Aero Nautical E Ng I N E E R I Ng

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NASA SP-7037(234)

AERO NAUTICAL ENG I N E E R ING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 234)

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 December 1988 in

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

Scientific and Technical Information Division 1989 National Aeronautics and Space Administration Washington, DC This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A08. INTRODUCTION

This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 539 reports, journal articles and other documents originally announced iii December 1988 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, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, 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 respective announcement journals. The IAA item:; will precede the STAR items within each category Seven indexes -- subject, personal author, corporate source, foreign technology, contract number, report number, and accession number -- are included. An annual cummulative index will be published.

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

iii TABLE OF CONTENTS

Page Category 01 Aeronautics (General) 783

Category 02 Aerodynamics 785 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 801 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 802 Includes digital and voice communication with aircraft; air navigation systems (satellite and ground based); and air traffic control.

Category 05 Aircraft Design, Testing and Performance 803 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 813 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 81 5 Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and onboard auxiliary power plant:; for aircraft.

Category 08 Aircraft Stability and Control 826 Includes aircraft handling qualities: piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 832 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 836 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles: space transportation; space communications, spacecraft communications, command and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft propulsion and power.

Category 11 Chemistry and Materials 837 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.

PRECEDING PAGE BLANK NOT FILMED Category 12 Engineering 844 Includes engineering (general); communications and radar; electronics and electrical engineering; fluid mechanics and heat transfer; instrumentation and photography; lasers and masers; mechanical engineering; quality assurance and reliability; and structural mechanics.

Category 13 Geosciences Includes geosciences (general); earth resources and remote sensing; energy production 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 857 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 861 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics.

Category 17 Social Sciences 862 Includes social sciences (general); administration and management; documentation and information science; economics and cost analysis; law, political science, and space policy; and urban technology and transportation.

Category 18 Space Sciences N.A. Includes space sciences (general); astronomy; astrophysics; lunar and planet- ary exploration; solar physics; and space radiation.

Category 19 General 862

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

vi TYPICAL REPORT CITATION AND ABSTRACT

NASASPONSORED 1 ON MICROFICHE ACCESSION NUMBER -N88-10026'# National Aeronautics and Space Administration -CORPORATE SOURCE Ames Research Center, Moffett Field. Calif TITLE- HIMAT FLIGHT PROGRAM: TEST RESULTS AND PROGRAM ASSESSMENT OVERVIEW AUTHORS- DWAIN A DEETS, V MICHAEL DEANGELIS, and DAVID P LUX PUBLICATION DATE -Jun 1986 30 p H- AVAILABILITY SOURCE REPORT NUMBERS- (NASA-TM-86725, H-1283, NAS 1 15 86725) Avail NTlS HC PRICE CODE- AO3/MF A01 CSCL 01C 4 COSATI CODE The Highly Manueverable Aircraft Technology (HiMAT) iwogram consisted of design, fabrication of two subscale remotely piloted research vehicles (RPRVs). and flight test This technical memorandum describes the vehicles and test approach An overview of the flight test results and comparisons with the design predictions are presented These comparisons are macle on a single-discipline basis, so that aerodynamics, structure,:, flight controls, and propulsion controls are examined one by one The interactions between the disciplines are then examined, with the conclusions that the integration of the various techiologies contributed to total vehicle performance gains An asses!;ment is made of the subscale RPRV approach from the standpoint of research data quality and quantity. unmanned effects as compared with manned vehicles. complexity. and cost It is concluded that the RPRV technique, as adopted in this program, resul ed in a more complex and costly vehicle than expected but is reasonable when compared with alternate ways of obtaining comparable results Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT ON MICROFICHEI ACCESSION NUMBER- A88-lW95k TITLE -SYNTHESES OF REDUCEDORDER CONTROLLERS FOR ACTIVE FLUlTER SUPPRESSION AUTHORS- ATSUSHI FUJlMORl and HlROBUMl OHTA Japan Society for tJOURNAL TITLE Aeronautical and Space Sciences. Journal (ISSN 0021-46163). vol. 35. no. 402, 1987, p. 353-362. In Japanese, with abstract in English. refs Reduced-order controllers for active flutter suppreseion of a two-dimensional airfoil are studied using two design approaches. One is based on the generalized Hessenberg representaticin (GHR) in the time domain, and the other, called the Nyquist frequency approximation (NFA). is a method in the frequency domain. In the NFA method, the reduced-order controllers are designed so that the stability margin of the Nyquist plot may be increasd over a specific frequency range. To illustrate and to make a coinparison between the two methods, numerical simulations are carried out using a thirteenth-order controlled plant. It is to be noted that the GHR method can yield quasi-optimal controllers in the !sense of minimizing quadratic performance indices. The designed controllers, however, do not have enough stability margin, and the order reduction resulting from full state controllers may not be satisfactory. On the other hand. reduced-order controllws in. the NFA method can be descgned with increased stability margin at the expense of the performance index. For all simulation cases, the NFA method yields secondorder controllers with 'm better stability margin than those by the GHR method. Thus, the NFA method provides an effective method for synthesizing robust reduceduder controllers. Author

vii 1 AERONAUTICAL $9 i ENGINEERING A Continuing Bibliography (Suppl. 234)

I JANUARY 1989 t

01 3.0-cruise SST is evaluated, with a view to the development schedule and initial operating date into which the maturity of various AERONAUTICS (GENERAL) essential technologies will translate. Attention is given to the effect of advanced aerodynamic, propulsion, structural and subsystem technologies on takeoff gross weight. A dramatic impact IS noted to result from the combination of prospective technological advances in flow laniinarization, advanced structures and materials, etc. O.C. A88-53757# YA-7F - A TWENTY YEAR ECONOMIC LIFE EXTENSION AT A88-53771# + COSTS WE CAN AFFORD A. R. RUDNICKI, JR. and J. W. MAYNOR, JR. (LTV Aerospace SOVIET APPLICATIONS FOR HYPERSONIC VEHICLES and Defense Co., Aircraft Modernization and Support Div., Dallas, REUBEN F. JOHNSON (General Dynamics Corp., Fort Worth, TX) TX) AIAA, AHS, and ASEE, Aircraft Design, Systems and AIAA, AHS, and ASSEE,Aircraft Design, Systems and Operations Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 10 p. Meeting, Atlanta, GA, Sept. 7-9, 1988. 20 p. refs (AIAA PAPER 88-4460) (AIAA PAPER 88-4507) The USAF requirement for an interim close air An assessment is made of the prospective uses of a Soviet support/battlefield air interdiction aircraft that will be survivable in hypersonic transport (HST) aircraft, in both the near and longer mediumlhigh-threat arenas of the late 1990s. using largely term. It is suggested that the primary purpose of an HST might off-the-shelf technologies, is presently answered through a variant be to serve as a large sensor platform for naval reconnaissance of the A-7D Corsair II attack aircraft. The upgrading of the A-7D that would be capable of supplementing satellite coverage in areas proposed encompasses the addition of an afterburning engine, of momentarily exceptional interest with great flexibility and celerity. aerodynamic refinements, and state-of-the-art avionics. The two A secondary but more consequential application may be to take YA-7F prototypes planned will be equipped with F100-PW-220 the form of a beam-weapons platform for the conduct of antisatellite afterburning turbofans, but the engine bay will be configured to warfare. It is postulated that initial vehicle designs will be quite accept either this or the alternative F110 engine, which possesses rudimentary, and will be only gradually improved, in contrast to Western concern with initial produrn of a highly refined aircraft. similar’ characteristics. O.C. ^^

A88-53760*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. A8843782 SOME .KEY CONSIDERATIONS FOR HIGH-SPEED CIVIL PREDICTING, DETIERMINING, AND CONTROLLING TRANSPORTS MANUFACTURING VARIATION IN A NEW FACILITY CHARLES E. K. MORRIS, JR., MATTHEW M. WINSTON, and MARK EULERT ancl LUIS LUCERO (McDonnell Douglas Helicopter SHELBY J. MORRIS, JR. (NASA, Langley Research Center, Co., Mesa, AZ) SAWE, Annual Conference, 46th, Seattle, WA, Hampton, VA) AIAA, AHS, and ASEE, Aircraft Design, Systems May 18-20, 1987. 12 p. and Operations Meeting, Atlanta, GA, Sept. 7-9,1988. 8 p. refs (SAWE PAPER 1771) (AIAA PAPER 88-4466) The process csf determining and estimating manufacturing Factors affecting’ the development of a new generation of variation for an aircraft is discussed. The problem of measuring high-speed (supersonic/hypersonic) transports are reviewed. variations and determining what part of the variation is attributable Market projections of growth on long-range routes indicate a to design changes i3nd not to manufacturing variation is examined. potential need for faster transport aircraft by the turn of the century. Tracking changes and determining the actual weight of detaiKparts- - A review of NASA-sponsored studies shows how both market are considered. Results from efforts to measuring manufac forces and technology combine to define mission performance variation are presented. . .,; ,, and vehicle design constraints. The vehicle worth and price projected for a given vehicle are shown to relate to an assumed i A88-53800’ National Aeronautics and Space Administration. 1. technology level. Preliminary results from an initial set of vehicle Ames Research Center, Moffett Field, Calif. concepts lead to the conclusion that currently projected technology AERODYNAMICS will need to be enhanced with increased research to meet the RANDOLPH A. GRAVES, JR. (NASA, Ames Research Center, first market window around the year 2000. Author Moffett Field, CA) Exxon Air World, vol. 40, no. 2, 1988, p. 6-8. .%. A projection is made of likely improvements in the economics A8843761 ‘# National Aeronautics and Space Administration. of commercial aircraft operation due to developments in Langley Research Center, Hampton, Va. aerodynamics in tlie next half-century. Notable among these TECHNOLOGY SENSITIVITY STUDIES FOR A MACH 3.0 CIVIL improvements arc active laminar flow control techniques’ TRANSPORT application to third-generation SSTs, in order to achieve an LID PETER G. COEN (NASA, Langley Research Center, Hampton, value of about 20; this is comparable to current subsonic transports, VA) AIAA. AHS, and ASEE, Aircraft Design, Systems and and has the further consequence of reducing cabin noise. Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 9 p. refs Wave-cancellation systems may also be used to eliminate sonic (AIAA PAPER 88-4469) boom overpressurcs, and rapid-combustion systems may be able The level of technological sophistication required for the to eliminate all pollutants from jet exhausts other than C02. economic viability and environmental acceptability of a Mach O.C.

ORIGINAL PAGE IS 783 OF POOR QUALITY 01 AERONAUTICS (GENERAL)

A88-54246# N88-28879"# National Aeronautics and Space Administration. SECOND SOURCING OF A JET ENGINE Langley Research Center, Hampton, Va. JIMMY HIX (United Technologies Corp., Pratt and Whitney, West EFFECTS OF INDEPENDENT VARIATION OF MACH AND Palm Beach, FL) ASME, Gas Turbine and Aeroengine Congress REYNOLDS NUMBERS ON THE LOW-SPEED AERODYNAMIC and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 9 p. CHARACTERISTICS OF THE NACA 0012 AIRFOIL SECTION (ASME PAPER 88-GT-145) CHARLES L. LADSON Oct. 1988 97 p This paper describes in detail the process of developing a (NASA-TM-4074; L-16472; NAS 1.154074) Avail: NTlS HC 'build to print' alternate manufacturing source, which does not A05/MF A01 CSCL 01B have access to the original design agent, for the engine of the A comprehensive data base is given for the low speed U.S. Navy's newest jet fighter. The data used in the second sourcing aerodynamic characteristics of the NACA 0012 airfoil section. The process and the validation of the data are examined, and the Langley low-turbulence pressure tunnel is the facility used to obtain engineering methods used in data transfer, training, and source the data. Included in the report are the effects of Mach number qualification are discussed. Manufacturing source substantiation and Reynolds number and transition fixing on the aerodynamic and the roles of various U.S. government agencies are addressed. characteristics. Presented are also comparisons of some of the The benefits accrued from second sourcing and the remaining results with previously published data and with theoretical long-term questions are considered. The trials, lessons, and estimates. The Mach number varied from 0.05 to 0.36. The triumphs associated with second sourcing are reviewed. C.D. Reynolds number, based on model chord, varied from 3 x 10 to the 6th to 12 x 10 to the 6th power. Author

A88-55000 DAEDALUS - THE MAKING OF THE LEGEND JOHN S. LANGFORD (Institute for Defense Analyses, Alexandria, VA) Technology Review (ISSN 0040-1692), vol. 91, Oct. 1988, N88-28880'# United Technologies Research Center, East p. 24-35. Hartford, Conn. The Daedalus flight, which was the longest human-powered AN UNSTEADY HELICOPTER ROTOR: FUSELAGE flight recorded, is discussed. The process of designing the plane, INTERACTION ANALYSIS Final Report the way in which the plane was transported to Greece (where the PETER F. LORBER and T. ALAN EGOLF Washington NASA flight took place), and the conditions of the flight are examined. Sep. 1988 123 p The flight covered 72 miles in 2 hours and 48 minutes in April, (Contract NAS1-17469) 1988. The practical applications of the technology developed for (NASA-CR-4178; NAS 1.26:4178; R88-956977-15) Avail: NTlS Daedalus to future aircraft, such as the construction of HC AOWMF A01 CSCL 01B solar-powered aircraft are considered. R.B. A computational method was developed to treat unsteady aerodynamic interactions between a helicopter rotor, wake, and fuselage and between the main and tail rotors. An existing lifting A8845041 line prescribed wake rotor analysis and a source panel fuselage COST BENEFITS OF NONDESTRUCTIVE TESTING IN analysis were coupled and modified to predict unsteady fuselage AIRCRAFT MAINTENANCE surface pressures and airloads. A prescribed displacement DONALD J. HAGEMAIER (Douglas Aircraft Co., Long Beach, CA) technique is used to position the rotor wake about the fuselage. Materials Evaluation (ISSN 0025-5327), vol. 46, Sept. 1988, p. Either a rigid blade or an aeroelastic blade analysis may be used 1272, 1274, 1275 (7 ff.). refs to establish rotor operating conditions. Sensitivity studies were Some specific benefits and cost savings resulting from the performed to determine the influence of the wake fuselage effective impementation of nondestructive inspection in conjunction geometry on the computation. Results are presented that describe with aircraft maintenance are identified. It is noted that specific the induced velocities, pressures, and airloads on the fuselage costs associated with a given nondestructive test or inspection and on the rotor. The ability to treat arbitrary geometries is should be considered in relation to consequential upstream demonstrated using a simulated helicopter fuselage. The manufacturing costs associated with nondestructive evaluation computational results are compared with fuselage surface pressure (e.g., the reduced yield because of the parts that fail tests) and measurements at several locations. No experimental data was consequential downstream cost savings (e.g., decreased premature available to validate the primary product of the analysis: the removal rate, reduced failure rate, and reduced liability costs). In vibratory airloads on the entire fuselage. A main rotor-tail rotor most situations, these indirect costs are much larger than the interaction analysis is also described, along with some hover and direct costs associated with nondestructive testing. The need for developing the engineering and economic methodology to optimize forward flight. Author tradeoff s between downstream cost savings and inspection and manufacturing costs is emphasized. V.L.

N88-28857# Advisory Group for Aerospace Research and N88-29717# Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seine (France). Fluid Dynamics Panel. Development, Neuilly-Sur-Seine (France). Structures and Materials BOUNDARY LAYER SIMULATION AND CONTROL IN WIND Panel. TUNNE LS THE FLIGHT OF FLEXIBLE AIRCRAFT IN TURBULENCE: Apr. 1988 462 p STATE-OF-THE-ART IN THE DESCRIPTION AND MODELLING (AGARD-AR-224; ISBN-92-635-0457-7; AD-A1 98667) Avail: OF ATMOSPHERIC TURBULENCE NTlS HC A20/MF A01 Jun. 1988 11 1 p Meeting held in Cesme, Turkey, 4-9 Oct. The results of a study performed by AGARD Working Group 1987 09 on boundary layer simulation in wind tunnels are presented (AGARD-R-734-ADD; ISBN-92-835-0456-5) Avail: NTlS HC with emphasis on the transonic speed regime. This report is AO6/MF A01 intended to display the current state-of-the-art in boundary layer The large scale use of flight recorders by commercial airlines, simulation where Reynolds number is or cannot be simulated and coupled with the enhanced quality of results offered by modern give attention to wind tunnel effects as well as to document the computer based reduction processes makes it possible to broaden physical aspects of boundary layer simulation and the research knowledge of the phenomenon of atmospheric turbulence. At the needed. Finally, a simulation methodology is proposed which can same time, new methods for predicting the response of flexible serve wind tunnel user and operator as an ordered thinking process aircraft to turbulence are being proposed, and novel gust alleviation for the design of wind tunnel tests where viscous effects are systems are being designed and tested. The presentations made important. at a workshop held for the discussion of these ideas are given.

784 02 AERODYNAMICS

N88-29725# Advisory Group for Aerospace Research and A88-52686# Development, Neuilly-Sur-Seine (France). Structures and Materials WAKE-INDUCED UNSTEADY AERODYNAMIC INTERACTIONS Panel. IN A MULTISTAGE COMPRESSOR THE FLIGHT OF FLEXIBLE AIRCRAFT IN TURBULENCE: VINCENT R. CAPECE and SANFORD FLEETER (Purdue University, STATE-OF-THE-ART IN THE DESCRIPTION AND MODELLING West Lafayette, IN) Journal of Propulsion and Power (ISSN OF ATMOSPHERIC TURBULENCE 0748-4658), vol. 4, Sept.-Oct. 1988, p. 458-465. USAF-supported Dec. 1987 187 p Meeting held in Athens, Greece, 28 Sep. - 3 research. Previously cited in issue 20, p. 2915, Accession no. Oct. 1986 A86-42653. refs (AGARD-R-734; ISBN-92-635-0426-7) Avail: NTlS HC AO9/MF A0 1 A8842795 The flight of flexible aircraft in turbulence was studied. A PROJECTION-GRID SCHEME FOR CALCULATING Presentations given at the first of two workshops on the subject TRANSONIC FLOW PAST A PROFILE are provided. Topics covered here are: (1) Measurements of [PROEKTSIONNO-!iETOCHNAlA SKHEMA DLIA RASCHETA turbulence by specially equipped aircraft, and (2) Data collection OBTEKANIIA PROFILIA TRANSZVUKOVYM POTOKOMJ and reduction of incremental accelerations observed in commercial IU. B. LlFSHlTS and A. A. SHAGAEV Zhurnal Vychislitel’noi flights. Matematiki i Mateniaticheskoi Fiziki (ISSN 0044-4669). vol. 28, Aug. 1988, p. 1163-1176. In Russian. refs N88-29735# Advisory Group for Aerospace Research and The boundary villue problem for the full potential equation is Development, Neuilly-Sur-Seine (France). Flight Mechanics approximated by a conservative projection-grid scheme based on Panel. the integral equality method. Additional dissipation, required for ADVANCES IN FLYING QUALITIES the isolation of a stable solution in the supersonic region, is May 1988 194 p Lecture held in Delft, Netherlands, 26-27 introduced by modifying the density formula in accordance with May 1988, in Rome, Italy, 30-31 May 1988, and in Torrance, Calif., artificial compressilility concepts. The resulting system of grid 15-16 Jun. 1988 equations is linearized at each iteration step and solved by a (AGARD-LS-157; ISBN-92-635-0461-5) Avail: NTlS HC AO9/MF multigrid algorithm. V.L. A01 Judging the suitability of an aircraft to safely and effectively A88-53 106# perform its mission without undue pilot skill and discomfort is what A THREE DIMENSIONAL ZONAL NAVIER-STOKES CODE FOR flying qualities is all about. Central to such judgement, and to the SUBSONIC THROUGH HYPERSONIC PROPULSION design of suitable aircraft plus flight control systems, is an FLOWFIELDS understanding of what the pilot can do with ease and comfort or ROBERT H. BUSH (McDonnell Aircraft Co., Saint Louis, MO) AIAA, conversely what bothers him. The lectures are designed to impart ASME, SAE, and ASEE, Joint Propulsion Conference, 24th. Boston, such understanding to both novice and seasoned practioners in MA, July 11-13, 1988. 12 p. refs flying qualities and flight control and thereby to provide the bridge (AIAA PAPER 88-21330) required to extend flying qualities requirements from simple classic A three dimens,ional flowfield code has been written for response aircraft, to the responses attending the use of full time propulsion integration studies. Geometric flexibility is provided by active control. Mathematical models of pilot control behavior are a flexible boundary condition implementation and a zonal grid explained. The application of various model to flying qualities are strategy. A new Total Variation Diminishing scheme was discussed; and the influences, regarding the generic likes and implemented for hypersonic flows. Applications include forebody, dislikes of pilots drawn from such studies are listed. inlet, diffuser and afterbody flows, from Mach .8 to Mach 7.4 Author

A88-53138# 02 A FULL NAVIER-STOKES ANALYSIS OF A THREE DIMENSIONAL HYPERSONIC MIXED COMPRESSION INLET JEFFERY A. WHITE (Pratt and Whitney, West Palm Beach, FL) AERODYNAMICS and CHAE M. RHIE: (Pratt and Whitney, East Hartford, CT) AIAA, ASME, SAE, and A!SEE, Joint Propulsion Conference, 24th, Boston, Includes aerodynamics of bodies, combinations, wings, rotors, and MA, July 11-13, 19138. 12 p. refs control surfaces; and internal flow in ducts and turbomachinery. (AIAA PAPER 88-3077) Three dimensional effects in a mixed compression inlet typical of supersonic corribustion ramjet engine is studied using a full A88-52685# Navier-Stokes analysis method. The solution procedure uses a ANALYSIS OF ROTOR TIP CLEARANCE LOSS IN multi-step pressure correction method with an implicit density AXIAL-FLOW TURBINES treatment to establish the pressure and velocity fields. The stong SAEED FAROKHI (Kansas, University, Lawrence) Journal of shocks are captured using a smart numerical dissipation scheme Propulsion and Power (ISSN 0748-4658), vol. 4, Sept.-Oct. 1988, which adapts monotonically at extrema. Numerical solutions for a p. 452-457. refs mixed compression forebodyhlet are presented including Tip clearance flow is a major contributor to the losses in axial performance calculations. Author flow turbines. Tip shrouding reduces the extent of this loss at the expense of more structural complexity and increased centrifugal A88-53140# blade stresses. Recent technological advance in the area of active STATOR/ROTOR INTERACTION IN A TRANSONIC TURBINE clearance control promises to minimize the tip clearance loss MICHAEL B. GlLES (MIT, Cambridge, MA) AIAA, ASME, SAE, without the adverse tip shrouding effects. Due to complexity of and ASEE, Joint Propulsion Conference, 24th, Boston, MA, July rotor tip flows, a comprehensive tip clearance loss model that 11-13, 1988. 13 p. Research supported by Rolls-Royce, PLC. accounts for the tip shape, relative wall motion, tip loading, and refs stage characteristics has not yet been developed. In the present (AIAA PAPER 88-fi093) paper, the rotor tip clearance flow is aerothermodynamically A numerical procedure is presently used to calculate statorhotor analyzed and a loss model is presented that includes the interaction in the case of a highly loaded transonic first turbine above-mentioned effects. Tip leakage discharge coefficient and stage, by solving for the inviscid unsteady Euler equations (including the stage loading factor are taken as modeling parameters. Finally, quasi-three-dimensional terms). Attention is given to the earlier tip clearance loss models are reviewed and comparisons propagation and reflection of shocks originating at the trailing edge are drawn with the present work. Author of the upstream stator; these produce a 40-percent variation in

785 02 AERODYNAMICS the lift on the rotor, leading to structural vibrations and increased Universitet, Tomsk, USSR) Teplofizika Vysokikh Temperatur (ISSN losses. A simple technique is used to couple the calculations on 0040-3644), vol. 26, July-Aug. 1988, p. 751-758. In Russian. the stator and rotor grids. O.C. refs Hypersonic flow of a viscous heat-conducting gas past a smooth A88-53250 blunt body at angles of attack and sideslip is examined in the DEVELOPMENTS IN COMPUTATIONAL METHODS FOR context of a model of a three-dimensional viscous shock layer. A HIGH-LIFT AERODYNAMICS numerical method of a high order of approximation with respect D. A. KING (British Aerospace, PLC, Hatfield, England) and B. R. to the transverse coordinate is developed for integrating equations WILLIAMS (Royal Aircraft Establishment, Farnborough, England) of a three-dimensional hypersonic viscous shock layer at Aeronautical Journal (ISSN 0001-9240), vol. 92, Aug.-Sept. 1988, moderately small Reynolds numbers in the absence of plane p. 265-288. refs symmetry in the flow. The effect of the Reynolds number and Several improvements are suggested for interaction techniques angles of attack and sideslip on the shock wave behavior, surface in order to improve predictions of high-lift wing configuration friction and heat transfer coefficients, and flow structure in the aerodynamics up to and beyond the stall of flow. It is noted that shock layer is examined. V.L. the direct coupling of the viscous and the inviscid flows is replaced by semiinverse and quasi-simultaneous coupling; this leads to a A88-54151# substantial improvement in the estimate of maximum lift. These AN EXPERIMENTAL INVESTIGATION INTO THE REASONS OF improvements are illustrated by the novel FELMA method for REDUCING SECONDARY FLOW LOSSES BY USING LEANED viscous transonic flow prediction about high-lift airfoils. FELMA BLADES IN RECTANGULAR TURBINE CASCADES WITH features a new type of grid generation employing incompressible INCIDENCE ANGLE streamlines and equipotentials with a transonic FEM that uses a ZHONGQI WANG, WENYUAN XU, WANJIN HAN, and JIE BAI multigrid solver. O.C. (Harbin Institute of Technology, People's Republic of China) ASME, Gas Turbine and Aeroengine Congress and Exposition, A88-53762'# Analytical Services and Materials, Inc., Hampton, Amsterdam, Netherlands, June 6-9, 1988. 7 p. Research supported Va. by National Fund of Natural Sciences. refs SUCTION LAMlNARlZATlON OF HIGHLY SWEPT (ASME PAPER 88-GT-4) SUPERSONIC LAMINAR FLOW CONTROL WINGS Using experiments and models, the reasons for reducing the W. PFENNINGER and C. S. VEMURU (Analytical Services and secondary flow losses in rectangular turbine cascades by the use Materials, Inc., Hampton, VA) AIAA, AHS, and ASEE, Aircraft of leaned blades were investigated. It is shown that the dominant Design, Systems and Operations Meeting, Atlanta, GA, Sept. 7-9, factor in controlling the secondary flow loss in turbine cascades 1988. 11 p. refs is the static pressure gradient along the blade height inside the (Contract NASI-18235) cascade channel, especially on the suction surface near the throat (AIAA PAPER 88-4471) of cascades. The use of the straight leaned and curvilinear leaned An evaluation is made of a suction-based method for the blades was found to have a beneficial role in establishing the laminarization of highly-swept supersonic wings at cruise Mach necessary static pressure gradient. The effectiveness of applying numbers in the 2.0-2.5 range, in the interest of the reduction of the positively or negatively leaned blades was increased with the wave drag due to lift. The laminar boundary layer development, increase of the incidence angle in the hub or the tip regions, as well as Tollmien-Schlichting and crossflow instabilities, have respectively. I.S. been analyzed for the case of an X66 supercritical airfoil at 60 and 72 deg sweep, for Mach numbers of 1.56 and 2.52, A88-54157# respectively. Strong suction is found to be needed at the front AERODYNAMIC AND HEAT TRANSFER MEASUREMENTS ON part of the upper surface and both the upper and lower rear A TRANSONIC NOZZLE GUIDE VANE pressure-rise areas. O.C. E. T. WEDLAKE, A. J. BROOKS, and S. P. HARASGAMA (Royal Aircraft Establishment, Farnborough, England) ASME, Gas Turbine A88-53970 and Aeroengine Congress and Exposition, Amsterdam, CONDITIONS OF THE INDUCTION-PLASMATRON MODELING Netherlands, June 6-9, 1988. 8 p. refs OF THE CONVECTIVE NONEQUlLlBRlUM HEAT TRANSFER (ASME PAPER 88-GT-10) OF BODIES IN HYPERSONIC FLOW [USLOVIIA A series of tests have been carried out on an annular cascade MODELlROVANllA KONVEKTIVNOGO NERAVNOVESNOGO of nozzle guide vanes designed for a high-capacity single-stage TEPLOOBMENA TEL S GIPERZVUKOVYMI POTOKAMI NA transonic turbine. Measurements of local heat transfer rates and INDUKTSIONNYKH PLAZMOTRONAKH] aerodynamic data around the blade surface and on the end walls A. F. KOLESNIKOV and M. I. IAKUSHIN (AN SSSR, lnstitut Problem are presented, and the new test facility used in this study is briefly Mekhaniki, Moscow, USSR) Teplofizika Vysokikh Temperatur described. The measurements are shown to be repeatable and (ISSN 0040-3644), vol. 26, July-Aug. 1988, p. 742-750. In consistent with both predictions and previous test results from a Russian. refs two-dimensional cascade. The inlet turbulence level is found to The possibility of the modeling of nonequilibrium heat transfer be adequate to insure the suction surface boundary layer processes by using a 100-kW induction plasmatron with a transition. V.L. 0.06-m-diameter discharge channel is investigated. Relations are established between the parameters of hypersonic flow past a A88-54165# smooth body and characteristics of subsonic jet flow past cylindrical AN EXPERIMENTAL INVESTIGATION INTO THE INFLUENCE models, and it is shown that these relations, when implemented OF BLADE LEANING ON THE LOSSES DOWNSTREAM OF in induction plasmatrons, provide full capabilities for the modeling ANNULAR CASCADES WITH A SMALL DIAMETER-HEIGHT of nonequilibrium heat transfer in a dissociated boundary layer RATIO near the critical point. V.L. WANJIN HAN, ZHONGQI WANG, and WENYUAN XU (Harbin Institute of Technology, People's Republic of China) ASME, Gas A88-53971 Turbine and Aeroengine Congress and Exposition, Amsterdam, THREE-DIMENSIONAL HYPERSONIC VISCOUS SHOCK Netherlands, June 6-9, 1988. 8 p. refs LAYER ON BLUNT BODIES IN FLOW AT ANGLES OF (ASME PAPER 88-GT-19) ATTACK AND SIDESLIP [GIPERZVUKOVOI Low-speed annular cascade tunnel test results are presented PROSTRANSTVENNYI VlAZKll UDARNYI SLOl NA for five types of cascades with different leaned blades. It is found ZATUPLENNYKH TELAKH, OBTEKAEMYKH POD UGLAMI that, for the annular cascade with a small diameter-blade height ATAKI I SKOL'ZHENIIA] ratio and cylindrical inner and outer endwalls, the application of A. I. BORODIN and S. V. PElGlN (Tomskii Gosudarstvennyi positively leaned blades can not only reduce the energy losses in

786 02 AERODYNAMICS the cascade but also improve flow behavior downstream. The originating from profile wake flows and the position and extent of decisive factor in reducing the energy losses downstream is not separation bubbles. The latter are most often detected by the reaction of the stage but the control of the amount of the visualization method:; like surface oil flow patterns or schlieren low-energy gas getting into downstream, especially into the region photographs, as well as by typical properties in wall pressure near the hub. V.L. distribution curves. In addition to that, the infrared image technique which has found many applications in a wide range of technical A88-54173# activities in the recent years, may also be used. Compared with FLOW FIELD IN THE TIP GAP OF A PLANAR CASCADE OF other methods, this technique has distinct advantages in fluid TURBINE BLADES mechanics applications. The whole model can be observed, without M. YARAS, YINGKANG ZHU, and S. A. SJOLANDER (Carleton disturbing the boundary layer by tappings, measuring materials or University, Ottawa, Canada) ASME, Gas Turbine and Aeroengine probes. Some typical infrared images are presented and interpreted Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. using results of pressure distribution measurements, hot-film 10 p. Research supported by Pratt and Whitney Canada. refs measurements and surface oil flow visualizations. Author (Contract NSERC-A-1671) (ASME PAPER 88-GT-29) A88-54 183# Measurements are presented for the flow in the tip gap of a THE EFFECT OF THE INLET VELOCITY PROFILE IN THE planar cascade of turbine blades. Three clearances of from 2.0 to THREE-DIMENSIONAL FLOW IN A REAR AXIAL 3.2 percent of the blade chord were considered. Detailed surveys COMPRESSOR STAlGE of the velocity magnitude, flow direction and total pressure within VACLAV CYRUS (Statni Vyzkumny Ustav Konstrukce Stroju, the gap were supplemented by blade surface and endwall static Bechovice, Czechoslovakia) ASME, Gas Turbine and Aeroengine pressure measurements. The results help to clarify the relationship Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. between the leakage mass flow rate distribution and the driving 9 p. refs pressure differences. It was found that even for the present (ASME PAPER EE-GT-~~) relatively large clearances, fluid near the endwall experiences a Three-dimensional flow calculations were obtained in a pressure difference which is comparable with the blade pressure low-speed real axial compressor stage with an aspect ratio of 1. difference. It is also shown that a simple model can predict with The working conditions of a multistage compressor stage are good accuracy the mass flow rate distribution and the magnitude modelled using a splscially designed screen and lengthened inlet and direction of the velocity vectors within the gap. Author annulus. The flow mechanism in the rotor and stator blade rows was analyzed for an inlet velocity profile with thin end-wall boundary A88-54 175# layer thicknesses, arld for a distorted inlet velocity profile with a TRANSITION MODELING EFFECTS ON VISCOUS/INVISCID high-turbulence intensity level. R.R. INTERACTION ANALYSIS OF LOW REYNOLDS NUMBER AIRFOIL FLOWS INVOLVING LAMINAR SEPARATION A88-54188# BUBBLES EXPERIMENTAL IN\IESTIGATION OF MULTISTAGE G. J. WALKER (Tasmania, University, Hobart, Australia), P. H. INTERACTION GUST AERODYNAMICS SUBROTO (Indonesian Air Force, Djakarta, Indonesia), and M. F. VINCENT R. CAPECE: and SANFORD FLEETER (Purdue University, PLATZER (U.S. Naval Postgraduate School, Monterey, CA) ASME, West Lafayette, IN) ASME, Gas Turbine and Aeroengine Congress Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 10 p. Netherlands, June 6-9, 1988. 11 p. Navy-supported research. USAF-supported research. refs refs (ASME PAPER EE-GT-~~) (ASME PAPER 88-GT-32) The fundamental flow physics of multistage blade-row This paper presents a viscous/inviscid interaction analysis of interactions are expximentally investigated at realistic reduced flow over a NACA 65-213 airfoil at a chord Reynolds number of frequency values. Unique data are obtained which describe the 240,000 using a calculative method by Cebeci et al. (1986). The fundamental unsteady aerodynamic interaction phenomena on the computed characteristics of a midchord laminar separation bubble stator vanes of a three-stage axial-flow research compressor. In are compared with experimental laser-Doppler anemometer these experiments, the effects on vane-row unsteady aerodynamics measurements by Hoheisel et al. (1984). Attention is focused on of the following are investigated and quantified: (1) steady vane problems of modeling the laminar-turbulent transition zone within aerodynamic loading, (2) aerodynamic forcing-function waveform the viscous layer are addressed. The location and extent of the (including both the c hordwise and transverse gust components), transition zone which best models the observed separation bubble (3) solidity, (4) potential interactions, and (5) isolated-airfoil steady behavior is parametrically studied. The required transition length flow separation. Author is found to be almost an order of magnitude smaller than that predicted from conventional transition length correlations. A A88-54189'# Flow Application Research, Fremont, Calif. physical model for this greatly reduced transition length in positive DESIGN POINT VAGllATlON OF 3-D LOSS AND DEVIATION pressure gradient flows is proposed. C.D. FOR AXIAL COMPRESSOR MIDDLE STAGES WILLIAM B. ROBERTS (Flow Application Research, Fremont, CA), A88-54 176# GEORGE K. SERCIVY (Iowa State University of Science and DETECTION OF SEPARATION BUBBLES BY INFRARED Technology, Ames), and DONALD M. SANDERCOCK (NASA, Lewis IMAGES IN TRANSONIC TURBINE CASCADES Research Center, Cleveland, OH) ASME, Gas Turbine and W. BRAEUNLING (DFVLR, lnstitut fuer Experimentelle Aeroengine Congress and Exposition, Amsterdam, Netherlands, Stroemungsmechanik, Goettingen, Federal Republic of Germany), June 6-9, 1988. 14 p. refs A. QUAST (DFVLR, lnstitut fuer Entwurfs-Aerodynamik, Brunswick, (Contract NAG3-521) Federal Republic of Germany), and H.-J. DlETRlCHS (MTU (ASME PAPER 88-G r-57) Motoren- und Turbine-Union Muenchen GmbH, Munich, Federal The available data on middle-stage research compressors Republic of Germany) ASME, Gas Turbine and Aeroengine operating near desisn point are used to derive simple empirical Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. models for the spariwise variation of three-dimensional viscous 9 p. refs loss coefficients for middle-stage axial compressor blading. The (ASME PAPER 88-GT-33) models make it possible to quickly estimate the total loss and In a test facility for straight cascades, equipped with profiles deviation across the blade span when, the three-dimensional designed for a highly loaded gas turbine rotor of a high-pressure distribution is superimposed on the bo-dimensional variation stage, experiments were conducted to clarify some effects of shock calculated for each blade element. It $noted that extrapolated wave-boundary layer interactions. The specific aim was to estimates should be used with caution sirice the correlations have determine both the position and strength of compression shocks been derived from a limited data base. V.L.

QRIGlNAL PAGE IS 787 OF POOR QUALITY 02 AERODYNAMICS

A88-54190# A88-54201# THE USE OF FINS TO REDUCE THE PRESSURE DROP IN A DEVELOPMENT OF A 3D NAVIER STOKES SOLVER FOR ROTATING CAVITY WITH A RADIAL INFLOW APPLICATION TO ALL TYPES OF TURBOMACHINERY J. W. CHEW, B. STRATFORD (Rolls-Royce, PLC, Derby, England), W. N. DAWES (Cambridge University, England) ASME, Gas P. R. FARTHING, and J. M. OWEN (Sussex, University, Brighton, Turbine and Aeroengine Congress and Exposition, Amsterdam, England) ASME, Gas Turbine and Aeroengine Congress and Netherlands, June 6-9, 1988. 11 p. refs Exposition, Amsterdam, Netherlands, June 6-9, 1988. 11 p. (ASME PAPER 88-GT-70) Research sponsored by Rolls-Royce, PLC, Ruston Gas Turbines, The current stage of development of a code aimed at solving PLC, and SERC. refs the three-dimensional Navier-Stokes equations in any type of (ASME PAPER 88-GT-58) turbomachinery geometry is described. The generality and A combined theoretical and experimental study of radial inflow robustness of the code are demonstrated on the basis of five through a rotating cavity is reported. It is shown that radial fins different test cases, three axial and two radial configurations. A attached to one of the disks are effective in reducing the pressure grid independence study which demonstrates near grid independent drop across the cavity. The mathematical model is an extension solutions for transonic compressor cascade flow is included as of earlier plane-disk momentum-integral methods; the fins are well. K.K. treated as rectangular rib elements and a rough-disk model is derived. Numerical solutions of the integral equations are given. A88-54206’# National Aeronautics and Space Administration. An approximate linear solution is also derived. Experiments were Lewis Research Center, Cleveland, Ohio. conducted when both disks were plane and when one of the FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW disks was fitted with 60 radial fins. Flow visualization revealed the ROBERT E. KIELB and JOHN K. RAMSEY (NASA, Lewis Research flow structure in the cavity and confirmed some of the assumptions Center, Cleveland, OH) ASME, Gas Turbine and Aeroengine used in the theoretical model. Measurements and predictions of Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. the pressure drop across the cavity were in reasonable 7 p. refs agreement. Author (ASME PAPER 88-GT-78) An application of a simple aeroelastic model to an advanced supersonic axial flow fan is presented. Lane’s cascade theory is A88-54192# used to determine the unsteady aerodynamic loads. Parametric THE USE OF BEZIER POLYNOMIAL PATCHES TO DEFINE studies are performed to determine the effects of mode coupling, THE GEOMETRICAL SHAPE OF THE FLOW CHANNELS OF Mach number, damping, pitching axis location, solidity, stagger COMPRESSORS angle, and mistuning. The results show that supersonic axial flow QINGHUAN WANG and XIAOYAN HUANG (Chinese Academy of fan and compressor blades are susceptible to a strong torsional Sciences, Institute of Engineering Thermophysics, Beijing, People’s mode flutter having critical reduced velocities which can be less Republic of China) ASME, Gas Turbine and Aeroengine Congress than one. Author and Exposition, Amsterdam, Netherlands, June 6-9. 1988. 5 p. refs A88-54207# (ASME PAPER 88-GT-60) TURBULENCE MEASUREMENTS IN A MULTISTAGE Casey’s (1982) method is presently developed through the use LOW-PRESSURE TURBINE of Bezier polynomial patches to define the geometrical shape of A. BINDER, TH. SCHROEDER, and J. HOURMOUZIADIS (MTU compressor flow channels. By means of this method, the Motoren- und Turbinen-Union Muenchen GmbH, Munich, Federal geometry-defining process for the blade profile and the contour of Republic of Germany) ASME, Gas Turbine and Aeroengine the blade’s meridional channel can be generated by the same Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. number of patches. In addition, no restrictions are imposed on 11 p. refs linearity in the spanwise direction in order to match the distribution (ASME PAPER 88-GT-79) of flow angles at the inlet, as well as to satisfy the requirements The flow in the rotor blades of a five stage low pressure turbine of various load models. The method is especially suitable for was investigated experimentally using hot-film probes. Time incorporation by CAD systems. O.C. averaging, Fourier transforms and ensemble averaging are applied for data reduction. The techniques prove to be a very helpful instrument for the assessment of the flow characteristics in the A88-54200# relative frame. A strong interaction is identified between two THE RELATIVE MERITS OF AN INVISCID EULER 3-0 AND successive rows of rotor blades. A physical model, developed QUASI-3-D ANALYSIS FOR THE DESIGN OF TRANSONIC from velocity and turbulence results, gives a comprehensive ROTORS understanding of the phenomenon. The main parameter is the D. P. MILLER and A. C. BRYANS (General Electric Co., Aircraft nonuniformity of the flow entering the downstream blade row. Engine Business Group, Lynn, MA) ASME, Gas Turbine and Separation occurs when the wake of the upstream rotor blades Aeroengine Congress and Exposition, Amsterdam, Netherlands, enters the blade passage near the leading edge, preferably on June 6-9, 1988. 13 p. refs the pressure side. The interaction is quasi-steady in the relative (ASME PAPER 88-GT-69) frame and rotates with the rotor speed. It was observed only in It is the purpose of this paper to examine the flow fields in an one of three investigated blade rows. Further studies are necessary advanced modern transonic rotor design using both axisymmetric to identify the mechanism correlating the nonuniformity to the and three dimensional techniques. Also, to determine the deviation separation. Author of the axisymmetric flow from three-dimensional flow field and whether this seriously affects the results. Inviscid Euler solvers A88-54208# are now widely used to analyze transonic flows through COMPUTATION OF THREE-DIMENSIONAL TURBULENT turbomachines giving a reasonably accurate indication of the flow TURBOMACHINERY FLOWS USING A COUPLED field in blade passages. Although viscous effects are important, PARABOLIC-MARCHING METHOD the inviscid analysis provides significant knowledge of the flow K. R. KIRTLEY and B. LAKSHMINARAYANA (Pennsylvania State field which is essential to transonic design. The blade-to-blade University, University Park) ASME, Gas Turbine and Aeroengine loading and work distributions are determined quite realistically by Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. the three-dimensional and quasi-three-dimensional inviscid 10 p. Navy-sponsored research. refs analyses. Through-flow and blade-to-blade inviscid solutions are (ASME PAPER 88-GT-80) presented for a highly loaded transonic rotor. Numerical solutions A new coupled parabolic-marching method was developed to for various transonic rotor designs operating at peak efficiency compute the three-dimensional turbulent flow in a turbine end wall are also compared with test data. Author cascade, a compressor cascade wake, and an axial flow

788 02 AERODYNAMICS

, compressor rotor passage. The method solves the partially unsteady-flow calculation case with theory and experiment, parabolized incompressible Navier-Stokes equation and continuity respectively. Results are shown for typical stator-to-rotor-pitch in a coupled fashion. The continuity equation was manipulated ratios and stator outlet-flow angles. These results show that the ' using pseudocompressibility theory to give a convergent algorithm first spatial harmonic of the unsteady force may decrease for for complex geometries. The computed end wall boundary layers higher stator-to-rotor-pitch ratios. This trend is explained by and secondary flow compared well with the experimental data for considering the mechanisms by which the unsteady forces are I the turbine cascade as did the wake profiles for the compressor generated. In this paper the mechanism by which the potential-flow cascade using a k-epsilon turbulence model. Suction side boundary interaction affects the flow field to generate these unsteady forces layers, pressure distributions and exit stagnation pressure losses is shown to vary with the stator-to-rotor-pitch ratio and with the compared reasonably well with the data for the compressor rotor. outlet-flow angle of the stator. Author Author A88-54214# A88-542 1O# ON THE PREDICTION OF UNSTEADY FORCES ON NUMERICAL SOLUTION TO TRANSONIC POTENTIAL GAS-TURBINE BLADES. II - VISCOUS-WAKE-INTERACTION EQUATIONS ON S2 STREAM SURFACE IN A TURBOMACHINE AND AXIAL-GAP EFFECTS J. Y. DU, J. 2. XU (Chinese Academy of Sciences, Institute of THEODOSIOS P. KORAKlANlTlS (Washington University, Saint Engineering Thermophysics, Beijing, People's Republic of China), Louis, MO) ASME, Gas Turbine and Aeroengine Congress and Y. Q. ZHAO, and Y. GUO (Nanhua Power Research Institute, Exposition, Amsterdam, Netherlands, June 6-9, 1988. 7 p. refs Zhuzhou, People's Republic of China) ASME, Gas Turbine and (ASME PAPER 88-GT-90) Aeroengine Congress and Exposition, Amsterdam, Netherlands, This paper is a contribution to the study of the generation of June 6-9, 1988. 5 p. refs unsteady forces on turbine blades due to viscous wake interaction (ASME PAPER 88-GT-82) and potential-flow interaction from upstream blade rows. A A nonisentropic potential method on an S2 stream surface computer program is used to compute the unsteady forces on a has been developed for the design and analysis of transonic rotor. Typical results for isolated viscous-wake interaction (no compressors with shocks, in which the entropy increase across a potential-flow interaction) are shown. These results indicate that shock may be directly calculated from the momentum equations the first spatial harmonic of the unsteady force may decrease for in the divergence form. The numerical results show that the higher stator-to-rotor-pitch ratios. This trend is explained by nonisentropic shock is weaker, placed one or two meshes further considering the mechanisms by which the unsteady forces are upstream compared to the classical potential calculation, and is generated. The mechanism by which the viscous wakes affect in good agreement with the experimental data. Author the flow field to generate these unsteady forces is shown to vary with the stator-to-rotor-pitch ratio and with the outlet-flow angle of A8844211# the stator. It is also shown that by varying the axial gap between QUASI-3D SOLUTIONS FOR TRANSONIC, INVISCID FLOWS rotor and stator one can attempt to minimize the magnitude of BY ADAPTIVE TRIANGULATION the unsteady part of the forces generated by the combined effects D. GRAHAM HOLMES, SCOTT H. LAMSON (GE Corporate of viscous-wake interaction and potential-flow interaction. Author Research and Development Center, Schenectady, NY), and STUART D. CONNELL (General Electric Co., Aircraft Engine A80-542 16# Business Group, Cincinnati, OH) ASME, Gas Turbine and CALCULATION OF COMPLETE THREE-DIMENSIONAL FLOW Aeroengine Congress and Exposition, Amsterdam, Netherlands, IN A CENTRIFUGAL ROTOR WITH SPLllTER BLADES June 6-9, 1988. 9 p. refs DIAN-KUI LIU and LE-JIAN JI (Chinese Academy of Sciences, (ASME PAPER 88-GT-83) Institute of Engineering Thermophysics, Beijing. People's Republic This paper describes an algorithm for computing of China) ASME, Gas Turbine and Aeroengine Congress and two-dimensional transonic, inviscid flows. The solution procedure Exposition, Amsterdam, Netherlands, June 6-9, 1988. 7 p. refs uses an explicit Runge-Kutta time marching, finite volume scheme. (ASME PAPER 88-Gl-93) The computational grid is an irregular triangulation. The algorithm The flow within a centrifugal rotor has strong characteristics of can be applied to arbitrary two-dimensional geometries. When used three-dimensional effect. A procedure called 'stream-surface for analyzing flows in blade rows, terms representing the effects coordinates iteration' for the calculation of complete of changes in streamsheet thickness and radius, and the effects three-dimensional flow in turbo-machinery is first described. Splitter of rotation, are included. The solution is begun on a coarse grid, blade techniques have been used in many rotors, especially in and grid points are added adaptively during the solution process, centrifugal compressors and pumps with high flow capacity. The using criteria such as pressure and velocity gradients. Advantages difficulty of the calculation of the flow field for this type of rotor is claimed for this approach are: (1) the capability of handling arbitrary that the mass flow ratio between the two sub-channels is unknown geometries (e.g., multiple, dissimilar blades); (2) the ability to resolve for the given total flow capacity. An assumption on how to small-scale features (e.g., flows around leading edges, shocks) determine this mass flow ratio and a procedure to calculate the with arbitrary precision; and (3) freedom from the necessity of complete three-dimensional flow are presented. Finally, some generating 'good' grids (the algorithm generates its own grid, given design criteria for the splitter blades are put forward. Experimental an initial coarse grid). Solutions are presented for several examples data from two centrifugal pump impellers equipped with different that illustrate the usefulness of the algorithm. Author splitter blades are also given to demonstrate the efficiency of the present calculation method. Author A80-542 13# ON THE PREDICTION OF UNSTEADY FORCES ON A88-54217# GAS-TURBINE BLADES. I - TYPICAL RESULTS AND PREDICTION OF COMPRESSOR CASCADE PERFORMANCE POTENTIAL-FLOW-INTERACTIONEFFECTS USING A NAVIER-STOKES TECHNIQUE THEODOSIOS P. KORAKlANlTlS (Washington University, Saint R. L. DAVIS (United Technologies Research Center, East Hartford, Louis, MO) ASME, Gas Turbine and Aeroengine Congress and CT), D. E. HOBBS, and H. D. WEINGOLD (Pratt and Whitney, Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs East Hartford, CT) ASME, Gas Turbine and Aeroengine Congress (ASME PAPER 88-GT-89) and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 13 p. This paper is a contribution to the study of the generation of Research supported by United Technologies Corp. refs unsteady forces on turbine blades due to potential-flow interaction (ASME PAPER 88-~~-96) and viscous-wake interaction from upstream blade rows. A An explicit, time mlarching, multiple-grid Navier-Stokes technique computer program is used to compute the unsteady forces on a is demonstrated for the prediction of quasi-three-dimensional rotor. The accuracy of the computer program is tested by comparing turbomachinery compressor cascade performance over the entire the results of a steady-flow calculation case and of an incidence range. A numerical investigation has been performed in

789 02 AERODYNAMICS

which the present Navier-Stokes procedure was used to analyze Effort has been concentrated on improving the blade-to-blade a series of compressor cascade viscous flows for which analysis and developing a two-dimensional blade-to-blade profile corresponding experimental data are available. Results from these design method. The development and verification of the analysis calculations show that the current viscous flow procedure is capable program have already been reported in detail (Willis, 1987 and of predicting cascade profile loss and airfoil pressure distributions Willis and Goulas, 1987). This paper presents the design or inverse with high accuracy. The results from this numerical investigation solution. The analysis method uses an inviscid stream function in the form of comparisons between the predicted profile loss, solution coupled with an integral boundary layer calculation. In exit gas angle, and pressure distributions with experimental data the design program the required changes in the blade geometry are presented in this paper. Results from a grid refinement study are effected via a transpiration type model. It is therefore a 'profile are also shown to demonstrate that the Navier-Stokes solutions refinement', rather than an 'original' design procedure, and is are grid independent. Author necessarily an iterative solution. A required velocity distribution may be specified over only part of the blade surface. Two examples A88-542 18# are presented in this paper to illustrate the capability of the design THE INFLUENCE OF TURBINE CLEARANCE GAP LEAKAGE program. Author ON PASSAGE VELOCITY AND HEAT TRANSFER NEAR BLADE TIPS. I - SINK FLOW EFFECTS ON BLADE PRESSURE A88-54222# SIDE THREE DIMENSIONAL FLOW IN RADIAL-INFLOW TURBINES D. E. METZGER and K. RUED (Arizona State University, Tempe) M. ZANGENEH-KAZEMI, W. N. DAWES, and W. R. HAWTHORNE ASME, Gas Turbine and Aeroengine Congress and Exposition, (Cambridge University, England) ASME, Gas Turbine and Amsterdam, Netherlands, June 6-9, 1988. 9 p. refs Aeroengine Congress and Exposition, Amsterdam, Netherlands, (ASME PAPER 88-GT-98) June 6-9, 1988. 9 p. refs A study has been conducted to investigate influences of tip (ASME PAPER 88-GT-103) leakage flow on heat transfer and flow development along the The flow through an impeller of a low speed radial-inflow turbine pressure side of a gas turbine blade. An analysis of the sink has been analyzed using a fully three-dimensional viscous program character of the flow situation indicates that high velocities and and good correlations with instantaneous measurements of casing accelerations are generated very near the gap, and an apparatus static pressure and exit flow distribution have been obtained. The was specifically designed to model the phenomena and to permit flow at the exit of the turbine shows a pronounced non-uniformity resolution of the expected localized near-gap heat transfer with a wake region of high absolute flow angle near the casing. enhancement. In the experiments, leakage flow was drawn from The predictions show that the flow is fully attached inside the an adjustable streamwise corner slot in a straight square test impeller, while secondary flows can be observed especially in the channel. A thin stainless steel ohmic-heated test surface adjacent exducer moving low momentum fluid towards the casing-suction to the slot simulated the airfoil surface. Supporting non-intrusive corner. The presence of these secondary flows is discussed with mean and fluctuating flowfield measurements were conducted with reference to classical secondary flow theory. However, the a laser-Doppler anemometer to aid interpretation of the heat comparison of measurements and numerical predictions indicate transfer results and to provide a basis for comparison with future that the wake flow pattern is only partly due to the secondary numerical predictions. The flowfield measurements confirm that flow. It is shown that in fact the tip leakage flow also plays a near the gap the flow is highly accelerated, and indicate apparent significant role in the wake generation and correspondingly some relaminarkation of the initially turbulent boundary layer. The heat modelling of the leakage flow is essential in any attempted transfer measurements show that leakage generates large numerical simulations. Author increases in local heating near the gap. The presence of this undesirable enhancement helps to explain observed in-service A88-54228# material distress and failure of blades that appear to initiate at EFFECTS OF INCIDENCE ON THREE-DIMENSIONAL FLOWS the pressure side tip. Author IN A LINEAR TURBINE CASCADE A. YAMAMOTO and H. NOUSE (National Aerospace Laboratory, A88-54219# Chofu, Japan) ASME, Gas Turbine and Aeroengine Congress THE INFLUENCE OF TURBINE CLEARANCE GAP LEAKAGE and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 15 p. ONPASSAGEVELOCITYANDHEATTRANSFERNEAR refs BLADE TIPS. II - SOURCE FLOW EFFECTS ON BLADE (ASME PAPER 88-GT-110) SUCTION SIDES The paper discusses effects of the incidence on cascade K. RUED and D. E. METZGER (Arizona State University, Tempe) three-dimensional flows and the associated loss generation ASME, Gas Turbine and Aeroengine Congress and Exposition, mechanisms in a low-speed linear turbine cascade with a design Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs turning angle of 107.1 degrees. Using a small five-hole pitot tube, (ASME PAPER 88-GT-99) the cascade flow was surveyed in great detail at fifteen or sixteen Corner source flow experiments were carried out in a water planes located axially throughout the cascade, at five different tunnel to model the influence of tip leakage flow on heat transfer incidences from 7.2 to -53.3 degrees. Blade-to-blade flows at the and flow development along the suction side of a gas turbine cascade midspan and near the endwalls, meridional flows near blade. The most significant effect of the leakage flow is a strong the blade surfaces, and static and total pressure distributions were increase in local heat transfer rates immediately adjacent to the analyzed and many of them were presented by using tomographic gap. The observed heat transfer effects appear to be very important representations of vectors and scalar contours and by streaklines from the standpoint of blade tip durability; they seem to at least (or particle path lines) in order to easily understand the partially account for the sometimes unexplained thermal distress extraordinarily complicated flows and the associated loss and material failures experienced on blade tips in practice. K.K. mechanisms. The present study gives not only new information on the incidence effects but also many solid experimental facts in A88-54220# a quantitative manner to our knowledge already known or A FAST INTERACTIVE TWO-DIMENSIONAL BLADE-TO-BLADE speculated. Author PROFILE DESIGN METHOD G. D. WlLLlS (NEI-APE, Ltd. W. H. Allen, Bedford. England) and A88-54240# A. GOULAS (Salonika, University, Greece) ASME, Gas Turbine BASE PRESSURE IN TRANSONIC SPEEDS - A COMPARISON and Aeroengine Congress and Exposition, Amsterdam, BETWEEN THEORY AND EXPERIMENT Netherlands, June 6-9, 1988. 7 p. refs F. MOTALLEBI (Teheran, University, Iran) ASME, Gas Turbine (ASME PAPER 88-GT-100) and Aeroengine Congress and Exposition, Amsterdam, To help with the design of axial flow stream turbine blading a Netherlands, June 6-9, 1988. 10 p. refs suite of flow analysis programs has been adapted and developed. (ASME PAPER 88-GT-132) 02 AERODYNAMICS

The problem of base pressure in the absence of base bleed transition, natural transition, or a combination of both; i.e., a has been investigated for a symmetrical model with a square-cut transition which started naturally but ended abruptly with a trailing edge. The model was mounted at zero angle of attack in bubble. Author a transonic wind tunnel covering a range of mainstream Mach number from 0.6 to 1.3. The role of vortex shedding was found to A88-54252# be of great importance in the prediction of base pressure. A EFFECT OF FREE-STREAM TURBULENCE, REYNOLDS semi-theoretical analysis for the prediction of base pressure in NUMBER, AND INCIDENCE ON AXIAL TURBINE CASCADE subsonic and transonic speeds which includes the effect of vortex PERFORMANCE shedding is proposed. Author S. B. VIJAYARAGHAVAN and P. KAVANAGH (Iowa State University of Science and Technology, Ames) ASME, Gas Turbine and A88-54242# Aeroengine Congress and Exposition, Amsterdam, Netherlands, PERIODICITY, SUPERPOSITION, AND 3D EFFECTS IN June 6-9, 1988. 8 p. Research supported by General Motors SUPERSONIC COMPRESSOR FLUTTER AERODYNAMICS Corp. refs G. A. GEROLYMOS (SNECMA, Moissy-Cramayel, France) ASME, (ASME PAPER 88-GT-152) Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, A large-scale, low-speed, axial turbine cascade designed for Netherlands, June 6-9, 1988. 8 p. refs high-loading and high-turning was tested over a range of Reynolds (ASME PAPER 88-GT-136) number, turbulence level, and incidence angle. End wall suction Blade-to-blade surface and three-dimensional methods based was applied to provide two-dimensional flow over a large spanwise on the numerical integration of the unsteady Euler equations are region of the airfoil. In all, thirty-six test conditions were examined. presently used to study various aspects of vibrating compressor Overall cascade performance, including mass-averaged loss cascade unsteady aerodynamics in the supersonic flutter region. coefficents at each test flow condition, was determined from The influence of the vibrating blade in a wave-assembly vibration detailed five-hole pressure probe traverses in an exit plane of the mode decays rapidly with pitchwise-distance from the blade; it is cascade. In addition, using glue-on hot-film gages and surface therefore possible to formulate the bladed disk aeroelastic problem oil-flow visualizations, transition and/or separation was identified in any assembly-modal basis. It is projected that three-dimensional over the suction surface of the airfoil. The measured transition methods will replace blade-to-blade surface methods when further start and end points were compared against predictions using increases in computer capacity are realized. O.C. existing transition models. Also, the measured losses were compared against predicted losses from boundary layer calculations based on finite difference analysis. Author A88-54244# DESIGN OF HIGH PERFORMANCE FANS USING ADVANCED AERODYNAMIC CODES A88-54259# GEORGES KARADIMAS (SNECMA, Moissy-Cramayel, France) NUMERICAL ANALYSIS OF AIRFOIL AND CASCADE FLOWS ASME, Gas Turbine and Aeroengine Congress and Exposition, BY THE VISCOUS/INVISCID INTERACTIVE TECHNIQUE Amsterdam, Netherlands, June 6-9, 1988. 6 p. refs C. J. HWANG, F. L. JIANG, J. M. HSlEH (National Cheng Kung (ASME PAPER 88-GT-141) University, Tainan, Republic of China), and S. B. CHANG In the recent past, the performance of transonic fans has been (Chung-Shan Institute of Science and Technology, Taichung, significantly improved. In addition, through the extensive use of Republic of China) /\SME, Gas Turbine and Aeroengine Congress advanced aerodynamic computation codes the development time and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. required has been considerably reduced. Methods used range from refs the definition of airfoils in quasi-three-dimensional flow with (ASME PAPER ~~-GT-I~o) boundary layer optimization to the analysis of three-dimensional Steady, incompressible/subsonic compressible, attached, and inviscid flow for the stage operation at the design point and in separated flows for isolated airfoils and airfoil cascades are off-design conditions. Such a set of methods was used to design investigated via a two-dimensional viscous-inviscid interaction the fan blade of the CFM56-5 engine to a very high performance calculation method. 14 semiinverse method couples a full-potential level. This paper discusses the optimization of rotor and stator code with a laminar/transition/turbulent finite difference code. An airfoils, the assessment of off-design performance, and the algebraic eddy-viscosity formulation is employed to study the operational stability of this fan. A detailed comparison of full size turbulent flow. Empirical data correlations are used to predict the component test data with computation results shows the validity location of the transition from laminar to turbulent flow. The FLARE of these methods and also identifies those areas where progress approximation and inverse method are introduced to treat the is still required. Author separated flows. R.R.

A88-54251# A88-54266# INVESTIGATION OF BOUNDARY LAYER TRANSITION AND SURFACE HEAT TRANSFER FLUCTUATIONS ON A TURBINE SEPARATION IN AN AXIAL TURBINE CASCADE USING ROTOR BLADE DUE. TO UPSTREAM SHOCK WAVE PASSING GLUE-ON HOT-FILM GAGES A. B. JOHNSON, M. J. RIGBY, M. L. G. OLDFIELD, R. W. S. B. VIJAYARAGHAVAN and P. KAVANAGH (Iowa State University AINSWORTH (Oxford University, England), and M. J. OLIVER of Science and Technology, Ames) ASME, Gas Turbine and (Rolls-Royce, PLC, Derby, England) ASME, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 7 p. Research supported by General Motors June 6-9, 1988. 13 p. Research supported by Rolls-Royce, PLC. Corp. refs refs (ASME PAPER 88-GT-151) (Contract F33615-84-C-2475) Experiments were conducted with glue-on hot-film gages in a (ASME PAPER 88-GT-172) large-scale axial turbine cascade to identify transition and/or A theoretical and experimental study of the observed rapid separation on the suction surface of the blade. Standard strain-gage large-scale surface heat transfer rate fluctuations associated with type temperature sensors were adapted and used as the gages the impingement of nozzle-guide-vane trailing edge shock waves and transition and separation were identified by examining the on a transonic turbine rotor blade is presented. A simple first-order mean and RMS voltage output. To assist with interpreting the perturbation analysis of the boundary layer equations indicates output of the gages, surface oil-flow visualizations were used. that the transient adiabatic heating and cooling of the boundary Results of this study showed that transition and separation could layer by passing shock waves and rarefactions can produce high be easily identified with the hot-film gages. Depending upon the temperature gradients, near the surface, leading to large conductive Reynolds number and free stream turbulence level, the suction heat transfer rate f1uc:tuations. The theory predicts fluctuating heat surface boundary layer was found to undergo bubble-induced transfer rates which agree well with experimental values. R.R.

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A88-54278# A88-54288# EFFECT OF SHOCK WAVE MOVEMENT ON AERODYNAMIC EXPERIMENTAL INVESTIGATION OF THE INSTABILITY OF ANNULAR CASCADE OSCILLATING IN THREE-DIMENSIONAL FLOW IN AN ANNULAR COMPRESSOR TRANSONIC FLOW CASCADE HlROSHl KOBAYASHI (National Aerospace Laboratory, Chofu, H. D. SCHULZ and H. E. GALLUS (Aachen, Japan) ASME, Gas Turbine and Aeroengine Congress and Rheinisch-Westfaelische Technische Hochschule, Federal Republic Exposition, Amsterdam, Netherlands, June 6-9, 1988. 11 p. refs of Germany) ASME, Gas Turbine and Aeroengine Congress and (ASME PAPER 88-GT-187) Exposition, Amsterdam, Netherlands, June 6-9, 1988. 14 p. Effects attributable to shock wave movement on cascade flutter DFG-supported research. refs were examined for both turbine and compressor blade rows using (ASME PAPER 88-GT-201) a controlled oscillating annular cascade test facility and a method A detailed experimental investigation was carried out to examine for accurately measuring time-variant pressures on blade surfaces. the influence of blade loading on the three-dimensional flow in an The nature of the effects and the blade surface area influenced annular compressor cascade. Data were acquired over a range of by the shock movement were clarified in a wide range of Mach incidence angles. Included are airfoil and endwall flow visualization, number, reduced frequency, and interblade phase angle. An measurement of the static pressure distribution on the flow passage unsteady aerodynamic force was generated by the shock surfaces, and radial-circumferential traverse measurements. The movement, which significantly affected the occurrence of the data indicate the formation of a strong vortex near the rear of the compressor and turbine cascade flutter. For the turbine cascade, blade passage. This vortex transports low momentum fluid close the interblade phase angle controlled the effect of the force, while to the hub toward the blade suction side and seems to be partly in the compressor, the reduced frequency dominated it. The responsible for the occurrence of a hub corner stall. The effect of chordwise extent on blade surface influenced by the shock increased loading on the growth of the hub corner stall and its movement was suggested to be about 6 percent of the chord impact on the passage blockage is discussed. Detailed mapping length. Author of the blade boundary layer was done to determine the loci of boundary layer transition and flow separation. The data have been compared with results from an integral boundaty layer method. Author A88-54285# BEHAVIOUR OF THE LEG OF THE HORSESHOE VORTEX A88-54289# AROUND THE IDEALIZED BLADE WITH ZERO ATTACK TEST RESULTS AND THEORETICAL INVESTIGATIONS ON ANGLE BY TRIPLE HOT-WIRE MEASUREMENTS THE ARL 19 SUPERSONIC BLADE CASCADE SHlNJl HONAMI, TAKAAKI SHIZAWA (Tokyo, Science University, A. FOURMAUX, R. GAILLARD, G. LOSFELD, and G. MEAUZE Japan), and MASAYUKI TAKAHAMA (Mitsubishi Heavy Industries, (ONERA, Chatillon-sous-Bagneux, France) ASME, Gas Turbine Ltd., Takasago, Japan) ASME, Gas Turbine and Aeroengine and Aeroengine Congress and Exposition, Amsterdam, Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. Netherlands, June 6-9, 1988. 7 p. 8 p. refs (ASME PAPER 88-GT-202) (ASME PAPER 88-GT-197) This paper presents the ONERA contribution in a joint The paper presents flow measurements within the leg protion experimental program on the aerodynamics of supersonic airfoil of the horseshoe vortex. An uncambered blade of constant cascades. The first part deals with the specific ONERA way of thickness downstream with ' a half-circular nose of an idealized running cascade tests: description of the test facility, of the test turbine blade was installed on a flat plate. The six components of model and of the instrumentation and data reduction. Then, after the Reynolds stresses were measured in addition to the three a brief theoretical analysis of the ARL 19 cascade, some mean velocity components at two cross-sectional planes by a experimental results are presented and discussed. Author triple wire probe. The predominant vortical motion of the secondary flow occurs at the corner of the blade and the endwall. The effect of the penetrating motion of the free-stream toward the corner A88-54293# region induced by the vortex on the Reynolds stress is found in INFLUENCE OF DEPOSIT ON THE FLOW IN A TURBINE mean u-squared profiles near the blade, but not in mean v-squared CASCADE profiles. The diffusion of the Reynolds stresses is observed in the A. BOELCS and 0. SARI (Lausanne, Ecole Polytechnique Federale, crossflow direction. Author Switzerland) ASME, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 12 p. Research supported by Brown Boveri et Cie. refs (ASME PAPER 88-GT-207) Factors affecting flow in a gas turbine cascade operating under A8844286 transonic flow conditions were investigated. Special consideration CALIBRATION OF CFD METHODS FOR HIGH MACH NUMBER was given to the effect of the deposit growing on the rotor blade AEROENGINE FLOWFIELDS on the configuration and stability of shock waves. Experiments JOHN R. CHAWNER, GREGORY S. SPRAGLE, and RICHARD J. were carried out in a linear cascade over a range of isentropic MATUS (General Dynamics Corp., Fort Worth, TX) ASME, Gas exit Mach numbers from 0.6 to 1.6 and three different inlet flow Turbine and Aeroengine Congress and Exposition, Amsterdam, angles. The results of the flow field measurements indicate that Netherlands, June 6-9, 1988. 8 p. refs the choked flow conditions are reached at different steady-state (ASME PAPER 88-GT-199) isentropic outlet Mach numbers for the two blade shapes that The level of confidence in several CFD methods for high-Mach were used: the original, 'clean' blade and the blade bearing a aeroengine flowfields was investigated by comparing the CFD simulated deposit. However, the 'deposit', typical for a gas turbine, flowfields, obtained using a beam-warming-based unsteady did not significantly modify the boundary layer separation point. A Navier-Stokes code PARC developed by Cooper (1 987), a comparison of these results with the calculations, using the beam-warming-based parabolized Navier-Stokes (PNS) code, and time-marching method of Denton (1982) yielded good agreement a MacCormack-based PNS code, with experimental data obtained only for the 'clean' blade. for a blunt cone at Mach 10.6, an inlet at Mach 7.4, a combustor I.S. at Mach 2.4, and an axisymmetric plug nozzle at Mach 3.2. These CFD codes showed good overall agreement with experimental A88-54296# data for wall pressures, integrated forces and pressure, Mach TIP LEAKAGE IN A CENTRIFUGAL IMPELLER number, and chemical species profiles. In addition, the PARC code T. Z. FARGE, M. W. JOHNSON, and T. M. A. MAKSOUD (Liverpool, was found to be able to give a very accurate prediction of thrust University, England) ASME, Gas Turbine and Aeroengine for the axisymmetric nozzle. I.S. Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988.

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7 p. SERC-supported research. refs formulation is given in this paper and some preliminary results are (ASME PAPER 88-GT-210) included. Author The effects of tip leakage have been studied using a 1 meter diameter shrouded impeller where a leakage gap is left between A88-54309# the inside of the shroud and the impeller blades. A comparison is A COMPARISON BETWEEN MEASUREMENTS AND made with results for the same impeller where the leakage gap is TURBULENCE MODELS IN A TURBINE CASCADE PASSAGE closed. The static pressure distribution is found to be almost PIETRO ZUNINO, MARINA UBALDI, ANTONIO SATTA, and unaltered by the tip leakage, but significant changes in the ENRICO PElSlNO (Genova, Universita, Genoa, Italy) ASME, Gas secondary velocities alter the size and position of the passage Turbine and Aeroengine Congress and Exposition, Amsterdam, wake. Low momentum fluid from the suction-side boundary layer Netherlands, June 6-9, 1988. 10 p. refs of the measurement passage and tip leakage fluid from the (Contract CNR-86,00938,59) neighboring passage contribute to the formation of a wake in the (ASME PAPER 88-GT-226) suction-side shroud corner region. The inertia of the tip leakage Detailed measurements of mean velocity, turbulence intensity flow then moves this wake to a position close to the center of and Reynolds stresses have been performed in the passage of a the shroud at the impeller outlet. Author cascade of turbine rotor blades. By using the experimental values of the mean velocity, the turbulence quantities are computed with A88-54297# three different turbulence closure models. The results are analyzed and compared with the experimental data. The capability of the PERFORMANCE OF A COMPRESSOR CASCADE closure models to describe the turbulence development associated CONFIGURATION WITH SUPERSONIC ENTRANCE FLOW A - with secondaly flows in a turbine cascade is discussed. Author REVIEW AND COMPARISON OF EXPERIMENTS IN THREE INSTALLATIONS G. K. SEROVY and T. H. OKllSHl (Iowa State University of Science A88-543 14# and Technology, Ames) ASME, Gas Turbine and Aeroengine MEASUREMENT AND MODELLING OF THE GAS TURBINE Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. BLADE TRANSITION PROCESS AS DISTURBED BY WAKES 12 p. refs J. E. LAGRAFF (Slyracuse University, NY), D. A. ASHWORTH (Contract F49620-83-K-0023) (Rolls-Royce, PLC, Derby, England), and D. L. SCHULTZ ASME, (ASME PAPER 88-GT-211) Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, A compressor blade cascade whose airfoil section is Netherlands, June 6-9, 1988. 8 p. refs representative of advanced profiles for Mach 1.4-1.8 operation (Contract AF-AFOSR-85-0295) has been tested with supersonic entrance flow conditions in three (ASME PAPER 88-GT-232) linear-cascade facilities, in order to ascertain the reproducibility of Heat transfer nieasurements were obtained on a transonic test conditions and measured performance, as well as to generate turbine blade undergoing natural transition and simulating the effect data sets for the validation of CFD methods for turbomechanical of NGV wake interactions. Wide-bandwidth heat transfer applications. Attention is presently given to the experimental instrumentation successfully tracked trajectories of both unsteady apparatus- and method-related problems encountered. A wake passing events and transitional turbulent spots on the airfoil high-confidence data set has been obtained. O.C. under the conditions of the simulated gas turbine environment. Based on low-speed theory and results of the final three-dimensional stages of boundary layer transition, the present A88-54302# observations are modeled by a time-marching scheme of both the COMPUTATION OF THE JET-WAKE FLOW STRUCTURE IN A inviscid wake passing interaction and the random generation and LOW SPEED CENTRIFUGAL IMPELLER growth of turbulent spots. R.R. B. L. LAPWORTH and R. L. ELDER (Cranfield Institute of Technology, England) ASME, Gas Turbine and Aeroengine A88-54315# Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. WAKE-BOUNDARY LAYER INTERACTIONS IN AN AXIAL 12 p. refs FLOW TURBINE ROTOR AT OFF-DESIGN CONDITIONS (ASME PAPER 88-GT-217) H. P. HODSON and J. S. ADDISON (Cambridge University, The low speed flow through the shrouded de-Havilland Ghost England) ASME, Gas Turbine and Aeroengine Congress and centrifugal impeller is computed using an incompressible elliptic Exposition, Amsterdam, Netherlands, June 6-9, 1988. 12 p. calculation procedure. The three-dimensional viscous flow Research supported by the Central Electricity Generating Board. equations are solved using the SIMPLE algorithm in an arbitrary refs generalized coordinate system. A non-staggered grid arrangement (ASME PAPER 88-GT-233) is implemented in which pressure oscillations are eliminated using Rotor-blade surface flow visualization, surface-mounted hot-film an amended pressure correction scheme. Flow computations are anemometry, and exit pitot traverses are used to experimentally performed at 'nominal' low speed design and above design flow study the effects of varying the flow coefficient and Reynolds rates, and (on the coarse grids used in the calculations) good number on the performance of a single-stage low-speed turbine agreement is obtained with the experimentally observed jet-wake rotor blade at midspan. Over the Reynolds number range structure of the flow. Author considered, the rotor midspan performance is found to be dominated by the wction surface transition process. The results A88-54303# show that the rotor midspan profile remains unchanged from the A NEW SINGULAR INTEGRAL APPROACH FOR A VERTICAL zero incidence value until pressure side stall occurs. R.R. ARRAY OF AIRFOILS DENNIS WILSON (Texas, University, Austin) ASME, Gas Turbine A88-54318# and Aeroengine Congress and Exposition, Amsterdam, A UNIFIED SOLUTION METHOD FOR THE FLOW Netherlands, June 6-9, 1988. 7 p. refs CALCULATIONS ALONG S1 AND S2 STREAM SURFACES (ASME PAPER 88-GT-218) USED FOR THE COMPUTER-AIDED DESIGN OF Recently, a singular integral method was developed for solving CENTRIFUGAL COMPRESSORS two-dimensional compressible potential flows. The original QINGHUAN WANQ and HAOYU YU (Chinese Academy of formulation limited the applicability to single bodies in a uniform Sciences, Institute o'f Engineering Thermophysics, Beijing, People's freestream. Currently, modifications are beig made so that the Republic of China) ASME, Gas Turbine and Aeroengine Congress flowfield around multiple bodies can also be calculated. Because and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 6 p. of the unique manner in which the integral equations are formulated, refs they are especially well-suited for analysis and inverse design (ASME PAPER 88-GT-237) calculations of a row of similar airfoils. A brief descripton of the In order to facilitate the aerodynamic design for the

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computer-aided design of centrifugal compressor, a unified direct in finite-difference formulation. The method assumes a problem method for the flow calculations along S1 and S2 stream traveling-wave assembly mode of vibration. In this manner, the surfaces is presented. A single stream function equation expressed flow is computed in a single channel by applying the corresponding by nonorthogonal curvilinear coordinates and the unified matrix chorochronical periodicity condition at the permeable pitchwise direct solution for the governing equation are used. This method limits. The blade vibratory mode is an input to the method obtained greatly simplified the quasi-three-dimensional and full dimensional by a standard finite element method structural analysis code. A computing program, while improving the computing accuracy and number of results are presented, for a transonic fan rotor, illustrating the convergence rate. Numerical examples illustrate the advantages the possibilities of the method, both in started and unstarted of the new technique for the computer-aided design of centrifugal supersonic flow conditions. Author compressors. Author A00-54341# A00-54323# AN EXPERIMENTAL INVESTIGATION OF A VORTEX FLOW TURBULENCE MEASUREMENTS AND SECONDARY FLOWS CASCADE IN A TURBINE ROTOR CASCADE YAN-PING TANG and MAO-ZHANG CHEN (Beijing Institute of D. G. GREGORY-SMITH (Durham, University, England), J. A. Aeronautics and Astronautics, People’s Republic of China) ASME, WALSH (Logica Space and Defence Systems, Ltd., London, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, England), C. P. GRAVES (Gilbert Gilkes and Gordon, Ltd., Kendal, Netherlands, June 6-9, 1988. 7 p. England), and K. P. FULTON (Rolls-Royce, PLC, Derby, England) (ASME PAPER 88-GT-265) ASME, Gas Turbine and Aeroengine Congress and Exposition, A new type of compressor cascade, called the vortex flow Amsterdam, Netherlands, June 6-9, 1988. 10 p. Research cascade (shortly VFC), has been developed in the paper. The supported by Ministry of Defence Procurement Executive, VFC is made up of the normal compressor cascade (shortly NCC) Rolls-Royce, PLC, and SERC. refs with NACA-65-0010 profile and vortex generator. Experiments are (ASME PAPER 88-GT-244) conducted for researching the effects of a large scale streamwise This paper presents results for turbulence measurements that control vortex on the flow structure inside cascade passage. The have been made using hot-wire anemometry in the endwall region results are encouraging. Based on the present investigation the of a high turning rotor blade cascade. It is shown that the levels vortical flow pattern and loss mechanism of VFC have been of turbulence are very high in the regions of the flowfield containing discussed. Author the passage vortex and its associated loss core. A comparison with the total pressure loss measurements illustrates the A00-54343# mechanisms of loss generation within the cascade. The growth of THE EFFECT OF THE REYNOLDS NUMBER ON THE the total pressure loss and turbulent kinetic energy were found to THREE-DIMENSIONAL FLOW IN A STRAIGHT COMPRESSOR have similar distributions through the cascade. Author CASCADE VACLAV CYRUS (Statni Vyzkumny Ustav Konstrukce Stroju, A00-54327# Bechovice, Czechoslovakia) ASME, Gas Turbine and Aeroengine STRUCTURE OF TIP CLEARANCE FLOW IN AN ISOLATED Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. AXIAL COMPRESSOR ROTOR 9 p. refs MASAHIRO INOUE and MOT00 KUROUMARU (Kyushu University, (ASME PAPER 88-GT-269) Fukuoka, Japan) ASME. Gas Turbine and Aeroengine Congress A straight compressor cascade of aspect ratio 2 was tested in and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. a low speed tunnel within Reynolds number Re(1) = 45,000 - Research supported by the Kurata Foundation. refs 150,000 and inlet flow angle alpha 1 = 35 - 48 deg. The profile (ASME PAPER 88-GT-251) of the blade was NACA 65-12-10. The purpose of the paper was Ensemble-averaged and phase-locked flow patterns in various to obtain data on three-dimensional flow in a straight cascade at tip clearances of two axial compressor rotors were obtained by a low Reynolds numbers. Some experimental results on secondary periodic multisampling technique with a hot wire in the clearance flow have been made into simple correlation relations. Author and with a high response pressure sensor on the casing wall. A leakage flow region distinct from a through flow region exists at every clearance. In the case of a small tip clearance, the leakage A00-54347# jet flow interacts violently with the through flow near the leading A NEW VARIATIONAL FINITE ELEMENT COMPUTATION FOR edge, and a rolling-up leakage vortex decays downstream. As the AERODYNAMIC INVERSE PROBLEM IN TURBINES WITH clearance increases, a stronger leakage vortex comes into LONG BLADES existence at a more downstream location, and a reverse flow due REN QIN, FENMING YI, and HONGGUANG WANG (Harbin Institute to the vortex grows noticeably. A scraping vortex is recognized at of Technology, People’s Republic of China) ASME, Gas Turbine the pressure side near the trailing edge only for the small clearance. and Aeroengine Congress and Exposition, Amsterdam, A horse-shoe vortex appears in the upstream half of the through Netherlands, June 6-9, 1988. 6 p. refs flow region for every tip clearance. The solidity does not affect (ASME PAPER 88-GT-275) the flow pattern substantially except for the interaction of the A novel finite element computation for aerodynamic inverse leakage vortex with the adjacent blade and wake. Author problems in turbines with long blades is presented with allowance made for the effect of blade thickness, blade force, and other A00-54331# factors on aerodynamic parameters. A comparison is made NUMERICAL INTEGRATION OF THE 3D UNSTEADY EULER between the computational results and those obtained using the EQUATIONS FOR FLUTTER ANALYSIS OF AXIAL FLOW finite difference method in noncurvilinear coordinates. It is noted COMPRESSORS that the present computer program can also be applied to the G. A. GEROLYMOS (SNECMA, Moissy-Cramayel, France) ASME, aerodynamic design of axial compressors with some Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, modifications. K.K. Netherlands, June 6-9, 1988. 10 p. refs (ASME PAPER 88-GT-255) A00-54356# In order to analyze axial-flow compressor flutter, methods are NUMERICAL SIMULATION OF INVISCID TRANSONIC FLOW required that compute the unsteady flow through vibrating THROUGH NOZZLES WITH FLUCTUATING BACK PRESSURE cascades. A three-dimensional fully nonlinear method has been A. BOELCS, T. H. FRANSSON (Lausanne, Ecole Polytechnique developed by numerically integrating the three-dimensional Federale. Switzerland), and M. F. PLATZER (US. Naval unsteady Euler equations, in the time-domain. The equations are Postgraduate School, Monterey, CA) ASME, Gas Turbine and discretized in a moving grid, which conforms with the vibrating Aeroengine Congress and Exposition, Amsterdam, Netherlands, blades and are integrated using the explicit MacCormack scheme, June 6-9, 1988. 14 p. Research sponsored by the National

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Research Council. refs viscous/inviscid flows. The present method involves a global (ASME PAPER 88-GT-287) numerical inviscid flow region calculation based on a transonic A numerical method based on the flux vector splitting approach small disturbance method coupled to a compressible turbulent is used to solve the problem of unsteady one-dimensional and boundary layer code. The local transonic shock/turbulent two-dimensional inviscid transonic flow, with emphasis on the boundary-layer interaction is included as a local module in the determination of the shock position through nozzles with shock location to produce a general hybrid inviscid boundary-layer time-varying back pressure. Both the amplitude and frequency of interaction analysis code. R.R. the imposed fluctuating exit pressure are found to be important parameters in locating the unsteady shock. It is also found that A88-54940# the average unsteady shock position is not necessarily identical INCOMPRESSIBLE INDlClAL RESPONSE OF INFINITE with the steady-state position, and that an unsteady shock AIRFOILS IN TANDEM - SOME ANALYTICAL RESULTS movement imposed by oscillating back pressure may introduce a V. G. MENGLE (California, University, Los Angeles) IN: significant lift and moment. R.R. Developments in Mechanics. Volume 14(b) - Midwestern Mechanics Conference, 20th, West Lafayette, IN, Aug. 31-Sept. 2, 1987, A88-54375*# National Aeronautics and Space Administration. Proceedings. West Lafayette, IN, Purdue University, 1987, p. Lewis Research Center, Cleveland, Ohio. 857-862. refs EXPERIMENTAL INVESTIGATION OF THE PERFORMANCE OF The aerodynamic response to arbitrary motion of infinite airfoils A SUPERSONIC COMPRESSOR CASCADE in tandem can be found from their indicial response. Such an T. L. TWEEDT (NASA, Lewis Research Center, Cleveland, OH), indicial response i:j found here for the case of simultaneous H. A. SCHREIBER, and H. STARKEN (DFVLR, lnstitut fuer step-change in the quasi-steady circulations of all the airfoils. In Antriebstechnik, Cologne, Federal Republic of Germany) ASME, particular, the Laplace-transformed lift response is found in terms Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, of Gauss hypergeometric functions and analytically studied in the Netherlands, June 6-9, 1988. 13 p. refs complex Laplace-variable domain. The small-time asymptotic (ASME PAPER 88-GT-306) solution is shown to be derivable from that of the corresponding Supersonic cascade wind tunnel results are presented for a unstaggered cascadte by simply replacing the blade gap d by jd, linear, supersonic compressor cascade derived from the near-tip where j = sq rt -1. Then, l-point Pade approximants are used to section of a high-throughflow axial flow compressor rotor over the find the indicial response for small and large times, and it turns inlet Mach number range of 1.30-1.71. Laser anemometry was out to be oscillation-damped. The inadequacy of l-point Pade used to obtain flow-velocity measurements showing the wave approximants to represent the indicial response for all times is pattern in the entrance region. Attention is given to the attributed to the Stokes phenomenon. Author uniqueincidence relationship for this cascade, which relates the supersonic inlet Mach number to the inlet flow direction. An A88-54941# Purdue Univ., West Lafayette, Ind. empirical correlation is obtained for the influence of the independent AERODYNAMICALLY FORCED RESPONSE OF AN AIRFOIL parameters of back pressure, axial velocity density ratio, and blade INCLUDING PROFILE AND INCIDENCE EFFECTS element performance. O.C. HSIAO-WE1 D. CHIANG and SANFORD FLEETER (Purdue University, West Lafayette, IN) IN: Developments in Mechanics. A88-54869 Volume 14(b) - Midwestern Mechanics Conference, 20th, West NEAR-FIELD PRESSURE RADIATION AND FLOW Lafayette, IN, Aug. 31 -Sept. 2, 1987, Proceedings. West Lafayette, CHARACTERISTICS IN LOW SUPERSONIC CIRCULAR AND IN, Purdue University, 1987, p. 865-870. USAF-NASA-supported ELLIPTIC JETS research. refs E. GUTMARK. K. C. SCHADOW. K. J. WILSON. and C. J. BICKER A structural dynamics model is developed and utilized to predict (U.S. Navy, Naval Weapons Center, China Lake, CA) Physics of the effects of airfoil profile, incidence angle, and two-dimensional Fluids (ISSN 0031-9171), vol. 31, Sept. 1988, p. 2524-2532. refs gust direction on the aerodynamically forced response of an airfoil The near-field pressure fluctuations of circular and elliptic in an incompressible flow. An energy balance is performed between underexpanded supersonic jets were studied experimentally. Unlike the unsteady aerodynamic work and the energy dissipated through the case of low subsonic jets, the pressure fluctuation the airfoil structural and aerodynamic damping, with predictions of characteristics at the minor axis plane of the elliptic jet were very the unsteady aerodynamics obtained from a complete first order different from those of the major axis plane. The amplitude of the model. It is then demonstrated that the steady aerodynamic loading pressure fluctuations at the minor axis was more than an order of and the gust direction strongly affect the amplitude of response. magnitude higher than at the other plane. This section of the jet Also, classical thin airfoil unsteady aerodynamic models result in was also characterized by a larger spreading rate and higher nonconservative predictions. Author amplification rate of the velocity fluctuations. The circular jet was similar to the major axis plane of the elliptic jet. The spectra of A88-54942# the near-field pressure fluctuations of both jets exhibited the highest THE AERODYNAMICS OF AN ANNULAR CASCADE OF peak at a frequency corresponding to the jets' preferred mode THREE-DIMENSIONAL AIRFOILS frequency. The spectral peak related to the screech tone was JOSEPH NEAL and SANFORD FLEETER (Purdue University, West much stronger at the minor axis plane and had the same frequency Lafayette, IN) IN: Developments in Mechanics. Volume 14(b) - as at the other plane. The amplitude of the dominant pressure Midwestern Mechanics Conference, 20th, West Lafayette, IN, Aug. fluctuation frequencies was mapped in the entire near field, and 31-Sept. 2, 1987, Proceedings. West Lafayette, IN, Purdue each one was found to be dominant in a different region. Author University, 1987, p. 871-876. A series of experiments are described which quantify the A88-54907# aerodynamic performance of a three-dimensional airfoil row APPLICATION OF A HYBRID ANALYTICAL/NUMERICAL designed to operate over a wide range of incidence angles with METHOD TO THE PRACTICAL COMPUTATION OF low losses and no flow separation. The airfoils, designed at SUPERCRITICAL VISCOUS/INVISCID TRANSONIC FLOW NASA-Lewis using an inverse, inviscid, design code with boundary FIELDS layer correction, have a high thickness-to-chord ratio, spanwise G. R. INGER (Iowa State University of Science and Technology, varying flow turning, and a swept trailing edge to maintain constant Ames) IN: Developments in Mechanics. Volume 14(a) - Midwestern solidity over the airfoil span. Author Mechanics Conference, 20th, West Lafayette, IN, Aug. 31-Sept. 2, 1987, Proceedings. West Lafayette, IN, Purdue University, 1987, A88-54943# p. 366-371. AERODYNAMICALLY FORCED RESPONSE OF A nonasymptotic triple deck theory of shock-turbulent boundary STRUCTURALLY MISTUNED BLADED DISKS IN SUBSONIC layer interaction has been applied to the analysis of transonic FLOW

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VINCENT R. CAPECE, GREGORY H. HENDERSON, and A88-55093# SANFORD FLEETER (Purdue University, West Lafayette, IN) IN: QUADRATURE FORMULA FOR A DOUBLE-POLE SINGULAR Developments in Mechanics. Volume 14(b) - Midwestern Mechanics INTEGRAL Conference, 20th, West Lafayette, IN, Aug. 31-Sept. 2, 1987, RAJENDRA K. BERA (National Aeronautical Laboratory, Bangalore, Proceedings. West Lafayette, IN, Purdue University, 1987, p. India) AlAA Journal (ISSN 0001-1452), vol. 26, June 1988, p. 877-882. 752-754. The subsonic aerodynamically forced response of a structurally Stark’s (1971) quadrature formula for Cauchi integrals is mistuned bladed disk is investigated by developing a mathematical presently extended in a straightfoward fashion to evaluate the model which includes the effects of aeroelastic coupling. A dual double-pole singular integrals typically encountered in linear lifting mode representative of the forced vibration is utilized together surface theory. The advantage of Stark’s formula is that it is with a two-dimensional,inviscid, subsonic, unsteady aerodynamic tailorable for integrands containing a weight function that is airfoil cascade model. By considering a ten-bladed rotor, it is shown assumed to be positive and integrable, though not necessarily that the response mode and the unsteady aerodynamics determine regular. O.C. if mistuning is beneficial. Author A88-55094’# North Carolina State Univ., Raleigh. GRID EMBEDDING TECHNIQUE USING CARTESIAN GRIDS A88-54944# FOR EULER SOLUTIONS NONUNIFORM VANE SPACING EFFECTS ON ROTOR BLADE R. A. MICHELTREE, H. A. HASSAN (North Carolina State FORCED RESPONSE AND NOISE GENERATION University, Raleigh), and M. D. SAWS (NASA, Langley Research JOHN R. FAGAN, JR. and SANFORD FLEETER (Purdue University, Center, Hampton, VA) AlAA Journal (ISSN 0001-1452). vol. 26, West Lafayette, IN) IN: Developments in Mechanics. Volume June 1988, p. 754-756. refs 14(b) - Midwestern Mechanics Conference, 20th, West Lafayette, (Contract NCC1-22) IN, Aug. 31 -Sept. 2, 1987, Proceedings. West Lafayette, IN, Purdue Grid-embedding techniques are presently applied to the University, 1987, p. 883-888. solutions of the Euler equations on Cartesian grids for the NACA A mathematical model is developed to analyze the effects on 0012 airfoil and the multielement SKFl.l airfoil at transonic speeds. the rotor unsteady aerodynamics associated with altering the Based on comparisons with solutions on fine grids, it is shown harmonic content of the rotor inlet flow field, accomplished by that the present scheme, when used in conjunction with the nonuniform circumferential spacing of the airfoils in the upstream Runge-Kutta time-stepping scheme as well as Cartesian grids, vane row. The stator-rotor interactions are modeled by a cascade yields reduced memory requirements and a substantial reduction of rotor blades moving relative to a nonuniform circumferentially in computational time, without loss of accuracy. O.C. spaced stator vane cascade. The rotor inlet flow field is determined by tracking a typical rotor blade through the wakes of the stator A88-55313# row, with each velocity history decomposed into harmonic NUMERICAL SOLUTION OF THE HYPERSONIC VISCOUS components. This model is then applied to a modern compressor configuration and the beneficial effects of nonuniform vane spacing SHOCK LAYER EQUATIONS WITH CHEMICAL NONEQUILIBRIUM on both forced response and noise generation demonstrated. Author J. W. SHEN IAF, International Astronautical Congress, 39th, Bangalore, India, Oct. 8-15, 1988. 10 p. refs (IAF PAPER ST-86-08) A88-54946# The surface pressure distribution is measured for a blunt PREDICTION OF TURBULENCE GENERATED RANDOM sphere-cone in a hypersonic wind tunnel to check the reliability of VIBRATIONAL RESPONSE OF TURBOMACHINERY BLADING the numerical results of the implicit finite-difference scheme. The THOMAS E. BOOTH and SANFORD FLEETER (Purdue University, hypersonic nonequilibrium laminar flow over slender sphere-cone West Lafayette, IN) IN: Developments in Mechanics. Volume is calculated and the global continuity equation and normal 14(b) - Midwestern Mechanics Conference, 20th, West Lafayette, momentum equation are solved. It is shown that schematic viscosity IN, Aug. 31 -Sept. 2, 1987, Proceedings. West Lafayette, IN, Purdue exists in the implicit finite-difference scheme, although the physical University, 1987, p. 894-899. USAF-sponsored research. distortion due to the schematic viscosity is small and can be An analysis is developed to predict the turbulence generated neglected in the body region. The numerical results are presented single-degree-of-freedom bending and torsion mode response of and compared with results using other methods. R.B. a blade row in a subsonic compressible flow field. The turbulence is assumed to be random in the neighborhood of the blade natural N88-28860# Messerschmitt-Boelkow-Blohm G.m.b.H., Bremen frequency of interest and to generate constant amplitude, harmonic, (West Germany). Civil Transport Aircraft Div. unsteady aerodynamic forces and moments on the blading with DELTA WING CONFIGURATIONS equally distributed frequencies. The resulting random vibrations J. SZODRUCH ln AGARD, Boundary Layer Simulation and Control thus occur at the blade natural frequency. The unsteady in Wind Tunnels p 30-49 Apr. 1988 aerodynamics generated by the blade response and the effect of Avail: NTlS HC A20/MF A01 blade aerodynamic coupling are also considered. Author The flow field over a slender delta wing at angle of attack immersed in a supersonic stream can be divided into two characteristic regions. The windward or pressure side faces the A88-55077*# National Aeronautics and Space Administration. oncoming flow and is strongly influenced by the bow shock wave; Langley Research Center, Hampton, Va. the leeward or suction side is dominated by the effects of MULTIGRID ACCELERATION OF THE FLUX-SPLIT EULER inviscid/viscous interaction. It is mainly the leeward flow which is EQUATIONS then affected by Reynolds number changes and especially these W. KYLE ANDERSON, JAMES L. THOMAS (NASA, Langley effects are discussed in more detail. In the past, for subsonic, Research Center, Hampton, VA), and DAVID L. WHITFIELD transonic, and supersonic free stream Mach numbers the essential (Mississippi State University, Mississippi State) AlAA Journal issue of design with slender wings, where vortices occur over the (ISSN 0001-1452), vol. 26, June 1988, p. 649-654. Previously cited wing at virtually every flight condition, is to fix the location of the in issue 07, p. 831, Accession no. A86-19784. refs separation lines so that the vehicle is always controllable. This is why Reynolds number effects in these flow regimes were A88-55078# considered of secondary importance. On the other hand at EFFICIENT EULER SOLVER WITH MANY APPLICATIONS hypersonic speeds the influence of Reynolds number on peak GIN0 MORETTI (G.M.A.F., Inc., Freeport, NY) AlAA Journal heating as well as on the development and size of characteristic (ISSN 0001-1452), vol. 26, June 1988, p. 655-660. Previously cited patterns in the flow field are more important. Here hypersonic in issue 08, p. 1037, Accession no. A87-22576. refs viscous interaction is dominating, especially near the wing apex,

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and the vortices induce high rates of heat transfer along the are well-documented. The effects of acceleration and deceleration attachment line. The discussion is confined to free stream Mach on the aerodynamic forces of a wing have not been explored in numbers from high subsonic to supersonic. With respect to depth because a specially designed unsteady testing facility is Reynolds number effects it is of major importance to define the necessary. The present water channel is able to provide a wide different types of vortical flow in that velocity range and to consider variety of free stream conditions. The test section of the water the influence of wing geometry. Author channel measures 1'9-in. by 18-in. and has a maximum flow rate of 3 ft/sec. In addition, a rotating gate provides programmable N88-28882*# Texas A8M Univ., College Station. unsteady flow velocities. GRA INVESTIGATION OF HELICOPTER ROTOR BLADE/WAKE INTERACTIVE IMPULSIVE NOISE N88-28886# Florida State Univ., Tallahassee. Fluid Mechanics S. J. MILEY, G. F. HALL, and E. VONLAVANTE Jan. 1987 Research Lab. 117 p UNSTEADY FLOW PAST AN NACA 0012 AIRFOIL AT HIGH (Contract NCA2-OR-773-301) ANGLES OF ATTACK Technical Report, Jul. 1986 - Dec. 1987 (NASA-CR-177435; NAS 1.26:177435) Avail: NTlS HC AO6/MF A. KROTHAPALLI, L. LOURENCO, and L. VANDOMMELEN 2 A01 CSCL01A Mar. 1988 26 p An analysis of the Tip Aerodynamic/Aeroacoustic Test (TAAT) (Contract AF-AFOSR .0243-86) data was performed to identify possible aerodynamic sources of (AD-A194650; FMRL-TR-2; AFOSR-88-0415TR) Avail: NTlS HC bladelvortex interaction (BVI) impulsive noise. The identification is AO3/MF A01 CSCL 01C based on correlation of measured blade pressure time histories A whole field experimental technique, commonly referred to with predicted blade/vortex intersections for the flight condition(s) as Particle Image Velocimetry, was used for the measurement of where impulsive noise was detected. Due to the location of the the instantaneous two-dimensional velocity fields about an recording microphones, only noise signatures associated with the impulsively started NACA 0012 airfoil at high angles of attack. advancing blade were available, and the analysis was accordingly The velocity field was measured with sufficient accuracy, such restricted to the first and second azimuthal quadrants. The results that the time evolution of the vorticity field was obtained. The show that the blade tip region is operating transonically in the experiments were performed in a towing at a Reynolds number of azimuthal range where previous BVI experiments indicated the 1400, based on the chord of the airfoil. For angles of attack impulsive noise to be. No individual bladehortex encounter is greater than about 20 deg, the flow field at the upper surface of identifiable in the pressure data; however, there is indication of the airfoil show large scale vortical motions with the following multiple intersections in the roll-up region which could be the origin time dependent scenario. At the initial stages of the airfoil startup, of the noise. Discrete blade/vortex encounters are indicated in a separation bubble iit the leading edge was generated and with the second quadrant; however, if impulsive noise were produced time, it grows into an isolated primary vortex which dominated the here, the directivity pattern would be such that it was not recorded whole flow field. Trailing behind this primary vortex were two counter by the microphones. It is demonstrated that the TAAT data base rotating vortices. This multiple vortex structure grow together and is a valuable resource in the investigation of rotor move along the upper surface until it reaches the trailing edge. At aerodynamic/aeroacoustic behavior. Author this time, the primary vortex induces a trailing edge vortex. The primary and trailing edge vortices then form the wake flow field. N88-28883# Max-Planck-lnstitut fuer Stroemungsforschung, GRA Goettingen (West Germany). NOISE GENERATION AND BOUNDARY LAYER EFFECTS IN N88-28887# Dayton Univ., Ohio. Research Inst. VORTEX-AIRFOIL INTERACTION AND METHODS OF DIGITAL AN INTEGRAL EQUATION FOR THE LINEARIZED UNSTEADY HOLOGRAM ANALYSIS FOR THESE FLOW FIELDS Interim SUPERSONIC FLOW OVER A WING Final Report, May 1986 - Report No. 2, 28 Nov. 1987 - 28 Mar. 1988 Aug. 1987 G. E. MElER 31 Mar. 1988 10 p KARL G. GUDERLEY Dec. 1987 79 p (Contract DAJA45-87-C-0051) (Contract F33615-86-1;-3200) (AD-A194191) Avail: NTlS HC A02/MF A01 CSCL 20D (AD-Al93773; UDR-TH-87-95; AFWAL-TR-87-3107) Avail: NTlS For the generation of impulsive sound waves caused by parallel HC A05lMF A01 CSCL 20D interaction of a vortex and an airfoil in a plane flow field, two This report derives an integral equation for the linearized different mechanisms are responsible by experimental evidence. supersonic unsteady potential flow over a wing. Every integral The first one originates from the area of the stagnation point of equation formulation for a problem that appears originally in the the airfoil: a temporal increase of pressure and density - in form of a partial differential equation presupposes the availability consequence of the incoming vortex - relaxes by sound wave of a fundamental solution. Such a fundamental solution is available emission, when the vortex vanishes behind the airfoils nose. This for the problem at hand in the literature. It is rederived here to is called a compressibility wave. The second one is reasoned by show its particular properties. The integral equation originally a supersonic flow regime, which appears, when the stationary obtained requires one to carry out a limiting process in which one airfoil flow is augmented by the flow field of the vortex: at the approaches the planform from above or below. This formulation shoulder of the airfoil we get an unsteady return to subsonics by is brought into a form in which this limiting process no longer a shock wave. This moves upstream after the vortex has passed appears and one works solely with information available at the and is named transonic wave. Evidently both mechanisms only planform. Examples which .can be treated analytically bring some occur, if the flow field at the airfoil is augmented by the vortex, properties which have a bearing on a numerical approach into Le., the vortex has a special spin orientation with respect to the sharper focus. GRA airfoil. GRA N88-28891'# Kansas Univ. Center for Research, Inc., Lawrence. N88-28884# University of Southern California, Los Angeles. Dept. Flight Research Lab. of Aerospace Engineering. CALCULATION OF AERODYNAMIC CHARACTERISTICS OF UNSTEADY WATER CHANNEL Final Report, Dec. 1984 - Dec. AIRPLANE CONFIGURATIONS AT HIGH ANGLES OF ATTACK 1987 Final Report CHIH-MING HO 29 Mar. 1988 15 p J. B. TSENG and C. EDWARD LAN Oct. 1988 116 p (Contract AF-AFOSR-0064-85) (Contract NAG1-635) (AD-A194231; AFOSR-88-0466TR) Avail: NTlS HC A03/MF A01 (NASA-CR-4182; NAS 1.26:4182; CRINC-FRL-730-1) Avail: CSCL 148 NTlS HC AO6/MF AO'I CSCL 01A When an airplane undergoes maneuvering, the motion includes Calculation of longitudinal and lateral directional aerodynamic many modes: pitching, plunging, translation, acceleration and characteristics of airplanes by the VORSTAB code is examined. deceleration. The aerodynamics of the first three types of motion The numerical predictions are based on the potential flow theory

797 02 AERODYNAMICS with corrections of high angle of attack phenomena; namely, vortex N88-28895'# National Aeronautics and Space Administration. flow and boundary layer separation effects. To account for the Langley Research Center, Hampton, Va. vortex flow effect, vortex lift, vortex action point, augmented vortex STEADY AND UNSTEADY TRANSONIC PRESSURE lift and vortex breakdown effect through the method of suction MEASUREMENTS ON A CLIPPED DELTA WING FOR analogy are included. The effect of boundary layer separation is PITCHING AND CONTROL-SURFACE OSCILLATIONS obtained by matching the nonlinear section data with the three ROBERT W. HESS, F. W. CAZIER, JR., and ELEANOR C. dimensional lift characteristics iteratively. Through correlation with WYNNE Washington, D.C. Oct. 1986 118 p MF as results for nine fighter configurations, it is concluded that reasonably supplement accurate prediction of longitudinal and static lateral directional (NASA-TP-2594; L-16082; NAS 1.60:2594) Avail: NTlS HC aerodynamics can be obtained with the VORSTAB code up to an AO6IMF A01 CSCL 01A angle of attack at which wake interference and forebody vortex Steady and unsteady pressures were measured on a clipped effect are not important. Possible reasons for discrepancy at higher delta wing with a 6-percent circular-arc airfoil section and a angles of attack are discussed. Author leading-edge sweep angle of 50.40 deg. The model was oscillated in pitch and had an oscillating trailing-edge control surface. Measurements were concentrated over a Mach number range from 0.88 to 0.94; less extensive measurements were made at Mach N88-28893# Advisory Group for Aerospace Research and numbers of 0.40, 0.96, and 1.1 2. The Reynolds number based on Development, Neuilly-Sur-Seine (France). mean chord was approximately 10 x 10 to the 6th power. The AERODYNAMIC DATA ACCURACY AND QUALITY: interaction of wing or control-surface deflection with the formation REQUJREMENTS AND CAPABILITIES IN WIND TUNNEL of shock waves and with a leading-edge vortex generated complex TESTING pressure distributions that were sensitive to frequency and to small MARION L. LASTER (Arnold Engineering Development Center, changes in Mach number at transonic speeds. Author Arnold Air Force Station, Tenn.) Jul. 1988 13 p Presented at the AGARD Fluid Dynamics Panel Symposium, Naples, Italy, 28 Sep. - 1 Oct. 1987 N88-29731# National Aeronautical Establishment, Ottawa (AGARD-AR-254; ISBN-92-835-0468-2) Avail: NTlS HC AOBIMF (Ontario). Unsteady Aerodynamics Lab. A0 1 AIRCRAFT DYNAMICS: AERODYNAMIC ASPECTS AND WIND This report presents a technical evaluation and assessment of TUNNEL TECHNIQUES the AGARD Fluid Dynamics Panel Symposium on Aerodynamic K. J. ORLIK-RUECKEMANN ln AGARD, The Flight of Flexible Data Accuracy and Quality; Requirements and Capabilities in Wind Aircraft in Turbulence: State-of-the-Art in the Description and Tunnel Testing, held in September 1987 in Naples, Italy. The major Modelling of Atmospheric Turbulence 14 p Dec. 1987 Previously issues addressed were: what data acuracy is needed by users; announced as N88-13320 what accuracy is presently achieved; and what can be done to Avail: NTlS HC AO9/MF A01 improve the situation? Users have asked that cruise drag be The dynamic behavior of modern fighter aircraft depends more measured to a precision of one drag count for transports and two and more on unsteady aerodynamics. Until recently, the designer for military fighters; it was shown that this is possible when concentrated on classical problems such as aeroelasticity and reference methods can be used. However, one or two drag count flutter. Dynamic stability parameters were most often determined uncertainty is not state-of-the-art for the direct scaling concept by low angle of attack calculation methods, without much recourse and improvement will require.a thorough understanding of all these to experiment. The results obtained from the few dynamic parameters which significantly contribute to wind tunnel uncertainty, experiments performed were used to confirm the absence of including bias and precision. A reduction in total uncertainty appears problems rather than as design parameters. New requirements for possible but a reduction to a level of one or two drag count also fighter aircraft performance include the ability to fly at high angles appears formidable. Author of attack in the presence of extensive regions of separated or vortical flows, relaxed static stability, greatly increased agility, and an interest in unorthodox geometries such as closely coupled canard or tail first configurations. The time lags and unsteady N88-28894*# Boeing Commercial Airplane Co., Seattle, Wash. phenomena associated with flow fields resulting from rapid VARIABLE SWEEP TRANSITION FLIGHT EXPERIMENT maneuvers and large amplitude motions significantly affect the (VSTFE)-PARAMETRIC PRESSURE DISTRIBUTION dynamic behavior of modern fighter aircraft and become as BOUNDARY LAYER STABILITY STUDY AND WING GLOVE important for aircraft design as the classical static performance DESIGN TASK Contractor Report, Feb. 1983 - Nov. 1984 criteria. A review is made of the various aerodynamic aspects RODGER A. ROZENDAAL Washington, D.C. Jun. 1986 affecting aircraft dynamic behavior and some experimental 167 p techniques. Author (Contract NASl-15325) (NASA-CR-3992; NAS 1.26:3992; D6-52511) Avail: NTlS HC AO8IMF A01 CSCL 01A N88-29747# Southwest Research Inst., San Antonio, Tex. The Variable Sweep Transition Flight Experiment (VSTFE) was A STUDY OF THE EFFECT OF RANDOM INPUT MOTION ON initiated to establish a boundary-layer transition data base for LOW REYNOLDS NUMBER FLOWS Final Report, Sep. 1985 - laminar flow wing design. For this experiment, full-span Nov. 1987 upper-surface gloves will be fitted to a variable sweep F-14 aircraft. JAMES F. UNRUH, JOEL T. PARK, and JAMES E. JOHNSON The results of two initial tasks are documented: a parametric May 1988 64 p pressure distribution/boundary-layer stability study and the design (Contract NO0014-85-C-0840) of an upper-surface glove for Mach 0.8. The first task was (AD-A195559; SWRI-8814) Avail: NTlS HC A04lMF A01 CSCL conducted to provide a data base from which wing-glove pressure 20D distributions could be selected for glove designs. Boundary-layer The SwRl (Southwest Research Institute) large water tunnel stability analyses were conducted on a set of pressure distributions was modified by the addition of a large test section (.71 m x .81 for various wing sweep angles, Mach numbers, and Reynolds m x 1.8 m long) to provide low Reynolds number flows with low number in the range of those anticipated for the flight-test program. blockage for models in a highly separated flow condition. Flow The design procedure for the Mach 0.8 glove is described, and characteristics are documented and other physical features are boundary-layer stability calculations and pressure distributions are described. The feasibility of conducting water tunnel experiments presented both at design and off-design conditions. Also included involving unsteady aero-hydrodynamics was demonstrated by is the analysis of the clean-up glove (smoothed basic wing) that performing a series of flow visualization studies on a oscillating will be flight-tested initially and the analysis of a Mach 0.7 glove airfoil (NACA 0012). This experiment was carried out at a reduced designed at the NASA Langley Research Center. Author frequency of 0.26 and at a Reynolds number of 50,000. For this

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condition, the flow was not fully separated until 17 degress angle Sciences, Jerusalem, Israel, 28 Aug. - 2 Sep. 1988 of attack, and the downstream wash of the separated flow occurred (NASA-TM-100665; NAS 1.15:100665) Avail: NTlS HC A02/MF at 22 degrees. GRA A01 CSCL01A t Aerodynamic methods for aeroelastic analysis are applied to N88-29750'# National Aeronautics and Space Administration. various flow problems. These methods include those that solve Ames Research Center, Moffett Field, Calif. the three dimensional transonic small disturbance (TSD) potential THREE-DIMENSIONAL NAVIER-STOKES SIMULATIONS OF equation, the two dimensional (2-D) full potential (FP) equation, TURBINE ROTOR-STATOR INTERACTION and the 2-D thin layer Navier-Stokes equations. Flutter analysis MAN MOHAN RAI Mar. 1988 6 p performed using TSD aerodynamics show that such methods can (NASA-TM-100081; A-88106; NAS 1.15:100081) Avail: NTlS HC be used to analyze some aeroelastic phenomena. For thicker I AO2/MFA01 CSCL01A bodies and larger amplitude motions, a nonisentropic FP method Fluid flows within turbomachinery tend to be extremely complex is presented. The unsteady FP equation is modified to model the in nature. Understanding such flows is crucial to improving current entropy jumps across shock waves. The conservative form of the designs of turbomachinery. The computational approach can be modified equation is solved in generalized coordinates using an used to great advantage in understanding flows in turbomachinery. implicit, approximate factorization method. Pressures calculated on A finite difference, unsteady, thin layer, Navier-Stokes approach the NLR 7301 and NACA 64A010A airfoils using the nonisentropic to calculating the flow within an axial turbine stage is presented. FP method are presented. It is shown that modeling shock The relative motion between the stator and rotor airfoils is made generated entropy extends the range of validity of the FP method. possible with the use of patched grids that move relative to each A Navier-Stokes code is correlated with pressures measured on a other. The calculation includes endwall and tip leakage effects. supercritical airfoil at transonic speeds. When corrections are made An introduction to the rotor-stator problem and sample results in for wind tunnel wall effects, the calculations correlate well with the form of time averaged surface pressures are presented. The the measured data. Author numerical data are compared with experimental data and the agreement between the two is found to be good. Author N88-29767# European Space Agency, Paris (France). HISTORY OF AEROELASTICITY IN GERMANY FROM THE N88-29752*# National Aeronautics and Space Administration. BEGINNING TO 1945 Langley Research Center, Hampton, Va. PETER BUBLITZ (Deutsche Forschungs- und Versuchsanstalt fuer AERODYNAMICS IN GROUND EFFECT AND PREDICTED Luft- und Raumfahrt, Goettingen, West Germany ) Jul. 1988 LANDING GROUND ROLL OF A FIGHTER CONFIGURATION 466 p Transl. into ENGLISH of Geschicte der Entwicklung der WITH A SECONDARY-NOZZLE THRUST REVERSER Aeroelastik in Deutschland von den Anfaengen bis 1945 DANIEL W. BANKS Oct. 1988 131 p (Goettingen, Fed. Republic of Germany, DFVLR), Dec. 1986 319 (NASA-TP-2834; L-16435; NAS 1.60:2834) Avail: NTlS HC p Original language document was announced as N88-10003 A07/MF A01 CSCL 01A (ESA-TT-1082; DFVLR-MITT-86-25; ETN-88-93050) Avail: NTlS An experimental investigation of the in-ground effect HC A20/MF A01; original German version available from DFVLR, aerodynamic characteristics and predicted landing-ground-roll VB-PL-DO, 90 60 58, 5000 Cologne, Fed. Republic of Germany performance of wing-canard fighter configuration with a secondary 98 deutsche marks nozzle thrust reverser was completed. These tests were conducted The history of research into the aeroelasticity problems of in the Langley 14 by 22 foot Subsonic Wind Tunnel using a model airframes in Germany is outlined. It is shown that almost 20 yr equipped with a pneumatic jet for thrust simulation of nozzle elapsed after the beginning of powered flight before the physics pressure ratios up to 4.0. The model was tested in the landing of such aeroelasticity problems as static divergence and flutter rollout configuration at approx. wheel touchdown height for a range were properly understood. Even then, it was not possible to avoid of decreasing dynamic pressure from 50 psf down to 10 psf. the aeroelastic problems which arose from the rapid progress of Landing-ground-roll predictions of the configuration were calculated aviation at the time. This led to the continual introduction of new using the wind tunnel results. Author research topics. ESA

N88-29753'# National Aeronautics and Space Administration, N88-29768# Army Aviation Systems Command, St. Louis, Mo. Washington, D.C. TEST OF AN 0.8-SCALE MODEL OF THE AH-64 APACHE IN A PRELIMINARY INVESTIGATION OF DRAG REDUCTION AND THE NASA LANGLEY FULL-SCALE WIND TUNNEL MECHANISM FOR A BLUNT BODY OF REVOLUTION WITH FREDERICK A. RAITCH May 1988 49 p SLANTED BASE (AD-A1961 29; USAAVSCOM-TM-87-D-5) Avail: NTlS HC XUEJIAN XIA and XIAOSHEN YU Aug. 1988 17 p Transl. AOS/MF A01 CSCL 01A into ENGLISH from Acta Aerodynamica Sinica (People's Republic This document summarizes the tests of an 0.8-scale model of of China), v. 4, Mar. 1986 p 99-107 Transl. by Scientific Translation the upper half of the AH-64 air vehicle in the NASA Langley Service, Santa Barbara, Calif. full-scale tunnel, primarily to determine the large-scale blockage (Contract NASW-4307) effects discovered during earlier tests of the same model in the (NASA-TT-20349; NAS 1.77:20349) Avail: NTlS HC A03/MF NASA Langley 4- by 7-meter tunnel. As background information, A01 CSCL01A and to provide continuity, the earlier program is outlined. The This is a preliminary study of the drag reduction effect and its models were large and heavy, and therefore the balances had mechanism of a blunt body of revolution with a 21-deg slant angle large capabilities. Yet, because of operational limitations with both by using a series of base plates. Drag coefficients were measured wind tunnels involved, the only data that overlapped in flight to investigate the effect of base installation position and plate conditions were at very low velocities. Thus, the results of these height. An effective drag reduction device was found. Through tests were inconclusive due to the time-honored difficulty of small the measurement of base pressure and total pressure distribution differences in large numbers. This effect carried over into other, and flow pattern display, flow characteristics and drag reduction auxiliary tests performed during the same test series, each mechanism in the vortex near the wake were investigated. concerned with an attempt to detect small differences. GRA Author N88-29769# Air Force Inst. of Tech., Wright-Patterson AFB, N88-29754'# National Aeronautics and Space Administration. Ohio. School of Engineering. Langley Research Center, Hampton, Va. ANGLE OF ATTACK AND SIDESLIP ESTIMATION USING AN APPLICATION OF UNSTEADY AERODYNAMIC METHODS FOR INERTIAL REFERENCE PLATFORM M.S. Thesis TRANSONIC AEROELASTIC ANALYSIS JOSEPH E. ZEIS, JR Jun. 1988 169 p WOODROW WHITLOW, JR. Sep. 1988 10 p Presented at (AD-A194876; AFIT/GAE/AA/88J-2) Avail: NTlS HC A08/MF the 16th Congress of the International Council of the Aeronautical A01 CSCLOlB

799 02 AERODYNAMICS

Flight test concepts are developed for the estimation of angle (AD-A196247; AFOSR-88-0656TR) Avail: NTlS HC AO2IMF A01 of attack (alpha) and sideslip (beta) using an inertial reference CSCL 20D platform. This development was further broken down into real-time, A substantial body of work on transonic aerodynamics and inflight estimation of alpha and post-flight estimation of alpha and problems using related applied mathematical techniques was beta. Following theoretical development, the concepts were tested carried out on this AFOSR grant. A listing of the main publications with NASA F-15A flight data and examined real-time during a produced with the support of this grant is given. GRA NASA Highly Integrated Digital Engine Control (HIDEC) flight test using the F-15A aircraft. Angle of attack is a critical parameter in N88-29778*# National Aeronautics and Space Administration. the maneuverable, high performance aircraft of today. Yet many Langley Research Center, Hampton, Va. errors are present in the current methods of obtaining this angle. RECENT ADVANCES IN TRANSONIC COMPUTATIONAL An accurate method of alpha and beta estimation could eliminate AEROELASTICITY the need for such probes, and allow these quantities to be used JOHN T. BATINA, ROBERT M. BENNETT, DAVID A. SEIDEL, for a broad range of applications. An inflight estimator was HERBERT J. CUNNINGHAM, and SAMUEL R. BLAND Sep. developed for computational speed and accuracy using inertial 1988 28 p Presented at the Symposium on Advances and navigation system linear accelerations and angular rates. A second Trends in Computational Structural Mechanics and Fluid Dynamics, system based on linear recursive modeling was developed for Washington, D.C., 17-19 Oct. 1988 post-flight estimation of alpha and beta. The data and programs (NASA-TM-100663; NAS 1.15:100663) Avail: NTlS HC AO3/MF specified in this research are applicable only to those aircraft A01 CSCL01A mentioned, but the methods of estimation are universal. GRA A transonic unsteady aerodynamic and aeroelasticity code called CAP-TSD was developed for application to realistic aircraft N88-29771'# National Aeronautics and Space Administration. configurations. The code permits the calculation of steady and Lewis Research Center, Cleveland, Ohio. unsteady flows about complete aircraft configurations for EULER ANALYSIS OF A SWIRL RECOVERY VANE DESIGN aeroelastic analysis in the flutter critical transonic speed range. FOR USE WITH AN ADVANCED SINGLE-ROTATION The CAP-TSD code uses a time accurate approximate factorization PROPFAN algorithm for solution of the unsteady transonic small disturbance CHRISTOPHER J. MILLER 1988 15 p Presented at the 24th potential equation. An overview is given of the CAP-TSD code Joint Propulsion Conference, Boston, Mass., 11-1 3 Jul. 1988; development effort and results are presented which demonstrate sponsored by AIAA, ASME, SAE and ASEE various capabilities of the code. Calculations are presented for (NASA-TM-101357; E-4387; NAS 1.1 51101 357; AIAA-88-3152) several configurations including the General Dynamics 1/9 scale Avail: NTlS HC A03/MF A01 CSCL 01A F-16 aircraft model and the ONERA M6 wing. Calculations are Recent work has demonstrated the propulsive efficiency also presented from a flutter analysis of a 45 deg sweptback improvement available from single- and counter-rotation propfans wing which agrees well with the experimental data. Descriptions as compared with current technology high bypass ratio turbofans. are presented of the CAP-TSD code and algorithm details along The concept known as swirl recovery vanes (SRV) is examined with results and comparisons which demonstrate these recent through the use of a 3-D Euler code. At high speed cruise developments in transonic computational aeroelasticity. Author conditions, the SRV can improve the efficiency level of a single-rotation propfan, but a concern is to have adequate hub N88-29779# Naval Ship Research and Development Center, choke margin. The SRV was designed with 2-D methods and was Bethesda, Md. Aviation Dept. predicted to have hub choking at Mach 0.8 cruise. The 3-D Euler ANALYSIS OF A FIXED-PITCH X-WING ROTOR EMPLOYING analysis properly accounts for sweep effects and 3-D relief, and LOWER SURFACE BLOWING Final Report, Apr. 1985 - Sep. predicts that at cruise the SRV will recover roughly 5 percent of 1985 the 10 percent efficiency loss due to swirl and have a good hub ALAN W. SCHWARTZ and ERNEST 0. ROGERS Nov. 1987 choke margin. Author 27 p Presented at the Circulation Control Workshop, Moffett Field, Calif., 19-21 Feb. 1986 Previously announced as N88-17602 Submitted for publication N88-29776'# National Aeronautics and Space Administration. (AD-A187379; DTRC-87/045) Avail: NTlS HC AO3/MF A01 Langley Research Center, Hampton, Va. CSCL 01A PRESSURE DISTRIBUTIONS FROM SUBSONIC TESTS OF AN Lower surface blowing (LSB) is investigated as an alternative ADVANCED LAMINAR-FLOW-CONTROL WING WITH to the variable blade pitch requirement for the X-wing Circulation LEADING- AND TRAILING-EDGE FLAPS Control (CC) rotor concept. Additional trailing edge blowing slots ZACHARY T. APPLIN and GARL L. GENTRY, JR. Jul. 1988 on the lower surfaces of CC airfoils provide a bidirectional lift 339 p capability that effectively doubles the control range. The operational (NASA-TM-4040-PT-2; L-16405; NAS 1.1 5~4040-PT-2) Avail: requirements of this rotor system are detailed and compared to NTlS HC A15/MF A01 CSCL 01A the projected performance attributes of LSB airfoils. Analysis shows An unswept, semispan wing model equipped with full-span that, aerodynamically, LSB supplies a fixed pitch rotor system with leading- and trailing-edge flaps was tested in the Langley 14- by the equivalent lift efficiency and rotor control of present CC rotor 22-Foot Subsonic Tunnel to determine the effect of high-lift designs that employ variable blade pitch. Aerodynamic demands components on the aerodynamics of an advanced of bidirectional lift production are predicted to be within the laminar-flow-control (LFC) airfoil section. Chordwise pressure capabilities of current CC airfoil design methodology. Emphasis in distributions near the midsemispan were measured for four this analysis is given to the high speed rotary wing flight regime configurations: cruise, trailing-edge flap only, and trailing-edge flap unique to stoppable rotor aircraft. The impact of a fixed pitch with a leading-edge Krueger flap of either 0.10 or 0.12 chord. restriction in hover and low speeed flight is briefly discussed. Part 1 of this report (under separate cover) presents a Author representative sample of the plotted pressure distribution data for each configuration tested. Part 2 presents the entire set of plotted N88-29781# National Aeronautical Establishment, Ottawa and tabulated pressure distribution data. The data are presented (Ontario). without analysis. Author THE USE OF HOT-FILM TECHNIQUE FOR BOUNDARY LAYER STUDIES ON A 21 PERCENT THICK AIRFOIL N88-29777# Rensselaer Polytechnic Inst., Troy, N.Y. M. KHALID May 1987 54 p THEORETICAL AERODYNAMICS, TRANSONIC FLOW Final (NAE-AN-45; NRC-27892) Avail: NTlS HC A04/MF A01 Report, 1 Jul. 1982 - 31 Oct. 1987 A heat transfer method of studying boundary layer flows over JULIAN D. COLE 12 Feb. 1988 5 p airfoils at transonic test conditions was investigated. The method (Contract AF-AFOSR-0155-82) employs very thin DlSA hot-film gauges housing Constant

800 03 AIR TRANSPORTATION AND SAFETY

Temperature Anemometer probes. Provided that the thickness A8865290 dimension of the films remains less than the critical disturbances HELICOPTER CREW SEAT FAILURE ANALYSIS height for inducing transition of the laminar boundary layer, the JOHN G. COWIE (US. Army, Materials Technology Laboratory, heat transfer response from the films, positioned carefully on the Watertown, MA) IN: ISTFA 1987 - International Symposium for model surface, can be studied to determine the boundary layer Testing and Failure Analysis: Advanced materials; Proceedings of characteristics. Results from an application study on a 21 percent the Symposium, Los Angeles, CA, Nov. 9-13, 1987. Metals Park, thick laminar flow airfoil model are presented and dissussed. OH, ASM International, 1987, p. 171-178. Author A failure analysis was conducted on a helicopter crew seat which failed during an FAA simulated crash survivability test. This seat is an advanced composite of ultrahigh strength steel and Kevlar. The failure which resulted in the steel fracturing into several 03 pieces was due to a small crack emanating from one of the shock-absorber mounting holes. Stresses generated during the crash test achieved high enough levels to propagate the small AIR TRANSPORTATION AND SAFETY crack. The exact initiation site was the tensile (aft) side of the shock-absorber mounting hole. In addition to the small crack, the Includes passenger and cargo air transport operations; and aircraft inside surface of the hole exhibited many deep 'score-marks' as accidents. a result of poor machining practice. The small crack originated from one of these score-marks. Mechanical property tests conducted on the steel proved the material to be within A8 8- 5 3 5 4 0 specification. However, the relatively low fracture toughness and CARING FOR THE HIGH-TIME JET Charpy energy enabled the small crack to easily propagate at the J. M. RAMSDEN and JOHN MARSDEN Flight International (ISSN design stress. Author 0015-3710), vol. 134, Sept. 3, 1988, p. 153-156. An investigative account is given of the factors that led to the N88-28896'# Nevada Univ., Reno. Engineering Research and catastrophic fuselage pressurized structure failure of Aloha N73711, Development Center. a 8737-200 airliner with 89,000 flights completed over its long AERODYNAMICS OF SEEING ON LARGE TRANSPORT career. Structural failure may have been initiated by a tear along AIRCRAFT Final Technical Report, 1 Dec. 1985 - 30 Nov. 1986 the lap joint at either one of two different stringers; the explosive WILLIAM C. ROSE 15 Aug. 1988 4 p decompression may then have bent the right window panel (Contract NCC2-382) outwards, ripping the rest of the section around the butt-joints, (NASA-CR-183122; NAS 1.26:183122) Avail: NTlS HC A02/MF and tearing it raggedly off below floor level on the left side of the A01 CSCLOlC aircraft. Attention is presently given to the characteristics of a Efforts were undertaken to obtain a set of data that examined typical fuselage lap joint. O.C. the level of turbulence and the scale sizes in the shear layer existing over the fence quieted cavity on the NASA-Ames Kuiper A8844400 Airborne Observatory (KAO). These data were to be taken during ICING TECHNOLOGY BIBLIOGRAPHY the present study and compared with data taken from previous SAE Aerospace Information Report SAE AIR 4015, Nov. 1987, wind tunnel experiments, for which both aerodynamic and direct 149 p. refs optical measurements were made. The data obtained during the (SAE AIR 4015) present study were presented and discussed in light of their impact A compendium of references from the open literature on icing on the quality of optical images, that is, seeing through the shear technology is presented, including both national and foreign layer. In addition, scaling relationships were presented that allow sources. The general topics addressed include: meteorology of optical data obtained in one aerodynamic environment to be icing clouds, meteorological instruments, propeller icing, induction estimated for another one at perhaps different Mach numbers, system icing, gas turbine engine and inlet icing studies, wing icing, scale sizes, or aircraft configurations. Author windshield icing, ice adhesion and mechanical properties, heat transfer, helicopter climatic tests and icing, and helicopter rotor N88-28898 Civil Aviation Authority, London (England). blade icing. Other general subjects considered are: engine snow SMOKE HOODS NET SAFETY BENEFIT ANALYSIS ingestion and snow measurements, droplet trajectories and Nov. 1987 25 p impingement, ice accretion modeling, icing test facilities and icing (CAA-PAPER-87017; ISBN-0-86-039330-5; ETN-88-92653) Avail: simulation, aircraft ice formation, runway icing, microwave sensing Civil Aviation Authority, Greville House, 37 Gratton Road, and ice protection systems, iced airfoil performance, land and sea Cheltenham, United Kingdom 7 pounds ice studies, fluid and two-phase flow dyanmics, liquid evaporation The benefits to airline passengers of smoke hoods were and ice crystal formation studies, electrical modeling, and radome assessed by studying past accidents. It is concluded that the icing. C.D. provision of effective passenger smoke hoods in public transport aircraft of more than 30 seats would result in a modest saving of A8845288 life. The analysis shows that the saving expected is of the order A PROFILE OF US AIR FORCE AIRCRAFT MISHAP of 9 fire related deaths per year world-wide if the accidentlfire INVESTIGATION history of the past 20 yr is broadly repeated. This total would be JOSEPH F. TILSON (USAF, Directorate of Aerospace Safety, massively reduced if credit is taken for lavatory fire precautions in Norton AFB, CA) IN: ISTFA 1987 - International Symposium for the VARlG 8707 near Orly (France) in 1973. The analysis also Testing and Failure Analysis: Advanced materials; Proceedings of shows that even if the wearing of smoke hoods results in a delayed the Symposium, Los Angeles, CA, Nov. 9-13, 1987. Metals Park, or slower evacuation, the net benefit remains positive, but OH, ASM International, 1987, p. 159-162. reduced. ESA An account is given of the administrative organization and roles of the USAF Safety Investigation Board (SIB), whose primary N88-28899# Deutsche Forschungs- und Versuchsanstalt fuer function is to ascertain the causes of mishaps. Attention is given Luft- und Raumfahrt, Stuttgart (West Germany). Inst. fuer to the SIB president's management of a given investigation and Bauweisen und Konstruktionsforschung. the function of engineers and laboratory analysts. It is noted that CRASH SIMULATION CALCULATIONS AND COMPONENT technological advancements are significantly affecting SIB analyses IDEALIZATION FOR AN AIRFRAME. COMPUTER CODE of mishaps, in the form of crash-survivable flight data recorders, KRASH 79 [CRASHSIMULATIONSRECHNUNGEN UND failure analyses of composite materials, fly-by-wire/fly-by-light flight BAUTEILIDEALISIERUNG FUER EINEN control systems, and advanced maneuvering flight profiles. O.C. FLUGZEUGUNTERBODEN. RECHENCODE KRASH 791

80 1 03 AIR TRANSPORTATION AND SAFETY

WOLFGANG G. HIENSTORFER 28 Jan. 1987 164 p In envelope. Phase 2 consisted of forward flight testing in artificial GERMAN and natural icing conditions of the second generation design only. (ETN-88-92971) Avail: NTlS HC AO8/MF A01 Phase 3 consisted of limited artificial rain erosion tests of the A metal airframe of an aircraft of the weight class 3T was second generation design. Phase 4 consisted of performance and investigated in crash cases with a mainly vertical impact component handling qualities evaluation of the second generation design. using the simulation program KRASH 79. The results of the Hover and level flight performance were greatly improved over simulation calculations are shown in the form of acceleration/time the first generation, but a significant performance penalty still exists. evolutions of the discretized masses of the idealized structure Handling qualities were essentially unchanged from the standard and of structural displacements in the frame. The deformation UH-1H. Two unsatisfactory and six undesirable reliability and behavior of a given seat structure was determined, and the maintainability characteristics were identified. GRA dynamic-response index allows one to predict back injuries. Configuration-typical force/displacement characteristics under axial pressure loading were obtained in dimensionless form, allowing the determination of the dynamic response of the airframe. ESA 04

N88-28900'# National Aeronautics and Space Administration, AIRCRAFT COMMUNICATIONS AND NAVIGATION Washington, D.C. CONTRIBUTIONS TO THE MODELING OF WIND SHEAR FOR Includes digital and voice communication with aircraft; air navigation DANGER STUDIES systems (satellite and ground based); and air traffic control. MANFRED SWOLINSKY Sep. 1988 190 p Transl. into ENGLISH of Beitraege zur Modellierung von Scherwind fuer Gefaehrdungsuntersuchungen (Brunswick, Fed. Republic of A8842952 Germany, Technischen Univ. Carolo-Wilhelmina), Apr. 1986 200 p MICROPROCESSOR FUNCTIONAL-ADAPTIVE PROCESSING Original language document was announced as N88-10463 Transl. OF SIGNALS OF RADIO-NAVIGATION SYSTEMS IN AN by Scientific Translation Service, Santa Barbara, Calif. ONBOARD SUBSYSTEM [MIKROPROTSESSORNAIA (Contract NASW-4307) FUNKTSIONAL'NO-ADAPTlVNAlA OBRABOTKA SIGNALOV (NASA-TT-20293; NAS 1.77:20293) Avail: NTlS HC AO9/MF SISTEM RADlONAVlGATSll V BORTOVOI PODSISTEME] A01 CSCLOlC A. K. BERNIUKOV Radiotekhnika (ISSN 0033-8486), July 1988, Wind models for flight simulation and the study of the danger p. 78-83. In Russian. refs during landing due to wind shear were developed. It is demonstrated The paper presents an analysis of the feasibility of digital that the typical wind conditions in weather phenomena such as functional-adaptive processing in the case of a microprocessor thunderstorm downdrafts and surface boundary layer wind shear implementation of an onboard receiver of the angle-measurement can be approximated by simple engineeringf models, whereby channel of a pulse-time aircraft navigation and landing system of known solutions and flow forms from flow mechanics were adapted. MLS type and of a Shoran system. An algorithm for eliminating The good agreement between models and airborne measurements the effect of multipath noise on the navigation/landing system is is demonstrated. Based on the developed models the degree of examined. B.J. danger during landing under different wind shear conditions was estimated. Author A88-53628# PROCESSING PSEUDO SYNTHETIC APERTURE RADAR N88-29783# Loughborough Univ. of Technology (England). Dept. IMAGES FROM VISUAL TERRAIN DATA of Transport Technology. M. E. STURGELL (USAF, Avionics Laboratory, Wright-Patterson AN ANALYSIS OF TIME AND SPACE REQUIREMENTS FOR AFB, OH) and J. R. LEWONSKI (USAF, Flight Dynamics Laboratory, AIRCRAFT TURNROUNDS Wright-Patterson AFB, OH) IN: AIAA, Flight Simulation ROBERT E. CAVES Aug. 1987 41 p Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, Technical (TT-8705) Avail: NTlS HC AO3/MF A01 Papers. Washington, DC, American Institute of Aeronautics and By their very nature, airport aprons occupy the space between Astronautics, 1988, p. 10-16. the runway system and the terminal buildings. Most aitempts to (AIAA PAPER 88-4576) increase runway capacity, by the use of parallel taxiways or larger The paper discusses a solution in the area of simulating aircraft, reduce the available apron space. Similarly, the growth of synthetic aperture radar (SAR) high resolution map imagery from piers and satellites to provide extra gates also restricts the apron. terrain board visual data to aid a pilot in determining safe landing The situation is worsened further when more space is required vectors on bomb-damaged runways. The visual data were obtained for passenger processing, due to the rate of increase of processing from a terrain board system using a method that considered image efficiency not keeping pace with traffic growth, yet there is no centers, rotations, and fields-of-view. The image processing room for landsite expansion. Discussed is the influence of aircraft software was developed to convert the collected still images into technology on apron capacity Author pseudo-SAR images. A program was written to process and store the large number of pseudo-SAR images onto a videodisc as an N88-29785# Army Aviation Engineering Flight Activity, Edwards ordered library. This library was randomly accessed and displayed AFB, Calif. in a real-time flight simulation through a videodisc based system. JUH-1H REDESIGNED PNEUMATIC BOOT DEICING SYSTEM After the pilot designated a reasonable touchdown point on the FLIGHT TEST EVALUATION Final Report, 15 Nov. 1983 - 7 SAR cockpit display the simulation host passed the appropriate Mar. 1986 coordinates to the Inertial Navigation Systems which computed MATTHEW S. GRAHAM, LORAN A. HAWORTH, and JACK L. the proper approach vector for display. Author KIMBERLY Aug. 1987 144 p (AD-A194918; USAAEFA-83-13) Avail: NTlS HC A07/MF A01 N88-28906# Royal Signals and Radar Establishment, Malvern CSCL 08L (England). The U.S. Army Aviation Engineering Flight Activity conducted FINE RESOLUTION ERRORS IN SECONDARY SURVEILLANCE an evaluation of the Pneumatic Boot Deicing System (PBDS) with RADAR ALTITUDE REPORTING two pneumatic deicer boot designs, referred to as second and D. B. JENKINS, 6. A. WYNDHAM, and P. BANKS Jan. 1988 third generation. The objective of the test was to conduct feasibility 45 p Sponsored by the Civil Aviation Authority, London, United testing of the pneumatic system concept for deicing helicopter Kingdom rotor blades in forward flight, and to assess any changes to aircraft (RSRE-87019; BR106199; ETN-88-93137) Avail: NTlS HC performance and handling qualities. Phase 1 consisted of a ground A03/MF A01 and inflight structural loads survey which established an operational Faults in the three C bits used to encode the fine resolution

802 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

part of the secondary surveillance radar (SSR) pressure altitude DAVID L. SIMPSON, ED. (National Aeronautical Establishment message, for use in airborne collision avoidance systems, were Ottawa, Canada) Symposium sponsored by the International investigated for aircraft using UK airspace and transmitting SSR Committee on Aeronautical Fatigue. Warley, England, Engineering Mode A Identification Codes other than the Conspicuity Codes Materials Advisory Services, Ltd., 1987, 641 p. For individual items 4321 and 4322. Of 132,773 aircraft trajectories investigated, 581 see A8842652 to A88-52673. trajectories, involving at least 68 aircraft, exhibit a C bit fault, a The present conference discusses damage tolerance in frequency of occurrence of 0.44 percent. On the basis of SSR pressurized fuselages, the fatigue of mechanically-alloyed AI, the , Mode A Identification Code, aircraft in a sample of 44,191 fatigue behavior of adhesively-bonded aircraft structures, the trajectories were identified and examined separately involving those modeling and analysis of the effect of 'cold-working' on fatigue undertaking international flights under civil air traffic control (ATC), life, the damage tolerance of an Arall lower wing skin panel, and those undertaking domestic flights under civil ATC, those receiving the concise description and reconstruction of spectrum loading. a service from military ATC, and those transmitting codes issued Also discussed are the use of composite materials to repair metallic by airport approach ATC. The frequency of C bit faults varies structures, the effect of thickness on crack growth rate, the significantly according to the type of flight, and is particularly high transition to novel structural technologies for new aircraft, the among aircraft transmitting approach codes, suggesting that the impact and damage-tolerance properties of CFRP, and the damage overall frequency found in any given volume of airspace depends tolerance of impact-damaged CFRP wing skin laminates. O.C. on the types of flight undertaken in that airspace, and might be ESA high in the vicinity of airport approaches. A88-52652 DAMAGE TOLERANCE IN PRESSURIZED FUSELAGES N88-28907 Civil Aviation Authority, London (England). T. SWIFT (Douglas Aircraft Co., Long Beach, CA) IN: New UK AIRMISSES INVOLVING COMMERCIAL AIR TRANSPORT materials and fatigue resistant aircraft design; Proceedings of the Apr. 1988 66 p Fourteenth ICAF Symposium, Ottawa, Canada, June 8-1 2, 1987. (CAA-1/88; ISSN-0951-6301; ETN-88-93146) Avail: Civil Aviation Warley, England, Engineering Materials Advisory Services, Ltd., Authority, Greville House, 37 Gratton Road, Cheltenham, United 1987, p. 1-77. refs Kingdom The fatigue and damage tolerance capability of pressurized Airmiss statistics from 1977 to Aug. 1987 for United Kingdom fuselage structure is extremely sensitive to stress level, geometrical airspace are presented. Reports of incidents are summarized. design, and material choice. Considerable improvements have been ESA made in designing fuselage structure to sustain large, obviously detectable damage. The historical evolution of these improvements N88-29788 Eurocontrol Experimental Centre, Bretigny (France). is discussed. Consideration is given to the difficulties and current OBSERVED TRACK-KEEPING PERFORMANCE OF DClO concerns associated with in-service, noninspectable, multisite AIRCRAFT EQUIPPED WITH THE COLLINS AINS-70 AREA damage within a damage tolerance philosophy that depends upon NAVIGATION SYSTEM: KARLSRUHE AND MASSTRICHT inspection. Recommendations are given related to operating stress UACS (UPPER AREA CONTROL CENTRES) Report, Mar. 1982 level, design detail, and material choice required for long service - Oct. 1984 life and large damage capability of minimum-gage pressurized L. CLARKE, H. DAVID, and W. OENEMA Feb. 1987 92 p structure. Author (EEC-202) Avail: NTlS HC E05/MF E05; copy not available from STI Facility CSCL 17G The results are described which were obtained from data on A88-52653 964 flights by DClO aircraft equipped with the Collins AINS-70 FATIGUE CRACK GROWTH CHARACTERIZATION OF JET Area Navigation System which is based on automatic double DME TRANSPORTSTRUCTURES updating of inertial sensors. Author M. MILLER, V. K. LUTHRA, and U. G. GORANSON (Boeing Commercial Airplane Co., Seattle, WA) IN: New materials and fatigue resistant aircraft design; Proceedings of the Fourteenth ICAF Symposium, Ottawa, Canada, June 8-12, 1987. Warley, England, Engineering Materials Advisory Services, Ltd., 1987, p. 79-125. refs AIRCRAFT DESIGN, TESTING AND Structural airworthiness requirements for new and maturing jet PERFORMANCE transports include demonstration of damage tolerance and an assurance that damage will be detected before safety is affected. This paper describes aspects of the development of structural Includes aircraft simulation technology. inspections on Boeing models 757 and 767 and the implications in terms of fatigue crack growth analysis techniques used to support damage detection assessments. A simple analytical crack growth A88-52375 model is described and correlated with an extensive test data JUMP STRUT MEANS SHORTER TAKEOFF ROLLS base, including the key variables of spectrum type, thickness, JAMES H. BRAHNEY Aerospace Engineering (ISSN 0736-2536), vol. 8, Sept. 1988, p. 17-19. material, and load sequence effects. This model is shown to predict A 'jump strut'-equipped nose landing gear can cut fighter aircraft crack growth to an accuracy suitable for engineering assessment by large teams of analysts. Author takeoff roll lengths in half; alternatively, that capability can be translated into a 25-percent payload increase when enough runway distance is available for a normal ground roll. It is presently noted A88-52654 that the jump strut system can be retrofitted to existing aircraft EVALUATION OF NEW MATERIALS IN THE DESIGN OF landing gears, with only a modest increase in weight. Whereas a AIRCRAFT STRUCTURES typical tactical aircraft may require 1000 feet of runway for a takeoff M. IOANNOU, L. J. KOK, T. M. FIELDING, and N. J. MCNEILL speed of 140 knots, the same aircraft could be airborne at 500 (de Havilland Aircraft Company of Canada, Ltd., Downsview) IN: feet, with only a 100-knot takeoff speed. NASA-Ames has New materials and fatigue resistant aircraft design; Proceedings investigated the application of the jump strut principle to the Quiet of the Fourteenth ICAF Symposium, Ottawa, Canada, June 8-12, STOL Research Aircraft. O.C. 1987. Warley, England, Engineering Materials Advisory Services, Ltd., 1987, p. 127-149. A88-52651 Experimental and analytical evaluations of AI-Li alloys and Arall NEW MATERIALS AND FATIGUE RESISTANT AIRCRAFT have been performed to determine their suitability as candidate DESIGN; PROCEEDINGS OF THE FOURTEENTH ICAF materials in the design of aircraft structures. A description of the SYMPOSIUM, OTTAWA, CANADA, JUNE 8-12, 1987 analytical approach and the experimental results are presented.

