Aeronautical Engineering

NASA SP-7037 (309) October 1994

(NASA-SP-7037(309)) AERONAUTICAL N95-1289A- ENGINEERING: A CONTINUING BIBLIOGRAPHY WITH INDEXES (SUPPLEMENT 309) (NASA) 83 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 1994 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 212 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) N94-36231 — N94-37480 Open Literature (A-60000 Series) A94-61024 — A94-61885

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 STAR specific categories and the remaining STAR major categories. This arrangement offers the user the most advantageous breakdown for individual objectives. The citations include the original accession numbers from the respective announcement journals.

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

A cumulative index for 1994 will be published in early 1995.

Information on availability of documents listed, addresses of organizations, and CASI price schedules are located at the back of this issue. TABLE OF CONTENTS

Category 01 Aeronautics 563

Category 02 Aerodynamics 564 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 569 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 570 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 570 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 577 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 577 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 579 Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 582 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 583 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 584 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellents and fuels; and materials processing.

Category 12 Engineering 586 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.

INItNHONAUT BUNI Category 13 Geosciences N.A. 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 597 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 599 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 N.A. 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 N.A.

Subject Index A-1 Personal Author Index B-1 Corporate Source Index C-1 Foreign Technology Index 0-1 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 ON MICROFICHE

ACCESSION NUMBER N94-10675*# National Aeronautics and Space Administration. CORPORATE SOURCE Langley Research Center, Hampton, VA. TITLE STATIC INTERNAL PERFORMANCE OF A SINGLE EXPANSION RAMP NOZZLE WITH MULTIAXIS THRUST VECTORING CAPABILITY AUTHORS FRANCIS J. CAPONE and ALBERTO W. SCHIRMER (George Washington Univ., Hampton, VA.) Washington Jul. 1993 PUBLICATION DATE 272 p CONTRACT NUMBER (Contract RTOP 505-62-30-01) REPORT NUMBERS (NASA-TM-4450;L-17163;NAS 1.15:4450) Avail: CASI HCA12/ AVAILABILITY AND MFA03 PRICE CODE An investigation was conducted at static conditions in order to determine the internal performance characteristics of a multiaxis thrust vectoring single expansion ramp nozzle. Yaw vectoring was achieved by deflecting yaw flaps in the nozzle sidewall into the nozzle exhaust flow. In order to eliminate any physical interference between the variable angle yaw flap deflected into the exhaust flow and the nozzle upper ramp and lower flap which were deflected for pitch vectoring, the downstream comers of both the nozzle ramp and lower flap were cut off to allow for up to 30 deg of yaw vectoring. The effects of nozzle upper ramp and lower flap cutout, yaw flap hinge line location and hinge inclination angle, sidewall containment, geometric pitch vector angle, and geometric yaw vector angle were studied. This investigation was conducted in the static-test facility of the Langley 16-foot Transonic Tunnel at nozzle pressure ratios up to 8.0. Author (revised)

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED i ACCESSION NUMBER A94-60042* National Aeronautics and Space Administration. CORPORATE SOURCE Lewis Research Center, Cleveland, OH. TITLE EXPERIMENTAL INVESTIGATION OF COUNTER-ROTATING PROPFAN FLUTTER AT CRUISE CONDITIONS AUTHORS ORAL MEHMED NASA Lewis Research Center, Cleveland, OH and AUTHOR'S AFFILIATION ANATOLE P. KURKOV Journal of Propulsion and Power (ISSN JOURNAL TITLE PUBLICATION DATE 0748-4658) vol. 10, no. 3 May-June 1994 p. 343-347 refs REPORT NUMBER (BTN-94-EIX94321333310) Copyright This article presents wind-tunnel experimental flutter results, at transonic relative flows, for a 0.62-m-diam composite propfan model. A blade row that fluttered was tested alone, and with a stable aft counter-rotating blade row. The major objectives of the experiment were to study the effect of the second blade row on the row in flutter, and to investigate the flutter. Results show that the second row had a small stabilizing effect. Two distinct flutter modes were found within the operating regime of the rotor both apparently single- degree-of-freedom instabilities, associated respectively with the first and second natural blade modes. For both flutter modes, flutter boundary, frequency, nodal diameter, and blade displacement data are given. The blade displacement data, obtained with an optical method, gives an indication of the flutter mode shape at a span near the blade tip. Author (El)

vii AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 309) October 1994

01 throughout the decade. In their struggle to survive and prosper as markets shrink, aerospace companies are applying and mixing a broad AERONAUTICS (GENERAL) array of strategies. The author analyzes corporate behaviors and strategies of big military enterprises. El

A94-61855 A94-61782 VORTEX CUTTING BY A BLADE. PART 1: GENERAL ONE-EQUATION TURBULENCE MODEL FOR THEORY AND A SIMPLE SOLUTION AERODYNAMIC FLOWS J. S. MARSHALL Iowa Univ., Iowa City, IA AIAA Journal (ISSN P. R. SPALART Boeing Commercial Airplane Group, Seattle, WA 0001-1452) vol. 32, no. 6 June 1994 p. 1154-1150 refs and S. R. ALLMARAS Recherche Aerospatiale (ISSN 0034-1223) (BTN-94-EIX94421374957)' Copyright no. 1 1994 p. 5-21 refs A simplified theory for long-wave motion of vortex filaments with (BTN-94-EIX94401367449) Copyright variable core radius is given, for small values of the ratio epsilon - A transport equation for the turbulent viscosity is assembled using max(sigma/L) of core radius sigma to axial length scale L, which offers empiricism and arguments of dimensional analysis, Galilean invari- a number of advantages for numerical computations of the vortex ance, and selective dependence on the molecular viscosity. It has response. An analytical solution of this theory is then obtained for the similarities with the models of Nee and Kovaszany, Secundov et a!., and axial flow within a straight vortex filament following cutting of the vortex Baldwin and Barth. The equation includes a nonviscous destruction by a flat blade at an angle of attack alpha. El term that depends on the distance of the wall. El A94-61856 A94-61783 FLUCTUATING WALL PRESSURES NEAR SEPARATION IN COMPUTATION OF TRANSONIC FLOWS AROUND A WING- HIGHLY SWEPT TURBULENT INTERACTIONS PLUS-FUSELAGE CONFIGURATION TAKING VISCOUS J. D. SCHMISSEUR Wright-Patterson Air Force Base, Dayton, EFFECTS AND A THIN SEPARATED REGION INTO OH AIAA Journal (ISSN 0001 -1452) vol. 32, no. 6 June 1994 ACCOUNT p. 1151-1157 refs V. E. KOVALEV Inst. Hydro-Aeriodynamique Central, Moscow (BTN-94-EIX94421374958) Copyright (Russia) and O. V. KARAS Recherche Aerospatiale (ISSN 0034- Fluctuating wall pressures have been measured in Mach 5 1223) no. 1 1994 p. 23-38 refs interactions generated by sharp, unswept fins at angles of attack of 16 (BTN-94-EIX94401367450) Copyright to 28 deg. The results show that rms pressure distributions, like the An algorithm and a program were developed for computing the mean, can be collapsed in conical coordinates. The wall pressure signal transonic flow around a wing-plus-fuselage configuration taking vis- near separation is intermittent and is qualitatively similar to that cous effects into account. They are based on a semi-inverse viscous- measured in unswept interactions and other swept flows. El inviscid coupling method that also takes the possible existence of a thin separated region into account. The inviscid fluid flow is computed by A94-61865* National Aeronautics and Space Administration. Goddard numerically integrating the complete potential equation expressed in Space Right Center, Greenbelt, MD. conservative form. El LOW-DIMENSIONAL DESCRIPTION OF THE DYNAMICS IN SEPARATED FLOW PAST THICK AIRFOILS A94-61785 ANIL E. DEANE NASA. Goddard Space Right Center, Greenbelt, MULTIDOMAIN METHOD FOR SEVERAL BODIES IN MD and CATHERINE MAVRIPLIS AIAA Journal(\SSHQQ01-1452) RELATIVE MOTION vol. 32. no. 6 June 1994 p. 1222-1227 refs WEN-ZHONG SHEN LIMSI-CNRS, Orsay (France) and S. (BTN-94-EIX94421374967) Copyright HUBERSON Recherche Aerospatiale (ISSN 0034-1223) no. 1 Results are presented for the numerical simulation of unsteady 1994 p. 53-66 refs viscous incompressible flow past thick airfoils. Specifically, flow past a (BTN-94-EIX94401367452) Copyright NACA 4424 at an angle of attack of 2.5 deg and Reynolds numbers in We present a numerical study of the flow around two airfoils. The the range of 1700-4000 has been simulated using the spectral element first one is oscillating while the second is fixed. A muttidomain method method. At these conditions the flow is separated and an unsteady is used. An appropriate discretization scheme is used in eax^subdomain. wake is formed. Application of the method of empirical eigenfunctions A finite difference method is used in the near solid walls. A vortex reveals the structures of the most energetic components of the flow. method is used in the rest of the domain. El Author (revised by El)

A94-61788 A94-61868 COPING WITH THE DEFENSE CUTBACK SWIRL CONTROL IN AN S-DUCT AT HIGH ANGLE OF JOHN C. DYER Mitre Corp. Aerospace America (ISSN 0740- ATTACK 722X) vol. 32, no. 1 January 1994 p. 20-25 P. F. WENG Shanghai Jiao Tong Univ., Shanghai (China) and R. (BTN-94-EIX94401216109) Copyright W. QUO AIAA Journal (ISSN 0001 -1452) vol. 32, no. 6 June The drop in defense-related employment will be experienced 1994 p. 1321-1322 refs

563 01 AERONAUTICS (GENERAL)

(BTN-94-EIX94421374970) Copyright augments NASA TM-101025, TRENDS: The Aeronautical Post-Test, The problem of angular swirl flow in an S-shaped inlet without Database Management System, Jan. 1990, written by the same guide vanes has come to the fore in the past several years. Many authors. Author (revised) possible modifications of the inlet geometry have been used in the reduction of swirl. This paper describes an improvement of a severely distorted swirl flow in an S-shaped duct at very high angle of attack using N94-37352 Naval Postgraduate School, Monterey, CA. a variable lip technique. Author (revised by El) PLANNING GERMAN ARMY HELICOPTER MAINTENANCE AND MISSION ASSIGNMENT M.S. Thesis A94-61877 ACHIMSGASLIK Mar. 1994 106p Limited Reproducibility: More EQUIVALENT PLATE STRUCTURAL MODELING FOR WING than 20% of this document may be affected by microfiche quality SHAPE OPTIMIZATION INCLUDING TRANSVERSE SHEAR (AD-A280483) Avail: CASI HC A06 ELI LIVNE Univ. of Washington, Seattle, WA AIM Jouma/(ISSN German Army light helicopter transportation regimens operate 45 0001-1452) vol. 32, no. 6 June 1994 p. 1278-1288 refs Bell UH-1D helicopters to support demanding missions throughout (BTN-94-EIX94421374979) Copyright Europe. Maintenance period scheduling, major exercise and regular A new technique for structural modeling of airplane wings is mission assignment decisions directly influence the readiness of the presented taking transverse shear effects into account The kinematic helicopter fleet. Currently, all planning is done manually, which is assumptions of first-order shear deformation plate theory in combina- unstructured and time consuming. This thesis describes a decision tion with numerical analysis, where simple polynomials are used to support system designed to assist with maintenance planning and define geometry, construction, displacement approximations, lead to mission assignment The yearly maintenance and event scheduling analytical expressions for elements of the stiffness and mass matrices problem and the short term mission assignment tasks are formulated and load vector. El and solved as elastic mixed integer linear programs. Resulting yearly schedules and short term sortie plans are both generated in a fraction N94-36648** National Aeronautics and Space Administration. Hugh of the time previously required with solution quality superior to their L. Dryden Right Research Facility, Edwards, CA. manual counterparts. DTIC PRELIMINARY ANALYSIS FOR A MACH 8 CROSSFLOW TRANSITION EXPERIMENT ON THE PEGASUS (R) SPACE BOOSTER 02 LESLIE GONG, W. LANCE RICHARDS, RICHARD C. MONAGHAN, and ROBERT D.QUINN Nov. 1993 23 p Presented at the Society AERODYNAMICS for Experimenal Mechanics, Structural Testing Technology at High Temperature 2 Conference, Ojai, CA, 8-10 Nov. 1993 Includes aerodynamics of bodies, combinations, wings, rotors, and (Contract RTOP 505-70-91) control surfaces; and internal flow in ducts and turbomachinery. (NASA-TM-104272; H-1954; NAS 1.15:104272) Avail: CASIHC A03/ MFA01 A boundary-layer transition is proposed for a future flight mission A94-61620 of the air-launched Pegasus space booster. The flight experiment EFFECTS OF NOZZLE EXIT GEOMETRY ON FOREBODY requires attaching a glove assembly to the wing of the first-stage VORTEX CONTROL USING BLOWING booster. The glove design consists of a spring and hook attachment NATHAN M. GITTNER North Carolina State Univ., Raleigh, NC system which allows for thermal growth of a steel 4130 skin. The results and NDAONA CHOKANI Journal of Aircraft (ISSN 0021 -8669) from one- and two-dimensional thermal analyses of the initial design are vol. 31, no. 3 May-June 1994 p. 503-509 refs presented. Results obtained from the thermal analysis using turbulent (BTN-94-EIX94401358964) Copyright flow conditions showed a maximum temperature of approximately 305 An experimental study has been undertaken to examine the C and a chordwise temperature gradient of less than 8.9 C/cm for the influence of the blowing nozzle exit geometry on the effectiveness of the critical areas in the upper glove skin. The temperatures obtained from aft blowing technique for forebody vortex control. The experiments these thermal analyses are well within the required temperature limits were conducted with a 3.0-caliber tangent ogive model at subsonic of the glove. Author (revised) velocities and a Reynolds number of 8.4 x 10(exp 4) based on the model diameter. Asymmetric aft blowing was accomplished using both a N94-37332*# National Aeronautics and Space Administration. Ames single nozzle and a double nozzle configuration. Detailed surface Research Center, Moffett Reid, CA. pressure measurements on the model were obtained and local side TRENDS: A FLIGHT TEST RELATIONAL DATABASE forces determined. The experimental results show that both the height USER'S GUIDE AND REFERENCE MANUAL and the width of the blowing nozzle exit geometry are important M. J. BOND), W. S. BJORKMAN, and J. L CROSS Jun. 1994 parameters that determine the effectiveness of aft blowing; a broad, 286 p See also N90-25149 low-positioned blowing nozzle exit geometry is found to be most (Contract RTOP 505-59-36) effective for the forebody vortex control technique using aft blowing. (NASA-TM-108806; A-94042; NAS 1.15:108806) Avail: CASI HC A13/ Author (El) MF A03 This report is designed to be a user's guide and reference manual for users intending to access rotocraft test data via TRENDS, the A94-61623 relational database system which was developed as a tool for the INFLUENCE OF AERODYNAMIC FORCES IN ICE SHEDDING aeronautical engineer with no programming background. This report R. J. SCAVUZZO Univ. of Akron, Akron, OH, M. L. CHU, and V. has been written to assist novice and experienced TRENDS users. ANANTHASWAMY Journal of Aircraft (tSSN 0021-8669) vol. 31. TRENDS is a complete system for retrieving, searching, and analyzing no. 3 May-June 1994 p. 526-530 refs both numerical and narrative data, and for displaying time history and (BTN-94-EIX94401358967) Copyright statistical data in graphical and numerical formats. This manual pro- Stresses in accreted ice on a typical airfoil impact tee caused by vides a 'guided tour' and a 'user's guide' for the new and intermediate- aerodynamic forces have been studied using finite element analyses. skilled users. Examples for the use of each menu item within TRENDS The objective of this study is to determine the significance of these is provided in the Menu Reference section of the manual, including full stresses relative to values needed to cause ice shedding. In the case coverage for TIMEHIST, one of the key tools. This manual is written studied, stresses are not significant (less than 10%) when compared to around the XV-15 Tilt Rotor database, but does include an appendix on the fracture value for airspeeds below a Mach number of 0.45. Above the UH-60 Blackhawk database. This user's guide and reference this velocity, the influence of aerodynamic forces on impact ice stresses manual establishes a ref enable source for the research community and should be considered in the analyses of ice shedding. Author (El)

564 AERODYNAMICS 02

A94-61624 predicting the onset of transition with two versions of the e-double-prime UNSTEADY AERODYNAMIC CHARACTERISTICS OF A method. Author (El) DUAL-ELEMENT AIRFOIL ISMAIL H. TUNCER Naval Postgraduate School, Monterey, CA A94-61630 and LAKSHMI N. SANKAR Journal of Aircraft (ISSN 0021-8669) DRAG AND WAKE MODIFICATION OF AXISYMMETRIC vol. 31, no. 3 May-June 1994 p. 531-537 refs BLUFF BODIES USING COANDA BLOWING (BTN-94-EIX94401358968) Copyright J. B. FREUND Stanford Univ., Stanford, CA and M. G. MUNGAL Unsteady aerodynamic behavior and load characteristics of a VR- Journal of Aircraft (\SSM 0021 -8669) vol. 31, no. 3 May-June 1994 7 slat/airfoil combination oscillating sinusoidally between 5-25 deg have p. 572-578 refs been studied. The unsteady, compressible Navier-Stokes equations (BTN-94-EIX94401358974) Copyright are solved on a multiblock grid using an approximate factorization finite This work investigates the ability of Coanda jet blowing to modify difference scheme. In the case of a single airfoil, a massive flow the base pressure of a cylindrical body aligned axially in a flow, and separation and formation of a strong vortex is observed. The vortex- thereby, produce overall drag reduction. It is found that blowing through induced suction and the shedding of the vortex into the wake is one or two slot jets concentric to the outer body circumference can responsible for high aerodynamic loads and the subsequent stall of the significantly influence the entire base flow region. The recirculating airfoil. In the case of a slat/airfoil combination, the suction peak at the wake is eliminated and is replaced by freestream fluid entrained by the leading edge of the airfoil is reduced significantly in comparison to the Coanda blowing. Base pressure rises significantly and leads to drag single airfoil. Flow separation is confined to the trailing edge of the main reduction of up to 30% beyond the thrusting action of the Coanda jet airfoil, and the formation of a strong vortical structure is not observed. A comparison between the power savings through drag reduction and The slat/airfoil combination does not experience a massive flow sepa- the power requirement of the Coanda jet demonstrates that net benefits ration, and the aerodynamic lift does not undergo the characteristic are attainable at certain body geometries and flow conditions. By deep dynamic stall hysteresis loops. Author (El) judiciously selecting the jet blowing velocity, it is possible to produce a nearfy flat wake velocity profile requiring little net power. Author (El) A94-61626 LIFT ENHANCEMENT OF AN AIRFOIL USING A GURNEY FLAP AND VORTEX GENERATORS A94-61631 BRUCE L. STORMS Sterling Software, Moffett Field, CA and REDUCTION IN SIZE AND UNSTEADINESS OF VTOL CORY S. JANG Journal of Aircraft (ISSN 0021-8669) vol. 31, GROUND VORTICES BY GROUND FENCES no. 3 May-June 1994 p. 542-547 refs T. B. HARMAN Pennsylvania State Univ., University Park, PA, J. (BTN-94-EIX94401358970) Copyright M. CIMBALA, and M. L. BILLET Journal of Aircraft (ISSN 0021 - Experimental measurements of surface pressure distributions 8669) vol. 31, no. 3 May-June 1994 p. 579-584 refs and wake profiles were obtained for an NACA 4412 airfoil to determine (BTN-94-EIX94401358975) Copyright the lift, drag, and pitching-moment coefficients for various configura- A ground vortex, produced when a jet impinges on the ground in tions. The addition of a Gumey flap increased the maximum lift the presence of crossflow, is encountered by V/STOL aircraft hovering coefficient from 1.49 up to 1.96, and decreased the drag near the near the ground, and is known to be hazardous to the aircraft. The maximum lift condition. There was, however, a drag increment at low- objective of this research was to identify a ground-based technique by to-moderate lift coefficients. Additional nose-down pitching moment which both the mean size and fluctuation in size of the ground vortex was also generated by increasing the Gumey flap height Good could be reduced. A simple passive method has been identified and correlation was observed between the experiment and Navier-Stokes examined in the laboratory. Specifically, one or two fine wire mesh computations of the airfoil with a Gumey flap. Two deployable configu- screens (ground fences), bent in a horseshoe shape, located on the rations were also tested with the hinge line forward of the trailing edge ground in front of the jet impingement point proved to be very effective. by one and 1.5 flap heights, respectively. These configurations pro- The ground fences work by decreasing the momentum of the upstream- vided performance comparable to that of the Gumey flap. The applica- traveling wall jet, causing an effectively higher freestream-to-jet velocity tion of vortex generators to the baseline airfoil delayed boundary-layer ratio V/V(sub j), and therefore, a ground vortex smaller in size and separation and yielded an increase in the maximum lift coefficient of unsteadiness. At V/V(sub j) & 0.15, the addition of a single ground fence 0.34. In addition, there was a significant drag penalty associated with resulted in a 70% reduction in mean size of the ground vortex. With two the vortex generators, which suggests that they should be placed where ground fences, the mean size decreased by about 85%. Fluctuations they will be concealed during cruise. The two devices were also shown in size decreased nearly in proportion to the mean size, for both the to work well in concert Author (El) single and double fence configurations. These results were consistent over a wide range of jet Reynolds number (10(exp 4) less than Re(sub A94-61629 jet) less than 10(exp 5)); further development and full-scale Reynolds CALCULATION OF THREE-DIMENSIONAL LOW REYNOLDS number testing are required, however, to determine if this technique can NUMBER FLOWS be made practical for the case of actual VTOL aircraft Author (El) TUNCER CEBECI California State Univ., Long Beach, CA, HSUN H. CHEN, and BENG P. LEE Journal of Aircraft (ISSN 0021-8669) A94-61637 vol. 31, no. 3 May-June 1994 p. 564-571 refs INLET DRAG PREDICTION FOR AIRCRAFT CONCEPTUAL (BTN-94-EIX94401358973) Copyright DESIGN An interactive boundary-layer stability-transition approach is used PAUL MALAN Virginia Polytechnic Inst. and State Univ., to calculate the performance characteristics of an infinite swept wing at Blacksburg, VA and EUGENE F. BROWN Journal of Aircraft low Reynolds numbers for several angles of attack. The inviscid flow (ISSN 0021-8669) vol. 31, no. 3 May-June 1994 p. 616-622 solutions are obtained from an inviscid method based on conformal refs mapping and the viscous flow solutions from an inverse boundary-layer (BTN-94-EIX94401358981) Copyright scheme which uses the Hilbert integral formulation to couple the Recent efforts to upgrade the aircraft conceptual design code inviscid and viscous flow. The onset of transition Is calculated by the e- ACSYNT prompted a study of inlet drag prediction methods suited to double-prime method, based on two- and three-dimensional versions conceptual design. Existing methods were expanded to enable the drag of linear stability theory. Calculated results for an Infinite swept wing with of four different inlet types (subsonic pilot, supersonic pilot, supersonic an Eppler airfoil cross section are presented for sweep angles corre- two-dimensional, and supersonic conical) to be predicted over the sponding to lambda = 30,40, and 45 deg, and for Reynolds numbers complete Inlet operating range.These methods have been successfully of 3 x 10(exp 5) and 4.6 x 10(exp 5). The effect of sweep angle on lift incorporated into ACSYNT and are presented together with test cases and drag coefficients is investigated together with the accuracy of representing a range of inlet geometries. Author (El)

565 02 AERODYNAMICS

A94-61638 COMPOSITE STRUCTURED AND UNSTRUCTURED COMPUTATION OF THREE-DIMENSIONAL HYPERSONIC MESHES FLOWS IN CHEMICAL NONEOUILIBRIUM H. HEFAZI California State Univ., Long Beach, CA, V. CHIN, and S. MENNE Deutsche Aerospace A.G., Munich (Germany), C. L. T. CHEN Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 WEILAND, and M. PRTZNER Journal of Aircraft (ISSN 0021-8669) May-June 1994 p. 651-658 refs vol. 31, no. 3 May-June 1994 p. 623-630 refs (BTN-94-EIX94401358986) Copyright (BTN-94-EIX94401358982) Copyright A two-dimensional zonal interactive scheme, based on Euler An algorithm for the simulation of three-dimensional hypersonic equations, has been developed for computing flows about complex flows in chemical nonequilibrium is presented. The basic flow solver is geometries. A composite structured and unstructured grid, using based on a quasiconservative formulation of the Euler or Navier-Stokes conformal mapping and Delaunay triangulation, respectively, is first equations. The Jacob! matrices are split according to the sign of their generated about the geometry. The finite-volume Euler method is then eigenvalues. The derivatives of the conservative variables are split modified to couple zones with structured and unstructured grids. accordingly. A third-order upwind space discretization is used in Solutions about multielement airfoils and iced airfoils are given as conjunction with an optimized three-stage Runge-Kutta explicit time examples of the applications of the scheme. The zonal interaction stepping scheme. The chemistry source terms are treated point- scheme and accuracy and efficiency of the solutions are discussed. implicitly. For inviscid flow, the code is applied to the complete Author (El) HERMES 1.0 configuration. The influence of mesh resolution is studied by comparing a fine grid with a coarse grid solution. The coarse grid A94-61645 solution is usually sufficient to describe global flow phenomena. The NUMERICAL INVESTIGATIONS ON TWO-DIMENSIONAL analysis of local flow details requires refined meshes. For viscous flow, CANARD-WING AERODYNAMIC INTERFERENCE the flow about generic configurations (double-ellipse, hemisphere- SAN-YIH LIN Inst. of Aeronautics and Astronautics, Tainan cylinder-flare, hyperbola-flare) is investigated by performing grid sensi- (Taiwan, Province of China), YAN-SHIN CHIN, and YUH-YING tivity studies as well as by comparing different transport models. WANG Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 Author (El) May-June 1994 p. 672-679 refs (BTN-94-EIX94401358989) Copyright A94-61639* National Aeronautics and Space Administration. Ames A finite element method for solving of the Euler and Navier-Stokes Research Center, Moffett Reid, CA. equations is used to study the unsteady aerodynamics of a two- NAVIER-STOKES COMPUTATIONS FOR OSCILLATING dimensional canard-wing aerodynamic interference. The method used CONTROL SURFACES a discontinuous finite element method for spatial discretization and an SHIGERU OBAYASHI NASA. Ames Research Center, Moffett explicit Runge-Kutta time integration for temporal discretization. The Field, CA and GURU P. GURUSWAMY Journal of Aircraft (ISSN problems of a flow over an airfoil with/without viscosity, a flow over a 0021-8669) vol. 31, no. 3 May-June 1994 p. 631-636 refs pitching airfoil, and an airfoil-vortex interaction are tested to show the (BTN-94-EIX94401358983) Copyright accuracy of the proposed numerical method. Finally, the results of two- Unsteady Navier-Stokes computations have been performed for dimensional canard-wing aerodynamic interference in steady and simulating transonic flows over wings with oscillating control surfaces unsteady transonic flows are shown to demonstrate the robustness of using a locally moving grid and a stationary-mismatched zoning the numerical algorithm and qualitative and quantitative aerodynamic scheme. An F-5 wing and a clipped delta wing are chosen for the influence of one airfoil on the other. Author (El) present study. The computed unsteady pressures and the response characteristics to the control surface motions are compared with A94-61646 experimental data. The results successfully predict main features of the DESIGN OF OPTIMIZED AIRFOILS IN SUBCRITICAL FLOW unsteady pressure profiles, such as the double peaks at the shock wave J. OLEJNICZAK Minnesota Univ., Minneapolis, MN and A. S. and at the hinge time. Author (El) LYRINTZIS Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 May-June 1994 p. 680-687 refs A94-61640 (BTN-94-EIX94401358990) Copyright PREDICTION METHOD FOR UNSTEADY AXISYMMETRIC An airfoil design method based on optimization procedures in FLOW OVER PARACHUTES computational aerodynamics is presented. This article extends the J. H. STRICKLAND Sandia National Lab., Albuquerque. NM method to include subcritical compressible flow and a modified Stratford Journal of Aircra ft (\SSH 0021 -8669) vol. 31, no. 3 May-June 1994 recovery distribution to alleviate the hard stall that is typical of Stratford- p. 637-643 refs type airfoils. A procedure for optimizing the drag is also presented (BTN-94-EIX94401358984) Copyright based on the Squire-Young drag formula. The performance character- A method which is capable of solving the axisymmetric flowfield istics of this airfoil are then tested with a compressible panel method and over bluff bodies consisting of thin shells such as disks, partial spheres, boundary-layer solver. The procedures for both incompressible and rings, and other such shapes is presented in this article. The body may compressible flow have generated airfoils which generate more lift and be made up to several shells whose edges are separated by gaps. The less drag than other comparable airfoils. High-lift airfoils which display body may be moved axially according to arbitrary velocity time histories. a smooth stall region have also been developed which hold promise for In addition, the surfaces may possess axial and radial degrees of general aviation use. In addition, these airfoils offer the potential of flexibility such that points on the surfaces may be allowed to move improved performance in applications such as high-endurance aircraft, relative to each other according to some specified function of time. The propellers, fans, and windmill blades where high lift-to-drag ratios are surfaces may be either porous or impervious. The present solution desired. A specific example of an airfoil designed for a wind turbine is technique is based on the axisymmetric vortcity transport equation. presented and compared to an existing airfoil. Author (El) This technique requires relatively large numbers of ring vortices (1000 or more) to obtain good simulations. Since the direct calculation of A94-61647 perturbations from large numbers of ring vortices is computationally LEADING-EDGE VORTEX BREAKDOWN FOR WING Intensive, a fast muttipole method was used to greatly reduce computer PLANFORMS WITH THE SAME SLENDERNESS RATIO processing time. Several example calculations are presented for disks, WILLIAM A. STRAKA George Washington Univ., Hampton. VA disks with holes, hemispheres, and vented hemispheres. These results and MICHAEL J. HEMSCH Journal of Aircraft (ISSN 0021 -8669) are compared with steady and unsteady experimental data. vol. 31.no. 3 May-June 1994 p. 688-695 refs Author (El) (BTN-94-EIX94401358991) Copyright A dye flow visualization investigation was conducted on two sets A94-61642 of wing planforms to better understand the effects of planform shaping TWO-DIMENSIONAL EULER ZONAL METHOD USING on leading-edge vortex breakdown. The first set of planforms consisted

