--- Aeronautical NA,3Ar S?-/bJ\r '(;.)3, Engineering February 1988 A Continuing Bibliography with Indexes

National Aeronacrtics and Space Administration

Aeronautical Engineering Aem :iMg Aeronautical Engin ngirieeiring Aeronautical E %Ia IEncjineering Aevonauti n(i5Uticikl Engineering Aeronaut Aeronautical Engineering Aero 3nrhg A,eronautical EngineeringI nqineering!I Aeronautical Engine -a1w4 Enqineering Aeronautical Ei niautid Engineering Aeronaut!

Pleronautical Enaineerinu- Aeru NASA SP-7037(223)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(Supplement 223)

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in January 1988 in

Scientific and Technical Aerospace Reports (S JAR) lnternational Aerospace Abstracts (IAA).

Scientific and Technical Information Division 1988 National Aeronautics and Space Administration Washington, DC This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A07. INTRODUCTION

This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037)lists 423 reports, journal articles and other documents originally announced in January 1988 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (lAA). The coverage includes documents on the engineering and theoretical aspects of design, construc- tion, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and as- sociated 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 items will precede the STAR items within each category Seven indexes -- subject, personal author, corporate source, foreign technology, contract number, report number, and accession number -- are included. An annual cummulative index will be published.

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

iii TABLE OF CONTENTS

Page Category 01 Aeronautics (General) 1

Category 02 Aerodynamics 2 Includes aerodynamicsof bodies, combinations,wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 19 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 19 Includes digital and voice communicationwith aircraft; air navigation systems (satel- lite and ground based); and air traffic control.

Category 05 Aircraft Design, Testing and Performance 23 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 25 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 28 Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and onboard auxiliary power plants for aircraft.

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

Category 09 Research and Support Facilities (Air) 39 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 40 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; space communications, spacecraft communications, command and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft pro- pulsion and power.

Category 11 Chemistry and Materials 40 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing. Category 12 Engineering 43 Includes engineering (general); communications and radar; electronics and electri- cal engineering; fluid mechanics and heat transfer; instrumentation and photo- graphy; lasers and masers; mechanical engineering; quality assurance and relia- bility; and structural mechanics.

Category 13 Geosciences 57 Includes geosciences (general); earth resources and remote sensing; energy pro- duction and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.

Category 14 Life Sciences 57 Includes life sciences (general); aerospace medicine; behavioral sciences; man/ system technology and life support; and space biology.

Category 15 Mathematical and Computer Sciences 58 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 61 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and ther- modynamics and statistical physics.

Category 17 Social Sciences 62 includes social sciences (general); administration and management; documenta- tion and information science; economics and cost analysis; law, political science, and space policy; and urban technology and transportation.

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

Category 19 General 62

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

vi TYPICAL REPORT CITATION AND ABSTRACT

NASA SPONSORED 1rON 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 *-AVAILABILITY SOURCE REPORT NUMBERS- (NASA-TM-86725; H-1283; NAS 1.1586725) Avail: NTlS HC PRICE CODE- AO3/MF A01 CSCL 01c 4 COSATI CODE The Highly Manueverable Aircraft Technology (HIMAT) program 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 made on a single-discipline basis, so that aerodynamics, structures, 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 technologies contributed to total vehicle performance gains. An assessment 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, resulted 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 ANDABSTRACT

ON MICROFICHE

ACCESSION NUMBER- A88-10095k TITLE -SYNTHESES OF REDUCED-ORDER CONTROLLERS FOR ACTIVE FLUTTER SUPPRESSION AUTHORS- ATSUSHI FUJlMORl and HlROBUMl OHTA Japan Society for -JOURNAL TITLE Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. 35, no. 402, 1987. p. 353-362. In Japanese, with abstract in English. refs Reduced-order controllers for active flutter suppression of a two-dimensional airfoil are studied using two design approaches. One is based on the generalized Hessenberg representation (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 increased over a specific frequency range. To illustrate and to make a comparison 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 controllers irk the NFA method can be designed with increased stability margin at the expense of the performance index. For all simulation cases, the NFA method yields second-order controllers with a better stability margin than those by the GHR method. Thus, the NFA method provides an effective method for synthesizing robust reduced-order controllers. Author

vii AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 223)

FEBRUARY 1988

01 current, and ultrasonic inspection techniques are used at the center; the advantages of these NDT for detecting surface defects are examined. The use of a preventive (scheduled) maintenance AERONAUTICS (GENERAL) concept to maintain engines and aircraft is discussed. I.F.

A88-13082# DESIGN AND FABRICATION TRIAL OF A COMPOSITE FLAP STRUCTURE A88-10370# KENZO TAKASAKI, NOBUKAZU YANAI, ISAO ISHII, and AN ORIENT EXPRESS TO CAPTURE THE MARKET NAOHITO TSUDA Japan Society for Aeronautical and Space RICHARD DEMEIS Aerospace America (ISSN 0740-722)0, vol. Sciences, Journal (ISSN 0021-4663), vol. 34, no. 394, 1986, p. 25, Sept. 1987, p. 44-47. 614-618. In Japanese. The development of a high-speed aircraft for travel to the Orient The design and fabrication trial of the composite flap structure is discussed. The economic benefits and commercial applications of a medium-size cbmmercial transport aircraft are described. An for an SST are investigated. A number of designs for an SST are integrated fabrication method involving the combination of steel presented and analyzed; fuel, safety, and environmental concerns and rubber components is applied to the construction of the flap are addressed. The National Aerospace Plane and the X-30 project structure. The integrated composite structure results in a lightweight are examined. I.F. and low-cost design as compared with the honeycomb sandwich structure. S.H. A88-10657 NEW SOVIET HELICOPTER TECHNOLOGY AND ITS N88-10003# Deutsche Forschungs- und Versuchsanstalt fuer POTENTIAL FOR INDUSTRIAL USE [NEUE SOWIETISCHE Luft- und Raumfahrt, Goettingen (West Germany). Abteilung HUBSCHRAUBERTECHNIK UND DEREN EINSATZPERSPEKTI- Stabilitaet und Antwort. VEN IM INDUSTRIEFLUG] THE HISTORY OF AEROELASTICITY RESEARCH IN GERMANY EKKEHARD SCHEER (Interflug Gesellschaft fuer Internationalen FROM THE BEGINNING UNTIL 1945 Flugverkehr mbH, Berlin, German Democratic Republic) PETER BUBLITZ Dec. 1986 319 p In GERMAN; ENGLISH Technisch-oekonomische Information der zivilen Luftfahrt (ISSN summary Report will also be annouced as translation 0232-5012), vol. 23, no. 3, 1987, p. 113-116. In German. (ESA-TT-1082) The new Soviet helicopters Ka-32 and Mi-26 are described, (DFVLR-MITT-86-25; ISSN-0176-7739; ETN-87-90444) Avail: and the potential spectrum of their uses in the economy of the NTlS HC A14/MF A01; DFVLR, Cologne, West Germany DM 98 DDR is considered. The configurations, components, and Twenty years elapsed between the beginning of powered flight equipment of these helicopters are described, their particular and the comprehension of such aeroelasticity problems as static advantages are mentioned, and the values of their parameters divergence and flutter. The way in which the first aeroelasticians are listed in comparison with those of the Mi-8. The applications overcame the difficulties and founded this field of research is of the helicopters in the construction of facilities for energy described. ESA generation, harbors and coastal facilities, dams, traffic facilities, coal burning plants, and factory construction and reconstruction N88-10986# Joint Publications Research Service. Arlington, Va. are discussed. C.D. ENSURING THE SERVICE LIFE OF DESIGNS (EXPERIENCE IN AIRCRAFT CONSTRUCTION) A80-10877 A. F SELIKHOV and ZHUKOVSKIY ln its USSR Report: ANTI-TANK HELICOPTERS FOR THE RICH AND NOT SO Engineering and Equipment p 1-11 4 May 1987 Transl. into RICH ENGLISH from Mashinovedeniye (Moscow, USSR), no. 5, Sep.-Oct. MARK LAMBERT lnteravia (ISSN OMO-5168), vol. 42, Sept. 1986 p 11-18 1987, p. 921-923, 925, 926. Avail: NTlS HC AO7IMF A01 Current designs and characteristic features of antitank The high cost of an aircraft makes it necessary to operate it helicopters are discussed. The new and improved capabilities and for 20 to 25 years with ever increasing intensity. Increasing designs of helicopters manufactured by various companies are requirements on weight improvement, a significant level of variable described. Particular consideration is given to the location of sights loads, long service life and large number of functional and loading for launching TOW and HOT missiles, observation sights, and cycles results in the fact that the service life of the main load light antitank helicopters such as the TOW-firing 500MD and the bearing structure of an aircraft is limited, i.e., the design may 406 Combat Scout. I.F. exhaust its load carrying capacity prematurely. The most frequently encountered and most hazardous due to unexpected causes of A88-11672 possible cessation of operation is structural fatigue due to SCHEDULED MAINTENANCE PROGRAM HELPS DELTA exhaustion of its load carrying capacity and initial production defects MAINTAIN QUALITY and also damage caused by corrosion and wear. Criteria are LENA NlRO Materials Evaluation (ISSN 0025-5327), vol. 45, evumerated which place limitations on providing the required Sept. 1987, p. 1054-1056. service life of the design with minimum expenditures of mass. Delta’s quality control program and their Technical Operations The typical distribution of service life of a design before the first Center in Atlanta are described. Magnetic particle, fluorescent damage in operation is shown. The measures which must be penetrant, radiographic isotope, high- and low-frequency eddy implemented during the very beginning of design, during

1 02 AERODYNAMICS manufacture of the aircraft and reliability before beginning of design A88-10300 are briefly discussed. E.R. NECESSARY OPTIMALITY CONDITIONS FOR THREE-DIMEN- SIONAL BODIES IN SUPERSONIC GAS FLOW [NEOBKHODIMYE USLOVllA OPTIMACNOSTI PROSTRANSTVENNYKH TEL V SVERKHZVUKOVOM POTOKE GAZA] I. E. MlKHAlLOV Zhurnal Vychislitel'noi Matematiki ? Matematicheskoi Fiziki (ISSN 0044-4669), vol. 27. July 1987. p. 02 11 1 1-1 1 14. In Russian. The problem of determining the optimal shape of a three-dimensional body in supersonic stationary flow of a gas is AERODYNAMICS analyzed under the assumption that all the flow parameters are continuous in the determinacy region of the body. The necessary Includes aerodynamics of bodies, combinations, wings, rotors, and extreme conditions are derived by using the method of Lagrangian control surfaces; and internal flow in ducts and turbomachinery. multipliers. The solvability of the conjugate boundary value problem is demonstrated. V.L. A88-10093# A NUMERICAL METHOD FOR SUBSONIC UNSTEADY LIFTING A88-10354'# National Aeronautics and Space Administration. SURFACES - BIS. 111 - SOME ADDITIONAL NUMERICAL Ames Research Center, Moffett Field, Calif. RESULTS NAVIER-STOKES SIMULATIONS OF ROTOWSTATOR MASAMI ICHIKAWA and SHlGENORl AND0 Japan Society for INTERACTION USING PATCHED AND OVERLAID GRIDS Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. MAN MOHAN RAI (NASA, Ames Research Center, Moffett Field, 35, no. 402, 1987, p. 339-345. In Japanese, with abstract in CA) (Computational Fluid Dynamics Conference, 7th, Cincinnati, English. refs OH, July 15-17, 1985, Technical Papers, p. 282-298) Journal of This paper presents some additional numerical results to Propulsion and Power (ISSN 0748-4658), vol. 3, Sept.-Oct. 1987, previous papers concerning a new computation method for p. 387-396. Previously cited in issue 19, p. 2743, Accession no. unsteady subsonic lifting surfaces, BIS (box-in-strip). It consists of A85-40952. refs two parts. One is a comparison between BIS and PCKFM (piecewise continuous kernel-function method); the other is a comparison between BIS and analytical solutions for circular and/or A88-10355'# National Aeronautics and Space Administration. elliptic planform wings in steady incompressible flow. As a result, Lewis Research Center, Cleveland, Ohio. it is found that PCKFM yields fairly close results to BIS in the EXPLICIT MULTIGRID ALGORITHM FOR QUASI-THREE-DIMEN- case of the rectangular wing with AR = 10 and that correlation SIONAL VISCOUS FLOWS IN TURBOMACHINERY between BIS and analytical solutions is much better than in the RODRICK V. CHlMA (NASA, Lewis Research Center, Cleveland, case of VLM. Author OH) Journal of Propulsion and Power (ISSN 0748-4658). vol. 3, Sept.-Oct. 1987, p. 397-405. Previously cited in issue 07, p. 828, Accession no. A86-19644. refs A88- 10094# THE FLOW VISUALIZATION ON THE ROTARY WING WITH A88-10356# LOW ASPECT RATIO CASCADE VISCOUS FLOW ANALYSIS USING THE TADAHARU WATANUKI, MASAYOSHI MATSUZAKA, HlROTOSHl NAVIER-STOKES EQUATIONS KUBOTA, KOJIRO SUZUKI, KOUlCHl SAGAWA et al. Japan ROGER L. DAVIS, RON-HO NI, and JAMES E. CARTER (United Society for Aeronautical and Space Sciences, Journal (ISSN Technologies Corp., East Hattford, CT) Journal of Propulsion 0021-4663), vol. 35, no. 402, 1987, p. 346-352. In Japanese, with and Power (ISSN 0748-4658), vol. 3, Sept.-Oct. 1987, p. 406-414. abstract in English. refs Research supported by the United Technologies Corp. Previously Flow patterns on a rotary wing with a low aspect ratio of 3.3 cited in issue 07. p. 828. Accession no. A86-19645. refs are experimentally investigated in the Goettingen type low speed wind tunnel. Single rotation propeller blade with a radius of 0.3 m A88- 10357# is used as the model wing for the flow visualization. The flow CALCULATION OF THREE-DIMENSIONAL VISCOUS FLOWS IN phenomena on the blade are visualized by means of oil flow, tuft, TURBOMACHINERY WITH AN IMPLICIT RELAXATION mini-tuft, and china clay methods and recorded by simultaneous METHOD photography. The experimental results clearly show that the C. HAH (General Electric Co., Schenectady, NY) Journal of mini-tuft method is more suitable for visualizing the flow on the Propulsion and Power (ISSN 0748-4658), vol. 3, Sept.-Oct. 1987, rotary wing. Author p. 415-422. Previously cited in issue 11, p. 1475, Accession no. A86-26649. refs

A88-10264 A88-10359# SUPERSONIC FLOW AROUND A SPHERE IN A THERMAL NUMERICAL SOLUTIONS OF SCRAMJET NOZZLE FLOWS INHOMOGENEITY [SVERKHZVUKOVOE OBTEKANIE SFERY V J. A. SCHETZ, F. S. BILLIG, and S. FAWN (Johns Hopkins TEPLOVOI NEODNORODNOSTI] University, Laurel, MD) Journal of Propulsion and Power (ISSN V. P. GOLOVIZNIN, G. I. MISHIN, IU. L. SEROV, and I. P. IAVOR 0748-4658), vol. 3, Sept.-Oct. 1987, p. 440-447. Navy-supported (AN SSSR, Fiziko-Tekhnicheskii Institut, Leningrad, USSR) Zhurnal research. Previously cited in issue 18, p. 2610, Accession no. Tekhnicheskoi Fiziki (ISSN 0044-4642), vol. 57, July 1987, p. A85-39689. refs 1433-1435. In Russian. refs The dynamics of flow around spherical models in air in the A88-10361'# Science Applications InternationalCorp., Princeton, presence of a temperature gradient was investigated experimentally N.J. at a ballistic testing facility using an instrument with a 15-ns laser PARABOLIZED NAVIER-STOKES ANALYSIS OF DUCTED source to photograph the flow patterns. Flow patterns are SUPERSONIC COMBUSTION PROBLEMS presented for a 20-mm-diameter polished duralumin ball moving N. SINHA and S. M. DASH (Science Applications International at a speed of 1.98 km/s through heated air. It is found that the Corp.. Princeton, NJ) Journal of Propulsion and Power (ISSN experimentally observed separation of the head shock wave from 0748-4658), vol. 3, Sept.-Oct. 1987, p. 455-464. Previously cited the model, Delta/R, differs substantially from the expected values, in issue 07, p. 828, Accession no. A86-19628. refs which is attributed to the nonsteady nature of the flow. V.L. (Contract NAS1-16535)

2 02 AERODYNAMICS

A88-10492’ National Aeronautics and Space Administration. A88-10660 Langley Research Center, Hampton, Va. ARBITRARY WINGS OF LOW ASPECT RATIO IN SUBSONIC PRESSURE FIELD DUE TO DRAG REDUCING OUTER LAYER FLOW DEVICES IN TURBULENT BOUNDARY LAYERS LAZAR DRAGOS (Bucuresti, Universitatea, Bucharest, Rumania) P. R. BANDYOPADHYAY and R. D. WATSON (NASA, Langley Zeitschrift fuer angewandte Mathematik und Physik (ISSN Research Center, Hampton, VA) Experiments in Fluids (ISSN 0044-2275), vol. 38, July 1987, p. 648-652. refs 0723-4864), vol. 5, no. 6, 1987, p. 393-400. refs The study of the theory of wings of low aspect ratio in (Contract NASI-17296) incompressible fluids, or compressible subsonic flow, is expanded The wall static pressure in the vicinity of drag reducing outer to include the case of wings of arbitrary planform. Explicit formulas layer devices in flat wall turbulent boundary layers has been for the calculation of the lift and moment coefficients are derived measured and compared with an inviscid theory. Symmetric and for wings of arbitrary planform. The fundamental formulas for the cambered airfoil devices have been examined at small angles of lift and moment coefficients are obtained using Green’s formula. attack and very low chord Reynolds numbers. Airfoil devices impose R.R. a sequence of strong favorable and adverse pressure gradients on the boundary layer whose drag is to be reduced. At very small angles of attack (+ or - 2 deg), this pressure field extends up to about three chord lengths downstream of the trailing edge of an airfoil device. Also examined are the pressures on the upper and A88-10983# lower surfaces of a symmetric airfoil device in the freestream and NUMERICAL SOLUTION OF STREAM FUNCTION EQUATIONS near the wall. The freestream pressure distribution around an airfoil IN TRANSONIC FLOWS section is altered by the wall proximity. The relevance of lift J. Z. XU, W. Y. NI, and J. Y. DU (Chinese Academy of Sciences, enhancement caused by wall proximity to drag reduction has been Institute of Engineering Thermophysics, Beijing, People’s Republic discussed. The pressure distributions on the flat wall beneath the of China) ASME, International Gas Turbine Conference and symmetric airfoil devices are predicted well by the inviscid theory. Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 5 p. refs However, the remaining pressure distributions are predicted only (ASME PAPER 87-GT-18) qualitatively, presumably because of strong viscous effects. In order to develop the transonic stream function approach, Author one of the momentum equations is employed to form the principal equation of the stream function which does not contain the terms of the vorticity and the entropy, and the other one is used to calculate the density directly. Since the density is uniquely determined, the problem that the density is a double-valued function A88-10498*# California Univ., Berkeley. of mass flux in the stream function formulation disappears and EXPERIMENTAL STUDY OF THREE-DIMENSIONAL SEPARATED the entropy increase across the shock is naturally included. The FLOW SURROUNDING A HEMISPHERE-CYLINDER AT INCI- numerical results for the transonic cascade flow show that the DENCE shock obtained from the present method is slightly weaker. It is ANDREW J. MEADE, JR. (California, University, Berkeley) and placed further downstream compared to the irrotational stream LEWIS B. SCHIFF (NASA, Ames Research Center, Moffett Field, function calculation, and is closer to the experimental data. CA) AIAA, Atmospheric Flight Mechanics Conference, Monterey, Author CA, Aug. 17-19, 1987. 14 p. refs (AIAA PAPER 87-2492) Detailed experimental surface pressure coefficient measurements, obtained for a hemisphere-cylinder-flaremodel in a low supersonic flow (freestream M = 1.2) at various angles of attack (0 deg to 27.5 deg), have been analyzed. The pressure A88-10989# values for each angle of attack were smoothed and checked against A SIMPLIFIED METHOD FOR 3-0 POTENTIAL FLOW IN their respective oil-flow photographs. The smoothed results were TURBOMACHINERY USING VORTEX SHEET BOUNDARY then used to validate a theory which relates the number and type CONDITIONS of singular points observed in the oil-flow patterns with local H. JIANG, R. CAI, and Y. ZHU (Chinese Academy of Sciences, surface-pressureextrema. Author Institute of Engineering Thermophysics, Beijing, People’s Republic of China) ASME, International Gas Turbine Conference and Exhibition, 32nd. Anaheim, CA, May 31-June 4, 1987. 7 p. Research supported by the Chinese Academy of Sciences. refs (ASME PAPER 87-GT-28) A88-10562# Within the framework of inviscid flow theory, the character of MULTIGRID LOCALIZATION AND MULTIGRID GRID three-dimensional flow in turbomachinery blade row is discussed. GENERATION FOR THE COMPUTATION OF VORTEX One of the important differences between three-dimensional and STRUCTURES AND DYNAMICS OF FLOWS IN CAVITIES AND two-dimensional flow in turbomachinery is the discontinuity of ABOUT AIRFOILS velocity at the two sides of the trailing edge and across the KARL GUSTAFSON and ROBERT LEBEN (Colorado, University, downstream boundary. The inconsistency of the traditional Boulder) University of Colorado and USAF, Copper Mountain periodicity conditions for the downstream boundary and of the Conference on Multigrid Methods, 3rd, Copper Mountain, CO, Apr. axisymmetric assumption for the outlet flow with the 6-10, 1987, Paper. 15 p. refs three-dimensionality of turbomachinery flow is discussed also. For A robust multigrid nested subdomain scheme is applied to a three-dimensional potential flow, the vortex sheet boundary Stokes flow in a unit cavity, and the resolution of 25 corner conditions (VSSC) for the downstream boundary and a fully subvortices is reported. The algorithm is shown to be competitive three-dimensional condition for outlet flow are presented. A with a near optimum AD1 technique, and it is applied to the infinite simplified method is developed by implementation of VSBC on a airfoil domain problem. Results are then presented for full unsteady fixed vortex boundary in order to predict the fully three-dimensional Navier-Stokes flow about an NACA 0015 airfoil. The solution flow in blade passage as well as downstream of blade row. In the procedure consists of using the multigrid solver for the stream present investigation two calculations are carried out. In one function computations, using an AD1 scheme to advance the calculation the traditional boundary conditions are imposed while vorticity values in time, and using the multigrid grid generation in another one, the VSBC are used to demonstrate the capability technique to provide the boundary-fitted coordinates. Good of the newly developed boundary conditions. The agreement resolution of fine vortical detail and temporal correlation between between some calculated results and the theoretical analysis is the experimental and numerical studies are noted. R.R. very good. Author

3 02 AERODYNAMICS

A88-10990# steady, two-dimensional, transonic turbine cascade flows. The A GENERALIZED NUMERICAL METHOD FOR SOLVING DIRECT method is applied to the strong conservation form of the unsteady INVERSE AND HYBRID PROBLEMS OF BLADE CASCADE Navier-Stokesequations written in arbitrary curvilinear coordinates. FLOW BY USING STREAMLINEGO-ORDINATE EQUATION Cascade flow solutions are obtained on an orthogonal, NAI-XING CHEN and FENG-XIAN ZHANG (Chinese Academy of body-conforming ’0 grid with the standard k-epsilon turbulence Sciences, Institute of Engineering Thermophysics, Beijing. People’s model. Author Republic of China) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 5 p. refs A88-11015# (ASME PAPER 87-GT-29) THE DESIGN OF SHOCK-FREE COMPRESSOR CASCADES This paper describes a generalized numerical method for solving INCLUDING VISCOUS BOUNDARY LAYER EFFECTS direct, inverse and hybrid aerodynamic problems of the blade AHMED A. HASSAN (Arizona State University, Tempe) ASME, cascade flow on the stream surface of revolution. The International Gas Turbine Conference and Exhibition, 32nd, computational method is based on the numerical solution of the Anaheim, CA, May 31-June 4, 1987. 10 p. refs streamline coordinate equation by a linear relaxation scheme. Two (ASME PAPER 87-GT-71) conventional blade cascades and a tandem blade have been A numerical procedure for the design of shock-free transonic calculated by the present method. Author compressor cascades is proposed, taking viscous effects into account and assuming that the boundary layer is fully attached A88-10991# over the blade. A modified inviscid hodograph-based inverse-design A NEW METHOD OF CALCULATING OPTIMUM VELOCITY algorithm and an inverse boundary layer algorithm (Miner et al., DISTRIBUTION ALONG THE BLADE SURFACE ON ARBITRARY 1971) are iteratively combined. The present method decouples STREAM SURFACE OF REVOLUTION IN TURBOMACHINES the inviscid subsonic and supersonic regions of the flow, allowing ZlXlANG ZOU and DING YUAN (Chinese Academy of Sciences, the solution of either an elliptic or hyperbolic-type partial differential Institute of Engineering Thermophysics, Beijing, People’s Republic equation for the full stream function. The procedure is demonstrated of China) ASME, International Gas Turbine Conference and with two examples of shock-free compressor blades. R.R. Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 5 p. refs (ASME PAPER 87-GT-30) A method for calculating the optimum velocity distribution along the blade surface in a two-dimensional incompressible flow is A88-11022# described. This method is based on the theory of boundary layer THREE-DIMENSIONAL CALCULATION OF WALL BOUNDARY and the calculation of cascade loss, and it employs the Pontijagin LAYER FLOWS IN TURBOMACHINES maximum principle and new optimum techniques. The physical W. L. LINDSAY (Pratt and Whitney, Quebec, Canada), H. 6. model and equations used in the calculation are presented. The CARRICK (Impetrial Chemical Industries, PLC, Middlesbrough, procedure involves initially calculating the incompressible steady England), and J. H. HORLOCK (Open University, Milton Keynes, flow and then extending it to that of the imcompressible flow on England) ASME, International Gas Turbine Conference and an arbitrary surface of revolution. This method is also applicable Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 10 p. refs to the optimum design of two-dimensional compressor blades and (ASME PAPER 87-GT-82) long thin revolutionary bodies of axial symmetry. I.F. An integral method is used to calculate the three-dimensional turbulent boundary layer development through the blade rows of A88-11003# turbomachines. Simultaneous equations are solved for the growth THROUGH-FLOW ANALYSIS OF A MULTI-STAGE of streamwise and cross-flow momentum thicknesses, entrainment, COMPRESSOR OPERATING AT NEAR-STALL CONDITIONS the wall shear stress, and the position of maximum cross-flow. ROBERT P. DRlNG and DAVID H. JOSLYN (United Technologies The method is shown to predict flows very successfully for lightly Research Center, East Hartford, CT) ASME, International Gas loaded compressor blading (the experiments of Horlock, 1963, Turbine Conference and Exhibition, 32nd, Anaheim, CA, May but less successfully for a highly loaded compressor cascade (the 31-June 4,1987.10 p. Research supported by United Technologies experiments of Lindsay, 1974). In general, the method was found Corp. refs to overestimate the secondary or cross-flow observed in the highly (Contract NO0014-85-C-0657) loaded turbine blades of the Carrick (1975) experiments. R.R. (ASME PAPER 87-GT-51) An assessment of through-flow theory was undertaken based on detailed measurements obtained in a large-scale rotating compressor rig. This assessment is focused specifically on the A88-11024# compressor aerodynamics at near-stall conditions since the NUMERICAL SOLUTION OFTHREE-DIMENSIONALTURBULENT three-dimensionality of the flow is at its worst under these FLOWS FOR MODERN GAS TURBINE COMPONENTS circumstances, and the assumptions of axisyrnmetry in the theory C. HAH (General Electric Co., Schenectady, NY) and J. H. LEYLEK are tested far more severely than at design conditions. This (General Electric Co., Aircraft Engine Business Group, Cincinnati, assessment demonstrates that a reasonably accurate prediction OH) ASME, International Gas Turbine Conference and Exhibition, can be achieved but that major discrepancies can occur near the 32nd, Anaheim, CA, May 31-June 4, 1987. 8 p. refs endwalls where blockage is high. It is also demonstrated that (ASME PAPER 87-GT-84) large errors can be incurred when the spanwise description of This paper describes the development and assessment of a blockage is inaccurate in its detailed distribution or in its level. computer code for three-dimensional compressible turbulent flows Author in modern gas turbine components. The code is based on a high-order upwinding relaxation scheme with fully conservative A88-11005# control volume. A three-dimensional Reynolds-averaged NAVIER-STOKES SOLUTION FOR STEADY TWO-DIMENSIONAL Navier-Stokes equation is solved with a two-equation turbulence TRANSONIC CASCADE FLOWS model that has a low Reynolds number modification near the 0. KEY KWON (General Motors Cop, Allison Gas Turbine Div., solid wall. The code is applied to the study of compressible flow Indianapolis, IN) ASME, International Gas Turbine Conference inside turbine blade rows of modern gas turbines. Measured data and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 8 p. and calculations are carefully compared for the production and refs convection of aerodynamic loss to evaluate the code as an (ASME PAPER 87-GT-54) advanced design technique. The predicted aerodynamic A robust, time-marching Navier-Stokes solution procedure based performance is further compared with predictions based on current on the explicit hopscotch method is presented for the solution of design techniques. Author

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A88-11035# A88-11046# EXPERIMENTAL INVESTIGATIONS OF FLOWS THROUGH A A TRACE GAS TECHNIQUE TO STUDY MIXING IN A TURBINE PLANE CASCADE AT LARGE ANGLES OF ATTACK WITH STAGE SEPARATIONS H. D. JOSLYN and R. P. DRlNG (United Technologies Research CHUAN-GANG GU, LAI-QIN LUO, and YONG-MIA0 MIA0 (Xian Center, East Hartford, CT) ASME, International Gas Turbine Jiaotong University, People’s Republic of China) ASME, Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, International Gas Turbine Conference and Exhibition, 32nd. 1987. 8 p. refs Anaheim, CA, May 31-June 4, 1987. 7 p. refs (ASME PAPER 87-GT-118) (ASME PAPER 87-GT-96) An experimental technique to study mixing in a turbine stage Measurements of various parameters in the flows through a is demonstrated. An axisymmetric, radial temperature profile at cascade at different angles of attack have been performed. The the inlet to the first stator of a large-scale, low-speed, single-stage, parameters, such as Reynolds stresses, pressure distribution on axial flow turbine model is simulated with a radial trace gas the blade surface, velocity distribution in the blade passage, and concentration distribution. Mixing or redistribution of the inlet profile the position of the separation point are measured at a large angle by three-dimensional aerodynamic mechanisms is determined from of attack with separations. In addition, the development of the trace gas concentration measurements made in both the stationary wake is also investigated. A new formula with a second order of and rotating frames of reference at various locations through the accuracy has been developed to analyze the signals of hot wire turbine. The trace gas concentration contours generated are in flows with high turbulence intensity. The data by a hot wire are consistent with flow pitch angle measurements made downstream compared with those by conventional measurement techniques of the first stator and with surface flow visualization on the rotor and by flow visualizations. The results are satisfactory. Author airfoil and the hub endwall. It is demonstrated that this trace gas technique is well suited to quantify many aspects of the redistribution and diffusion of an inlet temperature profile as it is convected through a turbine stage. Author

A88-11043# A88-11067# SHOCK EMBEDDING DISCONTINUOUS SOLUTION OF A DISCUSSION OF THE MEAN S2 STREAM SURFACES ELLIPTIC EQUATION FOR INVERSE PROBLEM OF TRANSONIC APPLIED TO QUASI-THREE-DIMENSIONAL CALCULATION S2 FLOW PROGRAMS FOR TURBOMACHINERY DESIGN HONGJI CHEN and CHUNG-HUA WU (Chinese Academy of XUJIN ZHU and ZHONGQI WANG (Harbin Institute of Technology, Sciences, Institute of Engineering Thermophysics. Beijing, People’s People’s Republic of China) ASME, International Gas Turbine Republic of China) ASME, International Gas Turbine Conference Conference and Exhibition, 32nd. Anaheim, CA, May 31-June 4, and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 8 p. 1987. 11 p. refs refs (ASME PAPER 87-GT-150) (ASME PAPER 87-GT-115) Various definitions of the S2m surfaces applied to A simple, accurate and reliable computer code, using a quasi-three-dimensional flow calculations in turbomachinery design conservative form of the stream-function principal equation and are clarified, and an extended version of the true S2 stream surface, embedding the shock relations into the principal equation, has the pitch-averaged generalized S2 (PAG S2) stream surface, is been programmed in order to calculate the transonic flow over considered. The governing equations for PAG S2 are derived the whole S2 surface containing the discontinuity of a passage through introducing nonorthogonal curvilinear coordinates and shock. The program has application to the solution of the nonorthogonal velocity components into the pitch-averaged three-dimensional transonic flow in a fan or compressor through equations. It is demonstrated that PAG S2 is a more universally iterative computation of transonic S1 and S2 flows. The method applicable model for solving the pitch-averaged flow properties of is used to calculate the S2 flow in a typical transonic rotor. R.R. turbine blade passage flow. Neither S2m nor quasi-S2m (an imperfect version of PAG S2) are predicted to give correct mean solutions of the flow-through. R.R.

A88-11044# A88-11071# OFF-DESIGN PERFORMANCE OF SUPERSONIC COMPRES- NUMERICAL COMPUTATION OF NON-ISENTROPIC POTENTIAL SORS WITH FIXED AND VARIABLE GEOMETRY EQUATIONS FOR TRANSONIC CASCADE FLOWS K.-D. BROICHHAUSEN (MTU Motoren- und Turbinen-Union J. 2. XU, J. Y. DU, and W. Y. NI (Chinese Academy of Sciences, Muenchen GmbH, Munich, Federal Republic of Germany), H. E. Institute of Engineering Thermophysics, Beijing, People’s Republic GALLUS, and R. MOENIG (Aachen, Rheinisch-Westfaelische of China) ASME, International Gas Turbine Conference and Technische Hochschule, Federal Republic of Germany) ASME, Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987.6 p. Research International Gas Turbine Conference and Exhibition, 32nd, supported by the Chinese Academy of Sciences and Gas Turbine Anaheim, CA, May 31-June 4, 1987. 14 p. DFG-supported Establishment of China. refs research. refs (ASME PAPER 87-GT-159) (ASME PAPER 87-GT-116) Based on the analysis of the momentum equations and the The blading and flow path geometry of supersonic axial flow nonisentropic flow, an ’isentropic density’, which is computed compressors employing combinations of characteristic rotors and according to the isentropic relation and is dependent on the stators with fixed and variable geometry is investigated. For the temperature only, is separated from the density. The entropy supersonic compressor stages presently investigated, it is shown increase across the shock may be directly calculated from the that the three-dimensional passage geometry has an important momentum equations in the divergence form. Iterating it with the influence on the off -design performance. Semiempirical models classical potential equation may solve the nonisentropic transonic are obtained that numerically describe flow phenomena including flowfield conveniently. It is seen from the calculations of transonic the shock-wall, profile-wall, and end-wall boundary layer losses. cascade flow on the surface of revolution that the shock in the These models are incorporated into a streamline curvature nonisentropic calculation is weaker and is located further upstream calculation method in order to provide information regarding the compared to the classical potential solution, and is in agreement off-design performance. R.R. with the experimental results. Author

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A88-11072*# National Aeronautics and Space Administration. equations of motion are combined into a single elliptic second-order Lewis Research Center, Cleveland, Ohio. partial differential equation of the streamline field; this equation is APPLICATION OF ADVANCED COMPUTATIONAL CODES IN referred to as the unified equation of motion (UEM). The UEM is THE DESIGN OF AN EXPERIMENT FOR A SUPERSONIC used to trace streamline positions. Then, the velocity field is THROUGHFLOW FAN ROTOR determined by differentiating the stream function field and the use JERRY R. WOOD, JAMES F. SCHMIDT, RONALD J. STEINKE. of the computed streamlines. The method was applied to obtain RODRICK V. CHIMA, and WILLIAM G. KUNIK (NASA, Lewis incompressible blade-to-bladeflow solutions for S1 turbornachinery, Research Center, Cleveland, OH) ASME, International Gas and the results are compared with experimental data and with Turbine Conference and Exhibition, 32nd. Anaheim, CA, May results of other numerical methods. IS. 31-June 4. 1987. 15 p. Previously announced in STAR as N87-22630. refs (ASME PAPER 87-GT-160) Increased emphasis on sustained supersonic or hypersonic cruise has revived interest in the supersonic throughflow fan as a A88-11088# possible component in advanced propulsion systems. Use of a A MULTI-GRID ALGORITHM FOR 2-D TRANSONIC POTENTIAL fan that can operate with a supersonic inlet axial Mach number is CASCADE FLOW attractive from the standpoint of reducing the inlet losses incurred WE1 JI, HONGDE JIANG, and RUlXlAN CAI (Chinese Academy of in diffusing the flow from a supersonic flight Mach number to a Sciences, Institute of Engineering Thermophysics, Beijing, People’s subsonic one at the fan face. The design of the experiment using Republic of China) ASME, International Gas Turbine Conference advanced computational codes to calculate the components and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 6 p. required is described. The rotor was designed using existing refs turbomachinery design and analysis codes modified to handle fully (ASME PAPER 87-GT-180) supersonic axial flow through the rotor. A two-dimensional A fast effective multigrid algorithm for calculating axisymmetric throughflow design code plus a blade element code two-dimensional transonic cascade flow governed by full-potential were used to generate fan rotor velocity diagrams and blade equations is presented in this paper. Numerical results obtained shapes. A quasi-three-dimensional, thin shear layer Navier-Stokes show the powerful effect of the method in both accelerating code was used to assess the performance of the fan rotor blade convergence and improving accuracy. In addition, according to shapes. The final design was stacked and checked for the conservation of potential equations, a reasonable treatment three-dimensional effects using a three-dimensional Euler code for cascade-leading-edge calculations in H-type grids is also interactively coupled with a two-dimensional boundary layer code. presented. The nozzle design in the expansion region was analyzed with a three-dimensional parabolized viscous code which corroborated the results from the Euler code. A translating supersonic diffuser was designed using these same codes. Author A88-1109 1# A88-11077# ANALYSIS OF WINDAGE LOSSES AND VELOCITY CHARACTERIZATION OF SHOCK WAVE END WALL DISTRIBUTION FOR A SHROUDED ROTATING DISK BOUNDARY LAYER INTERACTIONS IN A TRANSONIC W. GAERTNER (Muenchen, Technische Universitaet, Munich, COMPRESSOR ROTOR Federal Republic of Germany) ASME, International Gas Turbine 0. C. RABE, A. J. WENNERSTROM (USAF. Aero Propulsion Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, Laboratory, Wright-Patterson AFB, OH), and W. F. OBRIEN, JR. 1987. 7 p. (Virginia Polytechnic Institute and State University, Blacksburg) (ASME PAPER 87-GT-186) ASME, International Gas Turbine Conference and Exhibition, 32nd, An analysis of experimental results was carried out, establishing Anaheim, CA, May 31-June 4, 1987. 8 p. refs a direct correlation between measured velocity profiles and windage (ASME PAPER 87-GT-166) losses for a rotating disk inside a shrouded stator as typically The passage shock wave end wall boundary layer interaction found in turbomachinery. The analysis gives information on the in a transonic compressor was investigated with a laser transit regions of the rotating and static parts, which have a dominant anemometer. The transonic compressor used in this investigation effect upon disk windage. Author was developed by the General Electric Company under contract to the Air Force. The compressor testing was conducted in the Compressor Research Facility at Wright-Patterson Air Force Base, Ohio. Laser measurements were made in two blade passages at seven axial locations from 10 percent of the axial blade chord in A88-11096# front of the leading edge to 30 percent of the axial blade chord STABILITY OF CONICAL AND CURVED ANNULAR DIFFUSERS into the blade passage. At three of these axial locations, laser FOR MIXED-FLOW COMPRESSORS traverses were taken at different radial immersions. A total of A. ABlR (Research Products, Rehovot, Israel) and A. WHITFIELD twenty-seven different locations were traversed circumferentially. (Bath, University, England) ASME, International Gas Turbine The measurements reveal that the end wall boundary layer in this Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, region is separated from the core flow by what appears to be a 1987. 7 p. refs shear layer where the passage shock wave and all ordered flow (ASME PAPER 87-GT-191) seem to end abruptly. Author The internal flow structures for two curved diffusers, a straight conical diffuser, and a straight radial annular diffuser were A88-11087# measured using a two channel hot wire anemometry system and UNIFIED EQUATION OF MOTION (UEM) APPROACH AS a five hole pitot static tube. The experimental test facility was APPLIED TO S1 TURBOMACHINERY PROBLEMS composed of two axial flow fans that supplied air to the diffusers S. ABDALLAH, C. F. SMITH, and M. W. MCBRIDE (Pennsylvania via a rotating screen arrangement. All the diffusers tested had an State University, State College) ASME, International Gas Turbine inlet width of 56 mm and inlet and discharge radii of 300 mm and Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 508 mm, respectively. Profiles of the flow throughout the diffusers 1987. 7 p. refs are analyzed. It is observed that the straight annular diffuser is (Contract N00024-794-6043; N00024-85-C-6041) the least stable and the radial annular diffuser exhibits the best (ASME PAPER 87-GT-179) suitability characteristics. It is detected that the flow stability of A simple approach is developed for the solution of inviscid the two curved diffusers can be improved by reducing the passage blade-to-blade flow in turbomachines. In this approach the width. I.F.

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A88-11097# found with a steady potential flow solution. The quasi-steady FLOW INVESTIGATIONSON SWIRLING COMPRESSIBLE FLOW response was found to be in fair agreement with the in-phase THROUGH A VANELESS RADIAL DIFFUSER part of the measured unsteady response for the lowest oscillation D. P. AGRAWAL, S. M. YAHYA, and D. N. REDDY (Indian Institute frequency, with progressively worse agreement of the in-phase of Technology, New Delhi, India) ASME, International Gas Turbine part for higher frequencies. Data acquired under oscillatory Conference and Exhibition, 32nd. Anaheim, CA, May 31-June 4. conditions agreed with linearized unsteady potential flow predictions 1987. 8 p. refs over most of the entire chord for low to moderate incidence, and (ASME PAPER 87-GT-193) agreement between theory and experiment was better at higher The present study deals with the experimental investigation of frequencies. R.R. swirling compressible flow through a parallel walled vaneless radial diffuser. A swirl generator of vortex-nozzle type is used for supplying A88-11121*# National Aeronautics and Space Administration. swirling compressible flow at the diffuser inlet. The desired flow Lewis Research Center, Cleveland, Ohio. angles are achieved by adjusting inlet swirl-vane angles from 2.5 A METHOD FOR CALCULATING TURBULENT BOUNDARY to 12.5 deg. The results are presented in terms of performance LAYERS AND LOSSES IN THE FLOW CHANNELS OF parameters such as pressure recovery and loss coefficient for TURBOMACHINES various diffuser inlet Mach numbers from 0.3 to 0.8 and flow-angle LAWRENCE F. SCHUMANN (NASA, Lewis Research Center; US. range from 20 to 35 deg. Author Army, Propulsion Directorate, Cleveland, OH) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May A88-11101# 31-June 4, 1987. 10 p. Previously announced in STAR as MODELLING THE UNSTEADY FLOW IN A TURBINE ROTOR N87-15944. refs PASSAGE (ASME PAPER 87-GT-225) D. J. DOORLY (University College, London, England) ASME, An interactive inviscid core flow-boundary layer method is International Gas Turbine Conference and Exhibition, 32nd, presented for the calculation of turbomachine channel flows. For Anaheim, CA, May 31June 4, 1987. 12 p. Research supported by this method, a one-dimensional inviscid core flow is assumed. Rolls-Royce, PLC and SERC. refs The end-wall and blade surface boundary layers are calculated (ASME PAPER 87-GT-197) using an integral entrainment method. The boundary layers are The effects of the wakes shed by an upstream blade row in assumed to be collateral and thus are two-dimensional. The forcing the transition of an otherwise laminar rotor blade boundary boundary layer equations are written in a streamline coordinate layer are well recognized. Previous experiments have demonstrated system. The streamwise velocity profiles are approximated by that the forced transition of the laminar boundary layer may greatly power law profiles. Compressibility is accounted for in the influence the surface heat flux. The effect of the wakes on the streamwise direction but not in the normal direction. Equations surface heat flux when the undisturbed boundary layer is already are derived for the special cases of conical and two-dimensional turbulent have been studied using an experimental simulation rectangular diffusers. For these cases, the assumptions of a technique. The results have been analyzed with a view to one-dimensional core flow and collateral boundary layers are valid. establishing how well the effects of the wakes can be described Results using the method are compared with experiment and good by a model which treats only their turbulence content. The effects quantitative agreement is obtained. Author of wake-passing at a reduced Reynolds number are also reported. Author A88-11125# A88-11106# CALCULATION OF A THREE-DIMENSIONAL TURBOMACHINERY THE BASE PRESSURE AND LOSS OF A FAMILY OF FOUR ROTOR FLOW WITH A NAVIER-STOKES CODE TURBINE BLADES MATTHEW J. WARFIELD and B. LAKSHMINARAYANA L. XU and J. D. DENTON (Cambridge University, England) ASiiE, (Pennsylvania State University, University Park) ASME, International Gas Turbine Conference and Exhibition, 32nd, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 11 p. Research supported by Anaheim, CA, May 31-June 4, 1987. 10 p. Navy-supported the Royal Aircraft Establishment. refs research. refs (ASME PAPER 87-GT-202) (ASME PAPER 87-GT-232) Measurements of the effect of trailing edge geometry on the The paper deals with a numerical solution of the full base pressure and loss of a family of four turbine cascades are Navier-Stokes equations governing the flowfield in a turbomachinery presented. The measurements were made in the transonic range rotor. A two-equation turbulence model (k-epsilon) coupled with a of Mach number from 0.8 to 1.2. It is found that, for blades with vectorial eddy viscosity model based on an algebraic Reynolds typical trailing edge thickness,the trailing edge loss is the major stress model is used to account for the anisotropic effects of source of profile loss at these speeds and that the base pressure rotation and three dimensionality. The predicted blade to blade plays a dominant role in determining the loss. For blades with profiles of velocity at various radial locations as well as the thick trailing edges an accurate prediction of base pressure is streamwise velocity profiles in the blade boundary layer show good crucial to loss prediction. However, it is found that current methods agreement with experimental data. Author of base pressure prediction are unable to give reliable prediction. Author A8&11126'# Pratt and Whitney Aircraft, East Hartford, Conn. INTER AND INTRA BLADE ROW LASER VELOCIMETRY A88-11118# STUDIES OF GAS TURBINE COMPRESSOR FLOWS UNSTEADY AERODYNAMIC MEASUREMENTS ON A ROTATING M. CARLSON WILLIAMS (Pratt and Whitney, East Hartford, CT) COMPRESSOR BLADE ROW AT LOW MACH NUMBER ASME, International Gas Turbine Conference and Exhibition, 32nd, L. W. HARDIN, R. 0. CARTA, and J. M. VERDON (United Anaheim, CA, May 31-June 4, 1987. 10 p. Technologies Research Center, East Hartford, CT) ASME, (Contract NAS3-20646) International Gas Turbine Conference and Exhibition, 32nd, (ASME PAPER 87-GT-235) Anaheim, CA, May 31-June 4, 1987. 12 p. refs The use of a two-component LDV to study the flow within gas (Contract F49620-81-C-0088) turbine intrablade passages and air flow through multistage (ASME PAPER 87-GT-221) compressor rigs is investigated. The LDV, multistage compressor, A heavily instrumented blade row rotating in a realistic and the data acquisition system employed in the experiments are compressor model is experimentally investigated to study the described. The velocity magnitude and air angle as a function of unsteady response of a blade row to a prescribed oscillation. rotor position were mapped; modulations in the multistage Data obtained for steady state conditions agreed with previous compressor data resulted in the application of spectral analysis pneumatic data at all flow conditions, and agreement was also techniques to identify and characterize the periodic fluctuations. It

7 02 AERODYNAMICS is noted that the two-component LDV is applicable to the leaves the wall. The e exp n transition prediction method is characterization of the aerodynamics of flows. I.F. extended to separated flows. It is shown that a simple bursting criterion is provided by Stratfords limiting pressure distribution for A88-11136# a zero skin friction turbulent boundary layer. A universal description THEORETICAL AND EXPERIMENTAL ANALYSIS OF A of the laminar part of the bubble is proposed, resulting in a simple COMPRESSOR CASCADE AT SUPERCRITICAL FLOW bubble prediction method. The effect of tripping devices to decrease CONDITIONS the adverse effect of the bubble on drag is discussed. The final chapter presents some results of low Reynolds number airfoil A. WEBER.-~~ M. FADEN. H. STARKEN. and V. JAWTUSCH IDFVLR. lnstitut fuer Antriebstechnik, Cologne, Federal Republic of designs and tests. Author Germany) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA. May 31-June 4, 1987. 11 p. A88-11178 Research sponsored by the Arbeitsgemeinschaft lndustrieller ON MASSIVE LAMINAR SEPARATION AND LIFT ANOMALIES Forschungsvereinigungen. refs IN SUBCRITICAL RE-RANGE (ASME PAPER 87-GT-256) H. K. CHENG, ED. (Southern California, University, Los Angeles, Theoretical and experimental results for profile Mach number CA) IN: Aerodynamics at low Reynolds numbers Re greater distribution, loss behavior, and exit flow angle have been compared than 10 to the 4th and less than 10 to the 6th; Proceedings of for a compressed rotor cascade at M1 = 0.85. A two-dimensional the International Conference, London, England, Oct. 15-18, 1986. finite element method and McNally’s (1 970) integral boundary layer Volume 1 . London, Royal Aeronautical Society, 1986, p. 2.1-2.41. method are coupled iteratively by adding the displacement Navy-supported research. refs thickness to the metal blade contour. The averaged exit flow Lift anomalies arising from massive laminar separation are properties and the total pressure loss coefficient are determined studied in the framework of steady-state solutions to the problem by using the conservation laws. Good agreement is found between of a body-scaleflow, with the ’triple-deck’ as a key element. Existing experimental and theoretical results regarding profile Mach number studies by this approach are summarized; more complete results, distribution over the whole incidence range. It is suggested that representing multiple steady states of the open- and closed-wake discrepancies for losses at negative incidences can be reduced models, provide an analytical basis for explaining lift hysteresis, by more accurately accounting for the shock boundary layer symmetry breaking, and other forms of lift anomalies in a subcritical interaction, the shock induced separation, and the strength of the flow. The importance of time-accurate analyses in providing the shock wave. R.R. data base for the assessment of these bifurcating steady states is discussed. Also noted is the relevance of the development A88-11176 from the triple-deck theory of the marginal stall to an explanation AERODYNAMICS AT LOW REYNOLDS NUMBERS RE GREATER of the anomalous LID increase of certain airfoils just before stall THAN 10 TO THE 4TH AND LESS THAN 10 TO THE 6TH; at a high subcritical Re. Author PROCEEDINGS OF THE INTERNATIONAL CONFERENCE, LONDON, ENGLAND, OCT. 15-18, 1986. VOLUMES 1, 2, & 3 Conference supported by the US. Navy. London, Royal A88-11179 Aeronautical Society, 1986, p. Vol. 1, 280 p.; vol. 2, 287 p.; vol. A SIMPLE METHOD FOR THE PREDICTION OF SEPARATION 3, 390 p . For individual items see A88-11177 to A88-11210. BUBBLE FORMATION ON AEROFOILS AT LOW REYNOLDS Various papers on aerodynamics at low Reynolds numbers NUMBER are presented. The topics addressed include: massive laminar F. N. COTON and R. A. MCD. GALBRAITH (Glasgow, University, separation and lift anomalies in the subcritical Re range, smoke-wire Scotland) IN: Aerodynamics at low Reynolds numbers Re greater study of low Re flow over a NASA LRN(1)-1007 airfoil section, than 10 to the 4th and less than 10 to the 6th; Proceedings of transition and separation control on a low-Re number airfoil, recent the International Conference, London, England, Oct. 15-18, 1986. developments in boundary layer computation and in the calculation Volume 1 . London, Royal Aeronautical Society, 1986, p. 3.1-3.17. of flow over low-Re airfoils, determination of the 2-0 characteristics refs of airfoils at low Re, recent wind tunnel experiments at low Re, An aerofoil analysis code is described and its application to low-Re aerodynamics research at NASA Langley Research Center, separated laminar flows discussed. A technique is developed for use of wind tunnel data in the design of radio-controlled contest the prediction of the onset of long separation bubble formation model sailplanes, and wind tunnel testing of small-scale on an aerofoil, from the separated laminar flow condition. pressure-tapped model propellers. Also discussed are: prediction Comparison with experimentally obtained data for one aerofoil is of a microlight biplane’s airfoil performance using a computer made and good agreement is obtained. Comments on the general model, low-Re airfoil family for horizontal axis wind turbines, applicability of the method are made, and its limitations experimental investigation of the aerodynamics of the hang glider, discussed. Author aerodynamics of gliding parachutes, development of an efficient oceanographic fairing for operation at Re = 250,000, selection of airfoil sections for use in man-powered aircraft, and aerodynamic A88-11180 force coefficients determined from a vertical axis wind turbine A THEORETICAL STUDY OF SPANWISE-PERIODIC 3-D simulator. C.D. DISTURBANCES IN THE WAKE OF A SLIGHTLY STALLED WING AT LOW REYNOLDS NUMBERS A88-11177 G. R. INGER (Iowa State University of Science and Technology, AERODYNAMICS AT LOW REYNOLDS NUMBERS - A REVIEW Ames) IN: Aerodynamics at low Reynolds numbers Re greater OF THEORETICAL AND EXPERIMENTAL RESEARCH AT DELFT than 10 to the 4th and less than 10 to the 6th; Proceedings of UNIVERSITY OF TECHNOLOGY the International Conference, London, England, Oct. 15-18, 1986. J. L. VAN INGEN and L. M. M. BOERMANS (Delft, Technische Volume 1 . London, Royal Aeronautical Society, 1986, p. 4.1-4.21. Hogeschool, Netherlands) IN: Aerodynamics at low Reynolds refs numbers Re greater than 10 to the 4th and less than 10 to the (Contract AF-AFOSR-85-0357) 6th; Proceedings of the InternationalConference, London, England, For a slightly aft-stalling, large aspect-ratio wing in laminar flow, Oct. 15-18, 1986. Volume 1 . London, Royal Aeronautical Society, the formation and properties of spanwise-periodic, threedimensional, 1986, p. 1.1-1.41. DFVLR-supported research. refs small disturbances within the boundary layer along the otherwise straight This paper gives a review of research on low Reynolds number separation line in a nominally two-dimensional flow is investigated. The aerodynamics. Typical for this Reynolds number range is the physical mechanism, streamline inclination at separation, local steamline occurrence of significant effects of laminar separation bubbles. curvature above separation, local instability criterion at separation, and Results of flow visualization studies are used to define an empirical eigenvalue problem for the neutrally stable disturbances are relation for the angle gamma at which the separation streamline analyzed for streamwise vortex formation at separation. The

8 02 AERODYNAMICS implications of the results for the near-wake structure and A88-11184 momentum defect are considered. C.D. BOUNDARY LAYER AND PERFORMANCE CHARACTERISTICS FROM WIND TUNNEL TESTS OF A LOW REYNOLDS NUMBER LIEBECK AIRFOIL P. LEBLANCK, R. H. LIEBECK, and R. BLACKWELDER (Southern California, University, Los Angeles, CA) IN: Aerodynamics at low Reynolds numbers Re greater than 10 to the 4th and less than A88-11181 Virginia Univ., Charlottesville. 10 to the 6th; Proceedings of the International Conference, London, England, Oct. 15-18, 1986. Volume 1 London, Royal Aeronautical A SMOKE-WIRE STUDY OF LOW REYNOLDS NUMBER FLOW . OVER A NASA LRN(1) - 1007 AIRFOIL SECTION Society, 1986, p. 8.1-8.19. refs S. S. FISHER (Virginia, University, Charlottesville) and J. D. (Contract NO0014-84-K-0500) ABBITT IN: Aerodynamics at low Reynolds numbers Re greater Experimental data is presented for an investigation of both than 10 to the 4th and less than 10 to the 6th; Proceedings of global performance parameters and more detailed boundary layer the International Conference, London, England, Oct. 15-18, 1986. flowfield characteristics of a Liebeck LA2573A airfoil designed for Volume 1 . London, Royal Aeronautical Society, 1986, p. 5.1-5.28. use at low Reynolds numbers. Hot-wire mean velocity and turbulent refs intensity profiles illustrate the development of a laminar separation Smoke-filament visualization photographs are presented for bubble through transition and reattachment, while boundary layer two-dimensional flow over a NASA LRN(1) - 1007 airfoil section spectra highlight the progression of instabilities toward transition. designed specifically for high-efficiency operation at low chord Increases in the free stream turbulence level promote earlier Reynolds numbers. Results are included for chord Reynolds transition and a smaller separation bubble. Author numbers of 60,000, 100,000. and 220,000 and for angles of attack ranging from 0 to 16 degrees. Two kinds of laminar separation A88-11185 bubble are found to develop in the flow over the airfoil. The sites ATMOSPHERIC TURBULENCE AND GUST ON THE, and characteristics of formation of these bubbles are described, PERFORMANCE OF A WORTMANN FX 63-137 WING and their dimensional properties are estimated. The transition-to-tur- H.-T. LIU (Flow Research Co., Kent, WA) IN: Aerodynamics at bulence Reynolds numbers, surface pressure coefficient distributions, low Reynolds numbers Re greater than 10 to the 4th and less and lift coefficents deduced from the measured coefficients are com- than 10 to the 6th; Proceedings of the International Conference, pared with those obtained by other authors. C.D. London, England, Oct. 15-18, 1986. Volume 1 . London, Royal Aeronautical Society, 1986, p. 9.1 -9.25. refs (Contract N00014-85-C-0214) The unsteady effects of turbulence and gust on the performance of a full-scale Wortmann FX 63-137 wing with a 3.66 m span and 0.61 m chord are experimentally studied. The chord Reynolds number ranges from 80,000 to 450.000 and the turbulence intensity A88-11182 from 8 to over 40 percent. The spectra of the wind components AN ANALYSIS OF UNSTEADY, TWO-DIMENSIONALSEPARATION show that the reduced frequencies experienced by the wing may BUBBLES be up to 0.1 or higher, indicating that unsteady effects are important. HELEN REED (Arizona State University, Tempe) and LAURA The instantaneous angle of attack of the wing is mainly governed PAULEY (Stanford University, CA) IN: Aerodynamics at low by variations in the vertical wind component. Thus, the wing Reynolds numbers Re greater than 10 to the 4th and less than experiences mainly a plunging rather than a pitching motion, 10 to the 6th; Proceedings of the InternationalConference, London, together with sweeping and longitudinal oscillations due to the England, Oct. 15-18, 1986. Volume 1 . London, Royal Aeronautical unsteady, three-dimensional wind field. Significant lift overshoot is Society, 1986, p. 6.1-6.18. refs observed in the full-scale data, resulting in a significant increase (Contract NO001 4-84-K-0232; NO001 4-86-K-0066) in the C(L)max and in the stall angle. A twofold reduction in C(D)min The following is a report on the ongoing analysis of unsteady, is also observed. C.D. two-dimensional separation bubbles by triple-deck theory. Velocity profiles are presented for various freestream pressure gradients A884 1186' National Aeronautics and Space Administration. expected in low-Reynolds-numberflight. The companion experiments for predictive-model verification are described. Author Lewis Research Center, Cleveland, Ohio. TRANSITION AND SEPARATION CONTROL ON A LOW-REYNOLDS NUMBER AIRFOIL S. M. MANGALAM, A. BAR-SEVER (AS&M, Inc., Hampton, VA), K. B. M. Q. ZAMAN (NASA, Lewis Research Center, Cleveland, OH), and W. D. HARVEY (NASA, Langley Research Center, Hampton, VA) IN: Aerodynamics at low Reynolds numbers Re greater than 10 to the 4th and less than 10 to the 6th; Proceedings A88-11183 of the InternationalConference, London, England, Oct. 15-18, 1986. LOW REYNOLDS NUMBER AIRFOIL DESIGN AT THE DOUGLAS Volume 1 . London, Royal Aeronautical Society, 1986, p. AIRCRAFT COMPANY 10.1-10.19. refs R. H. LIEBECK (Douglas Aircraft Co., Long Beach, CA) IN: (Contract NASl-17670; NAS1-17683; NASl-18235) Aerodynamics at low Reynolds numbers Re greater than 10 to The major problem associated with the aerodynamic the 4th and less than 10 to the 6th; Proceedings of the International performance of airfoils at low Reynolds numbers is the presence Conference, London, England, Oct. 15-18, 1986. Volume 1 . of extensive laminar boundary-layer separation resulting in a large London, Royal Aeronautical Society, 1986, p. 7.1-7.24. refs increase in presssure drag and a decrease in lift. The rapid Development of low Reynolds number airfoil technology at the deterioration in airfoil characteristics can be largely eliminated by Douglas Aircraft Company over the past 15 years is described. artificially controlling the flow through the introduction of suitable This includes an explanation of some fluid mechanical problems, disturbances in the boundary layer such that transition occurs ahead such as control of the omnipresent laminar separation bubble, of the anticipated laminar separation. This paper presents the which are unique to the low Reynolds number flight regime. results of wind-tunnel tests conducted on a 10-cm model of LRN Performance trades between design C(I), C(m), C(l)max, and t/c (1)-1007 airfoil with passive (roughness trips) and active (acoustic are discussed and illustrated with wind tunnel results from several excitation) controls to trigger transition and suppress separation. example airfoils. Recommendations for future airfoil design and Significant improvements in the aerodynamic characteristics of the testing are offered. Author airfoil were observed. Results of this study for a chord Reynolds

9 02 AERODYNAMICS number range of 40,000 to 250,000 are presented in this paper. A88-11190' Notre Dame Univ., Ind. Author LOW REYNOLDS NUMBER WIND TUNNEL MEASUREMENTS - THE IMPORTANCE OF BEING EARNEST THOMAS J. MUELLER, STEPHEN M. BATILL, MICHAEL BRENDEL, MARK L. PERRY, DIANE R. BLOCH (Notre Dame, University, IN) et al. IN: Aerodynamics at low Reynolds numbers A88-11187 CONTROL SURFACE EFFECTS ON THE LOW REYNOLDS Re greater than 10 to the 4th and less than 10 to the 6th; NUMBER BEHAVIOR OF THE WORTMANN FX 63-137 Proceedings of the International Conference, London, England, J. F. MARCHMAN, 111 and V. SUMANTRAN (Virginia Polytechnic Oct. 15-18, 1986. Volume 2 . London, Royal Aeronautical Society, Institute and State University, Blacksburg) IN: Aerodynamics at 1986, p. 14.1-14.18. Research supported by the University of Notre low Reynolds numbers Re greater than 10 to the 4th and less Dame. refs than 10 to the 6th; Proceedings of the International Conference, (Contract NSG-1419; N00014-83-K-0239) A method for obtaining two-dimensional aerodynamic force London, England, Oct. 15-18, 1986. Volume 1 . London, Royal Aeronautical Society, 1986, p. 11.l-11.14. refs coefficients at low Reynolds numbers using a three-component (Contract NOOOl 4-84-K-0093) external platform balance is presented. Regardless of method, The effects of control-surface deflections on the flow around however, the importance of understanding the possible influence and on the aerodynamic performance of two Wortmann FX 63-137 of the test facility and instrumentation on the final results cannot wings were studied experimentally in the Virginia Tech Stability be overstated. There is an uncertainty in the ability of the facility Wind Tunnel. Tests were conducted at Reynolds numbers from to simulate a two-dimensional flow environment due to the 70,000 to 300,000 on wings of aspect ratio four and nine with confinement effect of the wind tunnel and the method used to various arrangements of 30 percent chord trailing edge control mount the airfoil. Additionally, the ability of the instrumentation to accurately measure forces and pressures has an associated surfaces deflected between angles of + or - 40 degrees and used as both plain flaps and ailerons. Positive flap deflection yielded uncertainty. This paper focuses on efforts taken to understand fairly conventional flap behavior and caused no noticeable changes the errors introduced by the techniques and apparatus used at in basic low Reynolds number flow patterns. Negative deflections the University of Notre Dame, and, the importance of making an cause large changes in the flow and marked deterioration of lift earnest estimate of the uncertainty. Although quantitative estimates and drag. Negative deflections may alter the basic nature of stall of facility induced errors are difficult to obtain, the uncertainty in at a given Reynolds number. Aileron behavior was predictable measured results can be handled in a straightforward manner and and resembles that expected at higher Reynolds numbers. The provide the experimentalist, and others, with a basis to evaluate results include force, moment, and pressure distribution data. experimental results. Author Author A88-11191 RECENT DEVELOPMENTS IN THE CALCULATION OF FLOW OVER LOW REYNOLDS-NUMBER AIRFOILS TUNCER CEBECI, G. S. WANG, K. C. CHANG, and J. CHOl A88-11188 (California State University, Long Beach) IN: Aerodynamics at RECENT DEVELOPMENTS IN BOUNDARY LAYER COMPUTA- low Reynolds numbers Re greater than 10 to the 4th and less TION than 10 to the 6th; Proceedings of the International Conference, R. EPPLER (Stuttgart, Universitaet, Federal Republic of Germany) London, England, Oct. 15-18, 1986. Volume 2 . London, Royal IN: Aerodynamics at low Reynolds numbers Re greater than 10 Aeronautical Society, 1986, p. 15.1 -15.1 3. refs to the 4th and less than 10 to the 6th; Proceedings of the (Contract NOOOl 4-85-K-0346) International Conference, London, England, Oct. 15-18, 1986. A method developed previously for high Reynolds number flows Volume 2 . London, Royal Aeronautical Society. 1986, p. is extended and used to calculate the flow over low 12.1-1 2.1 8. Reynolds-number airfoils and to obtain results which can be The most important and difficult part of the boundary layer compared with measurements. It is based on the interaction of computation for low Reynolds numbers is to simulate the laminar solutions of inviscid and boundary-layer equations and involves separation bubble. A very simple and successfully applied model the flow around the airfoil and its wake. The inviscid equations is a bubble analogue which can be evaluated from a conventional are solved by a conformal-mapping procedure and the computational method based upon the integral momentum and boundary-layer equations by an inverse finite-difference procedure energy equation. Recently, it turned out that this model was not with an interaction formula. The emphasis of the paper is on sharp enough and yielded a too short analogy of the bubble. transition in low Reynolds number flows with separation and on Modificationsare discussed which improve the model. Comparisons the influence of the wake which is known to be important with with experiments are presented. Author high angles of attack and high Reynolds numbers. A correlation formula based on linear stability theory is developed and used to calculate transition. The results show that the accurate prediction of transition is important and is satisfied by the present formula. A88-11189 They also demonstrate the need to include the wake in low ON SOME UNSTEADY AERODYNAMICS CHARACTERISTICS Reynolds-number flow calculations for all angles of attack. OF AN NACA 0012 AT REYNOLDS NUMBERS OF 125,000 AND Author 400,000 M. FLETCHER and E. COVERT (MIT, Cambridge, MA) IN: A88-11192 Aerodynamics at low Reynolds numbers Re greater than 10 to ON THE DETERMINATION OF THE 2-D CHARACTERISTICS the 4th and less than 10 to the 6th; Proceedings of the International OF AEROFOILS AT LOW REYNOLDS NUMBERS Conference, London, England, Oct. 15-18, 1986. Volume 2 . D. I. A. POLL and A. MANSOOR (Cranfield Institute of Technology, London, Royal Aeronautical Society, 1986, p. 13.1-13.33. refs England) IN: Aerodynamics at low Reynolds numbers Re greater The unsteady pressures and boundary layers of an NACA 0012 than 10 to the 4th and less than 10 to the 6th; Proceedings of airfoil at Reynolds numbers of 125,000, 400,000, 700,000, and 1 the International Conference, London, England, Oct. 15-18, 1986. million and reduced frequencies of 0.5, 1.0, 2.0, and 6.4 are Volume 2 . London, Royal Aeronautical Society, 1986, p. examined. The flow quality of the facility is discussed, and the 16.1-1 6.1 6. refs effects of reduced frequency on the pressure distribution and of This paper describes an experimental investigation of the Reynolds number are considered. The Law of the Wall and Law aerodynamic characteristics of the NACA 23012 aerofoil in the of the Wake relations are addressed for unsteady boundary Reynolds number range 200,000 to 400,000. Tests were conducted layers. C.D. using a variable aspect ratio rig in an open-jet wind tunnel. Lift

10 02 AERODYNAMICS forces and pitching moments were deduced by integrating surface A88-11198 pressures, and the drag force was obtained by the wake traverse PREDICTION OF A MICROLIGHT BIPLANE'S AEROFOIL technique. Special attention was paid to the attainment of infinite PERFORMANCE USING A COMPUTER MODEL aspect ratio - or two-dimensional - flow conditions. Preliminary P. G. WALTON (Sunderland Polytechnic, England) IN: data are compared with existing information covering the Reynolds Aerodynamics at low Reynolds numbers Re greater than 10 to number range 700,000 to 9 million. Guidelines for the investigation the 4th and less than 10 to the 6th; Proceedings of the International of two-dimensional aerofoil characteristics in open-jet wind tunnels Conference, London, England, Oct. 15-18, 1986. Volume 3 . are proposed. Author London, Royal Aeronautical Society, 1986, p. 23.1-23.33. refs A project to design the wing section of the MBA Tiger Cub A88-11193 440 microlight biplane is discussed. The basic airfoil found on the RECENT WIND TUNNEL EXPERIMENTS AT LOW REYNOLDS standard aircraft is evaluated, a high-lift device is studied, and the NUMBERS effect of variable airfoil geometry due to unstable properties of DIETER ALTHAUS (Stuttgart, Universitaet, Federal Republic of the fabric used to cover the wings is examined. Three approaches Germany) IN: Aerodynamics at low Reynolds numbers Re greater are used in the study: semiinverse viscous flow predictions, wind than 10 to the 4th and less than 10 to the 6th; Proceedings of tunnel experiments, and flight tests. The usefulness of these the International Conference, London, England, Oct. 15-18, 1986. methods is compared. C.D. Volume 2 . London, Royal Aeronautical Society, 1986, p. 18.1 -18.42. refs Work conducted on low Reynolds number aerodynamics at the Institute for Aerodynamics and Gasdynamics of the University A88-11200 of Stuttgart is reviewed. The general characteristics of testing in AN EXPERIMENTAL INVESTIGATION OF THE AERODYNAMICS the laminar wind tunnel and model wind tunnel at the facility are OF THE HANG GLIDER described. Tests to determine the effects of hysteresis in lift and M. V. COOK and E. A. KILKENNY (Cranfield Institute of Technology, drag on the FX 63-137, the Lissaman 7669, the Miley 06-13-128, England) IN: Aerodynamics at low Reynolds numbers Re greater the AH 79-100 B, and the E 214 airfoils are reviewed. It is concluded than 10 to the 4th and less than 10 to the 6th; Proceedings of that hysteresis at low Reynolds numbers is caused by two different the International Cqnference, London, England, Oct. 15-18, 1986. mechanisms: at low angles of attack by transition from subcritical Volume 3 . London, Royal Aeronautical Society, 1986, p. 25.1-25.20. to supercritical state of flow and vice-versa, and at high angles of SERC-supported research. refs attack by bursting and reattachment of a laminar separation bubble near the leading edge. C.D.

A88-11194' National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. A88-11201 LOW-REYNOLDS NUMBER AERODYNAMICS RESEARCH AT THE AERODYNAMICS OF GLIDING PARACHUTES NASA LANGLEY RESEARCH CENTER J. S. LINGARD (G.Q. Defence Equipment, Ltd., Parachute Div., WILLIAM D. HARVEY (NASA, Langley Research Center, Hampton, Woking, England) IN: Aerodynamics at low Reynolds numbers VA) IN: Aerodynamics at low Reynolds numbers Re greater Re greater than 10 to the 4th and less than 10 to the 6th; than 10 to the 4th and less than 10 to the 6th; Proceedings of Proceedings of the International Conference, London, England, the International Conference, London, England, Oct. 15-18, 1986. Oct. 15-18, 1986. Volume 3 . London, Royal Aeronautical Society, Volume 2 . London, Royal Aeronautical Society, 1986, p. 1986, p. 26.1-26.41. refs 19.1-19.49. refs The development of gliding parachutes is reviewed, and it is The present status of various types of low-Reynolds number shown how simple aerodynamic theory explains the performance aerodynamics research being conducted at the Fluid Dynamics of the most successful gliding decelerator to date, the ram air Branch of NASA Langley Research Center is reviewed. The parachute. The use of the same theory to identify the features facilities, testing techniques, airfoil design, and experimental limiting that performance, thus leading to the development of a verification are addressed, and ongoing studies of laminar parachute giving gliding efficiency considerably better than any separation bubbles, boundary layer stability and transition control, previous nonrigid device, is shown. C.D. and low-Reynolds number juncture flow are discussed. The possibility of improving vehicle characteristics at low Reynolds numbers and the general trends of the most promising research in these areas are examined. C.D. A88-11202 THE EFFECT OF GRIT ROUGHNESS ON THE PERFORMANCE A88-11197 OF THE WORTMANN FX63-137 AIRFOIL AT A CHORD THE CALCULATION OF FLOW ABOUT AEROFOILS AT LOW REYNOLDS NUMBER OF 100,000 REYNOLDS NUMBER WITH APPLICATION TO REMOTELY ARTHUR F. HUBER, II and THOMAS J. MUELLER (Notre Dame, PILOTED VEHICLES University, IN) IN: Aerodynamics at low Reynolds numbers Re B. R. WILLIAMS (Royal Aircraft Establishment, Farnborough, greater than 10 to the 4th and less than 10 to the 6th; Proceedings England) IN: Aerodynamics at low Reynolds numbers Re greater of the InternationalConference, London, England, Oct. 15-18, 1986. than 10 to the 4th and less than 10 to the 6th; Proceedings of Volume 3 . London, Royal Aeronautical Society, 1986, p. 28.1-28.16. the International Conference, London, England, Oct. 15-18, 1986. Research supported by the University of Notre Dame. refs Volume 3 . London, Royal Aeronautical Society, 1986, p. (Contract NO0014-83-K-0239) 22.1 -22.49. refs An experimental investigation was conducted on the Experimental results from tests on five airfoils (NACA 4412, performance and boundary-layer characteristics of the Wortmann NACA 64/3/-418, Gottingen 797, Wortmann FX63-137, and FX63-137 airfoil with and without distributed grit roughness. Data GA/W/-2) are compared with calculations by a viscous-inviscid were obtained through use of a three-component strain gage force interaction method. Particular attention is paid to flows at a balance and static pressure measuring equipment at a test chord Reynolds number just below one million. It is shown that the Reynolds number of Rc = 100,000. Emphasis was placed on theoretical method gives adequate predictions of the variation of determining the effect of grit placement and size on performance lift and drag, and movement of the position of transition from parameters. Prediction of the transition location by the criterion laminar to a turbulent boundary layer with increasing incidence. due to Klebanoff et ai. (1955) was found to have limited application. The paper concludes with some suggestions for improving the In most cases airfoil performance was degraded, but in some viscous-inviscid interaction method, which would allow calculations instances minimum drag was reduced and maximum lift to drag at even lower Reynolds numbers. Author ratio increased. Author

11 02 AERODYNAMICS

A88-11203 A88- 11 206 PRELIMINARY MEASUREMENTS OF THE FLIGHT PERFOR- THE PERFORMANCE OF MODEL AIRCRAFT USING FLOW MANCE OF AN RPV COMPARED WITH WIND TUNNEL AND CFD INVIGORATORS, GLIDING IN THE CRITICAL RANGE OF ESTIMATES REYNOLDS NUMBER D. J. DYER and J. L. STOLLERY (Cranfield Institute of Technology, MARTYN S. PRESSNELL (Hatfield Polytechnic, England) IN: England) IN: Aerodynamics at low Reynolds numbers Re greater Aerodynamics at low Reynolds numbers Re greater than 10 to than 10 to the 4th and less than 10 to the 6th; Proceedings of the 4th and less than 10 to the 6th; Proceedings of the International the International Conference, London, England, Oct. 15-18, 1986. Conference, London, England, Oct. 15-18, 1986. Volume 3 . Volume 3 . London, Royal Aeronautical Society, 1986, p. 29.1 -29.14. London, Royal Aeronautical Society, 1986, p. 32.1-32.32. refs Research supported by the Ministry of Defence. refs The behavior of the Benedek 6356b airfoil, fitted with a The results of wind tunnel tests on replacement wings for the leading-edge turbulator and various combinations of invigorators X-RAE 1 experimental RPV are reported and discussed. The and operating in the critical range of Reynolds number, was sections used were the Goettingen 797, the Wortmann FX 63-137, investigated experimentally. The effects observed are attributed to and the NACA 64(3)-418. Tests over the Reynolds number range the formation, control, and eventual collapse of vortex bubble flow from 300,000 to 1 million showed that the 797 and the Wortmann in the boundary layer. This information is used to predict the gliding wing sections have good performance characteristics. Comparisons performance of free-flight competition models conforming to the with the computational model of Williams (1984) revealed that the FA1 International classes F1A. F1B and for Coupe D’Hiver, and model shows considerable promise of coping with laminar A1 glider classes. It is shown that significant advantage may be separation, transition, turbulent reattachment, and turbulent gained by operating models with an appropriate aspect ratio. separation likely to occur in the above Re range. The addition of Author roughness degraded the performance of all three sections, particularly the 797. Full-scale tests on a complete RPV model clearly showed the advantages of fitting a wing of Wortmann rather than flat-bottomed section. C.D.

A88-11207 A88-11204 SELECTION OF AEROFOIL SECTIONS FOR USE IN AERODYNAMICS OF UNMANNED AIRCRAFT AT FULL-SCALE MAN-POWERED AIRCRAFT IN THE RAE 24FT WIND-TUNNEL KEITH SHERWIN (Nanyang Technological Institute, Singapore) IN: W. J. G. TREBBLE (Royal Aircraft Establishment, Farnborough, Aerodynamics at low Reynolds numbers Re greater than 10 to England) IN: Aerodynamics at low Reynolds numbers Re greater the 4th and less than 10 to the 6th; Proceedings of the International than 10 to the 4th and less than 10 to the 6th; Proceedings of Conference, London, England, Oct. 15-18, 1986. Volume 3 . the International Conference, London, England, Oct. 15-18, 1986. London, Royal Aeronautical Society, 1986, p. 33.1-33.8. refs Volume 3 . London, Royal Aeronautical Society, 1986, p. The availability and choice of airfoil sections for use in the 30.1 -30.29. refs design of man-powered aircraft are studied. In particular, the data Wind-tunnel tests have been made on full-scale models of the available on the Lissaman 7769 section are reviewed and X-RAE 1 and X-RAE 2 unmanned aircraft in the RAE 24 ft wind comparison is made with the equivalent aerodynamic Performance tunnel over a Reynolds number range (0.5-1.2) x 10 to the 6th. of the Wortmann FX 63-137, FX 76-MP-120, and FX 76-MP-160 The results show that substantial increases in lifting capability sections using two criteria: power/weight ratio, which is suitable could be achieved by choosing a wing section (Wortmann for man-powered aircraft used for training, and liftldrag ratio, which FX63-137) more appropriate to the range of Reynolds number is suitable for man-powered aircraft for speed/sports competition. associated with the required airspeed range from 20 m/s to 50 The FX 63-137 is found to have no performance advantage; the m/s. The UMA stalls from the root trailing-edge so the 1 deg 7769 and the FX 76-MP-120 have excellent performance. The washout provided appears to be unnecessary. The UMAs have latter can operate at higher C(L) values, resulting in a smaller adequate stability margins and both have powerful nose-down wing area for a given speed and hence a more compact aircraft. moments at the stall. Some increase in lift/drag ratio occurs as On the other hand, the 7769 allows for easier construction due to the Reynolds number is raised. Author its simple shape and its tolerance for imperfections. C.D.

A88-11205 LOW ALTITUDWAIRSPEED UNMANNED RESEARCH AIRCRAFT (LAURA) PRELIMINARY DEVELOPMENT RICHARD J. FOCH (US Navy, Naval Research Laboratory, Washington, DC) and RANDALL E. WYATT (US. Navy, Office of A88-11208 Naval Research, Arlington, VA) IN: Aerodynamics at low Reynolds WIND-TUNNELTESTRESULTS OF EPPLER 387 AEROFOILS AND numbers Re greater than 10 to the 4th and less than 10 to the COMPARISONS WITH FLIGHT TEST AND COMPUTATION 6th; Proceedings of the InternationalConference, London, England, T. J. PATRICK (University College, London, England) IN: Oct. 15-18, 1986. Volume 3 . London, Royal Aeronautical Society, Aerodynamics at low Reynolds numbers Re greater than 10 to 1986, p. 31 .l-31.29. Navy-supported research. refs the 4th and less than 10 to the 6th; Proceedings of the International The stringent constraints on the design of the Low Conference, London, England, Oct. 15-18, 1986. Volume 3 . Altitude/Airspeed Unmanned Research Aircraft (LAURA) requires London, Royal Aeronautical Society, 1986, p. 34.1-34.8. refs the development of both highly efficient low Reynolds number Wind tunnel test results on the Eppler Profile 387 are compared airfoils and advanced airframes/systems. The aerodynamic with each other and with computational results. Free gliding development of multiple planform configurations are presented. characteristics of one test model are measured over a Reynolds Preliminary designs for aft tail twin boom, span-hinged conventional number range of 49,000 to 68,000. A set of composite wingltail, unswept tandem wing, and tip-joined swept tandem wing characteristics Eppler 387 airfoils is assembled, giving wind tunnel configurations are provided. Select wind tunnel test results for values for Re between 60,000 and 200,000 and Williams code each configuration are also included. C.D. predictions for Re above 200,000. C.D.

12 02 AERODYNAMICS

A88-11210 A88-12059 SMOKE-WIRE AND THIN-FILM-GAUGE OBSERVATIONS OF TRANSONIC EXPANSIONS [0 TRANSZVUKOVYKH RAZLOZ- LAMINAR SEPARATION BUBBLES ON AN NACA 23012-64 HENIIAKH] AIRFOIL SECTION A. L. BREZHNEV and I. A. CHERNOV Prikladnaia Matematika i S. S. FISHER and D. C. HORGER (Virginia, University, Mekhanika (ISSN 0032-8235), vol. 51, July-Aug. 1987, p. 688-690. Charlottesville) IN: Aerodynamics at low Reynolds numbers Re In Russian. refs greater than 10 to the 4th and less than 10 to the 6th; Proceedings The paper is concerned with the problem of finding particular of the International Conference, London, England, Oct. 15-18, 1986. solutions to inhomogeneous linearized transonic equations arising Volume 3 . London, Royal Aeronautical Society, 1986, p. 36.1 -36.24. in transonic expansions that are expressed explicitly in terms of Research supported by the University of Virginia and US. Navy. the principal solution to the Karman-Falkovich equation. First and refs second corrections to the solution for the Karman-Falkovich The smoke-wire flow visualization technique and the surface equation are derived. In contrast to the first correction, the second thin-film heat transfer gauge method are used here, together with correction is shown to contain curvilinear integrals. V.L. surface pressure coefficient measurements, to characterize the behavior of laminar separation bubbles as they form on the suction A88-12065 side of a NACA 23012-64 airfoil section. Thin-film gauges are STABILITY OF SUPERSONIC FLOW OF AN IDEAL GAS WITH used to follow the development of unsteady flow patterns within A HEAD SHOCK WAVE PAST CYLINDRICAL CHANNELS AND these bubbles. Signals from the gauges are shown to be highly CAVITIES [OB USTOlCHlVOSTl OBTEKANIIA TSILINDRICHES- sensitive to flow fluctuations occurring within their immediate KlKH KANALOV I POLOSTEI SVERKHZVUKOVYM POTOKOM vicinity, up to frequencies as high as 1000 Hz. With these gauges, IDEALNOGO GAZA S GOLOVNOI UDARNOI VOLNOI] it is possible to detect the development of unstable oscillatory wave motions within the bubble-free shear layer which are quite V. T. GRIN', N. N. SLAVIANOV, and N. I. TlLLlAEVA Akademiia small in magnitude. Signals from these gauges also provide a Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN clear indication of transition to turbulence within this layer. It is 0568-5281), July-Aug. 1987, p. 114-121. In Russian. refs possible to deduce the approximate point of boundary layer surface The stability of supersonic flow of an ideal gas with a head reattachment from these signals. C.D. shock wave past cylindrical channels and cavities is investigated in the context of both distributed and concentrated parameter models using a first-order difference scheme with the isolation of the head shock. A stability analysis based on the linearized concentrated parameter model indicates that there exists a critical cavity length above which homogeneous supersonic flow becomes A88- 11 280 unstable. The qualitative results obtained on the basis of the NUMERICAL SOLUTION OF COUPLED PROBLEMS OF concentrated parameter model are shown to support and SUPERSONIC FLOW PAST DEFORMABLE SHELLS OF FINITE complement the results obtained earlier from physical and THICKNESS [0 CHISLENNOM RESHENll SVIAZANNYKH numerical experiments with the distributed parameter model. ZADACH SVERKHZVUKOVOGO OBTEKANIIA DEFORMIRUE- V.L. MYKH OBOLOCHEK KONECHNOI TOLSHCHINY] P. N. KOROTIN, I. B. PETROV, V. B. PIROGOV, and A. S. KHOLODOV Zhurnal Vychislitel'noi Matematiki i Matematicheskoi A88-12071 Fiziki (ISSN 0044-4669), vol. 27, Aug. 1987, p. 1233-1243. In OXYGEN RECOMBINATION IN A SUPERSONIC COOLED FLOW Russian. refs [REKOMBINATSIIA KISLORODA V SVERKHZVUKOVOM The problem considered here concerns supersonic flow of an OKHLAZHDAIUSHCHEMSIA POTOKE] inviscid non-heat-conducting gas past a blunt body which V. K. DUSHIN, I. E. ZABELINSKII, and 0. P. SHATALOV simultaneously undergoes elastic deformation. The body is formed Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN by a single-layer or a multiple-layer shell of finite thickness with 0568-5281), July-Aug. 1987, p. 160-165. In Russian. refs specified elastic-plastic properties; the shell may be stiffened by Oxygen recombination in supersonic cooled flows is investigated ribs. Under the effect of a head shock wave, the body may change here by the following two methods: by measuring ultraviolet its shape through deflections, thus affecting gas flow. The problem emission absorption by oxygen molecules forming in a supersonic is solved by using an explicit grid scheme classified as a positive nozzle and by measuring gas pressure inside the nozzle. For this approximation scheme. V.L. particular problem, the absorption spectroscopy method is found to be much more sensitive, making it possible to measure the recombination rate constant for low degrees of initial oxygen dissociation and at lower temperatures (1 000 K). The piezoelectric method makes it possible to conduct measurements at higher temperatures for much higher (by an order of magnitude) concentrations of recombining atoms. The results obtained are A88-12056 compared with data in the literature, and an expression for the STRONG GAS INJECTION INTO SUPERSONIC FLOW WITH TUR- oxygen atom recombination rate constant is proposed. V.L. BULENT MIXING [SIL'NYI VDUV GAZA V SVERKHZVUKOVOI POTOK PRI TURBULENTNOM SMESHENII] A88-12073 1. I. VIGDOROVICH Prikladnaia Matematika i Mekhanika (ISSN EFFECT OF ENERGY RELEASE IN THE SHOCK LAYER ON 0032-8235), vol. 51, July-Aug. 1987, p. 600-610. In Russian. THE SUPERSONIC FLIGHT OF BODIES [VLIIANIE ENER- refs GOVYKELENIIA V UDARNOM SLOE NA SVERKHZVUKOVOI Strong distributed injection of a gas through a porous plate POLET TEL] into supersonic flow is analyzed for the case where the boundary S. I. ARAFAILOV Akademiia Nauk SSSR, Izvestiia, Mekhanika layer is forced away from the plate and the injected gas is separated Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. 1987, p. 178-182. from the incoming flow by a turbulent mixing layer. A criterion for In Russian. refs the detachment of the turbulent boundary layer during injection is The presence of an energy release region in supersonic flow formulated, as is a similarity rule reflecting the dependence of gives rise to perturbations propagating from the energy release flow over the plate on the conditions at the end of the porous source. The effect of such flow on a body is determined by the region. Pressure and injection layer thickness distribution curves intensity of the source and by the configuration and location of are presented, and the force characteristics of the flow are the energy release region. Here, the dependence of the calculated. V.L. aerodynamic characteristic of a blunt cone on the parameters of

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an energy release source is analyzed by using results of the A88-12284# numerical integration of equations of motion for a gas. V.L. TWO-DIMENSIONAL TRANSONIC AERODYNAMIC DESIGN METHOD MICHAEL B. GILES and MARK DRELA (MIT, Cambridge, MA) AlAA Journal (ISSN 0001-1452), vol. 25, Sept. 1987, p. A88-12074 1199-1 206. refs ANALYSIS OF SUPERSONIC HETEROGENEOUS FLOW IMPING- (Contract F49620-78-C-0084) ING ON AN OBSTACLE [RASCHET SVERKHZVUKOVOGO GETEROGENNOGO POTOKA PRI NATEKANll NA PREGRADU] L. A. KANTOR, S. A. KANTOR, and M. P. STRONGIN Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN A88-12292# 0568-5281), July-Aug. 1987, p, 182-185. In Russian. refs EXACT AND ASYMPTOTIC EXPRESSIONS OF THE LIFT SLOPE A model is developed which describes supersonic motion of a COEFFICIENT OF AN ELLIPTIC WING high-temperature gas containing powder particles. Characteristics AHARON HAUPTMAN (California Institute of Technology, of the flow are analyzed for the case when the flow impinges on Pasadena) AlAA Journal (ISSN 0001-1452),- vol. 25, Sept. 1987, an obstacle, a typical case in plasma technology, particularly in p. 1261, 1262. refs the deposition of plasma-sprayedcoatings. The results of the study (Contract NR PROJECT 062-737; NO001 4-82-(2-0043; NSF demonstrate the possibility of the supersonic plasma spraying of MSM81-18429-AO3) coatings of fine (about 4 microns) powders. V.L. The Hauptman and Miloh (1987) analytical treatment for the classical lifting surface problem of an elliptic planform in incompressible flow (which may be either steady or unsteady) is A88-12075 based on the expansion of the linearized acceleration potential in OPTIMAL LIFTING WINGS WITH REQUIRED LONGITUDINAL a series of ellipsoidal harmonics, and leads to very simple BALANCING CHARACTERISTICS [OPTIMAL'NYE NESUSHCHIE closed-form expressions for the aerodynamic coefficients in terms KRYL'IA S TREBUEMYMI PRODOL'NO BALANSIROVOCHNYMI of the arbitrary aspect ratio. The asymptotic forms into which these KHARAKTERISTIKAMI] exact expressions can be easily expanded, to any order of the E. M. PROKHOROV Akademiia Nauk SSSR, Izvestiia, Mekhanika aspect ratio or its inverse (in the respective cases of high and Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. 1987, p. 185-189. low aspect ratios), are presently obtained and compared with other In Russian. refs existing approximations. O.C. The paper is concerned with infinitely thin wings producing weak perturbations in supersonic flow of an ideal gas. For a given planform and free-stream Mach number, the optimum wing surface A88-12293# is determined by finding a limited function of the local angles of GLOBAL MARCHING TECHNIQUE FOR PREDICTING attack corresponding to a minimal drag coefficient for given pitching SEPARATED FLOWS OVER ARBITRARY AIRFOILS moment and lifting force coefficients. The problem is solved in AHMAD A. M. HALlM (USAF, Institute of Technology, terms of a class of piecewise constant functions for wings of Wright-Patterson AFB, OH) AlAA Journal (ISSN 0001-1 452), complex geometry. V.L. vol. 25, Sept. 1987, p. 1263-1266. Previously cited in issue 08, p. 1043, Accession no. A87-22725. A88-12276# FURTHER VISUALIZATION OF COMBINED WING TIP AND STARTING VORTEX SYSTEMS A88-12483 P. FREYMUTH, W. BANK (Colorado, University, Boulder), and F. THE DEVELOPMENT OF WING THEORY [DIE ENTWICKLUNG FlNAlSH AlAA Journal (ISSN 0001-1452). vol. 25, Sept. 1987, DER TRAGFLUEGELTHEORIE] p. 1153-1 159. refs R. EPPLER (Stuttgart, Universitaet, Federal Republic of Germany) (Contract F49620-84-C-0065) Zeitschrift fuer Flugwissenschaften und Weltraumforschung (ISSN The combined wing tip and starting vortex systems of a variety 0342-068X), vol. 11, May-June 1987, p. 133-144. In German. of wing planforms have been visualized in a starting flow of constant refs acceleration. Movie sequences display the initial development of The induced drag for wings of finite thickness is computed a variety of interesting vortex systems generated by these flow here from lifting line theory with vortex roll-up, and first results configurations. Vortices always formed closed systems in are presented. The lifting line is located at the trailing edge of the accordance with Helmholtz's law. Author wing. The planform with straight trailing edge and swept-back leading edge is shown to be advantageous. A dramatic difference appears between winglets above and below the wing; this difference A88-12280'# National Cheng Kung Univ., Tainan (Taiwan). is confirmed by simple experiments on free-flying models. C.D. REFINED NUMERICAL SOLUTION OF THE TRANSONIC FLOW PAST A WEDGE SA. LIANG (National Cheng Kung University, Tainan, Republic of China) and K.-Y. FUNG (Arizona, University, Tucson) AlAA A88-13077# Journal (ISSN 0001-1452), vol. 25, Sept. 1987, p. 1171-1175. WING DESIGN WITH A THREE-DIMENSIONAL TRANSONIC Previously cited in issue 19, p. 2738, Accession no. A85-40709. INVERSE METHOD refs TADAYUKI TANIOKA, JUNlCHl MIYAKAWA, JUN OGINO, and (Contract AF-AFOSR-83-0071; NGT-03-002-800) KANlCHl AMANO Japan Society for Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. 34. no. 394, 1986, p. 582-586. In Japanese. A88-12282# Wing design performed using the ISOBAR technique with a VISCID/INVISCID INTERACTION ANALYSIS OF SUBSONIC three-dimensional transonic inverse method is described, and TURBULENT TRAILING-EDGE FLOWS wind-tunnel test results are presented. The proposed approach MARK BARNET and JOSEPH M. VERDON (United Technologies was used to design the wings for the next-generation civilian aircraft Research Center, East Hartford, CT) AlAA Journal (ISSN with a length of 37.5 m, a width of 35.5 m, a wing area of 120 sq 0001-1452), vol. 25, Sept. 1987, p. 1184-1193. Previously cited in m, a maximum takeoff weight of 64.4 tons, and an occupancy of issue 08,p. 1041, Accession no. A87-22649. refs 150 passengers. The air pressure distribution was determined. (Contract N00014-83-C-0430) S.H.

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A88-13078# N88-10006# National Aerospace Lab., Amsterdam (Netherlands). AN AERODYNAMIC DESIGN STUDY OF TRANSONIC Fluid Dynamics Div. TRANSPORT WINGS A TRANSONIC MODEL REPRESENTATION FOR TWO-DIMEN- KOHEI TANAKA, MASAAKI NAKADATE, and KANlCHl AMANO SIONAL WALL INTERFERENCE ASSESSMENT Japan Society for Aeronautical and Space Sciences, Journal (ISSN J. SMITH Feb. 1986 23 p 0021-4663), vol. 34, no. 394, 1986, p. 587-591. In Japanese. (NLR-TR-860264; B8709827; ETN-87-90823) Avail: NTlS HC refs AOWMF A01 An aerodynamic wing design study for a transonic transport It is shown that for a two-dimensional airfoil a subsonic aircraft carrying 150 passengers for relatively short distances is formulation may underestimate the actual displacement effect by carried out. Two-dimensional transonic airfoil design is described, up to 50% for supercritical flow conditions. Extension of the and wind-tunnel-test results are reported. It is shown that the subsonic model representation by a transonic doublet, derived in preferred wing is of the front-and-rear loading type, and that M(DD) an approximative way, is shown to constitute a considerable control can be achieved by the adjustment of the wing cross-section improvement. ESA area distribution. S.H.