803 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

The cost effectiveness of their application is also addressed. factors were derived from coupon specimen testing with the Author simplistic loading for large composite structures and with quasi-realistic environmental fatigue loading. Details of test results, A88-52659 their application to design and proof of the composite structure, ASPECTS OF THE FATIGUE BEHAVIOUR OF TYPICAL and the testing procedure are given. Author ADHESIVELY BONDED AIRCRAFT STRUCTURES A. GALASSO, A. DEL CORE (Aeritalia S.p.A., Gruppo Velivoli da A88-52666 Trasporto, Naples, Italy), A. LANCIOTTI, and L. LAZZERI (Pisa, ENSTAFF - A STANDARD TEST SEQUENCE FOR COMPOSITE Universita, Italy) IN: New materials and fatigue resistant aircraft COMPONENTS COMBINING LOAD AND ENVIRONMENT design; Proceedings of the Fourteenth ICAF Symposium, Ottawa, DIETER SCHUETZ and JOHANN J. GERHARZ (Fraunhofer-Institut Canada, June 8-12, 1987. Warley, England, Engineering Materials fuer Betriebsfestigkeit, Darmstadt. Federal Republic of Germany) Advisory Services, Ltd.. 1987, p. 227-262. refs IN: New materials and fatigue resistant aircraft design; Proceedings An evaluation has been made of the prospects for the extension of the Fourteenth ICAF Symposium, Ottawa, Canada, June 8-12, of structural adhesive bonding techniques to primary aircraft 1987. Warley, England, Engineering Materials Advisory Services, structures, especially for the construction of selected fuselage Ltd., 1987, p. 425-444. refs panels of the ATR 72 aircraft. Attention is given to the results of The development of a loading standard for tests with composites an evaluation of the fatigue behavior typical of fighter aircraft combining mechanical loads with temperature cycles in a structures. The adhesive presently employed, AF-163, is easy to flight-by-flight program is described. Special attention is also paid use in production runs, and has been found to yield performance to the moisture preconditioning of specimen and the moisture levels that render this technology safe from the viewpoint of management during the test. Author fatigue. O.C. A88-52668 A88-52660 DAMAGE TOLERANCE ASPECTS OF AN EXPERIMENTAL USE OF COMPOSITE MATERIALS TO REPAIR METAL ARALL F-27 LOWER WING SKIN PANEL STRUCTURES L. H. VAN VEGGEL, A. A. JONGEBREUR (Fokker Aircraft, C. A. ELKINS (Central Servicing and Development Establishment, Amsterdam, Netherlands), and J. W. GUNNINK (Delft, Technische Norfolk, England) IN: New materials and fatigue resistant aircraft Hogeschool, Netherlands) IN: New materials and fatigue resistant design; Proceedings of the Fourteenth ICAF Symposium, Ottawa, aircraft design; Proceedings of the Fourteenth ICAF Symposium, Canada, June 8-12, 1987. Warley, England, Engineering Materials Ottawa, Canada, June 8-12, 1987. Warley, England, Engineering Advisory Services, Ltd., 1987, p. 263-282. Materials Advisory Services, Ltd., 1987, p. 465-502. refs The background to the use of composite materials to repair This paper deals with the damage tolerance aspects of metal structure is described with a summary of the types of material structures built from ARALL. After a brief introduction of the design used. The patch design and repair procedure are given in detail, of the ARALL F27 panel, the damage tolerance aspects of the together with the limitations on the use of this method of repair. panel itself and detail components are discussed. Attention is given Six applications are briefly described with photographs of the to ARALL coupon properties and results of fatigue tests on individual repairs and reinforcements. A summary of the current structural parts. A comparison is then made with the results of applications is given before future applications are discussed. the all metal wing panel configuration. The structural performance Author of ARALL laminates is excellent in tension-loaded-fatigue prone areas due to the good damage tolerance properties of this A88-52662 material. Author FATIGUE CRACK PROPAGATION TEST PROGRAMME FOR THE A320 WING A88-52670 1. G. GRAY (British Aerospace, PLC, Civil Aircraft Div., Bristol, DAMAGETOLERANCEOFIMPACTDAMAGEDCARBON England) IN: New materials and fatigue resistant aircraft design; FIBRE COMPOSITE WING SKIN LAMINATES Proceedings of the Fourteenth ICAF Symposium, Ottawa, Canada, T. J. VAN BLARICUM, D. S. SAUNDERS, G. CLARK, and T. E. June 8-12, 1987. Warley, England, Engineering Materials Advisory PREUSS (Department of Defence, Aeronautical Research Services, Ltd., 1987, p. 297-335. Research supported by British Laboratories, Melbourne, Australia) IN: New materials and fatigue Aerospace, PLC. refs resistant aircraft design; Proceedings of the Fourteenth ICAF This paper presents the results from an A320 crack propagation Symposium, Ottawa, Canada, June 8-1 2, 1987. Warley, England, coupon test program. It shows the effect of gust truncation, active Engineering Materials Advisory Services, Ltd., 1987, p. 537-556. gust load alleviation, low level gust omission and ground load refs spectra truncation on the crack propagation lives for three different This paper describes the work ARL has carried out in developing aluminum alloys, L97 (2024-T351), 7010-T7651 and 71 50-T651. static and fatigue compression test procedures for large gage area Author specimens, as well as work currently underway in the development of NDI techniques for assessment of the defects in composites. A88-52665 Also described briefly are the results of a number of experimental ACCOUNTING FOR SERVICE ENVIRONMENT IN THE programs which have been completed or are currently in FATIGUE EVALUATION OF COMPOSITE AIRFRAME progress. Author STRUCTURE JOHANN J. GERHARZ, MATTHIAS BERG (Fraunhofer-lnstitut fuer A8842671 Betriebsfestigkeit, Darmstadt, Federal Republic of Germany), and IMPACT AND DAMAGE TOLERANCE PROPERTIES OF CFRP OGUZ GOEKGOEL (Messerschmitt-Boelkow-Blohm GmbH, SANDWICH PANELS - AN EXPERIMENTAL PARAMETER Hamburg, Federal Republic of Germany) IN: New materials and STUDY FOR THE FOKKER 100 CA-EP FLAP fatigue resistant aircraft design; Proceedings of the Fourteenth L. H. VAN VEGGEL (Fokker Aircraft, Amsterdam, Netherlands) ICAF Symposium, Ottawa, Canada, June 8-12, 1987. Warley, IN: New materials and fatigue resistant aircraft design; Proceedings England, Engineering Materials Advisory Services, Ltd., 1987, p. of the Fourteenth ICAF Symposium, Ottawa, Canada, June 8-12. 403-424. Research supported by Messerschmitt-Boelkow-Blohm 1987. Warley, England, Engineering Materials Advisory Services, GmbH; Bundesministerium der Verteidigung. refs Ltd., 1987, P. 557-583. (Contract BMVG-RUEFO-4) As a part of the development work on the Fokker FlOO flap, a In fatigue proof testing of large composite structures only parameter study was performed to investigate the effect of different incomplete simulation of expected environment is economically impact parameters, fatigue parameters and material parameters feasible. To account for missing environmental effects application on the impact and damage tolerance properties of sandwich panels. of the compensation factor concept is proposed. The compensation The objective of the program was to determine how to treat impact

804 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

damage during the certification program of the Fokker F100 A88-53149# CFRP-flap, to identify the most important parameters and to PROPULSION SYSTEM INTEGRATION FOR MACH 4 TO 6 determine the allowable strain level. Author VEHICLES VICTOR SALEMANN (Boeing Co., Seattle, WA) and MARK A88-52672 ANDREWS (USAF, Wright Aeronautical Laboratories, CERTIFICATION OF PRIMARY COMPOSITE AIRCRAFT Wright-Patterson AFB, OH) AIAA, ASME, SAE, and ASEE, Joint STRUCTURES Propulsion Conference, 24th. Boston, MA, July 11-13, 1988. 19 p. R. S. WHITEHEAD (Northrop Corp., Aircraft Div., Hawthorne, CA) (AIAA PAPER 88-3239A) IN: New materials and fatigue resistant aircraft design; Proceedings A comparative evaluation is conducted of alternative of the Fourteenth ICAF Symposium, Ottawa, Canada, June 8-12, powerplants and their integration with vehicle inlet and exhaust 1987. Warley, England, Engineering Materials Advisory Services, geometries for the Mach 4-6 flight regime. The powerplant cycles Ltd., 1987, p. 585-617. refs in question are the turbojet, turbofan, variable-cycle turbofan, An evaluation is made of lessons learned in the course of two ejector turbofan, and air turboramjet; their prospective performance major USAF composite primary structures R&D programs, in order is considered in view of the various inlet, ducting, and exhaust to formulate a series of recommended certification procedures. system design requirements. Three basic integrations of twin engine Attention is given to static strength, fatigue/durability, and damage installations with Mach 6 vehicle fuselage/wing configurations are tolerance. It is noted that (1) composite structures are uniquely formulated and compared with respect to takeoff gross weight for sensitive to out-of-plane loads; (2) a multiplicity of potential failure a given mission. O.C. modes exists; and (3) the failure modes of full-scale structures are difficult to predict; however, (4) static strength testing is able A88-53 16 1# to identify structural 'hot spots'. O.C. COOL GAS GENERATOR SYSTEMS ROBERT D. PEHA and J. SCOTT NEISH (Rocket Research Co., A88-52673 Redmond, WA) AIAA, ASME, SAE, and ASEE, Joint Propulsion STRUCTURAL TECHNOLOGY TRANSITION TO NEW Conference, 24th, Boston, MA, July 11-13, 1988. 5 p. AIRCRAFT (AIAA PAPER 88-3363) JOHN W. LINCOLN (USAF, Aeronautical Systems Div., The paper describes the operation and application of three Wright-Patterson AFB, OH) IN: New materials and fatigue resistant cool gas generator systems used for emergency/recovery purposes aircraft design; Proceedings of the Fourteenth ICAF Symposium, in the CH-46 helicopter emergency flotation system, 747 emergency Ottawa, Canada, June 8-12, 1987. Warley, England, Engineering escape slide, and Torpedo MK 50 buoyancy. All of these inflation Materials Advisory Services, Ltd., 1987, p. 619-629. systems utilize a solid propellant gas generator to initially pressurize The method presented has been developed in order to ensure a working fluid before expulsion from the inflator. Consistent that a given structural technology can be successfully transferred operation over a wide storage temperature range and tailorable from the laboratory to the full-scale development of an aircraft. gas temperature are among the advantages of these systems. Five factors are noted to be common to past successful transfers K.K. of novel technologies: (1) stabilized processing methods for the materials in question; (2) producibility; (3) well-characterized A88-53249 materials properties; (4) the predictability of structural performance; THE MINIMISATION OF HELICOPTER VIBRATION THROUGH and (5) supportability. The aircraft development schedule must be BLADE DESIGN AND ACTIVE CONTROL taken into account when the data base for each of these factors S. P. KING (Westland Helicopters, Ltd., Yeovil, England) is established. O.C. Aeronautical Journal (ISSN 0001-9240), vol. 92, Aug.-Sept. 1988, p. 247-263. A88-52692# A treatment is presented of the problem of helicopter vibration TECHNOLOGY OF FLIGHT SIMULATION at main rotor blade passing frequency product bR, where b is the V. SRlNlVAS (Aeronautical Development Establishment, Bangalore, number of blades and R the rotor speed. The magnitude of the India) (Seminar on Pilot Training through Flight Simulators, rotor vibration can be minimized through careful rotor design and Bangalore, India, Apr. 3, 4, 1987) Aeronautical Society of India, placement of the fuselage natural vibration frequencies relative to Journal (ISSN 0001-9267), vol. 39, Nov. 1987, p. 143-152. refs bR, as presently illustrated by the case of the Westland 30-300 The design and performance of flight simulators used for the aircraft. Attention is also given to active vibration control methods training of Indian military and commercial pilots are reviewed. Topics employing self-adaptive systems for higher-harmonic blade pitch discussed include the requirements for environmental and control and active airframe structural response control at key equipment cues; the generation of motion, visual, control-feel, locations. O.C. instrument, aural, navigation and communication, and flight cues; the simulation computer system; real-time interfaces; and the A88-53539 instructor station. A flow chart and photographs of the military THETURBOPROPCHALLENGE simulator are provided, and the effectiveness and cost-efficiency ALAN POSTLETHWAITE Flight International (ISSN 001 5-3710), of simulator training are demonstrated on the basis of statistical vol. 134, Sept. 3, 1988, p. 101, 102, 104-107. data. T.K. While the 74-seat ATR72 twin-turboprop commuter airliner has been designed for use by regional airlines, it appears to possess A88-52697# a degree of operational performance and economy that may directly POSSIBLE FUTURE DEVELOPMENTS OF MOTORGLIDERS challenge turbofan airliners on short-range routes. It is accordingly AND LIGHT AIRCRAFT projected that as many as 350 of these aircraft may be sold, not PIER0 MORELLI (Torino, Politecnico, Turin, Italy) Aeronautical only in the deregulated U.S. market, but in the European Economic Society of India, Journal (ISSN 0001-9267), vol. 39, Nov. 1987, p. Community market when it undergoes liberalization after 1992. 179-188. Attention is presently given to the design features and After a brief review of the development of light aircraft and manufacturing methods employed in ATR72 production. O.C. sailplanes in the past 50 years, the basic innovations in sailplane technology are outlined. The recent development of motor gliders A88-53634# is then illustrated. In order to stimulate the development of light REAL-TIME SIMULATION OF HELICOPTERS USING THE aircraft with low operational costs, a new type of competition is BLADE ELEMENT METHOD suggested where speed and fuel consumption are both taken into KOOS ZWAANENBURG (Applied Dynamics International, Ann accout. Finally, the possible development of a self-sustaining motor Arbor, MI) IN: AIAA, Flight Simulation Technologies Conference, glider is considered. Author. Atlanta, GA, Sept. 7-9, 1988, Technical Papers. Washington, DC,

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American Institute of Aeronautics and Astronautics, 1988, p. studies, a comparison was made of the handling qualities for several 49-53. aircraft configurations when flown in the NT-33A compared to the (AIAA PAPER 88-4582) same configurations flown in a ground Vertical Motion Simulator; This paper discusses the experience gained in applying the allowable time delays were determined for several different aircraft AD 100 computer to the real-time simulation of helicopters using types during up-and-away tracking tasks. The third NT-33A program the blade element method. The use of a single computer, together was designed to investigate the effect of feel-system dynamics with the ADSIM simulation language, eliminates many of the on the aircraft handling qualities. It was shown that an aircraft problems associated with the application of multiple configuration with known poor handling qualities was not general-purpose computers, programmed in FORTRAN, to such a necessarily evaluated as such in a ground simulator. It is large and complex real-time simulation. In particular, this paper emphasized that calibration and documentation is an essential shows that the implementation of the blade element rotor equations step in the set-up of a simulation of the aircraft dynamics, as well for the UH-GOA Black Hawk helicopter is a straightforward task as of the time-delay and the control-stick characteristics. I.S. on the AD 100. Author A88-53652# A88-53649# VISTA/F16 - THE NEXT HIGH-PERFORMANCE IN-FLIGHT VSRA IN-FLIGHT SIMULATOR - ITS EVALUATION AND SIMULATOR APPLICATIONS GARY K. HELLMANN, DAVID E. FREARSON, and JACK BARRY, MASAKI KOMODA (Tokyo Metropolitan Institute of Technology, JR. (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Japan), NAGAKATSU KAWAHATA (Nihon University, Chiba, OH) IN: AIAA, Flight Simulation Technologies Conference, Atlanta, Japan), YUKlCHl TSUKANO, and TAKATSUGU ON0 (National GA, Sept. 7-9, 1988, Technical Papers. Washington, DC, American Aerospace Laboratory, Tokyo, Japan) IN: AIAA, Flight Simulation Institute of Aeronautics and Astronautics, 1988, p. 198-205. Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, Technical (AIAA PAPER 88-4610) Papers. Washington, DC, American Institute of Aeronautics and A new, high-performance in-flight simulator aircraft is required Astronautics, 1988, p. 171-1 81. refs by the Air Force to support aeronautical research and development (AIAA PAPER 88-4605) over the next twenty-five to thirty years. The Variable Stability The paper describes an in-flight simulator named VSRA (variable In-Flight Simulator Test Aircraft (VISTA) is a USAF Advanced stability and response airplane), in some detail. The VSRA system Development Program to design, build, test, and field an improved is designed based upon an explicit model following theory. Only high perfomance in-flight simulator using an F-16D as the host linearized dynamics are assumed. Discussed are technical aircraft. The primary mission of VISTA will be in-flight simulation difficulties which are pertinent to the VSRA systems and have of the flight characteristics and pilot interfaces of new flight vehicles been overcome to achieve good model following capabilities. Two and advanced weapon systems. Author examples of VSRA's application to studying problems concerning man-machine dynamic systems are included to show that the VSRA is a mandatory device to some classes of flight mechanical A8&53752'# National Aeronautics and Space Administration. problem. Author Ames Research Center, Moffett Field, Calif. THE APPLICATION OF ARTIFICIAL INTELLIGENCE A88-53650*# National Aeronautics and Space Administration. TECHNOLOGY TO AERONAUTICAL SYSTEM DESIGN Lyndon B. Johnson Space Center, Houston, Tex. E. E. BOUCHARD (Lockheed Aeronautical Systems Co., Burbank, NASA SHUTTLE TRAINING AIRCRAFT FLIGHT SIMULATION CA), G. H. KIDWELL (NASA, Ames Research Center, Moffett Field, OVERVIEW CA), and J. E. ROGAN (Georgia Institute of Technology, Atlanta) CHARLES R. JUSTIZ and SURESH M. PATEL (NASA, Johnson AIAA, AHS, and ASEE, Aircraft Design, Systems and Operations Space Center, Houston, TX) IN: AIAA, Flight Simulation Meeting, Atlanta, GA, Sept. 7-9, 1988. 21 p. refs Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, Technical (AIAA PAPER 88-4426) Papers. Washington, DC, American Institute of Aeronautics and This paper describes the automation of one class of aeronautical Astronautics, 1988, p. 182-190. design activity using artificial intelligence and advanced software (AIAA PAPER 88-4608) techniques. Its purpose is to suggest concepts, terminology, and The Shuttle Training Aircraft (STA) is a variable stability, variable approaches that may be useful in enhancing design automation. control law flying simulator used by NASAIJSC to train astronauts By understanding the basic concepts and tasks in design, and in the final landing phase of a Space Shuttle Orbiter. A general the technologies that are available, it will be possible to produce, outline is given for the STA flight simulation system. An overview in the future, systems whose capabilities far exceed those of today's is given of the software generation and verification process through methods. Some of the tasks that will be discussed have already the Advanced Validation System (AVAS). The flight test techniques been automated and are in production use, resulting in significant for software verification will be reviewed and the process for productivity benefits. The concepts and techniques discussed are releasing the software for flight training will be covered. The applicable to all design activity, though aeronautical applications astronaut STA training syllabus is examined. Parameter matching are specifically presented. Author with the Orbiter in the final approach phase of de-orbit and landing is briefly examined. Simulation performance will be assessed A88-53753# against flight data, performance measurement, and cue A QUASI-PROCEDURAL, KNOWLEDGE-BASED SYSTEM FOR synchronization. Author AIRCRAFT DESIGN ILAN KROO (Stanford University, CA) and MASAMI TAKA1 AIAA, AB8-53651# AHS, and ASEE, Aircraft Design, Systems and Operations Meeting, GROUND SIMULATOR REQUIREMENTS BASED ON Atlanta, GA, Sept. 7-9, 1988. 11 p. refs IN-FLIGHT SIMULATION (AIAA PAPER 88-4428) LOUIS H. KNOTS and RANDALL E. BAILEY (Calspan Advanced An aircraft-design program has been developed that combines Technology Center, Buffalo, NY) IN: AIAA, Flight Simulation a rule-based advice and warning system with an extensible set of Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, Technical analysis routines in an unconventional architecture; its procedural Papers. Washington, DC, American Institute of Aeronautics and modules for aircraft aerodynamics, structures, propulsion, and Astronautics, 1988, p. 191-1 97. refs operating costs calculations allow results to be obtained upon (Contract F33615-83-C-3603) execution in the requisite order. These modules are procedural, (AIAA PAPER 88-4609) allowing programmers a degree of flexibility for the inclusion of The results of three research programs initiated to evaluate either brief definitions or complex local procedures. This structure issues relevant to the simulation fidelity of the NT-33A in-flight is encapsulated in an executive routine with a highly interactive, simulator aircraft are discussed. In the course of two of these event-driven, graphical interface and expert system. O.C.

806 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A88-53754*# Georgia Inst. of Tech., Atlanta. G. M. GREGOREK, R. R. BOYD, and P. S. WEISSMAN (Ohio DEVELOPMENT OF A MICRO-COMPUTER BASED State University, Columbus) AIAA, AHS, and ASEE, Aircraft INTEGRATED DESIGN SYSTEM FOR HIGH ALTITUDE LONG Design, Systems and Operations Meeting, Atlanta, GA, Sept. 7-9, ENDURANCE AIRCRAFT 1988. 13 p. DAVID W. HALL (David Hall Consulting, Sunnyvale, CA) and J. (AIAA PAPER 88-4484) EDWARD ROGAN (Georgia Institute of Technology, Atlanta) AIAA, Of four eight-student design teams, two undertook the design AHS, and ASEE, Aircraft Design, Systems and Operations Meeting, of a Mach 5-cruise HST and the remaining two of a Mach 3-cruise Atlanta, GA, Sept. 7-9, 1988. 23 p. NASA-sponsored research. SST each of the aircraft would carry 250 passengers over 6500 refs n. mi., and would be able to operate from 15,000-ft runways. Four (AIAA PAPER 88-4429) design concepts were conceived and evaluated; the SSTs were a A microcomputer-based integration of aircraft design disciplines variable-sweep oblique wing and a cranked arrow wing, both using has been applied theoretically to sailplane, microwave-powered conventional turbojets and liquid hydrocarbon fuels, while the HSTs aircraft, and High Altitude Long-Endurance (HALE) aircraft respectively employ fixed-sweep and variable-sweep wings, and configurational definition efforts. Attention is presently given to are powered by variable-cycle turbojetlramjet propulsion systems the further development of such integrated-disciplines approaches fueled by methane. Development and operating cost considerations through the incorporation of AI techniques; these are then applied favor the SSTs over the HSTs. O.C. to the aforementioned case of the HALE. The 'windFrame' language used, which is based on HyperTalk, will allow designers to write A88-53765# programs using a highly graphical, user interface-oriented PRELIMINARY DESIGN OF TWO TRANSPACIFIC HIGH SPEED environment. O.C. CIVIL TRANSPORTS LOUIS J. HENDRICH (Kansas, University, Lawrence) AIAA, AHS, A88-53758# and ASEE, Aircraft Design, Systems and Operations Meeting, CANARD CERTIFICATION LOADS - PROGRESS TOWARD Atlanta, GA, Sept. 7-9, 1988. 8 p. Research supported by ALLEVIATING FAA CONCERNS Universities Space Research Association. refs TERENCE J. BARNES and EDWARD A. GABRIEL (FAA, (AIAA PAPER 88-44858) Washington, DC) AIAA, AHS, and ASEE, Aircraft Design, Systems Two high speed civil transport design concepts are presented. and Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 14 p. Both transports are designed for a 5500 n.m. range with 300 (AIAA PAPER 88-4462) passengers. The first design concept is a Mach 2.5 joined-wing An evaluation is made of FAA concerns with permitted structural single fuselage transport. The second design concept is a Mach loads on general aviation aircraft with canard configurations; such 4.0, twin fuselage, variable sweep wing transport. The use of aircraft include the Beech Starship, OMAC Laser 3000, AVTEK conventional hydrocarbon fuels is emphasized to reduce the 400, Piaggio P-180, and Gyroflug Speed Canard. A canard aircraft's amount of change required in current airport facilities. Advanced forward airfoil is the first to penetrate gusts, causing pitch-up and aluminum alloys are used in the designs when possible to reduce main wing IiftAoading increases. In addition, the influence of the material and production costs over more 'exotic' materials. Methods forward lifting surface on the main wing varies with both its location to reduce the airport noise, community noise, and fly-over noise and the given flight conditions. A lifting-surface or full-configuration are incorporated into the designs. In addition, requirements set aerodynamic model is recommended for the evaluation of forward forth by the FARs have been addressed. Author airfoil effects. O.C. A88-53767# A88-53759# PLANFORM EFFECTS ON HIGH SPEED CIVIL TRANSPORT A COMPARISON OF CFD AND FULL SCALE VARIEZE WIND DESIGN TUNNEL RESULTS S. H. CASS and C. M. BALL (California State Polytechnic University, MARK E. BEYER (OMAC, Inc., Albany, GA) AIAA, AHS, and Pomona) AIAA, AHS, and ASEE, Aircraft Design, Systems and ASEE, Aircraft Design, Systems and Operations Meeting, Atlanta, Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 13 p. refs GA, Sept. 7-9, 1988. 11 p. refs (AIAA PAPER 88-4487) (AIAA PAPER 88-4463) A Universities Space Research Association (USRA) sponsored Computational fluid dynamic analysis, CFD, is compared the (undergraduate) study is presented on planform effects on high full scale wind tunnel results. The configuration modeled is the speed civil transport design in the Mach 3 to 6 range. A request Rutan VariEze with leading edge droops and a low canard. for proposal and mission profile was common to four aircraft Comparisons incorporate results from wind tunnel tests conducted designs. These air-craft were designed to the same mission in by NASA in the Langley 30 by 60 Foot Tunnel. Computational order to draw conclusions regarding the performance of the aircraft. modeling makes use of VariEze kit plans, scale drawings, and The four configurations considered were the blended-wing-body cordax data taken directly from the wind tunnel model. Analysis concept, joined wing concept, oblique wing concept and the caret was performed using computer codes VSAERO and MCARF (waverider) concept. This paper presents the overall trends revised for use on the Compaq 386. Author common to the four configurations during high speed flight. Conclusions on the best planform are left to the reader due to A88-53763# the fact that the designs all have positive and negative aspects. THE IMPACT OF VTOL ON THE CONCEPTUAL DESIGN However, the paper points out these positive and negative aspects PROCESS for each area of the design. Author DANIEL P. RAYMER (Lockheed Aeronautical Systems Co., Burbank, CA) AIAA, AHS, and ASEE, Aircraft Design, Systems A88-53768# and Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 16 p. DESIGN CONCEPTS FOR AN ADVANCED CARGO refs ROTORCRAFT (AIAA PAPER 88-4479) D. P. SCHRAGE (Georgia Institute of Technology, Atlanta), M. F. The factors influencing the conceptual design of jet VTOL COSTELLO, and D. N. MITTLEIDER AIAA, AHS, and ASEE, aircraft are discussed. The paper is intended to introduce the Aircraft Design, Systems and Operations Meeting, Atlanta, GA, CTOL-experienced aircraft conceptual designer to some of the Sept. 7-9, 1988. 11 p. refs unique requirements and pitfalls which must be considered when (AIAA PAPER 88-4496) performing configuration layout and vehicle sizing on a VTOL The Advanced Cargo Rotorcraft (ACR) heavy-lift helicopter's aircraft concept. Author configurational possibilities are presently evaluated for a case of no speed requirement greater than 200 kts. Single-main rotor, A88-53764# tanden-rotor, and 'warm-cycle' ACR helicopter configurations are HIGH SPEED TRANSPACIFIC PASSENGER FLIGHT considered; of these, the technologies entailed by the former two

807 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE configurations are most ready for implementation, and therefore for the 1990s that will yield significant weight and cost savings render them the lowest-risk and minimum-cost solutions. If payload over current structural and materials techniques. Attention is requirements rise far enough to drive vehicle gross weight above presently given to a utility helicopter fuselage developed under 100,000 Ibs, the warm cycle ACR alternative becomes the most ACAP auspices which meets U.S. Army survivability requirements, attractive. O.C. while exceeding 17-percent cost and 22-percent weight reduction requirements with a figure of 23 percent in each category. O.C. A88-53769# INTEGRATED THRUST VECTORING ON THE X-29A A8843783 J. F. KLAFIN (Grumman Corp., Aircraft Systems Div., Bethpage, LOCKHEED HlTB - STOL PERFORMANCE FEATURES NY) AIAA, AHS, and ASEE, Aircraft Design, Systems and GUY W. PACKARD (Lockheed-Georgia Co., Marietta) SAWE, Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 17 p. refs Annual Conference, 46th, Seattle, WA, May 18-20, 1987. 18 p. (AIAA PAPER 88-4499) (SAWE PAPER 1772) The X-29A forward swept wing planform offers special An account is given of the lift-enhancement and low speed advantages at high angle-of-attack for thrust vectoring evaluation. stability and control-improving design changes made to the The goal of this investigation was to evaluate the controllability of C-130-based High Technology Test Bed (HTTB) aircraft in order the X-29A with multiaxis thrust vectoring for angles-of-attack up to achieve the 1500-foot runway length requirement anticipated to +90 deg. Analytical design techniques were applied to integrate for next-generation tactical cargo aircraft. Configurational two-axis thrust vectoring with the X-29A aerodynamic flight control modifications of the airframe encompassed longer-chord flaps and laws. Lateral-directional control law cross-coupling provided roll leading edges, spoilers, extended-chord control surfaces, control about the velocity vector. Piloted simulations were used empennage leading edge extensions, and a high sink-rate landing for handling quality evaluation with the aircraft trimmed outside gear. A more powerful engine was incorporated. All HTTB primary the X-29A flight envelope at 0.2 Mach, 15,000 feet and 33 deg flight controls were changed from ’boost’ type to full-power angle-of-attack. Longitudinal control achieved a Level 1 handling operation. O.C. quality rating for angles-of-attack up to + 90 deg. Lateral-directional control achieved a Level 2 handling quality rating up to +75 deg A88-53784 angle-of-attack. Better lateral-directional ratings appeared ULTIMATE FACTOR FOR STRUCTURAL DESIGN OF MODERN achievable with control law improvements. Aircraft controllability FIGHTERS at very low speeds and high angles-of-attack can open superagility 0. SENSBURG, 0. BARTSCH, and H. BERGMANN vistas for tactical applications. The capability can be provided; the (Messerschmitt-Boelkow-Blohm GmbH, Munich, Federal Republic tactics require development. Author of Germany) SAWE, Annual Conference, 46th, Seattle, WA, May 18-20, 1987. 33 p. refs A88-53770# (SAWE PAPER 1775) ASSESSMENT OF A SOVIET HYPERSONIC TRANSPORT An examination and reevaluation is conducted of the classic RICHARD D. WARD, MARK A. LEAGUE, and EDDIE MOORE fighter aircraft structural design stipulation of a 1.5 ultimate stress (General Dynamics Corp., Fort Worth, TX) AIAA, AHS, and ASEE, factor, in light of the application of highly redundant flight control Aircraft Design, Systems and Operations Meeting, Atlanta, GA, systems (FCSs) to highly unstable aircraft, such as those with Sept. 7-9, 1988. 14 p. canard configurations. This total dependence of aircraft stability (AIAA PAPER 88-4506) on FCSs, and the dependence of applied loads on the FCS in An evaluation has been made of existing indications of Soviet turn, means that design loads cannot be exceeded; it is therefore interest in, and progress towards, an operational hypersonic judged possible to reduce the ultimate load factor to 1.4 or less. transport (HST) applicable in both the civilian and the military O.C. spheres. The first hard data on a Soviet HST was obtained at the 1987 Paris Air Show, which indicated that research had been A8843786 conducted by the Tupolev design bureau on a Mach 5-6 cruise A DIFFERENT APPROACH TO THE INTERRELATED vehicle of 100 m length; its first flight was projected to be in SUBJECTS OF WEIGHT, PERFORMANCE, AND PRICE AS 1999, and would be large enough to carry 300 passengers over APPLIED TO COMMERCIAL TRANSPORT AIRCRAFT 4500 miles. Methane is the probable fuel employed. An account EDMOND J. GAUTHIER (Boeing Commercial Airplane Co., Seattle, is given of the organization of the present analysis effort. O.C. WA) SAWE, Annual Conference, 46th. Seattle, WA, May 18-20, 1987. 27 p. A8 8- 5 3 7 7 6 (SAWE PAPER 1779) THE CRITICALITY OF WEIGHT AND BALANCE ON Commercial airplane sizing is a complex process in which COMPETITION AIRCRAFT experts in the diverse disciplines of mass properties, aerodynamics, BRUCE J. BOLAND (Lockheed-California Co., Burbank) SAWE, propulsion, and finance perform studies and iterate these studies Annual Conference, 46th, Seattle, WA, May 18-20, 1987. 19 p. until a satisfactory design is evolved. Because each discipline has (SAWE PAPER 1756) its own set of fine-tuned detailed parametric relationships often The sensitivity of a high-performance short-coupled aircraft to buried deep within elaborate computer programs, it is not easy to weight change and center of gravity movement is demonstrated. understand the big picture - how the individual parameters influence A ’hands-on’ application of weight and balance principles is the size (weight) of the resultant design. This paper employs many provided. The aircraft considered, the Tsunami, is an all metal simplifications in all disciplines in order to develop a method for low-wing monoplane designed for the purpose of racing, record an easy understanding of airplane sizing. It begins with a different setting, and research. K.K. approach to weight categories, followed by an overall performance parameter derivation, and introduces a ballpark evaluation of A88-53781 airplane price. The resulting simplified method is then applied to ADVANCED COMPOSITE AIRFRAME PROGRAM (ACAP) - AN the value of a pound and to fuel efficiency comparisons. Author UPDATE AND FINAL ASSESSMENT OF WEIGHT SAVING POTENTIAL A88-53789 WILLIAM H. MARR (U.S. Army, Aeronautical Systems Div., Fort OVERVIEW OF LOCKHEED C-130 HIGH TECHNOLOGY TEST Eustis, VA) and JOHN G. SUTTON (United Technologies Corp., BEDPROGRAM Sikorsky Aircraft, Stratford, CT) SAWE, Annual Conference, 46th, CLARENCE M. CAMPBELL (Lockheed-Georgia Co., Marietta) Seattle, WA, May 18-20, 1987. 26 p. refs SAWE, Annual Conference, 46th, Seattle, WA, May 18-20, 1987. (SAWE PAPER 1770) 29 p. refs The U.S. Army’s Advanced Composite Airframe Program (ACAP) (SAWE PAPER 1786) is charged with the development of helicopter primary structures The High Technology Test Bed (HTTB) flight test aircraft is a

808 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

highly instrumented platform based on the four-engine ‘2-130 1987. 16 p. tactical airlifter for the study of prospective benefits from the (SAWE PAPER 1798) integration of such generic technologies as HUDs, mission An evaluation is made of the development status and computers, GPS, FLIR, metal-matrix composites, weather-mapping applicability to state-of-the-art medium-range transport aircraft of radars, etc. STOL is a major goal of the HTTB effort, and is technologies that may improve airline operating cost. The aircraft reflected in the incorporation of more powerful engines, empennage in question are of B757 class. Attention is given to factors figuring leading-edge extensions, a high sink-rate landing gear, and an in direct operating costs, the cost effects of AI-Li alloy and extended-chord aileron. A roll-, pitch-, and yaw-augmenting digital advanced composite structures’ introduction, the operational flight control system is also incorporated. O.C. advantages of such systems as electronic engine controls and fly-by-wire control for relaxed static stability flight characteristics, A88-53790 and the effect on operating economics of airport delays that may ESTIMATING FUSELAGE WEIGHT PENALTY REQUIRED TO be precluded through improved technologies’ application. O.C. SUPPRESS NOISE FROM PROPFANS PHILIP L. BREUER (Boeing Military Airplane Co., Wichita, KS) A88-543 1O# SAWE, Annual Conference, 46th, Seattle, WA, May 18-20, 1987. HELICOPTER HEALTH MONITORING FROM ENGINE TO 7 P. ROTOR (SAWE PAPER 1787) J. F. MARRIOTT and J. F. M. KAYE (Hawker Siddeley Dynamics With advances in counter-rotating, unducted propfan propulsion Engineering, Ltd., Welwyn Garden City, England) ASME, Gas technology, an accurate and rapid method of estimating the Turbine and Aeroengine Congress and Exposition, Amsterdam, fuselage weight penalty due to suppression of external noise Netherlands, June 6-9, 1988. 7 p. generated by propfans is needed to support initial aircraft design. (ASME PAPER 88-GT-227) Such a method for use in the preliminary/conceptual design phase The practical aspects of helicopter health and usage monitoring is presented in this paper. This method predicts the fuselage weight systems are discussed with emphasis on the implications of penalty based upon specific air vehicle configuration data, acoustic on-board vibration monitoring. The discussion includes a brief phenomena, and mission requirements. The noise level is review of monitoring system evolution, monitoring requirements analytically determined at discrete fuselage panel locations over and functions, integrated monitoring system design concepts, and the entire fuselage, and the total weight penalty is the sum of the operating requirements, limits, and standards. A general diagram delta weights calculated for these individual panels. Use and of an integrated health and usage monitoring system is shown. application of input parameters are discussed and examples V.L. showing the sound pressure level patterns on the fuselage surface for different longitudinal engine locations are shown. Author A88-54954# DYNAMICS OF HELICOPTER ROTORS J. K. SURESH and V. RAMAMURTI (Indian Institute of Technology, A88-53791 Madras) IN: Developments in Mechanics. Volume 14(c) - CRASHWORTHINESS VS. AIRWORTHINESS Midwestern Mechanics Conference, 20th, West Lafayette, IN, Aug. PHILIP F. KAUFMAN (US. Navy, Naval Air Development Center, 31 -Sept. 2, 1987, Proceedings. West Lafayette, IN, Purdue Warminster, PA) SAWE, Annual Conference, 46th, Seattle, WA, University, 1987, p. 1042-1047. refs May 18-20, 1987. 17 p. refs The large-deformation dynamic behavior of bearingless (SAWE PAPER 1788) helicopter rotors is investigated analytically. The geometrical This paper discusses the relevance of the standards set for configuration of the problem is illustrated with drawings; the airworthiness of an aircraft and the safety of flight to the fundamental equations of motion are derived (taking nonlinear and requirements of crashworthiness of the aircraft and aircraft composite characteristics into account); and a formulation for the installations in case of an accident. It is emphasized that the equilibrium condition is obtained. T.K. crashworthiness is an important aspect of the aircraft design process and that crashworthiness can be achieved by an effective mix of many crashworthiness factors. These factors include A88-55317# providing a protective shell, adequate tie downs, energy attenuation PILOTAGE SYSTEM FOR THE PRONAOS GONDOLA (seats, landing gear, fuselage, and cargo), eliminating environmental G. BRONDINO (CNES, Toulouse, France) IAF, International debris, and minimizing post-crash hazards, such as egress, fire, Astronautical Congress, 39th, Bangalore, India, Oct. 8-15, 1988. and toxic fumes. The solution that takes in consideration all these 6P elements has to be examined within the framework of a total (IAF PAPER 88-008) In the framework of Pronaos, a French program for systems approach to crashworthy design. 1,s. submillimetric astronomy, a balloon-gondola vehicle carrying a 2-m submillimetric telescope is being developed. The scientific A8843797 requirements for the observations demand a precision of + or - WEIGHT GROWTH IN AIRLINE SERVICE 15 arcsecs, and a stability of 5 arcsecs rms on the pointing accuracy J. H. WOOD (British Airways, PLC, Hounslow, England) SAWE, during the flight. The gondola weighs 2200 kg at take off, has Annual Conference, 46th, Seattle, WA, May 18-20, 1987. 11 p. dimensions of 4 X 4 m at the base and is 7.5 m high. The flight (SAWE PAPER 1796) has a typical altitude of 36 km and the estimated volume of the An analysis is conducted into the reasons for weight growth in balloon is 800,000 cu m. A detailed description of the system and several different aircraft fleets during the last 12-18 months. A simulation results are presented. R.B. major refurbishment program has been conducted for the One-Eleven airliners, in conjunction with mandatory modifications; N88-28867# Aircraft Research Association Ltd., Bedford these encompass turbofan engine noise-suppression device (England). retrofits, the fireblocking of passenger and crew seats, and the TRANSPORT-TYPE CONFIGURATIONS installation of toilet smoke detection systems and floor-proximity A. B. HAINES and A. ELSENAAR (National Aerospace Lab., escape path lighting. Other fleet aircraft studied are the 8747, Amsterdam, Netherlands ) /n AGARD, Boundary Layer Simulation B737, 8757, Tristar, and Concorde. O.C. and Control in Wind Tunnels p 139-163 Apr. 1988 Avail: NTlS HC A2O/MF A01 A88-53798 Various reasons can be advanced for treating transports as a ECONOMICAL TECHNOLOGY APPLICATION IN COMMERCIAL separate, distinct class of aircraft for the purpose of defining a TRANSPORT DESIGN detailed viscous simulation methodology. The detailed methodology MICHAEL L. DRAKE (Boeing Commercial Airplane Co., Seattle, as described was based on past experience and an appreciation WA) SAWE, Annual Conference, 46th. Seattle, WA, May 18-20, of how the advances in computational fluid dynamics can be

809 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE exploited to place the methodology on a more scientific basis. It used to estimate the unknown parameters by optimization of the is recommended that, to gain experience, the proposed likelihood function. For the state estimation both time-varying and methodology should be applied for a significant period in parallel steady-state filters are used. In the filtering approach the unknown with whatever is the established practice. Any large differences in parameters are estimated as augmented states using the extended the extrapolated results should be assessed to find whether the Kalman filter. The estimation results from three model postulates, reasons justify departure from existing practice: in other words, one linear and two nonlinear, to extract aircraft derivatives from the methodology that was set forth should be better, being on a simulated and flight test data are used for comparison. Aspects sound scientific basis, but it will still have to prove itself in the such as convergence, computational time, parameter estimates future. Author and their accuracies are evaluated for each of the four estimation algorithms. ESA NEE-28868# Aircraft Research Association Ltd., Bedford (England). NEE-289 12# Technische Univ., Brunswick (West Germany). COMBAT AIRCRAFT Fakultaet fuer Maschinenbau und Elektrotechnik. A. B. HAINES ln AGARD, Boundary Layer Simulation and Control A CONTRIBUTION TO THE QUANTITATIVE ANALYSIS OF in Wind Tunnels p 164-190 Apr. 1988 THE INFLUENCE OF DESIGN PARAMETERS ON THE Avail: NTlS HC A20/MF A01 OPTIMAL DESIGN OF PASSENGER AIRCRAFT Ph.D. Thesis Devising a viscous simulation methodology for model tests of [EIN BEITRAG ZUR QUANTITATIVEN ANALVSE DES a combat aircraft design is more difficult than for a subsonic EINFLUSSES VON AUSLEGUNGSPARAMETERN AUF DEN transport. The geometry is more complicated and hence, more OPTIMALEN ENTWURF VON VERKEHRSELUGZEUGEN] difficult to model for a computational fluid dynamics (CFD) HANS-WILHELM POHL 1987 160 p In GERMAN calculation; the flow patterns are more complex and can contain (ETN-88-92979) Avail: NTlS HC A08/MF A01 various interacting features; there is more interest in the The dependencies of passenger aircraft design parameters on development of the flow beyond the buffet-onset boundary; the several factors were analyzed, with emphasis on the effects of ability to manipulate the boundary layer in the model tests is more fuel price increases. With a view to optimization calculations a limited. The emphasis in the methodology rests on the in-depth two-phase program system for the aircraft was developed; it is study of the flow patterns and, in particular, the identification of represented in the form of timing charts. The first part of the the scale-sensitive viscous effects in the flow patterns over the program pre-optimizes a large number of design parameters, model under test. The description of these flow patterns and of performs sensitivity studies, and indentifies side-minima. The results how, in principle, to construct a methodology to meet the various are used as initial values in the second part of the program to possible situations, is based on past experience and on an determine the optimized design with substantially better precision. awareness of the advances in CFD methods. Author The optimization programs determine the effects of external boundary conditions on the design. The effects of fuel costs and NEE-28908# Conrad Technologies, Inc., King of Prussia, Pa. capital costs on the optimum design are presented. ESA STRUCTURAL DYNAMICS OF MANEUVERING AIRCRAFT Final Report, Jul. 1986 - Sep. 1987 NEE-28913# European Space Agency, Paris (France). M. M. REDD1 Sep. 1987 90 p ADDITIONAL INVESTIGATIONS INTO THE AIRCRAFT (Contract N62269-86-C-0278) LANDING PROCESS TEST DISTRIBUTIONS (AD-A192376; CTI-8601; NADC-88014-60) Avail: NTlS HC HANNS-JUERGEN PETERS (Deutsche Forschungs- und A05/MF A01 CSCL 20K Versuchsanstalt fuer Luft- und Raumfahrt, Cologne, West Ger- The technical objectives of the research are to establish the many) Jun. 1988 74 p Transl. into ENGLISH of Erganzende Unter- minimum level of modeling necessary for predicting the dynamic suchungen zum Landeprozess von Flugzeugen - Testver- stresses in fighter aircraft during maneuvers and transitions teilungen, Cologne, Federal Rep. of West Germany (DFVLR) Orig- between maneuvers, to identify the physical phenomena which inal language document was announced as N88-16686 are significant, to identify potential shortfalls in current aircraft (ESA-TT-1099; DFVLR-MITT-87-13; ETN-88-93055) Avail: NTlS design technology and to identify areas for further research. A HC A04/MF A01; original German version available from DFVLR, symmetric wing, modeled as a beam with quasi-steady aerodynamic VB-PL-DO, 90 60 58, 5000 Cologne, Fed. Republic of Germany loads introduced through the vortex lattice method, is used for 25.50 deutsche marks the dynamic evaluation. The dynamical equations of motion are The landing times for the 10 German civil airports, without solved in the time domain by the Runge-Kutta method specialized waiting times due to aircraft allocations to holding areas, were to second order equations. The maneuver dynamic analysis investigated using a simulation model for the landing process. program, MANDYN, written in FORTRAN 77, uses the parameters Test distributions were developed. Results are synthetic landing of real variable-geometry airplane. An extensive investigation of time distributions with waiting times, the adaptation of which to dynamic loads resulting from a simple maneuver for various severity the empirical landing time distribution was evaluated using the levels revealed that the lowest natural frequency and load Chi-square test. Further improvements of the adaptation of the application time are significant factors in determining the validity simulated distribution to the empirical one can be obtained by of the load factor approach. Recommendations based on the study structural changes of the test distribution, e.g., by limitation of the results are made. GRA maximum landing time. ESA NEE-2891 1# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Brunswick (West Germany). Abteilung NEE-28914' National Aeronautics and Space Administration. Mathematische Verfahren und Datentechnik. Ames Research Center, Moffett Field, Calif. ESTIMATION OF AIRCRAFT PARAMETERS USING FILTER HIGH PERFORMANCE FORWARD SWEPT WING AIRCRAFT ERROR METHODS AND EXTENDED KALMAN FILTER Patent RAVINDRA JATEGAONKAR (Technische Univ., Brunswick, West DAVID G. KOENIG, inventor (to NASA), KlYOSHl AOYAGI, inventor Germany ) and ERMlN PLAETSCHKE Mar. 1988 59 p (to NASA), MICHAEL R. DUDLEY, inventor (to NASA), and SUSAN (DFVLR-FB-88-15; ISSN-0171-1342; ETN-88-92933) Avail: NTlS B. SCHMIDT, inventor (to NASA) 30 Aug. 1988 14 p Filed HC A04/MF A01; DFVLR, VB-PL-DO, 90 60 58, 5000 Cologne, 24 Nov. 1986 Supersedes N87-18561 (25 - 11. p 1439) Fed. Republic of Germany, 23 Deutsche marks (NASA-CASE-ARC-11636-1 ; US-PATENT-4,767,083; Four algorithms for parameter estimation in linear and nonlinear US-PATENT-APPL-SN-933963; US-PATENT-CLASS-244-12.3; systems accounting for process and measurement noise using US-PATENT-CLASS-244-12.4; US-PATENT-CLASS-244-207; two different approaches, namely direct approach and filtering US-PATENT-CLASS-244-45-A;US-PATENT-CLASS-244-55) approach, are compared. In the direct approach the iterative Avail: US Patent and Trademark Office CSCL 01C Gauss-Newton method incorporating a suitable state estimator is A high performance aircraft capable of subsonic, transonic and

810 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

supersonic speeds employs a forward swept wing planform and Study requirements, assumptions and guidelines were identified at least one first and second solution ejector located on the inboard regarding carrier suitability, aircraft missions, technology availability, section of the wing. A high degree of flow control on the inboard and propulsion considerations. Conceptual designs were executed sections of the wing is achieved along with improved for two missions, a full multimission aircraft and a minimum mission maneuverability and control of pitch, roll and yaw. Lift loss is aircraft using three different propulsion systems, the UnDucted ' delayed to higher angles of attack than in conventional aircraft. In Fan (UDF), the Propfan and an advanced Turbofan. Detailed aircraft one embodiment the ejectors may be advantageously positioned optimization was completed on those configurations yielding gross spanwise on the wing while the ductwork is kept to a minimum. weight performance and carrier spot factors. Propfan STOVL Official Gazette of the US. Patent and Trademark Office conceptual designs were exercised also to show the effects of STOVL on gross weight, spot factor and cost. An advanced N88-28915*# Douglas Aircraft Co., Inc., Long Beach, Calif. technology research plan was generated to identify additional CRITICAL JOINTS IN LARGE COMPOSITE PRIMARY investigation opportunities from an airframe contractors standpoint. AIRCRAFT STRUCTURES. VOLUME 2 TECHNOLOGY Life cycle cost analysis was accomplished yielding a comparison DEMONSTRATION TEST REPORT of the UDF and propfan configurations against each other as well BRUCE L. BUNIN Jun. 1985 209 p as against a turbofan with equivalent state of the art (Contract NAS1-16857) turbo-machinery. Author (NASA-CR-172587; NAS 1.26:172587; ACEE-26-TR-3478-VOL-2) Avail: NTlS HC AlO/MF A01 CSCL 01C N88-28918'# National Aeronautics and Space Administration. A program was conducted to develop the technology for critical Ames Research Center, Moffett Field, Calif. structural joints in composite wing structure that meets all the TEST RESULTS AT TRANSONIC SPEEDS ON A CONTOURED design requirements of a 1990 commercial transport aircraft. The OVER-THE-WING PROPFAN MODEL results of four large composite multirow bolted joint tests are ALAN D. LEVIN, DONALD B. SMELTZER. and RONALD C. presented. The tests were conducted to demonstrate the SMITH Jul. 1986 98 p technology for critical joints in highly loaded composite structure (NASA-TM-88206; A-86082; NAS 1.1 5:88206) Avail: NTlS HC and to verify the analytical methods that were developed throughout A05/MF A01 CSCL 01C the program. The test consisted of a wing skin-stringer transition A semispan wing/body model with a powered highly loaded specimen representing a stringer runout and skin splice on the propeller has been tested to provide data on the propulsion wing lower surface at the side of the fuselage attachment. All installation drag of advanced propfan-powered aircraft. The model tests were static tension tests. The composite material was Toray had a supercritical wing with a contoured over-the-wing nacelle. It T-300 fiber with Ciba-Geigy 914 resin in 10 mil tape form. The was tested in the Ames Research Center's (ARC) 14-foot Transonic splice members were metallic, using combinations of aluminum Wind Tunnel at a total pressure of 1 atm. The test was conducted and titanium. Discussions are given of the test article, at angles of attack from -0.5 to 4 deg at Mach numbers ranging instrumentation, test setup, test procedures, and test results for from 0.6 to 0.8. The test objectives were to determine propeller each of the four specimens. Some of the analytical predictions performance, exhaust jet effects, propeller slipstream interference are also included. Author drag, and total powerplant installation drag. Test results indicated a total powerplant installation drag of 82 counts (0.0082) at a N88-28916'# Douglas Aircraft Co., Inc., Long Beach, Calif. Mach number of 0.8 and a lift coefficient of 0.5, which is CRITICAL JOINTS IN LARGE COMPOSITE PRIMARY approximately 29 percent of a typical airplane cruise drag. AIRCRAFT STRUCTURES. VOLUME 3: ANCILLARY TEST Author RESULTS BRUCE L. BUNIN and R. L. SAGUl Washington, D.C. Jun. N88-29721# Lockheed Aeronautical Systems Co., Burbank, Calif. 1985 338 p Dynamic Loads Div. (Contract NAS1-16857) A SUMMARY OF METHODS FOR ESTABLISHING AIRFRAME (NASA-CR-172588; NAS 1.26:172588; DESIGN LOADS FROM CONTINUOUS GUST DESIGN ACEE-26-TR-3958A-VOL-3) Avail: NTlS HC A1 5/MF A01 CRITERIA CSCL 01c RICHARD N. MOON ln AGARD, The Flight of Flexible Aircraft A program was conducted to develop the technology for critical in Turbulence: State-of-the-Art in the Description and Modelling of structural joints for composite wing structure that meets all the Atmospheric Turbulence 40 p Jun. 1988 design requirements of a 1990 commercial transport aircraft. The Avail: NTlS HC AOG/MF A01 results of a comprehensive ancillary test program are summarized, Continuous gust design criteria for airframe design are specified consisting of single-bolt composite joint specimens tested in a in FAR 25, JAR 25 and various US. military specs. Two forms of variety of configurations. These tests were conducted to criterion, the design envelope approach and the mission analysis, characterize the strength and load deflection properties that are are usually referenced as an acceptable means of compliance. required for multirow joint analysis. The composite material was However, these criteria do not provide methods of applying the Toray 300 fiber and Ciba-Geigy 914 resin, in the form of 0.005 statistical results of the airframe manufacturer, subject to approval and 0.01 inch thick unidirectional tape. Tests were conducted in of the certifying agency. Some of the methods that are currently single and double shear for loaded and unloaded hole used by US. airframe manufacturers are summarized. Continuous configurations under both tensile and compressive loading. Two gust design requirements- from various certifying agencies are different layup patterns were examined. All tests were conducted reviewed. A brief discussion is also provided on the methods at room temperature. In addition, the results of NASA Standard employed to include the effect of the L-1011 Tristar active controls Toughness Test (NASA RP 1092) are reported, which were wing load alleviation system on the loads due to corrective roll conducted for several material systems. Author control in turbulence. Author

N88-28917'# Boeing Military Airplane Development, Wichita, N88-29722# Messerschmitt-Boelkow-BlohmG.m.b.H., Hamburg Kans. (West Germany). Civil and Transport Aircraft Div. MULTIPLE-PURPOSE SUBSONIC NAVAL AIRCRAFT (MPSNA): COMPARISON OF THE INFLUENCE OF DIFFERENT GUST MULTIPLE APPLICATION PROPFAN STUDY (MAPS) Final MODELS ON STRUCTURAL DESIGN Report MANFRED MOLZOW ln AGARD, The Flight of Flexible Aircraft R. M. ENGELBECK, C. T. HAVEY, A. KLAMKA, C. L. MCNEIL, in Turbulence: State-of-the-Art in the Description and Modelling of and M. A. PAIGE Sep. 1986 219 p Atmospheric Turbulence 17 p Jun. 1988 (Contract NAS3-24529) Avail: NTlS HC AO6/MF A01 (NASA-CR-175104; NAS 1.26:175104; D500-11313-1) Avail: Depending on the country of certification, different gust models NTlS HC AlO/MF A01 CSCL 01C and means of compliance of the airworthiness requirements have

81 1 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE to be covered in structural design of civil transport aircraft. The for stabilization, maneuvering and recovery from any possible influence on aircraft design from gust models, aircraft modeling, attitude, as well as for trim. Flying qualities aspects of agility include and control systems and laws is demonstrated on example of a the need for nonlinear flying qualities metrics, and control systems short to medium range transport aircraft. Recommendations for that provide both rapid maneuvering and good damping for tight future harmonized approaches in gust methods and modeling are tracking. For all aspect engagement, the pilot needs to be given. Author thoroughly integrated with displays, automatic flight control modes and other systems. For dynamic longitudinal flying qualities, N88-29738# National Aerospace Lab., Amsterdam MIL-STD 1797 presents the Control Anticipation Parameter of an (Netherlands). equivalent classical system as a primary criterion, but gives several LOW-SPEED LONGITUDINAL FLYING QUALITIES OF alternatives in recognition of other problems. Author MODERN TRANSPORT AIRCRAFT H. A. MOOIJ ln AGARD, Advances in Flying Qualities 16 p N88-29789'# National Aeronautics and Space Administration. May 1988 Langley Research Center, Hampton, Va. Avail: NTlS HC AO9/MF A01 COMPRESSION PYLON Patent Application The suitability of an aircraft with respect to human control is JAMES C. PATTERSON, JR., inventor (to NASA) 23 Jun. 1988 determined by its handling qualities. In modern transport aircraft 14 P the handling qualities are determined to a high degree by the (NASA-CASE-LAR-13777-1; NAS 1.71:LAR-13777-1; flight control system. An introduction to the following aspects of US-PATENT-APPL-SN-210480) Avail: NTlS HC AO3/MF A01 closed loop flight control systems for modern transport aircraft is CSCL 01c given: stabilization and maneuvering functions, candidate A compression pylon for an aircraft with a wing-mounted engine, implementation forms, manipulators for flight control, and that does not cause supersonic airflow to occur within the mathematical representations of the airtramelflight control system fuselage-wing-pylon-nacelle channel is presented. The chord length combination required for prediction and evaluation purposes. of the pylon is greater than the local chord length of the wing to Regarding criteria for good handling qualities of transport aircraft, which it is attached. The maximum thickness of the pylon occurs the terminal flight phase (takeoff, initial climb, final approach and at a point corresponding to the local trailing edge of the wing. As landing) are of prime interest. A treatise on a number of promising a result, the airflow through the channel never reaches supersonic quantitative criteria for transport aircraft equipped with advanced velocities. NASA flight control systems is given. Two groups of criteria are distinguished: criteria based on the dynamic characteristics of the N88-29790'# Draper (Charles Stark) Lab., Inc., Cambridge, aircraft alone and criteria based on the dynamic characteristics of Mass. the pilot/aircraft closed loop system. In the latter case, a INTELLIGENT FAULT DIAGNOSIS AND FAILURE quasi-linear describing function for the human controller behavior MANAGEMENT OF FLIGHT CONTROL ACTUATION SYSTEMS is used. Author Final Report, May 1986 - Mar. 1988 WILLIAM F. BONNICE and WALTER BAKER May 1988 90 p N88-29739# Systems Technology, Inc., Hawthorne, Calif. (Contract NAS2-12404) ADVANCES IN FLYING QUALITIES CONCEPTS AND (NASA-CR-177481; NAS 1.26:177481; CSDL-R-2055) Avail: CRITERIA FOR A MISSION ORIENTED FLYING QUALITIES NTlS HC A05/MF A01 CSCL 01C SPECIFICATION The real-time fault diagnosis and failure management (FDFM) ROGER H. HOH ln AGARD, Advances in Flying Qualities 28 p of current operational and experimental dual tandem aircraft flight May 1988 control system actuators was investigated. Dual tandem actuators Avail: NTlS HC AO9/MF A01 were studied because of the active FDFM capability required to There has been considerable activity over the past 8 years to manage the redundancy of these actuators. The FDFM methods upgrade the military flying qualities specifications for conventional used on current dual tandem actuators were determined by aircraft, as well as for V/STOLs and helicopters. The primary examining six specific actuators. The FDFM capability on these objectives of these upgrades has been to account for the use of six actuators was also evaluated. One approach for improving the high gain, high authority augmentation, and to more directly reflect FDFM capability on dual tandem actuators may be through the the requirements of the intended missions into the specifications. application of artificial intelligence (AI) technology. Existing AI The methodologies developed to accomplish the latter objective approaches and applications of FDFM were examined and are summarized. A brief overview of the Lower Order Equivalent evaluated. Based on the general survey of AI FDFM approaches, Systems and Bandwidth criteria follows. Problems with the the potential role of AI technology for real-time actuator FDFM specification of control sensitivity, and potential solutions are then was determined. Finally, FDFM and maintainability improvements discussed, followed by a brief presentation of the use of time vs for dual tandem actuators were recommended. Author frequency domain criteria. An empirical method to combine the Cooper-Harper Handling Qualities Ratings (HQRs) from each axis N88-29792# Anamet Labs., Inc., Hayward, Calif. of control into an overall rating is then presented. Finally, a COMPUTER PROGRAMS FOR GENERATION OF NASTRAN proposed specification for precision flare and landing is given, AND VIBRA-6 AIRCRAFT MODELS Final Report, Dec. 1985 - followed by an example application of the method. Author Dec. 1986 STEVEN G. HARRISON Apr. 1988 94 p N88-29740# Air Force Wright Aeronautical Labs., (Contract F33615-84-C-3216) Wright-Patterson AFB, Ohio. (AD-A195467; REPT-1286-1A; AFWL-TR-87-21) Avail: NTlS HC A SECOND LOOK AT MIL PRIME FLYING QUALITIES A05/MF A01 CSCL 12E REQUIREMENTS This report describes a series of computer programs designed ROBERT J. WOODCOCK ln AGARD, Advances in Flying Qualities to aid the analyst in preparing input data for aircraft models to be 15 p May 1988 analyzed using NASTRAN and/or VIBRA-6. The programs permit Avail: NTlS HC AO9/MF A01 creation of either beam or plate-type models of aircraft, subsequent Current and projected applications of flying qualities criteria postprocessing of NASTRAN OUTPUT2 files, and creation of are addressed. The current state of the art, its deficiencies, and VIBRA-6 AERO, IMOD and LOAD fixed data decks. In addition, needs for further work are addressed. The rationale for the new the analyst may specify use of either the Ritz procedure or standard US. Military Standard and Handbook on flying qualities is briefly NASTRAN eigensolvers to derive normal modes of the aircraft for discussed. With advanced vehicles, the scope of flying qualities is use in the VIBRA-6 vulnerability assessment. A command expanding, opening new areas to investigate and creating new procedure is provided to orchestrate the execution of the various problems. With relaxed static stability now commonly used, control programs, to keep track of file assignments and to maintain a margin is a prime safety consideration: control must be available history of program use. GRA

812 06 AIRCRAFT INSTRUMENTATION

N88-29795# RAND Corp., Santa Monica, Calif. for advanced hypersonic vehicles such as NASP were estimated AIRCRAFT AIRFRAME COST ESTIMATING RELATIONSHIPS based on anticipated trajectories and vehicle configurations. STUDY APPROACH AND CONCLUSIONS Surface pressure based measurements systems such as the Shuttle R. W. HESS and H. P. ROMANOFF Dec. 1987 107 p Entry Air Data System (SEADS) appear to be the most promising (Contract F49620-86-C-0008) candidates for advanced hypersonic vehicles. A SEADS-like (R-3255-AF; LC-87-28382; ISBN-0-8330-0610-2) Avail: NTlS HC forebody pressure distribution system for air data measurement AO6/MF A01 combined with an inlet surface pressure array for active inlet control Generalized equations are presented for estimating the is considered to be the most viable air data measurement development and production costs of aircraft airframes. Provided configuration. Due to the stringent requirements on the air data are separate cost estimating relationships (CERs) for engineering, and inlet control parameters, as well as the need to locate the tooling, manufacturing labor, and quality-control hours; surface pressure sensors in regions of extreme thermal load manufacturing material, development support, and flight-test cost; resulted in rigorous pressure transducer requirements (0.1 percent and total program cost. The CERs, expressed in the form of accuracy at 3000 F orifice temperature). Existing-technology high exponential equations, were derived by multiple least-squares precision pressure transducers were found to require active or regression analysis. They were derived from a data base consisting passive cooling in a hypersonic air data system. Author of 34 military aircraft with first flight dates ranging from 1948 to 1978. Most of the aircraft technical data were obtained from either A88-53827# original engineering documents such as manufacturers’ DIGITAL EMULATION OF THE AH-64A CONTRAST TRACKER performance substantiation reports, or from official Air Force and CHRIS CAST0 (McDonnell Douglas Helicopter Co., Mesa, AZ) Navy documents. The cost data were obtained from the airframe AIAA, NASA, and AFWAL, Conference on Sensors and manufacturers, either directly from their records or indirectly through Measurement Techniques for Aeronautical Applications, Atlanta, standard DoD reports such as Contractor Cost Data Reporting GA, Sept. 7-9, 1988. 5 p. system. Author (AIAA PAPER 88-46528) A low-cost system for simulating the contrast tracker of the AH-64A helicopter target acquisition designation system is proposed. Two VME-based circuit boards, a single-board computer (SBC) and a video frame grabber, function as a digital image processor which accepts video input from the simulation system’s AIRCRAFT INSTRUMENTATION image generator or IR effects processor. An Ada program running on the SBC is designed to track potential targets which are stored Includes cockpit and cabin display devices; and flight instruments. in the digital image. R.R.

A88-53830*# National Aeronautics and Space Administration. A88-53156# Hugh L. Dryden Flight Research Facility, Edwards, Calif. NAVY APPLICATION OF A STANDARD FATIGUE AND AN AIRBORNE SYSTEM FOR VORTEX FLOW VISUALIZATION ENGINE MONITORING SYSTEM ON THE F-18 HIGH-ALPHA RESEARCH VEHICLE ARlF DHANlDlNA (Northrop Corp., Electronics Div., Hawthorne, ROBERT E. CURRY (NASA, Flight Research Center, Edwards, CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, CA) and DAVID M. RICHWINE (PRC Systems Services, Edwards, 24th, Boston, MA, July 11-13, 1988. 13 p. refs CA) AIAA, NASA, and AFWAL, Conference on Sensors and (AIAA PAPER 88-3315) Measurement Techniques for Aeronautical Applications, Atlanta, A fatigue and engine monitoring system (FEMS) specified by GA, Sept. 7-9, 1988. 13 p. refs the Navy for implementation on the F-l4A+, F-14D, and A-6F (AIAA PAPER 88-4671) weapon systems is described. The FEMS consists of an airborne A flow visualization system for the F-18 high-alpha research data acquisition system (ADAS) and a data storage set. The way vehicle is described which allows direct observation of the in which the ADAS functions in these weapon systems is separated vortex flows over a wide range of flight conditions. The discussed. K.K. system consists of a smoke generator system, on-board photographic and video systems, and instrumentation. In the A88-53772# present concept, smoke is entrained into the low-pressure vortex DEVELOPMENT, ANALYSIS, AND FLIGHT TEST OF THE core, and vortice breakdown is indicated by a rapid diffusion of LOCKHEED AERONAUTICAL SYSTEM COMPANY HTTB HUD the smoke. The resulting pattern is observed using photographic M. E. HOLBROOK (Lockheed Aeronautical Systems Co., Marietta, and video images and is correlated with measured flight GA) AIAA, AHS, and ASEE, Aircraft Design, Systems and conditions. R.R. Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 5 p. (AIAA PAPER 88-451 1) A88-54725 A HUD suitable for a tactical airlifter with autonomous STOL DEVELOPMENT OF A MHZ RF LEAK DETECTOR TECHNIQUE capability, such as the High Technology Test Bed (HTTB) C-130 FOR AIRCRAFT HARDNESS SURVEILLANCE research aircraft, has been developed and tested aboard the HTTB. LOTHAR 0. HOEFT, TOM M. SALAS, JOSEPH S. HOFSTRA (BDM This process involved the selection of a baseline system, its Corp., Albuquerque, NM), .and WILLIAM D. PRATHER (USAF, analysis, the iterative definition of display design requirements, Weapons Laboratory, Kirtland AFB, NM) IN: IEEE 1988 the simulation of sections of the proposed flight station in an International Symposium on Electromagnetic Compatibility, Seattle, engineering simulator, engineering pilot analysis, the correction of WA, Aug. 2-4, 1988, Record. New York, Institute of Electrical and problems, and interfacing with actual hardware. O.C. Electronics Engineers, Inc., 1988, p. 21 0-217. refs A technique for electromagnetically exciting aircraft that A88-53826# produces surface magnetic- and electric-field distributions similar PRELIMINARY DEFINITION OF PRESSURE SENSING to those resulting from exposure to plane waves is presented. REQUIREMENTS FOR HYPERSONIC VEHICLES Surface magnetic fields in the range of 1 to 10 mA/m are easily R. JOHN HANSMAN, JR. and BRYAN H. KANG (MIT, Cambridge, produced for frequencies between 1 and 10 MHz. Measurement MA) AIAA, NASA, and AFWAL, Conference on Sensors and of the magnetic field at a prescribed distance from the outside Measurement Techniques for Aeronautical Applications, Atlanta, and inside surfaces of hardened apertures, such as window screens GA, Sept. 7-9, 1988. 10 p. Research supported by the Charles and gasketed doors, using a small loop sensor and a Stark Draper Laboratory, Inc. refs battery-operated field-strength meter allows the shielding (AIAA PAPER 88-4652) effectiveness of these hardening elements to be determined. When The air data and engine inlet control measurement requirements a current probe is substituted for the loop, this technique can

813 06 AIRCRAFT INSTRUMENTATION also be used to characterized conductive penetrations. This N88-28923# Management Consulting and Research, Inc., Falls technique has great potential as an aircraft hardness surveillance Church, Va. tool because it is simple to implement, quantitative and capable AIRCRAFT AVIONICS AND MISSILE SYSTEM INSTALLATION of not only characterizing each hardening element, but also finding COST STUDY. VOLUME 1: TECHNICAL REPORT AND the electromagnetic hot spots. I.E. APPENDICES A THROUGH E Final Report, Apr. 1987 - Feb. 1988 KIRSTEN M. PEHRSSON and GEORGE R. KREISEL 12 Feb. 1988 233 p N88-28919'# CK Consultants, Inc., Mariposa, Calif. (Contract N00600-84-D-4171) AVIONICS SYSTEM DESIGN FOR HIGH ENERGY FIELDS A (AD-A194605; MCR-TR-8711/12-1) Avail: NTlS HC A1 1/MF GUIDE FOR THE DESIGNER AND AIRWORTHINESS A01 CSCLO5C SPECIALIST Final Report This report documents a parametric cost model for aircraft ROGER A. MCCONNELL Jun. 1987 235 p (Contract NAS2-12448) avionics installations and modifications. Cost and technical data collected during a previous avionics installation cost study, as well (NASA-CR-181590; NAS 1.261181590; DOT/FAA/CT-87/19) as data collected from data sources identified during this effort Avail: NTlS HC A1 1/MF A01 CSCL 01 D were used to analyze costs of individual avionics black-box Because of the significant differences in transient susceptibility, modifications or installations into aircraft. The report details the the use of digital electronics in flight critical systems, and the methodology used to construct the data base and develop reduced shielding effects of composite materials, there is a definite to need to define pracitices which will minimize electromagnetic cost-estimating relationships (CERs). Details of CERs developed for non-recurring costs, recurring installation/modification kit costs, susceptibility, to investigate the operational environment, and to develop appropriate testing methods for flight critical systems. The labor costs, and manhours are provided, as well as the supporting data used in the analyses. The report is only available to authorized design practices which will lead to reduced electromagnetic susceptibility of avionics systems in high energy fields is described. US. Government personnel. GRA The levels of emission that can be anticipated from generic digital devices. It is assumed that as data processing equipment becomes an ever larger part of the avionics package, the construction N88-29365*# Arizona State Univ., Tempe. Dept. of Computer methods of the data processing industry will increasingly carry Science. over into aircraft. In Appendix 1 tentative revisions to RTCA AVIONIC EXPERT SYSTEMS DO-160B, Environmental Conditions and Test Procedures for FOROUZAN GOLSHANI /n NASA, Marshall Space Flight Center, Airborne Equipment, are presented. These revisions are intended Second Conference on Artificial Intelligence for Space Applications to safeguard flight critical systems from the effects of high energy p 123-129 Aug. 1988 Sponsored in part by Sperry Research electromagnetic fields. A very extensive and useful bibliography Trust Foundation on both electromagnetic compatibility and avionics issues is Avail: NTlS HC A99/MF E03 CSCL 01D included. Author At the heart of any intelligent flight control system, there is a knowledge based expert system. The efficiency of these knowledge bases is one of the major factors in the success of aviation and space control systems. In the future, the speed and the capabilities N88-28921# Crew Systems Consultants, Yellow Springs, Ohio. of the expert system and their underlying data base(s) will be the IMPROVEMENT OF HEAD-UP DISPLAY STANDARDS. limiting factors in the ability to build more accurate real time space VOLUME 2 EVALUATION OF HEAD-UP DISPLAYS TO controllers. A methodology is proposed for design and construction ENHANCE UNUSUAL ATTITUDE RECOVERY Final Report, 1 of such expert systems. It is noted that existing expert systems Oct. 1984 - 15 Jun. 1987 are inefficient (slow) in dealing with nontrivial real world situations RICHARD L. NEWMAN Sep. 1987 61 p that involve a vast collection of data. However, current data bases, (Contract F33615-85-C-3602) which are fast in handling large amounts of data, cannot carry (AD-A194601 ; TR-87-14; AFWAL-TR-87-3055-VOL-2) Avail: out intelligent tasks normally expected from an expert system. NTlS HC A04/MF A01 CSCL 25C The system presented provides the power of deduction (reasoning) Several variations of head-up display symbologies were along with the efficient mechanisms for management of large data evaluated in a fixed base simulator to study their effect on unusual bases. In the system, both straight forward evaluation procedures attitude recovery using head-up display data alone. The results and sophisticated inference mechanisms coexist. The design indicate that pitch scale compression, additional bank information, methodology is based on mathematics and logic, which ensures and slanted pitch ladder lines enhance recoveries from unusual the correctness of the final product. Author attitudes. Automatic deletion of the velocity vector symbol at high angles-of-attack also enhances recovery. Recommendations for GRA future head-up display symbologies are made. N88-29719# Technische Univ., Brunswick (West Germany). Inst. for Guidance and Control. FLIGHT TEST EQUIPMENT FOR THE ON-BOARD N88-28922# Crew Systems Consultants, Yellow Springs, Ohio. MEASUREMENT OF WIND TURBULENCE IMPROVEMENT OF HEAD-UP DISPLAY STANDARDS. G. SCHAENZER, M. SWOLINSKY, and P. VOERSMANN (Aerodata VOLUME 5: HEAD UP DISPLAY ILS (INSTRUMENT LANDING Flugmesstechnik G.m.b.H., Brunswick, West Germany ) /n AGARD, SYSTEM) ACCURACY FLIGHT TESTS Final Report, 1 Oct. The Flight of Flexible Aircraft in Turbulence: State-of-the-Art in 1984 - 15 Jun. 1987 the Description and Modelling of Atmospheric Turbulence 11 p RICHARD L. NEWMAN and RANDALL E. BAILEY Sep. 1987 Jun. 1988 45 P Avail: NTlS HC AO6/MF A01 (Contract F33615-85-C-3602; F33615-83-C-3603) The knowledge of the actual wind and turbulence situation (AD-A194602; TR-87-13; AFWAL-TR-87-3055-VOL-5) Avail: along the flight path of an aircraft is an important factor in the NTlS HC AO3/MF A01 CSCL 01 D area of meteorological and aeronautical research. Different flight An in-flight investigation of the effect of head-up display symbol test programs for the onboard implementation of offline and online accuracy has been conducted using a variable stability T-33 aircraft. wind and turbulence measuring systems are presented. The The results indicate that 100 to 200 ft lateral errors and 500 to theoretical principle of the determination of all three components 1500 ft longitudinal errors in locating a contact analog synthetic of the wind vector is stated. A summary of the installed sensors, runway did not cause difficulties for the evaluation pilots. There the data acquisition systems and computer equipment is presented was no apparent tendency for the subjects to follow HUD cues and the essential effects of sensor errors on the accuracy of and ignore real world cues. GRA wind determination are discussed. Author

814 07 AIRCRAFT PROPULSION AND POWER

I N88-29730# National Aeronautical Establishment, Ottawa Previously cited in issue 20, p. 3154, Accession no. A87-45161. (Ontario). Flight Research Lab. refs THE NAE ATMOSPHERIC RESEARCH AIRCRAFT (Contract F33615-8242-2255) J. I. MACPHERSON and S. W. BAILLIE ln AGARD, The Flight of Flexible Aircraft in Turbulence: State-of-the-Art in the Description A88-52684*# Purdue Univ., West Lafayette, Ind. 1 and Modelling of Atmospheric Turbulence 19 p Dec. 1987 CONTROL OF ROTOR AERODYNAMICALLY FORCED Avail: NTlS HC AO9/MF A01 VIBRATIONS BY SPLITTERS The Flight Research Laboratory of the NAE of Canada operates SANFORD FLEETER, DAVID A. TOPP (Purdue University, West a T-33 and a Twin Otter aircraft instrumented for atmospheric Lafayette, IN), and DANIEL HOYNIAK (NASA, Lewis Research research studies. The instrumentation in the aircraft is described Center, Cleveland, OH) (Structures, Structural Dynamics and with emphasis on the strapped down inertial Doppler system used Materials Conference, 27th, San Antonio, TX, May 19-21, 1986, to derive the mean and turbulent components of the atmospheric Technical Papers. Part 2, p. 77-88) Journal of Propulsion and motion. Example data from several research projects are presented Power (ISSN 0748-4658), vol. 4, Sept.-Oct. 1988, p. 445-451. to demonstrate the measurement and analysis capabilities of the Previously cited in issue 18, p. 2612, Accession no. A86-38892. aircraft and their data playback facilities. Author refs

N88-29797# Essex Corp., Alexandria, Va. A88-52698# USE OF COLOR CRTS (CATHODE RAY TUBES) IN AIRCRAFT VIABILITY RATING BY FUEL INDEXING METHOD COCKPIT A LITERATURE SEARCH, REVISION B Final Report P. P. S. SARMA, S. N. ACHARYA, E. K. SINHA (Indian Airlines, STEVEN L. HALE and HANNS J. BILLMAYER Apr. 1988 24 p Hyderabad, India), and U. P. SlNGH (Indian Airlines, Madras, (Contract DAAAl5-88-C-0005; DA PROJ. 1L1-62716-A-700) India) Aeronautical Society of India, Journal (ISSN 0001-9267), (AD-A195062; EFR-014-REV-E; HEL-TN-3-88-REV-E) Avail: VOI.39, NOV. 1987, p. 189-196. NTlS HC A02/MF A01 CSCL 09E This article suggests and demonstrates a method of quantifying A literature search was conducted to assess the utility and the net response of an aircraftlengine to a cumulated complexity feasibility of incorporating color cathode ray tubes (CRTs) in military of operational variables. This method makes use of the most aircraft cockpits and is presented in annotated bibliography format. sensitive operational input, the fuel, as the indexing medium. An The advantages and disadvantages of color CRTs are reviewed. aircraftlengine is rated as per fuel index for the purpose of It is concluded that the incorporation of color on aircraft CRTs assessment of comparative performance viabilities within a type will prove beneficial and that potential problems associated with or group. These ratings are categorized into (1) operational viability the use of color displays can be eliminated with proper display ratings and (2) overhaul viability ratings for the purpose of reviewing design and the advancement of technology. GRA and rectification action, which includes tracking down, prevention, and correction of defective procedures, systems, and/or N88-29800# Air Force Wright Aeronautical Labs., components. Author Wright-Patterson AFB, Ohio. A MULTIPROCESSOR AVIONICS SYSTEM FOR AN A88-53 102# UNMANNED RESEARCH VEHICLE Final Report, 1 Jan. 15 - ADVANCED TECHNOLOGY ENGINE SUPPORTABILITY Dec. 1987 - PRELIMINARY DESIGNER’S CHALLENGE DANIEL E. THOMPSON Mar. 1988 197 p JOHN J. CIOKAJLO and JAMES E. HARTSEL (General Electric (AD-A194806; AFWAL-TR-88-3003) Avail: NTlS HC AO9/MF Co., Evendale, OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion A01 CSCL 12F Conference, 24th, Boston, MA, July 11-13, 1988. 7 p. AFWAL/FIGL is developing a new Unmanned Research Vehicle (AIAA PAPER 88-2796) (URV) testbed system for low cost flight testing of advanced flight The US. military services have undertaken a cooperative control concepts. This new system will incorporate a program with private industry aimed at the integration of radically modular/reconfigurable airframe, will possess greater aerodynamic advanced engineering disciplines, including supportability, into capabilities, and will utilize an advanced avionics/control system future fighter aircraft propulsion systems having three times the allow embedded computation of flight test applications. to thrust/weight values typical of state-of-the-art engines. This effort, AFWAL/FIGL has utilized its in-house experience in multiprocessor systems technologies to develop a first phase prototype system which is scheduled to proceed over a period of 15 years, will grapple with the possibilities for supportability of novel materials comprised of multiple microprocessors and a parallel backplane used in engine structural components. O.C. bus. A multiprocessor software operating system and interprocessor communications protocol have been developed and tested. To demonstrate the capabilities of the system and the development A88-53103# of parallel software, an applications set of parallel software tasks TESTING OF THE 578-DX PROPFAN PROPULSION SYSTEM have been developed and demonstrated. The hardware and D. C. CHAPMAN (General Motors Corp., Allison Gas Turbine Div., software architecture, approach taken in the development, and Indianapolis, IN), J. GODSTON (United Technologies Corp., Pratt results achieved are described in this report. GRA and Whitney Group, East Hartford, CT), and D. E. SMITH (United Technologies, Corp., Hamilton Standard Div., Windsor Locks, CT) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, July 11-13, 1988. 11 p. 07 (AIAA PAPER 88-2804) In preparation for a flight test program, the 578-DX Propfan AIRCRAFT PROPULSION AND POWER Demonstrator Propulsion System has undergone comprehensive testing of such major components as the gearbox, the turbine Includes prime propulsion systems and systems components, e.g., power section, and the propulsion system mounts. Additional gas turbine engines and compressors; and on-board auxiliary power evaluations have been undertaken of the engine and propfan plants for aircraft. control systems, the lubrication and heat-rejection system, and interactions among major system components. Attention is given to the results obtained with both aluminum propeller blades and A88-52676# composite, spar-and-shell propfan blades. O.C. COMBUSTION-GENERATED TURBULENCE IN PRACTICAL COMBUSTORS A88-53 104# D. R. BALLAL (Dayton, University, OH) Journal of Propulsion UDF ENGINE/MD80 FLIGHT TEST PROGRAM and Power (ISSN 0748-4658), vol. 4, Sept.-Oct. 1988, p. 385-3913, HERBERT E. NICHOLS (General Electric Co., Cincinnati, OH)

815 07 AIRCRAFT PROPULSION AND POWER

AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 24th, MA) and E. M. GREITZER (MIT, Cambridge, MA) AIAA, ASME, Boston, MA, July 11-13, 1988. 14 p. SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, (AIAA PAPER 88-2805) July 11-13, 1988. 11 p. refs The fuel efficiency improvements demonstrated by the Unducted (AIAA PAPER 88-3001) Fan (UDF) engine during its flight trials as one of the two engines A similarity principle that facilitates the inference of exhaust of an MD80 airliner are comparable to preflight predictions; cruise systems' performance on the basis of model tests conducted with SFC levels of the order of 20-40 percent better than current uniform stagnation temperatures is presented and verified in light low-to-moderate bypass turbofans were obtained. UDF of calculations and comparisons with existing data. Potential demonstrator engine acoustics also met important noise emission applications encompass single-flow nozzles, forced mixers, exhaust goals, including an 82-dBA worst-seat cabin internal noise limit. jets, and ejector nozzles. It is shown that appropriately chosen When employing a 10-blade front rotor/E-blade rear rotor, the performance parameters will be similar for both hot flow and cold UDF met FAR 36 Part Ill community noise limits. O.C. flow model tests, as long as the initial Mach numbers and total pressures of the flowfield are simulated. O.C. A88-53111# DIRECT LIFT ENGINE FOR ADVANCED V/STOL TRANSPORT A88-53 136# ROBERT F. TAPE (Rolls-Royce, Inc., Atlanta, GA) and RAYMOND ATR PROPULSION SYSTEM DESIGN AND VEHICLE BULL (USAF, Wright Aeronautical Laboratories, Wright-Patterson INTEGRATION AFB, OH) AIAA. ASME, SAE, and ASEE, Joint Propulsion J. A. BOSSARD, K. L. CHRISTENSEN, and G. E. POTH (Aerojet Conference, 24th, Boston, MA, July 11-13, 1988. 9 p. Research Techsystems Co., Sacramento, CA) AIAA, ASME, SAE, and supported by USAF and Rolls-Royce, Inc. ASEE, Joint Propulsion Conference, 24th, Boston, MA, July 11-13, (AIAA PAPER 88-2890A) 1988. 10 p. A 'direct-lift' 40,000-lb thrust class engine concept has been (AIAA PAPER 88-3071) formulated for application in future advanced V/STOL military The air turboramjet (ATR) propulsion cycle and its prospective transport aircraft of approximately C-130 scaling. The design features are presently discussed with a view to ATR turbomechanical configurations considered achieve thrust:weight advantages in advanced missile powerplant applications, by values of the order of 33:l through the use of both advanced, comparison to conventional turbojets and rocket/ramjets. The low-density materials and innovative design features. A swiveling advantages encompass enhanced survivability through of the entire engine is judged best for thrust-vectoring with engines higher-than-turbojet speeds, coupled with the possibility of of this type, and large-radius bellmouth intakes with longitudinal lower-than-ramjet-speed initial operation, to obviate the ramjet's doors are the chosen installation design for three or more engines requisite booster rocket. The strong interactions between the ATR mounted in tandem. O.C. engine and airframe flight characteristics render the complete vehicle's design optimization iteration process critical. O.C. A88-53119# TOWARDS THE OPTIMUM DUCTED UHBR ENGINE A88-53137'# National Aeronautics and Space Administration. J. A. BORRADAILE (Rolls-Royce, PLC. London, England) AIAA, Lewis Research Center, Cleveland, Ohio. ASME, SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, A PRELIMINARY DESIGN STUDY OF SUPERSONIC MA, July 11-13, 1988. 7 p. THROUGH-FLOW FAN INLETS (AIAA PAPER 88-2954) PAUL J. BARNHART (NASA, Lewis Research Center, Cleveland; Next-generation ultrahigh bypass ratio (UHBR) ducted turbofans Sverdrup Technology, Inc., Middleburg Heights, OH) AIAA, ASME, with variable-pitch blading and downgeared fan rotors offer specific SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, fuel consumption improvements of the order of 10 percent over July 11-13, 1988. 11 p. refs comparable-output conventional turbofans, with a 50-percent (Contract NAS3-24105) increase in fan rotor diameter but only small changes in weight (AIAA PAPER 88-3075) and maintenance cost; high cruise speed and installation position From Mach 3.20 cruise propulsion systems, preliminary design advantages are also noted. Attention is given to an alternative studies for two supersonic through-flow fan primary inlets and a configuration with the same bypass ratio, where the engine-front single core inlet were undertaken. Method of characteristics and UHBR fan rotor is replaced by a contrarotating low pressure one-dimensional performance techniques were applied to assess turbine/ducted two-stage fan at the engine's aft end. O.C. the potential improvements supersonic through-flow fan technology has over more conventional systems. A fixed geometry supersonic A88-53121# through-flow fan primary inlet was found to have better performance FUTURE SUPERSONIC TRANSPORT NOISE - LESSONS FROM than a conventional inlet design on the basis of total pressure THE PAST recovery, air flow, aerodynamic drag and size and weight. M. J. T. SMITH, B. W. LOWRIE, J. R. BROOKS (Rolls-Royce, Author PLC, London, England), and K. W. BUSHELL (Rolls-Royce, Inc., Atlanta, GA) AIAA, ASME, SAE, and ASEE, Joint Propulsion A88-53151'# Vigyan Research Associates, Inc., Hampton, Va. Conference, 24th, Boston, MA, July 11-13, 1988. 16 p. refs CFD PREDICTION OF THE REACTING FLOW FIELD INSIDE A (AIAA PAPER 88-2989) SUBSCALE SCRAMJET COMBUSTOR While the small, carefully operated Concorde SST fleet has T. CHITSOMBOON (Vigyan Research Associates, Inc., Hampton, come to be accepted at important airports, next-generation SSTs VA), G. E. NORTHAM, R. C. ROGERS, and G. S. DlSKlN (NASA, will be larger than Concorde and must therefore enlist advanced Langley Research Center, Hampton, VA) AIAA, ASME, SAE, techniques to comply with FAR Part 36, Stage 3. This entails the and ASEE, Joint Propulsion Conference, 24th. Boston, MA, July use of an engine cycle which, during takeoff, is equivalent to a 11-13, 1988. 7 p. high bypass ratio turbofan with a mean exhaust velocity no greater (Contract NASI-17919) than 400 m/sec. Such variable-cycle engines, whether for Mach (AIAA PAPER 88-3259) 2 or 3 cruise, are technically possible but difficult to develop. A three-dimensional, Reynolds-averaged Navier-Stokes CFD Variable engine cycle is further entailed by overland flight code has been used to calculate the reacting flowfield inside a requirements, which require subsonic flight to prevent sonic boom hydrogen-fueled, subscale scramjet combustor. Pilot fuel was overpressures. O.C. injected transversely upstream of the combustor and the primary fuel was injected transversely downstream of a backward facing A88-53122# step. A finite rate combustion model with two-step kinetics was A USEFUL SIMILARITY PRINCIPLE FOR JET ENGINE used. The CFD code used the explicit MacCormack algorithm with EXHAUST SYSTEM PERFORMANCE point-implicit treatment of the chemistry source terms. Turbulent W. M. PRESZ, JR. (Western New England College, Springfield, mixing of the jets with the airstream was simulated by a simple

816 07 AIRCRAFT PROPULSION AND POWER mixing length scheme, whereas near wall turbulence was accounted critical combustor and turbine elements. Toward these ends, efforts for by the Baldwin-Lomax model. Computed results were compared were undertaken in instrumentation, combustion, turbine heat with experimental wall pressure measurements. Author transfer, structural analysis, fatiguelfracture, and surface protection. Attention is presently given to the organization of HOST activities A88-53167# and their specific subject matter. O.C. DIMENSIONING OF TURBINE BLADES FOR FATIGUE AND CREEP A88-54140'# National Aeronautics and Space Administration. 6. DAMBRINE and J. P. MASCARELL (SNECMA, Moissy-Cramayel, Lewis Research Center, Cleveland, Ohio. France) La Recherche Aerospatiale (English Edition) (ISSN ASSESSMENT, DEVELOPMENT, AND APPLICATION OF 0379-38OX), no. 1, 1988, p. 35-45. refs COMBUSTOR AEROTHERMAL MODELS Improving the performance of aircraft engines entails raising J. D. HOLDEMAN (NASA, Lewis Research Center, Cleveland, OH), the gas temperature at the turbine intake. This has led SNECMA H. C. MONGIA (General Motors Corp., Indianapolis, IN), and E. J. to improve cooling techniques, mechanical computation methods, MULARZ (NASA, Lewis Research Center; U.S. Army, Propulsion lifetime prediction methods and the materials themselves. This Directorate, Cleveland, OH) IN: Toward improved durability in article presents the dimensioning problems, and in particular the advanced aircraft engine hot sections; Proceedings of the use of the ONERA method for determining the lifetime of turbine Thirty-third ASME International Gas Turbine and Aeroengine blades. Author Congress and Exposition, Amsterdam, Netherlands, June 5-9, 1988. New York, American Society of Mechanical Engineers, 1988, p. A88-53774# 23-37. Previously announced in STAR as NEE-1 9469. refs THE RTM322 ENGINE IN THE S-70C HELICOPTER The gas turbine combustion system design and development PAUL E. SCEARS and PETER SEWELL (Rolls-Royce, PLC, effort is an engineering exercise to obtain an acceptable solution Leavesden, England) AIAA, AHS, and ASEE, Aircraft Design, to the conflicting design trade-offs between combustion efficiency, Systems and Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 9 gaseous emissions, smoke, ignition, restart, lean blowout, burner P. exit temperature quality, structural durability, and life cycle cost. (AIAA PAPER 88-4576) For many years, these combustor design trade-offs have been An account is given of the design features and S-70C carried out with the help of fundamental reasoning and extensive helicopter-based developmental flight testing status of the 2000-hp component and bench testing, backed by empirical and experience class RTM322 turboshaft engine, which is a candidate for future correlations. Recent advances in the capability of computational incorporation into not only production S-70s but also H-60, EHlO1, fluid dynamcis codes have led to their application to complex 3-D and "90 helicopters; a power growth potential of the order of flows such as those in the gas turbine combustor. A number of 3000 hp is projected for the engine. Attention is given to installation, U.S. Government and industry sponsored programs have made control, and enginelairframe dynamic characteristics, as well as significant contributions to the formulation, development, and ground and flight test results. The digital control system used will verification of an analytical combustor design methodology which significantly ease the engine's integration into series production will better define the aerothermal loads in a combustor, and be a aircraft. O.C. valuable tool for design of future combustion systems. The contributions made by NASA Hot Section Technology (HOST) A88-54137* National Aeronautics and Space Administration. sponsored Aerothermal Modeling and supporting programs are Lewis Research Center, Cleveland, Ohio. described. Author TOWARD IMPROVED DURABILITY IN ADVANCED AIRCRAFT ENGINE HOT SECTIONS; PROCEEDINGS OF THE A8844141 '# National Aeronautics and Space Administration. THIRTY-THIRD ASME INTERNATIONAL GAS TURBINE AND Lewis Research Center, Cleveland, Ohio. AEROENGINE CONGRESS AND EXPOSITION, AMSTERDAM, REVIEW AND ASSESSMENT OF THE DATABASE AND NETHERLANDS, JUNE 5-9, 1988 NUMERICAL MODELING FOR TURBINE HEAT TRANSFER DANIEL E. SOKOLOWSKI, ED. (NASA, Lewis Research Center, H. J. GLADDEN and R. J. SIMONEAU (NASA, Lewis Research Cleveland, OH) Congress and Exposition sponsored by ASME. Center, Cleveland, OH) IN: Toward improved durability in advanced New York, American Society of Mechanical Engineers, 1988, 128 aircraft engine hot sections; Proceedings of the Thirty-third ASME p. For individual items see A88-54138 to A88-54146. International Gas Turbine and Aeroengine Congress and Exposition, The present conference on durability improvement methods Amsterdam, Netherlands, June 5-9, 1988. New York, American for advanced aircraft gas turbine hot-section components discusses Society of Mechanical Engineers, 1988, p. 39-55. refs NASA's 'HOST' project, advanced high-temperature The objectives of the HOST Turbine Heat Transfer subproject instrumentation for hot-section research, the development and were to obtain a better understanding of the physics of the application of combustor aerothermal models, and the evaluation aerothermodynamic phenomena and to assess and improve the of a data base and numerical model for turbine heat transfer. analytical methods used to predict the flow and heat transfer in Also discussed are structural analysis methods for gas turbine hot high-temperature gas turbines. At the time the HOST project was section components, fatigue life-prediction modeling for turbine hot initiated, an across-the-board improvement in turbine design section materials, and the service life modeling of thermal barrier technology was needed. A building-block approach was utilized coatings for aircraft gas turbine engines. O.C. and the research ranged from the study of fundamental phenomena and modeling to experiments in simulated real engine environments. A88-54138'# National Aeronautics and Space Administration. Experimental research accounted for approximately 75 percent of Lewis Research Center, Cleveland, Ohio. the funding while the analytical efforts were approximately 25 NASA HOST PROJECT OVERVIEW percent. A healthy government/industry/university partnership, with D. E. SOKOLOWSKI (NASA, Lewis Research Center, Cleveland, industry providing almost half of the research, was created to OH) IN: Toward improved durability in advanced aircraft engine advance the turbine heat transfer design technology base. hot sections; Proceedings of the Thirty-third ASME International Author Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 5-9, 1988. New York, American Society of A88-54 143# Mechanical Engineers, 1988, p. 1-4. refs STRUCTURAL ANALYSIS APPLICATIONS NASA's Hot Section Technology, or 'HOST', program has R. L. MCKNIGHT (General Electric Co., Aircraft Engine Business developed improved analytical models for the aerothermal Group, Cincinnati, OH) IN: Toward improved durability in advanced environment, thermomechanical loading, material behavior, aircraft engine hot sections; Proceedings of the Thirty-third ASME structural response, and service life of aircraft gas turbine engines' International Gas Turbine and Aeroengine Congress and Exposition, hot section components. These models, in conjunction with Amsterdam, Netherlands, June 5-9, 1988. New York, American sophisticated computer codes, can be used in design analyses of Society of Mechanical Engineers, 1988, p. 83-95. refs

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An account is given of the application of computer codes for The propulsion system simulation described here includes the the efficient conduct of three-dimensional inelastic analyses to following major components: the digital models and data monitor, aircraft gas turbine combustor, turbine blade, and turbine stator an electronic verifier unit, a control data acquisition system, and vane components. The synergetic consequences of the program’s the actual FADEC, which can be either a breadboard or an engine activities are illustrated by an evaluation of the computer analyses mounted unit. It is noted that integrated flight and propulsion control of thermal barrier coatings and of the Space Shuttle Main Engine’s simulators will have an increasing impact on the design process, High Pressure Fuel Turbopump turbine blading. This software, in support of early concept evaluations, system integration tests, flight conjunction with state-of-the-art supercomputers, can significantly clearance, and flight test support. V.L. reduce design-task burdens. O.C. A88-54170# A88-54146’# National Aeronautics and Space Administration. A DETAILED CHARACTERIZATION OF THE VELOCITY AND Lewis Research Center, Cleveland, Ohio. THERMAL FIELDS IN A MODEL CAN COMBUSTOR WITH VIEWS ON THE IMPACT OF HOST WALL JET INJECTION J. B. ESGAR (NASA, Lewis Research Center; Sverdrup Technology, C. D. CAMERON, J. BROUWER, C. P. WOOD, and G. S. Inc., Cleveland, OH) and D. E. SOKOLOWSKI (NASA, Lewis SAMUELSEN (California, University, Irvine) ASME, Gas Turbine Research Center, Cleveland, OH) IN: Toward improved durability and Aeroengine Congress and Exposition, Amsterdam, in advanced aircraft engine hot sections; Proceedings of the Netherlands, June 6-9, 1988. 8 p. refs Thirty-third ASME International Gas Turbine and Aeroengine (Contract FO8635-83-C-0052; NO0140-83-C-9151) Congress and Exposition, Amsterdam, Netherlands, June 5-9, 1988. (ASME PAPER 88-GT-26) New York, American Society of Mechanical Engineers, 1988, p. This work represents a first step in the establishment of a 117-1 23. data base to study the interaction and influence of liquid fuel The Hot Section Technology (HOST) Project, which was initiated injection, wall jet interaction, and dome geometry on the fuel air by NASA Lewis Research Center in 1980 and concluded in 1987, mixing process in a flowfield representative of a practical was aimed at improving advanced aircraft engine hot section combustor. In particular, the aerodynamic and thermal fields of a durability through better technical understanding and more accurate model gas turbine combustor are characterized via detailed spatial design analysis capability. The project was a multidisciplinary, maps of velocity and temperature. Measurements are performed multiorganizational, focused research effort that involved 21 at an overall equivalence ratio of 0.3 with a petroleum JP-4 fuel. organizations and 70 research and technology activities and The results reveal that the flowfield characteristics are significantly generated approximately 250 research reports. No major hardware altered in the presence of reaction. Strong on-axis backmixing in was developed. To evaluate whether HOST had a significant impact the dome region, present in the isothermal flow, is dissipated in on the overall aircraft engine industry in the development of new the case of reaction. The thermal field exhibits the primary, engines, interviews were conducted with 41 participants in the secondary and dilution zone progression of temperatures project to obtain their views. The summarized results of these characteristic of practical gas turbine combustors. A parametric interviews are presented. Author variation on atomizing air reveals a substantial sensitivity of the mixing in this flow to nozzle performance and spray symmetry. A88-54153# Author MULTIVARIABLE TURBOFAN ENGINE CONTROL FOR FULL FLIGHT ENVELOPE OPERATION A88-54224# JOHN A. POLLEY, SHRIDER ADIBHATLA, and PAUL J. HOFFMAN DESIGN OPTIMIZATION OF GAS TURBINE BLADES WITH (General Electric Co., Cincinnati, OH) ASME, Gas Turbine and GEOMETRY AND NATURAL FREQUENCY CONSTRAINTS Aeroengine Congress and Exposition, Amsterdam, Netherlands, TSU-CHIEN CHEU (Textron, Inc., Avco Lycoming Textron Div., June 6-9, 1988. 10 p. refs Stratford, CT), BO PING WANG (Texas, University, Arlington), and (ASME PAPER 88-GT-6) TING-YU CHEN (National Chunghsing University, Taichung, The design of a full flight envelope nonlinear multivariable Republic of China) ASME, Gas Turbine and Aeroengine Congress controller is described for a single-bypass variable-cycle jet engine. and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 6 p. The nonlinear controller is obtained by using appropriate engine refs corrected parameters to schedule multivariable linear compensator (ASME PAPER 88-GT-105) gains designed at selected operating points of the flight envelope. In this paper an automated procedure is presented to obtain The KQ (K-matrix compensator, Q-desired response) multivariable the minimum weight design of gas turbine blades with geometry control design technique is used to design the compensators using and multiple natural frequency constraints. The objective is linear state-space models obtained from a detailed nonlinear achieved using a combined finite element-sequential linear aerothermo model. The controller is implemented in the detailed programming, FEM-SLP technique. Thickness of selected finite nonlinear aerothermo model. The paper decribes an example KQ elements are used as design variables. Geometric constraints are compensator design, the corrected-parameter gain scheduling imposed on the thickness variations such that the optimal design approach and controller performance validation by nonlinear has smooth aerodynamic shape. Based on the natural frequencies simulation. Computer simulations for sea-level static, and and mode shapes obtained from finite element analysis an assumed supersonic operating points are included to show the closed-loop mode reanalysis technique is used to provide the approximate transient performance in the presence of an acceleration fuel derivatives of weight and constraints with respect to design schedule. Author variables for sequential linear programming. The results from SLP provide the initial design for the next FEM-SLP process. An example A88-54 168# is presented to illustrate the interactive system developed for the REAL TIME SIMULATORS FOR USE IN DESIGN OF optimization procedure. Author INTEGRATED FLIGHT AND PROPULSION CONTROL SYSTEMS A88-54239# WILLIAM J. DAVIES, CHARLIE L. JONES, and ROBERT A. AN EMISSIONS DATABASE FOR U.S. NAVY AND AIR FORCE NOONAN (United Technologies Corp., Pratt and Whitney, West AIRCRAFT ENGINES Palm Beach, FL) ASME, Gas Turbine and Aeroengine Congress HENRY B. FAULKNER, MELVIN PLATT (Northern Research and and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 5 p. Engineering Corp.. Woburn, MA), ANTHONY F. KLARMAN (U.S. (ASME PAPER 88-GT-24) Naval Air Propulsion Test Center, Trenton, NJ), and MARK D. New testing requirements necessitated by the integration of SMITH (USAF, Engineering and Services Center, Tyndall AFB, Full Authority Digital Electronic Controls (FADEC) with the flight FL) ASME, Gas Turbine and Aeroengine Congress and Exposition, control are examined with emphasis on the need for the use of Amsterdam, Netherlands, June 6-9, 1988. 7 p. refs real time integrated flight and propulsion control test benches. (ASME PAPER 88-GT-129)

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This paper presents a data base on the pollutant emission by A88-54301# the U.S. Navy and Air Force aircraft engines collected over the ANALYSIS OF EFFICIENCY SENSITIVITY ASSOCIATED WITH , last twenty years. The resulting data base contains all of the TIP CLEARANCE IN AXIAL FLOW COMPRESSORS ' available emission data as well as background information on each IAN N. MOYLE (US. Naval Postgraduate School, Monterey, CA) engine model tested for emission and the conditions for each ASME, Gas Turbine and Aeroengine Congress and Exposition, test. In addition, all of the unclassified operational engine models Amsterdam, Netherlands, June 6-9, 1988. 7 p. Navy-supported of the US. Navy and Air Force are listed, whether or not emission research. refs data are available, and, for models for which emission data are (ASME PAPER 88-GT-216) 1 not available, a similar engine model whose data can be reasonably The effects of tip clearance changes on efficiency in axial substituted is identified. IS. compressors are typically established experimentally. The ratio of change of efficiency with change of clearance gap varies A88-54247# significantly for different compressors in the published data. An DESIGN AND TEST OF NON-ROTATING CERAMIC GAS analysis of this sensitivity range in terms of the blade and stage TURBINE COMPONENTS design parameters was initiated. The analysis revealed that the ANDRE L. NEUBURGER and GILLES CARRIER (Pratt and Whitney sensitivity range largely resulted from a derivation at constant flow Canada, Longueuil) ASME, Gas Turbine and Aeroengine Congress of the efficiency decrement. It was also found that a generalized and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. loss method of generating the sensitivities produced a much refs improved correlation of the change in efficiency with change in (ASME PAPER 88-GT-146) clearance over a variety of machines, configurations and speeds. This paper deals with elements of an on-going ceramics Author research and development program at a major manufacturer of turbine engines for general aviation and commuter aircraft. The A88-54304# program comprises design and test of non-rotating, ceramic FLOW MEASUREMENTS IN ROTATING STALL IN A GAS components for two widely used turboprop engines. The design, TURBINE ENGINE COMPRESSOR analysis and test of three components are discussed: a simple R. C. BEST, J. G. C. LAFLAMME, and W. C. MOFFATT (Royal ceramic turbine shroud, a metal and ceramic turbine shroud, and Military College of Canada, Kingston) ASME, Gas Turbine and an all-ceramic nozzle vane assembly. Fabrication and assembly Aeroengine Congress and Exposition, Amsterdam, Netherlands, of these components are described. A discussion of non-destructive June 6-9, 1988. 7 p. DND-supported research. refs evaluation and component prooftesting includes a prooftest strategy (ASME PAPER 88-GT-219) that seeks to retain the stronger half of a sample of specimens. Hot sensor anemometry has been used to make detailed flow Candidate ceramics, silicon carbide and silicon nitride, are assessed measurements on the first four stages of a 10-stage compressor and chosen as the shroud and vane materials. The paper also operating as part of a turbojet engine mounted on a test stand. includes assessment of improvements in fuel efficiency, specific Results for a number of axial and tangential locations show clear power and operating cost, some based on test results and some evidence of rotating stall in the front stages during the part-speed on analysis. Author operation of the engine. The stall cell configuration and rotating speed as well as details of flow speed and angle at hub, mid and A88-54249# tip radii are discussed. It is concluded that, although rotating stall A UK PERSPECTIVE ON ENGINE HEALTH MONITORING has its origins in flow instability, it is a highly reproducible (EHM) SYSTEMS FOR FUTURE TECHNOLOGY MILITARY phenomenon. V.L. ENGINES N. A. BAIRSTO (RAF, London, England) ASME, Gas Turbine A88-54306# and Aeroengine Congress and Exposition, Amsterdam, TRANSIENT PERFORMANCE TRENDING FOR A TURBOFAN Netherlands, June 6-9, 1988. 6 p. ENGINE (ASME PAPER 88-GT-148) J. R. HENRY and W. C. MOFFATT (Royal Military College of The first part of the paper deals with the background to the Canada, Kingston) ASME, Gas Turbine and Aeroengine Congress UK experience in EHM. The programs that have led to the UK's and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 11 p. experience are given and some lessons learned are outlined which DND-supported research. refs will be applied to Engine Health Monitoring (EHM) in future engines. (ASME PAPER 88-GT-222) The UK policy for the fleetwide fit of EHM equipment is stated. In The feasibility of using engine data acquired during takeoff to the second part, the application of EHM to advanced technology trend the performance of a modern turbofan engine (GE-F404) is engines is examined from a personal viewpoint. Future engines investigated. Representative engine data from operational aircraft will include materials and aerothermal cycles that are in the are used to estimate various trending parameters, with a data research and development field. The impact of a structured capture window used to minimize the scatter of nominal engine approach to durability, the anticipated reduction of engine spares performance. The factors influencing the repeatability of takeoff holdings and the requirement to improve flight safety and enhance data, such as throttle rate, variable geometry, and instrumentation engine availability are advanced as arguments in support of the effects, are discussed in detail. The trending of transient development of EHM techniques alongside the development of performance data is shown to be a viable means of detecting future engines. Author certain engine faults, and recommendations concerning the implementation of such a program for the F404 engine are made. A88-54295# V.L. FAULT DIAGNOSIS OF GAS TURBINE ENGINES FROM TRANSIENT DATA A88-543 12# G. L. MERRINGTON (Department of Defence, Aeronautical PRECISION ERROR IN A TURBOFAN ENGINE MONITORING Research Laboratories, Melbourne, Australia) ASME, Gas Turbine SYSTEM and Aeroengine Congress and Exposition, Amsterdam, J. R. HENRY and W. C. MOFFATT (Royal Military College of Netherlands, June 6-9, 1988. 7 p. refs Canada, Kingston) ASME, Gas Turbine and Aeroengine Congress (ASME PAPER 88-GT-209) and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 7 p. The desirability of being able to extract relevant fault diagnostic DND-supported research. refs information from transient gas turbine data records is discussed. (ASME PAPER 88-GT-229) A method is outlined for estimating the effects of unmeasured Precision error in the turbofan engine monitoring system of a fault parameters from input/output measurements. The resultant modern fighter, based on steady state and transient data records, sensitivity of the technique depends on the sampling rate and the is examined. The general design and operation of the engine measurement noise. Author. monitoring system are described, and a method is presented for

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estimating the overall system precision. It is found that precision Garrett Auxiliary Power Div., Phoenix, AZ) ASME, Gas Turbine errors in sensing are much lower than those in the conditioning and Aeroengine Congress and Exposition, Amsterdam, and processing of engine data. It is further shown that possible Netherlands, June 6-9, 1988. 12 p. improvements in the monitoring system are constrained by data (ASME PAPER 88-GT-243) sampling rates and digital word formats. V.L. The Advanced Gas Turbine development program designated 'AGT101' exposed ceramic gas turbine components to over 250 A88-54317# hours of operation, including 85 hours of engine hot section tests A METHANOL/OXYGEN BURNING COMBUSTOR FOR AN at over 2200 F, before its completion in June 1987. The ceramic AIRCRAFT AUXILIARY EMERGENCY POWER UNIT gas turbine component development effort then proceeded in E. CARR and H. TODD (Lucas Aerospace, Ltd., Burnley, August 1987 with the 5-year Advanced Turbine Technology England) ASME, Gas Turbine and Aeroengine Congress and Applications Project, which will improve ceramic component Exposition, Amsterdam, Netherlands, June 6-9, 1988. 4 p. fabrication processes as well as analysis, testing, and verification (ASME PAPER 88-GT-236) procedures. Ceramic component reliability and durability will also High altitude facility performance test results are presented for be tested in engine operating environments. O.C. a 300-kW output oxygen-oxidant combustor, applicable to emergency aircraft electrical or hydraulic power turbine use, that A88-54326# is cooled by the methanol it employs as fuel. It is found that the FLOW COMPUTATION AND BLADE CASCADE DESIGN IN combustor lights reliably at 20 km simulated altitude with -40 C TURBOPUMP TURBINES oxygen temperature, and possesses a mechanical service life that GILLES BILLONNET (ONERA, Chatillon-sous-Bagneux, France) is in excess of prospective aircraft applications requirements. ASME, Gas Turbine and Aeroengine Congress and Exposition, O.C. Amsterdam, Netherlands, June 6-9, 1988. 10 p. refs (ASME PAPER 88-GT-248) A88-54319# The aerodynamic blade cascade design of a two stage axial LINEAR STATE VARIABLE DYNAMIC MODEL AND supersonic turbine is investigated by using an inviscid flow ESTIMATOR DESIGN FOR ALLISON T406 GAS TURBINE computation method. The flow inside such kind of turbine is ENGINE characterized by high inlet Mach numbers and large deflection S. VITTAL RAO, D. MOELLENHOFF (Missouri-Rolla, University, angles as well as supersonic flow matching between stator and Rolla), and J. A. JAEGER (General Motors Corp., Allison Gas rotor. Most of the computed flow configurations give strong shock Turbines Div., Indianapolis, IN) ASME, Gas Turbine and waves in the blade-to-blade channels, so that boundary-layer Aeroengine Congress and Exposition, Amsterdam, Netherlands, separation phenomena are anticipated. The inverse mode June 6-9. 1988. 7 p. Research supported by General Motors calculation is applied in order to avoid adverse pressure gradients Corp. on the walls. The semiinverse method allows to get the geometry (ASME PAPER 88-GT-239) of a blade profile corresponding to a given pressure distribution This paper describes a procedure for developing a State on the suction side and the pressure side, the solidity being fixed. Variable Model for the Allison T406 gas turbine engine. This linear A new design of the turbine blade cascade is then considered in model is useful for designing controllers using modern control order to achieve the desired velocity diagram. Author techniques. The engine and V-22 rotor system is modeled around an operating point by using four state variables and one input variable. For a given power setting, it is observed that two linear A88-54333# models are sufficient to represent the engine dynamics over the RECENT ADVANCES IN ENGINE HEALTH MANAGEMENT entire flight envelope. A relationship between surge margin and KENNETH PIPE and CELIA FISHER (Stewart Hughes, Ltd., the state variables is also developed. It is demonstrated that these Southampton, England) ASME, Gas Turbine and Aeroengine linear models are useful in designing an estimator for Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. accommodating hard sensor failures. Author 6 p. Research supported by the Ministry of Defence Procurement Executive. (ASME PAPER 88-GT-257) A8844321# New measurement capabilities developed in the last five years NUMERICAL CORRELATION OF GAS TURBINE COMBUSTOR have greatly enhanced the ability of monitoring systems to produce IGNITION acceptable engine distress and maintenance information to pilots. F. P. LEE, T. KOBLISH (Textron, Inc., Textron-Turbo Components, The more recent advances are particularly useful for military and Walled Lake, and N. MARCHIONNA (Textron, Inc., Stratford, MI), helicopter engines. This paper describes three new techniques, CT) ASME, Gas Turbine and Aeroengine Congress and Exposition, with descriptions of their application. These include direct Amsterdam, Netherlands, June 6-9, 1988. 6 p. refs aerodynamic thrust measurement, gas path distress analysis and (ASME PAPER 88-GT-242) analysis of the dynamic behavior of gas turbines. The paper In single can combustor ignition tests, different results were concludes by suggesting the impact of these techniques on systems obtained for pressure atomizing and airblast atomizing fuel injectors design for future engines. Author as well as for various ignition locations. In order to understand the effect of fuel spray characteristics and ignition locations on gas turbine combustion ignition characteristics, a computer A88-54335# simulation of fuel droplet ignition at engine starting flow conditions A COMPARISON OF ENGINE DESIGN LIFE OPTIMIZATION has been conducted. An ignition model for evaporating fuel droplets RESULTS USING DETERMINISTIC AND PROBABILISTIC LIFE was incorporated with the numerical droplet tracking scheme in PREDICTION TECHNIQUES the computational flow field, which included a simulated ignition EDWARD J. REED (Pratt and Whitney, West Palm Beach, FL) point source. A large number of various size droplets were ASME, Gas Turbine and Aeroengine Congress and Exposition, computed for their trajectories and ignition reactions. A statistical Amsterdam, Netherlands, June 6-9, 1988. 5 p. data base was established to calculate the ignition probability of (ASME PAPER 88-GT-259) droplets in terms of number and mass fraction. A correlation This paper documents a study conducted to determine the between predicted ignition probability trends and experimental optimum design life of a turbine disk. The study traded weight ignition data for two different injector/ignitor configurations was against maintenance with the optimum being determined through demonstrated. Author a life cycle cost analysis. Both deterministic and probabilistic life prediction techniques were employed to establish maintenance A88-54322# frequency and cost. Comparing probabilistic with deterministic life AGTlOl/ATTAP CERAMIC TECHNOLOGY DEVELOPMENT optimization results was a major objective of this study. Both life G. L. BOYD and D. M. KREINER (Allied-Signal Aerospace Co., prediction techniques resulted in the same optimum life conclusion

820 07 AIRCRAFT PROPULSION AND POWER

with the probabilistic analysis giving additional insight into the rated at 6150 shp which is being developed to power the decision drivers. Author multiservice V-22 Osprey tilt rotor aircraft. The V-22 is a vertical takeoff and landing (VTOL) aircraft. To achieve VTOL the engine ’ A88-54337# nacelles, located at the tip of each wing, are tilted upward placing STRUCTURAL DESIGN AND ITS IMPROVEMENTS THROUGH the axis of rotation of the prop-rotor and engine in a vertical THE DEVELOPMENT OF THE XF3-30 ENGINE orientation. Once airborne, the nacelles are tilted forward such HIDEKATSU KlKUCHl (Japan Defence Agency, Tokyo) and that the axis of rotation is horizontal for the ’airplane’ mode. The 1 KlYOSHl ISH11 (Ishikawajima-Harima Heavy Industries Co., Ltd., requirement to operate both horizontally and vertically places Tokyo, Japan) ASME, Gas Turbine and Aeroengine Congress additional requirements on the engine lubrication system. The I and Exposition, Amsterdam, Netherlands, June 6-9. 1988. 7 p. sumps must be scavenged over this wide range of orientations. A (ASME PAPER 88-GT-261) unique approach, patented by General Motors, was used to The XF3-30 engine has been successfully completed its scavenge the oil from each of the three sumps. This scavenge Qualification Test at March 1986 and the production has started system is lighter and lower in cost than conventional approaches. as the powerplant for Japan Self Defence Force’s intermediate The test facilities and development are discussed in this paper. trainer T-4. The first flight of the T-4 powered by two XF3-30 Author engine was made on July 29, 1985. More than 500 test flights have been made in these two years and engine flight time has accumulated to over 1500 hours. Strict structural integrity A88-54369# requirements have been imposed on this XF3-30 engine to meet XG40 - ADVANCED COMBAT ENGINE TECHNOLOGY the MIL-E-5007D specification. This paper describes the structural DEMONSTRATOR PROGRAMME features of this engine and some structural problems encountered A. F. JARVIS (Rolls-Royce, PLC, Bristol, England) ASME, Gas through the development. The improvements for these Turbine and Aeroengine Congress and Exposition, Amsterdam, development problems are covered. Author Netherlands, June 6-9, 1988. 12 p. Research supported by Ministry of Defence Procurement Executive. A88-54346# (ASME PAPER 88-GT-300) RESPONSE OF LARGE TURBOFAN AND TURBOJET ENGINES The XG40 R&D program was instituted in 1982 in order to TO A SHORT-DURATION OVERPRESSURE produce gas turbine engine technologies that would be applicable M. G. DUNN (Calspan Advanced Technology Center, Buffalo, NY), to 1990s fighter aircraft, while lending themselves to broader R. M. ADAMS, and V. S. OXFORD (DNA, Washington, DC) ASME, application in civilian engine programs. The performance goals of Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, the XG40 encompassed the achievement of a 1O:l thrust:weight Netherlands, June 6-9, 1988. 9 p. refs ratio with good dry thrust SFC, as well as stringent operating (Contract DNA001-83-C-0182) cost, reliability, and durability requirements. Direct fighter aircraft (ASME PAPER 88-GT-273) applications of this engine are the European Fighter Aircraft and A high-thrust, low bypass ratio turbofan and a high-thrust turbojet future, reengined Tornados. Attention is given to the design features were subjected to ground tests to ascertain the influence of thrust of the fan, high-pressure compressor, combustion chamber, high- settling and overpressure level on operating characteristics. The and low-pressure turbines, and engine control systems. O.C. results obtained indicate that, while overpressure has little influence on either high-pressure compressor speed or exhaust gas total pressure, the magnitude of the overpressure has a pronounced A88-54370# influence on turbine exhaust total pressure and on the inlet casing DESIGN ASPECTS OF RECENT DEVELOPMENTS IN and diffuser casing radial displacements. The turbojet’s turbine ROLLS-ROYCE RB211-524 POWERPLANTS casing was significantly affected by the overpressure, while the R. J. PARKES (Rolls-Royce, PLC, Derby, England) ASME, Gas turbofan’s casing was relatively insensitive. O.C. Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 10 p. A88-54363# (ASME PAPER 88-GT-301) CAUSES FOR TURBOMACHINERY PERFORMANCE This paper describes recent design changes in the RB211-524 DETERIORATION powerplant. In response to the market requirement for a wide W. TABAKOFF (Cincinnati, University, OH) ASME, Gas Turbine bodied aircraft to make journeys of increased range, the specific and Aeroengine Congress and Exposition, Amsterdam, fuel consumption of the latest -524 engine has been improved by Netherlands, June 6-9, 1988. 6 p. refs 14 percent, compared with initial versions. The potential of the (Contract DAAG29-82-K-0029) three shaft concept has been coupled with the latest aerodynamic (ASME PAPER 88-GT-294) technology to produce over 25 percent more thrust at essentially Experiments have been carried out on a two-stage gas turbine the same engine size. This increased thrust has been achieved with blunt leading edge blades and on a single-stage axial flow while meeting the latest noise and gaseous emissions regulations, compressor to investigate the effect of particulates and erosion and while achieving continuing improvements in engine reliability. on performance deterioration. It is found that particle concentrations Electronic engine control has been introduced to provide improved change the pressure distribution along the turbine blades and aircraft operation and maintenance. A. decrease the performance of the turbine. The degree of performance deterioration increases with particle concentration and diameter. The compressor rig experiments indicate a significant A88-54371# reduction in engine efficiency due to erosion damage. The DEVELOPING THE ROLLS-ROYCE TAY performance deterioration is mainly due to changes in the blade N. J. WILSON (Rolls-Royce, PLC, East Kilbride, Scotland) ASME, leading and trailing edges, tip leakage, surface roughness, and Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, changes in pressure distribution. V.L. Netherlands, June 6-9, 1988. 13 p. (ASME PAPER 88-GT-302) A88-54366# The evolution of the Tay engine, launched in response to the DEVELOPMENT OF THE T406-AD-400 OIL SCAVENGE requirement for an engine suitable for powering a noise compliant SYSTEM FOR THE V-22 AIRCRAFT aircraft in the 70-100 seat range, is reviewed. The engine is derived JOHN R. ARVlN (General Motors Corp., Allison Gas Turbine Div., from the Spey Mk 555 installed in the Fokker F28 aircraft and Indianapolis, IN) ASME, Gas Turbine and Aeroengine Congress incorporates several latest technology features, modularity and and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 5 p. maintenability being the key areas addressed in the design. The (ASME PAPER 88-GT-297) general design, main components, and the principal performance The T406-AD-400 is a front drive, free power turbine engine characteristics of the Tay 650 engine are described. V.L.

82 1 07 AIRCRAFT PROPULSION AND POWER

~aa-54372# The -229 engine has a thrust-to-weight ratio of 8.0, with a 20-30 ENERGY MANEUVERABILITY AND ENGINE PERFORMANCE percent performance increase over the -220 model across the REQUIREMENTS flight map. Significant improvements in maintainability have been MICHAEL J. CADDY and WILLIAM K. ARNOLD (US. Navy, Naval incorporated while retaining the proven durability and operability Air Development Center, Warminster, PA) ASME, Gas Turbine features of the -220 engine. Author and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. ~a8-5438~ (ASME PAPER 88-GT-303) A TURBINE WHEEL DESIGN STORY The ’energy maneuverability’ concept is presently defined in WILSON R. TAYLOR, KEITH WHELESS, and LEE G. GRAY (USAF, simplistic terms as an introduction to a method for the comparative Aeronautical Systems Div., Wright-Patterson AFB, OH) ASME, evaluation of fighter aircraft. A tradeoff sensitivity analysis is then Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, developed for a generic future-generation fighter that illustrates Netherlands, June 6-9, 1988. 6 p. the relationship between engine performance requirements and (ASME PAPER 88-GT-316) fighter maneuverability. It is found that, while thrust vectoring yields The features of the jet fuel starter (JFS), which is used to no significant energy maneuverability-related improvement, it can start the FlOO main propulsion engines for the F-15 fighter aircraft, furnish enhanced stability and control characteristics at high-alpha are discussed. In an attempt to prolong the lifespan of the JFS, conditions, as well as improve aircraft agility. O.C. the USAF conducted an analysis of the disk to determine if it was reasonable to eliminate the fragmentation holes and slots. In ~aa-54374# addition, a NASTRAN finite element stress analysis was performed. DEVELOPMENT OF THE F404/RM12 FOR THE JAS 39 The power turbine wheel redesign considered meets the GRIPEN requirements of containment; it can be manufactured at a lower L. LARSSON (Volvo Flygmotor AB, Trollhattan, Sweden), L. B. cost and yield an improved life. K.K. VENO, and W. J. DAUB (General Electric Co., Aircraft Engine Business Group, Cincinnati, OH) ASME, Gas Turbine and A88-54386# Aeroengine Congress and Exposition, Amsterdam, Netherlands, EVALUATION OF POTENTIAL ENGINE CONCEPTS FOR A June 6-9, 1988. 7 p. HIGH ALTITUDE LONG ENDURANCE VEHICLE (ASME PAPER 88-GT-305) EDWARD J. KOWALSKI (Boeing Co., Seattle, WA) ASME, Gas The F404/RM12 engine is a derivative of the F404-GE-400 Turbine and Aeroengine Congress and Exposition, Amsterdam, used by the F-18 for the propulsion system requirements of the Netherlands, June 6-9, 1988. 9 p. refs Swedish JAS 39 fighter aircraft. A new three-stage fan module is (ASME PAPER 88-GT-321) incorporated which yields a 10-percent airflow increase and superior The potential of several propulsion system candidates for a birdstrike resistance. An increase in the compressor discharge high-altitude long-endurance (HALE) aircraft is evaluated. The pressure limit furnishes improved thrust in specific regions of the engines examined include the classical turbofan engine with bypass flight envelope, and a higher turbine inlet temperature yields a ratios up to 8, the ultrahigh bypass ratio turbofan with bypass sea level static thrust of 18,105 Ibs, by comparison to the ratios up to 20, the unducted fan engine, and the turboprop in a F404-GE-400’s 16,000 Ibs. Hot section materials have been pusher and tractor configuration with single and counter rotation improved to allow service life requirements to be met under the propfans. The impact of high altitude (up to 60,000 feet) surveillance enhanced temperature and pressure conditions. O.C. mission requirements on aircraft design characteristics, engine cycle characteristics, and propulsion system concepts is A88-54379# discussed. V.L. STRATIFIED CHARGE ROTARY ENGINES FOR AIRCRAFT ROBERT E. MOUNT and GASTON GUARDA (John Deere AW-54507 Technologies International, Inc.. Rotary Engine Div., Wood-Ridge, TOWARDS SIMULTANEOUS PERFORMANCE - APPLICATION NJ) ASME, Gas Turbine and Aeroengine Congress and Exposition, OF SIMULTANEOUS STABILIZATION TECHNIQUES TO Amsterdam, Netherlands, June 6-9, 1988. 10 p. refs HELICOPTER ENGINE CONTROL (ASME PAPER 88-GT-311) K. DEAN MINT0 (GE Corporate Research and Development Substantial progress has been made over the past two years Center, Schenectady, NY) IN: 1988 American Control Conference, in the technological status and production aspects of Stratified 7th, Atlanta, GA, June 15-17, 1988, Proceedings. Volume 2. New Charge Rotary Engines, a new propulsion technology for aircraft York, Institute of Electrical and Electronics Engineers, 1988, p. of the 1990s. A 400 HP aircraft engine, designed in cooperation 852-859. refs with Avco-Lycoming (during late 1986) is currently undergoing Ongoing research aimed at refining a design algorithm, namely testing at John Deere’s Rotary Engine Division. Current status simultaneous stabilization, is reported. Through application of the and design features are reported in this paper and related to simultaneous stabilization design technique to a realistic aerospace overall research and technology enablement efforts toward several control problem, an attempt is made to demonstrate the practical families of advanced liquid cooled, turbocharged and intercooled utility of the method, and identify the technical issues that remain engines over a wide power range for commercial general aviation. to be resolved. The focus of this study is the GE T700 turboshaft Capabilities for high altitude, long endurance, military unmanned engine, when coupled to the Apache and Blackhawk helicopter aircraft missions are examined. Application to fixed and rotary airframes. Experiences are described with an indirect design wing aircraft are planned. Author technique to obtain an LTl compensator that simultaneously satisfies two loop-shaping type performance criteria, one for each ~aa-s43ao# engine-airframe combination. I.E. F100-PW-229 - HIGHER THRUST IN SAME FRAME SIZE BERNARD L. KOFF (Pratt and Whitney, West Palm Beach, FL) ~8a-54619 ASME, Gas Turbine and Aeroengine Congress and Exposition, FIBER OPTICS FOR AIRCRAFT ENGINE CONTROLS Amsterdam, Netherlands, June 6-9, 1988. 6 p. MARK A. OVERSTREET and ROBERT F. HOSKIN (General Motors (ASME PAPER 88-GT-312) Corp., Allison Gas Turbine Div., Indianapolis, IN) IN: 1988 The F100-PW-229 fighter aircraft engine is a higher-thrust American Control Conference, 7th, Atlanta, GA, June 15-17, 1988, derivative of the F100-PW-220 and in the same frame size. The Proceedings. Volume 3. New York, Institute of Electrical and increased thrust was achieved by increasing the flow and pressure Electronics Engineers, 1988, p. 1819-1 824. ratio of the two-spool compression system, accompanied by an An examination is made of the fundamental physical increase i’n turbine temperature. The increased-length compression characteristics of fiber-optic sensor technology, including EM1 system was offset by an innovative design intermediate case and (electromagnetic interference) immunity, light weight and small size, a reduced length combustor to maintain overall engine axial length. high temperature and radiation tolerance, flexibility, stability, and

822 07 AIRCRAFT PROPULSION AND POWER durability. Principles of operation for fiber-optic sensors and systems Group, Cincinnati, OH) IN: 1988 American Control Conference, are discussed, including basic design principles, extrinsic vs. 7th, Atlanta, GA, June 15-17, 1988, Proceedings. Volume 3. New intrinsic sensing, and typical fiber-optic links. A discussion of the York, Institute of Electrical and Electronics Engineers, 1988, p. state of the art and applications provides the status of development 1846-1851. and outlook for various fiber sensor types (pressure, temperature, (Contract F33615-86-C-2666) etc.) for the applications defined. I.E. The potential of electrical power systems for engine actuation, fuel delivery and power generation have been investigated, A8844620 projecting technology developments in magnetic materials, VERY HIGH SPEED INTEGRATED CIRCUITS/GALLIUM insulation systems, and advanced power electronics for the year ARSENIDE ELECTRONICS FOR AIRCRAFT ENGINE 2000. The results of the projections are described, and the key CONTROLS technological developments required to achieve those designs are MARK A. OVERSTREET (General Motors Corp., Allison Gas identified. Comparisons to similar systems based on technologies Turbine Div., Indianapolis, IN) IN: 1988 American Control used today are made to demonstrate the advantages of the future Conference, 7th, Atlanta, GA, June 15-17, 1988, Proceedings. electrical control and accessory systems for the advanced aircraft Volume 3. New York, Institute of Electrical and Electronics engines. The particular applications discussed are motor-driven Engineers, 1988, p. 1825-1830. actuator system, motor-driven fuel delivery system, three alternate VHSIC/GaAs technology has been studied to define how it generating systems, fan-driven cantilevered generator, can be developed and applied to improve control system gas-generator-compressor-driven starterlgenerator, and separate performance for aircraft engines. The results of this study are turbine-driven generator. I.E. presented. Discussed are related programs and the common areas of VHSIC and GaAs technology with emphasis on the unique A8844624 optoelectronic and adverse environment characteristics of GaAs. POTENTIAL APPLICATION OF COMPOSITE MATERIALS TO Attributes of materials, devices, circuits, systems, and other topics FUTURE GAS TURBINE ENGINES are addressed, along with future application requirements for engine JAMES C. BIRDSALL, WILLIAM J. DAVIES (Pratt and Whitney, control application. The state of the art in VHSWGaAs components East Hartford, CT), RICHARD DIXON (United Technologies Corp., and their possible applications are discussed. A summary is Hamilton Standard Div., Windsor Locks, CT), MATTHEW J. WARY presented of the environmental and performance payoffs offered, (Parker Hannifin Corp., Parker Bertea Aerospace Group, Itvine, and some conclusions are provided about the current state of the CA), GARY A. WIGELL (Sundstrand Corp., Rockford, IL) et al. art as it applies to engine control applications, future applications IN: 1988 American Control Conference, 7th, Atlanta, GA, June potential, risk, and the degree of further development required. 15-17, 1988, Proceedings. Volume 3. New York, Institute of LE. Electrical and Electronics Engineers, 1988, p. 1852-1856. Several firms have evaluated the viability of composite materials A8844621 and control component design to reduce engine control system THE CHARACTERIZATION OF HIGH TEMPERATURE weight. Each of the component suppliers has used ELECTRONICS FOR FUTURE AIRCRAFT ENGINE DIGITAL engine-manufacturer requirements to evaluate the benefits and ELECTRONIC CONTROL SYSTEMS shortfalls of composite materials when used in the gas turbine J. D. WILEY (Wisconsin, University, Madison) and D. C. DENING control environment. Study results indicate a significant weight (General Electric Co., Syracuse, NY) IN: 1988 American Control reduction, up to 30 percent, when composites are used for Conference, 7th, Atlanta, GA, June 15-17, 1988, proceedings. electronic control housings, actuators, and fuel pumps. This Volume 3. New York, Institute of Electrical and Electronics projected benefit is tempered with requirements for electromagnetic Engineers, 1988, p. 1831-1 836. compatibility, fluid tolerance, and ability to withstand high (Contract F33615-86-C-2666) environmental temperatures and vibration levels. LE. A characterization of high-temperature electronics is presented including high-temperature effects, semiconductors, and barrier A8844658 metallizations. Design solutions and material selections for SCHEDULING TURBOFAN ENGINE CONTROL SET POINTS BY mitigation of high-temperature effects are indicated. The following SEMI-INFINITE OPTIMIZATION semiconductor materials are considered for future high-temperature D. M. STIMLER (GE Control Systems Laboratory, Schenectady, applications: silicon, gallium arsenide, gallium phosphide, silicon NY) IN: 1988 American Control Conference, 7th, Atlanta, GA, carbide, and diamondlike carbon. I.E. June 15-17, 1988, Proceedings. Volume 3. New York, Institute of Electrical and Electronics Engineers, 1988, p. 2256-2263. refs A88-54622 It is shown that modern semiinfinite optimization methods DATA FLOW ANALYSIS OF CONCURRENCY IN A TURBOJET provide a powerful method for determining the operating schedules ENGINE CONTROL PROGRAM of control set points for advanced turbofan engines, giving the PHILLIP L. SHAFFER and TIMOTHY L. JOHNSON (GE Corporate engineer considerable design freedom. The use of these methods Research and Development Center, Schenectady, NY) IN: 1988 to develop engine schedules which optimize complex performance American Control Conference, 7th, Atlanta, GA, June 15-17, 1988, objectives and explicitly satisfy performance requirements on Proceedings. Volume 3. New York, Institute of Electrical and engine variables is shown. This approach is also shown to provide Electronics Engineers, 1988, p. 1837-1845. refs insights as to the limits of engine performance and the control The amount of concurrency which is inherent in an engine requirements of the engine. The methods are illustrated by control algorithm and a methodology for computing this measure determining portions of the steady-state and transient operating based on existing programs are presented. The control is schedules of a state-of-the-art single-bypass turbofan engine. partitioned into functional blocks, followed by analyses of data LE. dependencies and of execution time. Concurrency is increased by modification and decomposition of bottleneck functions. For the A88-54938# control program analyzed, exploitation of concurrency at the A STUDY OF AERODYNAMIC NOISE FROM A function level allows a reduction of execution time to 15 percent CONTRA-ROTATING AXIAL COMPRESSOR STAGE of the sequential execution time. LE. P. 6. SHARMA and D. S. PUNDHIR (Indian Institute of Technology, New Delhi, India) IN: Developments in Mechanics. Volume 14(b) A8844623 - Midwestern Mechanics Conference, 20th, West Lafayette, IN, HIGH TEMPERATURE, LIGHTWEIGHT, SWITCHED Aug. 31-Sept. 2, 1987, Proceedings. West Lafayette, IN, Purdue RELUCTANCE MOTORS AND GENERATORS FOR FUTURE University, 1987, p. 801-806. Research supported by the Aerospace AIRCRAFT ENGINE APPLICATIONS Research and Development Board of India. refs ElKE RICHTER (General Electric Co., Aircraft Engine Business The paper reports an investigation of aerodynamic noise from

823 07 AIRCRAFT PROPULSION AND POWER

a contra-rotating axial compressor stage of 0.66 hub-tip ratio. behind the rotor. The single scoop inlet was also tested at a Measurements of noise at three axial locations from intake to the position further aft. Tests were also done without an inlet. These exit of the compressor stage are reported for different speed ratios. results emphasize the importance of avoiding critical speeds in Spectrum analysis of noise signals is also presented. The axial the continuous operating range. B.W. spacing between the rotors is shown to have a marked influence on the noise generation from contra-rotating rotors. Author N88-28928'# Hamilton Standard, Windsor Locks, Conn. SRdA AEROELASTIC MODEL DESIGN REPORT N88-28925# Naval Air Development Center, Warminster, Pa. D. NAGLE, S. AUYEUNG, and J. TURNBERG Washington, D.C. Air Vehicle and Crew Systems Technology Directorate. Oct. 1986 118 p AGARD (ADVISORY GROUP FOR AEROSPACE RESEARCH (Contract NAS3-23051) AND DEVELOPMENT) ENGINE DISC MATERIAL (NASA-CR-174791; NAS 1.26:174791; HSER-9251) Avail: NTlS COOPERATIVE TEST (SUPPLEMENTARY PROGRAM) HC AO6/MF A01 CSCL 21E EUN U. LEE 12 Aug. 1987 47 p A scale model was designed to simulate the aeroelastic (AD-A193678; NADC-87169-60) Avail: NTlS HC A03/MF A01 characteristics and performance of the 2.74 meter (9 ft.) diameter CSCL 11F SR-7L blade. The procedures used in this model blade design From a gas turbine engine compressor spool of Ti-17 alloy, are discussed. Included in this synopsis is background information cylindrical unnotched specimens and flat double edge notched concerning scaling parameters and an explanation of manufacturing specimens were machined and fatigue-tested. The flat double edge limitations. A description of the final composite model blade, made notched specimens were also subjected to electrical potential drop of titanium, fiberglass, and graphite, is provided. Analytical methods measurements. The microstructure and fracture surface for determining the blade stresses, natural frequencies and mode morphology of the representative specimens were examined. The shapes, and stability are discussed at length. Author variation of fatigue life, N, with applied stress range, delta sigma, was described by an equation of the form log N = a + b (delta N88-28929*# General Electric Co., Cincinnati, Ohio. Aircraft sigma). The variation of normalized crack voltage, (V/V sub o)/(V Engine Business Group. sub R/V sub Ro), with normalized crack length, (a/w), was given E3 1OC COMPRESSOR TEST ANALYSIS OF HIGH-SPEED by an equation of the form (V/V sub o)/(V sub R/V sub Ro) = A POST-STALL DATA + A sub 1 (a/w) + A sub 2 (a/w)sq + A sub 3 (a/w) cu. GRA S. D. DVORAK, W. M. HOSNY, and W. G. STEENKEN Oct. 1986 109p N88-28926# Advisory Group for Aerospace Research and (Contract NAS3-24211) Development, Neuilly-Sur-Seine (France). (NASA-CR-179521; NAS 1.26:179521; R86AEB564) Avail: NTlS AGARD ENGINE DISC COOPERATIVE TEST PROGRAMME HC AO6/MF A01 CSCL 21E A. J. A. MOM and M. D. RAIZENNE (National Aeronautical In-stall characteristics from high-speed post-stall transients are Establishment, Ottawa, Ontario ) Aug. 1988 87 p determined. The transient, surge-cycle nature of high-speed (AGARD-R-766; ISBN-92-835-0475-5) Avail: NTlS HC A05/MF post-stall operation precludes the possibility of obtaining in-stall A0 1 characteristics in a steady-state manner, as is posSible during The initial results of an AGARD test program on fatigue behavior low-speed post-stall operation, which is characterized by of engine disc materials are described. The first phase of the quasi-steady rotating-stall behavior. Maximum likelihood parameter program, the Core Program, was aimed at test procedure and estimation techniques were used to obtain the quasi-steady specimen standardization and calibration of the various laboratories. high-speed characteristics from transient data. The necessary data A detailed working document is included which describes the testing was first obtained from a specially instrumented compressor that fundamentals and procedures and includes the analysis procedures was tested well beyond its limits of normal operation. The unsteady, used for handling the test data. Fatigue crack initiation and post-stall data thus obtained was then digitized and processed propagation testing was performed on Ti-6AI-4V material under through a simplified analytical model to construct the input-output room temperature and constant amplitude loading conditions using relationship necessary for estimation. In-stall characteristics were four different specimen designs. All results were statistically determined using this estimation procedure at two different analyzed for possible significant differences in material behavior high-speed conditions, 90 and 98.5 percent corrected speed. The due to disc processing variables, specimen location in the disc or estimated characteristics were found to be robust in the presence testing laboratory. Author of measurement noise and unmodelled system dynamics, but the compressor response-time constants, also estimated, were more N88-28927*# Hamilton Standard, Windsor Locks, Conn. sensitive to these same disturbances. The experimentally EXPERIMENTAL AND ANALYTICAL EVALUATION OF THE determined low-speed in-stall characteristics and the estimated EFFECTS OF SIMULATED ENGINE INLETS ON THE BLADE high-speed in-stall characteristics were then incorporated into a VIBRATORY STRESSES OF THE SR-3 MODEL PROP-FAN one-dimensional compressor simulation model developed as a Final Report parallel effort to the compressor testing and data reduction effort, PREM N. BANSAL Sep. 1985 118 p which yielded predictable results. Author (Contract NAS3-24222) . (NASA-CR-174959: NAS 1.26:174959) Avail: NTlS HC AO6/MF N88-28930'# United Technologies Corp., East Hartford, Conn.

