Aeronautical Engineering

NASA SP-7037 (298) December 1993

AERONAUTICAL ENGINEERING

(NASA-SP-7037(298)) AERONAUTICAL N94-23711 ENGINEERING: A CONTINUING BILLIOGRAPHY WITH INDEXES (SUPPLEMENT 298) (NASA) 102 p Unclas

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AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

National Aeronautics and Space Administration Scientific and Technical Information Program Washington, DC 1993 This publication was prepared by the NASA Center for AeroSpace Information, 800 Elkridge Landing Road, Linthicum Heights, MD 21090-2934, (301) 621-0390. INTRODUCTION

This issue of Aeronautical Engineering — A Continuing Bibliography with Indexes (NASA SP-7037) lists 328 reports, journal articles, and other documents recently announced in the NASA STI Database.

Accession numbers cited in this issue include: Scientific and Technical Aerospace Reports (STAR) (N-10000 Series) None for this issue International Aerospace Abstracts (IAA) (A-10000 Series) A93-52651 — A93-54347

The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles.

Each entry in the publication consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged by the first nine SLAflspecific categories and the remaining STAR major categories. This arrangement offers the user the most advanta- geous breakdown for individual objectives. The citations include the original accession numbers from the respective announcement journals.

Seven indexes—subject, personal author, corporate source, foreign technology, contract number, report number, and accession number—are included.

A cumulative index for 1993 will be published in early 1994.

Information on availability of documents listed, addresses of organizations, and CASI price sched- ules are located at the back of this issue. Page Intentionally Left Blank TABLE OF CONTENTS

Category 01 Aeronautics 1175

Category 02 Aerodynamics 1175 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 1189 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 1190 Includes digital and voice communication with aircraft; air navigation systems (satellite and ground based); and air traffic control.

Category 05 Aircraft Design, Testing and Performance 1191 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 1192 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 1193 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 1205 Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 1207 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 1210 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; space communications, spacecraft communications, command and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft propulsion and power.

Category 11 Chemistry and Materials 1211 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellents and fuels; and materials processing.

Category 12 Engineering 1214 Includes engineering (general); communications and radar; electronics and electrical engineering; fluid mechanics and heat transfer; instrumentation and photography; lasers and masers; mechanical engineering; quality assurance and reliability; and structural mechanics.

Pftft i'V, mTENTKWAlLY -UtANK Category 13 Geosciences 1222 Includes geosciences (general); earth resources and remote sensing; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.

Cateogory14 Life Sciences N.A. Includes life sciences (general); aerospace medicine; behavioral sciences; man/ system technology and life support; and space biology.

Category 15 Mathematical and Computer Sciences 1222 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 1225 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics.

Category 17 Social Sciences 1226 Includes social sciences (general); administration and management; documentation and information science; economics and cost anaylsis; 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 1227

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 Appendix APP-1

VI TYPICAL REPORT CITATION AND ABSTRACT

NASA SPONSORED JON MICROFICHE U ACCESSION NUMBER —» N93-10098*# Old Dominion Univ., Norfolk, VA. Dept. of Mechani- «- CORPORATE SOURCE cal Engineering and Mechanics. TITLE -> NAVIER-STOKES DYNAMICS AND AEROELASTIC COMPUTA- TIONS FOR VORTICAL FLOWS, BUFFET AND AEROELASTIC APPLICATIONS Progress Report, 1 Oct. 1991 - 30 Sept. 1992 AUTHOR -» OSAMA A. KANDIL Sep. 1992 38 p <- PUBLICATION DATE CONTRACT NUMBER -> (Contract NAG 1-648) REPORT NUMBER -» (NASA-CR-190692; NAS 1.26:190692) Avail: CASI HC A03/MF <- AVAILABILITY AND A01 PRICE CODE The accomplishments achieved during the period include conference and proceedings publications, journal papers, and abstracts which are either published, accepted for publication or under review. Conference presentations and NASA highlight publications are also included. Two of the conference proceedings publications are attached along with a Ph.D. dissertation abstract and table of contents. In the first publication, computational simulation of three- dimensional flows around a delta wing undergoing rock and roll- divergence motions is presented. In the second publication, the unsteady Euler equations and the Euler equations of rigid body motion, both written in the moving frame of reference, are sequetially solved to simulate the limit-cycle rock motion of slender delta wings. In the dissertation abstract, unsteady flows around rigid or flexible delta wings with and without oscillating leading-edge flaps are considered. L.R.R.

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED

ACCESSION NUMBER -» A93-12007* National Aeronautics and Space Administration, f- CORPORATE SOURCE Langley Research Center, Hampton, VA. TITLE -4 NUMERICAL SIMULATIONS OF HIGH-SPEED FLOWS ABOUT WAVERIDERS WITH SHARP LEADING EDGES AUTHORS -> KEVIN D. JONES and F. C. DOUGHERTY (Colorado Univ., AUTHORS' AFFILIATION JOURNAL TITLE — > Boulder) Journal of Spacecraft and Rockets (ISSN 0022-4650) vol. PUBLICATION DATE — > 29, no. 5 Sept.-Oct. 1992 p. 661-667. Research supported by Univ. of Colorado and DLR refs CONTRACT NUMBER -> (Contract NAG 1-880) Copyright A procedure is developed for the numerical simulation of stagnation-free inviscid supersonic and hypersonic flows about waveriders with sharp leading edges. The numerical approach involves the development of a specialized grid generator (named HYGRID), an algebraic solution-adaptive grid scheme, and a modified flow solving method. A comparison of the results obtained for several waverider geometries with exact solutions, other numerical solutions, and experimental results demonstrated the ability of the new procedure to produce stagnation-free Euler solutions about sharp-edged configurations and to describe the physics of the flow in these regions. I.S. AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 298) December 1993

01 London Royal Aeronautical Society 1992 51 p. For individual items see A93-54288 to A93-54295 AERONAUTICS (GENERAL) (ISBN 1-85768-045-6) Copyright Consideration is given to helicopter operations in cold climates, operating helicopters in a demanding environment (mountain flying and high evaluations), Royal Navy helicopter operations in the maritime environment, environmental effects on helicopter operations during desert shield and desert storm, and the T-700 A93-52690# helicopter engine. Also discussed are night operations of Royal USAF IN-FLIGHT SIMULATION - A COST-EFFECTIVE Air Force support helicopters, avionic systems in support of covert OPERATING APPROACH helicopter operations, and the LONGBOW force multiplier for STEVEN R. MARKMAN (USAF, Wright Lab., Wright-Patterson AFB, continuous operations. AIAA OH) In AIAA Flight Simulation Technologies Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington A93-54295 American Institute of Aeronautics and Astronautics 1993 p. LONGBOW - FORCE MULTIPLIER FOR CONTINUOUS 316-319. OPERATIONS (AIAA PAPER 93-3604) DAVID L LUNDQUIST (Martin Marietta Electronic Systems, A major factor in the success of the U.S. Air Force's in-flight Orlando, FL) In Helicopter operations in severe environments; simulation program has been keeping operating costs low while Proceedings of the Conference, London, United Kingdom, June 4, retaining needed skills, capabilities, and operational flexibility. A 1992 London Royal Aeronautical Society 1992 p. 8.1-8.5. suitable management approach and operating concept are critical Copyright to the success of this program. The Air Force has developed, LONGBOW provides enhanced warfighting capability for Apache owned, and used in-flight simulators since the early 1950s. The enabling it to conduct combat operations under conditions including current aircraft, the NT-33A and the NC-131H, are operated as adverse weather and limited visibility. LONGBOW integrates a Fire national resources and are available for use throughout the U.S. Control Radar and RF fire-and-forget HELLFIRE missile onto the Government, U.S. industry, and foreign allied governments. The Apache attack helicopter. The system operates in terrain profile, nature of the program often requires quick response and the ability ground targeting and air targeting modes. LONGBOW delivers a to adapt to the needs of the user. The current operating concept ten-fold increase in combat effectiveness compared to AH64-A is Air Force management and ownership of the aircraft, contractor Apache in clear weather and an even greater improvement in operation by a highly specialized contractor, and a tasking type adverse environments. As an improvement to a fielded, contract on which to employ the contractor. This operating combat-proven weapon system, LONGBOW is an efficient means approach has proven to satisfy all of these requirements. This to provide a force multiplier in an era of diminishing resources. approach has evolved over the history of the program to make the aircraft available to users and to insure valuable and cost effective results. 02

A93-54104 AERODYNAMICS VARIOUS APPLICATIONS OF ROBOTS IN AIRCRAFT ENGINE OVERHAUL O. SASAHARA (Japan Airlines Co. Ltd., Engine Maintenance Includes aerodynamics of bodies, combinations, wings, rotors, and Center, Tokyo) In ISABE - International Symposium on Air control surfaces; and internal flow in ducts and turbomachinery. Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington American Institute of Aeronautics and Astronautics 1993 p. 1323-1326. A93-52770* National Aeronautics and Space Administration. (ISABE 93-7129) Copyright Langley Research Center, Hampton, VA. Japan Airlines (JAL) is developing various automated, UPWIND-BIASED, POINT-IMPLICIT RELAXATION computer-linked maintenance systems for aircraft engine overhaul. STRATEGIES FOR HYPERSONIC FLOWFIELD SIMULATIONS The automation results in (1) Better Quality - Standardizing ON SUPERCOMPUTERS processes and eliminating defects. (2) Labor Savings - Eliminating PETER A. GNOFFO (NASA, Langley Research Center, Hampton, monotonous processes. It is also neutralizing Japan's high labor VA) Apr. 1989 10 p. International Conference on cost. (3) Better Working Environment - Eliminating the hazardous Supercomputing, 4th and World Supercomputer Exhibition, 3rd, environment caused by chemicals, debris and noise. This paper Santa Clara, CA, Apr. 30-May 5, 1989, Paper refs reports the status of robot applications in JAL engine Copyright maintenance. An upwind-biased, point-implicit relaxation algorithm for obtaining the numerical solution to the governing equations for three-dimensional, viscous, hypersonic flows in chemical and A93-54287 thermal nonequilibrium is described. The algorithm is derived using HELICOPTER OPERATIONS IN SEVERE ENVIRONMENTS; a finite-volume formulation in which the inviscid components of PROCEEDINGS OF THE CONFERENCE, LONDON, UNITED flux across cell walls are described with Roe's averaging and KINGDOM, JUNE 4, 1992 Harten's entropy fix with second-order corrections based on Yee's

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Symmetric Total Variation Diminishing scheme. The relaxation HOSHIO TSUJITA and SHIMPEI MIZUKI Japan Society of strategy is well suited for computers employing either vector or Mechanical Engineers, Transactions B (ISSN 0387-5016) vol. parallel architectures, and the relation between computer 59, no. 559 March 1993 p. 782-789. In JAPANESE refs architecture and algorithm is emphasized. It is also well suited to Copyright the numerical solution of the governing equations on unstructured Three-dimensional incompressible turbulent flow within a linear grids. Because of the point-implicit relaxation strategy, the algorithm turbine cascade with tip clearance is analyzed numerically. The remains stable at large Courant numbers without the necessity of governing equations involving the standard k-epsilon model are solving large, block tri-diagonal systems. A single relaxation step solved in the physical component tensor form with a boundary depends only on information from nearest neighbors. Predictions fitted coordinate system using coarse grids. In the analysis, the for pressure distributions, surface heating, and aerodynamic blade tip geometry is treated accurately in order to predict the coefficients compare well with experimental data for Mach 10 flow detailed flow phenomena through the tip clearance in the case of over a blunt body. Predictions for the hypersonic flow of air in a blade with large thickness. The results are also compared with chemical and thermal nonequilibrium (velocity = 8917 m/s, altitude the experimental data. Although the number of grids employed in = 78 km.) over the Aeroassist Flight Experiment (AFE) the present study is rather coarse, the computed results show configuration obtained on a multi-domain grid are discussed. good agreement with the measured ones. Moreover, the results exhibit the locus of minimum pressure at the rear part of the A93-52946 pressure side at the blade tip. Author (revised) NON-SELF-SIMILARITY OF A BOUNDARY LAYER FLOW OF A HIGH-TEMPERATURE GAS IN A LAVAL NOZZLE A93-53193 [NEAVTOMODEL'NOST TECHENIYA V POGRANICHNOM PRESSURE DISTRIBUTION MEASUREMENT AROUND SLOE VYSOKOTEMPERATURNOGO GAZA V SOPLE HYPERSONIC DELTA WINGED SEMICONE - MEASUREMENT LAVALYA] BY MEANS OF MAGNET TAPE A. V. DMITRENKO Aviatsionnaya Tekhnika (ISSN 0579-2975) MASATOMI NISHIO and MUTSUO KOTAKE Japan Society of no. 1 1993 p. 38-42. In RUSSIAN refs Mechanical Engineers, Transactions B (ISSN 0387-5016) vol. Copyright 59, no. 559 March 1993 p. 790-794. In JAPANESE refs Results of calculations of boundary layer flows of a Copyright high-temperature gas in a Laval nozzle are reported. It is shown, This paper describes measurements of pressure distribution in particular, that non-self-similarity in the boundary layer of the around a semicone body with a wing traveling at the hypersonic nozzle is determined mainly by the combined effect of the Mach speed of Mach number 10. The semiapex angles of the delta number and the temperature factor. The calculated velocity and wing and semicone are 30 and 15 deg, respectively. The temperature profiles and turbulent characteristics are in satisfactory measurements are carried out under the condition that the angles agreement with the classical experimental data over a wide range of attack are 0, 10, and 20 deg. In this study, the pressure of Mach numbers and temperature factors. AIAA distribution measuring method using magnetic tape has been improved to be suitable for measuring pressure distribution around A93-52958 hypersonic vehicles. The pressure distributions are measured by CALCULATION OF THE POSITION OF THE FLOW utilizing the improved method. Author (revised) SEPARATION LINE IN AN ANALOG MODEL OF FLOW PAST A BODY [RASCHET POLOZHENIYA LINII OTRYVA POTOKA V A93-53200* National Aeronautics and Space Administration. ANALOGOVOJ MODEL! OBTEKANIYA TELA] Ames Research Center, Moffett Field, CA. A. S. BUT, L. N. MAKAROV, and I. N. RODIONOV Aviatsionnaya NUMERICAL STUDY OF A DELTA PLANFORM WITH Tekhnika (ISSN 0579-2975) no. 1 1993 p. 87-89. In MULTIPLE JETS IN GROUND EFFECT RUSSIAN refs K. CHAWLA, W. R. VAN DALSEM, and K. V. RAO (NASA, Ames Copyright Research Center, Moffett Field, CA) Sep. 1989 15 p. SAE, A method for determining the position of the flow separation Aerospace Technology Conference and Exposition, Anaheim, CA, line on the fuselage of a helicopter is proposed which does not Sept. 25-28, 1989 refs require the full calculation of the boundary layer. In accordance (SAE PAPER 892283) Copyright with the method proposed here, the position of the separation The flow past a 60-deg delta wing equipped with two line is determined from the separation points, which are determined thrust-reverser jets near the inboard trailing edge has been analyzed by using Stratford's formula. The further modeling of flow past by numerical solution of the 3D thin-layer Navier-Stokes equations. the fuselage is carried out using the method of Makarov et al. An implicit, partially flux-split, approximately-factored Navier-Stokes (1990). AIAA solver coupled with a multiple grid embedding scheme has been adapted to this problem. Studies of the impact of numerical A93-52959 parameters (e.g., grid refinement and dissipation levels), and EFFECT OF BOUNDARY LAYER SUCTION ON THE THRUST flow-field parameters such as the height of the delta wing above AND AERODYNAMIC EFFICIENCY OF A HYPERSONIC the ground plane and the jet size on the solution, were performed. FLIGHT VEHICLE [VLIYANIE SLIVA POGRANICHNOGO Results of these numerical studies indicate some challenges in SLOYA NA TYAGOVO-AEHRODINAMICHESKUYU the accurate resolution of complex 3D free shear layers and jets. EHFFEKTIVNOST' GIPERZVUKOVOGO LETATEL'NOGO Nevertheless, flow features such as jet deformation and ground APPARATA] vortex formation observed in experimental flow visualizations are YU. P. GUN'KO, I. I. MAZHUL', and D. V. SHCHERBIK captured. Further, comparisons with experimental data confirm the Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 1 1993 p. ability to simulate the loss of wing-borne lift, commonly referred 89-92. In RUSSIAN refs to 'suckdown, as the delta planform flies at slow speeds in close Copyright proximity to the ground. Detailed analysis of the numerical results The effect of boundary layer suction ahead of the air intake has also given additional insight into the structure of the ground on the thrust and aerodynamic characteristics of a hypersonic vortex and the mechanisms of lift loss. Author (revised) flight vehicle with a ramjet engine is estimated analytically. In particular, attention is given to suction by means of a suction A93-53202* National Aeronautics and Space Administration. wedge. Data are presented for various configurations of an air Ames Research Center, Moffett Field, CA. intake with a suction wedge in a flight vehicle. AIAA LOW ASPECT RATIO WING CODE VALIDATION EXPERIMENT MICHAEL E. OLSEN and H. L. SEEGMILLER (NASA, Ames A93-53192 Research Center, Moffett Field, CA) AIAA Journal (ISSN NUMERICAL ANALYSIS OF FLOW WITHIN CASCADE WITH 0001-1452) vol. 31, no. 10 Oct. 1993 p. 1744-1752. AIAA, TIP CLEARANCE Aerospace Sciences Meeting and Exhibit, 30th, Reno, NV, Jan.

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6-9, 1992, AIAA Paper 92-0402. Previously cited in issue 09, p. (Contract NAG3-1168) 1352, Accession no. A92-26255 rets Copyright Copyright An assessment of the near-wall and low-Reynolds-number functions used in low-Reynolds-number k-epsilon models suggests A93-53204* National Aeronautics and Space Administration. that they are not suitable for the near-wall region of unsteady Ames Research Center, Moffett Field, CA. turbulent boundary layers, where the flow is characterized by rapid EFFECTIVE TREATMENT OF THE SINGULAR LINE changes in phase. An improved low-Reynolds-number k-epsilon BOUNDARY PROBLEM FOR THREE-DIMENSIONAL GRIDS model is developed in this paper. The near-wall and GRANT PALMER (NASA, Ames Research Center, Moffett Field, low-Reynolds-number functions in this model are formulated as CA) and ETHIRAJ VENKATAPATHY (Eloret Inst, Mountain View, functions of the local turbulent Reynolds numbers instead of the CA) AIAA Journal (ISSN 0001-1452) vol. 31, no. 10 Oct. inner variable y(+). The present model also has the correct 1993 p. 1757, 1758. AIAA, Aerospace Sciences Meeting and asymptotic behavior in the near-wall region. The turbulence model Exhibit, 30th, Reno, NV, Jan. 6-9, 1992, AIAA Paper 92-0545. has been incorporated in an unsteady boundary-layer code and Previously cited in issue 10, p. 1555, Accession no. A92-28202 validated for unsteady turbulent boundary layers with and without refs adverse pressure gradients. The predictions agree well with the Copyright experimental data and the theoretical analysis. For the cases tested, the present model correctly predicts the unsteady near-wall flow and the unsteady shin friction at various frequencies. A93-53205 Author (revised) ZONAL-LOCAL SOLUTION METHOD FOR THE TURBULENT NAVIER-STOKES EQUATIONS A93-53209 D. DRIKAKIS and S. TSANGARIS (Athens, National Technical MULTIGRID NAVIER-STOKES CALCULATIONS FOR Univ., Greece) AIAA Journal (ISSN 0001-1452) vol. 31, no. 10 THREE-DIMENSIONAL CASCADES Oct. 1993 p. 1759, 1760. Abridged, refs FENG LIU (California Univ., Irvine) and ANTONY JAMESON Copyright (Princeton Univ., NJ) AIAA Journal (ISSN 0001-1452) vol. 31, A zonal-local solution method is developed for the solution of no. 10 Oct. 1993 p. 1785-1791. AIAA, Aerospace Sciences the compressible Navier-Stokes equations. The main feature of Meeting and Exhibit, 30th, Reno, NV, Jan. 6-9, 1992, AIAA Paper the method is coupling of the Navier-Stokes equations with the 92-0190. Previously cited in issue 08, p. 1169, Accession no. Euler equations and the local mesh solution procedure. Mesh A92-23799 Research supported by DARPA and IBM Corp. sequencing (multilevel) technique is also used for the improvement refs of the efficiency of the algorithm. The methodology is applied to (Contract N00014-89-J-1366; N00014-86-K-0759) turbulent flowfields past an airfoil. A flux vector splitting method Copyright with an upwind scheme up to fourth-order accuracy is used for the discretization of the inviscid fluxes. The system of the equations is solved by an unfactored implicit method using Gauss-Seidel A93-53212* National Aeronautics and Space Administration. relaxation. Ames Research Center, Moffett Field, CA. SPACE MARCHING CALCULATIONS ABOUT HYPERSONIC CONFIGURATIONS USING A SOLUTION-ADAPTIVE MESH A93-53207 ALGORITHM BOUNDARY LAYER AND PRESSURE MEASUREMENTS ON A ALBERT D. HARVEY, SUMANTA ACHARYA (Louisiana State Univ., CYLINDER WITH UNSTEADY CIRCULATION CONTROL Baton Rouge), and SCOTT L LAWRENCE (NASA, Ames Research All ZANDIEH and J. G. LEISHMAN (Maryland Univ., College Center, Moffett Field, CA) AIAA Journal (ISSN 0001-1452) vol. Park) AIAA Journal (ISSN 0001-1452) vol. 31, no. 10 Oct. 31, no. 10 Oct. 1993 p. 1809-1818. refs 1993 p. 1769-1776. Research supported by Minta-Martin Fund (Contract NCA2-326; NCA2-522) for Aeronautical Research refs Copyright Copyright A solution-adaptive marching algorithm is developed and Unsteady boundary-layer and surface pressure measurements applied to a three-dimensional parabolized Navier-Stokes equation were made on a circular cylinder with time-varying blowing applied solver. The resulting algorithm obtains accurate solutions by using from a narrow spanwise slot. The effects of mean blowing level, a spatial-marching/adaptive grid procedure. The adaptation step blowing frequency, and boundary-layer trip location were examined redistributes grid points line by line in both crossflow directions, at a Reynolds number of 2.2 x 10 exp 5 based on cylinder diameter. with grid point motion controlled by forces analogous to tensional Time-resolved pressures were recorded using pressure sensors and torsional spring forces with the tensional force proportional to located on the Coanda surface and around the circumference of the error measure or weighting functions. The solution-adaptive the cylinder. Flush-mounted hot film probes were positioned both marching procedure is applied to the hypersonic flow about two upstream and downstream of the slot to provide a qualitative generic aircraft configurations. The first of these is an all-body-type measurement of the boundary-layer characteristics. The results geometry with elliptical cross sections and is studied at angles of have shown that the shear stress just downstream of the slot attack of 0.5, and 15 deg. The second geometry is a generic was always in-phase with the plenum pressure. However, increasing blended-wing-body design. Results are presented that demonstrate reduced frequency generally resulted in increasingly larger phase the improvements in flowfield resolution obtainable with the lags between the application of blowing and the development of solution-adaptive marching procedure over conventional fixed grid the flow over the remainder of the Coanda surface. For both techniques. Computed pilot pressure profiles obtained using the steady and unsteady blowing, the jet entrained the outer flow at solution-adaptive algorithm show improved agreement with the slot and remained attached to the Coanda surface, provided experimental data compared to predictions obtained using a fixed a fully attached laminar or turbulent boundary layer was obtained grid. just prior to reaching the slot. Author (revised) A93-53214* National Aeronautics and Space Administration. A93-53208* National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. Lewis Research Center, Cleveland, OH. OBSERVATIONS OF LIQUID JETS INJECTED INTO A HIGHLY LOW-REYNOLDS-NUMBER K-EPSILON MODEL FOR ACCELERATED SUPERSONIC BOUNDARY LAYER UNSTEADY TURBULENT BOUNDARY-LAYER FLOWS ARTHUR W. JOHNSON and K. R. SREENIVASAN (Yale Univ., SIXIN FAN, BUDUGUR LAKSHMINARAYANA (Pennsylvania State New Haven, CT) AIAA Journal (ISSN 0001-1452) vol. 31, no. Univ., University Park), and MARK BARNETT (United Technologies 10 Oct. 1993 p. 1827-1834. Research supported by NASA Research Center, East Hartford, CT) AIAA Journal (ISSN refs 0001-1452) vol. 31, no. 10 Oct. 1993 p. 1777-1784. refs Copyright

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Experiments were conducted to observe the cross-sectional FU-LIN TSUNG (Georgia Inst. of Technology, Atlanta) AIAA structure and streamwise growth of round transverse liquid jets Journal (ISSN 0001-1452) vol. 31, no. 10 Oct. 1993 p. injected into a highly accelerated boundary layer in supersonic 1857-1862. AIAA Computational Fluid Dynamics Conference, flow. The accompanying shock structure was also visualized. In 10th, Honolulu, HI, June 24-27, 1991, Technical Papers, p. 780-787. one case, a round jet of acetone was injected into a fully turbulent Previously cited in issue 17, p. 2850, Accession no. A91-40769 Mach 2.5 boundary layer that was subsequently accelerated and Research supported by U.S. Army refs partially laminarized through a sharp Prandtl-Meyer expansion Copyright corner. In the second case, a jet was injected into the laminarized Mach 3.2 boundary layer downstream of the expansion corner at A93-53219 the same jet-to-freestream momentum ratio. The jet and shock THRUST IMPARTED TO AN AIRFOIL BY PASSAGE THROUGH structure in both cases were visualized using schlieren optics. A SINUSOIDAL UPWASH FIELD Wall-flow patterns were visualized using paints. It was found that HERBERT S. RIBNER (Toronto Univ., Downsview, Canada) AIAA the lateral spreading of jets injected downstream of the expansion Journal (ISSN 0001-1452) vol. 31, no. 10 Oct. 1993 p. fan was augmented close to the wall and had a cross-sectional 1863-1868. Research supported by NSERC refs structure significantly different from that of the jet injected upstream: Copyright the upstream jet spreads rapidly at the expansion corner in both The passage of an airfoil through a sinusoidal upwash field the lateral and vertical directions. (Sears, 1941) is analyzed further to yield the wavelength-dependent thrust: the 'Katzmayr effect'. The shed vorticity is shown to induce A93-53216 an opposed flow that reduces the kinetic energy: the decrement SKIN-FRICTION TOPOLOGY OVER A SURFACE MOUNTED is found to match exactly the work done by the thrust. The 'Sears SEMI-ELLIPSOIDAL WING AT INCIDENCE function for thrust' is then applied to passage through turbulence TIMOTHY A. JOHNSON and VIRENDRA C. PATEL (Iowa Univ., described by a one-dimensional power spectrum. Finally, some Iowa City) AIAA Journal (ISSN 0001-1452) vol. 31, no. 10 acoustical implications of relaxing the postulated incompressibility Oct. 1993 p. 1842-1849. Research supported by DARPA are briefly discussed. It is argued that the radiated dipole noise, refs like the thrust, draws its energy from the flowfield. (Contract N00014-88-K-0001; N00014-91-J-1204; N00014-89-J-1342) A93-53231* National Aeronautics and Space Administration. Copyright Langley Research Center, Hampton, VA. Flow visualization methods have been used to study the TRANSITION CORRELATION IN SUBSONIC FLOW OVER A skin-friction topology of a 12:6:1 semi-ellipsoid wing at incidence FLAT PLATE intersecting a plane wall. Results were obtained for incidences J. A. MASAD and M. R. MALIK (High Technology Corp., Hampton, from 0 to 25 deg in 5 deg increments. Major changes in the VA) AIAA Journal (ISSN 0001-1452) vol. 31, no. 10 Oct. topology demarcate divisions between general ranges designated 1993 p. 1953-1955. refs as follows: symmetry, low, intermediate, and high incidences. As (Contract NAS1-19299) a function of incidence, the topological evolution is influenced by Copyright both three-dimensional pressure gradients and transition to A 2D subsonic flow over a flat plate with a freestream Mach turbulence. A slight twist in the experimental model suggests that number M(infinity) up to 0.8 is considered. The flow can experience the topology and associated separation modes (singular vs continuous uniform suction through the wall and the wall can be nonsingular) are highly sensitive to slight geometric asymmetries. heated or cooled continuously with a fixed wall temperature. For a specific combination of M(infinity), suction velocity, and level of A93-53217 heat transfer, the mean flow problem is solved and linear stability PRISMATIC GRID GENERATION FOR THREE-DIMENSIONAL calculations are performed to compute the location on the flat COMPLEX GEOMETRIES plate where the factor representing the integration of growth rates Y. KALLINDERIS and S. WARD (Texas Univ., Austin) AIAA reaches nine. These calculations are repeated for several Journal (ISSN 0001-1452) vol. 31, no. 10 Oct. 1993 p. combinations of flow parameters and the theoretically predicted 1850-1856. refs transition location is presented in the form of a correlation that (Contract AF-AFOSR-91-0022) can account for the effect of wall suction, heat transfer, and Mach Copyright number. AIAA The paper describes generation of semiunstructured prismatic grids for three-dimensional complex geometries. A new method of A93-53233 generation is presented, which couples both algebraic and elliptic FAST THREE-DIMENSIONAL VORTEX METHOD FOR steps. This combination yields low computation cost, as well as UNSTEADY WAKE CALCULATIONS smoothness of the grid. Main advantages of the developed grid KIAT CHUA and TODD R. QUACKENBUSH (Continuum Dynamics, generator are its direct control of grid orthogonality and spacing, Inc., Princeton, NJ) AIAA Journal (ISSN 0001-1452) vol. 31, as well as its generality for treatment of three-dimensional no. 10 Oct. 1993 p. 1957, 1958. Abridged. AIAA Applied geometries. The method marches a surface consisting of triangular Aerodynamics Conference, 10th, Palo Alto, CA, June 22-24, 1992, faces away from the body surface. Employment of prismatic Technical Papers. Pt. 1, p. 230-238. Previously cited in issue 19, elements is a relatively new approach toward three-dimensional, p. 3246, Accession no. A92-45496 refs complex geometry numerical simulations of viscous flows. A body (Contract DE-FG05-91ER-81207; DAAL03-89-C-0004) surface is covered with triangles, which gives the geometric Copyright flexibility, whereas the structure of the mesh in the direction normal to the surface provides better resolution of the viscous regions. A93-53314 An F-16A aircraft geometry was included in the applications to APPLICATION OF THE SMALL PARAMETER METHOD TO investigate efficiency and to demonstrate robustness of the method THE PROBLEM OF THREE-DIMENSIONAL FLOW OF A in handling relatively complex topologies. Grid generation time for VISCOUS GAS PAST BODIES [PRIMENENIE METODA the entire aircraft domain was of the order of minutes on a MALOGO PARAMETRA K ZADACHE PROSTRANSTVENNOGO workstation. OBTEKANIYA TEL POTOKOM VYAZKOGO GAZA] G. A. TIRSKIJ, S. V. UTYUZHNIKOV, and N. K. YAMALEEV A93-53218 Prikladnaya Matematika i Mekhanika (ISSN 0032-8235) vol. 56, THREE-DIMENSIONAL NAVIER-STOKES/FULL-POTENTIAL no. 6 Nov.-Dec. 1992 p. 1023-1032. In RUSSIAN refs COUPLED ANALYSIS FOR VISCOUS TRANSONIC FLOW Copyright LAKSHMI N. SANKAR (Georgia Inst. of Technology, Atlanta), BALA The problem of three-dimensional hypersonic flow of a viscous K. BHARADVAJ (Douglas Aircraft Co., Long Beach, CA), and gas past blunt spherical bodies is analyzed using a system of

1178 02 AERODYNAMICS equations of the full viscous shock layer. It is shown that the use gasdynamic structure is characteristic of a pseudodiscontinuity and of the small parameter method in conjunction with the method of is essentially inhomogeneous over the duct cross section. In this global iterations makes it possible to reduce the computer time case, the extent of combustion or the amount of heat transferred by approximately a factor of 100 in comparison with finite difference to the flow are determined by measuring static pressure on the computations using a strictly three-dimensional formulation. The duct wall. The use of a one-dimensional method may lead to an validity of the small parameter method is supported by experimental erroneous result. The method proposed here is based on the results. The examples considered include flow past blunt cones characteristics of the change of the inhomogeneity coefficient, and bicones of large length at small angles of attack and flow which is derived from a one-dimensional representation of the past a nearly axisymmetrical body at zero angle of attack. AIAA conservation equations. The method uses the pressure differential of isothermal flow with heat transfer; friction and heat transfer to A93-53315 the wall are taken into account. As an example, the method is COMPARISON OF GASDYNAMIC MODELS IN HYPERSONIC applied to the combustion of hydrogen and kerosene. AIAA FLOW [SRAVNENIE GAZODINAMICHESKIKH MODELEJ PRI GIPERZVUKOVOM OBTEKANII TEL] A93-53551 S. V. ZHLUKTOV, S. V. UTYUZHNIKOV, V. S. SHCHELIN, and V. CALCULATION OF A COMPRESSIBLE THREE-DIMENSIONAL G. SHCHERBAK Prikladnaya Matematika i Mekhanika (ISSN BOUNDARY LAYER ON A SWEPT WING [RASCHET 0032-8235) vol. 56, no. 6 Nov.-Dec. 1992 p. 1033-1038. In SZHIMAEMOGO TREKHMERNOGO POGRANICHNOGO SLOYA RUSSIAN refs NA STRELOVIDNOM KRYLE] Copyright V. E. KOVALEV TsAGI, Trudy no. 2465 1990 p. 3-31. In Various gasdynamic models describing chemically RUSSIAN refs nonequilibrium flows are compared with particular reference to Copyright stationary flow past the nose section of the Buran and Space A modified version of Keller's block method is proposed for Shuttle vehicles during their descent from the orbit. The models calculating a compressible three-dimensional boundary layer on a considered include a locally self-similar approximation of the wing of finite span. A hybrid difference scheme is developed in Navier-Stokes equations, a model of a chemically equilibrium and which the Keller-Cebeci templates and a zigzag are used with nonequilibrium full viscous shock layer, and a model of a thin weight coefficients that are dependent on the velocity vector viscous shock layer. In all the models, the physicochemical direction relative to the finite difference cell. A comparison of the processes are considered by using the same constants of results of calculations with exact solutions for a laminar boundary gas-phase chemical reactions. Good agreement is obtained layer and experimental data for a turbulent boundary layer between the results of calculations of the heat flow at the critical demonstrates the sufficient accuracy of the proposed algorithm point. AIAA for solving boundary layer equations. AIAA

A93-53333 A93-53552 CONSTRUCTION OF WAKES IN THE DISCRETE VORTEX CALCULATION OF FLOW FIELDS NEAR A LIFTING WING METHOD [O POSTROENII SLEDOV V METODE DISKRETNYKH [RASCHET POLEJ TECHENIYA OKOLO NESUSHCHEGO VIKHREJ] KRYLA] I. K. LIFANOV (Voenno-Vozdushnaya Inzhenernaya Akademiya, S. G. IGNAT'EV, O. V. KARAS', and A. V. SMIRNOV TsAGI, Moscow, Russia) Rossijskaya Akademiya Nauk, Doklady (ISSN Trudy no. 2465 1990 p. 32-46. In RUSSIAN refs 0869-5652) vol. 330, no. 5 June 1993 p. 574-578. In Copyright RUSSIAN refs Calculations are made of transonic flow fields near a thick Copyright swept wing of finite span. The load increment is estimated for the The use of the discrete vortex method for solving problems of isolated blade of a hypothetical propeller located in the field of flow of an ideal (nonviscous) fluid past a body is discussed. In flow from an aircraft wing. The possibility of reducing the load particular, attention is given to the calculation of wakes and jets increment by changing the propeller orientation is demonstrated. behind bodies of various configurations. Some characteristic The calculation results are compared with the available phenomena associated with wake and jet flows are briefly experimental and analytical data. AIAA examined. AIAA

A93-53364 A93-53555 RECENT ADVANCES IN COMPUTATIONAL ANALYSIS OF THE FLOW LAG ANGLE IN THE ROTOR OF A CENTRIFUGAL HYPERSONIC VEHICLES COMPRESSOR WITH ALLOWANCE FOR VISCOSITY EFFECTS R. F. WALTER (W.J. Schafer Associates, Inc., Albuquerque, NM) [RASCHET UGLA OTSTAVANIYA POTOKA V RABOCHEM Fizika Goreniya i Vzryva (ISSN 0430-6228) vol. 29, no. 3 KOLESE TSENTROBEZHNOGO KOMPRESSORA S UCHETOM May-June 1993 p. 66-71. refs VYAZKOSTNYKH EHFFEKTOV] Copyright V. G. SHVAROV TslAM, Trudy no. 1233 1989 p. 12-18. The nonequilibrium gasdynamics processes of importance to In RUSSIAN refs hypersonic aerobraking vehicles are reviewed. Recent Copyright improvements in understanding these phenomena and in the An approximate method is proposed for calculating the flow detailed numerical modeling of these processes will be discussed. lag angle and the power loss coefficient of the rotors of the The paper concludes by describing the extent to which these centrifugal stage of a compressor with allowance for total pressure models have been incorporated into multidimensional losses in the rotor and rotor friction against the casing of the computational fluid dynamics (CFD) computer codes. stage. A comparison is made between theory and results of test calculations for a compressor stage. The accuracy of the method A93-53365 is evaluated. AIAA DETERMINATION OF HEAT TRANSFER TO FLOW IN A DUCT WITH A PSEUDODISCONTINUITY [OPREDELENIE A93-53573 TEPLOPODVODA K POTOKU V KANALE S MOVING WALL EFFECTS IN TRANSVERSE SUBSONIC FLOW PSEVDOSKACHKOM] PAST A ROTATING CYLINDER [EHFFEKTY P. K. TRET'YAKOV Fizika Goreniya i Vzryva (ISSN 0430-6228) DVIZHUSHCHEJSYA STENKI, VOZNIKAYUSHCHIE PRI vol. 29, no. 3 May-June 1993 p. 71-77. In RUSSIAN refs POPERECHNOM OBTEKANII VRASHCHAYUSHCHEGOSYA Copyright TSILINDRA DOZVUKOVYM POTOKOM] Heat transfer due to propellent combustion in a duct with V. P. KOZLOV Moskovskij Universitet, Vestnik, Seriya 1 - supersonic flow leads to flow deceleration. The resulting Matematika, Mekhanika (ISSN 0579-9368) no. 1 Jan.-Feb.

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1993 p. 79-84. In RUSSIAN refs condition. No regions of flow separation could be identified in the Copyright data plots of the mean intrablade flow field. The relative flow Pressure distributions on the surface of a rotating cylinder in about the blades remained subsonic during flutter operation. The transverse subsonic flow is investigated experimentally for critical blades were found to have a higher than expected tip loading at Reynolds numbers. It is found that the presence of a moving wall both operating conditions. This is thought to have been caused nearly always leads to a strong asymmetry in pressure distribution. by the outer blade sections twisting under load to higher than The asymmetry is caused not only by the boundary layer transition expected effective blade angles. This high tip loading resulted in but also by other hydrodynamic effects associated with the strong vortices and a very nonuniform flow downstream of the restructuring of the separated flow in the wall region. AIAA tips of the forward-swept blades. This high tip loading may also have caused the blade flutter. Author (revised) A93-53574 AERODYNAMIC CHARACTERISTICS OF CONICAL TRIANGULAR-PLANFORM WINGS OF LOW ASPECT RATIO IN SUBSONIC STALLED FLOW [AEHRODINAMICHESKIE A93-53592*# National Aeronautics and Space Administration. KHARAKTERISTIKI KONICHESKIKH KRYL'EV TREUGOL'NOJ Lewis Research Center, Cleveland, OH. FORMY V PLANE MALOGO UDLINENIYA PRI DOZVUKOVOM STREAMWISE VORTICITY GENERATION AND MIXING SRYVNOM OBTEKANII] ENHANCEMENT IN FREE JETS BY 'DELTA-TABS' V. I. VORONIN, G. S. UL'YANOV, and A. I. SHVETS Moskovskij K. B. M. Q. ZAMAN (NASA, Lewis Research Center, Cleveland, Universitet, Vestnik, Seriya 1 - Matematika, Mekhanika (ISSN OH) Jul. 1993 14 p. AIAA, Shear Flow Conference, Orlando, 0579-9368) no. 1 Jan.-Feb. 1993 p. 101-104. In RUSSIAN FL, July 6-9, 1993 Previously announced in STAR as refs N93-31648 refs Copyright (AIAA PAPER 93-3253) Copyright Results of theoretical and experimental aerodynamic studies The effect of triangular tabs, placed at the nozzle exit, on the are presented for conical wings of triangular planform at subsonic evolution of free jets is investigated. The effect, a large distortion velocities with leading-edge stall. The wings considered represent of the jet cross section and a resultant increase in mixing conical surfaces with aspect ratios of 1.07-1.86. The aerodynamic downstream, has been inferred before to be due to a pair of characteristics of the wings are presented as a function of the streamwise vortices originating from each tab. In this paper, the relative deflection and the sweep angle. It is found that, as the generation mechanism of the streamwise vorticity (omega sub x) Mach number increases from 0.4 to 0.8, the lifting force and drag is considered first. Two sources are postulated. One is the upstream coefficients increase by 5-7 percent, while the lift-drag ratio remains 'pressure hill', produced by the tab, which appears to be the practically constant. AIAA dominant source. Another is due to vortex filaments shed from the sides of the tab and reoriented downstream by the mean shear of the mixing layer. In the case of a 'delta-tab', a triangular A93-53575 tab with its apex leaning downstream, vorticity from the two sources UNSTEADY AERODYNAMIC CHARACTERISTICS OF THREE explain the stronger effect in that configuration. Data on the vorticity RECTANGULAR WINGS OF DIFFERENT ASPECT RATIOS evolution for the effect of two delta-tabs are presented, up to [NESTATSIONARNYE AEHRODINAMICHESKIE twelve jet diameters from the exit, which show that the streamwise KHARAKTERISTIKI TREKH PRYAMOUGOL'NYKH KRYL'EV vortices persist even at the farthest measurement station. The RAZLICHNOGO UDLINENIYA] magnitude of omega sub x-maximum decays continually with EH. P. GREBESHOV and E. P. SHAKARVENE TsAGI, Trudy distance from the nozzle, its ratio to azimuthal vorticity maximum no. 2485 1990 p. 1-31. In RUSSIAN refs is found to be about 1/5 everywhere. The relative effect of a Copyright delta-tab on jets from an axisymmetric nozzle and a 8:1 rectangular Experimental data are presented for three rectangular wings nozzle is also studied. The mixing layer distortion is found to be with aspect ratios of 1, 2, and 4, respectively. The results are less pronounced in the rectangular case. The jet mixing, as presented in the form of steady and unsteady coefficients of the manifested by the mass flux measured at a downstream station, lifting force, drag, and longitudinal moment and derivatives of these is increased in the axisymmetric jet but it is decreased in the coefficients. The unsteady characteristics are obtained over a wide rectangular jet under consideration by the delta-tab. range of Strouhal numbers (0.4-4) and angles of attack (0-26 deg). An approximate analytical expression is proposed which relates the drag coefficient, obtained under nonstationary flow conditions, to the kinematic motion parameters (angle of attack, angular A93-53618 velocity, and their first time derivatives). AIAA 3D LAMINAR AND 2D TURBULENT COMPUTATIONS WITH THE NAVIER-STOKES SOLVER FLU3M A93-53591*# . National Aeronautics and Space Administration. C. JOUET and P. D'ESPINEY (ONERA, Chatillon, France) ONERA, Lewis Research Center, Cleveland, OH. TP no. 1993-105 1993 12 p. International Conference on LASER VELOCIMETER MEASUREMENTS OF THE FLOW Numerical Methods in Laminar and Turbulent Flow, 8th, Univ. of FIELD GENERATED BY A FORWARD-SWEPT PROPFAN Swansea, United Kingdom, July 18-23, 1993 Research supported DURING FLUTTER by DRET refs GARY G. PODBOY and MARTIN J. KRUPAR (NASA, Lewis (ONERA, TP NO. 1993-105) Research Center, Cleveland, OH) Jul. 1993 50 p. AIAA, Fluid In the present work, an upwind numerical approach for the Dynamics Conference, 24th, Orlando, FL, July 6-9, 1993 refs solution of the compressible Reynolds averaged Navier-Stokes (AIAA PAPER 93-2919) Copyright equations is presented; this work has been done using the 3D Results are presented from an investigation to measure the multidomain code FLU3M. Turbulence closure is obtained using flow field generated by a forward-swept propfan operating in flutter the Jones-Launder k-epsilon model. A Roe type Riemann solver at a low forward velocity. For comparison to the flutter condition, for the fully coupled hyperbolic system is briefly described; a Beam flow field data are also presented for a slightly reduced rotational and Warming type implicit linearization is used in order to accelerate speed just below flutter. The forward-swept propfan was tested the convergence. First, two laminar 3D-results on a lenticular as the front rotor of a counterrotating pusher propeller. A laser section missile are compared with available experimental data for Doppler velocimeter (LDV) was used to measure the velocity field flow at supersonic Mach numbers for a validation purpose. Then, in planes normal to the model centerline downstream of the rotor two 2D turbulent computations are shown. For the first one, the and in planes of constant radius within the blade passages at characteristic features of a single turbulent boundary layer are each operating condition. The mean time-averaged flow about the discussed. For the second one, a shock wave-boundary layer blades did not change drastically as the propfan rotational speed interaction flow is considered and results are compared with was increased from the stable operating point to the flutter experimental data. Author (revised)

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A93-53736* National Aeronautics and Space Administration. pivot, Reynolds number, angular velocity and maximum angle of Langley Research Center, Hampton, VA. attack are researched. Body-fitted grid generation with moving AERODYNAMIC CHARACTERISTICS OF THE HL-20 boundaries is used to obtain the numerical solution of the GEORGE M. WARE and CHRISTOPHER I. CRUZ (NASA, Langley incompressible Navier-Stokes equations. The time-dependent Research Center, Hampton, VA) Journal of Spacecraft and curvilinear coordinate system which coincides with a contour of a Rockets (ISSN 0022-4650) vol. 30, no. 5 Sept.-Oct. 1993 p. moving boundary is transformed into a fixed rectangular coordinate 529-536. AIAA, Applied Aerodynamics Conference, 9th, Baltimore, system in the calculation plane. The changes in CD and CL during MD, Sept. 23-25, 1991, AIAA Paper 91-3215. Previously cited in the pitching motion are obtained. Author (revised) issue 23, p. 4008, Accession no. A91-53865 refs A93-53799 A93-53739* National Aeronautics and Space Administration. STUDY ON SURGE AND ROTATING STALL IN AXIAL Langley Research Center, Hampton, VA. COMPRESSORS. Ill - NUMERICAL MODEL FOR AERODYNAMIC HEATING ENVIRONMENT MULTIBLADE-ROW COMPRESSORS DEFINITION/THERMAL PROTECTION SYSTEM SELECTION HIROSHI ISHII and YASUSHIGE KASHIWABARA Japan Society FOR THE HL-20 of Mechanical Engineers, Transactions B (ISSN 0387-5016) vol. K. E. WURSTER and H. W. STONE (NASA, Langley Research 59, no. 560 April 1993 p. 1127-1133. In JAPANESE refs Center, Hampton, VA) Journal of Spacecraft and Rockets (ISSN Copyright 0022-4650) vol. 30, no. 5 Sept.-Oct. 1993 p. 549-557. refs This paper proposes a new numerical model expanding on the Copyright previous fundamental model, which aims at a more accurate Definition of the aerothermal environment is critical to any representation of both surge and rotating stall for practical vehicle such as the HL-20 Personnel Launch System that operates applications. The model deals with the full set of fluid equations within the hypersonic flight regime. Selection of an appropriate for two-dimensional unsteady compressible flow in the axial and thermal protection system design is highly dependent on the circumferential directions throughout the compressor. The blade accuracy of the heating-environment prediction. It is demonstrated rows are replaced by semiactuator disks, where the blade row that the entry environment determines the thermal protection characteristics are expressed by the total pressure loss versus system design for this vehicle. The methods used to predict the the incidence angle. The basic function and validity of the proposed thermal environment for the HL-20 Personnel Launch System model are examined through numerical simulation of both surge vehicle are described. Comparisons of the engineering solutions and rotating stall in multiblade-row compressors. with computational fluid dynamic predictions, as well as wind-tunnel test results, show good agreement. The aeroheating predictions A93-53837 over several critical regions of the vehicle, including the stagnation THREE-DIMENSIONAL VISCOUS FLOW ANALYSIS OF areas of the nose and leading edges, windward centerline and COMPRESSOR CASCADE CHANNELS wing surfaces, and leeward surfaces, are discussed. Results of HIDENORI YOSHIDA, TAKASHI KAWASHIMA, and KEIJI predictions based on the engineering methods found within the SAKAGAWA Japan Society of Mechanical Engineers, MINIVER aerodynamic heating code are used in conjunction with Transactions B (ISSN 0387-5016) vol. 59, no. 561 May 1993 the results of the extensive wind-tunnel tests on this configuration p. 1524-1531. In JAPANESE refs to define a flight thermal environment. Finally, the selection of the Copyright thermal protection system based on these predictions and current A three-dimensional Navier-Stokes (NS) numerical analysis grid technology is described. is developed for turbomachinery based on the outer flow grid for aircrafts, in which the Reynolds averaged NS equations are solved A93-53740* National Aeronautics and Space Administration. using an implicit finite-volume TVD scheme with a two-equation Langley Research Center, Hampton, VA. turbulence model. The new grid was validated in two-dimensional HL-20 COMPUTATIONAL FLUID DYNAMICS ANALYSIS compressor cascade tests with solid side walls, measuring the K. J. WEILMUENSTER and FRANCIS A. GREENE (NASA, Langley three-dimensional flow pattern, and comparing the test data with Research Center, Hampton, VA) Journal of Spacecraft and the results of the three-dimensional viscous flow analysis. It was Rockets (ISSN 0022-4650) vol. 30, no. 5 Sept.-Oct. 1993 p. found that the computed results agree well with the experimental 558-566. refs data, such as the static pressure distribution on the blade surface, Copyright the total pressure loss distribution at the outlet of the cascade, The essential elements of a computational fluid dynamics and the pitchwide-averaged flow angle distribution. AIAA analysis of the HL-20/personnel launch system aerothermal environment at hypersonic speeds including surface definition, grid A93-53840 generation, solution techniques, and visual representation of results SHOCK SHAPES AROUND SLENDER DIAMOND CONES are presented. Examples of solution technique validation through TRAVELING AT HYPERSONIC SPEED comparison with data from ground-based facilities are presented, MASATOMI NISHIO and MUTSUO KOTAKE Japan Society of along with results from computations at flight conditions. Mechanical Engineers, Transactions B (ISSN 0387-5016) vol. Computations at flight points indicate that real-gas effects have 59, no. 561 May 1993 p. 1566-1572. In JAPANESE refs little or no effect on vehicle aerodynamics and, at these conditions, Copyright results from approximate techniques for determining surface The shock shapes around slender diamond cones were obtained heating are comparable with those obtained from Navier-Stokes using the law of conservation of mass and the equivalence principle solutions. for hypersonic flows passing slender bodies. Theoretical shock shape obtained by this method agreed well with the experimental A93-53798 result obtained by the first electric discharge method. It was NUMERICAL ANALYSIS OF A FLAT PLATE IN A PITCHING confirmed that this method is effective in calculating the shock MOTION. II - EFFECT ON THE FLOW OF THE POSITION OF shape around an arbitrary slender body traveling at hypersonic THE PIVOT, ETC speed. HIDEYUKI OHBA and SHIGEAKI KURODA Japan Society of Mechanical Engineers, Transactions B (ISSN 0387-5016) vol. A93-53841 59, no. 560 April 1993 p. 1121-1126. In JAPANESE refs ANALYSIS OF UNSTARTED SUPERSONIC FLUTTER IN Copyright CASCADE BY SEMIACTUATOR DISK THEORY Flows around a flat plate exhibiting a pitching motion in a HIROFUMI DOI and SHOJIRO KAJI Japan Society of Mechanical uniform crossflow are studied numerically. Two cases of pitching Engineers, Transactions B (ISSN 0387-5016) vol. 59, no. 561 motion, sinusoidal oscillation, and oscillation with constant velocity May 1993 p. 1573-1579. In JAPANESE refs are analyzed, and the effects on the flow of the position of the Copyright

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Unstarted supersonic flutter in a cascade is characterized by coordinates, so that not only the boundary conditions are kept on the existence of a detached bow shock wave ahead of each the real body surface, but the time-dependent body-fitted airfoil. To study the influence of the bow shock wave on this coordinates are built in a very simple way as well. The NACA64A-10 flutter, analysis is performed on the corresponding flowfield with airfoil which oscillates in pitching about its 1/4 chord point is use of the semiactuator disk theory. We investigate oscillation in computed, and the computed results are in good agreement with the bending mode with the interblade phase angle, considering experimental data. Calculated results for the airfoil oscillating in the effect of reflection of the pressure wave and the production heaving and both in heaving and pitching are also presented. of a vorticity wave and an entropy wave by the bow shock wave. Author (revised) The results show that the existence of detached bow shock waves greatly destabilizes bending oscillation, and the flutter boundary A93-53853 drastically extends to a high-frequency region. Author (revised) NUMERICAL STUDY OF SUPERSONIC FLOW OVER A BACKWARD STEP WITH TRANSVERSE INJECTION A93-53842 WEI-JIANG ZHOU, HAN-DONG MA (Beijing Inst. of Aerodynamics, VELOCITY FLUCTUATION BASED ON THE DIFFERENCE IN China), and YAN-WEN MA (Chinese Academy of Sciences, Inst. THE FLOW PATTERN IN THE CHANNELS OF A of Mechanics, Beijing, China) Acta Aeronautica et Astronautica CENTRIFUGAL IMPELLER Sinica (ISSN 1000-6893) vol. 14, no. 1 Jan. 1993 p. HIROMU TSURUSAKI, TOMOHIRO TATEISHI, and YOSHINOBU A14-A19. In CHINESE refs TSUJIMOTO Japan Society of Mechanical Engineers, The interaction between a supersonic flow around a backward Transactions B (ISSN 0387-5016) vol. 59, no. 561 May 1993 step and transverse injectors (Ma(j) = 1.05) located on the p. 1626-1631. In JAPANESE refs downstream of the step is simulated with finite difference method, Copyright by solving the N-S equations numerically. First, the supersonic When an open-type impeller was operated near the flow rate flows over a backward step without an injector are computed, for shockless entry, a large component in the velocity fluctuation and the results are compared with the experiment and other spectrum was observed outside the impeller. The frequency of calculations. Then, the injector is added, with the pressure ratio this component was equal to that of the impeller rotation. The p(j)/p(infinity) varying from 3.033 to 7.033 and the injector width, origin of this component was studied experimentally. The flow w, equal to 0.1 h or 0.2 h (h = step height). The reasonable conditions near the flow rate where the large component was structures of vortex and waves are presented, and the effects of observed were determined for an open impeller and for a closed p(j)/p(infinity) and w on flow properties are investigated. Within impeller. From the experiment, it became clear that the flow pattern the present parameter region, the calculations show that the including a backflow region in the open impeller was changed pressure at the step bottom is almost linearly related to the factor near the above mentioned flow rate, and, at that particular flow Q (Q = wp(j)/hp(infinity)). Author (revised) rate, two types of velocity distributions existed in the impeller channels. Thus, the large component of the velocity fluctuation was observed outside the impeller. The flow pattern which caused A93-53858 the velocity fluctuation is discussed. Author (revised) NUMERICAL SOLUTION OF N-S EQUATIONS FOR HYPERSONIC FLOW OVER CAPSULE-TYPE VEHICLES A93-53843 WEI-JIANG ZHOU (Beijing Inst. of Aerodynamics, China) Acta NUMERICAL ANALYSIS OF THE FLOW THROUGH A Aeronautica et Astronautica Sinica (ISSN 1000-6893) vol. 14, CENTRIFUGAL IMPELLER BY VORTEX DISTRIBUTION no. 1 Jan. 1993 p. A68-A71. In CHINESE refs MODEL OF A BOUNDARY LAYER. I - THEORETICAL The laminar N-S equations for hypersonic flow over capsule-type ANALYSIS reentry vehicles are solved using the second-order windward TVD HONG GAO and KYOJI KAMEMOTO Japan Society of Mechanical scheme. The detailed flowfield structures and pressure distribution Engineers, Transactions B (ISSN 0387-5016) vol. 59, no. 561 along the body surface are given, and its good agreement with May 1993 p. 1632-1639. In JAPANESE refs experiment and reference is shown. The calculations also show Copyright that the variation of radius R2 does not cause much flowfield This paper presents a numerical analysis method for a separated change in the afterbody, but it has a great effect on the heating unsteady flow in a centrifugal impeller. Considering the influence rate near the shoulder. In the case of R2 = 0.2, the heating rate of the boundary layer, the flow, which is assumed to be peak on the shoulder is slightly less than the stagnation values; two-dimensional, inviscid, and incompressible, is analyzed using however, when R2 is equal to 0.05, this peak is much higher and both the boundary element method and the discrete vortex method. exceeds the stagnation value by 30 percent. Author (revised) Based on Karman's momentum and Poisson's equation, the changes in the displacement thickness are solved and the A93-53859 separation point on the boundary layer is determined automatically A PRELIMINARY INVESTIGATION OF THE CONTROL OF by the shape factor H of the turbulent flow. The velocity field and SEPARATED FLOW BY MEANS OF EXCITATION the pressure distributions are solved for the discharge coefficient CHENG XU (East China Inst. of Technology, Nanjing, China), c(e) = Q/Qn (in this paper, c(e) = 0.6). Author (revised) SHI-YING ZHANG, and MING-DE ZHOU (Nanjing Aeronautical Inst., China) Acta Aeronautica et Astronautica Sinica (ISSN A93-53852 1000-6893) vol. 14, no. 1 Jan. 1993 p. A72-A75. In AN IMPLICIT DIFFERENCE SCHEME OF EULER EQUATION CHINESE refs FOR UNSTEADY TRANSONIC FLOW Force measurements combined with flow visualization are used ZHENG-HONG GAO (Northwestern Polytechnical Univ., Xian, to investigate the control of two-dimensional leading-edge China) Acta Aeronautica et Astronautica Sinica (ISSN separation by means of flap oscillation. It is found that the results 1000-6893) vol. 14, no. 1 Jan. 1993 p. A7-A13. In of control are related to the modeled natural flow patterns. When CHINESE refs the natural flow pattern is a closed separation bubble, the excitation A continuous flux splitting method for unsteady Euler equations causes a lift loss. A reduction of the reattachment length and the based on time-dependent body fitted coordinates is described, drag of the model can be achieved by proper frequency excitation. and the method is used to derive an implicit difference equation The most effective Strouhal number range based on the for solving the unsteady transonic flow with Euler equations. In reattachment length and the main stream velocity for drag reduction order to reduce the computer time for solving the block-matrix is 3-5. When the natural flow pattern is full separation, proper equations, a characteristic matrix transformation is used. This frequency excitation changes the flowfield into a closed separation transformation does not change the discrete order of the equations, bubble, and a lift increment is achieved. The most effective Strouhal but the CPU for solving the matrix equations can be reduced number range based on the chord of the model and the main greatly. The numerical computation is made in the moving stream velocity for lift increment is 0.70-2.5. Author (revised)

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A93-53860 A93-53983 ANALYTICAL EXPRESSION OF DISSIPATION INTEGRAL FOR NUMERICAL STUDY ON INCEPTION OF STALL CELLS IN KINETIC ENERGY INTEGRAL EQUATION ROTATING STALL LONG-DE HE (Chinese Academy of Sciences, Inst. of Mechanics, TOSHIO NISHIZAWA (National Aerospace Lab., Chofu, Japan) and Beijing, China) Acta Aeronautica et Astronaulica Sinica (ISSN HIROYUKI TAKATA (Tokai Univ., Hiratsuka, Japan) In ISABE - 1000-6893) vol. 14, no. 1 Jan. 1993 p. A76-A79. In International Symposium on Air Breathing Engines, 11th, Tokyo, CHINESE refs Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington A dissipation integral method is developed for calculating American Institute of Aeronautics and Astronautics 1993 p. compressible turbulent boundary layers on planar bodies. An 63-72. refs analytical expression of dissipation integral for kinetic energy (ISABE 93-7007) Copyright integral equation is derived by two-layer eddy viscosity turbulence This paper discusses numerically the inception of stall cells in model and the power law of the velocity profile. The analytical rotating stall, especially putting importance on the number of stall expression depends on the local values of skin friction, shape cells. Examinations are made for both of the isolated cascade factor, Mach number, and Reynolds number based on momentum and the rotor with guide vanes upstream. In the isolated cascade thickness. The method is easy to use, and thus the calculation of operating around the stall inception point, a plural number of stall the turbulent boundary layers is significantly simplified. The cells may be propagated only when the flow fluctuation is small. analytical expression is in better agreement with experimental data But only one cell propagates for the fully developed rotating stall. than other theoretical results. Author (revised) With the inlet guide vanes, greater numbers of the stall cells can grow up to steadily propagating ones. The number of stall cells depends on both the axial spacing between the two cascades A93-53868 and the relative exit flow angle of guide vanes. The results are TRANSONIC AREA RULE ABOUT LIFTING CONFIGURATIONS confirmed by comparison with both experiment and analysis. QING-WEI ZHAO and BING-XUAN ZHANG (Beijing Univ. of Author (revised) Aeronautics and Astronautics, China) Acta Aeronautica et Astronautica Sinica (ISSN 1000-6893) vol. 14, no. 2 Feb. 1993 A93-53984 p. B1-B6. In CHINESE refs SOME MEASUREMENTS OF STALL IN AN AXIAL IMPELLER This paper develops the nonlinear area ruling method applied P. A. RAJAN and S. SOUNDRANAYAGAM (Indian Inst. of Science, to lifting configurations by using the matched asymptotic expansion Bangalore, India) In ISABE - International Symposium on Air and gives the conservational condition under which the integral Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, strength of the equivalent sources depending on the lift distribution Proceedings. Vol. 1 Washington American Institute of Aeronautics is equal to zero. This conservational condition can be used to and Astronautics 1993 p. 73-84. refs determine the corrective quantities of the above mentioned (ISABE 93-7008) Copyright equivalent sources in the region of the trailing edge of the wing. Measurements have been made in a single stage axial impeller, The computed results show that the method is capable of including the stalled flow regime, using conventional combination, accurately predicting the transonic wave drag for general airplanes yaw-pitch probes as well as a single rotated inclined hot wire. An or their components which have zero lift or lift and providing optimal unexpected finding was that, contrary to the accepted belief that option for the low-cost wave drag configurations, and the method a stall cell is a region of reduced flow, a high velocity jetlike flow has enough accuracy when applied up to free-stream Mach = existed within the cell at the root, the fluid in the high velocity jet 1.5 and alpha =10 deg. Author (revised) being conjectured to have migrated radially inwards from the tip region. Correlations developed from tests on high hub to tip diameter ratio machines do not conform to the present results A93-53982 though the value of psi-(T-s) at Stall is in broad agreement. The A 2-D COMPRESSIBLE N-S SIMULATION OF STARTING- AND stall cell has a spiral configuration which is oriented parallel to STALLING-FLOWS IN A COMPRESSOR CASCADES SYSTEM the main flow streamlines in a frame of reference moving with the EISUKE OUTA, DAI KATO (Waseda Univ., Tokyo, Japan), and cell, implying no motion of the external flow through the cell. The KAORU CHIBA (Ishikawajima-Harima Heavy Industries Co., Ltd., flow within the cell is not radically different from the external flow. Research and Development Dept., Tokyo, Japan) In ISABE - The stall cell reaches its final velocity after inception in about International Symposium on Air Breathing Engines, 11th, Tokyo, eight revolutions of the rotor though it takes about 25 revolutions Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington to attain a final size. Author (revised) American Institute of Aeronautics and Astronautics 1993 p. 53-62. Research supported by Waseda Univ refs (ISABE 93-7006) Copyright A93-53985 A numerical simulation of unsteady flow in linear cascades of THE LEADING EDGE VORTEX OF A ROTATING STALL CELL F. A. E. BREUGELMANS, E. FABRY, and J. MIJS (von Karman a compressor is conducted by applying a TVD finite difference Inst. for Fluid Dynamics, Rhode-Saint-Genese, Belgium) In ISABE scheme. Two-dimensional compressible Navier-Stokes equations - International Symposium on Air Breathing Engines, 11th, Tokyo, are solved iteratively in a rotor-fixed moving frame and in a Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington stator-fixed frame. Instead of applying a turbulence model, a very American Institute of Aeronautics and Astronautics 1993 p. fine grid system is used. The flow induced by rotor blade motion 85-90. refs are analyzed as an initial value problem without specifying an incidence flow angle. To alter a load on the compressor, a throttle (ISABE 93-7009) Copyright A single cell rotating stall pattern has been investigated in the resistance is provided at the outflow boundary. Two combinations leading edge region of the cell. The experimental and data of the number of rotor and stator blades are concerned; a treatment procedures are developed to this purpose. The existence one-rotor/one-stator and a three-rotor/five-stator combinations. of a vortex is shown and its extent in the axial and tangential The Reynolds number and the Mach number in the latter case direction demonstrated. are 300,000 and 0.3. The stage characteristics such as pressure rise, incidence angle, and wake profiles show very similar features with compressor test data. Configurations of blade vortices, A93-53986 formation and convection of wakes, and propagation of stalled THE ENERGY DISSIPATION IN A ROTATING STALL CELL cells are satisfactorily demonstrated. The speeds of the stall O. EERTINK and F. A. E. BREUGELMANS (von Karman Inst. for propagation at early stages of the development are computed to Fluid Dynamics, Rhode-Saint-Genese, Belgium) In ISABE - be 84 percent of the blade speed in the rotor and roughly 15 International Symposium on Air Breathing Engines, 11th, Tokyo, percent in the stator. The number of stall cells is not found definitely, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington since the number of blades is very low. Author (revised) American Institute of Aeronautics and Astronautics 1993 p.

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91-96. refs A93-54005 (ISABE 93-7010) Copyright INVESTIGATION OF THE FLOW FIELD THROUGH A The stall cell is investigated for the energy dissipation VARIABLE PITCH FAN ROTOR WITH AN INLET TOTAL capabilities. The kinetic energy contained in rotating stall cells in PRESSURE DISTORTION an axial flow compressor is determined from measurements with T. KAYA, A. CARRERE, and R. BARENES (Ecole Nationale a crossed hot wire in the upstream space between inlet guide Superieure de I'Aeronautique et de I'Espace, Toulouse, France) vanes and rotor. The closing and opening sequence of the throttling In ISABE - International Symposium on Air Breathing Engines, is performed and the transition between the different patterns 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 demonstrated. Washington American Institute of Aeronautics and Astronautics 1993 p. 332-339. refs (ISABE 93-7029) Copyright An experimental and numerical investigation of the flow field A93-53987 through a variable pitch fan rotor has been conducted. First, the REVIEW OF STALL, SURGE AND ACTIVE CONTROL IN steady state measurements have been compared with the results AXIAL COMPRESSORS of a quasi-three-dimensional numerical calculation when the inlet I. J. DAY (Cambridge Univ., United Kingdom) In ISABE - flow is homogeneous. Then, the inlet flow has been distorted by International Symposium on Air Breathing Engines, 11th, Tokyo, a screen placed 1.4 fan diameters upstream of the fan. The periodic Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington and random fluctuations have been separately measured, as a American Institute of Aeronautics and Astronautics 1993 p. function of the fan-blade incidence. Finally, a linearized method 97-105. Research supported by Rolls-Royce, PLC and SERC has been used to analyze the attenuation capacity of the fan refs when the .fan-blade incidence is changed. (ISABE 93-7011) Copyright This paper reviews the work done on stall, surge and active control over the past ten years. A great deal of theoretical and A93-54006 experimental activity has taken place making this period of research NAVIER-STOKES COMPUTATION OF THE THREE one of the most fruitful since work on compressor instabilities DIMENSIONAL FLOW FIELDS THROUGH A TRANSONIC FAN began. The review covers the part played by two-dimensional, BLADE long lengthscale disturbances in the theoretical treatment of stall O. NOZAKI, K. YAMAMOTO, K. KIKUCHI, Y. SAITO, N. inception, and focuses on the way this work leads to the original SUGAHARA, and A. TAMURA (National Aerospace Lab., Tokyo, proposal that active control might be applied to compressor Japan) In ISABE - International Symposium on Air Breathing instabilities. The experimental demonstration of the existence of Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. long lengthscale disturbances is discussed, followed by the 1 Washington American Institute of Aeronautics and successful attempts to control these disturbances. The existence Astronautics 1993 p. 340-346. refs of three-dimensional, short lengthscale disturbances was (ISABE 93-7030) Copyright discovered during this period and it is shown how these The three dimensional transonic flow fields of a fan stage have disturbances can also be controlled using active techniques. been analyzed by a computational solution of Navier-Stokes Detailed studies of surge in axial compressors are reported showing equations employing an implicit finite difference method with high clearly that rotating stall is responsible for the onset of surge. accuracy upwind scheme. Experimental data were also introduced The successful attempts to control surge in axial machines follow for verifying the computation. The fan stage model under naturally from this observation. Finally, the review covers the current consideration consists of rotor blades and outlet guide vanes. In studies of stall inception in aero-engine compressors. order to deal with the flow through multiple rows a zonal approach was utilized, where computational domains are arranged for each row and boundary conditions are replaced repeatedly at each time step. This approach has been applied to a fan model for a wide A93-53988 range of mass flow to evaluate the over-all characteristics. In the AN INVESTIGATION OF POST STALL TRANSIENTS AND paper the numerical approach is illustrated and significant results RECOVERABILITY OF AXIAL COMPRESSION SYSTEMS for actual fan designs are discussed in comparison with J. HU, G. C. TANG, and H. M. ZHANG (Nanjing Aeronautical experimental data. Inst., China) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington American Institute of Aeronautics and A93-54007 Astronautics 1993 p. 106-116. refs THE STREAMLINE THROUGHFLOW METHOD OF AXIAL (ISABE 93-7012) Copyright TURBOMACHINERY FLOW ANALYSIS A simplified approximate method is proposed to predict the T. W. VON BACKSTROM and T. H. ROOS (Stellenbosch Univ., poststall behaviors and recoverability from stalled flow both with South Africa) In ISABE - International Symposium on Air Breathing uniform and with circumferential nonuniform inlet flow in multistage Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. axial compression systems. The method leads to a set of three 1 Washington American Institute of Aeronautics and simultaneous nonlinear first-order partial differential equations, and Astronautics 1993 p. 347-354. refs the numerical simulations show that the investigation of poststall (ISABE 93-7031) Copyright transient behaviors, recoverability from rotating stall or surge, and The turbomachinery inviscid throughflow equation is the effects of compression system parameters and inlet flow fundamentally a statement of the conservation of tangential vorticity nonuniformity can be carried out through this method. It can be under the influence of various source terms. This equation is used to deal with rotating distortion too. It has been found that transformed from an equation for the stream function value in an both the inlet distortion amplitude and propagation speed have axial-radial coordinate system to an equation for streamline radial strong effect on the stability and poststall transient behaviors. position in an axial-position-streamfunction coordinate system. The The study of the effect of system parameters on recoverability transformed equation is shown to satisfy the compatibility equations shows that the B, Ic, and m all have little effect on the recoverability for incompressible flow across actuator disks and is solved by of the compression system, but alpha and compressor Gauss-Seidel iteration. The streamline throughflow method is axisymmetrical characteristics have a strong effect on it. Some shown to predict streamline radial position well for incompressible quantitative comparisons with available experimental results and flow through an annulus, over a fan nose bullet and through a some qualitative comparisons with test data are made. It shows single and a pair of twin actuator disks in an annulus. The method that the proposed model is very simple, accurate, and can be extended to compressible flows and flow within blade dependable. Author (revised) rows.

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A93-54009 These regions are identified by measuring the variations of flow THE EFFECTS OF END-BEND REGULATIONS OF velocity, angle and pressure. The impeller outlet flow is COMPRESSOR BLADE ON THE OUTLET FLOW FIELD characterized by defining certain non-dimensional parameters and GUOCHUAN WU and JILING XIN (Nanjing Univ. of Aeronautics correlating them with flow coefficient which are useful in the design and Astronautics, China) In ISABE - International Symposium of centrifugal impellers. on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington American Institute of Aeronautics and Astronautics 1993 p. 366-370. refs A93-54031 (ISABE 93-7033) Copyright PERFORMANCE IMPROVEMENT BY FORWARD-SKEWED The effects of different end-bend regulations of compressor BLADING OF AXIAL FAN MOVING BLADES blades on the outlet flow field of a compressor plane cascade NOBUYUKI YAMAGUCHI, TETSUO TOMINAGA, JYO MASUTANI are experimentally studied. A method of designing the end-bend (Mitsubishi Heavy Industries, Ltd., Takasago, Japan), and compressor blade is theoretically developed. The experimental MITSUSHIGE GOTO (Mitsubishi Heavy Industries, Ltd., Nagasaki, results show that increasing the end-bend angle and end-bend Japan) In ISABE - International Symposium on Air Breathing height restricts the high-loss region in the cascade corner. A new Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. secondary flow model is deduced, leading to a proposal to design 1 Washington American Institute of Aeronautics and end-bend compressor blades in terms of secondary vorticity theory. Astronautics 1993 p. 580-589. refs Reliable and optimal data for application of end-bend blades to (ISABE 93-7055) Copyright engineering practice are also provided. AIAA Forward-skewing, a new concept for reducing secondary losses in axial compressors, was experimentally applied to the moving A93-54023 blades of a low-speed axial fan. An optimized forward-skewed THE UNSTEADY FLOW PAST A SUPERSONIC SPLITTER blading confirmed an improvement of peak efficiency by nearly 1 PLATE percent and an enlarged iso-efficiency contour area for N. PEAKE and D. G. CRIGHTON (Cambridge Univ., United variable-pitch moving-blade operation. Some experimental and Kingdom) In ISABE - International Symposium on Air Breathing numerical investigations were conducted with respect to the effect Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. of the skewing on the internal flow behavior. They suggested that 1 Washington American Institute of Aeronautics and the forward skewing controlled the microstructure of the tip region Astronautics 1993 p. 511-513. refs flow, which might have reduced the secondary loss around the (ISABE 93-7047) Copyright tip. A theoretical analysis of unsteady vortex shedding by supersonic jet nozzles is presented which is relevant to the operation of A93-54033 powerplants for future generations of supersonic passenger aircraft. TIP CLEARANCE EFFECTS ON THE FLOW FIELD OF AN The model problem of a 2D rigid splitter plate with supersonic AXIAL TURBINE ROTOR BLADE CASCADE mean flow on one side and still air on the other and with a plane M. GOVARDHAN, N. VENKTRAYULU, and V. S. VISHNUBHOTLA acoustic wave incident on the splitter plate from infinity in the (Indian Inst. of Technology, Madras, India) In ISABE - International moving stream is considered. Emphasis is given to the precise Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. form of the unsteady behavior of the vortex sheet as it leaves the 20-24, 1993, Proceedings. Vol. 1 Washington American Institute trailing edge of the plate. AIAA of Aeronautics and Astronautics 1993 p. 598-608. refs (ISABE 93-7057) Copyright A93-54029 The flow through a blade passage and downstream of a blade TRANSONIC DISCHARGE FLOWS AROUND DIFFUSER VANES trailing edge was experimentally studied. Results are presented FROM A CENTRIFUGAL IMPELLER for four cases of tip clearance, including zero clearance, in the T. YAMANE (National Aerospace Lab., Tokyo, Japan), H. FUJITA, form of contours of local loss coefficient along with secondary and T. NAGASHIMA (Tokyo Univ., Japan) In ISABE - International velocity vectors, spanwise variation of pitchwise average total Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. pressure loss coefficient, surface static pressure distribution, and 20-24, 1993, Proceedings. Vol. 1 Washington American Institute the overall loss distribution along the axis of the cascade. The of Aeronautics and Astronautics 1993 p. 563-571. refs effect of clearance fluid on the passage flow and the growth of (ISABE 93-7053) Copyright the clearance vortex are reported. AIAA Complex flow structure within the interaction region of a centrifugal impeller and diffuser vanes due to discharged wake has been analyzed by fully unsteady 3D viscous calculation based A93-54034 upon a TVD code. Computational results revealed that the impeller EFFECTS OF WAKE INTERACTION OF TWO TURBINE discharge wake, inside of which speed is transonic, flows into CASCADES ON SECONDARY/TIP-LEAKAGE FLOWS AND diffuser vanes like traveling waves, but is immediately dissipated LOSSES before it reaches the vane throat. Time averaged results of fully A. YAMAMOTO (National Aerospace Lab., Chofu, Japan), R. unsteady calculation have been compared with the results of steady MURAO, Y. SUZUKI, and Y. AOI (Aoyama Gakuin Univ., Tokyo, stage calculation that uses pitchwise averaging at the rotor/stator Japan) In ISABE - International Symposium on Air Breathing intersection. Some experimental work has been also made and Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. compared with computational results. Author (revised) 1 Washington American Institute of Aeronautics and Astronautics 1993 p. 609-619. refs A93-54030 (ISABE 93-7058) Copyright CORRELATIONS FOR FLOW PROPERTY VARIATION AT In order to study the interaction of turbine stator and rotor OUTLET OF A CENTRIFUGAL IMPELLER blade rows, two different linear cascades were installed in series, S. RAMAMURTHY and K. MURUGESAN (National Aeronautical and the downstream cascade flows were measured in detail where Lab., Bangalore, India) In ISABE - International Symposium on the location of the upstream cascade was changed several times Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, relative to the downstream cascade. The results show that the Proceedings. Vol. 1 Washington American Institute of Aeronautics net total pressure loss generated in the downstream cascade and Astronautics 1993 p. 572-579. refs becomes maximum when the wakes of the upstream cascade (ISABE 93-7054) Copyright pass over the blade suction surfaces of the downstream cascade, Detailed measurements using hot-wire anemometery and high and that tip leakage loss generated in the downstream cascade frequency Kulite transducer at centrifugal impeller outlet reveal a does not depend on the relative location of both cascades. Wake complex nature of flow behavior across blade to blade pitch. The interaction with the endwall flow and secondary flows of the impeller outlet flow has two distinct regions called jet and wake. downstream cascade are also shown.

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A93-54044 H. USUI and A. YAMAMOTO (National Aerospace Lab., Chofu, RESEARCH AND DEVELOPMENT OF HIGH PRESSURE Japan) In ISABE - International Symposium on Air Breathing COMPRESSOR FOR SST AND HST ENGINE Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. K. CHIBA and K. KOBAYASHI (Ishikawajima-Harima Heavy 2 Washington American Institute of Aeronautics and Industries Co., Ltd., Tokyo, Japan) In ISABE - International Astronautics 1993 p. 949-954. refs Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. (ISABE 93-7092) Copyright 20-24, 1993, Proceedings. Vol. 1 Washington American Institute The paper describes effects of the inlet flow angle on the of Aeronautics and Astronautics 1993 p. 711-716. Research flows before, within and after a turbine rotor. An annular cascade supported by Agency of Industrial Science and Technology of and a fiber-type L2FV(Laser-2-Focus Velocimeter) were used as Japan refs the test turbine and the velocimeter. Flows were measured at a (ISABE 93-7068) Copyright total of eight measuring planes for three rotational speeds including The aerodynamic design of a high pressure compressor for a a speed corresponding to the design incidence. The test results SST/HST engine requires highly advanced technology in order to were shown using velocity vectors and velocity contours to clarify achieve the target of high performance. The objective of the present the effects of the inlet flow angle on the rotor internal flow fields. research work is to obtain aerodynamic design technology for achieving higher efficiency in the transonic compressor having five A93-54069 stages, a pressure ratio of 4.85 and a tip speed of 330 m/s. The 3D AND 2.5D VISCOUS FLOW COMPUTATIONS FOR AXIAL design of rotors and stators has been carried out by use of a FLOW TURBINE BLADES quasi-3D code and a 3D code to reduce losses. The blade element ANTOINE FOURMAUX, GILLES BILLONNET (ONERA, Chatillon, performance has been evaluated by the compressor rig test, while France), and BERTRAND PETOT (SNECMA, Moissy-Cramayel, the overall performance of the compressor has been obtained. France) In ISABE - International Symposium on Air Breathing This paper presents a discussion of the aerodynamic design and Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. the test results. Author (revised) 2 Washington American Institute of Aeronautics and Astronautics 1993 p. 955-964. Research supported by DRET A93-54051* National Aeronautics and Space Administration. and Service Technique des Programmes Aeronautiques refs Marshall Space Flight Center, Huntsville, AL. (ISABE 93-7093) Copyright NAVIER-STOKES ANALYSIS OF TURBINE FLOWFIELD AND The application of two methods for the computation of flows EXTERNAL HEAT TRANSFER in turbine channels is presented. They solve the unsteady sets of J. LUO and B. LAKSHMINARAYANA (Pennsylvania State Univ., quasi-3D and 3D full mass averaged Navier-Stokes equations in a University Park) In ISABE - International Symposium on Air relative frame of reference. The equations are solved by a classical Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, finite volume technique including an implicit stage. A mixing length Proceedings. Vol. 2 Washington American Institute of Aeronautics turbulence model that is adapted to 3D and complex geometries and Astronautics 1993 p. 766-780. refs is used. The calculations of several turbine rotor geometries (Contract NAS8-38867) including tip clearance are presented. The first geometry is a (ISABE 93-7075) Copyright stationary low-pressure airfoil cascade and the second one is an An explicit 2D Navier-Stokes code has been modified and used actual high-pressure turbine rotating row of airfoils. The influence to analyze the aerodynamics and heat transfer of a transonic of the leakage flow on the main flow is analyzed. The application turbine cascade. This code is based on a four-stage Runge-Kutta of the quasi-3D code to the calculation of high pressure inlet scheme. An algebraic Reynolds stress model (ARSM) and two guide vane including heat transfer with trailing edge cooling is versions of low Reynolds number (LRN) two-equation turbulence presented. The validation of the heat transfer calculation results models, Chien's (1982) LRN k-epsilon model and Coakley's (1983) vs experimental ones is presented. Two types of the trailing edge LRN q-omega model, have been employed in the computations. geometries are studied and compared in terms of cooling efficiency The surface pressure distributions and wake profiles are predicted and global losses. Author (revised) well by all the models. The k-epsilon model and the k-epsilon/ARSM model yield better predictions of heat transfer A93-54070 than the q-omega model. The k-epsilon/ARSM solutions show RECENT DEVELOPMENTS PERFORMED AT ONERA FOR THE some significant, though not dramatic, differences in the predicted SIMULATION OF 3D INVISCID AND VISCOUS FLOWS IN skin friction coefficients, heat transfer rates, and performance TURBOMACHINERY BY THE SOLUTION OF EULER AND parameters, as compared to the k-epsilon model. The predicted NAVIER-STOKES EQUATIONS semiwake width is consistent with the measurement and V. COUAILLIER (ONERA, Chatillon, France) In ISABE - correlation. Author (revised) International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington A93-54062* National Aeronautics and Space Administration. American Institute of Aeronautics and Astronautics 1993 p. Lewis Research Center, Cleveland, OH. 965-973. Research supported by DRET and SNECMA refs AERODYNAMIC INVERSE DESIGN AND ANALYSIS FOR A (ISABE 93-7094) Copyright FULL ENGINE This paper presents a synthesis of the numerical developments JOSE M. SANZ (NASA, Lewis Research Center, Cleveland, OH) performed in the Euler and Navier-Stokes solvers SESAME and In ISABE - International Symposium on Air Breathing Engines, CANARI during the last five years. The different physical models 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 used are recalled, and the numerical schemes developed in a cell Washington American Institute of Aeronautics and Astronautics vertex approach or in a cell centered approach are detailed. Some 1993 p. 895-902. typical applications obtained with the different methods (ISABE 93-7086) Copyright implemented in the solvers are presented to illustrate the A numerical design methodology for multistage turbomachinery capabilities of these solvers to simulate flows in turbomachinery. is being developed that minimizes the use of experimental data required in the design process. This approach is resulting in an A93-54071* National Aeronautics and Space Administration. efficient method of enlarging the design database for Lewis Research Center, Cleveland, OH. turbomachinery bidding. This capability has been demonstrated THREE-DIMENSIONAL FLOW ANALYSIS INSIDE for blade sections, and the goal is to extend it to fully three TURBOMACHINERY STAGES WITH STEADY AND UNSTEADY dimensional, multistage configurations. NAVIER-STOKES METHOD W. W. COPENHAVER, S. L. PUTERBAUCH (USAF, Aeropropulsion A93-54068 Lab., Wright-Patterson AFB, OH), and C. HAH (NASA, Lewis EXPERIMENTAL ANALYSIS OF TURBINE ROTOR FLOW AT Research Center, Cleveland, OH) In ISABE - International DESIGN AND OFF-DESIGN CONDITIONS Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept.

