume equivalent was 0.404. It was found the vortex shedding process behind the upstream square cylinder. that efficient and stable BLC could be achieved only by the The of the square cylinder depends upon the combination of Ringloeb cusp at the slot's leading-edgewith suction nondimensional spacing normalized by the characteristic length of flow and with the presence of the tailboom. The fan (or pump) the cylinder. Once the spacing between the square cylinder and design is an essential part of the system design: a procedure was the airfoil becomes greater than the critical value, the airfoil does --A ---..:a- --.e -i--ifir*nt dfnrt nn thn \mrteu sheddin? yncess developed for determining tne optimum ian ciesign parariioittis llUL p'""u' ",,, .ny'""Y"'" -..-_.-.. . -. from the vehicle's wind-tunnel test data. GRA behind the upstream cylinder. ESA

N87-10046# Air Force Inst. of Tech., Wright-Patterson AFB, N87-10051 Texas Univ., Austin. Ohio. UNSTEADY FLOW OVER AN AIRFOIL INSIDE A WIND TUNNEL APPLICATION OF BIFURCATION AND CATASTROPHE WITH AND WITHOUT TRANSPIRATION Ph.D. Thesis THEORIES TO NEAR STALL FLIGHT MECHANICS M.S. Thesis W. J. TEDESCHI 1985 205 p C. A. HAWKINS 1985 247 p Avail: Univ. Microfilms Order No. DAB609435 (AD-A167697; AFIT/CI/NR-86-54T) Avail: NTlS HC A1 1/MF This research uses the viscous/inviscid interaction model to A01 CSCL01A calculate the lift and drag characteristics of a two-dimensional This thesis sought to develop nonlinear systems analysis airfoil inside two types of wind tunnels. The first is a conventional techniques capabie oi ariaiyLiiiy ani pisiictifig ihe complex .,-..-cniiti-wd .. -.. wind.. .. .- tllnngl.. with an airfoil oscilllating transversely to the behavior found in high-angle-of-attack flight. The primary research freestream. In the second wind tunnel, an unsteady transverse method involved calculation of equilibrium surfaces where the time flow field is produced by a time-varying fluid transpiration of the rate of change of each of the state variables is set to zero in the wind tunnel walls. Subsonic flows in the one to five million Reynolds aircraft equations of motion, and the states that will satisfy that number range are considered. A computer code based on the condition are found for various control deflections. The equilibrium theoretical model formulated in this study is used to predict the surfaces were calculated numerically through use of continuation unsteady flow field around the airfoil. The nonlinear inviscid flow methods. An equilibrium trajectory analysis of a fifth order model problem is solved analytically for the disturbance velocity potential of the aircraft showed significant adverse yaw problems at high using a unqiue for Fourier transform method. The bounded influence AOA as well as the presence of roll coupling. Bifurcational behavior coefficients which explicitly contain the airfoil thickness distribution

13 02 AERODYNAMICS and wind tunnel geometry provide an advantage over traditional tunnel simulation method that could provide dynamic ground effect Panel methods. The viscous flow problem utilizes a finite-difference data, (2) to demonstrate that the dynamic ground effect wind-tunnel numerical formulation to solve the unsteady boundary layer testing could produce data comparable to flight test data, and (3) equations. Dissert. Abstr. to provide information on the physical mechanisms involved in dynamic ground effect for highly swept delta wings. The dynamic N87-10052 Notre Dame Univ., Ind. ground effect data obtained from the wind-tunnel simulation EXPERIMENTAL STUDY OF THE BOUNDARY LAYER ON A provided a closer approximation to the actual flight test data than LOW REYNOLDS NUMBER AIRFOIL IN STEADY AND do static test data. For highly swept (6 deg. to 75 deg.), UNSTEADY FLOW Ph.D. Thesis low-aspect-ratio wings static ground effect data greatly M. BRENDEL 1986 413 p overpredicted the increase in C sub L, C sub D and C sub M as Avail: Univ. Microfilms Order No. DA8612989 height over the span decreased below .4. For low-swept (lambda An experimental study of the boundary layer on a Wortman sub LE less than 30 deg.) low-aspect-ratio wings the discrepancy FX63-137 airfoil at a Reynolds number of 100,000 and several was much less. The visual observations of the flow field confirmed angles of attack was conducted for steady and unsteady that vortex lag existed for highly swept, low-aspect-ratio wings in incompressibile flow. Pressure distributions and single-element dynamic ground effect. Dissert. Abstr. hot-wire boundary layer surveys were obtained. A significant portion of the work consisted of the design, fabrication, and testing of an unsteady flow facility. Additionally, the design of data acquisition and data processing techniques for unsteady flow experiments N87-10834# Centre d'Etudes et de Recherches, Toulouse were investigated. A benchmark test was conducted to validate (France). Dept. dEtudes et de Recherches en the techniques and the test facility by studying the response of a Aerothermodynamique. laminar boundary layer to a periodic unsteady freestream. Results REPORT ON TESTS OF A CAST 10 AIRFOIL WITH FIXED were found to agree with existing analytical and experimental data. TRANSITION IN THE T2 TRANSONIC CRYOGENIC WIND The same techniques were then employed in the study of the TUNNEL WITH SELF-ADAPTIVE WALLS airfoil boundary layer. Characteristics of the pressure distributions, A. SERAUDIE, A. BLANCHARD, and J. F. BRElL Aug. 1985 boundary layer velocity profiles, integrated boundary layer 266 p thicknesses, and shape parameters were documented. Criteria for (RT-OA-63/1685; DERAT-6/5019-DN) Avail: NTlS HC A1 2/MF locating laminar separation, transition, and reattachment were A01 developed and compared with flow visualization. These criteria Described are tests on the CAST 10 airfoil in tripped-transition, were used to study the behavior of the separation bubble in carried out in the cryogenic and transonic wind-tunnel T2 fitted unsteady flow. Dissert. Abstr. with self-adaptive walls. These tests follow those which were performed in natural transition and were presented in a previous N87-10330'# Deutsche Forschungs- und Versuchsanstalt fuer note. Firstly, a complement was realized to pinpoint the location Luft- und Raumfahrt, Wesseling (West Germany). of the natural transition on the upper surface of the airfoil; this EXPERIMENTAL AND THEORETICAL DOPPLER-LIDAR was done by a longitudinal exploration in the boundary layer. SIGNATURES OF AIRCRAFT WAKE VORTICES Secondly, in a first stage, the transition was only tripped on the F. KOEPP and W. A. KRICHBAUMER ln NASA. Langley Research lower surface with a carborundum strip of 0.045 mm thickness, Center 13th International Laser Radar Conference 3 p Aug. situated at 5% of chord (T 112 D). These tests were performed 1986 here to separate the phenomena in relation to the lower surface Avail: NTlS HC A15/MF A01 CSCL 01A and those in relation to the upper surface which occur in natural The DFVLR laser Doppler anemometer is a C02 continuous transition (TN). In a second stage, the transition was normally wave homodyne system designed for boundary layer wind tripped on both sides of the profile (TD), likewise at x/c = 5% measurements. During the last three years, it was mainly used in and h = 0.045 mm. The test configurations of the previous serial the wake-vortex program at Frankfurt airport for determination of were experimented again and results obtained in the three cases vortex strength, transport, and lifetime. The strategy for that special (TN), (T 1/2 N) and (TD) were compared, in particular those type of measurement was previously reported in detail along with concerned with the effect of the Reynolds number on aerodynamic single experimental results. Therefore, herein is given a short coefficients of the airfoil. The gathering of the experimental values summary of the data concerning questions of air traffic control. In around a Reynolds number of 20 millions is observed; but before addition to the experimental activities a computer model describing this number, the evolutions of the curves in the three cases tested wake-vortex behavior was installed. It allows the comparison of are different. Author the measured data with the hydrodynamically predicted quantities. On the other hand, it leads to an improved procedure for future wake-vortex measurements. E.R. N87-10835'# Sverdrup Technology, Inc., Arnold Air Force Station, N87-10832 British Aerospace Aircraft Group, Bristol (England). Tenn. Aerodynamics Research Dept. LARGE PERTURBATION FLOW FIELD ANALYSIS AND A BIBLIOGRAPHY OF AERODYNAMIC HEATING SIMULATION FOR SUPERSONIC INLETS Final Report REFERENCES M. 0. VARNER, W. R. MARTINDALE, W. J. PHARES, K. R. KNEILE, J. R. DEANE and P. C. DEXTER Jul. 1982 80 p and J. C. ADAMS, JR. Sep. 1984 126 p (BAE-BT-13481; BAE-AERO-INFORM-33; ETN-86-97948) Avail: (Contract NAS3-23682) Issuing Activity (NASA-CR-174676; NAS 1.26:174676) Avail: NTlS HC A07/MF Almost 600 references on aerodynamic heating are listed in A01 CSCL01A this bibliography. ESA An analysis technique for simulation of supersonic mixed compression inlets with large flow field perturbations is presented. N87-10833 Kansas Univ., Lawrence. The approach is based upon a quasi-one-dimensional inviscid AN EXPERIMENTAL INVESTIGATION OF DYNAMIC GROUND unsteady formulation which includes engineering models of EFFECT Ph.D. Thesis unstartlrestart, bleed, bypass, and geometry effects. Numerical R. C. CHANG 1985 108 p solution of the governing time dependent equations of motion is Avail: Univ. Microfilms Order No. DA8608382 accomplished through a shock capturing finite difference algorithm, A wind-tunnel investigation has been made at low speed to of which five separate approaches are evaluated. Comparison with determine the dynamic ground effect for low-aspect-ratio wings experimental supersonic wind tunnel data is presented to verify with sharp leading edges at constant angles of attack. The three the present approach for a wide range of transient inlet flow main purposes of this investigation were: (1) to develop a wind conditions. Author

14 02 AERODYNAMICS

N87-10836'# Bihrle Applied Research, Inc., Jericho, N. Y. thrust-vector angle was varied from -20 deg. to 60 deg., and nozzle LOW SPEED ROTARY AERODYNAMICS OF F-18 pressure ratio was varied from 1.0 (jet off) to approximately 10.0. CONFIGURATION FOR 0 DEG TO 90 DEG ANGLE OF AlTACK Author TEST RESULTS AND ANALYSIS R. HULTBERG Washington NASA Aug. 1984 255 p (Contract NASl-16205) (NASA-CR-3608; NAS 1.263608) Avail: NTlS HC A1 2/MF A01 CSCL OlA Aerodynamic characteristics obtained in a rotational flow N87-10840"# Hamilton Standard, Windsor Locks, Conn. environment, utilizing a rotary balance located in the Langley Spin EFFECT OF ANGULAR INFLOW ON THE VIBRATORY Tunnel, are discussed and presented in tabular form for a 1\10 RESPONSE OF A COUNTER-ROTATING PROPELLER scale F-18 airplane model. The rotational aerodynamic J. E. TURNBERG and P. C. BROWN 15 Jan. 1985 75 p characteristics were established for the basic airplane, as well as (Contract NAS3-24222) the influence of control deflections and the contribution of airplane (NASA-CR-174819; NAS 1.26:174819) Avail: NTlS HC AO4/MF components, i.e., body, wing, leading edge extension, horizontal A01 CSCL01A and vertical tails, on these characteristics up to 90 deg angle of This report presents the results of a propeller vibratory stress attack. Spin equilibrium conditions predicted using the measured survey on the Fairey Gannet aircraft aimed at giving an assessment data are also presented and compared with spin model and full of the difference in vibratory response between single and scale flight results. Author counter-rotating propeller operation in angular inflow. The survey showed that counter-rotating operation of the propeller had the N87-10837'# Bihrle Applied Research, Inc., Jericho, N. Y. effect of increasing the IP response of the rear propeller by ROTARY BALANCE DATA AND ANALYSIS FOR THE X-29A approximately 25 percent over comparable single-rotation operation AIRPLANE FOR AN ANGLE-OF-ATTACK RANGE OF 0 DEG while counter-rotating operation did not significantly influence the TO 90 DEG IP response of the front propeller. Author J. N. RALSTON Washington- NASA Aug. 1984 215 p (Contract NASl-16205) [NASA-CR-3747: NAS 1.2637471 Avail: NTlS HC AlO/MF A01

CSCL 01A ~ . The rotational aerodynamic characteristics are discussed for a A In .__I_ -_A_, 1 .L_ " nna _._^-- TL- ..U^^&^ 110 s~meIIIUUUI 01 ~IIUA-LYM aiipiaiia. IIIG GIIGLLD i3 ioiatioii Oii ;gi-;cgi; '# ;.jaiioiiai AeiOnauiics and Space AJmiiiisiia;ion. the aerodynamics of the basic modei were determined, as weli as Ames Research Cenier, Moifeii Field, Caiii. the influence of airplane components, various control deflections, TRANSONIC FLOW ANALYSIS FOR ROTORS. PART 2 and several forebody modifications. These data were measured THREE-DIMENSIONAL, UNSTEADY, FULL-POTENTIAL using a rotary balance, over an angle of attack range of 0 to 90 CALCULATION deg, for clockwise and counter clockwise rotations covering an I. C. CHANG Jan. 1985 27 p omega b/2V range of 0 to 0.4. Author (NASA-TP-2375; A-9682; NAS 1.60:2375) Avail: NTlS HC AO3/MF A01 CSCL 01A N87-10838'# National Aeronautics and Space Administration. A numerical method is presented for calculating the Langley Research Center, Hampton, Va. three-dimensional unsteady, transonic flow past a helicopter rotor EFFECTS OF TAIL SPAN AND EMPENNAGE ARRANGEMENT blade of arbitrary geometry. The method solves the full-potential ON DRAG OF A TYPICAL SINGLE-ENGINE FIGHTER AFT END equations in a blade-fixed frame of reference by a time-marching J. R. BURLEY, II and B. L. BERRIER Sep. 1984 136 p implicit scheme. At the far-field, a set of first-order radiation (NASA-TP-2352; L-15742; NAS 1.60:2352) Avail: NTlS HC conditions is imposed, thus minimizing the reflection of outgoing A07/MF A01 CSCL 01A wavelets from computational boundaries. Computed results are An investigation was conducted in the Langley 16 foot Transonic presented to highlight radial flow effects in three dimensions, to Tunnel to determine the effects of tail span and empennage compare surface pressure distributions to quasi-steady predictions, arrangement on drag of a single engine nozzle/afterbody model. and to predict the flow field on a swept-tip blade. The results Tests were conducted at Mach numbers from 0.50 to 1.20, nozzle agree well with experimenta! data for bo!!? straight- and swept-tip pressures frm 1.0 (jet off) to 8.0, and angles of attack from -3 to blade geometries. Author 9 deg, depending upon Mach numbers. Three empennage arrangements (aft, staggered, and forward) were investigated with several different tail spans. The results of the investigation indicate that tail span and Dosition have a significant effect on the drag at transonic speeds. Unfavorable tail interference was largely due to the outer portion of the tail surfaces. The inner portion near the N87-10842*# Rockwell International Corp., Los Angeles, Calif. nozzle and afterbody did little to increase drag other than surface SUPERSONIC SECOND ORDER ANALYSIS AND OPTIMIZATION skin friction. Tail positions forward of the nozzle generally had PROGRAM USER'S MANUAL lower tail interference. Author W. C. CLEVER Sep. 1984 223 p (Contract NASl-15820) N87-10839*# National Aeronautics and Space Administration. (NASA-CR-172342; NAS 1.26:172342) Avail: NTlS HC AlO/MF Langley Research Center, Hampton, Va. A01 CSCL 01A STATIC INTERNAL PERFORMANCE OF Approximate nonlinear inviscid theoretical techniques for SINGLE-EXPANSION-RAMP NOZZLES WITH predicting aerodynamic characteristics and surface pressures for THRUST-VECTORING CAPABILITY UP TO 60 DEG relatively slender vehicles at supersonic and moderate hypersonic B. L. BERRIER and L. D. LEAVITT Oct. 1984 144 p speeds were developed. tmpnasis was piaceo on approaches (NASA-TP-2364; L-15766; NAS 1.60:2364) Avail: NTlS HC that would be responsive to conceptual configuration design level A07/MF A01 CSCL 01A of effort. Second order small disturbance theory was utilized to An investigation has been conducted at static conditions (wind meet this objective. Numerical codes were developed for analysis off) in the static-test facility of the Langley 16-FOOt Transonic and design of relatively general three dimensional geometries. Tunnel. The effects of geometric thrust-vector angle, sidewall Results from the computations indicate good agreement with containment, ramp curvature, lower-flap lip angle, and ramp length experimental results for a variety of wing, body, and wing-body on the internal performance of nonaxisymmetric shapes. Case computational time of one minute on a CDC 176 single-expansion-ramp nozzles were investigated. Geometric are typical for practical aircraft arrangement. Author

15 02 AERODYNAMICS

N87-10843'# National Aeronautics and Space Administration. N87-10849 Stanford Univ., Calif. Langley Research Center, Hampton, Va. COMPUTATION OF TRANSONIC SEPARATED WING FLOWS PILOTED SIMULATION STUDY OF THE EFFECTS OF AN USING AN EULEWNAVIER STOKES ZONAL APPROACH Ph.D. AUTOMATED TRIM SYSTEM ON FLIGHT CHARACTERISTICS Thesis OF A LIGHT TWIN-ENGINE AIRPLANE WITH ONE ENGINE U. KAYNAK 1986 186 p INOPERATIVE Avail: Univ. Microfilms Order No. DAB612751 E. C. STEWART, P. W. BROWN, and K. R. YENNI Nov. 1986 A computer program called Transonic Navier Stokes (TNS) 41 P has been developed which solves the EulerINavier-Stokes (NASA-TP-2633; L-16147; NAS 1.60:2633) Avail: NTlS HC equations around wings using a zonal giid approach. In the present A03lMF A01 CSCL 01A zonal scheme, the physical domain of interest is divided into several A simulation study was conducted to investigate the piloting subdomains called zones and the governing equations are solved problems associated with failure of an engine on a generic light interactively. The advantages of the Zonal Grid Approach are as twin-engine airplane. A primary piloting problem for a light follows: (1) the grid for any subdomain can be generated easily, twin-engine airplane after an engine failure is maintaining precise (2) grids can be, in a sense, adapted to the solution, (3) different control of the airplane in the presence of large steady control equation sets can be used in different zones, and (4) this approach forces. To address this problem, a simulated automatic trim system allows for a convenient data base organization scheme. Using which drives the trim tabs as an open-loop function of propeller this code, separated flows on a NACA 0012 section wing and on slipstream measurements was developed. The simulated automatic the NASA Ames WING C have been computed. First, the effects trim system was found to greatly increase the controllability in of turbulence and artificial dissipation models incorporated into asymmetric powered flight without having to resort to complex the code are assessed by comparing the TNS results with other control laws or an irreversible control system. However, the trim-tab CFD codes and experiments. Then a series of flow cases are control rates needed to produce the dramatic increase in described where data is available. The computed results, including controllability may require special design consideration for cases with shock-induced separation, are in good agreement with automatic trim system failures. Limited measurements obtained in experimental data. Finally, some futuristic cases are presented to full-scale flight tests confirmed the fundamental validity of the demonstrate the abilities of the code for massively separated cases proposed control law. Author which do not have experimental data. Dissert. Abstr.

N87-10846# National Aerospace Lab., Amsterdam (Netherlands). 03 Div. UNSTEADY AIRLOAD COMPUTATIONS FOR AIRFOILS AIR TRANSPORTATION AND SAFETY OSCILLATING IN ATTACHED AND SEPARATED COMPRESSIBLE FLOW R. HOUWINK Apr. 1985 12 p Presented at joint AGARD Includes passenger and cargo air transport operations; and aircraft FDP and FMP Symposium on Unsteady Aerodynamics: accidents. Fundamentals and Applications to Aircraft Dynamics, Goettingen, West Germany, 6-9 May 1985 Sponsored by Netherlands Agency for Aerospace Research A87-10866 (NLR-MP-85040-U; 88668292; ETN-86-98491) Avail: NTlS HC CASE STUDY OF ROYAL AUSTRALIAN AIR FORCE P3B ORION A02lMF A01 AIRCRAFT GROUND OXYGEN FIRE INCIDENT Developments in coupled inviscid flow-boundary layer J. W. GRUBB (Embassy of Australia, Washington, DC) IN: computations are discussed for airfoils in unsteady motion in Flammability and sensitivity of materials in oxygen-enriched attached and separated subsonic and transonic flow. The atmospheres; Proceedings of the Symposium, Washington, DC, applicability of quasi-simultaneous strong interaction coupling April 23. 24, 1985. Volume 2 . Philadelphia, PA, American Society procedures for transonic small perturbation theory and boundary for Testing and Materials, 1986, p. 171-179. layer integral methods is illustrated for oscillating airfoils with Data from the January 1986 RAAF ground fire which destroyed shock-induced separation. The relevance of the predicted airloads a P3B Orion aircraft are discussed. The fire occurred during the for aeroelastic applications is illustrated using the analysis of an removal of an onboard oxygen cylinder; a diagram of the oxygen aeroelastic instability of a supercritical wing wind tunnel model. system is provided. Examination of the oxygen system revealed that the fire initiated in the manifold check valve (MCV) assembly ESA due to a leaking poppet valve, the presence of contaminants in the system, and failure to bleed the system to 3.33 MPa before cylinder disconnection. The various contaminants detected, which N87-10847# Center for Mathematics and Computer Science, include iron oxide dust, copper-based alloys, steel, AI, and corrosive Amsterdam (Netherlands). Dept. of Numerical Mathematics. products, are described. The source of the contamination, the EULER FLOW SOLUTIONS FOR A TRANSONIC WIND TUNNEL effectiveness of the oxygen system filters, and the fitting of the SECTION poppet valves to the MCV assembly were investigated. It is noted B. KOREN Jan. 1986 18 p Submitted for publication Sponsored that due to the findings the oxygen system was cleaned, a new by Netherlands Technology Foundation type of poppet valve was incorporated into the system, and a (CWI-NM-R8601; 88667670; ETN-86-98505) Avail: NTlS HC cleaning and inspection program was developed. I.F. AO21MF A01 Two dimensional Euler flow computations were performed for A87-11368 a wind tunnel section, designed for research on transonic shock FIRE OCCURRING AND EXPANDING IN CONNECTION WITH wave boundary layer interaction. For the discretization of the Euler OILS IN AVIATION [FEUERENTSTEHUNG UND- AUSBREITUNG equations, a finite volume Osher discretization was applied. The DURCH OELE IN DER LUFTFAHRT] solution method is a nonlinear multigrid iteration with a symmetric E. JANTZEN (DFVLR, lnstitut fuer technische Physik, Stuttgart, point Gauss-Seidel relaxation method. Initial finest grid solutions West Germany) DFVLR-Nachrichten(ISSN 001 1-4901), July 1986, are obtained by full multigrid. Grid adaptation was applied to obtain p. 13-15. In German. a sharp shock. The mathematical quality of four different boundary Investigations have shown that oils employed in an aircraft conditions for the oulet flow is indicated. The solutions of two represent a possible cause for the start and the propagation of transonic flows with shock are presented: a choked and a fire. Thus, fires, having their origin in the hydraulic system, caused non-choked flow. Both flow solutions show good shock capturing. a damage of approximately 160 million dollars in the U.S. Air ESA Force during the period from 1970 to 1979. The present article is

16 03 AIR TRANSPORTATION AND SAFETY

concerned with investigations which have been conducted with the impact sequence, and a severe fire erupted immediately. Of the objective to reduce the hazards for the start and the propagation the 163 persons aboard, 134 passengers and crewmwmbers were of a fire in connection with the hydraulic system of an aircraft, killed, 24 passengers and 3 cabin attendants survived. The National giving particular attention to studies performed by the DFVLR. Transportation Safety Board determines that the probable causes The chemical structure of oils and their fire-related characteristics of the accident were the flightcrew's decision to initiate and were considered along with basic studies regarding ignition and continue the approach into a cumulonimbus cloud which they fire propagation, and tests and investigations concerning practical observed to contain visible lightning; the lack of specific guidelines, problems. Topics discussed are related to a device for the study procedures, and training for avoiding and escaping from low-altitude of self-ignition at hot metal areas in the case of very small amounts wind shear; and the lack of definitive, real-time wind shear hazard of oil, fire-propagation studies with a high-speed camera, and the information. This resulted in the aircraft's encounter at low altitude burning characteristics of various hydraulic oils. G.R. with a microburst-induced, severe wind shear from a rapidly developing thunderstorm located on the final approach course. A87-11900 Author THEORETICAL ASPECTS AND PRACTICAL QUESTIONS REGARDING THE ASSURANCE OF FLIGHT SAFETY [ZU ElNlGEN THEORETISCHEN ASPEKTEN UND PRAKTISCHEN N87-10054'# National Aeronautics and Space Administration. FRAGEN DER GEWAEHRLEISTUNG DER FLUGSICHERHEITI Langley Research Center, Hampton, Va. A. RIECHE (Berlin, Humboldt-Universitaet, East Germany) DOPPLER RADAR DETECTION OF WIND SHEAR Technisch-oekonomische Information der zivilen Luftfahrt (ISSN V. E. DELNORE, Comp. (PRC Kentron, Inc.. Hampton, Va.) and 023245012), vol. 22, no. 3-4, 1986, p. 151-155. In German. refs V. A. MCCLELLAN (Research Triangle Inst., Research Triangle Questions concerning the position of flight safety as a part of Park, N.C.) Sep. 1985 118 p Presented at a Meeting, safety considerations in the general areas of traffic and production Hampton, Va., 24-25 Sep., 1985; sponsored in part by FAA are examined, taking into account the assurance of the technical (NASA-CP-2435; NAS 1.552435; FAA/PM-86/31) Avail: NTlS safety of aircraft and air traffic control ground installations, the HC AO6/MF A01 CSCL 01C maintenance of aircraft and ground installations, the employment In response to the Nation's needs for decreasing the threat of of aircraft control and air traffic control technologies which provide violent weather phenomena to aviation, a two-day meeting was conditions for the conduction of safe flights, and regulations which held. This meeting, which brought together representatives from permit a safe termination of flights in certain emergency situations. NASA, the Federal Aviation Administration, and the avionics Attention is given to flight safety and the safety requirements of industry, focused on the applicability of Doppler radar techniques t- thn rlntnr&rr rl Ir...-lr.,rI ... :-A -k--- societya flight SZ!P!y znd eCnngmiCr, !!igh! s2fe!y 2nd discip!ine, iu ,BIG "T,G..,,l"II UI lUW lcilEil Wlll" DII=cI. 8.G. and the definitim c! !he category 'flight safeti'. G.R.

A87-12683# N87-10055# Federal Aviation Administration, Atlantic City, N.J. CHARACTERIZING HEIGHT KEEPING ERROR DISTRIBUTION CRASHWORTHINESS EXPERIMENT SUMMARY FULL-SCALE BASED ON INDIRECT OBSERVATION TRANSPORT CONTROLLED IMPACT DEMONSTRATION S. NAGAOKA (Ministry of Transport, Electronic Navigation PROGRAM Flnal Report Research Institute, Mitaka, Japan) IN: Navigation and environment; D. JOHNSON and L. GARODZ Jun. 1986 629 p Proceedings of the Fifth International Congress, Tokyo, Japan, (DOT/FAA/CT-85/20) Avail: NTlS HC A99/MF A01 October 1-5, 1985 . Tokyo, Japan Institute of Navigation, 1986, p. On December 1, 1984, the Federal Aviation Adminstration 125-132. refs (FAA), and NASA, conducted an air-to-ground impact test The distributions of relative vertical distances are analyzed using demonstration with a remotely piloted jet transport category aircraft. vertical navigational error data collected at Sendai, Japan during This demonstration, identified as the Full-Scale Transport l 1978-1983. The modeling of the RVD distribution is described Controlled Impact Demonstration (CID) Program, was the and the models are compared to empirical data. It is observed culmination of four years of effort by the two agencies. The major that the double exponential (DE) and double-double exponential FAA objecvtives included the demonstration of antimisting fuel (DDE) models best represent the RVD distribution and show the and a series of fire safety and structural type crashworithness best correlation with the empirical data. The HKE distribution can experiments. The NASA demonstrated objectives also extended also be expressed by DE and DDE models. The distribution !o !he crashworthiness experiment area. A summary of :he FAA characteristics of the HKE and the RVD are defined as: (1) structural experiments is provided which included an instrumented symmetry about the zero mean, (2) unimodal with the mode being fuselage structure and an associated analytical KRASH model, located at zero, and (3) the probability density function does not on-board seatlcabin restraint and flight data recorder system increase monotonically with respect to the magnitude of error. installations, and a post-impact accident investigation exercise. The I.F. summary contains a description of each experiment, related Dre and post test activities, and resulting data. Author N87-10053# National Transportation Safety Board, Washington, D. C. AIRCRAFT ACCIDENT REEPORT, DELTA AIR LINES, INC., N87-10056# National Transportation Safety Board, Washington, LOCKHEED L-1011-385-1, N726DA, DALLASIFORT WORTH D. C. Bureau of Field Operations. INTERNATIONAL AIRPORT, TEXAS, AUGUST 2, 1985 Aircraft AIRCRAFT ACCIDENT REPORTS BRIEF FORMAT US CIVIL Accident Report, 2 Aug. 1985 AND FOREIGN AVIATION, ISSUE NUMBER 2 OF 1985 15 Aug. 1986 169 p ACCIDENTS (PB86-910406; NTSB/AAR-86/05) Avail: NTIS HC A08/MF A01 7 May 1986 404 p On August 2, 1985, at 180552 central daylight time, Delta Air (PB86-916916 NTSB/AAB-86/16) Avail: NTlS HC A18/MF A01; Lines flight 191, a Lockheed L-1011-385-1, N726DA. crashed while also available on subscription, North American Continent HC appiodiifiy iu hid UII rurlway iii ai ine Daiias Fon Wonh $itl5.uu/year; ail otners write for quote CSCL 01B International Airport, Texas. While passing through the rain shaft The publication contains selected aircraft accident reports in beneath a thunderstorm flight 191 entered a microburst which the brief format occurring in U. S. civil and foreign aviation operations pilot was unable to traverse successfully. The airplane struck the during calendar year 1985. Approximately 200 general aviation ground about 6,300 feet north of the approach end of runway and air carrier accidents contained in the publication represent a 17L, hit a car on a highway north of the runway killing the driver, random selection. The publication is issued irregularly, normally struck two water tanks on the airport, and broke apart. Except for eighteen times each year. The brief format represents the facts, a section of the airplane containing the aft fuselage and conditions, circumstances and probable cause(s) for each empennage, the remainder of the airplane disintegrated during accident. GRA

17 03 AIR TRANSPORTATION AND SAFETY

N87-10851 Central Bureau of Statistics, Voorburg (Netherlands). discusses key design parameters, features and constraints. Hoofafdeling Statistieken van Verkeer en Vervoer. Author AVIATION STATISTICS, 1984 [STATISTIEK VAN DE LUCHTVAARTI A87-10143 1985 70 p Partly in DUTCH and ENGLISH Original contains STOCHASTIC MODELLING OF RADAR RETURNS color illustrations P. THOMAS (Bell-Northern Research, Montreal, Canada) and S. (ISBN-90-357-0386-3;ISSN-0168-552X; ETN-86-98074) Avail: HAYKIN (McMaster University, Hamilton, Canada) IEE Issuing Activity Proceedings, Part F - Communications, Radar and Signal Statistics on world aviation and Dutch aviation are given. Graphs Processing (ISSN 0143-7070), vol. 133, pt. F, no. 5, Aug. 1986, p. showing passenger transport and goods transport are presented. 476-481. NSERC-supported research. refs Data concerning commercial and noncommercial flights, The paper considers the stochastic modeling of radar returns. passengers, and mail transport are tabulated. Flight and transport In particular, returns from a typical airport surveillance radar (ASR) from Dutch airports are listed. ESA system have been modeled as autoregressive-moving average (ARMA) processes. Both maximum-likelihood (ML)- and N87-10852# National Transportation Safety Board, Washington, autocorrelation-based techniques have been used. Order selection D. C. algorithms were studied and modified to optimize their performance NATIONAL TRANSPORTATION SAFETY BOARD SAFETY for short-data records necessitated by the nonstationary radar RECOMMENDATION environment. Distinctively different models have been found for 11 Feb. 1986 17 p typical combinations of ground, weather and aircraft returns. Avail: NTlS HC AO2/MF A01 Author Modifications were discussed for the following areas: detailed inspection of engine exhaust manifold assemblies, wye assemblies, A87-10931 turbo inlet elbow assemblies, and collector assemblies for cracks AIRBORNE RECONNAISSANCE IX; PROCEEDINGS OF THE due to exhaust gas erosion in Cessna T310, 320, 340, 401, and MEETING, SAN DIEGO, CA, AUGUST 20, 21, 1985 411 series aicraft and model 402. 402A, 4028. 414, 421, 421A, F. R. LAGESSE, ED. (McDonnell Aircraft Co., Saint Louis, MO) and 421 6 aircraft; fuel system contamination due to deteriorated and P. HENKEL, ED. (General Dynamics Corp., Saint Louis, MO) sponge-filled fuel reservoir tanks; and weight calculation and Meeting sponsored by SPIE. Bellingham, WA, Society of balance for passenger loads that deviate from standard average Photo-Optical Instrumentation Engineers (SPIE Proceedings. weight. B.G. Volume 561), 1985, 179 p. For individual items see A87-10932 to A87-10950. (SPIE-561) The present conference considers topics in high altitude 04 reconnaissance equipment and its application to various missions, the receipt, processing and exploitation of reconnaissanceimagery, and issues related to the design and application of real-time image AIRCRAFT COMMUNICATIONS AND NAVIGATION acquisitions equipment. Among the topics discussed are image resolution limits due to mechanical vibration, atmospheric effects Includes digital and voice communicationwith aircraft; air navigation on oblique reconnaissance, the piloting of unmanned air vehicles, systems (satellite and ground based); and air traffic control. the impact of microprocessors on reconnaissance hardware, the acoustooptic implementation of SlGlNT systems for spread spectrum communications, data compression for IR A87-10047 reconnaissance, the synergism between tactical electronic support GLOBAL POSITIONING SYSTEM APPLICATIONS measures and imaging sensors, and the development status of T. S. LOGSDON and J. D. ASHLEY (Rockwell International Corp., real-time processing. O.C. Satellite Systems Div., Seal Beach, CA) IN: Space Congress, 23rd. Cocoa Beach, FL, April 22-25, 1986, Proceedings . Cape A87-10944 Canaveral, FL, Canaveral Council of Technical Societies, 1986, p. RAPID TARGET LOCATOR 8-1 to 8-9. refs J. BISBEE (Litton Industries, ltek Optical Systems Div., Lexington, The Navstar GPS is a space-based radio-navigation system MA) IN: Airborne reconnaissance IX; Proceedings of the Meeting, that employs dual-frequency L-band transmissions to provide San Diego, CA, August 20, 21, 1985 . Bellingham, WA, Society of continuous, worldwide navigation coverage to an unlimited number Photo-Optical Instrumentation Engineers, 1985, p. 89-94. of users. The configuration, capabilities, and operation of the GPS While airborne electrooptical reconnaissance systems can satellites are described. The Navstar system has been tested and transmit an image in real time to an imagery interpreter’s console, the operating ranges and accuracy levels of the system are it takes a further 15 min for the interpreter to issue a report; the compared with those of other radio-navigation systems. It is greatest delay in this process is the need to determine the target’s observed that the Navstar system is as accurate or more accurate location by means of an Analytical Photogrammetric Positioning than other navigation systems currently in use. The uses of the System, which uses stereophotomaps to determine the coordinates GPS satellites in militaty, air traffic control, time synchronization, of a point on the ground. An attempt has been made to reduce offshore oil exploration, and iceberg tracking are discussed. I.F. the time to the issuance of a report to 2 min without compromising accuracy, so that moving target location is accurate to about 100 A87-10137 ft in less than half a min. This Rapid Target Locator concept MILITARY AERONAUTICAL SATELLITE COMMUNICATIONS employs a library of digitized maps, together with automated D. CUMMINGS and C. G. WILDEY (Marconi Defence Systems, correlation and continuous position estimates that are made on Ltd., Watford, England) IEE Proceedings,Part F - Communications, the basis of the aircraft’s navigation equipment. O.C. Radar and Signal Processing (ISSN 0143-7070), vol. 133, pt. F, no. 4. July 1986, p. 411-419. refs A87-10947 The paper describes the development of Europe’s first super DATA COMPRESSION FOR IR RECONNAISSANCE high frequency (SHF) military aircraft satellite communications W. MCCRACKEN (Honeywell, Inc., Electro-Optics Div., Lexington, (’aerosatcoms’) terminal. This development marks the accelerating MA) IN: Airborne reconnaissance IX; Proceedings of the Meeting, international interest in both civil and military aerosatcoms which San Diego, CA, August 20, 21, 1985 . Bellingham, WA, Society of has been spurred by recent advances in space, microwave, Photo-Optical Instrumentation Engineers, 1985, p. 115-1 19. modulation and antenna technologies. The paper examines the Recent trends in airborne reconnaissance force the designers impact of these advances on the military aircraft project and of IR reconnaissance sensors to study data compression methods

18 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION so that the sensors can be more efficiently interfaced with real A87-11337 time data links and with magnetic recorders. The previous FUNDAMENTALS OF NAVIGATION ACCORDING TO successful efforts in compressing FLlR data are briefly noted. GEOPHYSICAL FIELDS [OSNOVY NAVlGATSll PO Infrared line scanners have only recently become candidates for GEOFlZlCHESKlM POLIAM] the data compression. Some of the requirements and problems I. N. BELOGLAZOV, G. I. DZHANDZHGAVA, and G. P. CHlGlN are noted for compressing line scan data. Applicable methods Moscow, Izdatel’stvo Nauka, 1985, 328 p. In Russian. refs are presented, and a hybrid DPCMIHuffman Coder is described The theory of navigation and guidance systems using with some successful results. Author geophysical fields, as well as navigation equipment and techniques, are reviewed with reference to work published abroad. Topics discussed include surface geophysical fields, their characteristics, A87-10948 and measurement techniques; anomalous three-dimensional PHOTOGRAMMETRIC TOOLS FOR PANORAMIC SECTOR geophysical fields; and memory and data processing devices for SCAN IMAGERY IN THE VIDARS ANALYSIS STATION navigation systems using geophysical fields. The discussion also F. W. LEBERL. M. STEVENS, E. KIENEGGER (VEXCEL Corp., covers the structure, the principle of operation, and software Boulder, CO), V. KAUFMANN (Graz, Technische Universitaet und requirements of navigation systems using geophysical fields and Forschungszentrum, Austria), and G. C. GUSTAFSON (James Madison University, Harrisonburg, VA) IN: Airborne synthesis of algorithms for estimating vertical motion parameters. V.L. reconnaissance IX; Proceedings of the Meeting, San Diego, CA, August 20, 21, 1985 . Bellingham, WA, Society of Photo-Optical Instrumentation Engineers, 1985, p. 120-130. refs Computer-assistedphotointerpretation is a recent development supported by the advent of numerous interpretation stations. A unique universal station is ’VIDARS’ which has recently been A87-11370 equipped with a new software system that incorporates complex LASER REMOTE SENSING PROCEDURES PROVIDE AN AID photogrammetric mensuration capabilities. Photo-interpreters TO AVIATION DURING THE APPROACH FOR LANDING typically find it difficult to perform mensuration tasks; therefore [LASER-FERNERKUNDUNGSVERFAHREN HELFEN DER the implementation of the photogrammetric functions must not LUFTFAHRT BElM LANDEANFLUG] burden the user with a need to understand photogrammetric C. WERNER (DFVLR, lnstitut fuer Optoelektronik, theories. This paper illustrates a difficult application of VIDARS to Oberpfaffenhofen, West Germany) DFVLR-Nachrichten (ISSN sector-scan panoramic tiim imagery ana wiii show bow well :he Xi i-430; j, 2iiki t988, i;. 19-24. !R German. E!S user can perform target positioning tasks within his interpretation This paper presents a descriptiori of two laser remote sensing work. Author procedures. One method makes it possible to determine slant visibility with respect to the path of the approaching aircraft during A87-10949 fog. The second method was used for measurements providing MANAGEMENT OF AIRBORNE RECONNAISSANCE IMAGES information regarding the danger to which small aircraft landing THROUGH REAL-TIME PROCESSING shortly behind large aircraft are exposed on account of vortex N. H. ENDSLEY (Ball Corp., Ball Aerospace Systems Div., Boulder, evolution. Under conditions of bad weather, the Runway Visual CO) IN: Airborne reconnaissance IX; Proceedings of the Meeting, Range (RVR) data transmitted to the pilot during the approach San Diego, CA. August 20, 21, 1985 . Bellingham, WA, Society of are not always very accurate. One of the laser methods discussed Photo-Optical Instrumentation Engineers, 1985, p. 157-164. may provide a solution to this problem, and a device implementing USAF-sponsored research. refs the considered procedure has been tested at the airport Digital airborne reconnaissance images generated by Munich-Riem in West Germany. The optical radar procedure utilized electrooptical sensors are able to furnish photographic is based on the use of a laser. The second method described, film-competitive resolution, as well as better spectral selectivity, which is concerned with wind relations, is based on a utilization increased dynamic range, and better radiometric accuracy than of the Doppler effect. Measurements with the developed device conventional film; the primary advantage to which attention is were started at the airport FrankfurtIMain in summer 1983. G.R. presently given, however, is the efficient real-time processing of images for immediate transmission to users. Digital resampling, or ’image warping’, is discussed as a necessary component of future digital reconnaissance, since it allows reduced fabrication and alignment costs for multisensor systems while providing precise A87-11662 geometric correction and alignment of images. The use of hardware THE METHODOLOGY AND TOOLS FOR PROCESSING RADAR IO irnpienwni ail aiii&t-ii geiiei&piip;se ;c:.nmp!i~g ~:X~SSP k - rm.C-. .--fin --IC CInl lTll C DfiI le I CC EVA1 I lATlnNs UA IA LWC I nVUuLuUmL L I VY I I-Y * --. --- - -. . . . - presented. O.C. RADAR] D. ALVAREZ (Direction Generale de I’Aviation Civile, Centre A87-11061 d’Etudes de la Navigation Aerienne, Orly, France) Navigation KNOWLEDGE-BASED TACTICAL TERRAIN ANALYSIS (Paris) (ISSN 0028-1530), vol. 34, July 1986, p. 300-321. In J. GILMORE, D. HO, S. TYNOR, A. SEMECO, C.-C. TSANG French. (Georgia Institute of Technology, Atlanta) et al. IN: Applications The complexity of modern air traffic control radar networks of digital image processing VIII; Proceedings of the Meeting, San and the data they provide, when combined with the large volume Diego, CA, August 20-22, 1985 . Bellingham, WA, Society of of traffic over industrialized nations, requires a high degree of Photo-Optical Instrumentation Engineers, 1985, p. 182-189. refs automation in the signal processing systems. The automation is The performance of autonomous vehicle systems is currently especially crucial for providing early warning of possible collision limited by their inability to accuraieiy anaiyLe iiieii SiiiGiifidiEg ska!icns, Lo.. zu!nmaticnlly detecting and projecting aircraft environment. In order to function in a dynamic real world separation distances which fall beneath a threshold value. The environment, an autonomous vehicle system must be capable of French have developed the CENA system which detects, decodes, interpreting terrain based upon predetermined mission goals. This filters, smooths and displays aircraft positions and associated data paper describes a concept of knowledge-based terrain analysis on ATC screens. The CENA system digests the data arriving from currently being developed to support the information needs of an primary and secondary radar beacons and compares different flight autonomous helicopter system. The terrain analysis system consists paths with reference trajectories, taking into account the types of of five integrated processing stages. Each process is discussed in aircraft detected. Trained personnel continually monitor the system detail and supported by a number of mission oriented examples. to ensure its reliability, including the limitation of displays to data Author essential for the performance of ATC tasks. M.S.K.

19 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

A87-11663 A87-11807# POLAR NAVIGATION ASSISTED BY SATELLITE [NAVIGATION FANS - A U.S. PERSPECTIVE POLAIRE ASSISTEE PAR SATELLITE] S. B. PORITZKY (FAA, Washington, DC) IN: Radio Technical G. BODENEZ and M. DAMENE Navigation (Paris) (ISSN Commission for Aeronautics, Annual Assembly Meeting and 0028-1530), vol. 34, July 1986, p. 330-337. In French. Technical Symposium, Washington, DC, November 19-21, 1985, Aircraft flying polar routes experience navigation difficulties due Proceedings . Washington, DC, Radio Technical Commission for to fading of the horizontal component of the earth’s magnetic Aeronautics, 1985, p. 133-144. field and because of limitations on the capabilities of inertial The ICAO Future Air Navigation System (FANS) Committee gyroscopes. The option exists of improving polar navigation by was established to identify potential systems and techniques for access to navigation satellites. Numerical models are defined for improving communications, navigation and surveillance systems calculating position data from GEO satellite signals and making and to lay the groundwork for international standardization of the corrections for atmospheric refraction of the signals. Techniques systems. Acceptance of a new system hinges on the perceived for generating accurate loxodromic maps to utilize the satellite need and the willingness (and ability) to pay for it. The latter signals are described. M.S.K. factor has been a constraining force in numerous developing areas of the world. Studies of the benefits of satellite-based navigation systems led to the identification of several areas in which international civil aviation can benefit from satellites: better position and altitude resolution in the 290-1000 ft altitude interval, improved data link communications, and improved performance standards A87-11664 and an airborne separation ensurance capability. The logistics COMBINED UTILIZATION OF LORAN AND GPS - THE BEST which would have to be implemented to realize these goals with FROM EACH SYSTEM [UTILISATION COMBINEE DU LORAN an internationally accepted standard satellite navigation system ET DU GPS LE MEILLEUR DE CHAQUE SYSTEME] are discussed. M.S.K. P. BRAISTED. R. ESCHENBACH, and A. TlWARl (Trimble Navigation Co., Mountain View, CA) (Institute of Navigation, National Technical Meeting, Long Beach, CA, Jan. 21, 1986) Navigation (Paris) (ISSN 0028-1530). vol. 34, July 1986, p. 338-345. In French. The Loran system has been functioning since the 1960s and A87-12676 furnishes comprehensive navigational reference data for the NAVIGATION AND ENVIRONMENT; PROCEEDINGS OF THE Northern Hemisphere. However, the established grid has gaps in FIFTH INTERNATIONAL CONGRESS, TOKYO, JAPAN, the middle of the continents and the middle of the oceans and in OCTOBER 1-5, 1985 all other locations furnishes data with accuracy to 5 n. mi. The Congress sponsored by the International Association of the GPS system will permit worldwide navigation by access to signals Institutes of Navigation, Japan Maritime Promoting Association, from four satellites whose positions are known. The GPS is to and Japanese Shipowners’ Association. Tokyo, Japan Institute of furnish positioning data accurate to 50 m, starting after 1987. The Navigation, 1986, 341 p. For individual items see A87-12677 to GPS system can furnish signals which are strong enough to A87-12690. calculate the phase of the Loran cycle, which is at times uncertain Papers are presented on hydrographic contributions to safety because of the low power of the Loran signals. The GPS provides at sea from 1975-1985; laser airborne depth sounding in Australia; global coverage, but periods will exist where the GPS signal cannot the electronic chart; disturbances to airborne navigation and be accessed. Since the Loran signals are continuous in time, the communication systems caused by atmospheric statics; navigation Loran system can furnish navigational data when the GPS is not by gradient of geophysical parameter; the safe distance of nautical accessible. M.S.K. equipment from magnetic compasses; monitoring of the terminal flight phases environment; and routing and the environment. Consideration is given to the global radio navigation system; the GPS; an integrated GPS/dead-reckoning system; the ring laser gyro dither positional pickoff; characterizing height keeping error distribution using indirect observations; the microwave landing A87-11806# system; air traffic control systems; the aircraft flight deck; the use TRANSITION TO NEW SYSTEMS AND INTERNATIONAL of differential Loran-C in Norwegian offshore activities; multiradar PERSPECTIVES tracking; and the identification of marine vessels from ship and J. S. SMlT (Rijksluchtvaartdienst, The Hague, Netherlands) IN: shore. Topics discussed include interference of the aeronautical Radio Technical Commission for Aeronautics, Annual Assembly Navaids from FM broadcasting services; probability estimation of Meeting and Technical Symposium, Washington, DC. November oil spills from a tanker; a unified certification system for merchant 19-21, 1985, Proceedings . Washington, DC, Radio Technical marine officers; human dynamic response to the oscillatory motion Commission for Aeronautics, 1985, p. 119-1 30. of fishing vessels in the application of the collision rate as a Although new technological developments can hold obvious danger criterion for marine traffic; and the safety of modern shipping benefits for the enhancement of safety and efficiency of air traffic, and requirements in hydrographic surveying and nautical charting. no new system can be realistically considered without defining I.F. the transition process. The ICAO established the Future Air Navigation Systems Committee to identify potential hardware and techniques for the improvement of communications, navigation and surveillance systems. FANS has recognized the potential of satellite-based navigation and communications relay systems and the MLS. The implementation of the systems on an international scale depends on their utility for international civil aviation. Criteria A87-12678# are defined on which to base selections among satellite navigation DISTURBANCES BROUGHT BY ATMOSPHERIC STATICS TO systems (NAVSTAR, GLONASS, GEOSTAR, etc.). None of the AIRBORNE NAVIGATION AND COMMUNICATION SYSTEMS systems can become an international standard until an organization H. BONGRAIN (Navigation /Paris/, vol. 33, Oct. 1985, p. 442-464) capable of operating and maintaining the system is established. IN: Navigation and environment; Proceedings of the Fifth Finally, impediments and possible venues which can be explored International Congress, Tokyo, Japan, October 1-5, 1985 . Tokyo, to develop internationally-usedsystems and implement them while Japan Institute of Navigation, 1986, p. 35-42. Translation. Previously other systems continue in use are discussed. M.S.K. cited in issue 06, p. 691, Accession no. A86-18695.

20 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

A87-12680# A07-12689# INTEGRATION OF GPS WITH OTHER RADIONAVIGATION A NEW CONCEPT IN AIR TRAFFIC CONTROL - THE SYSTEMS MULTI-RADAR TRACKING (MRT) G. F. SAGE (Navigation Technology, Inc., Cool, CA) and J. D. E. PASCARELLA, S. PALMIER1 (Aeronautica Militare Italiana, LUSE (Interstate Electronics Corp., Newport Beach, CA) Rome, Italy), and C. PETROSELLINI IN: Navigation and (Navigation /Paris/, vol. 34, Apr. 1986, p. 196-206) IN: Navigation environment; Proceedings of the Fifth International Congress, and environment; Proceedings of the Fifth International Congress, Tokyo, Japan, October 1-5. 1985 . Tokyo, Japan Institute of Tokyo, Japan, October 1-5, 1985 . Tokyo, Japan Institute of Navigation, 1986, p. 191-200. Navigation, 1986, p. 89-99. Previously cited in issue 18, p. 2609, The multiradar tracking (MRT) system provides one position Accession no. A86-39560. refs information on a single plan position indicator by detecting the different echoes of a single target arriving from multiple radar A87-12684# stations with partially superimposed coverages. The operation of THE U.S. FEDERAL RADIONAVIGATION PLAN the MRT, which is based on SSR data, and the configuration of D. C. SCULL (DOT, Washington, DC) IN: Navigation and the system are considered. The radar echoes processing and flight environment; Proceedings of the Fifth International Congress, data updating with the MRT system are discussed. The Tokyo, Japan, October 1-5, 1985 . Tokyo, Japan Institute of performance of MRT operations in an air traffic control automatic Navigation, 1986, p. 133-143. refs system was evaluated at Ciampino Airport in Rome; it is observed The development of radio navigatiiton systems is examined. that compared to a monoradar the multiradar operating algorithm The roles of the DOD and DOT in planning radio navigation systems improves the echoes performances, and that the system is capable are discussed. The objectives of the Federal Radionavigation Plan, of providing economical, safe, and efficient radar control for a in particular the implementation of the GPS, are considered. The large area. The development of a radar tracking system which functions of radio beacons, Loran-C, VOR/DME, Omega, Tacan, will supply meteorological data for the entire Italian airspace is ILS/MLS, and Transit are described; these systems are to be proposed. I.F. replaced by the GPS which will provide military and civil air, marine, and land navigation assistance. The technical, economic, and A87-1269O# institutional issues related in civil use of GPS are studied. The INTERFERENCE OF THE AERONAUTICAL NAVAIDS formation of civil satellite navigation systems in the U.S. and Europe (FREQUENCY BAND 108-118 MHZ) FROM F.M BROADCASTING is proposed. I.F. SERVICE (88-108 MHZ) 0. CAREL and J. M. LOSCOS (Direction Generale de I’Aviation Civiie, Paris, Fraittiej I?.? X&ga:ion and envircnmen!; Proceedings A87-12685# of the Fifth Iniernationai Congress, Tokyo, Japan, October 1-5, A LOW COST COMMERCIAL GPS SET 1985 . Tokyo, Japan Institute of Navigation, 1986, p. 259-267. N. B. HEMESATH (Rockwell International Corp., Cedar Rapids, IA) IN: Navigation and environment; Proceedings of the Fifth International Congress, Tokyo, Japan, October 1-5, 1985 . Tokyo, N87-10057 Southern Methodist Univ., Dallas, Tex. Japan Institute of Navigation, 1986, p. 145-151. A DECENTRALIZED FAULT-TOLERANT APPROACH TO The development of a low cost GPS for commercial use is ESTIMATION IN MULTI-SENSOR NAVIGATION SYSTEMS Ph.D. discussed. The GPS is a space-based system which transmits on Thesis two RF channels, L1, L2, has two codes, CIA, P, and the number 8. D. BRUMBACK 1985 139 p of tracking channels are equivalent to the number of satellites Avail: Univ. Microfilms Order No. DA8604722 tracked simultaneously. The final constellation will consist of 18 This investigation considers the problem of designing estimation algorithms for aided-inertial navigation in which both global satellites in six separate orbital planes of three satellites each; accuracy and reliability in the presence of soft sensor failures is the deployment schedule for the system is examined. The cost and performance of GPS user equipment designed for commercial required. The approach is to correlate subsets of available sensor data to create multiple estimates of the aircraft navigation state. use are evaluated. A GPS set composed of the L1 channel, the A two-ellipsoid overlap test is used to determine which local CIA code, and one tracking channel is described and the set’s estimates agree and which disagree. Knowledge of the underlying performance satisfies the GPS specifications. I.F. sensor set then provides information to determine which estimates are correct, and which sensors have failed. The estimates that A87-12686# are based on the unfailed sensors are then combined to obtain FLIGHT EXPERIMENTS ON MLS ELEVATION GUIDANCE the global estimate. Monte Carlo simulation results are presented K. KOREMURA and T. KATANO (Ministry of Transport, Electronic for a system composed of two inertial navigation systems and a Navigation Research Institute, Mitaka, Japan) (Navigation /Paris/, Doppler radar. The soft failure considered in this application is an VU;. 34, A~R.:%E, p. 53 72) !E: F?zvigz!inn and environment: accelerometer bias shift. False alarm and detection probabilities, Proceedings of the Fifth International Congress, Tokyo, Japan, mean detection-time, and the estimation error of tne tauit-toierani October 1-5. 1985 . Tokyo, Japan Institute of Navigation, 1986, p. system are determined numerically. It is shown that the 153-160. Previously cited in issue 11, p. 1480, Accession no. fault-tolerant approach yields improved performance, compared to A86-27899. a global filter, in the presence of the soft failure. Dissert. Abstr.

A87-12687# N87-10853# Radio Technical Commission for Aeronautics, AUTOMATED FUNCTIONS FOR AIR TRAFFIC CONTROL Washington, D. C. Special Committee 153. SYSTEMS MINIMUM OPERATIONAL PERFORMANCE STANDARDS FOR M. LUCERTlNl (CNR, IASI, Rome, Italy) IN: Navigation and AIRBORNE ILS GLIDE SLOPE RECEIVING EQUIPMENT environment; Proceedings of the Fifth International Congress, OPERATING WITHIN THE RADIO FREQUENCY RANGE OF -.tonyu, japan, Ot:~bs: 5, !9P5 . Tekye, Jzpsn lngtittita of 328.6-335.4 MHZ Navigation, 1986, p. 161-169. refs Jul. 1986 71 p Revised The aim of this paper is to give evidence that with suitable (RTCA/DO-192; RTCA/DO-l32A-REV) Avail: NTlS HC A04/MF algorithms, parallel computing systems, and software optimization A01 ; also available from RTCA Secretariat $25.00 it is possible to provide a real-time complete conflict alert analysis This document was prepared by Special Committee 153 of the for a sufficiently large number of aircraft. A strategy is presented Radio Technical Commission for Aeronautics. It was approved by to decompose the problem into subproblems such that parallel RTCA on July 18, 1986, and supersedes RTCA/DO-l32A, computation of subproblems will be possible. In particular the Performance Standards Airborne ILS Glide Slope Receiving algorithmic structure is shown to be suitable for the implementation Equipment, November 2, 1978. RTCA is an association of on a multiprocessor computer system. Author aeronautical organizations of the United States from both

21 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION government and industry. Dedicated to the advancement of INS only, Doppler only and TAS/HDG navigation modes, and aeronautics, RTCA seeks sound technical solutions to problems control of the various C-130 communication/navigation(comm/nav) involving the application of electronics and telecommunications to systems. The SCNS ICDS consists of three Integrated Control aeronautical operations. Its objective is the resolution of such Display Units (ICDU) and one Bus Integration Computer Unit (BICU) problems by mutual agreement of its member organizations. The for all C-130 aircraft except that the HC-130H will have an additional findings of RTCA are in the nature of recommendations to all ICDU for the radio control. GRA organizations concerned. Since RTCA is not an official agency of the United States Government, its recommendations may not be regarded as statements of official government policy unless so enunciated by the Federal government organization or agency 05 having statutory jurisdiction over matters to which the recommendations relate. In preparation of these standards RTCA AIRCRAFT DESIGN, TESTING AND SC-153 took into consideration comments received on behalf of the European Organization for Civil Aviation Electronics PERFORMANCE (EUROCAE) WG-5. Author Includes aircraft simulation technology. N87-10854'# Massachusetts Inst. of Tech., Cambridge. Flight Transportation Lab. A87-10574 POTENTIAL IMPACTS ADVANCED TECHNOLOGIES ON THE OF PALMDALE AND THE BOMBER CONNECTION ATC CAPACITY HIGH-DENSITY TERMINAL AREAS OF Air International (ISSN 0306-5634), vol. 31, Aug. 1986, p. 65-73, R. W. SIMPSON, A. ODONI, and SALAS-ROCHE Oct. R. F. 89. 1986 175 p (Contract NAG1-472) The B-1B bomber is now in production in Palmdale, CA, and (NASA-CR-4024; NAS 1.26:4024) Avail: NTlS HC A08/MF A01 may be followed by the 8-2 Advanced Technology Bomber. The CSCL 17G area has been known for military aircraft production and 'black', Advanced technologies for airborne systems (automatic flight classified programs since at least the 1950s. The Orbiters are control, flight displays, navigation) and for ground ATC systems also manufactured in one of the local facilities. The B-18 aircraft, (digital communications, improved surveillance and tracking, which carries 161 defensive avionics systems, has a primary automated decision-making) create the possibility of advanced ATC mission of low-altitude, supersonic penetration into enemy territory operations and procedures which can bring increased capacity for with nuclear bombs and cruise missiles. The all-weather aircraft is runway systems. A systematic analysis is carried out to identify built of 42.5 percent aluminum, 17.6 percent titanium, 7 percent certain such advanced ATC operations, and then to evaluate the steel, 2-3 percent composites and 30.6 percent fiberglass. The potential benefits occurring over time at typical US high-density aircraft will be based far enough inland to permit a 5 min scramble airports (Denver and Boston). The study is divided into three parts: time to offset a 7 min time span between launch and arrival of (1) A Critical Examination of Factors Which Determine Operational hostile submarine-launched ballistic missiles. Numerous design Capacity of Runway Systems at Major Airports, is an intensive details and demonstration and test flight programs being flown by review of current US separation criteria and terminal area ATC the early production units are delineated. M.S.K. operations. It identifies 11 new methods to increase the capacity of landings and takeoffs for runway systems; (2) Development of A87-10575 Risk Based Separation Criteria is the development of a rational YAKOVLEV FORGER structure for establishing reduced ATC separation criteria which R. BRAYBROOK Air International (ISSN 0306-5634), vol. 31, meet a consistent Target Level of Safety using advanced Aug. 1986, p. 81-86. technology and operational procedures; and (3) Estimation of Although it appears that the Soviets began development of a Capacity Benefits from Advanced Terminal Area Operations - VTOL aircraft in the 196Os, the expense of the effort may have Denver and Boston, provides an estimate of the overall annual delayed the program. The concept of jet lifting was retained and improvement in runway capacity which might be expected at Denver tested in the Yak-38 Freehand, which displayed a high degree of and Boston from using some of the advanced ATC procedures automatic stability control but required a deep inset of the cockpit developed in Part 1. Whereas Boston achieved a substantial 37% to maintain balance. The Yak-38 Forger was introduced on increase, Denver only achieved a 4.7% increase in its overall antisubmarine carriers in 1971 and was tracked at a speed of annual capacity. Author Mach 1.05 by radar. Numerous comparisons are made between the design features observed in photographs of the Forger and N87-10855# Lear Siegler, Inc., Grand Rapids, Mich. Instrument the Harrier aircraft, noting the incorporation of many positive Div. features in the Forger that have only been proposed for the Harrier. OPERATING AND SUPPORT HAZARD ANALYSIS FOR Finally, projections are made of the mission scenarios and SELF-CONTAINED NAVIGATION SYSTEM LSI MODEL 6216A, capabilities of the aircraft. M.S.K. B AND C, GROUP B J. T. REEVES 30 May 1986 20 p A87- 10940 (Contract FO9603-85-C-1224) GROUND AND FLIGHT TESTS OF TORNADO (AD-A169381; REPT-6216-019) Avail: NTlS HC A02/MF A01 RECONNAISSANCE POD CSCL 17G W. FRANKE (Messerschmitt-Boelkow-Blohm GmbH, Munich, West This document constitutes the Operating and Support Hazard Germany) IN: Airborne reconnaissance IX; Proceedings of the Analysis (OSHA) for the C-130 Self-contained Navigation System Meeting, San Diego, CA, August 20, 21, 1985 . Bellingham, WA, (SCNS) Group LRUs. It provides a hazard assessment of use and Society of Photo-Optical Instrumentation Engineers, 1985, p. maintenance of the individual LRUs provided by LSI. The purpose 59-66. of an OSHA is to identify and control hazards to personnel and This paper describes the efforts which have been performed to the system, or related to production, installation, maintenance, to qualify the newly designed Tornado reconnaissance pod for its test, operation, etc. This OSHA is limited to design of the Group application to various missions. These efforts included B LRUs as the design affects operational use and maintenance comprehensive ground and flight tests. Reconnaissance Pods are safety of personnel working in or around the equipment, including designed so as not to limit the flight performance of the arcraft. ground and flight crews. The SCNS is comprised of a Doppler On the other hand, reconnaissance equipments require a stable Velocity Sensor (DVS), Inertial Navigation System (INS), Integration environment, which is in contrast to the ambient conditions of Computation and Display System (ICDS), and the associated outboard stores on high performance fighter aircraft. To ensure installation Group A kit to provide Doppler aided INS navigation, that the designers fulfilled their tasks to match these conflicting

22 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE requirements to a good technical solution, the tests described in low-order panel methods to powerplant installation studies. Also this paper have been carried out. Author addressed are: three-dimensional flow analysis of turboprop inlet and nacelle Configurations, application of computational methods A87-10941 to the design of large turbofan engine nacelles, comparison of full PILOTING OF UNMANNED AIR VEHICLES. II potential and Euler solution algorithms for aeropropulsive flow field R. E. CLAPP (Gould. Inc., Systems and Simulation Div., Melville, computations, subsonic/transonic, supersonic nozzle flows and NY) IN: Airborne reconnaissance IX; Proceedings of the Meeting, nozzle integration, subsonic/transonic prediction capabilities for San Diego, CA, August 20, 21, 1985 . Bellingham, WA, Society of nozzle/afterbody configurations, three-dimensional viscous design Photo-Optical Instrumentation Engineers, 1985, p. 67-73. refs methodology of supersonic inlet systems for advanced technology Attention is given to the unmanned air vehicle piloting aircraft, and a user’s technology assessment. C.D. requirements imposed by command-and-control sequences, visual displays, communications, and the design and operation of remote control stations. In order to prevent operator overwork, heuristic A87-11780# programs are incorporated by vehicle controls, leaving the operator CFD APPLICATIONS TO ENGINE/AIRFRAME INTEGRATION to intervene only at the critical points of the mission. The vehicle E. .t TINOCO and A. W. CHEN (Boeing Commercial Airplane is preprogrammed to fly to a series of selected points automatically, Co., Seattle, WA) IN: Numerical methods for engine-airframe while operators monitor, update, or alter the flight programs as integration . New York, American Institute of Aeronautics and required. The testing hierarchy incorporated by the vehicle Astronautics, Inc., 1986, p. 219-255. refs encompasses sensors and data links. O.C. The use of CFD methods for the design and analysis of wing pylon-mounted enginelairframe configurations typical of subsonic A87-11343 transports is studied. The computational methods utilized include: METHODS OF IN-FLIGHT AEROPHYSICAL STUDIES [YETODY a linear panel code for the analysis of subcritical flows about AEROFIZICHESKIKH ISSLEDOVANII V POLETE] highly complex configurations; a full potential, finite volume A. D. MIRONOV, A. N. ZAMIATIN, A. A. KOROLEV, A. V. RODNOV, wing/body/strut/naceIle code; a three-dimensional, and M. G. FOMIN Moscow, Izdatel’stvo Mashinostroenie, 1985, time-dependent Euler formulation for isolated nacelles and for 112 p. In Russian. refs wing/body/nacelle/propfan configurations; and an axisymmetric The work describes aerophysical study methods used during explicit Navier-Stokes code for exhaust system analysis and flight tests to investigate phenomena that cannot be fully simulated exhaust plume calibration. Both the Euler isolated code nacelle in wind tunnel tests. These phenomena include flow past aircraft code and the full potential code are iteratively coupled to a surfaces, the development of vortex wakes, the propagztion o! ihtee-dirnensionai boundary layer method with shock shock waves from a flying aircraft, sonic booms. and aircraf! noise. wave/boundary layer interaction. A brief description of each Measurement equipment and experiment planning for the in-flight computational method is given, followed by application examples. studies are discussed, and experimental results are presented. C.D. B.J.

~87-11661 ~87-11781 # DIRIGIBLES FOR WHAT? [DES DIRIGEABLES POUR QUO1 - - CFD A USER’S TECHNOLOGY ASSESSMENT FAIRE?] - G. C. PAYNTER and E. TJONNELAND (Boeing Military Airplane M. DE BROSSARD Navigation (Paris) (ISSN 0028-1 vol. 530), Co., Seattle, WA) IN: Numerical methods for engine-airframe 34, July 1986, p. 269-290. In French. integration . New York, American Institute of Aeronautics and Lighter than air vehicles (LTA), until the late 1930s, were Astronautics, Inc., 1986, p. 505-537. refs considered on even par with winged aircraft for many air transport Current CFD technology for propulsion integration is assessed, operations. Safety and performance advantages gave winged and areas where further research and development will improve aircraft advantages which only recently are again being challenged the current technology in using CFD for installation design are by LTAs. Air freight and groundside facilities costs and pollution defined. The need for a strategy that makes feasible the analysis levels are all lower with LTAs, which can operate out of areas of propulsion installation flow within the constraints of available with no airports. Safety is enhanced by using helium, no longer a computer memory and speed is discussed, and the zonal modeling rare gas, as the lifting agent. The dimensions and performance strategy is defined as a way to satisfy this need. Examples of the levels of classic rigid, semi-rigid and flexible airships of the past use of zonal modeling are cited, the current capabilities of this are reviewed, and projections are made of the performance levels model are assessed, and suggestions for its improvement are which can be achieved with modern flexible LTAs serving made. The development, acquisition, and application of CFD are passenger and freight transport roles. Numerical models are discussed, and a user’s assessment of current capability is given discussed for predicting the lifetime and designing the control laws ,.,i+k .nnl.,4 *^ ^^_^...-- ..,.,,,wyu,u .” wur,l,,utcl oya~~~~ta,diyuiiiiiiris, geomerry ana mesn !E pi!z!ing and na.jigaiiiig liiudai II Lias. Finaiiy. numerous generation, turbulence modeling, and experimental validation. photographs are provided of typical airships. M.S.K. C.D. A87-11776 NUMERICAL METHODS FOR ENGINE-AIRFRAME INTEGRATION A87-11798 S. N. 8. MURTHY, ED. (Purdue University, West Lafayette. IN) JAS39 GRIPEN - A SWEDISH SOLUTION TO A MULTI-ROLE and G. C. PAYNTER, ED. (Boeing Airplane Co., Seattle, WA) New NEED York, American Institute of Aeronautics and Astronautics, Inc. B. WANSTALL lnteravia (ISSN 0020-5168). vol. 41, Aug. 1986, (Progress in Astronautics and Aeronautics. Volume 102), 1986, p. 867-870. 554 p. For individual items see A87-11777 to A87-11781. The design and components of the lightweight, multirole combat Various papers nn numerirz! me!hnds !B: cnginG-aiifiams aiiciaii, iiie LASS9 Gripen, are described. I his interceptor, ground integration are presented. The individual topics considered include: attack, and reconnaissance aircraft is single-engined, has a delta scientific computing environment for the 1980s, overview of planform, canards are fully fly controls, advanced avionics, and a prediction of complex turbulent flows, numerical solutions of the take-off weight of 8 tons. The engine is a modular low-bypass, compressible Navier-Stokes equations, elements of computational reheated turbofan weighing 1050 kg with a 8210 kg thrust. The enginelairframe integrations, computational requirements for software for the aircraft, which is based on a standardized efficient engine installation, application of CAE and CFD techniques computing system, and the fly-by-wire flight control system are to complete tactical missile design, CFD applications to examined. The capabilities of the multimode pulse-Doppler radar engine/airframe integration, and application of a second-generation are discussed. The arming of the aircraft is considered. I.F.

23 A87-11848 A87-12138' Rice Univ., Houston, Tex. IMPACT RESISTANT HYBRID COMPOSITE FOR AIRCRAFT GUIDANCE STRATEGIES FOR NEAR-OPTIMUM TAKE-OFF LEADING EDGES PERFORMANCE IN A WINDSHEAR S. C. NOLET and P. M. SANDUSKY (USAF, Sacramento Air A. MIELE, T. WANG (Rice University, Houston, TX), and W. W. Logistics Center, McClellan AFB, CA) SAMPE Quarterly (ISSN MELVIN (Delta Air Lines, Inc., Atlanta, GA) Journal of Optimization 0036-0821), vOI. 17, July 1986, p. 46-53. Theory and Applications (ISSN 0022-3239), vol. 50, July 1986, p. The Air Force A-10 aircraft has been exposed to a great number 1-47. refs of bird strike incidents over its lifetime. Damage to the wing leading (Contract NAG1-516) edge and substructure is common, resulting in excessive This paper is concerned with guidance strategies for maintenance and downtime. A new design utilizing a hybrid laminate near-optimum performance in a windshear. This is a wind of graphitelepoxy and Kevlar/epoxy has proven very effective in characterized by sharp change in intensity and direction over a preventing damage to the aircraft due to bird impact. The design relatively small region of space. The take-off problem is considered utilizes a solid laminate construction because integral stiffeners with reference to flight in a vertical plane. First, trajectories for and core designs have insufficient shear strengths to carry the optimum performance in a windshear are determined for different extreme loading of impact. The laminate used in the leading edge windshear models and different windshear intensities. Use is made design is quite thick at the nose section to prevent local buckling. of the methods of optimal control theory in conjunction with the A clevis joint is used in the new part to more efficiently carry dual sequential gradient-restoration algorithm (DSGRA) for optimal vertical shear loads. Thermal 'spring-in' during manufacturing control problems. In this approach, global information on the wind presented a major problem for installation of such a stiff part. flow field is needed. Then, guidance strategies for near-optimum Author performance in a windshear are developed, starting from the optimal trajectories. Specifically, three guidance schemes are presented: (1) gamma guidance, based on the relative path inclination; (2) theta guidance, based on the pitch attitude angle; and (3) acceleration guidance, based on the relative acceleration. A87-11898 In this approach, local information on the wind flow field is THE CLASSIFICATION OF WIND SHEARS FROM THE POINT needed. Author OF VIEW OF AERODYNAMICS AND FLIGHT MECHANICS [EINTEILUNG DER WINDSCHERUNGEN AUS DER SICHT DER AERODYNAMIK UND FLUGMECHANIK] A87-12649 F. SEIDLER (Hochschule fuer Verkehrswesen, Dresden, East BRAKING PERFORMANCE OF AIRCRAFT TIRES Germany) and G. HENSEL (Interflug Gesellschaft fuer S. K. AGRAWAL Progress in Aerospace Sciences (ISSN lnternationalen Flugverkehr mbH, Berlin, East Germany) 0376-0421), vol. 23. no. 2, 1986, p. 105-150. refs Technisch-oekonomische Information der zivilen Luftfahrt (ISSN This paper brings under one cover the subject of aircraft braking 0232-5012), vol. 22, no. 3-4, 1986, p. 107-112. In German. performance and a variety of related phenomena that lead to A study of international statistical data shows that in about aircraft hydroplaning, overruns, and loss of directional control. three quarters of all serious accidents which occurred with jet Complex processes involving tire deformation, tire slipping, and propelled airliners wind shear was either one of the main causes fluid pressures in the tire-runway contact area develop the friction of the accident or represented a major contributory cause. The forces for retarding the aircraft; this pape; describes the physics present article is concerned with wind shear related problems. of these processes. The paper reviews the past and present The necessity of a use of different concepts, definitions, and research efforts and concludes that the most effective way to divisions is explained, and the concepts and definitions required combat the hazards associated with aircraft landings and takeoffs for the division of wind and wind shear into different categories is on contaminated runways is by measuring and displaying in realtime discussed. A description of the context between meteorological the braking performance parameters in the aircraft cockpit. and aerodynamics-flight mechanics concepts, definitions, and Author divisions is also provided. Attention is given to wind and wind components, general characteristics of wind shear and the A87-12650 meteorological terms, the basic types of wind shear for A REVIEW OF ADVANCED TURBOPROP TRANSPORT aerodynamics-flight mechanics investigations, special types of wind ACTIVITY shear for aerodynamics-flight mechanics investigations, and R. H. LANGE (Lockheed-Georgia Co., Marietta) Progress in possibilities regarding a change of the wind component. G.R. Aerospace Sciences (ISSN 0376-0421), vol. 23, no. 2, 1986, p. 151-166. refs An overview is presented of propfan aircraft design concepts, system studies, and tests directed toward the resolution of technical A87-11899 issues related to advanced propfan transport aircraft. The system DYNAMIC FLIGHT OPTIMIZATION [DYNAMISCHE studies addressed include civil and military transport applications FLUGOPTIMIERUNG] and data on the performance, noise, and operating costs of propfan P. HACKER (Interflug Gesellschaft fuer lnternationalen Flugverkehr aircraft design concepts. NASA propfan projects with industry, mbH, Berlin, East Germany) Technisch-oekonomischeInformation including the Propfan Test Assessment program, are also der zivilen Luftfahrt (ISSN 0232-5012), vol. 22. no. 3-4, 1986, p. reviewed. C.D. 146-150. In German. refs The introduction of microprocessor technology provides new A87-13021'# National Aeronautics and Space Administration. effective possibilities for the optimization of flight conditions, taking Langley Research Center, Hampton, Va. into account the utilization of complex mathematical procedures, LAMINAR FLOW CONTROL FOR TRANSPORT AIRCRAFT such as the 'dynamic optimization'. Algorithms can be established APPLICATIONS as a basis for the calculation of flight conditions with the aid of R. D. WAGNER (NASA, Langley Research Center, Hampton, VA) flight planning installations and flight management systems. A National Aerospace Laboratory, Conference on Energy Efficient mathematical model which is suitable for the required calculations Aircraft Technology Towards 21st Century, Tokyo, Japan, May on the available small computers is discussed along with the basic 30, 1986, Paper. 6 p. refs relations of dynamic optimization, the approximation of the The incorporation of laminar flow control into transport aircraft fundamental characteristics, approaches for static optimization, the is discussed. Design concepts for the wing surface panel of laminar algorithm of dynamic optimization, and the implementation of the flow control transport aircraft are described. The development of program. It is possible to determine the optimal flight speed with small amounts of laminar flow on small commercial transports minimal fuel consumption. G.R. with natural or hybrid flow control is examined. Techniques for

24 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

eliminating the insect contamination problem in the leading-edge N87-10063’# Florida Atlantic Univ., Boca Raton. Dept. of region are proposed. I.F. Mechanical Engineering. TOWARD COMPARING EXPERIMENT AND THEORY FOR CORROBORATIVE RESEARCH ON HINGELESS ROTOR STABILITY IN FORWARD FLIGHT (AN EXPERIMENTAL AND ANALYTICAL INVESTIGATION OF ISOLATED ROTOR-FLAP-LAG STABILITY IN FORWARD FLIGHT) Annual N87-10060 Maryland Univ., College Park. AEROELASTIC STABILITY OF COMPOSITE ROTOR BLADES Report G. GAONKAR Aug. 1986 33 p Prepared for Army Aviation IN HOVER Ph.D. Thesis Research and Development Command, Moffett Field, Calif. C. H. HONG 1985 144 p Avail: Univ. Microfilms Order No. DA8608813 (Contract NCC2-361) (NASA-CR-179711; NAS 1.26:179711) Avail: NTlS HC AO3/MF The aeroelastic stability of flap bending, lead-lag bending, and A01 CSCL 01C torsion of hingeless and bearingless composite blades in hover For flap-lag stability of isolated rotors, experimental and are investigated using a finite element theory based on Hamilton’s f analytical investigations are conducted in hover and forward flight principle. The hingeless blade is treated as a single cell laminated on the adequacy of a linear quasisteady aerodynamics theory with shell beam. Bearingless blade configuration is assumed as the dynamic inflow. Forward flight effects on lag regressing mode are one consisting of a single flexbeam with a wrap-around type torque emphasized. Accordingly, a soft inplane hingeless rotor with three tube and the pitch links located at the leading edge and the blades is tested at advance ratios as high as 0.55 and at shaft trailing edge of the torque tube. For analysis, the outboard main I angles as high as 20 degrees. The 1.62 m model rotor is untrimmed blade and the torque tube are assumed to be made of metals with an essentially unrestricted tilt of the tip path plane. In (isotroic materials), and the flexbeam is assumed to be a laminated combination with lag natural frequencies, collective pitch settings I-section beam. The energy expressions and governing differential and flap-lag coupling parameters, the data base comprises nearly equations are derived for moderately large deflections. Quasisteady 1200 test points (damping and frequency) in forward flight and strip theory is used to evaluate the aerodynamic forces and the 200 test points in hover. By computerized symbolic manipulation, unsteady aerodynamic effects are introduced approximately through dynamic inflow modeling. Numerical results are calculated for the a linear analytical model is developed in substall to predict stability margins with mode identificaton. To help explain the correlation selected various hingeless and bearingless blade configurations, between theory and data it also predicts substall and stall regions categorized as symmetric and antisymmetric, based on the lay-up of the rotor disk from equilibrium values. The correlation shows in the laminates. For both the hingeless and bearingless blade bc?h ?he s!:eng:h:s 8nd wealifie~~esof iiie iiieuiy in subsiaii. cofiiiguiaiioiis, sysiemaiic siuaies are made to identify the Author importance of the stiffness coupling terms on blade stability with changing fibers orientation and for different configurations. Dissert. Abstr. N87-10064# Army Aviation Systems Command, St. Louis, Mo. SUMMARY OF ARTIFICIAL AND NATURAL ICING TESTS CONDUCTED ON US ARMY AIRCRAFT FROM 1974 TO 1985 Final Report H. W. CHAMBERS and J. Y. ADAMS Jul. 1986 223 p 1 (Contract DTFA03-80-A-00199) I N87- 10061 # Aeronautical Research Labs., Melbourne (FAA/CT-85/26; TR-85-F-11) Avail: NTlS HC AlO/MF A01 I (Australia). The U.S. Army Aviation Systems Command conducts , ANALYSIS OF THE VIBRATION OF THE INPUT BEVEL PINION airworthiness qualification testing on aircraft under artificial and I IN RAN WESSEX HELICOPTER MAIN ROTOR GEARBOX natural icing conditions. A JCH-47C helicopter with a Helicopter WAK143 PRIOR TO FAILURE Icing Spray System (HISS) installed is used for generating a i P. D. MCFADDEN Sep. 1985 51 p simulated natural icing environment. The artificial icing tests are (ARL-AERO-PROP-R-169; AR-004-049) Avail: NTlS HC A04/MF followed by natural icing tests to assure a wide variety of flight A01 conditions are tested and to verify artificial icing test results. Also I Following the crash of an RAN Wessex helicopter caused by discussed is the use of deice and anti-ice systems; the impact of the catastrophic fatigue failure of the input spiral bevel pinion in ice accretion and shedding characteristics, performance the main rotor gearbox, routine recordings of the gearbox vibration considerations, stability and control, and vibration characteristics; have been analyzed by ARL. It has been shown that conventional and the cloud parameters measurement equipment and test aircraft spectral analysis of the vibration is unable to give adequate instrumentation used for documenting test data. The test indication of the presence of the fatigue crack but that an alternative methodology and requirements used for qualifying aircraft for flight technique of vibration analysis called signal averaging can give into icing conditions, instrumentation, and special eauipment are ~Z~insC! !hs CKX!: 42 !XX:S Ssfoia kkie. Efihaficafi-iaciiui iiie summarized, and the details for tests conducted are contained in signal average using a computer enables detection of the crack the references. The report documents in part 14 years of U.S. as early as 103 hours before failure. Author Army experience in conducting inflight aircraft icing tests and is provided to the FAA under interagency agreement in the preparation of manuals and other documents relative to the certification of civil aircraft as appropriate. Author

N87-10062# National Aeronautical Lab., Bangalore (India). N87-10065’# General Dynamics Corp., Fort Worth, Tex. Systems Engineering Div. DESIGN AND FABRICATION OF THE NASA DECOUPLER 1 PYLON FOR THE F-16 AIRCRAFT Final Report, Jan. 1982 I EFFECTS OF FLAP POSITION ON LONGITUDINAL - PARAMETERS OF HFB-320 Aug. 1983 R. \’. dATEGAONKAR arid S. SAiAKFiiSiiiiA Feb. IYU~: // p J. U. CLAYTON, R. L. HALLER, and J. M. HASSLER, JR. Jan. (NAL-TM-SE-8602) Avail: NTIS HC AO5/MF A01 1985 204 p Parameter estimation results to evaluate the effects of small (Contract NAS1-16879) changes in flap position on the longitudinal derivatives of HFB-320 (NASA-CR-172354; NAS 1.26:172354) Avail: NTlS HC AlO/MF aircraft are presented. Maximum likelihood estimation procedure A01 CSCLOlC 1 is used for kinematic consistency checking of flight test data and The NASA Decoupler Pylon is a passive means of suppressing also for estimation of aerodynamic derivatives. Linear and nonlinear wing-store flutter. The feasibility of demonstrating this concept on models are used to estimate dimensional and non-dimensional the F-16 aircraft was established through model wind tunnel tests derivatives directly. Author and analyses. As a result of these tests and studies a ship set of I 25 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

Decoupler Pylons was designed and fabricated for a flight test associated with same. These subsystems are discussed in terms demonstration on the F-16 aircraft. Basic design criteria were of basic design guidelines, interaction with other helicopter developed during the analysis study pertaining to pylon pitch subsystems, system trade studies, and first order analytical design stiff ness, alignment system requirements, and damping approaches adequate for preliminary design purposes. Author requirements. A design was developed which utilized an electrical motor for the pylon alignment system. The design uses a four N87-10069# Pisa Univ. (Italy). Dipt. de Energetica. pin, two link pivot design which results in a remote pivot located ENGINE-TRANSMISSION-STRUCTURAL AIRFRAME MEMBERS at the center of gravity of the store when the store is in the COMPATIBILITY aligned position. The pitch spring was fabricated from a tapered D. DIN1 In AGARD Engine-Airframe Integration for Rotorcraft 33 constant stress cantilevered beam. The pylon has the same p May 1986 external lines as the existing production pylon and is designed to Avail: NTlS HC AO8/MF A01 use a MAU-12 ejection rack which is the same as the one used The sophistication of current turbine-powered helicopters have with the production pylon. The detailed design and fabrication introduced many new problems involving the compatibility of the was supported with a complete ground test of the pylon prior to major multidegree of freedom systems: rotor, control, airframe, shipment to NASA. Author drive train, and powerplant. The solutions to the various problems were obtained from the application of basic engineering principles. N87-10066# Boeing Military Airplane Development, Seattle, Engine installation is described in the helicopter, particularly the Wash. A-129, i.e., power plant attachment, oil cooling system, engine VULNERABILITY METHODOLOGY AND PROTECTIVE control and monitoring, electric starting system, location of MEASURES FOR AIRCRAFT FIRE AND EXPLOSION HAZARDS. components and leading particulars, and anti-vibration devices. VOLUME 3: ON-BOARD INERT GAS GENERATOR SYSTEM The design of the transmission system is dictated by the (OBIGGS) STUDIES. PART 1: OBIGGS GROUND configuration of the helicopter. An aerodynamic analysis is PERFORMANCE TESTS Final Report, Aug. 1982 - Jul. 1984 conducted on the helicopter mission in order to obtain complete C. L. ANDERSON Jan. 1986 200 p spectra of the rotor loads and moments as well as the maneuver (Contract F33615-78-C-2063) loads and transient for maximum transmission reliability. The (AD-A167357; D180-28862-VOL-3-PT-1; application of fiber reinforced resin composites to selected areas AFWAL-TR-85-2060-V-3-PT-1) Avail: NTlS HC AO9/MF A01 of the helicopter drive system will produce weight and cost savings CSCL 01c as well as improvements in reliability and safety. These Results of performance evaluation tests of a molecular sieve improvements which were demonstrated in airframe applications (MSIGG) and a permeable membrane inert gas generator (PMIGG) can be transferred to structural components in the drive system, system for airplane fuel tank inerting are presented. The IGG with high weight saving. Author units, sized to inert the wing tanks of a KC-135, and the test facilities at Wright-Patterson AFB are described. Steady state performance envelope, endurance, and KC-135 mission simulation N87-10070# Rolls-Royce Ltd., Watford (England). tests are conducted. The weight and fuel penalties of the MSIGG IMPACT OF IPS AND IRS CONFIGURATIONS ON ENGINE and the PMIGG installed in a KC-135 are compared. GRA INSTALLATION DESIGN J. R. BALLARD In AGARD Engine-Airframe Integration for N87-10067# Advisory Group for Aerospace Research and Rotorcraft 14 p May 1986 Development, Neuilly-Sur-Seine (France). Propulsion and Avail: NTlS HC AOB/MF A01 Energetics Panel. Helicopters operate in a variety of roles many of which pose ENGINE-AIRFRAME INTEGRATION FOR ROTORCRAFT severe problems to the engine due to ingestion of sand, ice, salt, Loughton, England May 1986 154 p Lecture Series held in and other foreign objects. It is possible to design a compromise St. Louis, Mo., 2-3 Jun. 1986, in Rome, Italy, 9-10 Jun. 1986, and engine intake which combats all these hazards to a limited degree. in Marseilles, France, 12-13 Jun. 1986 Engine design should be coordinated with both engine and airframe (AGARD-LS-148; ISBN-92-835-1529-3) Avail: NTlS HC A08/MF mounted separator performance characteristics to ensure that A0 1 optimized designs can be offered to customers with very different Topics addressed include numerous airframe integration aspects operational requirements. A design method was outlined which relating to rotor wing aircraft. Various areas of engine airframe would allow the erosion reduction characteristics of engine and integration, including the impact of advanced engine design airframe Intake Protection System (IPS) designs to be taken into variables to specific propulsion subsystems, will be discussed. account during engine design. The Infrared Suppression (IRS) Other propulsion system integration aspects such as designs can be integrated with IPS scavenge requirements to engine/rotor/drive system torsional stability and transient response produce a low signature engine installation. B.G. will also be discussed. Additional areas considering the specification and qualification requirements of propulsion items will be N87-10071# Army Aviation Systems Command, St. Louis, Mo. examined. Engineering Dept. ENGINE-AIRFRAME INTEGRATION FOR ROTORCRAFT: N87- 10068# Sikorsky Aircraft, Stratford, Conn. Propulsion COMPONENT SPECIFICATIONS AND QUALIFICATION Systems. J. A. RAY In AGARD Engine-Airframe Integration for Rotorcraft ENGlN E-AIR FRAME INTEGRATION CONSIDERATIONS FOR lop May 1986 PRELIMINARY AIR VEHICLE PERFORMANCE ANALYSIS Avail: NTlS HC A08/MF A01 R. C. FRAWLEY and H. N. SHOHET In AGARD Engine-Airframe Both past history and current principles associated with Integration for Rotorcraft 21 p May 1986 engine-airframe integration for rotorcraft are provided as related Avail: NTlS HC A08/MF A01 to component specification requirements and their individual Helicopter enginelairframe integration issues are examined from qualification assurance. Component specification and qualification a preliminary design viewpoint with emphasis on those areas where requirements have tended to be generic and standardized without an impact on aircraft power available and/or aerodynamics is consideration of actual usage, location, and exposure. As such, involved. The areas of the helicopter propulsion system specifically overall requirements have had problems of being overly restrictive addressed include: the engine air induction system considering in some cases and not exacting enough in others. The current aerodynamic performance, anti-icing, exhaust gas re-ingestion, and trend in tailoring for specific applications as well as insuring system inlet particle separation; the engine exhaust system considering performance requirements by conducting early component/bench aerodynamic performance, engine compartment cooling, and level tests will be discussed along with lessons learned from past exhaust ejector system; and lastly, engine bleed air extraction as efforts. Components involved in the overall engine-airframe it relates to environmental control systems and the trade studies integration effort such as pumps, fans, starter, valves, sensors,

26 infrared suppressors, inlet particle separators, and fuel cells will N87-10858 Virginia Polytechnic Inst. and State Univ., be discussed. Author Blacksburg. ENERGY MANAGEMENT OF 3-DIMENSIONAL MINIMUM-TIME INTERCEPT Ph.D. Thesis N87-10072# Garrett Turbine Engine Co., Phoenix, Ariz. H. G. VISSER 1985 124 p INFLUENCE OF ENGINE VARIABLES ON FUTURE HELICOPTER Avail: Univ. Microfilms Order No. DA8605366 A real-time computer algorithm to control and optimize aircraft SYSTEMS flight profiles is described and applied to a three-dimensional M. L. EARLY and P. K. ZEINER ln AGARD Engine-Airframe minimum-time intercept mission. The proposed scheme has roots Integration for Rotorcraft 24 p May 1986 in two well-known techniques; singular perturbations and Avail: NTlS HC A08/MF A01 neighboring-optimal guidance. Use of singular-perturbation ideas A helicopter system defined for the year 2000 must make numerous assumptions about future technology and system is made in terms of the assumed trajectory-family structure. A heading/energy family of prestored point-mass-model state-Euler requirements. In the case of propulsion system options, the required solutions is used as the baseline in this scheme. The next step is to 15 year development cycle (from preliminary engine cycle 5 to generate a near-optimal guidance law that will transfer the aircraft studies through engine development to production) complicates to the vicinity of this reference family. The control commands fed the process of optimizing the engine/rotorcraft system. A to the autopilot consist of the reference controls plus correction well-disciplined approach to engine definiton studies to yield engine terms which are linear combinations of the altitude and path-angle candidates that best use emerging technologies is illustrated. An deviations from reference values, weighted by a set of precalculated advanced, single-engine helicopter requiring a 2000-shp powerplant gains. In this respect the proposed scheme resembles was used a a base-line vehicle. Both simple and heat-recovery neighboring-optimal guidance. However, in contrast to the cycles were evaluated, using trade factors to establish engine neighboring-optimal guidance scheme, the reference control and effects on helicopter direct operating cost (DOC), the optimization parameter assumed for purposes of illustration. Author state variables as well as the feedback gains are stored as functions of energy and heading in the present approach. A detailed description of the feedback laws and of some of the mathematical tools used to construct the controller is presented. Numerical N87-10073# Societe Nationale lndustrielle Aerospatiale, examples, comparing open-loop optimal and approximate feedback Marignane (France). Helicopter Div. solutions for a sample high-performance fighter, illustrate the HELICOPTER AIR INTAKE PROTECTION SYSTEMS attractiveness of the guidance scheme. Optimal three-dimensional Y. EE!ASER?/E??E an:! P. CAB!?!? i't~ ASARE Eiigiii&iiifiaiiig flight in the presence of a terrain limit is studied in some detail. Integration foi Rotoieiaft 20 p May 1986 Dissert. Abstr. Avail: NTlS HC AOB/MF A01 The primary function of an engine air intake is to provide air N87-10859'# General Dynamics Corp., Fort Worth, Tex. supply with minimum pressure drop and distortion. Static or dynamic DESIGN AND FABRICATION OF THE NASA DECOUPLER air intakes are selected according to both the type of engine air PYLON FOR THE F-16 AIRCRAFT, ADDENDUM 2 Final Report, intake and the helicopter missions envisaged. The other function Jan. - Oct. 1984 of an engine air intake is to protect the engine against foreign J. D. CLAYTON, R. L. HALLER, and J. M. HASSLER, JR. Feb. object ingestion, sand erosion, and the various atmospheric agents 1985 99 p such as rain, snow, and ice. As a general rule, the air intake (Contract NASl-16879) protection systems are all the more penalizing as regards (NASA-CR-172494; NAS 1.26:172494) Avail: NTlS HC A05/MF performance as they are efficient. The best tradeoff is therefore A01 CSCLOlC between both functions. The dimensioning and test criteria for The decoupler pylons which were originally designed and each function of an air intake is examined and then the various assembled with bushings in the pivot joints were retrofitted with development stages are given for the SA 366 G1 Dauphin air roller bearings. This retrofit, the supporting analyses and the fixture intake as an example. Author tests of the modified pylons are reported in this document. The loads and stress analysis was directed toward the redesigned parts which were the pylon links and pins. The loads and stress N87-10074# Army Aviation Systems Command, St. Louis, Mo. analysis indicates that the pylons with the bearing installation have Engineering Dept. reduced capacity with respect to the bushing design. Fixture tests ENGINE-AIRFRAME INTEGRATION FOR ROTORCRAFT: of the redesigned pylons were conducted in the GD/FW facility. SYSTEM SPECIFICATIONS AND QUALIFICATION Breakout friction tests and vibration tests were conducted. The J. A. RAY ln AGARD Engine-Airframe Integration for Rotorcraft tests show that the joint friction is approximately one-half the lop May 1986 level with hezrings 2s mmpared I:.+ the bushing ins:o!!a:ion. The Avail: NTlS HC A08/MF A01 vibration test data was used to tune the pylon mathematical Both past history and current principles associated with simulation and this revised pylon simulation was used to recompute engine-airframe integration for rotorcraft are provided as related airplane modes of vibration. These computed modes of vibration to system specification requirements and the resulting qualification were used in complete airplane symmetric and antisymmetric flutter assurance. System specification requirements have evolved and aeroservoelastic analyses. Author through periods of few details and lack of definitive requirements to the opposite extreme of exacting details and extremely specific N87-10860'# General Dynamics Corp., Fort Worth, Tex. requirements. The current trend of performance related DESIGN AND FABRICATION OF THE NASA DECOUPLER specifications is intended to enhance the freedom of design while PYLON FOR THE F-16 AIRCRAFT, ADDENDUM 1 Final Report, meeting the essential mission related requirements. This has Aug. - Oct. 1983 required a revised qualification program effort to insure essential J. D. CLAYTON ;Ind R L. H.A.LLEF! kn. !E5 ?C! p requirements are being met throughout the develpment effort. (Contract NASl-16879) Lessons learned in this evaluation as well as current methods will (NASA-CR-172355; NAS 1.26:172355) Avail: NTlS HC A04/MF be discussed for overall engine-airframe integration system A01 CSCL 01C requirement. In particular, system qualification will be addressed The results of the final analyses which were conducted using for such areas as adverse environment requirements for icing, a revised structural simulation of the Decoupler Pylon are reported cold/hot temperatures and sand/dust; mission related requirements in this addendum. The simulation incorporates the previously for engine response, infrared signature reduction, and published results of ground tests performed on the flight Decoupler crashworthiness; and basic engine integration requirements for Pylons mounted in a test fixture at General Dynamic's Fort Worth torsional stability, vibration, and cooling. Author facility. The analyses show that the Decoupler Pylon will suppress

27 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE wing-store flutter for the GBU-8 flight test stores configuration on equations of motion governing flight. After this step aerodynamics an F-16 airplane. The feasibility of carrying a B-61 on the pylons model identification can take place. In flight simulation, the opposite is also investigated with the conclusion that the pylons would process occurs. From the available aerodynamic and engine model need to be modified in order to demonstrate flutter suppression. specific forces and angular accelerations can be computed. Then The results of a ground vibration test performed on the 114 scale the equations of motion can be integrated in order to determine F-16 flutter model and a wind tunnel test with this model and a the flight path. Consequently there is a strong similarity in the model Decoupler Pylon are given. Author way flight test results are processed and reduced in order to obtain aerodynamic information and the way simulations are N87-10861’# National Aeronautics and Space Administration. executed using a given model. ESA Ames Research Center, Moffett Field, Calif. X-29A LONGITUDINAL AND DIRECTIONAL FORCE AND MOMENT SUPPLEMENTAL TRANSONIC WIND TUNNEL TEST RESULTS A. H. BOWERS Aug. 1984 289 p (NASA-TM-85909; H-1257; NAS 1.1 5:85909) Avail: NTlS HC AIRCRAFT INSTRUMENTATION Al3/MF A01 CSCL 01C Aerodynamic data from NASA Ames Research Center’s 11-Foot Includes cockpit and cabin display devices; and flight instruments. Transonic Wind Tunnel are plotted for the 1/8-scale X-29A forward-swept wing aircraft model. Eleven configurations were tested to provide supplemental data to investigate single surface A87-10933 failure modes, complex nonlinearities, and model buildup. These LONG RANGE E-O RECONNAISSANCE SYSTEM AND FLIGHT data can be used for control system refinements, pilot training, TEST RESULTS flight planning, and aerodynamic model validation. Data are F. PALAZZO (Fairchild Weston Systems, Inc., Imaging Systems presented as corrected wind tunnel data without analysis to Div., Syosset, NY) IN: Airborne reconnaissance IX; Proceedings document results that are being used for the aerodynamic model. of the Meeting, San Diego, CA, August 20, 21, 1985 . Bellingham, Author WA, Society of Photo-Optical Instrumentation Engineers, 1985, p. 13-17. N87-10862*# Kansas Univ. Center for Research, Inc., Beginning 1977, Fairchild Weston Systems developed a Lawrence. long-range E-0 Reconnaissance System. The goal was to develop PARAMETRIC ANALYSIS OF A PASSIVE CYCLIC CONTROL and experimentally demonstrate the capabilities of a sensor using DEVICE FOR HELICOPTERS Charge Coupled Device (CCD) Time Delay and Integration (TDI) H. KUMAGAI Oct. 1984 135 p technology. It was shown to be possible to electronically subtract (Contract NCC2-175) the background, due to haze, from each picture element (PIXEL) (NASA-CR-166608; NAS 1.26:166608; KU-FRL-568-1) Avail: and amplify the remaining differences to enhance the reproduced NTlS HC A07/MF A01 CSCL 01C scene. The large image signal-to-noise ratio required was obtained A parametric study of a passive device which provides a cyclic through the use of a TDI. An optically contiguous focal plane, longitudinal control moment for a helicopter rotor was performed. built up of TDI chips, was integrated into a long focal length It utilizes a rotor blade tip which is structurally decoupled from camera, which was testflown. This paper describes the experiment the blade inboard section. This rotor configuration is generally and the results obtained. Author called the Free-Tip Rotor. A two dimensional numerical model was used to review the Constant Lift Tip Rotor, a predecessor of AW-10934 the current configuration, and then the same model was applied THE KS147A LOROP CAMERA SYSTEM to the Passive Cyclic Control Device. The Constant Lift Tip was 0. OSTREM and J. G. HUGHES (Recon/Optical, Inc., CAI Div., proven to have the ability to suppress the vibratory lift loading on Barrington, IL) IN: Airborne reconnaissance IX; Proceedings of the tip around the azimuth and to eliminate a significant negative the Meeting, San Diego, CA, August 20, 21. 1985 . Bellingham, lift peak on the advancing tip. The Passive Cyclic Control Device WA, Society of Photo-Optical Instrumentation Engineers, 1985, p. showed a once-per-revolutionlift oscillation with a large amplitude, 18-25. while minimizing the higher harmonic terms of the lift oscillation. Attention is given to the design of the Long Range Oblique This once-per-revolution oscillation results in the cyclic moment Photography (‘LOROP’) KS-147A camera carried by the RF-5E to trim the rotor longitudinally. A rotor performance analysis was aircraft in a nose installation. Key design features are a performed by a three dimensional numerical model. It indicated seven-element, 1676-mm focal length fl5.6 lens, a two-axis that the vortices shed from the junction between the tip and the gyrostabilized scan head, a passive isolation mount, a closed loop inboard section has a strong influence on the tip, and it may autocollimation autofocus, and a self-contained thermal system. severely limit the tip performance. It was also shown that the In-flight resolution in excess of 70 Ip/mm is achievable; the Free-Tip allows the inboard section to have a larger twist, which camera’s modular design allows repackaging in numerous other results in a better performance. Author configurations, as called for by the aircraft in question. O.C.