566 AERODYNAMICS 02

of five cropped planforms, including a 66.3-deg delta, 80/55 double- N94-36394*# California Polytechnic State Univ., San Luis Obispo. delta, and three blended 80/55 double-deltas. The second set of CA. Dept of Aeronautical Engineering. planforms consisted of nine planforms of the same slendemess ratio, NUMERICAL INVESTIGATION OF MULTI-ELEMENT AIRFOILS including a 69.3-deg delta, two gothics, three double-deltas, and three Final Technical Report corresponding blended double-deltas. Results of these experiments RUSSELL M. CUMMINGS Oct. 1993 14 p have indicated that planforms with a common slendemess ratio de- (Contract NCC2-761) velop quite similar characteristics for breakdown of the apex vortex at (NASA-CR-194592; NAS 1.26:194592) Avail: CASI HC A03/MF A01 the trailing edge. It was found that planform shaping significantly alters The flow over multi-element airfoils with flat-plate lift-enhancing the forward progression of breakdown along the wing as angle of attack tabs was numerically investigated. Tabs ranging in height from 0.25 is increased. The effect of increasing filleting to double-delta planforms percent to 1.25 percent of the reference airfoil chord were studied near was shown to degrade the apex vortex breakdown characteristics of the the trailing edge of the main-element. This two-dimensional numerical planforms. Also, it was found that by moving the kink location of the simulation employed an incompressible Navier-Stokes solver on a double-delta aft on the planform, breakdown characteristics are im- structured, embedded grid topology. New grid refinements were used proved. Author (El) to improve the accuracy of the solution near the overlapping grid boundaries. The effects of various tabs were studied at a constant Reynolds number on a two-element airfoil with a slotted flap. Both A94-61810 computed and measured results indicated that a tab in the main- NEW AIRFOIL-DESIGN CONCEPT WITH IMPROVED element cove improved the maximum lift and lift-to-drag ratio relative to AERODYNAMIC CHARACTERISTICS the baseline airfoil without a tab. Computed streamlines revealed that DEMETER G. FERTIS Akron Univ., Akron, OH Journal of the additional turning caused by the tab may reduce the amount of Aerospace Engineering (ISSN 0893-1321) vol. 7, no. 3 July 1994 separated flow on the flap. A three-element airfoil was also studied over p. 328-339 refs a range of Reynolds numbers. For the optimized flap rigging, the (BTN-94-EIX94401372110) Copyright computed and measured Reynolds number effects were similar. When The research in this paper is the result of an experimental study the flap was moved from the optimum position, numerical results regarding a new airfoil-design concept, which is developed to produce indicated that a tab may help to reoptimize the airfoil to within 1 percent greater lift coefficients overamuch broader range of operational angles of the optimum flap case. Author of attack, to improve or eliminate stall at virtually all operational airspeeds, to increase functional lift-to-drag ratios over a greater range N94-36466# EMA, Mansfield, TX. of operational angles of attack, and to be adaptable for aircraft of both ROTORWASH ANALYSIS HANDBOOK. VOLUME 1: the fixed-wing and the rotary-wing types. The writer has combined his DEVELOPMENT AND ANALYSIS Final Report effort with L. L. Smith, and a U.S. Patent, entitled 'Airfoil,1 Patent No. SAMUEL W. FERGUSON Jun. 1994 336 p Prepared for 4,606,519, was obtained on August 19, 1986. Patents were also Systems Control Technology, Inc., Arlington, VA obtained or are pending in other countries. The experimental results, (Contract DTFA01-87-C-00014) obtained by using the new airfoil-design concept, have been compared (SCT-93RR-17-VOL-1; DOT/FAA/RD-93^1-VOL-1) Avail: CASI HC with experimental results obtained from a conventional NACA 23012 A15/MF A03 airfoil. Right performance tests by using a 2.134-m (7.0 ft) model and Rotorcraft operations at heliports and airports are investigated to remote-control devices, as well as flow-separation studies, were also better understand and quantify the potential hazards associated with performed. The results were compared with the ones obtained by using various types of rotorwash flow fields. Mathematical models for the the NACA 23012 airfoil. Author (El) various types are developed. These mathematical models are used in conjunction with hazard analysis models to develop an analysis methodology for evaluation of the potential tor rotorwash-related mishaps in N94-36261* Naval Surface Warfare Center, Bethesda, MD. Ship various operational scenarios. Correlation of all developed mathemati- Systems Directorate. cal models with flight test, scale-model, and laboratory test data is TIPJET 80-INCH MODEL ROTOR HOVER TEST: TEST NO. provided wherever possible. Heliport design examples using the devel- 1198 Final Report, Jan. - Dec. 1991 oped analysis methodology and the associated ROTWASH computer ALAN W. SCHWARTZ Sep. 1993 97 p program are provided. Documentation, a program listing, and a user's (Contract PROJ. RR22-M59) guideare provided forverston2.1 of the FORTRAN 77-based ROTWASH (AD-A279680; CDRKNSWC/SSD-93/54) Avail: CASIHC A05/MF A02 computer program in report appendices (see Volume 2 of this report). An experimental investigation was conducted to examine the An extensive bibliography of rotorwash related technical documents is aerodynamic properties of a Tipjet integrated pneumatic lift/reaction- also provided. Author (revised) drive rotor system in hover. For this rotor system, a single source of compressed air directly powers the rotor as a radial outflow turbine while N94-36467* EMA, Mansfield, TX. simultaneously supplying the high velocity jet sheet that produces lift by ROTORWASH ANALYSIS HANDBOOK. VOLUME 2: means of circulation control (CC) along the blades. A sub scale model APPENDIXES Final Report of such a fully pneumatic Tipjet rotor system was constructed and SAMUEL W. FERGUSON Jun. 1994 192 p Prepared for tested on the hover test facility at the David Taylor Model Basin. The Systems Control Technology, Inc., Arlington, VA model was tested to identify unique attributes of the integrated lift/drive (Contract DTFA01-87-C-00014) system including mutual interference between tip nozzle flow and CC (SCT-93RR-17-VOL-2; DOT/FAA/RD-93-31-VOL-2) Avail: CASI HC jet sheets and the impact of drawing CC supply air from a flowing A09/MF A02 plenum'. Test results are presented for the model is four configurations: Documentation, a program listing, and a user's guide are provided CC rotor with tip nozzles closed, rotor locked with nozzles thrusting, tip for version 2.1 of the FORTRAN 77-based ROTWASH computer drive CC rotor with controlled rpm, and tip-jet self drive equilibrium. The program in report appendices. An extensive bibliography of rotorwash basic rotor lifting system, while exhibiting the highest augmentation related technical documents is also provided. This listing is subdivided ratio ever recorded tor a CC rotor, suffers an induced power penalty due into different rotorwash topics. A companion report, entitled 'Evaluation to the nonlifting region of the blade span where the tip nozzles are of Rotorwash Characteristics for Tittrotor and Tittwing Aircraft in Hover- located. As expected, an internal pressure drop due to the flow rate in ing Right,' DOT/FAA/RD-90/16, evaluates rotorwash characteristics of the blade duct was observed. There was no evidence of mutual 11 different types of tiltrotor and tiltwing aircraft for comparison pur- interference effects between the lift and drive systems. Overall, the poses. Another companion report, entitled 'Analysis of Rotorwash rotor exhibited a constant, linear response of lift versus pressure Effects in Helicopter Mishaps,' DOT/FAA/RD-90/17, presents an analy- regardless of the slot height or the equilibrium tip speed. sis of several of the more common types of rotorwash related helicopter Author (revised) mishaps. Much of the information provided in this second companion 567 02 AERODYNAMICS

report is updated by this report A third report, DOT/FAA/RD-90/25, order-accurate, flux-difference-splitting, algorithm is implemented and 'Rotorwash Computer Model - User's Guide,' is replaced by this more employed to solve the Navier-Stokes equations. The equations are comprehensive report and its updated version of the ROTWASH solved using a finite volume methodology. The aerodynamic and static- computer program. Author stability characteristics are investigated to determine if conventional supersonic missile configurations can be flown at Mach numbers higher N94-36686*# National Aeronautics and Space Administration. Lewis than 5. The effects of nosetip blunting and boundary-layer condition are Research Center, Cleveland, OH. demonstrated. The structure of the flow near the fins is significantly MIXING AND NOISE BENEFIT VERSUS THRUST PENALTY IN affected by the turbulent transport of momentum in regions of blocked SUPERSONIC JETS USING IMPINGEMENT TONES cross flow. Turbulence and the blockage phenomenon cause bleeding GANESH RAMAN (NYMA, Inc., Brook Park, OH.) and EDWARD around the fin leading edges. Ultimately, this results in lower fin J. RICE May 1994 17 p Proposed for presentation at the 30th effectiveness and reduced static stability. The aerodynamic character- Joint Propulsion Conference, Indianapolis, IN, 27-29 Jun.1994; istics of the HART missile are predicted at Mach numbers beyond the sponsored by AIAA, ASME, SAE, and ASEE experimental free-flight testing capabilities. The current predictions (Contract NAS3-27186; RTOP 537-02-22) indicated that the pitching-moment coefficient decreases with increas- (NASA-TM-106583; E-8844; NAS 1.15:106583; AIAA PAPER 94- ing Mach number much less than previous numerical computations. 2955) Avail: CASI HC A03/MF A01 The present results also suggest that the clipped-delta-fin configuration This paper reports the results of an experimental investigation on is stable beyond Mach 7. DTIC the effect of impingement tones generated by obstacles of various geometries on the spreading of a supersonic jet flow. A rectangular N94-36942*# National Aeronautics and Space Administration. supersonic jet was produced using a convergent-divergent nozzle that Langley Research Center, Hampton, VA. was operated near its design point (with shocks minimized). The AUTOMATIC PROCEDURES FOR COMPUTING COMPLETE immersion of obstacles in the flow produced an intense impingement CONFIGURATION GEOMETRY FROM INDIVIDUAL tone which then propagated upstream (as feedback) to the jet lip and COMPONENT DESCRIPTIONS excited the antisymmetric hydrodynamic mode in the jet thus setting up RAYMOND L BARGER and MARY S. ADAMS Jul. 1994 14 p a resonant self-sustaining loop. The violent flapping motion of the jet (Contract RTOP 509-10-11-01) due to excitation of the antisymmetric mode, combined with the (NASA-TM-4607; L-17395; NAS 1.15:4607) Avail: CASI HC A03/MF unsteady wakes of the obstacles, produced large changes in jet mixing. A01 It was possible to control the frequency and amplitude of the impinge- Procedures are derived for developing a complete airplane ment tone excitation by varying the nozzle-to-obstacle distance and the surface geometry starting from component descriptions. The proce- obstacle immersion. By proper shaping of the obstacles it was possible dures involve locating the intersection lines of adjacent components to reduce the thrust penalty significantly. Author and omitting any regions for which part of one surface lies within the other. The geometry files utilize the wave-drag (Harris) format, and N94-36687*# Eloret Corp., Palo Alto, CA. output files are written in Hess format. Two algorithms are used: one, EXPERIMENTAL INVESTIGATION OF NOZZLE/PLUME if both intersecting surfaces have airfoil cross sections; the other, if one AERODYNAMICS AT HYPERSONIC SPEEDS Final of the surfaces has circular cross sections. Some sample results in Technical Report, 1 Aug. 1987 • 31 Jan. 1994 graphical form are included. Author DAVID W. BOGDANOFF, JEAN-LUC CAMBIER, and PERIKLES PAPADOPOULOS 29 Apr. 1994 15 p N94-36944*# National Aeronautics and Space Administration. Hugh (Contract NCC2-487) L Dryden Right Research Center, Edwards, CA. (NASA-CR-195829; NAS 1.26:195829) Avail: CASI HC A03/MF A01 CONTROLLING FOREBODY ASYMMETRIES IN FLIGHT: Much of the work involved the Ames 16-Inch Shock Tunnel EXPERIENCE WITH BOUNDARY LAYER TRANSITION facility. The facility was reactivated and upgraded, a data acquisition STRIPS system was configured and upgraded several times, several facility DAVID F. FISHER and BRENT R. COBLEIGH Washington Jul. calibrations were performed and test entries with a wedge model with 1994 22 p Presented at the 6th Biennial Right Test Conference, hydrogen injection and a full scramjet combustor model, with hydrogen Colorado Springs, CO, 20-23 Jun. 1994 injection, were performed. Extensive CFD modeling of the flow in the (Contract RTOP 505-68-71) facility was done. This includes modeling of the unsteady flow in the (NASA-TM-4595; H-1992; NAS 1.15:4595; AIAA PAPER 94-1826) driver and driven tubes and steady flow modeling of the nozzle flow. Copyright Avail: CASI HC A01/MF A01 Other modeling efforts include simulations of non-equilibrium flows and The NASA Dryden Right Research Center has an ongoing turbulence, plasmas, light gas guns and the use of non-ideal gas program to investigate aircraft flight characteristics at high angles of equations of state. New experimental techniques to improve the attack. As part of this investigation, longitudinal boundary layer transi- performance of gas guns, shock tubes and tunnels and scramjet tion strips were installed on the F-18 HARV forebody, a preproducfion combustors were conceived and studied computationally. Ways to F/A-18 radome with a nose-slice tendency, and the X-31 aircraft improve scramjet engine performance using steady and pulsed deto- forebody and noseboom to reduce asymmetric yawing moments at nation waves were also studied computationally. A number of studies high angles of attack. The transition strips were effective on the F-18 were performed on the operation of the ram accelerator, including HARV at angles of attack above 60 deg. On the preproduction F/A-18 investigations of in-tube gasdynamic heating and the use of high radome at an angle of attack near 50 deg the strips were not effective. explosives to raise the velocity capability of the device. When the transition strips were installed on the X-31 noseboom, a Author (revised) favorable effect was observed on the yawing moment dynamics but the magnitude of the yawing moment was not decreased. Author N94-36729# Air Force Inst of Tech., Wright-Patterson AFB, OH. School of Engineering. N94-36950*# National Aeronautics and Space Administration. AN AERODYNAMIC AND STATIC-STABILITY ANALYSIS OF Langley Research Center, Hampton, VA. THE HYPERSONIC APPLIED RESEARCH TECHNOLOGY AUTOMATIC COMPUTATION OF EULER-MARCHING AND (HART) MISSILE Ph.D. Thesis SUBSONIC GRIDS FOR WING-FUSELAGE KENNETH J. MORAN Apr. 1994 124 p CONFIGURATIONS (AD-A280631; AFIT/DS/AA/94-3) Avail: CASI HC A06/MF A02 RAYMOND L BARGER, MARY S. ADAMS, and RAMKI R. KRISHNAN The flow about the complete Hypersonic Applied Research Jul. 1994 20 p Technology (HART) missile is simulated for inviscid, laminar, and (Contract RTOP 509-10-11-01) turbulent conditions and Mach numbers from 2 to 6. An explicit, second- (NASA-TM-4573; L-17364; NAS 1.15:4573) Avail: CASI HC A03/

568 AIR TRANSPORTATION AND SAFETY 03

MFA01 shown. Also, grids for realistic geometries, a NACA 0012 airfoil and a Algebraic procedures are described for the automatic generation wing/nacelle installation, were created. The flow over a NACA 0012 of structured, single-block flow computation grids for relatively simple airfoil was used as a test case for the flow solver. Eight separate cases configurations (wing, fuselage, and fin). For supersonic flows, a quasi were run. They were both the inviscid and viscous solutions for two two-dimensional grid for Euler-marching codes is developed, and some freestream Mach numbers and airfoil angle of attacks of 0 to 3.86 sample results in graphical form are included. A type of grid for subsonic degrees. The Mach numbers chosen were for a subsonic case, Mach flow calculation is also described. The techniques are algebraic and are 0.6, and a case where supersonic regions and a shock wave exists, based on a generalization of the method of transfinile interpolation. Mach 0.8. These test case conditions were selected to match experi- Author mentally obtained data for code comparison. The results show that the code accurately predicts the flow field for all cases. Author N94-36966*# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. N94-37378** National Aeronautics and Space Administration. Hugh NAVIER-STOKES AND POTENTIAL THEORY SOLUTIONS L. Dryden Right Research Center, Edwards, CA. FOR AHELICOPTER FUSELAGE AND COMPARISON WITH MEASUREMENT UNCERTAINTY AND FEASIBILITY STUDY EXPERIMENT OF A FLUSH AIRDATA SYSTEM FOR A HYPERSONIC FLIGHT MARK S. CHAPFIN (Vigyan Research Associates, Inc., Hampton, EXPERIMENT VA.) and JOHN D. BERRY (Army Aviation Systems Command, STEPHEN A. WHITMORE and TIMOTHY R. MOES Washington Hampton, VA.) Jun. 1994 31 p Prepared in cooperation with Jun. 1994 18 p Presented at the Applied Aerodynamics Army Aviation Systems Command, Hampton, VA Conference, Colorado Springs, CO, 20-23 Jun. 1994 (Contract NAS1-19672; RTOP 505-59-36-01; RTOP 023-10-01-01) (Contract RTOP 505-68-40) (NASA-TM-4566; L-17325; MAS 1.15:4566; ATCOM-TR-94-A-013) (NASA-TM-4627; H-2010; NAS 1.15:4627; AIAA PAPER 94-1930) Avail: CASI HC A03/MF A01 Copyright Avail: CASI HC A03/MF A01 A thin-layer Navier-Stokes code and a panel method code are Presented is a feasibility and error analysis for a hypersonic flush used to predict the flow over a generic helicopter fuselage. The airdata system on a hypersonic flight experiment (HYFLfTE). HYFLITE computational results are compared with pressure data at four experi- heating loads make intrusive airdata measurement impractical. Al- mental conditions. Both methods produce results that agree with the though this analysis is specifically for the HYFLITE vehicle and experimental pressure data. However, separation patterns and other trajectory, the problems analyzed are generally applicable to hyper- viscous flow features from the Navier-Stokes code solution are shown sonic vehicles. A layout of the flush-port matrix is shown. Surface that cannot be easily modeled with the panel method. Author pressures are related airdata parameters using a simple aerodynamic model. The model is linearized using small perturbations and inverted N94-37219 Michigan State Univ., East Lansing, Ml. Dept of Me- using nonlinear least-squares. Effects of various error sources on the chanical Engineering. overall uncertainty Eire evaluated using an error simulation. Error UNSTEADY FLOW FIELD OF LARGE-AMPLITUDE PITCHING sources modeled include boundarylayer/viscous interactions, pneu- AIRFOILS Final Technical Report, Jul. 1992 - Nov. 1993 matic lag, thermal transpiration in the sensor pressure tubing, misalign- MANOOCHEHR M. KOOCHESFAHANI 1 Feb. 1994 33 p ment in the matrix layout, thermal warping of the vehicle nose, sampling Limited Reproducibility: More than 20% of this document may be resolution, and transducer error. Using simulated pressure data for affected by microfiche quality input to the estimation algorithm, effects caused by various error (Contract AF-AFOSR-0417-89) sources are analyzed by comparing estimator outputs with the original (AO-A280444; AFOSR-94-0355TR) Avail: Issuing Activity (Defense trajectory. To obtain ensemble averages the simulation is run repeat- Technical Information Center (DTIC)) edly and output statistics are compiled. Output errors resulting from the This research program investigated the physical mechanisms various error sources are presented as a function of Mach number. involved in the onset of leading edge separation when airfoils pitch to Final uncertainties with all modeled error sources included are pre- high angles of attack. Both constant pitch rate and variable pitch rate sented as a function of Mach number. Author motions were considered. The highlights of results from a combined experimental and computational effort are described in this report. The conclusions from this research indicate the need for boundary-layer 03 resolved measurements of the flow behavior near the leading edge and the evolution of the reverse flow regions on the suction surface. AIR TRANSPORTATION AND SAFETY Furthermore, the deliberate shaping of the pitch trajectory for the purpose of optimization of separation delay is suggested as one way to Includes passenger and cargo air transport operations; and aircraft manage the flow and aerodynamic behavior of an airfoil. DTIC accidents.

N94-37283*# National Aeronautics and Space Administration. Lewis A94-61787 Research Center, Cleveland, OH. MACH 2 AND MORE A METHOD FOR FLOW SIMULATION ABOUT COMPLEX RICHARD PIELLISCH Aerospace America (ISSN 0740-722X) GEOMETRIES USING BOTH STRUCTURED AND vol. 32, no. 1 January 1994 p. 17-19 rets UNSTRUCTURED GRIDS (BTN-94-EIX94401216108) Copyright JAMES R. DEBONIS Jul. 1994 60 p Advanced materials will be the key to a viable High Speed Civil (Contract RTOP 537-02-23) Transport, but profitability is still the major concern for manufacturers (NASA-TM-106633; E-8955; NAS 1.15:106633) Avail: CASI HC A04/ and airlines. The author discusses the technological challenges of an MFA01 aircraft that will carry three times as many passengers as the Concorde A computational fluid dynamics code which utilizes both struc- at considerably higher speeds, with over 50% more range andafraction tured and unstructured grids was developed. The objective of this study of the older aircraft's emissions. El was to develop and demonstrate the ability of such a code to achieve solutions about complex geometries in two dimensions. An unstruc- N94-36530 Boeing Commercial Airplane Co., Seattle, WA. tured grid generator and flow solver were incorporated into the PARC2D WORLD JET AIRPLANE INVENTORY AT YEAR-END 1993 structured flow solver. This new unstructured grid generator capability Mar. 1994 127 p See also PB93-174324 allows for easier generation and manipulation of complex grids. Several (PB94-164993) Avail: issuing Activity (National Technical Information examples of the grid generatiorvcapabilities are provided. The coupling Service (NTIS)) of different grid topologies and the manipulation of individual grids is The Marketing Department of Boeing Commercial Airplane Group

569 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

publishes the World Jet Airplane Inventory. The document contains (NASA-CR-196098; NAS 1.26:196098) Avail: CASI HC A03/MF A01 data on the world commercial jet airplane fleet (including some military The research results described here are intended to enhance the derivatives) and reflects the status of this fleet as accurately as possible effectiveness of the DATALINK interface that is scheduled by the as of December 31,1993. (Any fleet changes that have occurred since Federal Aviation Administration (FAA) to be deployed during the 1990's year-end 1993 will not be reflected in these data). World Jet Airplane to improve the safety of various aspects of aviation. While voice has a Inventory is composed of a selected numberof reports fromJETTRACK, natural appeal as the preferred means of communication both among a computer-based jet airplane inventory systems. Reet data in this humans themselves and between humans and machines as the form system are obtained from many different sources, including airframe of communication that people find most convenient, the complexity and manufacturers, airplane owners and operators, governments, and flexibility of natural language are problematic, because of the confu- trade publications. The document provides details for announced sions and misunderstandings that can arise as a result of ambiguity, orders, deliveries, and inventories for all commercial jet airplanes built unclear reference, intonation peculiarities, implicit inference, and pre- in the United States and Western Europe with a capacity of 60 seats or supposition. The DATALINK interface will avoid many of these prob- more. In addition, the year-end 1993 inventory data in Sections 5 and lems by replacing voice with vision and speech with written instructions. 7 include operators of the Soviet built Tupolev TU-134, TU-154, TU- This report describes results achieved to date on an on-going research 204, llyushin IL-62IL-86, IL-96 and Yakovlev Yak-42 airplanes. effort to refine the protocol of the DATALINK system so as to avoid NTIS many of the linguistic problems that still remain in the visual mode. In particular, a working prototype DATALINK simulator system has been developed consisting of an unambiguous, context-free grammar and parser, based on the current air-traffic-control language and incorpo- 04 rated into a visual display involving simulated touch-screen buttons and three levels of menu screens. The system is written in the C program- AIRCRAFT COMMUNICATIONS AND NAVIGATION ming language and runs on the Macintosh II computer. After reviewing work already done on the project, new tasks for further development are Includes digital and voice communication with aircraft; air navigation described. Author systems (satellite and ground based); and air traffic control.