A01 CSCL 21E ' THE EFFECTS OF INLET TURBULENCE AND A cooperative wind tunnel test program, referred to as GUN-3, ROTOWSTATOR INTERACTIONS ON THE AERODYNAMICS had been conducted previously to assess the effect of inlet AND HEAT TRANSFER OF A LARGE-SCALE ROTATING configuration and location on the inlet face pressure recovery and TURBINE MODEL. VOLUME 3: HEAT TRANSFER DATA inlet drag in the presence of a high-speed advanced turboprop. TABULATION 65 PERCENT AXIAL SPACING Final Report These tests were conducted with the inlets located just downstream R. P. DRING, M. F. BLAIR, and H. D. JOSLYN Washington, of the SR-3 model Prop-Fan, a moderately swept, eight-bladed D.C. May 1986 235 p 62.2 cm (24.5 inch) diameter advanced, high-speed turboprop (Contract NAS3-23717) model fabricated from titanium. During these tests, two blades of (NASA-CR-179468; NAS 1.269 79468; UTRC/R86-95648O-VOL-3) the SR-3 model Prop-Fan were strain gaged to measure the Avail: NTlS HC A1 1/MF A01 CSCL 21 E vibratory blade stresses occurring during the inlet aerodynamic This is Volume 3 - Heat Transfer Data Tabulation (65% Axial test program. The purpose of the effort reported herein was to Spacing) of a combined experimental and analytical program which reduce and analyze the test results related to the vibratory strain was conducted to examine the effects of inlet turbulence on airfoil gage measurements obtained. Three inlet configurations had been heat transfer. The experimental portion of the study was conducted tested. These were: (1) single scoop, (2) twin scoop, and (3) in a large-scale (approximately 5X engine), ambient temperature, annular. Each of the three inlets was tested at a position just rotating turbine model configured in both single stage and

824 07 AIRCRAFT PROPULSION AND POWER

stage-and-a-half arrangements. Heat transfer measurements were KRISHNA RAO V. KAZA, MARC H. WILLIAMS, ORAL MEHMED, obtained using low-conductivity airfoils with miniature and G. V. NERAYANAN (Sverdrup Technology, Inc., Cleveland, thermocouples welded to a thin, electrically heated surface skin. Ohio.) 1988 26 p Presented at the 24th Joint Propulsion Heat transfer data were acquired for various combinations of low Conference, Boston, Mass., 11-13 Jul. 1988; sponsored in part by or high inlet turbulence intensity, flow coefficient, first-stator/rotor AIAA, ASEE, ASME and SAE axial spacing, Reynolds number and relative circumferential position (NASA-TM-100964; E-4229; NAS 1.1 5:100964; AIAA-88-3154) of the first and second stators. Author Avail: NTlS HC A03/MF A01 CSCL 21E An analytical investigation of aeroelastic response of metallic N88-29803# Rolls-Royce Ltd., Derby (England). and composite propfan models in yawed flow was performed. The V2500 ENGINE COLLABORATION analytical model is based on the normal modes of a rotating blade G. E. KIRK and M. ITOH 26 Oct. 1987 6 p Presented at the and the three dimensional unsteady lifting surface aerodynamic 1987 Tokyo International Gas Turbine Conference, Tokyo, Japan, theory including blade mistuning. The calculated blade stresses or 26-30 Oct. 1987 strains are compared with published wind tunnel data on two (PNR90423; ETN-88-92668) Avail: NTlS HC A02/MF A01 metallic and three composite propfan wind tunnel models. The International collaboration in developing the V2500 gas turbine comparison shows a good agreement between theory and engine is described. The engine configuration and parts are experiment. Additional parametric results indicate that blade outlined. Engineering management and communication are response is very sensitive to the blade stiffness and also to blade discussed. ESA frequency and mode shape mistuning. From these findings, it is concluded that both frequency and mode shape mistuning should N88-29804*# United Technologies Corp., East Hartford, Conn. be included in aeroelastic response analysis. Furthermore, both THE EFFECTS OF INLET TURBULENCE AND calculated and measured strains show that combined blade ROTOWSTATOR INTERACTIONS ON THE AERODYNAMICS frequency and mode shape mistuning has beneficial effects on AND HEAT TRANSFER OF A LARGE-SCALE ROTATING response due to yawed flow. Author TURBINE MODEL. VOLUME 2 HEAT TRANSFER DATA TABULATION. 15 PERCENT AXIAL SPACING Final Report N88-29808# National Aerospace Lab., Amsterdam (Netherlands). R. P. DRING, M. F. BLAIR, and H. D. JOSLYN Washington, Structures and Materials Div. D.C. May 1986 242 p FAILURE ANALYSIS FOR GAS TURBINES (Contract NAS3-23717) A. J. A. MOM 18 Apr. 1987 36 p In DUTCH; ENGLISH (NASA-CR-179467; NAS 1.26:179467; UTRC-R86-956480-VOL-2) summary Presented at the Symposium van de Bond voor Avail: NTlS HC A1 1/MF A01 CSCL 21 E Materialenkennis Schade in Constructies voor Gebruik bij Hoge A combined experimental and analytical program was Temperature, Wageningen, The Netherlands, 16 Oct. 1986 conducted to examine the effects of inlet turbulence on airfoil (NLR-MP-87037-U; 88803805; ETN-88-92612) Avail: NTlS HC heat transfer. The experimental portion of the study was conducted A03/MF A01 in a large-scale (approx 5X engine), ambient temperature, rotating A number of failures in gas turbines are discussed, including turbine model configured in both single stage and stage-and-a-half methods of preventing similar failures, in order to illustrate the arrangements. Heat transfer measurements were obtained using diversity of failure analysis. The significance of failure analysis is low-conductivity airfoils with miniature thermcouples welded to a explained, and the potential benefits of failure analysis for gas thin, electrically heated surface skin. Heat transfer data were turbine users are mentioned. The background, reasons, and acquired for various combinations of low or high inlet turbulence materials investigation of the F-16 crash in Lauwersmeer intensity, flow coefficient, first-stator/rotor axial spacing, Reynolds (Netherlands) are described. For the fracture of first-stage turbine number and relative circumferential position of the first and second blades of a jet motor, the damage analysis and the lifetime analysis stators. Aerodynamic measurements obtained as part of the are outlined. Damage due to crack formation in compressor drive program include distributions of the mean and fluctuating velocities shafts is treated. ESA at the turbine inlet and, for each airfoil row, midspan airfoil surface pressures and circumferential distributions of the downstream N88-29809# Rolls-Royce Ltd., Derby (England). steady state pressures and fluctuating velocities. Analytical results DEVELOPING THE ROLLS-ROYCE TAY include airfoil heat transfer predictions produced using existing N .J. WILSON 30 Jun. 1988 14 p Presented at the 33rd 2-0 boundary layer computation schemes and an examination of ASME Gas Turbine Conference, Amsterdam, The Netherlands, Jun. solutions of the unsteady boundary layer equations. The results 1988 are reported in four separate volumes, of which this is Volume 2: (PNR90447; ETN-88-92680) Avail: NTlS HC AOS/MF A01 Heat Transfer Data Tabulation; 15 Percent Axial Spacing. Author The evolution of the Tay engine, launched in response to the requirement for an engine suitable for powering a FAR Part 36 N88-29805# Minnesota Univ., Minneapolis. Dept. of Mechanical Stage 3 noise compliant aircraft in the 70 to 100 seat range is Engineering. reviewed. The engine, which is derived from the Spey (RB183) STUDIES OF GAS TURBINE HEAT TRANSFER AIRFOIL Mk 555 installed in the Fokker F28 aircraft, incorporates latest SURFACE AND END-WALL COOLING EFFECTS Annual technology features which are already in service in large turbofan Report, Mar. 1987 - Mar. 1988 engines. Modularity and maintainability in the design of the engine E. R. ECKERT, R. J. GOLDSTEIN, S. V. PATANKAR, and T. W. are discussed in regard to operation in service. ESA SIMON Mar. 1988 58 p (Contract F49620-85-C-0049) N88-29810# General Electric Co., Cincinnati, Ohio. Advanced (AD-A195165; A4-TR-88-0546) Avail: NTlS HC A04/MF A01 Technology Operation. CSCL 20M EMPIRICAL FLUTTER PREDICTION METHOD Final Report, Research results on curved surface heat transfer, airfoil heat Sep. 1984 - Sep. 1987 transfer, film cooling and end-wall heat transfer are presented. J. K. CASEY 5 Mar. 1988 358 p These studies focus on the recovery process of a turbulent (Contract F33615-84-C-2457) boundary layer from curvature, heat transfer measurements and (AD-A195699; R87AEG; AFWAL-TR-87-2087) Avail: NTlS HC numerical prediction techniques of film-cooling on an adiabatic A16/MF A01 CSCL 20D flat plate by injection through a single row of holes. GRA Design of advanced technology engines is often limited by compressor blade instability or flutter. Test points from the annular N88-29807'# National Aeronautics and Space Administration. cascade data base were analyzed, to predict from aeromechanical Lewis Research Center, Cleveland, Ohio. data which of 14 types of stability or instability would result. The AEROELASTIC RESPONSE OF METALLIC AND COMPOSITE basic approach was to identify for each pair of stability regions, PROPFAN MODELS IN YAWED FLOW linear combinations (hyperplanes) of the aeromechanical variables,

825 07 AIRCRAFT PROPULSION AND POWER whose numerical value would be above a critical level for all test 7 or 8 percent higher, but the combustion chamber must be points in one stability region and would be below the critical level modified to avoid vibrations. ESA for test points in the other stability region. It was found that 76 pct of the pairs of stability regions allowed a hyperplane to N88-29911# Pratt and Whitney Aircraft, West Palm Beach, Fla. discriminate between the two regions, but for 24 pct a curved Engineering Div. surface or nonlinear combination variables would be needed. FUEL PROPERTY EFFECTS ON THE US NAVY'S TF30 Review of 85 pct of the 891 test points used to construct the ENGINE hyperplanes revealed that the hyperplanes correctly identify the S. A. MOSIER and P. A. KARPOVICH (Naval Air Propulsion Test stability condition of 59 pct of the points in a literal sense, but Center, Trenton, N.J.) In AGARD, Combustion and Fuels in Gas are correct in a broader practical sense for 79 pct of the points. Turbine Engines 15 p Jun. 1988 When the hyperplanes were applied to 51 validation test points Avail: NTlS HC A22/MF A01 taken from several actual engine/rig test data, they gave virtually The TF30 engine was introduced into Navy service in 1972 no correct results, which was not immediately explainable. GRA and is scheduled to continue to power the carrier based F14 for some time. Although the engine was designed and developed to operate on specification grade JP-5 fuel, it is conceivable that N88-29811'# Southwest Research Inst., San Antonio, Tex. Dept. during its lifetime, the TF30 might have to operate on out-of-spec of Materials Sciences. or broadened-spec fuels. This contingency could arise should the CONSTITUTIVE MODELING FOR ISOTROPIC MATERIALS availability of high grade petroleum crude oil used for aircraft fuel Final Report production be decreased. Therefore, a program of experimentation K. S. CHAN, U. S. LINDHOLM, and S. R. BODNER Jun. 1988 and analysis was conducted to evaluate the effects of 155 p broadened-spec petroleum fuels on the performance, durability and (Contract NAS3-23925; SWRl PROJ. 06-7576) operability of the TF30-P-414A engine. As fuel quality deteriorated, (NASA-CR-182132; NAS 1.26:182132) Avail: NTlS HC AO8/MF some reductions in engine performance characteristics were A01 CSCL 21E observed. However, based upon limited time testing, the The third and fourth years of a 4-year research program, part TF30-P-414A engine was shown to be capable of operating on of the NASA HOST Program, are described. The program goals liquid petroleum fuels having a wide range of properties. Author were: (1) to develop and validate unified constitutive models for isotropic materials, and (2) to demonstrate their usefulness for structural analysis of hot section components of gas turbine engines. The unified models selected for development and evaluation were those of Bodner-Partom and of Walker. The unified approach for elastic-viscoplastic constitutive equations is a viable AIRCRAFT STABILITY AND CONTROL method for representing and predicting material response characteristics in the range where strain rate and temperature dependent inelastic deformations are experienced. This conclusion Includes aircraft handling qualities; piloting; flight controls; and autopilots. is reached by extensive comparison of model calculations against the experimental results of a test program of two high temperature Ni-base alloys, B1900+ Hf and Mar-M247, over a wide temperature A88-53148# range for a variety of deformation and thermal histories including VEHICLE MANAGEMENT SYSTEMS THE LOGICAL uniaxial, multiaxial, and thermomechanical loading paths. The - EVOLUTION OF INTEGRATION applicability of the Bodner-Partom and the Walker models for STEVE W. JACOBS (McDonnell Aircraft Co., Saint Louis, MO) structural applications has been demonstrated by implementing and CHARLES A. SKlRA (USAF, Aero Propulsion Laboratory, these models into the MARC finite element code and by performing Wright-Patterson AFB, OH) AIAA, ASME, SAE, and ASEE, Joint a number of analyses including thermomechanical histories on Propulsion Conference, 24th, Boston, MA, July 11-13, 1988. 9 p. components of hot sections of gas turbine engines and benchmark (AIAA PAPER 88-3175) notch tensile specimens. The results of the 4-year program have Vehicle management is the integrated control of the flight, been published in four annual reports. The results of the base propulsion, and aircraft utility systems. The implementation of this program are summarized in this report. The tasks covered include: concept into a control architecture forms a Vehicle Management (1) development of material test procedures, (2) thermal history System (VMS). A practical VMS design can provide significant effects, and (3) verification of the constitutive model for an performance and supportability benefits to military aircraft. alternative material. Author Performance enhancements are achieved by integrated control to optimize previously independent systems. Supportability is N88-29813# Research Inst. of National Defence, Stockholm increased through the comprehensive diagnostics, component (Sweden). commonality, and reduced complexity provided by integrated digital REVIEW OF RESEARCH CONCERNING SOLID FUEL RAMJET systems. This paper reviews the concept of a VMS and addresses (SOFRAM) AT THE RESEARCH INSTITUTE OF NATIONAL the issues of functional and physical integration. A generic approach DEFENCE (FOA) 2 to VMS design is outlined and illustrated. Key elements for future RALF ELIASSON May 1988 21 p In SWEDISH; ENGLISH VMS bench and flight demonstration are also identified. Author summary (FOA-C-20714-2.1; ISSN-0347-3694; ETN-88-93058) Avail: A88-53251 NTlS HC A03/MF A01 MODELLING OF AIRCRAFT PROGRAM MOTION WITH An airbreathing engine for velocities over Mach 1.8 is described. APPLICATION TO CIRCULAR LOOP SIMULATION A tube-formed propellant of an outer diameter 72 mm was studied. W. BLAJER (Radom, Wyzsza Szkola Inzynierska, Poland) Results show that to reach the optimum length of the motor it is Aeronautical Journal (ISSN 0001-9240), vol. 92, Aug.-Sept. 1988, necessary to use a propellant with a higher burning rate than p. 289-296. refs HTPB. Ten different compositions of HTPB propellants were tested: The objective of this paper is to present the principles of a 10 percent ammonium perchlorate increases combustion velocity mathematical model of aircraft prescribed motion. Requirements by 40 percent, but a higher amount can lead to pressure vibrations imposed on the aircraft motion are treated as program constraints in the combustion area; the addition of 5 percent lampblack reduces on the system and both the transient dynamic solution of motion the velocity by 20 percent. Computed figures are given for artillery equations and the control ensuring the exact realization of the ammunition of 155 mm driven by SOFRAM. A secondary air intake prescribed motion are obtained as a result. The approach used is (a by-pass) was also investigated. Stable combustion is achieved equivalent to the Lagrange multiplier method, generalized for the with 42 percent of the air by-passed, the mechanical output being purpose of this paper. It consists of the solution of the set of

826 08 AIRCRAFT STABILITY AND CONTROL

differentiallalgebraic equations of index exceeding three. The implementation of the logic software which operates with the control presented mathematical model has been applied to the simulation mode panel (CMP) of an aircraft is presented. The CMP is the of aircraft prescribed motion in a loop. The flight along an ideal pilot control panel for the automatic flight control system of a circle and the flight with additionally demanded constant velocity commercial-type research aircraft of Langley Research Center's are described. Some results of numerical calculations are Advanced Transport Operating Systems (ATOPS) program. A demonstrated. Author mouse-driven color-display emulation of the CMP, which was developed with AI methods and used to test the AI software logic A88-53755# implementation, is discussed. The operation of the CMP was A KNOWLEDGE BASED SYSTEM OF SUPERMANEUVER enhanced with the addition of a display which was quickly SELECTION FOR PILOT AIDING developed with AI methods. The display advises the pilot of HUBERT H. CHIN (Grumman Corp., Aircraft Systems Div., conditions not satisfied when a mode does not arm or engage. Bethpage, NY) AIAA, AHS, and ASEE, Aircraft Design, Systems The implementation of the CMP software logic has shown that and Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 9 p. refs the time required to develop, implement, and modify software (AIAA PAPER 88-4442) systems can be significantly reduced with the use of the AI The Maneuver Selection Aiding System, 'MASAS', employs methods. I.E. fuzzy logic, tactical planning, and knowledge-base techniques to select supermaneuver strategies, such as controlled-sideslip and A88-54474 high-alpha tactics, that will aid pilots during defined missions. A WORKSTATION FOR THE INTEGRATED DESIGN AND MASAS encompasses a supermaneuverable selector, a tactical SIMULATION OF FLIGHT CONTROL SYSTEMS planner, and an executive planner; each of these interfaces with RICHARD DEAN COLGREN (Lockheed Aeronautical Systems Co., both a knowledge base and an exceptions-handler. The selector Burbank, CA) IN: 1988 American Control Conference, 7th, Atlanta, uses the Max-Min operator on the fuzzy relations matrix to select GA, June 15-17, 1988, Proceedings. Volume 1. New York, Institute suitable strategies; regional planning qualifies regional threat effects of Electrical and Electronics Engineers, 1988, p. 608-613. refs and identifies potentially safe supermaneuvers among threats and The development of a workstation which integrates design, within geometry constraints. O.C. analysis, and simulation methods used for flight-control-system synthesis is described. Aerodynamic, propulsion, and structural A88-53796 models can be directly interfaced for analysis and synthesis work, INFLIGHT CG-CONTROL - SYSTEM ASPECTS and the results transferred to a flight simulator and to the dynamic H. DRACHENBERG (Messerschmitt-Boelkow-Blohm GmbH, structural model. The workstation is implemented with an executive Bremen, Federal Republic of Germany) SAWE, Annual which handles most inputloutput operations internally so that data Conference, 46th, Seattle, WA, May 18-20, 1987. 25 p. refs management by the user is minimized. Also planned is an (SAWE PAPER 1795) expert-aided approach, by which predicted flying qualities are used The lnflight Center-of-Gravity (CG) Control System that entered to evaluate the performance of the closed-loop system. If the airline operation in 1985 aboard the A-310-300 airliner determines desired flying qualities are not attained, a rule base would advise and controls CG position through the manipulation of fuel volumes the user on how to modify the flight control system. A modular located within the aircraft's horizontal tailplane (the 'trim tank'), as approach allows novel techniques to be implemented easily as well as in its fuselage and wings. Attention is presently given to executives or as additional modules. I.E. the eIectricaVelectronics systems considerations that entered into the definition, design, testing, certification, and operation of this A88-54526' National Aeronautics and Space Administration. system, as well as to the form taken by the cockpit displays Ames Research Center, Moffett Field, Calif. responsible for the monitoring of the system. O.C. CONSIDERATIONS FOR AUTOMATED NAP-OF-THE-EARTH ROTORCRAFT FLIGHT A88-53799 VICTOR H. L. CHENG and BANAVAR SRIDHAR (NASA, Ames IMMP - A COMPUTER SIMULATION OF FUEL CG VERSUS Research Center, Moffett Field, CA) IN: 1988 American Control VEHICLE ATTITUDE Conference, 7th. Atlanta, GA, June 15-17, 1988, Proceedings. GERALD JON MOLCZYK (General Dynamics Corp., Convair Div., Volume 2. New York, Institute of Electrical and Electronics San Diego, CA) SAWE, Annual Conference, 46th, Seattle, WA, Engineers, 1988, p. 967-976. refs May 18-20, 1987. 23 p. The authors consider nap-of-the-earth (NOE) rotorcraft flight (SAWE PAPER 1801) as one of the applications in which obstacle avoidance plays a The Interactive Maneuvering Model Program, IMMP, simulates key role, and investigate the prospects of automating the guidance the center-of-gravity (CG) displacement behavior of a fuel mass functions of NOE flight. Based on a proposed structure for the in a semidepleted fuel tank during aircraft maneuvering by means guidance functions, obstacle detection and obstacle avoidance are of a FEM analysis of the tank's cross-sectional area. This allows identified as the two critical components requiring substantial the evaluation of iterative vertical and lateral CG drift, followed by advancement before an automating guidance system can be complete CG determination on the basis of the coordinated realized. The major sources of difficulties in developing these two 'stacking' of cross-sectional mass-properties elements. IMMP components are discussed, including sensor requirements for which furnishes accurate, cost-effective mass properties inputs for flight a systematic analysis is provided. I.E. simulations concerned with operational and technical evaluations of aircraft performance. O.C. A88-54528 PERIODIC NEIGHBORING OPTIMUM REGULATOR APPLIED A88-54424' National Aeronautics and Space Administration. TO A HYPERSONIC SCRAMJET CRUISER Langley Research Center, Hampton, Va. C.-H. CHUANG, Q. WANG, and J. L. SPEYER (Texas, University, APPLICATION OF AI METHODS TO AIRCRAFT GUIDANCE Austin) IN: 1988 American Control Conference, 7th, Atlanta, GA, ANDCONTROL June 15-17, 1988, Proceedings. Volume 2. New York, Institute of RICHARD M. HUESCHEN and JOHN W. MCMANUS (NASA, Electrical and Electronics Engineers, 1988, p. 983-989. refs Langley Research Center, Hampton, VA) IN: 1988 American For a reasonable model of a hypersonic scramjet cruiser, Control Conference, 7th, Atlanta, GA, June 15-17, 1988, optimum fuel cruise trajectories are determined. Two local Proceedings. Volume 1. New York, Institute of Electrical and minimums are obtained which give nearly the same fuel Electronics Engineers, 1988, p. 195-201. refs consumption. One local minimum is periodic which has amplitude A research program for integrating artificial intelligence (AI) variations of about 25,000 feet and a mean of about 100,000 techniques with tools and methods used for aircraft flight control feet. The other local minimum is a static path where the maximum system design, development, and implementation is discussed. The thrust is just equal to the aerodynamic drag. This static path seems application of the AI methods for the development and to be unobtainable except possibly asymptotically. However, for

827 08 AIRCRAFT STABILITY AND CONTROL the periodic path which is realizable, a periodic neighboring optimum trajectories. In addition to being useful for helicopter regulator is derived. This regulator includes variations in the control nap-of-the-earth guidance, the trajectory planning solution is of variables of lift coefficient and thrust switch times. The mass change interest in several other contexts, such as robotic vehicle guidance of the vehicle, which is tacitly assumed negligible in producing and terrain-following guidance for cruise missiles and aircraft. A the nominal path, is included explicitly in this regulator. The distinguishing feature of the present research is that the terrain performance of this regulator presented. I.E. constraint and the threat envelopes are incorporated in the equations of motion. Second-order necessary conditions are A88-54549' City Coll. of the City Univ. of New York. examined. I.E. EIGENSTRUCTURE ASSIGNMENT FOR THE CONTROL OF HIGHLY AUGMENTED AIRCRAFT A8844598 KENNETH M. SOBEL (City College, New York) and FREDERICK H(INFIN1TY)-OPTIMAL DESIGN FOR HELICOPTER CONTROL J. LALLMAN (NASA, Langley Research Center, Hampton, VA) IN: ANDREW YUE and IAN POSTLETHWAITE (Oxford University, 1988 American Control Conference, 7th, Atlanta, GA, June 15-17, England) IN: 1988 American Control Conference, 7th. Atlanta, 1988, Proceedings. Volume 2. New York, Institute of Electrical GA, June 15-17, 1988, Proceedings. Volume 2. New York, Institute and Electronics Engineers, 1988, p. 1267-1276. refs of Electrical and Electronics Engineers, 1988, p. 1679-1684. Eigenstructure assignment is utilized to design flight control Research supported by the Royal Aircraft Establishment. refs laws for aircraft with many control effectors. It is shown that a Results of a study into the use of H(infinity)-optimization for previous eigenstructure design for the flight propulsion control the design of robust feedback control laws for improving the coupling (FPCC) aircraft lateral dynamics with three control surfaces handling qualities of a battlefield helicopter are reported. Control exhibits a lack of stability robustness because the control laws are designed for precise control of pitch and roll attitude, distribution matrix is nearly rank-deficient. A method is mapped yaw rate, and heave velocity in the hover fight condition. LE. back, reducing the control space to two dimensions by using the singular value decomposition. After the design is complete, the controller is mapped back to the original three-dimensional control A8844650 space. This design approach yields a controller with both smaller DETECTION, IDENTIFICATION AND ESTIMATION OF gains and improved multivariable stability margins at the aircraft SURFACE DAMAGE/ACTUATOR FAILURE FOR HIGH inputs. An interesting characteristics of the control mapping, as PERFORMANCE AIRCRAFT applied to the given example, is that the most effective inputs A. K. CAGLAYAN, K. RAHNAMAI, and S. M. ALLEN (Charles have the larger gains while the less effective inputs have smaller River Analytics, Inc., Cambridge, MA) IN: 1988 American Control gains. I.E. Conference, 7th, Atlanta, GA, June 15-17, 1988, Proceedings. Volume 3. New York, Institute of Electrical and Electronics A88-54570' Rice Univ., Houston, Tex. Engineers, 1988, p. 2206-2212. refs OPTIMIZATION AND GUIDANCE OF PENETRATION LANDING (Contract F33615-844-3608) TRAJECTORIES IN A WINDSHEAR A hierarchical failure detection, identification, and estimation A. MIELE, T. WANG (Rice University, Houston, TX), and W. W. (FDIE) algorithm for use in a self-repairing flight-control system in MELVIN (Delta Airlines, Inc., Atlanta, GA) IN: 1988 American a high-performance aircraft is described. This hierarchical FDlE Control Conference, 7th, Atlanta, GA, June 15-17, 1988, system consists of two subsystems: (1) an actuator-failure detection Proceedings. Volume 2. New York, Institute of Electrical and (AFD) system that detects stuck, runaway, and floating actuator Electronics Engineers, 1988, p. 1428-1439. Research supported failures based on local information and (2) a surface-damage by Boeing Commercial Airplane Co. and Air Line Pilots detection and isolation (SDDI) system which detects partial surface Association. refs loss failures and provides an estimate for the surface control (Contract NAG1-516) effectiveness parameters after the impairment based on global The optimization and guidance of penetration landing information. Preliminary FDlE results are presented from a 6-DOF trajectories in a windshear are considered. It is assumed that the nonlinear simulation of a combat reconfigurable-control aircraft aircraft is controlled by the angle of attack and the power setting. under typical flight conditions, pilot inputs, and gust levels. LE. For the optimal trajectory, the performance index being minimized measures the deviation of the flight trajectory from the nominal A8844652 trajectory. In turn, the nominal trajectory includes two parts: the A HYPERSTABLE MODEL-FOLLOWING FLIGHT CONTROL approach part (nominal glide slope constant) and the flare part SYSTEM USED FOR RECONFIGURATION FOLLOWING (nominal glide slope varying linearly with the horizontal distance). AIRCRAFT IMPAIRMENT Numerical results show that the optimal trajectory deviates C. J. DITTMAR (General Electric Co., Aircraft Control Systems somewhat from the nominal trajectory in the shear region. A Dept., Binghamton, NY) IN: 1988 American Control Conference, guidance scheme is developed to approximate the optimal 7th, Atlanta, GA, June 15-17, 1988, Proceedings. Volume 3. New trajectory. The angle of attack is determined by the windshear York, Institute of Electrical and Electronics Engineers, 1988, p. intensity, the absolute path inclination, and the glide slope angle, 221 9-2224. refs while the power setting is determined by the windshear intensity Techniques have been developed for remixing the commands and the velocity. Numerical results indicate that the guidance issued by flight control laws that assume unimpaired operation. trajectory is close to the optimal trajectory. I.E. This approach allows impairments to be accommodated that previously were not. This increase in fault tolerance does not A88-54571' Georgia Inst. of Tech., Atlanta. decrease reliability because no additional hardware is installed on HELICOPTER TRAJECTORY PLANNING USING OPTIMAL the aircraft. Instead, previously existing redundant control surfaces CONTROL THEORY are used to greater advantage. A recent effort has focused on an P. K. A. MENON (Georgia Institute of Technology, Atlanta), V. H. implicit approach, as opposed to a previously mechanized explicit L. CHENG (NASA, Ames Research Center, Moffett Field, CA), approach. The implicit approach, which is termed hyperstable and E. KIM IN: 1988 American Control Conference, 7th, Atlanta, model-following flight control (HMFC), is estimated to be an order GA, June 15-17, 1988, Proceedings. Volume 2. New York, Institute of magnitude smaller in size than the explicit approach, which is of Electrical and Electronics Engineers, 1988, p. 1440-1447. termed the control reconfiguration feature (CRF). This reduction refs in size is accomplished without a loss in performance. In fact, (Contract NAG2-463) performance can increase because the reduced complexity allows A methodology for optimal trajectory planning, useful in the a higher iteration rate, and hence reduced reconfiguration time. nap-of-the-earth guidance of helicopters, is presented. This HMFC will successfully reconfigure under conditions for which the approach uses an adjoint-control transformation along with a CRF will not, while possessing robustness with respect to one-dimensional search scheme for generating the optimal disturbances and unmodeled states. I.E.

828 08 AIRCRAFT STABILITY AND CONTROL

A88-54653 A88-54660 AUTOMATED DESIGN OF CONTINUOUSLY-ADAPTIVE APPROXIMATION SCHEMES FOR AN CONTROL - THE ’SUPER-CONTROLLER’ STRATEGY FOR AEROELASTIC-CONTROL SYSTEM RECONFIGURABLE SYSTEMS J. TURl and S. M. RANKIN, 111 (Worcester Polytechnic Institute, JOHN F. ELDER, IV and ROGER L. BARRON (Barron Associates, MA) IN: 1988 American Control Conference, 7th, Atlanta, GA, Inc., Stanardsville, VA) IN: 1988 American Control Conference, June 15-17, 1988, Proceedings. Volume 3. New York, Institute of 7th, Atlanta, GA, June 15-17, 1988, Proceedings. Volume 3. New Electrical and Electronics Engineers, 1988, p. 2266, 2267. refs York, Institute of Electrical and Electronics Engineers, 1988, p. The problem of designing active control schemes for flutter 2225-2231. Research supported by Century Computing, Inc. and suppression in flexible aircraft is discussed. Based on a well-posed Universal Energy Systems, Inc. refs state-space formulation, the authors present an abstract framework Modern military aircraft undergo rapid and often unpredictable to study approximation techniques for the active flutter control of changes in dynamics during flight. This requires a method for an airfoil with flap in two-dimensional unsteady flow of an inviscid developing simple, robust, high-performance control systems that incompressible fluid. Conditions on the abstract approximation vary in real time with operating and fault-condition changes in the scheme are formulated which guarantee the uniform convergence system being controlled; that is, that reconfigure rapidly to face of the approximate solutions in bounded time intervals, and it is rapidly changing conditions. A supercontroller strategy is outlined shown how the conditions can be applied to the that shows promise of meeting this need. The authors describe averaging-projections approximation scheme. LE. the supercontroller design technique and preliminary simulation results that are based on single-effector and simultaneous A88-54661 multiple-effector impairments of a control-reconfigurable combat A MINIMAL REALIZATION ALGORITHM FOR FLIGHT aircraft. I.E. CONTROL SYSTEMS CHUN SHUNG HSU, D. HOU (Washington State University, A88-54654 Pullman), and GREGORY ROBEL (Boeing Commercial Airplane APPLICATION OF SUPERCONTROLLER TO FIGHTER Co., Seattle, WA) IN: 1988 American Control Conference, 7th, AIRCRAFT RECONFIGURATION Atlanta, GA, June 15-17, 1988, Proceedings. Volume 3. New York, HARRY N. GROSS (US. Air Force Academy, Colorado Springs, Institute of Electrical and Electronics Engineers, 1988, p. CO) and BARRY S. MIGYANKO (USAF, Flight Dynamics 2268-2270. refs Laboratory, Wright-Patterson AFB, OH) IN: 1988 American Control A computationally simple procedure to obtain a minimal Conference, 7th, Atlanta, GA, June 15-17, 1988, Proceedings. realization from a given transfer-function matrix is presented. The Volume 3. New York, Institute of Electrical and Electronics simplicity of the method is a consequence of taking advantage of Engineers, 1988, p. 2232-2237. refs the fact that many models of flight-control systems have distinct A discussion is presented of a fighter aircraft control system and/or pairs of complex-valued eigenvalues. Two illustrative design using the supercontroller methodology. A polynomial flight-control examples (X-29 and Airbus A300) are provided to network is developed for each control surface to enable the aircraft demonstrate the applicability of the method. I.E. to perform a range of maneuvers at a single flight condition subject to locked control surfaces. Performance is compared to that of A88-55064# the baseline aircraft and of a reconfigurable aircraft with explicit PILOTNEHICLE ANALYSIS OF A TWIN-LIFT HELICOPTER failure detection and isolation. I.E. CONFIGURATION IN HOVER R. A. HESS (California, University, Davis) and P. M. TRAN (General Dynamics Corp., Pomona, CA) Journal of Guidance, Control, A88-54656 and Dynamics (ISSN 0731-5090), vol. 11, Sept.-Oct. 1988, p. ROBUST CONTROL STRATEGY FOR TAKE-OFF 465-472. Previously cited in issue 08, p. 1052, Accession no. PERFORMANCE IN A WINDSHEAR A87-22571. refs Y. H. CHEN and S. PANDEY (Syracuse University, NY) IN: 1988 American Control Conference, 7th, Atlanta, GA, June 15-17, 1988, A88-55275# Proceedings. Volume 3. New York, Institute of Electrical and CONTROL SURFACE SELECTION BASED ON ADVANCED Electronics Engineers, 1988, p. 2244-2249. refs MODES PERFORMANCE A robust control strategy has been studied for an aircraft during MARIO INNOCENT1 (Auburn University, AL) and ALDO TONON takeoff. The effects of different wind-shear intensities have been (Aeritalia S.p.A., Turin, Italy) AIAA, Atmospheric Flight Mechanics analyzed for different models. As the complexity of the model Conference, Minneapolis, MN, Aug. 15-17, 1988. 10 p. refs increases and as a more complete model is taken into account, (AIAA PAPER 88-4356) the survivability of the aircraft degrades. However, the robust control The problem of control surface configuration selection is strategy yields results which are comparable to the best known presently considered for the implementation of an advanced fighter results. The robust control is designed via a deterministic approach. flight control system’s fuselage-aiming mode. Both canardlflap and The only information it utilizes is the upper bound of the allowable elevator/flap combinations are considered for control in the col?trol magnitude. The resulting system behavior (namely, the longitudinal plane, while rudder-and-vertical fin and axisymmetric stability) is described in a deterministic way. LE. brakes are evaluated in the lateral plane. The figure-of-merit defined for these configurational alternatives is based exclusively on A88-54659 closed-loop dynamics behavior and flight control system MULTIPLE-MODEL PARAMETER-ADAPTIVE CONTROL FOR requirements. O.C. IN-FLIGHT SIMULATION THOMAS J. BERENS and DANIEL J. BIEZAD (USAF, Institute of N88-28931# Air Force Inst. of Tech., Wright-Patterson AFB, Technology, Wright-Patterson AFB, OH) IN: 1988 American Ohio. School of Engineering. Control Conference, 7th, Atlanta, GA, June 15-17, 1988, TIME PERIODIC CONTROL OF A MULTI-BLADE HELICOPTER Proceedings. Volume 3. New York, Institute of Electrical and Ph.D. Thesis Electronics Engineers, 1988, p. 2264, 2265. refs STEPHEN G. WEBB May 1988 218 p The authors incorporate a priori information into a multiple-model (AD-A194435; AFIT/DS/AA/88-2) Avail: NTlS HC AlO/MF A01 estimation algorithm which assigns a probability weighting to each CSCL 01c estimator within a bank of estimators. Final parameter estimates The flap-lag equations of motion of an isolated rotor blade used in adaptive control are formed as a probabilistic weighted and those for a rigid helicopter containing four blades free to flap sum of individual estimates. Simulations of the system show and lag are derived. Control techniques are developed which excellent tracking performance throughout the flight envelope. stabilize both systems for a variety of flight conditions. Floquet LE. theory is used to investigate the stability of a rotor blade’s flap-lag

829 08 AIRCRAFT STABILITY AND CONTROL motion. A modal control technique, based on Floquet theory, is turbulence. It shows a good agreement between the two sets of used to eliminate the blade’s instabilities using collective and cyclic results and it emphasizes the better modeling of the turbulence pitch control mechanisms. The technique shifts the unstable roots using the isotropic model rather than the cylindrical one. Author to desired locations while leaving the other roots unaltered. The control, developed for a single design point, is shown to significantly N88-29724# Civil Aviation Authority, Redhill (England). reduce or eliminate regions of flap-lag instabilities for a variety of Airworthiness Div. off-design conditions. Both scalar and vector control are A REVIEW OF MEASURED GUST RESPONSES IN THE LIGHT successfully used to stabilize the blade’s motion. Coupling the OF MODERN ANALYSIS METHODS flap-lag equations of motion of four rotor blades to a rigid airframe V. CARD In AGARD, The Flight of Flexible Aircraft in Turbulence: alters the flap lag, and airframes roots. The airframe roots are State-of-the-Art in the Description and Modelling of Atmospheric stabilized using a combination of the body’s pitch attitude and Turbulence 14 p Jun. 1988 pitch rate feedback to the main rotor’s longitudinal cyclic pitch. Avail: NTlS HC AO6/MF A01 The modal control technique is used to eliminate multiple blade In the past simplified models of aircraft used to assess instabilities by first controlling a pair of unstable roots at a specific operational gust statistics have led to conservative estimates of design point. The resulting closed loop system is a new linear derived gust exceedances. Modern refinements in aircraft modeling system with periodic coefficients. Another modal controller is techniques have gradually introduced conservatism in the process designed for this new system to shift a second pair of unstable of calculating gust loads. Gust statistics reviewed in the light of roots to desired locations. GRA these modern analytical methods support the CAA view that gust velocities developed for use with simple rigid aircraft models are N88-28932# Messerschmitt-Boelkow-Blohm G.m.b.H., Bremen too severe for use with a modern dynamic analysis. Even in the (West Germany). Unternehmensbereich Transport- und light of improved safety targets, a 10 per cent reduction in design Verkehrsflugzeuge. gust velocity can be readily justified. Further reductions may be VARIABLE WING CAMBER CONTROL SYSTEMS FOR THE justified on the basis of mission analysis considerations, or by FUTURE AIRBUS PROGRAM Final Report, Jun. 1987 investigation of more recent acceleration statistics collected by JUERGEN RENKEN Bonn, Fed. Republic of Germany the current generation of transport aircraft. In the latter case, it Bundesministerium fuer Forschung und Technologie Feb. 1988 will be essential to account for all relevant features of the subject 132 p In GERMAN; ENGLISH summary aircraft in the derivation of gust velocities so as to obtain a true (Contract BMFT-LFL-83618) picture of the gust statistics. Author (MBB-UT-104/88; ETN-88-92965) Avail: NTlS HC A07/MF A01 The physics background of camber variation is overviewed. N88-29726*# National Aeronautics and Space Administration. The principles of the mechanical realization of chordwise and Langley Research Center, Hampton, Va. spanwise camber variation, including the effects of elastic STATUS REVIEW OF ATMOSPHERE TURBULENCE AND deformation, the actuation and control concepts, camber laws and AIRCRAFT RESPONSE performance maximization including the effects on the operational J. C. HOUBOLT In AGARD, The Flight of Flexible Aircraft in flight and the implementation of the variable camber function in Turbulence: State-of-the-Art in the Description and Modelling at an A-320 aircraft are described. The potential fuel saving benefits Atmospheric Turbulence 11 p Dec. 1987 of camber variation and the technical investment are related to Avail: NTlS HC AO9/MF A01 CSCL 01C the other high cost, high risk technological efforts aiming at further A brief review is made of the understanding of aircraft encounter fuel saving performed in the entire aircraft scenario. It is concluded of atmospheric turbulence, both from the point of view of describing that with the presented camber variation a technology is available or modeling the turbulence and with respect to the ability to which offers a considerable fuel saving potential at low cost, low calculate resulting airplane loads. Some of the more recent studies risk, and with a negligible weight increase. ESA of gust measurements and of reducing airline gust response data are discussed. Special attention is given to gust analysis N88-29718# Federal Aviation Administration, Seattle, Wash. requirements as involved in airplane certification and whether there CURRENT AND PROPOSED GUST CRITERIA AND ANALYSIS is a need for additional or different requirements. A review is METHODS AN FAA OVERVIEW made of a recent study in which amazingly simple and universal TERENCE J. BARNES In AGARD, The Flight of Flexible Aircraft gust response equations were discovered; the possible impact of in Turbulence: State-of-the-Art in the Description and Modelling of these new findings on future work is indicated. Author Atmospheric Turbulence 12 p Jun. 1988 Avail: NTlS HC AO6/MF A01 N88-29729# Taylor (J.), Camberley (England). An FAA overview is presented of the gust criteria and analysis AN INTERIM COMPARISON OF OPERATIONAL CG RECORDS methods used in the various types of flight vehicle certified under IN TURBULENCE ON SMALL AND LARGE CIVIL AIRCRAFT the FAR’S. The current criteria for small airplanes, transports, and J. TAYLOR In AGARD, The Flight of Flexible Aircraft in rotorcraft are presented, and the status of proposed criteria for Turbulence: State-of-the-Art in the Description and Modelling of the tilt rotor and aerospace plane are discussed. The amount of Atmospheric Turbulence 31 p Dec. 1987 discussion on each class of vehicle depends on the significance Avail: NTlS HC AO9/MF A01 of gust loads as design loads, and the importance of vehicle Operational records have been made on British Airways aircraft flexibility. Transport airplane gust criteria development, usage and for the period May 1980 to April 1985 and analyzed for about problems are discussed in some detail. Analysis methods used by 650,000 flying hours on a number of different aircraft. Records U.S. industry are covered in a separate paper. Author were obtained for about 2 to 5 minutes of Normal Acceleration, Pitch Angle, Roll Angle, Height and Speed for nearly all those N88-29723# Office National d’Etudes et de Recherches events which had an increment of 1 g or more, i.e., 29 events; Aeronautiques, Paris (France). similar records were also obtained for nearly all those events with MEASUREDANDPREDICTEDRESPONSESOFTHENORD an increment of 0.5 g or more with flaps down from May 1983 to 260 AIRCRAFT TO THE LOW ALTITUDE ATMOSPHERIC April 1985, Le., 33 events. An interim examination of the 29 events TURBULENCE with 1 excess g or more, with special emphasis on 15 of them is J. L. MEURZEC and F. POlRlON In AGARD, The Flight of made and includes an estimate of the interaction of maneuvers Flexible Aircraft in, Turbulence: State-of-the-Art in the Description and turbulence, an estimate of the frequency of occurrence of and Modelling of Atmospheric Turbulence 9 p Jun. 1988 high level intensity gusts and of the equiprobability relationships Avail: NTlS HC AO6/MF A01 of gust levels and gust gradients. It was found that gusts that are A program of in situ measures using the Nord 260 plane important for a particular response are strongly dependent on the equipped with accelerometers has allowed the comparison of the rate per sub 5 km at which zero crossings occur in that response. predicted and the measured responses of the flexible aircraft to Using the Kaynes formula for gust intensity and zero crossings, it

830 08 AIRCRAFT STABILITY AND CONTROL

was found that the equiprobability relationships of gust levels and N88-29816'# Odetics, Inc., Anaheim, Calif. ' gust gradients can be represented on a single diagram for all THREAT EXPERT SYSTEM TECHNOLOGY ADVISOR sizes of aircraft at all heights. Author E. R. KURRASCH and L. R. TRlPP Aug. 1987 101 p (Contract NAS2-12558) (NASA-CR-177479; NAS 1.26:177479) Avail: NTlS HC AO6/MF N88-29732# British Aerospace Aircraft Group, Weybridge A01 CSCLOlC 1 (England). Military Aircraft Div. A prototype expert system was developed to determine the RE-ASSESSMENT OF GUST STATISTICS USING CAADRP feasibility of using expert system technology to enhance the DATA performance and survivability of helicopter pilots in a combat threat B. W. PAYNE, A. E. DUDMAN, and K. C. GRlFFlTHS ln AGARD, environment while flying NOE (Nap of the Earth) missions. The The Flight of Flexible Aircraft in Turbulence: State-of-the-Art in basis for the concept is the potential of using an Expert System the Description and Modelling of Atmospheric Turbulence 22 p Advisor to reduce the extreme overloading of the pilot who flies Dec. 1987 NOE mission below treetop level at approximately 40 knots while Avail: NTlS HC AO9/MF A01 performing several other functions. The ultimate goal is to develop The measured incremental c.g. accelerations of the BAC 1-11 a Threat Expert System Advisor which provides threat information operating on scheduled flights are compared with the equivalent and advice that are better than even a highly experienced copilot. theoretical predictions in a gust environment. Some of the results The results clearly show that the NOE pilot needs all the help in of the study are: (1) An analysis of the measured Civil Airworthiness decision aiding and threat situation awareness that he can get. It Authority Data Recording Program data, based upon a significant clearly shows that heuristics are important and that an expert 58,733 flying hours, gave an incremental vertical c.g. acceleration system for combat NOE helicopter missions can be of great help of 1.25 g at the datum probability value of 2 x .00005 exceedances to the pilot in complex threat situations and in making decisions. per hour; (2) The theoretical predictions from all the flight segments Author in the Mission Analysis gave an incremental c.g. acceleration of .238 g at the datum exceedance value; and (3) Therefore in the comparison between the measured and predicted analyses for a N88-29817*# Draper (Charles Stark) Lab., Inc., Cambridge, similar mission considerable differences were found with measured Mass. frequencies of exceedance of about one half those predicted using DEVELOPMENT AND DEMONSTRATION OF AN ON-BOARD current airworthiness requirements. Author MISSION PLANNER FOR HELICOPTERS OWEN L. DEUTSCH and MUKUND DESAI May 1988 126 p (Contract NAS2-12419) N88-29814# Air Force Inst. of Tech., Wright-Patterson AFB, Ohio. School of Engineering. (NASA-CR-177482; NAS 1.26:177482; CSDL-R-2056) Avail: NTlS HC A07/MF A01 CSCL 01C AN ANALYSIS OF LATERAL-DIRECTIONAL HANDLING Mission management tasks can be distributed within a planning QUALITIES AND EIGENSTRUCTURE OF HIGH hierarchy, where each level of the hierarchy addresses a scope PERFORMANCE AIRCRAFT M.S. Thesis MICHAEL J. COSTIGAN Jun. 1988 218 p of action, and associated time scale or planning horizon, and requirements for plan generation response time. The current work (AD-A194874; AFlT/GAE/AA/EEJ-l) Avail: NTlS HC AlO/MF is focused on the far-field planning subproblem, with a scope and A01 CSCL01A planning horizon encompassing the entire mission and with a The relationship between an aircraft's lateral-directional handling qualities and its corresponding eigenstructure is examined. response time required to be about two minutes. The far-feld planning problem is posed as a constrained optimization problem Intuition and simple methematical models were used to develop desirable eigenvectors. For conventional aircraft, the dutch roll and algorithms and structural organizations are proposed for the solution. Algorithms are implemented in a developmental eigenvector was shown to a function of the roll to sideslip (philbeta) ratio. Flight control laws to produce the desired eigenstructures environment, and performance is assessed with respect to optimality and feasibility for the intended application and in were derived using eigenstructure assignment with output feedback. comparison with alternative algorithms. This is done for the three The control laws were based on a twelfth order linear model of major components of far-field planning: goal planning, waypoint the lateral-directional dynamics of the YA-7D DIGITAC, and varied path planning, and timeline management. It appears feasible to the dutch roll phi/beta ratio. The handling qualities of the YA-7D meet performance requirements on a 10 Mips flyable processor were examined. The flight testing consisted of both open loop tasks, and closed loop tasks in which Cooper-Harper ratings were (dedicated to far-field planning) using a heuristically-guided assigned. GRA simulated annealing technique for the goal planner, a modified A' search for the waypoint path planner, and a speed scheduling technique developed for this project. Author N88-29815'# Lockheed-Georgia Co., Marietta. N-VERSION SOFTWARE DEMONSTRATION FOR DIGITAL N88-29818# Texas A&l Univ., Kingsville. FLIGHT CONTROLS Final Report A FIBER OPTIC COLLECTIVE FLIGHT CONTROL SYSTEM DENNIS B. MULCARE and LYNN A. BARTON Apr. 1987 FOR HELICOPTERS M.S. Thesis 152 p (Contract NAS2-11853) ELLIS WAYNE GOLSON May 1988 62 p (AD-A195406) Avail: NTlS HC A04/MF A01 CSCL 20F (NASA-CR-181483; NAS 1.26:181483; AD-A189864; The objective of this thesis is design a fiber optic transmission DOT/FAA/CT-86/33) Avail: NTlS HC AOWMF A01 CSCL 01 D to system to replace the present collective flight control system for This report illustrates how four independently developed helicopters. A discussion of the present collective control system versions of digital flight controls applications software might be is presented as well as fiber optic system components necessary used in quadruplex system architecture. This approach to software fault tolerance is called N-version software. Here each computer to provide positive collective control of the aircraft. Computer simulation has been utilized where possible to verify modulation channel has distinct versions of Ada programming units performing the same functions concurrently. Since intermediate software and receiver circuitry. The fiber optic system provides advantages in weight, survivability, and cockpit organization. GRA results are voted to detect and isolate discrepant computations, cross-channel synchronization occurs at each voting plane. The demonstration of this system was based on a high-level software N88-29819*# Manudyne Systems, Inc., Los Altos, Calif. design, English language specifications, and associated Ada MINIMUM-COMPLEXITY HELICOPTER SIMULATION MATH program unit specifications parts. The demonstration was MODEL Final Contractor Report, Jul. 1985 - Jul. 1987 performed in non-realtime on a single VAX 8600 computer using ROBERT K. HEFFLEY and MARC A. MNlCH Apr. 1988 102 p an Ada multitasking test harness to effect voting plane Prepared for Army Research and Technology Labs., Moffett Field, synchronization and test case application and analyses. GRA Calif.

83 1 09 RESEARCH AND SUPPORT FACILITIES (AIR)

(Contract NAS2-11665) A88-53629# (NASA-CR-177476; NAS 1.26:177476; USAAVSCOM-TR-87-A-7) IMAGE EXTRAPOLATION FOR FLIGHT SIMULATOR VISUAL Avail: NTlS HC AO6/MF A01 CSCL 01C SYSTEMS An example of a minimal complexity simulation helicopter math KEITH BLANTON jlvex Corp., Norcross, GA) IN: AIAA, Flight model is presented. Motivating factors are the computational Simulation Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, delays, cost, and inflexibility of the very sophisticated math models Technical Papers. Washington, DC, American Institute of now in common use. A helicopter model form is given which Aeronautics and Astronautics, 1988, p. 17-22. addresses each of these factors and provides better engineering (AIAA PAPER 88-4577) understanding of the specific handling qualities features which are Flight simulator visual systems which can render detailed terrain apparent to the simulator pilot. The technical approach begins databases with realistic texturing are typically very expensive. with specification of features which are to be modeled, followed However, constraining the terrain to be an absolutely flat plane by a build up of individual vehicle components and definition of can offer tremendous advantages in many important simulation equations. Model matching and estimation procedures are given scenarios over conventional systems. This paper outlines the which enable the modeling of specific helicopters from basic data fundamental principles behind a new approach based on this sources such as flight manuals. Checkout procedures are given assumption and describes some of the implementation issues which which provide for total model validation. A number of possible must be considered. The result is a visual system which can model extensions and refinement are discussed. Math model generate images with high quality texturing and detail and maintain computer programs are defined and listed. Author a guaranteed frame rate. These techniques are the basis around which the IVEX Corporation VDS-1000 flight simulator visual system was designed. Author 09 A88-53630# DYNAMIC TEXTURE IN VISUAL SYSTEM MASARU FUJINO and MASATO OGATA (Mitsubishi Precision Co., RESEARCH AND SUPPORT FACILITIES (AIR) Ltd.. Kamakura, Japan) IN: AIAA, Flight Simulation Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, Technical Papers. Includes airports, hangars and runways; aircraft repair and overhaul Washington, DC, American Institute of Aeronautics and facilities; wind tunnels; shock tube facilities; and engine test Astronautics, 1988, p. 23-25. blocks. (AIAA PAPER 88-4578) In the current CGI visual system, texture mapping is used to enhance the detail of image. The state of the ocean waves and A88-53135*# Virginia Univ., Charlottesville. stirring of grass on the ground surface, however, are not sufficiently UNIQUE, CLEAN-AIR, CONTINUOUS-FLOW, simulated. To improve the image, it is developed a system which HIGH-STAGNATION-TEMPERATURE FACILITY FOR computes linear combinations of some basic patterns, and using SUPERSONIC COMBUSTION RESEARCH the computation results, a multistage color mixing is performed. R. H. KRAUSS, J. C. MCDANIEL, JR., J. E. SCOTT, JR., R. B. Parameters specifying texture patterns are controlled to generate WHITEHURST, 111, C. SEGAL (Virginia, University, Charlottesville) various dynanmic textures. The image of dynamic ocean surface et al. AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, will produce effective training of ASW mission by helicopter. 24th. Boston, MA, July 11-13, 1988. 27 p. NASA-supported Author research. refs (AIAA PAPER 88-3059A) A88-53635# Accurate, spatially-resolved measurements can be conducted PRESENTANDFUTUREDEVELOPMENTSOFTHENLR of a model supersonic combustor in a clean air/continuous flow MOVING BASE RESEARCH FLIGHT SIMULATOR supersonic combustion facility whose long run times will allow not C. J. JANSEN (Nationaal Lucht- en Ruimtevaartlaboratorium, only the point-by-point mapping of flow field variables with laser Amsterdam, Netherlands) IN: AIAA, Flight Simulation Technologies diagnostics but facilitate the simulation of steady-state combustor Conference, Atlanta, GA, Sept. 7-9, 1988, Technical Papers. conditions. The facility will provide a Mach 2 freestream with static Washington, DC, American Institute of Aeronautics and pressures in the 1 to 1/6 atm range, and stagnation temperatures Astronautics, 1988, p. 54-61. of up to 2000 K. O.C. (AIAA PAPER 88-4584) The paper presents an ovetview of the upgrading program of A8843626 the NLR Flight Simulator. The avionics system consists of an AIAA, FLIGHT SIMULATION TECHNOLOGIES CONFERENCE, ARlNC bus interface system to couple 0.a. EFIS displays, a ATLANTA, GA, SEPT. 7-9, 1988, TECHNICAL PAPERS general-purpose graphics station, and a programmable EFIS. The Conference sponsored by AIAA. Washington, DC, American new fully hydrostatic 6-degrees-of-freedom motion system with high Institute of Aeronautics and Astronautics, 1988, 367 p. For individual bandwidth (only 45 deg phase lag at 4 Hz for acceleration items see A8843627 to A88-53671. commands from the simulator computer) is described in more detail. The conference presents papers on wide-field-of-view helmet Finally, the digital motion interface and the proposed bus interface mounted display systems for helicopter simulation, processing system are described. Author pseudosynthetic aperture radar images from visual terrain data, image extrapolation from flight simulator visual systems, multiple A88-53642'# National Aeronautics and Space Administration. frame rate integration, real-time simulation of helicopters using Langley Research Center, Hampton, Va. the blade element method, present and future developments of THE LANGLEY ADVANCED REAL-TIME SIMULATION (ARTS) the NLR moving base research flight simulator, and SYSTEM mission-oriented simulator development. Other topics include a DANIEL J. CRAWFORD, JEFF I. CLEVELAND, II, and RICHARD computer systems upgrade for the Shuttle mission training facility, 0. STAB (NASA, Langley Research Center, Hampton, VA) IN: tactical air combat in a real-time multiple engagement simulation, AIAA, Flight Simulation Technologies Conference, Atlanta, GA, simulation tools for crew system assessment, a methodology for Sept. 7-9, 1988, Technical Papers. Washington, DC, American simulation validation using optimal time history matching, and Institute of Aeronautics and Astronautics, 1988, p. 109-121. human performance data in simulation design. Consideration is (AIAA PAPER 88-4595) also given to visual-vestibular interaction of pilot's perception of This paper is intended as a status report on the ARTS system. aircraft or simulator motion, time delay compensation using It briefly describes the architecture and principal subsystems supplementary cues in aircraft simulator systems, and software including: the CAMAC network system (hardware and software), tools for building dedicated real-time applications. K.K. the clocking system, the signal converters, the control consoles,

832 09 RESEARCH AND SUPPORT FACILITIES (AIR)

and the minicomputer and microcomputer interfaces. The delays, and results of a study to determine simulator hardware performance and reliability of the system exceeds expectations time delay are discussed. An average total system delay of about and component failure data over an 11month period are presented. 87 milliseconds is found. An analysis of pilot performance did not Planned enhancements, including the replacement of the reveal any significant changes due to increased simulator delays, mainframe computers, are discussed. Author but did show that the pilot control activity increased in the low-speed high-gain tasks. Although with increased time delay the A88-53653'# National Aeronautics and Space Administration. Cooper-Harper rating increased (indicating degradation in perceived Langley Research Center, Hampton, Va. handling qualities), for the type of helicopter simulated, there was SIMULATOR EVALUATION OF TAKEOFF PERFORMANCE no definite time delay at which the ratings changed abruptly. MONITORING SYSTEM DISPLAYS R.R. DAVID 8. MIDDLETON, LEE H. PERSON, JR. (NASA, Langley Research Center, Hampton, VA), and RAGHAVACHARI A88-53667'# Army Aviation Research and Development SRIVATSAN (Vigyan Research Associates, Inc., Hampton, VA) IN: Command, Moffett Field, Calif. AIAA, Flight Simulation Technologies Conference, Atlanta, GA, THE EFFECT OF PERSPECTIVE DISPLAYS ON ALTITUDE Sept. 7-9, 1988, Technical Papers. Washington, DC, American AND STABILITY CONTROL IN SIMULATED ROTARY WING Institute of Aeronautics and Astronautics, 1988, p. 206-214. refs FLIGHT (AIAA PAPER 88-461 1) K. A. O'DONNELL (US. Army, Aeroflightdynamics Directorate, The development of head-up and head-down cockpit displays Moffett Field, CA), W. W. JOHNSON, and C. T. BENNETT (NASA, to convey symbolic status and advisory information to the pilot to Ames Research Center, Moffett Field, CA) IN: AIAA, Flight aid him in his decision to continue or abort takeoff is described. It Simulation Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, also describes a pilot-in-the-loop evaluation of the displays using Technical Papers. Washington, DC, American Institute of the NASA Langley transport systems research vehicle fixed-base Aeronautics and Astronautics, 1988, p. 325-331. refs simulator. It was found that the head-up display was monitored (AIAA PAPER 88-4634) with little effort and did not obstruct or distract from the runway The effect of perspective displays on flight performance is scene. K.K. investigated using two simulation experiments. In the first, a perspective grid display was superimposed on computer-generated A88-53657# terrain and subjects attempted to maintain their initial attitude in a REAL-TIME SIMULATION - A TOOL FOR DEVELOPMENT AND simulated hover using terrain and/or one of four grid patterns. VERIFICATION Horizontal lines produced the best attitude control performance. DAVID R. BLOEM and ROBERT NAIGUS (SLI Avionics System In the second experiment, a square grid was studied in combination Corp., Grand Rapids, MI) IN: AIAA, Flight Simulation Technologies with various visual display configurations and grid attachment Conference, Atlanta, GA, Sept. 7-9, 1988, Technical Papers. conditions. It was found that performance with the panel-mounted Washington, DC, American Institute of Aeronautics and display was significantly worse than with the out-the-window or Astronautics, 1988, p. 244-249. helmet-mounted displays. The results suggested that the partial (AIAA PAPER 88-4618) grid attachment condition improved hovering performance with the A baseline real-time laboratory simulation tool for the panel-mounted display. K.K. development and verification of avionics systems ranging from a flight management system to a navigation attack system is A88-53847' National Aeronautics and Space Administration. described. This tool is used for all aspects of product development Langley Research Center, Hampton, Va. including system/software development, full system verification and THE APPLICATION OF CRYOGENICS TO HIGH REYNOLDS validation, on-site flight test support, and field customer training NUMBER TESTING IN WIND TUNNELS. II - DEVELOPMENT support. The laboratory design methodology and its associated AND APPLICATION OF THE CRYOGENIC WIND TUNNEL configuration are discussed as well as specific design features of CONCEPT the real-time simulation. K.K. R. A. KILGORE and D. A. DRESS (NASA, Langley Research Center, Hampton, VA) Cryogenics (ISSN 001 1-22754 Sept. 1984, p. A88-53658# 484-493. refs SIMULATOR TRANSPORT DELAY MEASUREMENT USING The development and application of the cryogenic wind tunnel STEADY-STATE TECHNIQUES concept at the Langley Research Center are described. Particular WILLIAM V. JOHNSON and MATTHEW S. MIDDENDORF (Systems attention is given to the low-speed cryogenic tunnel and the pilot Research Laboratories, Inc., Dayton, OH) IN: AIAA, Flight transonic cryogenic tunnel. The major conclusions with respect to Simulation Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, the operation and performance of the pilot transonic cryogenic Technical Papers. Washington, DC, American Institute of tunnel after almost 4000 h of operation at cryogenic temperatures Aeronautics and Astronautics, 1988, p. 250-254. are that: (1) purging, cooldown, and warm-up times are acceptable (AIAA PAPER 88-4619) and can be predicted with good accuracy, and that (2) the quantity This paper describes a flight simulator transport delay of liquid nitrogen required for cooldown and running can be measurement technique along with detailed apparatus descriptions predicted with good accuracy. The U.S. National Transonic Facility and application considerations. The frequency domain method is described in detail. K.K. described was used to measure the delay in a flight simulator used for research investigating temporal fidelity effects on human A88-54280# performance. The transport delay is differentiated from the total ACQUISITION OF UNSTEADY PRESSURE MEASUREMENTS delay in the system. Further, time delay contributions from each FROM A HIGH SPEED MULTI-STAGE COMPRESSOR part of the simulation are described. Author WILLIAM W. COPENHAVER and CHRISTOPHER J. WORLAND (USAF, Aero Propulsion Laboratory, Wright-Patterson AFB, OH) A88-53659# ASME, Gas Turbine and Aeroengine Congress and Exposition, DETERMINATION OF HELICOPTER SIMULATOR TIME DELAY Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs AND ITS EFFECTS ON AIR VEHICLE DEVELOPMENT (ASME PAPER 88-GT-189) JOHN WOLTKAMP, S. RAMACHANDRAN, and ROGER BRANSON Two methods for acquiring transient pressure measurements (McDonnell Douglas Helicopter Co., Mesa, AZ) IN: AIAA, Flight from a high speed multi-stage compressor are presented. Data Simulation Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, were obtained from upstream, inter-stage and downstream Technical Papers. Washington, DC, American Institute of measurement locations on the compressor during unsteady Aeronautics and Astronautics, 1988, p. 255-263. refs operation. The two methods of data acquisition were real time (AIAA PAPER 88-4620) digital conversion of close coupled pressures and frequency The system architecture, techniques of measuring throughput modulated (FM) analog recording of high response measurements.

833 09 RESEARCH AND SUPPORT FACILITIES (AIR)

The close coupled measurements provide for a nominal frequency because of differences in size, Reynolds number capability, running response of 70 Hz while the high response measurements provided time, and test objectives. Many of the methods of boundary-layer 200 Hz nominal response. A description of both acquisition systems control developed in two-dimensional airfoil testing can be applied is provided with discussion of the limitations involved in both in tests of transport configurations, but sometimes the methods. Examples and comparisons of data obtained by both three-dimensional flow fields that develop on tranpsort aircraft can methods are presented. Author make application of the two-dimensional methods difficult or impossible. The discussion is intended to be a representative, but A88-54357# not exhaustive, survey of the various methods of high Reynolds A NEW METHOD OF MODELING UNDEREXPANDED number simulation in the testing of high-aspect-ratio aircraft. EXHAUST PLUMES FOR WIND TUNNEL AERODYNAMIC Author TESTING V. SALEMANN and J. M. WILLIAMS (Boeing Co., Seattle, WA) N88-28861# British Aerospace Public Ltd. Co., Weybridge ASME, Gas Turbine and Aeroengine Congress and Exposition, (England). Aircraft Group. Amsterdam, Netherlands, June 6-9, 1988. 10 p. refs COMPLEX CONFIGURATIONS (Contract F33615-84-C-0518) A. G. T. CROSS In AGARD, Boundary Layer Simulation and (ASME PAPER 88-GT-288) Control in Wind Tunnels p 50-67 Apr. 1988 A method for modeling hot underexpanded exhaust plumes Avail: NTlS HC A20/MF A01 with cold model scale plumes has been developed to support a The practice of simulating high flight Reynolds number behavior wind tunnel test of a rocket powered crew ejection seat. The in a low Reynolds number facility is well known. However the method involves scaling the model and nozzle external geometry problems now encountered at transonic speeds are considerable (including the nozzle exit area), matching the model dynamic and vary for different model designs such that it is difficult to pressure ratio to the full-scale dynamic pressure ratio, and matching predict with real confidence the actual flight conditions. In two the model thrust coefficient to the full-scale thrust coefficient. A dimensions these scale effects become more apparent as the generalized method-of-characteristics computer code was used to degree of supercritical flow is increased and in particular with determine the plume shapes of both a hot half-scale nozzle of rearward movement of shocks. In three dimensions the problems area ratio 3.2 and a cold model scale nozzle of area ratio 1.3. R.R. are more severe particularly when wing sweep is high due to vortex and turbulent attachment line flows, both of which are Reynolds number dependent and when complex configurations A88-54384# are considered the potential for scale sensitive effects is NAVY V/STOL ENGINE EXPERIENCE IN ALTITUDE TEST considerable owing to the many regions where flow separation FACILITY can occur. The designer will often seek to avoid scale sensitive WILLIAM H. CUNNINGHAM and JOSEPH F. BOYTOS (U.S. Navy, flow separations in model tests and this amounts to designing for Naval Air Propulsion Center, Trenton, NJ) ASME, Gas Turbine low Reynolds number with a reduction in the potential gains to be and Aeroengine Congress and Exposition, Amsterdam, had for design for full scale. By furthering the understanding of Netherlands, June 6-9, 1988. 12 p. scale effects more realiable use can be made of Reynolds number (ASME PAPER 88-GT-317) simulation techniques, so enabling design for conditions closer to The Pegasus V/STOL Engine used in the AV-EB/GR MK5 full scale with significant gains in flight performance. The current Harrier II Aircraft presents several unique installation requirements practice with regard to high Reynolds number simulation in for testing in an Altitude Test Facility. These requirements are transonic wind tunnels for industrial standards of testing relating dictated by the fact that the Pegasus engine has four separate to complex aircraft configurations is reviewed. Author exhaust nozzles, and the short, highly-curved Harrier inlet creates unusual inlet distortion conditions.The Naval Air Propulsion Center has designed and fabricated equipment which has been used to N88-28865# National Research Council of Canada, Ottawa test the Pegasus engine under simulated altitude conditions. During (Ontario). engine testing, problems were encountered with the rear nozzle COMPUTATIONAL TOOLS FOR SIMULATION exhaust collectors and the proposed solutions are presently being METHODOLOGIES implemented. This paper describes the development of the Navy Y. Y. CHAN In AGARD, Boundary Layer Simulation and Control capability to test the Pegasus engine in an uninstalled performance in Wind Tunnels p 115-131 Apr. 1988 configuration, and with total pressure distortion screens; with aircraft Avail: NTlS HC A20/MF A01 accessories loaded; and with a mock-up of the AV-8B aircraft In the brief review of the computational capabilities for viscous inlet to determine the effects of combined total and static pressure flows, it was shown that the methods of solution of the governing distortion on engine performance and surge margin. Author equations were well developed. Turbulence modeling is adequate for simple flows, though further verification and developments are N88-28859*# National Aeronautics and Space Administration. still needed for complex flows. Interactions of viscous and inviscid Langley Research Center, Hampton, Va. flows, which are basic characteristics of transonic flows are HIGH-ASPECT-RATIO WINGS propertly formulated and analyzed. Attached flows can be predicted JOHN B. PETERSON, JR. In AGARD, Boundary Layer Simulation accurately for a wide range of Reynolds numbers. Flows with and Control in Wind Tunnels p 21-29 Apr. 1988 moderate separations near the leading or trailing edges and the Avail: NTlS HC A2O/MF A01 CSCL 148 shock wave-boundary layer interactions can be treated by the High-aspect-ratio aircraft include most transport aircraft such interactive methods. Methods for two-dimensional flows are better as commercial and military transports, business aircraft, and cargo developed while three-dimensional and unsteady flow methods are aircraft. Generally, these types of aircraft are designed to cruise showing rapid progress. In general, computations can be applied over a narrow range of lift coefficients and Mach numbers in the to simple configurations or components of a complex configuration. performance of their mission. Emphasis is therefore placed on The interaction of computational simulations with wind tunnel test the cruise performance of transport aircraft and every effort is programs has effectively augmented the capabilities of these tests. made to obtain accurate wind-tunnel data to use as a basis for The information provided by computations is now essential for prediction of full-scale cruise performance. However, off-cruise design and checking of the test and for interpretation and performance is also important and methods were developed for extrapolation of the results. Due to strict requirement of accuracy extrapolating wind-tunnel data on buffet and flutter at transonic in aerodynamic tests, applications of computation are limited, at speed. Transport-type aircraft were tested extensively in various present, to stimulation of attached flows. For complex flow wind tunnels around the world and many different test techniques simulations, especially with flow separation, further development were developed to simulate higher Reynolds numbers. Methods is needed in better understanding the physical nature of the flow developed for one tunnel may not be applicable to another tunnel and its modeling. Author a34 09 RESEARCH AND SUPPORT FACILITIES (AIR)

N88-28933"# Applied Cryogenics and Materials Consultants, velocimeter (LDV) data taken in earlier studies. The tests were Inc., Hampton, Va. conducted at three inlet angles from near design incidence towards TECHNOLOGY FOR PRESSURE-INSTRUMENTED THIN the expected stall condition at a Mach number of 0.25 and Reynolds AIRFOIL MODELS Final Report number of about 700,000. Wake profiles were obtained from 0.08 DAVID A. WIGLEY Washington Sep. 1988 42 p to 0.2 chord lengths downstream of the blade. Good agreement (Contract NASl-18066) was found with LDV measurements. Measurements at the highest (NASA-CR-4173; NAS 1.26:4173) Avail: NTlS HC A03/MF A01 incidence angle showed that the wake constituted one third of CSCL 148 the flow and yet no separation occurred before the trailing edge A novel method of airfoil model construction was developed. on the suction side of the blade. G RA This Laminated Sheet technique uses 0.8 mm thick sheets of A286 containing a network of pre-formed channels which are N88-29742# British Aerospace Public Ltd. Co., Preston vacuum brazed together to form the airfoil. A 6.25 percent model (England). of the X29A canard, which has a 5 percent thick section, was THE ROLE OF SIMULATION IN FLYING QUALITIES AND built using this technique. The model contained a total of 96 FLIGHT CONTROL SYSTEM RELATED DEVELOPMENT pressure orifices, 56 in three chordwise rows on the upper surface A. G. BARNES ln AGARD, Advances in Flying Qualities 21 p and 37 in three similar rows on the lower surface. It was tested May 1988 in the NASA Langley 0.3 m Transonic Cryogenic Tunnel. Unique Avail: NTlS HC AO9/MF A01 aerodynamic data was obtained over the full range of temperature Flight simulation makes a vital contribution to the understanding and pressure. Part of the data was at transonic Mach numbers of flying quality requirements and to the clearance of modern and flight Reynolds number. A larger two dimensional model of aircraft flight controls. The background to the use of simulators, the NACA 64a-105 airfoil section was also fabricated. Scale up both airborne and ground based is presented, and the experimental presented some problems, but a testable airfoil was fabricated. techniques, including validation and hardware requirements are Author discussed. The limitations which equipments can impose are presented, and examples are given of the use of flight simulation N88-28934# Massachusetts Inst. of Tech., Lexington. in flying qualities research. Finally, the techniques required for the AIRPORT SURFACE TRAFFIC AUTOMATION STUDY clearance of current designs are highlighted, and a direction for WALTER M. HOLLISTER 9 May 1988 80 p future research is indicated. Author (Contract F19628-85-C-0002) (AD-A194553; ATC-156; DOT/FAA/PS-87/1) Avail: NTlS HC N88-29820"# National Aeronautics and Space Administration. A05/MF A01 CSCL 17G Langley Research Center, Hampton, Va. This report documents a study of requirements for an Airport COMPUTER PROGRAMS FOR CALCULATION OF STING Surface Traffic Automation (ASTA) system. The objective was to PITCH AND ROLL ANGLES REQUIRED TO OBTAIN ANGLES determine the necessary functions, establish the cost and benefits, OF ATTACK AND SIDESLIP ON WIND TUNNEL MODELS and outline a modular system design. The highest priority function JOHN B. PETERSON, JR. Jul. 1988 47 p identified was an improved surface surveillance and communication (NASA-TM-100659; NAS 1.15:100659) Avail: NTlS HC AO3/MF system. The greatest potential for safety benefits is provided by A01 CSCL14B automatic conflict alert and collision warning for pilots and Two programs have been developed to calculate the pitch controllers to prevent runway incursion accidents. Strategic and and roll angles of a wind-tunnel sting drive system that will position tactical planning assistance to maximize runway utilization can a model at the desired angle of attack and and angle of sideslip improve controller productivity while keeping them responsible for in the wind tunnel. These programs account for the effects of final decisions. The report contains a modular design for ASTA sting offset angles, sting bending angles and wind-tunnel stream and includes specifications for a man-in-the loop simulation of the flow angles. In addition, the second program incorporates inputs system. GRA from on-board accelerometers that measure model pitch and roll with respect to gravity. The programs are presented in the report N88-28935# Naval Postgraduate School, Monterey, Calif. and a description of the numerical operation of the programs with FLOW VISUALIZATION ON A SMALL SCALE M.S. Thesis a definition of the variables used in the programs is given. ROY L. HIXSON, 111 Mar. 1988 42 p Author (AD-A194728) Avail: NTlS HC A03/MF A01 CSCL 148 A quarter scale model of the planned renovated form of an N88-29821*# Stanford Univ., Calif. Dept. of Aeronautics and existing flow visualization tunnel was designed and constructed to Astronautics. test the quality of flow and for small scale research and flow AN EXPERIMENTAL STUDY OF AN ADAPTIVE-WALL WIND visualization demonstrations. Three flow visualization techniques TUNNEL were developed, including fog injection, helium bubbles, and smoke ZEKl CELIK and LEONARD ROBERTS Aug. 1988 155 p wire. In addition to velocity calibration and test section mapping (Contract NCC2-77) of the tunnel, the latter two of these methods were used for (NASA-CR-183152; NAS 1.26:183152; JIAA-TR-87) Avail: NTlS visualizing flows around three different shaped bodies as HC AOWMF A01 CSCL 148 demonstration that the tunnel's design objectives were realized. A series of adaptive wall ventilated wind tunnel experiments Both techniques produced excellent photographic results of flows was carried out to demonstrate the feasibility of using the side around a block of rectangular cross section, a circular cylinder wall pressure distribution as the flow variable for the assessment and an airfoil. GRA of compatibility with free air conditions. Iterative and one step convergence methods were applied using the streamwise velocity N88-28936# Naval Postgraduate School, Monterey, Calif. component, the side wall pressure distribution and the normal HOT-WIRE MEASUREMENTS OF COMPRESSOR BLADE velocity component in order to investigate their relative merits. WAKES IN A CASCADE WIND TUNNEL M.S. Thesis The advantage of using the side wall pressure as the flow variable ADEM BAYDAR Mar. 1988 58 p is to reduce the data taking time which is one the major contributors (AD-A194737) Avail: NTlS HC A04/MF A01 CSCL 148 to the total testing time. In ventilated adaptive wall wind tunnel A hot-wire system, with software designed for calibrating and testing, side wall pressure measurements require simple taking data with single, double and triple hot-wire sensors instrumentation as opposed to the Laser Doppler Velocimetry used separately, or three probes at once, was verified and used to to measure the velocity components. In ventilated adaptive wall make wake measurements downstream of a compressor stator tunnel testing, influence coefficients are required to determine the blade in a cascade wind tunnel. Using a single hot-wire probe, pressure corrections in the plenum compartment. Experiments were velocity and turbulence data were obtained in the wake of the carried out to evaluate the influence coefficients from side wall controlled-diffusion blade in order to verify laser Doppler pressure distributions, and from streamwise and normal velocity

835 09 RESEARCH AND SUPPORT FACILITIES (AIR)

distributions at two control levels. Velocity measurements were A. HENDERGOTT, E. STANEWSKY, and E. WEDEMEYER Apr. made using a two component Laser Doppler Velocimeter system. 1987 15p Author (18-222-87-A-08) Avail: NTlS HC AO3/MF A01 Wind tunnel tests in the rubber tube test section have been performed in order to investigate the possibility of reducing N8&29822# AeroVironment, Inc., Monrovia, Calif. supersonic wall interferences by adaptation of the rubber walls. DEVELOPMENT AND DESIGN OF WINDTUNNEL AND TEST FACILITY FOR RPV (REMOTE PILOTED VEHICLE) Although the spacing of the jack positions is not sufficiently close ENHANCEMENT DEVICES Final Report, 15 Sep. 1987 15 for the supersonic wall adaptation, encouraging results were - obtained for a cone-cylinder model. Apr. 1988 Author BART D. HIBBS, HERMAN M. DREES, and PETER B. LISSAMAN 15 Apr. 1988 59 p N88-29825*# Southwest Research Inst., San Antonio, Tex. (Contract DAAHOl-87-C-1049; ARPA ORDER 5916) SPRAY AUTOMATED BALANCING OF ROTORS METHODS (AD-A194842; AV-FR-88/807) Avail: NTlS HC A04/MF A01 AND MATERIALS Final Report CSCL 148 ANTHONY J. SMALLEY, RICHARD M. BALDWIN, and WILBUR Viscous drag represent a significant power demand on flight R. SCHICK Aug. 1988 122 p vehicles. Reductions of this requirement could result in higher (Contract NAS3-25069; DA PROJ. 1L1-62209-AH-76) speeds and altitudes, longer endurance and heavier payloads. (NASA-CR-182151; NAS 1.26:182151; AVSCOM-TR-88-C-018) General streamlining by shape control is highly developed so that Avail: NTlS HC AO6/MF A01 CSCL 148 the viscous drag of most vehicles consists mainly of turbulent The work described consists of two parts. In the first part, a skin friction. Recent work in surface (riblets, etc.) and near-surface survey is performed to assess the state of the art in rotor balancing (vortex generator, etc.) devices has indicated that even this drag technology as it applies to Army gas turbine engines and associated level can be further reduced by modifying the turbulent process power transmission hardware. The second part evaluates thermal near the surface. Drag reductions of about seven percent have spray processes for balancing weight addition in an automated been claimed for riblets and have been generally supported by balancing procedure. The industry survey reveals that: (1) various experiments. Engineering applications of these devices computerized balancing equipment is valuable to reduce errors, shows great potential, but to date have not been extensively improve balance quality, and provide documentation; (2) slow-speed pursued because of lack of definitive data. Remote Piloted Vehicles balancing is used exclusively, with no forseeable need for (RPV’s) would benefit from these devices, but operate over a production high-speed balancing; (3) automated procedures are Reynolds number range such that much standard aeronautical desired; and (4) thermal spray balancing is viewed with cautious research is inapplicable. A new facility is required to test and optimism whereas laser balancing is viewed with concern for flight develop new devices appropriate for RPV’s. This facility should propulsion hardware. The FARE method (FueVAir Repetitive be capable of testing, with and without pressure gradients, over Explosion) was selected for experimental evaluation of bond the necessary range of scales and speeds with sufficient accuracy strength and fatigue strength. Material combinations tested were that engineering design decisions can be made about existing tungsten carbide on stainless steel (17-4), lnconel 718 on lnconel devices and improved, advanced units to be developed. A special 718, and Triballoy 800 on lnconel 718. Bond strengths were entirely purpose closed-return wind tunnel has been designed with a 26 adequate for use in balancing. Material combinations have been foot long, 4 foot by 4 foot working cross-section driven by a 40 identified for use in hot and cold sections of an engine, with HP motor and operating at speeds up to 120 ft/sec. GRA fatigue strengths equivalent to those for hand-ground materials. Author N88-29823# Air Force Inst. of Tech., Wright-Patterson AFB. Ohio. CONTROLLED DEGRADATION OF RESOLUTION OF HIGH-QUALITY FLIGHT SIMULATOR IMAGES FOR TRAINING EFFECTIVENESS EVALUATION M.S. Thesis 10 DENNIS D. KAlP 1988 66 p (AD-A1961 89; AFIT/CI/NR-88-46) Avail: NTlS HC A04/MF A01 ASTRONAUTICS CSCL 051 A flight simulator is a device used to train pilots and air Includes astronautics (general); astrodynamics; ground support crews without the use of an actual aircraft. The use of flight systems and facilities (space); launch vehicles and space vehicles; simulators for training is widespread in both the military and civilian space transportation; spacecraft communications, command and sector. The use of flight simulators has significant advantages tracking; spacecraft design, testing and performance; spacecraft over the operation of the actual aircraft. In addition, pilots and air instrumentation; and spacecraft propulsion and power. crews can practice complex and/or dangerous maneuvers in a flight simulator without risking loss of life or aircraft. As described by Schachter 6. sophisticated flight simulators recreate most of A88-53 105# the aspects of flying: aircraft instruments, motion of the aircraft, COMBINED ENGINES FOR FUTURE LAUNCHERS gravitational forces, radar, and out-the-window views. Most modern MARCEL F. POULIQUEN (Societe Europeenne de Propulsion. flight simulators use computer generated imagery (CGI) to produce Suresnes, France), MICHEL DOUBLIER (SNECMA, Corbeil, the out-the-window views in real-time in response to inputs from France), and DOMINIQUE SCHERRER (ONERA, flight controls. The imagery can be displayed in a variety of ways: Chatillon-sous-Bagneux, France) AIAA, ASME, SAE, and ASEE, on large CRTs, projected onto the inside of a dome, or through Joint Propulsion Conference, 24th, Boston, MA, July 11-13, 1988. helmet-mounted displays. Different training tasks are presumed to 6 P. have different requirements with respect to brightness, contrast, (AIAA PAPER 88-2823) and resolution. The goal for visual display flight training simulators In 1986, studies were initiated in France under CNES (Centre in general. is not realism, but training effectiveness. Therefore, National d’Etudes Spatiales) contract to evaluate new propulsion the design requirements for flight simulators should take into concepts for Advanced Space Transportation Systems. A number consideration the desired training task. GRA of combined engine cycles using airbreathing and rocket propulsion were listed and a systematic analysis of the most promising N88-29824# Deutsche Forschungs- und Versuchsanstalt fuer concepts was initiated. At the moment, the airturborocket, the Luft- und Raumfahrt, Goettingen (West Germany). airturborocket-ram-rocket, the airturboexpander-ram-rocket have SUPERSONIC WALL ADAPTATION IN THE RUBBER TUBE been evaluated. The paper gives the main results and describes TEST SECTION OF THE DFVLR GOETTINGEN the arrangement of the concepts. Author

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A88-54567" Georgia Inst. of Tech., Atlanta. with mechanical properties from the microscopic point of view. It TRAJECTORY OPTIMIZATION AND GUIDANCE LAW was found that the fatigue life is governed by the internal microcrack DEVELOPMENT FOR NATIONAL AEROSPACE PLANE or void formation, hence the fatigue life in the case of cumulative APPLICATIONS loading can be estimated by the inspection of inner microcracks. A. J. CALISE, J. E. CORBAN, and G. A. FLANDRO (Georgia Final fracture at higher stress amplitude is initiated from the Institute of Technology, Atlanta) IN: 1988 American Control specimen interior like composites and not like metals. Author Conference, 7th, Atlanta, GA, June 15-17, 1988, Proceedings. Volume 2. New York, Institute of Electrical and Electronics A88-53164# Engineers, 1988, p. 1406-141 1. refs FLAME STABILIZATION IN SUPERSONIC COMBUSTION (Contract NAG1-784) M. BARRERE and A. MESTRE (ONERA. Chatillon-sous-Bagneux, The problem of onboard trajectory optimization for an France) La Recherche Aerospatiale (English Edition) (ISSN airbreathing, single-stage-to-orbit vehicle is examined. A simple 0379-38OX), no. 1, 1988, p. 1-13. refs model representative of the aerospace plane concept, including a The nature of procedures thus far identified for the stabilization dual-mode propulsion system composed of scramjet and rocket of flames in supersonic flow is discussed, and their applications engines, is presented. Consideration is restricted to hypersonic in various supersonic combustor-stabilization systems are analyzed. flight within the atmosphere. An energy state approximation is These considerations are of prominent importance in the design used in a four-state model for flight of a point mass in a vertical optimization of scramjet engines, whether fueled by such plane. Trajectory constraints, including those of dynamic pressure conventional hydrocarbon fuels as kerosene or by hydrogen. Both and aerodynamic heating, are initially ignored. Singular perturbation the step technique, which establishes stagnant areas in the methods are applied in solving the optimal control problem of recirculation kernels and low velocity areas in the boundary layers, minimum fuel climb. The resulting reduced solution for the energy and the creation of pockets or vortices in the flow, are considered state dynamics provides an optimal altitude profile dependent on to be useful methods for combustion stabilization. O.C. energy level and control for rocket thrust. A boundary-layer analysis produces an approximate lift control solution in feedback form and accounts for altitude and flight path angle dynamics. The A88-53542 reduced solution optimal climb path is presented for the C/C COMPOSITE MATERIALS FOR AIRCRAFT BRAKES unconstrained case and the case for which a maximum dynamic SHRIKANT AWASTHI and JERRY L. WOOD (Allied-Signal pressure constraint is enforced. I.E. Aerospace Co., Bendix Wheels and Brakes Div., South Bend, IN) Advanced Ceramic Materials (ISSN 0883-5551), vol. 3, Sept. 1988, p. 449-451. C/C composites can simultaneously function as aircraft landing 11 gear brakes' friction materials, heat sinks, and structural components. The important C/C composite brake performance CHEMISTRY AND MATERIALS parameters of peak torque, oxidation characteristics, and stability, among others, are controlled through engineering of the composition and processing of the material. The heat capacity of Includes chemistry and materials (general); composite materials; C/C brakes is 2.5 times that of steel, while its strength at elevated inorganic and physical chemistry; metallic materials; nonmetallic temperatures is 2 times that of steel; 40-percent weight savings materials; and propellants and fuels. over conventional steel brakes are thereby obtainable. O.C.

A8842655 A88-53556 FATIGUE OF ELEVATED TEMPERATURE POWDER NICRAL/BENTONITE THERMAL SPRAY POWDER FOR HIGH METALLURGY ALUMINUM ALLOY MECHANICALLY TEMPERATURE ABRADABLE SEALS FASTENED JOINTS M. A. CLEGG and M. H. MEHTA (Sherritt Gordon Mines, Ltd., J. C. EKVALL and L. BAKOW (Lockheed-California Co., Burbank) Fort Saskatchewan, Canada) IN: Thermal spray: Advances in IN: New materials and fatigue resistant aircraft design; Proceedings coatings technology; Proceedings of the National Thermal Spray of the Fourteenth ICAF Symposium, Ottawa, Canada, June 8-12, Conference, Orlando, FL, Sept. 14-17, 1987. Metals Park, OH, 1987. Warley, England, Engineering Materials Advisory Services, ASM International, 1988, p. 41-45. Research supported by the Ltd., 1987. p. 151-1 75. National Research Council of Canada. refs (Contract F33615-83-C-3200) The function and basic requirements of turbine engine clearance Results are presented for constant amplitude fatique tests control abradable seals are reviewed. For the specific case of an conducted at room temperature and 260 C on lap joint specimens abradable seal operating in the temperature range 650-850 C, the fabricated from 7075-T6 (room temperature only), CZ42 use of a thermal sprayed deposit of an alloy composite powder (AI-7.1 Fe-6.OCe) and CU78 (AI-8.3Fe-4.OCe) sheet materials. consisting of a bentonite core particle coated with an alloy layer Specimens were fabricated with NAS1200 and LSl5905 A-286 of NiCrAl is described. A series of tests were carried out to arrive flush head rivets, and A-286 and Ti-6AI-4V Hi-Loks. Variables at an optimum combination of abradability, erosion resistance, and evaluated with LSl5905 rivets included A-286 aging treatment and oxidation resistance in the thermal sprayed deposit. The selected rivet head countersink angle. The NASl200 rivets provided joints composite powder consists of a closely sized bentonite core in with the best fatigue performance at both room and elevated the range 75-150 microns, coated with an alloy consisting of Ni5 temperature. Author pct Cr3 pct AI, such that the alloy coating to core ratio is 80:20 by weight. When flame sprayed by standard practice this powder A88-52657 was found to produce an abradable seal with the optimum MICROSCOPIC INNER DAMAGE CORRELATED WITH combination of desired properties. Author MECHANICAL PROPERTY DEGRADATION DUE TO SIMULATED FATIGUE LOADING IN METAL MATRIX A88-53566 COMPOSITES EXPERIMENTAL AND THEORETICAL ASPECTS OF THICK AKlRA KOBAYASHI and NOBUO OHTANI (Tokyo, University, THERMAL BARRIER COATINGS FOR TURBINE Japan) IN: New materials and fatigue resistant aircraft design; APPLICATIONS Proceedings of the Fourteenth ICAF Symposium, Ottawa, Canada, G. JOHNER, V. WILMS (Leybold AG, Hanau, Federal Republic of June 8-12, 1987. Warley, England, Engineering Materials Advisory Germany), K. K. SCHWEITZER, and P. ADAM (MTU Motoren- Services, Ltd., 1987, p. 195-214. und Turbinen-Union Muenchen GmbH, Munich, Federal Republic SiC/Aluminum composites are subjected to two-stage fatigue of Germany) IN: Thermal spray: Advances in coatings technology; loading to investigate the inner material damage in correlation Proceedings of the National Thermal Spray Conference, Orlando,

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FL, Sept. 14-17, 1987. Metals Park, OH, ASM International, 1988, special fluids; dependence of the reliability of engines on fuel p. 155-166. refs properties; characteristics of friction systems and the use of oils Thick (2 mm) plasma-sprayed yttria-stabilized-zirconia coatings and lubricants in various mechanisms; and the use and properties are shown to effectively insulate the turbine casings of small gas of fluids for hydraulic power systems, deicing liquids, and turbines. It is shown that the most ideal structure, one containing detergents. The discussion also covers the environmental aspects tetragonal and cubic phases and no monoclinic phases, can be of the use of fuels and lubricants and safety engineering in handling achieved if the powder is fully melted. A thermal barrier coating flammable materials. V.L. that is dense and exhibits a fine network of segmentation cracks can be achieved by ’hot spraying’ (which assures the complete A88-54145’# National Aeronautics and Space Administration. melting of the powder and microwelding of the individual Lewis Research Center, Cleveland, Ohio. platelets). R.R. LIFE MODELING OF THERMAL BARRIER COATINGS FOR AIRCRAFT GAS TURBINE ENGINES A8 8- 5 3 83 8 R. A. MILLER (NASA, Lewis Research Center, Cleveland, OH) MEETING THE HIGH TEMPERATURE CHALLENGE - THE IN: Toward improved durability in advanced aircraft engine hot NON-METALLIC AERO ENGINE sections; Proceedings of the Thirty-third ASME International Gas R. H. JEAL (Rolls-Royce, PLC, Derby, England) Metals and Turbine and Aeroengine Congress and Exposition, Amsterdam, Materials (ISSN 0266-7185), vol. 4, Sept. 1988, p. 539-542. Netherlands, June 5-9, 1988. New York, American Society of Substantial increases in gas turbine engine performance are Mechanical Engineers, 1988, p. 109-115. Previously announced in obtainable through the introduction of advanced, highly STAR as NEE-15060. refs refractory /low-density materials such as metal-matrix and Thermal barrier coating life models developed under the NASA ceramic-matrix composites, whose design methodologies and Lewis Research Center’s Hot Section Technology (HOST) Program manufacturing technologies are currently under intensive are summarized. An initial laboratory model and three development. It is speculated that future aircraft engines, perhaps design-capable models are discussed. Current understanding of becoming operational in the first decade of the next century, will coating failure mechanisms are also summarized. Author have a glass- or metal-matrix compressor and a ceramic turbine; design methodologies for turbine components will involve the A88-54166# design of an appropriate material as well as the component’s FLAME SPEEDS IN FUEL SPRAYS WITH HYDROGEN structure. O.C. ADDITION P. E. SOJKA, A. H. LEFEBVRE (Purdue University, West Lafayette, A8843955 IN), and G. A. RICHARDS ASME, Gas Turbine and Aeroengine EFFECT OF LOADING ASYMMETRY ON THE LOW-CYCLE Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. FATIGUE OF ZHS6F ALLOY UNDER CYCLIC TEMPERATURE 8 p. refs CHANGES [VLIIANIE ASlMMETRll NAGRUZHENIIA NA (ASME PAPER 88-GT-20) MALOTSIKLOVUIU USTALOST’ SPLAVA ZHS6F PRI The influence of hydrogen addition on the burning rates of TSIKLICHESKOM IZMENENII TEMPERATURY] kerosine sprays in air is studied experimentally. Flame speeds are A. N. VETROV and V. I. MOLODKIN (Kievskii lnstitut lnzhenerov measured as a function of fuel drop size, equivalence ratio, and Grazhdanskoi Aviatsii, Kiev, Ukrainian SSR) Problemy Prochnosti hydrogen concentration. The results obtained show that (ISSN 0556-171X), Aug. 1988. p. 46-50. In Russian. evaporation rates have a controlling effect on flame speeds over The low-cycle fatigue behavior of ZhS6F blade alloy under wide ranges of mean drop size. They also demonstrate that the asymmetric nonisothermal loading is investigated experimentally, burning rates of liquid kerosine-air mixtures are augmented and statistical estimates of lognormal thermal-cycling life distribution appreciably by the addition of small quantities of hydrogen to the of the specimens are obtained by the maximum likelihood method. air flowing into the combustion zone. Author A mathematical life model is proposed which is based on the approximation of maximum stress amplitude diagrams under A88-54167# axisymmetric low-cycle loading by a shifted-ellipse equation. A EFFECT OF MOLECULAR STRUCTURE ON SOOT comparison is made between model predictions and experimental FORMATION CHARACTERISTICS OF AVIATION TURBINE data. V.L. FUELS OMER L. GULDER, BORIS GLAVINCEVSKI (National Research A8843996 Council of Canada, Div. of Mechanical Engineering, Ottawa), and CORROSION AND PROTECTION OF GAS TURBINE BLADES SUDHAKAR DAS (Indian Institute of Petroleum, Dehradun, India) [KORROZIIA I ZASHCHITA LOPATOK GAZOVYKH TURBIN] ASME, Gas Turbine and Aeroengine Congress and Exposition, VALENTIN IL‘ICH NlKlTlN Leningrad, Izdatel’stvo Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs Mashinostroenie, 1987, 272 p. In Russian. refs (ASME PAPER 88-GT-21) The characteristics of the damage of gas turbine blades resulting The smoke point has been shown to be quantitatively related from sulfide-oxide corrosion, the mechanisms of this type of to the molecular structure of hydrocarbon fuels. Here, a fast corrosion, and its various forms are reviewed. Different types of technique for determining molecular composition of commercial anticorrosion coatings and methods for depositing such coating and experimental fuels, in terms of carbon type structure by using on the blades of gas turbines are then discussed. In particular, a proton NMR spectrometry is described. By measuring the attention is given to the possibility of extending the life of gas smoke-point soot yields of a laminar diffusion flame with a group turbine plants by using corrosion-resistant alloys, fuel additives, of fuels (all having a constant H/C ratio) it is shown that neither and surface and bulk alloying of the blades. V.L. the smoke point nor H/C ratio alone can describe the sooting propensity of turbine fuels. The results indicate that smoke point A8844001 and H/C are complementary to each other in describing the sooting PRINCIPLES OF THE USE OF FUELS AND LUBRICANTS IN propensities of turbine fuels. Author CIVIL AVIATION [OSNOVY PRlMENENllA GORIUCHE-SMAZOCHNYKH MATERIALOV V GRAZHDANSKOI A88-54225# AVIATSII] THE BLOWOUT OF TURBULENT JET FLAMES IN ALEKSEI ALEKSEEVICH LlNlNOV Moscow, Izdatel’stvo CO-FLOWING STREAMS OF FUEL-AIR MIXTURES Transport, 1987, 312 p. In Russian. refs M. G. KIBRYA, G. A. KARIM, and I. WIERZBA (Calgary, University, Various jet, diesel, gasoline, and gaseous fuels used in civil Canada) ASME, Gas Turbine and Aeroengine Congress and aviation are examined, as are lubricants and various special fluids Exposition, Amsterdam, Netherlands, June 6-9, 1988. 6 p. used in engines, systems, and mechanisms. In particular, attention NSERC-supported research. refs is given to the general characterization of fuels, lubricants, and (ASME PAPER 88-GT-106)

838 11 CHEMISTRY AND MATERIALS

The blowout limit of a turbulent jet diffusion flame in co-flowing measuring Smoke Number was made with the objective of obtaining streams of lean fuel air mixtures is examined. The blowout limit of details relevant to its accuracy and applicability. Mixtures of the flame, and thereby the maximum thermal output of a burner iso-octane and benzene were used as fuel, thereby permitting the can be extended significantly, without any modification to the effects of hydrogen content to be established. The results are burner, through the presence of a small amount of fuel correlated with others obtained previously. Author homogeneously mixed with the surrounding air. The extent of this extension is related to the observed limit of fuel concentration in the surrounding stream that brings about flame flashback A88-54269# conditions. The flame blowout limits involving different gaseous FIBER METAL ACOUSTIC MATERIALS FOR GAS TURBINE hydrocarbon fuels have been established at atmospheric pressure EXHAUST ENVIRONMENTS and the data were correlated in terms of the surrounding fuel MICHAEL S. BEATON (Brunswick Corp., Technetics Div., De Land, concentrations relative to their corresponding flashback limits. FL) ASME, Gas Turbine and Aeroengine Congress and Exposition, Author Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs (ASME PAPER 88-GT-175) A88-54226# Feltmetal fiber metal acoustic materials function as broad band EVAPORATION OF FUEL DROPLETS IN TURBULENT acoustic absorbers. Their acoustic energy absorbance occurs COMBUSTOR FLOW through viscous flow losses as sound waves pass through the S. WITTIG, W. KLAUSMANN, B. NOLL, and J. HIMMELSBACH tortuous pore structure of the material. A new Feltmetal fiber metal (Karlsruhe, Universitaet, Federal Republic of Germany) ASME, acoustic material has been designed for use in gas turbine auxiliary Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, power unit exhaust environments without supplemental colling. The Netherlands, June 6-9, 1988. 6 p. refs physical and acoustic properties of FM 827 are discussed. Exposure (Contract DFG-SFB-167) tests were conducted under conditions which simulated auxiliary (ASME PAPER 88-GT-107) power unit operation. Weight gain and tensile strength data as a Detailed measurements of a recirculating, droplet charged air function of time of exposure at 650 C are reported. Fabrication of flow within a model combustor are compared with predictions based components with fiber metal acoustic materials is easily on three different evaporation models. Similar results are obtained accomplished using standard roll forming and gas tungsten arc with the simplified d-squared law, the uniform temperature model, welding practices. Author and thin skin model for relatively short droplet-heatup phases. Discrepancies, however, are observed under conditions where the droplet heating phase is relatively long, i.e., at low temperature conditions. Extended evaporation models, therefore, are necessary A88-54277# when the ignition performance is to be analyzed. Author NEW EROSION RESISTANT COMPRESSOR COATINGS H. J. KOLKMAN (Nationaal Lucht- en Ruimtevaartlaboratorium, A88-54257# Amsterdam, Netherlands) ASME, Gas Turbine and Aeroengine FLOW IN LINER HOLES FOR COUNTER-CURRENT Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. COMBUSTION SYSTEMS 6 p. Research supported by the Royal Netherlands Air Force. N. ABUAF (General Electric Co., Schenectady, NY), N. S. refs RASMUSSEN, and L. C. SZEMA (General Electric Co., Aircraft (ASME PAPER 88-GT-186) Engine Business Group, Evendale, OH) ASME, Gas Turbine and The erosion resistance of a conventional improved Aeroengine Congress and Exposition, Amsterdam, Netherlands, aluminum-based compressor coating (Sermetel 5380 DP) and of June 6-9, 1988. 8 p. refs several new coatings, including TIN, Ti28, and tungsten carbide (ASME PAPER 88-GT-158) (WC 100 and WC 111) coatings, was investigated. The test Heavy duty gas turbine combustion systems have a 'reverse specimens were 2-mm thick AIS1 41 0 steel coupons austenitized flow' combustion-cooling air network. High-temperature gradients and tempered to a hardness of R(C) = 26. The coated and have been observed in some combustion liners around the plain uncoated specimens were tested in a compressor rig of Kolkman holes, or around the cylindrical inserts welded into the mixing (1982, 1983), in which specimens could be tested under simulated holes. Flow visualization tests were performed in a countercurrent service conditions (150 C temperature, 130 m/s air velocity, and flow facility. Measurements of pressure and velocity distributions quartz erodent with mean particle velocity of 55 m/s), and the in and around the mixing hole jet were taken, and mass flow erosion rate was measured as a function of the angle of attack rates and discharge coefficients were calculated in order to (alpha = IO, 20, 40, 60, and 90 deg). It was found that new characterize and compare the two geometries. The results with a compressor coatings exhibited lower erosion rates than the plain hole (square-edged orifice) and the cylindrical insert show conventional coating, with the Ti26 coating showing the highest the presence of a sharp separation region at the trailing edge erosion resistance. IS. (combustion side) of the liner hole, which may cause the high-temperature gradients observed under operating conditions. The measured discharge coefficients show a dependence on the A88-54282# insert geometry, the flow parameter (K). and the bottom section WHISKER ORIENTATION MEASUREMENTS IN INJECTION (combustion side) counter-current flow velocity. Author MOLDED S13N4-SIC COMPOSITES J. T. NEIL and D. A. NORRIS (GTE Laboratories, Inc., Waltham, A88-54262# MA) ASME, Gas Turbine and Aeroengine Congress and NOTES ON THE OCCURRENCE AND DETERMINATION OF Exposition, Amsterdam, Netherlands, June 6-9, 1988. 6 p. CARBON WITHIN GAS TURBINE COMBUSTORS (Contract DE-AC05-840R-21400) J. ODGERS and E. R. MAGNAN (Universite Laval, Quebec, (ASME PAPER 88-GT-193) Canada) ASME, Gas Turbine and Aeroengine Congress and Hot pressed composites of Si3N4 containing 30 percent SIC Exposition, Amsterdam, Netherlands, June 6-9, 1988. 7 p. whiskers have shown substantial improvements in strength and NSERC-supported research. refs fracture toughness relative to monolithic silicon nitride. Injection (ASME PAPER 88-GT-164) molded samples made of this composite material distorted in a Details are presented of two series of experiments to investigate systematic manner during densification by hot isostatic pressing. carbon determination in gas turbine combustion chambers. The Whisker orientation and aspect ratio measurements based on first series employed a gravimetric technique to examine carbon digitized SEM micrographs were used to evaluate microstructure distribution within the various zones of a combustor with the aim with respect to injection molding direction. Results show definite of identifying zones of formation and oxidation. In the second orientation of whiskers during injection molding which can be related series a fairly comprehensive investigation of the technique of to the observed densification distortion. Author

839 11 CHEMISTRY AND MATERIALS

A88-54283# Angeles, CA, Nov. 9-13, 1987. Metals Park, OH, ASM International, THE PERFORMANCE OF A SURROGATE BLEND IN 1987, p. 109-114. refs SIMULATING THE SOOTING BEHAVIOR OF A PRACTICAL, A Naval aircraft main landing gear fitting failed upon landing DISTILLATE JP-4 after five years of service. Examination of the aluminum 7049 T73 C. P. WOOD and G. S. SAMUELSEN (California, University, die forging revealed an unusual brittle fracture zone located at Irvine) ASME, Gas Turbine and Aeroengine Congress and the forging parting plane. The intergranular fracture surface had Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs the appearance of a stress corrosion crack in a material thought (Contract FO8635-86-C-0309; NO0140-83-C-9151) to be resistant to such attack. The results of extensive examination (ASME PAPER 88-GT-194) and testing are evaluated. Residual tensile stress and less than A surrogate fuel has been developed to simulate the atomization optimum heat treatment appear to have contributed to the parting and combustion performance of a practical petroleum distillate plane failure. Theories, including stress corrosion cracking, JP-4. The surrogate is comprised of fourteen pure hydrocarbons corrosion fatigue and hydrogen assisted cracking, are offered to and formulated to reproduce the distillation curve and compound explain the unexpected morphology of the initial fracture surface. class composition of the parent petroleum distillate fuel. The Author present study addresses the sooting performance of the two fuels, as well as that of two reference fuels (isooctane and a high aromatic N88-28979# Dornier-Werke G.m.b.H., Oberpfaffenhofen (West petroleum JP-5) of purposefully disparate properties. The sooting Germany). Claudius Dornier Seastar. performance of the petroleum and surrogate JP-4 are nearly DEVELOPMENT OF A GLASS FIBER WING FOLLOWING THE identical and distinctly different from that of either the isooctane CONSTRUCTION REGULATION FAR PART 23 or the JP-5. The surrogate represents, as a result, an attractive [ ENTWICKLUNG EINES GLASFASERTRAGFLUEGELS NACH fuel blend for the study of fuel compositional effects on the FAR PART 231 combustion performance of practical fuels in spray-fired H. LUCAS 1986 31 p In GERMAN Presented at the 4th combustor. Author BMFT Statusseminars, Munich, Fed. Republic of Germany, 28-30 Apr. 1986 A8844351# (Contract BMFT-LFK-8531) THERMAL BARRIER COATINGS FOR JET ENGINES (ETN-88-92966) Avail: NTlS HC A03/MF A01 F. C. TORIZ, A. B. THAKKER, and S. K. GUPTA (Rolls-Royce, A wing was developed for the amphibious aircraft Seastar using Inc., Atlanta, GA) ASME, Gas Turbine and Aeroengine Congress low pressure processing (LPP) of fiber reinforced plastics. The and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 9 p. fundamentals and the development of the LPP technique are refs outlined. The technical and economic advantages of the LPP (ASME PAPER 88-GT-279) technique are explained. The application of the LPP construction Recent research aimed at the development of thermal barrier method to aircraft following the regulation FAR Part 23 is outlined. coatings (TBC) for vane airfoils and rotating turbine blades is It is shown that the LPP technique fulfils regulation requirements reviewed. Particular attention is given to the work done on the and is suited for any type of high quality vehicle cell. ESA prevention of coating failure to the thermal cycling, oxidation of the bond coat, erosion due to gas stream solid particles, deposition N88-28983'# Douglas Aircraft Co., Inc., Long Beach, Calif. of gas stream molten debris, and acid leaching of coating phase CRITICAL JOINTS IN LARGE COMPOSITE PRIMARY stabilizers. Attention is also given to the objectives of minimizing AIRCRAFT STRUCTURES. VOLUME 1: TECHNICAL SUMMARY the performance losses due to rough coatings and insuring the Final Report consistently high quality of the coatings. The TBC systems BRUCE L. BUNIN Sep. 1985 64 p discussed include chromia silica titania, ceria yttria stabilized (Contract NASl-16857) zirconia, magnesia stabilized zirconia, yttria stabilized zirconia, and (NASA-CR-3914; NAS 1.26:3914; ACEE-26-FR-3504) Avail: zirconia titania yttria. V.L. NTlS HC A04/MF A01 CSCL 11D A program was conducted at Douglas Aircraft Company to develop the technology for critical joints in composite wing structure A88-54364# that meets all the design requirements of a 1990 commercial TURBOMACHINERY ALLOYS AFFECTED BY SOLID transport aircraft. In fulfilling this objective, analytical procedures PARTICLES for joint design and analysis were developed during Phase 1 of W. TABAKOFF (Cincinnati, University, OH) ASME, Gas Turbine the program. Tests were conducted at the element level to supply and Aeroengine Congress and Exposition, Amsterdam, the empirical data required for methods development. Large Netherlands, June 6-9, 1988. 8 p. DOE-supported research. refs composite multirow joints were tested to verify the selected design (ASME PAPER 88-GT-295) In operating gas turbine engines in dusty environments, severe concepts and for correlation with analysis predictions. The Phase 2 program included additional tests to provide joint design and erosion of compressor and turbine components results. This erosion analysis data, and culminated with several technology adversely affects engine Performance. Predicting erosion in the demonstration tests of a major joint area representative of a rotating machine of gas turbine is a complex problem. This paper commercial transport wing. The technology demonstration program presents test data from the high temperature material erosion of Phase 2 is discussed. The analysis methodology development, facility at the University of Cincinnati. Data were obtained between structural test program, and correlation between test results and a target temperature of ambient and 649 C (1200 F) for AM355, Rene 41 and L605 cobalt. In addition, particle velocity and analytical strength predictions are reviewed. Author impingement angle were varied. Author N88-29004# Aptech Engineering Services, Inc., Sunnyvale, Calif. A88-54857# STRESS INTENSITY FACTORS FOR CRACKED METALLIC COMPOSITES BREAK THE ICE STRUCTURES UNDER RAPID THERMAL LOADING Final RICHARD DEMEIS Aerospace America (ISSN 0740-722X), vol. Report, Aug. 1986 - May 1987 26, Sept. 1988, p. 46, 47. RUSSELL C. CIPOLLA and KIMBLE J. CLARK Oct. 1987 75 p (Contract F33615-86-C-3217) A8845286 (AD-A191 219; AES-8609709F-1; AFWAL-TR-87-3059) Avail: SERVICE FAILURE OF A 7049 T73 ALUMINUM AIRCRAFT NTlS HC A04/MF A01 CSCL 20K FORGING High intensity heating of aircraft structures can challenge the M. L. MCCARTHY (US.Navy, Naval Aviation Depot, Norfolk, VA) structural integrity of critical aircraft components, especially when IN: ISTFA 1987 - International Symposium for Testing and Failure they may contain flaws. The evaluation of flawed components Analysis: Advanced materials; Proceedings of the Symposium, Los requires the application of fracture mechanics wherein crack tip

840 11 CHEMISTRY AND MATERIALS stress intensity factors are used to provide a quantitative means The UFD-S instrument was difficult to set up and calibrate without of assessing structural integrity. The primary objectives of this reference samples of known characteristics. Also, extensive project were to develop an analysis method for computing stress operator training is required to calibrate and operate the UFD-S intensity factors for severe thermal loadings of interest to the Air instrument. The UFD-S uses a wheel probe which does not require Force and to demonstrate the applicability of the method to small a liquid couplant and allows continuous scanning of the specimen. microcomputers. GRA The inspection speed of the UFD-S was therefore much greater than that of the other two instruments. Surface roughness, surface N88-29042# Southwest Research Inst., San Antonio, Tex. Oelvoir curvature, and variations in paint thickness were observed to limit Fuels and Lubricants Research Facility. the applicability of the instruments. GRA DEVELOPMENT OF A TEST METHOD TO DETERMINE POTENTIAL PEROXIDE CONTENT IN TURBINE FUELS. PART N88-29889# Dayton Univ., Ohio. 2 Interim Report, Sep. 1985 - May 1987 FATIGUE CRACK GROWTH CHARACTERISTICS OF ARALL G. E. FODOR, D. W. NAEGELI, K. B. KOHL, and J. P. CUELLAR, (TRADEMARK)-1 Interim Report, Aug. 1987 - Jan. 1988 JR. Jun. 1987 32 p JOHN J. RUSCHAU May 1988 34 p (Contract NO0014-85-CO2520; DAAK70-85-C-0007; (Contract F33615-84-C-5130) DAAK70-87-(2-0043) (AD-A1961 85; UDR-TR-88-21; AFWAL-TR-88-4075) Avail: NTlS (AD-A192244; BFLRF-243-PT-2) Avail: NTlS HC AO3/MF A01 HC A03/MF A01 CSCL 11D CSCL 21 D Constant amplitude and spectrum fatigue crack growth rate Through the generally accepted 43 C and 65 C bottle storage properties were evaluated for ARALL-1 aluminum laminate. Testing method of accelerated aging, the relative ratings of six selected was performed on M(T) specimens under both lab air and high fuels’ oxidative tendencies were established. In the 43 C test, humidity conditions. Crack length monitoring was performed on storage for about 12 weeks produces results that are comparable each aluminum ply utilizing electrical-potential drop techniques to to a full year’s storage under ambient conditions. To develop a gain a better insight into the fatigue cracking process. Results practical test method for the prediction of peroxide potential of indicate an outstanding superiority of ARALL-1 in terms of fatigue fuels, experimental conditions were sought so that the oxidative crack growth resistance over conventionally produced 7000 series tendencies of fuels could be assessed within a reasonable time. aluminum. Fatigue cracking in each of the aluminum plies was Accordingly, a matrix of experiments was designed to allow fairly uniform, with no large discrepancies in total crack length or selection of reaction conditionally, the results of experiments should growth rates observed between the various plies. For samples allow the development of global reaction kinetics to aid the tested under a fighter-type load history, the effect of high humidity determination of fuel peroxidation potential and to shed light on was actually beneficial, with fatigue crack growth rates typically the reaction mechanism. The oxidations were carried out in a one-half of those developed under lab air conditions. Explanations stirred pressurized reactor at 60, 80, 100, and 120 C, under oxygen based on increased delamination regions are offered to explain pressures of 240, 790, or 1140 kPa (abs) for periods of up to 70 this behavior. GRA hours. GRA

N88-29877# Technische Univ., Berlin (West Germany). Inst. N88-29890# Rensselaer Polytechnic Inst., Troy, N.Y. fuer Luft- und Raumfahrt. PROCESSING TECHNOLOGY RESEARCH IN COMPOSITES INVESTIGATIONS ON THE MODIFICATION OF STRUCTURAL Final Report, 1 Oct. 1986 - 30 Sep. 1987 RELIABILITY BY SUBSTITUTION OF ALUMINUM BY CARBON RUSSELL J. DIEFENDORF 31 Dec. 1987 6 p FIBER REINFORCED PLASTICS IN AIRCRAFT (Contract AF-AFOSR-0053-87) CONSTRUCTlON[UNTERSUCHUNGENZURVERAENDERUNG (AD-A195693; AFOSR-88-0669TR) Avail: NTlS HC A02/MF A01 DER STRUKTURZUVERLAESSIGKEIT BE1 SUBSTITUTION CSCL 11D VON ALUMINIUM DURCH KOHLEFASERKUNSTSTOFF IN Chemical vapor deposition has been used for over fifteen years FLUGZEUGKONSTRUKTIONEN] for depositing carbon matrices in carbonlcarbon composites used BERND ZIEGLER 1988 188 p In GERMAN for reentry nose-tips, rocket nozzle throat inserts, and aircraft (ILR-MITT-195; ETN-88-93115) Avail: NTlS HC AO9/MF A01 brakes. The same technology is appropriate for depositing silicon Reliability theory for elementary components is outlined in the carbide or other matrices in ceramic-ceramic composites, or case of serial and parallel connected systems and the obtained ceramidcarbon composites. Furthermore, chemical vapor redundancy is analyzed. Investigations for the determination of deposition is a powerful technique for applying the graded oxidation material strength distribution and reliability properties of aluminum resistant coatings required for carbon/carbon composites in long alloy and carbon reinforced plastics are described. Tensile strength time oxidizing environments. Modern instrumentation allows many and elongation are measured for AlCuMg alloy components in variations in properties to be made which had been impossible in serial and parallel systems and their reliability is evaluated. For the past. It is for these reasons that we proposed the acquisition carbon reinforced plastics variation of fiber angles effects is studied of a state-of-the-art Low Pressure Chemical Vapor Deposition on tensile strength and reliability of aircraft components. ESA Apparatus. GRA

N88-29885# Southwest Research Inst., San Antonio, Tex. N88-29910# Advisory Group for Aerospace Research and EVALUATION OF BOND TESTING EQUIPMENT FOR Development, Neuilly-SurSeine (France). Propulsion and INSPECTION OF ARMY ADVANCED COMPOSITE AIRFRAME Energetics Panel. STRUCTURES Final Report, 1 Jul. 1987 - 12 Feb. 1988 COMBUSTION AND FUELS IN GAS TURBINE ENGINES HEGEON KWUN and DAVID G. ALCAZAR 12 Feb. 1988 45 p Jun. 1988 515 p In ENGLISH and FRENCH Symposium held (Contract DLA900-84-C-0910) in Chania, Greece, 19-23 Oct. 1987 (AD-A195795) Avail: NTlS HC AO3/MF A01 CSCL 01C (AGARD-CP-422; ISBN-92-835-0465-6) Avail: NTlS HC A22/MF Forty-one ultrasonic bond testing instruments for nondestructive A0 1 inspection of composite airframe structures were evaluated based The attention of combustor designers and researchers has on information available in the literature. In addition, three of these focused upon two main factors: the identification of the significance instruments, the Fokker Bondtester Model 80-L, the Bondascope of fuel degradation upon combustion design and performance, 2100, and the Sonatest UFD-S, were evaluated in the laboratory and the potential prizes to be gained by the development of using ten specimens of composite airframe structures supplied by better design techniques. The aim of the conference was to review the Army. All the specimens had unknown flaw conditions. Both progress made in these areas under four main subject headings: the Fokker Bondtester and the Bondascope required only a few namely, alternative fuels and fuel injection, combustor development, hours of operator training in calibration and operation. Both soot and radiation, and the development of mathematical models instruments require a liquid couplant and are used for spot checking. for the design of gas turbine combustors.

84 1 11 CHEMISTRY AND MATERIALS

N88-29913# Purdue Univ., West Lafayette, Ind. School of N88-29918# Deutsche Forschungs- und Versuchsanstalt fuer Mechanical Engineering. Luft- und Raumfahrt, Cologne (West Germany). Inst. fuer ATOMIZATION OF ALTERNATIVE FUELS Antriebstechnik. ARTHUR H. LEFEBVRE In AGARD, Combustion and Fuels in INFLUENCE OF OPERATING CONDITIONS ON THE Gas Turbine Engines 14 p Jun. 1988 ATOMIZATION AND DISTRIBUTION OF FUEL BY AIR BLAST Avail: NTlS HC A22/MF A01 ATOMIZERS The influence of atomization quality on several key aspects of M. CAO, H. EICKHOFF, F. JOOS. and B. SIMON (Technische combustion performance is reviewed. The performance parameters Univ., Munich, West Germany ) In AGARD, Combustion and considered include combustion efficiency, lean blowout, and lean Fuels in Gas Turbine Engines 8 p Jun. 1988 Sponsored by lightup, and also the pollutant emissions of carbon monoxide, the Federal German Ministry of Research and Technology, Berlin unburned hydrocarbons, oxides of nitrogen, and smoke. The fuel Avail: NTlS HC A22/MF A01 properties of importance are described and equations are presented The performance of a gas turbine combustion chamber depends for estimating the effects of changes in fuel properties on spray essentially on the distribution of the fuel in the primary zone. characteristics for the main types of fuel nozzle employed in aero Ignition, stability of combustion, wall temperatures, and smoke and gas turbines, namely plain orifice, pressure swirl, and airblast pollutant emission are all affected. Maintaining a fixed geometry, atomizers. The anticipated effects on atomization of changes from the droplet size and spray angle under variation of the air pressure conventional to alternative fuels is discussed. Author drop at constant temperature were measured using two test liquids in an air blast atomizer system. Correlation equations were provided for both variables. Known correlations were confirmed for the droplet size. The spray angle is pressure related, increasing very N88-29915# Karlsruhe Univ. (West Germany). Lehrstuhl und rapidly with increasing pressure. Author Inst. fuer Thermische Stroemungsmaschinen. TURBULENCE EFFECTS ON THE DROPLET DISTRIBUTION N88-29919# Cranfield Inst. of Tech., Bedford (England). School BEHIND AIRBLAST ATOMIZERS of Mechanical Engineering. S. WITTIG, W. KLAUSMANN, and B. NOLL In AGARD, SPRAY PERFORMANCE OF A VAPORIZING FUEL INJECTOR Combustion and Fuels in Gas Turbine Engines 13 p Jun. 1988 A. K. JASUJA and H. C. LOW (Rolls-Royce Ltd., Bristol, England) Sponsored in part by the Forschunbsvereinigung In AGARD, Combustion and Fuels in Gas Turbine Engines 13 p Verbrennungskraftmaschinen,e.V., and German National Science Jun. 1988 Foundation, Fed. Republic of Germany Avail: NTlS HC A22/MF A01 Avail: NTlS HC A22/MF A01 The spray performance of a vaporizer fuel injector of a type Turbulent fluctuations of the airflow in gas turbine combustion that has accumulated extensive setvice experience in sub- and chambers have decisive influence on the mixing of fuel droplets super-sonic commercial and military aircraft applications is and air both in premixing regions and primary zones. Detailed examined. Spray performance data covers a wide range of measurements in a recirculating, droplet charged airflow in a operating conditions including the effects of fuel quality as well as combustor model are conducted with an optical diffraction type the atomizing air temperature. The objective is to further not only particle sizer. These investigations yield information about the local the current level of understanding regarding the fundamental fuel concentrations as well as the local concentration weighted functional aspects of vaporizer technology but also the data base diameter distributions under cold and hot airflow conditions. The for future designs. Author spray is produced by a prefilming airblast nozzle, which is built into the combustor model. The calculation of the above mentioned N88-29920# Lava1 Univ. (Quebec). Dept. du Genie Mecanique. quantities using a new computational model shows that in THE CHARACTERIZATION OF COMBUSTION BY FUEL considering turbulence fluctuations significant improvement of the COMPOSITION: MEASUREMENTS IN A SMALL results is obtained and excellent agreement between predicted CONVENTIONAL COMBUSTOR and measured values is achieved. Therefore, the results indicate D. KRETSCHMER and J. ODGERS In AGARD, Combustion and that turbulence can be one of the major influencing parameters on droplet distribution. Author Fuels in Gas Turbine Engines 10 p Jun. 1988 Sponsored by National Defence Canada Avail: NTlS HC A22/MF A01 In a continuing program on the effects of fuel properties on N88-29916# United Technologies Research Center, East Hartford, combustion, some 20 pure hydrocarbons and synthesized fuels Conn. were tested at atmospheric conditions in a one third scale version NOZZLE AIRFLOW INFLUENCES ON FUEL PATTERNATION of an aircraft type combustor. This combustor used a Simplex T. J. ROSFJORD and W. A. ECKERLE (Clarkson Univ., Potsdam, type pressure jet atomizer. Each fuel was burned over a range of N.Y.) In AGARD, Combustion and Fuels in Gas Turbine Engines air-fuel ratios, and at each condition, a full exhaust gas analysis 12 p Jun. 1988 Previously announced in IAA as A88-44765 was done, exhaust temperature distribution was measured, as also (Contract F33615-85-C-2515) weak extinction. The results and their implications are discussed. Avail: NTlS HC A22/MF A01 Author The velocity and turbulence levels downstream of eight variations of a model gas turbine, aerating, fuel nozzle were N88-29922# Rolls-Royce Ltd., Bristol (England). measured. The nozzle configurations were assemblies which HIGH PERFORMANCE TURBOFAN AFTERBURNER SYSTEMS purposefully altered the airflow in a swirler or contouring swirl A. SOTHERAN In AGARD, Combustion and Fuels in Gas Turbine vane trailing edges. Data were acquired by a traversing, two Engines 10 p Jun. 1988 component laser velocimeter in planes 0.060 in. or 2.50 in. Avail: NTlS HC A22/MF A01 downstream from the nozzle exit. Analyses of these data indicated The modern turbofan afterburner is characterized by its high that very symmetric flow fields can be produced. Such control boost and efficiency and by its compact geometry which is achieved was easier to achieve for the airflow than the fuel, supporting the by locating the flameholding baffles immediately downstream of position that nozzle patternation quality was more dependent on the turbine exhaust plane of the engine core and bypass gas the fuel distribution in the nozzle. The presence of swirler wakes stream. At the confluence, the stream divider may be a simple could always be discerned at the nozzle exit; the extreme variations cylinder or it may be of lobed configuration to encourage mixing imposed by coarse swirlers could dominate the flow. Such airflow between the two gas streams in the downstream jet pipe in order influences were not apparent in the velocity profiles at downstream to improve the unboosted thrust of the engine. The geometry of locations. However, their influence in convecting a higher fuel mass the afterburner hardware must be adapted to suit the choice of flux persisted from the nozzle exit and produced extreme variations mixed or unmixed configurations. In flight, selection of the in the spray pattern. Author afterburner must be fast and reliable under all flight conditions

842 11 CHEMISTRY AND MATERIALS

with times to full thrust of the order of only a second or two. a gas turbine is presented. A 3-D numerical solution technique is Both the light up and the subsequent acceleration to full thrust used to solve the governing time averaged partial differential are expected to be smooth with no excessive initial thrust jump. equations and the physical modeling for the turbulence, combustion Synchronization and matching of the afterburner fuel with the and thermal radiation. The heat transfer modeling is emphasized. variable final nozzle must be accurate at all times to maintain the A method to calculate the distribution of temperature, radiative engine turbomachinery on its required running lines. The afterburner heat flux and total heat flux of the liner is described. The must always be free of combustion driven pressure oscillations implications of neglecting radiative heat transfer in gas turbine which can occur either in cross stream modes or in longitudinal combustion chamber calculations are discussed. The influence of modes, both of which can be mechanically damaging and, in some working pressure on the radiative heat transfer is investigated cases, cause fan surge and other intolerable effects in the engine. comparing the radiative heat flux and the temperature distribution The afterburner must incorporate appropriate measures to avoid of the liner for three different working pressures: 5, 15 and 25 various potential thermal problems including fuel boiling and bar. Author gumming in the supply manifolds and excessive heat transfer to the jet pipe and aircraft engine bay. Author N88-29930# Royal Aircraft Establishment, Farnborough (England). Propulsion Dept. N88-29925# Southwest Research Inst., San Antonio, Tex. GAS TURBINE SMOKE MEASUREMENT A SMOKE FUEL EFFECTS ON FLAME RADIATION AND HOT-SECTION GENERATORFORTHEASSESSMENTOFCURRENTAND DURABILITY FUTURE TECHNIQUES C. A. MOSES and P. A. KARPOVICH (Naval Air Propulsion Test S. P. GlRLlNG In AGARD, Combustion and Fuels in Gas Turbine Center, Trenton, N.J.) In AGARD, Combustion and Fuels in Gas Engines 10 p Jun. 1988 Turbine Engines 16 p Jun. 1988 Avail: NTlS HC A22/MF A01 Avail: NTlS HC A22/MF A01 Smoke measurement from gas turbine engines is one The results of combustor experiments relating to fuel effects instrumentation technique that remains, literally, a black art. Current on combustor durability are summarized and analyzed with respect methods are inaccurate, slow, insensitive and unable to detect to Navy aircraft operations and maintenance. By combining life transients. A smoke generator was developed capable of ratio models with data on mission profiles, models were developed generating by pyrolysis of aviation kerosene, stable levels of smoke that predict the impact of flying an aircraft on a fuel of reduced for prolonged periods, representative of that from engines. Particle hydrogen content in terms of the combustor life lost in flying a size measurements have enabled the comparison of smokes from typical mission. To determine the effect of decreasing hydrogen different sources and provided a greater understanding of the content on maintenance requirements, the life ratio models were problems of representative sampling using currently approved combined with data obtained from maintenance depots on methods. Several alternative measurement techniques were combustor life along with information on the importance of evaluated using the smoke generator, precluding the need for combustor life in determining engine overhaul schedules. From expensive engine testing. This has promoted research into this, it was possible to identify which engines or aircraft would be instrumentation that will give a truer indication of particulate criteria most affected by decreases in hydrogen content, and at what of interest to the engine designer and customer, for example truer point increases in maintenance requirements are likety to be visibility and erosiveness. Author realized. Author N88-29935# General Electric Co., Cincinnati, Ohio. Aircraft N88-29926# California Univ., Irvine. Combustion Lab. Engines. THE PERFORMANCE OF A SURROGATE BLEND IN NUMERICAL MODELS FOR ANALYTICAL PREDICTIONS OF SIMULATING JP-4 IN A SPRAY-FUELED COMBUSTOR COMBUSTOR AEROTHERMAL PERFORMANCE G. S. SAMUELSEN and C. P. WOOD In AGARD, Combustion CHARACTERISTICS and Fuels in Gas Turbine Engines 6 p Jun. 1988 Sponsored D. L. BURRUS, W. SHYY, and M. E. BRAATEN (General Electric in part by the Naval Air Propulsion Center Co., Schenectady, N.Y.) In AGARD, Combustion and Fuels in (Contract FO8635-86-C-0309) Gas Turbine Engines 25 p Jun. 1988 Avail: NTlS HC A22/MF A01 Avail: NTlS HC A22/MF A01 A surrogate fuel was developed to simulate the atomization An overview of the work performed at GE Aircraft Engines and combustor performance of a practical distillate JP-4. The under an ongoing program to develop and improve the surrogate is comprised of 14 pure hydrocarbons and formulated sophisticated analytical models for the design and analysis of based on the distillation curve and compound of the distillate aircraft turbine engine combustors is presented. This effort has parent. In previous work, the atomization performance (evaluated focused on the full three-dimensional (3-0) elliptic combustor in terms of the atomization quality in an isothermal chamber), and internal flow model. The objectives of the program are reviewed. the combustor performance (evaluated in terms of the velocity The progress made in the past five years is discussed starting and thermal fields in a spray fueled combustor) were found to be with the initial application and assessment of first generation 3-D equivalent for the parent and surrogate JP-4. The sooting combustor models based on Cartesian grids, progressing to the performance of the two fuels is addressed, as well as two reference development and recent application of an improved second fuels (a JP-5 and isooctane) of purposefully disparate properties. generation 3-D combustor model based on a body fitted generalized The sooting performance of the parent and surrogate JP-4 are curvilinear grid. Finally, a brief review of planned future modeling nearly identical, and distinctly different from that of either the JP-5 activities to be conducted under this program will be discussed. or the isooctane. The surrogate represents, as a result, an attractive Author fuel blend for the study of fuel compositional effects on the sooting performance of petroleum fuels in spray fueled combustor. N88-29962# Aptech Engineering Services, Inc., Sunnyvale, Author Calif. STRESS INTENSITY FACTORS FOR CRACKED METALLIC N88-29929# lnstituto Superior Tecnico, Lisbon (Portugal). Dept. STRUCTURES UNDER RAPID THERMAL LOADING Final of mechanical Engineering. Report, Aug. 1986 - May 1987 RADIATION TRANSFER IN GAS TURBINE COMBUSTORS RUSSELL C. CIPOLLA and KIMBLE J. CLARK Oct. 1987 74 p M. G. CARVALHO and P. J. M. COELHO In AGARD, Combustion (Contract F33615-86-C-3217; AF PROJ. 3005) and Fuels in Gas Turbine Engines 22 p Jun. 1988 Sponsored (AES-8609709F-1; AFWAL-TR-87-3059) Avail: NTlS HC by lnstituto Nacional de lnvestigacao Cientifica, Lisbon, Portugal A04/MF A01 CSCL 11F Avail: NTlS HC A22/MF A01 High intensity heating of aircraft structures can challenge the The prediction of the local flow, heat transfer and combustion structural integrity of critical aircraft components, especially when processes inside a three-dimensional can combustor chamber of they may contain flaws. The evaluation of flawed components

843 11 CHEMISTRY AND MATERIALS requires the application of fracture mechanics wherein crack tip cascade test conditions. A two-dimensional cascade test was stress intensity factors are used to provide a quantitative means conducted at engine-level Mach number and Reynolds number of assessing structural integrity. The primary objectives were to distributions in order to obtain baseline data that can be used develop an analysis method for computing stress intensity factors with engine data in order to quantify the effects of environmental for severe thermal loadings of interest to the Air Force and to conditions on heat transfer levels and distributions. O.C. demonstrate the applicability of the method to microcomputers. A methodology was developed based on influence functions to A88-53128# determine stress intensity factors for structures exposed to intense GASTEMPERATURE MEASUREMENTSIN SHORT DURATION thermal heating. A demonstration of the method is given and results TURBOMACHINERY TEST FACILITIES detailed. Author L. N. CATTAFESTA and A. H. EPSTEIN (MIT, Cambridge, MA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 24th, N88-29991# Coordinating Research Council, Inc., Atlanta, Ga. Boston, MA, July 11-13, 1988. 8 p. Research supported by Hydroperoxide Potential of Jet Fuels Panel. Rolls-Royce, Inc. and USAF. refs DETERMINATION OF THE HYDROPEROXIDE POTENTIAL OF (AIAA PAPER 88-3039) JET FUELS Thermocouple rakes for use in short-duration turbomachinery Apr. 1988 11 1 p test facilities have been developed using very fine thermocouples. (AD-A195975; CRC-559) Avail: NTlS HC AO6/MF A01 CSCL Geometry variations were parametrically tested and showed that 21 D bare quartz junction supports (76 microns in diameter) yielded In 1963 and in 1976, peroxide attack on certain engine rubber superior performance, and were rugged enough to survive parts was found with the use of some Far Eastern fuels. The considerable impact damage. Using very low cost signal problem was corrected by requiring oxidation inhibitor be added conditioning electronics, temperature accuracies of 0.3 percent to fuels meeting Specifications DERD 2494 and MIL-T-5624. were realized yielding turbine efficiency measurements at the Because the majority of commercial aviation turbine fuel had not 1-percent level. Ongoing work to improve this accuracy is shown significant peroxide formation, CRC was requested to described. Author develop a technique which would identify the hydroperoxide-forming tendencies of jet fuels. Heating the fuel at 65 C for four weeks and measuring the peroxide number is concluded to be an adequate A88-53 142# Go/No Go test. GRA NAVIER-STOKES SOLUTIONS FOR ROTATING 3-D DUCT FLOWS 6. N. SRIVASTAVA (Avco Research Laboratory, Inc., Everett, MA) AIAA. ASME, SAE, and ASEE, Joint Propulsion Conference, 12 24th. Boston, MA, July 11-13, 1988. 11 p. refs (AIAA PAPER 88-3098) ENGINEERING This paper deals with the computation of three-dimensional viscous turbulent flow in a rotating rectangular duct of low aspect Includes engineering (general); communications; electronics and ratio using thin-layer Navier-Stokes equations. Scalar form of an electrical engineering; fluid mechanics and heat transfer; approximate factorization implicit scheme along with a modified instrumentation and photography; lasers and masers; mechanical q-omega turbulence model has been utilized for mean flow engineering; quality assurance and reliability; and structural predictions. The predicted mean flow behavior has been favorably mechanics. compared with the experimental data for mean axial velocity, channel pressure and cross-flow velocities at a flow Mach number of 0.05 and a rotational speed of 300 rpm. Author A88-52733 FIBRE OPTIC FLOW SENSORS BASED ON THE 2 FOCUS A88-53 145# PRINCIPLE ADVANCED STRUCTURAL INSTRUMENTATION - AN H. SELBACH and A. LEWIN (Polytec GmbH, Waldbronn, Federal OVERVIEW Republic of Germany) IN: Laser anemometry - Advances and ANTHONY J. DENNIS (United Technologies Research Center, East applications; Proceedings of the Second International Conference, Hartford, CT) AIAA, ASME, SAE, and ASEE, Joint Propulsion Glasgow, Scotland, Sept. 21-23, 1987. Berlin and New York, Conference, 24th, Boston, MA, July 11-13, 1988. 3 p. Springer-Verlag, 1988, p. 195-206. refs (AIAA PAPER 88-3144) Flow sensors are widely used in air-breathing engines to provide An attempt was made to demonstrate the accuracy and the engineers with sufficient information concerning the flow losses. durability of advanced strain and temperature sensors in an The laser 2 focus velocimeter has become a very powerful tool environment typical of advanced gas turbine engines. A first-stage for detailed internal flow studies in turbomachinery and other turbine disk which operates at a maximum temperature of 1250 F situations where a harsh environment and the size of the particles at a speed of 13,200 rpm was the test component selected for required make measurements difficult. So far, laser focus this demonstration. The strain sensors were new alloy wire and velocimeters which incorporate optical fibers have not been advanced thin film static gages as well as the twin core fiber-optic available. This paper discusses new optical designs based on strain sensor. The survivability of a heat flux sensor and a special optical fibers for two-dimensional and three-dimensional time of strain gage overcoat layer was also revealed. K.K. flight velocimeters. Author

A88-53123# A88-53 166# DESIGN CODE VERIFICATION OF EXTERNAL HEAT NEW VERSION ANTISTATIC COATING TESTER TRANSFER COEFFICIENTS A. BRUERE (ONERA, Chatillon-sous-Bagneux, France) La F. 0. SOECHTING and 0. P. SHARMA (United Technologies Corp., Recherche Aerospatiale (English Edition) (ISSN 0379-38OX), no. Pratt and Whitney Group, West Palm Beach, FL) AIAA, ASME, 1, 1988, p. 29-34. SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, For new antistatic coatings applied to the composite materials July 11-13, 1988. 6 p. used in aeronautical construction, the performance of the CORAS (AIAA PAPER 88-301 1) antistatic-coating resistivity meter had to be improved. The A comparative study is conducted for measured and predicted performance of the new version is increased by a factor of 100, heat-transfer coefficients of air-cooled turbine blade airfoils. A for measurements of surface resistances of 100 kohm/unit area modified version of the STAN-5 boundary layer code was used to or less, with an accuracy and resolution of the order of 10 kohm/unit obtain analytical predictions of the heat transfer levels for the area. Author a44 12 ENGINEERING

A8843563 strength and a cleaner matrix than composites fabricated from HYPERVELOCITY APPLICATION OF TRIBOLOGICAL powder metal cloth monotapes, and the present technique is less COATINGS expensive than the powder metal fabrication techniques. R.R. ED COVE (General Electric Co., Lynn, MA) and R. COLE (Plasma Technology, Inc., South Windsor, CT) IN: Thermal spray: Advances A88-53795 in coatings technology; Proceedings of the National Thermal Spray INDUSTRIAL PRODUCTION OF CFRP-COMPONENTS IN Conference, Orlando, FL, Sept. 14-17, 1987. Metals Park, OH, AIRBUS CONSTRUCTION ASM International, 1988, p. 123-130. JUERGEN MASKOW (Airbus Industrie, Toulouse, France) SAWE, Application of the sliding wear tribological coating ’Tribaloy’ Annual Conference, 46th, Seattle, WA, May 18-20. 1987. 9 p. T-800 to various jet engine components using a hypervelocity (SAWE PAPER 1794) oxyfuel thermal spray system has been successfully demonstrated. An account is given of the application of CFRP construction to Qualitative coating-properties evaluations were performed which the vertical stabilizer of the A340 airliner. The results obtained characterized external surface hardness, microstructure, bond include a 20-percent weight saving over the aluminum alloy tensile strength, and component wear. Engine tests indicate that alternative structure, together with a parts-count reduction of from component life can be more than tripled using the present 2072 metallic parts to 96 and a reduction of the number of fasteners system. R.R. from 50,000 to 5800. The CFRP structure takes the form of integrally-stiffened laminate stabilizer skins that are mounted on a A88-53571 stiffening framework. A robotic prepreg tape-laying apparatus is HIGH TEMPERATURE TESTING OF PLASMA SPRAYED employed. O.C. THERMAL BARRIER COATINGS J. NERZ, G. BANCKE, H. HERMAN (New York, State University, A88-53829# Stony Brook), and D. S. ENGLEBY (Engleby and Others Co., Inc., INSTRUMENTATION AND TECHNIQUES FOR STRUCTURAL Morehead City, NC) IN: Thermal spray: Advances in coatings DYNAMICS AND ACOUSTICS MEASUREMENTS technology; Proceedings of the National Thermal Spray RICHARD TALMADGE, GENE MADDUX, and DOUGLAS Conference, Orlando, FL, Sept. 14-17, 1987. Metals Park, OH, HENDERSON (USAF, Aeronautical Systems Div., Wright-Patterson ASM International, 1988, p. 253-257. AFB, OH) AIAA, NASA, and AFWAL, Conference on Sensors (Contract NO0014-86-C-0016) and Measurement Techniques for Aeronautical Applications, Mar-M200 superalloy tubes have been coating using Atlanta, GA, Sept. 7-9, 1988. 13 p. refs state-of-the-art plasma spray techniques and tested at high (AIAA PAPER 88-4667) temperatures in a study of the failure mechanisms of thermal This paper summarizes the instrumentation and techniques used barrier coatings. The high temperature behavior was evaluated by the Structural Dynamics Branch of the Air Force Wright using a natural gas flame rig and static furnace oxidation tests. Aeronautical Laboratories in dynamic testing of aircraft, spacecraft, Cycled nd uncycled samples were evaluated using optical and and missiles. Modal testing of aircraft is discussed, including electron metallography and electron microprobe analysis. The accelerometers, automatic gain ranging amplifiers, and signal results indicate that for thermal barrier coatings with vacuum plasma multiplexers. Laser techniques of structural motion measurement sprayed bond coats, failure results from bond-coat-oxidation-in- are discussed, including a description of video holography duced stresses developed near the bond coat/thermal barrier in- (electronic speckle pattern interferometry) and its application to terface. Thermal barrier coatings with air plasma spray bond coats modal testing of aircraft and missile components. Acoustic testing degrade more rapidly due to the decreased oxidation resistance of structures at elevated temperatures is discussed, including of the bond coat. Failure, in this case, occurs at the bond coat/ techniques for achieving higher sound-pressure levels and the substrate interface. Author development of high-temperature accelerometers and microphones. Author A88-53579 PLASMA SPRAYED TUNGSTEN CARBIDE-COBALT A88-53840 COATINGS SURFACE ENGINEERING FOR HIGH TEMPERATURE B. DULIN (Plasma-Technics, Inc., Hollywood, FL) and A. R. NICOLL ENVIRONMENTS (Plasma-Technik AG, Wohlen, Switzerland) IN: Thermal spray: A. E. WEATHERILL and B. J. GILL (Union Carbide UK, Ltd., Advances in coatings technology; Proceedings of the National Coatings Service Div., Swindon, England) Metals and Materials Thermal Spray Conference, Orlando, FL, Sept. 14-1 7, 1987. Metals (ISSN 0266-7185). vol. 4, Sept. 1988, p. 551-555. refs Park, OH, ASM International, 1988, p. 345-351. refs An account is given of the techniques applicable to the design The use of the plasma spray process in fabricating WC-Co and fabrication of carefully formulated surface coatings capable layers of 12 and 17 percent Co, respectively, to various aircraft of furnishing mechanical, chemical, and thermal resistance in gas engine specifications is described. Consideration is also given to turbine engine hot-section environments. Both detonation-gun and the development of the plasma spraying of various WC-Co powders plasma-spraying methodologies are discussed; the former is used to meet general industrial requirements. It is noted that the plasma to deposit W-, Cr-, and Co-based compositions that impart rubbing spray parameters are correlated with bond strength, microhardness, or fretting wear resistance, while the latter confer thermal insulation phase content, and microstructure of the coatings. Semiautomatic and oxidation and thermal shock resistance, especially in the case metallographic preparation is also discussed. K.K. of combustion chamber components. O.C.