N87-10863# National Aerospace Lab., Amsterdam (Netherlands). A87-10935 Flight Div. INTEGRATION OF THE KS-147A LOROP INTO THE RF-BE CORRELATION BETWEEN FLIGHT SIMULATION AND R. L. WALKE and J. P. DUDA (Northrop Corp., Aircraft Div., PROCESSING OF FLIGHT TESTS BASED ON INERTIAL Hawthorne, CA) IN: Airborne reconnaissance IX; Proceedings of MEASUREMENTS the Meeting, San Diego, CA, August 20, 21, 1985 . Bellingham, A. M. H. NIEUWPOORT, J. H. BREEMAN, L. J. J. ERKELENS, WA, Society of Photo-Optical Instrumentation Engineers, 1985, p. and P. J. J. VANDERGEEST 19 Jul. 1985 23 p Presented at 26-33. AGARD Flight Mechanics Panel Symposium of Flight Simulation, The RF-5E single-cockpit tactical reconnaissance aircraft was Cambridge, England, 3 Sep. - 3 Oct. 1985 designed in 1981 to carry a variety of low, medium and high (NLR-MP-850584; 68667020; ETN-86-98493) Avail: NTlS HC altitude sensor configurations mounted internally on AO2/MF A01 interchangeable pallets. Presently, the high resolution, 66-inch focal Flight tests and simulations were performed using conventional length, 1/56. KSOl47A LOROP (Long Range Oblique Photographic) and dynamic techniques based on inertial measurements. The use camera is being incorporated by the aircraft, to provide a standoff of inertial sensors in flight testing implies that specific forces and capability exceeding 30 nautical miles. This paper addresses the body rates are determined which are directly employed in the design process employed to mechanically and electrically integrate flight path reconstruction procedure. This procedure uses the the KS-147A into the RF-SE, while maintainig the concept of

28 06 AIRCRAFT INSTRUMENTATION

interchangeable sensor pallets. The paper will include a discussion the ability of sensors to track the image motion at their focal of the design requirements imposed on the suppliers of the plane; this application has proven to be especially effective in the KS-147A camera and the Photographic Sensor Control System, case of oblique-pointing sensors. O.C. as well as a detailed design discussion of the structural, electrical and environmental control components necessary to install the camera in the aircraft. Finally, the planned ground and flight test A87-10950 activities are presented. Author RECONNAISSANCE INTERFACE - THE NEAR REAL TIME IS NOW A87-10936 W. G. FISHELL (Fairchild Communications and Electronics Co., OPERATIONAL USAGE OF THE KS-147A (LOROP) IN THE Germantown, MD) IN: Airborne reconnaissance IX; Proceedings RF-SE of the Meeting, San Diego, CA, August 20, 21, 1985 . Bellingham, D. G. BURRIS (Northrop Corp., Aircraft Div., Hawthorne, CA) IN: WA, Society of Photo-Optical Instrumentation Engineers, 1985. p. Airborne reconnaissance IX; Proceedings of the Meeting, San 165-172. Diego. CA. August 20, 21, 1985 . Bellingham, WA, Society of Reconnaissance interface products over the past ten years Photo-Optical Instrumentation Engineers, 1985, p. 34-41. have focused on the interface between the aircraft, including its The KS-147A Long Range Oblique Photographic (LOROP) cockpit, and the peculiar interfaces required to control and annotate Camera is being developed to satisfy an operational tactical information in tactical reconnaissance sensors. Compared to older reconnaissance requirement. This paper addresses that specific systems like those in the RF-4 which contains multiple boxes and requirement and the capabilities of the KS-147A in the Northrop analog interfaces, today’s reconnaissance interface is much simpler RFdE to meet that need. Particular emphasis is given to specific in a single, highly reliable unit, controlled by its own programmable flight planning parameters, maintenance preparations and ground microprocessor. Furthermore, recent engineering development requirements of the camera system, inflight considerations and systems have demonstrated how this single, programmable unit typical mission profiles. The paper concludes with an assessment can be adapted to a variety of sensors, including the recent mix of the RF-5EIKS-147A Camera system to provide an effective and match requirement for electro optics and/or film type of tactical reconnaissance standoff capability. Author sensors. This presentation provides a sampling of some of the many reconnaissance interface functions this unit can and does A87-10937 perform. Author EFFECTS OF ATMOSPHERE ON OBLIQUE RECONNAISSANCE P. N. SLATER (Arizona, University. Tucson! IN: Airborne .r.- ALIA- .I not- ILL IL~ reconnaissance IX; Proceedings of the Meeting, San Diegn, CA, EXPERT SYSTEMS FOR AIDING COMBAT PILOTS August 20, 21, 1985 . Bellingham, WA, Society of Photo-Optical B. M. ANDERSON, C. MCNULTY, and G. S. LYSTAD (Texas Instrumentation Engineers, 1985, p. 42-46. refs Instruments, Inc., Dallas) IN: Annual Aerospace Applications of This paper shows how atmospheric scattering can affect the Artificial Intelligence Conference, lst, Dayton, OH, September signal-to-noise ratio, the spatial resolution, and the noise equivalent 16-19, 1985, Proceedings . Dayton, OH, AAAIC Secretariat, 1985, reflectance difference of an oblique CCD reconnaissance camera p. 54-60. refs operating in the pushbroom mode. An example is given that The emergency procedures expert system (EPES) for handling compares these quantities for 75 and 85 deg oblique imagery emergency situations for tactical aircraft pilots is described. EPES with the near-nadir case for a flat, horizontal target. The effect of is activated when the aircraft is damaged and loses capabilities, imaging the target at various azimuths with respect to the sun is thereby initiating mission replanning. The system must provide examined. Author advice as to whether or not to pursue a particular course of action, and must resolve conflicts between goals. The latter arise when A87-10939 opposing actions are specified by multiple emergencies. SINGLE OR DUAL POD CONCEPTS FOR TACTICAL Performance of the system is illustrated by means of sample F-16 RECONNAISSANCE missions. In one scenario, the EPES must provide advice on correct J. I. BERGGREN (FFV, Aero Engineering Div., Linkoping, actions when the canopy is lost and the towershaft fails, situations Sweden) IN: Airborne reconnaissance IX; Proceedings of the which require recommended airspeeds of a maximum of 180 and Meeting, San Diego, CA, August 20, 21, 1985 . Bellingham, WA, a minimum of 250 kt, ;espectively. The prosvision of mission options Society of Photo-Optical Instrumentation Engineers, 1985, p. for sequential failures on a deepstrike mission is also described, 52-58. and a block diagram is provided of the multiple expert system An evaluation is made of the optimum tactical reconnaissance architecture. M.S.K. system meeting both high speed/low level penetration missions and standoff missions; single and dual pod system configurations 8:~ccnsidc;ed kit :ac;icel, iechfiiiai, ai J economic viewpoinis. ABi-i2218# Although a dual pod system allows LCCs to be minimized in cases THE ASPRO PARALLEL INFERENCE ENGINE (A REAL-TIME where tactical requirements allow a minimization of the number of EXPERT SYSTEM) standoff sensors, the single pod system allows the selection of B. R. REED, J. H. SMIT. and R. W. LOTT (Goodyear Aerospace both standoff and penetration modes during a reconnaissance Corp., Digital Systems Dept., Akron, OH) IN: Annual Aerospace mission. O.C. Applications of Artificial Intelligence Conference, 1st, Dayton, OH, September 16-19, 1985, Proceedings . Dayton, OH, AAAIC A87-10943 Secretariat, 1985, p. 248-259. RECONNAISSANCE AND THE MICROPROCESSOR Design and functional of the Aspro flight qualified parallel ’ J. L. CAPTAIN (Teledyne Ryan Aeronautical, San Diego, CA) and processor are outlined. A block diagram is provided for the five R. A. STURZ (Recon/Optical Inc., Pacific El0 Center, La Jolla, functional subsystems of the Aspro architecture. The distribution CAI IN: Airborne mcnnnzissrmre !X; !?cceedizgc o! !he Meding, o! :ha :hiss tipas of memory is ikeiiijd, aioriy wiih regisier, , San Diego, CA, August 20, 21, 1985 . Bellingham, WA, Society of arithmetic and array control functions, and the array hardware, Photo-Optical Instrumentation Engineers, 1985, p. 85-88. which contains 1792 processing alements. Aspro weights 37 Ib, A comprehensive evaluation is made of the cumulative impact occupies a volume of 0.44 cu ft and consumes 200 W power. of microprocessors’ application to reconnaissance systems, which Software such as Assembler, FORTRAN, a Librarian, and a Linker began with the use of solid state logic devices for control and have been developed for Aspro and will also work in the VAX timing functions and proceeded, beginning in the mid-l97Os, to environment. Techniques be which Aspro is employed as a real-time involve microprocessor control of internal sensor-related functions, expert system complete with parallel inferencing are described. Attention is given to a typical state-of-the-art microprocessor Aspro is to be installed on the E-2C early warning aircraft to application in forward motion compensation devices, which regulate perform tracking command and control functions. M.S.K.

29 06 AIRCRAFT INSTRUMENTATION

A87-12677# N87-10075# Deutsche Forschungs- und Versuchsanstalt fuer LASER AIRBORNE DEPTH SOUNDING IN AUSTRALIA Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer M. F. PENNY, R. H. ABBOT, D. M. PHILLIPS, B. BILLARD. D. Flugfuehrung. REES (Department of Defence, Electronics Research Laboratory, PROCEEDINGS OF THE 13TH SYMPOSIUM ON AIRCRAFT Adelaide, Australia) et al. IN: Navigation and environment; INTEGRATED DATA SYSTEMS Proceedings of the Fifth International Congress, Tokyo, Japan, Feb. 1986 586 p Symposium held in Hamburg, West Germany, October 1-5. 1985 . Tokyo, Japan Institute of Navigation, 1986, p. 17-19 Sep. 1985 9-17. (DFVLR-MITT-86-04;ISSN-0176-7739; ETN-86-98176) Avail: A laser airborne depth sounder (LADS) designed for a NTIS HC A25/MF A01; DFVLR, Cologne, West Germany, DM hydrographic survey in Australian coastal waters is examined. The 150 sounding pattern for LADS is 270 m wide and the spacing between The application of aircraft integrated data systems for monitoring adjacent soundings is 10 m. LADS contains a Nd:YAG laser, and and recording flight and aircraft condition and performance, to the infrared and green laser pulses are utilized to calculate depth. improve safety, reliability, and economy of aircraft operation was The aircraft and ground analysis equipment are described. LADS discussed. was utilized to profile the Great Barrier Reef; to investigate the ESA effects of ocean swell and layered turbid water off Fremantle in West Australia; and in South Australia gulf waters, the accuracy and depth error analysis were studied. The role of water turbidity in depth sounding performance is discussed. The LADS system must generate an accurate surface model, based on the observed N87-10076# Messerschmitt-Boelkow-Blohm G.m.b.H., Hamburg reflections from the sea surface by the IR and green receiving (West Germany). channels, in order to calculate depth, and depth estimations for A-310 AIRCRAFT INTEGRATED DATA SYSTEMS (AIDS) LADS are based on the propagation times of the subsurface beam DESIGN PHILOSOPHY and the velocity of light in water. The fixing of the sounder position, H. KALBE ln DFVLR Proceedings of the 13th Symposium on the navigation of LADS, and the on-ground analysis of the data Aircraft Integrated Data Systems p 9-28 Feb. 1986 are considered. I.F. Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, DM 150 The A-310 air data system customer requirements and integration problems were examined. The repercussions of these A87-12688# aspects on the system architecture are discussed, and a solution THE EVOLUTION OF AIR TRANSPORT AIRCRAFT FLIGHT which covers the problems is presented. ESA DECK J. CASTIES (Thomson-CSF, Paris, France) IN: Navigation and environment; Proceedings of the Fifth International Congress, Tokyo, Japan, October 1-5, 1985 . Tokyo, Japan Institute of Navigation, 1986, p. 171-179. N87-10077# Hamilton Standard, Farmington, Conn. Improvements in aircraft flight decks made possible with AIRCRAFT INTEGRATED DATA SYSTEMS (AIDS): EVOLUTION advances in shadow-mask color tube and large scale integration AND REVOLUTION technology are described. The capabilities and data provided by C. F. BUKOWSKI ln DFVLR Proceedings of the 13th Symposium the electronic flight instrument system, which is composed of a on Aircraft Integrated Data Systems p 29-45 Feb. 1986 primary flight display and a navigation display, and the electronic Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, centralized aircraft monitor display system, which consists of two DM 150 CRT display units, are examined. The implementation of an Development of aircraft integrated data systems (AIDS) from improved electronic instrument system and a side stick/fly-by-wire 1970 to the present is discussed. User desirable features are aircraft control system into the A 320 is discussed. I.F. considered. Present and perceived AIDS integration/relationships with other aircraft systems, and the tools and resources necessary for implementation are treated. ESA

A87-12694 DATA PROCESSING AND CALIBRATION FOR AN AIRBORNE SCATTEROMETER R. BERNARD, D. VIDAL-MADJAR, F. BAUDIN, and G. LAURENT N87-10078# Nord-Micro Elektronic Feinmechanik G.m.b.H., (Centre de Recherches en Physique de I’Environnement Terrestre Frankfort (West Germany). et Planetaire, Issy-les-Moulineaux, France) IEEE Transactions MODERN AIRCRAFT INTEGRATED DATA SYSTEMS (AIDS) on Geoscience and Remote Sensing (ISSN 0196-2892). vol. GE-24, TECHNOLOGY EXEMPLIFIED ON THE A-320 Sept. 1986, p. 709-716. CNES-ESA-supported research. refs D. WALDMANN and K. WNUK ln DFVLR Proceedings of the The ERASME-radar system has been designed to be easily 13th Symposium on Aircraft Integrated Data Systems p 47-74 mounted on small helicopters or aircraft. As it is used for research Feb. 1986 investigations on radar remote-sensing applications, it has to be Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, well calibrated in every configuration, both absolutely and relatively DM 150 for comparisons at different points of the swath. The data The hardware design, software organization, and data processing, which allows for antenna pattern correction and for processing of the flight data interface unit (FDIU) and the data flight parameters correction (pitch, roll, altitude), is described as management unit (DMU) for the A-320 aircraft are described. The an introduction to the calibration procedures: internal calibration, DMU and FDIU provide high flexibility and expansion capability to external calibration on corner reflectors for absolute calibration keep pace with airline requirements. For example, the units are (within 1 dB), and a statistical approach which uses experimental equipped with EEPROM’s of size 8 k by 8, but footprint, wiring, data itself and analyzes the correlation between the processed and memory management are provided for memory chips with data and recorded flight parameters. This method provides a way higher capacity. In the DMU prewired spare board slots are provided to check or adjust calibration for specific flight configurations, and for future air data system applications as there is the supervision allows a relative accuracy of better than 0.5 dB for data comparison of the structural health of aircraft components. Technologies like within the radar swath. Such a method can be used to calibrate gate arrays and surface mounted devices are used so that the any airborne or spaceborne scatterometer when accurate antenna equipment shows important reduction in physical size, weight, and measurement is not feasible. Author power consumption compared to the predecessor. ESA

30 06 AIRCRAFT INSTRUMENTATION

N87-10079# Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn a Central Data Unit (CDU) and programmed through a removable (West Germany). electrical module plugged in the CDU. A mass memory stores the EXPERIENCE WITH THE ONBOARD CHECKOUT AND data for immediate use after the flight. Outputs of DMU are to MONITORING SYSTEM (OCAMS) OF A MILITARY AIRCRAFT printer and digital AIDS recorder. Long term analysis reports for RESULTING IMPROVEMENTS AND THE CONSEQUENCE FOR engine monitoring are engine cruise, and engine take-off trend FUTURE DESIGN reports as well as auxiliary power unit report. Short term analysis K. NUMBERGER and K. PROBST In DFVLR Proceedings of the is done through engine real time, engine gas path limit exceedance, 13th Symposium on Aircraft Integrated Data Systems p 75-92 engine stall, engine divergence, engine start, and engine Feb. 1986 mechanical limit exceedance report. A prehistory of the data is Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, printed or recorded after the report of the exceeded limit. ESA DM 150 The Onboard Checkout and Monitoring System was designed to provide for test and diagnosis of defects to avionic and certain N87-10083# British Airways, Heathrow (England). nonavionic equipments. Experience showed what could be CHOOSING AIRCRAFT INTEGRATED DATA SYSTEMS (AIDS) improved. Engine and structure monitoring must be improved, still ARCHITECTURE SUITABLE FOR ENGINE HEALTH and it was realized more information would be useful to store, MONITORING (EHM) ON FUTURE GENERATION ENGINES that the high sensitivity of the BIT detected also very transient D. E. FOXLEY In DFVLR Proceedings of the 13 Symposium on faults. In order to cover these problems, the data acquisition unit Aircraft Integrated Data Systems p 161-176 Feb. 1986 of the crash recorder system will be extended with an engine and Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, structural life monitoring system. Using the opportunity of DM 150 introducing a data communication bus into the avionic system, Airborne engine monitoring system architectures including air facilities for data collection, correlation, and event monitoring will and ground elements are assessed. It is very desirable to perform be initiated. Based on this the principal structure of the monitoring the analysis function in the airborne computer, but it requires and test systems of future aircraft can be designed. ESA considerable effort to achieve, and it is probably unrealistic to expect an engine manufacturer to provide such a system to a N87-10080# Plessey Co. Ltd., Havant (England). diversity of airlines, many of whom do not wish to utilize it. What INTEGRATED MONITORING SYSTEMS FOR TACTICAL is important is that what they provide should not preclude AIRCRAFT incorporating it in an airborne computer. The approach for the P. J. D. BRISTOWE and R. L. THOMPSON In DFVLR Proceedings V2500 engine is to provide only an analysis module and a plot oi the i3ih Syiiiposiim e:: Aircraf! !n!egn_!ec! Data Systems p mnduk, leaving the airline to embed these into their system, 93-124 Feb. 1986 whether it be a mainframe or dedicated one. Important interfaces Avail: NTlS HC A25/MF A01; DFVLR. Cologne, West Germany, such as file structure have not yet been defined. Even so, it is DM 150 clear their system will need a mainframe or large minicomputer to An aircraft integrated monitoring system integrating previously run on, so perhaps the ultimate in transportable software will have stand alone avionic boxes in military aircraft, with consequent to wait for another generation of equipment. ESA savings in equipment cost, weight, and volume is described. The crash-protected accident data recorder combines digital data

1 recordings with 3 channels of voice. The data acquisition and processing unit combines the acquisition of accident data, and N87-10084# Deutsche Lufthansa A.G.. Hamburg (West Germany). engine and structural parameters with the real-time implementation Power Plant Engineering Div. of engine and structural algorithms to determine component fatigue LUFTHANSA’S AIRCRAFT INTEGRATED DATA SYSTEMS life. Other facilities include parameter exceedance monitoring, trend (AIDS) BASED A-310 ENGINE CONDITION MONITORING SYSTEM: PROGRESS ACHIEVED BETWEEN THE 12TH AND I monitoring and event snapshots with simple latched displays for maintenance purposes. ESA 13TH AIDS SYMPOSIUMS G. DIENGER In DFVLR Proceedings of the 13th Symposium on N87-10081# Civil Aviation Authority, Redhill (England). Aircraft Integrated Data Systems p 177-205 Feb. 1986 Airworthiness Div. Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, APPLICATION OF OPERATIONAL FLIGHT RECORDING TO DM 150 HELICOPTERS The A-31 0 aircraft integrated data system which acquires, H. D. RUBEN In DFVLR Proceedings of the 13th Symposium monitors, records, and prints data for aircraft/engine condition on Aircraft Integrated Data Systems p 125-138 Feb. 1986 monitoring and trouble shooting is discussed. The data is fed-in Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, and processed on-line by a comprehensive ground based diagnosis DM 150 information system. Operational experience based on regular and Operational flight data recording tests were carried usiily ad hoc system reports, and development status are described. helicopters. One helicopter carries a data recorder running E8A continuously, and a second helicopter of a different type is being similarly equipped. The objective of the exercise is to establish real time utilization of the helicopter so that design assumptions, N87-10086# Technische Hochschule, Aachen (West Germany). I particularly with respect to fatigue, can be validated. It is too early Dept. of Aerospace Engineering. to draw conclusions. ESA WIND SHEAR MEASUREMENT ON BOARD A MORANE 893 H. NELLES In DFVLR Proceedings of the 13th Symposium on N87-10082# Societe de Fabrication d’lnstruments de Mesure, Aircraft Integrated Data Systems p 235-266 Feb. 1986 t Massy (France). Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, t THE AIRBORNE INTEGRATED DATA SYSTEM (AIDS) FOR THE DM 150 AIRBUS A-310 ENGINE C6NDiTiON iviGNiTGiiiiiG Tn investigate wind shear during flight, a pneumatic sensing C. JOUVENOT ln DFVLR Proceedings of the 13th Symposium device was developed and installed on board a single engine on Aircraft Integrated Data Systems p 139-160 Feb. 1986 light aircraft. The device measures the difference in total pressure ,I Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, between two positions vertically displaced from the airplane. The 1 DM 150 mass flow rate created by the difference in pressure is measured I The A-310 aircraft integrated data system (AIDS) is developed by a hot-wire probe. The signal of this probe is a function of the I in a single six modular common unit combining flight data wind shear. Results collected by this system compare favorably acquisition unit and Data Management Unit (DMU) with no possible with those of a ground based sensing system and of a research interaction between the two units. The system is controlled through aircraft. ESA I

31 N87-10087# Deutsche Forschungs- und Versuchsanstalt fuer N87-10091# Eurocontrol Agency, Brussels (Belgium). Luft- und Raumfahrt, Brunswick (West Germany). THE AWGROUND TRANSFER OF AIRCRAFT INTEGRATED Forschungszentrum. DATA SYSTEMS (AIDS) FOR AIR TRAFFIC CONTROL (ATC) PERFORMANCE MONITORING OF SENSORS IN HIGH PURPOSES PRESENT EXPERIMENTS AND POSSIBLE FUTURE RELIABLE FLIGHT CONTROL SYSTEMS USING INTENTIONS DETERMINISTIC OBSERVERS M. E. COX In DFVLR Proceedings of the 13th Symposium on N. STUCKENBERG In its Proceedings of the 13th Symposium Aircraft Integrated Data Systems p 349-372 Feb. 1986 on Aircraft Integrated Data Systems p 261-284 Feb. 1986 Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, DM 150 DM 150 Use of SSR Mode S links for air traffic control (ATC) is The output vector of a sensor set used in a flight control discussed. Experiments indicate that data derived from aircraft in system of a transport aircraft was monitored by an observer. Since real time via the Mode S link can be very helpful in ATC related the observer includes a mathematical model of the aircraft, dynamic applications, including the enhancement of short-term deviations in the sensor performance due to failures can be meteorological forecast data. The work shows that digital aircraft detected. This idea is used in a sensor concept which achieves a can provide a range of potentially useful parameters that can be high reliability with less sensor hardware than conventional accessed via an ARlNC 429 data port associated with the flight redundancy concepts. Flight test results show the feasibility of data acquisition system. It is believed that European ATC system the concept under the constraint of disturbances and model requirements for aircraft data will expand rapidly with the inaccuracies. ESA implementation of Mode S, in the mid 1990’s. By that date, however, there are likely to be applications which have yet to be evaluated to support dependent surveillance and approach and departure control. There may also be air/ground data channels, e.g., ACARS, ASDAR plus other satellite systems stemming from the PROSAT N87-10088# Flight Data Co., London (England). experiments. ESA THE IMPACT OF FLIGHT DATA ON AN AIRLINE: A CASE STUDY P. WALLER In DFVLR Proceedings of the 13th Symposium on Aircraft Integrated Data Systems p 285-307 Feb. 1986 Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, DM 150 A medium size airline acquired a flight data recorder playback N87-10092# Trans World Airlines, Inc., Kansas City, Mo. and analysis facility for three aircraft fleets. The effects on the AIRLINE DATA ACQUISITION IN AN ACARS ENVIRONMENT user department are examined in relation to system accessibility. T. R. DEGNER In DFVLR Proceedings of te 13th Symposium Analysis program developments resulting from the user becoming on Aircraft Integrated Data Systems p 373-390 Feb. 1986 more aware of the possibilities are presented. Comparisons Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, between this new user airline and others that have exploited flight DM 150 recorder data over many years are drawn. ESA The data acquisition system on TWA aircraft is described. It combines a tape-based system and an ACARS-based system. The tape-based system is plagued by low reliability, large data volume, long delays between events and analysis, and poor flexibility. An N87-10089# Sundstrand Data Control, Inc., Redmond, Wash. ACARS only system will allow removal of the airborne tape Avionics System Div. recorders and ground tape transmission units. The ACARS-based DATA RECOVERY TECHNIQUES, AN UPDATE system allows real-time on-line data collection. This provides the G. S. L. BENN In DFVLR Proceedings of the 13th Symposium user with a high-integrity system with great flexibility. The system on Aircraft Integrated Data Systems p 309-328 Feb. 1986 design is being driven by user needs and the expected benefits. Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, ESA DM 150 Innovations in flight data recovery techniques are reviewed. Data presentation methods designed to offer the data specialist rapid aces and greater understanding of data are included. Hardware used to manipulate data, and use of personal computers to access and examine flight recorded information are described. Techniques resulting from improvements in flight and ground N87-10093# National Transportation Safety Board, Washington, hardware and application software are proposed, including the D. C. use of artificial intelligence and three dimensional display FLIGHT RECORDERS NEW US REGULATIONS AND NEW technology. ESA INTERNATIONAL CIVIL AVIATION ORGANIZATION (ICAO) STANDARDS C. A. ROBERTS and D. R. GROSS1 In DFVLR Proceedings of the 13th Symposium on Aircraft Integrated Data Systems p 391-41 7 Feb. 1986 N87-10090# Deutsche Lufthansa Aktiengesellschaft. Frankfurt Avail: NTlS HC A25/MF A01; DFVLR. Cologne, West Germany, am Main (West Germany). Abteilung Flugbetriebstechnik. DM 150 SOFTWARE FOR FLIGHT RECORDER DATA PROCESSING On January 8, 1985, the U.S. Federal Aviation Administration DEVELOPED BY LUFTHANSA issued a Notice of Proposed Rulemaking regarding improved flight H. A. KAISER In DFVLR Proceedings of the 13th Symposium recorders. It called for: expanded-parameter digital recorders on on Aircraft Integrated Data Systems p 329-348 Feb. 1986 new air carrier airplanes manufactured 2 yr after the rule is adopted, Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, regardless of the date of original type certificate; digital recorders DM 150 to replace foil recorders within 2 yr of the rule change, and 5 Computer software to evaluate flight recorder data is described. additional parameters within 7 yr; and voice recorders on certain Software to transcribe raw data to magnetic tape, to perform quality commuter airplanes. The International Civil Aviation Organization checks of the recorded data, to evaluate selectable parameters (ICAO) recorder amendments were adopted in March 1985, and and their subsequent graphical display, and to display aircraft became effective on July 29, 1985. The upgraded US. recorder movement three dimensionally is available. ESA requirements and the ICAO amendments are assessed. ESA

32 06 AIRCRAFT INSTRUMENTATION

N87-10094# Lear Siegler, Inc., Grand Rapids, Mich. Instrument N87-10097# Naval Air Test Center, Patuxent River, Md. Div. UNITED STATES NAVY - CANADIAN FORCES SOLID STATE DATA COMPRESSION TECHNIQUES FOR MULTIFUNCTION FLIGHT DATA RECORDERKRASH POSITION LOCATOR FLIGHT DATA RECORDERS EXPERIMENT ON THE 8-720 CONTROLLED IMPACT F. SAGGIO, 111 In DFVLR Proceedings of the 13th Symposium DEMONSTRATION on Aircraft Integrated Data Systems p 41 9-443 Feb. 1986 D. M. WATTERS In DFVLR Proceedings of the 13th Symposium Avail: NTlS HC A25/MF A01; DFVLR, Cologne. West Germany, on Aircraft Integrated Data Systems p 509-530 Feb. 1986 DM 150 Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, Basic principles of data compression systems are discussed, DM 150 emphasizing multifunction flight data recording applications. The A solid state flight data recorderlcrash position locator categorization of data compression methods is discussed, and (SSFDR/CPL) was developed, configured for and crash tested in reversible and irreversible compression techniques are described. the FAA/NASA Boeing B-720. The SSFDRICPL system contains Algorithm selection and development, and optimization of data nonvolatile memory and a CPL radio beacon airfoil. The CPLIRBA labeling and formatting techniques are considered. Data provides a selectable overt and covert locating capability. The decompression principles are introduced, and multifunction flight SSFDWCPL was ejected from the B-720 upon crash and radiated data recording applications which embody data compression the overt emergency signals for 5 to 10 sec before silenced by a techniques are highlighted. By using the spare computing capability fuel induced short in the transmitter. The SSFDR was subjected of the onboard microprocessor, more functions may be added, or to the worst case fuel fire from the crash, but no data were lost. new applications may be possible. ESA ESA

N87-10095# Fairchild Weston Systems, Inc., Sarasota, Fla. THE FAIRCHILD CVDR: A NEW COMBINATION VOICE AND DATA RECORDER H. F. NAPFEL and B. J. HAWKINS In DFVLR Proceedings of the 13th Symposium on Aircraft Integrated Data Systems p 445-474 N87-10098# Deutsche Forschungs- und Versuchsanstalt fuer Feb. 1986 Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer Avail: NTlS HC A25/MF AO1; DFVLR, Cologne, West Germany, Flugmechanik. DM_. 150 COMPARATIVE EVALUATION OF REDUNDANT FLIGHT DATA I he Faircniid cockpit voice and data recorder deveioped to RECORDED BY A DIGITAL AIRCRAFT INTEGRATED DATA meet the SAE Aerospace Standard 8039 for Type 3 recorders for SYSTEM RECORDER (DAR) ON BOARD AN AIRBUS A-310 general aviation is described. It is designed to meet or exceed AIRCRAFT TSO C-51a and DO160B environment and survivability 0. WEBER and G. ROSENAU In its Proceedings of the 13th requirements. It records data and voice simultaneously. Calibration Symposium on Aircraft Integrated Data Systems p 531-567 Feb. data and time are stored on recording medium for life for later 1986 data verification. Microprocessor circuitry provides exceptional Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, flexibility and reliability of data storage. It features automatic test DM 150 of voice recorder function at power-up and continuous verification Flight data collected during two A-310 flights by a digital AIDS of flight data recording function during operation. No manual testing recorder were analyzed. Sixty-four standard data words and 137 is required. It uses internal GMT for datalvoice correlation. The data words which could be selected from the ARlNC 429 bus as tape stops automatically after detection of nonflying status. It has desired were recorded per second. From a flight-mechanical complete ARlNC 542 and ARlNC 542 expanded parameter standpoint, redundant data from different sources are analyzed compatibility. It records last 33 min of each flight for voice and for take-off, landing, and en route. The characteristics of the data, and last 8 hr of excerpted data for previous flight standard A-310 AIDS are compared to those of the A-300 AIDS correlation. ESA and the potential benefit of additional data to a reliable reconstruction of a flight is shown. The reconstruction of the motion state of the aircraft is more complete than with the older equipment; N87-10096# Federal Aviation Administration, Atlantic City, N.J. a completely satisfactory reconstruction of the flying motion, THE BOEING B 720 AIRCRAFT CONTROLLED IMPACT however, is not possible in cases where measured values of the DEMONSTRATION (CID): FLIGHT DATA RECORDER/COCKPIT flow angles are required. ESA VOICE RECORDER EXPERIMENT L. J. GARODZ and G. G. LEROY (Lockheed Aircraft Service, Inc., Ontario, Calif 1 /n DFVLR Proceedinon nf the 13th Symposium on Aircraft Integrated Data Systems p 475-507 Feb. 1986 (Contract DOT/FAA/CT-85/28P) Avail: NTlS HC A25/MF A01; DFVLR, Cologne, West Germany, DM 150 A controlled crash was used to evaluate the adequacy and N87-10099# Technische Univ., Brunswick (West Germany). usefulness of state-of-the-art Flight Data Recorder (FDR) and INVESTIGATIONS ON A DIGITAL BIT SYNCHRONIZER FOR A Cockpit Voice Recorder (CVR) recorded data in postcrash aircraft DETAILED FLIGHT DATA RECOVERY accident investigation and analysis, particularly in human H. D. VONLAUE In DFVLR Proceedings of the 13th Symposium factors/crashworthiness. The crash shows a gross design on Aircraft Integrated Data Systems p 569-584 Feb. 1986 deficiency in TSO-C51 a specification, regarding recorder Avail: NTlS HC A25/MF AO1; DFVLR, Cologne, West Germany, performance when recording data under relatively low g-loads, DM 150 well within human tolerance limits, which may be experienced in A flight recorder digital bit synchronizer to process (with cross unusual attitude flight. The experiment reveals that sampling rates correlation considering several bits) even distorted signals as occur are too low for certain aircraft performance parameter signals, after aircraft crashes, was developed. Reliability of the recovered particularly aircraft linear accelerations and pitch and roll attitude. bits was measured. Results show that bit synchronization based Either the sampling rates should be increased or the attitude on correlation permits a more reliable bit recognition in critical information pitch rate and roll-rate signals should be recorded. It cases than previous procedures. One disadvantage of the is proved that a separate power supply (battery pack and static procedure is the large amount of calculation involved. The hardware inverter) can properly operate an FDAU and three DFDR’s even developed, however, achieves a processing speed of 20 k baud. after basic aircraft electrical power is no longer available. ESA ESA

33 06 AIRCRAFT INSTRUMENTATION

N87-10864’# National Aeronautics and Space Administration. 07 Langley Research Center, Hampton, Va. GROUND-BASED TIME-GUIDANCE ALGORITHM FOR AIRCRAFT PROPULSION AND POWER CONTROL OF AIRPLANES IN A I IME-METERED AIR TRAFFIC CONTROL ENVIRONMENT A PILOTED SIMULATION STUDY C. E. KNOX and N. IMBERT (Office National d’Etudes et de Includes prime propulsion systems and systems components, e.g., Recherches Aerospatiales, Toulouse, France) Nov. 1986 36 p gas turbine engines and compressors; and onboa rd auxiliary power (NASA-TP-2616; L-16116; NAS 1.60:2616) Avail: NTlS HC plants for aircraft. AO3/MF A01 CSCL 01D The rapidly increasing costs of flight operations and the requirement for increasedfuel conservation have made it necessary A87-10899 to develop more efficient ways to operate airplanes and to control NATURAL FREQUENCY ANALYSIS OF COMPRESSOR ROTOR air traffic for arrivals and departures to the terminal area. One BLADES concept of controlling arrival traffic through time metering has S. K. SANE, C. S. GURUJEE. A. R. MALPANI, and C. M. P. been jointly studied and evaluated by NASA and ONERA/CERT FERNANDES (Indian Institute of Technology, Bombay, India) IN: in piloted simulation tests. From time errors attained at checkpoints, Finite elements in computational mechanics - FEICOM ’85; airspeed and heading commands issued by air traffic control were Proceedings of the International Conference, Bombay, India, computed by a time-guidance algorithm for the pilot to follow that December 2-6. 1985. Volume 2 . Oxford, Pergamon Press, 1985, would cause the airplane to cross a metering fix at a preassigned p. 645-654. refs time. These tests resulted in the simulated airplane crossing a The vibrational response of a transonic compressor rotor blade metering fix with a mean time error of 1.0 sec and a standard with a high degree of twist is investigated analytically and deviation of 16.7 sec when the time-metering algorithm was used. experimentally. A first-stage formulation of the blade geometry is With mismodeled winds representing the unknown in wind-aloft derived; FEM analysis is performed using eight-node isoparametric forecasts and modeling form, the mean time error attained when elements, 12-node isoparametric elements, and two modified crossing the metering fix was increased and the standard deviation versions of the helicoidal element of Walker (1978); and the remained approximately the same. The subject pilots reported that analytical results are compared with values obtained experimentally the airspeed and heading commands computed in the guidance (by clamping the blade rigidly in a root-clamp block and exciting it concept were easy to follow and did not increase their work load electromagnetically) in a table. It is found that the 12-node above normal levels. Author isoparametric element has the best convergence and gives the most accurate results, whereas the helicoidal elements fail to converge satisfactorily. T.K.

A87-12965# A TEST RESEARCH FOR IMPROVING THE PERFORMANCE OF V-TYPE FLAMEHOLDER USED IN AN AFTERBURNER H. TAN and J. WANG (Nanjing Aeronautical Institute. People’s Republic of China) Journal of Engineering Thermophysics, vol. 7, May 1986, p. 179-181. In Chinese, with abstract in English. This paper describes the V-type flameholder with gaps used in a jet engine afterburner. It was found from model tests that the recovery coefficient of total pressure increased, the quenching limit for poor fuel was extended, and the combustion efficiency improved. The unit fuel consumption rate decreased about 1 percent under full-scale engine tests. Author

N87-10865# Air Force Human Resources Lab., Brooks AFB, Tex. LOW-COST AVIONICS SIMULATION FOR AIRCREW TRAINING Interim Report, Jan. 1984 - Jun. 1985 B. J. EDWARDS Jul. 1986 26 p A87-13008# (AD-A169198; AFHRL-TR-85-38) Avail: NTlS HC AO3/MF A01 CONDITION MONITORING OF LARGE COMMERCIAL CSCL 09E TURBOFAN ENGINES This report documents the evaluation of a low-cost B. VAN DE WATER (Qantas Airways, Ltd., Sydney, Australia) IN: microcomputer based avionics system trainer as a substitute for Joint National Symposium on the Influence of Aviation on aircraft-based training. The training was provided to C-141 pilots Engineering and the Future of Aeronautics in Australia, Melbourne, to train them to perform several procedural tasks associated with Australia, August 8, 9. 1985, Preprints . Barton, Australia/Brookfield, the operation of the Fuel Savings Advisory System (FSAS). This VT, Institution of Engineers/Brookfield Publishing Co., 1985, p. system is being retrofitted on C-141 and C5A aircraft. Operational 33, 34. aircrews must be trained to operate the FSAS in order to be A development history and current status evaluation are mission qualified. This report documents an experiment in which presented for large, high bypass turbofan engine condition trainees learned to operate the FSAS, either in the aircraft or via monitoring techniques that assess compressor erosion and the low-cost alternative. Results showed both groups required the damage, combustor and turbine oxidation, and roller bearing same amount of training time to learn to perform the tasks. Thus, spalling and fatigue. Attention is given to borescopes, magnetic the low-cost alternative was shown to be an effective substitute chip detectors, SEM. and vibration monitoring. Effective condition for the aircraft for training the FSAS tasks. A cost analysis monitoring has been instrumental in the prevention of in-flight comparing the two training methods shows the low-cost trainer is failures and the maximization of MTBFs. A tabulation of reasons capable of avoiding more than 8 million dollars in training costs if for major disassembly and heavy maintenance in a major airline’s it is employed to train current C-141 and C-5A aircrews in the JT9D and RB211 engines over the course of 1984 is presented. FSAS tasks. GRA O.C.

34 08 AIRCRAFT STABILITY AND CONTROL

N87-10085# Philips ZentrallaboratoriumG.m.b.H., Hamburg (West N87-10868# Rolls-Royce Ltd., Derby (England). Germany). ENGINE PERFORMANCE MONITORING FOR AIRLINES A SYSTEM THEORETICAL BASED METHOD FOR MODULE J. A. CHANTRY 6 Mar. 1986 15 p FAILURE DIAGNOSTIC OF TURBINE ENGINES (PNR-90305; ETN-86-98016) Avail: NTIS HC A02/MF A01 M. ROESNICK In DFVLR Proceedings of the 13th Symposium The costs and benefits of engine performance monitoring are on Aircraft Integrated Data Systems p 207-233 Feb. 1986 recalled. The Rolls Royce engine monitoring system is described. Avail: NTIS HC A25/MF A01; DFVLR, Cologne, West Germany, ESA DM 150 A method for module failure diagnostic of turbine engines based N87-11200*# National Aeronautics and Space Administration. on gas path analysis is presented. An effective failure diagnostic Lewis Research Center, Cleveland, Ohio. of all main modules is possible by a system theoretical based AEROTHERMAL MODELING PROGRAM, PHASE 2 method. The basis of the method is a reduced model, gained by E. J. MULARZ ln its Turbine Engine Hot Section Technology, a degree of observability. The application of the state estimation 1984 4 p Oct. 1984 and analytical redundancy guarantees that the failure diagnostic Avail: NTlS HC A17/MF A01 CSCL 21 E method is applicable even if the measurements are disturbed by The accuracy and utility of current aerothermal models for gas random and systematic errors. Simulation results of the JT9D turbine combustors must be improved. Three areas of concern engine are presented. ESA are identified: improved numerical methods for turbulent viscous recirculating flows: flow interaction; and fuel injector-air swirl characterization. Progress in each area is summarized. B.G. N87-10100'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. N87-11207'# General Electric Co., Fairfield, Conn. Aircraft RESPONSE OF A SMALL-TURBOSHAFT-ENGINE Engine Business Group. COMPRESSION SYSTEM TO INLET TEMPERATURE COMPONENT SPECIFIC MODELING DISTORTION M. ROBERTS ln NASA. Lewis Research Center Turbine Engine T. J. BIESIADNY, G. A. KLANN (Army Research and Technology L. Hot Section Technology, 1984 12 p Oct. 1984 Labs., Cleveland, Ohio.), and J. K. LllTLE Sep. 1984 28 p Avail: NTlS HC A17/MF A01 CSCL 21E (NASA-TM-83765;E-21 98; NAS 1.26:83765; Modern jet engine design imposes extremely high loadings and USAAVSCOM-TR-84-C-13) Avail: NTlS HC AOWMF A01 CSCL temperatures on hot section components. A series of 21 E interdisciplinary modeling and analysis techniques which were An experimental investigation was conducted into the response s=ecia!iz& :n ;s&&== :hie& Qr>+'-.;;;+,-nmnr.nio"irr , . . iromk.,-_...--- me+.-.---. oi a smaii-turboshaii-e~~n~CC-FT~~CI~T: Z;C:Z: :z :::z~;-::::G ourner linings, noiiow air-cooiea turbine blades, and air-cooled ana transient inlet temperature distortions. Transient temperature turbine vanes) were developed and verified. These techniques will ramps range from less than 100 K/sec to above 610 K/sec and incorporate data as well as theoretical methods from many diverse generated instantaneous temperatures to 420 K above ambient. areas, including cycle and performance analysis, heat transfer Steady-state temperature distortion levels were limited by the analysis, linear and nonlinear stress analysis, and mission analysis. engine hardware temperature list. Simple analysis of the Building on the proven techniques already available in these fields, steady-state distortion data indicated that a particle separator at the new methods developed will be integrated to predict the engine inlet permitted higher levels of temperature distortion temperature, deformation, stress, and strain histories throughout a before onset of compressor surge than would be expected without complete flight mission. B.G. the separator. Author

N87-10866'# Lockheed-Georgia Co., Marietta. PTA TEST BED AIRCRAFT ENGINE INLET MODEL TEST REPORT, REVISED J. P. HANCOCK May 1985 81 p AIRCRAFT STABILITY AND CONTROL (Contract NAS3-24339) (NASA-CR-174845; NAS 1.26:174845; LG85ER0012-REV) Avail: Includes aircraft handling qualities; piloting; flight controls; and NTlS HC A05/MF A01 CSCL 21E autopilots. The inlet duct test for the Propfan Testbed Assessment (PTA) program was completed in November 1984. The basic test duct was designed using the Lockheed QUADPAN computational code. A87-10519*# Princeton Univ., N. J. Test objectives were to experimentally evaluate, modify as required, OPTIMAL FLIGHT PATHS THROUGH MICROBURST WIND and eventually verify satisfactory performance as well as PROFILES A,,,+lr~n~;~.-.-.-.---+:h:l:&. 11--- A 1-1-8 -I-.. -.,J,,s- uvlIlwrrrlullll)r. IIIEia.JuI=u LULII ~ICS,IJI~ recovery ior R. F. STENGEL (Princeton University, NJ) and M. L. PSlAKl the basic duct was 0.993 with no swirl and 0.989 for inflow with a Journal of Aircraft (ISSN 0021-8669),vol. 23, Aug. 1986, p. 629-635. 30 degree simulated swirl angle. This compared to a predicted FAA-supported research. Previously cited in issue 21, p. 3052, recovery of 0.979 with no swirl. Measured circumferential distortion Accession no. A85-43872. refs with swirl, based on a least-square curve fit of the data, was (Contract NGL-31-001-252) 0.204 compared to a maximum allowable value of 0.550. Other measured distortion parameters did as well or better relative to A87-11369 their respective maximum allowable values. The basic duct MANEUVER OPTIMIZATION IN THE CASE OF COMBAT configuration with no refinements is recommended for the PTA AIRCRAFT [ MANOEVEROPTIMIERUNG VON inlet as a minimum cost installation. Author KAMPFFLUGZEUGEN] E. BERGER, W. GRIMM, P. HILTMANN, K. MORITZ. and K. WELL .,e--.-*,.- ,# 1-01 WOW ft Ruiis-iioycs iid., Derioy (England). (DFVLR, lnstitut fuer Dynamik der Flugsysteme, Oberpfaffenhofen, FUTURE AERO-ENGINE CONTROL SYSTEMS, WHY FADEC? West Germany) DFVLR-Nachrichten(ISSN 001 1-4901), July 1986, COST, DESIGN CYCLE TIMESCALE, RELIABILITY, WEIGHT p. 16-19. In German. AND SIZE TARGETS Digital and manned air combat simulation studies have shown H. F. CANTWELL 14 Feb. 1986 13 p that pilots have not enough time to concentrate on essential (PNR-90298; ETN-86-98015) Avail: NTIS HC A02/MF A01 decisions, because the various tasks related to target detection, The requirements for a civil aircraft gas turbine control system target recognition, and weapon and aircraft control demand too are summarized. The advantages of full authority digital electronic much of their attention. The present article is concerned with the control over hydromechanical concepts are outlined. ESA possibility to help the pilot on the basis of the calculation of optimal

35 08 AIRCRAFT STABILITY AND CONTROL or suboptimal real-time control operations, taking into account the for this survey. Not all of the information obtained was consistent, feasibility of an employment in a scenario simulation performed particularly with respect to technology readiness. The synthesis of with the aid of an onboard computer. It has been found that the information into the perception of the state-of-technology is calculations involved in the determination of the precise optimal presented. Author solutions require often too much time. For this reason, use is made of approximate and suboptimal solutions. Attention is given to two approaches which require a system reduction procedure, time-minimal and range-maximal trajectories in the vertical plane, a three-dimensional mission involving the interception of a target N87-10103'# National Aeronautics and Space Administration. in minimal time, and pursuit and escape maneuvers in the case Ames Research Center, Moffett Field, Calif. G.R. of two aircraft equipped with missiles. IN-FLIGHT TOTAL FORCES, MOMENTS AND STATIC AEROELASTIC CHARACTERISTICS OF AN OBLIQUE-WING A87-12082 RESEARCH AIRPLANE NON-LINEAR STABILITY ANALYSIS OF AIRCRAFT AT HIGH R. E. C'JRRY and A. G. SIM Oct. 1984 30 p ANGLES OF AlTACK (NASA-TP-2224; H-1181; NAS 1.60:2224) Avail: NTlS HC N. SRI NAMACHCHIVAYA (Illinois, University, Urbana) and S. T. A03lMF A01 CSCL 01C ARIARATNAM (Waterloo, University, Canada) International A low-speed flight investigation has provided total force and Journal of Non-Linear Mechanics (ISSN 0020-7462), vol. 21, no. moment coefficients and aeroelastic effects for the AD-1 3, 1986, p. 217-228. refs oblique-wing research airplane. The results were interpreted and The pitching motion of an aircraft in steady flight at a high compared with predictions that were based on wind tunnel data. angle of at!ack is investigated analytically in the framework of An assessment has been made of the aeroelastic wing bending nonlinear stability theory. The approximations adopted by Hui and design criteria. Lateral-directional trim requirements caused by Tobak (1984) are applied, but the method of averages is used asymmetry were determined. At angles of attack near stall, flow instead of the Fredholm-alternative approach. Both Hopf and visualization indicated viscous flow separation and spanwise vortex degenerate Hopf (DH) bifurcations are predicted, and two periodic flow. These effects were also apparent in the force and moment DH paths with different frequencies are identified and characterized. data. Author The DH paths are found to be either both stable or both unstable. Numerical results are presented in graphs for the DH regime of both flat-plate and double-wedge airfoils, and the bifurcating periodic motion in the double-wedge case is shown to be unstable. T.K. N87-10870'# National Aeronautics and Space Administration. A87-12268 Langley Research Center, Hampton, Va. THE LATERAL DYNAMIC STABILITY AND CONTROL OF A INTERFERENCE EFFECTS OF THRUST REVERSING ON LARGE RECEIVER AIRCRAFT DURING AIR-TO-AIR HORIZONTAL TAIL EFFECTIVENESS OF TWIN-ENGINE REFUELLING FIGHTER AIRCRAFT AT MACH NUMBERS FROM 0.15 TO 0.90 A. W. BLOY, P. J. LAMONT, H. A. ABU-ASSAF, and K. A. M. ALI F. J. CAPONE and M. L. MASON Oct. 1984 104 p (Manchester, Victoria University, England) Aeronautical Journal (NASA-TP-2350; L-15811; NAS 1.60:2350) Avail: NTlS HC (ISSN 0001-9240), vol. 90, June-July 1986. p. 237-243. refs AO6/MF A01 CSCL 01C The lateral dynamic stability and control of a large receiver An investigation was conducted in the Langley 16 foot Transonic aircraft was considered during air-to-air refuelling. A simple Tunnel to determine the interference effects of thrust reversing aerodynamic model was developed in order to determine the on horizontal tail effectiveness of a twin engine, general research aerodynamic forces and moments acting on the receiver aircraft fighter model at approach and in-flight speeds. Twin vertical tails due to the tanker aircraft's vortex field. These forces and moments at three longitudinal locations were tested at a cant angle of 0 were then expressed in derivative form and included in the deg. One configuration was also tested at a cant angle of 20 linearized equations of motion. Solution of these equations revealed deg. Two nonaxisymmetric nozzle reverser concepts were studied. a divergent oscillation, characteristic of air-to-air refueling and Test data were obtained at Mach numbers of 0.15, 0.60, and consisting mainly of bank and sideways displacements. An 0.90 and at angles of attack from -3 to 9 deg. Nozzle pressure approximation to this mode, which highlights two important ratios varied from jet off to 7.0, depending upon Mach number. At aerodynamic derivatives was made. The values of these derivatives landing approach speed (Mach number 0.1 5), thrust reverser depend mainly on the vertical separation between the tanker and operation usually resulted in large variations (up to 70% increase) receiver aircraft and the ratio of the tanker-to-receiver aircraft wing in horizontal tail effectiveness as nozzle pressure ratio was varied spans. In flight, it appears that the pilot controls the divergent at zero angle of attack or as angle of attack was varied at constant mode by frequent alternate movements of the ailerons. Author nozzle pressure ratio. There was always a decrease in effectiveness at Mach numbers of 0.60 and 0.90 as a result of reverser N87-10102'# Textron, Inc., Irvine, Calif. operation. Author TECHNOLOGY REVIEW OF FLIGHT CRUCIAL FLIGHT CONTROL SYSTEMS (APPLICATION OF OPTICAL TECHNOLOGY) H. A. REDIESS and E. C. BUCKLEY Sep. 1984 48 p (Contract NASl-17403) N87-10871'# National Aeronautics and Space Administration. (NASA-(33-172332;NAS 1.26:172332) Avail: NTlS HC AO3/MF Ames Research Center, Moffett Field, Calif. A01 CSCLOlC FLIGHT-DETERMINED AERODYNAMIC DERIVATIVES OF THE The survery covers the various optical elements that are AD-1 OBLIQUE-WING RESEARCH AIRPLANE considered in a fly-by-light flight control system including optical A. G. SIM and R. E. CURRY Oct. 1984 40 p sensors and transducers, optical data links, so-called optical (NASA-TP-2222; H-1179; NAS 1.60:2222) Avail: NTlS HC actuators, and opticaVelectro-optical processing. It also addresses AO3/MF A01 CSCL 01C airframe installation, maintenance, and repair issues. Rather than The AD-1 is a variable-sweep oblique-wing research airplane an in-depth treatment of optical technology, the survey that exhibits unconventional stability and control characteristics. concentrates on technology readiness and the potential In this report, flight-determined and predicted stability and control advantagesldisadvantages of applying the technology. The derivatives for the AD-1 airplane are compared. The predictions information was assembeld from open literature, personal are based on both wind tunnel and computational results. A final interviews, and responses to a questionnaire distributed specifically best estimate of derivatives is presented. Author

36 09 RESEARCH AND SUPPORT FACILITIES (AIR)

N87-10872# Societe Nationale lndustrielle Aerospatiale, Toulouse N87-10104# National Aeronautical Lab., Bangalore (India). (France). Div. Avions. Aerodynamics Div. EFFICIENCY OF VARIOUS CONTROL SURFACES IN STEADY TUNNEL INTERFERENCE FROM PRESSURE MEASUREMENTS AND UNSTEADY FLOW ON CONTROL SURFACES R. BARREAU, R. DESTUYNDER, and G. ANDERS 2 Sep. 1985 R. GOPINATH Aug. 1983 27 p 71 p In FRENCH Presented at 61st AGARD Meeting on (AE-TM-8-83) Avail: NTlS HC A03/MF A01 Structures and Materials Panel Subcommittee on Aeroelasticity, Interference due to tunnel walls has been evaluated from Oberammergau, West Germany, 9 Sep. 1985 Original language pressure measurements on controi surfaces by a method due to document was announced as A86-24633 Capelier, Chevallier and Bouniod, using a simple exponential type (SNIAS-861-111-101;JBE/SB-443.524/85; ETN-86-97139) of decay for extrapolating the pressure coefficients beyond the Avail: NTlS HC A04/MF A01 measurement stations to + or - infinity, respectively. The method The three dimensional subsonic and transonic flow steady and has been validated against data presented at an AGARD meeting unsteady effects associated with the action of control surfaces on Transonic Test Sections at NASA Langley, which discussed (ailerons, flaps and spoilers) were studied experimentallyto improve the merits of the various methods for evaluating the wall the efficiency of aircraft control design. Large models provided interference from pressure measurements. Author with a large number of measuring points were tested in a wind tunnel. It is shown that the design of control surfaces applied to supercritical wings requires precautions. ESA N87-10874 British Aerospace Aircraft Group, Warton (England). Wind Tunnel Dept. PRACTICAL EVALUATION OF WALL PRESSURE SIGNATURE CORRECTION METHODS IN THE 2.7M X 2.1M LOW SPEED 09 WIND TUNNEL J. G. PROCTOR Jan. 1986 69 p (BAE-ARG-204; ETN-86-97943) Avail: Issuing Activity RESEARCH AND SUPPORT FACILITIES (AIR) The chart and matrix methods of using wind tunnel wall static pressure distribution to calculate blockage and lift effects were Includes airports, hangars and runways; aircraft repair and overhaul assessed using pressure rails in a low speed wind tunnel. The facilities; wind tunnels; shock tubes; and aircraft engine test iIse of !apped rsjls fer press~remeasuremen! p:=ves siitable. stanas. Overall sampling rate is slow. Corrections for two larger flat plates agree well with published data. Conventional techniques are, however, as good. Compared to the standard, aircraft-model A87-12585 blockage corrections are lower than expected, possibly due to TRANSFORMATION OF A PLANE UNIFORM SHOCK INTO experimental technique. Incidence correction due to lift effect does CYLINDRICAL OR SPHERICAL UNIFORM SHOCK BY WALL not agree well with current methods, and care must be taken in SHAPING the selection of singularity span. The methods cannot be Y. SAILLARD, H. BARBRY, and C. MOUNIER (CEA, considered as a viable replacement for current techniques. The Villeneuve-Saint-Georges, France) IN: Shock waves and shock results for the aircraft model at high incidence are disappointing, tubes; Proceedings of the Fifteenth International Symposium, and the cause is not identified. ESA Berkeley, CA. July 28-August 2, 1985 . Stanford, CA. Stanford University Press, 1986, p. 147-153. refs A theoretical method is presented for the calculation of the wall shape of a shock tube, which changes an initial plane shock N87-10875 British Aerospace Aircraft Group, Bristol (England). of uniform strength into a cylindrical or spherical shock of uniform Civil Div. strength in some solid angle and without Mach reflections. This PROP-FAN SLIPSTREAM EFFECTS USING STATIC method uses Whitham’s theory of shocks in characteristic form. It SIMULATORS LOW SPEED TASK, PHASE 1 Final Report has been numerically treated and gives the complete shock A. C. WILLMES 5 Jul. i985 49 p evoiution during its propagation into the convergent section of the (BAE-B59R/R-D/610/13498; RA/6/16/85; ETN-86-97944) shock tube. The nozzle geometry and shock amplifications Avail: Issuing Activity theoretically expected are indicated and one sample of numerical A device to produce a 14 inch diameter simulated prop fan results is given. Author slipstream was built and tested in a low speed wind tunnel. Tests were carried out with the simulator in front of a VanrJiiard model and an A320 model. Both models were tested with high lift systems A87-12646 deployed. Separate and combined effects of slipstream swirl and HIGH TEMPERATURE HEAT TRANSFER FOR GAS TURBINES supervelocity components were investigated. The technique is USING SHOCK TUBES considered to be established. Data for swept and straight wing H. T. NAGAMATSU and R. E. DUFFY (Rensselaer Polytechnic aircraft at a variety of flap configurations is available. ESA Institute, Troy, NY) IN: Shock waves and shock tubes; Proceedings of the Fifteenth International Symposium, Berkeley, CA, July 28-August 2, 1985 . Stanford, CA, Stanford University Press, 1986, p. 901-908. refs External local heat transfer rates were measured at the N87-10876’# National Aeronautics and Space Administration, stagnation region for circular cylinders, over a flat plate with and Washington, D.C. without a pressure gradient, and in the junction region of a flat AERONAUTICAL FACIL!T!ES ASSESSMENT plate and circular cylinder mounted normal to the plate over a F. E. PANARANDA, comp. Nov. 1985 204 p temperature range of 350 and 2500 K and various Reynolds and (NASA-RP-1146; NAS 1.61:1146) Avail: NTlS HC AlO/MF A01 Mach numbers anticipated in advanced gas turbines. Thin film CSCL 148 platinum heat gages were used to measure the local heat flux for A survey of the free world’s aeronautical facilities was laminar, transition and turbulent boundary layers. Hot wires were undertaken and an evaluation made on where the relative strengths used to measure the turbulence level after the incident and and weaknesses exist. Special emphasis is given to NASA’s own reflected shock waves in the test section. The experimental heat capabilities and needs. The types of facilities surveyed are: Wind flux data were correlated with the laminar and turbulent theories Tunnels; Airbreathing Propulsion Facilities; and Flight Simulators and the transition phenomenon was examined. Author Author

37 09 RESEARCH AND SUPPORT FACILITIES (AIR)

N87-10878# Deutsche Forschungs- und Versuchsanstalt fuer for composite structural analysis, and the use of adhesively bonded Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer and mechanically fastened joints are considered. The effects of Entwurfsaerodynamik. environmental factors on the composites' durability, the damage THE HIGH SPEED CASCADE WIND TUNNEL: STILL AN tolerance of fiber composite laminates, nondestructive and repair IMPORTANT TEST FACILITY FOR INVESTIGATIONS ON procedures, aircraft applications, and airworthiness considerations TURBOMACHINERY BLADES are discussed. I.F. H. HOHEISEL Mar. 1986 36 p In GERMAN; ENGLISH summary A87-10859 (DFVLR-MITT-86-11; ISSN-01767739; ETN-86-98179) Avail: FIAMMABILITY AND SENSITIVITY OF MATERIALS IN NTlS HC AO3/MF A01; DFVLR, Cologne, West Germany DM 14 OXYGEN-ENRICHED ATMOSPHERES; PROCEEDINGS OF THE The importance of the high speed cascade wind tunnel was SYMPOSIUM, WASHINGTON, DC, APRIL 23, 24,1985. VOLUME demonstrated. Starting from the conception of this wind tunnel 2 and the requirements for cascade wind tunnels in which M. A. BENNING, ED. (Air Products and Chemicals, Inc., Allentown, compressible flows have to be studied, the usability and PA) Symposium sponsored by ASTM. Philadelphia, PA, American qualification of this test facility for research work is described with Society for Testing and Materials , 1986, 243 p. For individual examples of turbine and compressor cascade investigations. items see A87-10860 to A87-10867. Necessary additional equipment is discussed. ESA Papers concerned with the design and operation of oxygen systems are presented. Emphasis is given to the ignition of metals and alloys by high-velocity particles; the ignition of metals and alloys in gaseous oxygen by frictional heating; a model of metal 10 ignition which includes the effect of oxide generation; the calculation of ignition and combustion temperatures using laser heating; and ASTRONAUTICS the use of the accelerating rate calorimeter in oxygen compatibility testing. Topics treated include the behavior of fire spreading along Includes astronautics (general); astrodynamics; ground support high-temperature mild steel and aluminum cylinders in oxygen; systems and facilities (space); launch vehicles and space vehicles; the burn propagation rates of metals and alloys in gaseous oxygen; space transportation; space communications; spacecraft the flammability of carbon steel determined by pressurized oxygen communications; command and tracking; spacecraftdesign; testing index measurements; and the RAAF P3B Orion aircraft ground and performance; spacecraft instrumentation; and spacecraft oxygen fire incident. Also discussed are cleaning methods and propulsion and power. procedures for military oxygen equipment, the threshold sensitivities of tests to detect oil film contamination in oxygen equipment; a new detector system that enables fully instrumental operation of N87-10169"# Energy Science Labs., Inc., San Diego, Calif. oxygen reciprocating compressors; and quantitative low-tech GUIDEBOOK FOR ANALYSIS OF TETHER APPLICATIONS Final measurement of fluid nonvolatile residue. I.F. Report J. A. CARROLL Mar. 1985 47 p A87-11372 (Contract NAS8-35499) PROPERTIES AND PROCESSING OF FIBER-REINFORCED (NASA-CR-178904;NAS 1.26:178904) Avail: NTlS HC AO3/MF POLY ETHERETHERKETONE (PEEK) [EiGENSCHAFTEN UND A01 CSCL22A VERARBEITUNG VON FASERVERSTAERKTEM This guidebook is intended as a tool to facilitate initial analyses POLYETHERETHERKETON /PEEK/] of proposed tether applications in space. The guiding philosophy G. KEMPE (DFVLR, lnstitut fuer Bauweisen- und is that a brief analysis of all the common problem areas is far Konstruktionsforschung, Stuttgart, West Germany) more useful than a detailed study in any one area. Such analyses DFVLR-Nachrichten (ISSN 0011-4901), July 1986, p. 29-33. In can minimize the waste of resources on elegant but fatally flawed German. concepts, and can identify the areas where more effort is needed The employment of composite structural components is steadily on concepts which do survive the initial analyses. The simplified increasing in aircraft construction. Studies have been conducted formulas, approximations, and analytical tools included should be with the objective to use for such applications also thermoplastic used only for preliminary analyses. For cietailed analyses, the materials. The best results with respect to resistance against higher references with each topic and in the bibliography may be useful. temperatures and chemicals have been obtained with B.G. carbon-fiber-reinforcedPEEK. The characteristics of this material were investigated, taking into account also suitable processing approaches. Attention is given to a DSC (Differential Scanning 11 Calorimetry) diagram, the advantages of a processing temperature in the temperature range from 383 to 400 C, a study of the effects of temperature and time, various types of bending tests, fracture CHEMISTRY AND MATERIALS energy relations, the advantages of carbon fiber (CF) PEEK compared to CF epoxy, and details regarding proposed Includes chemistry and materials (general); composite materials; manufacturing procedures. G.R. inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing. A87-11791 AERONAUTICAL MANUFACTURERS REQUIREMENTS FOR NEW MATERIALS A87-10294 G. HILAIRE (Aerospatiale, Laboratoire Central, Suresnes, France) COMPOSITE MATERIALS FOR AIRCRAFT STRUCTURES Materiaux et Techniques (ISSN 0032-6895), vol. 74, May-June B. C. HOSKIN, ED. and A. A. BAKER, ED. (Department of Defence, 1986, p. 213-217. In English and French. Aeronautical Research Laboratories, Melbourne, Australia) New Fuel price increases over the past decade have encouraged York, American Institute of Aeronautics and Astronautics, Inc., aircraft manufacturers to increase flight efficiency through 1986, 245 p. No individual items are abstracted in this volume. improvements in the engines, aerodynamics or material weight. The use of composite materials for aircraft structural and For weight savings, the primary candidate materials for airframe aeronautical applications is examined. The basic theory of fiber manufacturers are light alloys such as AI-Li and organic matrix reinforcements, and the physical and mechanical properties of composites such as CFRP. Utilization of a new material requires composite and resin systems are described. The component forms a database on the static strength, fatigue strength, toughness, and manufacturing procedures for composites, the basic theory corrosion and shock resistance, and electrical properties.