A88-13079# N88-10007'# FWG Associates, Inc., Tullahoma, Tenn. HIGH-LIFT-DEVICE DESIGN AND LOW-SPEED WIND-TUNNEL ANALYSES AND ASSESSMENTS OF SPAN WISE GUST TEST GRADIENT DATA FROM NASA 8-578 AIRCRAFT Final Report MASANOBU OGAKI, TAKESHI WATANABE, and KANlCHl WALTER FROST, HO-PEN CHANG, and ERIK A. RINGNES Aug. AMANO Japan Society for Aeronautical and Space Sciences, 1987 350 p Journal (ISSN 0021-4663), vol. 34, no. 394. 1986, p. 592-599. In (Contract NAS1-17989) Japanese. (NASA-CR-178288; NAS 1.26:178288) Avail: NTlS HC A15/MF The design of high-lift devices for transport aircraft is described, A01 CSCL 01A and wind-tunnel-test results are presented. A parametric study of Analysis of turbulence measured across the airfoil of a Cambera the positioning of the high-lift devices is carried out using a method 8-57 aircraft is reported. The aircraft is instrumented with probes of two-dimensional boundary layer calculation, and the parameters for measuring wind at both wing tips and at the nose. Statistical for flap and slat positions are determined. Reynolds number effects properties of the turbulence are reported. These consist of the in the wind tunnel are examined. S.H. standard deviations of turbulence measured by each individual probe, standard deviations and probability distribution of differences in turbulence measured between probes and auto- and two-point A88-13096' Kansas Univ., Lawrence. spatial correlations and spectra. Procedures associated with OBSERVATIONS AND ANALYSES OF NATURAL LAMINAR calculations of two-point spatial correlations and spectra utilizing FLOW OVER A NONLIFTING AIRFRAME SURFACE data were addressed. Methods and correction procedures for PAUL M. H. W. VIJGEN (Kansas, University, Lawrence) SAE, assuring the accuracy of aircraft measured winds are also General Aviation Aircraft Meeting and Exposition, Wichita, KS, Apr. described. Results are found, in general, to agree with correlations 28-30, 1987. 14 p. refs existing in the literature. The velocity spatial differences fit a (Contract NAG1-345) GaussianIBessel type probability distribution. The turbulence (SAE PAPER 871020) agrees with the von Karrnan turbulence correlation and with A NASA-sponsored flight experiment program has been two-point spatial correlations developed from the von Karman conducted with a twin-engined, propeller-driven general aviation correlation. Author aircraft, in order to ascertain the transition location and mode over the nonaxisymmetric fuselage forebody. Attention is given to the transition instrumentation layout and the flight test plan matrix. N88-10008'# National Aeronautics and Space Administration. The results obtained for transition in varying freestream and Lewis Research Center, Cleveland, Ohio. propeller conditions will furnish insights into transition mechanisms ADVANCED TURBOPROP WING INSTALLATION EFFECTS and the significance of crossflow instability during transition in MEASURED BY UNSTEADY BLADE PRESSURE AND NOISE realistic nonaxisymmetric fuselage forebodies at angles of attack LAURENCE J. HEIDELBERG and RICHARD P. WOODWARD and sideslip. O.C. 1987 23 p Presented at the 11th Aeroacoustics Conference, Sunnyvale, Calif., 19-21 Oct. 1987; sponsored by AlAA NEE- 10005# Karlsruhe Univ. (West Germany). (NASA-TM-100200; E-3737; NAS 1.I 5:100200; AIAA-87-2719) Stroemungsmechanische Bernessungsgrundlagen fuer Avail: NTlS HC A03/MF A01 CSCL 01A Bauwerke. A single rotation model propeller (SR-7A) was tested at POSSIBILITIES FOR THE MODELING OF DYNAMICALLY simulated takeoff/approach conditions (Mach 0.2). in the NASA LOADED CYLINDRICAL STRUCTURAL PARTS IN THE WIND Lewis 9- by 15-Ft Anechoic Wind Tunnel. Both unsteady blade TUNNEL [MODELLIERUNGSMOEGLICHKEITENDER DYNAMIS- surface pressures and noise measurements were made for a tractor CHEN BELASTUNG ZYLINDRISCHER BAUWERKE IM WIND- configuration with propeller/straight wing and propeller alone KANAL] configurations. The angle between the wing chord and propeller F. MENACHER and J. MAIER-ERBACHER 1987 38 p In axis (droop angle) was vaned along with the wing angle of attack GERMAN to determine the effects on noise and unsteady loading. A method (KU-SFB-210/T/24; ETN-87-90370) Avail: NTlS HC AO3/MF was developed that uses unsteady blade pressure measurements A0 1 to provide a quantitative indication of propeller inflow conditions, The loading of cylindrical structures by the natural wind and at least for a uniform (across the propeller disk) inflow angle. The its modelling in the wind tunnel were investigated to obtain wing installation caused a nearly uniform upwash at the propeller information on random loading of thin structures. The fundamentals inlet as evidenced by the domination of the pressure spectra by of random vibrations of structures under wind loading, namely the the first shaft order. This inflow angle increased at a rate of almost theory of multiple input linear systems, are presented. The 150 percent of that of the wing angle-of-attack for a propeller-wing theoretical and experimental determination of the wind speed spacing of 0.54 wing chords at a constant droop angle. The flyover correlations and the pressure on the structure are discussed. noise, as measured by the maximum blade passing frequency Theoretically as well as experimentally the vertical and horizontal level, correlates closely with the propeller inflow angle (approx. transfer functions, describing the relation between speed and 0.6 dB per degree of inflow angle) for all droop angles and wing pressure, were separately analyzed. The errors due to this angles of attack tested, including the propeller alone data. Large separation are discussed. The comparison between natural model changes in the unsteady pressure responses on the suction surface measurements becomes difficult if de-integrated vortex parts reach of the blade were observed as the advance ratio was varied. The the cylindrical structure. ESA presence of a leading edge vortex may explain this behavior since

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changes in the location of this vortex would change with loading low Reynolds numbers. The intent is to further the understanding (advance ratio). Author of the complex flow phenomena so that analytic methods for predicting their formulation and development can be improved. N88-10009'# National Aeronautics and Space Administration. These analytic techniques have applications in the design and Langley Research Center, Hampton, Va. performance prediction of airfoils operating in the low Reynolds WIND-TUNNEL INVESTIGATION OF A FULL-SCALE GENERAL number flight regime. Author AVIATION AIRPLANE EQUIPPED WITH AN ADVANCED NATURAL LAMINAR FLOW WING N88-10012'# Georgia Inst. of Tech., Atlanta. School of DANIEL G. MURRI and FRANK L. JORDAN, JR. Nov. 1987 Aerospace Engineering. 136 p INTEGRATION OF DYNAMIC, AERODYNAMIC AND STRUC- (NASA-TP-2772; L-16283; NAS 1.60:2772) Avail: NTlS HC TURAL OPTIMIZATION OF HELICOPTER ROTOR BLADES A07/MF A01 CSCL 01A Semiannual Status Report No. 2,14 Apr. - 13 Oct. 1987 An investigation was conducted in the Langley 30- by 60-Foot DAVID A. PETERS 2 Nov. 1987 34 p Wind Tunnel to evaluate the performance, stability, and control (Contract NAG1-710) characteristics of a full-scale general aviation airplane equipped (NASA-CR-181441; NAS 1.26:181441) Avail: NTlS HC A03/MF with an advanced laminar flow wing. The study focused on the A01 CSCL01A effects of natural laminar flow and advanced boundary layer The purpose of the research is to study the integration of transition on performance, stability, and control, and also on the structural, dynamic, and aerodynamic considerations in the effects of several wing leading edge modifications on the design-optimization process for helicopter rotorblades. This is to stalVdeparture resistance of the configuration. Data were measured be done in three phases. Task 1 is to bring on-line computer over an angle-of-attack range from -6 to 40 deg and an codes that could perform the finite-element frequency analyses of angle-of-sideslip range from -6 to 20 deg. The Reynolds number rotor blades. The major features of this program are summarized. was varied from 1.4 to 2.4 x 10 to the 6th power based on the The second task was to bring on-line an optimization code for mean aerodynamic chord. Additional measurements were made the work. Several were tried and it was decided to use CONMIN. using hot-film and sublimating chemical techniques to determine Explicit volume constraints on the thicknesses and lumped masses the condition of the wing boundary layer, and wool tufts were used in the optimization were added. The specific aeroelastic used to study the wing stall characteristics. The investigation constraint that the center of mass must be forward of the quarter showed that large regions of natural laminar flow existed on the chord in order to prevent flutter was applied. The bending-torsion wing which would significantly enhance cruise performance. Also, coupling due to cg-ea offset within the blade cross section was because of the characteristics of the airfoil section, artificially included. Also included were some very simple stress constraints. tripping the wing boundary layer to a turbulent condition did not The first three constraints are completed, and the fourth constraint significantly effect the lift, stability, and control characteristics. The is being completed. B.G. addition of a leading-edge droop arrangement was found to increase the stall angle of attack at the wingtips and, therefore, was considered to be effective in improving the staWdeparture N88-10013*# Kansas Univ. Center for Research, Inc., Lawrence. resistance of the configuration. Also the addition of the droop Flight Research Lab. arrangement resulted in only minor increases in drag. Author TRANSONIC ANALYSIS AND DESIGN OF AXISYMMETRIC BODIES IN NONUNIFORM FLOW N88-10010# Office of Naval Research, London (England). JEN-FU CHANG and C. EDWARD LAN Nov. 1987 77 p INTERNATIONAL CONFERENCE ON THE AERODYNAMICS AT (Contract NAG1-308) LOW REYNOLDS NUMBERS BETWEEN lO(4) AND lO(6) (NASA-CR-4101; NAS 1.26:4101; CRINC-FRL-602-3) Avail: THOMAS J. MUELLER 31 Aug. 1987 19 p Conference held NTlS HC A05/MF A01 CSCL 01A in London, England, 15-18 Oct. 1986 An inviscid nonuniform axisymmetric transonic code was (ONRL-7-023-C) Avail: NTlS HC AO3/MF A01 developed for applications in analysis and design. Propfan Presentations made at the International Conference on slipstream effect on pressure distribution for a body with and without Aerodynamics at Low Reynolds Numbers, which took place in sting was investigated. Results show that nonuniformity causes London from 15 to 18 October 1986, are reviewed. Topics include pressure coefficient to be more negative and shock strength to airfoil design methods and verification, airfoil calculation methods, be stronger and more rearward. Sting attached to a body reduced low Reynolds number research at NASA Langley Research Center, the pressure peak and moves the rear shock forward. Extent and unsteady aerodynamic characteristics, wind turbine applications, Mach profile shapes of the nonuniformity region appeared to have separation bubbles, experimental facilities and testing, and remotely little effect on the pressure distribution. Increasing nonuniformity piloted vehicles. Author magnitude made pressure coefficient more negative and moved the shock rearward. Design study was conducted with the CONMIN N88-10011'# Notre Dame Univ., Ind. Dept. of Aerospace and optimizer for an ellipsoid and a body with the NACA-0012 counter. Mechanical Engineering. For the ellipsoid, the general trend showed that to reduce the THE STRUCTURE OF SEPARATED FLOW REGIONS pressure drag, the front portion of the body should be thinner and OCCURRING NEAR THE LEADING EDGE OF AIRFOILS the contour of the rear portion should be flatter than the ellipsoid. INCLUDING TRANSITION Semiannual Status Report, May - Oct. For the design of a body with a sharp trailing edge in transonic 1987 flow with an initial shape given by the NACA-0012 contour, the THOMAS J. MUELLER Oct. 1987 37 p pressure drag was reduced by decreasing the nose radius and (Contract NSG-1419) increasing the thickness in the aft portion. Drag reduction (NASA-CR-181434; NAS 1.26:181434) Avail: NTlS HC A03/MF percentages are given. Author A01 CSCL 01A All the time and effort was directed toward acquiring, reducing, N88-10014# Imperial Coll. of Science and Technology, London and analyzing more hot-wire anemometer data. Some static (England). Dept. of Aeronautics. pressure distribution data were also acquired to support the analysis DlSDERSlON IN THE WAKE OF AIRCRAFT: AN INVESTIGATION of the velocity profile data. Laser Doppler Velocimetry data were OF THE EFFECTS OF A GROUND PLANE ON TRAILING not acquired due to equipment problems. Included were seven VORTICES. LITERATURE SURVEY combinations of chord Reynolds number, angle of attack, and J. K. HARVEY and T. R. STEINER Jun. 1986 69 p acoustic forcing using the NACA 663-018 airfoil. This research (IC-AERO-REP-66-04; ISSN-0308-7247; ETN-87-90689) Avail: has as its objective the detailed documentation of the structure NTlS HC A04/MF A01 and behavior of the transitional separation bubble and the Physical processes of trailing vortice are discussed, and the redeveloping boundary layer after reattachment over an airfoil at complexities and subtleties of aircraft wake flow are explored. A

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literature survey detects little work of direct relevance to the N88-10765'# National Aeronautics and Space Administration. problem of dispersion of aircraft wake material, especially near Ames Research Center, Moffett Field, Calif. the ground. However, problems and likely areas of useful research COMPARISON OF WIND TUNNEL AND FLIGHT TEST are identified. ESA AFTERBODY AND NOZZLE PRESSURES FOR A TWIN-JET FIGHTER AIRCRAFT AT TRANSONIC SPEEDS JACK NUGENT and ODlS C. PENDERGRAFT, JR. Mar. 1987 N88-10015# Technische Univ., Berlin (West Germany). 125 p Fachbereich Verkehrswesen. (NASA-TP-2588; H-1214; NAS 1.60:2588) Avail: NTIS HC A METHOD FOR THE CALCULATION OF TRANSONIC FLOWS AO6/MF A01 CSCL 01A FOR THE CONTROL OF ADAPTIVE WIND TUNNELS Ph.D. Afterbody and nozzle pressures measured on a l/lPscale Thesis [VERFAHREN ZUR BERECHNUNG TRANSSONISCHER model and in flight on a twin-jet fighter aircraft were compared as STROEMUNGEN FUER DIE REGELUNG ADAPTIVER Mach number varied from 0.6 to 1.2, Reynolds number from 17.5 WINDKANAELE] million to 302.5 million, and angle of attack from 1 to 7 deg. At RAINER REBSTOCK 1986 122 p In GERMAN Sponsored Mach 0.6 and 0.8,nozzle pressure coefficient distributions and by the Bundesministerium fuer Forschung und Technologie, West nozzle axial force coefficients agreed and showed good Germany recompression. At Mach 0.9 and 1.2, flow complexity caused a (ETN-87-90411) Avail: NTIS HC AO6/MF A01 loss in recompression for both flight and wind tunnel nozzle data. Numerical methods for the adjustment of three-dimensional, The flight data exhibited less negative values of pressure coefficient adaptive test sections for wind tunnel walls were developed. The and lower axial force coefficients than did the wind tunnel data. required wall form was designed by the stepwise modification of Reynolds number effects were noted only at these Mach numbers. a starting contour. The bad convergence characteristics of the Jet temperature and mass flux ratio did not affect the comparisons classical iterative adaptive method in the three-dimensional case of nozzle axial flow coefficient. At subsonic speeds, the levels of were demonstrated theoretically and by a numerical simulation. It pressure coefficient distributions on the upper fuselage and lower is shown that the replacement of the constant control factor by a nacelle surfaces for flight were less negative than those for the matrix, which takes into account the remote Mach number and model. The model boundary layer thickness at the aft rake station the test section geometry, allows the calculation of the adapted exceeded that for the forward rake station and increased with wall contour practically in one step. A method for the testing of increasing angle of attack. The flight boundary layer thickness at three-dimensional models in wind tunnels with two flexible walls is the aft rake station was less than that for the forward rake station proposed. Wall deviations, allowing the suppression of interferences and decreased with increasing angle of attack. Author on the model axis, are proposed. ESA N88-10767# Texas Univ., Austin. Dept. of Aerospace Engineering and Engineering Mechanics. N88-10016# Technische Hochschule, Darmstadt (West Germany). THE AEROTHERMODYNAMIC ENVIRONMENT FOR HOLES IN Fachbereich Maschinenbau. HYPERSONIC CONFIGURATIONS INVESTIGATIONS OF SEPARATED FLOW STATES ON WINGS JOHN J. BERTIN, WILLIAM J. TEDESCHI, ALBINO C. OF MEDIUM ASPECT RATIO TAKING INTO ACCOUNT THE BUSTAMANTE, and ERIC W. REECE (Sandia National Labs., WIND TUNNEL INTERFERENCE PROBLEM Ph.D. Thesis Albuquerque, N. Mex.) Aug. 1987 34 p Presented at the [UNTERSUCHUNGEN ABGELOESTER STROEMUNGSZUS- AlAA Aerodynamics Flight Mechanics Conference, Monterey, Calif., TAENDE AN TRAGFLUEGELN MllTLERER STRECKUNG UNTER 17-19 AUg. 1987 BERUECKSICHTIGUNG DES WINDKANALINTERFERENZPROB- (Contract DE-AC04-76DP-00789) LEMS PROBLEMS] (DE87-014651; SAND-86-2875C-FP; CONF-870830-2-FP) Avail: JOHANNES KElL 1985 208 p In GERMAN NTlS HC A03/MF A01 (ETN-87-90437) Avail: NTlS HC AlO/MF A01 A series of test programs have been conducted in Tunnel B Wind tunnel experiments were conducted for the investigation of the Arnold Engineering Development Center (AEDC) in which of separated, subsonic flow about wings in the range of high wedges and spherically-blunted cones (with surface openings and angles of attack. The pressure distributions and aerodynamic base vents) were exposed to a Mach 8 stream. Measurements of coefficients of the wings were measured. The effect of the design the heat transfer and pressure from the recompression face of parameters on the separation behavior was deduced from the external surface port were compared with the corresponding measurements on five wings of equal aspect ratio, but different sweep. The measurements were evaluated with a calculation values computed using the rotational method-of-characteristicsfor method which considers the buoyancy as well as the displacement a nonadiabatic, two-dimensional flow. The computed flow field provided reasonable estimates of the experimental measurements. correction. Corrections were determined for the open and the Over the range of test conditions, the expansion-fan flow directly closed wind tunnel test section with circular cross section with a impinged on only a small fraction of the surface port recompression straight rectangular wing. ESA face and it immersed the entire recompression face. The recompression pressures and heat-transfer rates could be N88-10018# Royal Aircraft Establishment, Farnborough correlated as a function of the cavity pressure ratio. DOE (England). ON THE PROSPECTS FOR INCREASING DYNAMIC LIFT N88-10771'# National Aeronautics and Space Administration. D. G. MABEY May 1986 37 p Langley Research Center, Hampton, Va. (RAE-TM-AERO-2068; BR100237; ETN-87-90955) Avail: NTlS EFFECT OF EMPENNAGE ARRANGEMENT ON SINGLE-ENGINE HC A03/MF A01 NOULE/AFTERBODY STATIC PRESSURES AT TRANSONIC Research, mainly at low speeds, into the development of SPEEDS dynamic lift is reviewed. Sudden movement of aerodynamic WILLIAM P. HENDERSON and JAMES R. BURLEY, I1 Nov. surfaces can generate dynamic lift due to the transient development 1987 230 p of separated flow. These dynamic effects are large and well (NASA-TP-2753; L-16223; NAS 1.60:2753) Avail: NTlS HC established for airfoils. They are considered likely to be small for A1 1/MF A01 CSCL 01A highly swept wings and negligible for slender wings, but there is An investigation has been conducted in the Langley 16-Foot little experimental evidence to support this inference. Dynamic lift Transonic Tunnel to determine the effects on empennage might be increased if conventional sinusoidal motions can be arrangement on single-engine nonle/afterbody static pressures. replaced by appropriate periodic sawtooth motions. The control of Tests were done at Mach numbers from 0.60 to 1.20, nozzle large-scale flow separations by rapid movements of aerodynamic pressure ratios from 1.0 (jet off) to 8.0. and angles of attack from surfaces requires further investigation and a program of wind tunnel -3 to 9 deg (at jet off conditions), depending on Mach number. tests to resolve controversial issues is suggested. ESA Three empennage arrangements (aft, staggered, and forward) were

17 02 AERODYNAMICS

investigated. Extensive measurements were made of static pressure valid in the range of supersonic and hypersonic speeds. The on the nozzlelafterbody in the vicinity of the tail surfaces. method does not require calculation of the details of the stream Author lines and can be used for various swept wings at moderate angle of attack or yaw angle. A comparison between theoretical and N88-10772'# National Aeronautics and Space Administration. experimental results is given. Author Langley Research Center, Hampton, Va. WALL INTERFERENCE TESTS OF A CAST 10-2/DOA 2 AIRFOIL IN AN ADAPTIVE-WALL TEST SECTION RAYMOND E. MINECK Dec. 1987 100 p (NASA-TM-4015; L-16334; NAS 1.1 54015) Avail: NTlS HC A05/MF A01 CSCL 01A A wind-tunnel investigation of a CAST 10-21DOA 2 airfoil model has been conducted in the adaptive-wall test section of the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT) and in the National N88-10777'# National Aeronautics and Space Administration. Aeronautical Establishment High Reynolds Number Two-Dimensional Ames Research Center, Moffett Field, Calif. Test Facility. The primary goal of the tests was to assess two different ANALYTICAL MODELING OF HELICOPTER STATIC AND wall-interference correction techniques: adaptive test-section walls DYNAMIC INDUCED VELOCITY IN GRASP and classical analytical corrections. Tests were conducted over a DONALD L. KUNZ and DEWEY H. HODGES (Georgia Inst. of Mach number range from 0.3 to 0.8 and over a chord Reynolds Tech., Atlanta.) Nov. 1987 10 p number range from 6 million to 70 million. The airfoil aerodynamic (NASA-TM-100026; A-87341 ; NAS 1.151 00026; characteristic from the tests in the 0.3-m TCT have been corrected USAAVSCOM-TR-87-A-11) Avail: NTlS HC AO2/MF A01 CSCL for wall interference by the movement of the adaptive walls. No addi- 01A The methodology used by the General Rotorcraft Aeromechanical tional corrections for any residual interference have been applied to the data, to allow comparison with the classically corrected data from Stability Program (GRASP) to model the characteristics of the flow the same model in the conventional National Aeronautical Establish- through a helicopter rotor in hovering or axial flight is described. Since ment facility. The data are presented graphically in this report as the induced flow plays a significant role in determining the aeroelastic integrated force-and-movement coefficients and chordwise pressure properties of rotorcraft, the computation of the induced flow is an impor- distributions. Author tant aspect of the program. Because of the combined finite-element/mul- tibody methodology used as the basis for GRASP, the implementation of induced velocity calculations presented an unusual challenge to N88-10773'# National Aeronautics and Space Administration. the developers. To preserve the modelling flexibility and generality Langley Research Center, Hampton, Va. of the code, it was necessary to depart from the traditional methods INTERGRATION EFFECTS OF D-SHAPED, UNDERWING, of computing the induced velocity. This is accomplished by AFT-MOUNTED, SEPARATE-FLOW, FLOW-THROUGH NACELLES calculating the actuator disc contributions to the rotor loads in a ON A HIGH-WING TRANSPORT separate element called the air mass element, and then performing MILTON LAMB, JOHN R. CARLSON, and ODlS C. the calculations of the aerodynamic forces on individual blade PENDERGRAFT, JR. Nov. 1987 24 p elements within the aeroelastic beam element. Author (NASA-TM-4018; L-16342; NAS 1.15401 8) Avail: NTlS HC A03/MF A01 CSCL 01A An experimental investigation was conducted in the Langley 16-Foot Transonic Tunnel at freestream Mach numbers from 0.70 to 0.82 and angles of attack from -3.0 to 4.0 deg to determine the integration effects of D-shaped, underwing, aft-mounted, separate-flow, flow-through nacelles on a high-wing transonic transport configuration. The results showed that the aft-mounted nacelle/pylon produced an increase in lift over that of the wing-body N88-10779'# National Aeronautics and Space Administration. configuration by pressurizing much of the wing lower surface in Lewis Research Center, Cleveland, Ohio. front of the pylon. For the D-shaped nacelle, a substantial region A NATURAL LOW FREQUENCY OSCILLATION IN THE WAKE of supersonic flow over the wing, aft of the lip of the nacelle, OF AN AIRFOIL NEAR STALLING CONDITIONS cancelled the reduction in drag caused by the increase in pressures K. B. M. Q. ZAMAN and D. J. MCKlNZlE 1987 17 p Prepared ahead of the lip, to increase interference and form drag compared for presentation at the 26th Aerospace Sciences Meeting, Reno, with a similar circular-shaped nacelle. The installed drag of the Nev., 11-14 Jan. 1988; sponsored by AlAA D=shaped nacelle was essentially the same as that of an (NASA-TM-100213; E-3822; NAS 1.15:100213; AIAA-88-0131) aft-mounted circular nacelle from a previous investigation. Avail: NTlS HC A03/MF A01 CSCL 01A Author An unusually low frequency oscillation in the flow over an airfoil was explored experimentally. Wind tunnel measurements were N88-10776'# National Aeronautics and Space Administration, carried out with a two dimensional airfoil model at a chord Reynolds Washington, D.C. number of 100,000. During deep stall the usual bluff-body shedding CALCULATION OF AERODYNAMIC HEAT TRANSFER FOR occurred at a Strouhal number. But at the onset of stall a low BLUNT-NOSED THIN WINGS AT DIFFERENT ANGLES OF frequency periodic oscillation occurred, the corresponding Strouhal ATTACK AT SUPERSONIC SPEEDS number being an order of magnitude lower. The phenomenon SHUXUAN XU Nov. 1987 17 p Transl. into ENGLISH from occurred in relatively unclean flow when the freestream turbulence Acta Aerodynamica Sinica (People's Republic of China), v. 4, Dec. was raised to 0.4 percent, but did not in the cleaner flow with 1986 p 398-405 Original language document was announced in turbulence intensity of 0.1 percent. It could also be produced by IAA as A87-28338 Transl. By Kanner (Leo) Associates, Redwood certain high frequency acoustic excitation. Details of the flow field City, Calif. Prepared by China Univ. of Science and Technology, are compared between a case of low frequency oscillation at People's Republic of China alpha = 15 deg and a case of bluff-body shedding at alpha = (Contract NASW-4005) 22.5 deg. The origin of the low frequency oscillation traces to the (NASA-lT-20127; NAS 1.77:20127) Avail: NTIS HC A03/MF upper surface of the airfoil and is seemingly associated with the A01 CSCL01A periodic formation and breakdown of a large separation bubble. A method for calculating aerodynamic heat transfer on thin The intense flow fluctuations impart significant unsteady forces to wings at angles of attack is provided, based on the assumption the airfoil but diminish rapidly within a distance of one chord from of small cross flow and the calculation of an infinite cylinder. It is the trailing edge. Author

18 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

03 antimisting kerosene (AMK), crashworthiness StructuraVrestraint, analytical modeling, cabin fire safety, flight data recorders, AIR TRANSPORTATION AND SAFETY post-impact investigation, instrumentation/data acquisition systems, remotely piloted vehicle/flight control systems, range and flight safety provisions, etc. This report describes the aircraft, Includes passenger and cargo air transport operations; and aircraft experiments, systems, activities, and events which lead up to the accidents. Controlled Impact Demonstration (CID). An overview of the final unmanned remote control flight and sequence of impact events are delineated. Preliminary post CID observations are presented. A88-10658 Author FLIGHT SAFETY AND RISK FFLUGSICHERHEIT UND RlSlKOl ALEXANDER RIECHE (Berlin, Humboldt-Universitaet, German Democratic Republic) Technisch-oekonomische Information der N88-10781# National Transportation Safety Board, Washington, zivilen Luftfahrt (ISSN 0232-5012), vol. 23, no. 3, 1987, p. 126-128. D. C. Bureau of Field Operations. In German. AIRCRAFT ACCIDENT REPORTS, BRIEF FORMAT, US CIVIL Theoretical aspects of flight safety and risks are discussed, AND FOREIGN AVIATION. ISSUE NUMBER 1: 1986 and their manifestations as concrete risks are considered. Risk is ACCIDENTS addressed from the standpoint of Marxist socialist ideology in an 28 May 1987 410 p abstract way. A philosophical and abstract discussion of risk (PB87-916903; NTSB/AAB-87/03) Avail: NTlS HC A18/MF A01; reduction is presented. C.D. also available on subscription, North American Continent HC $185.00/year, all others write for quote CSCL 01C A88-12644 The publication contains selected aircraft accident reports in AIRCRAFT AND EQUIPMENT FACTORS IN THE OCCURRENCE Brief Format occurring in U.S. civil and foreign aviation operations OF SUSPENSION LINE TWISTS WITH U.S. ARMY during Calendar Year 1986. Approximately 200 General Aviation PARACHUTES and Air Carrier accidents contained in the publication represent a WILLIAM P. BURKE (U.S. Army, Research Institute for the random selection. The publication is issued irregularly, normally Behavioral and Social Sciences, Fort Benning, GA) Human Factors eighteen times each year. The Brief Format represents the facts, (ISSN 0018-7208), VOI.29, Aug. 1987, p. 483-492. conditions, circumstances and probable cause(s) for each Data were collected by self-report for the trainees of two classes accident. GRA of the Basic Airborne Course at Fort Benning, GA, who were asked if they had developed twists in their suspension line during N88-10782# Transportation Research Board, Washington, D.C. each of the five jumps of the course. These data were then related ISSUES IN AIR TRANSPORT AND AIRPORT MANAGEMENT to the conditions of deployment for each jump - type of parachute J. P. SCHWIETERMAN, F. A. SPENCER, M. GHAFOURI, T. N. used, type of equipment carried, type of aircraft jumped from, and LAM, and J. R. G. BRANDER 1986 58 p so forth. The proportion of jumpers with twists during a given (PB87-204509; TRB/TRR-l094; ISBN-309-04114-7; LC-87-7628) jump with its associated conditions of deployment was compared Avail: NTlS HC A04/MF A01 CSCL 01C by the chi-square test with the proportion of jumpers with twists The six papers in this report deal with the following: alternatives from other jumps made under different conditions of deployment. to the hub; a survey of nonstop air service opportunities; No effect of type of parachute on the occurrence of twists was accessibility in the deregulated domestic airline network; air detected, but a strong and significant effect of combat equipment transport deregulation and airport congestion; the search for was associated with an increase in the proportion of twists. There efficient solutions; methodology for planning and operations was, in addition, a significant but slightly smaller effect attributable management of airport terminal facilities; a prescription for efficient to the type of aircraft used for jumps, with more twists occurring management of the Canadian Government's civilian aircraft fleet; during jumps from the C-141 than during jumps from the (2-123. and analyzing the financial impact on airports of remote airport Author ground transportation. GRA

N88-10020# Luftfahrt-Bundesamt, Brunswick (West Germany). Flugunfalluntersuchungsstelle. AIRCRAFT ACCIDENTS Annual Report, 1984 [FLUGUNFALL 04 JAHRESBERICHT, 19841 Sep. 1986 120 p In GERMAN (JB-84; ISSN-0178-8094; ETN-87-90396) Avail: NTlS HC AIRCRAFT COMMUNICATIONS AND NAVIGATION AO6/MF A01 All accidents in 1984 with German aircraft at home and abroad, Includes digital and voice communication with aircraft; air navigation as well as with foreign aircraft in Germany, which were announced systems (satellite and ground based); and air traffic control. to the aircraft investigation service, are listed. Concepts used in the examination of aircraft accidents are explained. The accidents are listed for aircrafts above 5.7T, between 2 and 5.7T, below 2T, A88-10437 helicopters, powered gliders, gliders, parachutes, hang gliders, ROBOTIC AIR VEHICLE - A PILOT'S PERSPECTIVE ultralight aircraft, balloons, and other types of aircraft. ESA JESSE BLAIR (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) and KARL E. SCHRICKER (Texas N88-10021'# National Aeronautics and Space Administration. Instruments, Inc., Dallas) IEEE Aerospace and Electronic Systems Langley Research Center, Hampton, Va. Magazine (ISSN 0885-8985), vol. 2, Sept. 1987, p. 8-11. FULL-SCALE TRANSPORT CONTROLLED IMPACT DEMON- The algorithms and technological features needed to develop STRATION PROGRAM Final Summary Report robotic air vehicles (RAVs) are examined. The proposed RAV is Sep. 1987 82 p Prepared in cooperation with NASA, Ames an unmanned air vehicle capable of passive terrain following, terrain Research Center, Moffett Field, Calif. and FAA, Atlantic City, N.J. avoidance, obstacle avoidance, and autonomous navigation. The (NASA-TM-89642; NAS 1.1589642; DOT/FAA/CT-87/10) Avail: need to combine the remotely piloted vehicle airframe and NTlS HC AOWMF A01 CSCL 01C propulsion concept with AI is discussed. RAV simulations and The Federal Aviation Administration (FAA) and NASA conducted demonstrations have been designed. The simulations will evaluate a full-scale air-to-surface impact-survivable impact demonstration the functioning of the RAV software algorithms during various with a remotely piloted transport aircraft on 1 December 1984, at mission scenarios, and the demonstrations will test the ability of Edwards Air Force Base, California. The test article consisted of RAVs to fly a jet aircraft, execute an instrument/qualification check, experiments, special equipment, and supporting systems, such as a mission ready check, and a tactical qualification check. I.F.

19 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

A88-10676 A88-10680# MODERN TECHNOLOGY IN POSITIONING AND NAVIGATION; DEVELOPMENT AND TRENDS IN RADIO POSITION FINDING NAVIGATION MEETING, DUESSELDORF, FEDERAL REPUBLIC [ENTWICKLUNGEN UND TRENDS DER FUNKORTUNG] OF GERMANY, MAY 6-8, 1987, REPORTS [MODERNE TECH- MANFRED BOEHM (Standard Elektrik Lorenz AG, Stuttgart, NOLOGIE IN ORTUNG UND NAVIGATION; NAVIGATIONSTAG- Federal Republic of Germany) (Deutsche Gesellschaft fuer Ortung UNG, DUESSELFDORE FEDERAL REPUBLIC OF GERMANY, und Navigation, Navigationstagung ueber moderne Technologie in MAY 64,1987, VORTRAEGE] Ortung und Navigation, Duesseldorf, Federal Republic of Germany, Meeting organized and sponsored by the Deutsche Gesellschaft May 6-8, 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, fuer Ortung und Navigation. Ortung und Navigation (ISSN no. 2. 1987, p. 230-249. In German. refs 0474-7550), vol. 28, no. 2. 1987, 294 p. In German. For individual The history and fundamental principles of radio position-finding items see A88-10677 to A88-10688. (RPF) are reviewed, with an emphasis on currently available Technological and applications aspects of state-of-the-art technology and development trends. Consideration is given to basic positioning and navigation equipment are discussed in reviews methods for avoiding measurement errors due to reflections; the and reports, with an emphasis on developments in the FRG. The problems posed by range limitations; the transition from analog to general topics addressed include user perspectives on the impact digital RPF technology; satellite RPF systems; the shift from of modern technology; the current technological status and future ground-based to onboard RPF computers; the characteristics of development trends; and applications to land, sea, and air specific RPF systems; and the trend toward integrated systems transportation. Consideration is given to the physical and combining communication, navigation, and surveillance functions. technological bases of past and present navigation methods; the Extensive diagrams, drawings, photographs, and tables listing impact of modern technology on ATC, ship-crew training, and RPF-system features are provided. T.K. transport-aircraft avionics; radio, radar, and satellite positioning systems; vessel traffic services; onboard collision-avoidance systems; and proposals for a European data network to acquire, process, and display air-traffic information. T.K. A88-10682# INERTIAL NAVIGATION - TECHNOLOGICAL STATUS AND A88-10677# DEVELOPMENT TRENDS [TRAEGHEITSNAVIGATION- STAND BMFT-SUPPORTED PROJECTS IN THE FIELDS POSITION-FIND- DER TECHNIK UND ENTWICKLUNGSTENDENZEN] ING, NAVIGATION, AND TRAFFIC SAFETY [VOM BMFT GEFOER- 6.STIELER (DFVLR, lnstitut fuer Flugfuehrung, Brunswick, Federal DERTE PROJEKTE DER BEREICHE ORTUNG, NAVIGATION UND Republic of Germany) (Deutsche Gesellschaft fuer Ortung und VERKEHRSSICHERUNG] Navigation, Navigationstagung ueber moderne Technologie in H. A. HERTRICH (BMFT, Bonn, Federal Republic of Germany) Ortung und Navigation, Duesseldorf, Federal Republic of Germany, (Deutsche Gesellschaft fuer Ortung und Navigation, May 6-8, 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, Navigationstagung ueber moderne Technologie in Ortung und no. 2, 1987, p. 262-289. In German. refs Navigation, Duesseldorf, Federal Republic of Germany, May 6-8, The history and current status of inertial navigation systems 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, no. 2, (INSs) are surveyed, with an emphasis on developments in the 1987, p. 159-168. In German. FRG, and illustrated with extensive diagrams, drawings, and The current status of air navigation, positioning, and traffic-safety photographs. Topics addressed include the invention and further RBD projects sponsored by the FRG Ministry of Science and refinement of the gyrocompass and INSs based on it, Technology (BMFT) is reviewed; sample results are summarized; state-of-the-art strapdown systems, the impact of the ring-laser and future trends are indicated. The primary aims of the BMFT gyro (RLG) on modern INS technology, efforts to reduce the size programs include (1) assuring FRG input into international ATC of RLGs, and the fiber-optic gyro as an alternative to the RLG. systems, (2) supporting domestic development of smaller aircraft Consideration is given to proposed designs for digital-outputoptical and helicopters, (3) solving ATC problems, and (4) providing accelerometers; applications of INS technology to specialized competent advice to the civil-aviation community. Specific projects measurement problems; and the mechanical configurations of in advanced avionics (fiber-optic ring-laser gyros, cockpit advanced platform-type INSs for long-term autonomous navigation, equipment, obstacle-warning radars, and weight/center-of-gravity geodesy, and surveying. T.K. measurement systems), ATC (precision DME for the ICAO MLS), and flight-control (for the A-300, A-310, and A-320) are described in more detail and illustrated with photographs. T.K. A88-10684# A88-10678# HYBRID POSITIONING AND NAVIGATION SYSTEMS - THE IMPORTANCE OF MODERN POSITIONING AND TECHNOLOGICAL STATUS AND DEVELOPMENT TRENDS IN NAVIGATION TECHNOLOGY FOR ATC [BEDEUTUNG POSITION-FINDING AND NAVIGATION PROCEDURES MODERNER TECHNOLOGIE FUER ORTUNG UND NAVIGATION [HYBRIDE ORTUNGS UND NAVIGATIONSSYSTEME - STAND IN DER FLUGSICHERUNG] DER TECHNIK UND ENTWICKLUNGSTENDENZEN VON J. LISCHKA (Bundesanstalt fuer Flugsicherung, Frankfurt am Main, ORTUNGS UND NAVIGATIONSVERFAHREN] Federal Republic of Germany) (Deutsche Gesellschaft fuer Ortung K. HURRASS (DFVLR, lnstitut fuer Flugfuehrung, Brunswick, und Navigation, Navigationstagung ueber moderne Technologie in Federal Republic of Germany) (Deutsche Gesellschaft fuer Ortung Ortung und Navigation, Duesseldorf, Federal Republic of Germany, und Navigation, Navigationstagung ueber moderne Technologie in May 6-8, 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, Ortung und Navigation, Duesseldorf, Federal Republic of Germany, no. 2, 1987, p. 181-186. In German. May 6-8, 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, The developmental history and current status of ATC technology no. 2, 1987, p. 323-337. In German. refs in the FRG are examined in a general overview. Topics addressed The fundamental principles of Kalman digital filtering are include the fundamental purposes of ATC, the goals outlined for explained, and the application of Kalman filters to different types the FRG ATC services in 1954, the capabilities of the present of advanced integrated navigation systems is described and state-of-the-art air-situation display system DERD-MC, and the illustrated with diagrams and graphs. The advantages of combining problems encountered in gaining public and user acceptance of the short-term accuracy and steady response of onboard navigation new advanced systems. Consideration is given to the greater systems with the long-term accuracy of radio or satellite positioning susceptibility of complex systems to total (rather than partial) systems in an integrated system are discussed; the mathematical breakdown, the introduction of MLS, microprocessor-basedspeech derivation of Kalman filters is shown; the basic application and data transmission, advanced radars and radar displays, and techniques are outlined; and examples in air, land, and ship the use of simulators in ATC training. T.K. navigation are presented. T.K.

20 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

A88-10687# aircraft simulations. Flight director steering commands and path AUTONOMOUS ONBOARD COLLISION AVOIDANCE FOR guidance were computed for a straight-in approach and three AIRCRAFT AND SHIPS [BORDAUTONOMER KOLLISIONS- complex curved paths (offset, hook, and river) using three different SCHUTZ IN LUFTFAHRT UND SCHIFFAHRT] algorithms. The algorithms computed lateral deviation based on: PETER FORM (Braunschweig, Technische Universitaet, Brunswick, (1) capturing the next straight path, (2) based on a continuous Federal Republic of Germany) (Deutsche Gesellschaft fuer Ortung curved path, and (3) based on ground speed and nominal bank und Navigation, Navigationstagung ueber moderne Technologie in angle. If flight director steering commands were used, all three Ortung und Navigation, Duesseldorf, Federal Republic of Germany, forms of guidance could be used to fly any of the curved approach May 6-8, 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, paths and flight director guidance reduced all path tracking errors. no. 2, 1987, p. 389-397. In German. refs A diagram of the arrangement of the flight instruments and profiles The current development status of onboard collision-warning of different types of guidance are presented. I.F. systems for ships end aircraft is surveyed, and the results of recent numerical simulations of the TCAS II secondary-radarltrans- A88-12474 ponder system for aircraft are summarized. Topics addressed include THE CONFLICT RESOLUTION PROCESS FOR TCAS II AND the different requirements of marine and air traffic, the international SOME SIMULATION RESULTS standard Automated Radar Plotting Aid for ships, and the basicoperat- R. L. FORD (Royal Signals and Radar Establishment, Malvern, ing principles and range of applicability of TCAS II. The simulation England) Journal of Navigation (ISSN 0373-4633), vol. 40, Sept. results for typical heavy traffic conditions (such as those encountered 1987, p. 283-302; Discussion, p. 302, 303. Research supported over Britain and the FRG) indicate that TCAS II would give a traffic by the Civil Aviation Authority. refs advisory once every 6.5-8 flight hours (or 0.2 ATC hours) and a The principles underlying the Traffic Alert and Collision resolution advisory about once every 15 flight hours (or 1 ATC hour). Avoidance System which was designed to resolve conflicts between The potential advantages of a TCAS-type system for ships are consi- airborne aircraft are discussed. Simulation results obtained with a dered. T.K. fast-time computer model for random traffic are presented. They include statistics on miss distance and warning time for a simple traffic pattern. K.K. A88-10688# DEVELOPMENT STUDIES OF A EUROPEAN DATA NETWORK FOR ACQUISITION, PROCESSING, AND DISPLAY OF A88-12733 AIR-TRAFFIC DATA [ANSAETZE ZU ElNEM EUROPAEISCHEN REAL-TIME RECONNAISSANCE - AN ENGINEERING DATENVERBUNDNER ZUR ERFASSUNG, VERARBEITUNG PERSPECTIVE UND DARSTELLUNG VON LUFWERKEHRSDATEN] NORMAN W. BOESE and ANTHONY S. CLARK (Control Data HANSJUERGEN F. VON VlLLlEZ (Eurocontrol, Maastricht, Corp., Minneapolis, MN) IN: Airborne reconnaissance X; Netherlands) (Deutsche Gesellschaft fuer Ortung und Navigation, Proceedings of the Meeting, San Diego. CA, Aug. 19, 20, 1986 . Navigationstagung ueber moderne Technologie in Ortung und Bellingham, WA, Society of Photo-Optical Instrumentation Navigation, Duesseldorf, Federal Republic of Germany, May 6-8, Engineers, 1987, p. 28-32. 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, no. 2, New electrooptical (EO) systems are currently being developed 1987, p. 418-427. In German. for tactical reconnaissance. To ensure that these systems can be A prototype data network developed as part of a developed within budget, it is essential that operational and Eurocontrol/FRG/Benelux program to facilitate the international technical requirements be developed together. This paper is an exchange of ATC radar data is described. The Radar Data attempt at defining technical capabilities and costs in terms of Interchange Network (Radin) is designed to link the civilian ATC operational requirements. Author centers at Bremen, Duesseldorf, Brussels, Amsterdam, and Maastricht and the Dutch and Belgian military ATC centers, A88-12737 providing real-time flexible-format access to a wide range of SYNCHRONIZING VIDEO SIGNALS TO STANDARD IRlG TIME information from hardware of different generations. When CODES implemented, Radin should greatly reduce the need for verbal LESTER TURNER (Video Datacom, Fountain Valley, CA) IN: coordination of the transfer of ATC between neighboring centers. Airborne reconnaissance X; Proceedings of the Meeting, San Diego, Plans call for gradual implementation in five phases, using the CA, Aug. 19, 20, 1986 . Bellingham. WA, Society of Photo-Optical integration network structure and Common ICAO Data Interchange Instrumentation Engineers, 1987, p. 49-54. Network protocols for the data transmission. T.K. An IRlG codelvideo signal synchronizer has been developed that generates EIA RS 170/RS170A/RS330 and NTSC compatible A88-10728 video synchronizing signals that are directly referenced to an input FAST STABLE SOLUTION OF A DISPERSION EQUATION OF standard IRlG Type A or B modulated serial time code. When an LINEAR FILTERING [BYSTROE USTOICHIVOE RESHENIE IRlG modulated serial time code is introduced into the synchronizer, DISPERSIONNOGO URAVNENllA LlNElNOl FIL'TRATSII] detection of the beginning of a time code frame initiates generation A. N. KOROLLEV, ED. Radiotekhnika (ISSN 0033-8486), June of the first field in the first frame (00) in the output video signal. 1987, p. 21-23. In Russian. The video synchronizing signals are phase locked to the input The paper examines the solution of a dispersion equation for time code modulated carrier. A very stable crystal controlled the filtering of the primary parameters, Le., the delay time and oscillator time base in the synchronizer insures that the phase Doppler-frequency difference, in a four-position flight-vehicle radar lock loop is jitter free and video signal output continues even if system. It is shown that, for short periods of time, it is possible to the input time code is removed. The output composite video increase the speed of the solution by 3-9 times without decreasing synchronizing signal is able to synchronize the operation of different the accuracy. B.J. video signal sources and directly references their video output signals to the available IRlG modulated serial time code. Author A88-10874 FLIGHT DIRECTOR GUIDANCE FOR MLS A88-13087# JAMES H. BRAHNEY Aerospace Engineering (ISSN 0736-2536), A HYBRID NAVIGATION SYSTEM WITH GPS vol. 7, Sept. 1987, p. 30-35. TORU TANABE and MASATOSHI HARIGAE Japan Society for The advantages of using MLS compared to the instrument Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. landing system are: easier installation of the system; more 35, no. 396, 1987, p. 8-14. In Japanese. refs channels; improved glide slope and azimuth; and increased The design, characteristics, and performance of a hybrid flexibility. The flexibility provided by the multiple, curved navigation system using the GPS are described. The designs of three-dimensional approach paths of MLS is evaluated using pilot the GPS-INS, GPS-STAR, and GPS-INS-STAR systems are

21 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION discussed and compared. The performance of the GPS receiver N88-10784 Alabama Univ., Huntsville. with a digital signal processor is examined. S.H. GLOBAL POSITIONING SATELLITE-BASED AUTOMATIC LANDING SYSTEM AND WIND ESTIMATED FEEDBACK FOR THE AH-64 HELICOPTER Ph.D. Thesis A88-13088# ABDOLLAH HOMAIFAR 1986 288 p CIVIL AVIATION APPLICATION OF THE GLOBAL POSITIONING Avail: Univ. Microfilms Order No. DA8713429 SYSTEM (GPS) AND ITS ISSUES A real time simulation of a helicopter is used to investigate KOlCHl KIMURA Japan Society for Aeronautical and Space the Global Positioning Satellite guidance and control during a fully Sciences, Journal (ISSN 0021-4663), vol. 35, no. 396, 1987, p. automatic spiral descent and landing .flare maneuver in the 15-21. In Japanese. refs presence of crosswind and turbulence. The spiral descent offers Recent trends in the utilization of the GPS for civil aviation are a landing pattern, restricted in area, which is useful near congested reviewed. Attention is given to GPS precision, the user equivalent airports, for both civil and military operations. It was shown that range, and the probable error. The relationship between satellite combined optimal estimation and control techniques are feasible radio-position determination and the GPS is examined. S.H. for reduction of spiral descent guidance errors. The optimal estimation is accomplished using an extended Kalman filter, resulting in an estimated state of an aircraft and crosswind. This A88-13090# estimated state constitutes an input to an optimal linear regulator. GPS/INS HYBRID NAVIGATION FOR AIRCRAFT Improvements in accuracy are made by adding an altimeter and NAOHIRO YAMASHITA and HlROSHl KlJlMA Japan Society for body mounted accelerometers. Modifications of the steady-state, Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. reduced-order Kalman filter are described which provide a 35, no. 396, 1987, p. 29-36. In Japanese. refs satisfactory estimator in such cases. The results of applying these The efficiency of the GPS/INS hybrid navigation system is techniques to the design of an estimator for aircraft position and evaluated by computer simulation. In the GPS the error was found crosswind are presented. A design of an optimal controller for to increase with maneuvering of the aircraft, while in the INS the spiral descent and landing flare with augmented crosswind is also error was found to increase with time. Future prospects for the included. The linear optimal regulator theory is utilized to derive hybrid system are assessed. S.H. state feedback gain for guidance and control. The estimator and controller performances are verified using a Monte Carlo simulation. Dissert. Abstr. A88-13093# GPS RECEIVERS FOR AIR NAVIGATION CHOGO SEKINE Japan Society for Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. 35, no. 396, 1987, p. 51-56. In Japanese. The paper describes the design and characteristics of the GPS receiver for air navigation using the C/A code. Various functions N88-10810# Carleton Univ., Ottawa (Ontario). Dept. of System of the GPS receiver are considered, including the single-channel and Computer Engineering. sequence, the high-speed single-channel sequence, and the AN EXPERT SYSTEM FOR AIRCRAFT CONFLICT RESOLUTION five-channel sequence. S.H. IN DENSE AIRSPACES B. A. BOWEN In AGARD, Knowledge Based Concepts and Artificial Intelligence: Applications to Guidance and Control 13 p A88-13094# Aug. 1987 Sponsored by Transport Canada FLIGHT TEST RESULTS FOR A GPS RECEIVER IN A Avail: NTlS HC A07/MF A01 HELICOPTER AND A BUSINESS AIRCRAFT A hybrid, knowledge-based system is described which provides TOSHlMlCHl OKITA and AKlRA IGA Japan Society for advice to air traffic controllers on the optimal tactics for resolving Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. predicted aircraft conflicts. The overall functional architecture is 35, no. 396, 1987. p. 57-62. In Japanese. refs described which has both computational algorithms and rule bases Flight test results for the four-channel GPS receiver in containing the knowledge and experience of controllers in the air helicopters and turboprop business aircraft are reported. No effect traffic environment. The system is designed to replicate the way of the helicopter rotary wing on the GPS receiver was observed. a controller might react to a predicted conflict. It responds to A block diagram of the receiver is presented. S.H. conflict predictions with resolution advice, which depends on both formal rules and on heuristics obtained from controllers. Author N88-10025# European Space Agency, Paris (France). TEST EQUIPMENT WITH FIBER OPTIC DATA BUS AND LASER GYRO STRAPDOWN SYSTEM LTN-90 FOR THE HELICOPTER BO-105 HANS-JUERGEN HOTOP and HANS-PETER ZENZ Apr. 1987 49 p Transl. into ENGLISH of Aufbau einer Messtechnik mit N88-10815# Deutsche Forschungs- und Versuchsanstalt fuer Lichtleitfasern und einem LaserkreiseCStrapdown-System LTN-90 Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer im Hubschrauber BO-105 (Brunswick, Fed. Republic of Germany, Flugfuehrung. DFVLR) 1985 Original language document announced as A RULE-BASED SYSTEM FOR ARRIVAL SEQUENCING AND N86-17333 SCHEDULING IN AIR TRAFFIC CONTROL (ESA-TT-1038; DFVLR-MITT-85-10; ETN-87-90669) Avail: NTlS U. VOELCKERS In AGARD, Knowledge Based Concepts and HC AO3/MF A01; original report in German available from Artificial Intelligence: Applications to Guidance and Control 12 p DFVLR, Cologne, West Germany DM 19 Aug. 1987 The measuring instruments with a MUDAS interface system Avail: NTlS HC A07/MF A01 for flight-testing navigation systems in the helicopter BO-105 are A rule based system is presented that is designed to assist described. The bit-serial bus was constructed using fiber optics. human controllers in efficiently merging high density inbound traffic The reference data from a laser gyro strapdown navigation system into congested airports. The rationale for the design of a rule were corrected by application of optimal filter techniques and based system and the critical requirements for the development external measurements. The results of testing the overall system of a rule based system for application to air traffic control are are presented, and the accuracy of the development of the discussed. The system uses the OPS5 production system and is reference trajectory compared with the data of the laser radar programmed in FRANZ LISP with embedded C functions. The PATS is explained with reference to a test flight. ESA system still has limited capabilities. Author

22 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

05 A88-10675 B-1B COMBINES BRISK LOW-ALTITUDE HANDLING, MORE AIRCRAFT DESIGN, TESTING AND CAPABLE AVIONICS DAVID M. NORTH, BRUCE D. NORDWALL, and WILLIAM B. PERFORMANCE SCOTT Aviation Week and Space Technology (ISSN 0005-2175), vol. 127, Sept. 14, 1987, p. 54, 55, 58 (9 ff.). Includes aircraft simulation technology. The performance of the B-1B is evaluated. The systems and capabilities of the aircraft are described. Particular consideration is given to its low-altitude performance, landing characteristics, A88-10049 in-flight refueling capabilities, and the offensive electronic systems. FLIGHT CHARACTERISTICS OF AIRCRAFT WITH GAS-TURBINE The engine start and initial taxi, the ride of the aircraft, and its ENGINES [LETNYE KHARAKTERISTIKI SAMOLETOV S GAZO- internal navigation system are discussed. I.F. TURBlNNYMl DVIGATELIAMI] BORIS VASIL’EVICH KALINICHENKO Moscow, Izdatel’stvo A88-10871 Mashinostroenie, 1986, 144 p. In Russian. refs STARTING SYSTEM FOR COLD WEATHER Methods are presented for the in-flight determination of the JAMES H. BRAHNEY Aerospace Engineering (ISSN 0736-2536), performance characteristics of turbojet and turboprop aircraft. vol. 7, Sept. 1987, p. 11-14. Attention is given to measurements of aircraft speed, flight altitude, The use of high pressure pneumatic start systems for military pressure, and Mach number; determination of aerodynamic tactical aircraft operating in extremely cold weather environments corrections and their physical meaning; generalized maneuverability is examined. There are two methods for implementing a pneumatic characteristics, and determination of the speed of turbojet and starting system: (1) an impingement start system and (2) a turboprop aircraft by the acceleration method. The discussion also pressurized air start system. The pressurized air start system is covers the equivalent height and differential correction methods compared to electric and hydraulic starting systems in terms of for determining the speed of horizontal flight under given conditions, weight and volume. It is observed that the pressurized air start maximum flight distance and time, and takeoff and landing system can be utilized without causing weight problems, but with characteristics of turbojet and turboprop aircraft. V.L. volume penalties. The size of the air pressure vessel can be reduced by increaslng the system pressure; a system pressure of A88-10655 4000 psi was estimated as optimum for the start system. Proposed NEW SOVIET COMMERCIAL AIRLINERS [NEUE SOWJETISCHE future improvements in pneumatic systems, in particular weight VERKEHRSFLUGZEUGE] and volume reductions, are discussed. I.F. FRITZ SEIDLER (Hochschule fuer Verkehrswesen, Dresden, German Democratic Republic) Technisch-oekonomische A88-10873 Information der zivilen Luftfahrt (ISSN 0232-5012). vol. 23, no. 3, AIRCRAFT TYRES 1987, p. 89-100. In German. STUART BIRCH Aerospace Engineering (ISSN 0736-2536), vol. Significant tendencies in the development of commercial 7, Sept. 1987, p. 24-27, aviation construction are reviewed, and new types of Soviet The use of radial tires on aircraft is examined. The advantages commercial airliners are described. Advances that have recently provided by using aramid instead of nylon belting in the tires are been made in the distance of travel, load capacity, and flight discussed. The problems encountered using radials on aircraft are velocity of commercial airliners are addressed. The aircraft the deflection rate of the section height and the technical difficulties considered include the IL-114, intermediate distance Tu-204, and of developing a thin-walled radial. The average life for a radial tire the long-distance 1L-96-300. New types of Soviet helicopters and is 200 landings; it will provide weight savings of 10-15 percent, hybrid aircraft are also discussed. C.D. require fewer tire changes, run cooler, and reduce foreign object damage. The tires will be useful for about 1200-2000 landings, but will require 10-12 retreads; the procedures for retreading radials A88-10656 are described. I.F. THE FOURTH GENERATION OF TL COMMERCIAL AIRCRAFT [UEBER DIE 4. GENERATION DERTL-VERKEHRSFLUGZEUGE] A88-10875 OTTO POLACEK (Ceskoslovenska Vedeckotechnicka Spolecnost, HlTB - THE ULTIMATE TEST BED Prague, Czechoslovakia) Technisch-oekonomische Information JAMES H. BRAHNEY Aerospace Engineering (ISSN 0736-2536), der zivilen Luftfahrt (ISSN 0232-5012), vol. 23, no. 3, 1987, p. vol. 7, Sept. 1987, p. 58-61. 103-107. In German. refs The design and systems of the High Technology Test Bed Advances in commercial aircraft that are represented by the (HTTB), which is a modified L-100-20, are described. The HTTB fourth generation of TL airliners are discussed. The requirements was designed as an airborne test platform that would provide a imposed on this generation of aircraft are summarized, and the vehicle for integrated testing of systems to investigate STOL use of quantitative modeling in the development of the third and performance enhancements, survivability improvements, and fourth generation of the TL aircraft is reviewed. The development advanced flight station designs. Consideration is given to the of new constructional technologies, the use of artificial materials HTTB’s structural extensions to the vertical and horizontal and composites, and the economics of air travel are considered. stabilizers, the spoiler system, the dual rotary electromechanical C.D. actuators, and the electronic system. The HTTB is applicable for evaluating navigation systems and advanced cockpit displays, and A88-10659 has been utilized to test the wing-mounted SAMSON (special THE WILL TO EUROPEAN UNITY AS EXEMPLIFIED BY A320 avionics mission strap-on now) pod. A diagram of the aircraft is [WILLE ZUR EUROPAEISCHEN ElNHElT AM BEISPIEL A3201 provided. I.F. JEAN ROEDER Luft- und Raumfahrt (ISSN 0173-6264), vol. 8, 3rd Quarter, 1987, p. 38, 40, 42-44 (5 ff.). In German. A88-10876 The roles of various European governments in the development THE ANTONOV AN-74 BRINGS HIGH TECH TO LOW of the A320 aircraft are discussed. The technology of the aircraft TEMPERATURES is briefly considered, and the A320’s profile is compared with that MARK LAMBERT lnteravia (ISSN 0020-5168), vol. 42, Sept. of the A310. The aircraft’s flight control surfaces, architecture, 1987, p. 907-909. flight envelope, flight control system, load alleviation system, The design of the An-74, which was developed for support of side-stick controller, approach configuration, and Integrated Air all types of operations in extreme low temperatures, is described. Data and Inertial System are shown and discussed. The aircraft’s The An-74 fuselage is 1.5 m longer than that of the An-72; the automatic monitoring and ’ministick’ are addressed. C.D. gross weight is 1500 kg greater than that of the An-72; the thrust

23 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

of the turbofans is 63.7 kN each; and cruising speed is 705 km/hr. speeds. Transonic capabilities are judged to be feasible in The aircraft has a maximum passenger capacity of 52 and can next-generation aircraft. O.C. carry a maximum payload of 10,000 kg. The flight controllnavigation and flight characteristics, such as upper surface blowing system A88-13081# and speeds at takeoff, are examined. I.F. ADVANCED COMPOSITE HORIZONTAL STABILIZER FOR NEXT-GENERATION COMMERCIAL AIRCRAFT A88-11195 SAKAE YOKOTA and MAKOTO HIRAHARA Japan Society for THE USE OF WIND TUNNEL DATA IN THE DESIGN OF RADIO Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. CONTROLLED CONTEST MODEL SAILPLANES 34, no. 394, 1986, p. 608-614. In Japanese. refs MARTIN SIMONS (Adelaide, University, Australia) IN: The experimental design of an advanced composite horizontal Aerodynamics at low Reynolds numbers Re greater than 10 to stabilizer for next-generation commercial aircraft carrying 150 the 4th and less than 10 to the 6th; Proceedings of the International passengers is described, and its structural characteristics are Conference, London, England, Oct. 15-18, 1986. Volume 2 . investigated. The spar structure has a multistringer design while London, Royal Aeronautical Society, 1986, p. 20.1-20.62. refs the outer panel has an integral skin design. Based on the FAR The tasks which a model sailplane must accomplish during a Part 25 design standard, the stabilizer uses a graphitelepoxy championship contest are reviewed, and the effects of changing composite. S.H. the airfoil section and varying other important parameters pertaining to the performance of model sailplanes are mathematically A88-13085# investigated using wind tunnel data. Taper effects, aspect ratio SOME TOPICS ON AIRCRAFT LANDING GEAR DESIGN effects, span effects, and the effects of flap modifications are HlROAKl NAKAMURA Japan Society for Aeronautical and Space considered. Typical sailplane dimensions and the use of wind Sciences, Journal (ISSN 0021-4663), vol. 34, no. 395, 1986, p. tunnels to obtain data about airfoils are also reviewed. C.D. 647-649. In Japanese. Problems in the design of aircraft landing gear are described. A88-124 12 Structural design for weight and cost reduction of the landing COMPOSITE MATERIALS IN ROTORCRAFT gear is considered along with the general concept of landing-gear WALTER SONNEBORN (Bell Helicopter Textron, Inc., Fort Worth, design evaluation. The airframellanding-gear weight ratio is TX) Vertiflite (ISSN 0042-4455), vol. 33. Sept.-Oct. 1987, p. considered. S.H. 10-17. The present evaluation of state-of-the-art helicopter and tilt-rotor N88-10026’# National Aeronautics and Space Administration. aircraft structural design development notes that military rotorcraft Ames Research Center. Moffett Field. Calif. development programs have led to virtually all-composite airframes, HIYAT FLIGHT PROGRAM: TEST RESULTS AND PROGRAM using highly automated composite manufacturing techniques that ASSESSMENT OVERVIEW improve composite structures’ cost-effectiveness. The applicability DWAIN A. DEETS, V. MICHAEL DEANGELIS, and DAVID P. LUX of these technologies throughout the helicopter manufacturing Jun. 1986 30 p industry is discussed. Attention is given to the development status (NASA-TM-86725; H-1283; NAS 1.1586725) Avail: NTlS HC of thermosetting fiberlepoxy materials in such applications as the A03/MF A01 CSCL 01C primary structure and the rotor hub of the V-22 Osprey military The Highly Manueverable Aircraft Technology (HiMAT) program tilt-rotor aircraft. O.C. consisted of design, fabrication of two subscale remotely piloted research vehicles (RPRVs), and flight test. This technical A88-12413 memorandum describes the vehicles and test approach. An COMPOSITES TECHNOLOGY IN ARMY AVIATION overview of the flight test results and comparisons with the design JAMES P. WALLER (US. Army, Aviation Applied Technology predictions are presented. These comparisons are made on a Directorate, Fort Eustis, VA) Vertiflite (ISSN 0042-4455). vol. 33. single-discipline basis, so that aerodynamics, structures, flight Sept.-Oct. 1987, p. 18-24. controls, and propulsion controls are examined one by one. The U.S. Army Aviation RBD programs in advanced helicopter interactions between the disciplines are then examined, with the structures technology have been instrumental in the development conclusions that the integration of the various technologies of rotorcraft applications of composite materials. Attention is given contributed to total vehicle performance gains. An assessment is to the development status of advanced composite materials in made of the subscale RPRV approach from the standpoint of rotor systems, propulsion components and drivetrains, airframes, research data quality and quantity, unmanned effects as compared and landing gears. In one case, the evaluation of composite with manned vehicles, complexity, and cost. It is concluded that manufacturing methods’ potential for the reduction of construction the RPRV technique, as adopted in this program, resulted in a costs led to the design and fabrication of the UH-60 helicopter’s more complex and costly vehicle than expected but is reasonable transition section, which demonstrated a 30-percent cost reduction. when compared with alternate ways of obtaining comparable The wholesale commitment to composites came in the wake of results. Author the subsequent Advanced Composite Air Frame Program, which demonstrated improvements in structural crashworthiness as well N88-10027# LTV Missiles and Electronics Group, Dallas, Tex. as cost and weight savings. O.C. Missiles Div. DESIGN PRINCIPLES AND PRACTICES FOR IMPLEMENTATION A88-12645 OF MIL-STD-1760 IN AIRCRAFT AND STORES Final Report, PREPARE FOR THE 21ST CENTURY - THE 1987 ALEXANDER Jul. - Dec. 1986 A. NIKOLSKY LECTURE D. E. LAUTNER, A. J. MAREK, W. M. DRUM, and R. R. J. M. DREES American Helicopter Society, Journal (ISSN FERNANDEZ Jun. 1987 432 p 0002-8711), vol. 32, July 1987, p. 3-14. refs (Contract N60530-85-C-0091) Helicopter, X-wing, and tilt-rotor VTOL aircraft configurational (AD-A183724; REPT-3-52110-6R-128) Avail: NTlS HC A1 9lMF and component technology development trends are projected into A01 CSCLOlC the 21st century, in order to evaluate the prospects for speed The trends in weapon system designs (aircraft and stores) enhancement, maneuver envelope expansion, range extension, has resulted in a growing concern over the general proliferation mission complexity and payload improvement, and ease of of aircraft-to-store electrical interfacing requirements and the operation in a variety of applications. Attention is given to rotary resulting high cost to achieve interoperability between aircraft and wing wakelfixed lifting surface aerodynamic interference effects stores. MIL-STD-1760 was prepared to reduce the aircraftlstore in hover and cruise regimes. Variable turbomachine blading in electrical integration problem by specifying a standard electrical turboshaft engines is recommended as a way of minimizing fuel interface between aircraft and stores. The standard electrical consumption in cruise and furnishing auxiliary propulsion for dash interface is based on recognized trends in store management

24 06 AIRCRAFT INSTRUMENTATION systems which use serial digital transmission for control, monitor, of the aircraft response being clearly displayed on a Nichols and release of stores. This report deals with the interoperability Chart. ESA requirements as described in MIL-STD-1760 and is intended to be an aid to understanding and meeting the requirements for both current and future weapon systems. In general. this report provides the following: (1) An overview of MIL-STD-1760 requirements, exclusions and future growth provisions. (2) Detail design N88-10788'# National Aeronautics and Space Administration. considerations applicable to the Aircraft Station Interface (ASI). Ames Research Center, Moffett Field, Calif. (3) Detail design considerations applicable to the Mission Store FLIGHT RESEARCH AT NASA AMES RESEARCH CENTER: A Interface (MSI). (4) AircraftIStore Physical Design Considerations. TEST PILOT'S PERSPECTIVE (5) A commentary on the requirements in MIL-STD-1760. GRA G. WARREN HALL Sep. 1987 13 p (NASA-TM-100025; A-87323; NAS 1.1 5:100025) Avail: NTlS HC N88-10028# National Aerospace Lab., Amsterdam (Netherlands). AO3/MF A01 CSCL 01C Informatics Div. In 1976 NASA elected to assign responsibility for each of the PROBLEM AND SOLUTION FORMULATIONS FOR THE various flight regimes to individual research centers. The NASA GENERATION OF 3D BLOCK-STRUCTURED GRIDS Ames Research Center at Moffett Field, California was designated J. W. BOERSTOEL 3 Mar. 1986 16 p Presented at the 1st lead center for vertical and short takeoff and landing, V/STOL International Conference on Numerical Grid Generation in research. The three most recent flight research airplanes being Computational Fluid Dynamics, 14-17 Jul. 1986, Landshut, Fed. flown at the center are discussed from the test pilot's perspective: Republic of Germany the Quiet Short Haul Research Aircraft; the XV-15 Tilt Rotor (NLR-MP-86020-U; 88701063; ETN-87-90825) Avail: NTlS HC Research Aircraft; and the Rotor Systems Research Aircraft. AO3lMF A01 Author The technical concepts of a method for the generation of 3D block-structured grids are presented. The generation process is decomposed in four steps: topological block decomposition; geometrical modeling of known and unknown coordinate functions; grid initialization by multilinear transfinite interpolation; and elliptic N88- 108 12# Royal Aircraft Establishment, Farnborough cell partitioning. The elliptic method is based on simple partial (England). differential equations representing locally decoupled ID stretchings TOWARDS THE UNMANNED COCKPIT followed by 3D rotations. Mesh-size and smoothness control occurs BRIAN ELLIS ln AGARD, Knowledge Based Concepts and with user-provided weight functions that are inversely proportional Artificial Intelligence: Applications to Guidance and Control 12 p to desired mesh sizes. Test results are shown. ESA Aug. 1987 Avail: NTlS HC A07/MF A01 N88-10029# Deutsche Forschungs- und Versuchsanstalt fuer Trends in air warfare make the development of autonomous Luft- und Raumfahrt, Brunswick (West Germany). Abteilung unmanned aircraft necessary. Advances in intelligent knowledge- Flugzeugsteuerung und- Regelung. based systems (IKBS) and in computing technology will make it pos- AN OBSERVER APPROACH TO THE ESTIMATION OF sible. The case for unmanned aircraft and their probable evolution is HELICOPTER AIRSPEED Ph.D. Thesis - Technische Univ. made. Some indications are offered of the developments that will be BURKHARD MUELLER Apr. 1987 152 p In GERMAN; called for in the IKBS themselves and in the computing hardware. ENGLISH summary Author (DFVLR-FB-87-13; ISSN-0171-1342; ETN-87-90597) Avail: NTlS HC AOB/MF A01; DFVLR, Cologne, West Germany DM 52.50 Difficulties in measuring the airspeed of helicopters because of low dynamic pressures in the low airspeed regime and because of the rotor downwash influencing the flow field around the fuselage are reviewed, and a nonlinear state observer for the estimation of helicopter airspeed is described. Uncertainties in the models of helicopter dynamics affect the method. A procedure that allows a simple adaptation of the models to real conditions is presented. It 06 is shown that parameter sensitivity can be reduced and the low static stability regime can be handled. The results are verified by flight tests. ESA AIRCRAFT INSTRUMENTATION

N88-10787# Loughborough Univ. of Technology (England). Dept. Includes cockpit and cabin display devices; and flight instruments. of Electrical and Electronic Engineering. DECOUPLING AND STABILIZATION OF SPEED AND HEIGHT IN F4 PHANTOM AIRCRAFT USING OUTPUT FEEDBACK M.S. A88-10436 Thesis FDAD - A LAWFIELD TEST TOOL J. M. HAMMER 1987 176 p BRUCE FENCHEL and JOSEPH AUER (Northrop Corp., Defense (ETN-87-90926) Avail: NTlS HC AOS/MF A01 Systems Div., Rolling Meadows, IL) IEEE Aerospace and The equations of motion of an F4 aircraft are numerically Electronic Systems Magazine (ISSN 0885-8985), vol. 2, Sept. 1987, evaluated for straight and level flight at Mach 1.1 at sea level. p. 5-7. The inputs of the system are speed demand and height demand; Flight Data Analysis and Display, FDAD, is a hardware and the outputs are speed and height, to be stabilized and decoupled software tool that permits the monitoring of the hardware and using output feedback and cascade compensation. The algebraic software of a multiprocessor electronic countermeasure, ECM, approach, the root locus approach, and the frequency response system in a noninterfering mode. FDAD monitors user-defined approach are compared. The first two have considerable memory addresses and hardware lines and displays in real-time drawbacks, the major one being the necessity to specify exactly the changes to these locations. Data is also stored for subsequent the pole positions in the stabilized aircraft when a large range of analysis and display. This tool allows developers to identify the pole positions is acceptable. The frequency response approach, operating characteristics of an extremely complex and fast system however, provides a logical and methodical means of arriving at with the assurance that the instrumentation does not alter the solutions for the compensation matrix elements, with the stability true performance of that system. Author

25 06 AIRCRAFT INSTRUMENTATION

A88-10679# A88-12574# THE IMPACT OF MODERN TECHNOLOGY ON AIRCRAFT EXPERT SYSTEM CONTROL FOR AIRBORNE RADAR AVIONICS EQUIPMENT [AUSWIRKUNG MODERNER TECH- SURVEILLANCE NOLOGIE IN DER AVIONIK-AUSRUESTUNGVON FLUGZEUGEN] ROBERT J. MCKENZIE and DAVID G. MULLENS (Boeing DIETER REICHOW (Deutsche Lufthansa AG, Hamburg, Federal Aerospace Co., Seattle, WA) IN: AlAA Computers in Aerospace Republic of Germany) (Deutsche Gesellschaft fuer Ortung und Conference, 6th, Wakefield, MA, Oct. 7-9, 1987, Technical Papers Navigation, Navigationstagung ueber moderne Technologie in Washington, DC, American Institute of Aeronautics and Ortung und Navigation, Duesseldorf, Federal Republic of Germany, Astronautics, 1987, p. 353-357. refs May 6-8, 1987) Ortung und Navigation (ISSN 0474-7550). vol. 28, (AIAA PAPER 87-2854) no. 2, 1987, p. 219-228. In German. The paper describes the application of an expert system to The recent developmental history and current status of the control of a phased array radar. The goal of the research transport-aircraft avionics are reviewed and illustrated with was to investigate operational radar control strategies which extensive diagrams, graphs, and flow charts. Topics addressed demonstrate gain in radar performance. A test bed, consisting of include the emphases on increased safety and flight capability, a prototype expert system controller and a phased array radar greater automation, and reduced fuel consumption in the 1970s; simulator, was built to conduct experimental runs of surveillance the goals of modern avionics design (crew and component scenarios. The test bed was incrementally developed as a hybrid redundance, reduced or delayable corrective measures, and between conventional algorithmic programs and an expert system, transparence); and the application of digital systems to achieve taking advantage of the best features of each. Attention is focused these goals in the 1980s. Consideration is given to cabin on a description of the test bed and a discussion of advanced AI electronics, data links, fault-tolerant systems, and onboard development environments and expert system run-time electronic documentation. T.K. performance. Author

A88-12655 AIRSPEED MEASUREMENT WITH A C02 LIDAR BERTRAND MORBIEU and JACQUES MANDLE (Crouzet, S.A., Division Aerospatiale, Valence, France) IN: Contemporary optical instrument design, fabrication, and testing; Proceedings of the Meeting, Innsbruck, Austria, Apr. 17, 18, 1986 . Bellingham, WA, A88-10685# Society of Photo-Optical Instrumentation Engineers, 1986, p. OPTIMAL INFORMATION PROCESSING FOR SENSORS AND 220-224. Research sponsored by the Ministere de la Defense SENSOR SYSTEMS THE CASE OF RADAR SENSORS - Armee de I’Air and DRET. refs [OPTIMALE INFORMATIONSAUFBEREITUNG FUER SENSOREN A laser Doppler technique has been developed since 1978 to UND SENSORSYSTEME AM BEISPIEL RADARSENSOREN] provide aircraft air data calibration. A CW C02 laser sensor PETER SCHMITT (AEG AG, Ulm, Federal Republic of Germany) performs a coherent detection of the light scattered by the aerosols (Deutsche Gesellschaft fuer Ortung und Navigation, sustained in the air. The instrument has successfully flown in the Navigationstagung ueber moderne Technologie in Ortung und vibrating environments of helicopter and aircraft. Author Navigation, Duesseldorf, Federal Republic of Germany, May 6-8, 1987) Ortung und Navigation (ISSN 0474-7550), vol. 28, no. 2, 1987. p. 356-370. In German. A88-12728 Data-processing architectures (DPAs) for hybrid onboard AIRBORNE RECONNAISSANCE X; PROCEEDINGS OF THE air-navigation systems are examined analytically. The advantages MEETING, SAN DIEGO, CA, AUG. 19, 20, 1986 of combining different types of optical and radar sensors are PAUL HENKEL, ED. (General Dynamics Corp., Saint Louis, MO) reviewed, and DPAs in which fast, dedicated preprocessors and FRANCIS R. LAGESSE, ED. Meeting sponsored by SPIE. connected directly to the sensor transmit reduced data to slower, Bellingham, WA, Society of Photo-Optical Instrumentation more flexible main processors are described in detail for the case Engineers (SPIE Proceedings. Volume 694), 1987, 176 p. For of primary radar sensors. Overall hybrid DPAs in which data from individual items see A88-12729 to A88-12751. different sensors are combined directly after the preprocessor and (SP IE-694) after main-processor treatment are compared, taking the impact The present conference on airborne reconnaissance considers of advances in semiconductor technology into account. Extensive topics in primary data collection system design, the management diagrams and flow charts are provided. T.K. of reconnaissance sensor data, reconnaissance systems’ research and development status, and the achievement of real-time intelligence. Attention is given to airborne minefield detection, forest fire detection, high speed transform image compression, data link design tradeoffs for electrooptical reconnaissance systems, and airborne reconnaissance sensor pods. Also discussed CCD millime- ter-wave imaging sensors, an advanced CCD reconnaissance detec- A88-12569# tor, recent developments in IR data processing, and the requirements TOWARDS THE DESIGN OF AN INTELLIGENT AEROSPACE of low altitude reconnaissance. O.C. SYSTEM M. EL-ARABATY (Military Technical College, Cairo, Egypt) IN: I AlAA Computers in Aerospace Conference, 6th, Wakefield, MA. A88-12731 Oct. 7-9, 1987, Technical Papers . Washington, DC, American SENSOR CONTROL/DATA DISPLAY SET (SC/DDS) FOR FILM Institute of Aeronautics and Astronautics, 1987, p. 318-328. refs AND/OR ELECTRO OPTICS (EO) (AIAA PAPER 87-2844) W. FISHELL and J. RADER (Fairchild Communications and In dense multiple aircraft surveillance environments, radar Electronics Co., Germantown, MD) IN: Airborne reconnaissance tracking of maneuvering aircraft is difficult due to the problem of X; Proceedings of the Meeting, San Diego, CA, Aug. 19, 20, 1986 discriminating against nearby target reports in the correlation . Bellingham, WA, Society of Photo-Optical Instrumentation process. Three main problems are given: the multitarget tracking, Engineers, 1987, p. 14-20. the probability of detection, and the assignment algorithm operating Recent sensor control development systems, designed for in a dense target environment. The key performance characteristics demonstration of Electro Optics (EO) Systems, have required similar of the designed algorithm is the flexibility for adaption to other control signals as those required for film sensors. From this tracking environments and incorporation into existing tracker similarity of interface controls and functions (along with cost designs. A new approach is given for the structure of a rule-based considerations) comes the realization that reconnaissance systems aerospace expert system. Author of the future must evolve in a modular fashion to produce the

26 06 AIRCRAFT INSTRUMENTATION level of sophistication, or complexity, required for each specific A88-12742 mission. Fairchild Communications and Electronics Company has SENSOR CONFIGURATION FOR A SHORT TO MEDIUM RANGE developed an AN/ASQ-197, Sensor Control/Data Display Set RECONNAISSANCE POD (SC/DDS) to control sensors and annotate film in the F/A-l8(R) INGVAR H. JOHANSSON (FFV Aerotech, Linkoping, Sweden) IN: Reconnaissance System. The An/ASQ-197, with its programmability, Airborne reconnaissance X; Proceedings of the Meeting, San Diego, is the basic building block of this hybrid system of the future, for film CA, Aug. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical and/or EO. This paper presents some of the considerations and fea- Instrumentation Engineers, 1987, p. 88-91. tures of such a system. Author The GREEN BARON pod is designed and developed specifically for penetrating reconnaissance and for reconnaissance up to medium distance. An Infra Red Line Scanner (IRLS) in combination with a panoramic camera are the main short range sensors, the A88-12736 IRLS as an all weather sensor and the panoramic camera to get MAGNETIC RECORDING FOR NEAR REAL TIME RECONNAIS- horizon to horizon coverage and stereo interpretation. For SANCE APPLICATIONS reconnaissance up to medium distance the choice was a camera W. D. KESSLER (Fairchild Weston Systems, Inc.. Data Systems with 12 inch focal length. This focal length gives moderate focusing Div., Sarasota, FL) IN: Airborne reconnaissance X; Proceedings problems when operating over a wide distance range. Influence of the Meeting, San Diego, CA, Aug. 19, 20, 1986 . Bellingham, on performance caused by environment is easier to deal with WA, Society of Photo-Optical Instrumentation Engineers, 1987, p. compared to operating a camera with longer focal length. This 43-48. refs paper concentrates on the reasons for choosing a focal length of The definition of recording for 'near real time reconnaissance' 12 inches for the pod. Author applications is reviewed along with the requirements for a recorder to be used in this application. Next the storage medium (magnetic tape) and its importance is discussed. Following this, the recording A88-12748 technologies available to achieve the required results are IMAGING THROUGH THE ATMOSPHERE FOR AIRBORNE presented. Both longitudinal fixed head and helical scan rotary RECONNAISSANCE head technologies are considered along with some of their merits N. S. KOPEIKA (Negev, University, Beersheba, Israel) IN: Airborne and demerits. Finally, a brief look into the future of this storage reconnaissance X; Proceedings of the Meeting, San Diego, CA, technology is presented. Author Aug. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical Instrumentation Engineers, 1987, p. 132-139. refs Turbulence, atmospheric background, and aerosol forward scattering MTFs are presented and analyzed with regard to both A88-12740 low elevation rpv and high elevation reconnaissance applications. DATALINK DESIGN TRADE-OFFS FOR ELECTRO-OPTICAL Turbulence is seen to limit image quality only at very high spatial RECONNAISSANCE SYSTEMS frequencies where degradation effects are likely to take place WILLIAM N. WAGGENER (Fairchild Weston Systems, Inc., Data anyway as a result of vibrational and diffraction effects. Background Systems Div., Sarasota, FL) IN: Airborne reconnaissance X; and aerosol MTFs limit low spatial frequency contrast as well. Proceedings of the Meeting, San Diego, CA. Aug. 19, 20, 1986 . However, this can be overcome somewhat by proper selection of Bellingham, WA, Society of Photo-Optical Instrumentation imaging wavelength. This analysis can aid in sensor selection for Engineers, 1987, p. 70-78. system design from the standpoints of both wavelength selection The design of the datalink for real-time electrooptical and sensor resolution. Author reconnaissance systems is a function of many system variables with many conflicting requirements. The datalink design must A88-12749 consider cost and frequency management issues. Sensor data ARGUMENTS FOR ELECTRO-OPTICAL RECONNAISSANCE rate has a particularly strong impact on a number of key design SYSTEMS parameters. As the data rate increases, RF bandwidth increases ROBERT L. SKILLEN (Litton Industries, Inc., ltek Optical Systems forcing the datalink to operate at higher carrier frequencies. With Div., Lexington, MA) IN: Airborne reconnaissance X; Proceedings a fixed RF bandwidth constraint, the higher rate decreases anti-jam of the Meeting, San Diego, CA, Aug. 19, 20, 1986 . Bellingham, processing margin, increases cost and generally increases system WA, Society of Photo-Optical Instrumentation Engineers, 1987, p. complexity. With data compression, the bandwidth can be 140-144. decreased at the expense of an increasing sensitivity to datalink Electrooptical (EO) digitally-recorded systems for tactical errors. In this paper, the sensitivity of the datalink design to a airborne reconnaissance require lower light levels for operation number of the most important design requirements is examined than film-based systems despite their greater haze-penetration with particular attention paid to the datalink cost and frequency capability. EO systems also allow the incorporation of a real-time management issues. Author imagery distribution net allowing all levels of command to see the target simultaneously; this does not jeopardize more careful subsequent study of the digital images obtained. About 10 times A88-12741 greater area can be covered with an EO system by an image AIRBORNE RECONNAISSANCE POD FLIGHT TEST interpreter, in comparison to the study of film on a light table. P. HENKEL (General Dynamics Corp., Fort Worth, TX) and R. O.C. STURZ (Recon/Optical, Inc., CAI Div., Barrington, IL) IN: Airborne reconnaissance X Proceedings of the Meeting, San Diego, CA, A88-12750 Aug. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical SOFTCOPY VERSUS HARDCOPY Instrumentation Engineers, 1987, p. 80-87. PIERRE DEMATHIEU (Matra Technology, Inc., San Jose, CA) IN: An account is given of the design features and performance Airborne reconnaissance X; Proceedings of the Meeting, San Diego, capabilities of a reconnaissance sensor-carrying pod for use by CA, Aug. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical such tactical aircraft as the F-16. The pod design requirements Instrumentation Engineers, 1987, p. 145-149. call for not only a minimization of size, weight, and cost, but also In most ot the existing reconnaissance systems, the film is the entailment of only minimal aircraft modifications for pod used as a storage medium. But more and more the photointerpreter incorporation, and the accomodation of multiple sensor types and processes the film information with the help of digital image combinations of sensors with their associated system components. displays. As the sensors are more and more digital or at least A rotatable nose compartment is used which allows both vertical electronic, the film appears to be just an intermediate step, with and forward oblique photography in high speed low altitude many shortcomings. Going into completely digital systems seems reconnaissance missions that may preclude direct flight over a to be very promising, but not very easy to do right now in respect target site. O.C. to some operational needs. Author

27 06 AIRCRAFT INSTRUMENTATION

A88-12751 07 RECENT DEVELOPMENTS IN INFRARED DATA PROCESSING WILLIAM L. MCCRACKEN (Honeywell, Inc., Electro-optics Div., AIRCRAFT PROPULSION AND POWER Lexington, MA) IN: Airborne reconnaissance X; Proceedings of the Meeting, San Diego, CA, Aug. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical Instrumentation Engineers, 1987, p. Includes prime propulsion systems and systems components, e.g., 150-157. gas turbine engines and compressors; and on-board auxiliary power The erceptionally great data rates generated by advanced plants for aircraft. military aircraft IR linescan sensors in low level penetration reconnaissance missions calls for the use of an automated data management system (DMS), if optimum use of onboard sensors A8&10358'# Johns Hopkins Univ., Laurel, Md. by the crew is to be achieved. Attention is presently given to the EVOLUTION AND APPLICATION OF CFD TECHNIQUES FOR development status of DMSs, as well as of data recorders and SCRAMJET ENGINE ANALYSIS automatic target cuers; all employ VLSl and VHSlC implementations M. E. WHITE (Johns Hopkins University, Laurel, MD), J. P. of dense, high speed image processing chips. Progress to date DRUMMOND, and A. KUMAR (NASA, Langley Research Center, on the algorithms needed to operate the DMS and autocuer Hampton, VA) Journal of Propulsion and Power (ISSN 0748-4658), hardware is also noted. O.C. vol. 3, Sept.-Oct. 1987, p. 423-439. Previously cited in issue 07, p. 894, Accession no. A86-19970. refs

A88-10362# ANALYTICAL STUDY OF SWIRLER EFFECTS IN ANNULAR PROPULSIVE NOZZLES JOE D. HOFFMAN, H. DOYLE THOMPSON, and DAVID L. MARCUM (Purdue University, West Lafayette, IN) Journal of Propulsion and Power (ISSN 0748-4658), vol. 3, Sept.-Oct. 1987, p. 465, 466. USAF-sponsored research. Previously cited in issue 07, p. 848, Accession no. A86-19965. refs

N88-10030'# Battelte Columbus Labs., Ohio. A88-10371# DIGITAL SYSTEM BUS INTEGRITY Final Report MULTIMODES TO MACH 5 DONALD ELDREDGE and ELLIS F. HlTT Mar. 1987 100 p RICHARD DEMEIS Aerospace America (ISSN 0740-722X). vol. Prepared in cooperation with Lockheed-Georgia Co., Marietta 25, Sept. 1987, p. 50-53. (Contract NAS2-11853) Various designs for a variable cycle propulsion system for an (NASA-CR-181446; NAS 1.2611 81446; DOT/FAA/CT-86/44) SST are analyzed. The objectives of the multimode engine are to Avail: NTlS HC AO5/MF A01 CSCL 01D combine the performance capabilities of the turbofan, turbojet, This report summarizes and describes the results of a study ramjet, and scramjet into one design. The advantages and of current or emerging multiplex data buses as applicable to digital limitations of a turbojet, turboamjet, air turboamjet, variable cycle flight systems, particularly with regard to civil aircraft. Technology turbofan ramjet, turboscramjet, and turbine bypass engine are for pre-1995 and post-1995 timeframes has been delineated and examined and compared. It is noted that the turbine bypass engine critiqued relative to the requirements envisioned for those periods. is the most effective design proposed. I.F. The primary emphasis has been an assured airworthiness of the more prevalent type buses, with attention to attributes such as A88-10987# fault tolerance, environmental susceptibility, and problems under ALTITUDE TESTS OF THE XF3-30 TURBOFAN continuing investigation. Additionally, the capacity to certify systems MASAYUKI KITAMURA (Japan Defense Agency, Technical relying on such buses has been addressed. Author Research and Development Institute, Tokyo), MORIMASA UCHIDA (Air Self-Defense Force, Tokyo, Japan), and SATOSHI YASHIMA (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 6 p. (ASME PAPER 87-GT-25) The XF3-30 turbofan has been successfully developed as the propulsion system for the Japan Air Self Defence Force's XT-4 military intermediate trainer. Altitude tests were conducted four times in ATF and four times on FTB in the engine development program. Utilizing the results of each test, the engine has been improved in sufficient time to meet the aircraft development N88-10031# Deutsche Forschungs- und Versuchsanstalt fuer program schedule, and successful flight tests of XT-4 powered by Luft- und Raumfahrt, Brunswick (West Germany). Abteilung XF3-30 have been made. Author Anthropotechnik und Simulation. COLOR DISPLAY PROGRAMMING FOR AVIATION A88-10988# HERMANN WIESNER Nov. 1986 52 p In GERMAN; ENGLISH DEVELOPMENT OF THE XF3-30 TURBOFAN ENGINE summary HlDEJlRO YAMADA, HlROSHl HAMATANI (Japan Defense (DFVLR-MITT-87-03; ISSN-0176-7739; ETN-87-90447) Avail: Agency, Technical Research and Development Institute, Tokyo), NTlS HC A04/MF A01; DFVLR, Cologne, West Germany DM 37 and KAZUHIKO ISHIZAWA (Ishikawajima-Harima Heavy Industries A software concept for electronic displays suitable for a variety Co., Ltd., Aero-Engine Div, Tokyo, Japan) ASME, International of applications in aviation was developed. The hardware of the Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May display system is outlined. The programs for the symbol generator, 31-June 4, 1987. 7 p. microprocessor-bipolar, and fixed blanking windows are described. (ASME PAPER 87-GT-26) The software was implemented for the proven display technology The XF3-30 is the low-bypass-ratio turbofan engine which has flown in the Airbus A-310 aircraft. In the light of future developments been developed to power the XT-4 intermediate trainer for the in display technology, the software provides more features than Japan Air Self Defence Force. All of the qualification tests including can be utilized with the hardware currently employed. Electronic endurance tests, low cycle fatigue test, altitude test, foreign object displays for a helicopter were taken to demonstrate the software ingestion test, and environmental icing test were successfully det ai I s . ESA completed by March 1986. A flight test of the XT-4 trainer aircraft

28 07 AIRCRAFT PROPULSION AND POWER

powered by two of the XF3-30 engines has proceeded without the burnt section; welding using the tungsten insert gas method; any engine-related problems. Author hand blending; brazing compound application; and final inspection. It is noted that this repair technique has reduced the scrappage A88- 10993# rate for the vane ring and an average of 100 units are INVESTIGATION OF INTEGRATED SELECTION OF OPTIMUM repairedhonth. I.F. ENGINE CYCLE PARAMETERS JIN ZHANG, DAGUANG CHEN, XlNGJlAN ZHU, and ZHlLl ZHU (Beijing Institute of Aeronautics and Astronautics, People's Republic of China) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 7 p. A88-11027# Translation. Previously cited in issue 20, p. 2852, Accession no. ELECTRONIC TREND MONITORING AND EXCEEDANCE A84-41783. refs RECORDING SYSTEMS - A MEANS TO IMPROVED TURBINE (ASME PAPER 87-GT-39) ENGINE RELIABILITY A method for integrating the selection of optimal aircraft engine MICHAEL G. MOORE (Semco Instruments, Inc., North Hollywood, cycle parameters is proposed from the viewpoint of system CA) ASME, International Gas Turbine Conference and Exhibition, engineering, and a control scheme is proposed which takes into 32nd, Anaheim, CA, May 31-June 4, 1987. 8 p. account matching and interaction between the engine and the (ASME PAPER 87-GT-87) aircraft. A rapid method for predicting turbojet or turbofan engine The paper discusses engine-mountable compact microprocessor- off-design performance is adopted and an empirical formula for based rcording systems that can supply data relevant to the mainte- estimating the engine weight is developed. An augmented engine nance planning of a turbine engine and, thus, improve its reliability. scheme that meets modification requirements is presented as an Consideration is given to the significant data to be recorded, the example. The results show that the optimum cycle parameters requirements of an airborne/aircraft recorder, and the information/con- and the control scheme are quite different if the mission, clusions available after the analysis of data.The recorded data provide modification requirements, or technical constraints are varied. records of an engine/aircraft abuse and maintain cycle counts based Author upon complex formulas; data are provided in a format that is useful in predicting maintenance requirements. IS. A88-10996# FRICTION DAMPING OF RANDOM VIBRATION IN GAS TURBINE ENGINE AIRFOILS ALOK SINHA (Pennsylvania State University, University Park) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 7 p. refs (Contract NSF MSM-85-04579) A88-11028# (ASME PAPER 87-GT-44) CORRELATIONS OF FUEL PERFORMANCE IN A FULL-SCALE The optimal value of slip load is calculated for a frictionally COMMERCIALCOMBUSTOR ANDTWO MODEL COMBUSTORS damped turbine blade subjected to random excitation. The nature T. T. BOWDEN, D. M. CARRIER, and L. W. COURTENAY (Shell of excitation is assumed to be Gaussian white noise and the Research, Ltd., Thornton Research Centre, Chester, England) statistics of response are obtained using equivalent linearization ASME, International Gas Turbine Conference and Exhibition, 32nd, approach. The results from this technique are compared with those Anaheim, CA, May 31-June 4, 1987. 6 p. Research supported by from numerical simulations. Author the Ministry of Defence. refs (ASME PAPER 87-GT-89) A88-10998"# Princeton Univ., N. J. Results from a statistically-designed correlation exercise have LOCALIZATION OF NATURAL MODES OF VIBRATION IN demonstrated excellent agreement between the performance of BLADED DISKS two combustor models and a full-scale Tyne engine combustor, 0. 0. BENDIKSEN (Princeton University, NJ) and N. A. VALERO validating the model combustor approach to response and ASME, International Gas Turbine Conference and Exhibition, 32nd, performance prediction. The linear correlations found indicate that Anaheim, CA, May 31-June 4, 1987. 11 p. refs only a minimum number of measurements are necessary to confirm (Contract NAG3-308) the relationship between the model and the full-scale combustor. (ASME PAPER 87-GT-46) Results show that a common mechanism of soot formation occurs A study is presented of the mode localization phenomenon in within all three combustors. R.R. imperfect blade-disk and blade-shroud-disk assemblies. The results indicate that unshrouded blades mounted on stiff disks are especially susceptible, and even small blade imperfections within manufacturing tolerances are likely to trigger mode localization. Increasing the interblade coupling by adding shrouds or reducing A88-11029# the disk stiffness greatly reduces the localization susceptiblity, EXPERIMENTAL METHOD FOR THE COMBUSTION although certain modes may still become localized if the shrouds EFFICIENCY CALCULATION IN A REHEAT DUCT are free to slip. Author A. CADIOU (ONERA, Chatillon-sous-Bagneux, France) ASME, International Gas Turbine Conference and Exhibition, 32nd, A88-10999# Anaheim, CA, May 31-June 4, 1987. 7 p. SNECMA-sponsored COMPRESSOR TURBINE VANE RING (PT6 ENGINE) REPAIR research. refs DEVELOPMENT (ASME PAPER 87-GT-90; ONERA, TP NO. 1987-54) N. SOURIAL (Pratt and Whitney Canada, Longueuil) ASME, An efficient method for the experimental measurement of the International Gas Turbine Conference and Exhibition, 32nd, combustion efficiency in a reheat duct is developed, with application Anaheim, CA, May 31-June 4, 1987. 5 p. to the comparison of different reheat systems. The present (ASME PAPER 87-GT-47) downstream to upstream method involves static pressure A process for repairing the compressor turbine vane ring in measurements along the duct, and gas sampling in its outlet cross the PT6 engine is described. The compressor turbine vane ring section. Results are given for a three annular V-gutters flame consists of 14 air-cooled vanes integrally cast from Co alloys and holder. Optimization is achieved with the present method by trading protected with a thin layer of diffused NiAl coating, and it is located off betweeen the length of the duct and the pressure drop induced directly at the exit of an annular combustion chamber. The repair by the flame holder. Experimental correlations concerning the effect procedure involves: subjecting the vane ring to heat treatment in of geometrical parameters are performed in order to optimize the a vacuum furnace; fluorescent penetrant inspection; removal of size of the combustion reheat system. R.R.

29 07 AIRCRAFT PROPULSION AND POWER , A88-11039# practical engineering approach for dealing with stage mistuning. CURRENT GAS TURBINE COMBUSTION AND FUELS RESEARCH Author AND DEVELOPMENT J. E. PETERS (Illinois, University, Urbana) ASME, International A88-11076# Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May VERIFICATION OF COMPRESSOR DATA ACCURACY BY 31-June 4, 1987. 17 p. refs UNCERTAINTY ANALYSIS AND TESTING METHODS (ASME PAPER 87-GT-107) N. D. POTTl and D. C. RABE (USAF, Aero Propulsion Laboratory, i Current research and development work on gas turbine Wright-Patterson AFB, OH) ASME, International Gas Turbine combustion and fuels is surveyed on the basis of publications in Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, open literature and of gas-turbine manufacturers’ reports. 1987. 5 p. Consideration is given to both aircraft and industrial applications (ASME PAPER 87-GT-165) regarding the alternative fuels (in particular, the ’heavier’ alternative A transonic compressor designed and instrumented by the fuels for aircraft applications), and computer modeling. Two General Electric Company was recently evaluated during several , examples of research and development for specific design test programs in the Compressor Research Facility at I considerations are illustrated with a discussion of recent efforts Wright-Patterson Air Force Base. An analytical uncertainty analysis on staged combustion for NOx control and on fuel injection. I.S. was performed for the individual measurements, as well as the calculated performance parameters. During the tests, the A88-11048# experimental values of precision uncertainty were compared to TIME-AVERAGED HEATFLUX DISTRIBUTIONS AND COMPARI- the analytical predictions. The spatial variation of the individual SON WITH PREDICT10 FOR THE TELEDYNE 702 HP TURBINE discharge measurements was evaluated for its effect on the STAGE uncertainty of the measured parameters and calculated I M. G. DUNN (Calspan Corp., Buffalo, NY) and R. E. CHUPP performance. Through the comparison of the analytical and (Teledyne, Inc., Toledo, OH) ASME, International Gas Turbine measured uncertainty and the evaluation of spatial variation, a Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, final uncertainty of the measured performance is presented, and 1987.8 p. Research supported by Teledyne Independent Research the overall quality of the test results is assessed. Through these and Development Funds. refs data reviews, a more accurate understanding of the performance (ASME PAPER 87-GT-120) of the test compressor is obtained. Author Time-averaged heat-flux distributions for the vane and blade of the CAE 702 HP full-stage rotating turbine are presented, with A88-11078# a shock tube used as a short-duration heat source to which the INTRODUCTION AND APPLICATION OF THE GENERAL turbine is subjected, and thin-film gages used to obtain heat-flux ELECTRIC TURBINE ENGINE MONITORING SOFTWARE measurements. The vane data are shown to be bounded by the WITHIN KLM ROYAL DUTCH AIRLINES turbulent flat plate and the fully turbulent STAN 5 prediction models, HANS LUCAS (KLM Royal Dutch Airlines, Schiphol Airport, ~ and the blade data are found to be well predicted by the k-epsilon Netherlands) and JOHN E. PAAS (General Electric Co., Aircraft model on both the pressure and the suction surfaces. The STAN Engine Business Group, Cincinnati, OH) ASME, International 5 fully turbulent calculation for the blade is shown to fall above Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May the data, and the STAN 5 fully laminar calculation to fall 31-June 4, 1987. 6 p. refs substantially below the data. R.R. (ASME PAPER 87-GT-167) The development, design, and application of the Ground-based A88-11066# Engine Monitoring (GEM) system are described. The monitoring THE PERFORMANCE ESTIMATION OF TRANSONIC TURBINE system combines multiple engine performance and mechanical AT DESIGN AND OFF-DESIGN CONDITIONS analysis functions into a single ground-based computer system. MANCHU GE (Chinese Academy of Sciences, Institute of The multiple functions and capabilities of the GEM, which include Engineering Thermophysics, Beijing, People’s Republic of China) engine performance, vibration signals, and engine control ASME, International Gas Turbine Conference and Exhibition, 32nd, parameters analyses, performance simulation, and automatic trend Anaheim, CA, May 31-June 4, 1987. 6 p. refs shift recognition and alter functions, are examined. The integration (ASME PAPER 87-GT-148) of the GEM into the KLM operations, and the benefits provided A performance estimation method for the determination of the by the system are discussed. I.F. gasdynamic parameters of turbines at design and off-design conditions is presented. The method involves the simultaneous A88-11079’# Pratt and Whitney Aircraft, West Palm Beach, solution of equations including the S2 stream surface equation, Fla. the loss equations, and the deviation angle correction. The CONCEPTUAL DESIGN OF AN OPTIC BASED ENGINE approach is shown to avoid the false choking condition and to CONTROL SYSTEM achieve rapid convergence. The reduced flow rate, efficiency, and W. J. DAVIES (Pratt and Whitney, Engineering Div., West Palm expansion ratio are found to agree well with experimental results, Beach, FL), R. J. BAUMBICK (NASA, Lewis Reserach Center, with a difference of within 1 percent between computational and Cleveland, OH), and R. W. VlZZlNl (US. Navy, Naval Air Propulsion experimental data near the design condition. R.R. Test Center, Trenton, NJ) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, A88-11070# 1987. 8 p. ON PREDICTING THE RESONANT RESPONSE OF BLADED (ASME PAPER 87-GT-168) DISK ASSEMBLIES Use of optics in the aircrafl engine control systems would J. H. GRIFFIN (Carnegie-Mellon University, Pittsburgh, PA) ASME, provide immunity to electromagnetic effects (such as lightning, International Gas Turbine Conference and Exhibition, 32nd. radar, and nuclear pulses) for flight and propulsion control systems Anaheim, CA, May 31-June 4, 1987. 7 p. refs located throughout the aircraft and in need of communication and (Contract F33615-844-2454) would result in weight reduction. This paper discusses a conceptual (ASME PAPER 87-GT-158) design of an optic engine control system that is being developed The vibratory response of blades in gas turbine engines varies by the Fiber Optic Control System Integration (FOCSI) program. because of mistuning. An approach is developed for calculating The features inherent in each of the optic-based components of the statistical distribution of peak resonant stresses in engine the optic system, which includes the on-engine full authority digital blading. It is used to predict the vibratory response of an electonic control, optic sensors, optic-based actuators, and an optic unshrouded fan stage. The results of the calculation compare data bus for communication with the aircraft flight control system favorably with test data for the lower frequency modes. The are described in detail. The diagrams of the FOCSI control system procedure can be used to predict fleet durability and offers a and its components are included. IS.

30 07 AIRCRAFT PROPULSION AND POWER

A88-11085# program structure from conception to transition to full-scale PREDICTION OF GAS TURBINE COMBUSTOR-LINER development is examined and a model is provided. I.F. TEMPERATURE YOUSEF S. H. NAJJAR (King Abdulaziz University, Jeddah, Saudi Arabia) and RlAD M. DROUBI ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31June 4, 1987. 6 p. refs A88-11110# (ASME PAPER 87-GT-177) VELOCITY SCALED AEROELASTIC TESTING OF ADVANCED Broadening of fuel specifications decreases the hydrogen TURBOPROPS content and increases the aromatics and final boiling point. The EDWARD F. CRAWLEY and ERIC H. DUCHARME (MIT, cumulative effect will be an increase in soot formation hence flame Cambridge, MA) ASME, International Gas Turbine Conference radiation which affects flame tube durability. In this work an and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 11 p. analytical study is made where empirical formulae are developed Research supported by General Electric Co. refs for luminosity, radiation and convection at idle and full load (ASME PAPER 87-GT-209) conditions. These equations predict combustor liner temperature An innovative experimental procedure for the subvelocity scale with high degree of agreement with previous experimental work. testing of anisotropic aeroelastic models is developed and applied Author to the Advanced Turboprop. The scaling laws for an anisotropic, rotating model are developed. These scaling laws indicate that by proper choice of model geometry, stiffness, and density, all of the A88-11090# important aeroelastic similarity parameters can be satisfied in a A NEW METHOD (FTDCDF) FOR THE BLADE DESIGN OF AXIAU full-velocity scaled test. In a subvelocity scaled test, all the similarity MIXED-FLOW COMPRESSIONS AND ITS APPLICATIONS parameters except for the Mach number can be matched. The CHUAN-GANG GU (Xian Jiaotong University, People’s Republic development of the model building technology to construct reduced of China) ASME, International Gas Turbine Conference and stiffness anisotropic models for subvelocity scaled testing is then Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 7 p. refs reviewed. In order to experimentally verify the sub-velocity scaled (ASME PAPER 87-GT-183) procedure, a propeller model was constructed based on the G.E. A new design method with unequal work along the height of UDF MPS model, and the aeroelastic and performance data are the blade in axialhnixed-flow compressors, called The Flow-Type favorably compared. Finally, as an illustration of the versatility of Design of Controlled Diffusion Factors (FTDCDF), is described. the sub-velocity scaled approach, the model is used to demonstrate The idea of the method is to control the distribution of the diffusion the sensitivity of ATP blade flutter to mass distribution. Author factors along the height of the blade in the vaneless space in order to design a blade with good aerodynamic properties. The theoretical basis of FTDCDF and its computational method are studied in detail. Comparison between the results of this method and those of others shows that the FTDCDF program has good A88-11111# accuracy and convergence. Author DIGITAL CONTROLS FOR GAS TURBINE ENGINES K. ROBINSON (Dowty and Smiths Industries Controls, Ltd., A88-11094# Cheltenham, England) ASME, International Gas Turbine THE AEROMECHANICAL RESPONSE OF AN ADVANCED Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, TRANSONIC COMPRESSOR TO INLET DISTORTION 1987. 13 p. refs J. T. DATKO, JR. and J. A. O’HARA (USAF, Aero Propulsion (ASME PAPER 87-GT-211) Laboratory, Wright-Patterson AFB, OH) ASME, International Gas The functional requirements of gas turbine engine control Turbine Conference and Exhibition, 32nd, Anaheim, CA, May systems and the application of electronic control systems to the 31June 4, 1987. 11 p. refs fulfilling of these requirements are considered. British Civil (ASME PAPER 87-GT-189) Certification and commercial requirements for digital engine control An advanced transonic compressor was tested in the systems (DECs) are discussed, in addition to issues involved in Compressor Research Facility at the Aero Propulsion Laboratory. the trade-off between system integrity and reliability. Several Full The compressor was operated with seven different total-pressure Authority Digital Engine Controls (FADEC) programs are described, distortion screens located at the inlet, along with baseline testing including DECs for turboshafts, turboprops, a VTOL aircraft, a large of two ’clean’ inlet configurations. Of particular interest was the civil fan-engine, remote piloted vehicles, and augmented engines. forced vibratory reponse of the first-stage integrally bladed disk A FADEC configuration consisting of two lanes in one and using (blisk) to the various distortions. This paper presents a summary only three microprocessors is also considered. R.R. of the blisk vibratory responses to each of the distortion screens. Effects of instrumentation on the dynamic response of the blisk are illustrated. Author

A88-11107# A88-11113# THE UNITED KINGDOM ENGINE TECHNOLOGY DEMONSTRA- THE TURBOMACHINE BLADING DESIGN ACHIEVED BY TOR PROGRAMME SOLVING THE INVERSE FIELD PROBLEM W. J. CHRISPIN (Ministry of Defence /Procurement Executive/, T. S. LUU and B. VINEY (CNRS, Laboratoire d’lnformatique pour London, England) ASME, International Gas Turbine Conference la Mecanique et les Sciences de I’lngenieur, Orsay, France) ASME, and Exhibition, 32nd, Anaheim, CA, May 31 June 4, 1987. 8 p. International Gas Turbine Conference and Exhibition, 32nd, (ASME PAPER 87-GT-203) Anaheim, CA, May 31-June 4, 1987. 6 p. refs The engine technology demonstrator programs in the UK are (ASME PAPER 87-GT-215) discussed. These programs are needed to ensure that engine The paper describes a design procedure for the determination technologies are available prior to full-scale engineering of the geometry of the blading of the turbomachine with prescribed development and to reduce development risks and costs. The thickness and bound vorticity distribution. An optimized programs generate fundamental design concepts and evaluate two-dimensional cascade design example is shown. The them at rig and component levels; the integrated approach used quasi-three-dimensional ’S2’-’S11 stream function formulation is in the programs is described, and an example demonstrating its developed. The design of guide vanes downstream of a lateral applicability is presented. The relationship between government inlet casing is described. A new approach by introducing a potential and industry in the operation of the demonstrations, in particular like function to treat the three-dimensional rotational flow is also funding and program management, is considered. The demonstrator formulated. Author

31 07 AIRCRAFT PROPULSION AND POWER

A88-11122# common to typical gas turbine exhaust silencer are examined in AGTlOl - CERAMIC GAS TURBINE DEVELOPMENT detail. An arrangement diagram is included. I.S. G. L. BOYD, M. L. EASLEY, and D. M. KREINER (Garrett Turbine Engine Co., Phoenix, AZ) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 17 p. (ASME PAPER 87-GT-228) A88-11137'# McDonnell Aircraft Co., St. Louis, Mo. The critical ceramic component development and the engine HIDEC ADAPTIVE ENGINE CONTROL SYSTEM FLIGHT evaluation of the ceramic hot section in the AGTlOl are described. EVALUATION RESULTS Ceramic structure test evaluation at 2500 F, ceramic combustor W. A. YONKE, R. J. LANDY (McDonnell Aircraft Co., Saint Louis, operation using various fuels, and ceramic static seal leakage MO), and J. F. STEWART (NASA, Flight Research Center, Edwards reduction are reported. Fabrication development of the turbine AFB, CA) ASME, International Gas Turbine Conference and rotor is emphasized. A 100-hr engine test of the ceramic structures Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 8 p. refs to 2100 F, and an 85-hr engine test of the all-ceramic hot section (ASME PAPER 87-GT-257) to 220 F, have been accomplished, and full speed operation to An integrated flight propulsion control mode, the Adaptive 100,000 rpm and a ceramic rotor tip speed of 3200 ft/sec have Engine Control System (ADECS), has been developed and flight been demonstrated. R.R. tested on an F-15 aircraft as part of the NASA Highly Integrated Digital Electronic Control program. The ADECS system realizes A88-11123# additional engine thrust by increasing the engine pressure ratio A TRADE-OFF STUDY OF ROTOR TIP CLEARANCE FLOW IN (EPR) at intermediate and afterburning power, with the amount of A TURBINE/EXHAUST DIFFUSER SYSTEM EPR uptrim modulated using a predictor scheme for angle-of-attack SAEED FAROKHI (Kansas, University, Lawrence) ASME, and sideslip angle. Substantial improvement in aircraft and engine International Gas Turbine Conference and Exhibition, 32nd, performance was demonstrated, with a 16 percent rate of climb Anaheim, CA, May 31-June 4, 1987. 7 p. refs increase, a 14 percent reduction in time to climb, and a 15 percent (ASME PAPER 87-GT-229) reduction in time to accelerate. Significant EPR uptrim capability In a modern gas turbine power plant, the axial exhaust diffuser was found with angles-of-attack up to 20 degrees. R.R. accounts for up to 10 percent of the generator power. An unshrouded rotor, due to its highly energetic tip clearance flow, improves the pressure recovery characteristic of the exhaust diffuser, while the power production within the blading suffers a loss as a result of the tip leakage flow. In this paper, these conflicting trends are thermodynamically investigated and A88-11139# nondimensional expressions are derived which facilitate the task CYCLIC SPINNING TESTING OF AERO-ENGINE DISCS of a gas turbine system designer. Conservatively, 1 percent thermal H. AOANO, T. CHIKATA, R. SATOH, T. WAKATSUKI, and M. efficiency gain results from elimination of the last rotor tip clearance HlKlTA (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, flow. Author Japan) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 8 p. refs (ASME PAPER 87-GT-259) A88-11127# Aero-engine disks must demonstrate sufficient low-cycle-fatigue BOUNDARY LAYER PROFILE INVESTIGATIONS DOWNSTREAM lives. Here, results from several cyclic spinning tests are reported. OF AN AERO-ENGINE INTAKEANTI-ICING AIR EXHAUSTSLOT During the testing, some disks were burst, and some disks were S. J. DOWNS (Rolls-Royce, PLC, Derby, England) and E. H. JAMES cracked. Through the experience of the testing, a technique for (Loughborough University of Technology, England) ASME, detecting crack initiation in the disks during spinning tests is International Gas Turbine Conference and Exhibition, 32nd, developed. Using this technique, it is possible to stop driving before Anaheim, CA, May 31-June 4, 1987. 7 p. the disks would burst. Procedures and data are presented in (ASME PAPER 87-GT-237) detail. Author The boundary-layer profile downstream of the antiicing air (AIA) exhaust slot of a two-dimensional aero-engine inlet section was investigated by means of a pitot rake. Results are presented for a range of inlet air flows with and without exhaust AIA introduced. The boundary layer was found to be turbulent, owing to the A88-11196 presence upstream in the wind tunnel of a fixed water spray grid. WIND TUNNEL TESTING OF SMALL SCALE PRESSURE Injection of AIA produced a sublayer downstream of the AIA TAPPED MODEL PROPELLERS exhaust plane. Three methods of deriving boundary-layer thickness D. W. HURST, D. T. OWEN (Southampton, University, England), from the experimental data were used, and the experimental and P. N. METHVEN (Dowty Rotol, Ltd., Gloucester, England) measurements confirmed theoretical predictions. Author IN: Aerodynamics at low Reynolds numbers Re greater than 10 to the 4th and less than 10 to the 6th; Proceedings of the A88-11128# International Conference, London, England, Oct. 15-18. 1986. GAS TURBINE EXHAUST SYSTEMS - DESIGN CONSIDERA- Volume 2 . London, Royal Aeronautical Society, 1986, p. TIONS 21.1-21.22. refs ROY A. MORRIS (Cullum Detuners, Ltd., Heanor, England) ASME, Wind tunnel tests conducted to study the scale effects resulting International Gas Turbine Conference and Exhibition, 32nd, from the use of small-scale pressure-tapped models instead of Anaheim, CA, May 31-June 4, 1987. 8 p. full-scale propellers are described. The tested propeller blade had (ASME PAPER 87-GT-238) a diameter of 0.705 m and a chord of 0.049 m at 70 percent This paper discusses the specifications which the prospective radius. The blade had 24 chordwise tappings positioned at seven user of a gas turbine should give to the designer of the spanwise stations, producing a total of 168 measuring points. power-turbine exhaust system. Basic factors include the initial Results from proving trials on this propeller model are included acoustic performance of the particular installation (considering, in which show the effects of changes in rotational speed, blade angle, particular, the inadequacy of the dBA weighting criteria for use in free-stream velocity, and number of blades on the pressure locations near residential areas) and the importance of multiple-set distribution. Scale effect results are reproduced for both the static installations. Other important elements in the overall acoustic running condition and nonstatic conditions. The results show that, performance of an the installation are the plant design, the exhaust over the measured operating range, models of this size can be gas path, and the types of materials and finishes. The components safely used to represent conventional full-scale propellers. C.D.