A88-53581. National Aeronautics and Space Administration. A88-53954 Lewis Research Center, Cleveland, Ohio. DEFORMATION AND DAMAGE OF THE MATERIAL OF GAS COMPOSITE MONOLAYER FABRICATION BY AN ARC-SPRAY TURBINE ENGINE BLADES DURING THERMAL CYCLING IN PROCESS GAS FLOW [DEFORMIROVANIE I POVREZHDENIE LEONARD J. WESTFALL (NASA, Lewis Research Center, MATERIALA LOPATOK GTD PRI TEPLOSMENAKH V Cleveland, OH) IN: Thermal spray: Advances in coatings GAZOVOM POTOKE] technology; Proceedings of the National Thermal Spray G. N. TRET’IACHENKO and V. G. BARILO (AN USSR, lnstitut Conference, Orlando, FL, Sept. 14-17, 1987. Metals Park, OH, Problem Prochnosti, Kiev, Ukrainian SSR) Problemy Prochnosti ASM International, 1988, p. 417-426. refs (ISSN 0556-171X), Aug. 1988, p. 39-42. In Russian. refs A single layer (monotape) technique for fabricating complex The thermodynamic processes of energy dissipation in the high-temperature tungsten-fiber-reinforced superalloy composites material of wedge-shaped zones of gas turbine blades are is proposed. The fabrication of sheets of arc-sprayed monotape investigated analytically. A procedure for determining that part of 38 cm wide and 122 cm long has been demonstrated. Composites energy dissipated in the blade material which corresponds to fabricated using the method are shown to have equal tensile damage accumulation is proposed. It is shown that, by using the

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entropy increment resulting from irreversible material deformation work done at the NASA Lewis Research Center and at various as a fatigue life criterion, it is possible to predict the service life contract and grant facilities. Author of gas turbine blades. V.L. A88-54152'# United Technologies Research Center, East A8843961 Hartford, Conn. CALCULATION OF STRESS RELAXATION IN THE THE EFFECTS OF TURBULENCE AND STATOWROTOR SURFACE-HARDENED LAYER NEAR A HOLE IN THE DISK INTERACTIONS ON TURBINE HEAT TRANSFER. II - EFFECTS OF A GASTURBINE ENGINE [RASCHET RELAKSATSII OF REYNOLDS NUMBER AND INCIDENCE NAPRlAZHENll V POVERKHNOSTNO UPROCHNENNOM SLOE M. F. BLAIR, R. P. DRING, and H. D. JOSLYN (United Technologies U OTVERSTllA DISKA TURBINY GTD] Research Center, East Hartford, CT) ASME, Gas Turbine and IU. P. SAMARIN, E. V. GRINEVICH, L. A. MURATOVA, and V. P. Aeroengine Congress and Exposition, Amsterdam, Netherlands, RADCHENKO (Kuibyshevskii Politekhnicheskii Institut, Kuibyshev, June 6-9, 1988. 8 p. refs USSR) Problemy Prochnosti (ISSN 0556-171X), Aug. 1988, p. (Contract NAS3-23717) 87-92. In Russian. refs (ASME PAPER 88-GT-5) The relaxation of residual compressive stresses generated in Part I of this paper presents airfoil heat transfer data obtained the surface layer of a workpiece during plastic surface working is in a rotating turbine model at its design rotor incidence. This portion examined. A method is proposed for calculating residual stress of the paper presents heat transfer data obtained in the same relaxation in the surface-hardened layer near a hole in a gas model for various combinations of Reynolds number and inlet turbine disk under conditions of general creep in the plane stressed turbulence and for a very wide range of rotor incidence. On the state. The method is based on the conjugation of solutions to suction surfaces of the first stage airfoils the locations and lengths two problems: the creep problem for a disk with stress raisers in of transition were influenced by both the inlet turbulence level the form of circular holes and the problem of stress relaxation in and the Reynolds number. In addition it was demonstrated that the surface-hardened layer near a hole in a disk with allowance on the first stage pressure surfaces combinations of high Reynolds for the evolution of the stress-strain state of the disk. The number and high turbulence can produce heat transfer rates well procedure, which has been implemented in software, is in excess of two-dimensional turbulent flow. Rotor heat transfer demonstrated by performing a stress relaxation analysis for a distributions indicate that for relatively small deviations from the turbine disk of El698 alloy at 700 C. V.L. design incidence, local changes to the heat transfer distributions were produced on both pressure and suction sides near the stagnation region. For extremely large negative incidence the flow A88-53998 was completely separated from the rotor pressure surface MECHANIZATION OF JOINT PRODUCTION DURING THE producing very high local heat transfer. Author ASSEMBLY OF AIRCRAFT STRUCTURES [MEKHANIZATSIIA OBRAZOVANIIA SOEDlNENll PRI SBORKE AVIATSIONNYKH A88-54164'# Sverdrup Technology, Inc., Cleveland, Ohio. KONSTRUKTSIII DEVELOPMENT OF A THERMAL AND STRUCTURAL GENNADll MlKHAlLOVlC SHCHETININ, MlKHAlL IVANOVICH ANALYSIS PROCEDURE FOR COOLED RADIAL TURBINES LYSOV, and VALENTIN MlKHAlLOVlC BUROV Moscow, GANESH N. KUMAR (Sverdrup Technology, Inc., Cleveland, OH) Izdatel'stvo Mashinostroenie, 1987, 256 p. In Russian. refs and RUSSELL G. DEANNA (NASA, Lewis Research Center; US. The fundamentals of the design of various positioning devices Army, Propulsion Directorate, Cleveland, OH) ASME, Gas Turbine and special mechanization aids for producing joints during the and Aeroengine Congress and Exposition, Amsterdam, assembly of aircraft structures are presented. In particular, attention Netherlands, June 6-9, 1988. 8 p. refs is given to the conditions of assembly and characterization of (ASME PAPER 88-GT-18) assembly systems; typical assembly processes and advanced A procedure for computing the rotor temperature and stress equipment for producing riveted joints; mechanization of hole distributions in a cooled radial turbine is considered. Existing codes machining during the bench assembly of components and units; for modeling the external mainstream flow and the internal cooling and mechanization of the production of riveted and bolted joints flow are used to compute boundary conditions for the heat transfer during field assembly. The discussion also covers the general and stress analyses. An inviscid, quasi three-dimensional code structure of a flexible assembly system, the principal stages of computes the external free stream velocity. The external velocity assembly line design, and prediction of assembly mechanization is then used in a boundary layer analysis to compute the external requirements. V.L. heat transfer coefficients. Coolant temperatures are computed by a viscous one-dimensional internal flow code for the momentum A88-54139'# National Aeronautics and Space Administration. and energy equation. These boundary conditions are input to a Lewis Research Center, Cleveland, Ohio. three-dimensional heat conduction code for calculation of rotor ADVANCED HIGH TEMPERATURE INSTRUMENTATION FOR temperatures. The rotor stress distribution may be determined for HOT SECTION RESEARCH APPLICATIONS the given thermal, pressure and centrifugal loading. The procedure D. R. ENGLUND and R. G. SEASHOLTZ (NASA, Lewis Research is applied to a cooled radial turbine which will be tested at the Center, Cleveland, OH) IN: Toward improved durability in advanced NASA Lewis Research Center. Representative results from this aircraft engine hot sections; Proceedings of the Thirty-third ASME case are included. Author International Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 5-9, 1988. New York, American A88-54 169# Society of Mechanical Engineers, 1988, p. 5-21. refs AN EXPERIMENTAL DATA BASE FOR THE COMPUTATIONAL Programs to develop research instrumentation for use in turbine FLUID DYNAMICS OF COMBUSTORS engine hot sections are described. These programs were initiated R. E. CHARLES and G. S. SAMUELSEN (California, University, to provide improved measurements capability as support for a Irvine) ASME, Gas Turbine and Aeroengine Congress and multidisciplinary effort to establish technology leading to improved Exposition, Amsterdam, Netherlands, June 6-9, 1988. 5 p. refs hot section durability. Specific measurement systems described (ASME PAPER 88-GT-25) here include hea: flux sensors, a dynamic gas temperature A model axisymmetric gas-fired can combustor is used here to measuring system, laser anemometry for hot section applications, establish the sensitivity of the aerodynamic and thermal structure an optical system for viewing the interior of a combustor during to inlet boundary conditions and to thereby establish a operation, thin film sensors for surface temperature and strain comprehensive data base for the computational fluid dynamics of measurements, and high temperature strain measuring systems. combustors. The data presented include mean and rms values of The paper will describe the state of development of these sensors the axial and azimuthal velocities as well as Reynolds stress data and measuring systems and, in some cases, will show examples obtained using two-component laser velocimetry and mean of measurements made with this instrumentation. The paper covers temperatures from thermocouple measurements. Specific results

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show that the reactor operation is especially sensitive to modest A88-54193# , changes in both the inlet geometry and the fuel injection angle. PREDICTION OF THE PRESSURE DISTRIBUTION FOR C.D. RADIAL INFLOW BETWEEN CO-ROTATING DISCS JOHN W. CHEW and ROBERT J. SNELL (Rolls-Royce, PLC, Derby, England) ASME, Gas Turbine and Aeroengine Congress and j A88-54181# Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs HEAT TRANSFER, PRESSURE DROP, AND MASS FLOW (ASME PAPER 88-GT-61) ' RATE IN PIN FIN CHANNELS WITH LONG AND SHORT The problem of radial inflow between two plane co-rotating TRAILING EDGE EJECTION HOLES disks with the angular velocity of the fluid at inlet equal to that of S. C. LAU, J. C. HAN, and T. BATTEN (Texas A & M University, the disks is considered. An integral solution technique for turbulent College Station) ASME, Gas Turbine and Aeroengine Congress flow, based on that of von Karman (1921), is described. Solutions and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 10 p. are shown to be in good agreement with most of the available refs experimental data. For incompressible flow the pressure drop (Contract NSF CBT-87-13833) coefficient is a function of just two non-dimensional parameters: (ASME PAPER 88-GT-42) the radius ratio for the cavity and a throughflow parameter. For The turbulent heat transfer and friction characteristics in the air flows compressibility can be important and an additional pin fin channels with small trailing edge ejection holes found in non-dimensional parameter is needed. Results for a wide range internally-cooled turbine airfoils have been experimentally of conditions are presented graphically. These show the sensitivity investigated. It is found that the overall heat transfer increases of the pressure coefficient to the governing parameters and provide when the length of the trailing edge ejection holes is increased a quick method for estimating the pressure drop. Author and when the trailing edge ejection holes are configured such that much of the cooling air is forced to flow further downstream in the radial flow direction prior to exiting. The increase in the A88-54 197# overall heat transfer is shown to be accompanied by an increase THE EFFECTS OF AN EXCITED IMPINGING JET ON THE in the overall pressure drop. R.R. LOCAL HEAT TRANSFER COEFFICIENT OF AIRCRAFT TURBINE BLADES P. J. DlSlMlLE and D. M. PAULE (Cincinnati, University, OH) A88-54185# ASME, Gas Turbine and Aeroengine Congress and Exposition, LAMINAR FLOW VELOCITY AND TEMPERATURE Amsterdam, Netherlands, June 6-9, 1988. 6 p. Research supported DISTRIBUTIONS BETWEEN COAXIAL ROTATING DISKS OF by the Charles A. Lindbergh Fund. refs FINITE RADIUS (ASME PAPER 88-GT-66) J. F. LOUIS (MIT, Cambridge, MA) and D. T. ORLETSKY ASME, The primary objective of this paper is to present the results of Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, research into the effects of periodic excitation upon the local heat Netherlands, June 6-9. 1988. 9 p. refs transfer characteristics of a turbine blade cooled by an impinging (ASME PAPER 88-GT-49) jet of air. A curved plate (used to simulate the inner leading edge Predictions of the laminar flow and temperature distribution of a turbine blade) was subjected to a two-dimensional jet flow between coaxial rotating disks of finite radius have been obtained field (Re = 10,000) with a superimposed periodic acoustic using a computer model solving the Navier-Stokes equation for a disturbance. When compared to the naturally disturbed flow, the laminar fluid of constant properties. To do this, a stream vorticity excited flow field was found to reduce the local Nusselt number model in the r-z plane is used in the solution of the Navier-Stokes and cool the blade less efficiently (by as much as ten percent in equation. The velocity fields were obtained for both shrouded and the extreme cases). The results of the study appear to indicate unshrouded disks with or without radial throughflow for either that harmonic disturbances present a serious controlling factor in co-rotating or counter-rotating disks. Velocity profiles predicted by the quest for optimization of turbine blade cooling techniques. By this model were compared to experimental data, to a similarity isolating dominant frequencies in gas turbine engines and working solution and to a large aspect ratio model. The results obtained to suppress them, it is believed that significant contributions towards by this model closely matched the experimental data, and the the desired increase in turbine inlet temperature could be large aspect ratio solution for the cases considered. The uncoupled possible. Author energy equation was then solved using the calculated velocity distribution for the temperature distribution between the disks. This was done for two cases: (1) two isothermal disks, and (2) one isothermal disk and one adiabatic disk. Author A88-54 199# A RADIAL MIXING COMPUTATION METHOD J. DE RUYCK and CH. HIRSCH (Brussel, Vrije Universiteit, Brussels, A88-54191# Belgium) ASME, Gas Turbine and Aeroengine Congress and FLOW IN SINGLE AND TWIN ENTRY RADIAL TURBINE Exposition, Amsterdam, Netherlands, June 6-9, 1988. 14 p. VOLUTES USAF-supported research. refs N. LYMBEROPOULOS, N. C. BAINES, and N. WATSON (Imperial (ASME PAPER 88-GT-68) College of Science and Technology, London, England) ASME, A radial mixing calculation method is presented where both Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, convective and turbulent mixing processes are included. The Netherlands, June 6-9, 1988. 8 p. refs secondary flows needed for the convective mixing are derived (ASME PAPER 88-GT-59) from pitch-averaged vorticity equations combined with integral Flow in the vaneless volute of a radial-inflow turbine is methods for the three-dimensional end-wall boundary layers, profile investigated numerically and experimentally for cases of single boundary layers, and asymmetric wakes. The convective transport and twin entry to the volute and for the particular case of unequal due to secondary flows is computed explicitly. The method is flows, or partial admission, to the volutes. The computational model applied to a cascade and two single-stage rotors. The three test is based on a quasi-three-dimensional solution to the Euler cases show a very different secondary flow behavior which allows equations, in which the radial and tangential components are fully the analysis of the relative importance of the different secondary solved but the axial component is only treated to simulate the flow effects. Turbulent diffusion is found to be the most important mixing of the two streams. In the single entry case, the agreement mixing mechanism, whereas convective mixing becomes significant with experimental data is good. In the twin entry case, the essential when overall radial velocities exceed about 5 percent of the main features of the flowfield, and particularly the interaction and mixing velocities. The wake diffusion coefficient is found to be of the two streams, can be modeled, but the solution is limited by representative for the turbulent radial mixing and is the only the coarseness of the grid in the axial direction. V.L. empirical constant to be determined. Author

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A80-54209# at four flow coefficients. From these measurements, lift coefficient USEOFCONTROLFEEDBACKTHEORYTOUNDERSTAND is determined. Also, loss of lift coefficient near the tip is calculated, OTHER OSCILLATIONS and is attributed mainly to the tip leakage flows. Author K. J. RUMFORD and R. ANDREJCZYK (Textron, Inc., Avco Lycoming Textron Div., Stratford, CT) ASME, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, A80-54230# June 6-9, 1988. 8 p. GAS TURBINE STUDIES AT OXFORD 1969-1987 (ASME PAPER 88-GT-81) T. V. JONES (Oxford University, England) ASME, Gas Turbine The TF40B control system and the rotor system of the U.S.Navy and Aeroengine Congress and Exposition, Amsterdam, LCAC Hovercraft are described. A history of early development Netherlands, June 6-9, 1988. 12 p. refs problems and their solution is followed by a more obscure problem (ASME PAPER 88-GT-112) that was traced by logical deduction to a mechanical vibration of Gas turbine heat transfer studies commenced at Oxford a control component. This vibration resulted in fuel flow oscillations University in 1969 when transient techniques previously used for that fed back and amplified the mechanical vibration. The solution measurements in hypersonic flows were applied to the gas turbine to this problem is described and a unique application of classical environment. Shock tubes were employed and subsequently a new closed loop control analysis to this unusual and unwanted feedback form of transient tunnel, the Isentropic Light Piston Tunnel, was follows. Author developed specifically for turbine heat transfer testing. During the following years further short duration facilities were developed to study blade and vane external aerodynamics, and also the heat A88-54223# transfer in cooling passages was examined using liquid crystal FURTHER ASPECTS OF THE UK ENGINE TECHNOLOGY techniques. All these transient facilities are described, and the DEMONSTRATOR PROGRAMME development of the instrumentation peculiar to these is explained. D. W. HUGHES and W. J. CHRISPIN (Ministry of Defence The results of the work on external and internal heat transfer are Procurement Executive, London, England) ASME, Gas Turbine summarized. In particular, the film cooling studies, the blade and and Aeroengine Congress and Exposition, Amsterdam, vane external heat transfer work, and the wake simulation Netherlands, June 6-9, 1988. 6 p. experiments are outlined. Author (ASME PAPER 88-GT-104) This paper is a follow-up of the Chrispin (1987) paper on the U.K. engine technology program, which discussed the background A08-54234# to the establishment of this program together with a summary of THE VORTEX-FILAMENT NATURE OF THE REVERSE FLOW the program’s overall activity. This paper discusses in detail the ON THE VERGE OF ROTATING STALL nature of the individual program elements, with special attention Y. N. CHEN, U. HAUPT, and M. RAUTENBERG ASME, Gas given to stages in the development of a large-military-engine Turbine and Aeroengine Congress and Exposition, Amsterdam, demonstrator program and a small-engine demonstrator program. Netherlands, June 6-9, 1988. 19 p. DFG-supported research. The management details of the technology demonstrator programs refs are described. I.S. (ASME PAPER 88-GT-120) The reverse flow formed from the outlet of the rotor/impeller A08-54227# along the casinglshroud toward the inlet of an axiaVcentrifugal AIR FLOW PERFORMANCE OF AIR SWIRLERS FOR GAS compressor was investigated using colored dye injected through TURBINE FUEL NOZZLES the shroud at the outlet edge of the impeller. Particular attention CHARLES A. MARTIN (Parker Hannifin Corp., Gas Turbine Fuel was given to the stable spiral vortex filaments that compose the Systems Div., Cleveland, OH) ASME, Gas Turbine and Aeroengine reverse flow. The results indicated that the vortex filaments are Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. composed of Taylor’s vortex pairs, but with unequal vortex strengths 8 p. refs within the pair; they form the transition range from a laminar to a (ASME PAPER 88-GT-108) turbulent three-dimensional boundary layer with a very steep The performance of air swirlers with a range of swirl angles tangential velocity profile. It is shown that the orderly path of the and diameters is examined and discussed in the context of recently reverse flow is enabled by the cessation of the leakage flow of published papers. Parameters included in this discussion are swirl the rotor tip clearance. I.S. number, swirler thrust, swirler torque, and swirler solidity. Results suggest that swirler ’see through’ is not necessarily bad, but may A88-54236’# United Technologies Research Center, East be beneficial with respect to swirl number and other parameters. Hartford, Conn. The use of the mean swirler radius to calculate the swirl number THE EFFECTS OF TURBULENCE AND STATOR/ROTOR and the resulting benefits is discussed and demonstrated. INTERACTIONS ON TURBINE HEAT TRANSFER. I DESIGN Author - OPERATING CONDITIONS M. F. BLAIR, R. P. DRING, and H. D. JOSLYN (United Technologies A88-54229’# Indian Inst. of Tech., Madras. Research Center, East Hartford, CT) ASME, Gas Turbine and EFFECT OF STAGE LOADING ON ENDWALL FLOWS IN AN Aeroengine Congress and Exposition, Amsterdam, Netherlands, AXIAL FLOW COMPRESSOR ROTOR June 6-9, 1988. 12 p. refs N. SITARAM (Indian Institute of Technology, Madras, India) ASME, (Contract NAS3-23717) Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, (ASME PAPER 88-GT-125) Netherlands, June 6-9, 1988. 7 p. refs A combined experimental and analytical program was conducted (Contract NSG-3032) to examine the effects of inlet turbulence, stator-rotor axial spacing, (ASME PAPER 88-GT-111) and relative circumferential spacing of first and second stators on This paper reports results from investigations conducted to turbine airfoil heat transfer. The experimental portion of the study determine the effect of stage loading on endwall flows in a low was conducted in a large-scale (approximately 5X engine), ambient speed axial flow compressor. These investigations consisted of temperature, stage-and-a-half rotating turbine model. The data two sets of measurements. The first set consisted of radial indicate that while turbine inlet turbulence can have a very strong transverse of flow properties at the rotor inlet and exit, at five impact on the first stator heat transfer, its impact in downstream flow coefficients. These measurements are used to determine the rows is minimal. The effects on heat transfer produced by relatively boundary layer integral parameters. The displacement thicknesses large changes in stator/rotor spacing or by changing the relative at the rotor hub and tip agree reasonably well with Smith’s (1970) row-to-row circumferential positions of stators were very small. correlation for multistage axial compressors. The second set Analytical results consist of airfoil heat transfer distributions consisted of measurements of static pressures on the rotor blade computed with a finite-difference boundary layer code. Author 12 ENGINEERING

A8844241 # A88-54261# OPTIMIZATION DESIGN OF THE OVER-ALL DIMENSIONS OF SPRAY AUTOMATED BALANCING OF ROTORS - CONCEPT CENTRIFUGAL COMPRESSOR STAGE AND INITIAL FEASIBILITY STUDY QINGHUAN WANG and ZHlQlN SUN (Chinese Academy of ANTHONY J. SMALLEY, RICHARD M. BALDWIN, and WILBUR Sciences, Institute of Engineering Thermophysics, Beijing, People’s R. SCHICK (Southwest Research Institute, San Antonio, TX) Republic of China) ASME, Gas Turbine and Aeroengine Congress ASME, Gas Turbine and Aeroengine Congress and Exposition, and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 6 p. Amsterdam, Netherlands, June 6-9, 1988. 8 p. Research supported refs by the Southwest Research Institute. (ASME PAPER 88-GT-134) (ASME PAPER 88-GT-163) A new procedure employed in computer-aided design of The system design for implementing the spray automated centrifugal compressor stage to determine its over-all dimensions balancing of rotors (SABOR) concept are presented, and the is described in this paper. By the use of the COMPLEX METHOD, method is used to balance a spinning disk without stopping it. the arbitrary number of variables to be optimized can be specified Test results demonstrate the ability of the SABOR method to to remove the hidden danger of the local optima which stems control both angle of application and rate of application to the from adopting a few, for example two or three, variables to be extent needed for effective automated balancing. The bond optimized. This procedure is available for any complicated implicit strengths of materials deposited by the fuel air repetitive explosion nonlinear objective function and ensures establishment of a true process for use in small gas turbine engines are found to be optimum solution. Numerical calculations have been carried out suitable for the level of centrifugal stresses expected. R.R. by using the computer program described here to check the ability of the optimization method. The results obtained by the calculations A88-54263# agree fairly well with that obtained by experiments. Author THE OIL-FREE SHAFT LINE BRUNO WAGNER (Societe de Mecanique Magnetique, Saint-Marcel, France) ASME, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. A88-54245# 12 p. refs A TRANSIENT FLOW FACILITY FOR THE STUDY OF THE (ASME PAPER 88-GT-168) THERMOFLUID-DYNAMICS OF A FULL STAGE TURBINE This paper recalls the principles and main features of the active UNDER ENGINE REPRESENTATIVE CONDITIONS magnetic bearings and especially the advantages for R. W. AINSWORTH, D. L. SCHULTZ, M. D. DAVIES, C. J. P. R. turbomachines, such as oil-free operation and vibration control. FORTH, M. A. HlLDlTCH (Oxford University, England) et al. ASME, Field experiences are described for different shaft line Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, configurations. The trend of the design optimization is the active Netherlands, June 6-9, 1988. 14 p. Research supported by the magnetic bearing in the process gas itself. But at the present Ministry of Defence Procurement Executive, Rolls-Royce, PLC, and stage, the active magnetic bearing is a proven technology. SERC. refs Author (ASME PAPER 88-GT-144) The design and construction of a new experiment, to investigate the steady and unsteady heat transfer and aerodynamic behavior A88-54265# of a rotating turbine in a transient facility, is described. The need FULLY SCALED TRANSONIC TURBINE ROTOR HEAT for this experiment is discussed in the context of previous rotating TRANSFER MEASUREMENTS bar wake and shock simulation work carried out in the Oxford G. R. GUENETTE, A. H. EPSTEIN, M. B. GILES, R. HAIMES transient cascade facility, and research elsewhere on the effects (MIT, Cambridge, MA), and R. J. G. NORTON (Rolls-Royce, Inc., of rotating and three-dimensional flowfields on turbine Atlanta, GA) ASME, Gas Turbine and Aeroengine Congress and aerodynamics and heat transfer. The outline concept and mode Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. Research of operation of the turbine module are given before novel features supported by Rolls-Royce, Inc. and Navy. refs (ASME PAPER 88-GT-171) of the design are presented in detail. The future work program and possible plans for further facility improvements are given. The heat transfer to an uncooled transonic single-stage turbine Author has been measured in a short duration facility which fully simulates all the nondimensional quantities of interest for fluid flow and heat transfer (the Reynolds, Prandtl, and Rossby numbers; the temperature ratios: and corrected speed and weight flow). Data A88-54250# from heat flux gages about the midspan of the rotor profile, THE MEASUREMENT OF STRESS AND VIBRATION DATA IN measured from dc to more than 10 times blade passing frequency TURBINE BLADES AND AEROENGINE COMPONENTS (60 kHz), is presented in both time-resolved and mean-heat-transfer D. E. OLIVER (Ometron, Inc., Herndon, VA) and D. J. BERRY form. These rotating blade data are compared to previously (Ometron, Ltd., England) ASME, Gas Turbine and Aeroengine published heat-transfer measurements on the same profile in a Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. two-dimensional cascade with bar passing to simulate blade-row 4 p. refs interaction effects (Ashworth et al., 1985). The results are (ASME PAPER 88-GT-149) qualitatively quite similar at midspan. The data are also compared This paper describes an instrumental set up that utilizes the to a two-dimensional Navier-Stokes calculation of the blade mean thermoelastic effect to provide full field stress data and vibration section, and the implications for turbine design are discussed. data for aeroengine components and turbine blades, together with Author the theoretical aspects of the thermoelastic effect upon which the stress measurements are based. It is shown that laser Doppler A88-54272# interferometric techniques can be incorporated into this THE FEASIBILITY, FROM AN INSTALLATIONAL VIEWPOINT, stress-measuring instrument, called SPATE stress analyzer. Results OF GAS-TURBINE PRESSURE-GAIN COMBUSTORS from typical aeroengine components obtained using SPATE J. A. C. KENTFIELD (Calgary, University, Canada) ASME, Gas correlated well with strain gages, while yielding benefits of full Turbine and Aeroengine Congress and Exposition, Amsterdam, field data which can be used to provide more comprehensive Netherlands, June 6-9, 1988. 7 p. refs description of the structure under test. The stress analyzer was (Contract NSERC-A-7928) applied to a wide range of materials and geometries including (ASME PAPER 88-GT-181) weldments, plastic models, and composites. The availability of a The principles of pressure-gain combustors based on the wave laser interferometer attachment to the SPATE system offers the rotor and pulse-combustor concepts were reviewed briefly. A study, facility to produce vibration and stress data from the same based on experimental data, in which current-technology experimental set up. IS. pressure-gain combustors were applied to three aircraft-engine

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derivative industrial gas-turbines, covering a power range from 275 vibration-related outages may significantly affect the availability of kW (370 hp) to 29 MW (39,000 hp), showed that engine power gas turbine units; some individual vibration problems may cause increased by 6.5 to 9.6 percent with corresponding reductions of as many as 300 hours or more of unavailability. I.S. equal magnitude in specific fuel consumption. it was concluded that pressure-gain combustors appear to offer sufficent A88-54292# improvements in performance without incurring crippling EXPERIMENTAL INVESTIGATION OF ROTATING STALL IN A installational penalties, although decreases in engine power/weight MISMATCHED THREE STAGE AXIAL FLOW COMPRESSOR ratios were noted, to warrant further research and development. G. L. GIANNISSIS, A. B. MCKENZIE, and R. L. ELDER (Cranfield Author Institute of Technology, England) ASME, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, A88-54273# June 6-9, 1988. 8 p. refs BRUSHES AS HIGH PERFORMANCE GAS TURBINE SEALS (ASME PAPER 88-GT-205) J. G. FERGUSON (Rolls-Royce, PLC, Systems and Transmissions This paper reports on an examination of rotating stall in a low Research Dept., Bristol, England) ASME, Gas Turbine and speed three stage axial flow compressor operating with various Aeroengine Congress and Exposition, Amsterdam, Netherlands, degrees of stage mismatch. The objective of this study was to June 6-9, 1988. 8 p. simulate the mismatching when operating near surge. The study (ASME PAPER 88-GT-182) of the stall zones involved the use of fast response measurement A brush seal replacing the best currently available finned techniques. The study clearly shows how stages can operate in labyrinth seal in a gas turbine application requiring a clearance of an axi-symmetric fashion even when heavily stalled, rotating stall 0.7 mm can reduce leakage to merely 10 percent that of the inception requiring the stall of more than one stage. The study labyrinth device. This dramatic improvement in performance is also compares conditions required for full span and part span associated with its maintenance even during and after transient stall and suggests that the part span stall structure is the more differential movements. Comparative test results have been relevant to high speed multistage compressors. Author obtained with an RB199 engine that demonstrate brush seals’ yielding of significant thrust improvements, of the order of 3 percent, A88-54298# for a given stator outlet temperature. O.C. ROLLING ELEMENT BEARING MONITORING AND DIAGNOSTICS TECHNIQUES A88-54281# R. G. HARKER and J. L. SANDY (Bently Nevada Corp., Minden) INVESTIGATION INTO THE EFFECT OF TIP CLEARANCE ON ASME, Gas Turbine and Aeroengine Congress and Exposition, CENTRIFUGAL COMPRESSOR PERFORMANCE Amsterdam, Netherlands, June 6-9, 1988. 8 p. JOOST J. BRASZ (United Technologies Corp., Carrier Research (ASME PAPER 88-GT-212) Div., Syracuse, NY) ASME, Gas Turbine and Aeroengine Congress Rolling element bearings require distinctly different techniques and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 10 p. for monitoring and diagnostics from those used for fluid-film type refs bearings. A description of these techniques and the instrumentation (ASME PAPER 88-GT-190) used to acquire the necessary data is provided for comparison. The effect of the axial clearance between the tip of an Also included are some case studies to illustrate how these unshrouded impeller and its stationary shroud on the overall techniques are applied. Author compressor performance was investigated. The experiments were carried out in a closed-loop centrifugal compressor test rig with A88-54299# the impeller running at a rotational Mach number 1.39. The results THERMOMECHANICAL ADVANCES FOR SMALL GAS indicated that, if a linear relationship is assumed, the pressure TURBINE ENGINES - PRESENT CAPABILITIES AND FUTURE ratio decreases by 0.77 percent and the efficiency decreases by DIRECTION IN GAS GENERATOR DESIGNS 0.33 points for each percent increase in clearance ratio; there are M. PROPEN, H. VOGEL. and S. AKSOY (Textron, Inc., Avco also an input head reduction of about 0.25 percent and an output Lycoming Textron, Stratford, CT) ASME, Gas Turbine and head reduction of about 0.65 percent. However, the data seem to Aeroengine Congress and Exposition, Amsterdam, Netherlands, indicate a nonlinear effect, with stronger performance sensitivity June 6-9, 1988. 8 p. refs at smaller clearances. A comparison with the results of a (ASME PAPER 88-GT-213) clearance-loss model showed that improved performance prediction Performance requirements of tomorrow’s gas turbines demand can be obtained by including the effect of clearance on impeller major improvements in specific fuel consumption and thrust to work input. I.S. weight ratio. These stringent requirements, in turn, drive the need for higher operating temperatures and lighter weight engines. Such A88-54291# technical improvements impose severe thermal, structural, and ASSESSMENT OF GAS TURBINE VIBRATION MONITORING metallurgical demands upon turbine components. A broad spectrum ALEXANDER LIFSON, ANTHONY J. SMALLEY (Southwest of technology programs is underway at Textron Lycoming to Research Institute, San Antonio, TX), GEORGE H. QUENTIN address these challenging requirements. This paper outlines the (Electric Power Research Institute, Palo Alto, CA), and CHARLES thermal, structural, and materials research needed for achieving L. KNAUF ASME, Gas Turbine and Aeroengine Congress and the goals of the small gas turbines of tomorrow. Author Exposition, Amsterdam, Netherlands, June 6-9, 1988.8 p. Research sponsored by the Electric Power Research Institute. refs A88-54300# (ASME PAPER 88-GT-204) REAL TIME NEUTRON RADIOGRAPHY APPLICATIONS IN This paper discusses the basis for the selection and assessment GAS TURBINE AND INTERNAL COMBUSTION ENGINE of vibration monitoring equipment for industrial gas turbines, TECHNOLOGY provides information on the advantages and disadvantages of JOHN T. LINDSAY and C. W. KAUFFMAN (Michigan, University, different vibration transducer types, and describes typical Ann Arbor) ASME, Gas Turbine and Aeroengine Congress and applications of these transducers. Consideration is given to the Exposition, Amsterdam, Netherlands, June 6-9, 1988. 8 p. refs gas turbine vibration limits and trending, as well as to the typical (ASME PAPER 88-GT-214) costs of gas turbine vibration monitoring systems. Special attention This paper describes a real-time neutron radiography (RTNR) is given to the analysis of relevant data from the ERAS (EPRI facility, developed at the University of Michigan for NDT testing of reliability assessment system developed by Brown and Young, flows generated by gas turbine and internal-combustion engines, 1984) data base compiled for the years 1982-1986, using data together with the results of the RTNR applications. It is shown from 13 power plants with a total number of 28 turbines operating that RTNR can be used to detect coking and debris deposition in in combined cycles and 31 operating as peaking units. Examples gas turbine nozzles; to image a fuel spray from an injector in an of vibration monitoring results are presented. It is shown that operating single-cylinder diesel engine; to locate a lubrication

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blockage; and to study lubrication problems in operating standard A88-54342# internal-combustion engines. The RTNR facility can also be applied LASER - A GAS TURBINE COMBUSTOR MANUFACTURING to measurements not directly related to gas turbine engines, such TOOL as monitoring objects or phenomena that are changing and/or J. TERENCE FEELEY (Laser Fare, Ltd., Inc., Smithfield, RI) and moving. Schematic diagrams of RTNR are included. I.S. E. JACK SWEET ASME, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 6 p. refs A88-54305# (ASME PAPER 88-GT-267) THEORETICAL INVESTIGATION OF THE INTERACTION BETWEEN A COMPRESSOR AND THE COMPONENTS Processes have been developed for the machining and welding DURING SURGE of gas turbine engine combustor liners with laser outputs. Major JUERGEN BRUMM, HASSAN KALAC, and INGOLF TEIPEL goals of these development efforts encompassed the cutting and (Hannover, Universitaet, Hanover, Federal Republic of Germany) drilling of chrome-nickel alloys and refractory ceramics, in order ASME, Gas Turbine and Aeroengine Congress and Exposition, to yield precise dimensions without airflow pattern-disrupting burrs Amsterdam, Netherlands, June 6-9, 1988. 6 p. DFG-supported or slag; laser welding operations were required to result in no research. refs dimensional distortions and to leave no built-in cracks that might (ASME PAPER 88-GT-220) propagate in response to fatigue loading. Results superior to those The surge phenomenon in a compression system consisting obtainable with conventional punching, drilling, and welding have of a compressor, a duct, and a plenum is analyzed using a been achieved. O.C. theoretical model based on the application of mass, momentum, and energy conservation equations of one-dimensional flow. The A88-54345# set of hyperbolic differential equations is solved numerically using A NEW SOURCE OF LIGHTWEIGHT, COMPACT MULTIFUEL a predictor-corrector scheme. At the interface between two POWER FOR VEHICULAR, LIGHT AIRCRAFT AND AUXILIARY components, coupling conditions for pressure and flow velocity APPLICATIONS - THE JOINT DEERE SCORE ENGINES are taken from the method of characteristics. The performance of CHARLES JONES (John Deere Technologies International, Inc., the compressor is determined by its performance map, which Wood-Ridge, NJ) ASME, Gas Turbine and Aeroengine Congress describes the relationship between pressure and mass flux for all and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 9 p. conditions from stable performance to inverse mass flow. The refs pressure-time history is compared with data in the literature, and (ASME PAPER 88-GT-271) the general time dependent surge performance is considered in Deere & Co. has actively pursued development of the multifuel comparison with the quasi-steady characteristic. V.L. Wankel-type stratified charge engine since February, 1984. During this period, a new R & D facility has been established where development is in progress for three new engine families having A88-54311# basic displacements of .66, 1.72 and 5.8 liters/rotor, for a 1 to 8 COMPARISON OF CERAMIC VS. ADVANCED SUPERALLOY rotor engine output range from 37 to 2250 kW (50 to 3,000 HP). OPTIONS FOR A SMALL GAS TURBINE TECHNOLOGY The initial SCORE (stratified charge omniverous rotary engines) DEMONSTRATOR production engines are expected to be placed into service next T. BORNEMISZA and J. NAPIER (Sundstrand Turbomach, San year. This series of three engine families offers the size, weight Diego, CA) ASME. Gas Turbine and Aeroengine Congress and and low vibration characteristics of small gas turbines and the Exposition, Amsterdam, Netherlands, June 6-9, 1988. 10 p. refs fuel efficiency and initial cost characteristics of diesel engines. (ASME PAPER 88-GT-228) This paper describes the combustion concept, relates relevant In the pursuit of higher turbine inlet temperatures for history and gives the current development status for all three next-generation APU gas turbines, a series of comparative tests basic sizes. Author has been run to ascertain the relative advantages and disadvantages of ceramic radial-inflow turbine rotors vs. air-cooled A88-54354# superalloy ones, at operating temperatures in excess of 2000 F. WEIBULL ANALYSIS TECHNIQUES ON A DESKTOP The ceramic turbine is fabricated from hot-pressed silicon nitride; COMPUTER the air-cooled superalloy turbine is fabricated by isothermal forging J. L. BYERS (U.S. Navy, Naval Air Development Center, from single-crystal, rapid solidification-rate Alloy 'Y', which Warminster, PA) ASME, Gas Turbine and Aeroengine Congress possesses exceptional creep life. While the ceramic turbine entails and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 5 p. higher risks, far greater potential benefits will result from increased refs development investment. O.C. (ASME PAPER 88-GT-285) This paper presents a summary of a task to provide individual A88-54328'# Cornell Univ., Ithaca, N.Y. US. Navy project engineers with analytical tools that enable them NUMERICAL RESULTS FOR AXIAL FLOW COMPRESSOR to perform Weibull failure and related analyses on a desktop INSTABILITY computer. An integrated computer program that allows Navy F. E. MCCAUGHAN (Cornell University, Ithaca, NY) ASME, Gas analysts to perform rigorous trade-off and what-if analyses in an Turbine and Aeroengine Congress and Exposition, Amsterdam, interactive manner without having to send the problem off to a Netherlands, June 6-9, 1988. 9 p. refs central computer facility. The resulting computer codes exist in (Contract NAG3-349) several forms to fit the various needs and computer configurations, (ASME PAPER 88-GT-252) such as: direct input of data, data file creation and update, and Using Cornell's supercomputing facilities, an extensive study nonprinting versions for those who have no printer available. of the Moore-Greitzer model was carried out, which gives accurate Included in the codes are three Monte Carlo routines and several and reliable information about compressor instability. The test-plan generation codes. Author bifurcation analysis in the companion paper shows the dependence of the mode of compressor response on the shape of the rotating A88-54355'# Pratt and Whitney Aircraft, East Hartford, Conn. stall characteristic. The numerical results verify and extend this CURRENTSTATUSANDFUTURETRENDSINTURBINE with a more accurate representation of the characteristic. The APPLICATION OF THERMAL BARRIER COATINGS effect of the parameters on the shape of the rotating stall KEITH D. SHEFFLER and DINESH K. GUPTA (Pratt and Whitney, characteristic is investigated, and it is found that the parameters East Hartford, CT) ASME, Gas Turbine and Aeroengine Congress with the strongest effects are the inlet length, and the shape of and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 9 p. the compressor pressure rise vs. mass flow diagram (i.e. tall refs diagrams vs. shallow diagrams). The effects of inlet guide vane (Contract NAS3-23944) loss on the characteristic are discussed. Author (ASME PAPER 88-GT-286)

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This paper provides an overview of the current status and is described using a remote eddy current/visual inspection system future trends in application of thermal barrier coatings (TBC) to for steam turbine blades and an air-transportable multitechnique turbine components, and in particular to high turbine airfoils. turbine rotor inspection system as examples. The design Included are descriptions of the favorable results achieved to date requirements for these systems are examined, and it is shown with bill-of-material applications of plasma deposited TBC, and how unique design solutions have been found in each case to recent experience with developmental coatings applied by electron provide transportable reliable remote NDE systems. Based on the beam-physical vapor deposition. Author experience gained in developing and using the systems described here, the principal steps in developing a portable remote inspection A88-54361# system are identified. V.L. BOUNDARY-LAYER FLOWS IN ROTATING CAVITIES C. L. ONG and J. M. OWEN (Sussex, University, Brighton, England) ASME, Gas Turbine and Aeroengine Congress and A88-55154 Exposition, Amsterdam, Netherlands, June 6-9, 1988. 10 p. NEW APPARATUS FOR STUDYING FATIGUE DEFORMATION Research supported by SERC, Rolls-Royce, PLC, and Ruston Gas AT HIGH MAGNIFICATIONS Turbines, PLC. refs ROBERT R. STEPHENS and DAVID W. HOEPPNER (Utah, (ASME PAPER 88-GT-292) University, Salt Lake City) Review of Scientific Instruments (ISSN Differential boundary layer equations modelling the flow between 0034-6748), vol. 59, Aug. 1988, pt. 1, p. 1412-1419. Research two corotating air-cooled gas-turbine disks are solved to study supported by Rolls-Royce, PLC. refs the velocity distribution inside the entraining and nonentraining One of the steps taken to enhance accurate fatigue life boundary layers and in the inviscid core. The equations are estimations and material modeling is the development of an discretized using the box scheme of Keller and Cebeci (1972), electrohydraulic, servocontrolled feedback fatigue apparatus that and the Cebeci-Smith (1974) eddy-viscosity model is used to treat has been joined to a scanning electron microscope. This apparatus the turbulent-flow case. Good agreement between the present allows in situ observations of cyclically loaded specimens computations and previous experimental results is obtained for a undergoing fatigue deformation. Using this apparatus, recordings wide range of flow rates and rotational speeds. R.R. can be made of the events related to the surface response of materials under different loading conditions, showing how microstructural features influence crack nucleation and propagation A88-54385# behavior. With the development of this apparatus, existing FIBER OPTICS BASED JET ENGINE AUGMENTER VIEWING mathematical models describing the fatigue process can be SYSTEM enhanced or improved, and more accurate fatigue life estimation P. J. MURPHY, D. W. JONES, R. R. JONES, 111 (Sverdrup Technology, Inc., Arnold AFB, TN), and A. E. LENNERT ASME, methods can be obtained. The apparatus developed is described Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, herein, as well as a few selected results. Author Netherlands, June 6-9, 1988. 5 p. (ASME PAPER 88-GT-320) A88-55372# An augmenter viewing system employing a coherent fiber-optic APPLICATION OF THE THEORY OF ANISOTROPIC array was developed for use in jet engine testing applications at THIN-WALLED BEAMS AND PLATES FOR WINGS MADE AEDC. Real-time viewing of the test article afterburner was obtained FROM COMPOSITE MATERIAL in a severe environment under high temperature and vibration N. V. BANICHUK, V. V. KOBELEV, and A. D. LARICHEV (AN levels. The optical system consisted of a conventional front-end SSSR, Moscow, USSR) IAF, International Astronautical Congress, lens assembly coupled with the fiber-optic array, and a solid-state 39th, Bangalore, India, Oct. 8-15, 1988. 11 p. refs color video camera mounted inside the test cell. The advantages (IAF PAPER 88-275) and problems associated with a fiber-optics-based viewing system Solutions are presented for divergence and static bending will be discussed in comparison with more conventional viewing problems for anisotropic wings, which are modeled as anisotropic techniques for this application. Author thin-walled beams of closed cross section. The governing equations are derived using variational principles, with special attention given A88-54566 to coupled torsion-bending effects. The effect of anisotropic FAULT DETECTION IN MULTIPLY-REDUNDANT tailoring on the critical divergence speed of the wing is investigated MEASUREMENT SYSTEMS VIA SEQUENTIAL TESTING analytically. Optimum orientations of anisotropy axes for the wing ASOK RAY (Pennsylvania State University, University Park) IN: skin are calculated by the successive optimization method. V.L. 1988 American Control Conference, 7th, Atlanta, GA, June 15-17, 1988, Proceedings. Volume 2. New York, Institute of Electrical and Electronics Engineers, 1988, p. 1400-1405. refs A88-55456 The theory and application of a sequential test procedure for THE NON-DESTRUCTIVE TESTING OF WELDS IN fault detection and isolation. The test procedure is suited for CONTINUOUS FIBRE REINFORCED THERMOPLASTICS development of intelligent instrumentation in strategic processes G. R. EDWARDS (Welding Institute, Cambridge, England) IN: like aircraft and nuclear plants where redundant measurements Composites evaluation; Proceedings of the Second International are usually available for individual critical variables. The test Conference on Testing, Evaluation and Quality Control of procedure consists of (1) a generic redundancy management Composites-TEQC 87, Guildford, England, Sept. 22-24, 1987. procedure which is essentially independent of the fault detection Sevenoaks, England and Stoneham, MA, Butterworths, 1987, p. strategy and measurement noise statistics, and (2) a modified 3-10. refs version of sequential probability ratio test algorithm for fault Practices used in the nondestructive testing for defects in detection and isolation, which functions within the framework of thermoplastic composite materials are discussed, with special this redundancy management procedure. The sequential test attention given to the current practice for the NDT of composite procedure is suitable for real-time applications using commercially aircraft structures and the test equipment used in these procedures. available microcomputers and its efficacy has been verified by The NDT methods applicable for the detection of particular possible online fault detection in an operating nuclear reactor. LE. defects, such as delamination/disbonds, porosity, inclusions, fiber misalignment, broken fibers, matrix cracking, weak bonds, and A88-55042 fiberlmatrix volume are examined. Special consideration is given DESIGN CONSIDERATIONS IN REMOTE TESTING to tests that include adhesively bonded joints and welded joints. EUGENE R. REINHART (Reinhart and Associates, Inc., Austin, It is emphasized that, for testing welded joints in thermoplastic TX) Materials Evaluation (ISSN 0025-5327). vol. 46, Sept. 1988, composites, the existing test procedures must be further developed p. 1301-1306, 1308. 1309. refs and include such procedures as computerized ultrasonic immersion A general approach to the design of portable remote systems tests and thermography. I.S.

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N88-29061# Naval Ocean Systems Center, San Diego, Calif. N88-29112# Naval Postgraduate School, Monterey, Calif. EFFECT OF PHASE ERRORS IN STEPPED-FREQUENCY A MAPPING OF THE VISCOUS FLOW BEHAVIOR IN A I RADAR SYSTEMS Final Report, Jan. 1987 - Jan. 1988 CONTROLLED DIFFUSION COMPRESSOR CASCADE USING H. E. VANBRUNDT Apr. 1988 12 p LASER DOPPLER VELOCIMETRY AND PRELIMINARY (AD-A194476; AD-E500985; NOSC/TR-1211) Avail: NTlS HC EVALUATION OF CODES FOR THE PREDICTION OF STALL AO3/MF A01 CSCL 171 Ph.D. Thesis Stepped-frequency waveforms are being considered for inverse YEKUTIEL ELAZAR Mar. 1988 252 p synthetic aperture radar (ISAR) imaging from ship and airborne (AD-A194490; NPS67-88-001) Avail: NTlS HC A12/MF A01 platforms and for detailed radar cross section (RCS) measurements CSCL 20D of ships and aircraft. These waveforms make it possible to achieve Detailed measurements were made at M=0.25 and Re sub c resolutions of 1.0 foot by using existing radar designs and = 700,000 of the flow through a linear compressor cascade of processing technology. One problem not yet fully resolved in using controlled diffusion (CD) blading using a two-component argon-ion stepped-frequency waveform for ISAR imaging is the deterioration laser Doppler velocimeter system. The measurements included in signal level caused by random frequency error. Random mapping of the inviscid flow in the passage between two adjacent frequency error of the stepped-frequency source results in reduced blades, boundary layer surveys, and wake surveys. Viscous flow peak responses and increased null responses. The resulting phenomena such as a laminar separation region with reattachment reduced signal-to-noise ratio is range dependent. Two of the major on the suction surface, and laminar to turbulent transition on the concerns addressed in this report are radar range limitations for pressure surface were resolved, and the viscous growth to the EAR and the error in calibration for RCS measurements caused trailing edge was defined for three inlet angles from design by differences in range between a passive reflector used for an incidence to near stall. Numerical calculations to predict the flow RCS reference and the target to be measured. In addressing these were carried out using a fully developed boundary layer code, a concerns, NOSC developed an analysis to assess the tolerable strongly interactive viscous inviscid code and a Navier Stokes frequency error in terms of resulting power loss in signal power code. It was shown that the common weakness of numerical and signal-to-phase noise. GRA predictors was in the modelling of transition and turbulence. The documented data can be used generally to calibrate compressor cascade analysis codes and thus enable reliable predictions of N88-29110# Scientific Research Associates, Inc., Glastonbury, stall. GRA Conn. AN EFFICIENT PATCHED GRID NAVIER-STOKES SOLUTION N88-29 124# Von Karman Inst. for Fluid Dynamics, FOR MULTIPLE BODIES, PHASE 1 Final Report No. 1 Rhode-Saint-Genese (Belgium). Y. T. CHAN and BERNARD C. WEINBERG 3 Feb. 1988 32 p MODELING OF LARGE STALL IN AXIAL COMPRESSORS (Contract DAAL03-87-C-0010) [MODELISATION DU GRAND DECROCHAGE DANS LES (AD-A1941 66; SRA-R88-930015-F; ARO-25053.1-EG-SBI) Avail: COMPRESSEURS AXIAUX] NTlS HC A03/MF A01 CSCL 12A D. BUlSlNE Feb. 1988 69 p In FRENCH A major problem area in current computational fluid dynamics (VKI-TN-164; ETN-88-92720) Avail: NTlS HC A04/MF A01 technology concerns flows about complex configurations formed A model to describe the behavior of large three-dimensional by multiple components in relative motion. Major difficulties flow structures in stalled flow, e.g., return, stagnation, and centrifuge encountered in such problems are those associated with the grid. zones, is outlined. The interblade channels and spaces are modeled For such applications, the geometric constraints of the component by macroelements which are sufficiently parameterized to take elements often require that patched grids be employed. Herein, a account of structures found in experimental studies. These novel and efficient procedure is described to solve the elements, directed by equations for mass budget, amount of motion, time-dependent, multidimensional Navier-Stokes equations about and vorticity, are then assembled. Pressure was calculated by multiple body configurations. In contrast to existing patched grid integration over the entire space constituted by the machine of approaches, the present method calculates the entire flow field the local elliptic system with respect to the boundary conditions over both grids simultaneously, without iteration. By eliminating for inflow and outflow. Only the first member operator was tested. iteration within a time step and allowing time steps to be chosen Results are encouraging. ESA by accuracy considerations, rather than by stability limits, this procedure could lead to a substantial savings in computer run N88-29142*# National Aeronautics and Space Administration. time. In addition, for steady state problems improved convergence Lewis Research Center, Cleveland, Ohio. rates could be expected. To demonstrate the capabilities and OPTICAL MEASUREMENT OF UNDUCTED FAN BLADE advantages of the new procedure, a problem of current interest DEFLECTIONS in turbomachinery, the flow field in a rotor-stator stage, is ANATOLE P. KURKOV 1988 14 p Proposed for presentation investigated using the developed procedure. A steady state flow at the 34th International Gas Turbine and Aeroengine Congress field about a cascade of displaced tandem Joukowski airfoils is and Exposition, Toronto, Ontario, 4-8 Jun. 1989 considered. The accuracy of the calculations and CPT time used (NASA-TM-100966; E-4131-1; NAS 1.15:100966) Avail: NTlS HC are compared with a calculation using a continuous deformed grid AO3/MF A01 CSCL 148 algorithm and a patched grid with iteration. GRA A nonintrusive optical method for measuring unducted fan (or propeller) blade deflections is described and evaluated. The measurement does not depend on blade surface reflectivity. N88-29111# Naval Postgraduate School, Monterey, Calif. Deflection of a point at the leading edge and a point at the trailing FLOW VISUALIZATION BY LASER SHEET M.S. Thesis edge in a plane nearly perpendicular to the pitch axis is obtained JOSEPH S. CHLEBANOWSKI, JR. Mar. 1988 33 p with a single light beam generated by a low-power, helium-neon (AD-A194481) Avail: NTlS HC A03/MF A01 CSCL 148 laser. Quantitiative analyses are performed from taped signals on A flow visualization system using smoke and a laser sheet for a digital computer. Averaging techniques are employed to reduce illumination has been designed and developed for use in the 32- random errors. Measured static deflections from a series of x 45-inch low speed wind tunnel. Major design features include a high-speed wind tunnel tests of a counterrotating unducted fan portable smoke rake designed for ease of installation and removal, model are compared with available, predicted deflections, which the use of fiber optics to transport the laser light in a safe and are also used to evaluate systematic errors. Author convenient manner, and a portable traversing mechanism to traverse and orient the laser light sheet. The capabilities of the N88-29204# Anamet Labs., Inc., Hayward, Calif. flow visualization system have been demonstrated by producing INTERACTIVE PLOTTING OF NASTRAN AERODYNAMIC qualitative photographic recordings of complex flow patterns past MODELS USING NPLOT AND DISSPLA Final Report, Jun. - an airfoil model and a missile model. GRA Aug. 1987 12 ENGINEERING

STEVEN G. HARRIS Mar. 1988 32 p are validated by comparison with experiment. Overall good (Contract F33615-84-C-3216) agreement is observed with static pressure comparisons. (AD-A194115; REPT-587-1A; AFWL-TR-87-99) Avail: NTlS HC Preliminary flow analysis indicates the existence of a number of A03/MF A01 CSCL 01A interesting flow structures including shocks, pressure wave systems The computer program NPLOT is extended to permit interactive and regions of flow separation. Viscous-inviscid interactions, plotting of NASTRAN doublet lattice aerodynamic models. In Computational fluid dynamics, Navier-stokes equations, addition, a translator is developed between Precision Visuals Turbulence. GRA 01-3000 plot package and ISSCO’s DISSPLA plot package to permit NPLOT to be run at facilities that support only DISSPLA. The resulting package is useful as a general debugging tool for N88-30066’# United Technologies Research Center, East NASTRAN aerodynamic analysis and as an integral part of nuclear Hartford, Conn. vulnerability model generation programs developed in previous ASSESSMENT OF A 3-D BOUNDARY LAYER ANALYSIS TO work. GRA PREDICT HEAT TRANSFER AND FLOW FIELD IN A TURBINE PASSAGE Final Analysis Report N88-29996# Army Natick Research and Development Command, 0. L. ANDERSON 29 Aug. 1985 93 p Mass. (Contract NAS3-23716) CONTROL SYSTEMS FOR PLATFORM LANDINGS (NASA-CR-174894; NAS 1.26:174894; R85-956834) Avail: NTlS CUSHIONED BY AIR BAGS Final Technical Report, Jul. - Aug. HC AO5/MF A01 CSCL 20D 1985 An assessment was made of the applicability of a three EDWARD W. ROSS Jul. 1987 40 p dimensional boundary layer analysis of heat transfer, total pressure (AD-A1961 54; NATICK/TR-88/021) Avail: NTlS HC AOS/MF losses, and streamline flow patterns on the surfaces of both A01 CSCL 15E stationary and rotating turbine passages. In support of this effort, This report presents an exploratory mathematical study of an analysis was developed to calculate a general nonorthogonal control systems for airdrop platform landings cushioned by airbags. surface coordinate system for arbitrary three dimensional surfaces The basic theory of airbags is reviewed and solutions to special and also to calculate the boundary layer edge conditions for cases are noted. A computer program is presented, which compressible flow using the surface Euler equations and calculates the time-dependence of the principal variables during a experimental pressure distributions. Calculations are presented for landing under the action of various control systems. Two existing the pressure, endwall, and suction surfaces of a stationary cascade control systems of open-loop type are compared with a conceptual and for the pressure surface of a rotating turbine blade. The results feedback (closed-loop) system for a fairly typical set of landing strongly indicate that the three dimensional boundary layer analysis conditions. The feedback controller is shown to have performance can give good predictions of the flow field, loss, and heat transfer much superior to the other systems. The feedback system on the pressure, suction, and endwall surface of a gas turbine undergoes an interesting oscillation not present in the other passage. Author systems, the source of which is investigated. Recommendations for future work are included. GRA N88-30069# Tennessee Univ., Tullahoma. N88-30006# Air Force Weapons Lab., Kirtland AFB, N. Mex. CONTAMINATION AND DISTORTION OF STEADY FLOW EMPTAC (ELECTROMAGNETIC PULSE TEST AIRCRAFT) FIELD INDUCED BY DISCRETE FREQUENCY DISTURBANCES USER’S GUIDE Final Report, Oct. 1984 - Dec. 1986 IN AIRCRAFT GAS ENGINES Final Report, Jan. - Dec. 1987 DALE R. CLEAVELAND and AVERY BURKHARD Apr. 1988 M. KUROSAKA Apr. 1988 5 p 56 P (Contract AF-AFOSR-0049-83) (AD-A195072; AFWL-TR-88-28) Avail: NTlS HC A04/MF A01 (AD-A195440; AFOSR-88-0640TR) Avail: NTlS HC A02/MF A01 CSCL 20N CSCL 20D This guide was established to give test managers a way to The main objective of this program was to acquire fundamental familiarize themselves with the Air Force Weapons Laboratory’s understanding of two aerodynamic effects induced by vortices shed electromagnetic pulse (EMP) test aircraft program located at by blades of aircraft gas turbines: (1) the instantaneous separation Kirtland Air Force Base (KAFB), New Mexico. Brief descriptions of total temperature and pressure around vortices in the wake of the available EMP test facilities at KAFB are also included. shed and its time averaged effect; and (2) the issue of over 100 This guide should give prospective customers (users) adequate percent efficiency measured near the hub section of an advanced information to scope the magnitude of their test effort and to turbofan design of the Air Force Aeropropulsion Laboratory. accomplish general planning without extensive involvement in test Through the combination of experimental and theoretical execution details. GRA investigations, the mechanisms of the two phenomena have been identified. GRA N88-30064# Rutgers - The State Univ., New Brunswick. N. J. Dept. of Mechanical and Aerospace Engineering. NUMERICAL SIMULATION OF NOZZLE FLOWS Final Report, N88-30091# Rolls-Royce Ltd., Derby (England). May 1984 - Aug. 1987 POSITRON EMISSION TOMOGRAPHY A NEW TECHNIQUE DOYLE D. KNIGHT and DATA V. GAITONDE 18 Feb. 1988 FOR OBSERVING FLUID BEHAVIOR IN ENGINEERING 91 P SYSTEMS (Contract F33615-84-K-3009) P. A. E. STEWART, J. D. ROGERS, R. T. SKELTON, P. SALTER, (AD-A1951 44; RU-TR-169-MAE-F; AFWAL-TR-87-3110) Avail: M. ALLEN, R. PARKER, P. DAVIS, P. FOWLES, M. R. NTlS HC A05/MF A01 CSCL 20D HAWKESWORTH, M. A. ODWYER et al. 17 Sep. 1988 27 p A three-dimensional grid generation code implementing the Presented at the EWD NDT Conference, London, United Kingdom, multisurface technique is developed with major emphasis on the 13-17 Sep. 1987 Sponsored by the United Kingdom Science use of color computer graphics. A precise control method is and Engineering Research Council employed to permit grid point control. A significant departure from (PNR90471; ETN-88-92698) Avail: NTlS HC A03/MF A01 existing approaches is the extension of user interaction to all Positron emission tomography for flow tracing and measurement phases of grid generation. This facilitates easy and rapid within metal structures in general and operating engines in particular developments of grids especially for 3-D applications. The code is is introduced. The principles involved are outlined, and a mobile employed to generate grids for a 3-D axisymmetric nozzle and an positron camera system is described. Examples of the camera’s aircraft type section. The flow is a non-axisymmetric nozzle, capability drawn from its use to study annular oil volumes simulated computed under the assumptions of horizontal and vertical by positron line sources in a power turbine shaft and in a small symmetry. The Mach number of external flow is 1.2. The results helicopter engine are presented. ESA

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N88-30093*# National Aeronautics and Space Administration. calculation flow and stability code program. A whole series of Hugh L. Dryden Flight Research Facility, Edwards, Calif. unsteady measurements were carried out in order to describe the TECHNIQUES USED IN THE F-14 VARIABLE-SWEEP machine’s functioning around surge point. Author TRANSITION FLIGHT EXPERIMENT BIANCA TRUJILLO ANDERSON, ROBERT R. MEYER, JR., and N88-30140# Industrial Quality, Inc., Gaithersburg, Md. HARRY R. CHILES Jul. 1988 25 p Presented at the 4th DEVELOPMENT OF GRADED REFERENCE RADIOGRAPHS AlAA Flight Test Conference, San Diego, Calif., 18-20 May 1988 FOR ALUMINUM WELDS, PHASE 1 Final Report, 7 Jul. 1987 - (NASA-TM-100444; H-1461; NAS 1.15:100444; AIAA-88-2110) 7 Mar. 1988 Avail: NTlS HC AO3/MF A01 CSCL 20D DANIEL POLANSKY, EDWARD CRISCUOLO, HAROLD BERGER, This paper discusses and evaluates the test measurement and THOMAS S. JONES 7 Mar. 1988 33 p techniques used to determine the laminar-to-turbulent boundary (Contract DAAK70-87-C-0027) layer transition location in the F-14 variable-sweep transition flight (AD-A195594) Avail: NTlS HC A03/MF A01 CSCL 11F experiment (VSTFE). The main objective of the VSTFE was to The purpose of this Small Business Innovation Research Phase determine the effects of wing sweep on the laminar-to-turbulent 1 project was to develop a data bank for graded sets of reference transition location at conditions representative of transport aircraft. radiographs of aluminum welds. Reference radiographic documents Four methods were used to determine the transition location: (1) of this type are extremely valuable for procurements related to a hot-film anemometer system; (2) two boundary-layer rakes; (3) ships, aircraft, other vehicles, construction and similar projects surface pitot tubes; and (4) liquid crystals for flow visualization. Of that include aluminum welds. The reference radiographs serve as the four methods, the hot-film anemometer system was the most a recognized way of acceptance or rejection of welds. There are reliable indicator of transition. Author no recognized standards for graded reference radiographs of aluminum welds. The only alternative at present is to use graded N88-30 107# Aeronautical Research Labs., Melbourne sets of reference radiographs for steel welds such as ASTM (Australia). standard E-390. This is not a technically acceptable alternative DEVELOPMENT AND INSTALLATION OF AN because the radiographic contrasts and general appearance are INSTRUMENTATION PACKAGE FOR GE F404 INVESTIGATIVE different for steel welds as compared to aluminum welds. During TESTING this Phase 1 project, a data bank of production radiographs of D. K. STREATFEILD Jan. 1988 36 p aluminum welds was collected. Several thousand radiographs are (ADA196265; ARL/AERO-PROP-TM-446; DODA-AR-004-584) presently in the data bank. From this data bank, a set of proposed Avail: NTlS HC A03/MF A01 CSCL 21E reference radiographs has been assembled. These include five The development and installation of an Instrumentation Package grades of reference radiographs for three types of porosity, fine for GE F404 Investigative Testing is described. The package is scattered porosity, coarse scattered porosity and linear porosity. used in conjunction with the ARL MOBILE (Transient) Data The suggested reference radiograph document also includes three Acquisition System (MODAS) and can be used on the F404 engine grades of clustered porosity, two illustrations of inadequate at both Fixed or Mobile Engine Test locations. GRA penetration, two illustrations of tungsten inclusions, and examples of longitudinal and transverse cracks, lack of fusion and undercut. GRA N88-30128’# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. N88-30142# California Univ., Berkeley. Dept. of Materials Science HELICOPTER TRANSMISSION RESEARCH AT NASA LEWIS and Mineral Engineering. RESEARCH CENTER MODELING OF MICROMECHANISMS OF FATIGUE AND JOHN J. COY, DENNIS P. TOWNSEND, DAVID G. LEWlCKl (Army FRACTURE IN HYBRID MATERIALS Annual Report No. 1,15 Aviation Systems Command, Cleveland, Ohio.), and HAROLD H. Apr. 1987 - 14 Apr. 1988 COE 1988 19 p Prepared for presentation at the International R. 0. RITCHIE, W. YU, and S. C. SIU May 1988 59 p Conference on Gearing, Zhengzhou, Peoples Republic of China, (Contract AF-AFOSR-0158-87) 5-10 Nov. 1988; sponsored in part by the Chinese Mechanical (AD-A195604; UCB/R/88/A1053) Avail: NTlS HC A04/MF A01 Engineering Society CSCL 11D (Contract DA PROJ. 1L1-62209-A-47-A) The obvious benefits of the design of aerospace structures (NASA-TM-100962; E-4181 ; AVSCOM-TM-88-C-003; NAS using lighter materials with high specific strengths and stiff ness 1.15:100962) Avail: NTlS HC A03/MF A01 CSCL 131 has led in recent years to the development of numerous reinforced A joint helicopter transmission research program between NASA composite materials, which have become serious commercial Lewis Research Center and the US. Army Aviation Systems competitors to traditional monolithic metallic alloys. While significant Command has existed since 1970. Program goals are to reduce advances in processing technology have made the fabrication of weight and noise and to increase life and reliability. Reviewed are such hybrid materials more of an economic reality, their widespread significant advances in technology for gears and transmissions use in airframes or other critical structures has in general been and the experimental facilities at NASA Lewis for helicopter limited by serious deficiencies in particular mechanical properties, transmission testing are described. A description of each of the such as ductility, toughness and fatigue. This problem is often rigs is presented along with some significant results from the compounded by the lack of fundamental studies which provide a experiments. Author rational basis for the underlying sources of crack-propagation resistance in these materials, and in particular which define the N88-30129# Ecole Nationale Superieure de I’Aeronautique et critical role of composite microstructure. Accordingly, the current de I’Espace, Toulouse (France). program is aimed at studying the physics and micromechanisms STUDIES OF UNSTEADY AXIAL-COMPRESSOR FUNCTIONING of fracture toughness and particularly the fatigue-crack growth A. CARRERE 1986 55 p In FRENCH Sponsored by resistance in laminate, discontinuously-reinforced and Direction des Recherches, Etudes et Techniques, Paris, France continuously-reinforced metal-matrix composites, with special Avail: NTlS HC E04/MF E04; copy not available from STI Facility reference to the role of microstructure. GRA Unsteady functioning of axial flow compressors are studied just before a surge. The ENSAE compressor test bench, consisting N88-30143# Grumman Aerospace Corp.. Bethpage, N.Y. of two transonic axial compressor stages, is specially designed to AUTOMATED EARLY FATIGUE DAMAGE SENSING SYSTEM record steady and unsteady measurements at a number of points. Final Report, 5 Dec. 1983 - 6 Sep. 1987 Axisymmetric flow in this compressor was first studied and ALAN HENCKEN and MICHAEL HORN Mar. 1988 93 p described using experimental methods (study of distribution at the (Contract F33615-83-C-3225) inlet and diagram of the compressor field in the steady mode), (AD-A19571 7; AFWAL-TR-88-3008) Avail: NTlS HC AO5/MF then compared to axisymmetric flow calculated by the SNECMA A01 CSCL 11F

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Structural fatigue testing plays a vital role in assuring the long 13 term integrity of aerospace vehicles and components. However, substantial uncertainty involving large-scale complex structural tests GEOSCIENCES does exist due to their inherent one shot nature. Crack propagation not revealed by a catastrophic failure during a single test can cause structural problems later in production aircraft. The overall Includes geosciences (general); earth resources; energy production objective of this program was to develop a reliable nondestructive and conversion; environment pollution; geophysics; meteorology testing system for the detection of initiating cracks generated during and climatology; and oceanography. structural fatigue testing. The goals were to: (1) detect cracks as small as 0.050 in. in complex structures, and (2) develop a detection system that could be operated by technician-level personnel N88-29258*# Electro Magnetic Applications, Inc., Denver, Colo. typically assigned to structural test areas. GRA INVESTIGATIONS INTO THE TRIGGERED LIGHTNING RESPONSE OF THE F106B THUNDERSTORM RESEARCH AIRCRAFT TERENCE H. RUDOLPH, RODNEY A. PERALA, PAUL M. MCKENNA, and STEVEN L. PARKER Washington, D.C. Jun. 1985 215 p (Contract NASl-16984) (NASA-CR-3902; NAS 1.26:3902; EMA-854-02) Avail: NTlS HC AlO/MF A01 CSCL 048 N88-30157# Aeronautical Research Inst. of Sweden, Stockholm. An investigation has been conducted into the lightning Structures Dept. characteristics of the NASA F106B thunderstorm research aircraft. STANDARD FATIGUE SPECIMENS FOR FASTENER The investigation includes analysis of measured data from the EVALUATION aircraft in the time and frequency domains. Linear and nonlinear BJORN PALMBERG and LARS JARFALL (Saab-Scania, Goteberg, computer modelling has also been performed. In addition, new Sweden ) Oct. 1987 51 p computer tools have been developed, including a new enhanced (Contract FMV-FFL-82250-85-076-73-001) nonlinear air breakdown model, and a subgrid model useful for (FFA-TN-1987-68; ETN-88-93062) Avail: NTlS HC A04/MF A01 analyzing fine details of the aircraft's geometry. Comparison of Spectrum fatigue testing was carried out using single shear measured and calculated electromagnetic responses of the aircraft joints with U-channel splice plates and four different fastener to a triggered lightning environment are presented. Author systems. Single column, double row joints were used. The joints frequently developed splice plate failures making the completion N88-29259'# National Aeronautics and Space Administration. of the testing program not worthwhile. Studies of secondary Langley Research Center, Hampton, Va. bending, amount of load transfer and fastener flexibility were THE 1983 DIRECT STRIKE LIGHTNING DATA, PART 1 performed successfully. The base plate material in the joints was MITCHEL E. THOMAS Washington, D.C. Aug. 1985 439 p 5 mm thick aluminum alloy 7050-T73651. The four different fastener (NASA-TM-86426-PT-1; NAS 1.1 5:86426-PT-l) Avail: NTlS HC systems included Hi-lok and Hi-tigue fasteners mounted in plain A19/MF A01 CSCL 048 holes, interference fit holes, and cold worked holes. Bending ratio Data waveforms are presented which were obtained during depends slightly on the fastener system used and having a the 1983 direct strike lightning tests utilizing the NASA F106-B magnitude in the range 0.27 'to 0.41. Midpoint supporting increases aircraft specially instrumented for lightning electromagnetic secondary bending. Load transfer is 49 percent for the single measurements. The aircraft was operated in the vicinity of the specimen tested with an adequate strain gaging. A large difference NASA Langley Research Center, Hampton, Virginia, in a in fastener flexibility between Hi-lok and Hi-tigue fasteners is thunderstorm environment to elicit strikes. Electromagnetic field observed. Flexibility ranges from 5.9 to 19.5 mrn/MN. ESA data and conduction currents on the aircraft were recorded for attached lightning. Part 1 contains 435 pages of lightning strike data in chart form. Author

N88-29260*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. THE 1983 DIRECT STRIKE LIGHTNING DATA, PART 2 MITCHEL E. THOMAS Washington, D.C. Aug. 1985 447 p (NASA-TM-86426-PT-2; NAS 1,15386426-PT-2) Avail: NTlS HC N88-30163# Air Force Inst. of Tech., Wright-Patterson AFB, Al9/MF A01 CSCL 048 Ohio. School of Engineering. Data waveforms are presented which were obtained during AN INVESTIGATION OF CONSTITUTIVE MODELS FOR the 1983 direct strike lightning tests utilizing the NASA F106-B PREDICTING VISCOPLASTIC RESPONSE DURING CYCLIC aircraft specially instrumented for lightning electromagnetic LOADING M.S. Thesis measurements. The aircraft was operated in the vicinity of the DAVID A. SHAFFER Jun. 1988 95 p NASA Langley Research Center, Hampton, Virginia, in a (AD-A194875; AFIT/GAE/AA/87D-21) Avail: NTlS HC A05/MF thunderstorm environment to elicit strikes. Electromagnetic field A01 CSCL20K data and conduction currents on the aircraft were recorded for The Air Force's Engine Structural Integrity Program (ENSIP) attached lightning. Part 2 contains 443 pages of lightning strike (Ref 1) requires determination of damage tolerance for jet engine data in chart form. Author components in order to allow more economical rejection criteria to be adopted. To this end, means have been developed for N88-29261'# National Aeronautics and Space Administration. predicting fatigue crack growth in jet engine components such as Langley Research Center, Hampton, Va. turbine disks made of nickel-based superalloys and operating at THE 1983 DIRECT STRIKE LIGHTNING DATA, PART 3 elevated temperatures. The presence of time-dependent plastic MITCHEL E. THOMAS Washington, D.C. Aug. 1985 450 p deformation greatly affects crack propagation rates, particularly at (NASA-TM-86426-PT-3; NAS 1.1 586426-PT-3) Avail: NTlS HC elevated temperatures and thus must be accounted for when Al9/MF A01 CSCL 048 modelling crack growth in turbine materials. The purpose of this Data waveforms are presented which were obtained during thesis was to investigate the frequency response aspects of the the 1983 direct strike lightning tests utilizing the NASA F106-B Bodner-Partom constitutive law's behavior and to compare its aircraft specially instrumented for lightning electromagnetic results with those of other models and to cyclic and non-cyclic measurements. The aircraft was operated in the vicinity of the uniaxial tensile test data. GRA NASA Langley Research Center, Hampton, Virginia, in a

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thunderstorm environment to elicit strikes. Electromagnetic field Astronautics (Peoples Republic of China) data and conduction currents on the aircraft were recorded for (Contract NASW-4307) attached lightning. Part 3 contains 446 pages of charts depicting (NASA-TT-20342; NAS 1.77:20342) Avail: NTlS HC AO3/MF additional lightning strike data. Author A01 CSCLO4B The Dryden model is usually used in studying the response of N88-29727"# National Aeronautics and Space Administration. flight vehicles to atmospheric turbulence. For a modern flight Langley Research Center, Hampton, Va. simulator, it is necessary to generate random winds (in Dryden A SUMMARY OF ATMOSPHERIC TURBULENCE model or sometimes others) with a digital computer. A theoretically MEASUREMENTS WITH SPECIALLY-EQUIPPED AIRCRAFT IN strict new method to meet this purpose is proposed. By this method, THE US a three dimensional atmospheric turbulence can be obtained which H. N. MURROW ln AGARD, The Flight of Flexible Aircraft in contains three components of wind velocity and three components Turbulence: State-of the Art in the Description and Modelling of of wind velocity gradient. The reliability of this method is checked Atmospheric Turbulence 11 p Dec. 1987 by comparing the theoretical autocorrelation value. A numerical Avail: NTlS HC AO9/MF A01 CSCL 046 example has shown a satisfactory result. Finally, some proposals The technique of measurement of atmospheric turbulence in concerning the use of this mathematical model in a flight simulator the form of true gust velocity is summarized. Specific aspects are given. Author pointed out are related to NASA programs conducted over the last 15 years. Liberal use is made of references for details. Some recommendations resulting from a Spring 1986 workshop on 15 atmospheric turbulence are also presented. Author

N88-29728# Royal Aircraft Establishment, Bedford (England). MATHEMATICAL AND COMPUTER SCIENCES MEASUREMENT AND ANALYSIS OF LOW ALTITUDE ATMOSPHERIC TURBULENCE OBTAINED USING A Includes mathematical and computer sciences (general); computer SPECIALLY INSTRUMENTED GNAT AIRCRAFT operations and hardware; computer programming and software; G. W. FOSTER and J. G. JONES ln AGARD, The Flight of computer systems; cybernetics; numerical analysis; statistics and Flexible Aircraft in Turbulence: State-of-the Art in the Description probability; systems analysis; and theoretical mathematics. and Modelling of Atmospheric Turbulence 45 p Dec. 1987 Avail: NTlS HC AOS/MF A01 Detailed measurements of atmospheric turbulence made by a A88-52823 specially instrumented Gnat aircraft at altitudes below one thousand PREDICTION OF THE EXTREME VALUES OF THE PHASE feet over a variety of terrains are described. A program of flying COORDINATES OF STOCHASTIC SYSTEMS yielded about 400 runs for which time histories of the three [PROGNOZIROVANIE EKSTREMACNYKH ZNACHENll components of turbulence are available. These runs are analyzed FAZOVYKH KOORDINAT STOKHASTICHESKIKH SISTEM] to give parameters which summarize the statistical characteristics A. N. BALABUSHKIN and F. 6. GUL'KO Avtomatika i of the turbulence encountered. A very strong relationship between Telemekhanika (ISSN 0005-2310), June 1988, p. 70-77. In two parameters from the Statistical Discrete Gust Analysis Russian. refs technique and one from the Power Spectral Density technique is The paper is concerned with the problem of estimating the identified. Author minimum (maximum) value of a coordinate of a linear dynamic object along the path of its further motion, with allowance made N88-29734# Office National d'Etudes et de Recherches for small stochastic perturbations. It is shown how such estimates Aerospatiales, Paris (France). can be used for the control of systems with constraints on the EXTREME GUSTS DISTRIBUTION phase coordinates. An example of such an application is the GABRIEL COUPRY ln AGARD, The Flight of Flexible Aircraft in prediction of the minimum altitude during a second approach to Turbulence: State-of-the-Art in the Description and Modelling of landing. V.L. Atmospheric Turbulence 9 p Dec. 1987 In FRENCH; ENGLISH summary Original language document was announced in IAA as A88-53631# A87-44328 MULTIPLE FRAME RATE INTEGRATION Avail: NTlS HC AOS/MF A01 A. HARALDSDOTTIR (Applied Dynamics International. Ann Arbor, A model of extreme atmospheric turbulence is proposed based MI) and R. M. HOWE (Michigan, University, Ann Arbor) IN: on 5 years of commercial flight data for events with load factors AIAA, Flight Simulation Technologies Conference, Atlanta, GA, in encess of 0.5. The Pratt formula is found to lead to incoherent Sept. 7-9, 1988, Technical Papers. Washington, DC, American atmospheric descriptions, while the Hall formula, with appropriate Institute of Aeronautics and Astronautics, 1988, p. 26-35. refs choice of scale, is found to lead to a coherent turbulence (AIAA PAPER 88-4579) description which is relatively independent of the type of aircraft The multiple frame-rate method is introduced, including considered. For strong turbulences, the average number of techniques for converting slow data sequence outputs from slow overshoots by a nautical mile are found to decrease exponentially subsystems to fast data sequence inputs for fast systems. The with gust amplitude. The incidences of gusts exceeding a threshold suitability of various integration algorithms for multiple framing is value are found to obey a Poisson distribution whose mean discussed. The implementation of multiple frame-rate integration decreases exponentially with amplitude, indicating that the using the simulation language ADSIM for the AD 100 computer is probability of the occurrence of big gusts can be represented by described, including sofware which allows, without program Gumbel's extreme value theory. Author recompiling, choice of multiple-frame ratios and choice of different interpolation or extrapolation algorithms for slow-to-fast system N88-30266'# National Aeronautics and Space Administration, interfacing. The paper concludes with an example of multiple Washington, D.C. framing applied to the simulation of a combined air frame and A DIGITAL SIMULATION TECHNIQUE FOR THE DRYDEN flight control system in order to improve both the accuracy and ATMOSPHERIC MODEL stability of the simulation. Author ZHENYAN ZHAO, YELUN XIAO, and YlJlAN SHI Aug. 1988 20 p Transl. into ENGLISH from Acta Aeronautica et Astronautica A88-53637# Sinica (Peoples Republic of China), v. 7, no. 5, Oct. 1986 p ARTIFICIAL INTELLIGENCE SYSTEMS FOR AIRCRAFT 433-443 Original language document was announced in IAA as TRAINING - AN EVALUATION A87-24715 Transl. by SCITRAN, Inc., Santa Barbara, Calif. Original THOMAS G. HOLZMAN and ROBERT W. PATTERSON (Lockheed document was prepared by Beijing Inst. of Aeronautics and Aeronautical Systems Co., Marietta, GA) IN: AIAA, Flight

857 15 MATHEMATICAL AND COMPUTER SCIENCES

Simulation Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, vertical plane under the effect of gravity, thrust force, and Technical Papers. Washington, DC, American Institute of aerodynamic lift and drag forces. A criterion for the optimal control Aeronautics and Astronautics, 1988, p. 73-81. of the vehicle with constraints on the center-of-mass coordinates (AIAA PAPER 88-4588) is established. B.J. This paper summarizes aircraft operation and maintenance training problems and suggests how they might be remedied A88-54202"# Texas A&M Univ., College Station. through intelligent computer-assisted instruction (ICAI). The paper ACTIVE CONTROL OF TRANSIENT ROTORDYNAMIC focuses on a rigorous evaluation methodology designed to facilitate VIBRATION BY OPTIMAL CONTROL METHODS selection of the best artificial intelligence (AI) system for meeting A. B. PALAZZOLO, R. R. LIN, R. M. ALEXANDER (Texas A & M an organization's ICAl needs. A recent application of this University, College Station), and A. F. KASCAK (NASA, Lewis methodology revealed that at least a half dozen AI system Research Center, Cleveland, OH) ASME, Gas Turbine and possessed the majority of features identified as conducive to good Aeroengine Congress and Exposition, Amsterdam, Netherlands, maintenance training. However, no candidate system excelled on June 6-9, 1988. 8 p. Research supported by Texas A & M all dimensions of value to CAI. Widespread deficiencies were University. refs noted in the areas of interactive videodisc and authoring systems. (Contract NAG3-763) Trade-offs in features were found between two major classes of (ASME PAPER 88-GT-73) computers, known as general purpose work-stations and LISP Although considerable effort has been put into the study of machines. Author steady state vibration control, there are few methods applicable to transient vibration control of rotorbearing systems. In this paper A88-53654'# Psycho-Linguistic Research Associates, Menlo optimal control theory has been adopted to minimize rotor vibration Park, Calif. due to sudden imbalance, e.g., blade loss. The system gain matrix SMART COMMAND RECOGNIZER (SCR) - FOR is obtained by choosing the weighting matrices and solving the DEVELOPMENT, TEST, AND IMPLEMENTATION OF SPEECH Riccati equation. Control forces are applied to the system via a COMMANDS feedback loop. A seven mass rotor system is simulated for CAROL A. SIMPSON (Psyco-Linguistic Research Associates, illustration. A relationship between the number of sensors and the Woodside, CA), JOHN W. BUNNELL (NASA, Ames Research number of modes used in the optimal control model is investigated. Center; SYRE, Inc., Moffett Field, CA), and ROBERT R. KRONES Comparisons of responses are made for various configurations of (Sterling Software, Informatics Div., Palo Alto, CA) IN: AIAA, modes, sensors, and actuators. Furthermore, spillover effect is Flight Simulation Technologies Conference, Atlanta, GA, Sept. 7-9, examined by comparing results from collocated and noncollocated 1988, Technical Papers. Washington, DC, American Institute of sensor configurations. Results show that shaft vibration is Aeronautics and Astronautics, 1988, p. 215-221. refs significantly attenuated in the closed loop system. Author (Contract NAS2-12425; NAS2-11555; NAS2-11631) (AIAA PAPER 88-4612) The SCR, a rapid prototyping system for the development, A88-54426 testing, and implementation of speech commands in a flight RULE-BASED MECHANISMS OF LEARNING FOR simulator or test aircraft, is described. A single unit performs all INTELLIGENT ADAPTIVE FLIGHT CONTROL functions needed during these three phases of system ROBERT F. STENGEL (Princeton University, NJ) and DAVID A. development, while the use of common software and speech HANDELMAN IN: 1988 American Control Conference, 7th, Atlanta, command data structure files greatly reduces the preparation time GA, June 15-17, 1988, Proceedings. Volume 1. New York, Institute for successive development phases. As a smart peripheral to a of Electrical and Electronics Engineers, 1988, p. 208-213. refs simulation or flight host computer, the SCR interprets the pilot's (Contract DAAG29-84-K-0048) spoken input and passes command codes to the simulation or The authors investigate how certain aspects of human learning flight computer. K.K. can be used to characterize learning in intelligent adaptive control systems. Reflexive and declarative memory and learning are described. It is shown that model-based systems-theoretic adaptive A88-53671# SOME BENEFITS OF DISTRIBUTED COMPUTING control methods exhibit attributes of reflexive learning, whereas ARCHITECTURES FOR TRAINING SIMULATORS the problem-solving capabilities of knowledge-based systems of artificial intelligence are naturally suited for implementing declarative WILLIAM B. FORBES and JEFFREY B. KAUFFMAN (Digital Equipment Corp., Marlboro, MA) IN: AIAA, Flight Simulation learning. Issues related to learning in knowledge-based control Technologies Conference, Atlanta, GA, Sept. 7-9, 1988, Technical systems are addressed, with particular attention given to rule-based Papers. Washington, DC, American Institute of Aeronautics and systems. A mechanism for real-time rule-based knowledge acquisition is suggested, and utilization of this mechanism within Astronautics, 1988, p. 354-360. It is shown that using real-time accelerator (RTA) processors the context of failure diagnosis for fault-tolerant flight control is demonstrated. I.E. to handle the I/O processing requirements of an avionics simulation application can produce substantial improvements in the predictability of system performance. The RTA is a small low-cost N88-29313# Advisory Group for Aerospace Research and processor running a low overhead real-time system kernel; it is Development, Neuilly-Sur-Seine (France). Fluid Dynamics Panel. well suited as a dedicated processor for low-level time-critical tasks. THREE DIMENSIONAL GRID GENERATION FOR COMPLEX The RTA processors are true general-purpose processors in that CONFIGURATIONS RECENT PROGRESS they are programmable in high-level languages, they are JOSEPH F. THOMPSON, J. L. STEGER, and H. YOSHIHARA, multitasking, and they conform to a well-established processor ed. (Boeing Military Airplane Development, Seattle, Wash.) Mar. architecture. K.K. 1988 162p (AGARD-AG-309; ISBN-92-835-0451-8; AD-A196776) Avail: A88-53876 NTlS HC AOWMF A01 A PROBLEM OF OPTIMAL CONTROL WITH CONSTRAINTS Some of the capabilities of the Computational Fluid Dynamics ON THE COORDINATES OF THE CENTER OF MASS [OB (CFD) community are surveyed for griding complex three ODNOI ZADACHE OPTIMAL'NOGO UPRAVLENIIA PRI dimensional configurations. The intent is to provide some insight OGRANICHENIIAKH NA KOORDINATY TSENTRA MASS] as to the present state of grid generation for aircraft configurations V. G. GlURDZHlEV and M. T. SAKSONOV (Dushanbinskii in order to help assess whether this task presents a long term Gosudarstvennyi Pedagogicheskii Institut, Dushanbe, Tadzhik stumbling block to routine use of CFD in aerodynamic applications. SSR) Akademiia Nauk Tadzhikskoi SSR, Doklady (ISSN A brief review is given of some of the techniques that are available 0002-3469), vol. 31, no. 2, 1988, p. 79-82. In Russian. for generating body conforming curvilinear grids. In order to assess Consideration is given to the motion of a flight vehicle in the capabilities in grid generation, colleagues at selected institutions

858 15 MATHEMATICAL AND COMPUTER SCIENCES

were solicited to describe their experiences and difficulties in grid up to the generation of the full block volume grids. The multiple generation of complex configurations. block concept is shown to facilitate the gridding of very complex geometries and also to allow larger sized grids to be run with a N88-29314# Boeing Military Airplane Development, Seattle, multiple block Euler solver. The entire grid generation process is Wash. broken into logical steps, each step is described in detail. Three LESSONS LEARNED IN THE MESH GENERATION FOR PN/S examples of grid systems generated with these techniques are CALCULATIONS given, thereby validating the procedure. Finally, current research H. YOSHIHARA In AGARD, Three Dimensional Grid Generation topics in grid generation and future plans are discussed. Author for Complex Configurations: Recent Progress p 15-22 Mar. 1988 N88-29318'# National Aeronautics and Space Administration. Avail: NTlS HC A08/MF A01 Langley Research Center, Hampton, Va. Experiences encountered in the 2D mesh generation with the GRID GENERATION ON AND ABOUT A CRANKED-WING elliptic differential equation method are described for the FIGHTER AIRCRAFT CONFIGURATION parabolized Navier-Stokes calculations over a generic fighter at a ROBERT E. SMITH, JOAN I. PITTS, LARS-ERIK ERIKSSON, and supersonic Mach number and for a wing/fuselage at hypersonic MICHAEL R. WlESE (Computer Sciences Corp., Hampton, Va.) Mach numbers. Importance of the mesh quality is stressed, and ln AGARD, Three Dimensional Grid Generation for Complex the need of an improved cost effective treatment of the shocks is Configuration: Recent Progress p 56-64 Mar. 1988 pointed out. Author Avail: NTlS HC AO8/MF A01 CSCL 096 Experiences at the NASA Langley Research Center generating N88-29315'# National Aeronautics and Space Administration. grids about a cranked wing fighter aircraft configuration is described. Ames Research Center, Moffett Field, Calif. A single block planar grid about the fuselage and canard used THREE-DIMENSIONAL ELLIPTIC GRID GENERATION FOR AN with a finite difference Navier-Stokes solver is also described. A F-16 dual block nonplanar grid about the complete configuration and REESE L. SORENSON ln AGARD, Three Dimensional Grid used with a finite volume Euler solver is presented. The very Generation for Complex Configurations: Recent Progress p 23-28 important aspect of computing the aircraft surface grid, starting Mar. 1988 with a standardized model description, is also presented. Author Avail: NTlS HC AO8/MF A01 CSCL 096 A case history depicting the effort to generate a computational N88-29319# Messerschmitt-Boelkow G.m.b.H., Munich (West grid for the simulation of transonic flow about an F-16 aircraft at Germany). Helicopter and Military Aircraft Group. realistic flight conditions is presented. The flow solver for which GRID GENERATION FOR AN ADVANCED FIGHTER AIRCRAFT this grid is designed is a zonal one, using the Reynolds averaged A. EBERLE and W. SCHWARZ ln AGARD, Three Dimensional Navier-Stokes equations near the surface of the aircraft, and the Grid Generation for Complex Configurations: Recent Progress p Euler equations in regions removed from the aircraft. A body 65-76 Mar. 1988 conforming global grid, suitable for the Euler equation, is first Avail: NTlS HC A08/MF A01 generated using 3-D Poisson equations having inhomogeneous The grid generation process for a realistic and complex fighter terms modeled after the 2-D GRAPE code. Regions of the global type aircraft is described. The method is based on the solution of grid are then designated for zonal refinement as appropriate to biharmonic equations and uses a single block concept. Only a accurately model the flow physics. Grid spacing suitable for solution few user specified input parameters are necessary for the of the Navier-Stokes equations is generated in the refinement construction of the space grid and therefore this grid generation zones by simple subdivision of the given coarse grid intervals. system is very simple to handle. The grid is intended for calculations That grid generation project is described, with particular emphasis with an Euler code at transonic and supersonic speeds. Author on the global coarse grid. Author N88-29320# Tennessee Univ. Space Inst., Tullahoma. Dept. of N88-29316# Aircraft Research Association Ltd., Bedford Engineering Science and Mechanics. (England). ALGEBRAIC GRID GENERATION FOR FIGHTER TYPE COMPONENT ADAPTIVE GRID GENERATION FOR AIRCRAFT AIRCRAFT CONFIGURATIONS JOHN STEINHOFF ln AGARD, Three Dimensional Grid N. P. WEATHERILL and J. A. SHAW ln AGARD, Three Generation for Complex Configurations: Recent Progress p 77-84 Dimensional Grid Generation for Complex Configurations: Recent Mar. 1988 Progress p 29-39 Mar. 1988 Avail: NTlS HC A08/MF A01 Avail: NTlS HC A08/MF A01 A systematic procedure is presented for synthesizing a complex A method is presented which is capable of generating computational grid for fighter type aircraft out of a number of component adaptive grids. The approach is illustrated using simpler elementary grids. This method is useful when a grid is wing-body-canard geometries but is applicable to a wide range of required over an object which, though complex, consists of a complex aerodynamic configurations. The new method of topology number of simpler pieces, such as an aircraft with a number of generation, combined with the approach taken to grid control, lifting surfaces. The procedure presented allows a smooth complex provide a powerful means of exploring the most suitable topology grid to be generated which becomes exactly equal to each for a given geometry. Grid control parameters are available to the elementary grid as the surface corresponding to that elementary user to modify the grids for particular geometries but the system grid is approached. In this way, methods which may have previously does not require the user to partake in long interactive sessions been developed for each piece do not have to be changed and on a workstation to generate grids. The suitability of the component can be used as black boxes, whether they are algebraic, partial adaptive grids for flow simulation is demonstrated by comparing differential equation based, or whether the grids are just given theoretical predictions with experiment. Author numerically. This blending technique is only one of several tools which was used to generate effective grids. Other techniques N88-29317# General Dynamics Corp., Fort Worth, Tex. include projection methods for generating surface grids. Some GENERATION OF MULTIPLE BLOCK GRIDS FOR ARBITRARY advantages and limitations of the method are discussed and 3D GEOMETRIES examples are given of its use in generating complex fighter grids. J. P. STEINBRENNER, S. L. KARMAN, JR., and J. R. CHAWNER Author ln AGARD, Three Dimensional Grid Generation for Complex Configurations: Recent Progress p 40-55 Mar. 1988 N88-29321# Mississippi State Univ., Mississippi State. Dept. of Avail: NTlS HC AO8/MF A01 Aerospace Engineering. A grid generation procedure was developed to create complex COMPOSITE GRID GENERATION FOR AIRCRAFT block grid systems, beginning with the generation of block surfaces, CONFIGURATIONS WITH THE EAGLE CODE

859 15 MATHEMATICAL AND COMPUTER SCIENCES

JOE F. THOMPSON and LAWRENCE E. LlJEWSKl (Air Force 1988 Armament Lab., Eglin AFB, Fla.) ln AGARD, Three Dimensional Avail: NTlS HC A08/MF A01 Grid Generation for Complex Configurations: Recent Progress p A new grid generation code is described which is based on 85-95 Mar. 1988 the multi-block approach. Grid generation around 3-D configurations Avail: NTlS HC A08/MF A01 is divided into 3 major parts, namely, surface definition, surface A general three dimensional grid generation code based on a grid generation and field grid generation. Coons' patches are used composite block structure is discussed. The code can operate to define the surfaces and their intersection lines. Surface grids either as an algebraic generation system or as an elliptic generation and field grids are generated using the numerical solution of an system. Provision is made for orthogonality at boundaries and elliptic system. An effective means for the control of the grid complete continuity at block interfaces. The code can operate in spacing was developed which is based on an iterative determination two or three dimensions, or on a curved surface. The input is of the source terms in the elliptic system. The code is used to structured to be user oriented, and arbitrary block configurations generate grids around a wing-body combination and a high bypass can be treated. Author nacelle configuration. Author

N88-29322# Deutsche Forschungs- und Versuchsanstalt fuer N88-29337# Naval Postgraduate School, Monterey, Calif. Luft- und Raumfahrt, Goettingen (West Germany). Inst. for FEASIBILITY STUDY OF A MICROPROCESSOR CONTROLLED Theoretical Fluid Mechanics. ACTUATOR TEST MECHANISM M.S. Thesis ANALYTICAL SURFACES AND GRIDS GREGORY L. GOODE Mar. 1988 102 p HELMUT SOBIECZKY In AGARD, Three Dimensional Grid (AD-A194654) Avail: NTlS HC AO6/MF A01 CSCL 12F Generation for Complex Configurations: Recent Progress p 96-105 This thesis describes the investigation of the feasibility of using Mar. 1988 a commercially available microcomputer to control and test a Avail: NTlS HC A08/MF A01 missile fin actuator. Topics discussed include system modelling, The use of analytical shape generation is described for automated data acquisition, system identification, simulation and wing-body configurations and flow boundary conditions. Flexibility controller design. Modularity, both functional and conceptual, is in geometry definition allows for simple computational grid stressed in the design process as well as integration of modules interpolation. A test case for experiment and code validation is during the modelling and simulation process. Verification of the illustrated. Author computer simulation is used extensively as an interactive tool to modify the system model. The hybrid system under investigation contains analog and discrete components, some of which are N88-29323# Dornier-Werke G.m.b.H., Friedrichshafen (West both nonlinear and discontinuous. The use of digital systems, their Germany). Theoretical Aerodynamics. limitations and advantages are highlighted in the modelling of these MESH GENERATION FOR INDUSTRIAL APPLICATION OF components and the development of a control system EULER AND NAVIER STOKES SOLVERS Author (GRA) W. FRITZ, W. HAASE, and W. SEIBERT In AGARD, Three Dimensional Grid Generation for Complex Configurations: Recent N88-29489'# George Washington Univ., Hampton, Va. Progress p 106-123 Mar. 1988 TWO BIASED ESTIMATION TECHNIQUES IN LINEAR Avail: NTlS HC A08/MF A01 REGRESSION: APPLICATION TO AIRCRAFT A considerable increase has been made in recent years in the VLADISLAV KLEIN Jul. 1988 41 p ability to compute flow I fields about three dimensional (NASA-TM-100649; NAS 1.15:100649) configurations. In order to reach their full potential, robust grid Avail: NTlS HC AO31MF A01 CSCL 12A generation techniques for complicated aerodynamic configurations Several ways for detection and assessment of collinearity in must be developed. Three different methods are presented which measured data are discussed. Because data collinearity usually can be characterized as automatic grid generation for complete results in poor least squares estimates, two estimation techniques aircraft configurations, completely interactive grid generation and which can limit a damaging effect of collinearity are presented. generation of solution adaptive grids for Navier-Stokes calculations. These two techniques, the principal components regression and Although all the presented grid generation techniques use only mixed estimation, belong to a class of biased estimation techniques. elliptical grid generation, they show already that there is no unique Detection and assessment of data collinearity and the two biased grid generation technique. E.R. estimation techniques are demonstrated in two examples using flight test data from longitudinal maneuvers of an experimental N88-29324# Calspan Field Services, Inc., Arnold AFS, Tenn. aircraft. The eigensystem analysis and parameter variance EXPERIENCE WITH THREE DIMENSIONAL COMPOSITE decomposition appeared to be a promising tool for collinearity GRIDS evaluation. The biased estimators had far better accuracy than J. A. BENEK, T. L. DONEGAN, and N. E. SUHS ln AGARD, the results from the ordinary least squares technique. Author Three Dimensional Grid Generation for Complex Configurations: Recent Progress p 124-138 Mar. 1988 Previously announced N88-30378# Mississippi State Univ., Mississippi State. Dept. of as N87-26021 Aerophsyics and Aerospace Engineering. Avail: NTlS HC AO8/MF A01 GENERATION OF SURFACE GRIDS THROUGH ELLIPTIC Experience with the three dimensional, chimera grid embedding PARTIAL DIFFERENTIAL EQUATIONS FOR AIRCRAFT AND scheme is described. Applications of the inviscid version to a MISSILE CONFIGURATIONS Final Report, Jun. 1987 - Mar. multiple body configuration, a wing-body-tail configuration, and an 1988 estimate of wind tunnel wall interference are described. Applications Z. U. WARS1 16 May 1988 27 p to viscous flows include a 3-D cavity and another multi-body (Contract AF-AFOSR-0143-85) configuration. A variety of grid generators is used, and several (AD-A195639; ASE-88-6; AFOSR-88-0636TR) Avail: NTlS HC embedding strategies are described. Author AOBIMF A01 CSCL 12A The main aim of the project was to develop a set of partial N88-29325# Deutsche Forschungs- und Versuchsanstalt fuer differential equations which are the most optimum for the generation Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer of grid lines in arbitrary surfaces. Equations have been developed Entwurfsaerodynamik. on the basis of differential-geometric concepts which are elliptic GRID GENERATION AROUND TRANSPORT AIRCRAFT in character and look to be the most optimum among the class CONFIGURATIONS USING A MULTI-BLOCK STRUCTURED of equations which can be used to generate the surface COMPUTATIONAL DOMAIN coordinates. The developed equations require a specification of R. RADESPIEL In AGARD, Three Dimensional Grid Generation the forcing function which depends on the geometry of the given for Complex Configurations: Recent Progress p 139-153 Mar. surface. The surface in which the coordinates are to be introduced

860 16 PHYSICS

is usually given in discrete data form. Methods have been on the dynamics of the fuselage-air-trim-air system. The maximum developed which fit a function over the given data to evaluate the SPL may vary from 123 down to 118 dB in the extreme cases forcing function for complicated shapes, e.g., an airplane, the where only attachment and density of the trim panel are changed. functional fit and the eventual grid generation for the fuselage The results also show that a porous absorbent in the air space and wings are done separately and then integrated to obtain the may give an additional decrease down to a maximum of 114 dB grid lines on the surface. GRA by carefully tuning the mass density of the porous material. ESA

N88-29523# Southampton Univ. (England). Inst. of Sound and Vibration Research. 16 A COMPARISON OF SIMPLE ANALYTICAL MODELS FOR REPRESENTING PROPELLER AIRCRAFT STRUCTURAL AND PHYSICS ACOUSTIC RESPONSES A. J. BULLMORE Feb. 1988 127 p Sponsored by the Includes physics (general); acoustics; atomic and molecular Department of Trade and Industry, London, England physics; nuclear and high-energy physics; optics; plasma physics; (ISVR-TR-153; ETN-88-92824) Avail: NTlS HC A07/MF A01 solid-state physics; and thermodynamics and statistical physics. The effectiveness of active noise control applied to reduce the internal sound pressure levels in the cabin of propeller driven aircraft, specifically the BAe 748 aircraft, was examined. The model N88-29514'# Duke Univ., Durham, N. C. Dept. of Mechanical is required only to produce results for frequencies below 200 Hz, Engineering and Materials Science. the range of the greatest effectiveness of the noise control system. ASYMPTOTIC MODAL ANALYSIS AND STATISTICAL ENERGY The chosen model consists of a finite aluminum cylinder, 16 m ANALYSIS Progress Report, 15 Oct. 1987 - 14 Apr. 1988 long, 1.3 m radius, with a structural damping factor of 0.3. It is EARL H. DOWELL 21 Jul. 1988 110 p excited by an external pressure field. The internal acoustic field is (Contract NAG1-709) modeled by a cylindrical room acoustics model excited by the (NASA-CR-183077; NAS 1.26:183077) Avail: NTlS HC AO6/MF normal vibrations of the shell wall, but only over a region extending A01 CSCL20A from z=1.5 to 12.5 m, and from theta = 60 to 300 deg. The Statistical Energy Analysis (SEA) is defined by considering the cylindrical room is assumed to have the same length and radius asymptotic limit of Classical Modal Analysis, an approach called as the structural cylinder model. ESA Asymptotic Modal Analysis (AMA). The general approach is described for both structural and acoustical systems. The N88-29524 National Physical Lab., Teddington (England). Div. theoretical foundation is presented for structural systems, and of Radiation Science and Acoustics. experimental verification is presented for a structural plate NOISE LEVELS FROM A JET-ENGINED AIRCRAFT responding to a random force. Work accomplished subsequent to MEASUREDATGROUNDLEVELANDAT1.2MABOVETHE the grant initiation focusses on the acoustic response of an interior GROUND cavity (Le., an aircraft or spacecraft fuselage) with a portion of R. C. PAYNE Jan. 1988 42 p the wall vibrating in a large number of structural modes. First (NPL-AC-114; ISSN-0143-7143; ETN-88-93141) Avail: National results were presented at the ASME Winter Annual Meeting in Physics Laboratory, Teddington, Middlesex, TWl 1 OLW, United December, 1987, and accepted for publication in the Journal of Kingtom Vibration, Acoustics, Stress and Reliability in Design. It is shown During flight tests using a British Aerospace HS125-700, noise that asymptotically as the number of acoustic modes excited measurements were obtained using microphones close to the becomes large, the pressure level in the cavity becomes uniform ground plane and at a height of 1.2 m. Substantial differences except at the cavity boundaries. However, the mean square from ground level to 1.2 m in measurements of perceived noise pressure at the cavity corner, edge and wall is, respectively, 8, 4, level and effective perceived noise level were observed. The and 2 times the value in the cavity interior. Also it is shown that differences depend on ground cover and flight maneuver. The when the portion of the wall which is vibrating is near a cavity ground-plane microphones generally produce noise levels which corner or edge, the response is significantly higher. Author closely approximate pressure-doubled values. A procedure for correcting 1/3-octave band sound pressure levels measured 1.2 N88-29520# Aeronautical Research Inst. of Sweden, Stockholm. m above the ground, to obtain pressure-doubled levels, was Structures Dept. examined. The procedure is successful when used in adjustments ANALYSIS OF THE TRANSMISSION OF SOUND INTO THE of perceived noise levels but, because of inaccurate estimates of PASSENGER COMPARTMENT OF A PROPELLER AIRCRAFT duration corrections, is less suitable in the case of effective USING THE FINITE ELEMENT METHOD perceived noise level, especially for aircraft in approach to landing. PETER GORANSSON Mar. 1988 16 p Presented at the 3rd It is concluded that to avoid significant variations in measured International Conference on Advances in Structural Dynamics, noise levels measurements should be made using a ground-plane Southampton, England, Jul. 1988 microphone. ESA (Contract FFA-STU-HU-2812) (FFA-TN-1988-15; ETN-88-92809) Avail: NTlS HC A03/MF A01 N88-30398# Aeronautical Research Labs., Melbourne The double wall construction of an aircraft cabin was analyzed (Australia). to see if sound transmission phenomena found in experiments THE DEVELOPMENT OF ACOUSTIC EMISSION FOR can be reproduced. The eigenvalues and eigenmodes of the plane STRUCTURAL INTEGRITY MONITORING OF AIRCRAFT cross section were calculated, with and without the inner trim C. M. SCALA, S. J. BOWLES, and L. G. SCOTT Jan. 1988 pannels, emphasizing the effects of different attachment of the 35 P trim panels to the frames and also of the weight and stiffness of (AD-A196264; ARL/MAT-R-120; DODA-AR-004-585) Avail: NTlS the trim panels. The calculated modes were used to calculate the HC A03/MF A01 CSCL 148 sound levels arising from an external pressure field acting on the This paper reviews procedures for distinguishing between outer shell. The analysis is performed with the finite element system acoustic emission (AE) from fatigue crack propagation and from ASKA-acoustics. The intervention between the structural parts and spurious sources in aircraft applications. Particular emphasis is the fluid in the different cavities is modeled with a symmetric placed on the development of procedures applicable during AE coupling formulation with pressure and displacement potential as monitoring of complex-shaped components. First, procedures to fluid degrees of freedom. The acoustic field is modeled with special eliminate extraneous sources are evaluated, including the use of acoustic finite elements and the coupling to the structure is handled guard sensors and source location systems. The capabilities of with interface elements. Analysis of an aircraft cross section shows additional signal-processing (which in principle can range from that the transmission of low frequency sound is strongly dependent adaptive to non-adaptive) for identifying and locating AE from

86 1 16 PHYSICS

fatigue crack propagation are then evaluated. The problems in the joint company, CFM International, current status of the CFM56 applying adaptive processing are illustrated by AE results from a program, and commercial and military product support. The Macchi aircraft in-flight and Mirage aircraft during full-scale fatigue discussion also covers quality assurance, component improvement testing. The ARL development of semi-adaptive processing based program, and configuration management. V.L. on background research on AE sources, sensors, calibration and other techniques is described. Successful application of this N88-30471# Army War Coll., Carlisle Barracks, Pa. processing to the Mirage test above is then detailed, and the CHINA’S ACQUISITION AND USE OF FOREIGN AVIATION value of using reduced adaptation in processing is demonstrated. TECHNOLOGY GRA MARY VONBRIESEN 30 Mar. 1988 26 p (AD-A194827) Avail: NTlS HC A03/MF A01 CSCL 05D N88-30399’# Planning Research Corp., Hampton, Va. System Following the establishment of diplomatic relations between Services. the United States and the People’s Republic of China in 1979, AIRCRAFT NOISE PREDICTION PROGRAM PROPELLER many people in both countries looked forward to the rapid transfer ANALYSIS SYSTEM IBM-PC VERSION USER’S MANUAL of technology between the two countries. On the Chinese side, VERSION 2.0 the hopes were to modernize rapidly, leapfrogging the slow SANDRA K. NOLAN Aug. 1988 236 p development process followed by most other nations. For their (Contract NAS1-18000) part, many Americans saw not only a potential market of over (NASA-CR-181689; NAS 1.26:181689) Avail: NTlS HC All/MF one billion but also a chance to play the China card against the A01 CSCL20A Soviet Union. This study focuses on China’s acquisition and use The IBM-PC version of the Aircraft Noise Prediction Program of foreign technology in the aviation industry, pointing out the (ANOPP) Propeller Analysis System (PAS) is a set of computational patterns of Chinese behavior in these transactions. GRA programs for predicting the aerodynamics, performance, and noise of propellers. The ANOPP-PAS is a subset of a larger version of ANOPP which can be executed on CDC or VAX computers. This 19 manual provides a description of the IBM-PC version of the ANOPP-PAS and its prediction capabilities, and instructions on GENERAL how to use the system on an IBM-XT or IBM-AT personal computer. Sections within the manual document installation, system design, ANOPP-PAS usage, data entry preprocessors, and ANOPP-PAS functional modules and procedures. Appendices to the manual include a glossary of ANOPP terms and information on error diagnostics and recovely techniques. Author A88-53773# FLIGHT TESTING OF FIGHTERS DURING THE WORLD WAR II ERA SHAHID SlDDlQl (Aviation Advanced Technology Applications, 17 Orlando, FL) AIAA, AHS, and ASEE, Aircraft Design, Systems and Operations Meeting, Atlanta, GA, Sept. 7-9, 1988. 5 p. refs SOCIAL SCIENCES (AIAA PAPER 88-4512) An account is given of the features of three typical flight test programs conducted by Allied countries during World War II: (1) Includes social sciences (general); administration and management; at NACA-Langley, for the P-51; (2) at San Diego, for a repaired documentation and information science; economics and cost A6M2 ’Zero’ fighter captured after a crash landing in the Aleutians analysis; law and political science; and urban technology and and flown in simulated combat against the F4F-4 USN carrier transportation. fighter and the P-51A USAAF fighter; and (3) for the FW-190A-3 at RAE-Farnborough. Attention is given to the quantitative results of comparative studies of roll capability for the various fighters A a 8- 5 3 78 8 tested. O.C. USE__~ OF- A DETAIL COST MODEL TO PERFORM CONCEPTUAL PHASE COST ANALYSIS PAUL SCHWARTZ (Grumman Corp., Aircraft Systems Div., Bethpage, NY) SAWE, Annual Conference, 46th, Seattle, WA, May 18-20, 1987. 13 p. (SAWE PAPER 1784) A detail cost model which can be used in cost analysis and at higher levels of the work breakdown structure is examined. The model was developed to perform cost versus system parameter evaluations early in the design cycle. The use of up-front parametric models, the costing concept of this model, and calibrating the model against development costs are discussed. The model is compared with other development cost models with good results. The model does not include elements such as flight test in its development costs. R.B.

A88-54365# THE CFM56 ENGINE FAMILY - AN INTERNAL DEVELOPMENT L. M. SPENCE (CFM International, Inc., Cincinnati, OH) and GEORGES SANGIS (CFM International, S.A., Paris, France) ASME, Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, Netherlands, June 6-9, 1988. 7 p. (ASME PAPER 88-GT-296) The joint effort by General Electric of the United States and Societe Nationale d’Etude et de Construction de Moteurs d’Aviation (SNEGMA) of France to develop the CFM56 turbofan engine family is described. In particular, attention is given to the organization of

862 SUBJECT INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 234) January 1989

Typical Subject Index Listing

ACOUSTICS AERODYNAMIC COEFFICIENTS Asymptotic modal analysis and statistical energy A preliminary investigation of drag reduction and SUBJECT HEADING analysis mechanism for a blunt body of revolution with slanted [ NASA-CR-1830771 p 861 N88-29514 base ACTIVE CONTROL [ NASA-TT-203491 p 799 N88-29753 1 The minimisation of helicopter vibration through blade AERODYNAMIC CONFIGURATIONS design and active control p 805 A88-53249 Towards the optimum ducted UHBR engine Ultra High AERODYNAMIC HEAT TRANSFER --- Active control of transient rotordynamic vibration by Bypass Ratio Calculationof aerodynamic heat transler for blunt-nosed optimal control methods thin wmgs al ddlerent angles of anack at supersonic [AlAA PAPER 88-29541 p 816 A88-53119 [ASME PAPER 88-GT-731 p 858 A88-54202 speeds Developments in computational methods for high-lilt Approximation schemes lor an aeroelastic-control INASA-TT-ZOtZ7I p 18 N88.10i76 aerodynamics p 786 A8843250 r system p 829 A8844660 Lockheed HTTB - STOL performancefeatures A cornparison of simple analytical models for [SAWE PAPER 17721 p 808 A88-53783 representing propeller aircralt structural and acoustic Aerodynamics numerical simulation using responses --- supercomputers p 783 A8843800 [ISVR-TR-153] p 861 N88-29523 ACTUATORS Performance of a compressor cascade configuration Detection. identification and estimation of surface with supersonic entrance flow - A review and comparison damagelactuator failure lor high performance aircraft of experiments in three installations p 828 A88-54650 [ASME PAPER 88-GT-211] p 793 A88-54297 Feasibility study of a microprocessor controlled actuator Delta wing configurations p 796 N88-28860 test mechanism Complex configurations p 834 N88-28861 The subject heading is a key to the subject content [AD-A1946541 p 860 N88-29337 Transport-typeconfigurations p 809 N88-28867 of the document The title is used to provide a ADAPTIVE CONTROL Combat aircraft p 810 N88-28868 description of the subject matter When the title is Microprocessor functional-adaptive processing of Three dimensional grid generation for complex signals of radio-navigation systems in an onboard conligurations:Recent progress insufficiently descriptive of document content, a subsystem p A88-52952 802 [AGARD-AG-309] p 858 N88-29313 title extension ISadded, separated from the title Rule-based mechanisms of learning for intelligent Component adaptive grid generation for aircraft by three hyphens The (NASA or AIAA) accession adaptive flight control p 858 A88-54426 configurations p 859 N88-29316 number and the page number are included in each Supersonic wall adaptation in the rubber tube test Experience with three dimensional composite grids section of the DFVLR Goettingen entry to assist the user in locating the abstract in p 860 N88-29324 [ 18-222-87-A-081 p 836 N88-29824 the abstract section If applicable. a report number AERODYNAMIC DRAG ADHESIVE BONDING A preliminary design study of supersonic through-flow is also included as an aid in identifying the docu- Aspects of the fatigue behaviour of typical adhesively fan inlets ment Under any one subject heading. the acces- bonded aircraft structures p 804 A88-52659 [AIAA PAPER 88-30751 p 81 6 A88-53137 sion numbers are arranged in sequence with the Use of composite materials to repair metal structures A preliminary investigation of drag reduction and p 804 A88-52660 AIAA accession numbers appearing first mechanism for a blunt body of revolution with slanted AERODYNAMIC CHARACTERISTICS base Three-dimensional hypersonic viscous shock layer on [ NASA-TT-203491 p 799 N88-29753 blunt bodies in flow at angles of attack and sideslip AERODYNAMIC FORCES p 786 A88-53971 Aerodynamically forced response of an airfoil including A An experimental investigation into the reasons of profile and incidence effects p 795 A88-54941 reducing secondary flow losses by using leaned blades Aerodynamically forced response of Structurally in rectangular turbine cascades with incidence angle mistuned bladed disks in subsonic flow A-7 AIRCRAFT [ASME PAPER 88-GT-41 p 786 A88-54151 YA-7F - A twenty year economic life extension at costs p 795 A88-54943 Periodicity. superposition, and 3D effects in supersonic we can afford Prediction of turbulence generated random vibrational [AIAA PAPER 88.44601 p 783 A88-53757 compressor flutter aerodynamics response 01 turbomachinery blading p 798 A88-54946 [ASME PAPER 88-GT-1381 p 791 A8844242 ACCELERATEDLIFETESTS Contamination and distortionof steady flow field induced A transient flow facility for the study of the by discrete frequency disturbances in aircraft gas Development of a test method to determine potential thermolluid-dynamics of a full stage turbine under engine peroxide content in turbine fuels Part 2 engines representative conditions [AD-A1954401 p 854 N88-30069 [AD-A1922441 p 841 N88-29042 [ASME PAPER 88-GT-1441 p 849 A88-54245 AERODYNAMIC LOADS ACCIDENT PREVENTION Flow computation and blade cascade design in Wake-induced unsteady aerodynamic interactions in a Simulator evaluation of takeoff performancemonitoring turbopump turbines multistage compressor p 785 A88-52686 system displays [ASME PAPER 88-GT-2481 p 820 A88-54326 Canard certification loads Progress toward alleviating [AiAA PAPER 88-4611 ] p 833 A8843653 - A new variational finite element computation for FAA concerns ACCURACY aerodynamic inverse problem in turbines with long [AIAA PAPER 88.44621 p 807 A88-53758 blades Aerodynamic data accuracy and quality Requirements Ultimate lactor for structural design of modern fighters [ASME PAPER 88-GT-2751 p 794 A88-54347 and capabilities in wind tunnel testing [SAWE PAPER 17751 p 808 A88-53784 Incompressible indicia1 response of infinite airfoils in [AGARD-AR-254] p 798 N88-28893 Unsteady flow past an NACA 0012 airfoil at high angles tandem - Some analytical results p 795 A88-54940 ACEE PROGRAM of anack SR-7A aeroelastic model design report The aerodynamics of an annular cascade 01 [AD-A194650] p 797 N88-28888 three-dimensional airfoils p 795 A8844942 [NASA-CR-174791] p 824 N88-28928 Stress intensity factors lor cracked metallic structures Grid embeddingtechnique using Cartesian gridsfor Euler under rapid thermal loading ACOUSTIC ATTENUATION solutions p 796 A88-55094 Fiber metal acoustic materials for gas turbine exhaust [AD-A191219] p 840 N88-29004 Effects of independent variation of Mach and Reynolds A summary of methods for establishing airframe design environments numbers on the low-speed aerodynamic characteristics [ASME PAPER 88 GT-1751 p 839 A88-54269 loads from continuous gust design criteria of the NACA 0012 airfoil section p 81 1 N88-29721 A comparison of simple analytical models for [ NASA-TM-40741 p 784 N88-28879 Status review of atmosphere turbulence and aircraft representing propeller aircraft structural and acoustic Aerodynamic data accuracy and quality: Requirements response p N88-29726 responses 830 and capabilities in wind tunnel testing A summary of atmospheric turbulence measurements [ISVR-TR-153] p 861 "3.29523 [AGARD-AR-2541 p 798 N88-28893 with specially-equipped aircraft in the US ACOUSTIC EMISSION Technology lor pressure-instrumented thin airfoil p 857 N88-29727 The development of acoustic emission for structural models Empirical flutter prediction method integrity monitoring of aircraft [NASA-CR-4173] p 835 N88-28933 [AD-AI 956991 p 825 N88-29810 [AD-A196264] p 861 N88-30398 Interactive plotting of NASTRAN aerodynamic models AERODYNAMIC NOISE ACOUSTIC MEASUREMENT using NPLOT and DISSPLA A study of aerodynamic noise from a contra-rotating Instrumentation and techniques for structural dynamics [ AD-A1941151 p 853 N88-29204 axial compressor stage p 823 A88-54938 and acoustics measurements Aircraft dynamics: Aerodynamic aspects and wind tunnel Nonuniformvane spacing effects on rotor blade forced [AIAA PAPER 88-46671 p 845 A8863829 techniques p 798 N88-29731 response and noise generation p 796 A88-54944

A- 1 AERODYNAMIC STABILITY SUBJECT INDEX

Noise generation and boundary layer effects in AIR DROP OPERATIONS Composite grid generation for aircraft configurationswith vortex-airfoil interaction and methods of digital hologram Control systems for platform landings cushioned by air the EAGLE code p 859 N88-29321 analysis for these flow fields bags Analytical surfaces and grids p 860 N88-29322 [AD-A19419t] p 797 N88-28883 [ AD-A1961 541 p 854 N88-29996 Mesh generation for industrial application of Euler and AERODYNAMIC STABILITY AIR FLOW Navier Stokes solvers p 860 N88-29323 Integrated thrust vectoring on the X 29A Air flow performance of air swirlers for gas turbine fuel Grid generation around transport aircraft configurations [AlAA PAPER 88.44991 p 808 A88 53769 nozzles using a multi-block structured computational domain Effect of shock wave movement on aerodynamic [ASME PAPER 88-GT-1081 p 848 A88-54227 p 860 N88-29325 instability of annular cascade oscillating in transonic flow Nozzle airflow influences on fuel patternation Recent advances in transonic computational [ ASME PAPER 88 GT 187 I p 792 A88-54278 p 842 N88-29916 aeroelasticity Pilotlvehicie analysis of a twin-lift helicopter AIR NAVIGATION [ NASA-TM-1006631 p 800 N88-29778 configuration in hover p 829 A88-55064 Microprocessor functional-adaptive processing of Generation of surface grids through elliptic partial AERODYNAMIC STALLING signals of radio-navigation systems in an onboard differential equations for aircraft and missile Flow measurements in rotating stall in a gas turbine subsystem p 802 A88-52952 configurations engine compressor [ AD-A1956391 p 860 N88-30378 Pilotage system for the Pronaos gondola French [ASME PAPER 88 GT-2191 p 819 A88 54304 --- AIRCRAFT CONSTRUCTION MATERIALS balloon-borne submillimeter telescope E3 1OC compressor test analysis of high-speedpost-stall New materials and fatigue resistant aircraft design; [IAF PAPER 88.0081 p 809 A88-55317 data Proceedings of the Fourteenth ICAF Symposium. Ottawa. [NASA CR 1795211 p 824 N88 28929 Observed track-keeping performance of DCI 0 aircraft Canada, June 8-12, 1987 p 803 A88-52651 AERODYNAMICS equippedwith the Collins AINS-70 area navigationsystem Evaluation of new materials in the design of aircraft Multigrid acceleration of the flux split Euler equations Karlsruhe and Masstricht UACs (Upper Area Control structures p 803 A88-52654 p 796 A88 55077 centres) Damage tolerance aspects of an experimentalArall F-27 Efficient Euler solver with many applications 1 EEC-202] p 803 N88-29788 lower wing skin panel p 804 A88-52668 p 796 A88-55078 AIR POLLUTION Impact and damage tolerance properties of CFRP Quadrature formula for a double-pole singular integral An emissions database for U S Navy and Air Force sandwich panels - An experimental parameter study for --- in linear lifting surface theory p 796 A88-55093 Aircraft engines the Fokker 100 CA-EP flap p 804 A88-52671 Theoretical aerodynamics transonic flow [ASME PAPER 88-GT-1291 p 81 8 A88-54239 Advanced Composite Airframe Program (ACAP) - An [ AD-At 962471 p 800 NE8 29777 AIR TRAFFIC CONTROL update and final assessment of weight saving potential AEROELASTICITY Fine resolution errors in secondarv surveillance radar [SAWE PAPER 17701 p 808 A88-53781 Flutter of a fan blade in supersonic axial flow altitude reporting Industrial production of CFRP-components in Airbus [ASME PAPER 88 GT 78) p 788 A88-54206 [ RSRE-870191 p 802 N88-28906 construction Numerical integrationof the 3D unsteady Euler equations AIRBORNE EQUIPMENT [SAWE PAPER 17941 p 845 A88-53795 for flutter analysis of axial flow compressors An airborne system for vortex flow visualization on the AIRCRAFT CONTROL [ASME PAPER 88-GT-255) p 794 A88-54331 F-I8 high-alpha research vehicle Vehicle Management Systems - The logical evolution Approximation schemes for an aeroelastic-control [AIAA PAPER 88 4671 ] p 813 A88-53830 of integration system p 829 A88-54660 Helicopter health monitoring from engine to rotor [AIAA PAPER 88.31751 p 826 A88-53148 VSRA in-flight simulator - Its evaluation and applications SR-7A aeroelastic model design report [ASME PAPER 88-GT-227) p 809 A88-54310 --- Variable Stability and Response Airplane [ NASA-CR-1747911 p 824 NE8 28928 AlRBORNElSPACEBORNE COMPUTERS Feasibility study of a microprocessorcontrolled actuator [AIAA PAPER 88-46051 p 806 A88-53649 Application of unsteady aerodynamic methods for test mechanism Smart command recognizer (SCR) - For development, transonic aeroelastic analysis [AD A1946541 p 860 N88 29337 test, and implementation of speech commands NASA TM 100665 p 799 N88 29754 1 1 Developmentand demonstrationof an on-board mission [AlAA PAPER 88.46121 p 858 A88-53654 History of aeroelasticity in Germany from the beginning planner for helicopters Ultimate factor for structural design of modern fighters to 1945 [NASA-CR-t77482] p 831 N88-29817 [SAWE PAPER 17751 p 808 A88-53784 [ESA TT-10821 p 799 N88 29767 AIRCRAFT ACCIDENT INVESTIGATION Application of AI methods to aircraft guidance and Recent advances in transonic computational Caring for the high-time let p 801 A88 53540 control p 827 A88-54424 aeroelasticity A profile of US Air Force aircraft mishap investigation Eigenstructure assignment for the control of highly [ NASA-TM-1006631 p 800 N88-29778 p 801 A88 55288 augmented aircraft p 828 A88-54549 Aeroelastic response of metallic and composite propfan AIRCRAFT ACCIDENTS Detection, identification and estimation of surface models in yawed flow Causes for turbomachinery performance deterioration damagelactuator failure for high performance aircraft [NASA TM 100964 I p 825 N88 29807 [ASME PAPER 88-GT-2941 p 821 A88-54363 p 828 A88-54650 AERONAUTICAL ENGINEERING Smoke hoods Net safety benefit analysis aircraft A hyperstabiemodel-following flight control system used Development and design of windtunnel and test facility accidents for reconfiguration following aircraft impairment for RPV (Remote Piloted Vehicle) enhancement devices [CAA-PAPER-870171 p 801 N88-28898 p 828 A88-54652 [ AD-A1948421 p 836 N88-29822 Failure analysis for gas turbines Robust control strategy lor take-off performance in a AEROSPACE INDUSTRY [NLR-MP 87037 U] p 825 N88-29808 windshear p 829 A88-54656 Design considerations in remote testing AIRCRAFT BRAKES High performance forward swept wing aircraft p 852 A88-55042 CIC composite materials for aircraft brakes [NASA-CASE-ARC-11636.1 1 p 810 N88-28914 Variable wing camber control systems for the future Aircraft airframe cost estimating relationships Study p 837 A88-53542 Airbus program approach and conclusions AIRCRAFT CARRIERS [R-3255-AF] p 813 N88-29795 Multiple-Purpose Subsonic Naval Aircraft (MPSNA) [MBB-UT-104188] p 830 N88-28932 Multiple Application Propfan Study (MAPS) Comparison of the influence of different gust models AEROSPACE VEHICLES [NASA-CR 1751041 p 811 N88-28917 on structural design p 81 1 N88-29722 Automated early fatigue damage sensing system AIRCRAFT COMPARTMENTS Advances in flying qualities: Concepts and criteria for [ADA1957171 p 855 N88 30143 Analysis of the transmissionof sound into the passenger a mission oriented flying qualities specification AEROTHERMOCHEMISTRY compartmentof a propeller aircraft using the finite element p 81 2 N88-29739 Numerical solution of the hypersonic viscous shock layer method A second look at MIL prime flying qualities equations with chemical nonequilibrium [FFA TN-1988.151 p 861 N88 29520 requirements p 81 2 N88-29740 [IAF PAPER ST 88-08] p 796 A88-55313 AIRCRAFT CONFIGURATIONS The role of simulation in flying qualities and flight control AEROTHERMODYNAMICS Ground simulator requirements based on in-flight system related development p 835 N88-29742 NASA HOST project overview - hot section simulation Angle of attack and sideslip estimation using an inertial technology p 817 A88-54138 [AIAA PAPER 88 46091 p 806 A88-53651 reference platform Assessment, development, and application of The criticality of weight and balance on competition [AD-A1948761 p 799 N88-29769 combustor aerothermal models p 817 A88-54140 aircraft A fiber optic collective flight control system for Review and assessment of the database and numerical [SAWE PAPER 17561 p 808 A88 53776 helicopters modeling for turbine heat transfer p 817 A88-54141 Preliminary definition of pressure sensing requirements [AD-A195406] p 831 N88-29818 Numericalmodels for analyticalpredictions of combustor for hypersonic vehicles Controlled degradation of resolution of high-qualityflight aerothermal performance characteristics [AlAA PAPER 88-46521 p 813 A88-53826 simulator images for training effectiveness evaluation p 843 N88-29935 Calculation of aerodynamic characteristics of airplane [AD-A196189] p 836 N88-29823 AFTERBURNING configurations at high angles of attack Numerical simulation of nozzle flows High performance turbofan afterburner systems [ NASA-CR 41 82) p 797 N88-28891 [ AD-A1951 441 p 854 N88-30064 Three dimensional grid generation for complex p 842 N88 29922 AIRCRAFT DESIGN configurations Recent progress AGING (MATERIALS) New materials and fatigue resistant aircraft design; [AGARD-AG-309] p 858 N88-29313 Development of a test method to determine potential Proceedings of the Fourteenth ICAF Symposium. Ottawa. Lessons learned in the mesh generation for PNIS oeroxide content in turbine fuels Part 2 Canada, June 8-12. 1987 p 803 A88-52651 calculations p 859 N88-29314 [AD-A1922441 p 841 N88-29042 Component adaptive grid generation for aircraft Fatigue crack propagation test programme for the A320 AH-64 HELICOPTER configurations p 859 N88-29316 wing p 804 A88-52662 Digital emulation of the AH-64A contrast tracker Generation of multiple block grids for arbitrary 3D Accounting for service environment in the fatigue [AlAA PAPER 88-465281 p 813 A88-53827 geometries p 859 N88-29317 evaluation of composite airframe structure Test of an 0 8-scale model of the AH-64 Apache in the Grid generation on and about a cranked-wing fighter p 804 A88-52685 NASA Langley full-scale wind tunnel aircraft configuration p 859 NE8 29318 The turboprop challenge --- design for cost-effective [ AD-AI 961291 p 799 N88-29768 Grid generalion for an advanced fighter aircraft regional-routeaircraft p 805 A88-53539 AIR DEFENSE p 859 N88 29319 The application of artificial intelligence technology to Soviet applications for hypersonic vehicles Algebraic grid generation for fighter type aircraft aeronautical system design [AIAA PAPER 88-45071 p 783 A88-53771 p 859 N88-29320 [AIAA PAPER 88.44261 p 806 A88-53752