38 11 CHEMISTRY AND MATERIALS

Processing techniques must be developed and perfected with A87-12651 regards to quality control and cost. The latter is evaluated in terms PROGRESS IN ADVANCED MATERIALS AND PROCESSES: of material expenditures, processing expenses, the opportunities DURABILITY, RELIABILITY AND QUALITY CONTROL; to eliminate waste, and ensuring that the use of the material is PROCEEDINGS OF THE SIXTH INTERNATIONAL EUROPEAN appropriate. M.S.K. SAMPE CONFERENCE, SCHEVENINGEN, NETHERLANDS, MAY 28-30, 1985 G. BARTELDS, ED. (Nationaal Lucht- en Ruimtevaartlaboratorium, Amsterdam, Netherlands) and R. J. SCHLIEKELMANN, ED. Conference sponsored by SAMPE, Ciba-Giegy, Hercules, Inc., A87-11844 Ministry of Economic Affairs of the Netherlands, et al. Amsterdam NICKEL COATED GRAPHITE FIBER CONDUCTIVE and New York, Elsevier (Materials Science Monographs. Volume COMPOSITES 29), 1985, 319 p. (For individual items see A87-12652 to R. E. EVANS, D. E. HALL, and B. A. LUXON (American Cyanamid A87-12667. Co., Chemical Research Div., Stamford, CT) SAMPE Quarterly Papers are presented on improvements in quality control (ISSN 0036-0821), vol. 17, July 1986, p. 18-26. refs methods for advanced materials; certification for composite airplane Nickel Coated Graphite (NCG) fiber, consisting of a thin structures; the uses of the aramide aluminum laminate; the continuous plating of high purity nickel over an aerospace-grade adhesion of AI joints; in-service environmental effects on carbon graphite core, offers 'performance added' features by combining fiber composite material; and durability airplane paint schemes. the light weight and high structural reinforcement of graphite fiber Topics discussed include the tensile characteristics of coreless with the thermal and electrical conductivity of nickel. These NCG silicon carbide fiber; an improved aramid fiber for aerospace filaments, which are composite constructions in their own right, applications; the correlation between microscopic properties of can be processed and impregnated with thermosetting or interface and mechanical performance of epoxy-carbon thermoplastic resins in the same manner that graphite fiber tows composites; the development of a toughened bismaleimide resin; are processed and impregnated to produce roving, tape or fabric and advances in toughness of structural composites based on prepreg. Therefore, NCG fibers can be readily integrated into interleaf technology. Consideration is given to a two-stage tape structural laminate assemblies using established composites placement system; gasoline engine components; Ariane 4 and manufacturing practices. Author composites; and advances in the resin injection process. Also discussed are the glass transition temperature for carbon fiber-reinforced materials; the applications of holographic NDT; the influence c! art.l!icia! 1-gina end prestrain on the corrosion behavior of a high stiefigth A! a!!oy; high temperature thermoplastic foam; A87-12096# ultra-high modulus composite materials; and the absolute properties SUPERPLASTICITY IN AEROENGINE TITANIUM ALLOY VT-9 of thermosets during cure. I.F. AND ITS MODIFIED COMPOSITIONS A. DUTTA and N. C. BIRLA (Defence Metallurgical Research A87-12652 Laboratory, Hyderabad, India) Defence Science Journal (ISSN 0011-748X). vol. 36, April 1986, p. 179-190. refs CERTIFICATION PROBLEMS FOR COMPOSITE AIRPLANE The alloy (Ti-6.5AI-3.3 Mo-l.6Zr-O.3Si) is a Soviet composition STRUCTURES designated VT-9. The excellent superplastic characteristics found D. CHAUMETTE (Avions Marcel Dassault-Breguet Aviation, in this alloy prompted the exploration of the possible use of Si-free Saint-Cloud, France) IN: Progress in advanced materials and processes: Durability, reliability and quality control; Proceedings of VT-9 in sheet form for superplastic forming. An optimum thermomechanical processing produced a microstructure that the Sixth International European SAMPE Conference, Scheveningen. Netherlands, May 28-30, 1985 Amsterdam and resulted in an elongation of 1700 percent at a fairly high deformation . rate (.002/sec). Thus, the same aeroengine alloy (VT-9) can be New York, Elsevier, 1985, p. 19-28. Basic regulations for fighter and civil transport composite aircraft used for superplastically formed airframe parts in the Si-free structures are examined. The development of the regulations for condition. The present study also shows that for making the forming composite material airframes is discussed. The sensitivity of process commercially viable, deformation temperature could be fowered by temporarily alloying with hydrogen in a particular composites to low energy impact damages and the existence of 'no growth' types damages in composites are analyzed; concentration range (0.1 to 0.2 wt pct). Author consideration is given to a correlation between inspection intervals and residual strength of the composite structures. The role of static tests in the designing of composite structures is described. It is determined that there is a need to evaluate the 5-8 percent A87-1~647' iiaiioiiai Aeicfiaii;ics ex! Space ,A.dmiiis!r:!inn scatter that occurs in the static tests in order to design the most Lewis Research Center, Cleveland, Ohio. reliable composite Structures. !.!=. FIBER-REINFORCED SUPERALLOY COMPOSITES PROVIDE AN ADDED PERFORMANCE EDGE A87-12659 D. W. PETRASEK (NASA, Lewis Research Center, Cleveland, OH), IN-SERVICE ENVIRONMENTAL EFFECTS ON CARBON FIBRE D. L. MCDANIELS, L. J. WESTFALL, and J. R. STEPHENS Metal COMPOSITE MATERIAL Progress (ISSN 0026-0665), Aug. 1986, 5 p. L. A. JONES (British Aerospace, PLC, Future Projects Dept., Fiber reinforcements are being explored as a means to Hatfield, England) IN: Progress in advanced materials and increasing the performance of superalloys past 980 C. processes: Durability, reliability and quality control; Proceedings of Fiber-reinforced superalloys (FRS), particularly tungsten FRS the Sixth International European SAMPE Conference, (TFRS) are candidate materials for rocket-engine turbopump blades Scheveningen, Netherlands, May 28-30, 1985 . Amsterdam and ki advancad Shu!!!~ en~ines:nr( in airhreathing and other rocket New York, Elsevier, 1985, p. 103-114. engines. Refractory metal wires are the reinforcement of choice The ettects oi iong periods ui tiiilina s.e;;.ice on csrhci !!her due to tolerance to fiber/matrix interactions. W alloy fibers have a composite (CFC) skinned flap deflector plates and CFC tailplane maximum tensile strength of 2165 MPa at 1095 C and a 100 hr bullet fairing access panels are analyzed. The composition and creep rupture strength at stresses up to 1400 MPa. A TFRS has manufacturing of the flap deflector plate made with CFC skins the potential of a service temperature 110 C over the strongest bonded to an AI alloy substructure and the bullet fairing access superalloy. Manufacturing processes being evaluated to realize the panel composed of a skin, a frame, and a reinforcing angle are FRS components are summarized, together with design features described. Preflight and post-flight component, and rail and lap which will be introduced in turbine blades to take advantage of shear tests were conducted. The effect of moisture on the the FRS materials and to extend their surface life. M.S.K. components is examined. It is observed that the deflector plates

39 11 CHEMISTRY AND MATERIALS failed as a result of shear induced by torsion on the component, examined. Various procedures for during laminates are evaluated. which was initiated by delamination of skins at trailing edges, and The effects of moisture and high temperature on the composites the access panels failed due to an attachment bolt pulling through are investigated. It is observed that the prepregs are useful at the skin. It is noted that the degradation in properties are more 177 and 232 C for a long-time period and at 260 C for a short significant when the resin not the fiber is predominant, and there time. I.F. is no indication of increasing degradation with length of time in service. I.F. A87-12882 FRACTOGRAPHIC ASPECTS OF THE CYCLIC FRACTURE A87-12660 TOUGHNESS OF 35KHN3MFA STEEL IN VACUUM, AIR, AND IMPROVED DURABILITY AIRLINE PAINT SCHEMES HYDROGEN [FRAKTOGRAFICHESKIE ASPEKTY R. W. BLACKFORD (Imperial Chemical Industries, PLC. London, TSlKLlCHESKOl TRESHINOSTOIKOSTI STALl 35KHN3MFA V England) IN: Progress in advanced materials and processes: VAKUUME, VOZDUKHE I VODORODE] Durability, reliability and quality control; Proceedings of the Sixth IU. V. ZlMA and L. IU. KOZAK (AN USSR, Fiziko-Mekhanicheskii International European SAMPE Conference, Scheveningen. Institut, Lvov, Ukrainian SSR) Fiziko-Khimicheskaia Mekhanika Netherlands, May 28-30,1985 . Amsterdam and New York, Elsevier, Materialov (ISSN 0430-6252), vol. 22, May-June 1986, p. 50-58. 1985, p. 115-124. In Russian. refs Methods for improving the durability of polyurethane finishes The microscopic characteristics of fatigue crack growth in a are analyzed. The effects of cleaners, polishes, and paint rotor steel, 35Kh3MFA, in vacuum, air, and hydrogen are formulation on airliner operating conditions are examined. The investigated using a scanning electron microscope. In particular, mechanism which causes surface degradation of polyurethane the formation of fatigue striations is examined in relation to the finishes under weathering conditions is described. Changes in crack closure effect, and it is shown that there is no exact appearance caused by resin breakdown are considered and correlation between the two phenomena. It is suggested that the modifications to the polyurethane surface which will reduce surface formation of striations is largely determined by structural sensitivity degradation are proposed. The use of cleaners/polishes which of crack closure, while the modifying effect of the medium depends contain abrasive and polymeric materials to clean the aircraft on its nature and physicochemical parameters. V.L. surface is discussed. I.F. A87-1290 1 A87-12661 A METHOD FOR CALCULATING THE SUSCEPTIBILITY OF JET ADVANCES IN TOUGHNESS OF STRUCTURAL COMPOSITES FUELS TO SMOKING [RASCHETNYI METOD OTSENKI BASED ON INTERLEAF TECHNOLOGY SKLONNOSTI REAKTIVNYKH TOPLIV K DYMLENIIU] R. B. KRIEGER, JR. (American Cyanamid Co., Engineering A. F. FINASHOV and N. F. DUBOVKIN Khimiia i Tekhnologiia Materials Dept., Havre de Grace, MD) IN: Progress in advanced Topliv i Masel (ISSN 0023-1169), no. 7, 1986, p. 38, 39. In materials and processes: Durability, reliability and quality control; Russian. Proceedings of the Sixth International European SAMPE A method for calculating the susceptibility of jet fuels to smoking Conference, Scheveningen, Netherlands, May 28-30. 1985 . is developed on the basis of the assumption that this property is Amsterdam and New York, Elsevier, 1985, p. 189-199. determined mainly by the elemental and group hydrocarbon The use of interleaf technology to improve the toughness of composition, density, and viscosity of the fuel. This assumption is structural composites is examined. Compression after impact and verified experimentally for several hydrocarbon fuels using a model hot-wet compression tests were applied to quasi-isotropiclaminates combustion chamber of a gas turbine engine, and an empirical in order to evaluate toughness. Impact failure modes in epoxy formula for determining the degree of smoking is obtained. It is formulations are studied. It is observed that the low resin content shown that the calculated results agree with experimental data to in composites produces thin resin bonds between plies resulting within 10-25 percent, depending on the excess air ratio, with a in thin stiff bonds; the addition of a tough resin interleaf (CYCOM confidence level of 0.95. V.L. HST-7) between each ply of the composite eliminates the thin stiff bonds and enhances the composite toughness. The critical A87-12902 parameters for the CYCOM HST-7 are a 41 percent resin content THICKENED OILS [ZAGUSHCHENNYE MASLA] and on ultimate strength of 66,000 psi compression at 200 F. A. I. AKHMEDOV, S. N. RUSTAMOVA, and N. D. ISMAILOVA The weight saving possible with the interleaf is evaluated and (AN ASSR, lnstitut Khimii Prisadok, Baku, Azerbaidzhan SSR) compared with AI, and it is detected that the CYCOM HST-7 Khimiia i Tekhnologiia Topliv i Masel (ISSN 0023-1169), no. 7, proviides a 45 percent weight advantage over AI in the hot-wet 1986, p. 43-45. In Russian. refs compression. I.F. The properties of thickened oils currently used for automobile, tractor, ship, and aircraft engines are briefly reviewed, as are some A87-12667 new thickening additives. The new thickeners are mostly DEVELOPMENT OF A TOUGHENED BlSMALElMlDE RESIN copolymers of isobutylene and alkyl methacrylates with stabilizing PREPREG FOR CARBON FIBER COMPOSITES comonomers (vinylaromatic and carbocyclic compounds). It is P. A. STEINER, M. BLAIR, G. GONG, J. MCKILLEN, and J. emphasized that the high viscosity index of thickened oils must BROWNE (Hysol Grafil Co., Pittsburgh, CA) IN: Progress in be combined with good low-temperature properties. Some of the advanced materials and processes: Durability, reliability and quality thickened oils reviewed allow cold starts at temperatures as low control; Proceedings of the Sixth International European SAMPE as -35 C. V.L. Conference, Scheveningen, Netherlands, May 28-30, 1985 . Amsterdam and New York, Elsevier, 1985, p. 297-308. refs A87-12928 A toughened bismaleimide resin, LR 100-740, which can be ALUMINAGOCRALY MATERIAL AS AN IMPROVED used in dry environments up to 260 C and humid environments INTERMEDIATE LAYER FOR GRADED CERAMIC GASPATH up to 177 C, can be autoclave cured at a temperature of 179 C SEALING IN AEROTURBINE ENGINES under a pressure of .59 MPa, and has improved fracture toughness H. E. EATON and R. C. NOVAK (United Technologies Research for use in aircraft structures is developed. The resin modulus, Center, East Hartford, CT) Ceramic Engineering and Science flexural mode, tan delta, and viscosity of the LR 100-740 resin Proceedings (ISSN 0196-6219), vol. 7, July-Aug. 1986, p. were evaluated. The resin is applied to Grafil high strain XA-S 727-736. carbon fibers and Grafil intermediate modulus Apollo IM carbon (Contract F33615-83-C-5026) fibers. The low resin content (30 percent) required for development Ceramic gas-path sealing is being used as shrouding in the of the prepregs and the maintenance of tack allow the use of turbine section of aircraft gas turbine engines to increase efficiency bleeder free cure procedures for the formation of the prepregs. and performance. A graded design overcomes the thermal The mechanical and physical properties of the two prepregs are expansion mismatch between the metallic substrate and the

40 11 CHEMISTRY AND MATERIALS abradable/thermally insulating ceamic top layer. Stabilized zirconia high attenuations are found. Variations in velocity depend on ply is the top layer material of choice due to its high temperature orientation, and the substructure arrangement. Metal substructures capability, and zirconia-metallics are used for the intermediate layer reduce the measured velocity compared with carbon fiber compositions. An alumina-metallic intermediate layer composition substructures. Studies which introduced a pointed brass probe has been demonstrated to have improved stability in comparison used as a source of simulated emission result in a considerable to the zirconia based system. Author decrease in the overall velocities measured. This phenomenon applies particularly to the flat plate specimens and, to a lesser A87- 1297 1# extent, to the honeycomb type of structure. ESA TESTING OF FE-CU-BASE ABLATIVE COMPOSITES. II [BADANIE KOMPOZYTOW ABLACYJNYCH NA OSNOWIE N87-10182'# Sikorsky Aircraft, Stratford, Conn. FE-CU. Ill FLIGHT SERVICE EVALUATION OF COMPOSITE HELICOPTER R. KROL Technika Lotnicza i Astronautyczna (ISSN 0040-1 145), COMPONENTS Annual Report, Oct. 1983 - Dec. 1985 vol. 41, March 1986, p. 5-7. In Polish. refs G. H. MARDOIAN and M. B. EZZO Sep. 1986 66 p The in-flight thermal loading of rocket and aircraft components (NASA-CR-178149; NAS 1.261178149; SER-510237; AR-3) employing ablative materials is examined. The ablation Avail: NTlS HC A04/MF A01 CSCL 11D phenomenon is defined, and examples of ablative materials are This report presents an assessment of composite helicopter given. Test results on an Fe-Cu-base ablative composite are tail rotor spars and horizontal stabilizers, exposed to the effects discussed. A method for calculating the specimen-wall temperature of the environment, after up to five and a half years of commercial distribution, the pressure required for liquid-metal flow, and the service. This evaluation is supported by test results of helicopter efficiency of heat absorption by the composite in the ablation components and panels which have been exposed to outdoor process is described. B.J. environmental effects since September 1979. Full scale static and fatigue tests have been conducted on graphite/epoxy and A87-13009# Kevlar/epoxy composite components obtained from Sikorsky Model NEW MATERIALS IN GAS TURBINE TECHNOLOGY S-76 helicopters in commercial operations in the Gulf Coast region G. R. JOHNSTON (Department of Defence, Materials Research of Louisiana. Small scale static and fatigue tests are being Laboratories, Melbourne, Australia) IN: Joint National Symposium conducted on coupons obtained from panels under exposure to on the Influence of Aviation on Engineering and the Future of outdoor conditions in Stratford, Connecticut and West Palm, Florida. Aeronautics in Australia, Melbourne, Australia, August 8. 9, 1985, The panel layups are representative of the S-76 components. Preprints . Barton, Australia/Brookfield, VT, Institution of Additionally, this report discusses the results of moisture absorption Engineersi'Biookfisld ?&i&ing CC.,1 W5, p. 35-38. refs evaluations and strength tests on the S-76 components and The present evaiuation of materials developed for use ir? gas composite panels with up to rive years of ouidooi exposuie. turbines places emphasis on novel, next-generation materials Author applicable to state-of-the-art engines. Attention is given to the results of engine trials conducted by Australia's Defense Science N87-10209# Products Research and Chemical Corp., Glendale, and Technology Organization to assess manufacturer-specified Calif. Research and Development Lab. protective coatings on first stage, high pressure turbine blades. POLYMER SYSTEMS FOR RAPID SEALING OF AIRCRAFT Comparisons are made between these data and those for STRUCTURES AT LOW TEMPERATURE Final Report, Sep. 1981 commercially available coatings in the same engines. - Aug. 1983 Recommendations for changes in coatings are made on the basis L. MORRIS, M. WILLIAMS, and N. CHAMPLIN 1 Nov. 1985 of these comparison results. O.C. 40 P (Contract N62269-81-C-0741; F61-542) A87-130 1O# (AD-A167667; NADC-85158-60) Avail: NTlS HC A03/MF A01 ADVANCED FIBRE COMPOSITES AND OTHER NEW CSCL 11A MATERIALS FOR AIRFRAME APPLICATIONS Materials examined for low temperature, rapid curing, fuel and A. A. BAKER (Department of Defence, Aeronautical Research water resistant sealants included hot melts, UV activated, moisture Laboratories, Melbourne, Australia) IN: Joint National Symposium curing, and anaerobic polymers. Two component polymers utilizing on the Influence of Aviation on Engineering and the Future of urethane cures, oxidation, and mercaptan-epoxy additions were Aeronautics in Australia, Melbourne, Australia, August 8, 9, 1985. evaluated. Epoxy cures of mercaptan terminated polythioethers Preprints . Barton, Australia/Brookfield, VT, Institution of gave excellent low temperature cures along with practical Engineers/Brookfield Publishing Co., 1985, p. 39-43. refs application times. Physical and chemical properties were examined The present development status evaluation for high and found to essentially meet requirements of MIL-S-85420 (AS). performance composite materials applicable to airframe structures Storage stability was excellent. GRA gives emphasis to state-of-the-art graphite-reinforced epoxy matrix composites, which currently dominate the field. c;omposire primary ;iiF-:33:3*# I?cnr;!ns P.ircw?! Co , Inr:, I ong Beach. Calif. structure property impacts on weight, acquisition and maintenance CRITICAL JOINTS IN LARGE COMPOSITE AIRCRAFT costs, and aerodynamic performance, are noted. Comparisons are STRUCTURE Contractor Report, Nov. 1981 - Jan. 1983 made with the performance levels and high temperature W. D. NELSON, 6. L. BUNIN, and L. J. HART-SMITH characteristics promised by metal-matrix composites and advanced Washington NASA Aug. 1983 41 p Presented at the 6th metallic alloy systems. Application of these materials in sporting Conference on Fiberous Composites in Structural Design, New goods and vehicles are also assessed. O.C. Orleans, La., 24-27 Jan. 1983 (Contract NASl-16857) N87-10180# British Aerospace Aircraft Group, Weybridge (NASA-CR-3710; NAS 1.263710; DP-7266) Avail: NTlS HC (England). AOWMF A01 CSCL 11D INVESTIGATION INTO THE ATTENUATION AND VELOCITY OF A program was conducted at Douglas Aircraft Company to ACOUSTlC EMiSSiafig iN ~~~~~~ F;BEg nnUDr\ClTC""I.,. --. .- dnv~lapthe technologv for critical structural joints of composite AIRCRAFT STRUCTURES wing structure that meets design requirements for a iYYu R. F. C. HALL Sep. 1985 99 p commercial transport aircraft. The prime objective of the program (Contract A93BI1362) was to demonstrate the ability to reliably predict the strength of (BAE-KGT-R-GEN-01349; BR97843; ETN-86-97947) Avail: NTlS large bolted composite joints. Ancillary testing of 180 specimens HC A05/MF A01 generated data on strength and load-deflection characteristics The attenuation and propagation velocity of acoustic emission which provided input to the joint analysis. Load-sharing between signals in carbon fiber composite honeycomb, monolithic multispar, fasteners in multirow bolted joints was computed by the nonlinear and integral stringer type constructions were investigated. Very analysis program A4EJ. This program was used to predict strengths

41 11 CHEMISTRY AND MATERIALS of 20 additional large subcomponents representing strips from a N87-10985# Federal Aviation Administration, Atlantic City, N.J. wing root chordwise splice. In most cases, the predictions were AN INVESTIGATION OF THE FAA VERTICAL BUNSEN BURNER accurate to within a few percent of the test results. In some FLAMMABILITY TEST METHOD Final Report cases. the observed mode of failure was different than anticipated. P. CAHILL Aug. 1986 15 p The highlight of the subcomponent testing was the consistent (DOT/FAA/CT-86/22) Avail: NTlS HC AO2/MF A01 ability to achieve gross-sectionfailure strains close to 0.005. That The vertical Bunsen burner test method, as specified in appendix represents a considerable improvement over the state of the art. F of the Federal Aviation Regulations - Part 25, was evaluated in Author order to update and clarify certain problem areas. Burner fuel, flame temperature and flame placement were investigated. It was determined that: (1) methane gas can be used as a replacement of alternative to B-gas. (2) a minimum flame temperature N87-10974*# Douglas Aircraft Co., Inc., Long Beach, Calif. specification is meaningless without specifying thermocouple wire DC-10 COMPOSITE VERTICAL STABILIZER GROUND TEST thickness, and (3) placing the flame at the midpoint of the lower PROGRAM Contractor Report, Dec. 1980 - May 1982 edge of the front face results in a more realistic and severe J. M. PALMER, JR., C. 0. STEPHENS, and J. 0. SUTTON evaluation of the specimen’s flammability properties. Author Washington NASA Aug. 1983 38 p Presented at the 6th Conference on Fiberous Composites in Structural Design, New N87-10990# European Space Agency, Paris (France). Orleans, La., 24-27 Jan. 1983 RESULTS OF WIND TUNNEL TESTS ON EXTERNAL (Contract NAS1-14869) COMBUSTION (NASA-CR-3715; NAS 1.26:3715; DP-7269) Avail: NTlS HC B. SCHAEFER Dec. 1985 52 p Transl. into ENGLISH from A03/MF A01 CSCL 11D “Ergebnisse von Windkanalversuchen zur Aussenverbrennung” A review of the structural configuration and ground test program (Cologne, West Germany) Original language document was is presented. Particular emphasis is placed on the testing of a announced as N86-15643 full-scale stub box test subcomponent and full span ground test (ESA-TT-959; DFVLR-FB-85-35; ETN-86-98245) Avail: NTlS HC unit. The stub box subcomponent was tested in an environmental A04/MF A01; original German version available at DFVLR, chamber under ambient, coldlwet, and hot/wet conditions. The Cologne, West Germany DM 56 test program included design limit static loads, fatigue spectrum Wind tunnel tests on external combustion were carried out to loading to approximately two service lifetimes (with and without study the flow distribution on a flat plate in a supersonic flow for damage), design limit damage tolerance tests, and a final residual spoiler optimization and combustion efficiency. The influence of stre igth test to a structural failure. The first full-scale ground test spoiler geometry, mass flow rate and injection angle on flow unit was tested under ambient conditions. The test unit was to distribution was studied. The separation area can be enlarged have undergone static, fatigue, and damage tolerance tests but a with the spoiler inclination against the flow. Resistance problems premature structural failure occurred at design limit load during and mass flow rate against a split overture are reduced with a the third limit load test. A failure theory was developed which hole-line flow nozzle. The area of increased pressure is enlarged explains the similarity in types of failure and the large load by injecting hydrogen in the recirculation area before the spoiler discrepancy at failure between the two test articles. The theory and by igniting the mixture. The cross force after ignition is five attributes both failures to high stress concentrations at the edge times as strong as the spoiler action. ESA of the lower rear spar access opening. A second full-scale ground test unit has been modified to incorporate the various changes resulting from the premature failure. The article has been N87-10994 British Aerospace Aircraft Group, Bristol (England). assembled and is active in the test program. Author Advanced Manufacturing Research Dept. INTERNATIONAL CONFERENCE - SUPERPLASTICITY IN AEROSPACE ALUMINIUM K. S. BROAD, comp. 23 Jul. 1985 12 p Conference held in N87-10975’# Douglas Aircraft Co., Inc., Long Beach, Calif. Bedford, England, 12-15 Jul. 1985 CRITICAL COMPOSITE JOINT SUBCOMPONENTS ANALYSIS (BAE-S85/AMR/0066; ETN-86-97945) Avail: Issuing Activity AND TEST RESULTS The use of superplastic aluminum in aerospace was discussed. B. L. BUNIN Washington NASA Sep. 1983 155 p Superplastic forming to produce cost effective lightweight parts (Contract NASl-16857) was considered. Limitations from microstructural fractures and (NASA-CR-3711; NAS 1.26:3711; ACEE-26-TR-3074) Avail: resultant properties were covered, particularly the problem of NTlS HC A08/MF A01 CSCL 11D cavitation. Special processing techniques and the evolution of alloys This program has been conducted to develop the technology to overcome limitations were treated. ESA for critical structural joints of a composite wing structure meeting design requirements for a 1990 commercial transport aircraft. A prime objective of the program was to demonstiate the ability to N87-11003# Deutsche Forschungs- und Versuchsanstalt fuer reliably predict the strength of large bolted composite joints. Load Luft- und Raumfahrt, Cologne (West Germany). Abteilung sharing between bolts in multirow joints was computed by a Korrosion. nonlinear analysis program (A4FJ) which was used both to assess GALVANIC CORROSION BETWEEN CARBON FIBER the efficiency of different joint design concepts and to predict the REINFORCED PLASTICS AND METALLIC AERONAUTICAL strengths of large test articles representing a section from a wing MATERIALS root chord-wise splice. In most cases, the predictions were accurate T. FOURRIER and H. BUHL Apr. 1986 86 p to within a few percent of the test results. A highlight of these (DFVLR-FB-86-16;ISSN-0171-1342; ETN-86-98184) Avail: NTlS tests was the consistent ability to achieve gross-section failure HC AOWMF A01; DFVLR, Cologne, West Germany DM 27 strains on the order of 0.005 which represents a considerable The electrochemical behavior of carbon fiber reinforced plastics improvement over the state of the art. The improvement was (CFRP) and the galvanic corrosion between CFRP and metallic attained largely as the result of the better understanding of the aeronautical alloys were investigated. Rest potentials, mixed load sharing in multirow joints provided by the analysis. The typical potentials, galvanic current densities, and polarization curves were load intensity on the structural joints was about 40 to 45 thousand measured. Influence of parameters such a pH-value, electrolyte pound per inch in laminates having interspersed 37 1/2-percent agitation, distance between the samples, and area ratio was 0-degree plies, 50-percent + or - 45-degrees plies and 12 studied. Aluminium alloys (2024, 7010, 7050, 7075, 8090) show a 1/2-percent 90-degrees plies. The composite material was Toray high sensitivity to galvanic corrosion with CFRP; Ti-6A1-4V is the 300 fiber and Ciba-Geigy 914 resin, in the form of 0.010-inch only alloy with uncritical galvanic corrosion behavior with CFRP. thick unidirectional tape. Author ESA

42 11 CHEMISTRY AND MATERIALS

N87-11004# National Aerospace Lab., Amsterdam (Netherlands). scanning electron microscopy (SEM), and electron micropulse Structures and Materials Div. (EMP) examination. B.G. CORROSION AND CORROSION PREVENTION IN AIRCRAFT STRUCTURES W. G. J. THART Mar. 1985 25 p In DUTCH; ENGLISH summary Presented at PBNA Course on Corrosion Prevention, N87-11194'# National Aeronautics and Space Administration. Utrecht, Netherlands, 16-23 Apr. and 7-14 May 1985 Lewis Research Center, Cleveland, Ohio. (NLR-MP-850294; 68667275; ETN-86-98490) Avail: NTlS HC COATING LIFE PREDICTION A02/MF A01 J. A. NESBllT and M. A. GEDWILL In its Turbine Engine Hot Materials used in aircraft and the operational environments Section Technology, 1984 12 p Oct. 1984 which cause the different kinds of corrosion are presented. The Avail: NTlS HC A17/MF A01 CSCL 11G corrosion-sensitive parts of aircraft structures are discussed. Hot-section gas-turbine components typically require some form Measures to provide optimal corrosion prevention (choice of of coating for oxidation and corrosion protection. Efficient use of materials, metallic coatings, surface treatment, painting) are coatings requires reliable and accurate predictions of the protective reviewed. Measures to be taken during the design phase and life of the coating. Currently engine inspections and component during maintenance are outlined. ESA replacements are often made on a conservative basis. As a result, there is a constant need to improve and develop the life-prediction N87-11014# Federal Aviation Administration, Atlantic City, N.J. capability of metallic coatings for use in various service AVGAS/AUTOGAS COMPARISON: WINTER FUELS Interim environments. The purpose of this present work is aimed at Report developing of an improved methodology for predicting metallic A. M. FERRARA Jul. 1986 53 p coating lives in an oxidizing environment and in a corrosive (DOT/FAA-CT-86/21) Avail: NTlS HC A04/MF A01 environment. Author This report describes dynamometer tests which simulated conditions found in a general aviation aircraft. In these tests, automobile gasoline was tested and compared with aviation gasoline. The tendency for vapor lock and detonation was N87-11195*# National Aeronautics and Space Administration. measured as a function of gasoline grade, Reid Vapor Pressure, Lewis Research Center, Cleveland, Ohio. and the age of the fuel. Author INTRODUCTION TO LIFE MODELING OF THERMAL BARRIER COATINGS N87-11181'# National Aeronautics and Space Administration. R. A. MILLER In its Turbine Engine Hot Section Technology. Lewis Research Center, Cleveland, Ohio. 1984 6 p Oct. 1984 COMBUSTION OVERVIEW Avail: NTlS HC A17/MF A01 CSCL 11G D. F. SCHULTZ In its Turbine Engine Hot Section Technology, Thermal barrier coatings may be applied to air-cooled turbine 1984 6 p Oct. 1984 section airfoils to insulate such components from hot gases in Avail: NTlS HC A17/MF A01 CSCL 218 the engine. The coatings, which typically consist of about 0.01 to The objective of this effort is to develop improved analytical 0.04 cm of zirconia-yttria ceramic over about 0.01 cm of NiCrAlY models of the internal combustor flow field and liner heat transfer or NiCrAlZr alloy bond coat, allow increased gas temperatures or as a means to shorten combustor development time and increase reduced cooling air flows. This, in turn, leads to marked turbine engine hot section life. A four-element approach was improvements in engine efficiency and performance. However, selected to meet this objective. First, existing models were utilized certain risks are associated with designing for maximum benefits, to determine their deficiencies. Supporting research was then and eventually a point is reached where coating loss would commenced to improve the exisiting models. While the research immediately jeopardize the underlying component. Therefore, effort is in progress, the models are being refined to improve designers must be able to accurately predict the life of a given numerics and numerical diffusion. And lastly, the research results bill-of-material coating in any particular design. The results of an and improved numerics will be integrated into existing models. in-house aeronautics, base research and technology program which Author is designed to provide the first steps towards developing mission-capable life-prediction models are outlined. Author N87-11l82'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. SURFACE PROTECTION S. R. LEVINE In its Turbine Engine Hot Section Technology, N87-11204'# National Aeronautics and Space Administration. 1984 10 p Oct. 1984 Lewis Research Center, Cleveland, Ohio. Avail: NTIQ Uc .A!7/MF .A.Q! CsCL !!F FLAK RA=:AT:G:: The surface protection subproject consists of three major J. D. WEAR In its Turbine Engine Hot Section Technology, thrusts: airfoil deposition model; metallic coating life prediction; 1984 10 p Oct. 1984 and thermal barrier coating (TBC) life prediction. The time frame Avail: NTlS HC A17/MF A01 CSCL 218 for each of these thrusts and the expected outputs are presented. Total radiation and heat flux data was obtained on a combustor Further details are given for each thrust such as specific element liner by advanced instrumentation. If the results obtained by the schedules and the status of performance; in-house, via grant, or special instrumentation are considered to be representative of the via contract. B.G. total radiation and heat flux, then the effect of variation of engine operating parameters and of fuel type can be more easily obtained. N87-11193*# General Electric Co., Fairfield, Conn. The special instrumentation used for these investigations consisted EFFECTS OF SURFACE CHEMISTRY ON HOT CORROSION of five total radiometers and two total heat flux gages. The LIFE radiometers were nrranrp-i axially a.nd rirr~imfgrentirr!!y !hrtxgh R. E. FRYXELL and B. K. GUPTA (TRW, Inc., Cleveland, Ohio) sliding air seals in the outer liner. The two heat flux gages were In NASA. Lewis Research Center Turbine Engine Hote Section welded in the outer liner between two circumferential radiometers. Technology, 1984 14 p Oct. 1984 Static pressures were obtained on both the cold and the hot side (Contract NAS3-23926) of the outer liner in the area of the heat flux gages. Liner metal Avail: NTlS HC A17/MF A01 CSCL 11F temperatures were also obtained. The combustor inlet pressure Hot corrosion life prediction methodology based on a was varied over a nominal range of 0.5 to 2.07 MPa, inlet air combination of laboratory test data and field service turbine temperature from 550 to 670 K, and fuel-air ratio from about 0.01 5 components, which show evidence of hot corrosion, were to 0.040. The two fuels tested were ASTM Jet A and a fuel examined. Components were evaluated by optical metallography, designated as ERBS V. Results of the tests are discussed. B.G.

43 12 ENGINEERING

12 screw presses. Future trends in computer-aided forging and design processes, materials, and techniques are projected. O.C. ENGINEERING A87-10516# Includes engineering (general); communications and radar; TENSION ANALYSIS OF STIFFENED AIRCRAFT STRUCTURES electronics and electrical engineering; mechanics and heat transfer; M. MOHAGHEGH (Boeing Commercial Airplane Co., Seattle, WA) instrumentation and photography; lasers and masers; mechanical (Structures, Structural Dynamics, and Materials Conference, 26th, engineering; quality assurance and reliability; and structural Orlando, FL, April 15-17, 1985, Technical Papers. Part 1, p. mechanics. 665-672) Journal of Aircraft (ISSN 0021-8669), vol. 23, Aug. 1986, p. 609, 610. Previously cited in issue 13. p. 1896, Accession no. A85-30298. A87-10115 DECAY OF END EFFECTS IN GRAPHITE/EPOXY BOLTED ~a7-10720 JOINTS A COMPUTER-AIDED NONDESTRUCTIVE INSPECTION L. CARLSSON. P. SINDELAR, and S. NILSSON (Flygtekniska SYSTEM Forsoksanstalt, Bromma. Sweden) Composites Science and R. C. ADDISON, JR.. J. M. F. LEE, A. H. MUIR, JR., and A. W. Technology (ISSN 0266-3538), vol. 26, no. 4, 1986, p. 307-321. THIELE (Rockwell International Science Center, Thousand Oaks, refs CA) IN: Review of progress in quantitative nondestructive The local disturbances introduced into the strength of a material evaluation. Volume 5A - Proceedings of the Twelfth Annual Review, by a fastener bolt in a single-row bolted joint in a graphitelepoxy Williamsburg, VA, June 23-28, 1985 . New York, Plenum Press, composite plate loaded in tension are examined. Consideration is 1986, p. 789-799. Research supported by the Rockwell International given to plates with constant thickness and to plates with a Corp. transition from a thicker to thinner cross section. Unlike procedures (Contract F33657-81-GO21 0) followed for isotropic metal plates, account is taken of anisotropy Attention is given to a computer-aided nondestructive inspection in the plate materials within the finite element formulation. The system designed for improving the speed and quality of the models show that the characteristic decay length, Le., the distance ultrasonic evaluation of diffusion-bonded parts of the B-1B aircraft. over which a nonequilibrated cross-sectional stress decays to a The system consists of a host computer, a data acquisition and negligible value, is proportional to the square root of the ratio of multi-axis control (DAMAC) system, and a custom mechanical the elasticity to the applied stress. A simplified formula is defined scanning system. The host computer uses menu-driven software for quantifying the decay rate for a constant thickness material. to provide a user-friendly interface for the operator; an array The models show that the decay length is significantly less in a processor permits the acquisition of entire waveforms for component with a reduction in thickness. M.S.K. subsequent analysis. In order to eliminate time-consuming part alignment procedures, the DAMAC permits raster scans to be performed on parts that lie at arbitrary orientation with respect to A87-10121 the tank. In addition, the DAMAC controls the ultrasonic SPECIFICATION OF GAS TURBINE DISC FORGINGS pulser-receiver and synchronizes the data acquisition with the R. H. JEAL (Rolls-Royce, Ltd., Derby, England) Materials Science scanning motions. The custom mechanical scanning system and Technology (ISSN 0267-0836). vol. 2, July 1986, p. 721-727. contains three servo-controlled linear axes capable of vector The cost of failures in gas turbine discs, both in human life movements within a 10 x 16 x 3 ft volume; the scanning speed is and financial terms, is particularly high, and it has always been 20 ips. K.K. recognized that the component must be fully specified against the design requirement, and totally predictable in operation. This was A87-1072 1 originally achieved by making a reproducible forging consistent COMPUTERIZED ULTRASONIC TEST INSPECTION with the design strength assumptions and which approached the ENHANCEMENT SYSTEM FOR AIRCRAFT COMPONENTS engineer’s model of the material as ’elastic, isotropic, and free R. G. PARENT (Lockheed-Georgia Co., Marietta) IN: Review of from defects’. Today’s improved understanding of materials progress in quantitative nondestructive evaluation. Volume 5A - behaviour in terms of the relationship between material property Proceedings of the Twelfth Annual Review, Williamsburg, VA, June and microstructure, together with the designer’s need for 23-28, 1985 . New York, Plenum Press, 1986, p. 801-809. higher-strength materials, has led to an approach which now Attention is given to the computerized ultrasonic test inspection recognizes the role of both structure and ’defects’ within the forging. enhancement (CUTIE) system which was designed to meet the This, and the need to improve the the cyclic properties of following program goals: (1) automation of the inspection technique components, is now imposing on the forger complex microstructural and evaluation of the discontinuities for aircraft components while and quality requirements that can be met only by process control maintaining reasonable implementation costs and reducing the and by a move towards closer-to-size and more complex shape overall inspection costs; and (2) design of a system which would requirements. Future materials needs are discussed in relation to allow for easy modification so that new concepts could be controlling the discontinuity behaviour, together with the change implemented. The system’s ultrasonic test bridge, C-scan recorder, in philosophy that this is bringing to the control of the manufacturing computer control, and ultrasonic flaw detector are described. process. Author Consideration is also given to the concurrent development of an eight element array transducer (for increasing the inspection rate) A87-10124 and a high-speed data acquisition system (for signature analysis). FORGING OF BLADES FOR GAS TURBINES K.K. D. C. WRIGHT and D. J. SMITH (Doncasters Monk Bridge, Ltd., Leeds. England) Materials Science and Technology (ISSN A87-10727 0267-0836), vOI. 2, July 1986, p. 742-747. MANUFACTURING TECHNOLOGY FOR NONDESTRUCTIVE The forging of Ni-based superalloy gas turbine blades has EVALUATION (NDE) SYSTEM TO IMPLEMENT RETIREMENT progressed to the point where precision methods can FOR CAUSE (RFC) PROCEDURES FOR GAS TURBINE ENGINE cost-effectively yield dimensionally accurate products, retaining COMPONENTS competitiveness with casting methods. Attention is presently given D. L. BlRX and D. G. DOOLIN (Systems Research Laboratories, to forged blade performance and economic requirements, quality Inc., Dayton, OH) IN: Review of progress in quantitative standards, alloy forgeability criteria, stages in forged blade nondestructive evaluation. Volume 5A - Proceedings of the Twelfth manufacture, grain flow characteristics encountered in upsetting Annual Review, Williamsburg, VA, June 23-28, 1985 . New York, and extrusion, and the configuration of state-of-the-art hydraulic Plenum Press, 1986, p. 877-884.

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A87-10728 orthogonal servo-controlled deflecting mirrors. An infrared imager, EVALUATION OF CAPTURED WATER COLUMN TECHNOLOGY whose scanning mirrors oscillate in the vertical and the horizontal FOR ADVANCED ULTRASONIC SIZING TECHNIQUES directions, is used as the detector. The analysis technique used G. M. LIGHT, W. R. VAN DER VEER (Southwest Research Institute, to extract the diffusivity from these images is based on a thin San Antonio, TX), D. S. STUBBS, and W. C. HOPPE (Systems infinite plate assumption, which requires waiting a given period of Research Laboratories, Inc.. Dayton, OH) IN: Review of progress time for the temperature to equilibrate throughout the thickness of in quantitative nondestructive evaluation. Volume 5A - Proceedings the sample. The technique is shown to be accurate to within two of the Twelfth Annual Review, Williamsburg, VA, June 23-28, 1985 percent for values of the order of those for composite diffusivities, I . New York, Plenum Press, 1986, p. 885-892. and to be insensitive to convection losses. I.F. (Contract F33615-81-C-5002)

A87-10730 A87-10765 RFC AUTOMATED INSPECTION OVERVIEW NONDESTRUCTIVE INSPECTION OF COMPOSITE D. A. STUBBS and W. C. HOPPE (Systems Research Laboratories, STRUCTURES BY LOW-VELOCITY IMPACT Inc., Dayton, OH) IN: Review of progress in quantitative R. D. ADAMS, A. M. ALLEN (Bristol, University, England), and P. nondestructive evaluation. Volume 5A - Proceedings of the Twelfth CAWLEY (Imperial College of Science and Technology, London, Annual Review, Williamsburg, VA, June 23-28, 1985 . New York, England) IN: Review of progress in quantitative nondestructive Plenum Press, 1986, p. 901-910. evaluation. Volume 58 - Proceedingsof the Twelfth Annual Review, (Contract F33615-81-C-5002) Williamsburg, VA, June 23-28, 1985 . New York, Plenum Press, The RFC Inspection System uses eddy current and ultrasonic 1986, p. 1253-1258. techniques to perform automatic inspection of gas turbine engine A prototype instrument, called 'Tapometer', has been designed components. Current flaw size requirements are 0.010 inch (length) on the basis of the coin-tap-test principle, incorporating both x 0.005 inch (depth) surface connected cracks and 0.020 inch time-domain and frequency-domain methods of comparing diameter penny shaped, maloriented internal voids. Successful and mechanical impulses on good and bad areas of a structure. The reliable detection of these small flaws requires sophisticated Tapometer technique will work wherever the 'coin-tapping' can be inspection equipment and techniques. Details of both the eddy used but, unlike the coin-tap test, it is quantitative and recordable. current and ultrasonic inspections is presented along with the In addition, the Tapometer is used without a couplant between philosophy and reasons supporting each component of the the tapping head and the test structure, presenting a great inspections. Inspection components presented include: part I.~V~R?I.~Pir: tes!~ C! %ani. h~fieyc~mban6 fik%-i&ifcic& dimensioning, probe calibration, adaptive scanning, threshold composites. The Tapometer was used successfuiiy to detect detection, signal processing, and flaw position correlation. delaminations in solid carbon-fiber-reinforced plastics, and defects Additional material is presented highlighting the problems and in honeycomb sandwich panels, bonded aluminum structures, solutions associated with a sophisticated, automatic inspection crushed cores in helicopter rotor blades, and massive system. Author rubber/steel/polyester composite tubes. IS.

A87-10732 PREDICTIVE MODELS AND RELIABILITY IMPROVEMENT IN ELECTROMAGNETIC NONDESTRUCTIVE EVALUATION A87-10768 R. E. BEISSNER (Southwest Research Institute, San Antonio, TX) VARIATIONS IN ULTRASONIC BACKSCATTER ATTRIBUTED IN: Review of progress in quantitative nondestructive evaluation. TO POROSITY Volume 5A - Proceedings of the Twelfth Annual Review, D. E. YUHAS, C. L. VORRES, and R. ROBERTS (Magnaflux Corp., Williamsburg, VA, June 23-28, 1985 . New York, Plenum Press, Elk Grove Village, IL) IN: Review of progress in quantitative 1986, p. 919-926; Discussion, p. 927. refs nondestructive evaluation. Volume 58 - Proceedings of the Twelfth (Contract W-7405-ENG-82; F33615-82-C-5020) Annual Review. Williamsburg, VA, June 23-28, 1985 . New York, Examples are provided which show how the use of theoretical Plenum Press, 1986, p. 1275-1284. refs models can improve the reliability of electromagnetic NDE. These (Contract W-7405-ENG-82) models can aid in the following: (1) selection of an inspection In the present approach to composite porosity determination method, (2) verification of an NDE method, and (3) development from ultrasonic backscatter data, the insonification of composites and analysis of an inspection plan in terms of probability of at nonperpendicular incident angles reduces specular surface detection data. The present examples refer to the use of the reflection and yields backscatter characteristics that are dependent electric current perturbation probe in the inspection of aircraft on the angular relation between the direction of sound propagation engine components. Recommendations for future model and fiber orientation. Attention is given to the nature of ultrasonic develnpment inch!& sn ins.es!igi!icr: sf !kc right ang]c co:nc: backscatter from cJraphite/e?nYy mmpngitec, nn&r !!?e u.~rl.i:g problem. There is also a need for improved models of the eddy hypothesis that the scattering from porosity may be isotropic relative currentlflaw interaction and their extension to more complex defect to the more directed scattering of the fibers. O.C. shapes. K.K.

A87-10750* National Aeronautics and Space Administration. A87-10791 Langley Research Center, Hampton, Va. ELECTROMAGNETIC METHODS TO DETECT CORROSION IN QUANTITATIVE THERMAL DlFFUSlVlTY MEASUREMENTS OF AIRCRAFT STRUCTURES COMPOSITES S. N. ROWLAND, G. BURKHARDT, and A. S. BlRRlNG (Southwest D. M. HEATH, W. P. WINFREE, J. S. HEYMAN, W. E. MILLER Research Institute, San Antonio, TX) IN: Review of progress in (NASA, Langley Research Center, Hampton, VA), and C. S. WELCH quantitative nondestructive evaluation. Volume 5B - Proceedings (NASA, Langley Research Center: Hamptnn: Cnllege nf Wi!liam n! ?he Tule!!?!? P.r:nua! !?e,ie:.:. ?!i!!ia.msbu:g, \'A, ?i;ns 23-28,:sg5 and Mary, Williamsburg, VA) IN: Review of progress in quantitative . New York, Plenum Press, 1986, p. 1549-1556. refs nondestructive evaluation. Volume 58 - Proceedings of the Twelfth The application of electromagnetic methods to the detection I Annual Review, Williamsburg, VA, June 23-28, 1985 . New York, of corrosion is examined. The operation and capabilities of the I Plenum Press, 1986, p. 1125-1 132. electric current perturbation and remote field eddy current 1 techniques designed to detect and measure corrosion between I A remote radiometric technique for making quantitative thermal I diff usivity measurements is described. The technique was designed layers, and the dark field eddy current method for detecting to make assessments of the structural integrity of large composite corrosion around fasteners are described. Diagrams of the 1 parts, such as wings, and can be performed at field sites. In the corrosion between layers and the three electromagnetic 1 measurement technique, a C02 laser beam is scanned using two experimental arrangements are provided. I.F.

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A87-10867 interferometry, is applicable for determining the turbulence CLEANING METHODS AND PROCEDURES FOR MILITARY frequency spectrum of boundary layers in compressible flow. The OXYGEN EQUIPMENT - INVESTIGATION RESULTS turbulence, in terms of air density fluctuations, is detected by D. W. SCHROLL (USAF. Aeronautical Systems Div., monitoring interferometric fringe phase shifts (in real time) formed Wright-Patterson AFB, OH) IN: Flammability and sensitivity of by one beam which passes through the boundary layer and a materials in oxygen-enriched atmospheres; Proceedings of the reference beam which is outside the boundary layer. This technique Symposium, Washington, DC, April 23. 24, 1985. Volume 2 . is nonintrusive to the flow field unlike other commonly used Philadelphia, PA, American Society for Testing and Materials, 1986, methods such as pitot tube probing and hot-wire anemometry. p. 180-203. refs Model boundary-layerdata are presented at Mach 8 and compared Over the past several years a number of briefings have been with data recorded using other methods during boundary-layer given at the Oxygen Standardization CoordinatingGroup concerning transition from laminar to turbulent flow. Spectra from the BLTD cleaning methods and procedures for military oxygen equipment. reveal the presence of a high-frequency peak during transition, Of particular concern has been the diversity of methods, cleaning which is characteristic of spectra obtained with hot wires. The compounds, and cleanliness criteria that exist in the military and BLTD is described along with operational requirements and industry in the manufacture, shipment, aircraft installation, and limitations. Author maintenance of military oxygen equipment. This is discussed in some depth in this paper. Author A87-11112# MODELING AND ANALYSIS OF THE DYNAMICS OF A DRILL A87- 10898 PENETRATING A THIN PLATE A HIGHER ORDER BEAM ELEMENT FOR VIBRATION OF P. G. REINHALL and D. W. STORTI (Washington, University, BEAMS WITH DISCONTINUITIES Seattle) ASME, Transactions, Journal of Applied Mechanics G. SUBRAMANIAN (Indian Institute of Technology, Madras, India) (ISSN 0021-8936), vol. 53, Sept. 1986, p. 690-694. refs and T. S. BALASUBRAMANIAN (National Aerospace Laboratory, (Contract NSF MEA-84-04862) Bangalore, India) IN: Finite elements in computational mechanics (ASME PAPER 86-WAIAPM-33) - FEICOM '85; Proceedings of the International Conference, A simplified model of the drilling process which is useful in Bombay, India, December 2-6, 1985. Volume 2 . Oxford, Pergamon understanding the problem of noncircular-hole production is Press, 1985, p. 627-634. proposed. The dynamics of a drill penetrating a circular hole in a A higher-order beam element for the analysis of vibration in rigid plate are studied analytically and numerical methods are then beams with step, spring, lumped-mass, or inertial discontinuities is used to include the effects of material removal. It is shown that developed and demonstrated. The element employs four degrees certain drill trajectories which lead to noncircular holes can be of freedom per node (deflection, slope, bending moment, and shear stabilized by material removal. Based on these findings, careful force) and permits treatment of axial-force effects. The numerical drill-speed selection is recommended as a means of minimizing results of applications to problems involving spring-supported the probability of noncircular hole production, and it is pointed out beams, axially loaded discontinuous beams, beams with that even this solution may not be sufficient for the case of very concentrated masses and inertias, a stepped helicopter rotor blade, soft or composite plate materials. Author a model launch vehicle, and a launch-vehicle-model supporting sting are presented in tables. T.K. A87-11113# EFFECT OF TANGENTIAL TORQUE ON THE DYNAMICS OF A87-10900 FLEXIBLE ROTORS NATURAL FREQUENCY ANALYSIS OF PRETWISTED PLATES K. 6. YIM (Sundstrand Corp., Rockford, IL), S. T. NOAH, and J. S. K. SANE, C. S. GURUJEE, A. R. MALPANI, V. N. SHARMA, M. VANCE (Texas A&M University, College Station) ASME, and C. M. P. FERNANDES (Indian Institute of Technology, Bombay, Transactions, Journal of Applied Mechanics (ISSN 0021 -8936), vol. India) IN: Finite elements in computational mechanics - FEICOM 53, Sept. 1986, p. 711-718. refs '85; Proceedings of the International Conference, Bombay, India, (Contract NSF MEA-81-1 5330) December 2-6, 1985. Volume 2 . Oxford, Pergamon Press, 1985, (ASME PAPER 86-WAIAPM-23) p. 655-663. refs The effect of tangential load torque on the dynamics of rotors The vibrational behavior of turret-lathe-pretwisted rectangular has been studied analytically using both cantilevered and pla3s of thickness 5.86, 4.89, 3.16, and 1.47 mm and aspect between-bearing rotor models. External damping, distributed shaft ratio 0.75, 1.OO, 1.50, 2.00, and 2.50 is investigated experimentally mass, and gyroscopic moments are taken into account. A number and analytically. Eight-node isoparametric quadrilateral, 12-node of analytical approaches, including the classical method and a isoparametric, helicoidal (Walker, 1978), and triangular finite modified transfer matrix method have been utilized and they all elements are employed in the analysis, and the results are gave results with excellent agreement. For realistic levels of torque, compared with those obtained by electromagnetic and the major effect is found to be on the whirl stability of the system. electrodynamic excitation of the rigidly clamped plates in tables Stability is found to depend most strongly on the dimensionless and graphs. Superior results are obtained using the 12-node ratio of torque to damping, and on the mode shape. Author isoparametric element (at the cost of more computational work in formulating the stiffness and mass matrices) or the helicoidal A87-11127# element (at the cost of more work at the eigenvalue-evaluation A REDUNDANCY MANAGEMENT PROCEDURE FOR FAULT stage). T.K. DETECTION AND ISOLATION A. RAY (Pennsylvania State University, University Park) and M. A87-10971 DESAI (Charles Stark Draper Laboratory, Inc., Cambridge, MA) A NONPERTURBING BOUNDARY-LAYER TRANSITION ASME, Transactions, Journal of Dynamic Systems, Measurement, DETECTION and Control (ISSN 0022-0434). vol. 108, Sept. 1986, p. 248-254. J. E. OHARE (Calspan Corp.. Arnold Air Force Station, TN) IN: refs High speed photography, videography, and photonics 111; This paper presents the theoretical basis of a novel redundancy Proceedings of the Meeting, San Diego, CA, August 22, 23, 1985 management procedure developed for fault detection and isolation . Bellingham, WA. Society of Photo-Optical Instrumentation (FDI) in strategic processes such as spacecraft, aircraft, and nuclear Engineers, 1985, p. 58-63. plants where multiply-redundant measurements are available for A laser interferometer technique is being applied to the individual variables. The set of redundant measurements may characterization of boundary-layer conditions on models in comprise both direct sensor outputs and analytically derived supersonic and hypersonic wind tunnels in the von Karman Facility measurements. The redundancy management procedure presented at Arnold Engineering Development Center (AEDC). The in this paper is essentially independent of the fault detection Boundary-Layer Transition Detector (BLTD), based on lateral strategy and measurement noise statistics, and builds upon the

46 12 ENGINEERING concept of partitioning the set of measurements into ’consistent’ the conjugate gradient method applied to turbulent flow and ’inconsistent’ subsets for purposes of estimation and fault calculations, and numerical experiments with a total variation isolation, respectively. The proposed procedure is suitable for diminishing MacCormack scheme. Other topics include real-time applications using commercially available microcomputers partially-parabolic calculations of three-dimensional viscous flow and its efficacy has been verified on-line in operating nuclear through turbomachinery cascades, implicit finite-difference reactors. Author simulation of separated hypersonic flow over an indented nosetip, stability of collocation-Chebyschev schemes with application to A87-11336 the Navier-Stokes equations, and numerical experiments with DAMPING OF THE VIBRATIONS OF DEFORMABLE BODIES inviscid vortex-stretched flow around a cranked delta wing. Papers [DEMPFIROVANIE KOLEBANll DEFORMIRUEMYKH TEL] are also presented on large eddy simulation of atmospheric V. V. MATVEEV Kiev, Izdatel’stvo Naukova Dumka, 1985, 264 turbulence, application of patched meshes to viscous and inviscid p. In Russian. refs flows, higher-order flux difference splitting schemes for the Euler Methods for determining the damping characteristics and for equations using upstream interpolations, and the efficient use of describing the mechanical hysteresis of the vibration of deformable vector computers with emphasis on computational fluid dynamics. bodies are examined. The results of a comprehensive study of R.R. the damping properties of a wide class of metal materials and highly stressed structural elements are generalized with allowance A8741503 for production and service related factors. Methods for increasing IMPLICIT AND SEMI-IMPLICIT METHODS FOR THE the reliability of machine elements by reducing the level of COMPRESSIBLE NAVIER-STOKES EQUATIONS vibration-induced stresses are discussed. V.L. M. 0. BRISTEAU (Institut National de Recherche en lnformatique et an Automatique, Rocquencourt, France), B. MANTEL, J. A87-11481# PERIAUX, C. POULETTY (Avions Marcel Dassault Breguet Aviation, A STUDY ON THE AXIALLY CURVED MIXEPFLOW VANELESS Saint-Cloud, France), R. GLOWINSKI (Paris VI, Universite; lnstitut DIFFUSERS National de Recherche en lnformatique et an Automatique. T. SAKAI (Tokyo Science University, Japan), T. AWAI, and T. Rocquencourt, France) et al. IN: Conference on Numerical NAKAGAWA JSME. Bulletin (ISSN 0021-3764), vol. 29, June Methods in Fluid Mechanics, 6th. Goettingen, West Germany, 1986, p. 1759-1764. September 25-27, 1985, Proceedings . Brunswick, West Germany, The flow patterns and pressure-recovery factors (PRFs) of one Friedr. Vieweg und Sohn, 1986, p. 9-22. refs purely conical and three axially curved vaneless diffusers for (Contract DRET-83-403) rnixed-iio;v;u’ &?ermined experimentally at :u;bonachines are SP\.~TI!methods for the numerical simulation of compressible Reynolds numbers 200.000-2:C,!JCO in a test rig including a blower, viscous flows mcde!ed by !he unsteady Navier-Stokes equations two surge tanks, and a rotating screen (imparting swirl to the air and using finite elements are presented. The full Navier-Stokes entering the diffuser). The results are presented in tables, graphs, system and a model obtained by assuming that the total enthalpy and diagrams and characterized in detail. The PRF and is constant are compared using a fully implicit scheme of gear effectiveness of the simple curved diffuser are found to be lower type and splitting operator techniques which decouple the various than those of the conical diffuser, but addition of inner-wall guide physical effects. A direct method based on a cascade of Poisson fences is shown to improve the performance significantly. T.K. problems is used for the generalized Stokes problem, and either highly stable rational Runge-Kutta techniques using dynamic A87-11492# relaxation or quasi-Newton/conjugate gradient algorithms NUMERICAL ANALYSIS WITH GENERALIZED J-INTEGRAL superlinearly convergent are employed to solve the nonlinear M. WANG and L. XU Northwestern Polytechnical University, subproblems. Numerical simulations of two-dimensional transonic Journal, vol. 4, July 1986, p. 297-304. In Chinese, with abstract in and supersonic flows around a NACA0012 airfoil are in good English. refs agreement with available measurements, though stiff test cases A finite element model is presented for obtaining numerical and three-dimensional computations require self-adaptive solutions to a generalized J-integral for structures experiencing refinement procedures to provide sensitive improvement of the complex loading. The stresses can include thermal, body force solution where accuracy is needed. R.R. and external loads singly or in combination. Implementation of the model in a computer prograrr! is demonstrated. along with the outputs of the stresslstrain field, the numerical values of the A87-11522 generalized J-integral, the stress intensity factor, and predictions EXPERIENCES WITH AN UNFACTORED IMPLICIT of the crack extension. The model is useful for predicting the PREDICTOR-CORRECTOR METHOD fatigue life of aircraft engine components and electric generators. W. KORDULLA (DFVLR, lnstitut fr Theoretische M.S.K. Stroemungsmechanik, Goettingen, West Germany) IN: Conference 0:: ?!cmerirs! Methndn in Fluid Mechanics, 6th, Goettingen, West A87-11501 Germany, September 25-27, 1985, Proceedings . Brunswick. West CONFERENCE ON NUMERICAL METHODS IN FLUID Germany, Friedr. Vieweg und Sohn, 1986, p. 185-192. refs MECHANICS, 6TH, GOElTINGEN, WEST GERMANY, A finite volume formulation of MacCormack’s (1985) SEPTEMBER 25-27, 1985, PROCEEDINGS predictor-corrector scheme using flux-splitting for the convection D. RUES, ED. and W. KORDULLA, ED. (DFVLR, lnstitut fuer terms and central differencing for the viscous terms is described Theoretische Stroemungsmechanik, Goettingen, West Germany) which is combined with a relaxation scheme based on the Conference supported by the Gesellschaft fuer angewandte line-Gauss-Seidel method. Results for supercritical flow past a Mathematik und Mechanik, DFG, DFVLR, et al. Brunswick, West RAE2822 airfoil, using a C-type mesh, are presented, and Germany, Friedr. Vieweg und Sohn (Notes on Numerical Fluid second-order accurate spatial discretization was employed to obtain Mechanics. Volume 13), 1986, 418 p. For individual items see accurate results and fast convergence to steady state. No artificial AB7-115UZ IOA67-i i648. numerical diffusion. is employed, and accurate stagnation point Papers are presented on implicit and semiimplicit methods for pressures are found. The Cp-distribution for rne iine rriesii eAbbEi the compressible Navier-Stokes equations, a multigrid oscillations in the region of supersonic flow, and the fine mesh Marker-and-Cell algorithm for three-dimensional flow computation, solution experiences increasing covergence with increasing time solution of the Euler equations for missile configurations, and a step, taking about 2.25 times more time for convergence than finite difference Galerkin method for the solution of the that of the coarse mesh. Good prediction of lift and drag is found Navier-Stokes equations. Also considered are an application of for the coarse mesh solution, while the fine mesh solution is about the two-dimensional time-marching Euler code to transonic 8 and 5 percent off, respectively, in comparison with experimentally turbomachinery flow, a numerical method for vortex sheet roll-up, observed values. R.R.

47 12 ENGINEERING

A87-11792 velocity-distribution measurements were carried out for a model AERONAUTICAL RESEARCH SPIN-OFFS ON THE diffuser with a high resistance coefficient wire gauze. Author DEVELOPMENT OF CIVIL APPLICATIONS FOR ALUMINIUM ALLOYS N. HURET and Y. DE BONY (Cegedur Pechiney, Departement A87-12445 Techniques Avancees, Paris, France) Materiaux et Techniques A REINFORCING BAND NEAR THE FLANGE OF A HEATED (ISSN 0032-6895), vol. 74, May-June 1986, p. 219-225. In English CYLINDRICAL CASING [BANDAZHNOE KOL’TSO U FLANTSA and French. NAGREVAEMOI TSlLlNDRlCHESKOl OBOLOCHKI] Several examples are discussed of the transfer of aeronautical A. G. ZGUROVSKll and I. I. MARINETS Problemy Prochnosti AI metallurgy to civil applications. The development of AI alloys (ISSN 0556-171X), July 1986, p. 70-72. In Russian. refs and forming techniques for aerospace applications is traced from It is shown that by using an additional reinforcing band near WW II to the present, noting the spin-off of heavy plate shaping the flange of a cyclindrical casing heated by internal gas flow, it technologies to use in high speed presses and casings for injection is possible to reduce the thermal stresses in the casing due to a molding machines. Techniques employed to produce cold rigid flange to the level of stresses produced by reinforcing precision-drawn AI tubes employed in the Airbus 300 have found bands. The stress-reducing effect of such a band is demonstrated applications as lightweight structural elements in a hang glider, with reference to an exhaust pipe of an aircraft power plant. for bow arrows, and for other sporting goods. M.S.K. V.L.

~87-1iaoo A87-12648 AVIONICS IN THE SUB-MICROSCOPIC WORLD HIGH SPEED FLOW VISUALISATION J. RHEA lnteravia (ISSN 0020-5168), vol. 41, Aug. 1986, p. 907, P. J. BRYANSTON-CROSS (Warwick, University, Coventry, 908. 91 1, 912. England) Progress in Aerospace Sciences (ISSN 0376-0421). The development of very high-speed integrated circuits vol. 23, no. 2, 1986, p. 85-104. refs (VHSICs) is considered. The reduced feature size of these circuits Three whole-field instantaneous flow visualization methods are results in less weight, volume, and power, and therefore increased reviewed. Laser fluorescence and pulsar laser velocimetry are very performance for radars, and electronic countermeasure systems. briefly considered, while holographic interferometry is treated in The use of VHSlCs in operational weapon system and the detail. This method, its theory, and its applicability to both application of a high-speed circuit to an airborne signal processor two-dimensional and three-dimensional visualization are are examined. The formation of submicron ’super chips’ which summarized, and its applications to three-dimensional visualization will operate at speeds of 50-100 MHz and be 1-1/2 inches on of a rotating compressor, an annular turbine cascade EPFL, and the side is analyzed. The use of technology to develop GaAs radial turbomachinery are examined. Its utilization in the microwave/millimeter wave integrated circuits which will have two-dimensional holographic visualization of transonic flow, in gigahertz operating speed capabilities and reduced size is two-dimensional steam turbine base flow research, and in described. These circuits increase the central processing power will visualizing structures within the boundary layer is addressed. of weapons systems; various applications for these ICs are C.D. proposed. Research in the area of ultrapure crystal growth in space is discussed. I.F. A87-12656 ~87-11a43 HOW TO MAINTAIN A CONSISTENT QUALITY IN YOUR AUTOMATICALLY WOVEN THREE-DIRECTIONAL COMPOSITE BONDING PROCESS? STRUCTURES G. CARLSSON (SAAB-Scania AB, Linkoping, Sweden) IN: P. S. BRUNO, D. 0. KEITH, and A. A. VICARIO, JR. (Hercules Progress in advanced materials and processes: Durability, reliability Aerospace Co., Magna, UT) SAMPE Quarterly (ISSN 0036-0821), and quality control; Proceedings of the Sixth International European VOI. 17, July 1986, p. 10-17. SAMPE Conference, Scheveningen. Netherlands, May 28-30, 1985 Three-directional (3-D) fiber reinforced composites were . Amsterdam and New York, Elsevier, 1985, p. 61-70. demonstrated with advantages for certain missile and space Bonding of aircraft structures brings a lot of problems to the structures. The applications range from carbon-carbon (c-c) to manufacturer. The nature of adhesives and the bonding processes’ carbon-epoxy structures. Three-D carbon fiber preforms were sensitivity to humidity, temperature, and contamination make it woven using automated techniques developed by Aerospatiale of necessary to keep all parameters in the process under close France and then impregnated and processed into c-c or control, and eliminate as many possibilities of random deviations carbon-epoxy structures. Demonstrated structures include c-c ITEs as possible. This paper describes one approach to the problem, and exit cones for rocket nozzles and carbon-epoxy adapter rings showing an automated line for surface treatment and a for rocket cases. Other potential applications, including satellite through-transmissionultrasonic tester for a 100-percent inspection truss joints and meteroid impact shields for Space Station of all bonded areas. Author components, are identified. Advantages of these structures include automated fabrication, improved mechanical properties, and greater raliability. Author A87-12894 THE POSSIBILITY OF THE NONDISTURBING MOTION OF A A87-12133# BODY IN A FLUID [O VOZMOZHNOSTI EXPANSION OF FLOW DUE TO RESISTANCE OF A WIRE NEVOZMUSHCHAIUSHCHEGO DVlZHENllA TELA V GAUZE PLACED IN A PARALLEL-SIDED CHANNEL ZHIDKOSTI] A. IT0 Japan Society for Aeronautical and Space Sciences, V. I. MERKULOV (AN SSSR, lnstitut Teoreticheskoi i Prikladnoi Journal (ISSN 0021-4663), vol. 34, June 1986, p. 308-315. In Mekhaniki, Novosibirsk, USSR) Akademiia Nauk SSSR,Sibirskoe Japanese, with abstract in English. refs Otdelenie, Izvestiia, Seriia Tekhnicheskie Nauki (ISSN 0002-3434), This paper describes the analytical and experimental study of June 1986, p. 37-44. In Russian. flow expansion due to the resistance of a wire gauze placed in a The body shape and the control actions resulting in zero parallel-sided channel. First, Taylor’s source model was improved perturbations beyond the limits of the control surface are by introducing source-strength correction, and flow profiles and determined analytically, and it is shown that such conditions are drag coefficients were calculated for various gauze heights. Next, satisfied for some doubly connected systems. In this case, control measurements were also made on flow profiles and drag is reduced to vortex generation on part of the control surface. coefficients for resistance coefficients up to 20 in a smoke The required vortex sheet can be provided by wings that flap in wind-tunnel. Consequently, agreement between calculated and accordance with a certain law. The motion of such bodies near a measured values was obtained. Furthermore, flow observation and free surface does not produce waves or wave drag. V.L.

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A87-13003# turbomachine flow, and the various assumptions made, are first COMPUTER INTEGRATED MANUFACTURING considered, following which the increased role of experimental R. C. BECKETT (Commonwealth Aircraft Corp., Ltd., Melbourne, studies due to the introduction of such techniques as laser Australia) IN: Joint National Symposium on the Influence of anemometry is discussed. Examples of the interaction of these Aviation on Engineering and the Future of Aeronautics in Australia, approaches are given including the general numerical solution of Melbourne, Australia, August 8, 9, 1985, Preprints . Barton, the inviscid equations of motion (Stuart and Heatherington, 1974), Australia/Brookfield, VT, Institution of Engineers/Brookfield the development of actuator-disk theory and its stimulation of the Publishing Co., 1985, p. 5-12. detailed measurement of the flow within turbomachines, and the Attention is given to a proprietary system for computer-based observation of a large free area of separated flow in the flow design, manufacturing, quality control and production control. The through compressor cascades at high incidence leading to six areas of computerized process application encompass airframe analytical approaches assuming a free streamline. R.R. manufacturing, airframe modification and repair, engineering design and development, aircraft engine component manufacturing, gas A87-13026 turbine assembly/testing and repairloverhaul, and high technology RESONANT AND NON-RESONANT ACOUSTIC PROPERTIES OF foundry operations. It is noted that increased use of computer ELASTIC PANELS. I - THE RADIATION PROBLEM control results in businesses’ greater capital intensiveness, with F. G. LEPPINGTON, E. G. BROADBENT (Imperial College of computer systems that have a shorter effective economic life than Science and Technology, London, England), K. H. HERON, and has been historically typical. O.C. S. M. MEAD (Royal Aircraft Establishment, Farnborough, England) Royal Society (London), Proceedings, Series A - Mathematical A87-13007# and Physical Sciences (ISSN 0080-4630), vol. 406, no. 1831, Aug. ADVANCES IN THE VIBRATION MONITORING OF GEARS AND 8, 1986, p. 139-171. refs ROLLING ELEMENT BEARINGS An elastic panel is excited by a time harmonic force and the P. D. MCFADDEN (Department of Defence, Aeronautical Research power flow is calculated, averaged over a frequency band and all Laboratories, Melbourne, Australia) IN: Joint National Symposium source positions. The two-dimensional problem is investigated on the Influence of Aviation on Engineering and the Future of asymptotically, for frequencies that are sufficiently high to ensure Aeronautics in Australia, Melbourne, Australia, August 8, 9, 1985, that many panel modes are near resonance. The asymptotic results Preprints . Barton, Australia/Brookfield, VT, Institution of are different according as the frequency is above or below the EngineerslBrookfield Publishing Co., 1985, p. 27-32. coincidence value; in the latter case account has to be taken of The early detection of failure in mechanical systems is presently both resonance and nonresonance contributions to the power flow. approached from the viewpoint of a recently gained understanding A transition formula is given fnr frequencies near rcinsldence and c?! !he vibrcition geneis:& bi ii%kig eieiiiefii bearings ihai coniain the results agree we!! with numerica! calculations. Corresponding spalling defects as weli as by gears with fatigue cracks. A defect‘s results are given for the three-dimensional problem of the impact excites resonances that can be detected by a transducer rectangular panel and previous theory is justifed and extended. mounted on the casing of the mechanism; bandpass filtering of Author the signal allows one of the resonances to be isolated and demodulated, leaving a train of impulses caused by the impacts. Although this technique has been developed for close monitoring N87-10016# Tokyo Univ. (Japan). Inst. of Space and of aircraft propulsion systems, it is applicable to other mechanical Astronautical Science. systems. O.C. STUDY OF THREE-DIMENSIONAL SEPARATION ON A SPHEROID AT INCIDENCE A87-13011# Y. ISHU and Y. OSHIMA (Ochanomizu Women’s Univ., Tokyo STRUCTURAL DESIGN WITH NEW MATERIALS (Japan).) ln its Proceedings of the Symposium on Mechanics for B. C. HOSKIN (Department of Defence, Aeronautical Research Space Flight, 1985 9 p 1985 Laboratories, Melbourne, Australia) IN: Joint National Symposium Avail: NTlS HC A12/MF A01 on the Influence of Aviation on Engineering and the Future of Experimental observation of flow separation on a spheroid at Aeronautics in Australia, Melbourne, Australia, August 8, 9. 1985, various angles of attack was carried out in low Reynolds number Preprints . Barton, Australia/Brookfield, VT, Institution of flow using a water channel by flow visualization method. Color oil Engineers/Brookfield Publishing Co., 1985, p. 44-47. refs method was adapted to make the surface separation pattern visible, Attention is given !c the developmerit status of the advanced and hpdrcgen bubble method was effective for visuaiization of the structural design methods which complement state-of-the-art flow field around the model. The results support the lightweight materials’ use in aircraft primary structures. The ways three-dimensional separation criteria proposed by Maskell. Wang, in which the introduction of fiber-reinforced polymer matrix and Han and Patel. and mechanism of the flow interaction with composites has affected airframe structure design and analysis the longitudinal vortices along the body surface is made clear. procedures are characterized. Attention is given to sinole-ply Airthnr mecaanics, symmetric, orthotropic and quasi-orthotropic laminate properties, the laminate stress-strain law, and such in-service N87-10029# Tokyo Univ. (Japan). Inst. of Space and composite structure factors as environmental effects, near-invisible Astronautical Science. impact damage, and fatigue. O.C. REPORT OF THE INTERNATIONAL SYMPOSIUM ON COMPUTATIONAL FLUID DYNAMICS, TOKYO A87-13015# K. OSHIMA /n its Proceedings of the Symposium on Mechanics THE BALANCE BETWEEN THEORETICAL, COMPUTATIONAL for Space Flight, 1985 8 p 1985 AND EXPERIMENTAL WORK IN TURBOMACHINES Avail: NTlS HC A12/MF A01 J. H. HORLOCK (Open University, Milton Keynes, England) IN: The International Symposium on Computational Fluid Joint National Symposium on the Influence of Aviation on Dynamics-Tokyo was held on Sept. 9 thru 12, 1985 at Kenchiku Engineering and the Future of Aeronautics in Australia, Melbourne, Kaikan of Tokyo. Based on the recnmmend?!iny! give!? h;~ !he Ausiraiia, August e, 9, 1985, Supplementary Papers . Barton, International Advisory Committee Members a few distinguished CFD Australia/Brookfield, VT, Institution of Engineers/Brookfield scientists were asked to present a review paper on each specialized Publishing Co., 1985, p. 1-13. refs field, and 23 out of them were able to accept the invitation. They The interrelation between theoretical, computational and were noted as INVITED on the Program. Total of 97 abstracts of experimental work in turbomachine flow is discussed, including contributed papers were submitted, and, based on referee reports both work related to the flow description of an existing machine, made by all the International Advisory Committee Members, 75 of and work in the design of a high efficiency machine. The them were accepted for presentation. Out of these 98 papers development of theoretical and computational methods in including the invited ones, 35 came from USA, 28 from Japan

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and 35 from rest of the world. All of these papers are listed. N87-10400*# Boeing Commercial Airplane Co., Seattle, Wash. E.R. FAULT TOLERANT CONTROL LAWS Final Report U. L. LY and J. K. HO 1986 113 p N87-10244 Pennsylvania State Univ., University Park. (Contract NASl-17635) AN EXPERIMENTAL INVESTIGATION OF END-WALL (NASA-CR-178094; NAS 1.26:178094) Avail: NTlS HC AO6/MF FLOWFIELD OF A COMPRESSOR ROTOR Ph.D. Thesis A01 CSCL 140 K. N. SACHIDANANDAMURTHY 1985 266 p A systematic procedure for the synthesis of fault tolerant control Avail: Univ. Microfilms Order No. DA8606379 laws to actuator failure has been presented. Two design methods An investigation of the end-wall flowfield in a single-stage were used to synthesize fault toleiant controllers: the conventional compressor rotor is presented. The main emphasis of the LQ design method and a direct feedback controller design method investigation was to measure the flowfield in detail in a low-speed SANDY. The latter method is used primarily to streamline the compressor rotor. A single-channellaser Doppler velocimeter (LDV) full-state Q feedback design into a practical implementable output was used to measure the flowfield in the tip clearance region. feedback controller structure. To achieve robustness to control The investigation was carried out for two tip clearances actuator failure, the redundant surfaces are properly balanced (clearance/chord = 1.78 arid 3.4 percent). In addition, the relative according to their control effectiveness. A simple gain schedule stagnation pressure field, corresponding to a tip clearance of 1.78 based on the landing gear up/down logic involving only three percent, was also measured using a Kiel probe to supplement the gains was developed to handle three design flight conditions: Mach LDV measurement. The measurements showed that the leakage .25 and Mach .60 at 5000 ft and Mach .90 at 20,000 ft. The fault flow originated at about one-quarter-chord location. Past tolerant control law developed in this study provides good stability quarter-chord location, the inteaction between the leakage flow augmentation and performance for the relaxed static stability and the annulus-wall boundary layer resulted in unconventional aircraft. The augmented aircraft responses are found to be invariant and skewed boundary layer profiles. Inside the rotor passage, the to the presence of a failure. Furthermore, single-loop stability leakage flow effects were augmented by the leakage flow margins of +6 dB in gain and +30 deg in phase were achieved emanating from the entire blade chord length. Downstream of the along with -40 dB/decade rolloff at high frequency. Author rotor, the interaction between the leakage flow and the rotor wake resulted in rapid wake decay at higher radii. The leakage flow N87-10404# National Aeronautical Lab., Bangalore (India). which was intense at larger clearance might have rapidly smoothed Structures Div. the irregularities downstream of the rotor. EFFECT OF STATIC INPLANE LOADS AND BOUNDARY CONDITIONS ON THE FLUTTER OF FLAT RECTANGULAR N87-10262 Iowa State Univ. of Science and Technology, Ames. PANELS APPLICATION OF A POTENTIAL CODE TO GENERAL STEADY A. JOSH1 and B. R. SOMASHEKAR Feb. 1986 38 p FLOWS IN THREE DIMENSIONS Ph.D. Thesis (NAL-TM-ST-8604) Avail: NTlS HC AO3/MF A01 A. A. RANGWALLA 1986 88 p Presented are investigations of the problem of flutter of initially Avail: Univ. Microfilms Order No. DAB615078 stressed rectangular panels having various types of boundary A low order panel method is described for the calculation of conditions including the elastic end restraint. Using the Galerkins incompressible unsteady inviscid flow over general configurations. modal analysis technique the solutions are obtained for various The numerical method is based upon piecewise constant doublet cases of panel aspect ratio, thickness ratio, and elastic stiff ness and source distributions. The wake and the geometry of the body of the support. The results show that the flutter mode is primarily are made to evolve with time. The unperturbed flow is chosen as determined by the first and the second vibration modes. The results the internal Dirichlet boundary condition and the source distribution also show that the effect of elastic end can be reasonably is determined by the external Neumann boundary condition. The accurately modelled by simple closed form analytical expressions. application of the Kutta condition for this formulation is Author straightforward. Two cases are examined. One is the impulsive start of a finite rectangular wing and the other is the interference N87-10405# British Aerospace Aircraft Group, Weybridge between a propeller and a wing. The development of the circulation (England). Structures Dept. near the root for the first case is compared with the theoretical THE EFFECTS OF TEMPERATURE AND LOADING RATE ON solution of an impulsively started two dimensional flat plate. The R-CURVES USING THE CLWL TECHNIQUES numerical results are very well behaved. The results for the S. NOWAK Jul. 1985 66 p interference between a propeller and a wing did conform with (Contract A93B/1391) physical expectations. Also, this case is sufficiently general and (BAE-MSM-R-GEN-0544; BR97093; ETN-86-97946) Avail: NTlS has many aerodynamic features that either have not been solved HC A04/MF A01 or were solved for special cases. Dissert. Abstr. The effects on crack growth resistance curves of typical aircraft temperature and loading rate variations were investigated. The N87-10391*# National Aeronautics and Space Administration. crack line wedge loaded specimen was used and 2 aluminum Lewis Research Center, Cleveland, Ohio. alloys, specifications 7475T761 and BSL72 were considered. It is TESTING OF UH-GOA HELICOPTER TRANSMISSION IN NASA found that at low temperature or high strain rates the resistance LEWIS 2240-KW (3000-HP) FACILITY to crack growth of 7475T61 is considerably reduced, whereas A. M. MITCHELL, F. B. OSWALD, and H. H. COE Aug. 1986 that of BSL72 benefits slightly. The combined effect of low 30 P temperature and high strain rates is shown to further increase the (NASA-TP-2626; E-2941; NAS 1.60:2626) Avail: NTlS HC difference between the two alloys. ESA A03/MF A01 CSCL 131 The US. Army’s UH-GOA Black Hawk 2240-kW (3000-hp) class, N87-11017# Deutsche Forschungs- und Versuchsanstalt fuer twin-engine helicopter transmission was tested at the NASA Lewis Luft- und Raumfahrt, Goettingen (West Germany). Inst. fuer Research Center. The vibration and efficiency test results will be Theoretische Stroemungsmechanik. used to enhance the data base for similar-class helicopters. Most ADVANCED METHOD FOR COMPUTING THE FLOW AROUND of the data were obtained for a matrix of test conditions of 50 to WINGS WITH REAR SEPARATION AND GROUND EFFECT 100 percent of rated rotor speed and 20 to 100 percent of rated K. JACOB Jan. 1986 65 p input power. The transmission’s mechanical efficiency at 100 (DFVLR-FB-86-17;ISSN-017-1342; ETN-86-98276) Avail: NTlS percent of rated power was 97.3 and 97.5 percent with its inlet HC A04/MF A01; DFVLR, Cologne, West Germany DM 21 50 oil maintained at 355 and 372 K (180 and 210 F), respectively. A method for computing the subsonic flow around wings with The highest vibration reading was 72 g’s rms at the upper housing moderate to high aspect ratio and low sweep at high angles of side wall. Other vibration levels measured near the gear meshes attack was improved by introducing the curved basic flow concept. are reported. Author It was extended to include the ground effect by utilizing the reflected

50 12 ENGINEERING image concept. The state of the art is presented, and theoretical conceptual design, preliminary testing to resolve problem areas, results are compared with measurements. Conclusions concerning prototype design and fabrication, and rig testing. Successful tests the scope of the method are drawn. ESA were completed with the viewing system in the laboratory. in a high pressure combustor rig, and on a Pratt and Whitney PW20307 N87-1l020# Rolls-Royce Ltd., Derby (England). jet engine. Both film and video recordings were made during the NET SHAPE FORMING: THE ROUTE TO LOW COST tests. Digital image analysis techniques were used to enhance COMPONENTS. THE VIEW POINT OF THE AEROSPACE images and bring out special effects. The use of pulsed laser INDUSTRY illumination was also demonstrated as a means for observing liner J. A. MOORE 6 Mar. 1986 25 p Presented at Institution of surfaces in the presence of luminous flame. Author Production Engineers Seminar, London, England, 21 Nov. 1985 (PNR-90306; ETN-86-98017) Avail: NTlS HC A02/MF A01 Aerospace products which give the most benefit from Nett and near Nett purchases, and where it is recognised that even N87-11149# Deutsche Forschungs- und Versuchsanstalt fuer though their volume may be low their value is extremely light, are Luft- und Raumfahrt, Brunswick (West Germany). Abteilung fuer discussed. Turbine blades, nozzle guide vanes, casings, rings, Flugversuchstechnik. fabrications, and major rotating components are cited. ESA DIGITAL DATA RECORDING ON FLOPPY DISKS APPLIED FOR ON-BOARD USE IN HELICOPTERS N87-11128# Air Force Armament Lab., Eglin AFB, Fla. R. HOLLAND, H. MEYER, and P. PFLEGING May 1986 37 p THREE-DIMENSIONAL UNSTEADY EULER EQUATIONS In GERMAN; ENGLISH summary SOLUTIONS ON DYNAMIC GRIDS Final Technical Report, Jan. (DFVLR-MITT-86-10; ISSN-0176-7739; ETN-86-98178) Avail: - Jun. 1985 NTlS HC AOS/MF A01; DFVLR, Cologne, West Germany DM D. M. BELK, J. M. JANUS, and D. L. WHITFIELD Apr. 1986 16.50 30 P A direct data recording system for helicopter flight tests was (AD-A168041 ; AD-E801301 ; AFATL-TR-86-21) Avail: NTlS HC developed. The system stores the flight test data in an onboard AOWMF A01 CSCL 20D mass memory. It fulfills the requirements imposed by the high A method is presented for solving the three-dimensional vibration level of helicopters, and by the limited space and weight unsteady Euler equations on dynamic grids based on flux vector possibilities. Hardware configuration, software, and terminal are splitting. The equations are cast in curvilinear coordinates and a described. The system can be easily built and used. Comparisons finite volume discretization is used for handling arbitrary geometries. with analog data recording shows an improvement of data quality. The discretized equations are solved using an explicit upwind ESA second-order predictor corrector scheme that is stable for a CFL of 2. Characteristic variable boundary conditions are developed and used for unsteady impermeable surfaces and for the far-field boundary. Dynamic-grid results are presented for an oscillating N87-11175 Cirrus Computers Ltd., Fareham (England). airfoil and for a store separating from a reflection plate. For the INVESTIGATION OF OPTIMAL COMPLEXITY OF BITE AND ITS cases considered of stores separating from a reflection plate, the EFFECTS ON RELIABILITY, MAINTAINABILITY, MONITORING unsteady aerodynamic forces on the store are significantly different AND FAULT PREDICTION from forces obtained by steady-state aerodynamics with the body W. R. MOORE and R. I. DAMPER Mar. 1984 47 p inclination angle changed to account for plunge velocity. GRA (ETN-86-97976) Avail: Issuing Activity The application of Built-in-Test (BIT) techniques in the N87-11129# Air Force Academy, Colo. Research Lab. maintenance of military and aircraft electronic systems is reviewed. VISUALIZATION OF THREE-DIMENSIONAL FORCED Despite the relative ease with which BIT can be added, and the UNSTEADY SEPARATED FLOW apparently good performance claimed by designers, there are clear M. ROBINSON, H. HELIN, F. GILLIAM, J. RUSSELL, and J. indications that BIT very often fails in practice in its aims of easy WALKER 1986 11 p maintainability with lowskilled labor. A particular problem is the (AD-A168939; FJSRL-TJ-86-0007) Avail: NTlS HC A02/MF A01 rate of false-alarms, where fault-free units are removed CSCL 20D unnecessarily and there is evidence that the overall maintenance Three-dimensional unsteady flow separation was visualized for costs could be lower with less scphisticated BIT. The optimum a semi-infinite span wing pitched upward at a constant rate from level of BIT is, however, very difficult to predict and a convincing 0 to 60 deg angles of attack. Initially, many of the same complex case can be made for the BIT specification to be developed in flow perturbations. including the formation of leading and trailing an interactive way throughout the course of design, development, edge vortices observed from two-dimensional flow separation were commissioning and field operation, in the light of the available ~~,-,-,&~i-,fifi~i~wing, :he Jl-... JL-14 tame fi wthar evi&rli, "sillY IIV.. 4Irl" .. U" .". ...-. technoloav and of the whole maintenance strategy. Against this complicated by a wing tip vortex that developed orthogonal to the background, BIT deployment is seen as much a management separation induced leading and trailing edge vortices. The tip flow problem, as a technical one. ESA distorted the development of the initially two-dimensional inboard, leading edge vortex. The simple pitching motion history permitted resolution of the development of individual vortices as a function of airfoil motion parameters. Also, vortex-vortex interactions were N87-11179'# Vigyan Research Associates, Inc., Hampton, Va. examined between separation-induced vortices and wingtip STRESS ANALYSIS OF PATHFINDER-2 MODELS Final Report, vortices. The interactions were characterized for time periods that 28 Feb. 1980 - 30 Jun. 1984 extended well beyond the actual pitching motions. Author (GRA) S. C. MEHROTRA and C. T. L. MILLS Oct. 1984 39 p (Contract NASI-16114) Ne?-! !!44*# Qni!ed Technnlnnies Corp.. East Hartford. Conn. (NASA-CR-172458; NAS 1.26:172458) Avail: NTlS HC AO3/MF HOT SECTION VIEWING SYSTEM A01 CSCL 20K W. W. MOREY Sep. 1984 141 p Stress analysis of the Pathfinder 2 fighter model was performed (Contract NAS3-23156) to determine a method for leading- and trailing-edge attachment (NASA-CR-174773; NAS 1.26:174773; R84-925830-33) Avail: that gives acceptable stress levels. Structural modeling of the NTlS HC A07/MF A01 CSCL 148 wing was done using the finite element code SPAR. For the models This report covers the development and testing of a prototype studied, one ordinary lap joint was found to be satisfactory for the combustor viewing system. The system allows one to see and leading-edge flap, however, the alternating surface segmented lap record images from the inside of an operating gas turbine joint method fo attachment was necessary for the trailing-edge combustor. The program proceeded through planned phases of flap to obtain acceptable stress levels. Author

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N87-11180'# National Aeronautics and Space Administration. heat flux on airfoils in areas of strong non-one-dimensional flow Lewis Research Center, Cleveland, Ohio. were also identified. B.G. TURBINE ENGINE HOT SECTION TECHNOLOGY, 1984 Oct. 1984 400 p Conference held in Cleveland, Ohio, 23-24 N87-11187*# National Aeronautics and Space Administration. Oct. 1984 Lewis Research Center, Cleveland, Ohio. (NASA-CP-2339; E-2267; NAS 1.55:2339) Avail: NTlS HC LASER ANEMOMETERS OF HOT-SECTION APPLICATIONS A1 7/MF A01 CSCL 20K R. G. SEASHOLTZ, L. G. OBERLE. and D. H. WEIKLE ln its Presentations were made concerning the hot section Turbine Engine Hot Section Technology, 1984 11 p Oct. 1984 environment and behavior of combustion liners, turbine blades, Avail: NTlS HC A17/MF A01 CSCL 148 and waves. The presentations were divided into six sessions: Laser anemometers are being developed for use in the turbine instrumentation, combustion, turbine heat transfer, structural facilities at Lewis that are involved in the Turbine Engine Hot analysis, fatigue and fracture, and surface properties. The principal Section Technology Program. The status of the program is given objective of each session was to disseminate research results to along with some results accomplished since 1983. B.G. date, along with future plans. Topics discussed included modeling of thermal and fluid flow phenomena, structural analysis, fatigue N87-11188'# United Technoloaies- Research Center, East and fracture, surface protective coatings, constitutive behavior, Hartford, Conn. stress-strain response, and life prediction methods. HIGH TEMPERATURE STATIC STRAIN GAGE PROGRAM C. HULSE, R BAILEY, and H. GRANT (Pratt and Whitney Aircraft, N87-11183'# National Aeronautics and Space Administration. East Hartford, Conn.) In NASA. Lewis Research Center Turbine Lewis Research Center, Cleveland, Ohio. Engine Hot Section Technology, 1984 6 p Oct. 1984 FATIGUE AND FRACTURE: OVERVIEW Avail: NTlS HC A17/MF A01 CSCL 148 G. R. HALFORD ln its Turbine Engine Hot Section Technology, Development of electrical resistance strain gages for static strain 1984 4 p Oct. 1984 measurements of nickel or cobalt superalloy parts inside a gas Avail: NTlS HC A17/MF A01 CSCL 20K turbine engine on a test stand was inititated. Measurements of A brief overview of the status of the fatigue and fracture this type are of great importance because without reliable programs is given. The programs involve the development of knowledge of the stresses and strains which exist in specific appropriate analytic material behavior models for cyclic components, it will be difficult to fully appreciate where stress-strain-temperature-time/cyclic crack initiation, and cyclic improvements in design and materials can be implemented. The crack propagation. The underlying thrust of these programs is the first part of this effort consists of a strain gage alloy development development and verification of workable engineering methods for program which will be followed by an investigation of complete the calculation, in advance of service, of the local cyclic strain gage systems. Efforts to date are summarized. B.G. stress-strain response at the critical life governing location in hot section compounds, and the resultant crack initiation and crack N87-11189'# National Aeronautics and Space Administration. growth lifetimes. B.G. Lewis Research Center, Cleveland, Ohio. EVALUATION RESULTS OF THE 700 DEG C CHINESE STRAIN N87-11184'# National Aeronautics and Space Administration. GAGES Lewis Research Center, Cleveland, Ohio. H. F. HOBART ln its Turbine Engine Hot Section Technology, HOST TURBINE HEAT TRANSFER OVERVIEW 1984 8 p Oct. 1984 J. E. ROHDE ln its Turbine Engine Hot Section Technology, Avail: NTlS HC A17/MF A01 CSCL 148 1984 6 p Oct. 1984 There is a continuing interest and need for resistance strain Avail: NTlS HC A17/MF A01 CSCL 20D gages capable of making static strain measurements on Improved methods of predicting airfoil local metal temperatures components located in the hot section of gas turbine engines. A require advances in the understanding of the physics and methods paper by Tsen-tai Wu describes the development and evaluation of analytically predicting the following four aerothermal loads: hot of high temperature gauges fabricated from specially developed gas flow over airfoils, heat transfer rates on the gas-side of airfoils, Fe-Cr-AI-V-Ti-Y alloy wire. Several of these gages and a quantity cooling air flow inside airfoils, and heat transfer rates on the of P12-2 ceramic adhesive were purchased for evaluation. Nine coolant-side of airfoils. A systematic building block research members of the aircraft turbine engine community were invited to approach is being pursued to investigate these four areas of participate in an evaluation of these gages. Each participant was concern from both the experimental and analytical sides. sent one strain gage, a small amount of ceramic adhesive, Experimental approaches being pursued start with fundamental instructions for mounting the gage on a test beam, and a set of experiments using simple shapes and flat plates in wind tunnels, suggestions for the experiment. Data on gage factor variation with progress to more realistic cold and hot cascade tests using airfoils, temperature, apparent strain, and drift are discussed. Author continue to progress in large low-speed rigs and turbines and warm turbines, and finally, combine all the interactive effects in N87-11199*# Pratt and Whitney Aircraft, East Hartford, Conn. tests using real engines or real engine type turbine rigs. Analytical THERMAL BARRIER COATING LIFE PREDICTION MODEL approaches being pursued also build from relatively simple steady DEVELOPMENT two dimensional inviscid flow and boundary layer heat transfer J. DEMASI and K. SHEFFLER ln NASA. Lewis Research Center codes to more advanced steady two and three dimensional viscous Turbine Engine Hot Section Technology, 1984 10 p Oct. 1984 flow and heat transfer codes. These advanced codes provide more Avail: NTlS HC A17/MF A01 CSCL 14D physics to model better the interactive effects and the true The objective of this program is to develop an integrated life real-engine environment. Author prediction model accounting for all potential life-limiting Thermal Barrier Coating (TBC) degradation and failure modes including N87-11186"# Pratt and Whitney Aircraft, East Hartford, Conn. spallation resulting from cyclic thermal stress, oxidative degradation, DEVELOPMENT OF HEAT FLUX SENSORS IN TURBINE hot corrosion, erosion, and foreign object damage (FOD). The AIRFOILS mechanisms and relative importance of the various degradation W. H. ATKINSON and R. R. STRANGE ln NASA. Lewis Research and failure modes will be determined, and the methodology to Center Turbine Engine Hot Section Technology, 1984 10 p Oct. predict predominant mode failure life in turbine airfoil application 1984 will be developed and verified. An empirically based correlative Avail: NTlS HC A17/MF A01 CSCL 14B model relating coating life to parametrically expressed driving forces The objective is to develop heat flux sensors suitable for use such as temperature and stress will be employed. The two-layer on turbine airfoils and to verify the operation of the heat flux TBC system being investigated, designated PWA264, currently is measurement techniques through laboratory experiments. The in commercial aircraft revenue service. It consists of an inner low requirements for a program to investigate the measurement of pressure chamber plasma-sprayed NiCoCrAlY metallic bond coat