A94-61682 05 CAPTURE REGION FOR TRUE PROPORTIONAL NAVIGATION GUIDANCE WITH NONZERO MISS-DISTANCE AIRCRAFT DESIGN, TESTING AND DEBASHISH GHOSE Indian Inst. of Science, Bangalore, India PERFORMANCE Journal of Guidance, Control, and Dynamics (ISSN 0731 -5090) vol. 17, no. 3 May-June 1994 p. 627-628 refs Includes aircraft simulation technology. (BTN-94-EIX94401358176) Copyright In this note, an analytical solution to the problem of job training the capture region of a missile pursuing a nomaneuvering target the using A94-61266 a TPN guidance law, with acceptable nonzero miss-distance, is pre- SOME BASIC CONSIDERATIONS ON ANGLES DESCRIBING sented. It is shown that the capture region is enlarged, and deviates AIRPLANE FLIGHT MANEUVERS from its circular shape, in comparison with the zero miss-distance case. OSAMU KATO Nagoya Univ., Nagoya (Japan) Journal of In contrast to previous results, the capture region is obtained without Guidance, Control, and Dynamics (ISSN 0731 -5090) vol. 17, no. 2 solving the equations of motion in closed form. El March-April 1994 p. 378-384 refs (BTN-94-EIX94381311179) Copyright Several angles to describe the flight maneuvers of an airplane are A94-61769 introduced. First relative Euler angles, which show one flight attitude ON THE GENERALIZATION OF TRUE PROPORTIONAL relative to another flight attitude, are defined. Next, rolling angle, NAVIGATION pitching angle, and yawing angle, which are other than Euler angles, are D. GHOSE Indian Inst. of Science, Bangalore (India) IEEE defined. In addition, nose moving angle is defined as a quantity that Transactions on Aerospace and Electronic Syst ems (ISSN 0018- shows the length of the attitude path along which the flight attitude 9251) vol. 30, no. 2 April 1994 p. 545-555 refs changes. Comparative studies between similar angles in the small- (BTN-94-EIX94401377808) Copyright disturbance theory are made in large flight maneuvers. A formula which A simple framework to define generalized true proportional navi- relates the rolling angle to the variation of roll angle is obtained by gation (GTPN) guidance laws is presented. It is shown that this means of the attitude projection method and Stokes theorem. It is framework subsumes many of the generalizations presented in the shown that although the differences between the relative roll angle, earlier literature. The capture regions of a number of GTPN guidance rolling angle, and variation of roll angle are sufficiently small in small- laws are obtained through a rigorous qualitative analysis. The method disturbance flight mechanics, those differences become considerably of analysis is simpler and lends itself directly to an easy geometrical larger in large flight maneuvers. Numerical examples are presented to interpretation. A considerable amount of misinterpretation in the previ- illustrate these results. Author (El) ous results, arising out of certain basic misconceptions, are corrected here. It is shown that a logical application of the guidance philosophy, through a minor modification of GTPN to take into account the direction of rotation of the line-of-sight (LOS), contributes substantially to the A94-61267 expansion of the capture region in the relative velocity space. El SOME NONINTUITIVE FEATURES IN TIME-EFFICIENT ATTITUDE MANEUVERS OF COMBAT AIRCRAFT SPIRO BOCVAROV Virginia Polytechnic Inst. and State Univ., N94-37013** Boston Univ., MA. Blacksburg, VA, EUGENE M. CLIFF, and FREDERICK H. LUTZE AN ERROR-RESISTANT LINGUISTIC PROTOCOL FOR AIR Journal of Guidance, Control, and Dynamics (ISSN 0731 -5090) vol. TRAFFIC CONTROL Final Report, Jan. - Sep. 1989 17, no. 2 March-April 1994 p. 385-388 refs STEVEN GUSHING 1989 46 p Prepared in cooperation with (BTN-94-EIX94381311180) Copyright Stonehill Coll., North Easton, MA In some cases, numerical extremal trajectories for time-optimal (Contract NAG2-564) attitude maneuvers for combat aircraft exhibit a nonintuitive feature in

570 AIRCRAFT DESIGN, TESTING AND PERFORMANCE 05 which the extremal roll-control causes the vehicle to initially roll the nonlinear effects of the angular rate, which themselves are influenced "wrong way.' Using data for the high angle-of-attack research vehicle, by the effect of convective time lag. A flow hypothesis is presented that we present a brief exposition and engineering explanation of this and can explain the unusual experimental results. Author (El) related phenomena. The explanations are based on analyses of the structure of the aircraft mathematical model. Author (El) A94-61625 HUNTING PHENOMENA OF THE BALLOON MOTIONS A94-61268 OBSERVED OVER ANTARCTICA RANGE OPTIMAL TRAJECTORIES FOR AN AIRCRAFT FLYING JUN NISHIMURA Kanagawa Univ., Yokohama (Japan) Journal IN THE VERTICAL PLANE of Aircraft (ISSN 0021-8669) vol. 31, no. 3 May-June 1994 HANS SEYWALD Analytical Mechanics Associates, Inc., Hamp- p. 538-541 refs ton, VA, EUGENE M. CLIFF, and KLAUS H. WELL Journal of (BTN-94-EIX94401358969) Copyright Guidance, Control, and Dynamics (ISSN 0731-5090) vol. 17, no. 2 It was reported that the strong hunting motions of the balloons March-April 1994 p. 389-398 refs were observed just after reaching the ceiling altitude for the balloons (BTN-94-EIX94381311181) Copyright launched at Antarctica in the daytime. Such hunting motions are Range optimal trajectories for an aircraft flying in the vertical plane observed at middle latitude only for the nighttime launching. In this are obtained from Pontrvagin's minimum principle. Control variables article, the thermal analysis of the balloon motions is performed by are the load factor, which appears nonlineariy in the equations of considering the atmospheric temperature and the environmental radia- motion, and the throttle setting, which appears only linearly. Both tion conditions at the balloon altitudes. We found that the hunting controls are subject to fixed bounds. Additionally, a dynamic pressure phenomena over summer Antarctica are caused by the fact that the limit is imposed, which represents a first-order state-inequality con- balloons over Antarctica encounter similar thermal conditions of flights straint. For fixed flight time, initial coordinates, and final coordinates of at night over the midlatitude. Author (El) the trajectory, the effect of the load factor limit on the resulting optimal switching structure is studied. All trajectories involve singular control A94-61627 along arcs with active dynamic pressure limit. For large flight times the SIGNIFICANCE OF THE DIHEDRAL EFFECT IN RAPID optimal switching structures have not yet been found. Author (El) FUSELAGE-REORIENTATION MANEUVERS SPIRO BOCVAROV Virginia Polytechnic Inst. and State Univ.. A94-61616 Blacksburg, VA, EUGENE M. CLIFF, and FREDERICK H. LUTZE SURVEY AND COMPARISON OF ENGINEERING BEAM Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 May-June 1994 THEORIES FOR HELICOPTER ROTOR BLADES p. 548-555 refs DONALD L. KUN2 McDonnell Douglas Helicopter Co, Mesa, AZ (BTN-94-EIX94401358971) Copyright Journal of Aircraft (ISSN 0021 -8669) vol. 31, no. 3 May-June 1994 A study is presented about the role the dihedral effect (rolling p. 473-479 refs moment due to sideslip) can have in fuselage-reorientation maneuvers (BTN-94-EIX94401358960) Copyright that involve high angles of attack. A mathematical model for attitude The article presents a review of the development of engineering maneuvers is developed, which accurately represents the High Angle- beam theories for helicopter rotor blades, and history of the develop- of-Attack Research Vehicle, including propulsive moments generated ment from past to present solutions and the characteristics and by thrust-vectoring. The fuselage-reorientation problem is posed as an differences among these various formulations is also explained. This unconstrained time-optimal control problem, and numerical extrenal survey of the state of the art in rotating beam analysis provides trajectories are obtained. These trajectories are examined in order to practicing engineers with an overview of methodologies from which determine if and when the dihedral effect contributes significantly to the they can choose for applications. El maneuvers. Results indicate that for most reorientation maneuvers the dihedral effect is small, and that these minimum-time trajectories occur A94-61619 with small sideslip angles. Author (El) LOADING CHARACTERISTICS OF FINITE WINGS UNDERGOING RAPID UNSTEADY MOTIONS: A A94-61632 THEORETICAL TREATMENT WIND-TUNNELTESTTECHNIQUES FOR UNMANNED AERIAL ERIC J. JUMPER Univ. of Notre Dame, Notre Dame, IN and VEHICLE SEPARATION INVESTIGATIONS RONALD J. HUGO Journal of Aircraft (ISSN 0021-8669) vol. 31, S. A. MOYER Naval Air Warfare Center, Warminster, PA and M. no. 3 May-June 1994 p. 495-502 refs D. TALBOT Journal of Aircraft (ISSN 0021 -8669) vol. 31, no. 3 (BTN-94-EIX94401358963) Copyright May-June 1994 p. 585-590 refs This article describes an unsteady, incompressible, lifting-tine (BTN-94-EIX94401358976) Copyright method for determining spanwise loading and moments on a wing Wind-tunnel tests of an unmanned aerial vehicle (UAV) separating undergoing arbitrary dynamic motions. The method is compared to an from two fighter aircraft have been conducted. UAVs present different unsteady vortex-lattice method and a constant-source, constant-dou- concerns in separation testing than do conventional stores due to the blet paneling method and appears to predict span loading as well as presence of large lifting surfaces, physical size, and control surface these methods. The method is also compared to experimental data for effects. The planning and results of these recent investigations give an aspect-ratio-four wing undergoing a near-constant pitch-rate several new results with respect to the separation testing of complex motion. Author (El) configurations. Separation trajectory simulations using experimental data have been used to demonstrate the unique requirements of UAV A94-61622 separation testing. The simulation demonstrates that simplifications in UNIQUE HIGH-ALPHA ROLL DYNAMICS OF A SHARP-EDGED the aerodynamic grid proximity testing matrix can be made without 65 DEC DELTA WING sacrificing simulation accuracy. Results indicate that simplification in L E. ERICSSON Lockheed Missiles and Space Co., Inc. Sunnyvale, ejector modeling used with simple stores should not be applied to CA and E. S. HANFF Journal of Aircraft (ISSN 0021 -8669) vol.31, UAVs. The simulations also indicated that it is important to property no. 3 May-June 1994 p. 520-525 refs model the aircraft control surface effects on the UAV. Autho(EI) (BTN-94-EIX94401358966) Copyright An analysis has been performed of experimental results obtained A94-61643 in roll oscillation tests at 30-deg angle of attack of a 65-deg sharp-edged ACTIVE CONTROL OF WING ROCK USING TANGENTIAL delta wing in order to uncover the fluid mechanical phenomena causing LEADING-EDGE BLOWING the unusual, highly nonlinear .vehicle dynamics. In addition to the G. S. WONG Stanford Univ., Stanford. CA, S. M. ROCK, N. J. expected effect of convective flow time lag, the test results show highly WOOD, and L. ROBERTS Journal of Aircraft (ISSN 0021-8669)

571 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

vol. 31, no. 3 May-June 1994 p. 659-665 refs A94-61675 (BTN-94-EIX94401358987) Copyright ANALYSIS AND CONTROL OF BIFURCATION PHENOMENA Experiments were performed to demonstrate positive poststall IN AIRCRAFT FLIGHT roll control of a free-to-rol l wind-tunnel delta wing model using tangential MARK A. PINSKY Nevada Univ., Reno, NV and BILL ESAY leading-edge blowing. Previous static experiments had shown that Journal of Guidance, Control, and Dynamics (ISSN 0731-5090) vol. significant rolling moments could be produced up to an angle of attack 17, no. 3 May-June 1994 p. 591-598 refs of 55 deg using asymmetric tangential leading-edge blowing. The (BTN-94-EIX94401358169) Copyright implication was that poststall dynamic roll control ought to be possible This paper addresses a theoretical framework for unified method- using only blowing. Todemonstrate experimentally that this was indeed ology which allows analysis of nonlinear stability and efficient control of the case, a free-to-roll wind-tunnel model sting mounting system and a high-dimensional nonlinear plants modeling aircraft flight. It is shown pair of fast acting blowing control servo-valves were developed and that analysis of nonlinear transition phenomena (bifurcations) is central manufactured. An automatic feedback roll control algorithm using to revealing the limitation of robust control (i.e., an accurate estimate of tangential leading-edge blowing was then synthesized and imple- the basin of stability). Omitting transition behavior causes over control mented on a digital controller. Results from the present dynamic and provides a very local stabilization. Analysis and control of bifurca- experiments indicated that with just symmetric blowing alone, wing rock tions of aircraft flight are given in the spirit of the generalized normal at an angle of attack of 55 deg was damped. Furthermore, with the use forms method, which provides one with the nonreducible system that of an automatic roll feedback control algorithm employing asymmetric preserves stability characteristics of the initial plant Stabilization of a blowing, the same wing rock was stopped in less than one cycle of the plant's bifurcations is then given in terms of the resonance control limit-cycle oscillation. Author (El) methodology. Efficiency of the developed methodology is demonstrated by analyzing and controlling an unstable nonlinear plant rel- evant to the lateral dynamics of an aircraft. Whereas the initial plant is A94-61649 governed by a number of coupled nonlinear equations, the reduced COMPREHENSIVE MODEL OF ANISOTROPIC COMPOSITE system (the resonance normal form) turns out to be much easier to AIRCRAFT WINGS SUITABLE FOR AEROELASTIC analyze and even integrable in many cases. Analysis of bifurcations of ANALYSES the resonance normal forms may shape efficient control actions which G. KARPOUZIAN Naval Academy, Annapolis, MD and L. a pilot may undertake to ensure stability of an aircraft in a prescribed LIBRESCU Journal of Aircraft (ISSN 0021 -8669) vol. 31, no. 3 neighborhood of a trim condition and also can furnish a design of a May-June 1994 p. 703-712 refs flight's automatic control. Author (El) (BTN-94-EIX94401358993) Copyright A comprehensive plate-beam structural model suitable for N94-363218 Advisory Group for Aerospace Research and Develop- aeroelastic analyses of aircraft wings made of anisotropic composite ment, Neuilly-Sur-Seine (France). Right Mechanics Panel. materials is developed. The equations governing the static and dy- RECENT ADVANCES IN LONG RANGE AND LONG namic aeroelastic equilibrium of cantilevered swept-wing structures ENDURANCE OPERATION OF AIRCRAFT [LES PROGRES and the associated boundary conditions are derived by means of the REGENTS DANS LE DOMAINE DES OPERATIONS Hamilton variational principle. These equations incorporate a number AERIENNES A LONGUE DISTANCE ET DE LONGUE of effects: 1) anisotropy of the materials of constituent layers, 2) warping DUREE] inhibition, 3) transverse shear flexibility, and 4) rotatory inertias. A Nov. 1993 317 p In ENGLISH and FRENCH Symposium held uniform swept-wing model composed of a transversely isotropic mate- in The Hague, Netherlands, 24-27 May 1993 rial is considered to illustrate the coupled and separate effects of (AGARD-CP-547;ISBN-92-835-0726-6) Copyright Avail: CASI HC transverse shear deformation and warping restraint upon its divergence A14/MF A03 and static aeroelastic load distribution. An exact method based upon Over the past few years, the use of aircraft in long range and/or the Laplace integral transform technique is used to solve the above long endurance operations has proved to be a successful use of military mentioned problems. The results displayed in this article reveal the resources. Technologies which improve the range and endurance of importance of transverse shear and warping restraint effects in predict- aircraft have seen considerable advances over the past ten years. ing more accurately the static aeroelastic response of swept-forward Aircraft design for these features has matured considerably while the wings. However, for swept-back wings, these effects represent higher- procedure of air-to-air refuelling has made global deployment and 244- order corrections to the classical theory. Author (El) hour operations a reality. This Symposium attempted to summarize the latest technological advances in the various fields which in a combined A94-61674 manner define the range and endurance of airborne vehicles, i.e.: NONDIMENSIONAL FORMS FOR SINGULAR PERTURBATION airframe design technologies, including aerodynamic structures; pro- ANALYSES OF AIRCRAFT ENERGY CLIMBS pulsion technology; the human factors problems associated with A. J. CAUSE Georgia Inst. of Technology, Atlanta, GA and N. these types of missions; and air-to-air refuelling technologies and MARKOPOULOS Journal of Guidance, Control, and Dynamics procedures. (ISSN 0731-5090) vol. 17, no. 3 May-June 1994 p. 584-590 refs N94-36322# Wright Lab., Wright-Patterson AFB, OH. (BTN-94-EIX94401358168) Copyright HIGH ALTITUDE LONG ENDURANCE AIRCRAFT DESIGN This paper presents a systematic approach for identifying the STUDIES perturbation parameter in singular perturbation analysis of aircraft V. B. VENKAYYA and V. A. TISCHLER In AGARD, Recent optimal trajectories and guidance. The approach is based on a Advances in Long Range and Long Endurance Operation of Aircraft nondimensionalization of the equations of motion. It is used to evaluate 17 p Nov. 1993 the appropriateness of forced singular perturbation formulations used Copyright Avail: CASI HC A03/MF A03 in the past for transport and fighter aircraft It is also used to assess the This paper presents the results of structural optimization studies applicability of energy state approximations and singular perturbation made on a High Altitude Long Endurance (HALE) aircraft at Wright analysis for airbreathing transatmospheric vehicles with hypersonic Research and Development Center (now Wright Laboratory) during the cruise and orbital capabilities. In particular, the family of problems late eighties. The purpose of this study is to investigate the feasibility of related to aircraft energy climbs is considered. For energy climbs developing an ultralightweight airfrarne that can operate at high alti- constrained to a vertical plane, it is shown that the singular perturbation tudes for extended periods of time in order to provide continuous parameter can logically be taken as the maximum allowable longitudi- reconnaissance, surveillance, communications and targeting func- nal load factor of vehicle. Two-time-scale behavior is suggested when tions. A variety of structural concepts and material studies were made this load factor is sufficiently less than one. Author (El) prior to setting on a twin boom very high aspect ratio wing airframe. The

572 AIRCRAFT DESIGN, TESTING AND PERFORMANCE 05 wing and fuselage structures are made of truss substructures covered N94-36325# Naval Air Warfare Center, Warminster, PA. Aircraft Div. with skins, both made of high strength, high modulus, lightweight THE CASE FOR SURFACE EFFECT RESEARCH, composite materials. Extensive structural optimization studies were PLATFORM APPLICATIONS AND TECHNOLOGY conducted in order to obtain a lightweight structure. The large size of the DEVELOPMENT OPPORTUNITIES aircraft drove the design to a stiffness critical structure. Author J. M. L. REEVES In AGARD, Recent Advances in Long Range and Long Endurance Operation of Aircraft 10 p Nov. 1993 Copyright Avail: CASI HC A02/MF A03 This paper commences by defining the conventional understanding of Surface Effect phenomenon and compares theories which show N94-36323# Alenia Aeronautica, Turin (Italy). Preliminary Design small reductions in drag occur above one span height above the Dept surface. A discussion on reports of pilots who have flown their aircraft TECHNOLOGICAL CHALLENGES OF HIGH ALTITUDE LONG in surface effect ensues. From this, a broader understanding of surface ENDURANCE UNMANNED CONFIGURATIONS effect is developed supported by low speed wind tunnel tests and R. BARGETTO and R. SPEZZAFERRO In AGARD, Recent Russian published technical documentation. The author divides sur- Advances in Long Range and Long Endurance Operation of Aircraft face effect platforms or, perhaps, better described as Enhanced 12 p Nov. 1993 Performance Low Flying Platforms (EPLFP's) into three distinct cat- Copyright Avail: CASI HC A03/MF A03 egories. Potential applications of surface effect platforms are discussed This paper presents the conceptual work performed in Alenia based on the changing world, the evolving airline industry and airport during the recent years for defining some possible configurations for constraints. Missions and specific mission examples are given. Rea- military and civil HALE (High Altitude Long Endurance) aircraft capable sons for the pursuit of rather large platforms are presented as are some of carrying very different kinds of payioads and with mission durations of the major technical hurdles which will have to be overcome for them ranging from one to two days. Also in relation to the aircrew fatigue to succeed. Technology opportunities are discussed. A summary implied by such a long flight time, they all have been conceived as DMA concludes the paper. Author (UnManned Aircraft), achieving in that way a significant reduction of mass and complexity, withstanding the maturity of automatic control system. The aeromechanical aspect of the configurations (i.e., aerodynamics, propulsion, structures, systems, weights and performances) N94-36326# Office National rfEtudes et de Recherches Aerospatiales, will be discussed in detail considering that HALE-UMA type of aircraft Paris (France). have to face some technical challenges in many fields generated by the THE FUTURE OF LARGE CAPACITY/LONG RANGE rather demanding requirements in terms of payload and endurance. MULTIPURPOSE AIR CARGO FLEETS [L'AVENIR Author D'AVIONS CARGOS MULTI-ROLES A LARGE CAPACITE ET GRAND RAYON D'ACTION] PHILIPPE POISSON-QUINTON In AGARD, Recent Advances in Long Range and Long Endurance Operation of Aircraft 8 p Nov. N94-36324# Aerospatiale, Toulouse (France). Aircraft Div. 1993 In FRENCH FUTURE SUPERSONIC COMMERCIAL TRANSPORT Copyright Avail: CASI HC A02/MF A03 AIRCRAFT: A TECHNOLOGICAL CHALLENGE FOR LONG Both commercial and military aspects of Cargo Transport Avia- HAUL TRAFFIC [AVION DE TRANSPORT SUPERSONIQUE tion were discussed at the International Symposium organized by the FUTUR: UN DEFI TECHNOLOGIQUE POUR LE VOL LONG French Aerospace Academy, held in March 1993 in Strasbourg. This COURRIER] paper summarizes some of the contributions and discussions dealing J.-L. GALVANl In AGARD, Recent Advances in Long Range and with the future role of the Air Cargo Transportation in relation to a global Long Endurance Operation of Aircraft 8p Nov. 1993 In FRENCH international policy of military and humanitarian intervention, including Copyright Avail: CASI HC A02/MF A03 their technical and operational aspects. In a first part, the status of the Long haul traffic is a key sector that is constantly increasing. World's Air Cargo activity is reviewed in terms of the main operational Since Concorde entry into service in 1976, it has tripled and will again cargo airplanes, their capacity and their range, used both for commer- double by the end of the century. There is no doubt that this long haul cial and military purposes; It includes the family of large cargos traffic development will create an increasing interest in high speed. The developed by Antonov in Ukraine and preliminary designs of huge entry into service of a HSCT will enable flight time to be divided at least cargo projects by the Russian laboratory TsAGI for 250 to 500 tons by 2 on these long routes, and could capture 20 percent to 40 percent payload, and by NASA with spanloader or conventional schemes for of the long range market. To face up this future air transport landscape intermodal containers transport. In a second part, the present U.S. Aerospatiale, who jointly with British Aerospace has accumulated an Military Airlift forces are analyzed, with some comments on their recent unique experience in high speed transport with the Concorde program, global airlift deployment during the Gulf War. It is concluded that, as is studying a potential successor, the Alliance project cruising at Mach regards long term global policy, such existing task forces are totally 2. Due to the significant progress in technology already achieved or inadequate to either stop immediately some local conflicts around the foreseen in the near future, the entry into service of a second generation world, or to save population, in case of major natural or man-made supersonic transport can be envisaged as early as 2005. The success disasters. That is why a much larger airlift system should be developed of this project is strongly linked to the capability of the aircraft and the on an intergovernmental basis, the main objective would be its 'strategic 1 1 engine manufacturers to provide the appropriate technology level to efficiency instead of a 'profit earning capacity , as used in commercial make the airplane environmentally acceptable and economically at- aviation. For that purpose, a 'supercargo' can be defined, developed tractive. A significant effort in R & D is necessary to make available the and produced in the framework of an international consensus between challenging technologies: new materials, aerodynamics, propulsion.... the major aeronautical powers. Its size, configuration, operational Considering the level of investment required and the complexity of the characteristics and performance must be discussed, and a compro- problems to be solved, a dose collaboration involving industrial part- mise agreed to cope with the main military and humanitarian missions; ners is necessary on a world wide basis. This collaboration has already but such 'supercargo' airplane would be certainly much larger than the started. FoUowingalong experience of bilateral cooperation, Aerospatiale present ones, with two to four times their payload, and a transcontinen- and British Aerospace joined again in 1990 to study together a second tal range capability; for their development, advantage would be taken generation supersonic aircraft around their respective concepts (AST of the best technologies that would become available in the next and Alliance). Both partners are also cooperating with DASA, Boeing, decade, and of the availability of design capability in the world's aircraft McDonnell Douglas, the Japanese Industries, Alenia and Tupolev industry resulting from the present crisis. A flying wing configuration is within an International Study Group. Author suggested as a basis for a preliminary project Finally, there is certainly

573 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

a commercial spin-off of such massive supercargo production, if used N94-36332* Aerospatiale, Toulouse (France). Aerodynamics Con- to compete successfully with the surface transportation systems of ception Dept large intermoda) containers already used on major international CALCULATIONS USED TO OPTIMIZE THE INSTALLATION OF markets. Author CIVIL AIRCRAFT ENGINES [UTILISATION DES METHODES DE CALCUL POUR OPTIMISER L'INSTALLATION MOTRICE N94-36327# Deutsche Aerospace A.G., Munich (Germany). Military DES AVIONS DE TRANSPORT] Aircraft. X. MONTHUS. PH. COLIN, PH. MOGILKA, and A. MOLBAY- OPTIMISATION OF COMPOSITE AIRCRAFT STRUCTURES ARSAN In AGARD, Recent Advances in Long Range and Long BY DIRECT MANUFACTURING APPROACHES Endurance Operation of Aircraft 31 p Nov. 1993 In FRENCH G. BERCHTOLDand J. KLENNER /n AGARD. Recent Advances Copyright Avail: CASI HC A03/MF A03 in Long Range and Long Endurance Operation of Aircraft 12 p Within the research program on AIRBUS, the Aerodynamics Nov. 1993 Conception Department of Aerospacial Avions is responsible for the Copyright Avail: CASI HC A03/MF A03 research on the aerodynamics of the reactor's pylon, air inlet (or The present high performance aircraft designs are increasingly technical evaluation on the system provided by the constructor) and for using high strength composite structures, mainly made of unidirectional the optimization of aerodynamics in the ensemble of the engine carbon fiber tapes. But the composite technology is still afflicted with installation. This includes studies on minimizing undesirable effects several weak points, e.g. the lack of adequate mechanized tape (loss of carrying capacity, increase in drag) due to the interaction application techniques for complex compound structures, unsatisfying between wings, pylon, and engine pod. This article lists the various tools designs and design methods and missing continuous CAD/CAM- used by the above department in order to fulfill its task: the C.A.O. linkage. In this paper we will describe an 'Integrated Tape Laying system, principally conceived for aerodynamics concerns, the surface System1 (ITLS) which uses a new tape steering technology for auto- and volume representation systems as well as the main systems of 3D mated manufacturing of complex parts. This system integrates the calculations on complex geometric arrangements. Three recent appli- steering technology's potentials and restrictions completely in the cations of these methods are presented within the framework of the design process to avoid time consuming iteration loops and to optimize development of the AIRBUS A330/A340 aircraft, and associated the structure. To be able to understand the detailed process a short systems: air flow in the zone of pylon/wing intersection; effects due to overview about two different geometry models demonstrated on a the size of the engine in comparison to given wing characteristics and typical example will be given. From this the optimal detailed process will modelization of the jef s effect; and orientation of relationship between be derived, with an important influence from the specific manufacturing engine thrust and aircraft. Author technology. Finally some remarks on economic potentials are outlined with their impact on typical composite aircraft parts related to different N94-36340# Aerospace Engineering Test Establishment, Cold Lake automated manufacturing techniques. Author (revised) (Alberta). FLIGHT TEST CERTIFICATION OF A 480 GALLON N94-36330* Westiand Helicopters Ltd., Yeovil (England). COMPOSITE FUEL TANK ON CF-18 EH101: A NEW HELICOPTER CAPABLE OF LONG RANGE MARIO B. J. LAGRANGE In AGARD, Recent Advances in Long MISSIONS Range and Long Endurance Operation of Aircraft 22 p Nov. C. J. BATTISSON and H. E. TATTON-BROWN In AGARD, Recent 1993 Advances in Long Range and Long Endurance Operation of Aircraft Copyright Avail: CASI HC A03/MF A03 10 p Nov. 1993 The Aerospace Engineering Test Establishment (AETE), as the Copyright Avail: CASI HC A02/MF A03 Canadian Forces (CF) flight test authority, has recently completed flight The EH101 is a new medium helicopter being produced by EH tests and analysis of a major store certification program to establish an Industries, a company jointly owned by Agusta of Italy and Westiand of operational flight envelope for the carriage and jettison of a newly the UK. The aim of this presentation is to explore the roles in which the designed 480 gallon external fuel tank (EFT) for the CF-18 aircraft. The EH101 will be called upon to cover long ranges and examine its certification process involved a progressive series of analysis, wind suitability for these roles. The roles which will be examined fall into the tunnel tests, qualification tests, ground tests, and flight test activities. following categories: search and rescue, self-ferry, and special opera- Most of the preflight activities were performed by the designer, McDonnell tions. The successful completion of such missions will demand particu- Aircraft Company (McAir), while all flight testing was the responsibility lar capabilities of the crew and the machine. The following aspects of of AETE with engineering support from McAir. The progression of aircraft design will be looked at with respect to the EH101: in-flight events from the qualification testing to the final flight testing recommen- refuelling, all-weather capability, maintenance requirements, and crew dations are summarized herein. The primary focus of this paper is on environment. Because of the wide ranging nature of the subject and the the frying activities such as flutter, loads, stability and control, separa- limited time available this is intended to examine only the key points tion/jettison, and performance. Special instrumentation, flight test required for these roles and capabilities. Author (revised) techniques, and test concept philosophy are also discussed. This paper highlights various technical problems encountered, such as the near N94-36331# Eurocopter France, Marignane (France). flutter onset condition observed with tanks 50 percent full, the prema- THE CONVERTIBLE (HELICOPTER/AIRPLANE) EUROFAR: ture failure of the inboard wing spar pylon receptacle discovered after GENERAL CONSIDERATIONS ON THE TECHNICAL the last maneuvering loads flight, and the localized pitchup phenomena PROGRESS AND ON FUTURE ADVANCES [LE observed during stability and control (S&C) testing. A glance at the CONVERTIBLE TYPE EUROFAR: VUE D'ENSEMBLE DES increased range and payload capabilities is also included. Overall, the AVANCEMENTS TECHNIQUES ET MISSIONS FUTURES] 480 gallon EFT was determined to be a viable option for the CF-18 A. MARTINI and J. RENAUD In AGARD, Recent Advances in aircraft Author Long Range and Long Endurance Operation of Aircraft 7 p Nov. 1993 In FRENCH N94-36341* Dassault Aviation, Saint-Cloud (France). Direction Copyright Avail: CASI HC A02/MF A03 Generate Technique. Until the last few years, the idea of a convertible aircraft did not IN-FLIGHT REFUELING: DASSAULT AVIATION RESEARCH progress into testing because the available technology did not satisfy ON THE RAFALE AIRCRAFT [RAVITAILLEMENT EN VOL the cosfefficiency parameters, and because the need for such an L'EXPERIENCE DE DASSAULT-AVIATION APPLIQUEE AU aircraft was not felt Today, conditions are different Strategic necessi- RAFALE] ties and technical progress have created an atmosphere in the United CHARLES DEFREVILLE In AGARD, Recent Advances in Long States and in Europe where this old dream of engineers may be Range and Long Endurance Operation of Aircraft 11 p Nov. resurrected. Author 1993 In FRENCH