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20-24, 1993, Proceedings. Vol. 2 Washington American Institute Turbulence models adequate for the nozzle afterbody must still of Aeronautics and Astronautics 1993 p. 974-983. refs be developed. AIAA (ISABE 93-7095) Copyright This study presents a numerical method for solving the A93-54076 three-dimensional, Navier-Stokes equations for unsteady, viscous ON THE NUMERICAL SIMULATION OF THE flow through multiple turbomachinery blade rows. The method TWO-DIMENSIONAL FLOW FIELD AROUND A HYPERSONIC solves the fully three-dimensional Navier-Stokes equations with AIR-INTAKE-COMPRESSIBILITY EFFECTS an implicit scheme which is based on a control volume approach. G. FRESKOS, D. VANDROMME, and H. H. MINH (Centre Europeen A two-equation turbulence model with a low Reynolds number de Recherche et de Formation Avancee en Calcul Scientifique, modification is employed in the present study. A third-order accurate Toulouse, France) In ISABE - International Symposium on Air upwinding scheme is used to approximate convection terms while Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, a second order accurate central difference scheme is used for Proceedings. Vol. 2 Washington American Institute of Aeronautics the discretization of viscous terms. A second-order accurate and Astronautics 1993 p. 1023-1032. Research supported by scheme is employed for the temporal discretization. The numerical SNECMA and EEC refs method is applied to study the unsteady flow field of a subsonic (ISABE 93-7100) Copyright turbine stage and the unsteady flow field inside a transonic, The flow field around a hypersonic air-intake is computed. The high-through-flow, axial compressor stage. The stage calculation Reynolds-averaged Navier Stokes equations are solved. A is performed by coupling the stator and the rotor flow fields at two-equation turbulence model simulates the turbulent character each time step through an over-laid grid. of the flow field. The numerical results are compared with available experimental data. Modifications to account for the compressibility A93-54074 effects on the turbulent field are presented. Relative results and OPTIMIZATION OF AFTERBODIES AND ENGINE NOZZLE BY expectations are also discussed. USING CFD METHODS G. ROLLIN, T. MAUFFRET, M. AH-FA, and E. MAINGRE (SNECMA, A93-54078 Moissy-Cramayel, France) In ISABE - International Symposium DESIGN OF AIR INTAKES AND NOZZLES FOR TRANSONIC on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, ROTATIONAL FLOWS Proceedings. Vol. 2 Washington American Institute of Aeronautics FRANCESCO LAROCCA and LUCA ZANNETTI (Torino, and Astronautics 1993 p. 1003-1012. Research supported by Politecnico, Turin, Italy) In ISABE - International Symposium on Direction des Programmes de I'Aviation Civile refs Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, (ISABE 93-7098) Copyright Proceedings. Vol. 2 Washington American Institute of Aeronautics In the present and future aircrafts, the demands of efficiency and Astronautics 1993 p. 1042-1048. refs are such that it is and it will be impossible to reach the aircraft (ISABE 93-7102) Copyright aerodynamic optimum just with experimental studies. In this context In this paper a numerical method for solving inverse problem during the past decade many efforts have been expended to is presented. It refers to a compressible, two-dimensional, inviscid develop numerical methods able to reproduce the phenomena rotational flow governed by the Euler equations. The pressure occurring in the engine flow field. This paper presents a review of distribution is prescribed along the wall as design data and we the afterbody and engine nozzle methods used'to optimize these inquire for the geometry that it assumes by considering the wall components. In this area, two paths are considered. Firstly the itself as impermeable and movable. The shape of the wall is overall geometry must be designed. The aim of this first step is obtained at the end of the transient generated by an initial guessed to make sure that the general characteristics of the nozzle and configuration and described in time by the unsteady Euler afterbody are correct. A large number of geometries has to be equations. The numerical procedure for solving Euler equations is calculated in order to reach the objective. So there is a need for based on a time-dependent technique and uses an upwind finite a code able to calculate at low cost the entire flow field around volume approximation. Some numerical examples, which refer to 2D or axisymmetric geometries. Therefore we have developed a transonic flow in 2-D nozzles and diffusers, are presented. method of computation based on an automatic mesh generator connected with CATIA CAO system and a CFD method solving A93-54079 turbulent Navier-Stokes 2D equations. This method permits us to A STUDY OF THE STABILITY OF VORTICAL STRUCTURES IN get a first estimation of mass flow coefficient and thrust coefficient SUPERSONIC INLETS of nozzle and afterbody drag. Thus, this methodology was applied R. MARSILIO (Torino, Politecnico, Turin, Italy) In ISABE - to optimize supersonic engine nozzle design with axisymmetric International Symposium on Air Breathing Engines, 11th, Tokyo, geometry to engine a future supersonic aircraft. These examples Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington show the benefit of using intensively computational method for American Institute of Aeronautics and Astronautics 1993 p. nozzle and afterbody design. Author (revised) 1051-1061. refs (ISABE 93-7103) Copyright A93-54075 The stability of the vortical solutions of the inviscid, supersonic ADVANCED AERODYNAMIC AIRFRAME/NOZZLE conical corner flows, is investigated. Such flow configurations are INTEGRATION typical of supersonic inlet flows. Complex shock interactions DOUGLAS L BOWERS (USAF, Wright Lab., Wright-Patterson AFB, appear, with the formation of vorticity field in the corner region OH) In ISABE - International Symposium on Air Breathing Engines, and the vorticity itself converging into spiral singularity. Symmetric 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 or asymmetric flow configurations are generated within symmetric Washington American Institute of Aeronautics and Astronautics corners. The investigation is carried out by a numerical technique 1993 p. 1013-1022. refs based upon a space-marching procedure with a finite volume (ISABE 93-7099) approximation. A high order accuracy scheme is introduced founded A development status evaluation is presented for the on ENO scheme criteria. Numerical results are presented and computational and analytical methods that are to be used to discussed. define complex, next-generation fuselage aft-section/engine nozzle integrations for high performance aircraft. For A93-54080 nonviscous-dominated nozzle flows, the Euler flows with 2D and BOUNDARY CONDITIONS FOR UNSTEADY SUPERSONIC 3D adaptive unstructured grids are used as design tools. For INLET ANALYSES viscous flows, the Navier-Stokes codes are noted to still suffer DAVID W. MAYER and GERALD C. PAYNTER (Boeing Commercial from longstanding problems. Special experimental test cases must Airplane Group, Seattle, WA) In ISABE - International Symposium also be obtained as needed, in order to validate CFD methods. on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993,

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Proceedings. Vol. 2 Washington American Institute of Aeronautics a propulsion system using subsonic combustion. The supersonic and Astronautics 1993 p. 1062-1070. refs part of the inlet was simulated for inviscid, laminar viscous, and (ISABE 93-7104) Copyright turbulent viscous flow using an implicit upwind TVD finite difference New bleed and compressor face boundary conditions have method. The structured grids were adapted to the flow to obtain been developed to improve the accuracy of unsteady supersonic a good spatial resolution of the flow phenomena such as shocks inlet calculations. The new bleed boundary condition represents and shock boundary layer interactions. The results of the Euler changes in the bleed hole discharge coefficient with local flow simulations compare well with results obtained with a method of conditions; the local bleed flow rate can more than double as a characteristics. The results of the turbulent Navier-Stokes shock moves forward over a bleed band. This locally rapid increase simulations show that no separation occurs in the supersonic part. in bleed flow affects the motion of the normal shock and thus the The wall pressure agrees well with experimental results. Additional stability margin of the inlet. The new compressor face boundary to these results, first results obtained by using an explicit finite condition accounts for changes in the unsteady flow conditions at volume method based on unstructured grids are presented. It is the compressor face by specifying the compressor face corrected shown that the unsteady, local adaption used here is well suited mass flow or Mach number either as a constant or as a linear for the simulation of complex, hypersonic flow fields. The second function of the stagnation conditions. This boundary condition part of the numerical investigation is focused on the simulation of represents the flow at the compressor face more realistically than the complete inlet, i.e., supersonic plus subsonic part. The traditional fixed static pressure or mass flow conditions. Results time-accurate development of a steady flow field as well as the are reported for an Euler analysis of the dynamic response of an development of unstart for an inviscid flow is discussed. inlet normal shock to changes in the compressor face corrected Author (revised) mass flow. The dynamic response with both 20- and 90-deg throat bleed hole angles are reported. These results indicate that an A93-54087 extra margin of stability for the inlet is obtained with 90-deg bleed INFLUENCE OF CHEMICAL KINETICS EFFECTS IN NOZZLES holes because the increase in bleed flow rate as the shock moves SHAPE DESIGN forward over a bleed band is much larger for 90-deg holes than M. ONOFRI, B. FAVINI, and R. PACIORRI (Roma I, Univ., Rome, for 20-deg holes. Author (revised) Italy) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. A93-54082 2 Washington American Institute of Aeronautics and A STUDY ON MACH 3 TWO-DIMENSIONAL MIXED Astronautics 1993 p. 1143-1152. Research supported by Fiat COMPRESSION AIR-INTAKES Aviazione and ASI refs KIMIO SAKATA, RYOJI YANAGI, SHIGEMI SHINDO, AKIRA (ISABE 93-7112) Copyright MURAKAMI (National Aerospace Lab., Tokyo, Japan), SHINJI Theoretical and experimental studies on axisymmetric nozzles HONAMI (Tokyo Science Univ., Japan), ATSUSHIGE TANAKA, have shown that two dimensional flow effects have an important and KAZUO SHIRAISHI (Ishikawajima-Harima Heavy Industries Co., role on the nozzle performances. These effects are enhanced Ltd., Tokyo, Japan) In ISABE - International Symposium on Air when nozzles operate in the typical conditions of aerospace Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, applications, since chemical reactions of dissociation and atomic Proceedings. Vol. 2 Washington American Institute of Aeronautics recombination occur, which may be significantly influenced by the and Astronautics 1993 p. 1081-1089. Research supported by radial gasdynamic phenomena. In this paper the influence of the Science and Technology Agency, Agency of Industrial Science flowfield behavior on the finite rate chemical kinetics is analyzed and Technology, and New Energy and Technology Development for Single Expansion Ramp Nozzles (SERN), which display strong Organization refs unsymmetric flowfields. The analysis is focused on the throat region, (ISABE 93-7106) Copyright where these effects are stronger, in order to indicate the causes The supersonic air-intakes for the propulsion system of a vehicle of the flow behavior and provide qualitative evaluations of its flyable at supersonic speed are being studied. Considering the interaction with chemical kinetics, and consequently of their requirement for high Mach number capability, a configuration of influence on the nozzle performances. two-dimensional type with rectangular cross section and mixed compression system was selected. Several wind tunnel models A93-54093 were developed and tested in a 1m x 1m Mach 4 wind tunnel at NUMERICAL AND EXPERIMENTAL STUDY ON TWO- AND National Aerospace Laboratory as the main part of the study. THREE-DIMENSIONAL SUPERSONIC FLOW FIELD WITH This paper presents the results of the wind tunnel tests on these HYDROGEN INJECTION models designed for Mach 3. The test results with the simplified KAZUHIKO YOKOTA and SHOJIRO KAJI (Tokyo Univ., Japan) small scale models are also presented as the supplementary data. In ISABE - International Symposium on Air Breathing Engines, The test results and the model modification for the performance 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 improvement show the importance of establishing the shock Washington American Institute of Aeronautics and Astronautics systems, the optimized bleed to eliminate shock induced boundary 1993 p. 1202-1213. refs layer separation and the improved passage of the subsonic diffuser (ISABE 93-7118) Copyright for higher pressure recovery and stability. The side wall shape Nonreacting supersonic flow fields with sonic injection are effects the pressure recovery and the mass flow characteristics. investigated. As regards 2D investigations, three injection methods are examined by numerical analysis. The highest mixing efficiency A93-54083 is obtained by means of parallel injection. But the results show NUMERICAL SIMULATION OF A TWO-DIMENSIONAL that sufficient mixing efficiencies cannot be obtained by means of SUPERSONIC MIXED-COMPRESSION INLET any injection method in a 2D flow. As regards 3D investigations, V. HANNEMANN, M. GIRKE, K. HANNEMANN, and TH. SONAR a perpendicular air injection from a finite length slit is examined (DLR, Inst. fuer Stroemungsmechanik, Goettingen, Germany) In by experimental measurement and numerical analysis. Two slit ISABE - International Symposium on Air Breathing Engines, 11th, angle cases of 90 deg and 45 deg are treated. Flow visualization Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 by Schlieren pictures and 3D measurement of pitot pressure are Washington American Institute of Aeronautics and Astronautics performed. In addition, a numerical analysis simulating the 1993 p. 1090-1100. refs experimental condition is performed. In the numerical analysis, (ISABE 93-7107) Copyright the main flow air and the injected air are treated as different The intention of the paper is to show the potentiality of using species. The numerical results fairly agree with the experimental highly adapted grids for hypersonic flow simulations. For this data both qualitatively and quantitatively. All the results show that purpose a generic 2D supersonic mixed compression inlet was the 3D flow effect appears when the injection slit is finite, especially investigated. Here only the results of the different adaption near the slit ends. It is concluded that the three-dimensionality of strategies are discussed. The inlet has been designed as part of the flow enhances mixing. Author (revised)

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A93-54099 breakdown or stall occurring in any interactive boundary-layer CHARACTERISATION OF CONVENTIONAL AND solution at a finite value of the controlling parameter. CONTROLLED DIFFUSION STATOR BLADES IN A Author (revised) TRANSONIC COMPRESSOR STAGE Q. H. NAGPURWALA, B. R. PAI, and S. A. GURUPRASAD (National A93-54314 Aerospace Lab., Bangalore, India) In ISABE - International STUDY ON FLOW FIELD AROUND SLENDER DIAMOND CONE Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. TRAVELING AT HYPERSONIC SPEED 20-24, 1993, Proceedings. Vol. 2 Washington American Institute MASATOMI NISHIO and MUTSUO KOTAKE Japan Society of of Aeronautics and Astronautics 1993 p. 1263-1271. refs . Mechanical Engineers, Transactions B (ISSN 0387-5016) vol. (ISABE 93-7124) Copyright 59, no. 562 June 1993 p. 1925-1931. In JAPANESE refs This paper describes the design and performance evaluation Copyright of a controlled diffusion aerofoil (CDA) stator in a transonic axial This paper proposes a method to analyze the flow field around compressor stage. The overall and blade element performance, a slender diamond cone traveling at hypersonic speed. We used determined experimentally, as well as the results of computational the equivalence principle to analyze the problem. In order to apply flow analysis are compared with those obtained with a NACA the equivalence principle, we assumed that the flow field around double circular arc (DCA) stator tested with the same transonic a slender diamond cone traveling at hypersonic speed coincides rotor. The design of the CDA stator, having a low loading level with the two-dimensional unsteady flow field around a diamond similar to the conventional DCA stator, was based upon a geometric shape body expanding at a constant rate. Using conformal mapping, procedure, initially developed by Lubenstein, et al. (1984) but built we solved the flowfield to satisfy the boundary condition around into a suitable FORTRAN program during the present investigations. the expanding body. Using this analysis, the velocity distribution The surface Mach number profiles on CDA stator clearly indicated and the streamline around the body became clear. Consequently, forward loading and were typical of this class of aerofoils confirming we obtained the flow field around a slender diamond cone traveling the applicability of this geometric procedure for the design of CDA at hypersonic speed. Author (revised) blading. Author (revised) A93-54324* National Aeronautics and Space Administration. A93-54105 Lewis Research Center, Cleveland, OH. AERODYNAMICS OF TURBINE BLADES WITH MIXING OF MULTIPLE JETS WITH A CONFINED SUBSONIC TRAILING-EDGE DAMAGE - MEASUREMENTS AND CROSSFLOW COMPUTATIONS JAMES D. HOLDEMAN (NASA, Lewis Research Center, Cleveland, S. A. SJOLANDER, D. ISAACS, and W. A. KLEIN (Carleton Univ., OH) Progress in Energy and Combustion Science (ISSN Ottawa, Canada) In ISABE - International Symposium on Air 0360-1285) vol. 19, no. 1 Feb. 1993 p. 31-70. refs Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Copyright Proceedings. Vol. 2 Washington American Institute of Aeronautics An account is given of experimental and computational results and Astronautics 1993 p. 1327-1334. Research supported by on the mixing of single, double, and opposed rows of jets GasTOPS, Ltd. and Univ. Research Incentives Fund of Ontario characterized by an either isothermal or variable temperature refs mainstream in a confined subsonic crossflow; these flow (ISABE 93-7130) Copyright configurations are typical of gas turbine combustor dilution The effect of trailing-edge damage on the aerodynamics of chambers. It is established that the momentum-flux ratio is the turbine blades is examined experimentally and computationally. most significant flow variable. Combinations of flow and geometry The work is related to engine health monitoring. Measurements yielding optimum mixing were identified from experimental and have been made in a low-speed large-scale cascade which includes computational results. The orifice spacing and momentum-flux one blade with a semi-circular cutout to simulate trailing-edge relationships affected jet structure, which was significantly different damage. The blade losses and trailing-edge deviation were between jets injected from the inner wall of a turn and those measured for cutouts of 15 and 25 percent of the blade chord injected from the outer wall. AIAA and the incidence was varied through a range of +/- 10 degrees around the design value. The flow-turning ability of the blade was A93-54347 found to be affected more than its total pressure losses. The THE FLUID PHYSICS OF PARACHUTE INFLATION same flow was also modelled using the three-dimensional CARL W. PETERSON (Sandia National Labs., Albuquerque, NM) Navier-Stokes code of Dawes, with encouraging results. Physics Today (ISSN 0031-9228) vol. 46, no. 8, pt. 1 Aug. 1993 p. 32-39. Research supported by DOE refs A93-54266 Copyright SEPARATION PHENOMENON IN A HYPERSONIC FLOW WITH The physics of the motion of the parachute and the surrounding STRONG WALL COOLING - SUBCRITICAL REGIME air as the parachute emerges from the payload, inflates and C. N. ZHIKHAREV (TsAGI, Zhukovski, Russia) Theoretical and decelerates the payload is described. An attempt is made to model Computational Fluid Dynamics (ISSN 0935-4964) vol. 4, no. 5 the important event numerically to enable parachute designers to 1993 p. 209-226. refs use computers instead of trial-and-error flight tests. It is noted Copyright that the complexity of the parachute inflation problem suggests This paper is concerned with a hypersonic flow past a cooled that the development of parachute inflation technology will not be curved wall. The separation phenomenon at high Reynolds numbers completed soon. AIAA is described using an interactive boundary-layer approach. For a problem of this type, a distinction must be made between two regimes subject to whether the global interaction between the 03 boundary layer and the external flow is strong or weak. This depends on a hypersonic interaction parameter chi is approximately equal to MeRe exp -1/2: if chi is small, the interaction is weak; if AIR TRANSPORTATION AND SAFETY it is large, the interaction is strong. The present study is applied to a flow with a weak global interaction regime when chi goes to Includes passenger and cargo air transport operations; and aircraft 0. There are three principal motivations for the study. First, the accidents. problem of hypersonic boundary-layer separation is obviously of great practical interest. Second, the desire to demonstrate that marginal separation theory may be successfully applied to the A93-54288 description of a hypersonic flow separation. Third, there is interest ARCTIC ENVIRONMENT - HELICOPTER OPERATIONS IN in verifying the theoretical prediction by Smith (1988) of a local COLD CLIMATES

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TORE SKAAR (Royal Norwegian Air Force, Bardufoss Air Station, though modern technology has made considerable progress with Norway) In Helicopter operations in severe environments; the introduction of image intensifiers and thermal images, the main Proceedings of the Conference, London, United Kingdom, June 4, problems remain to be associated with human factors and realistic 1992 London Royal Aeronautical Society 1992 p. 1.1-1.11. training. AIAA Copyright Difficulties associated with helicopter operations in the Arctic environment are described using the Norwegian experience from 04 missions to the Arctic Islands of Svalbard. Different phases of a flight in severe climate conditions including preflight, start-up and take off, en route, and approach and landing are considered. AIRCRAFT COMMUNICATIONS AND NAVIGATION AIAA Includes digital and voice communication with aircraft; air navigation A93-54289 systems (satellite and ground based); and air traffic control. OPERATING HELICOPTERS IN A DEMANDING ENVIRONMENT - MOUNTAIN FLYING/HIGH EVALUATIONS TONY LOETSCHER (Swissair, Zurich, Switzerland) In Helicopter A93-52881 National Aeronautics and Space Administration. Ames operations in severe environments; Proceedings of the Conference, Research Center, Moffett Field, CA. London, United Kingdom, June 4, 1992 London Royal PASSIVE RANGE ESTIMATION FOR ROTORCRAFT Aeronautical Society 1992 p. 2.1-2.5. LOW-ALTITUDE FLIGHT Copyright B. SRIDHAR, R. SUORSA, and B. HUSSIEN (NASA, Ames Dangers associated with mountain flying are discussed focusing Research Center, Moffett Field, CA) Machine Vision and on helicopter performance at increased altitude, the mountain winds Applications (ISSN 0932-8092) vol.6 1993 p. 10-24. Previously effect, optical illusions, avalanches, rock falls, glaciers, power cable announced in STAR as N92-10003 refs and lift lines. It is concluded that the state-of-the-art helicopters (Contract RTOP 505-66-11) equipped with a hoist winch are capable to hover at high altitudes Copyright and to conduct air rescues at any slope in the Alps. AIAA The automation of rotorcraft low-altitude flight presents challenging problems in control, computer vision and image A93-54290 understanding. A critical element in this problem is the ability to ROYAL NAVY HELICOPTER OPERATIONS IN THE MARITIME detect and locate obstacles, using on-board sensors, and modify ENVIRONMENT the nominal trajectory. This requirement is also necessary for the PAUL G. MILLER (Ministry of Defence, Directorate of Naval safe landing of an autonomous lander on Mars. This paper Warfare, London, United Kingdom) In Helicopter operations in examines some of the issues in the location of objects using a severe environments; Proceedings of the Conference, London, sequence of images from a passive sensor, and describes a Kalman United Kingdom, June 4, 1992 London Royal Aeronautical filter approach to estimate the range to obstacles. The Kalman Society 1992 p. 3.0-3.7. refs filter is also used to track features in the images leading to a Copyright significant reduction of search effort in the feature extraction step The current status of Royal Navy helicopters and particular of the algorithm. The method can compute range for both straight areas of operational concern and technical challenge are line and curvilinear motion of the sensor. A laboratory experiment considered. Particular attention is given to environmental conditions was designed to acquire a sequence of images along with sensor for launch and recovery, landing and recovery aids, helicopter motion parameters under conditions similar to helicopter flight. reliability, and future trends in the development of the Merlin Range estimation results using this imagery are presented. helicopter. AIAA A93-53172 A93-54291 A VISION-BASED METHOD FOR AUTONOMOUS LANDING ENVIRONMENTAL EFFECTS OF OPERATIONS DURING HUSEYIN H. YAKALI and DANIEL RAVIV (Florida Atlantic Univ., DESERT SHIELD/DESERT STORM Boca Raton) In Mobile robots VI; Proceedings of the Meeting, JAMES A. RAY (U.S. Army, Aviation Systems Command, Saint Boston, MA, Nov. 14, 15, 1991 Bellingham, WA Society of Louis, MO) In Helicopter operations in severe environments; Photo-Optical Instrumentation Engineers 1992 p. 205-216. Proceedings of the Conference, London, United Kingdom, June 4, refs 1992 London Royal Aeronautical Society 1992 p. 4.1-4.8. Copyright Copyright This paper presents eight visual cues to be used as part of a The environmental problems, the initiatives taken during the control loop for autonomous landing. The idea is based on fixating Operation Desert Shield/Desert Storm, and the overall results of the camera at the vanishing point of the projection of the runway these efforts are discussed. The Operation Desert Shield/Desert in the image. 2-D geometrical cues are used to derive the visual Storm employs about 9000 aircraft with about a fourth of these cues. The visual cues that are extracted are the relative location aircraft involved in southwest Asia operations. This vast deployment of the camera to the runway in terms of the runway width, and sustainment mission within the severe desert environment orientation of the camera, and relevant angles such as glide slope represented both a significant challenge to the technology as well angle. as to the support systems. The operational readiness rates were much higher during this operation than in peacetime. AIAA A93-53603 A REACTIVE APPROACH FOR DISTRIBUTED AIR TRAFFIC A93-54293 CONTROL ROYAL AIR FORCE SUPPORT HELICOPTERS - NIGHT KARIM ZEGHAL (ONERA, Chatillon; Paris VI, Univ., France) and OPERATIONS JACQUES FERBER (Paris VI, Univ., France) ONERA, TP no. R. A. FORSYTHE (RAF Odiham, Basingstoke, United Kingdom) 1993-83 1993 11 p. International Conference on Artificial In Helicopter operations in severe environments; Proceedings of Intelligence, Expert Systems, and Natural Language, 13th, Avignon, the Conference, London, United Kingdom, June 4, 1992 London France, May 24-28, 1993 refs Royal Aeronautical Society 1992 p. 6.1-6.6. (ONERA, TP NO. 1993-83) Copyright In this paper, we explore a fully decentralized approach for air The night capabilities of the Royal Air Force battlefield helicopter traffic, which allows to define the principle of a ground-based air are reviewed. The use of night vision goggles complements the traffic control system as well as the logic of an airborne collision conventional skills of an aircrew and makes it possible to avoidance system. The distributed conflict resolution mechanism significantly increase the night capabilities. It is concluded that we present is based on symmetrical force fields method, which

1190 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE allows an efficient coordination of avoiding actions. Experimental The system is designed to be capable of full flight-envelope partial results highlight the reliability of the conflict resolution method. As model-following and employs new features to reduce checkout opposed to prior approaches used in Robotics or in distributed Al and calibration time. These include computer-flown test input to solve the coordination problem, this mechanism requires no sequences and on-line parameter identification. This paper communication or negotiation between agents. In the view of a describes the aircraft, its software development system, real-time ground-based system, we also propose the principle of a distributed computer hardware, user interface, and advanced inflight simulation implementation of the resolution mechanism, which made the and calibration methods. A 'quick response' inflight simulation system highly tolerant to processors losses. capability is now available to the aerospace industry which may be used as a tool in the development of new aircraft and flight A93-53604 control systems. CRAASH - A COORDINATED COLLISION AVOIDANCE SYSTEM A93-52937 KARIM ZEGHAL (ONERA, Chatillon; Paris VI, Univ., France) and NONLINEAR DEFORMATION MECHANICS OF MULTILAYER JACQUES FERBER (Paris VI, Univ., France) ONERA, TP no. TRANSPARENCY ELEMENTS - SOME CALCULATION 1993-84 1993 6 p. ESM'93, Lyon, France, June 7-9, 1993 RESULTS [NELINEJNAYA MEKHANIKA DEFORMIROVANIYA refs MNOGOSLOJNYKH EHLEMENTOV OSTEKLENIJ - (ONERA, TP NO. 1993-84) NEKOTORYE REZULTATY RASCHETOV] This paper defines the logic of an airborne collision avoidance A. I. KALASHNIKOV, V. I. PAJMUSHIN, and V. A. FIRSOV system based on symmetrical force field methods. The mechanism Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 1 1993 p. 3-5. ensures the avoidance of any forms of intruders and particularly, In RUSSIAN it coordinates the avoidance actions between aircraft equipped Copyright with this collision avoidance system. As opposed to prior Solutions are presented for a series of problems concerned approaches used in robotics or in distributed Al, this coordination with the stress-strain state of multilayer aircraft transparencies. model requires no communication or negotiation between aircraft. The effect of the geometrical and physical nonlinearity of the Experimentation has highlighted the coordination mechanism problems on the solution results is estimated. Attention is also resilience or reliability in high intruder density and high dynamics given to the effect of the deformability of the fastening elements conditions. This approach also depicts the principle of a distributed on the stress-strain state of a multilayer porthole. AIAA air traffic control system. A93-52954 A93-53866 ESTIMATION OF THE EFFECT OF THE LONGITUDINAL FAULT TOLERANT NAVIGATION FOR AIRCRAFT LANDING MOMENT DUE TO THE ENGINE THRUST ON THE MASS OF A HAN-GUO ZHANG and HONG-YUE ZHANG (Beijing Univ. of SUBSONIC PASSENGER AIRCRAFT [OTSENKA VLIYANIYA Aeronautics and Astronautics, China) Acta Aeronautica et PRODOL'NOGO MOMENTA OT TYAGI DVIGATELEJ NA Astronautica Sinica (ISSN 1000-6893) vol. 14, no. 1 Jan. 1993 MASSU DOZVUKOVOGO PASSAZHIRSKOGO SAMOLETA] p. A104-A108. In CHINESE refs V. P. GOGOLIN Aviatsionnaya Tekhnika (ISSN 0579-2975) no. This paper studies a sensor fault-tolerant system for an aircraft 1 1993 p. 72-74. In RUSSIAN refs in a microwave landing system environment. The objective of the Copyright fault tolerant system is to detect failures in .navigation aid An analysis is presented which demonstrates the importance instruments and on-board sensors and to provide reliable estimates of considering changes in the longitudinal moment due to the for the aircraft states in the possible presence of these sensor engine thrust when changing the location of engines on an aircraft. malfunctions. A failure detection and isolation algorithm is used to Thus, changes in the longitudinal moment should be considered detect and isolate the navigation aid instrument failures. The in addition to changes in the mass of the wing, mass of the nonlinear filtering technique using separated-bias estimation is used fuselage, drag coefficient, and lifting force when relocating the to generate the state estimation of the aircraft. State estimates engines from the fuselage to the wing. A hypothetical passenger are used by an automatic guidance and control system to land aircraft with characteristics similar to those of the Tu-154 aircraft the aircraft along a prescribed path. Author (revised) is examined as an example. AIAA

A93-53405 05 INNOVATIVE BAGGING TECHNIQUES ON A COMPOSITE P-51 MUSTANG REPLICA MURDO CAMERON (Flight Training Devices, Gardena, CA), RAY AIRCRAFT DESIGN, TESTING AND CULL (Dow Corning Corp., Midland, Ml), and BRUCE MENK (KR PERFORMANCE Anderson, Santa Ana, CA) In International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals Includes aircraft simulation technology. Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 Covina, CA Society for the Advancement of Material and Process Engineering 1992 p. T366-T374. A93-52691# Copyright A RAPID PROTOTYPING SYSTEM FOR INFLIGHT An account is given of the innovative mold-bagging techniques SIMULATION USING THE CALSPAN LEARJET 25 that are being used to fabricate the two fuselage halves of a S. A. BUETHE and P. R. DEPPE (Calspan Corp., Buffalo, NY) In composite fighter-replica aircraft. The bag was formed by means AIAA Flight Simulation Technologies Conference, Monterey, CA, of a new castable, a high-tear strength translucent silicone Aug. 9-11,1993, Technical Papers Washington American Institute elastomer that is applied directly to the mold tool; reinforcing fabric of Aeronautics and Astronautics 1993 p. 320-323. is employed to improve the durability of the bag, which is 10 m in (AIAA PAPER 93-3606) Copyright length and 3 m in width; its structure forms not only the fuselage Inflight simulations of new aircraft and/or flight control systems shell, but its longerons and engine mounts, as well. The bag's often require considerable preparation time and expense. Our castable silicone elastomers cure at room temperature. AIAA objective was to develop a new inflight simulator with a 'quick response' capability. The Calspan Learjet 25 inflight simulator has A93-53721 been upgraded to meet this objective through implementation of ANALYSIS OF SPATIAL MOTION DYNAMICS OF A a graphical block diagram programming system with automatic HELICOPTER FOR VARIOUS MODELS OF THE INDUCED code generation. The simulation code is targeted to a set of floating VELOCITY FIELD point digital signal processors (DSP) which operate in parallel. Z. DZYGADLO and G. KOWALECZKO (Military Univ. of

1191 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

Technology, Warsaw, Poland) Journal of Technical Physics (ISSN leakage test is discussed. Charts are established for practical 0324-8313) vol. 34, no. 2 1993 p. 119-143. refs use. Copyright Problems of dynamics of spatial motion of a helicopter are A93-54077 considered making use of the three models of induced velocity WIND TUNNEL TESTS OF THE MODEL OF field over the region of the main rotor, which are known from the INTAKE-AIRFRAME INTEGRATION literature. They are: the uniform velocity distribution and the Glauert TAKESHI ITO, AKIRA MURAKAMI, SHIGEMI SHINDO, KIMIO and Mangier-Squire models, in which the velocity depends on the SAKATA, JUNNICHI NODA (National Aerospace Lab., Tokyo, azimuth and the radius. The natural motions of the helicopter Japan), ATSUSHIGE TANAKA, and KAZUO SHIRAISHI have been studied for the three models of induced velocity (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan) mentioned above, the couplings between the longitudinal and lateral In ISABE - International Symposium on Air Breathing Engines, motions being and being not taken into consideration. 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington American Institute of Aeronautics and Astronautics A93-53769* National Aeronautics and Space Administration. 1993 p. 1033-1041. refs Hugh L. Dryden Flight Research Facility, Edwards, CA. (ISABE 93-7101) Copyright FLIGHT RESEARCH SIMULATION TAKES OFF A series of Mach 3 tests of the model for the intake-airframe LAWRENCE J. SCHILLING and DALE A. MACKALL (NASA, Flight integration problem was performed in NAL's M4 supersonic wind Research Center, Edwards, CA) Aerospace America (ISSN tunnel, and the data were analyzed aerodynamically. The model 0740-722X) vol. 31, no. 8 Aug. 1993 p. 18-21. of the air-intake with diverter was installed on the bottom surface Copyright of the airframe which was designed for Mach 3 flight. Schlieren The simulation configurations used in research flight test, method and oil-flow technique were applied for considering the including nonreal-time, real-time all-software, hardware-in-the-loop, flow structure around and on the model. Some qualitative and iron bird, and aircraft-in-the-loop, are reviewed. It is concluded quantitative considerations on the effects of the existence of the that progress in simulation technology will demonstrate new air-intake to the airframe aerodynamic coefficients were made clear, concepts, evaluate designs, enhance the quality of flight test, and and influence of the forebody boundary layer to the air-intake minimize flight risks. AIAA was also analyzed. Some recommendations for future study were made. Author (revised) A93-53771 ENGINEERING SIMULATORS ENHANCE 777 DEVELOPMENT DON BROOKS (Boeing Co., Seattle, WA) Aerospace America 06 (ISSN 0740-722X) vol. 31, no. 8 Aug. 1993 p. 30-32, 41. Copyright AIRCRAFT INSTRUMENTATION A new approach to the use of engineering simulators in the new airplane's flight deck design and in its crew interface validation Includes cockpit and cabin display devices; and flight instruments. is described. The approach is based on two simulators: the first is dedicated to flight deck development and design, and the second is an integration device with the flexibility to support development. A93-52994 An engineering simulator that is placed in service 50 months ahead SENSORS WITH CENTROID BASED COMMON SENSING of certification and in-context evaluations and exhaustive airline SCHEME AND THEIR MULTIPLEXING reviews enable the 777 flight deck engineering team to get the E. BERKCAN, J. TEIMANN, and G. BROOKSBY (GE Corporate design correct the first time. AIAA Research and Development Center, Schenectady, NY) In Fiber optic and laser sensors X; Proceedings of the Meeting, Boston, A93-53772 MA, Sept. 8-11, 1992 Bellingham, WA Society of Photo-Optical REMOVING THE RISK FROM ROTORCRAFT TESTING Instrumentation Engineers 1993 p. 362-370. refs MICHAEL FERRANTI (Sikorsky Aircraft, Stratford, CT) Aerospace Copyright America (ISSN 0740-722X) vol. 31, no. 8 Aug. 1993 p. The ability to multiplex sensors with different measurands but 34-37. with a common sensing scheme is of importance in aircraft and Copyright aircraft engine applications; this unification of the sensors into a Full mission simulations aimed at testing high-risk rotorcraft common interface has major implications for weight, cost, and designs in low-risk environments are discussed which are based reliability. A new class of sensors based on a common sensing on engineering development simulation (EDS) as a support tool. scheme and their E/O Interface has been developed. The approach The networked simulations complement operational test and detects the location of the centroid of a beam of light; the set of evaluation by testing contract exit criteria, evaluating proposed fiber optic sensors with this sensing scheme include linear and flight test profiles prior to actual flight test, and enabling crews to rotary position, temperature, pressure, as well as duct Mach design the proper tactics, techniques, and procedures for new number. The sensing scheme provides immunity to intensity weapons systems before the aircraft is built. AIAA variations of the source or due to environmental effects on the fiber. A detector spatially multiplexed common electro-optic A93-53874 interface for these sensors has been demonstrated with a position INTERCONVERSION OF TWO KINDS OF METHODS FOR and a temperature sensors. CABIN LEAKAGE TEST QIN-FANG YU (Nanjing Aeronautical Inst., China) Acta A93-53876 Aeronautica et Astronautica Sinica (ISSN 1000-6893) vol. 14, INTEGRATED FIRE CONTROL SIMULATION SYSTEMS no. 2 Feb. 1993 p. B47-B51. In CHINESE refs JIAN-HUA ZHANG, YONG WU, PEI-SHEN ZHU, and There are two kinds of methods for the cabin leakage test: GUAN-ZHONG DAI (Northwestern Polytechnical Univ., Xian, the flow-rate method and the pressure-drop method. The pressure China) Acta Aeronautica et Astronautica Sinica (ISSN drop method is simple, but leakage rates cannot be directly read 1000-6893) vol. 14, no. 2 Feb. 1993 p. B59-B65. In out. If leakage rates should be determined, an interconversion CHINESE refs relationship would be used. In this paper, the interconversion of Integrated Fire Control Systems (IFCS) is a program to explore the two kinds of methods for the cabin leakage test is established. and exploit digital concepts in the integration of avionic systems. Leakage rates can be calculated from the method of the pressure Because of such considerations as cost equipment etc., the signal drop test, and the time of pressure drop can be calculated from emulation and structure of IFCS are emphasized. The main work the method of the leakage rate test. The application to the cabin is summarized as follows: mimic ADC, INS, RAD, and BU can be

1192 07 AIRCRAFT PROPULSION AND POWER established by a method called static true value plus sensor noise. microturbines with shroudless rotors is substantial and varies In order to simulate attacker flight dynamics in the air combat depending on the relative area of the radial clearance. Expressions without a pilot, a fuzzy controller is employed to form a are obtained for calculating the optimal upper overlap with pilot-aircraft-fire control system loop, which simplifies the scheme allowance for the clearances. AIAA and lowers the cost. An introduction to attack modes in MC is presented. A scheme is put forward for designing a symbol A93-52965 generator of HUD. The implementation development of ESTIMATION OF THE PARAMETERS OF THE MIL-STD-1553B data is also considered. Author (revised) ELECTRODYNAMIC SYSTEM ENGINE-EXHAUST JET [OTSENKA PARAMETROV EHLEKTRODINAMICHESKOJ A93-54294 SISTEMY DVIGATEL'-VYKHLOPNAYA STRUYA] AVIONIC SYSTEMS IN SUPPORT OF COVERT HELICOPTER G. P. POTAPOV Aviatsionnaya Tekhnika (ISSN 0579-2975) no. OPERATIONS 1 1993 p. 109-112. In RUSSIAN refs JERRY F. FISHER (GEC Avionics, Ltd., Airport Works, Rochester, Copyright United Kingdom) In Helicopter operations in severe environments; Some analytical expressions are derived which relate the Proceedings of the Conference, London, United Kingdom, June 4, parameters of the electrodynamic system nozzle-exhaust to the 1992 London Royal Aeronautical Society 1992 p. 7.1-7.3. thermogasdynamic parameters of the working medium of an engine. Copyright These relations can be used for developing new passive diagnostics Covert avionics mission systems for battlefield helicopters systems and for refining the existing methods of diagnostics using capable of operating day and night in poor weather conditions the electrophysical properties of the working medium. AIAA without being detected or jammed are described. A covert mission system integrates a range of capabilities including a night vision A93-53554 system, day/night targeting, autonomous navigation, defensive SELECTION OF A METHOD FOR PROTECTING AIRCRAFT ESM and ECM, air-to-ground weapon delivery, and air-to-air weapon GAS TURBINE ENGINES AGAINST DAMAGE BY FOREIGN delivery. The integration of these systems, both electronically and OBJECTS (MATHEMATICAL MODELS) [VYBOR METODA in the cockpit, is the factor which will determine the success of ZASHCHITY AVIATSIONNYKH GTD OT POVREZHDENIJ the system. AIAA POSTORONNIMI PREDMETAMI /MATEMATICHESKIE MODEL!/] N. V. VASHCHENKO TslAM, Trudy no. 1233 1989 p. 6-11. In RUSSIAN refs 07 Copyright A classification of methods for protecting aircraft gas turbine AIRCRAFT PROPULSION AND POWER engines against damage by foreign objects is presented. The problem of selecting a particular engine protection method is Includes prime propulsion systems and systems components, e.g., formulated, and mathematical models for solving the problem are gas turbine engines and compressors; and on-board auxiliary power developed in terms of stochastic and linear programming. A plants for aircraft. stochastic model for the selection of a protection method is developed both for the initial selection and for selection at the stage of modernization. AIAA A93-52949 ESTIMATION OF THE CHANGE OF AXIAL-FLOW A93-53589*# National Aeronautics and Space Administration. COMPRESSOR CHARACTERISTICS DURING LONG-TERM Lewis Research Center, Cleveland, OH. SERVICE [OTSENKA DEFORMATSII KHARAKTERISTIK INITIAL RESULTS FROM THE NASA LEWIS WAVE ROTOR OSEVOGO KOMPRESSORA V USLOVIYAKH DLITEL'NOJ EXPERIMENT EHKSPLUATATSII] JACK WILSON (Sverdrup Technology, Inc., Lewis Research Center D. V. BELYAEV, EH. R. PIKULA, and V. S. TALYZINA Group, Brook Park, OH) and DENNIS FRONEK (NASA, Lewis Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 1 1993 p. Research Center, Cleveland, OH) Jun. 1993 10 p. AIAA, 50-54. In RUSSIAN rets SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, Copyright 29th, Monterey, CA, June 28-30, 1993 Previously announced in Results of experimental studies of changes in the parameters STAR as N93-32368 refs of plane compressor cascades due to erosion wear are reported. (AIAA PAPER 93-2521) Copyright To predict changes in the characteristics of multistage axial-flow Wave rotors may play a role as topping cycles for jet engines, compressors due to the erosion wear of the blades, a correction since by their use, the combustion temperature can be raised is introduced into a two-dimensional axisymmetric mathematical without increasing the turbine inlet temperature. In order to design model for calculating flow in the blade passage. As an example, a wave rotor for this, or any other application, knowledge of the calculations are presented for an axial-flow compressor in which loss mechanisms is required, and also how the design parameters the blade geometry has been modified and the radial clearance affect those losses. At NASA LeRC, a 3-port wave rotor experiment increased to simulate the erosion wear. AIAA operating on the flow-divider cycle, has been started with the objective of determining the losses. The experimental scheme is A93-52963 a three factor Box-Behnken design, with passage opening time, THE COMBINED EFFECT OF CLEARANCES AND friction factor, and leakage gap as the factors. Variation of these PERIPHERAL OVERLAPS ON THE EFFICIENCY OF factors is provided by using two rotors, of different length, two MICROTURBINES WITH SHROUDLESS ROTORS different passage widths for each rotor, and adjustable leakage [SOVMESTNOE VLIYANIE ZAZOROV I PERIFERIJNOJ gap. In the experiment, pressure transducers are mounted on the PEREKRYSHI NA EHFFEKTIVNOST' MIKROTURBIN S rotor, and give pressure traces as a function of rotational angle at RABOCHIMI KOLESAMI BEZ BANDAZHA] the entrance and exit of a rotor passage. In addition, pitot rakes B. A. KRYLOV and S. A. GUSAROV Aviatsionnaya Tekhnika monitor the stagnation pressures for each port, and orifice meters (ISSN 0579-2975) no. 1 1993 p. 103-107. In RUSSIAN measure the mass flows. The results show that leakage losses refs are very significant in the present experiment, but can be reduced Copyright considerably by decreasing the rotor to wall clearance spacing. Experimental data are presented on the combined effect of the upper overlap and of the axial and radial clearances on the A93-53702 efficiency of axial-flow microturbines with shroudless rotors. It is LOW-FREQUENCY COMBUSTION OSCILLATIONS IN A found that the effect of the upper overlap on the efficiency of MODEL AFTERBURNER

1193 07 AIRCRAFT PROPULSION AND POWER

M. A. MACQUISTEN and A. P. DOWLING (Cambridge Univ., United The ways in which IHPTET can meet new DOD science and Kingdom) Combustion and Flame (ISSN 0010-2180) vol. 94, technology policy goals are addressed, and steps that need to be no. 3 Aug. 1993 p. 253-264. Research supported by taken to assure rapid acceptance of IHPTET are considered. Rolls-Royce, PLC and Ministry of Defence Procurement Executive Attention is given to the development and application of advanced of United Kingdom refs aerodynamic and thermodynamic models and theories, the creation Copyright of innovative structural designs, and the development and Low-frequency combustion oscillations, involving the interaction application of advanced high-strength low-density materials. between longitudinal acoustic waves and unsteady combustion, AIAA are investigated for a model afterburner. An experimental rig, in which a confined flame is stabilized in the wake of a conical A93-53979 gutter, is run with inlet conditions representative of an engine DESIGN AND TECHNOLOGY FOR ENGINE MANUFACTURE afterburner. Results are presented for inlet Mach numbers in the T. BROUGHTON (Rolls-Royce, PLC, Derby, United Kingdom) In range of 0.15-0.27, with inlet temperatures up to 630 K. Comparison ISABE - International Symposium on Air Breathing Engines, 11th, is made between theory and experiment. Although the theory was Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 developed from low Mach number data, it is found to apply equally Washington American Institute of Aeronautics and Astronautics well at these faster flow rates. The theory is able to predict the 1993 p. 19-25. frequency of the instability and the mode shape, accurately (ISABE 93-7002) Copyright reproducing the changes due to variations in the inlet Mach number The use of simultaneous engineering to optimize the use of and temperature. The effect of altering the downstream boundary innovative technology in the manufacture of aerogas turbines is condition by replacing the open end by a choked nozzle is also demonstrated. It is shown that all the elements of the engineering investigated. Such a change is found to be highly destabilizing, process can be developed to achieve fast and economic engine both experimentally and theoretically. Again, predictions from the design and development through simultaneous engineering aided theory are in good agreement with the observations. by computer integration. Examples of successful implementation Author (revised) are given. AIAA

A93-53862 A93-53980 National Aeronautics and Space Administration. Lewis A STUDY OF SURGE CONTROL BY USING PULSE CUT-OFF Research Center, Cleveland, OH. FOR DUAL SPOOL TURBO-JET ENGINE PROPULSION TECHNOLOGY CHALLENGES FOR JIAN-GUO SUN, SI-MING HU (Nanjing Aeronautical Inst, China), TURN-OF-THE-CENTURY COMMERCIAL AIRCRAFT CAI-HONG JIANG, and WAN-FENG SUN (Shenyang Aeroengine JOSEPH A. ZIEMIANSKI and CALVIN L BALL (NASA, Lewis Research Inst., China) Acta Aeronautica et Astronautica Sinica Research Center, Cleveland, OH) In ISABE - International (ISSN 1000-6893) vol. 14, no. 1 Jan. 1993 p. A85-A89. In Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. CHINESE refs 20-24, 1993, Proceedings. Vol. 1 Washington American Institute A dynamic model of dual-spool turbojet engine with post-stall of Aeronautics and Astronautics 1993 p. 26-37. Previously capability is used. By utilizing this model, the surge is successfully announced in STAR as N93-32351 refs induced by opening nozzle, main combustor fuel-step, and throttling (Contract RTOP 505-62-10) nozzle. The simulation results are coincident with test results (ISABE 93-7003) Copyright obtained from the literature. The above dynamic model is adopted This paper highlights the efforts being performed or sponsored to simulate surge operation induced by opening nozzle, and the by NASA, in cooperation with the U.S. civil aviation industry, to mechanism of surge control of fuel pulse cut-off (FPCO) for address the propulsion system technological challenges that must dual-spool turbojet engine is investigated by computer simulations. be met in order to ensure a viable future for the industry. Both The effect of parameters of FPCO on surge control is analyzed. the subsonic and supersonic aeropropulsion programs are Some guidelines of the surge-control design for dual-spool turbojet considered. Subsonic transport propulsion program elements, engines are brought forward. Author (revised) including ultra-high-bypass-ratio turbofans with attendant noise reduction efforts, high-efficiency cores, and combustor emissions A93-53976 reductions are discussed in terms of goals, technical issues, and ISABE - INTERNATIONAL SYMPOSIUM ON AIR BREATHING problem solutions. Similarly, the high-speed research propulsion ENGINES, 11TH, TOKYO, JAPAN, SEPT. 20-24, 1993, efforts addressing a high-speed commercial transport are reviewed PROCEEDINGS. VOLS. 1 & 2 in terms of environmental barrier issues, such as oxides of nitrogen FREDERICK S. BILLIG, ED. (Johns Hopkins Univ., Laurel, MD) and noise reduction, and the related economic issues. Washington American Institute of Aeronautics and Astronautics 1993 p. Vol. 1, 737 p.; vol. 2, 677 p. For individual items see A93-53981 A93-53977 to A93-54109 JAPAN'S RESEARCH AND DEVELOPMENT PROGRAM FOR (ISBN 1-56347-071-3) Copyright AIRBREATHING ENGINE TECHNOLOGIES Various papers on air-breathing engines are presented. The HIROYUKI MOUSE (National Aerospace Lab., Tokyo, Japan) In general topics addressed include: stall and surge, hypersonic ISABE - International Symposium on Air Breathing Engines, 11th, propulsion systems, combustion, turbomachinery flows, fluid Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 mechanics problems, supersonic combustion, structure problems, Washington American Institute of Aeronautics and Astronautics supersonic transport, mixing, heat transfer problems, engine 1993 p. 41-49. refs simulation and control, axial turbines, integration, inlets, nozzles, (ISABE 93-7005) Copyright and engine condition monitoring. AIAA The current status and future directions of some Japanese research and development programs related to air-breathing engine A93-53978 technologies are briefly discussed. The technologies considered THE CHALLENGE OF IHPTET include an ultrahigh bypass ratio engine, an air turbo ramjet engine, RICHARD J. HILL (USAF, Wright Lab., Wright-Patterson AFB, a super/hypersonic transport propulsion system, and a subscale OH) In ISABE - International Symposium on Air Breathing Engines, scramjet engine and test facility. AIAA 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington American Institute of Aeronautics and Astronautics A93-53991 1993 p. 12-18. MACH 5 TURBORAMJET REQUIREMENTS AND DESIGN (ISABE 93-7001) Copyright APPROACH The goals, status, challenges, and future of the IHPTET WILLIAM L. WEBB and JAMES D. HILL (Pratt & Whitney Group, (Integrated High Performance Turbine Engine Technology) initiative West Palm Beach, FL) In ISABE - International Symposium on are discussed. The time phases of the IHPTET goals are shown. Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993,

1194 07 AIRCRAFT PROPULSION AND POWER

Proceedings. Vol. 1 Washington American Institute of Aeronautics A93-53996 and Astronautics 1993 p. 149-158. refs AN ULTRA LOW NO(X) PILOT COMBUSTOR FOR STAGED (ISABE 93-7015) Copyright LOW NO(X) COMBUSTION The unique mission requirements of Mach 5 hypersonic aircraft M. N. KIM, H. S. ALKABIE, and G. E. ANDREWS (Leeds Univ., propulsion systems are summarized and related to engine United Kingdom) In ISABE - International Symposium on Air configuration. The appropriate materials for meeting the Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, requirements are considered along with the requirements regarding Proceedings. Vol. 1 Washington American Institute of Aeronautics inlet cooling, accelerator cooling, ram combuster cooling, nozzle and Astronautics 1993 p. 215-225. Research supported by cooling, the liner system, and NO(x) requirements. The ram Department of Cultural Affairs of Iraq, British Council, and Korean combustor configurations are discussed. AIAA Gas Corp refs (ISABE 93-7020) Copyright A93-53992 The pilot zone of a multistage stage lean/lean combustor DEVELOPMENT STUDY ON AIR TURBO RAMJET ENGINE design was investigated with, low NO(x) characteristics using radial FOR A FUTURE SPACE PLANE swirlers with vane passage fuel injection. The pilot was designed NOBUHIRO TANATSUGU, YOSHIHIRO NARUO, TETSUYA SATO to be connected in series to the next stage through the center of (Inst. of Space and Astronautical Science, Sagamihara, Japan), a larger radial swirler with a downstream larger combustor can. ITARU ROKUTANDA (Ishikawajima-Harima Heavy Industries Co., Comparison was made with central radial outward fuel injection in Ltd., Tokyo, Japan), and MASAHIRO UCHIDA (Kawasaki Heavy the pilot and it was shown that vane passage fuel injection had Industries, Ltd., Kobe, Japan) In ISABE - International Symposium substantially lower NO(x) emissions, comparable with those of the on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, low NO(x) main stages where the fuel injection was around the Proceedings. Vol. 1 Washington American Institute of Aeronautics main swirler exit periphery. The overall stability of a multistage and Astronautics 1993 p. 159-172. refs design is controlled by the proportion of air entering the pilot and (ISABE 93-7016) Copyright this was varied by varying the pilot blockage at a constant pressure An analytical and experimental study of the Air Turbo Ramjet loss. Very low pilot NO(x) could be achieved at all pilot flow (ATR) propulsion system for the two-stage-to-orbit launch system proportions and at maximum power inlet temperatures of up to is discussed. The ATR engine cycles using liquid hydrogen as 900 K. This pilot design could therefore be used with a low NO(x) fuel are analyzed, including design criteria and engine performance main combustor with no adverse influence on the combined NO(x), characteristics. Test results of the 1 /4-scale ATR engine with fan which is a crucial requirement of ultra low NO(x) multistage inlet diameter of 300 mm and overall length of 2200 mm are combustor designs. reported, including sea level static tests and test results on the tip turbine, combustor, heat exchanger, and engine operation. Wind A93-53997 tunnel results on the air intake with precooler are also reported. LOW NO(X) COMBUSTOR DEVELOPMENT USING AIAA AERODYNAMIC STAGING ASHWANI K. GUPTA (Maryland Univ., College Park) In ISABE A93-53994 - International Symposium on Air Breathing Engines, 11th, Tokyo, CONCEPTUAL DESIGN STUDY ON COMBINED-CYCLE Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington ENGINE FOR HYPERSONIC TRANSPORT American Institute of Aeronautics and Astronautics 1993 p. Y. WATANABE, H. MIYAGI, T. SEKIDO, H. MIYAGAWA 226-233. refs (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan), (ISABE 93-7021) Copyright F. TANAKA (Kawasaki Heavy Industries Co., Ltd., Kobe, Japan), The results are presented here from a Variable Geometry swirl T. AOKI (Mitsubishi Heavy Industries Co., Ltd., Tokyo, Japan), M. Combustor (VGC) that is in the form of multiconcentric telescopic MORITA, and R. YANAGI (National Aerospace Lab., Tokyo, arrangement. Parametric studies have shown the important effect Japan) In ISABE - International Symposium on Air Breathing of burner geometry and input operational parameters, including Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. coswirl and counterswirl, on NO(x) emission and combustion 1 Washington American Institute of Aeronautics and characteristics. The results show the potential advantages of CFLG Astronautics 1993 p. 188-197. Research supported by Agency (center fuel lean geometry), CFRG (center fuel rich geometry), of Industrial Science and Technology of Japan refs and PMG geometries for low NO(x) emission. The effect of coswirl (ISABE 93-7018) Copyright or counterswirl on combustion and emission is also found to be The engine of the Hypersonic Transport Propulsion System significant. Residence time, turbulent mixing, and temperature have Research Project, which is a combined-cycle engine composed of a strong effect on NO(x). The amount of NO2 in NO(x) depends a turboaccelerator for the lower speed range and a ramjet engine upon the availability of O atom concentration and is effected by for the high speed range, is discussed. The cycle definition of the the turbulence levels and temperature. Author (revised) target engine is described and the method and results of a configuration test are described. The status of the design of the A93-53998 demonstrator engine is addressed. AIAA THE PREDICTION OF THERMAL NO(X) IN GAS TURBINE EXHAUSTS A93-53995 G. F. PEARCE (Defence Science and Technology Organisation, ENERGY MANAGEMENT Aeronautical Research Lab., Melbourne, Australia), D. J. VANDENKERCKHOVE (VDK System, S.A., Brussels, Belgium) KRETSCHMER, J. ODGERS (Univ. Laval, Quebec, Canada), and and M. BARRERE (ONERA, Chatenay-Malabry, France) In ISABE G. WANG (Royal Military College, Kingston, Canada) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington American Institute of Aeronautics and Astronautics 1993 p. American Institute of Aeronautics and Astronautics 1993 p. 198-212. 234-243. Research supported by Canadian Panel on Energy (ISABE 93-7019) Copyright Research and Development, Department of Defence of Australia, The benefits derived from active management of all energetic DND, and NSERC refs resources which can be harnessed along the whole vehicle (ISABE 93-7022) Copyright trajectory, beyond the chemical energy of the propellant stored Using 2,200 data points from 14 different experimental series, onboard, are assessed. This harnessing is achieved by heating an attempt was made to develop an equation suitable for the the hydrogen fuel using exchanges located either internally or prediction of the NO(x) found in gas turbine exhausts. Nine different externally. The issue of active versus passive cooling is examined combustors were investigated of a very wide size range. Inlet along with the practical implications of energy transfer mechanisms temperatures and pressures ranged from 290 to 851 K and from and inlet geometry. AIAA 0.1 to 1.4 MPa respectively. Based upon the data pertinent to

1195 07 AIRCRAFT PROPULSION AND POWER typical gas turbine conditions, it is estimated that the A93-54003* National Aeronautics and Space Administration. repeatability/reproducibility is of the order of +/- 1 El unit at the Lewis Research Center, Cleveland, OH. low range (at 1 El unit, 50 percent) and +/- 2 El units (at 12 El FORCING FUNCTION MODELING FOR FLOW INDUCED units, 17 percent) and +/- 3 El units (at about 30 El units, 10 VIBRATION percent). The new equation was developed from a previous one SANFORD FLEETER (Purdue Univ., West Lafayette, IN) In ISABE which had been found to correlate data satisfactorily, but which - International Symposium on Air Breathing Engines, 11th, Tokyo, could not be used for prediction purposes without the need of Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington some experimental data. Author (revised) American Institute of Aeronautics and Astronautics 1993 p. 305-318. Research sponsored by NASA refs (ISABE 93-7027) Copyright The fundamental forcing function unsteady aerodynamics for A93-53999* National Aeronautics and Space Administration. application to turbomachine blade row forced response are Lewis Research Center, Cleveland, OH. considered, accomplished through a series of experiments EMISSION CHARACTERISTICS OF A MODEL GAS TURBINE performed in a rotating annular cascade and a research axial flow COMBUSTOR AT PRACTICAL CONDITIONS turbine. In particular, the unsteady periodic flowfields downstream S. A. DRENNAN, W. A. SOWA, and G. S. SAMUELSEN (California of rotating rows of perforated plates, airfoils and turbine blade Univ., Irvine) In ISABE - International Symposium on Air Breathing rows are measured with a cross hot-wire and an unsteady total Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. pressure probe. The unsteady velocity and static pressure fields 1 Washington American Institute of Aeronautics and were then analyzed harmonically and split into vortical and potential Astronautics 1993 p. 244-253. Research supported by Northrop gusts, accomplished by developing a gust splitting analysis which Corp. refs includes both gust unsteady static pressure and velocity data. (Contract F08635-90-C-0100; NAG3-1124) The perforated plate gusts closely were found to be linear theory (ISABE 93-7023) vortical gusts, satisfying the vortical gust constraints. The airfoil This paper reports on in situ and exit plane emissions and turbine blade row generated velocity perturbations did not measurements from a model gas turbine combustor at practical satisfy the vortical gust constraints. However, the decomposition air preheat temperatures and pressures for a range of operating of the unsteady flow field separated the data into a propagating conditions. The model combustor chosen for the study features vortical component which satisfied these vortical gust constraints two rows of jets (primary and dilution) with four jets per row, and and a decaying potential component. utilizes effusive air cooling holes on the liner wall. The combustor dome is equipped with a flat-vaned swirler with a vane angle of A93-54004 60 deg. Data are obtained at combustor pressures ranging from 2 EFFECTS OF BLADE GEOMETRY AND MODE SHAPE ON FAN to 10 atmospheres, air preheat temperatures from 204 C to 427 FLUTTER C, and combustor reference velocities from 10.0 to 20.0 m/s. An A. PETTERSSON (Chalmers Univ. of Technology, Goteborg, overall equivalence ratio of 0.3 was constant for all conditions. Sweden), L. D. G. SIDEN (Volvo Flygmotor AB, Trollhattan, Exit plane and in situ measurements are presented for HC, O2, Sweden), and U. HALL (Chalmers Univ. of Technology, Goteborg, CO2, CO, and NO(x). The results from exit plane NO(x) Sweden) In ISABE - International Symposium on Air Breathing measurements illustrate that the model combustor is representative Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. of current gas turbine combustors. The in situ data reveal effects 1 Washington American Institute of Aeronautics and of fuel/air and wall jet mixing on emission performance. Astronautics 1993 p. 319-331. Research supported by Volvo Author (revised) Flymotor AB refs (ISABE 93-7028) Copyright In this paper the VOLFAP flow code is used to predict the flutter behavior of a fan rotor. The sensitivity to changes in mode A93-54000 shape and blade geometry is studied. The effect or blade leading DESIGN AND TESTING METHODS OF HIGH PERFORMANCE edge cut-back, increased rotor tip stagger and modified part span COMBUSTORS FOR AIRBREATHING ENGINES shroud angle are simulated and compared with results from engine Y. M. TIMNAT (Technion - Israel Inst. of Technology, Haifa) In tests. The first two modifications do not show the improved ISABE - International Symposium on Air Breathing Engines, 11th, aeroelastic stability that has been experienced in tests. Simulations Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 using an increased part span shroud angle, however, indicate a Washington American Institute of Aeronautics and Astronautics drastically increased stability as do also engine test results. This 1993 p. 254-275. refs can be explained by a changed modal shape. (ISABE 93-7024) Copyright The aim of this paper is to discuss design and testing methods A93-54008 for high performance combustors used in different types of jet DESIGN OF HIGH-LOAD AVIATION TURBOMACHINES USING engines. The paper starts with a description of research we MODERN 3D COMPUTATIONAL METHODS performed on the subject, treating the following topics: conventional M. J. IVANOV, V. K. KOSTEGE, V. G. KRUPA, and R. Z. airbreathing combustors, solid fuel ramjet combustion chambers, NIGMATULLIN (Central Inst. of Aviation Motors, Moscow, Russia) including the influence of metal additives, slurry fuels for ramjets, In ISABE - International Symposium on Air Breathing Engines, and the development of thermal barrier coatings for blades of 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 coal-fired turbines. A number of diagnostic techniques are treated Washington American Institute of Aeronautics and Astronautics in detail: millisecond response thermo-couples, and a modified 1993 p. 355-365. refs line-reversal method for temperature measurements, particle size, (ISABE 93-7032) Copyright and velocity determination by means of LDA and PDA, including This paper presents a modern mathematical simulation of a critical comparison of these techniques. We discuss regression aerodynamic and thermal problems for gas turbine engine rate measurements by photography, ultrasonics, and MWs. The components design. Based on the reached level, the nearest phase transition from subsonic to supersonic flow in a ramjet combustor, of numerical simulation includes the development and application which takes place for a flight Mach number between 5 and 7, is of the complex 3D models of multistage turbomachines, and whole treated. After reviewing the work performed in the U.S., France flow passage of core and bypass engines. The following important and Russia, it is shown that further studies are warranted and we direction of numerical simulation will be the solution of conjugate propose to build a facility, in which particular attention is paid to multidisciplinary°problems for the individual components of air the measurement of the regression rate of energetic solid fuels, breathing engines. The typical example of this problem is the preferably in collaboration with investigators of other countries. thermal-stressed state of the high-load cooling turbine. The paper Author (revised) presents results of numerical simulation for multicomponent and

1196 07 AIRCRAFT PROPULSION AND POWER

multidisciplinary problems. Developing computational codes are main flow and coolant due to increment of the film coolant based on the high accuracy finite difference and finite element temperature. The effective cooling system with a combination of methods and realized on middle-class computers. regenerative cooling and film cooling also contributed to the Author (revised) advantages due to avoidance of excess cooling of engine wall. Author (revised) A93-54010 COMPLEMENTARY ROLE OF GROUND TESTING, FLIGHT A93-54013 TESTING, AND COMPUTATIONS IN AEROSPACE PLANE HYPERSONIC SHOCK-INDUCED COMBUSTION RAMJET PROPULSION DEVELOPMENT PERFORMANCE ANALYSIS V. K. Ill SMITH (Sverdrup Technology, Inc., Arnold AFB, TN) and JEAN P. SISLIAN and RUDOLPH DUDEBOUT (Toronto Univ., A. H. BOUDREAU (USAF, Arnold Engineering Development Center, Downsview, Canada) In ISABE - International Symposium on Arnold AFB, TN) In ISABE - International Symposium on Air Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington American Institute of Aeronautics Proceedings. Vol. 1 Washington American Institute of Aeronautics and Astronautics 1993 p. 413-420. refs and Astronautics 1993 p. 373-391. refs (ISABE 93-7037) Copyright (ISABE 93-7034) Hypersonic propulsion has enjoyed a renewed interest and The propulsion systems of conceptualized aerospace planes one possible mode of propulsion, which has yet to be systematically impose test and evaluation requirements which require large investigated, is that of a shock-induced combustion ramjet. In order technology steps, not merely an evolution of current technology. to assess the performance of a ramjet utilizing this mode of heat The deficiencies in hypersonic propulsion test and eval- addition, a computational scheme based on Godunov's (1976) uation methodology, encompassing ground testing, method was developed to determine the inviscid hypersonic flow computation/simulation, and flight testing, are addressed, and field produced by planar and axisymmetric bodies: The specific enabling technologies and approaches have been shock-induced finite-rate hydrogen-air combustion process was identified. The need for enhancing the traditional approach through modeled by 33 reactions between 13 species (H2, O2, H, O, OH, the use of an integrated triad of test and evaluation methodology H2O, HO2, H2O2, N, NO, HNO, N2, and NO2). The shock is illustrated with specific propulsion examples. Opportunities for (discontinuity) tracking capability of the computational scheme was international collaboration to meet the shortfalls are also cited. used to accurately determine shock or detonation wave and wall intersection points and construct a series of wall contours resulting A93-54011 in a body geometry for given free-stream conditions. Pressures CFD FOR RAMJET AND SCRAMJET POWERED VEHICLES acting on these planar and axisymmetric bodies were calculated P. GARNERO and C. STYLEMANS (Aerospatiale, and used to determine various aerodynamic and propulsive Verrieres-le-Buisson, France) In ISABE - International Symposium characteristics of external compressions ramjets over the range on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, of flight Mach numbers 11-20. Author (revised) Proceedings. Vol. 1 Washington American Institute of Aeronautics and Astronautics 1993 p. 392-402. refs A93-54014 (ISABE 93-7035) Copyright STUDY OF A PULSE RAMJET BASED ON TWIN VALVELESS Aerospatiale has been using ramjets on its missiles for more COMBUSTORS COUPLED TO OPERATE IN ANTIPHASE than thirty years and began high speed air-breathing studies for N. LIBIS and Y. GOLDMAN (Technion - Israel Inst. of Technology, missiles, combined cycle engines powered aircraft and single or Haifa) In ISABE - International Symposium on Air Breathing two stages-to-orbit launchers. The design of such vehicles involves Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. ramjet and scramjet engines. To be able to work more rapidly 1 Washington American Institute of Aeronautics and and with higher accuracy, we adapted our work methodology in Astronautics 1993 p. 421-435. refs using Computational Fluid Dynamics tools from the vehicles design (ISABE 93-7038) Copyright phase. These tools, composed of analytical, Euler, boundary layer An explanation of processes in a new type of pulse ramjet of and Navier-Stokes codes, are a complementary approach to wind unusual configuration, the experimental results of its operation and tunnel and propulsion bench tests. This new methodology will the analytical approach guiding its development are presented. allow us to analyze and optimize more rapidly and at lower cost The concept is based on coupling two valveless pulse engines at new configurations of air-breathing vehicles. their common inlet by a symmetric pulse ejector. The tests confirm the expected antiphase mode of the two combustion chambers' A93-54012 operation. A single chamber combustor with a transparent side EFFECT OF FILM COOLING/REGENERATIVE COOLING ON was used for fast photography, temperature field, gas pressure SCRAMJET ENGINE PERFORMANCES and composition monitoring to explain the oscillatory burning TAKESHI KANDA, GORO MASUYA, FUMIEI ONO, AKIO MORO, processes. An optimization process was exploited in order to find and YOSHIO WAKAMATSU (National Aerospace Lab., Kakuda, the best tailpipe geometry giving the highest achievable Japan) In ISABE - International Symposium on Air Breathing performance. For the selected tailpipe, the peak-to-peak phase Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. difference between the pressure in the combustion zone and the 1 Washington American Institute of Aeronautics and stagnation pressure at the exit plane tends to a minimum value of Astronautics 1993 p. 403-412. refs 60 deg. A characteristic method is applied for analysis of the (ISABE 93-7036) Copyright nonsteady flow in the inlet and exhaust pipes. Boundary conditions Film cooling was modeled for performance prediction of a at the duct ends including the changes in the combustion chamber scramjet engine. The model was based on experimental results of pressure and temperature are defined. A simple heat release compressible mixing layers for vicinity of the injection slot, and on scheme is used to simulate the combustion process. analytical results of turbulent boundary layer for the far region Author (revised) from the slot. After confirming consistency with the experimental results, the film cooling-model was integrated to a quasi-10 A93-54015 scramjet performance prediction model. Engine performances were A STUDY ON 3-D VELOCITY DISTRIBUTION OF ISOTHERMAL compared among three scramjets, which have different cooling FLOWS BEHIND AN AFTERBURNER FLAME STABILIZER systems from each other. In the engine with both film cooling and M. RAVICHANDRAN and V. GANESAN (Indian Inst. of Technology, regenerative cooling, coolant flow rate of the engine slightly Madras, India) In ISABE - International Symposium on Air exceeded stoichiometric flow rate even in high flight Mach numbers, Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, and it showed the best performances on specific impulse and Proceedings. Vol. 1 Washington American Institute of Aeronautics system pressure. The advantages were achieved with increment and Astronautics 1993 p. 439-448. refs of volume flow rate and decrement of velocity difference between (ISABE 93-7039) Copyright

1197 07 AIRCRAFT PROPULSION AND POWER

An experimental and numerical investigation of the 3D flow flames is also given, based on one-dimensional flame calculations fields behind a typical turbofan afterburner flame stabilizer is with various reaction mechanisms. presented. Five-hole pilot probe measurements downstream of the flame stabilizer allow the determination of three mean velocity A93-54019 components. The numerical calculations are performed using a PERIODIC CHEMICAL ENERGY RELEASE FOR ACTIVE SIMPLE based algorithm with staggered grid arrangement. The COMBUSTION CONTROL standard k - epsilon model is used for physical modeling. The K. C. SCHADOW, K. J. WILSON, E. GUTMARK, K. YU, and R. A. numerical results agree satisfactorily well with the time-mean SMITH (U.S. Navy, Naval Air Warfare Center, China Lake, CA) velocity measurements. The predicted turbulence kinetic energy In ISABE - International Symposium on Air Breathing Engines, contours have been presented. The flow field predictions have 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 also been extended to a practical turbojet afterburner system. Washington American Institute of Aeronautics and Astronautics Author (revised) 1993 p. 479-485. refs (ISABE 93-7043) A93-54016 An actuator was developed to control combustion in a dump ISOTHERMAL FLOW CHARACTERISTICS BEHIND V-SHAPE combustor and premixed combustor with flameholder. To suppress GUTTER WITH AND WITHOUT INJECTION pressure oscillations, the actuator generated periodic energy by YUJI IKEDA, SHIGEO HOSOKAWA, MASASHI MINATO, and spark-ignition of a stoichiometric mixture of fuel and air. Tests TSUYOSHI NAKAJIMA (Kobe Univ., Nada, Japan) In ISABE - were performed at near ambient and 180 kPa chamber pressure International Symposium on Air Breathing Engines, 11th, Tokyo, with the actuator located in the air inlet duct of the dump combustor Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington and integrated into the flameholder for the premixed combustor. American Institute of Aeronautics and Astronautics 1993 p. Suppression of pressure oscillations was achieved with open and 449-456. refs closed-loop control. The effects of the pulse actuator on the (ISABE 93-7040) Copyright shear-flow dynamics in the flameholding regime and therefore on Three-dimensional flow characteristics behind the V-gutter with the heat release characteristics were visualized using Mie scattering and without jet injection were investigated by LDV measurements. flow visualization. The difference of reverse flows with and without injection was measured in order to specify the flow characteristics for flame A93-54020 holding. The injected jet spread as an elliptical shape. The reverse NOZZLE EFFECTS ON LINEAR STABILITY BEHAVIOUR OF flow region at low equivalence ratio was a continuous circular-ring COMBUSTORS shape, while the combination of these reverse flow regions was GIUSEPPE BUSSI, GUIDO COLASURDO, and DARIO PASTRONE yielded with increase of equivalence ratio. The reverse flow ratio (Torino, Politecnico, Turin, Italy) In ISABE - International was almost proportional to the jet flow rate, that is, equivalence Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. ratio. Three typical flow characteristic parameters were proposed 20-24, 1993, Proceedings. Vol. 1 Washington American Institute in order to specify the flame holding and mixing characteristics at of Aeronautics and Astronautics 1993 p. 486-492. Research different equivalence ratio. supported by MURST refs (ISABE 93-7044) Copyright A93-54017 The influence of nozzle acoustic admittance on linear stability THE DESIGN AND DEVELOPMENT OF AN AFTERBURNER behavior of liquid propellent combustors is analyzed. Firstly, a H. V. HATTINGH, J. E. VAN NIEKERK, I. P. PENNINGTON, and means for evaluating the acoustic admittance exhibited by a S. J. VENTER In ISABE - International Symposium on Air supercritical convergent nozzle with a given geometry, approached Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, by a 3D oscillatory flow, is presented. The correct conditions which Proceedings. Vol. 1 Washington American Institute of Aeronautics must be assumed at the throat, where the equations are singular, and Astronautics 1993 p. 457-469. refs are pointed out. Neutral stability curves are then calculated for (ISABE 93-7041) Copyright different oscillation types and combustors lengths, to show the The design of an afterburner for a straight jet engine (no by-pass effect that the proper nozzle admittance assumption has on the airflow) was executed by using the appropriate theoretical and stability range. Conspicuous differences from previous published empirical tools. A non-flying afterburner was built to this design results, which were obtained by assuming the so-called 'short and tested in a laboratory with simulated gas flow into the nozzle' admittance, are observed. afterburner. Physical quantities were measured, outlet temperatures with a non-intrusive CARS system, from which thrust levels and A93-54022 combustion efficiencies may be calculated. NOISE REDUCTION OF SUPERSONIC HEATED JET WITH JET MIXING ENHANCEMENT BY TABS A93-54018 H. KOBAYASHI, H. OINUMA, M. MINODA (National Aerospace LARGE EDDY SIMULATION OF TURBULENT COMBUSTION Lab., Chofu, Japan), and E. OUTA (Waseda Univ., Tokyo, Japan) BEHIND FLAME HOLDERS In ISABE - International Symposium on Air Breathing Engines, R. RYDEN, L.-E. ERIKSSON, and S. OLOVSSON (Volvo Flygmotor 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 AB, Trollhattan, Sweden) In ISABE - International Symposium Washington American Institute of Aeronautics and Astronautics on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, 1993 p. 501-510. Research supported by MITI refs Proceedings. Vol. 1 Washington American Institute of Aeronautics (ISABE 93-7046) Copyright and Astronautics 1993 p. 470-478. Research supported by Effects of jet gas temperatures on underexpanded supersonic STU and Defence Materiel Department of Sweden refs jet noise reduction by small size tabs has been experimentally (ISABE 93-7042) Copyright investigated, using a supersonic jet noise test facility operated in Flow calculations for a turbulent premixed propane-air flame an anechoic room. The small size tab in comparison with ones behind a bluff body flame holder with triangular cross section used previously by other investigators was selected, based on have been performed using a large eddy simulation (LES) technique test results of underexpanded supersonic cold jet noise reduction, together with Magnussens eddy dissipation concept (EDC) for acquiring tabs with a large noise reduction level per percent combustion model. Computational results for a single-step reaction jet thrust loss. The far-field jet noise spectra and directivity were mechanism are compared to LDA and to temperature profiles measured from the conical covergent nozzles operated with the obtained by gas analysis. Grid density effects on mean and rms two tabs and without tabs, in super-critical jet operating conditions quantities are also presented in order to give some indication of of the maximum jet Mach number 1.684 and in jet gas temperature the accuracy of the turbulence modelling. A short discussion on conditions varied from 303 k to 773 k for each jet operating the modelling of NOx formation in an LES context for premixed condition. In the cases of high jet gas temperature, the tabs

1198 07 AIRCRAFT PROPULSION AND POWER efficiently eliminate the screech tone noise as well as reduce Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, broadband shock associated noise, by the maximum 7 dB in overall Proceedings. Vol. 1 Washington American Institute of Aeronautics sound pressure level. Author (revised) and Astronautics 1993 p. 550-560. refs (ISABE 93-7052) Copyright A93-54024 Dynamic characteristics as total systems of scramjet engines THE DEVELOPMENT OF A NEW AIR FILTRATION SYSTEM were investigated. We focused on unsteady unstart phenomena FOR THE ALOUETTE III HELICOPTER due to compound choking and unsteady interaction between engine L. J. H. DU PLESSIS, C. A. VAN DER MERWE, and I. J. modules. We did quasi-3D compressible inviscid calculations and RADEMEYER (Council for Scientific and Industrial Research, experiments for analyzing unstart phenomena, and 2D compressible Pretoria, South Africa) In ISABE - International Symposium on inviscid calculations for interaction between engine modules. It is Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, shown that the boundary layer flow spreads and pushes out the Proceedings. Vol. 1 Washington American Institute of Aeronautics main flow in engine inlets, and that engines designed assuming a and Astronautics 1993 p. 514-521. refs uniform inlet flow can be made unstart easily because of the (ISABE 93-7048) Copyright existence of a low flow speed region like a boundary layer. When This paper describes the development and evaluation of a side walls of engines swept backward, the transition from start to vortex tube filtration system for the SA 316B Alouette helicopter. unstart is rather continuous and the inlet performance at unstart The AS18 vortex tube which is used in the system demonstrates conditions is not so badly deteriorated as the performance of the exceptionally high filtration efficiency of 96.6 percent with an inlets without being swept backward. The results of the experiments associated pressure drop of 860 Pa. The tube also passes only show that the processes of transition from start to unstart depend 0.86 percent of dust of particle size 10 microns and up. This is remarkably on width and shear strength of the boundary layer. It between three and ten times better than any other such tube. is shown that a shock wave generated in front of one module This results in very good engine erosion protection in South African extends and that it blocks the flow coming into the adjacent conditions where the silica content of dust is up to 100 percent modules quickly, which makes the modules unstarted. at places. The advantages of the new vortex tube filtration system Author (revised) are illustrated. The helicopter performance and handling qualities is unaffected by the installation and it is therefore still able to fulfill all its mission requirements. This filtration system means a A93-54037 significant reduction in direct operating cost of the helicopter due AXIAL FLOW COMPRESSORS - MECHANICAL DESIGN to its excellent erosion protection balanced with good aerodynamic TRENDS performance and simplicity of installation and operation. H. A. GEIDEL, G. ZAEHRING, P. LOTTES, and H. J. SCHMUHL 'Author (revised) (MTU Motoren- und Turbinen-Union Muenchen GmbH, Munich, Germany) In ISABE - International Symposium on Air Breathing A93-54026 Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. IGNITION AND COMBUSTION PERFORMANCE OF A 1 Washington American Institute of Aeronautics and SCRAMJET COMBUSTOR WITH A FUEL INJECTION STRUT Astronautics 1993 p. 644-652. refs GORO MASUYA, TOMOYUKI KOMURO, ATSUO MURAKAMI (ISABE 93-7061) Copyright (National Aerospace Lab., Kakuda, Japan), NOBORU SHINOZAKI, Design objectives for axial aerocompressors are presented. The AKIHIRO NAKAMURA (Nissan Motor Co., Ltd., Kawagoe, main mechanical design challenges which must be met to achieve Japan), MOTOHIDE MURAYAMA, and KATSURA OHWAKI the objectives are described. Component optimization is (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan) emphasized. AIAA In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington American Institute of Aeronautics and Astronautics A93-54038 1993 p. 533-542. refs THERMAL FATIGUE LIFE ASSESSMENT OF A (ISABE 93-7050) Copyright CONVECTION-COOLED GAS TURBINE BLADE Ignition and combustion performance of a scramjet combustor TREVOR J. KIRSTEN, DAVID GREENBLATT, and MANFRED O. with a fuel injection strut was experimentally investigated. A vitiation DEDEKING (Council for Scientific and Industrial Research, Pretoria, air heater supplied Mach 2.5 airstream to the combustor at South Africa) In ISABE - International Symposium on Air Breathing stagnation conditions of 800-2200 K and 1.0 MPa. In order to Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. select strut configuration which does not produce major disturbance 1 Washington American Institute of Aeronautics and in the flowfield, five strut models with different leading edge Astronautics 1993 p. 653-661. refs geometry were tested without fuel injection. The nonreacting (ISABE 93-7062) Copyright flowfields were also investigated by computation with a 2D This paper demonstrates a method for predicting the life of Navier-Stokes code. Using a less flow-disturbing strut, combustion cooled gas turbine hot section components which are subjected and ignition tests were conducted. Pilot pressure and gas to large thermo-mechanical loads during engine operating cycles. composition survey was carried out to deduce mixing and The technique made use of an aerothermodynamic component combustion efficiencies. It was found that mixing and combustion incorporating measured engine data, a mean-line performance with a less flow-disturbing strut was considerably worse than those code, computational fluid dynamics and empirical correlations, and previously studied with a more flow-disturbing strut. Autoignition a structural finite element component. Results of the fluid flow and forced ignition with plasma torches were tested for hydrogen computations were used as boundary conditions for the structural fuel at the room temperature. Ignition characteristics of fuel injected blade life analysis which considered the combined effect of parallel and perpendicular to the airstream were quite different. thermo-mechanical fatigue and creep damage. The FEM The plasma igniters could successfully ignite both parallel and implementation was designed to be practical and streamlined, as perpendicular fuel jets without noticeable time delay between both the damage models used require a minimum of materials testing. sides of the strut. Author (revised) This system provides the designer with an expeditious prediction of the highly damaged regions and the expected mode of failure. A93-54028 Comparisons are presented between the predicted and actual STUDY ON UNSTART AND ITS PROPAGATION ALONG modes of failure and the critical regions of the component. The MODULES DUE TO COMPOUND CHOKING AND/OR prediction compare well with those found to exist in actual engine FLUCTUATIONS IN COMBUSTOR OF SCRAMJET ENGINES operation. This fluid-structure configuration can therefore be used TETSUYA SATO (Inst. of Space and Astronautical Science, with confidence for detecting failure modes during component Sagamihara, Japan), TAKUO ONODERA, and SHOJIRO KAJI upgrades, cooling modifications and other aerodynamic or structural (Tokyo Univ., Japan) In ISABE - International Symposium on modifications.

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A93-54039 promising system, the double-bypass variable cycle engine concept. APPLICATION OF FUNCTIONALLY GRADIENT MATERIALS This relatively simple concept optimizes engine performance over TO SCRAMJET ENGINES wide ranges of operation. It is employed in the F120 engine, GEAE's TOSHIHITO SAITO, SYUICHI UEDA, NOBORU SAKURANAKA, offering to power the United States Air Force's Advanced Tactical YOSHIO WAKAMATSU, MASAYUKI NIINO (National Aerospace Fighter (ATF) aircraft. The F120 is capable of operating in two Lab., Kakuda, Japan), TOSHIO NOMURA (Sumitomo Electric distinct modes, a single- and a double-bypass mode. The Industries, Ltd., Itami, Japan), IKUO YAMAOKA (Nissan Motor Co., single-bypass (turbojet) mode maximizes thrust in high power Ltd., Kawagoe, Japan), TORU SAITO (Nippon Steel Corp., Chiba, operation. The double-bypass (turbofan) mode minimizes fuel Japan), and SHIN-ICHIRO KIYOTO (Mitsubishi Heavy Industries, consumption during low power operation. Author (revised) Ltd., Nagoya, Japan) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, A93-54042 Proceedings. Vol. 1 Washington American Institute of Aeronautics RESEARCH AND DEVELOPMENT OF A and Astronautics 1993 p. 662-669. Research supported by TURBO-ACCELERATOR FOR SUPER/HYPERSONIC Science and Technology Agency of Japan refs TRANSPORT (ISABE 93-7063) Copyright H. ITAHARA, S. KOHARA (Ishikawajima-Harima Heavy Industries Thermal-stress relaxation-type functionally gradient materials Co., Ltd., Tokyo, Japan), F. TANAKA (Kawasaki Heavy Industries (FGMs) show promise as high temperature materials, and are Co., Ltd., Kobe, Japan), M. SUZUKI (Mitsubishi Heavy Industries presently under development for application to scramjet engines. Co., Ltd., Komaki, Japan), J. L. CABE (GE Aircraft Engines, We applied FGMs to a model of the cooling structure of the Cincinnati, OH), R. YANAGI, and M. MORITA (National Aerospace scramjet. Two kinds of FGM samples were fabricated and Lab., Chofu, Japan) In ISABE - International Symposium on Air experimentally evaluated with vitiation-type hot air flow. One sample Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, consisted of a CFRC (SiC/TiC) panel coated with an FGM Proceedings. Vol. 1 Washington American Institute of Aeronautics oxidation-resistant layer and the cooling structure made of copper. and Astronautics 1993 p. 694-700. Research supported by The other sample had cooling structure which was made of Agency of Industrial Science and Technology of Japan refs stainless steel and coated with NiCrAlY and partially stabilized (ISABE 93-7066) Copyright zirconia, PSZ (ZrO2). FGM part of these samples showed fair Research and development of a combined cycle engine for heat resistant characteristics under the high heat flux condition in future Mach 5 super/hypersonic transport, which could be these tests. However, the results suggested that there was room environmentally acceptable and economically viable, have been for improvement of production technology of large FGM panels carried out since 1989 in Japanese Hypersonic Transport from the standpoint of application to the scramjet. It seemed that Propulsion System Research Project sponsored by the Japanese the method of directly building up an FGM layer on the cooling Ministry of International Trade and Industry. The combined cycle structure surface might be better than a method joining the FGM engine consists of a turbo-accelerator for low-speed range and a panel to the cooling structure. Author (revised) ramjet for high-speed range. The turbo-accelerator is required to operate up to Mach 3, to be fuel efficient, to restrain the noxious A93-54040 National Aeronautics and Space Administration. Lewis emissions and to meet ICAO noise regulations. A variable cycle Research Center, Cleveland, OH. engine concept features the engine in order to achieve both the ENGINE TECHNOLOGY CHALLENGES FOR A 21ST CENTURY low noise level at take-off and landing and the high specific thrust HIGH-SPEED CIVIL TRANSPORT at altitude high speed. The demonstrator engine of the ROBERT J. SHAW (NASA, Lewis Research Center, Cleveland, turbo-accelerator is being designed and manufactured in the OH), SAMUEL GILKEY (GE Aircraft Engines, Evendale, OH), and collaboration. The high temperature core engine of the RICHARD HINES (Pratt & Whitney Group, Hartford, CT) In ISABE turbo-accelerator is also being designed and manufactured to - International Symposium on Air Breathing Engines, 11th, Tokyo, establish the high temperature technology aimed at the turbine Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington inlet temperature of 1973 K. Author (revised) American Institute of Aeronautics and Astronautics 1993 p. 673-683. Previously announced in STAR as N93-31671 refs A93-54043* National Aeronautics and Space Administration. (Contract RTOP 537-02-00) Lewis Research Center, Cleveland, OH. (ISABE 93-7064) Copyright MATERIAL REQUIREMENTS FOR THE HIGH SPEED CIVIL Ongoing NASA-funded studies by Boeing, McDonnell-Douglas, TRANSPORT General Electric, and Pratt & Whitney indicate that an opportunity JOSEPH R. STEPHENS (NASA, Lewis Research Center, Cleveland, exists for a 21st Century High-Speed Civil Transport (HSCT) to OH), RALPH J. HECHT (Pratt & Whitney Group, West Palm Beach, become a major part of the international air transportation system. FL), and ANDREW M. JOHNSON (GE Aircraft Engines, Cincinnati, However, before industry will consider an HSCT product launch OH) In ISABE - International Symposium on Air Breathing Engines, and an investment estimated to be over $15 billion for design 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 and certification, major technology advances must be made. An Washington American Institute of Aeronautics and Astronautics overview of the propulsion-specific technology advances that must 1993 p. 701-710. refs be in hand before an HSCT product launch could be considered (ISABE 93-7067) Copyright is presented. Under NASA-sponsored High Speed Research (HSR) programs, the materials and processing requirements have been identified A93-54041 for overcoming the environmental and economic barriers of the VARIABLE CYCLE ENGINE CONCEPT next generation High Speed Civil Transport (HSCT) propulsion MICHAEL E. BRAZIER and RANDY E. PAULSON (GE Aircraft system. The long (2 to 5 hours) supersonic cruise portion of the Engines, Cincinnati, OH) In ISABE - International Symposium HSCT cycle will place additional durability requirements on all hot on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, section engine components. Low emissions combustor designs Proceedings. Vol. 1 Washington American Institute of Aeronautics will require high temperature ceramic matrix composite liners to and Astronautics 1993 p. 684-693. refs meet an emission goal of less than 5g NO(x) per Kg fuel burned. (ISABE 93-7065) Copyright Large axisymmetric and two-dimensional exhaust nozzle designs GE powered the first United States jet in 1942. Since that are now under development to meet or exceed FAR 36 Stage III time, demands placed on aircraft systems have increased noise requirements, and will require lightweight, high temperature dramatically. Complexities in airframe requirements and mission metallic, intermetallic, and ceramic matrix composites to reduce profiles have spawned the need for more sophisticated and nozzle weight and meet structural and acoustic component versatile propulsion systems. A system combining the performance performance goals. This paper describes and discusses the of a turbojet in supersonic flight with a turbofan at subsonic flight turbomachinery, combustor, and exhaust nozzle requirements of has many benefits. GE Aircraft Engines (GEAE) has identified a the High Speed Civil Transport propulsion system.