52 underlayer (4 to 6 mils) and an outer air plasma-sprayed 7 w/o experimental measurements. Available P-l integrals were reviewed Y203-ZrO2 (8 to 12 mils) ceramic top layer. B.G. and the best approaches are being programmed into a finite element post processor for eventual comparison with experimental N87-11202'# Garrett Corp., Phoenix, Ariz. data. The experimental data will include cyclic crack growth tests NASA DILUTION JET MIXING, PHASE 3 under thermomechanical conditions, and, additionally, thermal R. SRINIVASAN, G. MYERS, and C. WHITE In NASA. Lewis gradients. B.G. Research Center Turbine Engine Hot Section Technology, 1984 11 p Oct. 1984 N87-11217'# Connecticut Univ., Storrs. Avail: NTlS HC A17/MF A01 CSCL 200 BIAXIAL CONSTITUTIVE EQUATION DEVELOPMENT Many of the gas turbine combustors in operation use multiple E. H. JORDAN and K. P. WALKER In NASA. Lewis Research rows of dilution jets, and some have geometries that are different Center Turbine Engine Hot Section Technology, 1984 7 p Oct. from circular holes. The data base available in literature is generally 1984 applicable to a single row of circular holes. Tests were performed Avail: NTlS HC A17IMF A01 CSCL 20K with uniform mainstream conditions for several orifice plate In developing the constitutive equations an interdisciplinary configurations. Temperature and pressure measurements were approach is being pursued. Specifically, both metallurgical and made in the test section at 4 axial and 11 transverse stations. continuum mechanics considerations are recognized in the These measurements were made with a 60-element rake probe. formulation. Experiments will be utilized to both explore general Test results for some of these cases are discussed. B.G. qualitative features of the material behavior that needs to be modeled and to provide a means of assessing the validity of the N87-11206*# General Electric Co., Fairfield, Conn. Aircraft equations being developed. The model under development explicitly Engine Business Group. recognizes crystallographic slip on the individual slip systems. This THE 3D INELASTIC ANALYSIS METHODS FOR HOT SECTION makes possible direct representation of specific slip system COMPONENTS phenomena. The present constitutive formulation takes the M. L. ROBERTS, R. L. MCKNIGHT, L. T. DAME, and P. C. CHEN anisotropic creep theory and incorporates two state variables into In NASA. Lewis Research Center Turbine Engine Hot Section the model to account for the effect of prior inelastic deformation Technology, 1984 3 p Oct. 1984 history on the current rate-dependent response of the material. Avail: NTlS HC A17/MF A01 CSCL 200 B.G. Advanced 3-D inelastic structuraVstress analysis methods and solution strategies for more accurate and yet more cost-effective N87-11221"# United Technologies Research Center, East analysis of combustors, turbine biaaes. and Vaiies aie being Hirtf~rd,Conn developed. The approach is to develop four different theories, MEASUREMENT OF AIRFOIL HEAT TRANSFER COEFFICIENTS one linear and three higher order with increasing complexities ON A TURBINE STAGE including embedded singularities. Progress in each area is R. P. DRlNG and M. F. BLAIR In NASA. Lewis Research Center reported. B.G. Turbine Engine Hot Section Technology, 1984 8 p Oct. 1984 Avail: NTlS HC A17/MF A01 CSCL 20D N87-11211'# Southwest Research Inst., San Antonio, Tex. The primary basis for heat transfer analysis of turbine airfoils CONSTITUTIVE MODELING FOR ISOTROPIC MATERIALS is experimental data obtained in linear cascades. A detailed set U. S. LINDHOLM In NASA. Lewis Research Center Turbine of heat transfer coefficients was obtained along the midspan of a Engine Hot Section Technology, 1984 8 p Oct. 1984 stator and a rotor in a rotating turbine stage. The data are to be Avail: NTlS HC A17/MF A01 CSCL 20K compared to standard analyses of blade boundary layer heat A state-of-the-art review of applicable constitutive models with transfer. A detailed set of heat transfer coefficients was obtained selection of two for detailed comparison with a wide range of along the midspan of a stator located in the wake of a full upstream experimental tests was conducted. The experimental matrix turbine stage. Two levels of inlet turbulence (1 and 10 percent) contained uniaxial and biaxial tensile, creep, stress relaxation, and were used. The analytical capability will be examined to improve cyclic fatigue tests at temperatures to 1093 C and strain rates prediction of the experimental data. B.G. from .0000001 to .001 /sec. Some nonisothermal cycles will also be run. The constitutive models will be incorporated into the MARC N87-11225*# Pratt and Whitney Aircraft, East Hartford, Conn. finite eiement structural analysis program with a demonstration COOLANT PASSAGE HEAT TRANSFER WITH ROTATION, A computation made for advanced turbine blade configuration. In PROGRESS REPORT the code development work, particular emphasis is being placed F. C. KOPPER In NASA. Lewis Research Center Turbine Engine on developing efficient integration algorithms for the highly Hot Section Technology, 1984 10 p Oct. 1984 nonlinear and stiff constitutive equations. Another area of emphasis Avail: NTlS HC A17/MF A01 CSCL 20D is !he zpprnpriate and efficient methodoloav for determing The objective of this 36-month experimental and analytical constitutive constants from a minimum extent of experimental program is io aeveiop a iieai iiafi6ki ani pieSSi;S 3:q da!absse, data. Author computational fluid dynamic techniques, and correlations for multipass rotating coolant passages with and without flow N87-11214'# General Electric Co., Fairfield, Conn. Aircraft turbulators. The experimental effort will be focused on the Engine Business Group. simulation of configurations and conditions expected in the blades ELEVATED TEMPERATURE CRACK GROWTH of advanced aircraft high pressure turbines so that the effects of K. S. KIM, J. F. YAU, R. H. VANSTONE, and J. H. LAFLEN In Coriolis and buoyancy forces on the coolant side flow can be NASA. Lewis Research Center Turbine Engine Hot Section rationally included in the design of turbine blades. Author Technology, 1984 10 p Oct. 1984 Avail: NTlS HC A17/MF A01 CSCL 20K N87-11226# George Washington Univ., Washington, D.C. School Critical gas turbine engine hot section components such as of Engineering and Applied Science. ----..---l- n-l-y nnnn AP-Arinu WITH APPLICTIONS blades, vanes, and combustor liners tend to develop minute cracks a I vbnrra I I- U"C.UI\ . I .-. .-.I-. .-.. _... .. during early stages of operations. The ability of currently available TO DURABILITY AND DAMAGE TOLERANCE ANALYSES Final path-independent (P-I) integrals to correlate fatigue crack Report, Jun. 1983 - Feb. 1985 propagation under conditions that simulate the turbojet engine J. N. YANG, W. H. HSI, and S. D. MANNING Sep. 1985 263 p combustor liner environment was determined. To date, an (Contract F33615-83-K-3226) appropriate specimen design and a crack displacement (AD-A168040; AFWAL-TR-85-3062) Avail: NTlS HC A1 2/MF measurement method were determined. Alloy 718 was selected A01 CSCL20K as the analog material based on its ability to simulate high Various stochastic models for fatigue crack propagation under temperature behavior at lower temperatures in order to facilitate either constant amplitude or spectrum loadings have been

53 12 ENGINEERING investigated. These models are based on the assumption that the 13 crack growth rate is a lognormal random process, including the general lognormal random process, lognormal white noise process, GEOSCIENCES lognormal random variable, and second moment approximations, such as Weibull, gamma, lognormal and Gaussian closure approximations. Extensive experimental data have been used for Includes geosciences (general); earth resources and remote the correlation study with various stochastic models. These include sensing; energy production and conversion; environment pollution; fastener hole specimens under fighter or bomber spectrum loadings geophysics; meteorology and climatology; and oceanography. and center-cracked specimens under constant amplitude loads. The data sets for the fastener hole specimens cover adequately A87-10116 different loading conditions, environments, load transfers and crack size range. It is shown that the white noise process is definitely REACTION TO AIRCRAFT NOISE IN RESIDENTIAL AREAS not a valid model for fatigue crack propagation. GRA AROUND AUSTRALIAN AIRPORTS R. B. BULLEN, A. J. HEDE. and E. KYRIACOS (National Acoustic Laboratories, Sydney, Australia) Journal of Sound and Vibration (ISSN 0022-46OX), vol. 108, July 22, 1986, p. 199-225. refs A large-scale of community reaction to aircraft noise was conducted around five Australian airports, involving interviews with over 3500 residents and the use of intensive and detailed noise measurement data. The major purpose of the study was to produce a valid and reliable dose/response relationship which could serve as a guide for planners, airport authorities and regulatory authorities. Features of the study include assessment of noise exposure by using measurement-based corrections to standard noise level N87-11231# Aeronautical Research Inst. of Sweden, Stockholm. figures for each aircraft type, and the use of a complex scale for Structures Dept. assessment of noise reaction (although simpler measures are RELEVANCE OF SHORT FATIGUE CRACK GROWTH DATA FOR included for comparison with previous studies). Much of the DURABILITY AND DAMAGE TOLERANCE ANALYSES OF dose/response analysis involves binary dependent variables, and AIRCRAFT probit analysis is used in this case in preference to standard A. F. BLOM Mar. 1986 19 p Presented at Engineering regression analysis. A dose/response function is found which Foundation Second International Conference on Small Fatigue predicts the proportion of residents in an area whose reaction Cracks, Santa Barbara, Calif., 5-10 Jan. 1986 Submitted for exceeds a defined threshold with a standard error of 4.6 dB. publication Sponsored by Swedish Board for Technical Approximately half this error can be explained by error in the Development measured variables, the rest being due to real inter-area differences (FFA-TN-1986-23;ETN-86-97857) Avail: NTlS HC A02/MF A01 in noise reaction. The only personal characteristic which can Starting from damage tolerance requirements and proceeding unambiguously be shown to substantially affect noise reaction is over the experimental and numerical means to verify these sensitivity to noise in general, which explains about 11 percent of requirements, it is concluded that the relevance of short fatigue the variance in measured individual noise reaction, compared with crack studies is limited to durability of the airframe. For engines, about 13 percent for noise exposure. Author the behavior of short cracks is crucial if a damage tolerant design is to be considered. It is suggested that any type of analysis involving short cracks has to be probabilistic. Such a technique is described. ESA

A87-10117 COMPARISON OF THE EFFECTIVENESS OF MEASURES OF AIRCRAFT NOISE EXPOSURE BY USING SOCIAL SURVEY N87-11233# National Aerospace Lab., Amsterdam (Netherlands). DATA Structures and Materials Div. R. B. BULLEN and A. J. HEDE (National Acoustic Laboratories, FATIGUE FRACTURE IN STEEL LANDING GEAR Sydney, Australia) Journal of Sound and Vibration (ISSN COMPONENTS 0022-46OX). vol. 108, July 22, 1986, p. 227-245. refs R. J. H. WANHILL 7 Jun. 1985 14 p Sponsored by the Royal Results from a social survey of reaction to aircraft noise are Netherlands Air Force Scientific Research Division of the used to investigate the effectiveness of various measures of noise Directorate of Material exposure. The measures tested include the equal energy index, (NLR-MP-85050-U; 88668293; ETN-86-98492) Avail: NTlS HC models involving a logarithmic trade-off of noise level and number AOP/MF A01 of events, 'peak-level' models and other non-standard noise The characteristics of fatigue and overload fracture in high descriptors. Analysis methods involve the use of probit analysis strength low alloy steel landing gear forgings were investigated. to investigate the relative efficiency of the various measures in Fatigue fracture was characterized by microserrated acicular ridges predicting noise reaction. The results from this investigation indicate and to a lesser extent by striation marks. Overload fracture was that the usual equal energy index gives a prediction of noise by microvoid coalescence (dimples). After corrosion due to outdoor reaction which is more accurate than most alternatives, and can exposure it is possible to identify fatigue fracture, but overload be improved only marginally when using the noise exposure dimples are much less evident. Constant amplitude and block variables available in this study. The largest improvement in the program (flight-by-flight) fatigue crack propagation rates are well predictive power of the equal-energy index is gained by adding to correlated by root mean values of the stress intensity factor range. it a linear term in the number of noise events. Time-of-day This is encouraging for analytical estimation of service failure crack weightings used in most existing noise exposure measures are propagation lives. ESA shown to be less than optimal. Author

54 13 GEOSCIENCES

A87-12679# N87-11242# Toulouse Univ. (France). Lab. d’Aerologie. MONITORING OF TERMINAL FLIGHT PHASES ENVIRONMENT AIRBORNE MEASUREMENT METHODS APPLIED TO THE OBSERVATIONS AND MODELS DETERMINATION OF BOUNDARY CONDITIONS AT THE SEA S. PALMIERI, R. COZZI, and G. CASU (Aeronautica Militare Italiana, SURFACE: THE TOSCANE EXPERIMENT [METHODES DE lspettorato Telecomunicazioni e Assistenza al Volo, Rome, Italy) MESURES AEROPORTEES APPLIQUEES A LA IN: Navigation and environment; Proceedings of the Fifth DETERMINATION DES CONDITIONS AUX LlMlTES SUR LA International Congress, Tokyo, Japan, October 1-5, 1985 . Tokyo, MER: EXPERIENCE TOSCANE] Japan Institute of Navigation, 1986, p. 61-68. P. DURAND, F. SAIQ. and A. DRUILHET In ESA Proceedings of The Doppler sodar, which is capable of providing continuous the Third International Colloquium on Spectral Signatures of Objects monitoring of the three-dimensional wind speed, was evaluated at in Remote Sensing p 23-28 Dec. 1985 In FRENCH Sponsored the Pantelleria Airport in Tunisia from August-October 1984. The by Inst. National d’Astronomie et de Geophysique sodar provides three-dimensional wind speed, wind direction, and Avail: NTlS HC A25/MF A01 echo intensity data every few minutes (5-10) with a vertical Two light aircraft were used to collect data on average boundary resolution of 20-50 m. The sodar data reveal a relation between layer conditions at the sea surface and on turbulent air flow over wind shear, and height and time. The effects of sea-breeze and the sea. The method for calculating turbulent flow is presented. topography are studied using a simple mesoscale model based Advantages and disadvantages of the aircraft for this type of data on a continuity equation. It is noted that sodar is useful for the collection are discussed, particularly problems related to analysis of wind shear and is capable of detecting downbursts. perturbations of information on the absolute speed of the aircraft. I.F. Consequences for the calculation of wind parameters and motion transfer are outlined. A solution which allows the turbulent horizontal kinetic energy global vertical motion transfer to be reconstructed is given. The relation between parameters calculated at the average flight altitude of 50 m and the conditions at the N87-10659’# National Aeronautics and Space Administration, real boundary layer is considered. ESA Washington, D.C. NASA AND FAA LAUNCH WIND SHEAR RESEARCH PROJECT D. J. RAHN 9 Oct. 1986 2 p N87-11252# Canada Centre for Remote Sensing, Ottawa (N.ASA-NFWS-REL-86-143) Avail: NTlS HC A02 CSCL 048 (Ontario). The Na?ional Aeronautics and Space Administration and the -.inE . 2 ANE K:! BAnO SCATKROMETER RESULTS FROM Federal Aviation Administration have signed a memorandum of CANADIAN PARTICIPATION IN THE ESA PROMESS OCEAN agreement calling for a joint 5-year, $24 million research project MEASUREMENT CAMPAIGN to develop technology for airborne wind-shear detection and A. L. GRAY and R. K. HAWKINS In ESA Proceedings of the avoidance. The most dangerous type of wind shear, the microburst, Third International Colloquium on Spectral Signatures of Objects is a small intense downdraft which, upon striking the ground, in Remote Sensing p 77-82 Dec. 1985 Sponsored by ESA spreads out into a circular vortex radiating in all directions. When and lnnotech Aviation encountered at low levels on approach or takeoff, the pilot usually Avail: NTlS HC A25/MF A01 has little time to react correctly to maintain the desired flight path Multipolarized C and Ku-band fanbeam scatterometer and X(VV) or even react enough to survive. Between 1964 and 1985, there and C(VV) SAR data were collected by aircraft during the ESA were at least 26 accidents and 3 incidents involving 626 fatalities PROMESS ocean backscatter experiment. The C(VV) and Ku(HH) and 235 injuries where wind shear was the direct cause or a scatterometer data for incidence angles from 10 to 58 deg for contributing factor. The NASA/FAA research project will cover straight flight lines and from 15 to 55 deg for circle flights is five major areas: technology assessment, present position sensor described. For light to moderate winds it is shown that there are integration, hazard characterization, pilot factors in wind shear and significantly larger changes in Ku backscatter than at C band for effects of heavy rain. This represents a consensus approach among the same change in wind speed. For the more important moderate the aviation community. Researchers will thoroughly assess the to high speed wind regime however, the advantage Ku-band data application of technologies such as Doppler and laser radar for has over C-band decreases and, on the basis of backscatter airborne equipment to detect the wind-shear danger with the intent sensitivity, satisfactory performance can be expected from the of avoiding it. They also will look at the current reactive systems ERS-AMI wind scatterometer. Results for C(VV) and Ku(HH) that tell a pilot he is in wind shear and offer the crew guidance indicate that both frequencies respond in approximately the same information to facilitate a safe exit from wind shear. Another goal way to a changing azimuth angle between the radar look and is to develop a better understanding of the complex wind structure wind directions. ESA * - --:---I- UI a IIIIC.IUUU13L.___^. Author

N87-11433 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). Inst. fuer N87-10665# National Oceanic and Atmospheric Administration, Physik der Atmosphaere. Boulder, Colo. Wave Propagation Lab. ICE ACCRETION DEPENDENCE ON CLOUD PHYSICAL SURFACE MEASUREMENTS OF GUST FRONTS AND PARAMETERS [DER EISANSATZ IN ABHAENGIGKEIT VON MICROBURSTS DURING THE JAWS (JOINT AIRPORT WOLKENPHYSIKALISCHEN PARAMETERN] WEATHER STUDIES) PROJECT STATISTICAL RESULTS AND H. E. HOFFMANN and R. ROTH In Deutscher Wetterdienst IMPLICATIONS FOR WIND SHEAR DETECTION, PREDICTION Reports of Meteorology, No. 23: Proceedings of the German -*.-Awn ._.-unnm---.. INF. .- Meteorologists Conference on the Global Climate and Our A. J. BEDARD and J. LEFEBVRE Apr. 1986 123 p Environment p jtj2-,63 -^^^IYoo 1110- uCnwnu-nFnldA&l (PB86-200847; NOAA-TM-ERL-WPL-135) Avail: NTlS HC Avail: Issuing Activity AO6/MF A01 CSCL 048 Ice deposition was investigated in order to determine flight During the 1982 Joint Airport Weather Studies Project (JAWS), limitations due to icing, and to verify forecasting methods and ice the authors identified 168 microbursts, 20 macrobursts, and 99 accretion models. A Do-28 aircraft was equipped for icing research gust fronts using surface sensors in the vicinity of Denver’s to determine the cloud physical parameters, liquid water content, Stapleton Airport. The report reviews aspects of these temperature, particle size, and particle phase. The effects of the measurements important to the problem of understanding and icing-relevant cloud physical parameters on the accretion of ice detecting wind shear hazardous to aircraft. GRA below the Ludlam limit were determined by regression. ESA

55 13 GEOSCIENCES

N87-11434 Deutscher Wetterdienst, Offenbach am Main (West 15 Germany). ICE ACCRETION CALCULATIONS ON CYLINDRICAL RODS MATHEMATICAL AND COMPUTER SCIENCES FOLLOWING THE BAlN MODEL, AND COMPARISON WITH EXPERIMENTAL RESULTS (FUCHS, SCHICKEL, KALUZA, UWIRA, 1985) [EISANSATZBERECHNUNGEN AN Includes mathematical and computer sciences (general); computer ZYLINDRISCHEN STAEBEN NACH DEM BAIN-MODELL UND operations and hardware; computer programming and software; VERGLEICH MIT EXPERIMENTELLEN ERGEBNISSEN] computer systems; cybernetics; numerical analysis; statistics and W. FUCHS In its Reports of Meteorology, No. 23: Proceedings probability; systems analysis; and theoretical mathematics. of the German Meteorologists Conference on the Global Climate and Our Environment p 164- 165 1986 In GERMAN Avail: Issuing Activity A87-10879 Measurements were performed from a DO-28 aircraft in zones CSA/NASTRAN - A GENERAL PURPOSE PROGRAM FOR of natural icing in order to determine the parameters required for STRUCTURAL ANALYSIS the model of Bain (1980) which calculates the icing degree on R. NARAYANASWAMI and J. G. COLE (Computerized Structural cylindrical rods. These parameters are atmospheric pressure and Analysis and Research Corp., Northridge, CA) IN: Finite elements temperature, size and number of cloud elements, flow velocity, in computational mechanics - FEICOM '85; Proceedings of the and rod diameter. The Bain model simplifies a model for pure International Conference, Bombay, India, December 2-6, 1985. water clouds. Good agreement is found between calculated and Volume 1 . Oxford, Pergamon Press, 1985, p. 23-38. refs measured icing velocities. ESA CSAINASTRAN is an advanced proprietary version of the NASTRAN general purpose computer program for the analysis of structures by the displacement approach of the finite element method. This paper discusses the organization of the NASTRAN program, its analysis capabilities, and details of enhancements available in the CSA/NASTRAN program. The paper concludes with a list of NASTRAN applications in the various industries that has made the program and other proprietary versions of the N87-11437 Freie Univ., Berlin (West Germany). program, like CSA/NASTRAN, a standard for structural analysis. THE INFLUENCE OF WEATHER-ACTIVE FRONTS ON VISUAL Author FLIGHT CONDITIONS [DER EINFLUSS VON WETTERAKTIVEN FRONTEN AUF SICHTFLUGBEDINGUNGEN] M. GEB, C. LINDEMANN, and W. WEHRY In Deutscher Wetterdienst Reports of Meteorology, No. 23: Proceedings of the A87-11779# German Meteorologists Conference on the Global Climate and A SURVEY OF COMPOSITE GRID GENERATION FOR GENERAL Our Environment p 170-171 1986 In GERMAN THREE-DIMENSIONAL REGIONS Avail: Issuing Activity J. F. THOMPSON (Mississippi State University, Mississippi State) Structured information describing the effects of weather-active IN: Numerical methods for engine-airframe integration . New York, fronts on visual flight conditions was provided. A potential cloud American Institute of Aeronautics and Astronautics, Inc., 1986, p. lower level and the effective ridge height of a wood were considered 52-85. refs to determine dangerous levels of visual perception. The leeward Three dimensional composite grids for code construction in and windward side are recognized. The results show that it is computational fluid dynamics applied to aircraft configurations are necessary to evaluate a broader set of cases with weather-active studied. The theory of the grids is addressed, discussing interface fronts, and to incorporate experiences of local weather advisers, continuity, discontinuous and continuous grid lines or slope, and fine-mesh radar data, and special flight measurements. ESA interface difference representations of such grid lines and slopes. Image points are discussed along with boundary point distributions and surrounding image layers.Current research results on discontinuous grid lines, overlaid grids, continuous grid lines, continuous grid line slope, surface grids, and general codes are reviewed. C.D.

N87-11461 Technische Univ., Hanover (West Germany). Inst. fuer Meteorologie und Klimatologie. STATISTICS OF WIND SHEAR DUE TO NOCTURNAL A87-12211 BOUNDARY LAYER JET AIRSTREAMS IN NORTH GERMANY ANNUAL AEROSPACE APPLICATIONS OF ARTIFICIAL [EINE STATlSTlK DER MIT NAECHTLICHEN INTELLIGENCE CONFERENCE, lST, DAYTON, OH, GRENZCHICHTSTRAHLSTROEMEN VERBUNDENEN SEPTEMBER 16-19, 1985, PROCEEDINGS WINDSCHERUNG IN NORDDEUTSCHLAND] J. R. JOHNSON, ED. (USAF, Wright Aeronautical Laboratories, K. P. WITTICH. J. HARTMANN, and R. ROTH ln Deutscher Wright-Patterson AFB, OH) Conference sponsored by NCR, VEDA, Wetterdienst Reports of Meteorology, No. 23: Proceedings of the Inc., Boeing Military Airplane Co., et al. Dayton, OH, AAAIC German Meteorologists Conference on the Global Climate and Secretariat, 1985, 359 p. For individual items see A87-12212 to Our Environment p 222-223 1986 In GERMAN A87-12220. Avail: Issuing Activity Topics of interest at the forefront of the development and Shear wind statistics were prepared for air traffic safety. The implementation of artificial intelligence (AI) systems are detailed. shear statistics are based on 14 nocturnal wind profiles. These Consideration is given to AI applications in the avionics displays nights were characterized by a boundary layer jet airstream whose in fighter aircraft, in manufacturing and in ground-based Shuttle wind maximum was 1.5 times the geostrophic ground wind, or navigation monitoring systems. An implementation of LISP on a even higher. Wind and temperature profile measurements with a SlMD is described, along with frame-based knowledge 5 m vertical resolution were performed. It is shown that the representation for processing planning. Progress in the use of nocturnal stabilization of the ground level atmosphere and the expert systems in an advisory role for the design of video display formation of a boundary layer jet stream cause an increase of the units and for trouble-shooting system problems in a tactical fighter wind shear. Increasing temperature gradients cause increased is assessed. Finally, design and performance features and shear within certain limits. Strong time variations of wind field and aplications of the ASPRO parallel processor inference engine are temperature gradients are correlated with high shear. ESA summarized. M.S.K.

56 16 PHYSICS

A87-12217# N87-11530# National Aerospace Lab., Amsterdam (Netherlands). TECHNICAL DIAGNOSIS BY AUTOMATED REASONING Informatics Div. D. ALLEN and K. RADER (Northrop Corp.. Aircraft Div., Hawthorne, REAL TIME DEBUGGING SOFTWARE PACKAGE FOR FLIGHT CA) IN: Annual Aerospace Applications of Artificial Intelligence SIMULATOR SOFTWARE SYSTEM WITH VARIABLE LABELED Conference, 1st. Dayton, OH, September 16-19, 1985, Proceedings COMMON BLOCKS . Dayton, OH, AAAIC Secretariat, 1985, p. 185-194. H. W. G. DEJONGE 2 May 1985 18 p In DUTCH; ENGLISH Features and applications of an automated diagnostic program summary Presented at the Netherlands Society for Informatics, (IN-ATE/P) which includes a rule-based heuristic search strategy and the Foundation Informatics Research in the Netherlands for aiding a technician trouble-shooting a system element are Symposium, Utiecht, Netherlands, 1-2 Apr. 1985 described. The element is represented as a logic model, which (NLR-MP-85013-U; 88667024; ETN-86-98489) Avail: NTlS HC permits the system to generate its own rule base. Introduction of AO2IMF A01 a true rulebase. i.e., expert knowledge, changes the program to a The support of software development by the application of true expert system. The logic model consists of a topological model system defined variables is surveyed. The large software system of the system being examined. Output is a recommended optimum consists of a large number of modules that share access to data sequence of tests based on a binary decision tree. The goal of in the direct addressable memory by the use of labeled common the output is to isolate the fault as quickly and cheaply as possible, blocks in which variable names for addressing fields are used and to identify the point at which tests must be made with individual freely. It is proposed to introduce a common-definition file for the components. A sample application of IN-ATE/P to trouble-shoot a management of common variable names, defined on system level, problem in the circuitry of an F-5 aircraft is outlined. Planned in a similar way as a data dictionary is used for the management enhancements and implementations of the IN-ATE12 are of data in data bases. A common-definition file can be applied for discussed. M.S.K. the creation of consistent sources for compilation, interactive debugging, and selection of variables for monitoring and recording of data during program execution. A software system which applies access to such a common-definition files is operational.The system is used for software development in FORTRAN 5. ESA

ns7-:oo::n" Chiba Unk. (Japan). .Cacu!t; e! EnginPering. IMAGES OF THREE DIMENSIONAL FLOWS IN COMPUTER 16 GRAPHICS N. NISHIKAWA, A. SUZUKI, and S. AKIYAMA ln Tokyo Univ. PHYSICS Proceedings of the Symposium on Mechanics for Space Flight, 1985 11 p 1985 Includes physics (general); acoustics; atomic and molecular Avail: NTlS HC Al2/MF A01 physics; nuclear and high-energy physics; optics; plasma physics; The numerical results are shown in graphic images for three solid-state physics; and thermodynamics and statistical physics. dimensional boundary-layer flows. It is shown that the presentation of images, especially in solid model graphics, allows the utilization of the widest band width sense in an effective manner to create A87-10293 physical or geometrical models and to understand their behavior MECHANICS OF FLOW-INDUCED SOUND AND VIBRATION. in simulated environments. As the results, external streamlines VOLUME 1GENERAL CONCEPTS AND ELEMENTARY SOURCE. and limiting streamlines obtained with finite difference calculations VOLUME 2 - COMPLEX FLOW-STRUCTURE INTERACTIONS are given for paraboloid, and for the front half region of W. K. BLAKE (David W. Taylor Naval Ship Research and wing-ellipsoid combination. Author Development Center, Bethesda, MD) Orlando, FL, Academic Press, Inc. , 1986. Vol. 1, 457 p.; vol. 2, 567 p. refs Physical and mathematical analyses of the vibration and sound induced by different types of fluid flow are presented in a comprehensive introduction intended primarily for practicing engineers. The elementary concepts are explained, and chapters are devoted to the theory of sound and its generation by flow; shear-layer instabilities, flow tones, and jet noise; dipole sound N87-11513# Massachusetts Inst. of Tech., Cambridge. Dept. of from cylinders; the fundamentals of flow-induced vibration and Elec. Engineering and Computer Sciences. noise; bubble dynamics and cavitation; hydrodynamically induced SIGNAL PROCESSING AND INTERPRETATION USING cavitation and bubble noise; turbulent wall-pressure fluctuations; MULTILEVEL SIGNAL ABSTRACTIONS structural response to turbulent wall flow and random sound; noise E. E. MlLlOS Jun. 1986 221 p radiation from pipe and duct systems; noncavitating lifting sections; (Contract N00014-81-K-0742; NSF ECS-84-07285) and noise from rotating machinery. Graphs, diagrams, drawings, (AD-A169166; TR-516) Avail: NTlS HC AlO/MF A01 CSCL and tables of numerical data are provided. T.K. 09B This thesis advances multilevel signal abstractions as a useful conceptual framework in signal processing. More specifically, A87-10444 multilevel abstractions for one-dimensional harmonic spectra are THE MECHANICS OF DYNAMICALLY TUNABLE GYROSCOPES developed and demonstrated to be useful in combining heuristics [MEKHANIKA DlNAMlCHESKl NASTRAIVAEMYKH with aigoriihmic iechniques in a varieiy ui sign& piocessing Q!ROEKCPCV] problems associated with real helicopter data, such as adjusting L. Z. NOVIKOV and M. IU. SHATALOV Moscow, Izdatel'stvo spectral estimation parameters and tracking fundamental frequency Nauka, 1985, 248 p. In Russian. refs and power of helicopter spectra. Furthermore, multilevel The theory of dynamically tunable gyroscopes, which are widely abstractions for two-dimensional wavenumber spectra are used used in modern inertial navigation systems, is presented. The as the basis for a diagnosis system that searches for inappropriate discussion covers generalized schemes of dynamically tunable parameter settings in an array processing system for direction gyroscopes including gyroscopes with a single-axis elastic determination. The diagnosis system illustrates the use of multilevel suspension, gyroscopes with a nonsymmetric rotor, and gyroscopes single abstractions in automating reasoning about complex signal with a rotating elastic suspension. All theoretical results are processing systems. GRA illustrated by specific calculation examples. V.L.

57

I 16 PHYSICS

A87-11766' Florida State Univ., Tallahassee. A87-11770*# National Aeronautics and Space Administration. RECENT ADVANCES IN AEROACOUSTICS Langley Research Center, Hampton, Va. A. KROTHAPALLI, ED. (Florida State University, Tallahassee) and THE EVOLUTION OF METHODS FOR NOISE PREDICTION OF C. A. SMITH, ED. (NASA, Ames Research Center, Moffett Field, HIGH SPEED ROTORS AND PROPELLERS IN THE TIME CA) New York, Springer-Verlag, 1986, 522 p. For individual DOMAIN items see A87-11767 to A87-11774. F. FARASSAT (NASA, Langley Research Center, Hampton, VA) The state of the art in theoretical and numerical models and IN: Recent advances in aeroacoustics . New York, Springer-Verlag, experimentation on broadband noise propagation from high speed 1986, p. 129-147. refs aircraft components such as jets and helicopter blades is detailed. Linear wave equation models which have been used over the Attention is given to noise produced by jets, shear layers and years at NASA Langley for describing noise emissions from high turbulence and to the acoustic properties of rotors. The generation speed rotating blades are summarized. The noise sources are and propagation of acoustic noise are discussed in terms of the assumed to lie on a moving surface, and analysis of the situation evolution of concepts for flow-tone generation to include has been based on the Ffowcs Williams-Hawkings(FW-H) equation. hydrodynamic instabilities. Consideration is also given to techniques Although the equation accounts for two surface and one volume for experimental studies and theoretical models for nonlinear source, the NASA analyses have considered only the surface terms. features of acoustic propagation of broadband noise and acoustic Several variations on the FW-H model are delineated for various propagation in partially-chokedor soft-walled ducts. M.S.K. types of applications, noting the computational benefits of removing the frequency dependence of the calculations. Formulations are also provided for compact and noncompact sources, and features of Long's subsonic integral equation and Farassat's high speed A87-11768' Florida State Univ., Tallahassee. integral equation are discussed. The selection of subsonic or high ON BROADBAND SHOCK ASSOCIATED NOISE OF speed models is dependent on the Mach number of the blade SUPERSONIC JETS surface where the source is located. M.S.K. C. K. W. TAM (Florida State University, Tallahassee) IN: Recent advances in aeroacoustics . New York, Springer-Verlag, 1986, p. A87-11771'# National Aeronautics and Space Administration. 25-51. refs Ames Research Center, Moffett Field, Calif. (Contract NAG3-182) HELICOPTER IMPULSIVE NOISE - THEORETICAL AND The characteristics and generation mechanisms of noise EXPERIMENTAL STATUS associated with the interactions of turbulence with the F. H. SCHMITZ and Y. H. YU (NASA, Ames Research Center; quasi-periodic broadband shock cells of supersonic jet engines US. Army, Aeromechanics Laboratory, Moffett Field, CA) IN: are reviewed. The noise possesses broadband spectra and Recent advances in aeroacoustics . New York, Springer-Verlag, directionality that are completely different from noise caused by 1986, p. 149-243. refs turbulence. Experimental data have shown that broadband noise The theoretical and experimental status of helicopter impulsive is most prominent in the forward arc, with peak frequencies being noise is reviewed. The two major source mechanisms of helicopter a function of the observation angle and the pressure mismatch in impulsive noise are addressed: high-speed impulsive noise and the engine. The noise originates in the engine as turbulence-shock blade-vortex interaction impulsive noise. A thorough physical interactions occur during downstream movement. Features of the explanation of both generating mechanisms is presented together phased point-source array model and the large turbulence with model and full-scale measurements of the phenomena. Current structures-shock cells interaction model are defined and model theoretical prediction methods are compared with experimental predictions are compared with experimental data on noise sources. findings of isolated rotor tests. The noise generating mechanisms Only a scaling of the noise component is found to be currently of high speed impulsive noise are fairly well understood - theory possible. More complete characterization depends on consideration and experiment compare nicely over Mach number ranges typical of the jet temperature and analysis of turbulence-shock interactions, of today's helicopters. For the case of blade-vortex interaction broadband shock and screech tones and shock noise in several noise, understanding of noise generating mechanisms and flow configurations. M.S.K. theoretical comparison with experiment are less satisfactory. Several methods for improving theory/experiment are suggested. Author A87-11769' Cornell Univ., Ithaca, N.Y. ANALYSES OF BROADBAND NOISE MECHANISMS OF A87-11773 ROTORS NONLINEAR ACOUSTIC PROPAGATION OF BROADBAND A. R. GEORGE (Cornell University, Ithaca, NY) IN: Recent NOISE advances in aeroacoustics . New York, Springer-Verlag, 1986, p. D. G. CRIGHTON (Leeds University, England) IN: Recent 87-127. NASA-supported research. refs advances in aeroacoustics . New York, Springer-Verlag. 1986, p. The various source mechanisms which generate broadband 41 1-454. refs noise on a range of rotors are reviewed. Analyses of these Data on nonlinear broadband jet noise propagation are mechanisms are presented and compared to existing experimental reviewed, along with several theoretical modeling approaches. The data. The sources considered are load fluctuations due to inflow data were obtained with groundside microphones at set distances turbulence, due to turbulent blade boundary layers passing the below the flight path of aircraft in constant climb gradients. Although trailing edge, and due to tip vortex formation turbulence. Vortex the data were coontaminated by the jet configurations, acoustic shedding noise due to laminar boundary layers and blunt trailing tests in laboratory conditions have confirmed the existence of edges is not considered in detail as it can be avoided in most nonlinear noise effects and shown that they may be cumulative. cases. Present analyses are adequate to predict the spectra from One model is described which employs an expansional amplitude a wide variety of experiments on fans, helicopter rotors, and wind such as frequency or range to identify frequency distortions at the turbines to within about 5 to 10 dB. Better knowledge of the peak frequency. Account is taken of attenuation, spreading, and inflow turbulence improves the accuracy of the predictions. Inflow spreading nonuniformity effects. A nonlinear plane wave signal turbulence noise depends strongly on ambient conditions and evolution model utilizes gaussian statistics to generate an exact dominates at low frequencies. Trailing edge and tip vortex noise solution, but cannot account for attenuation or to make corrections are important at higher frequencies if inflow turbulence is weak. for high frequencies. Finally, the effects of shock waves on the Boundary layer trailing edge noise increases slowly with angle of acoustics signals are considered, and data are cited for the attack but not as rapidly as tip vortex formation noise. Tip noise presence of nonzero skewness in jet noise signals, which can be can be important at high angles of attack for wide chord, square described with frequency dispersion terms in the plane wave signal edge tips. Author evolution model. M.S.K.

58 16 PHYSICS

A87-12995 N87-10750*# National Aeronautics and Space Administration. SOURCES AND OBSERVERS IN MOTION, II - ACOUSTIC Langley Research Center, Hampton, Va. RADIATION FROM A SMALL RIGID BODY IN ARBITRARY PREDICTION OF HELICOPTER ROTOR DISCRETE FREQUENCY MOTION. 111 - ACOUSTIC RADIATION FROM NON-COMPACT NOISE A COMPUTER PROGRAM INCORPORATING REALISTIC RIGID BODIES MOVING AT HIGH SPEED BLADE MOTIONS AND ADVANCED ACOUSTIC S. E. WRIGHT (Electric Power Research Institute, Palo Alto, CA) FORMULATION and D. J. LEE (Stanford University, CA) Journal of Sound and K. S. BRENTNER Oct. 1986 94 p Vibration (ISSN 0022-46OX). vol. 108, Aug. 8, 1986, p. 379-387, (NASA-TM-87721; L-16130; NAS 1.15:87721) Avail: NTlS HC 389-403. refs A05/MF A01 CSCL 20A The time-variant theory of sound propagation developed by A computer program has been developed at the Langley Wright (1982 and 1986) is extended from motion in a straight line Research Center to predict the discrete frequency noise of to arbitrary motion (of a compact source) and to the case of a conventional and advanced helicopter rotors. The program, called noncompact body such as a helicopter or propeller blade. The WOPWOP, uses the most advanced subsonic formulation of relation between surface displacement and fluid flux sources and Farassat that is less sensitive to errors and is valid for nearly all the behavior of a point source are analyzed; the special cases of helicopter rotor geometries and flight conditions. A brief derivation a nonvarying compact source and a compact body in circular of the acoustic formulation is presented along with a discussion motion are discussed; the onset of chord and span of the numerical implementation of the formulation. The computer noncompactness is described; and formulations for program uses realistic helicopter blade motion and aerodynamic distributed-sourceinterference are derived. The results of numerical loadings, input by the user, for noise calculation in the time domain. computations are presented in graphs and compared with A detailed definition of all the input variables, default values, and experimental measurements in some cases. The radiated acoustic output data is included. A comparison with experimental data shows signature in the compact-body case is shown to be dependent on good agreement between prediction and experiment; however, the speed and direction of flight and not on the body shape. In accurate aerodynamic loading is needed. Author the case of the rotating blade, the blade profile is found to affect the acoustic signature significantly only at tip speeds in excess of N87-10752*# General Electric Co., Cincinnati, Ohio. M = 0.9. T.K. FREE JET FEASIBILITY STUDY OF A THERMAL ACOUSTIC SHIELD CONCEPT FOR ASTNCE APPLICATION: DUAL STREAM NOZZLES Final Report 13. A. JANARDAN, J. F. BRAUSCH, and R. K. MAJJIGI A87-12996 Washington NASA Mar. 1985 203 p SOURCES AND OBSERVERS IN MOTION. iv AfOuSTiC - (Contract NAS3-22137) MEASUREMENTS ON AEROFOILS MOVING IN A CIRCLE AT (NASA-CR-3867; E-2392; NAS 1.26:3867) Avail: NTlS HC HIGH SPEED AlO/MF A01 CSCL 20A S. E. WRIGHT (Electric Power Research Institute, Palo Alto, CA) The influence of selected geometric and aerodynamic flow and W. CROSBY (Stanford University, CA) Journal of Sound variables of an unsuppressed coannular plug nozzle and a and Vibration (ISSN 0022-46OX), vol. 108, Aug. 8, 1986. p. coannular plug nozzle with a 20-chute outer stream suppressor 405-413. refs were experimentally determined. A total of 136 static and simulated Recently a rotor aerodynamics and noise facility has been flight acoustic test points were conducted with 9 scale model constructed at Stanford University. The experimental approach is nozzles. Also, aerodynamic measurements of four selected plumes to rotate blade elements from a quiet, rigid rotor arm in good were made with a laser velocimeter. The presence of the 180 anechoic conditions. The capabilities and limitations of this deg shield produced different mixing characteristics on the shield technique are considered, together with initial data. It is concluded side compared to the unshield side because of the reduced mixing that the approach provides a simple and inexpensive method of with ambient air on the shielded side. This resulted in a stretching. investigating rotor aerodynamicsand noise from windmilling speeds of the jet, yielding a higher peak mean velocity up to a length of through to high subsonic velocities. Author 10 equivalent diameters from the nozzle exit. The 180 deg shield in community orientation around the suppressed coannular plug nozzle yielded acoustic benefit at all observer angles for a simulated N87-10748# Tokyo Univ. (Japan). Inst, of Space and takeoff. While the effect of shield-to-outer stream velocity ratio Astronautical Science. was small at angles up to 120 deg, beyond this angle significant NUMERICAL AND EXPERIMENTAL STUDY OF DYNAMICS OF acoustic benefit was realized with a shield-to-outer stream velocity TWO-DIMENSIONAL BODY ratio of 0.64. Author N. IZUTSU Mar. 1986 67 p (ISAS-619; ISSN-0285-6808) Avail: NTlS HC A04/MF A01 N87-10753'# General Electric Co., Cincinnati, Ohio. Aircraft r--:--n..-; --"_ c.,.,,,, Autorotation of a two-dimensional elliptic cyiinaer around iis CI 1y11 IC YVJll IT** UI vvp spanwise axis fixed perpendicularly to a uniform flow was FREE-JET ACOUSTIC INVESTIGATION OF numerically simulated by means of a discrete vortex-blob method. HIGH-RADIUS-RATIO COANNULAR PLUG NOZZLES Final The results were compared with those of the experiments by a Report wind tunnel and a water channel, which were carried out in both P. R. KNOTT, B. A. JANARDAN, R. K. MAJJIGI, P. K. BHUTIANI, the autorotating state and the forced rotating state with constant and P. G. VOGT Washington NASA Oct. 1984 218 p angular velocities driven by a stepping motor. The behavior and (Contract NAS3-20619) the interaction of the vortices shed behind the rotating elliptic (NASA-CR-3818; E-2177; NAS 1.26:3818; R83AEB574) Avail: cylinder were studied, making use of visualization of the numerical NTlS HC AlO/MF A01 CSCL 20A simulation results. Moreover, animation of the displayed image The experimental and analytical results of a scale model was made to illustrate the vortex interaction processes. Based on simulated flight acoustic exploratory investigation of high radius tne momenr oi ineriia and iile ihiciiiisss iGio of thc cy!inde:, the ratin cnannular plug nozzles with inverted velocity and temperature starting condition of the autorotation was determined based on profiles are summarized. Six coannular plug nozzle configurations the mechanism of the autorotation. The driving force is produced and a baseline convergent conical nozzle were tested for simulated by eliminating the vortex created behind the retreating edge. By flight acoustic evaluation. The nozzles were tested over a range means of graphic simulation utilizing a color coded vorticity display of test conditions that are typical of a Variable Cycle Engine for and animation, processes of the merging, rearrangement, application to advanced high speed aircraft. It was found that in interaction and splitting of the vortices in the wake of the rotating simulate flight, the high radius ratio coannular plug nozzles maintain Wing were visualized making these processes clearly their jet noise and shock noise reduction features previously understandable. Author observed in static testing. The presence of nozzle bypass struts

59 16 PHYSICS will not significantly affect the acousticn noise reduction features A move away from the 1.2m system used 'In the certification of of a General Electric type nozzle design. A unique coannular plug other types of aircraft should be encouraged. Further work should nozzle flight acoustic spectral prediction method was identified be conducted to confirm the ideal microphone-to-plate separation and found to predict the measured results quite well. Special laser for jet powered aircraft, and to examine whether the otherwise velocimeter and acoustic measurements were performed which minimal deviations from pressure-doubling can be further have given new insights into the jet and shock noise reduction reduced. ESA mechanisms of coannular plug nozzles with regard to identifying further benificial research efforts. Author

N87-11576'# Pope (L. D.), Woodlands, Tex. N87-11579 Stanford Univ.. Calif. PROPELLER AIRCRAFT INTERIOR NOISE MODEL SEPARATION OF AIRBORNE AND STRUCTUREBORNE NOISE UTILIZATION STUDY AND VALIDATION RADIATED BY PLATES CONSTRUCTED OF CONVENTIONAL L. D. POPE Sep. 1984 248 p AND COMPOSITE MATERIALS WITH APPLICATIONS FOR (Contract NAS1-17281) PREDICTION OF INTERIOR NOISE PATHS IN PROPELLER (NASA-CR-172428; NAS 1.26:172428; REPT-84-001) Avail: DRIVEN AIRCRAFT Ph.D. Thesis NTlS HC A1 1/MF A01 CSCL 20A M. C. MCGARY 1986 315 p Utilization and validation of a computer program designed for Avail: Univ. Microfilms Order No. DAB612765 aircraft interior noise prediction is considered. The program, entitled The anticipated application of advanced turboprop propulsion PAIN (an acronym for Propeller Aircraft Interior Noise), permits (in systems and the use of composite materials in primary structure theory) predictions of sound levels inside .propeller driven aircraft is expected to increase the interior noise of future aircraft to arising from sidewall transmission. The objective of the work unacceptably high levels. The absence of technically and reported was to determine the practicality of making predictions economically feasible noise source-path diagnostics tools has been for various airplanes and the extent of the program's capabilities. a prime obstacle in the development of efficient noise control The ultimate purpose was to discern the quality of predictions for treatments for propeller driven aircraft. A new diagnostic method tonal levels inside an aircraft occurring at the propeller blade which permits the separation and prediction of the fully coherent passage frequency and its harmonics. The effort involved three airborne and structureborne components of the sound radiated by tasks: (1) program validation through comparisons of predictions plates or thin shells has been developed. Analytical and with scale-model test results; (2) development of utilization experimental studies of the proposed method were performed on schemes for large (full scale) fuselages; and (3) validation through plates constructed of both conventional and composite materials. comparisons of predictions with measurements taken in flight tests The results of the study indicate that the proposed method can on a turboprop aircraft. Findings should enable future users of be applied to a variety of aircraft materials, could be used in the program to efficiently undertake and correctly interpret flight, and has fewer encumbrances than the other diagnostic tools predictions. Author currently available. The study has also revealed that the noise radiation of vibrating plates in low frequency regime due to N87-11577'# Virginia Polytechnic Inst. and State Univ., combined airborne and structureborne inputs possesses a strong Blacksburg. synergistic nature. The large influence of the interaction between AN EXPERIMENTAL INVESTIGATION OF THE INTERIOR NOISE the airborne and structureborne terms has been hitherto ignored CONTROL EFFECTS OF PROPELLER SYNCHROPHASING by researchers of aircraft interior noise problems. noise problems. J. D. JONES and C. R. FULLER Oct. 1986 103 p Dissert. Abstr. ' (Contract NAG1-390) (NASA-CR-178185; NAS 1.26:178185) Avail: NTlS HC AO6/MF A01 CSCL20A N87-11615# Rolls-Royce Ltd., Derby (England). Materials A simplified cylindrical model of an aircraft fuselage is used to Engineering Group. investigate the mechanisms of interior noise suppression using COST EFFECTIVE SINGLE CRYSTALS synchrophasing techniques. This investigation allows isolation of M. J. GOULETTE, D. SPILLING, and R. P. ARTHEY 18 Feb. important parameters to define the characteristics of P. 1986 11 p synchrophasing. The optimum synchrophase angle for maximum (PNR-90319; ETN-86-98021) Avail: NTlS HC A02/MF A01 noise reduction is found for several interior microphone positions Cost effectiveness constraints in aerospace single crystal with pure tone source excitation. Noise reductions of up to 30 dB technology were met by improving single crystal casting techniques, are shown for some microphone positions, however, overall alloy development, and orientation measurement. The first led to reductions are less. A computer algorithm is developed to the adoption of the technically more difficult seeding technique as decompose the cylinder vibration into modal components over a a result of its greater flexibility. The second resulted in the wide range of synchrophase angles. The circumferential modal development of a series of three alloys to meet specific turbine response of the shell vibration is shown to govern the transmission applications. The third requirement was met by the development of sound into the cylinder rather than localized transmission. As of a rapid and accurate orientation Laue measurement technique well as investigating synchrophasing, the interior sound field due (SCORPIO) suitable for the production environment. ESA to sources typical of propellers has been measured and discussed. Author

N87-11578# Rolls-Royce Ltd., Derby (England). N87-11616# Rolls-Royce Ltd., Derby (England). Metallurgical AIRCRAFT NOISE MEASUREMENT THE 1.2 METRE Research Labs. MICROPHONE HEIGHT SAGA DEVELOPMENT OF SINGLE CRYSTAL ALLOYS FOR SPECIFIC M. J. T. SMITH 18 Feb. 1986 7 p Presented at lnternoise ENGINE APPLICATIONS 86, Boston, Mass., Jut. 1986 D. A. FORD and R. P. ARTHEY 17 Feb. 1986 11 p (PNR-90315; ETN-86-98020) Avail: NTlS HC A02/MF A01 (PNR-90320; ETN-86-98022) Avail: NTIS HC AO2/MF A01 The spectral differences in noise measurements on a range of A comprehensive family of alloys which meets the requirements aircraft types, when using microphones placed in a variety of of particular engine applications was developed. Alloy SRR is a locations between ground level and 10m were studied. Results high strength alloy to replace DS MM002 in applications where show that an inverted microphone configuration, on an easily increased creep, tensile, and fatigue strength are required; RR2000 portable plate, can be specified to eliminate the severe ground is designed for blades requiring low density or high impact interference effects experienced with the International Standard resistance; RR2060 was developed as a nozzle guide vane alloy, 1.2m high microphone. The move towards such a system by ICAO, with exceptional resistance to environmental attack and thermal for propeller powered light aircraft noise certification, is approved. fatigue. ESA

60 17 SOCIAL SCIENCES

17 A87-10942 INTEGRATED LOGISTICS FOR RECONNAISSANCE SYSTEMS SOCIAL SCIENCES E. A. VINTHEDEN (Forsvaret Materielverk, Stockholm, Sweden) IN: Airborne reconnaissance IX; Proceedings of the Meeting, San Diego, CA, August 20, 21, 1985 . Bellingham, WA, Society of Includes social sciences (general); administration and management; Photo-Optical Instrumentation Engineers, 1985, p. 74-84. documentation and information science; economics and cost Baselines are presented for a logistics reconnaissance system analysis; law, political science, and space policy; and urban management program, emphasizing LCC and having a view to technology and transportation. the most severe operational conditions. An attempt is made to develop fixed price, LCC-guaranteed multirole aircraft logistics for the year 2000 which incorporate an automated early warning feature A87-10508 and employ a mix of logistics personnel in the field; this personnel THE ROLE OF CHOICE OF LAW IN DETERMINING DAMAGES mix should encompass conscripts with comparatively little FOR INTERNATIONAL AVIATION ACCIDENTS specialized knowledge. O.C. K. S. CAGLE Journal of Air Law and Commerce (ISSN 0021-8642), vol. 51, Summer 1986, p. 953-1006. refs The increase in international air travel has not prompted A87-11804# uniformity among the laws governing damage awards to passengers THE SYSTEM ENGINEERING AND INTEGRATION CONTRACT injured in international flight. An investigation is conducted regarding - AN OVERVIEW the various agreements and regulations which may be involved in S. L. COPPS (Martin Marietta Cop, Air Traffic Control Div., the determination of damages for international flight accidents. An Washington, DC) IN: Radio Technical Commission for Aeronautics, analysis is performed of the liability limits available under the Annual Assembly Meeting and Technical Symposium, Washington, Warsaw system and the manner in which they are applied. Flights DC, November 19-21, 1985, Proceedings . Washington, DC, Radio not covered by the Warsaw system are also considered, taking Technical Commission for Aeronautics, 1985. p. 65-93. into account the foreign laws limiting liability, American approaches The systems engineering and integration actions which are regarding the choice of law analysis, and foreign approaches to being and have been implemented for realization of the National choice of law analysis. It is found that the choice of law analysis Airspace System (NAS) are summarized. The NAS is a can lead to widely divergent damage awards. Attention is given to modernization of the entire U.S. ATC system to improve current efforts to amend the Warsaw Convention and the Hague Protocol performance and to prepare for future demands. The project is a in Guatemala City in 1971, the Montreal Protocols adopted in joint FAAIMartin-Marietta (prime contractor) effort which is requiring 1975, and an alternative which provides uniformity among damage !u!! in!egrs?.!br! n! ac!ivlties cf private industry with established FAA awards in international transportation. G.R. practices. The private sector is furnishing the engineering and sytems integration and management expertise necessary to accomplish the $1 1.7 billion project under FAA guidance and A87-10509 monitoring. A block diagram is provided of the management KEEP YOUR EYE ON THE BIRDIE AIRCRAFT ENGINE BIRD - hierarchy. The NAS plan is updated each year to track progress INGESTION and changes in the Plan. The task is complicated by the need to A. MICHAEL Journal of Air Law and Commerce (ISSN R. maintain the existing ATC sytem while installing the new equipment 0021-8642), vol. 51, Summer 1986, p. 1007-1035. refs and training the operators. The feat is being handled by following In connection with the increasing speed of modern aircraft, a master transition plan which directs and monitors the progress the problem referred to as ’bird strike’ has become a hazard to and the interrelatedness of each sub-project of the Plan. M.S.K. aircraft. This is particularly true in the case of turboprop and jet aircraft. This article is concerned with the hazard posed to aircraft when birds are ingested into aircraft engines. A description is A87-11805# presented of federal regulations which recognize the hazard that PROJECT MANAGEMENT SUPPORT birds pose to aircraft by requiring aircraft engines to continue D. A. HARTEL (ARINC Research Corp., National Airspace Systems operation following bird ingestion. Bird ingestion crashes and cases Div., Annapolis, MD) IN: Radio Technical Commission for are discussed, taking into account the ’Boston Electra’ litigation, Aeronautics, Annual Assembly Meeting and Technical Symposium, the ’Executive Aviation’ litigation, the ’Miree’ litigation, the ’Hawaiian Washington, DC, November 19-21, 1985, Proceedings . Airlines’ litigation, and the modern trend. Attention is given to the Washington. DC, Radio Technical Commission for Aeronautics, various theories of liability proposed by plaintiffs, the legal defenses 1985, p. 99-106. available, and possible methods and procedures for avoiding bird The functions and activities of the Project Management Support ingestion. G.R. (PMS) group, which was established to ensure that the technical, schedule and cost objectives of the 90 projects of the National A87-10510 Airspace System Plan are accomplished are described. The PMS THE CRASH OF DELTA FLIGHT 191 - ARE THE NIGHTMARES personnel come from private industry and the Federal government. COMPENSABLE? The group reviews and documents technical specifications, R. PERLMAN Journal of Air Law and Commerce (ISSN implements management control systems for individual and interdependent projects, devises critical path schedules for the 0021-8642), vol. 51, Summer 1986, p. 1037-1084. refs On August 2, 1985, a wide-bodied airliner carrying 162 people various projects, and provides logistics support, including audits was involved in an aviation accident during its final descent into of project contractors. Also, the PMS on occassion provides Dallas/Fort Worth airport. There were only 31 survivors. The technical direction, i.e., guidance on the interpretation of technical present Comment is concerned with the causes of action available specifications. The functions of the group are illustrated through a in Texas which may allow survivors and witnesses of the crash to description of activities for the NADIN II data switching resources recover damages for emotional distress. The question of a project for establishing a packet-switched network for data communications in the NAS. M.S.K. bysiander’s riyiii oi ~etiuvwyin TCAZ fOi &magss caissd bj :hc negligent infliction of emotional distress is considered, taking into account the general situation in Texas, and the application of N87-10774# Committee on Appropriations (U. S. Senate). bystander rules in aircraft cases. Cases related to pain and suffering NATIONAL AERONAUTICS AND SPACE ADMINISTRATION actual damages are also considered, giving attention also to the In its Department of Housing and Urban Development-Independent unique pain and suffering caused by the terrifying fear that death Agencies Appropriation Bill, 1987 p 64-70 1986 is imminent, which is often called preimpact fear. The application Avail: US Capitol, Senate Document Room Of emotional distress damages to the bystanders and survivors of The appropriations for research, development, and procurement the considered flight is discussed. G.R. activities of NASA are discussed. B.G.

61 17 SOCIAL SCIENCES

N87-10779# Air Force Wright Aeronautical Labs., 19 Wright-Patterson AFB. Ohio. AIR FORCE TECHNICAL OBJECTIVE DOCUMENT FISCAL GENERAL YEAR 1987 W. E. BERNER and A. M. SALUS Dec. 1985 77 p Supersedes AMAL-TR-84-4000 (AD-A167324; AFWAL-TR-85-4000; AFWAL-TR-84-4000) Avail: NTlS HC A05/MF A01 CSCL 01C This technical objective document describes the technical A87-11339 program in materials to meet future Air Force operational needs. SCIENTIFIC PROBLEMS OF AVIATION AND SPACE: HISTORY The technology program is divided into ten focal areas which AND PRESENT STATE [NAUCHNYE PROBLEMY AVlATSlI I encompass the full spectrum of materials capabilities required for KOSMONAVTIKI: ISTORllA I SOVREMENNOST’] future aircraft, missile, space and electronic systems. These ten B. V. RAUSHENBAKH, ED. Moscow, Izdatel’stvo Nauka, 1985, areas are: Thermal Protection Materials and Structures; Metallic 200 p. In Russian. No individual items are abstracted in this Structural Materials; Nonmetallic Structural Materials; volume. Nondestructive Evaluation; Aerospace Propulsion Materials; Papers are presented on such topics as Chaplygin’s studies Nonstructural Materials; Electromagnetic Windows and Electronic on wing aerodynamics, Isaev’s spacecraft engine designs, the Materials; Laser Hardened Materials; Computer Aided automation of design work in aviation, current problems in the Manufacturing/Manufacturing R&D; and Systems Support. GRA testing of aircraft engines, ways to reduce effective thrust loss in supersonic aircraft powerplants, and air-flow stability in gas turbine engine compressors. Attention is also given to the numerical theory of the motion of the earth and Venus according to Venera probe observations, solar-sail rotor dynamics, the effect of additional degrees of freedom on the dynamics of a gravity gradient satellite with a magnetic damper, and numerical and analytical theories of the motion of the outer satellites of Jupiter. Questions of law and international cooperation pertaining to space are also considered. B.J.

N87-10827’# National Aeronautics and Space Administration, Washington, D.C. AERONAUTICS AND SPACE REPORT OF THE PRESIDENT 1985 148p (NASA-TM-89239; NAS 1.1589239; GPO-495-812) Avail: NTlS HC AO?/MF A01 CSCL 058 The achievements and activities of the United States aeronautics and space programs for 1985 are examined. The activities are listed by the sponsoring government agency. B.G. ,

SPACE SCIENCES

Includes space sciences (general); astronomy; astrophysics; lunar and planetary exploration; solar physics; and space radiation.

N87-10791 Cornell Univ., Ithaca, N.Y. INFRARED EMISSION LINES FROM PLANETARY NEBULAE Ph.D. Thesis M. A. SHURE 1985 156 p Avail: Univ. Microfilms Order No. DA8525805 The ionic abundances and electron temperatures in the central regions of a number of planetary nebulae were determined using infrared fine-structure lines in the 15 to 40 micron range. The 91 cm telescope of the NASA Kuiper Airborne Observatory was used to measure the following lines: (S Ill) 18.71, (Ar Ill) 21.83, (Ne V) 24.28, (0 IV) 25.87, (S Ill) 33.47, and Ne (Ill) 36.02 microns. Line emission was integrated over the entire emitting region in a total of twenty-two planetary nebulae, ranging from medium to high excitation. All except the (Ar 111) line were detected at greater than 3 sigma. Although optical emission lines were used for decades to derive both abundances and temperatures, use of the infrared lines offer two distinct advantages over the optical lines: infrared line emission is insensitive to temperature; and the high excitation ions O(IV) and Ne(V) prove regions closer to the central star than do the bright optical lines. As a consequence, abundances derived from infrared lines do not require accurate temperatures for nebulae, in contrast to the case for temperature-sensitiveoptical lines. Infrared ionic abundances are therefore potentially much more accurate than the optical abundances. By comparing integrated radio free-free emissions to the infrared line fluxes, abundances were determined for nineteen nebulae. Dissert. Abstr.

62 SUBJECT INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 270) February 1987

Qpical Subject Index Listing

ACOUSTIC EXCITATION Rotary balance data and analysis for the X 29A airplane AERODYNAMIC BALANCE Mechanics of flow-inducedsound and vibration. Volume for an angle of attack range of 0 deg to 90 deg Low speed rotary aerodynamics of F-I8 conlguration 1 General concepts and elementary source. Volume 2 . INASA CR 37471 p 15 N87 10837 to 90 deg angle 01 attack Test results and Complex flow-structure interactions --.Book Piloted simulation study of the effects of an automated p 57 A87-10293 trim system on flight characteristics of a light twin engine Excitation of the natural oscillations of a boundary layer airplane with one engine inoperative by an external acoustic field p4 A87-10610 INASA TP 2633 I p 16 N87 10843 ACOUSTIC MEASUREMENT AERODYNAMIC CHARACTERISTICS Sources and Observers in motion IV - Acoustic Aerodynamic anomalies Can CFD prevent or correct measurements on aerofoils moving in a circle at high them? Computational Fluid Dynamics for transport sped p 59 A87-12996 aircraft design p4 A87 10521 ACOUSTIC PROPAGATION Conical wing of maximum lift-to-dragratio in a supersonic Nonlinear acoustic propagation of broadband noise gas flow p4 A87 10615 p 58 A87-11773 ACOUSTIC SIMULATION Mathematical modeling of separated flow past a wing profile and aerodynamic hysteresis p 5 A87 10619 Freelet acoustic investigation of high-radius-ratio Methods of in flight aerophysical studies Russian The subject heading is a key to the subject content coannular plug nozzles book p 23 A87 11343 of the document The title is used to provide a INASA-CR-3818I p 59 N87-10753 ACOUSTIC VELOCITY Calculation of boundary layer of a three dimensional description of the subject matter When the title is S shaped inlet p 6 A87 11495 Investigation into the attenuationand velocity of acoustic Similarity law for the supersonic flow past flat surfaces insufficiently descriptive of the document content. emissions in carbon fiber composite aircraft structures with intense distributed inlection p 10 A87 12843 the title extension is added, separated from the title I BAE-KGT-R-GEN-013491 p 41 N87-10180 Laminar flow control for transport aircraft applications ADDIT I V ES by three hyphens The (NASA or AIAA) accession p 24 A87-13021 Thickened oils p 40 A87-12902 number and the page number are included in each ADHESIVE BONDING Prediction of gust loadings and alleviation at transonic speeds entry to assist the user in locating the abstract in How to maintain a consistent ouality in vour bonding I AU-Alb1148 1 p 13 N87-10047 the abstract section If applicable. a report number process? p 48 A87-12656 AERIAL RECONNAISSANCE Engine-airframe integration considerations lor is also included as an aid in identifying the preliminary air vehicle performance analysis Airborne reconnaissance IX; Proceedings of the p 26 N87 10068 document Under any one subject heading the Meeting. San Diego. CA. August 20, 21. 1985 Supersonic second order analysis and optimization accession numbers are arranged in sequence with ISPIE-561 I p 18 A87-10931 program users manual the AIAA accession numbers appearing first Long range E-0 ReconnaissanceSystem and flight test results p 28 A87-10933 [ NASA-CR 172342 I p 15 N87 10842 The KS-147A LOROP camera system AERODYNAMIC COEFFICIENTS Effects of flap position on longitudinal parameters of p 28 A87-10934 HFB-320 Integration of the KS-t47A LOROP into the RF-5E NAL-TM-SE 8602 p 25 N87-10062 p 28 A87-10935 : 1 Report on tests 01 a CAST 10 airfoil with lixed transition Operational usage of the KS-147A (LOROP) in the in the T2 transonic cryogenic wind tunnel with sell adaptive RF-5E p 29 A87-10936 walls Effects of atmosphere on oblique reconnaissance ... IRT OA 63116851 p 14 N87-10834 in CCD cameras p 29 A87-10937 Flight-determined aerodynamic derivatives of the AD-I Single or dual pod concepts for tactical reconnaissance p 29 A87-10939 oblique wing research airplane A NASA TP 2222 p36 N87 10871 Ground and flight tests of Tornado reconnaissance I I pod p 22 A87-10940 AERODYNAMIC CONFIGURATIONS A-10 AIRCRAFT Supersonic second order analysis and optimization Integrated logistics for reconnaissance systems Impact resistant hybrid composite for aircraft leading program user s manual p 61 A87-10942 edges p 24 A87 11848 I NASA CR 172342 1 p 15 N87-10842 Reconnaissance and the microprocessor --- in aircraft AERODYNAMIC DRAG A-310 AIRCRAFT applications p 29 A87-10943 Drag reducing outer layer devices 9" rough wall turbulent A 310 Aircraft Integrated Data Systems IAIDS) design Rapid rargei locator p 18 A87.iOY44 philosophy p 30 N87 10076 boundary layers p8 A87-11890 Data compression for IR reconnaissance The Airborne Integrated Data System (AIDS) for the Expansion of flow due to resistance of a wire gauze p 18 A87-10947 placed in a parallel sided channel p 48 A87-12133 Airbus A 310 engine condition monitoring Management of airborne reconnaissance images p31 N87 10082 The prediction of the drag of aerofoils and wings at through real-time processing p 19 A87-10949 high subsonic speeds p 9 A87 12266 Lufthansa s Aircraft Integrated Data Systems (AIDS) Reconnaissance interlace. The near real time is now Unsteady drag over cylinders and aerofoils in transonic based A 310 engine condition monitonng system Progress D 29 A87-10950 shork iuhe Ilnur~ pin 687

A- 1 AERODYNAMIC NOISE SUBJECT INDEX

Unsteady airload computations for airfoils oscillating in International Conference - Superplasticity in Aerospace The methodology and tools for processing radar data anached and separated compressible flow Aluminium . p19 A87-11662 [ NLR-MP-85040-Ul p 16 N87-10846 [ BAE-S85/AMR/0066] p 42 N87-10994 The system engineenng and integration contract . An AERODYNAMIC NOISE AEROSPACE INDUSTRY overview p 61 A87-11804 Sources and observers in motion. IV - Acoustic The influence of aerospace developments upon Project management support p 61 A87-11805 measurements on aerofoils moving in a circle a1 high developments in manufacturing p 1 A87-13002 FANS - A U S perspective p 20 A87-11607 speed p59 A87-12996 AEROSPACE SYSTEMS Automated functions for air traffic control systems Effect of static inplane loads and boundary conditions Air Force technical objective document fiscal year p21 A87-12687 on the flutter of flat rectangular panels 1987 A new concept in air traffic control - The multi-radar [ NAL-TM-ST-86041 p 50 N87-10404 [ ADA167324 ] p 62 N87-10779 tracking (MRT) p 21 A87-12689 Design and fabrication of the NASA decoupler pylon AEROTHERMODYNAMICS Helicopter MLS Flight Inspection Project for the F-16 aircraft. addendum 2 A bibliography of aerodynamic healing references [ DOT/FAAtCT-86/141 p2 N67-10002 [ NASA-CR-1724941 p 27 N87-10859 [BAE-BT-13481I p 14 N87-10832 The airlground transfer of aircraft integrated data Propeller aircraft interior noise model utilization study Host turbine heal transfer overview systems (AIDS) for Air Traffic Control (ATC) purposes and validation p 52 N87-11184 Present expenments and possible future intentions [ NASA-CR-1724281 p60 N87-11576 Aerothermal modeling program, phase 2 P 32 N87-10091 AERODYNAMIC STABILITY p 35 N87-11200 Potential impacts of advanced technoiogies on the ATC Acta Aeronautica et Aslronautica Sinica (selected AFTERBURNING capacity of high-density terminal areas articles) A test research for improving the performance of V-type [NASA-CR-4024] p 22 N67-10854 [ AD-A16791 81 p3 N87-10004 flameholder used in an afterburner p 34 A87-12965 Ground-based lime-guidance algorithm for control of Wind tunnel test of the modified goldschmied model AIR DATA SYSTEMS airplanes in a time-metered air traffic control environment: with propulsion and empennage: Analysis of test results Proceedings of the 13th Symposium on Aircran A piloted simulation study [ADA1673601 p13 N87-10045 Inlegrated Data Systems [NASA-TP-2616] p34 N87-10864 Performance and quality flight test textbook. Volume 2: [ DFVLR-MITT-86-04] p 30 N87-10075 AIR TRANSPORTATION Flying qualities A-310 Aircraft Integrated Data SystemS (AIDS) design Theoretical aspects and practical questions regarding [ AD-A1681241 p 3 N87-10830 philosophy p30 N87-10076 the assurance of flight safety p 17 A87-11900 Transonic flow analysis for rotors. Part 2: ' Aircraft Integrated Data Systems (AIDS): Evolution and AIRBORNE EQUIPMENT Three-dimensional, unsteady. full-potential calculation revolution p30 N87-10077 Airborne reconnaissance IX; Proceedings of the [ NASA-TP-23751 p15 N87-10841 Modern Aircraft Integrated Data Systems (AIDS) Meeting, San Diego. CA. August 20, 21. 1985 AERODYNAMIC STALLING technology exemplified on the A-320 p 30 N87-10078 [SPIE-561] p 18 A87-10931 Vortex sirnulationof propagating stall in a linear cascade Experience with the Onboard Checkout And Monitoring The KS-147A LOROP camera system of airfoils p5 A87-11117 System (OCAMS) of a military aircraft resulting p 28 A87-10934 Application of bifurcation and catastrophe theories lo improvements and the consequence for future design Operational usage of the KS-147A (LOROP) in the near stall flight mechanics p31 N87-10079 RF-5E D 29 A87-10936 [ AD-A1676971 p 13 N87-10046 Integrated monitoring systems for tactical aircraft Single or dual pod concepts for tactical AERODYNAMICS p 31 N87-10080 reconnaissance p 29 A87-10939 Recent developments in FEM-CFD p 5 A87-1141 I The Airborne Integrated Data System (AIDS) for the Integrated logistics for reconnaissance systems Numencal and physical aspects of aerodynamic flows Airbus A-310 engine condition monitoring p 61 A87-10942 111; Proceedings of the Third Symposium, California State p 31 N87-10082 Rapid target locator p 16 A87-10944 University, Long Beach, CA, January 21-24, 1985 Choosing Aircraft Integrated Data Systems (AIDS) Data processing and calibration for an airborne p 8 A87-11782 architecture suitable for Engine Health Monitonng (EHM) scallerometer p 30 A87-12694 Calculation methods for aerodynamic flows - A review on future generation engines p31 N87-10083 Minimum operational performance standards for p 8 A67-11783 Lufthansa's Aircraft Integrated Data Systems (AIDS) airborne ILS glide slope receiving equipment operating The classification of wind shears from the point of view based A-310 engine condition monitoringsystem: Progress within the radio frequency range of 328 6-335 4 MHz of aerodynamics and flight mechanics achieved between the 12th and 13th AIDS Symposiums [ RTCA/DO-192] p 21 N67-10853 p 24 A87-11898 p 31 N87-10084 AIRBORNE LASERS The balance between theoretical. computational and Data recovery techniques, an update --- flight data Laser airborne deoth soundina in Australia experimental work in turbomachines p 49 A87-13015 p 32 N87-10089 p 30 A87-12677 AEROELASTIC RESEARCH WINGS The airtground transfer of aircraft integrated data AIRBORNE SURVEILLANCE RADAR In-flight total forces. moments and static aeroelastic systems (AIDS) for Air Traffic Control (ATC) purposes: Stochastic modelling of radar returns characteristics of an oblique-wing research airplane Present experiments and possible future intentions p 18 A87-10143 [NASA-TP-2224] p 36 N87-10103 p 32 N87-10091 AIRBORNESPACEBORNE COMPUTERS AEROELASTICITY Airline data acquisition in an ACARS environment Reconnaissance and the microprocessor --- in aircraft Unsteady transonics of a wing with tip store p 32 N87-10092 applications p 29 A87-10943 p 4 A87-10524 Comparative evaluation of redundant flight data The ASPRO parallel inferenceengine (A real-time expert Aeroelastic stability of composite rotor blades in hover recorded by a digital aircraft integrated data system system) p 29 A87-12218 p25 N87-10060 recorder (DAR) on board an Airbus A-310 aircraft Digital data recording on floppy disks applied for Design and fabrication of the NASA decoupler pylon p 33 N87-10098 on-board use in helicopters for the F-16 aircraft AIR FLOW [ DFVLR-MI?T-86-10] p 51 N87-11149 [NASA-CR-172354] p25 N67-10065 Airborne measurement methods applied to the AIRCRAFT ACCIDENT INVESTIGATION Effect of static inplane loads and boundary conditions determination of boundary conditions at the sea surface. Case study of Royal Australian Air Force P3B Onon on the flutter of flat rectangular panels The TOSCANE experiment p 55 N87-11242 aircraft ground oxygen fire incident p 16 A87-10866 [NAL-TM-ST-66041 p 50 N67-10404 AIR LAW Aircraft accident reports Bnef formal US c~iland foreign Performance and quality flight test textbook. Volume 2: The role of choice of law in determining damages for aviation issue number 2 of 1985 accidents Flying qualities international aviation accidents p 61 A87-10508 [ PB86-9169161 p17 NE710056 [ AD-A1661 24 1 p 3 N67-10830 Keep your eye on the birdie - Aircraft engine bird The Boeing B 720 aircraft Controlled Impact AERONAUTICAL ENGINEERING ingestion p 61 A87-10509 Demonstration (CID) Flight data recordertcockpit voice Graduate engineering research participation in Flight recorders: New US regulations and new recorder expenment p 33 N87-10096 aeronautics International Civil Aviation Organization (ICAO) United Slates Navy - Canadian Forces solid state flight [NASA-CR-l79796] p 3 N87-10826 standards p 32 N87-10093 data recorderlcrash position locator expenment on the AERONAUTICAL SATELLITES AIR NAVIGATION 8.720 controlled impact demonstration Military aeronautical satellite communications Fundamentals of navigation according to geophysical p 33 N87-10097 p 18 A87-10137 fields --- Russian book p 19 A87-11337 AIRCRAFT ACCIDENTS AERONAUTICS Radio Technical Commission for Aeronautics. Annual The role of choice of law in determining damages for Scientific problems of aviation and space: History and Assembly Meeting and Technical Symposium, international aviation accidents p 61 A87-10508 present state --- Russian book p 62 A87-11339 Washington, DC. November 19-21, 1985. Proceedings Keep your eye on the birdie - Aircraft engine bird Radio Technical Commission for Aeronautics. Annual p1 A87-11601 ingestion p 61 A67-10509 Assembly Meeting and Technical Symposium, Transition to new systems and international The crash of Della Flight 191 - Are the nightmares Washington, DC, November 19-21, 1985. Proceedings per speclives p 20 A87-11806 compensable? p 61 A87-10510 p I A87-11601 Navigation and environment; Proceedings of the Fifth National Transportation Safety Board safety Joint National Symposium on the Influence of Aviation International Congress, Tokyo, Japan, October 1-5. 1985 recommendation p 18 N87-10852 on Engineeringand the Future of Aeronautics in Australia, p A87-12676 20 AIRCRAFT COMMUNICATION Melbourne. Australia. August 8. 9, 1985, Prepnnts and Characterizing height keeping error distribution based Supplementary Papers p 1 A87-13001 Military aeronautical satellite communications on indirect observation p 17 A67-12683 p 18 A87-10137 Developments at ARL to meet future Australian needs The U.S. Federal Radionavigation Plan in aeronautics p2 A87-13017 p 21 A87-12684 Disturbancesbrought by atmospheric statics to airborne AEROSPACE ENGINEERING Interferenceof the aeronauticalnavaids (frequencyband navigatlon and communication systems Annual Aerospace Applications of Artificial Intelligence 106-118 MHz) from F.M broadcasting service (88-108 p 20 A87-12678 Conference, 1st. Dayton. OH, September 16-19. 1965. MHz) p 21 A87-12690 AIRCRAFT COMPARTMENTS Proceedings p 56 A87-12211 AIR TO AIR REFUELING An expenmental investigationof the intenor noise control Joint National Symposium on the Influence of Aviation The lateral dynamic stability and control of a large effects of propeller synchrophasing on Engineeringand the Future of Aeronautics in Australia. receiver aircran during air-to-air refuelling [ NASA-CR-1781851 p 60 N87-11577 Melbourne, Australia, August 8, 9, 1985. Prepnnts and p36 A87-12268 AIRCRAFT CONFIGURATIONS Supplementary Papers p 1 A87-13001 AIR TRAFFIC CONTROL Effects of tail span and empennage arrangement on Developments at ARL lo meet future Australian needs Stochastic modelling of radar returns drag of a typical single-enginefighter aft end in aeronautics p2 A87-13017 p 16 A87-10143 [NASA-TP-23521 p 15 N87-10836

A-2 SUBJECT INDEX AIRCRAFT SPIN

AIRCRAFT CONSTRUCTION MATERIALS AIRCRAFT ENGINES Toward comparing experiment and theory for Composite materials for aircraft structures _..Book Evaluation of captured water column technology for corroborative research on hingeless rotor stability in p 38 A87-10294 advanced ultrasonic sizing techniques forward fight (an experimental and analytical investigation Properties and processing of fiber-reinforced p 45 A87-10728 of isolated rotor-flaplag stability in forward flight) polyetheretherketone (PEEK) p 38 A87-11372 Numerical analysis with generalized J-integral (NASA-CR-1797111 p25 N87-10063 Aeronautical manufacturers requirements for new p 47 A87-11492 AIRCRAFT NOISE materials p 38 A87-11791 Superplasticity in aeroengine titanium alloy VT-9 and Reaction to aircraft noise in resldential areas around Aeronautical research spin-offs on the development of its modified compositions p39 A87-12096 Australian airports p 54 A87-10116 civil applications for aluminium alloys p 48 A87-11792 A reinforcingband near the flange of a heated cylindrical Comparison of the effectiveness of measures of aircraft casing p 48 A87-12445 Impact resistant hybrid composite aircraft leading noise exposure by using social survey data for Advances in the vibration minitoring of gears and rolling edges p 24 A87-11848 p 54 A87-10117 element bearings p49 A87-1F7 Methods of in-flight aerophysical studies -__Russian Fiber-reinforced superalloy composites provide an Engine-Airframe Integration for Rotorcraft book p 23 A87-11343 added performance edge p39 A87-12647 [AGARD-LS-1481 p26 N87-10067 Improved durability airline paint schemes Engine-airkame integration considerations for Recent advances in aeroacoustics p 58 A87-11766 p 40 A87-12660 Preliminary air vehicle performance analysis Helicopter impulsive noise . Theoretical and New matenals in gas turbine technology p26 N87-10068 expenmental status p 58 A87-11771 p41 A87-13009 Engine-airkame integration for rotorcrak Component Resonant and non-resonant acoustic properties of Advanced fibre composites and other new materials for specifications and qualification p 26 N87-10071 elastic panels. I - The radiation problem airframe applications p 41 A87-13010 Influence of engine variables on future helicopter p 49 A87-13026 Structural design with new materials systems p27 N87-10072 Prediction of helicopter rotor discrete frequency noise: p49 AE7-13011 Helicopter air intake protection systems A computer program incocporating realistic blade motions Polymer systems for rapid sealing of aircraft structures p 27 N87-10073 and advanced acoustic formulation at low temperature Engine-airframe integration for rotorcraft: System [NASA-TM-87721I p59 N87-10750 [AD-At 676671 p 41 N87-10209 specifications and qualification p27 N87-10074 An experimentalinvestigation of the interior noise control Choosing Aircraft Integrated Data Systems (AIDS) International Conference Superplasticityin Aerospace effects of propeller synchrophasing - architecture suitable for Engine Health Monitoring (EHM) Aluminium [NASA-CR-178185] p 60 N87-11577 on future generation engines p31 N87-10083 [BAE-S85/AMR/0066] p 42 N87-10994 Aircraft mise measurement: The 1.2 metre microphone Future aereengine control systems. why FADEC? Cost, height saga Galvanic corrosion between carbon fiber reinforced design cycle timescale. reliability, weight and size targets [PNR-90315] p 60 N87-11578 plastics and metallic aeronautical materials --_ Full Authority Digital Electronic Control (FADEC) AIRCRAFT PARTS [ DFVLR-FB-86-16] p 42 N87-11003 [PNR-90298] p 35 N87-10867 Computerized ultrasonic test inspection enhancement AIRCRAFT CONTROL Engine performance monitoring for airlines system for aircraft components p 44 A87-10721 Reconnaissance interface - The near real time is now [PNR-903051 p35 N87-10868 In-service environmental effects on carbon fibre p 29 A87-10950 Turbine Engine Hot Section Technology, 1984 composite material p 39 A87-12659 The lateral dynamic stability and control of a large [ NASA-CP-2339] p 52 N87-11180 Advances in toughness of stnrctural composites based receiver aircraft during air-to-air refuelling AIRCRAFT EQUIPMENT on interleaf technology p40 A87-12661 p 36 A87-12268 Airborne reconnaisame IX; Proceedings of the AIRCRAFT PILOTS Application of bifurcation and catastrophe theories to Meeting, San Diego. CA. August 20, 21, 1985 Expert systems for aiding combat pilots near stall flight mechanics iSPIE-56i I p 18 A87-10931 p 29 A87-12212 [AD-A1676971 p 13 N87-10046 Single or dual pod concepts for tactical AIRCRAFT PRODUCTION Low speed rotary aerodynamics of F-18 configuration reconnaissance p 29 A87-10939 Palmdale and the bomber connection for 0 deg to 90 deg angle 01 attack: Test results and Aii Force technical obpctive document fiscal year p 22 A87-10574 analysis 1987 The influence of aerospace developments upon [NASA-CR-3608] p 15 N87-10836 [AD-A1673241 p 62 N87-10779 developments in manufacturing p 1 A87-13002 Rotary balance data and analysis for the X-BA airplane AIRCRAFT FUELS Computer integrated manufacturing for an angle-of-attack range of 0 deg to 90 deg Avgaslautogas comparison: Winter fuels p49 A87-13003 [NASA-CR-3747] p 15 N87-10837 [DOT/FAA-CT86/21] p 43 N87-11014 Manufacture of bonded composite assemblies for AIRCRAFT DESIGN AIRCRAFT GUIDANCE aircraft p 1 A87-13005 Aerodynamic anomalies - Can CFD prevent or correct Guidance strategies for near-optimum takeoff Future developments and manufacturing at GAF them? ..- Computational Fluid Dynamics for transport performance in a windshear p 24 A87-12138 p2 A87-13013 aircraft design p4 A87-10521 Flight expecimets on MLS elevation guidance Future developments and manufacturing at C.A.C Palmdale and the bomber connecton p21 A87-12686 p2 A87-13014 p 22 A87-10574 Energy management of 3-dimensional minimum-time AIRCRAFT PRODUCTION COSTS Yakovlev Forger --- history of the Yak-38 Soviet Very intercept p 27 N87-10858 Net shape forming: The route to low cost components. Short Takaand Landing aircraft. p 22 A87-10575 AIRCRAFT HAZARDS The view point of the aerospace industry Ground and flight tests of Tornado reconnaissance Fire occurring and expanding in Connection with oils in [PNR-90306] p 51 N87-tl020 pod p 22 A87-10940 aviation p 16 A87-11368 AIRCRAFT RELIABILITY Dirigibles - For what? p 23 A87-11681 Doppler Radar Detectionof Wind Shear Summary of artificial and natural icing tests conducted Numerical methods for engine-airframeintegration [ NASA-CP-24351 p 17 N87-10054 on US Army aircraft from 1974 to 1985 p 23 A87-11776 Vulnerability methodology and protective measures for [ FAA/CT-85/26] p25 N87-10064 CFD appiications to engine/airframe integration aircraf: fire and explosion hazards. Volume 3: On-Board National Transportation Safety Board safety p 23 A87-11780 Inert Gas Generator System (OBIGGS) studies. Part 1: recommendation pl8 N87-10852 CFD - A user's technology assessment -__for propulsion OBIGGS ground performance tests AIRCRAFT SAFETY integration and aircraft engine installation [AD-A167357] p 26 N87-10066 Braking performance of aircraft tires p 23 A87-11781 Surface measurements of gust fronts and microbursts p24 A87-12649 JAS39 Gripen - A Swedish solution to a multi-role during the JAWS (Joint Airport Weather Studies) Project: Condition monitoring of large commercial turbofan need p 23 A87-11798 Statistical results and implicationsfor wind shear detection, engines p 34 A87-13008 --..A:-*:-- ..-a ,.."Am,;"" __A ^_...__I:-:- ____I. A p'""'u.L'"" "8," .-. -a:':-:-, - .^.^ Siiusiuini liasiyii wiiii iiuw uiaiatiai. ,,,""..,,,*3 "Y"""~*y "I_. at,t,,..,a, (.I," IIatUI~,'LM'y .w=,i) *YIIYV*LW" p 49 A87-13011 [ PB66-2008471 p 55 N67-10665 on US Army aircraft from 1974 to 1985 The future of international air transport An investigation of the FAA vertical Bunsen burner [ FAA/CT-85/26] p25 N87-10064 p2 A87-13016 flammability test method Vulnerability methodology and protective measures for Laminar flow control for transport aircraft applications [WT/FAA/CT-B6/22] p 42 N87-10985 aircraft fire and explosion hazards. Volume 3: On-Board p 24 A87-13021 AIRCRAFT HYDRAULIC SYSTEMS Inert Gas Generator System (OBIGGS) studies. Part 1: Spin-tunnel investigation of a 1/25-scale model of the Fire occurring and expanding in connection with oils in OBIGGS ground performance tests General Dynamics F-16XL airplane aviation p16 A87-11368 [AD-A167357] p26 N87-10066 [ NASA-TM-856601 P 12 N87-10041 AIRCRAFT INSTRUMENTS NASA and FAA launch wind shear research project Engine-AirframeIntegration for Rotorcraft The evolution of air transport aircraft flight deck [ NASA-NEWS-REL-86-1431 p55 N87-10659 [ AGARD-LS-1481 P26 N87-10067 p 30 A87-12688 Surface measurements of gust fronts and microbursts Engine-transmission-structural airframe members AIRCRAFT LANDING during the JAWS (Joint Airport Weather Studies) Project compatibility P26 N87-10069 Laser remote sensing procedures provide an aid to Statistical results and implicationsfor wind shear detection. Response of a small-turboshaft-engine compression aviation during the approach for landing prediction and modeling svstem to inlet temoerature distortion p 1 a 47.r 1 ?7n [ PB86-2008471 p55 N87-10665 Ice accretion dependence [NASA-TM-83765] P 35 N87-10100 Project management support p 61 A87-11805 on cloud physical In-flight total forces, moments and static aeroelastic parameters p 55 N87-11433 characteristics of an oblique-wing research airplane Monitoring of terminal flight phases environment Ice accretion calculations on cylindrical rods following Observations and models p 55 A87-12679 [ NASA-TP-22241 P 36 N87-10103 the Bain model. and comparisonwith experimental results Supersonic second order analysis and optimization AIRCRAFT MAINTENANCE (Fuchs. Schickel, Kaluza. Uwira. 1985) program user's manual Condition monitoring of large commercial turbofan p 56 N87-11434 NASA-CR-1723421 p 15 N87-10842 engines p 34 A87-13008 The influence of weather-active fronts on visual flight Efficiency of various control surfaces in steady and Polymer systems for rapid sealing of aircraft structures conditions p 56 N87-11437 unsteady flow at low temperature AIRCRAFT SPIN [SNIAS-861-111-101] p 37 N87-10872 [ AD-A1676671 p 41 N87-10209 Low speed rotary aerodynamics of F-18 configuration Relevance of short fatigue crack growth data for AIRCRAFT MANEUVERS for 0 deg to 90 deg angle of anack Test results and durability and damage tolerance analyses of aircraft Maneuver optimization in the case of combat aircraft analysis [FFA-TN-1986-23] p 54 N87-11231 p 35 A87-11369 [ NASA-CR-36081 p 15 N87-10836