574 AIRCRAFT DESIGN, TESTING AND PERFORMANCE 05

Copyright Avail: CASI HC A03/MF A03 12 p Nov. 1993 The Rafale is the latest combat aircraft built by Dassault Aviation. Copyright Avail: CASI HC A03/MF A03 It is equipped with an in-flight refueling system using a fixed pole. This This paper presents a process that leads from comprehensive article relates the important steps taken during its conception and the tanker system requirements analysis to the development of a technol- various technologies that were used: structure, aerodynamics, sys- ogy 'road map.' This road map is a matrix listing key technology tems, etc. The second part of the article describes the testing that was requirements for future air refueling tanker aircraft capabilities and the conducted in-flight as well as on the ground, making it possible to current status of research and development activities in these key corroborate the performance of the systems and the flight characteris- areas. Generalized examples from material prepared under a U.S. Air tics of this aircraft Transl. by FLS Force Contracted Research and Development (CRAD) study are utilized. Multimission capabilities (i.e., tanker, and cargo and passen- N94-36342# Frontier Technology, Inc., Beavercreek, OH. ger transport) are often preferred for these new aircraft This allows the FUTURE TANKER CONSIDERATIONS AND REQUIREMENTS flexibility of use for many purposes besides that of just air refueling: LAVON JORDAN and MICHAEL KRIMMER In AGARD, Recent military cargo and passenger deployments, humanitarian relief, medi- Advances in Long Range and Long Endurance Operation of Aircraft cal air evacuation, executive transport, etc. For this reason these 7 p Nov. 1993 tankers are often referred to as tanker/transports' to emphasize these Copyright Avail: CASI HC A02/MF A03 capabilities. In this paper, the term tanker1 is used to describe what in Starting seven years ago, the USAF Aeronautical Systems Center all likelihood will be a tanker/transport Author (revised) began analyzing future tanker system requirements and developing plans for satisfying these requirements. Frontier Technology, Inc. (FTI) supported the USAF in four of the efforts. Frontier has completed one N94-36346# Royal Netherlands Air Force, The Hague. Training and KC-135 multipoint analysis and is currently doing a second one. The Transport Aircraft and Helicopter Div. completed effort determined: the pros and cons of hose-drogue refuel- THE KDC-10 PROGRAMME OF THE ROYAL NETHERLANDS ing and the best fuel pumping rate for the KC-135 using two wing air AIR FORCE refueling pods. The current job involves a more in-depth, overall PAUL R. BRINKGREVE In AGARD, Recent Advances in Long assessment of operational needs, concepts of operation, and alterna- Range and Long Endurance Operation of Aircraft 6 p Nov. 1993 tive wing pods. It emphasizes compatibility with Allied and U.S. Navy Copyright Avail: CASI HC A02/MF A03 aircraft receivers. Frontier Technology is presenting two related papers Replacement of the RNLAF F-27 transport fleet, first mooted in at this AGARD symposium. This paper covers the rationale and 1984, became a serious option a few years later because of a growing requirements for multipoint refueling. It covers trends and future need for AAR capacity. Years of discussion and market research employment of aerial refueling tankers, as well as the increasing resulted in a requirement for (among others) two DC-10 aircraft to be importance of interoperability. Derived from text modified into tanker/transport aircraft. The budget was not sufficient to develop new KMD-11 tanker aircraft, nor did it allow buying existing N94-36343* Naval Air Warfare Center, Patuxent River, MD. Right tanker aircraft. On the basis of earlier programs from other countries, Test and Engineering Group. involving different aircraft, RNLAF decided that it should be possible to AERIAL REFUELING INTEROPERABILITY FROM A RECEIVER modify two DC-10 aircraft into so-called KDC-10 aircraft. With assis- FLYING QUALITIES PERSPECTIVE tance from McDonnell Douglas Aircraft (MDA), four aircraft were D. J. LUDWIG In AGARD, Recent Advances in Long Range and selected on the basis of a number of criteria. These aircraft were studied Long Endurance Operation of Aircraft 7 p Nov. 1993 thoroughly. On the basis of condition and price two Martinair DC10-30 Copyright Avail: CASI HC A02/MF A03 CF aircraft were purchased on 30 June 1992. These will be modified into Over the past decade, there has been increased emphasis on KDC-10 tanker/transport aircraft. The RNLAF contracted MDA to study interservice and international operability with respect to aerial refueling feasibility, timetable, and cost of modifying two (Martinair) DC-10-30 CF (AR). One area concerning interoperability that needs to be considered aircraft into tanker/transport aircraft. The study concluded that the in light of the increased trend towards large multipoint tankers is program was feasible within the proposed time frame, given that USAF receiver flying qualities during AR. This paper stresses the importance would cooperate. Also the total cost estimate could be kept within of conducting receiver proximity trials to optimize refueling position budget It was not possible to keep the KC-10 Aerial Refuelling Operator behind the tanker and providing the pilot with the best receiver flying (ARO) station, so a new Remote Aerial Refuelling Operator (RARO) qualities for AR that can be attained. Receiver flying qualities behind the station will have to be developed. The design, however, is not com- tanker can be seriously degraded if proper steps to optimize receiver pletely new as it has been implemented on other aircraft The RNLAF refueling positions are not taken prior to final design. Poor receiver flying expects the first KDC-10 aircraft to be in service by January 1995, the qualities in the refueling positions can reduce engagement success second to follow approximately three months later. Based on this, the rate, increase the amount of training required, increase mishaps, modification of the first aircraft is scheduled to start on 1 July 1994 and increase refueling cycle time and seriously degrade mission effective- the second in December 1994. Development of the modification ness of the tanker. There are, of course, many other considerations program has already begun. USAF has been requested to assist regarding tanker/receiver compatibility such as airspeed/altitude com- RNLAF in program management, contracting, and purchasing of patibility, fuel system compatibility, communications, night lighting, etc. certain parts. Author But this paper primarily addresses receiver flying qualities and the importance of refueling position behind the tanker as it pertains to flying qualities. Specific programs discussed are Navy trials with the Air Force KC-10 and KC-135 tankers and Navy programs to bring a wing pod N94-36347* Aerospace Engineering Test Establishment, Cold Lake tanker capability to the P-3 airplane. Additionally, efforts underway to (Alberta). Right Dynamics. enhance tanker mission effectiveness of the KC-130 with a variable CC-130H(T) TACTICAL AERIAL REFUELLING TANKER geometry drogue are discussed and their ramifications explored. DEVELOPMENT FLIGHT TEST PROGRAMME Author ANDREW REIF and MARC TREMBLAY In AGARD, Recent Advances in Long Range and Long Endurance Operation of Aircraft N94-36344* McDonnell-Douglas Aerospace, Long Beach, CA. Trans- 16 p Nov. 1993 port Aircraft. Copyright Avail: CASI HC A03/MF A03 TANKER SYSTEM AND TECHNOLOGY REQUIREMENTS This paper describes the development flight test program for the DEFINITION: A TANKER TECHNOLOGY ROAD MAP CC-130H(T) Tactical Aerial Refuelling Tanker. The Canadian opera- JOHN KORIAGIN and BERTON B. RUND In AGARD, Recent tional requirement is first described, followed by a detailed discussion Advances in Long Range and Long Endurance Operation of Aircraft of the test item, receiver aircraft, and the ground/flight test method and

575 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

preliminary results. The development is significant since it represents N94-36618# Dornier-Werke G.m.b.H., Friedrichshafen (Germany). the first certification of the Right Refuelling Limited Mk 32B refuelling LANDING OF AN UNMANNED HELICOPTER ON A MOVING pods on a Hercules aircraft. Further flight testing to be conducted in the PLATFORM. HIGH ACCURACY NAVIGATION AND TRACKING near future are also mentioned. Author HANS-PETER ENGELBERT and JOHANNES SCHROEDER In AGARD, Pointing and Tracking Systems 9p May 1994 Copyright Avail: CASI HC A02/MF A02 Drones are of great importance for reconnaissance and surveillance in military applications. In regard to maritime drones Domier N94-36380*# National Aeronautics and Space Administration. Ames demonstrated the automatic landing of a drone on a moving ship motion Research Center, Moffett Reid, CA. simulator in December 1991. The landing accuracy is determined by the THE REDUCTION OF TAKEOFF GROUND ROLL BY THE tracking process. The tracking is performed by a laser tracker, which APPLICATION OF A NOSE GEAR JUMP STRUT measures the drone position relative to the ship. Not only the drone but JOSEPH C. EPPEL, MARTIN D. MAISEL, J. GREER MCCLAIN, and also the ship is equipped with an INS (Inertial Navigation System). The W. LUCE May 1994 16 p landing computations are performed in earth-fixed coordinates, whereby (Contract RTOP 505-59-36) the earth-fixed positions are delivered by the INS. The determination of (NASA-TM-108822; A-94082; NAS1.15:108822) Avail: CASIHC A03/ the drone position results from a combination of measurement values MFA01 from the airborne INS and data from the ship laser tracker. The A series of flight tests were conducted to evaluate the reduction combination of the different information in the drone is performed in a of takeoff ground roll distance obtainable from a rapid extension of the Kalman-filter. The concept was verified in an experimental program. nose gear strut The NASA Quiet Short-haul Research Aircraft (QSRA) During the experimental program 13 flights were performed. The used for this investigation is a transport-size short take off and landing tracking accuracy was approximately 0.2 m. Author (STOL) research vehicle with a slightly swept wing that employs the upper surface blowing (USB) concept to attain the high lift levels required lor its low-speed, short-field performance. Minor modifications to the conventional nose gear assembly and the addition of a high- pressure pneumatic system and a control system provided the extend- N94-36644** National Aeronautics and Space Administration. Hugh able nose gear, or jump strut, capability. The limited flight test program L. Dryden Right Research Facility, Edwards, CA. explored the effects of thrust-to-weight ratio, wing loading, storage tank CORRELATION OF ANALYTICAL AND EXPERIMENTAL HOT initial pressure, and control valve open time duration on the ground roll STRUCTURE VIBRATION RESULTS distance. The data show that a reduction of takeoff ground roll on the MICHAEL W. KEHOE and VIVIAN C. DEATON Aug. 1993 21 p order of 10 percent was achieved with the use of the jump strut, as Presented at the SEM Structural Testing Technology at High Tem- predicted. Takeoff performance with the jump strut was also found to be peratures 2 Conference, Ojai, CA, 8-10 Nov. 1993 essentially independent of the pneumatic supply pressure and was only (Contract RTOP 505-63-50) slightly affected by control valve open time within the range of the (NASA-TM-104269; H-1943; NAS 1.15:104269) Avail: CASI HC A03/ parameters examined. Author (revised) MFA01 High surface temperatures and temperature gradients can affect the vibratory characteristics and stability of aircraft structures. Aircraft designers are relying more on finite-element model analysis methods to ensure sufficient vehicle structural dynamic stability throughout the N94-36465 Air Univ., Maxwell AFB, AL Airpower Research Inst desired flight envelope. Analysis codes that predict these thermal AIRCRAFT BATTLE DAMAGE REPAIR FOR THE 1990'S AND effects must be correlated and verified with experimental data. Experi- BEYOND mental modal data for aluminum, titanium, and fiberglass plates heated DARRELL H. HOLCOMB 20 Jul. 1994 55 p Limited at uniform, nonuniform, and transient heating conditions are presented. Reproducibility: More than 20% of this document may be affected by The data show the effect of heat on each plate's modal characteristics, microfiche quality a comparison of predicted and measured plate vibration frequencies, (AO-A278635; AU-ARI-93-4) Avail: Issuing Activity (Defense Techni- the measured modal damping, and the effect of modeling material cal Information Center (DTIC)) property changes and thermal stresses on the accuracy of the analyti- Combat aircraft that are damaged and sitting on the ground are cal results at nonuniform and transient heating conditions. Author completely useless to air component commanders. The goal of the United States Air Force's Aircraft Battle Damage Repair (ABDR) Program is to rapidly restore these damaged aircraft to some level of combat capability. To be effective, the repairs must allow the aircraft to return to combat in time to affect the outcome of the battle. Effective N94-36767*# National Aeronautics and Space Administration. battle damage repair capability can truly be a force multiplier. This Langley Research Center, Hampton, VA. research project suggests methods to improve the Air Force's ability to FORWARD SWEEP, LOW NOISE ROTOR BLADE Patent provide this critical service to operational field commanders. Recent Application changes to the way the Air Force accomplishes its mission necessitate THOMAS F. BROOKS, inventor (to NASA) 2 May 1994 8 p improvements to the ABDR Program. New technology, defense (NASA-CASE-LAR-14569-1; NAS 1.71 :LAR-14569-1; US-PATENT- downsizing, and the introduction of composite wings all affect the Air APPL-SN-238044) Avail: CASI HC A02/MF A01 Force and consequently its aircraft battle damage repair philosophy. A A forward-swept, low-noise rotor blade includes an inboard sec- comprehensive review of the current ABDR Program with emphasis on tion, an aft-swept section, and a forward-swept outboard section. The areas of improvement is therefore in order. This study begins with a rotor blade reduces the noise of rotorcraft, including both standard review of the ABDR Program and is followed by a brief historical helicopters and advanced systems such as tiltrotors. The primary noise background of batte damage repair, an outline of the current USAF reduction feature is the forward sweep of the planform over a large program status, and a description of basic repair techniques and portion of the outer blade radius. The rotor blade also includes an aft- philosophies. Next is a comparison of different approaches to ABDR by swept section. The purpose of the aft-swept region is to provide a partial other military services. The study then identifies both technical and balance to pitching moments produced by the outboard forward-swept programmatic challenges which the program must address to remain portion of the blade. The noise source showing maximum noise viable. The final chapter contains conclusions, recommendations for reduction is blade-vortex interaction (BVl) noise. Also reduced are improvements, and highlights of areas requiring further research. thickness, noise, high speed impulsive noise, cabin vibration, and DTIC loading noise. NASA

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06 M. BADGER Pratt & Whitney Canada, Inc. Montreal, Que, Canada, A. JULIEN, A. D. LEBLANC, S. H. MOUSTAPHA, A. PRABHU, and A. AIRCRAFT INSTRUMENTATION A. SMAILYS Journal of Engineering for Gas Turbines and Power, Transactions of the ASME (ISSN 0742-4795) vol. 116, no. 2 April Includes cockpit and cabin display devices; and flight instruments. 1994 p. 322-330 refs (BTN-94-EIX94311331064) Copyright A94-61644* National Aeronautics and Space Administration. The PT6 engine entered service in the mid-1960s. Since then, Langley Research Center, Hampton. VA. application of new technology has enabled low-cost development of TAKEOFF PERFORMANCE MONITORING SYSTEM DISPLAY engines approaching 1500 kW, the introduction of electronic controls, OPTIONS improved power-to-weight ratio, higher cycle temperature, and reduced DAVID B. MIDDLETON NASA. Langley Research Center, specific fuel consumption. At the same time, PT6 field experience in Hampton, VA, LEE H. PERSON, JR., and RAGHAVACHARI business, commuter, helicopter, and trainer applications has resulted SRIVATSAN Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 in engines with low Direct Operating Cost and a reputation for rugged May-June 1994 p. 666-671 refs design and a high standard of engine reliability. This paper will highlight (BTN-94-EIX94401358988) Copyright some interesting examples of this technical evolution, including the ; This article summarizes the development of head-up and head- development of electronic controls and the application of the latest down cockpit displays for an airplane takeoff performance monitoring three-dimensional aerodynamic and stress analysis to both compres- system (TOPMS). Basic TOPMS displays provide pilots with real-time sor and turbine components. Author (El) graphic Information concerning their airplane's current and projected runway performance. The displays also indicate the status of associated airplane systems (e.g., flaps, engines) and, optionally, they provide 'GO/NO-GO' advice and a continually updated prediction of where the airplane can be braked to a stop. The displays have been A94-61115 developed and evaluated on the NASA Transport System Research COMMENTS ON THE DEVELOPMENT OF THE EARLY Vehicle (TSRV) B-737 simulator by more than 40 government, airline, WESTINGHOUSE TURBOJETS, 1941-1946 and industry pilots who rated the displays favorably and judged them S. WAY Journal of Engineering for Gas Turbines and Power, easy to monitor. The TOPMS has also been flight tested successfully Transactions of the ASME (ISSN 0742-4795) vol. 116, no. 2 April on the TSRV B-737. Based on these evaluations and on discussions 1994 p. 315-321 refs with the commercial aircraft community, the displays have evolved to (BTN-94-EIX94311331063) Copyright a baseline final configuration containing basic performance and sys- The early thinking leading to the American Turbojet engine is tem-status data to which GO/NO-GO advisory and predicted stop point reviewed. This included ideas pertaining to ramjets and rockets, and information can be added as options. Author (El) culminated in the axial flow turbojet engine concept. The role of the NACA Subcommittee on Jet Propulsion under the leadership of Dr. W. N94-37401** General Electric Co., Cincinnati, OH. Aircraft Engines F. Durand is stressed. Early problems with the new engine are FIBER OPTIC (FLIGHT QUALITY) SENSORS FOR ADVANCED mentioned, including flame tube light-off, interconnecting tubes, and AIRCRAFT PROPULSION Final Report, Jan. 1990 - Jun. 1994 fuel injection problems. An early major design innovation was the GARYL. POPPEL Jul. 1994 90 p change to a single annular combustion chamber, replacing the 24 cans. (Contract NAS3-25805; RTOP 505-62-50) This change culminated in the 19XB engine. The purposes of this paper (NASA-CR-191195; NAS 1.26:191195; R94AEB175) Avail: CASIHC are to show the magnitude of the problems encountered, and to give A05/MF A01 credit to the many dedicated persons who made the American Axial Development of flight prototype, fiber-optic sensing system com- Flow Turbojet Engine a success. Author (El) ponents for measuring nine sensed parameters (three temperatures, two speeds, three positions, and one flame) on an F404-400 aircraft engine is described. Details of each sensor's design, functionality, and environmental testing, and the electro-optics architecture for sensor A94-61459 signal conditioning are presented. Eight different optical sensing tech- RESEARCH ON THE ENGINEERING APPLICATION OF THE niques were utilized. Design, assembly, and environmental testing of ANTI-SWIRL MEASURES IN ENGINE/INLET COMPATIBILITY an engine-mounted, electro-optics chassis unit (EOU), providing MIL- GUOCAI YANG 61st Research Inst., China Aerospace Corp., C-1553 data output, are related. Interconnection cables and connectors Chengdu (China) Tuijin Jishu/Joumal of Propulsion Technology between the EOU and the sensors are identified. Results of sensor/ (ISSN 1001-4055) no. 2 April 1994 p. 17-24 In CHINESE cable/circuitry integrated testing, and installation and ground testing of refs the sensor system on an engine in October 1993 and April 1994 are (BTN-94-EIX94381353571) Copyright given, including comparisons with the engine control system's electrical Based on the mechanism of inlet swirl, the measures were studied sensors. Lessons learned about the design, fabrication, testing, and to prevent and restrain the inlet swirl of present aircraft in an all-round integration of the sensor system components are included. Author way from the inlet design point of view. It is expected that this thinking will benefit the solution of the problems in engine/inlet compatibility arising from swirl. El 07 AIRCRAFT PROPULSION AND POWER A94-61460 Includes prime propulsion systems and systems components, e.g., gas EXPERIMENTAL INVESTIGATION ON SELECTING THE RAMP turbine engines and compressors; and on-board auxiliary power plants AND LIP PARAMETERS OF A TWO-DIMENSIONAL EXTERNAL for aircraft COMPRESSION INLET XUEUANG ZHANG Chengdu Aircraft Industrial Corp., Chengdu (China) Tuijin Jishu/Joumal of Propulsion Technology (ISSN 1001 - A94-61114 4055) no. 2 April 1994 p. 12-16,57 In CHINESE refs PT6 ENGINE: 30 YEARS OF GAS TURBINE TECHNOLOGY (BTN-94-EIX94381353570) Copyright EVOLUTION A l/ll-scale model of a two-dimensional external compression

577 07 AIRCRAFT PROPULSION AND POWER

supersonic inlet with M(sub max) = 1.8 was tested from M = 0.8 to 1.8. 1994 p. 730-736 refs The ramp of the inlet is side-mounted vertically, and its duct is (BTN-94-EIX94401358996) Copyright bifurcated. The effects of the ramp angles, internal lip angles and circle The effect of compressibility on unsteady blade pressures is lip radius on the internal performances of the inlet were presented. The studied by solving the three-dimensional Euler equations. The opera- experimental results showed that a small change in ramp angle caused tion of the eight-bladed SR7L propfan at 4.75-deg angle of attack was a large changes in inlet total pressure recovery, in circumferential considered. Euler solutions were obtained for three Mach numbers, 0.6, steady-pressure distortion, and in buzz margin; whereas a small 0.7, and 0.8, and the predicted blade pressure waveforms were change in the internal lip angle and lip radius effects the change of inlet compared with flight data. The predictions show that the change in performances not as significantly as expected at subsonic speed, but pressure waveforms are minimal when the Mach number is increased does effect it significantly at supersonic speed. El from 0.6 to 0.7, as observed in the flight experiments. Increasing the Mach number from 0.7 to 0.8 produces significant changes in predicted pressure levels. The predicted amplitudes, however, differ from mea- A94-61636* National Aeronautics and Space Administration. surements at some transducer locations. Also, the predicted appear- Langley Research Center, Hampton, VA. ance of a shock in the highly loaded portion of the blade revolution is not INVISCID PARAMETRIC ANALYSIS OFTHREE-DIMENSIONAL indicated by the measurements. At all three Mach numbers the INLET PERFORMANCE measured (installed propfan) pressure waveforms at the majority of SCOTT D. HOLLAND NASA. Langley Research Center, transducer locations show a relative phase lag compared to the Hampton, VA and JOHN N. PERKINS Journal of Aircraft (ISSN computed (propfan alone) waveforms. This appears to be due to 0021-8669) vol. 31, no. 3 May-June 1994 p. 610-615 refs installation effects. Measured waveforms in the blade tip region show (BTN-94-EIX94401358980) Copyright nonlinear variations which are not captured by the present numerical The advantages and design requirements of propulsion/airframe procedure. Author (El) integration for the high Mach number flight of air-breathing vehicles have led to extensive study of the three-dimensional sidewall-compres- N94-36333* Naval Air Warfare Center, Warminster. PA. Aircraft Oiv. sion scramjet inlet in recent years. Inlets of this genre afford a relatively PROPULSION SYSTEM SELECTION FOR A HIGH ALTITUDE simple, generic geometry while producing a highly complex, three- LONG ENDURANCE AIRCRAFT dimensional flowfield dominated by shock/shock and shock/boundary- JOHN D. CYRUS and JOSEPH FRANZ In AGARD, Recent layer interactions. While the importance of the viscous effects in Advances in Long Range and Long Endurance Operation of high-speed inlet interactions is recognized, the present work addresses Aircraft 7p Nov. 1993 in a parametric fashion the inviscid effects of leading-edge sweep Copyright Avail: CASI HC A02/MF A03 (between 0-70 deg) and inflow Mach number (between 2-12) on the inlet This paper addresses the major propulsion system options for performance. Two-dimensional oblique shock theory is appropriately High Altitude Long Endurance aircraft internal combustion engines, modified to account for the three-dimensional effects of leading-edge turbine engines and fuel cells. The paper identifies the technology sweep and is applied throughout the inlet configuration to obtain inviscid drivers for the vehicle and assesses trie secondary equipment require- shock impingement locations, mass capture, inlet compression, total ments for the various system options. Critical technologies and devel- pressure recovery, and kinetic energy efficiency. Comparison of these opment requirements are addressed in terms of mission capability for results with CFD indicates that the parametric trends are identified by both near-term and advanced systems. This AGARDograph was this computationally quick and inexpensive method for preliminary sponsored by the Right Mechanics Panel. Author design applications. Author (El) N94-36334# Rolls-Royce Ltd., Bristol (England). PROPULSION SYSTEM TECHNOLOGIES FOR LONG RANGE AND LONG ENDURANCE AIRCRAFT A94-61650 K. R. GARWOOD In AGARD, Recent Advances in Long Range WHIRL-FLUTTER SUPPRESSION IN ADVANCED and Long Endurance Operation of Aircraft 7 p Nov. 1993 TURBOPROPS AND PROPFANS BY ACTIVE CONTROL Copyright Avail: CASI HC A02/MF A03 TECHNIQUES The NATO requirement for increased range and endurance of F. NITZSCHE DLR - Inst. of Aeroelasticity, Gottingen (Germany) aircraft is also associated with the necessity to reduce the initial and life Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 May-June cycle costs of these aircraft. Consideration of these conflicting require- 1994 p. 713-719 refs ments leads to the prioritization of engine technologies for different (BTN-94-EIX94401358994) Copyright vehicle types and presented here are views of engine manufacturers The feasibility of using the active control technique to suppress the addressing these challenges over the range of aircraft. This paper will whirl-flutter instability of advanced turboprops is investigated. Aerody- discuss the prioritization of technologies required for the range of air namic vanes are incorporated at the engine nacelle to generate control vehicles and examine how increases in endurance and range affect the airloads. The actuator system is driven by a control law that is based on balance of technology within each propulsion unit type. It is convenient the Kalman filter estimation of the critical aeroelastic modes of the to group the vehicles in the following way: transport, tanker, AWACS; structure. The results demonstrate that the compensator provides maritime patrol; combat; and special purpose. Each grouping has the enough controllability to prevent the whirl-flutter onset well beyond the challenges of range or duration subject to Us class, although clearly in design speed. The present study suggests that a very efficient vibration absolute terms the range of transport vehicles is significantly different isolation in advanced turboprops may be achieved both by optimizing from that of a combat aircraft It is primarily these differences in the the engine-propeller suspension in the actual flying envelope and groupings that give rise to the differences in technology prioritization. by employing the active control technique to deal with the safe Derived from text margins required by the present aircraft certification regulations. Author (El) N94-36335* Industrieanlagen-Betriebsgesellscriaftm.b.H., Ottobrunn (Germany). THE STRATO 2C PROPULSION SYSTEM: A LOW COST A94-61652 APPROACH FOR A HIGH ALTITUDE LONG ENDURANCE UNSTEADY BLADE PRESSURES ON A PROPFAN: AIRCRAFT PREDICTED AND MEASURED COMPRESSIBILITY H. TOENSKOETTER In AGARD, Recent Advances in Long EFFECTS Range and Long Endurance Operation of Aircraft 6 p Nov. 1993 M. NALLASAMY Sverdrup Technology, Inc., Brook Park, OH Copyright Avail: CASI HC A02/MF A03 Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 May-June For the STRATO 2C - a High Altitude Long Endurance Research

578 AIRCRAFT STABILITY AND CONTROL 08

Aircraft - a low cost propulsion system was designed and is now under Blacksburg, VA Journal of Guidance, Control, and Dynamics (ISSN development. The approach to achieve the aim of low development 0731-5090) vol. 17, no. 2 March-April1994 p. 330-336 refs procurement and in-service costs is a compound propulsion system (BTN-94-EIX94381311172) Copyright based on a highly supercharged liquid cooled piston engine with charge This paper presents a method for the solution of the constrained air inter-cooling and the extensive usage of available components. The control allocation problem for the case of three moments. The control concept of the propulsion system and the main components are allocation problem is to find the 'besf combination of several flight described. Aspects of controlling the three-stage turbocharger system control effectors for the generation of specified body-axis moments. are discussed. The way to realize the power plant in three years is The number of controls is greater than the number of moments being presented and the test program is addressed. Author controlled, and the ranges of the controls are constrained to certain limits. The controls are assumed to be individually linear in their effect N94-37448*# National Aeronautics and Space Administration. Lewis throughout their ranges of motion and complete in the sense that they Research Center, Cleveland, OH. generated moments in arbitrary combinations. The best combination of PREDICTION OF FILM COOLING ON GAS TURBINE AIRFOILS controls is taken to be an apportioning of the controls that yields the VIJAY K. GARG and RAYMOND E. GAUGLER Jul. 1994 31 p greatest total moment in a specified ratio of moments without exceeding Presented at the 39th International Gas Turbine and Aeroengine any control constraint The method of solving the allocation problem is Congress and Exposition, The Hague, Netherlands, 13-16 Jun. presented as an algorithm and is demonstrated for a problem of seven 1994; sponsored by ASME aerodynamic controls on an F-18 airplane. Author (El) (Contract RTOP 505-62-52) (NASA-TM-106653; E-8965; NAS1.15:106653) Avail: CASIHC A03/ MFA01 A94-61261 A three-dimensional Navier-Stokes analysis tool has been devel- REDUCED-ORDER H(INF) COMPENSATOR DESIGN FOR AN oped in order to study the effect of film cooling on the flow and heat AIRCRAFT CONTROL PROBLEM transfer characteristics of actual turbine airfoils. An existing code ROBERT C. OSBORNE Massachusetts Univ., Amherst, MA, (Amone et a)., 1991) has been modified for the purpose. The code is an RICHARD J. ADAMS, CHIN S. HSU. and SIVA S. BANDA Journal explicit, multigrid, cell-centered, finite volume code with an algebraic of Guidance, Control, and Dynamics (ISSN 0731-5090) vol. 17, turbulence model. Eigenvalue scaled artificial dissipation and variable- no. 2 March-April 1994 p. 341-345 refs coefficient implicit residual smoothing are used with a full-multJgrid (BTN-94-EIX94381311174) Copyright technique. Moreover, Mayle's transition criterion (Mayle, 1991) is used. A recently introduced method for designing H-infinity compensa- The effects of film cooling have been incorporated into the code in the tors based on minimal-order observers is considered for an aircraft form of appropriate boundary conditions at the hole locations on the control problem. The purpose of this paper is to bridge the gap between airfoil surface. Each hole exit is represented by several control volumes, theory and application by presenting a practical utilization of a new thus providing an ability to study the effect of hole shape on the film- design approach. Manual flight control systems for the lateral axis of a cooling characteristics. Comparison is fair with near mid-span experi- fighter aircraft are developed using both full-order and reduced-order mental data for four and nine rows of cooling holes, five on the shower compensators, and the results are compared. It is demonstrated that head, and two rows each on the pressure and suction surfaces. The this method can be used to directly design reduced-order compensa- computations, however, show a strong spanwise variation of the heat tors that result in a system satisfying a closed-loop H-infinity bound. transfer coefficient on the airfoil surface, specially with shower-head Author (El) cooling. Author