A-2 SUBJECT INDEX AIRCRAFT MAINTENANCE

A quasi-procedural, knowledge-basedsystem for aircraft Viability rating by fuel indexing method Design aspects of recent developments in Rolls-Royce design p 81 5 A88-52698 RB211-524 powerplants [AIAA PAPER 88.44281 p 806 A88-53753 Advanced technology engine supportability - Preliminary [ASME PAPER 88-GT-3011 p 821 A88-54370 Development of a micro-computer based integrated designer's challenge Developing the Rolls-Royce Tay design system for high altitude long endurance aircraft [AlAA PAPER 88-27961 p 815 A88-53102 [ASME PAPER 88-GT-3021 p 821 A88-54371 [AIAA PAPER 88-4429) p 807 A88-53754 UDF enginelMD80 flight test program Stratified Charge Rotary Engines for aircraft A comparison of CFD and full scale VariEze wind tunnel [AIAA PAPER 88.28051 p 815 A88-53104 [ASME PAPER 88-GT-3111 p 822 A88-54379 Direct lift engine for advanced V/STOL transport results FIOO-PW-229- Higher thrust in same frame size [AIAA PAPER 88-2890Al p 816 A88-53111 [AIAA PAPER 88.44631 p 807 A88-53759 [ASME PAPER 88-GT-3121 p 822 A88-54380 Technology sensitivity studies for a Mach 3.0 civil Vehicle Management Systems - The logical evolution A turbine wheel design story transport of integration [ASME PAPER 88-GT-3161 p 822 A88-54383 [AlAA PAPER 88-44691 p 783 A88-53761 [AIAA PAPER 88.31751 p 826 A88-53148 The impact of VTOL on the conceptual design Navy application of a standard fatigue and engine Fiber optics based jet engine augmenter viewing process monitoring system system [AIAA PAPER 88-44791 p 807 A8843763 [AIAA PAPER 88-33151 p 81 3 A88-53156 [ASME PAPER 88-GT-3201 p 852 A88-54385 High speed transpacific passenger flight Meeting the high temperature challenge - The Evaluation of potential engine concepts for a high [AlAA PAPER 88-44841 p 807 A88-53764 non-metallic aero engine p 838 A88-53838 altitude long endurance vehicle Preliminary design of two transpacific high speed civil Toward improved durability in advanced aircraft engine [ASME PAPER 88-GT-3211 p 822 A88-54386 transports hot sections; Proceedings of the Thirty-third ASME Fiber optics for aircraft engine controls [AlAA PAPER 88-448561 p 807 A88-53765 International Gas Turbine and Aeroengine Congress and p 822 A88-54619 Planform effects on high speed civil transport design Exposition. Amsterdam. Netherlands. June 5-9. 1988 Very high speed integrated circuitslgallium arsenide [AIAA PAPER 88-44871 p 807 A8863767 p 817 A88-54137 electronics for aircraft engine controls Assessment of a Soviet hypersonic transport NASA HOST project overview --- hot section p 823 A88-54620 [AIAA PAPER 88-4506) p 808 A88-53770 technology p 81 7 A88-54138 The characterizationof high temperalure electronics for Development, analysis. and flight test of the Lockheed Structuralanalysis applications ---for aircraft gas turbine future aircraft engine digital electronic control systems Aeronautical System Company HTTB HUD combustors p 817 A88-54143 p 823 A88-54621 Views on the impact of HOST hot section [AIAA PAPER 88-4511 1 p 81 3 A8863772 --- High temperature, lightweight, switched reluctance technology p818 AM-54146 Flight testing of fighters during the World War ll era motors and generators for future aircraft engine The effects of an excited impingingjet on the local heat [AlAA PAPER 88-45121 p 862 A88-53773 applications p 823 A88-54623 The criticality of weight and balance on competition transfer coefficient of aircraft turbine blades Composites break the ice --- fiber reinforced materials aircraft [ASME PAPER 88-GT-661 p 847 A88-54197 for deicing of aircraft surfaces and engines [SAWE PAPER 17561 p 808 A8833776 Further asoects of the UK enaine technoloav -. p 840 A88-54857 Predicting. determining. and controlling manufacturing demonstrator programme variation in a new facility --- aircraft production [ASME PAPER 88-GT-1041 p 848 A8844223 AGARD engine disc cooperative test programme [SAWE PAPER 1771I p 783 A88-53782 An emissions database for U.S. Navv and Air Force [AGARD-R-766] p 824 N88-28926 Lockheed HTTB - STOL performance features Aircraft engines Developing the Rolls-Royce Tay [SAWE PAPER 17721 p 808 A88-53783 [ASME PAPER 88-GT-1291 p 818 A88-54239 [ PNR90447I p 825 N88-29809 Ultimate factor for structural design of modern fighters Second sourcing of a jet engine Fuel effects on flame radiation and hot-section [SAWE PAPER 17751 p 808 A88-53784 [ASME PAPER 88-GT-1451 p 784 A88-54246 durability p 843 N88-29925 Use of a detail cost model to perform conceptual phase Oesian and test of non-rotatina ceramic aas turbine Contaminationand distortion of steady flow field induced cost analysis components by discrete frequency disturbances in aircraft gas [SAWE PAPER 17841 p 862 A88-53788 [ASME PAPER 88-GT-1461 p 819 A88-54247 engines Estimatingfuselage weight penalty required to suppress A UK Dersoective on Enaine Health Monitorina-. EHMl . [AD-A1954401 p 854 N88-30069 noise from propfans systems'for iuture technology military engines AIRCRAFT EQUIPMENT [SAWE PAPER 17871 p 809 A88-53790 [ASME PAPER 88-GT-1481 p 81 9 A88-54249 The Flight of Flexible Aircraft in Turbulence: Crashworthinessvs. airworthiness The measurementof stress and vibrationdata in turbine State-of-the-Art in the Description and Modelling of [SAWE PAPER 17881 p 809 A8863791 blades and aeroengine components Atmospheric Turbulence Economical technology application in commercial [ASME PAPER 88-GT-1491 p 849 A88-54250 [ AGARD-R-7341 p 785 N88-29725 transport design Calibration of CFD methods for high Mach number A summary of atmospheric turbulence measurements [SAWE PAPER 17981 p 809 A88-53798 aeroengine flowfields with specially-equippedaircraft in the US Daedalus - The making of the legend [ASME PAPER 88-GT-1991 p 792 A88-54286 p 857 N88-29727 p 784 A88-55000 Thermomechanical advances for small gas turbine Standard fatigue specimens for fastener evaluation --- Control surface selection based on advanced modes engines - Present capabilities and future direction in gas aircraft components performance generator designs [FFA-TN-I987.681 p 856 N88-30157 [AIAA PAPER 88.43561 p 829 A8845275 [ASME PAPER 88-GT-2131 p 850 A88-54299 AIRCRAFT FUEL SYSTEMS Complex configurations p 834 N88-28861 Theoretical investigation of the interaction between a Effect of molecular structure on soot formation Transport-type configurations p 809 N88-28867 compressor and the components during surge characteristics of aviation turbine fuels Combat aircraft p 810 N88-28868 [ASME PAPER 88-GT-2201 p 851 A88-54305 [ASME PAPER 88-GT-PI 1 p 838 A88-54167 Variable Sweep Transition Flight Experiment Transient performance trending for a turbofan engine AIRCRAFT FUELS (VSTFE)-parametric pressure distribution boundary layer [ASME PAPER 88-GT-2221 p 819 A88-54306 Viability rating by fuel indexing method stability study and wing glove design task Comparison of ceramic vs. advancedsuperalloy options p 815 A88-52698 [NASA-CR-39921 p 798 "38-28894 for a small gas turbine technology demonstrator Principles of the use of fuels and lubricants in civil A contributiontothe quantitativeanalysisof the influence [ASME PAPER 88-GT-2281 p 851 A88-54311 aviation --- Russian book p 838 A88-54001 of design parameters on the optimal design 01 passenger A methanol/oxygen burning combustor for an aircraft Combustion and fuels in gas turbine engines aircraft auxiliary emergency power unit [AGARD-CP-4221 p 841 N88-29910 [ ETN-88-929791 p 810 N88-28912 [ASME PAPER 88-GT-2361 p 820 A88-54317 AIRCRAFT GUIDANCE Critical joints in large composite primary aircraft Linear stale variable dynamic model and estimator Application of AI methods lo aircraft guidance and structures. Volume 2: Technology demonstration test design for Allison T406 gas turbine engine control p 827 A88-54424 report [ASME PAPER 88-GT-2391 p 820 A88-54319 Trajectory optimization and guidance law development [NASA-CR-172587] p 811 N88-28915 AGTlOl /ATTAP ceramic technology development for national aerospace plane applications Critical joints in large composite primary aircraft [ASME PAPER 88-GT-2431 p 820 A88-54322 p 837 A8834567 structures. Volume 3: Ancillary test results Recent advances in engine health management Optimization and guidance of penetration landing [NASA-CR-172588] p 811 N88-28916 [ASME PAPER 88-GT-2571 p 820 A88-54333 trajectories in a windshear p 828 A88-54570 The Flight of Flexible Aircraft in Turbulence: A comparison of engine design life optimization results AIRCRAFT HAZARDS State-of-the-Art in the Description and Modelling of using deterministic and probabilistic life prediction Icing Technology Bibliography Atmospheric Turbulence techniques [SAE AIR 40151 p 801 A88-54400 [AGARD-R-734-ADD] p 784 N88-29717 [ASME PAPER 88-GT-2591 p 820 A88-54335 Development of a MHz RF leak detector technique for Current and proposedgust criteria and analysis methods: Structural design and its improvements through the aircraft hardness surveillance p 81 3 A88-54725 An FAA overview p 830 N88-29718 development of the XF3-30 engine Extreme gusts distribution p 857 N88-29734 A summary of methods for establishing airframe design [ASME PAPER 88-GT-2611 p 821 A88-54337 AIRCRAFT INDUSTRY loads from continuous gust design criteria China's acquisition and use of foreign aviation Laser - A gas turbine combustor manufacturingtool p 811 N88-29721 [ASME PAPER 88-GT-2671 p 851 A8844342 technology Comparison of the influence of different gust models [ ADA1 948271 p 862 N88-30471 A new source of lightweight, compact multifuel power on structural design p 81 1 N88-29722 AIRCRAFT LANDING Measured and predicted responses of the Nord 260 for vehicular, light aircraft and auxiliary applications - The Processingpseudo synthetic aperture radar images from joint Oeere Score engines aircraft to the low altitude atmospheric turbulence visual terrain data [ASME PAPER 88-GT-2711 p 851 A8844345 p 830 N88-29723 [AIAA PAPER 88.45761 p 802 A88-53628 A review of measured gust responses in the light of Response of large turbofan and turbojet engines to a Oplimization and guidance of penetration landing modern analysis methods p 830 N88-29724 short-durationoverpressure tralectories in a windshear p 828 A88-54570 Aircraft dynamics: Aerodynamic aspects and wind tunnel [ASME PAPER 88-GT-2731 p 821 A88-54346 Additional investigations into the aircraft landing techniques p 798 N88-29731 Development of the T406-AD-400 oil scavenge system process: Test distributions Compression pylon for the V-22 aircraft [ ESA-TT-I099 I p 810 N88-28913 [NASA-CASE-LAR-13777-1] p 812 N88-29789 [ASME PAPER 88-GT-2971 p 821 A88-54366 AIRCRAFT MAINTENANCE AIRCRAFT ENGINES XG40 - Advanced combat engine technology Use of composile materials lo repair metal structures Control of rotor aerodynamically forced vibrations by demonstrator programme p 804 A88-52660 splitters p 81 5 A88-52684 [ASME PAPER 88-GT-3001 p 821 A88-54369 Caring lor the high-time jet p 801 A8843540

A-3 AIRCRAFT MANEUVERS SUBJECT INDEX

Artificial intelligence systems for aircraft training - An Predicting. determining, and controlling manufacturing AIRDROPS evaluation vanation in a new facility --- aircraft production Control systems for plalform landings cushioned by air [AIAA PAPER 88-45881 p 857 A88 53637 [SAWE PAPER 17711 p 783 A88-53782 bags A UK perspective on Engine Health Monitoring (EHM) Use of a detail cost model to perform conceptual phase [AD-A196154] p 854 N88-29996 systems for future technology military engines cost analysis AIRFIELD SURFACE MOVEMENTS [ASME PAPER 88 GT 1481 p 819 A88 54249 [SAWE PAPER 17841 p 862 A88-53788 Airport surface traffic automation study Recent advances in engine health management Mechanization of joint production during the assembly [AD-At 945531 p 835 N88-28934 [ASME PAPER 88-GT 2571 p 820 A88-54333 of aircraft structures --- Russian book AIRFOIL PROFILES Cost benefits of nondestructive testing in aircraft p 846 A88-53998 A projection-gnd scheme for calculating transonic flow maintenance p 784 A88-55041 AIRCRAFT RELIABILITY past a profile p 785 A88-52795 AIRCRAFT MANEUVERS Advanced technology engine supportability - Preliminary Aerodynamically forced response of an airfoil including Modelling of aircraft program motion with application designer's challenge profile and incidence effects p 795 A88-54941 to circular loop simulation p 826 A88-53251 [AIAA PAPER 88-27961 p 81 5 A88-53102 An efficient patched grid Navier-Stokes solution for A knowledge based system of supermaneuver selection multiple bodies, phase 1 Caring for the high-time jet p 801 A88-53540 for pilot aiding [AD-A194166] p 853 N88-29110 [AIAA PAPER 88-44421 p 827 A88-53755 Crashworthiness vs. airworthiness AIRFOILS IMMP A computer simulation of fuel CG versus vehicle [SAWE PAPER 1788) p 809 A88-53791 Design code verification of external heat transfer anit u d e The Flight of Flexible Aircraft in Turbulence: coefficients [SAWE PAPER 18011 p 827 A88-53799 State-of-the-Art in the Description and Modelling of [AIAA PAPER 88-3011 ] p 844 A88-53123 Structural dynamics of maneuvenng aircraft Atmospheric Turbulence Developments in computational methods for high-lift [AD-A192376] p 810 N88-28908 [AGARD-R-734-ADD] p 784 N88-29717 aerodynamics p 786 A88-53250 An intenm comparison of operational CG records in Current and proposed gust critena and analysis methods: Numencal analysis of airfoil and cascade flows by the turbulence on small and large civil aircraft An FAA overview p 830 N88-29718 viscouslinviscid interactive technique p 830 N88-29729 Re-assessment of gust statistics using CAADRP data [ASME PAPER 88-GT-1601 p 791 A88-54259 AIRCRAFT MODELS p 831 N88-29732 New erosion resistant compressor coatings The minimisation of helicopter vibration through blade The development of acoustic emission for structural [ASME PAPER 88-GT-1861 p 839 A88-54277 design and acbve control p 805 A88-53249 integrity monitonng of aircraft Test results and theoretical investigations on the ARL Modelling of aircraft program motion with application [ AD-At 962641 p 861 N88-30398 19 supersonic blade cascade to circular loop stmulabon p 826 A88-53251 AIRCRAFT SAFETY [ASME PAPER 88-GT-2021 p 792 A88-54289 Real-time simulation of helicopters using the blade Helicopter health monitoring from engine to rotor A new singular integral approach for a vertical array of airfoils element method [ASME PAPER 88-GT-2271 p 809 A88-54310 [AIM PAPER 88-45821 p 805 A88-53634 [ASME PAPER 88-GT-2181 p 793 A88-54303 The Flight of Flexible Aircraft in Turbulence: Estimation of aircraft parameters using filter error Thermal bamer coatings for let engines State-of-the-Art in the Description and Modelling of methods and exiended Kalman filter [ASME PAPER 88-GT-2791 p 840 A88-54351 Atmospheric Turbulence [DFVLR-FB-88-151 p 810 N88-28911 Current status and future trends in turbine application [AGARD-R-734-ADDl p 784 N88-29717 Interactive plotting of NASTRAN aerodynamic models of thermal bamer coatings using NPLOT and DISSPIA AIRCRAFT STABILITY [ASME PAPER 88-GT-2861 p 851 A88-54355 [ADA1941 I51 p 853 N88-29204 The effect of perspective displays on altitudeand stability Incompressible indicia1 response of infinite airfoils in Analysis of the transmission of sound into the passenger control in simulated rotary wing flight tandem - Some analytical results p 795 A88-54940 compartment of a propeller aircraft using the finite element [AIM PAPER 88-46341 p 833 A88-53667 The aerodynamics of an annular cascade of method High performance forward swept wing aircraft three-dimensional airfoils p 795 A8844942 [FFA-TN 1988-151 p 861 NE8 29520 [NASA-CASE-ARC-I1636-1 1 p 810 N88-28914 Computational tools for simulation methodologies A comparison of simple analytical models for A second look at MIL prime flying qualities p 834 N88-28865 representing propeller aircraft structural and acoustic requirements p 812 N88-29740 Effects of independent variation of Mach and Reynolds responses AIRCRAFT STRUCTURES numbers on the low-speed aerodynamic characteristics [ISVR-TR-153] p 861 N88-29523 Damage tolerance in pressurized fuselages of the NACA 0012 airfoil section Computer programs for generation of NASTRAN and p 803 A88-52652 [ NASA-TM-40741 p 784 N88-28879 VIBRA-6 aircraft models Fatigue crack growth characterization of jet transport Noise generation and boundary layer effects in [AD-A195467] p 812 N88-29792 structures p 803 A88-52653 vortex-airfoil interaction and methods of digital hologram AIRCRAFT NOISE Evaluation of new matenals in the design of aircraft analysis for these flow fields Future supersonic transport noise - Lessons from the structures p 803 A88-52654 [AD-A194191] p 797 N88-28883 past Aspects of the fatigue behaviour of typical adhesively Unsteady flow past an NACA 0012 airfoil at high angles [AIAA PAPER 88-29891 p 816 A88-53121 bonded aircraft structures p 804 A88-52659 of anack Developing the Rolls-Royce Tay Enstaff - A standard test sequence for composite [AD-A194650] p 797 N88-28886 [ASME PAPER 88-GT-3021 p 821 A88 54371 components combining load and environment The effects of inlet turbulence and rotorlstator Aircraft noise prediction program propeller analysis p 804 A88-52666 interactions on the aerodynamics and heat transfer of a system IBM-PC version users manual version 2 0 Certification of primary composite aircraft structures large-scale rotatingturbine model. Volume 3: Heat transfer [ NASA-CR-1816891 p 862 N88-30399 p 805 A88-52672 data tabulation 65 percent axial spacing AIRCRAFT PARTS Structural technology transition to new aircraft [ NASA-CR-1794681 p 824 N88-28930 The criticality of weight and balance on competition p 805 A88-52673 The use of hot-film technique lor boundary layer studies aircraft Navy application of a standard fatigue and engine on a 21 percent thick airfoil [SAWE PAPER 17561 p 808 A8843776 monitoring system [NAE-AN-45] p 800 N88-29781 AIRCRAFT PERFORMANCE [AIAA PAPER 88-33151 p 813 A88-53156 The effects of inlet turbulence and rotorlstator Viability rating by fuel indexing method Mechanization of joint production during the assembly interactions on the aerodynamics and heat transfer of a p 81 5 A88-52698 of aircraft structures --- Russian book large-scalerotating turbine model. Volume 2: Heat transfer Simulator evaluation of takeoff performance monitoring p 846 A88-53998 data tabulation. 15 percent axial spacing system displays Composites break the ice --- fiber reinforced materials [NASA-CR-179467] p 825 N88-29804 [AIAA PAPER 88-4611 I p 833 A88-53653 for deicing of aircraft surfaces and engines Studies 01 gas turbine heat transfer airfoil surface and YA-7F - A twenty year economic life extension at costs p 840 A88-54857 end-wall cooling effects we can afford Service failure of a 7049 T73 aluminum aircraft forging [ AD-AI 951651 p 825 N88-29805 [AIAA PAPER 88-44601 p 783 A88-53757 p 840 A88-55286 AIRFRAME MATERIALS A different approach to the interrelated subjects 01 Critical joints in large composite pnmary aircraft Accounting for service environment in the fatigue weight. performance. and price as applied to commercial structures. Volume 2: Technology demonstration test evaluation of composite airframe structure transport aircraft report p 804 A88-52665 [SAWE PAPER 17791 p 808 A88-53786 [NASA-CR-I 725871 p 81 1 N88-28915 AIRFRAMES Energy maneuverability and engine performance Critical joints in large composite primary aircraft Advanced Composite Airframe Program (ACAP) - An requirements structures. Volume 3: Ancillary test results update and final assessment of weight saving potential [ASME PAPER 88-GT-3031 p 822 A88-54372 [ NASA-CR-1 72588 I p 81 1 N88-28916 [SAWE PAPER 17701 p 808 A88-53781 The aerodynamics of an annular cascade of Asymptotic modal analysis and statistical energy Crash simulation calculations and component three-dimensional airfoils p 795 A88-54942 analysis idealization for an airframe. Computer code KRASH 79 High performanceforward swept wing aircraft [NASA-CR-183077] p 861 N88-29514 [ ETN-88-929711 p 801 N88-28899 [NASA-CASE-ARC-I1636-1 1 p 810 N88-28914 A comparison of simple analytical models for Stress intensity factors for cracked metallic structures Measured and predicted responses of the Nord 260 rewesentina Drooeller aircraft structural and acoustic under rapid thermal loading aircraft to the low altitude atmosphenc turbulence responses [ AD-At 9121 91 p 840 N88-29004 p 830 N88-29723 [ISVR-TR-153] p 861 "3.29523 A summary of methods for establishing airframe design Status review of atmosphere turbulence and aircraft Aircraft airframe cost estimatina relationshivs Studv loads from continuous gust design criteria response p 830 N88-29726 approach and conclusions p 81 1 N88-29721 Aircraftdynamics Aerodynamic aspects and wind tunnel [R-3255-AF] p 81 3 N88-29795 Aircraft airframe cost estimating relationships: Study techniques p 798 N88-29731 AIRCRAFT SURVIVABILITY approach and conclusions AIRCRAFT POWER SUPPLIES Robust control strategy for take-oft performance in a [R-3255-AF] p 81 3 N88-29795 High temperature, lightweight. switched reluctance windshear p 829 A88-54656 Evaluation of bond testing equipment for inspection of motors and generators for future aircraft engine Threat expert system technology advisor Army advanced composite airframe structures applications p 823 A88-54623 [ NASA-CR-1774791 p 831 N88-29816 [AD-AI 957951 p 841 "3-29885 AIRCRAFT PRODUCTION AIRCRAFT WAKES AIRPORT PLANNING Structural technology transibon to new aircraft Wake-induced unsteady aerodynamic interactions in a Airport surface traffic automation study p 805 A88-52673 multistage compressor p 785 A88-52686 [AD-A194553] p 835 N88-28934

A-4 SUBJECT INDEX BLADE TIPS

AIRPORTS ARTIFICIAL INTELLIGENCE A new source of lightweight. compact multifuel power An analysis of time and space requirements for aircraft Artificial intelligence systems for aircraft training - An for vehicular, light aircraft and auxiliary applications - The turnrounds evaluation joint Deere Score engines [TT-8705] p 802 N88-29783 [AIAA PAPER 88-45881 p 857 A8843637 [ASME PAPER 88-GT-2711 p 851 A88-54345 ALGEBRA Smarl command recognizer (SCR) - For development, AVIONICS Algebraic grid generation for fighter type aircraft test, and implementation of speech commands Real-time simulation - A tool for development and p 859 N88-29320 [AIAA PAPER 88-46121 p 858 A88-53654 verification Compositegrid generation for aircraft configurations with The application of artificial intelligence technology to [AIAA PAPER 88-46181 p 833 A88-53657 the EAGLE code p 859 N88-29321 aeronautical system design Some benefits of distributedcomputing architectures for ALGORITHMS [AIAA PAPER 88-44261 p 806 A88-53752 training simulators p 858 A88-53671 A quasi-procedural,knowledge-based system for aircraft A minimal realization algorithm for flight control Development of a MHz RF leak detector technique for design systems p 829 A88-54661 aircraft hardness surveillance p 813 A88-54725 [AIAA PAPER 88-44281 p A88-53753 An efficient patched grid Navier-Stokes solution for 806 Avionics system design for high energy fields: A guide Application of AI methods to aircraft guidance and multiple bodies, phase 1 for the designer and airworthiness specialist control p 827 A8844424 [ AD-A 1941 66 p N88-29110 [NASA-CR-t815901 p 814 N88-28919 1 853 Rule-based mechanisms of learning for intelligent Aircraft avionics and missile system installation cost ALTITUDE CONTROL adaptive flight control p 858 A88-54426 study. Volume 1: Technical report and appendices A The effect of perspective displays on altitudeand stability ASTRONAUT TRAINING through E control in simulated rotary wing flight NASA Shuttle Training Aircraft flight simulation [AD-A194605] p 81 4 N88-28923 [AIAA PAPER 88-46341 p 833 A88-53667 ovewiew Avionic expert systems p 814 N88-29365 ALTITUDE TESTS [AIAA PAPER 88-46081 p 806 A88-53650 Navy V/STOL Engine experience in Altitude Test AXIAL FLOW ASYMPTOTIC METHODS Flutter of a fan blade in supersonic axial flow Facility Asymptotic modal analysis and statistical energy [ASME PAPER 88-GT-3171 p 834 A88-54384 [ASME PAPER 88-GT-781 p 788 A88-54206 analysis Studies of unsteady axial-compressor functioning ALUMINUM [ NASA-CR-1830771 p 861 N88-29514 p 855 N88-30129 Fatigue crack growth characteristics of ARALL ATMOSPHERIC EFFECTS AXIAL FLOW TURBINES (trademark). 1 Image extrapolation for flight simulator visual systems Analysis of rotor tip clearance loss in axial-flow [AD-A196185] p 841 NEB-29889 [AIAA PAPER 88.45771 p 832 A88-53629 turbines p 785 A88-52685 Development of graded reference radiographs for ATMOSPHERIC TURBULENCE Flow in single and twin entry radial turbine volutes aluminum welds, phase 1 The Flight of Flexible Aircraft in Turbulence: [ASME PAPER 88-GT-591 p 847 A88-54191 [ AD-A195594 1 p 855 N88-30140 State-of-the-Art in the Description and Modelling of A fast interactivetwo-dimensional blade-to-bladeprofile ALUMINUM ALLOYS Atmospheric Turbulence design method Evaluation of new materials in the design of aircraft [AGARD-R-734-ADD] p 784 N88-29717 [ASME PAPER 88-GT-1001 p 790 A88-54220 structures p 803 A88-52654 Current and proposed gust criteriaand analysis methods: Investigation of boundary layer transitionand separation Fatigue of elevated temperature powder metallurgy An FAA overview p 830 N88-29718 in an axial turbine cascade using glue-on hot-film gages aluminum alloy mechanically fastened joints Flight test equipment for the on-board measurement of [ASME PAPER 88-GT-1511 o 791 A68-54251 p 837 A88-52655 wind turbulence p 814 NEB-29719 Effect of free-stream turbblence, Reinolds number, and Microscopic inner damage correlated with mechanical Measured and predicted responses of the Nord 260 incidence on axial turbine cascade pehormance properly degradation due to simulated fatigue loading in aircraft lo the low altitude atmospheric turbulence [ASME PAPER 88-GT-1521 p 791 A88-54252 metal matrix composites p 837 A88-52657 p 830 N88-29723 Aspects of the fatigue behaviour of typical adhesively The Flight of Flexible Aircraft in Turbulence: B bonded aircraft structures p 804 A88-52659 State-of-the-Art in the Description and Modelling of Fatigue crack propagation test programme for the A320 Atmospheric Turbulence BALANCING wing p 804 A88-52662 [AGARD-R-7341 p 785 N88-29725 Spray automated balancing of rotors -Concept and initial Service failure of a 7049 T73 aluminum aircraft forging Status review of atmosphere turbulence and aircraft feasibility study p 840 A88-55286 response p 830 "3-29726 [ASME PAPER 88-GT-1631 p 849 A88-54261 ANALYSIS (MATHEMATICS) A summary of atmospheric turbulence measurements Spray automated balancing of rotors Methods and Theoretical aerodynamics, transonic flow with specially-equipped aircraft in the US materials [AD-A196247] p 800 N88-29777 p 857 N88-29727 [ NASA-CR-1821511 p 836 N88-29825 ANGLE OF ATTACK The NAE atmospheric research aircraft BALLOON-BORNE INSTRUMENTS Jump strut means shorter takeoff rolls p 815 N88-29730 Pilotage system for the Pronaos gondola --- French p 803 A88-52375 Extreme gusts distribution p 857 N88-29734 balloon-bornesubmillimeter telescope [IAF PAPER 88-0081 p 809 A88-55317 An airborne system for vortex flow visualization on the A digital simulation technique forthe Drydenatmospheric BASEPRESSURE F-18 high-alpha research vehicle model Base pressure in transonic speeds - A comparison [AIAA PAPER 88-46711 p 813 A88-53830 [ NASA-TT-203421 p 857 N88-30266 Calculation of aerodynamic characteristics of airplane between theory and experiment AlTACKING (ASSAULTING) [ASME PAPER 88-GT-1321 p 790 A88-54240 configurations at high angles of attack Determination of the hydroperoxide potential of jet [ NASA-CR-41821 p 797 N88-28891 BEAMS (SUPPORTS) fuels Application of the theory of anisotropic thin-walled Angle of attack and sideslip estimation using an inertial [AD-A195975] p 844 N88-29991 beams and dates for winos made from comDosite reference platform ATTITUDE (INCLINATION) material [ AD-A1948761 p 799 N88-29769 Improvement of head-up display standards. Volume 2: [IAF PAPER 88-2751 p 852 A88-55372 Computer programs for calculation of sting pitch and Evaluation of head-up displays loenhance unusual attitude BEARINGS roll angles required to obtain angles of attack and sideslip recovery Active control of transient rotordynamic vibration by on wind tunnel models IAD-AI 94601 ] p 814 N88-28921 optimal control methods [ NASA-TM-100659] p 835 N88-29820 ATTITUDE CONTROL [ASME PAPER 88-GT-731 p 858 A88-54202 ANISOTROPIC PLATES Angle of attack and sideslip estimation using an inertial BIAS Application of the theory of anisotropic thin-walled reference platform Two biased estimation techniques in linear regression beams and plates for wings made from composite [ AD-A1948761 p 799 N88-29769 Application to aircraft material AUTOMATIC CONTROL [ NASA-TM-1006491 p 860 N88-29489 [IAF PAPER 88.2751 p 852 A88-55372 Feasibility study of a microprocessor controlledactuator BIBLIOGRAPHIES ANNULAR FLOW test mechanism Icing Technology Bibliography Experimental investigation of the three-dimensional flow [ AD-A1946541 p 860 N88-29337 [SAE AIR 40151 p 801 A88-54400 in an annular compressor cascade Spray automated balancing of rotors: Methods and BlHARMONlC EQUATIONS [ASME PAPER 88-GT-2011 p 792 A88-54288 materials Grid generation for an advanced fighter aircraft The aerodynamics of an annular cascade of [NASA-CR-182151] p 836 N88-29825 p 859 N88-29319 three-dimensional airfoils p 795 A8864942 AUTOMATIC FLIGHT CONTROL BLADE TIPS ARC SPRAYING A hyperstable model-followingflight control system used Analysis of rotor tip clearance loss in axial-llow Composite monolayer fabrication by an arc-spray for reconfigurationfollowing aircraft impairment turbines p 785 A88-52685 process p 845 A88-53581 p 828 A88-54652 Flow field in the tip gap of a planar cascade of turbine ARCHITECTURE (COMPUTERS) blades Automated design of continuously-adaptivecontrol -The Some benefitsof distributed computing architecturesfor [ASME PAPER 88-GT-291 p 787 A8864173 'super-controller'strategy for reconfigurable systems training simulators p 858 A88-53671 The influence of turbine clearance gap leakage on p 829 A88-54653 A multiprocessor avionics system for an unmanned passage velocity and heat transfer near blade tips I .Sink research vehicle AUTOMATIC PILOTS flow effects on blade pressure side [AD-A194806] p 81 5 N88-29800 Considerationsfor automated nap-of-the-earthrotorcraft [ASME PAPER 88-GT-981 p 790 A88-54218 N-version software demonstration for digital flight flight p 827 A88-54526 The influence of turbine clearance gap leakage on controls AUTOMATION passage velocity and heat transfer near blade tips II - [NASA-CR-181483] p 831 N88-29815 Mechanization of joint production during the assembly Source flow effects on blade suction sides AREA NAVIGATION of aircraft structures --- Russian book [ASME PAPER 88-GT-991 p 790 A8864219 Observed track-keeping performance of DCI 0 aircraft p 846 A8863998 Tip leakage in a centrifugal impeller equipped with the Collins AINS-70 area navigation system: AUXILIARY POWER SOURCES [ASME PAPER 88-GT-2101 p 792 A88-54296 Karlsruhe and Masstricht UACs (Upper Area Control A methanolloxygen burning combustor for an aircraft Analysis of efficiency sensitivity associated with tip centres) auxiliary emergency power unit clearance in axial flow compressors [EEC-ZOZ] P 803 N88-29788 [ASME PAPER 88-GT-2361 p 820 A88-54317 [ASME PAPER 88-GT-2161 p 819 A88 54301

A-5 BLADE-VORTEX INTERACTION SUBJECT INDEX

Structure of tip clearance flow in an isolated axial Boundary-layer flows in rotating cavities Industrial production of CFRP-components in Airbus compressor rotor [ASME PAPER 88-GT-2921 p 852 A88-54361 construction [ASME PAPER 88-GT 2511 p 794 A88 54327 Noise generation and boundary layer effects in [ SAWE PAPER 17941 p 845 A88-53795 Experimental investigation of the performance of a vortex-airfoil interaction and methods of digital hologram Composites break the ice --- fiber reinforced materials supersonic compressor cascade analysis for these flow fields for deicing of aircraft surfaces and engines [ASME PAPER 88 GT 3061 p 795 A88-54375 [AD-A194191] p 797 N88-28883 p 840 A8844857 Incompressible indicia1 response of infinite airfoils in The use of hot-film technique for boundary layer studies The non-destructivetesting of welds in continuous fibre tandem Some analytical results p 795 A88 54940 on a 21 percent thick airfoil reinforced thermoplastics p 852 A88-55456 Investigationof helicopter rotor bladelwake interactive [NAE-AN-451 p 800 N88-29781 Investigationson the modification of Structural reliability impulslve noise BOUNDARYLAYERSEPARATION by substitution of aluminum by carbon fiber reinforced [ NASA-CR-1774351 p 797 N88-28882 Transition modeling effects on viscouslinviscid plastics in aircraft construction BLADE-VORTEX INTERACTION interaction analysis of low Reynolds number airfoil flows IILR-MITT-1951 p 841 N88-29877 On the prediction of unsteady forces on gas-turbine involving laminar separation bubbles CARBONCARBON COMPOSITES blades I Typical results and potential flow-interaction - [ASME PAPER 88-GT-321 p 787 A88-54175 CIC composite materials for aircraft brakes effects Investigationof boundary layer transition and separation p 837 A8843542 [ASME PAPER 88-GT 891 p 789 A88 54213 in an axial turbine cascade using glue-on hot-film gages CARGO AIRCRAFT On the prediction of unsteady forces on gas turbine [ASME PAPER 88-GT-151I p 791 A88-54251 Design concepts for an Advanced Cargo Rotorcraft blades II - Viscous-wake-interaction and axial-gap Calculation of aerodynamic characteristics of airplane [AIAA PAPER 88.44961 p 807 A88-53768 effects configurations at high angles of attack Lockheed HllB - STOL performance features [ASME PAPER 88-GT-901 p 789 A88-54214 [ NASA-CR-41821 p 797 N88-28891 ISAWE PAPER 17721 p 808 A88-53783 Investigation of helicopter rotor bladelwake interactive A study of the effect of random input motion on low CARTESIAN COORDINATES impulsive noise Reynolds number flows Grid embeddingtechnique using Cartesiangrids for Euler [NASA CR 1774351 p 797 N88-28882 [AD-A195559] p 798 N88-29747 solutions p 796 A88-55094 BLADES BOUNDARY LAYER TRANSITION CASCADE FLOW An experimentalinvestigation into the influence of blade Transition modeling effects on viscouslinviscid Detection of separation bubbles by infrared images in leaning on the losses downstream of annular cascades interaction analysis of low Reynolds number airfoil flows transonic turbine cascades with a small diameter height ratio involving laminar separation bubbles [ASME PAPER 88-GT-331 p 787 A88-54176 [ASME PAPER 88 GT 191 p 786 A88-54165 [ASME PAPER 88-GT-321 p 787 A88-54175 Design point variation of 3-13 loss and deviation for axial BLOWDOWN WIND TUNNELS Investigationof boundary layer transition and separation compressor middle stages Gas temperature measurements in short duration in an axial turbine cascade using glue-on hot-film gages [ASME PAPER 88-GT-571 p 787 A88-54189 turbomachinery test facilities [ASME PAPER 88-GT-1511 p 791 A8844251 Effects of incidence on three-dimensional flows in a [AIAA PAPER 88 30391 p 844 A88-53128 Measurement and modelling of the gas turbine blade linear turbine cascade BLOWOUTS transition process as disturbed by wakes [ASME PAPER 88-GT-1101 p 790 A8844228 The blowout of turbulent jet flames in co-flowingStreams [ASME PAPER 88-GT-2321 p 793 A88-54314 Numerical analysis of airfoil and cascade flows by the of fuel-air mixtures Variable Sweep Transition Flight Experiment viscouslinviscid interactive technique [ASME PAPER 88 GT-1061 p 838 A88 54225 (VSTFE)-parametric pressure distribution boundary layer [ASdE PAPER 88-GT-1601 p 791 A88-54259 BLUNT BODIES stability study and wing glove design task Effect of shock wave movement on aerodynamic Three-dimensional hypersonic viscous shock layer on [ NASA-CR-39921 p 798 N88-28894 instability of annular cascade oscillating in transonic flow blunt bodies in flow at angles of attack and sideslip Techniques used in the F-14 variable-sweep transition [ASME PAPER 88-GT-I871 p 792 A88-54278 p 786 A88-53971 flight experiment Expenmentalinvestigation of the three-dimensionalflow A preliminary investigation of drag reduction and [ NASA-TM-IO04441 p 855 N88-30093 in an annular compressor cascade mechanism for a blunt body of revolution with slanted BRAZING [ASME PAPER 88-GT-2011 p 792 A88-54288 base Technology for PreSSUre-inStNmented thin airfoil Performance of a compressor cascade configuration [ NASA-TT-203491 p 799 N88-29753 with supersonic entrance flow A review and comparison models - BLUNT LEADING EDGES [ NASA-CR-41731 p 835 N88-28933 of experlments in three installations Causes for turbomachinery performance deterioration BRISTOL-SIDDELEY BS 53 ENGINE [ASME PAPER 88-GT-2111 p 793 A88-54297 [ASME PAPER 88-GT-2941 p 821 A88-54363 Navy V/STOL Engine experience in Altitude Test Flow computation and blade cascade design in turbopump turbines BODIES OF REVOLUTION Facility A preliminary investigation of drag reduction and [ASME PAPER 88-GT-3171 p 834 A88-54384 [ASME PAPER 88-GT-2481 p 820 A88-54326 An experimental investigation a vortex flow cascade mechanism for a blunt body of revolution with slanted BUOYANCY of base Cool gas generator systems [ASME PAPER 88-GT-2651 p 794 A88-54341 [ NASA-TT 203491 p 799 N88-29753 [AIAA PAPER 88-33631 p 805 A88-53161 The effect of the Reynolds number on the BODY-WING CONFIGURATIONS BURNING RATE three-dimensional flow in a straight compressor cascade Planform effects on high speed civil transport design Flame speeds in fuel sprays with hydrogen addition [ASME PAPER 88-GT-2691 p 794 A8844343 [AIAA PAPER 88-44871 p 807 A8843767 [ASME PAPER 88-GT-201 p 838 A88-54166 Expenmental investigation of the performance of a Analytical surfaces and grids p 860 N88-29322 A methanolloxygen burning combustor for an aircraft supersonic compressor cascade BOEING 737 AIRCRAFT auxiliary emergency power unit [ASME PAPER 88-GT-3061 p 795 A8844375 Caring for the high-time jet p 801 A88-53540 [ASME PAPER 88-GT-2361 p 820 A88-54317 Aerodynamics in ground effect and predicted landing BONDING BYPASS RATIO ground roll of a fighter configuration with a Evaluation of bond testing equipment for inspection of Towards the optimum ducted UHBR engine --- Ultra High secondary-nozzlethrust reverser Army advanced composite airframe structures Bypass Ratio NASA-TP-28341 p 799 N88-29752 [ AD-AI 957951 p 841 N88-29885 [AIM PAPER 88.29541 p 816 A88-53119 CASCADE WIND TUNNELS BOUNDARYLAYERCONTROL An experimental investigationinto the influence of blade Suction laminarization of highly swept supersonic leaning on the losses downstream of annular cascades laminar flow control wings C with a Small diameter-height ratio [AIAA PAPER 88-4471I p 786 A88-53762 [ASME PAPER 88-GT-191 p 786 A88-54165 Boundary layer simulation and control in wind tunnels C-130 AIRCRAFT Test results and theoretical investigations on the ARL [AGARD-AR-224I p 784 "3.28857 Direct lift engine for advanced V/STOL transport 19 supersonic blade cascade High-aspect-ratiowings p 834 N88-28859 [AIM PAPER 88-2890Al p 816 A88-53111 [ASME PAPER 88-GT-2021 p 792 A88-54289 A mapping of the viscous flow behavior in a controlled Design concepts for an Advanced Cargo Rotorcraft Hot-wire measurements of compressor blade wakes in diffusion compressor cascade using laser Doppler [AlAA PAPER 88.44961 p 807 A88-53768 a cascade wind tunnel velocimetry and preliminary evaluation of codes for the Lockheed HTTB - STOL performance features [AD-A194737] p 835 N88-28936 prediction of stall [SAWE PAPER 17721 p 808 A88-53783 CATHODERAYTUBES [AD-A1944901 p 853 N88-29112 Overview of LockheedC-130 High Technology Test Bed Use of color CRTs (Cathode Ray Tubes) in aircraft Pressure distributions from subsonic tests of an Program cockpit: A literature search, revision E advanced laminar-flow-control wing with leading- and [ SAWE PAPER 17861 p 808 A88-53789 [ AD-AI 950621 p 815 N88-29797 trailing-edge flaps CALIBRATING CENTER OF GRAVITY [NASA-TM-4040 PT 21 p 800 N88-29776 Calibration of CFD methods for high Mach number Inflight CG-control - System aspects aeroengine flowfields BOUNDARY LAYER EQUATIONS [SAWE PAPER 17951 p 827 A88-53796 [ASME PAPER 88-GT-1991 p 792 A88-54286 Boundary layer flows in rotating cavities IMMP - A computer Simulation of fuel CG versus vehicle [ASME PAPER 88-GT-2921 p 852 A88-54361 CAMERAS anitude Fiber optics based jet engine augmenter viewing [SAWE PAPER 18Otl p 827 A88-53799 BOUNDARY LAYER FLOW system An experimentalinvestigation into the influence of blade [ASME PAPER 88-GT-3201 p 852 A88-54385 CENTER OF MASS leaning on the losses downstream of annular cascades CANARD CONFIGURATIONS A problem of optimal control with constraints on the with a small diameter-heightratio Canard certification loads - Progress toward alleviating coordinates of the center of mass p 858 A88-53876 [ASME PAPER 88-GT-191 p 786 A88 54185 FAA concerns CENTRIFUGAL COMPRESSORS Detection of separation bubbles by infrared images in [ AIAA PAPER 884462 I p 807 A88-53758 Calculation of complete three-dimensional flow in a transonic turbine cascades CARBON centrifugal rotor with splitter blades [ASME PAPER 88-GT-331 p 787 A88-54176 Notes on the occurrence and determination of carbon [ASME PAPER 88-GT-931 p 789 A88-54216 The vortex-filament nature of the reverse flow on the within gas turbine combustors Optimization design of the over-all dimensions of verge of rotating stall [ASME PAPER 88-GT-1641 p 839 A88-54262 centrifugal compressor stage [ASME PAPER 88-GT-1201 p 848 A8844234 CARBON FIBER REINFORCED PLASTICS [ASME PAPER 88-GT-I341 p 849 A88-54241 Wake-boundary layer interactionsin an axial flow turbine Impact and damage tolerance properties of CFRP Investigation into the effect of tip clearance on rotor at off-design conditions sandwich panels - An experimental parameter study for centrifugal compressor performance [ASME PAPER 88 GT-2331 p 793 A88-54315 the Fokker 100 CA-EP flap p 804 A88-52671 [ASME PAPER 88-GT-1901 D 850 A88-54281

A-6 SUBJECT INDEX COMPRESSOR BLADES

Tip leakage in a centrifugal impeller COAXIAL FLOW COMMERCIAL AIRCRAFT [ASME PAPER 88-GT-2101 p 792 A88-54296 Laminar flow velocity and temperature distributions Technology sensitivity studies for a Mach 3.0 civil A unified solution method for the flow calculations along between coaxial rotating disks of finite radius transport SI and S2 stream surfaces used for the computer-aided [ASME PAPER 88-GT-491 p 847 A88-54185 [AIAA PAPER 88-44691 p 783 A88-53761 design of centrifugal compressors COBALT A different approach to the interrelated subjects of [ASME PAPER 88-GT-2371 p 793 A88-54318 Plasma sprayed tungsten carbide-cobalt coatings weight, performance, and price as applied to commercial CENTRIFUGAL PUMPS p 845 A88-53579 transport aircraft Calculation of complete three-dimensional flow in a COCKPITS [SAWE PAPER 17791 p 808 A88-53786 centrifugal rotor with splitter blades Use of color CRTs (Cathode Ray Tubes) in aircraft Economical technology application in commercial [ASME PAPER 88-GT-931 p 789 A8864216 cockpit A literature search, revision B transport design [AD-AI 950621 p 815 N88-29797 CENTRIFUGES [SAWE PAPER 17981 p 809 A88-53798 Computation of the let-wake flow structurein a low speed CODING The CFM56 engine family - An internal development Fine resolution errors in SeCOndaN surveillance radar centrifugal impeller [ASME PAPER 88-GT-2961 p 862 A88-54365 altitude reporting [ASME PAPER 88-GT-2171 p 793 A88-54302 Critical joints in large composite primary aircraft [ RSRE-870191 p 802 N88-28906 structures. Volume 1: Technical summary CERAMIC COATINGS COLLINEARITY Plasma sprayed tungsten carbide cobalt coatings [NASA-CR-3914] p 840 N88-28983 Two biased estimation techniques in linear regression p 845 A88-53579 COMPONENT RELIABILITY Application to aircraft Instrumentation and techniques for structural dynamics Thermal barrier coatings for let engines [ NASA-TM-1006491 p 860 N88-29489 and acoustics measurements [ASME PAPER 88 GT 2791 p 840 A88 54351 COLLISION AVOIDANCE [AIAA PAPER 88-46671 p 845 A88-53829 CERAMIC MATRIX COMPOSITES Fine resolution errors in secondary surveillance radar COMPOSITE MATERIALS Processing technology research in composites altitude reporting Use of composite materials to repair metal structures [AD A1956931 p 841 N88-29890 [ RSRE-870191 p 802 "I-28906 p 804 A88-52860 CERAMICS UK airmisses involving commercial air transport Meeting the high temperature challenge - The Meeting the high temperature challenge - The [CAA-I 1881 p 803 N88-28907 non-metallic aero engine p 838 A88-53838 nonmetallic aero engine p 838 A88-53838 Airport surface traffic automation study Potential application of composite materials to future Design and test of non-rotating ceramic gas turbine [ AD-AI 945531 p 835 N88-28934 gas turbine engines p 823 A88-54624 components COLOR Application of the theory of anisotropic thin-walled [ASME PAPER 88-GT-1461 p 819 A88-54247 Use of color CRTs (Cathode Ray Tubes) in aircraft beams and plates for wings made from composite Comparison of ceramic vs. advanced superalloy options cockpit: A literaturesearch, material for a small gas turbine technology demonstrator [AD-A195062] P 815 N88-29797 [IAF PAPER 88.2751 p 852 A88-55372 [ASME PAPER 88-GT-2281 p 851 A88-54311 COMPOSITE STRUCTURES Use of color CRTs (Cathode Ray Tubes) in aircraft AGTt 01IATTAP ceramic technology development Accounting for service environment in the fatigue cockpit: A literature search, revision B [ASME PAPER 88-GT-2431 A88-54322 evaluation of composite airframe structure [AD-A195062] p 815 N88-29797 p 804 A88-52665 Processing technology research in composites 841 N88-29890 COMBUSTIBLE FLOW [AD-A1956931 Enstaff - A standard test sequence for composite Combustion-generated turbulence in practical components combining load and environment CERTIFICATION combustors p 815 A88-52676 p 804 A88-52666 Canard certification loads Progress toward alleviating _.. - CFD predictionof the reactingflow field inside a subscale Damaae tolerance of imDact damaaed carbon fibre ~AAconcerns scramjet combustor composite wing skin laminates p io4 A8862670 [AIAA PAPER 88-44621 p 807 A88-53758 [AIAA PAPER 88-32591 p 816 A88-53151 Impact and damage tolerance properties of CFRP CH-46 HELICOPTER Evaporation of fuel droplets in turbulent combustor sandwich panels - An experimental parameter study for Cool gas generator systems flow the Fokker 100 CA-EP flap p 804 A88-52671 [AIAA PAPER 88-33631 p 805 A88-53161 [ASME PAPER 88-GT-1071 p 839 A88-54226 Certification of primary composite aircraft structures CHANNEL FLOW COMBUSTION CHAMBERS p 805 A88-52672 Heat transfer. pressure drop, and mass flow rate in pin Flame stabilization in supersonic combustion Advanced Composite Airframe Program (ACAP) - An fin channels with long and short trailing edge ejection p 837 A88-53164 update and final assessment of weight saving potential holes Assessment, development. and application of [SAWE PAPER 17701 p 808 A88-53781 [ASME PAPER 88-GT-42) p 847 A88-54181 combustor aerothermal models p 817 A88-54140 Critical joints in large composite primary aircraft The use of Bezier polynomial patches to define the Structural analysis applications--- for aircraft gas turbine structures. Volume 2: Technology demonstration test geometrical shape of the flow channels of compressors combustors p 817 A88-54143 report [ASME PAPER 88-GT-601 p 788 A88-54192 An experimental data base for the computational fluid [NASA-CR-I725871 p 81 1 N88-28915 Unsteady water channel dynamics of combustors Critical joints in large composite primary aircraft [AD-A194231] p 797 N88-28884 [ASME PAPER 88-GT-251 p 846 A88-54169 structures. Volume 3: Ancillary test results CHEMICAL COMPOSITION A detailed characterizationof the velocity and thermal [NASA-CR-172588] p 81 1 N88-28916 The characterizatin of cornbustion by fuel cornposition: fields in a model can combustor with wall jet injection Critical joints in large composite primary aircraft Measurements in a small conventional combustor [ASME PAPER 88-GT-261 p 81 8 A88-54170 structures. Volume 1: Technical summary p 842 N88-29920 Flow in liner holes for counter-current combustion [NASA-CR-39141 p 840 N88-28983 The performanceof a surrogate blend in simulatingJP-4 systems Evaluation of bond testing equipment for inspection of in a spray-fueledcombustor p 843 N88-29926 [ASME PAPER 88-GT-1581 p 839 A8844257 Army advanced composite airframe structures CIRCULATION CONTROL ROTORS Notes on the occurrence and determination of carbon [ AD-A1957951 p 841 N88-29885 Analysis of a fixed-pitch X-wing rotor employing lower within gas turbine combustors COMPRESSIBILITY surface blowing [ASME PAPER 88-GT-1641 p 839 A88-54262 Compression pylon [AD-A187379] p 800 N88-29779 The feasibility. from an installational viewpoint. of [ NASA-CASE-LAR-I3777-1 1 p 81 2 NEB-29789 CIVIL AVIATION gas-turbine pressure-gaincombustors COMPRESSIBLE FLOW Some key considerations for high-speed civil (ASME PAPEH 88-GT-I81] p 849 A88-54272 A new singular integral approach for a vertical array of transports A methanolloxygen burning combustor for an aircraft airfoils [AIAA PAPER 88.44661 p 783 A88-53760 auxiliary emergency power unit [ASME PAPER 88-GT-2181 p 793 A88-54303 Preliminary design of two transpacific high speed civil [ASME PAPER 88-GT-2361 p 820 A8864317 COMPRESSION LOADS transports Numerical correlation of gas turbine combustor ignition Critical joints in large composite primary aircraft [AIAA PAPER 88-448581 p 807 A88-53765 [ASME PAPER 88-GT-2421 p 820 A88-54321 structures. Volume 3: Ancillary test results Planform effects on high speed civil transport design Laser - A gas turbine combustor manufacturingtool [ NASA-CR-1725881 p 81 1 N88-28916 [AIAA PAPER 88.44871 p 807 A88-53767 [ASME PAPER 88-GT-2671 p 851 A88-54342 COMPRESSOR BLADES Weight growth in airline service Combustion and fuels in gas turbine engines Prediction of compressor cascade performance using [SAWE PAPER 17961 p 809 A88-53797 [AGARD-CP-422] p 841 N88-29910 a Navier-Stokes technique Principles of the use of fuels and lubricants in civil Numerical models for analyticalpredictions of combustor [ASME PAPER 88-GT-961 p 789 A88-54217 aviation --- Russian book p 838 A88-54001 aerothermal performance characteristics Experimentalinvestigation of the three-dimensionalflow An interim comparison of operational CG records in p 843 N88-29935 in an annular compressor cascade turbulence on small and large civil aircraft COMBUSTION EFFICIENCY [ASME PAPER 88-GT-201I p 792 A88-54288 p 830 N88-29729 Atomization of alternative fuels p 842 N88-29913 Analysis of efficiency sensitivity associated with tip Re-assessmentof gust statistics using CAADRP data Spray performance of a vaporizing fuel inlector clearance in axial flow compressors p 831 N88-29732 p 842 N88-29919 [ASME PAPER 88-GT-2161 p 819 A88-54301 An analysis of time and space requirements for aircraft The characterizatin of combustion by fuel composition: Flow measurements in rotating stall in a gas turbine turnrounds Measurements in a small conventional combustor engine compressor [TT-87051 p 802 N88-29783 p 842 N88-29920 [ASME PAPER 88-GT-2191 p 81 9 A88-54304 CLEARANCES High performance turbofan afterburner systems The effect of the Reynolds number on the Analysis of rotor tip clearance loss in axial-flow p 842 N88-29922 three-dimensional flow in a straight compressor cascade turbines p 785 A88-52685 COMBUSTION PRODUCTS [ASME PAPER 88-GT-2691 p 794 A88-54343 Analysis of efficiency sensitivity associated with tip Gas turbine smoke measurement: A smoke generator Experimental investigation of the Performance of a clearance in axial flow compressors for the assessment of current and future techniques supersonic compressor cascade [ASME PAPER 88-GT-2161 p 819 A88-54301 p 843 N88-29930 [ASME PAPER 88-GT-3061 p 795 A88-54375 CLIMBING FLIGHT COMBUSTION STABILITY Hot-wire measurementsof compressor blade wakes in Improvement of head-up display standards. Volume 2: Flame stabilization in supersonic cornbustion a cascade wind tunnel Evaluationof head-updisplays to enhance unusual attitude p 837 A88-53164 [AD-A1947371 p 835 N88-28936 recovery High performance turbofan afterburner systems Empirical flutter prediction method [AD-A1946011 p 814 N88-28921 p 842 N88-29922 [AD-A195699] p 825 N88-29810

A-7 COMPRESSOR EFFICIENCY SUBJECT INDEX

COMPRESSOR EFFICIENCY Application of a hybrid analyticaVnumerical method to BNSheS as high performance gas turbine seals Acquisition of unsteady pressure measurements from the practical computation of supercritical viscous/inviscid [ASME PAPER 88-GT-1821 p 850 A88-54273 a high speed multi-stage compressor transonic flow fields p 795 A88-54907 A unified solution method for the flow calculations along [ASME PAPER 88-GT-1891 p 833 A88-54280 Efficient Euler solver with many applications SI and S2 stream surfaces used for the computer-aided Investigation into the effect of tip clearance on p 798 A88-55078 design of Centrifugal compressors centrifugal compressor performance Numerical solution of the hypersonic viscous shock layer [ASME PAPER 88-GT-2371 p 793 A88-54318 [ASME PAPER 88-GT-1901 p 850 A88-54281 equations with chemical nonequilibnum A workstation for the integrated design and simulation Analysis of efficiency senstvity associated with tip [ IAF PAPER ST-88-06] p 796 A8845313 of flight control systems p 827 A88-54474 clearance in axial flow compressors Boundary layer simulation and control in wind tunnels Structural dynamics of maneuvering aircraft [ASME PAPER 88-GT-2161 p 819 A88-54301 [AGARD-AR-224] p 784 N88-28857 [AD-AI923761 p 810 N88-28908 COMPRESSOR ROTORS Complex configurations p 834 N88-28881 Interactive plotting of NASTRAN aerodynamic models Structure of tip clearance flow in an isolated axial Computational tools for simulation methodologies using NPLOT and DISSPLA compressor rotor p 834 "3.28865 [AD-A1941I51 p 853 N88-29204 [ASME PAPER 88-GT-2511 p 794 A88-54327 Transport-type configurations p 809 N88-28867 COMPUTER ASSISTED INSTRUCTION COMPRESSORS Combat aircraft p 810 N88-28868 Artificial intelligence systems for aircraft training - An New erosion resistant compressor coatings An unsteady helicopter rotor: Fuselage interaction evaluation [ASME PAPER 88-GT-1861 p 839 A8844277 analysis [AIAA PAPER 88.45881 p 857 A88-53637 Theoretical investigation of the interaction between a [ NASA-CR-41781 p 784 N88-28880 COMPUTER GRAPHICS compressor and the components during surge Variable Sweep Transition Flight Experiment Dynamic texture in visual system [ASME PAPER 88-GT-2201 p 851 A88-54305 (VSTFE)-parametric pressure distribution boundary layer [AIAA PAPER 88.45781 p 832 A88-53630 AGARD (Advisory Group for Aerospace Research and stability study and wing glove design task Interactive plotting of NASTRAN aerodynamic models Development) engine disc material cooperative test INASA-CR-39921 p 798 N88-28894 using NPLOT and DISSPLA (supplementaryprogram) Three dimensional grid generation for complex [AD-A194115] p 853 N88-29204 [AD-A193678] p 824 N88-28925 configurations: Recent progress Numerical simulation of nozzle flows E3 IOCcompressor test analyss of high-speedpost-stall [AGARD-AG-3091 p 858 N88-29313 [AD-A195144] p 854 N88-30064 data Experience with three dimensional composite grids COMPUTER PROGRAMS [NASA-CR-1795211 p 824 N88-28929 p 860 N88-29324 Data flow analysis of concurrency in a turbojet engine A mapping of the viscous flow behavior in a controlled Recent advances in transonic computational control program p 823 A88-54622 diiusion compressor cascade using laser Doppler aeroelasticity Hot-wire measurements of compressor blade wakes in velocimetry and preliminary evaluation of codes for the (NASA-TM-100663I p 800 N88-29778 a cascade wind tunnel prediction of stall Numerical simulation of nozzle flows [ AD-AI 947371 p 835 N88-28936 [ AD-AI 944901 p 853 N88-29112 [ AD-AI 951441 p 854 N88-30064 Composite grid generation for aircraft configurationswith COMPUTATIONALFLUID DYNAMICS COMPUTATIONAL GRIDS the EAGLE code p 859 N88-29321 A three dimensional zonal Navier-Stokes code for A prolection-gnd scheme for calculating transonic flow Computer programs for generation of NASTRAN and subsonic through hypersonic propulsion flowfields past a profile p 785 A88-52795 VIBRA-6 aircraft models [AIM PAPER 88-28301 p 785 A88-53106 Quasi-3D solutions for transonic, inviscid flows by [AD-A195467] p 812 N88-29792 Stator/rotor interaction in a transonic turbine adaptive triangulation N-version software demonstration for digital flight [AIM PAPER 88-30931 p 785 A88-53140 [ ASME PAPER 88-GT-831 p 789 A88-54211 controls Navier-Stokes solutions for rotating 3-D duct flows Multigrid acceleration of the flux-split Euler equations [ NASA-CR-I81 4831 p 831 N88-29815 [AIAA PAPER 88.30981 p 844 A8843142 p 796 A88-55077 Computer programs for calculation of sting pitch and CFD predictionof the reactingHow field inside a subscale Grid embedding techniqueusing Cartesian grids for Euler roll angles required to obtain angles of attack and sideslip scramjet combustor solutions p 796 A88-55094 on wind tunnel models [AIAA PAPER 88-32591 p 816 A88-53151 An efficient patched gnd Navier-Stokes solution for [NASA-TM-1006591 p 835 N88-29820 Developments in computational methods for high-lift multiple bodies. phase 1 COMPUTER SYSTEMS DESIGN aerodynamics p 786 A88-53250 [AD-AI941661 p 853 N88-29110 Some benefits of distnbuted computing architecturesfor A comparisonof CFD and full scale VanEze wind tunnel Three dimensional grid generation for complex training simulators p 858 A88-53671 results configurations: Recent progress COMPUTER SYSTEMS PROGRAMS [AIAA PAPER 88-44631 p 807 A88-53759 [AGAR D-AG-309] p 858 N88-29313 N-version software demonstration for digital flight Aerodynamics --- numencai simulation using Lessons learned in the mesh generation for PN/S controls supercomputers p 783 A88-53800 calculations p 859 N88-29314 [NASA-CR-l81463] p 831 N88-29815 An experimental data base for the computational fluid Three-dimensional elliptic grid generation for an F-16 COMPUTER TECHNIQUES dynamics 01 Combustors p 859 N88-29315 Structural analysis applications --- for aircraft gas turbine [ASME PAPER 88-GT-251 p 846 A8844169 Component adaptive gnd generation for aircraft combustors p 81 7 A88-54143 The use of Bezier polynomial patches to define the configurations p 859 N88-29316 COMPUTERIZED SIMULATION geometrical shape of the flow channels of compressors Generation of multiple block grids for arbitrary 3D AIAA. Flight Simulation Technologies Conference. [ASME PAPER 88-GT-601 p 788 A88-54192 geometries p 859 N88-29317 Atlanta, GA. Sept. 7-9, 1988, Technical Papers A radial mixing cornputation method Grid generation on and about a cranked-wing fighter p 832 A88-53626 [ASME PAPER 88-GT-681 p 847 A88-54199 aircraft configuration p 859 N88-29318 Dynamic texture in visual system Developmentof a 3D Navier Stokes solver for application Grid generation for an advanced fighter aircraft [AIAA PAPER 88-45781 p 832 A88-53630 to a11 types of turbomachinery p 859 N88-29319 Multiple frame rate integration [ASME PAPER 88-GT-701 p 788 A88-54201 Algebraic gnd generation for fighter type aircraft [AIM PAPER 88-45791 p 857 A88-53631 Computation of three-dimensional turbulent p 859 N88-29320 Real-time simulation of helicopters using the blade turbamachinery flows using a coupled parabolic-marching Composite grid generationfor aircraft configurationswith element method method the EAGLE code p 859 N88-29321 [AIAA PAPER 88.4582) p 805 A88-53634 [ASME PAPER 88-GT-801 p 788 A88-54208 Analytical surfaces and gnds p 860 N88-29322 Present and future developments 01 the NLR moving Numerical solution to transonic potential equations on Experience with three dimensional composite grids base research flight simulator S2 stream surface in a turbomachine p 860 "3-29324 [AIAA PAPER 88-45841 p 832 A88-53635 [ASME PAPER 88-GT-821 p 789 A88-54210 Grid generation around transport aircraft configurations Design of high performance fans using advanced using a multi-block structured computational domain The Langley Advanced Real-Time Simulation (ARTS) aerodynamic codes p 860 N88-29325 system [ASME PAPER 88-GT-1411 p 791 AM-54244 Generation of surface grids through elliptic partial [AIM PAPER 88-45951 p 832 A88-53842 Numerical analysis of airfoil and cascade flows by the differential equations for aircraft and missile Determination of helicopter simulator time delay and its viscous/inviscid interactive technique configurations effects on air vehicle development [ASME PAPER 88-GT-1601 p 791 A88-54259 [AD-A1956391 p 860 N88-30378 [AIAA PAPER 88-48203 p 833 A88-53659 Calibration of CFD methods for high Mach number COMPUTER AIDED DESIGN Three dimensional flow in radial-inflow turbines aeroengine flowfields ATR propulsion system design and vehicle integration [ASME PAPER 88-GT-1031 p 790 A8844222 [ASME PAPER 88-GT-1991 p 792 A88-54286 --- AirTurboRamjet Numerical simulation of inviscid transonic flow through Computabon of the jet-wake flow structurein a low speed [AIAA PAPER 88-30711 p 816 A88-53136 nozzles with fluctuating back pressure centrifugal impeller The application of artlficial intelligence technology lo [ASME PAPER 88-GT-2871 p 794 A88-54356 [ASME PAPER 88-GT-2171 p 793 A88-54302 aeronautical system design A workstation for the integrated design and simulation A new singular integral approach for a vertical array of [AIAA PAPER 88-44261 p 806 A88-53752 of flight control systems p 827 A8844474 airfoils A quasi-procedural,knowledge-based system for aircraft Multiple-model parameter-adaptive control for in-flight [ASME PAPER 88-GT-2181 p 793 A88-54303 design simulation p 829 A88-54659 [AIM PAPER 88-44281 p 806 A8843753 Helicopter crew seat lailure analysis A Comparison between measurements and turbulence Development of a microcomputer based integrated models in a turbine cascade passage design system for high altitude long endurance aircraft p 801 A88-55290 [ASME PAPER 88-GT-2261 p 793 A8864309 [AIM PAPER 88-44291 p 807 A88-53754 Three-dimensionalelliptic grid generation for an F-16 A unified solution method for the flow calculations along A fast interactive two-dimensional blade-to-bladeprofile p 859 N88-29315 SI and S2 stream surfaces used for the computer-aided design method Feasibilitystudy of a microprocessorcontrolled actuator design of centrifugal compressors [ASME PAPER 88-GT-1001 p 790 A88-54220 test mechanism [ASME PAPER 88-GT-2371 p 793 A88-54318 Optimization design of the over-all dimensions of [AD-AI946541 p 860 N88-29337 Flow computation and blade cascade design in centrifugal compressor stage A fiber optic collective flight control system for turbopump turbines [ASME PAPER 88-GT-1341 p 849 A88-54241 helicopters [ASME PAPER 88-GT-2481 p 820 A88-54326 Design of high performance fans using advanced [ AD-At 954081 p 831 N88-29818 Boundary-layer flows in rotating cavities aerodynamic codes Minimum-complexityhelicopter simulation math model [ ASME PAPER 88-GT-2921 p 852 A8864381 [ASME PAPER 88-GT-1411 p 791 A88-54244 [ NASA-CR-I77476 J p 831 N88-29819 SUBJECT INDEX CYCLIC LOADS

CONCURRENT PROCESSING A workstation for the integrated design and simulation COST ESTIMATES Data flow analysis of concurrency in a turbojet engine of flight control systems p 827 A8844474 Aircraft avionics and missile system installation cost control program p 823 A88-54622 Towards Simultaneous performance - Application of studv. Volume 1: Technical reDort and amendices A CONFERENCES simultaneous stabilization techniques to helicopterengine through E New materials and fatigue resistant aircraft design; control p 822 A8864507 [AD-A1946051 p 814 N88-28923 Proceedings of the Fourteenth ICAF Symposium, Ottawa. Eigenstructure assignment for the control of highly COUNTERFLOW Canada, June 8-12. 1987 p 803 A88-52651 augmented aircraft p 828 A88-54549 Flow in liner holes for counter-current combustion AIAA, Flight Simulation Technologies Conference, H(infinity)-optimaldesign for helicopter control systems Atlanta. GA. Sept. 7-9. 1988. Technical Papers p 828 A88-54598 [ASME PAPER 88-GT-1581 p 839 A88-54257 p 832 A88-53626 Automated design of continuously-adaptivecontrol - The CRACK INITIATION Toward improved durability in advanced aircraft engine 'super-controller' strategy for reconfigurable systems New apparatus for studying fatigue deformation at high hot sections; Proceedings of the Thirty-third ASME p 829 A88-54653 magnifications p 852 A88-55154 International Gas Turbine and Aeroengine Congress and Robust control strategy for take-off performance in a AGARD engine disc cooperative test programme Exposition. Amsterdam. Netherlands, June 5-9. 1988 windshear p 829 A88-54656 [AGARD-R-766] p 824 N88-28926 p 81 7 A88-54137 A minimal realization algorithm for flight control CONFIGURATION INTERACTION CRACK PROPAGATION systems p 829 A88-54661 Fatigue crack growth characterization of jet transport An unsteady helicopter rotor: Fuselage interaction CONTROL THEORY analysts structures p 803 A88-52653 VSRA in-flight simulator - Its evaluation and applications Fatigue crack propagation test programme for the A320 [NASA-CR-41781 p 784 N88-28880 --- Variable Stability and Response Airplane CONSTITUTIVE EQUATIONS wing p 804 A88-52662 [AIAA PAPER 88-46051 p 806 A88-53649 Constitutive modeling for isotropic materials New apparatus for studying fatigue deformation at high Integrated thrust vectoring on the X-29A [NASA-CR-182132] p N88-29811 magnifications p 852 A88-55154 826 [AlAA PAPER 88.44991 p A88-53769 CONTAMINATION 808 Helicopter crew seat failure analysis Contaminationand distortionof steady flow field induced Use of control feedback theory lo understand other p 801 A88-55290 oscillations by discrete frequency disturbances in aircraft gas AGARD engine disc cooperative test programme [ASME PAPER 88-GT-811 p 846 A88-54209 engines [ AGARD-R-7661 p 824 N88-28926 [ AD-AI 954401 p 854 N88-30069 Eigenstructure assignment for the control of highly Stress intensity factors for cracked metallic structures CONTOURS augmented aircraft p 828 A88-54549 under rapid thermal loading Test results at transonic speeds on a contoured Fault detection in multiply-redundant measurement [AD-A1912191 p 840 N88-29004 over-the-wingpropfan model systems via sequential testing p 852 A88-54566 Fatigue crack growth characteristics of ARALL [ NASA-TM-882061 p 811 N88-28918 Optimization and guidance of penetration landing (trademark)-I CONTRAROTATING PROPELLERS trajectories in a windshear p 828 A88-54570 [AD-A196185] p 841 N88-29889 A study of aerodynamic noise from a contra-rotating Helicopter trajectory planning using optimal control Stress intensity factors for cracked metallic structures axial compressor stage p 823 A88-54938 theory p 828 A88-54571 under rapid thermal loading CONTROL CONFIGURED VEHICLES CONTROLLABILITY [AES-8609709F-l] p 843 NEB-29962 Detection. identification and estimation of surface Advances in Flying Qualities Modeling of micromechanisms of fatigue and fracture damagelactuator failure for high performance aircraft [AGARD-LS-I571 p 785 N88-29735 in hybrid materials p 828 A8844650 Advances in flying qualities: Concepts and criteria for [AD-A1956041 p 855 N88-30142 A hyperstable model-followingflight control system used a mission ortented flying qualities specification Automated early fatigue damage sensing system for reconfigurationfollowing aircraft impairment p 812 N88-29739 [AD-AI9571 71 p 855 N88-30143 p 828 A88-54652 The development of acoustic emission for structural A second look at prime flying qualities Automated design of continuously-adaptivecontrol -The MIL integrity monitoring of aircraft requirements p 812 N88-29740 'super-controller'strategy for reconfigurable systems [ AD-A1962641 p 861 N88-30398 p 829 A88-54653 The role of simulation in flying qualities and flight control CRACKING (FRACTURING) Application of supercontroller to fighter aircraft system related development p 835 N88-29742 AGARD (Advisory Group for Aerospace Research and reconfiguration p 829 A88-54654 An analysis of lateral-directionalhandling qualities and Development) engine disc material cooperative test CONTROL SIMULATION Eigenstructure of high performance aircraft (supplementary program) The Langley Advanced Real-Time Simulation (ARTS) [AD-A1948741 p 831 N88-29814 [AD-A193678] p 824 N88-28925 system Minimum-complexity helicopter simulation math model AGARD engine disc cooperative test programme [AIAA PAPER 88.45951 p 832 A88-53642 [ NASA-CR-1774761 p 831 N88-29819 [AGARD-R-766] p 824 N88-28926 Multiple-model parameter-adaptive control for in-flight CONTROLLERS Stress intensity factors for cracked metallic structures simulation p 829 A88-54659 Multivariable turbofan engine control for full flight under rapid thermal loading Pilollvehicle analysis of a twin-lift helicopter envelope operation [ AD-AI 912191 p 840 N88-29004 configurationin hover p 829 A88-55084 [ASME PAPER 88-GT-61 p 818 A88-54153 CRASHES CONTROL STABILITY Application of supercontroller lo fighter aircraft Crash Simulation calculations and component Towards simultaneous performance - Application of reconfiguration p 829 A88-54654 idealization for an airframe. Computer code KRASH 79 simultaneous stabilization techniques lo helicopterengine CONVECTIVE FLOW [ETN-88-92971I p 801 N88-28899 control p A88-54507 822 A radial mixing computation method CRASHWORTHINESS Fault detection in multiply-redundant measurement [ASME PAPER 88-GT-681 p 847 A88-54199 Crash simulation calculations and component systems via sequential testing p 852 A88-54586 idealization for an airframe. Computer code KRASH 79 CONVECTIVE HEAT TRANSFER H(infinity)-optimaldesign for helicopter control [ ETN-88-929711 p 801 N88-28899 Conditions of the induction-plasmatron modeling of the p 828 A88-54598 CREEP ANALYSIS convective nonequilibrium heat transfer of bodies in A hyperstable model-followingflight control system used Dimensioning of turbine blades for fatigue and creep hypersonic flow p 786 A88-53970 for reconfigurationfollowing aircraft impairment p 817 A88-53167 p 828 A8844652 Weibull analysis techniques on a desktop computer CROSS FLOW CONTROL SURFACES [ASME PAPER 88-GT-2851 p 851 A8844354 Tip leakage in a centrifugal impeller Canard certification loads - Progress toward alleviating COOLING SYSTEMS [ASME PAPER 88-GT-2101 p 792 A88-54296 FAA concerns Development of a thermal and structural analysis CRYOGENIC WIND TUNNELS [AIAA PAPER 88.44621 p 807 A88-53758 procedure for cooled radial turbines The application of cryogenics lo high Reynolds number Detection. identification and estimation of surface [ASME PAPER 88-GT-181 p 846 A88-54164 testing in wind tunnels. II - Development and application damagelactuator failure for high performance aircraft COORDINATES of the cryogenic wind tunnel concept p 828 A88-54650 Calculation of complete three-dimensional flow in a p 833 A88-53847 Control surface selection based on advanced modes centrifugal rotor with splitter blades Technology for pressure-instrumented thin airfoil performance [ASME PAPER 88-GT-931 p 789 A88-54216 models [AIM PAPER 88-43561 p 829 A88-55275 CORIOLIS EFFECT [NASA-CR-4173] p 835 N88-28933 Steady and unsteady transonic pressure measurements Dynamics of helicopter rotors p 809 A88-54954 CUES on a clipped delta wing for pitching and control-surface CORROSION PREVENTION Technology of flight simulation p 805 A88-52692 oscillations Corrosion and protection of gas turbine blades --- CUMULATIVE DAMAGE [ NASA-TP-25941 p 798 N88-28895 Russian book p 838 A88-53996 Microscopic inner damage correlated with mechanical CONTROL SYSTEMS DESIGN CORROSION RESISTANCE property degradation due lo simulated fatigue loading in Vehicle Management Systems The logical evolution - New erosion resistant compressor coatings metal matrix composites p 837 A88-52657 of integration [ASME PAPER 88-GT-1861 p 839 A8844277 Deformation and damage of the material of gas turbine [AIAA PAPER 88-31751 p 826 A88-53148 engine blades during thermal cycling in gas flow COST ANALYSIS VISTAIF16 - The next high-performance in-flight p 845 A88-53954 Use of a detail cost model to perform conceptual phase simulator CYCLES cost analysis [AIAA PAPER 88-46101 p 806 A88-53652 Time periodic control of a multi-blade helicopter [SAWE PAPER 17841 p 882 A88-53788 Smart command recognizer (SCR) . For development, [AD-A194435] p 829 N88-28931 test. and implementation of speech commands Cost benefits of nondestructive testing in aircraft CYCLIC LOADS [AIAA PAPER 88-46121 p 858 A88-53654 maintenance p 784 A88-55041 Accounting for service environment in the fatigue lnflight CG-control- System aspects Aircraft avionics and missile system installation cost evaluation of composite airframe structure [SAWE PAPER 17951 p 827 A88-53796 study. Volume 1: Technical report and appendices A p 804 A88-52665 Real time simulators for use in design of integratedflight through E Effect of loading asymmetry on the low-cycle fatigue and propulsion control systems [AD-A194605] p 814 N88-28923 of ZhS6F alloy under cyclic temperature changes [ASME PAPER 88-GT-241 p 818 A88-54168 Aircraft airframe cost estimating relationships: Study p 838 A88-53955 Rule-based mechanisms of learning for intelligent approach and conclusions New apparatus for studying fatigue deformation at high adaptive flight control p 858 A88-54426 [R-3255-AF] p 813 N88-29795 magnifications p 852 A88-55154

A-9 CYLINDRICAL BODIES SUBJECT INDEX

An investigation of constitutive models for predicting DETERIORATION DURABILITY viscoplastic response during cyclic loading Causes for turbomachinery performance deterioration Toward improved durability in advanced aircraft engine [ AD-Al948751 p 856 N88-30163 [ASME PAPER 88-GT-2941 p 821 A8844363 hot sections; Proceedings of the Thirty-third ASME CYLINDRICAL BODIES DIFFUSION FLAMES International Gas Turbine and Aeroengine Congress and AGARD (Advisory Group for Aerospace Research and The blowout of turbulentjet flames in co-flowing streams Exposition. Amsterdam, Netherlands, June 5-9. 1988 Development) engine disc material cooperative test of fuel-air mixtures p 817 A88-54137 (supplementary program) [ASME PAPER 88-GT-1061 p 838 A88-54225 Views on the impact of HOST --- hot section [ AD-AI 936781 p 824 N88-28925 DIGITAL ELECTRONICS technology p 818 A88-54146 The characterizationof high temperature electronics for DYNAMIC CHARACTERISTICS future aircraft engine digital electronic control systems Dynamics of helicopter rotors p 809 A88-54954 D p 823 A88-54621 DYNAMIC MODELS DIGITAL SIMULATION Linear state variable dynamic model and estimator DAMAGE design for Allison T406 gas turbine engine Automated early fatigue damage sensing system Modelling of aircraft program motion with application to circular loop simulation p 826 A88-53251 [ASME PAPER 88-GT-2391 p 820 A88-54319 [ AD-AI 957171 p 855 N88-30143 DYNAMIC RESPONSE Crash simulation calculations and component An investigation of constitutive models for predicting Aerodynamically forced response of an airfoil including idealization for an airframe. Computer code KRASH 79 viscoplastic response during cyclic loading profile and incidence effects p 795 A88-54941 [ETN-88-92971 p 801 N88-28899 [ AD-AI948751 p 856 N88-30163 I Aerodynamically forced response of structurally DAMAGE ASSESSMENT A digital simulation techniquefor the Dryden atmospheric mistuned bladed disks in subsonic flow Damage tolerance in pressurized fuselages model p 795 A8844943 p 803 A88-52652 [ NASA-TT-203421 p 857 N88-30266 Prediction of turbulence generated random vibrational Fatigue crack growth characterization of let transport DIGITAL SYSTEMS response of turbomachinery blading p 796 A8844946 structures p 803 A88-52653 Microprocessor functional-adaptive processing of Structural dynamics of maneuvering aircraft Damage tolerance aspects of an expenmental Arall F-27 signals of radio-navigation systems in an onboard [AD-A192376] p 81 0 N88-28908 lower wing skin panel p 804 A88-52668 subsystem p 802 A88-52952 The Flight of Flexible Aircraft in Turbulence: Certification of primary composite aircraft structures N-version software demonstration for digital flight State-of-the-Art in the Description and Modelling of p 805 A88-52672 controls Atmospheric Turbulence DATA ACQUISITION [ NASA-CR-181483I p 831 N88-29815 [AGARD-R-7341 p 785 N88-29725 Acquisition of unsteady pressure measurements from DIGITAL TECHNIQUES Status review of atmosphere turbulence and aircraft a high speed multi-stage compressor Avionics system design for high energy fields: A guide response p 830 N88-29726 [ASME PAPER 88-GT-1891 p 833 A88-54280 for the designer and airworthiness specialist Aircraft dynamics. Aerodynamic aspects and wind tunnel China’s acquisition and use of foreign aviation [NASA-CR-1815901 p 814 N88-28919 techniques p 798 N88-29731 technology DIRECTIONAL STABILITY DYNAMIC STRUCTURAL ANALYSIS [ AD-A1948271 p 862 N88-30471 Calculation of aerodynamic characteristics of airplane Aerodynamically forced response of an airfoil including DATAEASEMANAGEMENTSYSTEMS configurations at high angles of attack profile and incidence effects p 795 A88-54941 Avionic expert systems p 814 N88-29365 [ NASA-CR-41821 p 797 N88-28891 Structural dynamics of maneuvering aircraft DATA EASES DISKS (SHAPES) [AD-AI923761 p 810 N88-28908 Structural technology transition to new aircraft AGARD (Advisory Group for Aerospace Research and DYNAMIC TESTS p 805 A88-52673 Development) engine disc material cooperative test Instrumentationand techniques for structural dynamics An experimental data base for the computational fluid (supplementary program) and acoustics measurements dynamics of combustors [ AD-AI 93678 1 p 824 N88-28925 [AIAA PAPER 88.46671 p 845 A88-53829 [ASME PAPER 88-GT-251 p 846 A88-54169 DISPLAY DEVICES An emissions database for U.S. Navy and Air Force Simulator evaluation of takeoff performance monitoring Aircraft engines system displays E [ASME PAPER 88-GT-1291 p 818 A88-54239 [AIAA PAPER 88-4611 I p 833 A8843653 Avionic expert systems p 814 N88-29365 Use of color CRTs (Cathode Ray Tubes) in aircraft EDDYCURRENTS DATA FLOW ANALYSIS cockpit: A literature search, revision B The non-destructivetesting of welds in continuous fibre Data flow analysis of concurrency in a turbojet engine [AD-A195062I p 815 N88-29797 reinforced thermoplastics p 852 A88-55456 control program p 823 A88-54622 DISTILLATION EDDY VISCOSITY DATA INTEGRATION The performance of a surrogate blend in simulating the On the prediction of unsteady forces on gas-turbine Multiple frame rate integration sooting behavior of a practical. distillate JP-4 blades. II - Viscous-wake-interaction and axial-gap [AIAA PAPER 88-45791 p 857 A88-53631 [ASME PAPER 88-GT-1941 p 840 A88-54283 effects [ASME PAPER 88-GT-901 DEFENSE PROGRAM DISTORTION p 789 A88-54214 YA-7F .A twenty year economic life extension at costs Aerodynamics of seeing on large transport aircraft EFFICIENCY we can afford [NASA-CR-I83122] p 801 N88-28896 An efficient patched grid Navier-Stokes solution for [AlAA PAPER 88-44601 p 783 A8843757 Contaminationand distortion of steady flow field induced multiple bodies. phase 1 DEFLECTION by discrete frequency disturbances in aircraft gas [AD-A194166] p 853 N88-29110 Optical measurement of unducted fan blade engines EIGENVALUES Eigenstructure assignment for the control of highly deflections [ AD-AI 95440 1 p 854 N88-30069 [NASA-TM-l009661 p 853 N88-29142 augmented aircraft DOCUMENTS p 828 A8844549 DEFORMATION Development of graded reference radiographs for A minimal realization algorithm for fhght control New apparatus for studying fatigue deformation at high aluminum welds, phase 1 systems p 829 A88-54661 magnifications p 852 A88-55154 [ AD-AI 95594 I p 855 NEB-30140 EJECTION SEATS DEICERS DOPPLERRADAR A new method of modeling underexpanded exhaust JUH-1H redesignedpneumatic boot deicingsystem flight The NAE atmospheric research aircraft plumes for wind tunnel aerodynamic testing test evaluation p 815 N88-29730 [ASME PAPER 88-GT-2881 p 834 A88-54357 ELASTODYNAMICS [AD-A1949181 p 802 N88-29785 DRAG REDUCTION Dynamics of helicopter rotors p 809 A88-54954 DEICING A preliminary investigation of drag reduction and ELECTRIC GENERATORS Composites break the ice --- fiber reinforced materials mechanism for a blunt body of revolution with slanted High temperature. lightweight, switched reluctance for deicing of aircraft surfaces and engines base p 840 A8844857 [ NASA-TT-203491 p 799 “3.29753 motors and generators for future aircraft engine Compression pylon applications p 823 A8844623 DELTA WINGS ELECTRIC MOTORS Delta wing configurations p 796 N88-28860 [NASA-CASE-LAR-13777-1] p 812 N88-29789 Development and design of windtunnel and test facility High temperature. lightweight, switched reluctance Steady and unsteadytransonic pressure measurements motors and generators for future aircraft engine on a clipped delta wing for pitching and control-surface for RPV (Remote Piloted Vehicle) enhancement devices [AD-A194842] p 836 N88-29822 applications p 823 A88-54623 oscillations ELECTRICAL INSULATION [ NASA-TP-25941 p 798 N88-28895 DROP SIZE Influence of operating conditions on the atomizationand New version antistatic coating tester DEPOSITS distribution of fuel by air blast atomizers p 844 A88-53166 Influence of deposit on the flow in a turbine cascade p 842 N88-29918 ELECTRICAL MEASUREMENT [ ASME PAPER 88-GT-2071 p 792 A88-54293 DUCTED FLOW Development of a MHz RF leak detector technique for DESIGN ANALYSIS Navier-Stokes solutions for rotating 3-0 duct flows aircraft hardness surveillance p 81 3 A88-54725 Acontributiontothequantitativeanalysisof the influence [AIAA PAPER 88-30981 p 844 A88-53142 ELECTRICAL RESISTIVITY of design parameters on the optimal design of passenger Weibull analysis techniques on a desktop computer New version antistatic coating tester aircraft [ASME PAPER 88-GT-2851 p 851 A88-54354 p 844 A8863166 [ ETN-88-929791 p 810 N88-28912 DUCTILITY The 1983 direct strike lightning data, part 1 Euler analysis of a swirl recovery vane design for use Modeling of micromechanisms of fatigue and fracture [ NASA-TM-86426-PT-I ] p 856 N88-29259 with an advanced single-rotation propfan in hybrid materials The 1983 direct strike lightning data, part 2 [ NASA-TM-101357I p 800 “3.29771 [AD-A195604] p 855 N88-30142 [ NASA-TM-86426-PT-21 p 856 N88-29260 DESIGN TO COST DUCTS The 1983 direct strike lightning data. part 3 Use of a detail cost model lo perform conceptual phase Optical measurement of unducted fan blade [ NASA-TM-86426-PT-31 p 856 N88-29261 cost analysis deflections ELECTROMAGNETIC FIELDS ISAWE PAPER 17841 p 862 A88-53788 [ NASA-TM-100966I p 853 N88-29142 The 1983 direct strike lightning data. part 1 DETECTION DUMP COMBUSTORS [ NASA-TM-86426-PT-I ] p 856 N88-29259 Automated early fatigue damage sensing system Combuslion-generated turbulence in practical The 1983 direct strike lightning data, part 2 [ AD-A195717] p 855 N88-30143 combustors p 815 A8842676 [ NASA-TM-86426-PT-2I p 856 N88-29260 A-10 . SUBJECT INDEX EULER EQUATIONS OF MOTION

The 1983 direct strike lightning data, part 3 A useful similarity principle for jet engine exhaust system ENGINE MONITORING INSTRUMENTS [ NASA-TM-86426-PT-31 p 856 N88-29261 performance Navy application of a standard fatigue and engine ELECTROMAGNETIC MEASUREMENT [AIAA PAPER 88-30011 p 81 6 A88-53122 monitoring system The 1983 direct strike lightning data. part 1 A preliminary design study of supersonic through-flow [AIAA PAPER 88-33151 p 813 A88-53156 [ NASA-TM-86426-PT-I ] p 856 N88-29259 fan inlets A UK perspective on Engine Health Monitoring (EHM) The 1983 direct strike lightning data. part 2 [AIAA PAPER 88-30751 p 816 A88-53137 systems for future technology military engines [ NASA-TM-86426-PT-2I p 856 N88-29260 The RTM322 engine in the S-70C helicopter [ASME PAPER 88-GT-1481 p 819 A8844249 AlAA PAPER 88-4576 p 817 A88-53774 The 1983 direct strike lightning data. pari 3 I I Rolling element bearing monitoring and diagnostics Review and assessment of the database and numerical INASA-TM-86426-PT-3 1 p 856 N88-29261 techniques modeling for turbine heat transfer p 817 A88-54141 [ASME PAPER 88-GT-2121 p 850 A88-54298 ELECTROMAGNETIC PULSES Aerodynamic and heat transfer measurements on a EMPTAC (Electromagnetic Pulse Test Aircraft) user's Transient performance trending for a turbofan engine transonic nozzle guide vane [ASME PAPER 88-GT-2221 p 819 A88-54306 guide [ASME PAPER 88-GT-IO] p 786 A88-54157 [ AD-AI 95072 p 854 N88-30006 Helicopter health monitoring from engine to rotor I A fast interactive two-dimensionalblade-to-blade profile [ASME PAPER 88-GT-2271 p 809 A88-54310 ELECTROMAGNETIC SHIELDING design method Development of a MHz RF leak detector technique for [ASME PAPER 88-GT-1001 p 790 A8864220 Precision error in a turbofan engine monitoring system aircraft hardness Surveillance p 813 A88-54725 Further aspects of the UK engine technology [ASME PAPER 88-GT-2291 p 819 ~8a-54312 ELECTRONIC CONTROL demonstrator programme Recent advances in engine health management Real time simulatorsfor use in design of integrated flight [ASME PAPER 88-GT-1041 p 848 A88-54223 [ASME PAPER 88-GT-2571 p 820 A88-54333 and propulsion control systems Optimization design of the over-all dimensions of Fiber optics for aircraft engine controls [ASME PAPER 88-GT-241 p 81 8 A88-54168 centrifugal compressor stage p 822 A88-54619 Very high speed integrated circuitslgallium arsenide [ASME PAPER 88-GT-1341 p 849 A88-54241 Development and installation of an instrumentation electronics for aircraft engine controls Design of high performance fans using advanced package for GE F404 investigative testing p 823 A88-54620 aerodynamic codes [AD-AI 962651 p 855 N88-30107 The characterizationof high temperature electronics for [ASME PAPER 88-GT-141I p 791 A8844244 ENGINE PARTS future aircraft engine digital electronic control systems Second sourcing of a jet engine Meeting the high temperature challenge - The p 823 A88-54621 [ASME PAPER 88-GT-1451 p 784 A88-54246 nonmetallic aero engine p 838 A88-53838 ELECTRONIC EQUIPMENT The feasibility, from an installational viewpoint. of Surface engineering for high temperature Avionics system design for high energy fields: A guide gas-turbine pressure-gaincombustors environments p 845 A88-53840 for the designer and airworthiness specialist [ASME PAPER 88-GT-1811 p 849 A88-54272 Design and test of non-rotating ceramic gas turbine [NASA-CR-t81590] p 814 N88-28919 Thermomechanical advances for small gas turbine components ELECTRONIC EQUIPMENT TESTS engines - Present capabilities and future direction in gas [ASME PAPER 88-GT-1461 p 819 A88-54247 Real-time simulation - A tool for development and generator designs The measurementof stress and vibration data in turbine verification [ASME PAPER 88-GT-2131 p 850 A88-54299 blades and aeroengine Components [AIAA PAPER 88-46181 p 833 A88-53657 Real time neutronradiography applicationsin gas turbine [ASME PAPER 88-GT-1491 p 849 A88-54250 V2500 engine collaboration ELLIPTIC DIFFERENTIAL EQUATIONS and internal combustion engine technology [PNR90423] p 825 N88-29803 Compositegrid generationfor aircraft configurationswith [ASME PAPER 88-GT-2141 p 850 A88-54300 Determination of the hydroperoxide potential of let the EAGLE code p 859 N88-29321 Comparisonof ceramic vs. advanced superalloy options for a small gas turbine technology demonstrator fuels Generation of surface grids through elliptic partial [ADA195975 p 844 N88-29991 [ASME PAPER 88-GT-2281 p 851 A88-54311 1 differential equations for aircraft and missile An investigation of constitutive models for predicting configurations A methanolloxygen burning Combustor for an aircraft viscoplastic response during cyclic loading [AD-AI 956391 p 860 N88-30378 auxiliary emergency power unit [AD-A1948751 p 856 N88-30163 EMERGENCIES [ASME PAPER 88-GT-2361 p 820 A88-54317 ENGINE TESTING LABORATORIES Cool gas generator systems Linear state variable dynamic model and estimator A transient flow facility for the study of the [AIAA PAPER 88-33631 p 805 A88-53161 design for Allison T406 gas turbine engine thermofluid-dynamicsof a full stage turbine under engine ENERGY CONSUMPTION [ASME PAPER 88-GT-2391 p 820 A88-54319 representative conditions Energy maneuverability and engine performance A comparison of engine design life optimization results [ASME PAPER 88-GT-1441 p 849 A88-54245 requirements using deterministic and probabilistic life prediction ENGINE TESTS [ASME PAPER 88-GT-3031 p 822 A88-54372 techniques UDF engineIMD80 flight test program ENERGY DISSIPATION [ASME PAPER 88-GT-2591 p 820 A88-54335 [AIAA PAPER 88-28051 p 815 A88-53104 Deformation and damage of the material of gas turbine Structural design and its improvements through the Advanced high temperature instrumentation for hot engine blades during thermal cycling in gas flow development of the XF3-30 engine section research applications p 846 A88-54139 p 845 A88-53954 [ASME PAPER 88-GT-261I p 821 A8844337 Transient performance trending for a turbofan engine ENGINE AIRFRAME INTEGRATION A new source of lightweight. compact multifuel power [ASME PAPER 88-GT-2221 p 819 A88-54306 Propulsion system integration for Mach 4 to 6 vehicles for vehicular, light aircraft and auxiliary applications - The AGTI 01 IATTAP ceramic technology development [AIAA PAPER 88-3239Al p 805 A88-53149 joint Deere Score engines [ASME PAPER 88-GT-2431 p 820 A88-54322 The RTM322 engine in the S-70C helicopter [ASME PAPER 88-GT-2711 p 851 A88-54345 Stratified Charge Rotary Engines for aircraft [AIAA PAPER 88-4576) p 817 A86-53774 Development of the T406-AD-400oil scavenge system [ASME PAPER 88-GT-3111 p 822 A88-54379 FtOO-PW-229- Higher thrust in same frame size for the V-22 aircraft Fiber optics based jet engine augmenter viewing [ASME PAPER 88-GT-3121 p 822 A88-54380 [ASME PAPER 88-GT-2971 p 821 A88-54366 system [ASME PAPER 88-GT-3201 p 852 A88-54385 ENGINE CONTROL XG40 - Advanced combat enaine technoloav _. Evaluation of Dotential enaine ConceDts for a hiah A UK perspective on Engine Health Monitoring (EHM) demonstrator programme systems for future technology military engines altitude long endurance vehicie lASME PAPER 88-GT-3001 D 821 A8844369 [ASME PAPER 88-GT-1481 p 819 A8844249 [ASME PAPER 88-GT-3211 p 822 A88-54386 Desian asDects of recent develODmentS in Rolls-Rovce Precision error in a turbofan engine monitoring system Fuel property effects on the US Navy's TF30 engine RE21 17524 powerplants [ASME PAPER 88-GT-2291 p 819 A88-54312 D 826 N88-29911 Towards simultaneous performance - Application of [ASME PAPER 88-GT-3011 p 821 A88-54370 Fuel effects on flame radiation and hot-section simultaneous stabilizationtechniques to helicopter engine Develop ng lhe Rolls Royce Tay durability p 843 N88-29925 control p 822 A8844507 I ASME PAPER 88-GT-3021 p 821 A88 54371 ENGINES Fiber optics for aircraft engine controls Energy maneuverabAty and engine performance Empirical flutter prediction method p 822 A88-54619 requirements [ AD-Al956991 p 825 N88-29810 Very high speed integrated circuitslgallium arsenide IASME PAPER 88 GT 303 I p 822 A88-54372 EPOXY RESINS electronics for aircraft engine controls Ft00-PW-229 Higher thrust in same frame size Aspects of the fatigue behaviour of typical adhesively p 823 A88-54620 I ASME PAPER 88-GT 31 2 I p 822 A88-54380 bonded aircraft structures p 804 A88-52659 The characterizationof high temperature electronics for '42500 engone collaboration EROSION future aircraft engine digital electronic control systems I PNR90423 I p 825 NE8 29803 New erosion resistant compressor coatings p 823 A88-54621 Developing the Rolls-Royce Tay [ASME PAPER 88-GT-1861 p 839 A88-54277 High temperature, lightweight. switched reluctance I PNR90447 I p 825 N88-29809 Turbomachinery alloys affected by solid particles [ASME PAPER 88-GT-2951 p 840 A88-54364 motors and generators for future aircraft engine Combustson and bels in gas tdrbine engines applications p 823 A88-54623 IAGARD-CP-4221 p 841 N88 29910 ERROR ANALYSIS Potential application of composite materials to future Precision error in a turbofan engine monitoring system gas turbine engines p 823 A88-54624 ENGINE FAILURE [ASME PAPER 88-GT-2291 p 819 A88-54312 Fault diagnos s of gas turb8neengines from transient Scheduling turbofan engine control set points by Fine resolution errors in secondary surveillance radar data semi-infinite optimization p 823 A88-54658 altitude reporting ASME PAPER 88 GT 209 p 819 A88-54295 ENGINE DESIGN I I IRSRE-870191 D 802 N88-28906 Viability rating by fuel indexing method ENGINE INLETS ESTIMATING p 81 5 A88-52698 Propblsion system integration for Mach 4 to 6 vehicles Two biased estimation techniques in linear regression Advanced technology engine supportability-Preliminary I AlAA PAPER 88-3239AI p 805 A8863149 Application to aircraft designer's challenge Navy V/STOL Engine experience in Attitbde Test [ NASA-TM-1006491 p 860 N88-29489 [AIAA PAPER 88.27961 p 81 5 A88-53102 Facihty EULER EQUATIONS OF MOTION Direct lift engine for advanced V/STOL transport I ASME PAPER 88-GT-317I p 834 A8864384 Numerical integrationof the 3D unsteady Euler equations [AIAA PAPER 88-289OAl p 816 A88-53111 Experimentaland analytical evaluation of tne effects 01 for flutter analysis of axial flow compressors Towardsthe optimum ducted UHBR engine --- Ultra High simulated engme inlets on the blade vibratory slresses [ASME PAPER 88-GT-2551 p 794 A88-54331 Bypass Ratio of the SR-3 model propfan Multigrid acceleration of the flux-split Euler equations [AIAA PAPER 88.29541 p 816 A88-53119 [NASA CR-1749591 p 824 N88-28927 p 796 A88 55077

A-1 1 EUROPEAN AIRBUS SUBJECT INDEX

Efficient Euler solver with many applications Fault detection in multiply-redundant measurement FEASIBILITY ANALYSIS u 796 A88-55078 systems via Sequential testing p 852 A88-54566 Feasibility study of a microprocessor controlled actuator Grid embeddingtechnique using Cartesian grids for Euler Sewice failure of a 7049 T73 aluminum aircraft forging test mechanism solutions p 796 A88-55094 p 840 A88-55286 [AD-A1946541 p 860 N88-29337 Generation of multiple block grids for arbitrary 30 A profile of US Air Force aircraft mishap investigation JUH-1H redesigned pneumatic boot deicing system flight geometries p 859 N88 29317 p 801 A88-55288 test evaluation Mesh generation for industrial application of Euler and Helicopter crew seat failure analysis [AD-A194918] p 802 N88-29785 Navier Stokes solvers p 860 N88-29323 p 801 A88-55290 FEEDBACKCONTROL Euler analysis of a swirl recovery vane design for use Multivariable turbofan engine control for full fiight Intelligent fault diagnosis and failure management of with an advanced single-rotation propfan envelope operation flight control actuation systems INASA-TM-1013571 p 800 N88-29771 [ASME PAPER 88-GT-61 p 81 A88-54153 [ NASA-CR-I77481 1 p 812 N88-29790 8 EUROPEAN AIRBUS Use of control feedback theory to understand other Industrial production of CFRP-components in Airbus Failure analysis for gas turbines oscillations construction [NLR-MP-87037-U] p 825 N88-29808 [ASME PAPER 88-GT-811 p 848 A88-54209 [SAWE PAPER 17941 p 845 A88-53795 FAN BLADES Trajectory optimization and guidance law development lnflight CG-control- System aspects Optical measurement of unducted fan blade for national aerospace plane applications [SAWE PAPER 17951 p 827 A88-53796 deflections p 837 A88-54567 Variable wing camber control systems lor the future [NASA-TM-100966] p 853 N88-29142 H(infinity1-optimaldesign for helicopter control Airbus program FAR FIELDS p 828 A88-54598 [ MBB-UT-104/88] p 830 N88-28932 Development and demonstration of an on-board mission New apparatus for studying fatigue deformationat high EVACUATING (TRANSPORTATION) planner for helicopters magnifications p 852 A88-55154 Smoke hoods Net safety benefit analysls -- aircraft [NASA-CR-I 774821 p 831 N88-29817 Time periodic control of a multi-blade helicopter ac c i d e n 1 s FASTENERS [ AD-A 194435 ] p 829 N88-28931 [CAA-PAPER-87017] p 801 N88-28898 Standard fatigue specimens for fastener evaluation --- An analysis of lateral-directionalhandling qualities and EVAPORATION aircraft components Eigenstructure of high performance aircraft Evaporation of fuel droplets in turbulent combustor [FFA-TN-1987.681 p 856 N88-30157 [AD-A1948741 p 831 N88-29814 flow FATIGUE (MATERIALS) FIBER COMPOSITES [ASME PAPER 88-GT 1071 p 839 A88-54226 New materials and fatigue resistant aircraft design; Accounting for service environment in the fatigue EXHAUST FLOW SIMULATION Proceedings of the Fourteenth ICAF Symposium. Ottawa, evaluation of composite airframe structure A new method of modeling underexpanded exhaust Canada, June 8-12, 1987 p 803 A88-52651 p 804 A88-52665 plumes for wind tunnel aerodynamic testing Fatigue crack growth characteristics of ARALL Damage tolerance of impact damaged carbon fibre [ASME PAPER 88-GT-2881 834 A88 54357 p (trademark)-I composite wing skin laminates p 804 A88-52670 EXHAUST GASES [AD-A196185] p 841 "3.29889 CIC Composite materials for aircraft brakes An emissions database for S Navy and Air Force p A88-53542 U Modeling of micromechanisms of fatigue and fracture 837 Aircrafl engines Whisker orientation measurements in injection molded in hybrid materials [ASME PAPER 88-GT 1291 p 818 A88-54239 Si3N4-SiC composites [AD-A195604] p 855 N88-30142 EXHAUST NOZZLES [ASME PAPER 88-GT-1931 p 839 A88-54282 A useful similarity principle for jet engine exhaust system Automated early fatigue damage sensing system Dynamics of helicopter rotors p 809 A88-54954 performance [AD-At 957171 p 855 N88-30143 FIBER OPTICS [AIAA PAPER 88 3001 1 p 816 A88-53122 An investigation of constitutive models for predicting Fibre optic flow sensors based on the 2 focus Navy V/STOL Engine experience in Altitude Test viscoplastic response during cyclic loading principle p 844 A8842733 Facility [AD-A194875] p 856 N88-30163 Aerodynamics --- numerical simulation using [ASME PAPER 88-GT-3171 p 834 A88-54384 The development of acoustic emission for structural supercomputers p 783 A88-53800 Numerical simulation of nozzle flows integrity monitonng of aircraft Fiber optics based jet engine augmenter viewing [ AD-At 951441 p 854 N88-30064 [AD-A196264] p 861 N88-30398 system EXHAUSTSYSTEMS FATIGUE LIFE [ASME PAPER 88-GT-3201 p 852 A88-54385 Fiber metal acoustic materials for gas turbine exhaust Damage tolerance in pressunzed fuselages Fiber optics for aircraft engine controls environments p 803 A88-52652 p 822 A88-54619 [ASME PAPER 88-GT-1751 p 839 A88-54269 Microscopic inner damage correlated with mechanical A fiber optic collective flight control system for EXPERT SYSTEMS properly degradation due to simulated fatigue loading in helicopters A quasi-procedural.knowledge-based system for aircraft metal matnx composites p 837 A88-52657 [ AD-AI954061 p 831 NEB-29818 design Dimensioning of turbine blades for fatigue and creep FIBER ORIENTATION [AIAA PAPER 88-44281 p 806 A88-53753 p 817 A88-53167 Whisker orientation measurements in injection molded A knowledge based system of supermaneuverselection New apparatus for studying fatigue deformation at high Si3N4-SiC composites for pilot aiding magnifications p 852 A88-55154 [ASME PAPER 88-GT-1931 p 839 A88-54282 [AlAA PAPER 88.44421 p 827 A88-53755 AGARD (Advisory Group for Aerospace Research and FIBER STRENGTH Application of AI methods to aircraft guidance and Development] engine disc material cooperative test Composite monolayer fabrication by an arc-spray control p 827 A88-54424 (supplementary program) process p 845 A88-53581 Avionic expert systems p 81 4 N88-29365 [AD-A193678] p 824 N88-28925 FIGHTER AIRCRAFT Threat expert system technology advisor Spray automated balancing of rotors: Methods and Vehicle Management Systems - The logical evolution [NASA-CR-1774791 p 831 N88 29816 materials of integration EXTREMUM VALUES [ NASA-CR-I821 51 ] p 836 N88-29825 [AIAA PAPER 88.31751 p 826 A88-53148 Prediction of the extreme values of the phase FATIGUE TESTS Flight testing of fighters during the World War II era coordinates of stochastic systems p 857 A88-52823 Accounting for service environment in the fatigue [AIAA PAPER 88.45121 p 862 A88-53773 evaluation of composite airframe structure Ultimate factor for structural design of modern fighters p 804 A88-52665 [SAWE PAPER 17751 p 808 A88-53784 F Enstaft - A standard test sequence for composite Second sourcing of a jet engine components combining load and environment [ASME PAPER 88-GT-1451 p 784 A88-54246 F-106 AIRCRAFT p 804 A88-52666 Precision error in a turbofan engine monitoring system Investigations into the triggered lightning response of Damage tolerance aspects of an expenmental Arall F-27 [ASME PAPER 88-GT-2291 p 819 A88-54312 the F106B thunderstorm research aircraft lower wing skin panel p 804 A88-52668 Energy maneuverability and engine performance [ NASA-CR-39021 p 856 N88 29258 Damage tolerance of impact damaged carbon fibre requirements F-14 AIRCRAFT composite wing skin laminates p 804 A88-52670 [ASME PAPER 88-GT-3031 p 822 A88-54372 Techniques used in the F-14 variable-sweep transition Impact and damage tolerance properties of CFRP FIOO-PW-229 - Higher thrust in same frame size flight experiment sandwich panels - An experimental parameter study for [ASME PAPER 88-GT-3121 p 822 A88-54380 [ NASA-TM 1004441 p 855 N88-30093 the Fokker 100 CA-EP flap p 804 A88-52671 Automated design of continuously-adaptivecontrol. The F-15 AIRCRAFT Certificationof primary composite aircraft structures 'super-controller' strategy for reconfigurable systems A turbine wheel design story p 805 A88-52672 p 829 A88-54653 LASME PAPER 88-GT-3161 p 822 A88-54383 Navy application of a standard fatigue and engine Application of supercontroller to fighter aircraft F-16 AIRCRAFT monitoring system reconfiguration p 829 A88-54654 VISTAIF16 - The next high-performance in flight [AIM PAPER 88.33153 p 813 A88-53156 Control surface selection based on advanced modes simulator AGARD engine disc cooperative test programme performance [AIAA PAPER 88-46101 p 806 A88 53652 [AGARD-R-766] p 824 N88-28926 [AIAA PAPER 88.43581 p 829 A88-55275 Standard fatigue specimens for fastener evaluation --- Three-dimensional elliptic grid generation for an F-16 A profile of US Air Force aircraft mishap investigation aircraft components p 859 N88 29315 p 801 A88-55288 [ FFA-TN-I987-681 p 856 N88-30157 Combat aircraft p 810 N88-28868 F-I8 AIRCRAFT The development of acoustic emission for structural An airborne system for vortex flow visualization on the integrity monitoring of aircraft Multiple-Purpose Subsonic Naval Aircraft (MPSNA): F-18 high-alpha research vehicle [AD-A1962641 p 861 N88-30398 Multiple Application Propfan Study (MAPS) [AlAA PAPER 88-46711 p 813 A88-53830 FAULT TOLERANCE [ NASA-CR-175104] p 81 1 N88-28917 FAILURE Rule-based mechanisms of learning for intelligent Grid generation on and about a cranked-wing fighter Automated early fatigue damage sensing system adaptive flight control p 858 A88-54426 aircraft configuration p 859 N88-29318 [AD-A195717] p 855 N88-30143 FAULTS Grid generation for an advanced fighter aircraft FAILURE ANALYSIS Fault diagnosis of gas turbine engines from transient p 859 N88-29319 Dimensioningof turbine blades for fatigue and creep data Algebraic grid generation for fighter type aircraft p 817 A88-53167 [ASME PAPER 88-GT-2091 p 81 9 A88-54295 p 859 N88-29320

A-12 SUBJECT INDEX FLIGHT VEHICLES

Aircraft dynamics: Aerodynamic aspects and wind tunnel Improvement of head-up display standards. Volume 2: The effect of perspectivedisplays on altitude and stability techniques p 798 N88-29731 Evaluationof head-up displays to enhance unusual attitude control in simulated rotary wing flight FILM COOLING recovery [AlAA PAPER 88-46341 p 833 A88-53667 Weibull analysis techniques on a desktop computer [AD-A19460t ] p 814 N88-28921 IMMP .A computer simulation of fuel CG versus vehicle [ASME PAPER 88-GT-2851 p 851 A88-54354 Improvement of head-up display standards. Volume 5: attitude Studies of gas turbine heat transfer airfoil surface and Head up display ILS (Instrument LandingSystem) accuracy [SAWE PAPER I8011 p 827 A88-53799 end-wall cooling effects flight tests Complex configurations p 834 N88-28861 [ AD-At 951651 p 825 N88-29805 [AD-At 946023 p 814 N88-28922 Contributions to the modeling of wind shear for danger FINITE ELEMENT METHOD Time periodic control of a multi-blade helicopter studies Design optimizationof gas turbine blades with geometry [ADA1944351 p 829 N88-28931 [ NASA-TT-202931 p 802 N88-28900 and natural frequency constraints Avionic expert systems p 814 N88-29365 The role of simulation in flying qualities and flight control Advances in Flying Qualities [ASME PAPER 88-GT-1051 p 818 A88-54224 system related development p 835 N88-29742 N88-29 735 [AGARD-LS-157) p 785 N88-29735 Minimum-complexityhelicopter simulation math model A new variational finite element computation for Low-speed longitudinal flying qualities of modern [ NASA-CR-1774761 p 831 N88-29819 aerodynamic inverse problem in turbines with long transport aircraft p 812 N88-29738 A digital simulationtechnique for the Dryden atmospheric blades Advances in flying qualities: Concepts and criteria for [ASME PAPER 88-GT-2751 p 794 A88-54347 model a mission oriented flying qualities specification [ NASA-TT-203421 p 857 N88-30266 Analysis of the transmissionof sound into the passenger p 812 N88-29739 FLIGHT SIMULATORS compartmentof a propeller aircraft using the finite element The role of simulationin flying qualities and flight control AIAA, Flight Simulation Technologies Conference, method system related development p 835 "3-29742 Atlanta, GA. Sept. 7-9. 1988. Technical Papers [FFA-TN-t988-15] p 861 N88-29520 Intelligent fault diagnosis and failure management of p 832 A88-53626 FINITE VOLUME METHOD flight control actuation systems Image extrapolation for flight simulator visual systems Quasi-3D solutions for transonic, inviscid flows by [NASA-CR-1774811 p 81 2 N88-29790 [AlAA PAPER 88-45771 p 832 A88-53629 adaptive triangulation A multiprocessor avionics system for an unmanned Present and future developments of the NLR moving [ASME PAPER 88-GT-831 p 789 A88-54211 research vehicle base research flight simulator FINS [ AD-AI 948061 p 815 N88-29800 [AIAA PAPER 88-45841 p 832 A88-53635

The use of fins to reduce the pressure drop in a rotating An analysis of lateral-directional handling qualities and VSRA in-flight simulator I Its evaluation and applications cavity with a radial inflow Eigenstructureof high performance aircraft --- Variable Stability and Response Airplane [ASME PAPER 88-GT-581 p 788 A88-54190 [ AD-A1948741 p 831 N88-29814 [AIAA PAPER 88-46051 p 806 A88-53649 Feasibilitystudy of a microprocessorcontrolled actuator N-version software demonstration for digital flight NASA Shuttle Training Aircraft flight simulation test mechanism controls overview [AD-A194654] p 860 N88-29337 [NASA-CR-181483] p 831 N88-29815 [AlAA PAPER 88-46081 p 806 A88-53650 FIXED WINGS A fiber optic collective flight control system for VISTA/Fl6 - The next high-performance in-flight Analysis of a fixed-pitch X-wing rotor employing lower helicopters simulator surface blowing [ AD-At 95406) p 831 N88-29818 [AIAA PAPER 88-46101 p 806 A88-53652 [AD-A1873791 p 800 N88-29779 Controlled degradation of resolution of high-qualityflight Simulator evaluation of takeoff performance monitoring FLAME PROPAGATION simulator images for training effectiveness evaluation system displays Combustion-generated turbulence in practical [ AD-A1961891 p 836 N88-29823 [AlAA PAPER 88-46111 p 833 A8843653 combustors p 815 A88-52676 FLIGHT ENVELOPES Simulator transport delay measurement using Flame speeds in fuel sprays with hydrogen addition Multivariable turbofan engine control for full flight steady-state techniques [ASME PAPER 88-GT-201 p 838 A88-54166 envelope operation [AIAA PAPER 88.46191 p 833 A88-53658 FLAME STABILITY [ASME PAPER 88-GT-61 p 818 A88-54153 Development, analysis. and flight test of the Lockheed Flame stabilization in supersonic combustion FLIGHT HAZARDS Aeronautical System Company HlTB HUD p 837 A88-53164 Contributions to the modeling of wind shear for danger [AIAA PAPER 88-4511 ] p 813 A88-53772 FLAPS (CONTROL SURFACES) studies Real time simulators for use in design of integrated flight Variable wing camber control systems for the future [ NASA-TT-202931 p 802 N88-28900 and propulsion control systems Airbus program FLIGHT INSTRUMENTS [ASME PAPER 88-GT-241 p 818 A88-54168 [MBB-UT-104/88] p 830 N88-28932 The NAE atmospheric research aircraft A workstation for the integrated design and simulation FLAT PLATES p 815 N88-29730 of flight control systems p 827 A88-54474 Behaviour of the leg of the horseshoe vortex around FLIGHT MANAGEMENT SYSTEMS Multiple-model parameter-adaptive control for in-flight the idealizedblade with zero attack angle by triple hot-wire Vehicle Manaaement Svstems - The loaical evolution simulation p 829 A88-54659 measurements of integration Controlled degradationof resolution of high-quality flight [ASME PAPER 88-GT-1971 p 792 A88-54285 [AIAA PAPER 88-31751 p 826 A88-53148 simulator images for training effectiveness evaluation Studies of gas turbine heat transfer airfoil surface and FLIGHT SAFETY [ AD-A1961891 p 836 N88-29823 end-wall cooling effects Crashworthinessvs. airworthiness FLIGHT TESTS [AD-A195165] p 825 N88-29805 [SAWE PAPER 17881 p 809 A88-53791 Testing of the 578-DX propfan propulsion system FLEXIBLE BODIES Icing Technology Bibliography [AIAA PAPER 88-28041 p 81 5 A88-53103 Current and proposedgust criteria and analysis methods: [SAE AIR 40151 p 801 A88-54400 UDF engine/MDBO flight test program An FAA overview p 830 N88-29718 UK airmisses involving commercial air transport [AIAA PAPER 88.28051 p 815 A88-53104 Measured and predicted responses of the Nord 260 [CAA-1/e81 p 803 N88-28907 VISTAIF16 - The next high-performance in-flight aircraft to the low altitude atmospheric turbulence FLIGHT SIMULATION simulator p 830 N88-29723 Technology of flight simulation p 805 A88-52692 [AIAA PAPER 88-46101 p 806 A88-53652 Development, analysis. and flight test of the Lockheed FLIGHT CHARACTERISTICS Modelling of aircraft program motion with application ATR propulsion system design and vehicle integration to circular loop simulation p 826 A88-53251 Aeronautical System Company HTTB HUD --- AirTurboRamjet [AlAA PAPER 88-451 11 p 81 3 A88-53772 AIAA. Flight Simulation Technologies Conference. [AIAA PAPER 88-30711 p 816 A88-53136 Flight testing of fighters during the World War II era Atlanta, GA, Sept. 7-9, 1988, Technical Papers A profile of US Air Force aircraft mishap investigation [AIM PAPER 88-45121 p 862 A88-53773 p 801 A88-55288 p 832 A88-53626 The RTM322 engine in the S-70C helicopter Advances in Flying Qualities Processingpseudo synthetic aperture radar imagesfrom [AIAA PAPER 88-45761 p 817 A8843774 [AGARD-LS-157] p 785 N88-29735 visual terrain data Overview of Lockheed C-130 High Technology Test Bed Advances in flying qualities: Concepts and criteria for [AIAA PAPER 88.45761 p 802 ~88.53628 Program a mission oriented flying qualities specification Image extrapolation for flight simulator visual systems [ SAWE PAPER 17861 p 808 A88-53789 p 812 N88-29739 [AIAA PAPER 88-45771 p 832 A88-53629 A study of aerodynamic noise from a contra-rotating A second look at MIL prime flying qualities Dynamic texture in visual system axial compressor stage p 823 A88-54938 requirements p 812 N88-29740 [AIAA PAPER 88-45781 p 832 A88-53630 Daedalus - The making of the legend The role of simulationin flying qualities and flight control Multiple frame rate integration p 784 A88-55000 system related development p 835 N88-29742 [AIAA PAPER 88-45791 p 857 A88-53631 TWO biased estimation techniques in linear regression: FLIGHT CONTROL Real-time simulation of helicopters using the blade Application to aircraft lnflight CG-control - System aspects element method [ NASA-TM-1006491 p 860 N88-29489 [SAWE PAPER 17951 p 827 A88-53796 [AIM PAPER 88-45821 p 805 A88-53634 Flight test equipment for the on-board measurement of wind turbulence p 814 N88-29719 Real time simulatorsfor use in design of integrated flight Present and future developments of the NLR moving Angle of attack and sideslip estimation using an inertial and propulsion control systems base research flight simulator reference platform [ASME PAPER 88-GT-241 p 818 A88-54168 [AIAA PAPER 88.45841 p 832 A88-53635 Application of AI methods to aircraft guidance and [AD-A194876] p 799 N88-29769 control p 827 A8844424 The Langley Advanced Real-Time Simulation (ARTS) A multiprocessor avionics system for an unmanned Rule-based mechanisms of learning for intelligent system research vehicle 832 A88-53642 [AIAA PAPER 88-45951 p 832 A88-53642 adaptive flight control p 858 A88-54426 [ AD-A1948061 p 815 N88-29800 A workstation for the integrated design and simulation NASA Shuttle Training Aircraft flight simulation An analysis of lateral-directional handling qualities and of flight control systems p 827 A88-54474 overview Eigenstructureof high performance aircrafi Eigenstructure assignment for the control of highly [AIM PAPER 88-46081 p 806 A8863650 IAD-AI948741 D 831 N88-29814 augmented aircraft p 828 A88-54549 Ground simulator requirements based on in-flight Techniques'used in the F-14 varmbie-sweeptransition A minimal realization algorithm for flight control simulation flight experiment systems p 829 A88-54661 [AIM PAPER 88-46091 p 806 A88-53651 [ NASA-TM-1004441 p 855 N88-30093 Control surface selection based on advanced modes Real-time simulation - A tool for development and FLIGHT VEHICLES performance verification A problem of optimal control with constraints on the [AIAA PAPER 88-43561 p 829 A88-55275 [AIAA PAPER 88-46181 p 833 A88-53657 coordinates of the center of mass D 858 A88-53876

A-13 FLOTATION SUBJECT INDEX

FLOTATION Structure of tip clearance flow in an isolated axial Numerical integration of the 3D unsteady Euler equations Cool gas generator systems compressor rotor for flutter analysis of axial flow compressors [AIM PAPER 88.33631 p 805 A88 53161 [ASME PAPER 88-GT 251 I p 794 A88-54327 [ASME PAPER 88-GT 2551 p 794 A88-54331 FLOW CHARACTERISTICS FLOW MEASUREMENT Application of unsteady aerodynamic methods for Near-field pressure radiation and flow characteristics in Fibre optic flow sensors based on the 2 focus transonic aeroelastic analysis low supersonic circular and elliptic lets principle p 844 A8842733 [NASA-TM-t 006651 p 799 N88-29754 p 795 A88-54869 Flow in single and twin entry radial turbine volutes Recent advances in transonic computational FLOW COEFFICIENTS [ASME PAPER 88-GT 591 p 847 A88 54191 aeroelasticity Experimental investigation of rotating stall in a Behaviour of the leg of the horseshoe vortex around [NASA TM-1006631 p 800 N88-29778 mismatched three stage axial flow compressor the idealized blade with zero attack angle by triple hot-wire FLUX VECTOR SPLITTING [ASME PAPER 88-GT-205I p 850 A8834292 measurements Multigrid acceleration of the flux-split Euler equations Wake-boundarylayer interactions in an axial flow turbine [ASME PAPER 88 GT-1971 p 792 A88 54285 p 796 A88-55077 rotor at on-design conditions FLY BY WIRE CONTROL Flow measurements in rotating stall in a gas turbine IASME PAPER 88-GT-2331 p 793 A88-54315 Integrated thrust vectoring on the X-29A engine compressor FLOW DISTRIBUTION [AlAA PAPER 88-44991 p 808 A8843769 [ASME PAPER 88-GT 2191 p 819 A8864304 A projection-grid scheme for calculating transonic flow A profile of US Air Force aircraft mishap investigation past a profile p 785 A8862795 A comparison between measurements and turbulence p 801 A88-55288 A three dimensional zonal Navier-Stokes code for models in a turbine cascade passage FOCUSING subsonic through hypersonic propulsion flowfields [ASME PAPER 88 GT 2261 p 793 A88-54309 Fibre optic flow sensors based on the 2 focus [AIAA PAPER 88-28301 p 785 A88-53106 Turbulence measurements and secondary flows in a principle p 844 A88-52733 CFD prediction of the reacting flow field inside a subscale turbine rotor cascade FOG scramjet combustor [ASME PAPER 88 GT-2441 p 794 A88 54323 Flow visualization on a small scale [AlAA PAPER 138-3259] p 816 A88-53151 The effect of the Reynolds number on the [AD-At947281 p 835 N88-28935 Flow field in the tip gap of a planar cascade of turbine three-dimensional flow in a straight compressor cascade FORCED VIBRATION blades [ASME PAPER 88 GT 2691 p 794 A8844343 Control of rotor aerodynamically forced vibrations by [ ASME PAPER 88-GT-29I p 787 A8844173 Positron emission tomography A new technique for splitters p 815 A88-52684 The effects of an excited impinging jet on the local heat Observing fluid behavior in engineering systems FORGING transfer coefficient of aircraft turbine blades [PNR9047t I p 854 N88 30091 Service failure of a 7049 T73 aluminum aircraft forging 1 ASME PAPER 88 GT-661 p 847 A88-54197 FLOW STABILITY p 840 A88-55286 On the prediction of unsteady forces on gas-turbine Flow measurements in rotating stall in a gas turbine FRACTURE MECHANICS blades I - Typical results and potential-flow-interaction engine compressor Fatigue crack growth characterization of let transport effects [ASME PAPER 88 GT-2191 p 81 9 A88 54304 structures p 803 A88-52653 [ASME PAPER 88-GT-891 p 789 A8844213 Theoretical investigation of the interaction between a Fault diagnosis of gas turbine engines from transient Behaviour of the leg of the horseshoe vortex around compressor and the components during surge data the idealized blade with zero attack angle by triple hot-wire [ ASME PAPER 88-GT 2201 p 851 A88 54305 [ASME PAPER 88-GT 2091 p 819 A88-54295 measurements Numerical results for axial flow compressor instability Stress intensity factors for cracked metallic structures [ASME PAPER 88-GT-1971 p 792 A88-54285 [ASME PAPER 88 GT 2521 p 851 A88-54328 under rapid thermal loading Calibration of CFD methods for high Mach number FLOW THEORY [AES-8609709F-t ] p 843 N88-29962 aeroengine flowfields Three dimensional flow in radial-inflow turbines Modeling of micromechanisms of fatigue and fracture [ASME PAPER 88-GT-1991 p 792 A88-54286 [ASME PAPER 88 GT-1031 p 790 A88 54222 in hybrid materials Structure of t~pclearance flow in an isolated axial FLOW VELOCITY LAD-AI95604 I p 855 NEE-30142 Compressor rotor Laminar flow velocity and temperature distributions FRACTURESTRENGTH [ASME PAPER 88-GT-251I p 794 A8844327 between coaxial rotating disks of finite radius Plasma sprayed tungsten carbide-cobalt coatings An experimental investigation of a vortex flow cascade [ASME PAPER 88 GT-491 p 847 A88-54185 p 845 A88-53579 [ ASME PAPER 88-GT-2651 p 794 A88-54341 Computation of the let-wake flow structure in a low speed Whisker orientation measurements in injection molded Nonuniform vane spacing effects on rotor blade forced centrifugal impeller Si3N4-SiC composites response and noise generation p 796 A88-54944 [ASME PAPER 88 GT 2171 p 793 A88-54302 [ASME PAPER 88-GT-1931 p 839 A88-54282 Computational tools for Simulation methodologies Delta wing configurations p 796 N88 28860 Helicopter crew seat failure analysis p 834 N88-28865 Unsteady water channel p 801 A88-55290 Transport-type configurations p 809 N88-28867 [AD A194231 I p 797 N88 28884 Modeling of micromechanisms of fatigue and fracture Combat aircran p 810 N88-28868 A study of the effect of random input motion on low in hybrid materials Noise generation and boundary layer effects in Reynolds number flows [ AD-A t 95604 1 p 855 N88-30142 vortex-airfoil interaction and methods of digital hologram (AD At955591 p 798 N88 29747 FRAMES (DATA PROCESSING) analysis for these flow fields FLOW VISUALIZATION Multiple frame rate integration [AD-A194t9t] p 797 N88-28883 An airborne system for vortex flow visualization on the [AIAA PAPER 88.45791 p 857 A88-53631 Unsteady flow past an NACA 0012 airfoil at high angles F-t 8 high-alpha research vehicle FREE FLOW of attack (AlAA PAPER 88.4671 I p 8 13 A88 53830 Effect of free stream turbulence. Reynolds number, and [AD-A1946501 p 797 N88-28886 The use of fins to reduce the pressure drop in a rotating incidence on axial turbine cascade performance Aerodynamics of seeing on large transport aircraft cavity with a radial inflow LASME PAPER 88-GT-1521 p 791 A88-54252 [NASA-CR-t831221 p 801 NE8 28896 [ASME PAPER 88 GT-581 p 788 A88-54190 Unsteady water channel Flow visualization by laser sheet Near-field pressure radiation and flow characteristics in [AD-A19423t I p 797 N88-28884 [AD-A194481 1 p 853 N88-29111 low supersonic circular and elliptic lets FREQUENCIES Three-dimensional elliptic grid generation for an F-16 p 795 A88-54869 Effect of phase errors in stepped frequency radar p 859 N88-29315 Noise generation and boundary layer effects in systems vortex airfoil interactmn and methods of digital hologram AD-At 944761 p 853 N88-29061 Component adaptive grid generation for aircraft I analysis for these flow fields Contamination and distortion of steady flow field induced configurations p 859 N88-29316 [AD A1941911 p 797 N88 28883 by discrete frequency disturbances in aircraft gas Generation of multiple block grids for arbitrary 30 Flow visualization on a small scale engines geometries p 859 N88-29317 [AD-A1947281 p 835 N88-28935 [AD-A195440] p 854 N88-30069 Grid generation for an advanced fighter aircraft Flow visualization by laser sheet FUEL COMBUSTION p 859 N88-29319 [AD A194481 I p 853 N88 291 t t The performance of a surrogate blend in simulating the Algebraic grid generation for fighter type aircraft A study of the effect of random input motion on low sooting behavior of a practical, distillate JP-4 p 859 N88-29320 Reynolds number flows [ASME PAPER 88-GT 194) p 840 A88-54283 Analytical surfaces and grids p 860 N88-29322 [AD At955591 p 798 N88 29747 Atomization of alternative fuels p 842 N88-29913 Grid generation around transport aircraft configurations Positron emission tomography A new technique for Turbulence effects on the droplet distribution behind using a multi-block structured computational domain observing fluid behavior in engineering systems airblast atomizers p 842 N88-29915 p 860 N88-29325 IPNR9047t I p 854 N88-30091 Influence of operatmg conditions on the atomization and An experimental study of an adaptive-wall wind tunnel FLOWMETERS distribution of fuel by air blast atomizers [NASA-CR-1831521 p 835 N88-29821 Fibre optic flow sensors based on the 2 focus p 842 N88-29918 principle p 844 A88-52733 The characterizatin of combustion by fuel composition Assessment of a 3 D boundary layer analysis to predict FLUID DYNAMICS Measurements in a small conventional combustor heat transfer and flow field in a turbine passage p 842 N88-29920 I NASA-CR-174894I p 854 N88-30066 Assessment of a 3-13 boundary layer analysis to predict heat transfer and flow field in a turbine passage High performance turbofan afterburner systems Contamination and distortion of steady flow field induced [ NASA-CR-I 74894 1 p 854 N88 30066 p 842 N88-29922 by discrete frequency disturbances in aircraft gas FLUID FILMS Radiation transfer in gas turbine combustors engines Rolling element bearing monitoring and diagnostics p 843 N88-29929 [ AD-A1954401 p 854 N88-30069 techniques Gas turbine smoke measurement A smoke generator Studies of unsteady axial-compressor functioning [ASME PAPER 88-GT 2121 p 850 A88-54298 for the assessment of current and future techniques p 855 N88-30129 FLUTTER p 843 N88-29930 FLOW GEOMETRY Approximation schemes for an aeroelastic-control FUEL CONSUMPTION The use of Bezier polynomial patches to define the system p 829 A88 54660 Towards the optimum ducted UHBR engine --- Ultra High geometrical shape of the flow channels of compressors Empirical flutter prediction method Bypass Ratio I ASME PAPER 88-GT-60 I p 788 A88-54192 [AD A1956991 p 825 N88 29810 [AlAA PAPER 88-29541 p8t6 A88-53119 Flow in liner holes for counter-current combustion FLUTTER ANALYSIS Development of the T406 AD-400 oil scavenge system systems Flutter of a fan blade in supersonic axial flow for the V-22 aircraft 1 ASME PAPER 88-GT-158I p 839 A88-54257 [ASME PAPER 88-GT 781 p 788 A88-54206 [ASME PAPER 88 GT-2971 p 821 A88 54366

A-14 SUBJECT INDEX GAS-SOLID INTERACTIONS

XG40 - Advanced combat engine technology GAS FLOW Brushes as high performance gas turbine seals demonstrator programme An experimentalinvestigation into the influence of blade [ ASME PAPER 88-GT-182I p 850 A88-54273 [ASME PAPER 88-GT-3001 p 821 A88-54369 leaning on the losses downstream of annular cascades Fault diagnosis of gas turbine engines from transient Design aspects of recent developments in Rolls-Royce with a small diameter-height ratio data RE211-524 powerplants [ ASME PAPER 88-GT-191 p 786 A88-54165 [ ASME PAPER 88-GT-2091 p 81 9 A88-54295 [ASME PAPER 88-GT-3011 p 821 A88-54370 GASGENERATORS Thermomechanical advances for small gas turbine FUEL CONTAMINATION Cool gas generator systems engines - Present capabilities and future direction in gas Development of a test method to determine potential [AIAA PAPER 88-33631 p 805 A88-53161 generator designs peroxide content in turbine fuels. Part 2 Thermomechanical advances for small gas turbine [ASME PAPER 88-GT-2131 p 850 A88-54299 [ AD-AI 922441 p 841 N88-29042 enaines - Present caoabilities and future direction in aas Real time neutron radiography applications in gas turbine Atomization of alternative fuels p 842 N88-29913 generator designs and internal combustion engine technology [ASME PAPER 88-GT-2131 p 850 A88-54299 Fuel effects on flame radiation and hot-section [ASME PAPER 88-GT-2141 p 850 A88-54300 durability p 843 N88-29925 GAS INJECTION Measurement and modelling of the gas turbine blade FUEL CONTROL An experimental data base for the computational fluid transition process as disturbed by wakes Nozzle airflow influences on fuel patternation dynamics of combustors [ASME PAPER 88-GT-2321 p 793 A88-54314 [ASME PAPER 88-GT-251 p 846 A88-54169 p 842 N88-29916 Linear state variable dynamic model and estimator FUEL FLOW GAS STREAMS design for Allison T406 gas turbine engine Thermal barrier coatings for jet engines Use of control feedback theory to understand other [ASME PAPER 88-GT-2391 p 820 A88-54319 [ASME PAPER 88-GT-2791 p 840 A88-54351 oscillations Numerical correlation of gas turbine combustor ignition GAS TEMPERATURE [ASME PAPER 88-GT-81J p 848 A88-54209 [ ASME PAPER 88-GT-2421 p 820 A88-54321 Fault diagnosis of gas turbine engines from transient Gas temperature measurements in short duration AGTI 01 /ATTAP ceramic technology development turbomachinery test facilities data [ASME PAPER 88-GT-2431 p 820 A88-54322 [AIAA PAPER 88.30391 p 844 A88-53128 [ASME PAPER 88-GT-2091 p 819 A88-54295 Laser - A gas turbine combustor manufacturing tool GAS TURBINE ENGINES FUEL INJECTION [ASME PAPER 88-GT-2671 p 851 A88-54342 Design code verification of external heat transfer A detailed characterization of the velocity and thermal Current status and future trends in turbine application coefficients fields in a model can combustor with wall jet injection of thermal barrier coatings [AlAA PAPER 88-30111 p 844 A88-53123 [ASME PAPER 88-GT-261 p 818 A88-54170 [ASME PAPER 88-GT-2861 p 851 A88-54355 Advanced structural instrumentation An overview Numerical correlation of gas turbine combustor ignition - Causes for turbomachinery performance deterioration [AIAA PAPER 88-31441 p 844 A88-53145 [ASME PAPER 88-GT-2421 p 820 A88-54321 [ASME PAPER 88-GT-2941 p 821 A88-54363 Experimental and theoretical aspects of thick thermal Combustion and fuels in gas turbine engines Turbomachinery alloys affected by solid particles barrier coatings for turbine applications [AGARD-CP-4221 p 841 N88-29910 [ ASME PAPER 88-GT-295I p 840 A88-54364 p 837 A88-53566 Spray performance of a vaporizing fuel injector A turbine wheel design story Meeting the high temperature challenge The p 842 N88-29919 - [ASME PAPER 88-GT-3161 p 822 A88-54383 non-metallic aero engine p 838 A88-53838 FUELSPRAYS Potential application of composite materials to future Surface engineering for high temperature Flame speeds in fuel sprays with hydrogen addition gas turbine engines p 823 A88-54624 environments p 845 A88-53840 [ASME PAPER 88-GT-201 p 838 A88-54166 Prediction of turbulence generated random vibrational Deformation and damage of the material of gas turbine Evaporation of fuel droplets in turbulent combustor response of turbomachinery blading p 796 A88-54946 engine blades during thermal cycling in gas flow flow V2500 engine collaboration p 845 A88-53954 [ASME PAPER 88-GT-1071 p 839 A88-54226 [ PNR90423 I p 825 N88-29803 Calculation of stress relaxation in the surface-hardened Numerical correlation of gas turbine combustor ignition Constitutive modeling for isotropic materials [ASME PAPER 88-GT-2421 p 820 A88-54321 layer near a hole in the disk of a gas-turbine engine [NASA-CR-1821321 p 826 N88-29811 p 846 A88-53961 Atomization of alternative fuels p 842 N88-29913 Spray automated balancing of rotors: Methods and Corrosion and protection of gas turbine blades Turbulence effects on the droplet distribution behind --- materials airblast atomizers p 842 N88-29915 Russian book p 838 A88-53996 [NASA-CR-182151] p 836 N88-29825 NASA HOST project overview hot section Nozzle airflow influences on fuel patternation --- Radiation transfer in gas turbine combustors technology p 81 7 A88-54138 p 842 N88-29916 p 843 N88-29929 Structuralanalysis applications ---for aircrafl gas turbine Influenceof operating conditions on the atomizationand Gas turbine smoke measurement: A smoke generator combustors p 81 7 A88-54143 distribution of fuel by air blast atomizers for the assessment of current and future techniques Life modeling of thermal barrier coatings for aircraft gas p 842 N88-29918 p 843 N88-29930 turbine engines p 838 A88-54145 Spray performance of a vaporizing fuel injector Assessment of a 3-D boundary layer analysis to predict Aerodynamic and heat transfer measurements on a p 842 N88-29919 heat transfer and flow field in a turbine passage transonic nozzle guide vane The characterizatin of combustion by fuel composition: [ NASA-CR-I74894 I p 854 N88-30066 [ASME PAPER 88-GT-IO] p 786 A88-54157 Measurements in a small conventional combustor GAS TURBINES Development of a thermal and structural analysis p 842 "3.29920 Assessment, development, and application of The performanceof a surrogate blend in simulatingJP-4 procedure for cooled radial turbines combustor aerothermal models p 817 A88-54140 [ASME PAPER 88-GT-181 p 846 A88-54164 in a spray-fueled combustor p 843 N88-29926 Review and assessment of the database and numerical An experimental data base for the computational fluid FUEL SYSTEMS modeling for turbine heat transfer p 817 A88-54141 Air flow performance of air swirlers for gas turbine fuel dynamics of combustors Flow field in the tip gap of a planar cascade of turbine [ASME PAPER 88-GT-251 p 846 A88-54169 nozzles blades ExDerimentalinvestiaation of multistaae interaction aust [ASME PAPER 88-GT-1081 p 848 A88-54227 [ASME PAPER 88-GT-291 p 787 A88-54173 aerodynamics FUEL TANKS On the prediction of unsteady forces on gas-turbine [ASME PAPER 88-GT-561 p 787 A88-54188 IMMP . A computer simulationof fuel CG versus vehicle blades. I - Typical results and potential-flow-interaction Further asDects of the UK enaine technoloav attitude effects demonstrator programme [SAWE PAPER 18011 p 827 A88-53799 [ASME PAPER 88-GT-891 p 789 A88-54213 FUEL TESTS [ASME PAPER 88-GT-I041 p 848 A88-54223 On lhe prediction of unsteady forces on gas-turbine Fuel property effects on the US Navy's TF30 engine Design optimizationof gas turbine blades with geometry blades. II - Viscous-wake-interaction and axial-gap and natural frequency constraints p 826 N88-29911 effects [ASME PAPER 88-GT-1051 p 818 A88-54224 FUEL-AIR RATIO [ ASME PAPER 88-GT-901 p 789 A88-54214 The blowout of turbulent jet flames in co-flowing streams Evaporation of fuel droplets in turbulent combustor Gas turbine studies at Oxford 1969-1987 of fuel-air mixtures flow [ASME PAPER 88-GT-1121 p 848 A88-54230 [ASME PAPER 88-GT-1071 p 839 A88-54226 [ASME PAPER 88-GT-1061 p 838 A88-54225 The effects of turbulence and stator/rotor interactions FULL SCALE TESTS Air flow performance of air swirlers for gas turbine fuel on turbine heat transfer. I - Design operating conditions A comparison of CFD and full scale VariEze wind tunnel nozzles [ASME PAPER 88-GT-1251 p 848 A88-54236 results [ASME PAPER 88-GT-I081 p 848 A88-54227 Assessment of gas turbine vibration monitoring [AIAA PAPER 88-44631 p 807 A88-53759 Design and test of non-rotating ceramic gas turbine [ASME PAPER 88-GT-2041 p 850 A88-54291 FUSELAGES components Comparison of ceramic vs. advanced superalloy options Damage tolerance in pressurized fuselages [ASME PAPER 88-GT-1461 p 819 A88-54247 for a-small gas turbine technology demonstrator p 803 A88-52652 Flow in liner holes for counter-current combustion [ASME PAPER 88-GT-2281 p 851 A88-54311 Estimatingfuselage weight penalty required to suppress systems AGARD (Advisory Group for Aerospace Research and noise from propfans [ASME PAPER 88-GT-1581 p 839 A88-54257 Development) engine disc material cooperative test [SAWE PAPER 17871 p 809 A88-53790 Sorav automatedbalancina of rotors - Conceot and initial (supplementary program) (AD-AI936781 p 824 N88-28925 Test of an 0.8-scale model of the AH-64 Apache in the feasibility study Failure analysis for gas turbines NASA Langley full-scale wind tunnel [ASME PAPER 88-GT-1631 p 849 A88-54261 [ AD-AI 961291 p 799 N88-29768 [ NLR-MP-8703741 p 825 N88-29808 Notes on the occurrence and determination of carbon Determination of the hydroperoxide potential of jet within gas turbine combustors fuels G [ASME PAPER 88-GT-1641 p 839 A88-54262 [AD-AI 959751 p 844 N88-29991 Fully scaled transonic turbine rotor heat transfer Contaminationand distortion of steady flow field induced GALLIUM ARSENIDES measurements by discrete frequency disturbances in aircraft gas Very high speed integrated circuits/gallium arsenide [ASME PAPER 88-GT-1711 p 849 A88-54265 engines electronics for aircraft engine controls Fiber metal acoustic materials for gas turbine exhaust [AD-A195440] p 854 N88-30069 p 823 A88-54620 environments GAS-SOLID INTERACTIONS GAS COOLING [ASME PAPER 88-GT-1751 p 839 A88-54269 On the prediction of unsteady forces on gas-turbine Studies of aas turbine heat transfer airfoil surface and The feasibilitv. from an installational viewDoint of blades. I - TvDical results and potential-flow-interaction end-wall coolkg effects gas-turbine pressure-gaincombustors effects [AD-AI951651 p 825 N88-29805 [ASME PAPER 88-GT-1811 p 849 A88-54272 [ASME PAPER 88-GT-891 p 789 A88-54213