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A93-54045 A93-54055 TANDEM TRANSVERSE HYDROGEN GAS INJECTION INTO A THE COMBUSTION PERFORMANCE OF METHANE-FUELED SUPERSONIC AIRFLOW RAM COMBUSTOR S. NOGUCHI (Ishikawajima-Harima Heavy Industries Co., Ltd., K. SUZUKI and K. SHIMODAIRA (National Aerospace Lab., Chofu, Tokyo, Japan), H. ITOH, Y. KOTANI, and T. NAGASHIMA (Tokyo Japan) In ISABE - International Symposium on Air Breathing Univ., Japan) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington American Institute of Aeronautics and 2 Washington American Institute of Aeronautics and Astronautics 1993 p. 811-821. refs Astronautics 1993 p. 719-727. refs (ISABE 93-7079) Copyright (ISABE 93-7069) Copyright The flameholder of a methane-fueled ram combustor is studied Hydrogen gas has been injected transversely into Mach 1.8 experimentally by 2D models. Here we have laid stress on the airflow from two circular sonic injectors which are mounted flush stability of the flame and combustion efficiency in the high-velocity and placed in tandem along the center line of the bottom wall flow of 100 m/s at 600 K. We have chosen the V-gutter as the plate of a test section. Both cold and hot (i.e., atmospheric and basic structure of the flameholder. But the simple gutter cannot heated to max 1460 K stagnation temperature) air flow conditions have enough ability to stabilize the flame in such a flow. Therefore, were tested. In the cold flow experiments, detailed measurements we have equipped the gutter with some short cylinders to induce were successful, and the tandem injection results showed a marked some pairs of small jets impinging oppositely. These pairs of jets difference from the single injection results in the pattern of shock play a very important part in stabilizing the primary flame and in waves and the distribution of pressure and hydrogen concentration increasing the combustion efficiency. In order to increase the near the injector region. Upon changing the injection pressure combustion efficiency, two ways of injecting the fuel gas are tested ratio between the two injectors, it has been revealed that a prior and evaluated. The first case is that the fuel is injected far upstream injection upstream of the main injection would be beneficial in of the flameholder and premixed with the air completely. The other terms of the total pressure loss in the air flow and the hydrogen case is that the fuel is injected inside the flameholder and makes concentration near the injector region while maintaining the mixing the diffusion flame. The higher combustion efficiency is observed performance. The flow features showed in general little difference in the latter case. A combustion efficiency of more than 95 percent as the air flow temperature was raised until the hydrogen burning is obtained. There are several rows of flameholders in the actual was observed; then the results became inevitably more qualitative ram combustor. In this case the combustion performance is than quantitative. Contrary to expectations from the cold flow tests, influenced by the other flameholder located nearby. The interaction a prior injection of cold hydrogen has resulted in quenching the effect has been investigated experimentally using the 2-row main injector flame. Author (revised) flameholder model. Author (revised)

A93-54056 A93-54048 STUDIES ON METHANE-FUEL RAM COMBUSTOR FOR HST DIRECT SIMULATION OF REACTING FUEL GAS FLOWS IN A COMBINED CYCLE ENGINE SUPERSONIC MIXING LAYER Y. KINOSHITA, J. KITAJIMA, Y. SEKI (Akashi Technical Inst., S. OBATA and T. NAGASHIMA (Tokyo Univ., Japan) In ISABE Japan), and A. TATARA (Kawasaki Heavy Industries, Ltd., Japan) - International Symposium on Air Breathing Engines, 11th, Tokyo, In ISABE - International Symposium on Air Breathing Engines, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 American Institute of Aeronautics and Astronautics 1993 p. Washington American Institute of Aeronautics and Astronautics 739-745. refs 1993 p. 822-830. Research supported by New Energy and (ISABE 93-7072) Copyright Industrial Technology Development Organization refs Direct simulation Monte Carlo method based on the Boltzmann (ISABE 93-7080) Copyright equation has been employed to analyze fuel gas mixing and This paper describes experimental studies on a methane-fuel reaction in 2D supersonic shear flow which is formed due to the ram combustor for the super/hypersonic transport propulsion meeting at a thin plate (lip) edge of two parallel flows, a supersonic system. A laboratory scale combustor was fabricated and air stream and a sonic hydrogen gas flow. The influence of combustion tests were carried out at the conditions of flight Mach hydrogen gas temperature upon the mixing within the shear layer 3 and Mach 5. Vitiation technique was used to simulate the air has been clarified, and by applying 16 reaction system the temperature of Mach 5 conditions. Ignition and flame stability relationship between the mixing and the endo/exothermic reaction characteristics were obtained at the temperature condition of Mach region has been analyzed to reveal the details of the ignition 3. Combustion characteristics, such as combustion efficiency, NO(x) process. Author (revised) emissions and pressure loss were measured at Mach 3 and Mach 5 conditions. Autoignition was observed clearly at high inlet air A93-54049 temperature conditions. The results indicate that the combustion A NEW COOLING SYSTEM FOR ULTRA HIGH TEMPERATURE efficiency at Mach 3 and the NO(x) emissions and autoignition at TURBINES Mach 5 are critical problems for the ram combustor. T. YOSHIDA, M. TAKI, F. MIMURA, T. KUMAGAI (National Aerospace Lab., Chofu, Japan), T. MAYA, and S. YAMAWAKI A93-54058 (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan) TEST RESULTS OF THE HYDROGEN FUELED MODEL In ISABE - International Symposium on Air Breathing Engines, COMBUSTOR FOR THE AIR TURBO RAMJET ENGINE 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 TAKESHI KASHIWAGI, MASAKAZU OBATA, YOUJI OHKITA Washington American Institute of Aeronautics and Astronautics (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan), 1993 p. 749-756. refs NOBUHIRO TANATSUGU, and YOSHIHIRO NARUO (Inst. of (ISABE 93-7073) Copyright Space and Astronautical Science, Sagamihara, Japan) In ISABE The authors have proposed a new concept of a combined - International Symposium on Air Breathing Engines, 11th, Tokyo, cooling system for ultrahigh temperature gas turbines in which Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington turbine inlet temperature is elevated at around 1700 C or higher. American Institute of Aeronautics and Astronautics 1993 p. The present paper deals with the introduction of the combined 838-845. refs cooling system consisting of ultrahigh temperature turbine (ISABE 93-7082) Copyright elements, heat pipes, and heat exchangers, a description of the The mixer type flameholder, combining in a single unit the successful manufacture of two kinds of turbine elements and a mixer and flameholder to equip air turbo ramjet engine combustors, high temperature heat pipe both for heat transfer experiments, with a view to more compact combustor design, has been improved and some reports of experimental studies of the heat pipe. to enhance the mixing of hydrogen fuel with air, with a mixer Author (revised) configuration that increases the momentum imparted to the fuel

1201 07 AIRCRAFT PROPULSION AND POWER

and air. Comparative tests performed on a land-based stationary has been expanded to cover the range from 25,000 to 30,000 bench covering both gutter and mixer types of flameholder have pounds of thrust, with models designed for aircraft fuselage side shown the improved mixer type flameholder to provide performance mounting as well as conventional, under-the-wing mounting. These at least equal to the gutter type in terms of: the absence of flame new models are designated the V2500-A5 for Airbus aircraft detachment, flame temperature distribution in the combustion installations, and the V2500-D5 for Douglas aircraft installations. chamber, allowable range of fuel equivalence ratio for stable The engines incorporate numerous design features, representing flameholding, and absence of flame instability. The improved mixer the latest aircraft engine technology, for increased thrust, improved type flameholder, while raising the flameholder temperature to the fuel efficiency, lower gaseous emissions, and lower noise than extent of calling for protective measures, and while remaining to the earlier -A1 model and other engines in its class. An extensive be further tested for actual combustion performance, promises test and development program led to simultaneous certification of successful practical application to ATR engine combustors, bringing the -A5 and -D5 models by the FAA in November of 1992. Since with it the possibility of realizing a more compact combustor then, the engines have been undergoing concurrent flight testing design. Author (revised) powering the Airbus A320 and A321, and the McDonnell Douglas MD-90 aircraft. V2500 engine development is continuing to further A93-54059 improve fuel efficiency, and to introduce a new combustor NUMERICAL SIMULATION OF RAMJET AND SCRAMJET technology for a further reduction in emissions. Author (revised) COMBUSTION USING TWO-DIMENSIONAL EULER EQUATIONS WITH FINITE RATE CHEMISTRY A93-54063 I. S. AKMANDOR (Middle East Technical Univ., Ankara, Turkey) PERFORMANCE AND CONFIGURATION ANALYSIS OF and UGUR ARKUN (Roketsan Missiles Industries, Inc., Ankara, JET-ENGINE OFF-DESIGN BEHAVIOR Turkey) In ISABE - International Symposium on Air Breathing U. GHEZZI, S. PASINI, L. FERRI DEGLI ANTONI, R. ANDRIANI Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. (Milano, Politecnico, Milan, Italy), and F. GAMMA (Roma I, Univ., 2 Washington American Institute of Aeronautics and Rome, Italy) In ISABE - International Symposium on Air Breathing Astronautics 1993 p. 846-855. refs Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. (ISABE 93-7083) Copyright 2 Washington American Institute of Aeronautics and Two dimensional/axisymmetric ramjet and scramjet combustion Astronautics 1993 p. 903-908. refs has been modeled with an implicit flux vector splitting scheme (ISABE 93-7087) Copyright which has been used for the solution of the conservative form of An analysis is conducted of the global off-design behavior of the Euler equations. A weakly coupled chemistry model has been an aircraft gas turbine engine. Attention is given to the ways in used to simulate the finite rate combustion of Hydrogen-Air and which the choice of a suitable working line facilitates the Kerosene-Air mixtures. The scheme is first order upwind. A realistic optimization of performance characteristics with respect to such multicomponent two step chemistry model has been used for H2-Air factors as thrust and/or specific fuel consumption. It is emphasized combustion. Kerosene-Air combustion has been modeled with a that variable-geometry turbine components are able to yield the single step, irreversible global reaction mechanism. Numerical degree of operational flexibility associated with many stages on results are compared with reacting ramp channel and non-reacting the basis of fewer stages. AIAA duct flow test cases. Flame holding capability of oblique shock wave has been illustrated. Related specific impulse have also been A93-54064 reported. DEVELOPMENTS TOWARDS VERSATILITY IN DIGITAL ENGINE CONTROL UNITS A93-54060 G. WALLE (BGT - Bodenseewerk Geraetetechnik GmbH, FINITE-RATE H2/AIR COMBUSTION EFFECTS IN CRJ FOR Ueberlingen, Germany) In ISABE - International Symposium on HYPERSONIC LAUNCHERS Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, M. CASSETTI (Rome I, Univ., Italy), F. BIAGIOLI (Centre for Proceedings. Vol. 2 Washington American Institute of Aeronautics Advanced Studies, Research and Development in Sardinia, Cagliari, and Astronautics 1993 p. 909-918. Research supported by Italy), and C. BRUNO (Rome I, Univ., Italy) In ISABE - International BGT - Bodenseewerk Geraetetechnik GmbH refs Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. (ISABE 93-7088) Copyright 20-24, 1993, Proceedings. Vol. 2 Washington American Institute The main features of modern digital engine control units are of Aeronautics and Astronautics 1993 p. 856-865. refs described on the basis of realized FADEC units for small (ISABE 93-7084) Copyright aeroengines. They show that FADEC units have become very Comparisons of numerical results with available experimental powerful, reliable, and indispensable accessories in modern data from an atmospheric H2/CO/N2/air flame are here used to engines. Control of future engine generations is, in principle, evaluate the accuracy of physical models used to numerically possible with present FADEC units as demonstrated by the results simulate the flowfield in a turbulent combustor with nonpremixed of experiments on a digitally controlled APU-demonstrator with injection of hydrogen and air, as would be involved in such future H2-combustion. Nevertheless the versatility of today's units for airbreathing hypersonic propulsion systems as that of Saenger. their use in different applications is still unsatisfactory. By analogy Attention is given to test results for a novel kinetics model based with the engine manufacturer's philosophy of a core that is reusable on the two independent scalars of mixture fraction and a kinetic in a product family by modifying the fan, a core digital engine progress variable. Large emissions of unconsumed H2 are control unit which easily and rapidly evolves into a customer predicted, as confirmed by tests. AIAA dedicated specific unit is defined. A dual processor architecture with a microcontroller for input/output and a microprocessor for A93-54061 main processing, a software structure with strong segregation of NEW DEVELOPMENTS WITH THE V2500 ENGINE hardware near-, executive- and application software, large spare G. J. SEVICH (Pratt and Whitney Group, East Hartford, CT), T. capacities in hardware and software, and flexibility to single or ALLAN (Rolls-Royce, PLC, London, United Kingdom), K. ISHIZAWA dual lane architectures are the main elements of a versatile engine (Japanese Aero Engines Corp., Japan), L. SCHWEIKL (MTU control concept, which is detailed in the paper. Author (revised) Motoren- und Turbinen-Union Muenchen GmbH, Munich, Germany), and G. BENSI (Fiat Aviazione S.p.A., Turin, Italy) In ISABE - A93-54065 International Symposium on Air Breathing Engines, 11th, Tokyo, THERMODYNAMIC AND NEUTRAL NETWORK COMPUTER Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington MODELLING OF IMPLANTED COMPONENT FAULTS IN A GAS American Institute of Aeronautics and Astronautics 1993 p. TURBINE ENGINE 869-894. J. D. MCLEOD (National Research Council of Canada, Ottawa) (ISABE 93-7085) Copyright In ISABE - International Symposium on Air Breathing Engines, The International Aero Engines V2500 aircraft engine family 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2

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Washington American Institute of Aeronautics and Astronautics surface. Both nozzles have an aspect ratio of 0.6, a turning angle 1993 p. 919-928. refs of 76 degrees, a mean exit Mach number of 1.2, and the same (ISABE 93-7089) Copyright conical outer wall contour. The experiments were conducted in a A gas turbine fault analysis methodology study has devel- large scale, single stage test facility with representative Mach and oped both thermodynamic and neural-network (Al-oriented) Reynold's numbers. Measurements in the form of nozzle and rotor computer-simulation engine models, whose results are presented exit surveys showed that the new nozzle has 8 percent lower and compared with experimental data. It is found that the effects losses as compared to the baseline and that the stage efficiency of 6-percent turbine nozzle erosion are both measurable and improved by 0.9 points. Comparison of the experimental results accurately simulated by both computer models. The parameters with those obtained from a 3D Euler flow solver is presented. most affected were compressor pressure ratio, fuel flow, and specific fuel consumption. The effects of turbine blade untwist are A93-54073 also important for engine performance. AIAA A COMPARATIVE ASSESSMENT OF TWO PRESENT GENERATION TURBINE ANALYSIS CODES A93-54066 KEVIN G. KILLEY (Council for Scientific and Industrial Research, DESIGN OF LIMIT-TRACKING SYSTEMS INCORPORATING A Aerotek, Pretoria, South Africa) and GRAHAM SMITH (Natal Univ., TURBOFAN ENGINE WITH CONSTANT DISTURBANCES Durban, South Africa) In ISABE - International Symposium on HIDEAKI YAMANE (Japan Defense Agency, Technical Research Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, and Development Inst., Tachikawa, Japan) and BRIAN PORTER Proceedings. Vol. 2 Washington American Institute of Aeronautics (Salford Univ., United Kingdom) In ISABE - International and Astronautics 1993 p. 991-999. refs Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. (ISABE 93-7097) Copyright 20-24, 1993, Proceedings. Vol. 2 Washington American Institute Two current analysis codes, LOSS3D and BTOB3D, are of Aeronautics and Astronautics 1993 p. 929-936. refs independently verified against certain experimental data in an (ISABE 93-7090) Copyright attempt to establish an analysis confidence level. The experimental A methodology is proposed for the design of limit-tracking results are presented on the basis of a series of tests performed systems incorporating multivariable plants with more outputs than on the VKI turbine blade, in the AEROTEK plane cascade wind inputs. The plants are subjected to unknown constant disturbances. tunnel. Once these experimental results were validated against The synthesis problem of limit-tracking systems and the design of the European Cascade Results, they formed the direct inputs into separate digital set-point tracking controllers are discussed. An the two analysis codes. Typically, the accuracy of the codes in implementation procedure is formulated in order to integrate predicting loss coefficients, exit flow angles, and blade surface separate controllers into a self-selecting controller with lowest-wins pressure distributions were evaluated. A version of LOSS3D (Euler strategies. The effectiveness of such controllers is "illustrated by Code) that included a blockage model, and the standard 3D designing limit-tracking systems incorporating a linear turbofan BTOB3D Navier-Stokes code, were used in the computation of engine model with disturbances. total pressure loss. Predicted and measured loss coefficient and flow angles were compared with standard design loss A93-54067 correlations. Author (revised) NEURAL NETWORK FAULT DIAGNOSIS OF A TURBOFAN ENGINE A93-54081 RICHARD EUSTACE (Defence Science and Technology STARTING CHARACTERISTICS OF SCRAMJET INLETS Organisation, Aeronautical Research Lab., Melbourne, Australia) KOUICHIRO TANI, TAKESHI KANDA (National Aerospace Lab., In ISABE - International Symposium on Air Breathing Engines, Kakuda, Japan), and TATSURU TOKUNAGA (Mitsubishi Heavy 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Industries Co., Ltd., Komaki, Japan) In ISABE - International Washington American Institute of Aeronautics and Astronautics Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 1993 p. 937-946, refs 20-24, 1993, Proceedings. Vol. 2 Washington American Institute (ISABE 93-7091) Copyright of Aeronautics and Astronautics 1993 p. 1071-1080. refs In this paper neural networks are applied to the problem of (ISABE 93-7105) Copyright fault detection and diagnosis in a turbofan engine. Steady state A series of scramjet inlet models were experimentally data are obtained from six different implanted faults involving investigated in a Mach 4 wind tunnel. The effects of sweep angle compressor variable geometry and exhaust nozzle area adjustment. and contraction ratio to the starting characteristics and aerodynamic Two different network architectures are applied to the problem performances were examined, as well as the effect of the inflow and a comparison is made. The first method uses a standard boundary layer. Top wall pressures along the center line of the back-propagation network, whilst the second method uses a inlets were measured, and mass capture ratio and total pressure Learning Vector Quantization (LVQ) network. Results show both efficiency were evaluated for each model. The internal flow of the networks achieve very high accuracy. The LVQ network has the inlets was visualized by the Schlieren method and the oil flow advantage of being quick to train, while the back-propagation technique. All these data indicated that there existed a gradual network gives an indication of the confidence of its diagnosis. transition from start to unstart condition. With a thin boundary The question of robustness is also discussed. Neural networks layer, aerodynamic performances were good and showed more are shown to be a useful diagnostic tool provided sufficient training sensitivity to the change of the contraction ratio. When the model data are available. had a large rearward sweep angle, e.g., 60 deg, in this testing, its aerodynamic performances were not good, but it easily started. A93-54072 The total pressure efficiency depended on the throat to freestream EFFECT OF NOZZLE DESIGN ON THE PERFORMANCE OF A Mach number ratio, not on the particular configurations. The HIGHLY LOADED TURBINE STAGE separation area was large in the forward sweep models, and the S. GIRGIS, S. H. MOUSTAPHA (Pratt & Whitney Canada, Inc., models showed poor starting characteristics. Author (revised) Montreal), and U, W. SCHAUB (National Research Council of Canada, Ottawa) In ISABE - International Symposium on Air A93-54084 Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, OFF-DESIGN PERFORMANCE OF SCRAMJET NOZZLES Proceedings. Vol. 2 Washington American Institute of Aeronautics TETSUO HIRAIWA, SHUUICHI UEDA, SHIGERU SATO, TOHRU and Astronautics 1993 p. 984-990. refs MITANI (National Aerospace Lab., Kakuda, Japan), MASAHIKO (ISABE 93-7096) Copyright YAMAMOTO (Ishikawajima-Harima Heavy Industries Co., Ltd., As part of a research program on the performance of a highly Tokyo, Japan), and MASASHI MATSUMOTO (Ishikawajima-Harima loaded turbine stage, two different nozzle designs were tested. A Heavy Industries Co., Ltd., Yokohama, Japan) In ISABE - baseline design and a new design which features leading edge International Symposium on Air Breathing Engines, 11th, Tokyo, ramps, tangential lean, and negative curvature on the suction Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington

1203 07 AIRCRAFT PROPULSION AND POWER

American Institute of Aeronautics and Astronautics 1993 p. and Astronautics 1993 p. 1153-1163. refs 1103-1114. refs (ISABE 93-7113) Copyright (ISABE 93-7108) Copyright Measurements have been carried out in the exhaust plume of An experimental study of NASP-like nozzles is presented. This a small turbojet engine. The measurements were taken in a study was conducted to investigate the nozzle flow affected by horizontal plane containing the central axis of the plume and they the ambient pressure. In order to elucidate the aerodynamic extended to 20 nozzle exit diameters downstream of the nozzle properties of the nozzle flow, detailed measurements of thrust, exit. The measured flow quantities included total temperature, total wall pressure and heat flux were carried out using cold nitrogen. and static pressure, and CO2 volume fraction. Cross-stream The nozzle flow was also visualized using a shear sensitive liquid profiles, centerline profiles and contour maps in the plane are crystal. Under the over-expanded condition, the interaction between presented for measured and calculated flow quantities. the internal flow and the external flow complicates the Computational fluid dynamic predictions have been made and are characteristics of nozzle performance. Wall pressure distributions compared with the experimental data. and shear stress visualization showed that the flow field in over-expanded nozzles can be approximated as a supersonic inlet A93-54100 flow compressed by sidewalls. The high pressure region generated NUMERICAL STUDY OF NITRIC OXIDE FORMATION IN A by shock waves and the boundary layer on the nozzle ramp yields HYPERSONIC RAMJET ENGINE a higher performance in scramjet nozzles than that estimated for P. MUEHLEK and H. SCHUETZ (DLR, Inst. fuer Antriebstechnik, a two-dimensional separation from the ramp. Cologne, Germany) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, A93-54085 Proceedings. Vol. 2 Washington American Institute of Aeronautics EVALUATION OF TURBORAMJET EXHAUST SYSTEMS FROM and Astronautics 1993 p. 1275-1283. refs SCALE MODEL TEST DATA (ISABE 93-7125) Copyright D. J. DUSA (GE Aircraft Engines, Cincinnati, OH) In ISABE - The 3D flowfield in a hypersonic ramjet engine is analyzed International Symposium on Air Breathing Engines, 11th, Tokyo, using a turbulent Navier-Stokes code incorporating finite rate Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington chemistry. The numerical procedure (ALE method) is based on a American Institute of Aeronautics and Astronautics 1993 p. finite volume discretization of the Lagrangian form of the unsteady 1115-1127. refs compressible balance equations. The ramjet configuration (ISABE 93-7109) Copyright investigated in this study consist of a cylindrical combustion Advances in aircraft propulsion system technology over the chamber with axial injection of hydrogen through a star-shaped past decade (in materials, structures, and analytical design injection device and a subsequent rectangular thrust nozzle. The methods), along with those anticipated for the next decade, have injection of hydrogen, the combustion process and the expansion renewed interest in the Mach 4.0 to 6.0 operating regime for both of the gas mixture to supersonic flow speeds is treated within commercial transports and military weapon systems. One of the one computational domain. The combustion processes of the propulsion systems being considered for these applications is the hydrogen as well as the formation of nitric oxide and the chemical dual mode turboramjet engine which utilizes a common inlet and nonequilibrium effects in the nozzle are described by a complex exhaust nozzle for both .modes of operation. With respect to the kinetic reaction mechanism. As a consequence of the axial fuel propulsion system, there are a number of component technologies injection only poor mixing is achieved and stratified reaction zones that will have to be developed before these Mach 4.0 to 6.0 are established. The formation of nitric oxide is controlled by the applications become a reality. Author (revised) local stoichiometry, i.e., temperature level, and the concentration of oxygen atoms.

A93-54086 A93-54102 OBSERVATION OF FLUCTUATION OF 2D-NOZZLE FLOWS A FINITE ELEMENT CODE FOR GAS TURBINE COMBUSTOR TOMOYUKI NAKAMURA and YOKICHI SUGIYAMA (Japan FLOW WITH STRETCHED LAMINAR FLAMELET MODELLING Defense Agency, Technical Research and Development Inst., P. IONTA, D. LENTINI, and F. RISPOLI (Roma I, Univ., Rome, Tachikawa) In ISABE - International Symposium on Air Breathing Italy) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington American Institute of Aeronautics and 2 Washington American Institute of Aeronautics and Astronautics 1993 p. 1128-1133. Astronautics 1993 p. 1293-1304. Research supported by (ISABE 93-7110) Copyright MURST refs In order to determine the fluctuation of 2D nozzle flows, (ISABE 93-7127) Copyright instantaneous flow visualization was carried out using flashing sheet The computational code XENIOS for gas turbine combustor beam for three types of scale models, a boat-tail model, an flow is presented. It introduces powerful solutions for body-fitted internal-aerodynamic model, and a transparent model. Both the grid management and numerical diffusion control, and for finite-rate boat-tail and internal-aerodynamic models made of stainless steel chemistry, which is the focus of the paper. The physical bases of with adjustable nozzle-flaps were tested for exhaust-jet-flow the Stretched Laminar Flamelet model are discussed, then its visualization at jet velocities as high as Mach 1.4, and the application to the prediction of the mean temperature field and of transparent model was tested for internal-flow visualization at jet CO and CO2 concentrations is reported. Results indicate the velocity of approximately 10 m/s. Results show that entrainment important role of finite-rate chemistry. An extension to the prediction of ambient air takes place in an unsteady 3D manner, a smaller of NO emissions is also discussed. aspect ratio enhances the entrainment, and inlet whirl spreads the jets at high speed but it just rotates middle portion of the jets A93-54103 at low speed, resulting in an S-like section flow-pattern in NUMERICAL SIMULATION OF GAS TURBINE COMBUSTORS downstream. Author (revised) WITH COMPLEX GEOMETRIES P. Dl MARTINO and G. CINQUE (Alfa Romeo Avio S.A.p.A., A93-54088 Pomigliano d'Arco, Italy) In ISABE - International Symposium MEASUREMENT AND PREDICTION OF FLOW IN A GAS on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, TURBINE ENGINE EXHAUST PLUME Proceedings. Vol. 2 Washington American Institute of Aeronautics J. MILBANK, S. M. HENBEST, and J. G. BAIN (Defence Science and Astronautics 1993 p. 1305-1320. refs and Technology Organisation, Aeronautical Research Lab., (ISABE 93-7128) Copyright Rshermens Bend, Australia) In ISABE - International Symposium A method is presented for calculating steady three-dimensional on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, two-phase turbulent reactive flows with curved irregular boundaries. Proceedings. Vol. 2 Washington American Institute of Aeronautics The gas phase equations are solved in an Eulerian frame of

1204 08 AIRCRAFT STABILITY AND CONTROL reference by a numerical technique based on the finite volume and instability properties of a 'buried nozzle' system, a configuration approach, while the equations describing droplet motion, which can be found in some turbofan engines, when the outer evaporation and burning are treated in a Lagrangian frame of cowling of the fan extends beyond the inner nozzle which emits reference. Turbulent transport is described by the standard the engine's exhaust gases. In this model, the primary flow issues k-epsilon model. The combustion model utilizes a conserved scalar into a coannular flow within a mixing chamber, and then the formulation and an assumed shape probability density function to coannular flow issues into the ambient medium from a secondary account for chemistry-turbulence interaction. The numerical scheme nozzle. Within the mixing chamber only fine-scale mixing takes employs structured non-orthogonal grids, node-centered variable place, and shear layers within the mixing chamber and downstream arrangement and Cartesian velocity components. A special of the secondary nozzle are assumed to sustain large-scale interpolation procedure is used to avoid checkerboard oscillations instability waves. The response of this system, in the acoustic far due to pressure-velocity coupling and a low diffusive and bounded field and in the mixing chamber, is obtained analytically from the scheme is introduced to approximate the convective terms in the asymptotic solution, at LF, of model subproblems whose solutions transport equations. The capabilities of the numerical procedure determine the wave reflection and transmission processes at the are demonstrated by simulating an annular combustion chamber primary and secondary nozzles. Analytical descriptions are given for which experimental results were available. The agreement of the various wave modes, the acoustic field strength and between calculation and experiments ranges from fair to good. directivity, and the conditions under which near-resonant response may occur, with large amplitudes of the perturbations in the mixing A93-54106 chamber and in the acoustic field. AIAA STRUCTURAL INTEGRITY VALIDATION OF LIMITED-LIFE ENGINES A93-54292 S. NARAYANA SWAMY, V. UNNIKRISHNAN, and R. V. THE T700 ... FROM SALT SPRAY TO SAND BLAST NARAYANA MURTHY (Ministry of Defence, Directorate of ANNA M. LISZEWSKI and GREGORY D. TALLEY (GE Aircraft Aeronautics, Bangalore, India) In ISABE - International Engines, Lynn, MA) In Helicopter operations in severe Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. environments; Proceedings of the Conference, London, United 20-24, 1993, Proceedings. Vol. 2 Washington American Institute Kingdom, June 4, 1992 London Royal Aeronautical Society of Aeronautics and Astronautics 1993 p. 1335-1345. refs 1992 p. 5.1-5.6. refs (ISABE 93-7131) Copyright Copyright The structural design criteria and validation methodology The T700 family of turboshaft and turboprop engines produced evolved concurrently with the development of a limited life low-cost by GE Aircraft Engines that has amassed millions of flight hours turbojet engine incorporating the expendable design concept are operating in a range of abusive environments across five continents described. Relevant hardware distresses revealed during the engine is described. The T700 is a front-drive turboshaft engine of modular testing are analyzed to identify the primary causes. The approach construction based on an inlet particle separator, axi-centrifugal adopted initially is reviewed in the light of the hardware experience compressor, through-flow annular combustor, air-cooled gas gained during development. Validation requirements including a generator turbine, uncooled power turbine, and self-contained lube package of tests to assure structural integrity for this class of system. A sound design approach, extensive and comprehensive low-cost, expendable engine, are suggested. Author (revised) testing, and demonstration of superior mission capability make it possible to successfully meet helicopter engine mission A93-54107 requirements. AIAA DEVELOPMENT OF A REAL TIME DYNAMIC ENGINE SIMULATION MODEL OF A TURBO FAN ENGINE G. BHARGAVA REDDY, SANJAY PALSANE, B. K. LAKSHMANAN, 08 and V. SUNDARARAJAN (Gas Turbine Research Establishment, Bangalore, India) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, AIRCRAFT STABILITY AND CONTROL Proceedings. Vol. 2 Washington American Institute of Aeronautics and Astronautics 1993 p. 1349-1352. refs Includes aircraft handling qualities; piloting; flight controls; and (ISABE 93-7132) Copyright autopilots. Recent developments in fighter aircraft engines have precipitated the requirements of more reliable, dynamic and accurate control systems for the stringent aircraft missions. In A93-52941 order to develop these control systems and to verify their STABILIZATION OF THE DYNAMIC CHARACTERISTICS OF functioning, real-time engine simulation models are inescapable. THE TWO-CHANNEL AUTOMATIC CONTROL SYSTEM OF Large scale non-linear thermodynamic simulation models are not AIRCRAFT [STABILIZATSIYA DINAMICHESKIKH capable of running in real-time even on large computers. KHRAKTERISTIK DVUKHKANAL'NOJ SISTEMY Implementation of simplified model offers an attractive and cheaper AVTOMATICHESKOGO UPRAVLENIYA SAMOLETA] solution. This paper describes the modeling of components in a A. I. BOGOMOLOV and P. K. SEMENOV Aviatsionnaya Tekhnika simplified way and an iteration and integration logic for the state (ISSN 0579-2975) no. 1 1993 p. 17-22. In RUSSIAN refs variables in terms of the partial derivatives. Model is validated for Copyright steady state and transients for different fuel inputs against large A method is proposed for ensuring the stability of the transient scale turbofan engine simulation model and are in fair agreement. process characteristics in the automatic pilot-aircraft system with The time response of engine state variables are also described. considerable crosstalk coupling between the control channels. The approach proposed here is an extension of the method proposed A93-54244 in an earlier study (Bogomolov and Semenov, 1992) for THE LOW FREQUENCY AEROACOUSTICS OF BURIED single-channel systems. The efficiency of the method is illustrated NOZZLE SYSTEMS by an example. AIAA M. V. TAYLOR (International Computers, Ltd., Bracknell, United Kingdom), D. G. CRIGHTON (Cambridge Univ., United Kingdom), A93-52942 and A. M. CARGILL (Rolls-Royce, PLC, Derby, United Kingdom) A METHOD FOR THE SPECTRAL-TIME IDENTIFICATION OF Journal of Sound and Vibration (ISSN 0022-460X) vol. 163, no. THE LONGITUDINAL AND LATERAL MOTIONS OF AN 3 May 22, 1993 p. 493-526. Research supported by SERC AIRCRAFT [METOD SPEKTRAL'NO-VREMENNOJ and Rolls-Royce, PLC refs IDENTIFIKATSM PRODOL'NOGO I BOKOVOGO DVIZHENIYA Copyright SAMOLETA] Results are presented of an investigation of the LF acoustic B. O. KACHANOV and K. B. KHROLOVICH Aviatsionnaya

1205 08 AIRCRAFT STABILITY AND CONTROL

Tekhnika (ISSN 0579-2975) no. 1 1993 p. 22-26. In Based on the bifurcation analysis and catastrophe theory RUSSIAN refs methodology (BACTM), the aircraft global dynamic stability in a Copyright rapid rolling maneuver is studied in this paper. Based on the study A method for the identification of models of the longitudinal of the bifurcation and catastrophe behavior of an aircraft in a and lateral motions of an aircraft is proposed which combines the rapid rolling maneuver entering from the vertical symmetry flight spectral and time approaches. The spectral approach makes it plane, the status of a rapid rolling maneuver entering from the possible to reduce the identification procedure to a linear problem, horizontal turn is discussed further. A general analytical formula while the time approach significantly improves the solution stability for determining the critical rolling rate is derived in the state-control with respect to different kinds of measurement noise. Details of space. It indicates that the Phillips critical rolling rate criterion is the identification procedure are discussed. AIAA only a special case of the general analytical formula developed in this paper. Author (revised) A93-52943 IDENTIFICATION OF THE PHASE CHARACTERISTICS AND A93-53877 WIND-INDUCED PERTURBATIONS OF AN AIRCRAFT FROM HARMONIC OSCILLATION IN FBW SYSTEM FLIGHT TEST RESULTS [IDENTIFIKATSIYA FAZOVYKH RONG S. SHAO (Shenyang Aircraft Research Inst., China) Acta KHARAKTERISTIK I VETROVYKH VOZMUSHCHENIJ Aeronautica et Astronautica Sinica (ISSN 1000-6893) vol. 14, SAMOLETA PO REZUL'TATAM LETNYKH ISPYTANIJ] no. 2 Feb. 1993 p. B66-B71. In CHINESE refs YU. V. KOZHEVNIKOV and A. YU. SIGAEV Aviatsionnaya Taking the research of nonlinear characteristics of the actuator Tekhnika (ISSN 0579-2975) no. 1 1993 p. 27-29. In loop as the point of departure, through the spectrum analysis and RUSSIAN refs the experimental verification, the physical essence of control Copyright surface buffet excited by the high-frequency odd harmonic of the A method for the identification of the phase characteristics of triangular wave in a high-gain fly-by-wire system has been aircraft and wind effects due to atmospheric turbulence is proposed discovered. The necessary condition of harmonic oscillation, as which is based on the decomposition of the identification problem. well as the frequency characteristics and the overcoming measures In the approach proposed here, integral quadratic functionals are of the buffet in FBW system are also presented. These are used as the criteria of identification quality. The method is applicable important references for the design of modern flight control to any kind of aircraft and flight regimes. AIAA systems. Author (revised)

A93-52944 A93-54268 National Aeronautics and Space Administration. Lewis SOLUTION OF THE BOUNDARY VALUE PROBLEM IN FLIGHT Research Center, Cleveland, OH. DYNAMICS BY THE OPPOSITE MOTION METHOD [RESHENIE A PARAMETER OPTIMIZATION APPROACH TO CONTROLLER KRAEVOJ ZADACHI DINAMIKI POLETA METODOM PARTITIONING FOR INTEGRATED FLIGHT/PROPULSION VSTRECHNYKH DVIZHENIJ] CONTROL APPLICATION E. A. KRAMARENKO and O. G. KOVRIZHKIN Aviatsionnaya PHILLIP H. SCHMIDT (Akron Univ., OH), SANJAY GARG (NASA, Tekhnika (ISSN 0579-2975) no. 1 1993 p. 30-34. In Lewis Research Center, Cleveland, OH), and BRIAN R. RUSSIAN refs HOLOWECKY (Akron Univ., OH) IEEE Transactions on Control Copyright Systems Technology (ISSN 1063-6536) vol. 1, no. 1 March A nonoptimization approach is proposed for solving the 1993 p. 21-36. refs boundary value problem of guiding a flight vehicle to a specified (Contract NAG3-1146; RTOP 505-62-50) terminal state on the basis of six phase coordinates. Control Copyright synthesis is carried out in steps using piecewise constant functions. A parameter optimization framework is presented to solve the The method is recommended for the generation of automatic problem of partitioning a centralized controller into a decentralized control signals in guiding a flight vehicle to a specified point on hierarchical structure suitable for integrated flight/propulsion control the basis of six phase coordinates in relatively simple maneuvers. implementation. The controller partitioning problem is briefly AIAA discussed and a cost function to be minimized is formulated, such that the resulting 'optimal' partitioned subsystem controllers will A93-53621 closely match the performance (including robustness) properties NON-LINEAR FLIGHT DYNAMICS of the closed-loop system with the centralized controller while PH. GUICHETEAU (ONERA, Chatillon, France) ONERA, TP no. maintaining the desired controller partitioning structure. The cost 1993-109 1993 14 p. NATO, AGARD, Lecture Series on Non function is written in terms of parameters in a state-space Linear Dynamics and Chaos, 191st, Stanford Univ., CA, June 9-11, representation of the partitioned sub-controllers. Analytical 1993 and Valbonne, France, June 16-18, 1993 Research expressions are obtained for the gradient of this cost function supported by Services Techniques des Programmes with respect to parameters, and an optimization algorithm is Aeronautiques refs developed using modern computer-aided control design and (ONERA, TP NO. 1993-109) analysis software. The capabilities of the algorithm are Techniques are presented for more accurately characterizing demonstrated by application to partitioned integrated aircraft behavior in flight regimes for which classical linearized flight/propulsion control design for a modern fighter aircraft in the analyses of nonlinear differential equations are either insufficient short approach to landing task. The partitioning optimization is or invalid. Bifurcation theory is shown to be applicable to such shown to lead to reduced-order subcontrollers that match the simple nonlinear phenomena as the Dutch roll instability. Attention closed-loop command tracking and decoupling performance is given to the results yielded by an application of bifurcation achieved by a high-order centralized controller. theory to the actual dynamical behavior of the Alpha-Jet military trainer, with a view to oscillatory motions and the results of a A93-54277 sensitivity analysis of departures and spin predictions for a given LONGITUDINAL CLOSED-LOOP PILOT/VEHICLE ANALYSIS set of parameters. AIAA OF DFBW AIRCRAFT DURING APPROACH AND LANDING YACHANG FENG, WANG Z. LIN, W. YONG, and CHEN GANG A93-53869 (Beijing Univ. of Aeronautics and Astronautics, China) Zeitschrift A STUDY OF AIRCRAFT GLOBAL DYNAMIC STABILITY IN fuer Flugwissenschaften und Weltraumforschung (ISSN RAPID ROLLING MANEUVER 0342-068X) vol. 16, no. 6 Dec. 1992 p. 357-362. refs CHANG LIU, JI-PING DING, and MING JIANG (Nanjing Aeronautical Copyright Inst., China) Acta Aeronautica et Astronautica Sinica (ISSN According to flight test data and pilot flying experience, a 1000-6893) vol. 14, no. 2 Feb. 1993 p. B7-B12. In frequency domain pilot model is developed with its parameters CHINESE refs varying through the approach and landing task. The DFBW aircraft

1206 09 RESEARCH AND SUPPORT FACILITIES (AIR) closed-loop pilot/vehicle model is formulated in this paper. The L D. ALLEN (CAE Electronics, Montreal, Canada) In AIAA nonlinear time domain computer numerical simulation gives a Flight Simulation Technologies Conference, Monterey, CA, Aug. quantitative analysis of aircraft longitudinal landing dynamic 9-11, 1993, Technical Papers Washington American Institute characteristics. The simulation result agrees well with the flight of Aeronautics and Astronautics 1993 p. 1-11. refs test of MCS aircraft. Thus the accuracy of both mathematical (AIAA PAPER 93-3545) Copyright models and simulation computer programs is validated. Many The paper describes the progress made in flight simulation beneficial results are obtained which show that the landing technology, starting with the first flight simulator, introduced in dynamics of some types of DFBW aircraft are acceptable. 1910 (the Sanders Teacher). Consideration is given to the early pilot-training devices (such as the Sanders Teacher, the Walters A93-54278 machine, and the Antoinette 'apprenticeship barrel' trainer); the AN AERODYNAMIC MODEL FOR THE LONGITUDINAL Link Trainer, introduced in 1929; and the Celestial Navigation MOTION OF FLIGHT TRAINING DEVICES [EIN Trainer, designed in 1939; these were ground-based aircraft or AERODYNAMISCHES MODELL FUER DIE aircraft simulating structures subjected to outside disturbances. LAENGSBEWEGUNG VON FLUGUEBUNGSGERAETEN] The development and evolution of the analog simulators, the R. BRAUNSTINGL (Graz, Technische Univ., Austria) Zeitschrift electronic simulator, and the modern simulator are then discussed, fuer Flugwissenschaften und Weltraumforschung (ISSN together with the digital computer techniques for flight simulation, 0342-068X) vol. 16, no. 6 Dec. 1992 p. 363-369. In the evolution of motion systems, and various visual systems for GERMAN refs producing 'out-the-window' visual scenes, with particualr attention Copyright given to the Dome Display and the Helmet Mounted Display. Also The paper at hand presents a simulation model for the discussed are data problems, the programming language, regulation longitudinal motion of fixed-wing aircraft. This model provides for of simulators, international standards, and the Advance a more realistic, type-specific flight simulation than has been Qualification Program regulations being presently developed by standard in general aviation until now. The model is meant to be simulator manufacturers and airlines. AIAA applied to flight training devices used in pilots' training and has already been put to the test there. It describes aerodynamic forces in the longitudinal plane of the aircraft and the pitching moment A93-52655# with the states of flight normally encountered in training courses. Choosing appropriate values for the model parameters makes it METHODOLOGY FOR INTEGRATION OF DIGITAL CONTROL possible to adapt the same model for different types of aircraft. LOADERS IN AIRCRAFT SIMULATORS AMNON KATZ and MARC F. SCHAMLE (Alabama Univ., The exactness with which the model renders the flight performance Tuscaloosa) In AIAA Flight Simulation Technologies Conference, data is demonstrated with an example. The measured flight Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington performance data of a PIPER PA28RT-201T, TURBO ARROW IV are compared with the model's simulation results. American Institute of Aeronautics and Astronautics 1993 p. 36-43. Research supported by FAA and Univ. of Alabama refs Author (revised) (AIAA PAPER 93-3551) Copyright A procedure is defined and demonstrated for programming a digital control loader in a flight simulator. The loader makes up 09 for the difference in control force between simulator and aircraft. Aerodynamic forces, inertial effects and artificial feel systems in RESEARCH AND SUPPORT FACILITIES (AIR) the aircraft are all included. Inertial effects and artificial feel systems in the simulator, if any, are accounted for. Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tube facilities; and engine test blocks. A93-52665# VISUAL WEATHER SIMULATION USING METEOROLOGICAL DATABASES A93-52651 BRUCE MONTAG (Southwest Research Inst., San Antonio, TX) AIAA FLIGHT SIMULATION TECHNOLOGIES CONFERENCE, In AIAA Flight Simulation Technologies Conference, Monterey, MONTEREY, CA, AUG. 9-11, 1993, TECHNICAL PAPERS CA, Aug. 9-11, 1993, Technical Papers Washington American Washington American Institute of Aeronautics and Astronautics Institute of Aeronautics and Astronautics 1993 p. 114-122. 1993 378 p. For individual items see A93-52652 to A93-52695 refs Copyright (AIAA PAPER 93-3566) Copyright Papers presented in this volume are grouped under the topics This paper presents the results of an internal research program of flight simulation history, simulation modeling, simulation facilities, at Southwest Research Institute for the development of a visual human factors and pilot cueing, modeling the simulation weather simulation and modeling system for flight training environment, simulation applications, motion systems, simulation applications. This weather simulation system concept, first networking, software engineering, simulation validation and presented at the 1990 AIAA Flight Simulation Technology verification, pilot training, and in-flight simulation. Particular Conference, provides the means to correlate and synchronize all consideration is given to the aircraft threat modeling from weather-related cues presented to the aircrew. The approach performance data, a high-fidelity video delivery system for real-time provides for direct correlation between out-the-window visual flight simulation research, a multistage integration model for human weather scenes, weather-processing sensor avionics displays, and egomotion perception, terrain modeling for real-time aircraft handling qualities through the use of a unified phototexture-based visual simulation, and use of a simulator in meteorological database. By ensuring dynamic weather cue aircraft accident investigation. Attention is also given to simulating correlation across all simulator subsystems, this technique enables motion effects on single-axis compensatory tracking, representation simulator instruction in weather-related flying to be highly of vehicle location in networked simulations, a reusable code for transferable to in-flight, mission-oriented situations. This research helicopter simulation, a flexible graphical simulation monitoring effort produced a unique method for generating real-time fly-through system, the future of flying work modeling for pilot educational weather conditions on a polygon-based visual system. The model tasks, and a rapid prototyping system for in-flight simulation using architecture also supports sensor simulation for driving forward-look the Calspan Learjet 25. AIAA wind profiling models and cockpit displays. Since the weather model is driven by gridded-field, digital meteorological data, aircrews can A93-52652# learn and practice line-oriented weather avoidance skills in a EVOLUTION OF FLIGHT SIMULATION realistic simulated weather environment. Author (revised)

1207 09 RESEARCH AND SUPPORT FACILITIES (AIR)

A93-52668# to develop an accurate real-time simulation in a timely, efficient A PRIMARY FLIGHT DISPLAY FOR FOUR-DIMENSIONAL manner. The SimLab facility and the software tools necessary for GUIDANCE AND NAVIGATION INFLUENCE OF TUNNEL SIZE an operating simulation will be discussed. Subsequent sections AND LEVEL OF ADDITIONAL INFORMATION ON PILOT will describe the development process through operation of the PERFORMANCE AND CONTROL BEHAVIOUR simulation; this includes acceptance of the model, validation, E. THEUNISSEN (Delft Univ. of Technology, Netherlands) In integration and production phases. AIAA Flight Simulation Technologies Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington American Institute A93-52673# of Aeronautics and Astronautics 1993 p. 140-146. refs SEMI-FULL-SCALE DYNAMIC SIMULATION COMPLEX ON (AIAA PAPER 93-3570) Copyright THE BASIS OF CENTRIFUGE A perspective display has been developed which integrates V. M. VASILETS (Inst. of Aviation and Space Medicine, Moscow, primary flight symbology with guidance and short-term navigation Russia) and O. A. YAKIMENKO (Military Air Force Engineering information. This serves to keep the pilot in the loop in a Academy, Moscow, Russia) In AIAA Flight Simulation four-dimensional ATC environment, and makes use of his ability Technologies Conference, Monterey, CA, Aug. 9-11, 1993, to oversee complex problems at a glance. The display can be Technical Papers Washington American Institute of Aeronautics used for both manual and for supervisory control, and has been and Astronautics 1993 p. 187-192. implemented in the moving-base flight simulator of the Delft (AIAA PAPER 93-3577) Copyright University of Technology. Several parameters in a perspective The paper considers a structure and fundamental characteristics display can be used to influence pilot performance and control of semifull-scale imitative dynamic simulation complex (IDSC) on behavior. To gain more insight in the underlying relations, an the basis of centrifuge. Capacities of the complex are illustrated experiment has been conducted to determine the influence of graphically with some results made of different experimental works tunnel size, flightpath vector and flightpath predictor configurations on investigation, optimization, and ergonomic justification of on pilot performance and control behavior. It was found that a performances of the closed loop 'pilot-control system- smaller tunnel yields better performance, while control behavior aircraft-environment' with different composition of antistress can be kept at a constant level by introduction of a flightpath facilities, different configuration of controls, and action of different predictor. flight factors. It must be emphasized that the represented results have a rather particular character, because they pursue an aim A93-52670# only to show IDSC capacities for imitative modeling of the THE DEVELOPMENT OF SIMONA - A SIMULATOR FACILITY investigation, design, and test of the flying-machine's specific FOR ADVANCED RESEARCH INTO SIMULATION tasks. Author (revised) TECHNIQUES, MOTION SYSTEM CONTROL AND NAVIGATION SYSTEMS TECHNOLOGIES A93-52675*# National Aeronautics and Space Administration. S. K. ADVANI (Delft Univ. of Technology, Netherlands) In AIAA Ames Research Center, Moffett Field, CA. Flight Simulation Technologies Conference, Monterey, CA, Aug. SIMULATION MOTION EFFECT ON SINGLE AXIS 9-11, 1993, Technical Papers Washington American Institute COMPENSATORY TRACKING of Aeronautics and Astronautics 1993 p. 156-166. Research JEFFERY A. SCHROEDER (NASA, Ames Research Center, Moffett supported by NWO refs Field, CA) In AIAA Flight Simulation Technologies Conference, (AIAA PAPER 93-3574) Copyright Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington The design and development of a new-technology American Institute of Aeronautics and Astronautics 1993 p. six-degrees-of-freedom research simulator at the Delft University 202-213. refs of Technology is described. This simulator will incorporate an (AIAA PAPER 93-3579) Copyright advanced hydraulic motion system and a light-weight moving An experiment that examined how changes in a motion platform platform for outstanding dynamic performance. The simulator will drive filter affect pilot-vehicle performance and opinion was become the core of the new International Centre for Research in conducted on the NASA Ames Vertical Motion Simulator. Pilots Simulation, Motion and Navigation Technologies, or 'SIMONA'. controlled a simplified helicopter model in the vertical or the Fundamental research in the SIMONA facility will be aimed towards directional axis and tracked a randomly moving target aircraft in the development of simulation modeling techniques, for the the presence of a random disturbance. With both tasks, variations refinement of motion system control, and for investigations into from full motion to fixed-base conditions were made in the high-pass pilot interactions in realistic navigation environments. This simulator, drive filter gain and natural frequency. The results indicate that now under construction, can be configured to represent a wide vertical motion did not affect the open-loop pilot-vehicle variety of vehicles including fixed and rotary-wing aircraft as well target-tracking crossover frequency, but target-tracking phase as surface vehicles for land and sea operations. This results in a margins improved with increased filter gain or decreased natural variety of multidisciplinary research roles for the simulator. frequency. Vertical disturbance-rejection crossover frequency Author (revised) increased with decreasing filter natural frequency, while disturbance rejection phase margins improved with increasing filter gain. Vertical A93-52671*# National Aeronautics and Space Administration. tracking errors increased significantly when all vertical motion was Ames Research Center, Moffett Field, CA. removed. No significant differences were measured among the DEVELOPMENT AND OPERATION OF A REAL-TIME directional configurations, which indicates that pure yaw motion SIMULATION AT THE NASA AMES VERTICAL MOTION cues may not be as important as previously thought in flight SIMULATOR simulation. CHRISTOPHER SWEENEY, SHIRIN SHEPPARD, and MONIQUE CHETELAT (SYRE; NASA, Ames Research Center, Moffett Field, A93-52676# CA) In AIAA Flight Simulation Technologies Conference, PILOT EVALUATIONS OF AUGMENTED FLIGHT SIMULATOR Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington MOTION American Institute of Aeronautics and Astronautics 1993 p. STUART T. GARROOD and LLOYD D. REID (Toronto Univ., 167-173. refs Downsview, Canada) In AIAA Flight Simulation Technologies (AIAA PAPER 93-3575) Copyright Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers The Vertical Motion Simulator (VMS) facility at the NASA Ames Washington American Institute of Aeronautics and Astronautics Research Center combines the largest vertical motion capability 1993 p. 214-221. Research supported by NSERC refs in the world with a flexible real-time operating system allowing (AIAA PAPER 93-3580) Copyright research to be conducted quickly and effectively. Due to the diverse In an earlier paper it was proposed that the turbulence induced nature of the aircraft simulated and the large number of simulations motion of a flight simulator could be augmented without affecting conducted annually, the challenge for the simulation engineer is the visual and instrument displays. This may be necessary if the

1208 09 RESEARCH AND SUPPORT FACILITIES (AIR) simulator's washout filters severely restrict its motion response to technique is used to conduct flight dynamics research of high atmospheric turbulence. The present study has implemented the performance aircraft using dynamically scaled models. The proposed technique on the University of Toronto Institute for free-flight drop model flight testing supplements research using Aerospace Studies Flight Research Simulator and carried out pilot computer analysis and wind tunnel testing. The drop models are evaluations for both high altitude and low altitude operations in scaled to approximately 20 percent of the size of the actual aircraft. the presence of atmospheric turbulence. The results indicate that This paper presents an introduction to the Free-Flight Drop Model the technique can successfully increase the simulator's motion Program which is followed by a description of the current response to turbulence in a manner that is acceptable to pilots. It instrumentation and telemetry systems used at the NASA Langley was found that a simple second-order transfer function Research Center, Plum Tree Test Site. The paper describes three representation of the aircraft is sufficient within the motion telemetry downlinks used to acquire the data, video, and radar augmentation channel. The resulting motions were judged to add tracking information from the model. Also described are two to the realism of the simulation and to compare favorably with telemetry uplinks, one used to fly the model employing a other training simulators. ground-based flight control computer and a second to activate commands for visual tracking and parachute recovery of the model. A93-52679*# National Aeronautics and Space Administration. The paper concludes with a discussion of free-flight drop model Ames Research Center, Moffett Field, CA. instrumentation and telemetry system development currently in PSEUDO AIRCRAFT SYSTEMS - A MULTI-AIRCRAFT progress for future drop model projects at the NASA Langley SIMULATION SYSTEM FOR AIR TRAFFIC CONTROL Research Center. Author (revised) RESEARCH REID A. WESKE and GEORGE L. DANEK (SYRE; NASA, Ames A93-52976 Research Center, Moffett Field, CA) In AIAA Flight Simulation A PROCEDURE FOR THE THERMAL AND STRENGTH Technologies Conference, Monterey, CA, Aug. 9-11, 1993, TESTING OF RADIOTRANSPARENT SHELLS [METODIKA Technical Papers Washington American Institute of Aeronautics TEPLOPROCHNOSTNYKH ISPYTANIJ RADIOPROZRACHNYKH and Astronautics 1993 p. 234-242. refs OBOLOCHEK] (AIAA PAPER 93-3585) L. G. BELOZEROV, V. A. KIREEV, V. G. KREJNIN, and V. V. Pseudo Aircraft Systems (PAS) is a computerized flight dynamics PIVOVAROV TsAGI, Trudy no. 11 1989 p. 81-91. In and piloting system designed to provide a high fidelity multi-aircraft RUSSIAN refs real-time simulation environment to support Air Traffic Control Copyright research. PAS is composed of three major software components The general design characteristics of radiotransparent shells that run on a network of computer workstations. Functionality is and their typical operating environment are briefly examined. A distributed among these components to allow the system to execute procedure is then described for the thermal and mechanical testing fast enough to support real-time operation. PAS workstations are of radiotransparent shells under conditions that closely approximate linked by an Ethernet Local Area Network, and standard UNIX the actual operating conditions. The discussion covers the test socket protocol is used for data transfer. Each component of program, loading and heating methods, methods of measurement PAS is controlled and operated using a custom designed Graphical during testing, and evaluation of the quality of radiotransparent User Interface. Each of these is composed of multiple windows, shell testing. AIAA and many of the windows and sub-windows are used in several of the components. Aircraft models and piloting logic are A93-53625 sophisticated and realistic and provide complex maneuvering and navigational capabilities. PAS will continually be enhanced with WIND OF CHANGE SIMON ELLIOTT Flight International (ISSN 0015-3710) vol. new features and improved capabilities to support ongoing and future Air Traffic Control system development. 144, no. 4377 July 13, 1993 p. 32, 33. Copyright The European Transonic Windtunnel, inaugurated on June 8, A93-52688# 1993, is briefly discussed. The closed-circuit tunnel design is HOW TO CONSIDER SIMULATION FIDELITY AND VALIDITY described and a typical daily tunnel schedule is examined. AIAA FOR AN ENGINEERING SIMULATOR BODING ZHANG (China Flight Test Establishment, Xian) In AIAA Flight Simulation Technologies Conference, Monterey, CA, Aug. A93-53768 9-11, 1993, Technical Papers Washington American Institute FLIGHT SIMULATION - AN OVERVIEW of Aeronautics and Astronautics 1993 p. 298-305. refs CARL LAPISKA (CAE-Link Corp., Binghamton, NY), LARRY ROSS (AIAA PAPER 93-3598) Copyright (McDonnell Douglas Aerospace, Huntington Beach, CA), and DON Simulation fidelity and validity for an engineering simulator have SMART (Lockheed Corp., Fort Worth, TX) Aerospace America always had a strong appeal to the simulation specialists and (ISSN 0740-722X) vol. 31, no. 8 Aug. 1993 p. 14-17, 33. customers. Along with enhancing the engineering simulator's Copyright standing in analysis and test task, simulation test and simulator The evolution of simulation technology over the past 60 years design are emphasizing the importance of simulation fidelity and is reviewed. Simulation based on a combination of real airframe validity. Based on some methods in the process of integration, parts and the duplication of the airframe itself in the computer testing, and acceptance for the SB-100 Flight Simulator, and a matches the real aircraft well enough to replace it for training comparison between simulation testing results and the results from purposes. Two major technology developments of the 70s include flight, the ways of how to consider simulation fidelity and validity the digital computers and the cathode ray tube (CRT) used in for an engineering simulator are discussed. Author (revised) multifunction cockpit displays which changed the approach to simulation. By 1980 simulation was capable of providing highly A93-52754* National Aeronautics and Space Administration. credible evaluations of complete system scenarios. Recent Langley Research Center, Hampton, VA. advances in simulation encompass reconfigurable simulator INSTRUMENTATION AND TELEMETRY SYSTEMS FOR technology based on deployable trainers that can be placed on FREE-FLIGHT DROP MODEL TESTING ships and deployed with troops in the field, networking and new CHARLES R. HYDE and JEFFREY J. MASSIE (NASA, Langley data transfer methods which make virtual battlefield possible and Research Center, Hampton, VA) Oct. 1993 9 p. International permit large exercises including simulated and live vehicles, and Foundation for Telemetering, Annual International Telemetering visual systems. AIAA Conference, 29th, Las Vegas, NV, Oct. 25-28, 1993, Paper refs This paper presents instrumentation and telemetry system A93-53774 techniques used in free-flight research drop model testing at the RED-HOT SIMULATION NASA Langley Research Center. The free-flight drop model test RICHARD DEMEIS Aerospace America (ISSN 0740-722X) vol.

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31, no. 8 Aug. 1993 p. 42, 43. algorithm, such as that used by the Space Shuttle, but instead Copyright requires a more adaptable guidance algorithm. Therefore, for this A unique, large-scale, computer-controlled aircraft fire .training analysis, a predictor-corrector guidance algorithm was developed simulator, which is currently being installed at Dallas-Ft. Worth that would provide successful touchdown conditions while not airport, is described. Simulators offer realistic training in dealing violating the dynamic pressure constraint. A flight-control system with fires, with a safety margin never before available. Training was designed and incorporated, along with the predictor-corrector scenarios in controlled situations consistently reproduce real-world guidance algorithm, into a six-DOF simulation, which showed that conditions using a Specialized Aircraft Fire Trainer. AIAA the HL-20 remained controllable and could reach the landing site and execute a successful landing under all off-nominal conditions A93-54275 simulated. Author (revised) EUROPE'S NEW WINDTUNNEL Aerospace (UK) (ISSN 0305-0831) vol. 20, no. 7 July 1993 p. 16-19. Copyright A93-53738* National Aeronautics and Space Administration. The design and behavior of the new European Transonic Langley Research Center, Hampton, VA. Windtunnel (ETW) are examined. The way that the tunnel design EFFECT OF LIFT-TO-DRAG RATIO IN PILOT RATING OF THE ensures minimal thermal distortions is shown. Test preparation at HL-20 LANDING TASK the ETW is addressed. The shorter runs that the ETW design E. B. JACKSON, ROBERT A. RIVERS (NASA, Langley Research allows are discussed, emphasizing the cost savings. AIAA Center, Hampton, VA), and MELVIN L. BAILEY (Lockheed Engineering and Sciences Co., Hampton, VA) Journal of Spacecraft and Rockets (ISSN 0022-4650) vol. 30, no. 5 10 Sept.-Oct. 1993 p. 543-548. refs Copyright A man-in-the-loop simulation study of the handling qualities of ASTRONAUTICS the HL-20 lifting-body vehicle was made in a fixed-base simulation cockpit at NASA Langley Research Center. The purpose of the Includes astronautics (general); astrodynamics; ground support study was to identify and substantiate opportunities for improving systems and facilities (space); launch vehicles and space vehicles; the original design of the vehicle from a handling qualities and space transportation; spacecraft communications, command and landing performance perspective. Using preliminary wind-tunnel tracking; spacecraft design, testing and performance; spacecraft data, a subsonic aerodynamic model of the HL-20 was developed. instrumentation; and spacecraft propulsion and power. This model was adequate to simulate the last 75-90 s of the approach and landing. A simple flight-control system was designed and implemented. Using this aerodynamic model as a baseline, A93-52885* National Aeronautics and Space Administration. visual approaches and landings were made at several vehicle Langley Research Center, Hampton, VA. lift-to-drag ratios. Pilots rated the handling characteristics of each ANALYSIS OF A TURNING POINT PROBLEM IN FLIGHT configuration using a conventional numerical pilot-rating scale. TRAJECTORY OPTIMIZATION Results from the study showed a high degree of correlation between C. GRACEY (NASA, Langley Research Center, Hampton, VA) Aug. the lift-to-drag ratio and pilot rating. Level 1 pilot ratings were 1989 20 p. IFAC, Workshop on Singular Perturbations and obtained when the L/D ratio was approximately 3.8 or higher. Asymptotic Methods in Systems and Control, Boston, MA, Aug. 17, 18, 1989, Paper refs The optimal control policy for the aeroglide portion of the minimum fuel, orbital plane change problem for maneuvering entry vehicles is reduced to the solution of a turning point problem for A93-53745* National Aeronautics and Space Administration. the bank angle control. For this problem a turning point occurs at Langley Research Center, Hampton, VA. the minimum altitude of the flight, when the flight path angle equals HL-20 OPERATIONS AND SUPPORT REQUIREMENTS FOR zero. The turning point separates the bank angle control into two THE PERSONNEL LAUNCH SYSTEM MISSION outer solutions that are valid away from the turning point. In a W. D. MORRIS, NANCY H. WHITE (NASA, Langley Research neighborhood of the turning point, where the bank angle changes Center, Hampton, VA), and RONALD G. CALDWELL (Rockwell rapidly, an inner solution is developed and matched with the two International Corp., Space Systems Div., Downey, CA) Journal outer solutions. An asymptotic analysis of the turning point problem of Spacecraft and Rockets (ISSN 0022-4650) vol. 30, no. 5 is given, and an analytic example is provided to illustrate the Sept.-Oct. 1993 p. 597-605. refs construction of the bank angle control. Copyright The processing, mission planning, and support requirements A93-53737* National Aeronautics and Space Administration. were defined for the HL-20 lifting-body configuration that can serve Langley Research Center, Hampton, VA. as a Personnel Launch System. These requirements were based SIX-DEGREE-OF-FREEDOM GUIDANCE AND on the assumption of an operating environment that incorporates CONTROL-ENTRY ANALYSIS OF THE HL-20 aircraft and airline support methods and techniques that are RICHARD W. POWELL (NASA, Langley Research Center, applicable to operations. The study covered the complete Hampton, VA) Journal of Spacecraft and Rockets (ISSN turnaround process for the HL-20, including landing through launch, 0022-4650) vol. 30, no. 5 Sept.-Oct. 1993 p. 537-542. refs and mission operations, but did not address the support Copyright requirements of the launch vehicle except for the integrated The ability of the HL-20 lifting body to fly has been evaluated activities. Support is defined in terms of manpower, staffing levels, for an automated entry from atmospheric interface to landing. This facilities, ground support equipment, maintenance/sparing evaluation was required to demonstrate that not only successful requirements, and turnaround processing time. Support results were touchdown conditions would be possible for this low lift-to-drag-ratio drawn from two contracted studies, plus an in-house analysis used vehicle, but also the vehicle would not exceed its design dynamic to define the maintenance manpower. The results of the contracted pressure limit of 400 psf during entry. This dynamic pressure studies were used as the basis for a stochastic simulation of the constraint limit, coupled with limited available pitch-control authority support environment to determine the sufficiency of support and at low supersonic speeds, restricts the available maneuvering the effect of variance on vehicle processing. Results indicate the capability for the HL-20 to acquire the runway. One result of this levels of support defined for the HL-20 through this process to be analysis was that this restrictive maneuvering capability does not sufficient to achieve the desired flight rate of eight flights per allow the use of a model-following atmospheric entry-guidance year.

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11 A93-53420 EVALUATION OF WATER-BORNE ADHESIVE BONDING CHEMISTRY AND MATERIALS PRIMERS FOR USE ON THE ADVANCED AIRCRAFT MATERIAL ALUMINUM-LITHIUM KAREN L. MEYLER and JOSEPH A. BRESCIA (U.S. Army, Includes chemistry and materials (general); composite materials; Armament Research, Development, and Engineering Center, inorganic and physical chemistry; metallic materials; nonmetallic Picatinny Arsenal, NJ) In International SAMPE Technical materials; and propellents and fuels. Conference, 24th and International SAMPE Metals and Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 Covina, CA Society for the Advancement A93-52870* National Aeronautics and Space Administration. of Material and Process Engineering 1992 p. T563-T576. Lewis Research Center, Cleveland, OH. refs STRESS RELAXATION OF LOW PRESSURE Copyright PLASMA-SPRAYED NICRALY ALLOYS A comparative study is conducted for three compositions of W. J. BRINDLEY and J. D. WHITTENBERGER (NASA, Lewis waterborne structural adhesive primers for AI-Li alloy surfaces. Research Center, Cleveland, OH) Materials Science and Two of these contained chromates, and one did not; the results Engineering, Part A - Structural Materials: Properties, obtained for them were compared with those of a widely employed Microstructures and Processing (ISSN 0921-5093) vol. A163 solvent-borne primer. Attention is given to the shear strength of 1993 p. 33-41. refs each primer/adhesive system, in view of wedge-crack extension Copyright tests conducted on samples in condensing humidity conditions The stress relaxation behavior of three NiCrAlY alloys that are and 60 C temperature during two weeks. Only one of the commonly used as bond coats for thermal barrier coatings (TBCs) waterborne primers performed as well as the solvent-borne has been directly measured. The relaxation study was conducted primer. AIAA at temperatures of 800-1000 C and over a wide range of stresses. It was established that all three bond coat alloys relaxed quite rapidly at temperatures of 900 C and above. Since the upper use A93-53434 temperatures for bond coats in gas turbine engines are between THE CHARACTERIZATION AND DEVELOPMENT OF 900 and 1000 C, bond coat relaxation is expected to occur in MATERIALS FOR ADVANCED TEXTILE COMPOSITES service. Therefore, relaxation of the bond coat has the potential J. T. HARTNESS, TIMOTHY L. GREENE, and LEO E. TASKE to affect TBC life. Furthermore, the relaxation differences observed (BASF Structural Materials, Inc., Charlotte, NC) In International between the three alloys offers a possible explanation for the SAMPE Technical Conference, 24th and International SAMPE differences in TBC life observed for these bond coats. While bond Metals and Metals Processing Conference, 3rd, Toronto, Canada, coat relaxation is expected to occur for a TBC in service, the Oct. 20-22, 1992, Proceedings. Vol. 24 Covina, CA Society for mechanism for a relaxation effect on TBC life, if it exists, is yet to the Advancement of Material and Process Engineering 1992 be determined. Author (revised) p. T776-T790. Copyright A93-52961 Work ongoing under a NASA Langley - Advanced Composite VISCOSITY OF AVIATION FUEL COMPONENTS - AROMATIC Technology (ACT) program is discussed. The primary emphasis of HYDROCARBONS (ALKYL BENZENES) [VYAZKOST the work centers around the development and characterization of KOMPONENTOV AVIATSIONNYKH TOPLIV - graphite fiber that has been impregnated with an epoxy powder. AROMATICHESKIE UGLEVODORODY /ALKILBENZOLY/] Four epoxies have been characterized in towpreg form as to their V. I. SKOMOROKHOV and A. F. DREGALIN Aviatsionnaya weaveability and braidability. Initial mechanical properties have Tekhnika (ISSN 0579-2975) no. 1 1993 p. 96-98. In been generated on each resin system. These include unidirectional RUSSIAN refs as well as 8-harness satin cloth. Initial 2D and 3D weaving and Copyright braiding trials will be reported on as well as initial efforts to develop The objective of the study is to present accurate reliable towpreg suitable for advanced tow placement. expressions for calculating the viscosity of aromatic hydrocarbons (alkyl benzenes), which are a major component of aviation fuels. A93-53445 A formula is proposed for calculating the viscosity of aromatic PREPARATION AND CHARACTERIZATION OF CONTINUOUS hydrocarbons in the region close to the solidification line. In the FIBER REINFORCED ZIRCONIUM DIBORIDE MATRIX region close to the saturation line, the use of the Frenkel formula COMPOSITES FOR A LEADING EDGE MATERIAL is recommended. AIAA KEVIN STUFFLE, WAYNE LOUGHER (Advanced Ceramics Research, Inc., Tucson, AZ), and STEPHANIE CHANAT (Buehler A93-53419 Southwest Research Center, Tucson, AZ) In International SAMPE 'NO VOC' WATER-BORNE CORROSION RESISTANT PRIMERS Technical Conference, 24th and International SAMPE Metals and FOR AEROSPACE BONDING APPLICATIONS Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, MICHAEL J. BARKER and THOMAS MOBLEY (BFGoodrich Co., 1992, Proceedings. Vol. 24 Covina, CA Society for the Adhesive Systems Div., Brecksville, OH) In International SAMPE Advancement of Material and Process Engineering 1992 p. Technical Conference, 24th and International SAMPE Metals and T935-T949. refs Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, (Contract N60921-90-C-0033) 1992, Proceedings. Vol. 24 Covina, CA Society for the Copyright Advancement of Material and Process Engineering 1992 p. Zirconium diboride with addition of silicon carbide has been T551-T562. demonstrated in earlier studies to be a material with superior Copyright properties for leading edges for hypersonic atmospheric flight and A comparative investigation has been conducted for the 'No reentry vehicles. However, this material is brittle and flaw sensitive, VOC' waterborne primer, which is to be used for protecting making it unreliable in such applications. Continuous fiber reinforced secondary-bonding operations-involving aerospace structure composites have been prepared with zirconium diboride-silicon surfaces, relative to the current, solvent-based industry standard carbide matrices, in studies concerned with improved reliability. primer. Lap-shear strength and T-peel strength vs temperature Composites were characterized for mechanical properties, and for were evaluated for Al substrates, and No VOC was found to have oxidation and ablation response in representative reentry low primer thickness sensitivity and high strength; durability tests conditions. Room temperature and elevated temperature flexure results are discussed in the framework of meeting and exceeding strengths, recession rate for oxidation at 1200 C, and arc-jet prospective corrosion resistance standards. AIAA ablation response are reported. Author (revised)

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A93-53448 the Advancement of Material and Process Engineering 1992 THE PROPERTIES OF NEWLY DEVELOPED HIGHLY DAMAGE p. T1107-T1122. refs TOLERANT AND EASY HANDLEABLE CARBON (Contract NAS2-12996) FIBER/MODIFIED BISMALEIMIDE PREPREG SYSTEM Copyright S. HAYASHI, M. FUKUMOTO, M. SUGIMORI (Mitsubishi Rayon An evaluation is conducted of a novel ceramic-matrix composite Co., Ltd., Product Development Lab., Nagoya, Japan), F. SAWADA (CMC) material system for use in the aeroconvective-heating (Mitsubishi Rayon Co., Ltd., Toyama Development Lab., Japan), environments encountered by the nose caps and wing leading and H. TADA (Mitsubishi Rayon Co., Ltd., Central Research Lab., edges of such aerospace vehicles as the Space Shuttle, during Ohtake, Japan) In International SAMPE Technical Conference, orbit-insertion and reentry from LEO. These CMCs are composed 24th and International SAMPE Metals and Metals Processing of an SiC matrix that is reinforced with Nicalon, Nextel, or carbon Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. refractory fibers in a 2D architecture. The test program conducted Vol. 24 Covina, CA Society for the Advancement of Material for the 2D CMCs gave attention to their subsurface oxidation. and Process Engineering 1992 p. T972-T982. refs AIAA Copyright A carbon fiber-reinforced bismaleimide-matrix composite A93-53506 thermosetting prepreg system has been developed with a view to ONGOING CHALLENGES FOR TITANIUM ALLOY prospective SST structural applications. While materials of this CLEANLINESS IMPROVEMENT IN AIRCRAFT ENGINE DISK type generally possess good hot/wet processing properties, the MATERIALS matrices thus formed are inherently brittle and exhibit poor damage CLIFFORD E. SHAMBLEN (GE Aircraft Engines, Cincinnati, OH) tolerance. A novel technique is here presented for improving In International SAMPE Technical Conference, 24th and damage tolerance using tough, 'fibriform' thermoplastic resins as International SAMPE Metals and Metals Processing Conference, coatings on thermosel prepreg surfaces. AIAA 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 3 Covina, CA Society for the Advancement of Material and Process A93-53451 Engineering 1992 p. M539-M545. refs WET LAYUP MATERIALS FOR REPAIR OF BISMALEIMIDE Copyright COMPOSITES A review is given of the need and the progress made toward PAUL MEHRKAM and ROLAND COCHRAN (U.S. Navy, Naval Air obtaining improved cleanliness in titanium alloy disk materials for Warfare Center, Warminster, PA) In International SAMPE aircraft engine applications. Since early fatigue crack initiation from Technical Conference, 24th and International SAMPE Metals and melt related inclusions can be a cause for premature component Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, failure, these anomalies must be considered in component design 1992, Proceedings. Vol. 24 Covina, CA Society for the and life predictions. The need to eliminate or, at least, significantly Advancement of Material and Process Engineering 1992 p. reduce the size and number of these melt related inclusions in T1006-T1016. refs titanium alloy disk materials is required to allow maximum utilization The U.S. Naval Air Warfare Center has conducted an evaluation of alloy capabilities. An overview is given of the progress made in of a range of candidate materials for elevated-temperature, wet identifying hearth melt processes which can achieve significantly layup patch composite structure repairs on high service temperature improved cleanliness levels compared to current production melt aircraft composite structures. The repair-patch materials in question processes. The hearth melt implementation status is also described. would be used in field and depot-level repair at about 204 C, as That overview is expanded to consider the remaining challenges in the case of bismaleimide and dicyanate ester. The evaluations for both the improved cleanliness melt processes and NDE gave attention to both vacuum bag processibility and resulting (non-destructive evaluation) required to verify the reduced inclusion mechanical properties. AIAA content for design consideration.

A93-53453* National Aeronautics and Space Administration. A93-53598 Lewis Research Center, Cleveland, OH. ORIGIN OF THE CARBON RICH SLIDING INTERFACE IN OVERVIEW OP NASA'S ADVANCED HIGH TEMPERATURE ALKALI CONTAINING MATRIX-SIC NICALON FIBRE ENGINE MATERIALS TECHNOLOGY PROGRAM COMPOSITES CAROL A. GINTY and HUGH R. GRAY (NASA, Lewis Research E. MOUCHON (ONERA, Chatillon, France) and PH. COLOMBAN Center, Cleveland, OH) In International SAMPE Technical (ONERA, Chatillon; CNRS, Thiais, France) ONERA, TP no. Conference, 24th and International SAMPE Metals and Metals 1993-77 1993 6 p. EUROMAT 93 - European Conference on Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Advanced Materials and Processes, 3rd, Paris, France, June 8-10, Proceedings. Vol. 24 Covina, CA Society for the Advancement 1993 refs of Material and Process Engineering 1992 p. T1029-T1043. (ONERA, TP NO. 1993-77) refs EDX, SEM, microindentation and flexural strength investigations NASA's 'HITEMP' program has been charged with development are here conducted for the effects of the Intel-facial reaction zone of propulsion systems technologies for next-generation civil and between Nicalon SiC fibers and an alkali-containing Nasicon matrix military aircraft, stressing high-temperature/low-density composites. material. A characterization is made of the reaction These encompass polymer-matrix composites for fans, ducts, and mechanisms/mechanical properties relationships. Attention is given compressor cases, and intermetallic and metallic alloy matrix to the origin of the carbon sliding interphase that is associated composites for applications in turbine disks, blades, and vanes, with this type of interface, which arises from the chemical attack and ceramic matrix composites for combustors and turbines. An of the Nicalon oxycarbide second phase by Na and P. AIAA overview is presented of program concerns and achievements to date. AIAA A93-53599 CARS TEMPERATURE MEASUREMENTS IN COMBUSTION A93-53459* National Aeronautics and Space Administration. [THERMOMETRIE DRASC APPLIQUEE AUX MILIEUX EN Ames Research Center, Moffett Field, CA. COMBUSTION] EVALUATION OF 2D CERAMIC MATRIX COMPOSITES IN P. BOUCHARDY, G. COLLIN, P. MAGRE, and M. PEALAT (ONERA, AEROCONVECTIVE ENVIRONMENTS Chatillon, France) ONERA, TP no. 1993-78 1993 15 p. In SALVATORE R. RICCITIELLO, WENDELL L. LOVE (NASA, Ames FRENCH Revue de I'lnstitut Francais du Petrole, vol. 48, no. 3, Research Center, Moffett Field, CA), and ALIZA May-June 1993, p. 247-259 refs BALTER-PETERSON (Eloret Inst., Sunnivale, CA) In International (ONERA, TP NO. 1993-78) Copyright SAMPE Technical Conference, 24th and International SAMPE Coherent anti-Stokes Raman diffusion (CARS) has now become Metals and Metals Processing Conference, 3rd, Toronto, Canada, an operational thermometric technique. After reviewing the principle Oct. 20-22, 1992, Proceedings. Vol. 24 Covina, CA Society for of the measurement, this article describes a CARS set-up. The

1212 11 CHEMISTRY AND MATERIALS different constraints that an experimenter must cope with are Proceedings. Vol. 1 Washington American Institute of Aeronautics described. The advantages and disadvantages of CARS and Astronautics 1993 p. 292-301. refs spectroscopy by scanning and multiplexing are compared. The (ISABE 93-7026) Copyright results of two experiments, one in a high-enthalpy flow and the The influences of flame operating conditions on the blowout other in a turbojet engine simulation combustion chamber, illustrate characteristics of turbulent disc/pilot stabilized jet diffusion flames the performances obtained as well as the difficulties most often have been experimentally considered. Results of blowout velocity encountered. Author (revised) are obtained at different jet and stabilizer disc diameters, combustion air velocities and fuel mixture dilution with nitrogen. A93-53602 The use of pilot flames together with the stabilizer disc to promote CORROSION OF CERAMIC MATRIX COMPOSITES flame stabilization is also considered. It is shown that the fuel jet T. SCANU (ONERA, Chatillon, France) and PH. COLOMBAN blowout velocity increases with the increase in jet diameter, (ONERA, Chatillon; CNRS, Thiais, France) ONERA, TP no. combustion air velocity, disc diameter and with employing small 1993-82 1993 5 p. EUROMAT 93 - European Conference on pilot flames. The blowout velocity is reduced with the addition of Advanced Materials and Processes, 3rd, Paris, France, June 8-10, nitrogen to the fuel. The results reveal that higher percentages of 1993 refs nitrogen addition to the fuel are only possible for flames operating (ONERA, TP NO. 1993-82) with large jet and stabilizer disc diameters and for flames operating Air stable ceramic matrix composites are promising for with pilot flames. thermostructural applications such as aircraft engine parts. Turbine parts are subject to both sulphuric acid and sodium molten salts corrosion due to sulphate traces in engine fuel and to the NaCI A93-54025 air content. This paper reports a study of acidic and sodium A STUDY OF SELF-IGNITION OF METHANE-HYDROGEN corrosion of various aluminosilicate matrices: LAS matrices in the MIXTURE FUEL INJECTED INTO HIGH ENTHALPY amorphous, beta eucryptite and beta spodumene forms; BAS matrix SUPERSONIC AIRSTREAMS in the form of monoclinic and hexagonal celsian, NASICON matrix, H. TAGUCHI, S. TOMIOKA, H. NAGATA, M. KONO (Tokyo Univ., and mullite matrix. Microstructure damages and ion exchange were Japan), and Y. UJIIE (Nihon Univ., Narashino, Japan) In ISABE analyzed by XRD, IR absorption, SEM, and Raman microprobe. - International Symposium on Air Breathing Engines, 11th, Tokyo, Drastic corrosion is observed for beta spodumene-containing Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington composites, with the formation or strong hydrogen bond or with American Institute of Aeronautics and Astronautics 1993 p. the cell expansion due to Li/Na exchange. Medium acidic attack 525-532. refs occurs for glassy LAS, beta eucryptite, BAS, and NASICON matrix (ISABE 93-7049) Copyright composites. On the other hand, beta eucryptite, NASICON, and In order to attain combustion of methane fuel in supersonic monoclinic celsian resist to alkaline melts. Mullite matrix composites airstreams of relatively low temperature, hydrogen fuel was added are never corroded. Author (revised) to the fuel as a ignition promoter. In experiments, rectangular combustor with backward step was adopted, and the A93-54001 methane-hydrogen mixture fuel was injected into supersonic TWO AND THREE-DIMENSIONAL PREDIFFUSER airstreams. The region where the self-ignition occurs was confirmed COMBUSTOR STUDIES WITH AIR-WATER MIXTURE by high speed direct photographs, and self-ignition characteristics S. N. B. MURTHY and P. LAING (Purdue Univ., West Lafayette, were investigated with parameters of equivalence ratio and fraction IN) In ISABE - International Symposium on Air Breathing Engines, of hydrogen in the fuel. The injection form was refined with use 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 of the obtained results to attain self-ignition with low fraction of Washington American Institute of Aeronautics and Astronautics hydrogen. The combustion of methane-hydrogen mixture fuel was 1993 p. 276-291. refs compared with that of hydrogen fuel by using wall static pressure (Contract DTFA-92-G-002) distributions and OH/CH emission images of the flame. It is (ISABE 93-7025) Copyright confirmed that the combustion of methane fuel in the airstreams Water ingestion into an aircraft gas turbine engine, arising is obtained by addition of hydrogen fuel, and it is argued that the during flight under conditions of rainfall, is known to have an self-ignition in refined injection form is obtained under same adverse affect on the operation and handling of the engine due conditions as that of hydrogen fuel, independently of the fraction to modifications in the performance of the individual components, of hydrogen in total injected fuels. The static pressure distribution and of the engine system. In a continuing effort on establishing and the flame shape in methane-hydrogen mixture fuel case were performance modifications and design improvements, an similar to those in hydrogen fuel case. Author (revised) experimental investigation has been performed with model two- and three-dimensional gas turbine prediffuser-combustor sectors utilizing a number of mixture and flow conditions in a tunnel A93-S4057 operating with a two-phase, air-liquid film-droplet mixture. For given HIGH DENSITY STRAINED HYDROCARBON FUELS FOR AIR entry conditions into the prediffuser (which can be related to the BREATHING PROPULSION exit conditions of the core compressor in a bypass engine, and, GABRIEL D. ROY (U.S. Navy, Office of Naval Research, Arlington, therefore, also to ingestion conditions at the engine face) the two VA) In ISABE - International Symposium on Air Breathing Engines, main issues are (i) the amount of water entering the primary zone 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 of the combustor, and (ii) the local reduction in temperature, Washington American Institute of Aeronautics and Astronautics flame-water interactions, and the vitiation caused by the vaporizing 1993 p. 831-837. refs of water. Flow visualization, and estimates of water flow and droplet (ISABE 93-7081) Copyright size in the primary zone have been undertaken under cold flow A new class of high density hydrocarbon fuels with strained conditions. Combustion tests have been carried out to establish molecules are being considered for utilization in the propulsion the effects on performance, recoverability of performance, and systems for ramjets and cruise missiles. These fuels have the flameout under various flow conditions. potential of increasing substantially their range. However, there are several scientific issues to be resolved before these fuels can A93-54002 be utilized. Such issues are addressed in a recently initiated BLOWOUT OF TURBULENT DISC/PILOT STABILIZED JET research program by the Office of Naval Research. Synthesis routes DIFFUSION FLAMES of these fuels have been established, and preliminary property Y. H. EL-BANHAWY, A. A. EL-EHWANY (Ain Shams Univ., Cairo, characterization, and droplet combustion studies have been done. Egypt), S. E. KHALIL, and A. S. ZAKHARY (Petroleum Research Fundamental studies are undertaken to understand the strain Inst., Cairo, Egypt) In ISABE - International Symposium on Air energy release mechanisms, and soot generation and transport in Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, premixed and diffusion flames, and its control. Author (revised)

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A93-54241 Technologies Conference, Monterey, CA, Aug. 9-11, 1993, REINFORCEMENT OF THE F-111 WING PIVOT FITTING WITH Technical Papers Washington American Institute of Aeronautics A BORON/EPOXY DOUBLER SYSTEM - MATERIALS and Astronautics 1993 p. 68-73. ENGINEERING ASPECTS (AIAA PAPER 93-3558) Copyright A. A. BAKER, R. J. CHESTER, M. J. DAVIS, J. D. ROBERTS, The Flight Systems and Simulation Research Laboratory and J. A. RETCHFORD (Defence Science and Technology (Simlab) at the NASA Ames Research Center, utilizes an extensive Organisation, Aeronautical Research Lab., Fishermens Bend, network of video image generation, delivery, processing, and display Australia) Composites (ISSN 0010-4361) vol. 24, no. 6 Sept. systems coupled with a large amplitude Vertical Motion Simulator 1993 p. 511-521. refs (VMS) to provide a high fidelity visual environment for flight Copyright simulation research. This paper will explore the capabilities of the Local regions in the D6ac steel F-111 wing pivot fitting surfer current Simlab video distribution system architecture with a view plastic deformation during the cold proof test employed to screen toward technical solutions implemented to resolve a variety of out flaws in the steel components of the airframe. This deformation video interface, switching, and distribution issues common to many produces residual stresses which can lead to a fatigue cracking simulation facilities. Technical discussions include a modular problem in service. This paper describes materials engineering approach to a video switching and distribution system capable of aspects of a program undertaken at the DSTO Aeronautical supporting both coax and fiber optic video signal transmission, Research Laboratory to develop an advanced fiber composite video scan conversion and processing techniques for lab doubter system aimed at reducing the strain in these regions during observation and recording, adaptation of image generation and the cold proof test, and also to reduce cyclic strain during display system video interfaces to industry standards, an all raster subsequent operation of the aircraft. The doubler system chosen solution for 'glass cockpit' configurations encompassing Head up, is boron/epoxy (over 120 plies thick) bonded with a structural film Head-down, and Out-the-Window display systems. adhesive. Aspects described include selection and characterization of composite and adhesive bonding system, doubler fabrication A93-52667# and application technology, and evaluation of a representative TERRAIN MODELING FOR REAL-TIME PHOTO-TEXTURE doubler specimen. Use of the doubler system was demonstrated BASED VISUAL SIMULATION to reduce the strain in the critical regions by over 30 percent, VENKAT DEVARAJAN and DONALD E. MCARTHUR (Texas Univ., confirming design predictions. Author (revised) Arlington) In AIAA Flight Simulation Technologies Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington A93-54250 American Institute of Aeronautics and Astronautics 1993 p. DEVELOPMENT OF MIL-H-53119, -54 C TO 175 C 133-139 refs HIGH-TEMPERATURE NONFLAMMABLE HYDRAULIC FLUID (AIAA PAPER 93-3607) Copyright FOR AIR FORCE SYSTEMS This paper describes a method for terrain modeling for a LOIS GSCHWENDER, CARL E. SNYDER, JR., and SHASHI K. real-time phototexture-based visual simulation, in which the terrain SHARMA (USAF, Wright Lab., Wright-Patterson AFB, OH) is modeled with a set of polygons and organized as a graph with Lubrication Engineering (ISSN 0024-7154) vol. 49, no. 8 Aug. each node corresponding to a polygon. The methods, algorithms, 1993 p. 621-630. STLE, Annual Meeting, 46th, Montreal, Canada, and data structures required to represent terrain elevation for the Apr. 29-May 2, 1991 refs image generating system are discussed. Particular attention is given Copyright to the problem of selection of the required subset of the polygon A nonflammable hydraulic fluid for -54 to 135 C operation has data base. AIAA been previously developed based on a chlorotrifluoroethylene oligomer (CTFE) base fluid formulated with performance improving A93-52677# additives, a proprietary antiwear additive, now herein described, REPRESENTATION OF VEHICLE LOCATION IN NETWORKED and a rust inhibitor, a specially prepared barium dinonylnaphthalene SIMULATIONS sulfonate (BSN). New requirements for advanced high performance KUO-CHI LIN, BRIAN GOLDIEZ, and HUAT NG (Central Florida aircraft led to a new fluid capable of operating from -54 to 175 C. Univ., Orlando, FL) In AIAA Flight Simulation Technologies The earlier nonflammable hydraulic fluid was limited in thermal Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers stability to 135 C by the rust inhibitor. This paper describes research Washington American Institute of Aeronautics and Astronautics and development leading to a successful formulation consisting 1993 p. 222-226. refs of the same CTFE base fluid, the same antiwear additive, and a (AIAA PAPER 93-3582) Copyright new zinc-based sulfonate antirust additive. Validation using an In a networked simulation environment, it is vital to assure actual state-of-the-art hydraulic pump was successfully that all vehicles maintain a consistent representation of the accomplished at 135 C, and the data are presented. geometry between themselves and between vehicles and the Author (revised) terrain over which they operate. Hence, all vehicles should be able to convert their position and orientation to common coordinates. Three coordinate systems, geocentric, geodetic, and topocentric, and the transformation from one system to another 12 are analyzed.