32 07 AIRCRAFT PROPULSION AND POWER

A88-11923# A88-13095# THE DEVELOPMENT OF 270 VDC SOLID STATE POWER THE SCRAYJET - TOWARD MACH 4-25 FLIGHT CONTROLLERS NOBUO CHlNZEl and GORO MASUYA Japan Society for R. Y. KINOSHITA, P. E. MCCOLLUM, and M. E. COLAN (Rockwell Aeronautical and Space Sciences, Journal (ISSN 0021 -4663), vol. International Corp., Anaheim, CA) IN: IECEC '87; Proceedings of 35, no. 400, 1987, p. 241-252. In Japanese. refs the Twenty-second lntersociety Energy Conversion Engineering Technological problems in the development of the scramjet Conference, Philadelphia, PA, Aug. 10-14, 1987. Volume 2 . New are characterized, and scramjet R&D in the United States and York, American Institute of Aeronautics and Astronautics, 1987, p. Japan is reviewed. Work from 1960 to 1975 is summarized, 905-910. including the free-jet engine, the variable geometry engine, the The electrical, mechanical and thermal designs of microproces- component integration model, and the thermal compression engine. sor-based 270Vdc Solid State Power Controllers (SSPCs), developed Also considered is work after 1975, including the airframe integrated using NADC specifications, are discussed. The SSPCs combine the engine and the dual combustor engine. S.H. capabilities to perform all the needed functions of load switching, overload protection, remote control, and Built-In-Test.The Solid-state Electric Logic interface linking the system controller and the SSPC N88-10032 Arizona State Univ., Tempe. controller is described, in addition to the current monitor. The controller MODELING AND MEASUREMENT OF HEAT TRANSFER ON design is based on an eight-bit factory mask-programmable ROM TURBINE BLADE TIPS Ph.D. Thesis CMOS microprocessor, and the main power switch is designed using HEE-KO0 MOON 1987 229 p power MOSFETs. Power is provided by an efficient, low power, mul- Avail: Univ. Microfilms Order No. DA871 1465 tiple output power supply. R.R. Local mass transfer measurements are made for flow through a narrow slot-type channel where one of the boundary walls contains a transverse rectangular cavity and the other is in motion. The study models heat transfer on the grooved tips of axial turbine blades. A naphthalene sublimation technique together with a A88-11976# microcomputer-controlledmeasurement system provides detailed AN IMPROVED STIRLING ENGINE FOR MODEL AIRCRAFT local mass transfer information. Overall mass transfer is not PROPULSION measurable affected by the moving boundary for cavity ROB MCCONAGHY (New Machine Co., Kirkland, WA) IN: IECEC depth-to-width ratios of 0.10, 0.25, 0.50, 1.00, and 1.50. As cavity '87; Proceedings of the Twenty-second lntersociety Energy depth increases, overall mass transfer stays essentially the same Conversion Engineering Conference, Philadelphia, PA, Aug. 10-14, until the immediate depth-to-width ratio of 0.5 is reached, then 1987. Volume 4 . New York, American Institute of Aeronautics increases. The direction of the moving wall relative to the mean and Astronautics, 1987, p. 1831-1 834. refs flow direction does not effect the overall mass transfer but does The design of an improved Stirling engine for model aircraft change local distributions, especially on the cavity floor and side propulsion is described. The engine is based on a previously walls. Stanton number averaged over the entire tip area decreases designed single cylinder, Beta-type engine which ran well but fell exponentially with gap Reynolds number over the test range of far short of the goal for power to weight ratio (300-400 Wlkg). .38 to 3.6 x 10 to the 4th power, but overall mass transfer increases. The paper describes design changes and test results for an Gap clearance is inversely related to overall mass transfer and improved version of this engine. Lightweight, tubular heat influences significantly the local mass transfer distribution in the exchangers replace the annular gap type previously used. Better gap regions. Dissert. Abstr. dynamic balance has also been achieved. Author

N88-10033# Georgia Inst. of Tech., Atlanta. School of Aerospace A88-12836 Engineering. PLUME INFRARED SIGNATURE MEASUREMENTS AND FLAME DRIVING OF LONGITUDINAL INSTABILITIES IN LIQUID COMPARISON WITH A THEORETICAL MODEL FUELED DUMP COMBUSTORS Final Report, 1 Jul. 1984 - 30 SANTO COGLIANDRO and PAOLA CASTELLI (Rinaldo Piaggio - Jun. 1987 lndustrie Aeronautiche e Meccaniche S.p.A., Finale Ligure, Italy) BEN T. ZINN, UDAY G. HEGDE, DlERK REUTER, and 6. R. IN: Infrared technology XII; Proceedings of the Meeting, San Diego, DANIEL 1 Jul. 1987 114 p CA, Aug. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical (Contract NO0014-84-K-0470) Instrumentation Engineers, 1986, p. 73-79. (AD-A183536) Avail: NTlS HC AO6/MF A01 CSCL 21 B The identification of the most important parameters in the plume This report describes the results of experimental and theoretical IR emissions of rotorcraft turboshaft engines is presently investigations of the mechanisms by which the core flow undertaken in the 1-14.5 micron band by a spectroradiometer, combustion process in coaxial, single inlet, dump type ramjet whose field test measurement results are then compared with engines drives longitudinal combustion instabilities. To this end, those of a computer model. Spatial results, which are available in the behavior of V-shaped flames, similar to those often occurring 128 x 128-element images, are important to the understanding of in ramjet combustors, stabilized in longitudinal acoustic fields has such phenomena as turbulence and nonaxisymmetric emission. been studied. The presence of burning vortical structures is Atmospheric transmittance and background emission are measured observed in the flame region. These structures appear at in order to yield the most realistic IR signatures possible. The frequencies close to the first natural acoustic frequency of the results are being applied in a rotorcraft IR signature-suppression combustor and are believed to be connected with a shear layer program. O.C. type of instability of the flame. Experiments conducted show that the unsteady combustion in these structures is capable of driving the acoustics at the fundamental acoustic mode frequency. With A88-13076# increase in fuel air ratio, a spontaneous instability involving the CURRENT DESIGN STATUS AND DESIGN TREND OF FUEL fundamental mode is observed and explained in terms of increased INJECTORS FOR JET ENGINES driving associated with the higher, unsteady heat release rates. YUKlNORl SAT0 Japan Society for Aeronautical and Space The results of experiments conducted with external acoustic Sciences, Journal (ISSN 0021-4663), vol. 34, no. 393, 1986, p. excitation of the flame at different frequencies are also reported 519-530. In Japanese. refs and confirm the idea that the vortical structures arise due to a Technological trends in fuel-injector design for jet engines are fluid mechanical instability of the flame. It is shown that the reviewed along with the efficiency parameters and requirements interactions between the vortical structures and the system's for jet-engine combustors. The functional characteristicsof air blast, acoustic field affect the heat release rates from the flame and pressure blast, rotary, and evaporative fuel injectors are compared. provide a mechanism for the driving of longitudinal mode The designs of various air-blast injectors are considered. S.H. instabilities. GRA

33 07 AIRCRAFT PROPULSION AND POWER

N88-10035# Technische Hochschule, Aachen (West Germany). N88-10791*# General Electric Co., Cincinnati, Ohio. Aircraft Inst. fuer Strahlantriebe und Turboarbeitsmaschinen. Engine Business Group. INVESTIGATION OF THE EXCITATION OF TURBINE BLADE BLADE LOSS TRANSIENT DYNAMICS ANALYSIS, VOLUME 1. VIBRATION IN AXIAL COMPRESSORS IN ROTATING STALL TASK 2 TETRA 2 THEORETICAL DEVELOPMENT Final Final Report [UNTERSUCHUNG DER SCHWINGUNGSER- Report REGUNG VO LAUFSCHAUFELN IN AXIALVERDICHTERN BE1 VINCENTE C. GALLARDO and GERALD BLACK Nov. 1986 ROTATING STALL] 92 P W. MOLL Oct. 1986 64 p In GERMAN (Contract NAS3-24381) (Contract DFG-KO-786/2-3-DER) (NASA-CR-179632; NAS 1.26:179632) Avail: NTlS HC AO5/MF (ETN-87-90377) Avail: NTlS HC A04/MF A01 A01 CSCL21E Measurements were performed on the seven-stage axial The theoretical development of the forced steady state analysis compressor of a gas turbine to study the characteristics of the of the structural dynamic response of a turbine engine having rotating separation zones in the first stages and their effects on nonlinear connecting elements is discussed. Based on modal the production of vibrations. A contactless optoelectronic measuring synthesis, and the principle of harmonic balance, the governing system for rotating compressor turbines was developed. The relations are the compatibility of displacements at the nonlinear unsteady flow quantities in the seven-stage compressor in rotating connecting elements. There are four displacement compatibility stall were determined using the split-film-probe measuring equations at each nonlinear connection, which are solved by technique. A calculation model for the prediction of the compressor iteration for the principle harmonic of the excitation frequency. behavior in the first stage of the axial compressor was developed The resulting computer program, TETRA 2, combines the original on the basis of a nonlinear theory. ESA TETRA transient analysis (with flexible bladed disk) with the steady state capability. A more versatile nonlinear rub or bearing element which contains a hardening (or softening) spring, with or without deadband, is also incorporated. Author

N88-10037# Technische Univ., Munich (West Germany). N88-10792’# General Electric Co., Cincinnati, Ohio. Aircraft Fakultaet fuer Maschinewesen. Engine Business Group. EXPERIMENTAL DETERMINATION OF THE OSCILLATORY BLADE LOSS TRANSIENT DYNAMICS ANALYSIS, VOLUME 2. FORCES ON TWO TURBINE BLADE PROFILES Ph.D. Thesis TASK 2: TETRA 2 USER’S MANUAL Final Report [EXPERIMENTELLE BESTIMMUNG DER SCHWINGUNGSER- GERALD BLACK and VINCENTE C. GALLARDO Nov. 1986 REGERKRAEFTE ZWElER TURBINENSCHAUFELPROFILE] 204 p MICHAEL HUBENSTEINER 1986 151 p In GERMAN (Contract NAS3-24381) Sponsored by Deutschen Forschungsgemeinschaft, West (NASA-CR-179633; NAS 1.26:179633) Avail: NTlS HC AlO/MF Germany A01 CSCL 21E (ETN-87-90417) Avail: NTlS HC AO8/MF A01 This is the user’s manual for the TETRA 2 Computer Code, a The behavior of two 50%-reaction blades of different profile program developed in the NASA-Lewis Blade Loss Program. shape in the case of cascade interference under steady and TETRA 2 calculates a turbine engine’s dynamic structural response unsteady flow was investigated in a cascade wind tunnel. The from applied stimuli. The calculation options are: (1) transient pressure distribution along the blade profiles was measured as a response; and (2) steady state forced response. Based on the function of the relative position of the blades. The friction wake method of modal syntheses, the program allows the use of linear, for both profiles was determined for different cascade distances. as well as nonlinear connecting elements. Both transient and steady The unsteady pressure distribution on the blade profiles was state options can include: flexible Bladed Disk Module, and measured in an air test turbine, and the oscillatory forces were Nonlinear connecting elements (includingdeadband, hardeningkoft- deduced. The amplitude of the oscillation depends on the axial ening spring). The transient option has the additional capability to distance between the cascades, the velocity triangles in the stage, calculate response with a squeeze film bearing module. TETRA 2 and the relative position of the blades in the neighboring oscillating output is summarized in a plotfile which permits post processing such cascade. Harmonics of the oscillatory forces were observed. The as FFTor graphical animation with the proper software and computer results show that production defects in the cascades can lead to equipment. Author significant unsteady forces on the blades. ESA

N88-10992# Joint Publications Research Service, Arlington, Va. TURBINES WITH COUNTERROTATING RUNNERS FOR AIRCRAFT POWER PLANTS Abstract Only N88-10789# Rolls-Royce Ltd., Derby (England). B. A. PONOMAREV and YU. V. STOSENKO ln its USSR Report: I THE WIDE CHORD FAN BLADE A ROLLS ROYCE FIRST Engineering and Equipment p 93 4 May 1987 Transl. into D. J. NICHOLAS 1 Jun. 1987 31 p Presented at the 8th ENGLISH from lzvestiya Vysshikh Uchebnykh Zavedeniy: BABE Conference, Cincinnati, Ohio, 15-19 Jun. 1987 Aviationnaya Tekhnika (Kazan, USSR), no. 2, Apr. - Jun. 1986 p (PNR90416; ETN-87-91005) Avail: NTlS HC AO3/MF A01 50-53 Original language document was announced in IAA as The performance benefits of the wide chord fan compared to A87-15211 the conventional, snubbered, high aspect ratio design are Avail: NTlS HC A07/MF A01 described. The main mechanical design aspects of the fabricated A classification of turbines with counter rotating rotors is blade are outlined. Criteria such as the choice of blade numbers, presented, and their classifications in aircraft power plants of FOD resistance, cyclic fatigue, and vibration characteristics are various types are examined. The principal gasdynamic examined together with the computer modeling and method of characteristics of the traditional (fixed stator) and nontraditional stressing which ensures the correct aerodynamic shape under (birotational) turbine designs are discussed. For birotational centrifugal and pressure load conditions. The physical construction turbines, characteristic kinematic relationships are obtained, and of the blade and the method of manufacture are summarized. an expression is proposed for determining the gasdynamic loading The RB 21 1-535 E4 service record is reviewed. ESA parameter. E.R.

34 08 AIRCRAFT STABILITY AND CONTROL

N88-lO993# Joint Publications Research Service, Arlington, Va. A88-10159' National Aeronautics and Space Administration. DIAGNOSIS OF FLOW CHANNEL IN AIRCRAFT GASTURBINE Langley Research Center, Hampton, Va. ENGINES ON BASIS OF VIBRATION SPECTRUM CHARACTERIS- FLYING COMPLEX APPROACH PATHS USING THE TICS Abstract Only MICROWAVE LANDING SYSTEM A. G. MIRONOV and S. M. DOROSHKO ln its USSR Report: CHARLES E. KNOX (NASA, Langley Research Center, Hampton, Engineering and Equipment p 93 4 May 1987 Transl. into VA) IN: Aerospace Behavioral Engineering Technology ENGLISH from lzvestiya Vysshikh Uchebsnykh Zavedeniy: Conference, 5th, Long Beach, CA, Oct. 13-16, 1986, Proceedings Aviatsionnaya Tekhnika (Kazan, USSR), no. 2, Apr. - Jun. 1986 p . Warrendale, PA, Society of Automotive Engineers, Inc., 1986, p. 45-49 Original language document was announced in IAA as 65-82. refs A87-15210 (SAE PAPER 861771) Avail: NTlS HC A07/MF A01 A piloted simulation study was conducted to examine the An improved vibration spectrum model is presented which allows requirements for using electromechanical flight instrumentation to for the presence of combination components. Methods are then provide guidance for manually controlled flight along complex, examined for evaluating the aerodynamic inhomogeneity of a rotor curved approach paths within the microwave landing system signal of a dual shaft gas turbine engine from the vibration parameters coverage. The data from these tests indicated that flight director based on the combination components. The accuracy of the results guidance is required for the manually controlled flight of a jet is confirmed experimentally. E.R. transport airplane on complex, curved approach paths. Each of the three guidance algorithms tested could be used to fly the paths. However, pilot comments indicated that the use of guidance N88-11152'# Garrett Turbine Engine Co., Phoenix, Ariz. based on capturing the next straight path segment may not be COMBUSTOR-DIFFUSER INTERACTION PROGRAM acceptable since full-scale lateral deflections normally resulted R. SRlNlVASAN and C. WHITE ln NASA. Lewis Research Center, during turns. Pilot comments indicated that all the approach paths Turbine Engine Hot Section Technology, 1985 p 121-125 Oct. tested could be used in normal airline operations. Approach paths 1985 with both multiple, sequential turns and short final path segments (Contract F33615-84-C-2427) were demonstrated. Author Avail: NTlS HC A19/MF A01 CSCL 21E A collection of empirical and analytical design methodology on combustor-diffuser systems was completed. A fully elliptic code was selected for analyzing the combustor-diffuser interaction. Analytical model predictions were obtained for all flow conditions at which Phase 2 tests will be conducted. These results will be A88-10163 compared with laser doppler velocimeter data. Furthermore, a IMPROVEMENTS IN AIRCRAFT SAFETY AND OPERATIONAL generalized nonorthogonal grid system is being developed to DEPENDABILITY FROM A PROJECTED FLIGHT PATH accurately simulate complex wall shapes. Author GUIDANCE DISPLAY JOHN DESMOND (Flight Dynamics, Inc., Portland, OR) IN: Aerospace Behavioral Engineering Technology Conference, 5th, Long Beach, CA, Oct. 13-16, 1986, Proceedings . Warrendale, PA, Society of Automotive Engineers, Inc., 1986, p. 113-124. 08 refs (SAE PAPER 861732) AIRCRAFT STABILITY AND CONTROL The advantages that can be gained in aircraft safety and operating dependability through the use of projected flight path Includes aircraft handling qualities; piloting; flight controls; and guidance are discussed. During a test program developed to autopilots. determine the improvement in approach path control and touchdown precision afforded by a projected flight path display, it was found that the availability of this information reduced the A88-10095# touchdown footprint, eliminated the short and long landings, and SYNTHESES OF REDUCEWRDER CONTROLLERS FOR reduced the number of go-arounds from six to zero. With the ACTIVE FLUlTER SUPPRESSION inertial flight path, pilots can identify not only the windshear event, ATSUSHI FUJlMORl and HlROBUMl OHTA Japan Society for but also the effect of the shear and the pilot's recovery action Aeronautical and Space Sciences, Journal (ISSN 0021-4663). vol. against it. The ability of pilots using the HUD Guidance System to 35, no. 402, 1987, p. 353-362. In Japanese, with abstract in meet the requirements of GAT 111 operations is evaluated. K.K. English. refs Reduced-order controllers for active flutter suppression of a two-dimensional airfoil are studied using two design approaches. One is based on the generalized Hessenberg representation(GHR) in the time domain, and the other, called the Nyquist frequency A88-10 164 approximation (NFA), is a method in the frequency domain. In the THE ADVANTAGE OF FLIGHTPATH-ORIENTED SITUATION NFA method, the reduced-order controllers are designed so that DISPLAYS DURING MICROBURST ENCOUNTERS the stability margin of the Nyquist plot may be increased over a J. G. OLIVER (Air Line Pilots Association, Washington, DC) IN: specific frequency range. To illustrate and to make a comparison Aerospace Behavioral Engineering Technology Conference, 5th, between the two methods, numerical simulations are carried out Long Beach, CA, Oct. 13-16, 1986, Proceedings . Warrendale, using a thirteenth-order controlled plant. It is to be noted that the PA, Society of Automotive Engineers, Inc., 1986, p. 125-127. GHR method can yield quasi-optimal controllers in the sense of (SAE PAPER 861733) minimizing quadratic performance indices. The designed controllers, It is maintained that the conventional instruments mounted in however, do not have enough stability margin, and the order commercial cockpits today do not adequately provide the reduction resulting from full state controllers may not be information necessary to enable a pilot to recognize the onset of satisfactory. On the other hand, reduced-order controllers in the a microburst early enough or to fly an optimum flightpath thereafter. NFA method can be designed with increased stability margin at An integrated instrument display that would portray the aircrafts's the expense of the performance index. For all simulation cases, actual flightpath integrated with an efficient, confusion-free display the NFA method yields second-order controllers with a better of airspeed or angle of attack and altitude above terrain is needed. stability margin than those by the GHR method. Thus, the NFA It is concluded that the accident rate will remain the same until a method provides an effective method for synthesizing robust predictory detection device is developed or flight-path oriented reduced-order controllers. Author instrumentation is made available. K.K.

35 08 AIRCRAFT STABILITY AND CONTROL

A88-10167 N88-10038# Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn AIRLINE REQUIREMENTS ON A FLY-BY-WIRE AIRCRAFT - A (West Germany). PILOT'S VIEW FLUTTER SUPPRESSION AND GUST LOAD ALLEVIATION. PETER H. HELDT (Deutsche Lufthansa AG, Cologne, Federal PART 1: RESULTS OF PHASE 1 TO 3. PART 2 DESCRIPTION Republic of Germany) IN: Aerospace Behavioral Engineering OF THE GARTEUR MODEL Technology Conference, 5th, Long Beach, CA, Oct. 13-16, 1986, H. HOENLINGER, R. MANSER, and D. MUSSMANN 20 Mar. Proceedings . Warrendale, PA, Society of Automotive Engineers, 1985 64 p Inc., 1986, p. 177-179. (MBB-LKE292/S/PUB/191; ETN-87-90579) Avail: NTlS HC (SAE PAPER 861804) A04/MF A01 The advantages of a fly-by-wire aircraft include added safety An adaptive flutter suppression system using target functions features, improved handling characteristics, reduction of training to adjust gain and phase of the control law was developed. The costs, and more flexibility in flight deck arrangement. The paper system was installed in a flutter model and tested successfully. discusses the ways in which these features match the operational The flutter speed can be increased 38%. A gust load alleviation requirements of airlines. Particular attention is given to the flight system was developed and tested on the model. Flutter suppressor I deck arrangement, system architecture, the controller, handling, and gust load alleviation systems were combined and investigated training, control laws and safety, and evaluation. K.K. under gusts. The wing root bending moment of the model can be decreased considerably. The model used for testing active control technology is described. It is a dynamically scaled subsonic model A88-12487 with hydraulically driven control surfaces. Basic geometry and mass A MATHEMATICAL MULTI-POINT MODEL FOR AIRCRAFT data are given. The model instrumentation, model suspension,

~ MOTION IN MOVING AIR and wind tunnel test set up is explained. ESA R. BROCKHAUS (Braunschweig, Technische Universitaet, Brunswick, Federal Republic of Germany) Zeitschrift fuer N88-10039'# Systems Technology, Inc., Hawthorne, Calif. Flugwissenschaften und Weltraumforschung (ISSN 0342-068X). vol. INVESTIGATION OF INTERACTIONS BETWEEN LIMB-MA- 11, May-June 1987, p. 174-184. refs NIPULATOR DYNAMICS AND EFFECTIVE VEHICLE ROLL CON- I The nonlinear equations of aircraft motion in moving air are TROL CHARACTERISTICS Final Report introduced and their interactions illustrated by block diagrams. This D. E. JOHNSTON and D. T. MCRUER Washington NASA mathematical model reflects the fact that wind and aircraft motion May 1986 65 p Previously announced as N86-32991 are strongly coupled, aircraft forces and moments being generated (Contract NAS2-11454) by the relative motion between the air and the aircraft. The usual (NASA-CR-3983; H-1320; NAS 1.263983) Avail: NTlS HC one-point model is first considered, using the classical approach A04/MF A01 CSCL OIC of overall quasi-steady derivatives. This is developed to provide a A fixed-base simulation was performed to identify and quantify I multipoint model, in which the effects of aircraft rotation, wind interactions between the pilot's hand/arm neuromuscular gradients, wing downwash, and engine flow can be modeled more subsystem and such features of typical modern fighter aircraft roll precisely by a generalized approach. Quasi-steady terms are rate command control system mechanization as: (1) force sensing replaced by the calculation of local velocities and forces. This side-stick type manipulator; (2) vehicle effective role time constant; approach has great potential for improving the accuracy with which and (3) flight control system effective time delay. The simulation aircraft motion is simulated. C.D. results provide insight to high frequency pilot induced oscillations (PIO) (roll ratchet), low frequency PIO, and roll-to-right control and handling problems previously observed in experimental and A88-12646 production fly-by-wire control systems. The simulation config- RECENT TILT ROTOR FLIGHT CONTROL LAW INNOVATIONS urations encompass andlor duplicate actual flight situations, I DWAYNE F. KIMBALL (Bell Helicopter Textron, Fort Worth, TX) reproduce control problems observed in flight, and validate the American Helicopter Society, Journal (ISSN 0002-871 l), vol. 32, concept that the high frequency nuisance mode known as roll July 1987, p. 33-42. refs ratchet derives primarily from the pilot's neuromuscular subsystem. This paper describes three distinct control law functions recently The simulations show that force-sensing side-stick manipulator developed in conjunction with full-scale development of the force/displacement/command gradients, command prefilters, and I Bell-Boeing V-22 Osprey tilt rotor. Two of these are designed to flight control system time delays need to be carefully adjusted to improve the speed response of the aircraft. The first quickens minimize neuromuscular mode amplitude peaking (roll ratchet thrust response to power lever inputs by varying proprotor RPM tendency) without restricting roll control bandwidth (with resulting through a governor feedforward circuit. The second gives the power sluggish or PI0 prone control). Author lever direct control of an aerodynamic brake formed by the aircraft's flaperon control surfaces. The third control law function is a model N88-10793# National Aerospace Lab., Tokyo (Japan). follower concept for mast torque control which protects against MEASUREMENTS IN THE FUNCTIONAL MOCK UP TEST OF drive system overtorque and reduces thrust axis workload in all THE NAL QSTOL AIRCRAFT CONTROL SYSTEM flight modes. The paper discusses the handling qualities of the AKlRA TADA, TOSHIO OGAWA, HlROYUKl YAMATO, TADAO aircraft that prompted the development of these functions, and UCHIDA, and NORlAKl OKADA Apr. 1987 30 p In JAPANESE; the improvements resulting from each as determined by analysis ENGLISH summary and flight simulation. Author (NAL-TR-928; ISSN-0389-4010) Avail: NTlS HC A03/MF A01 In the functional mock up test of the NAL QSTOL research aircraft control system, measurements were planned and conducted A88-13080# with the intention of obtaining both real time results to support DESIGN STUDY FOR AN FBW LATERAL CONTROL SYSTEM the development immediately, and reserved data suitable for YUlCHl HONDA, YASUO TAKEUCHI, and HISANAO NAKAYAMA academically rigorous and detailed analyses from various points Japan Society for Aeronautical and Space Sciences, Journal (ISSN of view. The physical quantities of 208 system variables were 0021-4663), vol. 34, no. 394, 1986, p. 600-607. In Japanese. converted to analog voltage signals, and supplied from junction refs boxes to devices for recording and analysis. The system A fly-by-wire (FBW) lateral control system for transport aircraft characteristics of primary interest in each test were investigated has been designed, and its safety and reliability have been using chart recorders, a two-channel X-Y recorder, an FFT analyzer, investigated. System control requirements and examples of and a monitoring unit of the on-board computers. A pre-processor control-system failure for the FAR 25 are discussed. Flying quality unit of a minicomputer system converted 64 channels of the analog requirements are discussed along with problems in the design of data to disk image digital data with a sampling rate of 100 Hx for the FBW control system. S.H. each channel. Up to two hours of test data were temporarily stored

I 36 08 AIRCRAFT STABILITY AND CONTROL in the desk file, and then, as a part of near time processings, N88-10799# Marconi Avionics Ltd., Rochester (England). Combat were transferred to magnetic tapes for preservation. A digital Aircraft Controls Div. filtering and sampling technique, designated the Filtering Sample, SOME APPROACHES TO THE DESIGN OF HIGH INTEGRITY was applied to the conversion of the pre-processor unit. The SOFTWARE Filtering Sample showed a good anti-aliasing effect within a J. T. SHEPHERD, D. J. MARTIN, and R. B. SMITH ln AGARD, reasonable increment of the processing work load. Author Fault Tolerant Considerations and Methods for Guidance and Control Systems 14 p Jul. 1987 Sponsored by Ministry of Defence, United Kingdom N88-10794# Aeronautical Research Labs., Melbourne Avail: NTlS HC A07/MF A01 (Australia). As the complexity of aircraft systems has increased and the performance requirements for such aircraft have become more A SURVEY OF AIRCRAFT INTEGRATED CONTROL TECHNOLOGY demanding the number of safety critical systems carried has R. D. HILL Sep. 1987 28 p increased. This allied to the preponderance of digital systems on (AR-004-561; ARL-SYS-TM-95) Avail: NTlS HC A03/MF A01 board the aircraft has meant that the software requirements of Current design techniques applied to aircraft flight control safety critical systems have become one of the key items in the systems have been surveyed and the increasing use of modern development of new aircraft. In the early days of high integrity control theory in the control system design of experimental systems analog techniques were used and a variety of redundancy technology demonstrator aircraft is described. The modern control techniques developed to cope with the need to obtain the required system design methodology is seen to be particularly suitable for level of integrity from system elements whose inherent reliability application to the design of controllers for complex, multivariable was low. With the advent of digital systems it is necessary to aircraft systems which are composed of dynamically interacting consider how much integrity can be achieved with system software subsystems. These will typically include the flight control, so that the total integrity of a safety critical system can be propulsion, and weapon systems. Some suggestions regarding the maintained. This can be achieved by fault avoidance or fault most appropriate form of future ARL involvement in this large and tolerance. To date the former has been the main method used to expanding area are made. Author achieve high integrity software. However, fault avoidance to be effective must assume an error free system, which is near impossible to achieve. Fault avoidance is combined with fault tolerance, which adjusts the system to its inherent errors, and is N88-10795# Cranfield Inst. of Tech., Bedford (England). College added to assure greater reliability. F.M.R. of Aeronautics. A PRELIMINARY INVESTIGATION INTO THE FEASIBILITY OF N88-10800# Deutsche Forschungs- und Versuchsanstalt fuer IMPLEMENTING A DIRECT SIDEFORCE CONTROL SYSTEM ON Luft- und Raumfahrt, Wesseling (West Germany). Inst. for Flight THE ASTRA HAWK BY MEANS OF AN ACTIVE CONTROL System Dynamics. SURFACE M.S. Thesis ROBUST CONTROL SYSTEM DESIGN V. A. ENGLISH Sep. 1986 196 p J. ACKERMANN ln AGARD, Fault Tolerant Considerations and (ETN-87-90924) Avail: NTlS HC AO9/MF A01 Methods for Guidance and Control Systems 14 p Jul. 1987 A computer program to test the effect of an auxiliary surface Previously announced as N81-11275 by simulating the direct sideforce modes of motion, in order to Avail: NTlS HC A07/MF A01 estimate the maximum mode performance benefits, was developed. The short period longitudinal mode of an F 4-E with horizontal The program is written as a design tool, which incorporates data canards is unstable in subsonic flight and insufficiently damped at for the flight envelope from Mach 0.3 to 0.8 and from sea level supersonic speed. The control system has to provide acceptable to 36,000 ft, for the basic aircraft, with provision to add in derivatives pole locations according to military specificationsfor flying qualities. due to the auxiliary surface. The program can be used to re-evaluate A fixed gain controller using three paralleled gyros is designed, the behavior of the aircraft with auxiliary surface as the such that the pole region requirements in four typical flight aerodynamics, geometry of the surface, position of the surface on conditions are robust with respect to a gain reduction to one the airframe, and hence derivatives of the surface are revised. third. Thus nothing bad happpens immediately when one or two ESA gyros fail. Failure detection alid redundancy management may be performed at a higher hierarchical level, and not necessarily extremely fast. The use of accelerometers or air data sensors for N88-10798'# National Aeronautics and Space Administration. angle of attack or dynamic pressure is totally avoided in this concept Langley Research Center, Hampton, Va. and no gain scheduling is necessary. The design for robustness THE APPLICATION OF EMULATION TECHNIQUES IN THE with respect to different flight conditions and sensor failures is ANALYSIS OF HIGHLY RELIABLE, GUIDANCE AND CONTROL performed by a novel parameter space design tool. Author COMPUTER SYSTEMS GERARD E. MIGNEAULT In AGARD, Fault Tolerant N88-10801'# National Aeronautics and Space Administration. Considerations and Methods for Guidance and Control Systems Langley Research Center, Hampton, Va. 12 p Jul. 1987 RELIABILITY MODELING OF FAULT-TOLERANT COMPUTER Avail: NTlS HC A07/MF A01 CSCL 01C BASED SYSTEMS Emulation techniques can be a solution to a difficulty that arises SALVATORE J. BAVUSO ln AGARD, Fault Tolerant in the analysis of the reliability of guidance and control computer Considerations and Methods for Guidance and Control Systems systems for future commercial aircraft. Described here is the 16 p Jul. 1987 difficulty, the lack of credibility of reliability estimates obtained by Avail: NTlS HC A07/MF A01 CSCL 01C analytical modeling techniques. The difficulty is an unavoidable Digital fault-tolerant computer-based systems have become consequence of the following: (1) a reliability requirement so commonplace in military and commercial avionics. These systems demanding as to make system evaluation by use testing infeasible; hold the promise of increased availability, reliability, and (2) a complex system design technique, fault tolerance; (3) system maintainability over conventional analog-based systems through reliability dominated by errors due to flaws in the system definition; the application of replicated digital computers arranged in and (4) elaborate analytical modeling techniques whose precision fault-tolerant configurations. Three tightly coupled factors of outputs are quite sensitive to errors of approximation in their input paramount importance, ultimately determining the viability of these data. Use of emulation techniques for pseudo-testing systems to systems, are reliability, safety, and profitability. Reliability, the major evaluate bounds on the parameter values needed for the analytical driver affects virtually every aspect of design, packaging, and field tachniques is then discussed. Finally several examples of the operations, and eventually produces profit for commercial application of emulation techniques are described. Author applications or increased national security. However, the utilization

37 08 AIRCRAFT STABILITY AND CONTROL

of digital computer systems makes the task of producing credible digital system was frame synchronized, which provided several reliability assessment a formidable one for the reliability engineer. advantages in implementing the resident backup software system. The root of the problem lies in the digital computer’s unique Since the time of the flight tests, two other flight vehicle programs adaptability to changing requirements, computational power, and have made a commitment to incorporate resident backup software ability to test itself efficiently. Addressed here are the nuances of similar in nature to the system described here. Author modeling the reliability of systems with large state sizes, in the Markov sense, which result from systems based on replicated redundant hardware and to discuss the modeling of factors which N88-10806# Advisory Group for Aerospace Research and can reduce reliability without concomitant depletion of hardware. Development, Neuilly-Sur-Seine (France). Guidance and Control Advanced fault-handling models are described and methods of Panel. acquiring and measuring parameters for these models are KNOWLEDGE BASED CONCEPTS AND ARTIFICIAL INTELLI- delineated. Author GENCE: APPLICATIONS TO GUIDANCE AND CONTROL Aug. 1987 145 p Lectures held in Ottawa, Ontario, 10-11 N88-10803# Deutsche Forschungs- und Versuchsanstalt fuer Sep., in Monterey, Calif., 14-15 Sep., in Delft, Netherlands, 12-13 Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer Oct., and in Lisbon, Portugal, 15-16 Oct. 1987 Flugfuehrung. (AGARD-LS-155; ISBN-92-835-1588-7) Avail: NTlS HC A07/MF OPTIMAL DETECTION OF SENSOR FAILURES IN FLIGHT A0 1 CONTROL SYSTEMS USING DETERMINISTIC OBSERVERS The intent of this lecture series was to clearly describe what NORBERT STUCKENBERG In AGARD, Fault Tolerant artificial intelligence techniques mean with respect to guidance Considerations and Methods for Guidance and Control Systems and control applications, to offer some concrete examples of 21 p Jul. 1987 applications to the maintenance area, some more speculative Avail: NTlS HC A07/MF A01 examples of applications to actual guidance and control tasks, A failure detection scheme for sensors of a flight control system and a projection of possible directions for the future. is presented. Based on analytic redundancy a duplex sensor configuration provides the fail-operational capability of a conventional triplex sensor system. This is achieved by using N88-10807# General Electric Co., Binghamton, N.Y. deterministic observers. It is shown how the performance of the OVERVIEW OF AGARD LECTURE SERIES NO. 155: KNOWL- failure detection scheme can be determined. With respect to this EDGE-BASED CONCEPTS AND ARTIFICIAL INTELLIGENCE AP- performance criterion the optimal observer is derived. Thus, the PLICATIONS TO GUIDANCE AND CONTROL performance eventually achievable by an optimal failure detection RIHCARD PAUL QUlNLlVAN In AGARD, Knowledge Based scheme is also described. The operational feasibility of the Concepts and Artificial Intelligence: Applications to Guidance and proposed concept is demonstrated by flight test results. Author Control 5 p Aug. 1987 Avail: NTlS HC A07/MF A01 N88-10804# Verilog SA., Toulouse (France). Several lectures dealing with artificial intelligence (AI) ASSESSMENT OF SOFTWARE QUALITY FOR THE AIRBUS applications to guidance and control are reviewed. The use of A310 AUTOMATIC PILOT various forms of AI techniques to help solve problems related to R. TROY and C. BALUTEAU (Societe Francaise d’Equipements guidance and control is a subject of current interest. Most, if not pour la Navigation Aerienne. Velizy-Villacoublay, France ) In all, of the practical applications utilize knowledge-basedtechniques AGARD, Fault Tolerant Considerations and Methods for Guidance to create so-called ’expert systems’. These systems seem to offer and Control System 13 p Jul. 1987 solutions to guidance and control problems that have a large Avail: NTlS HC A07/MF A01 judgment content. Examples include maintenance systems and As for the whole of the Automatic Flight Control System, the real-time, decision aiding systems. Author automatic pilot for the AIRBUS is a computer system with high criticality. In order to assess the quality of the software, a number N88-10808# Analytic Sciences Corp., Reading, Mass. of observations and measurements have been made during the AI EXPERT SYSTEM TECHNOLOGY ISSUES FOR GUIDANCE development cycle. A general method of evaluation, the data AND CONTROL APPLICATIONS collected, and some evaluation results are presented. The aims HAROLD L. JONES In AGARD, Knowledge Based Concepts of this analysis are to assess the impact of development constraints and Artificial Intelligence: Applications to Guidance and Control 7 on the quality of the product and to evaluate its operational p Aug. 1987 reliability. The results show conditions in which software may be Avail: NTlS HC A07/MF A01 adversely affected by modifications. In particular, they make it A perspective is provided on a set of technical issues, which, possible to appreciate the quality of design, the effectiveness of if unresolved, could limit the capability and acceptability of expert the verification and validation processes, and the flexibility of the systems decision making for avionics applications. Examples from software. The last part gives a tentative example of operational ongoing expert system development programs are used to illustrate reliability evaluation, taking into consideration the complexity of likely architectures and applications of future intelligent avionics the functions and the mission profile. Author systems. Author

N88-10805*# National Aeronautics and Space Administration. N88-10811# Lear Siegler, Inc., Grand Rapids, Mich. Instrument Ames Research Center, Moffett Field, Calif. and Avionic Systems Div. FLIGHT TEST OF A RESIDENT BACKUP SOFTWARE SYSTEM APPLICATION OF KNOWLEDGE-BASED TECHNIQUES TO DWAlN A. DEETS, WILTON P. LOCK, and VINCENT A. MEGNA AIRCRAFT TRAJECTORY GENERATION AND CONTROL (Draper, Charles Stark Lab., Inc., Cambridge, Mass ) In AGARD, MICHAEL W. BIRD In AGARD, Knowledge Based Concepts and Fault Tolerant Considerations and Methods for Guidance and Artificial Intelligence: Applications to Guidance and Control 12 p Control Systems 9 p Jul. 1987 Previously announced as Aug. 1987 N86-19325 (Contract F336 15-84-C-3626) Avail: NTlS HC A07/MF A01 Avail: NTlS HC A07/MF A01 A new fault-tolerant system software concept employing the A concept that embeds the knowledge-based techniques in a primary digital computers as host for the backup software portion trajectory generation and control system is defined. The control has been implemented and flight tested in the F-8 digital fly-by-wire system is called the Unified Trajectory control System (UTCS). airplane. The system was implemented in such a way that The objective of the system is to aid the pilot when operating in essentially no transients occurred in transferring from primary to the intense threat environment projected for the 1990’s. The UTCS backup software. This was accomplished without a significant has an architecture of independent trajectory generation elements increase in the complexity of the backup software. The primary whose operations are integrated by a knowledge-based system. 10 ASTRONAUTICS

This artificial intelligence (AI) technique utilizes production rules, A88-11470 an interface engine, and a system of frames for communicating FLIGHT SIMULATION with the trajectory generation elements. Author J. M. ROLFE, ED. (Ministry of Defence, London, England) and K. J. STAPLES, ED. (Royal Aircraft Establishment, Bedford, England) Cambridge and New York, Cambridge University Press, 1986, 294 p. No individual items are abstracted in this volume. N88-10818’# National Aeronautics and Space Administration, Theoretical and practical aspects of flight simulation (FS) are Washington, D.C. examined in an introductory textbook. Chapters are devoted to INVESTIGATION OF CONTROL LAW FOR ACTIVE FLUTTER the fundamental principles and history of FS; mathematical models SUPPRESSION of FS the simulation of aircraft systems; structures and cockpit WEIPENG WANG, ZHONGQUAN GU, and DEMAO ZHU Nov. systems; motion systems; visual systems; instructors’ facilities; 1987 18 p Transl. into ENGLISH from Acta Aeronautica et integration, testing, and acceptance; the simulator as a research Astronautica Sinica, People’s Republic of China, v. 7, Dec. 1986 tool; and the simulator as a training device. Diagrams, drawings, p 566-574 Original language document was announced in IAA graphs, photographs, and tables of numerical data are provided. as A87-29607 Transl. by Kanner (Leo) Associates, Redwood T.K. City, Calif. Prepared by Nanjing Aeronautical Coll., People’s Republic of China (Contract NASW-4005) (NASA-TT-20126; NAS 1.77:20126) Avail: NTlS HC A03/MF A01 CSCL 01C Discussed is the technology of active flutter suppression research by the use of the wind-tunnel model of a delta wing with low aspect ratio. The research includes the establishment of a mathematical model for the servo-aeroelastic system, and the synthesis and analysis of sub-optimal output feedback control laws for active flutter suppression. Author

A88-12488 DYNAMIC WIND TUNNEL BALANCES IN THE DFVLR SUBSONIC WIND TUNNEL IN BRAUNSCHWEIG [DYNAMISCHE WINDKANALWAAGEN AM NIEDERGESCHWINDIGKEITS-WIND- 09 KANAL DER DFVLR IN BRAUNSCHWEIG] G. KAUSCHE (DFVLR, Brunswick, Federal Republic of Germany) RESEARCH AND SUPPORT FACILITIES (AIR) Zeitschrift fuer Flugwissenschaften und Weltraumforschung (ISSN 0342-068)0, vol. 11, May-June 1987, p. 185-187. In German. refs Includes airports, hangars and runways; aircraft repair and overhaul Two dynamic balances for measuring dynamic derivatives in facilities; wind tunnels; shock tube facilities; and engine test wind tunnels of the DFVLR subsonic wind tunnel in Braunschweig, blocks. the Mobile Oscillatory Derivative Balance (MODB) and the Rotary Derivative Balance (RDB), are briefly described. Information is presented on the measurement methods used, recent improvements A88-10044 and operations, and the attainable results. It is shown that the MODB, TESTING OF AIRCRAFT ELECTRICAL EQUIPMENT [ISPYTANIE due to its mobility, has a higher productivity than the RDB. C.D. AVIATSIONNOGO ELEKTROOBORUDOVANllAl VALERll NIKOLAEVICH BERDNIKOV Moscow, Izdatel’stvo Mashinostroenie, 1986, 192 p. In Russian. refs Methods for the testing of aircraft electrical equipment, both at the stage of manufacture and during its development, are presented in a systematic manner. Attention is given to the technical requirements for the electrical equipment of aircraft, classification of test procedures, test equipment, technical documentation, and safety engineering during testing. The discussion covers testing of electrical, acoustic, and vibration characteristics, mechanical testing, environmental testing, and reliability testing. V.L.

N88-1W41# Royal Aircraft Establishment, Farnborough A88-10156 (England). LOW COST WINDOWLESS COCKPIT RESEARCH VEHICLE INVESTIGATION OF THE SUITABILITY OF THE 8FT X 6FT ROSS E. AILSLIEGER and DAVID T. PALMER (Boeing Military TRANSONIC WIND-TUNNEL FOR AEROACOUSTIC RESEARCH Airplane Co., Wichita, KS) IN: Aerospace Behavioral Engineering ON PROPELLERS Technology Conference, 5th, Long Beach, CA, Oct. 13-16, 1986, W. J. G. TREBBLE Jan. 1987 31 p Proceedings . Warrendale, PA, Society of Automotive Engineers, (RAE-TM-AERO-2093; BR102327; ETN-87-90697) Avail: NTlS Inc.. 1986, p. 45-49. HC AO3IMF A01 (SAE PAPER 861755) The 8ft x 6ft transonic wind tunnel is shown to have a very A commercial extension boom type forklift was modified for high noise level, but near field noise signals from a 0.73 m diameter operation from a remote crew station. Two interchangeable cockpits propeller are readily detected above the tunnel background noise were fabricated: (1) a generic helicopter cockpit with large windows at airspeeds up to at least Mach 0.6. Unfortunately the hard walls and (2) a windowless cockpit with three television scenes projected of the tunnel working chamber produce echoes which interfere on a panoramic display for outside vision. The vehicle is operated with the propeller noise signals. For the facility to be used for by a side-stick controller and a ’collective’ lever. The goal was to aeroacoustic research it is necessary to either develop complex develop a low-cost means to conduct research into windowless analytical methods using multiple microphone techniques or to aircraft operations. The vehicle tests have begun and will be line the interior walls of the working chamber with acoustic expanded as the cockpit electronics are developed. Author blankets. ESA

39 10 ASTRONAUTICS

10 the alloys. Alloys with a ratio of 3.5 or higher tend to favor the Cr oxides while those under 3.0 form mostly AI oxides. In general ASTRONAUTICS the AI203/aluminate spinel forming alloys have the better oxidation resistance. Increased cobalt content lowers the scaling resistance of the higher Cr allys while a 5.0 wt pct Co content is optimum Includes astronautics (general); astrodynamics; ground support for the AI controlling alloys. The refractory metals, particularly Ta, systems and facilities (space); launch vehicles and space vehicles; appear beneficial to both types of oxides, perhaps due to the space transportation; spacecraft communications, command and formation of the omnipresent trirutile Ni(Ta, Cb, Mo, W)206. Both tracking; spacecraft design, testing and performance; spacecraft scales break down as increasing amounts of NiO are formed. instrumentation; and spacecraft propulsion and power. Author

A88- 13086# A88-10180 AN OVERVIEW OF SPACE AND AIRCRAFT NAVIGATION APPLICABILITY OF A DIFFUSION COMBUSTION MODEL TO TATSUKlCHl KOSHIO Japan Society for Aeronautical and Space THE ANALYSIS OF SUPERSONIC TURBULENT REACTING Sciences, Journal (ISSN 0021-4663). vol. 35, no. 396, 1987, p. JETS [O PRlMENlMOSTl MODEL1 DIFFUZIONNOGO GORENllA 2-8. In Japanese. refs K RASCHETU SVERKHZVUKOVYKH TURBULENTNYKH Recent developments connected with the utilization of REAGIRUIUSHCHIKH STRUI] navigation satellites for the GPS and for air traffic control are S. 1. BARANOVSKII and V. A. PERMINOV Fizika Goreniia i reviewed. Consideration is given to the airspace management Vzfyva (ISSN 0430-6228), vol. 23, May-June 1987, p. 85-88. In system and to the operating principles of STAR GPS. The future Russian. refs prospects of navigation satellites are assessed. S.H. The combustion of a supersonic turbulent jet of hydrogen in air was modeled using boundary layer and diffusion combustion N88-10078# Deutsche Forschungs- und Versuchsanstalt fuer approximations. The model included the effect of concentration Luft- und Raumfahrt, Goettingen (West Germany). Inst. for pulsations on the mean values of the thermodynamic quantities. Experimental Fluid Mechanics. The results were compared with measurements obtained in an ANALYSIS OF FREE MOLECULAR EFFECTS ON THE ATTITUDE experiment with a zero ignition delay. It is found that, although an OF SATELLITES IN GEOSTATIONARY TRANSFER ORBIT. analysis including the effect of pulsations gives better results than PART 2 FORCE AND TORQUE MEASUREMENT IN FREE a quasi-laminar approach, the final rates of chemical reactions MOLECULAR WIND TUNNEL TESTS must be considered to correctly model combustion in supersonic G. KOPPENWALLNER and H. LEGGE Paris, France ESA flow. V.L. 1986 50 p (Contract ESOC-5762/83-D-IM(SC)) A88-10872 (DFVLR-IB-222-86-A-07; ESA-CR(P)-2408-VOL-2; ETN-87-90545) FLUIDS FOR DEICING AIRCRAFT SURFACES Avail: NTlS HC AO3/MF A01 Aerospace Engineering (ISSN 0736-2536), vol. 7, Sept. 1987, p. In order to determine the center of pressure of a satellite in 21-23. addition to lift, drag, and moment coefficients, the feasibility of The types of deicing/antiicing fluids and removal procedures combined force and torque measurements in free molecular wind currently used are discussed. The removal procedure involves spray tunnel experiments is analyzed. An electromagnetic two-component applications of aircraft deicing fluids, hot water, or a mixture of balance seems suitable for this task. ESA both; the procedures for applying the fluids on the aircraft are described. The deicing fluids used in North America are 80-90 percent ethylene glycol and 10-20 percent water corrosion inhibitors, wetting agents, and other glycols. The two types of 11 fluids used by European airlines are categorized by material requirements, freezing points, rheological properties, and antiicing CHEMISTRY AND MATERIALS performance characteristics. Type I has a minimum of 80 percent glycol and is used for deicing operations, and type II contains a Includes chemistry and materials (general); composite materials; minimum of 50 percent glycol and is applied in deicing and antiicing inorganic and physical chemistry; metallic materials; nonmetallic operations. The US. military utilizes two types of fluids that are materials; and propellants and fuels. basically the same except that the type II fluid contains sodium salt of tolytriazole. I.F.

A88-10031 National Aeronautics and Space Administration. A88-11001# Lewis Research Center, Cleveland, Ohio. COMBUSTION GAS PROPERTIES. 111 - PREDICTION OF THE THE EFFECT OF VARIATIONS OF COBALT CONTENT ON THE THERMODYNAMIC PROPERTIES OF COMBUSTION GASES OF CYCLIC OXIDATION RESISTANCE OF SELECTED NI-BASE AVIATION AND DIESEL FUELS SUPERALLOYS OEMER L. GUELDER (National Research Council of Canada, Div. CHARLES A. BARRETT (NASA, Lewis Research Center, Cleveland, of Mechanical Engineering, Ottawa) ASME, International Gas OH) IN: Alternate alloying for environmental resistance; Turbine Conference and Exhibition, 32nd, Anaheim, CA, May Proceedings of the Symposium, New Orleans, LA, Mar. 2-6, 1986 31-June 4, 1987. 7 p. refs . Warrendale, PA, Metallurgical Society, Inc., 1987, p. 21 1-231. (ASME PAPER 87-GT-49) Previously announced in STAR as N86-31702. Empirical formulas are presented by means of which the specific Cobalt levels were systematically varied in the Ni-base turbine heat, mean molecular weight, density, and specific heats ratio of alloys U-700 (cast), U-700m (PMIHIP), Waspaloy, Mar-M-247, aviation fuel-air and diesel fuel-air systems can be calculated as In-738, Nimonic-115, U-720, and SX-R-150. the cobalt levels ranged functions of pressure, temperature, equivalence ratio, and from 0 wt pct to the nominal commercial content in each alloy. hydrogen-to-carbon atomic ratio of the fuel. Comparisons of the the alloys were tested in cyclic oxidation in static air at 1000, results from the proposed formulas with the results obtained from 1100 and 1150 C for 500, 200, and 100 hr, respectively. An a chemical equilibrium code show that the mean absolute error in oxidation attack parameter, Ka, derived from the specific weight predicted specific heat is 0.8 percent, and that for molecular weight change versus time data was used to evaluate the oxidation is 0.25 percent. These formulas provide a very fast and easy behavior of the alloys along with X-ray diffraction analysis of the means of predicting the thermodynamic properties of combustion surface oxides. The alloys tend to form either Cr20Wchromite gases as compared to detailed equilibrium calculations, and they spinel or AI203/aluminate spinel depending on the Cr/AI ratio in are also valid for a wide range of complex hydrocarbon mixtures

40 11 CHEMISTRY AND MATERIALS and pure hydrocarbons as well as aviation and diesel fuels. show that the lower the fuel density, the better the high-altitude Author ignition performance. Test results also show that the prevailing theoretical model of spark ignition is reasonable. Author A88-11002# PACK CEMENTATION COATINGS FOR SUPERALLOYS - A A88-11095# REVIEW OF HISTORY, THEORY, AND PRACTICE APPLICATIONS OF CERAMIC COATING ON THE TURBINE G. W. GOWARD and L. W. CANNON (Turbine Components Corp., BLADES OF THE AGTJ-100B Branford, CT) ASME, International Gas Turbine Conference and KAZUO UCHIDA, AKlNORl KOGA, KlYOMl TESHIMA, and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 6 p. refs MASASHI ARAl (Engineering Research Association for Advanced (ASME PAPER 87-GT-50) Gas Turbines, Tokyo, Japan) ASME, International Gas Turbine Nickel- and cobalt-base superalloy blades and vanes in the Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, hot sections of all gas turbines are coated to enhance resistance 1987. 7 p. refs to hot corrosion. Pack cementation aluminizing is the most widely (ASME PAPER 87-GT-190) used coating process. Corrosion resistance of aluminide coatings The high inlet gas temperature (1673 K) of the AGTJ-100B can be increased by modification with chromium, platinum, or advanced high-temperature high-pressure turbine (developed for silicon. Chromium diffusion coatings can be used at lower an energy conservation pilot plant in Japan) requires superior temperatures. Pack cementation and related diffusion coatings thermal insulation; a ceramic thermal barrier coating (TBC) was serve well for most aircraft engine applications. The trend for developed for this purpose. This paper describes a series of tests industrial and marine engines is more toward the use of overlay that evaluated the thermal barrier performance and durability of coatings because of the greater ease of designing these to meet the TBC. The 0.2-0.3 mm thick coating (including the 0.1-mm-thick a wide variety of corrosion conditions. Author bond coat) is made of yttria-stabilized zirconia (Zr02-Y203); the bond coat material is MCrAIY. The blade profile platforms and A88-11010# shrouds are fully covered with the TBC in order not to expose PREDICTION OF NO AND CO DISTRIBUTION IN GAS TURBINE the coating edge to a high temperature and high-speed gas flow. COMBUSTORS Test results are included. IS. SHlNlCHl KAJITA (Kawasaki Heavy Industries, Ltd., Akashi, Japan) and RYUlCHl MATUMOTO (Kobe University, Japan) ASME, A88-11146 International Gas Turbine Conference and Exhibition, 32nd, HYDROGEN IN AIR TRANSPORTATION - FEASIBILITY STUDY Anaheim, CA, May 31-June 4, 1987. 6 p. refs FOR ZURICH AIRPORT, SWITZERLAND (ASME PAPER 87-GT-63) H. P. ALDER (Eidgenoessisches lnstitut fuer Reaktorforschung, An experimental and numerical investigation was performed to Wuerenlingen, Switzerland) International Journal of Hydrogen assess the performance of a procedure for the prediction of NO Energy (ISSN 0360-3199), vol. 12, no. 8, 1987, p. 571-585. refs and CO formed in gas turbine combustors. The experimental As a member of the Ad Hoc Executive Group (AHEG) for procedure consists of measuring the flow, temperature, and ’Hydrogen in Air Transportation’, the Swiss Group, composed of pollutant fields in a premixed-gas turbine combustor. The profiles representatives from industry, Swissair, the utilities and the of velocity, temperature, and concentrations of NO and CO within government, decided to carry out a study on the feasibility of the combustor are predicted by means of a three-dimensional refueling one cargo-aircraftper day with 15 to 30 t of liquid hydrogen model in which the k-epsilon two-dimensional model is used as a (LH2). For the mission California-Europe-Saudi Arabia, Zurich turbulence model, and in which the effect of turbulence on the Airport is well suited as a European base, provided the following reaction rate is taken into account by employing the modified option is chosen: electrolytic hydrogen production, liquefaction and eddy-break-up model. Although qualitative agreement between the storage at one site on the Airport. For the demonstration phase predicted and measured values was fairly good, quantitative the existing infrastructure can absorb the pilot installations without agreement was not obtained. R.R. additional secondary investment. For a commercial operation, however, the economics of the LH2 production has to be improved A88-11052# and the Airport infrastructure (land, power supply, cooling water, PREDICTION OF COMBUSTION PERFORMANCE OF AVIATION runways) has to be expanded. Author KEROSINES USING A NOVEL PREMIXED FLAME TECHNIQUE D. M. CARRIER and R. J. WETTON (Shell Research, Ltd., Thornton A88-12414 Research Centre, Chester, England) ASME, International Gas COMPOSITE DIRECTIONS AT KAMAN Turbine Conference and Exhibition, 32nd, Anaheim, CA, May PAUL F. MALONEY (Kaman Aerospace Corp.. Bloomfield, CT) 31-June 4, 1987. 7 p. Research supported by the Ministry of Vertiflite (ISSN 0042-4455), vol. 33, Sept.-Oct. 1987, p. 26-31. Defence of England. refs An account is given of the interdisciplinary approach employed (ASME PAPER 87-GT-125) by a major composite material aerospace structures manufacturer A novel method for predicting aviation fuel combustion in the design, analysis, material selection/characterization, tool performance has been developed in which the sooting point of a design, and nondestructive testing of all-composite helicopter main premixed flame is detected automatically. Comparisons with rotor blades. The K747 composite main rotor blade program for full-scale combustor data confirm that the technique is a more the U.S. Army’s AH-1 Cobra helicopter, initiated in 1975, has yielded realistic index of combustion quality than Smoke Point or hydrogen over 2600 such blades to date. Attention is given to the SH9F/G content. Author composite main rotor blade, which employs many features of the AH-1 blade but represents the next generation of computer-aided ABB-II ow design, tooling, and fabrication techniques; the use of solid INVESTIGATION OF HIGH-ALTITUDE IGNITION PERFORMANCE aluminum mandrels and matched steel molds yields a dimensionally OF SEVERAL CHINESE JET FUELS WITH DIFFERENT PROPER- exact product with excellent airfoil contour fidelity. O.C. TIES NENG-KUEN CHEN (Beijing Institute of Aeronautics and AB^-124 i5 Astronautics, People’s Republic of China) ASME, International BUILDING ON A SUCCESSFUL TRADITION - COMPOSITES AT Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May MDHC 31-June 4, 1987. 8 p. refs DEAN C. BORGMAN (McDonnell Douglas Helicopter Co., Mesa, (ASME PAPER 87-GT-178) AZ) Vertiflite (ISSN 0042-4455). vol. 33, Sept.-Oct. 1987, p. Investigation of high-altitude ignition performance of five 32-36. Chinese jet fuels with different properties has been conducted at A development history and current status report is presented a simulated-altitude facility. Jet fuels were tested in a small pilot for the advanced aerospace composite structures products of a combustion chamber taken from an existing engine. Test results major US. helicopter manufacturer. Beginning with composite main

41 11 CHEMISTRY AND MATERIALS

rotor and flexbeam tail rotor blades for the AH-64 helicopter, work Am12635 proceeded to Kevlar 29-reinforcedcomposite blades and reinforced HIGH-TEMPERATURE SHEET MATERIALS FOR GAS TURBINE thermosetting resin-based AH-1 helicopter fuselage structures. APPLICATIONS More recently, attention has been given to thermoplastic matrix B. HICKS (Lucas Aerospace, Ltd., Fabrications Div., Burnley, composites for the AH-64 military helicopter and for the England) (Royal Society, Conference on Mechanical Behaviour aerodynamic fairing secondary structures of the C-17 airlifter. of Superalloys, London, England, June 10, 11, 1986) Materials O.C. Science and Technology (ISSN 0267-0836), vol. 3, Sept. 1987, p. 772-781. Research supported by the Ministry of Defence. refs Am12626 Aircraft gas turbines contain various sheet metal fabrications, CONFERENCE ON MECHANICAL BEHAVIOR OF SUPERAL- such as combustion chambers, exhaust units, jet pipes, and reheat LOYS, LONDON, ENGLAND, JUNE 10,11,1986, SELECTED PA- liners, which operate for long periods under arduous conditions. PERS The properties required in a sheet alloy differ considerably from Conference sponsored by the Royal Society. Materials Science those of blades and vanes, so that alloys must be developed and Technology (ISSN 0267-0836), vol. 3, Sept. 1987. 129 p. For specifically for the purpose. The performance required of sheet individual items see A88-12627 to A88-12636. alloys is discussed and current alloys are reviewed in terms of The present conference on the development status of superalloy their fabrication, mechanical, and oxidation properties. Some recent compositions and processing methods for such applications as developments are described in the field of thermal barrier coatings, gas turbine blades and disks gives attention to the mechanical dispersion strengthened alloys, and porous laminate materials. property requirements and creep behavior of aircraft gas turbine Author materials, the low cycle fatigue behavior and the fatigue crack growth of superalloy blade materials at elevated temperatures, A88-12786 and novel materials for industrial gas turbines. Also discussed are BASIC CONCEPTS FOR BETTER HEAT PROTECTION recent developments in gas turbine disk materials, gas turbine SYSTEMS superalloy component service life-estimation methods, fatigue crack K. FRITSCHER (DNLR. lnstitut fuer Werkstoff-Forschung, propagation in Ni-based superalloys (with attention to the effects Cologne, Federal Republic of Germany) Zeitschrift fuer of microstructure, load ratio, and temperature), the effects of Werkstofftechnik (ISSN 0049-8688), vol. 18, Aug. 1987, p. environment on the crack growth behavior of superalloys under 265-277. refs various loading conditions, and high-temperature sheet materials Several mechanisms concerning material degradation at high for gas turbine applications. O.C. temperature are briefly reviewed. Oxidation kinetics, oxide structure, diffusion of species during oxidation, oxide scale formation, growth, A88-12628 and adhesion are considered. The hot corrosion mechanism is MECHANICAL PROPERTY REQUIREMENTS FOR AERO GAS examined from the chemical and physicochemical standpoints. The TURBINE MATERIALS improvement of corrosion resistance by superior oxide adhesion M. J. WEAVER (Royal Aircraft Establishment, Farnborough. is emphasized. Protective measures against each type of England) (Royal Society, Conference on Mechanical Behaviour degradation are discussed. Thermal barrier coatings (TBCs) for of Superalloys, London, England, June 10, 11, 1986) Materials the protection of metal structures subjected to excessive heat Science and Technology (ISSN 0267-0836), vol. 3, Sept. 1987, p. and corrosion are addressed, and a viable TBC concept of fully 695-700. dense ceramic coatings on suitable materials is presented. C.D. The outstanding performance of current military and civil aero gas turbine engines is linked closely to the way in which modern N8&10159# Starck (Hermann C.) Berlin, Baden (West design and manufacturing techniques have become totally Germany). integrated with materials designed specifically for operation within DEVELOPMENT AND PRODUCTION OF NEW AND MODIFIED the hostile environment of a gas turbine. Advanced titanium alloys POWDERS FOR SPRAYED COATINGS AND COMPONENTS FOR are used extensively throughout the compressor and nickel-base SAVING IMPORTANT RAW MATERIALS Flnal Report, Jun. superalloys dominate materials application in the turbine. In spite 1985 of current achievements, the engine designer is still under severe HElNZ ESCHNAUER, HELMUT MEINHARDT, and REINHOLD competitive pressure to improve engine performance still further LUTZ Bonn, West Germany Bundesministerium fuer Forschung and this will inevitably lead to even more demanding material und Technologie Dec. 1986 90 p In GERMAN; ENGLISH requirements. The present paper outlines the continuing trends in summary Sponsored by Bundesministerium fuer Forschung und engine development and describes the impact these are having Technologie, West Germany on materials technology in general and the mechanical property (BMFT-FB-T-86-129 ISSN-0340-7808; ETN-87-90561) Avail: requirements of nickel-base superalloys in particular. Author NTlS HC AO5/MF A01 ; Fachinformationszentrum, Karlsruhe, West Germany DM 18.50 Alloy systems for wear and corrosion protectionwere developed. A88-12032 Tough-hard, high chromium content composites of the type DEVELOPMENTS IN DISC MATERIALS Mi-Cr-B-Si plus hard materials were investigated. These alloys, F. SCZERZENIE and G. E. MAURER (Special Metals Corp., New which are supplied to the users mainly as spray powders, set Hartford, NY) (Royal Society, Conference on Mechanical more stringent requirements on powder production that uses a Behaviour of Superalloys, London, England, June 10, 11, 1986) vacuum-melt/inertgas atomization process. The same applies to Materials Science and Technology (ISSN 0267-0836), vol. 3, Sept. a developed high temperature solder, and alloys of the MCrAlY 1987, p. 733-742. refs type. The atomizing plant was modified and improved with a view Discs have always been the life- and reliability-limiting to the MCrAlY alloy, so that spray powders can be produced components of the gas turbine engine. Progress in disc materials which fulfil aircraft industry specifications. ESA development has been enhanced through the interaction of superalloy materials and metallurgical process development. Disc N88-10192# Air Force Wright Aeronautical Labs., Hampton, Va. service environment, property requirements, and physical COST SAVINGS POSSIBLE WITH AIR FORCE CONVERSION metallurgy are reviewed. Historically, the introduction of stronger, TO JP-8 AS ITS PRIMARY FUEL Summary Report, Jan. - Apr. more heat- and fatigue-resistant alloys has depended upon process 1987 developments such as vacuum induction melting, inert gas CHARLES R. MARTEL May 1987 29 p atomization, and thermomechanical processing. Current develop- (AD-A183784; AFWAL-TR-87-2037) Avail: NTlS HC AO3/MF ments and future directions are reviewed, including new melting prac- A01 CSCL05A tices for the manufacture of clean metals, the forging of fatigue resis- JP-4 has been the primary fuel for the USAF since 1951. tant microstructures and dual property discs. Author However. in 1979 the USAF converted to JP-8 as its primary jet

42 12 ENGINEERING fuel for its operations in Great Britain. Recently, the North Atlantic high-velocity environments. Towards this end a Mach 0.3 burner-rig Treaty Organization (NATO) began the switch from JP-4 (F40) to appartus was built to measure deposition rates from salt-seeded JP-8 (F34) as its primary jet fuel. However, JP-4 continues to be (mostly Na salts) combustion gases on the internally cooled the primary USAF jet fuel within the continental United States. cylindrical collector. Deposition experiments are underway. The cost and manpower savings possible by converting from JP-4 Author to JP-8, as the primary jet fuel for the Air Force, are identified and estimated. The much lower volatility of JP-8, as compared to JP-4, accounts for the anticipated savings. For example, aircraft 12 fuel systems must be purged prior to maintenance, and purging aircraft fuel systems that have contained JP4 can take hours to days. With JP-8 purging may not even be necessary under most ENGINEERING ambient temperatures. Another major savings is the reduced evaporation of JP-8, as compared to the more volatile JP-4. Finally, Includes engineering (general); communications; electronics and reduced fatalities and casualty losses resulting from ground and electrical engineering; fluid mechanics and heat transfer; flight accidents are estimated. GRA instrumentation and photography; lasers and masers; mechanical engineering; quality assurance and reliability; and structural N8&10938*# National Aeronautics and Space Administration. mechanics. Lewis Research Center, Cleveland, Ohio. HIGH TEMPERATURE METAL MATRIX COMPOSITES FOR FUTURE AEROSPACE SYSTEMS JOSEPH R. STEPHENS Oct. 1987 18 p Presented at the A88-10017 ASM International Composite Session, Cincinnati, Ohio, 13-15 Oct. PROBLEMS IN CONTINUUM MECHANICS WITH MIXED BOUND- 1987 ARY CONDITIONS [ZADACHI MEKHANlKl SPLOSHNYKH SRED (NASA-TM-100212; E-3821; NAS 1.15:100212) Avail: NTlS HC SO SMESHANNYMI GRANICHNYMI USLOVIIAMI] A03/MF A01 CSCL 11F VIKTOR MlKHAlLOVlCH ALEKSANDROV and EVGENll Research was conducted on metal matrix composites and VENlAMlNOVlC KOVALENKO Moscow, Izdatel'stvo Nauka, 1986, intermetallic matrix composites to understand their behavior under 335 p. In Russian. refs anticipated future operating conditions envisioned for aerospace Both classical results and new theoretical developments in the power and propulsion systems of the 21st century. Extremes in field of plane mixed problems are presented in a systematic environmental conditions, high temperature, long operating lives, manner. Particular attention is given to efficient analytical methods and cyclic conditions dictate that the test evaluations not only for solving mixed problems in continuum mechanics and their include laboratory testing, but simulated flight conditions. The mathematical justification. The problems examined include mixed various processing techniques employed to fabricate composites elasticity problems, such as contact interaction and stress are discussed along with the basic research underway to concentration near cracks and thin inclusions, as well as problems understand the behavior of high temperature composites, and the in hydrodynamics, such as wing problems, glide and shock, and relationship of this research to future aerospace systems. jet and cavitation flow problems. v. L. Author A88-10170 N8&11169*# Connecticut Univ., Storrs. COLOR DISPLAY TECHNOLOGY - AN OVERVIEW CONSTITUTIVE MODELING OF SUPERALLOY SINGLE J. ROBERT TRlMMlER (Sperry Corp., Phoenix, AZ) IN: Aerospace CRYSTALS WITH VERIFICATION TESTING Behavioral Engineering Technology Conference, 5th, Long Beach, ERIC JORDAN and KEVIN P. WALKER (Engineering Science CA, Oct. 13-16, 1986, Proceedings . Warrendale, PA, Society of Software, Inc., Smithfield, R.I.) In NASA. Lewis Research Center, Automotive Engineers, Inc., 1986, p. 201-208. refs Turbine Engine Hot Section Technology, 1985 p 277-286 Oct. (SAE PAPER 861692) 1985 Recent advances in CRT technology are discussed including (Contract NAG3-512) the shadow mask CRT for avionics displays, the beam index CRT, Avail: NTlS HC A19/MF A01 CSCL 11F penetration tubes, and the liquid crystaVCRT field sequential color The goal is the development of constitutive equations to display. Consideration is also given to the projection display system, describe the elevated temperature stress-strain behavior of single the color active matrix LCD, the vacuum fluorescent display, and crystal turbine blade alloys. The program includes both the the ac thin film electroluminescent display. It is believed that the development of a suitable model and verification of the model shadow mask CRT will continue to dominate the home TV through elevated temperature-torsion testing. A constitutive model market. is derived from postulated constitutive behavior on individual crystallographic slip systems. The behavior of the entire single A8&10497# crystal is then arrived at by summing up the slip on all the operative COUNTERROTATING DIFFERENTIAL CYLINDRICAL ROLLER crystallographicslip systems. This type of formulation has a number BEARING DEVELOPMENT of important advantages, including the prediction orientation BILL CRECELIUS (General Electric Co., Cincinnati, OH) AIAA, dependence and the ability to directly represent the constitutive SAE. ASME, and ASEE, Joint Propulsion Conference, 23rd, San behavior in terms which metallurgists use in describing the Diego, CA, June 29July 2, 1987. 9 p. refs micromechanisms. Here, the model is briefly described, followed (AIAA PAPER 87-1843) by the experimental set-up and some experimental findings to Advances in turbofan engine design have brought on the need date. Author for counterrotating main shaft roller bearings to operate to speeds greater than 3.7 million DN. To begin assimilating a data base, N88-11179'# National Aeronautics and Space Administration. four bearings were tested for 25 hours each - one with round Lewis Research Center, Cleveland, Ohio. rings. a soft trilobe. a hard trilobe, and a hard bilobe. Internally, EXPERIMENTAL VERIFICATION OF VAPOR DEPOSITION RATE all bearjngs functioned equally well. However, severe fretting and THEORY IN HIGH VELOCITY BURNER RIGS ring turning developed at the inner ring shaft interface with all SULEYMAN A. GOEKOGLU (Case Western Reserve Univ., out-of-round bearings. Differential sumps pose some unique Cleveland, Ohio.) and GILBERT J. SANTORO ln its Turbine problems, but no problem could be linked to counterrotation. Engine Hot Section Technology, 1985 p 383-390 Oct. 1985 Computer program CYLFLEX was enhanced with lubrication and Avail: NTlS HC A19/MF A01 CSCL 11F friction calculations to treat counterrotating roller bearings. Load The main objective has been the experimental verification of distribution, change in clearance, component kinematics, cage slip, the corrosive vapor deposition theory in high-temperature, and frictional heat rate were all addressed. Author

43 12 ENGINEERING

A88- 10570# and a heater made of a polyester sheet coated with MULTIGRID SOLUTION OF THE EULER EQUATIONS ON vapor-deposited gold, which produces uniform heat flux. After the UNSTRUCTURED AND ADAPTIVE MESHES initial selection and calibration of the composite sheet, accurate, D. MAVRlPLlS and A. JAMESON (Princeton University, NJ) quantitative, and continuous heat transfer coefficients were mapped University of Colorado and USAF, Copper Mountain Conference over the airfoil surface. Tests were conducted at two free-stream on Multigrid Methods, 3rd, Copper Mountain, CO, Apr. 6-10, 1987, turbulence intensities: 0.6 percent, which is typical of wind tunnels; Paper. 23 p. refs and 10 percent, which is typical of real engine conditions. In addition A multigrid algorithm for application to a sequence of completely to a smooth airfoil, the effects of local leading-edge sand roughness unstructured and unrelated meshes is discussed, and solutions were also examined for a value greater than the critical roughness. for the supercritical flow over a two-element airfoil system are The local heat transfer coefficients are presented for both presented. A Delaunay algorithm (Weatherill, 1985), in which the free-stream turbulence intensities for inlet Reynolds numbers from distribution of mesh points is either determined by conformal 1.20 to 5.55 x 10 to the 5th power. Comparisons are also made mapping techniques or by adaptive refinement of the previous with analytical values of heat transfer coefficients obtained from coarser mesh, is used to generate the meshes. Although the finest the STAN5 boundary layer code. Author mesh used in the adaptive refinement sequence contains about 1/4 as many mesh points as that used in the global refinement A88-10979# sequence, the calculated force coefficients for both solutions are INFLUENCE OF THE REYNOLDS NUMBER ON THE found to compare closely. R.R. PERFORMANCE OF CENTRIFUGAL COMPRESSORS R. A. STRUB (Gebrueder Sulzer AG, Winterthur, Switzerland), L. A88-10628 BONClANl (Nuovo Pignone S.p.A., Florence, Italy), C. J. BORER THREE-DIMENSIONAL FLOW IN A ROTOR - A STRICTLY (Dresser Industries, Inc., Waukesha, WI), M. V. CASEY (Sulzer THREE-DIMENSIONAL CALCULATION OF FLOWS IN TUR- Escher Wyss, Ltd., Zurich, Switzerland), S. L. COLE (Ingersoll-Rand BOMACHINES USING THE S142 METHOD [ECOULEMENT Co., Bristol, VA ) et al. ASME, International Gas Turbine TRlDlMENSlONNEL DANS UNE ROUE - CALCUL EFFECTIVE- Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, MENTTRIDIMENSIONNEL DES ECOULEMENTS DANS LES TUR- 1987. 6 p. refs BOMACHINES PAR LA METHODE S1-S2] (ASME PAPER 87-GT-10) D. BUlSlNE and P. MICHEAU (Lille I, Universite, Villeneuve-d'Ascq, Improved formulas are presented for the correction of the France) Journal de Mecanique Theorique et Appliquee (ISSN efficiency, the head, and the flow as influenced by the Reynolds 0750-7240), vol. 6, no. 4, 1987, p. 525-546. In French. refs number variation between workshop tests and specified conditions, The restrictions which are traditionally imposed to overcome carried out with the same machine. Tests have shown that a the instability of the S1-S2 method are investigated, and a strictly sufficiently good correlation between measured and predicted three-dimensional technique for the coupling of the S1 -S2 method values can be obtained with the proposed formulas. In addition, a is proposed which uses only the local equations and the boundary proposal is made for the allowable range, taking into account the conditions. The technique takes into account important processes inherent limitations for accurate testing at low Reynolds numbers. in the design of blade shapes, and it is demonstrated with the It is recommended that the proposed formulas and allowable range examples of an axial compressor and a rotor with a helical blade be reviewed by the ASME, the ISO, or any other associations for shape. The present method is found to accurately model the adoption in revised test codes for centrifugal compressors. interactions between processes including the secondary effects, Author the local radial equilibrium, and the downstream equilibrium between the jets, in addition to being able to predict the appearance A88-10992# of processes which degrade rotor performance. R.R. MOMENTUM EXCHANGES AND ENERGY TRANSFERS IN CROSS FLOW FANS A88-10726 JOSEPH MAZUR (Eaton Corp., Southfield, MI) and TRILOCHAN EXTENDED SYSTEMS OFVARIABLE STRUCTUREWITH MOBILE SINGH (Wayne State University, Detroit, MI) ASME. International RADIO-COMMUNICATION OBJECTS [PROTIAZHENNYE SIS- Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May TEMY IZMENIAIUSHCHEISIA STRUKTURY S PODVIZHNYMI 31-June 4, 1987. 7 p. refs OB'EKTAMI RADIOSVIAZI] (ASME PAPER 87-GT-32) N. 0. VARGANOV, V. V. VOSKOBOINIKOV, and A. F. MEVlS An experimental investigation of the flow in a cross flow fan at Radiotekhnika (ISSN 003343486), June 1987, p. 3-6. In Russian. three operating conditions is reported. Velocity and pressure maps Relationships are obtained for the fail-safe operation of for the flow field are presented along with a determination of the extended systems of variable structure with mobile momentum exchanges and energy transfers between the blading radio-communication objects. These relationships can be applied and the flow field regions. Author to the study of extended communication lines in civil-aviation systems. B.J. A88-1 lOOO'# Aerometrics, Inc., Mountain View, Calif. EXPERIMENTS ON SPRAY INTERACTIONS IN THE WAKE OF A BLUFF BODY A88-10969'# National Aeronautics and Space Administration. R. C. RUDOFF, M. J. HOUSER, and W. D. BACHALO (Aerometrics, Lewis Research Center, Cleveland, Ohio. Inc., Mountain View, CA) ASME, International Gas Turbine USE OF A LIQUID-CRYSTAL AND HEATER-ELEMENT COMPO- Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, SITE FOR QUANTITATIVE, HIGH-RESOLUTION HEAT-TRANSFER 1987. 9 p. refs COEFFICIENTS ON A TURBINE AIRFOIL INCLUDING TURBU- (Contract NAS3-24844) LENCE AND SURFACE-ROUGHNESS EFFECTS (ASME PAPER 87-GT-48) S. A. HIPPENSTEELE, L. M. RUSSELL, and F. J. TORRES (NASA, The dynamics of spray drop interaction within the turbulent Lewis Research Center, Cleveland, OH) IN: Pressure temperature wake of a bluff body were investigated using the Aerometrics measurements. New York, American Society of Mechanical Phase Doppler Particle Analyzer that determines both drop size Engineers, 1987, p. 105-120. Previously announced in STAR as and velocity. Detailed measurements obtained included spray drop N87-22181. refs size, axial and radial velocity, angle of trajectory, and size-velocity Local heat transfer coefficients were measured along the correlations. The gas-phase flow field was also ascertained via midchord of a three-times-size turbine vane airfoil in a static the behavior of the smallest drops. Results showed dramatic cascade operated at room temperature over a range of Reynolds differences in drop behavior when interacting with turbulence for numbers. The test surface consisted of a composite of the various size classes. Small drops were recirculated in a pair commercially available materials: a Mylar sheet with a layer of of toroidal vortices located behind the bluff body, whereas the cholestric liquid crystals, which change color with temperature, larger drops followed the general direction of the spray cone angle.

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The spray field interaction illustrated by these data casts some A88-11019# doubt on attempts to describe sprays via simple integral quantities DEVELOPMENT OF CERAMIC HOT SECTION COMPONENTS such as the Sauter mean diameter. Author FOR AGT 100 GAS TURBINE D. A. TURNER and R. L. HOLTMAN (General Motors Corp., Allison Gas Turbine Div., Indianapolis, IN) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May A88-11016# 31-June 4, 1987. 6 p. SEALING OF A SHROUDED ROTOR-STATOR SYSTEM WITH (ASME PAPER 87-GT-79) PRE-SWIRL COOLANT The development of the AGT 100 gasifier turbine components Z. B. EL-OUN, P. H. NELLER, and A. B. TURNER (Sussex, in structural ceramic materials is described. Development is defined University, Brighton, England) ASME, International Gas Turbine as the complete and iterative cycle from design, analysis, test, Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, and design refinement culminating in successful demonstration of 1987. 11 p. Research supported by SERC, Rolls-Royce PLC, and the design requirements. The components are analyzed by a linear GEC-Ruston Gas Turbine PLC. refs elastic probabilistic approach, which involves finite element (ASME PAPER 87-GT-72) simulation of the component combined with a Weibull Experimental results for a modeled gas turbine rotor-stator characterization of the brittle ceramic material strength distribution, system using both preswirled blade coolant and radially outward to calculate a probability of survival for the component in the flowing disc coolant are presented. Although the preswirled coolant operating environment. Component test failure investigation has flow is found to have little effect on the pressure distribution below resulted in design modifications, and an improvement in component the preswirl nozzles, it is shown that considerable contamination reliability has been demonstrated. Author of the preswirled coolant by the frictionally heated disc coolant can occur. A clear pressure inversion effect was found when A88-11033'# Texas A&M Univ., College Station. coolant was provided by the preswirl nozzles alone, while the EFFECT OF RIB ANGLE ON LOCAL HEAT/MASS TRANSFER. pressure under the rim seal increased with increasing rotational DISTRIBUTION IN A TWO-PASS RIB-ROUGHENED CHANNEL speed. Blade coolant flow increases the sealing flow requirement, P. R. CHANDRA, J. C. HAN, and S. C. MU(Texas A & M University, except at the lowest flow rates. R.R. College Station) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 9 p. refs (Contract NAS3-24227) A88-11017# (ASME PAPER 87-GT-94) PREDICTION OF TURBULENT SOURCE FLOW BETWEEN The naphthalene sublimation technique is used to investigate COROTATING DISKS WITH AN ANISOTROPIC TWO-EQUATION the heat transfer characteristics of turbulent air flow in a two-pass TURBULENCE MODEL channel. A test section that resembles the internal cooling SIAMACK A. SHlRAZl and C. RANDALL TRUMAN (New Mexico, passages of gas turbine airfoils is employed. The local Sherwood University, Albuquerque) ASME, International Gas Turbine numbers on the ribbed walls were found to be 1.5-6.5 times those Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, for a fully developed flow in a smooth square duct. Depending on 1987. 8 p. Research supported by Sandia National Laboratories the rib angle-of-attack and the Reynolds number, the average and University of New Mexico. refs ribbed-wall Sherwood numbers were 2.5-3.5 times higher than the (ASME PAPER 87-GT-73) fully developed values. R.R. An anisotropic form of a low-Reynolds-number two-equation turbulence model has been implemented in a numerical solution A88-11034# for incompressible turbulent flow between corotating parallel disks. PROCEDURES FOR DETERMINING SURFACE HEAT FLUX Transport equations for turbulent kinetic energy and dissipation USING THIN FILM GAUGES ON A COATED METAL MODEL IN rate were solved simultaneously with the governing equations for A TRANSIENT TEST FACILITY the mean-flow variables. Comparisons with earlier mixing-length J. E. DOORLY (Oxford University, England) ASME, International predictions and with measurements are presented. Good Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May agreement between the present predictions and the measurements 31-June 4, 1987. 10 p. Research supported by Rolls-Royce, PLC of velocity components and turbulent kinetic energy was obtained. and Royal Aircraft Establishment. refs The low-Reynolds-number two-equation model was found to (ASME PAPER 87-GT-95) adequately model the near-wall region as well as the effects of The paper describes how thin film surface heat flux gauges rotation and streamline divergence which required ad hoc may be used to measure surface heat transfer rate to assumptions in the mixing-length model. Author enamel-coated metal turbine blades. Flexible methods, which are also computationally efficient, for obtaining the heat transfer rate are described. Experimental results using the new coated metal turbine blades and processing techniques in a stationary transient A88-1 lOl8# cascade facility are given and are shown to agree well with results NUMERICAL PREDICTION OF TURBULENT FLOW IN using the existing method for gauges on single-layer substrate ROTATING CAVITIES blades. The application of the gauges for measuring highly unsteady A. P. MORSE (Sussex, University, Brighton, England) ASME, heat transfer is also discussed. Author International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 13 p. refs A88-11037# (ASME PAPER 87-GT-74) A QUALITATIVE METHOD FOR DETERMINING THE Predictions of the isothermal, incompressible flow in the cavity TEMPERATURE PATTERN OF RUN GAS TURBINE BLADES formed between two corotating plane discs and a peripheral shroud G. MCQUIGGAN and W. LINKERT (Westinghouse Canada, Inc., have been obtained using an elliptic calculation procedure and a Turbine and Generator Div., Hamilton) ASME, International Gas low-turbulenceReynolds number k-epsilon model for the estimation Turbine Conference and Exhibition, 32nd, Anaheim, CA, May of turbulent transport. Both radial inflow and outflow are investigated 31-June 4, 1987. 5 p. refs for a wide range of flow conditions involving rotational Reynolds (ASME PAPER 87-GT-102) number up to one million. Although predictive accuracy is generally The paper proposes a quick and inexpensive qualitative method good, the computed flow in the Ekman layers for radial outflow for determining the temperature pattern of run gas turbine blades often displays a retarded spreading rate and a tendency to (made from IN738 superalloy) that operate in the region of 815 C laminarize under conditions which are known from experiment to to 900 C. The method is based on measuring magnetism that produce turbulent flow. Author develops in normally nonmagnetic materials upon exposure to high 12 ENGINEERING temperatures. The magnetism induced in these alloys is thought A88-11055# to be the result of changes in the crystal lattice caused by operation A MODEL TO DETERMINE THE BEHAVIOUR OF A PRESSURE of the alloy in a corrosive environment at elevated temperature. MEASUREMENT EQUIPMENT DURING NONSTATIC OPERA- The development of a quantitative relationship might not be TIONS OF GASTURBINE ENGINES possible because of the interactive effects of temperature, K.-U. LEMMER and J. HASS (Hamburg, Universitaet der environment, and time. IS. Bundeswehr, Federal Republic of Germany) ASME, International Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 10 p. refs (ASME PAPER 87-GT-128) A88-11040# A mathematical model was developed to describe the behavior THERMODYNAMICS AND PERFORMANCE PROJECTIONS FOR of a pressure measurement equipment of gas-turbine engines INTERCOOLED/REHEAT/RECUPERATED GAS TURBINE during nonstatic operations. The model determines the influence SYSTEMS of the components of the measuring chain: a pressure measuring MAHER A. EL-MASRI (MIT, Cambridge, MA) ASME, International transducer, a hose pipe, and a pressure probe. It performs back Gas Turbine Conference and Exhibition, 32nd, Anaheim, CA, May calculations from the measured pressure signals to the real 31-June 4, 1987. 8 p. refs measuring value. The model was verified by pressure (ASME PAPER 87-GT-108) measurements with a calibrating device. The pressure Two methods for improving the performance of measurements during the transition between different operating intercooledhecuperated (ICR) systems are assessed. Reheat ICR points of a gas-turbine engine and the adjustment of these pressure (RICR) cycles are compared with nonreheat ICR cycles for values with the help of the measuring-chain model are described. Conservative and advanced components. The ICR cycles are for IS. two-shaft engines and the RlCR for two- and three-shaft engines. It is observed that for both conservative and advanced turbine A88-11068# component constraints without thermal barrier coating, the RlCR SPRAY PERFORMANCE OF A HYBRID INJECTOR UNDER cycle exceeds the ICR cycle by only 0.3 points and 6 percent in VARYING AIR DENSITY CONDITIONS specific output. Whether reheat is preferable to a simple cycle A. K. JASUJA (Cranfield Institute of Technology, England) ASME, turbine inlet temperature (TIT) depends on the form of the International Gas Turbine Conference and Exhibition, 32nd, temperature difference and the additional loss induced by the Anaheim, CA, May 31June 4, 1987. 7 p. Research sponsored by reheat itself, and the feasibility of applying reheat depends on the the Royal Aircraft Establishment. refs constraints and design tradeoffs. Cooling flow rates as a function (ASME PAPER 87-GT-155) of TIT for ICR and RlCR cycles and the use of water injection to The atomization characteristics of a fuel-air mixture preparation improve ICR cycle performance are examined. I.F. cum placement device featuring a conventional dual-orifice pressure atomizer spraying into a narrow diameter, airstream carrying tube are outlined in this paper. The experimental tests were carried out on gas oil over a range of ambient air pressures. A88-11041# A well established laser light-scattering technique was employed EFFECTS OF CHANNEL ASPECT RATIO ON HEAT TRANSFER for dropsize measurements. The spray quality data collected in IN RECTANGULAR PASSAGESHARP180-DEGTURNS the present investigation allows some interesting comparisons C. S. FAN and D. E. METZGER (Arizona State University, against conventional airblast and pressure atomized spray data. Tempe) ASME, International Gas Turbine Conference and Author Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 7 p. refs (ASME PAPER 87-GT-113) A88-11082# Measured Nusselt numbers are presented for forced convection APPLIED RELIABILITY/MAINTAINABlLlTV METHODOLOGY AS within and around sharp 180-deg turns in smooth channels of A FUNCTION WITHIN LIFE CYCLE COST rectangular cross section. The turn geometry is characterized by C. L. CALLIS and C. E. CURRY (General Motors Corp., Allison channel height, inlet and outlet channel widths, and clearance at Gas Turbine Div., Indianapolis, IN) ASME, International Gas the tip of the turn. Twenty-seven different geometry parameter Turbine Conference and Exhibition, 32nd, Anaheim, CA, May combinations were tested in the present study, extending previous 31-June 4, 1987. 7 p. refs work to two additional values of channel height and providing an (ASME PAPER 87-GT-172) assessment of the independent effect of channel aspect ratio for This paper demonstrates application of reliability and a wide variety of combinations of the other geometry parameters. maintainability (R&M) factors to determine supportability of aircraft Separately determined top wall, bottom wall, and side wall Nusselt turbine engines. R&M factors are expressed as operating and numbers are presented individually along with azimuthal averages. support parameters consistent with those required for LCC analysis In general, increasing channel aspect ratio results in smaller as well as operating support level determinations. Author azimuthal heat transfer variations and increased overall channel heat transfer. Author A8&11083'# Ford Motor Co., Dearborn, Mich. DEVELOPMENTOFTHE AGT101 REGENERATOR SEALS C. A. FUCINARI, J. K. VALIANCE, and C. J. RAHNKE (Ford Motor Co., Dearborn, MI) ASME, International Gas Turbine A8&11054# Conference and Exhibition, 32nd, Anaheim, CA, May 31June 4, COMPUTER PREDICTIONS OF EROSION DAMAGE IN GAS 1987. 10 p. DOE-supported research. TURBINES (Contract DENS-167) ABDEL AZlM A. F. EL-SAYED (Zagazig University, Egypt) and A. (ASME PAPER 87-GT-173) BROWN (Royal Military College of Science, Shrivenham, England) The design and development of the regenerator seals used in ASME, International Gas Turbine Conference and Exhibition, 32nd, the AGT101 gas turbine engine are described in this paper. The Anaheim, CA, May 31 June 4, 1987. 8 p. refs all ceramic AGT101 gas turbine engine was designed for 100 hp (ASME PAPER 87-GT-127) at 51 pressure ratio with 2500F(1371C) turbine inlet temperature. In this article an iterative procedure is presented for estimating Six distinct phases of seal design were investigated experimentally erosion in axial gas turbine blades. The procedure is applied to a and analytically to develop the final design. Static and dynamic two stage turbine and the erosion is estimated for a 12,000 hour test rig results obtained during the seal development program are engine running time. The effect of the erosion on engine presented. In addition, analytical techniques are described. The performance is estimated through changes in pressure coefficient program objectives of reduced seal leakage, without additional distribution around a blade section. Author diaphragm cooling, to 3.6 percent of total engine airflow and higher

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seal operating temperature resulting from the 2000F (1093C) inlet A8811 lOS# exhaust gas temperature were met. Author COMPARISON OF PREDICTED AND MEASURED VELOCITIES IN A COMPRESSOR DISK DRUM MODEL D. G. ALBERGA, G. E. STEPHENS (Pratt and Whitney, East Hartford. CT), and B. V. JOHNSON (United Technologies Research Center, East Hartford, CT) ASME. International Gas Turbine A8811092# Conference and Exhibition, 32nd, Anaheim, CA, May 31-June 4, LABYRINTH SEAL FLOW MEASUREMENT BY TRACER GAS 1987. 6 p. Research supported by Pratt and Whitney. refs INJECTION (ASME PAPER 87-GT-208) WILLIAM F. MCGREEHAN, FRED G. HAASER, and LAURENCE LDV measurements of tangential velocity distributions in the T. SHERWOOD (General Electric Co., Cincinnati, OH) ASME, bleed and the trapped cavities of an 11-cavity compressor drum International Gas Turbine Conference and Exhibition, 32nd, model were obtained at disk tangential Reynolds numbers of about Anaheim, CA. May 3lJune 4, 1987. 6 p. Research supported by 2 x 10 to the 6th and compared with predicted values. Experimental the General Electric Co. refs results show the tangential velocity profiles in the bleed cavity to (ASME PAPER 87-GT-187) vary from near-solid-body at low flow rates to near-free-vortex at A practical system for flow measurement in rotating seals using the highest flow rates. A decrease in tangential velocity strength the injection and sampling of a tracer gas is presented. Carbon in the trapped flow cavities with distance from the bleed cavity dioxide or helium is injected as a tracer into a labyrinth seal at a was also noted. The flow in the bleed and trapped cavities were controlled rate and gas samples are extracted downstream for modeled using an analysis coupling the flow in a core region with concentration measurement. Test results from a rotating labyrinth the flow in the disk boundary layers. The analytical model is shown seal rig were obtained over a range of seal pressure ratios and to accurately predict the tangential velocity distribution, and hence rotor speeds in order to determine the conditions which assure the pressure drop, for a range of flow conditions and cavity optimum tracer gas mixing. Seal leakage rates calculated by tracer locations. R.R. gas concentration are compared to venturi flow measurements. Author

A8&11100# FILM COOLING OF A TURBINE BLADE WITH INJECTION A8&11112# THROUGH TWO ROWS OF HOLES IN THE NEAR-ENDWALL APPLICATION OF THE TRANSIENT TEST TECHNIQUE TO REGION MEASURE LOCAL HEAT TRANSFER COEFFICIENTS R. J. GOLDSTEIN and P. H. CHEN (Minnesota, University, ASSOCIATED WITH AUGMENTED AIRFOIL COOLING Minneapolis) ASME, International Gas Turbine Conference and PASSAGES Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 7 p. H. J. SAABAS, S. C. ARORA, and W. ABDEL MESSEH (Pratt USAF-supported research. refs and Whitney Canada, Longueuil) ASME, International Gas Turbine (ASME PAPER 87-GT-196; ASME PAPER 87-GT-196) Conference and Exhibition, 32nd, Anaheim, CA, May 3lJune 4, Measurements of film cooling on a simulated turbine blade are 1987. 10 p. refs conducted using a mass transfer technique. Under the influence (ASME PAPER 87-GT-212) of the endwall, dramatic changes of film cooling performance occur Assumptions made in the application of a transient technique on the convex surface of the blade as compared to the region using active surface coatings for the determination of Nusselt where the flow is two-dimensional. The result is a triangular region, number distributions within augmented passages typical of gas where coolant is swept away from the surface by the three turbine airfoils are examined. An improved data reduction procedure dimensional vortex driven flow present between adjacent blades. and an alternative method for error analysis are proposed. It is In order to predict the area of this unprotected region, the influences found that for augmented surfaces, the one-dimensional conduction of several parameters including density ratio, blowing rate and assumption made in the heat transfer solution is not valid for all number of rows of injection holes are studied. The presence of times. It is also noted that the experimentally obtained quantities the endwall affects the film cooling performance on the concave cannot be treated as values that are randomly distributed about surface only slightly. Author some true value for all experimentally measured quantities. R.R.