A-3 AIRCRAFT STABILITY SUBJECT INDEX

AIRCRAFT STABILITY Turbine Engine Hot Section Technology, 1984 Free-jet acoustic investigation of high-radius-ratio Non-linear stability analysis of aircraft a1 high angles [ NASA-CP-23391 p 52 N87-11180 coannular plug nozzles of attack p 36 A87-12082 Surface protection p 43 N87-11182 [NASA-CR-3818] ' p59 N87-10753 The lateral dynamic stability and control of a large Host turbine heat transfer overview APPLICATIONS PROGRAMS (COMPUTERS) receiver aircraft dunng air-to-air reluelling p 52 N87-11184 CSA/NASTRAN - A general purpose program for structural analysis p A87-10879 p36 A87-12268 Development of heat flux Sensors in turbine airfoils 56 Application 01 bifurcation and catastrophe theones to p 52 N87-11186 APPROACH Laser remote sensing procedures provide an aid lo near stall flight mechanics Measurement of airfoil heat transfer cwfficients on a [AD-A167697] p 13 N87-10046 aviation during the approach for landing turbine stage p 53 N87-11221 AIRCRAFT STRUCTURES p 19 A87-11370 hayof end effects in graphitelepoxy bolted joints AIRFRAME MATERIALS APPROPRIATIONS p 44 A87-10115 Advanced fibre composites and other new materials for National Aeronautics and Space Administration Tension analysis of stiffened aircraft structures airframe applications p 41 A87-13010 p 61 N87-10774 p 44 A87-10516 AIRFRAMES ARCHITECTURE (COMPUTERS) Palmdale and the bomber connection Engine-Airframe Integration for Rotorcraft Choosing Aircraft Integrated Data Systems (AIDS) p 22 A87-10574 [ AGARD-LS-148I p26 N87-10067 architecture suitable for Engine Health Monitoring (EHM) Electromagnetic methods to detect corrosion in aircraft Engine-airframe integration for rotorcraft: Component on future generation engines p 31 N87-10083 structures p 45 A87-10791 specifications and qualification p 26 N87-10071 ARMED FORCES (UNITED STATES) Certification problems for composite airplane Influence of engine variables on luture helicopter Air Force technical objective document fiscal year structures p 39 A87-12652 systems p 27 N87-10072 1987 How to maintain a consistent quality in your bonding Engine-airframe integration for rotorcraft: System [ AD-A1673241 p 62 N87-10779 process? p 48 A87-12656 specificationsand qualification p 27 N87-10074 ARTIFICIAL INTELLIGENCE Annual Aerospace Applications of Artificial Intelligence Development of a toughened bismaleimide resin prepreg AIRLINE OPERATIONS Conference, 1st. Dayton, OH, September 16-19, 1985, for carbon fiber composites p 40 A87-12667 The future international air transport of Proceedings p 56 A87-12211 Polymer systems for rapid sealing of aircraft structures p2 A87-13016 at low temperature ASTRONAUTICS The impact of flight data on an airline: A case study [ AD-A1676671 p 41 N87-10209 Scientific problems of aviation and space: History and p 32 N87-10086 Critical joints in large composite aircraft structure present state --- Russian book p 62 A87-11339 Airline data acquisition in an ACARS environment [ NASA-CR-37101 p 41 N87-10973 ATMOSPHERIC BOUNDARY LAYER p 32 N87-10092 DC-IO commsite vertical stabilizer around test Airborne measurement methods applied to the program Aviation statistics, 1984 determination of boundary conditions at the sea surface: [NASA-CR-3715] p 42 N87-10974 [ ISBN-90-357-0386-3I p 18 N87-10851 The TOSCANE experiment p 55 N87-11242 Critical commsite.. ioint subcornwnents: Analysis and Engine performance monitoring for airlines ATMOSPHERIC EFFECTS test results [PNR-90305] p 35 N87-10868 Disturbances brought by atmospheric statics to airborne [NASA-CR-3711] p 42 N87-10975 AIRPORTS navigation and communication systems Corrosion and corrosion prevention in aircraft Reaction to aircraft noise in residential areas around p 20 A87-12678 structures Australian airports p 54 A87-10116 ATMOSPHERIC ELECTRICITY [ NLR-MP-850294 p 43 N87-11004 I Surface measurements of gust fronts and microbursts Disturbances brought by atmospheric statics to airborne Separation of airborne and structureborne noise radiated dunng the JAWS (Joint Airport Weather Studies) Project: navigation and communication systems by plates constructed of conventional and composite Statistical results and implications for wind shear detection. p 20 A87-12676 materials with applications for prediction of interior noise prediction and modeling ATMOSPHERIC MODELS paths in propeller driven aircraft p 60 N87-11579 [ PB86-2008471 p 55 N87-10665 Ice accretion calculations on cylindrical rods following AIRCRAFT TIRES Potential impacts of advanced technologies on the ATC the Bain model, and comparison with experimental results Braking performance of aircraft tires capacity of high-density terminal areas (Fuchs, Schickel. Kaluza. Uwira, 1985) p 24 A87-12649 [ NASA-CR-40241 p 22 N87-10854 p 56 N87-11434 AIRCRAFT WAKES AIRSHIPS Euler equations analysis of the initial roll-up of aircraft Dirigibles - For what? p 23 A87-11661 ATMOSPHERIC SCAlTERING wakes p4 A87-10522 ALGORITHMS Effects of atmosphere on oblique reconnaissance --- Experimental and theoretical Doppler-lidar signatures of Signal processing and interpretation using multilevel in CCD cameras p 29 A87-10937 aircraft wake vortices p 14 N87-10330 signal abstractions AUDIO EQUIPMENT AIRFOIL PROFILES [ AD-A1691 66 I p 57 N67-11513 The FairchildCVDR: A new combination voice and data Development of a turbomachinery design optimization ALUMINUM recorder --- Cockpit Voice and Data Recorder (CVDR) procedure using a multiple-parameter nonlinear InternationalConference - Superplasticity in Aerospace p 33 N87-10095 perturbation method Aluminium AUTOMATIC CONTROL [ NASA-CR-3831I p 2 N87-10003 [BAE-S85/AMR/OO66] p 42 N87-10994 Reconnaissance interface - The near real time is now Vortex shedding of a square cylinder in front of a slender ALUMINUM ALLOYS p 29 A87-10950 airfoil at high Reynolds numbers. Part 1: Spacing effect Aeronautical manufacturers requirements for new Automated functions for air traffic control systems [MPIS-23/1985] p 13 N87-10048 materials p 38 A87-11791 p 21 A87-12687 AIRFOILS Aeronautical research spin-offs on the development of AUTOMATIC FLIGHT CONTROL Vortex simulation of propagating stall in a linear cascade civil applications for aluminium alloys p 48 A87-11792 Piloted simulation study of the effects of an automated of airfoils p5 A87-11117 In-service environmental effects on carbon fibre trim system on flight characteristics of a light twin-engine Numerical solution of the Euler equations using rational composite material p 39 A87-12659 airplane with one engine inoperative Runge-Kuna method p 7 A87-11538 The effects of temperature and loading rate on R-curves [ NASA-TP-26331 p 16 N87-10843 A split-matrix method for the integration of the using the CLWL techniques --- crack growth resistarice Potential impacts of advanced technologies on the ATC quasi-conservative Euler-equations p 7 A87-11544 curve (R curve); crack line wedge load (CLWL) capacity of high-density terminal areas Theoretical treatment of gust simulation in the wind [ BAE-MSM-R-GEN-0544I p 50 N87-10405 [ NASA-CR-40241 p 22 N87-10854 tunnel p 9 A87-12148 Galvanic corrosion between carbon fiber reinforced Efficiency of various control surfaces in steady and The prediction of the drag of aerofoils and wings at plastics and metallic aeronautical materials unsteady flow high subsonic speeds p 9 A87-12266 [ DFVLR-FB-86-16] p 42 N87-11003 [SNIAS-861-111-101I p 37 N87-10872 An exact integral (field panel) method for the calculation ALUMINUM OXIDES of two-dimensional transonic potential flow around Alumina-CoCrAIY material as an improved intermediate AUTOMATIC LANDING CONTROL complex configurations p 9 A87-12267 layer for graded ceramic gas-path sealing in aeroturbine Helicopter MLS Flight Inspection Project Sources and observers in motion. IV - Acoustic engines p 40 A87-12928 [ WT/FAA/CT-86/14] p2 N87-10002 measurements on aerofoils moving in a circle at high ANECHOIC CHAMBERS AUTOMATIC TEST EQUIPMENT Speed p 59 A87-12996 Sources and Observers in motion. IV - Acoustic RFC automated inspection overview --- eddy current and The effect of free stream disturbances and control measurements on aerofoils moving in a circle at high ultrasonic testing of gas turbine engine parts surface deflections on the performance of the Wortmann speed p 59 A87-12996 p 45 A87-10730 airfoil at low Reynolds numbers p 11 N67-10007 ANGLE OF ATTACK Technical diagnosis by automated reasoning Analysis of two-dimensional incompressible flow past Numerical simulation of viscous supersonic flow over p 57 A87-12217 airfoils using unsteady Navier-Stokes equations a generic fighter configuration p 6 A87-11509 How to maintain a consistent quality in your bonding [NASA-CR-1798231 p 12 N87-10040 Non-linear stability analysis of aircraft at high angles process? p 48 A67-12656 Prediction of gust loadings and alleviation at transonic of attack p 36 A87-12082 AUTOMATION speeds Application of bifurcation and catastrophe theones lo Project management support p 61 A87-11805 [AD-A167748] p 13 N87-10047 near stall flight mechanics FANS - A US. perspective p 20 A87-11807 Unsteady flow over an airfoil inside a wind tunnel with [AD-A167697] p 13 N87-10046 and without transpiration p 13 N87-10051 Automatically woven three-directional composite Low speed rotary aerodynamics of F-18 configuration structures p 48 A87-11843 Experimental study of the boundary layer on a low for 0 deg to 90 deg angle of attack: Test results and Reynolds number airfoil in steady and unsteady flow analysis AUTOMOBILE FUELS p 14 N87-10052 [ NASA-CR-36061 p 15 N87-10836 Avgas/autogas comparison: Winter fuels p 43 N87-11014 Report on tests of a CAST 10 airfoil with fixed transition Rotary balance data and analysis for the X-29A airplane [DOT/FAA-CT-86/21 I in the T2 transonic cryogenic wind tunnel with self-adaptive for an angle-of-attackrange of 0 deg to 90 deg AUTONOMOUS NAVIGATION walls [NASA-CR-3747] p 15 N87-10837 Knowledge-based tactical terrain analysis --- [RT-OA-63/1685] p 14 N87-10834 ANNULAR NOZZLES autonomous helicopter systems p 19 A87-11061 Visualization of three-dimensional forced unsteady Free jet feasibility study of a thermal acoustic shield Operating and support hazard analysis for self-contained separated flow concept for ASTIVCE application: Dual stream nozzles navigation system LSI model 6216A. B and C. group B [ ADA1689391 p 51 N87-11129 [NASA-CR-3867] p 59 N87-10752 [AD-A169381I p 22 N87-10855

A-4 SUBJECT INDEX CHARGE COUPLED DEVICES

AUTOROTATION BODY-WING CONFIGURATIONS CAMBERED WINGS Numerical and experimental study of dynamics of The possibility of the nondisturbing motion of a body Supersonic, nonlinear, attached-flow wing design for two-dimensional body in a fluid p 48 A87-12894 high lift with experimental validation [ ISAS-6191 p 59 N87-10748 BOEING AIRCRAFT [ NASA-TP-23361 p12 N87-10042 AVIONICS CFD applications to enginelairframe integration Numerical methods and a computer program for Military aeronautical satellite wmrnunications p 23 A87-11780 subsonic and supersonic aerodynamic design and analysis p 18 A87-10137 BOLTS of wings with attainable thNSt considerations Avionics in the sub-microscopic world Critical joints in large composite aircraft structure [ NASA-CR-38081 p3 N87-10829 p 48 A87-11800 [NASA-CR-3710] p 41 N87-10973 CAMERAS The evolution of air transport aircraft flight deck Critical composite joint subcomponents: Analysis and The KS-147A LOROP camera system test results p30 A87-12688 p 28 A87-10934 Experience with the Onboard Checkout And Monitoring [NASA-CR-3711] p 42 N87-lp975 BOMBER AIRCRAFT Operational usage of the KS-147A (LOROP) in the System (OCAMS) of a military aircraft resulting RF-BE p 29 A87-10936 improvements and the consequence for future design Stochastic crack propagation with applications to durability and damage tolerance analyses Effects of atmosphere on oblique reconnaissance --- p31 N87-10079 in CCD cameras p 29 A87-10937 Integrated monitonng systems fcf tactical aircraft [AD-AlW40] p 53 N87-11226 Reconnaissance and the microprocessor --- in aircraft p31 N87-10080 BOOMS (EQUIPMENT) applications p 29 A87-10943 Operatingand support hazard analysis for self-contained Flight service evaluation of composite helicopter CANARD CONFIGURATIONS navigatbn system LSI model 6216A, E and C, grwp E components [AD-A169381] p 22 N87-10855 [ NASA-CR-1781491 p 41 N87-10182 Wind-tunnel investigation of the flight characteristics of Low-cost avionics simulation for aircrew training BOUNDARY LAYER CONTROL a canard general-aviation airplane configuration [ NASA-TP-26231 [ AD-A1691 981 p34 N87-10865 Optimal control of viscous flow at high Reynolds p 12 N87-10039 Future aero-engine control systems, why FADEC? Cost, numbers p5 A87-10620 CANOPIES design cycle timescale. reliability. weight and size targets Wind tunnel test of the modified goldschmied model Numerical simulation of viscous supersonic flow over --- Full Authority Digital Electronic Control (FADEC) with propulsion and empennage: Analysis of test results a generic fighter configuration p6 A87-11509 [PNR-90298] p 35 N87-10867 [AD-A167360] p13 N87-10045 CARBON FIBER REINFORCED PLASTICS AXIAL FLOW BOUNDARY LAVER EQUATIONS Properties and processing of fiber-reinforced A study on the axially curved mixed-flow vaneless Calculation of strong vixous/inviscid interactions on polyetheretherketone (PEEK) p 38 A87-11372 diffusers p 47 A87-11481 airfoils by zonal solutions of the Navier-Stokes equations In-service environmental effects on carbon fibre AXIAL LOADS p 7 A87-11540 composite material p 39 A87-12659 Numerical soluson of the 3-dimensional boundary layer A higher order beam element for vibration of beams Advances in toughness of structural composites based equations in the invmmode using finite differences with discontinuities p 46 A87-10898 on interfeaf technology p40 A87-12661 p 11 N87-10005 AXISYMMETRIC BODIES Developmentof a toughened bismaleimide resin prepreg Eody of revolution comparisons for axial- and BOUNDARYLAYERFLOW Application of a 2D time-marching Euler code to for carbon fiber composites p40 A87-12667 surface-singularitydistributions p4 A87-10525 Investigationinto the attenuation and velocity of acoustic Method of meridional sections in problems involving a transonic turbomachinery flow p6 A87-11516 emissions in carbon fiber composite aircraft structures three-dimensionalboundary layer p 4 A87-10609 Images of three dimensional flows in computer [ BAE-KGT-R-GEN-013491 p 41 N87-10180 Static internal performance of single-expansion-ramp graphics p57 N87-10017 nozzles with thrust-vectoring capability up to w deg ROLINDARV LAVER SEPARATION Galvanic corrosion between carbon fiber reinforced plastics and metallic aeronautical materials 1 NASA-TP-23641 p i5 N67-1iB39 Acta Aeronautica et Astronautica Sinica (selected AXISYMMETRIC FLOW articles) [ DFVLR-FB-86-16] p 42 N87-11003 A split-matrix method for the integration of the [ AD-A1679 181 p3 N87-10004 CARGO quasi-conservativeEuler-equations p 7 A87-11544 Experimental study of the boundary layer on a low National Transportation Safety Board safety Reynolds number airfoil in steady and unsteady flow recommendation p 18 N87-10852 p 14 N87-10052 CASCADE FLOW B Visualization of three-dimensional forced unsteady Vortex simulation of propagatingstall in a linear cascade separated flow of airfoils p5 A87-11117 El AIRCRAFT [ AD-A1 689391 p51 N87-11129 Experimental investigation on the performances of a Palmdale and the bomber connection BOUNDARY LAYER TRANSITION transonic turbine blade cascade for varying incidence p 22 A87-10574 Excitation of the natural oscillations of a boundary layer angles p 9 A87-12205 BACKSCATTERING by an external acoustii field p4 A87-10610 Transonic cascade flow solved by shock-capture Variations in ultrasonic backscatter attnbuted to A nonperturbing boundary-layer transition detection computationfollowed by separate-regioncomputation with p 46 A87-10971 porosity p 45 A87-10768 shock fitting p 10 A87-12956 BASE FLOW Report on tests of a CAST 10 airfoil with fixed transition A numerical analysis of supersonic bottom flow with in the T2 transonic cryogenic wind tunnel with self-adaptive An experimental study on large negatwe incidence thermal modification of the wake p 3 A87-10409 walls separated flow in two-dimensionalturbine cascades BEARINGS [RT-OA-63/1685] p 14 N87-10834 p 10 A87;12957 Advances in the vibration monitoringof gears and rolling BOUNDARYLAYERS CASCADE WIND TUNNELS element bearings p 49 A87-13007 A comparison of interactive boundary-layer and The high speed cascade wind tunnel: Still an important BENDING thin-layer Navier-Stokesprocedures p 8 A87-11785 test facility for investigations on turbomachinery blades Aeroelastic stability of composite rotor blades in hover An experimental investgation of end-wall flowfield of a [ DFVLR-Mll7-86-11] p 38 N87-10878 p 25 N87-10060 compressor rotor p 50 N87-10244 CATALYSTS BIBLIOGRAPHIES BOUNDARY VALUE PROBLEMS Polymer systems for rapid sealing of aircraft structures A bibliography of aerodynamic heating references Three-dimensionalunsteady Euler equations solutions at low temperature [EAE-ET-13481] p 14 N87-10832 on dynamic grids [ AD-A1676671 p 41 N87-10209 BIRD-AIRCRAFT COLLISIONS [AD-A168041] p 51 N87-11128 CENTRIFUGAL COMPRESSORS Keep your eye on the birdie - Aircraft engine bird BRAKING A study on the axially Curved mixed-flow vaneless ingestion p 61 A87-10509 Braking performance of aircraft tires diffusers p 47 A87-11481 BlSMALElMlDE p 24 A87-12649 CERAMICS Development of a toughened bismaleimide resin prepreg BROADBAND Alumina-MtirAiy maienai as an improved inisriiiaiiaia for carbon fiber composites p40 A87-12667 On broadband shock associated noise of supersonic layer for graded ceramic gas-path sealing in aeroturbine BIT SYNCHRONIZATION jets p 58 A87-11768 engines p 40 A87-12928 Investigationson a digital bit synchronizer for a detailed Analyses of broadband noise mechanisms of rotors CERTIFICATION flight data recovery p33 N87-10099 p 58 A87-11769 Certification problems for composite airplane BLADE TIPS Nonlinear acoustic propagation of broadband noise structures p 39 A87-12852 Parametric analysis of a passive cyclic control device Summary of artificial and natural icing tests conducted for helicopters p 58 A87-11773 BROADCASTING on US Army aircraft from 1974 to 1985 [NASA-CR-166608] p 28 N87-10862 [FAA/CT-85/26] p25 N87-10064 BLADES Interferenceof the aeronautical navaids (frequencyband Calculation of unsteady supersonic flow past a plane 108-118 MHz) from F.M broadcasting service (88-108 CHANNEL FLOW blade row under the effect of vortex inhomogeneities in MHz) p 21 A87-12690 Motion of a gas in a duct behind a moving body p5 A87-10675 the oncoming flow p5 A87-10618 BURNERS BLOWING An investigation of the FAA vertical Bunsen burner Expansion of flow due to resistance of a wire gauze Biiiiiiariiy iaw fen iina supisuivit, iivw p& fht ~uikes flamrnahility test method placed in a parallel-sided channel p 48 A87-12133 with intense distributed injection p 10 A87-12843 [ WT/FAA/CT-86/22] p 42 N87-10985 Study of three-dimensional separation on a spheroia at BLUNT BODIES incidence p 49 N87-10016 Numerical investigation of supersonic flow past CHANNELS (DATA TRANSMISSION) spike-tipped blunt bodies p4 A87-10614 C The air/ground transfer of aircraft integrated data Implicit finite-difference simulation of separated systems (AIDS) for Air Traffic Control (ATC) purposes: hypersonic flow over an indented nosetip C BAND Present experiments and possible future intentions p 7 A87-11533 The C and Ku band scanerometer results from Canadian p 32 N87-10091 A split-matrix method for the integration of the participation in the ESA PROMESS ocean measurement CHARGE COUPLED DEVICES quasi-conservative Euler-equations p 7 A87-11544 campaign p 55 N87-11252 Long range E-0 Reconnaissance System and flight test BODIES OF REVOLUTION CALIBRATING results p 28 A87-10933 Eody of revolution comparisons for axial- and Data processing and calibration for an airborne Management of airborne reconnaissance images surface-singularitydistributions p4 A87-10525 scatterometer p 30 A87-12694 through real-time processing p 19 A87-10949

A-5 CHECKOUT SUBJECT INDEX

CHECKOUT COMPOSITE STRUCTURES Conference on Numerical Methods in Fluid Mechanics, Experience with the Onboard Checkout And Monitoring Decay of end effects in graphitelepoxy bolted joints 6th. Goeningen. West Germany. September 25-27. 1985. System (OCAMS) 01 a military aircraft resulting p 44 A87-10115 Proceedings p 47 A87-11501 improvements and the consequence for future design Composite materials for aircraft structures --- Bwk Implicit and semi-implicit methods for the compressible p31 N87-10079 p 38 A87-10294 Navier-Stokesequations p 47 A87-11503 Real time debugging software package for flight Nondestructive inspection 01 composite structures by A pre-processed implicit algorithm for 30 viscous Simulator software system with variable labeled COMMON low-velocity impact p 45 A67-10765 compressible flow p6 A87-11510 blocks hlification problems lor composite airplane Finite element computations for high speed 30 inviscid [ NLR-MP-85013-Ul p 57 N87-11530 structures p 39 A87-12652 flows p 7 A87-11542 CIRCULAR CYLINDERS Manufacture of bonded composite assemblies for Numerical methods for engine-airframe integration A description 01 a turbulent flow past a circular cylinder aircraft p 1 A87-13005 p 23 A87-11776 by a discrete vortex method pll N87-10014 A survey of composite grid generation for general Investigationinto the attenuation and velocity of acoustic CIVIL AVIATION three-dimensionalregions p 56 A87-11779 Aircraft accident reports: Brief &mat US civil and foreign emissions in carbon fiber composite aircraft structures CFD applications to enginelairframeintegration avintion, issue number 2 of 1985 accidents [ BAE-KGT-R-GEN-013491 p 41 N87-10180 p 23 A87-11780 [ Pd86-9169161 p 17 N87-10056 Flight service evaluation of composite helicopter CFD - A user's technology assessment _.-for propulsion Aviation statistics, 1984 components integration and aircraft engine installation [ iSBN-90-357-0386-3] p 18 N87-10851 [ NASA-CR-1781491 p 41 N87-10182 p 23 A87-11781 CLEANING Critical joints in large composite aircraft structure Numencal and physical aspects of aerodynamic flows Cleaning methods and procedures for military oxygen [ NASA-CR-37101 p 41 N87-10973 111; Proceedings of the Third Symposium. California State equipment - Investigation results p 46 A87-10867 DGIO composite vertical stabilizer ground test University, Long Beach, CA. January 21-24, 1985 CLOUD GLACIATION program p8 A87-11782 Ice accretion dependence on cloud physical [NASA-CR-37151 p 42 N87-10974 Calculation methods for aerodynamic llows - A review parameters p 55 N87-11433 Critical composite joint subcomponents: Analysis and p6 A87-11783 CLOUD PHYSICS test results Computations of separated subsonic and transonic flow Ice accretion dependence on cloud physical [NASA-CR-3711I p 42 N67-10975 about airfoils in unsteady motion p 8 A87-11786 parameters p 55 N87-11433 'COMPOSITE WRAPPING A laminar boundary layer method for flows in planes Ice accretion calculations on cylindrical rods following Automatically woven threedirectional composite of symmetry and application to inclined ellipsoids of the Bain model, and comparisonwith experimental results structures p 48 A67-11843 revolution p9 A67-12146 (Fuchs. Schickel. Kaluza. Uwira. 1965) The prediction of the drag 01 aerofoils and wings at COMPRESSIBLE BOUNDARY LAYER p 56 N87-11434 high subsonic spads p9 A87-12266 A laminar boundary layer method for flows in planes COASTAL WATER An exact integral (field panel) method for the calculation of symmetry and application to inclined ellipsoids of Laser airborne depth sounding in Australia of two-dimensional transonic potential flow around revolution p9 A87-12146 p 30 A87-12677 complex configurations p9 A87-12267 COBALT ALLOYS COMPRESSIBLE FLOW Transonic cascade flow solved by shock-capture Alumina-CoCrAIY material as an improved intermediate Vortex-stretched flow around a cranked delta wing computationfollowed by separate-regioncomputation with layer for graded ceramic gas-path sealing in aeroturbine p3 A87-10520 shock fining p 10 A87-12956 engines p 40 A67-12928 Implicit and semi-implicit methods for the compressible The balance between theoretical, computational and High temperature static strain gage program Navier-Stokes equations p 47 A87-11503 experimental work in turbomachines p 49 A87-13015 p 52 N87-11188 A pre-processed implicit algorithm for 3D viscous Numerical solution of the 3dimensional boundary layer COCKPITS compressible flow p6 A87-11510 equations in the inverse mode using finite differences Integration of the KS-147A LOROP into the RF-5E Numerical experiment with inviscid vortex-stretched flow p 11 N87-10005 p 28 A87-10935 around a cranked delta wing. supersonic spaed Report of the InternationalSymposium on Computational Reconnaissance interface - The near real time is now p 7 A87-11537 Fluid Dynamics, Tokyo p 49 N87-10029 p 29 A87-10950 Quantitative study of shock-generated compressible Computational aerodynamics of supersonic lifting CODING vortex flows p 10 A87-12616 vehicles p 12 N87-10030 Application of a potential code to general steady llows Unsteady airload cornputations for airfoils oscillating in Computation of transonic separated wing flows using in three dimensions p 50 N87-10262 attached and separated compressible flow an EulerlNavier Stokes zonal approach COLLISION AVOIDANCE [ NLR-MP-85040-UI p 16 N87-10846 p 16 N87-10849 Automated lunctions for air traffic control systems COMPRESSION TESTS Advanced method for computing the flow around wings p 21 A87-12687 Advances in toughness of structural composites based with rear separation and ground effect COMBAT on interleaf technology p 40 A87-12661 [ DFVLR-FB-86-17] p 50 N87-11017 Expert systems lor aiding combat pilots COMPRESSOR BLADES Coolant passage heat transfer with rotation, a progress p 29 A87-12212 Natural frequency analysis of compressor rotor blades report p 53 N87-11225 COMBUSTIBLE FLOW p 34 A87-10899 COMPUTATIONAL GRIDS Acta Aeronautica et Astronautica Sinica (selected Transonic cascade flow solved by shock-capture Euler solutions on 0-0 grids around wings using local articles) computation followed by separate-regioncomputation with refinement p6 A87-11512 [ AD-A16791 81 p3 N67-10004 shock fining p 10 A87-12956 Experiences with an unfactored implicit COMBUSTION CHAMBERS COMPRESSOR ROTORS predictor-corrector method p 47 A87-11522 Hot section viewing system Natural frequency analysis of compressor rotor blades A simulation of rotor-stator interaction using the Euler [NASA-CR-l74773] p 51 N87-11144 p 34 A87-10899 equations and patched grids p 7 A87-11536 Combustion overview p 43 N87-11181 An experimental investigation of end-wall flowfield of a Numerical solution of the Euler equations using rational Flame radiation p 43 N87-11204 compressor rotor p 50 N87-10244 Runge-Kuna method p 7 A87-11538 Calculation of strong viscouslinviscid interactions on COMBUSTION PRODUCTS COMPRESSORS Response of a small-turboshaft-engine Compression airfoils by zonal solutions of the Navier-Stokes equations A method for calculating the susceptibility of jet fuels system to inlet temperature distortion p7 A87-11540 to smoking p40 A87-12901 [ NASA-TM-837651 p 35 N87-10100 A survey 01 composite grid generation for general COMMAND AND CONTROL COMPUTATIONAL FLUID DYNAMICS three-dimensional regions p 56 A87-11779 Piloting of unmanned air vehicles. II A numerical analysis of supersonic bottom flow with COMPUTER AIDED MANUFACTURING p 23 A87-10941 thermal modification of the wake p 3 A87-10409 Computer integrated manulacturing COMMERCIAL AIRCRAFT Unsteady aerodynamic modeling of a lighter wing in p 49 A87-13003 Condition monitoring of large commercial turbofan transonic flow p3 A87-10517 COMPUTER ASSISTED INSTRUCTION engines p 34 A87-13006 Aerodynamic anomalies - Can CFD prevent or correct Low-cost awonics simulation lor aircrew training The future of international air transport them? --- Computational Fluid Dynamics for transport [AD-A169198] p 34 N87-10865 p2 A87-13016 aircraft design p4 A87-10521 COMPUTER GRAPHICS Aircraft accident reports: Brief format US &il and foreign Euler equations analysis of the initial roll-up of aircraft Images of three dimensional flows in computer aviation. issue number 2 of 1985 accidents wakes p4 A87-10522 graphics p 57 N87-10017 [PB86-916916] p 17 N87-10056 Further development of the inlluence function method COMPUTER PROGRAMS COMPARISON for store aerodynamic analysis p4 A87-10523 Numerical methods and a computer program for Avgaslautogas comparison: Winter fuels Unsteady transonics of a wing with tip store subsonic and supersonic aerodynamic design and analysis [DoTIFAA-CT-66/21] p 43 N87-11014 p4 A87-10524 of wings with attainable thrust considerations COMPONENT RELIABILITY Method of meridional sections in problems involving a [ NASA-CR-3808I p3 N87-10829 Engine-transmission-structural airframe members three-dimensionalboundary layer p 4 A87-10609 Real time debugging software package lor flight compatibility p26 N87-10069 Numerical investigation of supersonic flow past simulator software system with variable labeled COMMON Engine-airframe integration for rotorcraft: Component spike-tipped blunt bodies p4 A87-10614 blocks Calculation of unsteady supersonic flow past a plane [ NLR-MP-65013-UI p 57 N87-11530 Specificationsand qualification p 26 N87-10071 blade row under the effect of vortex inhomogeneities in Propeller aircraft interior noise model utilization study COMPOSITE MATERIALS the oncoming flow p5 A87-10618 and validation Composite materials for aircraft structures --- Bwk Mathematical modeling of separated flow past a wing [ NASA-CR-1724281 p 60 N87-11576 p 38 A67-10294 profile and aerodynamic hysteresis p 5 A87-10619 COMPUTER SYSTEMS DESIGN Testing of Fe-Cu-baseablative composites. II Recent developments in FEM-CFD p 5 A87-11411 Choosing Aircraft Integrated Data Systems (AIDS) p 41 A87-12971 Computation of turbulent supersonic flows around architecture suitable for Engine Health Monitoring (EHM) Separation of airborneand structureborne noise radiated pointed bodies having crossflow separation on future generation engines p 31 N87-10083 by plates constructed of conventional and composite p 5 A87-11487 COMPUTER SYSTEMS PROGRAMS materials with applications for predlction of interior noise Calculation of boundary layer of a three dimensional Software for flight recorder data processing developed paths in propeller driven aircraft p 60 N87-11579 S-shaped inlet p6 A87-11495 by Lufthansa p 32 N87-10090 A-6 SUBJECT INDEX DATA PROCESSING

Real time debugging software package for flight The effect of free stream disturbances and control CRASH LANDING simulator software system with variable labeled COMMON Surface deflections on the perlormance of the Wortmann Aircraft accident reeport, Delta Air Lines, Inc.. Lockheed blocks airfoil at low Reynolds numbers p 11 N87-10007 L-1011-385-1. N726DA, Dallas/Fort Worth International [ NLR-MP-85013-U1 p 57 N87-11530 Prediction of gust loadings and alleviation at transonic Aim, Texas, August 2. 1985 COMPUTER TECHNIQUES speeds [ PB86-910406] p 17 N87-10053 A computer-aided MmdeStNCtNe inspection system [ AD-A1677481 p 13 N87-10047 The Boeing B 720 aircraft Controlled Impact p 44 A87-10720 Tunnel interference from pressure measurements on Demonstration (CID): Flight data recorderlcockpit voice Computerized ultrasonic test inspectin enhancement control surfaces recorder experiment p33 N87-10096 system for aircraft componenls p 44 A87-10721 [ AE-TM-8-83] p 37 N87-10104 United States Navy ~ Canadian Forces solid state flight Efficiency of various control surfaces in steady and Photogrammetric tools for panoramic sector scan data recordedcrash position locator experiment on the imagery in the VIDARS analysis station unsteady flow B-720 controlled impact demonstration [SNIAS-861-111-101] p 37 N87-1?872 p 19 A87-10948 p33 N87-10097 CONTROL SYSTEMS DESIGN Expert systems for aiding combat pilots CRASHES Performance monitwing of sensors in high reliable fliht p 29 A87-12212 control systems using deterministic Observers The crash of Delta Flight 191 . Are the nightmares COMPUTERIZED SIMULATION compensable? p 61 A87-10510 p32 N87-10087 A simulation of rotor-stator interaction using the Euler Technology review of flight crucial flight control systems CRASHWORTHINESS equations and patched grids p 7 A87-11536 (application of optical technology) Crashwcfthiness experiment summary full-scale CONCAVITY [NASA-CR-l72332] p 36 N87-10102 transport controlled impact demonstration program On the occurrence of regular reflection of shocks in Fault tolerant control laws [ WT/FAA/CT-85/20] p 17 N87-10055 concave corner flows p 10 A87-12586 [NASA-CR-178094] p 50 N87-10400 Aircraft accident reports: Brief format US civil and fcfeign CONFERENCES Future aero-engine control systems. why FADEC?Cost. aviation, issue number 2 of 1985 accidents Flammability and sensitivity of materials in design cycle timescale. reliability, weight and size targets [PB86-916916] p17 N87-10056 oxygen-enriched atmospheres; Proceedings of the --- Full Authority Digital Electronic Control (FADEC) The Boeing B 720 aircraft Controlled Impact Symposium, Washington. D€. April 23, 24. 1985. Volume [PNR-902981 p 35 N87-10867 Demonstration (CID): Flight data recorder/cockpit voice 2 p38 A87-10859 Efficiency of various control surfaces in steady and recorder experiment p33 N87-10096 Airborne reconnaissance IX Proceedings of the unsteady flow CREEP PROPERTIES Meeting, San Diego. CA, August 20, 21. 1985 [SNIAS-861-111-101~ p 37 N87-10872 Biaxial constitutive equation development [SPIE-561] p 18 A87-10931 CONTROL mEmv p 53 N87-11217 Conference on Numerical Methods in Fluid Mechanics, Performance and quality flight test textbook. Volume 2 CRITICAL LOADING 6th. Goeningen. West Germany, September 25-27, 1985, Flying qualities The effects of temperature and loading rate on R-curves Proceedings p47 A87-11501 [ AD-A1681 241 p3 N87-10830 using the CLWL techniques -_- crack growth resistance Recent advances in aeroacoustics p 58 A87-11766 CONVERGENT-DIVERGENT NOZZLES curve (R curve); crack line wedge load (CLWL) On broadband shock associated noise of supersonic Numerical methods for engine-airframeintegration [ BAE-MSM-R-GEN-05441 p 50 N87-10405 jets p 58 A87-11768 p A87-11776 Critical joints in large composite aircraft structure 23 COOLING SYSTEMS [ NASA-CR-37101 p 41 N87-10973 Numerical and physical aspects of aerodynamic flows Coolant passage heat transfer with rotation, a progress CROSS CORRELATION 111; Proceedings of the Third Symposium. California State report p 53 N87-11225 !kiv?xs!?;, Lnng EIpch. CA. January 21-24. 1985 COPPER ALLOYS Investigationson a digital bit synchronizer for a detailed flight data recovery p 33 N87-10099 p8 A87-11782 Testing of Fe-Cu-base ablative composites. II Radio Technical Commission for Aeronautics, Annual p 41 A6i-i297: CROSS FLOW Assembly Meeting and Technical Symposium, CORNER FLOW Computation of turbulent supersonic flows around Washington, E€. November 19-21, 1985. Proceedings On the occurrence of regular reflection of shocks in pointed bodies having crossflow separation pi A87-11801 concave corner flows p 10 A87-12586 p5 A87-11487 Annual Aerospace Applications of Artificial Intelligence CORROSION CURING Conference, 1st. Dayton, OH, September 16-19. 1985. Electromagnetic methods lo detect corrosion in aircraft Polymer systems for rapid sealing of aircraft Structures Proceedings p 56 A87-12211 structures p 45 A87-10791 at low temperature Progress in advanced materials and processes: Corrosion and ccfrosion prevention in aircraft [AD-A167667] p41 N87-10209 Durability.reliability and quality control: Proceedings of the structures CURVE0 BEAMS Sixth International European SAMPE Conference. [ NLR-MP-85029-Ul p 43 N87-11004 A higher order beam element for vibration of beams Scheveningen, Netherlands, May 28-30. 1985 CORROSION PREVENTION with discontinuities p46 A87-10898 p39 A87-12651 Improved durability airline paint schemes CYCLIC LOADS Navigation and environment; Proceedings of the Fifth p40 A87-12660 Fractographic aspects of the cyclic fracture toughness International Congress, Tokyo, Japan, October 1-5. 1985 Corrosion and corrosion prevention in aircraft of 35KhN3MFA steel in vacuum, air, and hydrogen p 20 A87-12676 structures p 40 A87-12882 Joint National Symposium on the Influence of Aviation [NLR-MP-85029-U] p 43 N87-11004 CYLINDRICAL BODIES on Engineeringand the Future of Aeronautics in Australia. COST EFFECTIVENESS Vortex shedding of a square cylinder in front of a Bender Melbourne. Australia, August 8. 9. 1985, Preprints and Influence of engine variables on future helicopter airfoil at high Reynolds numbers. Part 1: Spacing effect Supplementary Papers p 1 A87-13001 systems p 27 N87-10072 [ MPIS-23/1985] p 13 N87-10048 Report of the InternationalSymposium on Computational CYLINDRICAL SHELLS Fluid Dynamics, Tokyo p 49 N87-10029 The 3D inelastic analysis methods for hot section components p 53 N87-11206 A reinforcing band near the flange of a heated cylindrical Doppler Radar Detection 01 Wind Shear casing p 48 A87-12445 [ NASA-CP-24351 p17 N87-10054 Cost effective single crystals --- gas turbine Proceedings of the 13th Symposium on Aircraft components Integrated Data Systems [ PNR-903191 p60 N87-11615 D [DFVLR-MIlT-86-04] p 30 N87-10075 COST REDUCTION Turbine Engine Hot Section Technology, 1984 Net shape forming: The route to low cost components. DAMAGE [NASA-CP-2339] p 52 N87-11180 The view point of the aerospace industry Stochastic crack propagation with applications to LCUF!GL'%.T!9!! !UTFRA.CTION [PNR-90306] p 51 N87-I1020 durability and damage tolerance analyses A simulation of rotor-stator interaction using the Euler COUNTER ROTA1ION [ An-Al W040I p 53 N87-11226 equations and patched grids p 7 A87-11536 Rotary balance data and analysis for the X-29A airplane DATA ACQUISITION CONICAL BODIES for an angle-of-attack range of 0 deg to 90 deg Experimental study of the boundary layer on a low Conicalwing of maximum lift-to-drag ratio in a supersonic [ NASA-CR-37471 p 15 N87-10837 Reynolds number airfoil in steady and unsteady flow gas flow p4 A87-10615 Effect of angular inflow on the vibratory response of a p14 N87-10052 CONICAL FLOW counter-rotating propeller Airline data acquisition in an ACARS environment Supersonic flow around tip sides of wings [NASA-CR-174819] p 15 N87-10840 p32 N87-10092 p12 N87-10033 CRACK PROPAGATION Correlation between flight simulation and processing of CONICAL NOZLES Certification problems for composite airplane flight tests based on inertial measurements Density field of a viscous gas jet issuing from a conical structures p 39 A87-12652 1NLR-MP-65058-U] p 28 N87-10863 nozzle into vacuum p4 A87-10603 The effects of temperature and loading rate on R-curves DATA COMPRESSION CONSTITUTIVE EQUATIONS Data compression for IR reconnaissance Biaxial constitutive equation development using the CLWL techniques __-crack growth resistance curve (R curve); crack line wedge load (CLWL) p 18 A87-10947 p 53 N87-11217 [BAE-MSM-R-GEN-05441 p 50 N87-10405 Data compression techniques for multifunction flight CONSTRAINTS data recorders p33 N87-10094 Elevated temperature crack growiii Guidebook for analysis of tether applications DAlA LINK6 p 53 N87-11214 [NASA-CR-178904] p 38 N87-10169 The airlground transfer of aircraft integrated data CONTAMINATION Stochastic crack propagation with applications to systems (AIDS) for Air Traffic Control (ATC) purposes: Response of a small-turboshaft-engine compression durability and damage tolerance analyses Present experiments and possible future intentions system to inlet temperature distortion [AD-AI 680401 p 53 N87-11226 p32 N87-10091 [NASA-TM-837651 p35 N87-10100 Relevance of short fatigue crack growth data for DATA PROCESSING CONTRACT MANAGEMENT durability and damage tolerance analyses of aircraft Data processing and calibration for an airborne The system engineering and integration contract - An [FFA-TN-1986-23] p 54 N87-11231 scatterometer p 30 A87-12694 overview p 61 A87-11804 CRACKS Data recovery techniques. an update --- flight data CONTROLSURFACES Relevance of short fatigue crack growth data for p 32 N8i-10089 The possibility of the nondisturbing motion of a body durability and damage tolerance analyses of aircraft Software for flight recorder data processing developed in a fluid P 48 A87-12894 [ FFA-TN-I986.231 p 54 N87-11231 by Lufthansa p 32 N87-10090

A-7 SUBJECT INDEX

DATA RECORDING Potential impacts of advanced technologies on the ATC ELECTRONIC CONTROL Data compression techniques for multifunction flight capacity of high-density terminal areas Operatingand support hazard analysis for self-contained data recorders p33 N87-10094 [NASA-CR-40241 p 22 N87-10854 navigation system LSI model 6216A. B and C. group B Digital data recording on floppy disks applied for Operatingand support hazard analysisfor self-contained [AD-A169381] p 22 N87-10855 on-board use in helicopters navigation system LSI model 6216A. B and C. grwp B ELECTRONIC EQUIPMENT TESTS [DFVLR-MITT-86-10] p 51 N87-11149 [AD-A16938l I p 22 N87-10855 Investigationof optimal complexityof BITE and its effects DECOUPLING DOPPLER EFFECT on reliability, maintainability.monitoring and fault prediction Design and fabrication of the NASA decoupler pylon Operatingand support hazard analysis lor self-contained ___ Built-In Test (BITE) electronic systems for the F-16 aircraft, addendum 1 nawgatlon system LSI model 6216A. B and C, group B [ ETN-86-979761 p51 N87-11175 [ NASA-CR-1723551 p 27 N87-10860 [AD-A169381I p 22 N87-10855 ELLIPSOIDS A laminar boundary layer method for flows in planes DEFENSE PROGRAM DOPPLER RADAR Air Force technical objective document fiscal year of symmetry and application to inclined ellipsoids of Doppler Radar Detection of Wind Shear revolution p9 A87-12146 1987 [ NASA-CP-24351 p 17 N87-10054 [ AD-AI 673241 p 62 N87-10779 ELLIPTICAL CYLINDERS Expenmental and theoretical Doppler-lidarsignatures of Numerical and experimental study 01 dynamics of Aeronautics and space reporl of the President aircraft wake vortices p 14 N87-10330 [ NASA-TM-892391 p 62 N87-10827 two-dimensional body DELTA WINGS NASA and FAA launch wind shear research project [ISAS-619] p 59 N87-10748 [ NASA-NEWS-REL-86-143 p 55 N67-10659 Vortex-stretched flow around a cranked delta wing I ENERGY CONSERVATION p3 A87-10520 DRAG MEASUREMENT Ground-based time-guidance algorithm lor Control of Numerical experiment with inviscidvortex-stretched flow Unsteady drag over cylinders and aerofoils in transonic airplanes in a time-meteredair traffic control environment: around a cranked delta wing, supersonic speed shcck tube flows p 10 A87-12617 A piloted simulation study p 7 A87-11537 DRAG REDUCTION [ NASA-TP-26161 p 34 N87-10664 Expenmental investigations of three-dimensional Optimal control of viscous flow at high Reynolds ENGINE AIRFRAME INTEGRATION laminar boundary layers on a slender delta wing numbers p 5 A87-10620 Numerical methods for engine-airframeintegration p9 A87-12145 Drag reducingouter-layer devices in rough wall turbulent p 23 A67-11776 Analysls of the vwtical flow around a 60 deg Delta wing boundary layers p6 A87-11890 CFD applications to engine/airframe integration p 23 A67-11780 with vortex flap pll N87-10006 The possibility of the nondisturbing motion Of a body DENSITY DISTRIBUTION in a fluid p 48 A87-12894 CFD ~ A user's technology assessment --- for propulsion Density field 01 a viscous gas jet issuing from a conical integration and aircraft engine installation Laminar flow control for transport aircraft applications p 23 A87-11781 nozzle into vacuum p 4 A87-10603 D 24 A67-13021 ENGINE DESIGN DEPOSITION DRILLING The balance between theoretical. computational and Ice accretion dependence on cloud physical Modeling and analysis of the dynamics of a dnll experimental work in turbomachines p 49 A87-13015 par am e t er s p 55 N87-11433 penetrating a thin plate Component specific modeling p 35 N87-11207 DEPTH MEASUREMENT [ASME PAPER 86-WA/APM-33] p 46 A87-11112 ENGINE FAILURE Laser airborne depth sounding in Australia DYNAMIC STABILITY p 30 A87-12677 Advances in the vibration monitoring of gears and rolling Performance and quality flight test textbook Volume 2 element bearings p 49 A87-13007 DESIGN ANALYSIS Flying qualities Piloted simulation study of the effects of an automated The KS-147A LOROP camera system [ AD-A1 681 241 p3 N87-10830 trim system on flight characteristics of a light twin-engine p 28 A87-10934 DYNAMIC STRUCTURAL ANALYSIS Integration of the KS-147A LOROP into the RF-5E airplane with one engine inoperative Stress analysis of Pathfinder-2 models [NASA-TP-26331 p 16 N67-10843 p 28 A87-10935 [NASA-CR-1724581 p 51 N87-11179 ENGINE MONITORING INSTRUMENTS Piloting of unmanned air vehicles. II DYNAMICAL SYSTEMS Condition monitoring of large commercial turbofan p 23 A87-10941 Dynamic flight optimization p 24 A87-11899 engines p 34 A87-13006 Development of a turbomachinery design optimization An experimental investigation of dynamic ground Experience with the Onboard Checkout And Monitoring procedure using a multiple-parameter nonlinear effect p 14 N87-10833 System (OCAMS) of a military aircraft resulting perturbation method DYNAMOMETERS improvements and the consequence for future design [NASA-CR-3831] p2 N87-10003 Avgaslautogas comparison Winter luels p 31 N87-10079 Numerical methods and a computer program for [ WT/FAA-CT-86/21] p 43 N87-11014 subsonic and supersonic aerodynamic design and analysis The Airborne Integrated Data System (AIDS) for the 01 wings with attainable thrust considerations Airbus A-310 engine condition monitoring [ NASA-CR-38081 p3 N67-10829 E p 31 N87-10082 Design and fabrication of the NASA decoupler pylon Choosing Aircraft Integrated Data Systems (AIDS) lor the F-16 aircraft, addendum 2 ECONOMIC ANALYSIS architecture suitable lor Engine Health Monitoring (EHM) [ NASA-CR-1724941 p 27 N87-10859 The future of international air transport on future generation engines p 31 N87-10083 Development of heat flux sensors in turbine airfoils p2 A87-13016 Lufthansa's Aircraft Integrated Data Systems (AIDS) p 52 N87-11166 EDDYCURRENTS based A-310 engine condition monitoringsystem: Progress DESIGN TO COST RFC automated inspectionoverview --- eddy current and achieved between the 12th and 13th AIDS Symposiums ultrasonic testing of gas turbine engine parts JAS39 Gripen - A Swedish solution to a multi-role p 31 N87-10084 D 45 A87-10730 need p 23 A87-11796 Engine performance monitoring for airlines Predictwe models and reliability improvement in [PNR-90305] p 35 N87-10868 DIFFERENTIAL EQUATIONS electromagnetic nondestructive evaluation ENGINE NOISE AerOelastic stability of composite rotor blades in hover D 45 A67-10732 Nonlinear acoustic propagation of broadband noise p25 N87-10060 Electromagnetic methods to detect corrosion in aircraft p 58 A87-11773 DIFFUSERS structures p 45 A87-10791 Expansion of flow due to resistance of a wire gauze ELASTIC PLATES ENGINE PARTS placed in a parallel-sided channel p 48 A87-12133 Resonant and non-resonant acoustic properties 01 Manufacturingtechnology for nondestructiveevaluation DIGITAL DATA elastic panels I - The radiation problem (NDE) system to implement retirement for cause (RFC) Airline data acquisition in an ACARS environment p 49 A67-13026 procedures for gas turbine engine components p 32 N87-10092 ELECTRICAL RESISTIVITY p 44 A87-10727 Digital data recording on lloppy disks applied for Nickel coated graphite fiber COndUCtNe composltes Evaluation of captured water column technology lor on-board use in helicopters p 39 A87-11644 advanced ultrasonic sizing techniques [ DFVLR-MITT-86-10] p 51 N87-11149 High temperature static strain gage program p 45 A87-10728 DIGITAL TECHNIQUES p 52 N87-11188 RFC automated inspection overview -..eddy current and Photogrammetric tools for panoramic sector Scan Evaluation results 01 the 700 deg C Chinese strain ultrasonic testing of gas turbine engine parts imagery in the VIDARS analysis station gages p 52 N87-11189 p 45 A87-10730 p 19 A87-10948 ELECTRO-OPTICS Elevated temperature crack growth Management of airborne reconnaissance images Rapid target locator p 18 A87-10944 p 53 N87-11214 through real-time processing p 19 A87-10949 Technolcqy review of fliaht crucial fliqht control systems ENGINE TESTING LABORATORIES Future aero-enginecontrol systems. why FADEC? Cost, (applicationof optical techno~ogy) Aeronautical facilities assessment design cycle timescale, reliability, weight and size targets INASA-CR-1723321 D 36 N87-10102 [NASA-RP-1146] p 37 N87-10876 --- Full Authority Digital Electronic Control (FADEC) E~ECTROCHEMICA~CORROSION ' ENGINE TESTS [PNR-90298] p 35 N87-10867 Galvanic corrosion between carbon fiber reinforced A test research for improving the performance of V-type plastics and metallic aeronautical materials flameholder used in an afterburner p 34 A87-12965 DIRECTIONAL STABILITY [DFVLR-FB-86-16] p 42 N87-11003 Response of a small-turboshaft-engine compression Performance and quali flight test textbook. Volum 2: ELECTRODYNAMICS Flying qualities Guidebook for analysis of tether applications system to inlet temperature distortion [ NASA-TM-83765 p 35 N87-10100 [AD-A168124] p3 N87-10830 [NASA-CR-l76904] p 38 N87-10169 I DISCONTINUITY ELECTROMAGNETIC MEASUREMENT PTA test bed aircraft engine inlet model test report. A higher order beam element for vibration of beams Predictive models and reliability improvement in revised with discontinuities p 46 A87-10898 electromagnetic nondestructive evaluation [NASA-CR-1748451 p 35 N87-10866 DISCRETE FUNCTIONS p 45 A87-10732 ENVIRONMENT PROTECTION A description of a turbulent flow past a circular cylinder Electromagnetic methods to detect corrosion in aircraft Impact of IPS and IRS configurations on engine by a discrete vortex method p 11 N87-10014 Structures p 45 A87-10791 installation design p 26 N67-10070 DISPLAY DEVICES ELECTRON ENERGY ENVIRONMENTAL QUALITY Piloting of unmanned air vehicles. II Infrared emission lines from planetary nebulae Reaction to aircraft noise in residential areas around p 23 A87-10941 D 62 N67-10791 Australian airports p 54 A87-10116

A-8 SUBJECT INDEX FLIGHT CONTROL

Comparison of the effectiveness of measures of aircraft F A split-matrix method lor the integration of the noise exposure by using social survey data quasi-conservative Euler-equations p 7 A87-11544 p 54 A87-10117 F-IS AIRCRAFT Numerical solution of the 3-dimensionalboundary layer EPOXY RESINS Design and fabrication of the NASA decoupler pylon equations in the inverse mode using finite differences Polymer systems for rapid sealing of aircraft structures for the F-16 aircraft. addendum 2 p 11 N87-10005 at low temperature [ NASA-CR-1724941 p 27 N87-10859 Images of three dimensional flows in computer [ AD-A167667 ] p 41 N87-10209 F-18 AIRCRAFT graphics p57 N87-10017 Manufacture of bonded composite assemblies for EQUIPMENT SPECIFICATIONS Supersonic flow around tip sides of wings aircraft p 1 A87-13005 p 12 N87-10033 Engine-airframe integration for rotorcraft: Component F-5 AIRCRAFT specifications and qualification p26 N87-10071 Unsteady aerodynamic modeling of a fighter wing in Large perturbation flow field analysis and simulation for supersonic inlets ERROR ANALYSIS transonic flow p3 A87-10;l: Characterizing height keeping error distribution based FAILURE ANALYSIS [ NASA-CR-1746761 p 14 N87-10835 on indirect observation p 17 A87-12683 A system theocelcal based method for module failure FINITE ELEMENT METHOD Investigationof optimal complexityof BITE and its effects diagnostlc of turbine engines p 35 N87-10085 CSAINASTRAN ~ A general purpose program for on reliability. maintainability,monitoring and fault prediction FANS structural analysis p 56 A87-10879 --- Euilt-InTest (BITE) electronic systems A auasi-three-dimensronal method for diaaonal llow Recent developments in FEM-CFD p 5 A87-11411 [ ETN-86-979761 p 51 N87-11175 fans p 11 i87-12958 Numerical analysis with generalized J-integral ERROR DETECTION CODES FATIGUE (MATERIALS) p 47 A87-11492 A redundancy management procedure for fault detection Fatigue and fracture: Overview D 52 N87-11183 Implicit and semi-implicit methods for the compressible and isolation p 46 A87-11127 Relevance of short fatigue crack'growth data for Navier-Stokes equations p 47 A87-11503 ESTIMATING durability and damage tolerance analyses of aircraft Finite element computations for high speed 30 inviscid A decentralized fault-tolerant approach to estimation in [ FFA-TN-1986-231 p 54 N87-11231 flows p 7 A87-11542 FATIGUE LIFE multi-sensor navigation systems p 21 N87-10057 Constitutive modeling for isotropic materials Specification of gas turbine disc forgings ETHERS p 53 N87-11211 p 44 A87-10121 Properties and processing of fiber-reinforced FINITE VOLUME METHOD Stochastic crack propagation with applicatims to polyetheretherketone (PEEK) p 38 A87-11372 Euler solutions on 0-0grids around wings using local durability and damage tolerance analyses refinement p6 A87-11512 EULER EOUATIONS OF MOTION [AD-A168040] p 53 N87-11226 Efficient numerical method for transonic flow Euler equations analysis of the initial roll-up 01 aircraft FATIGUE TESTS sirnulalions p6 A87-11528 wakes p4 A87-10522 Fatigue fracture in steel landing gear components FIRE PREVENTION Euler solutions on 0-0grids around wings using local [NLR-MP-85050-U] p 54 N87-11233 An investigation of the FAA vertical Bunsen burner refinement p6 A87-11512 FAULT TOLERANCE flammability test method Application of a 2D time-marching Euler code to A decentralizedfault-tolerant approach lo estimation in [ DOT/FAA/CT-86/22] p 42 N87-10985 transonic turbomachinery flow p6 A87-11516 multi-sensor navigation systems p 21 N87-10057 FIRES Experiences with an unfactored implicit Fault tolerant control laws Case study of Royal Australian Air Force P3B Orion predictor-corrector method p 47 A87-11522 [NASA-CR-178094] p 50 N87-10400 aircraft ground oxygen fire incident p 16 A87-10866 Numerical experiments with a total variation diminishing FAULTTREES Fire occurring and expanding in connection with oils in (TVD) MacCormack scheme pb: A8i-iiSi6 TerhniczI diagnnsis by automated reasoning aviation p16 A87-11368 Efficient numerical method lor transonic flow p 57 A87-12217 Vulnerability methodology and protective measures lor simulations p 6 A87-11528 FEDERAL BUDGETS aircraft fire and explosion hazards. Volume 3 On-Board National Aeronautics and Space Administration A Simulation of rotor-stator interaction using the Euler Inert Gas Generator System (OBIGGS) studies. Pari 1: p 61 N87-10774 equations and patched grids p 7 A87-11536 OBIGGS ground performance tests FEEDBACKCONTROL [AD-A167357] p 26 N87-10066 Numericalexperiment with inviscid vortex-stretchedflow Guidance strategies for near-optimum take-off FLAMEHOLDERS around a cranked delta wing, supersonic speed performance in a windshear p 24 A87-12138 A test research for improving the performanceof V-type p7 A87-11537 Fault tolerant control laws flameholder used in an afterburner p 34 A87-12965 Numerical solution of the Euler equations using rational [ NASA-CR-1780941 p50 N87-10400 FLAME PROPAGATION Runge-Kulta method p7 A87-11538 FIBER COMPOSITES Flame radiation p43 N87-11204 A split-matrix method for the integration of the Composite materials for zircraft structures --- Book FLAMMABILITY quasi-conservativeEuler-equations p 7 A87-11544 p 38 A87-10294 Flammability and sensitivity of materials in Report of the International Symposiumon Computational Nickel coated graphite fiber conductive composites oxygen-enriched atmospheres; Proceedings of the Fluid Dynamics, Tokyo p 49 N87-10029 p 39 A87-11844 Symposium. Washington, DC. April 23. 24, 1985. Volume Euler llow solutions for a transonic wind tunnel section Advanced fibre composites and other new materials for 2 p 38 A87-10859 [CWCNM-R8601] p 16 N87-10847 airframe applications p 41 A87-13010 An investigation of the FAA vertical Bunsen burner Three-dimensional unsteady Euler equations solutions FIBER OPTICS flammability test method on dynamic grids Technology review of flight crucial flight control systems [ DOT/FAA/CT-86/22] p 42 N87-10985 [AD-A168041] p51 N87-11128 (application of optical technology) FLANGES [NASA-CR-1723321 p 36 N87-10102 EULERCAUCHY EQUATIONS A reinforcing band near the flange of a heated cylindrical FIBER REINFORCED COMPOSITES Computation of transonic separated wing flows using casing p 48 A87-12445 Quantitative thermal diffusivity measurements of an EulerINavier Stokes zonal approach FLAPS (CONTROL SURFACES) composites p 45 A87-10750 Effects of flap position on longitudinal parameters of p 16 N87-10843 Automatically woven three-airectional composite HFE-320 EXHAUST GASES structures p 48 A87-11843 [ NAL-TM-SE-88021 p 25 N87-10062 Laser anemometers of hot-section applications Fiber-reinforced superalloy composites provide an Toward comparing expenment and theory for p 52 N87-I1187 added performance edge p 39 A87-12647 corroborative research on hingeless rotor stability in EXHAUST SYSTEMS FIGHTER AIRCRAFT forward flight (an experimental and analytical investigation National Transportation Safety Board safety Single or dual pod concepts for tactical of isolated rotor-flap-lagstability in forward flight) recommendation p 18 N87-10852 reconnaissance p 29 A87-10939 [NASA-CR-179711] p25 N87-10063 EXPERIMENT DESIGN Maneuver optimization in tne case oi combai airuaii 6iress aiiaiyaia vi P&h:k&r-2 GC.%~ Numerical and experimental study of dynamics of p 35 A87-11369 [NASA-CR-1724581 p51 N87-11179 two-dimensional body Numerical simulation of viscous supersonic flow over FLAT PLATES [ ISAS-6191 p 59 N87-10748 a generic fighter configuration p6 A87-11509 Excitation of the natural oscillations of a boundary layer EXPERT SYSTEMS JAS39 Gripen - A Swedish Solution lo a multi-role by an external acoustic field p4 A87-10610 Knowledge-based tactical terrain analysis --- need p 23 A87-11798 FLEXIBLE BODIES autonomous helicopter systems p 19 A87-11061 Interference effects of thNSt reversing on horizontal tail Effect of tangential torque on the dynamics of flexible Expert systems for aiding combat pilots effectiveness of twin-engine lighter aircraft at Mach rotors p 29 A87-12212 numbers from 0.1 5 to 0.90 [ASME PAPER 86-WA/APM-23] p 46 A87-11113 Technical diagnosis by automated reasoning [ NASA-TP-23501 p 36 N87-10870 FLIGHT ALTITUDE p 57 A87-12217 FINANCIAL MANAGEMENT Characterizing height keeping error distribution based on indirect observation p 17 A87-12683 The ASPRO parallel inference engine (A real-timeexpert National Aeronautics and Space Administration system) P 29 A87-12218 p 61 N87-10774 FLIGHT CHARACTERISTICS Methods of in-flight aerophysical studies --- Russian EXTEDUkL CC"PE?!C!! ELIGINFS FINE STRUCTURE book p 23 A87-11343 Infraredemission lines from planetary neouiae Results of wind tunnel tests on external combustion Wind-tunnel investigation of the flight characteristics of p 62 N87-10791 [ESA-n-959] P 42 N87-10990 a canard general-aviationairplane configuration EXTERNAL STORE SEPARATION FINITE DIFFERENCE THEORY [NASA-TP-2623] p12 N87-10039 Further development of the influence function method Euler solutions on 0-0grids around wings using local FLIGHT CONDITIONS refinement p6 A87-11512 for store aerodynamic analysis p4 A87-10523 Disturbances brought by atmospheric statics to airborne EXTERNAL STORES Numerical experiments with a total variation diminishing navigation and communication systems Design and fabrication of the NASA decoupler pylon (TVD) MacCormack scheme p6 A87-11526 p 20 A87-12678 for the F-16 aircraft, addendum 1 lmolicit finite-difference Simulation of separated Monitoring of terminal flight phases environment [NASA-CR-l72355] p27 N87-10860 hypersonic flow over an indented nosetip Observations and models p 55 A87-12679 Three-dimensional unsteady Euler equations solutions D7 A87-11533 FLIGHT CONTROL on dynamic grids Numerical solution of the Euler equations using rational Maneuver optimization in the case of combat aircraft [AD-AI 68041 ] p 51 N87-11128 Runge-Kulla method p 7 A87-11538 p 35 A87-11369

A-9 SUBJECT INDEX

Spin-tunnel investigation of a 1125-xale model of the Dgital data recording on floppy disks applied for Mathematical modeling of separated flow past a wing General Dynamics F-16XL airplane on-board use in helicopters profile and aerodynamic hysteresis p 5 A87-10619 [ NASA-TM-856601 p 12 N87-10041 [ DFVLR-MITT-66-10] p51 N87-11149 FLOW DISTRIBUTION Performancemonitoring of sensors in high reliable flight FLIGHT SAFETY Body of revolution comparisons for axial- and control systems using deterministic ObSeNerS Optimal flight paths through microburst wind profiles surface-singularitydistributions p4 A87-10525 p32 N87-10087 p 35 A87-10519 A study on the axially CUNed mixed-flow vaneless Technology review of flight crucial flight COnlrOl Systems The classification of wind shears from the point of view diffusers p 47 A87-11481 (application of optical technology) of aerodynamics and flight mechanics A study of the flow field about an upper surface blown [ NASA-CR-1723321 p 36 N87-10102 p 24 A87-11898 wing and its effects on longitudinal static stability of a small Performance and quality flight test textbook. Volume 2: Theoretical aspacts and practical questions regarding jet airplane p 11 N87-10009 Flying qualities the assurance of flight safety p17 A87-11900 Computational aerodynamics of supersonic lifting [ AD-A1681241 p3 N87-10830 Characterizing height keeping error distribution based vehicles p 12 N87-10030 Energy management of 3-dimensional minimum-lime on indirect ObSeNatiOn p17 A87-12683 Supersonic flow around lip sides of wings intercept p 27 N87-10858 The US. Federal Radionavigation Plan p 12 N87-10033 FLIGHT HAZARDS p21 A87-12684 Unsteady flow over an airfoil inside a wind tunnel with Keep your eye on the birdie - Aircraft engine bird Automaled functions for air traffic control systems and without transpiration p 13 N87-10051 ingestion p 61 A87-10509 p21 A87-12687 An experimental investigation of end-wall flowfield of a Monitoring of terminal flight phases environment Ice accretion dependence on cloud physical compressor rotor p50 N87-10244 ObSeNaliOnS and models p 55 A87-12679 parameters p 55 N87-11433 Large perturbation flow field analysis and simulation for FLIGHT MANAGEMENT SYSTEMS Ice accretion calculations on cylindrical rods following supersonic inlets Dynamic flight optimization p 24 A87-11899 the Bain model, and comparison with experimental results [ NASA-CR-1746761 p 14 N87-10835 Grwnd-based timeguidance algorithm for control of (Fuchs. Schickel. Kaluza. Uwira, 1985) Results of wind tunnel tests on external combustion airplanes in a time-metered air traffic control environment p 56 N87-11434 [ESA-TT-959] p 42 N87-10990 A piloted simulation study The influence of weather-active fronts on visual flight Combustion ovewiew p43 N87-11181 [NASA-TP-26161 p 34 N87-10864 conditions p56 N87-11437 Host turbine heal transfer overview FLIGHT MECHANICS Statistics of wind shear due lo nocturnal boundary layer p 52 N87-11184 Scientific problems of aviation and space: History and . jet airstreams in North Germany p 56 N87-11461 Aerothermal modeling program, phase 2 pfesent state --- Russian book p 62 A87-11339 FLIGHT SIMULATION p 35 N87-11200 The classification of wind shears from the point of view Correlation between flight simulation and processing of Measurement of airfoil heal transfer coefficients on a of aerodynamics and flight mechanics flight tests based on inertial measurements turbine stage p 53 N87-11221 p 24 A87-11898 [ NLR-MP-85058-Ul p 28 N87-10863 FLOW EQUATIONS Guidance strategies for near-optimum lake-off Ground-based timeguidance algorithm for control of Euler flow solulions for a transonic wind tunnel section performance in a windshear p 24 A87-12138 airplanes in a time-metered air traffic control environment: [CWI-NM-R8601] p 16 N87-10847 Application of bifurcation and catastrophe theories to A piloted simulation study FLOW GEOMETRY near stall flight mechanics [NASA-TP-2616] p 34 N87-10864 A study on the axially CuNed mixed-flow vaneless [ AD-A1676971 p 13 N87-10046 LOWCOS~avionics simulation for aircrew training diffusers p 47 A87-11481 FLIGHT OPTIMIZATION [ AD-A1691 981 p 34 N87-10865 Euler solutions on 0-0 gnds around wings using local Optimal flight paths through microburst wind profiles FLIGHT SIMULATORS refinement p6 A87-11512 p 35 A87-10519 Aeronautical facilities assessment Efficient numerical method for transonic flow Dynamic flight optimization p 24 A87-11899 [NASA-RP-11461 p 37 N87-10876 simulations p 6 A87-11528 Wind tunnel test of the modified goldschmied model Real lime debugging software package for flight Transformation of a plane uniform shock into cylindrical with propulsion and empennage: Analysis of test results simulator software system with variable labeled COMMON or spherical uniform shock by wall shaping [ AD-A1673601 p 13 N87-10045 blocks p 37 A87-12585 Energy management of 3-dimensional minimum-lime [ NLR-MP-85013-U] p 57 N87-11530 FLOW MEASUREMENT intercept p 27 N87-10858 FLIGHT STABILITY TESTS A nonperturbing boundary-layertransition detection FLIGHT PATHS Performance and qualily flight test textbook. Volume 2: p 46 A87-10971 Optimal flight paths through microburst wind profiles Flying qualities The balance between theoretical. computational and p 35 A87-10519 [AD-A168124] p3 N87-10830 experimental work in turbomachines p 49 A87-13015 Energy management of 3-dimensional minimum-time FLIGHT TEST INSTRUMENTS Airborne measurement methods applied lo the intercept p 27 N87-10858 Correlation between flight simulation and processing of determination of boundary conditions a1 the sea surface: FLIGHT PLANS flight tests based on inertial measurements The TOSCANE experiment p 55 N87-11242 Operational usage of the KS-147A [LOROP) in the [ NLR-MP-85058-Ul p 28 N87-10863 FLOW RESISTANCE RF-BE p 29 A87-10936 FLIGHT TESTS Expansion of flow due lo resistance of a wire gauze FLIGHT RECORDERS Long range E-0 Reconnaissance System and flight test placed in a parallel-sided channel p 48 A87-12133 Crashworthiness experiment summary full-scale results p 28 A87-10933 FLOW STABILITY transport controlled impact demonstration program Ground and flight tests of Tornado reconnaissance Unsteady aerodynamic modeling of a fighter wing in [ DOT/FAA/CT-85/20] p 17 N87-10055 pod p 22 A87-10940 transonic flow p3 A87-10517 Proceedings of the 13th Symposium on Aircraft Flight experiments on MLS elevation guidance Vortex-stretched flow around a cranked delta wing Integrated Data Systems p 21 A87-I2686 p3 A87-10520 [ DFVLR-MITT-86-04] p 30 N87-10075 Design and fabncalion of the NASA decoupler pylon On the large-scale structures in two-dimensional. Integrated monitoring systems for tactical aircraft for the F-16 aircraft small-deficit. turbulent wakes p8 A87-12052 p 31 N87-10080 [ NASA-CR-1723541 p 25 N87-10065 FLOW VELOCITY Application of operational flight recording lo Applicabon of operational flight recording lo Laser anemometers of hot-section applications helicopters p 31 N87-10081 helicopters p 31 N87-10081 p 52 N87-11187 The Airborne Integrated Data System (AIDS) for the Wind shear measurement on board a MORANE 893 FLOW VISUALIZATION Airbus A-310 engine condition monitoring p 31 N87-10086 High speed flow visualisation p 48 A87-12648 p 31 N87-10082 Comparative evaluation of redundant flight data Development of a turbomachinery design optimization The impact of flight data on an airline: A case study recorded by a digital aircraft integrated data system procedure using a multiple-parameter nonlinear p 32 N87-10088 recorder (OAR) on board an Airbus A-310 aircraft perturbation method Data recovery techniques, an update --_ flight data p 33 N87-10098 [ NASA-CR-38311 p2 N87-10003 p 32 N87-10089 Response of a small-tubshaft-engine compression Analysis of the vortical flow around a 60 deg Della wing Software for flight recorder data processing developed system lo inlet temperature distortion with vortex flap p 11 N87-10006 by Lufthansa p32 N87-10090 [ NASA-TM-837651 p 35 N87-10100 Study of three-dimensionalseparation on a spheroid at Airline data acquisition in an ACARS environment In-flight total forces. moments and static aeroelastic incidence p 49 N87-10016 p32 N87-10092 characteristics of an oblique-wing research airplane FLUID DYNAMICS Flight recorders: New US regulations and new [ NASA-TP-22241 p 36 N87-10103 A comparison of interactive boundary-layer and International Civil Aviation Organization (ICAO) Flight service evaluation of composite helicopter thin-layer Navier-Stokes procedures p 8 A87-11785 standards p32 N87-10093 components Numerical and experimental study of dynamics of Data compression techniques lor multifunction flight [ NASA-CR-1781491 p 41 N87-10182 two-dimensional body data recorders p33 N87-10094 Performance and quality flight test textbook. Volume 2: [ ISAS-6191 p 59 N87-10748 The Fairchild CVDR: A new comblnation voice and data Flying qualities Three-dimensional unsteady Euler equations SOlUliOnS recorder --- Cockpit Voice and Data Recorder (CVDR) [ AD-A1681241 p3 N87-10830 on dynamic grids p33 N87-10095 Correlation between flight simulation and processing of [AD-A168041I p 51 N87-11128 The Boeing B 720 aircraft Controlled Impact flight tests based on inertial measurements FLUID FLOW Demonstration [CID): Flight data recorder/cockpit voice [NLR-MP-85058-U] p 28 N87-10863 Mechanics of flow-induced sound and vibration. Volume recorder experiment p 33 N87-10096 FLlR DETECTORS 1 General conceots and elementary source. Volume 2 - United States Navy - Canadian Forces solid state flight Data compression for IR reconnaissance Complex flow-stkclure interactions --- Book data recorder/crash position lxator experiment on the p 18 A87-10947 D 57 A87-10293 8-720 controlled impact demonstration FLOW DEFLECTION~~. FLUID MECHANICS p33 N87-10097 Method of meridional sections in problems involving a Conference on Numerical Methods in Fluid Mechanics, Comparative evaluation of redundant flight data three-dimensional boundary layer p 4 A87-10609 6th. Goellingen. West Germany, September 25-27, 1985. recorded by a digital aircraft integrated data system Numerical investigation of supersonic flow past Proceedings p 47 A87-11501 recorder (OAR) on board an Airbus A-310 aircraft spike-lipped blunt bodies p4 A87-10614 FLUlTER p33 N87-10098 Calculation of unsteady supersonic flow past a plane Design and fabrication of the NASA decoupler pylon Investigations on a diiital bit synchronizer for a detailed blade row under the effect of vortex inhomogeneities in for the F-16 aircraft flight data recovery p 33 N87-10099 the oncoming flow p5 A87-10618 [NASA-CR-1723541 p 25 N87-10065

A-10 SUBJECT INDEX HELICOPTERS

FLUrrER ANALYSIS High temperature static strain gage program GROUNDSUPPORTSYSTEMS Design and fabrication of the NASA decoupler pylon p 52 N87-11188 Integrated logistics for reconnaissance systems for the F-16 aircraft, addendum 2 Evaluation resuits of the 700 deg C Chinese strain p 61 A87-10942 [ NASA-CR-1724941 p27 N87-10859 gages p 52 N87-11189 GROUND TESTS Design and fabrication of the NASA decwplef pylon Coating life prediction p 43 N87-11194 Ground and flight tests of Tornado reconnaissance for the F-16 aircraft. addendum 1 Aerothermal modeling program. phase 2 pod p 22 A87-10940 [ NASA-CR-1723551 p27 N87-10860 p35 N87-11200 In-service environmental effects on carbon fibre FORGING NASA dilution jet mixing. phase 3 p 53 N87-11202 composite material p39 A87-12659 Elevated temperature crack growth Specifition of gas turbine disc forgings GUIDANCE SENSORS p 53 N87-11214 p 44 A87-10121 A decentralized fault-tolerant approach to estimation in Biaxial Constitutive equation development Forging of blades for gas turbines p 44 A87-10124 multi-sensor navigation systems p 21 N87-10057 p 53 N87-11217 FORMING TECHNIQUES GUST LOADS Cost effective single crystals -- gas turUine Net shape forming: The route to low cost components. Acta Aeronautica et Astronautica Sinica (selected components The view point of the aerospace industry articles) [PNR-90306] p51 N87-11020 [PNR-90319] p60 N87-11615 Development of single crystal alloys for specific engine [ADA16791 81 p3 N87-10004 FRACTOGRAPHY Prediction of gust loadings and alleviation at transonic applications Fractographic aspects of the cyclic fracture toughness speeds of 35KhN3MFA steel in vacuum, air, and hydrogen [ PNR-903201 p60 N87-11616 GAS TURBINES [AD-A167748) p 13 N87-10047 p 40 A87-12882 GUSTS High temperature heat transfer for gas turbines using FRACTURE MECHANICS Theoretical treatment of gust Simulation in the wind shock tubes p37 A87-12646 Fatigue and fracture: Overview p 52 N87-11183 tunnel p9 A87-12148 Stochastic crack propagation with applications to Measurement of airfoil heat transfer coefficients on a durability and damage tolerance analyses turbine stage p 53 N87-11221 [AD-A168040] p 53 N87-11226 GAS VISCOSITY H FRACTURESTRENGTH Density field of a viscous gas jet issuing from a conical Fractographic aspects of the cyclic fracture toughness noale into vacuum p4 A87-10603 HEAT FLUX of 35KhN3MFA steel in vacuum, air, and hydrogen GASEOUS FUELS High temperature heat transfer for gas turbines using p 40 A87-12882 Vulnerability methodology and pfotectie measures for shock tubes p37 A87-12646 FREE FLOW aircraft fire and explosion hazards. Volume 3: On-Board Development of heat flux sensors in turbine airfoils Numerical simulation of viscous supersonic flow over Inert Gas Generator System (OBIGGS) studies. Part 1: p 52 N87-11186 a generic fighter configuration p6 A87-11509 OBIGGS ground performance tests Flame radiation p 43 N87-11204 The effect of free stream disturbances and control [ AD-A1673571 p 26 N87-10066 HEATMEASUREMENT surface deflections on the performance of the Wwtmann An investigation of the FAA vertical Bunsen burner High temperature heat transfer for gas 1uMnes using airfoil at low Reynolds numbers p 11 N87-10007 flammability test method shock tubes p 37 A87-12646 FREE JETS [DOT/FAA/CT-86/22] p 42 N87-10985 Development of heat flux sensors in turbine airfoils Free jet feasibility study of a thermal accustic shield GASOLINE p52 N87-11186 concept for ASTlVCE application: Dual stream noales Avgaslautogas comparison: Winter fuels Measurement of airfoil heat transfer coefficients on a [DOT/FAA-CT-86/21] p 43 N87-11014 [ NASA-CR-38671 0 59 N87-10752 turbine stage p 53 N87-11221 HEAT iiEsisTANT AiiOi.S FRONTS (METEOROLOGY) GAUZE The influence of weather-active fronts on visual flight Expansion of flow diie :o resiskiice of a wi:e gauze Fiber-reinforced superalloy composites provide an conditions p 56 N87-11437 placed in a parallel-sided channel p 48 A87-12133 added performance edge p 39 A87-12647 FUEL CONSUMPTION GEARS Constitutive modeling for isotropic materials Influence of engine variables on future helicopter Advances in the vibration monitoring of gears and rolling p53 N87-11211 systems p 27 N87-10072 element bearings p 49 A87-13007 Biaxial constitutive equation development Ground-based time-guidance algorithm for control of Analysis of the vibration of the input bevel pinion in RAN p 53 N87-11217 airplanes in a time-metered air traffic control environment: Wessex helicopter main rotor gearbox WAK143 prior to Development of single crystal alloys for specific engine A piloted simulation study failure applications [NASA-TP-2616] p 34 N87-10864 [ARL-AERO-PROP-R-l69] p25 N87-10061 [PNR-90320] p60 N87-11616 FUEL CONTAMINATION Engine-Aitirame Integration for Rotorcraft HEAT SHIELDING National Transportation Safety Board safety [AGARD-LS-148] p 26 N87-10067 Free jet feasibility study of a thermal acoustic shield recommendation p 18 N87-10852 GENERAL AVIATION AIRCRAFT concept for AST/VCE application: Dual stream noales FUEL TANKS Wind-tunnel investigationof the flight characteristics of [ NASA-CR-38671 p 59 N87-10752 Vulnerability methodology and protective measures for a canard general-aviation airplane configuration HEAT TRANSFER aircraft fire and explosion hazards. Volume 3: On-Board [ NASA-TP-2623) p 12 N87-10039 Host turbine heat transfer overview Inert Gas Generator System (OBIGGS) studies. Part 1: GEOMAGNETISM p 52 N87-11184 OBIGGS ground performance tests Fundamentals of navigation according to geophysical Component specific modeling p 35 N87-11207 [AD-A1673571 p26 N87-1- fields --- Russian book p 19 A87-11337 HEAT TRANSFER COEFFICIENTS FUEL TESTS GEOMETRY Method of meridional sections in problems involving a A method for calculating the susceptibility of jet fuels NASA dilution jet mixing. phase 3 p 53 N87-11202 three-dimensionalboundary layer p 4 A87-10609 to smoking p 40 A87-12901 GLIDE PATHS Measurement of airfoil heat transfer coefficients on a Minimum operational performance standards for turbine stage p 53 N87-11221 airborne !LS glide slope receiving equipment operating Coolant passage heat transfer with rotation, a progress G within the radio frequency range of 328.6-335.4 MHz report p 53 N87-11225 [ RTCA/DO-l92 1 p 21 N87-10853 HELICOPTER DESIGN GAS DYNAMICS GLOBAL POSITIONING SYSTEM Impact of IPS and IRS configurations on engine Motion of a gas in a duct behind a moving body Global positioning system applications installation design p26 N87-10070 p5 A87-10675 p18 A87-10047 Influence of engine variables on future helicopter GAS EXPLOSIONS Combined utilization of Loran and GPS - The best from systems p 27 N87-10072 \I. .I--_^ Lilil. -".l,-A-, ^"a ".,.*",,.L... _^^^. ..^ ."""'a""'., "'V.""""'VY, Ull" V."."".'." I,,""*"."S !Cx each gyrlem p 20 A87-11664 Ualirnntar air intake nrntactinn ay%tarna aircraft fire and explosion hazards. Volume 3: On-Board Integration of GPS with other radionavigation systems p 27 N87-10073 Inert Gas Generator System (OBIGGS] studies. Part 1: p21 A87-12680 HELICOPTER PERFORMANCE OBIGGS ground performance tests A low cost commercial GPS set p 21 A87-12685 Transonic flow analysis for rotors. Part 2 [ AD-A1673571 p26 N87-10066 GOVERNMENTS Three-dimensional, unsteady, full-potential calculation GAS FLOW Aeronautics and space report of the President [ NASA-TP-23751 p 15 N87-10841 Conical wing of maximum lift-to-dragratio in a supersonic [ NASA-TM-892391 p 62 N87-10827 HELICOPTERS gas flow p4 A87-10615 GRANTS Knowledge-based tactical terrain analysis --- GAS JETS Graduate engineering research participation in autonomous helicopter systems p 19 A87-11061 Density field of a viscous gas jet issuing from a conical aeronautics Helicopter impulsive noise . Theoretical and noale into vacuum p 4 A87-10603 [ NASA-CR-1797981 p3 N87-10828 experimental status p 58 A87-11771 GAS TURBINE ENGINES GRAPHITE Helicopter MLS Flight Inspection Project Specification of gas turbine disc forgings Nickel coated graphite fiber conductive composites [ DOT/FAA/CT-86/141 p2 N87-10002 p 44 A87-10121 p 39 A87-11844 Analysis of the vibration of the input bevel pinion in RAN Forging of blades for gas turbines p 44 A87-10124 GRAPHITE-EPOXY COMPOSITES Wessex helicopter main rotor gearbox WAK143 prior to Manufacturingtechnology for nondestructiveevaluation uecay 01 ena eiiecrs in graphiieiepoxy boiiwu juiriis failure (NDE) system to implement retirement for cause (RFC) p 44 A87-10115 [ARL-AERO-PROP-R-l69] p25 N87-10061 procedures for gas turbine engine components Advances in toughness of Structural composites based Engine-Airframe Integration for Rotorcraft p 44 A87-10727 on interleaf technology p40 A87-12661 [ AGARD-LS-1481 p26 N87-10067 RFC automated inspection overview --- eddy current and GRAVITATIONAL FIELDS Engine-airframe integration considerations for ultrasonic testing of gas turbine engine parts Fundamentals of navigation according to geophysical preliminary air vehicle performance analysis p 45 A87-10730 fields --- Russian book p 19 A87-11337 p 26 N87-10068 New materials in gas turbine technology GROUND EFFECT (AERODYNAMICS) Engine-transmission-stNctural airframe members p41 A87-13009 An experimental investigation of dynamic ground compatibility p26 N87-10069 A system theoretical based method for module failure effect p 14 N87-10833 Engine-airframe integration for rotorcraft: System diagnostic of turbine engines p 35 N87-10085 Advanced method for computing the flow around wings specifications and qualification p 27 N87-10074 Hot section viewing system with rear separation and ground effect Application of operational flight recording to [NASA-CR-174773] p 51 N87-11144 [ DFVLR-FB-86-17) p50 N87-11017 helicopters p31 N87-10081

A-1 1 HFB-320 AIRCRAFT SUBJECT INDEX

Flight service evaluation of composite helicopter IGNITION INLET NOZZLES components Flammability and sensitivity of materials in PTA test bed aircraft engine inlet model test report, [ NASA-CR-1781491 p 41 N87-10182 oxygen-enriched atmospheres; Proceedings of the revised Testing of UH-GOA helicopter transmission in NASA Symposium. Washington, E€. April 23, 24, 1985. Volume [NASA-CR-I748451 p35 N87-10866 Lewis 2240-kW (3000-hp) faciltly 2 p 38 A87-10859 INLET PRESSURE [ NASA-TP-26261 p 50 N87-10391 IMAGE PROCESSING Flame radiation p 43 N87-11204 Parametric analysis of a passrve cyclic control device Photogrammetric tools for panoramic sector scan INLET TEMPERATURE for helicopters imagery in the VIDARS analysis station Response of a small-turboshaft-engine compression [ NASA-CR-1666081 p 28 N87-10862 p 19 A87-10948 system to inlet temperature distortion Digital data recording on lloppy disks applied for Management of airborne reconnaissance images [ NASA-TM-837651 p 35 N87-10100 on-board use in helicopters through real-time processing p 19 A87-10949 INSPECTION [ DFVLR-MITT-86-IO] p 51 N87-11149 Knowledge-based tactical terrain analysis --- A computer-aided nondestructive inspection system Signal processing and interpretation using multilevel autonomous helicopter systems p 19 A87-11061 p 44 A87-10720 Computerized ultrasonic test inspection enhancement signal abstractions IMAGING TECHNIQUES system for aircraft components p 44 A87-10721 [ AD-A1691 661 p 57 N87-11513 Rapid target locator p 18 A87-10944 INSTRUMENT APPROACH HFB-320 AIRCRAFT Images of three dimensional flows in computer Aircraft accident reeport. Delta Air Lines, Inc.. Lockheed Effects of flap position on longitudinal parameters of graphics p 57 N87-10017 L-1011-385-1, N726DA. Dallas/Fort Worth International HFB-320 IMPACT DAMAGE Airport, Texas, August 2. 1985 [ NAL-TM-SE-86021 p25 N87-10062 Certification problems for composite airplane [PB86-910406] p 17 N87-10053 HIGH REYNOLDS NUMBER Structures p 39 A87-12652 INSTRUMENT LANDING SYSTEMS Optimal control of viscous flow at high Reynolds Crashworthiness experiment summary full-scale Laser remote sensing procedures provide an aid to numbers p5 A87-10620 transport controlled impact demonstration program aviation during the approach for landing Vortex shedding of a square cylinder in front of a slender [ DOT/FAA/CT-85/201 p 17 N87-10055 p 19 A87-11370 airfoil at high Reynolds numbers. Part 1: Spacing effect IMPACT RESISTANCE Interference of the aeronautical navaids (frequency band [MPIS-23/1985] p 13 N87-10048 Impact resistant hybrid Composite for aircraft leading 108-118 MHz) from F.M broadcasting service (88-108 HIGH STRENGTH STEELS ’ edges p 24 A87-11848 MHz) p 21 A87-12690 Fatigue fracture in steel landing gear components IMPACT TESTS Minimum operational performance standards for [ NLR-MP-85050-U1 p 54 N87-11233 Nondestructive inspection of composite structures by airborne ILS glide slope receiving equipment operating HIGH TEMPERATURE low-velocity impact p 45 A87-10765 within the radio frequency range of 328.6-335.4 MHz High temperature static strain gage program IMPELLERS [RTCA/DO-192] p 21 N87-10853 p 52 N87-11188 A quasi-three-dimensional method for diagonal flow INTAKE SYSTEMS HIGH TEMPERATURE GASES fans p 11 A87-12958 Impact of IPS and IRS configurations on engine A reinforcingband near the flange of a heated cylindrical IN-FLIGHT MONITORING installation design p 26 N87-10070 Helicopter air intake protection systems casing p 48 A87-12445 Methods of in-flight aerophysical studies --- Russian HISTORIES book p 23 A87-11343 p 27 N87-10073 Dirigibles - For what? p 23 A87-11661 INTEGRATED CIRCUITS INCIDENCE Avionics in the sub-microscopic world HOLE GEOMETRY [MECHANICS) Study of three-dimensional separation on a spheroid at p 48 A87-11800 Modeling and analysis of the dynamics of a drill incidence p 49 N87-10016 INTERACTIONAL AERODYNAMICS penetrating a thin plate INCOMPRESSIBLE FLOW Quantitative study of shock-generated compressible [ASME PAPER 86-WAIAPM-331 p 46 A87-11112 Body of revolution comparisons for axial- and vortex flows p 10 A87-12616 HOLOGRAPHIC INTERFEROMETRY surface-singularity distributions p4 A87-10525 INTERNATIONAL COOPERATION Quantitative study of shock-generated compressible Theoretical treatment of gust Simulation in the wind Transition to new systems and internatlonal vortex flows p 10 A87-12616 tunnel p9 A87-12148 perspectives p 20 A87-11806 High speed flow visualisation p 48 A87-12648 Analysis of two-dimensional incompressible flow past The future of internationalair transport HOT CORROSION airfoils using unsteady Navier-Stokes equations p2 A87-13016 Surface protection p 43 N87-11182 INASA-CR-1798231 p 12 N87-10040 INTERNATIONAL LAW Effects of surface chemistry on hot corrosion life Experimental study of the boundary layer on a low The role of choice of law in determining damages for p43 N87-11193 Reynolds number airfoil in steady and unsteady flow internationalaviation accidents p 61 A87-10508 Coating life prediction p43 N87-11194 p 14 N87-10052 INVISCID FLOW HOTSURFACES Application of a potential code to general steady flows Vortex-stretched flow around a cranked delta wing Hot section viewing system in three dimensions p 50 N87-10262 p3 A87-10520 [NASA-CR-1747731 p 51 N87-11144 INDUSTRIES Vortex simulation of propagating stall in a linear cascade of airfoils p5 A87-11117 HUMAN REACTIONS Aeronautics and space report of the President Numerical experiments with a total variation diminishing Reaction to aircraft noise in residential areas around [ NASA-TM-892391 p 62 N87-10827 INERTIAL NAVIGATION (TVD) MacCormack scheme p A87-I1526 Australian airports p 54 A87-10116 6 The mechanics of dynamically tunable gyroscopes --- Numerical expenment with inviscidvortex-stretched flow Comparison of the effectiveness of measures of aircraft Russian book p 57 A87-10444 around a cranked delta wing, supersonic speed noise exposure by using social survey data A decentralized fault-tolerant approach to estimation in p 7 A87-11537 p 54 A87-10117 multi-sensor navigation systems p 21 N87-10057 Calculation of strong viscous/inviscid interactions on HYDROCARBON FUELS Operating and support hazard analysis for self-contained airfoils by zonal solutions of the Navier-Stokes equations A method for calculating the susceptibility of jet fuels navigation system LSI model 6216A. B and C. group B p 7 A87-11540 to smoking p 40 A87-12901 [AD-A16938l] p 22 N87-10855 Finite element computations for high speed 30 inviscid HYDRODYNAMICS INERTIAL PLATFORMS flows p 7 A87-11542 Wind tunnel test of the modified goldschmied model Correlation between flight simulation and processing of Viscous wing theory development. Volume 1: Analysis, with propulsion and empennage: Analysis 01 test results flight tests based on inertial measurements method and results [ AD-AI 673603 p 13 N87-10045 [NLR-MP-85058-U] p 28 N87-10863 [ NASA-CR-178156] p 12 N87-10043 HYPERSONIC FLOW INFERENCE Application of a potential code to general steady flows Implicit finite-difference simulation of separated The ASPRO parallel inferenceengine (A real-timeexpert in three dimensions p 50 N87-10262 hypersonic flow over an indented nosetip system) p 29 A87-12218 Large perturbation flow field analysis and simulation for p7 A87-11533 INFLATABLE STRUCTURES supersonic inlets HYPERSONIC SPEED Dingibles - For what? p 23 A87-11661 [NASA-CR-I746761 p 14 N87-10835 Supersonic second order analysis and optimization INFLUENCE COEFFICIENT IRON ALLOYS program user’s manual Further development of the influence function method Testing of Fe-Cu-base ablative composites. II [NASA-CR-172342] p 15 N87-10842 for store aerodynamic analysis p4 A87-10523 p 41 A87-12971 INFORMATION MANAGEMENT HYPERSONIC WIND TUNNELS ISOPARAMETRIC FINITE ELEMENTS A redundancy managementprocedure lor fault detection A nonperturbing boundary-layertransition detection Natural frequency analysis of pretwisted plates and isolation p 46 A87-11127 p 46 A87-10971 p 46 A87-10900 The methodology and tools for processing radar data p 19 A87-11662 I FANS - A U.S. perspective p 20 A87-11807 INFRAREDSPECTRA J Infrared emission lines from planetary nebulae ICE FORMATION J INTEGRAL Summary of artificial and natural icing tests conducted p 62 N87-10791 INGESTION [ENGINES) Numerical analysis with generalized J-integral on US Army aircraft from 1974 to 1985 p 47 A87-11492 [ FAA/CT-85/26] p 25 N87-10064 Impact of IPS and IRS configurations on engine installation design p 26 N87-10070 JET AIRCRAFT Ice accretion calculations on cylindrical rods following INJURIES A study 01 the flow field about an upper surface blown the Bain model, and Comparison with experimental results The role of choice of law in determining damages for wing and its effects on longitudinal static stability of a small (Fuchs, Schickel, Kaluza. Uwira. 1985) international aviation accidents p 61 A87-10508 let airplane p 11 N87-10009 p 56 N87-11434 INLET FLOW JET AIRCRAFT NOISE ICE PREVENTION Calculation of boundary layer of a three dimensional On broadband shock associated noise of supersonic Summary of artificial and natural icing tests conducted S-shaped inlet p6 A87-11495 lets p 58 A87-11768 on US Army aircraft lrom 1974 to 1985 A split-matrix method for the integration of the Nonlinear acoustic propagation 01 broadband noise [ FAA/CT-85/26] p 25 N87-10064 quasi-consewative Euler-equations p 7 A87-11544 D 58 A87-11773