ENGINEERING A93-52695# TEXTURE AS A VISUAL CUEING ELEMENT IN COMPUTER Includes engineering (general); communications; electronics and IMAGE GENERATION. I - REPRESENTATION OF THE SEA electrical engineering; fluid mechanics and heat transfer; SURFACE instrumentation and photography; lasers and masers; mechanical GREG BOOKOUT (Digital Visions, Mt. Shasta, CA) and JOHN engineering; quality assurance and reliability; and structural SINACORI (Montallegro Applied Sciences, Inc., Pebble Beach, mechanics. CA) In AIAA Flight Simulation Technologies Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington American Institute of Aeronautics and Astronautics 1993 p. A93-52659"# National Aeronautics and Space Administration. 341-347. refs Ames Research Center, Moffett Field, CA. (AIAA PAPER 93-3560) Copyright A HIGH FIDELITY VIDEO DELIVERY SYSTEM FOR REAL-TIME The objective of this paper is to advance hypotheses about FLIGHT SIMULATION RESEARCH texture as a visual cueing medium in simulation and to provide DANIEL A. WILKINS and CARL C. ROACH (SYRE; NASA, Ames guidelines for data base modelers in the use of computer image Research Center, Moffett Field, CA) In AIAA Flight Simulation generator resources to provide effective visual cues for simulation

1214 12 ENGINEERING purposes. The emphasis is on a texture decoration of the earth's of turbine rotor blades with a low-pressure cooling system. The surface data base in order to support low-level flight, i.e., flight at results of the study have been used in the design of a turbine elevations above the surface of 500 feet or less. The appearance cooling system for a turbofan engine. AIAA of the surface of the sea is the focus of this paper. The physics of the sea's appearance are discussed and guidelines are given A93-52968 for its representation for sea states from 0 (calm) to 5 (fresh CALCULATION OF SANDWICH PLATES WITH POLYMER breeze of 17-21 knots and sixfoot waves, peak-to-trough). The COMPOSITE SKINS UNDER CONDITIONS OF HIGH HUMIDITY viewpoints considered vary from 500 feet above the mean sea [RASCHET TREKHSLOJNYKH PLASTIN S OBSHIVKAMI IZ surface to an altitude just above the wave crests. POLIMERNYKH KOMPOZITSIONNYKH MATERIALOV, NAKHODYASHCHIKHSYA V USLOVIYAKH POVYSHENNOJ A93-52751* National Aeronautics and Space Administration. VLAZHNOSTI] Lewis Research Center, Cleveland, OH. I. B. MISHULIN TsAGI, Trudy no. 11 1989 p. 18-28. In PROGRESS TOWARDS UNDERSTANDING AND PREDICTING RUSSIAN refs HEAT TRANSFER IN THE TURBINE GAS PATH Copyright An engineering method is presented for estimating the ROBERT J. SIMONEAU and FREDERICK F. SIMON (NASA, Lewis temperature gradients, moisture concentration gradients, and Research Center, Cleveland, OH) International Journal of Heat and Fluid Flow (ISSN 0142-727X) vol. 14, no. 2 June 1993 changes in stresses and deflections induced by these gradients p. 106-128. rets in sandwich plates with heat-insulation coatings under conditions Copyright of high ambient temperatures and humidity. In particular, attention A new era is dawning in the ability to predict convection heat is given to ambient conditions that vary slowly in time, simulating transfer in the turbine gas path. We feel that the technical typical airport storage conditions. Results of calculations are community now has the capability to mount a major assault on presented for sandwich panels with load-bearing layers of a carbon this problem, which has eluded significant progress for a long composite and an organic fiber composite. AIAA time. In this paper we hope to make a case for this bold statement by reviewing the state of the art in three major and related areas, A93-52973 which we believe are indispensable to the understanding and DESIGN AND FABRICATION OF PANELS WITH CUTOUTS accurate prediction of turbine gas path heat transfer: [OSOBENNOSTI PROEKTIROVANIYA I IZGOTOVLENIYA configuration-specific experiments, fundamental physics and model PANELEJ S VYREZAMI] development, and code development. We begin our review with V. F. KUT'INOV, A. A. DUDCHENKO, V. A. KOZLOV, and V. I. the configuration-specific experiments, whose data have provided REZNICHENKO TsAGI, Trudy no. 11 1989 p. 58-62. In the big picture and guided both the fundamental modeling research RUSSIAN refs and the code development. Following that, we examine key Copyright modeling efforts and comment on what will be needed to A method is presented for determining the shape of a cutout incorporate them into the codes. In this region we concentrate on and the surface of a cutout reinforcement element that would bypass transition, 3D endwalls, and film cooling. We then review guarantee the retention of the undisturbed state of the panel and progress and directions in the development of computer codes to compatibility of displacements in the panels and those of the predict turbine gas path heat transfer. Finally, we cite examples reinforcement element. The method makes it possible to reduce and make observations on the more recent efforts to do all this the reinforcement mass and to optimize the shape of the cutout work in a simultaneous, interactive, and more synergistic manner. and that of the reinforcement element. The validity of the approach We conclude with an assessment of progress, suggestions for is supported by tensile test results for metal/composite sandwich how to use the current state of the art, and recommendations for panels with a reinforced round hole. AIAA the future. Author (revised) A93-52975 AN EXPERIMENTAL STUDY OF REINFORCED PANELS OF A93-52939 COMPOSITE MATERIALS [EHKSPERIMENTAL'NOE A NONLINEAR FINITE ELEMENT OF AN ARBITRARY BEAM ISSLEDOVANIE PODKREPLENNYKH PANELEJ IZ [NELINEJNYJ KONECHNYJ EHLEMENT PROIZVOL'NOGO KOMPOZITSIONNYKH MATERIALOV] BRUSA] V. M. ANDRIENKO, A. A. IONOV, and L. V. KOPYLOVA TsAGI, YU. V. SKOVRTSOV and KH. S. KHAZANOV Aviatsionnaya Trudy no. 11 1989 p. 73-80. In RUSSIAN refs Tekhnika (ISSN 0579-2975) no. 1 1993 p. 9-12. In Copyright RUSSIAN refs The strength and stability characteristics of reinforced panels Copyright of composite materials are examined with particular reference to A finite element of a curvilinear beam is proposed which can the structural applications of high-strength and high-modulus be used for the modeling of aircraft frames, spars, and stringers. composites in flight vehicles. Experimental and analytical data are The element is developed by using the hypothesis of thin sections. presented on the stability and strength of carbon composite panels The finite element model is based on an isoparametric formulation. of different types. The panels considered include panels reinforced Geometrical nonlinearity is considered in the context of the mean by closed-profile elements, panels with open-type reinforcement deflection theory. AIAA elements, and sandwich panels with a corrugated core. The weight efficiency of composite panels is estimated. AIAA A93-52950 EFFECT OF ROTATION ON HEAT TRANSFER AND A93-52979 HYDRAULIC RESISTANCE IN THE RADIAL COOLING A FINITE ELEMENT FOR MODELING SKINS OF COMPOSITE CHANNELS OF TURBINE ROTOR BLADES [VLIYANIE MATERIALS [KONECHNYJ EHLEMENT DLYA VRASHCHENIYA NA TEPLOOBMEN I GIDRAVLICHESKOE MODELIROVANIYA OBSHIVOK IZ KOMPOZITSIONNYKH SOPROTIVLENIE V RADIAL'NYKH OKHLAZHDAYUSHCHIKH MATERIALOV] KANALAKH RABOCHIKH LOPATOK TURBIN] I. V. KAZIMIROV TsAGI, Trudy no. 11 1989 p. 114-120. K. M. ISKAKOV, O. V. TRUSHIN, M. I. TSAPLIN, and YU. S. In RUSSIAN refs SHATALOV Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 1 Copyright 1993 p. 55-58. In RUSSIAN refs A finite element is proposed for implementing a model of a Copyright reinforced orthotropic shell under plane stress loading. The element Results of a modeling study indicate that rotation significantly is obtained using a linear formulation, with bilinear approximation (up to 60 percent) changes local heat transfer and increases, by of the unknown displacements within the element. The element a factor of 5-6, hydraulic resistance in the smooth radial channels has the shape of an arbitrary convex rectangle and consists of

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three layers: a skin and two stringer layers. The application of the A93-53429 finite element is illustrated by examples which demonstrate the STRUCTURAL APPLICATIONS OF AVIMID K3B LDF sufficient accuracy of the element for practical purposes. AIAA THERMOPLASTIC COMPOSITES ANDREW P. PERRELLA (Du Pont Composites, Wilmington, DE) In International SAMPE Technical Conference, 24th and A93-53224 International SAMPE Metals and Metals Processing Conference, FLUTTER ANALYSIS OF STIFFENED LAMINATED 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 COMPOSITE PLATES AND SHELLS IN SUPERSONIC FLOW Covina, CA Society for the Advancement of Material and Process CHUNG-LI LIAO and YEE-WIN SUN (National Taiwan Inst. of Engineering 1992 p. T711-T723. refs Technology, Taipei) AIAA Journal (ISSN 0001-1452) vol. 31, Copyright no. 10 Oct. 1993 p. 1897-1905. refs Composite applications on advanced aircraft require lightweight, Copyright high performance, tough material systems which are capable of This paper investigates the flutter instability of stiffened and operating at high service temperatures. These composite systems nonstiffened laminated composite plates and shells subjected to must also be producible and cost effective. Avimid K3B composite aerodynamic forces in the supersonic flow. The equation of motion materials and related process and part manufacturing technologies of the present problem is formulated using Hamilton's principle. offers a unique solutions to these requirements. The objective of Then, using the finite element method along with three-dimensional this paper is to describe selected Avimid K3B processing degenerated shell elements and three-dimensional degenerated approaches such as Long Discontinuous Fiber thermoforming and curved beam elements, the equation of motion is discretized. The fusion bonding. A review of the Avimid K3B F-16 Strake Door characteristic equation to study the flutter instability of the present Joint Development Program is presented. This program successfully problem is obtained from the previous finite element equation of developed, built and structurally validated a flight demonstration motion. Finally, natural frequency, critical dynamic pressure, and component using these materials and manufacturing methods. corresponding flutter mode shape are found by solving the Author (revised) characteristic equation. The effects of various parameters, such as skew angle, lamination scheme, subtended angle, and stiffening scheme on the flutter instability of stiffened and nonstiffened plates A93-53452 and shells in the supersonic flow are demonstrated through the REPAIR MATERIALS AND PROCESSES FOR THE MD-11 numerical examples. COMPOSITE TAILCONE TETSUYA YAMAMOTO (Mitsubishi Heavy Industries, Ltd., Nagoya, Japan) and GERARD R. BONNAR (McDonnell Douglas Corp., Long A93-53329 Beach, CA) In International SAMPE Technical Conference, 24th MATHEMATICAL MODELING OF THE THREE-DIMENSIONAL and International SAMPE Metals and Metals Processing TEMPERATURE FIELDS OF TURBINE BLADES Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. [MATEMATICHESKOE MODELIROVANIE TREKHMERNYKH Vol. 24 Covina, CA Society for the Advancement of Material TEMPERATURNYKH POLEJ TURBINNYKH LOPATOK] and Process Engineering 1992 p. T1017-T1028. V. M. EPIFANOV and I. V. STANKEVICH (Moskovskij Copyright Gosudarstvennyj Tekhnicheskij Univ., Moscow, Russia) This paper describes field and depot level repair methods for Rossijskaya Akademiya Nauk, Doklady (ISSN 0869-5652) vol. the MD-11 Composite Tailcone. The repair materials, processing 330, no. 3 May 1993 p. 318-320. In RUSSIAN refs methods, and mechanical properties of the test specimens and Copyright subcomponents are discussed. According to recent tests, the dry A method for the numerical modeling of three-dimensional carbon cloth and the liquid resin matrix that can be cured under nonlinear unsteady heat conduction problems is described which 93 C have better processing and mechanical properties than the is based on the finite element method. The method and the 121 C curing prepregs and film adhesives. The moisture in the algorithms proposed here have been implemented in a set of parent CFRP is the main cause of creating voids in the adhesive application software, GERMES-02-T. The software has been used layer during the 121 C/vacuum pressure cure cycle. The lower in a numerical investigation of the thermal state of a cooled turbine processing temperature (wet layup) showed better results than blade made of ZhS26VSNK alloy and a noncooled carbon/ceramic higher processing temperature (prepreg/adhesive layup) for composite blade. AIAA composite repair. Author (revised)

A93-53395* National Aeronautics and Space Administration. A93-53468* National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. Lewis Research Center, Cleveland, OH. DESIGN FOR CYCLIC LOADING ENDURANCE OF THE CHEMISTRY OF SAUDI ARABIAN SAND - A DEPOSITION COMPOSITES PROBLEM ON HELICOPTER TURBINE AIRFOILS MICHAEL C. SHIAO (Sverdrup Technology, Inc., Brook Park, OH) JAMES L. SMIALEK, FRANCES A. ARCHER, and RALPH G. and PAPPU L. N. MURTHY (NASA, Lewis Research Center, GARLICK (NASA, Lewis Research Center, Cleveland, OH) In Cleveland, OH) In International SAMPE Technical Conference, International SAMPE Technical Conference, 24th and International 24th and International SAMPE Metals and Metals Processing SAMPE Metals and Metals Processing Conference, 3rd, Toronto, Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Canada, Oct. 20-22, 1992, Proceedings. Vol. 3 Covina, CA Vol. 24 Covina, CA Society for the Advancement of Material Society for the Advancement of Material and Process Engineering and Process Engineering 1992 p. T241-T255. refs 1992 p. M63-M77. refs Copyright Copyright The present paper describes the application of the computer Operations in the Persian Gulf have exposed military helicopter code IPACS (Integrated Probabilistic Assessment of Composite turbines to excessive amounts of ingested sand. Fine particles, Structures) to air craft wing type structures. The code performs a less than 10 microns, are able to bypass the particle separators complete probabilistic structural analysis for composites taking into and enter the cooling and combustion systems. The initial sand account the uncertainties in geometry, boundary conditions, chemistry varies by location, but is made up of a calcium aluminum material properties, laminate lay-ups and loads. Results of the silicate glass, SiO2 low quartz, (Ca,Mg)CO3 dolomite, CaCO3 analysis are presented in terms of cumulative distribution functions calcite, and occasionally NaCI rocksalt. The sand reacts in the (CDF) and probability density function (PDF) of life of a wing type hot combustion gases and deposits onto the turbine vanes as composite structure under different hygrothermal environments CaSO4, glass, and various crystalline silicates. Deposits up to 5 subjected to random pressure. The sensitivity of fatigue life to a mm thick have been collected. Although cooling hole plugging is number of critical structural/material variables is also computed a considerable problem, excessive corrosion is not commonly from the analysis. observed due to the high melting point of CaSO4.

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A93-53493 SAMPE Metals and Metals Processing Conference, 3rd, Toronto, TOTAL QUALITY MANAGEMENT OF FORGED PRODUCTS Canada, Oct. 20-22, 1992, Proceedings. Vol. 3 Covina, CA THROUGH FINITE ELEMENT SIMULATION Society for the Advancement of Material and Process Engineering U. CHANDRA, S. RACHAKONDA, and S. CHANDRASEKHARAN 1992 p. M504-M516. Research supported by Nickel Development (Concurrent Technologies Corp., Johnstown, PA) In International Inst. and NSERC refs SAMPE Technical Conference, 24th and International SAMPE Copyright Metals and Metals Processing Conference, 3rd, Toronto, Canada, The paper discusses the metallurgical reasons for introducing Oct. 20-22, 1992, Proceedings. Vol. 3 Covina, CA Society for the electron-beam-melting technique to achieve clean melting and the Advancement of Material and Process Engineering 1992 to remove defects from superalloys and titanium alloys used in p. M379-M393. Research supported by U.S. Navy refs spacecraft engine components. Attention is given to the types of Copyright defects encountered in superalloy structures, the types of inclusions The paper reviews the entire thermo-mechanical history and their origin and treatment, the solidification defects, and the experienced by a complex shaped, high strength forged part during particular techniques used to avoid defects. It is concluded that all stages of its manufacturing process, i.e. forging, heat treatment, the electron-beam technology is at a stage where the method is and machining. It examines the current practice of selecting the viable, from both an economical and technical viewpoints. In spite process parameters using finite element simulation of forging and of the fact that the electron-beam melting brings its own problems quenching operations on an individual basis. Some recent work in regard to reliable operation, it holds the promise of producing related to the simulation of aging and machining operations is alloys with a level of property reliability far beyond that available summarized. The capabilities of several well-known finite element at present. AIAA codes for these individual simulations are compared. Then, an integrated simulation approach is presented which will permit the optimization of process parameters for all operations, as opposed A93-53514 to a single operation. This approach will ensure a total quality THE APPLICATION OF DIFFUSION BONDING IN THE management of forged products by avoiding costly problems which, MANUFACTURE OF AEROENGINE COMPONENTS under the current practice, are detected only at the end of the J. A. FITZPATRICK (Rolls-Royce, PLC, Aerospace Group, manufacturing cycle, i.e. after final machining. Barnoldswick, United Kingdom) In International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals A93-53498 Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, CASE STUDIES - APPLICATIONS OF LASER SYSTEMS FOR Proceedings. Vol. 3 Covina, CA Society for the Advancement CUTTING AND WELDING AEROSPACE PARTS of Material and Process Engineering 1992 p. M622-M628. TERRY L. VANDERWERT (Lumonics Corp., Laserdyne Div., Eden refs Prairie, MN) In International SAMPE Technical Conference, Copyright Rolls-Royce has developed and optimized diffusion bonding 24th and International SAMPE Metals and Metals Processing processes for the manufacture of advanced titanium alloy Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. aeroengine structures and components. Both categories of the Vol. 3 Covina, CA Society for the Advancement of Material and Process Engineering 1992 p. M439-M449. joining technique - 'liquid-phase' and 'solid-state' - are being applied Copyright in the production of both static fabrications and complex rotating parts. In order to utilize diffusion bonding processes in a production This paper presents three case studies of current industrial applications of laser systems, showing that multiaxis laser environment, the process parameters which contribute to consistent machining systems are satisfying demands for reduced formation of joints of the required strength have been critically examined. Process variables include temperature, pressure, time, part-production costs, higher quality, greater flexibility, and faster surface roughness and, in the case of liquid-phase diffusion turnaround on prototype and production aerospace parts. For example, laser cutting has replaced milling for trimming a bonding, interlayer composition, density and thickness. Mechanical testing (tensile, impact and fatigue) complemented by deep-drawn gas turbine part and increased throughput from 18 metallography has predominantly been used to identify the pieces per day to 18 pieces in 30 minutes. The case studies described include that of a job shop supplying aircraft engine permitted variations in the processes for the realistic and economical production manufacture of high quality lightweight parts, and those of two aircraft manufacturers. AIAA aeroengine fabrications. The development of a high integrity bond via optimized diffusion bonding processes has been fundamental A93-53499 to the development of Rolls-Royce's unique wide chord fan design FRICTION SURFACING AND LINEAR FRICTION WELDING concept. E. D. NICHOLAS (TWI, Forge and Resistance Processes Dept., Cambridge, United Kingdom) In International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals A93-53515 Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, DURABILITY PROPERTIES FOR ADHESIVELY BONDED Proceedings. Vol. 3 Covina, CA Society for the Advancement STRUCTURAL AEROSPACE APPLICATIONS of Material and Process Engineering 1992 p. M450-M463. D. K. SHAFFER, GUY D. DAVIS, DAVID K. MCNAMARA, TUSHAR refs K. SHAH, and ATUL DESAI (Martin Marietta Labs., Baltimore, Copyright MD) In International SAMPE Technical Conference, 24th and The paper describes the development of the friction-surfacing International SAMPE Metals and Metals Processing Conference, and linear-friction welding technologies, with particular attention 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 3 given to the equipment evolution and the application of the Covina, CA Society for the Advancement of Material and Process processes and advanced materials (such as intermetallics, Engineering 1992 p. M629-M644. refs metal-matrix composites (MMCs), ODS alloys, and powder Copyright metallurgy alloys) for the aerospace industry. The use of friction Causes of bond failures in adhesively joined aerospace surfacing to modify the surface material with MMCs, to repair components are investigated using the results of stepwise defects by plugging, and manufacture/reprocess materials is multidisciplinary failure analysis of a wide range of conventional described. AIAA (metal/adhesive) and unconventional (nonmetal/adhesive) interfacial disbonds that are encountered in real-world production A93-53503 and quality assurance environments. It is shown that the primary CLEAN MELTING AND THE REMOVAL OF DEFECTS FROM causes of adhesive bond degradation include poor surface AERO-ENGINE MATERIALS preparation, contamination of adherend surfaces, moisture or A. MITCHELL (British Columbia Univ., Vancouver, Canada) In aggressive ion ingress into the bonded joint, and improper curing International SAMPE Technical Conference, 24th and International or composition of the adhesive formulation. AIAA

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A93-53585*# National Aeronautics and Space Administration. technique and the multistage synthesis technique of Dzygadlo and Lewis Research Center, Cleveland, OH. Blaszczyk (1981). The vibration spectrum of an airplane of such MEASUREMENTS AND COMPUTATIONAL ANALYSIS OF configuration is calculated assuming uniform distribution of the HEAT TRANSFER AND FLOW IN A SIMULATED TURBINE mass and the elastic parameters of assemblies, if the rotation BLADE INTERNAL COOLING PASSAGE angle of the wing varies between 0 and 70 deg. Author (revised) LOUIS M. RUSSELL (NASA, Lewis Research Center, Cleveland, OH), DOUGLAS R. THURMAN (U.S. Army, Vehicle Propulsion A93-53810 Directorate; NASA, Lewis Research Center, Cleveland, OH), THE REDUCTION OF SKIN FRICTION BY RIBLETS UNDER PATRICIA S. SIMONYI (Sverdrup Technology, Inc., Lewis Research THE INFLUENCE OF AN ADVERSE PRESSURE GRADIENT Center Group, Brook Park, OH), STEVEN A. HIPPENSTEELE, and F. T. M. NIEUWSTADT, W. WOLTHERS, H. LEIJDENS (Delft PHILIP E. POINSATTE (NASA, Lewis Research Center, Cleveland, Technical Univ., Netherlands), K. KRISHNA PRASAD, and A. OH) Jun. 1993 28 p. AIAA, SAE, ASME, and ASEE, Joint SCHWARZ-VAN MANEN (Eindhoven Technical Univ., Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, Netherlands) Experiments in Fluids (ISSN 0723-4864) vol. 15, 1993 Previously announced in STAR as N93-31647 refs no. 1 1993 p. 17-26. refs (AIAA PAPER 93-1797) Copyright Copyright Visual and quantitative information was obtained on heat We address the effectiveness of riblets on skin friction reduction transfer and flow in a branched-duct test section that had several under the influence of an adverse pressure gradient. The significant features of an internal cooling passage of a turbine measurements were taken in a wind tunnel. Skin friction was blade. The objective of this study was to generate a set of observed with a drag balance which has a reproducibility of better experimental data that could be used to validate computer codes than 1 percent. The accuracy of the balance is estimated to be for internal cooling systems. Surface heat transfer coefficients and less than 1 percent for the case of a zero-pressure gradient and entrance flow conditions were measured at entrance Reynolds at most 3 percent for a pressure gradient. The data on skin friction numbers of 45,000, 335,000, and 726,000. The heat transfer data reduction at a zero pressure gradient were consistent with previous were obtained using an Inconel heater sheet attached to the surface results and amount to 5 percent at a dimensionless riblet width of and coated with liquid crystals. Visual and quantitative flow field s(-t-) = 13. We find that at all adverse pressure gradients the results using particle image velocimetry were also obtained for a skin friction reduction by riblets persists. At moderate pressure plane at mid channel height for a Reynolds number of 45,000. gradients the reduction increases somewhat to 7 percent. The The flow was seeded with polystyrene particles and illuminated velocity profile which is also measured exhibits the characteristic by a laser light sheet. Computational results were determined for shape for a boundary layer with an adverse pressure gradient the same configurations and at matching Reynolds numbers; these and agrees well with theory. From the velocity profiles measured surface heat transfer coefficients and flow velocities were computed at two stations we estimated with the help of a momentum balance with a commercially available code. The experimental and the skin friction and skin friction reduction. The results differ from computational results were compared. Although some general the drag-balance data. Due to the poor accuracy of the momentum trends did agree, there were inconsistencies in the temperature balance method which we estimate in our case, we conclude that patterns as well as in the numerical results. These inconsistencies the results obtained with this method are less reliable than those strongly suggest the need for further computational studies on obtained with the drag balance. This throws some doubt on previous complicated geometries such as the one studied. results on drag reduction under the influence of a pressure gradient which were based on the momentum balance method. A93-53596 Author (revised) HIGH TEMPERATURE HEAT EXCHANGERS FOR GAS TURBINES AND FUTURE HYPERSONIC AIR BREATHING A93-53812 PROPULSION PRODUCTION OF OSCILLATORY FLOW IN WIND TUNNELS PATRICK AVRAN and PIERRE BERNARD (ONERA, Chatillon, K. AL-ASMI and I. P. CASTRO (Surrey Univ., Guildford, United France) ONERA, TP no. 1993-75 1993 18 p. International Kingdom) Experiments in Fluids (ISSN 0723-4864) vol. 15, no. Conference on Aerospace Heat Exchanger Technology, 1st, Palo 1 1993 p. 33-41. refs Alto, CA, Feb. 15-17, 1993 refs Copyright (ONERA, TP NO. 1993-75) A method for producing oscillatory flow in open-circuit wind After surveying the results of ONERA's investigations to date tunnels driven by centrifugal fans is described. Performance of metallic and ceramic heat exchangers applicable to automotive characteristics of a new device installed on two such tunnels of and aircraft powerplants, which are primarily of finned-tube greatly differing size are presented. It is shown that sinusoidal counterflow configuration, attention is given to the influence of variations of the working section flow, having peak-to-peak heat-exchanger effectiveness on fuel consumption and exchanger amplitudes up to at least 30 percent of the mean flow speed and dimensions and weight. Emphasis is placed on the results of studies frequencies up to, typically, that corresponding to the acoustic of cryogenic heat exchangers used by airbreathing hypersonic quarter-wave-length frequency determined by the tunnel size, can propulsion systems. The numerical codes developed by ONERA be obtained with negligible harmonic distortion or acoustic noise for the modeling of heat exchanger thermodynamics are difficulties. A brief review of the various methods that have been evaluated. AIAA used previously is included, and the advantages and disadvantages of these different techniques are highlighted. The present technique A93-53776 seems to represent a significant improvement over many of them. FINITE ELEMENT ANALYSIS OF NATURAL VIBRATIONS OF Author (revised) AN AEROPLANE WITH ASYMMETRIC VARIABLE WING GEOMETRY A93-53815 J. BLASZCZYK (Military Technical Academy, Warsaw, Poland) REYNOLDS NUMBER DEPENDENCE OF THE DRAG Journal of Technical Physics (ISSN 0324-8313) vol. 34, no. 1 COEFFICIENT FOR LAMINAR FLOW THROUGH FINE-SCALE 1993 p. 79-100. refs PHOTOETCHED SCREENS Copyright T. J. O'HERN and J. R. TORCZYNSKI (Sandia National Labs., The paper considers a dynamic model of an airplane with an Albuquerque, NM) Experiments in Fluids (ISSN 0723-4864) vol. airfoil which can rotate in its plane about a cylindrical joint located 15, no. 1 1993 p. 75-81. refs on the fuselage. In the general case, the airplane under (Contract DE-AC04-76DP-00789) consideration is an asymmetric structure, which means the Copyright existence of a coupling between longitudinal and lateral motions. The laminar steady flow downstream of fine-mesh screens is Equations of dynamic equilibrium of deformable assemblies are studied. Instead of woven-wire screens, high-uniformity screens established by means of the Zienkiewicz (1971) finite element are fabricated by photoetching holes into 50.8-micron-thick Inconel

1218 12 ENGINEERING sheets. The resulting screens have minimum wire widths of 50.8 567-578. Research supported by CEC refs microns and inter-wire separations of 254 and 318 microns for Copyright the two screens examined. A flow facility has been constructed A method is described whereby structured multiblock meshes for experiments with these screens. Air is passed through the can be constructed from the solution of elliptic partial differential screens at upstream velocities yielding wire width Reynolds equations and which possess the property of orthogonality close numbers from 2 to 35. To determine the drag coefficient, pressure to boundaries and near orthogonality within the domain. To drops across the screens are measured using pressure transducers construct grids for viscous flow simulations which have appropriate and manometers. Three-dimensional flow simulations are also point distributions close to solid boundaries these grids are used performed. The computational drag coefficients consistently with point redistribution formulations. The result is high-quality grids overpredict the experimental values. However, the computational for use with both inviscid and viscous flow simulation algorithms. results exhibit sensitivity to the assumed wire cross section, Examples using the approach are given, and these include grids indicating that detailed knowledge of the wire cross section is for single and multicomponent aerofoils and bluff bodies. essential for unambiguous interpretation of experiments using photoetched screens. Standard semiempirical drag correlations for A93-53881 woven-wire screens do not predict the present experimental results A STUDY OF DAMAGE TOLERANCE OF THE LANDING GEAR with consistent accuracy. Author (revised) STRUCTURE FU-QI AN Acta Aeronautica et Astronautica Sinica (ISSN A93-53819 1000-6893) vol. 14, no. 2 Feb. 1993 p. B106-B108. In ON HOVERCRAFT OVERWATER HEAVE STABILITY CHINESE refs M. J. HINCHEY (Newfoundland Memorial Univ., St. John's, Canada) A brief introduction to the study of the damage tolerance and P. A. SULLIVAN (Toronto Univ., Downsview, Canada) Journal behavior of a main landing gear structure is given in this paper. of Sound and Vibration (ISSN 0022-460X) vol. 163, no. 2 May The study is performed with a landing gear which involves a 15, 1993 p. 261-273. Research supported by NSERC and complete procedure from fatigue crack initiation to crack growth, Canadian Transportation Development Centre refs residual strength and structural overall failure. First, real fatigue Copyright cracks are obtained by fatigue testing, then damage tolerance The dynamic heave stability of an air cushion vehicle or behavior is estimated. It is shown that cracks in the principal hovercraft hovering over deep water without forward motion is critical area are characterized by slow growth, and the investigated analytically. The principal feature of the analysis is crack-tolerant structure satisfies the requirement of residual the modeling of the motion of the water surface beneath the strength. Improved performance in terms of safety and reliability cushion caused by fluctuations in the pressure of the cushion or can be obtained by using the damage tolerance method to design cavity air. This surface motion interacts with the vehicle dynamics the landing gear structure. Author (revised) by modulating both the volume and exit flow area of the cushion. For analytical simplicity, the geometry chosen for study is a 2D A93-54021 section of a rigid wall plenum chamber; this enables exploitation ACTIVE CONTROL OF VORTEX BREAKDOWN BY A of classical linear wave formulas developed by Lamb for the surface SPINNING WAVE GENERATOR motion generated by a spatially uniform surface pressure oscillating M. KIKUCHI, K. HIRANO, T. YUGE (Miyazaki Univ., Japan), and sinusoidally in time. To assess stability characteristics, the Nyquist M. KUROSAKA (Washington Univ., Seattle) In ISABE - criterion is applied to the linearized equations. Results are International Symposium on Air Breathing Engines, 11th, Tokyo, presented for two cases: one is representative of a small test Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington vehicle, and the other of a large ice-breaking platform. They show American Institute of Aeronautics and Astronautics 1993 p. that the water surface motion significantly affects stability through 495-500. refs both of the proposed mechanisms, with cushion exit flow area (ISABE 93-7045) Copyright modulation usually being more important. A feature of the results The results of an experimental study on an active control of is that as the weight of a vehicle decreases many stability transitions the vortex breakdown are presented. Four different modes of occur. This suggests that simple guidelines for avoiding instability spinning disturbances are imposed on the vortex breakdown by a may not exist, so that stability augmentation devices may be spinning wave generator, which is a device to produce, at a required for vehicles designed to hover for extended periods over specified frequency, a sinusoidal wave disturbance spinning in the water. Author (revised) circumferential direction. It is shown that the m = 0 mode disturbances change the spiral type breakdown to the bubble type one and the m = +1 mode disturbances change the bubble A93-53820 type breakdown to the spiral one. KELVIN-HELMHOLTZ WAVE GENERATION BENEATH HOVERCRAFT SKIRTS A93-54035 P. A. SULLIVAN, C. WALSH (Toronto Univ., Downsview, Canada), NEW APPROXIMATE METHOD OF STRESS ANALYSIS FOR and M. J. HINCHEY (Newfoundland Memorial Univ., St. John's, BLADED ROTATING DISCS Canada) Journal of Sound and Vibration (ISSN 0022-460X) vol. H. KIKUCHI (Japan Defense Agency, Third Research Center, 163, no. 2 May 15, 1993 p. 275-282. refs Tokyo) and ROY A. COOKSON (Cranfield Inst. of Technology, Copyright United Kingdom) In ISABE - International Symposium on Air When a hovercraft is hovering over water, the air flow beneath Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, its skirts can interact with the water surface and generate waves. Proceedings. Vol. 1 Washington American Institute of Aeronautics These, in turn, can cause the hovercraft to undergo violent and Astronautics 1993 p. 623-636. refs self-excited heave motions. This note shows that the wave (ISABE 93-7059) Copyright generation is due to the classical Kelvin-Helmholtz mechanism A new stress analysis method was presented for determining where, beyond a certain air flow rate, small waves at the air the stress distribution in a rotating bladed disk by a 2D FEM, water interface extract energy from the air stream and grow. including the effects of asymmetry of the disk cross-section, blade loading and stiffening for radial-flow imellerand axial-flow type A93-53847 rotors. In the present analysis the effect of blades was considered THE CONSTRUCTION OF NEARLY ORTHOGONAL as a property of the material, i.e., equivalent density and Poisson's MULTIBLOCK GRIDS FOR COMPRESSIBLE FLOW ratio or Young's modulus, in order to use the axisymmetric 2D SIMULATION finite element stress analysis software. A comparison of the stress M. J. MARCHANT and N. P. WEATHERILL (Swansea Univ. College, calculated by the present method with the exact stresses of the United Kingdom) Communications in Numerical Methods in bladed rotating disk model and those measured in photoelastic Engineering (ISSN 0748-8025) vol. 9, no. 7 July 1993 p. model tests was present with good agreement. Author (revised)

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A93-54036 performing model tests under idealized conditions. This becomes THERMAL DESIGN AND ANALYSIS OF AN EXHAUST very clear in the case of the tests performed on an DIFFUSER UNIT IN A CERAMIC COMPOSITE application-oriented impingement-cooling configuration like that J. D. MCCAFFERTY and J. W. HANCOCK (Glasgow Univ., United often encountered in engine manufacture. In conclusion, as an Kingdom) In ISABE - International Symposium on Air Breathing example, temperature calculations are employed to demonstrate Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. the effect on the cooling effectiveness of varying the distances 1 Washington American Institute of Aeronautics and between insert and inner surface of the leading edge. It shows Astronautics 1993 p. 637-643. Research supported by how the effectiveness of the leading edge cooling can be increased Rolls-Royce, PLC and SERC refs by simple geometrical measures, which results in a considerable (ISABE 93-7060) Copyright improvement in service life. Author (revised) The exhaust diffuser unit of a modern air breathing engine has been chosen for a design study using ceramic composites. This is part of a wider research program to introduce new materials into aero-engines. Although the unit is relatively lightly stressed, it A93-54053* National Aeronautics and Space Administration. is subject to a severe thermal environment, and poses a significant Lewis Research Center, Cleveland, OH. test of the behavior of new materials. Material selection has been FLUID DYNAMICS AND CONVECTIVE HEAT TRANSFER IN based on deformation maps, using merit parameters for strength IMPINGING JETS THROUGH IMPLEMENTATION OF A HIGH and toughness under thermal shock. Heat transfer analysis of the RESOLUTION LIQUID CRYSTAL TECHNIQUE conceptual design has established the thermal transients, and K. KIM, B. WIEDNER, and C. CAMCI (Pennsylvania State Univ., allowed the estimation of thermally induced stresses. The stress University Park) In ISABE - International Symposium on Air levels are sufficient to induce micro-cracking in ceramic composites, Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, and has required the development of appropriate damage Proceedings. Vol. 2 Washington American Institute of Aeronautics mechanics models. and Astronautics 1993 p. 792-803. refs (Contract NAG3-989; NSF CTS-89-06452) A93-54050 (ISABE 93-7077) Copyright A combined convective heat transfer and fluid dynamics STUDIES ON COOLANT PROBLEMS IN AERONAUTICAL investigation in a turbulent round jet impinging on a flat surface is TURBINE CASCADES presented. The experimental study uses a high resolution liquid F. MARTELLI and V. MICHELASSI (Florence Univ., Italy) In crystal technique for the determination of the convective heat ISABE - International Symposium on Air Breathing Engines, 11th, transfer coefficients on the impingement plate. The heat transfer Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 experiments are performed using a transient heat transfer method. Washington American Institute of Aeronautics and Astronautics The mean flow and the character of turbulent flow in the free jet 1993 p. 757-765. Research supported by CEC refs is presented through five hole probe and hot wire measurements, (ISABE 93-7074) Copyright respectively. The flow field character of the region near the The investigation of the aerodynamic and heat transfer effects impingement plate plays an important role in the amount of of cooling jets requires both experimental and numerical convective heat transfer. Detailed surveys obtained from five hole investigations. A project along this guideline is currently carried probe and hot wire measurements are provided. An extensive out in a BRITE-Euram Program. This paper intends to present validation of the liquid crystal based heat transfer method against some numerical results obtained with three different solvers, explicit a conventional technique is also presented. After a complete single and multistep with and without multigridding, and various documentation of the mean and turbulent flow field, the convective mesh arrangements, H, HOH and CH grid types. A simple procedure heat transfer coefficient distributions on the impingement plate to treat the cooling jet at the trailing edge of a turbine blade is are presented. The near wall of the impingement plate and the presented which does not require excessive grid refinement. The free jet region is treated separately. The current heat transfer features of the different approaches are discussed mainly in terms distributions are compared to other studies available from the of the isentropic Mach number distribution of the blade, and some literature. The present paper contains complete sets of information conclusions are drawn on the capability of the methods on the three dimensional mean flow, turbulent velocity fluctuations, developed. and convective heat transfer to the plate. The experiments also prove that the present nonintrusive heat transfer method is highly A93-54052 effective in obtaining high resolution heat transfer maps with a HEAT TRANSFER AND MATERIAL TEMPERATURE heat transfer coefficient uncertainty of 5.7 percent. CONDITIONS IN THE LEADING EDGE AREA OF Author (revised) IMPINGEMENT-COOLED TURBINE VANES H. P. BERG (BMW Rolls-Royce GmbH, Oberursel, Germany), K. PFAFF (MTU Motoren- und Turbinen-Union Muenchen GmbH, Munich, Germany), and D. K. HENNECKE (Darmstadt Technical A93-54054 Univ., Germany) In ISABE - International Symposium on Air IMPINGEMENT COOLING WITH FILM COOLANT EXTRACTION Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, IN THE AIRFOIL LEADING EDGE REGIONS Proceedings. Vol. 2 Washington American Institute of Aeronautics LIGUO LI and ZHAOHUI LI (Nanjing Aeronautical Inst., China) and Astronautics 1993 p. 781-791. Research supported by In ISABE - International Symposium on Air Breathing Engines, MTU Motoren- und Turbinen-Union Muenchen GmbH refs 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 (ISABE 93-7076) Copyright Washington American Institute of Aeronautics and Astronautics The resultant effects on the cooling effectiveness at the leading 1993 p. 804-808. refs edge area of an impingement-cooled turbine vane by varying certain (ISABE 93-7078) Copyright geometrical parameters is described with reference to local internal An extensive experimental study is conducted to determine heat transfer coefficients determined from experiment and the heat transfer characteristics of arrays of air jets impinging on temperature calculations. The local heat transfer on the cooling-air perforated target surfaces in turbine blade leading edge regions side is determined experimentally with the aid of the analogy by six large-scale models. The relations of pressure loss and between heat- and mass transfer. The impingement cooling is Nusselt number to jet Reynolds number are obtained in a wide provided from an inserted sheet-metal containing a single row of range of parameter combinations of interest in cooled airfoil practice holes. The Reynolds Number and several of the cooling geometry for various models, respectively. These parameter combinations parameters were varied. The results demonstrate the high local are covered in a test matrix, including combinations of variations resolution of the method of measurement, which allows improved in jet Reynolds number, airfoil leading edge curvature analytical treatment of the leading-edge cooling configuration. radius-to-diameter ratio, jet pitch-to-diameter ratio, and jet These experiments also point to the necessity of not always impingement gap-to-diameter ratio. Author (revised)

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A93-54089 A93-54094 LIF VISUALIZATION OF 3-DIMENSIONAL HYPERSONIC CHARACTERISTICS OF HEAT EXCHANGER IN MIXING SUPERSONIC/SUBSONIC FLOWS TAKEO TOMITA, NAOKI HOMMA, TOSHI FUJIWARA, and AKIRA HIDETO MINEKAWA and TOSHI FUJIWARA (Nagoya Univ., SAITO (Nagoya Univ., Japan) In ISABE - International Symposium Japan) In ISABE - Inlernalional Symposium on Air Breathing on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Engines, 11th, Tokyo, Japan, Sepl. 20-24, 1993, Proceedings. Vol. Proceedings. Vol. 2 Washington American Institute of Aeronautics 2 Washington American Institute of Aeronautics and and Astronautics 1993 p. 1167-1173. refs Astronautics 1993 p. 1217-1221. (ISABE 93-7114) Copyright (ISABE 93-7119) Copyright Engines for hypersonic transport have problems on fuel-air There are a lot of problems to overcome in developing mixing. To study the flows in such engines, the LIF technique is air-breathing engines for a supersonic transporter. One of Ihem is used, where PLIF (planar laser-induced fluorescence) is convenient the high temperature of the flow entering the fan section which because it gives information without any interaction with the flow. becomes higher as the fly Mach number increases. One effective To provide a long-time-scale steady-state flow, an arcjet-type method to overcome this is a heat exchanger placed in the air electric thruster is used, simulating the main air stream, where a intake (which is called precooler). In this paper, Ihe possibility side jet simulating hydrogen fuel is visualized by the iodine-LIF and problems of the precooler are studied by resorting to the technique. The interaction between these two jets is shown. CFD method. This study pointed out that a simply shaped precooler Author (revised) like a flat plate can cool air only in the boundary layer; iherefore, the greater part of breathed air remains high-temperalure air. When A93-54090 Ihe precooler is located in the supersonic flow, owing to the ENHANCED FUEL-AIR MIXING IN HYPERSONIC ENGINES expansion wave from the corner of the precooler, the flow H. E. GILREATH, G. A. SULLINS, and R. RAUL (Johns Hopkins temperature near the precooler falls so that the effecl of precooler Univ., Laurel, MD) In ISABE - International Symposium on Air drops. Aulhor (revised) Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington American Institute of Aeronautics A93-54095 and Astronautics 1993 p. 1174-1181. refs COMPACT HEAT EXCHANGER FITTED TO ENGINES OF THE (ISABE 93-7115) Copyright INVERTED TYPE Experiments have been conducted to determine whether or YVES RIBAUD (ONERA, Palaiseau, France) and ISABELLE not the impingement of a periodic pattern of waves on a confined LURAULT (Ecole Polilechnique Feminine, Sceaux, France) In supersonic shear layer enhances mixing. The shear layer studied ISABE - International Symposium on Air Breathing Engines, 11th, is representative of the fuel-air mixing zone in a hypersonic engine's Tokyo, Japan, Sepl. 20-24, 1993, Proceedings. Vol. 2 combustor. Wavy walls, installed on the ceiling and/or floor of a Washington American Institute of Aeronautics and Astronautics special windtunnel facility, were used to generate various 1993 p. 1222-1231. Research supported by DRET refs impingement patterns, and the flow development was recorded (ISABE 93-7120; ONERA, TP NO. 1993-132) Copyright using spark schlieren photography. In the absence of wave An account is given of current practice in the design of cryogenic impingement, prominent quasi-coherent structures were observed heat exchangers applicable to hypersonic airbreathing vehicle in the shear layer. These structures became less distinct in the propulsion using LH2 fuel. Atlenlion is given lo the optimization of presence of the wave system while smaller scale disturbances the geometry, the prediction of heat-lransfer coefficients, and the became more pronounced. control of inlet air frosting characteristics for the 'PRIAM' counterflow heat-exchanger concept, in bolh sleady and unsteady A93-54092 operational regimes. The present results underscore the critical TWO-DIMENSIONAL AND THREE-DIMENSIONAL MIXING nature of the heat exchanger in an airbreathing, H2-fueled FLOW STRUCTURES WITH INJECTED THROUGH SLOTTED powerplant. AIAA NOZZLE AND CIRCULAR NOZZLE INTO SUPERSONIC FLOWS SHIGERU ASO, SATOSHI OKUYAMA, SHOZO MAEKAWA, MICHIAKI TANNOU (Kyushu Univ., Fukuoka, Japan), YASUNORI A93-54096 ANDO, YOSHIYUKI YAMANE (Ishikawajima-Harima Heavy A EULERIAN/LAGRANGIAN MODELLING TO CALCULATE Industries Co., Ltd., Yokohama, Japan), and MASAHIRO FUKUDA THE EVOLUTION OF A WATER DROPLETS SPRAY (National Aerospace Lab., Tokyo, Japan) In ISABE - International PAUL CREISMEAS (DGA, Orsay, France) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 Washington American Institute 20-24, 1993, Proceedings. Vol. 2 Washington American Institute of Aeronautics and Astronautics 1993 p. 1192-1201. refs of Aeronautics and Astronautics 1993 p. 1232-1240. refs (ISABE 93-7117) Copyright (ISABE 93-7121) Copyright Shock wave/turbulent boundary layer interaction regions We introduce a Eulerian/Lagrangian model to compule Ihe induced by gaseous secondary flows injected into supersonic flows evolution of a water spray inside a complex geometry. The air through slot and circular nozzles have been experimentally and flow is obtained by resolving time dependent incompressible Navier computationally investigated. In the experiments the flow fields Stokes equation. A finite difference method and a projection method are visualized by the Schlieren method and oil flow technique; are used. The turbulence is simulated by the Smagorinsky model. surface pressure and spatial total pressure distributions are The evolution of the water spray is calculated considering no measured in the whole interaction region. The total pressure ratio, turbulence effect on the droplet trajectories. The turbulence is P(c)/P(0) (P(c): total pressure of injected secondary flow, P(0): taken into account through correlations related to the Sherwood total pressure of freestream) is varied, and the change of the number and to the Nusselt number. The numerical results are flow field is investigated for slotted injection and circular injection. compared to those from Beard and Pruppacher (1971) and to The detailed flow structures in 2D and 3D mixing flow structures experimental data. We detect differences in the former case, and have been revealed. Especially for circular injection the surface we have a very good agreement in the latter one. We present a oil patterns show quite complicated flow in the interacting region study of the evolution of the MVD of a water spray in a realistic with primary and secondary separations. Also quite interesting pilot geometry: we simulate an icing test in a test cell concerning a pressure fields are revealed. The same flow fields have also been helicopter air intake screen. We pay attention to determine the simulated by solving Navier-Stokes equations with turbulent evolution of the water spray MVD parameter. It can be seen that modeling. Surface pressure and spatial pilot pressure distribulions in spite of weak inertia, droplets of low diameter are able to bump show quile good agreemenl wilh experimenls. The resulls suggesl the nosepiece of the test article. We can conduct the MVD near lhal Ihe numerical code is quile useful for supersonic mixing the air intake, and we notice that the proportion of droplets of flows. Aulhor (revised) large diameter breathed by the engine is negligible.

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A93-54098 15 EXPERIMENTAL INVESTIGATION OF BOUNDARY LAYER TRANSITION ON A FLAT PLATE WITH C4 LEADING EDGE MATHEMATICAL AND COMPUTER SCIENCES A. I. KALFAS and R. L. ELDER (Cranfield Inst. of Technology, United Kingdom) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Includes mathematical and computer sciences (general); computer Proceedings. Vol. 2 Washington American Institute of Aeronautics operations and hardware; computer programming and software; and Astronautics 1993 p. 1253-1262. Research supported by computer systems; cybernetics; numerical analysis; statistics and CEC refs probability; systems analysis; and theoretical mathematics. (ISABE 93-7123) Copyright This paper considers the effects of freestream turbulence intensity on the boundary layer transition over a range of Reynolds A93-52654# numbers. Bypass mode of transition has been considered using a AN ADVANCED ROTORCRAFT FLIGHT SIMULATION MODEL - flat plate with a C4 leading edge, designed to avoid laminar PARALLEL IMPLEMENTATION AND PERFORMANCE separation. This configuration provides the opportunity to study ANALYSIS the effect of a realistic turbomachinery leading edge shape on S. SARATHY (Georgia Inst. of Technology, Atlanta) and V. R. transition. Hot wire investigations of the boundary layer have been MURTHY (Syracuse Univ., NY) In AIAA Flight Simulation undertaken in order to acquire detailed information about the effect Technologies Conference, Monterey, CA, Aug. 9-11, 1993, of the freestream conditions on the structure of the boundary Technical Papers Washington American Institute of Aeronautics layer. This paper concludes with some global observations and and Astronautics 1993 p. 29-35. refs comparisons with theoretical predictions and with experimental (AIAA PAPER 93-3550) Copyright observations on a more conventional flat plate with a sharp leading Parallel processing techniques provide a powerful set of tools, edge. which can permit the use of computationally complex models for real-time flight simulation. Elastic blade element models provide adequate fidelity and accuracy needed to simulate advanced rotorcraft configurations. Parallel implementations of blade element A93-54276 code will be needed to model such rotorcraft for real-time simulation applications. Techniques to develop flight simulation models for HEAT LOADS AS KEY PROBLEM OF HYPERSONIC FLIGHT E. H. HIRSCHEL (Deutsche Aerospace AG, Munich, Germany) parallel (MIMD) architectures are presented in this paper. An Zeitschrift fuer Flugwissenschaften und Weltraumforschung (ISSN advanced rotorcraft flight simulation model, using the blade element approach, has been developed for an MIMD parallel computer, 0342-068X) vol. 16, no. 6 Dec. 1992 p. 349-356. refs Copyright based on a portable set of parallel primitives. Issues pertaining to this parallel development and implementation are also discussed. The problem of heat loads in hypersonic flight is addressed. Parallel speedup results for this model are provided based on Technical solutions to the problem as it affects airframes are execution times on an Encore Multimax 14-processor machine. sketched. The special problems of surface materials and aerothermodynamics are addressed. Related problems encountered involving simulation and prediction in the design of A93-52656# hypersonic vehicles are discussed. AIAA DYNAMIC SIMULATION FIDELITY IMPROVEMENT USING TRANSFER FUNCTION STATE EXTRAPOLATION WILLIAM J. BEZDEK and LARRY A. MOODY (McDonnell Douglas Aerospace, Saint Louis, MO) In AIAA Flight Simulation Technologies Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington American Institute of Aeronautics and Astronautics 1993 p. 44-52. refs (AIAA PAPER 93-3552) Copyright 13 To achieve maximum dynamic fidelity in a real time manned flight simulator, it is imperative that any hardware or computational GEOSCIENCES delays be reduced as much as possible. Unfortunately, some visual systems continue to have a significant processing time delay. To Includes geosciences (general); earth resources; energy production compensate for these delays, general form extrapolation schemes and conversion; environment pollution; geophysics; meteorology have been employed by the simulation industry. This paper presents and climatology; and oceanography. a transfer function extrapolation method which takes advantage of the second order nature of most aircraft models to extrapolate aircraft state with greater accuracy and at higher input signal A93-52898* National Aeronautics and Space Administration. frequencies. To be of practical benefit to the simulation community, Langley Research Center, Hampton, VA. issues of commonality and implementation have also been CASE STUDY OF A LOW-REFLECTIVITY PULSATING addressed. To allow this approach to be independent of aircraft MICROBURST - NUMERICAL SIMULATION OF THE DENVER, type, a method to calculate the transfer function damping and 8 JULY 1989, STORM natural frequency from the past values of the original aircraft model FRED H. PROCTOR (NASA, Langley Research Center, Hampton, is presented. VA) Oct. 1993 5 p. AMS, Conference on Severe Local Storms, 17th, Saint Louis, MO, Oct. 4-8, 1993, Paper refs A93-52660# An intense, low-reflectivity, and pulsating microburst event, HYBRID COMPLEX OF THE AIRCRAFT INTELLECTUALIZED detected on July 8, 1989 by the Low-Level Windshear Alert System CONTROL SYSTEMS SIMULATION AT THE STAGE OF THEIR north of Denver Stapleton Airport is described using a Terminal RESEARCH PROJECTING Area Simulation System (TASS) model (Proctor, 1987). This 3d A. I. YAKOVLEV and V. M. VASILETS (International Academy of nonhydrostatic cloud model includes parametrizations for both Engineering, Moscow, Russia) In AIAA Flight Simulation liquid- and ice-phase microphysics. Simulation results show that Technologies Conference, Monterey, CA, Aug. 9-11, 1993, the dissipating cloud induces a type-1 pulsating microburst event, Technical Papers Washington American Institute of Aeronautics with at least three distinct microburst pulses over a period of 20 and Astronautics 1993 p. 74-80. refs min. Virga from the dissipating cloud continued to maintain (AIAA PAPER 93-3559) Copyright hazardous windshear for a period much longer than the typical The paper examines the problem of simulating aircraft intelligent lifetime of a single microburst. AIAA control systems at the initial development state, with emphasis on

1222 15 MATHEMATICAL AND COMPUTER SCIENCES the flight factors affecting pilots and operators. Consideration is databases and for searching through them quickly. Various tuning given to the primary elements of an intelligent control system of parameters are explained and run-time performance figures are flight vehicles, the set of indices for the man-machine system offered. analyses, and the selection tasks for the 'best1 man-machine system. The tasks optimization scheme of the 'best' selection system is formulated taking into account the features of human A93-52681# participation. A simulation example of spacecraft intelligent control THE NUMERICAL ERRORS IN INVERSE SIMULATION system is described, and block diagrams of the control system K. C. LIN (Central Florida Univ., Orlando, FL), P. LU (Iowa State and its elements are presented. AIAA Univ. of Science and Technology, Ames), and M, SMITH (Central Florida Univ., Orlando, FL) In AIAA Flight Simulation Technologies A93-52663# Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers TRANSPORT DELAY COMPENSATION - AN INEXPENSIVE Washington American Institute of Aeronautics and Astronautics ALTERNATIVE TO INCREASING IMAGE GENERATOR 1993 p. 251-256. refs UPDATE RATE (AIAA PAPER 93-3588) Copyright FRANK M. CARDULLO and GARY GEORGE (New York State This paper analyzes the numerical errors of two categories of Univ., Binghamton) In AIAA Flight Simulation Technologies inverse simulation algorithms: differentiation inverse method and Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers integration inverse method. A first-order differential equation is Washington American Institute of Aeronautics and Astronautics used to demonstrate the concept. The results of the inverse 1993 p. 95-102. refs simulation are used as step-function inputs to the differential (AIAA PAPER 93-3563) Copyright equation for a forward simulation. The result is then compared Several delay compensation methods are investigated which with the original trajectory for the error measure. A second-order illustrate that the phase lag due to system delays can be differential equation is used to demonstrate the problem which compensated in many cases. The paper compares the behavior the integration inverse method may encounter when there are of three methods; a lead/lag formulation by Ricard and Harris unspecified state variables in the problem. A point-mass aircraft (1980), a predictor algorithm devised by McFarland (1988) and a model is used as a numerical example for the comparison of state predictor algorithm developed by Sobiski and Cardullo (1987). these two methods. The performance of these three algorithms is illustrated in response to system dynamics incorporating simulated aircraft dynamics, a pilot model, and various visual or other subsystem delays. The A93-52682# results indicate the two predictor schemes are both considerably A DUAL-EULER METHOD FOR SOLVING ALL-ATTITUDE superior to the lead/lag. The differences between the two predictor ANGLES OF THE AIRCRAFT algorithms are not quite as significant. The McFarland approach XUEQIAO HUANG (China Flight Test Establishment, Xian) In has substantial phase lag and gain distortion slightly above the AIAA Flight Simulation Technologies Conference, Monterey, CA, design bandpass. However, the McFarland compensator is Aug. 9-11,1993, Technical Papers Washington American Institute considerably simpler to implement. Author (revised) of Aeronautics and Astronautics 1993 p. 257-262. refs (AIAA PAPER 93-3589) Copyright A93-52678# This paper presents a new method, called dual-Euler method, IMPLEMENTATION OF EXPERT SYSTEMS WITHIN AN for solving exactly all-attitude angles of the aircraft. This method INTERACTIVE TACTICAL ENVIRONMENT is based on the inverse relationship of both the essence and the D. N. SIKSIK and R. D. ROURKE (CAE Electronics, Ltd., singular point-areas between the ordinary and the reversed Euler St.-Laurent, Canada) In AIAA Flight Simulation Technologies equations; it separates the area and alternatively calculates their Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers essence areas. That is, it still retains the advantage of Washington American Institute of Aeronautics and Astronautics straightforwardness and high accuracy of calculation in the essence 1993 p. 227-233. refs areas of the ordinary Euler equations, and can utilize the essence (AIAA PAPER 93-3583) Copyright areas of the reversed Euler equations instead of the singular areas The requirement for an interactive and realistic environment is of the ordinary Euler equations. In this dual-Euler angle coordinate present in simulation for both training and research. A necessary system, the essence area is expanded to the whole area and the factor in achieving this environment is the ability to model the singular area can be eliminated. Without principle defects and intelligence of the entities within it, thus providing a capability for method errors, the dual-Euler method can overcome the singularity realistic behavior and interaction. CAE's Interactive Tactical and get the most exact all-attitude angles of the aircraft. The Environment Management System (ITEMS) provides simulations testing results show that the transit of the attitude angle in the with an environment in which entities are closely modelled with whole area with the dual-Euler method is smooth and bona fide, respect to both systems and intelligence, allowing them to interact thereby it is an ideal all-attitude equation. Author (revised) with each other and with their environment in a realistic manner. ITEMS approaches the problem of simulating entity intelligence through the implementation of expert systems. The further A93-52683# improvement of networking geographically remote simulations INITIAL DEVELOPMENT OF A RESEARCH FLIGHT together and to ITEMS provides several enhancements including SIMULATOR SOFTWARE the capability for more cost-effective and realistic training. T. CALEFFI and E. M. BELO (Sao Paulo Univ., Sao Carlos, Brazil) In AIAA Flight Simulation Technologies Conference, A93-52680*# National Aeronautics and Space Administration. Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington Ames Research Center, Moffett Field, CA. American Institute of Aeronautics and Astronautics 1993 p. A RADAR ALTITUDE AND LINE OF SIGHT ATTACHMENT 263-266. refs RUSSELL SANSOM and DAVID DARLING (SYRE; NASA, Ames (AIAA PAPER 93-3590) Copyright Research Center, Moffett Field, CA) In AIAA Flight Simulation In this work, steps that were taken to design part of a flight Technologies Conference, Monterey, CA, Aug. 9-11, 1993, simulator software are described. It comprises the integration, Technical Papers Washington American Institute of Aeronautics look-up and set of flight differential equation routines, and the and Astronautics 1993 p. 243-250. refs aircraft data. The software was made in a modular form, to allow (AIAA PAPER 93-3587) Copyright future implementations. The method chosen to make the equations This paper describes a method of overcoming much of the integration was the fourth-order Runge-Kutta. The data were computational expense of finding radar altitude and determining disposed in a bidimensional matrix, called data pool, and the lines of sight in flight simulations over databases built from language used was the C language, due to its portability and data polygons. Methods are described for quantizing polygonal structures. Author (revised)

1223 15 MATHEMATICAL AND COMPUTER SCIENCES

A93-52684*# National Aeronautics and Space Administration. Technologies Conference, Monterey, CA, Aug. 9-11, 1993, Ames Research Center, Moffett Field, CA. Technical Papers Washington American Institute of Aeronautics ENHANCING REAL-TIME FLIGHT SIMULATION EXECUTION and Astronautics 1993 p. 289-297. refs BY INTERCEPTING RUN-TIME LIBRARY CALLS (AIAA PAPER 93-3596) Copyright NAMEJS REINBACHS (SYRE; NASA, Ames Research Center, Increasingly stringent standards for simulator fidelity have led Moffett Field, CA) In AIAA Flight Simulation Technologies to a need for continually improving the aerodynamic mathematical Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers models for flight simulations produced by Boeing Commercial Washington American Institute of Aeronautics and Astronautics Airplane Group (BCAG). An overview of the process used at BCAG 1993 p. 267-274. refs for producing and validating the flight updated aerodynamic model (AIAA PAPER 93-3591) Copyright is presented. Topics include flight-test planning, instrumenta- Standard operating system input-output (I/O) procedures tion requirements, aerodynamic coefficient extraction, and impose a large time penalty on real-time program execution. These simulator-to-flight validation. Particular emphasis is given to the procedures are generally invoked by way of Run-Time Library (RTL) extraction method which is used to identify aerodynamic coefficient calls. To reduce the time penalty, as well as add flexibility, a information for the entire model in both linear and nonlinear regions, technique has been developed to dynamically intercept these calls. including the effects of flow separation and aerodynamic hysteresis. The design and implementation of this technique, as applied to An actual example is provided showing the flight updated basic FORTRAN WRITE statements, are described. Measured lift coefficient compared to predicted data, and the resulting performance gains using this RTL intercept technique are on the improvement of the simulator-to-flight comparison of a deceleration order of 1000 percent. to full stall and the subsequent recovery.

A93-52685*# National Aeronautics and Space Administration. A93-52732 Langley Research Center, Hampton, VA. IDENTIFICATION OF NONLINEAR MECHANICAL SYSTEMS AN EVALUATION OF SOFTWARE TOOLS FOR THE DESIGN USING COMBINED STATE AND PARAMETER EVALUATION AND DEVELOPMENT OF COCKPIT DISPLAYS [IDENTIFIKATION NICHTLINEARER MECHANISCHER THOMAS D. ELLIS, JR. (Unisys Corp.; NASA, Langley Research SYSTEME DURCH KOMBINIERTE ZUSTANDS- UND Center, Hampton, VA) In AIAA Flight Simulation Technologies PARAMETERSCHAETZUNG] Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers CLAUS-PETER FRITZEN and S. SEIBOLD (Kaiserslautern Univ., Washington American Institute of Aeronautics and Astronautics Germany) Zeitschrift fuer Angewandte Mathematik und Mechanik 1993 p. 275-280. refs (ISSN 0044-2267) vol. 73, no. 7-8 1993 p. T 752-T 755. In (AIAA PAPER 93-3593) Copyright GERMAN Gesellschaft fuer Angewandte Mathematik und The use of all-glass cockpits at the NASA Langley Research Mechanik, Wissenschaftliche Jahrestagung, Univ. Leipzig, Center (LaRC) simulation facility has changed the means of design, Germany, Mar. 24-28, 1992, Vortraege. A93-52726 23-31 refs development, and maintenance of instrument displays. The Copyright human-machine interface has evolved from a physical hardware System identification methods permit faulty computational device to a software-generated electronic display system. This models to be corrected using measured values and also allow has subsequently caused an increased workload at the facility. As model-supported monitoring of rotors. The use of the extended computer processing power increases and the glass cockpit Kalman filter as an evaluator of states and of parameters, and of becomes predominant in facilities, software tools used in the design the method of instrumental variables, is examined. AIAA and development of cockpit displays are becoming both feasible and necessary for a more productive simulation environment. This A93-52762* National Aeronautics and Space Administration. paper defines LaRC requirements of a display software Langley Research Center, Hampton, VA. development tool and compares two available applications against CHARACTERIZATION OF THE FAULTED BEHAVIOR OF these requirements. As a part of the software engineering process, DIGITAL COMPUTERS AND FAULT TOLERANT SYSTEMS these tools reduce development time, provide a common platform SALVATORE J. BAVUSO (NASA, Langley Research Center, for display development, and produce exceptional real-time Hampton, VA) and PAUL S. MINER (Planning Research Corp., results. Author (revised) Aerospace Technologies Div., Hampton, VA) Jan. 1989 8 p. Hawaii International Conference on Systems Sciences, 22nd, A93-52686# Honolulu, HI, Jan. 3-6, 1989, Paper refs REUSABLE CODE FOR HELICOPTER SIMULATION A development status evaluation is presented for efforts JO A. PICKERINE (Loral Defense Systems, Akron, OH), KUO-CHI conducted at NASA-Langley since 1977, toward the LIN, CURTIS LISLE, and G. GURUPRASAD (Inst. for Simulation characterization of the latent fault in digital fault-tolerant systems. and Training, Orlando, FL) In AIAA Flight Simulation Technologies Attention is given to the practical, high speed, generalized gate-level Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers logic system simulator developed, as well as to the validation Washington American Institute of Aeronautics and Astronautics methodology used for the simulator, on the basis of faultable 1993 p. 281-288. refs software and hardware simulations employing a prototype (AIAA PAPER 93-3594) Copyright MIL-STD-1750A processor. After validation, latency tests will be The paper describes a method for developing reusable software performed. AIAA (i.e., reusable without change) for helicopter simulation. The reusability of software is achieved by following five steps: (1) the A93-52763* National Aeronautics and Space Administration. simulated system is object-oriented, with the object packaged Langley Research Center, Hampton, VA. separately from the simulation of the object; (2) for each object, a LINEAR QUADRATIC TRACKING PROBLEMS IN HILBERT package of single-function routines must be developed, which SPACE - APPLICATION TO OPTIMAL ACTIVE NOISE simulate that object's behavior; (3) each routine is given an interface SUPPRESSION module, to ensure unchanging argument lists; (4) each object H. T. BANKS (Brown Univ., Providence, Rl), R. J. SILCOX, S. L simulation must be given a generic package which lists the modules KEELING (NASA, Langley Research Center, Hampton, VA), and used in the simulation of the object and associated generic names; C. WANG (Brown Univ., Providence, Rl) Jun. 1989 7 p. IFAC, and (5) the routines and modules must be unit-independent, and Symposium on Control of Distributed Parameter Systems, the routines must be data structure independent. AIAA Perpignan, France, June 26-29, 1989, Paper refs (Contract NSF MCS-85-04316; F49620-86-C-0111; NAS1-18107) A93-52687# A unified treatment of the linear quadratic tracking (LOT) FLIGHT UPDATE OF AERODYNAMIC MATH MODEL problem, in which a control system's dynamics are modeled by a KENDALL W. NEVILLE and A. T. STEPHENS (Boeing Commercial linear evolution equation with a nonhomogeneous component that Airplane Group, Renton, WA) In AIAA Flight Simulation is linearly dependent on the control function u, is presented; the

1224 16 PHYSICS treatment proceeds from the theoretical formulation to a numerical massive use of numerical simulation has allowed to obtain several approximation framework. Attention is given to two categories of results about the behavior and performance of engines. The use LOT problems in an infinite time interval: the finite energy and the of numerical data for developing sets of logical rules for high finite average energy. The behavior of the optimal solution for flexibility Knowledge Bases is shown. Finally examples of Expert finite time-interval problems as the length of the interval tends to Systems for different aspects of turbofan simulation are presented infinity is discussed. Also presented are the formulations and and discussed. properties of LQT problems in a finite time interval. AIAA

A93-53620 STABILITY ANALYSIS THROUGH BIFURCATION THEORY. I, II 16 PH. GUICHETEAU (ONERA, Chatillon, France) ONERA, TP no. 1993-108 1993 22 p. NATO, AGARD, Lecture Series on Non PHYSICS Linear Dynamics and Chaos, 191st, Stanford Univ., CA, June 9-11, 1993 and Valbonne, France, June 16-18, 1993 refs (ONERA, TP NO. 1993-108) Includes physics (general); acoustics; atomic and molecular A brief presentation is made of bifurcation theory regarding physics; nuclear and high-energy physics; optics; plasma physics; nonlinear phenomena representative of high performance aircraft solid-state physics; and thermodynamics and statistical physics. dynamical behavior, and a methodology for the analysis of such systems is proposed. In the second part of this work, attention is given to problems associated with the introduction of control laws A93-52945 for the stabilization of unstable dynamic systems. The A STUDY OF OPTICAL DISTORTIONS ARISING IN state-of-the-art in treatments aimed at determining the attracting RADIATION TRANSMISSION THROUGH CAVITIES WITH GAS region of a stable equilibrium point is described. AIAA FLOW AROUND THEM [ISSLEDOVANIE OPTICHESKIKH ISKAZHENIJ, VOZNIKAYUSHCHIKH PRI PROKHOZHDENII IZLUCHENIYA CHEREZ POLOSTI, OBTEKAEMYE GAZOVYM A93-53642 POTOKOM] ON DEFINITION AND USE OF SYSTEMS ENGINEERING A. A. GILERSON and A. R. ALEKSEEV Aviatsionnaya Tekhnika PROCESSES, METHODS AND TOOLS (ISSN 0579-2975) no. 1 1993 p. 34-38. In RUSSIAN refs ARTHUR STONE, CHARLES SCOTT, and SHAWN RAHMANI Copyright (Rockwell International Corp., Collins Air Transport Div., Downey, Methods of pulsed laser interferometry are used to obtain data CA) In 1993 IEEE Aerospace Applications Conference, 14th, on the extent of optical distortions associated with air flow past Steamboat Springs, CO, Jan. 31-Feb. 5, 1993, Digest New York open and closed cavities at Mach 0.59-1.8. It is found that the Institute of Electrical and Electronics Engineers, Inc. 1993 p. extent of the distortions depends to a large degree on the flow 197-205. refs regime. For radiation wavelengths of 0.55 micron, the distortions Copyright may reach 2-5 wavelengths. AIAA A case study on the development and deployment of a systems engineering process for use on commercial avionics systems is discussed. The systems engineering process is presented in the A93-53194 context of the overall product development process, called the EXPERIMENTAL INVESTIGATION INTO THE MECHANISM OF common process (CP), which identifies goals, objectives, major DISCRETE FREQUENCY NOISE (DFN) GENERATION FROM A milestones and top level activities for the systems engineering, NACA 0012 BLADE hardware engineering, software engineering, project management HIDECHITO HAYASHI, TOHRU FUKANO, and YOSHIO KODAMA and authorization/budgeting processes. The systems engineering Japan Society of Mechanical Engineers, Transactions B (ISSN development plan is described. The scope of the systems 0387-5016) vol. 59, no. 559 March 1993 p. 802-806. In engineering process and its major activities are described. JAPANESE refs Emphasis is on using techniques that reduce cultural and Copyright organizational impact and improve the likelihood that the changes An experimental investigation was made into the mechanism are accepted. of discrete frequency noise (DFN) generation from a NACA 0012 blade placed in a uniform oncoming flow. It was clarified that A93-53770 DFN was generated when the boundary layer on the blade surface NETWORKS EXTEND SIMULATION'S REACH was laminar and separated at the location upstream of the trailing BRIAN F. GOLDIEZ (Central Florida Univ., Orlando, FL) Aerospace edge. A dead air region was formed just after the trailing edge of America (ISSN 0740-722X) vol. 31, no. 8 Aug. 1993 p. the blade. Therefore a Karman vortex street occurred. Meanwhile 22-25. we could not observe a close relationship between the existence Copyright of a separation bubble and the generation of DFN. That is, DFN Simulator networking called distributed interactive simulation was generated even when the attack angle of the flow was nearly (DIS) is discussed. DIS standards are capable of supporting zero and no separation bubble was observed. When a separation concurrent engineering by providing a convenient way to create a bubble existed, the boundary layer became turbulent and the flow rapid prototyping environment. DIS makes it possible to combine did not separate up to the trailing edge, so a dead air region was diverse simulation models to produce an integrated concurrent not formed behind the blade, which resulted in the disappearance engineering environment. AIAA of DFN. The prediction of the sound pressure level of DFN generated from this streamlined blade by Fukano's theory for a A93-54108 flat plate model agreed well with the measured value. EXPERT SYSTEMS FOR THE SIMULATION OF TURBOFAN Author (revised) ENGINES GIOVANNI TORELLA (Italian Air Force Academy, Pozzuoli, Italy) A93-53206 In ISABE - International Symposium on Air Breathing Engines, ACTIVE AERODYNAMIC CONTROL OF WAKE-AIRFOIL 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 2 INTERACTION NOISE - EXPERIMENT Washington American Institute of Aeronautics and Astronautics J. SIMONICH, P. LAVRICH (United Technologies Research Center, 1993 p. 1353-1366. refs East Hartford, CT), T. SOFRIN, and D. TOPOL (Pratt & Whitney (ISABE 93-7133) Copyright Group, East Hartford, CT) AIAA Journal (ISSN 0001-1452) vol. The main steps of a work carried out for developing Expert 31, no. 10 Oct. 1993 p. 1761-1768. DGLR/AIAA Aeroacoustics Systems for turbofan simulation are shown. The first part of paper Conference, 14th, Aachen, Germany, May 11-14, 1992, deals with the selection of computer language. Successively the Proceedings. Vol. 1, p. 229-237. Previously cited in issue 05, p.

1225 16 PHYSICS

823, Accession no. A93-19153 refs 17 Copyright SOCIAL SCIENCES

A93-53222 Includes social sciences (general); administration and management; SOME ACOUSTIC FEATURES OF PERFORATED TEST documentation and information science; economics and cost SECTION WALLS WITH SPLITTER PLATES analysis; law and political science; and urban technology and BORIS L MEDVED (National Research Council of Canada, Inst. transportation. for Aeronautical Research, Ottawa) AIAA Journal (ISSN 0001-1452) vol. 31, no. 10 Oct. 1993 p. 1885-1890. AIAA, Aerodynamic Ground Testing Conference, 16th, Seattle, WA, June A93-52653# 18-20, 1990, AIAA Paper 90-1418. Previously cited in issue 16, p. INTERNALLY COHERENT SYSTEM OF INNOVATION - THE 2615, Accession no. A90-37955 refs CASE OF FLIGHT SIMULATION Copyright ROGER MILLER and F. X. OLLEROS In AIAA Flight Simulation Technologies Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers Washington American Institute of Aeronautics A93-53615 and Astronautics 1993 p. 12-28. refs THE ACOUSTICS OF AXIAL COMPRESSORS [ACOUSTIQUE (AIAA PAPER 93-3548) Copyright DES COMPRESSEURS AXIAUX] This paper reports on the finding of a study of the flight SERGE LEWY ONERA, TP no. 1993-102 1993 22 p. In simulation industry, from a perspective of industrial economics. FRENCH EUR'Acoustique 93, Ecully, France, June 7-9, 1993 Our analysis corroborates two basic insights from the recent refs literature on industrial dynamics: first, that cooperation and (ONERA, TP NO. 1993-102) competition are complementary, rather than contrary, aspects of Line noise is examined for axial compressors, with emphasis industrial evolution; second, that both cooperation and competition on subsonic machines. The basic acoustic theory of axial are necessary for the emergence and effective functioning of compressors is presented, and the internal measurements that complex industries. Our main original contribution consists in are necessary to gain knowledge of the physical phenomena suggesting that, under conditions of increasing returns to market involved are indicated. Ways to reduce the noise produced by share, tight oligopolies are ideally suited to deliver an optimal axial compressors are also examined. AIAA combination of inter-firm cooperation and competition and, hence, a consistently high level performance.