A-15 GEOMETRY SUBJECT INDEX

On the prediction of unsteady forces on gas-turbine Extreme gusts distribution p 857 N88-29734 The effects of inlet turbulence and rotor/stator blades II - Viscous-wake-interaction and axial-gap GUSTS interactions on the aerodynamics and heat transfer of a eff ects A summary of methods for establishing airframe design large-scalerotating turbine model. Volume 3: Heat transfer [ ASME PAPER 88-GT-90 1 p 789 A88-54214 loads from continuous gust design criteria data tabulation 65 percent axial spacing The influence of turbine clearance gap leakage on p 811 N88-29721 [ NASA-CR-1794881 p 824 N88-28930 passage velocity and ieat transfer near blade tips I - Sink An interim comparison of operational CG records in The use of hot-film technique for boundary layer studies flow effects on blade pressure side turbulence on small and large civil aircraft on a 21 percent thick airfoil [ ASME PAPER 88-GT-981 p 790 A88-54218 p 830 N88-29729 [NAE-AN-451 p 800 N88-29781 The effects of inlet turbulence and rotor/stator A fast interactive two-dimensional blade-to-bladeprofile Re-assessment of gust statistics using CAADRP data interactions on the aerodynamics and heat transfer of a design method p 831 N88-29732 [ASME PAPER 88-GT-1001 p 790 A8864220 large-scalerotating turbine model. Volume 2: Heat transfer GEOMETRY data tabulation. 15 percent axial spacing Delta wing configurations p 796 N88-28860 H [NASA-CR-179467] p 825 N88-29804 GERMANY Assessment of a 3-13 boundary layer analysis to predict History of aeroelasticity in Germany from the beginning heat transfer and flow field in a turbine passage H-60 HELICOPTER to 1945 [NASA-CR-174894] p 854 N88-30066 The RTM322 engine in the S-70C helicopter [ ESA-TT-10821 p 799 N88-29767 HEAT TRANSFER COEFFICIENTS [ AlAA PAPER 88-45761 p 817 A8843774 GLASS FIBER REINFORCED PLASTICS Design code verification of external heat transfer Development of a glass fiber wing following the HARMONIC EXCITATION coefficients construction regulation FAR Part 23 The effects of an excited impinging let on the local heal [AIAA PAPER 88-3011 ] p 844 A88-53123 [ ETN-88.929661 p 840 N88-28979 transfer coefficient of aircraft turbine blades The effects of an excited impingingjet on the local heat [ASME PAPER 88-GT-661 p 847 A88-54197 GLIDERS transfer coefficient of aircraft turbine blades Possible future developments of motorgliders and light HARRIER AIRCRAFT [ASME PAPER 88-GT-661 p 847 A88-54197 aircraft p 805 A8842697 Navy V/STOL Engine experience in Altitude Test HELICOPTER CONTROL GOVERNMENTllNDUSTRY RELATIONS Facility The minimisation of helicopter vibration through blade Second sourcing of a let engine [ASME PAPER 88-GT-3171 p 834 A88-54384 design and active control p 805 A88-53249 [ASME PAPER 88-GT-1451 p 784 A88-54246 HEAD-UP DISPLAYS The effect of perspectivedisplays on altitude and stability GRAPHITE-EPOXY COMPOSITES Ground simulator requirements based on in-flight control in simulated rotary wing flight Structural technology transition to new aircraft Simulation I AIM PAPER 88-4634I p 833 A88-53667 p 805 A88-52673 [AIAA PAPER 88-46091 p 806 A88-53651 Design concepts for an Advanced Cargo Rotorcraft GRID GENERATION (MATHEMATICS) Development, analysis, and flight test of the Lockheed [AIAA PAPER 88-44961 p 807 A88-53768 Dimensioning of turbine blades for fatigue and creep Aeronautical System Company HnBHUD Towards simultaneous performance - Application of p 817 A88-53167 [AlAA PAPER 88-4511 I p 81 3 A8843772 simultaneous stabilization techniques to helicopter engine Three dimensional grid generation for Complex Improvement of head-up display standards Volume 2 control p 822 A88-54507 configurations Recent progress Evaluationof head-up displays to enhance unusual attitude Considerationsfor automated nap-of-the-earthrotorcraft flight p 827 A88-54526 I AGARD-AG-3091 p 858 N88-29313 ,Cl-O"LN--- -, Lessons learned in the mesh generation for PN/S [AD.A194@Jj] p 814 N88-28921 Helicopter trajectory planning using optimal control theory p 828 A88-54571 calculations p 859 N88 29314 Improvement of head up display standards Volume 5 H(infinity)-optimaldesign for helicopter control Three-dimensionalelliptic grid generation for an F-16 Head updisplay ILS (InstrumentLanding System)accuracy 859 N88-2931 p 828 A88-54598 Pilotlvehicle analysis of a twin-lift helicopter Component adaptive grid generation for aircraft p 814 N88 28922 configurations p 859 N88-29316 ~j4~~~~~6021 configuration in hover p 829 A88 55064 MEASUREMENT Generation of multiple block grids for arbitrary 3D Minimum complexity helicopter simulation math model geometries p 859 N88-29317 Fully scaled transonic turbine rotor heat transfer lNASA-CR-1774761 p 831 N88-29819 Grid generation on and about a cranked-wing fighter 849 A88-54265 HELICOPTER DESIGN 859 N88-29318 [ASME PAPER 88-GT 1711 aircraft configuration The minimisation of helicopter vibration through blade Grid generation for an advanced fighter aircraft HEAT RESISTANT ALLOYS design and active control p 805 A8843249 p 859 N88-29319 High temperature testing of plasma sprayed thermal Design concepts for an Advanced Cargo Rotorcraft Algebraic gnd generation for fighter type aircraft barrier coatings p 845 A88-53571 [AIAA PAPER 88 44961 p 807 A88 53768 D 859 N88-29320 Composite monolayer fabrication by an arc-spray Helicopter crew seat failure analysis Compositegrid generationfor aircraft configurationswith Process p 845 A88-53581 p 801 A88-55290 the EAGLE code p 859 N88-29321 Surface engineering for high temperature HELICOPTER ENGINES Analytical surfaces and grids p 860 N88-29322 environments p 845 A88-53840 The RTM322 engine in the S-70C helicopter Mesh generation for industrial application of Euler and Effect of loading asymmetry on the low-cycle fatigue [AIAA PAPER 88-45761 p 817 A8843774 Navier Stokes solvers P 860 N88-29323 of ZhS6F alloy under cyclic temperature changes Towards simultaneous performance - Application of -Exoerience with three dimensional comDosite arids 0 838 ,488-53955 simultaneous stabilizationtechniques to helicopter engine p 860 N88-29324 Comparison of ceramic vs advanced superalloy options control p 822 A8844507 Grid generation around transport aircraft configurations for a small gas turbine technology demonstrator HELICOPTER PERFORMANCE using a multi-block structured computational domain [ ASME PAPER 88-GT-2281 p 851 A8844311 Determinationof helicopter simulator time delay and its effects on air vehicle development p 860 N88-29325 Turbomachinery alloys affected by solid particles [AIAA PAPER 88-46201 p 833 A88-53659 GROUND EFFECT (AERODYNAMICS) [ASME PAPER 88-GT-2951 p 840 A88-54364 Aerodynamics in ground effect and predicted landing Helicopter health monitoring from engine to rotor HEAT SINKS [ASME PAPER 88-GT-227) p 809 A88-54310 ground roll of a fighter configuration with a The influence of turbine clearance gap leakage on secondary-nozzlethrust reverser HELICOPTERS passage velocity and heat transfer near blade tips I Sink [ NASA-TP-28341 p 799 "3.29752 - Investigation of helicopter rotor blade/wake interactive flow effects on blade pressure side impulsive noise GUST ALLEVIATORS [ ASME PAPER 88-GT-981 p 790 A88-54218 The Flight of Flexible Aircraft in Turbulence [ NASA-CR-1774351 p 797 N88-28882 State-of-the-Art in the Description and Modelling of HEAT TRANSFER JUH-1H redesignedpneumatic boot deicing system flight Atmospheric Turbulence Review and assessment of the database and numerical test evaluation [ AGARD-R-734-ADD] p 784 N88-29717 modeling for turbine heal transfer p 817 A8844141 [AD-A194918] p 802 N88-29785 A review of measured gust responses in the light of Aerodynamic and heat transfer measurements on a Threat expert system technology advisor modern analysis methods p 830 N88-29724 transonic nozzle guide vane [ NASA-CR-I 774791 p 831 N88-29816 Measurement and analysis of low altitude atmospheric [ ASME PAPER 88-GT-lo] p 786 A88-54157 Developmentand demonstrationof an on-board mission turbulence obtained using a specially instrumented Gnat The influence of turbine clearance gap leakage on planner for helicopters aircraft p 857 N88-29728 passage velocity and heat transfer near blade tips I - Sink [NASA-CR-177482] p 831 N88-29817 GUST LOADS flow effects on blade pressure side A fiber optic collective flight control system for Fatigue crack propagationtest programmefor the A320 [ ASME PAPER 88-GT-981 p 790 A88-54218 helicopters wing p 804 A88-52662 The influence of turbine clearance gap leakage on [AD-A195406] p 831 N88-29818 Experimentalinvestigation of multistage interaction gust passage velocity and heat transfer near blade tips II - HIGH ALTITUDE aerodynamics Source flow effects on blade suction sides Evaluation of potential engine concepts for a high [ASME PAPER 88-GT-561 p 787 A88-54188 [ ASME PAPER 88-GT-991 p 790 A88-54219 altitude long endurance vehicle Aerodynamically forced response of an airfoil including Gas turbine studies at Oxford 1969-1987 [ASME PAPER 88-GT-3211 p 822 A88-54386 profile and incidence effects p 795 A88 54941 [ASME PAPER 88-GT-1121 p 848 A88-54230 HIGH PRESSURE Current and proposedgust criteria and analysis methods The effects of turbulence and statorlrotor interactions E3 1OC compressortest analysis of high-speedpost-stall An FAA overview p 830 "3.2971 8 on turbine heat transfer I . Design operating conditions data Comparison of the influence of different gust models [ASME PAPER 88-GT-1251 p 848 A88-54236 [ NASA-CR-17952II p 824 N88 28929 on structural design p 81 1 N88-29722 A transient flow facility for the study of the HIGH SPEED A review of measured gust responses in the light of thermofluid-dynamicsof a full stage turbine under engine Acquisition of unsteady pressure measurements from modern analysis methods p 830 N88-29724 representativeconditions a high speed multi-stage compressor The Flight of Flexible Aircraft in Turbulence [ASME PAPER 88-GT-1441 p 849 A88-54245 [ASME PAPER 88-GT-1891 p 833 A88-54280 State-of-the-Art in the Description and Modelling of Fully scaled transonic turbine rotor heat transfer E3 1OC compressortest analysis of high-speedpost-stall Atmospheric Turbulence measurements data [ AGARD-A-734I p 785 N88-29725 [ASME PAPER 88-GT-1711 p 849 A88-54265 [ NASA-CR 1795211 p 824 "3.28929 An interim comparison of operational CG records in Surfaceheat transfer fluctuationson a turbine rotor blade HIGH STRENGTH STEELS turbulence on small and large civil aircraft due to upstream shock wave passing Fatigue crack growlh characterization of let transport p 830 N88-29729 [ASME PAPER 88-GT-1721 p 791 A8844266 structures p 803 A88-52653

A-16 SUBJECT INDEX INTEGRAL TRANSFORMATIONS

HIGH TEMPERATURE Some key considerations for high-speed civil The development of acoustic emission for structural The characterizationof high temperature electronics for transports integrity monitoring of aircraft future aircraft engine digital electronic control systems [AIAA PAPER 88-4466) p 783 A88-53760 [ AD-A1962641 p 861 N88-30398 p 823 A88-54621 Assessment of a Soviet hypersonic transport INCIDENCE HIGH TEMPERATURE ENVIRONMENTS [AIAA PAPER 88-45061 p 808 A88-53770 Effects of incidence on three-dimensional flows in a Advanced structural instrumentation - An overview Preliminary definition of pressure sensing requirements linear turbine cascade [AIAA PAPER 88.31441 p 844 A88-53145 for hypersonic vehicles [ASME PAPER 88-GT-1101 p 790 A88-54228 Review and assessment of the database and numerical [AIAA PAPER 88.46521 p 813 A8843826 Effect of free-stream turbulence, Reynolds number, and modeling for turbine heat transfer p 817 A88-54141 HYPERSONICBOUNDARYLAYER incidence on axial turbine cascade performance Views on the impact of HOST --- hot section Numerical solution of the hypersonic viscous shock layer [ASME PAPER 88-GT-1521 p 791 A88-54252 technology p 818 A88-54146 equations with chemical nonequilibrium INCOMPRESSIBLE FLOW Turbomachinery alloys affected by solid particles [IAF PAPER ST-88-08] p 796 A88-55313 Prediction of the pressure distribution for radial inflow [ASME PAPER 88-GT-2951 p 840 A88-54364 HYPERSONIC FLIGHT between co-rotating discs HIGH TEMPERATURE RESEARCH High speed transpacific passenger flight [ASME PAPER 88-GT-61I p 847 A88-54193 Toward improved durability in advanced aircraft engine [AlAA PAPER 88-44841 p 807 A8863764 INDUSTRIAL MANAGEMENT hot sections; Proceedings of the Thirty-third ASME Periodic neighboring optimum regulator applied lo a The CFM56 engine family - An internal development International Gas Turbine and Aeroengine Congress and hypersonic scramjet cruiser p 827 A88-54528 [ASME PAPER 88-GT-2961 p 862 A88-54365 Exposition. Amsterdam, Netherlands, June 5-9. 1988 HYPERSONIC FLOW INERTIAL NAVIGATION p 817 A88-54137 A three dimensional zonal Navier-Stokes code for Angle of attack and sideslip estimation using an inertial Advanced high temperature instrumentation for hot subsonic through hypersonic propulsion flowfields reference platform section research applications p 846 A8844139 [AIM PAPER 88-28301 p 785 A88-53106 [AD-AI948761 p 799 N88-29769 HIGH TEMPERATURE TESTS A full Navier-Stokes analysis of a three dimensional Observed track-keeping performance of DCIO aircraft Fatigue of elevated temperature powder metallurgy hypersonic mixed compression inlet equippedwith the Collins AINS-70 area navigation system: aluminum alloy mechanically fastened joints [AIAA PAPER 88.30771 p 785 A8843138 Karlsruhe and Masstricht UACs (Upper Area Control p 837 A88-52655 Conditions of the induction-plasmatronmodeling of the centres) HIGH THRUST convective nonequilibrium heat transfer of bodies in [EEC-2021 p 803 N88-29788 FIOO-PW-229- Higher thrust in same frame size hypersonic flow p 786 A8843970 INERTIAL PLATFORMS [ASME PAPER 88-GT-312) p 822 A88-54380 Gas turbine studies at Oxford 1969-1987 Angle of attack and sideslip estimation using an inertial HISTORIES [ASME PAPER 88-GT-1121 p 848 A88-54230 reference platform History of aeroelasticity in Germany from the beginning HYPERSONIC SHOCK [AD-A194876] p 799 N88-29769 to 1945 Three-dimensional hypersonic viscous shock layer on INFLUENCE COEFFICIENT [ESA-TTT-1082] p 799 N88-29767 blunt bodies in flow at angles of attack and sideslip Comparison of the influence of different gust models HOLE GEOMETRY (MECHANICS) p 786 A88-53971 on structural design p 81 1 N88-29722 Flow in liner holes for counter-current combustion HYPERSONIC VEHICLES An experimental study of an adaptive-wall wind tunnel systems Soviet applications for hypersonic vehicles [ NASA-CR-1831521 p 835 N88-29821 [ASME PAPER 88-GT-1581 p 839 A88-54257 [AIAA PAPER 88-45071 p 783 A88-53771 INFORMATION SYSTEMS HOLES (MECHANICS) HYPERVELOCITY EMPTAC (Electromagnetic Pulse Test Aircraft) user's Weibull analysis techniques on a desktop computer Hypervelocity application of tribological coatings guide [ASME PAPER 88-GT-2851 p 851 A8844354 p 845 A88-53563 [ AD-At 950721 p 854 N88-30006 HOLOGRAPHY INFRARED DETECTORS Noise generation and boundary layer effects in Detection of separation bubbles by infrared images in vortex-airfoil interaction and methods of digital hologram I transonic turbine cascades analysis for these flow fields [ASME PAPER 88-GT-331 p 787 A88-54176 [AD-A1941911 p 797 "3.28883 IBM COMPUTERS INLET FLOW HOT CORROSION Aircraft noise prediction program propeller analysis A preliminary design study of supersonic through-flow Turbomachinery alloys affected by solid particles system IBM-PC version user's manual version 2.0 fan inlets [ASME PAPER 88-GT-2951 p 840 A88-54364 [ NASA-CR-1816891 p 862 N88-30399 [AIAA PAPER 813-3075] p 816 A88-53137 HOTSURFACES ICE FORMATION The effects of turbulence and statorlrotor interactions Constitutive modeling for isotropic materials Icing Technology Bibliography on turbine heat transfer. II - Effects of Reynolds number [ NASA-CR-1821321 p 826 N88-29811 [SAE AIR 40151 p 801 A88-54400 and incidence HOT-FILM ANEMOMETERS JUH-1H redesignedpneumatic boot deicing system flight [ASME PAPER 88-GT-51 p 846 A88-54152 Turbulence measurements in a multistage low-pressure test evaluation The effect of the inlet velocity profile in the turbine [ AD-A19491 81 p 802 N88-29785 three-dimensional flow in a rear axial compressor stage [ASME PAPER 88-GT-791 p 788 A88-54207 ICE PREVENTION [ASME PAPER 88-GT-461 p 787 A88-54183 The use of hot-film technique for boundary layer studies Icing Technology Bibliography The effects of inlet turbulence and rotorlstator on a 21 percent thick airfoil [SAE AIR 40151 p 801 A88-54400 interactions on the aerodynamics and heat transfer of a large-scalerotating turbine model. Volume 3: Heat transfer [NAE-AN-451 p 800 N88-29781 Composites break the ice --- fiber reinforced materials data tabulation percent axial spacing HOVERCRAFT GROUND EFFECT MACHINES for deicing of aircraft surfaces and engines 65 Use of control feedback theory to understand other p 840 A88-54857 [NASA-CR-179468] p 824 N88-28930 oscillations The effects 01 inlet lurbulence and rotor/stator IGNITION [ASME PAPER 88-GT-811 p 848 A88-54209 interactions on the aerodynamics and heat transfer of a Numerical correlation of gas turbine combustor ignition HTPB PROPELLANTS large-scalerotating turbine model. Volume 2: Heat transfer Review 01 research concerning Solid Fuel Ramjet [ASME PAPER 88-GT-2421 p 820 A8864321 data tabulation. 15 percent axial spacing (SOFRAM) at the Research Institute of National Defence IMAGE ANALYSIS [ NASA-CR-1794671 P 825 N88-29804 (FOA) 2 Image extrapolation for flight simulator visual systems INLET NOZZLES [FOA-C-20714-2.1I p 826 N88-29813 [AIAA PAPER 88-45771 p 832 A88-53629 A full Navier-Stokes analysis of a three dimensional HUMAN FACTORS ENGINEERING IMAGE CONTRAST hypersonic mixed compression inlet The effect of perspectivedisplays on altitude and stability Digital emulation of the AH-64A contrast tracker [AIAA PAPER 88.30771 p 785 A88-53138 control in simulated rotary wing flight [AIAA PAPER 38-465261 p 81 3 A88-53827 An experimental data base for the computational fluid [AIAA PAPER 88-46341 p 833 A88-53687 IMAGE PROCESSING dynamics of combustors Advances in Flying Qualities Dynamic texture in visual system [ASME PAPER 88-GT-251 p 846 A88-54169 [AGARD-LS-157] p 785 N88-29735 [AIAA PAPER 88-45781 p 832 A88-53630 INPUT HUMIDITY Noise generation and boundary layer effects in A study of the effect of random input motion on low Fatigue crack growth characteristics of ARALL roriex-airfoil interaction and methods of digital hologram Reynolds number flows (trademark)-1 analysis for these flow fields [AD-A195559l p 798 N88-29747 [AD-A196185] p 841 N88-29889 [ AD-A194191 1 p 797 N88-28883 INSPECTION HYDROCARBON COMBUSTION IMPACT DAMAGE Evaluation of bond testing equipment for inspection of A methanolloxygen burning combustor for an aircraft Damage tolerance of impact damaged carbon fibre Army advanced composite airframe structures auxiliary emergency power unit composite wing skin laminates p 804 A88-52670 [ AD-A1957951 p 841 N88-29885 INSTRUMENT LANDING SYSTEMS [ASME PAPER 88-GT-2361 p 820 A88-54317 Impact and damage tolerance properties of CFRP HYDROCARBON FUELS Improvement of head-up display standards. Volume 5: sandwich panels - An experimental parameter study for Head up display ILS (InstrumentLanding System) accuracy Effect of molecular structure on soot formation the Fokker 100 CA-EP flap p 804 A88-52671 characteristics of aviation turbine fuels flight tests [ASME PAPER 88-GT-211 p 838 A88-54167 IMPACT LOADS [AD-A1946021 p 814 N88-28922 Control systems for platform landings cushioned by air The blowout of turbulentjet flames in co-flowing streams INSTRUMENT PACKAGES of fuel-air mixtures bags Overview of Lockheed C-I30 High Technology Test Bed [ AD-A 1961 54 p 854 N88-29996 [ASME PAPER 88-GT-1061 p 838 A88-54225 I Program The performance of a surrogate blend in simulating the IMPELLERS [SAWE PAPER 17861 p 808 A88-53789 sooting behavior of a practical, distillate JP-4 Tip leakage in a centrifugal impeller INTEGRAL EQUATIONS [ASME PAPER 88-GT-1941 p 840 A88-54283 [ASME PAPER 88-GT-2101 p 792 A88-54296 An integral equation for the linearized unsteady HYDROGEN Computationof the jet-wake flow structure in a low speed supersonic flow over a wing Flame speeds in fuel sprays with hydrogen addition centrifugal impeller [ AD-A193773 I p 797 N88-28887 [ASME PAPER 88-GT-201 p 838 A88-54166 [ASME PAPER 88-GT-2171 p 793 A88-54302 INTEGRAL TRANSFORMATIONS HYPERSONIC AIRCRAFT IN-FLIGHT MONITORING A new singular integral approach for a vertical array of Propulsion system integration for Mach 4 lo 6 vehicles Helicopter health monitoring from engine to rotor airfoils [AIAA PAPER 88-3239A1 p 805 A88-53149 [ASME PAPER 88-GT-2271 p 809 A88-54310 [ASME PAPER 88-GT-2181 p 793 A88-54303

A-17 INTERACTIONAL AERODYNAMICS SUBJECT INDEX

INTERACTIONAL AERODYNAMICS JET ENGINES Techniques used in the F-14 variable-sweep transition Wake-induced unsteady aerodynamic interactions in a A useful similarity principle for jet engine exhaust system flight experiment multistage compressor p 785 A88-52686 performance I NASA-TM-I 00444 1 p 855 N88-30093 Stator/rotor interaction in a transonic turbine [AIAA PAPER 88-30011 p 816 A88-53122 LAMINAR FLOW AIRFOILS [AlAA PAPER 88-30931 p 785 A88-53140 Flame speeds in fuel sprays with hydrogen addition Suction laminarization of highly swept supersonic Developments in computational methods for high-lift [ASME PAPER 88-GT-201 p 838 A88-54166 laminar flow control wings aerodynamics p 786 A88-53250 Fiber optics based jet engine augmenter viewing [AIAA PAPER 88-4471] p 786 A88-53762 The effects of turbulence and statorlrotor interactions system Transition modeling effects on viscous/inviscid on turbine heat transfer. ll - Effects of Reynolds number [ASME PAPER 88-GT-3201 p 852 A88-54385 interaction analysis of low Reynolds number airfoil flows and incidence An investigation of constitutive models for predicting involving laminar separation bubbles [ASME PAPER 88-GT-51 p 846 A88-54152 viscoplastic response during cyclic loading [ASME PAPER 88-GT-321 p 787 A8864175 Transition modeling effects on viscouslinviscid [AD-A194875] p 856 NEB-30163 LAMINAR WAKES interaction analysis of low Reynolds number airfoil flows A mapping of the viscous flow behavior in a controlled JETEXHAUST involving laminar separation bubbles diffusion compressor cascade using laser Doppler A useful similarity principle for jet engine exhaust system [ASME PAPER 88-GT-321 p 787 A88-54175 velocimetry and preliminary evaluation of codes for the performance Detection of separation bubbles by infrared images in prediction of stall [AIAA PAPER 88-3001I p 816 A88-53122 transonic turbine cascades [AD-AI 944901 p 853 N88-29112 [ASME PAPER 88-GT-331 p 787 A88-54176 JET FLOW LAMINATES Experimental investigationof multistage interaction gust The blowout of turbulent jet flames in co-flowingstreams Damage tolerance aspects of an experimentalArall F-27 of fuel-air mixtures aerodynamics lower wing skin panel p 804 A88-52668 [ASME PAPER 88-GT-561 p 787 A88-54188 [ASME PAPER 88-GT-1061 p 838 A8844225 Damage tolerance of impact damaged carbon fibre The effects of turbulence and statorlrotor interactions Computationof the jet-wake flow structure in alow speed composite wing skin laminates p 804 A88-52670 on turbine heat transfer I - Design operating conditions centrifugal impeller Modeling of micromechanisms of fatigue and fracture [ASME PAPER 88-GT-I251 p 848 A88-54236 [ASME PAPER 88-GT-2171 p 793 A88-54302 in hybrid materials JET IMPINGEMENT Numerical analysis of airfoil and cascade flows by the [AD-AI 956041 p 855 N88-30142 viscous/inviscid interactive technique The effects of an excited impingingjet on the local heat LAND USE transfer coefficient of aircraft turbine blades [ASME PAPER 88-GT-1601 p 791 A88-54259 An analysis of time and space requirements for aircraft Wake-boundary layer interactions in an axial flow turbine [ASME PAPER 88-GT-661 p 847 A88-54197 turnrounds JET MIXING FLOW rotor at off-design conditions [TT-87051 p 802 N88-29783 [ASME PAPER 88-GT-2331 p 793 A8864315 A useful similarity principle for jet engine exhaust system LANDING AIDS Application of a hybrid analyticallnumerical method to performance Control systems for platform landings cushioned by aur the practical computation of supercriticalviscouslinviscid IAlAA PAPER 88-30011 p 816 A88-53122 bags JET VANES transonic flow fields p 795 A88-54907 [AD-AI 961541 p 854 N88-89996 An unsteady helicopter rotor: Fuselage interaction Thermal barrier coatings for jet engines LANDING GEAR analysis [ASME PAPER 88-GT-2791 p 840 A8844351 Service failure of a 7049 T73 aluminum aircraft forging Nonuniform vane spacing effects on rotor blade forced INASA-CR-4178 1 p 784 NEB-28880 p 840 A88-55286 Experience with three dimensional composite grids response and noise generation p 796 A88-54944 LANDING LOADS p 860 N88-29324 JOINTS (JUNCTIONS) Control systems for platform landings cushioned by air Three-dimensionalNavier-Stokes simulations of turbine Aspects of the fatigue behaviour of typical adhesively bags rotor-stator interaction bonded aircraft structures p 804 A88-52659 [AD-AI 96154) p 854 N88-29996 [ NASA-TM-I00081 p 799 N88-29750 Mechanization of joint production during the assembly LANDING SIMULATION INTERACTIVE CONTROL of aircraft structures --- Russian book Additional investigations into the aircraft landing Mesh generation for industrial application of Euler and p 846 A88-53998 process: Test distributions Critical joints in large composite primary aircraft Navier Stokes solvers p 860 N88-29323 [ ESA-TT-1099] p 810 "3-28913 Numerical simulation of nozzle flows structures Volume 2: Technology demonstration test LAP JOINTS [AD-AI 951441 p 854 N88-30064 report Fatigue of elevated temperature powder metallurgy INTERNAL COMBUSTION ENGINES (NASA-CR-1725871 p 811 N88-28915 aluminum alloy mechanically fastened joints Critical joints in large composite primary aircraft Real time neutron radiography applicationsin gas turbine p 837 A88-52655 and internal combustion engine technology structures. Volume 3: Ancillary test results LASER ANEMOMETERS [ASME PAPER 88-GT-2141 p 850 A88-54300 [NASA-CR-172588] p 811 N88-28916 Fibre optic flow sensors based on the 2 focus INTERPOLATION Critical joints in large composite primary aircraft principle p 844 A88-52733 Analytical surfaces and grids p 860 N88-29322 structures. Volume 1: Technical summary LASER APPLICATIONS INVISCID FLOW [ NASA-CR-39141 p 840 N88-28983 Instrumentationand techniques for structural dynamics Developments in computational methods for high-lift JOUKOWSKI TRANSFORMATION and acoustics measurements An efficient patched grid Navier-Stokes solution for aerodynamics p 786 A88-53250 [AIAA PAPER 88-46671 p 845 A88-53829 The relative merits of an inviscid Euler 3-D and quasi-3-D multiple bodies, phase 1 Flow visualization by laser sheet analysis for the design of transonic rotors IAD-Al941661 p 853 NEB-29110 [AD-A194481] p 853 N88-29111 [ASME PAPER 88-GT-691 p 788 A88-54200 JP-4 JET FUEL LASER DOPPLER VELOCIMETERS Quasi3D solutions for transonic. inviscid flows by The performance of a surrogate blend in simulating the Hot-wire measurements of compressor blade wakes in adaptive triangulation sooting behavior of a practical, distillate JP-4 a cascade wind tunnel [ASME PAPER 88-GT-l94] p 840 A8864283 [ASME PAPER 88-GT-831 p 789 A88-54211 [AD-A194737] p 835 N88-28936 A fast interactive two-dimensionalblade-to-blade profile The performanceof a surrogate blend in simulatingJP-4 LASER DRILLING design method in a spray-fueledcombustor p 843 N88-29926 Laser - A gas turbine combustor manufacturingtool [ASME PAPER 88-GT-I001 p 790 A88-54220 [ASME PAPER 88-GT-2671 p 851 A8844342 Numerical simulation of inviscid transonic flow through LASER OUTPUTS nozzles with fluctuating back pressure K Flow visualization by laser sheet [ASME PAPER 88-GT-2871 p 794 A88-54356 KALMAN FILTERS [AD-A194481] p 853 N88-29111 ISOTROPIC MEDIA Estimation of aircraft parameters using filter error LASER WELDING Constitutive modeling for isotropic materials methods and extended Kalman filter Laser - A gas turbine combustor manufacturingtool [NASA-CR-182132I p N88-29811 826 [DFVLR-FB-88-15] p 810 N88-28911 [ASME PAPER 88-GT-2671 p 851 A88-54342 ITERATIVE SOLUTION LATERAL CONTROL Grid generation around transport aircraft configurations Canard certification loads - Progress toward alleviating using a multi-block structured computational domain L FAA concerns p N88-29325 860 [AIAA PAPER 88.44621 p 807 A88-53758 LABYRINTH SEALS LAUNCHERS J Brushes as high performance gas turbine seals Combined engines for future launchers [ASME PAPER 88-GT-1821 p 850 A88-54273 [AIAA PAPER 88.28231 p 836 A88-53105 LAMINAR BOUNDARY LAYER JET AIRCRAFT LEADING EDGE FLAPS Transition modeling effects on viscouslinviscid Caring for the high-time jet p 801 A88-53540 Pressure distributions from subsonic tests of an interaction analysis of low Reynolds number airfoil flows JET AIRCRAFT NOISE advanced laminar-flow-control wing with leading- and involving laminar separation bubbles Future supersonic transport noise - Lessons from the trailing-edge flaps [ASME PAPER 88-GT-321 p 787 A88-54175 past LAMINAR FLOW [ NASA-TM-4040-PT-21 p 800 N88-29776 (AIAA PAPER 88-29891 p 816 A88-53121 Aerodynamics --- numerical simulation using LEAKAGE Noise levels from a jet-engined aircraft measured at supercomputers p 783 A88-53800 The influence of turbine clearance gap leakage on ground level and at 1.2 m above the ground Laminar flow velocity and temperature distributions passage velocity and heat transfer near blade tips. II - [NPL-AC-I141 p 861 N88-29524 between coaxial rotating disks of finite radius Source flow effects on blade suction sides JET ENGINE FUELS [ASME PAPER 88-GT-491 p 847 A88-54185 [ASME PAPER 88-GT-991 p 790 A88-54219 Development of a test method to determine potential Variable Sweep Transition Flight Experiment Tip leakage in a centrifugal impeller peroxide content in turbine fuels. Part 2 (VSTFE)-parametric pressure distribution boundary layer [ASME PAPER 88-GT-ZlOl p792 A88-54296 , [ AD-A1922441 p 841 N88-29042 stability study and wing glove design task LEARNING MACHINES Fuel properly effects on the US Navy's TF30 engine [ NASA-CR-39921 p 798 N88-28894 Rule-based mechanisms of learning for intelligent p 826 N88-29911 Pressure distributions from subsonic tests of an adaptive flight control p 858 A88-54426 i Determination of the hydroperoxide potential of jet advanced laminar-flow-control wing with leading and LIFE (DURABILITY) fuels trailing-edge flaps Certification of primary composite aircraft structures ADA1959751 p 844 N88-29991 [ NASA-TM-4040-PT-21 p 800 N88-29776 p805 A88-52672 I I A-18 SUBJECT INDEX METAL FATIGUE

Life modeling of thermal barrier coatings for aircraft gas LOADING RATE MANIPULATORS turbine engines p 838 A88-54145 An investigation of constitutive models for predicting Low-speed longitudinal flying qualities of modern p 81 2 N88-29738 LIFE CYCLE COSTS viscoplastic response during cyclic loading transport aircraft YA-7F - A twenty year economic life extension at costs IAD-A1948751 p 856 N88-30163 MANUAL CONTROL we can afford LONGITUDINAL CONTROL Pilotlvehicle analysis of a twin-lift helicopter [AIAA PAPER 88-44601 p 783 A88-53757 Canard certification loads - Progress toward alleviating configuration in hover p 829 A88-55064 Use of a detail cost model to perform conceptual phase FAA concerns MASKS AlAA PAPER 88-44621 p 807 A88-53758 cost analysis 1 Smoke hoods: Net safety benefit analysis --- aircraft (SAWE PAPER 17841 p 862 A88-53788 Steady and unsteady transonic pressure measurements accidents on a clipped delta wing for pitching and control-surface p 801 N88-28898 Economical technology application in commercial [CAA-PAPER-870171 oscillations transport design MASS FLOW RATE [ NASA-TP-25941 p 798 N88-28895 [ SAWE PAPER 17981 p 809 A88-53798 Heal transfer, pressure drop, and mass flow rate in pin Low-speed longitudinal flying qualities of modern fin channels with long and short trailing edge ejection LIFT transport aircraft p 812 N88-29738 Direct lift engine for advanced V/STOL transport holes LONGITUDINAL STABILITY p 847 A88-54181 [ AlAA PAPER 88-2890A I p 816 A88-53111 [ASME PAPER 88-GT-421 Calculation of aerodynamic characteristics of airplane Theoretical investigation of the interaction between a Statorlrotor interaction in a transonic turbine configurations at high angles of attack 1 AlAA PAPER 88-30931 p 785 A88-53140 compressor and the components during surge [NASA-CR-41821 p 797 N88-28891 [ASME PAPER 88-GT-2201 p 851 A88-54305 Developments in computational methods for high-lift LOSSES MATERIALS TESTS aerodynamics p 786 A88-53250 An experimental investigation into the reasons of New materials and fatigue resistant aircraft design: LIFT AUGMENTATION reducing secondary flow losses by using leaned blades Proceedings of the Fourteenth ICAF Symposium. Ottawa. in rectangular turbine cascades with incidence angle Analysis of a fixed-pitch X-wing rotor employing lower Canada, June 8-12, 1987 p 803 A88-52651 surface blowing [ASME PAPER 88-GT-4 I p 786 A88-54151 [AD-A187379] p 800 N88-29779 LOW COST Evaluation of new materials in the design of aircraft structures p 803 A88-52654 LIFT DEVICES A multiprocessor avionics system for an unmanned Jump strut means shorter takeoff rolls research vehicle MATHEMATICAL MODELS p 803 A88-52375 IAD-Al94806l p 815 N88-29800 Modelling of aircraft program motion with application to circular loop simulation p 826 A88-53251 LIFT DRAG RATIO LOW LEVEL TURBULENCE Suction laminarizalion of highly swept supersonic Measurement and analysis of low altitude atmospheric The use of fins to reduce the pressure drop in a rotating laminar flow control wings turbulence obtained using a specially instrumented Gnat cavity with a radial inflow aircraft p 857 N88-29728 p 788 A88-54190 [ AlAA PAPER 88-4471 I p 786 A88-53762 [ASME PAPER 88-GT-581 LOW REYNOLDS NUMBER Contributions to the modeling of wind shear for danger LIFTING BODIES Transition modeling effects on viscouslinviscid Quadrature formula for a double-pole singular integral studies interaction analysis of low Reynolds number airfoil flows [ NASA-TT-20293I p 802 N88-28900 --- in linear lifting surface theory p 796 A88-55093 involving laminar separation bubbles Structural dynamics of maneuvering aircraft LIFTING ROTORS [ ASME PAPER 88-GT-321 p 787 A88-54175 IAD-Al923761 p 81 0 N88-28908 Pilotlvehicle analysis of a twin-lift helicopter A study of the effect of random input motion on low configuration in hover p 829 A88-55064 Modeling of large stall in axial compressors Reynolds number flows IVKI-TN-164 I p 853 N88-29124 LIGHT AIRCRAFT [ AD-AI 95559 I p 798 N88-29747 Status review of atmosphere turbulence and aircraft Possible future developments of motorgliders and light LOW SPEED STABILITY p 830 N88-29726 aircraft p 805 A88-52697 Low-speed longitudinal flying qualities of modern response A new source of lightweight. compact multifuel power transport aircraft p 812 N88-29738 Extreme gusts distribution p 857 N88-29734 for vehicular. light aircraft and auxiliary applications - The LOW SPEED WIND TUNNELS Advances in Flying Qualities joint Deere Score engines Effects of independent variation of Mach and Reynolds [ AGARD-LS-1571 p 785 N88-29735 [ASME PAPER 88-GT-2711 p 851 A88-54345 numbers on the low-speed aerodynamic characteristics Advances in flying qualities: Concepts and criteria for An interim comparison of operational CG records in of the NACA 0012 airfoil section a mission oriented flying qualities specification turbulence on small and large civil aircraft INASA-TM-40741 p 784 N88-28879 p 812 N88-29739 p 830 N88-29729 LUBRICANTS Minimum-complexity helicopter simulation math model LIGHTNING Principles of the use of fuels and lubricants in civil [NASA-CR-1774761 p 831 N88-29819 Investigations into the triggered lightning response of aviation --- Russian book p 838 A88-54001 Combustion and fuels in gas turbine engines the F106B thunderstorm research aircraft LUBRICATING OILS [AGARD-CP-422I p 841 N88-29910 [ NASA-CR-3902I p 856 N88-29258 Development of the T406-AD-400 oil scavenge system Numerical models for analytical predictions of combustor The 1983 direct strike lightning data, part 1 for the V-22 aircraft aerothermal performance characteristics [ASME PAPER 88-GT-2971 p 821 A88-54366 p 843 N88-29935 [ NASA-TM-86426-PT-1I p 856 N88-29259 Generation of surface grids through elliptic partial The 1983 direct strike lightning data, part 2 differential equations for aircraft and missile [ NASA-TM-86426-PT-21 p 856 N88-29260 M configurations The 1983 direct strike lightning data, part 3 [AD-A195639] p 860 N88-30378 [ NASA-TM-86426-PT-31 p 856 N88-29261 MACH NUMBER MCDONNELL DOUGLAS AIRCRAFT LINEAR PREDICTION A preliminary design study of supersonic through-flow UDF engineIMD80 flight test program Two biased estimation techniques in linear regression fan inlets [ AlAA PAPER 88-2805 p 815 A88-53104 Application to aircraft [AIAA PAPER 88-30751 p 816 A88-53137 MEASURING INSTRUMENTS I NASA-TM-1006491 p 860 N88-29489 A full Navier-Stokes analysis of a three dimensional Advanced high temperature instrumentation for hot LINEARITY hypersonic mixed compression inlet Section research applications p 846 A88-54139 An integral equation for the linearized unsteady [AIAA PAPER 88-30771 p 785 A8863138 Investigation of boundary layer transition and separation supersonic flow over a wing Test results and theoretical investigations on the ARL in an axial turbine cascade using glue-on hot-film gages [ AD-AI 937731 p 797 N88-28887 19 supersonic blade cascade [ASME PAPER 88-GT-1511 p 791 A88-54251 LININGS [ASME PAPER 88-GT-2021 p 792 A88-54289 Aerodynamics of seeing on large transport aircraft Flow in liner holes for counter-current combustion MACHINERY [NASA-CR-1831221 p 801 N88-28896 systems Rolling element bearing monitoring and diagnostics MECHANICAL PROPERTIES [ASME PAPER 88-GT-1581 p 839 A88-54257 techniques Fatigue crack growth characteristics of ARALL LIQUID ATOMIZATION [ASME PAPER 88-GT-2121 p 850 A88-54298 (trademark)-1 Atomization of alternative fuels p 842 N88-29913 MAGNETIC BEARINGS [ AD-A1961851 p 841 N88-29889 Turbulence effects on the droplet distribution behind The oil-free shaft line MECHANIZATION airblast atomizers p 842 N88-29915 [ASME PAPER 88-GT-1681 p 849 A88-54263 Mechanization of joint production during the assembly Influence of operating conditions on the atomization and of aircraft structures --- Russian book MAINTENANCE p 846 A88-53998 distribution of fuel by air blast atomizers Fuel effects on flame radiation and hot-section p 842 N88-29918 durability p 843 N88-29925 METAL COATINGS Spray performance of a vaporizing fuel injector Spray automated balancing of rotors - Concept and initial MAN MACHINE SYSTEMS feasibility study p 842 N88-29919 VSRA in-flight simulator - Its evaluation and applications The characterizatin of combustion by fuel composition [ASME PAPER 88-GT-I631 p 849 A88-54261 --- Variable Stability and Response Airplane METAL FATIGUE Measurements in a small conventional combustor [AIAA PAPER 88.46051 p 806 A88-53649 p 842 N88-29920 Fatigue crack growth characterization of let transport MAN POWERED AIRCRAFT The performance of a surrogate blend in simulating JP-4 structures p 803 A88-52653 Daedalus The making of the legend in a spray-fueled combustor p 843 N88-29926 - Fatigue of elevated temperature powder metallurgy p 784 A88-55000 LITHIUM ALLOYS aluminum alloy mechanically fastened joints Evaluation of new materials in the design of aircraft MANAGEMENT PLANNING p 837 A88-52655 structures p 803 A88-52654 Developmentand demonstration of an on-board mission Aspects of the fatigue behaviour of typical adhesively LOAD DISTRIBUTION (FORCES) planner for helicopters bonded aircraft structures p 804 A88-52659 Effect of stage loading on endwall flows in an axial flow [ NASA-CR-1774821 p 831 NEB-29817 Fatigue crack propagation test programme for the A320 compressor rotor MANEUVERABILITY wing p 804 A88-52662 1 ASME PAPER 88-GT-1111 p 848 A88-54229 Energy maneuverability and engine performance Effect of loading asymmetry on the low-cycle fatigue LOAD TESTS requirements of ZhS6F alloy under cyclic temperature changes Enstaff - A standard test sequence for composite [ASME PAPER 88-GT-303 I p 822 A88-54372 p 838 A88-53955 components combining load and environment A second look at MIL prime flying qualities AGARD engine disc cooperative test programme D 804 A88-52666 requirements p 81 2 N88-29740 IAGARD-R-7661 p 824 N88-28926 A-19 METAL FIBERS SUBJECT INDEX

METAL FIBERS MISSILE CONTROL Prediction of Compressor cascade performance using Composite monolayer fabrication by an arc-spray Feasibility study of a microprocessor controlled actuator a Navier-Stokes technique process p 845 A88-53581 test mechanism [ASME PAPER 88-GT-96) p 789 A8864217 Fiber metal acoustic materials for gas turbine exhaust [AD-At 946541 p 860 N88-29337 An efficient patched grid Navier-Stokes solution for environments MISSILE SYSTEMS multiple bodies, phase 1 I ASME PAPER 88-GT-1751 p 839 A88-54269 Aircraft avionics and missile system installation cost [AD-AI 941661 p 853 N88-29110 METAL FILMS study. Volume 1: Technical report and appendices A Lessons learned in the mesh generation for PN/S Composite monolayer fabrication by an arc-spray through E calculations p 859 N88-29314 process p 845 A88-53581 [ AD-A1946051 p 814 N88-28923 Mesh generation for industrial application of Euler and METAL MATRIX COMPOSITES MISSION PLANNING Navier Stokes solvers p 860 N88-29323 Microscopic inner damage correlated with mechanical Development and demonstration of an on-bardmission Experience with three dimensional composite grids property degradation due to simulated fatigue loading in planner for helicopters p 860 N88-29324 metal matrix composites p 837 A88-52657 [ NASA-CR-1774821 p 831 N88-29817 Three-dimensional Navier-Stokes simulations of turbine Damage tolerance aspects of an experimental Arall F-27 MODAL RESPONSE rotor-stator interaction lower wing skin panel p 804 A88-52668 Instrumentation and techniques for structural dynamics [NASA-TM-100081] p 799 N88-29750 Composite monolayer fabrication by an arc-spray and acoustics measurements Application of unsteady aerodynamic methods for process p 845 A88-53581 [AIAA PAPER 88.46671 p 845 A88-53829 transonic aeroelastic analysis METAL POWDER [ NASA-TM-1006651 p 799 "3-29754 Asymptotic modal analysis and statistical energy NiCrAVbentonite thermal spray powder for high NAVIGATION AIDS analysis temperature abradable seals p 837 A88-53556 A knowledge based system of supermaneuver selection [ NASA-CR-1830771 p 861 N88-29514 METAL SHELLS for pilot aiding Use of composite materials to repair metal structures MODEL REFERENCE ADAPTIVE CONTROL [AlAA PAPER 88-44421 p 827 A88-53755 p 804 A88-52660 A hyperstable model-followingflight control system used NAVIGATION INSTRUMENTS METALS for reconfigurationfollowing aircraft impairment ObSeNed track-keeping performance of DC10 aircraft Stress intensity factors for cracked metallic structures p 828 A88-54652 equippedwith the Collins AINS-70 area navigationsystem: under rapid thermal loading Multiplemodel parameter-adaptive control for in-flight Karlsruhe and Masstricht UACs (Upper Area Control [AD-At 912191 p 840 N88-29004 simulation p 829 A8844659 centres) MICROBURSTS (METEOROLOGY) MODELS [EEC-2021 p 803 N88-29788 Robust control strategy for take-off performance in a Constitutive modeling for isotropic materials NAVY windshear p 829 A88-54656 [ NASA-CR-I821 321 p 826 N88-29811 Navy V/STOL Engine experience in Altitude Test MICROCOMPUTERS MODULES Facility Development of a micro-computer based integrated EMPTAC (Electromagnetic Pulse Test Aircraft) user's [ASME PAPER 88-GT-3171 p 834 A8844384 design system for high altitude long endurance aircraft guide Multiple-Purpose Subsonic Naval Aircraft (MPSNA): [AlAA PAPER 88-44291 p 807 A88-53754 [AD-A195072] p 854 N88-30006 Multiple Application Propfan Study (MAPS) MICROCRACKS MOISTURE CONTENT [ NASA-CR-I751041 p 81 1 N88-28917 Microscopic inner damage correlated with mechanical Enstaff - A standard test sequence for composite NEAR FIELDS property degradation due to simulated fatigue loading in components comb ling load and environment Near-fieldpressure radiation and flow characteristicsin metal matrix composites p 837 A88-52657 p 804 A88-52666 low supersonic circular and elliptic jets MICROMECHANICS MOLECULAR STRUCTURE p 795 A88-54869 Modeling of micromechanisms of fatigue and fracture Effect of molecular structure on soot formation NEUTRON RADIOGRAPHY in hybnd materials characteristics of aviation turbine fuels Real time neutron radiography applications in gas turbine [AD-A1956041 p 855 N88-30142 [ASME PAPER 88-GT-211 p 838 A88-54167 and internal combustion engine technology MICROPHONES MONITORS [ASME PAPER 88-GT-2141 p 850 A88-54300 Noise levels from a jet-engined aircraft measured at Assessment of gas turbine vibration monitoring NICKEL ALLOYS ground level and at 1.2 m above the ground [ASME PAPER 88-GT-2041 p 850 A88-54291 NiCrAVbentonite thermal spray powder for high [NPL-AC-114] p 861 N88-29524 MOTION STABILITY temperature abradable seals p 837 A88-53556 MICROPROCESSORS An efficient patched gnd Navier-Stokes solution for Effect of loading asymmetry on the low-cycle fatigue Microprocessor functional-adaptive processing of multiple bodies, phase 1 of ZhS6F alloy under cyclic temperature changes signals of radio-navigation systems in an onboard [AD-A194166] p 853 N88-29110 p 838 A8863955 subsystem p 802 A8842952 NOISE GENERATORS Nonuniform vane spacing effects on rotor blade forced Feasibility study of a microprocessor controlledactuator response and noise generation p 796 A8844944 test mechanism N Noise generation and boundary layer effects in [ AD-AI 946541 p 860 N88-29337 NAP-OF-THE-EARTH NAVIGATION vortex-airfoil interaction and methods of digital hologram MICROSTRUCTURE Considerationsfor automated nap-ol-the-earthrotorcraft analysis for these flow fields Modeling of micromechanisms of fatigue and fracture flight p 827 A88-54526 [AD-A194191] p 797 N88-28883 in hybrid materials NASA PROGRAMS NOISE MEASUREMENT [AD-A195604] p 855 "3-30142 NASA HOST project overview --- hot section Noise levels from a jet-engined aircraft measured at MICROWAVE ANTENNAS technology p 817 A88-54138 ground level and at 1.2 m above the ground Pilotage system for the Pronaos gondola --- French Views on the impact of HOST --- hot section [NPL-AC-114] p 861 N88-29524 balloon-bornesubmillimeter telescope technology p 818 A88-54146 NOISE PREDICTION [IAF PAPER 88-008l p 809 A88-55317 SR-7A aeroelastic model design report Aircraft noise prediction program propeller analysis MIDAIR COLLISIONS [ NASA-CR-1747911 p 824 N88-28928 system IBM-PC version user's manual version 2.0 UK airmisses involving commercial air transport NASTRAN [NASA-CR-181689] p 862 N88-30399 [CAA-I/88] p 803 N88-28907 Interactive plotting of NASTRAN aerodynamic models NOISE PREDICTION (AIRCRAFT) MILITARY AIR FACILITIES using NPLOT and DISSPIA Future supersonic transport noise - Lessons from the EMPTAC (Electromagnetic Pulse Test Aircraft) user's [ AD-A 1941 15 ] p 853 N88-29204 past guide Computer programs for generation of NASTRAN and [AIAA PAPER 88.29891 p 816 A88-53121 [AD-A195072] p 854 N88-30006 VIBRA-6 aircraft models A comparison 01 simple analytical models for MILITARY AIRCRAFT [ AD-AI 954671 p 812 N88-29792 representing propeller aircraft structural and acoustic Structural design and its improvements through the NATIONAL AEROSPACE PLANE PROGRAM responses development of the XF3-30 engine Unique, clean-air, continuous-flow, [ISVR-TR-I53] p 861 N88-29523 [ASME PAPER 88-GT-261I p 821 A8864337 high-stagnation-temperature facility for supersonic NOISE PROPAGATION XG40 - Advanced combat engine technology combustion research Investigationof helicopter rotor bladelwake interactive demonstrator programme [AIAA PAPER 88-3059Al p 832 A88-53135 impulsive noise [ASME PAPER 88-GT-3001 p 821 A88-54369 Trajectory optimization and guidance law development [ NASA-CR-1774351 p 797 N88-28882 for national aerospace plane applications NOISE REDUCTION Development of the F404/RM12 for the JAS 39 p 837 A88-54567 Future supersonic transport noise - Lessons from the Gripen past [ASME PAPER 88-GT-3051 p 822 A8864374 NAVIER-STOKES EOUATION A three dimensional zonal Navier-Stokes code for [AIAA PAPER 88.29891 p 816 A88-53121 MILITARY HELICOPTERS subsonic through hypersonic propulsion flowfields Estimating fuselage weight penalty requiredto suppress Helicopter transmission research at NASA Lewis [AIM PAPER 88-28301 p 785 A88-53106 noise from propfans Research Center A full Navier-Stokesanalysis of a three dimensional [SAWE PAPER 17871 p 809 A8843790 [NASA-TM-1009621 p 855 N88-30128 hypersonic mixed compression inlet Fiber metal acoustic materials for gas turbine exhaust MILITARY TECHNOLOGY [AIM PAPER 88-30771 p 785 A88-53138 environments YA-7F. A twenty year economic life extension at costs Navier-Stokes solutions for rotating 3-0 duct flows [ASME PAPER 88-GT-1751 p 839 A88-54269 we can afford [AIAA PAPER 88-30981 p 844 A8843142 A comparison of simple analytical models for [AIM PAPER 88-44601 p 783 A8843757 CFD predictionof the reacting flow field inside a subscale representing propeller aircraft structural and acoustic Further aspects of the UK engine technology scramjet combustor responses demonstrator programme [AIAA PAPER 88-32591 p 816 A88-53151 [ISVR-TR-1531 p 861 N88-29523 [ASME PAPER 88-GT-1041 p 848 A88-54223 Laminar flow velocity and temperature distributions NONDESTRUCTIVE TESTS MISSILE CONFIGURATIONS between coaxial rotating disks of finite radius Real time neutron radiographyapplications in gas turbine Generation of surface grids through elliptic partial [ASME PAPER 88-GT-491 p 847 A88-54185 and internal combustion engine technology differential equations for aircraft and missile Developmentof a 3D Navier Stokes solver for application [ASME PAPER 88-GT-2141 p 850 A88-54300 configurations to all types of turbomachinery Cost benefits of nondestructive testing in aircraft [ AD-A1956391 p 860 N88-30378 [ASME PAPER 88-GT-701 p 788 A8864201 maintenance P 784 A88-55041

A-20 SUBJECT INDEX PREDICTION ANALYSIS TECHNIQUES

Design considerations in remote testing A contributionlo the quantitative analysis of the influence PILOT INDUCED OSCILLATION p 852 A88-55042 of design parameters on the optimal design of passenger Pilot/vehicle analysis of a twin-lift helicopter The non-destructive testing of welds in continuous fibre aircraft configurationin hover p 829 A88-55064 reinforced thermoplastics p 852 A88-55456 [ETN-88-92979] p 810 N88-28912 PILOT PERFORMANCE Evaluation of bond testing equipment for inspection of OPTOELECTRONIC DEVICES Simulator transport delay measurement using Army advanced composite airframe structures Very high speed integrated circuitsfgallium arsenide steady-state techniques [ AD-A1957951 p 841 "3.29885 electronics for aircraft engine controls [AIAA PAPER 88-46191 p 833 A88-53658 Automated early fatigue damage sensing system p 823 A88-54620 Determination of helicopter simulator time delay and its [AD-A195717] p 855 N88-30143 OSCILLATING FLOW effects on air vehicle development NONEQUlLlBRlUM THERMODYNAMICS Use of control feedback theory to understand other [AIAA PAPER 88-46201 p 833 A88-53659 oscillations Conditions of the induction-plasmatron modeling of the A knowledge based system of supermaneuver selection [ASME PAPER 88-GT-811 p 848 A88-54209 convective nonequilibrium heat transfer of bodies in for pilot aiding OSCILLATIONS hypersonic flow p 786 A88-53970 [AlAA PAPER 88-44421 p 827 A88-53755 NOSES (FOREBODIES) Steady and unsteady transonic pressure measurements on a clipped delta wing for pitching and control-surface Advances in Flying Qualities Use of composite materials to repair metal structures [AGARD-LS-157] p 785 N88-29735 p 804 A88-52660 oscillations [ NASA-TP-25941 p 798 N88-28895 Low-speed longitudinal flying qualities of modern NOZZLE DESIGN transport aircraft p 812 N88-29738 Aerodynamic and heat transfer measurements on a OVERPRESSURE transonic nozzle guide vane Response of large turbofan and turbojet engines to a Threat expert system technology advisor [NASA-CR-177479] p 831 N88-29816 [ASME PAPER 88-GT-IO] p 786 A88-54157 short-durationoverpressure NOZZLE FLOW [ASME PAPER 88-GT-2731 p 821 A88-54346 PILOT TRAINING Air flow performance of air swirlers for gas turbine fuel OXIDATION Technology of flight simulation p 805 A88-52692 nozzles Development of a test method to determine potential Artificial intelligence systems for aircraft training - An [ASME PAPER 88-GT-1081 p 848 A88-54227 peroxide content in turbine fuels. Part 2 evaluation Numerical simulation of inviscid transonic flow through [ AD-A192244 ] p 841 N88-29042 [AIAA PAPER 88-45881 p 857 A88-53637 nozzles with fluctuating back pressure OXIDATION RESISTANCE Simulator transport delay measurement using [ASME PAPER 88-GT-2871 p 794 A88-54356 Processing technology research in composites steady-statetechniques Aerodynamics in ground effect and predicted landing [AD-A1956931 p 841 N88-29890 [AlAA PAPER 88-46191 p 833 A88-53658 ground roll of a fighter configuration with a Controlleddegradation of resolutionof high-quality flight secondary-nozzle thrust reverser P simulator images for training effectivenessevaluation [NASA-TP-2834] p 799 N88-29752 [AD-A196189] p 836 N88-29823 Nozzle airflow influences on fuel patternation PARABOLIC DIFFERENTIAL EQUATIONS PITCH (INCLINATION) p 842 N88-29916 Lessons learned in the mesh generation for PNfS IMMP - A computer simulation of fuel CG versus vehicle Numerical simulation of nozzle flows calculations p 859 N88-29314 attitude [AD-AI951441 p 854 N88-30064 PARAMETER IDENTIFICATION [SAWE PAPER 18011 p 827 A88-53799 NUMERICAL INTEGRATION Estimation of aircraft parameters using filter error Time periodic control of a multi-blade helicopter Numericalintegration of the 3D unsteady Euler equations methods and extended Kalman filter [ AD-A1944351 p 829 N88-28931 for flutter analysis of axial flow compressors [DFVLR-FB-88-15] p 810 NEB-28911 PLASMA SPRAYING [ASME PAPER 88-GT-2551 p 794 A88-54331 PARTICLE EMISSION High temperature testing of plasma sprayed thermal Positron emission tomography: A new technique for barrier coatings p 845 A88-53571 0 Observing fluid behavior in engineering systems Plasma sprayed tungsten carbide-cobaltcoatings [ PNR904711 p 854 N88-30091 p 845 A88-53579 PARTICLE SIZE DISTRIBUTION 0 RING SEALS PLASMATRONS Turbulence effects on the droplet distribution behind Brushes as high performancegas turbine seals Conditions of the induction-plasmatron modeling of the airblast atomizers p 842 N88-29915 [ASME PAPER 88-GT-1821 p 850 A88-54273 convective nonequilibrium heat transfer of bodies in Influenceof operating conditions on the atomization and ONBOARDDATAPROCESSING hypersonic flow p 786 A88-53970 Trajectory optimization and guidance law development distribution of fuel by air blast atomizers p 842 N88-29918 PLASTIC AIRCRAFT STRUCTURES for national aerospace plane applications Industrial production of CFRP-components in Airbus p 837 A88-54567 PASSENGER AIRCRAFT The turboprop challenge --- design for cost-effective construction ONBOARD EQUIPMENT [SAWE PAPER 17941 p 845 A88-53795 Flight test equipment for the on-board measurement of regional-route aircraft p 805 A88-53539 High speed transpacific passenger flight Investigations on the modification of structural reliability wind turbulence p 814 N88-29719 by substitution of aluminum by carbon fiber reinforced OPERATING COSTS [AIAA PAPER 88-44841 p 807 A88-53764 plastics in aircraft construction Towards the optimum ducted UHBR engine Ultra High Weight growth in airline service --- [ILR-MITT-195] p 841 N88-29877 Bypass Ratio [SAWE PAPER 17961 p 809 A88-53797 PLOTTING [AIAA PAPER 88.29541 p 816 A88-53119 Development of a MHz RF leak detector technique for A contributionto the quantitative analysis of the influence aircraft hardness surveillance p 81 3 A88-54725 Interactive plotting of NASTRAN aerodynamic models using NPLOT and DISSPLA of design parameters on the optimal design of passenger Acontributionto thequantitativeanalysisof the influence aircraft of design parameters on the optimal design of passenger [ AD-A1941 151 p 853 N88-29204 [ ETN-88.929791 p 810 N88-28912 aircraft PNEUMATIC EQUIPMENT OPTICAL EQUIPMENT [ ETN-88-929791 p 810 N88-28912 JUH-1H redesigned pneumatic boot deicing system flight A fiber optic collective flight control system for PERFORMANCE PREDICTION test evaluation helicopters High-aspect-ratiowings p 834 N88-28859 (AD-Al949181 p 802 N88-29785 [ AD-A1 954061 p 831 N88-29818 Measured and predicted responses of the Nord 260 POINTING CONTROL SYSTEMS OPTICAL MEASUREMENT aircraft to the low altitude atmospheric turbulence Pilotage system for the Pronaos gondola --- French Optical measurement of unducted fan blade p 830 N88-29723 balloon-borne submillimeter telescope deflections Numerical models for analytical predictions of combustor [IAF PAPER 88-0081 p 809 A88-55317 [ NASA-TM-1009661 p 853 N88-29142 aerothermal performancecharacteristics POLYMER MATRIX COMPOSITES OPTICAL MEASURING INSTRUMENTS p 843 N88-29935 The non-destructivetesting of welds in continuous fibre Fiber optics for aircraft engine controls PERFORMANCE TESTS reinforced thermoplastics p 852 A88-55456 p 822 A88-54619 Controlled degradation of resolutionof high-quality flight POSITRONS OPTICAL PROPERTIES simulator images for training effectiveness evaluation Positron emission tomography: A new technique for Aerodynamics of seeing on large transport aircraft [AD-AI961891 p 836 N88-29823 observing fluid behavior in engineering systems [ NASA-CR-1831221 p 801 N88-28896 EMPTAC (Electromaanetic Pulse Test Aircraft) user's [ PNR904711 p 854 N88-30091 OPTIMAL CONTROL guide POTENTIAL FLOW A problem of optimal control with constraints on the [ AD-A1950721 p 854 N88-30006 A projection-gridscheme for calculating transonic flow coordinates of the center of mass p 858 A88-53876 PERIODIC VARIATIONS past a profile p 785 A88-52795 Active control of transient rotordynamic vibration by Time aeriodic control of a multi-blade helicoater A new singular integral approach for a vertical array of optimal control methods airfoils [AD-A194435] p 829 N88-28931 [ASME PAPER 88-GT-731 p 858 A88-54202 [ASME PAPER 88-GT-2181 p 793 A88-54303 PEROXIDES Considerationsfor automatednap-of-the-earth rotorcraft POTENTIAL THEORY Development of a test method to determine potential flight p 827 A88-54526 Numerical solution to transonic potential equations on peroxide content in turbine fuels. Part 2 Periodic neighboring optimum regulator applied to a S2 stream surface in a turbomachine [AD-A1922441 p 841 N88-29042 hypersonic scramjet cruiser p 827 A88-54528 [ASME PAPER 88-GT-821 p 789 A88-54210 Trajectory optimization and guidance law development Determination of the hydroperoxide potential of jet POWDER METALLURGY for national aerospace plane applications fuels Fatigue of elevated temperature powder metallurgy p 837 A88-54567 [ AD-A1959751 p 844 "3-29991 aluminum alloy mechanically fastened joints H(infinity)-optimaldesign for helicopter control PERSONAL COMPUTERS p 837 A88-52655 p 828 A88-54598 Aircraft noise prediction program propeller analysis PRECISION Scheduling turbofan engine control set points by system IBM-PC version user's manual version 2.0 Aerodynamic data accuracy and quality: Requirements semi-infiniteoptimization p 823 A88-54658 [ NASA-CR-1816891 p 862 N88-30399 and capabilities in wind tunnel testing OPTIMIZATION PHASE ERROR [AGARD-AR-254] p 798 N88-28893 Optimization design of the over-all dimensions of Effect of phase errors in stepped-frequency radar PREDICTION ANALYSIS TECHNIQUES centrifugalcompressor stage systems Computational tools for simulation methodologies [ASME PAPER 88-GT-1341 p 849 A88-54241 [AD-A1944761 p 853 N88-29061 p 834 NEB-28865

A-2 1 PRESSURE DISTRIBUTION SUBJECT INDEX

PRESSURE DISTRIBUTION PROPELLER EFFICIENCY QUALITY Prediction of the pressure distribution for radial inflow Aircraft noise prediction program propeller analysis Aerodynamic data accuracy and quality: Requirements between co-rotating discs system IBM-PC version user's manual version 2.0 and capabilities in wind tunnel testing [ASME PAPER 88-GT-611 p 847 A88-54193 [ NASA-CR-1816891 p 862 N88-30399 [ AGARD-AR-2541 p 798 N88-28893 Near-field pressure radiation and flow characteristics in PROPELLER FANS An analysis of lateral-directional handling qualities and low supersonic circular and elliptic lets Aeroelastic response of metallic and composite propfan Eigenstruclure of high performance aircraft p 795 A88-54869 models in yawed flow I AD-A1948741 p 831 N88-29814 Pressure distnbutions from subsonic tests of an [NASA-TM-1009641 p 825 N88-29807 advanced laminar-flow-control wing with leading- and PROPELLERS trailing-edge flaps Optical measurement of unducted fan blade R [ NASA-TM-4040-PT-21 p 800 N88-29776 deflections RADAR CROSS SECTIONS An experimental study of an adaptive-wall wind tunnel [ NASA-TM-I009661 p 853 N88-29142 ( NASA-CR-1831521 p 835 N88-29821 Effect of phase errors in stepped-frequency radar Analysis of the transmissionof sound into the passenger systems PRESSURE DROP compartmentof a propeller aircraft using the finite element Heat transfer. pressure drop, and mass flow rate in pin [AD-A1944761 p 853 N88-29061 method RADAR MAPS Iin channels with long and short trailing edge ejection [FFA-TN-1988-151 p 861 N88-29520 holes Processing pseudo synthetic aperture radar images from A comparison of simple analytical models for [ASME PAPER 88-GT-421 p 847 A88-54181 visual terrain data representing propeller aircraft structural and acoustic The use of fins 10 reduce the Pressure drop in a rotatinq [AIAA PAPER 88-45761 p 802 A88-53628 responses cavity with a radial inflow RADARRANGE [ISVR-TR-I 531 p 861 N88-29523 [ASME PAPER 88-GT-581 p 788 A88-54190 Effect of phase errors in stepped-frequency radar PRESSURE GRADIENTS Euler analysis of a swirl recovery vane design for use systems Design point variation of 3-D loss and deviation for axial with an advanced single-rotation propfan [AD-A194476] p 853 NEB-29061 compressor middle stages [NASA-TM-1013571 p 800 N88-29771 RADIAL FLOW (ASME PAPER 88-GT-571 p 787 A88-54189 PROPULSION SYSTEM CONFIGURATIONS The use of fins lo reduce the pressure drop in a rotating PRESSURE MEASUREMENT ATR propulsion system design and vehicle integration cavity with a radial inflow Acquisition of unsteady pressure measurements from --- AirTurboRamjet [ ASME PAPER 88-GT-581 p 788 A88-54190 a high speed multi-stage compressor [ AIAA PAPER 88-3071] p 816 A8863136 Flow in single and twin entry radial turbine volutes [ASME PAPER 88-GT-1891 p 833 A88-54280 Propulsion system integration for Mach 4 to 6 vehicles [ASME PAPER 88-GT-591 p 847 A88-54191 Steady and unsteady transonic pressuremeasurements [AIAA PAPER 88-3239A1 p 805 A88-53149 Prediction of the pressure distribution for radial inflow between co-rotating discs on a clipped delta wing for pitching and control-surface Real time simulatorsfor use in design of integrated flight oscillations and propulsion control systems [ASME PAPER 88-GT-611 p 847 A88-54193 INASA-TP-25941 p 798 N88-28895 [ASME PAPER 88-GT-241 p 818 A88-54168 Prediction of compressor cascade performance using a Navier-Stokestechnique PRESSURESENSORS Experimental and analytical evaluation of the effects of [ASME PAPER 88-GT-961 p 789 A88-54217 Preliminary definition of pressure sensing requirements simulated engine inlets on the blade vibratory stresses for hypersonic vehicles of the SR-3 model prop-fan Three dimensional flow in radial-inflow turbines [AIAA PAPER 88-46521 p 81 3 A88-53826 [ NASA-CR-1749591 p 824 N88-28927 [ASME PAPER 88-GT-1031 p 790 A88-54222 PROCESS CONTROL (INDUSTRY) PROPULSION SYSTEM PERFORMANCE RADIATION EFFECTS Avionics system design for high energy fields: A guide Hypervelocity application of tribological coatings Testing of the 578-DX propfan propulsion system p 845 A8863563 [AIAA PAPER 88-28041 p 815 A88-53103 for the designer and airworthiness specialist Predicting, determining. and controlling manufacturing INASA-CR-1815901 p 814 N88-28919 Combined engines for future launchers variation in a new facility --- aircraft production RADIATION HARDENING [AIAA PAPER 88-28231 p 836 A8843105 [SAWE PAPER 17711 p 783 A88-53782 EMPTAC (Electromagnetic Pulse Test Aircraft) user's A three dimensional zonal Navier-Stokes code for PRODUCT DEVELOPMENT guide subsonic through hypersonic propulsion flowfields Assessment, development, and application of [ AD-AI950721 p 854 N88-30006 [AIAA PAPER 88-28301 p 785 A88-53106 combustor aerothermal models p 817 A88-54140 RADIATIVE HEAT TRANSFER A UK perspective on Engine Health Monitoring (EHM) Development of a glass fiber wing following the Radiation transfer in gas turbine combustors systems for future technology military engines construction regulation FAR Pari 23 p 843 N88-29929 ETN-88-929661 p 840 N88-28979 [ASME PAPER 88-GT-1481 p 81 9 A88-54249 I RADIO ASTRONOMY Design aspects of recent developments in Rolls-Royce PRODUCTION ENGINEERING Pilotage system for the Pronaos gondola --- French RE211-524 powerplants Industrial production of CFRP-components In Airbus balloon-borne submillimeter telescope [ASME PAPER 88-GT-301I p 821 A88-54370 construction [IAF PAPER 88-0081 p 809 A88-55317 [SAWE PAPER 17941 p 845 A88-53795 Development of the F404lRM12 for the JAS 39 RADIO NAVIGATION PRODUCTION MANAGEMENT Gnpen Microprocessor functional-adaptive processing of The CFM56 engine family - An internal development [ASME PAPER 88-GT-3051 p 822 A8844374 [ASME PAPER 88-GT-2961 p 862 A88-54365 signals of radio-navigation systems in an onboard Evaluation of potential engine concepts for a high subsystem p 802 A88-52952 PROGRAMMING LANGUAGES altitude long endurance vehicle RADIO TELESCOPES Development of a micro-computer based integrated [ASME PAPER 88-GT-321 I p A88-54386 822 Pilotage system for the Pronaos gondola --- French design system for high altitude long endurance aircraft PROPULSIVE EFFICIENCY [AIM PAPER 88-44291 p A88-53754 balloon-borne submillimeter telescope 807 Towards the optimum ducted UHBR engine --- Ultra High PROP-FAN TECHNOLOGY [IAF PAPER 88-0081 p 809 A88-55317 Bypass Ratio RADIOGRAPHY Testing of the 578-DX propfan propulsion system [AIAA PAPER 88-29541 p 816 A88-53119 Development of graded reference radiographs for [AIAA PAPER 88-28041 p 815 A88-53103 PROTECTIVE COATINGS aluminum welds, phase 1 UDF engineIMD80 flight test program New version antistatic coating tester [ ADA1955941 p 855 N88-30140 [AIAA PAPER 88-28051 p 815 A88-53104 p 844 A8843166 RAMJET ENGINES Estimatingfuselage weight penalty requiredto suppress NiCrAllbentonite thermal spray powder for high noise from propfans temperature abradable seals p 837 A88-53556 ATR propulsion system design and vehicle integration [SAWE PAPER 17871 p 809 A88-53790 --- AirTurboRamjet Hypervelocityapplication of tribological coatings [AIAA PAPER 88-30711 Evaluation of potential engine concepts for a high p 845 A88-53563 p 816 A8843136 altitude long endurance vehicle Experimental and theoretical aspects of thick thermal Propulsion system integration for Mach 4 lo 6 vehicles [ASME PAPER 88-GT-3211 p 822 A8844386 barrier coatings for turbine applications [AIAA PAPER 88-3239Al p 805 A88-53149 Multiple-Purpose Subsonic Naval Aircraft (MPSNA): p 837 A88-53566 Review of research concerning Solid Fuel Ramjet Multiple Application Propfan Study (MAPS) Surface engineering for high temperature (SOFRAM) at the Research Institute of National Defence [ NASA-CR-I751 04 I p 81 1 NEB-28917 environments p 845 A88-53840 (FOA) 2 Test results at transonic speeds on a contoured Corrosion and protection of gas turbine blades --- [ FOA-C-20714-2.1] p 826 N88-29813 over-the-wing propfan model Russian book p 838 A88-53996 RANDOM NUMBERS [ NASA-TM-882061 p 811 N88-28918 Life modeling of thermal barrier coatings for aircraft gas A study of the effect of random input motion on low SR-7A aeroelastic model design report turbine engines p 838 A8844145 Reynolds number flows (NASA-CR-I74791 I p 824 N88-28928 New erosion resistant Compressor coatings 1 AD-AI955591 p 798 N88-29747 Optical measurement of unducted fan blade [ASME PAPER 88-GT-1861 p 839 A8844277 RANDOM PROCESSES deflections Processing technology research in composites Prediction of the extreme values of the phase [ NASA-TM-1009661 p 853 N88-29142 [AD-A195693 1 p 841 N88-29890 coordinates of stochastic systems p 857 A88-52823 Euler analysis of a swirl recovery vane design for use PULSE HEATING RANDOM VIBRATION with an advanced single-rotation propfan Stress intensity factors for cracked metallic structures Prediction of turbulence generated random vibrational [ NASA-TM-1013571 p 800 N88-29771 under rapid thermal loading response of turbomachinery blading p 796 A8864946 [AD-A1912191 p 840 N88-29004 REAL TIME OPERATION PROPELLANT PROPERTIES PYLONS Fuel properly eflects on the US Navy's TF30 engine Real-time simulation of helicopters using the blade p 826 N88-29911 Compression pylon element method [NASA-CASE-LAR-13777-11 p 812 N88-29789 The characterizatin of combustion by fuel composition: [AIAA PAPER 88-45821 p 805 A88-53634 Measurements in a small conventional combustor The Langley Advanced Real-Time Simulation (ARTS) p 842 N88-29920 Q system PROPELLER BLADES [AIAA PAPER 88-45951 p 832 A88-53642 Real-time Simulation of helicopters using the blade QUADRATURES Real-time simulation - A tool for development and element method Quadrature formula for a double-pole singular integral verification [AIAA PAPER 88-45821 p 805 A8843634 --- in linear lifting surface theoty p 796 A88-55093 [AIAA PAPER 88-46181 p 833 A88-53657

A-22 SUBJECT INDEX ROTOR SPEED

Real time simulatorsfor use in design of integrated flight RESONANT FREQUENCIES ROTATING STALLS and propulsion control systems Design optimizationof gas turbine blades with geometry The vortex-filament nature of the reverse flow on the [ASME PAPER 88-GT-241 p 818 A88-54168 and natural frequency constraints verge of rotating stall Intelligent fault diagnosis and failure management of [ASME PAPER 88-GT-1051 p 818 A88-54224 [ASME PAPER 88-GT-1201 p 848 A88-54234 flight control actuation systems RETROFllTlNG Experimental investigation of rotating stall in a [NASA-CR-t77481 1 p 812 N88-29790 Weight growth in airline service mismatched three stage axial flow compressor RECTANGULAR WIND TUNNELS [SAWE PAPER 17961 p 809 A8843797 [ASME PAPER 88-GT-205I p 850 A88-54292 Flow visualization on a small scale Aircraft avionics and missile system installation cost Theoretical investigation of the interaction between a [ AD-A1947281 p 835 "3.28935 study. Volume 1: Technical report and appendices A compressor and the components during surge REDUNDANCY through E [ASME PAPER 88-GT-2201 p 851 A88-54305 [AD-A194605) p 814 N88-28923 Fault detection in multiply-redundant measurement Numerical results for axial flow compressor instability REVERSED FLOW systems via requential testing p 852 A88-54566 [ASME PAPER 88-GT-2521 p 851 A88-54328 The vortex-filament nature of the reverse flow on the Investigationson the modification of structural reliability verge of rotating stall A mapping of the viscous flow behavior in a controlled by substitution of aluminum by carbon fiber reinforced [ASME PAPER 88-GT-I201 p 848 A88-54234 diffusion compressor cascade using laser Doppler plastics in aircraft construction REYNOLDS NUMBER velocimetry and preliminary evaluation of codes for the [ ILR-MITT-1951 p 841 N88-29877 The application of cryogenics to high Reynolds number prediction of stall REFRACTORY MATERIALS testing in wind tunnels. II - Development and application [AD-A194490] p 853 N88-29112 NiCrAlfbentonite thermal spray powder for high of the cryogenic wind tunnel concept Modeling of large stall in axial compressors temperature abradable seals p 837 A88-53556 p 833 A88-53847 [VKI-TN-I 641 p 853 N88-29124 REGRESSION ANALYSIS The effects of turbulence and statorfrotor interactions ROTOR AERODYNAMICS Two biased estimation techniques in linear regression: on turbine heat transfer. II - Effects of Reynolds number Control of rotor aerodynamically forced vibrations by Application to aircraft and incidence splitters p 815 A88-52684 [ NASA-TM-100649) p 860 N88-29489 [ASME PAPER 88-GT-51 p 846 A88-54152 Analysis of rotor tip clearance loss in axial-flow RELIABILITY ANALYSIS Effect of free-stream turbulence. Reynolds number, and turbines p 785 A88-52685 Investigationson the modification of structural reliability incidence on axial turbine cascade performance Statorfrotor interaction in a transonic turbine by substitution of aluminum by carbon fiber reinforced [ASME PAPER 88-GT-1521 p 791 A88-54252 [AIAA PAPER 88-30931 p 785 A88-53140 plastics in aircraft construction The effect of the Reynolds number on the The relative merits of an inviscid Euler 3-D and quasi-3-D [ILR-MITT-t 951 p 841 N88-29877 three-dimensionalflow in a straight compressor cascade analysis for the design of transonic rotors RELIABILITY ENGINEERING [ASME PAPER 88-GT-2691 p 794 A88-54343 [ASME PAPER 88-GT-691 p 788 A88-54200 Toward improved durability in advanced aircraft engine RIGID ROTOR HELICOPTERS Wake-boundary layer interactions in an axial flow turbine hot sections; Proceedings of the Thirty-third ASME Time periodic control of a multi-blade helicopter rotor at off-design conditions International Gas Turbine and Aeroengine Congress and [AD-A1944351 p 829 N88-28931 [ASME PAPER 88-GT-2331 p 793 A88-54315 Exposition. Amsterdam, Netherlands. June 5-9, 1988 ROBUSTNESS (MATHEMATICS) ROTORBLADES p 817 A88-54137 A hyperstablemodel-following flight control system used Aerodynamically forced response of structurally Intelligent fault diagnosis and failure management of for reconfiguration following aircraft impairment mistuned bladed disks in subsonic flow flight control actuation systems p 828 A88-54652 p 795 A88-54943 [ NASA-CR-1774811 p 81 2 N88-29790 Automateddesign of continuously-adaptivecontrol -The Dynamics of helicopter rotors p 809 A88-54954 RELUCTANCE 'super-controller' strategy for reconfigurable systems ROTOR BLADES (TURBOMACHINERY) High temperature, lightweight, switched reluctance p 829 A88-54653 Control of rotor aerodynamically forced vibrations by motors and generators for future aircraft engine Robust control strategy for take-off performance in a splitters p 815 A88-52684 applications p 823 A88-54623 windshear p 829 A88-54656 Analysis of rotor tip clearance loss in axial-flow REMOTE CONTROL ROCKET ENGINE DESIGN turbines p 785 A88-52685 Design considerations in remote testing Combined engines for future launchers p 852 A88-55042 Turbulence measurementsin a multistage low-pressure [AIAA PAPER 88-28231 p 836 A88-53105 turbine REMOTELY PILOTED VEHICLES ROLL [ASME PAPER 88-GT-791 p 788 A88-54207 Stratified Charge Rotary Engines for aircraft IMMP -A computer simulation of fuel CG versus vehicle Calculation of complete three-dimensional flow in a [ASME PAPER 88-GT-3111 p 822 A8844379 attitude centrifugal rotor with splitter blades Developmentand design of windtunnel and test facility [SAWE PAPER 18011 p 827 A88-53799 [ASME PAPER 88-GT-931 p 789 A88-54216 for RPV (Remote Piloted Vehicle) enhancement devices Aerodynamics in ground effect and predicted landing The influence of turbine clearance gap leakage on [AD-A194842] p 836 N88-29822 ground roll of a fighter configuration with a passage velocity and heat transfer near blade tips. I - Sink RESEARCH AIRCRAFT secondary-nozzlethrust reverser flow effects on blade pressure side - Overview of LockheedC-130 High Technology Test Bed [ NASA-TP-28341 p 799 N88-29752 [ASME PAPER 88-GT-981 p 790 A88-54218 program Computer programs for calculation of sting pitch and Three dimensional flow in radial-inflow turbines [SAWE PAPER 17861 roll angles required to obtain angles of attack and sideslip CASME PAPER 88-GT-1031 p 790 A88-54222 Development of the F404lRM12 for the JAS 39 on tunnel models Fully scaled transonic turbine rotor heat transfer Gripen [ NASA-TM-1006591 p 835 N88-29820 measurements [ASME PAPER 88-GT-3051 p 822 A88-54374 ROLLER BEARINGS LASME PAPER 88-GT-1711 p 849 A88-54265 Investigations into the triggered lightning response of Rolling element bearing monitoring and diagnostics Surface heat transfer fluctuations on a turbine rotor blade the F106B thunderstorm research aircraft techniques due to upstream shock wave passing [ NASA-CR-39021 p 856 N88-29258 [ASME PAPER 88-GT-2121 p 850 A88-54298 [ASME PAPER 88-GT-1721 p 791 A88-54266 The NAE atmospheric research aircraft Experimental investigation of rotating stall in a ROTARY ENGINES p 815 N88-29730 mismatched three stage axial flow compressor Stratified Charge Rotary Engines for aircraft RESEARCH ANDDEVELOPMENT [ASME PAPER 88-GT-2051 p 850 A8844292 [ASME PAPER 88-GT-311I p A88-54379 Possible future developments of motorgliders and light 822 Influence of deposit on the flow in a turbine cascade aircraft p 805 A88-52697 ROTARY WING AIRCRAFT [ASME PAPER 88-GT-2071 p 792 A8844293 Some key considerations for high-speed civil Design concepts for an Advanced Cargo Rotorcraft Tip leakage in a centrifugal impeller transports [AIAA PAPER 88.44961 p 807 A88-53768 [ASME PAPER 88-GT-2101 p 792 A88-54296 [AIAA PAPER 88.44661 p 783 A88-53760 ROTARY WINGS A comparison between measurements and turbulence History of aeroelasticity in Germany from the beginning Dynamics of helicopter rotors p 809 A88-54954 models in a turbine cascade passage to 1945 An unsteady helicopter rotor: Fuselage interaction [ASME PAPER 88-GT-2261 p 793 A88-54309 [ESA-TT-10821 p 799 N88-29767 analysis Turbulence measurements and secondary flows in a RESEARCH FACILITIES [NASA-CR-4178] p 784 N88-28880 turbine rotor cascade Unique, c Ie a n - ai r , continuous-flow. .JUH-1H redesignedpneumatic boot deicing system flight [ASME PAPER 88-GT-2441 p 794 A88-54323 high-stagnation-temperature facility for supersonic test evaluation Thermal barrier coatings for jet engines combustion research [ AD-A19491 81 p 802 N88-29785 [ASME PAPER 88-GT-2791 p 840 A88-54351 [AIAA PAPER 88-3059A1 p 832 A88-53135 ROTATING CYLINDERS Nonuniform vane spacing effects on rotor blade forced Helicopter transmission research at NASA Lewis Boundary-layer flows in rotating cavities response and noise generation p 796 A88-54944 Research Center [ASME PAPER 88-GT-2921 p 852 A88-54361 SR-7A aeroelastic model design report [NASA-TM-100962] p 855 N88-30128 ROTATING DISKS [ NASA-CR-I74791 1 p 824 N88-28928 RESEARCHMANAGEMENT Laminar flow velocity and temperature distributions ROTOR BODY INTERACTIONS Helicopter transmission research at NASA Lewis between coaxial rotating disks of finite radius On the prediction of unsteady forces on gas-turbine Research Center [ASME PAPER 88-GT-491 p 847 A88-54185 blades. I - Typical results and potential-flow-interaction [ NASA-TM-1009621 p 855 N88-30128 effects The use of fins to reduce the pressure drop in a rotating RESEARCH VEHICLES [ASME PAPER 88-GT-891 p 789 A88-54213 cavity with a radial inflow An airborne system for vortex flow visualization on the ROTOR SPEED [ASME PAPER 88-GT-581 p 788 A88-54190 F-18 high-alpha research vehicle Effect of stage loading on endwall flows in an axial flow [AIAA PAPER 88.46711 p 813 A88-53830 Prediction of the pressure distribution for radial inflow compressor rotor A multiprocessor avionics system for an unmanned between co-rotating discs [ASME PAPER 88-GT-1111 p 848 A88-54229 research vehicle [ASME PAPER 88-GT-611 p 847 A88-54193 Spray automated balancingof rotors - Concept and initial [AD-A1948061 p 81 5 N88-29800 ROTATING FLUIDS feasibility study RESIDUAL STRESS Navier-Stokes solutions for rotating 3-D duct flows [ASME PAPER 88-GT-1631 p 849 A88-54261 Calculation of stress relaxation in the surface-hardened [AIAA PAPER 88-30981 p 844 A88-53142 Experimental investigation of rotating stall in a layer near a hole in the disk of a gas-turbine engine Boundary-layer flows in rotating cavities mismatched three stage axial flow compressor p 846 A88-53961 [ASME PAPER 88-GT-2921 p 852 A88-54361 [ASME PAPER 88-GT-2051 p 850 A88-54292

A-23 ROTORS SUBJECT INDEX

ROTORS Turbulence measurements and secondary flows in a Aerodynamics in ground effect and predicted landing The effects of turbulence and statorlrotor interactions turbine rotor cascade ground roll of a fighter configuration with a on turbine heat transfer. II - Effects of Reynolds number [ASME PAPER 88-GT-2441 p 794 A88-54323 secondary-nozzle thrust reverser and incidence SECONDARYRADAR [ NASA-TP-28341 p 799 N88-29752 [ASME PAPER 88-GT-51 p 846 A88-54152 Fine resolution errors in secondary surveillance radar SHROUDED TURBINES Active control of transient rotordynamic vibration by altitude reporting Investigation into the effect of tip clearance on optimal control methods [ RSRE-870191 p 802 N88-28906 centrifugal compressor performance [ASME PAPER 88-GT-731 p 858 A88-54202 SELF ADAPTIVE CONTROL SYSTEMS [ASME PAPER 88-GT-1901 p 850 A88-54281 Investigation of helicopter rotor bladelwake interactive Automated design of continuously-adaptivecontrol - The Boundary-layer flows in rotating cavities impulsive noise 'super-conlroller' strategy for reconfigurablesystems [ASME PAPER 88-GT-2921 p 852 A88-54361 [NASA-CR-I774351 p 797 N88-28882 p 829 A88-54653 SIDE INLETS The effects of inlet turbulence and rotorlstator SELF REPAIRING DEVICES Hot-wire measurements of compressor blade wakes in interactions the aerodynamics and heat transfer a on of Detection, identification and estimation of surface a cascade wind tunnel large-scale rotatingturbine model. Volume 3: Heat transfer damagelactuator failure for high performance aircraft [ADA1947371 p 835 N88-28936 data tabulation 65 percent axial spacing p 828 A88-54650 SIDESLIP [NASA-CR-1794681 p 824 N88-28930 Angle of anack and sideslip estimation using an inertial SEMICONDUCTOR DEVICES Three-dimensional Navier-Stokesamulations of tufb~ne reference platform rotor-statorinteraction The characterization of high temperature electronicsfor future aircraft engine digital electronic control systems [AD-A1948761 p 799 N88-29769 [NASA-TM-100081I p 799 N88-29750 Computer programs for calculation of sting pitch and p 823 A88-54621 The effects of inlet turbulence and rotorlstator roll angles required to obtain angles of anack and sideslip interactions on the aerodynamics and heat transfer of a SEPARATED FLOW on wind tunnel models An experimental investigation into the influenceof blade large-scale rotating turbine model. Volume 2: Heat transfer [NASA-TM-100659] p 835 N88-29820 data tabulation. 15 percent axial spacing leaning on the losses downstream of annular cascades SIGNAL PROCESSING [NASA-CR-1794671 p 825 N88-29804 with a small diameter-height ratio Microprocessor functional-adaptive processing of Spray automated balancing of rotors: Methods and [ASME PAPER 88-GT-191 p 786 A88-54165 signals of radio-navigation systems in an onboard materials Numerical simulation of nozzle flows subsystem p 802 A8842952 [ NASA-CR-182151] p 836 N88-29825 [AD-A1951441 p 854 N88-30064 SIGNAL TO NOISE RATIOS RUBBER SEQUENTIAL ANALYSIS Effect of phase errors in stepped-frequency radar Determination of the hydroperoxide potential of jet Fault detection in multiply-redundant measurement systems fuels systems via sequential testing p 852 A88-54566 [AD-A1944761 p 853 N88-29061 [AD-A195975] p 844 N88-29991 SERVICE LIFE SIKORSKY AIRCRAFT RUNWAYS Damage tolerance in pressurized fuselages The RTM322 engine in the S-70C helicopter Improvement of head-up display standards. Volume 5: p 803 A88-52652 [AIAA PAPER 88-45761 p 817 A88-53774 Head up display ILS (Instrument Landing System) accuracy A comparison of engine design life optimization results Advanced Composite Airframe Program (ACAP) - An flight tests using deterministic and probabilistic life prediction update and final assessment of weight saving potential [AD-AI946021 p 814 N88-28922 techniques [SAWE PAPER 17701 p 808 A88-53781 Airport surface traffic automation study [ASME PAPER 88-GT-2591 p 820 A8844335 SILICON CARBIDES [AD-AI945531 p 835 N88-28934 Service failure of a 7049 T73 aluminum aircraft forging Microscopic inner damage correlated with mechanical An analysis of time and space requirements for aircraft p 840 A88-55286 property degradation due lo simulated fatigue loading in turnrounds Fuel effects on flame radiation and hot-section metal matrix composites p 837 A88-52657 [TT-8705] p 802 N88-29783 Whisker orientation measurements in injection molded durability p 843 N88-29925 Si3N4-SiC composites SHAFTS (MACHINE ELEMENTS) [ASME PAPER 88-GT-1931 p 839 A88-54282 S The oil-free shaft line Processing technology research in composites [ASME PAPER 88-GT-1681 p 849 A88-54263 [AD-A1956931 p 841 N88-29890 SAFETY SHAPE CONTROL SILICON NITRIDES Avionics system design for high energy fields: A guide Influence of deposit on the flow in a turbine cascade Whisker orientation measurements in injection molded for the designer and airworthiness specialist [ASME PAPER 88-GT-2071 p 792 A88-54293 Si3N4-SiC composites [ NASA-CR-I81 5901 p 814 N88-28919 SHEARLAYERS [ASME PAPER 88-GT-1931 p 839 A8844282 SAFETY FACTORS Aerodynamics of seeing on large transport aircraft SIMILARITY THEOREM Navy application of a standard fatigue and engine [ NASA-CR-1831221 p 801 N88-28896 A useful similarity principlefor jet engine exhaust system monitoring system SHOCK LAYERS performance [AIAA PAPER 88-3315) p 813 A88-53156 Three-dimensional hypersonic viscous shock layer on [AIAA PAPER 88-30011 p 816 A88-53122 Ultimate factor for structural design of modern fighters blunt bodies in flow a1 angles of attack and sideslip SIMULATION [SAWE PAPER 17751 p 808 A88-53784 p 786 A88-53971 Boundary layer simulation and control in wind tunnels A profile of US Air Force aircraft mishap investigation SHOCK TUNNELS [ AGARD-AR-224] p 784 N88-28857 p 801 A88-55288 Transport-typeconfigurations p 809 N88-28867 SANDWICH STRUCTURES Gas turbine studies at Oxford 1969-1987 [ASME PAPER 88-GT-1121 p 848 A8844230 SINGULAR INTEGRAL EQUATIONS Impact and damage tolerance properties of CFRP Quadrature formula for a double-pole singular integral sandwich panels - An experimental parameter study for SHOCK WAVE INTERACTION Detection of separation bubbles by infrared images in --- in linear lifting surface theory p 796 A88-55093 the Fokker 100 CA-EP flap p 804 A88-52671 SIZE DETERMINATION SCALE MODELS transonic turbine cascades [ASME PAPER 88-GT-331 p 787 A88-54176 Gas turbine smoke measurement A smoke generator A new method of modeling underexpanded exhaust for the assessment of current and future techniques plumes for wind tunnel aerodynamic testing Application of a hybrid analyticallnumerical method to the practicalcomputation of supercritical viscouslinviscid p 843 N88-29930 [ASME PAPER 88-GT-2881 p 834 A8844357 SKIN FRICTION transonic flow fields p 795 A88-54907 Flow visualization on a small scale Development and design of windtunnel and test facility [AD-A1947281 p 835 N88-28935 Efficient Euler solver with many applications for RPV (Remote Piloted Vehicle) enhancement devices p 798 A88-55078 Test of an 0.8-scale model of the AH-64 Apache in the [ADA1948421 p 836 N88-29822 NASA Langley full-scale wind tunnel Noise generation and boundary layer effects in SLENDER WINGS [AD-A1961291 p 799 NEB-29788 vortex-airfoilinteraction and methods of digital hologram High-aspect-ratiowings p 834 N88-28859 SCHEDULING analysis for these flow fields Delta wing configurations p 796 N88-28860 Scheduling turbofan engine control set points by [ AD-A1941 91 ] p 797 N88-28883 SLOPES semi-infinite optimization p 823 A88-54658 Numerical simulation of nozzle flows A preliminary investigation of drag reduction and SEALS (STOPPERS) [ AD-A1951 441 p 854 N88-30064 mechanism for a blunt body of revolution with slanted NiCrAllbentonite thermal spray powder for high SHOCK WAVE PROPAGATION base temperature abradable seals p 837 A88-53556 Numerical solution to transonic potential equations on [ NASA-TT-203491 p 799 N88-29753 SEATS S2 stream surface in a turbomachine SMOKE Helicopter crew seat failure analysis [ASME PAPER 88-GT-821 p 789 A88-54210 Smoke hoods: Net safety benefit analysis --- aircraft p 801 A88-55290 Surface heat transfer fluctuationson a turbine rotor blade accidents SECONDARY FLOW due to upstream shock wave passing [CAA-PAPER-87017] p 801 N88-28898 Flow visualization on a small scale An experimental investigation into the reasons of [ASME PAPER 88-GT-1721 p 791 A88-54266 reducing secondary flow losses by using leaned blades Etfect of shock wave movement on aerodynamic [AD-AI947281 p 835 N88-28935 Flow visualization by laser sheet in rectangular turbine cascades with incidence angle instability of annular cascade oscillating in transonic flow [AD-A194481] [ASME PAPER 88-GT-41 p 786 A88-54151 [ASME PAPER 88-GT-1871 p 792 A8844278 p 853 N88-29111 SHOCK WAVES Gas turbine smoke measurement: A smoke generator Design point variation of 3-D loss and deviation for axial Numerical solution of the hypersonic viscous shock layer for the assessment of current and future techniques compressor middle stages equations with chemical nonequilibrium p 843 N88-29930 [ASME PAPER 88-GT-571 p 787 A8844189 [IAF PAPER ST-88-08] p 796 A8845313 SOFTWARE TOOLS Prediction of cowressor cascade performance using SHORT TAKEOFF AIRCRAFT The application of artificial intelligence technology to a Navier-Stokes technique Jump strut means sholler takeoff rolls aeronauticalsystem design [ASME PAPER 88-GT-961 p 789 A88-54217 p 803 A8842375 [AIAA PAPER 88-44261 p 806 A8843752 Three dimensional flow in radial-inflowturbines Development. analysis, and flght test of the Lockheed Application of AI methods to aircraft guidance and [ASME PAPER 88-GT-1031 p 790 A8844222 Aeronautical System Company HTTB HUD control p 827 A88-54424 A comparison between measurements and turbulence [AIAA PAPER 88-4511 ] p 813 A8843772 SOLID-SOLID INTERFACES models in a turbine cascade passage Lockheed HTTB - STOL performance features Turbomachinery alloys affected by Solid particles [ASME PAPER 88-GT-2261 p 793 A8844309 [SAWE PAPER 17721 p 808 A88-53783 [ASME PAPER 88-GT-2951 p 840 A88-54364

A-24 SUBJECT INDEX SUPERSONIC AIRFOILS

' SONIC BOOMS The effects of inlet turbulence and rotorlstator Structural design and its improvements through the Future supersonic transport noise Lessons from the interactions on the aerodynamics and heat transfer of a development of the XF3-30 engine past large-scalerotating turbine model. Volume 3: Heat transfer [ASME PAPER 88-GT-2611 p 821 A88-54337 [AIAA PAPER 88.29891 p 816 A88-53121 data tabulation 65 percent axial spacing Comparison of the influence of different gust models ~ SOOT [ NASA-CR-1794681 p 824 N88-28930 on structural design p 81 1 N88-29722 Effect of molecular structure on soot formation Three-dimensionalNavier-Stokes simulations of turbine STRUCTURAL DESIGN CRITERIA characteristics of aviation turbine fuels rotor-stator interaction New materials and fatigue resistant aircraft design; [ASME PAPER 88-GT-211 p 838 A88 54167 [NASA-TM-100081] p 799 N88-29750 Proceedingsof the Fourteenth ICAF Symposium, Ottawa. Notes on the occurrence and determination of carbon The effects of inlet turbulence and rotorlstator Canada, June 8-12. 1987 p 803 A88-52651 within gas turbine combustors interactions on the aerodynamics and heat transfer of a Advanced Composite Airframe Program (ACAP) - An [ASME PAPER 88-GT-1641 p 839 A88-54262 large-scalerotating turbine model. Volume 2: Heat transfer update and final assessment of weight saving potential The performance of a surrogate blend in simulating the data tabulation. 15 percent axial spacing 1 [SAWE PAPER 17701 p 808 A88-53781 sooting behavior of a practical. distillate JP-4 [ NASA-CR-I794671 p 825 N88-29804 Ultimate factor for structural design of modern fighters [ASME PAPER 88-GT-1941 p 840 A88-54283 STEADY FLOW Combustion and fuels in gas turbine engines An efficient patched grid Navier-Stokes solution for [SAWE PAPER 17751 p 808 A88-53784 1 [AGARD-CP-422] p 841 N88-29910 multiple bodies, phase 1 Design optimization of gas turbine blades with geometry The performanceof a surrogate blend in simulatingJP-4 (AD-A1941661 p 853 "3-291 10 and natural frequency constraints in a spray-fueledcombustor p 843 N88-29926 Contamination and distortion of steady flow field induced [ASME PAPER 88-GT-I05] p 81 8 A8844224 SOUND TRANSMISSION by discrete frequency disturbances in aircraft gas SR-7A aeroelastic model design report Analysis of the transmissionof sound into the passenger engines [NASA-CR-174791] p 824 N88-28928 I compartmentof a propeller aircraft using the finite element [ AD-A1954401 p 854 N88-30069 STRUCTURAL FAILURE 1 method STEADY STATE Caring for the high-time jet p 801 A88-53540 [FFA TN 1988.151 p 861 N88-29520 Simulator transport delay measurement using The development of acoustic emission for structural SPACE SHUTTLE MISSIONS steady-state techniques integrity monitoring of aircraft NASA Shuttle Training Aircraft flight simulation [AIAA PAPER 88-46191 p 833 A88-53658 [AD-A1962641 p 861 N88-30398 overview Steady and unsteady transonic pressuremeasurements STRUCTURAL RELIABILITY [AIM PAPER 88-46081 p 806 A88-53650 on a clipped delta wing for pitching and control-surface Automated early fatigue damage sensing system SPACE TRANSPORTATION SYSTEM oscillations [ AD-A19571 7 1 p 855 N88-30143 Combined engines for future launchers [NASA-TP-25941 p 798 N88-28895 STRUCTURAL VIBRATION [AIAA PAPER 88.28231 p 836 A88-53105 STEP FUNCTIONS The minimisation of helicopter vibration through blade SPECTRUM ANALYSIS Effect of phase errors in stepped-frequency radar design and active control p 805 A8843249 A study of aerodynamic noise from a contra-rotating systems Use of control feedback theory to understand other axial compressor stage p 823 A88-54938 [ AD-A1944761 p 853 N88-29061 oscillations I SPEECH RECOGNITION STOCHASTIC PROCESSES [ASME PAPER 88-GT-811 p 848 A8844209 Smart command recognizer (SCR) For development, Prediction of the extreme values of the phase Assessment of gas turbine vibration monitoring test. and implementationof speech commands coordinates of stochastic systems p 857 A88-52823 [ASME PAPER 88-GT-2041 p 850 A88-54291 [AIAA PAPER 88.46121 p 858 A88-53654 STRAIN GAGES STRUCTURAL WEIGHT SPRAY CHARACTERISTICS Advanced structural instrumentation - An overview The criticality of weight and balance on competition , Turbulence effects on the droplet distribution behind [AIAA PAPER 88-31441 p 844 A88-53145 aircraft I airblast atomizers D 842 N88-29915 STRAPDOWN INERTIAL GUIDANCE [SAWE PAPER 17561 p 808 A88-53776 Nozzle airflow influences on fuel patternation The NAE atmospheric research aircraft Predicting, determining. and controlling manufacturing p 842 N88-29916 p 81 5 N88-29730 variation in a new facility --- aircraft production Spray Performance of a vaporizing fuel injector STREAM FUNCTIONS (FLUIDS) [SAWE PAPER 17711 p 783 A88-53782 p 842 N88-29919 A unified solution method for the flow calculations along Weight growth in airline service SPRAYED COATINGS S1 and S2 Stream surfaces used for the computer-aided [SAWE PAPER 17961 p 809 A8843797 NiCrAllbentonite thermal spray powder for high design of centrifugal compressors STRUTS temperature abradable seals p 837 A88-53556 [ASME PAPER 88-GT-2371 p 793 A88-54318 Test of an 0.8-scale model of the AH-64 Apache in the Hypervelocity application of tribological coatings STRESS ANALYSIS NASA Langley full-scale wind tunnel p 845 A88-53563 The measurement of stress and vibration data in turbine [AD-A196129] p 799 N88-29768 High temperature testing of plasma sprayed thermal blades and aeroengine components SUBSONIC FLOW barrier coatings p 845 A88-53571 [ASME PAPER 88-GT-1491 p 849 A88-54250 A three dimensional zonal Navier-Stokes code for Plasma sprayed tungsten carbide-cobalt coatings Structural dynamics of maneuvering aircraft subsonic through hypersonic propulsion flowfields p 845 A88-53579 [AD-A1923761 p 810 N88-28908 [AIAA PAPER 88.28301 p 785 A88-53106 Spray automated balancing of rotors: Methods and Aeroelastic response of metallic and composite propfan Experimentalinvestigation of the three-dimensionalflow materials models in yawed flow in an annular compressor cascade [ NASA-CR-l82151] p 836 N88-29825 [ NASA-TM-1009641 p 825 N88-29807 [ASME PAPER 88-GT-2011 p 792 A88-54288 SPRAYERS STRESS INTENSITY FACTORS Aerodynamically forced response of structurally Hypervelocityapplication of tribological coatings Stress intensity factors for cracked metallic structures mistuned bladed disks in subsonic flow p 845 A88-53563 under rapid thermal loading p 795 A8844943 STAGNATION PRESSURE [AD-A191219] p 840 N88-29004 SUBSONIC SPEED The feasibility. from an installational viewpoint. of Stress intensity factors for cracked metallic structures Pressure distributions from subsonic tests of an gas-turbine pressure-gaincombustors under rapid thermal loading advanced laminar-flow-control wing with leading- and [ASME PAPER 88-GT-1811 p 849 A8844272 trailing-edge flaps STAGNATION TEMPERATURE [AES-8609709F-l] p 843 N88-29962 STRESS RELAXATION [ NASA-TM-4040-PT-21 p 800 N88-29776 Unique. clean-air, continuous-flow, SUCTION Calculation of Stress relaxation in the surface-hardened high-stagnation-temperature facility for supersonic Suction laminarization of highly swept supersonic layer near a hole in the disk of a gas-turbine engine combustion research laminar flow control wings p 846 A88-53961 [AIAA PAPER 88-3059AI p 832 A8843135 [AIAA PAPER 88-4471I p 786 A88-53762 STATIC DISCHARGERS STRUCTURAL ANALYSIS The influence of turbine clearance gap leakage on New version antistatic coating tester Advanced structural instrumentation - An overview passage velocity and heat transfer near blade tips. II - p 844 A8863166 [AIAA PAPER 88-31441 p 844 A8843145 Source flow effects on blade suction sides STATIC TESTS Instrumentationand techniques for structural dynamics [ASME PAPER 88-GT-991 p 790 A88-54219 Certification of primary composite aircraft structures and acoustics measurements SUPERCOMPUTERS p 805 A88-52672 [AIAA PAPER 88.46671 p 845 A88-53829 Aerodynamics --- numerical Simulation using STATISTICAL ANALYSIS Structuralanalysis applications --- for aircraft gas turbine supercomputers p 783 A88-53800 Asymptotic modal analysis and statistical energy combustors p 817 A8844143 SUPERCRITICAL FLOW analysis Development of a thermal and structural analysis Application of a hybrid analyticallnumerical method to [NASA-CR-183077] p 861 N88-29514 procedure for cooled radial turbines the practical computation of supercritical viscouslinviscid Measurement and analysis of low altitude atmospheric [ASME PAPER 88-GT-181 p 846 A88-54164 transonic flow fields p 795 A88-54907 turbulence obtained using a specially instrumented Gnat Interactive plotting of NASTRAN aerodynamic models SUPERSONIC AIRCRAFT aircraft p 857 N88-29728 using NPLOT and DISSPLA Future supersonic transport noise - Lessons from the Re-assessmentof gust statistics using CAADRP data [AD-A194115] p 853 N88-29204 past p 831 N88-29732 [AIAA PAPER 88-29891 p 816 A88-53121 STATISTICAL DISTRIBUTIONS Computer programs for generation of NASTRAN and VIBRA-6 aircraft models Some key considerations for high-speed civil Additional investiaations into the aircraft landino [ AD-AI 95467 ] p 81 2 N88-29792 transports process Test distributions [AIAA PAPER 88.44661 p 783 A8843760 Constitutive modeling for isotropic materials [ ESA-TT-10991 p 810 "3-28913 Preliminary design of two transpacific high speed civil [ NASA-CR-1821321 p 826 N88-29811 STATOR BLADES transports Experimental investigation of rotating stall in a Stress intensity factors for cracked metallic structures [AIAA PAPER 88-448561 p 807 A88-53765 mismatched three stage axial flow compressor under rapid thermal loading An analysis of lateral-directional handling qualities and [ASME PAPER 88-GT-2051 p 850 A8844292 [AES-8609709F-I 1 p 843 N88-29962 Eigenstructureof high performance aircraft STATORS STRUCTURAL DESIGN [AD-A1948741 p 831 N88-29814 The effects of turbulence and statorlrotor interactions Damage tolerance in pressurized fuselages SUPERSONIC AIRFOILS on turbine heat transfer I1 - Effects of Reynolds number p 803 A88-52652 Test results and theoretical investigations on the ARL and incidence Evaluation of new materials in the design of aircraft 19 supersonic blade cascade [ASME PAPER 88-GT-51 p 846 A88-54152 structures p 803 A88-52654 [ASME PAPER 88-GT-2021 p 792 A88-54289 i A-25 SUPERSONIC COMBUSTION SUBJECT INDEX

SUPERSONIC COMBUSTION SURFACE PROPERTIES TECHNOLOGYASSESSMENT Unique. clean-air. continuous-flow, Surface heat transfer fluctuationson aturbinerotor blade Assessment, development, and application of high-stagnation-temperature facility for supersonic due lo upstream shock wave passing combustor aerothermal models p 817 A88-54140 combustion research [ASME PAPER 88-GT-1721 p 791 A88-54266 Thermomechanical advances for small gas turbine [AIM PAPER 88-3059Al p 832 A88-53135 SURFACE STABILITY engines - Present capabilities and future direction in gas Flame stabilization in supersonic combustion Empirical flutter prediction method generator designs p 837 A88-53164 [AD A1956991 p 825 N88-29810 [ASME PAPER 88-GT-2131 p 850 A88-54299 SUPERSONIC COMBUSTION RAMJET ENGINES SURVEILLANCE Recent advances in engine health management A full Navier-Stokes analysis of a three dimensional Aerodynamics of seeing on large transport aircraft [ASME PAPER 88-GT-2571 p 820 A8844333 hypersonic mixed compression inlet [NASA-CR-183122] p 801 N88-28896 Current status and future trends in turbine application of thermal barner coatings [AIAA PAPER 88-30771 p 785 A88-53138 SURVEILLANCE RADAR [ASME PAPER 88-GT-2861 p 851 A88-54355 CFD predictionof the reactingflow field inside a subscale Fine resolution errors in secondary surveillance radar Constitutrve modeling for isotropic malerials scramjet combustor altitude reporting [AIM PAPER 88-32591 p 816 A88-53151 [ RSRE-870191 p 802 N88-28906 [NASA-CR-182132] p 826 N88-29811 TECHNOLOGYTRANSFER Calibration of CFD methods for high Mach number SWEPT FORWARD WINGS Structural technology transition lo new aircraft aeroengine flowfields Structural technology transition to new aircraft [ASME PAPER 88-GT-1991 p 792 A88-54286 p 805 A88-52673 p 805 A88-52673 China's acquisition and use of foreign aviation Periodic neighbonng optimum regulator applied to a Application of the theory of anisotropic thin-walled technology hypersonic scramjet cruiser p 827 A88-54528 beams and plates for wngs made from composite [ AD-AI 94827 ] p 862 N88-30471 SUPERSONIC COMPRESSORS material Periodicity. superposition, and 3D effects in supersonic [IAF PAPER 88.2751 p 852 A88-55372 TECHNOLOGY UTILIZATION China's acquisition and use of foreign aviation compressor flutter aerodynamics High performance forward swept wing aircraft [ASME PAPER 88-GT-1361 p 791 A88-54242 [ NASA-CASE-ARC-11636 11 p 810 NEB-28914 technology [ ADA1 948271 p 862 "3-30471 Performance of a Compressor cascade configuration SWEPT WINGS TEMPERATURE DISTRIBUTION with supersonic entrance flow A review and comparison Suction laminarization of highly swept supersonic - A detailed characterization of the velocity and thermal of expenments in three installations laminar flow control wings fields in a model can cornbustor with wall jet injection [ASME PAPER 88-GT-211I p 793 A88-54297 [AIAA PAPER 88 4471 1 p 786 A88-53762 [ASME PAPER 88-GT-261 p 81 8 A88-54170 Techniques used in the F-14 vanable-sweep transition Expenmental investigation of the performance of a Laminar flow velocity and temperature distributions flight experiment supersonic compressor cascade between coaxial rotating disks of finite radius [NASA-TM 1004441 p 855 N88-30093 [ASME PAPER 88-GT-3061 p 795 A88-54375 [ASME PAPER 88-GT-491 p 847 A88-54185 SWIRLING SUPERSONIC DRAG TEMPERATURE MEASUREMENT Air flow performance of air swirlers for gas turbine fuel Suction laminarization of highly swept supersonic Gas temperalure measurements in short duration nozzles laminar flow control wings turbomachinery test facilities [ASME PAPER 88 GT-1081 p 848 A88-54227 [AIAA PAPER 88-4471 I p 786 A88-53762 [AIAA PAPER 88-30391 p 844 A8843128 Euler analysis of a swirl recovery vane design for use SUPERSONIC FLIGHT Weibull analysis techniques on a desktop computer with an advanced single-rotation propfan Technology sensitivity studies for a Mach 3.0 civil [NASA-TM-101357] p 800 N88-29771 [ASME PAPER 88-GT-2851 p 851 A88-54354 transport TEMPERATURESENSORS SYNTHETIC APERTURERADAR [AIAA PAPER 88.44691 p 783 A88-53761 Advanced structural instrumentation An overview Processing pseudo synthetic aperture radar images from - [AIAA PAPER 88-31441 p 844 A88-53145 High speed transpacific passenger flight visual terrain data TERMINAL BALLISTICS [AIAA PAPER 88-44841 p 807 A8843764 [AlAA PAPER 88-45761 p 802 A88-53628 Review of research concerning Solid Fuel Ramjet SUPERSONIC FLOW Effect of phase errors in stepped-frequency radar (SOFRAM) at the Research Institute of National Defence A preliminary design study of supersonic through-flow systems (FOA) 2 fan inlets [ AD-A1944761 p 853 N88-29061 [ FOA-C-20714-2.11 p 826 N88-29813 [AIAA PAPER 88-30751 p 816 A8863137 SYSTEM EFFECTIVENESS TERRAIN ANALYSIS Flutter of a fan blade in supersonic axial flow Controlled degradabon of resolution of high-qualityflight Processingpseudo synthetic aperture radar images from [ASME PAPER 88-GT-781 p 788 A88-54206 Simulator images for training effectiveness evaluation visual terrain data Performance of a compressor cascade configuration [ AD-A1961 891 p 836 N88-29823 [AIM PAPER 88-45761 p 802 A88-53628 with supersonic entrance flow - A review and comparison SYSTEM FAILURES TEST EQUIPMENT of experiments in three installations Detection, identification and estimation of surface New version antistatic coaling tester [ASME PAPER 88-GT-2111 ' p 793 A88-54297 damagelactuator failure tor high performance aircraft p 828 A88-54650 p 844 A88-53166 An integral equation for the linearized unsteady Lockheed HTTB - STOL performance features supersonic flow over a wing Application of supercontroller to fighter aircraft reconfiguration p 829 A88-54654 [SAWE PAPER 17721 p 808 A88-53783 [AD-A193773] p 797 N88-28887 TEST FACILITIES SYSTEM IDENTIFICATION Compression pylon Overview of Lockheed C-130 High Technology Test Bed Detection, identification and estimation of surface [ NASA-CASE-LAR-13777.11 p 812 N88-29789 Program damagelactuator failure for high performance aircraft SUPERSONIC FLUTTER p 828 A88-54650 [SAWE PAPER 17861 p 808 A88-53789 Periodicity. superposition. and 3D effects in supersonic Unsteady water channel Estimation of aircraft parameters using filter error compressor flutter aerodynamics [AD-A194231] p 797 N88-28884 methods and extended Kalman filter [ASME PAPER 88-GT-1361 p 791 A88-54242 Development and design of windtunnel and test facility [ DFVLR-FB-88-151 p 810 N88-28911 for RPV (Remote Piloted Vehicle) enhancement devices SUPERSONIC JET FLOW SYSTEMS ENGINEERING Near-field pressure radiation and flow characteristics in Unique. clean-air. continuous-flow. [AD-A1948421 p 836 N88-29822 Development and installation of an instrumentation low supersonic circular and elliptic jets high-stagnation-temperature facility for supersonic package for GE F404 investigative testing p 795 A88-54869 combustion research SUPERSONIC TRANSPORTS [AIAA PAPER 88-3059Al p 832 A88-53135 [AD-AI 962651 p 855 N88-30107 TEXTURES Aerodynamics --- numerical sirnulabon using SYSTEMS INTEGRATION Dynamic texture in visual system supercomputers p 783 A88-53800 Vehicle Manaaement Svstems - The locrical evolution [AIAA PAPER 88.45781 p 832 A88-53630 SUPERSONIC TURBINES of integration TF-30 ENGINE Fully scaled transonic turbine rotor heal transfer [AIAA PAPER 88-31751 p 826 A88-53148 Fuel properly effects on the US Navy's TF30 engine measurements Present and future develoDments of the NLR movina p 826 NEB-29911 [ASME PAPER 88-GT-1711 p 849 A88-54265 base research flight sirnulato; THERMAL ANALYSIS [AIAA PAPER 88-45841 p 832 A88-53635 SUPERSONIC WIND TUNNELS Development of a thermal and structural analysis Unique, clean-air, continuous-flow, SYSTEMS SIMULATION procedure for cooled radial turbines high-stagnation-temperature facility for supersonic Multiple frame rate integration [ASME PAPER 88-GT-181 p 846 A88-54164 combustion research [AIM PAPER 88-45791 p 857 A88-53631 THERMALBOUNDARYLAYER [AIAA PAPER 88-3059Al p 832 A88-53135 Design code verification of external heat transfer Supersonic wall adaptation in the rubber tube test T coefficients section of the DFVLR Goettingen [AIAA PAPER 88-301I] p 844 A88-53123 [ 18-222-87-A-081 p 836 N88-29824 TAKEOFF THERMAL CONDUCTIVITY SUPPORT SYSTEMS Simulator evaluation of takeoff performance monitonng Composites break the ice --- fiber reinforced materials Advanced technology engine supportability - Preliminary system displays for deicing of aircraft surfaces and engines designer's challenge [AIAA PAPER 88-48111 p 833 A88-53653 p 840 A88-54857 [AIAA PAPER 88-27961 p 815 A88-53102 Robust control strategy for lake-off performance in a THERMAL CONTROL COATINGS SURFACE COOLING windshear p 829 A88-54656 High temperature testing of plasma sprayed thermal Studies of gas turbine heat transfer airfoil surface and TARGET ACQUISITION barrier coatings p 845 A88-53571 end-wall cooling effects Digital emulation of the AH-64A contrast tracker Thermal barner coatings for jet engines [ AD-A1951651 p 825 N88-29805 [AIAA PAPER 88-465281 p 813 A88-53827 [ASME PAPER 88-GT-2791 p 840 A88-54351 SURFACE FINISHING TARGET SIMULATORS Current status and future trends in turbine application Surface engineering for high temperature Digital emulation of the AH-MA contrast tracker of thermal barrier coatings environments p 845 A88-53840 [AlAA PAPER 88-465281 p 81 3 A88-53827 [ASME PAPER 88-GT-2861 p 851 A88-54355 SURFACELAYERS TECHNOLOGICAL FORECASTING THERMAL CYCLING TESTS Calculation of stress relaxation in the surface-hardened XG40 - Advanced combat engine technology Enstaff - A standard test sequence for composite layer near a hole in the disk of a gas-turbine engine demonstrator programme components combining load and environment p 846 A88-53961 [ASME PAPER 88-GT-3001 p 821 A88-54369 D 804 A88-52666

A-26 SUBJECT INDEX TRANSONIC FLUTTER

High temperature testing of plasma sprayed thermal Experimentalinvestigation of the three-dimensional flow TRAINING SIMULATORS barrier coatings p 845 A88-53571 in an annular compressor cascade Determination of helicopter simulator time delay and its Effect of loading asymmetry on the low-cycle fatigue [ASME PAPER 88-GT-201I p 792 A88-54288 effects on air vehicle development of ZhS6F alloy under cyclic temperature changes The effect of the Reynolds number on the [ AlAA PAPER 88-46201 p 833 A88-53659 p 838 A8843955 three-dimensional flow in a straight compressor cascade Some benefits of distributed computing architectures for THERMAL FATIGUE [ASME PAPER 88-GT-2691 p 794 A88-54343 training simulators p 858 A88-53671 Fatigue of elevated temperature powder metallurgy Multigrid acceleration of the flux-split Euler equations Controlleddegradation of resolutionof high-quality flight aluminum alloy mechanically fastened joints p 796 A88-55077 simulator images for training effectiveness evaluation p 837 A88-52655 Experience with three dimensional composite grids [AD-A196189] p 636 N88-29823 p 860 N88-29324 THERMAL PROTECTION TRAJECTORY CONTROL Experimental and theoretical aspects of thick thermal Three-dimensional Navier-Stokes Simulations of turbine Optimization and guidance of penetration landing barrier coatings for turbine applications rotor-stator interaction trajectories in a windshear p 828 A88-54570 [ NASA-TM-1000811 p 799 "3.29750 p 837 A88-53566 TRAJECTORY OPTIMIZATION Surface engineering for high temperature THREE DIMENSIONAL MODELS Periodic neighboring optimum regulator applied to a environments p 845 A88-53840 Design point vanation of 3-D loss and deviation for axial hypersonic scramjet cruiser p 827 A88-54528 Life modeling of thermal barrier coatings for aircraft gas compressor middle stages Trajectory optimization and guidance law development turbine engines p 838 A88-54145 [ASME PAPER 88-GT-571 p 787 A88-54189 for national aerospace plane applications THERMAL RADIATION THRUSTREVERSAL p 837 A88-54567 Combustion and fuels in gas turbine engines Aerodynamics in ground effect and predicted landing Optimization and guidance of penetration landing ground roll a fighter configuration with a [AGARD-CP-4221 p 841 N88-29910 of trajectories in a windshear p 828 A88-54570 secondary-nozzle thrust reverser Helicopter trajectory planning using optimal control Radiation transfer in gas turbine combustors [NASA-TP-28341 p 799 N88-29752 p 843 N88-29929 theory p 828 A88-54571 THRUSTVECTORCONTROL THERMAL RESISTANCE TRANSFER FUNCTIONS IntegratedthNSt vectoring on the X-29A Meeting the high temperature challenge The A minimal realization algorithm for flight control - [AIAA PAPER 88-44991 p 808 A88-53769 nonmetallic aero engine p 838 A88-53838 systems p 829 A88-54661 THUNDERSTORMS TRANSFER OF TRAINING THERMAL STRESSES Investigations into the triggered lightning response of Deformation and damage of the material of gas turbine Artificial intelligence systems for aircraft training - An the F106B thunderstorm research aircraft evaluation engine blades during thermal cycling in gas flow [ NASA-CR-39021 p 856 N88-29258 p 845 A88-53954 [AlAA PAPER 88-45881 p 857 A88-53637 TILT ROTOR AIRCRAFT Stress intensity factors for cracked metallic structures TRANSIENT OSCILLATIONS Development of the T406-AD-400 oil scavenge system Actwe control of transient rotordynamic vibration by under rapid thermal loading for the V-22 aircraft [AD-A191219] p 840 N88-29004 optimal control methods [ASME PAPER 88-GT-297) p 821 A88-54366 [ASME PAPER 88-GT-731 p 858 A88-54202 Stress intensity factors for cracked metallic structures TIME LAG TRANSIENT PRESSURES under rapid thermal loading Ground simulator requirements based on in-flight Acquisition of unsteady pressure measurements from [AES-8609709F-l] p 843 N88-29962 simulation a high speed multi-stagecompressor THERMOCOUPLES [AlAA PAPER 88.46091 p 606 A66-53651 [ASME PAPER 66-GT-1891 p 833 A88-54280 Gas temperature measurements in short duration Simulator transport delay measurement using TRANSITION FLOW turbomachinery test facilities steady-state techniques Effects of incidence on three-dimensional flows in a [AIAA PAPER 88-30391 p 844 A88-53128 [AlAA PAPER 88-46191 p 833 A88-53658 linear turbine cascade THERMOPLASTIC RESINS Determination of helicopter simulator time delay and its [ASME PAPER 88-GT-1IO] p 790 A88-54228 The non-destructivetesting of welds in continuous fibre effects on air vehicle development TRANSMISSIONS (MACHINE ELEMENTS) reinforced thermoplastics p 852 A88-55456 [AIAA PAPER 88-46201 p 833 A88-53659 Helicopter transmission research at NASA Lewis THICKNESS TIME OPTIMAL CONTROL Research Center The use of hot-filmtechnique for boundary layer studies Helicopter trajectory planning using optimal control [ NASA-TM-1009621 p 855 N88-30128 on a 21 percent thick airfoil theory p 828 A68-54571 TRANSOCEANIC FLIGHT [ NAE-AN-451 p 800 N88-29781 High speed transpacific passenger flight TOLLMEIN-SCHLICHTING WAVES [AlAA PAPER 88-44841 p 807 A88-53764 THIN AIRFOILS Variable Sweep Transition Flight Experiment TRANSONIC COMPRESSORS Technology for pressure-instrumented thin airfoil (VSTFE)-parametric pressure distribution boundary layer Numerical solution to transonic potential equations models stability study and wing glove design task on S2 [ NASA-CR-41731 p 835 N88-28933 [ NASA-CR-39921 p 798 N88-28894 stream surface in a turbomachine THREAT EVALUATION [ASME PAPER 88-GT-821 p 789 A88-54210 TOMOGRAPHY Threat expert system technology advisor Studies of unsteady axial-compressor functioning Positron emission tomography: A new technique for [NASA-CR-l77479] p 831 N88-29816 p 655 N88-30129 observing fluid behavior in engineering systems THREE DIMENSIONAL BODIES TRANSONIC FLOW [PNR90471] p 854 N88-30091 The aerodynamics of an annular cascade of A projection-gridscheme for calculating transonic flow three-dimensional airfoils p 795 A88-54942 TRACKING (POSITION) past a profile p 785 A88-52795 THREE DIMENSIONAL BOUNDARY LAYER ObSeNed track-keeping performance of DClO aircraft Statorlrotor interaction in a transonic turbine Assessment of a 3-D boundary layer analysis to predict equipped with the Collins AINS-70 area navigation system: [AIAA PAPER 88-30931 p 785 A88-53140 heat transfer and flow field in a turbine passage Karlsruhe and Masstricht UACs (Upper Area Control Detection of separation bubbles by infrared images in [ NASA-CR-1748941 p 854 N88-30066 centres) transonic turbine cascades THREE DIMENSIONAL FLOW [EEC-ZOZ] p 803 N88-29788 [ASME PAPER 86-GT-331 p 787 A88-54176 A full Navier-Stokes analysis of a three dimensional TRAFFIC CONTROL The relative merits of an inviscidEuler 3-D and quasi-3-D hypersonic mixed compression inlet Airport surface traffic automation study analysis lor the design of transonic rotors [AIAA PAPER 88-30771 p 785 A88-53138 [AD-A1945531 p 835 N88-28934 [ASME PAPER 88-GT-691 p 788 A88-54200 Navier-Stokes solutions for rotating 3-D duct flows TRAILING EDGE FLAPS Quasi-3D solutions for transonic. inviscid flows by [AIAA PAPER 88-30981 p 844 A88-53142 Pressure distributions from subsonic tests of an adaptive triangulation The effect of the inlet velocity profile in the advanced laminar-flow-controlwing with leading- and [ASME PAPER 88-GT-831 p 769 A88-54211 three-dimensional flow in a rear axial compressor stage trailing-edge flaps Base pressure in transonic speeds - A comparison [ASME PAPER 86-GT-461 p 787 A88-54183 [ NASA-TM-4040-PT-21 p 800 N88-29776 between theory and experiment The relativemerits of an inviscid Euler 3-D and quasi-3-D TRAILING EDGES [ASME PAPER 88-GT-1321 p 790 A88-54240 analysis for the design of transonic rotors Heat transfer, pressure drop, and mass flow rate in pin Effect of shock wave movement on aerodynamic [ASME PAPER 88-GT-691 p 788 A88-54200 fin channels with long and short trailing edge ejection instability of annular cascade oscillating in transonic flow Development of a 3D Navier Stokes solver for application holes [ASME PAPER 88-GT-1871 p 792 A88-54278 to all types of turbomachinery [ASME PAPER 88-GT-421 p 847 A88-54181 Influence of deposit on the flow in a turbine cascade [ASME PAPER 88-GT-701 p 788 A88-54201 Base pressure in transonic speeds - A comparison [AS-ME PAPER 88-GT-2071 p 792 A88-54293 Computation of three-dimensional turbulent between theory and experiment Numerical simulation of inviscid transonic flow through turbomachinery flows using a coupled parabolic-marching [ASME PAPER 88-GT-1321 p 790 A88-54240 nozzles with fluctuating back pressure method [ASME PAPER 88-GT-2871 p 794 A88-54356 TRAINING AIRCRAFT Application a hybrid analyticallnumericalmethod to [ASME PAPER 88-GT-801 p 788 A88-54208 NASA Shuttle Training Aircraft flight simulation of the practical computation of supercritical viscouslinviscid Calculation of complete three-dimensional flow in a overview transonic flow fields p 795 A88-54907 centrifugal rotor with splitter blades [ AlAA PAPER 88-46081 p 806 A88-53650 [ASME PAPER 88-GT-931 p 789 A88-54216 Efficient Euler solver with many applications Structural design and its improvements through the Prediction of compressor cascade performance using p 796 A66-55078 a Navier-Stokes technique development of the XF3-30 engine Three-dimensional elliptic grid generation for an F-16 [ASME PAPER 88-GT-2611 p 821 A88-54337 [ASME PAPER 88-GT-961 p 789 A88-54217 p 859 N88-29315 Three dimensional flow in radial-inllowturbines TRAINING DEVICES Application of unsteady aerodynamic methods for [ASME PAPER 88-GT-1031 p 790 A88-54222 Technology of flight simulation p 805 A88-52692 transonic aeroelastic analysis Effects of incidence on three-dimensional flows in a TRAINING EVALUATION [ NASA-TM-1006651 p 799 N88-29754 linear turbine cascade Artificial intelligence systems for aircraft training - An Theoretical aerodynamics, transonic flow [ASME PAPER 88-GT-1101 p 790 A88-54228 evaluation [AD-A196247] p 800 N88-29777 A transient flow facility for the study of the [AIAA PAPER 88.45881 p 857 A88-53637 TRANSONIC FLUTTER thermofluid-dynamics of a full stage turbine under engine Controlleddegradation of resolutionof high-quality flight Effect of shock wave movement on aerodynamic representative conditions simulator images for training effectiveness evaluation instability of annular cascade oscillating in transonic flow [ASME PAPER 88-GT-1441 p 849 A88-54245 [AD-A1961 891 p 836 N88-29823 [ASME PAPER 88-GT-1871 p 792 A68-54278

A-27 TRANSONIC NOZZLES SUBJECT INDEX

TRANSONIC NOZZLES The influence of turbine clearance gap leakage on The use of Bezier polynomial patches lo define the Aerodynamic and heat transfer measurements on a passage velocity and heat transfer near blade tips. II . geometrical shape of the flow channels of compressors transonic nozzle guide vane Source flow effects on blade suction sides [ASME PAPER 88-GT-601 p 788 A88-54192 [ASME PAPER 88 GT 101 p 786 A88 54157 [ASME PAPER 88-GT-991 p 790 A88-54219 A radial mixing cornputation method TRANSONIC SPEED A fast interactive two-dimensionalblade-to-blade profile [ASME PAPER 88-GT-881 p 847 A88-54199 Test results at transonic speeds on a contoured design method Flutter of a fan blade in supersonic axial flow over-the-wing propfan model [ASME PAPER 88-GT-1001 p 790 A88-54220 [ASME PAPER 88-GT-781 p 788 A88-54206 [ NASA-TM-882061 p 811 N88-28918 Design optimizationof gas turbine blades with geometry Effect of stage loading on endwall flows in an axial flow Recent advances in transonic computational and natural frequency constraints compressor rotor aeroelasticity [ASME PAPER 88-GT-1051 p 818 A8844224 [ASME PAPER 88-GT-Ill] p 848 A8844229 [ NASA-TM-I006631 p 800 N88-29778 Effects of incidence on three-dimensional flows in a Acquisition of unsteady pressure measurements from TRANSONIC WIND TUNNELS linear turbine cascade a high speed multi-stage compressor The application of cryogenics to high Reynolds number [ASME PAPER 88-GT-1101 p 790 A8844228 [ASME PAPER 88-GT-1891 p 833 A88-54280 testing in wind tunnels II - Development and application Base pressure in transonic speeds - A comparison Experimental investigation of rotating stall in a of the cryogenic wind tunnel concept belween theory and experiment mismatched three stage axial flow compressor p 833 A88 53847 [ASME PAPER 88-GT-1321 p 790 A8864240 [ASME PAPER 88-GT-2051 p 850 A88-54292 Test results and theoretical investigations on the ARL The measurement of stress and vibration data in turbine Analysis of efficiency sensitivity associated with tip 19 supersonic blade cascade blades and aeroengine components clearance in axial flow compressors [ASME PAPER 88-GT-2021 p 792 A88-54289 [ASME PAPER 88-GT-1491 p 849 A88-54250 [ASME PAPER 88-GT-2161 p 819 A88-54301 Boundary layer Simulation and control in wind tunnels Investigationof boundary layer transition and separation Flow measurements in rotating stall in a gas turbine [ AGARD-AR-2241 p 784 N88-28857 in an axial turbine cascade using glue-on hot-film gages engine compressor TRANSPORT AIRCRAFT [ASME PAPER 88-GT-1511 p 791 A88-54251 [ASME PAPER 88-GT-2191 p 81 9 A88-54304 Design concepts for an Advanced Cargo Rotorcraft Effect of shock wave movement on aerodynamic Wake-boundary layer interactionsin an axial flow turbine [AIAA PAPER 88-44961 p 807 A88-53768 instability of annular cascade oscillating in transonic flow rotor at off-design conditions Assessment of a Soviet hypersonic transport [ASME PAPER 88-GT-I871 p 792 A88-54278 [ASME PAPER 88-GT-2331 p 793 A88-54315 [AIAA PAPER 88-45061 p 808 A88-53770 Behaviour of the leg of the horseshoe vortex around Structure of tip clearance flow in an isolated axial Soviet applications for hypersonic vehicles the idealizedblade with zero attack angle by triple hot-wire compressor rotor [AlAA PAPER 88-45071 p 783 A88-53771 measurements [ASME PAPER 88-GT-2511 p 794 A8844327 Development,analysis. and flight test of the Lockheed [ASME PAPER 88-GT-1971 p 792 A88-54285 Numerical results for axial flow compressor instability Aeronautical System Company HTTB HUD Measurement and modelling of the gas turbine blade [ASME PAPER 88-GT-2521 p 851 A88-54328 [AIAA PAPER 88 4511 I p 81 3 A88-53772 transition process as disturbed by wakes Numerical integrationof the 3D unsteadyEuler equations A different approach to the interrelated subjects of [ASME PAPER 88-GT-2321 p 793 A88-54314 for flutter analysis of axial flow compressors weight, performance. and price as applied to commercial A new variational finite element computation for [ASME PAPER 88-GT-2551 p 794 A88-54331 transport aircraft aerodynamic inverse problem in turbines with long An experimental investigation of a vortex flow cascade [SAWE PAPER 17791 p 808 A88-53786 blades [ASME PAPER 88-GT-2651 p 794 A88-54341 Economical technology application in commercial [ASME PAPER 88-GT-2751 p 794 A88-54347 The effect of the Reynolds number on the transport design Prediction of turbulence generated random vibrational three-dimensionalflow in a straight compressor cascade [SAWE PAPER 17981 p 809 A88-53798 response of turbomachinery blading p 796 A88-54946 [ASME PAPER 88-GT-2691 p 794 A88-54343 Critical joints in large composite primary aircraft TURBINE ENGINES Causes for turbomachinery performance deterioration structures Volume 1 Technical summary Statorlrotor interaction in a transonic turbine [ASME PAPER 88-GT-2941 p 821 A8844363 [ NASA-CR-39141 p 840 N88 28983 [ AlAA PAPER 88-30931 p 785 A88-53140 Experimental investigation of the performance of a Low-speed longitudinal flying qualities of modern Advanced high temperalure instrumentation for hot supersonic compressor cascade transport aircraft p 812 N88-29738 section research applications p 846 A88-54139 [ASME PAPER 88-GT-3061 p 795 A88-54375 TRIANGULATION A transient flow facility for the study of the Quasi-3D solutions for transonic. inviscid flows by lhermofluid-dynamicsof a full stage turbine under engine A study of aerodynamic noise from a contra-rotating axial compressor stage p 823 A88-54938 adaptive triangulation representativeconditions [ASME PAPER 88-GT-831 p 789 A88-54211 [ASME PAPER 88-GT-1441 p 849 A8844245 Modeling of large stall in axial compressors TRIBOLOGY Fiber optics for aircraft engine controls [VKCTN-1641 p 853 N88-29124 Hypervelocity application of tribological coatings p 822 A8844619 TURBOFAN AIRCRAFT p 845 A88-53563 TURBINE INSTRUMENTS Multiple-Purpose Subsonic Naval Aircraft (MPSNA): TUNGSTEN Gas temperalure measurements in short duration Multiple Application Propfan Study (MAPS) Composite monolayer fabrication by an arc-spray turbomachinery test facilities (NASA-CR-1751041 p 811 N88-28917 process p 845 A88-53581 [AIAA PAPER 88-30391 p 844 A88-53128 TURBOFAN ENGINES TUNGSTEN CARBIDES TURBINE PUMPS A preliminary design study of supersonic through-flow Plasma sprayed tungsten carbide-cobalt coatings Flow computation and blade cascade design in fan inlets p 845 A88-53579 turbopump turbines [AIAA PAPER 88.30751 p 816 A88-53137 TURBINE BLADES [ASME PAPER 88-GT-2481 p 820 A8834326 Multivariable turbofan engine control for full flight Design code verification of external heat transfer TURBINE WHEELS envelope operation coefficients Calculation of stress relaxation in the surface-hardened [ASME PAPER 88-GT-61 p 818 A88-54153 [AIAA PAPER 88-3011 I p 844 A8843123 layer near a hole in the disk of a gas-turbine engine Transient performance trending for a turbofan engine Dimensioningof turbine blades for fatigue and creep p 846 A88-53961 [ASME PAPER 88-GT-2221 p 819 A88-54306 p 817 A88-53167 A comparison of engine design life optimization results Precision error in a turbofan engine monitoring system Deformation and damage of the material of gas turbine using deterministic and probabilistic life prediction [ASME PAPER 88-GT-2291 p 819 A88-54312 engine blades dunng thermal cycling in gas flow techniques p 845 A88-53954 [ASME PAPER 88-GT-2591 p 820 A88-54335 Response of large turbofan and turbojet engines to a short-duration overpressure Effect of loading asymmetry on the low-cycle fatigue A turbine wheel design story of ZhS6F alloy under cyclic temperature changes [ASME PAPER 88-GT-3161 p 822 A88-54383 [ASME PAPER 88-GT-2731 p 821 A88-54346 p 838 A8843955 TURBINES The CFM56 engine family - An internal development Corrosion and protection of gas turbine blades --- The effects of inlet turbulence and rotorlstator (ASME PAPER 88-GT-2961 p 862 A88-54365 Russian book p 838 A88-53996 interactions on the aerodynamics and heat transfer of a Development of the F404lRM12 for the JAS 39 An experimental investigation into the reasons of large-scalerotating turbine model. Volume 3: Heat transfer Gripen reducing secondary flow losses by using leaned blades data tabulation 65 percent axial spacing [ASME PAPER 88-GT-3051 p 822 A88-54374 in rectangular turbine cascades with incidence angle [ NASA-CR-1794681 p 824 N88-28930 Evaluation of potential engine concepts for a high [ASME PAPER 88-GT-41 p 786 A88-54151 The effects of inlet turbulence and rotorlstalor altitude long endurance vehicle Aerodynamic and heat transfer measurements on a interactions on the aerodynamics and heat transfer of a [ASME PAPER 88-GT-3211 p 822 A88-54386 transonic nozzle guide vane large-scalerotating turbine model. Volume 2: Heat transfer Scheduling turbofan engine control set points by [ASME PAPER 88-GT-IO] p 786 A8844157 data tabulation. 15 percent axial spacing semi-infinite optimization p 823 A88-54658 [ NASA-CR-1794671 p 825 N88-29804 Flow field in the tip gap of a planar cascade of turbine Euler analysis of a swirl recovery vane design for use Studies of gas turbine heat transfer airfoil surface and blades with an advanced single-rotation propfan end-wall cooling effects [ASME PAPER 88-GT-291 p 787 A88-54173 [ NASA-TM-1013571 p 800 N88-29771 [AD-A195165] p 825 N88-29805 Developing the Rolls-Royce Tay The effects of an excited impinging let on the local heat An investigation of constitutive models for predicting [PNR90447] p 825 N88-29809 transfer coefficient of aircraft turbine blades viscoplastic response during cyclic loading [ASME PAPER 88-GT-661 p 847 A88-54197 [AD-A194875] p 856 N88-30163 High performance turbofan afterburner systems On the prediction of unsteady forces on gas turbine TURBOCOMPRESSORS p 842 N88-29922 blades I - Typical results and potential-flow-interaction Wake-induced unsteady aerodynamic interactions in a Contaminationand distortion of steady flow field induced effects multistage compressor p 785 A88-52686 by discrete frequency disturbances in aircraft gas [ASME PAPER 88-GT-891 p 789 A88-54213 The effect of the inlet velocity profile in the engines On the prediction of unsteady forces on gas-turbine three-dimensional flow in a rear axial compressor stage [ AD-AI 954401 p 854 N88-30069 blades I1 - Viscous-wake-interaction and axial-gap [ASME PAPER 88-GT-461 p 787 A88-54183 Development and installation of an instrumentation effects Expenmental investigationof multistageinteraction gust package for GE F404 investigative testing [ASME PAPER 88 GT-901 p 789 A88-54214 aerodynamics [AD-A196265] p 855 N88-30107 The influence of turbine clearance gap leakage on [ASME PAPER 88-GT-561 p 787 A88-54188 TURBOFANS passage velocity and heat transfer near blade tips I - Sink Design point vanation of 3-D loss and deviation for axial Design of high performance fans using advanced flow effects on blade pressure side compressor middle stages aerodynamic codes [ASME PAPER 88-GT-981 p 790 A88-54218 [ASME PAPER 88-GT-571 p 787 A88-54189 [ASME PAPER 88-GT-1411 p 791 A8834244 SUBJECT INDEX VELOCITY DISTRIBUTION