A94-61617 08 CHINE-SHAPED FOREBODY EFFECTS ON DIRECTIONAL AIRCRAFT STABILITY AND CONTROL STABILITY AT HIGH-ALPHA R. RAVI Virginia Polytechnic Inst. and State Univ., Blacksburg, Includes aircraft handling qualities; piloting; flight controls; and VA and WILLIAM H. MASON Journal of Aircraft (ISSN 0021-8669) autopilots. vol. 31, no. 3 May-June 1994 p. 480-487 refs (BTN-94-EIX94401358961) Copyright A94-61254 Computational fluid dynamics has been used to study the flowfields OPTIMUM FLIGHT TRAJECTORY GUIDANCE BASED ON over chine-shaped forebodies at low-speed high angle-of-attack condi- TOTAL ENERGY CONTROL OF AIRCRAFT tions with sideslip. The purpose is to define forebody geometries that SHU-FAN WU Nanjing Univ. of Aeronautics and Astronautics, provide good directional stability characteristics under these condi- Nanjing (China) and SUO-FENG QUO Journal of Guidance, tions. An analytically defined generic forebody model is described, and Control, and Dynamics (ISSN 0731-5090) vol. 17, no. 2 March- a parametric study of various forebody shapes was then conducted to April 1994 p. 291-296 refs determine which shapes promote a positive contribution to directional (BTN-94-EIX94381311167) Copyright stability at high angle of attack. An unconventional way of presenting the The guidance technique for optimal vertical flight trajectory with a results is used to illustrate how the positive contribution arises. The total energy control system (TECS) is discussed. The flight profile is effect of cross-sectional shape on directional stability was found to be optimized based on the point-mass energy state approximation model very significant Broad chine-shaped cross sections were found to of aircraft with direct operating cost as its index function. The guidance promote directional stability. Also, directional stability is improved if the law is developed with the total energy control concept used in TECS. chine is placed closer to the top of the cross section. Planform shapes To improve the guidance precision, several methods are adopted in the also played an important role in determining the forebody directional optimizations and tracking process, and two preprocessing algorithms, stability characteristics. Based on the results of this initial parametric the lead-compensation algorithm and the smooth filtering algorithm, are study, some guidelines for aerodynamic design to promote positive developed for the ideal optimal trajectory. Satisfactory digital simulation directional stability are presented. Author (El) results for a Boeing-707 transport model are finally obtained. Author (El) A94-61618 A94-61259 COMPUTATIONAL STUDY OF THE F-5A FOREBODY CONSTRAINED CONTROL ALLOCATION: THREE-MOMENT EMPHASIZING DIRECTIONAL STABILITY PROBLEM WILLIAM H. MASON Virginia Polytechnic Inst. and State Univ., WAYNE C. DURHAM Virginia Polytechnic Inst. and State Univ., Blacksburg, VA and R. RAVI Journal of Aircraft (ISSN 0021 -8669)

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vol. 31, no. 3 May-June 1994 p. 488-494 refs A94-61669 (BTN-94-EIX94401358962) Copyright EXPERIMENTAL DESIGN OF H(SUB INFINITY) WEIGHTING Computational fluid dynamics (CFD) has been used to study the FUNCTIONS FOR FLIGHT CONTROL SYSTEMS F-5A forebody flowfield at low-speed high angle-of-attack conditions CIANN-DONG YANG National Cheng Kung Univ., Tainan (Tai- combined with sideslip. The classic wind-tunnel experiment demon- wan), HANN-SHING JU, and SHIN-WHAR LIU Journal of Guid- strating the dominant contribution of the F-5A forebody to directional ance, Control, and Dynamics (ISSN 0731-5090) vol. 17, no. 3 stability at high angle of attack has been simulated computationally over May-June 1994 p. 544-552 refs an angle-of-attack range from 10 to 45 deg. The key wind-tunnel trend (BTN-94-EIX94401358163) Copyright for Cfsub n beta) was obtained computationally using the CFL3D code This paper introduces an experimental solution for H(sub infinity) to solve the Reynolds' equations employing the Baldwin-Lomax turbu- weighting function selection by exploiting an experimental planning lence model with the Degani-Schiff modification to account for massive method that has been used in quality control. Conducting matrix crossflow separation. The computations provide detailed and fascinat- experiments using special matrices, called orthogonal arrays, allows ing insights into the physics of flowfield. The results of the investigation the effects of several weighting parameters to be determined efficiently show that CFD has reached a level of development where computa- so that the resulting H(sub infinity) controller can satisfy many design tional methods can be used for high angle-of-attack aerodynamic specifications simultaneously in the environment for which the control- design. Author (El) ler is designed. To show the feasibility and efficiency of this methodology, a flight control system for an airplane is designed to satisfy 11 performance specifications simultaneously, when the airplane is undergoing a large shift in e.g. position. Author (El) • A94-61621 EVALUATION OF PARAMETER ESTIMATION METHODS FOR UNSTABLE AIRCRAFT A94-61672 R. V. JATEGAONKAR German Aerospace Research Establish- NONLINEAR MODEL-FOLLOWING CONTROL APPLICATION ment (DLR), Braunschweig (Germany) and F. THIELECKE Journal TO AIRPLANE CONTROL of Aircraft (ISSN 0021 -8669) vol. 31, no. 3 May-June 1994 WAYNE C. DURHAM Virginia Polytechnic Inst. and State Univ., p. 510-519 refs Blacksburg, VA, FREDERICK H. LUTZE. M. REMZI BARLAS, (BTN-94-EIX94401358965) Copyright and BRUCE C. MUNRO Journal of Guidance, Control, and While continuing to be of wide interest, the estimation of aerody- Dynamics (ISSN 0731-5090) vol. 17, no. 3 May-June 1994 namic derivatives from flight data of an unstable aircraft poses several p. 570-577 refs difficulties. The objective of this article is to provide an overview of some (BTN-94-EIX94401358166) Copyright of the more recently introduced estimation methods together with some Nonlinear model-following control design is applied to the problem of the conventional ones. Five options addressed here are 1) regression of control of the six degrees of freedom of an airplane that lacks direct startup, 2) equation decoupling, 3) filter error, 4) output error with control of lift and side force. The nonlinear expressions for the error artificial stabilization, and 5) multiple shooting method. An evaluation is dynamics of the model-following control are examined using Lyapunov made based on the parameter estimates both from simulated and flight stability analysis. The analysis results in nonlinear feedforward and data. The various methods yield comparable estimates from simulated feedback gains that are functions of the airplane and model states. As responses pertaining to the short period motion of an unstable aircraft a consequence, gain scheduling requirements for the implementation Their application to X-31A aircraft flight data in unstable flight regime of the model-following control are reduced to only those involving the brings out some practical aspects. It is found that the application of the estimation of stability and control derivatives of the airplane. The use of conventionally used output error method with artificial stabilization and these gains is shown through an example application to the control of of the multiple shooting method requires considerable engineering a nonlinear aerodynamic and engine model provided by NASA Ames- effort and can still pose difficulties when analyzing longer duration Dryden Right Research Facility. The model being followed is based on maneuvers. The estimates from the filter error and equation decoupling a trajectory generation algorithm, and represents a form of dynamic methods compare with each other well. It is demonstrated that they inversion. Author (El) provide an attractive and less laborious alternative to analyze longer duration maneuvers, e.g., consecutive elevator doublets or sweep inputs up to 30 s. Author (El) A94-61673 IMPLEMENTATION OF A FULL-ENVELOPE CONTROLLER A94-61658 FOR A HIGH-PERFORMANCE AIRCRAFT APPROXIMATE RECOVERY OF H-INFINITY LOOP SHAPES RICHARD J. ADAMS Wright Lab., Wright-Patterson AFB, OH, USING FIXED-ORDER DYNAMIC COMPENSATION JAMES M. BUFFINGTON, and SIVA S. BANDA Journal of EDWARD V. JR. BYRNS Systems Planning and Analysis, Inc., Guidance, Control, and Dynamics (ISSN 0731-5090) vol. 17, Falls Church, VA and ANTHONY J. CAUSE Journal of Guidance. no. 3 May-June 1994 p. 578-583 refs Control, and Dynamics (ISSN 0731 -5090) vol. 17, no. 3 May-June (BTN-94-EIX94401358167) Copyright 1994 p. 458-465 refs The design, implementation, and evaluation of a full-envelope (BTN-94-EIX94401358152) Copyright control system for the AIAA controls design challenge aircraft is This paper presents a method for designing fixed-order dynamic presented.The control problem is divided into separate longitudinal and compensator that approximates the H(sub infinity) full state feedback, lateral/directional designs. The longitudinal controller is a Mach number closed-loop transfer function properties from disturbance inputs to and flight path angle command system, and bank angle is commanded controlled outputs. The formulation uses an observer canonical form to through the lateral/directional autopilot A cross-axis filter minimizes represent the dynamic compensator which allows the design to be transient error during coupled maneuvers. Proportional plus integral treated as a modified constant gain feedback problem. The approxi- plus derivate structure is built into a linear quadratic synthesis problem mate is accomplished through a unique selection of the quadratic to generate state feedback gains. An implementable output feedback performance index weighting matrices. This design procedure is dem- solution is found through a linear transformation of the state feedback onstrated by two design examples. The first example is a simple fourth- gain matrix. The control system is gain scheduled with dynamic order model used to demonstrate the procedure. The second example pressure through polynomial curve fits of linear point design gains. isalongrtudnal flight

580 AIRCRAFT STABILITY AND CONTROL 08

N94-36329* Technische Univ., Munich (Germany). Inst. of Right to a separate program which performed the closed-loop, active control Mechanics and Right Control. calculations. An eigenvalue analysis was performed to determine the IMPROVEMENT OF ENDURANCE PERFORMANCE BY flutter stability of both open- and closed-loop systems. Sensor models, PERIODIC OPTIMAL CONTROL OF VARIABLE CAMBER based upon the feedback of pure state variables and based upon hub- G. SACHS and R. MEHLHORN In AGARD. Recent Advances mounted sensors, providing physically measurable accelerations, were in Long Range and Long Endurance Operation of Aircraft 7 p evaluated. It was shown that the onset of tilt-rotor whirl-flutter could be Nov. 1993 delayed from 240 to above 270 knots by feeding back vertical and span- Copyright Avail: CASI HC A02/MF A03 wise accelerations, measured at the rotor hub, to the longitudinal cyclic Other than in classical theory, endurance cruise is considered as pitch. Time response calculations at a 270-knot cruise condition an optimal periodic control problem where the state and control showed an active cyclic pitch control level of 0.009 deg, which equates variables change in a periodic manner. Variable camber is introduced to a very acceptable 9 pound active-control force applied at the as a further control in addition to angle of attack and thrust setting. By rotor hub. Author periodically varying camber in a coordinated process with the two other controls, it is possible to fully exploit its potential of improving the lift/drag N94-36733# Air Force Inst of Tech., Wright-Patterson AFB, OH. ratio for increasing the endurance of aircraft It is quantitatively shown School of Engineering. which gain in endurance performance can be achieved. Results are MIXED H2/H-INFINITY OPTIMIZATION WITH MULTIPLE H presented for an idealized engine model showing no control rate INFINITY CONSTRAINTS M.S. Thesis limitations as well as for a realistic model with constraints on control JULIO C. ULLAURI Jun. 1994 136 p rates imposed. The numerical values for the constraints are chosen (AD-A280572; AFIT/GAE/ENY/94J-04) Avail: CASI HC A07/MF A02 such that only slow thrust changes are admitted. Author A general mixed H2/H-infinity optimal control design with multiple H-infinity constraints is developed and applied to two systems, one SISO and the other MIMO. The SISO design model is normal accelera- N94-36384 Purdue Univ., West Lafayette, IN. School of Aeronautics tion command following for the F-16. This design constitutes the and Astronautics. validation for the numerical method, for which boundaries between the AEROSERVOELASTIC TAILORING WITH PIEZOELECTRIC H2 design and the H-infinity constraints are shown. The MIMO design MATERIALS: ACTUATOR OPTIMIZATION STUDIES Final consists of a longitudinal aircraft plant (short period and phugoid Report, 1 Oct. 1991 - 30 Sep. 1993 modes) with stable weights on the H2 and H-infinity transfer functions, TERRENCE A. WEISSHAAR and MARIO A. ROTEA 9 Feb. and is linear-time-invariant. The controller order is reduced to that of the 1994 48 p Limited Reproducibility: More than 20% of this plant augmented with the H2 weights only. The technique allows document may be affected by microfiche quality singular, proper (not necessarily strictly proper) H-infinity constraints. (Contract AF-AFOSR-0386-91) The analytical nature of the solution and a numerical approach for (AD-A278640; AERO-3; AFOSR-94-0263TR) Avail: Issuing Activity finding suboptimal controllers which are as dose as desired to optimal (Defense Technical Information Center (DTIC)) is developed. The numerical method is based on the Davidon-Retcher- This report summarizes aeroservoelastic tailoring studies in Powell algorithm and uses analytical derivatives and central differ- which adaptive material actuators are used to control structural deflec- ences for the first order necessary conditions. The method is applied to tion of aeroelastic systems. The problem is to furnish enough directed a MIMO aircraft longitudinal control design to simultaneously achieve control of a system to make the control of the phenomenon feasible. Nominal Performance at the output and Robust Stability at both the Specific research problems considered are: choice of the actuator input and output of the plant DTIC material for effective control; geometric arrangement for active control; and optimum coverage of surface panels for effective control. A specific method of controller design is suggested to determine, the limits of N94-36820*# National Aeronautics and Space Administration. control. It is applied to a typical section whose response to random Langley Research Center, Hampton, VA. atmospheric turbulence is to be controlled. A finite element method is GAIN WEIGHTED EIGENSPACE ASSIGNMENT developed to model actuator and sensor output for plate-like actuators JOHN B. DAVIDSON and DOMINICK ANDRISANI, II May 1994 and its use is illustrated for wing-like configurations to demonstrate the 32p benefits of orthotropic material actuators. Rnally, the problem of (Contract RTOP 505-64-30-01) optimum actuators to supply deflection of panels for wing surfaces is (NASA-TM-109130; NAS1.15:109130) Avail: CASI HC A03/MF A01 examined to determine optimally criteria for such panels and to use This report presents the development of the gain weighted strain energy as a guide for efficient use of actuator/host plate combi- eigenspace assignment methodology. This provides a designer with a nations. DTIC systematic methodology for trading off eigenvector placement versus gain magnitudes, while still maintaining desired closed-loop eigenvalue locations. This is accomplished by forming a cost function composed N94-36436*# Sterling Software, Inc., Moffett Reid, CA. of a scalar measure of error between desired and achievable eigenvec- ALLEVIATION OF WHIRL-FLUTTER ON A JOINED-WING tors and a scalar measure of gain magnitude, determining analytical TILT-ROTOR AIRCRAFT CONFIGURATION USING ACTIVE expressions for the gradients, and solving for the optimal solution by CONTROLS numerical iteration. For this development the scalar measure of gain JOHANNES M. VANAKEN 1991 27 p Presented at the magnitude is chosen to be a weighted sum of the squares of all the International Specialists' Meeting on Rotorcraft Basic Research individual elements of the feedback gain matrix. An example is pre- of the American Helicopter Society, Atlanta, GA, 25-27 Mar. 1991 sented to demonstrate the method. In this example, solutions yielding See also A92-14423 achievable eigenvectors dose to the desired eigenvectors are obtained (Contract NCC2-417) with significant reductions in gain magnitude compared to a solution (NASA-CR-196103; MAS 1.26:196103) Avail: CASI HC A03/MF A01 obtained using a previously developed eigenspace (eigenstructure) The feasibility of using active controls to delay the onset of whirl- assignment method. Author flutter on a jdned-wing tilt rotor aircraft was investigated. The CAMRAD/ JA code was used to obtain a set of linear differential equations which N94-36965** Washington Univ., Seattle, WA. Deptof Mechanical describe the motion of the joined-wing tilt-rotor aircraft. The hub motions Engineering. due to wing/body motion is a standard input to CAMRAD/JA and were MULTIRATE FLUTTER SUPPRESSION SYSTEM DESIGN FOR obtained from a structural dynamics model of a representative joined- THE BENCHMARK ACTIVE CONTROLS TECHNOLOGY WING wing tilt-rotor aircraft The CAMRAD/JA output consisting of the open- Final Report, 16 Jun. 1991 - 15 Jun. 1994 loop system matrices, and the airframe free vibration motion were input MARTIN C. BERG and GREGORY S. MASON 1994 79 p

581 08 AIRCRAFT STABILITY AND CONTROL

(Contract NCC1-156) USING EIGENSPACE ASSIGNMENT (NASA-CR-196112; NAS 1.26:196112) Avail: CASIHC A05/MF A01 ERIC N. JOHNSON (George Washington Univ., Washington, To study the effectiveness of various control system design DC.), JOHN B. DAVIDSON, and PATRICK C. MURPHY methodologies, the NASA Langley Research Center initiated the Jun. 1994 40 p Benchmark Active Controls Project In this project the various method- (Contract RTOP 505-64-52-01) ologies will be applied to design a flutter suppression system for the (NASA-TM-4548; L-17333; NAS 1.15:4548) Avail: CASI HC A03/MF Benchmark Active Controls Technology (BACT) Wing (also called the A01 PAPA wing). Eventually, the designs will be implemented in hardware When using eigenspace assignment to design an aircraft flight and tested on the BACT wing in a wind tunnel. This report describes a control system, one must first develop a model of the plant. Certain project at the University of Washington to design a multirate flutter questions arise when creating this model as to which dynamics of the suppression system for the BACT wing. The objective of the project was plant need to be included in the model and which dynamics can be left two fold. First, to develop a methodology for designing robust multirate out or approximated. The answers to these questions are important compensators, and second, to demonstrate the methodology by apply- because a poor choice can lead to dosed-loop dynamics that are ing it to the design of a multirate flutter suppression system for the BACT unpredicted by the design model. To alleviate this problem, a method wing. The contributions of this project are (1) development of an has been developed for predicting the effect of not including certain algorithm for synthesizing robust low order muftirate control laws (the dynamics in the design model on the final closed-loop eigenspace. This algorithm is capable of synthesizing a single compensator which development provides insight as to which characteristics of unmodeled stabilizes both the nominal plant and multiple plant perturbations; (2) dynamics will ultimately affect the closed-loop rigid-body dynamics. development of a multirate design methodology, and supporting soft- What results from this insight is a guide for eigenstructure control law ware, for modeling, analyzing and synthesizing multirate compensa- designers to aid them in determining which dynamics need or do not tors; and (3) design of a multirate flutter suppression system for NASA's need to be included and a new way to include these dynamics in the BACT wing which satisfies the specified design criteria This report flight control system design model to achieve a required accuracy in the describes each of these contributions in detail. Section 2.0 discusses dosed-loop rigid-body dynamics. The method is illustrated for a lateral- our design methodology. Section 3.0 details the results of our multirate directional flight control system design using eigenspace assignment flutter suppression system design for the BACT wing. Finally, Section for the NASA High Alpha Research Vehicle (HARV). Author 4.0 presents our conclusions and suggestions for future research. The body of the report focuses primarily on the results. The associated theoretical background appears in the three technical papers that are included as Attachments 1-3. Attachment 4 is a user's manual for the software that is key to our design methodology. Derived from text 09 RESEARCH AND SUPPORT FACILITIES (AIR) Includes airports, hangars and runways; aircraft repair and overhaul N94-37014*# National Aeronautics and Space Administration. facilities; wind tunnels; shock tube facilities; and engine test blocks. Langley Research Center, Hampton, VA. DESIGN AND EVALUATION OF A STOCHASTIC OPTIMAL FEED-FORWARD AND FEEDBACK TECHNOLOGY (SOFFT) FLIGHT CONTROL ARCHITECTURE N94-36437* Wichita State Univ., KS. Aerodynamic Labs. AARON J. OSTROFF and MELISSA S. PROFFITT Jun. 1994 THREE-DIMENSIONAL FORCE DATA ACQUISITION AND 20 p BOUNDARY CORRECTIONS FOR THE WALTER H. BEECH (Contract RTOP 505-64-30-01) MEMORIAL 7X10 FOOT LOW SPEED WIND TUNNEL (NASA-TP-3419; L-17273; NAS 1.60:3419) Avail: CASI HC A03/MF BONNIE L. JOHNSON, JAMES E. LEIGH, and KEVIN A. MOORE A01 Jun. 1993 47 p This paper describes the design and evaluation of a stochastic (AR93-2) Avail: CASI HC A03/MF A01 optimal feed-forward and feedback technology (SOFFT) control archi- The Walter H. Beech Memorial 7X10 Foot Low-Speed Wind tecture with emphasis on the feed-forward controller design. The Tunnel at The Wichita State University has gone through many recent SOFFT approach allows the designer to independently design the feed- upgrades. One significant major upgrade has been the streamlining of forward and feedback controllers to meet separate objectives and then the data acquisition and reduction system. This report covers the integrate the two controllers. The feed-forward controller has been upgrades to the software and supersedes previous reports on the data integrated with an existing high-angle-of-attack (high-alpha) feedback reduction routines for three-dimensional models tested in the wind controller. The feed-forward controller includes a variable command tunnel. A H P 9000/380 workstation processes the data by reduction and model with parameters selected to satisfy level 1 flying qualities with a correction equations in a HP BASIC/UX program. For the data to be high-alpha adjustment to achieve desired agility guidelines, a nonlinear corrected, model and test section correction constants are required. interpolation approach that scales entire matrices for approximation of These constants are used to correct the force and moment data for the plant model, and equations for.calculating feed-forward gains tunnel boundary and interference effects and to facilitate the reduction developed for perfect plant-model tracking. The SOFFT design was of the force and moment data into coefficient form. The data reduction applied to a nonlinear batch simulation model of an F/A-18 aircraft methods and equations needed to calculate the proper model con- modified for thrust vectoring. Simulation results show that agility stants are presented as well as examples illustrating the methods. guidelines are met and that the SOFFT controller fitters undesired pilot- These examples and the methods presented in this report are only tor induced frequencies more effectively during a tracking task than a flight three-dimensional models. Accuracy and rapid processing of data are controller that has the same feedback control law but does not have the of high importance in wind tunnel testing; accuracy and speed are SOFFT feed-forward control. Author achieved in this tunnel through the use of a HP 3852 Data Acquisition System. The final corrected data are presented to the customer in both graphical and tabulated forms in the reference axis or axes of their choice (body, wind, or stability). The on-line system is capable of providing immediate corrected tabulated data and plotted results N94-37059*# National Aeronautics and Space Administration. affording real time monitoring of the test objectives and thus providing Langley Research Center, Hampton, VA. the wind tunnel user with an invaluable management tool for the PREDICTING THE EFFECTS OF UNMODELED DYNAMICS customer's particular test requirements. Examples of the plotting ON AN AIRCRAFT FLIGHT CONTROL SYSTEM DESIGN capability are included. Author (revised)

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N94-36763* Federal Aviation Administration, Washington, DC. Office applications will be studied and demonstrated, including a rotary joint of Airport Planning and Programming. for solar panels. The first teams designed and manufactured pole shims ACCOMPLISHMENTS UNDER THE AIRPORT IMPROVEMENT to reduce the air-gaps and raise the vertical force capability as well as PROGRAM Annual Report No. 12, Fiscal Year 1993 on control system studies. The most recent team concentrated on the 1993 124 p operation of a single bearing station, which was successfully accom- (AD-A280661; DOT/FAA/PP-94-2) Avail: CASI HC A06/MF A02 plished with a PC-based digital controller. The paper will review the Annual report of the Airport Improvement Program (AIP) for the history and technical background of the ASPS hardware, followed by fiscal year ending September 30,1993, is the twelfth report of activity presentation of the progress made and the current status of the project under authority granted by the Airport and Airway Improvement Act of Author 1982, as amended. Section 521 of the Airport and Airway Improvement Act of 1982, as amended, requires that the Secretary of Transportation submit an annual report to Congress describing the accomplishments of the airport grant program. OTIC 10 ASTRONAUTICS

N94-37424* Systems Control Technology, Inc., Arlington, VA. Includes astronautics (general); astrodynamics; ground support sys- ANALYSIS OF VERTIPORT STUDIES FUNDED BY THE tems and facilities (space); launch vehicles and space vehicles; space AIRPORT IMPROVEMENT PROGRAM (AIP) Final Report transportation; spacecraft communications, command and tracking; DEBORAH J. PEISEN, WILLIAM T. SAMPSON, LINDA J. spacecraft design, testing and performance; spacecraft instrumenta- LABELLE, BRIAN M. SAWYER, J. RICHARD LUDDERS, tion; and spacecraft propulsion and power. STEPHEN V. BERARDO. RICHARD J. DYMENT, SAMUEL W. FERGUSON, ROBERT M. WINICK, and CLIFFORD R. BRAGDON May 1994 111 p (Contract DTFA01-93-C-00030) A94-61628* National Aeronautics and Space Administration. (SCT-93RR-21; DOT/FAA/RD-93/37) Avail: CASI HC A06/MF A02 Langley Research Center, Hampton, VA. It is expected that Advanced Vertical Flight (AVF) aircraft such as PRELIMINARY PILOTED SIMULATION STUDIES OF THE HL- the Civil TiltRotor (CTR) will become viable, important vehicles for the 20 LIFTING BODY relief of both ground and airport congestion. Furthermore, it is expected ROBERT A. RIVERS NASA. Langley Research Center, this will lead to expanded use of rotorcraft for scheduled passenger Hampton, VA, E. BRUCE JACKSON, and W. A. RAGSDALE service. To prepare for this eventuality, the FAA in 1988 funded a Journal of Aircraft (ISSN 0021 -8669) vol. 31, no. 3 May-June program of vertiport feasibility studies. Thirteen locations, encompass- 1994 p. 556-563 refs ing a range of cities, states, and regions, applied for and received funds. (BTN-94-EIX94401358972) Copyright Canada conducted its own study. The purpose of these studies was to NASA Langley Research Center is developing a lifting body facilitate the use of AVF aircraft by identifying areas in the United States vehicle, designated the HL-20, as one option of the proposed Personnel where the potential for missions using these aircraft is greatest so that Launch System for NASA's future manned access to space require- infrastructure requirements could be identified and implemented in a ments. Data derived from wind-tunnel and computational fluid dynam- timely manner. This report evaluates the fourteen studies to portray an ics analyses of the conceptual design led to the derivation of a flight overview of the status of potential scheduled passenger service and simulator model to investigate the potential flight characteristics of the required vertiport development within the United States, Puerto Rico, HL-20. A simulation investigation was initiated to determine if satisfac- and Canada. The report also evaluates the methodologies and as- tory unpowered horizontal landings could be accomplished. Control law sumptions used in these studies to reach conclusions regarding the design and trajectory development were directed toward this end. The feasibility of AVF aircraft service in these areas. Most studies con- study uncovered several deficiencies subsequently corrected through cluded that the primary mission would be short-haul passenger service design changes, and it validated the predicted subsonic aerodynamic between city centers and major urban areas. Some studies, particularly properties. Expanding the investigation to the Mach 4 to Mach 1 regime in the lesser developed areas (Puerto Rico and Alaska), concluded that revealed flight characteristics necessitating the development of innova- small package delivery and cargo missions were also feasible. Final tive control techniques. This article will present the significant results conclusions and recommendations include suggestions for planning uncovered to date by flight simulator evaluations of a lifting body class guidelines specifically for vertiports/large heliports developed primarily of vehicle, and will demonstrate the effectiveness of flight simulation as for passenger operations. Author an integrated part of the conceptual design phase. Author (El)

N94-37450** Old Dominion Univ., Norfolk, VA. Dept of Aerospace A94-61679 Engineering. ANALYTIC SOLUTION OF THE RICCATI EQUATION FOR THE LARGE ANGLE MAGNETIC SUSPENSION TEST FIXTURE HOMING MISSILE LINEAR-QUADRATIC CONTROL PROBLEM Progress Report, period ending 30 Apr. 1994 NEDELJKO LOVEREN Sarajevo Univ. (Yugoslovia) and MILOS COLIN P. BRITCHER Jul. 1994 21 p TOMIC Journal of Guidance, Control, and Dynamics (ISSN (Contract NAG1-1056) 0731-5090) vol. 17, no. 3 May-June 1994 p. 619-621 refs (NASA-CR-196138; NAS 1.26:196138) Avail: CASI HC A03/MF A01 (BTN-94-EIX94401358173) Copyright Over the past few decades, research has proven the feasibility of This Note has presented the analytic derivation of the optimal the concept of noncontacting magnetic bearing systems which operate closed-loop guidance law for a finite-bandwidth homing missile inter- with no wear or vibration. As a result, magnetic bearing systems are cepting a maneuvering target and has provided a simple analytic means beginning to emerge as integral parts of modem industrial and aero- of solving the matrix Riccati differential equation. The resulting optimal space systems. Further applications research is still required. NASA guidance law agrees with the result obtained by Cottrel and Asher. The has loaned an existing magnetic bearing device, the Annular Suspen- major contribution of this Note lies in the analytic solution of the matrix sion and Pointing System (ASPS), to ODU to permit student design Riccati differential equation. Author (El) teams the opportunity to pursue some of these studies. The ASPS is a protoype for a higrnaccuracy space payload pointing and vibration isolation system. The project objectives are to carry out modifications N94-37000# Joint Publications Research Service, Arlington, VA. and improvements to the ASPS hardware to permit recommissioning in JPRS REPORT: CENTRAL EURASIA. AVIATION AND a 1-g (ground-based) environment. Following recommissioning, new COSMONAUTICS, NO. 5, MAY 1993