A93-53616 A93-52930 AIR CARRIERS' LIABILITY FOR PASSENGER INJURY OR ACOUSTIC-WAVE PROPAGATION IN DUCTS AND DEATH - THE JAPANESE INITIATIVE AND RESPONSE TO FREE-FIELD RADIATION [PROPAGATION DES ONDES THE RECENT EC CONSULTATION PAPER ACOUSTIQUES DANS LES CONDUITS ET RAYONNEMENT EN BIN CHENG (London Univ., United Kingdom) Air & Space Law CHAMP LIBRE] (ISSN 0927-3379) vol. 18, no. 3 June 1993 p. 109-122. SERGE LEWY ONERA, TP no. 1993-103 1993 27 p. In FRENCH EUR'Acoustique 93, Ecully, France, June 7-9, 1993 refs Copyright refs The response of the Japanese Ministry of Transport to the (ONERA, TP NO. 1993-103) recent Consultation Paper which criticized the lack of worldwide The fundamental concepts of guided acoustic-wave propagation understanding on the objectives of the Warsaw Convention is are introduced, including plane waves at low frequency and the discussed. The Japanese Initiative and Response attempts to existence of oblique waves above the cutoff frequency. Analytical correct the overemphasis of the Warsaw System on limiting the calculations have made it possible to determine the complete air carrier's liability for passenger injury and death. To save the characteristics of the sound field, decomposed into the natural Warsaw System, it is recommended that the objective should be modes of ducts of rectangular or circular cross section. These absolute, unlimited, and secured liability of air carriers for passenger are essentially derived from the dispersion relation and the injury and death. AIAA boundary conditions on the walls. The far-field radiation is also investigated. AIAA A93-52931 AIR TRANSPORT AND THE ENVIRONMENT - REGULATING AIRCRAFT NOISE A93-53817 PETER DAVIES and JEFFREY GOH (Liverpool Univ., United A DYNAMIC STIFFNESS/BOUNDARY ELEMENT METHOD FOR Kingdom) Air & Space Law (ISSN 0927-3379) vol. 18, no. 3 THE PREDICTION OF INTERIOR NOISE LEVELS June 1993 p. 123-135. refs R. S. LANGLEY (Southampton Univ., United Kingdom) Journal Copyright of Sound and Vibration (ISSN 0022-460X) vol. 163, no. 2 May The history and present status of the law regarding regulation 15, 1993 p. 207-230. refs of aircraft noise are reviewed. Emphasis is given to European Copyright directives implementing ICAO standards and compliance by A method is presented for the prediction of the noise individual European states. Private actions as a control mechanism transmission into structures which have a constant cross-sectional are considered, including a human rights perspective. AIAA geometry. The structural vibrations are analyzed by using the dynamic stiffness method, while the boundary element method A93-53423 (BEM) is used to calculate the interior noise levels. The analysis 3-D BRAIDED PREFORMS; COST TO MANUFACTURE: procedure is a direct one, which means that there is no need to MAGNAWEAVE. I - IDENTIFYING COST FACTORS calculate the modes of vibration of either the structure or the ROBERT A. FLORENTINE (MAGNAWEAVE, Inc., Norristown, PA) interior airspace. Furthermore, a method is presented for the In International SAMPE Technical Conference, 24th and suppression of numerical damping in the BEM analysis, which International SAMPE Metals and Metals Processing Conference, allows the use of much fewer boundary elements than would 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 otherwise be needed. Particular attention is paid to the case of Covina, CA Society for the Advancement of Material and Process airborne noise transmission into an aircraft fuselage structure, and Engineering 1992 p. T621-T629. refs comparisons are made with previous experimental and theoretical Copyright results for a circular cylindrical test article. A model is presented for 3D braided preforms'

1226 19 GENERAL cost-to-manufacture (CTM) predictions that can establish the commercial viability of the process contemplated. Market selection is conducted as an iterative process in which the more reliable the input, the more tolerable the output is of lower probable return. The way in which the model is used therefore depends on the verifiability of inputs. AIAA

A93-53726 FLIGHT SAFETY IN EUROPE [FLUGSICHERUNG IN EUROPA] WALTER SCHWENK and RUEDIGER SCHWENK Zeitschrift fuer Luft- und Weltraumrecht (ISSN 0340-8329) vol. 42, no. 2 June 1993 p. 121-143. In GERMAN refs Copyright The legal regime of European flight safety is discussed. The Eurocontrol Agreement and its implementation are examined, emphasizing the European integration steps required for the implementation of the agreement. The main problems remaining in developing European flight safety in the framework of Eurocontrol are addressed. AIAA

A93-53727 STUMBLING BLOCKS FOR AIRPORT CONSTRUCTION IN THE NEW GERMAN FEDERAL STATES [STOLPERSTEINE BEIM FLUGPLATZAUSBAU IN DEN NEUEN BUNDESLAENDERN] STEFAN A. KAISER Zeitschrift fuer Luft- und Weltraumrecht (ISSN 0340-8329) vol. 42, no. 2 June 1993 p. 151-161. In GERMAN refs Copyright Ways to shorten the time in which airports of all kinds in Germany are constructed are considered. Emphasis Js given to the role of a new traffic planning acceleration law in the German federal states. AIAA

A93-53826* National Aeronautics and Space Administration, Washington, DC. INTERNATIONAL AEROSPACE STI LAURIE HARRISON and THOMAS LAHR (NASA, Washington) Sci-Tech News (ISSN 0036-8059) vol. 47, no. 3 Aug. 1993 p. 57, 58. refs Copyright A brief discussion is presented of the use being made by the American R&D community of international aerospace scientific and technical information (STI). The incorporation of international STI into the NASA Aerospace Database is addressed. AIAA

GENERAL

A93-53977 RESEARCH AND DEVELOPMENT OF AIRCRAFT ENGINE IN JAPAN - HISTORICAL REVIEW MASAKATSU MATSUKI (Nippon Inst. of Technology, Saitama, Japan) In ISABE - International Symposium on Air Breathing Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, Proceedings. Vol. 1 Washington American Institute of Aeronautics and Astronautics 1993 p. 7-11. (ISABE 93-7000) Copyright The history of Japanese aircraft engine production is briefly reviewed. The design targets achieved in engines over this period are identified. The tests performed on the engines are summarized. AIAA

1227 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 298) December 1993

Typical Subject Index Listing ADAPTIVE CONTROL Evaluation of 2D ceramic matrix composites in Space marching calculations about hypersonic aeroconvective environments p 1212 A93-53459 configurations using a solution-adaptive mesh algorithm Aerodynamic heating environment definition/thermal P1177 A93-53212 protection system selection for the HL-20 SUBJECT HEADING ADHESIVE BONDING P1181 A93-53739 'No VOC' water-borne corrosion resistant primers for AERODYNAMIC LOADS aerospace bonding applications p 1211 A93-53419 Methodology for integration of digital control loaders in Evaluation of water-borne adhesive bonding primers for aircraft simulators ACOUSTIC STREAMING use on the advanced aircraft material aluminum-lithium [AIAA PAPER 93-3551 ] p 1207 A93-52655 — A general introduction to aeroacoustics end P1211 A93-53420 The fluid physics of parachute inflation Durability properties for adhesively bonded structural atmospheric sound P1189 A93-54347 [NASA-CR-189717] p 102 N93 1:>021 aerospace applications p 1217 A93-53515 AEROACOUSTICS AERODYNAMIC NOISE Experimental investigation into the mechanism of Some acoustic features of perforated test section walls discrete frequency noise (OFN) generation from a NACA with splitter plates p 1226 A93-53222 0012 blade p 1225 A93-53194 A dynamic stiffness/boundary element method for the The low frequency aeroacoustics of buried nozzle prediction of interior noise levels p 1226 A93-53817 systems p 1205 A93-54244 AERODYNAMIC STABILITY AEROBRAKING Non-linear flight dynamics Recent advances in computational analysis of [ONERA, TP NO. 1993-109] p 1206 A93-53621 The subject heading is a key to the subject hypersonic vehicles p 1179 A93-53364 A study of the stability of vortical structures in supersonic content of the document. The title is used to Determination of heat transfer to flow in a duct with a inlets provide a description of the subject matter. When pseudodiscontinuity p 1179 A93-53365 [ISABE 93-7103] p1187 A93-54079 the title is insufficiently descriptive of document AERODYNAMIC CHARACTERISTICS AERODYNAMIC STALLING Flight update of aerodynamic math model Aerodynamic characteristics of conical content, a title extension is added, separated [AIAA PAPER 93-3596] p 1224 A93-52687 triangular-planform wings of low aspect ratio in subsonic from the title by three hyphens. The accession Stabilization of the dynamic characteristics of the Stalled flow p 1180 A93-53574 number and the page number are included in two-channel automatic control system of aircraft AERODYNAMICS each entry to assist the user in locating the p 1205 A93-52941 Aerodynamic inverse design and analysis for a full abstract in the abstract section. If applicable, a Identification of the phase characteristics and engine wind-induced perturbations of an aircraft from flight test [ISABE 93-7086] pi 186 A93-54062 report number is also included as an aid in iden- results p 1206 A93-52943 Advanced aerodynamic airframe/nozzle integration Effect of boundary layer suction on the thrust and tifying the document. Under any one subject [ISABE 93-7099] p1187 A93-54075 aerodynamic efficiency of a hypersonic flight vehicle heading, the accession numbers are arranged in AEROELASTICITY sequence. P1176 A93-52959 Aerodynamic characteristics of conical Flutter analysis of stiffened laminated composite plates triangular-planform wings of low aspect ratio in subsonic and shells in supersonic flow p 1216 A93-53224 stalled flow p1180 A93-53574 Finite element analysis of natural vibrations of an Unsteady aerodynamic characteristics of three aeroplane with asymmetric variable wing geometry rectangular wings of different aspect ratios p1218 A93-53776 P1180 A93-53575 AEROSPACE INDUSTRY Aerodynamic characteristics of the HL-20 International aerospace STI p 1227 A93-53826 p 1181 A93-53736 AEROSPACE PLANES Some measurements of stall in an axial impeller Analysis of a turning point problem in flight trajectory ABLATION [ISABE 93-7008] p 1183 A93-53984 optimization p 1210 A93-52885 Preparation and characterization of continuous fiber Design of high-load aviation turbomachines using HL-20 operations and support requirements for the reinforced zirconium diboride matrix composites for a modern 3D computational methods Personnel Launch System mission p 1210 A93-53745 leading edge material p1211 A93-53445 [ISABE 93-7032] p1196 A93-54008 Development study on Air Turbo Ramjet engine for a ACCELERATORS Starting characteristics of scramjet inlets future space plane Research and development of a turbo-accelerator for [ISABE 93-7105] p 1203 A93-54081 [ISABE 93-7016] p1195 A93-53992 super/hypersonic transport Off-design performance of scramjet nozzles Complementary role of ground testing, flight testing, and [ISABE 93-70661 p 1200 A93-54042 [ISABE 93-7108] p 1203 A93-54084 computations in aerospace plane propulsion ACOUSTIC PROPAGATION Aerodynamics of turbine blades with trailing-edge development The acoustics of axial compressors damage - Measurements and computations [ISABE 93-7034] p1197 A93-54010 [ISABE 93-7130] p1189 A93-54105 IONERA. TP NO. 1993-102] p 1226 A93-53615 Avionic systems in support of covert helicopter Effect of film cooling/regenerative cooling on scramjet Acoustic-wave propagation in ducts and free-field operations p 1193 A93-54294 engine performances radiation [ISABE 93-7036] p1197 A93-54012 AERODYNAMIC COEFFICIENTS [ONERA, TP NO. 1993-103] p 1226 A93-53616 Flight update of aerodynamic math model AEROTHERMODYNAMICS ACTIVE CONTROL [AIAA PAPER 93-3596] p 1224 A93-52687 Aerodynamic heating environment definition/thermal protection system selection for the HL-20 Linear quadratic tracking problems in Hilbert space - AERODYNAMIC CONFIGURATIONS p1181 A93-53739 Application to optimal active noise suppression Three-dimensional Navier-Stokes/full-potential coupled p 1224 A93-52763 analysis for viscous transonic flow p1178 A93-53218 HL-20 computational fluid dynamics analysis p1181 A93-53740 Active aerodynamic control of wake-airfoil interaction Analysis of spatial motion dynamics of a helicopter for Studies on coolant problems in aeronautical turbine noise - Experiment p 1225 A93-53206 various models of the induced velocity field cascades Review of stall, surge and active control in axial p1191 A93-53721 [ISABE 93-7074] p 1220 A93-54050 compressors AERODYNAMIC DRAG AFTERBODIES [ISABE 93-7011] p1184 A93-53987 The reduction of skin friction by riblets under the Optimization of afterbodies and engine nozzle by using influence of an adverse pressure gradient Periodic chemical energy release for active combustion CFD methods p 1218 A93-53810 control [ISABE 93-7098] p1187 A93-54074 [ ISABE 93-7043] p 1198 A93-54019 Reynolds number dependence of the drag coefficient AFTERBURNING Active control of vortex breakdown by a spinning wave for laminar flow through fine-scale photoetched screens Low-frequency combustion oscillations in a model generator p 1218 A93-53815 afterburner p 1193 A93-53702 [ISABE 93-7045] p 1219 A93-54021 AERODYNAMIC FORCES A study on 3-D velocity distribution of isothermal flows ACTUATORS An aerodynamic model for the longitudinal motion of behind an afterburner flame stabilizer Analysis of unstarted supersonic flutter in cascade by flight training devices p 1207 A93-54278 [ISABE 93-7039] p1197 A93-54015 semiactuator disk theory p1181 A93-53841 AERODYNAMIC HEAT TRANSFER The design and development of an afterburner Harmonic oscillation in FBW system Determination of heat transfer to flow in a duct with a [ISABE 93-7041 ] p1198 A93-54017 p 1206 A93-53877 pseudodiscontinuity p 1179 A93-53365 AIR BREATHING ENGINES Periodic chemical energy release for active combustion AERODYNAMIC HEATING High temperature heat exchangers for gas turbines and control A procedure for the thermal and strength testing of future hypersonic air breathing propulsion [ISABE 93-7043] p 1198 A93-54019 radiotransparent shells p 1209 A93-52976 [ONERA, TP NO. 1993-75] p 1218 A93-53596

A-1 AIR COOLING SUBJECTINDEX

ISABE - International Symposium on Air Breathing AIRCRAFT CONSTRUCTION MATERIALS Study of a pulse ramjet based on twin valveless Engines. 11th, Tokyo, Japan, Sept. 20-24, 1993, Overview of NASA's advanced high temperature engine combustors coupled to operate in antiphase Proceedings. Vols. 1 & 2 materials technology program p 1212 A93-53453 [ISABE 93-7038] p1197 A93-54014 [ISBN 1-56347-071-3] p1194 A93-53976 Case studies - Applications of laser systems for cutting Thermal fatigue life assessment of a convection-cooled Japan's research and development program for and welding aerospace parts p 1217 A93-53498 gas turbine blade airbreathing engine technologies Material requirements for the High Speed Civil [ISABE 93-7062] p1199 A93-54038 [ISABE 93-7005J p1194 A93-53981 Transport Variable cycle engine concept Development study on Air Turbo Ramjet engine for a [ISABE 93-7067] p 1200 A93-54043 (ISABE 93-7065] p 1200 A93-54041 future space plane Research and development of high pressure compressor AIRCRAFT CONTROL [ISABE 93-7016) p1195 A93-53992 for SST and HST engine Methodology for integration of digital control loaders in Design and testing methods of high performance [ISABE 93-7068] p 1186 A93-54044 aircraft simulators combustors for airbreathing engines Test results of the hydrogen fueled model combustor [AIAA PAPER 93-3551] p 1207 A93-52655 (ISABE 93-7024] p1196 A93-54000 for the air turbo ramjet engine Thermal design and analysis of an exhaust diffuser unit Hybrid complex of the aircraft intellectuafeed control [ISABE 93-7082] p 1201 A93-54058 in a ceramic composite systems simulation at the stage of their research New developments with the V2500 engine [ISABE 93-7060] p 1220 A93-54036 projecting [ISABE 93-7085] p 1202 A93-54061 High density strained hydrocarbon fuels for air breathing [AIM PAPER 93-3559] p 1222 A93-52660 Performance and configuration anaJysis of jet-engine propulsion Stabilization of the dynamic characteristics of the off-design behavior [ISABE 93-7081 ] p 1213 A93-54057 two-channel automatic control system of aircraft [ISABE 93-7087] p 1202 A93-54063 AIR COOLING P1205 A93-52941 Developments towards versatility in digital engine control Measurements and computational analysis of heat Solution of the boundary value problem in flight dynamics units transfer and flow in a simulated turbine blade internal by the opposite motion method p 1206 A93-52944 [ISABE 93-7088] p 1202 A93-54064 cooling passage A vision-based method for autonomous landing Effect of nozzle design on the performance of a highly [AIAA PAPER 93-1797] p 1218 A93-53585 p1190 A93-53172 loaded turbine stage AIR FLOW A reactive approach for distributed air traffic control [ISABE 93-7096] p 1203 A93-54072 Tandem transverse hydrogen gas injection into a [ONERA, TP NO. 1993-83] p1190 A93-53603 Measurement and prediction of flow in a gas turbine supersonic airflow AIRCRAFT DESIGN engine exhaust plume [ISABE 93-7069] p 1201 A93-54045 Flight research simulation takes off [ISABE 93-7113] p 1204 A93-54088 AIR INTAKES p1192 A93-53769 Various applications of robots in aircraft engine Effect of boundary layer suction on the thrust and Engineering simulators enhance 777 development overhaul aerodynamic efficiency of a hypersonic flight vehicle p1192 A93-53771 [ISABE 93-7129] p1175 A93-54104 P1176 A93-52959 Optimization of afterbodies and engine nozzle by using Aerodynamics of turbine blades with trailing-edge On the numerical simulation of the two-dimensional flow CFD methods damage - Measurements and computations field around a hypersonic air-intake-compressibility [ISABE 93-7098] p1187 A93-54074 [ISABE 93-7130] p1189 A93-54105 effects AIRCRAFT ENGINES Development of a real time dynamic engine simulation [ISABE 93-7100] p1187 A93-54076 Estimation of the parameters of the electrodynamic model of a turbo fan engine Wind tunnel tests of the model of intake-airframe system engine-exhaust jet p1193 A93-52965 [ISABE 93-7132] p 1205 A93-54107 integration Clean melting and the removal of defects from The low frequency aeroacoustics of buried nozzle [ISABE 93-7101] p1192 A93-54077 aero-engine materials p 1217 A93-53503 systems p1205 A93-54244 Design of air intakes and nozzles for transonic rotational Ongoing challenges for titanium alloy cleanliness Development of MIL-H-53119, -54 C to 175 C flows improvement in aircraft engine disk materials high-temperature nonflammable hydraulic fluid for Air [ISABE 93-7102] p1187 A93-54078 p 1212 A93-53506 Force systems p 1214 A93-54250 A study on Mach 3 two-dimensional mixed compression The application of diffusion bonding in the manufacture AIRCRAFT FUELS air-intakes of aeroengine components p 1217 A93-53514 Viscosity of aviation fuel components - Aromatic [ISABE 93-7106] p1188 A93-54082 Selection of a method for protecting aircraft gas turbine hydrocarbons (alkyl benzenes) p 1211 A93-52961 A Eulerian/Lagrangian modelling to calculate the engines against damage by foreign objects (Mathematical A study of surge control by using pulse cut-off for dual evolution of a water droplets spray models) p1193 A93-53554 spool turbo-jet engine p 1194 A93-53862 [ISABE 93-7121] p 1221 A93-54096 ISABE • International Symposium on Air Breathing AIRCRAFT GUIDANCE AIR LAW Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, A primary flight display for four-dimensional guidance Air carriers' liability for passenger injury or death - The Proceedings. Vols. 1 & 2 and navigation influence of tunnel size and level of Japanese Initiative and Response to the recent EC [ISBN 1-56347-071-3] p1194 A93-53976 additional information on pilot performance and control Consultation Paper p 1226 A93-52930 Research and development of aircraft engine in Japan behaviour Air transport and the environment - Regulating aircraft - Historical review [AIAA PAPER 93-3570] p 1208 A93-52668 noise p1226 A93-52931 [ISABE 93-7000] p 1227 A93-53977 Passive range estimation for rotorcraft low-altitude Flight safety in Europe p 1227 A93-53726 The challenge of IHPTET — Integrated High flight p1190 A93-52881 AIR NAVIGATION Performance Turbine Engine Technology AIRCRAFT INDUSTRY A primary flight display for four-dimensional guidance [ ISABE 93-7001 ] p 1194 A93-53978 Propulsion technology challenges for turn-of-the-century and navigation influence of tunnel size and level of Design and technology for engine manufacture — for commercial aircraft additional information on pilot performance and control Rolls-Royce aerospace business (ISABE 93-7003] p1194 A93-53980 behaviour [ISABE 93-7002] p1194 A93-53979 AIRCRAFT INSTRUMENTS [AIAA PAPER 93-3570] p 1208 A93-52668 Propulsion technology challenges for turn-of-the-century Instrumentation and telemetry systems for free-flight The development of SIMONA - A simulator facility for commercial aircraft drop model testing p 1209 A93-52754 advanced research into simulation techniques, motion [ISABE 93-7003] p1194 A93-53980 CRAASH - A coordinated collision avoidance system system control and navigation systems technologies Japan's research and development program for [ONERA, TP NO. 1993-84] p1191 A93-53604 [AIAA PAPER 93-3574] p 1208 A93-52670 airbreathing engine technologies AIRCRAFT LANDING AIR TRAFFIC [ISABE 93-7005] p1194 A93-53981 Fault tolerant navigation for aircraft landing Flight safety in Europe p 1227 A93-53726 Mach 5 turboramjet requirements and design p1191 A93-53866 AIR TRAFFIC CONTROL approach Pseudo Aircraft Systems - A multi-aircraft simulation [ISABE 93-7015] p1194 A93-53991 Longitudinal closed-loop pilot/vehicle analysis of DFBW system for air traffic control research Conceptual design study on combined-cycle engine for aircraft during approach and landing [AIAA PAPER 93-3585] p 1209 A93-52679 hypersonic transport p 1206 A93-54277 A reactive approach for distributed air traffic control [ISABE 93-7018] p1195 A93-53994 AIRCRAFT MAINTENANCE [ONERA, TP NO. 1993-83) p1190 A93-53603 Energy management — aircraft propulsion system Wet layup materials for repair of bismaleimide CRAASH - A coordinated collision avoidance system performance composites p 1212 A93-53451 [ONERA, TP NO. 1993-84] p 1191 A93-53604 [ISABE 93-7019] p1195 A93-53995 Repair materials and processes for the MD-11 AIR TRANSPORTATION An ultra low NO(x) pilot combustor for staged low NO(x) Composite Tailcone p 1216 A93-53452 Air transport and the environment - Regulating aircraft combustion Neural network fault diagnosis of a turbofan engine noise p 1226 A93-52931 [ISABE 93-7020] p1195 A93-53996 [ISABE 93-7091] p 1203 A93-54067 On definition and use of systems engineering processes, Low NO(x) combustor development using aerodynamic Various applications of robots in aircraft engine methods and tools p 1225 A93-53642 staging overhaul AIRCRAFT ACCIDENT INVESTIGATION [ISABE 93-7021] p1195 A93-53997 [ISABE 93-7129] p1175 A93-54104 Operating helicopters in a demanding environment - The prediction of thermal NO(x) in gas turbine Aerodynamics of turbine blades with trailing-edge Mountain flying/high evaluations p1190 A93-54289 exhausts damage - Measurements and computations AIRCRAFT ACCIDENTS [ISABE 93-7022] p1195 A93-53998 [ISABE 93-7130] p1189 A93-54105 Air carriers' liability for passenger injury or death - The Emission characteristics of a model gas turbine AIRCRAFT MANEUVERS Japanese Initiative and Response to the recent EC combustor at practical conditions A dual-Euler method for solving all-attitude angles of Consultation Paper p 1226 A93-52930 [ISABE 93-7023] p1196 A93-53999 AIRCRAFT COMPARTMENTS Two and three-dimensional prediffuser combustor the aircraft (AIAA PAPER 93-3589] p 1223 A93-52682 Interconversion of two kinds of methods for cabin studies with air-water mixture leakage test p1192 A93-53874 [ISABE 93-7025] p 1213 A93-54001 Non-linear flight dynamics AIRCRAFT CONFIGURATIONS Blowout of turbulent disc/pilot stabilized jet diffusion [ONERA, TP NO. 1993-109] p 1206 A93-53621 Low aspect ratio wing code validation experiment flames Analysis of spatial motion dynamics of a helicopter for p1176 A93-53202 [ISABE 93-7026] p 1213 A93-54002 various models of the induced velocity field Space marching calculations about hypersonic Design of high-load aviation turbomachines using p1191 A93-53721 configurations using a solution-adaptive mesh algorithm modern 3D computational methods A study of aircraft global dynamic stability in rapid rolling p1177 A93-53212 [ISABE 93-7032] p1196 A93-54008 maneuver p 1206 A93-53869

A-2 SUBJECT INDEX BOUNDARY LAYER FLOW

AIRCRAFT MODELS AIRSPEED AXIAL FLOW TURBINES A method for the spectral-time identification of the Analysis of spatial motion dynamics of a helicopter for 3D and 2.5D viscous flow computations for axial flow longitudinal and lateral motions of an aircraft various models of the induced velocity field turbine blades p 1205 A93-52942 P1191 A93-53721 [ISABE 93-7093] p1186 A93-54069 Analysis of spatial motion dynamics of a helicopter for ALGORITHMS various models of the induced velocity field A parameter optimization approach to controller P1191 A93-53721 partitioning for integrated flight/propulsion control B Finite element analysis of natural vibrations of an application p 1206 A93-54268 aeroplane with asymmetric variable wing geometry ALKYL COMPOUNDS BACKWARD FACING STEPS p 1218 A93-53776 Viscosity of aviation fuel components - Aromatic Numerical study of supersonic flow over a backward AIRCRAFT NOISE hydrocarbons (alkyl benzenes) p1211 A93-52961 step with transverse injection p 1182 A93-53853 Air transport and the environment - Regulating aircraft ALOUETTE HELICOPTERS BENDING MOMENTS noise p 1226 A93-52931 The development of a new air filtration system for the A nonlinear finite element of an arbitrary beam Experimental investigation into the mechanism of Alouette III helicopter p 1215 A93-52939 discrete frequency noise (DFN) generation from a NACA [ISABE 93-7048] p1199 A93-54024 The effects of end-bend regulations of compressor blade 0012 blade p 1225 A93-53194 ALPS MOUNTAINS (EUROPE) on the outlet flow field Active aerodynamic control of wake-airfoil interaction Operating helicopters in a demanding environment - (ISABE 93-7033] p1185 A93-54009 noise - Experiment p 1225 A93-53206 Mountain flying/high evaluations p1190 A93-54289 BINARY MIXTURES Engine technology challenges for a 21st Century ALUMINIDES Two and three-dimensional prediffuser combustor High-Speed Civil Transport Friction surfacing and linear friction welding studies with air-water mixture [ISABE 93-70641 p 1200 A93-54040 p 1217 A93-53499 (ISABE 93-7025] p 1213 A93-54001 AIRCRAFT PARTS ALUMINUM-LITHIUM ALLOYS Ongoing challenges for titanium alloy cleanliness Evaluation of water-borne adhesive bonding primers for BISMALEIMIDE improvement in aircraft engine disk materials use on the advanced aircraft material aluminum-lithium The properties of newly developed highly damage tolerant and easy handleable carbon fiber/modified p 1212 A93-53506 p 1211 A93-53420 Durability properties for adhesively bonded structural Friction surfacing and linear friction welding bismaleimide prepreg system p 1212 A93-53448 aerospace applications p 1217 A93-53515 p 1217 A93-53499 Wet layup materials for repair of bismaleimide AIRCRAFT PERFORMANCE ANALOG SIMULATION composites p 1212 A93-53451 Instrumentation and telemetry systems for free-flight Calculation of the position of the flow separation line BLADE TIPS drop model testing p 1209 A93-52754 in an analog model of flow past a body Numerical analysis of flow within cascade with tip AIRCRAFT PILOTS p1176 A93-52958 clearance p 1176 A93-53192 Longitudinal closed-loop pilot/vehicle analysis of DFBW ANNULAR FLOW Tip clearance effects on the flow field of an axial turbine aircraft during approach and landing The low frequency aeroacoustics of buried nozzle rotor blade cascade p 1206 A93-54277 systems P 1205 A93-54244 [ISABE 93-7057] p1185 A93-54033 AIRCRAFT STABILITY ARCTIC REGIONS Effects of wake interaction of two turbine cascades on Initial development of a research flight simulator Arctic environment - Helicopter operations in cold secondary/tip-leakage flows and losses software climates P 1189 A93-54288 [ISABE 93-7058] p1185 A93-54034 [AIAA PAPER 93-3590] p 1223 A93-52683 AROMATIC COMPOUNDS SLOWDOWN WIND TUNNELS Stabilization of the dynamic characteristics of the Viscosity of aviation fuel components - Aromatic Observations of liquid jets injected into a highly two-channel automatic control system of aircraft hydrocarbons (alkyl benzenes) p 1211 A93-52961 accelerated supersonic boundary layer p 1205 A93-52941 ASPECT RATIO P1177 A93-53214 Identification of the phase characteristics and Unsteady aerodynamic characteristics of three BLOWING rectangular wings of different aspect ratios wind-induced perturbations of an aircraft from flight test Boundary layer and pressure measurements on a p1180 A93-53575 results p 1206 A93-52943 cylinder with unsteady circulation control A study of aircraft global dynamic stability in rapid rolling ASYMPTOTIC METHODS p 1177 A93-53207 maneuver p 1206 A93-53869 Analysis of a turning point problem in flight trajectory BLUNT BODIES AIRCRAFT STRUCTURES optimization p 1210 A93-52885 Effective treatment of the singular line boundary problem Nonlinear deformation mechanics of multilayer Stability analysis through bifurcation theory. I, II for three-dimensional grids p 1177 A93-53204 transparency elements - Some calculation results — for [ ONER A, TP NO. 1993-108] p 1225 A93-53620 aircraft portholes p1191 A93-52937 ATMOSPHERIC ENTRY Application of the small parameter method to the A nonlinear finite element of an arbitrary beam Six-degree-of-freedom guidance and control-entry problem of three-dimensional flow of a viscous gas past p1215 A93-52939 analysis of the HL-20 p 1210 A93-53737 bodies p 1178 A93-53314 A study of optical distortions arising in radiation ATMOSPHERIC OPTICS Comparison of gasdynamic models in hypersonic flow transmission through cavities with gas flow around them A study of optical distortions arising in radiation p1179 A93-53315 p1225 A93-52945 transmission through cavities with gas flow around them BOEING AIRCRAFT Design and fabrication of panels with cutouts p 1225 A93-52945 Engineering simulators enhance 777 development p1215 A93-52973 ATMOSPHERIC TEMPERATURE p1192 A93-53771 A procedure for the thermal and strength testing of Arctic environment - Helicopter operations in cold BORIDES radiotransparent shells p 1209 A93-52976 climates p 1189 A93-54288 Preparation and characterization of continuous fiber A finite element for modeling skins of composite ATMOSPHERIC TURBULENCE reinforced zirconium diboride matrix composites for a materials p 1215 A93-52979 Identification of the phase characteristics and leading edge material p 1211 A93-53445 Evaluation of water-borne adhesive bonding primers for wind-induced perturbations of an aircraft from flight test BORON-EPOXY COMPOSITES use on the advanced aircraft material aluminum-lithium results P 1206 A93-52943 Reinforcement of the F-111 wing pivot fitting with a p 1211 A93-53420 ATTITUDE (INCLINATION) boron/epoxy doubler system - Materials engineering 3-D braided preforms; cost to manufacture: A dual-Euler method for solving all-attitude angles of aspects p1214 A93-54241 the aircraft Magnaweave. I - Identifying cost factors BOUNDARY CONDITIONS [AIAA PAPER 93-3589] p 1223 A93-52682 p 1226 A93-53423 Boundary conditions for unsteady supersonic inlet Structural applications of Avimid K3B LDF thermoplastic AUSTENITIC STAINLESS STEELS analyses Friction surfacing and linear friction welding composites — for advanced aircraft [ISABE 93-7104] p1187 A93-54080 p 1216 A93-53429 p1217 A93-53499 BOUNDARY ELEMENT METHOD AIRCRAFT WAKES AUTOMATIC FLIGHT CONTROL A dynamic stiffness/boundary element method for the Active aerodynamic control of wake-airfoil interaction Stabilization of the dynamic characteristics of the prediction of interior noise levels p 1226 A93-53817 noise - Experiment p 1225 A93-53206 two-channel automatic control system of aircraft Construction of wakes in the discrete vortex method p 1205 A93-52941 Numerical analysis of the flow through a centrifugal P1179 A93-53333 impeller by vortex distribution model of a boundary layer. AUTOMATIC PILOTS I - Theoretical analysis p 1182 A93-53843 AIRFOIL OSCILLATIONS Stabilization of the dynamic characteristics of the A preliminary investigation of the control of separated two-channel automatic control system of aircraft BOUNDARY LAYER CONTROL flow by means of excitation p 1182 A93-53859 p 1205 A93-52941 Boundary conditions for unsteady supersonic inlet analyses Forcing function modeling for flow induced vibration AUTONOMOUS NAVIGATION [ISABE 93-7104] p1187 A93-54080 [ISABE 93-7027] p1196 A93-54003 A vision-based method for autonomous landing The unsteady flow past a supersonic splitter plate p1190 A93-53172 BOUNDARY LAYER EQUATIONS Calculation ol a compressible three-dimensional [ISABE 93-7047] p1185 A93-54023 AVIATION METEOROLOGY boundary layer on a swept wing p 1179 A93-53551 AIRFOIL PROFILES Visual weather simulation using meteorological Active aerodynamic control of wake-airfoil interaction BOUNDARY LAYER FLOW databases Non-self-similarity of a boundary layer flow of a noise - Experiment p 1225 A93-53206 [AIAA PAPER 93-3566] p 1207 A93-52665 AIRFOILS high-temperature gas in a Laval nozzle Zonal-local solution method for the turbulent AVIONICS p1176 A93-52946 On definition and use of systems engineering processes, Navier-Stokes equations p1177 A93-53205 Effect of boundary layer suction on the thrust and methods and tools p 1225 A93-53642 Impingement cooling with film coolant extraction in the aerodynamic efficiency of a hypersonic flight vehicle airfoil leading edge regions Integrated fire control simulation systems p 1176 A93-52959 [ISABE 93-7078] p 1220 A93-54054 p1192 A93-53876 Boundary layer and pressure measurements on a AIRPORT PLANNING Avionic systems in support of covert helicopter cylinder with unsteady circulation control Stumbling blocks for airport construction in the new operations p 1193 A93-54294 p1177 A93-53207 German federal states p 1227 A93-53727 AXIAL FLOW Numerical analysis of the flow through a centrifugal AIRPORTS Some measurements of stall in an axial impeller impeller by vortex distribution model of a boundary layer. Red-hot simulation p 1209 A93-53774 [ISABE 93-7008] p 1183 A93-53984 I - Theoretical analysis p 1182 A93-53843

A-3 BOUNDARY LAYER SEPARATION SUBJECT INDEX

Study on unstart and its propagation along modules due CENTRIFUGAL COMPRESSORS CRAASH - A coordinated collision avoidance system to compound choking and/or fluctuations in combustor The flow lag angle in the rotor of a centrifugal compressor [ONERA, TP NO. 1993-84] p 1191 A93-53604 of scramjet engines with allowance for viscosity effects COMBINED CYCLE POWER GENERATION [ISABE 93-7052] p1199 A93-54028 P1179 A93-53555 Studies on methane-fuel ram combustor for HST BOUNDARY LAYER SEPARATION Velocity fluctuation based on the difference in the flow combined cycle engine Skin-friction topology over a surface mounted pattern in the channels of a centrifugal impeller [ISABE 93-7080) p 1201 A93-54056 semi-ellipsoidal wing at incidence p 1178 A93-53216 P1182 A93-53842 COMBUSTIBLE FLOW Separation phenomenon in a hypersonic flow with strong Numerical analysis of the flow through a centrifugal A finite element code for gas turbine combustor flow wall cooling - Subcritical regime p 1189 A93-54266 impeller by vortex distribution model of a boundary layer. with Stretched Laminar Flamelet modelling BOUNDARY LAYER TRANSITION I - Theoretical analysis p 1182 A93-53843 [ISABE 93-7127] p 1204 A93-54102 Moving wall effects in transverse subsonic flow past a Transonic discharge flows around diffuser vanes from COMBUSTION CHAMBERS rotating cylinder p 1179 A93-53573 An ultra low NO(x) pilot combustor for staged low NO(x) a centrifugal impeller Experimental investigation of boundary layer transition [ISABE 93-7053] p1185 A93-54029 combustion on a flat plate with C4 leading edge [ISABE 93-7020] p1195 A93-53996 Correlations for flow property variation at outlet of a [ISABE 93-7123] p 1222 A93-54098 Low NO(x) combustor development using aerodynamic centrifugal impeller BOUNDARY VALUE PROBLEMS staging Solution of the boundary value problem in flight dynamics [ISABE 93-7054] p1185 A93-54030 [ ISABE 93-7021 ] p 1195 A93-53997 by the opposite motion method p 1206 A93-52944 CENTRIFUGES Emission characteristics of a model gas turbine Effective treatment of the singular line boundary problem Semi-full-scale dynamic simulation complex on the basis combustor at practical conditions for three-dimensional grids p 1177 A93-53204 of centrifuge [ISABE 93-7023] p1196 A93-53999 BRAIDED COMPOSITES [AIM PAPER 93-3577] p 1208 A93-52673 Design and testing methods of high performance 3-D braided preforms; cost to manufacture: CERAMIC MATRIX COMPOSITES combustors for airbreathing engines Magnaweave. I - Identifying cost factors Preparation and characterization of continuous fiber [ISABE 93-7024] p1196 A93-54000 p1226 A93-53423 reinforced zirconium diboride matrix composites for a Two and three-dimensional prediffuser combustor BRANCHING (MATHEMATICS) leading edge material p 1211 A93-53445 studies with air-water mixture Stability analysis through bifurcation theory. I, II Evaluation of 2D ceramic matrix composites in [ISABE 93-7025] p 1213 A93-54001 [ONERA, TP NO. 1993-108] p 1225 A93-53620 aeroconvective environments p 1212 A93-53459 Study of a pulse ramjet based on twin valveless BURAN SPACE SHUTTLE Corrosion of ceramic matrix composites combustors coupled to operate in antiphase Comparison of gasdynamic models in hypersonic flow [ONERA, TP NO. 1993-82] p 1213 A93-53602 [ISABE 93-7038] p1197 A93-54014 P1179 A93-53315 Thermal design and analysis of an exhaust diffuser unit Nozzle effects on linear stability behaviour of BYPASS RATIO in a ceramic composite combustors Japan's research and development program for [ISABE 93-7060] p 1220 A93-54036 [ISABE 93-7044] p1198 A93-54020 airbreathing engine technologies Material requirements for the High Speed Civil Ignition and combustion performance of a scramjet Transport [ISABE 93-7005] p1194 A93-53981 combustor with a fuel injection strut [ISABE 93-7067] p 1200 A93-54043 [ISABE 93-7050] p1199 A93-54026 CERAMICS Overview of NASA's advanced high temperature engine Study on unstart and its propagation along modules due materials technology program p 1212 A93-53453 to compound choking and/or fluctuations in combustor CHANNEL FLOW of scramjet engines CANOPIES [ISABE 93-7052] p1199 A93-54028 The fluid physics of parachute inflation Effect of rotation on heat transfer and hydraulic The combustion performance of methane-fueled ram P1189 A93-54347 resistance in the radial cooling channels of turbine rotor combustor CARBON FIBER REINFORCED PLASTICS blades p1215 A93-52950 Velocity fluctuation based on the difference in the flow [ISABE 93-7079] p 1201 A93-54055 The properties of newly developed highly damage Studies on methane-fuel ram combustor for HST tolerant and easy handleable carbon fiber/modified pattern in the channels of a centrifugal impeller combined cycle engine bismaleimide prepreg system p 1212 A93-53448 P1182 A93-53842 CHEMICAL COMPOSITION [ISABE 93-7080] p 1201 A93-54056 Repair materials and processes for the MD-11 The chemistry of Saudi Arabian sand - A deposition Test results ol the hydrogen fueled model combustor Composite Tailcone p 1216 A93-53452 problem on helicopter turbine airfoils for the air turbo ramjet engine CASCADE FLOW P1216 A93-53468 (ISABE 93-7082] p 1201 A93-54058 Estimation of the change of axial-flow compressor CHLOROETHYLENE Finite-rate H2/air combustion effects in CRJ for characteristics during long-term service Development of MIL-H-53119, -54 C to 175 C hypersonic launchers p1193 A93-52949 high-temperature nonflammable hydraulic fluid for Air [ISABE 93-7084] p 1202 A93-54060 Numerical analysis of flow within cascade with tip Force systems p 1214 A93-54250 COMBUSTION CHEMISTRY clearance p 1176 A93-53192 CHOKED FLOW High density strained hydrocarbon fuels for air breathing Multigrid Navier-Stokes calculations for Study on unstart and its propagation along modules due propulsion three-dimensional cascades p 1177 A93-53209 to compound choking and/or fluctuations in combustor [ISABE 93-7061] p 1213 A93-54057 of scramjet engines Three-dimensional viscous flow analysis of compressor COMBUSTION CONTROL cascade channels p 1181 A93-53837 [ISABE 93-7052] p1199 A93-54028 Periodic chemical energy release for active combustion CHOKES (RESTRICTIONS) Analysis of unstarted supersonic flutter in cascade by control semiactuator disk theory p 1181 A93-53841 Low-frequency combustion oscillations in a model [ISABE 93-7043] p1198 A93-54019 afterburner p 1193 A93-53702 Numerical analysis of the flow through a centrifugal COMBUSTION EFFICIENCY impeller by vortex distribution model of a boundary layer. CIRCULAR CYLINDERS Boundary layer and pressure measurements on a The design and development of an afterburner I - Theoretical analysis p 1182 A93-53843 cylinder with unsteady circulation control [ISABE 93-7041] p1198 A93-54017 A 2-D compressible N-S simulation of starting- and p 1177 A93-53207 Ignition and combustion performance of a scramjet stalling-flows in a compressor cascades system CIRCULATION CONTROL AIRFOILS combustor with a fuel injection strut [ISABE 93-7006] p1183 A93-53982 Boundary layer and pressure measurements on a (ISABE 93-7050] p1199 A93-54026 Numerical study on inception of stall cells in rotating cylinder with unsteady circulation control The combustion performance of methane-fueled ram stall P1177 A93-53207 combustor (ISABE 93-70071 p 1183 A93-53983 CIVIL AVIATION I ISABE 93-7079) p 1201 A93-54055 Some measurements of stall in an axial impeller Overview of NASA's advanced high temperature engine COMBUSTION PHYSICS [ISABE 93-7008] p1183 A93-53984 materials technology program p 1212 A93-53453 High density strained hydrocarbon fuels for air breathing Review of stall, surge and active control in axial Propulsion technology challenges for turn-of-the-century propulsion compressors commercial aircraft [ISABE 93-7081] p 1213 A93-54057 [ ISABE 93-70111 p1184 A93-53987 [ISABE 93-7003] p1194 A93-53980 COMBUSTION STABILITY Forcing function modeling for flow induced vibration Engine technology challenges for a 21st Century Low-frequency combustion oscillations in a model | ISABE 93-7027] p1196 A93-54003 High-Speed Civil Transport afterburner p1193 A93-53702 Performance improvement by forward-skewed blading [ISABE 93-7064] p 1200 A93-54040 Blowout of turbulent disc/pilot stabilized jet diffusion of axial fan moving blades Material requirements for the High Speed Civil flames [ISABE 93-7055] p1185 A93-54031 Transport [ISABE 93-7026] p 1213 A93-54002 Tip clearance effects on the flow field of an axial turbine [ISABE 93-7067] p 1200 A93-54043 Study of a pulse ramjet based on twin valveless CLEANLINESS rotor blade cascade combustors coupled to operate in antiphase Ongoing challenges for titanium alloy cleanliness [ISABE 93-7057] p1185 A93-54033 [ISABE 93-7038] p1197 A93-54014 improvement in aircraft engine disk materials Effects of wake interaction of two turbine cascades on p 1212 A93-53506 Nozzle effects on linear stability behaviour of secondary/tip-leakage flows and losses COANDA EFFECT combustors [ISABE 93-7044] p1198 A93-54020 | ISABE 93-7058] p1185 A93-54034 Boundary layer and pressure measurements on a Studies on coolant problems in aeronautical turbine cylinder with unsteady circulation control COMBUSTION TEMPERATURE cascades P1177 A93-53207 Initial results from the NASA Lewis wave rotor 11SASE 93-7074) p 1220 &93-54050 COCKPIT SIMULATORS experimerrt Navier-Stokes analysis of turbine flowfield and external An evaluation of software tools for the design and [ AIAA PAPER 93-2521 ] p 1193 A93-53589 heat transfer development of cockpit displays CARS temperature measurements in combustion I ISABE 93-7075] p1186 A93-54051 [AIAA PAPER 93-3593] p 1224 A93-52685 [ONERA, TP NO. 1993-78] p 1212 A93-53599 A comparative assessment of two present generation COLLISION AVOIDANCE COMBUSTION VIBRATION turbine analysis codes A reactive approach for distributed air traffic control Low-frequency combustion oscillations in a model [ISABE 93-7097] p 1203 A93-54073 [ONERA, TP NO. 1993-83] p1190 A93-53603 afterburner p1193 A93-53702

A-4 SUBJECT INDEX CONTROL SYSTEMS DESIGN

COMMERCIAL AIRCRAFT Recent advances in computational analysis of Identification of nonlinear mechanical systems using Propulsion technology challenges for turn-of-the-century hypersonic vehicles p 1179 A93-53364 combined state and parameter evaluation commercial aircraft HL-20 computational fluid dynamics analysis p 1224 A93-52732 [ISABE 93-7003] p1194 A93-53980 p1181 A93-53740 Case study of a low-reflectivity pulsating microburst • Europe's new windtunnel p 1210 A93-54275 Numerical analysis of a flat plate in a pitching motion. Numerical simulation of the Denver. 8 July 1989, storm COMPENSATORY TRACKING II - Effect on the flow of the position of the pivot, etc p 1222 A93-52898 Simulation motion effect on single axis compensatory P1181 A93-53798 Fast three-dimensional vortex method for unsteady wake tracking Study on surge and rotating stall in axial compressors. calculations p 1178 A93-53233 [AIAA PAPER 93-3579] p 1208 A93-52675 III - Numerical model for multiblade-row compressors Total quality management of forged products through COMPONENT RELIABILITY p1181 A93-53799 finite element simulation p 1217 A93-53493 Thermodynamic and neutral network computer The construction of nearly orthogonal multiblock grids A reactive approach for distributed air traffic control modelling of implanted component faults in a gas turbine for compressible flow simulation p 1219 A93-53847 [ONERA, TP NO. 1993-83] p1190 A93-53603 engine CFD for ramjet and scramjet powered vehicles [ISABE 93-7089] p 1202 A93-54065 [ISABE 93-7035] p1197 A93-54011 Flight research simulation takes off COMPOSITE MATERIALS Finite-rate H2/air combustion effects in CRJ for p1192 A93-53769 Design and fabrication of panels with cutouts hypersonic launchers Numerical simulation of ramjet and scramjet combustion p 1215 A93-52973 [ISABE 93-7084] p 1202 A93-54060 using two-dimensional Euler equations with finite rate An experimental study of reinforced panels of composite Aerodynamic inverse design and analysis for a full chemistry materials p 1215 A93-52975 engine [ISABE 93-7083) p 1202 A93-54059 A finite element for modeling skins of composite [ISABE 93-7086] p1186 A93-54062 Thermodynamic and neutral network computer materials p 1215 A93-52979 3D and 2.5D viscous flow computations for axial flow modelling of implanted component faults in a gas turbine COMPOSITE STRUCTURES turbine blades engine Design for cyclic loading endurance of composites [ISABE 93-7093) p1186 A93-54069 [ISABE 93-7089] p 1202 A93-54065 p 1216 A93-53395 A comparative assessment of two present generation Recent developments performed at ONERA for the Innovative bagging techniques on a composite P-51 turbine analysis codes simulation of 3D inviscid and viscous flows in Mustang replica p 1191 A93-53405 [ISABE 93-7097] p 1203 A93-54073 turbomachinery by the solution of Euler and Navier-Stokes Structural applications of Avimid K3B LDF thermoplastic Optimization of afterbodies and engine nozzle by using equations composites — for advanced aircraft CFD methods [ISABE 93-7094] p1186 A93-54070 p 1216 A93-53429 [ISABE 93-7098] p1187 A93-54074 On the numerical simulation of the two-dimensional flow COMPRESSIBLE BOUNDARY LAYER Characteristics of heat exchanger in field around a hypersonic air-intake-compressibility Calculation of a compressible three-dimensional supersonic/subsonic flows effects boundary layer on a swept wing p 1179 A93-53551 [ISABE 93-7119] p 1221 A93-54094 [ISABE 93-7100] p1187 A93-54076 COMPUTATIONAL GRIDS COMPRESSIBLE FLOW Numerical simulation of a two-dimensional supersonic Effective treatment of the singular line boundary problem Zonal-local solution method for the turbulent mixed-compression inlet Navier-Stokes equations p 1177 A93-53205 for three-dimensional grids p1177 A93-53204 [ISABE 93-7107] p1188 A93-54083 Study on surge and rotating stall in axial compressors. Space marching calculations about hypersonic A finite element code for gas turbine combustor flow Ill - Numerical model for multiblade-row compressors configurations using a solution-adaptive mesh algorithm p1177 A93-53212 with Stretched Laminar Flamelet modelling P1181 A93-53799 [ISABE 93-7127] p 1204 A93-54102 Kelvin-Helmholtz wave generation beneath hovercraft The construction of nearly orthogonal multiblock grids Skirts p 1219 A93-53820 for compressible flow simulation p 1219 A93-53847 Numerical simulation of gas turbine combustors with The construction of nearly orthogonal multiblock grids Studies on coolant problems in aeronautical turbine complex geometries for compressible flow simulation p 1219 A93-53847 cascades [ISABE 93-7128] p 1204 A93-54103 The streamline throughflow method of axial [ISABE 93-7074] p 1220 A93-54050 Development of a real time dynamic engine simulation turbomachinery flow analysis COMPUTER AIDED DESIGN model of a turbo fan engine [ISABE 93-7031] p 1184 A93-54007 Flight research simulation takes off [ISABE 93-7132] p 1205 A93-54107 On the numerical simulation of the two-dimensional flow p1192 A93-53769 Expert Systems for the simulation of turbofan engines field around a hypersonic air-intake-compressibility Design and technology for engine manufacture — for [ISABE 93-7133] p 1225 A93-54108 effects Rolls-Royce aerospace business CONES [ISABE 93-7100] p1187 A93-54076 [ISABE 93-7002] p1194 A93-53979 Study on flow field around slender diamond cone COMPRESSOR BLADES Aerodynamic inverse design and analysis for a full traveling at hypersonic speed p 1189 A93-54314 Estimation of the change of axial-flow compressor engine CONFERENCES characteristics during long-term service [ISABE 93-7086] p1186 A93-54062 AIAA Flight Simulation Technologies Conference, p1193 A93-52949 A parameter optimization approach to controller Monterey, CA, Aug. 9-11, 1993, Technical Papers Three-dimensional viscous flow analysis of compressor partitioning for integrated flight/propulsion control p 1207 A93-52651 cascade channels p1181 A93-53837 application p 1206 A93-54268 ISABE - International Symposium on Air Breathing Velocity fluctuation based on the difference in the flow COMPUTER GRAPHICS Engines, 11th, Tokyo, Japan, Sept. 20-24, 1993, pattern in the channels of a centrifugal impeller Transport delay compensation - An inexpensive Proceedings. Vols. 1 & 2 p1182 A93-53842 alternative to increasing image generator update rate [ISBN 1-56347-071-3] p1194 A93-53976 A 2-D compressible N-S simulation of starting- and [AIAA PAPER 93-3563] p 1223 A93-52663 Helicopter operations in severe environments; stalling-flows in a compressor cascades system A radar altitude and line of sight attachment Proceedings of the Conference, London, United Kingdom, [ISABE 93-7006] p1183 A93-53982 [AIAA PAPER 93-3587] p 1223 A93-52680 June 4, 1992 The leading edge vortex of a rotating stall cell Texture as a visual cueing element in computer image [ISBN 1-85768-045-6] p1175 A93-54287 [ISABE 93-7009] p1183 A93-53985 generation. I - Representation of the sea surface CONSERVATION EQUATIONS The effects of end-bend regulations of compressor blade [AIAA PAPER 93-3560] p 1214 A93-52695 Determination of heat transfer to flow in a duct with a on the outlet flow field COMPUTER NETWORKS pseudodiscontinuity p 1179 A93-53365 [ISABE 93-7033] p1185 A93-54009 Representation of vehicle location in networked CONSTRUCTION Transonic discharge flows around diffuser vanes from simulations Stumbling blocks for airport construction in the new a centrifugal impeller [AIAA PAPER 93-3582] p 1214 A93-52677 German federal states p 1227 A93-53727 [ISABE 93-7053] p1185 A93-54029 Networks extend simulation's reach CONTOURS Correlations for flow property variation at outlet of a p 1225 A93-53770 Separation phenomenon in a hypersonic flow with strong centrifugal impeller COMPUTER PROGRAMMING wall cooling - Subcritical regime p 1189 A93-54266 [ISABE 93-7054] p1185 A93-54030 Initial development of a research flight simulator CONTROL SIMULATION COMPRESSOR EFFICIENCY software Hybrid complex of the aircraft intellectualized control Performance improvement by forward-skewed bfading [AIAA PAPER 93-3590] p 1223 A93-52683 systems simulation at the stage of their research of axial fan moving blades Reusable code for helicopter simulation projecting [ISABE 93-7055] p1185 A93-54031 [AIAA PAPER 93-3594] p 1224 A93-52686 [AIAA PAPER 93-3559] p 1222 A93-52660 Research and development of high pressure compressor COMPUTER PROGRAMS The numerical errors in inverse simulation for SST and HST engine Enhancing real-time flight simulation execution by [AIAA PAPER 93-3588] p 1223 A93-52681 [ISABE 93-7068] p1186 A93-54044 intercepting Run-Time Library calls CONTROL SURFACES COMPUTATIONAL FLUID DYNAMICS [AIAA PAPER 93-3591 ] p 1224 A93-52684 Transition correlation in subsonic flow over a flat plate Progress towards understanding and predicting heat Reusable code for helicopter simulation p1178 A93-53231 transfer in the turbine gas path p 1215 A93-52751 [AIAA PAPER 93-3594] p 1224 A93-52686 CONTROL SYSTEMS DESIGN Upwind-biased, point-implicit relaxation strategies for Design for cyclic loading endurance of composites Methodology for integration of digital control loaders in hypersonic flowfield simulations on supercomputers p1216 A93-53395 aircraft simulators P1175 A93-52770 COMPUTER TECHNIQUES [AIAA PAPER 93-3551 ] p 1207 A93-52655 Zonal-local solution method for the turbulent Prismatic grid generation for three-dimensional complex Hybrid complex of the aircraft intellectualized control Navier-Stokes equations p 1177 A93-53205 geometries p 1178 A93-53217 systems simulation at the stage of their research Low-Reynolds-number k-epsilon model for unsteady COMPUTER VISION projecting turbulent boundary-layer flows p1177 A93-53208 Passive range estimation for rotorcraft low-altitude [AIAA PAPER 93-3559] p 1222 A93-52660 Multigrid Navier-Stokes calculations for flight p1190 A93-52881 Transport delay compensation - An inexpensive three-dimensional cascades p1177 A93-53209 A vision-based method for autonomous landing alternative to increasing image generator update rate Space marching calculations about hypersonic p1190 A93-53172 [AIAA PAPER 93-3563] p 1223 A93-52663 configurations using a solution-adaptive mesh algorithm COMPUTERIZED SIMULATION Solution of the boundary value problem in flight dynamics p1177 A93-53212 A dual-Euler method for solving all-attitude angles of by the opposite motion method p 1206 A93-52944 Prismatic grid generation for three-dimensional complex the aircraft A vision-based method for autonomous landing geometries p 1178 A93-53217 [AIAA PAPER 93-3589] p 1223 A93-52682 p1190 A93-53172

A-5 CONTROL THEORY SUBJECT INDEX

Developments towards versatility in digital engine control CRACK INITIATION DIGITAL COMPUTERS units Ongoing challenges for titanium alloy cleanliness Characterization of the faulted behavior of digital [ISABE 93-7088] p 1202 A93-54064 improvement in aircraft engine disk materials computers and fault tolerant systems Design of limit-tracking systems incorporating a turbotan p 1212 A93-53506 p 1224 A93-52762 engine with constant disturbances CROSS FLOW DIGITAL SYSTEMS [ISABE 93-7090] p 1203 A93-54066 Observations of liquid jets injected into a highly Developments towards versatility in digital engine control A parameter optimization approach to controller accelerated supersonic boundary layer units partitioning lor integrated flight/propulsion control p1177 A93-53214 [ISABE 93-7088] p 1202 A93-54064 application p 1206 A93-54268 Mixing of multiple jets with a confined subsonic DISKS (SHAPES) CONTROL THEORY crossflow p1189 A93-54324 Ongoing challenges for titanium alloy cleanliness Integrated fire control simulation systems improvement in aircraft engine disk materials CRYOGENIC COOLING p1192 A93-53876 p 1212 A93-53506 Compact heat exchanger fitted to engines of the inverted CONTROLLABILITY type DISPLAY DEVICES Effect of lift-to-drag ratio in pilot rating of the HL-20 Dynamic simulation fidelity improvement using transfer [ISABE 93-7120] p 1221 A93-54095 landing task p 1210 A93-53738 function state extrapolation CRYOGENIC WIND TUNNELS [AIAA PAPER 93-3552] p 1222 A93-52656 CONTROLLERS Wind Of Change p 1209 A93-53625 Transport delay compensation - An inexpensive A parameter optimization approach to controller Europe's new windtunnel p 1210 A93-54275 alternative to increasing image generator update rate partitioning for integrated flight/propulsion control CURVED BEAMS [AIAA PAPER 93-3563] p 1223 A93-52663 application p 1206 A93-54268 A nonlinear finite element of an arbitrary beam CONVECTIVE HEAT TRANSFER pt215 A93-52939 A primary flight display for four-dimensional guidance Progress towards understanding and predicting heat CYCLIC LOADS and navigation influence of tunnel size and level of transfer in the turbine gas path p 1215 A93-52751 Design for cyclic loading endurance of composites additional information on pilot performance and control Mathematical modeling of the three-dimensional p 1216 A93-53395 behaviour temperature fields of turbine blades CYLINDRICAL SHELLS [AIAA PAPER 93-3570] p 1208 A93-52668 p 1216 A93-53329 A dynamic stiffness/boundary element method for the Pilot evaluations of augmented flight simulator motion Evaluation of 2D ceramic matrix composites in prediction of interior noise levels p 1226 A93-53817 [AIAA PAPER 93-3580] p 1208 A93-52676 aeroconvective environments p 1212 A93-53459 An evaluation of software tools for the design and Thermal fatigue life assessment of a convection-cooled development of cockpit displays gas turbine blade [AIAA PAPER 93-3593] p 1224 A93-52685 (ISABE 93-7062] p1199 A93-54038 DISTRIBUTED PROCESSING DAMAGE Fluid dynamics and convective heat transfer in impinging A reactive approach for distributed air traffic control The properties of newly developed highly damage [ONERA, TP NO. 1993-83] p1190 A93-53603 jets through implementation of a high resolution liquid tolerant and easy handleable carbon fiber/modified crystal technique bismaleimide prepreg system p 1212 A93-53448 DRAG REDUCTION The reduction of skin friction by riblets under the [ISABE 93-7077] p 1220 A93-54053 A study of damage tolerance of the landing gear CONVERGENT NOZZLES structure p 1219 A93-53881 influence of an adverse pressure gradient p1218 A93-53810 Nozzle effects on linear stability behaviour of DAMAGE ASSESSMENT combustors Selection of a method for protecting aircraft gas turbine A preliminary investigation of the control of separated [ISABE 93-7044] p1198 A93-54020 engines against damage by foreign objects (Mathematical flow by means of excitation p 1182 A93-53859 CONVERGENT-DIVERGENT NOZZLES models) p1193 A93-53554 DUCTED FLOW Non-self-similarity of a boundary layer flow of a Aerodynamics of turbine blades with trailing-edge Determination of heat transfer to flow in a duct with a high-temperature gas in a Laval nozzle damage - Measurements and computations pseudodiscontinuity p 1179 A93-53365 p1176 A93-52946 [ISABE 93-7130] p1189 A93-54105 The low frequency aeroacoustics of buried nozzle COOLANTS DATA BASES systems p 1205 A93-54244 Studies on coolant problems in aeronautical turbine International aerospace STI p 1227 A93-53826 DUMP COMBUSTORS cascades DATA SIMULATION Periodic chemical energy release for active combustion [ISABE 93-7074] p 1220 A93-54050 A study of surge control by using pulse cut-off for dual control COOLING spool turbo-jet engine p 1194 A93-53862 [ISABE 93-7043] p1198 A93-54019 Separation phenomenon in a hypersonic flow with strong DEBONDING (MATERIALS) DURABILITY wall cooling - Subcritical regime p 1189 A93-54266 Durability properties for adhesively bonded structural 'No VOC' water-borne corrosion resistant primers for COOLING SYSTEMS aerospace applications p 1217 A93-53515 aerospace bonding applications p 1211 A93-53419 Effect of rotation on heat transfer and hydraulic DEEP WATER DUST resistance in the radial cooling channels of turbine rotor On hovercraft overwater heave stability Environmental effects of operations during Desert blades p 1215 A93-52950 p1219 A93-53819 Shield/Desert Storm p 1190 A93-54291 DEFECTS Measurements and computational analysis of heat DYNAMIC MODELS Clean melting and the removal of defects from transfer and flow in a simulated turbine blade internal Semi-full-scale dynamic simulation complex on the basis aero-engine materials p 1217 A93-53503 cooling passage DELAY of centrifuge [AIAA PAPER 93-1797] p 1218 A93-53585 [AIAA PAPER 93-3577] p 1208 A93-52673 Transport delay compensation - An inexpensive Application of functionally gradient materials to scramjet alternative to increasing image generator update rate Finite element analysis of natural vibrations of an engines [AIAA PAPER 93-3563] p 1223 A93-52663 aeroplane with asymmetric variable wing geometry [ISABE 93-7063] p 1200 A93-54039 DELTA WINGS p 1218 A93-53776 A new cooling system for ultra high temperature Pressure distribution measurement around hypersonic DYNAMIC STABILITY turbines delta winged semicone - Measurement by means of On hovercraft overwater heave stability [ISABE 93-7073] p 1201 A93-54049 magnet tape p1176 A93-53193 p 1219 A93-53819 COORDINATE TRANSFORMATIONS Numerical study of a delta planform with multiple jets A study of aircraft global dynamic stability in rapid rolling Representation of vehicle location in networked in ground effect maneuver p 1206 A93-53869 simulations [SAE PAPER 892283] p1176 A93-53200 [AIAA PAPER 93-3582] p 1214 A93-52677 Active control of vortex breakdown by a spinning wave CORNER FLOW generator A study of the stability of vortical structures in supersonic [ISABE 93-7045] p 1219 A93-54021 inlets DESERTS ECONOMIC ANALYSIS [ISABE 93-7103] p1187 A93-54079 Environmental effects of operations during Desert Internally coherent system of innovation - The case of CORROSION Shield/Desert Storm p 1190 A93-54291 flight simulation Corrosion of ceramic matrix composites DESIGN TO COST [AIAA PAPER 93-3548] p 1226 A93-52653 [ONERA, TP NO. 1993-82] p 1213 A93-53602 Axial flow compressors - Mechanical design trends ECONOMIC FACTORS [ISABE 93-7061] p1199 A93-54037 CORROSION PREVENTION Engine technology challenges for a 21st Century Variable cycle engine concept Development of MIL-H-53119. -54 C to 175 C High-Speed Civil Transport [ISABE 93-7065] p 1200 A93-54041 high-temperature nonflammable hydraulic fluid for Air [ISABE 93-7064] p 1200 A93-54040 DIFFERENCE EQUATIONS Force systems p 1214 A93-54250 ELASTOMERS An implicit difference scheme of Euler equation for Innovative bagging techniques on a composite P-51 CORROSION RESISTANCE unsteady transonic flow p 1182 A93-53852 Mustang replica p1191 A93-53405 'No VOC' water-borne corrosion resistant primers for DIFFERENTIAL EQUATIONS aerospace bonding applications p 1211 A93-53419 Non-linear flight dynamics ELECTRO-OPTICS CORROSION TESTS [ONERA, TP NO. 1993-109] p 1206 A93-53621 Sensors with centroid based common sensing scheme and their multiplexing — fiber optic sensors in aircraft and The chemistry of Saudi Arabian sand - A deposition DIFFUSERS problem on helicopter turbine airfoils Two and three-dimensional predilfuser combustor aircraft engine applications p 1192 A93-52994 p 1216 A93-53468 studies with air-water mixture ELECTRODYNAMICS COST ANALYSIS [ISABE 93-7025] p 1213 A93-54001 Estimation of the parameters of the electrodynamic 3-D braided preforms; cost to manufacture: DIFFUSION FLAMES system engine-exhaust jet p 1193 A93-52965 Magnaweave. I - Identifying cost factors Blowout of turbulent disc/pilot stabilized jet diffusion ELLIPSOIDS p 1226 A93-53423 flames Skin-friction topology over a surface mounted COST EFFECTIVENESS [ISABE 93-7026] p 1213 A93-54002 semi-ellipsoidal wing at incidence p1178 A93-53216 USAF in-flight simulation - A cost-effective operating DIFFUSION WELDING ENERGY DISSIPATION approach The application of diffusion bonding in the manufacture The energy dissipation in a rotating stall cell [AIAA PAPER 93-3604] p1175 A93-52690 of aeroengine components p 1217 A93-53514 [ISABE 93-7010] p1183 A93-53986

A-6 SUBJECT INDEX FIBER COMPOSITES

ENERGY TRANSFER Performance and configuration analysis of jet-engine EXHAUST DIFFUSERS Energy management — aircraft propulsion system off-design behavior Transonic discharge flows around diffuser vanes from performance [ISABE 93-7087] p 1202 A93-54063 a centrifugal impeller |ISABE93-7019| p 1)95 A93-53995 Design of limit-tracking systems incorporating a turbofan [ISABE 93-70531 p1185 A93-54029 ENGINE AIRFRAME INTEGRATION engine with constant disturbances Thermal design and analysis of an exhaust diffuser unit Study on unstart and its propagation along modules due [ISABE 93-70901 p 1203 A93-54066 in a ceramic composite to compound choking and/or fluctuations in combustor Structural integrity validation of limited-life engines [ISABE 93-7060] p 1220 A93-54036 of scramjet engines [ISABE 93-7131] p 1205 A93-54106 EXHAUST EMISSION IISABE 93-7052! p1199 A93-54028 ENGINE FAILURE Emission characteristics of a model gas turbine Variable cycle engine concept Selection of a method for protecting aircraft gas turbine combustor at practical conditions | ISABE 93-70651 p 1200 A93-54041 engines against damage by foreign objects (Mathematical [ISABE 93-7023] p1196 A93-53999 models) p1193 A93-53554 Advanced aerodynamic airframe/nozzle integration EXHAUST GASES [ISABE 93-70991 p 1187 A93-54075 ENGINE INLETS Estimation of the parameters of the electrodynamic A new cooling system for ultra high temperature Wind tunnel tests of the model of intake-airframe system engine-exhaust jet p1193 A93-52965 turbines integration The prediction of thermal NO(x) in gas turbine [ISABE 93-7073] p 1201 A93-54049 exhausts [ISABE 93-71011 p1192 A93-54077 Wind tunnel tests of the model of intake-airframe [ISABE 93-7022] p 1195 A93-53998 ENGINE CONTROL integration A study of surge control by using pulse cut-off for dual [ISABE 93-7101] p1192 A93-54077 Measurement and prediction of flow in a gas turbine spool turbo-jet engine pi 194 A93-53862 Starting characteristics of scramjet inlets engine exhaust plume Developments towards versatility in digital engine control [ISABE 93-7105] p 1203 A93-54081 [ISABE 93-7113] p 1204 A93-54088 units Evaluation of turboramjet exhaust systems from scale EXHAUST NOZZLES [ISABE 93-7088) p 1202 A93-54064 model test data Advanced aerodynamic airframe/nozzle integration Design of limit-tracking systems incorporating a turbofan [ISABE 93-7109] p 1204 A93-54085 [ISABE 93-7099] p1187 A93-54075 engine with constant disturbances ENGINE NOISE Evaluation of turboramjet exhaust systems from scale [ISABE 93-7090] p 1203 A93-54066 The acoustics of axial compressors model test data Development of a real time dynamic engine simulation [ONERA, TP NO. 1993-102] p 1226 A93-53615 [ISABE 93-7109] p 1204 A93-54085 model of a turbo fan engine ENGINE PARTS Observation of fluctuation of 2D-nozzle flows [ISABE 93-7132] p 1205 A93-54107 The application of diffusion bonding in the manufacture [ISABE 93-7110] p 1204 A93-54086 ENGINE DESIGN of aeroengine components p 1217 A93-53514 EXPERT SYSTEMS Research and development of aircraft engine in Japan Corrosion of ceramic matrix composites Implementation of expert systems within an interactive - Historical review [ONERA, TP NO. 1993-82] p 1213 A93-53602 tactical environment [AIAA PAPER 93-3583] p 1223 A93-52678 [ISABE 93-70001 p 1227 A93-53977 ENGINE TESTS The challenge of IHPTET — Integrated High Design and testing methods of high performance Expert Systems for the simulation of turbofan engines Performance Turbine Engine Technology combustors for airbreathing engines [ISABE 93-7133] p 1225 A93-54108 [ISABE 93-70011 p1194 A93-53978 [ISABE 93-7024] p1196 A93-54000 Design and technology for engine manufacture — for Variable cycle engine concept Rolls-Royce aerospace business [ISABE 93-7065] p 1200 A93-54041 | ISABE 93-7002) p1194 A93-53979 Effect of nozzle design on the performance of a highly F-111 AIRCRAFT Propulsion technology challenges for turn-of-the-century loaded turbine stage Reinforcement of the F-111 wing pivot fitting with a commercial aircraft [ISABE 93-7096] p 1203 A93-54072 [ISABE 93-7003] p1194 A93-53980 boron/epoxy doubler system - Materials engineering ENVIRONMENT SIMULATION aspects p 1214 A93-54241 Mach 5 turboramjet requirements and design Implementation of expert systems within an interactive F-16 AIRCRAFT approach tactical environment Prismatic grid generation for three-dimensional complex [ISABE 93-70151 p1194 A93-53991 [AIAA PAPER 93-3583) p 1223 A93-52678 geometries p1178 A93-53217 Development study on Air Turbo Ramjet engine for a Pseudo Aircraft Systems - A multi-aircraft simulation FAILURE ANALYSIS future space plane system for air traffic control research Durability properties for adhesively bonded structural [ISABE 93-70161 p1195 A93-53992 [AIAA PAPER 93-3585] p 1209 A93-52679 aerospace applications p 1217 A93-53515 Conceptual design study on combined-cycle engine for ENVIRONMENTAL TESTS Fault tolerant navigation for aircraft landing hypersonic transport Durability properties for adhesively bonded structural p1191 A93-53866 [ISABE 93-7018] p1195 A93-53994 aerospace applications p 1217 A93-53515 FAN BLADES Energy management — aircraft propulsion system Helicopter operations in severe environments; performance Effects of blade geometry and mode shape on fan Proceedings of the Conference, London, United Kingdom, flutter [ISABE 93-7019] p1195 A93-53995 June 4, 1992 [ISABE 93-7028] p1196 A93-54004 An ultra low NO(x) pilot combustor for staged low NO(x) [ISBN 1-85768-045-6) p1175 A93-54287 combustion Investigation of the flow field through a variable pitch Environmental effects of operations during Desert [ISABE 93-7020] p1195 A93-53996 fan rotor with an inlet total pressure distortion Shield/Desert Storm p1190 A93-54291 Low NO(x) combustor development using aerodynamic [ISABE 93-7029] p1184 A93-54005 staging EQUATIONS OF MOTION Navier-Stokes computation of the three dimensional flow [ISABE 93-7021] p)195 A93-53997 Initial development of a research flight simulator fields through a transonic fan blade Design and testing methods of high performance software [ISABE 93-7030] p1184 A93-54006 combustors for airbreathing engines [AIAA PAPER 93-3590] p 1223 A93-52683 Performance improvement by forward-skewed blading [ISABE 93-7024] p1196 A93-54000 EQUATIONS OF STATE of axial fan moving blades Design of high-load aviation turbomachines using The numerical errors in inverse simulation [ISABE 93-7055] p1185 A93-54031 modern 3D computational methods [AIAA PAPER 93-3588] p 1223 A93-52681 FATIGUE LIFE [ISABE 93-7032] p1196 A93-54008 EROSION Design for cyclic loading endurance of composites The effects of end-bend regulations of compressor blade The chemistry of Saudi Arabian sand - A deposition p 1216 A93-53395 on the outlet flow field problem on helicopter turbine airfoils Clean melting and the removal of defects from [ISABE 93-7033] p1185 A93-54009 p 1216 A93-53468 aero-engine materials p 1217 A93-53503 CFD for ramjet and scramjet powered vehicles ERROR ANALYSIS Thermal fatigue life assessment of a convection-cooled [ISABE 93-7035] p1197 A93-54011 The numerical errors in inverse simulation gas turbine blade The design and development of an afterburner [AIAA PAPER 93-3588] p 1223 A93-52681 [ISABE 93-7062] p1199 A93-54038 [ISABE 93-7041] p1198 A93-54017 ERROR DETECTION CODES FATIGUE TESTS Thermal design and analysis of an exhaust diffuser unit Neural network fault diagnosis of a turbofan engine The application of diffusion bonding in the manufacture in a ceramic composite [ISABE 93-7091] p 1203 A93-54067 of aeroengine components p 1217 A93-53514 FAULT TOLERANCE [ISABE 93-7060] p 1220 A93-54036 EULER EQUATIONS OF MOTION Characterization of the faulted behavior of digital Axial flow compressors - Mechanical design trends A dual-Euler method for solving all-attitude angles of computers and fault tolerant systems [ISABE 93-7061] p1199 A93-54037 the aircraft p 1224 A93-52762 Thermal fatigue life assessment of a convection-cooled [AIAA PAPER 93-3589] p 1223 A93-52682 gas turbine blade Fault tolerant navigation for aircraft landing An implicit difference scheme of Euler equation for [ISABE 93-7062] p1199 A93-54038 p1191 A93-53866 unsteady transonic flow p 1182 A93-53852 Research and development of a turbo-accelerator for FEEDBACK CONTROL super/hypersonic transport Numerical simulation of ramjet and scramjet combustion A parameter optimization approach to controller [ISABE 93-7066] p 1200 A93-54042 using two-dimensional Euler equations with finite rate partitioning for integrated flight/propulsion control Research and development of high pressure compressor chemistry application p 1206 A93-54268 for SST and HST engine [ISABE 93-7083] p 1202 A93-54059 Longitudinal closed-loop pilot/vehicle analysis of DFBW [ISABE 93-7068] p1186 A93-54044 Recent developments performed at ONERA for the aircraft during approach and landing Test results of the hydrogen fueled model combustor simulation of 3D inviscid and viscous flows in p 1206 A93-54277 for the air turbo ramjet engine turbomachinery by the solution of Euler and Navier-Stokes FIBER COMPOSITES [ISABE 93-7082] p 1201 A93-54058 equations Preparation and characterization of continuous fiber New developments with the V2500 engine (ISABE 93-7094] p1186 A93-54070 reinforced zirconium diboride matrix composites for a [ISABE 93-7085] p 1202 A93-54061 EULER-LAGRANGE EQUATION leading edge material p 1211 A93-53445 Aerodynamic inverse design and analysis for a full A Eulerian/Lagrangian modelling to calculate the Origin of the carbon rich sliding interface in alkali engine evolution of a water droplets spray containing matrix-SiC nicalon fibre composites [ISABE 93-7086] p1186 A93-54062 [ISABE 93-7121] p 1221 A93-54096 [ONERA, TP NO. 1993-77] p 1212 A93-53598

A-7 FIBER OPTICS SUBJECT INDEX

FIBER OPTICS A parameter optimization approach to controller Internally coherent system of innovation - The case of Sensors with centroid based common sensing scheme partitioning for integrated flight/propulsion control flight simulation and their multiplexing — fiber optic sensors in aircraft and application p 1206 A93-54268 IAIAA PAPER 93-3548] p 1226 A93-52653 aircraft engine applications p 1192 A93-52994 FLIGHT MECHANICS Methodology for integration of digital control loaders in FIELD THEORY (PHYSICS) Solution of the boundary value problem in flight dynamics aircraft simulators CRAASH - A coordinated collision avoidance system by the opposite motion method p 1206 A93-52944 [AIAA PAPER 93-3551] p 1207 A93-52655 [ ONER A, TP NO. 1993-84] p 1191 A93-53604 Non-linear flight dynamics Dynamic simulation fidelity improvement using transfer FIGHTER AIRCRAFT (ONERA, TP NO. 1993-109] p 1206 A93-53621 function state extrapolation Low aspect ratio wing code validation experiment [AIAA PAPER 93-3552] p 1222 A93-52656 FLIGHT PATHS p1176 A93-53202 Transport delay compensation - An inexpensive Analysis of a turning point problem in flight trajectory A parameter optimization approach to controller alternative to increasing image generator update rate optimization p 1210 A93-52885 partitioning for integrated flight/propulsion control (AIAA PAPER 93-3563] p 1223 A93-52663 FLIGHT SAFETY application p 1206 A93-54268 Visual weather simulation using meteorological Flight safety in Europe p 1227 A93-53726 FILM COOLING databases Effect of film cooling/regenerative cooling on scramjet FLIGHT SIMULATION [AIAA PAPER 93-3566] p 1207 A93-52665 engine performances AIAA Flight Simulation Technologies Conference. The development of SIMONA - A simulator facility for [ISABE 93-7036) P1197 A93-54012 Monterey, CA, Aug. 9-11. 1993, Technical Papers advanced research into simulation techniques, motion Impingement cooling with film coolant extraction in the p 1207 A93-52651 system control and navigation systems technologies airfoil leading edge regions Evolution of flight simulation [AIAA PAPER 93-3574] p 1208 A93-52670 [ISABE 93-7078] p 1220 A93-54054 [AIAA PAPER 93-3545] p 1207 A93-52652 Development and operation of a real-time simulation at FINITE DIFFERENCE THEORY Internally coherent system of innovation - The case of the NASA Ames Vertical Motion Simulator Calculation of a compressible three-dimensional flight simulation [AIAA PAPER 93-3575] p 1208 A93-52671 boundary layer on a swept wing p 1179 A93-53551 [AIAA PAPER 93-3548] p 1226 A93-52653 Semi-full-scale dynamic simulation complex on the basis Numerical study of supersonic flow over a backward An advanced rotorcraft flight simulation model - Parallel of centrifuge step with transverse injection p 1182 A93-53853 implementation and performance analysis IAIAA PAPER 93-3577] p 1208 A93-52673 FINITE ELEMENT METHOD [AIAA PAPER 93-3550] p 1222 A93-52654 Simulation motion effect on single axis compensatory A nonlinear finite element of an arbitrary beam Methodology for integration of digital control loaders in tracking p 1215 A93-52939 aircraft simulators [AIAA PAPER 93-3579] p 1208 A93-52675 A finite element for modeling skins of composite [AIAA PAPER 93-3551] p 1207 A93-52655 Pilot evaluations of augmented flight simulator motion materials p 1215 A93-52979 Dynamic simulation fidelity improvement using transfer [AIAA PAPER 93-3580] p 1208 A93-52676 Flutter analysis of stiffened laminated composite plates function state extrapolation Implementation of expert systems within an interactive and shells in supersonic flow p 1216 A93-53224 [AIAA PAPER 93-3552] p 1222 A93-52656 tactical environment Mathematical modeling of the three-dimensional A high fidelity video delivery system for real-time flight [AIAA PAPER 93-3583] p 1223 A93-52678 temperature fields of turbine blades simulation research Initial development of a research flight simulator p 1216 A93-53329 [AIAA PAPER 93-3558] p 1214 A93-52659 software Total quality management of forged products through Hybrid complex of the aircraft intellectualized control [AIAA PAPER 93-3590] p 1223 A93-52683 finite element simulation p 1217 A93-53493 systems simulation at the stage of their research Flight update of aerodynamic math model Calculation of flow fields near a lifting wing projecting [AIAA PAPER 93-3596] p 1224 A93-52687 p1179 A93-53552 [AIAA PAPER 93-3559] p 1222 A93-52660 How to consider simulation fidelity and validity for an Finite element analysis of natural vibrations of an Visual weather simulation using meteorological engineering simulator aeroplane with asymmetric variable wing geometry databases [AIAA PAPER 93-3598] p 1209 A93-52688 p1218 A93-53776 [AIAA PAPER 93-3566] p 1207 A93-52665 USAF in-flight simulation - A cost-effective operating New approximate method of stress analysis for bladed A primary flight display for four-dimensional guidance approach rotating discs and navigation influence of tunnel size and level of [AIAA PAPER 93-3604] p1175 A93-52690 [ISABE 93-7059] p 1219 A93-54035 additional information on pilot performance and control FINITE VOLUME METHOD behaviour A rapid prototyping system for inflight simulation using Upwind-biased, point-implicit relaxation strategies for [AIAA PAPER 93-3570] p 1208 A93-52668 the Calspan Learjet 25 hypersonic flowfield simulations on supercomputers The development of SIMONA - A simulator facility for [AIAA PAPER 93-3606] p1191 A93-52691 P1175 A93-52770 advanced research into simulation techniques, motion Flight simulation - An overview p 1209 A93-53768 Numerical simulation of gas turbine combustors with system control and navigation systems technologies Networks extend simulation's reach complex geometries [AIAA PAPER 93-3574] p 1208 A93-52670 p 1225 A93-53770 [ISABE 93-7128] p 1204 A93-54103 Semi-full-scale dynamic simulation complex on the basis Engineering simulators enhance 777 development FIRE CONTROL of centrifuge p 1192 A93-53771 Integrated fire control simulation systems [AIAA PAPER 93-3577] 01208 A93-52673 Removing the risk from rotorcraft testing p1192 A93-53876 Representation of vehicle location in networked p1192 A93-53772 LONGBOW - Force multiplier for continuous simulations FLIGHT TESTS operations p 1175 A93-54295 [AIAA PAPER 93-3582] p 1214 A93-52677 Instrumentation and telemetry systems for free-flight FIRE FIGHTING A radar altitude and line of sight attachment drop model testing p 1209 A93-52754 Red-hot simulation p 1209 A93-53774 [AIAA PAPER 93-3587] p 1223 A93-52680 A method for the spectral-time identification of the FIXED WINGS A dual-Euler method for solving all-attitude angles of longitudinal and lateral motions of an aircraft Skin-friction topology over a surface mounted the aircraft p 1205 A93-52942 semi-ellipsoidal wing at incidence p 1178 A93-53216 [AIAA PAPER 93-3589] p 1223 A93-52682 An aerodynamic model for the longitudinal motion of Initial development of a research flight simulator Identification of the phase characteristics and flight training devices p 1207 A93-54278 software wind-induced perturbations of an aircraft from flight test FLAME HOLDERS [AIAA PAPER 93-3590] p 1223 A93-52683 results P 1206 A93-52943 Isothermal flow characteristics behind V-shape gutter Enhancing real-time flight simulation execution by Complementary role of ground testing, flight testing, and with and without injection intercepting Run-Time Library calls computations in aerospace plane propulsion | ISABE 93-7040] p1198 A93-54016 [AIAA PAPER 93-3591] p 1224 A93-52684 development Large eddy simulation of turbulent combustion behind Reusable code for helicopter simulation [ISABE 93-7034] p1197 A93-54010 flame holders [AIAA PAPER 93-3594] p 1224 A93-52686 Longitudinal closed-loop pilot/vehicle analysis of DFBW [ISABE 93-7042] P1198 A93-54018 Flight update of aerodynamic math model aircraft during approach and landing The combustion performance of methane-fueled ram [AIAA PAPER 93-3596] p 1224 A93-52687 p1206 A93-54277 combustor How to consider simulation fidelity and validity for an FLIGHT TRAINING [ISABE 93-7079] p 1201 A93-54055 engineering simulator Innovative bagging techniques on a composite P-51 FLAME STABILITY [AIAA PAPER 93-3598] p 1209 A93-52688 Mustang replica p1191 A93-53405 A study on 3-D velocity distribution of isothermal flows USAF in-flight simulation - A cost-effective operating FLOW CHARACTERISTICS behind an afterburner flame stabilizer approach Estimation of the change of axial-flow compressor I ISABE 93-7039] p1197 A93-54015 [AIAA PAPER 93-3604] p1175 A93-52690 characteristics during long-term service FLAT PLATES A rapid prototyping system for inflight simulation using P1193 A93-52949 Transition correlation in subsonic flow over a flat plate the Catspan Learjet 25 Isothermal flow characteristics behind V-shape gutter P1178 A93-53231 [AIAA PAPER 93-3606] p1191 A93-52691 with and without injection Numerical analysis of a flat plate in a pitching motion. Flight simulation - An overview p 1209 A93-53768 [ISABE 93-7040] p1198 A93-54016 II - Effect on the flow of the position of the pivot, etc Flight research simulation takes off Correlations for flow property variation at outlet of a 01181 A93-53798 p1192 A93-53769 centrifugal impeller The unsteady flow past a supersonic splitter plate Networks extend simulation's reach [ISABE 93-7054] p1185 A93-54030 [ISABE 93-7047] p1185 A93-54023 p 1225 A93-53770 Experimental investigation of boundary layer transition Removing the risk from rotorcraft testing FLOW DISTORTION on a flat plate with C4 leading edge P1192 A93-53772 A study of optical distortions arising in radiation [ISABE 93-7123] p 1222 A93-54098 An aerodynamic model for the longitudinal motion of transmission through cavities with gas flow around them FLIGHT ALTITUDE flight training devices p 1207 A93-54278 p 1225 A93-52945 A radar altitude and line of sight attachment FLIGHT SIMULATORS Review of stall, surge and active control in axial [AIAA PAPER 93-3587] p 1223 A93-52680 AIAA Flight Simulation Technologies Conference. compressors Flight safety in Europe p 1227 A93-53726 Monterey. CA. Aug. 9-11, 1993. Technical Papers [ISABE 93-7011] p1184 A93-53987 FLIGHT CONTROL p 1207 A93-52651 An investigation of post stall transients and recoverability Non-linear flight dynamics Evolution of flight simulation of axial compression systems IONERA, TP NO. 1993-109] p 1206 A93-53621 [AIAA PAPER 93-3545] p 1207 A93-52652 [ISABE 93-7012] p1184 A93-53988

A-8 SUBJECT INDEX GROUND EFFECT MACHINES

FLOW DISTRIBUTION FLUTTER GAS FLOW Measurements and computational analysis of heat Laser velocimeter measurements of the flow field A study of optical distortions arising in radiation transfer and flow in a simulated turbine blade internal generated by a forward-swept preplan during flutter transmission through cavities with gas flow around them cooling passage (AIAA PAPER 93-2919] p1180 A93-53591 p 1225 A93-52945 (AIAA PAPER 93-1797] p 1218 A93-53585 FLUTTER ANALYSIS Direct simulation of reacting fuel gas flows in a Laser velocimeter measurements of the flow field Flutter analysts of stiffened laminated composite plates supersonic mixing layer generated by a forward-swept preplan during flutter and shells in supersonic flow p 1216 A93-53224 IISABE 93-7072] p 1201 A93-54048 | AIAA PAPER 93-2919] p1180 A93-53591 Effects of blade geometry and mode shape on fan GAS INJECTION Investigation of the flow field through a variable pitch flutter Tandem transverse hydrogen gas injection into a fan rotor with an inlet total pressure distortion [ISABE 93-7028] pt196 A93-54004 supersonic airflow IISABE 93-7029] p1184 A93-54005 The unsteady flow past a supersonic splitter plate [ISABE 93-7069] P 1201 A93-54045 Navier-Stokes computation of the three dimensional flow [ISABE 93-7047] p1185 A93-54023 Numerical and experimental study on two- and fields through a transonic fan blade FLUX VECTOR SPLITTING three-dimensional supersonic flow field with hydrogen I ISABE 93-7030] p1184 A93-54006 An implicit difference scheme of Euler equation for injection unsteady transonic flow p 1182 A93-53852 Tip clearance effects on the flow field of an axial turbine [ISABE 93-7118] p1188 A93-54093 FLY BY WIRE CONTROL rotor blade cascade GAS JETS Harmonic oscillation in FBW system | ISABE 93-7057] p1185 A93-54033 Noise reduction of supersonic heated jet with jet mixing p 1206 A93-53877 enhancement by tabs Navier-Stokes analysis of turbine flowiield and external FORGING [ISABE 93-7046] p1198 A93-54022 heat transfer Total quality management of forged products through GAS TEMPERATURE [ISABE 93-7075] p1186 A93-54051 finite element simulation p 1217 A93-53493 Noise reduction of supersonic heated jet with jet mixing Finite-rate H2/air combustion effects in CRJ for FORM FACTORS enhancement by tabs hypersonic launchers Effects of blade geometry and mode shape on fan [ISABE 93-7046] p1198 A93-54022 (ISABE 93-7084] p 1202 A93-54060 flutter GAS TURBINE ENGINES Experimental analysis of turbine rotor flow at design and [ISABE 93-7028] p1196 A93-54004 Progress towards understanding and predicting heat off-design conditions FORMING TECHNIQUES transfer in the turbine gas path p 1215 A93-52751 t ISABE 93-7092] p1186 A93-54068 Structural applications of Avimid K3B LDF thermoplastic Selection of a method for protecting aircraft gas turbine On the numerical simulation of the two-dimensional flow composites — for advanced aircraft engines against damage by foreign objects (Mathematical field around a hypersonic air-intake-compressibility p 1216 A93-53429 models) p1193 A93-53554 effects FOURIER ANALYSIS High temperature heat exchangers for gas turbines and [ISABE 93-7100] p1187 A93-54076 Thrust imparted to an airfoil by passage through a future hypersonic air breathing propulsion Study on flow field around slender diamond cone sinusoidal upwash field p1178 A93-53219 [ONERA, TP NO. 1993-75] p 1218 A93-53596 traveling at hypersonic speed p 1189 A93-54314 FRACTURE MECHANICS Design and technology for engine manufacture — for FLOW EQUATIONS A study of damage tolerance of the landing gear Rolls-Royce aerospace business Calculation of flow fields near a lifting wing Structure p 1219 A93-53881 IISABE 93-7002] p1194 A93-53979 Reinforcement of the F-111 wing pivot fitting with a P1179 A93-53552 Propulsion technology challenges for turn-of-the-century boron/epoxy doubler system - Materials engineering The streamline throughflow method of axial commercial aircraft aspects p1214 A93-54241 turbomachinery flow analysis [ISABE 93-7003] p1194 A93-53980 FREE JETS [ISABE 93-7031] p1184 A93-54007 The prediction of thermal NO(x) in gas turbine Streamwise vorticity generation and mixing exhausts FLOW GEOMETRY enhancement in free jets by 'delta-tabs' [ISABE 93-7022] p1195 A93-53998 Velocity fluctuation based on the difference in the flow [AIAA PAPER 93-3253] p1180 A93-53592 Emission characteristics of a model gas turbine pattern in the channels of a centrifugal impeller FRICTION WELDING combustor at practical conditions p1182 A93-53842 Friction surfacing and linear friction welding [ISABE 93-7023] p1196 A93-53999 FLOW MEASUREMENT p 1217 A93-53499 Design of high-load aviation turbomachines using Pressure distribution measurement around hypersonic FUEL COMBUSTION modern 3D computational methods delta winged semicone - Measurement by means of Periodic chemical energy release for active combustion [ISABE 93-7032] p1196 A93-54008 magnet tape p1176 A93-53193 control Thermal fatigue life assessment of a convection-cooled Observations of liquid jets injected into a highly [ISABE 93-7043] p1198 A93-54019 gas turbine blade accelerated supersonic boundary layer FUEL CONTROL [ISABE 93-7062] p1199 A93-54038 P1177 A93-53214 A study of surge control by using pulse cut-off for dual A new cooling system for ultra high temperature Design and testing methods of high performance spool turbo-jet engine p 1194 A93-53862 turbines combustors for airbreathing engines [ISABE 93-7073] p 1201 A93-54049 FUEL INJECTION [ISABE 93-7024] p1196 A93-54000 New developments with the V2500 engine A study of self-ignition of methane-hydrogen mixture fuel [ISABE 93-7085) p 1202 A93-54061 Isothermal flow characteristics behind V-shape gutter injected into high enthalpy supersonic airstreams Thermodynamic and neutral network computer with and without injection [ISABE 93-7049] p 1213 A93-54025 modelling of implanted component faults in a gas turbine [ISABE 93-7040] p1198 A93-54016 Ignition and combustion performance of a scramjet Large eddy simulation of turbulent combustion behind engine combustor with a fuel injection strut [ISABE 93-7089] p 1202 A93-54065 flame holders [ISABE 93-7050] p1199 A93-54026 [ISABE 93-7042] p1198 A93-54018 Experimental analysis of turbine rotor flow at design and FUEL SPRAYS off-design conditions Correlations for flow property variation at outlet of a Blowout of turbulent disc/pilot stabilized jet diffusion [ISABE 93-7092] p1186 A93-54068 centrifugal impeller flames A finite element code for gas turbine combustor flow [ISABE 93-7054] p1185 A93-54030 [ISABE 93-7026] p 1213 A93-54002 with Stretched Laminar Flamelet modelling FLOW RESISTANCE FUEL-AIR RATIO [ISABE 93-7127] p 1204 A93-54102 Effect of rotation on heat transfer and hydraulic Hypersonic shock-induced combustion ramjet Numerical simulation of gas turbine combustors with resistance in the radial cooling channels of turbine rotor performance analysis complex geometries blades p 1215 A93-52950 [ISABE 93-7037] p1197 A93-54013 [ISABE 93-7128] p 1204 A93-54103 FLOW STABILITY LIF visualization of 3-dimensional hypersonic mixing Mixing of multiple jets with a confined subsonic Observation of fluctuation of 2D-nozzle flows [ISABE 93-7114] p 1221 A93-54089 crossflow p1189 A93-54324 [ISABE 93-7110] p 1204 A93-54086 Enhanced fuel-air mixing in hypersonic engines GERMANY FLOW VISUALIZATION [ISABE 93-7115] p 1221 A93-54090 Stumbling blocks for airport construction in the new Skin-friction topology over a surface mounted FUNCTIONALLY GRADIENT MATERIALS German federal states p 1227 A93-53727 semi-ellipsoidal wing at incidence p1178 A93-53216 Application of functionally gradient materials to scramjet GLASS FIBERS A preliminary investigation of the control of separated engines Nonlinear deformation mechanics of multilayer flow by means of excitation p1182 A93-53859 [ISABE 93-7063] p 1200 A93-54039 transparency elements - Some calculation results — for Observation of fluctuation of 2D-nozzle flows aircraft portholes p1191 A93-52937 FUSELAGES GOGGLES [ISABE 93-7110] p 1204 A93-54086 Calculation of the position of the flow separation line LIF visualization of 3-dimensional hypersonic mixing Royal Air Force support helicopters - Night operations in an analog model of flow past a body P1190 A93-54293 [ISABE 93-7114] p 1221 A93-54089 p1176 A93-52958 FLUID DYNAMICS GRAPHITE-EPOXY COMPOSITES An investigation of post stall transients and recoverability FUSION WELDING The characterization and development of materials for of axial compression systems Structural applications of Avimid K3B LDF thermoplastic advanced textile composites p 1211 A93-53434 [ISABE 93-7012] p1184 A93-53988 composites — for advanced aircraft GRID GENERATION (MATHEMATICS) p 1216 A93-53429 Fluid dynamics and convective heat transfer in impinging Prismatic grid generation for three-dimensional complex jets through implementation of a high resolution liquid geometries p 1178 A93-53217 crystal technique The construction of nearly orthogonal multiblock grids [ISABE 93-7077) p 1220 A93-54053 for compressible flow simulation p 1219 A93-53847 FLUID INJECTION GROUND BASED CONTROL Two-dimensional and three-dimensional mixing flow GAS DYNAMICS A reactive approach for distributed air traffic control structures with injected through slotted nozzle and circular Comparison of gasdynamic models in hypersonic flow [ONERA, TP NO. 1993-83) p1190 A93-53603 nozzle into supersonic flows P1179 A93-53315 GROUND EFFECT MACHINES [ISABE 93-7117] p 1221 A93-54092 Recent advances in computational analysis of On hovercraft overwater heave stability FLUID MECHANICS hypersonic vehicles p 1179 A93-53364 p 1219 A93-53819 The fluid physics of parachute inflation The design and development of an afterburner Kelvin-Helmholtz wave generation beneath hovercraft p1189 A93-54347 [ISABE 93-7041] p1198 A93-54017 Skirts p 1219 A93-53820