A-12 SUBJECT INDEX MECHANICAL DRIVES

Free jet feasibility study of a thermal acoustic shield Stress analysis of Pathfinder-2 models LOW SPEED WIND TUNNELS concept for ASTNCE application: Dual stream nozzles [ NASA-CR-1724581 p 51 N87-11179 An experimental investigation of dynamic ground [NASA-CR-38671 p 59 N87-10752 LEADING EDGE THRUST effect p 14 N87-10833 Free-jet acoustic investigation of high-radius-ratio Wind tunnel test of the modified goldschmied model Practical evaluation of wall pressure signaturecorrection coannular plug nozzles with propulsion and empennage: Analysis of test results methods in the 2 7m x 2 1m low speed wnd tunnel [ NASA-CR-38181 p 59 N87-10753 [ AD-A1673601 p 13 N87-10045 [BAE-ARG-Z04] p 37 N87-10874 JET ENGINE FUELS Numerical methods and a computer program for Prop-fan slipstream effects using static simulators Low A method for calculating the susceptibility of jet fuels subsonic and supersonic aerodynamic design and analysis speed task, phase 1 to smoking p40 A87-12901 of wings with attainable thrust considerations [ BAE-B59RIR-D1610113498] p 37 N87-10875 Flame radiation p43 N67-11204 [NASA-CR-3808] p3 N87-10829 LUBRICATING OILS LEADING EDGES Thickened oils p40 A87-12902 JET ENGINES Impact resistant hybrid composite for aircraft leading A test research for improving the performance of V-type edges p 24 A87-1'1848 flameholder used in an afterburner p 34 A87-12965 LEGAL LIABILITY Component specific modeling p 35 N87-11207 The role of choice of law in determining damages for M JET FLAPS international aviation accidents p 61 A87-10508 A study of the flow field about an upper surface blown Keep your eye on the birdie - Aircraft engine bird MAGNETIC DISKS Qgital data recording on floppy disks applied for wing and its effects on longitudinal static stability of a small ingestion p 61 A87-10509 jet airplane p 11 N87-10009 The crash of Delta Flight 191 - Are the nightmares on-board use in helicopters JET MIXING FLOW compensable? p 61 A87-10510 [DFVLR-MIlT-86-10I p 51 N87-11149 NASA dilubn jet mixing, phase 3 p 53 N87-11202 LIFE (DURABILITY) MAGNETIC RECORDING JET PROPULSION Turbine Engine Hot Section Technology, 1984 Data compression for IR reconnaissance Wind tunnel test of the modified goldschmied model [NASA-CP-23391 p 52 N87-11180 p 18 A87-10947 with propulsion and empennage: Analysis of test results Cornbustion overview p 43 N87-11181 MAINTAINABILITY [ AD-A1 673601 p 13 N87-10045 Surface protection p 43 N87-11182 Inveshgationof optimal complexityofBlTEand itseffects JET STREAMS (METEOROLOGY) Fatigue and fracture: Overview p 52 N87-11183 on reliability. maintainability.monitonng and fault prediction Built-In Test (BITE) electronic systems Statistics of wind shear due to nocturnal boundary layer Effects of surface chemistry on hot corrosion life --- jet airstreams in North Germany p 56 N67-11461 p 43 N87-11193 [ ETN-86-979761 p 51 N87-11175 JOINTS (JUNCTIONS) Coating life prediction p 43 N87-11194 MAINTENANCE Decay of end effects in graphitelepoxybolted joints Introduction to life modeling of thermal barrier Cleaning methods and procedures for military oxygen p44 A87-10115 coatings p 43 N87-11195 equipment - Investigation results p 46 A87-10867 Thermal bamer coating life prediction model Critical joints in large composite aircraft structure MANAGEMENT PLANNING development p 52 N87-11199 [ NASA-CR-37101 p 41 N87-10973 Engine-airframe integration for rotorcraft System Coolant .-Dassaae heat transfer with rotation, a Drwress specifications and qualification p27 N87-10074 Critical composite joint subcomponents: Analysis and report p53 Ni7-ii225 MANUAL CONTROL test results LIFE CYCLE COSTS Reconnaissance interface - The near real time is now [NASA-CR-37111 p 42 N87-10975 Integrated logistics for reconnaissance systems p 29 A87-10950 p 61 A87-10942 MANUFACTURING K LIFT The influence of aerospace developments upon A study of the flow field about an upper surface blown developments in manutacturing p i AB7-iS002 KETONES wing and its effects on longitudinal static stability of a smail Future aeveiopmenls and mandfzctunng a! GAF Properties and processing of fiber-reinforced jet airplane p 11 N87-10009 p 2 A87-13013 pelyetheretherketone(PEEK) p 38 A87-11372 Computational aerodynamics of supersonic lifting Future developments and manufactunng at C A C vehicles p 12 N87-10030 p2 A87-13014 LIFT DEVICES MASS DISTRIBUTION L A study of the flow field about an upper surface blown A hiqher order beam element for vibration of beams wing and its effects on longitudinal static stability of a small with diicontinuities p 46 A87-10898 LAMINAR BOUNDARY LAYER jet airplane pll N87-10009 MASS FLOW RATE Excitation of the natural oscillations of a boundary layer LIFT DRAG RATIO Results of wind tunnel tests on external combustion by an external acoustic field p4 A87-10610 Conical wing of maximum lift-to-dragratio in a supersonic [ESA-TT-959] p42 N87-10990 Experimental investigations of three-dimensional gas flow p4 A87-10615 MATERIALS laminar boundary layers on a slender delta wing LIFTING ROTORS New materials in gas turbine technology p9 A87-12145 Parametric analysis of a passive cyclic control device p 41 A67-13009 A laminar boundary layer methd for flows in planes for helicopters Structural design with new materials of symmetry and application to inclined ellipsoids of [ NASA-CR-1666081 p 26 N87-10862 p 49 A87-13011 revolution p9 A87-12146 LIGHT AIRCRAFT MATERIALS SCIENCE Experimental study of the boundary layer on a low Progress in advanced materials and pracesses: Piloted simulation study of the effects of an automated Reynolds number airfoil in steady and unsteady flow Durability, reliability and quality control; Proceedings of the trim system on flight characteristics of a light twin-engine Sixth International European SAMPE Conference, p 14 N87-10052 airplane with one engine inoperative LAMINAR FLOW Scheveningen. Netherlands, May 28-30, 1985 [ NASA-TP-26331 p 16 N87-10843 Implicit finite-difference simulation of separated p 39 A87-12651 hypersonic !!ow ever an indented nosetip Aircraft noise measurement: The 1.2 metre microphone MATHEMATICAL MODELS p 7 A87-11533 height saga Modeling and analysis of the dynamics of a drill Laminar flow control for transport aircraft applications [ PNR-903151 p 60 N87-11578 penetrating a thin plate p 24 A87-13021 LIGHT ALLOYS [ASME PAPER 86-WA/APM-33) p 46 A87-11112 LAMINATES Aeronautical manufacturers requirements for new Numerical simulation of viscous supersonic flow over Nondestructive inspection of composite structures by materials p 38 A87-11791 a generic fighter configuration p 6 A87-11509 low-velocity impact p 45 A87-10765 LININGS Computational aerodynamics of supersonic lifting .n.+=nrn= .~ in !noj?hnez+ nf +lnlcturalcommsites based Turbine Engine Hot Section Technology, 1984 vehicles p 12 N87-10030 on interleaf technology p 40 A87-12661 [ NASA-GP-ZWYJ p 52 ::03 ::!E? ?!:-c:kz! 2nd eryrimantal study of dvnamics of LANDING GEAR Combustion overview p43 N87-11181 two-dimensional body Fatigue fracture in steel landing gear components LOAD TESTS [ ISAS-6191 p 59 N87-10748 [ NLR-MP-85050-U) p 54 N87-11233 The effects of temperature and loading rate on Rcurves Correlation between flight simulation and processing of LANDING LOADS using the CLWL techniques -.-crack growth resistance flight tests based on inertial measurements Fatigue fracture in steel landing gear components curve (R curve); crack line wedge load (CLWL) [ NLR-MP-85058-UI p 28 N87-10863 [ NLR-MP-85050-Ul p 54 N87-11233 [ BAE-MSM-R-GEN-05441 p 50 N87-10405 Turbine Engine Hot Section Technology, 1984 LAP JOINTS LOGISTICS MANAGEMENT [ NASA-CP-23391 p 52 N87-11160 Stress analysis of Pathfinder-.? models Integrated logistics for reconnaissance systems Combustion overview p43 N87-11161 [NASA-CR-172458] p 51 N87-11179 p 61 A87-10942 Fatigue and fracture: Overview p 52 N67-11183 LASER ANEMOMETERS Thermal barrier coating life prediction model LONGITUDINALCONTROL Laser anemometers of hot-section applications development p 52 N87-11199 Effects of flap position on longitudinal parameters of p 52 N87-11187 Aerothermal modeling program, phase 2 HFB-320 LASER APPLICATIONS p 35 N87-11200 [ NAL-TM-SE-8602I p 25 N67-10062 Laser remote sensing proceriurrs ptoviria .id ;o The 3D inelastic analysis methods for hot section LORAN -- .I^-.."nC aviation during the approach for landing components p DJ 9'101-1 IC"" p 19 A87-11370 Combined utilization of Loran and GPS - The best from Component specific modeling p 35 N87-11207 LASER INTERFEROMETRY each system p 20 A87-11664 Constitutive modeling for isotropic materials A nonperturbing boundary-layertransition detection LOW ALTITUDE p 53 N87-11211 p 46 A87-10971 Management of airborne reconnaissance images Elevated temperature crack growth LATERAL STABILITY through real-time processing p 19 A87-10949 p 53 N87-11214 The lateral dynamic stability and control of a large LOW COST Stochastic crack propagation with applications to receiver aircraft during air-to-air refuelling A low cost commercial GPS set D 21 A87-12685 durability and damage tolerance analyses p 36 A67-12268 LOW REYNOLDS NUMBER IADA1 68040 1 D 53 N87-11226 LEADING EDGE FLAPS The effect of free stream disturbances and control MECHANICAL DRIVES Analysis of the vortical flow around a 60 dag Delta wing surface deflections on the performance of the Wortmann Engine-Airframe Integration for Rotorcraft with vortex flap p 11 N87-10006 airfoil at low Reynolds numbers p 11 N87-10007 [ AGARD-LS-1481 p26 N87-10067

A-13 MECHANICAL PROPERTIES SUBJECT INDEX

MECHANICAL PROPERTIES MOLECULAR ABSORPTION High temperature static strain gage program Superplasticity in aeroengine titanium alloy VT-9 and Vulnerability methodology and protective measures for p 52 N87-11188 its modified compositions p39 A87-12096 aircraft fire and explosion hazards. Volume 3: On-Board NICKEL COATINGS Advances in toughness of structural composites based Inert Gas Generator System (OBIGGS) studies. Part 1: Nickel coated graphite fiber COndUCtNe composites on interleaf technology p40 A87-12661 OBIGGS ground performance tests p 39 A87-11844 Developmentof a toughened bismaleimide resin prepreg [ AD-A1873571 p26 N87-10066 NOISE MEASUREMENT for carbon fiber composites p40 A87-12667 MOMENTUM TRANSFER Aircraft noise measurement: The 1.2 metre microphone Surface protection p 43 N87-11182 Guidebook for analysis of tether applications height saga [NASA-CR-1789041 p 38 N87-10169 [ PNR-903151 p60 N87-11578 METAL COMBUSTION NOISE POLLUTION Flammability and sensitivity of materials in MOTION Comparison of the effectiveness of measures of aircraft oxygenenriched atmospheres; Proceedings of the Sources and observers in motion, II -Acoustic radiation noise exposure by using social survey data Symposium. Washington, DC. April 23, 24. 1985. Volume from a small rigid body in arbitrary motion. Ill ~ Acoustic p 54 A87-10117 2 p 38 A87-10859 radiation from noncompact rigid bodies moving at high NOISE PREDICTION (AIRCRAm METAL FATIGUE Speed p 59 A87-12995 MRCA AIRCRAFT Analyses of bfoadband nase mechanisms of rotors Fatigue fracture in steel landing gear components p 58 A87-11769 [ NLR-MP-85050-Ul p 54 N87-11233 Ground and flight tests of Tornado reconnaissance pod p 22 A87-10940 The evolution of methods for noise prediction of high METAL MATRIX COMPOSITES speed rotors and propellers in the time domain MULTIPHASE FLOW Fiber-reinforcedsuperalloy composites provide an p 58 A87-11770 added performance edge p39 A87-12647 A study on the axially CuNed mixed-flow vaneless diffusers p 47 A87-11481 Prediction of helicopter rotor discrete frequency noise: METALOAS SYSTEMS MULTISENSOR APPLICATIONS A computer program incorporating realistic blade motions Flammability and sensitivity of materials in and advanced acoustic formulation A decentralized fault-tolerant approach to estimation in oxygenenriched atmospheres; Proceedings of the [NASA-TM-87721] p 59 N87-10750 multi-sensor navigation systems p 21 N87-10057 Symposium, Washington. DC, April 23. 24. 1985. Volume Propeller aircraft interim noise model utilization study 2 p 38 A87-10859 and validation METALLURGY N [ NASA-CR-1724281 p 60 N87-11576 Aeronautical research spin-ofls on the development of Separationof airborne and structurebornenoise radiated civil applications for aluminium alloys p 48 A87-11792 NASA PROGRAMS by plates constructed of conventional and composite MICROBURSTS National Aeronautics and Space Administration materials with applications for prediction of interior noise Optimal flight paths through microburst wind profiles p 61 N87-10774 paths in propeller driven aircraft p 60 N87-11579 p 35 A87-10519 Aeronautics and space report of the President NOISE PROPAGATION Aircraft accident reeport. Delta Air Lines, Inc., Lockheed [ NASA-TM-892391 ' p62 N87-10827 Nonlinear acoustic propagation of broadband noise L-1011-385-1, N726DA. DallaslFort Worth International Graduate engineenng research participation in p 58 A87-11773 Airport, Texas, August 2. 1985 aeronautics NOISE REDUCTION [ PB86-9104061 p 17 N87-10053 [NASA-CR-179798] p3 N87-10828 Free jet feasibility study of a thermal acoustic shield concept for ASTlVCE application: Dual stream nozzles Doppler Radar Detection of Wind Shear NASTRAN [ NASA-CR-38671 p 59 N87-10752 [ NASA-CP-2435] p 17 N87-10054 CSAlNASTRAN - A general purpose program for structural analysis p 56 A87-10879 Free-jet acoustic investigation of high-radius-ratio MICROELECTRONICS NATIONAL AIRSPACE SYSTEM coannular plug nozzles Avionics in the sub-microscopic world Radio Technical Cornmission for Aeronautics, Annual [ NASA-CR-3818 I p 59 N87-10753 p 48 A87-11800 Assembly Meeting and Technical Symposium, An experimentalinvestigation of the interior noise control MICROPHONES Washington, DC. November 19-21, 1985, Proceedings eftects of propeller synchrophasing Aircraft noise measurement: The 1.2 metre microphone p 1 A87-11801 [ NASA-CR-1781851 p 60 N87-11577 height saga The need to execute the National Airspace System Separation of airborne and structurebornenoise radiated [PNR-90315] p 60 N87-11578 Program and for R8D beyond p 1 A87-11802 by plates constructed of conventional and composite MICROPROCESSORS The system engineering and integration contract - An materials with applications for prediction of interior noise Reconnaissance and the microprocessor --- in aircraft overview p 61 A87-11804 paths in propeller dnven aircraft p 60 N87-11579 applications p 29 A87-10943 Project management support p 61 A87-11805 NOISE TOLERANCE MICROSTRUCTURE FANS - A U.S. perrpective p 20 A87-11807 Reaction to aircraft noise in residential areas around Superplasticity in aeroengine titanium alloy VT-9 and NAVIER-STOKES EOUATION Australian airports p 54 A87-10116 its modified compositions p39 A87-12096 Cornputation of turbulent supersonic flows around NONDESTRUCTIVE TESTS MICROWAVE LANDING SYSTEMS pointed bodies having crossflow separation A computer-aided nondestructive inspection system Flght experiments on MLS elevation guidance p 5 A87-11487 p 44 A87-10720 p 21 A87-12686 Implicit and semi-implicit methods for the compressible Manufacturingtechnology for nOndeStNCtive evaluation Int~rferenCeof the aeronauticalnavaids (frequencyband Navier-Stokesequations p 47 A87-11503 (NDE) system to implement retirement for cause (RFC) 108-118 MHz) from F.M broadcasting service (88-108 Experiences with an unfactored implicit procedures for gas turbine engine components MHz) p 21 A87-12690 predictor-correctwmethod p 47 A87-11522 p 44 A87-10727 Evaluation of captured water column technology for Helicopter MLS Flght Inspection hoject Calculation of strong viscouslinviscid interactions on advanced ultrasonic sizing techniques [DOTIFAA/CT-86/14] p2 N87-10002 airfoils by zonal solutions of the Navier-Stokes equations p 45 A87-10728 MILITARY AIRCRAFT p 7 A87-11540 A comparison of interactive boundary-layer and RFC automated inspection overview ---eddy current and Military aeronautical satellite communications thin-layer Navier-Stokesprocedures p 8 A87-11785 ultrasonic testing of gas turbine engine parts p 18 A87-10137 Report of the InternationalSymposium on Computational p 45 A87-10730 Cleaning methods and procedures for military oxygen Fluid Dynamics, Tokyo p 49 N87-10029 Predictive models and reliability improvement in equipment - Investigation results p 46 A87-10867 Analysis of two-dimensional incompressible flow past electromagnetic nondestructive evaluation Avionics in the Submicroscopic world airfoils using unsteady Navier-Stokes equations p 45 A87-10732 p 48 A87-11800 [NASA-CR-179823] p 12 N87-10040 Ouantitative thermal diffusivii measurements of Expert systems for aiding combat pilots Computation of transonic separated wing flows using composites p 45 A87-10750 p 29 A87-12212 an EulerINavier Stokes zonal approach Nondestructive inspection of composite structures by Future developments and manufacturing at GAF p 16 N87-10849 low-velocity impact p 45 A87-10765 p2 A87-13013 NAVIGATION AIDS Variations in ultrasonic backscatter attributed to Experience with the Onboard Checkout And Monitoring The mechanics of dynamically tunable gyroscopes ..- porosity p45 A87-10768 System (OCAMS) of a military aircraft resulting Russian book p 57 A87-10444 Electromagnetic methods to detect corrosion in aircraft improvements and the consequence for future design A decentralized fault-tolerant approach to estimation in structures p 45 A87-10791 p31 N87-10079 multi-sensor navigation systems p 21 N87-10057 NONLINEAR SYSTEMS NAVIGATION INSTRUMENTS Non-linear stability analysis of aircraft at high angles Integrated monitoring systems for tactical aircraft Disturbancesbrought by atmospheric statics to airborne of attack p 36 A87-12082 p31 N87-10080 navigation and communication systems Application of bifurcation and catastrophe theories to MILITARY HELICOPTERS p 20 A87-12678 near stall flight mechanics The future operations and procurement of rotary wing Potential impacts of advanced technologies on the ATC [AD-A167697] p 13 N87-10046 aircraft in the Royal Australian Navy p 2 A87-13012 Capacity of high-density terminal areas NORTHROP AIRCRAFT MILITARY TECHNOLOGY [NASA-CR-4024] p 22 N87-10854 The KS-147A LOROP camera system Summary of artificial and natural icing tests conducted NAVIGATION SATELLITES p 28 A87-10934 on US Army aircraft from 1974 to 1985 Combined utilization of Loran and GPS - The best from Integration of the KS-147A LOROP into the RF-BE [ FAAlCT-85/26] p25 N87-10064 each system p 20 A87-11664 p 28 A87-10935 MODELS NAVSTAR SATELLITES Operational usage of the KS-147A (LOROP) in the Spin-tunnel investigation of a 1l25-scale model of the Global positioning system applications RF-5E p 29 A87-10936 General Dynamics F-16XL airplane p 18 A87-10047 NOSE TIPS [NASA-TM-85660] p 12 N87-10041 NEAR WAKES Implicit finite-difference simulation of separated A numerical analysis of supersonic bottom flow with hypersonic flow Over an indented nosetip X-29A longitudinal and directional force and moment thermal modification of the wake p 3 A87-10409 p 7 A87-11533 supplemental transonic wind tunnel test results NETHERLANDS NOZLE FLOW [NASA-TM45909] p28 N87-10861 Aviation statistics. 1984 Density field of a viscous gas jet issuing from a conical MOISTURE CONTENT [ ISBN-90-357-0386.31 p 18 N87-10851 nozzle into vacuum p4 A87-10603 In-service environmental effects on carbon fibre NICKEL ALLOYS Vortex simulationof propagating stall in a linear cascade composite material p39 A87-12659 Forging of blades for gas turbines p 44 A87-10124 of airfoils p5 A87-11117

A-14 SUBJECT INDEX

Finite element computations for hgh speed 30 inviscid OXYGEN PHOTOINTERPRETATION flows p 7 A87-11542 Flammability and sensitivity of materials in Photogrammetric tools for panoramic sector scan Static internal performance of single-expansion-ramp oxygen-enrichad atmospheres; Proceedings of the imagery in the VIDARS analysis station nozzles with thrust-vectoring capability up to 60 deg Symposium. Washington, E,April 23. 24. 1985. Volume p 19 A87-10948 [ NASA-TP-23641 p 15 N87-10839 2 p 38 A87-10859 PHOTOMETERS NUMERICAL ANALYSIS OXYGEN SUPPLY EQUIPMENT Long range E-0Reconnaissance System and flight test Natural frequency analysis of compressor rotor blades Case study of Royal Australian Air Force P3B Orion results p 28 A87-10933 p 34 A87-10899 aircraft ground oxygen lire mcident p 16 A87-10866 Integration of the KS-147A LOROP into the RF-5E Cleaning methods and procedures for military oxygen Numerical analysis with generalized J-integral p 28 A87-10935 WUiPment - Investigation results p 46 A87-10867 p 47 A87-11492 PILOT PERFORMANCE Numerical methods and a computer program for Lowcost avionics simulation for aircrew training subsonic and supersonic aerodynamic design and analysis P [ AD-A1891 981 p 34 N87-10865 of wings with attainable thNSt considerations PILOTS (PERSONNEL) [ NASA-CR-3EOE1 p 3 N87-10829 P-3 AIRCRAFT Ground-based time-guidance algorithm for control of NUMERICAL FLOW VISUALIZATION Case Study of Royal Australian Air Force p3B Orion airplanes in a timemetered air traffic control environment: Numerical investigation of supersonic flow past aircraft ground oxygen lire incident p 16 A87-10866 A piloted simulation study spike-tipped blunt bodiis p4 A87-10614 PAINTS [ NASA-TP-26161 p 34 N87-10864 Mathematical modeling of separated flow past a wing lmpoved durability airline paint schemes PIPER AIRCRAFT profile and aerodynamic hysteresis p 5 A87-10619 p 40 A87-12660 Airborne measurement methods applied to the Conference on Numerical Memods in Fluid Mechanics, PANEL FLUll€R determination of boundary conditions at the sea surface: 6th. Goeltingen. West Germany. September 25-27, 1985. Resonant and non-resonant acoustic properties of The TOSCANE experiment p 55 N87-11242 Proceedings p 47 A87-11501 elastic panels. I - The radiation problem PITCH (INCLINATION) Numerical experiments with a total variation diminishing p 49 A87-13026 Acta Aeronautica et Astronautica Sinica (selected WO)MacCormack scheme p 6 A87-11526 Effect of static inplane loads and boundary conditions articles) on the flutter of flat rectangular panels Efficient numerical method for transonic flow [ AD-A16791 81 p3 N87-10004 [ NAL-TM-ST-86041 p 50 N87-10404 simulations p 6 A87-11528 PLANE WAVES PANEL METHOD (FLUID DYNAMICS) Transformationof a plane uniform shock into cylindrical An exact integral (field panel) method for the calculation or spherical uniform shock by wall shaping of two-dimensbnal transonic potential flow around p 37 A87-12585 0 complex configurations p9 A87-12267 PLANETARYBOUNDARYLAYER Application of a potential code to general steady flows Statistics of wind shear due to nocturnal boondary layer OBLIQUE SHOCK WAVES in three dimensions p 50 N87-10262 On the occurrence of regular reflection of shocks in PANORAMIC SCANNING jet airstreams in North Germany p 56 N87-11461 concave corner flows p 10 A87-12586 Photogrammetric tools for panoramic sector scan PLANETARY NEBULAE OBLIQUE WINGS imagery in the VIDARS analysis station Infrared emission lines from planetary nebulae In-flight total forces, moments and static aeroelastic p 19 A87-10948 p 62 N87-10791 characteristics of an oblique-wing research airplane PARALLEL PROCESSING (COMPUTERS) PLANNING [NASA-TP-2224] p 36 N87-10103 The ASPRO parallel inference engine (A real-timeexpert Air Force technical objective document fiscal year Flight-determinedaerodynamic derivatives of the AD-1 system) p 29 A87-12218 1987 oblique-wing research airplane PARAMETER IDENTIFICATION [AD-A167324] p 62 N87-10779 [ NASA-TP-22221 p 36 N87-10871 Effects of flap position on longitudinal parameters of PLASTIC AIRCRAFT STRUCTURES OBSERVABILITY (SYSTEMS) HFB-320 Composite matenals for aircraft structures --- Book Performance monitoring of sensors in high reliable flight [NAL-TM-SE-8602] p 25 N87-10062 p 38 A87-10294 control systems using deterministic ObSeNerS Correlation between flight Simulation and processing of Variations in ultrasonic backscatter attributed to p32 N87-10087 flight tests based on inertial measurements porosity p 45 A87-10768 OBSERVATION [NLR-MP-85058-U] p 28 N87-10863 Impact resistant hybrid composite for aircrafl leading Sources and ObseNerS in motion. II - Acoustic radiation PASSENGER AIRCRAFT edges p 24 A87-11848 from a small riiid body in arbitrary motion. 111 - Acoustic Future aero-engine control systems, why FADEC? Cost. Manufacture of bonded composite assemblies for radiation from non-compact rigid bodies moving at hgh design cycle timescale, reliability. weight and size targets aircraft p 1 A87-13005 Speed p59 A87-12995 --- Full Authority Digital Electronic Control (FADEC) Structural design with new materials OCEANSURFACE [PNR-90298] p 35 N87-10867 p 49 A87-13011 Airborne measurement methods applied to the PASSENGERS Investigationinto the attenuation and velocity of acoustic determination of boundary conditions at the sea surface: The crash of Delta Flight 191 - Are the nightmares emissions in carbon fiber composite aircraft structures The TOSCANE experiment p 55 N87-11242 compensable? p 61 A87-10510 [ BAE-KGT-R-GEN-013491 p 41 N87-10180 The C and KUband Scanerometer results from Canadian PERFORATED PLATES PLUG NOZZLES participation in the ESA PROMESS ocean measurement Modeling and analysis of the dynamics of a drill Free-jet acoustic investigation of high-radi0s-ratio campaign p 55 N87-11252 penetrating a thin plate coannular plug nozzles OIL ADDITIVES [ASME PAPER 86-WA/APM-33] p 46 A87-11112 [ NASA-CR-38181 p 59 N87-10753 Thickened oils p40 A87-12902 PERFORMANCE PREDICTION PODS (EXTERNAL STORES) OILS Single or dual pod concepts for tactical Fire occurring and expanding in connection with oils in Predictive models and reliability improvement in electromagnetic nondestructive evaluation reconnaissance p 29 A87-10939 aviation p16 A87-11368 Ground and flight tests of Tornado reconnaissance p 45 A87-10732 ONBOARD DATA PROCESSING pod p 22 A87-10940 Surface protection p43 N87-11182 Proceedings of the 13th Symposium on Aircraft POLAR NAVIGATION Integrated Data Systems PERFORMANCE TESTS Polar navigation assisted by satellite [ DFVLR-MITT-86-04] p30 N87-10075 Braking performance of aircraft tires p 20 A87-11663 ONE DIMENSIONAL FLOW p24 A87-12649 POLYSULFIDES Large perturbation flow field analysis and simulation for In-service environmental effects on carbon fibre Polymer systems for rapid sealing of aircraft structures supersonic inlets composite material D 39 A87-12659 at low i~m~raiiira [ NASA-CR-1746761 p 14 N87-10835 A test research for improving the performance of V-type [AD-A167667] p 41 N87-10209 OPTICAL EQUIPMENT flameholder used in an afterburner p 34 A87-12965 POROSITY Single or dual pod concepts for tactical Engine-airframe integration considerations for Variations in ultrasonic backscaner anributed to reconnaissance p 29 A87-10939 preliminary air vehicle perlorrnance analysis porosity p45 A87-10768 OPTICAL RADAR p26 N87-10068 POSITION (LOCATION) Experimentaland theoretical Doppler-lidarsignatures of Comparative evaluation of redundant flight data Polar navigation assisted by satellite aircraft wake vortices p 14 N87-10330 recorded by a digital aircraft integrated data system p 20 A87-11663 OPTIMAL CONTROL recorder (DAR) on board an Airbus A-310 aircraft POSITION INDICATORS Optimal control of viscous flow at high Reynolds p33 N87-10098 United States Navy - Canadian Forces solid state flight numbers P5 A87-10620 data recorderlcrash position locator expenment on the OPTIMIZATION Evaluation results of the 700 deg C Chinese strain gages p 52 N87-11189 8-720 controlled impact demonstration Development of a turbomachinery design optimization p 33 N87-10097 procedure using a multiple-parameter nonlinear PERTURBATION THEORY POTENTIAL FLOW Development of a turbomachinery design optimization perturbation method An exact integral (field panel) method for the calculation r.a.0. ,.-nnnr. prgc4nye tjrinz a mdii?la-?ararnatar nonlinaer LI.T\Un-”“-d”a I J v 2 iG7- i irirV3 oi wo-aimensionai transonic porenriai iiow around perturbation method ORBITAL MECHANICS complex configurations p9 A87-12267 [NASA-CR-38311 p2 N87-10003 Guidebook for analysis of tether applications Application of a potential code to general steady flows [NASA-CR-178904] P 38 N87-10169 PHOTOGRAMMETRY in three dimensions p 50 N87-10262 ORBITAL SPACE STATIONS Photogrammetric tools for panoramic sector scan POWER SPECTRA National Aeronautics and Space Administration imagery in the VIDARS analysis station Signal processing and interpretation using multilevel P 61 N87-10774 p 19 A87-10948 signal abstractions OSCILLATING FLOW PHOTOGRAPHIC EQUIPMENT [ AD-A1691 661 p 57 N87-11513 Excitation of the natural oscillations of a boundary layer The KS-147A LOROP camera system PREDICTION ANALYSIS TECHNIQUES by an external acoustic field P4 A87-10610 p 28 A87-10934 Prediction of gust loadings and alleviation at transonic Theoretical treatment of gust simulation in the wind Integration of the KS-147A LOROP into the RF-5E speeds tunnel P9 A87-12148 p 28 A87-10935 [ AD-A1677481 p 13 N87-10047

A-15 PREDICTIONS SUBJECT INDEX

Toward comparing experiment and theory for Separationof airbwne and Structureborne noise radiated RADIO FREQUENCY INTERFERENCE corroborative research on hingeless rotor stability in by plates constructed of conventional and composite Interferenceof the aeronauticalnavaids (frequencyband forward flight (an experimental and analytical investigation materials with applications for prediction of interior noise 108-118 MHz) from F.M broadcasting service (88-108 of isolated rotor-flaplag stability in forward flight) paths in propeller driven aircraft p 60 N87-11579 MHz) p21 A87-12690 [NASA-CR-179711) p25 N87-10063 PROPELLER SLIPSTREAMS RADIO NAVIGATION Supersonic second order analysis and optimization Prop-fan slipstream effects using static simulators: Low Navigation and environment; Proceedings of the Fifth program user's manual speed task, phase 1 International Congress. Tokyo, Japan, October 1-5, 1985 [ NASA-CR-172342) p 15 N87-10842 [ BAE-B59R/R-D/610/13498] p 37 N87-10875 p 20 A87-12676 Turbine Engine Hot Section Technology, 1984 PROPELLERS Integration of GPS with other radionavigationsystems [NASA-CP-23391 p 52 N87-11180 The evolution of methods for noise prediction of high p 21 A87-12680 Host turbine heat transfer ovewiew speed rotors and propellers in the time domain The U.S. Federal RadionavigationPlan p 52 N87-11184 p 58 A87-11770 p 21 A87-12684 Effects of surface chemistry on hot corrosion life PROPULSION A low cost commercial GPS set p 21 A87-12685 p 43 N87-11193 Wind tunnel test of the modified goldschmied model Interferenceof the aeronauticalnavaids (frequencyband Coating life prediction p 43 N87-11194 with propulsion and empennage: Analysis of test results 108-118 MHz) from F.M broadcasting service (88-108 Introduction to life modeling of thermal barrier [ AD-AI673601 p 13 N87-10045 MHz) p 21 A87-12690 coatings p 43 N87-11195 RADIOMETERS PROPULSION SYSTEM PERFORMANCE Thermal barrier coaling life prediction model Quantitative thermal diffusivity measurements of Aeronautical facilities assessment development p 52 N87-11199 composites p 45 A87-10750 [NASA-RP-1146] p 37 N87-10876 Aerothermal modeling program, phase 2 REAL TIME OPERATION p35 N87-11200 PROTECTION Rapid target locator p 18 A87-10944 Component specific modeling p 35 N87-11207 Helicopter air intake protection systems Data compression for IR reconnaissance Elevated temperature crack growth p 27 N87-10073 p 18 A87-10947 p 53 N87-11214 PROTECTIVE COATINGS Management of airborne reconnaissance images Measurement of airfoil heat transfer coefficients on a Surface protection p 43 N87-11182 through real-time processing p 19 A87-10949 turbine stage p 53 N87-11221 Coating life prediction p 43 N87-11194 Reconnaissance interface - The near real time is now Coolant passage heat transfer with rotation, a progress PROTOTYPES p 29 A87-10950 report p 53 N87-11225 Hot section viewing system The ASPRO parallel inference engine (A real-time expert PREDICTIONS [ NASA-CR-1747731 p 51 N87-11144 system) p 29 A87-12218 Experiences with an unfactored implicit PSYCHOLOGICAL EFFECTS Real time debugging software package for flight predictor-corrector method p 47 A87-11522 The crash of Delta Flight 191 - Are the nightmares simulator software system with variable labeled COMMON Surface measurements of gust fronts and microbursts compensable? p 61 A87-10510 blocks during the JAWS (Joint Airport Weather Studies) Projecl: PULSE COMMUNICATION [ NLR-MP-85013-Ul p 57 N87-11530 Statistical results and implicationsforwmd shear detection, Potential impacts of advanced technologies on the ATC REAlTACHED FLOW prediction and modeling capacity of high-density terminal areas Supersonic. nonlinear, attached-flow wing design for [ PB86-2008471 p 55 N87-10665 high lift with experimental validation [NASA-CR-4024] p 22 N87-10854 PREPREGS [ NASA-TP-2336I p 12 N87-10042 Development of a toughened bismaleimide resin prepreg PUSHBROOM SENSOR MODES RECTANGULAR PLATES for carbon fiber composites p40 A87-12667 Effects of atmosphere on oblique reconnaissance --- Natural frequency analysis cf pretwisted plates PRESIDENTIAL REPORTS in CCD cameras p 29 A87-10937 p 46 A87-10900 Aeronautics and space report of the President PYLONS RECTANGULAR WINGS [ NASA-TM-892391 p 62 N87-10827 Design and fabrication of the NASA decoupler pylon Euler equations analysis of the initial roll-up of aircraft PRESSURE DISTRIBUTION for the F-16 aircraft wakes p4 A87-10522 A comparison of interactive boundary-layer and [NASA-CR-1723541 p 25 N87-10065 REDUNDANCY thin-layer Navier-Stokes procedures p 8 A87-11785 Design and fabrication of the NASA decoupler pylon A redundancy management procedurefor fault detection Experimental study of the boundary layer on a low for the F-16 aircraft, addendum 1 and isolation p 46 A87-11127 Reynolds number airfoil in steady and unsteady flow [NASA-CR-172355] p 27 N87-10860 REFLECTED WAVES p 14 N87-10052 On the occurrence of regular reflection of shocks in Practicalevaluation of wall pressure signature correction concave corner flows p 10 A87-12586 methods in the 2.7m x 2.lm low speed wind tunnel Q REGULATIONS [ BAE-ARG-2041 p 37 N87-10874 Flight recorders: New US regulations and new PRESSUREMEASUREMENT QUALITY CONTROL International Civil Aviation Organization (ICAO) Tunnel interference from pressure measurements on How to maintain a consistent quality in your bonding standards p 32 N87-10093 control surfaces process? p 48 A87-12656 REINFORCEMENT RINGS [AE-TM-8-83] p 37 N87-10104 Engine-airframe integration for rotorcraft Component A reinforcing band near the flange of a heated cylindrical NASA dilution jet mixing, phase 3 p 53 N87-11202 specifications and qualification p 26 N87-10071 casing p 48 A87-12445 PRESTRESSING RELIABILITY ANALYSIS Natural frequency analysis of pretwisted plates Predictive models and reliability improvement in p 46 A87-10900 R electromagnetic nondestructive evaluation PROBLEM SOLVING p 45 A87-I0732 Engine-transmission-structural airframe members RADAR DATA A redundancy management procedure for fault detection compatibility p 26 N87-10069 Stochastic modelling of radar returns and isolation p 46 A87-11127 PRODUCTDEVELOPMENT p 18 A87-10143 RELIABILITY ENGINEERING Aeronautical manufacturers requirements for new RADAR DETECTION Investigationof optimal complexityof BITE and its effects materials p 38 A87-11791 The methodology and tools for processing radar data on reliability,maintainability, monitoring and fault prediction Aircraft Integrated Data Systems (AIDS): Evolution and p 19 A87-11662 --- Built-In Test (BITE) electronic systems revolution p 30 N87-10077 RADARMEASUREMENT [ETN-86-97976] p 51 N87-11175 Lufthansa's Aircraft Integrated Data Systems (AIDS) Doppler Radar Detection of Wind Shear REMOTE CONTROL based A-310 engine condition monitoringsystem: Progress [NASA-CP-2435] p 17 N87-10054 Piloting of unmanned air vehicles. II achieved between the 12th and 13th AIDS Symposiums RADAR SIGNATURES p 23 A87-10941 p 31 N87-10084 Experimental and theoretical Doppler-lidar signatures of REMOTE SENSING Development of single crystal alloys for specific engine aircraft wake vortices p 14 N87-10330 Laser remote sensing procedures provide an aid to applications RADAR TRACKING aviation during the approach for landing [PNR-90320] p60 N87-11616 A new concept in air traffic control - The multi-radar p 19 A87-11370 PROJECTMANAGEMENT tracking (MRT) p21 A87-12689 REMOTELY PILOTED VEHICLES Project management support p 61 A87-11805 RADIATION SOURCES Piloting of unmanned air vehicles. II PROP-FAN TECHNOLOGY Sources and observers in motion, II -Acoustic radiation p 23 A87-10941 A review of advanced turboprop transport activity from a small rigid body in arbitrary motion. 111 .Acoustic RESEARCH p 24 A87-12650 Aeronautical research spin-offs on the development of radiation from non-comDact.1 rioid bodies movino at hiah PTA test bod aircraft engine inlet model test report, Speed p 59 Aii7-12995 civil applications for aluminium alloys p 48 A87-11792 revised RADIATIVE HEAT TRANSFER RESEARCH AIRCRAFT [NASA-CR-174845] p 35 N87-10866 Combustion overview D 43 N87-11181 In-flight total forces, moments and static aerwlastic Prop-fan slipstream effects using static sirnulators: Low RADIO BEACONS characteristics of an oblique-wing research airplane speed task, phase 1 United States Navy - Canadian Forces solid state flight [ NASA-TP-22241 p 36 N87-10103 [BAE-B59R/R-D/610/13498] p 37 N87-10875 data recorderlcrash position locator experiment on the Flightdetermined aerodynamic derivatives of the AD-1 PROPELLER BLADES 8-720 controlled impact demonstration oblique-wing research airplane Effect of angular inflow on the vibratory response of a p 33 N87-10097 [ NASA-TP-22221 p 36 N87-10871 counter-rotating propeller RADIO COMMUNICATION RESEARCH ANDDEVELOPMENT [ NASA-CR-1748191 p 15 N87-10840 Radio Technical Commission for Aeronautics, Annual The need to execute the National Airspace System An experimentalinvestigation of the interior noise control Assembly Meeting and Technical Symposium. Program and for RBD beyond pl A87-11802 eflects of propeller synchrophasing Washington, DC, November 19-21, 1985, Proceedings Developments at ARL to meet future Australian needs [ NASA-CR-1781851 p60 N87-11577 p 1 A87-11801 in aeronautics p2 A87-13017 PROPELLER DRIVE RADIO CONTROL RESEARCH MANAGEMENT Propeller aircraft interior noise model utilization study Operating and suppor; hazard analysisfor self-contained Air Force technical objective document fiscal year and validation navigation system LSI model 6216A. B and C. group B 1987 [ NASA-CR-1724281 p60 N87-11576 [AD-A169381] p 22 N87-10855 [ AD-AI 67324 I p 62 N87-10779

A-16 SUBJECT INDEX

RESIDENTIAL AREAS Analysis of the vibration of the input bevel pinion in RAN SHOCK TUBES Reaction to aircraft noise in residential areas around Wessex heliter main rotor gearbox WAK143 prior to Unsteady drag over cylinders and aerofoils in transonic Australian airports p 54 A87-10116 failure shock tube flows p 10 A87-12617 RESONANT FREOUENCIES [ARL-AERO-PROP-R-169] p 25 N87-10061 High temperature heat transfer for gas turbines using Natural frequency analysis of compressor rotor blades Prediction of helicopter rotor discrete frequency noise: shock tubes p37 A87-12646 p 34 A87-10899 A computer program incorporating realistic blade motions SHOCK WAVE PROPAGATION Natural frequency analysis of pretwisted plates and advanced acoustic formulation Transformation of a plane uniform shock into cylindrical p46 A87-10900 [ NASA-TM-877211 p 59 N87-10750 or spherical uniform shock by wall shaping Resonant and non-resonant acoustic properties of Transonic flow analysis for rotm.. Part 2: p 37 A87-12585 Three-dimensional, elastic panels. I - The radiation problem unsteady, full-potential calculation On the occurrence of regular reflection of shocks in p 49 A87-13026 INASA-TP-23751 D 15 N87-10841 concave corner flows p 10 A87-12586 RUNGE-KUTTA METHOD SHOCK WAVES RETIREMENT FOR CAUSE Numerical solution of the Euler equations using rational Manufacturingtechnology for nondestructive evaluation On broadband shock associated noise of supersonic Runge-Kuna method p 7 A87-11538 (NDE) system to implement retirement for cause (RFC) jets p 58 A87-11768 RUNWAYS Transonic cascade flow solved by shock-capture procedures for gas turbine engine components Potential impacts of advanced technologies on the ATC p44 A87-10727 computation followed by separate-regioncomputation with capacity of high-density terminal areas shock fitting p 10 A87-12956 REVERSED FLOW [ NASA-CR-40241 p 22 N87-10854 Supersonic flow around tip sides of wings Numerical solution of the 3-dimensional boundary layer p 12 N87-10033 equations in the inverse mode using finite differences SHORT TAKEOFF AIRCRAFT pll N87-10005 S Yakovlev Forger --- history of the Yak-38 Soviet Very REYNOLDS NUMBER Short Takaand Landing aircraft. p 22 A87-10575 Report on tests of a CAST 10 airfoil with fixed transition SAFETY SIDE-LOOKING RADAR in the T2 transonic cryogenic wind tunnel with self-adaptive Operating and support hazard analysisfor self-contained Data processing and calibration for an airborne navigation system LSI model 6216A. B and C. group B walls scatterometer p 30 A87-12694 [RT-OA-63/1685] p 14 N87-10834 [AD-A169381] p22 N87-lOi55 SIEVES SAFETY FACTORS RIGID ROTORS Vulnerability methodology and protective measures for Crashworthiness experiment summary full-scale Sources and ObSeNerS in motion. IV - Acou~liC aircraft fire and explosion hazards. Volume 3 On-Board transport controlled impact demonstration program measurements on aerofoils moving in a circle at high Inert Gas Generator System (OBIGGS) studies. Part 1: [DOT/FAA/CT-85/20] p 17 N87-10055 speed p59 A87-12996 OBIGGS ground performance tests RIGID STRUCTURES National Transportation Safety Board safety [ADA1673571 p26 N87-10066 recommendation p 18 N87-10852 Sources and ObseNerS in motion. II - Acoustic radiation SIGNAL ANALYSIS SATELLITE COMMUNICATION from a small rigid body in arbitrary motion. Ill - Acoustic Stochastic modelling of radar returns radiation from non-compact rigid bodies moving at high Military aeronautical satellite communications p 18 A87-10143 speed p 59 A87-12995 p 18 A87-10137 SIGNAL PROCESSING Transitiion to new systems and international ROTARY GYROSCOPES Signal processing and interpretation using multilevel perspectives p 20 A87-11806 The mechanics of dynamically tunable gyroscopes --- signal abstractions SCAlTEROMETERS Russian book p 57 A87-10444 [ AD-A1691 661 p 57 N87-11513 Data orocessina and calibration for an airborne ROTARY STABILITY S!GNAL TO NOISE RATIOS Effect of tangential torque on the dynamics of flexible scatterometer p 30 A87-12694 Long range E-O ReconnaissanceSystem and flight test The C and Ku band scatterometer results from Canadian rotors results p 28 A87-10933 participation in the ESA PROMESS ocean measurement [ASME PAPER 86-WAIAPM-231 p 46 A87-11113 Effects of atmosphere on oblique reconnaissamu, --- campaign p 55 N87-11252 Low speed rotary aerodynamics of F-18 configuration in CCD cameras p 29 A87-10937 for 0 deg to 90 deg angle of attack Test results and SEALERS SIMILITUDE LAW analysis Polymer systems for rapid sealing of aircraft structures Similarity law for the supersonic flow past flat surfaces [ NASA-CR-3608] p 15 N87-10836 at low temperature with intense distributed injection p 10 A87-12843 Rotary balance data and analysis for the X-29A airplane [ AD-A1676671 p 41 N87-10209 SIMULATION for an angle-of-attack range of 0 deg to 90 deg SEALS (STOPPERS) Numerical simulation of viscous supersonic flow over [ NASA-CR-37471 p 15 N87-10837 Alumina-CoCrAIY material as an improved intermediate a generic fighter configuration p6 A87-11509 ROTARY WING AIRCRAFT layer for graded ceramic gas-path sealing in aeroturbine SIMULATORS The future operations and procurement of rotary wing engines p 40 A87-12928 Prop-fan slipstream effects using static Simulators: Low aircraft in the Royal Australian Navy p 2 A87-13012 SEPARATED FLOW speed task, phase 1 ROTARY WINGS Mathematical modeling of separated flow past a wing [ BAE-B59R/R-D/610/134981 p 37 N87-10875 Engine-airframe integration considerations for profile and aerodynamic hysteresis p 5 A87-10619 SINGLE CRYSTALS preliminary air vehicle performance analysis Computation of turbulent supersonic flows around Cost effective single crystals --- gas turbine p26 N87-10068 pointed bodies having crossflow separation components Response of a small-turboshaft-engine compression p5 A87-11487 [ PNR-90319) p60 N87-11615 system to inlet temperature distortion Implicit finite-difference simulation of separated Development of single crystal alloys for specific engine [ NASA-TM-83765] p 35 N87-10100 hypersonic flow over an indented nosetip applications Parametric analysis of a passive cyclic control device p 7 A87-11533 [PNR-90320] p 60 N87-11616 for helicopters SINGULARITY (MATHEMATICS) Computationsof separated subsonic and transonic flow [NASA-CR-1666081 p 28 N87-10862 Body of revolution comparisons for axial- and abaut airfoils in unsteady motion p 8 AW?1786 ROTOR AERODYNAMICS surface-singularitydistributions p4 A87-10525 Toward comparing experiment and theory for An experimental study on large negative incidence SKIN FRICTION corroborative research on hingeless rotor stability in separated flow in two-dimensional turbine cascades Effects of tail span and empennage arrangement on p 10 A87-12957 forward flight (an experimental and analytiical investigation drag of a typical single-engine fighter aft end of isolated rotor-flap-lag stability in forward flight) Acta Aeronautica et Astronautica Sinica (selected [ NASA-TP-23521 p 15 N87-10838 [NASA-CR-1797111 p25 N87-10063 articles) SLENDER BODIES I^-..- .-r" [ADA16791 81 p3 N87-10004 nuiun .,.YUYLI Vortex shedding of a square cylinder in front of a slender Analyses of broadband noise mechanisms of rotors Numerical solution of the 3-dimensional boundary layer airfoil at high neynoias numoers. Pari i. Sp&iy diiri; p 58 A87-11769 equations in the inverse mode using finite differences [MPIS-23/1985] p13 N87-10048 Helicopter impulsive noise - Theoretical and p 11 N87-10005 SLENDER WINGS experimental status p 58 A87-11771 Study of three-dimensional separation on a spheroid at Experimental investigations of three-dimensional ROTOR BLADES (TURBOMACHINERY) incidence p 49 N87-10016 laminar boundary layers on a slender delta wing Aerwlastic stability of composite rotor blades in hover Unsteady airload computations for airfoils oscillating in p9 A87-12145 p25 N87-10060 attached and separated compressible flow Advanced method for computing the flow around wings Toward comparing experiment and theory for [ NLR-MP-8504041 p 16 N87-10846 with rear separation and ground effect corroborative research on hingeless rotor stability in computation of transonic separated wing flows using [DFVLR-FB-86-17] p 50 N87-11017 forward flight (an experimental and analytical investigation an Euler/Navier Stokes zonal approach SMOKE of isolated rotor-flap-lag stability in forward flight) p 16 N87-10849 A method for calculating the susceptibility of jet fuels [NASA-CR-179711] p25 N87-10063 to smoking p 40 A87-12901 Advanced method for computing the flow around wings The high speed cascade wind tunnel: Still an important SODAR with rear separation and ground effect test facility for investigations on turbomachinery blades [DFVLR-FB-86-171 p 50 N87-11017 Monitoring of terminal flight phases environment [ DFVLR-MITT-8BlI ] p 38 N87-10878 C?hse'v~!innrand rnndnla 0 55 A87-12679 Turbine Engine Hot Section Technology. 1984 Visualization of three-dimensional forced unsteady SOUND WAVES [NASA-CP-2339] p 52 N87-11180 separated flow Mechanicsof flow-induced sound and vibration. Volume [AD-A168939] p 51 N87-11129 ROTORSPEED 1 General concepts and elementary source. Volume 2 . Effect of tangential torque on the dynamics of flexible SEPARATORS Complex flow-structure interactions --- Book rotors Impact of IPS and IRS configurations on engine p 57 A87-10293 [ASME PAPER 86-WA/APM-23] p 46 A87-11113 installation design p 26 N87-10070 Sources and observers in motion. II - Acoustic radiation The evolution of methods for noise prediction of high SERVICE LIFE from a small rigid body in arbitrary motion. 111 - Acoustic speed rotors and propellers in the time domain Flight service evaluation of composite helicopter radiation from non-compact rigid bodies moving at high P 58 A87-11770 components speed p 59 A87-12995 ROTORS [NASA-CR-178149] p 41 N87-10182 SPACE COMMERCIALIZATION A simulation of rotor-stator interaction using the Euler SHAPES National Aeronautics and Space Administration equations and patched grids p 7 A87-11536 Induced drag of a curved wing p 10 A87-12805 p 61 N87-10774

A-17 SUBJECT INDEX

SPACE EXPLORATION STEELS SUCTION Aeronautlcs and space report of the President Fractographic aspects of the cyclic fracture toughness Wind tunnel test of the modified goldschmied model [ NASA-TM-892391 p 62 N87-10827 of 35KhN3MFA steel in vacuum. air, and hydrogen with propulsion and empennage: Analysis of test results SPACE SURVEILLANCE (SPACEBORNE) p 40 A87-12882 [ AD-A167360 I p 13 N87-10045 Project management support p 61 A87-11805 STIFFNESS SUPERCRITICAL AIRFOILS SPACE TRANSPORTATION SYSTEM A higher order beam element for vibration of beams Computationsof separated subsonic and transonic flow National Aeronautics and Space Administration with discontinuities p 46 A87-10898 about airfoils in unsteady motion p 8 A87-11786 p 61 N87-10774 STOCHASTIC PROCESSES SUPERCRITICAL FLOW SPACECRAFT CONSTRUCTION MATERIALS Stochastic modelling of radar returns Supersonic. nonlinear. attached-flow wing design for International Conference - Superplasticity in Aerospace p 18 A87-10143 high lilt with experimental validation Aluminium Stochastic crack propagation with applications to [ NASA-TP-23361 p 12 N87-10042 [ BAE-S85/AMR/0066] p 42 N87-10994 durability and damage tolerance analyses SUPERPLASTICITY SPACING [ AD-A1680401 p 53 N87-11226 Superplasticity in aeroengine titanium alloy VT-9 and Vortex shedding of a square cylinder in front of a slender its modified compositions p 39 A87-12096 STRAIN GAGES airfoil at hlgh Reynolds numbers Part 1 Spacing effect International Conference - Superplasticityin Aerospace High temperature static strain gage program [ MPIS-23/1985] p 13 N87-10048 Aluminium p52 N87-11188 SPATIAL RESOLUTION [BAE-S85/AMR/0066] p 42 N87-10994 Effects of atmosphere on oblque reconnaissance _-- Evaluation results of the 700 deg C Chinese strain SUPERSONIC AIRCRAFT in CCD cameras p 29 A87-10937 gages p 52 N87-11189 Computational aerodynamics of supersonic lifting SPECIFICATIONS STREAMLINING vehicles PI2 N87-10030 Enqine-airframe integration for rotorcraft System Wind tunnel test of the modified goldschmied model SUPERSONIC AIRFOILS specifications and qualifiiation p 27 N87-10074 with propulsion and empennage: Analysis of test results Supersonic, nonlinear, attached-flow wing design for SPHERICAL COORDINATES [AD-AI673601 p 13 N87-10045 high lift with experimental validation Analysis of two-dimensional incompressible flow past STRESS ANALYSIS [NASA-TP-2336] p 12 N87-10042 airfoils using unsteady Navier-Stokes equations Stress analysis of Pathfinder2 models SUPERSONIC BOUNDARY LAYERS [ NASA-CR-1798231 p 12 N87-10040 [NASA-CR-1724581 p51 N87-11179 Excitation of the natural oscillations of a boundary layer SPHEROIDS . The 3D inelastic analysis methods for hot section by an external acoustic field p4 A87-10610 Study of three-dimensionalseparation on a spheroid at components p53 N87-11206 SUPERSONIC FLOW incidence p49 N87-10016 STRESS CORROSION CRACKING A numerical analysis of supersonic bottom flow with SPIKES (AERODYNAMIC CONFIGURATIONS) Fractographic aspects of the cyclic fracture toughness thermal modification of the wake p 3 A87-10409 Numerical investigation of supersonic flow past of 35KhN3MFA steel in vacuum, air, and hydrogen Numerical investigation of supersonic flow past spike-tipped blunt bodies p4 A87-10614 p 40 A87-12882 spike-tipped blunt bodies p4 A87-10614 SPIN DYNAMICS STRESS INTENSITY FACTORS Conicalwing of maximum lift-to-drag ratio in a supersonic Spin-tunnel investigation of a 1/25-scale model of the Stress analysis of Pathfinder-2 models gas flow p4 A87-10615 General Dynamics F-16XL airplane [NASA-CR-1724581 p51 N87-11179 Calculation of unsteady supersonic flow past a plane [ NASA-TM-856601 p 12 N67-10041 blade row under the effect of vortex inhomogeneities in STRESSSTRAIN DIAGRAMS SPIN TESTS the oncoming flow p5 A87-10618 Tension analysis of stiffened aircraft structures Spin-tunnel investigation of a 1125-scale model of the Motion of a gas in a duct behind a moving body p44 A87-10516 General Dynamics F-16XL airplane p5 A87-10675 [ NASA-TM-856601 p 12 N87-10041 STRESS-STRAIN RELATIONSHIPS Computation of turbulent supersonic flows around SPLITTING Fatigue and fracture: Overview p 52 N87-11163 pointed bodies having crossflow separation Three-dimensional unsteady Euler equations solutions STRUCTURAL ANALYSIS p 5 A87-11487 on dynamic grids Tension analysis of stiffened aircraft structures Numerical simulation of viscous supersonic flow over [AD-A168041] p 51 N87-11128 p 44 A67-10516 a generic fighter configuration p 6 A87-11509 SPOILERS CSAINASTRAN - A general purpose program for Experiences with an unfactcfed implicit Results of wind tunnel tests on external combustion structural analysis p 56 A87-10879 predictor-corrector method p 47 A87-11522 [ ESA-TT-9591 p 42 N87-10990 Guidebook for analysis of tether applications Numerical experiment with inviscid vortex-stretchedflow STABILITY [NASA-CR-178904] p 36 N87-10169 around a cranked delta wing. supersonic speed Acta Aeronautica et Astronautica Sinica (selected The 30 inelastic analysis methods for hot section p 7 A67-11537 articles) components p 53 N87-11206 On the Occurrence of regular reflection of shocks in [ AD-A16791 81 p3 N87-10004 Constitutive modeling for isotropic materials concave corner flows p 10 A87-12566 STABILITY AUGMENTATION p53 N87-11211 Similanty law for the supersonic flow past flat surfaces Fault tolerant control laws STRUCTURAL DESIGN with intense distributed injection p 10 A87-12843 [ NASA-CR-1780941 p 50 N87-10400 Structural design with new materials Acta Aeronautica et Astronautica Sinica (selected STABILITY DERIVATIVES p 49 A87-13011 articles) Further development of the influence function method In-flight total forces, moments and static aeroelastic [AD-A167918] p 3 N67-10004 for store aerodynamic analysis p4 A87-10523 characteristics of an oblique-wing research airplane Supersonic flow around tip sides of wings STABILIZERS (FLUID DYNAMICS) [ NASA-TP-22241 p 36 N87-10103 p 12 N67-10033 DC-10 composite vertical stabilizer ground test STRUCTURAL DESIGN CRITERIA Supersonic, nonlinear, attached-flow wing design for program Design and fabrication of the NASA decoupler pylon high lift with experimental validation [ NASA-CR-37151 p 42 N87-10974 for the F-16 aircraft [ NASA-TP-23361 p 12 N87-10042 STANDARDS [ NASA-CR-1723541 p 25 N87-10065 SUPERSONIC INLETS Flight recorders: New US regulations and new Engine-transmission-structural airframe members Larae Derturbation flow field analvsis and simulation for International Civil Aviation Organization (ICAO) compatibility p26 N87-10069 supeknic inlets standards p 32 N87-10093 Helicopter air intake protection systems [NASA-CR-1746761 p 14 N67-10635 Minimum operational performance standards for p27 N87-10073 SUPERSONIC JET FLOW airbcfne ILS glide slope receiving equipment operating Engine-airframe integration for rotorcraft: System On broadband shock associated noise of supersonic within the radio frequency range of 326.6-335.4 MHz specifications and qualification p 27 N87-10074 jets p 58 A87-11768 [RTCA/DO-192] p 21 N87-10853 STRUCTURAL VIBRATION SUPPORTSYSTEMS STATIC ELECTRICITY Mechanics of flow-induced sound and vibration. Volume Operatingand support hazard analysis for self-contained Disturbances brought by atmospheric statics to airborne 1 General concepts and elementary source. Volume 2 - nawgatlon system LSI model 6216A, B and C. group B navigation and communication systems Complex flow-structure interactions --- Book [AD-A169381] p 22 N87-10655 p 20 A87-12678 p 57 A87-10293 SUPPRESSORS STATIC STABILITY A higher order beam element for vibration of beams Free jet feasibility study of a thermal acoustic shield Wind tunnel test of the modified goldschmied model with discontinuities p 46 A87-10896 concept for ASTIVCE application Dual stream nozzles with propulsion and empennage: Analysis of test results Natural frequency analysis of pretwisted plates [NASA-CR-3867] p 59 N87-10752 [ AD-AI 673601 PI3 N67-10045 p 46 A87-10900 SURFACE NAVIGATION Performance and quality flight test textbook. Volume 2 Damping of the vibrations of deformable bodies --- Navigation and environment, Proceedings of the Fifth Flying qualities Russian book p 47 A87-11336 International Congress, Tokyo, Japan, October 1-5. 1985 [AD-AI 681 241 p3 N87-10630 Advances in the vibration monitoring of gears and rolling p 20 A87-12676 STATIC TESTS element bearings p 49 A87-13007 SURFACE REACTIONS Certification problems for composite airplane Effect of static inplane loads and boundary conditions Effects of surface chemistry on hot corrosion life structures p 39 A87-12652 on the flutter of flat rectangular panels p 43 N67-11193 STATISTICAL ANALYSIS [ NAL-TM-ST-86041 p 50 N87-10404 SURFACEROUGHNESSEFFECTS Statistics of wind shear due to nocturnal boundary layer STUDENTS Drag reducing outer-layer devices in rough wall turbulent bt airstreams in North Germany p 56 N87-11461 Graduate engineering research participation in boundary layers p 8 A87-11890 STATORS aeronautics SURFACETEMPERATURE A simulation of rotor-stator interaction using the Euler [NASA-CA-l79798] p3 N87-10828 Method of mendional sections in problems involving a equations and patched grids p 7 A87-11536 SUBSONIC FLOW three-dimensional boundary layer p 4 A87-10609 STEADY FLOW Vortex-stretched flow around a cranked delta wing SURVEYS Numerical experiments with a total variation diminishing p3 A87-10520 comparison of the effectiveness of measures of aircraft (TVD) MacCormack scheme p 6 A87-11526 Computationsof separated subsonic and transonic flow noise exposure by using Social survey data STEADY STATE about airfoils in unsteady motion p 6 A87-11786 p 54 A87-10117 Wind tunnel test of the modified goldschmied model SUBSONIC SPEED Technology review of flight crucial flight control systems with propulsion and empennage: Analysis of test results The prediction of the drag of aerofoils and wings at (applicatm of optical technology) [ AD-A1673601 p 13 N87-10045 high subsonic speeds p9 A87-12266 [NASA-CR-1723321 p 36 N87-10102 SUBJECT INDEX TRANSONIC COMPRESSORS

SWEDEN TENSILE STRENGTH Visualization of three-dimensional forced unsteady

JAS39 Gripen ~ A Swedish solution to a multi-role Tension analysis of stiffened aircraft structuTes separated flow need p 23 A87-11798 p44 A87-10516 [AD-A188939] p 51 N87-11129 SWEPT FORWARD WINGS TERRAIN ANALYSIS THRUST REVERSAL Performance and quality night test textbook. Volume 2 Knovledge-based tactical twain analysis .__ Interferenceeffects of thrust reverwng on horizontal tail Flying qualities autonomous heliter systems p 19 A87-11061 effectiveness of twin-engine fighter aircraft at Mach [AD-A1681241 p3 N87-10830 TETHERING numbers from 0.15 to 0.90 X-29A longitudinal and directional force and moment Guidebook for analysis of tether applications [ NASA-TP-23501 p 36 N87-10870 supplemental transonic wind tunnel test results [ NASA-CR-1789041 p 38 N87-10169 THRUSTVECTORCONTROL [NASA-TM-859091 p28 N87-10861 TETHERLINES Performance and quality flight test textbook. Volume 2: SYNCHRONOUS SATELLITES Guidebook for analysis of tether applications Flying qualities Polar navigation assisted by satellite [NASA-CR-178904] . p 38 N87-10>69 [ AD-A1881241 p3 N87-10830 p20 A87-11663 THERMAL COWTROL COATIHOS Static internal performance of single-expansion-ramp Introduction to modeling of thermal barrier SYNCHROPHASING lie nOZZl0S with thrust-vectoring capability up to 60 deg An experimentalinvesligatin of the interior noise control coatings p43 N87-11195 [NASA-TP-23641 p 15 N87-10839 Thermal barrier coating life prediction model effects of propeller synchrophasing THUNDERSTORMS [NASA-CR-178185] p60 N87-11577 development p 52 N87-11199 Aircraft accident reeport, Delta Air Lines, Inc.. Lockheed SYSTEMS ANALYSIS THERMAL MFFUSIVlTY L-1011-385-1, N726DA. DallasIFort Wwth International QuantiIaIive thermal ditfusivily measurements of A system theoretical based method for module failure Airport. Texas, August 2, 1985 dagnoslk of turbine engines p35 N87-100B5 composites p45 A87-10750 [PB86-910406] p 17 N87-10053 SYSTEMS ENQINEERING THERMAL EXPAWON TIME LAG Alumina-CoCrAIY material as an improved intermediate The system engineering and integration contract- An Long range E-O Reconnaissance System and fliht test overview p6l A87-11804 layer for graded ceramic gas-path sealing in aeroturbine resulls p 28 A87-10933 SYSTEMS INTEGRATION engines p 40 A87-12928 TIME MARCHING THERMAL STABILITY Integration of GPS with other radionavigation systems A pre-processed implicit algorithm for 3D viscous p21 A87-12680 Development of a tcughened bismaleimide resinprepreg compressible flow p6 A87-11510 Engine-Airframe Integration for Rotorcraft for carbon fiber composites p 40 A87-12667 Application of a 2D time-marching Euler code to [AGARDLS-t48] p26 N87-10067 THERMAL STRESSES transonic turbomachinery flow p6 A87-11516 Engine-airframe integration for rotorcraft: System A reinforcing band near the flange of a heated cylindrical TIME SERIES ANALYSIS specifications and qualification p27 N87-10074 casing p 48 A87-12445 Visualization of three-dimensional forced unsteady THERMOMECHANICAL TREATMENT separated flow Superplasticity in aeroengine titanium alloy VT-9 and [ AD-A1689391 p 51 N87-11129 T its modified compositions p 39 A87-12096 TIMING DEVICES THERMOPLASTIC RESINS Ground-based timeguidance algorithm for control of TAIL ASSEMBLIES Properties and processing of fiber-reinforced airplanes in a timemetered air traffic control environment Wind tunnel test of the modified goldschmied model pdyetherelherketone (PEEK) p 38 A87-11372 A piloted simulation sludy with propulsion and empennage: Analysis of test results THICKENERS [NASA-TP-2816] p34 N87-10864 [AD-A167360] p13 N87-10045 Thickened oils p40 A87-12902 TIP VANES _.I I ..I .-e Effects of tail span and empennage arrangement on inih r-a~a T-"-"n-ha*so.-,.," !iW -..-.,.,..I".;. "." !"r rotQrs. par! 2. drag of a typical wngle-engine fighter aft end Modeling and analysis of !he dynamics of a drill Three-dimensional. unsteady, full-potential calculation [NASA-TP-2352] p 15 N87-10838 penetrating a thin plate [ NASA-TP-23751 p15 N87-10841 Interference effects of thrust reversing on horizontal tail [ASME PAPER 86-WAIAPM-331 p 46 A87-11112 Paramehic analysis of a passive cyclic mtrol device effectiveness of twin-engine fighter aircraft at Mach THKKS for helicopters numbers from 0.15 to 0.90 Polymer systems for rapid sealing of aircrafl structures [NASA-CR-lW] p28 N87-10862 [ NASA-TP-23501 p 36 N87-10870 at low temperature TITANIUM ALLOYS TAIL ROTORS [ADA1676671 p41 N87-10209 Superplasticity in aeroengine titanium alloy VT-9 and Flight service evaluation of composite helicopter THIOPLASTICS its modified compositions p39 A87-12096 components Polymer systems for rapid sealing of aircraft structures Galvanic corrosion between carbon fiber reinforced [NASA-CR-178149] p 41 N87-10182 at low temperature plastics and metallic aeronautical materials TAKEOFF [AD-A167667] p41 N87-10209 [DFVLR-FB-86-16] p 42 N87-11003 Guidance strategies for nearoptimum take-off THREE DIMENSIONAL BODIES TOLERANCES (MECHANICS) performance in a windshear p 24 A87-12138 Acta Aeronautica et Astronautica Sinica (selected Stochastic crack propagation with applicatons to TAPE RECORDERS articles) durability and damage tolerawe analyses The Fairchild CVDR: A new combination voice and data [AD-A167918] p3 N87-10004 [ AD-A1680401 p 53 N87-11226 recorder --- Cockpit Voice and Data Recorder (CVDR) Viscous wing theory development. Volume 2: TORQUE p33 N87-10095 GRUMWING computer program user's manual Effect of tangential torque on the dynamics of flexible TARGET ACQUISITION [NASA-CR-178157] p 13 N87-10044 rotm Rapid target locator p 18 A87-10944 THREE DIMENSIONAL BOUNDARY LAYER [ASME PAPER 86-WA/APM-23] p 46 A87-11113 TECHNOLOGICAL FORECASTING Method of meridional &ns in problems involving a TRACKING (POSITION) Aircraft Integrated Data Systems (AIDS): Evolution and three-dimensionalboundary layer p 4 A87-10609 The methodology and twla for processing radar data revolution p30 N87-10077 Calculation of boundary layer of a three dimensional p 19 A87-11882 Air Force technics! objective document !iscaI year S-shaped inlet p 6 A87-11495 Signal processing and interpretation using multilevel 1987 Experimental investigations of three-dimensional signal abstractions [ AD-A1673241 p 62 N87-10779 laminar boundary layers on a slender delta wing [ AD-A1691661 p 57 N87-11513 TECHNOLOGY ASSESSMENT p9 A87-12145 TRAILING EDGE FLAPS Scientific problems of aviation and space: History and A laminar boundary layer method for flows in planes Manufacture of bonded composite assemblies for present slate --- Russian book p 62 A87-11339 of symmelry and application to inclined ellipsoids of aircraft p 1 A87-13005 CFD -A user's technology assessment --- for propulsion revolution p9 A87-12146 Stress analysis of Pathfinder-2 models :-I- :-- --A -:.^-..I. .."-:"A "'L'y'a.,""---. a,," "I,*,",. -...*...- ..."._.." .._.. Numerical solution of the Bdimensional boundary layer INASA-CR-1724581 p 51 N87-11179 p 23 A87-11781 equations in the inverse mode using finite differences TRAILING EDGES p 11 N87-10005 The system engineering and integration contract ~ An Viscous wing theory development. Volume 1: Analysis, overview p61 A87-11804 THREE DIMENSIONAL FLOW method and results A review of advanced turboprop transport activity Unsteady aerodynamic modeling of a fighter wing in [ NASA-CR-1781561 p12 N87-10043 p 24 A87-12650 transonic flow p3 A87-10517 TRAINING EVALUATION Technology review of flight crucial flight control systems Numerical simulation of viscous supersonic flow over Low-cost avionics simulation for aircrew training (application of optical technology) a generic fighter configuration p6 A87-11509 [ AD-A1691981 p34 N87-10865 [NASA-CR-172332] p 36 N87-10102 A pre-processed implicit algorithm for 30 viscous TRAJECTORY OPTIMIZATION Aeronautical facilities assessment compressible flow p6 A87-11510 Optimal flight paths through microburst wind profiles [NASA-RP-11461 p 37 N87-10876 Finite element computations for high speed 30 inviscid p 35 A87-10519 TECHNOLOGY TRANSFER flows p 7 A87-11542 Maneuver optimization in the case of combat aircrafl Aeronautical research spin-offs on the development of A SUNey of composite grid generation for general p 35 A87-11389 CMl applications for aluminium alloys p 48 A87-11792 three-dimensional regions p 56 A87-11779 Guidance strategies for near-optimum take-off TECHNOLOGY UTILIZATION A quasi-three-dimensional method for diagonal flow performance in a windshear p 24 A87-12138 107 ,*nrr, ^' .la*ilm""in"., minim,,m.time Influence of engine variables on future helicopter ians -c ..II ,.-. L"asJ, -----..---."'""'aY~"'"'..", " -...,-.. ".-.. ". systems p27 N87-10072 Study of three-dimensional separation on a spheroid at intercept p27 N87-10858 Modern Aircraft Integrated Data Systems (AIDS) incidence p49 N87-10016 TRANSMISSIONS (MACHINE ELEMENTS] technology exemplified on the A-320 p 30 N87-10078 Images of three dimensional flows in computer Analysis of the vibration of the input bevel pinion in RAN The impact of flight data on an airline: A case study graphics p57 N87-10017 Wessex helicopter main rotor gearbox WAK143 prior to p 32 N87-10088 Application of a potential code to general steady flows failure TEMPERATURE EFFECTS in three dimensions p 50 N87-10262 [ARL-AERO-PROP-R-169] p25 N87-10061 The effects of temperalure and loading rate on Rcurves Efficiency of various control surfaces in steady and Testing of UH-GOA helicopter transmission in NASA using the CLWL techniques -- crack grow resistance unsteady flow Lewis 2240-kW (3000-hp) facility curve (R curve); crack line wedge load (CLWL) [SNIAS-861-111-101] p 37 N87-10872 [ NASA-TP-26261 p50 N87-10391 [BAE-MSM-R-GEN-0544] p 50 N87-I0405 Three-dimensionalunsteady Euler equations solutions TRANSONIC COMPRESSORS TEMPERATURE MEASUREMENT on dynamic grids Natural frequency analysis of compressor rotor blades NASA dilution jet mixing, phase 3 p 53 N87-11202 [AD-A1680411 p 51 N87-11128 p 34 A87-10899

A-19 SUBJECT INDEX

TRANSONIC FLOW Constitutive modeling lor isotropic materials Visualization of three-dimensional forced unsteady Unsteady aerodynamic modeling of a fighter wing in p 53 N87-11211 separated flow transonic flow p3 A87-10517 TURBINE WHEELS [ AD-A168939 1 p 51 N87-11129 Unsteady transonics of a wing with tip store Specificationof gas turbine disc forgings p4 A87-10524 p 44 A87-10121 Application of a 2D time-marching Euler Code to Manufactunng technology for nondestructive evaluation U transonic turbomachinery flow p6 A87-11516 (NDE) system to implement retirement for cause (RFC) ULTRASONIC FLAW DETECTION Efficient numerical method for transonic flow procedures for gas turbine engine Components Computenzed ultrasonic test inspection enhancement slmulations p 6 A87-11528 p 44 A87-10727 system for aircraft components p 44 A87-10721 Numerical solution of the Euler equations using rational TURBOFAN ENGINES Runge-Kutta method p 7 A87-11538 Manufacturing technology for nondestructiveevaluation Condition monitoring of large commercial turbofan (NDE) system to implement retirement for cause (RFC) Computations of separated subsonic and transonic flow engines p 34 A87-13008 about airfoils in unsteady motion p 8 A87-11786 procedures for gas turbine engine components Acta Aeronautica et Astronautica Sinica (selected Experimental investigation on the performances of a p 44 A87-10727 articles) transonic turbine blade cascade for varying incidence Evaluation of captured water column technology for [ AD-AI 679181 p3 N87-10004 angles p9 A87-12205 advanced ultrasonic sizing techniques An exact integral (field panel) method for the calculation Coolant passage heat transfer with rotation, a progress p 45 A87-10728 of two-dimensional transonic potential flow around report p 53 N87-11225 RFC automated inspection overview --- eddy current and complex configurations p9 A87-I2267 TURBOJET ENGINE CONTROL ultrasonic testing of gas turbine engine parts Unsteady drag over cylinders and aerofoils in transonic Future aero-engine control systems, why FADEC? Cost, p 45 A87-10730 shock tube flows p 10 A87-12617 design cycle timescale. reliability, weight and size targets Variations in ultrasonic backscatter attributed to Transonic cascade flow solved by shock-capture --- Full Authority Digital Electronic Control (FADEC) porosity p 45 A87-10768 computationfollowed by separate-regioncomputation with [PNR-902981 p 35 N87-10867 How to maintain a consistent quality in your bonding shock fitting p 10 A87-12956 TURBOMACHINE BLADES process? p 48 A87-12656 Viscous wing theory development. Volume 1: Analysis, Forging of blades for gas turbines p 44 A87-10124 ULTRASONIC SCANNERS method and results Development of a turbomachinery design optimization A computer-aided nondestructiveinspection system [ NASA-CR-I781 561 p 12 N87-10043 . procedure using a multiple-parameter nonlinear p 44 A87-10720 Viscous wing theory development, Volume 2: perturbation method UNIFORM FLOW GRUMWING computer program user's manual [ NASA-CR-38311 p2 N87-10003 Numerical and experimental study of dynamics of [NASA-CR-178157] p 13 N87-10044 TURBOMACHINERY two-dimensional body Transonic flow analysis for rotors. Part 2: A pre-processed implicit algorithm for 3D viscous [ISAS-619] p 59 N87-10748 Three-dimensional, unsteady, full-potentialcalculation compressible flow p6 A87-11510 UNITED STATES [ NASA-TP-23751 p 15 N87-10841 Application of a 2D time-marching Euler code to Aeronautics and space report of the President Euler flow solutions for a transonic wind tunnel Section transonic turbomachinery flow p6 A87-11516 [ NASA-TM-892391 p 62 N87-10827 [CWI-NM-R8601] p 16 N87-10847 UNIVERSITIES TRANSONIC SPEED The halance between theoretical, computational and Graduate engineering research participation in Effects of tail span and empennage arrangement on experimental work in turbomachines p 49 A87-13015 aeronautics drag of a typical single-engine fighter aft end TURBOPROP AIRCRAFT [ NASA-CR-I79798 I p3 N87-10828 [ NASA-TP-23521 p 15 N87-10838 A review of advanced turboprop transport activity TRANSONIC WINO TUNNELS p 24 A87-12650 UNSTEADY FLOW Euler flow solutions for a transonic wind tunnel section How lo maintain a consistent quality in your bonding Unsteady transonics of a wing with tip store [CWI-NM-R8601] p 16 N87-10847 process? p 48 A87-12656 p4 A87-10524 Computation of transonic separated wing flows using TURBULENCE METERS Calculation of unsteady supersonic flow past a plane an EulerlNavier Stokes zonal approach A nonperturbing boundary-layer transition detection blade row under the effect of vortex inhomogeneities in p 16 N87-10849 p 46 A87-10971 the oncoming flow p5 A87-10618 X-29A longitudinal and directional force and moment TURBULENTBOUNDARYLAYER Implicit and semi-implicit methods for the compressible supplemental transonic wind tunnel test results A nonperturbing boundary-layer transition detection Navier-Stokes equations p 47 A87-11503 [ NASA-TM-859091 p 28 N87-10861 p 46 A87-10971 Computations of separated subsonic and transonic flow TRANSPORT AIRCRAFT Drag reducing outer-layer devices in rough wall turbulent about airfoils in unsteady motion p 8 A87-11786 Aerodynamic anomalies - Can CFD prevent or correct boundary layers p 8 A87-I 1890 Unsteady drag over cylinders and aerofoils in transonic them? --- Computational Fluid Dynamics for transport VISCOUSwing theory development. Volume 1. Analysis, shock tube flows p 10 A87-12617 aircraft design p4 A87-10521 method and results Analysis of two-dimensional incompressible flow past A review of advanced tuhprop transport activity [NASA-CR-178156] p 12 N87-10043 airfoils using unsteady Navier-Stokes equations p 24 A87-12650 TURBULENT FLOW [ NASA-CR-1798231 p 12 N87-10040 The evolution of air transport aircraft flight deck Computation of turbulent supersonic flows around Unsteady flow over an airfoil inside a wind tunnel with p 30 A87-12688 pointed bodies having crossflow separation and without transpiration p 13 N87-10051 Laminar flow control for transport aircraft applications p 5 A87-11487 Application of a potential code to general steady flows p 24 A87-13021 Numerical simulation of viscous supersonic flow over in three dimensions p 50 N87-10262 Crashworthiness experiment summary full-scale a generic fighter configuration p 6 A87-11509 transport controlled impact demonstration program Numerical solution of the 3-dimensional boundary layer Efficiency of various control surfaces in steady and [ DOT/FAA/CT-85/20] p 17 N87-10055 equations in the inverse mode using finite differences unsteady flow [SNIAS-861-111-101] p 37 N87-10872 Operating and support hazard analysis for self-contained p 11 N87-10005 navigation system LSI model 6216A. B and C. group B A description of a turbulent flow past a circular cylinder Three-dimensional unsteady Euler equations solutions [AD-A169381] p 22 N87-10855 by a discrete vortex method p 11 N87-10014 on dynamic grids TURBINE BLADES Report of the InternationalSymposium on Computational [AD-A168041] p 51 N87-11128 Expenmental investigation on the performances of a Fluid Dynamics. Tokyo p 49 N87-10029 USER MANUALS (COMPUTER PROGRAMS) transonic turbine blade cascade for varying incidence Unsteady flow over an airfoil inside a wind tunnel with Viscous wing theory development. Volume 2: angles p9 A87-12205 and wthout transpiration p 13 N87-10051 GRUMWING computer program user's manual An experimental study on large negative incidence TURBULENT WAKES [NASA-CR-178157] p 13 N87-10044 separated flow in two-dimensionalturbine cascades On the large-scale structures in two-dimensional, USER REQUIREMENTS p 10 A87-12957 small-deficit. turbulent wakes p 8 A87-12052 Engine-airframe integration for rotorcraft: Component Development of heat flux sensors in turbine airfoils A description of a turbulent flow past a circular cylinder specifications and qualification p 26 N87-10071 p 52 N87-11186 by a discrete vortex method pll N87-10014 Helicopter air intake protection systems Coolant passage heat transfer with rotation, a progress TWISTING p 27 N87-10073 report p 53 N87-11225 Natural frequency analysis of pretwisted plates Engine-airframe integration for rotorcraft: System TURBINE ENGINES p 46 A87-10900 specificationsand qualification p 27 N87-10074 Alumina-CoCrAIY material as an improved intermediate TWO DIMENSIONAL BODIES layer for graded ceramic gas-path sealing in aeroturbine A-310 Aircraft Integrated Data Systems (AIDS) design Numerical and experimental study of dynamics of philosophy p 30 N87-10076 engines p 40 A87-12928 two-dimensional body Turbine Engine Hot Section Technology, 1984 [ISAS-619] p 59 N87-10748 [NASA-CP-2339] p 52 N87-I1180 TWO DIMENSIONAL FLOW Combustion overview p 43 N87-I 1181 Application of a 2D time-marching Euler code to v Fatigue and fracture: Overview p 52 N87-11183 transonic turbomachinery flow p6 A87-11516 Efficient numerical method for transonic flow VACUUM Host turbine heat transfer ovefview Density field of a viscous gas jet issuing from a conical simulations p6 A87-11528 p 52 N87-11184 nozzle into vacuum p4 A87-10603 Calculation of strong viscouslinviscid interactions on Laser anemometers of hot-section applications VANELESS DIFFUSERS p 52 N87-11187 airfoils by zonal solutions of the Navier-Stokes equations p 7 A87-11540 A study on the axially curved mixed-flow vaneless Effects of surface chemistry on hot corrosion life On the large-scale structures in two-dimensional, diffusers p 47 A87-11481 p 43 N87-11193 small-deficit,turbulent wakes p8 A87-12052 VARIABLE SWEEP WINGS Introduction to life modeling of thermal barrier An exact integral (field panel) method for the calculation Flight-determined aerodynamic derivatives of the AD-I coatings p 43 N87-11195 of two-dimensional transonic potential flow around oblique-wing research airplane Thermal barrier coating life prediction model complex configurations p 9 A87-12267 [ NASA-TP-22221 p 36 N87-10871 development p 52 N87-11199 An experimental study on large negative incidence VARIATIONAL PRINCIPLES The 3D inelastic analysis methods for hot section separated flow in two-dimensional turbine cascades Numencal experiments with a total variation diminishing components p 53 N87-11206 p 10 A87-12957 WD) MacCormack scheme p6 A87-11526 SUBJECT INDEX WING PROFILES