583 11 CHEMISTRY AND MATERIALS

15 Mar. 1994 22 p Transl. into ENGLISH from various Russian application like the regenerator seal: fabricate it with an alloy which articles forms a lubricating oxide. The objective of this study was to explore this (JPRS-UAC-94-004) Avail: CASI HC A03/MF A01 concept for the regenerator seal. A study was conducted to develop Translated articles cover the following topics: mathematical mod- low-friction, wear-resistant surfaces on high-temperature alloys for the eling assists investigations of flight accidents; and SLBM conversion for temperature range 26 to 900 C. The approach investigated consisted civilian launches continues. Author of modifying the naturally occurring oxide film in order to improve its tribological properties. Improvement was needed at low temperatures where the oxide film, previously formed at high temperature, spalls due to stresses induced by sliding. Experiments with titanium, tungsten, and 11 tantalum additions showed a beneficial effect when added to nickel and CHEMISTRY AND MATERIALS nickel alloys. Low friction was maintained down to 100 C from 900 C. For unalloyed nickel friction and surface damage increased at 400 to 500 C. Other approaches proved less successful and require further Includes chemistry and materials (general); composite materials; inor- study. DOE ganic and physical chemistry; metallic materials; nonmetallic materials; and propellants and fuels. N94-36413*# Aluminum Co. of America, Alcoa Center, PA. Alloy Technology Div. A94-61113 NEW DEVELOPMENTS IN ALUMINUM FOR AIRCRAFT AND MATERIALS PERFORMANCE IN ADVANCED COMBUSTION AUTOMOBILES SYSTEMS JOCELYN I. PETIT In NASA. Langley Research Center, National K, NATESAN Argonne Natl. Lab., Argonne, IL Journal of Educators' Workshop: Update 1993. Standard Experiments in Engi- Engineering for Gas Turbines and Power, Transactions of the neering Materials Science and Technology p 419-450 Apr. 1994 AS/WE (ISSN 0742-4795) vol. 116, no. 2 April 1994 p. 331- Avail: CASI HC A03/MF A04 337 refs A common bond for the aircraft and automobile industry is the (BTN-94-EIX94311331065) Copyright need for cost-efficient, lightweight structures such as provided by A number of advanced technologies are being developed to aluminum based materials. The topics are presented in viewgraph form convert coal into clean fuels for use as feedstock in chemical plants and and cover the following: new developments in aluminum for aircraft and for power generation. From the standpoint of component materials, the automobiles; forces shaping future automotive materials needs; alumi- environments created by coal conversion and combustion in these num strength/weakness versus competitive materials; evolution of technologies and their interactions with materials are of interest The aluminum aerospace alloys; forces shaping future aircraft materials trend in the new or advanced systems is to improve thermal efficiency needs; fiber/metal structural laminates; and property requirements for and reduce the environmental impact of the process effluents. This jetliner and military transport applications. CASI paper discusses several systems that are under development and identifies requirements for materials application in those systems. N94-36474# Allied-Signal Aerospace Co., Kansas City, MO. Available data on the performance of materials in several of the REPLACEMENT OF SILICONE POLYMER A WITH SILICONE environments are used to examine the performance envelopes for POLYMER B AND THE SUBSEQUENT CHARACTERIZATION materials for several of the systems and to identify needs for additional OF THE NEW CELLULAR SILICONE MATERIALS work in different areas. Author (El) J. W. SCHNEIDER Apr. 1994 58 p (Contract DE-AC04-76DP-00613) (DE94-010105; KCP-613-5266) Avail: CASI HC A04/MF A01 A94-61473 The purpose of this project is to replace silicone polymer A with COATING THE BORON PARTICLES TO INCREASE THE silicone polymer B produced by Vendor B. Silicone polymer B and the COMBUSTION EFFICIENCY OF BORON FUEL resulting B-50 cellular silicone have been used to produce cushions for CHENFANG LI Xi'an Modem Chemistry Research Inst., Xi'an the W87 program. Approximately 5.5 years of stress relaxation aging (China) Tuijin Jishu/Joumal of Propulsion Technology (ISSN study data as well as actual part surveillance data have been collected, 1001-4055) no. 2 April 1994 p. 53-57 In CHINESE refs characterizing the stockpile life performance of the B-50 cellular (BTN-94-EIX94381353577) Copyright silicone cushion material. Process characterization of new cellular To coat the boron particles is an effective way to increase silicone materials as a result of replacing silicone polymer A with combustion efficiency of boron fuel. The latest two processes to coat silicone polymer B has been completed. Load deflection requirements the boron fuel with titanium and boron carbide were introduced, and the for the new cellular silicone materials based on silicone polymer B have study on the effect of boron with different coatings on the combustion been met The silicone polymer B based cellular silicone materials must property of ramjet rocket propellent was also described. El be compounded at densities of approximately 0.03 g/cu cm less than the silicone polymer A based cellular silicone materials in order to N94-36306 Argonne National Lab., IL achieve the same load deflection requirements has also been demon- WEAR-RESISTING OXIDE FILMS FOR 900 C strated. The change in silicone polymers from A to B involved a M. B. PETERSON (Wear Sciences, Inc., Arnold, MD.), S. Z. LI decrease in volatile content as well as a decrease in part shrinkage. (Institute of Metal Research, Shenyang, China.), and S. F. DOE MURRAY (Rensselaer Polytechnic Inst., Troy, NY.) Mar. 1994 56 p Limited Reproducibility: More than 20% of this document N94-36505 Sandia National Labs., Albuquerque, NM. may be affected by microfiche quality ADVANCED THERMALLY STABLE, COAL-DERIVED, JET (Contract W-31-109-ENG-38) FUELS DEVELOPMENT PROGRAM. EXPERIMENT SYSTEM (DE94-010093; ANL/OTM/CR-5) Avail: CASI HC A04 AND MODEL DEVELOPMENT Annual Report, Oct 1992 - Sep. For the past 50 years, temperatures in advanced heat engines 1993 have been increasing. New-generation engines will require lubricants E. A. KLAVETTER, S. J. MARTIN, W. TROTT, and T. J. OHERN for 1000 C and higher. One of the most critical applications is the Dec. 1993 50 p Limited Reproducibility: More than 20% of regenerator seals on the automotive gas turbine. In this seal, a metal this document may be affected by microfiche quality plate slides against a porous ceramic surface for several thousand (Contract DE-AC04-94AL-85000; DA PROJ. 3048) hours at speeds on the order of 10 cm/sec. For long-term usage above (AD-A278968; WL-TR-94-2003) Avail: Issuing Activity (Defense 900 C it will probably be necessary to use oxide lubricants. If effective Technical Information Center (DTIC)) ones can be found, then a simple solution would be available for an A program entitled Thermally Stable Jet Fuels Development" was

584 CHEMISTRY AND MATERIALS 11 initiated in FY89 by the U.S. Air Force, Aero Propulsion and Power developed for structures that must withstand high temperatures, pos- Directorate, working jointly with the Department of Energy, Pittsburgh sess high stiffness and be lighter. Scale-up of the TMC material system Energy Technology Center. Thermal stability of aviation fuels is of from the laboratory environment to large structural components has concern because of the potential operation problems arising from fuel required significant advancements in design, manufacturing and as- degradation under thermal stress conditions. Sandia National Labora- sembly technology. Numerous large scale, TMC components have tories has been conducting efforts to develop instrumentation for been developed, fabricated and tested to verify the feasibility of monitoring characteristics of jet fuel degradation and solids deposition structural/material concepts for hypersonic vehicles. These articles and develop models of those mechanisms from the data acquired using include thick laminate TMC wing structure, minimum gage TMC that instrumentation. This report describes the instrumentation devel- fuselage sections, and integrated TMC fuselage/cryogenic tank struc- opment,dataaoquisition,andmodelparameterdetermination. DTIC ture. A summary of the development and testing of these articles is presented. Author (revised)

N94-36649# Advisory Group for Aerospace Research and Develop- N94-36652* Textron Specialty Materials, Lowell, MA. ment, Neuilly-Sur-Seine (France). Structures and Materials Panel. SCS-6 (TM) FIBER REINFORCED TITANIUM CHARACTERISATION OF FIBRE REINFORCED TITANIUM JIM HENSHAW In AGARD, Characterisation of Fibre Reinforced MATRIX COMPOSITES [LA CARACTERISATION DES Titanium Matrix Composites 6p Feb. 1994 MATERIAUX COMPOSITES A MATRICE DE TITANE Copyright Avail: CASl HC A02/MF A03 RENFORCES PAR FIBRES] The low weight structurally efficient SCS-6 Fiber Reinforced Feb. 1994 260 p In ENGLISH and FRENCH The 77th Titanium, as produced by Textron Specialty Materials, is a material Meeting was held in Bordeaux, France, 27-28 Sep. 1993 Original awaiting the development of production applications. A multitude of contains color illustrations airframe and engine parts have been produced for test and develop- (AD-A2775206; AGARD-R-796; ISBN-92-835-0735-5) Copyright mental purposes and a production facility has been established to Avail: CASl HC A12/MF A03 fabricate preforms, intermediary products, and component shapes. The combination of stiffness, strength, and high temperature Author resistance provided by fiber reinforced titanium matrix composites offers major benefits for aircraft engine and airframe applications, N94-36655S British Petroleum Co. Ltd., Sunbury-on-Thames where these materials could be used to reduce weight or improve (England). Research and Engineering Centre. performance. This workshop on the subject of characterization of MANUFACTURE AND PROPERTIES OF SIGMA FIBRE titanium composites was intended to provide a forum for the exchange REINFORCED TITANIUM of information in this important area. Characterization in this case refers J. G. ROBERTSON In AGARD, Characterisation of Rbre to the understanding of the behavior of the composites as it relates to Reinforced Titanium Matrix Composites 8p Feb. 1994 the ability to predict their performance in real-life applications. It covers Copyright Avail: CASl HC A02/MF A03 various topics that include mechanical test techniques, NDE methods, Titanium Matrix Composites have long been known to offer pot life prediction models, and other factors that will affect the level of ential for use in aeroengine components. The cost of producing the fiber confidence with which these relatively new materials will be accepted and fabricating components has delayed large scale developments for application. because of concern over long term component costs. The slow development pace has, in turn, kept the fiber and composite price high N94-3665QJ Wright Lab., Wright-Patterson AFB, OH. Materials through low demand. Composite manufacturing routes using foil and Directorate. filament wound fiber has been used for many years. The difficulties of POSSIBILITIES AND PITFALLS IN AEROSPACE maintaining a suitable fiber distribution during hot isostatic pressing and APPLICATIONS OF TITANIUM MATRIX COMPOSITES the availability of cheap foil have effectively put this technique on the JAMES M. LARSEN, STEPHAN M. RUSS, and J. WAYNE JONES shelf. However excellent fiber distributions have been achieved even in In AGARD, Characterisation of Fibre Reinforced Titanium Matrix difficult geometries by a BP proprietary process. Mechanical properties Composites 21 p Feb. 1994 Sponsored by Systran Corp. comparable with the most expensive routes can be achieved with this, (Contract AFPROJ. 2302) one of the cheapest manufacturing routes. Author Copyright Avail: CASl HC A03/MF A03 High-temperature, light-weight materials represent enabling tech- N94-37323* British Columbia Univ., Vancouver. Dept of Metals and nology in the continued evolution of high-performance aerospace Materials Engineering. vehicles and propulsion systems being pursued by the U.S. Air Force. ALTERNATE MELTING AND REFINING ROUTES In this regard, titanium matrix composites (TMC's) appear to offer ALEC MITCHELL In AGARD, Impact of Materials Defects on unique advantages in terms of a variety of weight-specific properties at Engine Structures Integrity 8p Apr. 1993 high temperatures. However, a key requirement for eventual structural Copyright Avail: CASl HC A02/MF A02 use of these materials is a balance of mechanical properties that can Although most research and development effort in turbine alloys be suitably exploited by aircraft and engine designers without compro- has been in the past directed towards the understanding and improve- mising reliability. An overview of the current capability of titanium matrix ment of basic properties, it is a telling comment on the results that at composites is presented, with an effort to assess the balance of present we can only manufacture the components with a reliability properties offered by this class of materials. Emphasis is given to life- which, in the example case of a high pressure turbine disk, leads to a limiting cyclic and monotonic properties and the roles of high-tempera- service life of less than one-fifth of the theoretical life of the alloy ture, time-dependent deformation and environmental effects. An attempt component The purpose of this presentation is to examine the reasons is made to assess the limitations of currently available titanium matrix for this situation and to indicate ways in which we can improve on it. We composites with respect to application needs and to suggest avenues conclude that the techniques of melting, refining and casting which are for improvements in key properties. Author now being developed have the potential to make a large change in the in-service life of turbine components without any significant change in the state of alloy development Author N94-36651* McDonnell-Douglas Corp., Saint Louis, MO. APPLICATIONS OF TITANIUM MATRIX COMPOSITE TO N94-37324* Wright Lab, Wright-Patterson AFB, OH. Materials LARGE AIRFRAME STRUCTURE Dirctorate. TIMOTHY M. WILSON In AGARD, Characterisation of Fibre PROCESS ENHANCEMENTS OF SUPERALLOY MATERIAL Reinforced Titanium Matrix Composites 31 p Feb. 1994 RONALD H. WILLIAMS, KRISTINE A. LARK, SHARON Copyright Avail: CASl HC A03/MF A03 VUKELICH, DONALD R. PARILLE, and RICHARD W. SALKELD Advanced Titanium Matrix Composite (TMC) materials are being In AGARD, Impact of Materials Defects on Engine Structures

585 11 CHEMISTRY AND MATERIALS

Integrity 6 p Apr. 1993 Integrity 16 p Apr. 1993 Copyright Avail: CASI HC A02/MF A02 Copyright Avail: CASI HC A03/MF A02 Due to the ever-increasing demand for improvements in engine By specific reference to the powder metallurgy alloy API the paper performance and better fuel efficiency, complex high pressure turbine examines the role of defects in generating local residual stress fields. (HPT) blade designs have been introduced into military engines. The effects of defect size and location on crack initiation and low cycle Greater emphasis has, therefore, been placed on increasing the fatigue life are discussed. It is shown that at stress levels consistent with structural integrity and life of engine components. Materials defects those experienced by current engine components, defects can act must be of a small enough size and sparse enough in population to under cyclic loading as crack nucleators from cycle 1. Methods of enable the design of high thrust-to-weight ratio engines. This require- calculating appropriate stress intensity factors are briefly reviewed and ment has demanded the industry attainment of cleaner materials. In it is shown that at existing turbine disc operating temperatures, a linear order to meet this requirement possible process improvements were elastic fracture mechanics stress intensity factor can be used to evaluated. Enhancements were incorporated into the melting and calculate crack growth rates. Finally, the major lifting methods used for casting processes to reduce the size and number of dross defects aeroengine discs are briefly reviewed, and attention is drawn to the within high pressure turbine blades. The accomplishment of this goal specific problems created by the presence of macrostructural defects. was through the efforts of a joint United States Air Force, Pratt & Author Whitney Task Force Team. Process implementation has been successful in reducing the remaining deleterious defects present in directionally solidified single crystal and pel/crystalline nickel-base superalloy turbine blade materials. In conjunction with the introduction 12 of melting and casting process improvements, the refinement of nondestructive inspection techniques was investigated. Author ENGINEERING

Includes engineering (general); communications; electronics and elec- N94-37325# Imphy S.A., Imphy (France). trical engineering; fluid mechanics and heat transfer; instrumentation THE CONTROL OF CLEANNESS IN POWDER METALLURGY and photography; lasers and masers; mechanical engineering; quality MATERIALS FOR TURBINE DISKS assurance and reliability; and structural mechanics. G. RAISSON In AGARD, Impact of Materials Defects on Engine Structures Integrity 14 p Apr. 1993 Copyright Avail: CASI HC A03/MF A02 A94-61050 The origins of exogenous inclusions in powder metallurgy prod- WINDOW FUNCTIONS FOR THE CALCULATION OF THE TIME ucts are described and methodologies for assuring the quality of these DOMAIN AVERAGES OF THE VIBRATION OFTHE INDIVIDUAL alloys are reviewed. Elutriation, chemical dissolution, micrography, PLANET GEARS AND SUN GEAR IN AN EPICYCLIC GEARBOX electron beam button melting, ultrasonic inspection, and other tech- P. D. MCFADDEN Oxford Univ., Oxford (England) Journal of niques are described and compared. CASI Vibration and Acoustics. Transactions o f the ASME (ISSN 1048- 9002) vol. 116, no. 2 April 1994 p. 179-187 refs (BTN-94-E1X94311331047) Copyright N94-37326* Forge Societe Nationals d'Etude et de Construction de An existing technique which enables the estimation of the time Moteurs d'Aviation, Gennevilliers (France). domain averages of the tooth meshing vibration of the individual planet MAINTAINING CONSTANT STANDARDS DURING THE and sun gears in an epicydic gearbox from measured vibration signals FORGING PROCESS [MAITRISE DE LA has been revised. A key feature of the existing technique is the sampling REPRODUCTIBILITE DU PROCEDE DE FORGEAGE] of the vibration signal within a rectangular window in the time domain F. CHEVET and M. CARALP In AGARD, Impact of Materials when one of the planet gears is dose to the vibration transducer. The Defects on Engine Structures Integrity 23 p Apr. 1993 revised technique permits the use of other window functions, and a In FRENCH detailed analysis shows that the errors in the estimate of the time Copyright Avail: CASI HC A03/MF A02 domain average can be expressed in terms of the window function. The properties of aircraft engine discs made of a titanium and Several suitable window functions which enable a reduction in the level nickel alloy may be notably improved if deformations and temperatures of the errors are demonstrated by numerical examples and by the are monitored during the forging process. On engines of recent analysis of data from a test on a helicopter gearbox with deliberate fabrication, this optimization through thermomechanical treatment is damage to one of the planet gears. Author (El) also systematically applied. As an answer to this need SNECMA is using a monitoring system in its metal processing plant monitoring devices positioned on the heat deformation machinery record and A94-61057 statistically document the important parameters. This new monitoring MAINSTREAM INGRESS SUPPRESSION IN GAS TURBINE system, taking place at the time of fabrication, makes it possible to DISK CAVITIES immediately detect any variance in the fabrication and to rapidly correct V. I. KHILNANI Auburn Univ., Auburn, AL, L. C. TSAI, S. H. any possible abnormality. Thus checking and ensuring total duplication BHAVNANI, J. M. KHODADADI, J. S. GOODLING, and J. of the fabrication becomes systematic and the quality control checks on WAGGOTT Journal of Turbomachinery, Transactions of the the finished project (strongly linked to the conditions of transformation) AS/WE (ISSN 0889-504X) vol. 116, no. 2 April 1994 p. 339- have improved. Finally, because of the knowledge that was thus gained 346 refs on the forging process, our command of the thermomechanical treat- (BTN-94-EIX94311330101) Copyright ments was improved. Variations in parameters which were not re- The sealing characteristics of an air-cooled gas turbine disk cavity corded in the past and had an important influence on the microstructure have been studied using laser sheet flow visualization. Experiments of the parts were observed. Trans), by FLS were performed on a simplified half-scale model of an actual gas turbine disk cavity. This type of rotor-stator geometry with a double-toothed-rim (DTR) seal at the outer periphery and a labyrinth seal at the inner N94-373280 Defence Research Agency, Famborough, Hampshire periphery of the cavity has been tested for its ability in preventing (England). ingress of hot mainstream gases. The results show good agreement DEFECTS AND THEIR EFFECTS ON THE INTEGRITY OF with previously estimated design data. Experiments were conducted for NICKEL BASED AEROENGINE DISCS various labyrinth seal flow rates and rotational Reynolds numbers up to G. F. HARRISON, P. H. TRANTER, and L. GRABOWSKI 1.52 x 10(exp 6). The effects of rotor eccentricity on minimum purge In AGARD, Impact of Materials Defects on Engine Structures flows have also been discussed. Author (El)

586 ENGINEERING 12

A94-61058 self-induced flow and heat transfer in a rotating tube, together with STUDY OF ROTOR CAVITIES AND HEAT TRANSFER IN A additional theoretical work on heat transfer to the cylindrical wall of the COOLING PROCESS IN A GAS TURBINE tube. Earlier work has shown that self-induced flow can occur when a R. S. AMANO Wisconsin Univ.. Milwaukee, Wl, K. D. WANG, tube, with one end open and the other sealed, is rotated about its axis: and V. PAVELIC Journal of Turbomachinery, Transactions of the Ruid flows along the axis toward the sealed end and returns in an 4SME(ISSN0889-504X) vol. 116, no. 2 April 1994 p. 333- annular layer on the cylindrical wall. The flow and heat transfer on the 338 refs end wall are similar to those associated with the so-called free disk, and (BTN-94-EIX94311330100) Copyright measured velocity distributions in the tube and Nusselt numbers for the A high-temperature flow through a gas turbine produces a high end wall are in good agreement with those computed from numerical rate of turbulent heat transfer between the fluid flow field and the turbine solutions of the Navier-Stokes and energy equations. The Reynolds components. The heat transfer process through rotor disks causes analogy is used in this paper to provide a correlation for the computed thermal stress due to the thermal gradient just as the centrifugal force Nusselt numbers for the cylindrical wall, and design correlations are causes mechanical stresses; thus, an accurate analysis for the evalu- provided to enable the results to be applied to anti-icing systems for the ation of thermal behavior is needed. This paper presents a numerical nose bullets of aero-engines. Author (El) study of thermal flow analysis in a two-stage turbine in order to understand better the detailed flow and heat transfer mechanisms through the cavity and the rotating rotor-disks. The numerical compu- A94-61061 tations were performed to predict thermal fields throughout the rotating SIMULATION OF THE SECONDARY AIR SYSTEM OF AERO disks. The method used in this paper is the segregation method, which ENGINES requires a much smaller number of grids than actually employed in the K. J. KUTZ Muenchen G.m.b.H., Munich (Germany) and T. M. computations. The results are presented for temperature distributions SPEER Journal of Turbomachinery, Transactions of the ASME through the disk and the velocity fields, which illustrate the interaction (ISSN 0889-504X) vol. 116, no. 2 April 1994 p. 306-315 refs between the cooling air flow and gas flow created by the disk rotation. (BTN-94-EIX94311330097) Copyright The temperature distribution in the disks shows a reasonable trend. The This paper describes a computer program for the simulation of numerical method developed in this study shows that it can be easily secondary air systems. Typical flow system elements are presented, adapted for similar computations for air cooling flow patterns through such as restrictors, tappings, seals, vortices, and coverplates. Two- any rotating blade disks in a gas turbine. Author (El) phase flow as occurring in bearing chamber vent systems is briefly discussed. An algorithm is described for the solution of the resulting nonlinear equations. The validity of the simulation over the engine A94-61059 operation envelope is demonstrated by a comparison with test results. INGESTION INTO THE UPSTREAM WHEELSPACE OF AN Author (El) AXIAL TURBINE STAGE T. GREEN Univ of Sussex, Sussex, United Kingdom and A. B. TURNER Journal of Turbomachinery, Transactions of the ASME A94-61062 (ISSN 0889-504X) vol. 116. no. 2 April 1994 p. 327-332 refs DETAILED FLOW MEASUREMENTS AND PREDICTIONS FOR (BTN-94-EIX94311330099) Copyright A THREE-STAGE TRANSONIC FAN The upstream wheelspace of an axial air turbine stage complete W. J. CALVERT Defence Research Agency, Farnborough with nozzle guide vanes (NGVs) and rotor blades (430 mm mean (England) and A. W. STAPLETON Journal of Turbomachinery, diameter) has been tested with the objective of examining the combined Transactions of the ASME (ISSN 0889-504X) vol. 116, no. 2 effect of NGVs and rotor blades on the level of mainstream ingestion for April 1994 p. 298-305 refs different seal flow rates. A simple axial clearance seal was used with the (BTN-94-EIX94311330096) Copyright rotor spun up to 6650 rpm by drawing air through it from atmospheric Detailed flow measurements were taken at DRA Pyestock on a pressure with a large centrifugal compressor. The effect of rotational Rolls-Royce three-stage transonic research fan using advanced laser speed was examined for several constant mainstream flow rates by transit velocimetry and holography techniques to supplement the fixed controlling the rotor speed with an air brake. The circumferential pressure and temperature instrumentation. The results have been variation in hub static pressure was measured at the trailing edge of the compared with predictions using the DRA S1-S2 quasi-three-dimen- NGVs upstream of the seal gap and was found to affect ingestion sional flow calculation system at a range of speeds. The agreement was significantly. The hub static pressure distribution on the rotor blade generally encouraging, both for the overall performance and for details leading edges was rotor speed dependent and could not be measured of the internal flow such as positions of shock waves. Taken together in the experiments. The Denton three-dimensional CFD computer code with the computational efficiency of the calculations and previous was used to predict the smoothed time-dependent pressure field for the experience on single-stage transonic fans and core compressors, this rotor together with the pressure distribution downstream of the NGVs. establishes the S1-S2 system as a viable design tool for future The level and distribution of mainstream ingestion, and thus, the seal multistage transonic fans. Author (El) effectiveness, was determined from nitrous oxide gas concentration measurements and related to static pressure measurements made throughout the wheelspace. With the axial clearance rim seal close to A94-61063 the rotor the presence of the blades had a complex effect Rotor blades ADVANCED TRANSONIC FAN DESIGN PROCEDURE BASED in connection with NGVs were found to reduce mainstream ingestion ON A NAVIER-STOKES METHOD seal flow rates significantly, but a small level of ingestion existed even C. M. RHIE United Technologies Corp., East Hartford, CT, R. M. tor very high levels of seal flow rate. Author (El) ZACHARIAS, D. E. HOBBS, K. P. SARATHY, B. P. BIEDERMAN, C. R. LEJAMBRE, and D. A. SPEAR Journal of Turbomachinery, Transactions of the ASME (ISSN 0889-504X) vol. 116, no. 2 A94-61060 April 1994 p. 291-297 refs TRANSFER OF HEAT BY SELF-INDUCED FLOW IN A (BTN-94-EIX94311330095) Copyright ROTATING TUBE A fan performance analysis method based upon three-dimen- S. GILHAM Atkins (W. S.) Consultants Ltd., Surrey (United sional steady Navier-Stokes equations is presented in this paper. Its Kingdom), P. C. IVEY, and J. M. OWEN Journal of Turbomachinery, accuracy is established through extensive code validation effort Vali- Transactions of the ASME (ISSN 0889-504X) vol. 116, no. 2 dation data comparisons ranging from a two-dimensional compressor April 1994 p. 316-326 refs cascade to three-dimensional fans are shown in this paper to highlight (BTN-94-EIX94311330098) Copyright the accuracy and reliability of the code. The overall fan design proce- This paper provides a review of recently published research on dure using this code is then presented. Typical results of this design