A8&11102# HEAT TRANSFER TO ARRAYS OF IMPINGING JETS IN A CROSSFLOW 8. R. HOLLWORTH (Clarkson University, Potsdam, NY) and G. H. A8&1 1114# COLE (Idaho National Engineering Laboratories, Idaho Falls) DEVELOPMENT AND APPLICATION OF A HIGH FREQUENCY ASME, International Gas Turbine Conference and Exhibition, 32nd. WEDGE PROBE Anaheim, CA, May 31June 4, 1987. 9 p. refs H. BUBECK (Stuttgart, Universitaet, Federal Republic of Germany) (ASME PAPER 87-GT-198) and J. WACHTER ASME, International Gas Turbine Conference Convective heat transfer measurements for staggered arrays and Exhibition, 32nd, Anaheim, CA, May 31 June 4, 1987. 8 p. of round turbulent air jets impinging upon a heated flat surface DFG-supported research. refs were obtained in the mean jet Reynolds number range of (ASME PAPER 87-GT-216) 2500-25,000. Streamwise variations in spanwise-averaged heat To investigate the three dimensional unsteady flow behind transfer were found using microfoil heat flux sensors, and heat rotating blade rows of turbomachines, a high response pressure transfer profiles were found to be periodic, with a peak probe has been developed. Surface mounted miniature pressure corresponding to each spanwise row of holes. Peaks were transducers are used to measure the flow fluctuations, while the displaced in the streamwise direction by the crossflow, with the mean pressures are measured simultaneously with adjacent largest deflections being exhibited by those nearest the exhaust conventional pressure lead tubes. The steady state and the end of the channel. Array-averaged heat transfer coefficients dynamic behavior of the probe were investigated. The application obtained by numerically averaging the local measurements were of the probe to the rotor exit flow of an axial compressor is found to agree well with previous results. R.R. described and results are presented. Author

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A88-11116# A88-11142# NEUTRON AND POSITRON TECHNIQUES FOR FLUID PARTICLE TRANSPORT ACROSS THE TRANSPIRED TRANSFER SYSTEM ANALYSIS AND REMOTE TEMPERATURE TURBULENTBOUNDARYLAYER AND STRESS MEASUREMENT HAM01 KOZLU and JEAN F. LOUIS (MIT, Cambridge, MA) ASME, P. A. E. STEWART (Rolls-Royce, PLC, Advanced Projects Dept., International Gas Turbine Conference and Exhibition, 32nd, Bristol, England) ASME, International Gas Turbine Conference Anaheim, CA, May 31-June 4, 1987. 11 p. refs and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 15 p. (Contract DE-AC21-83MC-20334) Research supported by the Ministry of Defence (Procurement (ASME PAPER 87-GT-265) Executive). Wind tunnel data and theoretical results are used to study the (ASME PAPER 87-GT-219) effects of surface inclination and density of particulates on Present and projected applications of penetrating radiation deposition control by transpiration, with application to the control techniques to gas turbine research and development are of deposition of small particles contributing most of the mass of considered. Approaches discussed include the visualization and the solid carryover entering turbines burning coal-derived fuel. The measurement of metal component movement using high energy effects of size and injection rates on deposition are considered, X-rays, the measurement of metal temperatures using epithermal and the interaction between transpiration and the inertial impaction neutrons, the measurement of metal stresses using thermal neutron of particles is investigated using glass particles. Turbulent Schmidt diffraction, and the visualization and measurement of oil and fuel numbers obtained from tests conducted on an inclined plate with systems using either cold neutron radiography or emitting isotope coal particles in order to determine the density effects on the tomography. By selecting the radiation appropriate to the problem, particle concentration profiles were in agreement with the the desired data can be probed for and obtained through imaging predictions of Tchen (1974) for the flat plate. R.R. or signal acquisition, and the necessary information can then be extracted with digital image processing or knowledge based image A88-11439# manipulation and pattern recognition. R.R. AN OPTIMAL CONTROL METHOD FOR PASSAGE OF A FLEXIBLE ROTOR THROUGH RESONANCES Z. VIDERMAN and I. PORAT (Technion - Israel Institute of A88-11117# Technology, Haifa) ASME, Transactions, Journal of Dynamic EFFECT OF FLUID INERTIA ON THE PERFORMANCE OF Systems, Measurement, and Control (ISSN 0022-0434), vol. 109, SQUEEZE FILM DAMPER SUPPORTED ROTORS Sept. 1987, p. 216-223. refs L. A. SAN ANDRES and JOHN M. VANCE (Texas A & M University, This paper deals, by means of modal analysis, with the effects College Station) ASME. International Gas Turbine Conference of control forces on passage through resonances of a flexible and Exhibition, 32nd, Anaheim, CA, May 31-June 4, 1987. 12 p. rotor. Several control methods are evaluated, and the necessary refs number of dampers and their optimal location are determined. A (ASME PAPER 87-GT-220) fundamental interpretation is offered for the problem as a whole. The effect of fluid inertia on the synchronous steady-state Author operation of a centrally preloaded single mass flexible rotor supported in squeeze film bearing dampers is examined A88-11585# theoretically. For a model representative of some aircraft engine NDE AT TWELVE O'CLOCK HIGH applications, frequency response curves are presented exhibiting BERNHARD R. TIlTMANN (Rockwell International Science Center, the effect of fluid inertia on rotor excursion amplitudes and Thousand Oaks, CA) Mechanical Engineering (ISSN 0025-6501), imbalance transmissibilities for both pressurized and unpressurized vol. 109, Sept. 1987, p. 72-74. short open ended squeeze film damper supports. It is shown that The role of NDE in the evaluation of materials, in particular a significant reduction in amplitude response and transmitted force materials for aircraft components, is examined. Computer-based is possible for dampers operating at moderately large squeeze ultrasonic systems and real-time radiography are applicable for film Reynolds numbers. Furthermore, for unpressurized dampers analyzing material properties. The development of NDE methods, the possibilities of bi-stable operation and jump phenomena are such as fiber-optic borescopes, and X-ray, dye-penetrant, and shown to be reduced and virtually disappear at sufficiently large magnetic techniques for testing difficult to reach places (welds) is operating Reynolds numbers. Author being researched. The need for laser-based ultrasonic techniques for in-process and in-service control and monitoring of materials is discussed. Consideration is given to noncontacting acoustooptical A88-11120# process monitoring and the use of heat sources, such as laser beams, to generate thermal waves on the surface of materials. A STUDY OF THE EFFECTS OF THERMAL BARRIER COATING SURFACE ROUGHNESS ON THE BOUNDARY LAYER I.F. CHARACTERISTICS OF GAS-TURBINE AEROFOILS R. M. WAlT, J. L. ALLEN (Oxford University, England), N. C. A88-11825# BAINES (Imperial College of Science and Technology, London, FORCE COMMUTATED DIRECT FREQUENCY CHANGERS FOR England), J. P. SIMONS, and M. GEORGE (Rolls-Royce, PLC, AEROSPACE POWER APPLICATIONS Bristol, England) ASME, International Gas Turbine Conference Y. KIM and M. EHSANI (Texas A & M University, College Station) and Exhibition, 32nd. Anaheim, CA, May 31-June 4, 1987. 8 p. IN: IECEC '87; Proceedings of the Twenty-second lntersociety SERC-supported research. refs Energy Conversion Engineering Conference, Philadelphia, PA, Aug. (ASME PAPER 87-GT-223) 10-14, 1987. Volume 1 . New York, American Institute of The effect of thermal barrier coating surface roughness on the Aeronautics and Astronautics, 1987, p. 325-330. refs aerodynamic performance of gas-turbine aerofoils has been This paper describes a new VSCF system whose prime power investigated for the case of a profile typical of current first-stage source is a permanent magnet generator. The terminal voltage of nozzle guide vane design. Cascade tests indicate a potential for permanent magnet generator is not controllable since the excitation significant extra loss, depending on Reynolds number, due to is constant and the output frequency varies proportionally to the thermal barrier coating in its 'as-sprayed' state. In this situation engine speed. Forced turn-off frequency changers are employed polishing coated vanes is shown to be largely effective in restoring as the interface between permanent magnet generator and their performance. The measurements also suggest a critical low constant frequency supply. Control laws of the VSCF system, which Reynolds number below which the range of roughness tested has reduce power ratings of the system and increase efficiency in the no effect on cascade efficiency. Transition detection involved a VSCF, are established. Finally, microprocessor-based control novel use of thin-film anemometers painted and fired onto the techniques, which provide the input power factor control as well TBC surfaces. Author as voltage and frequency control, are described. Author

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A88-12294# system is described, including detailed equipment schematics and SIMILARITY OF EJECTOR WALL-PRESSURE DISTRIBUTIONS cost figures. Some details and guidance are given with regard to M. S. CHANDRASEKHARA, A. KROTHAPALLI (Florida State experience in reducing the interferometry fringe data via the Abel University, Tallahassee), and D. BAGANOFF (Stanford University, transformation to obtain density fields and, in turn, velocity fields. CA) AlAA Journal (ISSN 0001-1452). vol. 25, Sept. 1987, p. Finally, representative results are shown together with 1266-1268. complementary laser velocimetry measurements and Navier-Stokes (Contract F49620-79-C-0189) computations. C.D. The wall static pressure distribution of a multiple, underexpanded jet ejector of the kind employed in thrust A88-12732 augmentation is presently found to scale well with average throat VIDEO DATA LINK PROVIDES TELEVISION PICTURES IN NEAR static pressures. This effect is ascribed to the absence of the REAL TIME VIA TACTICAL RADIO AND SATELLITE well-defined acoustic interaction that is generally observed in the CHANNELS single underexpanded jet. The self-similarity obtained only holds, RICHARD V. HARTMAN (Singer Co., Dalmo Victor Div., Belmont, however, for short nozzle-to-throat distances; at greater distances, CA) IN: Airborne reconnaissance X Proceedings of the Meeting, a clear breakdown is noted. O.C. San Diego, CA, Aug. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical Instrumentation Engineers, 1987, p. 21 -25. A88-12657 Advances in sophisticated algorithms and parallel VLSl OPTICAL SYSTEMS FOR GAS TURBINE ENGINES processing have resulted in the capability for near real-time MARK WRIGLEY (Negretti Aviation, Croydon, England) IN: transmission of television pictures (optical and FLIR) via existing Contemporary optical instrument design, fabrication, and testing; telephone lines, tactical radios, and military satellite channels. Proceedings of the Meeting, Innsbruck, Austria, Apr. 17, 18, 1986 Concepts have been field-demonstrated with production-ready . Bellingham, WA, Society of Photo-Optical Instrumentation engineering development models using transform compression Engineers, 1986, p. 231 -237. techniques. Preliminary design has been completed for packaging The design and fabrication of a turbine-blade pyrometer an existing command post version into a 20-pound enclosure for transducer for in situ measurements of blade temperature in use on jeeps, backpacks, RPVs, helicopters, and reconnaissance operating gas-turbine engines are described and illustrated with aircraft. The system will also have a built-in error correction code diagrams, drawings, graphs, and photographs. Consideration is unit, allowing operation via communciations media exhibiting a bit given to the primary components (optical probe, fiber-optic cable, error rate of 0.01 or better. Author and electronics), the operating environment (extreme temperatures and pressures, vibration, EMI, and liquids), the design A88-12838" Aerospace Corp., Los Angeles, Calif. specifications, and specific fabrication techniques. It is pointed TEST OF IR ARRAYS ON THE KUIPER AIRBORNE out that electrooptic transducers of this type reduce the OBSERVATORY measurement error to + or - 10 C, and that the same sensors R. W. RUSSELL, G. S. ROSSANO, D. K. LYNCH, G. T. can be used to measure blade-tip clearance and shaft speed or COLON-BONET, J. A. HACKWELL (Aerospace Corp., Space to detect flame-out. T.K. Sciences Laboratory, Los Angeles, CA) et al. IN: Infrared technology XII; Proceedings of the Meeting, San Diego, CA, Aug. A88-12697 19, 20, 1986 . Bellingham. WA, Society of Photo-Optical SELF-ADJUSTING FLIGHT ELECTRONICS (SAFE) Instrumentation Engineers, 1986, p. 88-98. THOMAS P. CAUDELL (Hughes Artificial Intelligence Center, (Contract NAS2-12155) Calabasas, CA) and I. DAVID LEVY (Hughes Aircraft Co., NASA's Kuiper Airborne Observatory, which is a C-141 transport Electro-Optical and Data Systems Group, El Segundo, CA) IN: aircraft equipped with a 90-cm, all-reflective altazimuth telescope, Infrared detectors, sensors, and focal plane arrays; Proceedings has been engaged in the Kuiper Infrared Technology Experiment. of the Meeting, San Diego, CA, Aug. 21, 22, 1986 . Bellingham, Attention is presently given to the Experiment's flight series for WA, Society of Photo-Optical Instrumentation Engineers, 1986, p. state-of-the-arttwo-dimensional, 500-element arrays that use either 145-150. USAF-supported research. blocked impurity band or bulk silicon devices. The switched FET The design and performance of SAFExpert, an expert-system readout scheme used on the three arrays flown thus far yields program developed (as part of the SAFE program) to adjust the exceptionally low crosstalk. System sensitivities are found to be clock levels and biases of avionic CCD detector arrays, are sufficient for the detection of both pointlike and extended sources; described. The basic adjustment problem is defined; the several of each type have been used in staring and scanning expert-system approach (combining basic knowledge of the device experiments. O.C. physics and engineering experience) is explained; and the process flow and operation of SAFExpert are presented in diagrams and A88-12840 characterized in detail. In test optimizations involving three different AN UNCOOLED LINESCAN THERMAL IMAGER FOR GROUND CCD arrays preset to three different sets of (degraded-performance) AND AIRBORNE USE clock/bias levels, SAFExpert achieved 50-percent better bucket T. J. LIDDICOAT, M. V. MANS (Plessey Research Roke Manor, capacity in about 8 min than a human expert obtained (by manual Ltd., England), D. E. BURGESS, and P. A. MANNING (Royal Signals tweaking) in 30-60 min. The applicability of SAFExpert to other and Radar Establishment, Malvern, England) IN: Infrared parameter-adjustment and optimization problems is discussed. technology XII; Proceedings of the Meeting, San Diego, CA, Aug. T.K. 19, 20, 1986 . Bellingham, WA, Society of Photo-Optical Instrumentation Engineers, 1986, p. 108-114. Research supported A88-12725' Missouri Univ., Columbia. by the Ministry of Defence and Plessey Research and Technology, DEVELOPMENTAND IMPLEMENTATION OF AN AERODYNAMIC Ltd. HOLOGRAPHIC INTERFEROMETRY SYSTEM An account is given of the design features and performance JOHN B. MILES (Missouri-Columbia, University, Columbia), capabilities of pyroelectric IR sensors employing 64-element linear STEPHEN E. DUNAGAN, and JAMES L. BROWN (NASA, Ames detector arrays, germanium lenses, and a chopper for the Research Center, Moffett Field, CA) IN: High speed photography, modulation of the incoming radiation. In one of the two systems videography, and photonics IV; Proceedings of the Meeting, San presented; the peak value of the signal is read from the detector Diego, CA, Aug. 19, 20, 1986 . Bellingham, WA, Society of with the chopper in 'open' position and displayed in the form of a Photo-Optical Instrumentation Engineers, 1986, p. 186-198. refs grey-scale picture; in the second system, the difference between An aerodynamic holographic interferometry system has been the signals obtained with the chopper in 'open' and 'closed' developed and adapted for use with an existing supersonic wind positions is determined and displayed as a grey-scaled image. tunnel. The basis for the system is briefly discussed, and the flow The sensors may be used in a panned mode to give large-area investigation for which the system was developed is outlined. The surveillance, as well as in a staring mode to furnish image

49 information in virtue of the motion of the target. They may also Poe's method, and calculations are made of stress-strain, fastener be used in an aircraft-mounted linescan mode. O.C. flexibility, stress intensity factors, stringer load factor, and residual strength of the cracked panel. S.H. A88-12843 A COMPACT HIGH PERFORMANCE THERMAL IMAGER A. H. LETTINGTON (Royal Signals and Radar Establishment, A88-13084# Malvern, England) and W. T. MOORE (Rank Pullin Controls, Ltd., STRUCTURE SIMPLIFICATION AROUND A CUTOUT - Laughton, England) IN: Infrared technology XII; Proceedings of APPLICATION OF A SIMPLIFIED DAMAGE TOLERANCE the Meeting, San Diego, CA, Aug. 19, 20, 1986 . Bellingham, WA, DESIGN CHART Society of Photo-Optical Instrumentation Engineers, 1986, p. TETSUO UCHIMOTO, KANYA KOGA, and KOlCHl HIRAOKA 146-151. Japan Society for Aeronautical and Space Sciences, Journal (ISSN A compact, low-cost, high-performance thermal imager based 0021-4663), vol. 34, no. 394, 1986, p. 626-632. In Japanese. on a novel coaxial scanning technique is presented. Design refs requirements for this imager configuration encompass the The paper describes the development of a simplified damage avoidance of vignetting and pupil wander in the scanning elements tolerance design chart for the simplified structure around the cutout and objective lenses, as well as the maximization of detector cold for the next-generation commercial transport aircraft. The buildup shielding. The requirements are met by the use of SPRITE IR structure, outer panel, and frame seal are integrated to form the detectors, and the use of coincident pupils (as in the coaxial simplified structure, and a damage tolerance evaluation method is scanner). Attention is given to representative military applications established and compared with other methods. An analytical 1 for the thermal imager, including RPVs, airborne pods, helicopters, method for determining the stress intensity factor for cracks is ~ and land-based sights. O.C. discussed. S.H. 1 A88-12903 THIN-FILM TEMPERATURE SENSORS DEPOSITED BY RADIO FREQUENCY CATHODIC SPUlTERlNG N8&10209# National Bureau of Standards, Gaithersburg, Md. J. C. GODEFROY. C. GAGEANT. D. FRANCOIS, and M. PORTAT Center for Fire Research. ' (ONERA, Chatillon-sous-Bagneux, France) Journal of Vacuum TEST RESULTS AND PREDICTIONS FOR THE RESPONSE OF Science and Technology A (ISSN 0734-2101), vol. 5, Sept.-Oct. NEAR-CEILING SPRINKLER LINKS IN A FULL-SCALE I 1987, p. 291 7-2923. DRET-supported research. refs COMPARTMENT FIRE In order to gain better knowledge of the heat exchanges LEONARD Y. COOPER and DAVID W. STROUP Sep. 1987 occurring in aircraft turbines, ONERA is presently developing 45 P 1 thin-film heat sensors capable of operating up to a maximum (NBSIR-87-3633) Avail: NTlS HC AO3/MF A01 temperature of 1100 C. These high-temperature sensors are Data acquired during a test program which involved full-scale, 1 surface thermometers and fluxmeters of the gradient type. They sprinklered, compartment fires is presented and analyzed. This consist of metal films forming thermocouples and insulating films work focuses attention specifically on key features of the typical such as alumina or zircon stabilized by yttrium oxide. These layers sprinkler link deployment/response problem. It is found that the are deposited by RF cathodic sputtering on substrates such as elevated temperature, upper smoke layer which develops inevitably IN100, DS200, and CMSX2 superalloys which are either aluminized in compartment fires can have a major impact on the thermal or coated with an NiCoCrAlY alloy. The present state of response of sprinkler links. It is shown that traditionally accepted development of the thermometers is described as well as the first methods of predicting sprinkler response which do not account results obtained. Author for this upper layer can be totally inadequate. Link response predictions used here involve a new method of calculation which A80-12949 does take account of the smoke layer environment. Favorable ELASTIC BUCKLING OF INTERNALLY PRESSURIZED comparisons between predictions and experiment are obtained and CYLINDER-BULKHEAD COMBINATIONS experiments for further validation of this method are recommended. G. D. GALLETLY and J. BLACHUT (Liverpool, University, Finally, it is found that sprinkler link-to-ceiling spacing can have a England) Institution of Mechanical Engineers, Proceedings, Part significant effect on the thermal response of links and it is C - Mechanical Engineering Science (ISSN 0263-7154), vol. 201, recommended that a method which accounts for this effect be no. C4, 1987, p. 259-262. refs developed and validated. Author Unstiffened spherical caps attached to unstiffened cylindrical shells by means of circumferential stiffening rings are considered. The loading is by uniform internal pressure, and the object of the N88-10231 Forschungsinstitut fuer Hochfrequenzphysik, analysis is to determine if elastic bifurcation buckling can occur, Werthhoven (West Germany). and, if so, where the buckles will be located. The BOSOR 5 shell DETECTION OF TARGETS IN THE PRESENCE OF CLUTTER buckling program was used in the analysis, and several stiffener USING TARGET ECHO MODULATIONS CAUSED BY ROTATING geometries were investigated. Results show that elastic buckling STRUCTURES Thesls - Hochschule der Bunderwehr, can occur in the cylindrical portion of some cylinder-bulkhead Neublberg, West Germany combinations. If the structure is subjected to repeated loading, G. RETZER Nov. 1986 142 p In GERMAN; ENGLISH then the formation and disappearance of the elastic buckles could summary contribute to the initiation of fatigue cracks. Some of the geometries (Contract BMVG-T/RF31/71455/71340) investigated are like some commercial aircraft configurations. (REPT-12-66; LFD-256; ETN-87-90393) Avail: Issuing Activity Author The radar detection of hovering helicopters in the presence of clutter was investigated. It is shown that radar backscatter A88-13083# modulation by helicopter rotors can be described as line spectra STRESS INTENSITY FACTORS AND RESIDUAL STRENGTH OF in the frequency domain, with the spacings equivalent to the product A CRACKED STIFFENED PANEL of the rotor rotation frequency and the number of rotor blades. ATSUHIRO SASAKI and KOlCHl HIRAOKA Japan Society for Typical values are between 10 and 40 Hz. Experimental results Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. obtained with a coherent E-band pulse Doppler radar are in good 34, no. 394, 1986. p. 618-625. In Japanese. refs agreement with calculated values. Based on these results, a An analytical method for determining the stress intensity factors detector which allows the detection of hovering helicopters in the and residual strength of a cracked stiffened panel for the presence of clutter is proposed. The required radar parameters, next-generation commercial transport aircraft is presented. Crack such as radar dwell time and radar pulse repetition frequency, are verification for the panel is carried out using a modification of discussed. ESA

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N88-10278# European Space Agency, Paris (France). N88-10339*# General Electric Co., Lynn, Mass. Aircraft Engine EXPERIENCE ABOUT THE APPLICATION AND VALUATION OF Business Group. ROUGHNESS STRIPS FOR BOUNDARY LAYER TRANSITION THE DESIGN OF A TURBOSHAFT SPEED GOVERNOR USING CONTROL IN WIND TUNNEL TESTS IN THE HIGH-SPEED MODERN CONTROL TECHNIQUES Final Report, 30 Sep. 1982 RANGE - 20 Feb. 1985 SIEGHARD TUSCHE Mar. 1987 93 p Transl. into ENGLISH G. DELOSREYES and D. R. GOUCHOE Feb. 1986 220 p of Erfahrungen ueber die Anwendung und Beurteilung von (Contract NAS3-22763) Rauhigkeitsstreifen zur Beeinflussung des Grenzschichtumschlags (NASA-CR-175046; NAS 1.26:175046) Avail: NTlS HC A1 O/MF bei Windkanalversuchen im Hochgeschwindigkeitsbereich A01 CSCL 131 (Goetingen, Fed. Republic of Germany, DFVLR) 1986 Original The objectives of this program were: to verify the model of language document announced as N87-14291 off schedule compressor variable geometry in the T700 turboshaft (ESA-TT-1028; DFVLR-MITT-86-12; ETN-87-90664) Avail: NTlS engine nonlinear model; to evaluate the use of the pseudo-random HC A05/MF A01; original report in German available from binary noise (PRBN) technique for obtaining engine frequency DFVLR, Cologne, West Germany DM 56 response data; and to design a high performance power turbine Placing and application of artificial transition strips for speed governor using modern control methods. Reduction of T700 aerodynamic tests are described. Methods used in high-speed wind engine test data generated at NASA-Lewis indicated that the off tunnels for checking the effectiveness of transition strips are schedule variable geometry effects were accurate as modeled. given. ESA Analysis also showed that the PRBN technique combined with the maximum likelihood model identification method produced a Bode frequency response that was as accurate as the response N88-10283# National Aerospace Lab., Amsterdam (Netherlands). obtained from standard sinewave testing methods. The frequency Fluid Dynamics Div. response verified the accuracy of linear models consisting of engine MEASUREMENT TECHNIQUES IN LOW-SPEED TURBULENT partial derivatives and used for design. A power turbine governor FLOWS A REPORT ON EUROMECH 202 was designed using the Linear Quadratic Regulator (LQR) method B. VANDERBERG and A. BERTELRUD 5 Jun. 1986 17 p of full state feedback control. A Kalman filter observer was used Presented at the EUROMECH 202 Colloquium, Marknesse, The to estimate helicopter main rotor blade velocity. Compared to the Netherlands, 7-10 Oct. 1985 baseline T700 power turbine speed governor, the LQR governor (NLR-MP-860384; 88701065; ETN-87-90828) Avail: NTlS HC reduced droop up to 25 percent for a 490 shaft horsepower AO3/MF A01 transient in 0.1 sec simulating a wind gust, and up to 85 percent Measurement techniques in low speed turbulent flows and for a 700 shaft horsepower transient in 0.5 sec simulating a large typical swept wings were discussed. Wakes were included. ESA collective pitch angle transient. Author

N8&10377# British Aerospace Aircraft Group, Woodford N88-10305# Deutsche Forschungs- und Versuchsanstalt fuer (England). Structures Dept. Luft- und Raumfahrt, Cologne (West Germany). Abteilung fuer THE FATIGUE PROPERTIES OF AEROSPACE STEELS UNDER Turbinen und Schaufelkuehlung. CONSTANT AMPLITUDE AND FLIGHT-BY-FLIGHT SIMULATED COMPARISON OF DIFFERENT KINDS OF COMPACT CROSS LOADING Final Report FLOW HEAT EXCHANGERS J. A. FORSYTH Feb. 1986 34 p WERNER SIEMENS Sep. 1986 82 p In GERMAN; ENGLISH (Contract MOD-A93B/1548) summary Report will also be announced as translation (BAE-MSM-R-GEN-0566; BR99378; ETN-87-90679) Avail: NTlS (ESA-TT-1076) HC A03/MF A01 (DFVLR-FB-86-63; ISSN-0171-1342; ETN-87-90448) Avail: Fatigue tests were carried out to evaluate the fatigue properties NTlS HC A05/MF A01; DFVLR, Cologne, West Germany of alloy steels S99, S155 and AF1410, which span a wide range A computer program for the calculation of compact heat in toughness value (50 to 150 MPa square root m). The fighter exchangers for gas turbines was developed. The most important aircraft loading sequence (FALSTAFF) and conventional constant coefficients, pressure drops, and effectiveness of different kinds amplitude loading were used for the fatigue tests. The expected of exchangers were calculated as a function of Mach number, the tensile strength levels (specification minima) are met by the alloys dimensions of the exchanger, and the compactness. From the S99 and S155. The AF1410 material is slightly below specification. aerothermodynamic point of view, the plate exchanger is best, The fatigue performance of SI 55 is significantly inferior to that of closely followed by the lancet heat exchanger. The ribs of the S99 and AF1410. ESA plate version have no significant effect on the characteristics, but are required for stiffness and uniform channel height. The tube heat exchanger can only compete as far as the transferable heat N88-10386# National Aerospace Lab., Amsterdam (Netherlands). is concerned. ESA Structures and Materials Div. CRITERIA FOR DETERMINATION OF SIGNIFICANT LOAD CYCLES IN VARIABLE AMPLITUDE LOAD SEQUENCES NEE-10338 British Petroleum Co. Ltd., London (England). A. U. DEKONING and G. LlEFTlNG 1 Mar. 1986 41 p Presented STEERING MECHANISM Patent Application at the International Symposium on Fatigue Crack Closure, JOHN KIMBERLY WELLS, inventor 21 May 1986 12 p Filed Charleston, W.Va., May 1986 10 Oct. 1985 Priority 17 Oct. 1984 GB 8426278 (Contract NIVR-1823/01702-N) (EP-PATENT-0-181-7OO-Al; EP-PATENT-APPL-SN-85307273.4; (NLR-MP-860134; 88701061 ; ETN-87-90824) Avail: NTlS HC INT-PATENT-ClASS-B62D-l/18;ETN-87-98641) Avail: UK AO3/MF A01 Patent Office, 25 Southampton Buildings, London WCPA 1A4, The crack opening behavior of a fatigue crack in a centrally United Kingdom cracked panel was studied using a discretized version of the A collapsible steering mechanism for a vehicle, comp&sing a Dugdale and Barenblatt model. The effect of crack growth was steering shaft having a steering means connected to its upper included. .Results for constant amplitude loading agree with the end and a steering gear connected to its lower end is presented. literature. The effect of single overload-underload combinations The steering shaft comprises an elongated energy absorbing tube and of simple block loading programs on the crack opening having a bond between the tube and one or both of the steering behavior was analyzed. The results were compared with predictions gear and the steering means. The longitudinal axial component of based on an empirical model (CORPUS). The criteria used in the the bond is adapted to disrupt under crash impact and to allow CORPUS model to select significant load excursions in the applied the tube to progressively collapse and absorb the impact energy. load sequence were checked. Both models were used to predict ESA crack growth under a simplified landing gear load sequence. The

51 predicted crack opening loads and the crack growth lives agree N88-11081# Rolls-Royce Ltd., Derby (England). Advanced with experiment. ESA Research Lab. OPTICAL FLOW DIAGNOSTIC MEASUREMENTS IN TUR- N88-11002# Hoechst CeramTec A.G., Selb (West Germany). BOMACHINERY DEVELOPMENT OF A STATISTICALLY PROVEN INJECTION D. G. JONES and R. J. PARKER 1 Jun. 1987 13 p Presented MOLDING METHOD FOR REACTION BONDED SILICON at the 8th ISABE Conference, Cincinnati, Ohio, 15-19 Jun. 1987 NITRIDE, SINTERING REACTION BONDED SILICON NITRIDE, Previously announced in IAA as A87-46245 Sponsored by the AND SINTERED SILICON NITRIDE Final Report, 1 Jul. 1985 - United Kingdom Ministry of Defense Procurement Executive 30 Jun. 1986 (PNR90396; ETN-87-90999) Avail: NTlS HC AO3/MF A01 MATTHIAS STEINER 1987 49 p In GERMAN; ENGLISH Flow measurements within the passages of rotating model fans summary Sponsored by the Bundesministerium fuer Forschung was measured using laser holographic flow visualization and laser und Technologie, Federal Rep. of Germany transit anemometry. The complementary nature of the two (ETN-87-90575) Avail: NTlS HC AO3/MF A01 techniques uses the ability of holography to provide a diagnostic A statistically proven, series injection molding technique for identification in three dimensions of main features of the flow and ceramic components was developed for the construction of engines the ability of laser anemometry to provide quantitative and gas turbines. The flow behavior of silicon injection-molding measurements of the flow velocity at selected spatial locations. It materials was characterized and improved. Hot-isostatic-pressing is shown how the optical techniques, when suitably designed and reaction bonded silicon nitride (HIPRBSN) was developed. A ruggedized for a hostile environment, provide quantitative nondestructive component evaluation method was developed. An information of the intrapassage flows for a sequence of tests on injection molding line for HIPRBSN engine components wide chord fan blades, which aided the validation of their design precombustion chamber, flame spreader, and valve guide was intent. ESA developed. This line allows the production of small series for engine tests. ESA N88-11088*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. N88-1lOOS# Rolls-Royce Ltd., Derby (England). IMPACT OF TURBULENCE MODELING ON NUMERICAL INVESTMENT FOUNDRY MELTING STOCK. ROLLS ROYCE ACCURACY AND EFFICIENCY OF COMPRESSIBLE FLOW REQUIREMENTS AND DEMANDS IN TERMS OF QUALITY AND SIMULATIONS THE RELATIONSHIP TO END PRODUCT PERFORMANCE THOMAS J. COAKLEY Sep. 1986 9 p A. K. GIBBONS 28 Apr. 1987 5 p Submitted for publication (NASA-TM-88333; A-86326; NAS 1.1 5:88333) Avail: NTlS HC (PNR90397; ETN-87-91000) Avail: NTlS HC A02/MF A01 A02/MF A01 CSCL 20D Requirements and controls in terms of melt stock production Discussed is the numerical implementationof turbulence models procedures, quality, and acceptance for gas turbine investment used in viscous compressible flow simulations and their castings are discussed. The influence of melt stock quality on the performance described with respect to numerical accuracy, castings produced is reviewed. ESA efficiency and stability. The basic approach utilizes the Reynolds-averaged compressible Navier-Stokes equations in which N88-11048# Tennessee Univ., Knoxville. Dept. of Electrical the Reynolds stresses and heat fluxes are mathematically modeled Engineering. by suitable turbulence models. The turbulence models investigated PROCESS SUPPORT COMPRESSOR MOTOR ELECTROMAGNE- include zero-, one-, and two-equation eddy viscosity models. The TIC DESIGN SUMMARY flow fields investigated include theoretical and supersonic flows J. M. BAILEY Mar. 1987 31 p about two-dimensional and axisymmetric bodies. Discussions (Contract DE-AC05-840T-21400) concerning the numerical implementation of models include (DE87-014359; K/SUB-85-03528/2) Avail: NTlS HC A03/MF differencing procedures and boundary conditions used to assume A0 1 numerical stability and accuracy. Numerical performance is also A 30-hp, 15,000-rpm, permanent magnet motor has been evaluated by comparing computations with experimental results. designed and is now being built. The direct drive motor has 72 Author slots and eight poles. Using A. 0. Smith Magnetic, a flux plot was obtained and the flux density throughout one pole pitch has been N8&11089'# National Aeronautics and Space Administration. determined. The poles are connected in a four-pole series, parallel Ames Research Center, Moffett Field, Calif. WYE. Each pole requires 30 A for a total per phase current of 60 COMPUTATION OF TRANSONIC SEPARATED WING FLOWS A. The torque capability is 2638 oz-in. DOE USING AN EULEWNAVIER-STOKES ZONAL APPROACH UENVER KAYNAK, TERRY L. HOLST. and BRIAN J. CANTWELL (Stanford Univ., Calif.) Jul. 1986 152 p N88-11080#Rolls-Royce Ltd., Derby (England). (NASA-TM-88311; A-86271; NAS 1.1 5:88311) Avail: NTlS HC BOUNDARY LAYER PROFILE INVESTIGATIONS DOWNSTREAM A08/MF A01 CSCL 20D OF AN AERO-ENGINE INTAKE ANTI-ICING AIR EXHAUSTSLOT A computer program called Transonic Navier Stokes (TNS) S. J. DOWNS and E. H. JAMES (Loughborough Univ. of has been developed which solves the Euler/Navier-Stokes Technology, England ) 31 May 1987 8 p Presented at the equations around wings using a zonal grid approach. In the present 32nd ASME International Gas Turbine Conference and Exhibition, zonal scheme, the physical domain of interest is divided into several Anaheim, Calif., 31 May - 4 Jun. 1987 subdomains called zones and the governing equations are solved (PNR90378; ETN-87-90994) Avail: NTlS HC AO2/MF A01 interactively. The advantages of the Zonal Grid approach are as The boundary layer profile downstream of the anti-icing air follows: (1) the grid for any subdomain can be generated easily; exhaust slot of a two-dimensional aeroengine inlet section was (2) grids can be, in a sense, adapted to the solution; (3) different investigated by a pitot rake. Results for a range of inlet engine equation sets can be used in different zones; and, (4) this approach airflows with and without exhaust anti-icing air introduced are allows for a convenient data base organization scheme. Using presented. The boundary layer is found to be turbulent as expected this code, separated flows on a NACA 0012 section wing and on owing to the presence upstream in the wind tunnel of a fixed the NASA Ames WING C have been computed. First, the effects water spray grid which may be used to simulate engine operation of turbulence and artificial dissipation models incorporated into in clouds. Injection of anti-icing air produces a sublayer downstream the code are assessed by comparing the TNS results with other of the anti-icing air exhaust plane. Three methods of deriving CFD codes and experiments. Then a series of flow cases is boundary layer thickness from the experimental data were used described where data are available. The computed results, including and theoretical values determined. Experimental measurements cases with shock-induced separation, are in good agreement with confirm theoretical trends. ESA experimental data. Finally, some futuristic cases are presented to

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demonstrate the abilities of the code for massively separated cases for oil-off evaluation. These were: M2 steel to a 65% density, which do not have experimental data. Author CBS 1000M 65% density, and CBS 1000M 75% density. The bearing styles tested were ribbed cone (inner race) and ribbed N88-11lOl'# National Aeronautics and Space Administration. cup (outer race). Carburized solid CBS 600 was also used as a Marshall Space Flight Center, Huntsville, Ala. ribbed material for comparison of oil-off results. The tests were A 1987 PROGRESS REPORT OF MANUFACTURING conducted at six speeds from 4000 rpm (0.26 million DN) through TECHNIQUES FOR GRAVITY PROBE B GYROSCOPE ROTORS 37000 rprn (2.4 million DN).The ribbed cup style bearing achieved ROY A. TAYLOR, ED WHITE, and WILLIAM J. REED Sep. longer lives than the ribbed cone style. A standard bearing lasted 1987 32 p only 10 minutes at 4000 rpm; however, the 30-min oil-off goal (NASA-TM-100312; NAS 1.15:100312) Avail: NTlS HC AOWMF was achieved through 11000 rprn using the survivable ribbed cup A01 CSCL 148 bearing. The oil-off lives at 37000 rpm were less than 10 seconds. The significant improvements in the manufacture of Gravity The grinding of the powder metal materials and surface preparation Probe B gyroscope rotors developed since the publication of the to achieve an open porosity is extremely critical to the oil-off last report on this project are presented. The improvements include performance of the powder metal component. Author the polishing machine structure, rough laps, finishing/polishing laps, lapping procedure, measurement techniques, and a summary of the manufacturing status. These six areas represent significant improvements in the manufacture of the gyroscope rotors to meet N88-11139# Advisory Group for Aerospace Research and flight requirements. Author Development, Neuilly-Sur-Seine (France). RELIABILITY OF FINITE ELEMENT METHODS IN NORTH N88-11133# Rolls-Royce Ltd., Derby (England). AMERICA TRANSMISSION EFFICIENCY IN ADVANCED AEROSPACE JERZY J. KACPRZYNSKI Jul. 1987 25 p POWERPLANT (AGARD-R-748) Avail: NTlS HC AOWMF A01 J. A. DOMINY 2 Feb. 1987 14 p Presented at the The reliability of finite element analysis techniques in place of ASME/SAE/AIAA Joint Propulsion Conference, San Diego, Calif., structural test are discussed in the context of airworthiness 29 Jun. - 2 Jul. 1987 assessment. Using an example as illustration, it is shown that in (PNR90391; TER662; TlAl65189; ETN-87-90996) Avail: NTlS order to obtain meaningful results, the analysis must be performed HC A03/MF A01 with extreme care by an experienced analyst. The reliance on the For aerospace powerplant requiring high power reduction finite element analysis alone may result in serious misdiagnosis. gearboxes, an analytical method of estimating the efficiency of The verification and the certification of programs and the candidate transmissions was developed. The analysis was certification of users are discussed. Some of the most important calibrated against an existing transmission and applied to tests for validation of finite element programs are presented. gearboxes for single and contrarotating propfans and larger Author ultra-high-bypass ratio engines. In all cases the predicted efficiencies are broadly acceptable. The single most powerful influence is the gearbox configuration which is generally imposed by airframe requirements. ESA N88-11140"# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. N88-11134# Rolls-Royce Ltd., Derby (England). TURBINE ENGINE HOT SECTION TECHNOLOGY, 1985 THE USE OF KEVLAR ON AERO-ENGINE FAN CONTAINMENT Oct. 1985 443 p Conference held in Cleveland, Ohio, 22-23 CASINGS Oct. 1985 I. F. STEWART 18 May 1987 9 p Presented at the Impact (NASA-CP-2405; E-2727; NAS 1.55:2405) Avail: NTlS HC 87 Conference, Bremen, Federal Rep. of Germany, 18-22 May A19/MF A01 CSCL 20K 1987 The Turbine Engine Section Technology (HOST) Project Office (PNR90410; ETN-87-91003) Avail: NTlS HC A02/MF A01 of the Lewis Research Center sponsored a workshop to discuss The use of Kevlar to reduce the weight of fan containment current research pertinent to turbine engine hot section durability casings is described. Continuous layers of dry, woven Kevlar are problems. Presentations were made concerning hot section wrapped around a light former (the casing). Upon release, the environment and the behavior of combustion liners, turbine blades, blade punctures the casing and its energy is absorbed by the whole circumference of Kevlar, unlike a traditional metal casing and turbine vanes. which has to be thick enough so that all the blade energy is absorbed in the local area of impact where the blade hits the casing. Tests indicate that casing weights 50% of ARMVO casings are achievable. A theoretical model for predicting Kevlar deflections N88-11142'# United Technologies Research Center, East was developed. Over a wide range of blade energies, weave types, Hartford, Conn. wrapping tensions, and numbers of layers it gives good agreement THE DEVELOPMENT OF A HIGH TEMPERATURE STATIC with test results. The significant reduction in deflections predicted STRAIN GAGE SYSTEM for increased wrapping tension agrees well with measured test CHARLES 0. HULSE, RICHARD S. BAILEY, and HOWARD P. results. ESA GRANT (Pratt and Whitney Aircraft, East Hartford, Conn.) ln NASA. Lewis Research Center, Turbine Engine Hot Section N88-11135'# Timken Co., Canton, Ohio. Technology, 1985 p 45-49 Oct. 1985 IMPROVED OIL-OFF SURVIVABILITY OF TAPERED ROLLER (Contract NAS3-23722) BEARINGS Final Report, 1982 - 1987 Avail: NTlS HC A19/MF A01 CSCL 148 GARY E. KREIDER and PETER W. LEE Oct. 1987 86 p The objective of this program is to develop electrical resistance (Contract NAS3-23689; DA PROJ. 1L1-61102-AH-45) strain gages which will permit the measurement of static strains (NASA-CR-180804; NAS 1.26~80804; AVSCOM-TR-874-29) on nickel .and cobalt superalloy parts inside gas turbine engines Avail: NTIS HC A05/MF A01 CSCL 131 running on a test stand. The specific goal is to develop a complete The aim of this program is to improve the oil-off survivability system able to make strain measurements up to plus or minus of a tapered roller bearing when applied to a helicopter 2000 mu strain with a total error of no more than plus or minus transmission, since the tapered bearing has shown a performance 10 percent over a 50 hour period at 1250 K. The initial part of advantage in this application. However, the critical roller end-rib this work consisted of a strain gage alloy development effort in conjunction is vulnerable to damage in an oil-off condition. Three which a variety of alloys were evaluated after being prepared by powdered metal materials were selected to use as the rib material drop-casting or splat cooling. Author

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N88-11143'# Pratt and Whitney Aircraft, East Hartford, Conn. performed with uniform mainstream conditions for several orifice DEVELOPMENT OF HEAT FLUX SENSORS FOR TURBINE plate configurations. Schematics of the test section and the orifice AIRFOILS configurations are given. Temperature and pressure measurements WILLIAM H. ATKINSON, MARCIA A. CYR, and RICHARD R. were made in the test section at 4 axial and 11 transverse stations, STRANGE In NASA. Lewis Research Center, Turbine Engine using a 60-element rake probe. The measured temperature Hot Section Technology, 1985 p 51-58 Oct. 1985 distributions for these tests are reported. Author (Contract NAS3-23529) Avail: NTlS HC A19/MF A01 CSCL 14B N88-11154'# National Aeronautics and Space Administration. The objectives of this program are to develop heat flux sensors Lewis Research Center, Cleveland, Ohio. suitable for installation in hot section airfoils of advanced aircraft ON THE MIXING OF A ROW OF JETS WITH A CONFINED turbine engines and to experimentally verify the operation of these CROSSFLOW heat flux sensors in a cylinder in a cross flow experiment. J. D. HOLDEMAN In its Turbine Engine Hot Section Technology, Embedded thermocouple and Gardon gauge sensors were 1985 p 133-138 OCt. 1985 developed and fabricated into both blades and vanes. These were Avail: NTlS HC A19/MF A01 CSCL 20D then calibrated using a quartz lamp bank heat source and finally Mean temperature profiles calculated with an interactive subjected to thermal cycle and thermal soak testing. These sensors microcomputer code which evaluates dilution-zone design were also fabricated into cylindrical test pieces and tested in a alternatives are presented to show the effects of flow and geometric burner exhaust to verify heat flux measurements produced by these variables on the mixing of a single row of jets injected through sensors. The results of the cylinder in cross flow tests are given. sharp-edged orifices into a uniform flow of a different temperature Author in a constant area duct. In addition, this program is used to calculate profiles for opposed rows of jets with their centerlines in-line, by N88-11146'# National Aeronautics and Space Administration. assuming that the confining effect of an opposite wall is equivalent Lewis Research Center, Cleveland, Ohio. to that of a plane of symmetry between opposed jets. Author THE LEWIS STRAIN GAUGE LABORATORY: STATUS AND PLANS N88-11160'# Pratt and Whitney Aircraft, East Hartford, Conn. HOWARD F. HOBART and HERBERT A. WILL /n its Turbine Engine Hot Section Technology, 1985 p 77-79 Oct. 1985 COOLANT PASSAGE HEAT TRANSFER WITH ROTATION T. J. HAJEK and A. W. HlGGlNS In NASA. Lewis Research Avail: NTlS HC A19/MF A01 CSCL 148 An in-house lab was established for developing, testing, and Center, Turbine Engine Hot Section Technology, 1985 p 187-201 evaluating high-temperature strain gauges and to aid in in-house Oct. 1985 applications of high-temperature strain instrumentation. The lab is (Contract NAS3-23691) automated to provide computer control of oven temperatures, Avail: NTlS HC Al9/MF A01 CSCL 20D imposed strain, and data sampling. Author The objective is to develop a heat transfer and pressure drop data base, computationalfluid dynamic techniques, and correlations for multi-pass rotating coolant passages with and without flow N88-11150'# United Technologies Research Center, East turbulators. The experimental effort is focused on the simulation Hartford, Conn. of configurationsand conditions expected in the blades of advanced FUEL-INJECTOR/AIR-SWIRL CHARACTERIZATION aircraft high pressure turbines. With the use of this data base, the J. B. MCVEY, J. B. KENNEDY, and J. C. BENNETT (Connecticut effects of Coriolis and buoyancy forces on the coolant side flow Univ., Storrs.) In NASA. Lewis Research Center, Turbine Engine can be included in the design of turbine blades. Author Hot Section Technology, 1985 p 109-117 Oct. 1985 (Contract NAS3-24352) Avail: NTlS HC A19/MF A01 CSCL 20D N88-11161*# Stanford Univ., Calif. Thermosciences Div. The objectives of this program are to establish an experimental HEAT TRANSFER WITH VERY HIGH FREE STREAM data base documenting the behavior of gas turbine engine fuel TURBULENCE injector sprays as the spray interacts with the swirling gas flow ROBERT J. MOFFAT and PAUL K. MACIEJEWSKI In NASA. existing in the combustor dome, and to conduct an assessment Lewis Research Center, Turbine Engine Hot Section Technology, of the validity of current analytical techniques for predicting fuel 1985 p 203-215 OCt. 1985 spray behavior. Emphasis is placed on the acquisition of data (Contract NAG3-522) using injector/swirler components which closely resemble Avail: NTlS HC A19/MF A01 CSCL 20D components currently in use in advanced aircraft gas turbine Stanton numbers as much as 350 percent above the accepted engines, conducting tests under conditions that closely simulate correlations for flat plate turbulent boundary layer heat transfer or closely approximate those developed in actual combustors, and have been found in experiments on a low velocity air flow with conducting a well-controlled experimental effort which will comprise very high turbulence (up to 50 percent). These effects are far using a combination of low-risk experiments and experiments larger that have been previously reported and the data do not requiring the use of state-of-the-art diagnostic instrumentation. correlate as well in boundary layer coordinates (Stanton number Analysis of the data is to be conducted using an existing, and Reynolds number) as they do in simpler coordinates: h vs. X. TEACH-type code which employs a stochastic analysis of the The very high relative turbulence levels were achieved by placing motion of the dispersed phase in the turbulent continuum flow the test plate in different positions in the margin of a large diameter field. Author free jet. The large increases may be due to organized structures of large scale which are present in the marginal flowfield around N88-11153'# Garrett Turbine Engine Co., Phoenix, Ariz. a free jet. Author DILUTION JET MIXING PROGRAM, PHASE 3 R. SRINIVASAN, G. MYERS, and C. WHITE In NASA. Lewis N88-11162*# Minnesota Univ., Minneapolis. Research Center, Turbine Engine Hot Section Technology, 1985 PREDICTION OF TURBINE BLADE HEAT TRANSFER p 127-132 OCt. 1985 SUHAS V. PATANKAR In NASA. Lewis Research Center, Turbine (Contract NAS3-22110) Engine Hot Section Technology, 1985 p 217-219 Oct. 1985 Avail: NTlS HC A19/MF A01 CSCL 20D (Contract NAG3-579) The objectives of the program were: (1) to extend the data Avail: NTlS HC Al9/MF A01 CSCL 200 base on mixing of a single-sided row of jets with a confined It is planned to incorporate a number of low Reynolds number crossflow, (2) to collect a data base on mixing of multiple rows of turbulence models in a general two-dimensional boundary layer jets with confined crossflow, (3) to develop empirical jet mixing calculation procedure. This will be applied to different flow correlations, and (4) to perform limited three-dimensional conditions over turbine blades and the predictions will be compared calculations for some of these test configurations. The tests were with experimental data. The prediction activity will lead to a

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recommendation about a satisfactory turbulence model for turbine been based on classical inelastic methods. The unified constitutive blade heat transfer. Author theory to be developed will avoid the simplifying assumptions of classical theory and should more accurately represent the behavior N88-11163'# Scientific Research Associates, Inc., Glastonbury, of superalloy materials under cyclic loading conditions and high Conn. temperature environments. During the first two years of the FLOW IN A MODEL TURBINE STATOR program, extensive experimental correlations were made with two R. C. BUGGEIN, S. J. SHAMROTH, and W. R. BRILEY In NASA. representative unified models. The experiments were both uniaxial Lewis Research Center, Turbine Engine Hot Section Technology, and biaxial at temperatures up to 1093 C (2000 F). In addition, 1985 p 221-226 OCt. 1985 the unified models were adopted to the MARC finite element code (Contract NAS3-24358) and used for stress analysis of notched bar and turbine blade Avail: NTlS HC A19/MF A01 CSCL 20D geometries. Author In view of the complex nature of the flowfield in the hot section of gas turbine engines, the need to predict heat transfer and flow N88-11172'# General Electric Co., Cincinnati, Ohio. Aircraft losses, the possible appearance of separation and strong Engine Business Group. secondary flows, etc., the present effort is focusing upon a CONSTITUTIVE MODELING FOR ISOTROPIC MATERIALS Navier-Stokes approach to the three dimensional turbine stator V. G. RAMASWAMY, R. H. VANSTONE, L. T. DAME, and J. H. problem. The advantages of a full Navier-Stokes approach are LAFLEN ln NASA. Lewis Research Center, Turbine Engine Hot clear since when combined with a suitable turbulence model these Section Technology, 1985 p 307-320 Oct. 1985 equations represent the flow and heat transfer physics. In particular, (Contract NAS3-23927) the Navier-Stokes equations accurately represent possible Avail: NTlS HC A19/MF A01 CSCL 20K separated regions and regions of significant secondary flow. In Constitutive theories were evaluated against a large uniaxial addition, the Navier-Stokes approach allows representation of the and multiaxial data base that was generated as part of this work. entire flow field by a single set of equations, thus avoiding problems The experimental approach was to determine the constitutive associated with representing different regions of the flow by behavior of Rene 80 under a multitude of conditions that are different equations and then matching flow regions. Author important in the design of gas turbine blades and vanes. The experimental and analytical goals of this program were successfully N88-11164*# General Electric Co., Cincinnati, Ohio. Aircraft accomplished. A new multiaxial constitutive model which can Engine Business Group. represent the complex nonlinear high temperature behavior of Rene 3D INELASTIC ANALYSIS METHODS FOR HOT SECTION 80 was developed. The model was extensively verified on data at COMPONENTS several temperatures. Author L. T. DAME, P. C. CHEN, M. S. HARTLE, and H. T. HUANG ln NASA. Lewis Research Center, Turbine Engine Hot Section N88-11173'# Pratt and Whitney Aircraft, East Hartford, Conn. Technology, 1985 p 227-237 Oct. 1985 CREEP FATIGUE LIFE PREDICTION FOR ENGINE HOT (Contract NAS3-23698) SECTION MATERIALS (ISOTROPIC): THIRD YEAR PROGRESS Avail: NTlS HC Al9/MF A01 CSCL 20K REVIEW The objective is to develop analytical tools capable of RICHARD S. NELSON and JOHN F. SCHOENDORF ln NASA. economically evaluating the cyclic time dependent plasticity which Lewis Research Center, Turbine Engine Hot Section Technology, occurs in hot section engine components in areas of strain 1985 p 321-327 Oct. 1985 concentration resulting from the combination of both mechanical (Contract NAS3-23288) and thermal stresses. Three models were developed. A simple Avail: NTlS HC A19/MF A01 CSCL 20K model performs time dependent inelastic analysis using the power This program is designed to investigate fundamental damage law creep equation. The second model is the classical model of processes, identify modeling strategies, and develop practical Professors Walter Haisler and David Allen of Texas A and M models which can be used to guide the early design and University. The third model is the unified model of Bodner, Partom, development of new engines and to increase the durability of et al. All models were customized for linear variation of loads and existing engines. A review is given of the base program, completed temperatures with all material properties and constitutive models in 1984, which included the comparison and evaluation of several being temperature dependent. Author popular high-temperature life prediction approaches as applied to continuously cycled isothermal specimen tests. The option program, N88-11170'# National Aeronautics and Space Administration. of which one year is completed, is designed to develop models Lewis Research Center, Cleveland, Ohio. which can account for complex cycles and loadings, such as HIGH TEMPERATURE STRESSSTRAIN ANALYSIS thermomechanical cycling, cumulative damage, multiaxial stress/ ROBERT L. THOMPSON ln its Turbine Engine Hot Section strain rates, and environmental effects. Author Technology, 1985 p 287-301 Oct. 1985 Avail: NTlS HC A19/MF A01 CSCL 20K N88-11174'# General Electric Co.. Cincinnati, Ohio. Aircraft The objectives of the high temperature structures program are Engine Business Group. threefold: to assist in the development of analytical tools needed ELEVATED TEMPERATURE CRACK GROWTH to improve design analysis and procedures for the efficient and S. N. MALIK, R. H. VANSTONE, K. S. KIM, and J. H. IAFLEN accurate prediction of the nonlinear structural response of ln NASA. Lewis Research Center, Turbine Engine Hot Section hot-section components; to aid in the calibration, validation, and Technology, 1985 p 329-340 Oct. 1985 evaluation of the analytical tools by comparing predictions with (Contract NAS3-23940) experimental data; and to evaluate existing as well as advanced Avail: NTlS HC A19/MF A01 CSCL 20K temperature and strain measurement instrumentation. Author The purpose is to determine the ability of currently available P-l integrals to correlate fatigue crack propagation under conditions N88-11171"# Southwest Research Inst., San Antonio, Tex. that simulate the turbojet engine combustor liner environment. The CONSTITUTIVE MODELING FOR ISOTROPIC MATERIALS utility of advanced fracture mechanics measurements will also be ULRlC S. LINDHOLM ln NASA. Lewis Research Center, Turbine evaluated during the course of the program. To date, an appropriate Engine Hot Section Technology, 1985 p 303-306 Oct. 1985 specimen' design, a crack displacement measurement method, and (Contract NAS3-23925) boundary condition simulation in the computational model of the Avail: NTlS HC A19/MF A01 CSCL 20K specimen were achieved. Alloy 718 was selected as an analog The objective is to develop a unified constitutive model for material based on its ability to simulate high temperature behavior finite element structural analysis of turbine engine hot-section at lower temperatures. Tensile and cyclic tests were run at several components. This effort constitutes a different approach for strain rates so that an appropriate constitutive model could be non-linear finite-element computer codes which have heretofore developed. Suitable P-l integrals were programmed into a finite

55 12 ENGINEERING element post-processor for eventual comparison with experimental N88-11186'# Rensselaer Polytechnic Inst., Troy, N.Y. data. Author COMPOSITE STRUCTURAL MATERIALS Annual Progress Report no. 50, 1 May 1986 - 30 Apr. 1987 N88-11175*# Pratt and Whitney Aircraft, East Hartford, Conn. ROBERT G. LOEWY and STEPHEN E. WIBERLEY Aug. 1987 LIFE PREDICTION AND CONSTITUTIVE MODELS FOR ENGINE 93 P HOT SECTION ANISOTROPIC MATERIALS PROGRAM (Contract NGL-33-018-003) G. A. SWANSON In NASA. Lewis Research Center, Turbine (NASA-CR-181416; NAS 1.26:181416) Avail: NTlS HC A05/MF ' Engine Hot Section Technology, 1985 p 341-349 Oct. 1985 A01 CSCL20K (Contract NAS3-23939) The development and application of composite materials to Avail: NTlS HC Al9/MF A01 CSCL 20K aerospace vehicle structures which began in the mid 1960's has The purpose is to develop life prediction models for coated now progressed to the point where what can be considered entire anisotropic materials used in gas temperature airfoils. Two single airframes are being designed and built using composites. Issues crystal alloys and two coatings are now being tested. These include related to the fabrication of non-resin matrix composites and the PWA 1480; Alloy 185; overlay coating, PWA 286 and aluminide micro, mezzo and macromechanics of thermoplastic and metal coating, PWA 273. Constitutive models are also being developed matrix composites are emphasized. Several research efforts are for these materials to predict the plastic and creep strain histories presented. They are entitled: (1) The effects of chemical vapor of the materials in the lab tests and for actual design conditions. deposition and thermal treatments on the properties of pitch-based This nonlinear material behavior is particularily important for high carbon fiber; (2) Inelastic deformation of metal matrix laminates; temperature gas turbine applications and is basic to any life (3) Analysis of fatigue damage in fibrous MMC laminates; (4) prediction system. Author Delamination fracture toughness in thermoplastic matrix composites; (5) Numerical investigation of the microhardness of composite fracture; and (6) General beam theory for composite N88-11182*# National Aeronautics and Space Administration. structures. Author Lewis Research Center, Cleveland, Ohio. THERMAL EXPANSION MISMATCH AND OXIDATION IN THERMAL BARRIER COATINGS G. C. CHANG, W. PHUCHAROEN (Cleveland State Univ., Ohio.), and R. A. MILLER In its Turbine Engine Hot Section Technology, N88-11198# Aeronautical Research Labs., Melbourne 1985 p 405-425 OCt. 1985 (Australia). (Contract NCC3-27) THE INFLUENCE OF LOAD CYCLE RECONSTITUTION ON Avail: NTlS HC A19/MF A01 CSCL 131 FATIGUE BEHAVIOUR Thermal barrier coatings (TBC) for advanced gas turbine blades J. M. FINNEY and F. G. HARRIS Aug. 1986 37 p have been under intensive development during the last several (ARL-STRUC-R-424; AR-004-498) Avail: NTlS HC AO3/MF A01 years. This investigation is intended to achieve a clearer Fatigue experiments have been conducted to assess the understanding of the mechanical behavior of plasma sprayed influence of the method of reconstituting a load sequence from a zirconia-yttria TBCs, involving a nickle-chromium-aluminumbond range-pair counted load spectrum for a fighter aircraft. In addition coat. The near term objectives are to study the stress states in a to the original flight-by-flight sequence, several quite-structured relatively simple model TBC subjected to steady state thermal reconstituted sequences and random reconstituted sequences were loading. The resulting thermal expansion mismatch and oxidation used, all sequences having identical range-pair counts. There was have been primary targets for the study. The finite element little or no difference in crack propagation lives or total lives of approach and the effects of thermal mismatch and oxidation are two specimen geometries for the several structured sequences described. A proposed mechanism for oxidation induced coating which were designed to give the extremes in crack growth life. failure is also presented. Author There was, also, no significant difference in crack propagation lives for specimens tested under the flight-by-flight and random N88-11183'# Garrett Turbine Engine Co., Phoenix, Ariz. sequences. Crack growth under the more structured sequences THERMAL BARRIER COATING LIFE PREDICTION MODEL was significantly slower than under the more fluctuating sequences DEVELOPMENT (random and flight-by-flight), though the maximum difference of T. E. STRANGMAN, J. F. NEUMANN, and A. TASOOJI In NASA. 1.59:l is small relative to other uncertainties in fatigue life Lewis Research Center, Turbine Engine Hot Section Technology, assessment. These results provide a basis for implementing the 1985 p 427-432 OCt. 1985 Aircraft Fatigue Data Analysis System which utilizes strain Avail: NTlS HC Al9/MF A01 CSCL 131 range-pair counting. Author This program focuses on predicting the lives of two types of strain-tolerant and oxidation-resistantthermal barrier coating (TBC) systems that are produced by commercial coating suppliers to the gas turbine industry. The plasma-sprayed TBC system is composed N88-11202"# National Aeronautics and Space Administration. of a low pressure, plasma sprayed applied, oxidation resistant Langley Research Center, Hampton, Va. NiCrAlY bond coating. The other system is an air plasma sprayed AGARD STANDARD AEROELASTIC CONFIGURATIONS FOR yttria (8 percent) partially stabilized zirconia insulative layer. DYNAMIC RESPONSE. CANDIDATE CONFIGURATION I.-WING Author 445.6 E. CARSON YATES, JR. Aug. 1987 78 p N88-11185'# Pratt and Whitney Aircraft, East Hartford, Conn. (NASA-TM-100492; NAS 1.15:100492) Avail: NTlS HC AO5/MF THERMAL BARRIER COATING LIFE PREDICTION MODEL A01 CSCL20K DEVELOPMENT To promote the evaluation of existing and emerging unsteady J. T. DEMASI and K. D. SHEFFLER ln NASA. Lewis Research aerodynamic codes and methods for applying them to aeroelastic Center, Turbine Engine Hot Section Technology, 1985 p 445-455 problems, especially for the transonic range, a limited number of Oct. 1985 aerodynamic configurations and experimental dynamic response (Contract NAS3-23944) data sets are to be designated by the AGARD Structures and Avail: NTlS HC A19/MF A01 CSCL 131 Materials Panel as standards for comparison. This set is a sequel The objective is to develop an integrated life prediction model to that established several years ago for comparisons of calculated accounting for all potential life-limiting thermal barrier coating (TBC) and measured aerodynamic pressures and forces. This report degradation and failure modes, including spallation resulting from presents the information needed to perform flutter calculations for cyclic thermal stress, oxidation degradation, hot corrosion, erosion the first candidate standard configuration for dynamic response and foreign object damage. Author along with the related experimental flutter data. Author

56 14 LIFE SCIENCES

13 14

GEOSCIENCES LIFE SCIENCES

Includes geosciences (general); earth resources; energy production Includes life sciences (general); aerospace medicine; behavioral and conversion; environment pollution; geophysics; meteorology sciences; man/system technology and life support; and planetary and climatology; and oceanography. biology.

N88-10463# Technische Univ., Brunswick (West Germany). A88-10154' Psycho-Linguistic Research Associates, Menlo Park, Fakultaet fuer Maschinenbau und Elektrotechnik. Calif. CONTRIBUTIONS TO THE MODELING OF WIND SHEAR FOR VERSATILE SIMULATION TESTBED FOR ROTORCRAFT DANGER STUDIES Ph.D. Thesis [BEITRAEGE ZUR SPEECH I/O SYSTEM DESIGN MODELLIERUNG VON SCHERWIND FUER GEFAEHRDUNGSUN- CAROL A. SIMPSON (Psycho-Linguistic Research Associates, TERSUCHUNGEN] Menlo Park, CA) IN: Aerospace Behavioral Engineering MANFRED SWOLINSKY 1986 202 p In GERMAN Technology Conference, 5th, Long Beach, CA, Oct. 13-16, 1986, (ETN-87-90442) Avail: NTlS HC AlO/MF A01 Proceedings . Warrendale, PA, Society of Automotive Engineers, Wind models for flight simulation and the study of the danger Inc., 1986, p. 33-37. USAF-supported research. during landing due to wind shear were developed. It is demonstrated (Contract NAS2-12425) that the typical wind conditions in weather phenomena such as (SAE PAPER 861661) thunderstorm fall winds and surface boundary layer wind shear A versatile simulation testbed for the design of a rotorcraft can be approximated by simple engineering models, whereby speech I/O system is described in detail. The testbed will be known solutions and flow forms from flow mechanics were adapted. used to evaluate alternative implementations of synthesized speech The good agreement between models and airborne measurements displays and speech recognition controls for the next generation is demonstrated. Based on the developed models the degree of of Army helicopters including the LHX. The message delivery logic danger during landing under different wind shear conditions was is discussed as well as the message structure, the speech estimated. ESA recognizer command structure and features, feedback from the recognizer, and random access to controls via speech command. K.K.

A88- 10158 AN INTEGRATED DISPLAY FOR VERTICAL SITUATION AWARENESS IN COMMERCIAL TRANSPORT AIRCRAFT ROGER HOUCK, BRIAN D. KELLY, and JOHN WIEDEMANN (Boeing Commercial Airplane Co., Seattle, WA) IN: Aerospace Behavioral Engineering Technology Conference, 5th, Long Beach, CA, Oct. 13-16, 1986, Proceedings . Warrendale, PA, Society of Automotive Engineers, Inc., 1986, p. 61-64. (SAE PAPER 861770) The need for a sideview-presentation vertical situation display (VSD) for use in commercial transport aicraft is demonstrated. The preliminary conceptual VSD format includes an inside-out presentation with a moving scale and vertical map translating around a fixed airplane symbol. The information is scaled along altitude and distance axes to permit present, predicted, and future altitude requirements to be integrated with other relevant vertical situational information. It is believed that the completed VSD N88-10464# Deutsche Forschungs- und Versuchsanstalt fuer concept will improve the flightcrew's awareness of the aircraft's Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). Abteilung spatial position throughout the flight. K.K. Wolkenphysik. THE DEPENDENCE OF THE NORMALIZED ICE ACCRETION THICKNESS ON CLOUD-PHYSICAL PARAMETERS HANS-EBERHARD HOFFMANN, ROLAND ROTH, and JOHANN A88-10160. Boeing Commercial Airplane Co., Seattle, Wash. DEMMEL Jan. 1987 64 p In GERMAN; ENGLISH summary COMPARISON OF PROGRAMMABLE LEGEND KEYBOARD AND Report will also be announced as translation (ESA-UT-1080) DEDICATED KEYBOARD FOR CONTROL OF THE FLIGHT (DFVLR-FB-87-08; ISSN-0171-1342; ETN-87-90455) Avail: MANAGEMENT COMPUTER NTlS HC A04IMF A01; DFVLR, Cologne, West Germany DM JEAN M. CRANE, GEORGE P. BOUCEK, JR. (Boeing Commercial 24.50 Airplane Co., Seattle, WA), and WAYNE D. SMITH (Boeing Military Normalized ice accretion thickness was studied using the Airplane Co., Wichita, KS) IN: Aerospace Behavioral Engineering measurement results of 38 icing research aircraft flights in icing Technology Conference, 5th, Long Beach, CA, Oct. 13-16, 1986, clouds. Normalized ice accretion is the ice accretion thickness on Proceedings . Warrendale, PA, Society of Automotive Engineers, 3 metal cylinders in flow direction, for a true air speed of 125 kt, Inc., 1986, p. 83-90. refs and a flight path in clouds of 10 NM (i.e., 18.5 km). In the (Contract NAS1-17635) investigated range of liquid water content up to 0.50 g/cum, the (SAE PAPER 861772) normalized ice thickness grows linearly with increasing liquid water A study is described which compares two types of input devices content; it is a little larger for cloud particles freezing used to operate a flight management computer: a programmable instantaneously. The thickness is larger for smaller cylinder legend (multifunction) keyboard and a conventional (dedicated) diameters. In the temperature range between minus 2 and minus keyboard. Pilot performance measures, subjective responses, and 14 C, a difference in temperature has only a little influence, a timeline analysis were used in evaluating the two keyboard differences in particle phase and particle size distribution have no concepts. A discussion of the factors to be considered in the influence on the normalized ice accretion thickness. ESA implementation of a multifunction keyboard is included. Author

57 14 LIFE SCIENCES

A88-10 162 A88-10965' National Aeronautics and Space Administration. THE ADVANTAGES OF A PRIMARY FLIGHT DISPLAY Langley Research Center, Hampton. Va. J. E. HUTCHINSON (International Federation of Air Line Pilots TRADITIONAL VERSUS RULE-BASED PROGRAMMING Associations, Egham, England) IN: Aerospace Behavioral TECHNIQUES - APPLICATION TO THE CONTROL OF Engineering Technology Conference, 5th, Long Beach, CA, Oct. OPTIONAL FLIGHT INFORMATION 13-16, 1986, Proceedings . Warrendale, PA, Society of Automotive WENDELL R. RICKS and KATHY H. ABBOTT (NASA, Langley Engineers, Inc., 1986, p. 101-104. Research Center, Hampton, VA) SPIE, Technical Symposium (SAE PAPER 861730) Southeast on Optics, Electro-optics, and Sensors, Orlando, FL, The features of a primary flight display (PFD) are discussed as May 17-22, 1987, Paper. 8 p. refs well as its advantages over conventional instrumentation. The A traditional programming technique for controlling the display present PFD is part of the electronic flight instrument system which of optional flight information in a civil transport cockpit is compared is standard on the current series of Airbus models. Consideration to a rule-based technique for the same function. This application is given to failure indications, the airspeed scale, the flight path required complex decision logic and a frequently modified rule vector (FPV), and the FPV with head-up display. K.K. base. The techniques are evaluated for execution efficiency and implementation ease; the criterion used to calculate the execution efficiency is the total number of steps required to isolate hypotheses A88-12639' National Aeronautics and Space Administration. that were true and the criteria used to evaluate the implementability Ames Research Center, Moffett Field, Calif. are ease of modification and verification and explanation capability. PERSPECTIVE TRAFFIC DISPLAY FORMAT AND AIRLINE It is observed that the traditional program is more efficient than PILOT TRAFFIC AVOIDANCE the rule-based program; however, the rule-based programming STEPHEN R. ELLIS, MICHAEL W. MCGREEVY (NASA, Ames technique is more applicable for improving programmer Research Center, Moffett Field; California, University, Berkeley), productivity. I.F. and ROBERT J. HITCHCOCK (San Jose State University, CA) Human Factors (ISSN 0018-7208), vol. 29, Aug. 1987, p. A88-11115# 371-382. refs INITIAL USER EXPERIENCE WITH AN ARTIFICIAL (Contract NCC2-86) INTELLIGENCE PROGRAM FOR THE PRELIMINARY DESIGN Part-task experiments have examined perspective projections OF CENTRIFUGAL COMPRESSORS of cockpit displays of traffic information as a means of presenting CAROL J. RUSSO (General Electric Co., Aircraft Engine Business aircraft separation information to airline pilots. Ten airline pilots Group, Lynn, MA), DENNIS J. NICKLAUS, and SIU S. TONG served as subjects in an experiment comparing the perspective (General Electric Co., Schenectady, NY) ASME, International projection with plan-view projections of the same air traffic Gas Turbine Conference and Exhibition, 32nd. Anaheim, CA, May situations. The pilots' task was to monitor the traffic display in 31-June 4, 1987. 8 p. refs order to decide if an avoidance maneuver was needed. Pilots (ASME PAPER 87-GT-217) took more time to select avoidance maneuvers with a conventional An approach in which existing analysis codes are coupled to a plan-view display than with an experimental perspective display. generic AI framework, ENGINEOUS, is proposed for the evaluation In contrast to previous results, if the pilots selected a maneuver of the design of turbomachinery components. Using a simple and with the perspective display, they were more likely to choose one incomplete rule base, ENGINEOUS is shown to quickly identify with a vertical component. Tabulation of the outcomes of their nonobvious solutions balanced for conflicting multiple goals in a initial avoidance decisions with both perspective and plan-view small number of iterations which vary linearly with the number of displays showed that they were more likely to achieve required variables. The solution path and driving logic are easily visible, separation with maneuvers chosen with the aid of perspective and a parameter study option can rapidly evaluate potential design displays. Author trade-offs, allowing a critique of the selected design to balance performance against development risks. R.R.

A88-11394 COMPUTING COMPLEX FOR A SYSTEM FOR THE RADIO-ACOUSTIC SOUNDING OF THE ATMOSPHERE - 15 HARDWARE FACILITIES [VYCHISLITEL'NYI KOMPLEKS SISTEMY RADIOAKUSTICHESKOGO ZONDlROVANllA ATMOS- MATHEMATICAL AND COMPUTER SCIENCES FERY.APPARATNYE SREDSTVA] V. 1. ALEKHIN, 0. V. DRIAMOV, A. I. KLIUSHIN, I. V. KORWSEV, Includes mathematical and computer sciences (general); computer and G. I. SIDOROV Radiotekhnika (Kharkov) (ISSN 0485-8972), operations and hardware; computer programming and software; no. 76. 1986, p. 71-77. In Russian. refs computer systems; cybernetics; numerical analysis; statistics and The paper describes the computing complex of a radio-acoustic probability; systems analysis; and theoretical mathematics. sounding system which is used at airports to investigate the meteorological parameters of the atmospheric surface layer. This complex provides for the real-time input of period values of the Doppler frequency of the reflected signal, the calculation of A88-10929 meteorological-parameter values, and the printout of results. THE ACCURACY-RELATED PARAMETRIC REDUCTION OF Particular attenion is given to the design and operation of the MATHEMATICAL MODELS [0TOCHNOSTNOI PARAMETRICHES- controllers. B.J. KO1 REDUKTSll MATEMATICHESKIKH MODELEI] IGOR' EVGEN'EVICH EFIMOV (AN USSR, lnstitut Problem A88-12526 Modelirovaniia v Energetike, Kiev, Ukrainian SSR) Elektronnoe AIAA COMPUTERS IN AEROSPACE CONFERENCE, 6TH, Modelirovanie (ISSN 0204-3572), vol. 9, July-Aug. 1987, p. 3-7, WAKEFIELD, MA, OCT. 7-9, 1987, TECHNICAL PAPERS 89. In Russian. refs Conference sponsored by AIAA. Washington, DC, American The paper examines several approaches to the construction Institute of Aeronautics and Astronautics, 1987,397 p. For individual of algorithms for the simplification of mathematical models on the items see A88-12527 to A88-12579. basis of accuracy-related parametric reduction. This reduction Papers are presented on the analysis of Ada as a prototyping consists in a formalization of the coordination of the model structure language; the evaluation of a dual processor implementation for a and the accuracy indices of the model parameters. The results fault inferring nonlinear detection system; fault-tolerant systems; are of interest in connection with the analysis of aircraft flight intelligent interfaces to aircraft systems; the implementation of a dynamics. B.J. research prototype on a fault monitoring and diagnosis system;

58 15 MATHEMATICAL AND COMPUTER SCIENCES future data acquisition capabilities; and the application of AI artificial intelligence techniques for improved situational awareness. technology to the analysis and synthesis of reliable software Under this research effort, concepts were developed and a software systems. Topics discussed include the spaceplane's astronaut's architecture was designed to address the complexities of onboard associate; model-based health monitoring for reusable launch monitoring and diagnosis. This paper describes the implementation vehicles; Space Shuttle telemetry analysis by a real-time expert of these concepts in a computer program called FaultFinder. The system; avionics, AI, and embedded processing systems; implementation of the monitoring, diagnosis, and interface functions methodology requirements for intelligent systems architecture; and as separate modules is discussed, as well as the blackboard commonsense reasoning and superconductivity for self-replicating designed for the communication of these modules. Some related telerobots. Consideration is given to autonomous spacecraft issues concerning the future installation of FaultFinder in an aircraft operations; semiautonomous control for satellite servicing; and are also discussed. Author expert system control for airborne radar surveillance. I.F.

A8&12532'# Charles River Analytics, Inc., Cambridge, Mass. A88-12544# EVALUATION OF A DUAL PROCESSOR IMPLEMENTATION AOSP - MULTIPROCESSOR ARCHITECTURE AND SYSTEM FOR A FAULT INFERRING NONLINEAR DETECTION SYSTEM CONSIDERATIONS P. M. GODIWALA, A. K. CAGLAYAN (Charles River Analytics, DANIEL J. DECHANT and FRANK A. HORRIGAN (Raytheon Co., Inc., Cambridge, MA), and F. R. MORRELL (NASA, Langley Sudbury, MA) IN: AlAA Computers in Aerospace Conference, Research Center, Hampton, VA) IN: AlAA Computers in Aerospace 6th, Wakefield, MA, Oct. 7-9, 1987, Technical Papers . Washington, Conference, 6th, Wakefield, MA, Oct. 7-9, 1987, Technical Papers DC, American Institute of Aeronautics and Astronautics, 1987, p. . Washington, DC, American Institute of Aeronautics and 129-135. refs Astronautics, 1987, p. 43-51. refs (Contract F30602-78-C-0027; F30602-80-C-0206; (AIAA PAPER 87-2762) F3602-84-C-0094) The design of a modified fault inferring nonlinear detection (AIAA PAPER 87-2790) system (FINDS) algorithm for a dual-processor configured flight The architecture of the Advanced Onboard Signal Processor computer is described. The algorithm was changed in order to (AOSP). its embedded survivable local area network, its operating divide it into its translational dynamics and rotational kinematics system software, and its fault tolerance characteristics are and to use it for parallel execution on the flight computer. The described. The application of the AOSP to a sensor signal FINDS consists of: (1) a no-fail filter (NFF), (2) a set of test-of-mean processing system is examined. The partitioning of the application detection tests, (3) a bank of first order filters to estimate failure processing functions and the programming of the applications are levels in individual sensors, and (4) a decision function. NFF filter discussed. I.F. performance using flight recorded sensor data is analyzed using a filter autoinitialization routine. The failure detection and isolation capability of the partitioned algorithm is evaluated. A multirate A88-12558# implementation for the bias-free and bias filter gain and covariance AVIONICS, ARTIFICIAL INTELLIGENCE, AND EMBEDDED matrices is discussed. I.F. PROCESSING SYSTEMS PETER M. KOGGE (IBM, Federal Systems Div., Owego, NY) IN: A88-12539'# Bolt, Beranek, and Newman, Inc., Cambridge, AlAA Computers in Aerospace Conference, 6th, Wakefield, MA, Mass. Oct. 7-9, 1987, Technical Papers . Washington, DC, American INTELLIGENT INTERFACES TO AIRCRAFT SYSTEMS Institute of Aeronautics and Astronautics, 1987, p. 236-245. ROBERT SCHUDY, KEVIN CORKER, and SHELDON BARON (AIAA PAPER 87-2818) (BBN Laboratories, Inc., Cambridge, MA) IN: AlAA Computers in This paper addresses the characteristics that an embedded Aerospace Conference, 6th, Wakefield, MA, Oct. 7-9, 1987, processing system must have to support AI functions for various Technical Papers . Washington, DC, American Institute of avionics applications. The emphasis is on those kinds of functions Aeronautics and Astronautics, 1987, p. 93-99. refs that are unconventional in nature, computationally stressing, and (Contract NASl-17335) of high value to future real-time avionics systems. The topics (AIAA PAPER 87-2776) covered include a brief review of the major computational models An approach for developing intelligent aiding systems for airline for AI in use today, their appropriateness to several avionics AI flight crews is proposed. This approach proceeds in four cycles: applications, what their implementation means in terms of processor (1) National Traffic Safety Board data and pilot interviews are architectures, and how they might be supported in high performance used to determine the areas in which pilots require aid; (2) a pilot avionics systems of the near future. Author information processing model is designed; (3) an intelligent pilot-aiding model is developed; and (4) systems for implementing aiding functions are defined. This approach is utilized to design a A88-12575# general situation-response pilot-aiding system. The situation-re- AUTONOMOUS PROCESSING USING A BLACKBOARD sponse model and the structure of a general situation-response pilot- CHIPSET aiding system are described. The computer implementation of the STEPHEN A. UCZEKAJ (Boeing Aereospace Co., Seattle, WA), situation-response information processing model is examined. I.F. ROBERT GRAHAM, DZlEM NGUYEN, CALVIN LING, THOMAS SKILLMAN (Boeing High Technology Center, Seattle, WA) et al. IN: AlAA Computers in Aerospace Conference, 6th, Wakefield, A88-12540'# National Aeronautics and Space Administration. MA, Oct. 7-9, 1987, Technical Papers . Washington, DC, American Langley Research Center, Hampton, Va. Institute of Aeronautics and Astronautics, 1987, p. 358-362. refs IMPLEMENTATION OF A RESEARCH PROTOTYPE ONBOARD (AIAA PAPER 87-2855) FAULT MONITORING AND DIAGNOSIS SYSTEM In the present evaluation of the capabilities of a 'blackboard' MICHAEL T. PALMER, KATHY H. ABBOTT, PAUL C. SCHUTTE, AI chipset that can accomplish the cooperative working of separate and WENDELL R. RICKS (NASA, Langley Research Center, processes toward the solution of a problem in autonomous Hampton, VA) IN: AlAA Computers in Aerospace Conference, processing tasks, attention is given to the development of the 6th, Wakefield, MA, Oct. 7-9, 1987, Technical Papers. Washington, chipset that will support the blackboard framework. Chipset support DC, American Institute of Aeronautics and Astronautics, 1987, p. of the blackboard framework is by means of a blackboard control 100-107. refs unit that allows opportunistic problem-solving to be undertaken (AIAA PAPER 87-2777) among multiple clusters of processors dedicated to coarse-grain Due to the dynamic and complex nature of in-flight fault granularity in real-time embedded applications. The autonomous monitoring and diagnosis, a research effort was undertaken at processing capabilities are required for military aircraft threat NASA Langley Research Center to investigate the application of detection/avoidance and target location/identification. O.C.

59 15 MATHEMATICAL AND COMPUTER SCIENCES

A88-13109 N88-11429'# National Aeronautics and Space Administration. ADVANCED COMPUTING FOR MANUFACTURING Ames Research Center, Moffett Field, Calif. ALBERT M. ERISMAN and KENNETH W. NEVES (Boeing THE SPATIALLY NONUNIFORM CONVERGENCE OF THE Computer Services Co., Seattle, WA) Scientific American (ISSN NUMERICAL SOLUTION OF FLOWS 0036-8733), VOI.257, Oct. 1987, p. 163-169. ARGYRIS G. PANARAS Nov. 1987 30 p The use of supercomputers to help design aerodynamically (NASA-TM-100037; A-88016; NAS 1.15:100037) Avail: NTlS HC efficient aircraft is discussed. The vector and parallel architecture AOWMF A01 CSCL 12A of supercomputers that facilitates such applications is described. The spatial distribution of the numerical disturbances that are The development of software for computerized manufacturing generated during the numerical solution of a flow is examined. It applications is examined, and problems concerning the integration is shown that the distribution of the disturbances is not uniform. of user, graphics workstation, and supercomputer are addressed. In regions where the structure of a flow is simple, the magnitude C.D. of the generated disturbances is small and their decay is fast. However, in complex flow regions, as in separation and vortical areas, large magnitude disturbances appear and their decay may be very slow. The observed nonuniformity of the numerical disturbances makes possible the reduction of the calculation time N88-11165*# Pratt and Whitney Aircraft, East Hartford, Conn. by application of what may be called the partial-grid calculation 3-D INELASTIC ANALYSIS METHODS FOR HOT SECTION technique, in which a major part of the calculation procedure is COMPONENTS applied in selective subregions, where the velocity disturbances E. S. TODD In NASA. Lewis Research Center, Turbine Engine are large, and not within the whole grid. This technique is expected Hot Section Technology, 1985 p 239-243 Oct. 1985 to prove beneficial in large-scale calculations such as the flow (Contract NAS3-23697) about complete aircraft configurations at high angle of attack. Also, Avail: NTlS HC Al9/MF A01 CSCL 09B it has been shown that if the Navier-Stokes equations are written The objective is to produce a series of new computer codes in a generalized coordinate system, then in regions in which the that permit more accurate and efficient three dimensional inelastic grid is fine, such as near solid boundaries, the norms become structural analysis of combustor liners, turbine blades, and turbine infinitesimally small, because in these regions the Jacobian has vanes. Each code embodies a progression of mathematical models very large values. Thus, the norms, unless they are unscaled by for increasingly comprehensive representaion of the geometrical the Jacobians, reflect only the changes that happen at the outer features, loading conditions, and forms of nonlinear material boundaries of the computation domain, where the value of the response that distinguish these three groups of hot section Jacobian approaches unity, and not in the whole flow field. components. Author Author

N88-11166'# General Electric Co., Cincinnati, Ohio. Aircraft Engine Business Group. COMPONENT SPECIFIC MODELING R. L. MCKNIGHT and M. T. TIPTON In NASA. Lewis Research Center, Turbine Engine Hot Section Technology, 1985 p 245-257 Oct. 1985 (Contract NAS3-23687) Avail: NTlS HC A19/MF A01 CSCL 09B The objective is to develop and verify a series of interdisciplinary modeling and analysis techniques that have been specialized to address three specific hot section components. These techniques will incorporate data as well as theoretical methods from many diverse areas including cycle and performance analysis, heat transfer analysis, linear and nonlinear stress analysis, and mission analysis. The new methods developed will be integrated to provide N88-11435'# National Aeronautics and Space Administration. an accurate, efficient, and unified approach to analyzing combustor Ames Research Center, Moffett Field, Calif. burner liners, hollow air-cooled turbine blades, and air-colled turbine APPROACH TRAJECTORY PLANNING SYSTEM FOR MAXIMUM vanes. For these components, the methods developed will predict CONCEALMENT temperature, deformation, stress, and strain histories throughout a DAVID N. WARNER, JR. Jul. 1986 17 p complete flight mission. Author (NASA-TM-88258; A-86264; NAS 1.15:88258) Avail: NTlS HC AOB/MF A01 CSCL 12A A computer-simulation study was undertaken to investigate a maximum concealment guidance technique (pop-up maneuver), which military aircraft may use to capture a glide path from masked, N88-11382'# George Washington Univ., Washington, D.C. Dept. low-altitude flight typical of terrain following/terrain avoidance flight of Operations Research. enroute. The guidance system applied to this problem is the Fuel SOFTWARE RELIABILITY MODELS FOR FAULT-TOLERANT Conservative Guidance System. Previous studies using this system AVIONICS COMPUTERS AND RELATED TOPICS Final Report, have concentrated on the saving of fuel in basically conventional 1 Jul. 1981 - 30 Jun. 1987 land and ship-based operations. Because this system is based on DOUGLAS R. MILLER 4 Nov. 1987 17 p energy-management concepts, it also has direct application to the (Contract NAG1-1 79) pop-up approach which exploits aircraft performance. Although the (NASA-CR-181440; NAS 1.26:181440) Avail: NTlS HC AOWMF algorithm was initially designed to reduce fuel consumption, the A01 CSCLO9B commanded deceleration is at its upper limit during the pop-up Software reliability research is briefly described. General and, therefore, is a good approximation of a minimum-time solution. research topics are reliability growth models, quality of software Using the model of a powered-lift aircraft, the results of the study reliability prediction, the complete monotonicity property of reliability demonstrated that guidance commands generated by the system growth, conceptual modelling of software failure behavior, are well within the capability of an automatic flight-control system. assurance of ultrahigh reliability, and analysis techniques for Results for several initial approach conditions are presented. tault-tolerant systems. Author Author

60 16 PHYSICS

16 N88-10589# Southampton Univ. (England). Inst. of Sound and Vibration Research. PHYSICS ACTIVITIES REPORT OF THE INSTITUTE OF SOUND AND VIBRATION RESEARCH Annual Report, period ending Mar. 1987 Includes physics (general); acoustics; atomic and molecular 1987 49 p physics; nuclear and high-energy physics; optics; plasma physics; (ETN-87-90685) Avail: NTlS HC AO3/MF A01 solid-state physics; and thermodynamics and statistical physics. Research concerning fluid dynamics and acoustics; audiology and human effects; structures and machinery; and signal processing and control is summarized. Aircraft noise; underwater acoustics; A88-10047 silencers; biomechanics; noise measurement; hearing; structural AIRCRAFT ACOUSTICS I - EXTERIOR NOISE OF SUBSONIC dynamics; laser technology; automotive engineering; and active PASSENGER AIRCRAFT AND HELICOPTERS [AVIATSIONNAIA control are discussed. ESA AKUSTIKA. I - SHUM NA MESTNOSTI DOZVUKOVYKH PASSAZHIRSKIKH SAMOLETOV I VERTOLETOV] ANATOLll GRIGOR’EVIC MUNIN, ED. Moscow, Izdatel’stvo Mashinostroenie, 1986, 248 p. In Russian. No individual items are abstracted in this volume. N88-10592’# National Aeronautics and Space Administration. Problems related to the effect of the exterior noise produced Lewis Research Center, Cleveland, Ohio. by subsonic aircraft and helicopters on the environment and man NOISE OF A MODEL HIGH SPEED COUNTERROTATION are examined. The principal sources of noise produced by aircraft PROPELLER AT SIMULATED TAKEOFF/APPROACH CONDI- and helicopters are identified, and the physical pattern of noise TIONS (F7/A7) generation is examined. Various method of reducing the noise of RICHARD P. WOODWARD 1987 25 p Presented at the 11th aircraft and helicopters are discussed, and methods are presented Aeroacoustics Conference, Sunnyvale, Calif., 19-21 oct. 1987: for predicting the acoustic environment at airports with allowance sponsored by AlAA for the size of the aircraft park and the dynamics of flight (NASA-TM-100206; E-3766; NAS 1.15:100206; AIAA-87-2657) operations. V.L. Avail: NTlS HC AO3/MF A01 CSCL 20A A high speed advanced counterrotation propeller, was tested A88-10048 in the NASA-Lewis 9 x 15 foot Anechoic Wind Tunnel at simulated AIRCRAFT ACOUSTICS I1 - CABIN NOISE IN PASSENGER takeoff/approach conditions of 0.2 Mach number. Acoustic AIRCRAFT [AVIATSIONNAIA AKUSTIKA. I1 - SHUM V measurements were taken with fixed floor microphones, an axially SALONAKH PASSAZHIRSKIKH SAMOLETOVI translating microphone probe, and with a polar microphone probe ANATOLll GRIGOR’EVIC MUNIN Moscow, Izdatel’stvo which was fixed to the propeller nacelle and could take both Mashinostroenie, 1986, 264 p. In Russian. No individual items are sideline and circumferential acoustic surveys. Aerodynamic abstracted in this volume. measurements were also made to establish the propeller operating Results of theoretical and experimental studies of cabin noise conditions. The propeller was run over a range of blade setting and noise on the fuselage of passenger aircraft are presented, angles from 36.41365 to 41.1/39.4 deg, tip speeds from 165 to and methods of noise reduction are discussed. The discussion 259 m/sec, rotor spacings from 1.56 to 3.63 based on forward covers the principal noise sources, such as the gas jet, compressor, rotor tip chord to aerodynamic separation, and angles of attack to turbulent boundary layer, propeller, engine vibration, and air + or - 16 deg. First order rotor alone tones showed highest conditioning system. Cabin noise reduction methods discussed directivity levels near the propeller plane, while interaction tone include sound and vibration insulation and sound and vibration showed high levels throughout sideline directivity, especially toward absorption. Finally, methods for calculating cabin noise are the propeller rotation axis. Interaction tone levels were sensitive presented. V.L. to propeller row spacing while rotor alone tones showed little spacing effect. There is a decreased noise level associated with A88-12281*# Purdue Univ., West Lafayette, Ind. higher propeller blade numbers for the same overall propeller PREDICTION OF SOUND FIELDS IN CAVITIES USING thrust. Author BOUNDARY-ELEMENT METHODS R. J. BERNHARD, B. K. GARDNER, C. G. MOLL0 (Purdue University, West Lafayette. IN), and C. R. KlPP (ATIT Bell Laboratories, Whippany, NJ) AlAA Journal (ISSN 0001 -1452), vol. 25, Sept. 1987, p. 1176-1 183. Previously cited in issue 22, p. N88-10594 National Physical Lab., Teddington (England). Div. 3338, Accession no. A06-45404. refs of Radiation Science and Acoustics. (Contract NAG1-58) NOISE LEVELS FROM PROPELLER-DRIVEN AIRCRAFT MEASURED AT GROUND LEVEL AND AT 1.2 M ABOVE THE N88-10588# Air Force Occupational and Environmental Health GROUND Lab., Brooks AFB, Tex. R. C. PAYNE Mar. 1987 63 p FIRST ARTICLE TEST NOISE SURVEY OF THE A/F32T-9 (NPL-AC-110; ISSN-0143-7143; ETN-87-90931) Avail: Issuing LARGE TURBO FAN ENGINE ENCLOSED NOISE SUPPRESSOR Activity SYSTEM, SKY HARBOR IAP (INTERNATIONAL AIRPORT), Aircraft noise measurements using microphones close to the PHOENIX, ARIZONA Final Report, for Period Ending Nov. ground plane and at a height of 1.2 m showed substantial 1986 differences between measured A-weighted sound levels. The JEFFERY C. JENKINS and TERRY M. FAIRMAN Jun. 1987 differences depend on ground cover, aircraft type, and flight 160 p maneuver. The ground-plane microphones produced A-weighted (AD-A183799; USAFOEHL-87-082EH0186FNA) Avail: NTlS HC levels which closely approximate to pressure-doubled values. Two AOB/MF A01 CSCL 20A procedures for correcting A-weighted sound pressure levels The A/F32T-9 Large Turbofan Engine, Enclosed Noise measured 1.2 m above the ground, to obtain pressure-doubled Suppressor System (T-9 NSS) at Sky Harbor International Airport, levels, were examined. In one procedure the noise spectrum was Phoenix, Arizona was surveyed to determine noise levels at 100 assumed to be represented by a series of 113-octave bands, in meters. With an FlOl engine operating at afterburner power the the other by a number of pure tones or discrete narrow-bands of highest measured Overall Sound Level, A-Weighted (OASLA) was noise. Neither correction procedure is wholly successful. It is 88.7 dB(A). The measured OASLA values exceeded the 77 dB(A) concluded that, to avoid significant variations in measured criterion at all but five of the twenty-four sampling positions. A-weighted levels, noise measurements must be made using a GRA ground-plane microphone. ESA

61 16 PHYSICS

N88-10595# Motoren- und Turbinen-Union Muenchen G.m.b.H. rotor speed as the control variable over the range of 103% of (West Germany). the main-rotor speed (NR) to 75% NR, and with the forward speed NOISE EMISSION OF CIVIL AND MILITARY AERO-ENGINES. maintained at a constant value of 80 knots. Author SOURCES OF GENERATION AND MEASURES FOR ATTENUATION H. GRlEB and K. HElNlG Sep. 1986 25 p Presented at the 17 NATO Symposium on Aircraft Noise in the Modern Society, Mittenwald, West Germany, 22-25 Sep. 1986 (ETN-87-91021) Avail: NTlS HC AO3/MF A01 SOCIAL SCIENCES It is shown that noise reduction on high bypass ratio turbofans for civil airliners is well established. The noise levels achieved Includes social sciences (general); administration and management; meet the internationally agreed regulations (FAR 36). The same documentation and information science; economics and cost holds true for large military transport aircraft. Helicopter noise is analysis; law and political science; and urban technology and caused essentially by the main and tail rotors. Noise reduction on transportation. afterburner and dry engines for combat and strike aircraft, which represent the major noise annoyance to the public, is very difficult because: high specific thrust is mandatory for aircraft performance N88-10697# National Aerospace Lab., Amsterdam and effectiveness; jet noise with and without afterburning is (Netherlands). predominant; and the design of the reheat section and final AEROSPACE RESEARCH AT THE NATIONAL AEROSPACE (variable) nozzle in practice precludes the application of known LABORATORY (NLR) concepts for jet noise attenuation in dry and reheated operation. 1987 40 p Original contains color illustrations ESA (ETN-87-90821) Avail: NTlS HC AO3/MF A01 Research in fluid dynamics (wind tunnel tests, computational N88-10608# NKF Engineering, Inc., Reston, Va. aerodynamics, unsteady aerodynamics, aeroacoustics, propulsion); FIBER OPTIC ENGINEERING SENSOR SYSTEM. PRELIMINARY flight (handling qualities, aircraft performance, flight tests, systems, PROGRAM MANAGEMENT PLAN, PHASE 3 REVISION flight simulation, certification, air traffic control, human factors Jul. 1987 36 p engineering); aerospace structures and materials; satellite control; (Contract NO0014-874-2032) remote sensing; robotics; microgravity; and computing science is (AD-A183663; NKF-87103-003/03-REV) Avail: NTlS HC described. ESA A03/MF A01 CSCL 17E The principal objective of this program is to develop a Fiber Optic Engineering Sensor System (FOESS) including sensors, 19 telemetry, and displays for applications such as damage control, system control (Le., propulsion or steering) and intrusion defense systems for ship, aircraft and shore applications. This objective is GENERAL being achieved by research and engineering effort conducted in three, originally four, contractually defined phases. GRA

N88-10610# British Aerospace Aircraft Group, Preston (England). Maths Services Dept. A88-12202 THE DEVIATION OF LIGHT RAYS PASSING THROUGH A INVESTIGATIONS IN THE HISTORY AND THEORY OF CURVED WINDSCREEN DEVELOPMENT OF AEROSPACE SCIENCE AND TECHNOLOGY. S. WHITTLE 12 Jan. 1987 20 p NUMBER 5 [ISSLEDOVANIIA PO ISTORI I TEORll RAZVlTllA AV- (BAE-MSC.115; ETN-87-90680) Avail: NTlS HC A03/MF A01 IATSIONNOI I RAKETNO-KOSMICHESKOI NAUKI I TEKHNIKI. Formulas for the deviation of light rays passing through the NUMBER 51 windscreen of a fighter aircraft are obtained. The collimation of B. V. RAUSHENBAKH, ED. Moscow, Izdatel’stvo Nauka, 1986, the head up display can then be altered so that the display does 240 p. In Russian. No individual items are abstracted in this not appear further away than the ground. ESA volume. Several papers are presented concerning the history of aerospace science and technology. Papers are also presented on N88-11451’# National Aeronautics and Space Administration. the development of unmanned winged flight vehicles, glider design, Langley Research Center, Hampton, Va. aircraft with rocket engines, and variable wing geometry. B.J. HELICOPTER MAIN-ROTOR SPEED EFFECTS ON FAR-FIELD ACOUSTIC LEVELS ARNOLD W. MUELLER. OTIS S. CHILDRESS, and MARK HARDESTY (McDonnell-Douglas Helicopter Co.,Mesa, Ariz.) Oct. 1987 20 p Prepared for presentation at the 114th Meeting of the Acoustical Society of America, Miami, Fla., 16-20 Nov. 1987 (NASA-TM-100512; NAS 1.15:100512) Avail: NTlS HC A03/MF A01 CSCL20A The design of a helicopter is based on an understanding of many parameters and their interactions. For example, in the design stage of a helicopter, the weight, engine, and rotor speed must be considered along with the rotor geometry when considering helicopter operations. However, the relationship between the noise radiated from the helicopter and these parameters is not well understood, with only limited model and full-scale test data to study. In general, these data have shown that reduced rotor speeds result in reduced far-field noise levels. This paper reviews the status of a recent helicopter noise research project designed to provide experimental flight data to be used to better understand helicopter rotor-speed effects on far-field acoustic levels. Preliminary results are presented relative to tests conducted with a McDonnell Douglas model 500E helicopter operating with the SUBJECT INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 223) February 1988

Typical Subject Index Listing

A preliminary investigation into the feasibility of The effect of gnt roughness on the performance of the SUBJECT HEADING implementinga direct sideforce control system on the Astra Wortmann FX63-137 airfoil at a chord Reynolds number Hawk by means of an active control surface .--aircraft of 100,000 p 11 A88-11202 control Aerodynamics of unmanned aircraft at Iull-SCale in the [ ETN-87-909241 p 37 N88-10795 RAE 24ft wind-tunnel p 12 A88-11204 Investigation of control law for active flutter AERODYNAMIC HEAT TRANSFER The performance of model aircraft using flow Calculation of aerodynamic heat transfer for blunt-nosed suppress ion invigorators, gliding in the critical range of Reynolds [NASA-lT-201261 p 39 N88-10818 thin wings at dillerent angles of anack at supersonic number p12 A88-11206 ADA (PROGRAMMING LANGUAGE) speeds Effect 01 energy release in the shock layer on the AIM Computers in Aerospace Conference. 6th. I NASA-TTT-~OI27 1 p 18 N88-10i76 supersonic flight of bodies p 13 A88-12073 Wakefield. MA, Oct. 7-9, 1987, Technical Papers r Optimal lifting wings with required longitudinal balancing p58 A88-12526 characteristics p 14 A88-12075 ADAPTATION Wall interference tests of a CAST 10-2IDOA 2 airfoil An aerodynamic design study of transonic transport in an adaptive-wall test section wings p 15 AM-13078 [ NASA-TM-40151 p18 N88-10772 High-lift-device design and low-speed wind-tunnel test ADAPTIVE CONTROL p 15 A88-13079 HIDEC adaptive engine control system flight evaluation Integration of dynamic, aerodynamic and Structural results optimization of helicopter rotor blades [ASME PAPER 87-GT-2571 p 32 A88-11137 [NASA-CR-181441I p16 N88-10012 A method for the calculation of transonic llows for the Diagnosis of flow channel in aircraft gas-turbineengines The subject heading is a key to the subject content control of adaptive wind tunnels on basis of vibration spectrum characteristics of the document. The title is used to provide a [ETN-87-90411] p 17 N88-10015 p 35 N88-10993 description of the subject matter. When the title is ADAPTIVE FILTERS AERODYNAMIC COEFFICIENTS Multigrid solution of the Euler equations on unstructured insufficiently descriptive of document content, a Unsteady aerodynamic measurements on a rotating and adaplive meshes p 44 A88-10570 compressor blade row at low Mach number title extension is added, separated from the title ADHESION [ASME PAPER 87-GT-2211 p7 A88-11118 by three hyphens. The (NASA or AIAA) accession Basic concepts for better heat protection systems Exact and asymptotic expressions of the lift slope p 42 A88-12786 coefficient 01 an elliptic wing p 14 A88-12292 number and the page number are included in each AERIAL RECONNAISSANCE International Conference the Aerodynamics at Low entry to assist the user in locating the abstract in Airborne reconnaissanceX; Proceedings of the Meeting, on Reynolds Numbers between lO(4) and lO(6) San Diego. CA. Aug. 19.20. 1986 the abstract section. If applicable, a report number [ONRL-7-023-C] p16 N88-10010 [SPIE-694] p 26 A88-12728 is also included as an aid in identifying the docu- Investigations of separated flow stales wings of Sensor controlIdala display set (SCIDDS) for film on medium aspect ratio taking into account the wind tunnel ment. Under any one subject heading, the acces- and/or electro optics (EO) p 26 A88-12731 interference problem sion numbers are arranged in sequence with the Video data link provides television pictures in near real [ETN-87-90437] p 17 N88-10016 time via tactical radio and satellite channels AIAA accession numbers appearing first. AERODYNAMIC CONFIGURATIONS p 49 A88-12732 Problem and solution formulations for the generation Real-time reconnaissance - An engineering of 30 block-structured grids --- aircraft design perspective p21 A88-12733 [ NLR-MP-86020-U1 p25 NEB-10028 Magnetic recording lor near real time reconnaissance The aerothermodynamic environment for holes in applications p 27 A88-12736 hypersonic configurations A Synchronizing video signals to standard IRlG time [DE87-014651] p 17 N88-10767 codes p21 A88-12737 AERODYNAMIC DRAG A-320 AIRCRAFT Datalink design trade-offs for electro-optical The development of wing theory p 14 A88-12483 The will to European unity as exemplified by A320 reconnaissance systems p 27 A88-12740 AERODYNAMIC HEAT TRANSFER p 23 A88-10659 Airborne reconnaissance pod flight test Calculation of aerodynamic heat transfer for blunt-nosed ACCIDENTS p 27 A88-12741 thin wings at different angles of attack at supersonic Cost savings possrble mth Air Force conversion to JP-8 Sensor configuration for a short to medium range speeds as its pnmary fuel reconnaissance pod p 27 A88-12742 [ NASA-lT-201271 pl8 N88-10776 [AD-A183784] p 42 N88-10192 Imaging through the atmosphere lor airborne AERODYNAMIC INTERFERENCE reconnaissance p 27 A88-12748 A transonic model representation for two-dimensional ACCURACY wall interference assessment The accuracy-relaled parametnc reduction of Arguments for electro-optical reconnaissance systems [ NLR-TR-8602641 p15 N88-10006 mathematical models p 58 A88-10929 p 27 A88-12749 Wall interference tests of a CAST 10-2/DOA 2 airfoil Softcopy versus hardcopy digital image displays for Impact of turbulence modeling on numencal accuracy --- in an adaptive-wall test section aerial reconnaissance p 27 A88-12750 and efficiency of compressrble flow srmulasons [ NASA-TM-40151 p 18 N88-10772 [ NASA-TM-883331 p 52 NEB-11088 Recent developments in infrared data processing AERODYNAMIC LOADS p28 A88-12751 New Soviet commercial airliners p 23 A88-10655 ACOUSTIC MEASUREMENT AEROACOUSTICS The fourth generaton of TL commercial aircraft Investigation 01 the suitablity of the Eft x 6ft transonic Prediction 01 sound fields in cavities using p23 A88-10656 wind-tunnel for aeroacoustic research propellers on boundary-element methods p 61 A88-12281 AERODYNAMIC STALLING [ RAE-TM-AERO-2093] p39 N88-10041 Investiigation of the suitability of the Eft x 6ft transonic Through-flow analysis of a multi-stage compressor ACOUSTIC PROPERTIES wind-tunnel for aeroacouslic research on propellers operating at near-stall conditions First article test noise survey of the AIF32T-9 large turbo [ RAE-TM-AERO-20931 p39 N88-10041 [ASME PAPER 87-GT-511 p4 A88-11003 Ian engine enclosed noise suppressor system, Sky Harbor Noise of a model high speed counterrotation propeller A theoretical study of spanwise-periodic 3-D IAP (Internatonal Airport). Phoenix, Anzona at simulated takeoWapproach conditions (F7/A7) disturbances in the wake 01 a slightly stalled wing at low [ AD-At 837991 p6t N88-10588 [NASA-TM-100208] p61 N88-10592 Reynolds numbers p8 A88-11180 ACOUSTIC SOUNDING AERODYNAMIC BALANCE AERODYNAMICS Aerodynamics a1 Reynolds numbers Re greater than ComputinQcomplex for a system for the rado-acoustic Dynamic wind tunnel balances in the DFVLR subsonic low 10 to the 4th and less than 10 lo the 6th; Proceedings sounding of the atmosphere - Hardware facilitkas wind tunnel in Braunschweig p 39 A88-12488 of the International Conference. London, England, Oct. p 58 A88-11394 AERODYNAMIC CHARACTERISTICS 15-18, 1986. Volumes 1, 2, 8 3 p 8 A88-11176 ACOUSTICS On some unsteady aerodynamics characteristics of an Aerodynamics at low Reynolds numbers. A review of Actrvlbes repcft of the Institute of Sound and Vibfatron NACA 0012 at Reynolds numbers of 125.000 and theoretical and experimental research at Delft University 400.000 p 10 A88-11189 Research of Technology p8 ABS-11177 [ETN-87-90685] p 61 N88-10589 On the determination of the 2-D characteristics of Development and implementation of an aerodynamic ACTIVE CONTROL aerofoils at low Reynolds numbers p 10 A88-11192 holographic interferometry system p 49 A88-12725 Flutter suppreswn and gust load allevlaton Part 1 An experimental investigation of the aerodynamics of AEROELASTICITV Results 01 phase 1 lo 3 Part 2 Descnptron of the Garteur the hang gli ptl A88-11200 Velocitv scaled aeroelastic lestina of advanced model The aerodynamics 01 gliding parachutes turboprops [MBB-LKE292/S/PUB/t 91 1 p 36 N88-10038 p 11 A88-11201 [ASME PAPER 87-GT-2091 p3t A88-11110

A- 1 AERONAUTICAL ENGINEERING SUBJECT INDEX

The history of aeroelasticity research in Germany from Knowledge Based Concepts and Artificial Intelligence: The fatigue properties of aerospace steels under the beginning until 1945 _..airframes Applications to Guidance and Control constant amplitude and flight-by-flight simulated loading [DNLR-MIlT86-25] pl N88-10003 [AGARD-LS-155] p38 N88-10806 [BAE-MSM-R-GEN-05661 p 51 N88-10377 Analytical modeling of helicopter static and dynamic An expert system for aircraft conflict resolution in dense AIRCRAFT CONTROL induced velocity in GRASP airspaces p 22 N88-10810 Robotic air vehicle - A pilot's perspective p 19 A88-10437 [NASA-TM-100026] p 18 N88-10777 A rule-based system for arrival sequencing and AGAR0 standard aeroelastic configurations for dynamic scheduling in air traffic control p 22 N88-10815 The impact of modern technology on aircraft avionics equipment p 26 A88-10679 response. Candidate configuration I.-wing 445.6 AIR TRAFFIC CONTROLLERS(PERSONNEL) HlDEC adaptive engine control system flight evaluation [NASA-TM-1004921 p 56 N88-11202 An expert system for aircraft conflict resolution in dense results AERONAUTICAL ENGINEERING airspaces p 22 NEB-10810 Color display programming for aviation [ASME PAPER 87-GT-2571 p 32 A88-11137 A rule-based system for arrival sequencing and Design study for an FEW lateral control System [DFVLR-MIlT-87-031 p 28 N88-10031 scheduling in air traffic control p 22 N88-10815 AERONAUTICAL SATELLITES p 36 A88-13080 An overview of space and aircraft navigation AIR TRANSPORTATION Measurements in the functional mock up test of the p 40 A88-13086 Hydrogen in air transportation - Feasibility study for NAL QSTOL aircraft control system Zurich Airport, Switzerland p41 A68-11146 A hybrid navigation system with GPS [NAL-TR-928] p 36 N86-10793 p 21 A88-13087 Issues in air transport and airport management A survey of aircraft integrated control technology AEROSPACE ENGINEERING [PB87-2045091 p 19 N88-10782 [AR-004-561] p 37 N88-10794 Investigations in the history and theory of development AIRBORNE EQUIPMENT A preliminary investigation into the feasibility of of aerospace science and technology. Number 5 .-- Testing of aircraft electrical equipment --- Russian implementinga direct sideforce control system on the Astra Russian book p 82 A88-12202 book p 39 A88-10044 Hawk by means of an active control surface _-- aircraft AEROSPACE ENVIRONMENTS Fast stable solution of a dispersion equation of linear control High temperature metal matrix composites for future filtering -_-for flight vehicle radar system [ETN-87-909241 p 37 N88-10795 aerospace systems p 21 A88-10728 The application of emulation techniques in the analysis [ NASA-TM-1002121 p 43 N88-10938 HTTB .The ultimate test bed p 23 A88-10875 of highly reliable, guidance and control computer AEROSPACE INDUSTRY Airborne reconnaissance pod flight test systems p 37 N88-10798 Aerospace research at the National Aerospace p 27 A88-12741 Knowledge Based Concepts and Artificial Intelligence: Laboratory (NLR) Sensor configuration for a short to medium range Applications to Guidance and Control [ETN-87-90821I p 62 N88-10697 reconnaissance pod p 27 A88-12742 [AGARD-LS-1551 p38 N88-10806 AEROSPACE PLANES Arguments for electro-optical reconnaissance SYStemS Overview of AGAR0 Lecture Series No. 155: An Orient Express to capture the market p 27 A88-12749 Knowledge-based concepts and artificial intelligence p 1 A88-10370 Test of IR arrays on the Kuiper Airborne Observatory applications to guidance and control p 38 N88-10807 The scramjet. Toward Mach 4-25 flight p 49 A88-12838 AI expert system technology issues for guidance and p 33 A88-13095 AIRBORNE SURVEILLANCE RADAR control applications p 38 N88-10808 AEROSPACE SCIENCES Expert system Control tor anborne radar Surveillance Application of knowledgabased techniques to aircraft Investigations in the history and theory of development [AIM PAPER 67-28541 p 26 A88-12574 trajectory generation and control p 38 N88-10811 01 aerospace science and technology. Number 5 --- AIRBORNEISPACEBORNECOMPUTERS Towards the unmanned cockpit p 25 N88-10812 Russian book p 62 A88-12202 Comparison of programmable legend keyboard and Approach trajectory planning system for maximum AEROSPACE SYSTEMS dedicated keyboard for control of the flight management concealment Force commutated direct frequency changers for computer [NASA-TM-882581 p 60 N88-11435 aerospace power applications p 48 A88-11825 [SA€ PAPER 8617721 p57 A88-10160 AIRCRAFT DESIGN AEROTHERMODYNAMICS AlAA Computers in Aerospace Conference, 6th, Robotic air vehicle ~ A pilot's perspective The aerothermodynamic environment for holes in Wakefield. MA, Oct. 7-9. 1987, Technical Papers p 19 A88-10437 hypersonic configurations p58 A88-12526 New Soviet commercial airliners p 23 A88-10655 [DE87-014651] p 17 N88-10767 Evaluationof a dual processor implementationfor a fault The will to European unity as exemplified by A320 AFTERBODIES inferring nonlinear detectin system p 23 A88-10659 Comparison of wind tunnel and flight test afterbody and [AIAA PAPER 87-27621 p 59 A88-12532 Low altitudelairspeed unmanned research aircraft nozzle pressures for a twin-jet fighter aircraft at transonic Intelligent interfaces to aircraft systems (LAURA) preliminary development p 12 A88-11205 Selection of aerofoil sections for in man-powered speeds [AIM PAPER 87-27761 p 59 A88-12539 use [NASA-TP-2588] p 17 NEB-10765 Implementation of a research prototype onboard fault aircraft 012 A88-11207 Effect of empennage arrangement on single-engine monitoring and diagnosis system Investigations in the history and theory of development nonlelafterbody static pressures at transonic speeds [AIAA PAPER 87-27771 p59 A88-12540 of aerospace science and technology. Number 5 ._- [NASA-TP-2753] p 17 N88-10771 Avionics, artificial intelligence, and embedded Russian book p 62 A88-12202 AIR processing systems Wing design with a three-dimensionaltransonic inverse Fuel-injectorlair-swirlcharacterization [AIM PAPER 67.28181 p 59 A88-12558 method p 14 A88-13077 p 54 N88-11150 AIRCRAFT An aerodynamic design study of transonic transport Dilution jet mixing program. phase 3 Steering mechanism --_ vehicles wings p 15 A88-13078 p 54 N88-111 53 [EP-PATENT-0-181-700-A11 p 51 NEB-10338 High-lift-device design and low-speed wind-tunnel test AIR BREATHING ENGINES AIRCRAFT ACCIDENT INVESTIGATION p 15 A88-13079 An Orient Expcess to capture the market Aircraft accident reports. brief format, US civil and foreign Advanced composite honzontal stabilizer for p 1 A88-10370 aviation. Issue number 1: 1986 accidents next-generation commercial aircraft p 24 A88-13081 AIR CARGO [PB87-916903] p 19 N88-10781 Design and fabrication trial of a composite flap Aircraft accident reports, btief format, US civil and foreign AIRCRAFT ACCIDENTS structure p 1 A88-13082 aviation. Issue number 1: 1986 accidents Aircraft accidents Some topics on aircraft landing gear design [PB87-916903] p 19 N88-10781 [JB-&i] p 19 N88-10020 p 24 A88-13085 AIR FLOW Full-scale transport controlled impact demonstration International Conference on the Aerodynamics at Low Effect of rib angle on locel heatlmass transfer program Reynolds Numbers between lO(4) and lO(8) distribution in a *pass ribroughened channel [ NASA-TM-8W21 p 19 N88-10021 [ONRL-7-023-Cl p16 N88-10010 [ASME PAPER 87-GT-941 p 45 A88-11033 AIRCRAFT COMPARTMENTS Design principles and practices for implementation of Boundary layer profile investigations downstream of an Aircraft acoustics II - Cabin noise in passenger aircraft MIL-STD-1760 in aircraft and stores aerc-engine intake anti-icing air exhaust slot --- Russian book p61 A88-10048 [ AD-A1837241 p 24 N88-10027 [ASME PAPER 87-GT-2371 p32 AM-11127 Prediction of sound fields in cavities using Problem and solution formulations for the generation Boundary layer profile investigations downstream of an bcundary-element methods p61 AM-12281 of 30 block-structured grids .--aircraft design aero-engine intake anti-icing air exhaust slot Test results and predictions for the response of [NLR-MP-86020-U] p25 N88-10028 [PNR90378] p 52 N88-11080 near-ceiling sprinkler links in a full-scale compartment Aerospace research at the National Aerospace AIR NAVIGATION fire Laboratory (NLR) Optimal information processing for sensors and sensor [NBSIR-87-3633] p 50 N88-10209 [ETN-87-908211 p 62 NEB-10697 systems - The case of radar sensors p 26 A88-10685 AIRCRAFT CONFIGURATIONS Ensuring the service life of designs (experience in aircraft construction) p 1 N88-10986 Autonomous onboard collision avoidance for aircraft and The will to European unity as exemplified by A320 ships p21 A88-10687 p23 A88-10659 AIRCRAFT DETECTION lntergration effects of D-shaped, umlerwing, Towards the design of an intelligent aerospace system Civil aviation application of the Global PositioningSystem [AlAA PAPER 87-28441 p 26 A88-12569 (GPS) and its issues p22 A88-13088 aft-mounted, separate-flow. Row-through nacelles on a high-wing transport Autonomous processing using a blackboard chipset AIR TRAFFIC [NASA-TM-40181 p18 N88-10773 [AIAA PAPER 87-28551 p 59 A88-12575 Develcpment studies of a European data network for AIRCRAFT CONSTRUCTIONMATERIALS AIRCRAFT ENGINES acquisition, processing, and display of air-trafficdata The fourth generation of TL commercial aircraft Flight characteristics of aircraft with gas-turbine engines p21 A88-10688 p 23 A88-10656 _-- Russian book p23 A88-10049 The conflit resolution process for TCAS II and some Composite materials in rotorcraft p 24 A88-12412 Evolutionand application of CFD techniques for scramjet simulation results p 21 A88-12474 Composites technolog, in Army aviation engine analysis p 28 A88-10358 Perspective traffic display format and airline pilot traffic p24 A88-12413 Analytical study of swider effects in annular propulsive avoidance p 58 A88-12639 Mechanical property requirements for aero gas turbine nozzles p 28 A88-10362 AIR TRAFFIC CONTROL materials p 42 Am-12628 Multimodes to Mach 5 p28 A88-10371 BMFT-suppxted probts in the fields position-finding, Developments in disc materials -.-lor gas turbine Starting system for cold weather p 23 AM-10871 navigation. and traffi safety p20 A88-10677 engines p 42 A88-12632 Investigation of integrated selection of optimum engine An overview of space and aircraft navigation High-temperature sheet materials for gas turbine cycle parameters p 40 A88-13086 applications p 42 A88-12635 [ASME PAPER 87-GT-391 p 29 A88-10993