TURBOJET ENGINE CONTROL TURBULENTBOUNDARYLAYER UNDER SURFACE BLOWING Multivariable turbofan engine control for full flight Application of a hybrid analytical/ numerical method to Analysis of a fixed-pitch X-wing rotor employing lower envelope operation the practical computation of supercritical viscous/ inviscid surface blowing [ASME PAPER 88-GT-61 p 81 8 A88-54153 transonic flow fields p 795 A88-54907 [AD-AI 87379 1 p 800 N88-29779 Data flow analysis of concurrency in a turbojet engine A mapping of the viscous flow behavior in a controlled UNSTEADY AERODYNAMICS control program p 823 A88-54622 diffusion compressor cascade using laser Doppler Wake-induced unsteady aerodynamic interactions in a TURBOJET ENGINES velocimetry and preliminary evaluation of codes for the multistage compressor p 785 A88-52686 ATR propulsion system design and vehicle integration prediction of stall On the prediction of unsteady forces on gas-turbine --- AirTurboRamjet [AD-A1944901 p 853 N88-29112 blades. II - Viscous-wake-interaction and axial-gap [AIAA PAPER 88-30711 p 816 A88-53136 Studies of gas turbine heat transfer airfoil surface and effects Propulsion system integration for Mach 4 to 6 vehicles end-wall cooling effects l ASME PAPER 88-GT-901 p 789 A88-54214 [AD-A195165] p 825 N88-29805 [AIAA PAPER 88-3239Al p 805 A88-53149 Numerical simulation of inviscid transonic flow through TURBULENT FLOW Response of large turbofan and turbojet engines to a nozzles with fluctuating back pressure Combustion-generated turbulence in practical short-duration overpressure [ASME PAPER 88-GT-2871 p 794 A88-54356 combustors p 81 5 A88-52676 [ASME PAPER 88-GT-2731 p 821 A88-54346 Navier-Stokes solutions for rotating 3-D duct flows Nonuniform vane spacing effects on rotor blade forced TURBOMACHINERY [AIAA PAPER 88-30981 p 844 A88-53142 response and noise generation p 796 A88-54944 Development of a 3D Navier Stokes solver for application Prediction of the pressure distribution for radial inflow An unsteady helicopter rotor: Fuselage interaction to all types of turbomachinery between co-rotating discs analysis [ASME PAPER 88-GT-701 p 788 A88-54201 [ASME PAPER 88-GT-611 p 847 A88-54193 [ NASA-CR-41781 p 784 N88-28880 Computation of three-dimensional turbulent Turbulence measurements in a multistage low-pressure Application of unsteady aerodynamic methods for turbomachinery flows using a coupled parabolic-marching turbine transonic aeroeiastic analysis method [ASME PAPER 88-GT-791 p 788 A88-54207 I NASA-TM-1006651 p 799 N88-29754 [ASME PAPER 88-GT-801 p 788 A88-54208 Computation of three-dimensional turbulent History of aeroelasticity in Germany from the beginning Numerical solution to transonic potential equations on turbomachinery flows using a coupled parabolic-marching to 1945 S2 stream surface in a turbomachine method [ESA-TT-10821 p 799 N88-29767 [ASME PAPER 88-GT-821 p 789 A88-54210 [ASME PAPER 88-GT-801 p 788 A88-54208 Recent advances in transonic computational The oil-free shaft line Evaporation of fuel droplets in turbulent combustor aeroelasticity [ASME PAPER 88-GT-1681 p 849 A88-54263 flow [ NASA-TM-1008631 p 800 N88-29778 Causes for turbomachinery performance deterioration [ASME PAPER 88-GT-1071 p 839 A88-54: '6 Aeroelastic response of metallic and composite propfan [ASME PAPER 88-GT-2941 p 821 A88-54363 Turbulence measurements and secondary flows in a models in yawed flow Three-dimensionalNavier-Stokes simulations of turbine turbine rotor cascade [NASA-TM-100964] p 825 N88-29807 [ASME PAPER 88-GT-2441 p 794 A88-54323 rotor-stator interaction UNSTEADY FLOW Near-field pressure radiation and flow characteristics in [NASA-TM-100081] p 799 N88-29750 Numericalintegration of the 3D unsteadyEuler equations low supersonic circular and elliptic jets TURBOPROP AIRCRAFT for flutter analysis of axial flow compressors p 795 A88-54869 The turboprop challenge design for cost-effective [ASME PAPER 88-GT-2551 p 794 A88-54331 --- TURBULENTHEATTRANSFER regional-route aircraft p 805 A88-53539 The effects of turbulence and statorlrotor interactions An unsteady helicopter rotor: Fuselage interaction Multiple-Purpose Subsonic Naval Aircraft (MPSNA): on turbine heat transfer. II - Effects of Reynolds number analysis Multiple Application Propfan Study (MAPS) and incidence [NASA-CR-4178] p 784 N88-28880 [ NASA-CR-1751041 p 81 1 N88-28917 [ASME PAPER 88-GT-51 p 846 A88-54152 Unsteady water channel TURBOPROP ENGINES Heat transfer, pressure drop, and mass flow rate in pin [AD-A1942311 p 797 N88-28884 Design and test of non-rotating ceramic gas turbine fin channels with long and short trailing edge election Unsteadyflow past an NACA 0012 airfoil at high angles components holes of attack [ASME PAPER 88-GT-1461 p 819 A88-54247 [ASME PAPER 88-GT-421 p 847 A88-54181 [AD-A194650] p 797 N88-28886 Experimental and analytical evaluation of the effects of Studies of gas turbine heat transfer airfoil surface and An integral equation for the linearized unsteady simulated engine inlets on the blade vibratory stresses end-wall cooling effects supersonic flow over a wing of the SR-3 model propfan [ AD-AI 951651 p 825 N88-29805 [AD-AI937731 p 797 N88-28887 [NASA-CR-t74959] p 824 N88-28927 TURBULENT JETS Studies of unsteady axial-compressorfunctioning TURBORAMJET ENGINES The blowout of turbulent jet flames in co-flowingstreams p 855 N88-30129 Combined engines for future launchers of fuel-air mixtures UNSTEADY STATE [AIAA PAPER 88.28231 p 836 A88-53105 [ASME PAPER 88-GT-1061 p 838 A88-54225 Aircraftdynamics:Aerodynamic aspects and wind tunnel TURBOSHAFTS TURBULENT MIXING techniques p 798 N88-29731 A radial mixing computation method Advanced technology engine supportability- Preliminary USER MANUALS (COMPUTER PROGRAMS) designer's challenge [ASME PAPER 88-GT-681 p 847 A88-54199 Aircraft noise prediction program propeller analysis TURBULENT WAKES [AIAA PAPER 88-27961 p 81 5 A88-53102 system IBM-PC version user's manual version 2.0 Measurement and modelling of the gas turbine blade TURBULENCE [ NASA-CR-1816891 p 862 N88-30399 Aerodynamics of seeing on large transport aircraft transition process as disturbed by wakes [ NASA-CR-1831221 p 801 "3.28896 [ASME PAPER 88-GT-2321 p 793 A88-54314 Wake-boundary layer interactionsin an axial flow turbine The effects of inlet turbulence and rotorfstator rotor at off-design conditions v interactions on the aerodynamics and heat transfer of a [ASME PAPER 88-GT-2331 p 793 A88-54315 large-scalerotating turbine model. Volume 3: Heat transfer Hot-wire measurements of compressor blade wakes in VANES data tabulation 65 percent axial spacing a cascade wind tunnel Euler analysis of a swirl recovery vane design for use [NASA-CR-179468] p 824 N88-28930 with an advanced single-rotation propfan [AD-A194737] p 835 N88-28936 [NASA-TM-1013571 p N88-29771 The eflects of inlet turbulence and rotorfstator TWO DIMENSIONAL FLOW 800 interactions on the aerodynamics and heat transfer of a Quasi-3D solutions for transonic. inviscid flows bv VAPOR DEPOSITION large-scalerotating turbine model. Volume 2: Heat transfer adaptive triangulation Processing technology research in composites data tabulation. 15 percent axial spacing [ASME PAPER 88-GT-831 p 789 A88-54211 [AD-A195693] p 841 N88-29890 [NASA-CR-179467] p 825 N88-29804 Multiarid acceleration of the flux-split Euler eauations VARIABLE CYCLE ENGINES TURBULENCE EFFECTS p 796 A88-55077 Scheduling turbofan engine control set points by The effects of turbulence and statorlrotor interactions TWO DIMENSIONAL MODELS semi-infinite optimization p 823 A88-54658 on turbine heat transfer. I - Design operating conditions Application of the theory of anisotropic thin-walled VARIABLE GEOMETRY STRUCTURES [ASME PAPER 88-GT-1251 p 848 A88-54236 beams and plates for wings made from composite Techniques used in the F-I4 variable-sweeptransition Effect of free-streamturbulence. Reynolds number, and material flight experiment incidence on axial turbine cascade performance [ IAF PAPER 88-2751 p 852 A88-55372 [ NASA-TM-1004441 p 855 N88-30093 [ASME PAPER 88-GT-1521 p 791 A88-54252 VARIABLE SWEEP WINGS Turbulence effects on the droplet distribution behind Variable Sweep Transition Flight Experiment airblast atomizers p 842 "3-2991 5 U (VSTFE)-parametric pressure distribution boundary layer Radiation transfer in gas turbine combustors stability study and wing glove design task p 843 N88-29929 U.S.S.R. [ NASA-CR-39921 p 798 N88-28894 TURBULENCEMETERS Soviet applications for hypersonic vehicles Variable wing camber control systems for the future [AIM PAPER 88-45071 p 783 A88-53771 Flight test equipment for the on-board measurement of Airbus program wind turbulence p 814 N88-29719 UH-BOA HELICOPTER [MBB-UT-104/88] p 830 N88-28932 Real-time simulation of helicopters using the blade A summary of atmospheric turbulence measurements VARIATIONAL PRINCIPLES with specially-equippedaircraft in the US element method A new variational finite element computation for p 857 N88-29727 [AlAA PAPER 88-45821 p 805 A88-53634 aerodynamic inverse problem in turbines with long Measurement and analysis of low altitude atmospheric ULTRALIGHT AIRCRAFT blades turbulence obtained using a specially instrumented Gnat A comparisonof CFD and full scale VariEze wind tunnel [ASME PAPER 88-GT-2751 p 794 A88-54347 aircraft p 857 N88-29728 results VELOCITY DISTRIBUTION TURBULENCE MODELS [AIAA PAPER 88-44631 p 807 A88-53759 A detailed characterization of the velocity and thermal A comparison between measurements and turbulence Daedalus The making of the legend fields in a model can combustor with wall jet injection models in a turbine cascade passage p 784 A88-55000 [ASME PAPER 88-GT-261 p 81 8 A88-54170 [ASME PAPER 88-GT-2261 p 793 A88-54309 ULTRASONIC FLAW DETECTION The effect of the inlet velocity profile in the Prediction of turbulence generated random vibrational Design considerations in remote testing three-dimensional flow in a rear axial compressor stage response of turbomachinery blading p 796 A88-54946 p 852 A88-55042 [ASME PAPER 88-GT-46) p 787 A88-54183

A-29 VELOCITY MEASUREMENT SUBJECT INDEX

VELOCITY MEASUREMENT VORTEX SHEDDING Advanced Composite Airframe Program (ACAP) - An Turbulence measurements in a multistage low-pressure Base pressure in transonic speeds - A comparison update and final assessment of weight saving potential turbine between theory and experiment [SAWE PAPER 17701 p 808 A88-53781 [ASME PAPER 88 GT-791 p 788 A88-54207 [ASME PAPER 88-GT 1321 p 790 A88-54240 WELDED JOINTS Hot-wire measurements of compressor blade wakes in VORTICES Development of graded reference radiographs for a cascade wind tunnel An airborne system for vortex flow visualization on the aluminum welds. phase 1 [AD-A194737] p 835 N88-28936 F-18 high-alpha research vehicle [ AD-AI 955941 p 855 N88-30140 A mapping of the viscous flow behavior in a controlled [AIAA PAPER 88-4671I p 813 A88-53830 WELDING diffusion compressor cascade using laser Doppler An experimental investigationinto the influence of blade The non-destructivetesting of welds in continuous fibre velocimetry and preliminary evaluation of codes for the leaning on the losses downstream of annular cascades reinforced thermoplastics p 852 A88-55456 prediction of stall with a small diameter-heightratio WHISKER COMPOSITES IAD-A1 944901 p 853 N88-29112 [ASME PAPER 83-GT-191 p 786 A88-54165 Whisker orientation measurements in injection molded VERTICAL TAKEOFF Behaviour of the leg of the horseshoe vortex around Si3N4-SiC composites Development of the T406-AD-400oil scavenge system the idealized blade with zero attack angle by triple hot-wire [ASME PAPER 88-GT-1931 p 839 A88-54282 for the V-22 aircrafl measurements WIND SHEAR [ASME PAPER 88 GT 2971 p 821 A88-54366 [ASME PAPER 88-GT-1971 p 792 A88-54285 Optimization and guidance of penetration landing VERTICAL TAKEOFF AIRCRAFT An expenmental investigation of a vortex flow cascade trajectories in a windshear p 828 A88-54570 Direct Iifl engine for advanced VISTOL transport Robust control strategy for take-off performance in a [ASME PAPER 88-GT-2651 p 794 A88-54341 [AIAA PAPER 88-2890A1 p816 A88-53111 Noise generation and boundary layer effects in windshear p 829 A88-54656 The impact of VTOL on the conceptual design vortex-airfoil interaction and methods of digital hologram Contributions to the modeling of wind shear for danger process analysis for these flow fields studies [AlAA PAPER 88-44791 p 807 A88-53763 [AD-A194191I p 797 N88-28883 [ NASA-TT-202931 p 802 N88-28900 VHSlC (CIRCUITS) Unsteady flow past an NACA 0012 airfoil at high angles WINDTUNNEL APPARATUS Computer programs for calculation of sting pitch and Very high speed integrated circuitslgallium arsenide of attack electronics for aircraft engine controls [AD-A194650] p 797 N88-28886 roll angles required to obtain angles of attack and sideslip p 823 A88-54620 on wind tunnel models [ NASA-TM-1006591 p 835 N88-29820 VIBRATION DAMPING WIND TUNNEL CALIBRATION Control of rotor aerodynamically forced vibrations by W Flow visualization on a small scale splitters p 815 A88-52684 WAKES [AD-A194728] p 835 N88-28935 The minimisation of helicopter vibration through blade Computationof the let-wake flow structure in a low speed Hot-wire measurements of compressor blade wakes in design and active control p 805 A88-53249 centnfugal impeller a cascade wind tunnel Active control of transient rotordynamic vibration by [ASME PAPER 88-GT-2171 p 793 A88-54302 [AD-A194737] p 835 NEB-28936 optimal control methods Unsteady flow past an NACA 0012 airfoil at high angles WIND TUNNEL MODELS [ASME PAPER 88-GT-731 p 858 A88-54202 of attack Computationaltools for Simulation methodologies Approximation schemes for an aeroelastic-control [ AD-A1946501 p 797 N88-28886 p 834 N88-28865 system p 829 A88-54660 WALL FLOW Technology for pressure-instrumented thin airfoil VIBRATION MEASUREMENT Effect of stage loading on endwall flows in an axial flow models Assessment of gas turbine vibration monitonng compressor rotor [ NASA-CR-4173I p 835 N88-28933 [ASME PAPER 88-GT-2041 p 850 A88-54291 [ASME PAPER 88-GT-It1 I p 848 A88-54229 Test of an 0.8-scale model of the AH-64 Apache in the VIBRATION METERS Supersonic wall adaptation in the rubber tube test NASA Langley full-scale wind tunnel Helicopter health monitoring from engine to rotor section of the DFVLR Goettingen [AD-A1961291 p 799 NEB-29768 [ASME PAPER 88 GT-2271 p 809 A88-54310 [IB-222-87-A-08] p 836 N88-29824 Computer programs for calculation of sting pitch and VIBRATION TESTS WALL JETS roll angles required to obtain angles of attack and sideslip The measurement of stress and vibration data in turbine A detailed charactenzation of the velocity and thermal on wind tunnel models blades and aeroengine components fields in a model can combustor with wall jet inlection [ NASA-TM-1006591 p 835 N88-29820 [ASME PAPER 88-GT-I491 p 849 A88-54250 [ASME PAPER 88-GT-261 p 8 18 A88-54170 WIND TUNNEL TESTS Gas temperature measurements in short duration VlSCOPLASTlClN WALL PRESSURE turbomachinerytest facilities An investigation of constitutive models for predicting An experimental study of an adaptive-wall wind tunnel [AIAA PAPER 88-30391 p 844 A88-53128 viscoplastic response during cyclic loading [NASA-CR-1831521 p 835 N88-29821 A comparison of CFD and full scale VariEze wind tunnel [ AD-AI 94875 I p 856 N88-30163 WANKEL ENGINES A new source of lightweight. compact multifuel power results VISCOUS DRAG for vehicular. light aircraft and auxiliary applications The [AIAA PAPER 88-44631 p 807 A88-53759 Development and design of windtunnel and test facility - joint Deere Score engines Flight testing of fighters during the World War II era for RPV (Remote Piloted Vehicle) enhancement devices [ASME PAPER 88-GT-2711 p 851 A88-54345 [AIAA PAPER 88-45121 p 862 A88-53773 [ AD-AI 948421 p 836 N88-29822 WARFARE The application of cryogenics to high Reynolds number VISCOUS FLOW Soviet applications for hypersonic vehicles testing in wind tunnels. II - Development and application Developments in computational methods for high-lifl [AIAA PAPER 88-45071 p 783 A88-53771 of the cryogenic wind tunnel concept aerodynamics p 786 A88-53250 WATERTUNNELTESTS p 833 A88-53847 Three-dimensional hypersonic viscous shock layer on Unsteady water channel Gas turbine studies at Oxford 1969-1987 blunt bodies in flow at angles of attack and sideslip [AD-A194231] p 797 N88-28884 [ASME PAPER 88-GT-I121 p 848 A88-54230 p 786 A88-53971 WAVEFORMS Test results and theoretical investigations on the ARL Prediction of compressor cascade performance using Effect of phase errors in stepped-frequency radar 19 supersonic blade cascade a Navier-Stokes technique systems [ ASME PAPER 88-GT-2021 p 792 A88-54289 [ASME PAPER 88-GT-961 p 789 A88-54217 [AD-A194476] p 853 N88-29061 Measurement and modelling of the gas turbine blade Numerical analysis of airfoil and cascade flows by the The 1983 direct strike lightning data, part 1 transition process as disturbed by wakes viscouslinviscid interactive technique [NASA-TM-86426-PT-II p 856 N88-29259 [ASME PAPER 88-GT-2321 p 793 A88-54314 [ASME PAPER 88-GT-1601 p 791 A88-54259 The 1983 direct strike lightning data, part 2 A new method of modeling underexpanded exhaust Numericalsolution of the hypersonic viscous shock layer NASA-TM-86426-PT-21 p 856 N88-29260 plumes for wind tunnel aerodynamic testing equations with chemical nonequilibrium The 1983 direct stnke lightning data, part 3 [ASME PAPER 88-GT-2881 p 834 A88-54357 [IAF PAPER ST-88-08] p 796 A88-55313 [ NASA-TM-86426-PT-31 p 856 N88-29261 Experimental investigation of the performance of a supersonic compressor cascade Calculation of aerodynamic characteristics of airplane WEAPONS DEVELOPMENT [ASME PAPER 88-GT-3061 p 795 A88-54375 configurations at high angles of attack Naw aDDlication of a standard fatiaue and enqine Numericalsolution of the hypersonic viscous shock layer [ NASA-CR-41821 p 797 N88-28891 monitdring'system [AIAA PAPER 88-33151 p 813 A88-53156 equations with chemical nonequilibrium A mapping of the viscous flow behavior in a controlled WEAR RESISTANCE [IAF PAPER ST-88-08] p 796 A88-55313 diffusion compressor cascade using laser Doppler Plasma sprayed tungsten carbide-cobalt coatings High-aspect-ratiowings p 834 N88-28859 velocimetry and preliminary evaluation of codes for the D 845 A88-53579 Complex configurations p 834 N88-28861 prediction of stall WEIGHT (MASS) Effects of independent vanation of Mach and Reynolds AD-A194490 I p 853 N88-29112 Spray automated balancing of rotors Methods and numbers on the low-speed aerodynamic characteristics VISUAL PERCEPTION materials of the NACA 0012 airfoil section The effect of perspectivedisplays on altitude and stability [NASA-CR-1821511 p 836 N88-29825 [ NASA-TM-4074) p 784 N88-28879 control in simulated rotary wing flght WEIGHT ANALYSIS Aerodynamic data accuracy and quality: Requirements [AlAA PAPER 88-46341 p 833 A88-53667 Predicting. determining, and controlling manufacturing and capabilities in wind tunnel testing VOICE CONTROL variation in a new facility --- aircraft production [ AGARD-AR-254 I p 798 N88-28893 Smart command recognizer [SCR) - For development, [SAWE PAPER 17711 p 783 A88-53782 Steady and unsteady transonic pressure measurements test, and implementationof speech commands A different approach to the interrelated subjects of on a clipped delta wing for pitching and control-surface [AlAA PAPER 88-4612) p 858 A88-53654 weight. performance, and price as applied to commercial oscillations VON KARMAN EQUATION transport aircraft I NASA-TP-25941 p 798 NEB-28895 Prediction of the pressure distribution for radial inflow [SAWE PAPER 17791 p 808 A88-53786 Test results at transonic speeds on a contoured between co-rotating discs Estimatingfuselage weight penalty required to suppress over-the-wing propfan model [ASME PAPER 88-GT-61I p 847 A88-54193 noise from propfans [ NASA-TM-882061 p 811 N88-28918 VORTEX FILAMENTS [ SAWE PAPER 1787 1 p 809 A88-53790 Experimentaland analytical evaluation of the effects of The vortex-filament nature of the reverse flow on the WEIGHT REDUCTION simulated engine inletS on the blade vibratory stresses verge of rotating stall CIC composite materials for aircraft brakes of the SR-3 model propfan [ASME PAPER 88-GT 1201 p 848 A88-54234 p 837 A88-53542 [ NASA-CR-1749591 p 824 N88-28927

A-30 SUBJECT INDEX YAW

Test of an 0.8-scale model of the AH-64 Apache in the Y NASA Langley full-scale wind tunnel [AD-At961291 D 799 N88-29768 YAW Pressure distributions from subsonic tests of an Aeroelastic response of metallic and composite propfan advanced laminar-flow-control wing with leading- and modelsIn yawed {low trailing-edae flam [NASA-TM-100964] p 825 N88-29807 [ NAS?!-TM-404O-PT-2] p 800 N88-29776 An experimental study of an adaptive-wall wind tunnel [NASA-CR-183152] p 835 N88-29821 Supersonic wall adaptation in the rubber tube test section of the DFVLR Goettingen [ 18-222-87-A-081 p 836 N88-29824 WIND TUNNEL WALLS An experimental study of an adaptive-wall wind tunnel I NASA-CR-1831521 D 835 N88-29821 WIND TUNNELS Development and design of windtunnel and test facility for RPV (Remote Piloted Vehicle) enhancement devices [AD-A194842] p 836 N88-29822 WIND VELOCITY A review of measured gust responses in the light of modern analysis methods p 830 N88-29724 A summary of atmospheric turbulence measurements with specially-equipped aircraft in the US p 857 “3.29727 Re-assessment of gust statistics using CAADRP data p 831 N88-29732 A digital simulationtechnique for the Dryden atmospheric model [NASA-TT-203421 p 857 N88-30266 WING CAMBER Variable wing camber control systems for the future Airbus program [MBB-UT-104/88] p 830 N88-28932 WING LOADING Fatigue crack propagation test programme for the A320 wing p 804 A88-52662 A summary of methods for establishing airframe design loads from continuous gust design criteria p 81 1 N88-29721 WING PANELS Damage tolerance aspects of an experimental Arall F-27 lower wing skin panel p 804 A88-52668 Damage tolerance of impact damaged carbon fibre composite wing skin laminates p 804 A88-52670 WING PLANFORMS Planform effects on high speed civil transport design [AlAA PAPER 88-44871 p 807 A88-53767 An integral equation for the linearized unsteady supersonic flow over a wing [AD-AI937731 p 797 N88-28887 WINGS Transport-type configurations p 809 N88-28867 An integral equation for the linearized unsteady supersonic flow over a wing [AD-At 937731 p 797 N88-28887 Critical joints in large composite primary aircraft structures. Volume 2: Technology demonstration test report [NASA-CR-172587] p 811 N88-28915 Critical ioints in large composite primaly aircraft Structures. Volume 3: Ancillary test results [NASA-CR-1725881 p 81 1 N88-28916 Test results at transonic speeds on a contoured over-the-wing propfan model [ NASA-TM-882061 p 811 N88-28918 Development of a glass fiber wing following the construction regulation FAR Part 23 [ ETN-88-929661 p 840 N88-28979 Critical joints in large composite primary aircraft structures. Volume 1: Technical summary [ NASA-CR-39141 p 840 N88-28983 WORKLOADS (PSYCHOPHYSIOLOGY) Threat expert system technology advisor [NASA-CR-1774791 p 831 N88-29816 WORKSTATIONS A workstation for the integrated design and simulation of flight control systems p 827 A88-54474 WROUGHT ALLOYS Service failure of a 7049 T73 aluminum aircraft forging p 840 A88-55286 X

X WING ROTORS Analysis of a fixed-pitch X-wing rotor employing lower surface blowing [ AD-A1673791 p 800 N88-29779 X-29 AIRCRAFT Integrated thrust vectoring on the X-29A [AIAA PAPER 88.44991 p 808 A88-53769

A-3 1 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 234) January 1989

Typical Personal Author Index Listing ALLEN, M. BAKER, WALTER Positron emission tomography: A new technique for Intelligent fault diagnosis and failure management of observing fluid behavior in engineering systems flight control actuation Systems [PNR90471] p 854 N88-30091 [NASA-CR-1774811 p 812 "3-29790 ALLEN, S. M. BAKOW, L Detection, identification and estimation of surface Fatique of elevated temperature powder metallurgy-. alumin& alloy mechanically fastened joints GOUCHOE. D. R. damage/actuator failure for high performance aircraft p 837 A88-52655 The design of a turboshall speed governor usmg modern p 828 A88-54650 BALABUSHKIN, A. N. ANDERSON, BIANCA TRUJILLO Prediction of the extreme values of the phase p 51 NE8 10339 in Techniques used the F-14 variable-sweep transition coordinates of stochastic systems p 857 A8842823 flight experiment BALDWIN, RICHARD M. [ NASA-TM-1004441 p 855 N88-30093 Spray automated balancingof rotors. Concept and initial ANDERSON, 0. L. feasibility study Assessment of a 3-D boundary layer analysis to predict [ASME PAPER 88-GT-1631 p 849 A88 54261 heat transfer and flow field in a turbine passage Spray automated balancing of rotors Methods and [NASA-CR-1748941 p 854 N88-30066 materials ANDERSON, W. KYLE [NASA-CR 1821511 p 836 N88-29825 Multigrid acceleration of the flux-split Euler equations BALL, C. M. p 796 A88-55077 Planform effects on high speed civil transport design ANDREJCZYK, R. [AIAA PAPER 88-44871 p 807 A88-53767 Listings in this index are arranged alphabetically by Use of control feedback theory to understand other BALLAL, D. R. personal author The title of the document provides oscillations Combustion-generated turbulence in practical [ASME PAPER 88-GT-811 p 848 A88-54209 combustors p 81 5 A88-52676 the user with a brief description of the subject ANDREWS, MARK BANCKE, 0. matter The report number helps to indicate the Propulsion system integration for Mach 4 to 6 vehicles High temperature testing of plasma sprayed thermal type of document listed (e g , NASA report. [AIAA PAPER 88-3239Al p 805 A88-53149 barrier coatings p 845 A88-53571 translation. NASA contractor report) The page and AOYAGI, KlYOSHl BANICHUK, N. V. Application of the theory of anisotropic thin-walled accession numbers are located beneath and to the High performance forward swept wing aircraft [ NASA-CASE-ARC-11636-1 ] p 810 N88-28914 beams and plates for wings made from composite right of the title Under any one author's name the material APPLIN, ZACHARY T. [IAF PAPER 88.2751 p 852 A88-55372 accession numbers are arranged in sequence with Pressure distributions from subsonic tests of an BANKS, DANIEL W. the AIAA accession numbers appearing first advanced laminar-flow-control wing with leading- and trailing-edge flaps Aerodynamics in ground effect and predicted landing ground roll of a fighter configuration with a [ NASA-TM-4040-PT-21 p 800 N88-29776 A secondary-nozzlethrust reverser ARNOLD, WILLIAM K. [ NASA-TP-28341 p 799 N88-29752 Energy maneuverability and engine performance ABUAF, N. BANKS, P. requirements Flow in liner holes for counter-current combustion Fine resolution errors in secondary surveillance radar [ASME PAPER 88-GT-3031 p 822 A8844372 systems altitude reporting [ASME PAPER 88-GT-1581 p 839 A8844257 ARVIN, JOHN R. [RSRE 870191 p 802 N88-28906 Development of the T406-AD-400 oil scavenge system ACHARYA, S. N. BANSAL, PREM N. Viability rating by fuel indexing method for the V-22 aircraft Experimentaland analytical evaluation of the effects of p 815 A88-52698 [ASME PAPER 88-GT-2971 p 821 A8844366 simulated engine inlets on the blade vibratory stresses ADAM, P. ASHWORTH, D. A. of the SR-3 model prop-fan Experimental and theoretical aspects of thick thermal Measurement and modelling of the gas turbine blade [ NASA-CR-I749591 p 824 N88-28927 barrier coatings for turbine applications transition process as disturbed by wakes BARILO, V. 0. p 837 A8843566 [ASME PAPER 88-GT-2321 p 793 A88-54314 Deformation and damage of the material of gas turbine ADAMS, R. M. AUYEUNG, S. engine blades during thermal cycling in gas flow Response of large turbofan and turbojet engines to a SR-7A aeroelastic model design report p 845 A88-53954 short-durationoverpressure [ NASA-CR-1747911 p 824 N88-28928 BARNES, A. G. [ASME PAPER 88-GT-2731 p 821 A88-54346 AWASTHI, SHRIKANT The role of simulationin flying qualities and flight control ADDISON, J. S. CIC composite materials for aircraft brakes system related development p 835 N88-29742 Wake-boundary layer interactions in an axial flow turbine p 837 A88-53542 BARNES, TERENCE J. rotor at off-design conditions Canard certification loads Progress toward alleviating [ASME PAPER 88-GT-2331 p 793 A88-54315 FAA concerns ADIBHATLA, SHRIDER B [AIAA PAPER 88.44621 p 807 A8843758 Multivariable turbofan engine control for full flight Current and proposedgust criteria and analysis methods envelope operation BAI, JIE An FAA overview p 830 N88-29718 [ASME PAPER 88-GT-61 p 818 A88-54153 An experimental investigation into the reasons of BARNHART, PAUL J. AINSWORTH, R. W. reducing secondary flow losses by using leaned blades A oreliminarv,", desian studv of SuDersonic. throuah-flow A transient flow facility for the study of the in rectangular turbine cascades with incidence angle fan inlets thermofluid-dynamicsof a full stage turbine under engine [ASME PAPER 88-GT-41 p 786 A88-54151 [AIAA PAPER 88-30751 p 816 A88-53137 representative conditions BAILEY, RANDALL E. BARRERE, M. [ASME PAPER 88-GT-1441 p 849 A88-54245 Ground simulator requirements based on in-flight Flame stabilization in supersonic Combustion Surface heat transfer fluctuationson a turbine rotor blade simulation p 837 A88-53164 due to upstream shock wave passing [AIAA PAPER 88-48091 p 806 A88-53651 BARRON, ROGER L. [ASME PAPER 88-GT-1721 p 791 A88-54266 Improvement of head-up display standards Volume 5 Automated design of continuously-adaptivecontrol - The AKSOY, S. Head up display ILS (InstrumentLanding System) accuracy 'super-controller' strategy for reconfigurable systems Thermomechanical advances for small gas turbine flight tests p 829 A88-54653 enaines - Present caoabilities and future direction in oas [ AD-AI 946021 p 814 "3-28922 BARRY, JACK, JR. generator designs ' BAILLIE, S. W. VISTAIF16 - The next high-performance in-flight [ASME PAPER 88-GT-2131 p 850 A88-54299 The NAE atmospheric research aircraft simulator ALCAZAR, DAVID G. p 815 N88-29730 [AIAA PAPER 88-46101 p 806 A88-53652 Evaluation of bond testing equipment for inspection of BAINES, N. C. BARTON, LYNN A. Army advanced composite airframe structures Flow in single and twin entry radial turbine volutes N-version software demonstration for digital flight [ AD-A1957951 p 841 N88-29885 [ASME PAPER 88-GT-591 p 847 A88-54191 controls ALEXANDER, R. M. BAIRSTO, N. A. [ NASA-CR-I81 483 I p 831 N88-29815 Active control of transient rotordynamic vibration by A UK perspective on Engine Health Monitoring (EHM) BARTSCH. 0. optimal control methods systems for future technology military engines Ultimate factor for structural design of modern fighters [ASME PAPER 88-GT-731 p 858 A8844202 [ASME PAPER 88-GT-1481 p 819 A8844249 [SAWE PAPER 17751 p 808 A88-53784

B- 1 BATINA, JOHN 1. PERSONAL AUTHOR INDEX

BATINA, JOHN T. The effects of inlet turbulence and rotorlstator BRONDINO, 0. Recent advances in transonic computational interactions on the aerodynamics and heat transfer of a Pilotage system for the Pronaos gondola aeroelasticity large-scalerotating turbine model. Volume 2: Heat transfer [IAF PAPER 88-0081 p 809 A88-55317 [ NASA-TM-1006631 p 800 N88-29778 data tabulation. 15 percent axial spacing BROOKS, A. J. BATTEN, T. [ NASA-CR-1794671 p 825 N88-29804 Aerodynamic and heat transfer measurements on a Heat transfer. pressure drop, and mass flow rate in pin BLAJER, W. transonic nozzle guide vane fin channels with long and short trailing edge ejection Modelling of aircraft program motion with application [ASME PAPER 88-GT-101 p 786 A8864157 holes to circular loop simulation p 826 A88-53251 BROOKS, J. R. [ASME PAPER 88-GT-42) p 847 A88-54181 BLAND, SAMUEL R. Future supersonic transport noise - Lessons from the BAYDAR, ADEM Recent advances in transonic computational past Hot-wire measurements of compressor blade wakes in aeroelasticity [AIAA PAPER 88-29891 p 816 A88-53121 a cascade mnd tunnel [ NASA-TM-1006631 p 800 N88-29778 BROUWER, J. BLANTON, KEITH [AD-AI947371 p 835 N88-28936 A detailed characterization of the velocity and thermal Image extrapolation for flight simulator visual systems BEATON. MICHAEL S. fields in a model can combustor with wall jet injection [AIAA PAPER 88-45771 p 832 A88-53629 Fiber metal acoustic materials for gas turbine exhaust [ASME PAPER 88-GT-261 p 818 A88-54170 environments BLOEM, DAVID R. BRUERE, A. [ASME PAPER 88-GT-I751 p 839 A88-54269 Real-time simulation - A tool for development and New version antistatic coating tester BENEK, J. A. verification p 844 A88-53166 Experience with three dimensional composite grids [AIM PAPER 88-46181 p 833 A88-53657 p 860 N88-29324 BODNER. S. R. BRUMM, JUERGEN BENNETT, C. T. Constitutive modeling for isotropic matenals Theoretical investigation of the interaction between a compressor and the components during surge The effect of perspectivedisplays on altitudeand stability [ NASA-CR-1821321 p 826 N88-29811 control in simulated rotary wing flight BOELCS, A. [ASME PAPER 88-GT-2201 p 851 A88-54305 [AIAA PAPER 88-46341 p 833 A88-53667 Influence of deposit on the flow in a turbine cascade BRYANS, A. C. BENNETT, ROBERT M. [ASME PAPER 88-GT-2071 p 792 A88-54293 The relative merits of an inviscid Euler 3-D and quasi-3-D Recent advances in transonic computational Numerical simulation of inviscid transonic flow through analysis for the design of transonic rotors aeroelasticity nozzles with fluctuating back pressure [ASME PAPER 88-GT-691 p 788 A88-54200 [ NASA-TM-1006631 p 800 N88-29778 [ASME PAPER 88-GT-2871 p 794 A88-54356 BUBLITZ, PETER BERA, RAJENDRA K. BOLAND, BRUCE J. History of aeroelasticity in Germany from the beginning Quadrature formula for a double-pole singular integral The criticality of weight and balance on competition to 1945 p 796 A88-55093 aircraft [ESA-TT-10821 p 799 N88-29767 BERENS, THOMAS J. [SAWE PAPER 17561 p 808 A88-53776 BUISINE. D. Multiple-model parameter-adaptive control for in-flight BONNICE, WILLIAM F. Modeling of large stall in axial compressors simulation p 829 A88-54659 Intelligent fault diagnosis and failure management of (VKI-TN-1641 p 853 N88-29124 BERG. MATTHIAS flight control actuation systems BULL, RAYMOND Accounting for service environment in the fatigue [NASA-CR-177481] p 81 2 N88-29790 Direct lift engine for advanced V/STOL transport evaluation of composite airframe structure BOOTH. THOMAS E. [AIAA PAPER 88-2890Al p816 A88-53111 p 804 A88-52665 Prediction of turbulence generated random vibrational BULLMORE, A. J. response of turbomachinery blading p 796 A88-54946 BERGER, HAROLD A comparison of simple analytical models for Development of graded reference radiographs for BORNEMISZA, T. representing propeller aircraft structural and acoustic aluminum welds, phase 1 Companson of ceramic vs. advanced superalloy options responses [ADA1955941 p 855 N88-30140 for a small gas turbine technology demonstrator 1 ISVR-TR-1531 p 861 N88-29523 [ASME PAPER 88-GT-2281 p 851 A88-54311 BERGMANN. H. BUNIN, BRUCE L Ultimate factor for structural design of modern fighters BORODIN, A. I. Critical joints in large composite primary aircraft [SAWE PAPER 17751 p 808 A88-53784 Three-dimensional hypersonic viscous shock layer on structures. Volume 2: Technology demonstration test BERNIUKOV. A. K. blunt bodies in flow at angles of attack and stdeslip report Microprocessor functional-adaptive processing of p 786 A88-53971 [NASA-CR-172587] p 81 1 N88-28915 signals of radio-navigation systems in an onboard BORRADAILE, J. A. Critical joints in large composite primary aircraft subsystem p 802 A88-52952 Towards the optimum ducted UHBR engine structures. Volume 3: Ancillary test results BERRY, D. J. [AIAA PAPER 88-29541 p 816 A88-53119 The measurement of stress and vibration data in turbine [NASA-CR-l72588] p 811 N88-28916 BOSSARD, J. A. Critical joints in large composite primary aircraft blades and aeroengine components ATR propulsion system design and vehicle integration [ASME PAPER 88-GT-1491 p 849 A88-54250 structures. Volume 1: Technical summary [AIAA PAPER 88-30711 p 816 A8843136 BEST. R. C. [NASA-CR-39141 p 840 N88-28983 BOUCHARD, E. E. Flow measurements in rotating stall in a gas turbine BUNNELL, JOHN W. The application of artificial intelligence technology to engine compressor Smart command recognizer (SCR) - For development, aeronautical system design [ASME PAPER 88-GT-2191 p 81 9 A88-54304 test, and implementation of speech commands [AIAA PAPER 88-44261 p 806 A88-53752 BEYER, MARK E. [AIAA PAPER 88.46121 p 858 A8843654 A comparison of CFD and full scale VariEze wind tunnel BOWLES, S. J. BURKHARD, AVERY results The development of acoustic emission for structural EMPTAC (Electromagnetic Pulse Test Aircraft) user's [AIAA PAPER 88-44631 p 807 A88-53759 integrity monitoring of aircraft guide BICKER, C. J. [ ADA196264 1 p 861 N88-30398 [AD-At 950721 p 854 NEB-30006 Near-field pressure radiation and flow characteristics in BOYD, G. L BUROV, VALENTIN MlKHAlLOVlCH low supersonic circular and elliptic jets AGTlOl /ATTAP ceramic technology development Mechanization of joint production during the assembly p 795 A88-54869 [ASME PAPER 88-GT-2431 p 820 A8864322 of aircraft structures p 846 A88-53998 BIEZAD, DANIEL J. BOYD, R. R. BURRUS, D. L. Multiple-model parameter-adaptive control for in-flight High speed transpacific passenger flight Numericalmodels for analyticalpredictions of combustor simulation p 829 A88-54659 [AIAA PAPER 88-44841 p 807 A88-53764 aerothermal performance characteristics BILLMAYER, HANNS J. BOYTOS, JOSEPH F. p 843 N88-29935 Use of color CRTs (Cathode Ray Tubes) in aircraft Navy V/STOL Engine experience in Altitude Test BUSH, ROBERT H. cockpit: A literature search, revision B Facility A three dimensional zonal Navier-Stokes code for [AD-A1950621 p 815 N88-29797 [ASME PAPER 88-GT-3171 p 834 A88-54384 subsonic through hypersonic propulsion flowfields BILLONNET, GILLES BRAATEN, M. E. [AIAA PAPER 88-28301 p 785 A88-53106 Flow computation and blade cascade design in Numerical models for analyitcalpredictionsof combustor BUSHELL, K. W. turbopump turbines aerothermal performance characteristics Future supersonic transport noise - Lessons from the [ ASME PAPER 88-GT-2481 p 820 A88-54326 p 843 N88-29935 past BINDER, A. BRAEUNLING, W. [AIAA PAPER 88-29891 p 816 A88-53121 Turbulence measurements in a multistage low-pressure Detection of separation bubbles by infrared images in EYERS, J. L. turbine transonic turbine cascades Weibull analysis techniques on a desktop computer [ASME PAPER 88-GT-791 p 788 A88-54207 [ASME PAPER 88-GT-331 p 787 A88-54176 [ASME PAPER 88-GT-2851 p 851 A88-54354 BIRDSALL, JAMES C. BRAHNEY. JAMES H. Potential application of composite materials to future Jump strut means shorter takeoff rolls gas turbine engines p 823 A88-54624 p 803 A88-52375 C BLAIR, M. F. The effects of turbulence and statorfrotor interactions BRANSON, ROGER CADDY, MICHAEL J. on turbine heal transfer. II - Effects of Reynolds number Determinationof helicopter simulator time delay and its Energy maneuverability and engine performance and incidence effects on air vehicle development requirements [ASME PAPER 88-GT-51 p 846 A88-54152 [AIAA PAPER 88-46201 p 833 A88-53659 [ASME PAPER 88-GT-3031 p 822 A88-54372 The effects of turbulence and statorfrotor interactions BRASZ, JOOST J. CAGLAYAN, A. K. on turbine heat transfer. I - Design operating conditions Investigation into the effect of tip clearance on Detection, identification and estimation of surface [ASME PAPER 88-GT-1251 p 848 A88-54236 centrifugal compressor performance damagelactuator failure for high performance aircraft The effects of inlet turbulence and rotorfstator [ASME PAPER 88-GT-I901 p 850 A88-54281 p 828 A88-54650 interactions on the aerodvnamics and heat transfer of a BREUER. PHILIP L CALISE. A. J. large-scalerotating turbine model Volume 3 Heat transfer Estimatingfuselage weight penalty required to suppress Tralectory optimization and guidance law development data tabulation 65 percent axial spacing noise from propfans for national aerospace plane applications [NASA-CR-t79468] p 824 N88-28930 [SAWE PAPER 17871 p 809 A88-53790 p 837 A88-54567

8-2 PERSONAL AUTHOR INDEX DAS, SUDHAKAR

CAMERON, C. 0. CHEN. TING-YU COE, HAROLD H. A detailed characterization01 the velocity and thermal Design optimizationof gas turbine blades with geometry Helicopter transmission research at NASA Lewis fields in a model can combustor with wall jet injection and natural frequency constraints Research Center (ASME PAPER 88-GT-261 p 818 A88-54170 [ASME PAPER 88-GT-1051 p 818 A88-54224 [ NASA-TM-1009621 p 855 N88-30128 CAMPBELL, CLARENCE M. CHEN, Y. H. COELHO, P. J. M. Overview of LockheedC-130 High Technology Test Bed Robust control strategy lor take-olf perlormance in a Radiation transfer in gas turbine combustors Program windshear p 829 A88-54656 p 843 N88-29929 [SAWE PAPER 17861 p 808 A88-53789 CHEN, Y. N. COEN. PETER 0. CAO, M. The vortex-filament nature of the reverse flow on the Technology sensitivity studies for a Mach 3 0 civil Influenceof operatingconditions on the atomizationand verge of rotating stall transport distribution of fuel by air blast atomizers [ASME PAPER 88-GT-1201 p 848 A88-54234 [AIM PAPER 88-44691 p 783 A88-53761 p 842 N88-29918 CHENG, V. H. L. COLE, JULIAN 0. Theoretical aerodynamics, transonic flow CAPECE, VINCENT R. Helicopter trajectory planning using optimal control [ AD-At 962471 p N88-29777 Wake-induced unsteady aerodynamic interactions in a theory p 828 A88-54571 800 multistage compressor p 785 A88-52686 COLE, R. CHENG. VICTOR H. L. Experimental investigationof multistage interaction gust Hypervelocity application of tribological coatings Considerationsfor automatednap-of-the-earth rotorcraft aerodynamics p 845 A88-53563 flight p 827 A88-54526 [ASME PAPER 88-GT-561 p 787 A88-54188 COLGREN, RICHARD DEAN Aerodynamically forced response of structurally CHEU, TSU-CHIEN A workstatmn lor the integrated design and simulation mistuned bladed disks in subsonic flow Design optimizationof gas turbine blades with geometry of flight control systems p 827 A88-54474 p 795 A88-54943 and natural frequency constraints CONNELL, STUART 0. CARD, V. [ASME PAPER 88-GT-1051 p 818 A8844224 Quasi-3D solutions for transonic, inviscid flows by A review of measured gust responses in the light of CHEW, J. W. adaptive triangulation modern analysis methods p 830 N88-29724 The use of fins lo reduce the pressure drop in a rotating [ASME PAPER 88-GT-831 p 789 A88-54211 CARR, E. cavity with a radial inllow COPENHAVER, WILLIAM W. A methanolloxygen burning combustor for an aircraft [ASME PAPER 88-GT-581 p 788 A88-54190 Acquisition of unsteady pressure measurements from auxiliary emergency power unit CHEW, JOHN W. a high speed multi-stage compressor [ASME PAPER 88-GT-2361 p 820 A88-54317 Prediction of the pressure distribution for radial inflow [ASME PAPER 88-GT-I891 p 833 A88-54280 CARRERE, A. between co-rotating discs CORBAN, J. E. Studies of unsteady axial-compressorfunctioning [ASME PAPER 88-GT-61I p 847 A8844193 Trajectory Optimization and guidance law development p 855 N88-30129 CHIANG, HSIAO-WE1 0. for national aerospace plane applications CARRIER, GILLES Aerodynamically forced response of an airfoil including p 837 A88-54567 Design and test 01 non-rotating ceramic gas turbine profile and incidence effects P 795 A88-54941 COSTELLO, M. F. components CHILES, HARRY R. Design concepts for an Advanced Cargo Rotorcraft [ASME PAPER 88-GT-1461 p 81 9 A88-54247 Techniques used in the F-14 variable-sweep transition [AIAA PAPER 88-44961 p 807 A88-53768 CARVALHO, M. G. flight experiment COSTIGAN, MICHAEL J. Radiation transfer in gas turbine cornbustors [ NASA-TM-1004441 p 855 N88-30093 An analysis of lateral-directional handling qualities and p 843 N88-29929 CHIN, HUBERT H. Eigenstructure of high performance aircraft CASEY, J. K. A knowledge based system of supermaneuver selection [ AD-AI 948741 p 831 N88-29814 Empirical flutter prediction method for pilot aiding COUPRY, GABRIEL [AD-A195699] p 825 NEB-29810 [AIAA PAPER 88-44421 p 827 A8843755 Extreme gusts distribution p 857 N88-29734 CASS, S. H. CHITSOMBOON, T. COVE, ED Planform effects on high speed civil transport design CFD predictionof the reactingflow field inside a subscale Hypervelocity application of tribological coatings [AIAA PAPER 88-44871 p 807 A88-53767 scramjet combustor p 845 A88-53563 CASTO, CHRIS [AIAA PAPER 88-32591 p 816 A88-53151 COWIE, JOHN G. Digital emulation of the AH-64A contrast tracker CHLEBANOWSKI, JOSEPH S., JR. Helicopter crew seat failure analysis [AIAA PAPER 88-465261 p 813 A88-53827 Flow visualization by laser sheet p 801 A88-55290 COY, JOHN CATTAFESTA, L. N. [AD-At 94481 ] p 853 NEB-2911 I J. Helicopter transmission research a1 NASA Lewis Gas temperature measurements in short duration CHRISPIN, W. J. Research Center turbomachinery test facilities Further aspects of the UK engine technology [ NASA-TM-1009621 p 855 NEB-30128 LAlAA PAPER 88-30391 p 844 A88-53128 demonstrator programme [ASME PAPER 88-GT-1041 p 848 A88-54223 CRAWFORD, DANIEL J. CAVES, ROBERT E. The Langley Advanced Real-Time Simulation (ARTS) An analysis of time and space requirements lor aircraft CHRISTENSEN, K. L. ATR propulsion system design and vehicle integration system turnrounds [AIAA PAPER 88-3071I p 816 A88-53136 [AIAA PAPER 88.45951 p 832 A88-53642 [TT-87051 p 802 N88-29783 CHUANG, C.-H. CRISCUOLO, EDWARD CAZIER, F. W., JR. Periodic neighboring optimum regulator applied to a Development of graded reference radiographs for Steady and unsteady transonic pressure measurements hypersonic scramjet cruiser p 827 A88-54528 aluminum welds, phase 1 on a clipped delta wing for pitching and control-surface CIOKAJLO, JOHN J. [AD-A1955941 p 855 N88-30140 oscillations Advanced technology engine supportability- Preliminary CROSS, A. G. T. [ NASA-TP-25941 p 798 N88-28895 designer's challenge Complex configurations p 834 N88-28861 CELIK, ZEKl [AIAA PAPER 88-27961 p 815 A88-53102 CUELLAR, J. P., JR. An experimental study of an adaptive-wall wind tunnel CIPOLLA, RUSSELL C. Development of a test method lo determine potential INASA-CR-1831521 p 835 N88-29821 Stress intensity factors for cracked metallic structures peroxide content in turbine fuels. Part 2 CHAN, K. S. under rapid thermal loading [ AD-AI 922441 p 841 N88-29042 Constitutive modeling for isotropic materials [AD-A191219] p 840 N88-29004 CUNNINGHAM, HERBERT J. [ NASA-CR-1821321 p 826 N88-29811 Stress intensity factors lor cracked metallic structures Recent advances in transonic computational CHAN, Y. T. under rapid thermal loading aeroelasticity An efficient patched grid Navier-Stokes solution for [AES-8609709F-I ] p 843 N88-29962 [ NASA-TM-1006631 p 800 N88-29778 multiple bodies, phase 1 CLARK, 0. CUNNINGHAM, WILLIAM H. [ AD-At 941661 p 853 N88-29110 Damage tolerance 01 impact damaged carbon libre Navy V/STOL Engine experience in Altitude Test CHAN, Y. Y. composite wing skin laminates p 804 A88-52670 Facility Computationaltools lor simulation methodologies CLARK, KIMBLE J. [ASME PAPER 88-GT-3171 p 834 A88-54384 p 834 N88-28865 Stress intensity factors for cracked metallic structures CURRY, ROBERT E. CHANG, S. B. under rapid thermal loading An airborne system lor vortex llow visualization on the Numerical analysis of airfoil and cascade flows by the [AD-A191219] p 840 NEB-29004 F-18 high-alpha research vehicle viscouslinviscid interactive technique Stress intensity factors for cracked metallic structures [AlAA PAPER 88-46711 p 813 A8843830 [ASME PAPER 88-GT-1601 p 791 A88-54259 under rapid thermal loading (AES-8609709F-l] p 843 N88-29962 CYRUS, VACLAV CHAPMAN, 0. C. The effect of the inlet velocity profile in the CLARKE, L. Testing of the 578-DX proplan propulsion system three-dimensional llow in a rear axial compressor Stage Observed track-keeping performance of DCIO aircraft [AIAA PAPER 88-28041 p 815 A88-53103 [ASME PAPER 88-GT-461 p 787 A88-54183 equipped with the Collins AINS-70 area navigationsystem: CHARLES, R. E. Karlsruhe and Masstricht UACs (Upper Area Control The effect 01 the Reynolds number on the An experimental data base lor the computational fluid centres) three-dimensional flow in a straight compressor cascade dynamics 01 combustors [EEC-2021 p 803 N88-29788 [ASME PAPER 88-GT-2691 p 794 A88-54343 [ASME PAPER 88-GT-251 p 846 A88-54169 CLEAVELAND, DALE R. CHAWNER, J. R. EMPTAC (Electromagnetic Pulse Test Aircraft) user's Generation of multiple block grids for arbitrary 3D guide D geometries p 859 "3.2931 7 [ AD-A195072 1 p 854 N88-30006 CHAWNER, JOHN R. CLEGG. M. A. DAMBRINE. 8. Calibration of CFD methods for high Mach number NiCrAllbentonite thermal spray powder for high Dimensioning of turbine blades for fatigue and creep aeroengine flowfields temperature abradable seals p 837 A88-53556 p 81 7 A88-53167 [ASME PAPER 88-GT-I991 p 792 A88-54286 CLEVELAND, JEFF I., II DAS, SUDHAKAR CHEN, MAO-ZHANG The Langley Advanced Real-Time Simulation (ARTS) Effect of molecular structure on soot formation An experimental investigation of a vortex flow cascade system characteristics of aviation turbine fuels [ASME PAPER 88-GT-2651 p 794 A88-54341 [AlAA PAPER 88-45951 p 832 A88-53642 [ASME PAPER 88-GT-211 p 838 A88-54167

B-3 DAUB, W. J. PERSONAL AUTHOR INDEX

DAUB. W. J. DOWELL, EARL H. ELDER, JOHN F., IV Development of the F404lRM12 for the JAS 39 Asymptotic modal analysis and statistical energy Automated design of continuously-adaptivecontrol - The Gripen analysis ‘super-controller’strategy for reconfigurable systems [ASME PAPER 88-GT-3051 p 822 A8844374 [NASA-CR-1830771 p 861 N88-29514 p 829 A88-54653 DAVID, H. DRACHENBERG, H. ELDER, R. L. Observed track-keeping performance of DClO aircraft Inflight CG-control - System aspects Experimental investigation of rotating stall in a equipped with the Collins AINS-70 area navigation system: [SAWE PAPER 17951 p 827 A8843796 mismatched three stage axial flow compressor Karlsruhe and Masstricht UACs (Upper Area Control DRAKE, MICHAEL L. [ASME PAPER 88-GT-2051 p 850 A88-54292 centres) Economical technology application in commercial Computation of the jet-wakeflow Structurein a low speed r~~c-2021 p 803 N88-29788 transport design centrifugal impeller [SAWE PAPER 17981 p 809 A88-53798 DAVIES. M. R. D. [ASME PAPER 88-GT-2171 p 793 A88-54302 DREES, HERMAN M. A transient flow facility for the study of the ELIASSON, RALF Development and design of windtunnel and test facility thermofluid-dynamics of a full stage turbine under engine Review of research concerning Solid Fuel Ramjet for RPV (Remote Piloted Vehicle) enhancement devices representative conditions (SOFRAM) at the Research Institute of National Defence [AD-A1948421 p N88-29822 [ASME PAPER 88-GT-1441 p 849 A88754245 836 [FOA) 2 DRESS, D. A. DAVIES, WILLIAM J. The applicationof cryogenics to high Reynolds number [FOA-C-20714-2.1] p 826 N88-29813 Real time simulators for use in design of integrated flight ELKINS, C. A. testing in wind tunnels. II - Development and application and propulsion control systems Use of composite materials to repair metal structures [ASME PAPER 88-GT-241 p 818 A88-54168 of the cryogenic wind tunnel concept p 833 A88-53847 p 804 A88-52660 ELSENAAR, A. Potential application of composite materials to future DRING, R. P. gas turbine engines p 823 A88-54624 Transport-type configurations p 809 N88-28867 The effects of turbulence and statorlrotor interactions ENGELBECK, R. M. DAVIS, P. on turbine heat transfer. II Effects of Reynolds number - Multiple-Purpose Subsonic Naval Aircraft (MPSNA): Positron emission tomography: A new technique for and incidence Multiple Application Propfan Study (MAPS) observing fluid behavior in engineering Systems [ASME PAPER 88-GT-51 p 846 A88-54152 [NASA-CR-175104] p 811 N88-28917 [PNR904711 p 854 N88-30091 The effects of turbulence and statorlrotor interactions ENGLEBY, D. S. DAVIS, R. L. on turbine heat transfer. I - Design operating conditions High temperature testing of plasma sprayed thermal Prediction of compressor cascade performance using [ASME PAPER 88-GT-1251 p 848 A8844236 a Navier-Stokes technique The effects of inlet turbulence and rotorlstator barrier coatings p 845 A88-53571 ENGLUND, D. R. [ASME PAPER 88-GT-961 p 789 A88-54217 interactions on the aerodynamics and heat transfer of a Advanced high temperature instrumentation for hot DAWES, W. N. large-scale rotatingturbine model. Volume 3: Heat transfer Developmentof a 317 Navier Stokes solver for application data tabulation 85 percent axial spacing section research applications p 846 A88-54139 EPSTEIN, A. H. to all types of turbomachinery [NASA-CR-1794681 p 824 N88-28930 Gas temperature measurements in short duration (ASME PAPER 88-GT-70) p 788 A88-54201 The effects of inlet turbulence and rotorlstator turbomachinery test facilities Three dimensional flow in radial-inflowturbines interactions on the aerodynamics and heat transfer of a [AIAA PAPER 88.30391 p 844 A88-53128 [ASME PAPER 88-GT-1031 p 790 A88-54222 large-scale rotatingturbine model. Volume 2: Heat transfer Fully scaled transonic turbine rotor heat transfer DE RUYCK, J. data tabulation. 15 percent axial spacing measurements A radial mixing computation method [ NASA-CR-1794671 p 825 N88-29804 [ASME PAPER 88-GT-1711 p 849 A88-54265 [ASME PAPER 88-GT-681 p 847 A88-54199 DU, J. Y. ERIKSSON, LARS-ERIK DEANNA. RUSSELL G. Numerical solution to transonic potential equations on Grid generation on and about a cranked-wing fighter Development of a thermal and structural analysis S2 stream surface in a turbomachine aircraft configuration p 859 N88-29318 procedure for cooled radial turbines [ASME PAPER 88-GT-821 p 789 A88-54210 ESGAR, J. 8. [ASME PAPER 88-GT-181 p 846 A88-54164 DUDLEY, MICHAEL R. Views on the impact of HOST p 818 A88-54146 DEL CORE, A. High performance forward swept wing aircraft EULERT, MARK Aspects of the fatigue behaviour of typical adhesively [NASA-CASE-ARC-11636-1 I p 810 N88-28914 Predicting. determining, and controlling manufacturing bonded aircraft structures p 804 A88-52659 DUDMAN, A. E. variation in a new facility DEMEIS, RICHARD Re-assessment of gust stalistics using CAADRP data [SAWE PAPER 17711 p 783 A88-53782 Composites break the ice p 840 A88-54857 p 831 N88-29732 DENING. D. C. DULIN, 8. The characterization of high temperature electronics for Plasma sprayed tungsten carbide-cobaltcoatings F p 845 A88-53579 future aircraft engine digital electronic control systems FAGAN, JOHN R., JR. p 823 A88-54621 DUNN, M. G. Nonuniformvane spacing effects on rotor blade forced DENNIS, ANTHONY J. Response of large turbofan and turbojet engines to a response and noise generation p 796 A8844944 Advanced structural instrumentation - An overview short-duration overpressure FARGE, T. 2. [AIAA PAPER 88-31441 p 844 A88-53145 [ASME PAPER 88-GT-2731 p 821 A88-54346 Tip leakage in a centrifugal impeller DESAI, MUKUND DVORAK, S. D. [ASME PAPER 88-GT-2101 p 792 A88-54296 Development and demonstration of an on-board mission E3 1OC compressor test analysis of high-speedpost-stall FAROKHI, SAEED planner for helicopters data Analysis of rotor tip clearance loss in axial-flow [ NASA-CR-1774821 p 831 N88-29817 [ NASA-CR-1795211 p 824 N88-28929 turbines p 785 A88-52685 DEUTSCH, OWEN L. FARTHING, P. R. Development and demonstration of an on-board mission The use of fins to reduce the pressure drop in a rotating planner for helicopters E cavity with a radial inflow [ NASA-CR-1774821 p 831 N88-29817 [ASME PAPER 88-GT-581 p 788 A88-54190 DHANIDINA, ARlF EBERLE, A. FAULKNER, HENRY B. Navy application of a standard fatigue and engine Grid generation for an advanced fighter aircraft An emissions database for U.S. Navy and Air Force monitoring system p 859 N88-29319 Aircraft engines [AIAA PAPER 88-33151 p 813 A88-53156 ECKERLE, W. A. [ASME PAPER 88-GT-1291 p 818 A88-54239 DIEFENDORF, RUSSELL J. Nozzle airflow influences on fuel patternation FEELEY, J. TERENCE Processing technology research in composites p 842 N88-29916 Laser - A gas turbine combustor manufacturing tool [ AD-A1956931 p 841 N88-29890 ECKERT, E. R. [ASME PAPER 88-GT-2671 p 851 A88-54342 DIETRICHS, H.-J. Studies of gas turbine heat transfer airfoil surface and FERGUSON, J. G. Detection of separation bubbles by infrared images in end-wall cooling effects Brushes as high performancegas turbine seals transonic turbine cascades [AD-A195165] p 825 N88-29805 [ASME PAPER 88-GT-1821 p 850 A8844273 [ASME PAPER 88-GT-331 p 787 A8844176 EDWARDS, G. R. FIELDING, T. M. DISIMILE, P. J. The non-destructive testing of welds in continuous fibre Evaluation of new materials in the design of aircraft The effects of an excited impinging jet on the local heat reinforcedthermoplastics p 852 A88-55456 structures p 803 A88-52654 transfer coefficient of aircraft turbine blades FISHER, CELIA EGOLF, T. ALAN [ASME PAPER 88-GT-661 p 847 A8834197 Recent advances in engine health management An unsteady helicopter rotor: Fuselage interaction DISKIN, G. S. [ASME PAPER 88-GT-2571 p 820 A8844333 analysis CFD prediction of the reacting flow field inside a subscale FLANDRO, G. A. [NASA-CR-4178] p 784 scramjet combustor “3-28880 Trajectory optimization and guidance law development [AIAA PAPER 88.32591 p 816 A88-53151 EICKHOFF, H. for national aerospace plane applications Influenceof operating conditions on the atomization and DIlTMAR, C. J. p837 A88-54567 i A hyperstable model-followingflight control system used distribution of fuel by air blast atomizers FLEETER, SANFORD for reconfiguration following aircraft impairment p 842 N88-29918 Control of rotor aerodynamically forced vibrations by p 828 A88-54652 EKVALL. J. C. splitters 815 A88-52684 i DIXON, RICHARD Fatigue of elevated temperature powder metallurgy Wake-induced unsteady aerodynamic interactions in a Potential application of composite materials to future aluminum alloy mechanically fastened joints multistage compressor p 785 A88-52686 gas turbine engines p 823 A88-54624 p 837 A88-52655 Experimental investigationof multistage interactiongust DONEGAN, T. L. ELAZAR, YEKUTIEL aerodynamics Experience with three dimensional composite grids A mapping of the viscous flow behavior in a controlled [ASME PAPER 88-GT-561 p787 A88-54188 I p 860 N88-29324 diffusion compressor cascade using laser Doppler Aerodynamically forced response of an airfoil including DOUBLIER. MICHEL velocimetty and preliminary evaluation of codes for the profile and incidence effects p 795 A88-54941 Combined engines for future launchers prediction of stall The aerodynamics of an annular cascade of [AIAA PAPER 88-28231 p 836 A88-53105 [ AD-A1944901 p 853 N88-29112 three-dimensional airfoils p 795 A88-54942 ! 8-4 PERSONAL AUTHOR INDEX HARASGAMA, S. P.

Aerodynamically forced response of structurally GIANNISSIS, 0. L. GROSS, HARRY N. mistuned bladed disks in subsonic flow Experimental investigation of rotating stall in a Application of supercontroller to fighter aircraft p 795 A88-54943 mismatched three stage axial flow compressor reconfiguration p 829 A88-54654 Nonuniform vane spacing effects on rotor blade forced [ASME PAPER 88-GT-2051 p 850 A88-54292 GUARDA, GASTON response and noise generation p 796 A88-54944 GILES, M. 8. Stratified Charge Rotary Engines for aircraft Prediction of turbulence generated random vibrational Fully scaled transonic turbine rotor heat transfer [ ASME PAPER 88-GT-3111 p 822 A88-54379 response of turbomachinery blading p 796 A88-54946 measurements GUDERLEY, KARL G. FODOR, G. E. [ASME PAPER 88-GT-1711 p 849 A88-54265 An integral equation for the linearized unsteady Development of a test method to determine potential GILES, MICHAEL B. supersonic flow over a wing peroxide content in turbine fuels. Part 2 Stator/rotor interaction in a transonic turbine [AD-AI937731 p 797 N88-28887 [ AD-A1922441 p 841 N88-29042 [AIAA PAPER 88-30931 p 785 A88-53140 GUENETTE, G. R. FORBES, WILLIAM B. GILL, B. J. Fully scaled transonic turbine rotor heat transfer Some benefits of distributedcomputing architecturesfor Surface engineering for high temperature measurements training simulators p 858 A88-53671 environments p 845 A88-53840 [ASME PAPER 88-GT-1711 p 849 A88-54265 FORTH, C. J. P. GUL'KO, F. 8. GIRLING, P. A transient flow facility for the study of the S. Prediction of the extreme values of the phase Gas turbine smoke measurement: A smoke generator thermofluid-dynamicsof a full stage turbine under engine coordinates of stochastic systems p 857 A88-52823 for the assessment of current and future techniques representativeconditions GULDER, OMER L. [ASME PAPER 88-GT-1441 p 849 A8844245 p 843 N88-29930 Effect of molecular structure on soot formation FOSTER, G. W. GIURDZHIEV, V. G. characteristics of aviation turbine fuels Measurement and analysis of low altitude atmospheric A problem of optimal control with constraints on the [ASME PAPER 88-GT-211 p 838 A88-54167 turbulence obtained using a specially instrumented Gnat coordinates of the center of mass p 858 A88-53876 GUNNINK, J. W. aircraft p 857 N88-29728 GLADDEN, H. J. Damage tolerance aspects of an experimentalArall F-27 FOURMAUX, A. Review and assessment of the database and numerical lower wing skin panel p 804 A88-52668 Test results and theoretical investigations on the ARL modeling for turbine heat transfer p 817 A88-54141 GUO, Y. 19 supersonic blade cascade GLAVINCEVSKI, BORIS Numerical solution to transonic potential equations on [ASME PAPER 88-GT-2021 p 792 A88-54289 Effect of molecular structure on soot formation S2 stream surface in a turbomachine FOWLES, P. characteristics of aviation turbine fuels [ASME PAPER 88-GT-821 p 789 A88 54210 Positron emission tomography: A new technique for [ASME PAPER 88-GT-211 p 838 A88-54167 GUPTA, DINESH K. observing fluid behavior in engineering systems GODSTON, J. Current status and future trends in turbine application [ PNR904711 p 854 N88-30091 Testing of the 578-DX propfan propulsion system of thermal barrier coatings FRANSSON, T. H. [AIAA PAPER 88-28041 p 815 A88-53103 [ASME PAPER 88-GT-2861 p 851 A88-54355 Numerical simulation of inviscid transonic flow through GOEKGOEL, OGUZ GUPTA. S. K. nozzles with fluctuating back pressure Accounting for service environment in the fatigue Thermal barrier coatings for let engines [ASME PAPER 88-GT-2871 p 794 A88-54356 evaluation of composite airframe structure [ASME PAPER 88-GT 2791 p 840 A88 54351 FREARSON, DAVID E. p 804 A88-52665 GUTMARK, E. VISTA/F16 - The next high-performance in-flight GOLDSTEIN, R. J. Near-field pressure radiation and flow characteristics in simulator Studies of gas turbine heat transfer airfoil surface and low supersonic circular and elliptic jets [AIAA PAPER 88.46101 p 806 A88-53652 end-wall cooling effects p 795 A88 54869 FRITZ, W. [AD-A195165] p 825 N88-29805 Mesh generation for industrial application of Euler and GOLSHANI, FOROUZAN Navier Stokes solvers p 860 N88-29323 Avionic expert systems p 814 N88-29365 H FUJINO, MASARU GOLSON, ELLIS WAYNE Dynamic texture in visual system A fiber optic collective flight control system for HAASE. W. [AIAA PAPER 88.45781 p 832 A88-53630 helicopters Mesh generation for industrial application of Euler and FULTON, K. P. [ AD-A195406 ] p 831 N88-29818 Navier Stokes solvers p 860 N88-29323 Turbulence measurements and secondary flows in a GOODE, GREGORY L. HAGEMAIER, DONALD J. turbine rotor cascade Feasibilitystudy of a microprocessorcontrolled actuator Cost benefits of nondestructive testing in aircraft [ASME PAPER 88-GT-2441 p 794 A88-54323 test mechanism maintenance p 784 A8845041 [AD-A194654] p 860 N88-29337 HAIMES, R. GORANSON, U. G. Fullv scaled transonic turbine rotor heat transfer G Fatigue crack growth characterization of jet transport measurements structures p 803 A88-52653 [ASME PAPER 88-GT-1711 p 849 A88-54265 GABRIEL, EDWARD A. GORANSSON, PETER HAINES. A. B. Canard certification loads Progress toward alleviating - Analysis of the transmissionof sound into the passenger Transport-type configurations p 809 N88-28867 FAA concerns compartment of a propeller aircraft using the finite element Combat aircraft p 810 N88-28868 [AIAA PAPER 88-44621 p 807 A88-53758 method HALE, STEVEN L. GAILLARD, R. [FFA-TN-l988-15] p 861 N88-29520 Use of color CRTs (Cathode Ray Tubes) in aircraft Test results and theoretical investigations on the ARL GOULAS. A. cockpit: A literature search, revision B 19 supersonic blade cascade A fast interactive two-dimensionalblade-to-blade profile [AD-A195062] p 81 5 N88-29797 [ASME PAPER 88-GT-2021 p 792 A88-54289 design method HALL, DAVID W. GAITONDE, DAITA V. [ASME PAPER 88-GT-1001 p 790 A88-54220 Development of a micro-computer based integrated Numerical simulation of nozzle flows GRAHAM, MATTHEW S. design system for high altitude long endurance aircraft [ AD-A1951441 p 854 N88-30064 JUH-1ti redesignedpneumatic boot deicingsystem flight IAlAA PAPER 88-44291 p 807 A88-53754 GALASSO, A. test evaluation HALL, 0. F. Aspects of the fatigue behaviour of typical adhesively [ AD-AI 949181 p 802 N88-29785 Investigation of helicopter rotor bladelwake interactive impulsive noise bonded aircraft structures p 804 A88-52659 GRAVES, C. P. [ NASA-CR-1774351 p 797 N88-28882 GALLUS, H. E. Turbulence measurements and secondarv flows in a HAN, J. C. Experimental investigationof the three-dimensionalflow turbine rotor cascade Heat transfer. pressure drop, and mass flow rate in pin in an annular compressor cascade [ASME PAPER 88-GT-2441 p 794 A88-54323 fin channels with long and short trailing edge ejection [ASME PAPER 88-GT-2011 p 792 A88-54288 GRAVES. RANDOLPH A.. JR. Aerodynamics p 783 A88-53800 holes GAUTHIER, EDMOND J. [ASME PAPER 88-GT-421 p 847 A88-54181 GRAY, 1. G. A different approach to the interrelated subjects of HAN, WANJIN weight. performance, and price as applied to commercial Fatigue crack propagation test programme for the A320 wing p 804 A88-52662 An experimental investigation into the reasons Of transport aircraft reducing secondary flow losses by using leaned blades [SAWE PAPER 17791 p 808 A88-53786 GRAY, LEE G. A turbine wheel design story in rectangular turbine cascades with incidence angle GENTRY, GARL L., JR. [ASME PAPER 88-GT-41 p 786 A88-54151 [ASME PAPER 88-GT-3161 p 822 A88-54383 Pressure distributions from subsonic tests of an An experimentalinvestigation into the influence of blade GREGOREK, G. M. advanced laminar-flow-control wing with leading- and leaning on the losses downstream of annular cascades trailing-edge flaps High speed transpacific passenger flight [AIAA PAPER 88-44841 p 807 A88-53764 with a small diameter-height ratio [ NASA-TM-4040-PT-21 p 800 N88-29776 [ASME PAPER 88-GT-191 p 786 A88-54165 GREGORY-SMITH, D. G. GERHARZ, JOHANN J. Turbulence measurements and secondary flows in a HANDELMAN, DAVID A. Accounting for service environment in the fatigue turbine rotor cascade Rule-based mechanisms of learning for intelligent evaluation of composite airframe structure adaptive flight control p 858 A88-54426 [ASME PAPER 88-GT-2441 p 794 A88-54323 p 804 A88-52665 GREITZER, E. M. HANSMAN, R. JOHN, JR. Enstaff - A standard test sequence for composite A useful similarity principle for let engine exhaust system Preliminary definition of pressure sensing requirements components combining load and environment performance for hypersonic vehicles p 804 A88-52666 [AIAA PAPER 88-30011 p 816 A88-53122 [AIAA PAPER 88-46521 p 813 A88-53826 GEROLYMOS, 0. A. GRIFFITHS, K. C. HARALDSDOTTIR, A. Periodicity. superposition. and 3D effects in supersonic Re-assessmentof gust statistics using CAADRP data Multiple frame rate integration compressor flutter aerodynamics p 831 N88-29732 [AIAA PAPER 88-45791 p 857 A88-53631 [ASME PAPER 88-GT-1361 p 791 A88-54242 GRINEVICH, E. V. HARASGAMA, S. P. Numericalintegration of the 3D unsteady Euler equations Calculation of stress relaxation in the surface-hardened Aerodynamic and heat transfer measurements on a for flutter analysis of axial flow compressors layer near a hole in the disk of a gas-turbine engine transonic nozzle guide vane [ASME PAPER 88-GT-2551 p 794 A88-54331 D 846 A88-53961 [ASME PAPER 88-GT-101 p 786 A88-54157

8-5 HARKER, R. G. PERSONAL AUTHOR INDEX

HARKER. R. G. HILDITCH. M. A. HSIEH. J. M. Rolling element bearing monitoring and diagnostics A transient flow facilily for the study of the Numerical analysis of airfoil and cascade flows by the techniques thermofluiddynamics of a full stage turbine under engine viscous/inviscid interactive technique [ASME PAPER 88-GT-2121 p 850 A88-54298 representative conditions [ASME PAPER 88-GT-1601 p 791 A88-54259 HARRIS, STEVEN 0. [ASME PAPER 88-GT-1441 p 849 A88-54245 HSU, CHUN SHUNG Interactive ploning of NASTRAN aerodynamic models HIMMELSEACH, J. A minimal realization algorithm for flight control using NPLOT and DISSPLA Evaporation of fuel droplets in turbulent combustor systems p 829 A88-54661 [AD-A194115] p 853 N88-29204 flow HUANG, XIAOYAN [ASME PAPER 88-GT-1071 p 839 A88-54226 The use of Bezier polynomial patches lo define the HARRISON, STEVEN G. HIRSCH, CH. Computer programs for generation of NASTRAN and geometrical shape of the flow channels of compressors A radial mixing computation method [ASME PAPER 88-GT-601 p 788 A88-54192 VIBRA-6 aircraft models [ASME PAPER 88-GT-681 p 847 A88-54199 [ AD-AI 954671 p 812 N88-29792 HUESCHEN, RICHARD M. HIX, JIMMY Application of AI methods lo aircraft guidance and HARTSEL, JAMES E. Second sourcing of a let engine control p 827 A88-54424 Advanced technology engine supportabilily - Preliminary [ASME PAPER 88-GT-1451 p 784 A88-54246 HUGHES, D. W. designer's challenge HIXSON, ROY L., 111 Further aspects of the UK engine technology [AlAA PAPER 88-27961 p 815 A88-53102 Flow visualization on a small scale [AD-A1947281 p 835 N88-28935 demonstrator programme HASSAN. H. A. [ ASME PAPER 88-GT-1041 p 848 A88-54223 Gnd embeddingtechnique using Cartesiangrids for Euler HO, CHIH-MING HWANG, C. J. solutions p 796 A88-55094 Unsteady water channel [AD-A194231 p 797 N88-28884 Numerical analysis of airfoil and cascade flows by the HAUPT, U. I HOBES, D. E. viscous/inviscid interactive technique The vortex-filament nature of the reverse flow on the Prediction of compressor cascade performance using [ASME PAPER 88-GT-1801 p 791 A88-54259 verge of rotating stall a Navier-Stokes technique [ASME PAPER 88-GT-1201 p 848 A88-54234 [ASME PAPER 88-GT-961 p 789 A88-54217 HAVEY, C. T. HODSON, H. P. I Multiple-Purpose Subsonic Naval Aircraft (MPSNA): Wake-boundary layer interactions in an axial flow turbine IAKUSHIN, M. I. Multiple Application Propfan Study (MAPS) rotor at offdesign conditions [ NASA-CR-1751041 p 81 1 N88-28917 Conditions of the induction-plasmatronmodeling of the [ASME PAPER 88-GT-2331 p 793 A88-54315 convective nonequilibrium heat transfer of bodies in HAWKESWORTH, M. R. HOEFT, LOTHAR 0. Positron emission tomography: A new technique for hypersonic flow p 786 A88-53970 Development of a MHz RF leak detector technique for INGER, G. R. observing fluid behavior in engineenng systems aircraft hardness surveillance p 81 3 A88-54725 [PNR90471] p 854 N88-30091 Application of a hybrid analyticallnumerical method lo HOEPPNER, DAVID W. the practical computation of supercriticalviscous/inviscid HAWORTH, LORAN A. New apparatus for studying fatigue deformation at high transonic flow fields p 795 A88-54907 JUH-I H redesigned pneumatic boot deicing system flight magnifications p 852 A88-55154 INNOCENTI, MARIO lest evaluation HOFFMAN, PAUL J. Control surface selection based on advanced modes [AD-At 949181 p 802 N88-29785 Multivariable turbofan engine control for full flight performance envelope operation HAWTHORNE, W. R. [AIAA PAPER 88.43561 p 829 A88-55275 Three dimensional flow in radial-inflow turbines [ASME PAPER 88-GT-61 p 818 A88-54153 INOUE, MASAHIRO [ASME PAPER 88-GT-1031 p 790 A88-54222 HOFSTRA, JOSEPH S. Structure of tip clearance flow in an isolated axial HEFFLEY, ROBERT K. Development of a MHz RF leak detector technique for compressor rotor aircraft hardness surveillance p 81 3 A88-54725 Minimum-complexity helicopter Simulation math model [ASME PAPER 88-GT-251I p 794 A8834327 [NASA-CR-177476] p 831 N88-29819 HOH, ROGER H. IOANNOU, M. HELLMANN. GARY K. Advances in llying qualities: Concepts and criteria for Evaluation of new materials in the design of aircraft VISTA/F16 - The next high-performance in-flight a mission onented Hying qualities specification structures p 803 A88-52654 p 812 N88-29739 simulator ISHII, KlYOSHl [AIAA PAPER 88-46103 p 806 A88-53652 HOLEROOK, M. E. Structural design and its improvements through the Development, analysis, and flight test of the Lockheed development of the XF3-30 engine HENCKEN, ALAN Aeronautical System Company HTTB HUD Automated early fatigue damage sensing System [ASME PAPER 88-GT-2611 p 821 A88-54337 [AIAA PAPER 88-45111 p 813 A88-53772 [AD-A195717] p 855 N88-30143 ITOH, M. HOLDEMAN, J. D. V2500 engine collaboration HENDERGOTT, A. Assessment, development, and application of [ PNR904231 p 825 N88-29803 Supersonic wall adaptation in the rubber tube test combustor aerothermal models p 817 A88-54140 section of the DFVLR Goeningen WARY, MATTHEW J. HOLLISTER, WALTER M. Potential application of composite matenals lo future [ 18-222-87-A-081 p 836 N88-29824 Airport surface traffic automation study gas turbine engines p 823 A88-54624 HENDERSON, DOUGLAS [ AD-At 945531 p 835 "3.28934 lnslrumentationand techniques for structural dynamics HOLMES, D. GRAHAM and acoustics measurements Quasi-3D solutions for transonic. inviscid flows by J [AIAA PAPER 88-46671 p 845 A88-53829 adaptive triangulation HENDERSON, GREGORY H. [ASME PAPER 88-GT-831 p 789 A88-54211 JACOBS, STEVE W. Aerodynamically forced response of structurally HOLZMAN, THOMAS G. Vehicle Management Systems - The logical evolution mistuned bladed disks in subsonic flow Artificial intelligence systems for aircraft training - An of integration p 795 A88-54943 evaluation [AIAA PAPER 88-31751 p 826 A88-53148 HENDRICH, LOUIS J. [AIM PAPER 88-45881 p 857 A88-53637 JAEGER, J. A. Preliminary design of two transpacific high speed cwil HONAMI, SHlNJl Linear state variable dynamic model and estimator transports Behaviour of the leg of the horseshoe vortex around design for Allison T406 gas turbine engine [AIAA PAPER 88-4485Bl p 807 A88-53765 the idealized blade with zero anack angle by tnple hot-wire [ASME PAPER 88-GT-2391 p 820 A88-54319 HENRY, J. R. measurements JANSEN. C. J. Transient performance trending for a turbofan engine [ASME PAPER 88-GT-1971 p 792 A88-54285 Present and future developments of the NLR moving [ASME PAPER 88-GT-2221 p 819 A88-54306 HORN, MICHAEL base research flight simulator Precision error in a turbofan engine monitoring system Automated early fabgue damage sensing system [AlAA PAPER 88.45841 p 832 A88-53635 [ASME PAPER 88-GT-2291 p 819 A88-54312 [AD-A195717] p 855 N88-30143 JARFALL, LARS Standard fatigue specimens for fastener evaluation HERMAN, H. HOSKIN, ROBERT F. High temperature testing of plasma sprayed thermal Fiber optics for aircrafl engine controls [ FFA-TN-1987-681 p 858 N88-30157 barrier coatings p 845 A88-53571 p 822 A88-54619 JARVIS, A. F. HOSNY, W. M. XG40 - Advanced combat engine technology HESS, R. A. demonstrator programme Pilot/vehicle analysis of a twin-lift helicopter E3 10Ccompressor test analysis of high-speedpost-stall [ASME PAPER 88-GT-3001 p 821 A88-54369 configurabon in hover p 829 A88-55064 data [ NASA-CR-I79521 I p 824 N88-28929 JASUJA. A. K. HESS, R. W. Spray performanceof a vaporizing fuel injector Aircraft airframe cost estimating relationships: Study HOU, D. A minimal realization algorithm for flight control p 842 N88-29919 approach and conclusions JATEGAONKAR, RAVINDRA systems p 829 A88-54661 [ R-3255-AFI p 813 N88-29795 Estimation of aircraft parameters using filter error HESS, ROBERT W. HOUEOLT, J. C. methods and eaended Kalman filter Status review of atmosphere turbulence and aircraft Steady and unsteady transonic pressure measurements [DFVLR-FB-88-15] p 810 N88-28911 on a clipped delta wing for pitching and control-surface response p 830 N88-29726 JEAL. R. H. oscillations HOURMOUZIADIS, J. Meeting the high temperature challenge - The [NASA-TP-25941 p 798 N88-28895 Turbulence measurementsin a multistage low-pressure non-metallicaero engine p 838 A88-53838 HIEBS, BART D. turbine JENKINS, D. E. Development and design of windtunnel and test facility [ASME PAPER 88-GT-791 p 788 A88-54207 Fine resolution errors in secondary surveillance radar for RPV [Remote Piloted Vehicle) enhancement devices HOWE, R. M. altitude reporting [AD-AI94842 I p 836 N88-29822 Multiple frame rate integration [RSRE-87019] p 802 N88-28906 HIENSTORFER. WOLFGANG G. [AlAA PAPER 88-45791 p 857 A88-53631 JI, LE-JIAN Crash simulation calculations and component HOYNIAK, DANIEL Calculation of complete three-dimensional flow in a idealization for an airframe. Computer code KRASH 79 Control of rotor aerodynamically forced vibrations by centrifugal rotor with spliner blades [ETN-88-92971I p 801 N88-28899 spliners p 815 A88-52684 [ASME PAPER 88-GT-931 p 789 A88-54216

B-6 PERSONAL AUTHOR INDEX KORAKIANITIS, THEODOSIOS P.

JIANG, F. L. K KIMBERLY, JACK L. Numerical analysis of airfoil and cascade flows by the JUH-1 H redesigned pneumatic boot deicing system flight viscouslinviscid interactive technique KAIP, DENNIS D. test evaluation [ASME PAPER 88-GT-1601 p 791 A8844259 Controlleddegradation of resolutionof high-quality flight [ AD-AI 94918 1 p 802 N88-29785 JOHNER, G. simulator images for training effectiveness evaluation KING, D. A. Experimental and theoretical aspects of thick thermal [AD-AI961 891 p 836 N88-29823 Developments in computational methods for hig h-lift barrier coatings for turbine applications KALAC, HASSAN aerodynamics p 786 A88-53250 p 837 A88-53566 Theoretical investigation of the interaction between a KING, S. P. compressor and the components during surge The minimisation of helicopter vibration through blade JOHNSON, A. B. design and active control p 805 A88-53249 Surface heat transfer fluctuations a turbine rotor blade [ASME PAPER 88-GT-2201 p 851 A88-54305 on KIRK, G. E. KANG. BRYAN H. due to upstream shock wave passing V2500 engine collaboration Preliminary definition of pressure sensing requirements [ASME PAPER 88-GT-1721 p 791 A88-54266 (PNR904231 p 825 N88-29803 for hypersonic vehicles JOHNSON, JAMES E. KIRTLEY, K. R. [AIAA PAPER 88-46521 p 81 3 A88-53826 A study of the effect of random input motion on low Computation of three-dimensional turbulent Reynolds number flows KARADIMAS, GEORGES turbomachinery flows using a coupled parabolic-marching [ AD-AI 955591 p 798 N88-29747 Design of high performance fans using advanced method aerodynamic codes JOHNSON, M. W. [ASME PAPER 88-GT-801 p 788 A88-54208 [ASME PAPER 88-GT-1411 p 791 A8844244 Tip leakage in a centrifugal impeller KLAFIN, J. F. [ASME PAPER 88-GT-2101 p 792 A88-54296 KARIM, G. A. Integrated thrust vectoring on the X-29A The blowout of turbulent jet flames in co-flowingstreams [AIAA PAPER 88-44991 p A8863769 JOHNSON, REUBEN F. 808 of fuel-air mixtures KLAMKA, A. Soviet applications for hypersonic vehicles [ASME PAPER 88-GT-1061 p 838 A88-54225 [AlAA PAPER 88-45071 p 783 A88-53771 Multiple-Purpose Subsonic Naval Aircraft (MPSNA): KARMAN, S. L., JR. Multiple Application Propfan Study (MAPS) JOHNSON, TIMOTHY L. Generation of multiple block grids for arbitrary 3D [NASA-CR-1751041 p 81 I N88-28917 Data flow analysis of concurrency in a turbojet engine geometries p 859 N88-29317 KLARMAN. ANTHONY F. control program p 823 A88-54622 KARPOVICH, P. A. An emissions database for U.S. Navy and Air Force JOHNSON, W. W. Fuel property effects on the US Navy's TF30 engine Aircraft engines The effect of perspective displays on altitudeand stability p 826 N88-29911 [ASME PAPER 88-GT-1291 p 818 A88-54239 control in simulated rotary wing flight Fuel effects on flame radiation and hot-section KLAUSMANN, W. [AIAA PAPER 88-46341 p 833 A8843667 durability p 843 N88-29925 Evaporation of fuel droplets in turbulent combustor JOHNSON, WILLIAM V. KASCAK, A. F. flow Simulator transport delay measurement using Active control of transient rotordynamic vibration by [ASME PAPER 88-GT-1071 p 839 A88-54226 steady-state techniques optimal control methods Turbulence effects on the droplet distribution behind [AlAA PAPER 88.46191 p 833 A88-53658 [ASME PAPER 88-GT-731 p 858 A88-54202 airblast atomizers p 842 N88-29915 KLEIN, VLADISLAV KAUFFMAN, C. W. JONES, CHARLES Two biased estimation techniques in linear regression: Real time neutron radiographyapplications in gas turbine A new source of lightweight, compact multifuel power Application to aircraft and internal combustion engine technology for vehicular. light aircraft and auxiliary applications - The [ NASA-TM-1008491 p 860 N88-29489 joint Deere Score engines [ASME PAPER 88-GT-2141 p 850 A88-54300 KNAUF, CHARLES L. [ASME PAPER 88-GT-2711 p 851 A88-54345 KAUFFMAN, JEFFREY B. Assessment of gas turbine vibration monitoring Some benefitsof distributed computing architectures for JONES, CHARLIE L. [ASME PAPER 88-GT-2041 p 850 A88-54291 Real time simulators for use in design of integratedflight training simulators p 858 A88-53671 KNIGHT, DOYLE D. KAUFMAN, PHILIP F. and propulsion control systems Numerical simulation of nozzle flows Crashworthiness vs. airworthiness [ASME PAPER 88-GT-241 p 81 8 A88-54168 [AD-AI951 441 p 854 N88-30064 [SAWE PAPER 17881 p 809 A88-53791 JONES, D. W. KNOTTS. LOUIS H. KAVANAGH, P. Fiber optics based jet engine augmenter viewing Ground simulator requirements based on in-flight Investigation of boundary layer transition and separation system simulation in an axial turbine cascade using glue-on hot-film gages [ASME PAPER 88-GT-3201 p 852 A88-54385 [AIAA PAPER 88-46091 p 806 A8863651 [ASME PAPER 88-GT-1511 p 791 A88-54251 JONES, J. G. KOBAYASHI, AKlRA Effect of free-stream turbulence. Reynolds number, and Measurement and analysis of low altitude atmospheric Microscopic inner damage correlated with mechanical incidence on axial turbine cascade performance turbulence obtained using a specially instrumented Gnat property degradation due to simulated fatigue loading in [ASME PAPER 88-GT-1521 p 791 A88-54252 aircraft p 857 N88-29728 metal matrix composites p 837 A8842657 KAWAHATA, NAGAKATSU JONES, R. R., 111 KOBAYASHI, HlROSHl VSRA in-flight simulator - Its evaluation and Fiber optics based jet engine augmenter viewing Effect of shock wave movement on aerodynamic applications system instability of annular cascade oscillating in transonic flow [AIAA PAPER 88-46051 p 806 A8843649 [ASME PAPER 88-GT-3201 p 852 A88-54385 [ASME PAPER 88-GT-1871 p 792 A8844278 KAYE, J. F. M. KOBELEV, V. V. JONES, T. V. Helicopter health monitoring from engine to rotor Application of the theory of anisotropic thin-walled Gas turbine studies at Oxford 1989-1987 [ASME PAPER 88-GT-2271 p 809 A88-54310 [ASME PAPER 88-GT-1121 p 848 A88-54230 beams and plates lor wings made from composite KAZA. KRISHNA RAO V. JONES, THOMAS S. ma t e ria I Aeroelastic response of metallic and composite propfan [ IAF PAPER 88-275 1 p 852 A88-55372 Development of graded reference radiographs for models in yawed flow KOBLISH. T. aluminum welds, phase 1 [ NASA-TM-I009641 p 825 N88-29807 [AD-A195594] p 855 N88-30140 Numerical correlation of gas turbine combustor ignition KENTFIELD. J. A. C. [ ASME PAPER 88-GT-2421 p 820 A88-54321 JONGEBREUR. A. A. The feasibility, from an installational viewpoint. of KOENIG, DAVID 0. Damage tolerance aspects of an experimental Arall F-27 gas-turbine pressure-gain combustors High performance forward swept wing aircraft lower wing skin panel p 804 A88-52668 [ASME PAPER 88-GT-181I p 849 A88-54272 [ NASA-CASE-ARC-I1636-1 ] p 810 N88-28914 KHALID, M. JOOS, F. KOFF, BERNARD L. Influenceof operating conditions on the atomization and The use of hot-filmtechnique for boundary layer studies FIOO-PW-229 - Higher thrust in same frame size on a 21 percent thick airfoil distribution of fuel by air blast atomizers [ ASME PAPER 88-GT-3121 p 822 A88-54380 p 842 N88-29918 [NAE-AN-451 p 800 N88-29781 KOHL, K. B. KIBRYA. M. G. JOSLYN, H. D. Development of a test method to determine potential The blowout of turbulent iet flames in co-flowinastreams The effects of turbulence and statorlrotor interactions peroxide content in turbine fuels. Part 2 on turbine heat transfer. II - Effects of Reynolds number of fuel-air mixtures [ AD-At 922441 p 841 N88-29042 and incidence [ASME PAPER 88-GT-1061 p 838 A88-54225 KOK, L. J. [ASME PAPER 88-GT-51 p 846 A88-54152 KIDWELL, G. H. Evaluation of new materials in the design of aircraft The effects of turbulence and statorlrotor interactions The application of artificial intelligence technology to structures p 803 A8842654 on turbine heat transfer. I - Design operating conditions aeronautical system design [AIAA PAPER 88.44261 p 806 A88-53752 KOLESNIKOV, A. F. [ASME PAPER 88-GT-1251 p 848 A88-54236 Conditions of the induction-plasmatron modeling of the KIELB, ROBERT E. The effects of inlet turbulence and rotorlstator convective nonequilibrium heat transfer of bodies in Flutter of a fan blade in supersonic axial flow interactions on the aerodynamics and heat transfer of a hypersonic flow p 786 A88-53970 [ASME PAPER 88-GT-781 p 788 A88-54206 large-scale rotatingturbine model. Volume 3: Heat transfer KIKUCHI, HIDEKATSU KOLKMAN. H. J. data tabulation 65 percent axial spacing Structural design and its improvements through the New erosion resistant compressor coatings [NASA-CR-I 794681 p 824 N88-28930 p 839 A88-54277 development of the XF3-30 engine [ASME PAPER 88-GT-I861 The effects of inlet turbulence and rotorlstator [ASME PAPER 88-GT-2611 p 821 A88-54337 KOMODA, MASAKI interactions on the aerodynamics and heat transfer of a KILGORE, R. A. VSRA in-flight simulator - Its evaluation and large-scalerotating turbine model. Volume 2: Heat transfer The application of cryogenics to high Reynolds number applications data tabulation. I5 percent axial spacing testing in wind tunnels II - Development and application [AlAA PAPER 88-46051 p 806 A8833649 [ NASA-CR-1794671 p 825 N88-29804 of the crvoaenic wind tunnel conceDt KORAKIANITIS, THEODOSIOS P. JUSTIZ, CHARLES R. p 833 A88-53847 On the prediction of unsteady forces on gas-turbine NASA Shuttle Training Aircraft flight simulation KIM, E. blades 1 - Typical results and potential-flow-interaction overview Helicopter tralectory planning using optimal control effects [AlAA PAPER 88-46081 p 806 A8843650 theory p 828 A88-54571 [ASME PAPER 88-GT-891 p 789 A88-54213

B-7 KOWALSKI, EDWARD J. PERSONAL AUTHOR INDEX

On the prediction of unsteady forces on gas-turbine LANCIOlTI, A. LIU. DIAN-KUI blades. II . Viscous-wake-interaction and axial-gap Aspects of the fatigue behaviour of typical adhesively Calculation of complete three-dimensional flow in a effects bonded aircraft structures p 804 A88-52659 centrifugal rotor with splitter blades [ASME PAPER 88-GT-901 p 789 A88-54214 LANGFORD, JOHN S. [ASME PAPER 88-GT-931 p 789 A88-54216 KOWALSKI. EDWARD J. Daedalus - The making of the legend LORBER, PETER F. Evaluation of potential engine concepts for a high p 784 A88-55000 An unsteady helicopter rotor: Fuselage interaction altitude long endurance vehicle LAPWORTH, E. L. analysis [ASME PAPER 88-GT-3211 p 822 A88-54386 Comoutationof the iet-wakeflow structurein a low weed [ NASA-03-41781 p 784 N88-28880 KRAUSS, R. H. centriGga1 impeller . LOSFELD, G. Unique. clean-air. continuous-flow, [ASME PAPER 88-GT-2171 p 793 A88-54302 Test results and theoretical investigations on the ARL high-stagnation-temperature facility for supersonic LARICHEV. A. 0. 19 supersonic blade cascade combustion research Application of the theory of anisotropic thin-walled [ASME PAPER 88-GT-2021 p 792 A88-54289 beams and olates for winas made from comoosite [AIM PAPER 88-3059Al p 832 A8843135 LOUIS, J. F. material KREINER, 0. M. Laminar flow velocity and temperature distributions [IAF PAPER 88.2751 p 852 A88-55372 AGTlOl /ATTAP ceramic technology development between coaxial rotating disks of finite radius LARSSON. L. [ASME PAPER 88-GT-2431 p 820 A8834322 [ASME PAPER 88-GT-491 p 847 A88-54185 Development of the F404IRM12 for the JAS 39 LOURENCO, L. KREISEL, GEORGE R. Gnpen Unsteady flow past an NACA 001 2 airfoil at high angles Aircraft avionics and missile system installation cost [ASME PAPER 88-GT-3051 p 822 A88-54374 of attack study. Volume 1. Technical report and appendices A LASTER, MARION L. [ AD-AI946501 p 797 N88-28886 through E Aerodynamic data accuracy and quality Requirements [AD-A194605] p 814 N88-28923 LOW, H. C. and capabilities in wind tunnel testing Spray performance of a vaporizing fuel injector KRETSCHMER, 0. [AGARD-AR-254] p 798 N88-28893 p 842 N88-29919 The characterizatin of combustion by fuel composition: LAU, S. C. LOWRIE, B. W. Measurementsin a small conventional combustor Heat transfer, pressure drop, and mass flow rate in pin Future supersonic transport noise - Lessons from the p 842 N88-29920 fin channels with long and short trailing edge election past KRONES, ROBERT R. holes [AIAA PAPER 88-29891 p 816 A88-53121 Smart command recognizer (SCR) - For development, [ASME PAPER 88-GT-421 p 847 A88-54181 LUCAS, H. test, and implementationof speech commands LAZZERI. L Development of a glass fiber wing following the [AIM PAPER 88-46121 p 858 A88-53654 Aspects of the fatigue behaviour typical adhesively of construction regulation FAR Part 23 bonded aircraft structures p 804 A8842659 KROO, ILAN [ ETN-88-929661 p 840 N88-28979 A quasi-procedural,knowledge-based system for aircraft LEAGUE, MARK A. LUCERO, LUIS Assessment of a Soviet hypersonic transport design Predicting. determining, and controlling manufacturing [AIAA PAPER 88-44281 p 806 A8843753 [AIAA PAPER 88.45061 p 808 A88-53770 Variation in a new facility LEE, EUN U. KROTHAPALLI, A. [SAWE PAPER 1771 ] p 783 A88-53782 AGARD (Advisory Group for Aerospace Research and Unsteadyflow past an NACA 0012 airfoil at high angles LUTHRA, V. K. Development) engine disc material cooperative test of attack Fatigue crack growth characterization of jet transport (supplementary program) [ AD-A1946501 p 797 "3-28886 structures p 803 A8842653 [AD-A193678] p 824 N88-28925 KUMAR, GANESH N. LVMBEROPOULOS, N. LEE, F. P. Development of a thermal and structural analysis Flow in single and twin entry radial turbine volutes procedure for cooled radial turbines Numencal correlation of gas turbine combustor ignition [ASME PAPER 88-GT-591 p 847 A88-54191 [ASME PAPER 88-GT-181 p 846 A88-54164 [ASME PAPER 88 GT-2421 p 820 A88-54321 LVSOV, MlKHAlL IVANOVICH LEFEBVRE, A. H. KURKOV, ANATOLE P. Mechanization of joint production during the assembly Flame speeds in fuel sprays with hydrogen addition Optical measurement of unducted fan blade of aircraft structures p 846 A88-53998 [ASME PAPER 88-GT-201 p 838 A88-54166 deflections LEFEBVRE, ARTHUR H. [NASA-TM-100966] p 853 N88-29142 Atomization of alternative fuels p 842 N88-29913 M KUROSAKA, M. LENNERT, A. E. Contaminationand distortion of steady flow field induced Fiber optics based let engine augmenter viewing MACPHERSON, J. I. by discrete frequency disturbances in aircraft gas system The NAE atmospheric research aircraft engines [ASME PAPER 88-GT-3201 p 852 A8844385 [ AD-AI 954401 p 854 N88-30069 p 815 N88-29730 LEVIN, ALAN 0. MADDUX, GENE KUROUMARU, MOTOO Test results at transonic speeds on a contoured Instrumentationand techniques for structural dynamics Structure of tip clearance flow in an isolated axial over-the-wing propfan model and acoustics measurements compressor rotor [NASA TM-882061 p 81 1 N88-28918 [AIAA PAPER 88-46671 p 845 A88-53829 [ASME PAPER 88-GT-2511 p 794 A88-54327 LEWICKI, DAVID G. MAGNAN, E. R. KURRASCH. E. R. Helicopter transmission research at NASA Lewis Notes on the occurrence and determination of carbon Threat expert system technology advisor Research Center within gas turbine combustors [ NASA-CR-1774791 p 831 N88-29816 [NASA-TM 1009621 p 855 N88-30128 [ASME PAPER 88-GT-1641 p 839 A88-54262 KWUN, HEGEON LEWIN, A. MAKSOUD, T. M. A. Evaluation of bond testing equipment lor inspection of Fibre optic flow sensors based on the 2 focus Tip leakage in a centrifugal impeller Army advanced composite airframe structures principle p 844 A88-52733 [ASME PAPER 88-GT-2101 p 792 A88-54296 [AD-A1957951 p 841 N88-29885 LEWONSKI, J. R. MARCHIONNA, N. Processing pseudo synthetic aperture radar imagesfrom Numerical correlation of gas turbine combustor ignition visual terrain data [ASME PAPER 88-GT-2421 p 820 A88-54321 L [AIAA PAPER 88-45761 p 802 A88-53628 MARR, WILLIAM H. LIFSHITS, IU. B. Advanced Composite Airframe Program (ACAP) - An LADSON, CHARLES L A projection-gnd scheme lor calculating transonic flow update and final assessment of weight saving potential Effects of independent variation of Mach and Reynolds past a profile p 785 A88-52795 [SAWE PAPER 17701 p 808 A88-53781 numbers on the low-speed aerodynamic characteristics LIFSON, ALEXANDER MARRIOlT, J. F. of the NACA 0012 airfoil section Assessment of gas turbine vibration monitoring Helicopter health monitoring from engine to rotor [ NASA-TM-40741 p 784 "3.28879 [ASME PAPER 88-GT-2041 p 850 A88-54291 [ASME PAPER 88-GT-2271 p 809 A88-54310 LAFLAMME, J. G. C. LIJEWSKI, LAWRENCE E. MARSDEN, JOHN Flow measurements in rotating stall in a gas turbine Compositegnd generationfor aircraft configurationswith Caring for the high-time jet p 801 A88-53540 engine compressor the EAGLE code p 859 N88-29321 MARTIN, CHARLES A. [ASME PAPER 88-GT-2191 p 819 A88-54304 LIN, R. R. Air flow performance of air swirlers for gas turbine fuel LAGRAFF, J. E. Active control of transient rotordynamic vibration by nozzles Measurement and modelling of the gas turbine blade optimal control methods [ASME PAPER 88-GT-1081 p 848 A88-54227 transition process as disturbed by wakes [ASME PAPER 88-GT-731 p 858 A88-54202 MASCARELL. J. P. [ASME PAPER 88-GT-2321 p 793 A88-54314 LINCOLN, JOHN W. Dimensioningof turbine blades for fatigue and creep LAKSHMINARAVANA, E. Structural technology transition to new aircraft p 817 A8843167 Computation of three-dimensional turbulent p 805 A88-52673 MASKOW, JUERGEN turbomachineryflows using a coupled parabolic-marching LINDHOLM, U. S. Industrial production of CFRP-components in Airbus method Constitutive modeling for iwtropic materials construction [ASME PAPER 88-GT-801 p 788 A88-54208 [ NASA-CR-1821321 p 826 N88-29811 [SAWE PAPER 17941 p 845 A88-53795 LALLMAN, FREDERICK J. LINDSAY, JOHN T. MATUS, RICHARD J. Eigenstructure assignment for the control of highly Real time neutron radiography applicationsin gas turbine Calibration of CFD methods for high Mach number augmented aircraft p 828 A88-54549 and internal combustion engine technology aeroengine flowfields LAMSON, SCOTT H. [ASME PAPER 88 GT 2141 p 850 A88-54300 [ASME PAPER 88-GT-1991 p 792 A88-54286 Quasi-3D solutions for transonic, inviscid flows by LISSAMAN, PETER B. MAVNOR, J. W., JR. adaptive triangulation Development and design of windtunnel and test facility YA-7F - A twenty year economic life extension at costs [ASME PAPER 88-GT-831 p 789 A88-54211 for RPV (Remote Piloted Vehicle) enhancement devices we can afford LAN, C. EDWARD [AD-At 948421 p 836 N88-29822 [AIAA PAPER 88.44601 p 783 A88-53757 Calculation of aerodynamic characteristics of airplane LITVINOV, ALEKSEI ALEKSEEVICH MCCARTHV, M. L. configurations at high angles of attack Principles of the use of fuels and lubricants in civil Service failure of a 7049 T73 aluminum aircraft forging [ NASA-CR-41821 p 797 N88-28891 aviation p 838 A88-54001 p 840 A88-55286

8-8 PERSONAL AUTHOR INDEX NOLL, B.

MCCAUGHAN, F. E. MIGYANKO, BARRY S. MOUNT, ROBERT E. Numerical results for axial flow compressor instability Application of supercontroller to fighter aircraft Stratified Charge Rotary Engines for aircraft [ASME PAPER 88-GT-2521 p 851 A88-54328 reconfiguration p 829 A88-54654 [ASME PAPER 88-GT-311I p 822 A88-54379 MCCONNELL, ROGER A. MILEY, S. J. MOYLE, IAN N. Avionics system design for high energy fields: A guide Investigation of helicopter rotor blade/wake interactive Analysis of efficiency sensitivity associated with tip for the designer and airworthiness specialist impulsive noise clearance in axial flow compressors [NASA-CR-l8159Ol p 814 N88-28919 [NASA-CR-177435] p 797 N88-28882 [ASME PAPER 88-GT-2161 p 819 A88-54301 MCDANIEL, J. C., JR. MILLER, CHRISTOPHER J. MULARZ, E. J. Unique, clean-air. continuous-flow. Euler analysis of a swirl recovery vane design for use Assessment, development, and application of high-stagnation-temperature facility for supersonic with an advanced single-rotationpropfan combustor aerothermal models p 817 A88-54140 combustion research INASA-TM-I013571 p 800 N88-29771 MULCARE, DENNIS B. [AIAA PAPER 88-3059AI p 832 A88-53135 MILLER, D. P. N-version software demonstration for digital flight MCKENNA, PAUL M. The relative merits of an inviscid Euler 3-0and quasi-3-D controls Investigations into the triggered lightning response of analysis for the design of transonic rotors [NASA-CR-l814831 p 831 N88-29815 the F106B thunderstorm research aircraft [ASME PAPER 88-GT-691 p 788 A88-54200 MURATOVA, L. A. [ NASA-CR-39021 p 856 N88-29258 MILLER, M. Calculation of stress relaxation in the surface-hardened MCKENZIE. A. B. Fatigue crack growth characterization of jet transport layer near a hole in the disk of a gas-turbine engine Experimental investigation of rotating stall in a structures p 803 A88-52653 p 846 A88-53961 mismatched three stage axial flow compressor MILLER, R. A. MURPHY, P. J. [ASME PAPER 88-GT-2051 p 850 A88-54292 Life modeling of thermal barrier coatings for aircraft gas Fiber optics based jet engine augmenter viewing MCKNIGHT, R. L. turbine engines p 838 A88-54145 system Structural analysis applications p 81 7 A88-54143 MINTO, K. DEAN [ASME PAPER 88-GT-3201 p 852 A88-54385 MCMANUS, JOHN W. Towards simultaneous performance - Application of MURROW, H. N. Application of AI methods to aircraft guidance and simultaneous stabilizationtechniques to helicopter engine A summary of atmospheric turbulence measurements control p 827 A88-54424 control p 822 A88-54507 with specially-equippedaircraft in the US MCNEIL, C. L. MITTLEIDER, D. N. p 857 N88-29727 Multiple-Purpose Subsonic Naval Aircraft (MPSNA): Design concepts for an Advanced Cargo Rotorcraft Multiple Application Propfan Study (MAPS) [AIAA PAPER 88-44961 p 807 A88-53768 [ NASA-CR-I751 041 p 81 1 N88-28917 MNICH, MARC A. N MCNEILL, N. J. Minimum-complexityhelicopter simulation math model Evaluation of new materials in the design of aircraft [NASA-CR-1774761 p 831 N88-29819 NAEGELI, D. W. structures p 803 A88-52654 MOELLENHOFF, D. Development of a test method to determine potential MEAUZE, 0. Linear state variable dynamic model and estimator peroxide content in turbine fuels. Part 2 [ AD-A192244 p 841 N88-29042 Test results and theoretical investigations on the ARL design for Allison T406 gas turbine engine 1 19 supersonic blade cascade [ASME PAPER 88-GT-2391 p 820 A88-54319 NAGLE, D. [ASME PAPER 88-GT-2021 p 792 A88-54289 MOFFAlT, W. C. SR-7A aeroelastic model design report MEHMED, ORAL Flow measurements in rotating stall in a gas turbine [NASA-CR-174791I p 824 N88-28928 Aeroelastic response of metallic and composite propfan engine compressor NAIGUS, ROBERT models in yawed flow [ASME PAPER 88-GT-2191 p 81 9 A88-54304 Real-time simulation - A tool for development and [NASA-TM-100964] p 825 N88-29807 Transient performance trending for a turbofan engine verification MEHTA, M. H. [ASME PAPER 88-GT-2221 p 819 A88-54306 [AIAA PAPER 88.46181 p 833 A88-53657 NiCrAlIbentonite thermal spray powder for high Precision error in a turbofan engine monitoring system NAPIER, J. temperature abradable seals p 837 A88-53556 [ASME PAPER 88-GT-2291 p 819 A88-54312 Comparisonof ceramic vs. advanced superalloy options MEIER, 0. E. MOLCZYK, GERALD JON for a small gas turbine technology demonstrator Noise generation and boundary layer effects in IMMP - A computer simulation of fuel CG versusvehicle [ASME PAPER 88-GT-2281 p 851 A88-54311 vortex-airfoil interaction and methods of digital hologram anitude NEAL, JOSEPH analysis for these flow fields [SAWE PAPER 18011 p 827 A88-53799 The aerodynamics of an annular cascade of [AD-A194191I p 797 N88-28883 MOLODKIN, V. I. three-dimensionalairfoils p 795 A88-54942 MELVIN, W. W. Effect of loading asymmetry on the low-cycle fatigue NEIL, J. T. Optimization and guidance of penetration landing of ZhSGF alloy under cyclic temperature changes Whisker orientation measurements in inlection molded trajectories in a windshear p A88-54570 828 p 838 A8843955 Si3N4-SiC composites MENGLE, V. G. MOUOW, MANFRED [ASME PAPER 88-GT-1931 p 839 A88-54282 Incompressible indicia1 response of infinite airfoils in Comparison of the influence of different gust models NEISH, J. SCOTT tandem - Some analytical results p 795 A88-54940 on structural design p 81 1 "3-29722 Cool gas generator systems MENON, P. K. A. MOM, A. J. A. [AIAA PAPER 88-33631 p 805 A88-53161 Helicopter trajectory planning using optimal control AGARD engine disc cooperative test programme NERAYANAN, G. V. theory p 828 A8844571 [AGARD-R-766] p 824 N88-28926 MERRINGTON, G. L Failure analysis for gas turbines Aeroelastic response of metallic and composite propfan models in yawed flow Fault diagnosis of gas turbine engines from transient [ NLR-MP-87037-Ul p 825 N88-29808 [ NASA-TM-1009641 p 825 N88-29807 data MONGIA. H. C. [ASME PAPER 88-GT-2091 p 819 A88-54295 Assessment, development, and application of NERZ, J. MESTRE, A. combustor aerothermal models p 817 A88-54140 High temperature testing of plasma sprayed thermal Flame stabilization in supersonic combustion MOOIJ. H. A. barrier coatings p 845 A88-53571 p 837 A88-53164 Low-speed longitudinal flying qualities of modern NEUBURGER, ANDRE L. METZGER, D. E. transport aircraft p 812 N88-29738 Design and test of non-rotating ceramic gas turbine The influence of turbine clearance gap leakage on MOON, RICHARD N. components passage velocity and heat transfer near blade tips. I - Sink A summary of methods for establishing airframe design [ASME PAPER 88-GT-1461 p 819 A88-54247 flow effects on blade pressure side loads from continuous gust design criteria NEWMAN, RICHARD L. [ASME PAPER 88-GT-981 p 790 A88-54218 p 81 1 N88-29721 Improvement of head-up display standards. Volume 2: The influence of turbine clearance gap leakage on MOORE, EDDIE Evaluationof head-updisplays to enhance unusual attitude passage velocity and heat transfer near blade tips. I1 - Assessment of a Soviet hypersonic transport recovery Source flow effects on blade suction sides [AIAA PAPER 88-45061 p 808 A88-53770 [AD-A194601I p 814 N88-28921 [ASME PAPER 88-GT-991 p 790 A88-54219 MORELLI, PIER0 Improvement of head-up display standards. Volume 5: MEURZEC, J. L. Possible future developments of motorgliders and light Head up display ILS (InstrumentLanding System) accuracy Measured and predicted responses of the Nord 260 aircraft p 805 A88-52697 flight tests aircraft to the low altitude atmospheric turbulence MORETTI, GIN0 [AD-AI 946021 p 814 N88-28922 p 830 N88-29723 Efficient Euler solver with many applications NICHOLS, HERBERT E. MEYER, ROBERT R., JR. p 796 A88-55078 UDF engine/MDBO flight test program Techniques used in the F-14 variable-sweep transition MORRIS, CHARLES E. K., JR. [AIAA PAPER 88-28051 p 815 A88-53104 Some key considerations for high-speed civil flight experiment NICOLL, A. R. [NASA-TM-100444] p 855 N88-30093 transports Plasma sprayed tungsten carbide-cobalt coatings [AIAA PAPER 813-4486] p 783 A88-53760 MICHELTREE, R. A. p 845 A88-53579 MORRIS, SHELBY J., JR. Grid embedding techniqueusing Cartesiangrids for Euler NIKITIN, VALENTIN IL'ICH Some key considerations for high-speed civil solutions p 796 A88-55094 Corrosion and protection of gas turbine blades transports p 838 A88-53996 MIDDENDORF, MATTHEW S. [AIAA PAPER 88-44661 p 783 A88-53760 Simulator transport delay measurement using MOSES, C. A. NOLAN, SANDRA K. steady-state techniques Fuel effects on flame radiation and hot-section Aircraft noise prediction program propeller analysis [AIAA PAPER 88-46191 p 833 A88-53658 durability p 843 N88-29925 system IBM-PC version user's manual version 2.0 YIDDLETON, DAVID 8. MOSIER, S. A. [ NASA-CR-181689) p 862 N88-30399 Simulator evaluation of takeoff performance monitoring Fuel property effects on the US Navy's TF30 engine NOLL, B. system displays p 826 N88-29911 Evaporation of fuel droplets in turbulent combustor [AIAA PAPER 88-4611 1 p 833 A88-53653 MOTALLEBI, F. flow MIELE, A. Base pressure in transonic speeds - A comparison [ASME PAPER 88-GT-1071 p 839 A88-54226 Optimization and guidance of penetration landing between theory and experiment Turbulence effects on the droplet distribution behind trajectories in a windshear p 828 A88-54570 [ASME PAPER 88-GT-1321 p 790 A88-54240 airblast atomizers p 842 N88-29915

B-9 NOONAN, ROBERT A. PERSONAL AUTHOR INDEX

NOONAN, ROBERT A. OXFORD, V. S. PETERSON, JOHN B., JR. Real time simulatorsfor use in design of integrated flight Response of large turbofan and turbojet engines to a High-aspect-ratiowings p 834 N88-28859 and propulsion control systems short-duration overpressure Computer programs for calculation of sting pitch and [ASME PAPER 88-GT-241 p 818 A88 54168 [ASME PAPER 88-GT-2731 p 821 A88 54346 roll angles required to obtain angles of attack and sideslip NORRIS, D. A. on wind tunnel models Whisker orientation measurements in injection molded INASA-TM-1006591 p 835 N88-29820 Si3N4-SiC composites P PFENNINGER, W. [ASME PAPER 88-GT-1931 p 839 A88-54282 PACKARD, GUY W. Suction laminarization of highly swept supersonic NORTHAM, G. B. Lockheed HITB - STOL performance features laminar flow control wings CFD predictionof the reactingflow field insideasubscale [SAWE PAPER 17721 p 808 A8843783 [AIAA PAPER 88-4471] p 786 A88-53762 scramjet combustor PAIGE, M. A. PIPE, KENNETH [AIAA PAPER 88-32591 p 816 A88-53151 Multiple-Purpose Subsonic Naval Aircraft (MPSNA) Recent advances in engine health management NORTON, R. J. G. Multiple Application Propfan Study (MAPS) [ASME PAPER 88-GT-2571 p 820 A8844333 Fully scaled transonic turbine rotor heat transfer [ NASA-CR-1751041 p 811 N88-28917 PITTS. JOAN 1. measurements PALAZZOLO, A. B. Grid generation on and about a cranked-wing fighter [ASME PAPER 88-GT-1711 p 849 A88-54265 Active control of transient rotordynamic vibration by aircraft configuration p 859 N88-29318 NOUSE, H. optimal control methods PLAETSCHKE, ERMlN Effects of incidence on three-dimensional flows in a [ASME PAPER 88-GT-731 p 858 A88-54202 Estimation of aircraft parameters using filter error linear turbine cascade PALMBERG, BJORN methods and extended Kalman filter [ASME PAPER 88-GT-1101 p 790 A88-54228 Standard fatigue specimens for fastener evaluation [ DFVLR-FB-88-15] p 810 N88-28911 [ FFA-TN-1987.681 p 856 N88-30157 PLATT, MELVIN PANDEY. S. An emissions database for U.S. Navy and Air Force 0 Robust control strategy for take-off performance in a Aircraft engines windshear p 829 A88-54656 [ASME PAPER 88-GT-1291 p 818 A88-54239 O'DONNELL, K. A. PARK, JOEL T. PLATZER, M. F. The effect of perspectivedisplays on altitude and stability A study of the effect of random input motion on low Transition modeling effects on viscouslinviscid control in simulated rotary wing flight Reynolds number flows interaction analysis of low Reynolds number airfoil flows [AIM PAPER 88-46341 p 833 A88-53667 [ AD-Al955591 p 798 N88 29747 involving laminar separation bubbles ODGERS, J. PARKER, R. [ASME PAPER 88-GT-321 p 787 A88-54175 Notes on the occurrence and determination of carbon Positron emission tomography A new technique for Numerical simulation of inviscid transonic flow through within gas turbine combustors observing fluid behavior in engineering systems nozzles with fluctuating back pressure [ PNR9047t p 854 N88-30091 [ASME PAPER 88-GT-1641 p 839 A8844262 I [ASME PAPER 88-GT-2871 p 794 A88-54356 PARKER, STEVEN L. The characterizatin of combustion by fuel composition POHL, HANS-WILHELM Measurements in a small conventional combustor Investigations into the triggered lightning response of the F106B thunderstorm research aircraft A contribution to the quantitativeanalysis of the influence p 842 N88-29920 of design parameters on the optimal design of passenger [ NASA-CR 39021 p 856 N88-29258 ODWYER, M. A. PARKES, R. J. aircraft Positron emission tomography A new technique for [ ETN-88-929791 p 810 N88-28912 observing fluid behavior in engineering systems Design aspects of recent developments in Rolls-Royce RE21 1-524 powerplants POIRION, F. [ PNR904711 p 854 N88-30091 [ASME PAPER 88-GT-301I p 821 A88-54370 Measured and predicted responses of the Nord 260 OENEMA, W. aircraft to the low altitude atmospheric turbulence Observed track-keeping performance of DClO aircraft PATANKAR, S. V. Studies of gas turbine heat transfer airfoil surface and p 830 N88-29723 equipped with the Collins AINS-70 area navigationsystem end-wall cooling effects POLANSKY, DANIEL Karlsruhe and Masstricht UACs lUPDer Area Control Development of graded reference radiographs for centres) [ADA1951651 p 825 N88-29805 PATEL, SURESH M. aluminum welds, phase 1 [EEC-ZOZ] p 803 N88-29788 NASA Shuttle Training Aircraft flight simulation [AD-A195594] p 855 N88-30140 OGATA. MASATO overview Dynamic texture in visual system POLLEY, JOHN A. [AlAA PAPER 88.45781 p 832 A8863630 [AlAA PAPER 88.46081 p 806 A88-53650 Multivariable turbofan engine control for full flight PAlTERSON, JAMES C., JR. envelope operation OHTANI, NOBUO Compression pylon Microscopic inner damage correlated with mechanical [ASME PAPER 88-GT-61 p 81 8 A88-54153 property degradation due to simulated fatigue loading in [NASA-CASE-LAR13777-1 1 p 812 N88-29789 POSTLETHWAITE, ALAN metal matrix composites p 837 A88-52657 PATTERSON, ROBERT W. The turboprop challenge p 805 A88-53539 Artificial intelliaence svstems for aircraft trainina An OKIISHI, T. H. POSTLETHWAITE, IAN evaluation Performance of a compressor cascade configuration H(infinity)-optimaldesign for helicopter control with supersonic entrance flow - A review and comparison [AlAA PAPER 88-45881 p 857 A88-53637 p 828 A88-54598 of experiments in three installations PAULE, D. M. POTH, G. E. [ASME PAPER 88-GT-2111 p 793 A88-54297 The effects of an excited impinging jet on the local heat ATR propulsion system design and vehicle integratlon OLDFIELD, M. L. G. transfer coefficient of aircraft turbine blades [AIAA PAPER 88-3071] p 816 A88-53136 [ASME PAPER 88-GT-661 p 847 A88-54197 Surface heat transfer fluctuationson a turbine rotor blade POULIQUEN, MARCEL F. due to upstream shock wave passing PAYNE, B. W. Combined engines for future launchers [ ASME PAPER 88-GT-1721 p 791 A88-54266 Re-assessment of gust statistics using CAADRP data [AIAA PAPER 88.28231 p 836 A88-53105 OLIVER, D. E. p 831 N88-29732 PRATHER, WILLIAM D. The measurement of stress and vibration data in turbine PAYNE, R. C. Development of a MHz RF leak detector technique for blades and aeroengine components Noise levels from a jet-engined aircraft measured at aircraft hardness surveillance p 81 3 A8844725 [ASME PAPER 88-GT-1491 p 849 A88-54250 ground level and at 1.2 in above the ground PRESZ, W. M., JR. OLIVER, M. J. [ NPL-AC-1141 p 861 N88-29524 A useful similarity principle for jet engine exhaust system Surface heat transferfluctuations on a turbine rotor blade PEHA, ROBERT D. performance due to upstream shock wave passing Cool gas generator systems [AlAA PAPER 88-30011 p 816 A88-53122 [ASME PAPER 88-GT-1721 p 791 A88-54266 [AIAA PAPER 88.33631 p 805 A88-53161 PREUSS. T. E. ONG, C. L. PEHRSSON, KIRSTEN M. Damage tolerance of impact damaged carbon fibre Boundary-layerflows in rotating cavities Aircraft avionics and missile system installation cost composite wing skin laminates p 804 A88-52670 [ASME PAPER 88-GT-2921 p 852 A88-54361 study. Volume 1: Technical report and appendices A PROPEN, M. ONO, TAKATSUGU through E Thermomechanical advances for small gas turbine VSRA in-flight simulator - Its evaluation and [AD-AI 946051 p 814 N88-28923 engines - Present capabilities and future direction in gas applications PEIGIN, S. V. generator designs [AlAA PAPER 88-46051 p 806 A88-53649 Three-dimensional hypersonic viscous shock layer on [ASME PAPER 88-GT-2131 p 850 A88-54299 ORLETSKY, D. T. blunt bodies in flow at angles of attack and sideslip PUNDHIR, D. S. Laminar flow velocity and temperature distributions p 786 A88-53971 A study of aerodynamic noise from a contra-rotating between coaxial rotating disks of finite radius axial compressor stage p 823 A88-54938 [ASME PAPER 88-GT-491 p 847 A88-54185 PEISINO, ENRICO A comparison between measurements and turbulence ORLIK-RUECKEMANN, K. J. models in a turbine cascade passage Aircraft dynamics: Aerodynamic aspects and wind tunnel Q techniques p 798 N88-29731 [ASME PAPER 88-GT-226) p 793 A88-54309 OVERSTREET, MARK A. PERALA, RODNEY A. QIN. REN Fiber optics for aircraft engine controls Investigations into the triggered lightning response of A new variational finite element computation for p 822 A88-54619 the F106B thunderstorm research aircraft aerodynamic inverse problem in turbines with long Very high speed integrated circuitslgallium arsenide [ NASA-CR-39021 p 856 N88-29258 blades- __._ I electronics for aircraft engine controls PERSON, LEE H.. JR. [ASME PAPER 88-GT-2751 p 794 A8844347 p 823 A88-54620 Simulator evaluation of takeoff performance monitoring QUAST, A. OWEN, J. M. system displays Detection of separation bubbles by infrared images in The use of fins to reduce the pressure drop in a rotating [AIAA PAPER 88-4611 I p 833 A88-53653 transonic turbine cascades I cavity with a radial inflow PETERS, HANNSJUERGEN [ASME PAPER 88-GT-331 p 787 A88-54178 [ASME PAPER 88-GT-58l p 788 A88-54190 Additional investigations into the aircraft landing QUENTIN, GEORGE H. Boundary-layer flows in rotating cavities process: Test distributions Assessment of gas turbine vibration monitoring [ASME PAPER 88-GT-2921 p 852 A88-54361 [ ESA-IT-I0991 p 810 N88-28913 [ASME PAPER 88-GT-2041 p 850 A88-54291 1

6-10 PERSONAL AUTHOR INDEX SCHULTZ, D. L.

R ROBEL, GREGORY SALEMANN. VICTOR A minimal realization algorithm for flight control Propulsion system integrationfor Mach 4 to 6 vehicles RADCHENKO, V. P. systems p 829 A88-54661 [AIAA PAPER 88-3239Al p 805 A8833149 Calculation of stress relaxation in the surface-hardened ROBERTS, LEONARD SALTER, P. layer near a hole in the disk of a gas-turbine engine An experimental study of an adaptive-wall wind tunnel Positron emission tomography: A new technique for p 846 A88-53961 [NASA-CR-l831521 p 835 N88-29821 observing fluid behavior in engineering systems p 854 N88-30091 RADESPIEL, R. ROBERTS, WILLIAM B. [PNR90471I Grid generation around transport aircraft configurations Design point variation of 3-D loss and deviation for axial SAMARIN, IU. P. using a multi-block structured computational domain compressor middle stages Calculation of stress relaxation in the surface-hardened p 860 N88-29325 [ASME PAPER 88-GT-571 p 787 A88-54189 layer near a hole in the disk of a gas-turbine engine p 846 A88-53961 RAHNAMAI, K. ROGAN, J. E. SAMUELSEN, G. S. Detection. identification and estimation of surface The application of artificial intelligence technology to An experimental data base for the computational fluid damagelactuator failure for high performance aircraft aeronautical system design dynamics of combustors p 828 A88-54650 [AIAA PAPER 88-44261 p 806 A88-53752 RAI, MAN MOHAN [ASME PAPER 88-GT-251 p 846 A88-54169 ROGAN, J. EDWARD Three-dimensional Navier-Stokes simulations of turbine A detailed characterization of the velocity and thermal Development of a micro-computer based integrated rotor-stator interaction fields in a model can combustor with wall jet injection design system for high altitude long endurance aircraft [NASA-TM-100081] p 799 N88-29750 [ASME PAPER 88-GT-261 p 818 A88-54170 [AIAA PAPER 88.4429) p 807 A88-53754 RAITCH, FREDERICK A. The performanceof a surrogate blend in simulating the Test of an 0.8-scale model of the AH-64 Apache in the ROGERS, ERNEST 0. sooting behavior of a practical. distillate JP-4 NASA Langley full-scale wind tunnel Analysis of a fixed-pitch X-wing rotor employing lower [ASME PAPER 88-GT-1941 p 840 A88-54283 [AD-A196129] p 799 N88-29768 surface blowing The performanceof a surrogate blend in simulating JP-4 [ ADA1873791 p 800 N88-29779 RAIZENNE, M. D. in a spray-fueledcombustor p 843 N88-29926 AGARD engine disc cooperative test programme ROGERS, J. D. SANDERCOCK, DONALD M. [AGARD-R-766] p 824 N88-28926 Positron emission tomography: A new technique for Design point variation of 3-0 loss and deviation for axial RAMACHANDRAN, S. observing fluid behavior in engineering systems compressor middle stages Determination of helicopter simulator time delay and its [PNR90471 I p 854 N88-30091 [ASME PAPER 88-GT-571 p 787 A8844189 effects on air vehicle development ROGERS, R. C. SANDY, J. L. [AlAA PAPER 88-46201 p 833 A88-53659 CFD predictionof the reacting flow field inside a subscale Rolling element bearing monitoring and diagnostics RAMAMURTI, V. scramjet combustor techniques Dynamics of helicopter rotors p 809 A8864954 [AIAA PAPER 88-32591 p 816 A88-53151 [ASME PAPER 88-GT-2121 p 850 A88-54298 RAMSDEN, J. M. ROMANOFF, H. P. SANGIS, GEORGES Caring for the high-time jet p 801 A88-53540 Aircraft airframe cost estimating relationships: Study The CFM56 engine family - An internal development RAMSEY, JOHN K. approach and conclusions [ASME PAPER 88-GT-2961 p 862 A88-54365 Fluner of a fan blade in supersonic axial flow [ R-3255-AF] p 813 N88-29795 SARI, 0. Influence of deposit on the flow in a turbine cascade [ASME PAPER 88-GT-781 p 788 A88-54206 ROSE, WILLIAM C. [ASME PAPER 88-GT-2071 p 792 A88-54293 RANKIN, S. M., 111 Aerodynamics of seeing on large transport aircraft Approximation schemes for an aeroelastic-control [ NASA-CR-1831221 p 801 N88-28896 SARMA, P. P. S. system p 829 A88-54660 Viability rating by fuel indexing method ROSFJORD, T. J. p 81 5 A88-52698 RAO, S. VITTAL Nozzle airflow influences on luel panernation Linear state variable dynamic model and estimator p 842 N88-29916 SATTA, ANTONIO A comparison between measurements and turbulence design for Allison T406 gas turbine engine ROSS, EDWARD W. [ASME PAPER 88-GT-2391 p 820 A88-54319 Control systems for platform landings cushioned by air models in a turbine cascade passage [ASME PAPER 88-GT-2261 p 793 A88-54309 RASMUSSEN, N. S. bags Flow in liner holes for counter-current combustion [ AD-A1961 541 p 854 N88-29996 SAUNDERS, D. S. systems ROZENDAAL, RODGER A. Damage tolerance of impact damaged carbon fibre [ASME PAPER 88-GT-1581 p 839 A8844257 Variable Sweep Transition Flight Experiment composite wing skin laminates p 804 A8862670 RAUTENBERG, M. (VSTFE)-parametric pressure distribution boundary layer SCALA, C. M. The vortex-filament nature of the reverse flow on the stability study and wing glove design task The development of acoustic emission for structural verge of rotating stall [ NASA-CR-39921 p 798 N88-28894 integrity monitoring of aircraft [ASME PAPER 88-GT-1201 p 848 A8844234 RUDNICKI, A. R., JR. [ AD-A1962641 p 861 N88-30398 RAY, ASOK YA-7F - A twenty year economic life extension at costs SCEARS, PAUL E. Fault detection in multiply-redundant measurement we can afford The RTM322 engine in the S-70C helicopter systems via sequential testing p 852 A88-54566 [AIAA PAPER 88-44601 p 783 A8843757 [AlAA PAPER 88-45761 p 817 A8843774 RAYMER, DANIEL P. RUDOLPH, TERENCE H. SCHADOW, C. The impact of VTOL on the conceptual design K. Investigations into the triggered lightning response of Near-fieldpressure radiationand llow characteristicsin process the F106B thunderstorm research aircraft low supersonic circular and elliptic jets [AIAA PAPER 88-44791 p 807 A88-53763 [NASA-CR-3902] p 856 N88-29258 p 795 A88-54869 REDDI, M. M. RUED, K. SCHAENZER, G. Structural dynamics of maneuvenng aircraft The influence of turbine clearance gap leakage on [AD-A1923761 p 810 N88-28908 Flight test equipment for the on-board measurement 01 passage velocity and heat transfer near blade tips. I - Sink wind turbulence p 814 N88-29719 REED, EDWARD J. llow effects on blade pressure side SCHEMER, DOMINIQUE A comparison of engine design life optimization results [ASME PAPER 88-GT-981 p 790 A88-54218 Combined engines for future launchers using deterministic and probabilistic life prediction The influence of turbine clearance gap leakage on [AIAA PAPER 88-28231 p 836 A88-53105 techniques passage velocity and heat transfer near blade tips. II - [ASME PAPER 88-GT-2591 p 820 A8844335 Source flow effects on blade suction sides SCHICK, WILBUR R. Spray automated balancing of rotors - Concept and initial REINHART, EUGENE R. [ASME PAPER 88-GT-991 p 790 A88-54219 feasibility study Design considerations in remote testing RUMFORD, K. J. [ASME PAPER 88-GT-1631 p 849 A88-54261 p 852 A88-55042 Use of control feedback theory to understand other RENKEN, JUERGEN oscillations Spray automated balancing of rotors: Methods and Variable wing camber control systems lor the future [ASME PAPER 88-GT-81I p 848 A88-54209 materials Airbus program RUSCHAU, JOHN J. [ NASA-CR-I821 51 1 p 836 N88-29825 [ MBB-UT-l04/88] p 830 N88-28932 Fatigue crack growth characteristics of ARALL SCHMIDT, SUSAN B. RHIE, CHAE M. (trademark). 1 High performance forward swept wing aircraft A full Navier-Stokes analysis of a three dimensional [ ADA1 961851 p 841 N88-29889 [NASA-CASE-ARC-11636-1 1 p 810 N88-28914 hypersonic mixed compression inlet SCHRAGE, D. P. [AIAA PAPER 88-30771 p 785 A88-53138 Design concepts for an Advanced Cargo Rotorcraft RICHARDS, G. A. S [AIAA PAPER 88-44961 p 807 A88-53768 Flame speeds in fuel sprays with hydrogen addition SCHREIBER, H. A. [ASME PAPER 88-GT-201 p 838 A88-54166 SAGUI, R. L. Experimental investigation of the performance of a RICHTER, ElKE Critical joints in large composite primary aircraft supersonic compressor cascade High temperature, lightweight. switched reluctance structures. Volume 3: Ancillary test results [ASME PAPER 88-GT-3061 p 795 A88-54375 motors and generators for luture aircraft engine [NASA-CR-172588] p 81 1 N88-28916 SCHROEDER, TH. applications p 823 A88-54623 SAKSONOV, M. T. Turbulence measurements in a multistage low-pressure RICHWINE, DAVID M. A problem of optimal control with constraints on the turbine An airborne system lor vortex flow visualization on the coordinates of the center of mass p 858 A88-53876 [ASME PAPER 88-GT-791 p 788 A8864207 F-18 high-alpharesearch vehicle SALAS, M. D. [AIAA PAPER 88-46711 p 813 A88-53830 Grid embeddingtechniqueusing Cartesiangridslor Euler SCHUETZ, DIETER RIGBY, M. J. solutions p 796 A88-55094 Enstalf - A standard test sequence for COmpOSite Surface heat transfer fluctuations on a turbine rotor blade SALAS, TOM m. components combining load and envlronment p 804 A88-52666 due to upstream shock wave passing Development of a MHz RF leak detector technique for [ASME PAPER 88-GT-1721 p 791 A88-54266 aircraft hardness surveillance p 813 A8844725 SCHULTZ, D. L. RITCHIE, R. 0. SALEMANN, V. A transient flow facility for the study of the Modeling 01 micromechanisms of fatigue and fracture A new method of modeling underexpanded exhaust thermofluid-dynamics of a full stage turbine under engine in hybrid materials plumes lor wind tunnel aerodynamic testing representative conditions [AD-A195604] p 855 N88-30142 [ASME PAPER 88-GT-2881 p 834 A88-54357 [ASME PAPER 88-GT-1441 p 849 A8844245 B-11 SCHUU, H. D. PERSONAL AUTHOR INDEX

Measurement and modelling of the gas turbine blade SHI, YlJlAN SOBEL, KENNETH M. transition process as disturbed by wakes A digital simulationtechnique for the Dryden atmospheric Eigenstructure assignment for the control of highly [ASME PAPER 88 GT 2321 p 793 A88-54314 model augmented aircraft p 828 A88-54549 SCHUU, H. 0. [ NASA-TT-203421 P 857 NEE-30266 SOBIECZKY, HELMUT Experimental investigationof the three dimensionalflow SHIZAWA, TAKAAKI Analytical surfaces and grids p 860 N88-29322 in an annular compressor cascade Behaviour of the leg of the horseshoe vortex around SOECHTING, F. 0. [ASME PAPER 88 GT 201 I p 792 A88 54288 the idealizedblade with zero attack angle by triple hot-wire Design code verification of external heat transfer SCHWARR, ALAN W. measurements coefficients Analysis of a fixed pitch X-wing rotor employing lower [ASME PAPER 88-GT-1971 p 792 A88-54285 [AIAA PAPER 88-30111 p 844 A88-53123 surface blowing SHYY. W. SOJKA, P. E. [AD-A187379] p 800 N88-29779 Numerical models for analyticalpredictions of combustor Flame speeds in fuel sprays with hydrogen addition aerothermal performance characteristics [ASME PAPER 88-GT-201 p 838 A88-54166 SCHWARTZ, PAUL p 843 N88-29935 SOKOLOWSKI, D. E. Use of a detail cost model to perform conceptual phase SIDDIQI, SHAHID NASA HOST project overview p 817 A88-54138 cost analysis Flight testing of fighters during the World War II era [SAWE PAPER 1784) p 862 A88-53788 Views on the impact of HOST p 818 A88-54146 [AIAA PAPER 88-45121 p 862 A8843773 SOKOLOWSKI, DANIEL E. SCHWARZ, W. SIMON, 6. Toward improved durability in advanced aircraft engine Gnd generation for an advanced fighter aircraft Influenceof operating conditions on the atomizationand hot sections; Proceedings of the Thirty-third ASME p 859 N88 29319 distribution of fuel by air blast atomizers International Gas Turbine and Aeroengine Congress and SCHWEITZER, K. K p 842 N88-29918 Exposition. Amsterdam. Netherlands, June 5-9. 1988 Experimental and theoretical aspects of thick thermal SIMON, T. W. p 817 A88-54137 barrier coatings for turbine applications Studies of gas turbine heat transfer airfoil surface and SORENSON. REESE L. p 837 A88-53566 end-wall cooling effects Three-dimensionalelliptic grid generation for an F-16 SCOTT, J. E., JR. [AD-A195165] p 825 N88-29805 p 859 N88-29315 Unique clean air continuous flow SIMONEAU, R. J. SOTHERAN, A. high stagnation-temperature facility for supersonic Review and assessment of the database and numerical High performance turbofan afterburner systems combustion research modeling for turbine heat transfer p 817 A88-54141 p 842 N88-29922 [AIM PAPER 88 3059Al p 832 A88-53135 SIMPSON, CAROL A. SPENCE, L. M. SCOTT, L. G. Smart command recognizer (SCR) - For development, The CFM56 engine family - An internal development The development of acoustic emission for structural test. and implementationof speech commands [ASME PAPER 88-GT-2961 p 862 A88-54365 integrity monitonng of aircraft [AIAA PAPER 88-46121 p 858 A88-53654 SPEYER, J. L. [ AD-At 96264 1 p 861 N88-30398 SIMPSON, DAVID L Periodic neighbonng optimum regulator applied to a SEASHOLTZ, R. G. New materials and fatigue resistant aircraft design; hypersonic scramjet cruiser p 827 A88-54528 Advanced high temperature instrumentation for hot Proceedings of the Fourteenth ICAF Symposium. Ottawa, SPRAGLE, GREGORY S. section research applications p 846 A88-54139 Canada, June 8-12. 1987 p 803 A88-52651 Calibration of CFD methods for high Mach number SEGAL, C. SINGH, U. P. aeroengine flowfields Unique clean-air continuous flow Viability rabng by fuel indexing method [ASME PAPER 88-GT-1991 p 792 A88-54286 high stagnation-temperature facility for supersonic p 81 5 A88-52698 SRIDHAR, BANAVAR combustion research SINHA, E. K. Considerationsfor automated nap-of-the-earthrotorcraft [AIAA PAPER 88-3059Al p 832 A88-53135 Viability rating by fuel indexing method flight p 827 A88-54526 SEIBERT, W. p 815 A88-52698 SRINIVAS, V. Mesh generation for industrial application of Euler and SITARAM, N. Technology of flight simulation p 805 A88-52692 Navier Stokes solvers p 860 N88-29323 Eflect of stage loading on endwall flows in an axial flow SRIVASTAVA, 6. N. SEIDEL, DAVID A. compressor rotor Navier-Stokes solutions for rotating 3-D duct flows Recent advances in transonic computational [ASME PAPER 88-GT-t11] p 848 A88-54229 [AlAA PAPER 88.30981 p 844 A88-53142 aeroelasticity SIU, s. c. SRIVATSAN, RAGHAVACHARI [ NASA-TM-1006631 p 800 N88-29778 Modeling of micromechanisms of fatigue and fracture Simulator evaluation of takeoff performance monitoring SELBACH, H in hybrid materials system displays Fibre optic flow sensors based on the 2 focus [ AD-AI 956041 p 855 N88-30142 [AIAA PAPER 88-4611 ] p 833 A88-53653 principle p 844 A8842733 SJOLANDER, S. A. STAB, RICHARD 0. SENSBURG, 0. Flow field in the tip gap of a planar cascade of turbine The Langley Advanced Real-Time Simulation (ARTS) Ultimate factor for structural design of modern fighters blades system [SAWE PAPER 17751 p 808 A88-53784 [ASME PAPER 88-GT-291 p 787 A88-54173 [AIAA PAPER 88.45951 p 832 A88-53642 SEROVY, G. K. SKELTON, R. T. STANEWSKY, E. Performance of a compressor cascade configuration Positron emission tomography: A new technique for Supersonic wall adaptation in the rubber tube test with supersonic entrance flow - A review and comparison observing fluid behavior in engineenng systems section of the DNLR Goettingen of experiments in three installations [PNR904711 p 854 N88-30091 [ 18-222-87-A-081 p 836 N88-29824 [ASME PAPER 88-GT 21 1 I p 793 A88-54297 SKIRA. CHARLES A. STARKEN, H. SEROVY. GEORGE K. Vehicle Management Systems - The logical evolution Experimental investigation of the performance of a Design point variation of 3-0 loss and deviation for axial of integration supersonic compressor cascade compressor middle stages [AlAA PAPER 88-31751 p 826 A88-53148 [ASME PAPER 88-GT-3061 p 795 A88-54375 [ASME PAPER 88-GT 571 p 787 A88 54189 SMALLEY, ANTHONY J. STEENKEN, W. G. SEWELL, PETER Spray automatedbalancing of rotors - Concept and initial E3 1OC compressortest analysis of high-speedpost-stall The RTM322 engine in the S-70C helicopter feasibility study data [AIAA PAPER 88-45761 p 817 A88-53774 [ASME PAPER 88-GT-1631 p 849 A88-54261 [NASA-CR-179521] p 824 N88-28929 SHAFFER. DAVID A. Assessment of gas turbine vibration monitoring STEGER, J. L. An investigation of constitutive models for predicting [ASME PAPER 88-GT-2041 p 850 A88-54291 Three dimensional grid generation for complex viscoplastic response during cyclic loading Spray automated balancing of rotors: Methods and configurations: Recent progress [AD A1948751 p 856 N88 30163 materials [AGARD-AG-3091 p 858 N88-29313 SHAFFER, PHILLIP L [ NASA-CR-1821511 p 836 N88-29825 STEINBRENNER, J. P. Data flow analysis of concurrency in a turbojet engine SMELTZER, DONALD B. Generation of multiple block grids for arbitrary 3D control program p 823 A88 54622 Test results at transonic speeds on a contoured geometries p 859 N88-29317 SHAGAEV, A. A. over-the-wingpropfan model STEINHOFF, JOHN A projection-grid scheme for calculating transonic flow [NASA-TM-88206] p 811 NEB-28918 Algebraic grid generation for fighter type aircraft past a profile p 785 A88-52795 SMITH, 0. E. p 859 N88-29320 SHARMA, 0. P. Testing of the 578-DX propfan propulsion system STENGEL, ROBERT F. Design code verification of external heat transfer [AIAA PAPER 88.28041 p 815 A88-53103 Rule-based mechanisms of learning for intelligent coefficients SMITH, M. J. T. adaptive flight control p 858 A88-54426 [AIAA PAPER 88-3011 I p 844 A88-53123 Future supersonic transport noise - Lessons from the STEPHENS, ROBERT R. SHARMA, P. B. past New apparatus for studying fatigue deformation at high A study of aerodynamic noise from a contra rotating (AIAA PAPER 88-29891 p 816 A88-53121 magnifications p 852 A88-55154 axial compressor stage p 823 A88-54938 SMITH, MARK 0. STEWART, P. A. E. SHAW,J A. An emissions database for U.S. Naw and Air Force Positron emission tomography: A new technique for Component adaptive grid generation for aircraft Aircraft engines observing fluid behavior in engineering systems configurations p 859 N88 29316 [ASME PAPER 88-GT-1291 p 818 A88-54239 [PNR90471] p 854 N88-30091 SHCHETININ, GENNADll MlKHAlLOVlCH SMITH, ROBERT E. STIMLER, D. M. Mechanization of joint production during the assembly Grid generation on and about a cranked-wing fighter Scheduling turbofan engine control set points by of aircraft structures p 846 A88-53998 aircraft configuration p 859 N88-29318 semi-infiniteoptimization p 823 A88-54658 SHEFFLER, KEITH D. SMITH, RONALD C. STRATFORD, B. Current status and future trends in turbine application Test results at transonic speeds on a contoured The use of fins to reduce the pressure drop in a rotating of thermal barrier coatings over-the-wing propfan model cavity with a radial inflow [ASME PAPER 88-GT 2861 p 851 A88 54355 [ NASA-TM-882061 p 811 N88-28918 [ASME PAPER 88-GT-581 p 788 A88-54190 SHEN, J. W. SNELL. ROBERT J. STREATFEILD, D. K. Numerical solution of the hypersonic viscous shock layer Prediction of the pressure distribution for radial inflow Development and installation of an instrumentation equations with chemical nonequilibrium between co-rotating discs package for GE F404 investigative testing [ IAF PAPER ST 88 081 p 796 A88-55313 [ASME PAPER 88-GT-61I p 847 A88-54193 [ AD-AI 962651 p 855 N88-30107

8-12 PERSONAL AUTHOR INDEX WARSI, 2. U.