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process are shown for a current engine fan design. This new design no. 2 April 1994 p. 411-417 refs method introduces a major improvement over the conventional design (BTN-94-EIX94311331077) Copyright methods based on inviscid flow and boundary layer concepts. Using the The LV100 gas turbine engine is being developed for U.S. Army Navier-Stokes design method, fan designers can confidently refine ground vehicle use. A unique approach for controls and accessories is their designs prior to rig testing. This results in reduced rig testing and being used whereby the engine has no accessory gearbox. Instead a cost savings as the bulk of the iteration between design and experimen- high-speed starter/generator is mounted directly on the compressor tal verification is transferred to an iteration between design and compu- shaft and powers all engine accessories as well as supplies the basic tational verification. Author (El) electrical power needs of the vehicle. This paper discusses the evolution of the electrically driven LV100 accessory system starting with the A94-61098 Advanced Integrated Propulsion System (AIPS) demonstrator pro- INCREASED USE OF GAS TURBINES AS COMMERCIAL gram, through the current system to future possibilities with electric MARINE ENGINES vehicle propulsion. Issues in electrical vehicle propulsion are discussed C. O. BRADY General Electric Co., Evendale, OH and D. L. LUCK including machine type, electrical power type, and operation with a gas Journal of Engineering for Gas Turbines and Power, Transactions of turbine. Author (El) theASME (ISSN 0742-4795) vol. 116, no. 2 April 1994 p. 428- 433 refs A94-61102 (BTN-94-EIX94311331080) Copyright SELECTION CRITERIA FOR PLAIN AND SEGMENTED FINNED Over the last three decades, aeroderivative gas turbines have TUBES FOR HEAT RECOVERY SYSTEMS become established naval ship propulsion engines, but use in the D.R.REID FINTUBECorp.,Tulsa,OKandJ.TABOREK Journal commercial marine field has been more limited. Today, aeroderivative of Engineering for Gas Turbines and Power, Transactions of the gas turbines are being increasingly utilized as commercial marine ASME (ISSN 0742-4795) vol. 116, no. 2 April 1994 p. 406-410 engines. The primary reason for the increased use of gas turbines is refs discussed and several recent GE aeroderivative gas turbine commer- (BTN-94-EIX94311331076) Copyright cial marine applications are described with particular aspects of the gas Heat recovery heat exchangers with gas as one of the streams turbine engine installations detailed. Finally, the potential for future depend on the use of finned tubes to compensate for the inherently low commercial marine aeroderivative gas turbine applications is pre- gas heat transfer coefficient Standard frequency welded 'plain' fins sented. Author (El) were generally used in the past, until the high-frequency resistance welding technology permitted a cost-effective manufacture of 'seg- A94-61099 mented' fins. The main advantage of this fin design is that it permits MASHPROEKT SCIENTIFIC AND PRODUCTION higher heat flux and hence smaller, lighter weight units for most ASSOCIATION: A DESIGNER OF GAS TURBINES FOR operating conditions. While the criteria that dictate optimum design, MARINE AND INDUSTRIAL APPLICATIONS such as compactness, weight, and cost per unit area favor the V. I. ROMANOV SPA Mashproekt, Nikolayev (Ukraine) Journal segmented fin design, a few other considerations such as fouling, ease of Engineering for Gas Turbines and Power, Transactions of the of cleaning, and availability of dependable design methods have to be ASME (ISSN 0742-4795) vol. 116, no. 2 April 1994 p. 424-427 considered. This paper analyzes the performance parameters that (BTN-94-EIX94311331079) Copyright affect the selection of either fin type. Author (El) The paper describes the history of the development of gas turbine engines by the Mashproekt scientific and production association for A94-61104 marine and industrial applications. El INFLUENCE OF HIGH ROTATIONAL SPEEDS ON HEAT TRANSFER AND OIL FILM THICKNESS IN AERO-ENGINE A94-61100 BEARING CHAMBERS INVESTIGATION OF THE PART-LOAD PERFORMANCE OF S. WITTIG Universitaet Karlsruhe (T.H.), Karlsruhe, Germany, TWO 1.12 MW REGENERATIVE MARINE GAS TURBINES A. GLAHN, and J. HIMMELSBACH Journal of Engineering for T. KORAKIANITIS Washington Univ., St. Louis, MO and K. J. Gas Turbines and Power, Transactions of the ASME (ISSN 0742- BEIER Journal of Engineering for Gas Turbines and Power, 4795) vol. 116, no. 2 April 1994 p. 395-401 refs Transactions of the ASME (ISSN 0742-4795) vol. 116, no. 2 (BTN-94-EIX94311331074) Copyright April 1994 p. 418-423 refs Increasing the thermal loading of bearing chambers in modem (BTN-94-EIX94311331078) Copyright aero-engines requires advanced techniques for the determination of Regenerative and intercooled-regenerative gas turbine engines heat transfer characteristics. In the present study, film thickness and with low pressure ratio have significant efficiency advantages over heat transfer measurements have been carried out for the complex two- traditional aero-derivative engines of higher pressure ratios, and can phase oil/air flow in bearing chambers. In order to ensure real engine compete with modem diesel engines for marine propulsion. Their conditions, a new test facility has been built up, designed for rotational performance is extremely sensitive to thermodynamic-cycle parameter speeds up to n = 16,000 rpm and maximum flow temperatures of T(sub choices and the type of components. The performances of two 1.12 MW max) = 473 K. Sealing air and lubrication oil flow can be varied nearly (1500 hp) regenerative gas turbines are predicted with computer in the whole range of aero-engine applications. Special interest is simulations. One engine has a single-shaft configuration, and the other directed toward the development of an ultrasonic oil film thickness has a gas-generator/power-turbine combination. The latter arrange- measuring technique, which can be used without any reaction on the ment is essential for wide off-design operating regime. The perfor- flow inside the chamber. The determination of local heat transfer at the manceof each engined/ivingfixed-pitchandcontrollable-pitch propellers, bearing chamber housing is based on a well-known temperature or an AC electric bus (for electric-motor-driven propellers) is investi- gradient method using surface temperature measurements and a finite gated. For commercial applications the controllable-pitch propeller may element code to determine temperature distributions within the bearing have efficiency advantages (depending on engine type and shaft chamber housing. The influence of high rotational speed on the local arrangements). For military applications the electric drive provides heat transfer and the oil film thickness is discussed. Author(EI) better operational flexibility. Author (El) A94-61105 A94-61101 NEW HIGH-EFFICIENCY HEAVY-DUTY COMBUSTION ELECTRIC DRIVES ON THE LV100 GAS TURBINE ENGINE TURBINE 701F W. D. JONES General Electric Aircraft Engines, Lynn, MA and I. FUKUE Mitsubishi Heavy Industries, Ltd., Takasago, Japan, A. R. FLETCHER, JR. Journal of Engineering for Gas Turbines S. AOKI, K. AOYAMA, S. UMEMURA, A. MEROLA, M. NOCETO, and Power, Transactions of the ASME (ISSN 0742-4795) vol. 116, and M. ROSSO Journal of Engineering for Gas Turbines and

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Power, Transactions of the ASME (ISSN 0742-4795) vol. 116. are clearly an improvement over the previous generation of gas path no. 2 April 1994 p. 389-394 refs analysis programs, they still fail in many situations. This paper de- (BTN-94-EIX94311331073) Copyright scribes some of the failures and explores their relationship to the The 701F is a high-temperature 50 Hz industrial grade 220 MW underlying analysis technique. It also describes difficulties in imple- size engine based on a scaling of the 501F 150 MW class 60 Hz menting a gas path analysis program. The paper concludes with an machine, and incorporates a higher compressor pressure ratio to appraisal of weighted-least-squares-based gas path analysis. increase the thermal efficiency. The prototype engine is under a two- Author (El) year performance and reliability verification testing program at MHI's Yokohama Plant and was initially fired in June of 1992. This paper A94-61109 describes the 701F design features design changes made from 501 F. PERFORMANCE AND ECONOMIC ENHANCEMENT OF The associated performance and reliability verification test program are COGENERATION GAS TURBINES THROUGH also presented. Author (El) COMPRESSOR INLET AIR COOLING M. DELUCIA Universita di Firenze, Firenze, Italy, R. BRONCONI, A94-61106 and E. CARNEVALE Journal of Engineering for Gas Turbines and MODELS FOR PREDICTING THE PERFORMANCE OF Power, Transactions of the ASME (ISSN 0742-4795) vol. 116, BRAYTON-CYCLE ENGINES no. 2 April 1994 p. 360-365 refs T. KORAKIANITIS Washington Univ., St. Louis, MO and D. G. (BTN-94-EIX94311331069) Copyright WILSON Journal of Engineering for Gas Turbines and Power. Gas turbine air cooling systems serve to raise performance to Transactions of the ASME (ISSN 0742-4795) vol. 116, no. 2 peak power levels during the hot months when high atmospheric April 1994 p. 381-388 refs temperatures cause reductions in net power output. This work de- (BTN-94-EIX94311331072) Copyright scribes the technical and economic advantages of providing a com- Gas turbine performance is the result of choices of type of cycle, pressor inlet air cooling system to increase the gas turbine's power cycle temperature ratio, pressure ratio, cooling flows, and component rating and reduce its heat rate. The pros and cons of state-of-the-art losses. The output is usually given as efficiency (thermal, propulsive, cooling technologies, i.e., absorption and compression refrigeration, specific thrust, overall efficiency) versus specific power. This paper with and without thermal energy storage, were examined in order to presents a set of computer programs for the performance prediction of select the most suitable cooling solution. Heavy-duty gas turbine shaft-powerand jet-propulsion cycles: simple, regenerative, intercooled- cogeneration systems with and without absorption units were modeled, regenerative, turbojet, and turbofan. Each cycle is constructed using as well as various industrial sectors, i.e., paper and pulp, Pharmaceu- individual component modules. Realistic assumptions are specified for ticals, food processing, textiles, tanning, and building materials. The component efficiencies as functions of pressure ratio, cooling mass- ambient temperature variations were modeled so the effects of climate flow rate as a function of cooling technology levels, and various other could be accounted for in the simulation. The results validated the cycle losses. The programs can be used to predict design point and off- advantages of gas turbine cogeneration with absorption air cooling as design point operation using appropriate component efficiencies. The compared to other systems without air cooling. Author (El) effects of various cycle choices on overall performance are discussed. Author (El) A94-61111 EFFECT OF PRESSURE ON SECOND-GENERATION A94-61107 PRESSURIZED FLUIDIZED BED COMBUSTION PLANTS FAULT DIAGNOSIS IN GAS TURBINES USING A MODEL- A. ROBERTSON Foster Wheeler Development Corp, Livingston, BASED TECHNIQUE NJ and D. BONK Journal of Engineering for Gas Turbines and G. L. MERRINGTON DSTO, Victoria. Australia Journal of Power, Transactions of the ASME (ISSN 0742-4795) vol. 116, Engineering for Gas Turbines and Power, Transactions of the ASME no. 2 April 1994 p. 345-351 refs (ISSN 0742-4795) vol. 116, no. 2 April 1994 p. 374-380 refs (BTN-94-EIX94311331067) Copyright (BTN-94-EIX94311331071) Copyright In the search for a more efficient, less costly, and more environ- Reliable methods for diagnosing faults and detecting degraded mentally responsible method for generating electrical power from coal, performance in gas turbine engines are continually being sought In this research and development has turned to advanced pressurized fluid- paper, a model-based technique is applied to the problem of detecting ized bed combustion (PFBC) and coal gasification technologies. A degraded performance in a military turbofan engine from take-off logical extension of this work is the second-generation PFBC plant acceleration-type transients. In the past, difficulty has been experi- which incorporates key components of each of these technologies. In enced in isolating the effects of some of the physical processes this new type of plant, coal is devolatilized/carbonized before it is involved. One such effect is the influence of the bulk metal temperature injected into the PFB combustor bed, and the low-Btu fuel gas produced on the measured engine parameters during large power excursions. It by this process Is burned in a gas turbine topping combustor. By will be shown that the model-based technique provides a simple and integrating coal carbonization with PFB coal/char combustion, gas convenient way of separating this effect from the faster dynamic turbine inlet temperatures higher than 1149 deg C (2100 deg F) can be components. The important conclusion from this work is that good fault achieved. The carbonizer, PFB combustor, and paniculate-capturing coverage can be gleaned from the resultant pseudo-steady-state gain hot gas cleanup systems operate at 871 deg C (1600 deg F), permitting estimates derived in this way. Author (El) sulfur capture by lime-based sorbents and minimizing the release of coal contaminants to the gases. This paper presents the performance A94-61108 and economics of this new type of plant and provides a brief overview ASSESSMENT OF WEIGHTED-LEAST-SQUARES-BASED GAS of the pilot plant test programs being conducted to support its develop- PATH ANALYSIS ment Author (El) D. L. DOEL GE Aircraft Engines, Evendale, OH Journal of Engineering for Gas Turbines and Power, Transactions of the ASME A94-61116 (ISSN 0742-4795) vol. 116, no. 2 April 1994 p. 366-373 refs WORKING GROUP ACTIVITIES OF AGARD PROPULSION (BTN-94-EIX94311331070) Copyright AND ENERGETICS PANEL Manufacturers of gas turbines have searched for three decades A. S. UCER METU, Ankara, Turkey Journal of Engineering for fora reliable way to use gas path measurements to determine the health Gas Turbines and Power, Transactions of the -4SME(ISSN 0742- of jet engine components. They have been hindered in this pursuit by 4795) vol. 116, no. 2 April 1994 p. 307-314 refs the quality of the measurements used to carry out the analysis. Engine (BTN-94-E1X94311331062) Copyright manufacturers have chosen weighted-least-squares techniques to One of the major activities of AGARD panels is to form working reduce the inaccuracy caused by sensor error. While these algorithms groups, which assemble experts who work on the particular subject for

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two or three years. As a result of the work, an advisory report is A94-61127 published, which complies the state-of-the-art knowledge on the cho- ROTATING LASER-DOPPLER ANEMOMETRY SYSTEM FOR sen specific topic. This paper explains the philosophy and procedures UNSTEADY RELATIVE FLOW MEASUREMENTS IN MODEL adopted during the formation of working groups of the Propulsion and CENTRIFUGAL IMPELLERS Energetics Panel. Working groups concerning gas turbine technologies M. ABRAMIAN Pratt and Whitney Canada, Mississauga are presented. The selected working groups aim to improve the (Ontario) and J. H. G. HOWARD Journal of Turbomachinery, computational and experimental knowledge that would lead to the Transactions of the ASME (ISSN 0889-504X) vol. 116, no. 2 design of advanced aero gas turbine engines. Objective, scope, April 1994 p. 260-268 refs procedure, and important results of each working group will be ex- (BTN-94-EIX94311330092) Copyright plained. Working groups that were active during the 1980s and which The behavior of the relative flow in centrifugal turbomachines is were presently active are covered. Author (El) extremely complex due to the existence of various fluid dynamic phenomena and their interaction. At design and off-design operating conditions, the relative flow is subject to stationary unsteadiness, which A94-61125 includes the flow separation and wakes associated with passage INVISCIO-VISCOUS INTERACTION METHOD FOR THREE- pressure gradients, secondary flows, and boundary layer stability. It is DIMENSIONAL INVERSE DESIGN OF CENTRIFUGAL also subject to periodic unsteadiness from the rotating stall and the IMPELLERS cyclic flow phenomena induced by the casing. This paper describes the M. ZANGENEH Univ. Coll. of London, London (United Kingdom) mechanical and optical design of a rotating laser-Doppler anemometry Journal of Turbomachinery, Transactions of the ASME (ISSN system, which allows direct measurement of the relative flow by means 0889-504X) vol. 116, no. 2 April 1994 p. 280-290 refs of an optical derotator. By isolating the impeller rotational frequency (BTN-94-EIX94311330094) Copyright from the sampling frequency, it allows direct time-averaged measure- A three-dimensional design method for the design of the blade ments of the stationary behavior of the relative flow along with the geometry of centrifugal compressor impellers is presented. In this ensemble (phase)-averaged measurements of its periodic behavior. Its method the blade shape is computed for a specified circulation distri- success is demonstrated with measurements conducted in a low bution, normal (or tangential) thickness distribution, and meridional specific speed centrifugal impeller fitted with a single volute. Sample geometry. As the blade shapes are computed by using an inviscid slip results of the time-averaged blade-to-blade variation of total relative (or flow tangency) condition, the viscous effects are introduced indi- velocities along with their associated turbulence intensities are re- rectly by using a viscous/inviscid procedure. The three-dimensional ported. The (periodic) cyclic variations of the impeller exit flow, induced Navier-Stokes solver developed by Dawes is used as the viscous by the volute at low flow rates, are also presented for the suction and method. Two different approaches are described for incorporating the pressure sides. Author (El) viscous effects into the inviscid design method. One method is based on the introduction of an aerodynamic blockage distribution throughout the meridional geometry, while in the other approach a vorticity term A94-61128 directly related to the entropy gradients in the machine is introduced. OPERATIONAL STABILITY OF A CENTRIFUGAL The method is applied to redesign the blade geometry of Eckardf s 30 COMPRESSOR AND ITS DEPENDENCE ON THE deg backswept impeller as well as a generic high pressure ratio CHARACTERISTICS OF THE SUBCOMPONENTS (transonic) impeller. The results indicate that the entropy gradient R. HUNZIKER ETH Swiss Federal Inst. of Tech., Zurich approach can fairly accurately represent the viscous effects in the (Switzerland) and G. GYARMATHY Journal of Turbomachinery, machine. Author (El) Transactions of the ASME (ISSN 0889-504X) vol. 116, no. 2 April 1994 p. 250-259 (BTN-94-EIX94311330091) Copyright A94-61126 A centrifugal compressor was tested with three different diffusers EXPERIMENTAL INVESTIGATION OF THE STEADY AND with circular-arc vanes. The vane inlet angle was varied from 15 to 30 UNSTEADY RELATIVE FLOW IN A MODEL CENTRIFUGAL deg. Detailed static wall pressure measurements show that the pres- IMPELLER PASSAGE sure field in the diffuser inlet is very sensitive to flow rate. The stability M. ABRAMIAN Pratt and Whitney Canada, Mississauga limit regularly occurred at the flow rate giving the maximum pressure (Ontario) and J. H. G. HOWARD Journal of Turbomachinery, rise for the overall stage. Mild surge arises as a dynamic instability of Transactions of the ASME (ISSN 0889-504X) vol. 116, no. 2 the compression system. The analysis of the pressure rise character- April 1994 p. 269-279 istic of each individual subcomponent (impeller, diffuser inlet, diffuser (BTN-94-EIX94311330093) Copyright channel,...) reveals their contribution to the overall pressure rise. The The behavior of the relative flow in centrifugal turbomachines is diffuser channels play an inherently destabilizing role while the impeller extremely complex due to the existence of various fluid dynamic and the diffuser inlet are typically stabilizing. The stability limit was phenomena and their interaction. At design and off-design operating mainly determined by a change in the characteristic of the diffuser inlet conditions, the relative flow is subject to stationary unsteadiness, which Further, the stability limit was found to be independent of the develop- includes flow separation and wakes associated with passage pressure ment of inducer-tip recirculation. Author (El) gradients, secondary flows, and boundary layer stability. It may also be subject to periodic unsteadiness, as are the rotating stall and cyclic flow phenomena induced by the casing. This paper describes detailed A94-61129 measurements of the relative velocity field in a very low specific speed DEVELOPMENTS IN CENTRIFUGAL COMPRESSOR SURGE centrifugal pump impeller (N(sub s) s 515). Measurements were CONTROL: A TECHNOLOGY ASSESSMENT conducted by means of a recently developed rotating laser-Doppler K. K. BOTROS NOVACOR Research and Technology Corp., anemometry system. Detailed quantitative descriptions of the mean Calgary (Alberta) and J. F. HENDERSON Journal of and fluctuating components of the primary and secondary velocity Turbomachinery, Transactions of the ASME (ISSN 0889-504X) fields are presented for an impeller without volute at design, 50 percent vol. 116, no. 2 April 1994 p. 240-249 design, and shut-off conditions. The flow pattern in this low specific (BTN-94-EIX94311330090) Copyright speed impeller with high blade loading is dominated by the relative eddy There are a number of surge control schemes in current use for (a phenomenon also present in potential flow), which has suppressed centrifugal compressors employed in natural gas transmission sys- suction side separation. The cyclic variation of the impeller exit flow, tems. Basically, these schemes consist of a set of detection devices induced by the volute at low flow rates, is also presented for an impeller that either anticipate surge or detect it at its inception, and a set of fitted with a volute. Author (El) control devices that act to prevent surge from occurring. A patent

590 ENGINEERING 12 search was conducted in an attempt to assess the leva) and direction J. P. LONGLEY Cambridge Univ., Cambridge (United Kingdom) of technology development over the last 20 years and to define the Journal of Turbomachinery, Transactions of the ASME (ISSN focus for future R&D activities. In addition, the paper presents the 0889-504X) vol. 116, no. 2 April 1994 p. 202-215 current state of technology in three areas: surge control, surge detec- (BTN-94-EIX94311330087) Copyright tion, and surge suppression. Patent data obtained from on-line data- This paper presents a review of the different approaches to bases showed that most of the emphasis has been on surge control modeling the nonsteady fluid dynamics associated with two-dimen- rather than on detection and control and that the current trend in surge sional compressor flow fields. These models are used to predict the control will likely continue toward incremental improvement of a basic time development of flow field disturbances and have been found useful or conventional surge control strategy. Various surge suppression in both the study of rotating stall and the development of active control. techniques can be grouped in two categories: 0) those that are focused The opportunity to digest the earlier investigations has now made it on better compressor interior design, and (ii) others that attempt to possible to express the modeling ideas using only a very simple suppress surge by external and operational means. Author (El) mathematical treatment Here, the emphasis is on the underlying physical processes that the models simulate and how the assumptions A94-61130 within the models affect predictions. The purpose of this work is to ACTIVE STABILIZATION OF ROTATING STALL IN A THREE- produce, in a single document a description of compressor modeling STAGE AXIAL COMPRESSOR techniques, so that prospective users can assess which model is the J. M. HAYNES Massachusetts Inst. of Tech., Cambridge, MA, most suitable for their application. Author (El) G. J. HENDRICKS, and A. H. EPSTEIN Journal of Turbomachinery, Transactions of the ASME (ISSN 0889-504X) vol. 116, no. 2 April 1994 p. 226-239 refs (BTN-94-EIX94311330089) Copyright A94-61133 A three-stage, low-speed axial research compressor has been UNSTABLE BEHAVIOR OF LOW AND HIGH-SPEED actively stabilized by damping low-amplitude circumferentially traveling COMPRESSORS waves, which can grow into rotating stall. Using a circumferential array I. J. DAY Cambridge Univ., Cambridge (United Kingdom) and of hot-wire sensors, and an array of high-speed individually positioned C. FREEMAN Journal of Turbomachinery, Transactions of the control vanes as the actuator, the first and second spatial harmonics of ASME (ISSN 0889-504X) vol. 116, no. 2 April 1994 p. 194- the compressor were stabilized down to a characteristic slope of 0.9, 201 refs yielding an 8 percent increase in operating flow range. Stabilization of (BTN-94-EIX94311330086) Copyright the third spatial harmonic did not alter the stalling flow coefficient. The By far the greater part of our understanding about stall and surge actuators were also used open loop to determine the forced response in axial compressors comes from work on low-speed laboratory ma- behavior of the compressor. A system identification procedure applied chines. As a general rule, these machines do not model the compress- to the forced response data then yielded the compressor transfer ibility effects present in high-speed compressors and therefore doubt function. The Moore-Greitzer two-dimensional stability model was has always existed about the application of low-speed results to high- modified as suggested by the measurements to include the effect of speed machines. In recent years interest in active control has led to a blade row time lags on the compressor dynamics. This modified Moore- number of studies of compressor stability in engine-type compressors. Greitzer model was then used to predict both the open and closed-loop The instrumentation used in these experiments has been sufficiently dynamic response of the compressor. The model predictions agreed detailed that, for the first time, adequate data are available to make closely with the experimental results. In particular, the model predicted direct comparisons between high-speed and low-speed compressors. both the mass flow at stall without control and the design parameters This paper presents new data from an eight-stage fixed geometry needed by, and the range extension realized from, active control. engine compressor and compares them with low-speed laboratory Author (El) data. The results show remarkable similarities in both the stalling and surging behavior of the two machines, particularly when the engine A94-61131 compressor is run at intermediate speeds. The engine results also STALL INCEPTION AND DEVELOPMENT IN AN AXIAL FLOW show that, as in the laboratory tests, surge is precipitated by the onset AEROENGINE of rotating stall. This is true even at very high speeds where it had A. G. WILSON Rolls-Royce PLC, Derby (United Kingdom) and previously been thought that surge might be the result of a blast wave C. FREEMAN Journal of Turbomachinery, Transactions of tho moving through the compressor. This paper therefore contains new ASM£(ISSN0889-504X) vol. 116, no. 2 April 1994 p. 216- information about high-speed compressors and confirms that low- 225 refs speed testing is an effective means of obtaining insight into the behavior (BTN-94-EIX94311330088) Copyright of high-speed machines. Author (El) This paper describes the phenomenon of stall and surge in an axial flow aeroengine using fast response static pressure measurements from the compressor of a Rolls-Royce VIPER engine. It details A94-61134 the growth of flow instability at various speeds, from a small zone of SPANWISE TRANSPORT IN AXIAL-FLOW TURBINES. PART stalled fluid involving only a few blades into the violent surge motion of 2: THROUGHFLOW CALCULATIONS INCLUDING SPANWISE the entire machine. Various observations from earlier theoretical and TRANSPORT compressor rig results are confirmed by these new engine measure- K. L. LEWIS Cambridge Univ., Cambridge (United Kingdom) ments. The main findings are as follows: (1) The point of stall inception Journal of Turbomachinery, Transactions of the ASME (ISSN moves rearward as engine speed increases, and is shown to be simply 0889-504X) vol. 116, no. 2 April 1994 p. 187-193 refs related to the axial matching of the compressor. (2) The final unstable (BTN-94-EIX94311330085) Copyright operation of the machine can be divided into rotating stall at low speed In Part 1 of this paper, a repeating stage condition was shown to and surge or multiple surge at high speed. (3) The inception process is occur in two low aspect ratio turbines, typically after two stages. Both independent of whether the final unstable operation is rotating stall or turbulent diffusion and convective mechanisms were responsible for multiple surge. (4) Stall/surge always starts as a circumferentiaJly small spanwise transport In this part, two scaling expressions are deter- flow disturbance, rotating around the annulus at some fraction of rotor mined that account for the influence of these mechanisms in effecting speed. Author (El) spanwise transport These are incorporated into a throughflow model using a diffusive term. The inclusion of spanwise transport allows the A94-61132 use of more realistic loss distributions by the designer as input to the REVIEW OF NONSTEADY FLOW MODELS FOR COMPRESSOR throughflow model and therefore focuses attention on areas where STABILITY losses are generated. In addition, modeling of spanwise transport is

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shown to be crucial in predicting the attenuation of a temperature profile A94-61641 through a turbine. Author (El) UNSTRUCTURED MESH QUALITY ASSESSMENT AND UPWIND EULER SOLUTION ALGORITHM VALIDATION PAUL R. WOODARD Purdue Univ., West Lafayette, IN, JOHN T. BATINA, and HENRY T. Y. YANG Journal of Aircraft (ISSN A94-61135 0021-8669) vol. 31, no. 3 May-June 1994 p. 644-650 refs SPANWISE TRANSPORT IN AXIAL-FLOW TURBINES. (BTN-94-EIX94401358985) Copyright PART 1: THE MULTISTAGE ENVIRONMENT Quality assessment procedures are described for two and three K. L. LEWIS Cambridge Univ., Cambridge (United Kingdom) dimensional unstructured meshes. The procedures include measure- Journal of Turbomachinery, Transactions of the ASME (ISSN ment of minimum angles, element aspect ratios, stretching, and 0889-504X) vol. 116, no. 2 April 1994 p. 179-186 refs element skewness. Meshes about the ONERA M6 wing and the Boeing (BTN-94-EIX94311330084) Copyright 747 transport configuration are generated using an advancing front Selected experimental results, obtained from a detailed investi- method grid generation package of programs. Solutions of the Euler gation into the flow fields within two low-speed multistage turbines, are equations for these meshes are obtained at low angle of attack, presented. A repeating stage condition occurred typically after two transonic conditions. Results for these cases, obtained as part of a stages, with the secondary flows an important factor in the low aspect validation study, investigate accuracy of an implicit upwind Euler ratio geometry. A tracer gas technique was employed to identify the solution algorithm. Author (El) dominant mechanisms of spanwise transport and their relative significance. In the first stages of both machines, tracer transport was more A94-61767 intense near the endwalls than at midspan, while in the multistage ADAPTIVE MODEL ARCHITECTURE AND EXTENDED environment the transport was approximately constant across the KALMAN-BUCY FILTERS whole span. The convective influence of classical secondary flow, PETER J. COSTA Univ. of Saint Thomas, St. Paul. MN IEEE shroud leakage, and wake passage through a downstream blade was Transactions on Aerospace and Electronic Systems (ISSN 0018- identified and shown to be as significant as turbulent diffusion in 9251) vol. 30, no. 2 April 1994 p. 525-533 refs effecting cross-passage and spanwise transport. The data show that (BTN-94-EIX94401377806) Copyright spanwise transport should be included within any throughflow model In radar systems, extended Kalman-Bucy filters (EKBFs) are used and are used to calibrate two scaling models. These models are to estimate state vectors of objects in track. Rlter models accounting for presented in Part 2, where the influence of incorporating spanwise fundamental aerodynamic forces on reentry vehicles are well known. A transport into a throughflow model is investigated. Author (El) general model structure accommodating the dynamics of reentry vehicles in both exoatmospheric and endoatmospheric flight is presented. The associated EKBFs for these various models are described A94-61203 and the resulting associated parameter estimation and identification DESIGN OF A MULTI-CHANNEL TRUE FLAT FLUORESCENT problems are discussed. The effects of position, velocity, drag, and LAMP FOR AVIONIC AM-LCD BACKLIGHTING aerodynamic lift are described within a nested set of EKBF models. MUNISAMY ANANDAN Thomas Electronics, Inc., Wayne, NJ, Author (El) DOUGLAS KETCHUM, HANK ETLINGER, ROBERT KIRKER, and WILLIAM CARR IEEE Transactions on Electron Devices A94-61805 (ISSN 0018-9383) vol. 41, no. 4 April 1994 p. 504-510 refs BUCKLING AND VIBRATION ANALYSIS OF LAMINATED (BTN-94-EIX94311330477) Copyright PANELS USING VICONOPT For backlighting a direct view avionic liquid crystal display (LCD), DAVID KENNEDY University Coll., Cardiff (United Kingdom), a multi-channel true flat fluorescent lamp (T-FFL) has been designed FRED W. WILLIAMS, and MELVIN S. ANDERSON Journal of and developed. The design and development was accomplished Aerospace Engineering (ISSN 0893-1321) vol. 7, no. 3 July through 1) electric field plot for various ratios of depth to height of the 1994 p. 245-262 refs hollow cathode, 2) decrease of charge losses, 3) employment of (BTN-94-EIX94401372105) Copyright internal dielectric mirror, 4) monitoring of the penetration of internal The analysis aspects of the 23,000-line FORTRAN program positive column, and 5) design of a constant current drive for T-FFL A VICONOPT are described. Overall stiffness matrices assembled from luminance of 3000 fL. with a luminous efficiency of 16.2 l/w has been the earlier exact VIPASA flat plate stiffnesses are optionally coupled by achieved on a 3double prime diagonal T-FFL. Author (El) Lagrangian multipliers to find critical buckling loads, or natural frequencies of undamped vibration, of prismatic assemblies of anisotropic flat plates with arbitrarily located point supports or simple transverse supporting frames. The longitudinal continuity of typical wing and A94-61615 fuselage panels is closely approximated because the solutions are for STABILITY OF SKEW PLATES SUBJECTED TO the infinitely long structure obtained by repeating a bay and its supports AERODYNAMIC AND IN-PLANE FORCES longitudinally. Any longitudinally invariant in-plane plate stresses are T. H. YOUNG National Taiwan Inst. of Tech., Taipei (Taiwan, permitted, and very rapid solutions are guaranteed by numerous Province of China) and F. Y. CHEN Journal of Sound and refinements, including multilevel substructuring and a method for Vibration (ISSN 0022-460X) vol. 171, no. 5 April 14, 1994 repetitive cross sections that is exact for regular polygons used to p. 603-615 refs represent cylinders. Modal displacements and stresses in or between (BTN-94-EIX94321331202) Copyright plies of laminated plates are calculated and plotted, with values being In this paper an investigation is presented into the stability of skew recovered at all nodes of substructures. Comparison with usual ap- plates acted upon by both aerodynamic and in-plane forces simulta- proximate finite-element methods confirms that, for comparably con- neously. The in-plane force is assumed to be small in magnitude verged solutions, VICONOPT is typically between 100 and 10(sup 4) compared to the aerodynamic force. Due to this small in-plane force, the times faster. Author (El) system may become unstable before the aerodynamic force reaches its critical value. A finite element formulation is used to obtain the A94-61853 discretized system equations. The system equations are then partially NUMERICAL SIMULATION OF VORTEX-WEDGE uncoupled and reduced in size by the modal truncation method. Finally, INTERACTION the method of multiple scales is used to determine the transition curves JIN-HO PARK Korea Advanced Institute of Science and of the system. The effects of system parameters on the boundaries of Technology, Taejon, Korea and DUCK JOO LEE AIAA Journal the unstable regions are studied numerically. Author (El) (ISSN 0001-1452) vol. 32, no. 6 June 1994 p. 1126-1134