A-2 SUBJECT INDEX AIRFOILS

Time-averaged heat-flux distnbutions and companson AIRCRAFT MAINTENANCE The influence of load cycle reconstitution on fatigue wth prediction for the Teledyne 702 HP turbine stage Compressor turbine vane ring (PT6 engine) repair behaviour [ASME PAPER 87-GT-1201 p 30 A88-11048 development [ARL-STRUC-R-4241 p 56 N88-11198 Introduction and application of the General Electric [ASME PAPER 87-GT-471 p 29 A88-10999 AIRCRAFT TIRES turbine engine monitonng software wthin KLM Royal Dutch Introduction and application of the General Electric Aircraft lyres p 23 A88-10873 Airlines turbine engine monitoringsoftware within KLM Royal Dutch AIRCRAFT WAKES [ASME PAPER 87-GT-1671 p 30 A88-11078 Airlines Dispersion in the wake of aircraft: An investigation of Applied reliabilitylmaintainability methodology as a [ASME PAPER 87-GT-1671 p 30 A88-11078 the effects of a ground plane on trailing vortices. Literature function within life cycle cost --- of aircraft turbine engine Scheduled maintenance program helps Delta maintain SUNey [ASME PAPER 87-GT-1721 p 46 A88-11082 quality pl A88-11672 [ IC-AERO-REP-86-04] p 16 N88-10014 AIRCRAFT MANEUVERS AIRFOIL OSCILLATIONS The aeromechanics1response of an advanced transonic Global positioning satellite-based automatic landing A natural low frequency oscillation in the wake of an compressor to inlet distortion system and wind estimated feedback for the AH44 [ASME PAPER 87-GT-1891 p 31 A88-11094 airfoil near stalling conditions helicopter p 22 N88-10764 [NASA-TM-10021 3 I p 18 N88-10779 The United Kingdom engine technology demonstrator AIRCRAFT MODELS AIRFOIL PROFILES programme The use of wind tunnel data in the design of radio Selection of aerofoil sections for use in man-powered [ASME PAPER 87-GT-2031 p 31 A88-11107 controlled contest model sailplanes p 24 A88-11195 aircraft p 12 A88-11207 Effect of fluid inertia on the performance of squeeze The performance of model aircraft using flow Smokawire and thin-film-gauge observations of laminar film damper supported rotors invigorators, gliding in the critical range of Reynolds separation bubbles on an NACA 23012-64 airfoil section [ASME PAPER 87-GT-2201 p48 A88-11117 number p 12 A88-11206 p 13 A88-11210 An improved Stirling engine for model aircraft An improved Stirling engine for model aircraft AIRFOILS propulsion p 33 A88-11976 propulsion p 33 A88-11976 Syntheses of reduced-order controllers for active flutter Current design status and design trend of fuel injectors AIRCRAFT NOISE suppression p 35 A88-10095

for jet engines p 33 A88-13076 Aircraft acoustics I ~ Exterior noise of subsonic Calculation of three-dimensional viscous flows in Noise emission of civil and military aero-engines. passenger aircraft and helicopters -_.Russian book turbomachinery with an implicit relaxation method Sources of generation and measures for attenuation p 61 A88-10047 p2 A88-10357 [ETN-87-91021] p 62 N88-10595 Aircraft acoustics I1 .Cabin noise in passenger aircraft Multigrid localization and multigrid gnd generation for Russian book p 61 A88-10048 Turbines with counterrotating runners for aircraft power -.- the computation of vortex structures and dynamics of flows plants p 34 N88-10992 Noise 01 a model high speed counterrotation propeller in cavities and about airfoils p3 A88-10562 at simulated takeofflapproach conditions (F7/A7) Use of a liquid-crystal and heater-element composite Diagnosis of flow channel in aircraft gas-turbine engines [ NASA-TM-1002061 p 61 N88-10592 for quantitative, high-resolution heat-transfer coefficients basis of vibration spectrum characteristics on Noise levels from propeller-driven aircraft measured at p 35 N88-10993 on a turbine airfoil including turbulence and ground level and at 1.2 m above the ground surface-roughnesseffects p 44 A88-10969 Transmission efficiency in advanced aerospace [NPL-AC-1101 p 61 NEB-10594 The design of shock-free compressor cascades powerplant Noise emission of civil and military aero-engines. including viscous boundary layer effects IPNR903911 p 53 N88-11133 Sources of generation and measures for attenuation [ASME PAPER 87-GT-711 p4 A88-11015 The use of Kevlar on aero-engine Ian containment [ETN-87-91021I p 62 N88-10595 A trace gas technique to study mixing in a turbine casings AIRCRAFT PARTS stage [ PNR904101 p53 N88-11134 New Soviet helicopter technology and its potential for [ASME PAPER 87-GT-1181 p 5 A88-11046 Development of heat flux sensors lor turbine airloils industrial use p 1 A88-10657 Application of the transient test technique to measure p 54 N88-11143 AIRCRAFT PERFORMANCE local heat transfer cmfficients associated with augmented AIRCRAFT EQUIPMENT Improvements in aircraft safety and operational airfoil cooling passages Aircraft and equipment factors in the occurrence of dependability from a projected flight path guidance [ASME PAPER 87-GT-2121 p 47 A88-11112 suspension line twists with U.S. Army parachutes display A study of the effects of thermal barrier coating surface p 19 A88-12644 [SAE PAPER 8617321 p 35 A88-10163 roughness on the boundary layer characteristics of AIRCRAFT FUELS 6-1B combines brisk low-altitude handling, more capable gas-turbine aerofoils Combustion gas properties. 111 - Prediction of the avionics p 23 A88-10675 [ASME PAPER 87-GT-2231 p 48 A88-11120 thermodynamic properties of combustion gases of aviation The performance of model aircraft using flow On massive laminar separation and lift anomalies in and diesel fuels invigorators, gliding in the critical range of Reynolds subcritical Re-range p8 A88-11178 [ASME PAPER 87-GT-491 p 40 A88-11001 number p 12 A88-11206 A simple method for the prediction of separation bubble Current gas turbine combustion and fuels research and AIRCRAFT PILOTS formation on aerofoils at low Reynolds number development Application of knowledge-based techniques lo aircraft p8 A88-11179 [ASME PAPER 87-GT-1071 p 30 A88-11039 trajectory generation and control p 38 N88-10811 A smoke-wre study of low Reynolds number flow over Prediction of combustion performance of aviation AIRCRAFT POWER SUPPLIES a NASA LRN(1) - 1007 airfoil section p 9 A88-11181 kerosines using a novel premixed flame technique The development of 270 Vdc solid state power Low Reynolds number airfoil design at the Douglas [ASME PAPER 87-GT-1251 p 41 A88-11052 controllers .--for advanced aircraft electrical systems. Aircraft Company p9 A88-11183 AIRCRAFT GUIDANCE p 33 A88-11923 Transition and separation control on a low-Reynolds Improvements in aircraft safety and operational AIRCRAFT PRODUCTION number airfoil p9 A88-11186 dependability from a projected flight path guidance Building on a successful tradition - Composites at On some unsteady aerodynamics characteristics of an display MDHC p 41 A88-12415 NACA 0012 at Reynolds numbers of 125,M)o and [SAE PAPER 8617321 p 35 A88-10163 AIRCRAFT RELIABILITY 400,000 p 10 A88-11189 Flight director guidance for MLS p 21 A88-10874 Implementation of a research prototype onboard fault Recent developments in the calculation of flow over low The application of emulation techniques in the analysis monitoring and diagnosis system Reynolds-number airfoils p 10 A88-11191 of highly reliable. guidance and control computer [AlAA PAPER 87-27771 p 59 A88-12540 On the determination of the 2-D characteristics of systems p 37 NEE-10798 Ensuring the sewice life 01 designs (experiencein aircraft aerofoils at low Reynolds numbers p 10 A88-11192 Knowledge Based Concepts and Artificial Intelligence: construction) p 1 N88-10986 Recent wind tunnel experiments at low Reynolds Applications to Guidance and Control Reliability of finite element methods in North America numbers p 11 A88-11193 [AGARD-LS-1551 p38 N88-10806 [AGARD-R-748] p53 N88-11139 Low-Reynolds number aerodynamics research at NASA Overview of AGARD Lecture Series No. 155: AIRCRAFT SAFETY Langley Research Center pll A88-11194 Knowledge-based concepts and artificial intelligence Improvements in aircraft safety and operational Prediction of a microlight biplane's aerofoil performance applications to guidance and control p 38 N88-10807 dependability from a projected flight path guidance using a computer model p 11 A88-11198 AIRCRAFT HAZARDS display The effect of grit roughness on the performance of the Test results and predictions for the response of [SAE PAPER 8617321 p 35 A88-10163 Wortmann FX63-137 airfoil at a chord Reynolds number near-ceiling sprinkler links in a full-scale compartment BMFT-supported projects in the fields position-finding. of 100.OoO p 11 A88-11202 fire navigation. and traffic safety p 20 A88-10677 Wind-tunnel test results of Eppler 387 aerofoils and [ NBSIR-67-36331 p 50 N88-10209 Fluids for deicing aircraft surfaces p 40 A88-10872 comparisons with flight test and computation AIRCRAFT INSTRUMENTS Aircraft tyres p 23 A88-10873 p 12 A88-11208 FDAD - A lablfield test tool _-_Flight Data Analysis and Some approaches to the design of high integrity Two-dimensional transonic aerodynamic design Display p 25 A88-10436 software p 37 N88-10799 method p 14 A88-12284 Autonomous onboard collision avoidance for aircraft and Reliability of finite element methods in North America Global marching technique for predicting separated ships p 21 A88-10687 [AGARD-R-7481 p 53 N88-11139 flows over arbitrary airfoils p 14 A88-12293 Anti-tank helicopters for the rich and not so rich AIRCRAFT SPECIFICATIONS Wing design with a three-dimensional transonic inverse p 1 A88-10877 The Antonov An-74 brings high tech to low method p 14 A88-13077 Electronic trend monitoring and exceedance recording temperatures p 23 A88-10876 Analyses and assessments of span wise gust gradient systems - A means to improved turbine engine reliability Anti-tank helicopters for the rich and not so rich data from NASA 8-576 aircraft [ASME PAPER 87-GT-871 p 29 AM-1 1027 p 1 A88-10877 [NASA-CR-1782881 p 15 NEB-10007 Intellint interfaces to airman systems AIRCRAFT STABILITY The structure of separated flow regions occurring near [AIAA PAPER 87-27761 p 59 A88-12539 Decoupling and stabilization of speed and height in F4 the leading edge of airfoils including transition Optical systems for gas turbine engines Phantom aircraft using output feedback [ NASA-CR-1814341 p16 N88-10011 p49 A88-12657 [ ETN-87-909261 p 25 N88-10787 Wall interference tests of a CAST lOS/DOA 2 airfoil AIRCRAFT LANDING AIRCRAFT STRUCTURES in an adaptive-wall test section Global positioning satellite-based automatic landing Stress intensity factors and residual strength of a [NASA-TM-4015] p 18 N88-10772 system and wind estimated feedback for the AH44 cracked stiffened panel p 50 A88-13083 Development of heat flux sensors for turbine airfoils helicopter p 22 N88-10784 Structure simplificatiin around a cutout - Applicatiin of p $4 N88-11143 A rule-based system lor arrival sequencing and a simplified damage tolerance design chart Coolant passage heat transfer with rotation scheduling in air traffic control p 22 N88-10815 D 50 A88-13084 P 54 N88-11160

A-3 AIRFRAME MATERIALS SUBJECT INDEX

Thermal barrier coating life prediction model APPROACHCONTROL AUTONOMOUS NAVlQATlON development p56 N88-11183 Fliht director guidance for MLS p 21 AM-10874 Autonomous onboard collision avoidance for aircraft and Thermal banier coating life prediction model Approach trajectory planning system for maximum ships p21 A88-10887 development p56 N88-11185 concealment AUTONOMY AIRFRAME MATERIALS [ NASA-TM-882581 p60 N88-11435 Autonomws processing using a blackboard chipsel Composite structural materials ARCHITECTURE (COMPUTERS) [AIM PAPER 87-28551 p 59 AM-12575 [NASA-CR-1814161 p56 N88-11186 Optimal information processing for sensors and sensor AVIONICS AIRFRAMES systems - The case of radar sensors p 26 A88-10685 Tasting of aircraft electrical equipment --- Russian The United Kingdom engine technology demonstrator book p39 A88-10044 AOSP ~ Multiprocessor architecture and system 8-1B combines brisk low-altitudehandling, more capable programme considerations [ASME PAPER 87-GT-2031 p31 Am-11107 [AIAA PAPER 8727901 p 59 A88-12544 avionics p 23 A88-10675 Observations and analyses of natural laminar flow over BMFT-supported projects in the fields position-finding. Digital system integrity a nonlifting airframe surface bus navigation, and traffic safety p20 AM-10677 [ NASA-CR-1814461 p 28 N88-10030 [SAE PAPER 8710201 p 15 A88-13096 The impact of modern technology on aircraft avionics The history of aeroelasti research in Germany from An expert system for aircraft conflict resolution in dense equipment p26 A88-10679 the beginning until 1945 - airframes airspaces p22 N88-10810 Development and trends in radio position finding [DFVLR-MIlT-86-25] p1 N88-10003 ARMED FORCES (UNITED STATES) p20 A88-10880 AIRLINE OPERATIONS Cost savings possible with Air Force MHlYerSiOn to JP-8 Evalualionof a dual processor implementationfor a fault

Airline requirements on a fly-by-wire aircraft ~ A pilot's fs its primary fuel inferring nonlinear detection system view [ ADA1837841 p42 N88-10192 [AIM PAPER 87-27621 p 59 A88-12532 [SAE PAPER 8618041 p38 A88-10167 ARRAYS Avionics, artifidal intelligence. and embedded Scheduled maintenance program helps Delta maintain Heat transfer to arrays of impinging jets in a crossRow prdngsystems quality p1 A88-I1672 [ASME PAPER 87-GT-1981 p47 A88-11102 [AIM PAPER 87-28181 p59 A88-12558 Issues in air transport and airport management Test of IR arrays on the Kuiper Airbome Observatory Self-adjusting fliht electronics (SAFE) [PB87-204509] p 19 N88-10782 p 49 A88-12838 p49 A88-12697 AIRPORT PLANNING ARTIFICIAL INTELLIGENCE A hybrid navigation system with GPS Issues in air transport and airport management Initial user experience with an artificial intelligence p21 A88-13087 [ PB87-2045091 p 19 N88-10782 program for the preliminary design of centrifugal GPS receivers for air navigation p 22 A8E13093 AIRPORTS compressors Flight test results for a GPS receiver in a helicopter Hydrogen in air transpwtation - Feasibility study for [ASME PAPER 87-GT-217] p58 A88-11115 and a business aircraft p22 A88-13094 Zurich Airport, Switzerland p 41 A68-11146 Digital system bus integrity Avionics. arUfkial intelligence, and embedded N8 8-10030 [NASA-CR-181448] p26 N88-10030 First articletest mise survey of the AIF32T-9 large turbo processing systems fan engine enclosed noise suppressor system, Sky Harbor [AIM PAPER 87-28181 p59 A88-12558 AI expert system technology i85ue8 for guidance and IAP (International Airport), Phoenix, Mona control applications p38 N88-10808 Towards the of an intelliint aerospace system [ADA1837991 p61 NEE-10588 design AXIAL FLOW [AIM PAPER 87-28443 p26 AM-12569 AIRSPEED A trace gas technique to study mixing in a turbine system for airborne radar New Soviet commercial airliners p 23 A88-10655 Expert control surveillance StaW Airspeed measurement with a 02li [AIAA PAPER 87-28541 p26 A8812574 [ASME PAPER 87-GT-1181 p5 MU)-11048 p 26 A88-12655 Autonomous processing using a Mackboardchipset AXISYMMETRK: FLOW An obmer Woach to the estimation of helicopter [AIM PAPER 87-28551 p 59 A88-12575 Transonic expansions p 13 A88-12059 airspeed Application of knawledgebased techniques to aircraft Effect of emaennaae amanoement on sinale-enaine [ DFVLR-FB-87-13] p25 N88-10029 trajectory generation and control p 38 N88-10811 nonle/anerbody stak presS;res at transo-nic &s Decoupling and stabilization of speed and height in F4 ASPECT RATIO [NASA-TP-2753] p 17 N88-10771 Phantom aircraft using output feedback Arbitrary wings of low aspect ratio in subsonic flow [ ETN-87-909261 p 25 N88-10787 p 3 A88-10680 ALLOYS Effects of channel aspect ratio on heat transfer in B Creep fatigue life prediction for engine hot section rectangular passage sharp 18Odeg turns materials (isotropic): Third year progress review [ASME PAPER 87-GT-1131 p46 A88-11041 81AIRCRAFT B-1B combines brisk low-altitude handling, mare p55 N88-11173 InvesQations of separated Row states on wings of capable avionics p23 AM-10675 Life prediction and constitutive models for engine hot medium aspect ratio taking into accwnt the wind tunnel 857 AIRCRAFT section anisotrooic materials .Iwooram interference problem p56 N88-11175 [ETN-87-90437] p17 N88-10016 Analyses and assessments of span wise gust gradient ALTITUDE TESTS ASYMPTOTES data fmm NASA 8-578 aircraft [NASA-CR-178288] p15 N88-10007 Altitude tests of the XF3-30 turbofan Exact and asymptotic expressions of the lift slope [ASME PAPER 87-GT-251 p28 A88-10987 coefficient of an elliptic wing p 14 A88-12292 BEARINQS ANALOG TO DIGITAL CONVERTERS ATMOSPHERIC BOUNDARY LAYER Effect of fluid imntia an the performance of squeeze Measurements in the functional mock up test of the Atmospheric turbulence and gust on the performance film damper supported rotors NAL QSTOL aircraft control system of a Wortmann FX 63-137 wing p9 A88-11185 [ASME PAPER 87-GT-2201 p48 A88-11117 [NAL-TR-928] p 36 N88-10793 ATMOSPHERIC EFFECTS BIPUNES ANGLE OF ATTACK Analysis of free molecular on the altitude of Prediin of a microlight biplane's aerofoil performance effects using a computer model pll A88-11198 Experimentalstudy of three-dimensional separated flow satellites in geostationary transfer Part 2 Force and orbit. BLADE surrounding a hemispherecylinder at incidence torque maasurement in free molecular wind tunnel tests TIPS [AIM PAPER 87-24921 p 3 A88-10498 [ DFVLR-IB-222-88-A471 p 40 N88-10078 A trade-off study of rotor tip clearance flow In a Experimental investigations of flows through a plane ATMOSPHERIC OPTICS turbinelexhaust difhraer system [ASME PAPER 87-GT-2291 p32 A88-11123 cascade at large angles of attack with separations Imaging through the atmosphere for airborne Modeling and measurement of heat transfer on turbine [ASME PAPER 87-GT-961 p 5 A88-11035 reconnaissance p27 A88-12748 Calarlationof aerodynamic heat transfer for blunt-nosed ATMOSPHERIC SOUNDING blade tips p33 N88-10032 thin wings at different angles of attack at supersonic Computing complex for a system for rad-acoustic BLOWINQ the Strong gas injection into supersonic Row with turbulent @S sounding of the atmosphere. Hardware facilities mixing p13 A8812058 [NASA-TT-20127] p 18 N88-10778 p58 A88-11394 ANISOTROPY ATMOSPHERIC TURBULENCE BLUFF BODIES Experiments spray intmctions in wake of a bluff Life prediction and constitutive models for engine hot Atmospheric turbulence and gust on the perfmnce an the section anisotropic materials program of a Wortmann FX 63-137 wing p9 A8811185 bo61 [ASME PAPER 87-GT-481 p44 A88-11000 p56 N88-11175 AUDIOLOGY ANNULAR NOOZZLES Activitk repat of the Instilute of Sound and Vibration BLUNT BODIES Calculation of aerodynamic heat transfer for blunt-nosed Analybcal study of swirler effects in annular propulsive Research thin wings at different angles of attack at nozzles p28 A88-10362 [ETN-87-90685] p61 N88-10589 supersonic ANTONOV AIRCRAFT AUTOMATIC CONTROL speeds [ NASA-lT-201271 p 18 N88-10776 The Antonov An-74 brings huh tech to low Test results and predictions for response of the 80-105 HELICOPTER temperatures p23 A88-10876 near-ceiling sprinkler links in a full-scale compartment Test equipment with fiber optic data and laser gyro APPLICATIONS PROGRAMS (COMPUTERS) fire bus strapdown system LTN-90 for the helicopter 80-105 Use of a liquidcrystal and heater-element composite [NBSIR-87-3633] p50 N88-10209 for quantitative, high-resolution heat-transfer coefficients AUTOMATIC FLIGHT CONTROL [ESA-lT-1038] p 22 N88-10025 an a turbine airfoil including turbulence and Assessment of software quality for the AIRBUS A310 BOUNDARY ELEMENT METHOD surface-rwghness effects p 44 A88-10969 automatic pilot p 38 N88-10804 prediction of mnd fields in caviUea using Application of advanced computational codes in the AUTOMATIC PILOTS boundary-element methods p61 A88-12281 design of an experiment for a supersonic throughflow fan Assessment of software quality far the AIRBUS A310 BOUNDARY LAYER EWATlONS rotor automatic pilot p38 N88-10804 Wscid/invisdd interaction analysis of subsonic tutbulenl [ASME PAPER 87GT-1601 p6 A88-11072 Towards the unmanned wckpii p 25 N88-10812 trailing-edge Rorm p 14 A88-12282 Integration of dynamic. aerodynamic and structural AUTOMATIC TEST EWIPMENT BWNDARY LAYER FLOW optimization of helicopter rotor blades Implementation of a research prototype onboard fault Three-dimensional calculation of wall boundary layer [NASA-CR-181441] p16 N88-10012 monitoring and diagrosis system flows in turbomachines APPROACH [AIM PAPER 87-27771 p59 A88-12540 [ASME PAPER 87-GT-821 p4 A88-11022 Noise of a model hgh speed wuntenotation propeller AUTOMOBILES Characterizationof shock wave end wall boundary layer at simulated takeoff/approach condiins (F7/A7) Steering mechanism _-vehicles interactions in a transonic compressor rotor [NASA-TM-100206] p81 N88-10592 [EP-PATENT4-181-700-Al] p51 N88-10338 [ASME PAPER 87-GT-1663 p8 A88-11077

A-4 SUBJECT INDEX COMBUSTION CHAMBERS

Boundary layer and periormance characteristics from CARBON FIBERS Thermal banier coating life prediction model wind tunnel tests of a low Reynolds number Liebeck Composite structural materials development p 56 N88-11185 airfoil p9 A88-11184 [ NASA-CR-1814161 p56 N88-11186 CERAMICS Measurement techniques in low-speed turbulent flows: CARBON MONOXIDE Development of ceramic hot section components for A report on EUROMECH 202 Prediction of NO and CO distribution in gas turbine AGT 100 gas turbine [NLR-MPW38-U] p51 N88-10283 combustors [ASME PAPER 87-GT-791 p 45 A88-11019 Boundary layer profile investigations downstream of an [ASME PAPER 87-GT-631 p41 Am-11010 AGTlOl - Ceramic gas turbine development aero-engine intake anti-icing air exhaust slot CASCADE FLOW [ASME PAPER 87-GT-2281 p 32 A851 1122 [PNR90378] p 52 N88-11080 Cascade viscous flow analysis using the Navier-Stokes CHANNEL FLOW equations p 2 A88-10356 BOUNDARY LAYER SEPARATION Effect of rib angle on local heat/mass transfer Calculation of three-dimensional viscous flows in A smokewire study of low Reynolds number flow over distribution in a two-pass rib-roughened channel turbomachinery with an implicit relaxation method a NASA LRN(1) ~ 1007 airfoil section p 9 A88-1 1181 [ASME PAPER 87-GT-941 p45 AM-11033 p2 A88-10357 An analysis of unsteady, two-dimensional separation Numerical solution of stream function equations in Effects of channel aspect ratio on heat transfer in bubbles p9 AM-11182 transonic flows rectangular passage sharp 1BO-deg turns Transition and separation control on a low-Reynolds [ASME PAPER 87-GT-1131 p 46 A88-11041 [ASME PAPER 87-GT-181 p 3 A88-10983 number airfoil p9 ABS11186 A generalized numerical method for solving direct A method for calculating turbulent boundary layers and Recent developments in boundary layer computation inverse and hyhd problems of blade cascade flow by losses in the flow channels of turbomachines p10 A88-11188 using streamti- hate equation [ASME PAPER 87-GT-2251 p7 A88-11121 Smokewire and thin-filmgauge observations of laminar [ASME PAPER 87-GT-291 p4 A88-10990 Stability of supersonic flow of an ideal gas with a head separation bubbles on an NACA 2301284 airfoil section A new method of calculating optimum velocity shock wave past cylindrical channels and cavities p 13 A88-11210 distribution along the blade surface on arbitrary stream p 13 A88-12065 BWNDARY UYER STABILITY surface of revolution turbomachines CMANNELS (DATA TRANSMISSION) Expwimx the application and valuation of in about [ASME PAPER 87-GT-301 p4 A88-10991 Test equipment with fiber optic data bus and laser gyro roughness strips for boundary layer transition control in Navier-Stokes solution for steady two-dimensional strapdown system LTN-90 for the heliccpter 60-105 wind tunnel tests in the high-speed range [ ESA-lT-10381 p22 N88-10025 [ESA-TT-1028] p 51 N88-10278 transonic cascade flows [ASME PAPER 87-GT-541 p4 A88-11005 BOUNDARY UYER TRANSITION CHARGE COUPLED DEVICES The dmgn of shock-free compressor cascades Low-Reynoldsnumber aerodynamics research at NASA Self-adjusting flight electronics (SAFE) including boundary layer effects Langley Research Center pll A88-11194 viscws p49 A88-12697 [ASME PAPER 87-GT-711 p4 AW-11015 The smture of separated flow regions occurring near CIVIL AVIATION Experimental investigations of flows through a plane the leadw edge of airfoils including transition The United Kingdom engine technology demonstrator cascade at large angles of attack with separations [ NASA-CR-1814341 p16 N88-10011 programme [ASME PAPER 87-GT-961 p 5 AM-11035 BWNDARYUYERS [ASME PAPER 87-GT-2031 p31 A88-11107 Numerical computation of non-isentropic potential The Raw visualiiation the rotary with low aspect civil aviation application of the Global PositioningSystem on wing equations for transonic cascade flows ratio p 2 A88-10094 (GPS) and its issues p22 A88-13088 [ASME PAPER 87-GT-1591 p5 A88-11071 The Wnof shock-free compressor cascades A muiti-grid algorithm for 2-0 transonic potential cascade Aircraff accident reports, brief format, US civil and foreign including viscous boundary layer effects flow aviation. Issue number 1: 1986 accidents [ASME PAPER 87-GT-711 p4 A88-11015 [ASME PAPER 87-GT-1801 p6 A88-11088 [P687-9169031 p 19 N88-10781 The base oressure and loss of a familv of four turbine Film cooling of a turbine blade with injection through CLOUD GUClATlON blades rows of holes in the near-endwall region The dependence of the normalized ice accretion [ASME PAPER 87-GT-2021 p7 A88-11106 two [ASME PAPER 87-GT-1961 p47 A88-11100 thickness on cloud-physical parameters Bounderv laver wofile investhations downstream of an The turbomachine blading design achieved by solving [ DNLR-F6-8708] p57 N88-10464 aero-engik intake anti-icing airexhaust slot CLOUD PHYSICS [ASME PAPER 87-GT-2371 p32 A88-11127 the inverse feld problem [ASME PAPER 87-GT-2151 p31 A88-11113 The dependence of the normalized ice accretion Observations and analyses of natural laminar flaw over A study of the effects of thennal barrier coating surface thickness on cloud-physical parameters a nonling airhame surface roughness on the boundary layer characteristics 01 [DNLR-F6-87-08] p57 N88-10464 [SAE PAPER 8710201 p 15 A88-13096 gas-turbine aerofoils CLUllER BOUNDARYVALUEPROBLEMS [ASME PAPER 87-GT-2231 p48 A88-11120 Detection of targets in the presence of clutter using Problems in continuum mechanics with mixed boundary Inter and intra blade row laser velocimetry studies of conditions Russian book p43 A88-10017 target echo modulations caused by rotating structures - gas turbine compressor flows [ REPT-12861 p50 N88-10231 Necessary optimali condiis for threedimensional [ASME PAPER 87-GT-2351 p7 A88-11126 bodies in supersonic gas flow p 2 A88-10300 COBALT Theoretical and experimental analysis of a compressor A simplified method for 3-0 potential flow in The effect of variations of cobalt content on the cyclic cascade at supercritical flow conditions turbomachinery using vortex sheet boundary conditions oxidation resistance of selected Ni-base superalloys [ASME PAPER 87-GT-2561 p8 A88-11136 [ASME PAPER 87-GT-281 p3 ABS10989 p 40 A88-10031 Experimental determination of the oscillatory forces on On massive laminar separation and lianomalies in COBALT ALLOYS subcritical Rerange p8 A88-11178 two turbine blade profiles Compressor turbine vane ring (PT6 engine) repair [ETN-87-90417] p34 N88-10037 BUBBLES development A simple method for the prediion of separation bubble CATMODE RAY TUBES [ASME PAPER 87-GT-471 p29 A88.10999 The advantages of a primary flight diwlay formation on aerofoils at low Reynolds number COCKPITS [SAE PAPER 8617301 p 58 A88-10162 p8 A88-11179 Low cost windowless cockpit research vehicle CATHODIC COATlNOS An analysis of unsteady, Wudimensional separation [SAE PAPER 8617551 p39 A88-10156 buWS p9 A88-11182 Thin-film temperature sensors deposited by radio COLD WEATHER Low Reynolds number airioil design at the Douglas frequency cathodic sputtering p 50 A88-12903 Starting system for cold weather p 23 AM-10871 AirNan Company p9 A88-11183 CAVITATION FLOW COLLISION AVOIDANCE Boundary layer and pertonnance characteristics from Multigrid localization and multigrid grid generation for Autonomous onboard collision avoidancefor aircranand wind tunnel tests of a law Reynolds number Liebeck the computation of vortex structures and dynamics of flows ships p21 AM-10687 airfoil p9 A88-11184 in cavities and about airfoils p3 A88-10562 The conflict resolution process for TCAS II and some Smokewire and thin-filmgauge observations of laminar Comparison of predicted and measured velocities in a simulation results p21 A88-12474 separation bubbles on an NACA 2301284 airfoil section compressor disk drum model Perspective traffic display format and airline pilot traffic p 13 A88-11210 [ASME PAPER 87-GT-2081 p47 A88-11109 avoidance p 56 A88-12639 The sWraof separated flow regions occurring near CAVITIES COLOR TELEVISION the leading edge of airfoils including transition Prediiction of sound fields in cavities using Color display technology ~ An overview [ NASACR-1814341 p16 N88-10011 boundary-element methods p6l A88-12281 [SAE PAPER 8816921 p43 A88-10170 BULKMEADS CEILINQS (ARCHITECTURE) COMBUSTIBLE FLOW Elastic buckling of internally pressurized Test results and predictions for the response of Applicability of a diffusion combustion model to the analysis of supersonic turbulent reacting jets cylinder-bulkhead combinations p 50 A88-12949 neareelling sprinkler links in a full-scale compartment BURNER? fire p 40 A88-10180 Parabolied Navier-Stokes analysis of ducted verificetiar ot vapor deposition rate theory [NBSIR-873833] p 50 N88-10209 supersonic combustion problems p 2 A88-10361 in high veloaty burner rigs p43 N88-11179 CEMENTATION BUS CONDUCTORS Flame driving of longitudinal instabilities in liquid fueled Pack cementation coatings for superalloys ~ A review dump combustors Chgital system bus integrity of history, theory, and practice [NASACR-181446] p28 NM-10030 [ AD-A1835361 p33 N88-10033 [ASME PAPER 87-GT-501 p 41 A88-11002 COMBUSTION BYPASS RATIO CENTRIFUGAL COMPRESSORS The fourth generation of TL aircraft Particle transport across the transpired turbulent commercial Influence of the Reynolds number on the perfwmance pZ3 ABS10656 boundary layer of centrifugal compressors [ASME PAPER 87-GT-2651 p48 A88-11142 [ASME PAPER 87-GT-101 p 44 A88-10979 COMBUSTION CMAMBERS C Initial user experience with an artificial intelligence Numerical solutions of scramjet nozzle flows program for the preliminary design of centrifugal p2 A88-10359 CAMERAS wmpressors Prediction of NO and CO distribution in gas turbine Test of IR mays on Me Kuiper Ailborne Observatory [ASME PAPER 87-GT-2171 p58 A88-11115 combustors p49 A88-12838 CERAMIC COATINGS [ASME PAPER 87-GT-631 p41 AM-11010 CARBON DIOXIDE USERS Applications of ceramic coating on the turbine blades Correlations of fuel performance in a full-scale Airspwd measurement with a CO2 li of the AGTJ-1006 commercial combustor and two model combustors pZ6 A88-12655 [ASME PAPER 87-GT-1801 p41 ABS11095 [ASME PAPER 87-GT-891 p 29 A88-11028

A-5 COMBUSTION CHEMISTRY SUBJECT INDEX

Current gas turbine combustion and fuels research and Impact of turbulence modeling on numerical accuracy Calculation of a three-dimensionalturbomachinery rotor development and efficiency of compressible flow simulations flow with a Navier-Stokescode [ASME PAPER 87-GT-1071 p 30 A88-11039 [ NASA-TM-883331 p 52 N88-I 1088 [ASME PAPER 87-GT-2321 p 7 A88-11125 Spray performance of a hybrid injector under varying COMPRESSOR BLADES Theoretical and experimental analysis of a compressor air density conditions The design of shock-free compressor cascades cascade at supercritical flow conditions [ASME PAPER 87-GT-1551 p46 A88-11068 including viscous boundary layer effects [ASME PAPER 87-GT-2561 p8 A86-11136 Prediction of gas turbine combustor-liner temperature [ASME PAPER 87-GT-711 p4 A88-11015 Recent developments in boundary layer computation [ASME PAPER 87-GT-1771 p 31 A88-11085 A multi-gridalgorithmfor2-D transonic potential cascade p 10 A88-11188 Flame driving of longitudinal instabilities in liquid fueled flow Recent developments in the calculation of flow over low dump combustors [ASME PAPER 87-GT-1801 p6 A88-11088 Reynolds-number airfoils p 10 A88-11191 Preliminary measurements of the flight performance of [AD-A1835361 p 33 N88-10033 A new method (FTDCDF) for blade design of an RPV compared with wind tunnel and CFD estimates Turbine Engine Hot Section Technology, 1985 axiallmixed-flow compressors and its applications p 12 A88-11203 [ NASA-CP-24051 p 53 N88-11140 [ASME PAPER 87-GT-1831 p 31 A88-11090 Fuel-injectorlair-swirlcharacterization Wind-tunnel test results of Eppler 387 aerofoils and Unsteady aerodynamic measurements on a rotating p54 N88-11150 comparisons with flight test and computation compressor blade row at low Mach number p 12 A88-11208 Combustor-diffuserinteraction program [ASME PAPER 87-GT-221I p7 A88-I1118 p 35 N88-11152 Transonic expansions p 13 A88-12059 Dilution jet mixing program. phase 3 Inter and intra blade row laser velocimetry studies of Refined numerical solution of the transonic flow past a p 54 N88-11153 gas turbine cornpressor flows wedge p 14 A88-12280 On the mixing of a row of jets with a confined [ASME PAPER 87-GT-2351 p7 A88-11126 Two-dimensional transonic aerodynamic design crossflow p 54 NEB-111 54 Advanced turboprop wing installation effects measured method p 14 A88-12284 3D inelastic analysis methods for hot Section by unsteady blade pressure and noise Global marching technique for predicting separated components p55 N88-11164 [ NASA-TM-1002001 p 15 N88-10008 flows over arbitrary airfoils p 14 A88-I2293 3-D inelastic analysis methods for hot section COMPRESSOR EFFICIENCY Calculation of aerodynamic heat transfer for blunt-nosed components p 60 N88-11165 Process support compressor motor electromagnetic thin wings at different angles of attack at supersonic COMBUSTION CHEMISTRY design summary speeds [ NASA-TT-201271 p 18 N68-10776 Combustion gas properties. 111 ~ Prediction of the [ DE87-0143591 p 52 N88-11048 thermodynamic properties of combustion gases of aviation COMPRESSOR ROTORS Coolant passage heat transfer with rotation and diesel fuels Unsteady aerodynamic measurements on a rotating p 54 NEB-11160 [ASME PAPER 87-GT-491 p 40 A88-11001 compressor blade row at low Mach number The spatially nonuniform convergence of the numerical COMBUSTION EFFICIENCY [ASME PAPER 67-GT-221I p7 A88-11118 solution of flows Experimental method for the combustion efficiency Theoretical and experimental analysis of a compressor [ NASA-TM-1000371 p 60 N66-11429 calculation in a reheat duct cascade at supercntical flow conditions COMPUTATIONAL GRIDS [ASME PAPER 87-GT-901 D 29 A88-11029 [ASME PAPER 87-GT-2561 p 8 A88-11136 Navier-Stokes simulations of rotorlstator interaction . Prediction of combustion performance of aviation COMPRESSORS using patched and overlaid grids p 2 A88-10354 kerosines using a novel premixed flame technique Stability of conical and curved annular diffusers for Multigrid localization and multigrid grid generation for [ASME PAPER 87-GT-1251 p 41 A88-11052 mixed-flow compressors the computation of vortex structures and dynamics of flows COMBUSTION PHYSICS [ASME PAPER 87-GT-1911 p 6 A86-11096 in cavities and about airfoils p3 A88-10562 Numerical solutions of scramjet nozzle flows Comparison of predicted and measured velocities in a Multigrid solution of the Euler equations on unstructured D2 A88-10359 compressor disk dNm model and adaptive meshes p 44 A88-10570 Current gas turbine combustion and fuels research and [ASME PAPER 87-GT-2081 p 47 A88-11109 A multi-grid algorithm for2-D transonic potential cascade development Process support compressor motor electromagnetic flow [ASME PAPER 87-GT-1071 D 30 A88-11039 design summary [ASME PAPER 87-GT-1801 p 6 A88-11088 . Prediction of gas turbine combustor:liner temperature [DE87-014359] p 52 N88-11048 Numerical solution of coupled problems of supersonic [ASME PAPER 87-GT-1771 p 31 A88-11085 Combustor-diffuser interaction program flow past deformable shells of finite thickness COMBUSTION PRODUCTS p 35 NEB-111 52 p 13 A88-11280 Experimentalverification of vapor deposition rate theory COMPUTATIONAL FLUID DYNAMICS Problem and solution formulations for the generation in high velocity burner rigs p 43 N88-11179 A numerical method for subsonic unsteady lifting of 3D block-structured grids -.-aircraft design COMBUSTION STABILITY surfaces - BIS. 111 - Some additional numerical results [NLR-MP-86020-U] p 25 N88-10028 Flame driving of longitudinal instabilities in liquid fueled p2 A88-10093 COMPUTER AIDED DESIGN dump combustors Calculation of three-dimensional viscous flows in The fourth generation of TL commercial aircraft [ AD-A1835361 p33 N88-10033 turbornachinery with an implicit relaxation method p 23 A88-10656 COMMERCIAL AIRCRAFT p2 A88-10357 A generalized numerical method for solving direct An integrated display for vertical situation awareness Evolution and application of CFD techniques for scramjet inverse and hybrid problems of blade cascade flow by in commercial transport aircraft engine analysis p 28 A88-10358 using streamline-co-ordinateequation [SAE PAPER 8617701 p 57 A88-10158 Numerical solutions of scramjet nozzle flows [ASME PAPER 87-GT-291 p4 A88-10990 New Soviet commercial airliners p 23 A88-10655 p2 A88-10359 Investigation of integrated selection of optimum engine The fourth generation of TL commercial aircraft Parabolized Navier-Stokes analysis of ducted cycle parameters p 23 A66-10656 supersonic combustion problems p 2 A88-10361 [ASME PAPER 87-GT-391 p 29 A88-10993 Scheduled maintenance program helps Delta maintain Three-dimensional flow in a rotor - A strictly Advanced computing for manufacturing quality p 1 A66-11672 three-dimensional calculation of flows in turbomachines p 60 A88-13109 Intelligent interfaces to aircraft systems using the Sl-SZ method p44 A88-10628 Problem and solution formulations for the generation [AIAA PAPER 87-27761 p 59 A88-12539 Influence of the Reynolds number on the performance of 3D block-structured grids --- aircraft design COMMUNICATION EQUIPMENT of centrifugal compressors [ NLR-MP-86020-UI p25 N88-10028 Extended systems of variable structure with mobile [ASME PAPER 87-GT-101 p 44 A88-10979 A preliminary investigation into the feasibility of radio-communicationobjects p 44 A88-10726 Numerical solution of stream function equations in implementinga direct sideforce control system on the Astra COMPONENT RELIABILITY transonic flows Hawk by means of an active control surface --- aircraft Electronic trend monitoring and exceedance recording [ASME PAPER 87-GT-181 p 3 A88-10983 control systems - A means to improved turbine engine reliability A simplified method for 3-D potential flow in [ETN-87-90924] p 37 N88-10795 [ASME PAPER 87-GT-871 p 29 A88-11027 turbomachinery using vortex sheet boundary conditions COMPUTER AIDED MANUFACTURING COMPOSITE MATERIALS [ASME PAPER 87-GT-281 p 3 A88-10989 Advanced computing for manufacturing Composite materials in rotorcraft p 24 A88-12412 Through-flow analysis of a multi-stage compressor p 60 A88-13109 Composites technology in Army aviation operating at near-stall conditions COMPUTER PROGRAM INTEGRITY p 24 A88-12413 [ASME PAPER 87-GT-511 p4 A88-11003 Some approaches to the design of high integrity Composite directions at Kaman p 41 A88-12414 Navier-Stokes solution for steady two-dimensional software p 37 N88-10799 COMPOSITE STRUCTURES transonic cascade flows COMPUTER PROGRAMMING Building on a successful tradition - Composites at [ASME PAPER 87-GT-541 p4 A88-11005 Traditional versus rule-based programming techniques MDHC p 41 A88-12415 Numerical prediction of turbulent flow in rotating - Application to the control of optional flight information Advanced composite horizontal stabilizer for cavities p 58 A88-10965 mxtgeneration commercial aircraft p 24 A88-13081 [ASME PAPER 87-GT-741 p 45 A88-11018 AIAA Computers in Aerospace Conference, 6th. Design and fabrication trial of a composite flap Experimental method for the combustion efficiency Wakefield, MA, Oct. 7-9. 1987. Technical Papers structure p 1 A88-13082 calculation in a reheat duct p 58 A88-12526 COMPRESSED AIR [ASME PAPER 87-GT-901 p 29 A88-11029 Knowledge Based Concepts and Artificial Intelligence: Stability of conical and curved annular diffusers for Numerical computation of non-isentropic potential Applications to Guidance and Control mixed-flow compressors equations for transonic cascade flows [AGARD-LS-1551 p38 N88-10806 [ASME PAPER 87-GT-1911 p6 A88-11096 [ASME PAPER 87-GT-1591 p5 A88-11071 COMPUTER PROGRAMS COMPRESSIBLE FLOW Application of advanced computational des in the Numerical solution of three-dimensional turbulent flows Calculation of three-dimensional viscous flows in design of an experiment for a supersonic throughflow fan for modern gas turbine components turbomachinery with an implicit relaxation method rotor [ASME PAPER 87-GT-841 p4 A88-11024 p2 A88-10357 [ASME PAPER 87-GT-1601 p 6 A88-11072 Initial user experience with an artificial intelligence Numerical solution of three-dimensional turbulent flows A multigrid algorithmfor 2-D transonic potential cascade program for the preliminary design of centrifugal for modern gas turbine components flow compressors [ASME PAPER 87-GT-841 p4 A88-11024 [ASME PAPER 87-GT-1801 p6 A88-11088 [ASME PAPER 87-GT-2171 p 58 A88-11115 Flow investigations on swirling compressible flow A new method (FTDCDF) for blade design of Implementation of a research prototype onboard fault through a vaneless radial diffuser axiallmixed-flowcompressors and its applications monitoring and diagnosis system [ASME PAPER 87-GT-1931 p 7 A88-11097 [ASME PAPER 87-GT-1831 p31 AM-11090 [AIM PAPER 87.27771 p 59 A88-12540

A-6 SUBJECT INDEX DATA MANAGEMENT

Transonic analysis and design of axisymmetric bodies CONTROL STICKS CRACK INITIATION in nonuniform flow Steering mechanism _..vehicles Cyclic spinning testing of aero-engine discs [NASA-CR-4101] p 16 N88-10013 [EP-PATENT-0-181 -700-AI ] p 51 N88-10338 [ASME PAPER 87-GT-2591 p 32 A88-11139 Blade loss transient dynamics analysis, volume 1. Task CONTROL SURFACES CRACK PROPAGATION 2: TETRA 2 theoretical development The will to European unity as exemplified by A320 Criteria for determination of significant load cycles in [NASA-CR-179632] p 34 N88-10791 p 23 A88-10659 variable amplitude load sequences Computation of transonic separated wing flows using Control surface effects on the low Reynolds number [NLR-MP-86013-U] p 51 N88-10386 behavior of the Wortmann FX 63-137 an EulerlNavier-Stokes zonal approach Elevated temperature crack growth [NASA-TM-883111 p 52 N88-11089 p 10 A88-11187 p 55 N88-11174 CONTROL SYSTEMS DESIGN Combustor-diffuser interaction program CRACKING (FRACTURING) p 35 N88-11152 Conceptual design of an optic based engine control system Compressor turbine vane ring (PT6 engine) repair Software reliability models for fault-tolerant avionics development [ASME PAPER 87-GT-1681 p A88-11079 computers and related topics 30 The development of 270 Vdc solid state power [ASME PAPER 87-GT-471 p 29 A88-10999 [NASA-CR-181 4401 p60 N88-11382 controllers -..for advanced aircraft electrical systems. CRASHES COMPUTER SYSTEMS DESIGN p 33 A88-11923 Full-scale transport controlled impact demonstration The application of emulation techniques in the analysis Expert system control for airborne radar surveillance program of highly reliable, guidance and control computer [AIM PAPER 87-28541 p 26 A88-12574 [ NASA-TM-896421 p 19 N88-10021 systems p 37 N88-10798 The design of a turboshaft speed governor using modern CRASHWORTHINESS COMPUTER TECHNIQUES control techniques Steering mechanism --- vehicles Self-adjusting flight electronics (SAFE) [NASA-CR-175046] p 51 NEB-10339 [EP-PATENT-0-181-700-Al] p 51 N88-10338 p 49 A88-12697 Fiber optic engineering sensor system. Preliminary CREEP PROPERTIES COMPUTERIZED SIMULATION program management plan, phase 3 revision Creep fatigue life prediction for engine hot section Current gas turbine combustion and fuels research and [ADA1836631 p 62 N88-10608 materials (isotropic): Third year progress review development A survey of aircraft integrated control technology p 55 N88-11173 [ASME PAPER 87-GT-1071 p 30 A88-11039 [AR-004-561] p 37 N88-10794 CROSS FLOW Prediction of a microlight biplane'saerofoil performance A preliminary investigation into the feasibility of Momentum exchanges and energy transfers in cross using a computer model p 11 A88-11198 implementingadirect sideforce control System on the Astra flow fans Flight simulation --- Book p 39 A88-11470 Hawk by means of an active control surface --- aircraft [ASME PAPER 87-GT-321 p 44 A88-10992 A mathematical multi-point model for aircraft motion in control Three-dimensional calculation 01 wall boundary layer moving air p 36 A88-12487 [ ETN-87-90924 ] p 37 NEB-10795 flows in turbomachines GPSIINS hybrid navigation for aircraft Flight test of a resident backup software system [ASME PAPER 87-GT-821 p4 A88-11022 p 22 A88-13090 p 38 N88-10805 Heat transfer to arrays of impinging jets in a crossflow COMPUTERS Investigation of control law for active flutter [ASME PAPER 87-GT-1981 p 47 A88-11102 Computing complex for a system for the radio-acoustic suppression Comparison of different kinds of compact cross flow sounding of the atmosphere - Hardware facilities [NASA-TT-20126] p N88-10818 39 heat exchangers p 58 A88-11394 CONTROL THEORY CONCENTRATION (COMPOSITION) Recent tilt rotor flight control law innovations [DFVLR-FB-86-63] p51 N88-10305 The effect of variations of cobalt content on the cyclic p36 A88-12646 Dilution jet mixing program, phase 3 oxidation resistance of selected Ni-base superalloys A survey of aircraft integrated control technology p54 N88-11153 p40 A88-10031 [AR-004-561] p 37 N88-10794 On the mixing of a row of jets with a confined CONFERENCES CONTROLLERS crossflow p54 N88-11154 Modern technology in positioning and navigation; Syntheses of reduced-order controllers for active flutter CRYOGENIC EQUIPMENT Navigation Meeting, Duesseldorf, Federal Republic of suppression p35 A88-10095 Test of IR arrays on the Kuiper Airborne Gtservatory Germany. May 68,1987. Reports p 20 A88-10676 CONVERGENCE p 49 A88-12838 Aerodynamics at low Reynolds numbers Re greater than The smtiallv nonuniform converaence of the numerical CRYOGENIC WIND TUNNELS 10 to the 4th and less than 10 to the 6th; Proceedings solutwn.of fioks Wall interference tests of a CAST 10-2/DOA 2 airfoil of the Internatwnal Conference. London, England. Oct. [ NASA-TM-1OoO371 p60 N88-11429 in an adaptive-wall test section 15-18. 1986. Volumes 1. 2. 8 3 p8 A88-11176 COOLING [NASA-TM-4015] p 18 N88-10772 AIAA Computers in Aerospace Conference. 6th. Coolant passage heat transfer with rotation CUMULATIVE DAMAGE Wakefield. MA, Oct. 7-9, 1987, Technical Papers p54 N88-11160 Ensuring the service life of designs (experience in aircraft p 58 A88-12526 Heat transfer with very high free stream turbulence construction) p 1 N88-10986 Conference on Mechanical Behaviour of Superalloys, p 54 N88-11161 CYCLIC LOADS COOLING SYSTEMS London, England, June 10, 11. 1986. Selected Papers The fatigue properties of aerospace steels under Application of the transient test technique to measure p 42 A88-12626 constant amplitude and flight-by-flight simulated loading Airborne reconnaissanceX; Proceedingsof the Meeting, local heat transfer coefficients associated with augmented [ BAE-MSM-R-GEN-05661 p 51 N88-10377 San Diego. CA. Aug. 19,20, 1986 airfoil cooling passages Criteria for determination of significant load cycles in [SPIE-694] p 26 A88-12728 [ASME PAPER 87-GT-2121 p 47 A88-11112 International Conference on the Aerodynamics at Low Oxygen recombination in a supersonic cooled flow variable amplitude load sequences [NLR-MP-86013-U] p51 N88-10386 Reynolds Numbers between lO(4) and lO(6) p 13 A88-12071 [ONRL-7-023-C] p 16 N88-10010 CORE FLOW Constitutive modeling for isotropic materials Knowledge Based Concepts and Artificial Intelligence: Flame driving of longitudinal instabilities in liquid fueled p 55 N88-11171 Applications to Guidance and Control dump combustors The influence of load cycle reconstitution on fatigue [AGARD-LS-155] p38 N88-10806 [AD-A183536] p33 N88-10033 behaviour Turbine Engine Hot Section Technology, 1985 COROTATION [ARL-STRUC-R-424] p 56 N88-11198 [NASA-CP-2405] p 53 N88-11140 Prediction of turbulent source flow between corotating CYLINDRICAL BODIES CONFIGURATION MANAGEMENT disks with an anisotropic two-equation turbulence model Possibilities for the modeling of dynamically loaded AGARD standard aerodastic configurations for dynamic [ASME PAPER 87-GT-731 p45 A88-11017 cylindrical structural parts in the wind tunnel response. Candidate configuration I.-wing 445.6 CORRECTION [KU-SFB-21O/T/24] p15 N88-10005 [ NASA-TM-100492] p 56 N88-11202 Wall interference tests of a CAST 10-2/DOA 2 airfoil CYLINDRICAL SHELLS CONFORMAL MAPPING in an adaptive-wall test section Elastic buckling of internally pressurized Multigrid solution of the Euler equations on unstructured [NASA-TM-4015] p 18 N88-10772 cylinder-bulkhead combinations p 50 A88-12949 and adaptive meshes p 44 A88-10570 CORROSION RESISTANCE CONICAL FLOW Basic concepts for better heat protection systems Stability of conical and curved annular diffusers lor p 42 A88-12786 D mixed-flow compressors COST EFFECTIVENESS [ASME PAPER 87-GT-191 J p6 A88-11096 Traddional versus Nle-based programming techniques DAMPING CONSTITUTIVE EQUATIONS - Application to the control of optional flight information Investigation 01 control law for active flutter Constitutive modeling of superalloy single crystals with p 58 A88-10965 suppression verifiibon testing p 43 N88-11169 COST ESTIMATES [ NASA-TT-201261 p 39 N88-10818 CONSTRAINTS Cost savings possible with Air Force conversion to JP-8 DATA ACQUISITION Integration of dynamic, aerodynamic and structural as its primary fuel Inter and intra blade row laser velocimetry studies of optimization of heliter rotor blades [ AD-A1837841 p 42 N88-10192 gas turbine compressor flows [NASA-CR-181441] pi6 N88-10012 COST REDUCTION [ASME PAPER 87-GT-2351 p7 A88-11126 CONTINUUM MECHANICS Cost savings possible with Air Force conversion to JP-8 Optical systems for gas turbine engines Problems in continuum mechanics with mixed boundary as its primary fuel p49 A88-12657 conditions --- Russian book p43 A88-10017 [ AD-A1837841 p 42 N88-10192 DATA LINKS CONTRAROTATING PROPELLERS COUNTER ROTATION Video data link provides television pictures in near real Noise of a model high speed counterrotation propeller Counterrotating differential cylindrical roller bearing time via tactical radio and satellite channels at simulated takeofflapproach condibons (F7/A7) development p 49 A88-12732 [NASA-TM-100206] p 61 N88-10592 [AIAA PAPER 87-18431 p 43 A88-10497 Datalink design trade-offs for electro-optical CONTROLBOARDS Noise of a model high speed counterrotation propeller reconnaissance systems p 27 A88-12740 Comparison of programmable legend keyboard and at simulated takeofflapproach conditions (F7/A7) DATA MANAGEMENT dedicated keyboard for control of the flight management [ NASA-TM-100206] p 61 N88-10592 Airborne reconnaissanceX Proceedingsof the Meeting, computer Turbines with counterrotating runners for aircraft power San Diego, CA, Aug. 19.20, 1986 [SAE PAPER 8617721 p57 A88-10160 plants p '34 N88-10992 [SPIE-694] p 26 A88-12728

A-7 DATA PROCESSING SUBJECT INDEX

DATA PROCESSING DIGITAL SYSTEMS EFFICIENCY Development studies of a European data network for Digital system bus integrity Impact of turbulence modeling on numerical accuracy acquisition, processing. and display of air-traffic data [ NASA-CR-181446I p28 N88-10030 and efficiency of compressible flow simulations p 21 A88-10688 Reliability modeling of faun-tolerant computer based [ NASA-TM-883331 p 52 N88-11088 DATA STORAGE systems p37 N88-10801 EJECTORS Measurements in the functional mock up test of the DIGITAL TECHNIOUES Similarity of ejector wall-pressure distributions NAL QSTOL aircraft control system Softcopy versus hardcopy --- digital image displays for p 49 A88-12294 [ NAL-TR-9281 p 36 N88-10793 aerial reconnaissance p27 A88-12750 ELASTIC BUCKLING DECISION MAKING DILUTION Elastic buckling of internally pressurized Perspective traffic display format and airline pilot traffic Dilution jet mixing program. phase 3 cylinder-bulkhead combinatims p 50 AB-12949 avoidance p58 A88-12639 p54 N88-11153 ELASTIC DEFORMATION Application of knowledge-based techniques to aircraft Numerical solution of coupled problems of supersonic traiectwy generation and control p 38 N88-10811 DIRECTION FINDING flow past deformable shells of finite thickness Development and trends in radio poskn finding DECOUPLING p13 A88-11280 p20 A88-10680 Decoupling and stabilization of speed and height in F4 ELASTIC PROPERTIES Phantom aircraft using output feedback Hybrid positioning and navigation systems . Problems in continuum mechanics with mixed boundary [ETN-87-90926] p 25 N88-10787 Technological status and development trends in conditions -- Russian book p43 A88-10017 DEICERS position-findingand navigation procedures ELECTRIC CONNECTORS Fluids for deicing aircraft surfaces p 40 A88-10872 p20 A88-10684 Design principles and practices for implementation of DEICING DISPLAY DEVICES MIL-STD-1760 in aircraft and slores Fluids for deicing aircraft surfaces p 40 A88-10872 An integrated display for vertical situation awareness [ AD-A1837241 p 24 N88-10027 DEPOSITION in commercial transpolt aircraft ELECTRIC EOUIPMENT The dependence of the normalized ice accretion [SAE PAPER 8617701 p 57 A88-10158 Testing of aircraft electrical equipment --- Russian thickness on cloud-physical parameters The advantage of flightpath-oriented situation displays book p 39 AM-10044 [ DFVLR-FB-87-06] p 57 N88-10464 during microburst encounters ELECTRIC GENERATORS DESIGN ANALYSIS [SAE PAPER 8617331 p35 A88-10164 Force commutated direct frequency changers for Application of advanced computational codes in the Color display technology - An overview aerospace power applications p 48 A88-11825 design of an experiment for a supersonic throughflow fan [SAE PAPER 8616921 p 43 A88-10170 ELECTRIC NETWORKS rotor Perspective traffic display format and airline pilot traffic Design principles and practices for implementation of [ASME PAPER 87-GT-1601 p 6 A88-11072 avoidance p 58 A88-12639 MIL-STD1760 in aircraft and stores A new method (FTDCDF) for blade design of Sensor controlldata display set (SCIDDS) for film [ AD-A1 837241 p 24 N88-10027 axiallmixed-flow compressors and its applications andlor electro optics (EO) p26 A88-12731 [ASME PAPER 87-GT-1831 p31 A88-11090 ELECTRICAL RESISTANCE Softcopy versus hardq-.. digital image displays for Gas turbine exhaust systems - Design considerations The development of a high temperature static strain gaga aerial reconnaissance p27 A88-12750 system p53 N88-11142 [ASME PAPER 87-GT-2381 p 32 A88-11128 Color display programming for aviation Low Reynolds number airfoil design at the Douglas ELECTRO-OPTICS [DFVLR-MIlT-8743] p28 N88-10031 Aircraft Company p9 A88-11183 Sensor controlldata display set (SCIDDS) for film Fiber optic engineering sensor system. Preliminary Two-dimensional transonic aerodynamic design andlor electro optics (EO) p26 A88-12731 program management plan, phase 3 revision method p 14 A88-12284 Real-time reconnaissance An engineering [ADA1836631 p 62 N88-10608 - p21 A88-12733 An uncooled linescan thermal imager for ground and DISTRIBUTED PARAMETER SYSTEMS perspecwe airbome use p 49 A88-12840 Stability of supersonic flow of an ideal gas with a head Datalink design trade-offs for electrcmptical A compact high performance thermal imager shock wave past cylindrical channels and cavities reconnaissance systems p27 A88-12740 p50 A88-12843 p13 A88-12065 Arguments for electro-optical reconnaissance systems Current design status and design trend of fuel injectors DOMAINS p27 A@-12746 for jet engines p33 A88-13076 Syntheses of reduced-ordw controllers for active flutter ELECTROMAGNETISM DETECTION suppression p35 A88-10095 Process supporl compressor motor electromagnetic Evaluation of a dual processor implementation for a fault DRAG DEVICES design summary infening nonlinear detection system Pressure field due to drag reducing outer layer [DE87414359] p52 N88-11048 [AIM PAPER 87-27621 p 59 A88-12532 devices in turbulent boundary layers p3 A88-10492 ELECTROMAQNETS Optimal detection sensa failures in fliht control of DRAG REDUCTION Process support compressor motor electromagnetic systems using deterministic observers Pressure field due to drag reducing layer devices dmgn summary p38 N88-10803 cuter in turbulent bwndary layers p 3 A88-10492 [ DE874143591 p52 N88-11048 DETERMINANTS Transonic analysis and design of axisymmetric bodies Optimal detection of sensor failures in flight control ELECTRONIC CONTROL in nonuniform flow systems using deterministic observers The impact of modern technolosy on aircraft avionics [NASA-CR-41011 p16 N88-10013 equipment p26 A88-10679 p38 N88-10603 DRONE AIRCRAFT DEVIATION Digital controls for gas turbine engines Towards the unmanned cockpit p 25 N88-10812 [ASME PAPER 87-GT-2111 p31 A68-11111 The deviation of light rays passing through a curved DUCTED FLOW windscreen aircraft ELECTRONIC COUNTERMEASURES --. Parabolized Navier-Stokes analysis of ducted [BAE-MSC.115] p82 N88-10610 FDAD A lablfield test tool Flight Data Analysis and supersonic combustion problems p 2 A88-10361 - --- DIESEL FUELS Display p 25 A88-10436 Experimental method for the combustion efficiency Combustion gas properties. Prediction of the ELLIPSES 111 - calculation in a reheat duct thermodynamic properties of combustongases aviation of [ASME PAPER 87-GT-901 p 29 A88-11029 Exact and asymptotic expressions of the lift slope and diesel fuels DYNAMIC LOADS coefficient of an elliptic wing p14 A88-12292 [ASME PAPER 87-GT-491 p40 A88-11001 Possibilities for the modeling of dynamically loaded ELLIPTIC DIFFERENTIAL EQUATIONS DIFFRACTION cylindrical smctural parts in the wind tunnel Shock embedding discontinuous solution of elliptic The deviation of light rays passing through a curved [KU-SFB-21O/T/24] p15 N88-10005 equation for inverse problem of transonic 52 flow windscreen --- aircraft DYNAMIC RESPONSE [ASME PAPER 87-GT-1151 p5 A88-11043 [BAE-MSC.115] p82 N88-10610 On predicting the resonant response of bladed disk EMBEDDED COMPUTER SYSTEMS DIFFUSERS assemblies Avionics, artifiiial intelligence. and embedded Combuslordiffuser interaction program [ASME PAPER 87-GT-1581 p 30 A8&11070 processing systems p 35 N88-11152 Investigation of inleractbns between limbmanipulator [AIM PAPER 87-28181 p59 A86-12558 DIFFUSION dynamics and effective vehicle roll control ENCLOSURES A method for calculating turbulent boundary layers and characteristics The use of Kdar on aerc-engine fan containment losses in Row channels of turbomachines the [ NASA-CR-3983I p36 N88-10039 Casings [ASME PAPER 87-GT-2251 p7 A88-11121 Blade loss transient dynamics analysis, volume 1. Task [PNR90410] p53 N88-11134 DIFFUSION THEORY 2 TETRA 2 theoretbl development ENERGY CONSERVATION Applili of a difhrsion combustion model to the [NASACR-179632] p34 N88-10791 Cost savings possible with Air Force cormemion to JP8 analysis of supersonic turbulent reacting jets Blade loss transbent dynamics analysis, volume 2. Task as its primary hid p40 A88-10180 2: TETRA 2 user's manual DIGITAL COMPUTERS [ ADA1837841 p42 N88-10192 [NASA-CR-179633] p34 N88-10792 ENERGY CONVERSION EFFICIENCY Development and trends in radio position finding AGARD standard aeroelastic configurationsfor dynamic p20 A88-10680 Combustion gas properties. Ill - Prediction of the response. candidate configuration I.-wing 445.6 thermodynamic propertiesof combustion gases of aviation Reliability modeling of fault-tolerant computer based [NASA-TM-100492] p56 N88-11202 systems p37 N88-10801 and diesel fuels DIGITAL ELECTRONICS [ASME PAPER 87-GT-491 p40 A88-11001 Wil controls for gas turbine engines E ENERGY TRANSFER [ASME PAPER 87-GT-2111 p31 A88-11111 Momentum exchanges and energy transfers in cross DIGITAL FILTERS ECHO SOUNDING flow fans Hybrid positioning and navigation systems Detection of targets in the presence of clutter using [ASME PAPER 87-GT-321 p44 AM-10902 Technological status and development trends in target echo modulations caused by rotating structures Effect of energy release in the shock layer on the position-findingand navigation procedures [REPT-12-@6] p50 N88-10231 supersonic fliht of bodies p13 AB8-12073 p20 A88-10684 EDDY VISCOSITY ENGINE AIRFRAME INTEGRATION DIGITAL NAVlQATlON The design of shock-free compressor cascades Transonic analysis and design of axisymmetric bodii Development and trends in radio position finding including viscous boundary layer effects in nonuniform flow 1120 A88-10680 [ASME PAPER 87-GT-711 p4 A88-11015 [NASA-CR-llOl] pl6 N88-10013 SUBJECT INDEX FIGHTER AIRCRAFT

ENGINE CowTROL ENGINE STARTERS EXTERNAL STORES Investigation of integrated selectjon of optimum engine Starting system for cold weather p 23 A88-10871 Design principles and practices for implementation of cycle parsmet- ENGINE TESTS MIL-STD1760 in aircraft and stores [ASME PAPER 87-GT-391 p29 A88-10993 Development of the XF330 turbofan engine [ADA1837241 p24 N88-10027 Conceptual design of an optic based engine control [ASME PAPER 87-GT-261 p28 A88-10988 system Velocity scaled aeroelastic testing of advanced [ASME PAPER 87-GT-1881 p30 ABS11079 turbopropg F Digital contrds for gas tuftim engines [ASME PAPER 87-GT-2091 p31 A88-11110 [ASME PAPER 87-GT-2111 p31 ABS11111 AGT101 - Ceramic gas turbine development F-4 AIRCRAFT HlDEC adaptive engine control system fliht evaluation [ASME PAPER 87-GT-2281 p32 A88-11122 Robust control system design p 37 N88-10800 results Cyclic spinning testing of aero-engine discs FAIL-SAFE SYSTEMS [ASME PAPER 87-GT-2571 p32 A88-11137 [ASME PAPER 87-GT-2591 p32 A88-11139 Extended systems of variable structure with mobile ENGINE DEWN Diagnosis of flow channel in aircraft gas-turbine engines radmmmunkation objects p 44 A88-10728 basis of vibration spectrum characteristics Analyiical study of sw*ler effects in annular propulsive on FAILURE ANALYSlS p35 N88-10993 nozzles p28 A88-10362 Optimal detection of sensor failures in riiht control EQUATIONS OF MOTION Multimodes to Mach 5 p28 A88-10371 systems using deterministic observers Development the XF3-30 turbofan engine On predicting the resonant response of bladed disk of p38 N88-10803 [ASME PAPER 87-GT-261 p 28 A88-10988 assemblies FAN BLADES Development of ceramic hot section components for [ASME PAPER 87-GT-1561 p30 A88-11070 AGT 100 turbine Unified equation of motion (UEM) approach as applied Application of advanced computational codes in the gas design of experiment for a throughRow fan [ASME PAPER 87-GT-793 p45 ABS11019 to S1 turbomachinery pmMems an supersonic rotor OW-designperfmnceofsupenvniccompreruKxswith [ASME PAPER 87-GT-1791 p8 A88-11087 [ASME PAPER 87-GT-1601 p6 AM-11072 fixed and variable geometry A mathematical multi-point model for aircraft motion in [ASME PAPER 87-GT-1161 p 5 A88-11044 moving air p 36 A88-12487 First article test noise survey of the AlF32T-9 large turbo Adiscvsslon of the mean S2 straam surfaces applied Decwpling and stabilization of speed and heiiht in F4 fan engine enclosed noise suppreapor system, Sky Harbor to quasi-three-dimensional calculation programs for Phantom aircraft using output feedback IAP (International Airport). Phoenix. Arizona tubomachinerydesign [ETN-87-90926] p25 N88-10787 [ADA1837991 p61 N88-10588 [ASME PAPER 87-GT-1501 p5 ABS11067 EROSIVE BURNING The wide chord fan Made: A Rolls Royce first Development of the AGT101 regenerator sals Computer predictions of erosion damage in gas [PNR90416] p 34 N88-10789 [ASME PAPER 87-GT-1731 p46 A88-11083 turbines The use of Kevlar on aero-enaine fan containment AGT101 - Ceramic gas turbine development [ASME PAPER 87-GT-1271 p46 A88-11054 Casings [ASME PAPER 87-GT-2281 p32 ABS11122 ERROR ANALYSIS [PNR90410] p53 N88-11134 An improved Swing engine for model aircraft Some approaches to the design of high integrity FAR FIELDS PmprlSiOn p33 A88-11976 software p 37 NU-10799 Heliiter main-rotor SDeed effects on far-field awustic The scramjet - Toward Mach 4-25 fliht EULER EQUATIONS OF MOTION levels p 33 A88-13095 Explidt multigrid algorithm for quasi-three-dimensional [NASA-TM-100512] p 82 N88-11451 Fnt article test noise survey of the AlF32T-9 large turbo viscws Rom, in turbomachinery p 2 A88-10355 FATIGUE (MATERIALS) fan engine encloQed noise suppcessor system, Sky Harbor Multigrid solution of the Euler equations on unstructured The influence of load cycle reconstitution on fatigue IAP (International Airport), Phoenix, Arizona and adaptive meshes p44 A88-10570 behavioor [ADA1837991 p61 NEE10588 Computation of transonic separated wing flows using [ARL-STRUCR-424] p56 N88-11198 The wide chord fan blade: A Rolls Royce first an EulerlNavier-Stokes zonal approach FATIGUE LIFE [PNR90416] p34 N88-10789 [ NASA-TM-883111 p 52 N88-11089 Cyclic spinning testing of aero-engine discs Turbines with counterrotating runners for aircraft power EUROPEAN AIRBUS [ASME PAPER 87-GT-2591 p 32 A88-11139 @ants p 34 N88-10992 Assessment of software quality for the AIRBUS A310 The fatigue properties of aerospace steels under Transmission etfidency in advanced aerospace automatic pilot p38 N88-10804 constant ampiii and flight-by-fliht simulated loading EUROPEAN SPACE PROQRAMS [ BAE-MSM-R-GEN-05661 p51 N88-10377 [PNR90391] p53 NBS11133 Aerospace research at the National Aerospace Criteria for determination of significant load cycles in ENQINE FAILURE Laboratory (NLR) variable amplitude load sequences A natural low frequency oscillation in the wake of an [ ETN-87-90821J p 62 N88-10697 [NLR-MP-WOt3-U] p51 N88-10386 airfoil near stalling COnditioM EVALUATION Creep fabgue lite prediction for engine hot section [NASA-TM-1002131 pl8 NBS10779 Assessment of software quality for the AIRBUS A310 materials (isotropic): Third year progress review ENQINE INLETS automatic pilot p38 N88-10804 p55 N88-11173 Theaeromechaniiresponseofanadvancedtransonic EXHAUST DIFFUSERS The influence of load cycle reconstitution on fabgue compressor to inlet distortion A tradeoff study of rotor tip clearance flow in a behaviour [ASME PAPER 87-GT-1891 p31 A88-11094 turbinelexhaust diftuser system [ARL-STRUCR-424] p58 N88-11198 Bar- layer profile investigations dmvnntream of an [ASME PAPER 87-GT-229] p32 A88-11123 FATIGUE TESTS aefo.engine intake anti-icing air exhaust slot EXHAUST QASES Creep fa& lite prediin for engine hot section [PNRB0378] p52 N88-11080 Combustion gas properties. 111 - Prediction of the materials (isotropic): Third year progress review ENQINE YONlTORlNQ INSTRUMENlS thmmdynamic properties of combustiongases of aviation p55 N88-11173 Introduction and application of the General Electric and diesel fuels FAULT TOLERANCE turbine engine mnoring softwarewithinKLM Royal Dutch [ASME PAPER 87-GT-491 p40 A88-11001 Digital controls for gas turbine engines Airlines Prediction of NO and CO distribution in gas turbine [ASME PAPER 87-GT-2111 p31 A88-11111 [ASME PAPER 87-GT-1673 p30 A88-11078 combustors Evaluationof a dual processor implementationfor a fault ENGINE NOISE [ASME PAPER 87GT-631 p41 A88-11010 infening mlinear detection system Advanced awbopop wing installation Mecla measured Boundary layer profile investigations downstream of an [AIM PAPER 87-27621 p59 A8812532 by unateady blade pressure and noise aero-engine intake anti-icing air exhaust slot Implementation of a research prototype onboard fault [NASA-TM-l00200] p15 N88-10008 [ PNR903781 p52 N88-11080 monitoring and diagnosis system Fnt article test noise survey of the AlF32T-9 large turbo EXHAUST SYSTEMS [AIM PAPER 87-27771 p59 AM-12540 fan engine endosed noise suppressor system. Sky Harbor Some approaches to design huh integrity Gas twbine exhaust systems Design considerations Me of IAP (International Airport), Phoenii. Arizona - software p 37 N88-10799 [ASME PAPER 87-GT-2381 p32 A88-11128 [ADA1837991 p61 NEE10588 Robust control system design p 37 N88-10800 Noise emission of civil and mllitary aero-engines. EXPERIMENT DESlQN Reliability modding of fault-tolerant computer based Sources of generation and measures for attenuation Expefimental method for the combustion efficiency systems p37 N88-10801 [ETN87-91021] p82 N88-10595 calculation in a reheat duct Fliiht test of a resident backup software system ENQINE PARTS [ASME PAPER 87-GT-90) p29 A88-11029 p38 N88-10805 Development of ceramic hot section components for EXPERT SYSTEMS Software reliability models for fault-tolerant avionics AGT 100 gaa Wne Towards the design of an intelligent aerospace system computers and related topics [ASME PAPER 87-GT-791 p45 ABS11019 [AIM PAPER 87-28441 p 26 A88-1256g [ NASACR-1814401 p80 N88-11382 Numerical solution of threedimensional turbulent flows Expert system control for airborne radar surveillance FEEDBACK CONTROL for modem gas turbine components [AIM PAPER 87-28541 pi3 ABS12574 The design of a turboshaft speed governor wing modern [ASME PAPER 87-GT-841 p4 A88-11024 Self-adjusting riiht electronics (SAFE) control techniques Dwdopmmt of the AGTlOl regermator ada p49 ABS12697 [NASACR-175046] p51 NBS10339 [ASME PAPER 87-GT-1731 p46 A88-11083 KnowMge Based Concepts and Artificial Intelligence: FIBER OPTICS AGTlO1 - Ceramic gaa Wne dedopment Applications to Guidance and Control Conceptual design of an optic based engine control [ASME PAPER 87-GT-2281 p32 A88-11122 [AGARDLS-155] p38 N88-10806 system Development of a statistically pmven injection molding &exview of AGARD Lecture Series No. 155: [ASME PAPER 87-GT-1681 p30 A88-11079 method for reaction bonded silicon nitride, sintering Knowledge-based concepts and artifidal intelli Test equipment with fiber optic data bus and laser gyro reaction bonded silicon nitride, and sintered silicon applications to guidance and control p 38 N88-10807 strap&wn system LTN-90 for the helicopter 80105 nitride [ESA-lT-1038] p22 N88-10025 AI expert system technology iawss for guidance and (ETN-87-905751 p52 NBS11002 Fiber optic engineering sensor system. Preliminary control applications P38 N88-10808 Investment foundry melting stock. Rolls Royce program management plan. phase 3 revision requirements and demands in terms of qualty and the An expert system for aircraft conflict resolution in dense [ A6A1836631- p62 NE@-10608 relatiomhip to end product performance airspaces p22 NBS10810 FIQMTER AIRCRAFT [ PNRB03971 p52 NB&11003 Towards the unmanned cockpit p 25 NBS10812 Conceptunl dmgn of an optic based engine control Hih temperature stress-strain analyak A rulebased system for anival sequencing and system p55 NBS11170 scheduling in air traffic control p22 N88-10815 [ASME PAPER 87-GT-1881 p30 ABS11079

A-9 FILM COOLING SUBJECT INDEX

HiMAT flight program: Test results and program FLIGHT MANAGEMENT SYSTEMS FLOW DEFLECTION assessment overview Comparison of programmable legend keyboard and Necessary optimality conditions for three-dimensional [NASA-TM-86725] p 24 N88-10026 dedicated keyboard for control of the flight management bodies in supersonic gas flow p2 A88-10300 Comparison of wind tunnel and flight test afterbody and computer Numerical solution of coupled problems of supersonic nozzle pressures for a twin-jet fighter aircraft at transonic [SAE PAPER 8617721 p 57 A88-10160 flow past deformable shells of finite thickness speeds Optimal detection of sensor failures in flight control p 13 A88-11280 [ NASA-TP-25881 p 17 N88-10765 systems using deterministic Observers Refined numerical solution of the transonic flow past a Application of knowledge-based techniques to aircraft p 38 N88-10803 wedge p 14 A88-12280 trajectory generation and control p 38 N88-10811 FLIGHT MECHANICS FLOW DISTORTION The influence of load cycle reconstitution on fatigue The accuracy-related parametric reduction of The aeromechanical response of an advanced transonic behaviour mathematical models p 58 A88-10929 compressor to inlet distortion [ASME PAPER 87-GT-1891 p 31 A88-11094 [ARL-STRUC-R-4241 p 56 NEB-111 98 FLIGHT PATHS FLOW DISTRIBUTION FILM COOLING Flying complex approach paths using the microwave Momentum exchanges and energy transfers in cross Film cooling of a turbine blade with injection through landing system flow fans two rows of holes in the near-endwall region [SAE PAPER 8617711 p 35 A88-10159 [ASME PAPER 87-GT-1961 p 47 A88-11100 [ASME PAPER 87-GT-321 p 44 A88-10992 Improvements in aircraft safety and operational FINITE DIFFERENCE THEORY Experiments on spray interactions in the wake of a bluff dependability from a projected flight path guidance Vixidlinviscid interaction analysis of subsonic turbulent display trailingedge flows p 14 A88-12282 ZMEPAPER 87-GT-481 p 44 A88-11000 [SAE PAPER 8617321 p 35 A88-10163 FINITE ELEMENT METHOD Off-design performance of supersonic compressors with Development of ceramic hot section components for The advantage of flightpath-oriented situation displays fixed and variable geometry AGT 100 gas turbine during microburst encounters [ASME PAPER 87-GT-1161 p 5 A88-I1044 [ASME PAPER 87-GT-791 p 45 A88-11019 [SAE PAPER 8617331 p 35 A88-10164 A trace gas technique to study mixing in a turbine Reliability of finite element methods in North America Approach trajectory planning system for maximum stage [AGARD-R-748] p 53 N88-11139 concealment [ASME PAPER 87-GT-1181 p 5 A88-11046 Component specific modeling p 60 N88-11166 [ NASA-TM-882581 p 60 N88-11435 Characterizationof shock wave end wall boundary layer Constitutive modeling for isotropic matenals FLIGHT SAFETY interactions in a transonic compressor rotor p55 N88-11171 The advantage of flightpath-oriented Situation displays [ASME PAPER 87-GT-1661 p6 A88-11077 Constitutive modeling for isotropic materials during microburst encounters Film cooling of a turbine blade with injection through p 55 N88-111 72 [SAE PAPER 8617331 p35 A88-10164 two rows of holes in the near-endwall region Thermal expansion mismatch and oxidation in thermal Flight safety and nsk p 19 A88-10658 [ASME PAPER 87-GT-1961 p 47 A88-11100 barrier coatings p 56 N88-11182 EMFT-supported projects in the fields position-finding, Boundary layer and performance characteristics from FIRE FIGHTING navigation, and traffic safety p20 A88-10677 wind tunnel tests of a low Reynolds number Liebeck airfoil p9 A88-11184 Test results and predictions for the response of The importance of modern positioning and navigation Analysis of supersonic heterogeneous flow impinging near-ceiling sprinkler links in a full-scale compartment technology for ATC p 20 A88-10678 fire on an obstacle p 14 A88-12074 The impact of modern technology on aircraft avionics [ NESIR-87-36331 p 50 N88-10209 Wall interference tests of a CAST 10-2IDOA 2 airfoil equipment p 26 A88-10679 FLAME STABILITY in an adaptive-wall test section Flame driving of longitudinal instabilities in liquid fueled Development studies of a European data network for [ NASA-TM-40151 p 18 N88-10772 dump combustors acquisition, processing. and display of air-traffic data A natural low frequency oscillation in the wake of an [ AD-A1835361 p 33 N88-10033 p 21 A88-10688 airfoil near stalling conditions FLAT PLATES The conflict resolution process for TCAS II and Some [NASA-TM-100213] p 18 N88-10779 Heat transfer with very high free stream turbulence simulation results p 21 A88-12474 Fuel-injector/air-swirl characterization p54 N88-11161 Design study for an FEW lateral control system p54 N88-11150 FLATSURFACES p 36 A88-13080 Combustor-diffuser interaction program Heat transfer to arrays of impinging jets in a crossflow FLIGHT SIMULATION p 35 N88-11152 [ASME PAPER 87-GT-1981 p47 A88-11102 Flying complex approach paths using the microwave Heat transfer with very high free stream turbulence FLEXIBLE BODIES landing system p 54 NEB-11161 An optimal control method for passage of a flexible rotor [SAE PAPER 8617711 p 35 A88-10159 Flow in a model turbine stator p 55 N88-11163 through resonances p 48 A88-11439 Flight simulation --- Book p 39 A88-11470 The spatially nonuniform convergence of the numerical Wall interference tests of a CAST 10-2/DOA 2 airfoil The fatigue properties of aerospace steels under solution of flows in an adaptie-wall test section constant amplitude and flight-by-flight simulated loading [NASA-TM-100037] p60 N88-11429 [ NASA-TM-40151 p 18 N88-10772 [ EAE-MSM-R-GEN-05661 p 51 N88-10377 FLOW EOUATIONS FLIGHT ALTITUDE Contributions to the modeling of wind shear for danger Cascade viscous flow analysis using the Navier-Stokes Decoupling and stabilization of speed and height in F4 studies equations p2 A88-10356 Phantom aircraft using output feedback [ ETN-87-904421 p57 N88-10463 FLOW GEOMETRY [ ETN-87-909261 p 25 N88-10787 Global positioning satellite-based automatic landing Off-design performanceof supersonic compressors with FLIGHT CHARACTERISTICS system and wind estimated feedback for the AH64 fixed and vanable geometry Flight characteristics of aircraft with gas-turbine engines helicopter p 22 N88-10784 [ASME PAPER 87-GT-1161 p 5 A88-11044 --- Russian book p 23 A88-10049 FLIGHT TEST INSTRUMENTS FLOW MEASUREMENT Preliminary measurements of the flight performance of Test equipment with fiber optic data bus and laser gyro Labyrinth seal flow measurement by tracer gas an RPV compared with wind tunnel and CFD estimates strapdown system LTN-90 for the helicopter 80-105 injection p 12 A88-11203 [ESA-TT-10381 p22 N88-10025 [ASME PAPER 87-GT-1871 p 47 A88-11092

Low Reynolds number wind tunnel measurements ~ The A mathematical multi-point model for aircraft motion in FLIGHT TESTS moving air p 36 A88-12487 HTTE - The ultimate test bed p 23 A88-10875 importance of being earnest pi0 A88-11190 Measurement techniques in low-speed turbulent flows: FLIGHT CONTROL Development of the XF3-30 turbofan engine [ASME PAPER 87-GT-261 p 28 A88-10988 A report on EUROMECH 202 The will to European unity as exemplified by A320 [ NLR-MP-86038-Ul p 51 N88-10283 p 23 A88-10659 HlDEC adaptive engine control system flight evaluation results Optical flow diagnostic measurements in Flight director guidance for MLS p 21 A88-10874 [ASME PAPER 87-GT-2571 p 32 A88-11137 turbomachinery Traditional versus rule-based programming techniques Wind-tunnel test results of Eppler 387 aerofoils and [PNR90396] p 52 NEB-1 1081 - Application to the control of optional flight information comparisons with flight test and computation FLOW REGULATORS p 58 A88-10965 p 12 A88-11208 The performance of model aircraft using flow Recent tilt rotor flight control law innovations Airborne reconnaissance pod flight test invigorators, gliding in the critical range of Reynolds p 36 A88-12646 p 27 A88-12741 number p12 A88-11206 Digital system bus integrity Flight test results for a GPS receiver in a helicopter FLOW STABILITY [ NASA-CR-1814461 p 28 N88-10030 and a business aircraft p 22 A88-13094 Stability of conical and curved annular diffusers for A survey of aircraft integrated control technology HiMAT flight program: Test results and program mixed-flow compressors [AR-004-561] p 37 N88-10794 assessment overview [ASME PAPER 87-GT-1911 p6 A88-11096 Robust control system design p 37 N88-10800 [ NASA-TM-667251 p24 N88-10026 FLOW VISUALIZATION Optimal detection of sensor failures in flight control Comparison of wind tunnel and flight test afterbody and The flow visualization on the rotary wing with low aspect systems using deterministic Observers noale oressures for a twin-iet.~ fiohter aircraft at transonic ratio p2 A88-10094 p 38 N88-10803 speeds’ Sealino of a shrouded rotor-stator svstem with ore-swirl [ NASA-TP-25881 p 17 N88-10765 Flight test of a resident backup software system coolant Flight researh at NASA Ames Research Center: A p38 N88-10805 test [ASME PAPER 87-GT-721 p 45 A88-11016 pilot’s perspective A trace gas technique to study mixing in a turbine FLIGHT HAZARDS [ NASA-TM-lCG3251 p 25 N88-10788 stage Flight safely and risk p 19 A88-10658 Flioht test of a resident backup software system [ASME PAPER 87-GT-1181 p 5 A88-11046 Aircraft accidents p 38 N88-10805 [JE-84] p 19 N88-10020 FLOW CHARACTERISTICS A smoke-wire study of low Reynolds number flow over Contributions to the modeling of wind shear for danger Through-flow analysis of a multi-stage compressor a NASA LRN(1) - 1007 airfoil section p 9 A88-11181 studies operating at near-stall conditions An experimental investigation of the aerodynamics of [ETN-67-90442] p57 NEB-10463 [ASME PAPER 87-GT-51 I p4 A88-11003 the hang glider pll A88-11200 The dependence of the normalized ice accretion The performance estimation of transonic turbine at Smoke-wire and thin-filmgaugeObservations of laminar thickness on cloud-physical parameters design and offdesign conditions separation bubbles on an NACA 23012-64 airfoil section [DFVLR-FE-87-08] p57 N88-10464 [ASME PAPER 87-GT-1481 p 30 A88-11066 p 13 A88-11210

A-10 SUBJECT INDEX GAS TURBINE ENGINES

Further visualization of combined wing tip and starting FUEL CONSUMPTION A model to determine the behaviour of a pressure vortex systems p 14 A88-12276 New Somet commercial airliners p 23 A88-10655 measurement equipment during non-static operations of Dispersion in the wake of aircraft An investigation of The impact of modern technology on aircraft avionics gasturbine engines the effects of a ground plane on trailing vortices. Literature equipment p 26 A88-10679 [ASME PAPER 87-GT-1281 p 46 A88-11055 suwey FUEL INJECTION Spray performance of a hybrid injector under varying [ ICAERO-REP-86-04] p16 N88-10014 Spray performance of a hybrid injector under varying air density conditions Optical flow diagnostic measurements in air density conditions [ASME PAPER 87-GT-1551 p 46 A88-11068 turbomachinery [ASME PAPER 87-GT-1551 p 46 A88-11068 Development of the AGTlO1 regenerator seals [PNR90396] p 52 "3-1 1081 Current design status and design trend of fuel injectors [ASME PAPER 87-GT-1731 p 46 A88-11083 FLUID DYNAMICS for jet engines p 33 A88-13076 Prediction of gas turbine combustor-liner temperature FUEL OILS The structure of separated flow regions occurring near [ASME PAPER 87-GT-1771 p 31 A88-11085 Investigation of high-altitude ignition performance of the leading edge of airfoils including transition Applications of ceramic coating on the turbine blades [ NASA-CR-181434I p 16 NEB-10011 several Chinese jet fuels with different properties of the AGTJ-1008 [ASME PAPER 87-GT-1781 p 41 A88-11086 [ASME PAPER 87-GT-1901 p 41 A88-11095 Aerospace research at the National Aerospace FUEL SPRAYS Digital controls for gas turbine engines Laboratory (NLR) Experiments on spray interactions in the wake of a bluff (ETN-87-90821I p62 NEB-10697 [ASME PAPER 87-GT-2111 p 31 A88-11111 body Application of the transient test technique to measure FLUID FLOW [ASME PAPER 87-GT-481 p 44 A88-1 loo0 local heat transfer coefficientsassociated with augmented Analytical modeling of helicopter static and dynamic Fuel-injectorlair-swirl characterization airfoil cooling passages induced velocity in GRASP p 54 N88-11150 [ASME PAPER 87-GT-2121 p 47 A88-11112 [NASA-TM-100026] p 18 N88-10777 FUEL TESTS AGTlOl - Ceramic gas turbine development FLUTTER Correlations of fuel performance in a full-scale [ASME PAPER 87-GT-2281 p 32 A88-11122 Flutter suppression and gust load allewation. Part 1: commercial combustor and two model combustors Mechanical property requirements for aero gas turbine Results of phase 1 to 3. Part 2: Description of the Garteur [ASME PAPER 87-GT-891 p 29 A88-11028 materials p 42 A88-12628 model Developments in disc materials --_ for gas turbine [MBB-LKE292lSlPUB/191I p 36 N88-10038 Prediction of combustion performance of aviation kerosines using a novel premixed flame technique engines p 42 A88-12632 A natural low frequency oscillation in the wake of an [ASME PAPER 87-GT-1251 p4t A88-11052 High-temperature sheet materials for gas turbine airfoil near stalling conditions applications p 42 A88-12635 [NASA-TM-1002131 p 18 N88-10779 Investigation of high-altitude ignitin performance of several Chinese jet fuels with different properties Optical systems for gas turbine engines FLUTTER ANALYSIS [ASME PAPER 87-GT-1781 p 41 A88-11086 p 49 A88-12657 Syntheses of reduced-order controllers for active flutter Thin-film temperature sensors deposited by radio FUEL-AIR RATIO suppression p 35 A88-10095 frequency cathodic sputtering p 50 A88-12903 SDrav Derformance of a hvbrid iniector under vawina Investigation of control law for active flutter .. .- Current design status and design trend of fuel injectors air density conditions suppresson for jet engines p 33 A88-13076 [ASME PAPER 87-GT-1551 p 46 A88-11068 [ NASA-lT-201261 p 39 N88-10818 Turbines with counterrotating runners for aircraft power FLY BY WIRE CONTROL FULL SCALE TESTS plants p 34 N88-10992 Airline requirements on a fly-by-wire aircraft - A pilot's Aerodynamics of unmanned aircraft at full-scale in the Diagnosis of flow channel in aircraft gas-turbine engines view RAE 24fl wind-tunnel p 12 A88-11204 on basis of vibration spectrum charactenstics [SAE PAPER 8618041 p 36 A88-10167 FUNCTIONAL DESIGN SPECIFICATIONS p 35 N88-10993 Design study for an FBW lateral control system Anti-tank helicopters for the rich and not so rich Development of a statistically proven injection molding p 36 A88-13080 p 1 A88-10877 method for reaction bonded silicon nitride, sintering Flight test of a resident backup software system FUSELAGES reaction bonded silicon nitride. and sintered silicon p 38 N88-10805 Observations and analyses of natural laminar flow over nitride FORCED VIBRATION a nonlifting airframe surface [ETN-87-90575] p 52 NEB-11002 The aeromechanicalresponse of an advanced transonic [SAE PAPER 8710201 p 15 A88-13096 Investment foundry melting stock. Rolls Royce compressor to inkt distortion requirements and demands in terms of quality and the [ASME PAPER 87-GT-1891 p 31 A88-1to94 relationship to end product performance FORTRAN G [PNR90397] p 52 N88-I 1003 Self-adjusting flight electronics (SAFE) Turbine Engine Hot Section Technology. 1985 p 49 A88-12697 GAS DYNAMICS [NASA-CP-2405] p 53 NEB-11140 Plume infrared signature measurements and comparison The performance estimation of transonic turbine at The development of a high temperaturestatic strain gage with a theoretical model ... of turboshaft engines design and off-designconditions system p 53 N88-11142 p 33 A88712836 [ASME PAPER 87-GT-1481 p 30 A88-11066 The Lewis Strain Gauge Laboratory: Status and plans FOURIER SERIES GAS FLOW p 54 N88-11146 On predicting the resonant response of bladed disk Necessary optirnality conditions for three-dimensional Fuel-injectorlair-swirlcharacterization assemblies bodies in supersonic gas flow p2 A88-10300 p 54 N88-11150 [ASME PAPER 87-GT-1581 p 30 A88-11070 Numerical solution of coupled problems of supersonic Combustor-diffuserinteraction program FRACTURE MECHANICS flow past deformable shells of finite thickness p 35 N88-11152 Elevated temperature crack growth p13 A88-11280 Dilution jet mixing program, phase 3 p 55 N88-11174 p 54 N88-11153 GAS INJECTION Composite structural materials On the ,mixing of a row of jets with a confined Labyrinth seal flow measurement by tracer gas [NASA-CR-181416] p 56 N88-11186 crossflow p 54 NEB-11154 injection FRACTURESTRENGTH Coolant passage heat transfer with rotation Stress intensity faclors and residual strength of a [ASME PAPER 87-GT-1871 p 47 A88-11092 p 54 N88-11160 cracked stiffened panel p50 A88-13083 GAS TEMPERATURE Heat transfer with very high free stream turbulence FREE JETS A trace gas technique to study mixing in a turbine p 54 N88-11161 Heat transfer with very high free stream turbulence stage Prediction of turbine blade heat transfer p 54 NEB-1 1161 [ASME PAPER 87-GT-1181 p 5 A88-11046 p54 N88-11162 FREE MOLECULAR FLOW GAS TURBINE ENGINES Flow in a model turbine stator p 55 N88-11163 Analysis of free molecular effects on the attitude of Flight characteristics of aircraft with gas-turbine engines 3D inelastic analysis methods for hot section satellites in geostationary transfer orbit. Part 2 Force and --- Russian book p 23 A88-10049 components p 55 N88-11164 torque measurement in free molecular wind tunnel tests Compressor turbine vane ring (PT6 engine) repair 3-D inelastic analysis methods for hot section [ DFVLR-IB-222-86-A-071 p40 N88-10078 development components p60 N88-11165 FREQUENCYCONTROL [ASME PAPER 87-GT-471 p 29 A88-10999 Component specific modeling p 60 N88-11166 Force commutated direct frequency changers for Prediction of NO and CO distribution in aas turbine Constitutive modeling of superalloy single crystals with aerospace power applications p 48 A88-I 1825 combustors verification testing p 43 N88-11169 FREQUENCY MODULATION [ASME PAPER 87-GT-631 p 41 A88-11010 High temperature stress-strain analysis On predicting the resonant response of bladed disk Development of ceramic hot section components for p 55 N88-11170 assemblies AGT 100 gas turbine Constitutive modeling for isotropic materials [ASME PAPER 87-GT-1581 p 30 A88-11070 [ASME PAPER 87-GT-791 p 45 A88-11019 p55 N88-11171 FREQUENCYRESPONSE Numerical solution of three-dimensional turbulent flows Constitutive modeling for isotropic materials Effect of fluid inertia on the perlormame of squeeze for modern gas tutbine components p 55 N88-11172 film damper supported rotors Creep fatigue life prediction for engine hot section [ASME PAPER 87-GT-841 p 4 A88-11024 [ASME PAPER 87-GT-2201 p 48 A88-11117 materials (isotropic): Third year progress review FRICTION A qualitative method for determining the temperature p 55 NEB-t 1173 pattern run gas turbine blades Friction damping of random vibration in gas turbine of Elevated temperature crack growth [ASME PAPER 87-GT-1021 p 45 A88-11037 engine airfoils p 55 N88-11174 [ASME PAPER 87-GT-441 p29 A88-10996 Current gas turbine combustion and fuels research and Life prediction and constitutive models for engine hot FRICTION FACTOR development section anisotropic materials program Analysis of windage losses and velocity distribution for [ASME PAPER 87-GT-1071 p 30 A88-11039 p 56 NEB-11175 a shrouded rotating disk Thermodynamics and performance projections for Experimental verification of vapor deposition rate theory [ASME PAPER 87-GT-1861 p6 A88-11091 interc~1edlreheatlrecuperat~gas turbine systems in high velocity burner rigs p43 N88-11179 FUEL COMBUSTION [ASME PAPER 87-GT-1081 p 46 A88-11040 Thermal expansion mismatch and oxidation in thermal Prediction of combustion performance of aviation Computer prediitis of erosion damage in gas banier coatings p56 NEB-11182 kerosines using a novel premixed flame technique turbines Thermal barrier coating life prediction model [ASME PAPER 87-GT-1251 p 41 A88-11052 [ASME PAPER 87-GT-1271 p 46 A88-11054 development p 56 N88-11183

A-1 1 GAS TURBINES SUBJECT INDEX

GAS TURBINES GUSTS HEAT TRANSFER COEFFICIENTS Friction damping of random vibration in gas turbine Atmospheric turbulence and gust on the performance Use of a liquid-crystal and heater-element composite engine airfoils of a Wortmann FX 63-137 wing p9 A88-11185 for quantitative, high-resolution heat-transfer coefficients [ASME PAPER 87-GT-441 p 29 A88-10996 Analyses and assessments of span wise gust gradient on a turbine airfoil including turbulence and Pack cementation coatings for superalloys - A review data from NASA 8-576 aircraft surface-roughnesseffects p 44 A88-10969 of histwy. theory. and practice [NASA-CR-178288] p 15 N88-10007 Application of the transient test technique to measure [ASME PAPER 87-GT-501 p41 AM-11002 GYROCOMPASSES local heat transfer coefficientsassociated with augmented Effect of rib angle on local heallmass transfer Inertial navigation - Technological status and airfoil cooling passages distribution in a two-pass rib-roughened channel development trends p 20 A88-10682 [ASME PAPER 87-GT-2121 p47 A88-11112 Heat transfer with very high free stream turbulence lASME PAPER 87-GT-941 p 45 A88-11033 GYROSCOPES p 54 N88-11161 The performance estimation of transonic turbine at A 1987 progress report of manufacturing techniques for HEAT TRANSMISSION design and offdesign conditions Gravity Probe B gyroscope rotors Time-averaged heat-flux distributions and comparison [ASME PAPER 87-GT-1481 p 30 A88-11066 [ NASA-TM-100312 I p 53 N86-11101 Comparison of predicted and measured velocities in a with prediction for the Teledyne 702 HP turbine stage compressor disk drum model [ASME PAPER 87-GT-1201 p 30 A88-11048 [ASME PAPER 87-GT-208) p 47 A88-11109 HELICOPTER DESIGN A study of the effects of thermal barrier coating surface H New Soviet helicopter technology and its potential for roughness on the boundary layer characteristics of industrial use p 1 A88-10657 HANG GLIDERS gas-turbine aerofoils Anti-tank helicopters lor the rich and not so rich An experimental investigation of the aerodynamics of [ASME PAPER 87-GT-2231 p48 A88-11120 p 1 A88-10877 the hang glider pll A88-11200 A trade-off study of rotor tip clearance flow in a Composite directions at Kaman p 41 A68-12414 turbinelexhaust diffuser system HEAD-UP DISPLAYS Prepare lor the 21st century - The 1987 Alexander A. [ASME PAPER 87-GT-2291 p 32 A88-11123 The advantages of a primary flight display Nikolsky Lecture --- examples of future design possibilities Inter and intra blade row laser velocimetry studies of [SAE PAPER 8617301 p 58 A88-10162 of helicopters p24 A88-12645 gas turbine compressor flows Improvements in aircraft safety and operational Integration of dynamic, aerodynamic and structural [ASME PAPER 87-GT-2351 p7 A88-11126 dependability from a projected flight path guidance optimization of helicopter rotor blades Gas turbine exhaust systems . Design considerations display [NASA-CR-1814411 p 16 N88-10012 [ASME PAPER 87-GT-2381 p32 A88-11128 [SAE PAPER 8617321 p 35 A88-10163 HELICOPTER PERFORMANCE Comparison 01 different kinds of compact cross flow The deviation of light rays passing through a curved New Soviet helicopter technology and its potential for heat exchangers windscreen --- aircraft industrial use p 1 A88-10657 [DFVLR-FB-86-631 p 51 N88-10305 [BAE-MSC.l15] p 62 NEB-10610 An Observer aooroach to the estimation of helicooter Development of a statistilly proven injection molding HEAT EXCHANGERS airspeed method for reaction bonded silicon nitride, sintering Comparison of different kinds of compact cross flow [ DFVLR-FB-87-131 p25 N88-10029 reaction bonded silicon nitride. and sintered silicon heat exchangers HELICOPTERS nitride [DFVLR-FB-86-63] p 51 N88-10305 Aircraft acoustics I . Exterior noise of subsonic [ETN-87-90575] p 52 N66-11002 HEAT FLUX passenger aircraft and helicopters --- Russian book GENERAL AVIATION AIRCRAFT Procedures for determining surface heat flux using thin p 61 A88-10047 Fliiht test results for a GPS receiver in a helicopter film gauges on a coated metal model in a transient test Building on a successful tradition - Composites at and ibusiness aircraft p 22 A88-13094 facility MDHC p 41 A88-12415 Wind-tunnel investigation of a full-scale general aviation [ASME PAPER 87-GT-951 p 45 A86-11034 Flight test results for a GPS receiver in a helicopter airplane equipped with an advanced natural laminar flow Time-averaged heat-flux distributions and comparison and a business aircraft p 22 A88-13094 wing with prediction for the Teledyne 702 HP turbine stage Detection of targets in the presence of clutter using [NASA-TP-2772] p 16 N88-10009 target echo modulations caused by rotating structures [ASME PAPER 87-GT-1201 p 30 A88-11048 Aircraft accident reports, brief format, US civil and foreign [REPT-12-86] p 50 N88-10231 Development of heat flux sensors for turbine airfoils aviation. Issue number 1: 1986 accidents Analytical modeling of helicopter static and dynamic p 54 N88-11143 [ PB87-9169031 p 19 N88-10781 induced velocity in GRASP GLIDERS HEAT PIPES [ NASA-TM-1000261 p 18 N88-10777 The use of wind tunnel data in the design of radio Experimental method for the combustion efficiency Global positioning satellite-based automatic landing controlled contest model sailplanes p 24 A88-11195 calculation in a reheat duct system and wind estimated feedback for the AH-64 GLIDING [ASME PAPER 87-GT-901 p 29 A88-11029 helicopter p 22 N88-10784 The aerodynamics of gliding parachutes HEAT RESISTANT ALLOYS Improved oil-off survivability of tapered roller bearings p 11 A88-11201 The effect of variations of cobalt content on the cyclic [ NASA-CR-1808041 p 53 NEB-11135 The performance of model aircraft using flow oxidation resistance of selected Ni-base superalloys Helicopter main-rotor speed effects on far-fieldacoustic invigorators, gliding in the critical range of Reynolds p 40 A88-10031 levels number p12 A88-11206 Pack cementation coatings for superalloys . A review [ NASA-TM-1005121 p 62 NEB-11451 GLOBAL POSITIONING SYSTEM of histofy. theory, and practice HEURISTIC METHODS An overview of space and aircraft navigation [ASME PAPER 87-GT-501 p41 A88-11002 An expert system for aircraft conflict resolution in dense p 40 A88-13086 Conference on Mechanical Behaviour of Superalloys. airspaces p 22 N88-10810 A hybrid navigation system with GPS London, England, June 10. 11, 1986, Selected Papers HIGH ALTITUDE p 21 A88-13087 p 42 A88-12626 Investigation of high-altitude ignition performance of CivilaviationapplicationoftheGlobal PositioningSystem Basic concepts for bener heat protection systems several Chinese jet fuels with different properties (GPS) and its issues p 22 A88-13088 p 42 A88-12786 [ASME PAPER 87-GT-1781 p 41 A88-11086 HIGH REYNOLDS NUMBER GPSf INS hybrid navigation for aircraft The development of a high temperaturestatic strain gage p22 A88-13090 system p53 NM-11142 The effect of grit roughness on the performance of the GPS receivers for air navigation p 22 A88-13093 Wortmann FX63-137 airfoil at a chord Reynolds number Fliiht test results for a GPS receiver in a helicopter Constitutive modeling of superalloy single crystals with Of 100,Ooo p 11 A88-11202 verification testing p 43 N88-11169 and a business aircraft p 22 A88-13094 Selection of aerofoil sections for use in man-powered Global positioning satellite-based automatic landing Constitutive modeling for isotropic materials aircraft p 12 A88-11207 system and wind estimated feedback for the AH44 p 55 N88-11171 Wall interference tests of a CAST 10-2/DOA 2 airfoil helicopter p 22 N88-10784 Constilulive modeling for isotropic materials in an adaptive-wall test section GOVERNMENTllNDUSTRY RELATIONS p 55 N88-11172 [NASA-TM-4015] p 18 N88-10772 The United Kingdom engine technology demonstrator HEAT TRANSFER HIGH STRENGTH ALLOYS programme Use of a liquid-crystal and heater-element composite Conference on Mechanical Behaviour of Superalloys, [ASME PAPER 87-GT-2033 p31 A88-11107 for quantitative, high-resolution heat-transfer coefficients London, England, June 10, 11, 1986. Selected Papers GRAIN SIZE on a turbine airfoil including turbulence and p 42 AM-12626 Particle transpwt across the transpired turbulent surface-roughnesseffects p44 A88-10969 Developments in disc materials --- for gas turbine boundary layer Effect of rib angle on local heallmass transfer engines p 42 A88-12632 [ASME PAPER 87-GT-2651 p 48 A88-11142 distribution in a two-pass rib-roughened channel HIGH STRENGTH STEELS GRAVITY PROBE B [ASME PAPER 87-GT-941 p 45 A88-11033 The fatigue properties of aerospace steels under A 1987 progress report of manufacturingtechniques for Effects of channel aspect ratio on heat transfer in constant amplitude and flight-by-flight simulated loading Gravity Probe B gyroscope rotm rectangular passage sharp 18Odeg turns [ BAE-MSM-R-GEN-05661 p 51 N88-10377 [ NASA-TM-1003121 p53 NEE-11101 [ASME PAPER 87-GT-1131 p46 AM-11041 HIGH TEMPERATURE High temperature metal matrix composites for future GRIT Heat transfer to arrays of impinging jets in a crossflow The effect of grit roughness on the performance of the [ASME PAPER 87-GT-1981 p 47 A88-11102 aerospace systems Wortmann FX63-137 airfoil at a chord Reynolds number [NASA-TM-100212] p 43 N88-10938 Modeling and measurement of heat transfer on turbine Of 100,ooo p 11 A88-11202 High temperature stress-strain analysis blade tips p33 NEB-10032 GROUND EFFECT (AERODYNAMICS) p 55 N88-11170 Oispedn in the wake 01 aircraft: An investigation of The aerothermodynamic environment for holes in Elevated temperalure crack growth the effects of a ground plane on trailing vortices. Literature hypersonic configurations p 55 N88-11174 Survey [DE87-014651] p 17 N88-10767 HIGH TEMPERATURE GASES [IGAERO-REP-86-041 p 16 N88-10014 Coolant passage heat transfer with rotation Analysis of supersonic heterogeneous flow impinging GUST LOADS p54 N88-11160 on an obstacle p 14 A88-12074 Flutter suppression and gust load alleviation. Parl 1 : Prediction of turbine blade heat transfer HIGHLY MANEUVERABLE AIRCRAFT Results of phase 1 to 3. Part 2 Description of the Garleur p 54 N88-11162 HiMAT flight program: Test results and program model Flow in a model turbine stator p 55 N88-11163 assessment overview [MBB-LKE292ISlPUBI191] p 36 N88-10038 Component specific modeling p 60 N88-11166 [NASA-TM-867251 p24 NEB-10026