A-9 GROUND TESTS SUBJECT INDEX

GROUND TESTS HELICOPTER PERFORMANCE HYDROGEN FUELS Complementary role of ground testing, flight testing, and Helicopter operations in severe environments; Energy management — aircraft propulsion system computations in aerospace plane propulsion Proceedings of the Conference, London, United Kingdom, performance development June 4, 1992 [ISABE 93-7019] p1195 A93-53995 [ISABE 93-7034] p1197 A93-54010 [ISBN 1-85768-045-6] p1175 A93-54287 Hypersonic shock-induced combustion ramjet GUIDE VANES Arctic environment - Helicopter operations in cold performance analysis Numerical study on inception of stall cells in rotating climates p 1189 A93-54288 [ISABE 93-7037] p1197 A93-54013 stall Operating helicopters in a demanding environment - A study of self-ignition of methane-hydrogen mixture fuel [ISABE 93-7007] p1183 A93-53983 Mountain flying/high evaluations p1190 A93-54289 injected into high enthalpy supersonic airstreams [ISABE 93-7049] p 1213 A93-54025 GUST LOADS Avionic systems in support of covert helicopter HYDROGEN OXYGEN ENGINES Forcing function modeling for flow induced vibration operations p 1193 A93-54294 Finite-rate H2/air combustion effects in CRJ for [ISABE 93-7027] p1196 A93-54003 LONGBOW - Force multiplier for continuous hypersonic launchers operations p1175 A93-54295 [ISABE 93-7084] p 1202 A93-54060 H HELICOPTERS Compact heat exchanger fitted to engines of the inverted Reusable code for helicopter simulation type [AIAA PAPER 93-3594] p 1224 A93-52686 HARMONIC OSCILLATION [ISABE 93-7120] p 1221 A93-54095 Analysis of spatial motion dynamics of a helicopter for Harmonic oscillation in FBW system HYPERSONIC AIRCRAFT various models of the induced velocity field p 1206 A93-53877 Effect of boundary layer suction on the thrust and p1191 A93-53721 aerodynamic efficiency of a hypersonic flight vehicle HEAT EXCHANGERS HIGH PRESSURE p1176 A93-52959 High temperature heat exchangers for gas turbines and Research and development of high pressure compressor Mach 5 turboramjet requirements and design future hypersonic air breathing propulsion for SST and HST engine approach [ONERA, TP NO. 1993-75] p 1218 A93-53596 [ISABE 93-7068] p1186 A93-54044 [ISABE 93-7015] p1194 A93-53991 Characteristics of heat exchanger in HIGH RESOLUTION Conceptual design study on combined-cycle engine for supersonic/subsonic flows Fluid dynamics and convective heat transfer in impinging hypersonic transport [ISABE 93-7119] p 1221 A93-54094 jets through implementation of a high resolution liquid [ISABE 93-7018) p1195 A93-53994 Compact heat exchanger fitted to engines of the inverted crystal technique Research and development of a turbo-accelerator for type [ISABE 93-7077] p 1220 A93-54053 super/hypersonic transport [ISABE 93-7120] p 1221 A93-54095 HIGH REYNOLDS NUMBER [ISABE 93-7066] p 1200 A93-54042 HEAT FLUX Zonal-local solution method for the turbulent Research and development of high pressure compressor Progress towards understanding and predicting heat Navier-Stokes equations p1177 A93-53205 for SST and HST engine transfer in the turbine gas path p 1215 A93-52751 HIGH TEMPERATURE [ISABE 93-7068] p1186 A93-54044 Application of functionally gradient materials to scramjet High temperature heat exchangers for gas turbines and HYPERSONIC BOUNDARY LAYER engines future hypersonic air breathing propulsion Separation phenomenon in a hypersonic flow with strong [ISABE 93-7063] p 1200 A93-54039 [ONERA, TP NO. 1993-75] p 1218 A93-53596 wall cooling - Subcritical regime p 1189 A93-54266 HEAT OF COMBUSTION Studies on coolant problems in aeronautical turbine HYPERSONIC COMBUSTION Energy management — aircraft propulsion system cascades Hypersonic shock-induced combustion ramjet performance [ISABE 93-7074] p 1220 A93-54050 performance analysis [ISABE 93-7019] p1195 A93-53995 HIGH TEMPERATURE ENVIRONMENTS [ISABE 93-7037] p1197 A93-54013 HEAT RESISTANT ALLOYS The properties of newly developed highly damage Enhanced fuel-air mixing in hypersonic engines Clean melting and the removal of defects from tolerant and easy handleable carbon fiber/modified [ISABE 93-7115) p 1221 A93-54090 aero-engine materials p 1217 A93-53503 bismaleimide prepreg system p 1212 A93-53448 HYPERSONIC FLIGHT Aerodynamic heating environment definition/thermal Material requirements for the High Speed Civil Overview of NASA's advanced high temperature engine materials technology program p 1212 A93-53453 protection system selection for the HL-20 Transport p1181 A93-53739 [ISABE 93-7067] p 1200 A93-54043 Thermal design and analysis of an exhaust diffuser unit in a ceramic composite HL-20 computational fluid dynamics analysis HEAT TRANSFER [ISABE 93-7060] p 1220 A93-54036 p1181 A93-53740 Effect of rotation on heat transfer and hydraulic Development of MIL-H-53119, -54 C to 175 C Studies on methane-fuel ram combustor for HST resistance in the radial cooling channels of turbine rotor high-temperature nonflammable hydraulic fluid for Air combined cycle engine blades p 1215 A93-52950 Force systems p 1214 A93-54250 [ISABE 93-7080] p 1201 A93-54056 Measurements and computational analysis of heat HIGH TEMPERATURE GASES Finite-rate H2/air combustion effects in CRJ for transfer and flow in a simulated turbine blade internal Non-self-similarity of a boundary layer flow of a hypersonic launchers cooling passage high-temperature gas in a Laval nozzle [ISABE 93-7084] p 1202 A93-54060 [AIAA PAPER 93-1797] p 1218 A93-53585 P1176 A93-52946 LIF visualization of 3-dimensional hypersonic mixing Navier-Stokes analysis of turbine flowfield and external A new cooling system for ultra high temperature |ISABE 93-7114] p 1221 A93-54089 heat transfer turbines Enhanced fuel-air mixing in hypersonic engines [ISABE 93-7075] p1186 A93-54051 [ISABE 93-7073] p 1201 A93-54049 [ISABE 93-7115] p 1221 A93-54090 HEAT TRANSFER COEFFICIENTS HIGH TEMPERATURE TESTS Numerical study of nitric oxide formation in a hypersonic Measurements and computational analysis of heat Stress relaxation of low pressure plasma-sprayed ramjet engine transfer and flow in a simulated turbine blade internal NiCrAlY alloys p1211 A93-52870 [ISABE 93-7125] p 1204 A93-54100 cooling passage HIGH THRUST Heat loads as key problem of hypersonic flight [AIAA PAPER 93-1797] p 1218 A93-53585 Design and technology for engine manufacture — for P1222 A93-54276 Heat transfer and material temperature conditions in the Rolls-Royce aerospace business HYPERSONIC FLOW leading edge area of impingement-cooled turbine vanes [ISABE 93-7002] p1194 A93-53979 Upwind-biased, point-implicit relaxation strategies for [ISABE 93-7076) p 1220 A93-54052 HIGHLY MANEUVERABLE AIRCRAFT hypersonic flowfield simulations on supercomputers Impingement cooling with film coolant extraction in the Stability analysis through bifurcation theory. I, II p1175 A93-52770 Pressure distribution measurement around hypersonic airfoil leading edge regions [ONERA, TP NO. 1993-108] p 1225 A93-53620 [ISABE 93-7078] p 1220 A93-54054 HILBERT SPACE delta winged semicone - Measurement by means of Linear quadratic tracking problems in Hilbert space - magnet tape p 1176 A93-53193 HEAT TREATMENT Application to optimal active noise suppression Space marching calculations about hypersonic Total quality management of forged products through configurations using a solution-adaptive mesh algorithm finite element simulation p 1217 A93-53493 p 1224 A93-52763 HILSCH TUBES P1177 A93-53212 HEAVING The development of a new air filtration system for the Application of the small parameter method to the On hovercraft overwater heave stability Alouette III helicopter problem of three-dimensional flow of a viscous gas past p 1219 A93-53819 [ISABE 93-7048] p1199 A93-54024 bodies p1178 A93-53314 Kelvin-Helmholtz wave generation beneath hovercraft HUMAN FACTORS ENGINEERING Comparison of gasdynamic models in hypersonic flow skirts p 1219 A93-53820 AIAA Flight Simulation Technologies Conference, p1179 A93-53315 HELICOPTER CONTROL Monterey, CA, Aug. 9-11, 1993, Technical Papers Shock shapes around slender diamond cones traveling Removing the risk from rotorcraft testing p 1207 A93-52651 at hypersonic speed p 1181 A93-53840 P1192 A93-53772 Effect of lift-to-drag ratio in pilot rating of the HL-20 Numerical solution of N-S equations for hypersonic flow landing task p 1210 A93-53738 HELICOPTER DESIGN over capsule-type vehicles p1182 A93-53858 The development of a new air filtration system for the HYDRAULIC FLUIDS Numerical simulation of a two-dimensional supersonic Alouette III helicopter Development of MIL-H-53119. -54 C to 175 C mixed-compression inlet [ISABE 93-7048] p1199 A93-54024 high-temperature nonflammable hydraulic fluid for Air [ISABE 93-7107) p1188 A93-54083 Royal Navy helicopter operations in the maritime Force systems p 1214 A93-54250 Separation phenomenon in a hypersonic flow with strong environment P1190 A93-54290 HYDROCARBON FUELS A study of self-ignition of methane-hydrogen mixture fuel wall cooling - Subcritical regime p 1189 A93-54266 The T700 ... from salt spray to sand blast HYPERSONIC HEAT TRANSFER p 1205 A93-54292 injected into high enthalpy supersonic airstreams [ISABE 93-7049] p 1213 A93-54025 Heat loads as key problem of hypersonic flight HELICOPTER ENGINES High density strained hydrocarbon fuels for air breathing p 1222 A93-54276 The chemistry of Saudi Arabian sand - A deposition propulsion HYPERSONIC INLETS problem on helicopter turbine airfoils [ISABE 93-7081] p 1213 A93-54057 On the numerical simulation of the two-dimensional flow p 1216 A93-53468 HYDROCARBONS field around a hypersonic air-intake-compressibility The T700 ... from salt spray to sand blast Viscosity of aviation fuel components - Aromatic effects p 1205 A93-54292 hydrocarbons (alkyl benzenes) p 1211 A93-52961 [ISABE 93-7100] p1187 A93-54076

A-10 SUBJECT INDEX LASER DOPPLER VELOCIMETERS

HYPERSONIC SHOCK Transonic area rule about lifting configurations Noise reduction of supersonic heated jet with jet mixing Hypersonic shock-induced combustion ramjet P1183 A93-53868 enhancement by tabs performance analysis A 2-D compressible N-S simulation of starting- and [ISABE 93-7046] p1198 A93-54022 | ISABE 93-7037 ] p 1197 A93-54013 stalling-flows in a compressor cascades system Two-dimensional and three-dimensional mixing flow HYPERSONIC SPEED [ISABE 93-7006] p1183 A93-53982 structures with injected through slotted nozzle and circular Heat loads as key problem of hypersonic flight Transonic discharge flows around diffuser vanes from nozzle into supersonic flows p 1222 A93-54276 a centrifugal impeller (ISABE 93-7117] p 1221 A93-54092 Study on flow field around slender diamond cone [ISABE 93-7053] p1185 A93-54029 Numerical and experimental study on two- and traveling at hypersonic speed p1189 A93-54314 Effects of wake interaction of two turbine cascades on three-dimensional supersonic flow field with hydrogen secondary/tip-leakage flows and losses HYPERSONIC VEHICLES injection [ISABE 93-7058] p1185 A93-54034 Recent advances in computational analysis of [ISABE 93-7118] p1188 A93-54093 Study on flow field around slender diamond cone hypersonic vehicles p 1179 A93-53364 JET PROPULSION traveling at hypersonic speed p 1189 A93-54314 Engine technology challenges for a 21st Century Evaluation of 2D ceramic matrix composites in INTERACTIVE CONTROL aeroconvective environments p 1212 A93-53459 High-Speed Civil Transport Implementation of expert systems within an interactive [ISABE 93-7064] p 1200 A93-54040 High temperature heat exchangers for gas turbines and tactical environment JET THRUST future hypersonic air breathing propulsion [AIAA PAPER 93-3583) p 1223 A93-52678 Numerical study of a delta plantorm with multiple jets [ONERA, TP NO. 1993-751 p 1218 A93-53596 INTERFERENCE LIFT in ground effect Thrust imparted to an airfoil by passage through a [SAE PAPER 892283] p1176 A93-53200 sinusoidal upwash field p 1178 A93-53219 I INTERMETALLICS Overview of NASA's advanced high temperature engine ICE ENVIRONMENTS materials technology program p 1212 A93-53453 Arctic environment - Helicopter operations in cold Material requirements for the High Speed Civil climates p1189 A93-54288 Transport K-EPSILON TURBULENCE MODEL ICE FORMATION [ISABE 93-7067] p 1200 A93-54043 Numerical analysis of flow within cascade with tip Compact heat exchanger fitted to engines of the inverted INTERNATIONAL COOPERATION clearance p1176 A93-53192 type Flight safety in Europe p 1227 A93-53726 Low-Reynolds-number k-epsilon model for unsteady [ISABE 93-7120] p 1221 A93-54095 Europe's new windtunnel p 1210 A93-54275 turbulent boundary-layer flows p1177 A93-53208 IGNITION LIMITS INTERNATIONAL RELATIONS 3D laminar and 2D turbulent computations with the A study of self-ignition of methane-hydrogen mixture fuel Air transport and the environment - Regulating aircraft Navier-Stokes solver FLU3M injected into high enthalpy supersonic airstreams noise p 1226 A93-52931 [ONERA. TP NO. 1993-105] pt180 A93-53618 [ISABE 93-7049] p 1213 A93-54025 INVISCID FLOW KALMAN FILTERS IGNITION TEMPERATURE Construction of wakes in the discrete vortex method Identification of nonlinear mechanical systems using Ignition and combustion performance of a scramjet P1179 A93-53333 combined state and parameter evaluation combustor with a fuel injection strut Kelvin-Helmholtz wave generation beneath hovercraft p 1224 A93-52732 [ISABE 93-7050] p1199 A93-54026 skirts P 1219 A93-53820 Passive range estimation for rotorcraft low-altitude ILLUMINATION The streamline throughflow method of axial flight p1190 A93-52881 Nonlinear deformation mechanics of multilayer turbomachinery flow analysis KARMAN VORTEX STREET transparency elements - Some calculation results — for [ISABE 93-7031] p1184 A93-54007 Experimental investigation into the mechanism of aircraft portholes p1191 A93-52937 Hypersonic shock-induced combustion ramjet discrete frequency noise (DFN) generation from a NACA IMAGE ANALYSIS performance analysis 0012 blade p1225 A93-53194 [ISABE 93-7037] p1197 A93-54013 Passive range estimation for rotorcraft low-altitude The leading edge vortex of a rotating stall cell ISOPARAMETRIC FINITE ELEMENTS flight p1190 A93-52881 [ISABE 93-7009] p1183 A93-53985 IMAGE PROCESSING A nonlinear finite element of an arbitrary beam KELVIN-HELMHOLTZ INSTABILITY Terrain modeling for real-time photo-texture based visual p 1215 A93-52939 Kelvin-Helmholtz wave generation beneath hovercraft simulation ISOTHERMAL FLOW skirts p1219 A93-53820 [AIAA PAPER 93-3607] p 1214 A93-52667 Determination of heat transfer to flow in a duct with a A radar altitude and line of sight attachment pseudodiscontinuity p 1179 A93-53365 KINETIC ENERGY [AIAA PAPER 93-3587] p 1223 A93-52680 A study on 3-D velocity distribution of isothermal flows Thrust imparted to an airfoil by passage through a Texture as a visual cueing element in computer image behind an afterburner flame stabilizer sinusoidal upwash field p 1178 A93-53219 generation. I - Representation of the sea surface [ISABE 93-7039] p1197 A93-54015 Analytical expression of dissipation integral for kinetic [AIAA PAPER 93-3560] p 1214 A93-52695 Isothermal flow characteristics behind V-shape gutter energy integral equation — calculation of turbulent IMPACT TESTS with and without injection compressible boundary layer in aerodynamics The application of diffusion bonding in the manufacture [ISABE 93-7040] p1198 A93-54016 p1183 A93-53860 of aeroengine components p 1217 A93-53514 The energy dissipation in a rotating stall cell INFLATABLE STRUCTURES [ISABE 93-7010] p1183 A93-53986 The fluid physics of parachute inflation P1189 A93-54347 INJURIES JET ENGINES Estimation of the parameters of the electrodynamic Air carriers' liability for passenger injury or death - The system engine-exhaust jet p 1193 A93-52965 Japanese Initiative and Response to the recent EC LAMINAR FLOW Initial results from the NASA Lewis wave rotor Consultation Paper p 1226 A93-52930 Multigrid Navier-Stokes calculations for experiment INLET FLOW three-dimensional cascades p1177 A93-53209 [AIAA PAPER 93-2521 ] p 1193 A93-53589 A study of the stability of vortical structures in supersonic 3D laminar and 2D turbulent computations with the inlets The design and development of an afterburner Navier-Stokes solver FLU3M [ISABE 93-7103] p1187 A93-54079 [ISABE 93-7041] p1198 A93-54017 [ONERA, TP NO. 1993-105] p1180 A93-53618 Off-design performance of scramjet nozzles Performance and configuration analysis of jet-engine Reynolds number dependence of the drag coefficient (ISABE 93-7108] p 1203 A93-54084 off-design behavior for laminar flow through fine-scale photoetched screens INLET PRESSURE (ISABE 93-7087] p 1202 A93-54063 p 1218 A93-53815 Investigation of the flow field through a variable pitch JET FLOW A finite element code for gas turbine combustor flow fan rotor with an inlet total pressure distortion Construction of wakes in the discrete vortex method with Stretched Laminar Flamelet modelling [ISABE 93-7029] p1184 A93-54005 p1179 A93-53333 [ISABE 93-7127] p 1204 A93-54102 INLET TEMPERATURE Blowout of turbulent disc/pilot stabilized jet diffusion LAMINATES Initial results from the NASA Lewis wave rotor flames Nonlinear deformation mechanics of multilayer experiment [ISABE 93-7026] p 1213 A93-54002 transparency elements - Some calculation results — for [AIAA PAPER 93-2521 ] p1193 A93-53589 Observation of fluctuation of 2D-nozzle flows aircraft portholes p1191 A93-52937 Heat transfer and material temperature conditions in the [ISABE 93-7110] p 1204 A93-54086 Flutter analysis of stiffened laminated composite plates and shells in supersonic flow p 1216 A93-53224 leading edge area of impingement-cooled turbine vanes Mixing of multiple jets with a confined subsonic LANDING GEAR [ISABE 93-7076] p 1220 A93-54052 crossflow p1189 A93-54324 INTEGRAL EQUATIONS A study of damage tolerance of the landing gear JET IMPINGEMENT Analytical expression of dissipation integral for kinetic structure p 1219 A93-53881 Heat transfer and material temperature conditions in the energy integral equation — calculation of turbulent LANDING INSTRUMENTS leading edge area of impingement-cooled turbine vanes compressible boundary layer in aerodynamics A vision-based method for autonomous landing [ISABE 93-7076] p 1220 A93-54052 P1183 A93-53860 P1190 A93-53172 INTEGRAL TRANSFORMATIONS Fluid dynamics and convective heat transfer in impinging LASER ANEMOMETERS A method for the spectral-time identification of the jets through implementation of a high resolution liquid Experimental analysis of turbine rotor flow at design and longitudinal and lateral motions of an aircraft crystal technique off-design conditions p 1205 A93-52942 [ISABE 93-7077] p 1220 A93-54053 [ISABE 93-7092] p1186 A93-54068 INTERACTIONAL AERODYNAMICS Impingement cooling with film coolant extraction in the LASER CUTTING Active aerodynamic control of wake-airfoil interaction airfoil leading edge regions Case studies - Applications of laser systems for cutting noise - Experiment p 1225 A93-53206 [ISABE 93-7078] p 1220 A93-54054 and welding aerospace parts p 1217 A93-53498 Analytical expression of dissipation integral for kinetic JET MIXING FLOW LASER DOPPLER VELOCIMETERS energy integral equation — calculation of turbulent Streamwise vorticity generation and mixing Isothermal flow characteristics behind V-shape gutter compressible boundary layer in aerodynamics enhancement in free jets by 'delta-tabs' with and without injection p1183 A93-53860 (AIAA PAPER 93-3253] p1180 A93-53592 [ISABE 93-7040] p1198 A93-54016

A-11 LASER INDUCED FLUORESCENCE SUBJECT INDEX

Large eddy simulation of turbulent combustion behind LIQUID ROCKET PROPELLANTS METHANE flame holders Nozzle effects on linear stability behaviour of A study of self-ignition of methane-hydrogen mixture fuel (ISABE 93-70421 p1198 A93-54018 combustors injected into high enthalpy supersonic airstreams LASER INDUCED FLUORESCENCE [ ISABE 93-7044 J p1198 A93-54020 [ISABE 93-7049] p 1213 A93-54025 LIF visualization of 3-dimensional hypersonic mixing LIQUID-VAPOR INTERFACES Studies on methane-fuel ram combustor for HST [ISABE 93-71141 p 1221 A93-54089 Kelvin-Helmholtz wave generation beneath hovercraft combined cycle engine LASER INTERFEROMETRY skirts p 1219 A93-53820 [ISABE 93-7080] p 1201 A93-54056 A study of optical distortions arising in radiation LOCAL AREA NETWORKS MICROBURSTS (METEOROLOGY) transmission through cavities with gas flow around them Pseudo Aircraft Systems - A multi-aircraft simulation Case study of a low-reflectivity pulsating microburst - p 1225 A93-52945 system for air traffic control research Numerical simulation of the Denver, 8 July 1989, storm LASER WELDING [AIAA PAPER 93-3585] p 1209 A93-52679 p 1222 A93-52898 Case studies - Applications of laser systems for cutting LONGITUDINAL CONTROL MICROWAVE LANDING SYSTEMS and welding aerospace parts p 1217 A93-53498 A method for the spectral-time identification of the Fault tolerant navigation for aircraft landing LATERAL CONTROL longitudinal and lateral motions of an aircraft p1191 A93-53866 A method for the spectral-time identification of the p 1205 A93-52942 longitudinal and lateral motions of an aircraft MIDAIR COLLISIONS CRAASH - A coordinated collision avoidance system p 1205 A93-52942 Longitudinal closed-loop pilot/vehicle analysis of DFBW (ONERA, TP NO. 1993-84] p1191 A93-53604 LAY-UP aircraft during approach and landing Wet layup materials for repair of bismaleimide p 1206 A93-54277 MILITARY AIRCRAFT composites p 1212 A93-53451 LONGITUDINAL STABILITY Europe's new windtunnel p 1210 A93-54275 LEADING EDGE FLAPS An aerodynamic model for the longitudinal motion of MILITARY HELICOPTERS A preliminary investigation of the control of separated flight training devices p 1207 A93-54278 Royal Navy helicopter operations in the maritime flow by means of excitation p 1182 A93-53859 LOSSES environment p1190 A93-54290 LEADING EDGES Initial results from the NASA Lewis wave rotor Environmental effects of operations during Desert Preparation and characterization of continuous fiber experiment Shield/Desert Storm p1190 A93-54291 reinforced zirconium diboride matrix composites for a [AIAA PAPER 93-2521 ] p 1193 A93-53589 Royal Air Force support helicopters - Night operations leading edge material p1211 A93-53445 LOW ALTITUDE P1190 A93-54293 Wet layup materials for repair of bismaleimide Passive range estimation for rotorcraft low-altitude Avionic systems in support of covert helicopter composites p 1212 A93-53451 flight p1190 A93-52881 operations p1193 A93-54294 The leading edge vortex of a rotating stall cell LOW ASPECT RATIO WINGS LONGBOW - Force multiplier for continuous (ISABE 93-7009] p1183 A93-53985 Low aspect ratio wing code validation experiment operations p 1175 A93-54295 Heat transfer and material temperature conditions in the P1176 A93-53202 leading edge area of impingement-cooled turbine vanes MIXING LAYERS (FLUIDS) Aerodynamic characteristics of conical Streamwise vorticity generation and mixing [ISABE 93-7076] p 1220 A93-54052 triangular-planform wings of low aspect ratio in subsonic enhancement in free jets by 'delta-tabs' Impingement cooling with film coolant extraction in the stalled flow p1180 A93-53574 airfoil leading edge regions | AIAA PAPER 93-3253] p1180 A93-53592 LOW FREQUENCIES [ISABE 93-7078] p 1220 A93-54054 Effect of film cooling/regenerative cooling on scramjet Low-frequency combustion oscillations in a model Experimental investigation of boundary layer transition engine performances afterburner p 1193 A93-53702 on a flat plate with C4 leading edge [ISABE 93-7036] p1197 A93-54012 [ISABE 93-7123] p 1222 A93-54098 The low frequency aeroacoustics of buried nozzle Direct simulation of reacting fuel gas flows in a LEAKAGE systems p 1205 A93-54244 supersonic mixing layer Interconversion of two kinds of methods for cabin LOW REYNOLDS NUMBER | ISABE 93-7072] p 1201 A93-54048 Low-Reynolds-number k-epsilon model for unsteady leakage test p 1192 A93-53874 Enhanced fuel-air mixing in hypersonic engines turbulent boundary-layer flows p 1177 A93-53208 LEAR JET AIRCRAFT [ISABE 93-7115] p 1221 A93-54090 A rapid prototyping system for inflight simulation using MIXING LENGTH FLOW THEORY the Calspan Learjet 25 M Mixing of multiple jets with a confined subsonic [AIAA PAPER 93-3606] p1191 A93-52691 crossflow p1189 A93-54324 LEGAL LIABILITY MAN MACHINE SYSTEMS MOISTURE CONTENT Air carriers' liability for passenger injury or death - The Calculation of sandwich plates with polymer composite Japanese Initiative and Response to the recent EC Pilot evaluations of augmented flight simulator motion [AIAA PAPER 93-3580] p 1208 A93-52676 skins under conditions of high humidity Consultation Paper p 1226 A93-52930 p1215 A93-52968 LIFT MAN-COMPUTER INTERFACE Repair materials and processes for the MD-11 Transonic area rule about lifting configurations An evaluation of software tools for the design and P1183 A93-53868 development of cockpit displays Composite Tailcone p 1216 A93-53452 [AIAA PAPER 93-3593] p 1224 A93-52685 LIFT DRAG RATIO MOLTEN SALTS Effect of lift-to-drag ratio in pilot rating of the HL-20 MANEUVERABLE REENTRY BODIES Corrosion of ceramic matrix composites landing task p 1210 A93-53738 Analysis of a turning point problem in flight trajectory [ONERA, TP NO. 1993-82] p 1213 A93-53602 optimization p 1210 A93-52885 MOMENT DISTRIBUTION LIFTING BODIES MANNED SPACECRAFT Aerodynamic characteristics of the HL-20 Estimation of the effect of the longitudinal moment due Aerodynamic heating environment definition/thermal to the engine thrust on the mass of a subsonic passenger p1181 A93-53736 protection system selection for the HL-20 aircraft p 1191 A93-52954 LIFTING REENTRY VEHICLES P1181 A93-53739 Six-degree-of-freedom guidance and control-entry HL-20 computational fluid dynamics analysis MONTE CARLO METHOD analysis of the HL-20 p 1210 A93-53737 p1181 A93-53740 Direct simulation of reacting fuel gas flows in a Aerodynamic heating environment definition/thermal MARINE ENVIRONMENTS supersonic mixing layer protection system selection for the HL-20 Royal Navy helicopter operations in the maritime [ISABE 93-7072] p 1201 A93-54048 p1181 A93-53739 environment p 1190 A93-54290 MOTION PERCEPTION HL-20 computational fluid dynamics analysis MATHEMATICAL MODELS Pilot evaluations of augmented flight simulator motion p1181 A93-53740 Flight update of aerodynamic math model [AIAA PAPER 93-3580] p 1208 A93-52676 HL-20 operations and support requirements for the [AIAA PAPER 93-3596] p 1224 A93-52687 MOTION SIMULATION Personnel Launch System mission p 1210 A93-53745 MEASURING INSTRUMENTS The development of SIMONA - A simulator facility for LIGHT BEAMS Sensors with centroid based common sensing scheme advanced research into simulation techniques, motion Sensors with centroid basdd common sensing scheme and their multiplexing — fiber optic sensors in aircraft and system control and navigation systems technologies and their multiplexing — fiber optic sensors in aircraft and aircraft engine applications p 1192 A93-52994 [AIAA PAPER 93-3574] p 1208 A93-52670 MECHANICAL PROPERTIES aircraft engine applications p 1192 A93-52994 Simulation motion effect on single axis compensatory The characterization and development of materials for LINE OF SIGHT tracking advanced textile composites p1211 A93-53434 A radar altitude and line of sight attachment [AIAA PAPER 93-3579] p 1208 A93-52675 [AIAA PAPER 93-3587] p 1223 A93-52680 Repair materials and processes for the MD-11 Composite TailCOne p 1216 A93-53452 Pilot evaluations of augmented flight simulator motion LINEAR PROGRAMMING Evaluation of 2D ceramic matrix composites in [AIAA PAPER 93-3580] p 1208 A93-52676 Selection of a method for protecting aircraft gas turbine aeroconvect'rve environments p 1212 A93-53459 MULTIGRID METHODS engines against damage by foreign objects (Mathematical Origin of the carbon rich sliding interface in alkali models) p1193 A93-53554 Multigrid Navier-Stokes calculations for containing matrix-SiC nicalon fibre composites three-dimensional cascades p 1177 A93-53209 LINEAR QUADRATIC REGULATOR [ONERA. TP NO. 1993-77) p 1212 A93-53598 Linear quadratic tracking problems in Hilbert space - MULTIPLEXING MELTING Sensors with centroid based common sensing scheme Application to optimal active noise suppression Clean melting and the removal of defects from p 1224 A93-52763 and their multiplexing — fiber optic sensors in aircraft and aero-engine materials p 1217 A93-53503 aircraft engine applications p 1192 A93-52994 LIQUID CRYSTALS METAL BONDING Fluid dynamics and convective heat transfer in impinging Stress relaxation of low pressure plasma-sprayed MULTIPROGRAMMING jets through implementation of a high resolution liquid NiCrAlY alloys p1211 A93-52870 An advanced rotorcraft flight simulation model - Parallel crystal technique METAL FATIGUE implementation and performance analysis | ISABE 93-7077] p 1220 A93-54053 Clean melting and the removal of defects from [AIAA PAPER 93-3550] p 1222 A93-52654 LIQUID INJECTION aero-engine materials p 1217 A93-53503 MULTIVARIABLE CONTROL Observations of liquid jets injected into a highly METAL MATRIX COMPOSITES Design of limit-tracking systems incorporating a turbofan accelerated supersonic boundary layer Friction surfacing and linear friction welding engine with constant disturbances P1177 A93-53214 p 1217 A93-53499 [ISABE 93-7090] p 1203 A93-54066

A-12 SUBJECT INDEX PLASTIC AIRCRAFT STRUCTURES

N NONFLAMMABLE MATERIALS Study of a pulse ramjet based on twin valveless Development of MIL-H-53119, -54 C to 175 C combustors coupled to operate in antiphase NAP-OF-THE-EARTH NAVIGATION high-temperature nonflammable hydraulic fluid for Air [ISABE 93-7038] p1197 A93-54014 Passive range estimation for rotorcralt low-altitude Force systems p 1214 A93-54250 OUTLET FLOW flight p 1190 A93-52881 NONINTRUSIVE MEASUREMENT The effects of end-bend regulations of compressor blade NASA PROGRAMS LIF visualization of 3-dimensional hypersonic mixing on the outlet flow field Propulsion technology challenges for turn-of-the-century I ISABE 93-7114) p 1221 A93-54089 [ISABE 93-7033) p1185 A93-54009 commercial aircraft NONLINEAR SYSTEMS Transonic discharge flows around diffuser vanes from [ISABE 93-7003] p1194 A93-53980 Identification of nonlinear mechanical systems using a cenlrilugal impeller NASA SPACE PROGRAMS combined state and parameter evaluation [ISABE 93-7053] p1185 A93-54029 International aerospace STI p 1227 A93-53826 p 1224 A93-52732 Correlations for flow property variation at outlet of a NAVIER-STOKES EQUATION NONUNIFORM FLOW centrifugal impeller Numerical study of a delta planform with multiple jets An investigation of post stall transients and recoverability [ISABE 93-7054] p1185 A93-54030 in ground effect of axial compression systems OZONE DEPLETION [SAE PAPER 892283] p1176 A93-53200 [ISABE 93-7012] p1184 A93-53988 Engine technology challenges for a 21st Century Effective treatment of the singular line boundary problem NOZZLE DESIGN High-Speed Civil Transport for three-dimensional grids p 1177 A93-53204 Low-frequency combustion oscillations in a model (ISABE 93-7064] p 1200 A93-54040 Zonal-local solution method for the turbulent afterburner p1193 A93-53702 Navier-Stokes equations p 1177 A93-53205 Effect of nozzle design on the performance of a highly Multigrid Navier-Stokes calculations for loaded turbine stage three-dimensional cascades p 1177 A93-53209 [ISABE 93-7096] p 1203 A93-54072 Space marching calculations about hypersonic Optimization of afterbodies and engine nozzle by using P-51 AIRCRAFT configurations using a solution-adaptive mesh algorithm CFD methods Innovative bagging techniques on a composite P-51 P1177 A93-53212 [ISABE 93-7098] p1187 A93-54074 Mustang replica p 1191 A93-53405 Three-dimensional Navier-stokes/full-potential coupled Advanced aerodynamic airframe/nozzle integration PARACHUTE DESCENT analysis for viscous transonic flow p1178 A93-53218 [ISABE 93-7099) p1187 A93-54075 The fluid physics of parachute inflation 3D laminar and 2D turbulent computations with the Design of air intakes and nozzles for transonic rotational p1189 A93-54347 Navier-Stokes solver FLU3M flows PARACHUTE FABRICS IONERA, TP NO. 1993-105] p1180 A93-53618 [ISABE 93-7102] p1187 A93-54078 The fluid physics of parachute inflation Numerical solution of N-S equations for hypersonic flow Influence of chemical kinetics effects in nozzles shape p1189 A93-54347 over capsule-type vehicles p1182 A93-53858 design PARALLEL PROCESSING (COMPUTERS) Navier-Stokes computation of the three dimensional flow [ISABE 93-7112] p1188 A93-54087 An advanced rotorcraft flight simulation model - Parallel fields through a transonic fan blade NOZZLE FLOW implementation and performance analysis [ISABE 93-7030] p1184 A93-54006 Nozzle effects on linear stability behaviour of [AIAA PAPER 93-3550] p 1222 A93-52654 Navier-Stokes analysis of turbine flowfield and external combustors PARAMETER IDENTIFICATION heat transfer [ISABE 93-7044] p1198 A93-54020 Identification of nonlinear mechanical systems using [ISABE 93-7075] p1186 A93-54051 Off-design performance of scramjet nozzles combined state and parameter evaluation Recent developments performed at ONERA for the [ISABE 93-7108) p 1203 A93-54084 p 1224 A93-52732 simulation of 3D inviscid and viscous flows in Observation of fluctuation of 2D-nozzle flows A method for the spectral-time identification of the turbomachinery by the solution of Euler and Navier-Stokes [ISABE 93-7110] p 1204 A93-54086 longitudinal and lateral motions of an aircraft equations The low frequency aeroacoustics of buried nozzle p 1205 A93-52942 [ISABE 93-7094] p1186 A93-54070 systems p 1205 A93-54244 Estimation of the parameters of the electrodynamic Three-dimensional flow analysis inside turbomachinery NOZZLE GEOMETRY system engine-exhaust jet p 1193 A93-52965 stages with steady and unsteady Navier-Stokes method Advanced aerodynamic airframe/nozzle integration PASSENGER AIRCRAFT [ISABE 93-7095] p1186 A93-54071 [ISABE 93-7099] p1187 A93-54075 Estimation of the effect of the longitudinal moment due NAVIGATION INSTRUMENTS Influence of chemical kinetics effects in nozzles shape to the engine thrust on the mass of a subsonic passenger Fault tolerant navigation for aircraft landing design aircraft p 1191 A93-52954 P1191 A93-53866 [ISABE 93-7112] p 1188 A93-54087 PERFORATED PLATES NAVY Design and fabrication of panels with cutouts Two-dimensional and three-dimensional mixing flow p 1215 A93-52973 Royal Navy helicopter operations in the maritime structures with injected through slotted nozzle and circular environment p 1190 A93-54290 PERFORMANCE PREDICTION nozzle into supersonic flows NEURAL NETS How to consider simulation fidelity and validity for an [ISABE 93-7117] p 1221 A93-54092 Neural network fault diagnosis of a turbofan engine engineering simulator [ISABE 93-7091] p 1203 A93-54067 NOZZLE INSERTS [AIAA PAPER 93-3598] p 1209 A93-52688 NICKEL ALLOYS Streamwise vorticity generation and mixing Thermodynamic and neutral network computer enhancement in free jets by 'delta-tabs' Stress relaxation of low pressure plasma-sprayed modelling of implanted component faults in a gas turbine [AIAA PAPER 93-3253] p1180 A93-53592 NiCrAlY alloys p 1211 A93-52870 engine NIGHT FLIGHTS (AIRCRAFT) NUMERICAL INTEGRATION [ISABE 93-7089] p 1202 A93-54065 Royal Air Force support helicopters - Night operations The numerical errors in inverse simulation PERTURBATION THEORY p1190 A93-54293 [AIAA PAPER 93-3588] p 1223 A93-52681 Analysis of spatial motion dynamics of a helicopter for NIGHT VISION various models of the induced velocity field Royal Air Force support helicopters - Night operations p1191 A93-53721 P1190 A93-54293 PILOT PERFORMANCE NITRIC OXIDE A primary flight display for four-dimensional guidance Numerical study of nitric oxide formation in a hypersonic OBJECT-ORIENTED PROGRAMMING and navigation influence of tunnel size and level of ramjet engine Enhancing real-time flight simulation execution by additional information on pilot performance and control | ISABE 93-7125] p 1204 A93-54100 intercepting Run-Time Library calls behaviour NITROGEN OXIDES [AIAA PAPER 93-3591 ] p 1224 A93-52684 [AIAA PAPER 93-3570] p 1208 A93-52668 An ultra low NO(x) pilot combustor for staged low N0(x) Reusable code for helicopter simulation Simulation motion effect on single axis compensatory combustion [AIAA PAPER 93-3594] p 1224 A93-52686 tracking [ISABE 93-7020] p 1195 A93-53996 OBSTACLE AVOIDANCE [AIAA PAPER 93-3579] p 1208 A93-52675 Low NO(x) combustor development using aerodynamic Passive range estimation for rotorcraft low-altitude Effect of lift-to-drag ratio in pilot rating of the HL-20 staging flight p1190 A93-52881 landing task p 1210 A93-53738 [ISABE 93-7021] p1195 A93-53997 OCEAN SURFACE PILOT TRAINING The prediction of thermal NO(x) in gas turbine Texture as a visual cueing element in computer image Evolution of flight simulation exhausts generation. I - Representation of the sea surface [AIAA PAPER 93-3545] p 1207 A93-52652 [ISABE 93-7022] p1195 A93-53998 [AIAA PAPER 93-3560] p 1214 A93-52695 PITCHING MOMENTS NOISE MEASUREMENT Numerical analysis of a flat plate in a pitching motion. OPERATING TEMPERATURE II - Effect on the flow of the position of the pivot, etc Some acoustic features of perforated test section walls Studies on coolant problems in aeronautical turbine with splitter plates p 1226 A93-53222 p1181 A93-53798 cascades NOISE POLLUTION Investigation of the flow field through a variable pitch [ISABE 93-7074] p 1220 A93-54050 Air transport and the environment - Regulating aircraft fan rotor with an inlet total pressure distortion OPTIMAL CONTROL noise p 1226 A93-52931 [ISABE 93-7029] p1184 A93-54005 Linear quadratic tracking problems in Hilbert space - NOISE PREDICTION PLANE STRESS Application to optimal active noise suppression A dynamic stiffness/boundary element method for the A finite element for modeling skins of composite p 1224 A93-52763 prediction of interior noise levels p 1226 A93-53817 materials p 1215 A93-52979 NOISE REDUCTION OPTIMIZATION PLANFORMS Linear quadratic tracking problems in Hilbert space - Optimization of afterbodies and engine nozzle by using Numerical study of a delta planform with multiple jets Application to optimal active noise suppression CFD methods in ground effect p 1224 A93-52763 [ ISABE 93-7098] p1187 A93-54074 (SAE PAPER 892283) p1176 A93-53200 Noise reduction of supersonic heated jet with jet mixing ORBITAL MANEUVERS PLASMA SPRAYING enhancement by tabs Analysis of a turning point problem in flight trajectory Stress relaxation of low pressure plasma-sprayed [ISABE 93-7046] p1198 A93-54022 optimization p 1210 A93-52885 NiCrAlY alloys P1211 A93-52870 NONEOUILIBRIUM FLOW OSCILLATING FLOW PLASTIC AIRCRAFT STRUCTURES Recent advances in computational analysis of Production of oscillatory flow in wind tunnels An experimental study of reinforced panels of composite hypersonic vehicles p1179 A93-53364 p 1218 A93-53812 materials p 1215 A93-52975

A-13 PLUMES SUBJECTINDEX

PLUMES PRODUCT DEVELOPMENT Numerical study of nitric oxide formation in a hypersonic Measurement and prediction of flow in a gas turbine Engineering simulators enhance 777 development ramjet engine engine exhaust plume p1192 A93-53771 [ISABE 93-7125] p 1204 A93-54100 [ ISABE 93-7113 ] p 1204 A93-54088 Removing the risk from rotorcraft testing RANGEFINDING POLYIMIDES p1192 A93-53772 Passive range estimation for rotorcraft low-altitude Structural applications of Avimid K3B LDF thermoplastic PROGRAM VERIFICATION (COMPUTERS) flight p1190 A93-52881 composites — for advanced aircraft Low aspect ratio wing code validation experiment REACTING FLOW p 1216 A93-53429 p1176 A93-53202 Comparison of gasdynamic models in hypersonic flow POLYMER MATRIX COMPOSITES p1179 A93-53315 PROPELLER FANS Calculation of sandwich plates with polymer composite Direct simulation of reacting fuel gas flows in a Laser velocimeter measurements of the flow field skins under conditions of high humidity supersonic mixing layer generated by a forward-swept propfan during flutter P1215 A93-52968 [ISABE 93-7072] p 1201 A93-54048 [AIAA PAPER 93-2919] p1180 A93-53591 Overview of NASA's advanced high temperature engine Numerical study of nitric oxide formation in a hypersonic PROPULSION materials technology program p 1212 A93-53453 ramjet engine POROUS WALLS A parameter optimization approach to controller [ISABE 93-7125] p 1204 A93-54100 partitioning for integrated flight/propulsion control Some acoustic features of perforated test section walls REACTION KINETICS with splitter plates p 1226 A93-53222 application p 1206 A93-S4268 Numerical simulation of ramjet and scramjet combustion POSITION (LOCATION) PROPULSION SYSTEM CONFIGURATIONS using two-dimensional Euler equations with finite rate Representation of vehicle location in networked New developments with the V2500 engine chemistry simulations [ISABE 93-7085] p 1202 A93-54061 [ISABE 93-7083) p 1202 A93-54059 [AIAA PAPER 93-3582] p 1214 A93-52677 Evaluation of turboramjet exhaust systems from scale Finite-rate H2/air combustion effects in CRJ for POWER EFFICIENCY model test data hypersonic launchers The combined effect of clearances and peripheral [ISABE 93-7109] p 1204 A93-54085 [ISABE 93-7084] p 1202 A93-54060 overlaps on the efficiency of microturbines with shroudless Compact heat exchanger fitted to engines of the inverted Influence of chemical kinetics effects in nozzles shape rotors p1193 A93-52963 type design POWER LOSS [ISABE 93-7120] p 1221 A93-S4095 [ISABE 93-7112] p1188 A93-54087 The flow lag angle in the rotor of a centrifugal compressor PROPULSION SYSTEM PERFORMANCE A finite element code for gas turbine combustor flow with allowance for viscosity effects Complementary role of ground testing, flight testing, and with Stretched Laminar Flamelet modelling p1179 A93-53555 computations in aerospace plane propulsion [ISABE 93-7127] p 1204 A93-54102 PRANDTL-MEYER EXPANSION development REAL TIME OPERATION Observations of liquid jets injected into a highly [ISABE 93-7034] p1197 A93-54010 A high fidelity video delivery system for real-time flight accelerated supersonic boundary layer Performance and configuration analysis of jet-engine simulation research P1177 A93-53214 off-design behavior [AIAA PAPER 93-3558] p 1214 A93-52659 PRECOOLING [ISABE 93-7087] p 1202 A93-54063 Terrain modeling for real-time photo-texture based visual Characteristics of heat exchanger in simulation Thermodynamic and neutral network computer supersonic/subsonic flows [AIAA PAPER 93-3607] p 1214 A93-52667 modelling of implanted component faults in a gas turbine [ISABE 93-7119] p 1221 A93-54094 Development and operation of a real-time simulation at engine PREFORMS the NASA Ames Vertical Motion Simulator [ISABE 93-7089] p 1202 A93-54065 3-D braided preforms; cost to manufacture: [AIAA PAPER 93-3575] p 1208 A93-52671 Experimental analysis of turbine rotor flow at design and Magnaweave. I - Identifying cost factors Enhancing real-time flight simulation execution by off-design conditions intercepting Run-Time Library calls p 1226 A93-53423 [ ISABE 93-7092 ] p 1186 A93-54068 PREMIXED FLAMES [AIAA PAPER 93-3591] p 1224 A93-52684 Effect of nozzle design on the performance of a highly The prediction of thermal NO(x) in gas turbine Development of a real time dynamic engine simulation loaded turbine stage exhausts model of a turbo fan engine [ISABE 93-7096] p 1203 A93-54072 [ISABE 93-7022] p1195 A93-53998 [ISABE 93-7132] p 1205 A93-54107 PROTECTIVE COATINGS Large eddy simulation of turbulent combustion behind RECTANGULAR WINGS 'No VOC' water-borne corrosion resistant primers for flame holders Unsteady aerodynamic characteristics of three aerospace bonding applications p1211 A93-53419 [ISABE 93-7042] p1198 A93-54018 rectangular wings of different aspect ratios PROTOTYPES P1180 A93-53575 PREPREGS A rapid prototyping system for inflight simulation using REENTRY VEHICLES The characterization and development of materials for the Calspan Learjet 25 Numerical solution of N-S equations for hypersonic flow advanced textile composites p 1211 A93-53434 [AIAA PAPER 93-3606] p1191 A93-52691 The properties of newly developed highly damage over capsule-type vehicles p1182 A93-53858 tolerant and easy handleable carbon fiber/modified REFLECTANCE bismaleimide prepreg system p 1212 A93-53448 Case study of a low-reflectivity pulsating microburst - Numerical simulation of the Denver, 8 July 1989, storm Wet layup materials for repair of bismaleimide p 1222 A93-52898 composites p 1212 A93-53451 RADAR TRACKING Flight safety in Europe p 1227 A93-53726 REGENERATIVE COOLING Repair materials and processes for the MD-11 Effect of film cooling/regenerative cooling on scramjet Composite Tailcone p 1216 A93-53452 RADIAL FLOW The combined effect of clearances and peripheral engine performances PRESSURE DISTRIBUTION overlaps on the efficiency of microturbines with shroudless [ISABE 93-7036] p1197 A93-54012 Pressure distribution measurement around hypersonic rotors p 1193 A93-52963 REINFORCED PLATES delta winged semicone - Measurement by means of RADIANT COOLING Calculation of sandwich plates with polymer composite magnet tape p 1176 A93-53193 Heat loads as key problem of hypersonic flight skins under conditions of high humidity Moving wall effects in transverse subsonic flow past a p 1222 A93-54276 p 1215 A93-52968 rotating cylinder P1179 A93-53573 RADIATION DISTRIBUTION An experimental study of reinforced panels of composite PRESSURE DROP A study of optical distortions arising in radiation materials p 1215 A93-52975 The development of a new air filtration system for the transmission through cavities with gas flow around them Flutter analysis of stiffened laminated composite plates Alouette III helicopter p 1225 A93-52945 and shells in supersonic flow p 1216 A93-53224 [ISASE 93-7048] p1199 A93-54024 RAMAN SPECTRA Reinforcement of the F-111 wing pivot fitting with a PRESSURE GRADIENTS CARS temperature measurements in combustion boron/epoxy doubter system - Materials engineering The reduction of skin friction by riblets under the [ONERA, TP NO. 1993-78] p 1212 A93-53599 aspects p 1214 A93-54241 influence of an adverse pressure gradient RAMJET ENGINES REINFORCED SHELLS p1218 A93-53810 High temperature heat exchangers for gas turbines and A finite element for modeling skins of composite PRESSURE MEASUREMENT future hypersonic air breathing propulsion materials p 1215 A93-52979 Boundary layer and pressure measurements on a [ONERA, TP NO. 1993-75] p 1218 A93-53596 Flutter analysis of stiffened laminated composite plates cylinder with unsteady circulation control CFD for ramjet and scramjet powered vehicles and shells in supersonic flow p 1216 A93-53224 p1177 A93-53207 [ISABE 93-7035] p1197 A93-54011 REINFORCEMENT (STRUCTURES) PRESSURE OSCILLATIONS Hypersonic shock-induced combustion ramjet An experimental study of reinforced panels of composite Production of oscillatory flow in wind tunnels performance analysis materials p 1215 A93-52975 p 1218 A93-53812 [ISABE 93-7037] p1197 A93-54013 RELAXATION METHOD (MATHEMATICS) Study of a pulse ramjet based on twin valveless Investigation of the flow field through a variable pitch Upwind-biased, point-implicit relaxation strategies for combustors coupled to operate in antiphase fan rotor with an inlet total pressure distortion hypersonic flowfield simulations on supercomputers [ISABE 93-7038] p1197 A93-54014 [ISABE 93-7029] p1184 A93-54005 P1175 A93-52770 The combustion performance of methane-fueled ram PRIMERS (COATINGS) RESCUE OPERATIONS combustor Red-hot simulation p 1209 A93-53774 'No VOC' water-borne corrosion resistant primers for [ISABE 93-7079] p 1201 A93-54055 Operating helicopters in a demanding environment - aerospace bonding applications p1211 A93-53419 Studies on methane-fuel ram combustor for HST Mountain flying/high evaluations p 1190 A93-54289 Evaluation of water-borne adhesive bonding primers for combined cycle engine use on the advanced aircraft material aluminum-lithium [ISABE 93-7080] p 1201 A93-54056 RESEARCH AND DEVELOPMENT p1211 A93-53420 Test results of the hydrogen fueled model combustor International aerospace STI p 1227 A93-53826 PRISMS for the air turbo ramjet engine Research and development of aircraft engine in Japan Prismatic grid generation for three-dimensional complex [ISABE 93-7082] p 1201 A93-54058 - Historical review geometries p1178 A93-53217 Numerical simulation of ramjet and scramjet combustion [ISABE 93-7000] p 1227 A93-53977 PROBABILITY DENSITY FUNCTIONS using two-dimensional Euler equations with finite rate Japan's research and development program for Design for cyclic loading endurance of composites chemistry airbreathing engine technologies p 1216 A93-53395 [ISABE 93-7083] p 1202 A93-54059 [ISABE 93-7005] p1194 A93-53981

A-14 SUBJECT INDEX SPRAYERS

Development study on Air Turbo Ramjet engine for a Tip clearance effects on the flow field of an axial turbine SHOCK WAVE INTERACTION future space plane rotor blade cascade Analysis of unstarted supersonic flutter in cascade by IISABE 93-7016] p1195 A93-53992 [ISABE 93-7057] p1185 A93-54033 semiactuator disk theory p 1181 A93-53841 Research and development of a turbo-accelerator for ROTORCRAFT AIRCRAFT A study of the stability of vortical structures in supersonic super/hypersonic transport An advanced rotorcraft flight simulation model - Parallel inlets IISABE 93-7066] p 1200 A93-54042 implementation and performance analysis (ISABE 93-7103] p1187 A93-54079 RESEARCH FACILITIES (AIAA PAPER 93-3550) P 1222 A93-52654 SHOCK WAVE PROFILES The development ol SIMONA - A simulator facility for Removing the risk from rotorcraft testing Shock shapes around slender diamond cones traveling advanced research into simulation techniques, motion p1192 A93-53772 at hypersonic speed p 1181 A93-53840 system control and navigation systems technologies ROTORS SILICON CARBIDES [AIAA PAPER 93-3574] p 1208 A93-52670 Identification of nonlinear mechanical systems using Origin of the carbon rich sliding interface in alkali RESPONSE TIME (COMPUTERS) combined state and parameter evaluation containing matrix-SiC nicalon fibre composites Dynamic simulation fidelity improvement using transfer p 1224 A93-52732 [ONERA, TP NO. 1993-77] p 1212 A93-53598 function state extrapolation Initial results from the NASA Lewis wave rotor SILICONES (AIAA PAPER 93-3552] p 1222 A93-52656 experiment Innovative bagging techniques on a composite P-51 REYNOLDS NUMBER |AIAA PAPER 93-25211 p 1193 A93-53589 Mustang replica p1191 A93-53405 Reynolds number dependence of the drag coefficient RUN TIME (COMPUTERS) SKEWNESS for laminar flow through fine-scale photoetched screens Enhancing real-time flight simulation execution by Performance improvement by forward-skewed blading p 1218 A93-53815 intercepting Run-Time Library calls of axial fan moving blades RIBLETS [AIAA PAPER 93-3591 ] p 1224 A93-52684 [ISABE 93-7055] p1185 A93-54031 The reduction of skin friction by riblets under the SKIN (STRUCTURAL MEMBER) influence of an adverse pressure gradient A finite element for modeling skins of composite p 1218 A93-53810 materials p 1215 A93-52979 ROBOTICS SKIN FRICTION Various applications of robots in aircraft engine SANDS Low-Reynolds-number k-epsilon model for unsteady overhaul The chemistry of Saudi Arabian sand - A deposition turbulent boundary-layer flows p1177 A93-53208 IISABE 93-7129] p1175 A93-54104 problem on helicopter turbine airfoils Skin-friction topology over a surface mounted p 1216 A93-53468 ROBOTS semi-ellipsoidal wing at incidence p 1178 A93-53216 Various applications of robots in aircraft engine Environmental effects of operations during Desert The reduction of skin friction by riblets under the overhaul Shield/Desert Storm p1190 A93-54291 influence of an adverse pressure gradient [ISABE 93-7129] p1175 A93-54104 The T700 ... from salt spray to sand blast p1218 A93-53810 p 1205 A93-54292 ROTARY WING AIRCRAFT SLENDER BODIES Passive range estimation for rotorcraft low-altitude SANDWICH STRUCTURES Study on flow field around slender diamond cone flight p1190 A93-52881 Calculation of sandwich plates with polymer composite traveling at hypersonic speed p 1189 A93-54314 ROTARY WINGS skins under conditions of high humidity SLENDER CONES p1215 A93-52968 Calculation of the position of the flow separation line Shock shapes around slender diamond cones traveling in an analog model of flow past a body SAUDI ARABIA at hypersonic speed p1181 A93-53840 The chemistry of Saudi Arabian sand - A deposition P1176 A93-52958 SLIDING ROTATING CYLINDERS problem on helicopter turbine airfoils Origin of the carbon rich sliding interface in alkali p 1216 A93-53468 Moving wait effects in transverse subsonic flow past a containing matrix-SiC nicalon fibre composites rotating cylinder p1179 A93-53573 SCALE MODELS [ONERA. TP NO. 1993-77] p 1212 A93-53598 Semi-full-scale dynamic simulation complex on the basis ROTATING FLUIDS SOFTWARE ENGINEERING Effect of rotation on heat transfer and hydraulic of centrifuge Initial development of a research flight simulator [AIAA PAPER 93-3577] p 1208 A93-52673 resistance in the radial cooling channels of turbine rotor software blades p 1215 A93-52950 Instrumentation and telemetry systems for free-flight (AIAA PAPER 93-3590] p 1223 A93-52683 Design of air intakes and nozzles for transonic rotational drop model testing p 1209 A93-52754 SOFTWARE REUSE flows Evaluation of turborarnjet exhaust systems from scale Reusable code for helicopter simulation [ISABE 93-7102] p1187 A93-54078 model test data [AIM PAPER 93-3594] p 1224 A93-52686 ROTATING STALLS (ISABE 93-7109] p 1204 A93-54085 SOFTWARE TOOLS Study on surge and rotating stall in axial compressors. Observation of fluctuation of 2D-nozzle flows An evaluation of software tools for the design and Ill - Numerical model for multiblade-row compressors [ISABE 93-7110] p 1204 A93-54086 development of cockpit displays p1181 A93-53799 SECONDARY FLOW [AIM PAPER 93-3593] p 1224 A93-52685 Numerical study on inception of stall cells in rotating The combined effect of clearances and peripheral SOLAR RADIATION stall overlaps on the efficiency of microturbines with shroudless Environmental effects of operations during Desert [ISABE 93-7007] p1183 A93-53983 rotors p1193 A93-52963 Shield/Desert Storm p1190 A93-54291 Some measurements of stall in an axial impeller The effects of end-bend regulations of compressor blade SOLID-SOLID INTERFACES [ISABE 93-7008] p1183 A93-53984 on the outlet flow field Origin of the carbon rich sliding interface in alkali The leading edge vortex of a rotating stall cell [ISABE 93-7033] p1185 A93-54009 containing matrix-SiC nicalon fibre composites [ISABE 93-7009] p1183 A93-53985 [ONERA, TP NO. 1993-77] p 1212 A93-53598 Performance improvement by forward-skewed blading The energy dissipation in a rotating stall cell SOUND WAVES of axial fan moving blades [ISABE 93-7010] p 1183 A93-53986 Acoustic-wave propagation in ducts and free-field [ ISABE 93-7055] p1185 A93-54031 Review of stall, surge and active control in axial radiation compressors Effects of wake interaction of two turbine cascades on [ONERA, TP NO. 1993-103] p 1226 A93-53616 [ISABE 93-7011] p1184 A93-53987 secondary/tip-leakage flows and losses Low-frequency combustion oscillations in a model [ISABE 93-7058] p1185 A93-54034 An investigation of post stall transients and recoverability afterburner p 1193 A93-53702 of axial compression systems SEPARATED FLOW SPACE TRANSPORTATION [ISABE 93-701?] p1184 A93-53988 Calculation of the position of the flow separation line HL-20 operations and support requirements for the ROTOR AERODYNAMICS in an analog model of flow past a body Personnel Launch System mission p 1210 A93-53745 The combined effect of clearances and peripheral p1176 A93-52958 SPACECRAFT CONTROL overlaps on the efficiency of microturbines with shroudless Moving wall effects in transverse subsonic flow past a Six-degree-of-freedom guidance and control-entry rotors p 1193 A93-52963 rotating cylinder p 1179 A93-53573 analysis of the HL-20 p 1210 A93-53737 The flow lag angle in the rotor of a centrifugal compressor A preliminary investigation of the control of separated SPACECRAFT DESIGN with allowance for viscosity effects flow by means of excitation p 1182 A93-53859 HL-20 operations and support requirements for the P1179 A93-53555 SERVICE LIFE Personnel Launch System mission p 1210 A93-53745 Laser velocimeter measurements of the flow field Durability properties for adhesively bonded structural SPACECRAFT GUIDANCE generated by a forward-swept preplan during flutter aerospace applications p 1217 A93-53515 Six-degree-of-freedorr. guidance and control-entry [AIAA PAPER 93-2919] p1180 A93-53591 Selection of a method for protecting aircraft gas turbine analysis of the HL-20 p 1210 A93-53737 Numerical study on inception of stall cells in rotating engines against damage by foreign objects (Mathematical SPACECRAFT LANDING stall models) p 1193 A93-53554 Effect of lift-to-drag ratio in pilot rating of the HL-20 [ ISABE 93-7007 ] p 1183 A93-53983 landing task p 1210 A93-53738 SHEAR FLOW SPACECRAFT STRUCTURES Effects of blade geometry and mode shape on fan Direct simulation of reacting fuel gas flows in a flutter Evaluation of water-borne adhesive bonding primers for supersonic mixing layer use on the advanced aircraft material aluminum-lithium [ISABE 93-7028] p 1196 A93-54004 [ISABE 93-7072] p 1201 A93-54048 Investigation of the flow field through a variable pitch p1211 A93-53420 fan rotor with an inlet total pressure distortion SHEAR LAYERS SPATIAL MARCHING [ISABE 93-7029] p 1184 A93-54005 Enhanced fuel-air mixing in hypersonic engines Space marching calculations about hypersonic [ISABE 93-7115] p 1221 A93-54090 Navier-Stokes computation of the three dimensional flow configurations using a solution-adaptive mesh algorithm fields through a transonic fan blade SHELL STABILITY P1177 A93-53212 [ISABE 93-7030] p1184 A93-54006 A procedure for the thermal and strength testing of SPECIFIC IMPULSE ROTOR BLADES radiotransparent shells p 1209 A93-52976 Energy management — aircraft propulsion system New approximate method of stress analysis for bladed SHOCK LAYERS performance rotating discs Application of the small parameter method to the [ISABE 93-7019] p1195 A93-53995 [ISABE 93-7059] p 1219 A93-54035 problem of three-dimensional flow of a viscous gas past SPRAYERS ROTOR BLADES (TURBOMACHINERY) bodies p1178 A93-53314 A Eulerian/Lagrangian modelling to calculate the Some measurements of stall in an axial impeller Comparison of gasdynamic models in hypersonic flow evolution of a water droplets spray [ISABE 93-7008] p1183 A93-53984 p1179 A93-53315 [ISABE 93-7121] p 1221 A93-54096

A-15 STAGNATION PRESSURE SUBJECT INDEX

STAGNATION PRESSURE SUPERSONIC AIRCRAFT SUPERSONIC JET FLOW Initial results from the NASA Lewis wave rotor Wet layup materials for repair of bismaleimide Streamwise vorticity generation and mixing experiment composites p 1212 A93-53451 enhancement in free jets by 'delta-tabs' [AIAA PAPER 93-25211 p 1193 A93-53589 SUPERSONIC BOUNDARY LAYERS [AIAA PAPER 93-3253] p1180 A93-53592 STATE ESTIMATION Observations of liquid jets injected into a highly Numerical study of supersonic flow over a backward Fault tolerant navigation for aircraft landing accelerated supersonic boundary layer step with transverse injection p1182 A93-53853 p1191 A93-53866 P1177 A93-53214 Noise reduction of supersonic heated jet with jet mixing STATORS SUPERSONIC COMBUSTION enhancement by tabs Characterisation of conventional and controlled diffusion Determination of heat transfer to flow in a duct with a [ISABE 93-7046] p1198 A93-54022 stator blades in a transonic compressor stage pseudodiscontinuity p 1179 A93-53365 SUPERSONIC NOZZLES [ISABE 93-7124] p1189 A93-54099 A study of self-ignition of methane-hydrogen mixture fuel Influence of chemical kinetics effects in nozzles shape STEADY FLOW injected into high enthalpy supersonic airstreams design Three-dimensional flow analysis inside turbomachinery [ISABE 93-7112] p1188 A93-54087 [ISABE 93-7049] p 1213 A93-54025 stages with steady and unsteady Navier-Stokes method SUPERSONIC TRANSPORTS Tandem transverse hydrogen gas injection into a [ISABE 93-7095] p1186 A93-54071 Research and development of a turbo-accelerator for supersonic airflow STREAM FUNCTIONS (FLUIDS) super/hypersonic transport The streamline throughllow method of axial [ISABE 93-7069] p 1201 A93-54045 [ISABE 93-7066] p 1200 A93-54042 turbomachinery flow analysis SUPERSONIC COMBUSTION RAMJET ENGINES Material requirements for the High Speed Civil [ISABE 93-7031] p1184 A93-54007 CFD for ramjet and scramjet powered vehicles Transport STRESS ANALYSIS [ ISABE 93-7035 ] p 1197 A93-54011 I ISABE 93-7067] p 1200 A93-54043 New approximate method of stress analysis for bladed Effect of film cooling/regenerative cooling on scramjet Research and development of high pressure compressor rotating discs engine performances for SST and HST engine [ISABE 93-7059] p 1219 A93-54035 (ISABE 93-7036] p1197 A93-54012 [ISABE 93-7068] p 1186 A93-54044 STRESS RELAXATION Ignition and combustion performance of a scramjet Studies on methane-fuel ram combustor for HST Stress relaxation of low pressure plasma-sprayed combustor with a fuel injection strut combined cycle engine NiCrAlY alloys p 1211 A93-52870 | ISABE 93-7050] p1199 A93-54026 [ISABE 93-7080] p 1201 A93-54056 STRESS-STRAIN RELATIONSHIPS Study on unstart and its propagation along modules due A study on Mach 3 two-dimensional mixed compression Nonlinear deformation mechanics of multilayer to compound choking and/or fluctuations in combustor air-intakes transparency elements - Some calculation results — for of scramjet engines [ISABE 93-71C6] p 1188 A93-54082 aircraft portholes p1191 A93-52937 [ISABE 93-7052] p1199 A93-54028 SURFACE FINISHING Calculation of sandwich plates with polymer composite Application of functionally gradient materials to scramjet Evaluation of water-borne adhesive bonding primers for skins under conditions of high humidity engines use on the advanced aircraft material aluminum-lithium p 1215 A93-52968 [ISABE 93-7063] p 1200 A93-54039 p1211 A93-53420 STROUHAL NUMBER Numerical simulation of ramjet and scramjet combustion SURFACE TEMPERATURE Evaluation of 2D ceramic matrix composites in Unsteady aerodynamic characteristics of three using two-dimensional Euler equations with finite rate rectangular wings of different aspect ratios chemistry aeroconvective environments p 1212 A93-53459 P1180 A93-53575 [ISABE 93-7083] p 1202 A93-54059 SWEPT WINGS STRUCTURAL ANALYSIS Calculation of a compressible three-dimensional Starting characteristics of scramjet inlets Structural integrity validation of limited-life engines boundary layer on a swept wing p 1179 A93-53551 [ISABE 93-7105] p 1203 A93-54081 [ISABE 93-7131] p 1205 A93-54106 Calculation of flow fields near a lifting wing STRUCTURAL DESIGN Numerical simulation of a two-dimensional supersonic P1179 A93-53552 Axial flow compressors - Mechanical design trends mixed-compression inlet SWIRLING [ISABE 93-7061] p1199 A93-54037 [ISABE 93-7107] p1188 A93-54083 Low NO(x) combustor development using aerodynamic Structural integrity validation of limited-life engines Off-design performance of scramjet nozzles staging [ISABE 93-7131] p 1205 A93-54106 [ISABE 93-7108] p 1203 A93-54084 [ISABE 93-7021] p1195 A93-53997 STRUCTURAL ENGINEERING SUPERSONIC COMMERCIAL AIR TRANSPORT Active control of vortex breakdown by a spinning wave Structural integrity validation of limited-life engines Engine technology challenges for a 21st Century generator [ ISABE 93-7131] p 1205 A93-54106 High-Speed Civil Transport [ISABE 93-7045] p 1219 A93-54021 STRUCTURAL RELIABILITY [ISABE 93-7064] p 1200 A93-54040 SYSTEM IDENTIFICATION The T700 ... from salt spray to sand blast SUPERSONIC FLOW Identification of nonlinear mechanical systems using P1205 A93-54292 Flutter analysis of stiffened laminated composite plates combined state and parameter evaluation STRUCTURAL STABILITY and shells in supersonic flow p 1216 A93-53224 p1224 A93-52732 An experimental study of reinforced panels of composite Tandem transverse hydrogen gas injection into a SYSTEMS ENGINEERING materials p 1215 A93-52975 supersonic airflow Transport delay compensation - An inexpensive A study of damage tolerance of the landing gear [ISABE 93-7069] p 1201 A93-54045 alternative to increasing image generator update rate structure p 1219 A93-53881 Direct simulation of reacting fuel gas flows in a [AIAA PAPER 93-3563] p 1223 A93-52663 STRUCTURAL VIBRATION supersonic mixing layer Characterization of the faulted behavior of digital computers and fault tolerant systems Finite element analysis of natural vibrations of an [ISABE 93-7072] p 1201 A93-54048 aeroplane with asymmetric variable wing geometry p 1224 A93-52762 A study of the stability of vortical structures in supersonic p 1218 A93-53776 On definition and use of systems engineering processes, A dynamic stiffness/boundary element method for the inlets methods and tools p 1225 A93-53642 [ISABE93-7103] p1187 A93-54079 prediction of interior noise levels p 1226 A93-53817 Developments towards versatility in digital engine control Forcing function modeling for flow induced vibration Boundary conditions for unsteady supersonic inlet units [ISABE 93-7027] p1196 A93-54003 analyses [ISABE 93-7088] p 1202 A93-54064 SUBSONIC AIRCRAFT [ISABE 93-7104] p1187 A93-54080 SYSTEMS INTEGRATION Estimation of the effect of the longitudinal moment due Two-dimensional and three-dimensional mixing flow Methodology for integration of digital control loaders in to the engine thrust on the mass of a subsonic passenger structures with injected through slotted nozzle and circular aircraft simulators aircraft p1191 A93-52954 nozzle into supersonic flows [AIAA PAPER 93-3551 ] p 1207 A93-52655 [ISABE 93-7117] p 1221 A93-54092 SUBSONIC FLOW SYSTEMS SIMULATION Transition correlation in subsonic flow over a flat plate Numerical and experimental study on two- and Pseudo Aircraft Systems - A multi-aircraft simulation P1178 A93-53231 three-dimensional supersonic flow field with hydrogen system for air traffic control research Moving wall effects in transverse subsonic flow past a injection [AIAA PAPER 93-3585] p 1209 A93-52679 rotating cylinder p1179 A93-53573 [ISABE 93-7118] p1188 A93-54093 Integrated fire control simulation systems Aerodynamic characteristics of conical Characteristics of heat exchanger in p1192 A93-53876 triangular-planform wings of low aspect ratio in subsonic supersonic/subsonic flows stalled flow p 1180 A93-53574 [ISABE 93-7119] p 1221 A93-54094 Characteristics of heat exchanger in SUPERSONIC FLUTTER supersonic/subsonic flows Analysis of unstarted supersonic flutter in cascade by [ISABE 93-7119] p 1221 A93-54094 semiactuator disk theory p1181 A93-53841 TABS (CONTROL SURFACES) Mixing of multiple jets with a confined subsonic The unsteady flow past a supersonic splitter plate Streamwise vorticity generation and mixing crossflow p1189 A93-54324 [ISABE 93-7047] p1185 A93-54023 SUCTION enhancement in free jets by 'delta-tabs' SUPERSONIC INLETS [AIAA PAPER 93-3253] p1180 A93-53592 Effect of boundary layer suction on the thrust and A study of the stability of vortical structures in supersonic TACTICS aerodynamic efficiency of a hypersonic flight vehicle inlets Implementation of expert systems within an interactive P1176 A93-52959 [ISABE 93-7103] p1187 A93-54079 tactical environment SULFURIC ACID Boundary conditions for unsteady supersonic inlet [AIAA PAPER 93-3583] p 1223 A93-52678 Corrosion of ceramic matrix composites analyses IONERA, TP NO. 1993-82] p 1213 A93-53602 [ISABE 93-7104] p1187 A93-54080 TAIL SURFACES SUPERCOMPUTERS A study on Mach 3 two-dimensional mixed compression Repair materials and processes for the MD-11 Upwind-biased, point-implicit relaxation strategies for air-intakes Composite Tailcone p 1216 A93-53452 hypersonic flowfield simulations on supercomputers | ISABE 93-7106] p1188 A93-54082 TARGET RECOGNITION p1175 A93-52770 Numerical simulation of a two-dimensional supersonic LONGBOW - Force multiplier for continuous SUPERCRITICAL AIRFOILS mixed-compression inlet operations p 1175 A93-54295 Characterisation of conventional and controlled diffusion [ ISABE 93-7107 ] p 1188 A93-54083 TAYLOR SERIES stator blades in a transonic compressor stage Off-design performance of scramjet nozzles Fast three-dimensional vortex method for unsteady wake [ISABE 93-7124] p1189 A93-54099 [ISABE 93-7108] p 1203 A93-54084 calculations p 1178 A93-53233

A-16 SUBJECTINDEX TRANSONIC WIND TUNNELS

TECHNOLOGY ASSESSMENT THERMOPLASTIC RESINS THRUST-WEIGHT RATIO The challenge of IHPTET — Integrated High Structural applications of Avimid K3B LDF thermoplastic Estimation of the effect of the longitudinal moment due Performance Turbine Engine Technology composites — for advanced aircraft to the engine thrust on the mass of a subsonic passenger (ISABE 93-7001 ] p 1194 A93-53978 p 1216 A93-53429 aircraft p1191 A93-52954 Design and technology for engine manufacture — for THERMOSETTING RESINS TITANIUM ALLOYS Rolls-Royce aerospace business 'No VOC' water-borne corrosion resistant primers for Friction surfacing and linear friction welding I ISABE 93-7002] p1194 A93-53979 aerospace bonding applications p 1211 A93-53419 p 1217 A93-53499 Propulsion technology challenges for turn-of-the-century THIN AIRFOILS Ongoing challenges for titanium alloy cleanliness commercial aircraft Thrust imparted to an airfoil by passage through a improvement in aircraft engine disk materials I ISABE 93-7003] p1194 A93-53980 sinusoidal upwash field p 1178 A93-53219 p 1212 A93-53506 Japan's research and development program for THIN PLATES TOOLING airbreathing engine technologies Design and fabrication of panels with cutouts Innovative bagging techniques on a composite P-51 [ISASE 93-7005] p1194 A93-53981 p 1215 A93-52973 Mustang replica p1191 A93-53405 THREE DIMENSIONAL BODIES Complementary role of ground testing, flight testing, and TOTAL QUALITY MANAGEMENT Two and three-dimensional prediffuser combustor computations in aerospace plane propulsion Total quality management of forged products through studies with air-water mixture development finite element simulation p 1217 A93-53493 [ISABE 93-7025] p 1213 A93-54001 (ISABE 93-7034] p 1)97 A93-54010 THREE DIMENSIONAL BOUNDARY LAYER On definition and use of systems engineering processes, TELEMETRY Calculation of a compressible three-dimensional methods and tools p 1225 A93-53642 Instrumentation and telemetry systems for free-flight boundary layer on a swept wing p 1179 A93-53551 TRACKING PROBLEM drop model testing p 1209 A93-52754 THREE DIMENSIONAL FLOW Linear quadratic tracking problems in Hilbert space - TEMPERATURE CONTROL Progress towards understanding and predicting heat Application to optimal active noise suppression A procedure for the thermal and strength testing of transfer in the turbine gas path p 1215 A93-52751 p 1224 A93-52763 radiotransparent shells p 1209 A93-52976 Numerical study of a delta planform with multiple jets TRAILING EDGES TEMPERATURE MEASUREMENT in ground effect Numerical study of a delta planform with multiple jets CARS temperature measurements in combustion [SAE PAPER 892283] p1176 A93-53200 in ground effect I ONER A, TP NO. 1993-78) p 1212 A93-53599 Effective treatment of the singular line boundary problem [SAE PAPER 892283] p1176 A93-53200 TEMPERATURE PROFILES for three-dimensional grids p 1177 A93-53204 Aerodynamics of turbine blades with trailing-edge Non-self-similarity of a boundary layer flow of a Multigrid Navier-Stokes calculations for damage - Measurements and computations high-temperature gas in a Laval nozzle three-dimensional cascades p 1177 A93-53209 [ISABE 93-7130] p1189 A93-54105 P1176 A93-52946 Space marching calculations about hypersonic TRAINING DEVICES TEMPORAL RESOLUTION configurations using a solution-adaptive mesh algorithm An aerodynamic model for the longitudinal motion of CARS temperature measurements in combustion P1177 A93-53212 flight training devices p 1207 A93-54278 Skin-friction topology over a surface mounted IONERA, TP NO. 1993-78] p 1212 A93-53599 TRAINING SIMULATORS TENSILE STRENGTH semi-ellipsoidal wing at incidence p 1178 A93-53216 AIAA Flight Simulation Technologies Conference, Origin of the carbon rich sliding interface in alkali Prismatic grid generation for three-dimensional complex Monterey, CA, Aug. 9-11, 1993, Technical Papers containing matrix-SiC nicalon fibre composites geometries p 1178 A93-53217 p 1207 A93-52651 [ONERA, TP NO. 1993-77] p 1212 A93-53598 Three-dimensional Navier-Stokes/full-potential coupled analysis for viscous transonic flow p 1178 A93-53218 Evolution of flight simulation Thermal design and analysis of an exhaust diffuser unit Fast three-dimensional vortex method for unsteady wake [AIAA PAPER 93-3545] p 1207 A93-52652 in a ceramic composite calculations p 1178 A93-53233 Implementation of expert systems within an interactive [ISABE 93-7060) P 1220 A93-54036 3D laminar and 20 turbulent computations with the tactical environment TENSILE TESTS Navier-Stokes solver FLU3M [AIAA PAPER 93-3583] p 1223 A93-52678 Design and fabrication of panels with cutouts [ONERA, TP NO. 1993-105] p1180 A93-53618 Flight update of aerodynamic math model p1215 A93-52973 Reynolds number dependence of the drag coefficient [AIAA PAPER 93-3596] p 1224 A93-52687 The application of diffusion bonding in the manufacture for laminar flow through fine-scale photoetched screens How to consider simulation fidelity and validity for an of aeroengine components p 1217 A93-53514 p 1218 A93-53815 engineering simulator TERRAIN ANALYSIS Three-dimensional viscous flow analysis of compressor [AIAA PAPER 93-3598] p 1209 A93-52688 Terrain modeling for real-time photo-texture based visual cascade channels p 1181 A93-53837 Flight simulation - An overview p 1209 A93-53768 simulation Navier-Stokes computation of the three dimensional flow Red-hot simulation p 1209 A93-53774 [AIAA PAPER 93-3607] p 1214 A93-52667 fields through a transonic fan blade TRAJECTORY ANALYSIS LONGBOW - Force multiplier for continuous [ISABE 93-7030] p1184 A93-54006 The numerical errors in inverse simulation operations p1175 A93-54295 Isothermal flow characteristics behind V-shape gutter [AIAA PAPER 93-3588] p 1223 A93-52681 with and without injection TEXTILES TRAJECTORY OPTIMIZATION [ISABE 93-7040] p1198 A93-54016 The characterization and development of materials for Analysis of a turning point problem in flight trajectory 3D and 2.5D viscous flow computations for axial flow advanced textile composites p 1211 A93-53434 optimization p 1210 A93-52885 TEXTURES turbine blades [ISABE 93-7093] p1186 A93-54069 TRANSFER FUNCTIONS Terrain modeling for real-time photo-texture based visual Recent developments performed at ONERA for the Dynamic simulation fidelity improvement using transfer simulation simulation of 3D inviscid and viscous flows in function state extrapolation [AIAA PAPER 93-3607] p 1214 A93-52667 turbomachinery by the solution of Euler and Navier-Stokes [AIAA PAPER 93-3552] p 1222 A93-52656 Texture as a visual cueing element in computer image equations TRANSITION FLOW generation. I - Representation of the sea surface [ISABE 93-7094] p1186 A93-54070 Transition correlation in subsonic flow over a flat plate [AIAA PAPER 93-3560] p 1214 A93-52695 Three-dimensional flow analysis inside turbomachinery p1178 A93-53231 THERMAL CONTROL COATINGS stages with steady and unsteady Navier-Stokes method TRANSONIC COMPRESSORS Stress relaxation of low pressure plasma-sprayed [ISABE 93-7095] p1186 A93-54071 Characterisation of conventional and controlled diffusion NiCrAlY alloys p1211 A93-52870 A comparative assessment of two present generation stator blades in a transonic compressor stage Calculation of sandwich plates with polymer composite turbine analysis codes [ISABE 93-7124] p1189 A93-54099 skins under conditions of high humidity [ISABE 93-7097] p 1203 A93-54073 TRANSONIC FLOW P1215 A93-52968 LIF visualization of 3-dimensional hypersonic mixing Low aspect ratio wing code validation experiment THERMAL FATIGUE [ISABE 93-7114] p 1221 A93-54089 p1176 A93-53202 Thermal fatigue life assessment of a convection-cooled Two-dimensional and three-dimensional mixing flow Three-dimensional Navier-Stokes/full-potential coupled gas turbine blade structures with injected through slotted nozzle and circular analysis for viscous transonic flow p1178 A93-53218 [ISABE 93-7062) p1199 A93-54038 nozzle into supersonic flows Calculation of flow fields near a lifting wing THERMAL PROTECTION [ISABE 93-7117] p 1221 A93-54092 P1179 A93-53552 Aerodynamic heating environment definition/thermal Numerical and experimental study on two- and An implicit difference scheme of Euler equation for protection system selection for the HL-20 three-dimensional supersonic flow field with hydrogen unsteady transonic flow p 1182 A93-53852 P1181 A93-53739 injection Transonic area rule about lifting configurations THERMAL RESISTANCE [ISABE 93-7118) p1188 A93-54093 p1183 A93-53868 Navier-Stokes computation of the three dimensional flow A procedure for the thermal and strength testing of Mixing of multiple jets with a confined subsonic fields through a transonic fan blade radiotransparent shells p 1209 A93-52976 crossflow p1189 A93-54324 Application of functionally gradient materials to scramjet [ISABE 93-7030] p1184 A93-54006 THREE DIMENSIONAL MODELS engines Transonic discharge flows around diffuser vanes from Mathematical modeling of the three-dimensional [ISABE 93-7063] p 1200 A93-54039 a centrifugal impeller temperature fields of turbine blades THERMAL STRESSES [ISABE 93-7053] p1185 A93-54029 p1216 A93-53329 Application of functionally gradient materials to scramjet Navier-Stokes analysis of turbine flowfield and external engines Design of high-load aviation turbomachines using heat transfer [ISABE 93-70631 p 1200 A93-54039 modern 3D computational methods [ ISABE 93-7075 ] p 1186 A93-54051 Heat loads as key problem of hypersonic flight [ISABE 93-7032] p1196 A93-54008 Design of air intakes and nozzles for transonic rotational p 1222 A93-54276 THRUST flows THERMODYNAMIC EFFICIENCY Thrust imparted to an airfoil by passage through a [ISABE 93-7102] p1187 A93-54078 Variable cycle engine concept sinusoidal upwash field p 1178 A93-53219 TRANSONIC WIND TUNNELS [ISABE 93-7065] p 1200 A93-54041 THRUST MEASUREMENT Some acoustic features of perforated test section walls THERMOMECHANICAL TREATMENT Effect of boundary layer suction on the thrust and with splitter plates p 1226 A93-53222 Total quality management of forged products through aerodynamic efficiency of a hypersonic flight vehicle Wind of change p 1209 A93-53625 finite element simulation p 1217 A93-53493 p1176 A93-52959 Europe's new windtunnel p 1210 A93-54275