VECTORS (MATHEMATICS) Quantitative study of shock-generated compressible Guidance strategies lor near-optimum take-off Three-dimensional unsteady Euler equations solutions vortex flows p 10 A87-12616 performance in a windshear p 24 A87-12138 on dynamic grids Analysis of the vortical flow around a 60 deg Delta wing Monitoring of terminal flight phases environment [AD-A168041] p 51 N87-11128 with vortex flap p 11 N87-10006 Observations and models p 55 A87-12679 VERTICAL LANDING Viscous wing theory development Volume 1 Analyss. Aircraft accident reeport. Delta Air Lines. Inc.. Lockheed Yakovlev Forger _-- history of the Yak-38 Soviet Very method and results L-1011-385-1, N726DA. Dallas/Fort Worth International Short Takaand Landing aircraft. p 22 A87-10575 [NASA-CR-178156] p12 N87-10043 Airport, Texas, August 2, 1985 VERTICAL TAKEOFF An expenmental investigation 01 end-wall flowfield of a [PB86-910406] p 17 N87-10053 compressor rotor p 50 N87-10244 Yakovlev Forger ._.history of the Yak-38 Soviet Very Doppler Radar Detection 01 Wind Shear Expenmental and theoretical Doppler-lidar signatures of Short Takaand Landing aircraft. p 22 A87-10575 [ NASA-CP-24351 p 17 N87-10054 VIBRATION DAMPING aircraft wake vortices p 14 N87-10330 VORTICITY EQUATIONS Wind shear measurement on board a MORANE 893 Damping 01 the vibrations of deformable bodies _-_ p31 N87-10086 Russian book p 47 A87-11336 A descnption 01 a turbulent flow past a circular cylinder by a discrete vortex method pll N87-10014 NASA and FAA launch wind shear research project Des@ and fabrication 01 the NASA decoupler pylon VULNERABILITY [NASA-NEWS-REL-86143] p55 N87-10659 for the F-16 aircraft. addendum 2 Vulnerability methodology and protectrve measures for Statistics of wind shear due to nocturnal boundary layer [ NASA-CR-1724941 p 27 N87-10859 aircraft fire and explowon hazards Volume 3 On-Board jet airstreams in North Germany p 56 N87-11461 Design and fabrication of the NASA decoupler pylon Inert Gas Generator System (OBIGGS) studies Part 1 WIND TUNNEL TESTS lor the F-16 aircraft. addendum 1 OBIGGS ground performance tests Theoretical treatment of gust simulation in the wind [ NASA-CR-1723551 p27 N87-10860 [ AD-A1673571 p26 N87-10066 tunnel p9 A87-12148 VIBRATION MEASUREMENT Experimental investigation on the performances of a Advances in the vibration monitoring 01 gears and rolling transonic turbine blade cascade lor varying incidence element bearings p49 A87-13007 W angles p9 A87-12205 Analysis of the vibration of the input bevel pinion in RAN The effect 01 free stream disturbances and control WALL FLOW Wessex helicopter main rotor gearbox WAK143 prior to surface deflections on the performance of the Wortmann Drag reducing outer-layer devices in rough wall turbulent failure airfoil at low Reynolds numbers p 11 N87-10007 boundary layers p 8 A87-11890 [ ARL-AERO-PROP-R-1691 p25 N87-10061 Wind-tunnel investigation of the llight characteristics of Transformation of a plane uniform shock into cylindrical Testing of UH-GOA helicopter transmission in NASA a canard general-aviationairplane Configuration or spherical uniform shock by wall shaping Lewis 2240-kW (3000-hp) facility [ NASA-TP-26231 p 12 N87-10039 p 37 A87-12585 [ NASA-TP-26261 p 50 N87-10391 Unsteady flow over an airfoil inside a wind tunnel with WALL TEMPERATURE VIBRATION MODE and without transpiration p 13 N87-10051 Testing of Fe-Cu-base ablative composites. II Resonant and non-resonant acoustic properties of Design and fabrication 01 the NASA decoupler pylon p 41 A87-12971 elastic panels. I - The radiation problem for the F-16 aircraft WALLS p 49 A87-13026 [ NASA-CR-1723541 p25 N87-10065 An experimental investigation of end-wall flowfield of a VIBRATORY LOADS In-flight total forces, moments and static aeroelastic compressor rotor p 50 N87-10244 Effect of angular inflow on the vibratory response of a charactenstics of an oblique-wing research airplane WARNING SYSTEMS counter-rotating propeller [ NASA-TP-22241 p 36 N87-10103 A redundancy management procedure for fault detection [NASA-CR-174819] p 15 N87-10840 Tunnel interference from pressure measurements on and isolation p 46 A87-11127 VIEWING control surfaces A...^".",-A ',."-.i-..- '^."i. .-....,.,., " ^,^"." r7V.YIIICI.I" IYIII.I.m.1 I", ., Hot section viewing system 011 LlOill.. iri,i/.,a ','.""' [AE-TM-8-83] p 37 N87-10104 p 21 A87-12687 [ NASA-CR-I747731 p 51 N87-11144 An experimentai invesiigarion of dynamic ground NASA and FAA launch wind shear research project VISCOSITY effect p 14 N87-10833 [ NASA-NEWS-REL-86-143] p 55 N87-10659 Thickened oils p 40 A87-12902 X-29A longitudinal and directional force and moment WATER DEPTH VISCOUS FLOW supplemental transonic wind tunnel test results Laser %-ne depth sounding in Australia Optimal control of viscous flow at high Reynolds [NASA-TM-85909] p 28 N87-10861 p A87-12677 numbers p 5 A87-10620 30 Interference effects 01 thNSt reversing on horizontal tail WATER IMMERSION Implicit and semi-implicit methods for the compressible effectiveness of twin-engine fighter aircraft at Mach Evaluation of captured water column technology for Navier-Stokesequations p 47 A87-11503 numbers from 0.15 to 0.90 advanced ultrasonic sizing techniques Numerical simulation of viscous supersonic flow over [ NASA-TP-23501 p 36 N87-10870 p 45 A87-10728 a generic fighter configuration p 6 A87-11509 Efficiency of various control surfaces in steady and WAVE DRAG A pre-processed implicit algorithm for 3D viscous unsteady flow The possibility of the nondisturbing motion of a body compressible flow p6 A87-11510 [SNIAS-861-111-101] p 37 N87-10872 Calculation of strong viscouslinwscid interactions on in a fluid p 48 A87-12894 Propfan slipstream effects using static simulators: Low airfoils by zonal solutions of the Navier-Stokesequations WAVE GENERATION speed task, phase 1 p7 A87-11540 Analyses of broadband noise mechanisms 01 rotors [ BAE-B59R/R-D/610/13498] p 37 N87-10875 p 58 A67-11769 Finite element computations for high speed 30 inviscid The high speed cascade wind tunnel: Still an important flows p7 A87-11542 WEATHER test facility for investigations on turbomachinery blades Viscous wing theory development. Volume 1: Analysis, The influence of weather-active fronts on visual flight [ DFVLR-MITT-86-11] p 38 N87-10878 conditions p 56 N87-11437 method and results Results of wind tunnel tests on external combustion 1 NASA-CR-1781561 p 12 N87-10043 WEAVING [ESA-T-959] p42 N87-10990 Viscous wing theory development. Volume 2: Automatically woven three-directional composite WIND TUNNEL WALLS structures p 48 A87-11843 GRUMWING computer program user's manual Unsteady flow over an airfoil inside a wind tunnel with iP4ASA-CR-1781571 p 13 N87-10044 WEDGES 3-d without transpiration p13 N87-10051 Unsteady flow over an airfoil inside a wind tunnel with The effects of temperature and loading rate on A-curves Tunnel interference from pressure measurements on and without transpiration p 13 N87-10051 using the CLWL techniques --- crack growth resistance control surfaces VISIBILITY curve (R curve); crack line wedge load (CLWL) [ AE-TM-8-83] p 37 N87-10104 The influence of weather-active fronts on visual flight [ BAE-MSM-R-GEN-05441 p 50 N87-10405 Practical evaluationof wall pressure signature correction conditions p 56 N87-11437 WEIGHT (MASS) methods in the 2.7m x 2.lm low speed wind tunnel VISUAL FLIGHT National Transportation Safety Board safety [ BAE-ARG-2041 p 37 N87-10874 I--_IS _... ., recommendation p 16 N87-10852 lllr *IIII"=lorl Gf nra.,,r,-a.-,,*r llVlIli)..... Gfi .;sua; :;ah; VJ!UD T"UUE1P conditions p 56 N87-11437 WEIGHT REDUCTION Aeronautical facilities assessment VOICE Engine-transmission-structural airframe members [NASA-RP-1146] p 37 N87-10876 The Fairchild CVDR: A new combination voice and data compatibility p26 N87-10069 WIND VELOCITY MEASUREMENT recorder --- Cockpit Voice and Data Recorder (CVDR) lnlluence of engine variables on future helicopter Experimental and theoretical Doppler-lidarsignatures 01 p33 N87-10095 systems p 27 N87-10072 aircraft wake vortices p 14 N87-10330 VORTEXGENERATORS WEST GERMANY WING FLOW METHOD TESTS The possibility of the nondisturbing motion of a body Statistics of wind shear due to nocturnal boundary layer Experimental investigations of three-dimensional in a fluid p 48 A87-12894 jet airstreams in North Germany p 56 N87-11461 laminar boundary layers on a slender delta wing VORTEX SHEDDING WIND (METEOROLOGY) p9 A87-12145 Calculation of unsteady supersonic flow past a plane Surface measurements 01 gust fronts and microbursts WING OSCILLATIONS blade row under the effect of vortex inhomogeneities in during the JAWS (Joint Airport Weather Studies) Project: Unsteady airload computations lor airfoils oscillating in the oncoming flow p5 A87-10618 Statistical results and implicationsfor wind shear detection. attached and separated compressible flow Vortex shedding 01 a square cylinder in front of a slender prediction and modeling [ NLR-MP-85040-U] p 16 N87-10846 airfoil at high Reynolds numbers. Part 1: Spacing effect ...... [ PB86-2008471 - ..-.^.."-..-.*- p55 N87-10665 WING PLANFORMS [MPIS-23/1985] p 13 N87-10048 ninu mCRaun=m=m I COmputation of transonic separated wing flows using VORTEX STREETS Wind shear measurement on board a MORANE 893 an EulerINavier Stokes zonal approach p 31 N87-10086 Euler equations analysis of the initial roll-up of aircraft p 16 N87-10849 wakes p4 A87-10522 The C and Ku band scanerometer results from Canadian WING PROFILES VORTICES participation in the ESA PAOMESS ocean measurement Unsteady aerodynamic modeling of a fighter wing in Vortex-stretched flow around a cranked delta wing campaign p 55 N87-11252 transonic flow p3 A87-10517 p3 A87-10520 WIND SHEAR Conical wing 01 maximum lift-to-dragratio in a supersonic Vortex simulation of propagating stall in a linear cascade Optimal flight paths through microburst wind profiles gas flow p4 A87-10615 01 airfoils p5 A87-11117 p 35 A87-10519 Mathematical modeling of separated flow past a wing Numerical experiment with inviscid vortex-stretched flow The classification of wind shears from the point of view profile and aerodynamic hysteresis p 5 A87-10619 around a cranked delta wing, supersonic speed 01 aerodynamics and flight mechanics The possibility of the nondisturbing motion of a body p 7 A87-11537 p 24 A87-11898 in a fluid p 48 A87-12894

A-2 1 WING ROOTS SUBJECT INDEX

WING ROOTS Critical composite joint subcomponents: Analysis and test results [ NASA-CR-37111 p 42 N87-10975 WlNG TIP VORTICES Visualization of three-dimensional forced unsteady separated flow [ADA1689391 p51 N87-I1129 WING TIPS Unsteady transonics of a wing with tip store p4 A87-10524 Suoersonic flow around ti0 sides of winas p i2 N87-10033 WINMUSEUGE STORES Desian and fabrication ot the NASA decoupler pylon tor thef-16 aircran [ NASA-CR-1723541 p25 N87-10065 Design and fabrication of the NASA decoupler pylon tor the F-16 aircratl. addendum 1 [ NASA-CR-1723551 p27 N87-10860 WINGS Euler solutions on 0-0grids around wings using local refinement p6 A87-11512 The prediction of the drag ot aerofoils and wings at high subsonic speeds p 9 A87-12266 Induced drag ot a curved wing p 10 A87-12805 Acta Aeronautica et Astronautica Sinica (selected articles) [AD-A1679181 p3 N87-10004 A study of the llow field about an upper surface blown wing and its effects on longitudinal static stability ot a small jet airplane p 11 N87-10009 Viscous wing theory development. Volume 1: Analysis, method and results [NASA-CR-178156] p12 N87-10043 Viscws wing theory development. Volume 2

I GRUMWING computer program user's manual [ NASA-CR-1781571 p13 N87-10044 Visualization of three-dimensional forced unsteady separated flow [AD-At68939] p5t N87-11129 X X-10 AIRCRAFT X-29A longitudinal and directonal force and moment supplemental transonic mnd tunnel test results [NASA-TM-85909] p 28 N87-10861 Y YIELD POINT Relevance of short fatigue crack growth data for I durability and damage tolerance analyses ot aircraft [FFA-TN-1986-23] p54 N87-11231 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 210) February 1987

Typical Personal Author Index Listing

PERSONAL AUTHOR ALVAREZ, D. BEDARD. A. J. The methodology and tools lor processing radar data Surface measurements of gust fronts and microbursts p19 A87 11662 during the JAWS (Joint Airport Weather Studies) Project- ANDERS, G. Statistical results and implicationstor wind shear detectton. BERNER. W. E. Efficiency Of various control surfaces in steady and prediction and modeling Au Force technical objective document fiscal year unsteady flow IPB86-200847 I p 55 N87-10665 IT987 [SNIAS-861 111 101 I p37 N87 10872 BEISSNER. R. E. [AD-A167324] p 62 N87-10779 ANDERSON. E. M. Predictive models and reliability improvement in Expert systems for aiding combat pilots electromagnetic nondestructive evaluation p29 A87 12212 p 45 A87-10732 BELK, D. ANDERSON. C. L. M. Three-dimensional unsteady Euler equations solutions Vulnerability methodology and protective measures for aircraft fire and explosion hazards Volume 3 On-Board on dynamic grrds AD-A168041 p51 N87-11128 Inert Gas Generator System (OBIGGS) studies Part 1 I I OBIGGS ground performance tests BELOGLAZOV. 1. N. I I AD A167357 I p 26 N87 10066 Fundamentals 01 navigation according to geophysical fields p 19 A87-11337 ARIARATNAM. S. 1. BELOTSERKOVSKII. S. Non-linear stability analysis of aircraft at high angles M. Mathematical modeling of separated flow past a wing Listings in this index are arranged alphabetically by of anack p 36 A87 12082 profile and aerodynamic hysteresis p 5 A87-10619 ARTHEV. R. P personal author The title of the document provides BENN. G. S. L. Cost eflective single crystals Data recovery techniques. an update the user with a brief description of the subject IPNR 903191 p60 N87 11615 p 32 N87-10089 matter The report number helps lo indicate the Development 01 single crystal alloys lor specific engine BENNING. M. A. type of document listed (eg , NASA report, applications Flammabilily and sensitivity of materials in I ~hp903331 -En L4rn ..e.,. rransiarion. NASA contractor repon) The page and VU" a""/ I i"," oxygen-enricned atmospheres. Proceedings ot the ASHLEY, J. D. Symposium. 'JYasimgion. X, April 23, 24. i985 Volume accession numbers are located beneath and to the Global positioning system applications 2 p 38 A87-10859 right of the title Under any one authors name the p 18 A87 10047 BENVENUTO. G. accession numbers are arranged in sequence with ATKINSON. W. H. Experimental investigation on the performances 01 a transonic turbine blade cascade for varying incidence the AlAA accession numbers appearing first Development 01 heat flux sensors in turbine airfoils p52 N87 11186 angles p9 A87-12205 AWAI. T BERGER, E. A study on the axially curved mixed flow vaneless Maneuver optimization in the case of combat aircraft diffusers D 47 A87 11481 p 35 A87-11369 A BERGGREN, J. 1. Single or dual pod concepts for tactical ABBOT. R. H. B reconnaissance p 29 A87-10939 Laser airborne depth sounding in Australia BERNARD. R. p30 A8712677 BAILEY, R Data processing and calibration for an airborne ABU-ASSAF. H. A. High temperature static strain gage program scatterometer p 30 A87-12694 BERNER, W. E. The lateral dynamic stability and control of a large p 52 N87 11188 receiver aircraft during air-to air refuelling Air Force technical oblective document Iisca'l year BAKER.* A p 36 A87-12268 1987 Composite materials lor aircralt structures ADAMS. J. C., JR. [AD-A167324 I p 62 N87-10779 p38 A8710294 Large perturbation flow field analysis and simulation for BERRIER, E. L. supersonic inlets Advanced fibre composiles and other new materials lor Effects of tail span and empennage arrangement on 1 NASA-CR-1746761 p14 N87 10835 airframe applications p41 A87 13010 drag 01 a typical singleengine fighter aft end ADAMS. J. V. BALAKRISHNA. S ! NASA-TP.2352 1 p 15 N87-10838 Summary of artificial and natural icing tests conducted Elfects of llap position on longitudinal parameters of Static internal performance of single-expansion-ramp on US Army aircraft from 1974 to 1985 HFB 320 nozzles with thrust-vectoring capability up to 60 deg IFAA/CT-85/261 p 25 N87-10064 I NAL TM-SE 8602 I p25 N87 10062 I NASA-TP-2364 1 p 15 N87-10839 ADAYS. R. D. BALASUBRAMANIAN. 1. S BERSHADER, D. Nondestructive inspection 01 composite structures by A higher order beam element lor vibration of beams Quantitative study 01 shock-generated compressible low-velocity impact p 45 A87 10765 with discontinuities p 46 A87 10898 vortex flows p 10 A87-12616 ADDISON, R. C.. JR. RAllARn I F) RHIITIANI, P K A computer-aided nondestructive inspection system Impact of IPS and IRS configurations on engine Free-let acoustic investigation of high-radius-ratio p 44 A87-10720 installation design p 26 N87-10070 coannular plug nozzles AGRAWAL, S. K. BANDVOPADHVAV, P R I NASA-CR-3818I p 59 N87-10753 Braking performance of aircraft tires Drag reducingouter layer devices in rough wall turbulent BIESIADNY. 1. J. p 24 A87-12649 boundary layers p 8 A87 11890 Response of a small-turboshaft-enginecompression system to inlet temperature distortion AKHMEDOV. A. 1. BARBRV. H I NASA-TM-83765I p 35 N87-10100 Thickened oils p 40 A87-12902 Translormation of a plane uniform shock into cylindrical AK1VAMA.S. or spherical unilorm shock by wall shaping BILLARD. B. Images of three dimensional flows in computer p37 A87 12585 Laser airborne depth sounding in Australia p 30 A87-12677 graphics p 57 N87-10017 BARREAU, R. BILLMANN. E. R. ALCORN. J. C. Efficiency of various control surfaces in steady and Helicopter MLS Flight Inspection Project Radio Technical Commission for Aeronautics. Annual unsteady flow DOT/FAA/CT-86/14 p2 N87-10002 Assembly Meeting and Technical Symposium. I I ISNIAS861 111 1011 p 37 N87 10872 BIRLA, N. C. Washington. DC. November 19 21. 1985 Proceedinqs RARTF_l_X. Superpiasliciry in aeroengine titanium alloy V I -Y and p 1 A87 11801 Progress in advanced materials and processes its modified compositions p 39 A87-12096 ALI, K. A. M. Durability reliability and quality control Proceedings of the BIRRING, A. S. The lateral dynamic stability and control 01 a large Sixth International European SAMPE Conference Electromagnetic methods to detect corrosion in aircralt receiver aircraft during air to-air reluelling Scheveningen hetherlands May 28 30 1985 structures p 45 A87-10791 p 36 A87-12268 p39 A87 12651 BIRX. D. L. ALLEN, A. M. BAUDIN, F Manufacturingtechnology for nondestructive evaluation Nondestructive inspection of composite structures by Data processing and calibration lor an airborne (NDE) system to implement retlrement lor cause (RFC) low-velocity impact p 45 A87 10765 scatterometer p 30 A87 12694 procedures lor gas turbine engine components ALLEN, D. BECKElT,R C. p 44 A87-10727 Technical diagnosis by automated reasoning Computer inlegrated manulacturinq BISBEE. J. P 57 A87-12217 D 49 A87 13003 Rapid large1 locator p 18 A87-10944

B- 1 BLACKFORD, R. W. PERSONAL AUTHOR INDEX

BLACKFORD. R. W. BROWNE, J. CARLSSON, L Improved durability airline paint schemes Development of a toughened bismaleimideresin prepreg Decay of end effects in graphitelepoxy bolted joints p40 A87-12660 for carbon fiber composites p40 A87-12667 p 44 A87-10115 BLAIR, Y. BRUMBACK, B. D. CARROLL, J. A. Development of a toughened bismaleimideresin prepreg A decentralized fault-tolerant approach to estimation in Guidebook for analysis of tether applications for carbon fiber composites p40 A87-12667 multi-sensor navigation systems p 21 N87-10057 [NASA-CR-178904] p 38 N87-10169 BLAIR. Y. F. BRUNO, P. S. CASTIES, J. Measurement of airfoil heat transfer coefficients on a Automatically woven three-directional composite The evolution of air transport aircraft flight deck structures p 48 A87-11843 turbirw stage p 53 N87-11221 p 30 A87-12688 BRUTIAN, M. A. BLAKE. W. K. CASU, 0. Optimal control of viscous flow at high Reynolds Mechanics of flow-induced sound and vibration. Volume Monitoring of terminal flight phases environment 1 General concepts and elementary source. Volume 2 numbers p 5 A87-10620 . Observations and models p 55 A87-12679 Complex flow-structure interactions p 57 A87-10293 BRYANSTONCROSS, P. J. BLANCHARD, A. High speed flow visualisation p 48 A87-12648 CAWLEY, P. Report on tests of a CAST 10 airfoil with fixed transition BUCKLEY, E. C. Nondestructive inspection of composite structures by in the T2 transonic cryogenic wind tunnel with self-adaptwe Technology review of flight crucial flight control systems low-velocity impact p 45 A87-10765 walls (application of optical technology) CEBECI, T. [RT-OA-63/1685] p 14 N87-10834 [NASA-CR-172332] p 36 N87-10102 Numerical and physical aspects of aerodynamic flows BLOY, A. F. BUHL, H. 111; Proceedings of the Third Symposium. California State Relevance of short fatigue crack growth data for Galvanic corrosion between carbon fiber reinforced University. Long Beach, CA. January 21-24. 1985 durability and damage tolerance analyses of aircraft plastics and metallic aeronautical materials p 8 A87-11782 [FFA-TN-1986-23] p54 N87-11231 [DFVLR-FB-86-16] p 42 N87-11003 Calculation methods for aerodynamic flows - A review BLOW. 0. BUKOWSKI. C. F. p 8 A87-11783 Numerical simulation of viscous supersonic flow over Aircraft Integrated Data Systems (AIDS): Evolution and A comparison of interactive boundary-layer and a generic fighter configuration p 6 A87-11509 revolution p30 N87-10077 thin-layer Navier-Stokes procedures p 8 A87-11785 BLOY, A. W. BULLEN, R. B. ’ CENKO, A. The lateral dynamic stability and control of a large Reaction to aircraft noise in residential areas around Further development of the influence function method receiver aircraft dunng air-to-air refuelling Australian airports p 54 A87-10116 for store aerodynamic analysis p4 A87-10523 p 36 A87-12268 Comparison of the effectivenessof measures of aircraft CHAMBERS, H. W. BODENEZ, G. noise exposure by using social survey data Summary of artificial and natural icing tests conducted Polar navigation assisted by satellite p 54 A87-10117 on US Army aircraft from 1974 to 1985 p20 A87-11663 BUNIN. B. L [ FAAICT-85/26] p25 N87-10064 BONDAREV, E. N. Critical joints in large composite aircraft structure CHAMPAGNE, F. Density field of a viscous gas jet issuing from a conical [NASA-CR-37101 p 41 N87-10973 On the large-scale structures in two-dimensional, nozzle into vacuum p4 A87-10603 CXtical composite joint subcomponents: Analysis and smalldeficit. turbulent wakes p8 A87-12052 BONGRAIN, H. test results Disturbancesbrought by atmospheric statics to airborne [ NASA-CR-37111 p 42 N87-10975 CHAMPLIN, N. navigation and communication systems BURGASOV. M. P. Polymer systems for rapid sealing of aircraft structures p 20 A87-12678 Density field of a viscous gas jet issuing from a conical at low temperature BOWERS, A. H. nozzle into vacuum p4 A87-10603 [ AD-A1676671 p 41 N87-10209 X-29A longitudinal and directional force and moment BURKHARDT, 0. CHANG. 1. C. supplemental transonic wind tunnel test results Electromagneticmethods to detect corrosion in aircraft Transonic flow analysis for rotors. Part 2: [ NASA-TM-859091 p 28 N87-10861 structures p 45 A87-10791 Threedimensional. unsteady, full-potential calculation BRAISTED, P. BURLEY. J. R., II (NASA-TP-23751 p 15 N87-10841 Combined utilization of Loran and GPS - The best from Effects of tail span and empennage arrangement on CHANG, K. C. each system p20 A87-11664 drag of a typical single-enginefighter aft end A cornparison of interactive boundary-layer and BRAUSCH, J. F. [ NASA-TP-23521 p 15 N87-10838 thin-layer Navier-Stokesprocedures p 8 A87-11785 Free jet feasibility study of a thermal acoustic shield BURRIS, D. 0. CHANG. R. C. concept for ASTIVCE application: Dual stream nozzles Operational usage of the KS-147A (LOROP) in the An experimental investigation of dynamic ground [ NASA-CR-38671 p 59 N87-10752 RF-BE p 29 A87-10936 effect p 14 N87-10833 BRAYBROOK, R. BUTENKO, K. K. CHANTRY. J. A. Yakovlev Forger p 22 A87-10575 Calculation of unsteady supersonic flow past a plane Engine performance monitoring for airlines BREEYAN, J. H. blade row under the effect of vortex inhomogeneities in [PNR-903051 p35 N87-10868 Correlation between flight simulation and pfocessing of the oncoming flow p5 A87-10618 CHAUMETTE, 0. flight tests based on inertial measurements Certification problems for composite airplane [ NLR-MP-85058-UI p 28 N87-10863 structures p 39 A87-12652 BREIL, J. F. C CHAUSSEE, D. S. Report on tests of a CAST 10 airfoil with fixed transition Numerical simulation of viscous supersonic flow over in the T2 transonic cryogenic wind tunnel with self-adaptive CABRIT, P. a generic fighter configuration p6 A87-11509 walls Helicopter air intake protection systems CHEN, A. W. [RT-OA-63/1685] p 14 N87-10834 p 27 N87-10073 CFD applications to enginelairframeintegration BRENDEL, M. CAGLE, K. S. p 23 A87-11780 Experimental study of the boundary layer on a low The role of choice of law in determining damages for CHEN, P. C. Reynolds number airfoil in steady and unsteady flow international aviation accidents p 81 A87-10508 The 3D inelastic analysis methods for hot section p 14 N87-10052 CAHILL, P. components p 53 N87-11206 BRENTNER, K. S. An investigation of the FAA vertical Bunsen burner CHEN, S. Prediction of helicopter rotor discrete frequency noise: flammability test method Acta Aeronautica et Astronautica Sinica (selected A computer program incorporating realistic blade motions [ DOT/FAA/CT-86/22] p 42 N87-10985 articles) and advanced acoustic formulation CAI, Z [ AD-A16791 81 p3 N87-10004 [NASA-TM-87721] p 59 N87-10750 A quasi-three-dimensional method for diagonal flow CHEN, X. BRISTEAU, Y. 0. fans p 11 A87-12958 Acta Aeronautica et Astronautica Sinica (selected Implicit and semi-implicit methods for the compressible CANTWELL, H. F. articles) Navier-Stokes equations p 47 A87-11503 Future aero-engine control systems, why FADEC? Cost. [AD-A167918] p3 N87-10004 BRISTOWE, P. J. D. design cycle timescale. reliability, weight and size targets CHIGIN. G. P. Integrated monitoring systems for tactical aircraft [PNR-90298] p 35 N87-10867 Fundamentals of navigation according to geophysical p 31 N87-10080 fields p 19 A87-11337 BROAD, K. S. CAPONE, F. J. Interference effects of thrust reversing on horizontal tail CHOW, R. R. International Conference - Superplasticity in Aerospace Viscous wing theory development. Volume 1: Analysis, Aluminium effectiveness of twin-engine fighter aircraft at Mach numbers from 0.15 to 0.90 method and results [ BAE-S85/AMR/0066] p 42 N87-10994 [ NASA-CR-1781561 p 12 N87-10043 BROADBENT, E. G. [NASA-TP-2350] p 36 N87-10870 CAPTAIN, J. L Viscous wing theory development. Volume 2: Resonant and non-resonant acoustic properties of GRUMWING computer program user’s manual Reconnaissance and the microprocessor elastic panels. I - The radiation problem [NASA-CR-178157] p 13 N87-10044 p 29 A87-10943 p 49 A87-13026 CHUSHKIN, P. 1. BROWN, G. L CAREL, 0. Computational aerodynamics of supersonic lifting Developments at ARL to meet future Australian needs Interferenceof the aeronauticalnavaids (frequencyband vehicles p 12 N87-10030 in aeronautics p2 A87-13017 108-118 MHz) from F.M broadcasting service (88-108 CLAES, D. BROWN, P. C. MHz) p 21 A87-12690 Efficient numerical method for transonic flow Effect of angular inflow on the vibratory response of a CARLSON, H. W. simulations p 6 A87-11528 counter-rotating propeller Numerical methods and a computer program for CLAPP. R. E. [NASA-CR-174819] p 15 N87-10840 subsonic and supersonic aerodynamic design and analysis Piloting of unmanned air vehicles. II BROWN, P. W. Of wings with attainable thrust considerations p 23 A87-10941 Piloted simulation study of the effects of an automated [NASA-CR-3808] p3 N87-10829 CLAYTON, J. D. trim system on flight characteristics of a light twin-engine CARLSSON. G. Design and fabrication of the NASA decoupler pylon airplane with one engine inoperative How to maintain a consistent quality in your bonding for the F-16 aircraft [NASA-TP-2633] p 16 N87-10843 process? p 48 A87-12656 [ NASA-CR-1723541 p 25 N87-10065 8-2 PERSONAL AUTHOR INDEX GHIA, U.

Design and fabrication of the NASA decoupler pylon DELNORE, V. E. F for the F-16 aircraft, addendum 2 Doppler Radar Detection of Wind Shear 1 NASA-CR-1724941 p 27 N87-10859 [ NASA-CP-24351 p 17 N87-10054 FARASSAT, F. Design and fabrication of the NASA decoupler pylon DEMASI, J. The evolution of methods for noise prediction of hgh for the F-16 aircraft, addendum 1 Thermal barrier coating life prediction model speed rotors and propellers in the time domain INASA-CR-1723551 p27 N87-10860 development p 52 N87-11199 p 58 A87-11770 CLEVER, W. C. DESAI, Y. FEDOROV. R. M. Supersonic second order analysis and optimization A redundancy management procedure for fault detection Mathematical modeling of separated flow past a wing program user's manual and isolation p 46 A87-11127 profile and aerodynamic hysteresis p 5 A87-10619 [NASA-CR-172342] p 15 N87-10842 DESTUYNMR, R. FERNANDES, C. M. P. COE. H. H. Efficiency of various contrd surfaces in steady and Natural frequency analysis of compressor rotor blades Testing of UH-GOA helicopter transmission in NASA unsteady flow p34 A87-10899 Lewis 2240-kW (3000-hp) facility [SNIAS-861-111-101] p 37 N87-10672 Natural frequency analysis of pretwisted plates [ NASA-TP-26261 p50 N87-10391 DEXTER, P. C. p 46 A87-10900 COLE, J. 0. FERRARA, A. M. A bibliography of aerodynamic heating references CSA/NASTRAN ~ A general purpose program for Avgaslautogas cornparison: Winter fuels [BAE-BT-13481] p 14 N87-10832 structural analysis p56 A87-10879 [DOT/FAA-CT-86/21] p 43 N87-11014 COPPS. s. L DIENGER. 0. FILIPPOV, IU. 0. Lufthansa's Aircraft Integrated Data Systems (AIDS) The system engineering and integration contract ~ An Motion of a gas in a duct behind a moving body OVeNhW p 61 A87-11804 based A-310 engine conditionmonitoring system: Progress p5 A87-10675 COX, M. E. achieved between the 12th and 13th AIDS Symposiums FINASHOV, A. F. The air/ground transfer of aircraft integrated data p31 N87-10084 A method for calculating the susceptibility of jet fuels systems (AIDS) for Air Traffic Control (ATC) purposes: DINI, D. to smoking p40 A87-12901 Present experiments and possible future intentions Engine-transmission-structural airframe members FISHELL. W. 0. p32 N87-10091 compatibility p26 N87-10069 Reconnaissance interface - The near real time is now COZZI, R. WOLIN. D. 0. p29 A87-10950 Monitoring of terminal flight phases environment Manufacturingtechnology for nondestructive evaluation FOMIN, M. 0. Observations and models p 55 A87-12679 (NDE) system to implement retirement for cause (RFC) Methods of in-flight aerophysical studies CRIGHTON, D. G. procedures for gas turbine engine components p 23 A87-11343 Nonlinear acoustic propagation of bfoadband noise p 44 A87-10727 FORD, D. A. p 58 A87-11773 DRING, R. P. Development of single crystal alloys for specific engine CROSBY, W. Measurement of airfoil heat transfer coefficients on a applications Sources and observers in motion. IV - Acwstic turbine stage p 53 N87-11221 [PNR-903201 p60 N87-11616 measurements on aerofoils moving in a circle at high DRUILHET, A. FOURRIER. T. speed p59 A87-12996 Airborne measurement methods applied to the Galvanic corrosion between carbon fiber reinfocced CUCKSON, 1. M. determination of boundary conditions at the sea surface: plastics and metallic aeronautical materials Manufacture of bonded composite assemblies for The TOSCANE experiment p 55 N87-11242 [ DFVLR-FB-66-16] p42 N87-11003 aircraft p 1 A87-13005 DSA. J. M. FOXLEY, D. E. CUMMINGS, D. !?a?; o! :e-o!-!ion cc-psrisons !c? %Y!P!- .E(! Choosina Aircraft Intearated Data Svstems (AIDS) Military aeronautical satellite communications surface-singularitydistributions p4 A87-10525 architecture suitable for Engine Health Monitoring (EHM) p 18 A87-10137 DUBOVKIN, N. F. on future generation engines p 31 N87-10083 CURRY, R. E. A method for calculating the susceptibility of jet fuels FRANKE, W. In-flight total forces. moments and static aeroelasti to smoking p40 A87-12901 Ground and flight tests of Tornado reconnaissance characteristics of an oblique-wing research airplane DUDA, J. P. pod p 22 A87-10940 [NASA-TP-2224] p 36 N87-10103 Integration of the KS-147A LOROP into the RF-SE Flight-determinedaerodynamic derivatives the AD-1 FRAWLEY, R. C. of p 28 A87-10935 oblique-wing research airplane Engine-airframe integration considerations for DUFFY, R. E. preliminary air vehicle performance analysis [ NASA-TP-22221 p36 N87-10871 Hgh temperature heat transfer for gas turbines using p26 N87-10068 shock tubes p37 A87-12646 FRYXELL, R. E. D DURAND, P. Effects of surface chemistry on hot corrosion life Airborne measurement methods applied to the p 43 N87-11193 DALTON, C. determination of boundary conditions at the sea surface: FUCHS, W. The TOSCANE experiment p 55 N87-11242 Body of revolution comparisons for axial- and Ice accretion calculations on cylindrical rods following surface-singularitydistributions p4 A87-10525 DUTTA, A. the Bain model, and comparisonwith experimental results Superplasticity in aeroengine titanium alloy VT-9 and DAME, L. T. (Fuchs. Schickel. Kaluza. Uwira. 1985) its modified compositions p39 A87-12096 The 30 inelastic analysis methods for hot section p 56 N87-1.1434 DZHANDZHGAVA, 0.1. components p 53 N87-11206 FULLER, C. R. DAMENE, M. Fundamentals of navigation according to geophysical fields p 19 A67-11337 An experimentalinvestigation of the interior noise control Polar navigation assisted by satellite effects of propeller synchrophasing p20 A87-11663 [NASA-CR-1781851 p 60 N87-11577 DAMPER, R. 1. investigation of optimal compiexity of BITE and its effects E on reliability, maintainability, monitoring and fault EARLY. M. L G prediction Influence of engine variables on future helicopter [ ETN-86-979761 p 51 N87-11175 systems p 27 N87-10072 GAONKAR, 0. DAVIE, R. S. EATON, H. E. Toward comparing experiment and theory for The influence of aerospace developments upon Alumina-CoCrAIY material as an improved intermediate corroborative research on hingeless rotor stability in developments in manufacturing p 1 A87-13002 layer for graded ceramic gas-path sealing in aeroturbine forward flight (an experimentaland analytical investigation DAWES, W. N. engines p 4i) A67- i2526 ui isuiaiad ruiw-ikp-kig s.&&Lty k kik~id%$t; A pre-processed implicit algorithm for 30 viscous EDWARDS, B. J. [NASA-CR-179711] p25 N87-10063 compressible flow p6 A87-11510 Low-cost avionics simulation for aircrew training GARODZ, L. DE BONY, Y. [ AD-A1691 981 p 34 N87-10865 Crashworthiness experiment summary full-scale Aeronautical research spin-offs on the development of ENDSLEY, N. H. transport controlled impact demonstration program civil applications for aluminium alloys p 48 A87-11792 Management of airborne reconnaissance images [DOT/FAA/CT-85/20] p 17 N87-10055 DE BROSSARD. M. through real-time processing p 19 A67-10949 GARODZ. L. J. Dirigibles - For what? p 23 A87-11661 ENGEN, D. D. The Boeing B 720 aircraft Controlled Impact DEANE, J. R. The need to execute the National Airspace System Demonstration (klD): Flight data recorder/cockpit voice A bibliography of aerodynamic heating references Program and for RAD beyond p 1 A67-11802 recorder experiment p 33 N87-10096 [BAE-BT-13481] p 14 N87-10832 ERIKSSON, L.-E. GEB, M. Euler solutions on grids around wings using local DEGANI, D. 0-0 The influence of weather-active fronts on visual flight refinement p6 A87-11512 Computation of turbulent supersonic flows around conditions p 56 N87-11437 ERKELENS, J. J. pointed bodies having crossflow separation L Cnne!g!ion khvaan fltnht rimillation and processing of GEDWILL, M. A. p 5 A87-11487 lj flight tests based on inertial measurements Cbaiing iiie prediciiori 4; ?Si-;ii 34 DEGNER. T. R. [NLR-MP-85058-U] p 28 N67-10863 GEORGE, A. R. Airline data acquisition in an ACARS environment ESCHENBACH, R. Analyses of broadband noise mechanisms of rotors p32 N87-10092 Combined utilization of Loran and GPS - The best from p 58 A87-11769 DEJONGE, H. W. 0. each system p20 A87-11664 GHIA, K. N. Real time debugging software package for flight EVANS, R. E. Analysis of two-dimensional incompressible flow past . simulator software system with variable labeled COMMON Nickel coated graphite fiber conductive composites airfoils using unsteady Navier-Stokes equations blocks p 39 A67-11844 [NASA-CR-179823] p 12 N87-10040 [ NLR-MP-85013-UI p 57 N87-11530 ULO, M. B. GHIA, U. DEIASERVETTE, X. Flight service evaluation of composite helicopter Analysis of two-dimensional incompressible flow past Helicopter air intake protection systems components airfoils using unsteady Navier-Stokes equations D27 N87-10073 [NASA-CR-1781491 p 41 N87-10182 [ NASA-CR-1798231 p 12 N87-10040

8-3 GILLIAM, F. PERSONAL AUTHOR INDEX

GILLIAY. F. HAPPEL, H.-W. HOPPE, W. C. Visualization of three-dimensional forced unsteady Application of a 2D time-marching Euler code to Evaluation of captured water column technology for separated flow transonic turbomachinery flow p6 A87-11516 advanced ultrasonic sizing techniques [AD-A1689391 p 51 N87-11129 HART-SMITH, L J. p 45 A87-10728 GILLIN, L Y. Critical joints in large composite aircraft structure RFC automated inspection overview The influence of aerospace developments upon [NASA-CR-37101 p 41 N87-10973 p 45 A87-10730 developments in manufactunng p 1 A87-13002 HARTEL, D. A. HORLOCK, J. H. GILYORE. J. Project management support p 61 A87-11805 The balance between theoretical, computational and Knowledge-basedtactical terrain analysis HARTMANN, J. experimental work in turbomachines p 49 A87-13015 Statistics of wind shear due to nocturnal boundary layer p19 A87-11061 HORNUNG, H. jet airstreams in North Germany p 56 N87-11461 GLOWINSKI, R. On the occurrence of regular reflection of shocks in HASSAN, H. A. Implicit and semi-implicit methods for the compressible concave comer flows p 10 A87-12586 Euler equations analysis of the initial roll-up of aircraft Navier-Stokes equations p 47 A87-11503 wakes p4 A87-10522 HOSKIN, B. C. GOLDSCHYIED, F. R. HASSLER, J. Y.. JR. Composite materials for aircraft structures Wind tunnel test of the modified goldschmied model Design and fabrication of the NASA decoupler pylon p 38 A87-10294 with propulsion and empennage: Analysis of test results for the F-16 aircraft Structural design with new materials [ AD-A1673601 p 13 N87-10045 [ NASA-CR-1723541 p25 N87-10065 p 49 A87-13011 GOLOVICHEV, V. I. Design and fabrication of the NASA decwpler pylon HOUWINK, R. A numerical analysis of supersonic bottom flow with for the F-16 aircraft, addendum 2 Computationsof separated subsonic and transonic flow thermal modification of the wake p 3 A87-10409 [NASA-CR-1724941 p 27 N87-10859 about airfoils in unsteady motion p 8 A87-11766 GONG, 0. HAWKINS, 8. J. Unsteady airload computations for airfoils oscillating in Development of a toughened bismaleimideresin prepreg The Fairchild CVDR: A new combination voice and data attached and separated compressible flow for carbon fiber composites p40 A87-12667 recorder p 33 N87-10095 [ NLR-MP-85040-U] p 16 N87-10846 GOORJIAN, P. Y. HAWKINS, C. A. HSI, W. H. Unsteady transonics of a wing with tip store Application of bifurcation and catastrophe theones to Stochastic crack propagation with applications to p4 A87-10524 . near stall flight mechanics durability and damage tolerance analyses GOPINATH, R. [ AD-A1676971 p 13 N87-10046 [AD-A168040] p 53 N87-11226 Tunnel interference from pressure measurements on HAWKINS, R. K. HUA, Y. control surfaces The C and Ku band scatterometer results from Canadian Transonic cascade flow solved by shock-capture [AE-TM-8-83] p 37 N87-10104 participation in the ESA PROMESS ocean measurement computationfollowed by separate-regioncomputation with GOULETTE, Y. J. campaign p 55 N87-11252 shock fitting p 10 A87-12956 Cost effective single crystals HAYKIN, S. HUGHES, J. 0. Stochastic modelling of radar returns [PNR-90319] p60 N87-11615 The KS-147A LOROP camera system GRANT, H. p 18 A87-10143 p 28 A87-10934 High temperature static strain gage program HEATH, D. M. Ouantitatie thermal diffusivity measurements of HULSE, C. p 52 N87-11188 High temperature static strain gage program composites p 45 A87-10750 GRAY, A. L. HEDE. A. J. p 52 N87-11188 The C and Ku band scatterometer resultsfromCanadian Reaction to aircraft noisa in residential areas around HULTBERG, R. participation in the ESA PROMESS ocean measurement Australian airports p54 A87-10116 Low speed rotary aerodynamics of F-18 configuration campaign p 55 N87-11252 Comparison of the effectiveness of measures of aircraft for 0 deg to 90 deg angle of attack Test results and GRIMY, W. noise exposure by using social survey data analysis Maneuver optimization in the case of combat aircraft p 54 A87-10117 [NASA-CR-36081 p 15 N87-10836 p 35 A87-11369 HUYMEL, D. HELIN. H. GROSSI, D. R. Visualization of three-dimensional forced unsteady Expenmental investigations of three-dimensional laminar boundary layers on a slender delta wing Flight recorders: New US regulations and new separated flow p9 A87-12145 International Civil Aviation Organization (ICAO) [AD-A1689391 p 51 N87-11129 standards p 32 N87-10093 HUO, X. HEMESATH, N. 8. Acta Aeronautica et Astronautica Sinica (selected GRUBB, J. W. A low cost commercial GPS set p 21 A87-12685 articles) Case study of Royal Australian Air Force P3B Orion HENKEL, P. aircraft ground oxygen fire incident p 16 A87-10866 [ AD-A16791 81 p3 N67-10004 Airborne reconnaissance IX; Proceedings of the GUPTA, B. K. HURET, N. Meeting, San Diego. CA, August 20. 21. 1985 Aeronautical research spin-offs on the development of Effects of surface chemistry on hot corrosion life [SPIE-561] p 18 A87-10931 civil applications for aluminium alloys p 48 A87-11792 p 43 N87-11193 HENSEL, G. GURUJEE, C. S. The classification of wind shears from the point of view Natural frequency analysis of compressor rotor blades of aerodynamics and flight mechanics I p 34 A87-10899 p 24 A87-11898 Natural frequency analysis of pretwisted plates HERON, K. H. IMBERT, N. p46 A87-10900 Resonant and non-resonant acoustic properties of Ground-based time-guidance algorithm for control of GURUSWAMY, 0. P. elastic panels. I - The radiation problem airplanes in a time-meteredair traffic control environment: Unsteady transonics of a wing with tip store p 49 A87-13026 A piloted simulation study p4 A87-10524 [NASA-TP-2616] p34 N87-10864 HEYYAN, J. S. GUSTAFSON, 0. C. Quantitative thermal diffusivity measurements of ISHU, Y. Photogrammetric tools for panoramic sector scan Study of three-dimensionalseparation on a spheroid at composites p 45 A87-10750 imagery in the VIDARS analysis station incidence p 49 N87-10016 HILAIRE. 0. p 19 A87-10948 ISMAILOVA, N. D. Aeronautical manufacturers requirements for new Thickened oils p40 A87-12902 materials p 38 A87-11791 ITO, A. H HILTMANN, P. Expansion of flow due to resistance of a wire gauze Maneuver optimization in the case of combat aircraft placed in a parallel-sided channel p 48 A87-12133 HACKER, P. p 35 A87-11369 ITOH, K. Dynamic flight optimization p 24 A87-11899 HO, D. Unsteady drag over cylinders and aerofoils in transonic HALFORD, G. R. Knowledge-based tactical terrain analysis shock tube flows p 10 A87-12617 Fatigue and fracture: Overview p 52 N87-11183 p 19 A87-11061 IZUTSU, N. HALL, D. E. HO, J. K. Numerical and experimental study of dynamics of Nickel coated graphite fiber conductiye composites Fault tolerant control laws two-dimensional body p 39 A87-11844 [NASA-CR-178094] p 50 N87-10400 [ ISAS-6191 p 59 N87-10748 HALL, R. F. C. HOBART, H. F. Investigationinto the attenuation and velocity of acoustic Evaluation results of the 700 deg C Chinese strain emissions in carbon fiber composite aircraft structures p 52 N87-11189 J [ BAE-KGT-R-GEN-013491 p 41 N87-10180 gages HOFFMANN, H. E. HALLER, R. L JACOB, K. Design and fabrication of the NASA decoupler pylon Ice accretion dependence on cloud physical Advanced method for computing the flow around wings parameters p 55 N87-11433 for the F-16 aircraft with rear separation and ground effect [ NASA-CR-1723541 p 25 N87-10065 HOHEISEL, H. [DFVLR-FB-86-17] p 50 N67-11017 Design and fabrication of the NASA decoupler pylon The high speed cascade wind tunnel: Still an important JANARDAN, 8. A. for the F-16 aircraft. addendum 2 test facility for investigations on turbomachinery blades Free jet feasibility study of a thermal acoustic shield [ NASA-CR-1724941 p 27 N87-10859 [DFVLR-MITT-86-11] p38 N87-10878 concept for ASTIVCE application: Dual stream nozzles DeNn and fabrication of the NASA decoupler pylon HOLLAND, R. [NASA-CR-3867] p 59 N87-10752 for the F-16 aircraft, addendum 1 Digital data recording on floppy disks applied for Free-jet acoustic investigation of high-radius-ratio [ NASA-CR-I723551 p 27 N87-10860 on-board use in helicopters coannular plug nozzles HANCOCK, J. P. [ DFVLR-MITT-86-10] p 51 N87-11149 [ NASA-CR-3818I p 59 N87-10753 PTA test bed aircraft engine inlet model test report, HONG, C. H. JANTZEN. E. revised AerOelastic stability of composite rotor blades in hover Fire occurring and expanding in connection with oils in [ NASA-CR-1748451 p 35 N87-10866 p 25 N87-10060 aviation D 16 A87-11368 PERSONAL AUTHOR INDEX YAJJIGI, R. K.

JANUS, J. M. KNOTT. P. R. LEBERL, F. W. Three-dimensional unsteady Euler equations solutions Free-jet acoustic investigation 01 high-radius-ratio Photogrammetric tools for panoramic sector scan on dynamic grids coannular plug nozzles imagery in the VIDARS analysis station [AD-A168041] p 51 N87-11128 [NASA-CR-3818] p 59 N87-10753 p 19 A87-10948 JATEGAONKAR. R. V. KNOX, C. E. LEE, D. J. Effects of llap position on longitudinal parameters of Ground-based time-guidance algorithm for wntrol of Sources and observers in motion, II -Acoustic radiation HFB-320 airplanes in a lime-metered air traffic control environment: from a small rigid body in arbitrary motion. 111 ~ Acoustic [ NAL-TM-SEg6021 p25 N87-10062 A piloted simulation study radiation from non-compact rigid bodies moving at high JEAL, R. H. [NASA-TP-2616] p34 N87-10864 Speed p59 A87-12995 Specification of gas turbine disc forgings KOEPP, F. LEE, J. M. F. p 44 A87-10121 Experimental and theoretical Doppler-lidar signatures of A computer-aided nondestructive inspection system JOHNSON, D. aircraft wake vortices . p 14 N87-10?30 p44 A87-10720 Crashworthiness experiment summary full-scale KOKOREV, A. LEFEBVRE, J. transport controlled impact demonstration program S Density field of a viscous gas jet issuing from a conical Surface measurements of gust lronts and microbursts [ DOT/FAA/CT-85/20] p 17 N87-10055 during the JAWS (Joint Airport Weather Studies) Project: JOHNSON, J. R. nozzle into vacuum p4 A87-10603 KOPPER. F. C. Statistical results and implications for wind shear detection, Annual Aerospace Applications of ArMicial lntellie prediction and modeling Conference. 1st. Dayton, OH, September 16-19, 1985, Coolant passage heat transfer with rotation, a progress rm p 53 N87-11225 [PB86-200847] p 55 N87-10665 Proceedings p 56 A87-12211 LENT, H. M. JOHNSTON, 0. R. KORDULLA, W. Vortex shedding 01 a square cylinder in front of a slender New materials in gas turbine technology Conference on Numerical Methods in Fluid Mechanics, airfoil at high Reynolds numbers. Part 1: Spacing effect 6th. Goetlingen. West Germany, September 25-27, 1985. p41 A87-13009 [MPIS23/1985] p 13 N87-10048 JONES, J. D. Proceedings p 47 A87-11501 LEPPINGTON, F. 0. An experimentalinvestigation of the interior noise control Experiences with an unlactored impli Resonant and non-resonant acoustic properties 01 effects of propeller synchrophasing prediitotcwrector method p 47 A87-11522 elastic panels. I - The radiation problem [NASA-CR-l78185] p 60 N87-11577 KOREMURA. K. p49 A87-13026 JONES, L A. Flight experiments on MLS elevation guidance LEROY, G. 0. In-service environmental effects on carbon fibre p21 A87-12686 The Boeing B 720 aircraft Controlled Impact composite material p 39 A87-12659 KOREN, 8. Demonstration (CID): Flight data recorder/cockpit voice JONNAVITHULA, S. Euler flow solutions lor a transonic wind tunnel section recorder experiment p33 N87-10096 Vortex simulation01 propagating stall in a linear cascade [CWI-NM-RBM)l] p 16 N87-10847 LEVIN, V. A. 01 airfoils p5 A87-11117 KOROLEV, A. A. Similarity law lor the supersonic flow past flat surfaces JORDAN, E. H. Methods of in-flight aerophyhl studies with intense distributed injection p 10 A87-12843 Biaxial constitutive equation development p 23 A87-11343 LEVINE, S. R. p 53 N87-11217 Surface protection p 43 N87-11182 JOSHI, A. KOTOVSKII. V. N. Mathematical modeling of separated flow past a wing LIGHT, 0. M. Effect of static inplane loads and boundary conditions profile and aerodynamic hysteresis p 5 A87-10619 Evaluation of captured water column technology lor on the flutter 01 flat rectangular panels advanced ultrasonic sizing techniques LNAL- I M-ST-6604j p sc ::8:.:csc: KOUK, L IU. Fractograpnic aywcis oi iii cyciic iraciirw ;oiighi;eas p 45 A87-10728 JOUVENOT, C. of 35KhN3MFA steel in vacucim. Bir, and kjdroger! LINDEMANN. C. The Airbwne Integrated Data System (AIDS) for the p40 A87-12882 The influence 01 weather-active fronts on visuai flight Airbus A-310 engine condition monitoring KRAPIVSKII, P. L. conditions p56 N87-11437 p31 N87-10082 Optimal control of viscous flow a1 high Reynolds LINDHOLM, U. S. numbers p 5 A87-10620 Constitutive modeling for isotropic materials KRICHBAUMER. W. A. p53 N87-11211 K Experimental and theoreticalDoppler-lidar signatures of LITTLE, J. K. aircraft wake vortices p 14 N87-10330 Response of a small-turboshaft-engine compression KAISER, H. A. KRIEGER, R. E., JR. system to inlet temperature distortion Software for flight recorder data processing developed Advances in toughness 01 structural composites based [ NASA-TM-837651 p35 N87-10100 by Lufthansa p32 N87-10090 on inlerleaf technology p40 A87-12661 LIU, w. KALBE, H. KROL, R. An experimental study on large negative incidence A-310 Aircraft Integrated Data Systems (AIDS) design Testing of Fe-Cu-baseablative composites. II separated flow in two-dimensional turbine cascades philosophy p30 N87-10076 p 41 A87-12971 p 10 A87-12957 KARLOVSKII, V. N. KROTHAPALLI, A. LOCK, R. C. Numerical investigation of supersonic flow past Recent advances in aeroacoustics p 58 A87-11766 The prediction of the drag of aerofoils and wings at spike-tipped blunt bodies p4 A87-10614 KUMAGAI, H. high subsonic speeds p 9 A87-12266 LOEHNER, R. KATANO, 1. Parametric analysis 01 a passive cyclic control device Recent developments in FEM-CFD p 5 A87-i 1411 Flight experiments on MLS elevation guidance for helicopters LOGSDON. T. S. p21 A87-12686 [ NASA-CR-1666081 p 28 N87-10862 Global positioning system applications KAUFMANN. V. KWONG, C. M. Numerical experiments with a total variation diminishing p 18 A87-10047 Photogrammetric tools for panoramic sector scan LOSCOS, J. M. imagery in the VIDARS analysis station (TVD) MacCormack scheme p6 A87-11526 KYRIACOS, E. Interferenceof the aeronautical navaids (frequencyband p 19 A87-10948 108.118 MHz) from F.M broadcasting service (88-108 KAYNAK, U. Reaction to aircraft noise in residential areas around Australian airports p 54 A87-10116 MHz) p21 A87-12690 Computation of transonic separated wing flows using Lon, R. W. an EulerINavier Stokes zonal approach The ASPRO parallel inferenceengine (A real-timeexpert p 16 N87-10849 system) p 29 A87-12218 n fi L ".-*....nLII, I, V. I. LUCERTINI, M. .---.-A '..--.:--- I^- &.+.aW;,. rnn,rnl CYe,PmP Automatically woven three-directional composite LAFLEN, J. H. r\"L"IIIPITu IullrUvIII ,-, ".. .." ...- . structures P 48 A87-11843 Elevated temperature crack growth p 21 A87-12687 KEMPE, 0. p 53 N87-11214 LUNEV, V. V. Properties and processing of fiber-reinforced LAGESSE, F. R. Method of meridional sections in problems involving a polyetheretherketone (PEEK) P 38 A87-11372 Airborne reconnaissance IX; Proceedings of the three-dimensional boundary layer p 4 A87-10609 KENTWELL, J. A. C. Meeting. San Diego, CA. August 20. 21, 1985 LUSE. J. D. Future developments and manufacturingat C.A.C [SPIE-561] p 18 A87-10931 Integration of GPS with other radionavigationsystems P2 A87-13014 LAMONT, P. J. p 21 A87-12680 KIDD, W. M. The lateral dynamic stability and control of a large LUXON, 8. A. Future developments and manufacturingat GAF receiver aircraft during air-to-air refuelling Nickel coated graphite fiber conductive composites P2 A87-13013 p36 A87-12268 p 39 A87-11844 LY, L. KIENEGGER, E. LANGE, R. H. u. Fault tolerant control laws Photogrammetric tools for panoramic sector scan A review 01 advanced turboprop transport activity p 24 A87-12650 [ NASA-CR-1780941 p 50 N87-10400 ;,r,ayeiy in ;he '/IC^ES ;?:>;$k B!P!!"" LAFiGiii, V. i. LYSTAD. 0. S. P 19 A87-10948 Conical wing of maximum lilt-to-dragratio in a supersonic Expert systems for aiding combat pilots KIM, K. S. gas flow p4 A87-10615 p 29 A87-12212 Elevated temperature crack growth LASCHKA, 8. P 53 N87-11214 Theoretical treatment 01 gust simulation in the wind KLANN, 0. A. tunnel p9 A67-12148 M Response of a small-turboshaft-engine compression LAURENT, G. system to inlet temperature distortion Data processing and calibration for an airborne YAIKAPAR, 0. I. [NASA-TM-837651 P35 N87-10100 scatterometer p 30 A87-12694 Induced drag of a curved wing p 10 A87-12805 KNEILE, K. R. LEAVIlT, L D. MAJJIGI, R. K. Large perturbation flow field analysis and simulation for Static internal performance of single-expansion-ramp Free jet feasibility study of a thermal acoustic shield Supersonic inlets nozzles with thrust-vectoringcapability up to 60 deg concept for ASTIVCE application: Dual stream nozzles 1 NASA-CR-1746761 P 14 N87-10835 [NASA-TP-2364] p 15 N87-10839 [ NASA-CR-38671 p 59 N87-10752

B-5 MAKSIMOV, V. F. PERSONAL AUTHOR INDEX

Freejet acoustic investigation of high-radius-ratio MEHROTRA, S. C. MUELLER, B. coannular plug nozzles Stress analysis of Pathfinder-2models Implicit finite-difference Simulation of separated [ NASA-CR-3818J p 59 N87-10753 [NASA-CR-1724931 p 51 N87-11179 hypersonic flow over an indented nosetip p 7 A87-11533 MAKSIMOV, V. F. MEHTA, U. Motion of a gas in a duct behind a moving body A comparison of interactive boundary-layer and MUIR. A. H.. JR. p5 A87-10675 thin-layer Navier-Stokes procedures p 8 A87-11785 A computer-aided nondestructive inspection system MEIER, G. E. A. MALONE. J. B. p 44 A87-10720 Vortex shedding of a square cylinder in front of a slender Unsteady aerodynamic modeling of a fighter wng in MULARZ, E. J. airfoil at high Reynolds numbers. Part 1: Spacing effect transonic flow p3 A87-10517 Aerothermal modeling program, phase 2 [ MPIS-23/19851 p 13 N87-10048 p 35 N87-11200 MALPANI, A. R. MELNIK, R. E. Natural frequency analysis of compressor rotor blades Viscous wing theory development. Volume 1: Analysis, MURTHY. S. N. B. p 34 A87-10899 method and results Numerical methods for engine-airframe integration Natural frequency analysis of pretwisted plates [NASA-CR-178156] p 12 N87-10043 p23 A87-11776 p46 A87-10900 MELVIN, W. W. MYERS, G. MANDELLA, M. Guidance strategies for near-optimum take-off NASA dilution jet mixing, phase 3 P 53 N87-11202 Quantitative study of shock-generated compressible performance in a windshear p 24 A87-12138 vortex flows p 10 A87-12616 MERKULOV, V. 1. MANNING, S. D. The possibility of the nondisturbing motion Of a body Stochastic crack propagation with applications to in a fluid p 48 A87-12894 N durability and damage tolerance analyses MEYER, H. [AD-A168040] p 53 N87-11226 Digital data recording on floppy disks applied for NAGAMATSU, H. T. High temperature heat transfer for gas turbines using on-board use in helicopters MANTEL, B. shock tubes p37 A87-12646 Implicit and semi-implicit methods for the compressible [DNLR-MITT-86-101 p51 N87-11149 Navier-Stokes equations p 47 A87-11503 MEYER, R. NAGAOKA, S. Charactenzlng height keeping error distnbution based MARASLI, 8. Further development of the influence function method p 17 A87-12683 On the large-scale structures in two-dimensional. . for store aerodynamic analysis p4 A87-10523 on indirect observation small-deficit,turbulent wakes p8 A87-12052 MICHAEL, R. A. NAKAGAWA, T. MARCONI, F. Keep your eye on the birdie - Aircraft engine bird A study on the axially Curved mixed-flow vaneless ingestion p 61 A87-10509 Viscous wing theory development. Volume 1: Analysis. diffusers p 47 A87-11481 method and results MIELE, A. Vortex shedding of a square cylinder in front of a slender Guidance strategies for near-optimum take-off [NASA-CR-178156] p 12 N87-10043 airfoil at high Reynolds numbers Part 1 Spacing effect performance in a windshear p 24 A87-12138 MARDOIAN, G. H. [ MPIS-23/1985] p 13 N87-10048 MILIOS, E. E. Flight service evaluation of composite helicopter Signal processing and interpretation using multilevel NAKAJIMA, H. components A description of a turbulent flow past a Circular cylinder signal abstractions [NASA-CR-178149] p 41 N87-10182 by a discrete vortex method p 11 N87-10014 [AD-A1691661 p 57 N87-11513 MARGASON, R. J. MILLER, D. S. NAPFEL, H. F. Euler equations analysis of the initial roll-up of aircraft Supersonic, nonlinear. attached-flow wing design for The FairchildCVDR A new combination voice and data wakes p4 A87-10522 high lift with experimental validation recorder p 33 N87-10095 MARINETS, 1. 1. [NASA-TP-23361 p 12 N87-I0042 NARAYANASWAMI,R. A reinforcing band near the flange of a heated cylindrical MILLER, R. A. CSAlNASTRAN - A general purpose program for casing p 48 A87-12445 Introduction to life modeling of thermal barrier structural analysis p 56 A87-10879 MARTINDALE, W. R. coatings p 43 N87-11195 NELLES, H. Large perturbation flow field analysis and simulation for MILLER, W. E. Wind shear measurement on board a MORANE 893 supersonic inlets Quantitative thermal diffusivity measurements of p 31 N87-10086 [ NASA-CR-1746761 p 14 N87-10835 composites p 45 A87-10750 NELSON, W. D. MASLOV, A. A. MILLS, C. T. L. Cntical joints in large composite aircraft structure Excitation of the natural oscillations of a boundary layer Stress analysis of Pathfinder-2models [NASA-CR 37101 p 41 N87-10973 by an external acoustic field p4 A87-10610 [ NASA-CR-1724581 p 51 N87-11179 NESBITT, J. A. MASON. M. L MIRONOV. A. D. Coating life prediction p 43 N87-11194 Interference effects of thrust reversing on horizontal tail Methods of in-flight aerophysical studies NIEHUIS, R effectiveness of twin-engine fighter aircraft at Mach p 23 A87-11343 On the occurrence of regular reflection of shocks in numbers from 0.15 to 0.90 MITCHELL, A. M. concave corner flows p 10 A87-12586 [NASA-TP-23501 p 36 N87-10870 Testing of UH-GOA helicopter transmission in NASA NIEUWPOORT. A. M. H. MASON. W. H. Lewis 2240-kW (3000-hp) facility Correlation between flight Simulation and processing of Supersonic, nonlinear, attached-flow wing design for [NASA-TP-26261 p 50 N87-10391 flight tests based on inertial measurements high lift with experimental validation MITCHELTREE. R. A. [ NLR-MP-8505841 p 28 N87-10863 [ NASA-TP-23361 p 12 N87-10042 Euler equations analysis of the initial roll-up of aircraft NILSSON, S. MANEEV, V. V. wakes p4 A87-10522 Decay of end effects in graphite/epoxy bolted loints Damping of the vibrations of deformable bodies p 44 A87-10115 p 47 A87-11336 MOHAGHEGH, M. MCCLELLAN. V. A. Tension analysis of stiffened aircraft structures NISHIKAWA, N. p 44 A87-10516 Doppler Radar Detection of Wind Shear Images of three dimensional flows in computer [ NASA-CP-24351 p 17 N87-10054 MOON, Y. J. graphics p 57 N87-10017 MCCRACKEN, W. Quantitative study of shock-generated compressible NISHT, M. 1. Data compression for IR reconnaissance vortex flows p 10 A87-12616 Mathematical modeling of separated flow past a wing p 18 A87-10947 MOORE, J. A. profile and aerodynamic hysteresis p 5 A87-10619 MCDANIELS, D. L Net shape forming: The route to low cost components. NIXON, D. Fiber-reinforced superalloy composites provide an The view point of the aerospace industry Prediction of gust loadings and alleviation at transonic added performance edge p39 A87-12647 [PNR-90306] p 51 N87-11020 speeds MCFADDEN, P. D. MOORE, W. R. [AD-A167748] p 13 N87-10047 Advances in the vibration monitonng of gears and rolling Investigation of optimal complexityof BITE and itseffects NOAH, S. T. element bearings p 49 A87-13007 on reliability, maintainability, monitoring and fault Effect of tangential torque on the dynamics of flexible Analysis of the vibration ofthe input bevel pinion in RAN prediction rotors Wessex helicopter main rotor gearbox WAK143 prior to [ETN-86-97976] p 51 N87-11175 [ASME PAPER 86-WA/APM-23] p 46 A87-11113 failure MOREY, W. W. NOLET, S. C. . [ARL-AERO-PROP-R-l69] p 25 N87-10061 Hot section viewing system Impact resistant hybrid composite for aircraft leading MCGARY, M. C. [NASA-CR-l74773] p51 N87-11144 edges p 24 A87-11848 Separation of airborne and structureborne noise radiated MORGAN, K. NOVAK, R. C. by plates constructed of conventional and composite Recent developments in FEM-CFD p 5 A87-11411 Alumina-CoCrAIY material as an improved intermediate materials with applications for prediction of interior noise MORINISHI. K. layer for graded ceramic gas-path sealing in aeroturbine paths in propeller driven aircraft p 60 N87-11579 Numerical solution of the Euler equations using rational engines p 40 A87-12928 MCKILLEN, J. Runge-Kutta method p 7 A87-11538 NOVIKOV, L. Z. Development of a toughened bismaleimide resin prepreg The mechanics of dynamically tunable gyroscopes for carbon fiber composites p 40 A87-12667 MORITZ, K. p 57 A87-10444 MCKNIGHT, R. L Maneuver optimization in the case of combat aircraft The 3D inelastic analysis methods for hot section p 35 A87-11369 NOWAK, S. components p 53 N87-11206 MORRIS, L The effects of temperature and loadingrate on R curves MCNULTY, C. Polymer systems for rapid sealing of aircraft structures using the CLWL techniques Expert systems for aiding combat pilots at low temperature [BAE-MSM-R GEN-05441 p 50 N87-10405 p 29 A87-12212 [ AD-AI 676671 p 41 N87-10209 NUMBERGER, K. MEAD, S. M. MOUNIER, C. Expenence with the Onboard Checkout And Monitoring Resonant and non-resonant acoustic properties of Transformation of a plane uniform shock into cylindrical System (OCAMS) of a military aircraft resulting elastic panels. I - The radiation problem or spherical uniform shock by wall shaping improvements and the consequence for future design p 49 A87-13026 p 37 A87-12585 D 31 N87-10079

B-6 PERSONAL AUTHOR INDEX SAID, F.

0 PHILLIPS, 0. M. REINHALL, P. G. Laser airborne depth sounding in Australia Modeling and analysis of the dynamics of a drill OBERLE, L G. p 30 A87-12677 penetrating a thin plate Laser anemometers 01 hot-section applications PITTALUGA, F. [ASME PAPER 86-WA/APM-33] p 46 A87-11112 p 52 N87-11187 Experimental investigation on the performances of a RHEA, J. OWNI, A. R. transonic turbine blade cascade for varying incidence Avionics in the submicroscopic world Potential impacts of advanced technologies on the ATC angles p9 A87-12205 p 48 A87-11800 capacity of high-density terminal areas PIlTMAN, J. L RIECHE, A. [ NASA-CR-4024) p 22 N87-10854 Supersonic. nonlinear, anached-flow wing design for Theoretical aspects and practical questions regarding OGILVIE, P. L high lift with experimental validation the assurance of flight safely p17 A87-11900 Viscous mng theory development Volume 2 [ NASA-TP-23361 p 12 N87-10042 RIZZI, A. GRUMWING computer program user's manual POPE, L 0. Vortex-stretched flow around a cranked delta wing [ NASA-CR-1781571 p13 N87-10044 Propeller aircraft interior mise model utilization study p3 A87-10520 OHARE, J. E. and validation Numericalexperiment with inviscid vortex-stretched flow A nonperturbing boundary-layer transmn detection around a cranked delta wing, supersonic speed [NASA-CR-172428] p60 N87-11576 p 46 A87-10971 p 7 A87-11537 PORITZKY, S. 8. OSHIMA, K. ROBERTS, A. S.. JR. Report of the InternationalSymposium on Computational FANS - A US.perspective p 20 A87-11807 Graduate engineering research participation in Fluid Dynamics, Tokyo p49 N87-10029 POULErn, c. aeronautics OSHIMA, Y. Implicit and semi-implit methods for the compressible [NASA-CR-179798] p3 N87-10828 Study of three-dimensionalseparation on a spharcid at Navier-Stokesequations p 47 A87-11503 ROBERTS, C. A. incidence p49 N87-10016 PROBST, K. Flight recorders: New US regulations and new OSIPOV, A. A. Experience with the Onboard Checkout And Monitoring International Civil Aviation Organization (ICAO) Calculation of unsteady supersonic flow past a plane System (WAMS) 01 a military aircraft resulting standards p 32 N87-10093 blade row under the effect of vortex inhomogeneities in improvements and the consequence lor future design ROBERTS, M. L the oncoming flow p5 A87-10618 p 31 N87-10079 The 3D inelastic analysis methods for hot section OSSWALD, G. A. PROCTOR, J. 0. Components p 53 N87-11206 Analysis of two dimensional incompressible flow past Practical evaluationof wall pressure signaturecorrection Component specific modeling p 35 N87-11207 airfoils using unsteady Navier-Stokes equations methods in the 2.7m x 2.lm low speed wind tunnel ROBERTS, R. [ NASA-CR-1798231 p12 N87-10040 [ BAE-ARG-2041 p 37 N87-10874 Variations in ultrasonic backscaner attributed lo OSTREM, 0. PSIAKI, M. L porosity p45 A87-10768 The KS-147A LOROP camera system Optimal flight paths through microburst wind profiles ROBINSON, m. p 28 A87-10934 p 35 A87-10519 Visualization 01 three-dimensional forced unsteady OSWALD, F. B. PURCELL, C. J. separated flow Testing of UH-GOA helicopter transmission in NASA Vortex-stretched flow around a cranked delta wing [AD-A168939] p 51 N87-11129 Lewis 2240-kW (3000-hp) facility p3 A87-10520 RODNOV. A. V. NASA-TP-26261 D 50 N87-10391 I Numerical experiment mth inviscidvortex-stretched flow Methods of in-flight aerophysical studies Y. ou, around a cranked delta wing, supersonic speed p 23 A87-11343 A nuasi-three-dtmnnsional method for diaaonal flow ROESNICK. M. D 7 AB:.: :527 fans p 11 A87-12958 A system theoretical based method for module failure diagnostic of turbine engines p35 N87-10085 ROHDE, J. E. P R Host turbine heat transfer overview p 52 N87-11184 PALAZZO, F. RADER, K. ROSENAU, 0. Technical diagnosis by automaled reasoning Long range E-0 ReconnaissanceSystem and flghl test Comparative evaluation of redundant flight data p 57 A87-12217 results p 28 A87-10933 recorded by a digital aircraft integrated data system PALMER, J. M., JR. RADWAN, S. F. recorder (DAR) on board an Airbus A-310 aircraft Dc-10 composite vertical stabilizer ground test Numerical solution 01 the 3-dimensional boundary layer p33 N87-10098 program equations in the inverse mode using finite differences ROTH, R. [ NASA-CR-37151 p42 N87-10974 p 11 N87-10005 Ice accretion dependence on cloud physical PALMIERI. S. RAHN, 0. J. parameters p 55 N87-11433 Monitoring of terminal Right phases environment NASA and FAA launch wind shear research project Statistics of wind shear due to nmturnal boundary layer ObSeNaliOnS and models p 55 A87-12679 [NASA-NEWSREL-86-1431 p55 N87-10659 jet airstreams in North Germany p 56 N87-11461 A new concept in air traffic control - The multi-radar RAI, m. M. ROWLAND, S. N. tracking (MRT) p 21 A87-12689 A simulation of rotor-stator interaction using the Euler Electromagnetic methods lo detect corrosion in airwan PANARANDA, F. E. equations and patched grids p 7 A87-11536 structures p45 A87'10791 Aeronautical facilities assessment RALPH, N. ROZHDESTVENSKII,V. 1. [NASA-RP-1146] p 37 N87-10876 The future operations and procurement of rotary wing Similarity law for the supersonic flow past flat surfaces PARENT, R. 0. aircraft in the Royal Australian Navy p 2 A87-13012 with intense distributed injection p 10 A87-12843 Computerized ultrasonic test inspection enhancement RUBEN, H. D. SySlem for aircraft components p 44 A87-10721 RALSTON, J. N. Rotary balance data and analysis for the X-29A airplane Application of operational flight recording lo PASCARELLA, E. heiicoprers p31 N87-10081 A new concept in air traffic control - The multi-radar for an angle-of-attack range of 0 deg lo 90 deg [ NASA-CR-37471 p 15 N87-10837 RUES, 0. tracking (MRT) p 21 A87-12689 RAMAKRISHNAN, R. Conference on Numerical Methods in Fluid Mechanics, PAYNTER, 0. C. 6th. Goeningen, West Germany, September 25-27. 1985. Finite element computations lor high speed 30 inviscid Numerical methods for engine-airframe integration Proceedings p 47 A87-11501 flows p 7 A87-11542 p 23 A87-11776 Implicit finite-difference simulation 01 separated CFD - A user's technology assessment RANGWALLA, A. A. hypersonic flow over an indented nosetip .anniir.tinn .rr -6-. - ~-.- pcy'p ic3pnpr.i +.dY tinuue p 23 AB7-11781 I, i A67-i i6SS in three dimensions p 50 N87-10262 PENNY, M. F. RUSSELL, J. Laser airborne depth sounding in Australia RAUSHENBAKH, 8. V. Visualization of three-dimensional forced unsteady p 30 A87-12677 Scientific problems of aviation and space: History and separated flow present state p 62 A87-11339 PERAIRE. J. [ AD-A1689391 p 51 N87-11129 Recent developments in FEM-CFD p 5 A87-11411 RAY, A. RUSSELL, J. K. A redundancy management procedurefor fault detection PERIAUX. J. The influence 01 aerospace developments upon and isolation p 46 A87-11127 Implicit and semi-implicit methods lor the compressible developments in manufacturing p 1 A87-13002 Navier-Stokes equations p 47 A87-11503 RAY, J. A. RUSTAMOVA, S. N. Thickened oils p40 A87-12902 PERLMAN, R. Engine-airframe integrabon for rotorcraft: Component specifications and qualification p 26 N87-10071 The crash 01 Della Flight 191 - Are the nightmares compensable? p 61 A87-10510 Engine-airframe integration for rotorcraft: System specifications and qualification p 27 N87-10074 S PETRASEK, 0. W. REDIESS, H. A. Fiber-reinlorced superalloy composites provide an T--k.."l^.... .^..i^... ^I 'li"h, ^.IICial 'linh, rnntnri SACHIDANANDAMURTHY,K. N. , wu ,,,,",yy, ,-.,*.. ...y,. ...a ordome added performance edge p 39 A87-12647 -. "."".-. An experimental investigation of end-wall tlowtield 01 a (application of optical technology) PETROSELLINI, C. compressor rotor p 50 N87-10244 [NASA-CR-172332] p 36 N87-10102 A new concept in air traffic control - The multi-radar REED, 8. R. SAGE, 0. F. tracking (MRT) p21 A87-12689 The ASPRO parallel inference engine (A real-timeexpert Integration of GPS with other radionavigation systems PFLEGING, P. system) p 29 A87-12218 p 21 A87-12680 Digital data recording on floppy disks applied for REES, 0. SAGGIO, F., 111 on-board use in helicopters Laser airborne depth sounding in Australia Data compression techniques for multifunction flight [ DFVLR-MllT-86-10] p51 N87-11149 p 30 A87-12677 data recorders p 33 N87-10094 PHARES, W. J. REEVES, J. T. SAID, F. Large perturbation flow field analysis and simulation for Operatingand support hazard analysis for self-contained Airborne measurement methods applied to the supersonic inlets navigation system LSI model 6216A, B and C, group B determination of boundary conditions at the sea surface [NASA-CR-I746761 p 14 N87-10835 [AD-A169381] p 22 N87-10855 The TOSCANE expenment p 55 N87-11242

B-7 SAILLARD, Y. PERSONAL AUTHOR INDEX

SAILLARD. Y. SHEFFLER. K. STEPHENS, J. R. Transformation of a plane uniform shock into cylindrical Thermal barrier coating life prediction model Fiber-reinforced superalloy compoates provide an or spherical uniform shock by wall shaping develwment p 52 N87-11199 added performance edge p39 A87-12647 p 37 A87-12585 SHEVELL, R. S. STEVENS, M. SAKAI, T. Aerodynamic anomalies ~ Can CFD prevent or correct Photogrammetric tools for panoramic sector scan A study on the axially curved mixed-flow vaneless them? p4 A87-10521 imagery in the VIDARS analysis station diffusers p 47 A87-11481 SHOHET, H. N. p 19 A87-10948 Engine-airframe integration considerations for SAKHAROV. V. 1. STEWART, E. C. preliminary air vehicle performance analysis Numecical investigation of supemnic flow past Piloted simulation study of the effects of an automaled spiketipped blunt bodies p4 A87-10614 p26 N87-10068 trim system on flight characteristics of a light twin-engine SHOLLENBERGER, S. B. airplane with one engine inoperalive SALASROCHE, F. Helicopter MLS Flight Inspection Project Potential impacts of advanced technologies on the ATC [ NASA-TP-26331 p 16 N87-10843 [ DOT/FAA/CT-86/14] p 2 N87-10002 STOCK, H. W. capacity of high-density terminal areas SHURE, M. A. [ NASA-CR-40241 p 22 N87-10854 A laminar boundary layer method for flows in planes Infrared emission lines from planetary nebulae SALUS, A. M. of symmetry and application to inclined ellipsoids of p 62 N87-10791 revolution p9 A87-12146 Air Force technical objective document fiscal year SIM, A. G. STORTI, D. W. 1987 In-flight total forces. moments and static aeroelastic Modeling and analysis of the dynamics of a drill [AD-A1673241 p 62 N87-10779 characteristics of an oblique-wing research airplane penetrating a thin plate SANDUSKY. P. M. [NASA-TP-22241 p 36 N87-10103 [ASME PAPER 86-WAIAPM-331 p 46 A87-11112 Impact resistant hybrid composite for aircraft leading Flightdetermined aerodynamic derivatives of the AD-1 edges p 24 A87-11848 oblique-wing research airplane STRANGE, R. R. SANE, S. K. [NASA-TP-22221 p 36 N87-10871 Development of heat flux sensors in turbine airfoils Natural frequency analysis of compressor rotor blades SIMPSON, R. W. p 52 N87-11186 p34 A87-10899 Potential impacts of advanced technologies on the ATC STUBRS. D. A. Natural frequency analysis of pretwisted plates capacity of highdensity terminal areas RFC automated inspection overview p46 A87-10900 . [NASA-CR-40241 p 22 N87-10854 p 45 A87-10730 SANKAR, L N. SINCLAIR. P. M. STUBS, D. S. Unsteady aerodynamic modeling of a fighter wing in An exact integral (field panel) method for the calculation Evaluation of captured water column technology for transonic flow p3 A87-10517 of two-dimensional transonic potential flow around advanced ultrasonic sizing techniques p 45 A87-10728 SATOFUKA, N. complex configurations p9 A87-12267 Numencal solution of the Euler equations using rational SINDELAR, P. STUCKENBERG, N. RungeKuna method p 7 A87-11538 Decay of end effects in graphitelepoxy bolted joints Performancemonitoring of sensors in high reliable flight p 44 A87-10115 SATRAN, D. R. control systems using deterministic Observers SISTO, F. p32 N87-10087 Wind-tunnel investigation of the flight characteristics of Vortex simulation of propagatingstall in a linear cascade a canard general-aviation airplane configuration STURZ, R. A. of airfoils p5 A87-11117 [ NASA-TP-26231 p12 N87-10039 Reconnaissance and the microprocessor SLATER, P. N. p 29 A87-10943 SCHAEFER, 8. Effects of atmosphere on oblique reconnaissance SUBRAMANIAN, G. Results of wind tunnel tests on external combustion p 29 A87-10937 [ESA-lT-959] p 42 N87-10990 A higher order beam element for vibration of beams SMIT, J. H. with discontinuities p 46 A87-10898 SCHIFF, L B. The ASPRO parallel inference engine (A real-timeexpert SUMANTRAN, V. Computation of turbulent supersonic flows around system) p 29 A87-12218 The effect of free stream disturbances and control pointed bodies having crossflow separation SMIT, J. S. p 5 A87-11487 surface deflections on the performance of the Wortmann Transition to new systems and international airfoil at low Reynolds numbers p 11 N87-10007 SCHLIEKELMANN, R. J. perspectives p 20 A87-11806 SUNG, B. Progress in advanced materials and processes; SMITH, C. A. Analysis of the vortical flow around a 60 deg Delta wing Durability, reliability and quality control; Proceedings of the Recent advances in aeroacoustics D 58 A87-11766 with vortex flap p 11 N87-10006 Sixth International European SAMPE Conference. SMITH, D. J. SUTTON, J. 0. Scheveningen. Netherlands. May 28-30. 1985 Forging of blades for gas turbines p 44 A87-10124 DC-10 composite verhcal stabilizer ground test p 39 A87-12651 SMITH. M. J. T. program XHMATZ, M. A. Aircraft noise measurement The 1.2 metre microphone [ NASA-CR-37151 p 42 N87-10974 Calculation of strong viscouslinviscid interactions on height saga SUZUKI, A. airfoils by zonal solutions of the Navier-Stokesequations [PNR-903151 p 60 N87-11578 Images of three dimensional flows in computer p7 A87-11540 SOLIES, U. P. graphics p 57 N87-10017 SCHMITZ, F. H. A study of the flow field about an upper surface blown SYCHEV, V. V. Helicopter impulsive noise - Theoretical and wing and itseffects on longitudinalstatic stability of a small Optimal control of viscous flow at high Reynolds experimental status p 58 A87-11771 jet airplane p 11 N87-10009 numbers p5 A87-10620 SCHOELER, H. SOMASHEKAR, B. R. On the occurrence of regular reflection of shocks in Effect of static inplane loads and boundary conditions concave corner flows p 10 A87-12586 on the flutter of flat rectangular panels T SCHROLL, D. W. [NAL-TM-ST-86041 p 50 N87-10404 Cleaning methods and procedures for military oxygen SOTOMAYER. W. A. TAKAYAMA, K. equipment .Investigation results p 46 A87-10867 Unsteady aerodynamic modeling of a fighter wing in Unsteady drag over cylinders and aerofoils in transonic SCHULTZ, D. F. transonic flow p3 A87-10517 shock tube flows p 10 A87-12617 Combustion overview p 43 N87-11181 SPUIALE, C. G. TAM, C. K. W. SCULL, D. C. Vortex simulation of propagating stall in a linear cascade On broadband shock associated noise of supersonic The US. Federal Radionavigation Plan of airfoils p5 A87-11117 jets p 58 A87-11768 p21 A87-12684 SPILLING, P. D. TAN, H. SEASHOLTZ, R. 0. Cost effective single crystals A test research for improving the performanceof V-type Laser anemometers of hot-section applications [ PNR-903191 p60 N87-11615 flameholder used in an afterburner p 34 A87-12965 p 52 N87-11187 SRI NAMACHCHIVAYA, N. TEDESCHI. W. J. SEIDLER, F. Non-linear stability analysis of aircraft at high angles Unsteady flow over an airfoil inside a wind tunnel with The classification of wind shears from the point of view of attack p 36 A87- 12082 and without transpiration p 13 N87-10051 of aerodynamics and flight mechanics SRINIVASAN. R. TESSITORE, F. p 24 A87-11898 NASA dilution jet mixing, phase 3 p 53 N87-11202 Further development of the influence function method SEMECO, A. for store aerodynamic analysis p4 A87-10523 STAHARA, S S. Knowledge-basedtactical terrain analysis THART, W. G. J. Development of a tulbomachinery design optimization p19 A87-11061 Corrosion and corrosion prevention in aircrafl procedure using a multiple-parameter nonlinear SEMENOV, N. V. structures perturbation method Excitation of the natural oscillations of a boundary layer [NLR-MP-85029-U] p 43 N87-11004 [ NASA-CR-38311 p2 N87-10003 by an external acoustic field p4 A87-10610 THIELE, A. W. SENKEVICH, E. A. STEINER, P. A. A computer-aided nondestructive inspection system Method of meridional sections in problems involving a Development of a toughened bismaleimideresin prepreg p 44 A87-10720 threedimensionalboundary layer p 4 A87-10609 for calbon fiber composites p40 A87-12667 THOMAS,Stochastic P. modelling of radar returns SERAUDIE. A. STEINHOFF. J. Report on tests of a CAST 10 airfoil with fixtransition Viscous wing theory development. Volume 1; Analysis. p 18 A87-10143 in the T2 transonic cryogenic wind tunnel with h;-adaptive method and results THOMPSON, J. F. walls [ NASA-CR-1781561 p 12 N87-10043 A survey of composite grid generation for general [RT-OA-63/1685] p 14 N87-10834 STENGEL, R. F. three-dimensional regions p 56 A87-11779 SHARMA, V. N. Optimal flight paths through microburst wind profiles THOMPSON, R. L Natural frequency analysis of pretwisted plates p 35 A87-10519 Integrated monitoring systems for tactical aircraft p46 A87-10900 STEPHENS, C. 0. p 31 N87-10080 SHATALOV. M. IU. DC-10 composite vertical stabilizer ground test THORNTON, E. A. The mechanics of dynamically tunable gyroscopes program Finite element computations for high speed 30 inviscid p 57 A87-10444 [ NASA-CR-37151 D 42 N87-10974 flows p 7 A87-11542 PERSONAL AUTHOR INDEX YENNI, K. R.