A-12 SUBJECT INDEX JET ENGINES

HISTORIES Arguments for electro-optical reconnaissance systems INSTALLING The history of aeroelasticity research in Germany from p 27 A88-12749 Advanced turboprop wing installation effects measured the beginning until 1945 --- airframes IMPACT TESTS by unsteady blade pressure and noise [DFVLR-MITT-86-25] p 1 N88-10003 Full-scale transmrt controlled imDact demonstration [NASA-TM-100200] p 15 N88-10008 HOLE GEOMETRY (MECHANICS) program INTEGRALS Film cooling of a turbine blade with injection through [NASA-TM-89642] p 19 N88-10021 Elevated temperature crack growth two rows of holes in the near-endwall region IMPINGEMENT p 55 N88-11174 [ASME PAPER 87-GT-1961 p 47 A88-11100 Computer predictions of erosion damage in gas INTERACTIONAL AERODYNAMICS HOLOGRAPHIC INTERFEROMETRY turbines Navier-Stokes simulations of rotorlstator interaction Development and implementation of an aerodynamic [ASME PAPER 87-GT-1271 p 46 A88-11054 using patched and overlaid grids p 2 A88-10354 holographic interferometry system p 49 A88-12725 IN-FLIGHT MONITORING Timeaveraged heat-flux distnbutions and Comparison Flight characteristics of aircraft with gas-turbine engines Optical flow diagnostic measurements in with prediction for the Teledyne 702 HP turbine stage Russian book p A88-10049 turbomachinery --- 23 [ASME PAPER 87-GT-1201 p 30 A88-11048 FDA0 .A lablfield test tool __.Flight Data Analysis and [PNR90396] p 52 N88-11081 The calculation of flow about aerofoils at low Reynolds Display p 25 A88-10436 number with application remotely piloted vehicles HORIZONTAL TAIL SURFACES Implementation of a research prototype onboard fault to p 11 A88-11197 Advanced composite horizontal stabilizer for monitoring and diagnosis system next-generation commercial aircraft p 24 A88-13081 [AIM PAPER 87-27771 p 59 A88-12540 Viscidlinviscidinteraction analysis of subsonic turbulent HOT CORROSION INCIDENCE trailing-edge flows p 14 A88-12282 Pack cementation coatings for superalloys - A review Experimentalstudy of three-dimensionalseparated flow INTERMETALLICS of history. theory, and practice surrounding a hemisphere-cylinder at incidence High temperature metal matrix composites for future [ASME PAPER 87-GT-501 p 41 A88-11002 [AIAA PAPER 87-24921 p 3 A88-10498 aerospace systems Experimentalverification of vapor deposition rate theory INCOMPRESSIBLE FLOW [ NASA-TM-10021 21 p 43 NEB-10938 in high velocity burner rigs p 43 N88-111 79 A numerical method for subsonic unsteady lifting INTERNALPRESSURE

HOVERING surfaces - BIS. 111 ~ Some additional numerical results Elastic buckling of internally pressurized Detection of targets in the presence of clutter using p2 A88-10093 cylinder-bulkhead combinations p 50 A88-12949 target echo modulations caused by rotating structures A new method of calculating optimum velocity INTERNATIONAL COOPERATION [REPT-12-86] p 50 N88-10231 distribution along the blade surface on arbitrary stream The will to European unity as exemplified by A320 HYBRID NAVIGATION SYSTEMS surface of revolution in turbomachines p 23 A88-10659 Hybrid positioning and navigation systems - [ASME PAPER 87-GT-301 p4 A88-10991 Development studies 01 a European data network for Technological status and development trends in Numerical prediction of turbulent flow in rotating acquisition, processing, and display of air-traffic data position-finding and navigation procedures cavities p 21 A88-10688 [ASME PAPER 87-GT-741 p 45 A88-11018 p20 A88-10684 INVESTMENT CASTING Optimal information processing lor sensors and sensor Unified equation of motion (UEM) approach as applied Investment foundry melting stock. Rolls Royce systems - The case 01 radar sensors p 26 AM-10685 to S1 turbomachinery problems requirements and demands in terms of quality and the [ASME PAPER 87-GT-1791 p A88-11087 A hybrid navigation system with GPS 6 relationship to end product performance p 21 A88-13087 INDUCTION MOTORS [PNR90397] p 52 N88-11003 Process support compressor motor electromagnetic GPS/INS hybrid navigation for aircraft INVISCID FLOW design summary p22 A88-13090 Explicit multigrid algorithm for quasi-three-dimensional [ DE874143591 p 52 N88-11048 HYDRODYNAMICS INDUSTRIES viscous flows in turbomachinery p2 A88-10355 Problems in continuum mechanics mth mixed boundary New Soviet helicopter technology and its potential for Shock embedding discontinuous solution of elliptic conditions Russian book p 43 A88-10017 ___ industrial use p 1 A88-10657 equation for inverse problem of transonic 52 flow HYDROGEN-BASED ENERGY INELASTIC STRESS [ASME PAPER 87-GT-1151 p5 A88-11043 Hydrogen in air transportation - Feasibility study for Constitutive modeling of superalloy single crystals with A discussion of the mean S2 stream surfaces applied Zurich Airport, Switzerland p41 AM-11146 verification testing p 43 N88-11169 to quasi-three-dimensional calculation programs for HYPERSONIC FLIGHT INERTIA turbomachinery design An Orient Express to capture the market [ASME PAPER 87-GT-1501 p5 A88-11067 p 1 A88-10370 Effect of fluid inertia on the performance of squeeze Numerical computation of non-isentropic potential Multimodes to Mach 5 p 28 A88-10371 film damper supported rotors equations for transonic cascade flows The scramjet - Toward Mach 4-25 flight [ASME PAPER 87-GT-2201 p 48 A88-11117 [ASME PAPER 87-GT-1591 p 5 A88-11071 p 33 A88-13095 INERTIAL NAVIGATION HYPERSONIC FLOW Inertial navigation - Technological status and The base pressure and loss of a family of four turbine The aerothermodynamic environment for holes in development trends p 20 A88-10682 blades hypersonic configurations GPSlINS hybrid navigation for aircraft [ASME PAPER 87-GT-2021 p7 A88-11106 [DE87-014651] p 17 N88-10767 p22 A88-13090 An analysis of unsteady, two-dimensional separation HYPERSONIC VEHICLES Test equipment with fiber optic data bus and laser gyro bubbles p9 A88-11182 The aerothermodynamic environment for holes in strapdown system LTN-90 for the helicopter 60-105 The calculation of flow about aerofoils at low Reynolds hypersonic configurations [ESA-l-r-1038] p 22 N88-10025 number with application to remotely piloted vehicles [DE87-014651] p 17 N88-10767 INFORMATION DISSEMINATION p 11 A88-11197 HYPERVELOCITY WIND TUNNELS Development studies of a European data network for Transonic expansions p 13 A88-12059 Experience about the application and valuation of acquisition, processing, and display of air-traffic data Refined numerical solution of the transonic flow past a roughness strips for boundary layer transition control in p21 A88-10688 wedge p 14 A88-12280 wind tunnel tests in the high-speed range INFORMATION SYSTEMS ISOTHERMAL FLOW [ ESA-lT-10281 p 51 N88-10278 Traditional versus rule-based programming techniques Numerical prediction of tu~bulent flow in rotating cavities - Application to the control of optional flight information [ASME PAPER 87-GT-741 p 45 A88-11018 p 58 A88-10965 I ITERATIVE SOLUTION INFRARED DETECTORS Initial user experience with an artificial intelligence ICE FORMATION Test of IR mays on the Kuiper Airborne Observatory program for the preliminary deslgn of centrifugal p 49 A88-12838 The dependence of the normalized ice accretion compressors thickness on cloud-physical parameters An uncooled linescan thermal imager for ground and [ASME PAPER 87-GT-2171 p 58 A88-11115 [ DFVLR-FB-87-06I p57 N88-10464 airborne use p 49 A88-12840 ICE PREVENTION INFRARED IMAGERY Boundary layer profile investigations downstream of an Recent developments in infrared data processing J aero-engine intake anti-icing air exhaust slot p 28 A88-12751 [ PNR903781 p 52 N88-11080 An uncooled linescan thermal imager for ground and JET AIRCRAFT IDEAL GAS airborne use p 49 A88-12840 The Antonov An-74 brings high tech to low Stability of supersonic flow of an ideal gas with a head A compact high performance thermal imager temperatures p 23 A88-10876 shock wave past cylindrical channels and cavities p50 AM-12843 Effect of empennage arrangement on single-engine p13 A88-12065 noalelatterbody slam pressures at transonic speeds Optimal lifting wings with required longitudinal balancing INFRARED SIGNATURES [ NASA-TP-27531 p 17 NEB-10771 characteristics p 14 A88-12075 Plume infrared signature measurements and Comparison JET ENGINE FUELS with a theoretical model of turboshaft engines IGNITION --- Investigation of high-altitude ignition performance of Investigation of high-altitude ignition performance of p 33 A88-12836 several Chinese jet fuels with different properties several Chinese jet fuels with different properties INJECTION MOLDING [ASME PAPER 87-GT-1781 p 41 A88-11086 [ASME PAPER 87-GT-1781 p 41 A88-11086 Development of a statistically proven injection molding JET ENGINES IMAGE PROCESSING method for reaction bonded silicon nitride. sintering Oftdesign performance of supersonic compressorswith Recent developments in infrared data processing reaction bonded silicon nitride, and sintered silicon fixed and vanable geometry p 28 A88-12751 nitride [ASME PAPER 87-GT-1161 p5 A88-11044 A compact high performance thermal imager [ETN-87-90575] p 52 N88-11002 First article test noise survey of the AlF32T-9 large turbo p50 A88-12843 INJECTORS fan engine enclosed noise suppressor system, Sky Harbor IMAGING TECHNIQUES Fuel-injectorlair-smrlcharacterization IAP (Internamnal Airport). Phoenix, Anzona Magnetic recording for near real time reconnaissance p 54 N88-11150 [AD-A1837991 p 61 N88-10588 applications p 27 A88-12736 INLET FLOW Effect of empennage arrangement on single-engine Imaging through the atmosphere for airborne Combustordiffuser interaction program noalelafterbcdy static pressures at transonic speeds reconnaissance p27 AM-12748 p 35 N88-11152 [NASA-TP-27531 p 17 N88-10771

A-13 JET MIXING FLOW SUBJECT INDEX

The use of Kevlar on aero-engine fan containment Airspeed measurement with a C02 lidar LOSSES casings p 26 A88-12655 Blade loss transient dynamics analysis, volume 1. Task [ PNR904101 p 53 N88-11134 LASERGYROSCOPES 2: TETRA 2 theoretical development JET MIXING FLOW Test equipment with liber optic data bus and laser gyro [NASA-CR-l796321 p 34 N88-10791 Dilution jet mixing program. phase 3 strapdown system LTN-90 for the helicopter 80-105 Blade loss transient dynamics analysis. volume 2. Task p 54 N88-11153 [ ESA-TT-10381 p 22 N88-10025 2: TETRA 2 user's manual On the mixing of a row of jets with a confined LASER INTERFEROMETRY [ NASA-CR-1796331 p 34 NEB-10792 CrOSSlloW p 54 N88-111 54 Optical flow diagnostic measurements in LOW ALTITUDE JP-8 JET FUEL turbomachinery 6-1B combines brisk low-altitudehandling, morecapable Cost savings possible with Air Force conversion to JP-8 [PNR90396] p 52 N88-11081 avionics p 23 A88-10675 as its primary fuel LATERAL CONTROL Dispersion in the wake of aircraft An investigation of [AD-A183784] p 42 N88-10192 Design study for an FEW lateral control system the effects of a ground plane on trailing vortices. Literature p 36 A88-13080 Survey K Investigation of interactions between limb-manipulator [ IC-AERO-REP-86-04] p 16 N88-10014 dynamics and effective vehicle roll control LOW ASPECT RATIO WINGS KALMAN FILTERS characteristics The flow visualization on the rotary wing with low aspect Hybrid positioning and navigation systems - [ NASA-CR-39831 p 36 N88-10039 ratio p2 A88-10094 I Technological status and development trends in A preliminary investigation into the feasibility of LOW COST position-finding and navigation procedures implementinga direct sideforce control system on the Astra Low cost windowless cockpit research vehicle D 20 A88-10684 Hawk by means of an active control surface --- aircraft [SAE PAPER 8617551 p 39 A88-10156 KERNEL FUNCTIONS control LOW REYNOLDS NUMBER A numerical method for subsonic unsteady lifting [ ETN-87-909241 p 37 N88-10795 Prediction of turbulent source flow between corotating surfaces - BIS 111 - Some additional numencal results LEADING EDGES disks with an anisotropic two-equation turbulence model p2 A88-10093 Boundary layer profile investigations downstream of an [ASME PAPER 87-GT-731 p45 A88-11017 KEROSENE aero-engine intake anti-icing air exhaust slot Prediction of combustion performance of aviation [ASME PAPER 87-GT-2371 p 32 A88-11127 Aerodynamics at low Reynolds numbers Re greater than kerosines using a novel premixed flame technique The structure of separated flow regions occurring near 10 to the 4th and less than 10 to the 6th; Proceedings I [ASME PAPER 87-GT-1251 p 41 A88-11052 the leading edge of airfoils including transition of the International Conference. London, England, Oct. KEVLAR (TRADEMARK) [ NASA-CR-1814341 p 16 N88-10011 15-18. 1986. Volumes 1. 2, 8 3 p 8 A88-11176 The use of Kevlar on aero-engine fan containment LIFE (DURABILITY) Aerodynamics at low Reynolds numbers - A review of casings A qualitative method for determining the temperature theoretical and experimental research at Delft University [PNR90410] p 53 N88-11134 pattern of run gas turbine blades of Technology p8 A88-11177 KINETIC ENERGY [ASME PAPER 87-GT-1021 p 45 A88-11037 A simple method for the prediction of separation bubble Force commutated direct frequency changers for formation on aerofoils at low Reynolds number aerospace power applications p 48 A88-11825 Life prediction and constitutive models for engine hot p 8 A88-11179 KNOWLEDGE section anisotropic materials program Towards the unmanned cockpit p 25 N88-10812 p 56 N88-I 1175 A theoretical study of spanwise-periodic 3-0 Thermal barrier coating life prediction model disturbances in the wake of a slightly stalled wing at low development p 56 N88-11183 Reynolds numbers p8 A88-11180 L Thermal barrier coating life prediction model A smoke-wire study of low Reynolds number flow over development p 56 N88-11185 a NASA LRN(1) - 1007 airfoil section p 9 A88-I 1181 LABORATORIES LIFE CYCLE COSTS The Lewis Strain Gauge Laboratory: Status and plans An analysis of unsteady, two-dimensional separation Applied reliabilitylmaintainability methodology as a bubbles p9 A88-11182 p 54 N88-11146 function within life cycle cost --- of aircraft turbine engine LABYRINTH SEALS [ASME PAPER 87-GT-1721 p 46 A88-11082 Low Reynolds number airfoil design at the Douglas Aircraft Company p9 A88-11183 Labyrinth seal llow measurement by tracer gas LIFT injection On massive laminar separation and lift anomalies in Boundary layer and performance characteristics from [ASME PAPER 87-GT-1871 p 47 A88-11092 subcritical Re-range p8 A88-11178 wind tunnel tests of a low Reynolds number Liebeck LAMINAR BOUNDARY LAYER Exact and asymptotic expressions of the lift slope airfoil p9 A88-11184 A smoke-wire study of low Reynolds number flow over Transition and separation control on a low-Reynolds a NASA LRN(1). 1007 airfoil section p 9 A88-11181 coefficient of an elliptic wing p 14 A88-12292 number airfoil p9 A88-11186 Transition and separation control on a low-Reynolds On the prospects for increasing dynamic lift number airfoil p 9 A88-11186 [ RAE-TM-AERO-20681 p 17 N88-10018 Control surface effects on the low Reynolds number Smoke-wire and thin-film-gaugeobservations of laminar LIFT AUGMENTATION behavior of the Wortmann FX 63-137 separation bubbles on an NACA 23012-64 airfoil section On the prospects for increasing dynamic lift p 10 A88-11187 p 13 A88-11210 [ RAE-TM-AERO-20681 p 17 N88-10018 Recent developments in boundary layer computation LAMINAR FLOW LIFT DEVICES p 10 A88-11188 On massive laminar separation and lift anomalies in High-lift-device design and low-speed wind-tunnel test p 15 A88-13079 On some unsteady aerodynamics characteristics of an subcritical Re-range p8 A88-11178 LIFTING BODIES NACA 0012 at Reynolds numbers of 125,000 and A simple method for the prediction of separation bubble 400,000 p 10 A88-11189 A numerical method for subsonic unsteady lifting formation on aerofoils at low Reynolds number surfaces . BIS. 111 ~ Some additional numerical results Low Reynolds number wind tunnel measurements - The p8 A88-11179 p 2 A88-10093 importance of being earnest p10 A88-11190 A theoretical study of spanwise-periodic 3-0 LIGHT AIRCRAFT Recent developments in the calculation of flow over low disturbances in the wake of a slightly stalled wing at low Recent wind tunnel experiments at low Reynolds Reynolds-number airfoils p 10 A88-11191 Reynolds numbers p8 A88-11180 numbers p 11 A88-11193 On the determination of the 2-0 characteristics of Low Reynolds number airfoil design at the Douglas Prediction of a microlight biplane'saerofoil performance aerofoils at low Reynolds numbers p 10 A88-11192 Aircraft Company p9 A88-11183 using a computer model p 11 A88-11198 Observations and analyses 01 natural laminar flow over Selection of aerofoil sections for use in man-powered Recent wind tunnel experiments at low Reynolds a nonlifting airframe surface aircraft p 12 A88-11207 numbers p 11 A88-11193 [SAE PAPER 8710201 p 15 A88-13096 LIGHT BEAMS Low-Reynoldsnumber aerodynamics research at NASA LAMINAR FLOW AIRFOILS The deviation of light rays passing through a curved Langley Research Center p 11 A88-11194 Wind-tunnel investigation of a full-scale general aviation windscreen --- aircraft The calculation of flow about aerofoils at low Reynolds airplane equipped wth an advanced natural laminar flow [BAE-MSC.115] p 62 N88-10610 number with application to remotely piloted vehicles wing LINEAR ARRAYS p 11 A88-11197 [NASA-TP-2772] p 16 N88-10009 An uncooled linescan thermal imager for ground and International Conference on the Aerodynamics at Low airborne use p 49 A88-12840 I LANDING GEAR LINEAR FILTERS Reynolds Numbers between lO(4) and IO@) Some topics on aircraft landing gear design [ONRL-7-023-C] p 16 N88-10010 p 24 A88-13085 Fast stable solution of a dispersion equation of linear filtering for flight vehicle radar system LOW SPEED LASER ANEMOMETERS --- p 21 A88-10728 Low altitude/airspeed unmanned research aircraft Characterizationof shock wave end wall boundary layer (LAURA) preliminary development p 12 A88-11205 interactions in a transonic compressor rotor LINEAR QUADRATIC REGULATOR [ASME PAPER 87-GT-1661 p 6 A88-11077 The design of a turboshaft speed governor using modern On the prospects for increasing dynamic lift control techniques [ RAE-TM-AERO-20681 p17 N88-10018 Optical flow diagnostic measurements in [ NASA-CR-1750461 p 51 N88-10339 LOW TEMPERATURE ENVIRONMENTS turbomachinery LININGS [PNR90396] p 52 N88-11081 The Antonov An-74 brings high tech to low Turbine Engine Hot Section Technology, 1985 temperatures p 23 A88-10876 LASER APPLICATIONS [ NASA-CP-24051 p 53 N88-11140 NDE at twelve o'clock high p 48 A88-11585 LlOUlD CRYSTALS LUBRICANT TESTS LASER DOPPLER VELOCIMETERS Use of a liquidcrystal and heater-element composite Neutron and positron techniques for fluid transfer system Comparison of predicted and measured velocities in a for quantitative, high-resolution heat-transfer coefficients analysis and remote temperature and stress compressor disk dNm model on a turbine airfoil including turbulence and measurement [ASME PAPER 87-GT-2081 p47 A88-11109 surface-roughnesseffects p 44 A88-10969 [ASME PAPER 87-GT-2191 p 48 A88-11116 Inter and intra blade row laser velocimetry studies of LlOUlD HYDROGEN LUBRICATION gas turbine compressor flows Hydrogen in air transportation - Feasibility study for Improved oil-off survivability of tapered roller bearings [ASME PAPER 87-GT-2351 p7 A88-11126 Zurich Airport, Switzerland p 41 A88-11146 [ NASA-CR-1808041 p 53 N88-11135

A-14 SUBJECT INDEX NICKEL ALLOYS

M A mathematical multi-point model for aircraft motion in MODAL RESPONSE moving air p 36 A88-12487 An opbmal control method for passage of a flexible rotor MACH NUMBER Contributions to the modeling of wind shear for danger through resonances p 48 A88-11439 Initial user experience with an artificial intelligence studies MODELS .-Drwram for the oreliminarv.~ desian of centrifuaal [ETN-87-90442] p 57 N88-10463 Modeling and measurement of heat transfer on turbine compressors Impact of turbulence modeling on numerical accuracy blade tips p 33 N88-10032 [ASME PAPER 87-GT-2171 p58 A88-11115 and efficiency of compressible flow simulations Reliability modeling of fault-tolerant computer based Theoretical and extmrimental analvsis of a comoressor [NASA-TM-88333] p 52 NEB-11088 systems p 37 N88-10801 Turbine Engine Hot Section Technology, 1985 cascade at supercritical flow conditions MOMENTUM TRANSFER [ NASA-CP-24051 p 53 "3-1 1140 [ASME PAPER 87-GT-256) p8 A88-11136 Momentum exchanges and energy transfers in cross Life prediction and constitutive models for engine hot MAGNETIC PROPERTIES flow fans section anisotropic materials program A qualitative method for determining the temperature [ASME PAPER 87-GT-321 p 44 A88-10992 pattern of run gas turbine blades p 56 N88-11175 MONOTONE FUNCTIONS [ASME PAPER 87-GT-1021 p 45 A88-11037 Thermal barrier coating life prediction model MAGNETIC RECORDING development p 56 N88-11185 Software reliability models for fault-tolerant avionics computers and related topics Magnetic recording for near real time reconnaissance Software reliability models for fault-tolerant avionics [ NASA-CR-1814401 p 60 N88-11382 applications p 27 A88-12736 computers and related topics MAINTAINABILITY [ NASA-CR-1814401 p 60 N88-11382 MULTIPHASE FLOW Electronic trend monitoring and exceedance recording MEASURING INSTRUMENTS Stability of conical and curved annular diffusers for systems - A means to improved turbine engine reliability A model to determine the behaviour of a pressure mixed-flow compressors [ASME PAPER 87-GT-871 p 29 A88-11027 measurement equipment during non-static operations of [ASME PAPER 87-GT-1911 p6 A88-11096 Applied reliabilitylmaintainability methodology as a gasturbine engines MULTIPROCESSING (COMPUTERS) function within life cycle cost --- of aircraft turbine engine [ASME PAPER 87-GT-1281 p 46 A88-11055 AOSP - Multiprocessor architecture and system [ASME PAPER 87-GT-1721 p 46 A88-11082 MECHANICAL PROPERTIES considerations MAN MACHINE SYSTEMS Conference on Mechanical Behaviour of Superalloys, [AIAA PAPER 87-2790) p 59 A88-12544 Versatile simulation testbsd for rotorcraft speech IlO London, England, June 10, 11, 1986, Selected Papers MUSCULAR FUNCTION system design p 42 A88-12626 Investigation of interactions between limb-manipulator [SAE PAPER 8616611 p 57 A88-10154 Mechanical properly requirements for aero gas turbine dynamics and effective vehicle roll control An integrated display for vertical situation awareness materials p 42 A88-12628 charactenstics in wmmercial transport aircraft METAL COATINGS [ NASA-CR-39831 p 36 N88-10039 [SAE PAPER 8617701 p 57 A88-10158 Compressor turbine vane ring (PT6 engine) repair Flying complex apprdach paths using the microwave development landing system [ASME PAPER 87-GT-471 p 29 A88-10999 N [SAE PAPER 8617711 p 35 A88-10159 METAL FATIGUE The advantages of a primary flight display Turbine Engine Hot Section Technology, 1985 NAVIER-STOKES EQUATION [SAE PAPER 8617301 p58 A88-10162 [ NASA-CP-24051 p 53 N88-11140 Navier-Stokes simulations of rotorlstator interaction The advantage of flightpathoriented situation displays METAL MATRIX COMPOSITES using patched and overlaid grids p 2 A88-10354 during microburst encounters High temperature metal matrix composites for future Explicit multigrid algorithm for quasi-three-dimensional [SAE PAPER 8617331 p 35 A88-10164 aerospace systems viscous flows in turbomachinery p2 A88-10355 [NASA-TM-t00212] p 43 N88-10938 A rule-based system for arrival sequencing and Cascade viscous flow analysis using the Navier-Stokes Composite structural materials scheduling in air traffic control p 22 N88-10815 equations p2 A88-10356 MAN POWERED AIRCRAFT [NASA-CR-1814161 p 56 N88-11186 Calculation of three-dimensional viscous flows in Selection of aerofoil sections for use in man-powered METAL POWDER turbomachinery with an implicit relaxation method aircraft p 12 A88-11207 Development and production of new and modified MANCOMPUTER INTERFACE powders for sprayed coatings and components for saving p2 A88-10357 Intelligent interlaces to aircraft systems important raw materials Paratalized Navier-Stokes analysis of ducted [AIAA PAPER 87-27761 p 59 A88-12539 [ BMFT-FB-T-86-1291 p 42 N88-10159 supersonic combustion problems p 2 A88-10361 MANAGEMENT METAL SHEETS Navier-Stokes solution for steady two-dimensional Issues in air transport and airport management High-temperature sheet materials for gas turbine transonic cascade flows [PB87-204509] p 19 N88-10782 applications p 42 A88-12635 [ASME PAPER 87-GT-541 p4 A88-11005 MANAGEMENTMETHODS METEOROLOGICAL SERVICES Application of advanced computational codes in the Cost savings possible with Air Force conversion to JP-8 Computing complex for a system for the radio-acoustic design of an experiment for a supersonic throughflow fan as its primary bel sounding of the atmosphere - Hardware facilities rotor [ AD-AI 837841 p42 N88-10192 p 58 A88-11394 [ASME PAPER 87-GT-1601 p6 AM-11072 MANEUVERS MICROBURSTS Calculation of a three-dimensional turbomachinery rotor Approach trajectory planning system for maximum The advantage of flightpath-oriented situation displays flow with a Navier-Stokes code concealment during microburst encounters [ASME PAPER 87-GT-2321 p7 A88-11125 [NASA-TM-88258] p 60 N88-11435 [SAE PAPER 8617331 p35 A88-10164 Computation of transonic separated wing flows using MANIFOLDS MICROPROCESSORS an EulerlNavier-Stokes zonal approach LabMnth seal flow measurement by tracer gas Electronic trend monitoring and exceedance recording [NASA-TM-66311] p 52 N88-11089 injection systems - A means to improved turbine engine reliability Flow in a model turbine stator p 55 N88-11163 [ASME PAPER 87-GT-1871 p 47 A88-11092 [ASME PAPER 87-GT-871 p 29 A88-11027 NAVIGATION AIDS MANUAL CONTROL The development of 270 Vdc solid state power Modern technology in positioning and navigation: Flying complex approach paths using the microwave controllers --- for advanced aircran electrical systems. Navigation Meeting. DUesSBldort. Federal Republic of landing system p 33 A88-11923 Germany, May 6-8. 1987, Reports p 20 A88-10676 [SAE PAPER 861771) p35 A88-10159 MICROWAVE LANDING SYSTEMS BMFT-supported projects in the fields position-finding, Comparison of programmable legend keyboard and Flying complex approach paths using the microwave navigation, and traffic safety p 20 A88-10677 dedicated keyboard for control of the flight management landing system The importance of modern positioning and navigation computer [SAE PAPER 861771 ] p 35 A88-10159 technology for ATC p 20 A88-10678 [SAE PAPER 8617721 p57 A88-10160 Flight director guidance for MLS p 21 A88-10874 Hybrid positioning and navigation systems ~ MANUFACTURING MILITARY AIRCRAFT Technological status and development trends in Pack cementation coatings for superalloys - A review Low wst windmviess cockpit research vehicle position-finding and navigation procedures of history. theory, and practice [SAE PAPER 8617551 p 39 A88-10156 p 20 A88-10684 [ASME PAPER 87-GT-501 p 41 A88-11002 Starting system for cold weather p 23 A88-10871 Civil aviationapplication of the Global PositioningSystem A 1987 progress report of manufacturingtechniques for The United Kingdom engine technology demonstrator (GPS) and its issues p 22 A88-13088 Gravity Probe B gyroscope rotors programme NAVIGATION SATELLITES [NASA-TM-100312] p 53 N88-11101 [ASME PAPER 87-GT-2031 p31 AM-11107 An overview of space and aircraft navigation MASS BALANCE Low altitude/ airspeed unmanned research aircraft p 40 A88-13086 Boundary layer profile investigations downstream of an (LAURA) preliminary development p 12 A88-11205 A hybrid navigation system with GPS aero-engine intake anti-icing air exhaust slot Composites technology in Army aviation p 21 A88-13087 [ASME PAPER 87-GT-2371 p32 A88-11127 p 24 A88-12413 NEUTRONS MASS TRANSFER Autonomous processing using a blackboard chipset Neutron and positron techniquesfor fluid transfer system Effect of rib angle on local heatlmass transfer [AIAA PAPER 87.28551 p 59 A88-12575 analysis and remote temperature and stress distribution in a two-pass ribroughened channel MILITARY HELICOPTERS measurement [ASME PAPER 87-GT-941 p 45 A88-11033 Anti-tank helicopters for the rich and not so rich [ASME PAPER 87-GT-2191 p48 A88-11116 MATERIALS SCIENCE p 1 A88-10877 NICKEL Composite directions at Kaman p 41 A88-12414 MILITARY OPERATIONS Constitutive modeling for isotropic materials Mechanical properly requirements for aero gas turbine Aircraft and equipment factors in the occurrence of p 55 N88-11171 materials p 42 Am-12628 suspension line twists with US. Army parachutes NICKEL ALLOYS MATHEMATICAL MODELS p 19 A88-12644 The effect of variations of cobalt content on the cyclic The accuracy-related parametric reduction of MILITARY TECHNOLOGY oxidation resistance of selected Ni-base superalloys mathematical models p 58 A88-10929 Sensor configuration for a short to medium range p 40 A88-10031 A model to determine the behaviour of a pressure reconnaissance pod p 27 A88-12742 Mechanical properly requirements for aero gas turbine measurement equipment during non-static operations of MISSILE SYSTEMS materials p 42 A88-12628 gastumne engines Evolution and application of CFD techniquesfor scramjet High-temperature sheet materials for gas turbine [ASME PAPER 87-GT-1281 p 46 A88-11055 engine analysis p 28 A88-10358 applications p 42 A88-12635

A-15 NITRIC OXIDE SUBJECT INDEX

NITRIC OXIDE AOSP - Multiprocessor architecture and system Influence of the Reynolds number on the performance Prediction of NO and CO distribution in oas turbine considerations of centrifugal Compressors combustors [AIAA PAPER 87-27901 p 59 A88-12544 [ASME PAPER 87-GT-101 p 44 A88-10979 [ASME PAPER 87-GT-631 p 41 A88-11010 OPTICAL DATA PROCESSING Correlations of fuel performance in a full-scale NOISE lSOUNDI Recent developments in infrared data processing commercial combustor and two model combustors Ac?vities report of the Institute of Sound and Vibration p 28 ABB-12751 [ASME PAPER 87-GT-891 p 29 A88-11028 Research OPTICAL EQUIPMENT Thermodynamics and performance projections for [ ETN-87-906851 p 61 N88-10589 A compact high performance thermal imager intercooledlreheatlrecuperatedgas turbine systems NOISE GENERATORS p 50 A88-12843 [ASME PAPER 87-GT-1081 p 46 A88-11040 Time-averaged heat-flux distributions and comparison Noise emission of civil and military aero-engines. OPTICAL GYROSCOPES with prediction for the Teledyne 702 HP turbine stage Sources of generation and measures for attenuation Inertial navigation Technological status and - [ASME PAPER 87-GT-1201 p 30 A88-11048 [ETN87-91021I p 62 N88-10595 development trends p20 A88-10682 NOISE INTENSITY Computer predictions of erosion damage in gas OPTICAL RADAR First article test noise survey of the AIF32T-9 large turbo turbines Airspeed measurement with a C02 lidar [ASME PAPER 87-GT-1271 p 46 A88-11054 fan engine enclosed noise suppressor system, Sky Harbor p 26 A88-12655 IAP (International Airport), Phoenix, Arizona The performance estimation of transonic turbine at [AD-A183799] p 61 NEB-10588 OPTIMAL CONTROL design and off-design conditions Helicopter main-rotorspeed effects on far-field acoustic An optimal control method for passage of a flexible rotor [ASME PAPER 87-GT-1481 p 30 A88-11066 levels through resonances p 48 A88-11439 Global positioning satellite-based automatic landing [ NASA-TM-10051 21 p 62 N88-11451 OPTIMIZATION system and wind estimated feedback for the AH-64 NOISE MEASUREMENT Necessary optimality conditions for three-dimensional helicopter p 22 N88-10784 Noise levels from propellerdriven aircraft measured at bodies in supersonic gas flow p 2 A88-10300 PERFORMANCE TESTS ground level and at 1.2 m above the ground Investigation of integrated selection of optimum engine Testing of aircraft electrical equipment --- Russian [NPL-ACllO] p 61 N88-10594 cycle parameters book p39 A88-10044 NOISE PREDICTION (AIRCRAFT) [ASME PAPER 87-GT-391 p 29 A88-10993 Electronic trend monitoring and exceedance recording Prediction of sound fields in cavities using Initial user experience with an artificial intelligence systems - A means to improved turbine engine reliability boundaly-element methods p 61 A88-12281 program for the preliminary design of centrifugal [ASME PAPER 87-GT-871 p 29 A88-11027 NOISE PROPAGATION compressors Test results and predictions for the response of Noise emission of civil and military aero-engines. [ASME PAPER 87-GT-2171 p58 A88-11115 near-ceiling sprinkler links in a full-scale compartment Sources of generation and measures for attenuation OPTOELECTRONIC DEVICES fire [ET~-87-9iozi1 p 62 N88-10595 Optical systems for gas turbine engines [NBSIR-87-3633] p 50 N88-10209 I NOISE REDUCTION p 49 A88-12657 Constitutive modeling for isotropic materials p 55 N88-11172 First article test noise survey of the AIF32T-9 large turbo ORIFICES PERMANENT MAGNETS fan engine enclosed noise suppressor system. Sky Harbor Dilution jet mixing program. phase 3 Force commutated direct frequency changers for IAP [International Airport). Phoenix. Arizona p 54 N88-11153 aerospace power applications p48 A88-11825 [AD-A183799] p 61 N88-10588 OXIDATION Process support compressor motor electromagnetic Noise emission of civil and military aero-engines. Basic concepts for better heat protection systems Sources of generation and measures for attenuation p 42 A88-12786 design summary [DE87-014359] p 52 N88-11048 [ETN-87-91021I p 62 N88-10595 Thermal expansion mismatch and oxidation in thermal PILOT PERFORMANCE NONDESTRUCTIVE TESTS barrier coatings p 56 N88-11182 Versatile simulation testbed for rotorcraft speech I10 NDE at twelve o’clmk high p 48 A88-11585 OXIDATION RESISTANCE system design NONUNIFORM FLOW The effect of variations 01 wbalt content on the cyclic [SAE PAPER 8616611 p 57 A88-10154 The spatially nonuniform convergence of the numerical oxidation resistance of selected Ni-base superalloys Flying complex approach paths using the microwave solution of flows p 40 A88-10031 landing system [ NASA-TM-1000371 p 60 N88-11429 OXYGEN RECOMBINATION [SAE PAPER 8617711 p 35 A88-10159 NOZZLE FLOW Oxygen recombination in a supersonic cooled flow Comparison of programmable legend keyboard and Numerical solutions of scramjet nozzle flows p 13 A88-12071 p 2 A88-10359 dedicated keyboard for control of the flight management I Oxygen recombination in a supersonic cooled flow wrnputer p 13 A88-12071 P [SAE PAPER 8817721 p57 A88-10160 NOZZLE THRUST COEFFICIENTS The advantages of a primary flight display Comparison of wind tunnel and flight test afterbody and PANELS [SAE PAPER 8617301 p 58 A88-10162 nozzle pressures for a twin-jet fighter aircraft at transonic Stress intensity factors and residual strength of a Improvements in aircraft safety and operational speeds cracked stiffened panel p 50 A88-13083 dependability from a projected flight path guidance [ NASA-TP-25881 p 17 NEB-10765 PANORAMIC CAMERAS display NOZZLES Airborne reconnaissance pod flight test [SAE PAPER 8617321 p35 A88-10163 Effect of empennage arrangement on single-engine p 27 A88-12741 The advantage of flightpath-oriented situation displays nonlelafterbody static pressures at transonic speeds Sensor configuration for a short to medium range during microburst encounters [NASA-TP-27531 p 17 NEB-10771 reconnaissance pod p 27 A88-12742 [SAE PAPER 8617331 p35 A88-10164 NUMERICAL ANALYSIS PARABOLIC DIFFERENTIAL EQUATIONS Airline requirements on a fly-by-wire aircraft - A pilot‘s A numerical method for subsonic unsteady lifting Parabolized Navier-Stokes analysis of ducted view surfaces - BIS. 111 - Some additional numerical results supersonic combustion problems p 2 A88-10361 [SAE PAPER 8618041 p 36 A88-10167 p2 A88-10093 PARACHUTEDESCENT Perspective traffic display format and airline pilot traffic A generalized numerical method for solving direct Aircraft and equipment factors in the occurrence of avoidance p 58 A88-12639 inverse and hybrid problems of blade cascade flow by suspension line twists with U.S. Army parachutes Investigation of interactions between limbmanipulator using streamlinecoordinate equation p19 AM-12644 dynamics and effective vehicle roll control [ASME PAPER 87-GT-291 p4 A88-10990 PARACHUTES characteristics [NASA-CR-3983] p 36 N88-10039 Impact of turbulence modeling on numerical accuracy The aerodynamics of gliding parachutes PITCHING MOMENTS and efficiency of compressible flow simulations p 11 A88-11201 Unsteady aerodynamic measurements on a rotating [NASA-TM-88333] p 52 N88-11088 PARAMETERIZATION compressor blade row at low Mach number The spatially nonuniform convergence of the numehl The accuracy-related parametric reduction of mathematical models p 58 A88-10929 [ASME PAPER 87-GT-2211 p7 A88-11118 solution of flows PLASMA SPRAYING [NASA-TM-lOOO37] p60 N88-11429 PARTICLE LADEN JETS Computer predictions of erosion damage in gas Thermal expansion mismatch and oxidation in thermal NUMERICAL STABILITY turbines barrier coatings p 56 NEB-t 1182 Threedimensional flow in a rotor A strictly - [ASME PAPER 87-GT-1271 p 46 A88-11054 Thermal barrier coating life prediction model threedimensional calculation of flows in turbomachines PASSENGER AIRCRAFT development p56 N88-11183 using the Sl-SZ method p 44 A88-10628 Aircraft acoustics I - Exterior noise of subsonic PLASTIC PROPERTIES NUSSELT NUMBER passenger aircraft and helicopters --- Russian book 3D inelastic analysis methods for hot section Effects of channel asp3 ratio on heat transfer in p 61 A88-10047 components p55 N88-11164 rectangular passage sharp 18Odeg turns Aircraft acoustics II - Cabin noise in passenger aircraft PLUMES [ASME PAPER 87-GT-1131 p 46 A88-11041 -- Russian book p 61 A88-10048 Plume infrared signaturemeasurements and comparison NYQUIST FREQUENCIES Wing design with a threedimensional transonic inverse with a thewetical model __.of turboshaft engines Syntheses of reduced-order wntrollers for active flutter method p14 A88-13077 p 33 A88-12836 suppression p 35 A88-10095 An aerodynamic design study of transonic transport POROUSBOUNDARYLAYERCONTROL wings p 15 A88-13078 Strong gas injection into supersonic flow with turbulent PERFORATED PLATES mixing p 13 A88-12056 0 Film cooling of a turbine blade with injection through PORTABLE EQUIPMENT two rows of holes in the near-endwall region Extended systems of vanable structure with mobile OBSERVABILITY (SYSTEMS) [ASME PAPER 87-GT-1961 p47 A88-11100 radio-communicationobjects p 44 A88-10726 Optimal detection of Sensor failures in flight control Structure simplification around a cutout. Application of POSITION (LOCATION) I systems using deterministic ObSeNerS a simplified damage tolerance design chart Modern technology in positioning and navigation; p 38 NEB-10803 p 50 A88-13084 Navigation Meeting. Duesseldorf. Federal Republic of ONBOARD DATA PROCESSING PERFORMANCE PREDICTION Germany, May 6-8, 1987. Reports p 20 A88-10676 Optimal information processing for sensors and sensor Analytical study of swirler effects in annular propulsive BMFT-supported projects in the fields position-finding, systems - The case of radar sensors p 26 A88-10685 noales p 28 A88-10362 navigation, and traffic safety p 20 A88-10677

A-16 SUBJECT INDEX REINFORCED SHELLS

The importance of modern positioning and navigation PROBABILITY DENSITY FUNCTIONS Development studies of a European data network for technology for ATC p 20 A88-10678 Analyses and assessments of span wise gust gradient acquisition, processing. and display of air-traffic data Hybnd positioning and navigation systems - data from NASA 8-578 aircraft p21 A88-10688 Technological status and development trends in [NASA-CR-178288] p15 N88-10007 RADAR EQUIPMENT position-finding and navigation procedures PROBABILITY DISTRIBUTION FUNCTIONS Fast stable solution of a dispersion equation of linear p 20 A88-10684 Analyses and assessments of span wise gust gradient filtering --- for flight vehicle radar system Optimal information processing for sensors and sensor data from NASA 8-576 aircraft p21 A88-10728 systems - The case of radar sensots p 26 A88-10685 [NASA-CR-178288] p15 N88-10007 RADAR TARGETS POSITION ERRORS PRODUCTDEVELOPMENT Towards the design of an intelligent aerospace system A 1987 progress report of manufacturing techniques for Civil aviationapplication of the Global PositioningSystem [AIAA PAPER 87-28441 p 26 A88-12569 (GPS) and its issues p 22 A88-13088 Gravity Probe gyroscope rotors Expert system control for airborne radar surveillance [ NASA-TM-t00312] p 53 N88-11101 POSITRONS [AIM PAPER 87-28541 p 26 A88-12574 PRODUCTION ENGINEERING RADIO COMMUNICATION Neutron and positron techniquesfor fluid transfer system Development and production of new and modified analysis and remote temperature and stress Extended systems of variable structure with mobile powders for sprayed coatings and components for saving radiocommunicationobjects p44 A88-10726 measurement important raw materials [ASME PAPER 87-GT-2191 p48 A88-11116 RADIO FREQUENCY DISCHARGE [ BMFT-FB-T-86-1291 p 42 N88-10159 Thin-film temperature sensors deposited by radio POTENTIAL FLOW PROPELLER DRIVE frequency cathodic sputtering p 50 A88-12903 Numerical solution of stream function equations in Noise levels from propellerdriven aircraft measured at RADIO NAVIGATION transonic flows ground level and at 1.2 m above the ground Development and trends in radio position finding [ASME PAPER 87-GT-181 p 3 A88-10983 [ NPL-AC-1101 p61 N88-10594 p 20 A88-10680 A simplified method for 3-D potential flow in PROPELLER FANS RADIO PROBING turbomachinery using vortex sheet boundary conditions Transonic analysis and design of axisymmetric bodies Computing complex for a system for the radio-acoustic [ASME PAPER 87-GT-281 p 3 A88-10989 in nonuniform flow sounding of the atmosphere - Hardware facilities Numerical computation of non-isentropic potential [NASACR-4101] p16 N88-10013 p 58 A88-11394 equations for transonic cascade flows PROPELLERS RADIO RECEIVERS [ASME PAPER 87-GT-1591 p5 A88-11071 Wind tunnel testing of small scale pressuretapped model GPS receivers for air navigation p 22 A88-13093 A multi-grid algcfithmfor2-D transonic potential cascade propellers p 32 A88-11196 RAMJET ENGINES flow Advanced turboprop wing installation effects measured Numerical solutions of scramjet nozzle flows [ASME PAPER 87-GT-1801 p 6 A88-11088 by unsteady blade pressure and noise p2 A88-10359 POWDER METALLURGY [ NASA-TM-100200I p 15 N88-10008 Flame driving of longitudinal instabilities in liquid fueled Development and production 01 new and modified PROPORTIONAL COUNTERS dump combustors powders for sprayed coatings and components for saving Neutron and positron techniquesforfluidtransfer system [AD-A183536] p 33 N88-10033 important raw materials analysis and remote temperature and stress RANDOM VIBRATION [BMFT-FB-T-88-129] p 42 N88-10159 measurement Friction damping of random vibration in gas turbine POWER CONDITIONING [ASME PAPER 87-GT-2191 p48 A88-11116 engine airfoils Force commutated direct frequency changers for PROPULSION SYSTEM CONFIGURATIONS [ASME PAPER 87-GT-441 p 29 A88-10996 aerospace power applications p 48 A88-11825 Multimodes to Mach 5 p 28 A88-10371 REACTION BONDING PROPULSION SYSTEM PERFORMANCE PREDICTION ANALYSIS TECHNIOUES Development of a statistically proven injection molding Conelations of fuel performance in a lull-scale Prediction of NO and CO distribution in gas turbine method lcf reaction bonded silicon nitride, sintering commercial combustor and two model combustors reaction bonded silicon nitride, and sintered silicon combustors [ASME PAPER 87-GT-891 p 29 A88-11028 [ASME PAPER 87-GT-631 p 41 A88-11010 nitride Thermcdynamics and performance projections for [ ETN-87-905751 p 52 N88-11002 Prediction of turbulent source flow between corotating intercooled/reheat/recuperated gas turbine systems REACTION KINETICS disks with an anisotropic two-equation turbulence model [ASME PAPER 87-GT-1081 p 46 A88-11040 Parabolized Navier-Stokes analysis of ducted [ASME PAPER 87-GT-731 p 45 A88-11017 An improved Stirling engine for model aircraft supersonic combustion problems p 2 A88-10361 A simple method for the prediction of separation bubble propulsion p 33 A88-11976 REAL TIME OPERATION formation on aerofoils at low Reynolds number PROTECTIVE COATINGS Airborne reconnaissanceX Proceedingsof the Meeting. p8 A88-11179 Pack cementation coatings for superalloys - A review San Diego, CA. Aug. 19.20, 1986 Criteria for determination of significant load cycles in of history. theory. and practice [SPIE-694] p 26 A88-12728 variable ampliiude load sequences [ASME PAPER 87-GT-501 p 41 A88-11002 Real-time reconnaissance - An engineering fNLR-MP-86013-Ul 051 N88-10386 Procedures for determining surface heat flux using thin perspecti\le p21 A88-12733 Component specific modeling p 60 N88-11166 film gauges on a coated metal model in a transient test Magnebc recording for near real time reconnaissance PREDICTIONS facility applications p 27 A88-12736 Life prediction and constitutive models for engine hot [ASME PAPER 87-GT-951 p 45 A88-1 1034 Measurements in the functional mock up test of the section anisotropic materials program Development and production of new and modified NAL QSTOL aircraft control system p56 N88-11175 powders for sprayed coatings and components for saving [NAL-TR-9281 p36 N88-10793 Thermal banier coating life prediction model important raw materials RECTANGULAR WINGS development p56 N88-11185 [ BMFT-FB-T-86-1291 p42 N88-10159 A numerical method for subsonic unsteady lifting

Software reliability models for fault-tolerant avionics Lite prediction and constitutive models for engine hot surfaces - BIS. 111 ~ Some additional numerical results computers and related topics section anisotropic materials program p 2 A88-10093 [NASACR-181440] p60 N88-11382 p 56 N88-111 75 REDUCED ORDER FILTERS PREMIXED FLAMES PYROELECTRICITY Syntheses of reduced-order controllers for acke flutter Prediction of combustion performance of aviation An unwoled linescan thermal imager for ground and suppress ion p35 A88-10095 kerosines using a novel premixed flame technique airborne use p 49 A88-12840 REDUNDANCY [ASME PAPER 87-GT-1251 p41 A88-11052 Flght test of a resident backup software system PREPROCESSING p38 N88-10805 Measurements in the functional mock up test of the Q REDUNDANCY ENCODING NAL QSTOL aircraft control system Robust control system design p 37 N88-10800 [ NAL-TR-9281 p 36 N88-10793 OUALITY REENTRY VEHICLES PRESSURE DISTRIBUTION Assessment of software quality for the AIRBUS A310 The aerothermodynamic environment fcf holes in Pressure field due to drag reducing outer layer devices automatic pilot p38 N88-10804 hypersonic configurations in turbulent boundary layers p3 A88-10492 OUALITY CONTROL [DE87414651I p 17 N88-10767 Similarity of ejector wall-pressure distributions Scheduled maintenance program helps Delta maintain REFRACTORY COATINQS p49 AM-12294 quality p 1 A88-11672 Thermal barrier coating life prediction model Advanced turboprop wing installation effects measured development p56 N88-11183 Investment foundry melting stock. Rolls Royce by unsteady blade pressure and noise requirements and demands in terms of quality and the Thermal barrier coating life prediction model [ NASA-TM-1002001 p15 N88-10008 relationship to product performance development p56 N88-11185 Transonic analysis and desgn of axisymmetric bodii end [PNR90397] p52 N88-11003 REFRACTORY MATERIALS in nonuniform flow High temperature metal matrix composites for future [NASA-CR-4101I p16 N88-10013 Software reliability models for fault-tolerant avionics aerospace systems computers and related topics PRESSUREMEASUREMENT [NASA-TM-100212] p 43 N88-10938 A model to determine the behaviour of a pressure [ NASA-CR-l81440] p60 N88-11382 REFRACTORY METALS measurement equipment during non-static operations of QUIET ENGINE PROGRAM High-temperature sheet materials for gas turbine gasturbine engines Flight re& at NASA Ames Research Center: A test applitiOnS p42 A88-12635 [ASME PAPER 87-GT-1281 p46 AM-11055 pilot's perspective REGENERATORS Wind tunnel testing of small scale pressuretapped model [NASA-TM-l00025] p25 N88107BB Development of the AGTlOl regenerator seals propellers p32 A88-11196 [ASME PAPER 87-GT-1731 p46 A88-11083 PRESSURE REDUCTION REQIONS The base pressure and loss of a family of four turbine R Computation of transonic separated wing flows using blades an Euler/NavierStokes zonal approach [ASME PAPER 87-GT-2021 p7 A88-11106 RADAR DETECTION [ NASA-TMW11 ] p 52 N88-11089 PRESSURESENSORS Optimal information processing for sensors and sensor REINFORCED SHELLS Development and application of a high frequency wedge systems - The case of radar sensors p 26 A88-10685 Numerical solution of coupled problems of supersonic probe Autonomous onboard collision avoidance for aircraft and flow past deformable shells of finite thickness [ASME PAPER 87-GT-2161 p47 A88-11114 ships p21 A88-10687 p13 A88-11280

A-17 RELAXATION METHOD (MATHEMATICS) SUBJECT INDEX

RELAXATION METHOD (MATHEMATICS) RESIN MATRIX COMPOSITES ROTOR BLADES (TURBOMACHINERY) Calculation of three-dimensional viscous flows in Composlte structural materials A new method of calculating optimum velocity turbomachinery with an implicit relaxation method [ NASA-CR-1814161 p 56 N88-11186 distribution along the blade surface on arbitrary stream p2 A88-10357 RESONANT VIBRATION surface of revolution in turbomachines RELIABILITY Localization of natural modes of vibration in bladed [ASME PAPER 87-GT-301 p4 A88-10991 Software reliability models for fault-tolerant avionics disks Localization of natural modes of vibration in bladed computers and related topics [ASME PAPER 87-GT-461 p 29 A88-10998 disks [ NASA-CR-1814401 p60 N88-11382 An optimal control method for passage of a flexible rotor [ASME PAPER 87-GT-461 p 29 A88-10998 RELIABILITY ANALYSIS through resonances p 48 A88-11439 Application of advanced computational codes in the design of an experiment for a supersonic throughflow fan Applied reliabilitylmaintainability methodology as a REYNOLDS NUMBER rotor function within life cycle cost ..-of aircrafl turbine engine Influence of the Reynolds number on the performance [ASME PAPER 87-GT-1601 p 6 A88-11072 [ASME PAPER 87-GT-1721 p 46 A88-11082 of centrifugal compressors Unified equation of motion (UEM) approach as applied NDE at twelve o'clock high p 48 A88-11585 [ASME PAPER 87-GT-IO] p 44 A88-10979 RELIABILITY ENGINEERING to S1 turbomachinery problems Effects of channel aspect ratio on heat transfer in Design study for an FBW lateral control system [ASME PAPER 87-GT-1791 p 6 A88-11087 p 36 A88-13080 rectangular passage sharp 18Odeg turns Calculationof a three-dimensionalturbomachinery rotor [ASME PAPER 87-GT-1131 p 46 A88-11041 Stress intensity factors and residual strength of a flow with a Navier-Stokescode cracked stiffened panel p 50 A88-13083 Heat transfer to arrays of impinging jets in a crossflow [ASME PAPER 87-GT-2321 p 7 A88-11125 Structure simplification around a cutout - Application of [ASME PAPER 87-GT-1981 p 47 A88-11102 Integration of dynamic, aerodynamic and structural a simplified damage tolerance design chart A study of the effects of thermal barrier coating surface optimization of helicopter rotor blades p 50 A88-13084 roughness on the boundary layer characteristics of [NASA-CR-181441] p 16 N88-10012 The application of emulation techniques in the analysis gas-turbine aerofoils ROTOR SPEED of highly reliable, guidance and control computer [ASME PAPER 87-GT-2231 p 48 A88-11120 Helicopter main-rotor speed effects on far-field acoustic systems p 37 N88-10798 Particle transport across the transpired turbulent levels Some approaches to the design of high integrity boundary layer [NASA-TM-100512] p 62 N88-11451 software p 37 N88-10799 [ASME PAPER 87-GT-2651 p 48 A88-11142 ROTOR SYSTEMS RESEARCH AIRCRAFT Reliability modeling of fault-tolerant computer based The structure of separated flow regions occurring near Flight researh at NASA Ames Research Center: A test systems p 37 N88-10801 the leading edge of airfoils including transition pilot's perspective Software reliability models for fault-tolerant avionics [ NASA-CR-1814341 p 16 N88-10011 [NASA-TM-100025] p 25 N88-10788 computers and related topics RING LASERS ROTORCRAFT AIRCRAFT [ NASA-CR-1814401 p 60 N88-11382 Inertial navigation - Technological status and Composite materials in rotorcraft p 24 A88-12412 REMOTE SENSING development trends p 20 A88-10682 ROTORS Fiber optic engineering sensor system. Preliminary -ICY Three-dimensional flow in a rotor - A strictly nl-R 19 A88-10658 three-dimensional calculation of flows in turbomachines program management plan, phase 3 revision Flight safety and risk [ AD-A1836631 P 62 N88-10~8 using the S1-S2 method p44 A88-10628 REMOTE SENSORS Effect of fluid inertia on the performance of squeeze Robotic air vehicle A pilot's perspective Airborne reconnaissanceX Proceedings of the Meeting, - film damper supported rotors 19 A88-10437 San Diego, CA, Aug. 19,20, 1986 . [ASME PAPER 87-GT-2201 p48 A88-11117 [SPIE-664] p 26 A88-12728 ROLL An optimal control method for passage of a flexible rotor Sensor controlldata display set (SCIDDS) for film Investigation of interactions between limb-manipulator through resonances p 48 A88-11439 andfor electro optics (EO) p 26 A88-12731 dynamics and effective vehicle roll control characteristics Turbines with counterrotating runners lor aircrafl power REMOTELY PILOTED VEHICLES plants p 34 N88-10992 [ NASA-CR-39831 p 36 N88-10039 Robotic air vehicle - A pilot's perspective A 1987 progress report of manufacturingtechniques for p 19 A88-10437 ROLLER BEARINGS Counterrotating differential cylindrical roller bearing Gravity Probe B gyroscope rotors Atmospheric turbulence and gust on the performance [ NASA-TM-1003121 p 53 NEB-1 1101 of a Wortmann FX 63-137 wing p9 A88-11185 development RULES Control surface effects on the low Reynolds number [AIM PAPER 87-18431 p43 A88-10497 A Nle-based system for arrival sequencing and behavior of the Wortmann FX 63-137 Improved oil-off survivability of tapered roller bearings scheduling in air traffic control p 22 N88-10815 p 10 A88-11187 [NASA-CR-180804] p 53 N88-11135 The use of wind tunnel data in the design of radio ROTARY WINGS controlled contest model sailplanes p 24 A88-11195 The flow visualization on the rotary wing with low aspect The calculation of flow about aerofoils at low Reynolds ratio p2 A88-10094 S number with application to remotely piloted vehicles Analytical modeling of helicopter static and dynamic pll A88-11197 SAFETY DEVICES induced velocity in GRASP The use of Kevlar on aero-engine fan containment Preliminary measurements of the flight performance of [NASA-TM-1000261 p 18 N88-10777 an RPV compared with wind tunnel and CFD estimates casings ROTATING DISKS [PNR904101 p 53 NEB-1 1134 p 12 A88-11203 Prediction of turbulent source flow between corotating Aerodynamics of unmanned aircraft at full-scale in the SAMPLING disks with an anisotropic two-equation turbulence model Measurements in the functional mock up test of the RAE 24ft wind-tunnel p 12 A88-11204 [ASME PAPER 87-GT-731 p45 A88-11017 Low altitudelairspeed unmanned research aircraft NAL QSTOL aircraft control system Analysis of windage losses and velocity distribution for (LAURA) preliminary development p 12 A88-11205 [NAL-TR-928] p 36 N88-10793 a shrouded rotating disk Full-scale transport controlled impact demonstration SATELLITE ATTITUDE CONTROL [ASME PAPER 87-GT-1881 p6 A88-11091 program Aerospace research at the National Aerospace [NASA-TM-89642] p 19 N88-10021 Cyclic spinning testing of aero-engine discs Laboratory (NLR) HiMAT flight program: Test results and program [ASME PAPER 87-GT-2591 p 32 A88-11139 [ETN-87-90821] p 62 N88-10697 assessment overview Developments in disc materials -.. for gas turbine SATELLITE ORIENTATION [NASA-TM-86725] p 24 N88-10026 engines p42 A88-12632 Analysis of free molecular effects on the attitude 01 REPORTS ROTATING FLUIDS satellites in geostationary transfer orbit. Part 2 Force and Aircraft accidents Numerical prediction of turbulent flow in rotating torque measurement in free molecular wind tunnel tests [JB-84] p 19 N88-10020 cavities [ DFVLR-IB-222-86-A-071 p 40 N88-10078 REQUIREMENTS [ASME PAPER 87-GT-741 p 45 A88-11018 SATELLITE PERTURBATION Airline requirements on a fly-by-wire aircraft ~ A pilot's ROTATING STALLS Analysis of free molecular effects on the altitude of view Investigation of the excitation of turbine blade vibration satellites in geostationary transfer orbit. Part 2: Force and [SA€ PAPER 8618041 p36 A88-10167 in axial compressors in rotating stall torque measurement in free molecular wind tunnel tests RESEARCH AIRCRAFT [ ETN-87-903771 p34 N88-10035 [ DFVLR-IB-222-86-A-07I p 40 N88-10078 Low altitudelairspeed unmanned research aircraft ROTATION SATELLITE TELEVISION (LAURA) preliminary development p 12 A88-1 1205 Coolant passage heat transfer with rotation Video data link provides television pictures in near real RESEARCH ANDDEVELOPMENT p 54 N88-11160 time via tactical radio and satellite channels ROTOR AERODYNAMICS Color display technology ~ An overview p 49 A88-12732 [SAE PAPER 8616921 p 43 A88-10170 Navier-Stokes simulations of rotorlstator interaction SCALE MODELS AGT101 .Ceramic gas turbine development using patched and overlaid grids p 2 A88-10354 Correlations of fuel performance in a full-scale [ASME PAPER 87-GT-2281 p 32 A88-11122 Through-flow analysis of a multi-stage compressor commercial combustor and two model combustors operating at near-stall conditions The development of 270 Vdc solid state power [ASME PAPER 87-GT-891 p 29 A88-11028 [ASME PAPER 87-GT-51I p4 A88-11003 controllers for advanced aircraft electrical systems. Velocitv scaled aeroelastic testing of advanced --- Sealing of a shrouded rotor-stator system with pre-swirl p 33 A88-11923 turbo pr o p s coolant Investigations in the history and theory of development [ASME PAPER 87-GT-721 p 45 A88-11016 [ASME PAPER 87-GT-2091 p31 A88-11110 of aerospace science and technology. Number 5 .-- ROTORBLADES Wind tunnel testing of small scale pressuretapped model Russian book p 62 A88-12202 Sealing of a shrouded rotor-stator system with pre-swirl propellers p 32 A88-11196 Composites technology in Army aviation coolant SCALING LAWS p24 A88-12413 [ASME PAPER 87-GT-721 p 45 A88-11016 Velocity scaled aeroelastic testing of advanced Developments in disc materials --- for gas turbine On predicting the resonant response of bladed disk turboprops engines p42 A88-12632 assemblies [ASME PAPER 87-GT-2091 p31 A88-11110 RESEARCH VEHICLES [ASME PAPER 87-GT-1581 p 30 A88-11070 SCHEDULING Low cost windowless cockpit research vehicle Modelling the unsteady flow in a turbine rotor passage A rule-based system for arrival sequencing and [SAE PAPER 8617551 p39 A88-10156 [ASME PAPER 87-GT-1971 p 7 A88-11101 scheduling in air traffic control p 22 N88-10815 SUBJECT INDEX STRESS ANALYSIS

SCHMIDT NUMBER Measurements in the functional mock up test of the STANDARDS Particle transport across the transpired turbulent NAL QSTOL aircraft control system AGARD standard aeroelastic configurations for dynamic boundary layer [ NAL-TR-9281 p 36 NEB-10793 response. Candidate configuration I.-wing 445.6 [ASME PAPER 87-GT-2651 p 48 A88-11142 SILICON NITRIDES [NASA-TM-100492] p 56 NEB-11202 SEALS (STOPPERS) Development of a statistically proven injection molding STATIC CHARACTERISTICS Development of the AGT101 regenerator seals method for reaction bonded silicon nitride, sintering The Lewis Strain Gauge Laboratory: Status and plans [ASME PAPER 87-GT-1731 p 46 A88-11083 reaction bonded silicon nitride. and sintered silicon D 54 NEB-1 1146 SENSORS nitride STATIC PRESSURE Sensor configuration for a short to medium range [ETN-87-905751 p 52 N88-11002 Pressure field due to drag reducing outer layer devices reconnaissance pod p 27 A88-12742 SIMULATION in turbulent boundary layers p3 A88-10492 Impact of turbulence modeling on numerical accuracy Optimal detection of sensor failures in flight control Effect of empennage arrangement on single-engine and efficiency of compressible flow simulations nonle/afterbody static pressures at transonic speeds systems using deterministic ObseNerS [ NASA-TM-88333I p 52 N88-11088 p 38 N88-10803 [NASA-TP-2753] p 17 NEB-10771 SINGLE CRYSTALS STATISTICAL ANALYSIS SEPARATED FLOW Constitutive modeling of superalloy single crystals with Analyses and assessments of span wise gust gradient Experimental study of three-dimensionalseparated flow verification testing p 43 N88-11169 data from NASA B-57B aircraft surrounding a hemisphere-cylinderat incidence SODIUM CHLORIDES [NASA-CR-178288] p 15 N88-10007 [AIAA PAPER 87-24921 p 3 A88-10498 Experimentalverification of vapor deposition rate theory Software reliability models for fault-tolerant avionics Experimental investigations of flows through a plane in high velocity burner rigs p 43 N88-11179 computers and related topics cascade at large angles of attack with separations SOFTWARE ENGINEERING [ NASA-CR-1814401 p 60 N88-11382 [ASME PAPER 87-GT-961 p 5 A88-11035 Color display programming for aviation STATISTICAL CORRELATION On massive laminar separation and lift anomalies in [DFVLR-MIlT-87-03] p28 N88-10031 Conelations of fuel performance in a full-scale subcritical Re-range p 8 A88-11178 Some approaches to the design of high integrity commercial combustor and two model combustors A simple method for the prediction of separation bubble software p37 N88-10799 [ASME PAPER 87.GT-891 p 29 A88-11028 formation on aerofoils at low Reynolds number Assessment of software quality for the AIRBUS A310 STATOR BLADES p8 A88-11179 automatic pilot p 38 N88-10804 Sealing of a shrouded rotor-stator system with pre-swirl Low Reynolds number airfoil design at the Douglas Software reliability models for fault-tolerant avionics coolant Aircraft Company p9 A88-11183 computers and related topics [ASME PAPER 87-GT-721 p 45 A88-11016 Boundary layer and performance characteristics from [NASA-CR-181440] p 60 N88-11382 Unified equation of motion (UEM) approach as applied wind tunnel tests of a low Reynolds number Liebeck SOFTWARE TOOLS to S1 turbomachinery problems airfoil p9 A88-11184 FDAD - A lab/field test fool .--Flight Data Analysis and [ASME PAPER 87-GT-1791 p6 A88-11087 Global marching technique for predicting separated Display p 25 A88-10436 STATORS flows over arbitrary airfoils p 14 A88-12293 Traditional versus Nle-based programming techniques Navier-Stokes simulations of rotorlstator interaction The structure of separated flow regions occurring near - Application to the control of optional flight information using patched and overlaid grids p 2 A88-10354 the leading edge of airfoils including transition p58 A88-10965 Analysis of windage losses and velocity distribution for [NASA-CR-181 4341 p16 N88-10011 SOLID STATE DEVICES a shrouded rotating disk Investigations of separated flow states on wings of The development of 270 Vdc solid state power [ASME PAPER 87-GT-1861 p6 A88-11091 medium aspect ratio taking into account the wind tunnel controllers --- for advanced aircraft electrical systems. Flow in a model turbine stator p 55 N88-11163 interference problem p 33 A88-11923 STEADY FLOW [ETN-87-90437] p17 N88-10016 SOUND FIELDS Navier-Stokes solution for steady two-dimensional lntergration effects of &shaped, underwing. Prediction of sound fields in cavities using transonic cascade flows aft-mounted, separate-flow, flow-through nacelles on a boundary-element methods p 61 A88-12281 [ASME PAPER 87-GT-541 p 4 A88-11005 high-wing transport SPACECRAFT DESIGN Refined numerical solution of the transonic flow past a [NASA-TM-4018] p 18 N88-10773 Aerospace research at the National Aerospace wedge p 14 A88-12280 Computation of transonic separated wing flows using Laboratory (NLR) STEADY STATE an EulerlNavier-Stokeszonal approach [ETN-87-90821] p62 N88-10697 Blade loss transient dynamics analysis, volume 1. Task [NASA-TM-88311] p 52 N88-11089 SPACECRAFT PROPULSION 2: TETRA 2 theoretical development SERVICE LIFE High temperature metal matrix composites for future [ NASA-CR-1796321 p 34 N88-10791 New Soviet helicopter technology and its potential for aerospace systems Blade loss transient dynamics analysis, volume 2. Task industrial use p 1 A88-10657 [ NASA-TM-1002121 p 43 N88-10938 2 TETRA 2 user's manual Ensuringthe service life of designs (experiencein aircraft SPECIFIC HEAT [NASA-CR-179633] p 34 N88-10792 construction) p 1 N88-10986 Effects of channel aspect ratio on heat transfer in STEERING SHOCK ABSORBERS rectangular passage sharp 180-deg turns Steering mechanism ___ vehicles Steering mechanism -__vehicles [ASME PAPER 87-GT-1131 p 46 A88-11041 [ EP-PATENT-0-181-700-All p 51 N88-10338 [EP-PATENT-O-181 -700-AlI p 51 N88-10338 SPECTRORADIOMETERS STIRLING ENGINES SHOCKLAYERS Plume infrared signature measurements and comparison An improved Stirling engine for model aircraft Effect of energy release in the shock layer on the with a theoretical model --- of turboshaft engines propulsion p 33 A88-11976 supersonic flight of bodies p 13 A88-12073 p 33 A88-12836 STOKES FLOW SHOCK LOAOS SPEECH RECOGNITION Multigrid localizatin and multgrid gnd generation for Shock embedding discontinuous solution of elliptic Versatile simulation testbed for rotorcraft speech 110 the computationof vortex structures and dynamics of flows equation for inverse problem of transonic S2 flow system design in cavities and about airfoils p 3 A88-10562 [ASME PAPER 87-GT-1151 p 5 A88-11043 [SAE PAPER 8616611 p 57 A88-10154 STRAIN GAGES SHOCK WAVE PROPAGATION SPEED REGULATORS The development of a high temperaturestatic strain gage Stability of supersonic flow of an ideal gas with a head The design of a tuftashaft speed governor using modern system p 53 N88-11142 shock wave past cylindrical channels and cavities control techniques The Lewis Strain Gauge Laboratory: Status and plans p13 A88-12065 [NASA-CR-1750461 p 51 N88-10339 p 54 N88-11146 SHOCK WAVES SPHERES STRAIN MEASUREMENT Chaiacterization of shock wave end wall boundary layer Supersonic flow around a sphere in a thermal The development of a huhtemperature static strain gage interactions in a transonic compressor rotor inhomogeneity p2 A88-10264 system p 53 N88-11142 [ASME PAPER 87-GT-1661 p6 A88-11077 SPRAY CHARACTERISTICS The Lewis Strain Gauge Laboratory: Status and plans Modelling the unsteady flow in a turbine rotor passage Experiments on spray interactions in the wake of a bluff p54 N88-11146 [ASME PAPER 87-GT-1971 p7 A88-11101 body High temperature stress-strain analysis SHORT HAUL AIRCRAFT [ASME PAPER 87-GT-481 p 44 A88-11000 p 55 N88-11170 Flight researh at NASA Ames Research Center: A test Spray performance of a hybrid injector under varying STRAPDOWN INERTIAL GUIDANCE pilot's perspective air density conditions Inertial navigation - Technological status and [NASA-TM-100025] p 25 N88-10788 [ASME PAPER 87-GT-1551 p 46 A88-11068 development trends p 20 A88-10682 SHORT TAKEOFF AIRCRAFT SPRAYED COATINGS Test equipment with fiber optic data bus and laser gyro H?TB . The ultimate test bed p 23 A88-10875 Development and production of new and modified strapdown system LTN-90 for the helicopter 80-105 The Antonov An-74 brings high tech to low powders for sprayed coatings and components for saving [ ESA-lT-10381 p 22 N88-10025 temperatures p 23 A88-10876 important raw materials STREAM FUNCTIONS (FLUIDS) SHROUDED TURBINES [ BMFT-FB-T-86-1291 p 42 N88-10159 Numerical solution of stream function equations in Localization of natural modes of vibration in bladed SPRINKLING transonic flows I disks Test results and predictions for the response of [ASME PAPER 87-GT-181 p 3 A88-10983 [ASME PAPER 87-GT-461 p 29 A88-10998 near-ceiling sprinkler links in a full-scale compartment Shock embedding discontinuous solution of elliptic Sealing of a shrouded rotw-stator system with pre-swirl fire equation for inverse problem of transonic S2 flow coolant [NBSIR-87-3633I p 50 N88-10209 [ASME PAPER 87-GT-1151 p 5 A88-11043 [ASME PAPER 87-GT-721 p 45 A88-11016 SPUTTERING A discussion of the mean S2 stream surfaces applied Analysis of windage losses and velocity distribution for Thin-film temperature sensors deposited by rado to quasi-three-dimensional calculation programs for a shrouded rotating disk frequency cathodic spunering p50 A88-12903 turbomachinery design SQUEEZE FILMS [ASME PAPER 87-GT-1501 p 5 A88-11067 I [ASME PAPER 87-GT-1861 p 6 A88-11091 SIGNAL PROCESSING Effect of fluid inertia on the performance of squeeze STRESS ANALYSIS AOSP - MultiprOcessor architecture and system film damper supported rotors Criteria for determination of significant load cycles in considerations [ASME PAPER 87-GT-2201 p48 A88-11117 variable amplitude load sequences [AIAA PAPER 87-27901 p 59 A88-12544 STABILIZERS (FLUID DYNAMICS) [ NLR-MP-86013-UI p 51 N88-10386 Synchronizing video signals to standard RIG time Advanced composite horizontal stabilizer for 3D inelastic analysis methods for hot section codes p21 AM-12737 nenqeneratiin commercial aircraft p 24 A88-13081 components p55 NEB-11164

A-19 STRESS MEASUREMENT SUBJECT INDEX

Component specific modeling p 60 NEB-11166 SUPERSONIC COMPRESSORS Flow investigations on swirling compressible flow Constitutive modeling of superalloy single crystals with Offdesign performance of supersonic compressors with through a vaneless radial diffuser verification testing p 43 N88-11169 fixed and variable geometry [ASME PAPER 87-GT-1931 p 7 A88-11097 Constitutive modeling for isotropic materials [ASME PAPER 87-GT-1161 p 5 ABB-11044 SWITCHING CIRCUITS p 55 N88-1I1 71 SUPERSONIC FLIGHT The development of 270 Vdc solid state power STRESS MEASUREMENT An Orient Express to capture the market controllers --- for advanced aircraft electrical systems. Neutron and positron techniquesforfluidtransfer system p 1 A88-10370 p 33 A86-11923 analysis and remote temperature and stress Multimodes to Mach 5 p 26 A88-10371 SYNCHRONIZERS measurement Synchronizing video signals to standard IRlG time Effect of energy release in the shock layer on the [ASME PAPER 87-GT-2191 p48 A88-11116 supersonic flight of bodies p13 A68-12073 codes p 21 A66-12737 STRESSSTRAIN RELATIONSHIPS SYSTEMS ANALYSIS SUPERSONIC FLOW Constitutive modeling of superalloy single crystals with Digital system bus integrity Supersonic flow around a sphere in a thermal verification testing p 43 N88-111 69 [ NASA-CR-1814461 p28 N88-10030 High temperature stress-strain analysis inhomogeneity p2 A88-10264 Software reliability models for fault-tolerant avionics p 55 NEB-1 1170 Necessary optimality conditions for three-dimensional computers and related topics Constitutive modeling for isotropic materials bodies in supersonic gas flow p 2 A88-10300 [ NASA-CR-1814401 p 60 NEB-1 1382 p 55 NEB-1 1172 Experimental study of threedimensionalseparated flow SYSTEMS ENGINEERING STRESSES surrounding a hemispherecylinder a1 incidence Versatile simulation testbed for rotorcraft speech I/O Component specific modeling p 60 N88-11166 [AIM PAPER 87-24921 p3 A88-10496 system design STRUCTURAL ANALYSIS Application of advanced computational codes in the [SAE PAPER 8616611 p57 A88-10154

Localization of natural modes of vibration in bladed design of an experiment for a supersonic throughflow fan Real-time reconnaissance ~ An engineering disks rotor perspective p 21 A88-12733 [ASME PAPER 87-GT-461 p 29 A88-10998 [ASME PAPER 87-GT-1601 p6 A88-11072 Datalink design trade-offs for electro-optical Reliability of finite element methods in North America Numerical solution of coupled problems of supersonic reconnaissance systems p 27 A88-12740 [AGARD-R-748] p 53 NEB-1 1139 flow past deformable Shells of finite thickness Fiber optic engineering sensor system. Preliminary Turbine Engine Hot Section Technology, 1985 p 13 A66-11280 program management plan, phase 3 revision [ NASA-CP-24051 p53 N66-11140 Strong gas injection into supersonic flow with turbulent [ ADA1 836631 p62 NEB-10608 3D inelastic analysis methods for hot section mixing p 13 A88-12056 AI expert system technology issues for guidance and components p55 NEB-11164 Stability of supersonic flow of an ideal gas with a head control applications p 38 N86-10808 3-D inelastic analysis methods for hot section shock wave past cylindrical channels and cavities SYSTEMS INTEGRATION components p60 N66-11165 p 13 A88-12065 Design principles and practices for implementation of MIL-STD-1760 in aircraft and stores High temperature stress-strain analysis Oxygen recombination in a supersonic cooled flow [AD-A183724] p 24 N88-10027 p 55 NEB-11170 p 13 ABB-12071 SYSTEMS SIMULATION Constitutive modeling for isotropic materials Analysis of supersonic heterogeneous flow impinging p55 N88-11171 Versatile simulation testbed for rotorcraft speech 110 on an obstacle p 14 A88-12074 system design STRUCTURAL DESIGN Optimal lifting wings with required longitudinal balancing [SAE PAPER 8616611 p 57 A88-10154 Advanced composite horizontal stabilizer for characteristics p 14 A88-12075 next-generatbn commercial aircraft p 24 A88-13081 lntergration effects of D-shaped. underwing, Design and fabrication trial of a composite flap aft-mounted. separate-flow, flow-through nacelles on a T StNCtUE p 1 A88-13082 high-wing transport Structure simplification around a cutout - Application of [ NASA-TM-40181 p 18 N88-10773 TAIL ASSEMBLIES a simplified damage tolerance desgn chart SUPERSONIC JET FLOW Advanced composite horizontal stabilizer ior nextqeneration commercial aircraft p 24 A88-I 3081 p 50 A88-13084 Applicability of a diffusion combustion model to the Integration of dynamic. aerodynamic and structural analysis of supersonic turbulent reacting jets Effect of empennage arrangement on singlaengine optimization of helicopter rotor blades p 40 A88-10180 nonWafterbody static pressures at transonic speeds [NASA-CR-1814411 p 16 N88-10012 SUPERSONIC TEST APPARATUS [ NASA-TP-27531 p 17 N88-10771 STRUCTURAL DESIGN CRITERIA Verification of compressor data accuracy by uncertainty TAKEOFF Stress intensity factors and residual strength of a analysis and testing methods Noise of a model high speed counterrotation propeller cracked stiffened panel p 50 A88-13083 [ASME PAPER 87-GT-1651 p 30 A88-11076 at simulated takeofffapproach conditions (F7fA7) SURFACEGEOMETRY [NASA-TM-100206] p 61 N88-10592 STRUCTURALMEMBERS TAPERING Possibilities for the modeling of dynamically loaded Observations and analyses of natural laminar flow over Improved oil-off survivability of tapered roller bearings cylindrical structural parts in the wind tunnel a nonlifting airframe surface [ NASA-CR-1808041 p 53 N68-11135 [KU-SFB-210/T/24] p15 N88-10005 [SAE PAPER 8710201 p 15 A88-13096 SURFACE NAVIGATION TARGET ACQUISITION STRUCTURAL RELIABILITY Autonomous processing using a blackboard chipset NDE at twelve o'clock high p 48 A88-11585 Autonomous onboard collision avoidance for aircraft and ships p21 A88-10687 [AIM PAPER 87.28551 p 59 A88-12575 Ensuring the service life of designs (experience in aircraft TARGET RECOGNITION construction) p 1 N88-10986 SURFACEROUGHNESS Use of a liquidtrystal and heater-element composite Detection of targets in the presence of clutter using STRUCTURAL VIBRATION for quantitative. high-resolution heat-transfer coefficivts target echo modulations caused by rotating structures On predicting the resonant response of bladed disk on a turbine airfoil including turbulence and [ REPT-12-86] p50 N88-10231 assemblies surface-roughness effects p 44 ABB-10969 TASK COMPLEXITY [ASME PAPER 87-GT-1581 p A88-1 1070 30 Experience about the application and valuation of Perspective traffic display format and airline pilot traffic SUBSONIC AIRCRAFT roughness strips for boundary layer transition control in avoidance p 58 A88-12639 Aircraft acoustics I - Eaerior noise of subsonic wind tunnel tests in the high-speed range TECHNOLOGICAL FORECASTING passenger aircraft and helicopters .--Russian book [ESA-lT-1028] p 51 N88-10278 Prepare for the 2191 century - The 1987 Alexander A. p61 A88-10047 SURFACE ROUGHNESS EFFECTS Nikolsky Lecture --- examples of future design possibilities SUBSONIC FLOW The effect of grit roughness on the performance of the of helicopters p 24 A88-12645 Amtrary wings of low aspect ratio in subsonic flow Wortmann FX63-137 airfoil at a chord Reynolds number TECHNOLOGY ASSESSMENT p 3 A88-10660 of 100,000 p 11 A88-11202 Color display technology - An overview Viscidlinvisdd interaction analysis of subsonic turbulent SURFACETEMPERATURE [SAE PAPER 8616921 p 43 A88-10170 trailingedge flows p 14 A88-12282 Procedures for determining surface heal flux using thin The importance of modern positioning and navigation SUBSONIC WIND TUNNELS film gauges on a coaled metal model in a transient test technology for ATC p 20 A88-10678 Dynamic wind tunnel balances in the DFVLR subsonic facility Development and trends in radio position finding wind tunnel in Braunschweig p 39 A88-12486 [ASME PAPER 87-GT-951 p 45 A88-11034 p 20 A88-10680 SUPERCOMPUTERS SURVIVAL Inertial navigation . Technological status and Advanced computing for manufacturing Improved oil-off survivability of tapered roller bearings development trends p 20 A88-10682 p60 A88-13109 [ NASA-CR-1808041 p 53 NEB-1 1135 The United Kingdom engine technology demonstrator SUPERCRITICAL AIRFOILS SUSPENDING (HANGING) programme Aircraft and equipment factors in the occurrence of A transonic model representation for two-dimensional [ASME PAPER 87-GT-2031 p31 AM-11107 suspension line twists with US. Army parachutes wall interference assessmant Aerodynamics at low Reynolds numbers ~ A review of p 19 A88-12644 [ NLR-TR-86026-U1 p15 N88-10006 theoretical and experimental research at Delft University SWEPT WINGS SUPERCRITICAL FLOW of Technology p8 A88-11177 Investigations 01 separated flow states on wings of Theoretical and experimental analysis of a compressor Softcopy versus hardcopy ... digital image displays for medium aspect ratio taking into account wind tunnel the aerial reconnaissance p 27 A88-12750 cascade at supercritial flow conditions interference problem [ASME PAPER 87-GT-2561 p8 A86-11136 [ETN-87-90437] p17 N88-10016 Recent developments in infrared data processing SUPERSONIC COMBUSTION Measurement techniques in low-spe6d turbulent flows: p 28 A88-12751 Applicability of a diffusion combustion model to the A report on EUROMECH 202 Investigation of the suitability of the 8fl x 6ft transonic analysis of supersonic turbulent reacting jets [ NLR-MP-86038-Ul p 51 N88-10283 wind-tunnel for aeroacoustic research on propellers p40 AM-10180 SWIRLING [RAE-TM-AERO-2093] p39 N88-10041 SUPERSONIC COMBUSTION RAMJET ENGINES Analytical study of swirler effects in annular propulsive A survey of aircraft integrated control technology Evolution and application of CFD techniques for scramjet nozzles p 28 A88-10362 [AR-004-561] p37 N88-10794 engine analysis p 28 A88-10358 Sealing of a shrouded rotor-stator system with pre-swirl Transmission efficiency in advanced aerospace The scramjet - Toward Mach 4-25 flight coolant powerplant p33 A88-13095 [ASME PAPER 87-GT-721 p 45 A88-11016 [PNR903911 p53 N88-11133

A-20 SUBJECT INDEX TRANSONIC WIND TUNNELS

TECHNOLOGY UTILIZATION THREE DIMENSIONAL BODIES TRANSFER ORBITS New Soviet helicopter technology and its potential for Necessary optimali conditions for three-dimensional Analysis of free molecular effects on the attitude of industrial use p 1 A88-10657 bodies in supersonic gas flow p 2 A88-10300 satellites in geostationary transfer orbit. Part 2 Force and Composite directions at Kaman p 41 A88-12414 Problem and solution formulations for the generation torque measurement in free molecular wind tunnel tests TELEMETRY of 30 block-structured grids --- aircraft design [ DNLR-IB-222-86-A-07] p 40 N88-10078 Fiber optic engineering sensor system. Preliminary [NLR-MP-86020-U] p 25 N88-10028 TRANSIENT RESPONSE program management plan, phase 3 revision THREE DIMENSIONAL FLOW Application of the transient test technique to measure [AO-A183663] p62 N88-10608 Calculation of three-dimensional viscous flows in local heat transfer coefficients associated with augmented TELEVISION TRANSMISSION turbomachinery with an implicit relaxation method airfoil cooling passages Video data link provides television pictures in near real p2 A88-10357 [ASME PAPER 87-GT-2121 p47 A88-11112 time via tactical radio and satellite channels Experimentalstudy of three-dimensionalseparated flow TRANSMISSION EFFICIENCY p49 A88-12732 surrounding a hemispherecylinder at incidence Transmission efficiency in advanced aerospace TEMPERATURE DISTRIBUTION [AIM PAPER 87-24921 p3 A88-10498 powerplant

Supersonic flow around a sphere in a thermal Three-dimensional flow in a rotor ~ A strictly [PNR90391] p53 N88-11133 inhomogeneity p2 A88-10264 three-dimensional calculation of flows in turbomachines TRANSMISSION LINES On the mixing of a row of jets with a confined using the S1 42 method p44 A88-10628 Extended systems of variable structure with mobile crossflow p 54 N88-11154 A simplified method for 3-0 potential flow in radio-communicationobjects p 44 A88-10726 TEMPERATURE MEASUREMENT turbomachinery using vortex sheet boundary conditions TRANSMISSIONS (MACHINE ELEMENTS) Neutron and positron techniques for fluid transfer system [ASME PAPER 87-GT-281 p 3 A88-10989 Transmission efficiency in advanced aerospace analysis and remote temperature and stress Three-dimensional calculation of wall boundary layer powerplant measurement flows in twbomachines [PNR90391] p 53 N88-11133 [ASME PAPER 87-GT-2191 p48 A88-11116 [ASME PAPER 87-GT-821 p 4 A88-11022 Improved oil-off survivability of tapered roller bearings TEMPERATURE MEASURING INSTRUMENTS Numencal solution of threedimensionalturbulent flows [NASA-CR-1808041 p 53 NEB-1 1135 Procedures for determining surface heat flux using thin for modern gas turbine components TRANSONIC COMPRESSORS film gauges on a coated metal model in a transient test [ASME PAPER 87-GT-841 p 4 A88-11024 Verification of compressor data accuracy by uncertainty facility Shock embedding discontinuous solution of elliptic analysis and testing methods [ASME PAPER 87-GT-951 p 45 A88-11034 equation for inverse problem of transonic S2 flow [ASME PAPER 87-GT-1651 p 30 A88-11076 TEMPERATURE PROFILES [ASME PAPER 87-GT-1151 p 5 A88-11043 Characterizationof shock wave end wall boundary layer A trace gas technique to study mixing in a turbine A discussion of the mean S2 stream surfaces applied interactions in a transonic compressor rotor stage to quasi-three-dimensional calculation programs for [ASME PAPER 87-GT-1661 p 6 A88-11077 [ASME PAPER 87-GT-1181 p 5 A88-11046 turbomachinery design The aeromechanicalresponse of an advanced transonic TEMPERATURESENSORS [ASME PAPER 87-GT-1501 p 5 A88-11067 compressor to inlet distortion Development of heat flux sensors for turbine airfoils Application of advanced computational codes in the [ASME PAPER 87-GT-1891 p 31 A88-11094 p 54 N88-11143 design of an experiment for a supersonic throughflow fan TRANSONIC FLIGHT TENSILE STRENGTH rotor An aerodynamic design study of transonic transport Cyclic spinning testing of aero-engine discs [ASME PAPER 87-GT-1601 p6 A88-11072 wings p 15 A88-13078 [ASME PAPER 87-GT-2591 p 32 A88-11139 Development and application of a huh frequency wedge TRANSONIC FLOW TENSILE STRESS probe Multigrid solution of the Euler equations on unstructured ConstiMwe modeling of superalloy single crystals with [ASME PAPER 87-GT-2161 p47 A88-11114 and adaptive meshes p44 A88-10570 verification testing p 43 “3-11169 Calculation of a three-dimensional turbomachinery rotor Numerical solution of stream function equations in TENSILE TESTS flow with a Navier-Stokes code transonic flows Creep fatigue life prediction for engine hot section [ASME PAPER 87-GT-2321 p7 A88-11125 [ASME PAPER 87-GT-181 p3 A88-10983 materials (isotropic): Third year progress review Flow in a model turbine stator p 55 N88-11163 Navier-Stokes solution for steady two-dimensional p 55 NEB-111 73 THRUST AUGMENTATION transonic cascade flows Elevated temperature crack growth Similarity of ejector wall-pressure distributions [ASME PAPER 87-GT-541 p4 A88-11005 p 55 NEB-111 74 p 49 A88-12294 Shock embedding discontinuous solution of elliptic TERMINAL FACILITIES TILT ROTOR AIRCRAFT equation for inverse problem of transonic S2 flow Issues in air transport and airport management Recent tilt rotor flight control law innovations [ASME PAPER 87-GT-1151 p 5 A88-11043 [P887-204509] p 19 N88-10782 p36 A88-12646 The performance estimation of transonic turbine at TETHERLINES TILT ROTOR RESEARCH AIRCRAFT PROGRAM design and off-designconditions Aircraft and equipment factors in the Occurrence of Flight researh at NASA Ames Research Center: A test [ASME PAPER 87-GT-1481 p 30 A88-11066 suspension line twists with U.S. Army parachutes pilot‘s perspective Numerical computation of non-isentropic potential p 19 A88-12644 [NASA-TM-100025] p 25 N88-10788 equations for transonic cascade flows THERMAL CONTROL COATINGS TIME DEPENDENCE [ASME PAPER 87-GT-1591 p5 A88-11071 Thermal expansion mismatch and oxidation in thermal 3D inelastic analysis methods for hot Section A multigrid algorithmfor 2-0 transonic potential cascade banier coatings p56 NEB-11182 components p55 N88-11164 flow THERMAL PROTECTION TIME MARCHING [ASME PAPER 87-GT-1801 p 6 A88-11088 Thermal barrier coating lie prediction model Global marching technique for predicting separated The base pressure and loss of a family of four turbine development p56 N88-11183 flows Over arbitrary airfoils p 14 A88-12293 blades Thermal bamer coating lie prediction model TOMOGRAPHY [ASME PAPER 87-GT-2021 p7 AM-11106 development p56 N88-11185 Neutron and positron techniquesfor fluid transfer system Transonic expansions p 13 A88-12059 THERMAL STRESSES analysis and remote temperature and stress Refined numerical solution of the transonic flow past a Cyclic spinning testing of aero-engine discs measurement wedge p 14 A88-12280 [ASME PAPER 87-GT-2591 p 32 A88-11139 [ASME PAPER 87-GT-2191 p48 A88-11116 Two-dimensional transonic aerodynamic design TnERMODVNAMIC EFFICIENCY TOROUEMETERS method p 14 A88-12284 Thermodynamics and performance projections for Analysis of free molecular effects on the altiiude of Transonic analysis and design of axisymmetric bodies intercooled/reheat/recuperatedgas turbine systems satellites in geostationary transfer orbit. Part 2: Force and in nonuniform flow [ASME PAPER 87-GT-1081 p46 A88-11040 torque measurement in free molecular wind tunnel tests [NASA-CR-4101I p 16 N88-10013 A trade-off study of rotor tip clearance flow in a [ ONLR-IB-222-86-A-071 p 40 N88-10078 A method for the calculation of transonic flows for the turbinefexhaust diffuser system TRACE ELEMENTS control of adaptive wind tunnels [ASME PAPER 87-GT-2291 p 32 A88-11123 Labyrinth seal flow measurement by tracer gas [ETN-87-90411I p17 N88-10015 THERMODYNAMIC PROPERTIES injection Computation of transonic separated wing flows using Combustion gas properties. 111 - Prediction of the [ASME PAPER 87-GT-1871 p 47 A88-11092 an EulerlNavier-Stokes zonal approach thermodvnamic or0Dertie.s of combostion oases of aviation TRACKING PROBLEM [NASA-TM-88311] p52 N88-11089 and diesel fuels ’ Towards the design of an intelligent aerospace system TRANSONIC SPEED [ASME PAPER 87-GT-491 p40 A88-11001 [AIM PAPER 87.28441 p 26 A88-12569 Comparison of wind tunnel and flight test afterbody and THERMOMETERS TRAILING EDGES nozzle pressures for a twin-jet fighter aircraft at transonic Thin-film temperature sensors deposited by radio Arbitrary wings of low aspect ratio in subsonic flow speeds frequency cathodic sputtering p 50 A88-12903 p3 A88-10660 [NASA-TP-2588] p 17 N88-10765 THERMOSElTING RESINS The base pressure and loss of a family of four turbine Effect of empennage arrangement on single-engine Composite structural materials blades nonle/afterbody static pressures at transonic speeds [ NASA-CR-181416] p 56 N88-11186 [ASME PAPER 87-GT-2021 p7 A88-11106 [ NASA-TP-27531 p 17 N88-10771 THIN FILMS Viscid/inw& interaction analysis of subsonic turbulent TRANSONIC WIND TUNNELS Procedures for determining surface heat flux using thin trailing-edge flows p 14 A88-12282 A method for the calculation of transonic flows for the film gauges on a coated metal model in a transient test TRAINING AIRCRAFT control of adaptive wind tunnels facility Altitude tests of the XF3-30 turbofan [ETN-87-90411I p17 N88-10015 [ASME PAPER 87-GT-951 p 45 A88-11034 [ASME PAPER 87-GT-251 p28 A8810987 Investigation of the suitability of the 8fl x 6ft transonic Thin-film temperature sensors deposited by radio Development of the XF3-30 turbofan engine wind-tunnel for aeroacoustic research on propellers hequency cathodic sputtering p50 A88-12903 [ASME PAPER 87-GT-261 p28 ABS10988 [RAE-TM-AERO-2093] p39 N88-10041 THIN WINGS TRAJECTORY ANALYSIS Wall interference tests of a CAST 10-2/DOA 2 airfoil Optimal litling wings with required longitudinal balancing Approach trajectory planning system for maximum in an adaptive-wall test Section characteristics p 14 A88-12075 concealment [NASA-TM-4015] p 1.9 N88-10772 Calculation of aerodynamic heat transfer for blunt-nosed [NASA-TM88258] p60 N88-11435 Intergration effects of D-shaped. underwing, thin wings at different angles of attack at supersonic TRANSDUCERS aft-mounted. separate-flow, flow-through nacelles on a Optical systems for gas turbine engines high-wing transport ~~-l720127] p 18 N88-10776 p 49 A88-12657 [NASA-TM-40181 p 18 N88-10773

A-2 1 TRANSPORT AIRCRAFT SUBJECT INDEX

TRANSPORT AIRCRAFT Experimentalverification of vapor deposition rate theory Three-dimensional llow in a rotor . A strictly An integrated display for vertical situation awareness in high velocity burner rigs p 43 NEB-111 79 three-dimensional calculation of flows in turbomachines in commercial transport aircraft Thermal expansion mismatch and oxidation in thermal using the SI32 method p 44 A88-10628 [SAE PAPER 8617701 p 57 A88-10158 barrier coatings p 56 N88-111 82 Prediction of turbulent source flow between corotating An Orient Express to capture the market TURBINE ENGINES disks with an anisotropic two-equation turbulence model p 1 A88-10370 Electronic trend monitoring and exceedance recording [ASME PAPER 67-GT-731 p 45 A88-11017 The impact 01 modern technology on aircraft avionics systems - A means to improved turbine engine reliability Three-dimensional calculation of wall boundary layer equipment p 26 A88-10679 [ASME PAPER 87-GT-871 p 29 A88-11027 flows in turbomachines [ASME PAPER 87-GT-821 p4 A88-11022 Flight director guidance for MLS p 21 A88-10874 Time-averaged heat-flux distributions and comparison A discussion of the mean S2 stream surfaces applied The Antonov An-74 brings high tech to low with prediction lor the Teledyne 702 HP turbine stage to quasi-three-dimensional calculation programs for temperatures p 23 A88-10876 [ASME PAPER 87-GT-1201 p 30 A88-11048 High-liftdevice design and low-speed wind-tunnel test turbomachinery design Introduction and application of the General Electric p 15 A88-13079 [ASME PAPER 87-GT-1501 p 5 A88-11067 turbine engine monitoringsoftware within KLM Royal Dutch Full-scale transport controlled impact demonstration Unified equation 01 motion (UEM) approach as applied Airlines program to SI turbomachinery problems [ASME PAPER 87-GT-1671 p A88-11078 [NASA-TM-89642] p 19 N88-10021 30 [ASME PAPER 87-GT-1791 p6 A88-11087 lntergration effects of D-shaped. underwing, Applied reliabilitylmaintainability methodology as a The turbomachine blading design achieved by solving alt-mounted, separate-flow. flow-through nacelles on a function within life cycle cost ___ of aircraft turbine engine the inverse field problem high-wing transport [ASME PAPER 87-GT-1721 p 46 A88-11082 [ASME PAPER 87-GT-2151 p31 A88-11113 [NASA-TM-40181 p 18 N88-10773 Plume infrared signature measurements and comparison A method for calculating turbulent boundary layers and TRANSPORTTHEORY with a theoretical model -__of turboshaft engines losses in the flow channels of turbomachines Numerical solutions of scramjet nozzle flows p 33 A88-12836 [ASME PAPER 87-GT-2251 p7 A88-11121 p2 A88-10359 Blade loss transient dynamics analysis, volume 1. Task Optical flow diagnostic measurements in TURBINE BLADES 2 TETRA 2 theoretical development turbomachinery A simplified method for 3-D potential flow in [ NASA-CR-1796321 p 34 N88-10791 [PNR90396] p 52 NEB-11081 turbomachinery using vortex sheet boundary conditions Blade loss transient dynamics analysis, volume 2. Task TURBOPROP AIRCRAFT [ASME PAPER 87-GT-281 p3 A88-10989 2: TETRA 2 user's manual Noise of a model high speed counterrotation propeller Friction damping of random vibration in gas turbine [ NASA-CR-1796331 p 34 NEB-10792 at simulated takeofflapproach conditions (F71A7) engine airfoils Development of heat flux sensors for turbine airfoils [NASA-TM-100206] p 61 N88-10592 [ASME PAPER 87-GT-441 p 29 A68-10996 p 54 N88-11143 TURBOPROP ENGINES Procedures for determining surface heat flux using thin Thermal barrier coating life prediction model Velocity scaled aeroelastic testing of advanced film gauges on a coated metal model in a transient test development p 56 N88-11185 turboprops facility TURBINE EXHAUST NOZZLES [ASME PAPER 87-GT-2091 p 31 A88-11110 [ASME PAPER 87-GT-951 p 45 A88-I 1034 High-temperature sheet materials for gas turbine Advanced turboprop wing installation effects measured A qualitative method for determining the temperature applications p 42 A88-12635 by unsteady blade pressure and noise pattern of run gas turbine blades TURBINE INSTRUMENTS [ NASA-TM-1002001 p 15 NEB-10008 [ASME PAPER 87-GT-1021 p 45 A88-11037 Optical systems for gas turbine engines TURBOSHAFTS Computer predictions of erosion damage in gas p 49 A88-12657 Plume infrared signature measurements and comparison turbines TURBINE WHEELS with a theoretical model _-- of turboshaft engines [ASME PAPER 87-GT-1271 p 46 A88-11054 Localization of natural modes of vibration in bladed p 33 A88-12836 A discussion of the mean S2 stream surfaces applied disks The design of a turboshaft speed governor using modern to quasi-three-dimensional calculation programs for [ASME PAPER 87-GT-461 p 29 A88-10998 control techniques turbomachinery design Developments in disc materials --- for gas turbine [NASA-CR-175046] p 51 N88-10339 [ASME PAPER 87-GT-1501 p5 A88-11067 engines p 42 A88-12632 TURBULENCE Unified equation of motion (UEM) approach as applied TURBOCOMPRESSORS Impact of turbulence modeling on numerical accuracy to SI turbomachinery problems Through-flow analysis of a multi-stage compressor and efficiency of compressible flow simulations [ASME PAPER 87-GT-1791 p6 A88-11087 operating at near-stall conditions [ NASA-TM-883331 p 52 N88-11088 Applications of ceramic coating on the turbine blades [ASME PAPER 87-GT-511 p 4 A88-11003 Prediction of turbine blade heat transfer of the AGTJ-1M)B A new method (FTDCDF) for blade design of p 54 N88-11162 [ASME PAPER 87-GT-1901 p 41 A88-11095 axiallmixed-flowcompressors and its applications Flow in a model turbine stator p 55 N88-11163 Film cooling of a turbine blade with injection through [ASME PAPER 87-GT-1831 p 31 A88-11090 TURBULENCEEFFECTS two rows 01 holes in the near-endwall region Modelling the unsteady flow in a turbine rotor passage Imaging through the atmosphere for airborne [ASME PAPER 87-GT-1961 p47 A88-11100 [ASME PAPER 67-GT-1971 p 7 A68-11101 reconnaissance p 27 A88-12748 The base pressure and loss of a family of four turbine Developmentand application of a high frequency wedge TURBULENTBOUNDARYLAYER blades probe Pressure field due to drag reducing outer layer devices [ASME PAPER 87-GT-2021 p7 A88-11106 [ASME PAPER 87-GT-2161 p47 A88-11114 in turbulent boundary layers p3 A88-10492 The turbomachine blading design achieved by solving Inter and intra blade row laser velocimetry studies of Three-dimensional calculation of wall boundary layer the inverse field pfoblem gas turbine compressor flows flows in turbomachines [ASME PAPER 87-GT-2151 p31 A88-11113 [ASME PAPER 87-GT-2351 p7 A88-11126 [ASME PAPER 87-GT-821 p 4 A88-11022 Development and application of a high frequency wedge Modeling and measurement of heat transfer on turbine Modelling the unsteady flow in a turbine rotor passage probe blade tips p 33 N88-10032 [ASME PAPER 87-GT-1971 p7 A88-11101 [ASME PAPER 87-GT-2161 p47 A88-11114 Investigation of the excitation of turbine blade vibration Comparison of predicted and measured velocities in a A trade-off study of rotor tip clearance flow in a in axial compressors in rotating stall compressor disk drum model turbinelexhaust diffuser system [ ETN-87-903771 p 34 N88-10035 [ASME PAPER 87-GT-2081 p 47 A88-11109 [ASME PAPER 87-GT-2291 p 32 A88-11123 TURBOFAN AIRCRAFT A study of the effects of thermal barrier coating surface Modeling and measurement of heat transfer on turbine Altitude tests of the XF3-30 turbofan roughness on the boundary layer characteristics of blade tips p33 N88-10032 [ASME PAPER 87-GT-251 p 28 A88-10987 gas-turbine aerofoils Investigation of the excitation of turbine blade vibration TURBOFAN ENGINES [ASME PAPER 87-GT-2231 p 48 A88-11120 in axial compressors in rotating stall Counterrotating differential cylindrical roller bearing A method for calculating turbulent boundary layers and [ETN-87-90377] p34 N88-10035 development losses in the llow channels of turbomachines Experimental determination 01 the oscillatory forces on [AIAA PAPER 87-18431 p 43 A88-10497 [ASME PAPER 87-GT-2251 p 7 A88-11121 two turbine blade pfofiles Altitude tests of the XF3-30 turbofan Particle transport across the transpired turbulent [ETN-87-90417] p 34 N88-10037 [ASME PAPER 87-GT-251 p 28 A88-10987 boundary layer Blade loss transient dynamics analysis, volume 1. Task Development of the XF3-30 turbofan engine [ASME PAPER 87-GT-2651 p 48 A88-11142 2: TETRA 2 theoretical development [ASME PAPER 87-GT-261 p 28 A88-10988 Heat transfer with very high free stream turbulence [ NASA-CR-1796321 p 34 N88-10791 Investigation of integrated selection of optimum engine p 54 N88-11161 Blade loss transient dynamics analysis, volume 2. Task cycle parameters TURBULENT DIFFUSION 2: TETRA 2 userk manual [ASME PAPER 87-GT-391 p 29 A88-10993 Applicability of a diffusion combustion model to the [ NASA-CR-1796331 p34 N88-10792 First article test noise suwey of the A/F32T-9 large turbo analysis of supersonic turbulent reacting lets Turbine Engine Hot Section Technology, 1985 fan engine enclosed noise suppressor system, Sky Harbor p 40 A86-10 180 [ NASA-CP-24051 p 53 N88-11140 IAP (International Airport), Phoenix, Arizona TURBULENT FLOW Development of heat flux sensors for turbine airfoils [ AD-A1837991 p 61 N88-10588 Cascade viscous flow analysis using the Navier-Stokes p 54 N88-11143 The wide chord fan blade: A Rolls Royce first equations p 2 A88-10356 Prediction of turbine blade heat transfer [PNR90416] p 34 N88-10789 Prediction of turbulent source flow between wrotating p54 N88-11162 TURBOJET ENGINES disks with an anisotropic two-equation turbulence model 3D inelastic analysis methods for hot Section Investigation of integrated selection of optimum engine [ASME PAPER 87-GT-731 p 45 A88-11017 components p55 N88-11164 cycle parameters 3-D inelastic analysis methods for hot section [ASME PAPER 87-GT-391 p 29 A88-10993 Numerical prediction of turbulent flow in rotating components p60 N88-11165 TURBOMACHINE BLADES cavities Component specific modeling p 60 NEB-11166 A generalized numerical method for solving direct [ASME PAPER 87-GT-741 p 45 A88-11018 Constitutive modeling of superalloy single crystals with inverse and hybrid problems of blade cascade flow by Numerical solution of three-dimensionalturbulent flows verification testing p 43 N88-111 69 using streamline-co-ordinateequation for modern gas turbine components Constitutive modeling for isotropic materials [ASME PAPER 87-GT-291 p 4 A88-10990 [ASME PAPER 87-GT-841 p 4 A88-11024 p 55 NEB-111 71 TURBOMACHINERY Effect of rib angle on local heatlmass transfer Constitutive modelina for isotrwdc materials Ex~liitmultiarid alaorithm for auasi-three-dimensional distribution in a two-DBSSrib-rouahened channel ' p 55 N88-11172 viscous flows in turbomachinery ' p 2 A88-10355 [ASME PAPER 87-GT-941 - p 45 A86-11033