A-17 TRANSPORT AIRCRAFT SUBJECT INDEX

TRANSPORT AIRCRAFT Performance improvement by forward-skewed blading A Eulerian/Lagrangian modelling to calculate the The properties of newly developed highly damage of axial fan moving blades evolution of a water droplets spray tolerant and easy handleable carbon fiber/modified [ISABE 93-7055] p1185 A93-54031 [ISABE 93-7121] p 1221 A93-54096 bismaleimide prepreg system p 1212 A93-53448 Tip clearance effects on the flow field of an axial turbine Numerical study of nitric oxide formation in a hypersonic Wind of change p 1209 A93-53625 rotor blade cascade ramjet engine Propulsion technology challenges for turn-of-the-century [ISABE 93-7057) p1185 A93-54033 [ISABE 93-7125] p 1204 A93-54100 commercial aircraft New approximate method of stress analysis for bladed TURBULENT BOUNDARY LAYER IISABE 93-7003] p1194 A93-53980 rotating discs Low-Reynolds-number k-epsilon model for unsteady Conceptual design study on combined-cycle engine for [ISABE 93-7059] p 1219 A93-54035 turbulent boundary-layer flows p 1177 A93-53208 hypersonic transport Axial flow compressors - Mechanical design trends Analytical expression of dissipation integral for kinetic [ IS ABE 93-7018 ] p 1195 A93-53994 [ISABE 93-7061] p1199 A93-54037 energy integral equation — calculation of turbulent Noise reduction of supersonic heated jet with jet mixing Boundary conditions for unsteady supersonic inlet compressible boundary layer in aerodynamics enhancement by tabs analyses p1183 A93-53860 [ISABE 93-7046] p1198 A93-54022 [ISABE 93-7104] p1187 A93-54080 TURBULENT COMBUSTION TRANSVERSE WAVES TURBOFAN ENGINES Blowout of turbulent disc/pilot stabilized jet diffusion Numerical study of supersonic flow over a backward A study on 3-D velocity distribution of isothermal flows flames step with transverse injection p 1182 A93-53853 behind an afterburner flame stabilizer [ISABE 93-7026] p 1213 A93-54002 TRAVELING WAVES [ISABE 93-7039] p1197 A93-54015 Large eddy simulation of turbulent combustion behind Shock shapes around slender diamond cones traveling Axial flow compressors - Mechanical design trends flame holders at hypersonic speed P 11.81 A93-53840 [ISABE 93-7061] p1199 A93-54037 [ISABE 93-7042] p1198 A93-54018 TRISONIC WIND TUNNELS Design of limit-tracking systems incorporating a turbofan Numerical simulation of gas turbine combustors with Some acoustic features of perforated test section walls engine with constant disturbances complex geometries with splitter plates p 1226 A93-53222 [ISABE 93-7090] p 1203 A93-54066 [ISABE 93-7128] p 1204 A93-54103 TURBINE BLADES Neural network fault diagnosis of a turbofan engine TURBULENT DIFFUSION Effect of rotation on heat transfer and hydraulic [ISABE 93-7091] p 1203 A93-54067 Large eddy simulation of turbulent combustion behind resistance in the radial cooling channels of turbine rotor Development of a real time dynamic engine simulation flame holders blades p 1215 A93-52950 model of a turbo fan engine [ISABE 93-7042] p1198 A93-54018 Experimental investigation into the mechanism of [ISABE 93-7132] p 1205 A93-54107 TURBULENT FLOW discrete frequency noise (DFN) generation from a NACA Expert Systems for the simulation of turbofan engines Non-self-similarity of a boundary layer flow of a 0012 blade p 1225 A93-53194 (ISABE 93-7133] p 1225 A93-54108 high-temperature gas in a Laval nozzle Mathematical modeling of the three-dimensional TURBOFANS p1176 A93-52946 temperature fields of turbine blades Propulsion technology challenges for turn-of-the-century Numerical analysis of flow within cascade with tip p 1216 A93-53329 commercial aircraft clearance p 1176 A93-53192 Measurements and computational analysis of heat [ISABE 93-7003] p1194 A93-53980 Zonal-local solution method for the turbulent transfer and flow in a simulated turbine blade internal TURBOJET ENGINES Navier-Stokes equations p 1177 A93-53205 cooling passage A study of surge control by using pulse cut-off for dual Multigrid Navier-Stokes calculations for [AIAA PAPER 93-1797] p 1218 A93-53585 spool turbo-jet engine p 1194 A93-53862 three-dimensional cascades p 1177 A93-53209 Forcing function modeling for flow induced vibration Measurement and prediction of flow in a gas turbine 3D laminar and 2D turbulent computations with the [ISABE 93-7027] p1196 A93-54003 engine exhaust plume Navier-Stokes solver FLU3M Effects of wake interaction of two turbine cascades on [ISABE 93-7113] p 1204 A93-54088 [ONERA, TP NO. 1993-105] p1180 A93-53618 secondary/tip-leakage flows and losses Structural integrity validation of limited-life engines A Eulerian/Lagrangian modelling to calculate the [ISABE 93-7058] p1185 A93-54034 [ISABE 93-7131] p 1205 A93-54106 evolution of a water droplets spray Heat transfer and material temperature conditions in the TURBOMACHINE BLADES [ISABE 93-7121] p 1221 A93-54096 leading edge area of impingement-cooled turbine vanes A comparative assessment of two present generation Experimental investigation of boundary layer transition [ISABE 93-7076] p 1220 A93-54052 turbine analysis codes on a flat plate with C4 leading edge 3D and 2.5D viscous flow computations for axial flow [ISABE 93-7097] p 1203 A93-54073 [ISABE 93-7123] p 1222 A93-54098 turbine blades Characterisation of conventional and controlled diffusion TURBULENT WAKES [ISABE 93-7093] p1186 A93-54069 stator blades in a transonic compressor stage Laser velocimeter measurements of the flow field Aerodynamics of turbine blades with trailing-edge [ISABE 93-7124] p1189 A93-54099 generated by a forward-swept propfan during flutter damage - Measurements and computations TURBOMACHINERY [AIAA PAPER 93-2919] p 1180 A93-53591 (ISABE 93-7130] p1189 A93-54105 Aerodynamic inverse design and analysis for a full TURNING FLIGHT TURBINE ENGINES engine Analysis of a turning point problem in flight trajectory The chemistry of Saudi Arabian sand - A deposition [ISABE 93-7086] p1186 A93-54062 optimization p 1210 A93-52885 problem on helicopter turbine airfoils Recent developments performed at ONERA for the TVD SCHEMES p 1216 A93-53468 simulation of 3D inviscid and viscous flows in Three-dimensional viscous flow analysis of compressor CARS temperature measurements in combustion turbomachinery by the solution of Euler and Navier-Stokes cascade channels p 1181 A93-53837 [ONERA, TP NO. 1993-78] p 1212 A93-53599 equations Numerical solution of N-S equations for hypersonic flow The challenge of IHPTET — Integrated High [ISABE 93-7094] p1186 A93-54070 over capsule-type vehicles p1182 A93-53858 Performance Turbine Engine Technology Three-dimensional flow analysis inside turbomachinery A 2-D compressible N-S simulation of starting- and [ISABE 93-7001] p1194 A93-53978 stages with steady and unsteady Navier-Stokes method stalling-flows in a compressor cascades system Research and development of a turbo-accelerator for [ISABE 93-7095] p1186 A93-54071 [ISABE 93-7006] p1183 A93-53982 super/hypersonic transport TURBOPROP ENGINES [ISABE 93-7066] p 1200 A93-54042 The T700 ... from salt spray to sand blast TWO DIMENSIONAL FLOW Navier-Stokes analysis of turbine flowfield and external p 1205 A93-54292 Transition correlation in subsonic flow over a flat plate heat transfer TURBORAMJET ENGINES P1178 A93-53231 (ISABE 93-7075] p1186 A93-54051 Mach 5 turboramjet requirements and design 3D laminar and 2D turbulent computations with the Effect of nozzle design on the performance ol a highly approach Navier-Stokes solver FLU3M loaded turbine stage (ISABE 93-7015] p1194 A93-53991 [ONERA, TP NO. 1993-105] p1180 A93-53618 (ISABE 93-7096] p 1203 A93-54072 Development study on Air Turbo Ramjet engine for a On the numerical simulation of the two-dimensional flow TURBINES future space plane field around a hypersonic air-intake-compressibility A comparative assessment of two present generation [ISABE 93-7016] p1195 A93-53992 effects turbine analysis codes Evaluation of turboramjet exhaust systems from scale [ISABE 93-7100] p1187 A93-54076 [ISABE 93-7097] P 1203 A93-54073 model test data A study on Mach 3 two-dimensional mixed compression TURBOCOMPRESSORS [ISABE 93-7109] p 1204 A93-54085 air-intakes Estimation of the change of axial-flow compressor Characteristics of heat exchanger in [ISABE 93-7106] p1188 A93-54082 characteristics during long-term service supersonic/subsonic flows Observation of fluctuation of 2D-nozzle flows p1193 A93-52949 [ISABE 93-7119] p 1221 A93-54094 [ISABE 93-7110] p 1204 A93-54086 The combined effect of clearances and peripheral TURBULENCE MODELS Two-dimensional and three-dimensional mixing flow overlaps on the efficiency of microturbines with shroudless Analytical expression of dissipation integral for kinetic structures with injected through slotted nozzle and circular rotors p1193 A93-52963 energy integral equation — calculation of turbulent nozzle into supersonic flows The acoustics of axial compressors compressible boundary layer in aerodynamics [ISABE 93-7117] p 1221 A93-54092 (ONERA, TP NO. 1993-102] P 1226 A93-53615 p1183 A93-53860 Study on surge and rotating stall in axial compressors. Numerical study on inception of stall cells in rotating Numerical and experimental study on two- and Ill - Numerical model for multiblade-row compressors stall three-dimensional supersonic flow field with hydrogen injection p1181 A93-53799 [ISABE 93-7007] p 1183 A93-53983 [ ISABE 93-7118 ] p 1188 A93-54093 The energy dissipation in a rotating stall cell 3D and 2.5D viscous flow computations for axial flow [ISABE 93-7010] p1183 A93-53986 turbine blades TWO DIMENSIONAL MODELS Review of stall, surge and active control in axial [ISABE 93-7093] p1186 A93-54069 Estimation of the change of axial-flow compressor compressors Recent developments performed at ONERA for the characteristics during long-term service [ISABE 93-7011] p1184 A93-53987 simulation of 3D inviscid and viscous flows in P1193 A93-52949 An investigation of post stall transients and recoverability turbomachinery by the solution of Euler and Navier-Stokes A 2-D compressible N-S simulation of starting- and of axial compression systems equations stalling-flows in a compressor cascades system (ISABE 93-7012] p1184 A93-53988 [ISABE 93-7094] p1186 A93-54070 [ISABE 93-7006] p1183 A93-53982 The streamline throughflow method of axial Three-dimensional flow analysis inside turbomachinery New approximate method of stress analysis for bladed turbomachinery flow analysis stages with steady and unsteady Navier-Stokes method rotating discs (ISABE 93-7031 ] p 1184 A93-54007 [ISABE 93-7095] p 1186 A93-54071 [ISABE 93-7059] p 1219 A93-54035

A-18 SUBJECT INDEX ZIRCONIUM COMPOUNDS

The combustion performance of methane-fueled ram VISCOSITY WAVE PROPAGATION combustor Viscosity of aviation fuel components - Aromatic Acoustic-wave propagation in ducts and free-field IISABE 93-7079] p 1201 A93-54055 hydrocarbons (alkyl benzenes) p 1211 A93-52961 radiation Numerical simulation of a two-dimensional supersonic VISCOUS FLOW [ONERA.TPNO.1993-103] p1226 A93-53616 mixed-compression inlet Prismatic grid generation for three-dimensional complex WEAR RESISTANCE IISABE 93-7107] p 1188 A93-54083 geometries p1178 A93-53217 Estimation of the change of axial-flow compressor Three-dimensional Navier-Stokes/fuH-potential coupled characteristics during long-term service analysis for viscous transonic flow p 1178 A93-53218 p1193 A93-52949 U Application of the small parameter method to the WEATHER problem of three-dimensional flow of a viscous gas past Visual weather simulation using meteorological UNSTEADY AERODYNAMICS bodies p1178 A93-53314 databases Boundary layer and pressure measurements on a The flow lag angle in the rotor of a centrifugal compressor [AIAA PAPER 93-3566] p 1207 A93-52665 cylinder with unsteady circulation control with allowance for viscosity effects WEIGHT (MASS) p1177 A93-53207 p1179 A93-53555 Estimation of the effect of the longitudinal moment due Fast three-dimensional vortex method for unsteady wake 3D and 2.5D viscous flow computations for axial flow to the engine thrust on the mass of a subsonic passenger calculations p 1178 A93-53233 turbine blades aircraft p 1191 A93-52954 I ISABE 93-7093] p1186 A93-54069 WEIGHT REDUCTION Unsteady aerodynamic characteristics of three Recent developments performed at ONERA for the An experimental study of reinforced panels of composite rectangular wings of different aspect ratios simulation of 3D inviscid and viscous flows in materials p 1215 A93-52975 p1180 A93-53S75 turbomachinery by the solution of Euler and Navier-Stokes WIND PROFILES Analysis of unstarted supersonic flutter in cascade by equations Case study of a low-reflectivity pulsating microburst - semiactuator disk theory p 1181 A93-53841 [ISABE 93-7094] p1186 A93-54070 Numerical simulation of the Denver, 8 July 1989, storm Numerical analysis of the flow through a centrifugal VISUAL AIDS p 1222 A93-52898 impeller by vortex distribution model of a boundary layer. AIAA Flight Simulation Technologies Conference, WIND SHEAR I - Theoretical analysis p1182 A93-53843 Monterey, CA, Aug. 9-11, 1993, Technical Papers Case study of a low-reflectivity pulsating microburst - An implicit difference scheme of Euler equation for p 1207 A93-52651 Numerical simulation of the Denver, 8 July 1989, storm unsteady transonic flow p 1182 A93-53852 VISUAL SIGNALS p 1222 A93-52898 Forcing function modeling for flow induced vibration Texture as a visual cueing element in computer image Identification of the phase characteristics and IISABE 93-7027] p1196 A93-54003 generation. I - Representation of the sea surface wind-induced perturbations of an aircraft from flight test The unsteady flow past a supersonic splitter plate [ AIAA PAPER 93-35601 p 1214 A93-52695 results P 1206 A93-52943 IISABE 93-70471 p1185 A93-54023 VORTEX BREAKDOWN WIND TUNNEL DRIVES UNSTEADY FLOW Active control of vortex breakdown by a spinning wave Production of oscillatory flow in wind tunnels p 1218 A93-53812 Experimental investigation into the mechanism of generator discrete frequency noise (DFN) generation from a NACA [ISABE 93-7045] p 1219 A93-54021 WIND TUNNEL TESTS 0012 blade p 1225 A93-53194 VORTEX GENERATORS Some acoustic features of perforated test section walls Streamwise vorticity generation and mixing with splitter plates p 1226 A93-53222 Low-Reynolds-number k-epsilon model for unsteady enhancement in free jets by 'deJta-tabs' Aerodynamic characteristics of the HL-20 turbulent boundary-layer flows p 1177 A93-53208 [AIAA PAPER 93-3253] p1180 A93-53592 p1181 A93-53736 A 2-0 compressible N-S simulation of starting- and VORTEX SHEDDING Tandem transverse hydrogen gas injection into a stalling-flows in a compressor cascades system Numerical analysis of the flow through a centrifugal supersonic airflow IISABE 93-7006] p1183 A93-53982 impeller by vortex distribution model of a boundary layer. [ISABE 93-7069] p 1201 A93-54045 Three-dimensional flow analysis inside turbomachinery I - Theoretical analysis p 1182 A93-53843 A comparative assessment of two present generation stages with steady and unsteady Navier-Stokes method The unsteady flow past a supersonic splitter plate turbine analysis codes IISABE 93-70951 p1186 A93-54071 [ISABE 93-7047] p1185 A93-54023 [ISABE 93-7097] p 1203 A93-54073 Boundary conditions for unsteady supersonic inlet VORTEX SHEETS Wind tunnel tests of the model of intake-airframe analyses Thrust imparted to an airfoil by passage through a integration [ISABE 93-71041 p1187 A93-54080 sinusoidal upwash field p1178 A93-53219 [ISABE 93-7101] D1192 A93-54077 Starting characteristics of scramjet inlets Study on flow field around slender diamond cone VORTICES [ISABE 93-7105] p 1203 A93-54081 traveling at hypersonic speed p1189 A93-54314 Construction of wakes in the discrete vortex method A study on Mach 3 two-dimensional mixed compression UPWASH p1179 A93-53333 air-intakes Thrust imparted to an airfoil by passage through a Streamwise vorticity generation and mixing sinusoidal upwash field p 1178 A93-53219 [ISABE 93-7106] p1188 A93-54082 enhancement in free jets by 'delta-tabs' Europe's new windtunnel p 1210 A93-54275 UPWIND SCHEMES (MATHEMATICS) [AIAA PAPER 93-3253] p1180 A93-53592 Upwind-biased, point-implicit relaxation strategies for WIND TUNNELS The development of a new air filtration system for the Production of oscillatory flow in wind tunnels hypersonic flowfield simulations on supercomputers Alouette III helicopter P1218 A93-53812 p1175 A93-52770 [ISABE 93-7048] p1199 A93-54024 WINDOWS (APERTURES) A study of the stability of vortical structures in supersonic Nonlinear deformation mechanics of multilayer inlets transparency elements - Some calculation results — for [ISABE 93-7103] p1187 A93-54079 aircraft portholes p 1191 A93-52937 V/STOL AIRCRAFT VORTICITY WING LOADING Advanced aerodynamic airframe/nozzle integration Fast three-dimensional vortex method for unsteady wake Calculation of flow fields near a lifting wing | ISABE 93-7099 ] p 1187 A93-54075 calculations p 1178 A93-53233 p1179 A93-53552 VARIABLE CYCLE ENGINES WING PLANFORMS Variable cycle engine concept Aerodynamic characteristics of conical IISABE 93-7065] p 1200 A93-54041 w triangular-planform wings of low aspect ratio in subsonic VELOCITY DISTRIBUTION stalled flow p1180 A93-53574 Velocity fluctuation based on the difference in the flow WALL FLOW WING PROFILES pattern in the channels of a centrifugal impeller Skin-friction topology over a surface mounted Finite element analysis of natural vibrations of an p1182 A93-53842 semi-ellipsoidal wing at incidence p 1178 A93-53216 aeroplane with asymmetric variable wing geometry A study on 3-D velocity distribution of isothermal flows WALL TEMPERATURE p 1218 A93-53776 behind an afterburner flame stabilizer Separation phenomenon in a hypersonic flow with strong WINGS I ISABE 93-7039] p1197 A93-54015 wall cooling - Subcritical regime p 1189 A93-54266 Design for cyclic loading endurance of composites p 1216 A93-53395 VERTICAL MOTION SIMULATORS WALLS Reinforcement of the F-111 wing pivot fitting with a A high fidelity video delivery system for real-time flight Initial results from the NASA Lewis wave rotor boron/epoxy doubler system - Materials engineering simulation research experiment aspects p 1214 A93-54241 IAIAA PAPER 93-3558] p 1214 A93-52659 [AIAA PAPER 93-2521 | p1193 A93-53589 Development and operation of a real-time simulation at WIRE CLOTH WATER Reynolds number dependence of the drag coefficient the NASA Ames Vertical Motion Simulator A Eulerian/Lagrangian modelling to calculate the [AIAA PAPER 93-3575] p 1208 A93-52671 for laminar flow through fine-scale photoetched screens evolution of a water droplets spray p 1218 A93-53815 Simulation motion effect on single axis compensatory [ISABE 93-7121] p 1221 A93-54096 tracking WATER INJECTION IAIAA PAPER 93-3579] p 1208 A93-52675 Two and three-dimensional prediffuser combustor VIBRATION MODE studies with air-water mixture Finite element analysis of natural vibrations of an [ISABE 93-7025] p 1213 A93-54001 ZERO ANGLE OF ATTACK aeroplane with asymmetric variable wing geometry Application of the small parameter method to the p1218 A93-53776 WAVE EQUATIONS problem of three-dimensional flow of a viscous gas past A dynamic stiffness/boundary element method for the Acoustic-wave propagation in ducts and free-field bodies p1178 A93-53314 prediction of interior noise levels p 1226 A93-53817 radiation ZIRCONIUM COMPOUNDS Effects of blade geometry and mode shape on fan [ONERA, TP NO. 1993-103] p 1226 A93-53616 Preparation and characterization of continuous fiber flutter WAVE GENERATION reinforced zirconium diboride matrix composites for a I ISABE 93-7028] pt196 A93-54004 Kelvin-Helmholtz wave generation beneath hovercraft leading edge material p1211 A93-53445 VIDEO DATA skirts p 1219 A93-53820 A high fidelity video delivery system for real-time flight Active control of vortex breakdown by a spinning wave simulation research generator [AIAA PAPER 93-3558] p 1214 A93-52659 [ISABE 93-7045] p 1219 A93-54021

A-19 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 298) December 1993

Typical Personal Author Index Listing ANDREWS, G. E. BELO, E. M. An ultra low N0(x) pilot combustor for staged low NO(x) Initial development of a research flight simulator combustion software [ ISABE 93-7020 ] p 1195 A93-53996 [AIAA PAPER 93-3590) p 1223 A93-52683 PERSONAL AUTHOR ANDRIANI, R. BELOZEROV, L. G. Performance and configuration analysis of jet-engine A procedure for the thermal and strength testing of off-design behavior radiotransparent shells p 1209 A93-52976 I ISABE 93-7087] p 1202 A93-54063 BELYAEV, D. V. ADELMAN, HOWARD M. ANDRIENKO, V. M. >— Recent advances in multidisciplinary optimization of Estimation of the change of axial-flow compressor An experimental study of reinforced panels of composite characteristics during long-term service rotorcraft materials p 1215 A93-52975 (NASA-TM-107665) p 47 N93-10968 p1193 A93-52949 AOI, Y. BENSI, G. Effects of wake interaction of two turbine cascades on New developments with the V2500 engine secondary/tip-leakage flows and losses [ISABE 93-7085] p 1202 A93-54061 [ISABE 93-7058] p1185 A93-54034 AOKI, T. BERG, H. P. Heat transfer and material temperature conditions in the Conceptual design study on combined-cycle engine for leading edge area of impingement-cooled turbine vanes hypersonic transport [ISABE 93-7018] p1195 A93-53994 [ISABE 93-7076] p 1220 A93-54052 ARCHER, FRANCES A. BERKCAN, E. Listings in this index are arranged alphabetically Sensors with centroid based common sensing scheme by personal author. The title of the document The chemistry of Saudi Arabian sand - A deposition problem on helicopter turbine airfoils and their multiplexing p1192 A93-52994 is used to provide a brief description of the p 1216 A93-53468 BERNARD, PIERRE subject matter. The report number helps to ARKUN, UGUR High temperature heat exchangers for gas turbines and indicate the type of document (e.g., NASA Numerical simulation of ramjet and scramjet combustion future hypersonic air breathing propulsion report, translation, NASA contractor report). The using two-dimensional Euler equations with finite rate [ONERA, TP NO. 1993-75] p 1218 A93-53596 chemistry BEZDEK, WILLIAM J. page and accession numbers are located Dynamic simulation fidelity improvement using transfer beneath and to the right of the title. Under any [ISABE 93-7083) p 1202 A93-54059 ASO, SHIGERU function state extrapolation one author's name the accession numbers are Two-dim'ensional and three-dimensional mixing flow [AIAA PAPER 93-3552] p 1222 A93-52656 arranged in sequence. structures with injected through slotted nozzle and circular BHARADVAJ, BALA K. nozzle into supersonic flows Three-dimensional Navier-Stokes/full-potential coupled [ISABE 93-7117] p 1221 A93-54092 analysis for viscous transonic flow p 1178 A93-53218 AVRAN, PATRICK BHARGAVA REDDY, G. Development of a real time dynamic engine simulation High temperature heat exchangers for gas turbines and future hypersonic air breathing propulsion model of a turbo fan engine [ONERA, TP NO. 1993-75] p 1218 A93-53596 [ISABE 93-7132] p 1205 A93-54107 ACHARYA, SUMANTA BIAGIOLI, F. Space marching calculations about hypersonic Finite-rate H2/air combustion effects in CRJ for configurations using a solution-adaptive mesh algorithm B hypersonic launchers p1177 A93-53212 [ISABE 93-7084] p 1202 A93-54060 BILLIG, FREDERICK S. BAILEY, MELVIN L ADVANI, S. K. ISABE - International Symposium on Air Breathing The development of SIMONA - A simulator facility for Effect of lift-to-drag ratio in pilot rating of the HL-20 Engines. 11th, Tokyo, Japan, Sept. 20-24, 1993, landing task p 1210 A93-53738 advanced research into simulation techniques, motion Proceedings. Vols. 1 & 2 system control and navigation systems technologies BAIN, J. G. [ISBN 1-56347-071-3] p1194 A93-53976 | AIAA PAPER 93-3574] p 1208 A93-52670 Measurement and prediction of flow in a gas turbine BILLONNET, GILLES AH-FA, M. engine exhaust plume 3D and 2.5D viscous flow computations for axial flow Optimization of afterbodies and engine nozzle by using [ISABE 93-7113] p 1204 A93-54088 turbine blades CFD methods BAKER, A. A. [ISABE 93-7093] p1186 A93-54069 | ISABE 93-7098 J p 1187 A93-54074 Reinforcement of the F-111 wing pivot fitting with a BLASZCZYK, J. AKMANDOR, I. S. boron/epoxy doubler system - Materials engineering Finite element analysis of natural vibrations of an Numerical simulation of ramjet and scramjet combustion aspects p1214 A93-54241 aeroplane with asymmetric variable wing geometry using two-dimensional Euler equations with finite rate BALL, CALVIN L. p 1218 A93-53776 chemistry Propulsion technology challenges forturn-of-the-century BOGOMOLOV, A. I. | ISABE 93-7083] p 1202 A93-54059 commercial aircraft Stabilization of the dynamic characteristics of the AL-ASMI, K. [ISABE 93-7003] p1194 A93-53980 two-channel automatic control system of aircraft Production of oscillatory flow in wind tunnels BALTER-PETERSON, ALIZA p 1205 A93-52941 p 1218 A93-53812 Evaluation of 2D ceramic matrix composites in BONNAR, GERARD R. ALEKSEEV, A. R. aeroconvective environments p 1212 A93-53459 Repair materials and processes for the MD-11 A study of optical distortions arising in radiation BANKS, H. T. Composite Tailcone p 1216 A93-53452 transmission through cavities with gas flow around them Linear quadratic tracking problems in Hilbert space - BOOKOUT, GREG p 1225 A93-52945 Application to optimal active noise suppression Texture as a visual cueing element in computer image ALKABIE, H. S. p 1224 A93-52763 generation. I - Representation of the sea surface [AIAA PAPER 93-3560] p 1214 A93-52695 An ultra low NO(x) pilot combustor for staged low NO(x) BARENES, R. BOUCHARDY, P. combustion Investigation of the flow field through a variable pitch CARS temperature measurements in combustion | ISABE 93-7020] p1195 A93-53996 fan rotor with an inlet total pressure distortion [ONERA, TP NO. 1993-78] p 1212 A93-53599 ALLAN, T. [ISABE 93-7029] p1184 A93-54005 BOUDREAU, A. H. New developments with the V2500 engine BARKER, MICHAEL J. Complementary role of ground testing, flight testing, and [ISABE 93-7085] p 1202 A93-54061 'No VOC' water-borne corrosion resistant primers for computations in aerospace plane propulsion ALLEN, L. D. aerospace bonding applications p 1211 A93-53419 development Evolution of flight simulation BARNETT, MARK [ISABE 93-7034] p1197 A93-54010 | AIAA PAPER 93-3545] p 1207 A93-52652 Low-Reynolds-number k-epsilon model for unsteady BOWERS, DOUGLAS L. AN, FU-OI turbulent boundary-layer flows p 1177 A93-53208 Advanced aerodynamic airframe/nozzle integration A study of damage tolerance of the landing gear BARRERE, M. [ISABE 93-7099] p1187 A93-54075 structure p 1219 A93-53881 Energy management BRAUNSTINGL, R. ANDO, YASUNORI [ISABE 93-7019] p1195 A93-53995 An aerodynamic model for the longitudinal motion of Two-dimensional and three-dimensional mixing flow BAVUSO, SALVATORE J. flight training devices p 1207 A93-54278 structures with injected through slotted nozzle and circular Characterization of the faulted behavior of digital BRAZIER, MICHAEL E. nozzle into supersonic flows computers and fault tolerant systems Variable cycle engine concept |ISABE 93-7117] p 1221 A93-54092 p 1224 A93-52762 [ISABE 93-7065] p 1200 A93-54041

B-1 BRESCIA, JOSEPH A. PERSONAL AUTHOR INDEX

BRESCIA, JOSEPH A. CHESTER, R. J. DAY, I. J. Evaluation of water-borne adhesive bonding primers for Reinforcement of the F-111 wing pivot fitting with a Review of stall, surge and active control in axial use on the advanced aircraft material aluminum-lithium boron/epoxy doubler system - Materials engineering compressors P1211 A93-53420 aspects p 1214 A93-54241 [ISABE 93-7011) p1184 A93-53987 BREUGELMANS, F. A. E. CHETELAT, MONIQUE DEDEKING, MANFRED O. The leading edge vortex of a rotating stall cell Development and operation of a real-time simulation at Thermal fatigue life assessment of a convection-cooled [ISABE 93-7009) p!183 A93-53985 the NASA Ames Vertical Motion Simulator gas turbine blade The energy dissipation in a rotating stall cell [AIAA PAPER 93-3575] p 1208 A93-52671 [ISABE 93-7062] p1199 A93-54038 (ISABE 93-7010] P1183 A93-53986 CHIBA, K. DEMEIS, RICHARD BRINDLEY, W. J. Research and development of high pressure compressor Red-hot simulation p 1209 A93-53774 Stress relaxation of low pressure plasma-sprayed for SST and HST engine DEPPE, P. R. NiCrAlY alloys p 1211 A93-52870 [ISABE 93-7068] p1186 A93-54044 A rapid prototyping system for inflight simulation using BROOKS, DON the Calspan Learjet 25 CHIBA, KAORU Engineering simulators enhance 777 development [AIAA PAPER 93-3606] p1191 A93-52691 A 2-D compressible N-S simulation of starting- and P1192 A93-53771 DESAI, ATUL stalling-flows in a compressor cascades system BROOKSBY, G. Durability properties for adhesively bonded structural [ISABE 93-7006] p1183 A93-53982 Sensors with centroid based common sensing scheme aerospace applications p 1217 A93-53515 CHUA, KIAT and their multiplexing p1192 A93-52994 DEVARAJAN, VENKAT Fast three-dimensional vortex method for unsteady wake BROUGHTON, T. Terrain modeling for real-time photo-texture based visual calculations p1178 A93-53233 Design and technology for engine manufacture simulation CINQUE, G. [ISABE 93-7002] p1194 A93-53979 [AIAA PAPER 93-3607] p 1214 A93-52667 Numerical simulation of gas turbine combustors with BRUNO, C. complex geometries Dl MARTINO, P. Finite-rate H2/air combustion effects in CRJ for [ISABE 93-7128] p 1204 A93-54103 Numerical simulation of gas turbine combustors with hypersonic launchers COCHRAN, ROLAND complex geometries I ISABE 93-7084] p 1202 A93-54060 Wet layup materials for repair of bismaleimide [ISABE 93-7128] p 1204 A93-54103 BUETHE, S. A. composites p 1212 A93-53451 DING, JI-PING A rapid prototyping system for inflight simulation using COLASURDO, GUIDO A study of aircraft global dynamic stability in rapid rolling the Calspan Learjet 25 Nozzle effects on linear stability behaviour of maneuver p 1206 A93-53869 [ AIAA PAPER 93-3606] p 1191 A93-52691 combustors DMITRENKO, A. V. BUSSI, GIUSEPPE [ISABE 93-7044] p 1198 A93-54020 Non-self-similarity of a boundary layer flow of a Nozzle effects on linear stability behaviour of COLLIN, G. high-temperature gas in a Laval nozzle combustors P1176 A93-52946 CARS temperature measurements in combustion [ISABE 93-7044] p1198 A93-54020 [ONERA, TP NO. 1993-78] p 1212 A93-53599 DOI, HIROFUMI BUT, A. S. COLOMBAN, PH. Analysis of unstarted supersonic flutter in cascade by Calculation of the position of the flow separation line Origin of the carbon rich sliding interface in alkali semiactuator disk theory p 1181 A93-53841 in an analog model of flow past a body containing matrix-SiC nicalon fibre composites DOWLING, A. P. P1176 A93-52958 [ONERA, TP NO. 1993-77] p 1212 A93-53598 Low-frequency combustion oscillations in a model afterburner p1193 A93-53702 Corrosion of ceramic matrix composites DREGALIN, A. F. [ONERA, TP NO. 1993-82] p 1213 A93-53602 COOKSON, ROY A. Viscosity of aviation fuel components - Aromatic New approximate method of stress analysis for bladed hydrocarbons (alkyl benzenes) p 1211 A93-52961 CASE, J. L. DRENNAN, S. A. rotating discs Research and development of 3 turbo-accelerator for Emission characteristics of a model gas turbine super/hypersonic transport [ISABE 93-7059] p 1219 A93-54035 COPENHAVER, W. W. combustor at practical conditions [ISABE 93-7066] p 1200 A93-54042 [ISABE 93-7023] p1196 A93-53999 Three-dimensional flow analysis inside turbomachinery CALDWELL, RONALD G. DRIKAKIS, D. stages with steady and unsteady Navier-Stokes method HL-20 operations and support requirements for the Zonal-local solution method for the turbulent Personnel Launch System mission p 1210 A93-53745 [ISABE 93-7095] p1186 A93-54071 COUAILLIER, V. Navier-Stokes equations p 1177 A93-53205 CALEFFI, T. DU PLESSIS, L. J. H. Recent developments performed at ONERA for the Initial development of a research flight simulator The development of a new air filtration system for the simulation of 3D inviscid and viscous flows in software Alouette III helicopter turbomachinery by the solution of Euler and Navier-Stokes [AIAA PAPER 93-3590] p 1223 A93-52683 [ISABE 93-7048] p1199 A93-54024 equations CAMCI, C. DUDCHENKO, A. A. [ISABE 93-7094] p1186 A93-54070 Fluid dynamics and convective heat transfer in impinging Design and fabrication of panels with cutouts CREISMEAS, PAUL jets through implementation of a high resolution liquid P1215 A93-52973 A Eulerian/Lagrangian modelling to calculate the crystal technique DUDEBOUT, RUDOLPH evolution of a water droplets spray [ISABE 93-7077] p 1220 A93-54053 Hypersonic shock-induced combustion ramjet [ISABE 93-7121] p 1221 A93-54096 CAMERON, MURDO performance analysis CRIGHTON, D. G. Innovative bagging techniques on a composite P-51 [ISABE 93-7037] p1197 A93-54013 Mustang replica p 1191 A93-53405 The unsteady flow past a supersonic splitter plate [ISABE 93-7047] p1185 A93-54023 DUSA, D. J. CARDULLO, FRANK M. Evaluation of turboramjet exhaust systems from scale The low frequency aeroacoustics of buried nozzle Transport delay compensation - An inexpensive model test data systems p 1205 A93-54244 alternative to increasing image generator update rate [ISABE 93-7109] p 1204 A93-54085 CRUZ, CHRISTOPHER I. [AIAA PAPER 93-3563] p 1223 A93-52663 DZYGADLO, Z. Aerodynamic characteristics of the HL-20 CARGILL, A. M. Analysis of spatial motion dynamics of a helicopter for p1181 A93-53736 The low frequency aeroacoustics of buried nozzle various models of the induced velocity field CULL, RAY systems P 1205 A93-54244 P1191 A93-53721 CARRERE, A. Innovative bagging techniques on a composite P-51 Investigation of the flow field through a variable pitch Mustang replica p 1191 A93-53405 fan rotor with an inlet total pressure distortion [ISABE 93-7029] p1184 A93-54005 CASSETTI, M. EERTINK, O. The energy dissipation in a rotating stall cell Finite-rate H2/air combustion effects in CRJ for D'ESPINEY, P. [ISABE 93-7010] p1183 A93-53986 hypersonic launchers 3D laminar and 2D turbulent computations with the EL-BANHAWY, Y. H. [ISABE 93-7084] p 1202 A93-54060 Navier-Stokes solver FLU3M Blowout of turbulent disc/pilot stabilized jet diffusion CASTRO, I. P. [ONERA, TP NO. 1993-105] p1180 A93-53618 flames Production of oscillatory flow in wind tunnels DAI, GUAN-ZHONG [ISABE 93-7026] p 1213 A93-54002 p 1218 A93-53812 Integrated fire control simulation systems EL-EHWANY, A. A. CHANAT, STEPHANIE P1192 A93-53876 Preparation and characterization of continuous fiber DANEK, GEORGE L. Blowout of turbulent disc/pilot stabilized jet diffusion flames reinforced zirconium diboride matrix composites for a Pseudo Aircraft Systems - A multi-aircraft simulation [ISABE 93-7026] p 1213 A93-54002 leading edge material p 1211 A93-53445 system for air traffic control research ELDER, R. L. CHANDRA, U. [AIAA PAPER 93-3585] p 1209 A93-52679 Experimental investigation of boundary layer transition Total quality management of forged products through DARLING, DAVID on a flat plate with C4 leading edge finite element simulation p 1217 A93-53493 A radar altitude and line of sight attachment CHANDRASEKHARAN, S. [AIAA PAPER 93-3587] p 1223 A93-52680 [ISABE 93-7123] p 1222 A93-54098 Total quality management of forged products through DA VIES, PETER ELLIOTT, SIMON finite element simulation p 1217 A93-53493 Air transport and the environment - Regulating aircraft Wind of change p 1209 A93-53625 CHAWLA, K. noise p 1226 A93-52931 ELLIS, THOMAS D., JR. Numerical study of a delta planlorm with multiple jets DAVIS, GUY D. An evaluation of software tools for the design and in ground effect Durability properties for adhesively bonded structural development of cockpit displays [SAE PAPER 892283] p1176 A93-53200 aerospace applications p 1217 A93-53515 [AIAA PAPER 93-3593] p 1224 A93-52685 CHENG, BIN DAVIS, M. J. EPIFANOV, V. M. Air carriers' liability for passenger injury or death - The Reinforcement of the F-111 wing pivot fitting with a Mathematical modeling of the three-dimensional Japanese Initiative and Response to the recent EC boron/epoxy doubler system - Materials engineering temperature fields of turbine blades Consultation Paper p 1226 A93-52930 aspects p 1214 A93-54241 p 1216 A93-53329

B-2 PERSONAL AUTHOR INDEX HATTINGH, H. V.

ERIKSSON, L.-E. FUKUMOTO, M. GOTO, MITSUSHIGE Large eddy simulation of turbulent combustion behind The properties of newly developed highly damage Performance improvement by forward-skewed blading flame holders tolerant and easy handleable carbon fiber/modified of axial fan moving blades | ISABE 93-7042) p1198 A93-54018 bismaleimide prepreg system p 1212 A93-53448 | ISABE 93-7055] p1185 A93-54031 EUSTACE, RICHARD GOVARDHAN, M. Neural network fault diagnosis of a turbofan engine Tip clearance effects on the flow field of an axial turbine I ISABE 93-7091 ] p 1203 A93-54067 rotor blade cascade I ISABE 93-7057] p1185 A93-54033 GAMMA, F. GRACEY, C. Performance and configuration analysis of jet-engine Analysis of a turning point problem in flight trajectory off-design behavior optimization p 1210 A93-52885 I ISABE 93-7087] p 1202 A93-54063 FABRY, E. GANESAN, V. GRAY, HUGH R. The leading edge vortex of a rotating stall cell A study on 3-D velocity distribution of isothermal flows Overview of NASA's advanced high temperature engine (ISABE 93-7009] p1183 A93-53985 behind an afterburner flame stabilizer materials technology program p 1212 A93-53453 FAN, SIXIN [ISABE 93-7039] p1197 A93-54015 GREBESHOV, EH. P. Low-Reynolds-number k-epsilon model for unsteady GANG, CHEN Unsteady aerodynamic characteristics of three turbulent boundary-layer flows p1177 A93-53208 Longitudinal closed-loop pilot/vehicle analysis of DFBW rectangular wings of different aspect ratios FAVINI, B. aircraft during approach and landing p1180 A93-53575 Influence of chemical kinetics effects in nozzles shape p 1206 A93-54277 GREENBLATT, DAVID design GAO, HONG Thermal fatigue life assessment of a convection-cooled I ISABE 93-7112] p1188 A93-54087 Numerical analysis of the flow through a centrifugal gas turbine blade FENG, YACHANG impeller by vortex distribution model of a boundary layer. [ISABE 93-7062] p1199 A93-54038 Longitudinal closed-loop pilot/vehicle analysis of DFBW I - Theoretical analysis p 1182 A93-53843 GREENE, FRANCIS A. aircraft during approach and landing GAO, ZHENG-HONG HL-20 computational fluid dynamics analysis p 1206 A93-54277 An implicit difference scheme of Euler equation for p1181 A93-53740 FERBER, JACQUES unsteady transonic flow p1182 A93-53852 GREENE, TIMOTHY L A reactive approach for distributed air traffic control GARG, SANJAY The characterization and development of materials for [ONERA. TP NO. 1993-83] p1190 A93-53603 A parameter optimization approach to controller advanced textile composites p 1211 A93-53434 GSCHWENDER, LOIS CRAASH - A coordinated collision avoidance system partitioning for integrated flight/propulsion control Development of MIL-H-53119. -54 C to 175 C [ONERA. TP NO. 1993-84] p 1191 A93-53604 application p 1206 A93-54268 GARLICK, RALPH G. high-temperature nonflammable hydraulic fluid for Air FERRANTI, MICHAEL Force systems p 1214 A93-54250 Removing the risk from rotorcraft testing The chemistry of Saudi Arabian sand - A deposition problem on helicopter turbine airfoils GUICHETEAU, PH. p 1192 A93-53772 p 1216 A93-53468 Stability analysis through bifurcation theory. I, II FERRI DEGLI ANTONI, L. GARNERO, P. [ONERA, TP NO. 1993-108] p 1225 A93-53620 Performance and configuration analysis of jet-engine CFD for ramjet and scramjet powered vehicles Non-linear flight dynamics off-design behavior [ISABE 93-7035] p1197 A93-54011 [ONERA. TP NO. 1993-109] p 1206 A93-53621 [ISABE 93-7087] p 1202 A93-54063 GARROOD, STUART T. GUN'KO, YU. P. FIRSOV, V. A. Pilot evaluations of augmented flight simulator motion Effect of boundary layer suction on the thrust and Nonlinear deformation mechanics of multilayer [AIAA PAPER 93-3580] p 1208 A93-52676 aerodynamic efficiency of a hypersonic flight vehicle transparency elements - Some calculation results GEIDEL, H. A. p1176 A93-52959 p 1191 A93-52937 Axial flow compressors - Mechanical design trends GUPTA, ASHWANI K. FISHER, JERRY F. [ISABE 93-7061] p1199 A93-54037 Low NO(x) combustor development using aerodynamic Avionic systems in support of covert helicopter GEORGE, GARY staging operations p 1193 A93-54294 Transport delay compensation - An inexpensive [ISABE 93-7021] p1195 A93-53997 FITZPATRICK, J. A. alternative to increasing image generator update rate GURUPRASAD, G. The application of diffusion bonding in the manufacture [AIAA PAPER 93-3563] p 1223 A93-52663 Reusable code for helicopter simulation of aeroengine components p 1217 A93-53514 GHEZZI, U. [AIAA PAPER 93-3594] p 1224 A93-52686 FLEETER, SANFORD Performance and configuration analysis of jet-engine GURUPRASAD, S. A. Characterisation of conventional and controlled diffusion Forcing function modeling for flow induced vibration off-design behavior stator blades in a transonic compressor stage [ISABE 93-7027] p1196 A93-54003 [ISABE 93-7087] p 1202 A93-54063 GILERSON, A. A. [ISABE 93-7124] p1189 A93-54099 FLORENTINE, ROBERT A. GUSAROV, S. A. 3-D braided preforms; cost to manufacture: A study of optical distortions arising in radiation transmission through cavities with gas flow around them The combined effect of clearances and peripheral Magnaweave. I - Identifying cost factors overlaps on the efficiency of microturbines with shroudless p 1226 A93-53423 p 1225 A93-52945 GILKEY, SAMUEL rotors p1193 A93-52963 FORSYTHE, R. A. GUTMARK, E. Royal Air Force support helicopters - Night operations Engine technology challenges for a 21st Century High-Speed Civil Transport Periodic chemical energy release for active combustion p 1190 A93-54293 [ISABE 93-7064] p 1200 A93-54040 control FOURMAUX, ANTOINE GILREATH, H. E. [ISABE 93-7043] p1198 A93-54019 3D and 2.5D viscous flow computations for axial flow Enhanced fuel-air mixing in hypersonic engines turbine blades [ISABE 93-7115] p 1221 A93-54090 H [ISABE 93-7093] p1186 A93-54069 GINTY, CAROL A. FRESKOS, G. Overview of NASA's advanced high temperature engine HAH, C. On the numerical simulation of the two-dimensional flow materials technology program p 1212 A93-53453 field around a hypersonic air-intake-compressibility Three-dimensional flow analysis inside turbomachinery GIRGIS, S. stages with steady and unsteady Navier-Stokes method effects Effect of nozzle design on the performance of a highly [ISABE 93-7100] p1187 A93-54076 [ISABE 93-7095] p1186 A93-54071 loaded turbine stage HALL, U. FRITZEN, CLAUS-PETER [ISABE 93-7096] p 1203 A93-54072 Effects of blade geometry and mode shape on fan Identification of nonlinear mechanical systems using GIRKE, M. flutter combined state and parameter evaluation Numerical simulation of a two-dimensional supersonic [ISABE 93-7028] p1196 A93-54004 p 1224 A93-52732 mixed-compression inlet HANCOCK, J. W. FRONEK, DENNIS [ISABE 93-7107] p1188 A93-54083 Thermal design and analysis of an exhaust diffuser unit Initial results from the NASA Lewis wave rotor GNOFFO, PETER A. in a ceramic composite experiment Upwind-biased, point-implicit relaxation strategies for [ISABE 93-7060] p 1220 A93-54036 [AIAA PAPER 93-2521 ] p1193 A93-53589 hypersonic flowfield simulations on supercomputers HANNEMANN, K. FUJITA, H. p1175 A93-52770 Numerical simulation of a two-dimensional supersonic Transonic discharge flows around diffuser vanes from GOGOLIN, V. P. mixed-compression inlet a centrifugal impeller Estimation of the effect of the longitudinal moment due [ISABE 93-7107] p1188 A93-54083 [ISABE 93-7053] p1185 A93-54029 to the engine thrust on the mass of a subsonic passenger HANNEMANN, V. FUJIWARA, TOSHI aircraft p 1191 A93-52954 Numerical simulation of a two-dimensional supersonic LIF visualization of 3-dimensional hypersonic mixing GOH, JEFFREY mixed-compression inlet [ISABE 93-7114] p 1221 A93-54089 Air transport and the environment - Regulating aircraft [ISABE 93-7107] p1188 A93-54083 noise p 1226 A93-52931 Characteristics of heat exchanger in HARRISON, LAURIE supersonic/subsonic flows GOLDIEZ, BRIAN International aerospace STI p 1227 A93-53826 [ISABE 93-7119] p 1221 A93-54094 Representation of vehicle location in networked HARTNESS, J. T. FUKANO, TOHRU simulations The characterization and development of materials for Experimental investigation into the mechanism of [AIAA PAPER 93-3582] p 1214 A93-52677 advanced textile composites p 1211 A93-53434 discrete frequency noise (DFN) generation from a NACA GOLDIEZ, BRIAN F. HARVEY, ALBERT D. 0012 blade p 1225 A93-53194 Networks extend simulation's reach Space marching calculations about hypersonic FUKUDA, MASAHIRO p 1225 A93-53770 configurations using a solution-adaptive mesh algorithm Two-dimensional and three-dimensional mixing flow GOLDMAN, Y. p1177 A93-53212 structures with injected through slotted nozzle and circular Study of a pulse ramjet based on twin valveless HATTINGH, H. V. nozzle into supersonic flows combustors coupled to operate in antiphase The design and development of an afterburner [ISABE 93-7117] p 1221 A93-54092 [ISABE 93-7038] p1197 A93-54014 [ISABE 93-7041 ] p1198 A93-54017

B-3 HAYASHI, HIDECHITO PERSONAL AUTHOR INDEX

HAYASHI, HIDECHITO IKEDA, YUJI KALASHNIKOV, A. I. Experimental investigation into the mechanism of Isothermal flow characteristics behind V-shape gutter Nonlinear deformation mechanics of multilayer discrete frequency noise (DFN) generation from a NACA with and without injection transparency elements - Some calculation results 0012 blade p 1225 A93-53194 [ISABE 93-70401 p1198 A93-54016 p1191 A93-52937 HAYASHI, S. IONOV, A. A. KALFAS, A. I. The properties of newly developed highly damage An experimental study of reinforced panels of composite Experimental investigation of boundary layer transition tolerant and easy handleable carbon fiber/modified materials p 1215 A93-52975 on a flat plate with C4 leading edge bismaleimide prepreg system p 1212 A93-53448 IONTA, P. [ISABE 93-7123] p 1222 A93-54098 HE, LONG-DE A finite element code for gas turbine combustor flow KALLINDERIS, Y. Analytical expression of dissipation integral for kinetic with Stretched Laminar Flamelet modelling Prismatic grid generation for three-dimensional complex energy integral equation p 1183 A93-53860 [ISABE 93-7127] p 1204 A93-54102 geometries p1178 A93-53217 HECHT, RALPH J. ISAACS, D. KAMEMOTO, KYOJI Material requirements for the High Speed Civil Numerical analysis of the flow through a centrifugal Aerodynamics of turbine blades with trailing-edge Transport impeller by vortex distribution model of a boundary layer. damage - Measurements and computations | ISABE 93-7067] p 1200 A93-54043 I - Theoretical analysis p 1182 A93-53843 [ISABE 93-71301 p1189 A93-54105 HENBEST, S. M. KANDA, TAKESHI Measurement and prediction of flow in a gas turbine ISHII, HIROSHI Effect of film cooling/regenerative cooling on scramjet engine exhaust plume Study on surge and rotating stall in axial compressors. engine performances [ISABE 93-7113] p 1204 A93-54088 Ill - Numerical model for multiblade-row compressors [ISABE 93-7036] D1197 A93-54012 HENNECKE, D. K. p1181 A93-53799 Starting characteristics of scramjet inlets Heat transfer and material temperature conditions in the ISHIZAWA, K. [ISABE 93-7105] p 1203 A93-54081 leading edge area of impingement-cooled turbine vanes New developments with the V2500 engine KARAS', O. V. I ISABE 93-7076] p 1220 A93-54052 [ISABE 93-7085] p 1202 A93-54061 Calculation of flow fields near a lifting wing HILL, JAMES D. ISKAKOV, K. M. P1179 A93-53552 Mach 5 turboramjet requirements and design Effect of rotation on heat transfer and hydraulic KASHIWABARA, YASUSHIGE approach resistance in the radial cooling channels of turbine rotor Study on surge and rotating stall in axial compressors. [ISABE 93-7015] p1194 A93-53991 blades p 1215 A93-52950 Ill - Numerical model for multiblade-row compressors HILL, RICHARD J. ITAHARA, H. P1181 A93-53799 The challenge of IHPTET Research and development of a turbo-accelerator for KASHIWAGI, TAKESHI [ISABE 93-7001 | p1194 A93-53978 super/hypersonic transport Test results of the hydrogen fueled model combustor HINCHEY, M. J. [ISABE 93-7066] p 1200 A93-54042 for the air turbo ramjet engine On hovercraft overwater heave stability ITO, TAKESHI [ISABE 93-7082] p 1201 A93-54058 p 1219 A93-53819 Wind tunnel tests of the model of intake-airframe KATO, DAI Ketvin-Helmholtz wave generation beneath hovercraft integration A 2-D compressible N-S simulation of starting- and skirts p 1219 A93-53820 (ISABE 93-7101] p1192 A93-54077 stalling-flows in a compressor cascades system HINES, RICHARD ITOH, H. [ISABE 93-7006] p1183 A93-53982 Engine technology challenges for a 21st Century Tandem transverse hydrogen gas injection into a KATZ, AMNON High-Speed Civil Transport supersonic airflow Methodology for integration of digital control loaders in [ISABE 93-7064] p 1200 A93-54040 [ISABE 93-7069] p 1201 A93-54045 aircraft simulators HIPPENSTEELE, STEVEN A. IVANOV, M. J. [AIAA PAPER 93-3551 ] p 1207 A93-52655 Measurements and computational analysis of heat Design of high-load aviation lurbomachines using KAWASHIMA, TAKASHI transfer and flow in a simulated turbine blade internal modern 3D computational methods Three-dimensional viscous flow analysis of compressor- cooling passage [ISABE 93-7032] p1196 A93-54008 cascade channels p1181 A93-53837 [AIAA PAPER 93-1797] p 1218 A93-53585 KAY A, T. HIRAIWA, TETSUO Investigation of the flow field through a variable pitch Off-design performance of scramjet nozzles fan rotor with an inlet total pressure distortion [ISABE 93-7108] p 1203 A93-54084 [ISABE 93-7029] p1184 A93-54005 HIRANO, K. JACKSON, E. B. Active control of vortex breakdown by a spinning wave KAZIMIROV, I. V. Effect of lift-to-drag ratio in pilot rating of the HL-20 generator A finite element for modeling skins of composite landing task p 1210 A93-53738 materials p 1215 A93-52979 [ISABE 93-7045) p 1219 A93-54021 JAMESON, ANTONY HIRSCHEL, E. H. KEELING, S. L. Multigrid Navier-Stokes calculations for Heat loads as key problem of hypersonic flight Linear quadratic tracking problems in Hilbert space - three-dimensional cascades p 1177 A93-53209 p 1222 A93-54276 Application to optimal active noise suppression JIANG, CAI-HONG HOLDEMAN, JAMES D. p 1224 A93-52763 A study of surge control by using pulse cut-off for dual KHALIL, S. E. Mixing of multiple jets with a confined subsonic spool turbo-jet engine p 1194 A93-53862 crossflow p1189 A93-54324 Blowout of turbulent disc/pilot stabilized jet diffusion JIANG, MING HOLOWECKY, BRIAN R. flames A study of aircraft global dynamic stability in rapid rolling A parameter optimization approach to controller [ISABE 93-7026] p 1213 A93-54002 maneuver p 1206 A93-53869 partitioning for integrated flight/propulsion control KHAZANOV, KH. S. JOHNSON, ANDREW M. application p 1206 A93-54268 A nonlinear finite element of an arbitrary beam Material requirements for the High Speed Civil p 1215 A93-52939 HOMMA, NAOKI Transport LIF visualization of 3-dimensional hypersonic mixing [ISABE 93-7067] p 1200 A93-54043 KHROLOVICH, K. B. [ISABE 93-7114] p 1221 A93-54089 JOHNSON, ARTHUR W. A method for the spectral-time identification of the HONAMI, SHINJI Observations of liquid jets injected into a highly longitudinal and lateral motions of an aircraft A study on Mach 3 two-dimensional mixed compression accelerated supersonic boundary layer p 1205 A93-52942 air-intakes p1177 A93-53214 KIKUCHI, H. [ISABE 93-7106] p1188 A93-54082 JOHNSON, TIMOTHY A. New approximate method of stress analysis for bladed HOSOKAWA, SHIGEO Skin-friction topology over a surface mounted rotating discs Isothermal flow characteristics behind V-shape gutter semi-ellipsoidal wing at incidence p 1178 A93-53216 [ISABE 93-7059] p 1219 A93-54035 with and without injection JOUET, C. KIKUCHI, K. [ISABE 93-7040] p1198 A93-54016 3D laminar and 2D turbulent computations with the Navier-Stokes computation of the three dimensional flow HU, J. Navier-Stokes solver FLU3M fields through a transonic fan blade An investigation of post stall transients and recoverability [ONERA, TP NO. 1993-105] p1180 A93-53618 (ISABE 93-7030] p1184 A93-54006 of axial compression systems KIKUCHI, M. [ISABE 93-7012] p1184 A93-53988 Active control of vortex breakdown by a spinning wave HU, SI-MING K generator A study of surge control by using pulse cut-off for dual [ISABE 93-7045] p 1219 A93-54021 spool turbo-jet engine p 1194 A93-53862 KACHANOV, B. O. HUANG, XUEQIAO A method for the spectral-time identification of the KILLEY, KEVIN G. A comparative assessment of two present generation A dual-Euler method for solving all-attitude angles of longitudinal and lateral motions of an aircraft the aircraft p 1205 A93-52942 turbine analysis codes [ISABE 93-7097] p 1203 A93-54073 [AIAA PAPER 93-3589] p 1223 A93-52682 KAISER, STEFAN A. HUSSIEN, B. Stumbling blocks for airport construction in the new KIM, K. Passive range estimation for rotorcraft low-altitude German federal states p 1227 A93-53727 Fluid dynamics and convective heat transfer in impinging flight p1190 A93-52881 KAJI, SHOJIRO jets through implementation of a high resolution liquid HYDE, CHARLES R. Analysis of unstarted supersonic flutter in cascade by crystal technique Instrumentation and telemetry systems for free-flight semiactuator disk theory p1181 A93-53841 [ ISABE 93-7077) p 1220 A93-54053 drop model testing p 1209 A93-52754 Study on unstart and its propagation along modules due KIM, M. N. to compound choking and/or fluctuations in combustor An ultra low NO(x) pilot combustor for staged low NO(x) of scramjet engines combustion [ISABE 93-7052] p1199 A93-54028 (ISABE 93-7020 ] p 1195 A93-53996 Numerical and experimental study on two- and KINOSHITA, Y. IGNAT'EV, S. G. three-dimensional supersonic flow field with hydrogen Studies on methane-fuel ram combustor for HST Calculation of flow fields near a lifting wing injection combined cycle engine p1179 A93-53552 [ISABE 93-7118] p1188 A93-54093 [ISABE 93-7080] p 1201 A93-54056

B-4 PERSONAL AUTHOR INDEX MALIK, M. R.

KIREEV, V. A. KRUPA, V. G. LIBIS, N. A procedure for the thermal and strength testing of Design of high-load aviation turbomachines using Study of a pulse ramjet based on twin valveless radiouansparent shells p 1209 A93-52976 modern 3D computational methods combustors coupled to operate in antiphase KIRSTEN, TREVOR J. IISABE 93-7032] p1196 A93-54008 | ISABE 93-70381 p1197 A93-54014 Thermal fatigue life assessment of a convection-cooled KRUPAR, MARTIN J. LIFANOV, I. K. gas turbine blade Laser velocimeter measurements of the flow field Construction of wakes in the discrete vortex method [ISABE 93-7062] pi 199 A93-54038 generated by a forward-swept propfan during flutter p 1179 A93-53333 KITAJIMA, J. [AIAA PAPER 93-2919] p1180 A93-53591 LIN, K. C. Studies on methane-fuel ram combustor for HST KRYLOV, B. A. The numerical errors in inverse simulation combined cycle engine The combined effect of clearances and peripheral [ AIAA PAPER 93-3588] p 1223 A93-52681 | ISABE 93-7080] p 1201 A93-54056 overlaps on the efficiency of microturbines with shroudless LIN, KUO-CHI KIYOTO, SHIN-ICHIRO rotors p1193 A93-52963 Representation of vehicle location in networked Application of functionally gradient materials to scramjet KUMAGAI, T. simulations engines A new cooling system for ultra high temperature [AIAA PAPER 93-3582) p 1214 A93-52677 | ISABE 93-7063] p 1200 A93-54039 turbines Reusable code for helicopter simulation KLEIN, W. A. [ ISABE 93-7073] p 1201 A93-54049 [AIAA PAPER 93-3594] p 1224 A93-52686 Aerodynamics of turbine blades with trailing-edge KURODA, SHIGEAKI LIN, WANG Z. damage - Measurements and computations Numerical analysis of a flat plate in a pitching motion. Longitudinal closed-loop pilot/vehicle analysis of DFBW IISABE 93-7130] p 1189 A93-54105 II - Effect on the flow of the position of the pivot, etc KOBAYASHI, H. aircraft during approach and landing P1181 A93-53798 p 1206 A93-54277 Noise reduction of supersonic heated jet with jet mixing KUROSAKA, M. LISLE, CURTIS enhancement by tabs Active control of vortex breakdown by a spinning wave I ISABE 93-70461 p1198 A93-54022 Reusable code for helicopter simulation generator [ AIAA PAPER 93-3594] p 1224 A93-52686 KOBAYASHI, K. [ISABE 93-7045] p 1219 A93-54021 Research and development of high pressure compressor LISZEWSKI, ANNA M. KUT'INOV, V. F. for SST and HST engine The T700 ... from salt spray to sand blast Design and fabrication of panels with cutouts | ISABE 93-7068] p1186 A93-54044 p 1205 A93-54292 p1215 A93-52973 KODAMA, YOSHIO LIU, CHANG Experimental investigation into the mechanism of A study of aircraft global dynamic stability in rapid rolling discrete frequency noise (DFN) generation from a NACA maneuver p 1206 A93-53869 0012 blade p 1225 A93-53194 LIU, FENG KOHARA, S. Multigrid Navier-Stokes calculations for LAHR, THOMAS Research and development of a turbo-accelerator for three-dimensional cascades p1177 A93-53209 International aerospace STI p 1227 A93-53826 super/hypersonic transport LOETSCHER, TONY [ISABE 93-7066] p 1200 A93-54042 LAING, P. Two and three-dimensional prediffuser combustor Operating helicopters in a demanding environment - KOMURO, TOMOYUKI Mountain flying/high evaluations p 1190 A93-54289 Ignition and combustion performance of a scramjet studies with air-water mixture LOTTES, P. combustor with a fuel injection strut [ISABE 93-7025] p 1213 A93-54001 Axial flow compressors - Mechanical design trends LAKSHMANAN, B. K. | ISABE 93-70501 p1199 A93-54026 [ISABE 93-7061] p1199 A93-54037 KONO, M. Development of a real time dynamic engine simulation A study of self-ignition of methane-hydrogen mixture fuel model of a turbo fan engine LOUGHER, WAYNE Preparation and characterization of continuous fiber injected into high enthalpy supersonic airstreams [ISABE 93-71321 P 1205 A93-54107 reinforced zirconium diboride matrix composites for a IISABE 93-7049] p 1213 A93-54025 LAKSHMINARAYANA, B. leading edge material p1211 A93-53445 KOPYLOVA, L V. Navier-Stokes analysis of turbine flowfield and external An experimental study of reinforced panels of composite heat transfer LOVE, WENDELL L. materials p 1215 A93-52975 IISABE 93-7075] p1186 A93-54051 Evaluation of 2D ceramic matrix composites in aeroconvective environments p 1212 A93-53459 KOSTEGE, V. K. LAKSHMINARAYANA, BUDUGUR Design of high-load aviation turbomachines using Low-Reynolds-number k-epsilon model for unsteady LU, P. modern 3D computational methods turbulent boundary-layer flows p 1177 A93-53208 The numerical errors in inverse simulation [AIAA PAPER 93-3588] p 1223 A93-52681 IISABE 93-7032] p1196 A93-54008 LANGLEY, R. S. KOTAKE, MUTSUO A dynamic stiffness/boundary element method for the LUNDQUIST, DAVID L. Pressure distribution measurement around hypersonic • prediction of interior noise levels p 1226 A93-53817 LONGBOW - Force multiplier for continuous delta winged semicone - Measurement by means of operations p1175 A93-54295 LAPISKA, CARL magnet tape p1176 A93-53193 Flight simulation - An overview p 1209 A93-53768 LUO, J. Shock shapes around slender diamond cones traveling Navier-Stokes analysis of turbine flowfield and external LAROCCA, FRANCESCO at hypersonic speed p1181 A93-53840 heat transfer Design of air intakes and nozzles for transonic rotational Study on flow field around slender diamond cone (ISABE 93-7075] p1186 A93-54051 flows traveling at hypersonic speed p1189 A93-54314 LURAULT, ISABELLE KOTANI, Y. [ISABE 93-7102] p1187 A93-54078 LAVRICH, P. Compact heat exchanger fitted to engines of the inverted Tandem transverse hydrogen gas injection into a type Active aerodynamic control of wake-airfoil interaction supersonic airflow [ISABE 93-7120] p 1221 A93-54095 [ISABE 93-70691 p 1201 A93-54045 noise - Experiment p 1225 A93-53206 KOVALEV, V. E. LAWRENCE, SCOTT L. Calculation of a compressible three-dimensional Space marching calculations about hypersonic M boundary layer on a swept wing p 1179 A93-53551 configurations using a solution-adaptive mesh algorithm KOVRIZHKIN, O. G. P1177 A93-53212 MA, HAN-DONG Solution of the boundary value problem in flight dynamics LEIJOENS, H. Numerical study of supersonic flow over a backward by the opposite motion method p 1206 A93-52944 The reduction of skin friction by riblets under the step with transverse injection p 1182 A93-53853 KOWALECZKO, G. influence of an adverse pressure gradient MA, YAN-WEN Analysis of spatial motion dynamics of a helicopter for p 1218 A93-53810 Numerical study of supersonic flow over a backward various models of the induced velocity field LEISHMAN, J. G. step with transverse injection p 1182 A93-53853 p1191 A93-53721 Boundary layer and pressure measurements on a MACKALL, DALE A. KOZHEVNIKOV, YU. V. cylinder with unsteady circulation control Flight research simulation takes off Identification of the phase characteristics and p1177 A93-53207 p1192 A93-53769 wind-induced perturbations of an aircraft from flight test LENTINI, D. MACOUISTEN, M. A. results p 1206 A93-52943 A finite element code for gas turbine combustor flow Low-frequency combustion oscillations in a model KOZLOV, V. A. with Stretched Laminar Flamelet modelling afterburner p1193 A93-53702 Design and fabrication of panels with cutouts [ISABE 93-7127] p 1204 A93-54102 MAEKAWA, SHOZO p1215 A93-52973 Two-dimensional and three-dimensional mixing flow LEWY, SERGE KOZLOV, V. P. structures with injected through slotted nozzle and circular The acoustics of axial compressors nozzle into supersonic flows Moving wall effects in transverse subsonic flow past a [ONERA, TP NO. 1993-102] p 1226 A93-53615 rotating cylinder p1179 A93-53573 [ISABE 93-7117] p 1221 A93-54092 Acoustic-wave propagation in ducts and free-field KRAMARENKO, E. A. MAGRE, P. radiation Solution of the boundary value problem in flight dynamics CARS temperature measurements in combustion [ONERA, TP NO. 1993-103] p 1226 A93-53616 by the opposite motion method p 1206 A93-52944 [ONERA, TP NO. 1993-78] p 1212 A93-53599 KREJNIN, V. G. LI, LIGUO MAINGRE, E. A procedure for the thermal and strength testing of Impingement cooling with film coolant extraction in the Optimization of afterbodies and engine nozzle by using radiotransparent shells p 1209 A93-52976 airfoil leading edge regions CFD methods KRETSCHMER, D. [ ISABE 93-7078] p 1220 A93-54054 [ISABE 93-7098] p1187 A93-54074 The prediction of thermal NO(x) in gas turbine LI, ZHAOHUI MAKAROV, L. N. exhausts Impingement cooling with film coolant extraction in the Calculation of the position of the flow separation line [ISABE 93-70221 p1195 A93-53998 airfoil leading edge regions in an analog model of flow past a body KRISHNA PRASAD, K. [ISABE 93-7078] p 1220 A93-54054 p1176 A93-52958 The reduction of skin friction by riblets under the LIAO, CHUNG-LI MALIK, M. R. influence of an adverse pressure gradient Flutter analysis of stiffened laminated composite plates Transition correlation in subsonic flow over a flat plate p1218 A93-53810 and shells in supersonic flow p 1216 A93-53224 p1178 A93-53231

B-5 MARCHANT, M. J. PERSONAL AUTHOR INDEX

MARCHANT, M. J. MILLER, PAUL G. A study on Mach 3 two-dimensional mixed compression The construction of nearly orthogonal multiblock grids Royal Navy helicopter operations in the maritime air-intakes for compressible flow simulation p 1219 A93-53847 environment p 1190 A93-54290 [ISABE 93-7106] p1188 A93-54082 MARKMAN, STEVEN R. MILLER, ROGER MURAKAMI, ATSUO USAF in-flight simulation - A cost-effective operating Internally coherent system of innovation - The case of Ignition and combustion performance of a scramjet approach flight simulation combustor with a fuel injection strut | AIAA PAPER 93-3604) p1175 A93-52690 [AIAA PAPER 93-3548) p 1226 A93-52653 [ISABE 93-7050] p1199 A93-54026 MARSILIO, R. MIMURA, f. MURAO, R. A study of the stability of vortical structutes in supersonic A new cooling system for ultra high temperature Effects of wake interaction of two turbine cascades on inlets turbines secondary/tip-leakage flows and losses | ISABE 93-7058] p 1185 A93-54034 (ISABE 93-7103) p 1187 A93-54079 [ISABE 93-7073] p 1201 A93-54049 MARTELLI, F. MURAYAMA, MOTOHIDE MINATO, MASASHI Studies on coolant problems in aeronautical turbine Ignition and combustion performance of a scramjet Isothermal flow characteristics behind V-shape gutter cascades combustor with a fuel injection strut with and without injection [ISABE 93-7074] p 1220 A93-54050 [ISABE 93-7050] p1199 A93-54026 [ISABE 93-7040] p1198 A93-54016 MASAD, J. A. MURTHY, PAPPU L. N. Transition correlation in subsonic flow over a flat plate MINEKAWA, HIDETO Design for cyclic loading endurance of composites P1178 A93-53231 Characteristics of heat exchanger in p 1216 A93-53395 supersonic/subsonic flows MASSIE, JEFFREY J. MURTHY, S. N. B. Instrumentation and telemetry systems for free-flight [ISABE 93-7119] p 1221 A93-54094 Two and three-dimensional prediffuser combustor drop model testing p 1209 A93-52754 MINER, PAUL S. studies with air-water mixture MASUTANI, JYO Characterization of the faulted behavior of digital [ISABE 93-7025] p 1213 A93-54001 Performance improvement by forward-skewed blading computers and fault tolerant systems MURTHY, V. R. of axial fan moving blades p 1224 A93-52762 An advanced rotorcraft flight simulation model - Parallel [ISABE 93-7055] p1185 A93-54031 MINH, H. H. implementation and performance analysis MASUYA, GORO On the numerical simulation of the two-dimensional flow [AIAA PAPER 93-3550] p 1222 A93-52654 Effect of film cooling/regenerative cooling on scramjet field around a hypersonic air-intake-compressibility MURUGESAN, K. engine performances effects Correlations for flow property variation at outlet of a [ISABE 93-7036) p1197 A93-54012 [ISABE 93-7100] p1187 A93-54076 centrifugal impeller Ignition and combustion performance of a scramjet MINODA, M. [ISABE 93-7054] p1185 A93-54030 combustor with a fuel injection strut Noise reduction of supersonic heated jet with jet mixing [ISABE 93-7050] p1199 A93-54026 enhancement by tabs MATSUKI, MASAKATSU [ISABE 93-7046] p1198 A93-54022 N Research and development of aircraft engine in Japan MISHULIN, I. B. - Historical review Calculation of sandwich plates with polymer composite NAGASHIMA, T. [ ISABE 93-7000] p 1227 A93-53977 skins under conditions of high humidity Transonic discharge flows around diffuser vanes from MATSUMOTO, MASASHI p1215 A93-52968 a centrifugal impeller [ISABE 93-7053] p1185 A93-54029 Off-design performance of scramjet nozzles MITANI, TOHRU [ISABE 93-7108] p 1203 A93-54084 Off-design performance of scramjet nozzles Tandem transverse hydrogen gas injection into a MAUFFRET, T. [ISABE 93-7108] p 1203 A93-54084 supersonic airflow Optimization of afterbodies and engine nozzle by using [ISABE 93-7069] p 1201 A93-54045 MITCHELL, A. CFD methods Clean melting and the removal of defects from Direct simulation of reacting fuel gas flows in a [ISABE 93-7098] p1187 A93-54074 aero-engine materials p 1217 A93-53503 supersonic mixing layer MAYA, T. [ISABE 93-7072) p 1201 A93-54048 A new cooling system for ultra high temperature MIYAGAWA, H. Conceptual design study on combined-cycle engine for NAGATA, H. turbines hypersonic transport A study of self-ignition of methane-hydrogen mixture fuel [ISABE 93-7073] p 1201 A93-54049 [ISABE 93-7018] p1195 A93-53994 injected into high enthalpy supersonic airstreams MAYER, DAVIO W. [ISABE 93-7049] p 1213 A93-54025 Boundary conditions for unsteady supersonic inlet MIYAGI, H. Conceptual design study on combined-cycle engine for NAGPURWALA, O. H. analyses Characterisation of conventional and controlled diffusion [ISABE 93-7104] p1187 A93-54080 hypersonic transport [ISABE 93-7018] p1195 A93-53994 stator blades in a transonic compressor stage MAZHUL', I. I. [ISABE 93-7124) p1189 A93-54099 Effect of boundary layer suction on the thrust and MIZUKI, SHIMPEI NAKAJIMA, TSUYOSHI aerodynamic efficiency of a hypersonic flight vehicle Numerical analysis of flow within cascade with tip Isothermal flow characteristics behind V-shape gutter p1176 A93-52959 clearance p1176 A93-53192 with and without injection MCARTHUR, DONALD E. MOBLEY, THOMAS [ISABE 93-7040] p1198 A93-54016 Terrain modeling for real-time photo-texture based visual 'No VOC' water-borne corrosion resistant primers for simulation aerospace bonding applications p 1211 A93-53419 NAKAMURA, AKIHIRO Ignition and combustion performance of a scramjet [AIAA PAPER 93-3607] p 1214 A93-52667 MONTAG, BRUCE combustor with a fuel injection strut MCCAFFERTY, J. D. Visual weather simulation using meteorological [ISABE 93-7050] p1199 A93-54026 Thermal design and analysis of an exhaust diffuser unit databases in a ceramic composite [AIAA PAPER 93-3566] p 1207 A93-52665 NAKAMURA, TOMOYUKI [ISABE 93-7060] p 1220 A93-54036 MOODY, LARRY A. Observation of fluctuation of 2D-nozzle flows MCLEOD, J. D. Dynamic simulation fidelity improvement using transfer [ISABE 93-7110] p 1204 A93-54086 Thermodynamic and neutral network computer function state extrapolation NARAYANA MURTHY, R. V. modelling of implanted component faults in a gas turbine [AIAA PAPER 93-3552] p 1222 A93-52656 Structural integrity validation of limited-life engines engine MORITA, M. [ISABE 93-7131] p 1205 A93-54106 [ISABE 93-7089] P 1202 A93-54065 Conceptual design study on combined-cycle engine for NARAYANA SWAMY, S. MCNAMARA, DAVID K. hypersonic transport Structural integrity validation of limited-life engines Durability properties for adhesively bonded structural [ISABE 93-7018] p1195 A93-53994 [ ISABE 93-7131 ] p 1205 A93-54106 aerospace applications p 1217 A93-53515 Research and development of a turbo-accelerator for NARUO, YOSHIHIRO MEDVED, BORIS L. super/hypersonic transport Development study on Air Turbo Ramjet engine for a Some acoustic features of perforated test section walls [ISABE 93-7066] p 1200 A93-54042 future space plane with splitter plates p 1226 A93-53222 MORO, AKIO [ISABE 93-7016] p1195 A93-53992 MEHRKAM, PAUL Effect of film cooling/regenerative cooling on scramjet Test results of the hydrogen fueled model combustor Wet layup materials for repair of bismaleimide engine performances for the air turbo ramjet engine composites p 1212 A93-53451 [ISABE 93-7036] p1197 A93-54012 [ISABE 93-7082] p 1201 A93-54058 MORRIS, W. D. MENK, BRUCE NEVILLE, KENDALL W. HL-20 operations and support requirements for the Innovative bagging techniques on a composite P-51 Flight update of aerodynamic math model Personnel Launch System mission p 1210 A93-53745 Mustang replica p 1191 A93-53405 [AIAA PAPER 93-3596) p 1224 A93-52687 MOUCHON, E. NG, HUAT MEYLER, KAREN l_ Origin of the carbon rich sliding interface in alkali Representation of vehicle location in networked Evaluation of water-borne adhesive bonding primers for containing matrix-SiC nicalon fibre composites simulations use on the advanced aircraft material aluminum-lithium (ONERA, TP NO. 1993-77] p 1212 A93-53598 [AIAA PAPER 93-3582] p 1214 A93-52677 p1211 A93-53420 MOUSTAPHA, S. H. MICHELASSI, V. Effect of nozzle design on the performance of a highly NICHOLAS, E. D. Studies on coolant problems in aeronautical turbine loaded turbine stage Friction surfacing and linear friction welding cascades [ISABE 93-7096) p 1203 A93-54072 p 1217 A93-53499 [ISABE 93-7074] p 1220 A93-54050 MUEHLEK, P. NIEUWSTADT, F. T. M. MIJS, J. Numerical study of nitric oxide formation in a hypersonic The reduction of skin friction by riblets under the The leading edge vortex of a rotating stall cell ramjet engine influence of an adverse pressure gradient [ISABE 93-7009] p1183 A93-53985 [ISABE 93-7125] p 1204 A93-54100 p 1218 A93-53810 MILBANK, J. MURAKAMI, AKIRA NIGMATULLIN, R. Z. Measurement and prediction of flow in a gas turbine Wind tunnel tests of the model of intake-airframe Design of high-load aviation turbomachines using engine exhaust plume integration modem 3D computational methods [ISABE 93-7113] p 1204 A93-54088 [ISABE 93-7101] p1192 A93-54077 [ISABE 93-7032] p1196 A93-54008

B-6 PERSONAL AUTHOR INDEX RIBNER, HERBERTS.

NIINO, MASAYUKI ONODERA, TAKUO PIVOVAROV, V. V. Application of functionally gradient materials to scramje! Study on unstart and its propagation along modules due A procedure for the thermal and strength testing of engines to compound choking and/or fluctuations in combustor radiotransparent shells p 1209 A93-52976 [ISABE 93-7063] p 1200 A93-54039 of scramjet engines PODBOY, GARY G. NISHIO, MASATOMI [ISABE 93-7052] p1199 A93-54028 Laser velocimeter measurements of the flow field Pressure distribution measurement around hypersonic ONOFRI, M. generated by a forward-swept propfan during flutter delta winged semicone - Measurement by means of Influence of chemical kinetics effects in nozzles shape [AIAA PAPER 93-2919] p1180 A93-53591 magnet tape p 1176 A93-53193 design POINSATTE, PHILIP E. [ISABE 93-7112] p1188 A93-54087 Shock shapes around slender diamond cones traveling Measurements and computational analysis of heat OUTA, E. at hypersonic speed p 1181 A93-53840 transfer and flow in a simulated turbine blade internal Noise reduction of supersonic heated jet with jet mixing cooling passage Study on flow field around slender diamond cone enhancement by tabs [AIAA PAPER 93-1797] p 1218 A93-53585 traveling at hypersonic speed p1189 A93-54314 [ISABE 93-7046] p1198 A93-54022 PORTER, BRIAN NISHIZAWA, TOSHIO OUTA, EISUKE Design of limit-tracking systems incorporating a turbofan Numerical study on inception of stall cells in rotating A 2-D compressible N-S simulation of starting- and engine with constant disturbances stall stalling-flows in a compressor cascades system [ISABE 93-7090] p 1203 A93-S4066 [ISABE 93-7007] p1183 A93-53983 [ISABE 93-7006] p1183 A93-53982 POTAPOV, G. P. NODA, JUNNICHI Estimation of the parameters of the electrodynamic Wind tunnel tests of the model of intake-airframe system engine-exhaust jet p1193 A93-52965 integration POWELL, RICHARD W. [ISABE 93-7101] p1192 A93-54077 PACIORRI, R. Six-degree-of-freedom guidance and control-entry NOGUCHI, S. Influence of chemical kinetics effects in nozzles shape analysis of the HL-20 p 1210 A93-53737 Tandem transverse hydrogen gas injection into a design PROCTOR, FRED H. supersonic airflow [ISABE 93-7112) p1188 A93-54087 Case study of a low-reflectivity pulsating microburst - [ISABE 93-7069] p 1201 A93-54045 PAI, B. R. Numerical simulation of the Denver, 8 July 1989, storm NOMURA, TOSHIO Characterisation of conventional and controlled diffusion p 1222 A93-52898 Application of functionally gradient materials to scramjet stator blades in a transonic compressor stage PUTERBAUCH, S. L engines [ISABE 93-7124] p 1189 A93-54099 Three-dimensional flow analysis inside turbomachinery [ISABE 93-7063] p 1200 A93-54039 PAJMUSHIN, V. I. stages with steady and unsteady Navier-Stokes method MOUSE, HIROYUKI Nonlinear deformation mechanics of multilayer [ISABE 93-7095] p1186 A93-54071 Japan's research and development program for transparency elements - Some calculation results airbreathing engine technologies p1191 A93-52937 [ISABE 93-7005] p1194 A93-53981 PALMER, GRANT Effective treatment of the singular line boundary problem NOZAKI, O. for three-dimensional grids p 1177 A93-53204 OUACKENBUSH, TODD R. Navier-Stokes computation of the three dimensional flow PALSANE, SANJAY Fast three-dimensional vortex method for unsteady wake fields through a transonic fan blade Development of a real time dynamic engine simulation calculations p1178 A93-53233 [ISABE 93-7030] p1184 A93-54006 model of a turbo fan engine [ISABE 93-7132] p 1205 A93-54107 PASINI, S. Performance and configuration analysis of jet-engine RACHAKONDA, S. off-design behavior O'HERN, T. J. Total quality management of forged products through [ISABE 93-7087] p 1202 A93-54063 finite element simulation p 1217 A93-53493 Reynolds number dependence of the drag coefficient PASTRONE, OARIO for laminar flow through fine-scale photoetched screens RADEMEYER, I. J. Nozzle effects on linear stability behaviour of The development of a new air filtration system for the p 1218 A93-53815 combustors OBATA, MASAKAZU Alouette III helicopter [ISABE 93-7044] p1198 A93-54020 [ISABE 93-7048] p1199 A93-54024 Test results of the hydrogen fueled model combustor PATEL, VIRENDRA C. for the air turbo ramjet engine RAHMAN), SHAWN Skin-friction topology over a surface mounted On definition and use of systems engineering processes, [ISABE 93-7082] p 1201 A93-54058 semi-ellipsoidal wing at incidence p 1178 A93-53216 methods and tools p 1225 A93-53642 OBATA, S. PAULSON, RANDY E. RAJAN, P. A. Direct simulation of reacting fuel gas flows in a Variable cycle engine concept Some measurements of stall in an axial impeller supersonic mixing layer [ISABE 93-7065] p 1200 A93-54041 [ISABE 93-7008] p1183 A93-53984 [ISABE 93-7072] p 1201 A93-54048 PAYNTER, GERALD C. RAMAMURTHY, S. ODGERS, J. Boundary conditions for unsteady supersonic inlet Correlations for flow property variation at outlet of a The prediction of thermal NO(x) in gas turbine analyses centrifugal impeller exhausts [ISABE 93-7104] p1187 A93-54080 [ISABE 93-7054] p1185 A93-54030 PEAKE, N. [ISABE 93-7022] p1195 A93-53998 RAO, K. V. OHBA, HIDEYUKI The unsteady flow past a supersonic splitter plate Numerical study of a delta planform with multiple jets Numerical analysis of a flat plate in a pitching motion. [ISABE 93-7047] p1185 A93-54023 in ground effect I) - Effect on the flow of the position of the pivot, etc PEALAT, M. [SAE PAPER 892283] p1176 A93-53200 p1181 A93-53798 CARS temperature measurements in combustion RAUL, R. OHKITA, YOUJI [ONERA, TP NO. 1993-78] p 1212 A93-53599 Enhanced fuel-air mixing in hypersonic engines Test results of the hydrogen fueled model combustor PEARCE, G. F. [ISABE 93-7115] p 1221 A93-54090 for the air turbo ramjet engine The prediction of thermal NO(x) in gas turbine RAVICHANDRAN, M. [ISABE 93-7082] p 1201 A93-54058 exhausts A study on 3-D velocity distribution of isothermal flows [ISABE 93-7022) p1195 A93-53998 OHWAKI, KATSURA behind an afterburner flame stabilizer PENNINGTON, I. P. Ignition and combustion performance of a scramjet [ISABE 93-7039] p1197 A93-54015 The design and development of an afterburner combustor with a fuel injection strut RAVIV, DANIEL [ISABE 93-7041] p1198 A93-54017 [ISABE 93-7050] p1199 A93-54026 A vision-based method for autonomous landing PERRELLA, ANDREW P. p1190 A93-53172 OINUMA, H. Structural applications of Avimid K3B LDF thermoplastic Noise reduction of supersonic heated jet with jet mixing RAY, JAMES A. composites p 1216 A93-53429 Environmental effects of operations during Desert enhancement by tabs PETERSON, CARL W. [ISABE 93-7046] p1198 A93-54022 Shield/Desert Storm p 1190 A93-54291 The fluid physics of parachute inflation REID, LLOYD D. OKUYAMA, SATOSHI P1189 A93-54347 Pilot evaluations of augmented flight simulator motion Two-dimensional and three-dimensional mixing flow PETOT, BERTRAND [AIAA PAPER 93-3580] p 1208 A93-52676 structures with injected through slotted nozzle and circular 3D and 2.50 viscous flow computations for axial flow REINBACHS, NAMEJS nozzle into supersonic flows turbine blades Enhancing real-time flight simulation execution by [ISABE 93-7117) p 1221 A93-54092 [ISABE 93-7093] p1186 A93-54069 intercepting Run-Time Library calls OLLEROS, F. X. PETTERSSON, A. [AIAA PAPER 93-3591] p 1224 A93-52684 Internally coherent system of innovation - The case of Effects of blade geometry and mode shape on fan RETCHFORD, J. A. flight simulation flutter Reinforcement of the F-111 wing pivot fitting with a [AIAA PAPER 93-3548] p 1226 A93-52653 [ISABE 93-7028] p1196 A93-54004 boron/epoxy doubler system - Materials engineering OLOVSSON, S. PFAFF, K. aspects p 1214 A93-54241 Large eddy simulation of turbulent combustion behind Heat transfer and material temperature conditions in the REZNICHENKO, V. I. flame holders leading edge area of impingement-cooled turbine vanes Design and fabrication of panels with cutouts [ISABE 93-7042] p1198 A93-54018 [ISABE 93-7076] p 1220 A93-54052 p 1215 A93-52973 OLSEN, MICHAEL E. PICKERINE, JO A. RIBAUD, YVES Low aspect ratio wing code validation experiment Reusable code for helicopter simulation Compact heat exchanger fitted to engines of the inverted p1176 A93-53202 [AIAA PAPER 93-3594] p 1224 A93-52686 type ONO, FUMIEI PIKULA, EH. R. [ISABE 93-7120] p 1221 A93-54095 Effect of film cooling/regenerative cooling on scramjet Estimation of the change of axial-flow compressor RIBNER, HERBERT S. engine performances characteristics during long-term service Thrust imparted to an airfoil by passage through a [ISABE 93-7036] p1197 A93-54012 p1193 A93-5Z949 sinusoidal upwash field p 1178 A93-53219

B-7 RICCITIELLO, SALVATORE R. PERSONAL AUTHOR INDEX

RICCITIELLO, SALVATORE R. SANZ, JOSE M. SHAFFER, D. K. Evaluation of 2D ceramic matrix composites in Aerodynamic inverse design and analysis for a full Durability properties for adhesively bonded structural aeroconvective environments p 1212 A93-53459 engine aerospace applications p 1217 A93-53515 RISPOLI, F. [ISABE 93-7086] p1186 A93-54062 SHAH, TUSHAR K. A finite element code for gas turbine combustor flow SARATHY, S. Durability properties for adhesively bonded structural with Stretched Laminar Flamelet modelling An advanced rotorcraft flight simulation model - Parallel aerospace applications p 1217 A93-53515 [ISABE 93-7127] p 1204 A93-54102 implementation and performance analysis SHAKARVENE, E. P. RIVERS, ROBERT A. [AIAA PAPER 93-35501 p 1222 A93-52654 Unsteady aerodynamic characteristics of three Effect of lift-to-drag ratio in pilot rating of the HL-20 SASAHARA, O. rectangular wings of different aspect ratios landing task p 1210 A93-53738 Various applications of robots in aircraft engine p1180 A93-53575 ROACH, CARL C. overhaul SHAMBLEN, CLIFFORD E. A high fidelity video delivery system for real-time flight [ISABE 93-7129) p1175 A93-54104 Ongoing challenges for titanium alloy cleanliness simulation research SATO, SHIGERU improvement in aircraft engine disk materials (AIAA PAPER 93-3558] p 1214 A93-52659 Off-design performance of scramjet nozzles p 1212 A93-53506 ROBERTS, J. D. [ISABE 93-7108] p 1203 A93-54084 SHAO, RONG S. Reinforcement of the F-111 wing pivot fitting with a SATO, TETSUYA Harmonic oscillation in FBW system boron/epoxy doubler system - Materials engineering Development study on Air Turbo Ramjet engine for a p 1206 A93-53877 aspects p 1214 A93-54241 future space plane SHARMA, SHASHI K. RODIONOV, I. N. I ISABE 93-7016] p1195 A93-53992 Development of MIL-H-53119, -54 C to 175 C Calculation of the position of the flow separation line Study on unstart and its propagation along modules due high-temperature nonflammable hydraulic fluid for Air in an analog model of flow past a body to compound choking and/or fluctuations in combustor Force systems p 1214 A93-54250 P1176 A93-52958 of scramjet engines SHATALOV, YU. S. ROKUTANOA, ITARU [ISABE 93-7052] p1199 A93-54028 Effect of rotation on heat transfer and hydraulic Development study on Air Turbo Ramjet engine for a SAWAOA, F. resistance in the radial cooling channels of turbine rotor future space plane The properties of newly developed highly damage blades p 1215 A93-52950 [ISABE 93-7016] p1195 A93-53992 tolerant and easy handleable carbon fiber/modified SHAW, ROBERT J. ROLLIN, G. bismaleimide prepreg system p 1212 A93-53448 Engine technology challenges for a 21st Century Optimization of afterbodies and engine nozzle by using SCANU, T. High-Speed Civil Transport CFD methods Corrosion of ceramic matrix composites [ISABE 93-7064] p 1200 A93-54040 [ISABE 93-7098] p1187 A93-54074 [ONERA. TP NO. 1993-82] p 1213 A93-53602 SHCHELIN, V. S. RODS, T. H. SCHADOW, K. C. Comparison of gasdynamic models in hypersonic flow The streamline throughflow method of axial Periodic chemical energy release for active combustion p1179 A93-53315 turbomachinery flow analysis control SHCHERBAK, V. G. [ISABE 93-7031] p1184 A93-54007 [ ISABE 93-7043 ] p 1198 A93-54019 Comparison of gasdynamic models in hypersonic flow ROSS, LARRY SCHAMLE, MARC F. p1179 A93-53315 Flight simulation - An overview p 1209 A93-53768 Methodology for integration of digital control loaders in SHCHERBIK, D. V. ROURKE, R. D. aircraft simulators Effect of boundary layer suction on the thrust and Implementation of expert systems within an interactive [AIAA PAPER 93-3551 ] p 1207 A93-52655 aerodynamic efficiency of a hypersonic flight vehicle tactical environment SCHAUB, U. W. p1176 A93-52959 [AIAA PAPER 93-3583] p 1223 A93-52678 Effect of nozzle design on the performance of a highly SHEPPARD, SHIRIN ROY, GABRIEL D. loaded turbine stage Development and operation of a real-time simulation at High density strained hydrocarbon fuels for air breathing [ISABE 93-7096] p 1203 A93-54072 the NASA Ames Vertical Motion Simulator propulsion SCHILLING, LAWRENCE J. [AIAA PAPER 93-3575] p 1208 A93-52671 [ISABE 93-7081] p 1213 A93-54057 Flight research simulation takes off SHIAO, MICHAEL C. RUSSELL, LOUIS M. P1192 A93-53769 Design for cyclic loading endurance of composites Measurements and computational analysis of heat SCHMIDT, PHILLIP H. p 1216 A93-53395 transfer and flow in a simulated turbine blade internal A parameter optimization approach to controller SHIMODAIRA, K. cooling passage partitioning for integrated flight/propulsion control The combustion performance of methane-fueled ram [AIAA PAPER 93-1797) p 1218 A93-53585 application p 1206 A93-54268 combustor RYOEN, R. SCHMUHL, H. J. [ISABE 93-7079] p 1201 A93-54055 Large eddy simulation of turbulent combustion behind Axial flow compressors - Mechanical design trends SHINDO, SHIGEMI flame holders [ ISABE 93-7061 ] p 1199 A93-54037 Wind tunnel tests of the model of intake-airframe [ISABE 93-7042] p1198 A93-54018 SCHROEDER, JEFFERY A. integration Simulation motion effect on single axis compensatory [ISABE 93-7101] p1192 A93-54077 tracking A study on Mach 3 two-dimensional mixed compression [AIAA PAPER 93-3579] p 1208 A93-52675 air-intakes SCHUETZ, H. [ISABE 93-7106] p1188 A93-54082 SAITO, AKIRA Numerical study of nitric oxide formation in a hypersonic SHINOZAKI, NOBORU LIF visualization of 3-dimensional hypersonic mixing ramjet engine Ignition and combustion performance of a scramjet [ISABE 93-7114] p 1221 A93-54089 [ISABE 93-7125] p 1204 A93-54100 combustor with a fuel injection strut SAITO, TORU SCHWARZ-VAN MANEN, A. [ISABE 93-7050] p1199 A93-54026 Application of functionally gradient materials to scramjet The reduction of skin friction by riblets under the SHIRAISHI, KAZUO engines influence of an adverse pressure gradient Wind tunnel tests of the model of intake-airframe [ISABE 93-7063] p 1200 A93-54039 p 1218 A93-53810 integration SAITO, TOSHIHITO SCHWEIKL, L, [ISABE 93-7101] p1192 A93-54077 Application of functionally gradient materials to scramjet New developments with the V2500 engine A study on Mach 3 two-dimensional mixed compression engines [ISABE 93-7085] p 1202 A93-54061 air-intakes [ISABE 93-7063] p 1200 A93-54039 SCHWENK, RUEOIGER [ISABE 93-7106] p1188 A93-54082 SAITO, Y. Flight safety in Europe p 1227 A93-53726 SHVAROV, V. G. Navier-Stokes computation of the three dimensional flow SCHWENK, WALTER The flow lag angle in the rotor of a centrifugal compressor fields through a transonic fan blade Flight safety in Europe p 1227 A93-53726 with allowance for viscosity effects [ISABE 93-7030] p1184 A93-54006 SCOTT, CHARLES p1179 A93-53555 SAKAGAWA, KEIJI On definition and use of systems engineering processes, Three-dimensional viscous flow analysis of compressor SHVETS, A. I. methods and tools p 1225 A93-53642 Aerodynamic characteristics of conical cascade channels p1181 A93-53837 SEEGMILLER, H. l_ SAKATA, KIMIO triangular-planform wings of low aspect ratio in subsonic Low aspect ratio wing code validation experiment stalled flow p 1180 A93-53574 Wind tunnel tests of the model of intake-airframe p1176 A93-53202 integration SIDEN, L. D. G. SEIBOLD, S. Effects of blade geometry and mode shape on fan [ISABE 93-7101] p1192 A93-54077 Identification of nonlinear mechanical systems using A study on Mach 3 two-dimensional mixed compression flutter combined state and parameter evaluation [ISABE 93-7028] p1196 A93-54004 air-intakes p 1224 A93-52732 SIGAEV, A. YU. [ISABE 93-7106] p1188 A93-54082 SEKI, Y. SAKURANAKA, NOBORU Studies on methane-fuel ram combustor for HST Identification of the phase characteristics and wind-induced perturbations of an aircraft from flight test Application of functionally gradient materials to scramjet combined cycle engine results p 1206 A93-52943 engines [ISABE 93-7080] p 1201 A93-54056 [ISABE 93-7063] p 1200 A93-54039 SEKIDO, T. SIKSIK, D. N. SAMUELSEN, G. S. Conceptual design study on combined-cycle engine for Implementation of expert systems within an interactive Emission characteristics of a model gas turbine hypersonic transport tactical environment combustor at practical conditions [ISABE 93-7018] p1195 A93-53994 [AIAA PAPER 93-3583] p 1223 A93-52678 [ISABE 93-7023] p1196 A93-53999 SEMENOV, P. K. SILCOX, R. J. SANKAR, LAKSHMI N. Stabilization of the dynamic characteristics of the Linear quadratic tracking problems in Hilbert space - Three-dimensional Navier-Stokes/full-potential coupled two-channel automatic control system of aircraft Application to optimal active noise suppression analysis for viscous transonic flow p 1178 A93-53218 p 1205 A93-52941 p 1224 A93-52763 SANSOM, RUSSELL SEVICH, G. J. SIMON, FREDERICK F. A radar altitude and line of sight attachment New developments with the V2500 engine Progress towards understanding and predicting heat [AIAA PAPER 93-3587] p 1223 A93-52680 [ISABE 93-7085] p 1202 A93-54061 transfer in the turbine gas path p 1215 A93-52751

B-8 PERSONAL AUTHOR INDEX TRET'YAKOV, P. K.