TIYY, R. VOSKRESENSKY. 0. P. WHIPPLE, R. D. Vortex shedding of a square cylinder in front of a slender Computational aerodynamics of supersonic lifting Spin-tunnel investigation of a 1125-scale model of the airfoil at hgh Reynolds numbers. Part 1: Spacing effect v*les p 12 N87-10030 General Dynamics F-16XL airplane [ MPIS23119851 p 13 N87-10048 Supersonic flow arwnd tip sides of wings [NASA-TM-85660] p12 N87-10041 TINOCO, E. N. p12 N87-10033 WHITE, C. CFD applications to enginelairframe integration NASA dilution jet mixing, phase 3 p 53 N87-11202 p 23 A87-11780 WHITE, W. L TIWARI, A. w Spm-tunnel investiatin of a 1125-scale model 01 the Combined utilization of Loran and GPS ~ The best from General Dynamics F-16XL airplane each system p20 A87-11664 WAGNER, R. D. [ NASA-TM-856601 p12 N87-10041 TJONNELAND, E. Laminar flow control for transport aircraft applications WHITELAW. J. H. CFD - A user's technology assessment p 24 A87-13021 Calculation methods for aerodynamic flows - A review p 23 A87-11781 WAI, J. p8 A87-11783 TOKUNAGA, H. Numerical sirnulation of viscous supersonic flow over WHITFIELD. D. L Numerical solution of the Euler equations using rational a generic fighter conliguration p6 A87-11509 Three-dimensional unsteady Euler equations solutions Runge-Kulta method p7 A87-11538 WALDYANN, 0. on dynamic grids TRETIAKOV, P. V. Modern Aircraft Integrated Data Systems (AIDS) [AD-A168041] p 51 N87-11128 Conical wing of maximum lift-to-drag ratioin a supersonic technology exemplili on the A-320 p 30 N87-10078 WILDEY, C. G. gas flow p4 A87-10615 WALKE. R. L Miliry aeronautical satellite communications TSANG, C.C. Integratbn of the KE147A LOROP into the RF-5E p 18 A87-10137 Knowledge-based tactical terrain analysis p 28 A87-10935 WILLIAMS, Y. p19 A87-11061 WALKER, J. Polymer systems for rapid sealing of aircraft structures TU, E. L Visualization of three-dimensional forced unsteady at low temperature Unsteady transonics of a wing with tip store separated flow [ AD-A167667 1 p41 N87-10209 p4 A87-10524 [AD-A1689391 p 51 N87-11129 WILLYES, A. C. TURNBERG, J. E. WALKER, K. P. Propfan slipstream effects using static simulators: Low Effect of angular inflow on the vibratory response of a Biaxial constitutie equation development speed task, phase 1 counter-rotating prqxller p 53 N87-11217 [ BAE-B59RIR-D161OH 34981 p 37 N87-10875 [ NASA-CR-1748191 p15 N87-10840 WALKLEY. K. 6. WINFREE, W. P. TYNOR, S. Numerical methods and a computer program for Quantitative thermal diffusivity measurements 01 Knowledge-based tactical terrain analysis subsonic and supersonic aerodynamic design and analysis composites p 45 A87-10750 p19 A87-11061 of wings with attainable thNSt considerations WllllCH, K. P. TZUOO, K. L [ NASA-CR-36081 p3 N87-10829 Statistics of wind shear due to nocturnal boundary layer Prediction of gust loadings and alleviation at transonic WALLER, P. jet airstreams in North Germany p 56 N87-11461 speeds The impact of lliht data on an airline: A case study WNUK, K. [ ADA1677481 p13 N87-10047 p 32 N87-10088 Modern Aircraft Integrated Data Systems [AIDS) WANG, B. technology exemplified on the A-320 p 30 N87-10078 W Transonic cascade flow solved by shock-capture WRIGHT, D. C. computationfollowed by separate-regioncomputation with Forging of blades for gas turbines p 44 A87-10124 VAN DE WATER, B. shock fitting p 10 A87-12956 WRIGHT, S. E. WANG, J. Condition monitoring of large commercial turbofan Sources and observers in motion, II - Acoushc radiation A test research for improving the performance of V-type engines p34 A87-13008 from a small rigii body in arbitrary motion. 111 - Acoustic flameholder used in an afterburner p 34 A87-12965 VAN DER VEER, W. R. radiation from non-compact rigii bodies moving at high WANG, Y. Evaluation of captured water column technology for SPd p 59 A87-12995 Numerical anal)& with generalized J-integral advanced ultrasonic sizing techniques Sources and observers in motion. IV Acoustic p 47 A87-11492 - p 45 A87-10728 measurements on aerofoils moving in a circle at high WANG, T. VANCE, J. M. speed p 59 A87-12996 Guidance strategies for near-optimum take-off Effect of tangential torque on the dynamics of flexible WU, C.-H. rotors perfwmance in a windsheaf p 24 A87-12138 WANG, 2. Transonic cascade flow solved by shock-capture [ASME PAPER 86-WAIAPM-231 p 46 A87-11113 computation followed by separate-region computatin with VANDERGEEST. P. J. J. Transonic cascade flow solved by shock-capture computationfollowed by separate-region computation with shock fitting p10 A87-12956 Correlation between flight simulation and processing of WU, K. flight tests based on inertial measurements shock fining p 10 A87-12956 WANHILL, R. J. H. A quasi-three-dimensional method for diagonal flow [NLR-MP-85058-U] p 28 N87-10863 fans p 11 A87-12958 VANSTONE, R. H. Fatigue fracture in steel landing gear components WYGNANSKI, 1. Elevated temperature crack growth [NLR-MP-85050-U] p 54 N87-11233 WANSTALL, B. On the large-scale structures in two-dimenbional, p 53 N87-11214 small-deficit, turbulent wakes p8 A87-12052 VARNER, Y. 0. JAS39 Gripen - A Swedish solution to a multi-role Large perturbation flow field analysis and simulation for need p 23 A87-11798 supersonic inlets WATERS, D. M. United States Navy - Canadian Forces solid state flight [NASA-CR-174676] p 14 N87-10835 X VASILEV, I. A. data recorderlcrash position locator experiment on the Density field of a viscous gas jet issuing from a conical 8-720 controlled impact demonstration XING, 2. p 33 N87-10097 Calculation of boundary layer of a three dimensional nozzle into vacuum p4 A87-10603 VICARIO. A. A., JR. WEAR, J. D. S-shaped inlet p6 A87-11495 Automatically woven three-directional composite Flame radiation p43 N87-11204 xu, L. WEBER, 0. structures p 48 A87-11843 Numencal analysis with generalized J-integral VIDAL-MADJAR, D. Comparative evaluation of redundant flight data p 47 A87-11492 recorded by a digital aircraft integrated data system Data procevsiiiy at," uaiibai;inio ki an &*;;,e recorder (DAH) on Doara an AirOus n-2 iir eiruiaii Scatterometer p 30 A87-12694 VIGWROVICH, 1.1. p33 N87-10098 Y Similarity law for the supersonic flow past flat surfaces WEGNER, W. with intense distributed injection p 10 A87-12843 Theoretical treatment of gust simulation in the wind YAN, H. VINOGRADOV, IU. A. tunnel p9 A87-12148 Acta Aeronautica et Astronautica Sinica (selected Similarity law for the supersonic flow past flat surfaces WEHRY, W. articles) with intense distributed injection p 10 A87-12843 The influence of weather-active fronts on visual flight [AD-A167918] p 3 N87-10004 conditions p 56 N87-11437 VINTHEDEN, E. A. YANG, J. N. WEIKLE, D. H. Integrated logistics for reconnaissance systems Stochastic crack propagation with applications to Laser anemometers of hot-sectionapplications P 61 A87-10942 durability and damage tolerance analyses p 52 N87-11187 VISSER, H. 0. [ AD-Al680401 p 53 N87-11226 Energy management of 3dimensional minimum-time WEILAND, C. A split-matrix method for the integration of the YATES, R. J. intercept p 27 N87-10858 quasi-conservative Euler-equations p 7 A87-11544 The future of international air transport VOGT, P. G...... p2 A87-13016 Free-jet acoustic investigation of high-radius-ratio YYE'PU, c. 8. YAU, >. F. coannular plug nozzles Quantitative thermal diffusivity measurements of composites p 45 A87-10750 Elevated temperature crack growth [NASA-CR-3818] P 59 N87-10753 WELL, K. p 53 N87-11214 VON LAVANTE. E. Maneuver optimization in the case of combat aircraft YE, D. Efficient numerical method for transonic flow p 35 A87-11369 An experimental study on large negative incidence simulations P6 A87-11528 WERNER, C. separated flow in two-dimensionalturbine cascades VONLAUE, H. D. Laser remote sensing procedures provide an aid to p 10 A87-12957 Investigationson a digital bit synchronizer for a detailed aviation during the approach for landing YENNI, K. R. flight data recovery P 33 N87-10099 p 19 A87-11370 Piloted Simulation study of the effects of an automated VORRES. C. L WESTFALL, L J. trim system on Wihi characteristics of a light twin-engine Variations in ultrasonic backscatter attributed to Fiber-reinforced superalloy composites provide an airplane with one engine inoperative porosity P45 A87-10768 added performance edge p 39 A87-12647 [ NASA-TP-26331 p 16 N87-10843 YIM. K. B. PERSONAL AUTHOR INDEX

YIW, K. 8. Effect 01 tangential torque on the dynamics of flexible rotors [ASME PAPER 86-WA/APM-23] p 46 A87-11113 YOSHIZAWA, Y. A description of a turbulent flow past a circular cylinder by a discrete vortex method p 11 N87-10014 YU, Y. n. Helicopter impulsive noise - Theoretical and experimental status p 58 A87-11771 YUHAS, D. E. Variations in ultrasonic backscatter anributed to porosity p 45 A87-10768

UWIATIN, A. N. Methods 01 in-flight aerophysical studies p 23 A87-11343 ZEINER, P. K. Influence of engine variables on future helicopter systems p27 N87-10072 ZEN, S. Calculation of boundary layer of a three dimensional S-shaped inlet p6 A87-11495 ZQUROVSKII, A. G. A reinforcing band near the flange of a heated cylindrical casing p 48 A87-12445 ZHANG, H. Acta Aeronautica et Astronautica Sinica (selected attiiles) [ AD-A1679181 p3 N87-10004 ZHANG, J. Transonic cascade flow solved by shock-capture computation lollowed by separate-region computationwith shock fitting p 10 A87-12956 ZIENKIEWICZ, 0. C. Recent developments in FEM-CFD p 5 A87-11411 ZIMA. IU. V. Fractographic aspects of the cyclic fracture toughness 01 35KhN3MFA steel in vacuum, air, and hydrogen p 40 A87-12882

B-10 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 270) February 1987

Typical Corporate Source Index Listing

AIr Force Test Pllot School. Edwards AFB, Calif. Center for Mathematics and Computer Science, Performance and qualiv flight lest textbook Volume 2 Amsterdam (Netherlands). Flying qualities Euler flow Solutions lor a transonic wind tunnel section lADA1681241 p 3 N87 10830 I CWI-NM-R86Ol I p 16 N87-10847 CORPORATE SOURCE Air Force Wright Aeronautical Labs., Wright-Patterson Central Bureau of Statistics. Voorburg (Netherlands). AFB, Ohio. Aviation statistics. 1984 Air Force technical objective document fiscal year I ISBN-90.357-0386-3 I p 18 N87-10851 1987 Centre dEtudes et de Recherches, Toulouse (France). Army Avlatlon Syatems Cominand. St. Louis, Yo. [AD-A167324 I p62 N87 10779 Report on tests of a CAST 10 airfoil with fixed transition 'T Army Aeromechanlca Lab., Moffen Field, Calif. in the T2 transonic cryogenic wind tunnel with self-adaptive Summary of artificial and r,aturai lclng tests conducted Helicopter impulsive noise Theoretical and walls on US Army aircraft from 1974 to 1985 experimental statu5 p 58 A87 11771 IRT-OA-63/16851 p 14 N87-10834 rIFAA/CT-85/26 I P25 N87-10064 Army Avlatlon Systems Command, St. Louis. Mo. Chiba Univ. (Japan). Summary of artificial and natural icing tests conducted Images 01 three dimensional flows in computer on US Army aircraft from 1974 lo 1985 graphics p 57 N87-10017 I FAA/CT-85/26 I p 25 N87 10064 Cincinnati Univ., Ohio. Engine-airframe integration for rotorcran Component Analysis of two-dimensional incompressible flow past specifications and qualification p 26 N87-10071 airfoils using unsteady Navier-Stokes equalions Engine-airframe integration for rotorcraft System I NASA-CR-I79823 I p 12 N87-10040 specifications and qualification p 27 N87 10074 Cirrus Computers Ltd.. Fareham (England). Investigation 01 optimal complexity of BITE and its effects B on reliability. maintainability. monitoring and fault prediction Blhrle Applied Research. Inc.. Jericho, N. V. I ETN-86-97976I p51 N87-11175 Low speed rotary aerodynamics of F-18 confiauration Civil Aviatinn Al?!hnr!!y, Rcdk!!! !Enp!snd!. Lls::qs I:: zdex are 2::anged aIphabet,ialIy Dy :h:s for 0 deg to 90 deg angle of attack. Test results and ADDlication of operational flight recording tn iorprate suurw The title of the document is used ana I y s is helicopters p 31 N87-10081 to provide a brief description of the subject matter I NASA-CR-3608I p 15 N87-10836 College of William and Mary, Wllliamsburg. Va. The page number and the accession number are Rotary balance data and analysis for the X-29A airplane Ouantitative thermal diffusivity measurements of fw an angle-of-attack range 01 0 deg to 90 deg composites p 45 A87-10750 included in each entry to assist the user in locating I NASA-CR-3747 I p 15 N87-10837 Committee on Appropriations (U. S. Senate). the abstract in the abstract section If applicable, Boeing Co.. Seattle, Wash. National Aeronautics and Space Administration a report number is also included as an aid in Numerical simulation of VISCOUS supersonic flow over p 61 N87-10774 a generic lighter configuration p6 A87-11509 Connecticut Univ.. Storrs. identifying the document Boelng Commercial Airplane Co., Seattle, Wash. Biaxial constitutive equation development Fault tolerant control laws p 53 N87-11217 I NASA-CR-178094I p 50 N87-10400 Boeing Military Airplane Development, Seattle, Wash. Cornell Univ., Ithaca, N.V. Vulnerability methodology and protective measures lor Analyses of broadband noise mechanisms of rotors aircraft fire and explosion hazards Volume 3. On-Board p 58 A87-11769 A Inert Gas Generator System (OBIGGS) studies Part I infrared emission lines from planetary nebulae OBIGGS ground performance tests p 62 N87-10791 [AD-At673571 p 26 N87-10066 Academy of Science8 (USSR), Moscow. British Aerospace Aircraft Group, Bristol (England). Computational aerodynamics of supersonic lifting A bibliography of aerodynamic heating references D vehicles p 12 N87-10030 I BAE-BT-13481 I p 14 N87-10832 Supersonic flow around tip sides of wings Prop-fan slipstream effects using static simulators Low Delta Air Lines, Inc , Atlanta. Ga. p 12 N87-I0033 speed task, phase 1 Guidance strategies for near optimum take off Advlsory Group !of Aerospace Research and 1 BAE-a59RiR-D/610il3496j p 37 ii6i-iO875 penormance in a windshear p24 A87 12138 Development, Neullly-Sur-Seine (France). International Conference - Superplasticityin Aerospace Deutsche Forschungs- und Versuchsanstalt fuer Luft- Engine-Airframe Integration for Rotorcraft Aluminium und Raumfahrt. Brunswick (West Germany). I AGARD-LS-148I p 26 N87-10067 I BAE-S85/AMR/0066 I p 42 N87-10994 Proceedings of the 13th Symposium on Aircraft Aeronautlcal Reaearch Inst. of Sweden, Stockholm. British Aerospace Aircraft Group, Warton (England). Integrated Data Systems Relevance of short fatigue crack growth data for Practical evaluation of wall pressure signature correction I DFVLR-MITT 86-04 I p 30 N87 10075 durability and damage tolerance analyses of aircraft methods in the 2 71-17x 2 tm low speed wind tunnel Performance monitoring of sensors in high reliable flight - c. .am ..nn. :FF" T?! :9% '3 ; y'"'. ~.YI-IlLcll I eHE-HfiG-LU4 I p .3/ Nl)/-lUl)/4 control systems using deterministic observers Aeronautical Research Labs., Melbourne (Australia), Brltish Aerospace Aircraft Group, Weybridge p32 N87 10087 Analysis of the vibration of the input bevel pinion in RAN (England). \ Comparative evaluation of redundant flight data Wessex helicopter main rotor gearbox WAK143 prior to Investigationinto the attenuation and velocity of acoustic recorded by a digital aircraft integrated data system failure emissions in carbon fiber composite aircraft structures recorder (DAR) on board an Airbus A-310 aircraft IARL-AERO-PROP-R-169 I p 25 N87-10061 I BAE-KGT-R-GEN-01349I p 41 N87-10180 p 33 N87 10098 Air Force Academy, Coio. The effects of temperature and loading rate on R-curves The high speed cascade wind tunnel Still an important Visualization of three-dimensional forced unsteady using the CLWL techniques lest facility for investigations on turbomachinery blades separated flow I BAE-MSM-R-GEN-0544I p 50 N87-10405 IDFVLR MITT 86 11 1 p 38 N87-10878 [AD-At68939 I p51 N87-11129 Brltish Airways, Heathrow (England). Digital data recording on floppy disks applied for Alr Force Armament Lab., Eglin AFB, Fh. Choosing Aircraft Integrated Data Systems (AIDS) on board use in helicopters Three-dimensional unsteady Euler equations solutions architecture suitable for Engine Health Monitoring (EHM) I DFVLR-MITl86 10 I p 51 N87 11149 on dynamic gnds on future generation engines p 31 N87-10083 Deutsche Forschungs- und Versuchsanstalt fuer Luft- IAD-Al68041I p 51 N87-11128 und Raumfahrt. Cologne (West Germany). A!. =,.,e !!'.-e:: $?=J=<:c=- kb., 2:GGk.G KB. Tex. Galvanic corrosion between carbon fiber reinforced Low-cost avionics simulation for aircrew training C plastics and metallic aeronautical materials IAD-A169198 I p 34 N87-10865 I DFVLR FB-86-16 I p 42 N87 11003 Air Force Inst. of Tech., Wright-Patterson AFB, Ohlo. California State Univ., Long Beach. Deutsche Forschungs- und Versuchsanstalt fuer Luft- Application of bifurcation and catastrophe theories lo Numerical and physical aspects of aerodynamlc flows und Raumfahrt. Goettingen (West Germany). near stall flight mechanics Ill. Proceedings of the Third Symposium California State Advanced method for computing the flow around wings I AD-At67697 I p 13 N87-10046 University Long Beach CA January 21 24 1985 with rear separation and ground effect Air Force Systems Command, Wright-Patterson AFB, p8 A87 11782 [OFVLR FB86 171 p50 N87 11017 Ohio. Canada Centre for Remote Sensing. Ottawa (Ontario). Deutsche Forschungs- und Versuchsanstalt fuer Luft- Acta Aeronautica et Astronautica Sinica (selected The C and Ku band Scatterometer results from Canadian und Raumfahrt. Oberpfaffenhofen (West Germany). articles) participation in the €SA PROMESS ocean measurement IC? accretion dependence on cloud physical [AD-A1679181 p3 N87-10004 campai g n p 55 N87-11252 parameters p 55 N87 11433

c- 1 Deutsche Forschungs- und Versuchsanstalt fuer Luft- CORPORA TE SOURCE

D.utsch. Fonchungv und Venuchunatalt her Lufl- General Dynamics Corp., Fort Worth, Tax. M und Raumfahrt, Weuellng (Wart Germany). Design and fabrication of the NASA decoupler pylon Experimentaland theoretical Doppler-lidar signatures of for the F-16 aircraft Maryland Unlv., College Park. aircraft wake vortices p 14 N87-10330 [NASA-CR-172354] p 25 N87-10065 Aeroelastic stability of composite rotor blades in hover kutsch. Luflhanu Aktlengemlllchafl. Frankfurt am bsign and fabrication of the NASA decoupler pylon p25 N87-1W0 Main (Weat Germany). for the F-16 aircraft, addendum 2 Maurchuwtta Inat of Tach., Cambridge. Software for flight recwder data processing developed [ NASA-CR-1724941 p 27 N87-10859 Potenbal impacts of advanced technologies on the ATC by Lufthansa p 32 N87-10090 Design and fabrication of the NASA decoupler pylon capacity of highdensity terminal areas Dwt.ch. Luflhanu A.G., Hamburg (Weat Germany). for the F-16 aircraft, addendum 1 [ NASA-CR-40241 p 22 N87-10854 Lufthansa's Aircrafl Integrated Data Systems (AIDS) [NASA-CR-l72355] p 27 N87-10860 Signal processing and interpretation using multilevel based A-31 0 engine condition monitoringsystem: Progress General Electric Co., Clnclnnatl, Ohlo. signal abstractlons achieved between the 121h and 13th AIDS Symposiums Free jet feasibility study of a thermal acoustic shield [ AD-A1691 661 p 57 N87-11513 p31 N87-10084 concept for ASTIVCE application: Duel stream nozzles Max-Planck-lnaWut fwr Stroemungafonchung, Deutschw Wetterdknat, Otlenbwh am Main (West [NASA-CR-38671 p 59 N87-10752 Goefflngen (Wont Germany). Vortex sheddingof a square cylinder in front of a slender 0.rm;mY). Free-jet acoustic investigation of high-radius-ratio Ice accretion calculations on cylindrical rods following airfoil at high Reynolds numbers Part 1 Spacing effect wannular plug nozzles the Bain model. and comparisonwith experimental results [ MPIS23l1 985 ] p 13 N87-10048 [NASA-CR-3818] p 59 N87-10753 (Fuchs. Schickel. Kaluze. Uwira. 1985) MswrochmM-Boeikow-Blohm G.m.b.H., Hamburg p56 N87-11434 General Electric Co., Fairfield, ann. (Wont Germany). Douglu Alrcnfl Co., inc., Long Beach, Calif. Effects of dacechemistry on hot corrosion life A-310 Ancraft Integrated Data Systems (AIDS) deslgn Numerical and physical aspects of aerodynamic flows p 43 N87-11193 philosophy p30 N87-10076 111; Proceedings of the Third Symposium, California State The 3D inelastic analysis methods for hot section Mesaenchmitt-Boslkow-BlohmG.m.b.H., Ottobrunn University, Long Beach, CA. January 21-24, 1985 components p 53 N87-11206 (West Germany). p8 A87-11782 Component specific modeling p 35 N87-11207 Expenewe mth the Onboard Checkout And Monitonng A comparison of interactive boundary-layer and Elevated temperature crack growth System (OCAMS) of a military aircraft resulting thin-layer Navier-Stokesprocedures p 8 A87.11785 p 53 N87-11214 improvements and the consequence for future design Critical joints in large composite aircrafl structure George Washington Unlv., Waahlngton, D.C. p 31 N87-10079 [NASA-CR-3710] p 41 N87-10973 Stochastic crack propagation with applications to Mltwblahl Heavy-lnduatrba Ltd., Tokyo (Japan). E€-10 composite vertical stabilizer ground test durability and damage tolerance analyses A descnption of a turbulent flow past a circular cylinder program [ AD-A1680401 p 53 N87-11226 by a discrete vortex method p 11 N87-10014 [ NASA-CR-3715) p 42 N87.10974 Georgia Inat of Tech., Atlanta. Critical composite joint subcomponents: Analysis and Numerical solution of the 3-dimensional boundary layer test results equations in the inverse mode using finite differences N [NASA-CR-3711] p 42 N87-10975 p 11 N87-10005 National Aeronautical Lab., Bangalore (India). Goldschmled (Fablo R.), Monroevllie, Pa. Effects of flap position on longitudinal parameters of E Wind tunnel test of the modified goldschmied model HFB-320 with propulsion and empennage: Analysis of test results [ NAL-TM-SE-86021 p 25 N87-10062 Energy Science Lab.., Inc., San Dlego, Callt. [ AD-A1673601 p 13 N87-10045 Tunnel interference from pressure measurements on Guidebook for analysis of tether applications Grumman Aerospace Corp., Bothpage, N.Y. control surfaces [NASA-CR-178904] p 38 N87-10169 Viscous wing theory development. Volume 1: Analysis. [AE-TM-843] p 37 N87-10104 Eurocontrol Agency, Bruueis (Belgium). method and results Effect of static inplane loads and boundary conditions The airlground transfer of aircraft integrated data [NASA-CR-178156] p 12 N87-10043 on the flutter of flat rectangular panels systems (AIDS) for Air Traffic Control (ATC) purposes: Viscous wing theory development. Volume 2: [NAL-TM-ST-8604] p 50 N87-10404 Present experiments and possible future intentions GRUMWING computer program user's manual National Aeronautlca and Spaen Admlnlatratlon, p 32 N87-10091 [NASA-CR-178157] p 13 N87-10044 Wamhlngton. D.C. European Space Agency, Paris (France). NASA and FAA launch wind shear research project Results of wind tunnel tests on external combustion [NASA-NEWS-REL86-143] p55 N87-10659 [ ESA-TT-959] p42 N87-10990 H Aeronautics and space report of the President [NASA-TM-892391 p 62 N87-10827 Hamilton Standard, Farmlngton, Conn. Aeronautical facilities assessment F Aircraft Integrated Data Systems (AIDS): Evolution and [NASA-RP-11461 p 37 N87-10876 NatlOMl AwoMutka and Space Admlnlstratlon. Amen Fairchild Weaton Systems, Inc., Snrasota. Fin. revolution p30 N87-10077 Hamilton Standard, Wlndsor Locks, Conn. Rerearch Center, MofIett Field, Callt. The Fairchild CVDR: A new combination voice and data Unsteady transonics of a wing with tip store recorder p 33 N87-10095 Effect of angular inflow on the vibratory response of a counter-rotating propeller p 4 A87-10524 Federal Aviation Admlnlatntlon, Atlantic City, N.J. [NASA-CR-174819] p 15 N87-10840 Computation of turbulent supersonic flows around Helicopter MLS Flight Inspection Project pointed bodies having crossflow separation [ DOT/FAA/CT-86/141 p2 N87-10002 p 5 A87-11487 Crashworthiness experiment summary full-scale I Numerical simulation of viscous supersonrc flow over transport controlled impact demonstration program a genenc fighter configuration p6 A87-11509 [DOT/FAA/CT-85/20] p 17 N87-10055 infonnatlca General Corp., Palo Alto, Callt. A simulation of rotor-stator interaction using the Euler The Boeing B 720 aircraft Controlled Impact Unsteady transonics of a wing with tip store equations and patched grids p7 A87-11536 Demonstration (CID): Flight data recorderlcockpit voice p4 A87-10524 Recent advances in aeroacoustics p 58 A87-11766

recorder experiment p 33 N87-10096 Iowa State Univ. of Science and Technology, Amen. Helicopter impulsive noise ~ Theoretical and An investiiation of the FAA vertical Bunsen burner Application of a potential code to general steady flows experimental status p 58 A87-11771 flammability test method in three dimensions p 50 N87-10262 A comparison of interactive boundary-layer and [WTlFAAlCT-86/22] p 42 N87-10985 thin-layer Navier-Stokes procedures p 8 A87-11785 Avgaslautogas comparison: Winter fuels K In-flight total forces, moments and static aeroelastic [ DOTlFAA-CT-86/21] p 43 N87-11014 characteristics of an oblique-wing research airplane [NASA-TP-22241 p 36 N87-10103 Fllght Data Co., London (England). Kansas Unlv.. Lawrence. Transonic flow analysis for rotors. Part 2 The impact of flight data on an airline: A case study An experimental investigation of dynamic ground Three-dimensional, unsteady, full-potentialcalculation p N87-10088 32 effect p 14 N87-10833 [ NASA-TP-23751 p 15 N87-10841 Florida Atlantic Unlv.. haRaton. Kanaaa Univ. Center for Rerearch, Inc., Lawrence. X-29A longitudinal and directional force and moment Toward comparing experiment and theory for Parametric analysis of a passive cyclic control device supplemental transonic wind tunnel test results corroborative research on hingeless rotor stability in for helicopters [ NASA-TM-85909I p 28 N87-10861 forward flight (an experimental and analytical investigation [NASA-CR-I66608] p 28 N87-10862 Flight-determinedaerodynamic derivatives of the AD-I of isolated rotor-flap-lagstability in forward flight) Kentron Intematlonal, inc., Hampton, Va. oblique-wing research airplane [NASA-CR-l79711] p 25 N87-10063 Numerical methods and a computer program for [ NASA-TP-22221 p36 N87-10871 Florida State Unlv., Talinha.wa. subsonic and supersonic aerodynamic design and analysis NatloMl AerOMUtIca and Space Admlnlatratlon. Recent advances in aeroacoustics p 58 A87-11766 Of wings with attainable thrust considerations Langley Research Center, Hampton, Va. On broadband shock associated noise of supersonic [NASA-CR-3808] p3 N87-10829 Euler equations analysis of the initial roll-up of aircraft jets p 58 A87-11768 wakes p4 A87-10522 Fmie Unlv.. Borlln (Want Germany). Quantitative thermal diffusivity measurements of The influence of weather-actbe fronts on visual flight L composites p 45 A87-10750 conditions 0 56 N87-11437 bar Siegkr, Inc., Grand Rapids, Mlch. The evolution of methods for noise prediction of high Data compression techniques for multifunction flight speed rotors and propellers in the time domain data recorders p33 N87-10094 p 58 A87-11770 G Operatingand support hazard analysis for self-contained Drag reducingouter-layer devices in rough wall turbulent navigation system LSI model 6216A. B and C. group B boundary layers p 8 A87-11890 Garrett Corp.. Phoenix, Adz. [AD-A169381] p 22 N87-10855 Laminar flow control for transport aircraft applications NASA dilution jet mixing, phase 3 p 53 N87-11202 LockhsabOeorgla Co., Marietta. p 24 A87-13021 Garrett Turbine Englne Co., Phoenix, Adz PTA test bed aircraft engine inlet model test report. Wind-tunnel investigation of the flight characteristics of Influence of engine variables on future helicopter revised a canard general-aviation airplane configuration systems p27 N87-10072 [ NASA-CR-I748451 p 35 N87-10866 [NASA-TP-26231 p12 N87-10039 c-2 CORPORA TE SOURCE Toulouse Univ. (France).

Spin-tunnel investigation of a 1125scale model of the Naval Air Test Center. Patuxent Rlver, Md. Aircraft noise measurement: The 1.2 metre microphone General Dynamics F-16XL airplane United States Navy - Canadian Forces solid state flight height saga [ NASA-TM-856601 p 12 N87-10041 data recorderlcrash position locator expenment on the [ PNR-90315] p60 N87-11578 Supersonic. nonlinear, attached-flow wing design for 8-720 controlled impact demonstration Cost effective single crystals high lift with experimental validation p33 N87-10097 [ PNR-903191 p60 N87-11615 INASA-TP-23361 p12 N87-10042 Nlelwn Englnoerlngand Rewarch. Inc., Mountain Development of single crystal alloys for specific engine Doppler Radar Detection of Wind Shear view, cam. applications [ NASA-CP-24351 p 17 N87-10054 Development of a turbomachinery deslgn cptimizatmn [PNR-903201 p60 N87-11616 procedure using a multiple-parameter nonlinear Prediibon of hellcopter rotor discrete frequency noise: ROlls-ROyCe Ltd., Watford (England). perturbabon method A computer program incorporating realistic blade motions Impact of IPS and IRS configurations on engine [NASA-CR-3831 I p2 N87-10003 and advanced acoustic formulation installation design p26 N87-10070 [NASA-TM-87721] p59 N87-10750 Prediction of gust loadings and alleviation at transopic Effects of tail span and empennage arrangement on speeds [ AD-A1677481 p13 N87-10047 drag of a typical single-enginefighter aft end Nord-Mlcro Elektmnlc Feinmechanlk G.m.b.H., S [ NASA-TP-23521 p 15 N87-10838 Frankfort (West Germany). Static internal performance of single-expansion-ramp Modern Aircraft Integrated Data Systems [AIDS] Sikorsky Aircraft, Stratford, Conn. nozzles with thrust-vectoring capability up to 60 deg technology exetnplhed on the A-320 p 30 N87-10078 Engine-airframe integration considerations for [ NASA-TP-23641 p 15 N87-10839 North Carolina State Unlv., Ralebh. preliminary air vehicle performance analysis Piloted simulation study of the effects of an automated Euler equations analysis of the initial roll-up of aircraft p26 N87-10068 trim system on flight characteristics of a light twin-engine wakes p4 A87-10522 Flight service evaluation of composite helicopter airplane with one engine inoperative Notre Dame Unlv., Ind. components [ NASA-TP-26331 p16 N87-10843 Expenmental study of the boundary layer on a low [ NASA-CR-1781491 p 41 N87-10182 Ground-based time-guidance algorithm for control of Reynolds number airfoll in steady and unsteady flow Soclete de Fabrlcatlon dlnetrumenta de Mesure. airplanes in a time-meteredair traffic control environment: p 14 N87-10052 Mauy (France). A piloted simulabon study The Airborne Integrated Data System [AIDS) for the [NASA-TP-2616] p 34 N87-10864 Airbus A-310 engine condition monitoring Interference effects of thrust reversing on horizontal tail 0 p31 N87-10082 effectiveness of twin-engine fighter aircraft at Mach Soclete Nationale Industriello Aerospatlale, MarlgMne numbers from 0.1 5 to 0.90 Old Dominion Unhr.. Norfolk, Va. (France). [ NASA-TP-23501 p 36 N87-10870 Finite element computations for high speed 30 inviscid Helicopter air intake protection systems flows p7 A87-11542 Natlonal AOrOMUtks and Admlnlstratlon. Lewis p27 N87-10073 Space Graduate engineering research participation in Research Center, Cleveland. Ohio. Societe NatloMle Industriello Aero.paW.le, Toulouw aeronautics Fiber-reinforced superalloy composites provide an (France). [NASA-CR-179798] p3 N87-10828 added performance edge p39 A87-12647 Efficiency of various control surfaces in steady and Response of a small-turboshaft-engine Compression unsteady flow system to inlet temperature distortion P [SNIAS-861-111-101] p 37 N87-10872 -...e. I..nn-rccr Llunon- I wl-oI),”lr, p 35 NR7-10100 Southern Methodlst Unlv., Dallas, Tax. Testing of VH-6CA helicopter transmission in NASA Pennayfvanla State Unlv., Unlveralty Park. A !%^nn!ro!lzyl !e??l!.!nlara_nt apprnach to estimation in Lewis 2240-kW (3000-hp) facility An expenmental investigation of end-wall iiowiield uf & m?ll!i-Sensor navigation systems p 21 N87-10057 [ NASA-TP-26261 p50 N87-10391 compressor rotor p 50 N87-10244 Southwest Rewarch Inst., Sen Antonlo. Tex. Turbine Engine Hot Section Technology, 1984 Phlllps Zentrallaboratorium G.m.b.H., Hamburg (West Constitutive modeling for isotropic materials [ NASA-CP-23391 p52 N87-11180 Germany). p 53 N87-11211 Combustion overview p 43 N87-11181 A system theoretical based method for module falure Stanford Unlv.. Callf. diagnostic of turbine engines p35 N87-10085 Surface protection p 43 N87-11182 Computation of transonic separated wing flows using Plsa Unlv. (Italy). an Euler/Navier Stokes zonal approach Fatigue and fracture: Overview p 52 N87-11183 Engie-transmissmn-structural airframe members p 16 N87-10849 Host turbine heat transfer overview compatibility p26 N87-10069 p52 N87-11184 Separationof airborne and structurebornenoise radiated Pk.uy Co. Ltd., Havant (England). by plates constructed of conventional and composite Laser anemometers of hot-sectionapplications Inlegrated monltonng systems for tactical aircraft p 52 N87-11187 materials with applications for prediction of interior noise p 31 N87-10080 paths in propeller driven aircraft p 60 N87-11579 Evaluation results of the 700 deg C Chinese strain Pop. (L D.), Woodland& Tax. Sundstrand Data Control, Inc., Redmond, Wash. gages p 52 N87-11189 Propeller aircraft intenor noise model utilization study Data recovery techniques. an update Coating life prediction p 43 N87-11194 and validation p32 N87-10089 Introduction to life modeling of thermal barrier [ NASA-CR-1724281 p 60 N87-11576 coatings p 43 N87-11195 Pralt and Whltney Alrcraft, East Hartford, Conn. Sverdrup Technology, Inc., Arnold Alr FomStatlon, Aerothermal modeling program. phase 2 Development of heat flux sensors in turbine airfoils Tenn. p 35 N87-11200 p 52 N87-11186 Large perturbation flow field analysis and simulation lor Flame radiation p 43 N87-11204 Thermal barrier coating life prediction model supersonic inlets Natlonal Aerospace Lab., Amsterdam (Netherlands). development p 52 N87-11199 [ NASA-CR-1746761 p 14 N87-10835 Unsteady airload computations for airfoils oscillating in Coolant passage heat transfer with rotation. a progress attached and separated compressible flow report p 53 N87-13225 [ NLR-MP-85040-U] p 16 N87-10846 Prlnceton Unlv., N. J. T Correlation between flight Simulation and processing of Optimal flight paths through microburst mnd profiles flight tests based on inertial measurements p 35 A87-10519 Technlsche HOchschuIe, Aachen (West Germany). [ NLR-MP-85058-UI p 28 N87-10863 Products Research and Chemical Corp., Glendale. Wind shear measurement on board a MORANE 893 Corrosion and corrosion prevention in aircraft calif. p31 N87-10086 structures Polymer systems for rapid sealing of aircraft structures Technlsche Unlv., Brunswick (West Germany). [ NLR-MP-8502Y-U1 p 4; i.467-i ;so4 a1 iow iernpar,siuor Investigationson a digital bit synchronizer for a detailed ^^ .In- .*Ann Fatigue fracture in steel landing gear components [ AD-A1676671 p 41 N87-10209 flight data recovery p 90 I”o,-IvvII [ NLR-MP-850504] p 54 N87-11233 Technlsche Unlv., Hanover (West Germany). Real time debugging software package for flight Statistics of wind shear due to nocturnal boundary layer simulator software system with variable labeled COMMON R jet airstreams in North Germany p 56 N87-11461 blocks Tennessee Unlv., Knoxville. [ NLR-MP*85013-U] P 57 N87-11530 Radio Technlcal Commlulon for Aeronautics, A study of the flow field about an upper surface blown National Oceanlc and Atmospherlc Admlnlstmtlon, Washlngton, D. C. wing and its effects on longitudinalstatic stability of a small Boulder. Colo. Minimum operational performance standards for jet airplane p 11 N87-10009 Surface measurements of gust fronts and microbursts airborne ILS glide slope receiving equipment operating Texas Unlv., Austln. during the JAWS [Joint Airport Weather Studies) Project: within the radio frequency range of 328.6-335.4 MHz Unsteady flow over an airfoil inside a wind tunnel with Statistical results and implicationsfor wind shear detection, [ RTCAIDO-1921 p 21 N87-10853 and without transpiration p 13 N87-10051 prediction and modeling Rlce Unlv., Houaton, Tex. Textron. Inc., Itvine, Calif. [ PB86-2008471 P55 N87-10665 Guidance strategies for near-oplimum take-off Technology review of flight crucial flight control systems Yz?!n?lz!T!a?lrp?rhtim %few Board. Washinaton. D. performance in a windshear p 24 A87-12138 [application of optical technology) C. Rockwell Internatlonal Corp., Loa An&eS, CGK :?.!A.c.A.cp.372?n7! D 36 N87-10102 Aircraft accident reeport. mltaAir Lines, Inc., Lockheed Supersonic second order analysis and optimization Tokyo Unlv. (Japan). L-1011-385-1. N726DA. Dallas/Fort Worth International program user’s manual Study of three-dimensionalseparation on a spheroid at Airport, Texas, August 2. 1985 [NASA-CR-172342] p 15 N87-10842 incidence p49 N87-10016 [PB86910406] p 17 N87-10053 RoII.-Royce Ltd., Derby (England). Report of the InternationalSymposium on Computational Aircraft accident reports: Brief format US civil and foreign Future aero-engine control systems. why FADEC? Cost. Fluid Dynamics, Tokyo p49 N87-10029 aviation. issue number 2 of 1985 accidents design cycle timescale. reliability. weight and size targets Numerical and experimental study of dynamics of [PB86-916916] p 17 N87-10056 [PNR-90298] p 35 N87-10867 two-dimensional body Flight recorders: New US regulations and new Engine performance monitoring for airlines [ ISAS-6191 p 59 N87-10748 International Civil Aviation Organization [ICAO) [PNR-90305] p35 N87-10868 Toulou~Unlv. (France). standards p 32 N87-10093 Net shape forming: The route to low cost components. Airborne measurement methods applied to the National Transportation Safety Board safety The view point of the aerospace industry determination of boundary conditions at the sea surface: recornmendation p 18 N87-10852 [PNR-90306] p 51 N87-11020 The TOSCANE experiment p 55 N87-11242

c-3 Trans World Airlines, Inc., Kansas City, Mo. CORPORA TE SOURCE

Trans World Alrllnea. Inc.. Kanus Clty, Mo. Airline data acquisition in an ACARS environment p32 N87-10092 U

Unlted Technologies Cop., Eaat HaMord, COnn. Hot section viewing system [ NASA-CR-1747731 p 51 N87-11144 Unlted Technologlea Reuarch Center. East Hartford, Conn. High temperature static strain gage program D 52 N87-11188 Measurement of airfoil heat transfer -coefficients on a turbine stage p 53 N87-11221 Unlverslty Coll. of Swanua (Walaa). Recent developments in FEM-CFD p 5 A87-11411 V

Vlgyan ReMarch AaaocIatea. Inc., Harnpton, Va. Stress analysis of Pathfinder-2 models [ NASA-CR-I724581 p 51 N87-11179 Vlrglnla Polytechnic Inst. and Slate Unlv., Blackaburg. Analysis of the vortical flow around a 60 deg Delta wing with vortex flap p 11 N87-10006 The effect of free stream disturbances and control surface deflections on the performance of the Wortmann airfoil at low Reynolds numbers p 11 N87-10007 Energy management of 3-dimensional minimum-time intercept p 27 N87-10858 An experimental investigation of the interior noise control effects of propeller synchrophasing [NASA-CR-178185] p60 N87-11577

c-4 FOREIGN TECHNOLOGY INDEX

A ERON A UTIC AL .ENGINEE R ING / A Continuing Sibliography (Supplement 270) February 1987

Typical Foreign Technology Index Listing Developments at ARL to meet future Australian needs Efficiency of various control surfaces in steady and in aeronautics p2 A87-13017 unsteady flow Analysis of the vibration of the input bevel pinion in RAN [SNIAS-861-lll-101 I p 37 N87-10872 Wessex helicopter main rotor gearbox WAK143 prior to Airborne measurement methods applied to the failure determination of boundary conditions a1 the sea surlace [ ARL-AERO-PROP-R-I69 I p 25 N87-10061 The TOSCANE experiment p 55 N87-11242 COUNTRY OF INTELLECTUAL ORIGIN B G GERMANV,FEDERAL REPUBLIC OF BELGIUM The air/ground transfer of aircraft integrated data Ground and flight tests of Tornado reconnaissance pod p 22 A87-10940 AUSTRALIA systems (AIDS) for Air Traffic Control (ATC) purposes Fire occurring and expanding in connection with oils in Reaction to aircraft noise in residential areas around Present experiments and possible future intentions aviation p 16 A87-11368 rAuStrailan airwrts 0 54 A87-10116 p 32 N87-10091 Maneuver optimization in the case of combat aircraft p 35 A87-11369 C Laser remote sensing procedures provide an aid lo aviation during the approach for landing CANADA p 19 A87-11370 Stochastic modelling of radar returns Properties and processing of fiber-reinforced p 18 A87-10143 polyetheretherketone (PEEK) p 38 A87-11372 The C and Ku band scanerometer results from Canadian Conference on Numerical Methods in Fluid Mechanics participation in the €SA PROMESS ocean measurement 6th. Goeningen. West Germany, September 25-27. 1985. campaign p 55 N87-11252 Proceedinqs p 47 A87-11501 CHINA, PEOPLES REPUBLIC OF Applicallon 01 a 2D time-marching Euler code to Numerical analysis with generalized J-integral transonic turbomacninery flow p6 A87-11516 p 47 A87-11492 Experiences with an unfactored implicit predictor-corrector method p 47 A87-11522 Liskngs in this index are arranged alphabetically by Calculation of boundary layer of a three dimensional S-shaped inlet p6 A87-11495 Implicit finite-difference Simulation of separated country of intellectual origin The title of the Transonic cascade flow solved by shock-capture hypersonic flow over an indented nosetipp 7 A87-11533 document is used lo provide a brief description of computation followed by separate-regioncomputation with Calculation of strong viscouslinviscid interactions on the subject matter The page number and the shock fining p 10 A87-12956 An experimental study on large negative incidence airfoils by zonal solutions of the Navier-Stokes equations accession number are included in each entry to separated flow in two-dimensional turbine cascades p7 A87-11540 1 assist the user in locating the citation in the abstract p 10 A87-12957 A split-matrix method for the integration of the section A quasi-three-dimensional method for diagonal flow quasi-conservative Euler-equations p 7 A87-11544 fans p 11 A87-I2958 Experimental investigations of three-dimensional A test research for improving the performance of V type laminar boundary layers on a slender delta wing flameholder used in an afterburner p 34 A87-12965 p9 A87-I2145 Acta Aeronautica et Aslronaulica Sinica (selected A laminar boundary layer method for flows in planes articles) of symmetry and application to inclined ellipsoids of A [ AD-A167918 I p 3 N87-10004 revolution p9 A87-12146 Theoretical treatment of gust simulation in the wind AUSTRALIA tunnel p9 A87-12148 Reaction to aircraft noise in residential areas around F On the occurrence of regular reflection of shocks in Australian airports p 54 A87 10116 concave corner flows p 10 A87 12586 Comparison of the effectiveness of measures of aircraft FRANCE Vortex shedding of a square cylinder in front of a slender Implicit and semi implicit methods lot the compressible riuibe exposure by using social survey data airfoil at kjh9eywlds lumbers Part 1 Spacing effect Navier-Stokes equations p 47 A87-11503 p54 A87 10117 [MPlS 23/1985] p 13 N87 10048 Case study of Royal Australian Air Force P38 Orion Dirigibles . For what7 p23 A87 11661 Proceedings of the 131h Symposium on Aircraft aircraft ground oxygen fire incident p 16 A87-10866 The methodology and tools for processing radar data Integrated Data Systems p 19 A87-11662 Laser airborne depth sounding in Australia [ DFVLR-MI--86-04 I p 30 N87 10075 Polar navigation assisted by satellite p 30 A87-12677 A 310 Aircraft Integrated Data Systems (AIDS) design Joint National Symposium on the Influence of Aviation p 20 A87-11663 philosophy p 30 N87 10076 Aernnniilical mini#farii#rer+reniiirements lnr new I....+.-...I"- L*.C.BH ,,.+$FB+$5 pB,= s:'8'"me(b'pm) UI ~olyllleelllly call6 Lite FuLu#+!Vi ~~IulldUllLb111 MUblrdlld. Melbourne, Australia. August 8. 9. 1985. Preprints and malerials p 38 A87 11791 technology exerrplified on the A 320 p 30 N87-10078 Supplementary Papers p 1 A87-13001 Aeronautical research spin-oIIs on the development of Experience with the Onboard Checkout And Monitoring The influence of aerospace developments upon civil applications for aluminium alloys p 48 A87-It792 System (OCAMS) of a military aircraft resulting developments in manufacturing p 1 A87-13002 Transformation of a plane uniform shock into cylindrical improvements and the consequence for future design Computer integrated manufacturing or spherical uniform shock by wall shaping p31 N87 10079 p 37 A87 12585 p 49 A87-13003 Lufthansa s Aircraft Integrated Data Systems (AIDS) Manufacture of bonded composite assemblies for Certification problems for composite airplane based A 31 0 engine condition monitoring system Progress structures p39 A87 12652 aircraft p 1 A87-13005 achieved between the 12th and 13th AIDS Symposiums Advances in the vibration monitoring of gears and rolling Disturbances brought by atmospheric statics to airborne p 31 N87-10084 element bearings p 49 A87-13007 navigation and communication systems A system theoretical based method for module failure Condition monitoring of large commercial turbofan p 20 A87-12678 diagnostic of turbine engines p 35 N87-10085 engines p 34 A87-13008 The evolution of air transport aircraft flight deck Wind shear measurement on board a MORANE 893 New materials in gas turbine technology p 30 A87 12888 p 31 N87-10086 p 41 A87-13009 Interference of the aeronautical navaids (frequency band Performance monitorina of sensors in hiah reliable fliaht Advanced fibre composites and other new materials for iuu.iiu MMZ) rrom FM oroaocasling service (uu-IUU control systems using deterministic observers airframe applications p 41 A87-13010 MHz) p 21 A87-12690 p 32 N87 10087 Data processing and calibration for an airborne Structural design with new materials Software for flight recorder data processing developed scanerometer p 30 A87 12694 p 49 A87-I3011 by Lufthansa p32 N87 10090 Helicopter air intake protection SyslemS The future operations and procurement of rotary wing p 27 N87 10073 Comparative evaluation of redundant flight data aircraft in the Royal Australian Navy p 2 A87-13012 The Airborne Integrated Data System (AIDS) for the recorded by a digital aircraft integrated data system Future developments and manufacturing at GAF Airbus A-310 engine condition monitoring recorder (DAR) on board an Airbus A 310 aircraft p2 A87-I3013 p 31 N87-10082 p 33 N87-10098 Future developments and manulacluring at C A C Reporf on tests of a CAST 10 airfoil with fixed transition Investigations on a digital bit synchronizer for a detailed P2 A87-13014 in the T2 transonic cryogenic wind tunnel with self adaptive flight data recovery p 33 N87-10099 The future of international air transport walls Experimental and theoretical Doppler-lidar signatures of P2 A87-13016 [ RT-OA-63/16851 p 14 N87 10834 aircraft wake vortices p 14 N87 10330

D-1 FOREIGN TECHNOLOGY INDEX

The high speed cascade wind tunnel: Still an important N Fundamentals of navigation according to geophysical test facility for investigations on turbomachinery blades fields p 19 A87-11337 [ DFVLR-MITT-66-11] p 38 N87-10878 NETHERLANDS Scientific problems of aviation and space: History and Results of wind tunnel tests on external combustion Computationsof separated subsonic and transonic flow present state p 62 A87-11339 [ ESA-TT-9591 p42 N87-10990 about airfoils in unsteady motion p 8 A87-11786 Methods of in-flight aerophysical studies Galvanic corrosion between carbon fiber reinforced Transition to new systems and international p 23 A87-11343 perspectives p A87-11806 plastics and metallic aeronautical materials 20 A reinforcing band near the flange of a heated cylindrical Progress in advanced materials and processes: [DFVLR-FB-ffi-lG] p42 N87-11003 caslng p 48 A87-12445 Durability. reliability and quality control; Proceedings of the Advanced method for computing the flow around wings Induced drag of a curved wing p 10 A87-12805 with rear separation and ground effect Sixth International European SAMPE Conference. Scheveningen. Netherlands, May 28-30. 1985 Similarity law for the supersonic flow past flat surfaces [ DFVLR-FB-ffi-t7] p50 N87-11017 p 39 A87-12651 with intense distributed injection p 10 A87-12843 Digital data recording floppy disks applied for on Unsteady airload computations for airfoils oscillating in Fractographic aspects of the cyclic fracture toughness on-board use in helicopters attached and separated compressible flow of 35KhN3MFA steel in vacuum, air, and hydrogen [ DFVLR-MITT-86-10] p 51 N87-11149 [ NLR-MP-85040-U] p 16 N87-10846 p 40 A87-12882 Ice accretion dependence on cloud physical Euler flow solutions for a transonic wind tunnel section The possibility of the nondisturbing motion of a body parameters p 55 N87-11433 [CWI-NM-R86Ol] p 16 N87-10847 in a fluid p 48 A87-12894 Ice accretion calculations on cylindrical rods following Aviation statistics, 1984 A method for calculating the susceptibility of jet fuels the Bain model. and comparison with experimental results [ ISBN-90-357-0386-31 p 18 N87-10851 to smoking p 40 A87-12901 (Fuchs, Schickel. Kaluza. Uwira, 1985) Conelation between flight simulation and processing of Thickened oils p 40 A87-12902 p 56 N87-11434 flight tests based on inertial measurements Computational aerodynamics of supersonic lifting The influence of Weather-aCtNe fronts on visual flight [ NLR-MP-85058-UI p 28 N87-10863 vehicles p 12 N87-10030 conditions p 56 N87-11437 Corrosion and corrosion Drevention in aircraft Supersonic flow around tip sides of wings Statistics of wind shear due to nocturnal boundary layer structures p 12 N87-10033 jet airstreams in North Germany p 56 N87-11461 [NLR-MP-85029-U] p43 N87-11004 UNITED KINGDOM GERMANV,PEOPLES DEMOCRATIC REPUBLIC OF Fatigue fracture in steel landing gear components Specification of gas turbine disc forgings The classification of wind shears from the point of view . [NLR-MP-85050-U] p 54 N87-11233 p 44 A87-10121 of aerodynamics and flight mechanics Real time debugging software package for flight Forging of blades for gas turbines p 44 A87-10124 p 24 A87-11898 Simulator software system with variable labeled COMMON Military aeronautical satellite communications Dynamic flight optimization p 24 A87-11899 blocks p 18 A87-10137 Theoretical aspects and practical questions regarding [NLR-MP-85013-U] p 57 N87-11530 Palmdale and the bomber connection the assurance of flight safety p 17 A87-11900 p 22 A87-10574 Yakovlev Forger p 22 A87-10575 I P Nondestructive inspection of composite structures by low-velocity impact p 45 A87-10765 POLAND Recent developments in FEM-CFD p 5 A87-11411 INDIA Testing of Fe-Cu-base ablative composites. II A pre-processed implicit algorithm for 3D viscous A higher order beam element for vibration of beams p 41 A87-12971 wth discontinuities p 46 A87-10898 compressible flow p6 A87-11510 Natural frequency analysis of compressor rotor blades Numerical experiments with a total variation diminishing p 34 A87-10899 S (TVD) MacCormack Scheme p6 A87-11526 Natural frequency analysis of pretwisted plates Nonlinear acoustic propagation of broadband noise p46 A87-10900 SWEDEN p 58 A87-11773 Superplasticity in aeroengine titanium alloy VT-9 and Decay of end effects in graphite/epoxy bolted joints The prediction of the drag of aerofoils and wings at its modified compositions p39 A87-12096 p 44 A87-10115 high subsonic speeds p9 A87-12266 Effects of flap position on longitudinal parameters of Vortex-stretched flow around a cranked delta wing An exact integral (field panel) method for the calculation HFB-320 D3 A87-10520 of twodimensional transonic potential flow around [ NAL-TM-SE-8602] pi5 N87-10062 Single or dual pod concepts for tactical complex configurabons p9 A87-12267 Tunnel interference from pressure measurements on reconnaissance p 29 A87-10939 The lateral dynamic stability and control of a large control surfaces Integrated logistics for reconnaissance systems receiver aircraft dunng air-to-air refuelling [AE-TM-8-83] p 37 N87-10104 p 61 A87-10942 p 36 A87-12268 Effect of static inplane loads and boundary conditions Euler solutions on 0-0gnds around wings using local High speed flow visualisation p 48 A87-12648 on the flutter of flat rectangular panels refinement p6 A87-11512 In-service environmental effects on carbon fibre [ NAL-TM-ST-86041 p 50 N87-10404 Numerical experiment with inviscidvortex-stretched flow composite material p 39 A87-12659 ITALY around a cranked delta wing, supersonic speed Improved durability airline paint schemes Expenmental investigation on the performances of a p 7 A87-11537 p40 A87-12660 transonic turbine blade cascade for varying incidence How to maintain a consistent quality in your bonding The balance between theoretical, computational and angles p9 A87-12205 process? p 48 A87-12656 experimental work in turbomachines p 49 A87-13015 Monitonng of terminal flight phases environment Relevance of short fatigue crack growth data for Resonant and non-resonant acoustic properties of Observations and models p 55 A87-12679 durability and damage tolerance analyses of aircraft elastic panels. I - The radiation problem Automated functions for air baffic control systems [FFA-TN-t986 231 p 54 N87-11231 p 49 A87-13026 p 21 A87 12687 SWITZERLAND Impact of IPS and IRS configurations on engine A new concept in air traffic control - The multi-radar JAS39 Gripen - A Swedish solution to a multi-role installation design p26 N87-10070 tracking (MRT) p 21 A87-12689 need p 23 A87-11798 Integrated monitoring systems for tactical aircraft Engine-transmission-structural airframe members Avionics in the sub-microscopic world p31 N87-10080 compatibility p26 N87-10069 p48 A87-11800 Applicabon of operational flight recording to helicopters p3t N87-10081 Choosing Aircraft Integrated Data Systems (AIDS) J U architecture suitable for Engine Health Monitoring (EHM) on future generation engines p31 N87-10083 JAPAN U.S.S.R. The impact of flight data on an airline: A case study A study on the axially Curved mixed-flow vaneless A numerical analysis of supersonic bottom flow with p 32 N87-10088 diffusers p47 A87-11481 thermal modification of the wake p 3 A87-10409 Investigationinto the attenuation and velocity of acoustic Numerical solution of the Euler equations using rational The mechanics of dynamically tunable gyroscopes emissions in carbon fiber composite aircraft structures Runge-Kuna method p 7 A87-11538 p 57 A87-10444 [ BAE-KGT-R-GEN-01349I p 41 N87-10180 Expansion of flow due to resistance of a wire gauze Density field of a viscous gas jet issuing from a conical The effects of temperature and loading rate on R-curves placed in a parallel-sided channel p 48 A87-12133 nozzle into vacuum p4 A87-10603 using the CLWL techniques Unsteady drag over cylinders and aerofoils in transonic Method of meridional sections in problems involving a [BAE-MSM-R-GEN-05441 p 50 N87-10405 shock tube flows p 10 A87-12617 three-dimensional boundary layer p 4 A87-10609 A bibliography of aerodynamic heating references Navigation and environment; Proceedings of the Fifth Excitation of the natural oscillations of a boundary layer [BAE-BT-13481I p 14 N87-10832 International Congress, Tokyo, Japan, October 1-5. 1985 by an external acoustic field p4 A87-10610 Future aero-engine control systems, why FADEC? Cost. p 20 A87-12676 Numerical investigation of supersonic flow past design cycle timescale. reliability, weight and size targets Characterizing height keeping error distribution based spike-tipped blunt bodies p4 A87-10614 [PNR-90298] p 35 N87-10867 on indirect observation p 17 A87-12683 Conical wing of maximum lift-todrag ratio in a supersonic Engine performance monitoring for airlines Flight experiments on MLS elevation guidance gas flow p4 A87-10615 [PNR-903051 p 35 N87-10868 p 21 A87-12686 Calculation of unsteady supersonic flow past a plane Practical evaluation of wall pressure signature correction A description of a turbulent flow past a circular cylinder blade row under the effect of vortex inhomogeneities in methods in the 2.7m x 2.lm low speed wind tunnel by a discrete vortex method p 11 N87-10014 [BAE-ARG-2041 p 37 N87-10874 the oncoming flow p5 A87-10618 Study of three-dimensionalseparation on a spheroid at Prop-fan slipstream effects using static simulators: Low Mathematical modeling of separated flow past a wing incidence p 49 N87-10016 speed task, phase 1 profile and aerodynamic hysteresis p 5 A87-10619 Images of three dimensional flows in computer [ BAE-B59R/R-D1610113498] p 37 N87-10875 graphics p57 N87-10017 Optimal control of viscous flow at high Reynolds International Conference - Superplasticity in Aerospace Report of the InternationalSymposiurnonComputational numbers p 5 A87-10620 Aluminium Fluid Dynamics. Tokyo p49 N87-10029 Motion of a gas in a duct behind a moving body [BAE-S85/AMR/0066] p 42 N87-10994 Numerical and experimental study of dynamics of p5 A87-10675 Net shape forming: The route to low cost components. twodimensonal body Damping of the vibrations of deformable bodies The view point of the aerospace industry IISAS-6191 p 59 N87-10748 p 47 A87-11336 [PNR-90306] p 51 N87-11020 D-2 FOREIGN TECHNOLOGY INDEX UNITED KINGDOM

Investigationof optimal complexityof BITE and its effects on reliability. maintainability. monitoring and fault prediction [ ETN-86-979761 p 51 N87-11175 Aircraft noise measurement: The 1.2 metre microphone height saga [ PNR-903151 p60 N87-11578 Cost effective single crystals [ PNR-903191 p60 N87-11615 Development of single crystal alloys for specific engine applications IPNR-903201 p60 N87-11616

D-3 CONTRACT NUMBER INDEX

A ER 0N A UTlCA L ENGINEE R ING / A Continuing Bibliography (Supplement 270) February 1987

Typical Contract Number Index Listing

NCCl 84 P4 A87-10522 NCCP 175 P 28 N87-10862 NCC2-361 P 25 N87-10063 NAG1-472 p 22 N87- 10854 NGL 31-001 252 P 35 A87-10519 NGR-47-003-052 P3 N87-10828 NSF ECS-84-07285 P 57 N87-11513 NSF MEA-80 18565 P8 A87-11783 NSF MEA-81 15330 P 46 A87-11113 NSF MEA-84 04862 P 46 A87-11112 N00014-81 K-0742 P 57 N87-11513 NASA CONTRACT N00014-84-K 0741 P5 A87-11117 NUMBER NE??% NO0167 81 C 0075 P 13 N87-10045 1 1 1 1 1 NUMBER 1 N87-10047 N00167-83-C 01 14 P 13 N62269-81 C-0741 P 41 N87-10209 W-7405 ENG-82 P 45 A87-10732 P 45 A87-10768 Listings in this index are arranged alpha- 505-31 38 P 59 N87-10753 numerically by contract number Under eactl 505-31-53 P 51 N87-11179 505 32-6A P 35 N87-10100 contract number, the accession numbers denoting 505 33-43-07 P 25 N87-10065 documents that have been produced as a result of P 27 N87-10859 research done under that contract are arranged in P 27 N87-10860 N87-10752 ascending order with the AlAA accession numbers 505-40 74 P 59 505-40 90 01 P 15 N87-10838 appearing first The accession number denotes the 505-42-11 P 15 N87-10841 nturnher hy whirh the ritatian is identified in the P 28 N87-10862 abs!rac! sec!iw Preced!ng !he accessm number 505-43-13 01 P 12 N87-10041 P 15 N87-10836 is the page number on which the citation may be P 15 N87-10837 found 505 43 23-02 P 12 N87-10042 505 43-23-10 P3 N87-10829 505 43 42 P 14 N87-10835 AF AFOSR-0160-80 p 12 N87 10040 505 43-44 P 36 "37-10103 A93811362 p 41 N87-10180 P 36 N87-10871 A93Bl1391 p 50 N87 10405 505 43-90-07 P 15 N87-10839 DAAG29-83-K-0146 p 10 A87 12616 505 43-97 07 P 36 N87-10870 DOTIFAAICT-85128P p33 N87 10096 505-45 33 02 P 22 N87-10854 DRET-83-403 p47 A8711503 505-45-43 01 P 12 N87-10039 DTFA03-80-A 00199 p25 N87 10064 505-45-73-01 P 36 N87-10102 F09603 85-C-1224 p22 N87 10855 505 60-01 01 P 12 N87-10043 F33615-78-C-2063 p 26 N87-10066 P 13 N87-10044 F33615 81 C 5002 p 45 A87-10728 505 61-41 01 P 16 N87-10843 p45 A87 10730 505 62-51 P 50 N87-10391 F33615 82-C-3007 p4 A87 10523 505 66 41 31 P 17 N87-10054 F33615 82 C-5020 p45 A87 10732 533 02 81 P 28 NR7-10861 F33615-83-C-3215 p3 A87 10517 533 04 1A P 51 N87-11144 F33615-83-C 5026 p40 A8712928 P 52 N87-11180 F33615 83-K-3226 p 53 N87 11226 534 04 13 52 p 34 N87- 10864 F33657-81-C-0210 p44 A87 10720 535 03 11 01 P 59 N87-10750 F49620 79 C 0224 p 8 A87 12052 235 03 11 03 p 50 Ne?-17577 F61-542 p41 N87 10209 535 03 12 P 35 N87-10866 NAGW-478 p5 A87 11411 NAG1 390 p 60 N87 11577 NAG1-465 p 12 N87 10040 NAG1-472 p 22 N87 10854 NAG 1-516 "f:: A87 12138 h!Ar;? +C!q Ag7 3 37E.e r -- NASl 14869 p42 N87 10974 NASl 15820 p 15 N87 10842 NASl-1 6000 p 3 N87 10829 NASl 16114 p51 N87 11179 NASl 16205 p 15 N87 10836 p 15 N87 10837 NAS1-16857 p41 N87 10973 p42 N87 10975 NASl.16858 p 12 N87 10043 p 13 N87 10044 NASl-16879 p25 N87 10065 D27 N87 10859 P 27 N87-10860 NASl-1 7281 P 60 N87.11576 NAbl-17296 P8 A87-11890 NAS1-17403 P 36 N87-10102 NAS1-17635 P 50 N87-10400 NAS3-20619 P 59 N87-10753 NAS3 20836 P2 N87-10003 NAS3-22137 P 59 N87-10752 NAS3-23156 P 51 N87-11144 NAS3-23682 P 14 N87-10835 NAS3-23926 P 43 N87-11193 NAS3-24222 P 15 N87-10840 NAS3-24339 P 35 N87-10866 NAS8-35499 D 38 N87- 10169

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 210) February 1987

Qplcal Report Number Index Listing

,-, ,-, -, BAE-S85/AMR/0066 ...... p 42 N87-10994 # FRG-82-1 ...... p 13 N87-10045 # REPORT BR97093 ...... p50 N87-10405 # FTD-ID(RS)T-OlG9-86...... p 3 N87-10004 # NUMBER ...... p 41 N87-10180 # -- I-, I 88667020 ...... p28 N87-10863 # GPO-495-812 ...... p 62 N87-10827 * # A-9682 P 15 N87-10841 t B8667024 P 57 N87-11530 # ...... H-1179 ...... p 36 i- I 88667275 ...... D 43 N87-11004 # N87-10871 * # 88667670 ...... p 16 N87-10847 # H-1 181 ...... p 36 N87-10103 * # N87-10846 # H-1257 ...... p 28 N87-10861 * # N87-11233 # N87-10748 # CWI-NM-R8601 ...... p 16 N87-10847 # ISBN-90-357-0366-3 ...... p 18 N87-10851 # DERAT-6I5019-DN ...... p 14 N87-10834 # ISBN-92-835-1529-3 ...... p 26 N87-10067 # Listings in this index are arranged alpha- ISSN-0168-552X ...... p 18 N87-10851 # numerically by report number. The page number DFVLWFB-85-35 ...... p 42 N87-10990 # N87-11003 # ISSN-017-1342 ...... p 50 N87-11017 # indicates the page on which the citation is located. DFVLR-FB-86-17 ...... p 50 N87-11017 # ISSN-0171-1342 ...... p 42 N87-11003 # The accession number denotes the number by ISSN-0176-7739 ...... p 30 N87-10075 # which the citation is identified. An asterisk (*) DNLR-MITT-86-04 ...... p 30 N87-10075 # ISSN-0176-7739 ...... p 38 N87-10878 # ISSN-0176-7739 ...... p 51 N87-11149 # indicates that the item is a NASA report. A pound DFVLR-MITT-86-10 ...... p 51 N87-11149 # DFVLR-MITT-86-11 ...... p 38 N87-10878 # ISSN-0285-6808 ...... p 59 N87-10748 # sign (C) indicates that the item is available on ISSN-0436-1199 ...... p 13 N87-10048 # microfiche. DOTIFAA-CT-86I21 ...... p 43 N87-11014 # JBEISB-443.524185 ...... p 37 N87-10872 # DOTIFAAICT-85/20 ...... p 17 N87-10055 # DOTIFAAICT-86I14 ...... p 2 N87-10002 # KU-FRL-568-1 ...... p 28 N87-10862 ' # A-9682 ...... p 15 N87-10841 * # DOTIFAAICT-86122 ...... p 42 N87-10985 # L-15616 ...... p 12 N87-10041 * # ACEE-26-TR-3074 ...... p 42 N87-10975 * # DP-7266 ...... p 41 N87-10973 * # L-15742 ...... p 15 N87-10838 * # DP-7269 ...... p 42 N87-10974 * # L-15766 ...... p 15 N87-10839 * # N87-10042 ' # AD-A167324 ...... p 62 N87-10779 # DTNSRDCIASED-CR-01-66 ...... p 13 N87-10047 # N87-10870 ' # AD-A167357 ...... p 28 N87-10066 # DTNSRDCIASEDCR-02.86 ...... p 13 N87-10045 # L-15929 ...... p 12 N87-10039 * # AD-A167360 ...... p 13 N87-10045 # 1-16116 ...... p 34 N87-10864 * # AD-A167667 ...... p 41 N87-10209 # D180-28882-VOL-3-PT-1 ...... p 26 N87.10066 # L-16130 ...... p 59 N87-10750 * # ADA167697 ...... p 13 N87-10048 # L-16147 ...... p 16 N87-10843 * # AD-A167748 ...... p 13 N07-10047 # €2177 ...... p 59 N87-10753 * # AD-A167918 ...... p 3 N87-10004 # LGBSER0012-REV p E-2198 ...... p N87-10100 * # ...... 35 N87-10866 * # AD-A168040 ...... p 53 N87-11226 # 35 E-2267 ...... p 52 N87-11180. # AD-Al68041 ...... p 51 N87-11128 # MPIS-23I1985 13 E-2392 ...... p 59 N87-10752 * # ...... p N87-10048 # AD-A168124 ...... p 3 N87-10830 # AD-A168939 p 51 E-2941 ...... p 50 N87-10391 * # ...... N87-11129 # NAG€-85158-60 ...... P 41 N87-10209 AD-A169166 ...... p 57 N87-11513 # ESA-l-r-959 ...... p 42 N87-10990 # AD-A169198 ...... p 34 N87-10865 # NAL-TM-SE-8602 ...... P 25 N87-10062 AD-A169381 ...... p 22 N87-10855 # ETN-86-97139 ...... p 37 N87-10872 # ETN-86-97857 ...... p 54 N87-11231 # NAL-TM-ST-8604 ...... P 50 N87-10404 AD4301301 ...... p 51 N87-11128 # ETN-86-97943 ...... p 37 N87-10874 # ETN-86-97944 ...... p 37 N87-10875 # NAS 1.15:85660 ...... P 12 N87-10041 AE-TM-8-83 ...... p37 N@7-10104 # ETN-86-97945 ...... p 42 N87-10994 # NAS 1.15:85909 ...... P 28 N87-10861 ETN-86-97946 ...... p 50 N87-10405 # NAS 1.1587721 ...... P 59 N87-10750 AFATL-TR-86-21 ...... p 51 N87-11128 # ETN-86-97947 ...... p 41 N87-10180 # NAS 1.15:89239 ...... P 62 N87-10827 ETN-86-97948 p 14 NAS 1.26:166608 ...... P 28 N87-10862 AFHRL-TR-85-38 ...... p 34 N87-10865 # ...... N87-10832 # ETN-86-97976 ...... p 51 N87-11175 # NAS 1.26:172332 ...... P 36 N87-10102 NAS 1.26172342 ...... P 15 N87-10842 . r... *,.I ,.,n "e c .I ETN-86-98015 ...... p 35 N87-10867 # nr, I ,"I, 8.0 >-uv-- I ...... v"'0 ?!E? !Elf. y NAS 126: 172354 .- t I N-UO-MC I6 ...... p 35 ::0:-:3ese ff ...... P 25 N87-10065 ETNgS-98017 ...... p 51 N87-11020 # NAS 1.26:172355 ...... P 27 NB I-1UBW AFWAL-TR-84-4000 ...... p 62 N87-10779 # NAS 1.26172428 ...... D60 N87-11576 AFWAL-TR-85-2060-V-3-PT-1 ...... p 26 N87-10066 # ETN-86-98020 ...... p 60 N87-11578 # ETN-86-98021 p N87-11615 # NAS 1.26:172458 ...... p 51 N87-11179 ' # AFWAL-TR-85-3062 ...... p 53 N87-11226 # ...... 60 ETN-86-98022 p 60 N87-11616 # NAS 1 .26:172494 ...... p 27 N87-10859 * # AFWAL-TR-85-4000 ...... p 62 N87-10779 # ...... ETN-86-98074 ...... p 18 N87-10851 # NAS 1.26:174676 ...... p 14 N87-10835 * # 174773 ...... p 51 N87-11144 * # AGARD-LS-148 ...... p26 N87-10067 # ETN-86-98176 ...... p 30 N87-10075 # ETN-86-98178 ...... p 51 N87-11149 # 174819 ...... p 15 N87-10840 * # NAS 1.26174845 ...... p 35 N87-10886 * # AR-004-049 ...... p25 N87-10061 # ETN-86-98179 ...... p 38 N87-10878 # ETN-86-98184 ...... p 42 N87-11003 # NAS 1.26178094 ...... p 50 N87-10400 ' # AR-3 ...... p 41 N87-10182 * # ETN-86-98221 ...... p 13 N87-10048 # NAS 1.26:178149 ...... p 41 N87-10182 * # NAS 1.26178156 ...... p 12 N87-10043 * # ARL-AERO-PROP-R-169 ...... p 25 N87-10061 # ETN-86-98245 ...... p 42 N87-10990 # ETN-86-98276 ...... p 50 N87-11017 # NAS 1.26:178157 ...... p 13 N87-10044 * # ETN-86-98489 ...... p 57 N87-11530 # NAS 1.26:178185 ...... p 60 N87-11577 * # ASME PAPER 86-WAIAPM-23 .... p 46 A87-11113 # NAS 1.26:178904 ...... p 38 N87-10169 * # ASME PAPER 86-WAIAPM-33 .... p 46 A87-11112 # ETN-8698490 ...... p 43 N87-11004 # ETN-86-98491 ...... p 16 N87-10846 # ?!.L.S !.2c:!787!! ...... p 3s NR7-10063 * # NAS 1.26:179798 ...... p 3 N87-10828 * # BAE-AERO-INFORM-33 ...... p 14 N87-10832 # ETN-86-98492 ...... p 54 N87-11233 # ETN-86-98493 ...... p 28 N87-10863 # NAS 1.26179823 ...... p 12 N87-10040 ' # ETN-86-98505 ...... p 16 N87-10847 # NAS 1.263608 ...... p 15 N87-10836 * # BAE-ARG-204 ...... :...... p37 N87-10874 # NAS 1.263710 ...... p 41 N87-10973 ' # FAAICT-85126 ...... p 25 N87-10064 # NAS 1.263711 ...... p 42 N87-10975 * # BAE-BT-13481 ...... p 14 N87-10832 # NAS 1.263715 ...... p 42 N87-10974 * # FAAIPMgSl31 ...... p 17 N87-10054 * # NAS 1.263747 ...... p 15 N87-10837 # BAE-859RlR-DI610113498 ...... p 37 N87-10875 # NAS 1.263808 ...... p 3 N87-10829 * # NAS 1.263818 ...... p 59 N87-10753 * # FFA-TN-1986-23 p BAE-KGT-R-GEN-01349 ...... p 41 N87-10180 # ...... 54 N87-11231 # NAS 1.269831 ...... p 2 N87-10003 * # NAS 1.263867 ...... p 59 N87-10752 * # BAE-MSM-R-GEN-0544 ...... p 50 N87-10405 # FJSRL-TJ-86-0007 ...... p 51 N87-11129 # NAS 1.26:4024 ...... p 22 N87-10854 #

F- 1 NAS 1.2683765 REPORT NUMBER INDEX

NAS 1.26:83765 ...... p 35 N87-10100 * # PNR-90319 ...... p 60 N87-11615 # NAS 1.55:2339 ...... p 52 N87-11180 * # PNR-90320 ...... p 60 N87-11616 # NAS 1,552435 ...... p 17 N87-10054 * # NAS 1.60:2222 ...... p 36 N87-10871 * # P 37 N87-10875 # NAS 1.60:2224 ...... p 36 N87-10103 * # NAS 1.609336 p 12 N87-10042 # RE-725-VOL-1 ...... p 12 N87-10043 * # NAS 1.60:2350 ...... p 36 N87-10870 * # RE-726-VOL-2 ...... p 13 N87-10044 * # NAS 1.60:2352 ...... p 15 N87-10838 * # NAS 1.60:2364 ...... p 15 N87-10839 * # REPT-6216-019 ...... p 22 N87-10855 # NAS 1.60:2375 ...... p 15 N87-10841 * # REPT-84-001 ...... p 60 N87-11576 * # NAS 1.60:2616 ...... p 34 N87-10864 * # NAS 1.60:2623 ...... p 12 N87-10039 * # RT-OA-63/1685 ...... p 14 N87-10834 # P 50 N87-10391 * # P 16 N87-10843 * # RTCA/W-132A-REV ...... p 21 N87-10853 # NAS 1.61:1146 ...... p 37 N87-10876 * # RTCAIDO-192 ...... p 21 N87-10853 #

NASA-CP-2339 ...... p 52 N87-11180 * # R83AEB574 ...... p 59 N87-10753 * # NASA-CP-2435 ...... p 17 N87-10054 * # R84-925830-33 ...... p 51 N87-11144 * #

NASA-CR-166608 ...... p 28 N87-10862 * # SER-510237 ...... p 41 N87-10182 * # NASA-CR-172332 ...... N87-10102 * # NASA-CR-172342 ...... N87-10842 * # SNIAS-861-111-101 ...... p 37 N87-10872 # NASA-CR-172354 ...... p 25 N87-10065 * # NASA-CR-172355 ...... p 27 N87-10860 * # SPIE-561 ...... p 18 A87-10931 # NASA-CR-172428 ...... N87-11576 * # NASA-CR-172458 ...... N87-11179 * # P 57 N87-11513 # NASA-CR-172494 ...... p 27 N87-10859 * # P 25 N87-10064 # NASA-CR-174676 ...... p 14 N87-10835 * # NASA-CR-174773 ...... p 51 N87-11144 * # USAAVSCOM-TR-84-C-13 ...... p 35 N87-10100 * # NASA-CR-174819 ...... p 15 N87-10840 * # NASA-CR-174845 ...... p 35 N87-10866 * # NASA-CR-178094 ...... p 50 N87-10400 ' # NASA-CR-178149 ...... p 41 N87-10182 * # NASA-CR-178156 ...... p 12 N87-10043 * # NASA-CR-178157 ...... p 13 N87-10044 * # NASA-CR-178185 ...... p 60 N87-11577 * # NASA-CR-178904 ...... p 38 N87-10169 * # NASA-CR-179711 ...... p 25 N87-10063 * # NASAGR-179798 ...... p 3 N87-10828 * # NASA-CR-179823 ...... p 12 N87-10040 * # NASA-CR-3608 ...... p 15 N87-10836 * # NASA-CR-3710 ...... p 41 N87-10973 * # NASA-CR-3711 ...... N87-10975 * # NASA-CR-3715 ...... N87-10974 * # NASA-CR-3747 ...... p 15 N87-10837 * # NASA-CR-3808 ...... p 3 N87-10829 * # P 59 N87-10753 * # NASA-CR-3831 ...... p 2 N87-10003 * # NASA-CR-3867 ...... p 59 N87-10752 * # NASA-CR-4024 ...... p 22 N87-10854 * #

NASA-NEWS-REL-86-143 ...... p 55 N87-10659 * #

NASA-RP-1146 ...... p 37 N87-10876 * #

NASA-TM-83765 ...... p 35 N87-10100 * # NASA-TM-85660 ...... p 12 N87-10041 * # NASA-TM-85909 ...... p 28 N87-10861 * # NASA-TM-87721 ...... p 59 N87-10750 * # NASA-TM-89239 ...... p 62 N87-10827 * #

NASA-TP-2222 ...... p 36 N87-10871 * # NASA-TP-2224 ...... p 36 N87-10103 * # NASA-TP-2336 ...... p 12 N87-10042 * # NASA-TP-2350 ...... p 36 N87-10870 * # NASA-TP-2352 ...... p 15 N87-10838 * # NASA-TP-2364 ...... N87-10839 * # NASA-TP-2375 ...... N87-10841 * # NASA-TP-2616 ...... p 34 N87-10864 * # NASA-TP-2623 ...... p 12 N87-10039 * # NASA-TP-2626 ...... p 50 N87-10391 * # NASA-TP-2633 ...... p 16 N87-10843 * #

NEAR-TR-295 ...... p 2 N87-10003 * # NEAR-TR-352 ...... p 13 N87-10047 #

NLR-MP-85013-U ...... p 57 N87-11530 # NLR-MP-85029-U ...... p 43 N87-11004 # NLR-MP-85040-U ...... p 16 N87-10846 # P 54 N87-11233 # NLR-MP-850584 ...... p 28 N87-10863 #

NOM-TM-ERL-WPL-135 ...... p 55 N87-10665 #

NTSBIAAB-86/16 ...... p 17 N87-10056 #

NTSB/AAR-86/05 ...... p 17 N87-10053 #

PB86-200847 ...... p 55 N87-10665 # PB86-910406 ...... p 17 N87-10053 ff PB86-916916 ...... p 17 N87-10056 #

PNR-90298 ...... p 35 N87-10867 # PNR-90305 ...... p 35 N87-10868 # PNR-90306 ...... p 51 N87-11020 # PNR-90315 ...... p 60 N87-11576 # ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 270) February 1987

Typical Accession Number Index Listing

A87-10524 ' # P 4 A87-11770 * X p 58 A87-12957 X PlO N87-10089 # p32 A87-11771 'X p58 A87-12958 X p 11 N87-10090 W p32 A87-11773 # p58 A87-12965 X p 34 N87-10091 X p32 A87-12971 X p41 A87-11776 # p23 N87-10092 X p32 A87-12995 # p59 N87-10093 X p32 A87-11779 # p56 A87-12996 # P59 N87-10094 X p33 A87-11780 X p23 A87-13001 # PI N87-10095 X p33 A87-11781 X p 23 A87-13002 # P 1 A87-11782 * X p 8 N87-10096 X p33 NUMBER SPONSORED MICROFICHE NUMBER A87-13003 Cy p49 N87-10097 # p33 Rpqmm A87-11783 X p 8 A87-13005 W pl mm(xqm N87-10098 p33 X A87-11785 * X p 8 A87-13007 W p49 N87-1N99 # p33 A87-11786 X p 8 A87-13008 # P34 N87-10100 '# p 35 A87-11791 X p 38 A87-13009 W p41 N87-10102 '# p A87-11792 X p 48 A87-13010 W p41 36 N87-10103 '# p 36 A87-11798 # p 23 A87-13011 W p49 N87-10104 X p37 A87-11800 X p 48 A87-13012 # p2 Listings in this index are arranged alphanumerically N87-10169 'X p 38 A87-11801 # P 1 A87-13013 # p2 N87-10180 # p41 by accession number. The page number listed to A87-11802 X p 1 A87-13014 # P2 N87-10182 'X p 41 the right indicates the page on which the citation A87-11804 # p61 A87-13015 W p49 N87-10209 X p41 AB7-11805 # p6l A87-13016 W p2 is located. An asterisk (*) indlcates that the item Is N87-10244 # p50 A87-11806 # p20 A87-13017 W p2 N87-10262 # p50 a NASA report. A pound sign (#) indicates that the A87-11807 # P20 A87-13021 '# P 24 N87-10330 '# p 14 item is available on microfiche. A87-11843 # p48 A87-13026 # p49 A87-11844 X p 39 N87-10391 'X p 50 N87-10400 '# p 50 A87-11848 # p 24 N87-10002 # p2 N87-10404 # p50 A87-11890 'W p 8 N87-10003 'X P2 N87-10405 # p50 A87-11898 It p24 N87-10004 # P3 Ng7.1E5Q 'd 9 55 A87-11899 X p24 N87-10005 # p 11 N87-10865 # D55 A87-10047 P 18 A87-10935 # p28 A87-11900 I p17 N87-10006 X P 11 X N87-10748 # p59 A87-10936 # P29 A87-12052 # p 8 N87-10007 X p 11 A87-10115 X P44 N87-10750 # p 59 A87-10937 # P29 A87-12082 # p 36 N87-10009 X p 11 A87-10116 # P54 N87-10752 * # p 59 A87-10939 # P29 A87-12096 # p39 N87.10014 X Pll A87-10117 # p54 N87-10753 * # p 59 A87-10940 # P22 A87-12133 X p48 N87.10016 # P49 N87-10774 # P61 A87-10121 X P44 A87-10941 X P23 A87-12138 'X P 24 N87-10017 # P57 N87-10779 # p62 A87-10124 # p44 A87-10942 # P61 A87-12145 X P9 N87-10029 # P49 N87-10791 # p62 A87-10137 X Pl8 A87-10943 # P29 A87-12146 X p9 N87-10030 # p 12 N87-10827 * W p 62 A87-10143 X Pl8 A87-10944 # PI8 A87-12148 X p 9 N87-10033 # p 12 N87-10828 * # p 3 A87-10293 W P57 A87-10947 # PI8 A87-12205 X p9 N87-10039 ' # P 12 N87-10829 * # p 3 A87-10294 W p38 A87-10948 # PI9 A87-12211 X p56 N87-10040 * # p 12 N87-10830 # p3 A87-10409 X p3 A87-10949 # p19 A87-12212 X P29 N87-10041 '# p 12 N87-10832 C p 14 A87-10444 X P57 A87-10950 # P29 A87-12217 X P57 N87.10042 * # P 12 N87-10833 # p 14 A87-10508 X p6l A87-10971 # P46 A87-12218 # P29 N87-10043 '# P 12 N87-10834 # p 14 A87-10509 X p6l A87-11061 # PI9 A87-12266 X P 9 N87-10044 '# p 13 N87-10835 *# p 14 A87-10510 X p61 A87-11112 # P46 A87-12267 X P9 N87-10045 I p13 N87-10838 '#. p 15 A87-10516 X p44 A87-11113 X p46 A87-12268 X P36 N87-10046 W p 13 N87-10837 'I p 15 A87-10517 X p3 A87-11117 P5 A87-12445 # P48 N87-10047 # p 13 X N87-10838 W p 15 A87-10519 * X P 35 A87-11127 X p46 A87-12585 # P37 N87-10048 W p 13 N87-10839 '# p 15 A87-10520 X P3 A87-12586 # P 10 N87-10051 P 13 A87-11336 # P47 W N87-10840 'C p 15 A87-10521 X p4 A87-12616 # P 10 N87-10052 # p 14 A87-11337 # PI9 N87-10841 *# p 15 A87-10522 'X p 4 A87-12617 W P 10 N87-10053 # P 17 A87-11339 # p62 N87-10842 'W p 15 A87-10523 # p4 A87.12646 W P37 N87-:0054 'X p !7 A87-11343 # p23 N87-10843 '# p 16 A87-10524 * # p 4 A87-12647 ' W P 39 N87-10055 P 17 A87-11368 # p16 X N87-10846 # p16 A87-10525 # p4 A87-11369 # p35 A87-12648 X p48 N87-10056 # P 17 A87-10574 # p22 A87-11370 # PI9 A87-12649 X p24 N87-10057 # P21 A87-10575 # P22 A87-11372 # P38 A87-12650 X P 24 N87-10060 X p25 N87-10851 # p 18 A87-10603 # P4 A87-11411 *# P5 A87-12651 X P 39 N87-10061 W p25 N87-10852 # p 18 A87-10609 # p4 A87-11481 # P47 A87-12652 X P39 N87-10062 # A87-10610 # P4 ,,-.Am7.iOCCP .---- + PAR .mnv ann=* * Y N87-10853 # p21 A87-11487 '# P 5 I."#-I"""" I, r -- N87-1W54 .R P 22 A87-10614 W p4 A87-11492 # P47 A87-12659 X P 39 N87-10064 Cy P25 N87-10855 # p22 A87-10615 W P4 A87-11495 p 6 A87-12660 X P40 N87-10065 * X P 25 X N87-10858 # p27 A87-10618 X P5 A87-11501 X P47 A87-12661 X P40 N87-10066 # p26 N87-10859 * X p 27 A87-10619 X P5 A87-11503 # P47 A87-12667 X P 40 N87-10067 X p26 N87-10880 'I P27 A87-10620 # P5 A87-11509 ' P 6 A87-12676 # P 20 N87-10068 # P26 X N87-10861 'X p 28 A87-10675 X p5 A87-12677 X P 30 N87-10069 p26 A87-11510 X p6 X N87-10862 * # p 28 A87-10720 X p44 A87-12678 X P 20 N87-10070 # P% A87-11512 X p6 N87-10863 # p28 A87-10721 X P44 A87-11516 # p6 A87-12679 # P 55 N87-10071 # p 26 N87-10864 * # p 34 A87-10727 X P44 A87-12680 # P21 N87-10072 # p27 A87-11522 X P47 N87-10865 # p34 A87-10728 X P45 A87-12683 X P 17 N87-10073 # p 27 A87-11526 X p6 N87-10886.R p35 A87-10730 # P45 A87-12684 W P21 N87-10074 # p 27 A87-11528 X P6 N87-10867 # p 35 A87-10732 X p45 A87-11533 # P 7 A87-12685 # P21 N87-10075 # p30 N67-10868 # p35 A87-10750 X 045 A87-11536 '# p7 A87-12686 # P21 N87-10076 # p30 AA7-1076.5 # 045 N87-10870 * # P 36 b*,,,E17 +! p7 A87-12687 # p21 N87-10077 W p30 ..". . .--. NR7-1M171 * # D 36 A87-10768 X p45 A87-12EU8 R P.36 N87-10078 # P30 A87-11536 # p7 N87-10872 # p 37 A87-10791 X p45 A87-12689 X p21 N87-10079 # P31 A87-11540 X p7 N87-10874 # p37 A87-10859 # p38 A87-12690 X P21 N87-10080 P31 A87-11542 * X p 7 # N87-10875 # p37 A87-10866 X p 16 A87-12694 X p30 N87-10081 P31 A87-11544 # P7 X N87-10876 * # p 37 A87-10867 X p46 A87-12805 X P 10 N87-10082 # P31 A87-11661 X p 23 N87-10878 # p38 A87-10879 X p56 A87-11662 X P 19 A87-12843 X P 10 N87-10083 W p31 A87-10898 # p46 N87-10973 * # p 41 A87-11663 # p 20 A87-12882 X P% N87-10084 # p31 A87-10899 # p34 A87-12894 P48 N87-10974 * # p 42 X N87-10085 # p35 A87-10900 X p46 A87-11664 X P 20 A87-12901 X p40 N87-10975 * # p 42 A87-10931 X p 18 A87-11766 'X P58 A87-12902 X P40 N87-10086 X p31 N87-10985 # p42 A87-10933 X p 28 A87-11768 'X P 58 A87-12928 X p 40 N87-10087 X p32 N87-10990 # p42 A87-10934 W p28 A87-11769 '# p 58 A87-12956 # p 10 N87-10088 X P32 N87-10994 # p42 G-1 ACCESSION NUMBER INDEX N87-11003

N87-11003 # P42 N87-11004 # P43 N87-11014 # P43 N87-11017 # P50 N87-11020 # P 51 N87-11128 # p51 N87-11129 # p51 N87-11144 * # p 51 N87-11149 # p51 N87-11175 # P 51 N87-11179 * # P 51 N87-11180 *# p52 N87-11181 '# P43 N87-11182 '# P 43 N87-11183 * # p 52 N87-11184 * # p 52 N87-11186 * # p 52 N87-11187 * # p 52 N87-11188.X p52 N87-11189 * # p 52 N87-11193 '# P43 N87-11194 '# P43 N87-11195'# P43 N87-11199'# p52 N87-11200'# P35 N87-11202'# P53 N87-11204'# P43 N87-11206 * # P 53 N87-11207.d P35 N87-11211 '# P53 N87-11214 '# p 53 N87-11217 '# P 53 N87-11221 * # P 53 N87-11225 * # P 53 N87-11226 # P 53 N87-11231 # P 54 N87-11233 # p 54 N87-11242 # p55 N87-11252 # p 55 N87-11433 # p55 N87-11434 # p56 N87-11437 # p56 N87-11461 # p56 N87-11513 # p57 N87-11530 # p 57 N87-11576 * # p 60 N87-11577 '# p60 N87-11578 # P 60 N87-11579 # p 60 N87-11615 # p60 N87-11616 # p60 AVAILABILITY OF CITED PUBLICATIONS

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