A-22 SUBJECT INDEX WIND MEASUREMENT

Flow investigations on swirling compressible flow V VISCOUS FLOW through a vaneless radial diffuser Explicit multigrid algorithm for quasi-three-dimensional [ASME PAPER 87-GT-1931 p 7 A88-11097 V/STOL AIRCRAFT viscous flows in turbomachinery p2 A88-10355 A method for calculating turbulent boundary layers and Flight researh at NASA Ames Research Center: A test Cascade viscous llow analysis using the Navier-Stokes losses in the flow channels of turbomachines pilot's perspective equations p2 A88-10356 [ASME PAPER 87-GT-2251 p 7 A88-11121 [NASA-TM-100025] p 25 N88-10788 The design of shock-free compressor cascades Boundary layer profile investigations downstream of an VANELESS DIFFUSERS including viscous boundary layer effects aero-engine intake anti-icing air exhaust slot Flow investigations on swirling compressible flow [ASME PAPER 87-GT-71I p4 A88-11015 [ASME PAPER 87-GT-2371 p 32 A88-11127 through a vaneless radial diffuser An analysis of unsteady. two-dimensional separation [ASME PAPER 87-GT-1931 p7 A88-11097 Viscidlinviscidinteraction analysis of subsonic turbulent bubbles p9 A88-11182 trailing-edge flows p 14 A88-12282 VANES Use of a liquidcrystal and heater-element composite The calculation of flow about aerofoils at low Reynolds number with application to remotely piloted vehicles Measurement techniques in low-speed turbulent flows: for quantitative. high-resolution heat-transfer coefficients p 11 A88-11197 A remon EUROMECH 202 on a turbine airfoil including turbulence and [NLR-MP-86038-U] p 51 N88-10283 surface-roughnesseffects p 44 A88-10969 VOLATILITY Fuel-injectorlair-swidcharacterization Compressor turbine vane ring (PT6 engine) repair Cost savings possible with Air Force conversion to JP-8 p 54 N88-11150 development as its primary fuel TURBULENTJETS [ASME PAPER 87-GT-471 p 29 A88-10999 [ AD-A1837841 p 42 N88-10192 Heat transfer to arrays of impinging jets in a crossflow Turbine Engine Hot Section Technology, 1985 VORTEXGENERATORS [ASME PAPER 87-GT-1981 p 47 A88-11102 [NASA-CP-2405] p 53 N88-11140 Further visualization of combined wing tip and starting TURBULENT MIXING Development of heat flux sensors for turbine airfoils vortex systems p 14 A88-12276 Parabolized Navier-Stokes analysis of ducted p 54 N88-11143 VORTEX SHEETS supersonic combustion problems p 2 A88-10361 Component specific modeling p 60 N88-11166 A simplified method for 3-D potential flow in Strong gas injectin into supersonic flow with turbulent Constitutive modeling for isotropic materials turbomachinery using vortex sheet boundary conditions mixing p 13 A88-12056 p 55 N88-11172 [ASME PAPER 87-GT-281 p3 A88-10989 TURBULENT WAKES VAPOR DEPOSITION VORTICES Experimentson spray interactions in the wake of a bluff Experimentalverification of vapor deposition rate theory Multigrid localization and multigrid grid generation for in high velocity burner rigs p 43 N88-11179 WY the computation of vortex structures and dynamics of flows [ASME PAPER 87-GT-481 p44 AM-11000 VARIABLE CYCLE ENGINES in cavities and about airfoils p 3 A88-10562 Multimodes to Mach 5 p 28 A88-10371 Modelling the unsteady flow in a turbine rotor passage Further visualization of combined wing tip and starting VARIABLE GEOMETRY STRUCTURES [ASME PAPER 87-GT-1971 p7 A88-11101 vortex systems p14 AM-12276 Gff-desgn performance of supersonic compressors with A natural low frequency oscillation in the wake of an The development of wing theory p 14 A88-12483 airfoil near stalling conditions fixed and variable geometry VORTICITY [ASME PAPER 87-GT-1161 p5 A88-11044 [NASA-TM-100213] p 18 N88-10779 Momentum exchanges and energy transfers in cross TWISTING VELOCITY flow fans Analytical modeling of helicopter static and dynamic Aircraft and equipment factors in the occurrence of [ASME PAPER 87-GT-321 p 44 A88-10992 induced velocity in GRASP suspension line twists with US. Army parachutes [NASA-TM-1000261 p 18 N88-10777 p 19 A88-12644 TWO DIMENSIONAL BOUNDARY LAYER VELOCITY DISTRIBUTION W A new method of calculating optimum velocity Prediction of turbine blade heat transfer distribution along the blade surface on arbitrary stream p54 N88-11162 WALL FLOW surface of revolution in turbomachines TWO DIMENSIONAL FLOW A new method of calculating optimum velocity [ASME PAPER 87-GT-301 p4 A88-10991 A new method of calculating optimum velocity distribution along the blade surface on arbitrary stream Analysis of windage and velocity distribution for distribution along the blade surface on arbitrary stream losses surface of revolution in turbomachines surface of revolution in turbomachines a shrouded rotating disk [ASME PAPER 87-GT-301 p4 A88-10991 [ASME PAPER 87-GT-1861 p 6 A88-11091 [ASME PAPER 87-GT-301 p 4 A88-10991 Threedimensional calculation of wall boundary layer Comparison of predicted and measured velocities in a Navier-Stokes solution for steady two-dimensional flows in turbomachines compressor disk drum model transonic cascade flows [ASME PAPER 87-GT-821 p 4 A88-11022 [ASME PAPER 87-GT-2081 p 47 A88-11109 [ASME PAPER 87-GT-541 p4 A88-11005 Characterizationof shock wave end wall boundary layer Velocity scaled aeroelastic testing of advanced A smoke-wire study of low Reynolds number flow over interactions in a transonic compressor rotor turboprops [ASME PAPER 87-GT-1661 p 6 A88-11077 a NASA LRN(1) ~ 1007 airfoil Section p 9 A88-11181 On the determination of the 2-D characteristics of [ASME PAPER 87-GT-2091 p 31 A88-11110 Wall interference tests of a CAST 10-2lDOA 2 airfoil aerofoils at low Reynolds numbers p 10 A88-11192 VELOCITY MEASUREMENT in an adaptive-Wall test Section Twodimensional transonic aerodynamic design Developmentand application of a high frequency wedge [NASA-TM-4015] p 18 N88-10772 method p 14 A88-12284 probe WALL PRESSURE A transonic model representation lor two-dimensional [ASME PAPER 87-GT-2161 p 47 A88-11114 Pressure field due to drag reducing outer layer devices wall interference assessment Airspeed measurement with a C02 lidar in turbulent boundary layers p3 AM-10492 [ NLR-TR-86026-UI p 15 N88-10006 p 26 A88-12655 Similanty of ejector wall-pressure distributions TWO PHASE FLOW An ObseNW approach to the estimation of helicopter p 49 A88-12294 Analysis of supersonic heterogeneous flow impinging airspeed WALL TEMPERATURE on an obstacle p 14 A88-12074 [DNLR-FB-87-13] p 25 N88-10029 Prediction of gas turbine combustor-liner temperature VERTICAL ORIENTATION [ASME PAPER 87-GT-1771 p 31 A88-11085 An integrated display for vertical situation awareness WEAPON SYSTEMS U in commercial transport aircraft Design principles and practices for implementation of [SAE PAPER 8617701 p 57 A88-10158 MIL-STD-1760 in aircraft and stofes ULTRASONIC TESTS VERTICAL TAKEOFF AIRCRAFT [ AD-AI 837241 p24 N88-10027 NDE at twelve o'clock high p 48 A88-11585 Digital controls for gas turbine engines WEAPONS DELIVERY

UNIFORM FLOW [ASME PAPER 87-GT-2111 p 31 A88-11111 Robotic air vehicle ~ A pilot's perspective Analysis of supersonic heterogeneous flow impinging VIBRATION p 19 A88-10437 on an obstacle p 14 A88-12074 Investigation of the excitation of turbine blade vibration WEAR TESTS UNSTEADY FLOW in axial compressors in rotating stall Counterrotating differential cylindrical roller bearing Navier-Stokes simulations of rotorlstator interaction [ ETN-87-903771 p 34 N88-10035 development using patched and overlaid grids p 2 A88-10354 Activities report of the Institute of Sound and Vibration [AIAA PAPER 87-18431 p43 A88-10497 Multigrid localization and multigrid grid generation for Research WEDGE FLOW the computation of vortex structures and dynamics of flows [ETN-87-90685] p 61 N88-10589 Refined numerical solution of the transonic flow past a in cavities and about airfoils p 3 A88-10562 VIBRATION DAMPING wedge p 14 A88-12280 Modelling the unsteady flow in a turbine rotor passage Friction damping of random vibration in gas turbine WEIBULL DENSITY FUNCTIONS [ASME PAPER 87-GT-1971 p7 A88-11101 engine airfoils Development of ceramic hot sectin components for Development and application of a hgh frequency wedge [ASME PAPER 87-GT-441 p29 AM-10996 AGT 100 gas turbine A88-1101 9 [ASME PAPER 87-GT-791 p 45 A88-11019 probe An optimal control method for passage of a flexible rotor [ASME PAPER 87-GT-2161 p 47 A88-11114 through resonances p48 A88-11439 WEIGHT REDUCTION Unsteady aerodynamic measurements on a rotating The use of Kevlar on aero-engine fan containment VIBRATIONAL PECTRA compfessor blade row at low Mach number casings [ASME PAPER 87-GT-2211 p7 A88-11118 Diagnosis of flow channel in aircraft gas-turbineengines [PNR90410] p53 NM-11134 An analysis of unsteady, twc-dimensional separation on basis of vibration spectrum characteristics WEST GERMANY bubbles p9 A88-11182 p 35 N88-10993 The history of aeroelasticity research in Germany from On some unsteady aerodynamics characteristics of an VIBRATORY LOADS the beginning until 1945 __-airframes NACA 0012 at Reynolds numbers of 125.000 and Experimental determinatin of the oscillatory forces on [DFVLR-MIlTgG-25] p 1 N88-10003 400.000 p 10 A88-11189 two turbine blade profiles WIND (METEOROLOGY) Advanced turbqxop wing installation effects measured [ETN-87-90417] p34 N88-10037 Global positioning satellite-based automatic landing by unsteady blade pressure and noise VIDEO DATA system and wind estimated feedback for the AH-64 [NASA-TM-100200] p 15 N88-10008 Video data link provides television pictures in near real helicopter p22 N88-10784 USER MANUALS (COMPUTER PROGRAMS) time Via tactical radio and satellite channels WIND MEASUREMENT Blade loss transient dynamics analysis, volume 2. Task p 49 A88-12732 Analyses and assessments of span wise gust gradient 2 TETRA 2 user's manual Synchronizing video signals to standard IRlG time data from NASA 8-576 aircraft [ NASAGR-1796331 p34 N88-10792 codes p 21 A88-12737 [NASA-CR-l78288] p15 N88-10007

A-23 WIND SHEAR

WINO SHEAR Boundary layer profile investigations downstream of an Contributions to the modeling of wnd shear for danger aero-engine intake anti-icing air exhaust Slot studies [ASME PAPER 87-GT-2371 p 32 A88-11127 [ ETN-87-904421 p 57 N88-10463 Particle transport across the transpired turbulent WINOTUNNELAPPARATUS boundary layer Dynamic wind tunnel balances in the DFVLR subsonic [ASME PAPER 87-GT-2651 p 48 A88-11142 wind tunnel in Braunschweig p 39 A88-12488 Possibilities lor the modeling of dynamically loaded A method for the calculation of transonic flows for the cylindrical structural parts in the wind tunnel control of adaptive wind tunnels [ KU-SFB-21O/T/24] p 15 N88-10005 [ETN-87-904111 p17 N88-10015 WINDSHIELDS WINO TUNNEL MODELS The deviation of light rays passing through a curved Possibilities for the modeling of dynamically loaded windscreen --- aircraft cylindrical structural parts in the wind tunnel [BAE-MSC.115] p 62 N88-10610 [ KU-SFB-210/T/24] p15 N88-10005 WING FLAPS A transonic model representation for two-dimensional Design and fabrication trial of a composite flap wall interference assessment structure p 1 A88-13082 [ NLR-TR-86026-Ul p 15 N88-10006 WING PLANFORMS Flutter suppression and gust load alleviation. Part 1: An experimental investigation of the aerodynamics of Results of phase 1 to 3. Part 2: Description of the Garteur the hang glir pll A88-11200 model Further visualization of combined wing tip and starting [MBB-LKE292/S/PUB/191 I p 36 N88-10038 vortex systems p 14 A88-12276 Comparison of wind tunnel and flight test afterbody and Exact and asymptotic expressions of the lift slope nozzle pressures for a twin-jet fighter aircraft at transonic coefficient of an elliptic wing p 14 A88-12292 speeds WING PROFILES [ NASA-TP-25881 p 17 N88-10765 Arbitrary wings of low aspect ratio in subsonic flow WINO TUNNEL STABILITY TESTS p 3 A88-10660 Aerodynamics of unmanned aircraft at full-scale in the A theocetical study of spanwise-periodic 3-0 RAE 24fl wind-tunnel p 12 A88-11204 disturbances in the wake of a slightly stalled wing at low WINOTUNNELTESTS Reynolds numbers p8 A88-11180 Theoretical and experimental analysis 01 a compressor Control surface effects on the low Reynolds number cascade at supercritical flow conditions behavior of the Wortmann FX 63-137 [ASME PAPER 87-GT-2561 p8 A88-11136 p 10 A88-11187 Boundary layer and performance characteristics from WING TIP VORTICES wind tunnel tests of a low Reynolds number Liebeck Further visualization of combined wing tip and starting airfoil p9 AM-11184 vortex systems p 14 A88-12276 Transition and separation control on a low-Reynolds Dispersion in the wake of aircratt: An investigation of number airfoil p9 A88-11186 the effects of a ground plane on trailing vortices. Literature Low Reynolds number wind tunnel measurements - The SUNey importance 01 being earnest p10 A88-11190 [ ICAERO-REP-86-04] p16 N88-10014 Recent wind tunnel experiments at low Reynolds WINGS numbers p 11 A88-11193 Prdcbon of a microlight biplane's aerofoil performance Low-Reynolds number aerodynamics research at NASA using a computer model p 11 A88-11198 Langley Research Center p 11 A88-11194 Aerodynamics of unmanned aircraft at full-scale in the The use of wind tunnel data in the design of radio RAE 24fl wind-tunnel p 12 A88-11204 controlled contest model sailplanes p 24 A88-11195 The development of wing theory p 14 A88-12483 Wind tunnel testing of small scale pressuretapped model Wing design with a three-dimensional transonic inverse propellers p32 A88-11196 method p 14 A88-13077 Preliminary measurements of the flight performance of An aerodynamic design study of transonic transport an RPV compared with wind tunnel and CFD estimates wings p 15 A88-13078 p12 A88-11203 Advanced turboprop wing installation effects measured Wind-tunnel test results of Eppler 387 aerofoils and by unsteady blade pressure and noise comparisons with flight test and computation [ NASA-TM-1002001 p 15 N88-10008 p 12 A88-11208 Wind-tunnel investigation of a full-scale general aviation Development and implementation of an aerodynamic airplane equipped with an advanced natural laminar flow holographic interferometry system p 49 A88-12725 wing Wind-tunnel investigation of a full-scale general aviation [ NASA-TP-27721 p16 N88-10009 airplane equipped with an advanced natural laminar flow Computation of transonic separated wing flows using wing an EulerlNavier-Stokeszonal approach [ NASA-TP-27721 p 16 N88-10009 [ NASA-TM-88311I p 52 N88-11089 Investigations of separated flow states on wings 01 AGARD standard aeroelastic configurations for dynamic medium aspect ratio taking into account the wind tunnel response. Candidate configuration I.-wing 445.6 interference problem [ NASA-TM-1004921 p 56 N88-11202 [ETN87-90437] p17 N88-10016 Investigation of the suitability of the Eft x 611 transonic wind-tunnel for aeroacoustic research on propellers [ RAE-TM-AERO-20931 p39 N88-10041 Analysis of free molecular effects on the attitude 01 satellites in geostationary transfer orbit. Part 2: Force and torque measurement in free molecular wind tunnel tests [ DFVLR-IB-222-86-A-071 p40 N88-10078 Experience about the application and valuation of roughness strips for boundary layer transition control in wind tunnel tests in the high-speed range [ESA-lT-l0281 p51 N88-10278 Comparison of wind tunnel and flight test afterbody and nozzle pressures for a twin-jet fighter aircraft at transonic speeds [ NASA-TP-25881 p 17 N88-10765 Wall interference tests of a CAST 10-2/DOA 2 airfoil in an adaptive-wall test section [NASA-TM-40151 p 18 N88-10772 lntergration effects of D-shaped. underwing, aft-mounted, separate-flow. flow-through nacelles on a high-wing transport [ NASA-TMdOlB] pl8 N88-10773 WINO TUNNEL WALLS A transonic model representation lor two-dimensional wall interference assessment [NLR-TR-86026-U] p15 N88-10006 Wall interference tests of a CAST 10-2IDOA 2 airfoil in an adaptive-wall test don [ NASA-TM-40151 p 18 N88-10772 WIND TUNNELS Momentum exchanges and energy transfers in cross flow fans [ASME PAPER 87-GT-321 p44 A88-10992

A-24 PERSONAL AUTHOR INDEX

~~ AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 223) February 1988

Typical Personal Author Index Listing

ALEKSANDROV, VIKTOR MlKHAlLOVlCH BARNETT, MARK PERSONAL AUTHOR Problems in continuum mechanics with mixed boundary Viscidlinviscid interaction analysis of subsonic turbulent conditions p 43 A88-10017 trailing-edge flows p 14 A88-12282 ALLEN, J. L. BARON, SHELDON A study of the effects of thermal barrier coating surlace Intelligent interlaces to aircraft systems I roughness on the boundary layer characteristics of [AlAA PAPER 87.27761 p 59 A88 12539 GOUCHOE. 0. R. gas-turbine aerofoils F The desian 01 a turboshaft speed qovernor usinq modern BARRETT, CHARLES A. [ASME PAPER 87-GT-2231 p48 A88-11120 control techniques The effect of variations of cobalt content on the cyclic ALTHAUS. DIETER I I NASA-CR-1750461 o 51 N88-10339 oxidation resistance of selected Ni-base superalloys Recent wind lunnel experiments a1 low Reynolds p 40 ~8e-ioo31 numbers p 11 A88-11193 BATILL, STEPHEN M. AMINO, KANlCHl Low Reynolds number wind tunnel measurements. The Wing design with a three-dimensional transonic inverse importance of being earnest p 10 A88-11190 method p 14 A88-13077 An aerodynamic design study of transonic transport BAUMBICK. R. J. wings p I5 A88-13078 Conceptual design of an optic based engine control High-lift-devicedesign and low-speed wind-tunnel test system p 15 A88-13079 [ASME PAPER 87-GT-1681 p 30 A88-11079 ANDO. SHlGENORl BAVUSO. SALVATORE J. A numerical method for subsonic unsteady lifting Reliability modeling of fault-tolerant computer based Listings in this index are arranged alphabetically by surfaces. BIS. 111 - Some additional numerical results systems p37 N88 10801 personal author The title of the document provides p2 A88-10093 BENDIKSEN, 0.0. AOANO, H. Localization of natural modes of vibration in bladed the user with a brief description of the subject Cyclic spinning testing of aero-engine discs disks matter The report number helps to indicate the [ASME PAPER 87-GT-2591 p 32 A88-11139 [ASME PAPER 87 GT-461 p 29 A88-10998 type of document listed (e g , NASA report, ARAFAILOV, S. 1. BENNETT, J. C. translation. NASA contractor report) The page and Effect of energy release in the shock layer on the Fuel injectorlair-swirl characterization supersonic flight of bodies p 13 A88-12073 p 54 N88-11150 accession numbers are located beneath and to the ARM. MASASHI BERDNIKOV, VALERII NIKOLAEVICH right of the title Under any one author's name the Applications of ceramic coaling on the turbine blades Testing of aircraft electrical equipment accession numbers are arranged in sequence with of the AGTJ-t00B p 39 A88-10044 the AlAA accession numbers appearing first [ASME PAPER 87-GT-1901 p 41 A88-11095 BERNHARD, R. J. ARORA. S. C. Prediction of sound fields in cavities using Application of the transient lest technique to measure boundary-element methods p 61 A88-12281 local heal transfer coefficients associaled with augmented BERTELRUD, A. airfoil cooling passages A Measurement techniques in low speed turbulent flows [ASME PAPER 87-GT-2121 p47 A88-11112 A report on EUROMECH ATKINSON. WILLIAM H. 202 ABBITT, J. 0. [ NLR HP-860384 1 p 51 N88-10283 Development of heat flux sensors for turbine airfoils A smoke-wore study of low Reynolds number flow over BERTIN. JOHN J. a NASA LRN(1) - 1007 airfcil seclon p 9 A88-11181 p54 N88-It143 AUER. JOSEPH The aerolhermodynamic environment for holes in ABBOlT, KATHY H. FDA0 - A lablfield test tool p 25 A88-I0436 hypersonic configurations Traditional versus rule-based programming technques [DE87-0146511 p 17 N88-10767 - Appllcaton lo the control 01 optlonal flight information BILLIG, F. S. p 58 A88-10965 6 Numencal solutions of scramjet nozzle flows Implementation of a research prototype onboard fault p2 A88-10359 monilonng and diagnosis system BACHALO. W. 0. BIRCH. STUART [AIM PAPER 87.27771 p59 A88-12540 Expenments on spray interactions in the wake of a bluff Aircraft lyres p 23 A88-10873 ABDALLAH. S. body BIRD. MICHAEL W. Unified equation of motion (UEM) approach as applied [ASME PAPER 87-GT-481 p44 A88-tI000 Application 01 knowledge-based techniques to aircraft to S1 turbomachinery problems BAGANOFF. D. trapctory generatwn and control p 38 NEB-IO811 [ASME PAPER 87-GT-1791 p 6 A88-11087 Similarity of elector wall-pressure distributions BLACHUT. J. ABDEL MESSEH. W. p 49 ABS-12294 Elasbc buckling of internally pressunzed Applicaton of the transtenl test technique lo measure BAILEY, J. M. cylinder-bulkhead combinations p 50 A88-12949 local heat transfer coefficients associated wlh augmented Process support compressor motor electromagnetic BLACK. GERALD airfcil cooling passages design summary Blade loss transient dynamics analysis. volume 1 Task [ASME PAPER 87-GT-2121 p47 A88-11112 [ DE87-0143591 p 52 N88-11048 2 TETRA 2 theoretlcal development ABIR, A. BAILEY, RICHARD S. [NASA-CR-1796321 p34 N88-10791 Stability of conical and curved annular diffusers for The development of a high temperalure s:atic strain gage Blade loss transient dynamics analysis. volume 2 Task mixed-lkw compressors system p 53 N88-11142 2 TETRA 2 user's manual [ASME PAPER 87-GT-1911 p6 A88-11096 BAINES. N. C. [ NASA-CR-1796331 p 34 N88-10792 ACKERMANN. J. A study of the effects of thermal barrier coating surface BLACKWELDER, R. Robust cootrol system deyln p 37 N88-10800 roughness on the boundary layer charactenstics of Boundary layer and performance charactenstics from AGRAWAL, 0. P. gas-turbine aerofoils wind tunnel tests of a low Reynolds number Liebeck Flow investigations on swirling compressible flow [ASME PAPER 87-GT-2231 p48 A88-11120 airfcil p9 A88-11184 thmugh a vaneless ra&al drtfuser BALUTEAU, C. BLAIR. JESSE [ASME PAPER 87-GT-1931 p 7 A88-11097 Auessment.01 sobare quality for the AIRBUS A310 Robollc air vehlcle - A plot's perspecwe p19 A88-10437 AILSLIEGER. ROSS E. automatic pilot p 38 N88-10804 BLOCH, DIANE R. Low COS1 mndowless wckplt research vehlcle BANDYOPADHVAY, P. R. Low Reynolds number w~ndtunnel measurements. The [SA€ PAPER 8617551 p39 A88-10156 Pressure field due to drag reducing outer layer devices importance of bang earnest p10 A88-11190 ALBERGA, 0.0. in turbulent boundary layers p3 A88-10492 BOEHM. MANFRED Ccmpar~sonof predicted and measured veloatms in a BANK. W. Development and WeMs in rado postbon finding WmPWSSW 6sk dNm rod4 Further visualization of combined wing tip and starting p 20 A88-10680 [ASME PAPER 87-GT-2081 p47 A88-11109 vortex systems p 14 A88-12276 BOERMANS, L M. M. ALDER, ti. P. BAR-SEVER, A. Aerodynamics at low Reynolds numbers - A revw of Hydrogen in ar bansportaton - Feaslklity study for Transition and separation wntrol on a low-Reynolds Meorebcal and expenmental research at Dent Unrversily Zunch krpor(. Smtzerland p41 A88-11146 number airfoil p9 A88-11186 of Technology p8 A88-11177 ALEKHIN. V. 1. BARANOVSKII, S. 1. BOERSTOEL, J. W. mqcomplex for a system for the radwacousbc Applicability of a drtfusim wmbustion model to the Problem and sol^ formulams for the generawn swnd'ng Of the atmosphere - Hardware IauIWs analysis of supersonic turbulent reacting jets of 30 Mock-slfucluredgnds 058 Mu)-11394 p40 A88-10180 [ NLR-MP-86020UI p25 N88-10028

B- 1 BOESE, NORMAN W. PERSONAL AUTHOR INDEX

BOESE, NORMAN W. CAGLAYAN, A. K. CHEN. NENG-KUEN Real-time reconnaissance - An engineering Evaluation of a dual processor implementationfor a fault Investigation of high-altitude ignition performance of perspective p 21 A88-12733 inferring nonlinear detection system several Chinese jet fuels with different properties BONCIANI, L [AIAA PAPER 87-27621 p 59 A88-12532 [ASME PAPER 87-GT-1781 p 41 A88-11086 Influence of the Reynolds number on the performance CAI, R. CHEN, P. C. of centrifugal compressors A simplified method for 3-D potential flow in 3D inelastic analysis methods for hot Section [ASME PAPER 87-GT-101 p 44 A88-10979 turbomachinery using vortex sheet boundary conditions components p55 N88-11164 BORER, C. J. [ASME PAPER 87-GT-281 p 3 A88-10989 CHEN. P. H. Influence of the Reynolds number on the performance CAI, RUlXlAN Film cooling of a turbine blade with injection through of centrifugal compressors A multi-gridalgorithm for 2-Dtransonic potential cascade two rows of holes in the near-endwall region [ASME PAPER 87-GT-101 p 44 A88-10979 flow [ASME PAPER 87-GT-1961 p47 A86-11100 BORGMAN. DEAN C. [ASME PAPER 87-GT-1801 p 6 A88-11088 CHENG, H. K. On massive laminar separation and lift anomalies in Building on a successful tradition - Composites at CALLIS, C. L subcritical Re-range p8 A88-11178 MDHC p 41 A88-12415 Applied reliability/maintainability methodology as a CHERNOV, 1. A. BOUCEK, GEORGE P., JR. function within life cycle cost Transonic expansions p 13 A88-12059 Comparison of programmable legend keyboard and [ASME PAPER 87-GT-1721 p 46 A88-11082 dedicated keyboard for control of the flight management CHIKATA, T. CANNON, L W. computer Cyclic spinning testing of aero-engine discs Pack cementation coatings for superalloys A review [SAE PAPER 8617721 p 57 A88-10160 - [ASME PAPER 87-GT-2591 p 32 A88-11139 of history, theory, and practice BOWDEN, T. T. CHILDRESS. OTIS S. [ASME PAPER 87-GT-501 p41 A88-11002 Correlations of fuel performance in a full-scale Helicopter main-rotor speed effects on far-fieldacoustic commercial combustor and two model combustors CANTWELL, BRIAN J. levels [ASME PAPER 87-GT-891 p 29 A88-11028 Computation of transonic separated wing flows using [ NASA-TM-1005121 p 62 N88-11451 BOWEN, B. A. an Euler/Navier-Stokes zonal approach CHIMA, RODRICK V. An expert system for aircraft conflict resolution in dense [NASA-TM-88311I p 52 N88-11089 Explicit multigrid algorithm for quasi-three-dimensional airspaces p 22 NEB-10810 CARLSON, JOHN R. viscous flows in turbomachinery p2 A88-10355 BOYD, G. L lntergration effects of D-shaped. underwing. Application of advanced computational codes in the AGTlOl .Ceramic gas turbine development aft-mounted. separate-flow. flow-through nacelles on a design of an experiment for a supersonic throughflow fan [ASME PAPER 87-GT-2281 p 32 A88-11122 high-wing transport rotor BRAHNEY, JAMES H. [ NASA-TM-00181 p 18 N88-10773 [ASME PAPER 87-GT-1601 p6 A88-11072 Starting system for cold weather p 23 A88-10871 CARRICK, H. B. CHINZEI, NOBUO Flight director guidance for MLS p 21 A88-10874 Three-dimensional calculation of wall boundary layer The scramjet - Toward Mach 4-25 flight HlTB - The ultimate test bed p 23 A88-10875 flows in turbomachines p 33 A88-13095 BRANDER, J. R. G. [ASME PAPER 87-GT-821 p 4 A88-11022 CHOI, J. Issues in air transport and airport management CARRIER, D. M. Recent developmentsin the calculation of flow over low [ PB87-2045091 p 19 N88-10782 Correlations of fuel performance in a full-scale Reynolds-number airfoils p 10 A88-11191 BRENDEL, MICHAEL commercial combustor and two model combustors CHRISPIN. W. J. Low Reynolds number wind tunnel measurements - The [ASME PAPER 87-GT-891 p 29 A88-11028 The United Kingdom engine technology demonstrator importance of being earnest p 10 A88-11190 Prediction of combustion performance of aviation programme BREZHNEV, A. L kerosines using a novel premixed flame technique [ASME PAPER 87-GT-2031 p31 A88-11107 Transonic expansions p 13 A88-12059 [ASME PAPER 87-GT-I251 p 41 A88-11052 CHUPP, R. E. Time-averaged heal-flux distributions and comparison BRILEY, W. R. CARTA. R. 0. with prediction for the Teledyne 702 HP turbine stage Flow in a model turbine stator p 55 NEB-11163 Unsteady aerodynamic measurements on a rotating [ASME PAPER 87-GT-1201 p 30 A88-11048 compressor blade row at low Mach number BROCKHAUS. R. CLARK, ANTHONY [ASME PAPER 87-GT-2211 p7 A88-11118 S. A mathematical multi-point model for aircraft motion in Real-time reconnaissance - An engineering moving air p 36 A88-12487 CARTER, JAMES E. perspective p 21 A88-12733 BROICHHAUSEN, K.-D. Cascade viscous flow analysis using the Navier-Stokes COAKLEY, THOMAS J. Off-design performanceof supersonic compressorswith equations p2 A88-10356 Impact of turbulence modeling on numerical accuracy fixed and variable geometry CASEY. M. V. and efficiency of compressible flow simulations [ASME PAPER 87-GT-1161 p 5 A88-11044 Influence of the Reynolds number on the performance [NASA-TM-88333] p 52 N88-11088 BROWN, A. of centrifugal compressors COGLIANDRO, SANTO Computer predictions of erosion damage in gas [ASME PAPER 87-GT-101 p 44 A88-10979 Plume infrared signature measurements and comparison turbines CASTELLI. PAOLA with a theoretical model p 33 A88-12836 [ASME PAPER 87-GT-1271 p46 A88-11054 Plume infrared signature measurements and comparison COLAN, M. E. BROWN, JAMES L with a theoretical model p 33 A88-12836 The development of 270 Vdc solid state power Development and implementation of an aerodynamic CAUDELL. THOMAS P. controllers p 33 A88-11923 holographic interferometry system p 49 A88-12725 Self-adjusting flight electronics (SAFE) COLE, G. H. BUBECK, H. p 49 A88-12697 Heat transfer to arrays of impinging jets in a crossflow Development and application of a high frequency wedge CEBECI, TUNCER [ASME PAPER 87-GT-1981 p 47 A88-11102 probe Recent developments in the calculation of flow over low COLE, S. L [ASME PAPER 87-GT-2161 p47 A88-11114 Reynolds-number airfoils p 10 A88-11191 Influence of the Reynolds number on the performance BUBLITZ, PETER CHANDRA, P. R. of centrifugal compressors The history of aeroelasticity research in Germany from Effect of rib angle on local heallmass transfer [ASME PAPER 87-GT-101 p 44 A88-10979 the beginning until 1945 distribution in a two-pass rib-roughened channel COLON-BONET, 0. T. [DFVLR-MIlT-86-25] p 1 N88-10003 [ASME PAPER 87-GT-941 p 45 A88-11033 Test of IR arrays on the Kuiper Airborne Observatory BUGGEIN, R. C. CHANDRASEKHARA, m. s. p 49 A88-12838 Flow in a model turbine stator p 55 N88-11163 Similarity of ejector wall-pressure distributions COOK, M. V. BUISINE, D. p 49 A88-12294 An experimental investigation of the aerodynamics of Three-dimensional flow in a rotor - A strictly CHANG, 0. C. the hang glider p 11 A88-11200 threedimensbnal calculation of flows in turbomachines Thermal expansion mismatch and oxidation in thermal COOPER. LEONARD Y. using the Sl-SZ method p 44 A88-10628 barrier coatings p 56 N88-111 82 Test results and predictions for the response of CHANG, HO-PEN BURGESS, E. near-ceiling sprinkler links in a full-scale compartment D. Analyses and assessments of span wise gust gradient An uncooled linescan thermal imager for ground and fire data from NASA 8-576 aircraft airbcfne use p 49 A88-12840 [NBSIR-87-3633] p 50 N88-10209 [ NASA-CR-1782881 p 15 N88-10007 CORKER, KEVIN BURKE, WILLIAM P. CHANG, JEN-FU Aircraft and equipment factors in the occurrence of Intelligent interfaces to aircraft systems Transonic analysis and design of axisymmetric bodies [AIM PAPER 87-27761 p 59 A88-12539 suspension line twists with US. Army parachutes in nonuniform flow COTON, F. N. p 19 A88-12644 [NASA-CR-4101] p16 N88-10013 A simple method for the prediction of separation bubble BURLEY, JAMES R., II CHANG, K. C. formation on aerofoils at low Reynolds number Effect of empennage arrangement on single-engine Recent developments in the calculation of flow over low p8 A88-11179 nonle/afterbcdy static pressures at transonic speeds Reynolds-number airfoils p 10 A88-11191 [ NASA-TP-27531 p 17 N88-10771 CHEN, DAGUANG COURTENAY, L W. BUSTAMANTE, ALBINO C. Investigation of integrated selection of optimum engine Correlations of fuel performance in a full-scale The aerothermodynamic environment for holes in cycle parameters commercial combustor and two model combustors hypersonic configurations [ASME PAPER 87-GT-391 p 29 A88-10993 [ASME PAPER 87-GT-891 p29 A88-11028 [DE874146511 p 17 N88-10767 CHEN, HONGJI COVERT, E. Shock embedding discontinuous solution of elliptic On some unsteady aerodynamics characteristics of an equation for inverse problem of transonic S2 flow NACA 0012 at Reynolds numbers of 125,000 and C [ASME PAPER 87-GT-1151 p 5 A88-11043 400.000 p 10 A88-11189 CHEN, NAI-XING CRANE, JEAN m. CADICHI, A. A generalized numerical method for solving direct Comparison of programmable legend keyboard and Experimental method for the combustion efficiency invwse and hybrid problems of blade cascade flow by dedicated keyboard for control of the flight management calculation in a reheat duct using streamline-coordinateequation computer [ASME PAPER 87-GT-901 p 29 AM-11029 [ASME PAPER 87-GT-291 p 4 A88-10990 [SAE PAPER 8617721 p57 A88-10160

6-2 PERSONAL AUTHOR INDEX FRANCOIS, D.

CRAWLEY, EDWARD F. WORLY, J. E. EL-SAYED, ABDEL AZlM A. F. Velocity scaled aeroelastic testing of advanced Procedures fw determining surface heat flux using thin Computer predictions of erosion damage in gas turboprops film gauges on a coated metal model in a transient test turbines [ASME PAPER 87-GT-2091 p 31 A88-11110 facility [ASME PAPER 87-GT-1271 p 46 A88-11054 CRECELIUS, BILL [ASME PAPER 87-GT-951 p 45 A88-11034 ELDREDGE, DONALD Counterrotating differential cylindrical roller bearing DOROSHKO, S. M. Digital system bus integrity development Diagnosis of flow channel in aircraft gas-turbine engines [NASA-CR-1814461 p 28 N88-10030 [AIAA PAPER 87-18431 p 43 A88-10497 on basis of vibration spectrum characteristics ELLIS, BRIAN CURRY, C. E. p 35 N88-10993 Towards the unmanned cockpit p 25 N88-10812 Applied reliability/maintainability methodology as a DOWNS, S. J. ELLIS, STEPHEN R. function within life cycle cost Boundary layer profile investigations downstream of an Perspectie traffic display format and airline pilot traffic [ASME PAPER 87-GT-1721 p 46 A88-11082 aero-engine intake anti-icing air exhaust slot avoidance p 58 A88-12639 [ASME PAPER 87-GT-2371 p 32 A88-11127 CYR, MARCIA A. ENGLISH, V. A. Boundary layer profile investigations downstream of an Development of heat flux sensors for turbine airfoils A preliminary investigation into the feasibility of aero-engine intake anti-icing air exhaust slot p54 N88-11143 implementingadirect sideforce control system on the Astra [PNR90376] p 52 N88-11080 DRAGOS, WAR Hawk by means of an active control surface Arbitrary wings of low aspect ratio in subsonic flow [ETN-87-90924] p 37 N88-10795 D 03 A88-10660 EPPLER, R. ~ DREES, J. M. Recent developments in boundary layer computation DAME, L T. Prepare for the 21st century - The 1987 Alexander A. p 10 A88-11188 3D inelastic analysis methods for hot section Nikolsky Lecture p24 A88-12645 The development of wing theory p 14 A88-12483 components P 55 1164 DREM, MARK ERISMAN, ALBERT M. Constitutive modeling for isotropic materials Two-dimensional transonic aerodynamic design Advanced computing for manufacturing

p 55 N88-11172 method~ ~~ D 14 A88-12284 060 A88-13109 DANIEL, B. R. DRIAMOV, 0. V. ESCHNAUER, HElNZ Flame driving of longitudinal instabilities in liquid fueled Computing complex lor a system for the radio-acoustic Development and production of new and modified dump combustors sounding of the atmosphere - Hardware facilities powders for sprayed coatings and components lor saving [ AD-A1835361 p33 N88-10033 p 58 A88-11394 important raw materials DASH, S. M. DRING, R. P. [ BMFT-FB-T-86-1291 p 42 N88-10159 Parabolhed Navier-Stokes analysis of ducted A trace gas technique to study mixing in a turbine supersonic combustion problems p 2 A88-10361 stage DATKO, J. T., JR. [ASME PAPER 87-GT-1181 p 5 A88-11046 F The aeromechanicalresponse of an advancedtransonic DRING, ROBERT P. compressor to inlet distortion Through-flow analysis of a multi-stage compressor FADEN, M. [ASME PAPER 87-GT-1891 p 31 A88-11094 operating at near-stall conditions Theoretical and experimental analysis 01 a compressor DAVIES, W. J. [ASME PAPER 87-GT-51 I p4 A88-11003 cascade at supercritical flow conditions Conceptual design of an optic based engine control DROUBI, RlAD M. [ASME PAPER 87-GT-2561 p8 A88-11136 system Prediction of gas turbine combustor-liner temperature FAIRMAN. TERRY M. [ASME PAPER 87-GT-1681 p 30 A88-11079 [ASME PAPER 87-GT-1771 p 31 A88-11085 First article test noise survey of the A/F32T-9 large turbo DRUM, W. M. DAVIS, ROGER L fan engine enclosed noise suppressor system, Sky Harbor Design principles and practices for implementation of Cascade viscous flow analysis using the Navier-Stokes IAP (International Airport). Phoenix. Arizona MIL-STD-1760 in aircraft and stores equations p2 A88710356 [AD-A183799] p 61 N88-10588 [AD-A183724] p24 N88-10027 FAN, C. S. DEANGELIS, V. MICHAEL DRUMMOND, J. P. Effects 01 channel aspect ratio on heat transfer in HiMAT flight program: Test results and program Evolution and application of CFD techniquesforscramjet rectangular passage sharp 180-deg turns assessment overview engine analysis p 28 A88-10358 [ASME PAPER 87-GT-1131 p 46 A88-11041 [NASA-TM-86725] p24 N88-10026 DU, J. Y. FAROKHI. SAEED DECHANT. DANIEL J. Numerical solution of stream function equations in A trade-off study of rotor tip clearance flow in a AOSP - Multiprocessor architecture and system transonic flows turbinelexhaust diffuser system considerations [ASME PAPER 87-GT-181 p3 A88-10983 [ASME PAPER 87-GT-2291 p 32 A88-11123 [AIAA PAPER 87-27901 p 59 A88-12544 Numerical computation of non-isentropic potential FAVIN, S. DEETS, DWAlN A. equations for transonic cascade flows Numerical solutions of scramjet nozzle flows HiMAT flight program: Test results and program [ASME PAPER 87-GT-1591 p 5 A88-11071 p2 A88-10359 assessment overview DUCHARME. ERIC H. FENCHEL, BRUCE [ NASA-TM-867251 p 24 N68-10026 Velocity scaled aaroelastic testing of advanced FDAD - A lablfield test tool p 25 A88-10436 Flight test 01 a resident backup software System turboprops FERNANDEZ, R. R. p 38 N88-10805 [ASME PAPER 87-GT-2091 p31 A88-Ill10 Design principles and practices lor implementation of DEKONING, A. U. DUNAGAN, STEPHEN E. MIL-STD-1760in aircraft and stores Criteria for determination of sbnificant load cycles in Development and implementation of an aerodynamic [AD-A183724] p 24 N88-10027 variable amplitude load sequences holographic interferometry system p 49 A88-12725 FINAISH, F. [ NLR-MP-86013-UI p 51 N88-10386 DUNN, M. 0. Further visualization of combined wing tip and starting DELOSREYES, G. Time-averaged heat-flux distributions and comparison vortex systems p 14 A88-12276 The design of a turboshan speed governor using modern with prediction for the Teledyne 702 HP turbine stage FINNEY, J. Y. control techniques [ASME PAPER 87-GT-1201 p 30 A88-11048 The influence of load cycle reconstitution on fatigue [ NASA-CR-1750461 p 51 N88-10339 DUWIN, V. K. behaviour Oxygen recombination in a supersonic cooled flow DEMASI, J. T. [ ARL-STRUC-R-4241 p 56 N88-11198 p 13 A88-12071 Thermal barrier coating life prediction model FISHELL, W. development p 56 N88-11185 DYER, D. J. Sensor controlldata display set (SC/DDS) for film Preliminary measurements of the flight performance of and/or electro optics (EO) p 26 A88-12731 DEMATHIEU, PIERRE an RPV compared with mnd tunnel and CFD estimates FISHER, S. S. Softcopy versus hardcopy p 27 A88-12750 p 12 A88-11203 A smoke-wire study of low Reynolds number flow over DEYEIS, RICHARD a NASA LRN(1) - 1007 airfoil section p 9 A88-11 f8l I An Orient Express to capture the market Smoke-wire and thin-film-gaugeobservations of laminar p 1 A88-10370 E separation bubbles on an NACA 23012-64 airfoil section Multimcdes to Mach 5 p 28 A88-10371 P 13 A88-11210 DEYMEL, JOHANN EASLEY, M. L FLETCHER, M. The dependence of the normalized ice accretion AGT101 ~ Ceramic gas turbine development On some unsteady aerodynamics characteristics of an thickness on cloud-physical parameters [ASME PAPER 87-GT-2281 p 32 A88-11122 NACA 0012 at Reynolds numbers of 125.000 and [DFVLR-FB-87-08] p57 N88-10464 EFIMOV. IGOR' EVGENEVICH 400,000 p 10 A88-11189 The accuracy-related parametric reduction of DENTON. J. FOCH, RICHARD J. D. mathematical models p 58 A88-10929 The base pressure and loss of a family of four turbine Low altitude/airspeed unmanned research aircraft EHSANI, Y. blades (LAURA) preliminary development p 12 A88-11205 Force commutated direct frequency changers for [ASME PAPER 87-GT-2021 p7 A88-11106 FORD, R. L aerospace power applications p 48 A88-11825 DESMOND, JOHN The conflict resolution process for TCAS II and some Improvements in aircraft safety and operational EL-ARABATY, M. simulation results p 21 A88-12474 dependability from a projected flight path guidance Towards the design 01 an intelligent aerospace system FORM, PETER display [AIAA PAPER 87-28441 p 26 A88-12569 Autonomous onboard collision avoidance for aircraft and [SAE PAPER 8617321 p 35 A88-10163 EL-MASRI, YAHER A. ships p21 A88-10687 DOWNY, J. A. Thermodynamics and performance projections for FORSYTH, J. A. Transmission efficiency in advanced aerospace intercwledlreheat/recuperated gas turbine systems The fatigue properties of aerospace steels under powerplant [ASME PAPER 87-GT-1081 p 46 A88-11040 constant amplitude and flight-by-flight simulated loading [PNR90391] p 53 N88-11133 ELQUN, 2. B. [BAE-MSM-R-GEN-0566] p 51 N88-10377 WORLY, D. J. Sealing of a shrouded rotor-stator system with pre-swirl FRANCOIS. D. Modelling the unsteady flow in a turbine rotor passage coolant Thin-film temperature Sensors deposited by radio [ASME PAPER 87-GT-1971 p7 A88-11101 [ASME PAPER 87-GT-721 p 45 A88-11016 frequency cathodic sputtering p50 A88-12903 , FREYMUTH, P. PERSONAL AUTHOR INDEX

FREYMUTH, P. GRAHAM, ROBERT HARTMAN. RICHARD V. Further visualization of combined wing tip and starting Autonomous processing using a blackboard chipset Video data link provides television pictures in near real vortex systems p 14 A88-12276 [AIAA PAPER 87-28551 p 59 A88-12575 time via tactical radio and satellite channels FRITSCHER. K. GRANT, HOWARD P. p 49 A88-12732 Basic concepts for better heat protection systems The development of a high temperaturestatic strain gage HARVEY, J. K. p 42 A88-12786 system p 53 NEB-1 1142 Dispersion in the wake of aircraft: An investigation of FROST, WALTER GRIEB, H. the effects of a ground plane on trailing vortices. Literature Analyses and assessments of span wise gust gradient Noise emission of civil and military aero-engines. SUNey data from NASA 6-576 aircraft Sources of generation and measures for attenuation [ IC-AERO-REP-86-04] p 16 NEB-10014 [NASA-CR-178288] p 15 N88-10007 [ETN-87-91021] p 62 N88-10595 HARVEY, W. D. Transition and separation control on a low-Reynolds FUCINARI, C. A. GRIFFIN, J. H. number airfoil Development of the AGTlOl regenerator seals On predicting the resonant response of bladed disk p9 A88-11186 HARVEY, WILLIAM D. [ASME PAPER 87-GT-1731 p 46 A88-11083 assemblies Low-Reynolds number aerodynamics research at NASA FUJIMORI, ATSUSHI [ASME PAPER 87-GT-1581 p 30 A88-11070 Syntheses of reduced-ordercontrollers for active flutter Langley Research Center p 11 A88-11194 suppression p 35 A88-10095 GRIN', V. T. HASS, J. Stability of supersonic flow of an ideal gas with a head FUNG, K.-Y. A model to determine the behaviour of a pressure shock wave past cylindrical channels and cavities Refined numerical solution of the transonic flow past a measurement equipment during non-static operations of p 13 A88-12065 Wedge p 14 A88-12280 gasturbine engines GU, CHUANGANG [ASME PAPER 87-GT-1281 p 46 A88-11055 Experimental investigations of flows through a plane HASSAN, AHMED A. G cascade at large angles of attack with separations The design of shock-free compressor cascades [ASME PAPER 87-GT-961 p 5 A88-11035 including viscous boundary layer effects GAERTNER, W. A new method (FTDCDF) for blade design of [ASME PAPER 87-GT-711 p4 A88-11015 Analysis of windage losses and velocity distribution for axial/mixed-flow compressors and its applications HAUPTMAN, AHARON a shrouded rotating disk [ASME PAPER 87-GT-1831 p31 A88-11090 Exact and asymptotic expressions of the lift slope [ASME PAPER 87-GT-1861 p6 A88-11091 GU, ZHONGQUAN coefficient of an elliptic wing p 14 A88-12292 GAGEANT, C. Investigation of control law for active flutter HEGDE, UDAY 0. Thin-film temperature sensors deposited by radio suppression Flame driving of longitudinal instabilities in liquid fueled frequency cathodic sputtering p 50 A88-12903 [ NASA-lT-20126] p 39 N88-10818 dump combustors GALBRAITH, R. A. MCD. GUELDER, OEMER L [AD-A183536] p33 N88-10033 A simple method for the prediction of separation bubble Combustion gas properties. Ill - Prediction of the HEIDELBERG, LAURENCE J. formation on aerofoils at low Reynolds number thermodynamic properties of combustiongases of aviation Advanced turboprop wing installation affects measured p8 A88-11179 and diesel fuels by unsteady blade pressure and noise GALLARDO, VINCENTE C. [ASME PAPER 87-GT-491 p 40 A88-11001 [ NASA-TM-1002001 p 15 N88-10008 Blade loss transient dynamics analysis, volume 1. Task HEINIG, K. 2 TETRA 2 theoretical development GUSTAFSON, KARL Multigrid localization and multigrid grid generation for Noise emission of civil and military aero-engines. [ NASA-CR-1796321 p 34 N88-10791 the computation of vortex structures and dynamics of flows Sources of generation and measures for attenuation Blade loss transient dynamics analysis, volume 2. Task in cavities and about airfoils p3 A88-10562 [ETN-87-91021] p62 N88-10595 2: TETRA 2 user's manual HELDT, PETER H. [NASA-CR-179633] p 34 "3-10792 Airline requirements on a fly-by-wire aircraft - A pilot's GALLETLV. 0. D. H view Elastic buckling of internally pressurized [SAE PAPER 8618041 p 36 A88-10167 cylinder-bulkheadcombinations p 50 A88-12949 HAASER, FRED 0. HENDERSON, WILLIAM P. GALLUS, H. E. Labyrinth seal flow measurement by tracer gas Effect of emwnnage arrangement on sinale-enaine Otf-design performanceof supersonic compressors with injection nonle/afterbody static pressures at transonic speeds fixed and variable geometry [ASME PAPER 87-GT-1871 p 47 A88-11092 INASA-TP-2753 1 D 17 N88-10771 [ASME PAPER 87-GT-1161 p5 A88-11044 HACKWELL, J. A. HENKEL, P. GARDNER, B. K. Test of IR arrays on the Kuiper Airborne ObSeNatOry Airborne reconnaissance pod flight test Prediction of sound fields in cavities using p 49 A88-12838 p 27 A88-12741 boundary-element methods p 61 A88-12281 HAH, C. HENKEL, PAUL GE, MANCHU Calculation of three-dimensional viscous flows in Airborne reconnaissanceX; Proceedings of the Meeting. The performance estimation of transonic turbine at turbomachinery with an implicit relaxation method San Diego, CA, Aug. 19.20, 1986 design and offdesign conditions p2 A88-10357 [SPIE-694] p 26 A88-12728 [ASME PAPER 87-GT-1481 p 30 A88-11066 Numerical salution of three-dimensional turbulent flows HERTRICH, H. A. GEORGE, M. for modern gas turbine components BMFT-supported projects in the fields position-finding, A study of the effects of thermal barrier coating surface [ASME PAPER 87-GT-841 p 4 A88-11024 navigation, and traffic safety p 20 A88-10677 roughness on the boundary layer characteristics of HAJEK, T. J. HICKS, 8. gas-turbine aerofoils Coolant passage heat transfer with rotation High-temperature sheet materials for gas turbine [ASME PAPER 87-GT-2231 p48 Am-11120 p54 N88-11160 applications p42 A88-12635 GHAFOURI. M. HALIM, AHMAD A. M. HIGGINS, A. W. in air transport and airport management Issues Global marching technique for predicting separated Coolant passage heat transfer with rotation [ PB87-204509J p 19 N88-10782 flows over arbitrary airfoils p 14 A88-12293 p 54 NEB-11160 GIBBONS, A. K. HALL, 0. WARREN HIKITA, M. Investment foundry melting stock. Rolls Royce Flight researh at NASA Ames Research Center: A test Cyclic spinning testing of aero-engine discs requirements and demands in terms of quality and the @lot'sperspective [ASME PAPER 87-GT-2591 p 32 A88-11139 relationship to end product performance [NASA-TM-l00025] p 25 N88-10788 HILL, R. D. [PNR90397] p 52 NEB-1 1003 HAMATANI, HlROSHl A survey of aircraft integrated control technology GILES, MICHAEL B. Development of the XF3-30 turbofan engine [AR-004-561] p37 N88-10794 Two-dimensional transonic aerodynamic design [ASME PAPER 87-GT-261 p 28 A88-10988 HIPPENSTEELE. S. A. method p 14 A88-12284 HAMMER, J. M. Use of a liquid-crystal and heater-element composite GODEFROY, J. C. Decoupling and stabilization of speed and height in F4 for quantitative. high-resolution heat-transfer coefficients Thin-film temperature sensors deposited by radio Phantom aircraft using output feedback on a turbine airfoil including turbulence and frequency cathodic sputtering p50 A88-12903 [ ETN-87-909261 p 25 N88-10787 surface-roughnesseffects p44 A88-10969 GODIWALA, P. M. HAN, J. C. HIRAHARA, MAKOTO Evaluation of a dual processor implementationfor a fault Effect of rib angle on local heat/mass transfer Advanced composite horizontal stabilizer for infemng nonlinear detection system distribution in a two-pass rib-roughened channel nextgeneration commercial aircraft p 24 A88-13081 [AIM PAPER 87.27621 p 59 A88-12532 [ASME PAPER 87-GT-941 p 45 A88-11033 HIRAOKA, KOlCHl GOEKOGLU, SULEYMAN A. HARDESTY, MARK Stress intensity factors and residual strength of a Experimental verification of vapor deposition rate theory Helicopter main-rotor speed effects on far-field acoustic cracked stiffened panel p 50 A88-13083 in high velocity burner rigs p 43 N88-11179 levels Structure simplification around a cutout .Application of GOLDSTEIN, R. J. [ NASA-TM-1005121 p 62 N88-11451 a simplified damage tolerance design chart Film cooling of a turbine blade with injection through HARDIN, L W. p 50 A88-13084 two rows of holes in the near-endwall region Unsteady aerodynamic measurements on a rotating HITCHCOCK. ROBERT J. [ASME PAPER 87-GT-1961 p47 A88-11100 compressot blade row at low Mach number Perspective traffic display format and airline pilot traffic GOLOVIZNIN, V. P. [ASME PAPER 87-GT-2211 p7 A88-11118 avoidance p 58 A88-12639 Supersonic flow around a sphere in a thermal HARIGAE, MASATOSHI HIlT, ELLIS F. inhomogeneity p2 A88-10264 A hybrid navigation system with GPS Dgital system bus integrity GOUCHOE. D. R. p 21 A88-13087 [NASA-CR-181446] p 28 N88-10030 The design of a turboshaft speed governor using modern HARRIS, F. 0. HOBART, HOWARD F. control techniques The influence of load cycle reconstitution on fatigue The Lewis Strain Gauge Lahoratory: Status and plans [NASA-CR-175046] p 51 N88-10339 behaviour p 54 N88-11146 GOWARD. 0. W. [ARL-STRUC-R-424] p 56 NEB-11198 HODGES, DEWEY H. Pack cementation coatings for superalloys - A review HARTLE, M. S. Analytical modeling of helicopter static and dynamic of history, theory, and practice 3D inelastic analysis methods for hot section induced velocity in GRASP [ASME PAPER 87-GT-501 p41 A88-11002 components p55 NEB-11164 [ NASA-TM-1000261 p 18 N88-10777

8-4 PERSONAL AUTHOR INDEX KOROLLEV, A. N.

HOENLINGER, H. INGER, 0. R. KALINICHENKO, BORIS VASIL'EVICH Flutter suppression and gust load alleviation. Part 1: A theoretical study of spanwise-periodic 3-D Flight characteristics of aircraft with gas-turbine Results of phase 1 to 3. Part 2: Description of the Garteur disturbances in the wake of a slightly stalled wing at low engines p 23 A88-10049 model Reynolds numbers p8 A88-11180 KANTOR, L A. [MBB-LKE292/S/PUB/191] p36 N88-10038 ISHII, ISAO Analysis of supersonic heterogeneous flow impinging HOFFMAN, JOE D. Design and fabrication trial of a composite flap on an obstacle p 14 A88-12074 Analytical study of swirler effects in annular propulsive StNCtUre p 1 A88-13082 KANTOR, S. A. nozzles p 28 A88-10362 ISHIUWA. KAZUHIKO Analysis of supersonic heterogeneous flow impinging HOFFMANN, HANSEBERHARD Development of the XF3-30 turbofan engine on an obstacle p 14 A88-12074 The dependence of the normalized ice accretion [ASME PAPER 87-GT-261 p 28 A88-10988 KAUSCHE. G. thickness on cloud-physical parameters Dynamic wind tunnel balances in the DFVLR subsonic [ DFVLR-FB-87-08] p 57 NEB-10464 J wind tunnel in Braunschweig p 39 A88-12488 HOLDEMAN, J. D. KAYNAK, UENVER On the mixing of a row 01 jets with a confined JAMES, E. H. Computation of transonic separated wing flows using crossflow p 54 N88-11154 Boundary layer profile investigations downstream of an an EulerlNavier-Stokeszonal approach HOLLWORTH, 8. R. aero-engine intake anti-icing air exhaust slot [NASA-TM-88311] p 52 NEB-11089 Heat transfer to arrays of impinging jets in a crossflow [ASME PAPER 87-GT-2371 p32 AM-11127 KEIL, JOHANNES [ASME PAPER 87-GT-1981 p 47 A88-11102 Boundary layer profile investigations downstream of an Investigations of separated flow states on wings of HOLST, TERRY L aero-engine intake anti-icing air exhaust slot medium aspect ratio laking into account the wind tunnel Computation of transonic separated wing flows using [PNR90378] p 52 N88-11080 interference problem an EulerlNavier-Stokeszonal approach JAMESON, A. [ETN-87.904371 p 17 N88-10016 [NASA-TM-8831I] p 52 N88-11089 Multigrid solution of the Euler equations on unstructured KELLY, BRIAN D. HOLTMAN, R. L and adaptive meshes p 44 A88-10570 An integrated display lor vertical situation awareness Development of ceramic hot section components for JASUJA, A. K. in commercial transport aircraft AGT 100 gas turbine Spray performance of a hybrid injector under varying [SAE PAPER 8617701 p 57 A88-10158 [ASME PAPER 87-GT-791 p 45 A88-11019 air density conditions KENNEDY, J. 8. HOMAIFAR, ABDOLIAH [ASME PAPER 87-GT-1551 p 46 A88-11068 Global positioning satellite-based automatic landing Fuel-injector/air-swirlcharacterization JAWTUSCH, V. p 54 N88-111 50 system and wind estimated feedback for the AH-64 Theoretical and experimental analysis of a compressor KESSLER, W. D. helicopter p 22 N88-10784 cascade at supercritical flow conditions Magnetic recording for near real time reconnaissance HONDA, YUlCHl [ASME PAPER 87-GT-2561 p8 A88-11136 applications p 27 A88-12736 Design study for an FEW lateral control system JENKINS, JEFFERY C. p 36 A88-13080 First article test noise survey of the A/F32T-9 large turbo KHOLODOV, A. S. HORGER, D. C. fan engine enclosed noise suppressor system, Sky Harbor Numerical solution of coupled problems of supersonic Smoke-wire and thin-filmgauge observations of laminar IAP (International Airport), Phoenix, Arizona flow past deformable shells of finite thickness separation bubbles on an NACA 23012-64 airfoil section [AD-A183799] p 61 N88-10588 p 13 A88-11280 p13 AM-11210 JI, WE1 KIJIMA, HlROSHl HORLOCK, J. H. A multigrid algorithmfor 2-0 transonic potential cascade GPSIINS hybrid navigation for aircraft Three-dimensional calculation of wall boundary layer flrlw..-.. D22 A88-13090 flows in turbomachines [ASME PAPER 87-GT-1801 p 6 A88-11088 KILKENNY, E. A. [ASME PAPER 87-GT-821 p 4 A88-11022 JIANG, H. An experimental investigation of the aerodynamics of HORRIGAN, FRANK A. A simplified method for 3.0 potential flow in the hang glider p 11 A88-11200 AOSP . Multiprocessor architecture and system turbomachinery using vortex sheet boundary conditions KIM, K. S. considerations [ASME PAPER 87-GT-281 p3 A88-10989 Elevated temperature crack growth [AlAA PAPER 87.2790) p59 A88-12544 JIANG, HONGDE p 55 N88-11174 HOTOP, HANSJUERGEN A multigrid algorithmfor 2-D transonic potential cascade KIM. y. Test equipment with fiber optic data bus and laser gyro flow Force commutated direct frequency changers for strapdown system LTN-90 for the helicopter BO-105 [ASME PAPER 87-GT-1801 p 6 A88-11088 aerospace power applications p 48 A88-11825 [ESA-TT-1038] p 22 N88-10025 JOHANSSON, INGVAR H. HOUCK, ROGER KIMBALL, DWAYNE F. Sensor configuration for a short lo medium range Recent tilt rotor flight control law innovations An integrated display for vertical situation awareness reconnaissance pod p 27 A88-12742 in commercial transport aircraft p36 A88-12646 JOHNSON, B. V. [SAE PAPER 8617701 p57 AM-10158 KIMURA, KOlCHl Comparison of predicted and measured velocities in a HOUSER, J. Civil aviation application of the Global PositioningSystem M. compressor disk drum model Experimentson spray interactions in the wake of a bluff (GPS) and its issues p 22 A88-13088 [ASME PAPER 87-GT-2081 p 47 A88-11109 body KINOSHITA, R. Y. [ASME PAPER 87-GT-481 p 44 A88-11000 JOHNSTON, D. E. The development of 270 Vdc solid slate power HUANG, H. T. Investigation of interactions between limbmanipulator controllers p 33 A88-11923 dynamics and effective vehicle roll control 3D inelastic analysis methods for hot section KIPP, C. R. characteristics components p55 N88-11164 Prediction of sound fields in cavities using [NASA-CR-3983] p36 N88-10039 HUBENSTEINER, MICHAEL boundary-element methods p 61 A88-12281 JONES, D. 0. Experimental determination of the oscillatory forces on KITAMURA, MASAYUKI Optical flow diagnostic measurements in two turbine blade profiles Altitude tests of the XF3-30 turbofan turbomachinery [ETN-87-90417] p 34 N88-10037 [ASME PAPER 87-GT-251 p 28 A88-10987 [PNRW396] p 52 N88-11081 HUEER. ARTHUR F.. II KLIUSHIN, A. I. JONES, HAROLD L The effect of grit roughness on the performance of the Computing complex for a system for the radio-acoustic Wortmann FX63-137 airfoil at a chord Reynolds number AI expert system technology issues for guidance and sounding of the atmosphere - Hardware facilities control applications p38 N88-10808 Of 100,M)o p 11 A88-11202 p 58 A88-11394 HULSE, CHARLES 0. JORDAN, ERIC KNOX, CHARLES E. The development of a high temperature static strain gage Constitutive modeling of superalloy single crystals with Flying complex approach paths using the microwave system p53 N88-11142 verification testing p43 N88-11169 landing system HURRASS, K. JORDAN, FRANK L. JR. [SAE PAPER 861771 I p 35 A88-10159 Hybrid positioning and navigation systems - Wind-tunnel investigation of a full-scale general aviation KOGA, AKINORI Technological status and development trends in airplane equipped with an advanced natural laminar flow Applications of ceramic coating on the turbine blades position-finding and navigation procedures wing of the AGTJ-100B p 20 A88-10684 [ NASA-TP-27721 p16 N88-10009 [ASME PAPER 87-GT-1901 p 41 A88-11095 HURST, D. W. JOSLYN. DAVID H. KOGA, KANYA Wind tunnel testing of small scale pressuretapped model Through-flow analysis of a multi-stage compressor Structure simplification around a cutout Application of propellers p32 A88-11196 operating at near-stall conditions - a simplified damage tolerance design chart HUTCHINSON, J. E. [ASME PAPER 87-GT-511 p4 A88-11003 The advantages 01 a primary fliht display p 50 A88-13084 JOSLYN, H. D. [SAE PAPER 8617301 p58 AM-10162 KOGGE, PETER M. A trace gas technique to study mixing in a turbine Avionics. artificial intelliaence.". and embedded stage processing systems I [ASME PAPER 87-GT-1181 p A88-11046 [AIAA PAPER 87-28181 p 59 A88-12558 KOPEIKA. N. S. IAVOR, 1. P. Imaging through the atmosphere for airborne

K ~~ ~ ~~~ ~~ D Supersonic flow around a sphere in a thermal reconnaissance r-27 A88-12748-- - - inhomogeneity p 2 AM-10264 KOPPENWALLNER, 0. ICHIKAWA, MASAMI KACPRZYNSKI, JERZY J. Analysis of free molecular effects on the altitude of A numerical method for subsonic unsteady lifting Reliability of finite element methods in North America Satellites in geostationary transfer orbit. Part 2: Force and surfaces - BIS. 111 - Some additional numerical results [AGARD-R-748] P 53 N88-11139 torque measurement in free molecular wind tunnel tests p2 A88-10093 KAJITA, SHlNlCHl [ DFVLR-IB-222-86-A-07] p40 N88-10078 IGA, AKlRA Prediction of NO and CO distribution in gas turbine KOROLLEV, A. N. Fliht test results for a GPS receiver in a helicopter combustors Fast stable solution of a dispersion equation of linear and a business aircraft p 22 AM-13094 [ASME PAPER 87-GT-631 p 41 A88-11010 filtering p 21 A88-10728

8-5 KOROTIN, P. N. PERSONAL AUTHOR INDEX

KOROTIN, P. N. LEBLANCK, P. LUX, DAVID P. Numerical solution of coupled problems of supersonic Boundary layer and performance characteristics from HiMAT flight program: Test results and program flow past deformable shells of finite thickness wind tunnel tests of a low Reynolds number Liebeck assessment overview p 13 A88-11280 airfoil p9 A88-11184 [ NASA-TM-867251 p 24 N88-10026 KORYTTSEV, 1. V. LEE, PETER W. LYNCH, D. K. Computing complex for a system for the radio-acoustic Improved oil-off SUNiVability of tapered roller bearings Test of IR arrays on the Kuiper Airborne ObSeNatOry sounding of the atmosphere - Hardware facilities [NASA-CR-180804] p 53 N88-11135 p 49 A88-12838 p 58 A88-11394 LEGGE, H. KOSHIO, TATSUKICHI Analysis of free molecular effects on the attitude of An overview of space and aircraft navigation satellites in geostationary transfer orbit. Part 2: Force and M p 40 A88-13086 torque measurement in free molecular wind tunnel tests KOVALENKO, EVGENll VENIAMINOVICH MABEY, D. 0. [ DNLR-16-222-86-A-07I p 40 N88-10078 On the prospects for increasing dynamic lift Problems in continuum mechanics with mixed boundary LEMMER, K.4. conditions p 43 A88-10017 [RAE-TM-AERO-20681 p 17 N88-10018 A model to determine the behaviour of a pressure MACIEJEWSKI, PAUL K. KOZLU, HAMDI measurement wuioment durina non-static otmrations of Particle transport across the transpired turbulent Heat transfer with very high free stream turbulence gasturbine engine; p 54 N88-11161 boundary layer [ASME PAPER 87-GT-1281 p 46 A88-11055 [ASME PAPER 87-GT-2651 p48 A88-11142 MAIER-ERBACHER, J. KREIDER. GARY E. LElTINGTON, A. H. Possibilities for the modeling of dynamically loaded A compact high performance thermal imager Improved oil-off survivability of tapered roller bearings cylindrical structural parts in the wind tunnel p 50 A88-12843 [ NASA-CR-1808041 p 53 N88-11135 [ KU-SFB-210/T/24] p 15 N88-10005 KREINER. D. M. LEVY, I. DAVID MALIK, S. N. AGTlOl - Ceramic gas turbine development Self-adjusting flight electronics (SAFE) Elevated temperature crack growth [ASME PAPER 87-GT-2281 p 32 A88-11122 p 49 A88-12697 p 55 N88-11174 KROTHAPALLI, A. LEYLEK, J. H. MALONEY, PAUL F. Similarity of ejector wall-pressure distributions Numerical solution of three-dimensionalturbulent flows Composite directions at Kaman p 41 A88-12414 p 49 A88-12294 for modern gas turbine components MANDLE. JACQUES KUBOTA, HlROTOSHl [ASME PAPER 87-GT-841 p4 A88-11024 Airspeed measurement with a C02 lidar The flow visualization on the rotary wing with low aspect LIANG, S.-M. p 26 A88-12655 ratio p2 A88-10094 Refined numerical solution of the transonic flow past a MANGALAM, S. M. KUMAR, A. wedge p 14 A88-12280 Transition and separation control on a low-Reynolds Evolution and application of CFD techniquesfor scramjet LIDDICOAT, T. J. number airfoil p9 A88-11186 MANNING, P. engine analysis p 28 A88-10358 An uncooled linescan thermal imager for ground and A. An uncooled linescan thermal imager for ground and KUNIK, WILLIAM G. airborne use p 49 A88-12840 airborne use p 49 A88-12840 Application of advanced computational codes in the LIEBECK, R. H. design of an experiment for a supersonic throughflow fan MANSER, R. Low Reynolds number airfoil design at the Douglas Flutter suppression and gust load alleviation. Part 1: rotor Aircraft Company p9 A88-11183 Results of phase 1 to 3. Part 2: Description of the Garteur [ASME PAPER 87-GT-1601 p6 A88-11072 Bwndary layer and performance characteristics from KUNZ, DONALD L model wind tunnel tests of a low Reynolds number Liebeck [MBB-LKE292/S/PUB/lSl] p36 N88-10038 Analytical modeling of helicopter static and dynamic airfoil p9 A88-11184 induced velocity in GRASP MANSI, M. V. LIEFTING. 0. [NASA-TM-1OW261 p 18 N88-10777 An uncooled linescan thermal imager lor ground and KWON. 0. KEY Criteria for determination of significant load cycles in airborne use p 49 A88-12840 variable amplitude load sequences Navier-Stokes solution lor steady two-dimensional MANSOOR, A. [ NLR-MP-86013-UI p 51 N88-10386 transonic cascade flows On the determination of the 2-D characteristics of [ASME PAPER 87-GT-541 p4 A88-11005 LINDHOLM, ULRlC S. aerofoils at low Reynolds numbers p 10 A88-11192 Constitutive modeling lor isotropic materials MARCHMAN, J. F., 111 p55 N88-11171 Control surface effects on the low Reynolds number L LINDSAY, W. L. behavior of the Wortmann FX 63-137 Three-dimensional calculation of wall boundary layer p 10 A88-11187 LAFLEN, J. H. flows in turbomachines MARCUM, DAVID L Constitutive modeling for isotropic materials [ASME PAPER 87-GT-821 p 4 A88-11022 Analytical study of swirler effects in annular propulsive p 55 N88-11172 LING, CALVIN nozzles p 28 A88-10362 Elevated temperature crack growth Autonomous processing using a blackboard chipset MAREK, A. J. p 55 N88-11174 [AIAA PAPER 87-28551 p 59 A88-12575 Design principles and practices for implementation of LAGESSE, FRANCIS R. LINGARD. J. S. MIL-STD-1760in aircraft and stores [ AD-A1837241 p 24 N88-10027 Airborne reconnaissanceX Proceedings of the Meeting, The aerodynamics of gliding parachutes San Diego. CA, Aug. 19.20, 1986 p 11 A88-11201 MARTEL, CHARLES R. [SPIE-694] p 26 A88-12728 LINKERT, W. Cost savings possible with Air Force conversion to JP-8 as its primary fuel LAKSHMINARAYANA, B. A qualitative method for determining the temperature [AD-A183784] p 42 N88-10192 Calculation of a three-dimensionalturbomachinery rotor pattern of run gas turbine blades flow with a Navier-Stokes code [ASME PAPER 87-GT-1021 p 45 A88-11037 MARTIN, D. J. [ASME PAPER 87-GT-2321 p 7 A88-11125 LISCHKA, J. Some approaches to the design of high integrity software p 37 N88-10799 LAM. T. N. The importance of modern positioning and navigation Issues in air transport and airport management MASUYA, GORO technology for ATC p 20 A88-10678 [PB87-204509] p 19 N88-10782 LIU, H.-T. The scramjet - Toward Mach 4-25 flight LAMB, MILTON p 33 A88-13095 Atmospheric turbulence and gust on the performance MATSUZAKA, YASAYOSHI lntergration effects of D-shaped. underwing, of a Wortmann FX 63-137 wing p9 A88-11185 The flow visualization on the rotary wing with low aspect aft-mounted, separate-flow. flow-through nacelles on a LOCK, WILTON P. ratio p2 A88-10094 high-wing transport Flight test 01 a resident backup software system MATUMOTO, RYUlCHl [NASA-TM-4018] p 18 N88-10773 p 38 N88-10805 Prediction of NO and distribution in gas turbine LAMBERT, MARK LOEWY, ROBERT G. CO The Antonov An-74 brings high tech to low combustors Composite structural materials [ASME PAPER 87-GT-631 p 41 A88-11010 temperatures p 23 A88-10876 [ NASA-CR-1814161 p 56 N88-11186 MAURER, G. E. Anti-tank helicopters for the rich and not so rich LOUIS, JEAN F. Developments in disc materials p 42 A88-12632 p 1 A88-10877 Particle transport across the transpired turbulent MAVRIPLIS, D. LAN, C. EDWARD boundary layer Transonic analysis and design of axisymmetric bodies [ASME PAPER 87-GT-2651 p 48 A88-11142 Multigrid solution of the Euler equations on unstructured and adaptive meshes p 44 A88-10570 in nonuniform flow LUCAS, HANS INASA-CR-4101 p16 N88-10013 MAZUR, JOSEPH I Introduction and application of the General Electric Momentum exchanges and energy transfers in cross LANDY. R. J. turbine engine monitoring software within KLM Royal Dutch fhw fans HIDEC adaptive engine control system flight evaluation Airlines .. .- [ASME PAPER 87-GT-321 p 44 A88-10992 results [ASME PAPER 87-GT-1671 p 30 A88-11078 MCBRIDE. M. W. [ASME F'APER 87-GT-2571 p 32 A88-11137 LUO, LAl-QlN Unified equation of motion (UEM) approach as applied LAU, s. c. Experimental investigations of flows through a plane S1 turbomachinery problems Effect of rib angle on local heatlmass transfer cascade at large angles of attack with separations to distribution in a two-pass rib-roughened channel [ASME PAPER 87-GT-961 p 5 A88-11035 [ASME PAPER 87-GT-1791 p6 A88-11087 [ASME PAPER 87-GT-941 p 45 A88-11033 LUTZ, REINHOLD MCCOLLUM, P. E. LAUTNER. D. E. Development and production of new and modified The development of 270 Vdc solid state power Design principles and practices for implementation of powders for sprayed coatings and components for saving controllers p 33 A88-11923 MIL-STD-1760 in aircraft and stores important raw materials MCCONAGHY, ROB [AD-A183724] p 24 N88-10027 [ BMR-FB-T-86-1291 p 42 N88-10159 An improved Stirling engine lor model aircraft LEBEN, ROBERT LUU, T. S. propulsion p 33 A88-11976 Multigrid localization and multigrid grid generation for The turbomachine blading design achieved by solving MCCRACKEN, WILLIAM L the computation of vortex structures and dynamics of flows the inverse field problem Recent developments in infrared data processing in cavities and about airfoils p3 A88-10562 [ASME PAPER 87-GT-2151 p31 A88-11113 p 28 A88-12751 PERSONAL AUTHOR INDEX OWEN, D. T.

MCGREEHAN, WILLIAM F. MOENIG, R. NELLER, P. H. Labynnth seal flow measurement by tracer gas Oft-design performance of supersonic compressors with Sealing of a shrouded rotor-stator system with pre-swirl injection fixed and variable geometry ccmlant [ASME PAPER 87-GT-1871 p47 A88-11092 [ASME PAPER 87-GT-1161 p 5 A88-11044 [ASME PAPER 87-GT-721 p 45 A88-11016 MCGREEVY, MICHAEL W. MOFFAT, ROBERT J. NELSON, RICHARD Perspective traffic display format and airline pilot traffic Heat transfer with very high free stream turbulence S. Creep fatigue life prediction for engine hot section avoidance p 58 A88-12639 p 54 N88-11161 materials [isotropic): Third year progress review MCKENZIE, ROBERT J. MOLL, W. p 55 N88-11173 Expert system control for airborne radar surveillance Investigation of the excitation of turbine blade vibration [AIAA PAPER 87-28541 p 26 A88-12574 in axial compressors in rotating stall NEUMANN, J. F. MCKINZIE, 0. J. [ETN-87-90377] p34 N88-10035 Thermal barrier coating life prediction model A natural low frequency oscillation in the wake of an MOLLO, C. 0. development p 56 N88-11183 airfoil near stalling conditions Prediction of sound fields in cavities using NEVES, KENNETH W. [ NASA-TM-1002131 p 18 N88-10779 boundary-element methods p 61 A88-12281 Advanced computing for manufacturing MOON. HEE-KO0 MCKNIGHT, R. L p 60 A88-13109 Modeling and measurement of heat transfer on turbine Component specific modeling p 60 N88-11166 blade tips p 33 NEB-10032 NGUYEN, DZlEM MCQUIGGAN, 0. MOORE, MICHAEL G. Autonomous processing using a blackboard chipset A qualitative method for determining the temperature Electronic trend monitoring and exceedawe recording IAIAA PAPER 87.28551 p 59 A88-12575 pattern of run gas turbine blades systems - A means to improved turbine engine reliability NI, RON-HO [ASME PAPER 87-GT-1021 p 45 A88-11037 [ASME PAPER 87-GT-871 p 29 A88-11027 MCRUER, D. T. Cascade viscous flow analysis using the Navier-Stokes MOORE, W. T. equations p2 A88-10356 Investigation of interactions between limb-manipulator A compact high performance thermal imager dynamics and effective vehicle roll control p50 A88-12843 NI, W. Y. characteristics MORBIEU, BERTRAND Numerical solution of stream function equations in [NASA-CR-3983] p36 N88-10039 Airspeed measurement with a CO2 lidar transonic flows MCVEY, J. B. p 26 A88-12655 [ASME PAPER 87-GT-181 p3 A88-10983 Fuel-injectodair-swirlcharacterization MORRELL, F. R. Numerical computation of non-isentropic potential p 54 NEB-11150 Evaluationof a dual processor implementationfor a fault equations for transonic cascade flows MEADE, ANDREW J., JR. inferring nonlinear detection system [ASME PAPER 87-GT-1591 p5 A88-11071 Experimental study of three-dimensionalseparated flow [AIM PAPER 87-27621 p 59 A88-12532 NICHOLAS, D. J. surrounding a hemisphere-cylinderat incidence MORRIS, ROY A. The wide chord fan blade: A Rolls Royce first [AIAA PAPER 87-24921 p 3 A88-10498 Gas turbine exhaust systems - Design considerations [PNR90416] p 34 N88-10789 MEGNA, VINCENT A. [ASME PAPER 87-GT-2381 p 32 A88-1 1128 Flight test of a resident backup software system MORSE, A. P. NICKLAUS, DENNIS J. p 38 N88-10805 Numerical prediction of turbulent flow in rotating Initial user experience with an artificial intelligence MEINHARDT. HELMUT cavities program for the preliminary design of centrifugal Development and production of new and modified [ASME PAPER 87-GT-741 p45 A88-11018 compressors powders for sprayed coatings and components for saving MUELLER, ARNOLD W. [ASME PAPER 87-GT-2171 p 58 A88-11115 important raw materials Helicopter main-rotor speed effects on far-fieldacoustic NIRO, LENA [EMFT-FE-T-86-129] p 42 N88-10159 levels Scheduled maintenance program helps Delta maintain MENACHER, F. [ NASA-TM-1005121 p 62 N88-11451 quality p 1 A88.11672 MUELLER, BURKHARD Possibilities for the modeling of dynamically loaded An Observer approach the estimation of helicopter NORDWALL, BRUCE D. cylindrical structural parts in the wind tunnel to airspeed E-1E combines brisk low-altitude handling, more capable [KU-SFE-210/T/24] p 15 N88-10005 avionics [DFVLR-FE-87-13] p25 N88-10029 p 23 A88-10675 METHVEN, P. N. MUELLER, THOMAS J. NORTH, DAVID M. Wind tunnel testing of small scale pressuretapped model Low Reynolds number wind tunnel measurements -The E-1E combines brisk low-altitude handling, more capable propellers p32 A88-11196 importance of being earnest p10 A88-11190 avionics p 23 A88-10675 METZGER, D. E. The effect of grit roughness on the performance of the NUGENT, JACK Effects of channel aspect ratio on heat transfer in Wortmann FX63-137 airfoil at a chord Reynolds number Comparison of wind tunnel and flight test aft%- and rectangular passage sharp 180-deg turns of t 00.OOo p 11 A88-11202 noale pressures for a twin-jet fighter aircraft at transonic [ASME PAPER 87-GT-1131 p46 A88-11041 International Conference on the Aerodynamics at Low speeds MEVLS, A. F. Reynolds Numbers between lO(4) and lo@) [NASA-TP-2588] p 17 N88-10765 Extended systems of variable structure with mobile [ONRL-7-023-C] p16 N88-1M)lO radiocommunicationobjects p 44 A88-10726 The structure of separated flow regions occurring near MIAO, YONGMIAO the leading edge of airfoils including transition Experimental investigations of flows through a plane [NASA-CR-181434] p 16 NEB-10011 0 cascade at large angles of attack with separations MULLENS, DAVID G. [ASME PAPER 87-GT-961 p 5 A88-11035 Expert system control for airbmne radar surveillance OBRIEN, W. F., JR. MICHEAU, P. [AIAA PAPER 87.28541 p 26 A88-12574 Characterizationof shock wave end wall boundary layer Three-dimensional flow in a rotor - A stnctly MUNIN, ANATOLII GRIGOR'EVICH interactions in a transonic compressor rotor [ASME PAPER 87-GT-1661 p6 A88-11077 three-dimensional calculation of flows in turbomachines Aircraft acoustics I ~ Exterior noise of subsonic using the S1-S2 method p 44 A88-10628 passenger aircraft and helicopters p 61 A88-10047 O'HARA. J. A. YIQNEAULT. QERARD E. Aircraft acoustics I1 - Cabin noise in passenger aircraft The aerornechanicalresponse of an advanced tranwnic The application of emulation techniques in the analysis p 61 A88-10048 compressor to inlet distortion of highly reliable, guidance and control computer MURRI, DANIEL G. [ASME PAPER 87-GT-1891 p 31 A88-11094 systems p 37 N88-10798 Wind-tunnel investigation of a full-scale general aviation OGAKI, MASANOBU MIKHAILOV, 1. E. airplane equipped with an advanced natural laminar flow High-lift-device design and low-speed wind-tunnel test Necessary optimality conditions for three-dimensional wing p 15 A88-13079 bodies in supersonic gas Row p2 A88-10300 [NASA-TP-2772] pi6 N88-10009 OGAWA, TOSHIO MILES, JOHN B. MUSSMANN, D. Measurements in the functional mock up test of the Development and implementation of an aerodynamic Flutter suppression and gust load alleviation. Part 1: NAL QSTOL aircraft control system holographic interferometry system p 49 A88-12725 Results of phase 1 to 3. Part 2: Description of the Garteur [ NAL-TR-9281 p 36 N88-10793 model MILLER, WUQLAS R. OQINO, JUN Software reliability models for fault-tolerant avionics [MBE-LKE292/S/PUB/191] p36 N88-10038 Wing design with a three-dimensionaltransonic inverse computers and related topics MYERS, 0. method p 14 A88-13077 Dilution jet mixing program, phase 3 [NASA-CR-181440] p60 N88-11382 OHTA, HlROBUMl p54 N88-11153 MILLER, R. A. Syntheses of reducedorder controllers for active flutter Thermal expansion mismatch and oxidation in thermal suppression p35 A88.10095 barrier coatin$s p56 N88-11182 OKADA, NORIAKI MINECK, RAYMOND E. N Measurements in the functional mock up test of the Wall interference tests of a CAST 10-2/DoA airfoil 2 NAL QSTOL aircraft control system in an adaptivawall test section NAJJAR. YOUSEF S. H. [ NAL-TR-9281 p 36 N88-10793 [NASA-TM-4015] p 18 N88-10772 Prediction of gas turbine combustor-liner temperature MIRONOV, A. P. [ASME PAPER 87-GT-1771 p31 A88-11085 OKITA, TOSHlMlCHl Diagnosis of flow channel in aircraft gas-turbineengines NAKADATE, MASAAKI Flight test results for a GPS receiver in a helicopter on basis of vibration spectrum characteristics An aerodynamic design study of transonic transport and a business aircraft p22 A88-13094 p 35 N88-10993 wings p 15 A88-13078 OLIVER, J. 0. MISHIN, G. 1. NAKAMURA, HIROAKI The advantage of flightpath-oriented situation displays Supersonic flow around a sphere in a thermal Some topics on aircraft landing gear dedgn during microborst encounters inhomogeneity p2 A88-10264 p 24 A88-13085 [SAE PAPER 8617331 p35 AM-10164 MIYAKAWA, JUNlCHl NAKAVAMA, HISANAO OWEN, D. T. Wing design with a three-dimensional transonic inverse Design study for an FEW lateral control system Wind tunnel testing of small scale pressure tapped model method p 14 A88-13077 p 36 A88-13080 propellers P32 A88-11196

8-7 PAAS, JOHN E. PERSONAL AUTHOR INDEX

P PROKHOROV. E. M. RUDOFF, R. C. Optimal lifting wings with required longitudinal balancing Experiments on spray interactions in the wake of a bluff PAAS, JOHN E. characteristics p 14 A88-12075 MY Introduction and application of the General Electric [ASME PAPER 87-GT-481 p44 A88-11000 turbine engine monitoring software within KLM Royal Dutch RUSSELL, L M. Airlines Q Use of a liquidcrystal and heater-element composite [ASME PAPER 87-GT-167) p 30 A88-11078 for quantitative, high-resolution heat-transfer coefficients PALMER, DAVID T. QUINLIVAN, RIHCARD PAUL on a turbine airfoil including turbulence and Low cost windowless cockpit research vehicle Ovelview of AGARD Lecture Series No. 155: surface-roughnesseffects p 44 A88-10969 [SAE PAPER 8617551 p 39 A88-10156 Knowledge-based concepts and artificial intelligence RUSSELL, R. W. PALMER, MICHAEL T. applications to guidance and control p 38 N88-10807 Test of IR arrays on the Kuiper Airborne Observatory Implementation of a research prototype onboard fault p 49 A88-12838 monitoring and diagnosis system RUSSO, CAROL J. [AIAA PAPER 87.27771 p 59 A88-12540 R Initial user experience with an artificial intelligence PANARAS, ARGYRIS G. program for the preliminary design of centrifugal The spatially nonuniform convergence of the numerical RABE, D. C. compressors solution of flows Verification of compressor data accuracy by uncertainty [ASME PAPER 87-GT-2171 p 58 A88-11115 [ NASA-TM-1000371 p 60 N88-11429 analysis and testing methods PARKER, R. J. [ASME PAPER 87-GT-1651 p 30 A88-t 1076 Optical How diagnostic measurements in Characterizationof shock wave end wall boundary layer S turbomachinery interactions in a transonic compressor rotor SAABAS. H. J. [ PNR903961 p 52 N88-11081 [ASME PAPER 87-GT-1661 p6 A88-11077 Application of the transient test technique to measure PATANKAR, SUHAS V. RADER, J. local heat transfer coefficients associated with augmented Prediction of turbine blade heat transfer Sensor controlldata display set (SCIDDS) for film airfoil cooling passages p 54 N88-11162 andlor electro optics (EO) p 26 A88-12731 [ASME PAPER 87-GT-2121 p47 A88-11112 PATRICK, T. J. RAHNKE, C. J. SAGAWA, KOUlCHl Wind-tunnel test results of Eppler 387 aerofoils and Development of the AGT101 regenerator seals The flow visualization on the rotary wing with low aspect comparisons with flight test and computation [ASME PAPER 87-GT-1731 p 46 A88-11083 ratio p2 A88-10094 p 12 A88-11208 RAI, MAN MOHAN SAN ANDRES, L A. PAULEY, LAURA Navier-Stokes simulations of rotorlstator interaction Effect of fluid inertia on the performance of squeeze An analysis of unsteady, two-dimensional separation using patched and overlaid grids p A88-10354 2 film damper supported rotors bubbles p9 A88-11182 RAMASWAMY, V. G. [ASME PAPER 87-GT-2201 p48 A88-11117 PAYNE, R. C. Constitutive modeling for isotropic materials SANTORO, GILBERT J. Noise levels from propeller-driven aircraft measured at p 55 "3-1 1172 Experimental verification of vapor deposition rate theory ground level and at 1.2 m above the ground RAUSHENBAKH, 8. V. in high velocity burner rigs p 43 N88-11179 [NPL-AC-1101 p 61 N88-10594 Invest!gations in the history and theory of development SASAKI, ATSUHIRO PENDERGRAFT, ODlS C.. JR. of aerospace science and technology. Number 5 Stress intensity factors and residual strength of a Comparison of wind tunnel and flight test afterbody and p 62 A88-12202 cracked stiffened panel p 50 A88-13083 nozzle pressures for a twin-jet fighter aircraft at transonic REBSTOCK, RAINER SATO, YUKlNORl A method for the calculation of transonic flows for the speeds Current design status and design trend of fuel injectors [NASA-TP-2588] p 17 N88-10765 control of adaptive wind tunnels for jet engines p A88-13076 [ ETN-87.90411 I p 17 N88-10015 33 lntergration effects of D-shaped. underwing, SATOH, R. REDDY, D. N. aft-mounted. separate-flow, flow-through nacelles on a Cyclic spinning testing of aero-engine discs Flow investigations on swirling compressible flow high-wing transport [ASME PAPER 87-GT-2591 p 32 A88-11139 through a vaneless radial diffuser [ NASA-TM-40181 p 18 N88-10773 SCHEER. EKKEHARD [ASME PAPER 87-GT-1931 p 7 A88-11097 PERMINOV, V. A. New Soviet helicopter technology and its potential for REECE, ERIC W. Applicability of a diffusion combustion model to the industrial use p 1 A88-10657 The aerothermodynamic environment for holes in analysis of supersonic turbulent reacting jets SCHETZ, J. A. hypersonic configurations p 40 A88-10180 Numerical solutions of scramjet nozzle flows [DE87-014651I p 17 N88-10767 PERRY, MARK L p2 A88-10359 REED, HELEN Low Reynolds number wind tunnel measurements - The SCHIFF, LEWIS 8. An analysis of unsteady, two-dimensional separation importance of being earnest p 10 A88-11190 Experimentalstudy of three-dimensionalseparated flow bubbles p9 A88-11182 PETERS, DAVID A. surrounding a hemisphere-cylinderat incidence REED, WILLIAM J. Integration of dynamic, aerodynamic and structural [AIAA PAPER 87-24921 p3 A88-10498 A 1987 progress report of manufacturing techniques for optimization of helicopter rotor blades SCHMIDT, JAMES F. Gravity Probe B gyroscope rotors [ NASA-CR-18144t 1 p 16 N68-10012 Application of advanced computational codes in the [ NASA-TM-1OO3121 p 53 N88-11101 design of an experiment for a supersonic throughflow fan PETERS, J. E. REICHOW, DIETER rotor Current gas turbine combustion end fuels research and The impact of modern technology on aircraft avionics [ASME PAPER 87-GT-1601 p6 AM-11072 develc+Jment equipment p 26 A88-10679 SCHMITT, PETER [ASME PAPER 87-GT-1071 p 30 A88-11039 RETZER, 0. Optimal information processing for sensors and sensor PETROV, 1. 8. Detection of targets in the presence of clutter using systems The case of radar sensors p 26 A88-10685 Numerical solution of coupled problems of supersonic target echo modulations caused by rotating structures . SCHOENDORF, JOHN F. flow past deformable shells of finite thickness [ REPT-12-86] p 50 N88-10231 Creep fatigue life prediction for engine hot section p 13 A88-11280 REUTER, DlERK materials (isotropic): Third year progress review PHUCHAROEN, W. Flame driving of longitudinal instabilities in lquid fueled p 55 N88-11173 Thermal expansion mismatch and oxidation in thermal dump combustors SCHRICKER, KARL E. barrier coatings p56 N88-11182 [ AD-A1835361 p 33 N88-10033 Robotic air vehicle A pilot's perspective RICKS, WENDELL . PIROOOV. V. 8. R. p 19 A88-10437 Traditional versus Nle-based programming techniques Numerical solution of coupled problems of supersonic SCHUDY, ROBERT ~ Application to the control of optional flight information flow past deformable shells of finite thickness Intelligent interfaces to aircraft systems p13 AM-11280 p 58 A88-10965 [AIAA PAPER 87-27761 p59 A88-12539 Implementation of a research prototype onboard fault POLACEK, OlTO SCHUMANN, LAWRENCE F. monitoring and diagnosis system The fourth generation of TL commercial aircraft A method for calculating turbulent boundary layers and [AIAA PAPER 87-27771 p 59 A88-12540 p 23 A88-10656 losses in the flow channels of turbomachines RIECHE, ALEXANDER POLL, D. 1. A. [ASME PAPER 87-GT-2251 p7 A88-11121 Flight safely and risk p 19 A88-10658 On the determination of the 2-0 characteristics of SCHUlTE, PAUL C. RINGNES, ERIK A. aerofoils at low Reynolds numbers p 10 A88-11192 Implementation of a research prototype onboard fault Analyses and aSSessments of span wise gust gradient PONOMAREV, 8. A. monitoring and diagnosis system data from NASA 8-576 aircraft [AIM PAPER 87-27771 p 59 A88-12540 Turbines with counterrotating runners for aircraft power [NASA-CR-t78288] p 15 N88-10007 plants p 34 "3-1 0992 SCHWIETERMAN,J. P. ROBINSON, K. Issues in air transport and airport management PORAT, 1. Diiital controls for gas turbine engines [ PE87-2045091 p 19 NM-10782 An optimal control method for passage of a flexible rotor [ASME PAPER 87-GT-2111 p31 A88-11111 SCOlT. WILLIAM B. through resonances p48 A88-11439 ROEDER, JEAN 6-1B combines brisk low-altitude handling, more capable PORTAT, M. The will to European unity as exemplified by A320 avionics p 23 A88-10675 Thin-film temperature sensors deposited by radio p 23 A88-10659 SCZERZENIE, F. frequency cathodic sputtering p 50 AM-12903 ROLFE, J. M. Developments in disc materials p 42 A88-12632 POlTl, N. D. Flight simulation p39 A88-11470 Verification of compressor data accuracy by uncertainty ROSSANO, 0. S. SEIDLER, FRITZ analysis and testing methods Test of IR arrays on the Kuiper Airborne Observatory New Soviet commercial airliners p 23 A88-10655 [ASME PAPER 87-GT-1651 p 30 A88-11076 p49 A88-12838 SEKINE. CHOOO PRESSWELL, MARTYN S. ROTH, ROLAND GPS receivers for air navigation p 22 A88-13093 The performance of del aircraft using flow The dependence of the normalized ice accretion SELIKHOV, A. F invigorators. gliding in the critical range of Reynolds thickness on cloud-physical parameters Ensuring the service life of designs (experience in aircraft number p12 AM-11206 [DFVLR-FB-8708] p57 N88-10464 construction) p 1 NM-10986

8-8 PERSONAL AUTHOR INDEX TURNER, LESTER

SEROV, IU. L STAPLES, K. J. T Supersonic flow around a sphere in a thermal Flight simulation p 39 A88-11470 inhomogeneity p2 A88-10264 STARKEN, H. TAOA, AKlRA SHAMROTH, S. J. Theoretical and experimental analysis of a compressor Measurements in the functional mock up test of the Flow in a model turbine stator p 55 N88-11163 cascade at supercritical flow conditions NAL QSTOL aircraft control system SHATALOV, 0. P. [ASME PAPER 87-GT-2561 p8 A88-11136 [ NAL-TR-9281 p 36 N88-10793 Oxygen recombination in a supersonic cooled flow STEINER, MATTHIAS TAKASAKI, KENZO p 13 A88-12071 Development of a statistically proven injection molding Design and fabrication trial of a composite flap SHEFFLER, K. D. method for reaction bonded silicon nitride, sintering structure p 1 A88-13082 Thermal barrier coating lie prediction model reaction bonded silicon nitride, and sintered silicon TAKEUCHI, YASUO development p56 N88-11185 nitride Design study for an F0W lateral control system SHEPHERD, J. T. [ETN-87-90575] p 52 N88-11002 p 36 ABB-13080 Some approaches to the design of high integrity STEINER. T. R. TANABE, TORU software p 37 N88-10799 Disperston in the wake of aircraft: An investigation of A hybrid navigation system with GPS SHERWIN, KEITH the effects of a ground plane on trailing vortices. Literature p 21 A88-13087 Selection of aerofoil sections for use in man-powered SUNeY TANAKA, KOHEl aircraft p12 A88-11207 [ ICAERO-REP-86-04) p16 NEB-10014 An aerodynamic design study of transonic transport SHERWOOD. LAURENCE T. STEINKE, RONALD J. Labyrinth seal flow measurement by tracer gas wings p 15 A88-13078 Application of advanced computational codes in the TANIOKA, TADAYUKI injection design of an experiment for a supersonic throughflow fan Wing design with a threedimensionaltransonic inverse [ASME PAPER 87-GT-1871 p 47 AM-11092 rotor method p 14 A88-13077 SHIRAZI, SIAMACK A. [ASME PAPER 87-GT-1601 p 6 A88-11072 TASOOJI, A. Prediction of turbulent source flow between corotating STEPHENS, G. E. disks with an anisotropic two-eguation turbulence model Thermal barrier coating life prediction model Comparison of predicted and measured velocities in a [ASME PAPER 87-GT-731 p 45 A88-11017 development p56 N88-11183 compressor disk dNm model SIDOROV. 0. 1. [ASME PAPER 87-GT-2081 p 47 A88-11109 TAYLOR, ROY A. Computing complex for a system for the radb-acoustic A 1987 progress report of manufacturingtechniques for STEPHENS, JOSEPH R. sounding of the atmosphere ~ Hardware facilities Gravity Probe 0 gyroscope rotors High temperature metal matrix composites for future p 58 A88-11394 [ NASA-TM-1003121 p 53 N88-11101 SIEMENS, WERNER aerospace systems [ NASA-TM-1002121 p 43 N88-10938 TEDESCHI, WILLIAM J. Comparison of different kinds of compact cross flow The aerothermodynamic environment for holes in STEWART, 1. F. heat exchangers hypersonic configurations The use of Kevlar on aero-engine fan containment [DFVLR-F086-63] p 51 N88-10305 [DE87-014651] p 17 N88-10767 SIMONS, J. P. casings [PNR90410] p 53 NEB-111 34 TESHIMA, KlYOMl A study of the effects of thermal barrier coating surface Applications of ceramic coating on the turbine blades STEWART, J. roughness on the boundary layer characteristics of F. of the AGTJ-1000 HIDEC adaptive engine control system flight evaluation gas-turbine aerofoils [ASME PAPER 87-GT-1901 p41 AM-11095 [ASME PAPER 87-GT-2231 p48 A88-11120 results THOMPSON, H. DOYLE SIMONS, MARTIN [ASME PAPER 87-GT-2571 p32 Am-11137 Analytlcal study of swirler effects in annular propulsive The use of wind tunnel data in the design of radio STEWART, P. A. E. nozzles p 28 A88-10362 controlled contest model sailplanes p 24 A88-11195 Neutronand positron techniquesfor fluid transfer system SIMPSON, CAROL A. analysis and remote temperature and stress THOMPSON, ROBERT L Versatile simulation testbed for rotorcraft speech I10 measurement High temperature stress-strain analysis system design [ASME PAPER 87-GT-2191 p48 A88-11116 p 55 N88-11170 [SAE PAPER 8616611 p 57 A88-10154 STIELER, B. TILLIAEVA, N. 1. SINGH, TRILOCHAN Stability of supersonic flow of an ideal gas with a head Inertial navigation ~ Technological status and Momentum exchanges and energy transfers in cross development trends p 20 A88-10682 shock wave past cylindrical channels and cavities p 13 A88-12065 flow fans STOLLERY, J. L [ASME PAPER 87-GT-321 p 44 A88-10992 Preliminary measurements of the flight performance of TIPTON, M. T. SINHA, ALOK an RPV compared with wind tunnel and CFD estimates Component specific modeling p 60 N88-11166 Friction damping of random vibration in gas turbine p 12 A88-11203 TITTYANN, BERNHARD R. engine airfoils STOSENKO. YU. V. NDE at twelve o'clock high p 48 A88-11585 [ASME PAPER 87-GT-441 p 29 A88-10996 Turbines with counterrotating runners for aircraft power TODD, E. S SINHA, N. plants p 34 NEB-10992 3-D inelastic analysis methods for hot section Parabolized Navier-Stokes analysis of ducted STRANGE, RICHARD R. components p60 N88-11165 supersonic combustion prhlems p 2 A88-10361 TONG, SIU S. SKILLEN, ROBERT L Development of heat flux sensors for turbine airfoils p 54 N88-11143 Initial user experience with an artificial intelligence Arguments for electrooptical reconnaissance systems program for the preliminary design of centrifugal p 27 A88-12749 STRANGMAN, T. E. Thermal barrier coating life prediction model compressors SKILLMAN, THOMAS [ASME PAPER 87-GT-2171 p58 A88-11115 Autonomous processing using a blackboard chipset development p 56 N88-11183 TORRES, F. J. [AIAA PAPER 87-28551 p 59 A88-12575 STRONGIN, Y. P. Use of a liuidcrystal and heater-element composite SLAVIANOV, N. N. Analysis of supersonic heterogeneous flow impinging for quantitative. high-resolution heat-transfer coefficients Stability of supersonic flow of an ideal gas with a head on an obstacle p 14 A88-12074 on a turbine airfoil including turbulence and shock wave past cylindrical channels and cavitiis STROUP, DAVID W. surface-roughness effects p 44 A88-10969 p13 A88-12lX5 Test resuns and predictions for the response of SMITH, C. F. near-ceiling sprinkler links in a full-scale compartment TREBBLE. W. J. G. Unified equation of motin (UEM) approach as applied fire Aerodynamics of unmanned aircraft at full-scale in the to S1 turbomachinary problems [NBSIR-87-3633] p50 N88-10209 RAE 24lt wind-tunnel p12 A88-11204 [ASME PAPER 87-GT-1791 p 6 A88-11087 STRUB, R. A. Investigation of the suitability of the 8ft x 61t transonic SMITH, J. Influence of the Reynolds number on the performance wind-tunnel for aeroacoustic research on propellers A transonlc model representation for two-dimensional of centrifugal compressors [ RAE-TM-AERO-20931 p39 N88-10041 wall interference assessment [ASME PAPER 87-GT-101 p 44 A88-10979 TRIMMER. J. ROBERT [NLR-TR-86026-U] p 15 N88-10006 STUCKENBERG, NORBERT Color display technology. An overview SMITH, R. 8. Optimal detection of sensor failures in flight control [SA€ PAPER 8618921 p 43 A88-10170 Some approaches to the design of hgh integrity systems using deterministic ObseNers TROY, R. software p37 N88-10799 p38 N88-10803 Assessment of software quality for the AIRBUS A310 WAYNE D. wim. STURZ, R. automatic pilot p 38 N88-10804 Comparison of programmable legend keyboard and Airborne reconnaissance pod flight feat TRUMAN, C. RANDALL dediited keyboard for control of the fliht management p27 A88-12741 Prediction of turbulent source flow between corotating computer disks with an anisotropic two-eguation turbulence model SUMANTRAN, V. [SAE PAPER 8617721 p57 A88-10160 [ASME PAPER 87-GT-731 p 45 A88-11017 Control surface effects on the low Reynolds number SONNEBORN. WALTER TSUDA, NAOHITO behavior of the Wortmann FX 63-137 Composite materials in rotorcraft p 24 Am12412 Design and fabrication trial of a composite flap p 10 A88-11187 SOURIAL N. structure p 1 A88-13082 Compressor turbine vane ring (PT6 engine) repair SUZUKI, KOJIRO TURNER, A. B. development The flow visualization on the rowwing with low aspect Sealing of a shrouded rotor-stator system with preswirl [ASME PAPER 87-GT-471 p 29 A88-10999 ratio p 2 AM-10094 coolant SPENCER, F. A. SWANSON, 0. A. [ASME PAPER 87-GT-721 p 45 A88-11016 Issues in air transport and airport management Life prediction and constitutive models fw engine hot TURNER, D. A. [P087-204509] p 19 N88-10782 section anisotropic materials program Development of ceramic hot section components for SRINIVASAN. R. p 56 NEB-1 1175 AGT 100 gas turbine Combustordiftuser interaction program SWOUNSKY, MANFRED [ASME PAPER 87-GT-791 p45 A88-11019 p 35 N88-11152 Contributions to the modeling of wind shear for danger TURNER, LESTER Dilution jet mixing program, phase 3 studis Synchronizing video signals to standard IRlG time p54 N88-11153 [ETN87-90442] p 57 N88-10463 codes p 21 A88-12737