STURGELL, M. E. THOMPSON, DANIEL B. VEMURU, C. S. Processing pseudosynthetic aperture radar images from A multiprocessor avionics system for an unmanned Suction laminarization of highly swept supersonic visual terrain data research vehicle laminar flow wntrol wings [AIAA PAPER 88-45761 p 802 A88-53628 [AD-A194806] p 81 5 N88-29800 [AIAA PAPER 88-44711 p 786 A8863762 SUBROTO, P. H. THOMPSON, JOE F. VENO, L. B. Transition modeling effects on viscous/inviscid Compositegrid generationfor aircraft configurationswith Development of the F404/RM12 for the JAS 39 interaction analysis of low Reynolds number airfoil flows the EAGLE code p 859 N88-29321 Gripen involving laminar separation bubbles THOMPSON, JOSEPH F. [ASME PAPER 88-GT-3051 p 822 A8844374 [ASME PAPER 88-GT-321 p 787 A88-54175 Three dimensional grid generation for complex VETROV, A. N. SUHS, N. E. configurations Recent progress Effect of loading asymmetry on the low-cycle fatigue Experience with three dimensional composite grids [AGARD-AG-3091 p 858 N88-29313 of ZhS8F alloy under cyclic temperature changes p 860 N88-29324 TILSON, JOSEPH F. p 838 A88-53955 SUN, ZHlOlN A profile of Air Force aircraft mishap investigation VIJAYARAGHAVAN, S. B. Optimization design of the over-all dimensions of US p 801 A88-55288 Investigationof boundary layer transition and separation centrifugal compressor stage in an axial turbine cascade using glue-on hot-film gages TODD, H. [ASME PAPER 88-GT-1341 p 849 A88-54241 [ASME PAPER 88-GT-151I p 791 A88-54251 A methanoVoxygen burning combustor for an aircraft SURESH, J. K. Effect of free-stream turbulence, Reynolds number, and auxiliary emergency power unit Dynamics of helicopter rotors p 809 A88-54954 incidence on axial turbine cascade performance [ASME PAPER 88 GT-2361 p 820 A8864317 SUTTON, JOHN G. [ASME PAPER 88-GT-1521 p 791 A88-54252 Advanced Composite Airframe Program (ACAP) - An TONON, ALW VOERSMANN, P. update and final assessment of weight saving potential Control surface selection based on advanced modes Flight test equipment for the on-board measurement of performance [SAWE PAPER 17701 p 808 A88-53781 wind turbulence p 814 N88-29719 [AIAA PAPER 88-43561 p 829 A88-55275 SWEET, E. JACK VOGEL, H. Laser - A gas turbine combustor manufacturing tool TOPP, DAVID A. Thermomechanical advances for small gas turbine [ASME PAPER 88-GT-2671 p 851 A88-54342 Control of rotor aerodynamically forced vibrations by engines - Present capabilities and future direction in gas splitters p 815 A8842684 SWIFT, T. generator designs Damage tolerance in pressurized fuselages TORIZ, F. C. [ASME PAPER 88-GT-2131 p 850 A88-54299 p 803 A88-52652 Thermal barrier coatings for let engnes VONBRIESEN, MARY [ASME PAPER 88-GT-2791 p 840 A88-54351 SWOLINSKY, M. China's acquisition and use of foreign aviation Flight test equipment for the on-board measurement of TOWNSEND, DENNIS P. technology wind turbulence p 814 N88-29719 Helicopter transmission research at NASA Lewis [AD-A194827] p 862 N88-30471 Research Center SWOLINSKY, MANFRED VONLAVANTE, E. [NASA-TM 1009621 p 855 N88-30128 Contributionsto the modeling of wind shear for danger Investigation of helicopter rotor bladelwake interactive studies TRAN, P. M. impulsive noise [NASA-TT-202931 p 802 N88-28900 Pilotlvehicle analysis of a twin-lift helicopter [ NASA-CR-1774351 p 797 N88-28882 configuration in hover p 829 A88-55064 SZEMA, L. C. Flow in liner holes for counter-current combustion TRET'IACHENKO, G. N. systems Deformation and damage of the material of gas turbine W [ASME PAPER 88-GT-1581 p 839 A88-54257 engine blades during thermal cycling in gas flow p 845 A8843954 WAGNER, BRUNO SZODRUCH, J. The oil-free shaft line Delta wing configurations p 796 "3-28860 TRIPP, L. R. Threat expert system technology advisor [ASME PAPER 88-GT-1681 p 849 A88-54263 [NASA-CR-1774791 p 831 N88-29816 WALKER, G. J. T TSENG, J. 8. Transition modeling effects on viscous/inviscid Calculation of aerodynamic characteristics of airplane interaction analysis of low Reynolds number airfoil flows involving laminar separation bubbles TABAKOFF, W. configurations at high angles of attack [ASME PAPER 88-GT-321 p 787 A88-54175 Causes for turbomachinery performance deterioration [NASA-CR 41821 p 797 N88-28891 WALSH, J. A. [ASME PAPER 88-GT-2941 p 821 A88-54363 TSUKANO, YUKlCHl Turbulence measurements and secondary flows in a Turbomachinery alloys affected by solid particles VSRA in-flight simulator - Its evaluation and turbine rotor cascade [ASME PAPER 88-GT-2951 p 840 A88-54364 applications [AIAA PAPER 88-46051 p 806 A88 53649 [ASME PAPER 88-GT-2441 p 794 A88-54323 TAKAHAMA, MASAYUKI WANG, BO PING Behaviour of the leg of the horseshoe vortex around TURI, J. Approximation schemes for an aeroelastic control Design optimizationof gas turbine blades with geometry the idealized blade with zero attack angle by triple hot-wire and natural frequency constraints measurements system p 829 A88-54660 [ASME PAPER 88-GT-1051 p 81 8 A88-54224 [ASME PAPER 88-GT-1971 p 792 A8844285 TURNBERG, J. WANG, HONGGUANG TAKAI, MASAMI SR-7A aeroelastic model design report A new variational finite element computation for A quasi-procedural.knowledge-based system for aircraft [NASA-CR-174791] p 824 N88-28928 aerodynamic inverse problem in turbines with long design TWEEDT, T. L Experimental investigation of the performance of a blades [AlAA PAPER 88-44281 p 806 A88-53753 [ASME PAPER 88-GT-2751 p 794 A8844347 TALMADGE, RICHARD supersonic compressor cascade WANG, 0. Instrumentationand techniques for structural dynamics [ASME PAPER 88-GT-306) p 795 A88-54375 Periodic neighboring optimum regulator applied to a and acoustics measurements hypersonic scramlet cruiser p 827 A88-54528 [ AlAA PAPER 88-4667 1 p 845 A88-53829 WANG, QINGHUAN TANG, YAN-PING U The use of Bezier polynomial patches to define the An experimental investigationof a vortex flow cascade geometrical shape of the flow channels of compressors [ASME PAPER 88-GT-2651 p 794 A88-54341 UBALDI, MARINA A comparison between measurements and turbulence [ASME PAPER 88-GTBO] p 788 A88-54192 TAPE, ROBERT F. models in a turbine cascade passage Optimization design of the over-all dimensions of Direct lift engine for advanced V/STOL transport [ASME PAPER 88-GT-2261 p 793 A88-54309 centrifugal compressor stage [AIAA PAPER 88-2890A1 D 816 A88-53111 UNRUH. JAMES F. [ASME PAPER 88-GT-1341 p 849 A88-54241 TAYLOR, J. . A study of the effect of random input motion on low A unified solution method for the flow calculations along An interim comparison of operational CG records in Reynolds number flows SI and 52 stream surfaces used for the computer-aided turbulence on small and large civil aircraft [AD-A195559] p 798 N88-29747 design of centrifugal compressors p 830 N88-29729 [ASME PAPER 88-GT-2371 p 793 A88-54318 TAYLOR, WILSON R. WANG, T. A turbine wheel design story v Optimization and guidance of penetration landing [ASME PAPER 88-GT-3161 p 822 A88-54383 trajectories in a windshear p 828 A88-54570 TEIPEL. INGOLF VAN BLARICUM. T. J. WANG, ZHONGQI Theoretical investigation of the interaction between a Damage tolerance of impact damaged carbon fibre An experimental investigation into the reasons of compressor and the components during surge composite wing skin laminates p 804 A88-52670 reducing secondary flow losses by using leaned blades [ASME PAPER 88-GT-2201 p 851 A88-54305 VAN VEGGEL, L. H. in rectangular turbine cascades with incidence angle THAKKER, A. B. Damage tolerance aspects of an expenmentalArall F-27 [ASME PAPER 88-GT-41 p 786 A88-54151 Thermal barrier coatings for jet engines lower wing skin panel p 804 A88-52668 An experimentalinvestigation into the influence of blade [ASME PAPER 88-GT-2791 p 840 A88-54351 Impact and damage tolerance properties of CFRP leaning on the losses downstream of annular cascades THOMAS, JAMES L. sandwich panels - An experimental parameter study for with a small diameter-height ratio Multigrid acceleration of the flux-split Euler equations the Fokker 100 CA-EP flap p 804 A88-52671 [ASME PAPER 88-GT-191 p 786 A88-54165 p 796 A88-55077 VANBRUNDT, H. E. WARD, RICHARD D. THOMAS, MITCHEL E. Effect of phase errors in stepped-frequency radar Assessment of a Soviet hypersonic transport The 1983 direct strike lightning data. part 1 systems [AIAA PAPER 88.45061 p 808 A88-53770 [ NASA-TM-86426-PT-I ] p 856 N88-29259 [AD-A194476] p 853 N88-29081 WARSI, 2. U. The 1983 direct strike lightning data. part 2 VANWMMELEN, L. Generation of surface grids through elliptic partial [ NASA-TM-86426-PT-21 p 856 N88-29260 Unsteady flow past an NACA 0012 airfoil at high angles differential equations for aircraft and missile The 1983 direct strike lightning data, part 3 of attack configurations [ NASA-TM-86426-PT-31 p 856 N88-29261 [AD-A194650] p 797 N88-28886 [AD-A195639] p 860 N88-30378

8-13 WATSON, N. PERSONAL AUTHOR INDEX

WATSON, N. WILSON, DENNIS YARAS, m. Flow in single and twin entry radial turbine volutes A new singular integral approach for a vertical array of Flow field in the tip gap of a planar cascade of turbine [ASME PAPER 88-GT-591 p 847 A88-54191 airfoils blades WEATHERILL, A. E. [ASME PAPER 88-GT-2181 p 793 A88-54303 [ASME PAPER 88-GT-291 p 787 A88-54173 Surface engineering for high temperature WILSON, K. J. YI, FENMING environments p 845 A88-53840 Near-field pressure radiation and flow characteristics in A new variational finite element computation for WEATHERILL, N. P. low supersonic circular and elliptic jets aerodynamic inverse problem in turbines with long Component adaptive grid generation for aircraft p 795 A88-54869 blades configurations p 859 N88-29316 WILSON, N .J. [ASME PAPER 88-GT-2751 p 794 A88-54347 WEBB, STEPHEN G. Developing the Rolls-Royce Tay YOSHIHARA, H. Time periodic control of a multi-blade helicopter [PNR90447] p 825 N88-29809 Three dimensional grid generation for complex [ AD-A1944351 p 829 N88-28931 WILSON, N. J. configurations: Recent progress [AGARD-AG-309I p 858 N88-29313 WEDEMEYER, E. Developing the Rolls-Royce Tay Lessons learned in the mesh generation for PN/S Supersonic wall adaptation in the rubber tube test [ASME PAPER 88-GT-3021 p 821 A88-54371 calculations p 859 N88-29314 section of the DFVLR Goettingen WINSTON, MAlTHEW M. YU. HAOYU [16-222-87-A-081 p 836 N88-29824 Some key considerations for high-speed civil A unified solution method for the flow calculations along transports WEDLAKE, E. T. SI and S2 stream surfaces used for the computer-aided [AIM PAPER 88-44661 p 783 A88-53760 Aerodynamic and heat transfer measurements on a design of centnfugal compressors transonic nozzle guide vane WIlTIG, S. [ASME PAPER 88-GT-2371 p 793 A88-54318 [ASME PAPER 88-GT 101 p 786 A88-54157 Evaporation of fuel droplets in turbulent combustor YU, w. WEINBERG. BERNARD C. flow Modeling of micromechanisms of fatigue and fracture An efficient patched gnd Navier-Stokes solution for [ASME PAPER 88-GT-1071 p 839 A88-54226 in hybnd materials multiple bodies. phase 1 Turbulence effects on the droplet distnbution behind [AD-A1956041 p 855 N88-30142 [ AD-A1941 661 p 853 N88-29110 airblast atomizers p 842 N88-29915 YU, XIAOSHEN WEINGOLD, H. D. WOLTKAMP, JOHN A preliminary investigation of drag reduction and Prediction of compressor cascade performance using Determinationof helicopter simulator time delay and its mechanism for a blunt body of revolution with slanted a Navier-Stokestechnique effects on air vehicle development base [ASME PAPER 88-GT-961 p 789 A88-54217 [AlAA PAPER 88-46201 p 833 A88-53659 [ NASA-TT-203491 p 799 "3-29753 WEISSMAN. P. S. WOOD, C. P. YUE. ANDREW High speed transpacific passenger flight A detailed characterization of the velocity and thermal H(infinity)-optimaldesign for helicopter control [ AlAA PAPER 88-44841 p 807 A88-53764 fields in a model can combustor with wall jet injection p 828 A88-54598 WESTFALL, LEONARD J. [ASME PAPER 88-GT-26) p 818 A88-54170 Composite monolayer fabrication by an arc-spray The performance of a surrogate blend in simulating the process p 845 A88-53581 sooting behavior of a practical, distillate JP-4 z [ASME PAPER 88-GT-1941 p 840 A88-54283 WHELESS. KEITH ZANGENEH-KAZEMI, M. A turbine wheel design story The performanceof a surrogateblend in simulatingJP-4 Three dimensional flow in radial-inflow turbines [ASME PAPER 88-GT-3161 p 822 A88-54383 in a spray-fueled combustor p 843 N88-29926 [ASME PAPER 88-GT-1031 p 790 A88-54222 WHITE, JEFFERY A. WOOD, J. H. ZEIS. JOSEPH E., JR A full Navier-Stokes analysis of a three dimensional Weight growth in airline service Angle of attack and sideslip estimation using an inertial hypersonic mixed compression inlet [SAWE PAPER 17961 p 809 A88-53797 reference platform [AlAA PAPER 88-30771 p 785 A88-53138 WOOD, JERRY L [ AD-AI 948761 p 799 N88-29769 WHITEHEAD, R. S. CIC composite materials for aircraft brakes ZHAO, Y. 0. Certification of primary composite aircraft structures p 837 A8863542 Numerical solution to transonic potential equations on D 805 A88-52672 WOODCOCK, ROBERT J. S2 stream surface in a turbomachine WHITEHURST, R. E., 111 A second look a1 MIL prime flying qualities [ASME PAPER 88-GT-821 p 789 A88-54210 Unique, cI ea n - ai r , continuous-flow. requirements p 812 N88-29740 ZHAO. ZHENYAN high-stagnation-temperalure facility for supersonic WORLAND, CHRISTOPHER J. A digital simulationtechnique forthe Drydenatmospheric combustion research Acquisition of unsteady pressure measurements from model [AIAA PAPER 88-3059Al p 832 A88-53135 a high speed multi-stage compressor [ NASA-TT-203421 p 857 N88-30266 WHITFIELD, DAVID L [ASME PAPER 88-GT-1891 p 833 A88-54280 ZHU, YINGKANG Multigrid acceleration of the flux-split Euler equations WYNDHAM, 8. A. Flow field in the tip gap of a planar cascade of turbine D 796 A88-55077 Fine resolution errors in secondary surveillance radar blades WHITLOW, WOODROW, JR. altitude reporting [ASME PAPER 88-GT-291 p 787 A88-54173 ZIEGLER, BERND Application of unsteady aerodynamic methods for [ RSRE-870191 p 802 N88-28906 Investigations on the modification of structural reliability transonic aeroelastic analysis WYNNE, ELEANOR C. by substitution of aluminum by carbon fiber reinforced [ NASA-TM-1006651 p 799 N88-29754 Steady and unsteady transonic pressure measurements plastics in aircraft construction WIERZBA, I. on a clipped delta wing for pitching and control-surface [ILR-MITT-195] p 841 N88-29877 The blowout of turbulent let flames in co-flowinq streams oscillations ZUNINO, PIETRO of fuel-air mixtures [ NASA-TP-25941 p 798 N88-28895 A comparison between measurements and turbulence [ASME PAPER 88-GT-1061 p 838 A88-54225 models in a turbine cascade passage WIESE, MICHAEL R. [ASME PAPER 88-GT-2261 p 793 A88-54309 Grid generation on and about a cranked-wing fighter X ZWAANENBURG, KOOS aircraft configuration p 859 N88-29318 Real-time simulation of helicopters using the blade WIGELL, GARY A. XIA, XUEJIAN element method Potential application of composite malerials to future A preliminary investigation of drag reduction and [AlAA PAPER 88-45821 p 805 A8863634 gas turbine engines p 823 A88-54624 mechanism for a blunt body of revolution with slanted WIGLEY, DAVID A. base Technoloav for Dressure-instrumented thin airfoil [ NASA-TT-203491 p 799 N88-29753 "I models XIAO, YELUN [ NASA-CR-41731 p 835 N88-28933 Adigital simulation techniquefor the Dryden atmospheric WILEY, J. D. model The characterizationof high temperalure electronics for [ NASA-TT-203421 p 857 "3-30266 future aircraft engine digital electronic control systems XU, J. 2. p 823 A88-54621 Numerical solution lo transonic potential equations on WILLIAMS, B. R. S2 stream surface in a turbomachine Developments in computational methods for high-lift [ASME PAPER 88-GT-82] p 789 A88-54210 aerodynamics p 786 A88-53250 XU, WENYUAN WILLIAMS, J. M. An experimental investigation into the reasons of A new method of modeling underexpanded exhaust reducing secondary flow losses by using leaned blades plumes for wind tunnel aerodynamic testing in rectangular tuhne cascades with incidence angle [ASME PAPER 88-GT-2881 p 834 A8844357 [ASME PAPER 88-GT-41 p 786 A88-54151 WILLIAMS, MARC H. An experimentalinvestigation into the influence of blade Aeroelastic response of metallic and composite propfan leaning on the losses downstream of annular cascades models in yawed flow with a small diameter-heightratio [ NASA-TM-100964) p 825 N88-29807 [ASME PAPER 88-GT-I91 p 786 A88-54165 WILLIS, G. D. A fast interactive two-dimensional blade-to-bladeprofile design method Y [ASME PAPER 88-GT-1001 p 790 A88-54220 WILMS. V. YAMAMOTO, A. Expenmental and theoretical aspects of thick thermal Effects of incidence on three-dimensional flows in a barrier coatings for turbine applications linear turbine cascade p 837 A88-53566 [ASME PAPER 88-GT-I101 p 790 A88-54228 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 234) January 1989

AeroVironment, Inc., Monrovia, Calif. Army Aviation Systems Command, St. Louis, Mo. Typical Corporate Source Development and design of windtunnel and test facility Test of an 0 8-scale model of the AH-64 Apache in the Index Listing for RPV (Remote Piloted Vehicle) enhancement devices NASA Langley full-scale wind tunnel ( AD-A1948421 p 836 N88-29822 [AD-A196129] p 799 N88-29768 Air Force Inst. of Tech., Wright-Patterson AFB, Ohio. Army Natick Research and Development Command, Time periodic control of a multi-blade helicopter Mass. [AD-AI944351 p 829 N88-28931 Control systems for platform landings cushioned by air Angle of attack and sideslip estimation using an inertial bags CORPORATE SOURCE reference platform [ AD-AI 961541 p 854 N88-29996 [AD-A194878] p 799 N88-29769 Army Research and Technology Labs., Moffett Field, An analysis of lateral-directional handling qualities and Calif. Eigenstructureof high performance aircratt Minimum-complexityhelicopter simulation math model [AD-A1948741 p 831 N88-29814 [ NASA-CR-1774761 p 831 N88-29819 FedoralI Avlallon Admlnlstrallon. Atianllc Clly. N J Controlled degradationof resolution of high-qualityflight Army War Coll., Carlisle Barracks, Pa. Full scale iranspon controlled muaci demonsirai8on simulator images for training effectiveness evaluation China's acauisition and use of foreian aviation [AD-A196189] p 836 N88-29823 technology An investigation of constitutive models for predicting D 19 N88 10021 [AD-A1948271 p862 N88-30471 viscoplastic response during cyclic loading I [AD-A194875] p 856 N88-30163 Air Force Weapons Lab., Klrtlsnd AFB, N. Mex. EMPTAC (Electromagnetic Pulse Test Aircraft) user's B guide [ AD-A195072 1 p 854 N88-30006 Boeing Commercial Alrplane Co., Seattle, Wash. Air Force Wright Aeronautical Labs., Wright-Patterson Variable Sweep Transition Flight Experiment AFB, Ohlo. (VSTFE)-parametric pressure distribution boundary layer A second look at MIL prime flying qualities stability study and wing glove design task requirements p 81 2 N88-29740 [ NASA-CR-399.21 p 798 N88-28894 A multiprocessor avionics system for an unmanned Boeing Military Airplane Development, Seattle, Wash. research vehicle Lessons learned in the mesh generation for PN/S Listings in this index are arranged alphabetically [ AD-A1948061 p 815 N88-29800 calculations p 859 N88-29314 by corporate source The title of the document is Fatigue crack growth characteristics of ARALL Boeing Military Airplane Development, Wlchlta, Kans. used to provide a brief description of the subject (trademark)-I Multiple-Purpose Subsonic Naval Aircraft (MPSNA) [AD-AI 961851 p 841 "3-29889 Multiple Application Propfan Study (MAPS) matter The page number and the accession Aircraft Research Assoclatlon Ltd., Bedford (England). [ NASA-CR-1751041 p 81 I N88-28917 number are included in each entry to assist the Transport-type configurations p 809 N88-28867 British Aerospace Aircraft Group, Weybridge user in locating the abstract in the abstract sec- Combat aircraft p 81 0 N88-28868 (England). Re-assessmentof gust statistics using CAADRP data tion If applicable. a report number is also included Component adaptive grid generation for aircraft configurations p 859 N88-29316 p 831 N88-29732 as an aid in identifying the document Analytlcai Services and Materials, Inc., Hampton, Va. British Aerospace Public Ltd. Co., Preston (England). Suction laminarization of highly swept supersonic The role of simulationin flying qualities and flight control laminar flow control wings system related development p 835 N88-29742 A' [AIAA PAPER 88-4471 ] p 786 A88-53762 British Aerospace Public Ltd. Co., Weybrldge Anamet Labs., Inc., Hayward, Calif. (England). Advisory Group for Aerospace Research and Interactive plotting of NASTRAN aerodynamic models Complex configurations p 834 N88-28861 Development, Neullly-Sur-Seine (France). using NPLOT and DISSPLA Boundary layer simulation and control in wind tunnels [AD-A194115] p 853 N88-29204 C [AGARD-AR-224] p 784 N88-28857 Computer programs for generation of NASTRAN and Aerodynamic data accuracy and quality: Requirements VIBRA-6 aircraft models California Univ., Berkeley. and capabilities in wind tunnel testing [ AD-A1954671 p 81 2 N88-29792 Modeling of micromechanisms of fatigue and fracture [AGARD-AR-254] p 798 N88-28893 Applied Cryogenics and Materials Consultants, Inc., in hybrid materials AGARD engine disc cooperative test programme Hampton, Va. IAD-Al956041 p 855 N88-30142 [AGARD-R-766] p 824 N88-28926 Technology for pressure-instrumented thin airfoil California Univ., Irvlne. Three dimensional grid generation for complex models The performance of a surrogateblend in simulatingJP-4 configurations: Recent progress [ NASA-CR-41731 p 835 N88-28933 in a spray-fueled combustor p 843 N88-29926 [AGARD-AG-3091 p 858 NEB-29313 Aptech Engineering Services, Inc., Sunnyvale, Calif. Calspan Field Services, Inc., Arnold AFS. Tenn. The Flight of Flexible Aircraft in Turbulence: Stress intensity factors for cracked metallic structures Experience with three dimensional composite grids State-of-the-Art in the Description and Modelling of under rapid thermal loading p 860 N88-29324 Atmospheric Turbulence [ AD-AI 91 21 91 p 840 N88-29004 Clty Coll. of the City Unlv. of New Vork. [ AGARD-R-734-ADDl p 784 N88-29717 Stress intensity factors for cracked metallic structures Eigenstructure assignment for the control of highly The Flight of Flexible Aircraft in Turbulence: under rapid thermal loading augmented aircraft p 828 A8844549 State-of-the-Art in the Description and Modelling of [AES-8609709F-l I p 843 N88-29962 Clvii Aviation Authority, London (England). Smoke hoods: Net safety benefit analysis Atmospheric Turbulence Arizona State Univ., Tempe. (CAA-PAPER-870171 p 801 N88-28898 [AGARD-R-7341 p 785 N88-29725 Avionic expert systems p 814 N88-29365 Advances in Flying Qualities UK airmisses involving commercial air transport Army Avlation Engineering Flight Activity, Edwards [CAA-1/88] p 803 N88-28907 [AGARD-LS-157] p 785 N88-29735 AFB, Calif. Civil Aviation Authority, Redhlll (England). Combustion and fuels in gas turbine engines JUH-1H redesignedpneumatic boot deicingsystem flight [AGARD-CP-422] p 841 N88-29910 A review of measured gust responses in the light of test evaluation modern analysis methods p 830 N88-29724 Aeronautical Research Inst. of Sweden, Stockholm. [ AD-A1949181 p 802 N88-29785 CK Consultants, Inc., Mariposa, Calif. Analysis of the transmissionof sound into the passenger Army Aviation Research and Development Command, Avionics system design for high energy fields: A guide compartmentof a propeller aircraft using the finite element Cleveland, Ohio. for the designer and airworthiness specialist method Assessment, development, and application of [NASA-CR-181590] p 81 4 N88-28919 [ FFA-TN-1988-151 p 861 N88-29520 combustor aerothermal models p 817 A88-54140 Conrad Technologies, Inc., King of Prussia, Pa. Standard fatigue specimens for fastener evaluation Army Aviation Research and Development Command, Structural dynamics of maneuvering aircraft [ FFA-TN-I987.681 p 856 N88-30157 Moffett Field, Calif. [ AD-A1923761 p 810 N88-28908 Aeronautical Research Labs., Melbourne (Australia). The effect of perspectivedisplays on altitude and stability Coordinating Research Council, Inc., Atlanta, Ga. Development and installation of an instrumentation control in simulated rotary wing flight Determination of the hydroperoxide potential of jet package for GE F404 investigative testing [AIAA PAPER 88-46341 p 833 A88-53667 fuels [AD-A196265] p 855 N88-30107 Army Aviation Systems Command, Cleveland, Ohio. [ AD-A1959751 p 844 N88-29991 The development of acoustic emission for structural Development of a thermal and structural analysis Cornell Univ., Ithaca, N.V. integrity monitoring of aircraft procedure for cooled radial turbines Numerical results for axial flow compressor instability [ AD-AI962641 p 861 N88-30398 [ASME PAPER 88-GT-181 p 846 A88-54164 [ASME PAPER 88-GT-2521 p 851 A88-54328

c-1 Cranfield Inst. of Tech., Bedford (England). CORPORA TE SOURCE

Cranfield Inst. of Tech., Bedford (England). Essex Corp., Alexandria, Va. Iowa State Univ. of Science and Technology, Ames. Spray performance of a vaporizing fuel inlector Use of color CRTs (Cathode Ray Tubes) in aircraft Design point variation of 3-D loss and deviation for axial p 842 N88-29919 cockpit A literature search, revision B compressor middle stages Crew Systems Consultants, Yellow Springs, Ohio. [ ADA1 950621 p 815 N88-29797 [ASME PAPER 88-GT-571 p 787 A88-54189 Improvement of head-up display standards Volume 2 Eurocontrol Experimental Centre, Bretigny (France). Evaluationof head-up displays lo enhance unusual attitude Observed track-keeping performance of DCIO aircraft recovery eouiooed with the Collins AINS-70 area naviaation svstem K [AD-A194601] p 814 N88-28921 Karlsruhe and Masstncht UACs (Upper irea Cbntrol Improvement of head-up display standards Volume 5 centres) Kansas Univ. Center for Research, Inc., Lawrence. Head up display ILS (Instrument Landing System) accuracy [ EEC-2021 p 803 N88-29788 Calculation of aerodynamic characteristics of airplane configurations at high angles of attack flight tests European Space Agency, Paris (France). [ AD-A1946021 p 814 NE8 28922 [ NASA-CR-41821 p 797 N88-28891 Additional investigations into the aircraft landing Karlsruhe Univ. (West Germany). process Test distributions Turbulence effects on the droplet distribution behind [ESA-TTT-1099] p 810 "3.28913 D airblast atomizers p 842 N88-29915 History of aeroelasticity in Germany from the beginning Dayton Univ., Ohio. to 1945 An integral equation for the linearized unsteady [ESA-TT-1082] p 799 N88-29767 L supersonic flow over a wing [AD-A193773] p 797 N88-28887 Laval Univ. (Quebec). Fatigue crack growth characteristics of ARALL F The characterizatin of combustion by fuel composition: (tradernarkkl Measurements in a small conventional combustor [ AD-AI 961851 p 841 N88-29889 Federal Aviation Administration, Seattle. Wash. p 842 N88-29920 Delta Air Lines, Inc., Atlanta, Ga. Current and proposedgust criteria and analysis methods Lockheed Aeronautical Systems Co., Burbank, Calif. Optimization and guidance of penetration landing An FAA ovewiew p 830 "3.29718 The application of artificial intelligence technology to trajectories in a windshear p 828 A88-54570 Florida State Univ., Tallahassee. aeronautical system design Deutsche Forschungs- und Versuchsanstalt fuer Luft- Unsteady flow past an NACA 0012 airfoil at high angles [AIAA PAPER 88.44261 p 806 A88-53752 und Raumfahrt, Brunswlck (West Germany). of attack A Summary of methods for establishing airframe design Estimation of aircraft parameters using filter error [ AD-AI 946501 p 797 N88-28886 loads from continuous gust design criteria methods and extended Kalman filter Flow Application Research, Fremont, Calif. p 811 N88-29721 [DFVLR-FB-88 151 p 810 N88 2891 1 Design point variation of 3-D loss and deviation for axial Lockheed-Georgla Co., Marietta. Grid generation around transport aircraft configurations compressor middle stages N-version software demonstration for digital flight using a multi-block structured computational domain [ASME PAPER 88-GT-571 p 787 A88-54189 controls p 860 N88-29325 INASA-CR-1814831 p 831 N88-29815 Deutsche Forschungs- und Versuchsanstalt fuer Luft- Loughborough Univ. of Technology (England). und Raumfahrt, Cologne (West Germany). G An analysis of time and space requirements for aircraft Experimental investigation of the performance of a turnrounds supersonic compressor cascade General Dynamics Corp., Fort Worth, Tex. [ n-87051 p 802 N88-29783 [ASME PAPER 88 GT-3061 p 795 A88-54375 Generation of multiple block grids for arbitrary 3D Influence of operating conditions on the atomizationand geometries p 859 N88-29317 distribution of fuel by air blast atomizers General Electric Co., Cincinnati. Ohio. M E3 1OC compressor test analysis of high-speedpost-stall p 842 N88-29918 Management Consulting and Research, Inc., Falls data Deutsche Forschungs- und Versuchsanstalt fuer Luft- Church, Va. [ NASA-CR-1795211 p 824 "3.28929 und Raumfahrt, Goettingen (West Germany). Aircraft avionics and missile system installation cost Analytical surfaces and grids p 860 N88-29322 Empirical flutter prediction method study. Volume 1: Technical report and appendices A [ AD-AI 956991 p 825 N88-29810 Supersonic wall adaptation in the rubber tube test through E Numerical models for analyticalpredictionsof combustor section of the DFVLR Goettingen [ AD-A1946051 p 814 N88-28923 [ 18-222-87-A-081 p 836 N88-29824 aerothermal performance characteristics Manudyne Systems, Inc., Los Altos, Calif. p 843 N88-29935 Deutsche Forschungs- und Versuchsanstalt fuer Luft- Minimum-complexityhelicopter simulation math model General Motors Corp., Indianapolis, Ind. und Raumfahrt. Stuttgart (West Germany). [ NASA-CR-1774761 p 831 N88-29819 Assessment development, and application of Crash simulation calculations and component Massachusetts Inst. of Tech., Lexington. combustor aerothermal models p 817 A88-54140 idealization for an airframe Computer code KRASH 79 Airport surface traffic automation study [ ETN-88-92971 p 801 NE8 28899 George Washington Univ., Hampton, Va. I [AD-A194553] p 835 N88-28934 Two biased estimation techniques in linear regression Dornier-Werke G.m.b.H., Friedrichshafen (West Max-Planck-lnstitut fuer Stroemungsforschung, Application lo aircraft Germany). Goettingen (West Germany). [ NASA-TM-I006491 p 860 N88-29489 Mesh generation for industrial application of Euler and Noise generation and boundary layer effects in Georgia Inst. Tech., Atlanta. Navier Stokes solvers p 860 N88-29323 of vortex-airfoil interaction and methods of digital hologram The application of artificial intelligence technology to Dornier-Werke G.m.b.H., Oberpfaffenhofen (West analysis for these flow fields Germany). aeronautical system design [AD-A194191] p 797 N88-28883 [AIM PAPER 88.44261 p 806 A88-53752 Development of a glass fiber wing following the Messerschmltt-Boelkow-Blohm G.m.b.H., Bremen construction regulation FAR Part 23 Development of a micro-computer based integrated (West Germany). [ETN-88-929661 p 840 NE8 28979 design system for high altitude long endurance aircraft Delta wing configurations p 796 N88-28860 [ AIAA PAPER 88-44291 p 807 A8843754 Douglas Alrcraft Co.. Inc.. Long Beach, Calif. Variable wing camber control systems for the future Critical joints in large composite primary aircraft Trajectory optimization and guidance law development Airbus program for national aerospace plane applications structures Volume 2 Technology demonstration test [ MBB-UT-104/88] p N88-28932 p 837 A88-54567 830 report Messerschmltt-Boelkow-BlohmG.m.b.H., Hamburg [ NASA-CR-1725871 pall N8828915 Helicopter trajectory planning using optimal control (West Germany). theory p 828 A88 54571 Critical joints in large composite primary aircraft Comparison of the influence of different gust models Grumman Aerospace Corp., Bethpage, N.Y. structures Volume 3 Ancillary test results on structural design p 81 1 N88-29722 [ NASA-CR 172588 I p 811 N88-28916 Automated early fatigue damage sensing system Messerschmitt-Boelkow G.m.b.H., Munlch (West Critical joints in large composite primary aircraft [AD-A195717] p 855 N88-30143 Germany). structures Volume 1 Technical summary [NASA-CR-3914] p 840 N88-28983 Grid generation for an advanced fighter aircraft p 859 N88-29319 Draper (Charles Stark) Lab., Inc., Cambridge, Mass. H intelligent fault diagnosis and failure management of Minnesota Unlv., Minneapolis. flight control actuation systems Hamilton Standard, Windsor Locks, Conn. Studies of gas turbine heat transfer airfoil surface and [NASA CR-I774811 p 812 NE8 29790 Experimental and analytical evaluation of the effects of end-wall cooling effects Developmentand demonstrationof an on-board mission simulated engine inlets on the blade vibratory stresses [AD-A195165] p 825 N88-29805 planner for helicopters of the SR-3 model prop-fan Mississippi State Univ., Mississippi State. (NASA-CR-1774821 p 831 N88 29817 [NASA-CR-1749591 p 824 N88-28927 Multigrid acceleration of the flux-split Euler equations SR-7A aeroelastic model design report Duke Univ., Durham, N. C. D 796 A88-55077 [NASA-CR-1747911 p 824 N88-28928 Asymptotic modal analysis and statistical energy Compositegrid generationfor aircraft configurationswith analysis the EAGLE code p 859 N88-29321 [NASA-CR-1830771 p 861 N88-29514 I Generation of surface grids through elliptic partial differential equations for aircraft and missile Indian Inst. of Tech., Madras. configurations E Effect of stage loading on endwall flows in an axial flow [ AD-A1956391 p 860 N88-30378 compressor rotor Ecole Nationale Superieure de I'Aeronautique et de [ASME PAPER 88-GT-Ill] p 848 A88-54229 I'Espace. Toulouse (France). lndustrlal Quality. Inc., Galthersburg, Md. N Studies of unsteady axial-compressorfunctioning Development of graded reference radiographs for p 855 N88-30129 aluminum welds, phase 1 National Aeronautical Establishment, Ottawa (Ontario), Electro Magnetic Applications. Inc., Denver, Colo. [ ADA1955941 p 855 N88-30140 The NAE atmospheric research aircraft Investigations into the triggered lightning response of Instituto Superior Tecnico, Lisbon (Portugal). p 815 N88-29730 the F1068 thunderstorm research aircraft Radiation transfer in gas turbine combustors Aircrattdynamics Aerodynamic aspects and wind tunnel [NASA-CR-39021 p 856 N88-29258 p 843 N88-29929 techniques p 798 N88-29731 c-2 CORPORATE SOURCE Rensselaer Polytechnic Inst., Troy, N.Y.

The use of hot-film technique for boundary layer studies The 1983 direct strike lightning data, part 3 Naval Air Development Center, Warmlnster. Pa. on a 21 percent thick airfoil [ NASA-TM-86426-PT-31 p 856 N88-29261 AGARD (Advisory Group for Aerospace Research and [NAE-AN-451 p 800 N88-29781 Grid generation on and about a cranked-wing fighter Development) engine disc material cooperative test Natlonal Aeronautics and Space Administration, aircraft configuration p 859 N88-29318 (supplementaryprogram) [AD-A1938781 p 824 N88-28925 Washlngton, D.C. Status review of atmosphere turbulence and aircraft Contributionslo the modeling of wind shear for danger response p 830 N88-29726 Naval Ocean Systems Center, San Dlego, Calif. studies A summary of atmospheric turbulence measurements Effect of phase errors in stepped-frequency radar [ NASA-TT-202931 p 802 N88-28900 with specially-equippedaircraft in the US systems A preliminary investigation of drag reduction and p 857 N88-29727 [ AD-A194476 1 p 853 N88-29061 mechanism for a blunt body of revolution with slanted Aerodynamics in ground effect and predicted landing Naval Postgraduate School, Monterey, Callf. base ground roll of a fighter configuration with a Flow visualization on a small scale [NASA-TT-203491 p 799 N88-29753 secondary-nozzlethrust reverser [AD-AI 947281 p 835 N88-28935 A digital simulationtechnique for the Dryden atmospheric [ NASA-TP-28341 p 799 N88-29752 Hot-wire measurements of compressor blade wakes in model Application of unsteady aerodynamic methods for a cascade wind tunnel [NASA-TTT-20342] p 857 N88-30266 transonic aeroelastic analysis [AD-AI 947371 p 835 N88-28936 Natlonal Aeronautlcs and Space Admlnistratlon. Ames [ NASA-TM-1006651 p 799 N88-29754 Flow visualization by laser sheet Research Center, Moffett Fleld, Calif. Pressure distributions from subsonic tests of an [AD-A194481I p 853 N88-29111 Smart command recognizer (SCR) - For development, advanced laminar-flow-control wing with leading- and A mapping of the viscous flow behavior in a controlled test, and implementation of speech commands trailing-edge flaps diffusion compressor cascade using laser Doppler [AIAA PAPER 88-46121 p 858 A88-53654 [ NASA-TM-4040-PT-21 p 800 N88-29776 velocimetry and preliminary evaluation of codes for the The effect of perspectivedisplayson altitude and stability Recent advances in transonic computational prediction of stall control in simulated rotary wing flight aeroelasticity [AD-A1944901 p 853 N88-29112 [AlAA PAPER 88-46341 p 833 A88-53667 [ NASA-TM-1006631 p 800 N88-29778 Feasibilitystudy of a microprocessorcontrolled actuator The application of artificial intelligence technology to Compression pylon test mechanism aeronautical system design [NASA-CASE-LAR-13777-1J p 812 N88-29789 [AD-A194654] p N88 29337 [AIAA PAPER 88-44261 p 806 A8843752 860 Aerodynamics p 783 A88-53800 Computer programs for calculation of sting pitch and Naval Ship Research and Development Center, Considerationsfor automatednap-of-the-earth rotorcraft roll angles required to obtain angles of attack and sideslip Bethesda, Md. flight p 827 A88-54526 on wind tunnel models Analysis of a fixed-pitch X-wing rotor employing lower [ NASA-TM-1006591 p 835 N88-29820 Helicopter trajectory planning using optimal Control surface blowing theory p 828 A88-54571 National Aeronautlcs and Space Admlnistratlon. Lewis [AD-AI873791 p 800 N88-29779 High performance forward swept wing aircraft Research Center, Cleveland, Ohio. Nevada Unlv., Reno. [ NASA-CASE-ARC-11636-1 ] p 810 N88-28914 Control of rotor aerodynamically forced vibrations by Aerodynamics of seeing on large transport aircraft Test results at transonic speeds on a contoured splitters p 815 A88-52684 [NASA-CR-1831221 p 801 N88-28896 over-the-wing propfan model A preliminary design study of supersonic through-flow North Carolina State Univ.. Raleigh. [ NASA-TM-882061 p 811 N88-28918 fan inlets Grid embeddingtechnique using Cartesiangrids for Euler Three-dimensionalelliptic grid generation for an F-16 [AIAA PAPER 8830751 p 816 A88-53137 solutions p 796 A8865094 p 859 N88-29315 Composite monolayer fabrication by an arc-spray Three-dimensionalNavier-Stokes simulations of turbine process p 845 A88-53581 rotor-stator interaction Toward improved durability in advanced aircraft engine 0 [NASA-TM-1000811 p 799 N88-29750 hot sections; Proceedings of the Thirty-third ASME National Aeronautics and Space Admlnlstratlon. Hugh International Gas Turbine and Aeroengine Congress and Odetlcs, Inc., Anaheim, Calif. L. Dryden Flight Research Faclilty, Edward.. Cailf. Exposition. Amsterdam, Netherlands, June 5-9, 1988 Threat expert system technology advisor An airborne system for vortex flow visualization on the p 817 A8844137 [ NASA-CR-1774791 p 831 N88-29816 F-18 high-alpha research vehicle NASA HOST prolect overview p 817 A8844138 Office National dEtudes et de Recherche8 [AIAA PAPER 88-46711 p 81 3 A88-53830 Advanced high temperature instrumentation for hot Aeronautlques. Parls (France). Techniques used in the F-14 variable-sweep transition section research applications p 846 A88-54139 Measured and predicted responses of the Nord 260 flight experiment Assessment, development, and app~lcatlon of aircraft to the low altitude atmospheric turbulence [NASA TM-1004441 p 855 N88 30093 p N88-29723 combustor aerothermal models p 817 A88-54140 830 National Aeronautics and Space Admlnlstratlon. Office Nationald'Etudes et de Lyndon E. Johnson Space Center, Houston, Tex. Review and assessment of the database and numerical NASA Shuttle Training Aircraft flight simulation modeling for turbine heat transfer p 817 A88 54141 Aerospatiaies* (France)' Extreme gusts distribution p 857 N88-29734 overview Life modeling of thermal barrier coatings for aircraft gas [AIAA PAPER 88-46081 p 806 A88-53650 turbine engines p 838 A88-54145 Natlonal Aeronautlcs and Space Admlnistration. Views on the impact of HOST p 818 A88-54146 P Langley Research Center, Hampton, Va. Development of a thermal and structural analysis CFD prediction of the reactingflow field inside a subscale procedure for cooled radial turbines Plannlng Research Corp., Hampton, Va. scramlet combustor [ASME PAPER 88-GT-181 846 A88-54164 Aircraft noise prediction program propeller analysis [AIAA PAPER 88-32591 p 816 A88-53151 Designpoint variation of 3-D loss and deviation for axial The Langley Advanced Real-Time Simulation (ARTS) compressor stages System IBM-PC version user's manual version 2 o [NASA-CR-181689] p 862 N88-30399 system [ASME PAPER 88-GT-571 p 787 A88-54169 [AIAA PAPER 88-45951 p 832 A88-53642 Pratt and Whitney Alrcraft. East Hartford, COnn. Simulator evaluation of takeoff performance monitoring Active control of transient rotordynamic vibration by Current status and future trends in turbine application system displays optimal control methods of thermal barrier coatings [AIAA PAPER 88-4611 I 833 A88-53653 [ASME PAPER 88-GT-731 p 858 A88-54202 [ASME PAPER 88-GT-2881 p 851 A88-54355 Some key considerations for high-speed civil Fluner of a fan blade in supersonic axial flow Pratt and Whltney Aircraft, Weat Palm Beach, Fla. tm"S"0ri~ [ASME PAPER 88-GT-781 p 788 A88-54206 Fuel DroDerW eflects on the US Naw's TF30 enqine .I [AIAA PAPER 88.44661 p 783 A88-53760 Expenmental investigation of the performance of a p 826 N88-29911 Technology sensitivity studies for a Mach 3.0 civil supersonic compressor cascade PRC Systems Services Co.. Edwards, Callf. transport [ASME PAPER 88-GT-3061 p 795 A88-54375 An airborne system for vortex flow visualization on the [AIAA PAPER 88-4469) p 783 A8843761 Optical measurement of unducted fan blade F-18 high-alpha research vehicle The application of cryogenics to high Reynolds number deflections [AIAA PAPER 88-46711 p 813 A88-53830 testing in wind tunnels. II - Development and application [ NASA-TM-1009661 p 853 N88-29142 Psycho-Llnguistlc Research Associates, Menlo Park, of the cryogenic wind tunnel concept Euler analysis of a swirl recovery vane design for use Callf. p 833 A88-53847 with an advanced single-rotation propfan Smart command recognizer (SCR) - For development, Application of AI methods to aircraft guidance and [ NASA-TM-I013571 p 800 N88-29771 test, and implementation of speech commands control p 827 A8844424 Aeroelastic response of metallic and composite propfan [AIAA PAPER 88-46121 p 858 A8843654 Eigenstructure assignment for the control of highly models in yawed flow Purdue Unlv., West Lafayette, Ind. augmented aircraft p 828 A8844549 [ NASA-TM-1009641 p 825 N88-29807 Control of rotor aerodynamically forced vibrations by Multigrid acceleration of the flux-split Euler equations Helicopter transmission research at NASA Lewis splitters p 815 A88-52684 p 796 A8845077 Research Center Aerodynamically forced response of an airfoil including Gridembeddingtechnique using Cartesiangrids for Euler NASA-TM-I 009621 p 855 N88-30128 profile and incidence effects p 795 A88-54941 solutions p 796 A88-55094 Natlonal Aerospace Lab., Amsterdam (Netherlands). Atomization of alternative fuels p 842 N88-29913 High-aspect-ratiowings p 834 N88-28859 Low-speed longitudinal flying qualities of modern Effects of independent variation of Mach and Reynolds transport aircraft p 812 N88-29738 numbers on the low-speed aerodynamic characteristics R of the NACA 0012 airfoil section Failure analysis for gas turbines [ NASA-TM-4074J p 784 N88-28879 [NLR-MP-87037-Ul p 825 N88-29808 RAND Corp., Santa Monica, Callf. Steady and unsteady transonic pressure measurements Natlonal Physical Lab., Teddlngton (England). Aircraft airframe cost estimating relationships Study on a clipped delta wing for pitching and control-surface Noise levels from a let-engined aircraft measured at approach and conclusions oscillations ground level and at 1 2 m above the ground [ R-3255-AF] p 813 N88-29795 [ NASA-TP-25941 p 798 N88-28695 [NPL-AC-1141 p 861 N88-29524 Renaselaer Polytechnic Inst., Troy, N.Y. The 1983 direct strike lightning data. part 1 National Research Council of Canada, Ottawa Theoretical aerodynamics, transonic flow [NASA-TM-86426-PT-I] p 856 N88-29259 (Ontarlo). [AD-A1962471 p 800 N88-29777 The 1983 direct strike lightning data. part 2 Computationaltools for simulation methodologies Processing technology research in composites [ NASA-TM-86426-PT-21 p 856 N88-29260 D 834 N88-28865 [AD-A1956931 p 841 N88-29890 c-3 ~~~ ~

Research Inst. of National Defence, Stockholm (Sweden). CORPORA TE SOURCE

Research Inst of National Defence, Stockholm Technische Univ., Berlin (West Germany). (Sweden). Investigationson the modificationof structural reliability Review of research concerning Solid Fuel Ramjet by subsbtution of aluminum by carbon fiber reinforced (SOFRAM) at the Research Institute of National Defence plastics in aircraft construction (FOA) 2 [ ILR-MITT-1951 p 841 N88-29877 [FOA-C20714-2 11 p 826 NEB-29813 Technische Unlv., Brunswick (West Germany). Rice Unlv., Houston, Tex. A contnbutionto the quanbtative analysis of the influence Optimization and guidance of penetration landing of design parameters on the optimal design of passenger trajectones in a windshear p 828 A88-54570 aircraft Rolls-Royce Ltd., Bristol (England). [ ETN-88-929791 p 810 N88-28912 High performance turbofan afterburner systems Flight test equipment for the on-board measurement of p 842 N88-29922 wind turbulence p 814 N88-29719 RollkRoyce Ltd., Derby (England). Tennessee Unlv., Tullahoma. V2500 engine collaboration Contaminationand distorttonof steady flow field induced [PNR90423] p 825 N88-29803 by discrete frequency disturbances in aircraft gas Developingthe Roils-RoyceTay engines (PNR904471 p 825 N88-29809 [AD-A195440] p 854 N88-30069 Positron emission tomography A new technique for Tennessee Univ. Space Inst., Tullahoma. ObSeNing fluid behavior in engineenng systems Algebraic grid generation for fighter type aircraft [PNR90471] p 854 NE8 30091 p 859 N88-29320 Royal Aircraft Estsbllshment, Bedford (England). Texas A61 Unlv., Kingsville. Measurement and analysis of low altitude atmospheric A fiber optic collective flight control system for turbulence obtained using a specially InstNmented Gnat helicopters aircraft p 857 N88-29728 [AD-A1954061 p 831 N88-29818 Royal Aircraft Establishment, Farnborough (England). Texas A6M Univ., College Station. Gas turbine smoke measurement A smoke generator Active control of transient rotordynamic vibration by for the assessment of current and future techniques optimal control methods p 843 N88-29930 [ASME PAPER 88-GT-731 p 858 A88 54202 Royal Signals and Radar Establishment, Malvern investigation of helicopter rotor biadelwake interactive (England). impulsive noise Fine resolubon errors in secondary surveillance radar [NASA-CR-177435] p 797 N88 28882 altitude reporting [RSRE-870191 p 802 N88-28906 Rutgen - The State Unlv., New Brunswlck, N. J. U Numencal simulation of nozzle flows [AD-A195144] p 854 N88-30064 United Technologies Corp., East Hartford, Conn. The effects of inlet turbulence and rotorlstator interactions on the aerodynamics and heat transfer of a S large-scalerotating turbine model. Volume 3: Heat transfer data tabulation 65 percent axial spacing Xlentiflc Research Associates, Inc., Glastonbury, [ NASA-CR-I794681 p 824 N88-28930 Conn. The effects of inlet turbulence and rotorlstator An efficient patched grid Navier-Stokes solution for interactions on the aerodynamics and heat transfer of a multiple bodies, phase 1 large-scalerotating turbine model. Volume 2 Heat transfer [AD-A1941€6] p 853 N88-29110 data tabulation. 15 percent axial spacing Southampton Unlv. (England). [NASA-CR-179467] p 825 N88-29804 A companson of simple analytical models for United Technologies Research Center, East Hartford, representing propeller aircraft structural and acoustic Conn. responses The effects of turbulence and statorlrotor interactions [ISVR-TR-1531 p 861 N88-29523 on turbine heat transfer. 11 - Effects of Reynolds number Southwest Research Inst., San Antonio, Tex. and incidence Development of a test method to determine potential [ASME PAPER 88-GT-51 p 846 A88-54152 peroxide content in turbine fuels. Part 2 The effects of turbulence and statorlrotor interactions [AD-A192244] p 841 N88-29042 on turbine heat transfer. I - Design operating conditions A study of the effect of random input motion on low [ASME PAPER 88-GT-1251 p 848 A88-54236 Reynolds number flows An unsteady helicopter rotor: Fuselage interaction [AD-A195559] p 798 N88-29747 analysis Constitutive modeling for isotropic matenals [NASA-CR-4178] p 784 N88-28880 [NASA-CR-l82132] p 826 N88-29811 Nozzle airflow influences on fuel patternation Spray automated balancing of rotors: Methods and p 842 N88-29916 materials Assessment of a 3-0 boundary layer analysis to predict [ NASA-CR-182151] p 836 N88-29825 heat transfer and flow field in a turbine passage Evaluation of bond testing equipment for inspection of [NASA-CR-174894] p 854 NEB-30066 Army advanced composite airframe structures University of Southern California, Lo8 Angeles. [ AD-A1957951 p 841 N88-29885 Unsteady water channel Fuel effects on flame radiation and hot-section [AD-A194231] p 797 N88-28884 durability p 843 N88-29925 Stanford Univ.. Calif. An experimental study of an adaptive-wall wind tunnel v [ NASA-CR-1831521 p 835 N88-29821 Vigyan Research Associates, Inc., Hampton, Va. Sterling Software, Palo Alto, Calif. CFD predictionof the reactingflow field inside a subscale Smart command recognizer (SCR) - For development. scramlet combustor test, and implementation of speech commands [AIAA PAPER 88.32591 p 816 A88-53151 [AIAA PAPER 88-46121 p 858 A88-53654 Simulator evaluation of takeoff performance monitonng Sverdrup Technology, Inc., Mlddleburg Heights, Ohio. system displays A preliminary design study of supersonic through-flow [AIAA PAPER 88-4611 ] p 833 A88-53653 fan inlets Virginia Univ., Chartottesvllle. [AIAA PAPER 88-30751 p 816 A8843137 Unique clean-air. continuous-flow. Sverdrup Technology, inc., Cleveland, Ohio. high-stagnation-temperature facility for supersonic Views on the impact of HOST p 818 A88-54146 combustion research Development of a thermal and structural analysis [AIAA PAPER 88-3059AI p 832 A88-53135 procedure for mled radial turbines Von Karman Inst. for Fluid Dynamics, [ASME PAPER 88-GT-181 p 846 A88-54164 Rhode-Salnt-Genese (Belgium). Modeling of large stall in axial compressors Systems Technology, Inc., Hawthorne, Calif. [ VKI-TN-I641 p 853 N88-29124 Advances in flying qualities: Concepts and criteria for a mission oriented flying qualities specification p 812 N88-29739 T

Taylor (J.), Camberley (England). An intenm companson of operational CG records in turbulence on small and large civil aircraft p 830 N88-29729 c-4 FOREIGN TECHNOLOGY INDEX

~ ~ ~ AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 234) January 1989

Typical Foreign Technology Index Listing Effect of molecular structure on soot formation The effect of the Reynolds number on the characteristics of aviation turbine fuels three-dimensional flow in a straight compressor cascade [ASME PAPER 88-GT-211 p 838 A8844167 [ASME PAPER 88-GT-2691 p 794 A88-54343 Flow field in the tip gap of a planar cascade of turbine blades [ASME PAPER 88-GT-291 p 707 A88-54173 F The blowout of turbulent jet flames in co-flowingstreams of fuel-air mixtures FRANCE [ASME PAPER 88-GT-1061 p 838 A88-54225 Combined engines for future launchers Design and test of non-rotating ceramic gas turbine [AIAA PAPER 88-28231 p 836 A88-53105 components Flame stabilization in supersonic combustion JAPAN [ASME PAPER 89-GT-1461 p 81 9 A8844247 p 837 A8863164 A numerical method lof subsonic unsteady lllltng Notes on the occurrence and determination of carbon New version antistatic coating tester surlaces BIS Ill Some additional numerical results within gas turbine combustors p 844 A88-53166 r D 2 A88.10093 [ASME PAPER 88-GT-1641 p 839 A8844262 Dimensioning of turbine blades for fatigue and creep The feasibility. from an installational viewpoint, of p 817 A8843167 gas-turbine pressure-gain combustors Periodicity. superposition, and 3D effects in supersonic [ASME PAPER 88-GT-1811 p 849 A88-54272 compressor flutter aerodynamics Flow measurements in rotating stall in a gas turbine [ASME PAPER 88-GT-1361 p 791 A8844242 engine compressor Design of high performance fans using advanced [ASME PAPER 88-GT-2191 p 819 A88-54304 aerodynamic codes Transient performance Vending for a turbofan engine [ASME PAPER 88-GT-141J p 791 A88-54244 [ASME PAPER 88-GT-2221 p 819 A88-54306 The oil-free shafl line Precision error in a turbofan engine monitoring system [ASME PAPER 88-GT-1681 p 849 A88-54283 [ASME PAPER 88-GT-2291 p 81 9 A8864312 Test results and theoretical investigations on the ARL Computational tools for simulation methodologies 19 supersonic blade cascade Listings in this index are arranged alphabetically p 834 N88-28865 [ASME PAPER 88-GT-2021 p 792 A8844289 by country of intellectual origin The title of the The NAE atmospheric research aircraft Flow computation and blade cascade design in document is used to provide a brief description of p 81 5 N88-29730 turbopump turbines the sublect matter The page number and the ac- Aircraft dynamics: Aerodynamic aspects and wind tunnel [ASME PAPER 88-GT-2481 p 820 A8844326 techniques p 798 "3-29731 Numerical integrationof the 3D unsteady Euler equations 'cession number are included in each entry to as- The use of hot-filmtechnique for boundary layer studies for flutter analysis of axial flow cornpressors sist the user in locating the citation in the abstract on a 21 percent thick airfoil (ASME PAPER 88-GT-2551 p 794 Am-54331 section If applicable, a report number is also in- [NAE-AN-45] p 800 N88-29781 Pilotage system for the Pronaos gondola [IAF PAPER 88-0081 p 809 A88-55317 cluded as an aid in identifying the document The characterizatin of combustion by fuel composition: Measurements in a small conventional combustor Boundary layer simulation and control in wind tunnels p 842 N88-29920 [AGARD-AR-224] p 784 N88-28857 CHINA, PEOPLES REPUBLIC OF Three dimensional grid generation for complex An experimental investigation into the reasons of configurations: Recent progress reducing secondary flow losses by using leaned blades [AGARD-AG-3091 p 858 N88-29313 in rectangular turbine cascades with incidence angle The Flight of Flexible Aircraft in Turbulence: [ASME PAPER 88-GT-41 p 786 A88-54151 State-of-the-Art in the Description and Modelling of A An experimental investigation into the influence of blade Atmospheric Turbulence leaning on the losses downstream of annular cascades [AGARD-R-734-ADDJ p 784 N88-29717 Measured and predicted responses of the Nord 260 AUSTRALIA with a small diameter-height ratio Damage tolerance of impact damaged carbon fibre [ASME PAPER 88-GT-191 p 786 A8864165 aircraft to the low altitude atmospheric turbulence composite wing skin laminates p 804 A88-52670 The use of Bezier polynomial patches to define the p 830 N88-29723 The Flight of Flexible Aircraft in Turbulence: Transition modeling effects on viscous/inviscid geometrical shape of the flow channels of compressors State-of-the-Art in the Description and Modelling of interaction analysis of low Reynolds number airfoil flows [ASME PAPER 88-GT-601 p 788 A88-54192 Atmospheric Turbulence involving laminar separation bubbles Numerical solution to transonic potential equalions on [AGARD-R-734] p 785 N88-29725 [ASME PAPER 88-GT-321 p 787 A8844175 S2 stream surface in a turbomachine [ASME PAPER 88-GT-821 p 789 A88-54210 Extreme gusts distribution p 857 N88-29734 Fault diagnosis of gas turbine engines from transient Calculation of complete three-dimensional flow in a Advances in Flying Qualities data centrifugal rotor with splitter blades [AGARD-LS-157] p 785 N88-29735 [ASME PAPER 88-GT-2091 p 819 A88-54295 [ASME PAPER 88-GT-931 p 789 A88-54216 ObSeNed track-keeping performance of DCIO aircrafl Development and installation of an instrumentation Optimization design of the over-all dimensions of equipped with the Collins AINS-70 area navigation system: package for GE F404 investigative testing centrifugalcompressor stage Karlsruhe and Masstricht UACs (Upper Area Control [AD-A1962651 p 855 N88-30107 [ASME PAPER 88-GT-1341 p 849 A88-54241 centres) The development of acoustic emission for structural A unifiedsolution method for the flow calculations along [EEC-2021 p 803 N88-29788 integrity monitoring of aircrafl S1 and S2 stream surfaces used for the computer-arded Combustion and fuels in gas turbine engines [ AD-AI 962641 p 861 N88-30398 design of centrifugal cornpressors [AGARD-CP-422] p 841 N88-29910 [ASME PAPER 88-GT-2371 p 793 A88-54318 Studies of unsteady axial-compressor functioning An experimental investigationof a vortex flow cascade p 855 N88-30129 B [ASME PAPER 88-GT-2651 p 794 A8844341 A new variational finite element computation for BELGIUM aerodynamic inverse problem in turbines with long G A radial mixing computation method blades [ASME PAPER 88-GT-681 p 847 A88-54199 [ASME PAPER 88-GT-2751 p 794 A8844347 GERMANY,FEDERAL REPUBLIC OF Accounting for service environment in the fatigue Modeling of large stall in axial compressors Numerical solution of the hypersonic viscous shock layer evaluation of composite airframe structure [VKI-TN-164) p 853 N88-29124 equations with chemical nonequilibrium p 804 A88-52665 [IAF PAPER ST-88-08] p 796 A88-55313 Enstaff . A standard test sequence for composite A preliminary investigation of drag reduction and components combining load and environment C mechanism for a blunt body of revoluticn with slanted p 804 A8862666 base Fibre optic flow sensors based on the 2 focus CANADA ' [ NASA-TT-203491 p 799 N88-29753 principle p 844 A88-52733 New materials and fatigue resistant aircraft design. A digital simulation technique for the Drydenatmospheric Experimental and theoretical aspects of thick thermal Proceedings of the Fourteenth ICAF Symposium. Ottawa. model barrier coatings for turbine applications Canada, June 8-12, 1987 p 803 A88-52651 [ NASA-TT-203421 p 857 N88-30266 p 837 A88-53566 Evaluation of new malerials in the design of aircraft CZECHOSLOVAKIA Ultimate factor for structural design of modern fighters structures p 803 A88-52654 The effect of the inlet velocity profile in the [SAWE PAPER 17751 p 808 A8843784 NiCrAllbentonite thermal spray powder for high three-dimensional flow in a rear axial compressor stage lnflght CG-control .System aspects temperature abradable seals p 837 A88-53556 [ASME PAPER 88-GT-461 p 787 A88-54183 [SAWE PAPER 17951 p 827 A88-53796

D- 1 INDIA FOREIGN TECHNOLOGY INDEX

Detecbon of separation bubbles by infrared images in IRAN T transonic turbine cascades Base pressure in transonic speeds - A comparison [ASME PAPER 88-GT-331 p 787 A88-54176 between theory and experiment TAIWAN Turbulence measurements in a multistage low-pressure [ASME PAPER 88-GT-1321 p 790 A88-54240 Numerical analysis of airfoil and cascade flows by the turbine ITALY viscouslinviscid interactive technique [ASME PAPER 88-GT-791 p 788 A88-54207 Aspects of the fatigue behaviour of typical adhesively [ASME PAPER 88-GT-1601 p 791 A88-54259 Evaporation of fuel droplets in turbulent combustor bonded aircraft structures D 804 A88-52659 flow Possible future developments of motorgliders and light [ASME PAPER 88-GT-1071 p 839 A88-54226 aircraft p 605 A88-52697 U Experimental investigationof the three-dimensionalflow A comparison between measurements and turbul&ce in an annular compressor cascade U.S.S.R. models in a turbine cascade passage A projection-grid scheme for calculating transonic flow [ASME PAPER 88-GT-2011 p 792 A68-54288 [ASME PAPER 88-GT-2261 p 793 A88-54309 Theoretical investigation of the interaction between a past a profile p 785 A88-52795 compressor and the components during surge Prediction of the extreme values of the phase [ASME PAPER 88-GT-2201 p 851 A88-54305 coordinates of stochastic systems p 857 A88-52823 Delta wing configurations p 796 N88-28860 J Microprocessor functional-adaptive processing of signals of radio-navigation systems in an onboard Noise generation and boundary layer effects in JAPAN subsystem p 802 A68-52952 vortex-airfoil interaction and methods of digital hologram Microscopic inner damage correlated with mechanical A problem of optimal control with constraints on the analysis for these flow fields property degradation due to simulated fatigue loading in [AD-A194191] p 797 N68-28883 coordinates of the center of mass p 858 A88-53876 metal matrix composites p 837 A88-52657 Deformation and damage of the material of gas turbine Crash simulation calculations and component idealization for an airframe Computer code KRASH 79 Dynamic texture in visual system engine blades during thermal cycling in gas flow [ ETN-88-92971I p 801 NE8 28899 [AIAA PAPER 88-45781 p 832 A88-53630 p 845 A88-53954 Contnbutions to the modeling of wind shear for danger VSRA in-flight simulator - Its evaluation and Effect of loading asymmetry on the low-cycle fatigue of ZhS6F alloy under cyclic temperature changes studies applications p 838 A88-53955 [ NASA-TT-202931 p 802 N88-28900 [AIAA PAPER 88-48051 p 806 A88-53649 Calculation of stress relaxation in the surface-hardened Estimation of aircraft parameters using filter error Effects of incidence on three-dimensional flows in a layer near a hole in the disk of a gas-turbine engine methods and extended Kalman filter linear turbine cascade p 846 A88-53961 [ DFVLR-FB-88-15] p 810 N88-28911 [ASME PAPER 88-GT-1101 p 790 A88-54228 Conditions of the induction-plasmatronmodeling of the A contributiontothequantitative analysisof the influence Effect of shock wave movement on aerodynamic convective nonequilibrium heat transfer of bodies in of design parameters on the optimal design of passenger instability of annular cascade oscillating in transonic flow hypersonic flow p 786 A88-53970 aircraft [ASME PAPER 88-GT-1871 p 792 A88-54278 Three-dimensional hypersonic viscous shock layer on [ ETN-88 929791 p 810 N88-28912 Behaviour of the leg of the horseshoe vortex around Additional investigations into the aircraft landing blunt bodies in flow at angles of attack and sideslip the idealizedblade with zero attack angle by triple hot-wire p 786 A88-53971 process Test distributions measurements [ ESA-TT-10991 p 810 N88-28913 Corrosion and protection of gas turbine blades [ASME PAPER 88-GT-1971 p 792 A88-54285 p 838 A88-53996 Variable wina camber control svstems for the future Structure of tip clearance flow in an isolated axial Airbus program Mechanization of joint production during the assembly compressor rotor of aircraft structures p 846 A88-53998 [MBB-UT-104/68] p 830 "3-28932 [ASME PAPER 88-GT-2511 p 794 A88-54327 Develooment of a olass fiber wina following the Principles of the use of fuels and lubricants in civil Structural design and its improvements through the aviation p 838 A88-54001 construct;on regulation FAR Part 23 development of the XF3-30 engine [ ETN-88.929661 p 840 N88-26979 Application of the theory of anisotropic thin-walled [ASME PAPER 88-GT-2611 p 821 A88-54337 Gnd generabon for an advanced fighter aircraft beams and plates for wings made from composite D 859 N88-29319 material Analytical surfaces and grids p 860 N88-29322 N [IAF PAPER 88-2751 p 852 A88-55372 Mesh generation for industrial application of Euler and UNITED KINGDOM Navier Stokes solvers p 660 N68-29323 Use of composite materials to repair metal structures NETHERLANDS Grid generation around transport aircraft configurations p 804 A88-52660 using a multi-block structured computational domain Damage tolerance aspects of an expenmentalArall F-27 lower wing skin panel p 804 A88-52668 Fatigue crack propagation test programmefor the A320 p 860 N88-29325 wing p 604 A88-52662 Impact and damage tolerance properties of CFRP Flight test equipment for the on-board measurement of Towards the optimum ducted UHBR engine wind turbulence p 814 N88-29719 sandwich panels - An expenmental parameter study for [AIAA PAPER 88-29541 p 81 6 A88-53119 comparison of the influence of different gust models the Fokker 100 CA-EP flap p 804 A88-52671 on structural design p 81 1 N88-29722 Present and future developments of the NLR moving Future supersonic transport noise - Lessons from the past History of aeroelasticity in Germany from the beginning base research flight smulator [AlAA PAPER 88-29891 p 816 A88-53121 to 1945 [AIAA PAPER 88-45641 p 832 A88-53635 [ESA-TT-t082] p 799 N88-29767 New erosion resistant compressor coatings The minimisation of helicopter vibration through blade Supersonic wall adaptation in the rubber tube test [ASME PAPER 88-GT-I861 p 839 A88-54277 design and active control p 805 A88-53249 section of the DFVLR Goettingen Low-speed longitudinal flying qualities of modern Developments in computational methods for high-lift [ 18-222-87-A-061 p 836 NE8 29824 transport aircraft p 812 N88-29738 aerodynamics p 786 A88-53250 Investigationson the modificationof structural reliability Failure analysis for gas turbines The turboprop challenge p 605 A66-53539 by substitution of aluminum by carbon fiber reinforced [NLR-MP-87037-U] p 825 N88-29808 Caring for the high-time jet p 801 A88-53540 plastics in aircraft construction The RTM322 engine in the S-70C helicopter [ ILR-MITT-l95] p 841 N88-29877 [AIAA PAPER 86-45761 p 817 A88-53774 Turbulence effects on the droplet distribution behind Weight growth in airline service airblast atomizers p 842 N88-29915 P [SAWE PAPER 17961 p 809 A88-53797 Influence of operating conditions on the atomizationand POLAND Meeting the high temperature challenge - The distribution of fuel by air blast atomizers Modelling of aircraft program motion with application p 842 N88-29918 nonmetallic aero engine p 838 A88-53838 to circular loop simulation p 826 A88-53251 Surface engineering for high temperature PORTUGAL environments p 645 A68-53840 Radiation transfer in gas turbine combustors Aerodynamic and heat transfer measurements on a I p 843 N88-29929 transonic nozzle guide vane INDIA [ASME PAPER 88-GT-lo] p 766 A68-54157 Technology of flight simulation p 805 A88-52692 S The use of fins to reduce the pressure drop in a rotating Viability rating by fuel indexing method cavity with a radial inflow p 815 A86-52698 SWEDEN [ASME PAPER 88-GT-581 p 788 A88-54190 Effect of stage loading on endwall flows in an axial flow Development of the F404lRM12 for the JAS 39 Flow in single and twin entry radial turbine volutes compressor rotor Gripen [ASME PAPER 88-GT-591 p 847 A88-54191 [ASME PAPER 88-GT-1111 p 848 A88-54229 [ASME PAPER 88-GT-3051 p 822 A88-54374 Prediction of the pressure distribution for radial inflow A study of aerodynamic noise from a contra-rotating Analysis of the transmissionof sound into the passenger axial compressor stage p 823 A88-54938 between co-rotating discs compartmentof a propeller aircraft using the finite element [ASME PAPER 66-GT-611 p 847 A88-54193 The aerodynamics of an annular cascade of method Developmentof a 30 NavierStokes solver for application three-dimensionalairfoils p 795 A88-54942 [FFA-TN-1988-151 p 861 N88-29520 Dynamics of helicopter rotors p 809 A88-54954 to all types of turbomachinery Review of research concerning Solid Fuel Ramjet [ASME PAPER 88-GT-701 p 788 A88-54201 Quadrature formula for a double-pole singular integral (SOFRAM) at the Research Institute of National Defence A fast interactive two-dimensionalblade-to-blade profile p 796 A88-55093 (FOA) 2 design method INTERNATIONAL ORGANIZATION [FOA-C-20714-21 ] p 826 N88-29813 [ASME PAPER 88-GT-1001 p 790 A88-54220 Industrial production of CFRP-components in Airbus Standard fatigue specimens for fastener evaluation construction [ FFA-TN-1987-681 p 856 N88-30157 Three dimensional flow in radial-inflow turbines [SAWE PAPER 17941 p 845 A88-53795 SWITZERLAND [ASME PAPER 88-GT-1031 p 790 A88-54222 Aerodynamic data accuracy and quality Requirements Influence of deposit on the flow in a turbine cascade Further aspects of the UK engine technology and capabilities in wind tunnel testing [ASME PAPER 88-GT-2071 p 792 A88-54293 demonstrator programme [ AGARD-AR-254) p 798 N68-28893 Numencal simulation of inviscid transonic flow through [ASME PAPER 88-GT-104) p 848 A68-54223 AGARD engine disc cooperative test programme nozzles with fluctuating back pressure Gas turbine studies at Oxford 1969-1987 [ AGARD-R-7661 p 824 N88-28926 [ASME PAPER 88-GT-2871 p 794 A88-54356 [ASME PAPER 88-GT-1121 p 846 A88-54230

D-2 FOREIGN TECHNOLOGY INDEX UNITED KINGDOM

A transient flow facility for the study of the thermofluid-dynamics of a full stage turbine under engine representativeconditions [ASME PAPER 88-GT-1441 p 849 A88-54245 A UK perspective on Engine Health Monitoring (EHM) systems for future technology military engines [ASME PAPER 88-GT-1481 p 81 9 A8844249 Surface heat transfer fluctuationson a turbine rotor blade due to upstream shock wave passing [ASME PAPER 88-GT-1721 p 791 A88-54266 Brushes as high performance gas turbine seals [ASME PAPER 88-GT-1821 p 850 A88-54273 Expenmental investigation of rotating stall in a mismatched three stage axial flow compressor [ASME PAPER 88-GT-2051 p 850 A88-54292 Tip leakage in a centrifugal impeller [ASME PAPER 88-GT-2101 p 792 A88-54296 Computation of the jet-wake flow structure in a low speed centrifugal impeller [ASME PAPER 88-GT-2171 p 793 A88-54302 Helicopter health monitoring from engine to rotor [ASME PAPER 88-GT-2271 p 809 A88-54310 Wake-boundary layer interactions in an axial flow turbine rotor at off-design conditions [ASME PAPER 88-GT-2331 p 793 A88-54315 A methanoVoxygen burning combustor for an aircraft auxiliary emergency power unit [ASME PAPER 88-GT-2361 p 820 A88-54317 Turbulence measurements and secondary flows in a turbine rotor cascade [ASME PAPER 88-GT-2441 p 794 A88-54323 Recent advances in engine health management [ASME PAPER 88-GT-2571 p 820 A8844333 Boundary-layer flows in rotating cavities [ASME PAPER 88-GT-2921 p 852 A88-54361 XG40 - Advanced combat engine technology demonstrator programme [ASME PAPER 88-GT-3001 p 821 A88-54369 Design aspects of recent developments in Rolls-Royce RB211-524 powerplants t [ASME PAPER 88-GT-3011 p 821 A88-54370 Developing the Rolls-Royce Tay [ASME PAPER P9-GT-3021 p 821 A88-54371 H(infinity)-optimaldesign for helicopter control p 828 A88-54598 The nondestructive testing of welds in continuous fibre reinforced thermoplastics p 852 A88-55456 Complex configurations p 834 N88-28861 Transport-type configurations p 809 N88-28867 Combat aircraft p 81 0 N88-28868 Smoke hoods: Net safety benefit analysis [CAA-PAPER-87017] p 801 N88-28898 Fine resolution errors in secondary surveillance radar altitude reporting [ RSRE-870191 p 802 N88-28906 UK airmisses involving commercial air transport [ CAA- 1188 I p 803 N88-28907 Component adaptive grid generation for aircraft configurations p 859 N88-29316 A comparison of simple analytical models for representing propeller aircraft structural and acoustic responses [ISVR-TR-153] p 861 N88-29523 Noise levels from a jet-engined aircraft measured at ground level and at 1.2 m above the ground [NPL-AC-114] p 861 "3-29524 A review of measured gust responses in the light of modern analysis methods p 830 N88-29724 Measurement and analysis of low altitude atmospheric turbulence obtained using a specially instrumented Gnat aircraft p 857 N88-29728 An interim comparison of operational CG records in turbulence on small and large civil aircraft p 830 "3.29729 Re-assessmentof gust statistics using CAADRP data p 831 N88-29732 The role of simulationin flying qualities and flight control system related development p 835 N88-29742 An analysis of time and space requirementsfor aircraft turnrounds [TT-87051 p 802 N88-29783 V2500 engine collaboration [PNR904231 p 825 N88-29803 Developing the Rolls-Royce Tay [PNR90447] p 825 N88-29809 Spray performance of a vaporizing fuel injector p 842 N88-29919 High performance turbofan afterburner systems p 842 N88-29922 Gas turbine smoke measurement: A smoke generator for the assessment of current and future techniques p 843 N88-29930 Positron emission tomography: A new technique for observing fluid behavior in engineering systems [PNR90471] p 854 N88-30091

D-3 CONTRACT NUMBER INDEX iERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 234) January 1989

Typical Contract Number Index Listing

p 814 N88-28922 505-63-18 ...... p825 N88-29807 F33615-86-C-2666 ...... p 823 A88-54621 505-63-21-01 ...... p799 N88-29754 p 823 A88-54623 p 800 N88-29778 NAGl 179 D 60 N88.11382 F33615-86-C-3200 ...... p 797 N88-28887 505-63-51-07 ...... p862 N88-30399 F33615-86-C-3217 ...... p 840 N88-29004 505-63-51 ...... p855 N88-30128 p 843 N88-29962 N88-29489 F49620-83-K-0023 ...... p 793 A88-54297 505-66-11 ...... p831 N88-29817 F49620-85-C-0049 ...... p 825 N88-29805 505-66-51 ...... p831 N88-29816 p 81 3 N88-29795 532-06-11 ...... N8 8 . 2 9 7 9 0 NAGI-516 ...... p 828 A8844570 533-02-01-03 ...... N88-28891 CONTRACT NAGl-635 ...... p 797 N88-28891 533-04-1A ...... p826 N88-29811 NUMBER NAG1-709 ...... p 861 N88-29514 533-04-11 ...... p824 N88-28930 NAG1-784 ...... p 837 A88-54567 p825 N88-29804 NAG2-463 ...... p 828 A88-54571 533-04-12 ...... p854 N88-30066 NAG3-349 ...... p 851 A88-54328 534-03-13-30 ...... p840 N88-28983 NAG3-521 ...... p 787 A88-54189 535-03-01 ...... p811 N88-28917 NAG3-763 ...... p 858 A88-54202 p824 N88-28929 Listings in this index are arranged alpha- NASW-4307 ...... p 802 N88-28900 p853 N88-29142 numerically by contract number . Under each p 799 N88-29753 p 800 N88-29771 contract number . the accession numbers denoting p 857 N88-30266 535-03-11 ...... p811 N88-28918 NAS1-15325 ...... p 798 N88-28894 992-21-01 ...... p831 NEB-29819 documents that have been produced as a result of NAS1-16857 ...... p 81 1 N88-28915 research done under that contract are arranged in p 811 N88-28916 ascending order with the AlAA accession numbers p 840 N88-28983 NASl-16984 p 856 N88-29258 appearing first . The accession number denotes the ...... NASl-17469 ...... p 784 NEB-28880 number by which the citation is identified in the NASI-I7919 ...... p 816 A88-53151 abstract section . Preceding the accession number NASI-I8000 ...... p 862 N88-30399 is the page number on which the citation may be NASI -18066 ...... p 835 N88-28933 NASI -18235 p 786 A88-53762 found ...... NAS2-11555 ...... p 858 A88-53654 NAS2-11631 ...... p 858 A88-53654 AF PROJ. 3005 ...... p 843 N88-29962 NASP-11665 ...... p 831 N88-29819 AF-AFOSR-0049-83 ...... p 854 N88-30069 NASP-11853 ...... p 831 N88-29815 AF-AFOSR-0053-87 ...... p 841 N88-29890 NAS2-12404 ...... p 812 N88-29790 AF-AFOSR-0064-85 ...... NAS2-12419 ...... p 831 N88-29817 NAS2-12425 p 858 A88-53654 AF-AFOSR-0143-85 ...... p 860 N88-30378 ...... NAS2-12448 ...... p 814 N88-28919 AF-AFOSR-0155-82 ...... p 800 N88-29777 NAS2-12558 ...... p 831 N88-29816 AF-AFOSR-0158-87 ...... p 855 N88-30142 NAS3-23051 ...... p 824 N88-28928 AF-AFOSR-0243-86 ...... p 797 N88-28886 NAS3-23716 ...... p 854 N88-30066 AF-AFOSR-85-0295 ...... p 793 A88-54314 NAS3-23717 ...... p 846 A8844152 ARPA ORDER 5916 ...... p 836 N88-29822 p 848 A88-54236 BMFT-LFK-8531 ...... p 840 N88-28979 p 824 N88-28930 BMFT-LFL-83618 ...... p 830 N88-28932 p 825 N88-29804 BMVG-RUEFO-4 p 804 A88-52665 ...... NAS3-23925 ...... p 826 N88-2981I CNR-86.00938,59 ...... p 793 A88-54309 NAS3-23944 ...... p 851 A88-54355 DA PROJ. 1L1-62209-A-47-A ...... p 855 N88-30128 NAS3-24105 ...... p 816 A88-53137 DA PROJ. 1L1-62209-AH-76 p 836 N88-29825 NAS3-24211 ...... p 824 N88-28929 DA PROJ. 1L1-62716-A-700 p 815 N88-29797 NAS3-24222 ...... p 824 N88-28927 DAAA15-88-C-0005 ...... p 815 N88-29797 NAS3-24529 ...... p 81 1 N88-28917 DAAG29-82-K-0029 ...... p 821 A88-54363 NAS3-25069 ...... p 836 N88-29825 DAAG29-84-K-0048 ...... p 858 A88-54426 NCA2-OR-773-301 ...... p 797 N88-28882 DAAH01-87-12.1049 ...... p 836 N88-29822 NCC1-22 ...... p 796 A88-55094 DAAK70-85-C-0007 ...... p 841 N88-29042 NCC2-382 ...... p 801 N88-28896 DAAK70-87-C-0027 ...... p 835 NEB-29821 DAAK70-87-C-0043 ...... p 841 N88-29042 p 787 A88-54173 DAAL03-87-C-0010 ...... p 853 N88-29110 ...... p 849 A88-54272 DAJA45-87-C-0051 ...... p 797 N88-28883 p 847 A88-54181 DE-AC05-840R-21400 p 839 A88-54282 ...... p 848 A88-54229 DFG-SFB-167 ...... p 839 A88-54226 p 798 N88-29747 DLA900-84-C-0910 p 841 NEB-29885 ...... N00014-85-C02520 ...... p 841 N88-29042 DNA001-83-C-0182 p 821 A8844346 ...... N00014-86-C-0016 ...... p 845 A88-53571 FFA-STU-HU-2812 p 861 N88-29520 ...... N00140-83-C-9151 ...... p 818 A88-54170 FMV-FFL-82250-85-076-73-001 p 856 NEB-30157 ...... p 840 A88-54283 FO8635-83-C-0052 ...... p 818 A88-54170 N00600-84-D-4171 ...... p 814 N88-28923 FO8635-86-C-0309 D 840 A88-54283 ...... N62269-86-C-0278 ...... p 810 N88-28908 p 843 N88-29926 SWRl PROJ. 06-7576 ...... p 826 N88-29811 F19628-85-C-0002 p 835 N88-28934 ...... 307-50-06-03 ...... p 800 N88-29776 F33615-82-C-2255 D 815 A88-52676 ...... 505-33-43-09 ...... p 798 N88-28895 F33615-83-C-3200 ...... p 837 A88-52655 505-34-13-34 ...... p 856 N88-29258 505-45-13-02 ...... p 856 N88-29259 p 856 N88-29260 p 814 N88-28922 p 856 N88-29261 F33615-84-C-0518 p 834 A88-54357 505-60-21-04 ...... p 835 N88-29820 F33615-84-C-2457 ...... p 825 N88-29810 505-60-31-01 ...... p 798 N88-28894 F33615-84-C-2475 ...... p 791 A88-54266 505-60-4): ...... p 855 N88-30093 F33615-84-C-3216 ...... p 853 N88-29204 505-61-01-02 p 784 N88-28879 p 812 "3-29792 ...... p 835 N88-28933 F33615-84-C-3608 ...... p 828 A88-54650 F33615-84-C-5130 ...... p 841 N88-29889 505-61-51 ...... p 784 N88-28880 F33615-84-K-3009 ...... p 854 "3-30064 p 797 N88-28882 F33615-85-C-2515 ...... p 842 N88-29916 505-61-71-02 ...... p 799 "3.29752 F33615-85-C-3602 ...... p 814 N88-28921 505-62-OK ...... p 836 N88-29825

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 234) January 1989

Typical Report Number Index Listing

AD-A196185 ...... p 841 N88-29889 # AlAA PAPER 88-4442 ...... p 827 A88-53755 # AD-A196189 ...... p 836 N88-29823 # AlAA PAPER 88-4460 ...... p 783 A8843757 # AD-AI96247 ...... p 800 N88-29777 # AlAA PAPER 88-4462 ...... p 807 A88-53758 # AD-A196264 ...... p 861 N88-30398 # AlAA PAPER 88-4463 ...... p 807 A88-53759 # AD-AI96265 ...... p 855 N88-30107 # AlAA PAPER 88-4466 ...... p 783 A88-53760 * # AD-AI96776 ...... p 858 N88-29313 # AlAA PAPER 88-4469 ...... p A88-53761 * # AD-A198667 ...... p 784 N88-28857 # 783 AlAA PAPER 88-4471 ...... p 786 A88-53762 * # NASA CR 181446 , y,,NE8 10030, #, AlAA PAPER 88-4479 ...... p 807 A8863763 # AD-E500985 ...... p 853 N88-29061 # AlAA PAPER 88-4484 ...... p 807 A8843764 # AlAA PAPER 88-44858 ...... p 807 A88-53765 # AES-8609709F-1 ...... p 840 N88-29004 # AlAA PAPER 88-4487 ...... p 807 A88-53767 # AES-8609709F-1 ...... p 843 N88-29962 # NUMBER SPONSORED AlAA PAPER 88-4496 ...... p 807 A88-53768 # AlAA PAPER 88-4499 ...... p 808 A88-53769 # AFIT/CI/NR-88-46 ...... p 836 N88-29823 # ww AlAA PAPER 88-4506 ...... p 808 A88-53770 # AlAA PAPER 88-4507 ...... p 783 A88-53771 # , AFIT/DS/AA/88-2 ...... p 829 N88-28931 # AlAA PAPER 88-4511 ...... p 813 A88-53772 # AlAA PAPER 88-4512 ...... p 862 A8863773 # Listings in this index are arranged alpha- AFIT/GAE/AA/87D-21 ...... p 856 N88-30163 # AlAA PAPER 88-4576 ...... p A88-53628 # numerically by report number The page number AFIT/GAE/AA/88J-l ...... p 831 N88-29814 # 802 AlAA PAPER 88-4576 ...... p 817 A8863774 # AFIT/GAE/AA/88J-2 ...... p 799 N88-29769 # indicates the page on which the citation is located AlAA PAPER 88-4577 ...... p 832 A88-53629 # The accession number denotes the number by AlAA PAPER 88-4578 ...... p 832 A88-53630 # AFOSR-88-O415TR ...... p 797 N88-28886 # AlAA PAPER 88-4579 ...... p 857 A88-53631 # which the citation is identified. An asterisk (*) AFOSR-88-0466TR ...... p 797 N88-28884 # AlAA PAPER 88-4582 ...... p 805 A88-53634 # indicates that the item is a NASA report. A pound AFOSR-88-0636TR ...... p 860 N88-30378 # AlAA PAPER 88-4584 ...... p 832 A88-53635 # AFOSR-88-0640TR ...... p 854 N88-30069 # sign (X) indicates that the item is available on AlAA PAPER 88-4588 ...... p 857 A88-53637 # AFOSR-88-0656TR ...... p 800 N88-29777 # AlAA PAPER 88-4595 ...... p 832 A8863642 # microfiche. AFOSR-88-0669TR ...... p 841 N88-29890 # AlAA PAPER 88-4605 ...... p 806 A88-53649 # AlAA PAPER 88-4608 ...... p 806 A88-53650 * # A-86082 ...... p 811 N88-28918 * # AFWAL-TR-87-2087 ...... p N88-29810 # 825 AlAA PAPER 88-4609 ...... p 806 A88-53651 # A-88106 ...... p 799 N88-29750 * # AFWAL-TR-87-3055-VOL-2 ...... p 814 N88-28921 # AlAA PAPER 88-4610 ...... p 806 A88-53652 # AFWAL-TR-87-3055-VOL-5 ...... p 814 N88-28922 # AlAA PAPER 88-4611 ...... p 833 A88-53653 * # AFWAL-TR-87-3059 ...... p 840 N88-29004 # ACEE-26-FR-3504 ...... p 840 N88-28983 ' # AlAA PAPER 88-4612 ...... p 858 A88-53654 * # AFWAL-TR-87-3059 ...... p 843 N88-29962 # ACEE-26-TR-3478-VOL-2 ...... p 81 1 N88-28915 # AlAA PAPER 88-4618 ...... p 833 A8843657 # AFWAL-TR-87-3107 ...... p 797 N88-28887 # ACEE-26-TR-3958A-VOL-3 ...... p 81 1 N88-28916 * # AlAA PAPER 88-4619 ...... p 833 A88-53658 # AFWAL-TR-87-31 10 ...... p 854 N88-30064 # AlAA PAPER 88-4620 p 833 A88-53659 # AFWAL-TR-88-3003 ...... p 815 N88-29800 # ...... AD-A187379 ...... p 800 N88-29779 # AlAA PAPER 88-4634 ...... p 833 A88-53667 * # AFWAL-TR-88-3008 ...... p 855 N88-30143 # AD-A189864 ...... p 831 N88-29815 * # AlAA PAPER 88-46526 ...... p 813 A88-53827 # AFWAL-TR-88-4075 ...... p 841 N88-29889 # AD-A191219 ...... p 840 N88-29004 # AlAA PAPER 88-4652 ...... p 813 A88-53826 # AD-A192244 ...... p 841 N88-29042 # AlAA PAPER 88-4667 ...... p 845 A88-53829 # AFWL-TR-87-21 ...... p 812 N88-29792 # AD-AI92376 p 810 N88-28908 # AlAA PAPER 88-4671 ...... p 813 A88-53830 * # ...... AFWL-TR-87-99 ...... p 853 N88-29204 # AD-A193678 p 824 N88-28925 # ...... AFWL-TR-88-28 ...... p 854 N88-30006 # AD-AI93773 ...... p 797 N88-28887 # AIAA-88-21 10 ...... p 855 N88-30093 * # AD-A194115 ...... p 853 N88-29204 # AIAA-88-3152 ...... p 800 N88-29771 * # AGARD-AG-309 ...... p 858 N88-29313 # AD-AI94166 ...... pa53 N88-29110 # AIAA-88-3154 ...... p 825 N88-29807 * # AD-A194191 ...... p 797 N88-28883 # AGARD-AR-224 ...... p 784 N88-28857 # AD-A194231 p 797 ARL/AERO-PROP-TM-446 ...... p N88-30107 # ...... N88-28884 # AGARD-AR-254 ...... p 798 N88-28893 # 855 AD-A194435 ...... p 829 N88-28931 # p N88-29061 # ARL/MAT-R-l20 ...... p 861 N88-30398 # AD-AI94476 ...... 853 AGARD-CP-422 ...... p 841 N88-29910 # AD-A194481 ...... p 853 N88-2911 1 # AD-AI94490 p 853 N88-29112 # ARO-25053.1-EG-SBI ...... p 853 N88-29110 # ...... AGARD-LS-157 ...... p 785 N88-29735 # AD-A194553 ...... p 835 N88-28934 # AD-AI94601 p 814 N88-28921 # ASE-88-6 p N88-30378 /f ...... AGARD-R-734-ADD ...... p 784 N88-29717 # ...... 860 AD-AI94602 ...... p 814 N88-28922 # AGARD-R-734 ...... p 785 N88-29725 # AD-A194605 ...... p 814 N88-28923 # ASME PAPER 88-GT-100 ...... p 790 A88-54220 # AGARD-R-766 ...... p 824 N88-28926 # AD-A194650 ...... p 797 N88-28886 # ASME PAPER 88-GT-103 ...... p 790 A88-54222 # AD-AI94654 ...... p 860 N88-29337 # ASME PAPER 88-GT-104 ...... p 848 A88-54223 # AlAA PAPER 88-2796 ...... p 815 A88-53102 # AD-A194728 ...... p 835 N88-28935 # ASME PAPER 88-GT-I05 ...... p 818 A88-54224 # AlAA PAPER 88-2804 ...... p 815 A88-53103 # AD-AI94737 ...... p 835 N88-28936 # ASME PAPER 88-GT-106 ...... p 838 A88-54225 # AlAA PAPER 88-2805 ...... p 815 A88-53104 # p 815 N88-29800 # ASME PAPER 88-GT-107 ...... p 839 A88-54226 # AD-A194806 ...... AlAA PAPER 88-2823 ...... p 836 A88-53105 # AD-A194827 ...... p 862 N88-30471 # ASME PAPER 88-GT-108 ...... p 848 A88-54227 # AlAA PAPER 88-2830 ...... p 785 A88-53106 # ASME PAPER 88-GT-I 0 ...... p 786 A88-54157 # AD-AI94842 ...... p 836 N88-29822 # AlAA PAPER 88-2890A ...... p 816 A88-53111 # ASME PAPER 88-GT-110 ...... p 790 A88-54228 # ADA194874 ...... p 831 N88-29814 # AlAA PAPER 88-2954 ...... p 816 A88-53119 # ASME PAPER 88-GT-I 11 ...... p 848 A88-54229 * # AD-AI94875 ...... p 856 N88-30163 # AlAA PAPER 88-2989 ...... p 816 A88-53121 # AD-A194876 ...... p 799 N88-29769 ASME PAPER 88-GT-I 12 ...... p 848 A88-54230 # # AlAA PAPER 88-3001 ...... p 816 A88-53122 # AD-A194918 ...... p 802 N88-29785 # ASME PAPER 88-GT-120 ...... p 848 A88-54234 # AlAA PAPER 88.3011 ...... p 844 A88-53123 # p 815 N88-29797 # ASME PAPER 88-GT-125 ...... p 848 A88-54236 * # AD-AI95062 ...... AlAA PAPER 88-3039 ...... p 844 A88-53128 # AD-AI95072 ...... p 854 N88-30006 # ASME PAPER 88-GT-129 ...... p 818 A88-54239 # AlAA PAPER 88-3059A ...... p 832 A88-53135 * # ADA195144 ...... p 854 N88-30064 # ASME PAPER 88-GT-132 ...... p 790 A88-54240 # AlAA PAPER 88-3071 ...... p 816 A88-53136 # AD-AI95165 ...... p N88-29805 # ASME PAPER 88-GT-I34 ...... p 849 A88-54241 # 825 AlAA PAPER 88-3075 ...... p 816 A88-53137 ' # AD-AI95406 ...... p 831 N88-29818 # ASME PAPER 88-GT-136 ...... p 791 A88-54242 # AlAA PAPER 88-3077 ...... p 785 A88-53138 # AD-AI95440 p 854 N88-30069 # ASME PAPER 88-GT-141 ...... p 791 A8844244 # ...... AlAA PAPER 88-3093 ...... p 785 A88-53140 # AD-AI95467 ...... p 812 N88-29792 # ASME PAPER 88-GT-144 ...... p 849 A8864245 # AlAA PAPER 88-3098 ...... p 844 A88-53142 # AD-AI95559 ...... p 798 N88-29747 # ASME PAPER 88-GT-145 ...... p 784 A88-54246 # AlAA PAPER 88-3144 ...... p 844 A88-53145 # AD-A195594 p N88-30140 # ASME PAPER 88-GT-146 ...... p 819 A88-54247 # ...... 855 AlAA PAPER 88-3175 ...... p 826 A88-53148 # AD-AI95604 ...... p N88-30142 ASME PAPER 88-GT-148 ...... p 819 A88-54249 # 855 # AlAA PAPER 88-3239A ...... p 805 A88-53149 # AD-AI95639 ...... p 860 N88-30378 # ASME PAPER 88-GT-149 ...... p 849 A88-54250 # AlAA PAPER 138-3259 ...... p 816 A88-53151 * # AD-AI95693 ...... p 841 N88-29890 # ASME PAPER 88-GT-151 ...... p 791 A88-54251 # AlAA PAPER 613-3315 ...... p 813 A88-53156 # AD-A195699 ...... p N88-29810 # ASME PAPER 88-GT-152 ...... p 791 A88-54252 # 825 AlAA PAPER 88-3363 ...... p 805 A88-53161 # AD-A195717 ...... p 855 N88-30143 # ASME PAPER 88-GT-158 ...... p 839 A88-54257 # AD-AI95795 ...... p 841 N88-29885 # AlAA PAPER 88-4356 ...... p 829 A88-55275 # ASME PAPER 88-GT-160 ...... p 791 A88-54259 # AD-A195975 ...... p 844 N88-29991 # AlAA PAPER 88-4426 ...... p 806 A88-53752 * # ASME PAPER 88-GT-163 ...... p 849 A88-54261 # AD-A196129 ...... p 799 N88-29768 # AlAA PAPER 88-4428 ...... p 806 A88-53753 # ASME PAPER 88-GT-164 ...... p 839 A88-54262 # AD-A196154 ...... p 854 N88-29996 # AlAA PAPER 88-4429 ...... p 807 A8843754 * # ASME PAPER 88-GT-168 ...... p 849 A88-54263 #

F- 1 ASME PAPER 88-GT-171 REPORTNUMBER INDEX

ASME PAPER 88-GT-I71 ..... p 849 A8844265 # ASME PAPER 88 GT 60 p 788 A88-54192 # ETN-88-93055 ...... p 810 N88-28913 # ASME PAPER 88-GT-172 ...... p 791 A88-54266 # ASME PAPER 88 GT 61 p847 A8854193 # ETN-88-93058 ...... p 826 N88-29813 # ASME PAPER 88-GT-175 .... p 839 A88-54269 # ASME PAPER 88 GT-66 p847 A8854197 # ETN-88-93062 ...... p 856 N88-30157 # ASME PAPER 88-GT-I81 ...... p 849 A88-54272 # ASME PAPER 88 GT 68 p847 A8854199 # ETN-88-93115 ...... p 841 N88-29877 # ASME PAPER 88-GT-182 ... p 850 A88-54273 # ASME PAPER 88 GT 69 p 788 A88 54200 # ETN-88-93137 ...... p 802 N88-28906 # ASME PAPER 88-GT- I86 . . p 839 A88-54277 # ASME PAPER 88 GT 6 p818 A8834153 # ETN-88-93141 ...... p 861 N88-29524 ASME PAPER 88-GT-187 .... p 792 A88-54278 # ASME PAPER 88 GT 70 p 788 A88-54201 # ETN-88-93146 ...... p 803 N88-28907 ASME PAPER 88-GT-189 . p 833 A88-54280 # ASME PAPER 88 GT 73 I) 858 A88 54202 * # ASME PAPER 88-GT-18 ...... p 846 A8844164 * # ASME PAPER 88 GT 78 p 788 A88-54206 '# FFA-TN-1987-68 ...... p 856 N88-30157 # ASME PAPER 88-GT-190 .... p 850 A88-54281 # ASME PAPER 88 GT 79 p 788 A88 54207 # FFA-TN-1988-15 ...... p 861 N88-29520 # ASME PAPER 88-GT-I93 ...p 839 A88-54282 # ASME PAPER 88 GT 80 p 788 A88 54208 # ASME PAPER 88-GT-194 ... p 840 A88-54283 # ASME PAPER 88 GT 81 p 848 A88-54209 # FMRL-TR-2 ...... p 797 N88-28886 # ASME PAPER 88-GT-197 ..... p 792 A88-54285 # ASME PAPER 88 GT 82 p 789 A88-54210 # ASME PAPER 88-GT-199 ...... p 792 A88-54286 ASME PAPER 88 GT 83 p 789 A88 5421 1 # FOA-C-20714-2.1 ...... p 826 N88-29813 # ASME PAPER 88-GT-19 ...... p 786 A88-54165 # ASME PAPER 88 GT 89 p 789 A88 54213 # ASME PAPER 88-GT-POI p 792 A88-54288 # ASME PAPER 88 GT 90 p 789 A88 54214 # H-1461 ...... p 855 N88-30093 * # ASME PAPER 88-GT-202 ..... p 792 A88-54289 # ASME PAPER 88 GT 93 p 789 A8844216 # ASME PAPER 88-GT-204 ..... p 850 A88-54291 # ASME PAPER 88 GT 96 p 789 A88-54217 # HEL-TN-3-88-REV-B ...... p 815 N88-29797 # ASME PAPER 88-GT-205 ...... p 850 A88-54292 # ASME PAPER 88 GT 98 p 790 A88 54218 # ASME PAPER 88-GT-207 ... p 792 A88-54293 # ASME PAPER 88 GT 99 p 790 A88 54219 # HSER-9251 ...... p 824 N88-28928 * # ASME PAPER 88-GT-209 ...... p 819 A88-54295 # ASME PAPER 88-GT-20 ...... p 838 A88-54166 # ATC-156 ...... p835 N88-28934 # IAF PAPER ST-88-08 ...... p 796 A88-55313 # ASME PAPER 88-GT-210 ..... p 792 A88-54296 # ASME PAPER 88-GT-211 ...... p 793 A88-54297 # AV-FR-88/807 ...... p 836 N88-29822 # IAF PAPER 88-008 ...... p 809 A88-55317 # ASME PAPER 88-GT-212 ... p 850 A88-54298 # IAF PAPER 88-275 ...... p 852 A88-55372 # ASME PAPER 88-GT-213 ...... p 850 A88-54299 # AVSCOM-TM-88-C-003 ...... p 855 N88-30128 * # ASME PAPER 88-GT-214 ..... p 850 A88-54300 # 18-222-87-A-08 ...... p 836 N88-29824 # ASME PAPER 88-GT-216 ...... p 819 A88-54301 # AVSCOM-TR-88-C-018 ...... p 836 N88-29825 * # ASME PAPER 88-GT-217 ...... p 793 A88-54302 # ILR-MITT-195 ...... p 841 N88-29877 # ASME PAPER 88-GT-218 ...... p 793 A88-54303 # A4-TR-88-0546 ...... p 825 N88-29805 # ASME PAPER 88-GT-219 .... p 819 A88-54304 # ISBN-0-8330-0810-2 ...... p 813 N88-29795 # ASME PAPER 88-GT-21 ...... p 838 A88-54167 # BFLRF-243-PT-2 ...... p 841 N88-29042 # ISBN-0-86-039330-5 ...... p 801 N8 8 - 28 89 8 ASME PAPER 88-GT-220 ..... p 851 A88-54305 # ISBN-92-835-0426.7 ...... p 785 N88-29725 # ASME PAPER 88-GT-222 ...... p 819 A8864306 # BRIO6199 ...... p 802 N88-28906 # ISBN-92-835-0451-8 ...... p 858 N88-29313 # ASME PAPER 88-GT-226 ...... p 793 A88-54309 # ISBN-92-835-0457.7 ...... p 784 N88-28857 # ASME PAPER 88-GT-227 ...... p 809 A88-54310 # 88803805 ...... p 825 N88-29808 # ISBN-92-835-0458-5 ...... p 784 N88-29717 # ASME PAPER 88-GT-228 ...... p 851 A8864311 # ISBN-92-835-0461-5 ...... p 785 N88-29735 # ASME PAPER 88-GT-229 ...... p 819 A88-54312 # CAA-PAPER-87017 ...... p 801 N88-28898 ISBN-92-835-0465-8 ...... p 841 N88-29910 # ASME PAPER 88-GT-232 ..... p 793 A88-54314 # ISBN-92-835-0468-2 ...... p 798 N88-28893 # ASME PAPER 88-GT-233 ...... p 793 A88-54315 # CAA-1/88 ...... p 803 N88-28907 ISBN-92-835-0475-5 ...... p 824 N88-28926 # ASME PAPER 88-GT-236 ...... p 820 A88-54317 # ASME PAPER 88-GT-237 p793 A88-54318 # CRC-559 ...... p 844 N88-29991 # ISSN-0143-7143 ...... p 861 N88-29524 ASME PAPER 88-GT-239 ...... p 820 A88-54319 # ISSN-0171-1342 ...... p 810 N88-28911 # ASME PAPER 88-GT-242 ...... p 820 A88-54321 # CRINC-FRL-730-1 ...... p 797 N88-28891 * # ISSN-0347-3694 ...... p 826 N88-29813 # ASME PAPER 88-GT-243 ...... p 820 A88-54322 # ISSN-0951-6301 ...... p 803 N88-28907 ASME PAPER 88-GT-244 ...... p 794 A8844323 # CSDL-R-2055 ...... p 812 N88-29790 * # ASME PAPER 88-GT-248 ...... p 820 A88-54326 # CSDL-R-2056 ...... p 831 N88-29817 * # ISVR-TR-153 ...... p 861 N88-29523 # ASME PAPER 88-GT-24 ...... p 818 A88-54168 # ASME PAPER 88-GT-251 ...... p 794 A88-54327 # CTI-8601 ...... p 810 N88-28908 # JIAA-TR-87 ...... p 835 N88-29821 * # ASME PAPER 88-GT-252 ...... p 851 A88-54328 * # ASME PAPER 88-GT-255 ...... p 794 A88-54331 # DFVLR-FB-86-15 ...... p 810 N88-28911 # L-16082 ...... p 798 N88-28895 * # ASME PAPER 88-GT-257 ...... p 820 A88-54333 # L-I6405 ...... p 800 N88-29776 * # ASME PAPER 88-GT-259 ...... p 820 A8834335 # DFVLR-MIX-86-25 ...... p 799 N88-29767 # L-16435 ...... p 799 N88-29752 * # ASME PAPER 88-GT-25 ...... p 846 A88-54169 # DFVLR-MITT-67-13 ...... p 810 N88-28913 # L-16472 ...... p 784 N88-28879 * # ASME PAPER 88-GT-261 ...... p 821 A88-54337 # ASME PAPER 88-GT-265 ...... p 794 A88-54341 # DODA-AR-004-584 ...... p 855 N88-30107 # LC-87-28382 ...... p 813 N88-29795 # ASME PAPER 88-GT-267 ...... p 851 A88-54342 # DODA-AR-004-585 ...... p 861 N88-30398 # ASME PAPER 88-GT-269 ...... p 794 A88-54343 # MBB-UT-l04/88 ...... p 830 N88-28932 # ASME PAPER 88-GT-26 ...... p 818 A88-54170 # DOT/FAA/CT-86/33 ...... p 831 N88-29815 * # ASME PAPER 88-GT-271 ...... p 851 A88-54345 # DOT/FAA/CT-87/19 ...... p 814 N88-28919 * # MCR-TR-8711/12-1 ...... p 814 N88-28923 # ASME PAPER 88-GT-273 ...... p 821 A8844346 # ASME PAPER 88-GT-275 ...... p 794 A88-54347 # DOT/FAA/PS-87/ 1 p 835 N88-28934 # NADC-87169-60 ...... p 824 N88-28925 # ASME PAPER 88-GT-279 ...... p 840 A8844351 # NADC-88014-60 ...... p 810 N88-28908 # ASME PAPER 88-GT-285 ...... p 851 A8844354 # DTRC-87/045 p 800 N88-29779 # ASME PAPER 88-GT-286 ...... p 851 A88-54355 * # NAE-AN-45 ...... p800 N88-29781 # ASME PAPER 88-GT-287 ...... p 794 A88-54356 # D500 11313-1 p 811 N88-28917 * # ASME PAPER 88-GT-288 ...... p 834 A8844357 # D6-52511 p 798 N88-28894 ' # NAS 1 15:100081 ...... p 799 N88-29750 * # ASME PAPER 88-GT-292 ...... p 852 A88-54361 # NAS 1.15:100444 ...... p 855 N88-30093 * # ASME PAPER 88-GT-294 ...... p 821 A88-54363 # E4131 1 p 853 N88-29142 * # NAS 1.15:100649 ...... p 860 N88-29489 * # ASME PAPER 88-GT-295 ...... p 840 A88-54364 # E 4181 p 855 N88-30128 * # NAS 1.15:100659 ...... p 835 N88-29820 * # ASME PAPER 88-GT-296 ...... p 862 A88-54365 # E-4229 p 825 N88-29807 * # NAS 1.15 100663 ...... p 800 N88-29778 * # ASME PAPER 88-GT-297 ...... p 821 A88-54366 # E 4387 p 800 N88-29771 * # NAS 1.15 100665 ...... p 799 N88-29754 * # ASME PAPER 88-GT-29 ...... p 787 A88-54173 # NAS 1 15:100962 ...... p 855 N88-30128 * # ASME PAPER 88-GT-300 ...... p 821 A88-54369 # EEC-202 p 803 N88-29788 NAS 1.15.100964 ...... p 825 N88-29807 * # ASME PAPER 88-GT-301 ...... p 821 A88-54370 # NAS 1 15:100966 ...... p 853 "3-29142 * # ASME PAPER 88-GT-302 ...... p 821 A88-54371 # EFR-014-REV-B ...... p 815 N88-29797 # NAS 1.15:101357 ...... p 800 N88-29771 * # ASME PAPER 88-GT-303 ...... p 822 A88-54372 # NAS 1.15 4040-PT-2 ...... p 800 N88-29776 * # ASME PAPER 88-GT-305 ...... p 822 A88-54374 # EMA-85-R-02 ...... p 856 N88-29258 * # NAS 1.154074 ...... p 784 "3.28879 * # ASME PAPER 88-GT-306 ...... p 795 A88-54375 * # NAS 1 15:86426-PT-l ...... p 856 N88-29259 * # ASME PAPER 88-GT-311 ...... p 822 A88-54379 # €SA-TT-1082 ...... p 799 N88-29767 # NAS 1.15:86426-PT-2 ...... p 856 N88-29260 * # ASME PAPER 88-GT-312 ...... p 822 A88-54380 # ESA-rT-1099 ...... p 810 N88-28913 # NAS 1.15:86426-PT-3 ...... p 856 N88-29261 * # ASME PAPER 88-GT-316 ...... p 822 A88-54383 # NAS 1.15:88206 ...... p 811 N88-28918 * # ASME PAPER 88-GT-317 ...... p 834 A88-54384 # ETN-88-92612 ...... p 825 N88-29808 # NAS 1.26.172587 ...... p 811 N88-28915 * # ASME PAPER 88-GT-320 ...... p 852 A88-54385 # ETN-88-92653 ...... p 801 N88-28898 NAS 1.26:172588 ...... p 811 N88-28916 * # ASME PAPER 88-GT-321 ...... p 822 A88-54386 # ETN-88-92668 ...... p 825 N88-29803 # NAS 1.26:174791 ...... p 824 N88-28928 # ASME PAPER 88-GT-32 ...... p 787 A88-54175 # ETN-88-92680 ...... p 825 N88-29809 # NAS 1.26 174894 ...... p 854 N88-30066 * # ASME PAPER 88-GT-33 ...... p 787 A88-54176 # ETN-88-92698 ...... p 854 N88-30091 # NAS 1.26.174959 ...... p 824 N88-28927 * # ASME PAPER 88-GT-42 ...... p 847 A88-54181 # ETN-88.92720 ...... p 853 N88-29124 # NAS 1.26175104 ...... p 811 N88-28917 * # ASME PAPER 88-GT-46 ...... p 787 A88-54183 # ETN-88-92809 ...... p 861 N88-29520 # NAS 1.26177435 ...... p 797 N88-28882 * # ASME PAPER 88-GT-49 ...... p 847 A88-54185 # ETN-88-92824 ...... p 861 N88-29523 # NAS 1.26 177476 ...... p 831 N88-29819 * # ASME PAPER 88-GT-4 ...... p 786 A88-54151 # ETN-88-92933 ...... p 810 N88-28911 # NAS 1.26:177479 ...... p 831 N88-29816 * # ASME PAPER 88-GT-56 ...... p 787 A88-54188 # ETN-88-92965 ...... p 830 N88-28932 # NAS 1.26:177481 ...... p 812 N88-29790 * # ASME PAPER 88-GT-57 ...... p 787 A88-54189 ' # ETN-88-92966 ...... p 840 N88-28979 # NAS 1.26.177482 ...... p 831 N88-29817 * # ASME PAPER 88-GT-58 ...... p 788 A88-54190 # ETN-88-92971 ...... p 801 N88-28899 # NAS 1 26:179467 ...... p 825 N88-29804 * # ASME PAPER 88-GT-59 ...... p 847 A88-54191 # ETN-88-92979 ...... p 810 N88-28912 # NAS 1.26:179468 ...... p 824 N88-28930 * # ASME PAPER 88-GT-5 ...... p 846 A88-54152 * # ETN-88-93050 ...... p 799 N88-29767 # NAS 1.26.179521 ...... p 824 N88-28929 * #

F-2 -

REPORT NUMBER INDEX VKI-TN- 164

NAS 1.26:181483 ...... p 831 N88-29815 * # REPT-1286-IA ...... p 812 N88-29792 # NAS 1.26:181590 ...... p 814 N88-28919 * # REPT-587-IA ...... p 853 N88-29204 # NAS 1 26:181689 ...... p 862 N88-30399 * # RSRE-87019 ...... p 802 N88-28906 # NAS 1.26:182132 ...... p 826 N88-29811 ' # NAS 1 26:182151 ...... p 836 N88-29825 * # RU-TR-169-MAE-F ...... p 854 NEB-30064 # NAS 1.26:183077 ...... p 861 N88-29514 * # NAS 1 26:183122 ...... p 801 N88-28896 * # R85-956834 ...... p 854 N88-30066 * # NAS 1.26:183152 ...... p 835 N88-29821 * # R86AEB564 ...... p 824 N88-28929 * # NAS 1.26:3902 ...... p 856 N88-29258 * # R87AEG ...... p 825 N88-29810 # NAS 1 26:3914 ...... p 840 N88-28983 * # R88-956977-15 ...... p 784 NEB-28880 * # NAS 1.26.3992 ...... p 798 N88-28894 * # NAS 1.26:4173 ...... p 835 N88-28933 * # SAE AIR 4015 ...... p 801 A88-54400 NAS 1.26:4178 ...... p 784 N88-28880 * # NAS 1.26:4182 ...... p 797 N88-28891 * # SAWE PAPER 1756 ...... p 808 A88-53776 NAS 1.60:2594 ...... p 798 N88-28895 * # SAWE PAPER 1770 ...... p 808 A88-53781 NAS 1.60.2834 ...... p 799 N88-29752 * # SAWE PAPER 1771 ...... p 783 A88-53782 NAS 1.71:LAR-13777-1 ...... p 812 N88-29789 * # SAWE PAPER 1772 ...... p 808 A88-53783 NAS 1.77:20293 ...... p 802 N88-28900 * # SAWE PAPER 1775 ...... p 808 A88-53784 NAS 1.7720342 ...... p 857 N88-30266 * # SAWE PAPER 1779 ...... p 808 A88-53786 NAS 1 77:20349 ...... p 799 N88-29753 * # SAWE PAPER 1784 ...... p 862 A88-53788 SAWE PAPER 1786 ...... p 808 A88-53789 NASA-CASE-ARC-11636-1 ...... p 810 N88-28914 * SAWE PAPER 1787 ...... p 809 A88-53790 SAWE PAPER 1788 ...... p 809 A88-53791 NASA-CASE-IAR-13777-1 ...... p 812 N88-29789 # SAWE PAPER 1794 ...... p 845 A88-53795 SAWE PAPER 1795 ...... p 827 A8863796 NASA-CR-I72587 ...... p 811 N88-28915 * # SAWE PAPER 1796 ...... p 809 A88-53797 NASA-CR-172588 ...... p 811 N88-28916 * # SAWE PAPER 1798 ...... p 809 A88-53798 NASA-CR-174791 ...... p 824 N88-28928 * # SAWE PAPER 1801 ...... p 827 A88-53799 NASA-CR-174894 ...... p 854 N88-30066 * # NASA-CR-174959 ...... p 824 N88-28927 * # SRA-R88-930015-F ...... p 853 N88-29110 # NASA-CR-175104 ...... p 81 1 N88-28917 * # NASA-CR-177435 ...... p 797 N88-28882 * # SWRI-8814 ...... p798 N88-29747 # NASA-CR-177476 ...... p 831 N88-29819 * # NASA-CR-177479 ...... p 831 N88-29816 # TR-67-13 ...... p 814 N88-28922 # NASA-CR-177481 ...... p 812 N88-29790 * # TR-87-14 ...... p814 N88-28921 # NASA-CR-177482 ...... p 831 N88-29817 * # NASA-CR-179467 ...... p 825 N88-29804 * # TT-8705 ...... p802 N88-29783 # NASA-CR-I79468 ...... p 824 N88-28930 * # NASA-CR-179521 ...... p 824 N88-28929 * # UCB/R/88/A1053 ...... p 855 N88-30142 # NASA-CR-181483 ...... p 831 N88-29815 * # NASA-CR-I81590 ...... p 814 N88-28919 # UDR-TR-87-95 ...... p 797 N88-28887 # NASA-CR-I81689 ...... p 862 N88-30399 * # UDR-TR-88-21 ...... p 841 N88-29889 # NASA-CR-182132 ...... p 826 N88-29811 * # NASA-CR-182151 ...... p 836 N88-29825 * # US-PATENT-APPL-SN-210480 ..... p 812 N88-29789 * # NASA-CR-183077 ...... p 861 N88-29514 e # US-PATENT-APPL-SN-933963 ..... p 810 N88-28914 * NASA-CR-183122 ...... p 801 N88-28896 * # NASA-CR-I83152 ...... p 835 N88-29821 * # US-PATENT-CLASS-244.12.3 ...... p 810 N88-28914 * NASA-CR-3902 ...... p 856 N88-29258 * # US-PATENT-CLASS-244-12.4...... p 810 N88-28914 * NASA-CR-3914 ...... p 840 N88-28983 # US-PATENT-CLASS-244-207 ...... p 810 N88-28914 ' NASA-CR-3992 ...... p 798 N88-28894 * # US-PATENT-CLASS-244-45-A ..... p 810 N88-28914 * NASA-CR-4173 ...... p 835 N88-28933 * # US-PATENT-CLASS-244.55 ...... p 810 N88-28914 * NASA-CR-4178 ...... p 784 N88-28880 * # NASA-CR-4182 ...... p 797 NEB-28891 # US-PATENT-4.767.083 ...... p 810 N88-28914 *

NASA-TM-100081 ...... p 799 N88-29750 * # USAAEFA-63-13 ...... p 802 N88-29785 # NASA-TM-100444 ...... p 855 N88-30093 * # NASA-TM-100649 ...... p 860 NEB-29489 * # USAAVSCOM-TM-87-D-5...... p 799 N88-29768 # NASA-TM-100659 ...... p 835 N88-29820 * # NASA-TM-I00663 ...... p 800 N88-29778 * # USAAVSCOM-TR-87-A-7 ...... p 831 N88-29819 # NASA-TM-I00665 ...... p 799 N88-29754 * # NASA-TM-100962 ...... p 855 N88-30128 * # UTRC-R86-956480-VOL-2 ...... p 825 N88-29804 * # NASA-TM-100964 ...... p 825 N88-29807 * # NASA-TM-100966 ...... p 853 N88-29142 * # UTRC/R88-956480-VOL-3 ...... p 824 N88-28930 * # NASA-TM-101357 ...... p 800 N88-29771 * # NASA-TM-4040-PT-2 ...... p 800 N88-29776 * # VKI-TN-164 ...... p 853 N88-29124 # NASA-TM-4074 ...... p 784 N88-28879 * # NASA-TM-86426-PT-1 ...... p 856 N88-29259 * # NASA-TM-86426-PT-2 ...... p 856 N88-29260 * # NASA-TM-86426-PT-3 ...... p 856 N88-29261 * # NASA-TM-88206 ...... p 811 NEB-28918 * #

NASA-TP-2594 ...... p 798 N88-28895 * # NASA-TP-2834 ...... p 799 N88-29752 * #

NASA-TT-20293 ...... p 802 N88-28900 * # NASA-TT-20342 ...... p 857 N88-30266 * # NASA-TT-20349 ...... p 799 N88-29753 * #

NATICKITR-881021 ...... p 854 N88-29996 #

NLR-MP-870374 ...... p 825 N88-29808 #

NOSC/TR-l211 ...... p 853 N88-29061 #

NPL-AC-I14 ...... p 861 N88-29524

NPS67-88-001 ...... p 853 N88-29112 #

NRC-27892 ...... pa00 N88-29781 #

PNR90423 ...... p 825 N88-29803 # PNR90447 ...... p825 N88-29809 # PNR90471 ...... p854 N88-30091 #

R-3255-AF ...... p 813 N88-29795 # F-3 ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 234) January 1989

Typical Accession Number A8843783 p 808 A88-54227 # p848 A88-54361 # p 852 Index Listing A8843784 p 808 A8844228 # p790 A88-54363 # p 821 A88-54364 p 840 A88-53786 p 808 A88-54229 * # p 848 # A8844365 # p862 A88-53788 p 862 A8844230 # p848 A88-54366 # p 821 A8863789 p 808 A8844234 # p848 NHH 100fIH ' u 15 A88-53790 p 809 A8844369 # p 821 A88-54236 * # P 848 A8843791 p 809 A88-54370 # p 821 A88-54239 # p 818 A88-54371 # P 821 A8843795 p 845 A88-54240 # p790 A88-53796 p 827 A88-54372 # p822 A8844241 # p849 A8844374 # p822 L A88-53797 p 809 A88-54242 # p 791 rl A8843798 p 809 A8844375 * # P 795 A8834244 # p791 A- A8863799 p 827 A88-54379 # p822 A88-54245 # p849 A8844380 # p822 A88-53800 * p 783 A88-54246 # p784 A88-53826 # p813 A88-54383 # p822 A88-54247 # p 819 A88-54384 # p834 A8863827 # p813 A88-54249 # p 819 A88-53829 # p 845 A88-54385 # p852 A8864250 # p849 A88-54386 # P 822 A88-53830 * # p 81 3 A88-54251 # p791 A88-53838 p 838 A88-54400 p 801 Listings is this index are arranged alpha-numeri- A8844252 # p 791 A88-53840 p 845 A8864424 * p 827 cally by accession number The page number A8844257 # p839 A88-54426 p 858 A88-53847 * p 833 A88-54259 # p 791 listed to the right indicates the page on which the A88-53876 p 858 A88-54474 p 827 A88-54261 # p849 A88-54507 p 822 citation IS located An asterisk (*) indicates that A8843954 p 845 A8844262 # p839 A8843955 p 838 A88-54526 * p 827 the item is a NASA report A pound sign (#) indi- A88-54263 # p 849 A88-54528 p 827 A88-53961 p 846 A88-54265 # p849 cates that the item is available on microfiche A88-53970 p 786 A88-54549 * p 828 A88-54266 # p791 A88-54566 p 852 A88-53971 p 786 A88-54269 # P839 A88-53996 p 838 A88-54567 * p 837 A88-54272 # p 849 A88-54570 * p 828 A88-53998 p 846 A88-54273 # p850 p 786 A8844571 * p 828 A88-52375 p 803 A8843250 A88-54001 p 838 A88-54277 # p839 A88-52651 p 803 A8843251 p 826 A8844137 * p 817 A88-54598 p 828 A88-54278 # P792 A88-54619 p 822 A88-52652 p 803 A88-53539 p 805 A8844138 '# p 817 A88-54280 # p833 A88-54139 * p 846 A8844620 p 823 A 88 - 5 26 5 3 p 803 A88-53540 p 801 # A88-54281 # p 850 A88-52654 p 803 A8844140 * # p 817 A88-54621 p 823 A 88 - 5 35 42 p 837 A8864282 # p839 A8552655 p 837 A88-54141 '# p817 A88-54622 p 823 p 837 A88-54283 # p 840 A88-52657 p 837 A88-53556 A8844143 # p817 A88-54623 p 823 p 845 A88-54285 # p792 p 823 A88-52659 p 804 A88-53563 A88-54145 * # p 838 A88-54624 p 837 A88-54286 p 792 A88-52660 p 804 A88-53566 A88-54146 * # p 818 A88-54650 p 828 p 845 A88-54288 # p792 A88-52662 p 804 A88-53571 A88-54151 # p 786 A8844652 p 828 p 845 A8844289 # p792 A88-52665 p 804 A88-53579 A88-54152 * # p 846 A 88 - 5 46 5 3 p 829 p 845 A88-54291 # p850 A88-52666 p 804 A88-53581 * A88-54153 # p818 A88-54654 p 829 A 53 6 2 6 p 832 A88-54292 # p850 p 829 A 88 - 52 6 6 8 p 804 88 - A88-54157 # p 786 A88-54656 A88-53628 p 802 A8844293 # p 792 p 823 A88-52670 p 804 # A88-54164 * # p 846 A88-54658 p 832 A88-54295 # p819 A88-52671 p 804 A88-53629 # A88-54165 # p 786 A88-54659 p 829 p 832 A8844296 # p 792 A8862672 p 805 A88-53630 # A88-54166 # p838 A88-54660 p 829 p 857 A88-54297 # p793 p 829 A88-52673 p 805 A88-53631 # A8834167 # p838 A88-54661 p 805 A8844298 # PESO A88-52676 # p 815 A88-53634 # A88-54168 # p818 A88-54725 p 813 p 832 A88-54299 # p850 p 840 A88-52684 * # p 815 A88-53635 # A88-54169 # p846 A88-54857 # p 857 A88-54300 # p850 A88-52685 # p 785 A8843637 # A88-54170 # pa18 A8844869 p 795 p 832 A88-54301 # p 819 p 795 A88-52686 # p 785 A88-53642 * # A88-54173 # p 787 A88-54907 # A88-53649 # p 806 A8864302 # p 793 A8844938 # p 823 A8862692 # p 805 A88-54175 # p787 A8844303 # p 793 A88-52697 # p 805 A88-53650 * # p 806 A8844176 # p787 A8844940 # p 795 A88-53651 # p 806 A88-54304 # p819 A88-54941 # p 795 A88-52698 # p 815 A88-54181 # p847 A8864305 # p 851 A88-52733 p 844 A8863652 # p 806 A8864183 # p787 A8844942 # D 795 A88-54306 # p 819 p 795 A88-52795 p 785 A88-53653 ' # p 833 A8844185 # p847 A88-54943 # A8843654 * # p 858 A8844309 X p 793 A 88 - 5 49 4 4 # A88-52823 p 857 A8864188 # p787 A8844310 # p809 A88-52952 p 802 A88-53657 # p 833 A88-54189 # p 787 A8 8 - 54 9 4 6 # p 833 A8844311 # p 851 A88-53102 # p 815 A88-53658 # A88-54190 # p788 A8 8 - 54 9 5 4 # A88-53659 # p 833 A8864312 # P819 A8 8 - 55 0 0 0 A88-53103 # p 815 A88-54191 # p847 A8844314 # p793 A88-53104 # p 815 A88-53667 * # p 833 A88-54192 # p 788 A88-55041 p 784 A88-53671 # p 858 A8844315 # P 793 A8845042 p 852 A88-53105 # p 836 A88-54193 # p 847 A8844317 # p 820 A8843106 # p 785 A88-53752 * # p 806 A8844197 # p 847 A88-55064 # p 829 p A8844318 # p793 p 796 A88-53111 # p 816 A8843753 # 806 A88-54199 # p 847 A8845077 '# p 807 A8844319 # p 820 p 796 A88-53119 # p 816 A8843754 * # A88-54200 # p 788 A88-55078 # A8843755 # p 827 A88-54321 # p 820 A88-55093 # p 796 A88-53121 # p 816 A88-54201 # p 788 A8864322 # p820 A88-53122 # p 816 A8843757 # p 783 A8844202 * # p 858 A8845094 '# p 796 p 807 A8844323 # p 794 p 852 A88-53123 # p 844 A88-53758 # A88-54206 * # p 788 A88-55154 p 807 A88-54326 # p820 p 829 A88-53128 # p 844 A88-53759 # A88-54207 # p788 A88-55275 # p 783 A88-54327 # p794 p 840 A88-53135 * # p 832 A88-53760 '# A8844208 # p788 A88-55286 p 783 A8864328 * # p 851 D 801 A8843136 # p 816 A88-53761 '# A88-54209 # p848 A88-55288 A88-53762 * # p 786 A88-54331 # p794 A88-55290 p 801 A88-53137 * # p 816 A8844210 # p789 A8844333 # p820 A88-53118 # p 785 A88-53763 # p 807 A8844211 # p 789 A88-55313 # p 796 p 807 A88-54335 # p820 p 809 A88-53143 # p 785 A88-53764 # A8844213 # p789 A88-55317 # p 807 A8844337 # p821 p 1 A88-53142 # p 844 A8843765 # A88-54214 # p789 A8845372 # 852 p 807 A8844341 # p 794 p 852 A88-53145 # p 844 A88-53767 # A88-54216 # p 789 A88-55456 p 807 A8864342 # p 851 1 A88-53148 # p 826 A88-53768 # A8864217 # p 789 p A8844343 # p794 A88-53149 # p 805 A88-53769 # 808 A88-54218 # p790 N88-28857 # p784 p A88-54345 # p851 A88-53151 '# p 816 A88-53770 # 808 A8844219 # p 790 N88-28859 * # P 834 p 783 A88-54346 # P 821 A88-53156 # p 813 A8843771 # A88-54220 # p 790 N88-28860 # p796 A8843772 # p 813 A8844347 # P794 N88-28861 # p834 A88-53161 # p 805 A8844222 # p 790 A88-54351 # p 840 A8843773 # p 862 N88-28865 # p834 A88-53164 # p 837 A8844223 # p848 A8844354 # P851 A8863774 # p 817 N88-28867 # p809 A88-53166 # p 844 p A8844224 # p818 A88-54355 * # p 851 A 88 - 5 37 7 6 808 N88-28868 # p8lO A88-53167 # p 817 A88-53781 p 808 A88-54225 # p838 A88-54356 # p794 N88-28879 * # p 784 A88-53249 p 805 A 88 - 5 37 8 2 p 783 A88-54226 # p839 A8864357 # P834 G-1 ACCESSION NUMBER INDEX N88-28880

N88-28880 * # p 784 N88-29742 # p 835 N88-28882 * # p 797 N88-29747 # p 798 N88-29750 * # P 799 N88-28883 # p 797 N88-29752 * # p 799 N88-28884 # p797 N88-29753 * # P 799 N88-28886 # p 797 N88-29754 * # P 799 N88-28887 # p797 N88-29767 # P799 N88-28891 '# p 797 N88-29768 # p 799 N88-28893 # p 798 N88-29769 # p 799 N88-28894 * # p 798 N88-29771 * # p 800 N88-28895 * # p 798 N88-29776 * # p 800 N88-28896 * # p 801 N88-29777 # p800 NEB-28898 p 801 N88-29778 * # p 800 N88-28899 # p801 N88-29779 # p 800 N88-28900 * # p 802 NEB-29781 # p 800 N88-28906 # p802 N88-29783 # p802 N88-28907 p 803 N88-29785 # p 802 N88-28908 # p810 N88-29788 p 803 N88-28911 # p 810 N88-29789 # p 81 2 N88-28912 # pel0 N88-29790 * # p 812 N88-28913 # p810 N88-29792 # pa12 N88-28914 p 810 N88-29795 # p813 N88-28915 '# p 811 N88-29797 # p 815 N88-28916 '# p 811 N88-29800 # P 815 N88-28917 * # p 81 1 N88-29803 # p 825 N88-28918 * # p 81 1 N88-29804 * # p 825 N88-28919 '# p 814 N88-29805 # p825 N88-28921 # p814 N88-29807 * # p 825 N88-28922 # p814 N88-29808 # p825 N88-28923 # p814 N88-29809 # p825 N88-28925 # p824 N88-29810 # P825 N88-28926 # p824 N88-29811 * # p 826 N88-28927 * # p 824 N88-29813 # p826 N88-28928 * # p 824 N88-29814 # p831 N88-28929 * # p 824 N88-29815 * # p 831 N88-28930 * # p 824 N88-29816 * # p 831 N88-28931 # p 829 N88-29817 * # p 831 N88-28932 # p 830 N88-29818 # P831 N88-28933 * # P 835 N88-29819 * # p 831 N88-28934 # p 835 N88-29820 * # P 835 N88-28935 # p 835 NEB-29821 * # p 835 N88-28936 # p835 N88-29822 # P836 N88-28979 # P840 N88-29823 # P836 N88-28983 * # p 840 N88-29824 # p836 N88-29004 # p840 N88-29825 * # P 836 N88-29042 # P 841 N88-29877 # p841 N88-29061 # p 853 N88-29885 # 11841 N88-29110 # p 853 N88-29889 # p841 N88-29111 # p853 N88-29890 # P841 N88-29112 # p 853 N88-29910 # p841 N88-29124 # p853 N88-29911 # P826 N88-29142 * # p 853 N88-29913 # p 842 N88-29204 # p853 N88-29915 # p 842 N88-29258 * # p 856 N88-29916 # p 842 N88-29259 * # p 856 N88-29918 # p 842 N88-29260 * # p 856 N88-29919 # p 842 N88-29261 * # p 856 N88-29920 # p 842 N88-29313 # p 858 N88-29922 # p842 N88-29314 # p859 N88-29925 # p 843 N88-29315 * # p 859 N88-29926 # P843 N88-29316 # p859 N88-29929 # p 843 N88-29317 # p859 N88-29930 # p843 N88-29318 * # p 859 N88-29935 # p843 N88-29319 # p859 N88-29962 # p843 N88-29320 # p859 N88-29991 # p844 N88-29321 # p 859 N88-29996 # p 854 N88-29322 # p 860 N88-30006 # p854 N88-29323 # p 860 N88-30064 # p854 N88-29324 # p 860 N88-30066 * # p 854 N88-29325 # p860 N88-30069 # p854 N88-29337 # p 860 N88-30091 # p854 N88-29365 * # p 814 N88-30093 * # P 855 N88-29489 * # p 860 N88-30107 # p 855 N88-29514 * # p 861 N88-30128 * # P 855 N88-29520 # p861 N88-30129 # P 855 N88-29523 # p861 N88-30140 # P 855 N88-29524 p 861 N88-30142 # P855 N88-29717 # p 784 N88-30143 # P855 N88-29718 # p830 N88-30157 # P856 N88-29719 # pa14 N88-30163 # p856 N88-29721 # P 811 N88-30266 * # p 857 N88-29722 # p 811 N88-30378 # p 860 N88-29723 # p830 N88-30398 # p 861 N88-29724 # p830 N88-30399 * # p 862 N88-29725 # p785 N88-30471 # p 862 N88-29726 * # p 830 N88-29727 * # p 857 N88-29728 # p 857 N88-29729 # p 830 N88-29730 # p 815 N88-29731 # p 798 N88-29732 # p 831 N88-29734 # P 857 N88-29735 # p 785 N88-29738 # p 812 N88-29739 # p 812 N88-29740 # p 812

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IMPORTANT NOTICE NTlS Shipping and Handling Charges U.S., Canada, Mexico - ADD $3.00 per TOTAL ORDER All Other Countries - ADD $4.00 per TOTAL ORDER Exceptions - Does NOT apply to: ORDERS REQUESTING NTlS RUSH HANDLING ORDERS FOR SUBSCRIPTION OR STANDING ORDER PRODUCTS ONLY NOTE: Each additional delivery address on an order requires a separate shipping and handling charge. 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (234) 4. Title and Subtitle 5. Report Date Aeronautical Engineering January, 1989 A Continuing Bibliography (Supplement 234) 6. Performing O?ganizationCode

7. Author($ 8. Performing Organization Report No.

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

~ 13. TvDe_. of ReDort and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency Code

I 15. Supplementary Notes

16. Abstract This bibliography lists 539 reports, articles and other documents introduced into the NASA scientific and technical information system in December, 1988.

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

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price' Unclassified Unclassified 156 A08lHC

'For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Langley, 1989