SIMONEAU, ROBERT J. STONE, H. W. TANAKA, ATSUSHIGE Progress towards understanding and predicting heat Aerodynamic heating environment definition/thermal Wind tunnel tests of the model of intake-airframe transfer in the turbine gas path p 1215 A93-52751 protection system selection for the HL-20 integration SIMONICH, J. p1181 A93-53739 I ISABE 93-7101] p1192 A93-54077 Active aerodynamic control of wake-airfoil interaction STUFFLE, KEVIN A study on Mach 3 two-dimensional mixed compression noise - Experiment p 1225 A93-53206 Preparation and characterization of continuous fiber air-intakes SIMONYI, PATRICIA S. reinforced zirconium diboride matrix composites for a IISABE 93-7106] p1188 A93-54082 Measurements and computational analysis of heat leading edge material p 1211 A93-53445 TANAKA, F. transfer and flow in a simulated turbine blade internal STYLEMANS, C. Conceptual design study on combined-cycle engine for cooling passage CFD for ramjet and scramjet powered vehicles hypersonic transport | AIAA PAPER 93-1797| p 1218 A93-53585 | ISABE 93-70351 p1197 A93-54011 IISABE 93-7018] p1195 A93-53994 SINACORI, JOHN SUGAHARA, N. Research and development of a turbo-accelerator for Texture as a visual cueing element in computer image Navier-Stokes computation of the three dimensional flow super/hypersonic transport generation. I - Representation of the sea surface fields through a transonic fan blade [ISABE 93-7066] p 1200 A93-54042 (AIAA PAPER 93-3560] p 1214 A93-52695 I ISABE 93-7030] p1184 A93-54006 TANATSUGU, NOBUHIRO SISLIAN, JEAN P. SUGIMORI, M. Development study on Air Turbo Ramjet engine for a Hypersonic shock-induced combustion ramjet The properties of newly developed highly damage future space plane performance analysis tolerant and easy handleable carbon fiber/modified [ISABE 93-7016| p1195 A93-53992 [ISABE 93-7037] p1197 A93-54013 bismaleimide prepreg system p 1212 A93-53448 Test results of the hydrogen fueled model combustor SJOLANDER, S. A. SUGIYAMA, YOKICHI for the air turbo ramjet engine Aerodynamics of turbine blades with trailing-edge Observation of fluctuation of 2D-nozzle flows [ISABE 93-7082! p 1201 A93-54058 damage - Measurements and computations IISABE 93-7110] p 1204 A93-54086 TANG, G. C. I ISABE 93-7130 ] p1189 A93-54105 SULLINS, G. A. An investigation of post stall transients and recoverability SKAAR, TORE Enhanced fuel-air mixing in hypersonic engines of axial compression systems Arctic environment - Helicopter operations in cold [ISABE 93-7012) p1184 A93-53988 |ISABE 93-7115] p 1221 A93-54090 climates p1189 A93-54288 TANI, KOUICHIRO SULLIVAN, P. A. SKOMOROKHOV, V. I. Starting characteristics of scramjet inlets On hovercraft overwater heave stability Viscosity of aviation fuel components - Aromatic [ISABE 93-7105) p 1203 A93-54081 p 1219 A93-53819 hydrocarbons (alkyl benzenes) p 1211 A93-52961 TANNOU, MICHIAKI SKOVRTSOV, YU. V, Kelvin-Helmholtz wave generation beneath hovercraft Two-dimensional and three-dimensional mixing flow A nonlinear finite element of an arbitrary beam skirts p 1219 A93-53820 structures with injected through slotted nozzle and circular p 1215 A93-52939 SUN, JIAN-GUO nozzle into supersonic flows SMART, DON A study of surge control by using pulse cut-off for dual IISABE 93-7117] p 1221 A93-54092 Flight simulation - An overview p 1209 A93-53768 spool turbo-jet engine p 1194 A93-53862 TASKE, LEO E. SMIALEK, JAMES L. SUN, WAN-FENG The characterization and development of materials for The chemistry of Saudi Arabian sand - A deposition A study of surge control by using pulse cut-off for dual advanced textile composites p 1211 A93-53434 problem on helicopter turbine airfoils spool turbo-jet engine p1194 A93-53862 TATARA, A. p 1216 A93-53468 SUN, YEE-WIN Studies on methane-fuel ram combustor for HST SMIRNOV, A. V. Flutter analysis of stiffened laminated composite plates combined cycle engine Calculation of flow fields near a lifting wing and shells in supersonic flow p 1216 A93-53224 I ISABE 93-7080] p 1201 A93-54056 p1179 A93-53552 SUNDARARAJAN, V. TATEISHI, TOMOHIRO SMITH, GRAHAM Development of a real time dynamic engine simulation Velocity fluctuation based on the difference in the flow A comparative assessment of two present generation model of a turbo fan engine pattern in the channels of a centrifugal impeller turbine analysis codes [ISABE 93-7132] p 1205 A93-54107 p1182 A93-53842 | ISABE 93-7097] p 1203 A93-54073 SUORSA, R. TAYLOR, M. V. SMITH, M. Passive range estimation for rotorcraft low-altitude The low frequency aeroacoustics of buried nozzle The numerical errors in inverse simulation flight p1190 A93-52881 systems p 1205 A93-54244 [AIAA PAPER 93-3588] p 1223 A93-52681 TEIMANN, J. SUZUKI, K. SMITH, R. A. Sensors with centroid based common sensing scheme Periodic chemical energy release for active combustion The combustion performance of methane-fueled ram and their multiplexing p 1192 A93-52994 combustor control THEUNISSEN, E. I ISABE 93-7043] p1198 A93-54019 [ISABE 93-7079] p 1201 A93-54055 A primary flight display for four-dimensional guidance SMITH, V. K. Ill SUZUKI, M. and navigation influence of tunnel size and level of Complementary role of ground testing, flight testing, and Research and development of a turbo-accelerator for additional information on pilot performance and control computations in aerospace plane propulsion super/hypersonic transport behaviour development [ISABE 93-7066) p 1200 A93-54042 [AIAA PAPER 93-3570] p 1208 A93-52668 I ISABE 93-7034 ] ' p1197 A93-54010 SUZUKI, Y. THURMAN, DOUGLAS R. SNYDER, CARL E., JR. Effects of wake interaction of two turbine cascades on Measurements and computational analysis of heat Development of MIL-H-53119, -54 C to 175 C secondary/tip-leakage flows and losses transfer and flow in a simulated turbine blade internal high-temperature nonflammable hydraulic fluid for Air [ISABE 93-7058] p1185 A93-54034 cooling passage Force systems p 1214 A93-54250 SWEENEY, CHRISTOPHER [AIAA PAPER 93-17971 p 1218 A93-53585 SOFRIN, T. Development and operation of a real-time simulation at TIMNAT, Y. M. Active aerodynamic control of wake-airfoil interaction the NASA Ames Vertical Motion Simulator Design and testing methods of high performance noise - Experiment p 1225 A93-53206 [AIAA PAPER 93-3575] p 1208 A93-52671 combustors for airbreathing engines SONAR, TH. [ISABE 93-7024) p1196 A93-54000 Numerical simulation of a two-dimensional supersonic TIRSKIJ, G. A. mixed-compression inlet Application of the small parameter method to the | ISABE 93-71071 p1188 A93-54083 problem of three-dimensional flow of a viscous gas past SOUNDRANAYAGAM, S. TADA, H. bodies p1178 A93-53314 Some measurements of stall in an axial impeller The properties of newly developed highly damage TOKUNAGA, TATSURU | ISABE 93-70081 p1183 A93-53984 tolerant and easy handleable carbon fiber/modified Starting characteristics of scramjet inlets SOWA, W. A. bismaleimide prepreg system p 1212 A93-53448 [ISABE 93-7105] p 1203 A93-54081 Emission characteristics of a model gas turbine TAGUCHI, H. TOMINAGA, TETSUO combustor at practical conditions A study of self-ignition of methane-hydrogen mixture fuel Performance improvement by forward-skewed blading (ISABE 93-70231 p 1196 A93-53999 injected into high enthalpy supersonic airstreams of axial fan moving blades SREENIVASAN, K. R. [ISABE 93-7049] p 1213 A93-54025 [ISABE 93-7055) p1185 A93-54031 Observations of liquid jets injected into a highly TOMIOKA, S. TAKATA, HIROYUKI accelerated supersonic boundary layer A study of self-ignition of methane-hydrogen mixture fuel Numerical study on inception of stall cells in rotating P1177 A93-53214 injected into high enthalpy supersonic airstreams stall SRIDHAR, B. [ISABE 93-7049) p 1213 A93-54025 [ISABE 93-7007) p1183 A93-53983 Passive range estimation for rotorcraft low-altitude TOMITA, TAKEO flight p 1190 A93-52881 TAKI, M. LIF visualization of 3-dimensional hypersonic mixing STANKEVICH, I. V. A new cooling system for ultra high temperature [ISABE 93-7114) p 1221 A93-54089 Mathematical modeling of the three-dimensional turbines TOPOL, D. temperature fields of turbine blades [ISABE 93-70731 p 1201 A93-54049 Active aerodynamic control of wake-airfoil interaction p 1216 A93-53329 TALLEY, GREGORY D. noise - Experiment p 1225 A93-53206 STEPHENS, A. T. The T700 ... from salt spray to sand blast TORCZYNSKI, J. R. Flight update of aerodynamic math model p 1205 A93-54292 Reynolds number dependence of the drag coefficient | AIAA PAPER 93-3596] p 1224 A93-52687 TALYZINA, V. S. for laminar flow through fine-scale photoetched screens STEPHENS, JOSEPH R. Estimation of the change of axial-flow compressor p 1218 A93-53815 Material requirements for the High Speed Civil characteristics during long-term service TORELLA, GIOVANNI Transport P1193 A93-52949 Expert Systems for the simulation of turbofan engines | ISABE 93-70671 p 1200 A93-54043 TAMURA, A. [ISABE 93-7133] p 1225 A93-54108 STONE, ARTHUR Navier-Stokes computation of the three dimensional flow TRET'YAKOV, P. K. On definition and use of systems engineering processes, fields through a transonic fan blade Determination of heat transfer to flow in a duct with a methods and tools p 1225 A93-53642 [ISABE 93-7030] p1184 A93-54006 pseudodiscontinuity p1179 A93-53365

B-9 TRUSHIN, O. V. PERSONAL AUTHOR INDEX

TRUSHIN, O. V. Semi-full-scale dynamic simulation complex on the basis WILSON, JACK Effect of rotation on heat transfer and hydraulic of centrifuge Initial results from the NASA Lewis wave rotor resistance in the radial cooling channels of turbine rotor | AIAA PAPER 93-3577] p 1208 A93-52673 experiment blades p 1215 A93-52950 VENKATAPATHY, ETHIRAJ | AIAA PAPER 93-2521) p1193 A93-53589 TSANGARIS, S. Effective treatment of the singular line boundary problem WILSON, K. J. Zonal-local solution method for the turbulent for three-dimensional grids p 1177 A93-53204 Periodic chemical energy release for active combustion Navier-Stokes equations p1177 A93-53205 VENKTRAYULU, N. control TSAPLIN, M. I. Tip clearance effects on the flow field of an axial turbine [ISABE 93-7043] p1198 A93-54019 Effect of rotation on heat transfer and hydraulic rotor blade cascade WOLTHERS, W. resistance in the radial cooling channels of turbine rotor [ISABE 93-7057] p1185 A93-54033 The reduction of skin friction by riblets under the blades p 1215 A93-52950 influence of an adverse pressure gradient VENTER, S. J. TSUJIMOTO, YOSHINOBU p 1218 A93-53810 The design and development of an afterburner Velocity fluctuation based on the difference in the flow [ISABE 93-7041] p1198 A93-54017 WU, GUOCHUAN pattern in the channels of a centrifugal impeller The effects of end-bend regulations of compressor blade P1182 A93-53842 VISHNUBHOTLA, V. S. on the outlet flow field TSUJITA, HOSHIO Tip clearance effects on the flow field of an axial turbine [ISABE 93-7033] p1185 A93-54009 rotor blade cascade Numerical analysis of flow within cascade with tip WU, YONG clearance p1176 A93-53192 I ISABE 93-7057] p1185 A93-54033 Integrated fire control simulation systems TSUNG, FU-LIN VON BACKSTROM, T. W. p1192 A93-53876 Three-dimensional Navier-Stokes/full-potential coupled The streamline throughflow method of axial WURSTER, K. E. analysis for viscous transonic flow p1178 A93-53218 lurbomachinery flow analysis Aerodynamic heating environment definition/thermal TSURUSAKI, HIROMU [ISABE 93-7031] p 1184 A93-54007 protection system selection for the HL-20 Velocity fluctuation based on the difference in the flow VORONIN, V. I. p1181 A93-53739 pattern in the channels of a centrifugal impeller Aerodynamic characteristics of conical p1182 A93-53842 triangular-planform wings of low aspect ratio in subsonic stalled flow p1180 A93-53574 u XIN, JILING w The effects of end-bend regulations of compressor blade UCHIDA, MASAHIRO on the outlet flow field Development study on Air Turbo Ramjet engine for a WAKAMATSU, YOSHIO [ISABE 93-7033) p1185 A93-54009 future space plane Effect of film cooling/regenerative cooling on scramjet XU, CHENG [ISABE 93-7016] p1195 A93-53992 engine performances A preliminary investigation of the control of separated UEDA, SHUUICHI [ISABE 93-7036] p1197 A93-54012 flow by means of excitation p 1182 A93-53859 Off-design performance of scramjet nozzles Application of functionally gradient materials to scramjet [ISABE 93-7108] p 1203 A93-54084 engines UEDA, SYUICHI [ISABE 93-7063] p 1200 A93-54039 Application of functionally gradient materials to scramjet engines WALLE, G. YAKALI, HUSEYIN H. [ISABE 93-7063) p 1200 A93-54039 Developments towards versatility in digital engine control A vision-based method for autonomous landing UJIIE, Y. units p1190 A93-53172 [ISABE 93-7088] p 1202 A93-54064 A study of self-ignition of methane-hydrogen mixture fuel YAKIMENKO, O. A. injected into high enthalpy supersonic airstreams WALSH, C. Semi-full-scale dynamic simulation complex on the basis [ISABE 93-7049) p 1213 A93-54025 Kefvin-Helmholtz wave generation beneath hovercraft of centrifuge UL'YANOV, G. S. Skirts p1219 A93-53820 [AIAA PAPER 93-3577] p 1208 A93-52673 Aerodynamic characteristics of conical WALTER, R. F. YAKOVLEV, A. I. triangular-planform wings of low aspect ratio in subsonic Recent advances in computational analysis of Hybrid complex of the aircraft intellectualized control Stalled flow p 1180 A93-53574 hypersonic vehicles p 1179 A93-53364 systems simulation at the stage of their research UNNIKRISHNAN, V. WANG, C. projecting Structural integrity validation of lirnited-life engines Linear quadratic tracking problems in Hilbert space - [AIAA PAPER 93-3559] p 1222 A93-52660 [ISABE 93-7131] p 1205 A93-54106 Application to optimal active noise suppression YAMAGUCHI, NOBUYUKI USUI, H. p 1224 A93-52763 Performance improvement by forward-skewed blading of axial fan moving blades Experimental analysis of turbine rotor flow at design and WANG, G. [ISABE 93-7055] p1185 A93-54031 off-design conditions The prediction of thermal NO(x) in gas turbine YAMALEEV, N. K. [ISABE 93-7092] p1186 A93-54068 exhausts Application of the small parameter method to the UTYUZHNIKOV, S. V. [ISABE 93-7022) p1195 A93-53998 Application of the small parameter method to the problem of three-dimensional flow of a viscous gas past WARD, S. bodies p1178 A93-53314 problem of three-dimensional flow of a viscous gas past Prismatic grid generation for three-dimensional complex YAMAMOTO, A. bodies P1178 A93-53314 geometries p 1178 A93-53217 Comparison of gasdynamic models in hypersonic flow Effects of wake interaction of two turbine cascades on WARE, GEORGE M. P1179 A93-53315 secondary/tip-leakage flows and losses Aerodynamic characteristics of the HL-20 [ISABE 93-7058) p1185 A93-54034 P1181 A93-53736 Experimental analysis of turbine rotor flow at design and WATANABE, Y. off-design conditions Conceptual design study on combined-cycle engine for [ISABE 93-7092] p1186 A93-54068 VAN DALSEM, W. R. hypersonic transport YAMAMOTO, K. Numerical study of a delta planform with multiple jets [ISABE 93-7018] p1195 A93-53994 Navier-Stokes computation of the three dimensional flow in ground effect WEATHERILL, N. P. fields through a transonic fan blade [SAE PAPER 892283] p1176 A93-53200 The construction of nearly orthogonal multiblock grids [ISABE 93-7030] p1184 A93-54006 VAN DER MERWE, C. A. for compressible flow simulation p 1219 A93-53847 YAMAMOTO, MASAHIKO The development of a new air filtration system for the WEBB, WILLIAM L Off-design performance of scramjet nozzles Alouette III helicopter Mach 5 turboramjet requirements and design [ISABE 93-7108] p 1203 A93-54084 [ISABE 93-7048) pt199 A93-54024 approach YAMAMOTO, TETSUYA VAN NIEKERK, J. E. [ISABE 93-7015] p1194 A93-53991 Repair materials and processes for the MD-11 The design and development of an afterburner WEILMUENSTER, K. J. Composite Tailcone p 1216 A93-53452 [ISABE 93-7041] p1198 A93-54017 HL-20 computational fluid dynamics analysis YAMANE, HIDEAKI VANOENKERCKHOVE, J. p1181 A93-53740 Design of limit-tracking systems incorporating a turbofan Energy management WESKE, REID A. engine with constant disturbances [ISABE 93-7019] p1195 A93-53995 Pseudo Aircraft Systems - A multi-aircraft simulation [ISABE 93-7090) p 1203 A93-54066 VANDERWERT, TERRY L. system for air traffic control research YAMANE, T. Case studies - Applications of laser systems for cutting [AIAA PAPER 93-3585) p 1209 A93-52679 Transonic discharge flows around diftuser vanes from and welding aerospace parts p 1217 A93-53498 WHITE, NANCY H. a centrifugal impeller VANDROMME, D. HL-20 operations and support requirements for the [ISABE 93-7053] p1185 A93-54029 On the numerical simulation of the two-dimensional flow Personnel Launch System mission p 1210 A93-53745 YAMANE, YOSHIYUKI field around a hypersonic air-intake-compressibility WHITTENBERGER, J. D. Two-dimensional and three-dimensional mixing flow effects Stress relaxation of low pressure plasma-sprayed structures with injected through slotted nozzle and circular [ISABE 93-7100] p1187 A93-54076 NiCrAlY alloys p1211 A93-52870 nozzle into supersonic flows VASHCHENKO, N. V. WIEDNER, B. [ISABE 93-7117] p 1221 A93-54092 Selection of a method for protecting aircraft gas turbine Fluid dynamics and convective heat transfer in impinging YAMAOKA, IKUO engines against damage by foreign objects (Mathematical jets through implementation of a high resolution liquid Application of functionally gradient materials to scramjet models) p 1193 A93-53554 crystal technique engines VASILETS, V. M. [ISABE 93-7077] p 1220 A93-54053 [ISABE 93-7063) p 1200 A93-54039 Hybrid complex of the aircraft intellectualized control WILKINS, DANIEL A. YAMAWAKI, S. systems simulation at the stage of their research A high fidelity video delivery system for real-time flight A new cooling system for ultra high temperature projecting simulation research turbines [AIAA PAPER 93-3559] p 1222 A93-52660 [AIAA PAPER 93-3558] p 1214 A93-52659 [ISABE 93-7073] p 1201 A93-54049

B-10 PERSONAL AUTHOR INDEX ZIEMIANSKI, JOSEPH A.

YANAGI, R. ZHLUKTOV, S. V. Conceptual design study on combined-cycle engine for Comparison of gasdynamic models in hypersonic flow hypersonic transport P1179 A93-53315 [ISABE 93-7018] p1195 A93-53994 ZHOU, MING-OE Research and development of a turbo-accelerator for A preliminary investigation of the control of separated super/hypersonic transport flow by means of excitation p 1182 A93-53859 [ISABE 93-7066] p 1200 A93-54042 ZHOU, WEI-JIANG YANAGI, RYOJI Numerical study of supersonic flow over a backward A study on Mach 3 two-dimensional mixed compression step with transverse injection p 1182 A93-53853 air-intakes Numerical solution of N-S equations for hypersonic flow [ISABE 93-7106] p1188 A93-54082 over capsule-type vehicles p 1182 A93-53858 ZHU, PEI-SHEN YOKOTA, KAZUHIKO Integrated fire control simulation systems Numerical and experimental study on two- and P1192 A93-53876 three-dimensional supersonic flow field with hydrogen injection ZIEMIANSKI, JOSEPH A. Propulsion technology challenges for tum-of-the-century [ISABE 93-7118] p1188 A93-54093 commercial aircraft YONG, W. [ISABE 93-7003] p1194 A93-53980 Longitudinal closed-loop pilot/vehicle analysis of DFBW aircraft during approach and landing 'p 1206 A93-54277 YOSHIDA, HIOENORI Three-dimensional viscous flow analysis of compressor cascade channels p 1181 A93-53837 YOSHIDA, T. A new cooling system for ultra high temperature turbines [ISABE 93-7073] p 1201 A93-54049 YU, K. Periodic chemical energy release for active combustion control [ISABE 93-7043] p1198 A93-54019 YU, GIN-FANG Interconversion of two kinds of methods for cabin leakage test p1192 A93-53874 YUGE, T. Active control of vortex breakdown by a spinning wave generator [ISABE 93-7045] p 1219 A93-54021

ZAEHRING, G. Axial flow compressors - Mechanical design trends [ISABE 93-7061] p1199 A93-54037 ZAKHARY, A. S. Blowout of turbulent disc/pilot stabilized jet diffusion flames [ISABE 93-7026] p 1213 A93-54002 ZAMAN, K. B. M. O. Streamwise vorticity generation and mixing enhancement in free jets by 'delta-tabs' [AIAA PAPER 93-3253] p1180 A93-53592 ZANDIEH, ALI Boundary layer and pressure measurements on a cylinder with unsteady circulation control P1177 A93-53207 ZANNETTI, LUCA Design of air intakes and nozzles for transonic rotational flows [ISABE 93-7102] p1187 A93-54078 ZEGHAL, KARIM A reactive approach for distributed air traffic control [ONERA, TP NO. 1993-83] p1190 A93-53603 CRAASH - A coordinated collision avoidance system [ONERA, TP NO. 1993-84] p1191 A93-53604 ZHANG, BING-XUAN Transonic area rule about lifting configurations p1183 A93-53868 ZHANG, BODING How to consider simulation fidelity and validity for an engineering simulator [AIAA PAPER 93-3598] p 1209 A93-52688 ZHANG, H. M. An investigation of post stall transients and recoverability of axial compression systems [ISABE 93-7012] p1184 A93-53988 ZHANG, HAN-GUO Fault tolerant navigation for aircraft landing P1191 A93-53866 ZHANG, HONG-YUE Fault tolerant navigation for aircraft landing P1191 A93-53866 ZHANG, JIAN-HUA Integrated fire control simulation systems P1192 A93-53876 ZHANG, SHI-YING A preliminary investigation of the control of separated flow by means of excitation p 1182 A93-53859 ZHAO, QING-WEI Transonic area rule about lifting configurations p1183 A93-53868 ZHIKHAREV, C. N. Separation phenomenon in a hypersonic flow with strong wall cooling - Subcritical regime p 1189 A93-54266 B-11 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 298) December 1993

Typical Corporate Source Low aspect ratio wing code validation experiment Propulsion technology challenges for turn-of-the-century p1176 A93-53202 commercial aircraft Index Listing Effective treatment of the singular line boundary problem | ISABE 93-7003] p1194 A93-53980 for three-dimensional grids p 1177 A93-53204 Emission characteristics of a model gas turbine Space marching calculations about hypersonic combustor at practical conditions configurations using a solution-adaptive mesh algorithm [ISABE 93-7023] p1196 A93-53999 CORPORATE SOURCE p1177 A93-53212 Forcing function modeling for flow induced vibration Evaluation of 2D ceramic matrix composites in [ISABE 93-7027] p1196 A93-54003 aeroconvective environments p 1212 A93-53459 Engine technology challenges for a 21st Century High-Speed Civil Transport National Aeronautics and Space Administration. Hugh Aerodyne Research, Inc., Bilierica, MA. I ISABE 93-7064] p 1200 A93-54040 L. Dryden Flight Research Facility, Edwards, CA. — Stratospheric aircraft exhaust plume and wake chem- Material requirements for the High Speed Civil Flight research simulation takes off Transport istry studies P1192 A93-53769 [NASA-CR-189688] p 94 N93-12299 [ISABE 93-7067] p 1200 A93-54043 National Aeronautics and Space Administration. Fluid dynamics and convective heat transfer in impinging Langley Research Center, Hampton, VA. jets through implementation of a high resolution liquid An evaluation of software tools for the design and crystal technique development of cockpit displays | ISABE 93-7077] p 1220 A93-54053 [AIAA PAPER 93-3593] p 1224 A93-52685 Aerodynamic inverse design and analysis for a full Instrumentation and telemetry systems for free-flight engine drop model testing p 1209 A93-52754 [ISABE 93-7086] p1186 A93-54062 Characterization of the faulted behavior of digital Three-dimensional Mow analysis inside turbomachinery Listings in this index are arranged alphabetically computers and fault tolerant systems stages with steady and unsteady Navier-Stokes method by corporate source. The title of the document is P1224 A93-52762 [ISABE 93-7095] p1186 A93-54071 used to provide a brief description of the subject Linear quadratic tracking problems in Hilbert space - A parameter optimization approach to controller matter. The page number and the accession Application to optimal active noise suppression partitioning for integrated flight/propulsion control number are included in each entry to assist p 1224 A93-52763 application p 1206 A93-54268 Mixing of multiple jets with a confined subsonic the user in locating the abstract in the abstract Upwind-biased, point-implicit relaxation strategies for hypersonic flowfield simulations on supercomputers crossflow p1189 A93-54324 section. If applicable, a report number is also p1175 A93-52770 National Aeronautics and Space Administration. Marshall Space Flight Center, Huntsville, AL. included as an aid in identifying the document. Analysis of a turning point problem in flight trajectory optimization p 1210 A93-52885 Navier-Stokes analysis of turbine flowfield and external heat transfer Case study of a low-reflectivity pulsating microburst - [ISABE 93-7075] p1186 A93-54051 Numerical simulation of the Denver, 8 July 1989, storm p 1222 A93-52898 Observations of liquid jets injected into a highly accelerated supersonic boundary layer p1177 A93-53214 Transition correlation in subsonic flow over a flat plate p1178 A93-53231 N Aerodynamic characteristics of the HL-20 p1181 A93-53736 National Aeronautics and Space Administration, Six-degree-of-freedom guidance and control-entry Washington, DC. analysis of the HL-20 p 1210 A93-53737 Passive range estimation for rotorcraft low-altitude Effect of lift-to-drag ratio in pilot rating of the HL-20 flight p 1190 A93-52881 landing task p 1210 A93-53738 International aerospace STI p 1227 A93-53826 Aerodynamic heating environment definition/thermal Propulsion technology challenges for turn-of-the-century protection system selection for the HL-20 commercial aircraft p1181 A93-53739 (ISABE 93-7003} p1194 A93-53980 HL-20 computational fluid dynamics analysis Engine technology challenges for a 21st Century p1181 A93-53740 High-Speed Civil Transport HL-20 operations and support requirements for the [ISABE 93-7064] p 1200 A93-54040 Personnel Launch System mission p 1210 A93-53745 A parameter optimization approach to controller National Aeronautics and Space Administration. Lewis partitioning for integrated flight/propulsion control Research Center, Cleveland, OH. application p 1206 A93-54268 Progress towards understanding and predicting heat National Aeronautics and Space Administration. Ames transfer in the turbine gas path p 1215 A93-52751 Research Center, Moffett Field, CA. Stress relaxation of low pressure plasma-sprayed A high fidelity video delivery system for real-time flight NiCrAlY alloys p 1211 A93-52870 simulation research Low-Reynolds-number k-epsilon model for unsteady | AIAA PAPER 93-3558] p 1214 A93-52659 turbulent boundary-layer flows p 1177 A93-53208 Development and operation of a real-time simulation at Design for cyclic loading endurance of composites the NASA Ames Vertical Motion Simulator p 1216 A93-53395 [AIAA PAPER 93-3575) p 1208 A93-52671 Overview of NASA's advanced high temperature engine Simulation motion effect on single axis compensatory materials technology program p 1212 A93-53453 tracking The chemistry of Saudi Arabian sand - A deposition [AIAA PAPER 93-3579] p 1208 A93-52675 problem on helicopter turbine airfoils p 1216 A93-53468 Pseudo Aircraft Systems - A multi-aircraft simulation system for air traffic control research Measurements and computational analysis of heat transfer and flow in a simulated turbine blade internal [AIAA PAPER 93-3585] p 1209 A93-52679 cooling passage A radar altitude and line of sight attachment [AIAA PAPER 93-1797] p 1218 A93-53585 [AIAA PAPER 93-3587] p 1223 A93-52680 Initial results from the NASA Lewis wave rotor Enhancing real-time flight simulation execution by experiment intercepting Run-Time Library calls [AIAA PAPER 93-2521 ] p1193 A93-53589 [AIAA PAPER 93-3591] p 1224 A93-52684 Laser velocimeter measurements of the flow field Passive range estimation for rotorcraft low-altitude generated by a forward-swept propfan during flutter flight P1190 A93-52881 [AIAA PAPER 93-2919] p1180 A93-53591 Numerical study of a delta planform with multiple jets Streamwise vorticity generation and mixing in ground effect enhancement in free jets by 'delta-tabs' [SAE PAPER 892283] p1176 A93-53200 [AIAA PAPER 93-3253] p1180 A93-53592 C-1 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 298) December 1993

Implementation of expert systems within an interactive Typical Foreign Technology tactical environment Index Listing [AIAA PAPER 93-35831 p 1223 A93-52678 FRANCE Thrust imparted to an airfoil by passage through a High temperature heat exchangers for gas turbines and sinusoidal upwash field p 1178 A93-53219 future hypersonic air breathing propulsion Some acoustic features of perforated test section walls [ONERA, TP NO. 1993-75] p 1218 A93-53596 [COUNTRY OF INTELLECTUAL ORIGIN) with splitter plates p 1226 A93-53222 Origin of the carbon rich sliding interface in alkali containing matrix-SiC nicalon fibre composites Clean melting and the removal of defects from [ONERA, TP NO. 1993-77] p 1212 A93-53598 aero-engine materials p 1217 A93-53503 CARS temperature measurements in combustion On hovercraft overwater heave stability [ONERA, TP NO. 1993-78] p 1212 A93-53599 ARGENTINA p 1219 A93-53819 Corrosion of ceramic matrix composites — South American latest developments in the air law and Kelvin-Helmholtz wave generation beneath hovercraft [ONERA, TP NO. 1993-82] p 1213 A93-53602 air policy fields p 103 N93-12719 skirts p 1219 A93-53820 A reactive approach for distributed air traffic control Hypersonic shock-induced combustion ramjet [ONERA, TP NO. 1993-83] p1190 A93-53603 performance analysis CRAASH - A coordinated collision avoidance system (ISABE 93-7037] p1197 A93-54013 [ONERA, TP NO. 1993-84] p1191 A93-53604 Thermodynamic and neutral network computer The acoustics of axial compressors modelling of implanted component faults in a gas turbine [ONERA, TP NO. 1993-102] p 1226 A93-53615 engine Acoustic-wave propagation in ducts and free-field Listings in this index are arranged alphabetically | ISABE 93-7089] p 1202 A93-54065 radiation by country of intellectual origin. The title of the Effect of nozzle design on the performance of a highly [ONERA, TP NO. 1993-103] p 1226 A93-53616 document is used to provide a brief description loaded turbine stage 3D laminar and 2D turbulent computations with the of the subject matter. The page number and [ISABE 93-7096] p 1203 A93-54072 Navier-Stokes solver FLU3M [ONERA, TP NO. 1993-105] p1180 A93-53618 accession number are included in each entry Aerodynamics of turbine blades with trailing-edge damage - Measurements and computations Stability analysis through bifurcation theory. I, II to assist the user in locating the abstract in [ISABE 93-7130] p1189 A93-54105 [ONERA, TP NO. 1993-108] p 1225 A93-53620 the abstract section. If applicable, a report num- CHINA Non-linear flight dynamics [ONERA. TP NO. 1993-109] p 1206 A93-53621 ber is also included as an aid in identifying A dual-Euler method for solving all-attitude angles of the document. the aircraft Investigation of the flow field through a variable pitch [AIAA PAPER 93-3589] p 1223 A93-52682 fan rotor with an inlet total pressure distortion [ISABE 93-7029] p1184 A93-54005 How to consider simulation fidelity and validity for an CFD for ramjet and scramjet powered vehicles engineering simulator [ISABE 93-7035] p1197 A93-54011 [AIAA PAPER 93-3598] p 1209 A93-52688 3D and 2.5D viscous flow computations for axial flow An implicit difference scheme of Euler equation for turbine blades unsteady transonic flow p 1182 A93-53852 [ISABE 93-7093] p1186 A93-54069 Numerical study of supersonic flow over a backward Recent developments performed at ONERA for the step with transverse injection p 1182 A93-53853 simulation of 3D inviscid and viscous flows in Numerical solution of N-S equations for hypersonic flow turbomachinery by the solution of Euler and Navier-Stokes over capsule-type vehicles p1182 A93-53858 equations A preliminary investigation of the control of separated [ISABE 93-7094] p1186 A93-54070 flow by means of excitation p 1182 A93-53859 Optimization of afterbodies and engine nozzle by using Analytical expression of dissipation integral for kinetic CFD methods AUSTRALIA energy integral equation p 1183 A93-53860 [ISABE 93-7098] p1187 A93-54074 The prediction of thermal NO(x) in gas turbine A study of surge control by using pulse cut-off for dual On the numerical simulation of the two-dimensional flow exhausts field around a hypersonic air-intake-compressibility spool turbo-jet engine p 1194 A93-53862 | ISABE 93-7022! p1195 A93-53998 effects Fault tolerant navigation for aircraft landing Neural network fault diagnosis of a turbofan engine [ISABE 93-7100] p1187 A93-54076 p1191 A93-53866 | ISABE 93-7091] p 1203 A93-54067 Compact heat exchanger fitted to engines of the inverted Measurement and prediction of flow in a gas turbine Transonic area rule about lifting configurations type engine exhaust plume p1183 A93-53868 [ISABE 93-7120] p 1221 A93-54095 [ISABE 93-71131 p 1204 A93-54088 A study of aircraft global dynamic stability in rapid rolling A Eulerian/Lagrangian modelling to calculate the Reinforcement of the F-111 wing pivot fitting with a maneuver p 1206 A93-53869 evolution of a water droplets spray boron/epoxy doubter system - Materials engineering Interconversion of two kinds of methods for cabin [ISABE 93-7121] p 1221 A93-54096 aspects p 1214 A93-54241 leakage test p1192 A93-53874 AUSTRIA Integrated fire control simulation systems An aerodynamic model for the longitudinal motion of p1192 A93-53876 flight training devices p 1207 A93-54278 Harmonic oscillation in FEW system GERMANY p 1206 A93-53877 Identification of nonlinear mechanical systems using B A study of damage tolerance of the landing gear combined state and parameter evaluation structure p 1219 A93-53881 p1224 A93-52732 BELGIUM An investigation of post stall transients and recoverability Flight safety in Europe p 1227 A93-53726 Energy management of axial compression systems Stumbling blocks for airport construction in the new [ISABE 93-7012] p1184 A93-53988 | ISABE 93-7019] p1195 A93-53995 German federal states p 1227 A93-53727 BRAZIL The effects of end-bend regulations of compressor blade Axial flow compressors - Mechanical design trends Initial development of a research flight simulator on the outlet flow field [ISABE 93-7061] p1199 A93-54037 software [ISABE 93-7033] p1185 A93-54009 Heat transfer and material temperature conditions in the [AIAA PAPER 93-3590! p 1223 A93-52683 Impingement cooling with film coolant extraction in the leading edge area of impingement-cooled turbine vanes airfoil leading edge regions [ISABE 93-7076] p 1220 A93-54052 [ISABE 93-7078] p 1220 A93-54054 Developments towards versatility in digital engine control Longitudinal closed-loop pilot/vehicle analysis of OFBW units aircraft during approach and landing [ISABE 93-7088] p 1202 A93-54064 p 1206 A93-54277 CANADA Numerical simulation of a two-dimensional supersonic Evolution of flight simulation mixed-compression inlet | AIAA PAPER 93-3545! p 1207 A93-52652 [ ISABE 93-7107 ] p 1188 A93-54083 Internally coherent system of innovation - The case of Numerical study of nitric oxide formation in a hypersonic flight simulation EGYPT ramjet engine | AIAA PAPER 93-3548] p 1226 A93-52653 Blowout of turbulent disc/pilot stabilized jet diffusion [ISABE 93-7125] p 1204 A93-54100 Pilot evaluations of augmented flight simulator motion flames Heat loads as key problem of hypersonic flight | AIAA PAPER 93-3580! p 1208 A93-52676 [ISABE 93-7026] p 1213 A93-54002 p 1222 A93-54276

D-1 GREECE FOREIGN TECHNOLOGY INDEX

GREECE Shock shapes around slender diamond cones traveling Experimental analysis of turbine rotor flow at design and Zonal-local solution method for the turbulent at hypersonic speed p 1181 A93-53840 off-design conditions Navier-Stokes equations p1177 A93-53205 Analysis of unstarted supersonic flutter in cascade by [ISABE 93-7092] p1186 A93-54068 semiactuator disk theory p 1181 A93-53841 Wind tunnel tests of the model of intake-airframe Velocity fluctuation based on the difference in the flow integration pattern in the channels of a centrifugal impeller [ISABE 93-7101] p1192 A93-54077 P1182 A93-53842 Starting characteristics of scramjet inlets INDIA Numerical analysis of the flow through a centrifugal [ISABE 93-7105] p 1203 A93-54081 Some measurements of stall in an axial impeller impeller by vortex distribution model of a boundary layer. A study on Mach 3 two-dimensional mixed compression [ISABE 93-7008) p1183 A93-53984 I - Theoretical analysis p 1182 A93-53843 air-intakes A study on 3-D velocity distribution of isothermal flows Research and development of aircraft engine in Japan [ISABE 93-7106] p1188 A93-54082 - Historical review behind an afterburner flame stabilizer Off-design performance of scramjet nozzles [ISABE 93-7000] p 1227 A93-53977 [ISABE 93-7039] p1197 A93-54015 [ISABE 93-7108) P 1203 A93-54084 Correlations for flow property variation at outlet of a Japan's research and development program for airbreathing engine technologies Observation of fluctuation of 2D-nozzle flows centrifugal impeller [ISABE 93-7110] p 1204 A93-54086 (ISABE 93-7054] p1185 A93-54030 [ISABE 93-7005) p1194 A93-53981 A 2-D compressible N-S simulation of starting- and LIF visualization of 3-dimensional hypersonic mixing Tip clearance effects on the flow field of an axial turbine stalling-flows in a compressor cascades system [ISABE 93-7114] p 1221 A93-54089 rotor blade cascade [ISABE 93-7006] p1183 A93-53982 Two-dimensional and three-dimensional mixing flow [ISABE 93-7057] p1185 A93-54033 Numerical study on inception of stall cells in rotating structures with injected through slotted nozzle and circular Characterisation of conventional and controlled diffusion stall nozzle into supersonic flows stator blades in a transonic compressor stage [ISABE 93-7007] p1183 A93-53983 [ISABE 93-7117] p 1221 A93-54092 [ISABE 93-7124] p1189 A93-54099 Development study on Air Turbo Ramjet engine for a Numerical and experimental study on two- and Structural integrity validation of limited-life engines future space plane three-dimensional supersonic flow field with hydrogen [ISABE 93-7131] p 1205 A93-54106 [ISABE 93-7016] p1195 A93-53992 injection Development of a real time dynamic engine simulation Conceptual design study on combined-cycle engine for [ISABE 93-7118) p1188 A93-54093 model of a turbo fan engine hypersonic transport Characteristics of heat exchanger in [ISABE 93-7132) p 1205 A93-54107 [ISABE 93-7018] p1195 A93-53994 supersonic/subsonic flows INTERNATIONAL ORGANIZATION Navier-Stokes computation of the three dimensional flow [ ISABE 93-7119 ] p 1221 A93-54094 fields through a transonic fan blade The leading edge vortex of a rotating stall cell Various applications of robots in aircraft engine [ISABE 93-7030] p1184 A93-54006 [ISABE 93-7009] p1183 A93-53985 overhaul The energy dissipation in a rotating stall cell Effect of film cooling/regenerative cooling on scramjet [ISABE 93-7129] p1175 A93-54104 [ISABE 93-7010] p1183 A93-53986 engine performances [ISABE 93-7036) p1197 A93-54012 Study on flow field around slender diamond cone ISRAEL traveling at hypersonic speed p 1189 A93-54314 Design and testing methods of high performance Isothermal flow characteristics behind V-shape gutter combustors for airbreathing engines with and without injection [ISABE 93-7024) p1196 A93-54000 [ISABE 93-7040] p 1198 A93-54016 N Study of a pulse ramjet based on twin valveless Active control of vortex breakdown by a spinning wave combustors coupled to operate in antiphase generator [ISABE 93-7045] p 1219 A93-54021 NETHERLANDS [ISABE 93-7038] p1197 A93-54014 A primary flight display for four-dimensional guidance ITALY Noise reduction of supersonic heated jet with jet mixing enhancement by tabs and navigation influence of tunnel size and level of Nozzle effects on linear stability behaviour of additional information on pilot performance and control combustors [ISABE 93-7046] p1198 A93-54022 A study of self-ignition of methane-hydrogen mixture fuel behaviour [ISABE 93-7044] p1198 A93-54020 [AIAA PAPER 93-3570] p 1208 A93-52668 Studies on coolant problems in aeronautical turbine injected into high enthalpy supersonic airstreams [ISABE 93-7049] p 1213 A93-54025 The development of SIMON A - A simulator facility for cascades advanced research into simulation techniques, motion [ISABE 93-7074] p 1220 A93-54050 Ignition and combustion performance of a scramjet combustor with a fuel injection strut system control and navigation systems technologies Finite-rate H2/air combustion effects in CRJ for [AIAA PAPER 93-3574] p 1208 A93-52670 hypersonic launchers [ISABE 93-7050] p1199 A93-54026 Study on unstart and its propagation along modules due The reduction of skin friction by riblets under the [ISABE 93-7084) p 1202 A93-54060 influence of an adverse pressure gradient Performance and configuration analysis of jet-engine to compound choking and/or fluctuations in combustor of scramjet engines p 1218 A93-53810 off-design behavior NORWAY [ISABE 93-7087] p 1202 A93-54063 [ISABE 93-7052] p1199 A93-54028 Transonic discharge flows around diffuser vanes from Arctic environment - Helicopter operations in cold Design of air intakes and nozzles for transonic rotational climates p1189 A93-54288 flows a centrifugal impeller [ISABE 93-7102] p1187 A93-54078 [ISABE 93-7053] p1185 A93-54029 Performance improvement by forward-skewed blading A study of the stability of vortical structures in supersonic inlets of axial fan moving blades [ISABE 93-7055) p1185 A93-54031 [ISABE 93-7103] p1187 A93-54079 POLAND Effects of wake interaction of two turbine cascades on Influence of chemical kinetics effects in nozzles shape Analysis of spatial motion dynamics of a helicopter for design secondary/tip-leakage flows and losses various models of the induced velocity field [ISABE 93-7058) p1185 A93-54034 [ISABE 93-7112] p1188 A93-54087 p1191 A93-53721 A finite element code for gas turbine combustor flow New approximate method of stress analysis for bladed Finite element analysis of natural vibrations of an rotating discs with Stretched Laminar Flamelet modelling aeroplane with asymmetric variable wing geometry [ISABE 93-7059] p 1219 A93-54035 [ISABE 93-7127] p 1204 A93-54102 p 1218 A93-53776 Application of functionally gradient materials to scramjet Numerical simulation of gas turbine combustors with complex geometries engines [ISABE 93-7063] p 1200 A93-54039 [ISABE 93-7128] p 1204 A93-54103 Expert Systems for the simulation of turbofan engines Research and development of a turbo-accelerator for [ISABE 93-7133] p 1225 A93-54108 super/hypersonic transport RUSSIA [ISABE 93-7066] p 1200 A93-54042 Hybrid complex of the aircraft intellectualized control Research and development of high pressure compressor systems simulation at the stage of their research for SST and HST engine projecting [ISABE 93-7068] p1186 A93-54044 [AIAA PAPER 93-3559] p 1222 A93-52660 JAPAN Tandem transverse hydrogen gas injection into a Semi-full-scale dynamic simulation complex on the basis Numerical analysis of flow within cascade with tip supersonic airflow of centrifuge clearance p 1176 A93-53192 [ISABE 93-7069] p 1201 A93-54045 [AIAA PAPER 93-3577] p 1208 A93-52673 Pressure distribution measurement around hypersonic Direct simulation of reacting fuel gas flows in a Nonlinear deformation mechanics of multilayer delta winged semicone - Measurement by means of supersonic mixing layer transparency elements - Some calculation results magnet tape P1176 A93-53193 [ISABE 93-7072] p 1201 A93-54048 P1191 A93-52937 A nonlinear finite element of an arbitrary beam Experimental investigation into the mechanism of A new cooling system for ultra high temperature discrete frequency noise (DFN) generation from a NACA P1215 A93-52939 turbines 0012 blade p 1225 A93-53194 Stabilization of the dynamic characteristics of the [ISABE 93-7073] p 1201 A93-54049 The properties of newly developed highly damage two-channel automatic control system of aircraft tolerant and easy handleable carbon fiber/modified The combustion performance of methane-fueled ram p 1205 A93-52941 bismaleimide prepreg system p 1212 A93-53448 combustor A method for the spectral-time identification of the Repair materials and processes for the MD-11 [ISABE 93-7079] p 1201 A93-S4055 longitudinal and lateral motions of an aircraft Composite Tailcone p 1216 A93-53452 Studies on methane-fuel ram combustor for HST p 1205 A93-52942 Numerical analysis of a flat plate in a pitching motion. combined cycle engine Identification of the phase characteristics and II - Effect on the flow of the position of the pivot, etc [ISABE 93-7080] p 1201 A93-54056 wind-induced perturbations of an aircraft from flight test p1181 A93-53798 Test results of the hydrogen fueled model combustor results p 1206 A93-52943 Study on surge and rotating stall in axial compressors. for the air turbo ramjet engine Solution of the boundary value problem in flight dynamics III - Numerical model for multiblade-row compressors [ISABE 93-7082] p 1201 A93-54058 by the opposite motion method p 1206 A93-52944 p1181 A93-53799 Design of limit-tracking systems incorporating a turbofan A study of optical distortions arising in radiation Three-dimensional viscous flow analysis of compressor engine with constant disturbances transmission through cavities with gas flow around them cascade channels p1181 A93-53837 [ISABE 93-7090] p 1203 A93-54066 p 1225 A93-52945

D-2 FOREIGN TECHNOLOGY INDEX UNITED KINGDOM

Non-self-similarity of a boundary layer flow of a Large eddy simulation of turbulent combustion behind high-temperature gas in a Laval nozzle flame holders p1176 A93-52946 [ISABE 93-7042] p1198 A93-54018 Estimation of the change of axial-flow compressor SWITZERLAND characteristics during long-term service Operating helicopters in a demanding environment - p1193 A93-52949 Mountain flying/high evaluations p 1190 A93-54289 Effect of rotation on heat transfer and hydraulic resistance in the radial cooling channels of turbine rotor blades p 1215 A93-52950 Estimation of the effect of the longitudinal moment due to the engine thrust on the mass of a subsonic passenger TAIWAN, PROVINCE OF CHINA aircraft p1191 A93-52954 Flutter analysis of stiffened laminated composite plates Calculation of the position of the flow separation line and shells in supersonic flow p 1216 A93-53224 in an analog model of flow past a body TURKEY p1176 A93-52958 Numerical simulation of ramjet and scramjet combustion Effect of boundary layer suction on the thrust and using two-dimensional Euler equations with finite rate aerodynamic efficiency of a hypersonic flight vehicle chemistry P1176 A93-52959 [ISABE 93-7083] p 1202 A93-54059 Viscosity of aviation fuel components - Aromatic hydrocarbons (alkyl benzenes) 'p1211 A93-52961 The combined effect of clearances and peripheral u overlaps on the efficiency of microturbines with shroudless UNITED KINGDOM rotors p1193 A93-52963 Air carriers' liability for passenger injury or death - The Estimation of the parameters of the electrodynamic Japanese Initiative and Response to the recent EC system engine-exhaust jet p 1193 A93-52965 Consultation Paper p 1226 A93-52930 Calculation of sandwich plates with polymer composite Air transport and the environment - Regulating aircraft skins under conditions of high humidity noise p1226 A93-52931 p 1215 A93-52968 Friction surfacing and linear friction welding Design and fabrication of panels with cutouts P1217 A93-53499 p 1215 A93-52973 The application of diffusion bonding in the manufacture An experimental study of reinforced panels of composite of aeroengine components p 1217 A93-53514 materials p 1215 A93-52975 Wind of change p 1209 A93-53625 A procedure for the thermal and strength testing of Low-frequency combustion oscillations in a model radiotransparent shells p 1209 A93-52976 afterburner p1193 A93-53702 A finite element for modeling skins of composite Production of oscillatory flow in wind tunnels materials p 1215 A93-52979 p 1218 A93-53812 Application of the small parameter method to the A dynamic stiffness/boundary element method for the problem of three-dimensional flow of a viscous gas past prediction of interior noise levels p 1226 A93-53817 bodies p1178 A93-53314 The construction of nearly orthogonal multiblock grids Comparison of gasdynamic models in hypersonic flow for compressible flow simulation p 1219 A93-53847 p1179 A93-53315 Design and technology for engine manufacture Mathematical modeling of the three-dimensional [ISABE 93-7002] p1194 A93-53979 temperature fields of turbine blades Review of stall, surge and active control in axial p 1216 A93-53329 compressors Construction of wakes in the discrete vortex method [ISABE93-7011] p1184 A93-53987 p1179 A93-53333 An ultra low NO(x) pilot combustor for staged low NO(x) Determination of heat transfer to flow in a duct with a combustion pseudodiscontinuity p1179 A93-53365 [ISABE 93-7020] p1195 A93-53996 Calculation of a compressible three-dimensional The unsteady flow past a supersonic splitter plate boundary layer on a swept wing p 1179 A93-53551 [ISABE 93-7047] p1185 A93-54023 Calculation of flow fields near a lifting wing Thermal design and analysis of an exhaust diffuser unit p1179 A93-53552 in a ceramic composite Selection of a method for protecting aircraft gas turbine [ISABE 93-7060] p 1220 A93-54036 engines against damage by foreign objects (Mathematical Experimental investigation of boundary layer transition models) p 1193 A93-53554 on a flat plate with C4 leading edge The flow lag angle in the rotor of a centrifugal compressor [ISABE 93-7123] p 1222 A93-54098 with allowance for viscosity effects The low frequency aeroacoustics of buried nozzle p1179 A93-53555 systems p 1205 A93-54244 Moving wall effects in transverse subsonic flow past a Europe's new windtunnel p 1210 A93-54275 rotating cylinder p 1179 A93-53573 Helicopter operations in severe environments; Proceedings of the Conference, London, United Kingdom, Aerodynamic characteristics of conical triangular-planform wings of low aspect ratio in subsonic June 4, 1992 [ISBN 1-85768-045-6] p1175 A93-54287 stalled flow p1180 A93-53574 Royal Navy helicopter operations in the maritime Unsteady aerodynamic characteristics of three environment p1190 A93-54290 rectangular wings of different aspect ratios Royal Air Force support helicopters - Night operations P1180 A93-53575 p1190 A93-54293 Design of high-load aviation turbomachines using Avionic systems in support of covert helicopter modern 3D computational methods operations p1193 A93-54294 [ISABE 93-7032] p1196 A93-54008 Separation phenomenon in a hypersonic flow with strong wall cooling - Subcritical regime p 1189 A93-54266

SOUTH AFRICA The streamline throughflow method of axial turbomachinery flow analysis [ISABE 93-7031) p1184 A93-54007 The design and development of an afterburner [ISABE 93-7041] p1198 A93-54017 The development of a new air filtration system for the Alouette III helicopter [ISABE 93-7048] p1199 A93-54024 Thermal fatigue life assessment of a convection-cooled gas turbine blade [ISABE 93-7062] p1199 A93-54038 A comparative assessment of two present generation turbine analysis codes [ISABE 93-70971 p 1203 A93-54073 SWEDEN Effects of blade geometry and mode shape on fan flutter [ISABE 93-7028) p1196 A93-54004

D-3 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 298) December 1993

Typical Contract Number Index Listing

AF PROJ. 7231 p 29 N93-12489

Listings in this index are arranged alphanumerically by contract number. Under each contract number the accession numbers denoting documents that have been produced as a result of research done under the contract are shown. The accession number denotes the number by which the citation is identified in the abstract section. Preceding the accession number is the page number on which the citation may be found.

AF-AFOSR-91-0022 p 1178 A93-53217 DAAL03-89-C-0004 p 1178 A93-53233 DE-AC04-76DP-00789 p 1218 A93-53815 DE-FQ05-91ER-81207 p 1178 A93-53233 DTFA-92-G-002 p 1213 A93-54001 F08635-90-C-0100 p 1196 A93-53999 F49620-86-C-0111 p 1224 A93-52763 NAG3-1124 p 1196 A93-53999 NAG3-1146 p 1206 A93-54268 NAG3-1168 p 1177 A93-53208 NAG3-989 p 1220 A93-54053 NAS1-18107 p 1224 A93-52763 NAS1-19299 p 1178 A93-53231 NAS2-12996 p 1212 A93-53459 NAS8-38867 p 1186 A93-54051 NCA2-326 p 1177 A93-53212 NCA2-522 p 1177 A93-53212 NSF CTS-89-06452 p 1220 A93-54053 NSF MCS-85-04316 p 1224 A93-52763 N00014-86-K-0759 p 1177 A93-53209 N00014-88-K-0001 p 1178 A93-53216 N00014-89-J-1342 p 1178 A93-53216 N00014-89-J-1366 p 1177 A93-53209 N00014-91-J-1204 p 1178 A93-53216 N60921-90-C-0033 p 1211 A93-53445 RTOP 505-62-10 p 1194 A93-53980 RTOP 505-62-50 p 1206 A93-54268 RTOP 505-66-11 p 1190 A93-52881 RTQP 537-02-00 p 1200 A93-54040

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 298) December 1993

ISABE 93-7023 p 1196 A93-53999 ' ISABE 93-7110 p 1204 A93-54086 Typical Report Number ISABE 93-7024 p 1196 A93-54000 ISABE 93-7112 p 1188 A93-54087 Index Listing ISABE 93-7025 p 1213 A93-54001 ISABE 93-7113 p 1204 A93-54088 ISABE 93-7026 p 1213 A93-54002 ISABE 93-7114 p 1221 A93-54089 ISABE 93-7027 p 1196 A93-54003 ' ISABE 93-7115 p 1221 A93-54090 ISABE 93-7028 p 1196 A93-54004 ISABE 93-7117 p 1221 A93-54092 NASA ON ISABE 93-7029 p 1184 A93-54005 ISABE 93-7118 p 1188 A93-54093 SPONSORED MICROFICHE ISABE 93-7030 p 1184 A93-54006 ISABE 93-7119 p 1221 A93-54094 L ISABE 93-7031 p 1184 A93-54007 ISABE 93-7120 p 1221 A93-54095 I | ISABE 93-7032 p 1196 A93-54008 ISABE 93-7121 p 1221 A93-54096 NASA-CR-177598 .... p99 N93-10458 ' ft ISABE 93-7033 p 1185 A93-54009 ISABE 93-7123 p 1222 A93-54098 ISABE 93-7034 p 1197 A93-54010 ISABE 93-7124 p 1189 A93-54099 PAGE ACCESSION ISABE 93-7035 p 1197 A93-54011 ISABE 93-7125 p 1204 A93-54100 NUMBER NUMBER ISABE 93-7036 p 1197 A93-54012 ISABE 93-7127 p 1204 A93-54102 ISABE 93-7037 p 1197 A93-54013 ISABE 93-7128 p 1204 A93-54103 ISABE 93-7038 p 1197 A93-54014 ISABE 93-7129 p 1175 A93-54104 Listings in this index are arranged alphanumeri- ISABE 93-7039 p 1197 A93-54015 ISABE 93-7130 p 1189 A93-54105 cally by report number. The page number ISABE 93-7040 p 1198 A93-54016 ISABE 93-7131 p 1205 A93-54106 ISABE 93-7041 p 1198 A93-54017 ISABE 93-7132 p 1205 A93-54107 indicates the page on which the citation is ISABE 93-7042 p 1198 A93-54018 ISABE 93-7133 p 1225 A93-54108 located. The accession number denotes the num- ISABE 93-7043 p 1198 A93-54019 ber by which the citation is identified. An aster- ISABE 93-7044 p 1198 A93-54020 ISBN 1-56347-071-3 p 1 1 94 A93-53976 isk (•) indicates that the item is a NASA report. ISABE 93-7045 p 1219 A93-54021 ISBN 1-85768-045-6 p 1175 A93-54287 A pound sign (#) indicates that the item is avail- ISABE 93-7046 p 1198 A93-54022 ISABE 93-7047 p 1185 A93-54023 ONERA, TP NO. 1993-102 p 1226 A93-53615 able on microfiche. ISABE 93-7048 p 1199 A93-54024 ONERA, TP NO. 1993-103 p 1226 A93-53616 ISABE 93-7049 p 1213 A93-54025 ONERA, TP NO. 1993-105 p 1180 A93-53618 ISABE 93-7050 p 1199 A93-54026 ONERA, TP NO. 1993-108 p 1225 A93-53620 AIAA PAPER 93-1797 p 1218 A93-53585 ' # ISABE 93-7052 p 1199 A93-54028 ONERA. TP NO. 1993-109 p 1206 A93-53621 AIAA PAPER 93-2521 p 1193 A93-53589 ' # ISABE 93-7053 p 1185 A93-54029 ONERA, TP NO. 1993-132 p 1221 A93-54095 AIAA PAPER 93-2919 p 1180 A93-53591 ' # ISABE 93-7054 p 1185 A93-54030 ONERA, TP NO. 1993-75 p 1218 A93-53596 AIAA PAPER 93-3253 p 1180 A93-53592 • # ISABE 93-7055 p 1185 A93-54031 ONERA, TP NO. 1993-77 p 1212 A93-53598 AIAA PAPER 93-3545 p 1207 A93-52652 # ISABE 93-7057 p 1185 A93-54033 ONERA, TP NO. 1993-78 p 1212 A93-53599 ISABE 93-7058 p 1185 A93-54034 ONERA, TP NO. 1993-82 p 1213 A93-53602 AIAA PAPER 93-3548 p 1226 A93-52653 # ISABE 93-7059 p 1219 A93-54035 AIAA PAPER 93-3550 p 1222 A93-52654 # ONERA, TP NO. 1993-83 p 1190 A93-53603 ISABE 93-7060 p 1220 A93-54036 ONEHA, TP NO. 1993-84 p 1191 A93-53604 AIAA PAPER 93-3551 p 1207 A93-52655 # ISABE 93-7061 p 1199 A93-54037 AIAA PAPER 93-3552 p 1222 A93-52656 # ISABE 93-7062 p 1199 A93-54038 SAE PAPER 892283 p 1176 A93-53200 ' AIAA PAPER 93-3558 p 1214 A93-52659 * # ISABE 93-7063 p 1200 A93-54039 AIAA PAPER 93-3559 p 1222 A93-52660 # ISABE 93-7064 p 1200 A93-54040 AIAA PAPER 93-3560 p 1214 A93-52695 # ISABE 93-7065 p 1200 A93-54041 AIAA PAPER 93-3563 p 1223 A93-52663 # ISABE 93-7066 p 1200 A93-54042 AIAA PAPER 93-3566 p 1207 A93-52665 # ISABE 93-7067 p 1200 A93-54043 ' AIAA PAPER 93-3570 p 1208 A93-52668 # ISABE 93-7068 p 1186 A93-54044 AIAA PAPER 93-3574 p 1208 A93-52670 # ISABE 93-7069 p 1201 A93-54045 AIAA PAPER 93-3575 p 1208 A93-52671 • # ISABE 93-7072 p 1201 A93-54048 AIAA PAPER 93-3577 p 1208 A93-52673 # ISABE 93-7073 p 1201 A93-54049 AIAA PAPER 93-3579 p 1208 A93-52675 ' # ISABE 93-7074 p 1220 A93-54050 AIAA PAPER 93-3580 p 1208 A93-52676 # ISABE 93-7075 p 1186 A93-54051 ' AIAA PAPER 93-3582 p 1214 A93-52677 # ISABE 93-7076 p 1220 A93-54052 AIAA PAPER 93-3583 p 1223 A93-52678 # ISABE 93-7077 p 1220 A93-54053 ' AIAA PAPER 93-3585 p 1209 A93-52679 * # ISABE 93-7078 p 1220 A93-54054 AIAA PAPER 93-3587 p 1223 A93-52680 ' # ISABE 93-7079 p 1201 A93-54055 AIAA PAPER 93-3588 p 1223 A93-52681 # ISABE 93-7080 p 1201 A93-54056 AIAA PAPER 93-3589 p 1223 A93-52682 # ISABE 93-7081 p 1213 A93-54057 AIAA PAPER 93-3590 p 1223 A93-52683 # ISABE 93-7082 p 1201 A93-54058 AIAA PAPER 93-3591 p 1224 A93-52684 * # ISABE 93-7083 p 1202 A93-54059 AIAA PAPER 93-3593 p 1224 A93-52685 " # ISABE 93-7084 p 1202 A93-54060 AIAA PAPER 93-3594 p 1224 A93-52686 # ISABE 93-7085 p 1202 A93-54061 AIAA PAPER 93-3596 p 1224 A93-52687 # ISABE 93-7086 p 1186 A93-54062 ' AIAA PAPER 93-3598 p 1209 A93-52688 # ISABE 93-7087 p 1202 A93-54063 AIAA PAPER 93-3604 p 1175 A93-52690 # ISABE 93-7088 p 1202 A93-54064 AIAA PAPER 93-3606 p 1191 A93-52691 # ISABE 93-7089 p 1202 A93-54065 AIAA PAPER 93-3607 p 1214 A93-52667 # ISABE 93-7090 p 1203 A93-54066 ISABE 93-7091 p 1203 A93-54067 ISABE 93-7000 p 1227 A93-53977 ISABE 93-7092 p 1186 A93-54068 ISABE 93-7001 p 1194 A93-53978 ISABE 93-7093 p 1186 A93-54069 ISABE 93-7002 p 1194 A93-53979 ISABE 93-7094 p 1186 A93-54070 ISABE 93-7003 p 1194 A93-53980 ISABE 93-7095 p 1186 A93-54071 ' ISABE 93-7005 p 1194 A93-53981 ISABE 93-7096 p 1203 A93-54072 ISABE 93-7006 p 1183 A93-53982 ISABE 93-7097 p 1203 A93-54073 ISABE 93-7007 p 1183 A93-53983 ISABE 93-7098 p 1187 A93-54074 ISABE 93-7008 p 1183 A93-53984 ISABE 93-7099 p 1187 A93-54075 ISABE 93-7009 p 1183 A93-53985 ISABE 93-7100 p 1187 A93-54076 ISABE 93-7010 p 1183 A93-53986 ISABE 93-7101 p 1192 A93-54077 ISABE 93-7011 p 1184 A93-53987 ISABE 93-7102 p 1187 A93-54078 ISABE 93-7012 p 1184 A93-53988 ISABE 93-7103 p 1187 A93-54079 ISABE 93-7015 p 1194 A93-53991 ISABE 93-7104 p 1187 A93-54080 ISABE 93-7016 p 1195 A93-53992 ISABE 93-7105 p 1203 A93-54081 ISABE 93-7018 p 1195 A93-53994 ISABE 93-7019 p 1195 A93-53995 ISABE 93-7106 p 1188 A93-54082 ISABE 93-7020 p 1195 A93-53996 ISABE 93-7107 p 1188 A93-54083 ISABE 93-7021 p 1195 A93-53997 ISABE 93-7108 p 1203 A93-54084 ISABE 93-7022 p 1195 A93-53998 ISABE 93-7109 p 1204 A93-54085

F-1 ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 298) December 1993

Typical Accession Number A93-53499 p 1217 A93-53985 p 1183 A93-54075 p 1187 A93-53503 p 1217 A93-53986 p 1183 A93-54076 p 1187 Index Listing A93-54077 p 1192 A93-53506 p 1212 A93-53987 p 1184 A93-53988 p 1184 A93-54078 p 1187 A93-53514 p 1217 A93-53991 p 1194 A93-54079 p 1187 p 1217 A93-53515 A93-53992 p1195 A93-54080 p 1187 A93-53551 p 1179 A93-53994 p 1195 A93-54081 p 1203 A93-53552 p 1179 A93-53995 p1195 A93-54082 p 1188 A93-53554 p 1193 A93-53996 p 1195 A93-54083 p 1188 A93-53555 p 1179 A93-53997 p 1195 A93-54084 p 1203 A93-53573 p 1179 A93-53998 p1195 A93-54085 p 1204 A93-53574 p 1180 A93-53999 • p1196 A93-54086 p 1204 A93- 53575 p 1180 A93-54000 p 1196 A93-54087 p 1188 A93-53585 * # p 1218 A93-54001 p 1213 A93-54088 p 1204 A93-53589 ' ft p 1193 A93-54002 p1213 A93-54089 p 1221 A93-53591 '# p 1180 A93-54003 ' p 1196 A93-54090 p 1221 A93-53592 ' # p 1180 A93-54004 p 1196 A93-54092 p 1221 Listings in this index are arranged alphanumerically A93-53596 p 1218 A93-54005 p 1184 A93-54093 p 1188 A93-53598 p 1212 by accession number. The page number indicates the A93-54006 p 1184 A93-54094 p 1221 A93-53599 p 1212 page on which the citation is located. The accession A93-54007 p 1184 A93-54095 p 1221 A93-53602 p 1213 number denotes the number by which the citation is A93-54008 p 1196 A93- 54096 p 1221 A93-53603 p1190 A93-54009 p1185 A93- 54098 p 1222 identified. An asterisk (*) indicates that the item is a A93-53604 p 1191 A93-54010 p1197 A93-54099 p 1189 NASA report. A pound sign (#) indicates that the item A93-53615 p 1226 A93-5401 1 p1197 A93-54100 p 1204 A93-53616 p 1226 is available on microfiche. A93-54012 p 1197 A93-54102 p 1204 A93-53618 p 1180 A93-54013 p 1197 A93-54103 p 1204 A93-53620 p 1225 A93-54014 p 1197 A93-54104 p 1175 A93-53621 p 1206 A93-54015 P1197 A93-54105 P1189 A93-53625 p1209 A93-52651 p 1207 A93-52958 p 1176 A93-54016 p 1198 A93-54106 p 1205 A93-53642 p 1225 A93-52652 # p 1207 A93-52959 p 1176 A93-54017 p 1198 A93-54107 P1205 A93-53702 p1193 A93-52653 # p 1226 A93-52961 p 1211 A93-54018 p 1198 A93-54108 p 1225 A93-53721 p 1191 A93-52963 p 1193 A93-54019 p 1198 A93-54241 p 1214 A93-52654 ft P1222 A93-53726 p 1227 A93-52965 p 1193 A93-54020 p 1198 A93-54244 p 1205 A93-52655 ft p 1207 A93-53727 p 1227 A93-52968 p 1215 A93-54021 p 1219 A93-54250 p 1214 A93-52656 # p 1222 A93-53736 ' p 1181 A93-52973 p 1215 A93-54022 p 1198 A93-54266 p 1189 A93-52659 •# p 1214 A93-53737 " p 1210 A93-52975 p 1215 A93-54023 p 1185 A93-54268 p 1206 A93-52660 # p 1222 A93-53738 ' p1210 A93-52976 p 1209 A93-54024 p 1199 A93-54275 p 1210 A93-52663 # P1223 A93-53739 " p 1181 A93-52979 p1215 A93-54025 p 1213 A93-54276 p1222 A93-52665 ft p 1207 A93-53740 * p 1181 A93-52994 p 1192 A93-54026 p 1199 A93-54277 p 1206 A93-52667 # p 1214 A93-53745 ' p 1210 A93-53172 p 1190 A93-54028 p 1199 A93-54278 p1207 A93-52668 # 1208 A93-53768 p 1209 p A93-53192 p 1176 A93-54029 p 1185 A93- 54287 p 1175 A93-52670 # A93-53769 ' p 1192 p1208 A93-53193 p 1176 A93-54030 p 1185 A93-54288 p 1189 A93-52671 •# 1208 A93-53770 p1225 p A93-53194 p 1225 A93-54031 p 1185 A93-54289 p 1190 A93-52673 # 1208 A93-53771 p1192 p A93-53200 * p 1176 A93-54033 p 1185 A93-54290 p 1190 A93-52675 •ft A93-53772 p 1192 p1208 A93-53202 " p 1176 A93-54034 p 1185 A93-54291 p 1190 A93-52676 ft 1208 A93-53774 p 1209 p A93-53204 " p 1177 A93-54035 p 1219 A93-54292 p 1205 A93-52677 ft p 1214 A93-53776 p 1218 A93-53205 p 1177 A93-54036 p 1220 A93-54293 p 1190 A93-52678 ft 1223 A93-53798 p 1181 p A93-53206 p 1225 A93-54037 p 1199 A93- 54294 p 1193 A93-52679 1209 A93- 53799 p 1181 •# p A93-53207 p 1177 A93-54038 p 1199 A93-54295 p 1175 A93-52680 A93-53810 p1218 • # p 1223 A93-53208 * p 1177 A93-54039 p 1200 A93-54314 p 1189 A93-52681 A93-53812 p 1218 ft P1223 A93-53209 p 1177 A93-54040 p 1200 A93-54324 " p 1189 ft A93-52682 p 1223 A93-53212 ' p 1177 A93-53815 p1218 A93-54041 p 1200 A93-54347 p 1189 A93-53817 1226 A93-52683 ft P1223 A93-53214 • p 1177 p A93-54042 p 1200 A93-52684 1224 •ft p A93-53216 p 1178 A93-53819 p1219 A93-54043 • p 1200 1224 A93-53820 1219 A93-52685 •ft p A93-53217 p 1178 p A93-54044 p 1186 A93-52686 ft 1224 A93-53826 ' p1227 p A93-53218 p 1178 A93-54045 p 1201 A93-52687 A93-53837 1181 ft P1224 A93-53219 p 1178 p A93-54048 p 1201 A93-52688 ft A93-53840 p 1181 p 1209 A93-53222 p 1226 A93-54049 p 1201 A93-52690 ft P1175 A93-53224 p 1216 A93-53841 p 1181 A93-54050 p1220 A93-52691 A93-53842 p 1182 ft p 1191 A93-53231 ' p 1178 A93-54051 ' p 1186 A93-52695 1214 A93-53843 p 1182 ft p A93-53233 p 1178 A93-54052 p 1220 A93-52732 1224 A93-53847 p 1219 p A93-53314 p 1178 A93-54053 ' p 1220 ' A93-52751 P1215 A93-53315 p 1179 A93-53852 p 1182 A93-54054 p1220 A93-52754 A93-53853 p 1182 p1209 A93-53329 p 1216 A93-54055 p 1201 • A93-52762 P1224 A93-53333 p 1179 A93-53858 p 1182 A93-54056 p1201 A93-52763 ' A93-53859 p 1182 P1224 A93-53364 p 1179 A93-54057 p 1213 A93-52770 ' A93-53860 p1183 P1175 A93-53365 p 1179 A93-54058 p 1201 A93-52870 1211 A93-53862 p 1194 p A93-53395 ' p 1216 A93-54059 p 1202 A93-52881 A93-53866 p 1191 P1190 A93-53405 p 1191 A93-54060 p 1202 A93-52885 A93-53868 1183 p 1210 A93-53419 p 1211 p A93-54061 p 1202 A93-52898 * A93-53869 1206 P1222 A93-53420 p1211 p A93-54062 * p 1186 A93-52930 A93-53874 p 1226 A93-53423 p 1226 p1192 A93-54063 p 1202 A93-52931 p 1226 A93-53429 p 1216 A93-53876 p 1192 A93-54064 p1202 A93-52937 A93-53877 p1206 p 1191 A93-53434 p 1211 A93-54065 p 1202 A93-52939 A93-53881 p 1219 p 1215 A93-53445 p 1211 A93-54066 p 1203 A93-52941 A93-53976 p 1194 p 1205 A93-53448 p 1212 A93-54067 p 1203 A93-52942 A93-53977 p 1227 p1205 A93-53451 p 1212 A93-54068 p 1186 p 1194 A93-52943 p 1206 A93-53452 p 1216 A93-53978 A93-54069 p1186 A93-52944 p 1206 A93-53979 p 1194 A93-53453 * p 1212 A93-54070 p 1186 A93-52945 p 1225 A93-53980 p 1194 A93-53459 ' p 1212 A93-54071 ' p 1186 A93-52946 p 1176 A93-53981 p 1194 A93-52949 p 1193 A93-53468 * p 1216 A93-53982 P1183 A93-54072 p 1203 A93-52950 p1215 A93-53493 p 1217 A93-53983 p 1183 A93-54073 p 1203 A93-52954 p 1191 A93-53498 p 1217 A93-53984 P1183 A93-54074 p 1187

G-1 AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A93-10000 Series) Publications announced in IAA are available from theAIAA Technical Information Service as follows: Paper copies of accessions are available at $10.00 per document (up to 50 pages), additional pages $0.25 each. Standing order microfiche are available at the rate of $1.45 per microfiche for IAA source documents and $1.75 per microfiche for AIAA meeting papers. Minimum air-mail postage to foreign countries is $2.50.All foreign orders are shipped on payment of pro-forma invoices. All inquiries and requests should be addressed to:Technical Information Service, American Institute of Aeronautics and Astronautics, 555 West 57th Street, New York, NY 10019. Please refer to the accession number when requesting publications.

STAR ENTRIES (N93-10000 Series) One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below, and their addresses are listed on page APP-3. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line. Avail: CASI. Sold by the NASA Center for AeroSpace Information. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code following the letters HC or MF in the ST/ARcitation. Current values for the price codes are given in the tables on pageAPP-5. NOTE ON ORDERING DOCUMENTS: When ordering publications from CASI, use the N accession number or other report number. It is also advisable to cite the title and other bibliographic identification. Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. Avail: BLL (formerly NLL): British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England. Photocopies available from this organization at the price shown. (If none is given, inquiry should be addressed to the BLL.) Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collec- tions of Department of Energy reports, usually in microfiche form, are listed in Energy ResearchAbstracts. Services available from the DOE and its depositories are described in a booklet, DOE Technical Information Center- Its Functions and Sen//ces(TID-4660), which may be obtained without charge from the DOETechnical Information Center. Avail: ESDU. Pricing information on specific data, computer programs, and details on Engineering Sciences Data Unit (ESDU) topic categories can be obtained from ESDU International Ltd. Requesters in NorthAmerica should use the Virginia address while all other requesters should use the London address, both of which are on page APP-3. Avail: Fachinformationszentrum, Karlsruhe. Gesellschaft fur wissenschaftlich-technische Information mbH 7514 Eggenstein-Leopoldshafen 2, Germany. Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S. by Pendragon House, Inc. (PHI), Redwood City, CA. The U.S. price (including a service and mailing charge) is given, or a conversion table may be obtained from PHI. 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.

APP-1 Avail: NASA Public Document Rooms. Documents so indicated may be examined at or pur- chased from the National Aeronautics and Space Administration (JBD-4), Public Documents Room (Room 1H23), Washington, DC 20546-0001, or public document rooms located at NASA installations, and the NASA Pasadena Office at the Jet Propulsion Laboratory. Avail: NTIS. Sold by the NationalTechnical Information Service. Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) are available. For information concerning this service, consult the NTIS Subscription Section, Springfield, VA22161. Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstractsand 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, U.S. Patent and Trademark Office, at the standard price of $1.50 each, postage free. 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 (IMS) representative in their country, or by applying directly to the issuing organization. Avail: USGS. Originals of many reports from the U.S. Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed on pageAPP-S.The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction.

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APP-2 ADDRESSES OF ORGANIZATIONS

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APP-3 CASI PRICE TABLES (Effective August 1, 1993)

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APP-5 REPORT DOCUMENT PAGE 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (298)

Title and Subtitle 5. Report Date Aeronautical Engineering December 1993 A Continuing Bibliography (Supplement 298) 6. Performing Organization Code JTT 7. Author(s) 8. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Address NASA Scientific and Technical Information Program 11. Contract or Grant No.

12. Sponsoring Agency Name and Address 13. Type of Report and Period Covered National Aeronautics and Space Administration Special Publication Washington, DC 20546-0001 14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract This report lists 328 reports, articles and other documents recently announced in the NASA STI Database.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aeronautical Engineering Unclassified - Unlimited Aeronautics Subject Category - 01 Bibliographies

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified Unclassified 112 A06/HC For sale by the NASA Center for AeroSpace Information, 800 Elkridge Landing Road, Linthicum Heights, MD 21090-2934 FEDERAL REGIONAL DEPOSITORY LIBRARIES

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