B-9 TUSCHE, SIEGHARD PERSONAL AUTHOR INDEX

TUSCHE, SIEGHARD W WIEDEMANN, JOHN Experience about the application and valuation of An integrated display for vertical situation awareness roughness strips for boundary layer transition control in WACHTER, J. in commercial transport aircraft wind tunnel tests in the high-speed range Development and application of a high frequency wedge [SAE PAPER 8617701 p 57 A88-10158 [ESA-TT-1028] p 51 N88-10278 probe WIESNER, HERMANN [ASME PAPER 87-GT-2161 p47 A88-11114 Color display programming for aviation WAGGENER, WILLIAM N. [DFVLR-MITT-87-03] p 28 N88-10031 U Datalink design trade-offs for electro-optical WILL, HERBERT A. reconnaissance systems p 27 A88-12740 The Lewis Strain Gauge Laboratory: Status and plans UCHIDA, KAZUO WAKATSUKI, T. p 54 N88-11146 Applications of ceramic coating on the turbine blades Cyclic spinning testing of aero-engine discs WILLIAMS, B. R. of the AGTJ-100B [ASME PAPER 87-GT-2591 p 32 A88-11139 The calculation of flow about aerofoils at low Reynolds [ASME PAPER 87-GT-1901 p 41 A88-11095 WALKER, KEVIN P. number with application to remotely piloted vehicles UCHIDA, MORIMASA Constitutive modeling of superalloy single crystals with p 11 A88-11197 Altitude tests of the XF3-30 turbofan verification testing p 43 N88-11189 WILLIAMS, M. CARLSON [ASME PAPER 87-GT-251 p 28 A88-10987 WALLER, JAMES P. Inter and intra blade row laser velocimetry studies of UCHIDA, TADAO Composites technology in Army aviation gas turbine compressor flows Measurements in the functional mock up test of the p 24 A88-12413 [ASME PAPER 87-GT-2351 p7 A88-11126 NAL QSTOL aircraft control system WALTON, P. G. WOOD, JERRY R. [ NAL-TR-9281 p 36 N88-10793 Prediction of a microlight biplane's aerofoil performance Application of advanced computational codes in the UCHIMOTO, TETSUO using a computer model p 11 A88-11198 design of an experiment for a supersonic throughflow fan Structure simplification around a cutout - Application of WANG. 0. S. rotor a simplified damage tolerance design chart Rient developments in the calculation of flow over low [ASME PAPER 87.GT-1601 p 6 A88-11072 p 50 A88-13084 Reynolds-number airfoils p10 AM-11191 WOODWARD. RICHARD P. Advanced turboprop wing installation effects measured UCZEKAJ, STEPHEN A. WANG. WEIPENG Investigation of control law for active flutter by unsteady blade pressure and noise Autonomous processing using a blackboard chipset suppression [ NASA-TM-100200] p 15 N88-10008 [AIAA PAPER 87.28551 p 59 A88-12575 [ NASA-lT-201261 p 39 N88-10818 Noise of a model high speed counterrotation propeller WANG, ZHONGQI at simulated takeofflapproach conditions (F7lA7) A discussion of the mean 52 stream surfaces applied [NASA-TM-100206] p 61 N88-10592 v to quasi-three-dimensional calculation programs for WRIGLEY, MARK turbomachinery design Optical systems for gas turbine engines VALERO, N. A. [ASME PAPER 87-GT-1501 p 5 A88-11067 p 49 A88-12657 Localization of natural modes of vibration in bladed WARFIELD, MATTHEW J. WU, CHUNG-HUA disks Calculation of a three-dimensionalturbomachinery rotor Shock embedding discontinuous solution of elliptic [ASME PAPER 87-GT-461 p 29 A88-10998 flow with a Navier-Stokes code equation for inverse problem of transonic S2 flow VALLANCE, J. K. [ASME PAPER 87-GT-2321 p 7 A88-11125 [ASME PAPER 87-GT-1151 p 5 AM-11043 Development of the AGT101 regenerator seals WARNER, DAVID N., JR. WYATT, RANDALL E. [ASME PAPER 87-GT-1731 p 46 A88-11083 Approach trajectory planning system for maximum Low altitudelairspeed unmanned research aircraft VAN INGEN, J. L. concealment (LAURA) preliminary development p 12 A88-11205 Aerodynamics at low Reynolds numbers - A review of [ NASA-TM-BB25BI p60 N88-11435 theoretical and experimental research a1 Delft University WATANABE. TAKESHI of Technology p8 ABB-11177 High-lift-device design and low-speed wind-tunnel test X VANCE, JOHN M. p 15 A88-13079 Effect of fluid inertia on the performance of squeeze WATANUKI, TADAHARU XU, J. 2. film damper supported rotors The flow visualization on the rotary wing with low aspect Numerical solution of stream function equations in [ASME PAPER 87-GT-2201 p48 A88-11117 ratio p2 A88-10094 transonic flows [ASME PAPER 87-GT-181 p3 A88-10983 VANDERBERG, 8. WATSON, R. 0. Numerical computation of non-isentropic potential Measurement techniques in low-speed turbulent flows: Pressure fMdue to drag reducing outer layer devices equations for transonic cascade flows A report on EUROMECH 202 in turbulent boundary layers p 3 A88-10492 WATT, R. M. [ASME PAPER 87-GT-1591 p 5 A88-11071 [NLR-MP-86038-U] p 51 N88-10283 xu, L VANSTONE, R. n. A study of the effects of thermal barrier coating surface rouahness on the boundarv laver characteristics of The base pressure and loss of a family of four turbine Constitutive modeling for isotropic materials .. blades p55 N88-11172 gacturbine aerofoils [ASME PAPER 87-GT-2231 p 48 A88-I1120 [ASME PAPER 87-GT-2021 p7 A88-11106 Elevated temperature crack growth XU, SHUXUAN p 55 NEB-1 1174 WEAVER, M. J. Mechanical property requirements for aero gas turbine Calculation of aerodynamic heat transfer for blunt-nosed VARGANOV. N. 0. materials p 42 A88-12628 thin wings at different angles of attack at supersonic Extended systems of variable structure with mobile WEBER, A. speeds radio-communicationobjects p 44 A88-10726 Theoretical and experimental analysis of a compressor [NASA-TT-20127] p 18 N88-10776 VERDON, J. M. cascade at supercritical flow conditions Unsteady aerodynamic measurements on a rotating [ASME PAPER 87-GT-2561 p8 A88-11136 cornpressor blade row at low Mach number WELLS, JOHN KIMBERLY Y [ASME PAPER 87-GT-2211 p7 A88-11118 Steering mechanism VERWN, JOSEPH M. [EP-PATENT-0-181-700-Al] p 51 N88-10338 YAHYA, S. M. Viscidlinviscidinteraction analysis of subsonic turbulent WENNERSTROM, A. J. Flow investigations on swirling compressible flow trailing-edge flows p 14 A88-12282 Characterization of shock wave end wall boundary layer through a vaneless radial diffuser VIDERMAN, Z interactions in a transonic compressor rotor [ASME PAPER 87-GT-1931 p 7 A88-11097 An optimal control method for passage of a flexible rotor [ASME PAPER 87-GT-1661 p6 A88-11077 YAMADA, HlDEJlRO through resonances p 48 A88-11439 WETTON, R. J. Development of the XF3-30 turbofan engine VIGDOROVICH, 1.1. Prediction of combustion performance of aviation [ASME PAPER 87-GT-261 p 28 A88-10988 Strong gas injection into supersonic How with turbulent kerosines using a novel premixed flame technique YAMASHITA, NAOHIRO mixing p 13 A88-12056 [ASME PAPER 87-GT-1251 p 41 A88-11052 GPSllNS hybrid navigation for aircraft VIJGEN, PAUL M. n. w. WHITE, C. p 22 A88-13090 Observations and analyses of natural laminar flow over Combustordiffuserinteraction program YAMATO, HlROYUKl a nonlifting airframe surface p 35 N88-11152 Measurements in the functional mock up test of the [SAE PAPER 8710201 p15 A88-13096 Dilution jet mixing program, phase 3 NAL OSTOL aircraft control system VINEY, 8. p54 N88-11153 [NAL-TR-928] p 36 N88-10793 The turbomachine blading design achieved by solving WHITE, ED YANAI, NOBUKAZU A 1987 progress repoct of manufacturingtechniques for the inverse field problem Design and fabrication trial of a composite flap Gravity Probe gyroscope rotors [ASME PAPER 87-GT-2151 p31 A88-11113 B structure p 1 A88-13082 [ NASA-TM-100312] p 53 N88-11101 VIZZINI, R. W. WHITE, M. E. YASHIMA, SATOSHI Conceptual design of an optic based engine control Evolution and application of CFD techniques for scramjet Altitude tests of the XF3-30 turbofan system engine analysis p28 A88-10358 [ASME PAPER 87-GT-251 p 28 A88-10987 [ASME PAPER 87-GT-1681 p 30 A88-11079 WHITFIELD, A. YATES, E. CARSON, JR. VOELCKERS, U. Stability of conical and ~~edannular diffusers for AGAR0 standard eeroelastic configurations for dynamic A rule-based system for arrival sequencing and mixed-flow compressors response. Candidate configuration I.-wing 445.6 scheduling in air traffic control p 22 N88-10815 [ASME PAPER 87-GT-1911 p6 A88-11096 [NASA-TM-100492] p 56 N88-11202 VON VlLLlEZ, HANSJUERGEN F. wtiirrE. s. YOKOTA, SAKAE Development studies of a European data network fin The deviation of light rays passing through a curved Advanced composite horizontal stabilizer for acquisition. processing. and display of air-traffic data windscreen next-generation commercial aircraft p 24 A88-13081 p 21 A88-10688 [BAE-MSC.115] p62 N88-10610 YONKE, W. A. VOSKOBOINIKOV, V. V. WIBERLEY, STEPHEN E. HlDEC adaptive engine control system flight evaluation Extended systems of variable structure with mobile Composite structural materials results radiocornmunicatin objects p44 A88-10726 [ NASA-CR-1814161 p56 N88-11186 [ASME PAPER 87-GT-2571 p32 AM-11137

B-10 PERSONAL AUTHOR INDEX ZOU, ZlXlANG

YUAN, DING A new method of calculating optimum velocity distribution along the blade surface on arbitrary stream surface of revolution in turbomachines [ASME PAPER 87-GT-301 p4 A88-10991 Z UBELINSKII, 1. E. Oxygen recombination in a supersonic cooled flow p 13 A88-12071 UYAN, K. 8. Y. Q. Transition and separation control on a low-Reynolds number airfoil p9 A88-11186 A natural low frequency oscillation in the wake of an airfoil near stalling conditions [NASA-TM-1002131 p 18 N88-10779 ZENZ, HANSPETER Test equipment with fiber optic data bus and laser gyro strapdown system LTN-W lor the helicopter 80-105 [ ESA-TT-10381 p 22 N88-10025 ZHANG, FENG-XIAN A generalized numerical method for solving direct inverse and hybrid problems of blade cascade flow by using streamlineso-ordinateequation [ASME PAPER 87-GT-291 p 4 A88-10990 ZHANG, JIN Investigation of integrated selection of optimum engine cycle parameters [ASME PAPER 87-GT-391 p 29 A88-10993 ZHU, DEMAO Investigation 01 control law for active llutter suppression [ NASA-TT-201261 p 39 NEB-10818 ZHU, XlNGJlAN Investigation of integrated selection of optimum engine cycle parameters [ASME PAPER 87-GT-391 p 29 A88-10993 ZHU, XUJIN A discussion of the mean S2 stream surfaces applied to quasi-three-dimensional calculation programs for turbomachinery design [ASME PAPER 87-GT-1501 p5 A88-11067 ZHU, Y. A simplified method for 3-D potential flow in turbomachinery using vortex sheet boundary conditions [ASME PAPER 87-GT-281 p3 A88-10989 ZHU, ZHlLl Investigation of integrated selection of optimum engine cycle parameters [ASME PAPER 87-GT-391 p 29 A88-10993 ZHUKOVSKIY Ensuring the service life of designs (experiencein aircraft construction) p 1 N88-10986 ZINN, BEN T. Flame driving of longitudinal instabilities in liquid fueled dump combustors [AD-A183536] p 33 N88-10033 LOU, ZlXlANG A new method of calculating optimum velocity distribution along the blade surface on arbitrary stream surface of revolution in turbomachines [ASME PAPER 87-GT-301 p4 A88-10991

B-11 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 223) February 1988

Typical Corporate Source Index Listing Arlzons State Unlv., Tempe. A rule-based system for arrival sequencing and Modeling and measurement of heat transfer on turbine scheduling in air traffic control p 22 N88-10815 hlade tips p 33 N88-10032 Deutsche Forachungs- und Verauchunstalt fuer Luft- Arizona Unlv., TuC8On. und Raumfahrt. Cologne (West Germany). Refined numerical solution of the transonic flow past a Comparison of different kinds of compact cross flow CORPORATE SOURCE wedge p 14 A88-12280 heat exchangers Army Propulsion Lab., Cleveland, Ohlo. [ DFVLR-FB-86-63] p 51 N88-10305 A method for calculating turbulent boundary layers and Deutsche Forschunga- und VemUChMnSblt fuer Luft- losses in the flow channels of turbomachines und Raumfahrt, Goettlngen (West Germany). IASME PAPER 87-GT-225I p7 A88-11121 ~ ?- The history of aeroelasticity research in Germany from General Electric Co , Lynn, Mass. the beginning until 1945 The design 01 a turboshaft speed governor using modern IDFVLR-MITT-86-25] p 1 N88-10003 control techniques B Analysis of free molecular eflects on the anitude of I NASA CR 175046 I p51 N88 10339 satellites in geostationary transfer orbit Part 2 Force and r Eattelle Columbus Labs., Ohlo. Digital system bus integrity torque measurement in free molecular wind tunnel tests INASA-CR-1814461 p28 N88-10030 IDFVLR-16-222-86-A47 1 p40 N88-10078 Bell Telephone Labs.. Inc.. Whlppany, N. J. Deutache Forschungs- und Ver8UCh~nItaltfuer Luft- Prediction of sound fields in cavities using und Raumfahrt. Oberpfaffenhofen (West Germany). boundary-elementmethods p 61 A88-I2281 The dependence of the normalized ice accretion Boelng Commerclal Alrplane Co., Saattle. Waah. thickness on cloud-physical parameters [ DFVLR.FB-87-06] p 57 N88-10464 Comparison of programmable legend keyboard and dedicated keyboard for control of the flight management Deutsche Forschunga- und Ver8UChMn8hlt fuOr LUft- computer und Raumfahrt. Weuollng (Weat Germany). [SAE PAPER 8617721 p 57 A88-10160 Robust control system design p 37 N88-10800 Eoelng Mllltary Alrplane Development, Wlchlta. Kans. Comparison of programmable legend keyboard and E Listings in this index are arranged alphabetically by dedicated keyboard for control of the flight management corporate source The title of the document is used computer European Space Agency. Parls (Frence). to provide a brief description of the subject matter [SA€ PAPER 8617721 p 57 A88-10160 Test equipment with fiber optic data bus and laser gyro Bolt, Beranek. and Newman, Inc., Carnbrldge, Mars. The page number and the accession number are slrapdown system LTN-90 for the helicopter 80-105 Intelligent interfaces to aircraft systems [ €SA-TT-I0381 p22 N88-10025 included in each entry to assist tne user in locating [AIAA PAPER 87.27761 p 59 A88-12539 Experience about the application and valuation of the abstract in the abstract section If applicable Erltlah Aerospace Aircraft Group, Preston (England). roughness strips for boundary layer transition control in a report number is also included as an aid in The deviation of light rays passing through a Curved wind tunnel tests in the high-speed range windscreen [ESA-lT-l028l p 51 N88-10278 identifying the document [BAE-MSC 1151 p 62 NEB-10610 Brltlah Aerospace Alrcrafl Group, Woodford (England). The fatigue properties of aerospace steels under F constant amplitude and flight-by-flight simulated loading [ BAE-MSM-R-GEN-05661 p 51 N88-10377 Federal Avlatlon Adrnlnlatratlon, Atlantlc Clty. N.J. A Brltlah Petroleum Co. Ltd., London (England). Full-scale transport controlled impact demonstration Steering mechanism program [EP-PATENT-0-181-700-AlI p 51 NEB-10338 [ NASA-TM-896421 p 19 N88-10021 Advlwry Group for Aerospace ReMarch and Ford Motor Co., Deerborn. Mlch. Development, Neullly-Sur-Sdm (France). Development of the AGTlOl regenerator seals Knowledge Based Concepts and Artificial Intelligence C [ASME PAPER 87-GT-1731 p 46 A88-11083 Applications to Guidance and Control Forrchungalnatltut fuer Hochfreqwnzphyrlk. [AGARD-LS-l551 p38 N88-10806 Callfornla Unlv., Berkeley. Werthhoven (Weat Germany). Reliability of finite element methods in North America Expenmental study of three-dimensionalseparated flow Detection of targets in the presence of clutter uslng [ AGARD-R-7481 p 53 N88-1I139 surrounding a hemisphere-cylinder at incidence target ectw modulations caused by rotating structures [AIAA PAPER 87-24921 p3 A88-10498 Aerommtrlcs. Inc , Mountain VIew, Calli. [ REPT-12-86] p 50 N88-10231 Experiments on spray interactions in the wake of a bluff Perspective traffic display format and airline pilot traflic FWG AsoocIatea, Inc.. Tullahorna. Tenn. bodv avcidance p 58 A88-12639 Analyses and assessments of span mse gust gradient [ASME PAPER 87-GT-481 p44 A88-11000 Carleton Unlv., Ottawa (Ontarlo). data from NASA 8-576 aircran An expert system lor aircraft conflict resolution in dense [ NASA-CR-1782881 p 15 N88-10007 Aeronautical ReMarch Laba.. Melboum (Australla). airspaces p 22 N88-10810 A survey of aircraft integrated control technology Charlea River Analytlcs, Inc.. Carnbrldge. Mau. [AR-004-5611 p 37 N88-10794 Evaluationof a dual processor implementationfor a fault G The influence of load cycle re6onstitution on fatigue inferring nonlinear detection system behawour [AIM PAPER 87-27621 p 59 A88-12532 Gama Turblm Englm Co., F%oenlx, Ark. [ARL-STRUC-R-424] p56 N88-II19tF Conmctkut Unlv., Stom. Combustordifluser interaction program Aerospace COrp., LO8 AWS,CaIH. Constitutive modeling of superalloy slngle crystals mth p 35 N88-I I152 Test of IR arrays on the Kuiper Airborne observatory venftcatlon testmg p 43 N88-11169 Dilution jet mixing program, phase 3 p 49 A88-12838 Crnntkld lnrt of Tech., Bedford (England). p54 N88-It153 A preliminary investgatcon into the feaslbility of Thermal barrier coating life prediction rodel Alr Force acUpatlonal and Envlronrn0nt.l Health Lab.. implementcng a dkect sldeforce wnbd system on the Astra development p56 N88-11183 Brooks AFB. Tax. Hawk by means of an active control surface General Ehctrlc Co., Blnghamton. N.Y. First article test ncise SUNW of the A/F32T-9 large turbo [ETN87-90924] p 37 N88-10795 Overview of AGARD Lecture series No. 155: fan engine enclosed mse suppressor system. Sky Harbcf Knowledge-based concepts and artificial intelligence IAP (Internabonal Airport). Phoenix. Anzona applicatwns to guidance and control p 38 N88-10807 [ AD-A1837991 p 61 N88-10588 D G.rmrl Eioctrk Co., Clndnrutl, Ohlo. Alr Force Wrlght A.rwutlul Labs., Harnpton. Va. Blade loss trmSient dynamlcs analysis. volume 1. Task Cost samngs poasble mth Air Force M(Ivemon to JP-8 D.utKh. FonchUngS- Und VmUchNIUM fUOf LUft- 2 TETRA 2 theoretical development as 118 pnmary fuel und Raumlahrl, BIUMWkk (We01 (i.muny). [ NASA-CR-1796321 p34 N88-10791 [AD-A1837841 p42 N88-I0192 An observer approach to the estimation of helicopter Blade loss transient dynamics analysis. volume 2. Task Alabama Unk., Huntavllk. airspeed 2: TETRA 2 user’s menuat Global posctioning satellitebased automatic landing [DWLR-FB-87-13] ’ p 25 N88-10029 [NASACR-179633] p34 N88-10792 system and wind estimated feedbaclr for the AH44 color dmplay programming for aviation 3D inelastic analysis methods for hot section hellcopter p22 N88-10784 [DFVLR-MIlT87-03] p28 N88-10031 components p55 N88-11184 AM- Sdoncos Corp, R..dlng. Yur Optimal detection of sensor failures in fliht control Componentspeclficmodeling p60 N88-11166 AI expert system technology isatbas for guidance and systems using deterministic observers Constitutive modeling for isotropic materiels control appllcabons p38 N88-1M)08 p38 N88-10803 p55 N88-11172

c-1 General Electric Co., Lynn, Mass. CORPORA TE SOURCE

Elevated temperature crack growth McDonnell Alrcraft Co., St. Louls, Mo. Evaluation of a dual processor implementationfor a fault p 55 N88-11174 HIDEC adaptive engine control system flight evaluation inferring nonlinear detection syslem General Electric Co., Lynn, Mans. results [AIAA PAPER 87.27621 p 59 A88-12532 The design of a turboshaft speed governor using modern [ASME PAPER 87-GT-2571 p 32 A88-11137 Implementation of a research prototype onboard fault control techniques Messerschmltt-Boelkow-ElohmG.m.b.H., Ottobrunn monitoring and diagnosis system [ NASA-CR-1750461 p 51 N88-10339 (West Germany). [AIM PAPER 87-27771 p 59 A88-12540 George Washlngton Unlv., Waahlngton, D.C. Flutter suppression and gust load alleviation. Part 1: Wind-tunnel investigation of a full-scale general aviation Software reliability models for fault-tolerant avionics Results of phase 1 to 3. Part 2: Description of the Garteur airplane equipped with an advanced natural laminar flow computers and related topics model wing [ NASA-CR-1814401 p 60 N88-11382 [MBB-LKE292/S/PUB/191] p36 N88-10038 [ NASA-TP-27721 p 16 N88-10009 Georgla Inat. of Tech., Atlanta. Mlnnesota Unlv., Mlnneapolls. Full-scale transport controlled impact demonstration Integration of dynamic, aerodynamic and structural Prediction of turbine blade heat transfer program optimization of helicopter rotor blades p 54 N88-11162 [NASA-TM-89642] p 19 N88-10021 [NASA-CR-181441] p 16 N88-10012 ~issourlUnlv., Columbia. Comparison of wind tunnel and flight test afterbody and Flame driving of longitudinal instabilities in liquid fueled Development and implementation of an aerodynamic nozzle pressures for a twin-jet fighter aircraft at transonic dump combustors holographic interferometry system p 49 A88-12725 speeds [ AD-A1 835361 p 33 N88-10033 Motoren- und Turblnen-Union Muenchen G.m.b.H. [ NASA-TP-25881 p 17 N88-10765 (West Germany). Effect of empennage arrangement on single-engine nonle/afterbody static pressures at transonic speeds H Noise emission of civil and military aero-engines. Sources of generation and measures for attenuation [ NASA-TP-27531 p 17 N88-10771 [ETN-87-91021] p 62 "3-10595 Wall interference tests of a CAST 10-2/DOA 2 airfoil Hoochst CeramTec A.G.. Selb (West Germany). in an adaptive-wall test section Development of a statistically proven injection molding [NASA-TM-4015] p 18 N88-10772 method for reaction bonded silicon nitride, sintering N lntergration effects of D-shaped, undeming. reaction bonded silicon nitride, and sintered silicon aft-mounted, separate-flow, flow-through nacelles on a nitride Natlonal Aeronsutlw and Space Admlnlstratlon, high-wing transport [ ETN-87-90575I p 52 NEB-11002 Washington. D.C. [NASA-TM-4018] p 18 N88-10773 Calculation of aerodynamic heat transfer for blunt-nosed The application of emulation techniques in the analysis I thin wings at different angles of attack at supersonic of highly reliable. guidance and control computer speeds systems p 37 N88-10798 Imperial Coll. of Science and Technology, London [ NASA-TT-201271 p 18 N88-10776 Reliability modeling of fault-tolerant computer based (England). Investigation of control law for active flutter systems p 37 N88-10801 Dispersion in the wake of aircraft An investigation of suppression AGARD standard aeroelastic configurationsfor dynamic the effects of a ground plane on trailing vortices. Literature [ NASA-lT-201261 p 39 N88-10818 response. Candidate configuration I.-wing 445.6 [NASA-TM-100492] p N88-11202 Survey National Aeronautlcr and Space Admlnlstratlon. Amas 56 [ IC-AERO-REP-86-04] p 16 NEB-10014 Research Center, Moffett Fleld, Callf. Helicopter main-rotor speed effects on far-fieldacoustic Navier-Stokes simulations of rotor/stator interaction levels using patched and overlaid grids p 2 A88-10354 [NASA-TM-100512] p 62 NEB-11451 J Experimental study of three-dimensionalseparated flow Natlonal Aeronautlcs and Space Admlnlstratlon. Lewls surrounding a hemispherecylinder at incidence Research Center, Cleveland, Ohlo. Johns Hopklns Univ.. Laurel, Yd. [AIAA PAPER 87-24921 p3 A88-10498 The effect of variations of cobalt content on the cyclic Evolutionand application of CFD techniques for scramjet Perspective traffic display format and airline pilot traffic oxidation resistance of selected Ni-base superalloys engine analysis p 28 A88-10358 avoidance p 58 A88-12639 p 40 A88-I0031 Joint Publlcatlonr Research Servlce, Arlington, Va. Development and implementation of an aerodynamic Explicit multigrid algorithm for quasi-three-dimensional Ensuring the service life of designs (experiencein aircraft holographic interferometry system p 49 A88-12725 viscous flows in turbomachinery p 2 A88-10355 construction) p 1 N88-10986 Full-scale transport controlled impact demonstration Use of a liquid-crystal and heater-element composite Turbines with counterrotating runners for aircraft power program for quantitative, high-resolution heat-transfer ccelficients plants p 34 N88-10992 [ NASA-TM-896421 p 19 N88-10021 on a turbine airfoil including turbulence and Diagnosis of flow channel in aircraft gas-turbine engines HiMAT flight program: Test results and program surface-roughnesseffects p 44 A88-10969 on basis of vibration characieristics assessment overview Application of advanced computational codes in the P 35 N88-10993 [ NASA-TM-867251 p 24 N88-10026 design of an experiment for a supersonic throughflow fan Comparison of wind tunnel and flight test aftebdy and rotor nozzle pressures for a twin-jet fighter aircraft at transonic [ASME PAPER 87-GT-1601 p 6 A88-11072 K speeds Conceptual design of an optic based engine control [ NASA-TP-25881 p 17 N88-10765 system Kanua Unlv., Lawrence. Analytical modeling of helicopter static and dynamic [ASME PAPER 87-GT-1681 p 30 A88-11079 Observations and analyses of natural laminar flow over induced velocity in GRASP A method for calculating turbulent boundary layers and a nonlifting airframe surface [NASA-TM-1000261 p 18 N88-10777 losses in the flow channels of turbomachines [SAE PAPER 8710201 p15 A88-13096 Flight researh at NASA Ames Research Center: A test [ASME PAPER 87-GT-2251 p7 A88-11121 KOnMS Unlv. Center for Research. Inc., Lawrence. pilot's perspective Transition and separation control on a low-Reynolds Transonic analysis and design of axisymmetric bodies [NASA-TM-100025] p 25 "3-10788 number airfoil p9 A88-11186 in nonuniform flow Flight test a resident backup software system of Advanced turtmprop wing installation effects measured [NASA-CR-4101] p16 N88-10013 p 38 N88-10805 by unsteady blade pressure and noise Karlsruhe Unlv. (West Germany). Impact of turbulence modeling on numerical accuracy [NASA-TM-1002001 p15 N88-10008 Possibilities for the modeling of dynamically loaded and efficiency of compressible flow simulations Noise of a model high speed counterrotation propeller cylindrical structural parts in the wind tunnel [NASA-TM-88333] p 52 N88-11088 at simulated takeoff/approach conditions (F7/A7) [ KU-SFB-21O/T/24] p15 N88-10005 Computation of transonic separated wing flows using an EuledNavier-Stokes zonal approach [NASA-TM-l002061 p 61 N88-10592 [NASA-TM-88311] p 52 N88-11089 A natural low frequency oscillation in the wake of an L The spatially nonuniform convergence of the numerical airfoil near stalling conditions solution of flows [NASA-TM-10021 31 p 18 N88-10779 Lear Slegler, Inc., Grand Rapids, Mlch. [NASA-TM-1000371 p 60 N88-11429 High temperature metal matrix composites for future Flication of knowledge-based techniques to aircraft Approach trajectory planning system for maximum aerospace systems [NASA-TM-10021 21 p 43 NEB-10938 trajectwy generation and control p 38 N88-10811 concealment LockheedOeorgla Co., Marletta. [NASA-TM-88258] p 60 N88-11435 Turbine Engine Hot Section Technology, 1985 Digital system bus integrity National Aeronautlcr and Space Admlnlatratlon. Flight [ NASA-CP-24051 p 53 N88-11140 [ NASA-CR-1814461 p28 N88-10030 Research Center, Edwards, Callf. The Lewis Strain Gauge Laboratory: Status and plans HIDEC adaptive engine control system flight evaluation Loughborough Unlv. Technology (England). p 54 N88-11146 of results Decwpling and stabilization of speed and height in F4 On the mixing of a row of jets with a confined [ASME PAPER 87-GT-2571 p 32 A88-11137 crossflow p 54 NEB-11154 Phantom aircraft using output feedback National Aeronautlw and Space Admlnlstratlon. [ETN-87-90926] p 25 N88-10787 High temperature stress-strain analysis Langley Research Center, Hampton, Va. p 55 NEB-111 70 LTV Mluiks and Electronler Group, Dallas, Tex. Flying complex approach paths using the microwave Design principles and practices for implementation of landing system Experimental verification of vapor deposition rate theory MIL-STD-1760 in aircraft and stores [SAE PAPER 8617711 p 35 A88-10159 in high velocity burner rigs p 43 N88-11179 [AD-At83724] p24 N88-10027 Evolution and application of CFD techniquesfor scramjet Thermal expansion mismatch and oxidation in thermal Luftfahrt-Eundesemt. Erunawlck (West Germany). engine analysis p 28 A88-10358 barrier coatings p56 N88-11182 Aircraft accidents Pressure field due to drag reducing outer layer devices Natlonal Aeronautlcs and Space Adrnlnlrtratlon. [JB-841 p 19 N88-10020 in turbulent boundary layers p3 A88-10492 Marshall Space Fllght Center, Huntsville, Ala. Traditional versus rule-based programming techniques A 1987 progress report of manufacturingtechniques for - Application to the control of optional flight information Gravity Probe B gyroscope rotors M p 58 A88-10965 [ NASA-TM-1003121 p53 N88-11101 Transition and separation control on a low-Reynolds National Aerospace Lab., Amsterdam (Netherlands). Marconl Avlonlcs Ltd., Rochester (England). number airfoil p9 A88-11186 A transonic model representation for two-dimensional Some approaches to the design of high integrity Low-Reynoldsnumber aerodynamics research at NASA wall interference assessment software p37 N88-10799 Langley Research Center p 11 A88-11194 [NLR-TR-86026-U] p 15 NEB-10006 c-2 CORPORA TE SOURCE Virginia Unlv., Charlottesvllle.

Problem and solution formulations for the generation R Texas AIM Unlv., College Station. of 3D block-structured grids Effect of rib angle on local heatlmass transfer [NLR-MP-86020-U] p25 N88-10028 Rensrrelser Polytechnk Inst., Troy, N.Y. distribution in a two-pass rib-roughened channel Measurement techniques in low-speed turbulent flows: Composite structural materials [ASME PAPER 87-GT-941 p 45 A88-11033 A report on EUROMECH 202 [ NASA-CR-1814161 p 56 N88-11186 Texas Unlv., Auatln. [NLR-MP-86038-U] p 51 N88-10283 Rolls-Royce Ltd., Derby (England). The aerothermodynamic environment for holes in Criteria for determination of significant load cycles in The wide chord fan blade: A Rolls Royce first hypersonic configurations variable amplitude load sequences (PNR904161 p 34 N88-10789 [ DE877014651 ] p 17 N88-10767 [ NLR-MPB6013-UI p 51 N88-10386 Investment foundry melting stock. Rolls Royce Tlmken Co., Canton, Ohlo. Aerospace research at the National Aerospace requirements and demands in terms of quality and the Improved oil-off survivability of tapered roller bearings Laboratory (NLR) relationship to end product performance [NASA-CR-180804] p 53 N88-11135 [ ETN-87-908211 p62 N88-10697 (PNR903971 p52 N88-11003 Transportntlon Research Board, Waahlngton, D.C. Boundary layer profile investigations downstream of an Natlonal Aerospace Lab., Tokyo (Japan). Issues in air transport and airport management aero-engine intake anti-icing air exhaust slot Measurements in the functional mock up test of the [PB87-204509] p 19 N88-10782 [ PNR903781 p 52 N88-11080 NAL QSTOL aircraft control system Optical flow diagnostic measurements in [ NAL-TR-9281 p 36 N88-10793 turbomachinery U Natlonal Bureau of Standards, Galthornburg, Md. [PNR90396] p52 N88-11081 Test results and predictions for the response of Transmission efficiency in advanced aerospace Unlted Technologles Research Center, East Hartford, near-ceiling sprinkler links in a full-scale compartment wwemlant Conn. fire ~PNR60391] p 53 N88-111 33 The development01 a high temperaturestatic strain gage [NBSIR-87-3633] p50 N88-10209 The use of Kevlar on aero-engine fan containment system p 53 N88-11142 National Cheng Kung Unlv., Talnan (Taiwan). casings Fuel-injectorlair-swirlcharacterization Refined numencal solution of the transonic flow past a [PNR~~IO] p 53 N88-11134 p 54 NEB-1 1150 wedge P 14 A88-12280 Royal Aircraft Establlahment, Famborough (England). National Physical Lab., Teddlngton (England). On the prospects for increasing dynamic lift Noise levels from propellerdriven aircraft measured at [RAE-TM-AERO-ZCml D 17 N88-10018 V ground level and at 1.2 m above the ground Investigation of the suitability of the eft x 6ft transonic [NPL-AC-1101 p 61 "3-10594 wind-tunnel for aeroacoustic research on propellers S.A., Toulouse (France). Assessment 01 software quality for the AIRBUS A310 NatlOMl TransportationSafety Board, Washington, D. [ RAE-TM-AERO-20931 P 39 N88-10041 automatic pilot p NEB-10804 C. Towards the unmanned cockpit p 25 N88-10812 Vlrginla Unlv., CharlotlO~vllle, 38 Aircraft accident reports, brief format, US civil and foreign A smoke-wire study of low Reynolds number flow over aviation. Issue number 1: 1986 accidents a NASA LRN(1) ~ 1007 airfoil section p 9 A88-11181 [PB87-916903] p 19 N88-10781 S Naval Air Propulsion Teat Center, Trenton, N.J. Conceptual design of an optic based engine control San JOM State Unlv., Calif. system Perspective traffic display format and airline pilot traffic [ASME PAPER 87-GT-1681 p 30 A88-11079 avoidance p 58 A88-12639 NKF Englnwrlng, Inc., Reston, Va. Science Appllcatlona International Corp., Princeton. Fiber optic engineering sensor system. Preliminary N.J. program management plan, phase 3 revision Parabolized Navier-Stokes analysis of ducted [ AD-A1836631 p62 N88-10608 supersonic combustion problems p 2 A88-10361 Notre Dame Unlv.. Ind. Sclentlflc Research AuocIates, Inc., Glastonbury, Low Reynolds number wind tunnel measurements - The Conn. importance of being earnest p10 A88-11190 Flow in a model turbine stator p 55 N88-11163 The structure of separated flow regions occumng near Southampton Unlv. (England). the leading edge of airfoils including transition Activities report of the Institute of Sound and Vibration [NASA-CR-181434] p 16 N88-10011 Research [ ETN-87-906851 p 61 N88-10589 Southwest Research Inst., San Antonlo, Tax. 0 Constitutive modeling for isotropic materials p 55 N88-11171 Offlceof Naval Research, London (England). Stanford Unlv., Callf. International Conference on the Aerodynamics at Low Heat transfer with very high free stream turbulence Reynolds Numbers between lO(4) and lO(6) p 54 N88-11161 [ONRL-7-023-C] p 16 N88-10010 Starck (Hennann C.) Berlin, Baden (Went Germany). Development and production of new and modified powders for sprayed coatings and Components for saving P important raw materials [ BMFT-FB-T86-1291 p 42 N88-10159 Pratt and Whltney Aircraft, East Hertford, Conn. Systems Technology, Inc., Hawthorne, Callf. Inter and intra blade row laser velocimetry studies of lnvestioation of interactions between limb-manioulator gas turbine compressor flows dynamics and effective vehicle roll control [ASME PAPER 87-GT-2351 p7 A88-11126 characteristics Development of heat flux Sensors for turbine airfoils [NASA-CR-3983] p36 NEB-10039 p 54 N88-11143 Coolant passage heat transfer with rotation p 54 N88-11160 T 3-D inelastic analysis methods for hot section components p60 N88-11165 Technlsche Hochschule, Aachen (West Germany). Creep fatigue life prediction for engine hot section Investigation of the excitation of turbine blade vibration materials (isotropic): Third year progress review in axial compressors in rotating stall p 55 N88-111 73 [ETN-87-90377] p34 N88-10035 Life prediction and constitutive models for engine hot Technlsche Hochrchule, Darmstadt (West Germany). section anisotropc materials program Investigations of separated flow states on wings of p56 N88-11175 medium aspect ratio taking into account the wind tunnel Thermal barrier coating life prediction model interference problem development p 56 N88-11185 [ETN87-90437] p17 N88-10016 Pratl and Whitney Aircraft, West Palm Beech, Fla. Technlsche Unlv., Berlin (West Germany). Conceptual design of an optic based engine control A method for the calculation of transonic flows for the system control of adaptive wind tunnels [ASME PAPER 87-GT-1681 p 30 A88-11079 [ETN-87-90411] p 17 N88-10015 Princeton Unlv., N. J. Technlsche Unlv., Brunswlck (West Germany). Localization of natural modes of vituation in bladed Contributions to the modeling of wind shear for danger disks studies [ASME PAPER 87-GT-461 p 29 A88-10998 [ ETN-87.904421 p 57 N88-10463 Paycho-Ungulatk Research Auoclates, Menlo Park, Technlsche Unlv., Munich (West Germany). Callf. Experimental determination of the oscillatory forces on Versatile simulation testbed for rotorcraft speech I10 two turbine blade profiles system design [ETN87-90417] p34 N88-10037 [SAE PAPER 8616611 p57 A88-10154 Tennessee Unlv., KnoxvIIle. Purdue Unlv., West Lafayetto, Ind. Process support compressor motor electromagnetic Prediction of sound fields in cavities using design summary boundary-element methods p 61 A88-12281 [DE87-0143593 P 52 N88-11048

c-3 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 223) February 1988

Typical Foreign Technology Index Listing A simplified method for 3-13 potential llow in Reliability of finite element methods in North America turbomachinery using vortex sheet boundary conditions [ AGARD-A-748] p 53 N88-11139 [ASME PAPER 87-GT-281 p3 A88-10989 A generalized numerical method for solving direct inverse and hybnd problems of blade cascade flow by G INTELLECTUAL using streamhne-coadmateequation ORIGIN [ASME PAPER 87-GT-291 p4 A88-10990 GERMANY DEMOCRATIC REPUBLIC A new method of calculating optimum velocity New Soviet commercial airliners p 23 A88-10655 distnbutlon along the blade surface on arbitrary stream New Soviet helicopter technology and its potential for surface of revolution in turbomachines industrial use p 1 A88.10657 [ASME PAPER 87-GT-301 p 4 A88-10991 JAPAN Flight safety and risk p 19 A88-10658 A numerical method for subsonic unsteady lifting Investigation of integrated selection of optimum engine GERMANY,FEDERAL REPUBLIC OF surlaces . BIS 111 . Some additional numerical results cycle parameters [ASME PAPER 87-GT-391 p 29 A88-10993 Airline requirements on a fly-by-wire aircratt - A pilot's Experimental investigatlons of flows through a plane view cascade at large angles of anack with separations [SAE PAPER 8618041 p 36 A88-10167 [ASME PAPER 87-GT-961 p5 A88-11035 The will lo European unity as exemplified by A320 Shock embedding discontinuous solution of elliplic p 23 A88-10659 equation for inverse problem of transonic S2 flow Modern technology in positioning and navigation; [ASME PAPER 87-GT-1151 p5 A8811043 Navigation Meeting, Duesseldorf. Federal Republic of The performance estimation of transonic turbine at Germany, May 6-8. 1987. Reports p 20 A88-10676 design and off design conditions BMFT-supported projects in the fields position-finding, [ASME PAPER 87-GT-1481 p 30 A88-11066 navigation. and traffic safety p 20 A88-10677 A discussion of the mean S2 stream surfaces applied The importance of modern positioning and navigation to quas-three-dimensional calculation programs for technology for ATC p A88-10678 Listings in this index are arranged alphabetically 20 turbomachinery design The impact of modern technology on aircraft avionics by country of intellectual origin. The title of the [ASME PAPER 87-GT-1501 p 5 A88-11067 equipment p 26 A88-10679 Numerical computation of non-isentropic potential document is used to provide a brief description of Development and trends in radio position finding equations for transonic cascade llows p 20 A88-10880 the subject matter. The page number and the ac- [ ASME PAPER 87-GT-1591 p 5 A88-11071 cession number are included in each entry to as- Investigation of high-altitude ignitlon performance of Inertial navigation - Technological status and development trends p20 A88-10682 sist the user in locating the citation in the abstract several Chinese ]et fuels with different properties (ASME PAPER 87-GT-1781 p 41 A88-11086 Hybnd positioning and navigation systems - section. If applicable, a report number is also in- A multi-gndalgonthm for 2-0 transonic potential cascade Technological status and development trends in cluded as an aid in identifying the document. flow position-finding and navigation procedures [ASME PAPER 87-GT-1801 p6 A88-11088 p 20 A88-10684 A new method (FTCCDF) for blade design of Optimal information processing for sensors and Sensor axial/mixed-flow compressors and its applications systems - The case of radar Sensors p 26 A88-10685 [ASME PAPER 87-GT-1831 p31 A88-11090 Autonomous onboard collison avoidame for aircraft and Calculationof aerodynamic heat transfer lor blunt-nosed ships p21 A88-10687 thin wings at different angles of anack at supersonic Off-designperformance 01 supersonic compressors with speeds fixed and variable geometry A [NASA-lT-20127] p 18 N88-10776 [ASME PAPER 87-GT-1161 p 5 A88-11044 Investigation of control law for active fluner A model to determine the behaviour 01 a pressure AUSTRALIA suppresson measurement equipment during non-static operations of The use of wind tunnel data in the design of radio [NASA-lT-20126] p 39 N88-10818 gasturbine engines controlled contest model sailplanes p 24 A88-1 1195 CZECHOSLOVAKIA [ASME PAPER 87-GT-1281 p 46 A88-11055 The fourth generation of TL commercial aircraft A survey of aircraft integrated control technology Analysis 01 windage losses and velocity distribution for p23 A88-10656 [AR-004-561J p37 N88-10794 a shrouded rotating disk The influence of load cycle reconstitution on fatigue [ASME PAPER 87-GT-1861 p 6 A88-11091 behaviour E Development and applocetwn of a hlgh frequency wedge [ARL-STRUC-R-4241 p56 NEE-11198 probe EGYPT [ASME PAPER 87-GT-2161 p47 A88-11114 Computer predictions of erosion damage in gas Theoretical and experimental analysis of a compressor C turblnes cascade at supercritcal flow condiins [ASME PAPER 87-GT-1271 p 46 A88-11054 [ASME PAPER 87-GT-2561 p8 A88-11136 CANADA Towards the dewgn of an intelligent aerospace system Recent deve(opments in boundary layer computation Compressoc turbine vane ring (PT6 engine) repair [AIM PAPER 87.28441 p 26 A88-12569 p 10 A88-11188 development Recent wind tunnel experiments at low Rayrolds [ASME PAPER 87-GT-471 p 29 A88-10999 numbers pll A88-11193 Combustion gas properties. Ill - Prediction of the F The development 01 wing theory p 14 A88-12483 thermodynamic properties of combustiongases of aviation A mathematical multi-point model for aircraft motion in and diesel bels FRANCE moving air p36 A88-12487

[ASME PAPER 87-GT-491 p40 A8811001 Three-dimensional How in a rotor ~ A strictly Dynamic wind tunnel balances in the DFVLR subsooic Threedimensional calculation 01 wall boundary layer threedimensional calculation of flows in turbomachines wind tunnel in Braunschweig p39 A88-12488 flows in hntJ0machine-s using the s1-s2 method p44 A8810628 Basic concepts for benet heat protection systems [ASME PAPER 87-GT-821 p4 A88-11022 Experimental method for the combustion efficiency p42 A88-12786 A qualitative method for determining the temperatwe calculation in a reheat duct The history of aeroelastkity research in Germany from pallem of run gas turbine blades [ASME PAPER 87-GT-90] p29 A88-11029 the beginning until 1945 [ASME PAPER 87-GT-1021 p45 A8811037 The tulbomachine blading dwgn achieved by sohring [DFVLR-MIlT86-25] pl N88-10003 Possibilities for the modeling of dynamically loaded Application of the transient test technique to measure the inversa fwld problem cylindrical sbuchwal parts in wind tunnel local heat transfer associated with augmented [ASME PAPER 87-GT-2151 p31 A88-11113 the coefficients [ KU-SFB-21OIT1241 p15 N88-10005 aiffoil coding paasagm Airspeed measurement with a 032 lidar A method the calculation the [ASME PAPER 87-GT-2121 p47 A88-11112 lor of transonic tlom, for p 26 A88-12655 control of adaptive wind tunnels An expart system for aircraft conRi resolution in dense Thin-film temperature sensors deposited by radii [ETN-87-90411] p17 N80.10015 airspaces p22 N80.10810 frwCaMOdii spunering p 50 A88-12903 Investigations of separated Row slates on wings of Towards the unmanned cockpit p 25 NEE10812 Assessment of solhvare quality for the AIRBUS A310 medium aspect ratio laking into account the wind tunnel CHINA, PEOPLE'S REWBUC OF automatic pilot p38 N88-10804 intaiierence problem Numerical solution of stream bnclion equations in Knowledge Baaed Concepts and Artificial Intellii: [ETN-87-90437] p17 N88-10016 traMonicRowcl Applications to Guidance and Control Aircraft accidents [ASME PAPER 87-GT-18) p3 A8810983 [AGARDLSI 551 p38 N88-10808 [JBmI pl9 N88-10020

0-1 INDIA FOREIGN TECHNOLOGY INDEX

Test equipment with fiber optic data bus and laser gyro Development of the XF3-30 turbolan engine Anti-tank helicopters for the rich and not so rich strapdown system LTN-90 lor the helicopter 60-105 [ASME PAPER 87-GT-261 p 28 A88-10988 p 1 A88-10877 [ ESA-lT-10381 p 22 N88-10025 Prediction of NO and CO distribution in gas turbine Influence 01 the Reynolds number on the performance An observer approach to the estimation of helicopter combustors of centrifugal compressors airspeed [ASME PAPER 87-GT-631 p 41 A88-11010 [ASME PAPER 87-GT-101 p 44 A88-10979 [DNLR-F6-87-13] p 25 N88-10029 Applications of ceramic coating on the turbine blades Hydrogen in air transportation - Feasibility study for Color display programming for aviation 01 the AGTJ-1006 Zurich Airport. Switzerland p 41 A88-11146 [DNLR-MITT-87-03] p28 N88-10031 [ASME PAPER 87-GT-1901 p 41 A88-11095 Investigation of the excitation of turbine blade vibration Cyclic spinning testing of aero-engine discs in axial compressors in rotating stall [ASME PAPER 87-GT-2591 p 32 A88-11139 T [ ETN-87-903771 p 34 N88-10035 Current design status and design trend of fuel injectors Experimental determination of the oscillatory forces on for jet engines p 33 A88-13076 TAIWAN two turbine blade profiles Wing design with a three-dimensionaltransonic inverse Refined numerical solution of the transonic llow past a [ETN-87-90417] p34 N88-10037 method p 14 A88-13077 wedge p 14 A88-12280 Flutter suppression and gust load alleviation. Part 1 : An aerodynamic design study of transonic transport Results of phase 1 to 3. Part 2: Description of the Garteur wings p 15 A88-13078 model High-lift-device design and low-speed wind-tunnel test U [MEE-LKE292/S/PU6/191 p36 N88-10038 1 p 15 A88-13079 U.S.S.R. Analysis 01 free molecular effects on the attitude of Design study lor an FEW lateral control system Problems in continuum mechanics with mixed boundary satellites in geostationary transfer orbit. Part 2: Force and p 36 A88-13080 condRions p43 A88-10017 torque measurement in free molecular wind tunnel tests Advanced composite horizontal stabilizer for Testing of aircraft electrical equipment [ DNLR-16-222-86-A-071 p40 NEB-10078 next-generation commercial aircraft p 24 A88-13081 p 39 A88-10044 Development and production of new and modified Design and fabrication trial of a composite flap Aircraft acoustics I - Exterior noise of subsonic structure p 1 A88-13082 powders for sprayed coatings and components for saving passenger aircraft and helicopters p 61 A88-10047 important raw materials Stress intensity factors and residual strength of a Aircraft acoustics II .Cabin noise in passenger aircraft [ BMFT-FB-T-86-129] p 42 N88-10159 cracked stiffened panel p 50 A88-13083 p 61 A88-10048 Detection 01 targets in the presence 01 clutter using Structure simplification around a cutout - Application of Flight characteristics 01 aircraft with gas-turbine a simplified damage tolerance design chart target echo modulations caused by rotating structures engines p23 A88-10049 [ REPT-12-86] p50 N88-10231 p 50 A88-13084 Applicability of a diffusion combustion model to the Experience about the application and valuation of Some topics on aircraft landing gear design analysis of supersonic turbulent reacting jets roughness strips for boundary layer transition control in p 24 A88-13085 p 40 A88-10180 wind tunnel tests in the high-speed range An overview of space and aircraft navigation Supersonic flow around a sphere in a thermal [ESA-lT-10281 p 51 N88-10278 p 40 A88-13086 inhomogeneity p 2 A88-10264 Comparison of different kinds of compact cross flow A hybrid navigation system with GPS Necessary optimality conditions for three-dimensional heat exchangers p 21 A88-13087 bodies in supersonic gas flow p2 A88-10300 [DFVLR-F6-86-63] p 51 N88-10305 Civil aviation application of the Global PositioningSystem Extended systems of variable structure with mobile Contributions to the modeling of wind shear for danger (GPS) and its issues p 22 A88-13088 radio-communicationobjects p 44 A88-10726 studies GPSllNS hybrid navigation for aircraft Fast stable solution of a dispersion equation of linear [ETN-87-90442] p 57 N88-10463 p A88-13090 22 filtering p 21 A88-10728 The dependence 01 the normalized ice accretlon GPS receivers for air navigation p 22 A88-13093 The accuracy-related parametric reduction of thickness on cloud-physical parameters Flight test results for a GPS receiver in a helicopter mathematical models p 58 A88-10929 [DFVLR-FB-87-08] p57 N88-10464 and a business aircraft p A88-13094 22 Numerical solution of coupled problems of supersonic Noise emission of civil and military aero-engines. The scramjet Toward Mach 4-25 llight - Row past deformable shells of finite thickness Sources of generation and measures for attenuation p 33 A88-13095 p 13 A88-11280 [ETN-87-910211 p 62 N88-10595 Measurements in the functional mock up test of the Robust control system design p 37 N88-10800 NAL QSTOL aircraft control system Computing complex for a system for the radio-acoustic Optimal detection of sensor failures in flight control [NAL-TR-9281 p 36 N88-10793 sounding of the atmosphere - Hardware facilities systems using deterministic ObSeNerS p 58 A88-11394 p 38 N88-10803 Strong gas injection into supersonic flow with turbulent A rule-based system lor arrival sequencing and N mixing p 13 A88-12056 scheduling in air traffic control p22 N88-10815 Transonic expansions p 13 A88-12059 Development of a statistically proven injection molding NETHERLANDS Stability of supersonic flow of an ideal gas with a head method lor reaction bonded silicon nitride, sintering Introduction and application of the General Electric shock wave past cylindrical channels and cavities reaction bonded silicon nitride. and sintered silicon turbineenginemonitoringsoftwarewithin KLM Royal Dutch p 13 A88-12065 Airlines nitride Oxygen recombination in a supersonic cooled flow [ASME PAPER 87-GT-1671 p30 AM-11078 [ETN-87-90575] p52 N88-llLW2 p 13 A88-12071 Aerodynamics at low Reynolds numbers - A review of theoretical and experimental research at Delft University Effect of energy release in the shock layer on the I of Technology p8 A88-11177 supersonic flight of bodies p 13 A88-12073 A transonic model representation for two-dimensional Analysis of supersonic heterogeneous flow impinging INDIA wall interference assessment on an obstacle p 14 A88-12074 Flow investigations on swirling compressible flow [ NLR-TR-BWP&U] p15 N88-10006 Optimal lifting wings with required longitudinal balancing through a vaneless radial diffuser Problem and solution formulations for the generation characteristics p 14 A88-12075 [ASME PAPER 87-GT-1931 p 7 A88-11097 of 3D block-structured grids Investigations in the history and theory of development INTERNATIONAL ORGANIZ&TION [ NLR-MP-86020-UI p25 N88-10028 of aerospace science and technology. Number 5 The advantages of a primary flight display Measurement techniques in low-speed turbulent flows: p62 A88-12202 [SAE PAPER 8617301 p 58 A88-10162 A report on EUROMECH 202 Ensuring the service life of designs (experience in aircraft Development studies of a European data network for [NLR-MP-86038-U] p 51 N88-10283 construction) p 1 N88-10986 acquisition, processing, and display of air-traffic data Criteria for determination of significant load cycles in Turbines with counterrotating runners lor aircraft power p21 A88-10688 variable amplitude load sequences plants p 34 N88-10992 [NLR-MP-86013-U] p 51 N88-10386 ISRAEL Diagnosis of flow channel in aircraft gas-turbine engines Aerospace research at the National Aerospace Stability of conical and curved annular diffusers for on basis of vibration spectrum characteristics Laboratory (NLR) mixed-flow compressors p35 N88-10993 [ETN-87-90821] p 62 N88-10697 [ASME PAPER 87-GT-1911 p 6 A88-11096 UNITED KINGDOM An optimal control method for passage of a flexible rotor Sealing of a shrouded rotor-stator system with pre-swirl through resonances p 48 A88-11439 R coolant Imaging thrwgh the atmosphere for airborne [ASME PAPER 87-GT-721 p 45 A88-11016 reconnaissance p 27 A88-12748 ROMANIA (RUMANIA) Numerical prediction of turbulent flow in rotating ITALY Arbiiary wings of low aspect ratio in subsonic llow cavities Plume infrared signature measurements and comparison p 3 A88-10660 [ASME PAPER 87-GT-741 p 45 A88-11018 with a theoretical model p 33 A88-12836 Correlations of fuel performance in a full-scale commercial combustor and two model combustors S [ASME PAPER 87-GT-891 p 29 A88-11028 Procedures for determining surface heat flux using thin J SAUDI ARABIA Prediction of gas turbine combustor-liner temperature film gauges on a coated metal model in a transient test JAPAN [ASME PAPER 87-GT-1771 p31 A88-11085 facility A numerical method for subsonic unsteady lifting SINGAPORE [ASME PAPER 87-GT-951 p 45 A88-11034 surfaces - 61s. Ill ~ Some additional numerical results Selection of aerofoil Sections for use in man-powered Prediction of combustion performance of aviation p 2 A88-10093 aircraft p 12 A88-11207 kerosines using a novel premixed flame technique The flow visualization on the rotary wing with low aspect SWEDEN [ASME PAPER 87-GT-1251 p41 A88-11052 ratio p 2 A88-10094 Sensor configuration for a short to medium range Spray performance 01 a hybrid injector under varying Syntheses of reduced-order controllers for active flutter reconnaissance pod p 27 A88-12742 air density conditions suppression p35 A88-10095 SWITZERLAND [ASME PAPER 87-GT-1551 p46 A88-11068 Altitude tests of Me XF3-30 turbofan The Antomv An-74 brings high tech to low Modelling the unsteady flow in a turbine rotor passage [ASME PAPER 87-GT-251 p 28 A88-10987 temperatures p 23 A88-10876 [ASME PAPER 87-GT-1971 p7 A88-Ill01 D-2 FOREIGN TECHNOLOGY INDEX UNITED KINGDOM

The base pressure and loss of a family of four turbine The wide chord fan blade: A Rolls Royce first blades [PNR90416] p 34 N88-10789 [ASME PAPER 87-GT-2021 p7 ABS-11106 A preliminary investigation into the feasibility 01 The United Kingdom engine technology demonstrator implementinga direct sideforce control system on the Astra programme Hawk by means of an active control surface [ASME PAPER 87-GT-2031 p31 A88-11107 [ ETN-87-909241 p 37 N88-10795 Digital controls for gas turbine engines Some approaches to the design of high integrity [ASME PAPER 87-GT-2111 p31 A88-11111 software p 37 N88-10799 Neutron and positron techniquesfor fluid transfer system Investment foundry melting stock. Rolls Royce analysis and remote temperature and stress requirements and demands in terms of quality and the measurement relationship to end product performance [ASME PAPER 87-GT-2191 p48 A88-11116 [PNR90397] p52 N88-11003 A study of the effects of thermal barrier coating surface Boundary layer profile investigations downstream of an roughness on the boundary layer characteristics of aero-engine intake anti-icing air exhaust slot gas-turbine aerofoils [PNR90378] p 52 N88-11080 [ASME PAPER 87-GT-2231 p48 A88-11120 Optical flow diagnostic measurements in Boundary layer profile investigations downstream of an turbomachinery aero-engine intake anti-icing air exhaust slot [PNR90396] p 52 N88-11081 [ASME PAPER 87-GT-2371 p32 A88-11127 Transmission efficiency in advanced aerospace Gas turbine exhaust systems - Design considerations powerplant [ASME PAPER 87-GT-2381 p 32 A88-11128 [PNR90391] p 53 NEB-111 33 Aerodynamics at low Reynolds numbers Re greater than The use of Kevlar on aero-engine fan containment 10 to the 4th and less than 10 to the 6th; Proceedings casings of the International Conference. London. England, Oct. [PNR90410] p 53 N88-111 34 15-18. 1986. Volumes 1, 2. a 3 p8 ABS-11176 A simple method for the prediction of separation bubble formation on aerofoils at low Reynolds number p8 AM-11179 On the determination of the 2-D characteristics of aerofoils at low Reynolds numbers p 10 A88-11192 Wind tunnel testing of small Scale pressure tapped model propellers p32 AM-11196 The calculation of flow abwt aerofoils at low Reynolds number with application to remotely piloted vehicles p 11 A88-11197 Prediction of a microlight biplane’s aerofoif performance using a computer model p 11 A88-11198 An experimental investigation of the aerodynamics of the hang glider pll Am-11200 The aerodynamics of gliding parachutes p 11 A88-11201 Preliminary measurements of the flight performance of an RPV compared with wind tunnel and CFD estimates p12 A88-11203 Aerodynamics of unmanned aircraft at full-scale in the RAE 24ft wind-tunnel p 12 A88-11204 The performance of model aircraft using flow invigorators. gliding in the critical range of Reynolds number p 12 A88-11206 Wind-tunnel lest results of Eppler 387 aerofoils and comparisons with flight test and computation p 12 A88-11208 Flight simulation p 39 A88-11470 The conflict resolution process for TCAS II and some simulation results p 21 A88-12474 Conference on Mechanical Behaviour of Superalloys, London, England, June 10, 11, 1986, Selected Papers p 42 A88-12626 Mechanical property requirements for aero gas turbine materials p 42 A88-12628 High-temperature sheet materials for gas turbine applications p 42 A88-12635 Optical systems for gas turbine engines p 49 A88-12657 An uncooled linescan thermal imager lor ground and airborne use p 49 A88-12840 A compact high performance thermal imager p50 A88-12843 Elastic buckling of internally pressurized cylinder-bulkhead combinations p 50 A88-12949 Dimsion in the wake of aircratt: An investigation of the effects of a ground plane on trailing vortiies. Literature SUNeY [ ICAERO-REP-86-04] p16 N88-10014 On the prospects for increasing dynamic lift [RAE-TM-AERO-2068] p17 N88-10018 Investigation of the suitability of the 8fi x 6ft transonic wind-tunnel for aeroacoustic resaarch on propellers [RAE-TM-AERO-2093] p39 N88-10041 Steering mechanism [EP-PATENT-0-181-700-A1] p 51 N88-10338 The fatigue properties of aerospace steels under constant amplitude and flight-by-fliht simulated loading [ BAE-MSM-R-GEN-05661 p51 NM-10377 Activities report of the Institute of Sound and Vibration Research [ETN-87-90685] pel NM-10589 Noise levels from propellerdriven aircraft measured at ground level and at 1.2 m above the ground [ NPL-AC-1101 p61 N88-10594 The deviation of light rays passing through a CUN~ windscreen [ BAE-MSC. 1151 p62 N88-10610 Decoupling and stabilization of speed and height in F4 Phantom aircraft using output feedback [ETN-87-90926] p 25 N88-10787

D-3 CONTRACT NUMBER INDEX

~ AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 223) February 1988

Typical Contract Number Index Listing

NAS3-23691 ...... P 54 N88-11160 NAS3-23697 ...... p60 N88-11165 NAGI-179 p 60 N88-11382 NAS3-23698 ...... p55 N88-11164 NAS3-23722 ...... p53 N88-11142 NAB-23925 ...... p55 N88- 11 171 NAS3-23927 ...... NEB-1 1172 NAS3-23939 ...... p56 N88-11175 NAS3-23940 ...... p55 NEB-11174 NAS3-23944 ...... p56 N88-11185 NAS3-24227 ...... p45 a88-1 1033 NAS3-24352 ...... p54 N88-11150 NAS3-24358 ...... p55 NEB-11163 NAS3-24381 ...... p34 N88-10791 P 34 N88-10792 NAS3-24844 ...... p44 A88-11000 NCC2-86 ...... p58 A88-12639 Listings in this index are arranged alpha- NCC3-27 ...... p56 N88-11182 numerically by contract number . Under each NGL-33-018-003 ...... p56 N88-11186 NGT-03-002-800 ...... p14 A88-12280 contract number. the accession numbers denoting NIVR-1823/01702-N ...... p51 N88-10386 documents that have been produced as a result of N00014-85-C-0657 ...... p4 A88-11003 research done under that contract are arranged in NR PROJECT 062-737 ...... p14 A88-12292 ascending order with the AlAA accession numbers NSF MSM-81-18429-AO3 ...... p14 A88-12292 NSF MSM-85-04579 ...... p29 A88-10996 appearing first . The accession number denotes the NSG-1419 ...... p10 A88-11190 number by which the citation is identified in the P 16 N88-10011 abstract section. Preceding the accession number N00014-82-C-0043 ...... p14 A88-12292 N00014-83-C-0430 ...... p14 A88-12282 is the page number on which the citation may be N00014-83-K-0239 ...... p10 A88-11190 found. P 11 A88-11202 N00014-84-K-0093 ...... p10 A88-11187 N00014-84-K-0232 ...... p9 A88-11182 AF-AFOSR-83-0071 ...... p 14 A88-12280 N00014-84-K-0470 ...... p33 N88-10033 AF-AFOSR-85-0357 ...... p 8 A88-11180 N00014-84-K-0500 ...... p9 A88-11184 BMVG-T/RF31/71455/71340 ...... p M N88-10231 N00014-85-C-0214 ...... p9 A88-11185 DA PROJ. 1L1-61102-AH-45 ...... p 53 N88-11135 N00014-85-K-0346 ...... p10 A88-11191 DE-AC04-76DP-00789 ...... p 17 N88-10767 N00014-86-K-0066 ...... p9 A88-11182 DE-AC05-840T-21400 ...... p 52 N88-11048 N00014-87-C-2032 ...... p62 N88-10608 DE-AC21-83MC-20334 ...... p 48 A88-11142 N00024-79-C-6043 ...... p6 A88-11087 DEN3-167 ...... p 46 A88-11083 N00024-85-C-6041 ...... p6 A88-11087 DFG-KO-786/2-3-DER ...... p 34 N88-10035 N60530-85-C-0091 ...... p24 N88-10027 ESoC-5762/83-D-IM(SC) ...... p 40 N88-10078 505.33-78 ...... p34 n88-10791 F30602-78-C-0027 ...... p 59 A88-12544 P34 N88-10792 F30602-80-C-0206 ...... p 59 A88-12544 505-60-11 ...... p52 N88-11088 F33615-84-C-2427 ...... p 35 N88-111 52 505-60 ...... p60 N88-11429 F33615-84-C-2454 ...... p 30 A88-11070 505-61-01-02 ...... p18 N88-10772 F33615-84-C-3626 ...... p 38 N88-10811 505-61-41-01 ...... p16 N88-10009 F3602-84-C-0094 ...... p 59 A88-12544 505-62-21 ...... p18 NEB-10779 F49620-78-C-0084 ...... p 14 A88-12284 505-63-01 ...... p43 N88-10938 F49620-79-C-0189 ...... p 49 A88-12294 505-63-11 ...... p56 NEB-11202 F49620-81-C-0088 ...... p 7 A88-11118 505-63-21-05 ...... p15 N88-10007 F49620-84-C-0065 ...... p 14 A88-12276 505-63-51 ...... p53 N88-11135 MOD-A938/1548 ...... p 51 N86-10377 505-66-11 ...... p60 NEB-I1435 NAGI-179 ...... p 60 NEB-I 1382 505-67 ...... p36 N88-10039 NAG1308 ...... p 16 NEB-1001 3 505-68-91-06 ...... p17 NEB-10771 NAGI-345 ...... p 15 A88-I 3096 P18 N88-10773 NAG1-58 ...... p 61 A88-12281 532-06-01-09 ...... p62 N88-11451 NAG1-710 ...... p 16 N88-I001 2 533-02-21 ...... p17 N88-10765 NAG3408 ...... p 29 A88- 10998 533-02-71 ...... p24 NEB-10026 NAG3-512 ...... p 43 NEB-11169 533-04-12 ...... p53 NEB-11140 NAG3-522 ...... p 54 N88-11161 535-03-01-01 ...... p16 N88-10013 NAG3-579 ...... p 54 NEB-1I 162 535-03-01 ...... p61 N88-10592 NASW-4005 ...... p 18 N88-10776 535-03 ...... p15 N88-10008 P 39 NEB-1081 8 992-21-01 ...... p18 NEB-10777 NASI-16535 ...... p 2 A88-10361 999-31-05 ...... p25 N88-10788 NASI-17296 ...... p 3 A88-10492 NASI-17335 ...... p 59 A88-12539 NASI-17635 ...... p 57 A88-10160 NASI-1 7670 ...... p 9 AM-11186 NASl -17683 ...... p 9 A88-11186 NASI -17989 ...... p 15 N88-10007 NASI-18235 ...... p 9 A88-11186 NASP-I 1454 ...... p 36 N88-10039 NASZ-11853 ...... p 28 N88-10030 NASP-12155 ...... p 49 A88-12838 NAS2-12425 ...... p 57 A88-10154 NAS3-20646 ...... p 7 A88-11126 NAS3-22110 ...... p 54 N88-11153 NAS3-22763 ...... p 51 N88-10339 NAS3-23288 ...... p 55 N88-11173 NAS3-23529 ...... p 54 N88-1 1143 NAS3-23687 ...... p 60 N88-11166 NAS3-23689 ...... p 53 NEB-11135

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 223) February 1988

Typical Report Number Index Listing

ASME PAPER 87-GT-155 ...... p 46 A88-11068 # BAE-MSM-R-GEN-0566 ...... p 51 N88-10377 # ASME PAPER 87-GT-158 A88-11070 # ASME PAPER 87-GT-159 A88-11071 # BMFT-FB-T-86-129 ...... p 42 N88-10159 # ASME PAPER 87-GT-160 ...... p 6 A88-11072 * # ASME PAPER 87-GT-165 ...... p A88-11076 # 30 BR100237 p 17 N88-10018 # ASME PAPER 87-GT-166 .. A88-11077 # ...... BR102327 ...... p 39 N88-10041 # ASME PAPER 87-GT-167 .. A88-11078 # BR99378 ...... p51 N88-10377 # NASA-CR-I81446 p 28 N88-10030 * ff ASME PAPER 87-GT-168 ...... p 30 A88-11079 * # ASME PAPER 87-GT-172 ...... p 46 A88-11082 # -r I 88701061 p 51 N88-10386 # ASME PAPER 87-GT-173 A88-11083 * # ...... E8701063 p 25 N88-10028 # ASME PAPER 87-GT-177 A88-11085 # ...... NUMBER SPONSORED ASME PAPER 87-GT-178 ...... p 41 A88-11086 # 88701065 ...... p51 NEB-10283 # FlFl p 15 N88-10006 # ASME PAPER 87-GT-179 ...... p 6 A88-11087 # ASME PAPER 87-GT-180 A88-11088 # CONF-870830-2-FP ...... p 17 N88-10767 # -- ASME PAPER 87-GT-183 A88-11090 # ASME PAPER 87-GT-186 ...... p 6 A88-11091 # CRINC-FRL-602-3 ...... P 16 N88-10013 # Listings in this index are arranged alpha- ASME PAPER 87-GT-187 ...... p 47 A88-11092 # ASME PAPER 87-GT-189 ...... p 31 A88-11094 # numerically by report number. The page number ASME PAPER 87-GT-18 ...... p 3 A88-10983 # DE87-014651 indicates the page on which the citation is located. ASME PAPER 87-GT-190 A88-11095 # ...... p 17 N88-10767 # ASME PAPER 87-GT-191 A88-11096 # The accession number denotes the number by DFVLR-FB-86-63 p 51 N88-10305 A88-11097 # ...... # which the citation is identified. An asterisk (*) ASME PAPER 87-GT-193 ASME PAPER 87-GT-196 ...... p 47 A88-11100 # p25 NEB-10029 # indicates that the item is a NASA report. A pound ASME PAPER 87-GT-196 ...... p 47 A88-11100 # sign (X) indicates that the item is available on ASME PAPER 87-GT-197 ...... p 7 A88-11101 # DFVLR-IB-222-86-A-07 ...... p 40 N88-10078 # microfiche. ASME PAPER 87-GT-198 ...... p 47 A88-11102 # ASME PAPER 87-GT-202 ...... p 7 A88-11106 # DFVLR-MITT-65-10 P 22 N88-10025 # ASME PAPER 87-GT-203 ...... p 31 A88-11107 # ...... DFVLR-MIlT-86-12 P 51 NEB-10278 # A-86264 ...... p 60 N88-11435 ' # ASME PAPER 87-GT-208 ...... p 47 A88-11109 # ...... DFVLR-MITT-86-25 p 1 N88-10003 # p 52 NEB-11089 * # ASME PAPER 87-GT-209 ...... p 31 A88-11110 # ...... _.__p 28 N88-10031 # p 52 N88-11088 ' # ASME PAPER 87-GT-211 ...... p 31 A88-11111 # ASME PAPER 87-GT-212 ...... p 47 A88-11112 # A-87323 ...... p 25 N88-10788 ' # DOT/FAA/CT-86/44 p 28 N88-10030 * # ASME PAPER 87-GT-215 ...... p 31 A88-11113 # ...... DOT/FAA/CT-87/10 p 19 N88-10021 * # ASME PAPER 87-GT-216 p 47 A88-11114 # ...... N88-11429 * # ...... A-88016 ...... p 60 ASME PAPER 87-GT-217 ...... p 58 A88-11115 # E-2727 p 53 N88-11140 # ASME PAPER 87-GT-219 ...... p 48 A88-11116 # ...... AD-A183536 p33 N88-10033 # E-3737 p 15 N88-10008 * # ...... ASME PAPER 87-GT-220 ...... p 48 A88-11117 # ...... ADA183663 p 62 NEB-10608 # E-3766 ...... ASME PAPER 87-GT-221 ...... p 7 A88-11118 # ...... AD-A183724 p 24 N88-10027 # E-3821 p 43 NEB-10938 * ...... ASME PAPER 87-GT-223 ...... p 48 A88-11120 # ...... # AD-A183784 p 42 N88-10192 # E-3822 p 18 N88-10779 # ...... ASME PAPER 87-GT-225 p 7 A88-11121 * # ...... p 61 N88-10588 # ...... ASME PAPER 87-GT-228 ...... p 32 A88-11122 # EP-PATENT-APPL-SN-85307273.4 p 51 N88-10338 ASME PAPER 87-GT-229 ...... p 32 A88-11123 # AFWAL-TR-87-2037 p 42 N88-10192 # ...... ASME PAPER 87-GT-232 ...... p 7 AN-11125 # EP-PATENTO-181-700-A1 N88-10338 ASME PAPER 87-GT-235 ...... p 7 A88-11126 ' # ...... P 51 p 38 N88-10806 # ASME PAPER 87-GT-237 ...... p 32 A88-11127 # A88-11128 # ESA-CR(P)-2408-VOL-2 ...... P 40 NEB-10078 AGARD-R-748 ...... p 53 N88-11139 # ASME PAPER 87-GT-238 P 32 ASME PAPER 87-GT-256 ...... p 8 A88-11136 # N88-10278 ASME PAPER 87-GT-257 ...... p 32 A88-11137 ' # P 51 AlAA PAPER 87-1843 p 43 A88-10497 # N88-10025 ...... ASME PAPER 87-GT-259 ...... p 32 A88-11139 # P 22 AIM PAPER 87-2492 p 3 A88-10498 * # ...... ASME PAPER 87-GT-25 ...... p 28 A88-10987 # AlAA PAPER 87-2762 ...... p 59 A88-12532 * # ETN-87-90370 ...... N88-10005 ASME PAPER 87-GT-265 ...... D 48 A88-11142 # P 15 AlAA PAPER 87-2776 p 59 A88-12539 * # N88-10035 ...... ASME PAPER 87-GT-26 ...... p 28 A88-10988 # P 34 AIM PAPER 87-2777 p 59 A88-12540 * # N88-10231 ...... ASME PAPER 87-GT-28 ...... p 3 A88-10989 # PS AIMPAPER 87-2790 p 59 # ETN-87-90396 ...... N88-10020 ...... A88-12544 ASME PAPER 87-GT-29 D 4 A88-10990 # P 19 A88-12558 # ...... ETN-87-90411 AlAA PAPER 87-2818 ...... p 59 ASME PAPER 87-GT-30 ...... p 4 A88-10991 # P 17 N88-10015 AlAA PAPER 87-2844 ...... p 26 A88-12569 # ETN-87-90417 N88-10037 ASME PAPER 87-GT-32 ...... p 44 A88-10992 # ...... P 34 AlAA PAPER 87-2854 p 26 A88-12574 # N88-10016 ...... ASME PAPER 87-GT-39 ...... p 29 A88-10993 # ETN-87-90437 ...... P 17 AlAA PAPER 87-2855 p 59 A88-12575 ETN-87-90442 N88-10463 ...... # ASME PAPER 87-GT-44 ...... p 29 A88-10996 # ...... P 57 ETN-87-90444 N88-10003 ASME PAPER 87-GT-46 ...... p 29 Aw-10998 * # ...... D1 AIAA-87-2657 p 61 N88-10592 # ETN-87-90447 p 28 N88-10031 ...... A88-10999 # ...... # AIAA-87-2719 p 15 N88-10008 * # ETN-87-90448 p 51 ...... A88-11000 * # ...... N88-10305 # AIAA-88-0131 p 18 N88-10779 * # ETN-87-90455 p57 ...... ASME PAPER 87-GT-49 ...... p 40 A88-11001 # ...... N88-10464 # ASME PAPER 87-GT-50 ...... p 41 A88-11002 # ETN-87-90545 ...... p 40 N88-10078 # ARW-498 p 56 N88-11198 # ...... ASME PAPER 87-GT-51 ...... p 4 A88-11003 # ETN-87-90561 ...... p 42 N88-10159 # AR-004-561 ...... p37 N88-10794 # ETN-87-90575 N88-11002 # ASME PAPER 87-GT-54 ...... p 4 A88-11005 # ...... ETN-87-90579 ASME PAPER 87-GT-63 ...... p 41 A88-11010 # ...... N88-10038 # ARL-STRUC-R-424 p 56 N88-Ill98 # ...... ASME PAPER 87-GT-71 ...... p 4 A88-11015 # N88-10029 # N88-10278 # ASME PAPER 87-GT-72 ...... p 45 A88-11016 # ARL-SYS-TM-95 ...... p 37 N88-10794 # N88-10025 # ASME PAPER 87-GT-73 ...... p 45 A88-11017 # ETN-87-90679 N88-10377 # ASME PAPER 87-GT-74 ...... p 45 A88-11018 # __ ASME PAPER 87-GT-102 ...... p 45 A88-11037 # ETN-87-90680 N88-10610 # ASME PAPER 87-GT-79 ...... p 45 A88-11019 # _. ASME PAPER 87-GT-107 p A88-11039 # ...... 30 ASME PAPER 87-GT-82 ...... p 4 A88-11022 # N88-10589 # ASME PAPER 87-GT-108 p 46 AM-11040 # ...... ASME PAPER 87-GT84 ...... p 4 A88-11024 # ETN-87-90689 ._ N88-10014 # ASME PAPER 87-GT-10 p 44 A88-10979 # ...... ASME PAPER 87-GT-87 ...... p 29 A88-11027 # ETN-87-90697 __ N88-10041 # ASME PAPER 87-GT-113 p 46 A88-11041 # ETN-87-90821 _. N88-10697 # ...... ASME PAPER 87-GT-89 .. A88-11028 # ASME PAPER 87-GT-115 p 5 A88-11043 # ETN-87-90823 p 15 N88-10006 # ...... ASME PAPER 87-GT-90 .. A88-11029 # ...... ASME PAPER 87-GT-116 p 5 AM-11044 # ETN-87-90824 p 51 ...... ASME PAPER 87-GT-94 ...... p 45 A88-11033 * # ...... N88-10386 # ASME PAPER 87-GT-118 ...... p 5 A88-11046 # N88-10028 ASME PAPER 87-GT-95 ...... p 45 A88-11034 # # ASME PAPER 87-GT-120 ...... p 30 m-11048 # ETN-87-90828 ASME PAPER 87-GT-96 ...... p 5 A88-11035 # ...... N88-10283 # ASME PAPER 87-GT-125 ...... p 41 A88-11052 # ETN-87-90924 .. N88-10795 # ASME PAPER 87-GT-127 ...... p 46 A88-11054 # ETN87-90926 .. N88-10787 # ASME PAPER 87-GT-128 ...... p 46 A88-11055 # AVSCOM-TR-87-C-29 ...... p 53 N88-11135'# ETN-87-90931 ...... p 61 N88-10594 ASME PAPER 87-GT-148 ...... p 30 A88-11066 # ETN-87-90955 ...... N88-10018 # ASME PAPER 87-GT-150 ...... p 5 A88-11067 # BAE-MSC.115 ...... p 62 N88-10610 # N88-11080 #

F- 1 -

ETN-87-90996 REPORTNUMBER INDEX

ETN-87-90996 ...... p 53 N88-11133 # NASA-CR-181446 ...... p 28 N88-10030 * # N88-11081 # NASA-CR-3983 ...... N88-10039 * # N88-11003 # NASA-CR-4101 ...... N88-10013 * # ETN-87-91003 ...... p 53 N88-11134 # N88-10789 # NASA-TM-100025 ...... P 25 N88-10788 * # ETN-87-91021 ...... N88-10595 # P 18 N88-10777 * # ETN-87-98641 ...... p 51 N88-10338 NASA-TM-100037 ...... p 60 NEB-11429 * # NASA-TM-100200 ...... p 15 N88-10008 * # H-1214 ...... N88-10765 # NASA-TM-100206 ...... p 61 N88-10592 * # H-1283 ...... N88-10026 * # NASA-TM-100212 ...... p 43 NEB-10938 * # H-1320 ...... p 36 N88-10039 * # NASA-TM-100213 ...... p 18 N88-10779 * # NASA-TM-100312 ...... p 53 NEB-11101 * # P 16 N88-10014 # NASA-TM-100492 ...... p 56 NEB-1 1202 * # NASA-TM-100512 ...... p 62 N88-11451 ' # INT-PATENT-CLASS-B62D-1/18 . p 51 N88-10338 NASA-TM-4015 ...... p 18 N88-10772 * # NASA-TM-4018 ...... p 18 N88-10773 * # ISBN-309-04114-7 _._ N88-10782 # N88-10026 * # N88-10806 # N88-11435 * # NASA-TM-88311 ...... p 52 NEB-11089 * # ISSN-0143-7143 ...... p 61 N88-10594 NASA-TM-88333 ...... p 52 NEB-1 1088 * # N88-10029 # NASA-TM-89642 ...... p 19 N88-10021 * # N88-10305 # ISSN-0171-1342 ...... p 57 N88-10464 # NASA-TP-2588 ...... p 17 N88-10765 * # ISSN-0176-7739 ...... p 1 N88-10003 # NASA-TP-2753 ...... p 17 N88-10771 * # ISSN-0176-7739 ...... p 28 N88-10031 # NASA-TP-2772 ...... __._p 16 N88-10009 * # ISSN-0178-8094 ...... p 19 NEB-10020 # P 16 N88-10014 # NASA-TT-20126 ...... p 39 N88-10818 * # P 42 N88-10159 # NASA-TT-20127 ...... p 18 N88-10776 * # P 36 N88-10793 # NBSIR-87-3633 ...... p 50 N88-10209 # JB-84 ...... p 19 N88-10020 # N88-10608 # K/SUB-85-03528/2 ...... p 52 N88-11048 # NLR-MPg6013-U ...... p 51 N88-10386 # KU-SFB-210/T/24 ...... p 15 N88-lo005 # NLR-MP-860200-U...... p 25 N88-10028 # NLR-MP-86038-U ...... N88-10283 # L-16223 ...... p 17 N88-10771 * # L-16283 ...... p 16 N88-10009 * # NLR-TR-86026-U ...... p 15 N88-10006 # L-16334 ...... N88-10772 * # L-16342 ...... p 18 N88-10773 * # NPL-AC110 ...... p 61 N88-10594

LC-87-7628 ...... P 19 N88-10782 # NTSB/AAB-87/03 ...... p 19 N88-10781 #

LFD-256 ...... P 50 N88-10231 ONERA, TP NO. 1987-54 ...... p 29 A88-11029 # MBB-LKE292/S/PUB/191 ...... p 36 N88-10038 # ONRL-7-023-C ...... p 16 N88-10010 #

NAL-TR-928 ...... P 36 N88-10793 # N88-10782 # NEB-10781 # N88-10788 * # N88-10777 * # PNR90378 ...... p 52 N88-11080 # N88-11429 * # PNRW391 ...... p 53 N88-11133 # NAS 1.15100200 ...... p 15 N88-10008 * # PNR90396 ...... p 52 N88-11081 # NAS 1.15100206 ... N88-10592 * # N88-11003 # NAS 1.15100212 ___ N88-10938 * # N88-11134 # NAS 1.15:100213 .._ N88-10779 * # N88-10789 # NAS 1.15:100312 ...... p 53 N88-11101 * # NAS 1.15100492 ...... p 56 N88-11202 * # N88-10018 # NAS 1.15100512 ...... p 62 N88-11451 ' # N88-10041 # NAS 1.15:4015 ...... p 18 N88-10772 * # NAS 1.15:4018 ...... p 18 N88-10773 * # REPT-12-66 ...... p 50 N88-10231 NAS 1.1586725 N88-10026 * # REPT-3-5211O-6R-128 ._._._p24 N88-10027 # N88-11435 * # NAS 1.1 588311 ...... p 52 NEB-11089 * # SAE PAPER 861661 ...... P 57 A88-10154 * NAS 1.1 5:88333 ...... p 52 N88-11088 * # SAE PAPER 861692 ...... p 43 A88-10170 NAS 1.1589642 ...... p 19 N88-10021 # SAE PAPER 861730 ...... p 58 A88-10162 NAS 1.26375046 ...... p 51 N88-10339 * # A88-10163 NAS 1.26:178288 ...... p 15 N88-10007 * # A88-10164 NAS 1.26:179632 ...... N88-10791 * # A88-10156 N88-10792 * # A88-10158 N88-11135 * # SAE PAPER 861771 A88-10159 * N88-11186 * # SAE PAPER 861772 ...... P 57 A88-10160 * N88-10011 * # SAE PAPER 861804 ...... P 36 A88-10167 N88-11382 * # SAE PAPER 871020 ...... P 15 A88-13096 * N88-10012 # N88-10030 # SAND-86-2875GFP ...... p 17 N88-10767 # N88-10039 * # NAS 1.26:4101 NEB-10013 * # SPIE-694 ...... p 26 A88-12728 NAS 1,552405 N88-11140 * # NAS 1.60:2588 N88-10765 * # P 53 N88-11133 # N88-10771 * # N88-10009 * # TIA165189 ...... p 53 N88-11133 # N88-10818 * # N88-10776 * # TRB/TRR-1094 ...... p 19 N88-10782 #

NASA-CP-2405 .___. N88-11140 * # USAAVSCOM-TR-87-A-11 ...... p 18 N88-10777 * #

NASA-CR-175046 ...... p 51 N88-10339 * # USAFOEHL-87-082EH0186FNA .. p 61 N88-10588 # NASA-CR-178288 ...... p 15 N88-1MM7 * # NASA-CR-179632 ...... P 34 N88-10791 * # NASA-CR-179633 ...... p 34 N88-10792 # NASA-CR-180804 ...... p 53 N88-11135 * # NASA-CR-181416 ...... N88-11186 * # NASA-CR-181434 ...... N88-10011 * # NASA-CR-181440 ...... p 60 N88-11382 * # NASA-CR-181441 ...... p 16 N88-10012 * #

F-2 ACCESSION NUMBER INDEX

February 1988 AERONAUTICAL ENGINEERING /A Continuing Sibliography (Supplement 223)

1 Typical Accession Number Index Listing A88-11055 X p 46 A88-11208 p 12 A88-13083 # p 50 AM-11066 # p30 A88-11210 p 13 A88-13084 # p 50 A88-11280 p 13 A88-11067 # p5 A88-13085 # p24 A88-11394 p 58 A88-11068 # p46 A88-13086 # p40 I A88-11439 X p48 A88-13087 # p21 N88-10008 * 4 P 15 A88-11070 # p30 A88-11470 p 39 A88-11071 X p5 A88-13088 W p22 A88-11585 # p 48 A88-13090 # p 22 A88-11072 * # p 6 A88-11672 p 1 A88-11076 X p30 A88-13093 X p22 A88-11825 X p48 A88-13094 # p 22 A88-11077 # p6 A88-11923 # p 33 A88-11078 # p 30 A88-13095 .X p 33 A88-11976 # p33 A88-13096 p 15 A88-11079 * # p 30 A88-12056 p 13 A88-13109 p 60 A88-11082 # p 46 A88-12059 p 13 NUMBER SPONSORED MICROFICHE NUMBER A88-11083 * # p 46 A88-12065 p 13 Fl A88-11085 # p31 N88-10003 W p 1 A88-12071 p 13 N88-10005 # p15 A88-11086 # p41 A88-12073 p 13 A88-11087 X p6 N88-10008 X p15 A88-12074 p 14 NEB-10007 'X p 15 A88-11088 # p 6 A88-12075 p 14 Listings is this index are arranged alpha-numeri- A88-11090 # p 31 N88-10008 '# p 15 A88-12202 p62 N88-10009 'I p 16 cally by accession number. The page number A88-11091 X p 6 A88-12276 X p14 A88-11092 # p47 N88-10010 # p16 listed to the right indicates the page on which the A88-12280 'X p 14 N88-10011 'I p 16 A88-11094 # 031 A88-12281 'X p61 citation is located. An asterisk (*) indicates that A88-11095 # p41 N88-10012 *# p 16 A88-12282 W p 14 N88-10013 'X p 16 the item is a NASA report. A pound sign (#) indi- A88-11096 # p6 A88-12284 # p 14 A88-11097 # p 7 N88-10014 X p 16 cates that the item is available on microfiche. A88.12292 # p14 N88-10015 X p17 A88-11100 # p47 A88-12293 # p14 A88.11101 X p7 N88-10016 X p17 A88-12294 X p49 N88-10018 # p17 A88-11102 # p47 A88-12412 p 24 A88-11106 X p 7 N88-10020 X p 19 A88-10687 # P21 A88-12413 p 24 A88-10017 p43 A88-11107 # p31 N88-10021 'X p 19 A88-10688 # P21 A88-12414 p 41 A88-10031 * p40 A88-11109 X p47 N88-10025 # p22 A88-10726 P 44 A88-12415 p 41 A88-10044 p39 A88-11110 X p31 N88-10026 * # p 24 A88-10728 P 21 A88-12474 p 21 A88-11111 # p31 N88-10027 # 024 A88-10047 p61 A88-10871 p A88-12483 p 14 23 A88-11112 # p47 N88-10028 # p25 A88-10048 pEl A88-10872 p 40 A88-12487 p 36 A88-11113 # p31 N88-10029 X p25 A88-10049 p23 A88-10873 p A88-12488 p 39 23 A88-11114 # p47 N88-10030 'X p 28 A88-10093 # p2 A88-10874 P 21 A88-12526 p 58 A88-11115 # p58 N88-10031 # p28 A88-10094 X p2 A88-10875 p A88-12532 * # p 59 23 A88-11116 # p48 N88-10032 p33 A88-10095 X p 35 A88-10876 P23 A88-12539 'X p 59 . A88-11117 X p48 N88-10033 X p33 A88-10154 p 57 A88-10877 p 1 A88-12540 * # p 59 A88-11118 # p7 N88-10035 # p34 A88-10156 p 39 A88-10929 P 58 A88-12544 X p59 A88-11120 # p48 N88-10037 R p34 A88-10158 p 57 A88-10965 ' p 58 A88.12558 # p59 A88-11121 '# p7 N88-10038 # p36 A88-10159 * p 35 A88-10969 * W p 44 A88-12569 # p26 A88-11122 # p32 N88-10039 * W p 36 A88-10160 * p 57 A88-10979 X p44 A88-12574 # p26 A88-11123 # p32 N88-10041 W p39 A88-10162 p 58 A88-10983 X p3 A88-12575 # p59 A88-11125 # p7 N88-10078 W p40 A88-10163 p 35 A88-10987 # P 28 A88-12826 p 42 A88-11126 * # p 7 N88-10159 # p42 A88-10164 p35 A88-10988 # p 28 A88-12628 p 42 A88-11127 # p32 N88-10192 # p42 A88-10167 p 36 A88-10989 # P3 A88-12632 p 42 A88-11128 # p32 N88-10209 X p50 A88-10170 p 43 A88-10990 # P 4 A88-12635 p 42 A88-11136 X p8 N88-10231 p 50 A88-10180 p40 A88-10991 X p4 A88-12639 * p 58 A88-11137 '# p32 N88-10278 X p51 A88-10264 p 2 A88-10992 X p44 A88-12644 p 19 A88-11139 # p32 NM-10283 # p51 A88-10300 p2 A88-10993 # p29 A88-12645 p24 A88-11142 # p48 N88-10305 W p51 A88-10354 '# p 2 A88-12646 p36 D 51 A88-10996 # P29 A88-11148 p41 NRB-10338..~~ A88-10355 W P 2 A88-10998 X P 29 A88-12655 p 26 ' A88-11176 p8 N88-10339 ' # p 51 A88-10356 X p2 A88-10999 # p 29 A88-12657 p 49 A88-11177 p8 N88-10377 # p51 A88-10357 W p2 A88-11000 '# p44 A88712697 p 49 A88-11178 p8 N88-10386 # p51 A88-10358 * X p 28 A88-11001 # 040 A88-12725 * p 49 A88-11179 p8 N88.10463 W p57 A88-10359 # p2 A88-11002 W p41 A88-12728 p26 A88-11180 p8 N88-10464 X p57 A88-10361 'R p 2 A88-11003 W P4 A88-12731 p 26 A88-11181 * p9 N88-10588 # p61 A88-10362 C p28 A88-11005 # P4 AM-12732 p49 A88-11182 p9 N88-10589 X p81 A88-10370 I p 1 A88-11010 X p41 A88-12733 p 21 A88-11183 p9 N88-10592 'X p 61 A88-10371 # p28 A88-11015 X P4 A88-12736 p 27 A88-11184 p9 N88-10594 p61 A88-10436 p25 A88-11016 # P45 A88-12737 p 21 A88-11185 p 9 N88-10595 # p62 A88-10437 p 19 A88-11017 X p45 A88-12740 p 27 A88-11186 * p9 N88-10608 # p62 A88-10492 * p3 A88-11018 # p45 A88-12741 p 27 A88-11187 p10 N88-10610 # p62 A88-10497 X p43 A88-11019 # p45 A88-12742 p 27 A88-11188 p10 N88-10697 # p62 A88-10498 'X p 3 A88-11022 # p4 A88-12748 p 27 A88-11189 p 10 N88-10765 '# p 17 A88-10582 # p3 A88-11024 # p4 A88-12749 p 27 Mu)-11190 * p10 N88-10767 # p17 A88-10570 # p44 A88-11027 # p29 A88-12750 p27 A88-11191 p10 N88-10771 'I P 17 A88-10628 p44 A88-11028 X p29 A88-12751 p 28 A88-11192 p10 N88-10772 '# p 18 A88-10655 p23 A88-11029 # p29 A88-12788 p42 A88-11193 p 11 N88-10773 * # p 18 A88-10656 p23 A88-11033 ' W p 45 A88-12836 p 33 A88-11194 * p 11 N88-10776 '# p 18 A88-10657 pl A88-11034 X p45 A88-12838 * p 49 A88-11195 p24 N88-10777 'X p 18 A88-10658 p19 A88-11035 X p5 A88-12840 p 49 A88-11196 p32 N88-10779 'W p 18 A88-10659 p23 A88-11037 # p45 A88-12843 p50 A88-11197 pll N88-10781 # p 19 A88-10660 p3 A88-11039 X p30 A88-12903 p50 A88-11198 pll N88-10782 W p 19 A88-10675 p23 A88-11040 X p46 A8812849 p50 A88-11200 pll N88-10784 p22 A88-10676 p20 A88-11041 X p46 A88-13076 # p33 A88-11201 p 11 N88-10787 X p25 A88-10677 # p20 A88-11043 # P5 ASS-13077 # p 14 A88-11202 pll N88-10788 # p 25 A88-10678 # p20 A88-11044 # p5 A88-13078 # p 15 N88-10789 # p34 A88-10679 # p 26 A88-11203 p12 A88-11046 # p5 A88-13079 # pl5 N88-10791 * # p 34 Mu)-10880 # p20 A88-11204 p12 Mu)-11048 # p30 A88-13080 # P36 N88-10792 # p 34 A88-10682 # p20 A88-11205 p12 Mu)-11052 # p41 A88-11206 p12 A88-13081 # p24 N88-10793 t p 36 Am-10884 # p20 N88-10794 # p 37 A88-10885 # p26 Mu)-11054 # p46 A88-11207 p12 A88-13082 # pl G-1 ACCESSION NUMBER INDEX N88-10795

N88-10795 # P37 N88-10798 * # P 37 N88-10799 # P37 N88-10800 # p37 NEB-10801 * # p 37 N88-10803 # P38 N88-10804 # p 38 N88-10805 * # p 38 N88-10806 # P 38 N88-10807 # p 38 N88-10808 # p38 N88-10810 # P22 N88-10811 # P38 N88-10812 # P25 N88-10815 # P22 N88-10818 * # P 39 N88-10938 '# P 43 N88-10986 # p 1 N88-10992 # p34 N88-10993 # p35 N88-11002 # p 52 N88-11003 # p 52 N88-11048 # p 52 N88-11080 # P 52 N88-11081 # p 52 N88-11088 '# p 52 NEB-1 1089 * # P 52 N88-11101 '# P53 N88-11133 # P53 N88-11134 # P 53 N88-11135 '# P53 N88-11139 # P 53 N88-11140 * # P 53 NEB-1 1142 ' # P 53 N88-11143 # P 54 N88-11146 '# P 54 N88-11150 '# P 54 N88-11152'# P35 N88-11153'# P54 N88-11154 '# P54 N88-11160 '# P 54 N88-11161 '#' P54 N88-11162'# P54 N88-11163 '# P55 N88-11164 '# P 55 N88-11165 '# p60 N88-11166 '# P60 N88-11169*# P43 N88-11170 '# P 55 N88-11171 '# P55 N88-11172'# P55 N88-11173 '# P55 N88-11174 '# P55 N88-11175 '# P 56 N88-11179 '# p43 N88-11182 '# P 56 N88-11183 '# P 56 N88-11185 * # P 56 N88-11188'# P56 N88-11198 # p56 N88-11202 '# P 56 N88-11382 * # P 60 N88-11429 * # P 60 N88-11435 '# p60 N88-11451 * # P 62

6-2 AVAILABILITY OF CITED PUBLICATIONS

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Avai I: Fachinformationszentrum, Karlsruhe. Sold by the Fachinformationszentrum Energie, Physik, Mathematik GMBH, Eggenstein Leopoldshafen, Federal Republic of Germany, at the price shown in deutschmarks (DM).

Avail: HMSO. Publications of Her Majesty’s Stationery Office are sold in the U.S. by Pendragon House, Inc. (PHI), Redwood City, California. The U.S. price (including a service and mailing charge) is given, or a conversion table may be obtained from PHI.

Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purch- ased from the National Aeronautics and Space Administration, Public Documents Room (Room 126), 600 Independence Ave., S.W., Washington, D.C. 20546, or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory.

Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm. All requests should cite the author and the Order Number as they appear in the citation.

Avail: US Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks, US. Patent and Trademark Office, at the standard price of $1.50 each, postage free. (See discussion of NASA patents and patent applications below.)

Avail: (US Sales Only). These foreign documents are available to users within the United States from the National Technical Information Service (NTIS). They are available to users outside the United States through the International Nuclear Information Service (INIS) representative in their country, or by applying directly to the issuing organization.

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Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document. PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC: NASA and NASA-sponsored documents and a large number of aerospace publications are available to the public for reference purposes at the library maintained by the American Institute of Aeronautics and Astronautics, Technical Information Service, 555 West 57th Street, 12th Floor, New York, New York 10019. EUROPEAN: An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England for public access. The British Library Lending Division also has available many of the non-NASA publications cited in STAR. European requesters may purchase facsimile copy or microfiche of NASA and NASA-sponsored documents, those identified by both the symbols # and from ESA - Information Retrieval Service European Space Agency, 8-10 rue Mario-Nikis, 75738 CEDEX 15, France. FEDERAL DEPOSITORY LIBRARY PROGRAM In order to provide the general public with greater access to U.S. Government publications, Congress established the Federal Depository Library Program under the Government Printing Office (GPO), with 50 regional depositories responsible for permanent retention of material, inter-library loan, and reference services. At least one copy of nearly every NASA and NASA-sponsored publication, either in printed or microfiche format, is received and retained by the 50 regional depositories. A list of the regional GPO libraries, arranged alphabetically by state, appears on the inside back cover. These libraries are not sales outlets. A local library can contact a Regional Depository to help locate specific reports, or direct contact may be made by an individual.

STANDING ORDER SUBSCRIPTIONS NASA SP-7037 and its supplements are available from the National Technical Information Service (NTIS) on standing order subscription as PB 88-914100 at the price of $8.50 domestic and $17.00 foreign. The price of the annual index is $14.50. Standing order subscriptions do not terminate at the end of a year, as do regular subscriptions, but continue indefinitely unless specifically terminated by the subscriber. ADDRESSES OF ORGANIZATIONS

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Superintendent of Documents Department of Energy U.S. Government Printing Office Technical Information Center Washington, D.C. 20402 PO. Box 62 Oak Ridge, Tennessee 37830 University Microfilms ESA-Information Retrieval Service A Xerox Company ESRlN 300 North Zeeb Road Via Galileo Galilei Ann Arbor, Michigan 48106 00044 Frascati (Rome) Italy University Microfilms, Ltd. ESDU International, Ltd. Tylers Green 1495 Chain Bridge Road London, England McLean, Virginia 22101 U.S. Geological Survey Library ESDU International, Ltd. National Center - MS 950 251 -259 Regent Street 12201 Sunrise Valley Drive London, W1 R 7AD, England Reston, Virginia 22092

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NASAScientificand Technical Information U.S. Geological Survey Library Facility Box 25046 PO. Box 8757 Denver Federal Center, MS914 B.W.I. Airport, Maryland 21240 Denver, Colorado 80225 NTlS PRICE SCHEDULES (Effective January 1, 1988)

Schedule A STANDARD PRICE DOCUMENTS AND MICROFICHE

NORTH PRICE PAGE AMERICAN FOREIGN CODE RANGE PRICE PRICE A01 Microfiche $6.95 $13.90 A02 001 -010 9.95 19.90 A03 011 -050 12.95 25.90 A04-AO5 051-100 14.95 29.90 A06-AO9 101-200 19.95 39.90 AlO-Al3 201 -300 25.95 51.90 A14-Al7 301 -400 32.95 65.90 A18-A21 401 -500 38.95 77.90 A22-A25 501 -600 44.95 89.90 A99 601 -UP NO1 49.50 89.90 NO2 48.00 80.00

Schedule E EXCEPTION PRICE DOCUMENTS AND MICROFICHE

NORTH PRICE AMERICAN FOREIGN CODE PRICE PRICE E01 $ 8.50 17.00 E02 11.00 22.00 E03 12.00 24.00 E04 14.50 29.00 E05 16.50 33.00 E06 19.00 38.00 E07 21.50 43.00 E08 24.00 48.00 EO9 26.50 53.00 E10 29.00 58.00 Ell 31.50 63.00 E12 34.00 68.00 E13 36.50 73.00 E14 39.50 79.00 E15 43.00 86.00 E16 47.00 94.00 E17 51.00 102.00 E18 55.00 110.00 E19 61.00 122.00 E20 71.00 142.00 E99

'Contact NTlS for price quote.

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 (223) 5. Report Date February, 1988

~ 6. Performing Organization Code

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

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract This bibliography lists 423 reports, articles and other documents introduced into the NASA scientific and technical information system in January, 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 126 A07/HC