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refs EHUD GARTENBERG Old Dominion Univ., Norfolk, VA, (BTN-94-EIX94421374955) Copyright LEONARD M. WEINSTEIN, and EDWIN E. LEE AIAA Journal Interactions between vortical flows and a solid surface cause one (ISSN 0001-1452) vol. 32, no. 6 June 1994 p. 1242-1249 of the primary sources of noise and unsteady loading. The mechanism refs of the interaction is studied numerically for single Rankine vortex (BTN-94-EIX94421374975) Copyright impinging upon a wedge. A Euler-Lagrangian method is used to Aflow visualization study was performed using a focusing schlieren describe the vorticity dominant field. El system in the 0.3 m Transonic Cryogenic Tunnel at NASA Langley Research Center. The system proved to be a useful flow visualization A94-61862 tool for flows as low as M = 0.4. This study marked the first verification BOUNDARY CONDITIONS FOR UNSTEADY SUPERSONIC of the focusing schlieren technique in a major subsonic/transonic wind INLET ANALYSES tunnel and the first time that high-quality, detailed pictures of high- DAVID W. MAYER Boeing Commercial Airplane Group, Reynolds-number flows were obtained in a cryogenic wind tunnel. Seattle, WA and GERALD C. PAYNTER AIAA Journal (ISSN Author (revised by El) 0001-1452) vol. 32, no. 6 June 1994 p. 1200-1206 refs (BTN-94-EIX94421374964) Copyright N94-36328* Dassault Aviation, Saint-Cloud (France). Div.des Etudes New bleed and compressor face boundary conditions have been Avancees. developed to improve the accuracy of unsteady supersonic inlet LAMINAR FLOW STUDIES AT DASSAULT AVIATION: calculations. The new bleed boundary conditions relate changes in the CALCULATIONS AND FLIGHT TESTS [ETUDES bleed hole discharge coefficient to changes in the local flow conditions; D'ECOULEMENTS LAMINAIRES CHEZ DASSAULT the local bleed flow rate can more than double as a shock moves AVIATION: CALCULS ET ESSAIS EN VOL] forward over a bleed band in response to inlet flow disturbances. The J. C. COURTY, C. BULGUBURE, and D. ARNAL In AGARD, effects of inlet flow disturbances on the flow at the compressor face are Recent Advances in Long Range and Long Endurance Operation represented more realistically with this new boundary condition than of Aircraft 14 p Nov. 1993 In FRENCH with traditional fixed static pressure or mass flow conditions. Copyright Avail: CASI HC A03/MF A03 Author (revised by El) The tools used at Dassault Aviation to calculate the limits on laminar layers, transition criteria and analyses on linear stability are A94-61867 presented and analyzed as far as their precision but also as far as their SENSITIVITY DERIVATIVES FOR THREE-DIMENSIONAL effectiveness when they have to be used to optimize the design of SUPERSONIC EULER CODE USING INCREMENTAL aircrafts' wing systems. These calculations were used in the concept of ITERATIVE STRATEGY laminar deviation that was tested in the air on a FALCON 50, and in the VAMSHI MOHAN KORIVI Old Dominion Univ., Norfolk, VA, concept of a wing with an hybrid laminarity that was tested in the air on ARTHUR C. TAYLOR, GENE W. HOU, PARRY A. NEWMAN, and a FALCON 50 during a second phase, 1987-1990. Author HENRY E. JONES AIAA Journal (ISSN 0001-1452) vol. 32, no. 6 June 1994 p. 1319-1321 refs N94-36420*# Virginia Univ., Chariottesville, VA. Dept of Mechani- (BTN-94-EIX94421374969) Copyright cal, Aerospace and Nuclear Engineering. An incremental strategy was proposed to Relatively solve the very ANALYSIS OF HIGH SPEED FLOW, THERMAL AND large system of linear equations that are required to obtain quasianalyticaJ STRUCTURAL INTERACTIONS Final Report, 1 Jun. 1989 - sensitivity derivatives from advanced computational fluid dynamics 31 Mar. 1994 (CFD) codes. The technique was successfully demonstrated for two EARL A. THORNTON Jun. 1994 217 p large two-dimensional problems; a subsonic and a transonic airfoil. The (Contract NAG1-1013) principal feature of this incremental iterative strategy is that it allows the (NASA-CR-196017; MAS 1.26:196017; UVA/528308/MANE94/101) use of the identical approximate coefficient matrix operator and algo- Avail: CASI HC A10/MF A03 rithm to solve the nonlinear flow and the linear sensitivity equations. A Research for this grant focused on the following tasks: (1) the computationally efficient general methodology has been successfully prediction of severe, localized aerodynamic heating for complex, high demonstrated for rteratively solving the very large systems of linear speed flows; (2) finite element adaptive refinement methodology for equations required for obtaining quasianalytical sensitivity derivatives multi-disciplinary analyses; (3) the prediction of thermoviscoplastic from three-dimensional CFD codes. Author (revised by El) structural response with rate-dependent effects and large deformations; (4) thermoviscoplastic constitutive models for metals; and (5 A94-61872 coolant flow/structural heat transfer analyses. Derived from text LASER INTERFEROMETER SKIN-FRICTION MEASUREMENTS OF CROSSING-SHOCK-WAVE/TURBULENT-BOUNDARY- N94-36617# McDonnell-Douglas Aerospace, Saint Louis, MO. LAYER INTERACTIONS ICAAS PILOTED SIMULATION RESULTS T. J. GARRISON Pennsylvania State Univ., Univ Park, PA, G. R. J. LANDY, P. J. HALSKI, and R. P. MEYER In AGARD, Pointing S. SETTLES, N. NARAYANSWAMI. and D. D. KNIGHT AIAA and Tracking Systems 14 p May 1994 Jouma/(ISSN0001-1452) vol. 32, no. 6 June 1994 p. 1234- Copyright Avail: CASI HC A03/MF A02 1241 refs This paper reports piloted simulation results from the Integrated (BTN-94-EIX94421374974) Copyright Control and Avionics for Air Superiority (ICAAS) piloted simulation Wall shear stress measurements beneath crossing-shock-wave / evaluations. The program was to develop, integrate, and demonstrate turbulent boundary-layer interactions have been made for three inter- critical technologies which will enable United States Air Force tactical actions of different strengths. The interactions are generated by two fighter 'blue' aircraft to achieve superiority and survive when outnum- sharp fins at symmetric angles of attack mounted on a flat plate. The bered by as much as four to one by enemy aircraft during air combat shear stress measurements were made for fin angles of 7 and 11 deg engagements. Primary emphasis was placed on beyond visual range at Mach 3 and 15 deg at Mach 3.85. The measurements were made (BVR) combat with provisions for effective transition to close-in combat using a laser interferometer skin-friction meter, a device that deter- The ICAAS system was developed and tested in two stages. The first mines the wall shear by optically measuring the time rate of thinning of stage, called low risk ICAAS, was defined as employing aircraft and an oil film placed on the test model surface. Author (revised by El) avionics technology with an initial operational date no later than 1995. The second stage, called medium risk ICAAS, was defined as employ- A94-61B73 ing aircraft and avionics technology with an initial operational date no AERODYNAMIC INVESTIGATION WITH FOCUSING later than 1998. Descriptions of the low risk and medium risk simulation SCHLIEREN IN A CRYOGENIC WIND TUNNEL configurations are given. Normalized (unclassified) results from both

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the low risk and medium risk ICAAS simulations are discussed. The N94-36812*# Pennsylvania State Univ., University Park, PA. Dept of results show the ICAAS system provided a significant improvement in Computer Science and Engineering. air combat performance when compared to a current weapon system. A MODEL-BASED APPROACH FOR DETECTION OF RUNWAYS Data are presented for both current generation and advanced fighter AND OTHER OBJECTS IN IMAGE SEQUENCES ACQUIRED aircraft. The ICAAS technologies which are ready for flight testing in USING AN ON-BOARD CAMERA Final Technical Report, 24 order to transition to the fighter fleet are described along with technolo- Jan. 1992-31 May 1994 gies needing additional development Author (revised) RANGACHAR KASTURI, SADASHIVA DEVADIGA, and YUAN-LIANG TANG 18 Aug. 1994 125 p (Contract NAG1-1371) N94-36620# Thomson-TRT Defense, Guyancourt (France). (NASA-CR-196424; NAS 1.26:196424) Avail: CASI HC A06/MFA02 LASER DESIGNATION PODS OPTIMIZED CONCEPT FOR DAY/ This research was initiated as a part of the Advanced Sensor and NIGHT OPERATIONS [PODS DE DESIGNATION LASER UN Imaging System Technology (ASSIST) program at NASA Langley CONCEPT OPTIMISE POUR LES OPERATIONS JOUR/NUIT] Research Center. The primary goal of this research is the development YVES HUGUENIN In AGARD, Pointing and Tracking Systems of image analysis algorithms for the detection of runways and other 7p May 1994 In FRENCH objects using an on-board camera. Initial effort was concentrated on Copyright Avail: CASI HC A02/MF A02 images acquired using a passive millimeter wave (PMMW) sensor. The The conception of an optimized laser guided weapon that can be images obtained using PMMW sensors under poor visibility conditions used at any time requires some technologies which, today, are not due to atmospheric fog are characterized by very low spatial resolution 1 always compatible within the same equipment. From the 'day ATLIS but good image contrast compared to those images obtained using 1 concept, Thomson-CSF developed a complementary 'night pod. This sensors operating in the visible spectrum. Algorithms developed tor convertible laser designation pod is the result of technical and opera- analyzing these images using a model of the runway and other objects tional optimization. Transl. by FLS are described in Part 1 of this report. Experimental verification of these algorithms was limited to a sequence of images simulated from a single frame of PMMW image. Subsequent development and evaluation of N94-366270 McDonnell-Douglas Aerospace, Saint Louis, MO. algorithms was done using video image sequences. These images AEROSERVOELASTIC STABILIZATION CONSIDERATIONS have better spatial and temporal resolution compared to PMMW FOR POINTING AND TRACKING SYSTEMS images. Algorithms for reliable recognition of runways and accurate PETER Y. CHENG and RALPH E. LAMBERT In AGARD, Pointing estimation of spatial position of stationary objects on the ground have and Tracking Systems 6 p May 1994 been developed and evaluated using several image sequences. These Copyright Avail: CASI HC A02/MF A02 algorithms are described in Part 2 of this report A fist of all publications The high gain, wide bandwidth precision tracking/pointing sys- resulting from this work is also included. Derived from text tems used on advanced aircraft necessitate the consideration of aeroservoelasticity (ASE) early in the design process. Aircraft control systems are designed to meet stability, performance and, in the case of manned aircraft, handling qualities criteria defined by the Mil-Spec N94-36839** National Aeronautics and Space Administration. Lyndon requirements. As digital controllers are introduced, airfrarnes are made B. Johnson Space Center, Houston, TX. statically unstable, and as the push for increased dynamic response PRELOAD RELEASE MECHANISM Patent Application continues, the aeroservoelastic influences become increasingly impor- ROBERT M. GENEROLI, inventor (to NASA) (McDonnell- tant in the overall system performance. At times, the ASE consider- Douglas Corp., Houston, TX.) and HARRY J. YOUNG, inventor ations may dominate the rigid body control law design effort. This paper (to NASA) (McDonnell-Douglas Corp., Houston, TX.) 20 Apr. summarizes an approach to the ASE stabilization of a fighter aircraft 1994 18p when used as the integral part of a high bandwidth manual or automatic (NASA-CASE-MSC-22327-1; NAS 1.71:MSC-22327-1; US-PATENT- fire control tracking system. The same approach can be applied to APPL-SN-230571) Avail: CASI HC A03/MF A01 standard manual control aircraft where a more thorough ASE analysis This invention relates to a preload release mechanism compris- is desired. Author ing a preload spring assembly adapted to apply a preload to a first connector member which is mounted on a support structure and adapted for connection with a second connector member on an object N94-36808*# MCAT Inst, San Jose, CA. The assembly comprises telescoped bushings and a preload spring. A TURBULENCE MODELING OF FREE SHEAR LAYERS FOR tubular shaft extends through the spring assembly and openings in the HIGH PERFORMANCE AIRCRAFT Final Report first connector member and support structure, on which it is clamped. DOUGLAS SONDAK Oct 1993 11 p A plunger rod in the shaft is provided with a tip end and a recess in the (Contract NCC2-663) rod near the other end thereof. A retainer precludes passage of the rod (NASA-CR-196137; NAS 1.26:196137; MCAT-94-12) Avail: CASI HC through the shaft in one direction and an end cap closes the bore of the A03/MF A01 shaft at the other end and provides a shoulder which extends radially In many flowfield computations, accuracy of the turbulence model of the shaft A plunger return spring biases the plunger rod against the employed is frequently a limiting factor in the overall accuracy of the plunger retainer with the plunger tip protruding from the shaft and a computation. This is particularly true for complex flowfields such as spring assembly return spring engages at its ends the shoulder of the those around full aircraft configurations. Free shear layers such as end cap and one end of the spring assembly. Detents received in lateral wakes, impinging jets (in V/STOL applications), and mixing layers over openings in the tubular shaft are held captive by the plunger rod and one cavities are often part of these flowfields. Although flowfields have been end of the spring assembly to lock the spring assembly on the tubular computed for full aircraft, the memory and CPU requirements for these shaft and apply a preload to the first connector member. Upon comple- computations are often excessive. Additional computer power is re- tion of the connection, detents and spring assembly are released by quired for multidisciplinary computations such as coupled fluid dynam- plunger contact with the object to be connected, thereby releasing the ics and conduction heat transfer analysis. Massively parallel computers preload while the connection is maintained. NASA show promise in alleviating this situation, and the purpose of this effort was to adapt and optimize CFD codes to these new machines. The objective of this research effort was to compute the flowfield and heat N94-37125 Utah State Univ., Logan. UT. Dept. of Mechanical transfer for a two-dimensional jet impinging normally on a cool plate. Engineering. The results of this research effort were summarized in an AIAA paper LITERATURE REVIEW AND PRELIMINARY STUDIES OF titled 'Parallel Implementation of the k-epsilon Turbulence Model'. FRETTING AND FRETTING FATIGUE INCLUDING SPECIAL Appendix A contains the full paper. Derived from text APPLICATIONS TO AIRCRAFT JOINTS Final Report

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DAVID HOEPPNER, SAEED ADIBNAZARI, and MARK W. EFFECTS ON ENGINE COMPONENTS STRUCTURAL MOESSER Apr. 1994 70 p Sponsored by FAA Limited INTEGRITY Reproducibility: More than 20% of this document may be affected DAVID W. HOEPPNER In AGARD, Impact of Materials Defects on by microfiche quality Engine Structures Integrity 8 p Apr. 1993 (AD-A280310; DOT/FAA/CT-93/2) Avail: Issuing Activity (Defense Copyright Avail: CASI HC A02/MF A02 Technical Information Center (DTIC)) Ever since the development of aeroengines, 'defects' have been This report contains a review of the literature pertinent to fretting of significant concern to the assurance of structural integrity. Many of and fretting fatigue including special applications to aircraft joints. An these issues have been the focus of recent Structures and Materials introduction is given outlining the importance of fretting and fretting Panel (SMP) workshops and conferences. Although engine idealiza- fatigue failures. Proposed mechanisms of fretting and fretting fatigue tions of materials being homogeneous, continuous, and free of defects' are then discussed. Research in the literature indicates there are three are invoked to make the complex issues of load, stress and strain, stages to fretting fatigue life. The first is a period of crack nudeation, tractable, they were recognized as early as 1916, and later in the usually by adhesion and plastic deformation of contacting asperities in 1930's, as being oversimplistic and potentially in error. The epistemol- relative motion. Several other possible mechanisms are discussed as ogy of the role of discontinuities ('defects') in the design, selection, and well. In the second stage, propagation of nucleated cracks is deter- lifing of critical aeroengine components is reviewed herein. Utilization mined by the stress resulting from the surface tractions imposed by of 'defect-free' and 'initiation' based fatigue criteria (as well as other time fretting. The results of several investigations of the stress state and its dependent failure modes such as creep, wear, etc.) have led to much effect on the propagation of nucleated cracks are discussed. The stress success in the aeroengine industry. However, 'defects' also have led to state can either dramatically increase early crack propagation rates or numerous engine component failures in military and civilian aeroengines. retard crack propagation, depending upon the specifics of the contact And, as increasing demands are made on materials used in aeroengines, under study. The third stage is a period of crack propagation during the role of 'defects' will, undoubtedly, become more important and which fretting contact stresses are not significant to crack propagation. critical. The history and prognosis of these issues is discussed with a DTIC review of on-condition lifing, defect-tolerant and damage-tolerant approaches, including, but not limited to, Engine Structural Integrity N94-37128 Maryland Univ., College Park, MD. Program (ENSIP). The prognosis will suggest the need for trie following: A FUNDAMENTAL STUDY OF HYPERSONIC UNSTARTS Final (1) development of increased understanding of the physics of failure Report, 1 Oct. 1991 - 30 Sep. 1993 processes of aeroengine materials; (2) integration of 'defect1 consider- MARK J.LEWIS 29 May 1994 65 p Limited Reproducibility: ations in the lifing methodologies from conceptual to detail design (the More than 20% of this document may be affected by microfiche new paradigm of lifing); (3) assurance that knowledge of intrinsic quality materials behavior, including manufacturing specification and control, (Contract F49620-92-J-0006) is a prime consideration in the defect-tolerant approach; (4) non- (AD-A280506; AFOSR-94-0362TR) Avail: Issuing Activity (Defense destructive inspection and evaluation should be one of many tools used Technical Information Center (DTIC)) to monitor and assure the state of the materials and should be a Activities for the first year were primarily focused on laying the consideration in the lifing methodology at the earliest stage; (5) evalu- groundwork for accomplishing the ultimate goals of this investigation. ation and integration of the role of extraneous influences, such as Required hardware and software was obtained and implemented. Grid fretting, environmental attack, and the like, and how they are factored generators were tested and one was selected, as was the primary into the lifing procedure; and (6) development of consistent terminology computational tool. Activities in the second year were directed towards with standardized definitions. Author beginning the three dimensional Euler, then Navier-Stokes calculations, to establish a steady-state time accurate baseline, which could then be perturbed to study the influence of downstream disturbances. Both Euler and laminar Navier-Stokes solutions were calculated. N94-37329# Rat Aviazione S.pA, Turin (Italy). DTIC TURBINE DISKS: LIFING AGAINST DEFECTS AND MATERIALS DEVELOPMENT N94-37321* Advisory Group for Aerospace Research and Develop- E. CAMPO, G. PASQUERO. ALDO FREDIANI, and ROBERTO ment, Neuilly-Sur-Seine (France). Structures and Materials Panel. GALATOLO In AGARD, Impact of Materials Defects on Engine IMPACT OF MATERIALS DEFECTS ON ENGINE STRUCTURES Structures Integrity 12 p Apr. 1993 INTEGRITY [L'IMPACT DES DEFAUTS DES MATERIAUX SUR Copyright Avail: CASI HC A03/MF A02 L'INTEGRITE DES STRUCTURES DES MOTEURS] Structural integrity of turbine disks must be guaranteed with a high Apr. 1993 118p In ENGLISH and FRENCH The 74th meeting safety level. The Engine Structural Integrity Program as contained in was held in Patras, Greece, 27-28 May 1992 NIL-STD-1783 is aimed to enhance disk safety. A major design (AGARD-R-790;ISBN-92-835-0711-8) Copyright Avail: CASI HC requirement is the implementation of the Damage Tolerance concepts A06/MF A02 by assessing the disk life in presence of defects. This paper illustrates Engine failures due to materials defects are rare, but are still a the MIL-STD-1893 impact on turbine design as well as on material cause for concern to both manufacturers and lifting authorities. In these requirements, putting more emphasis on induced discontinuity features circumstances it is recognized that the introduction of higher strength than on evolutionary ones. Targets for future developments in lifing materials, new production routes and improved non-destructive evalu- procedures as well as in innovative materials are defined taking into ation methods may have significant implications for engine lifing and account possible differences in life management among NATO coun- safety. The impact of inherent defects on present and future component tries. Author manufacture and on aircraft engine operation is considered. Materials processing and control aspects are reviewed, placing particular emphasis on nickel and titanium engine disc materials. Variations in engineers', scientists' and lawyers' interpretation of the work 'defect was N94-37330# General Electric Co., Cincinnati, OH. Aircraft Engines. perhaps the most significant point to emerge from the meeting; so much SUBSTANTIATING POWDER METAL LIFE METHODOLOGIES so, that a small group agreed to develop a definition, and when FOR ENGINES established recommend it as standard AGARD materials technology. P. A. DOMAS In AGARD, Impact of Materials Defects on Engine Structures Integrity 8 p Apr. 1993 N94-37322# Utah Univ., Salt Lake City, UT. Dept of Mechanical Copyright Avail: CASI HC A02/MF A02 Engineering. The application of powder metal (PM) superalloys in aircraft HISTORY AND PROGNOSIS OF MATERIAL DISCONTINUITY turbine engine rotating components is prompted by performance driven

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high strength and creep resistance requirements. Rne grain, precipita- analysis must be considered to precisely determine the optimal tooth tion strengthened nickel-base alloys such as IN100, Rene'95, and indexing position. Author Rene'SBDT meet these requirements up to operating temperatures in the 1200-1300F (649-704C) range, in addition to burst and deformation limits, design constraints include durability (fatigue) and damage tolerance (crack growth resistance) capability to insure reliability and N94-36919*# Aerojet Delft Corp., Azusa, CA. safety. Fatigue life forthese alloys can be influenced by inhomogeneities EARTH OBSERVING SYSTEM/ADVANCED MICROWAVE (inclusions) intrinsic to the microstructure as the result of processing, SOUNDING UNIT-A (EOS/AMSU-A) SOFTWARE and by perturbations of the surface integrity during component manu- MANAGEMENT PLAN Final Report facture and subsequent usage. Understanding of PM fatigue behavior ROBERT SCHWANTJE 20 Jun. 1994 39 p and substantiation of life assessment methodology must appropriately (Contract NAS5-32314; RTOP 422-00-00) recognize these potential influences. New testing, modeling, and (NASA-CR-189362; NAS 1.26:189362; REPT-9803-1; REPT-10339; analysis schemes are necessitated in engineering development pro- CDRL-008) Avail: CASI HC A03/MF A01 grams addressing generation and validation of life prediction tech- This document defines the responsibilites for the management of niques for these materials. This paper outlines one approach to the like-cyde development of the flight software installed in the AMSU- substantiating PM fatigue life prediction that attempts to recognize A instruments, and the ground support software used in the test and homogeneous fatigue initiation by incorporating probabilistic models integration of the AMSU-A instruments. Author (revised) and development testing methods that address material volume and component feature effects. Complications and limitations being addressed in ongoing work are discussed. Author N94-37126 Massachusetts Inst of Tech., Cambridge. Lincoln Lab. AN AUTOMATED METHOD FOR LOW LEVEL WINDSHEAR ALERT SYSTEM (LLWAS) DATA QUALITY ANALYSIS DAVID A. CLARK and F.W.WILSON 26 May 1994 59 p Limited Reprodua'bility: More than 20% of this document may be affected by microfiche quality N94-37331# Motoren- und Turbinen-Union Muenchen G.m.b.H., (Contract DTFA01-91-Z-02036) Munich (Germany). (AD-A280313; ATC-207) Avail: Issuing Activity (Defense Technical PREDICTING DEFECT BEHAVIOUR Information Center (DTIC)) G. W. KOENIG and J. W. BERGMANN In AGARD, Impact of The Low Level Windshear Alert System (LLWAS) is an anemom- Materials Defects on Engine Structures Integrity 11 p Apr. 1993 eter-based surface network used for detection of hazardous wind shear Copyright Avail: CASI HC A03/MF A02 and acquisition of operational wind information in the airport terminal Fatigue is a statistical phenomenon with contributing factors area. The quality of wind data provided by the LLWAS anemometers is which are statistical in nature too. Therefore probabilistic lifing concepts important for the proper performance of the LLWAS wind shear appear to be appropriate. Major components of any probabilistic lifting detection algorithms. This report describes the development of an concept are: (1) microstructural characterization; (2) load history; and automated method for anemometer data quality analysis (DQA). This (3) material behavior. The results of any lifing model can only be as method identifies potential data quality problems through comparison significant as the input data. This paper reviews some important of wind data from each sensor within a network to the mean wind speed aspects regarding input data which are necessary for the prediction of and direction of the entire network. The design approach and implemen- defect behavior by probabilistic models. Author tation are described, and results from testing using data from the demonstration Phase III LLWAS network in Orlando, FL are reported. Potential improvements to the automated DQA algorithm are presented based on experience gained during analysis of the Orlando data. These recommended improvements are provided to assist future development and refinement of the DQA methodology to be performed by the N94-37457*# National Aeronautics and Space Administration. Lewis FAA Technical Center. DTIC Research Center, Cleveland, OH. DYNAMICS OF A SPLIT TORQUE HELICOPTER TRANSMISSION M.S. Thesis - Cleveland State Univ. TIMOTHY L KRANTZ Jun. 1994 69 p N94-37155* Lawrence Livermore National Lab., Uvermore, CA. (Contract DA PROJ. 1L1-62211-A-47-A; RTOP 505-62-10) PROJECT REPORT: AIRCRAFT (NASA-TM-106410; E-7881; NAS 1.15:106410; ARL-TR-291) Avail: DONALD J. WUEBBLES, STEVE BAUGHCUM, MUNIR METWALLY, CASI HC A04/MF A01 and ROBERT SEALS Apr. 1994 4 p Presented at the 4th Split torque designs, proposed as alternatives to traditional International Workshop on Global Emissions Inventories, Boulder, CO, planetary designs for helicopter main rotor transmissions, can save 30 Nov. -2 Dec. 1993 weight and be more reliable than traditional designs. This report (Contract W-7405-ENG-48) presents the results of an analytical study of the system dynamics and (DE94-011759; UCRL-JC-116530; CONF-9311208-1) Avail: CASI HC performance of a split torque gearbox that uses a balance beam A01/MF A01 mechanism for load sharing. The Lagrange method was applied to Analyses of scenarios of past and possible future emissions are develop a system of equations of motion. The mathematical model an important aspect of assessing the potential environmental effects includes time-varying gear mesh stiffness, friction, and manufacturing from aircraft including the proposed high speed civil transport (HSCT). errors. Cornell's method for calculating the stiffness of spur gear teeth The development of a detailed three-dimensional database that accu- was extended and applied to helical gears. The phenomenon of rately represents the integration of all aircraft emissions along realistic sidebands spaced at shaft frequencies about gear mesh fundamental flight paths for such scenarios requires complex computational model- frequencies was simulated by modeling total composite gear errors as ing capabilities. Such a detailed data set is required for the scenarios sinusoid functions. Although the gearbox has symmetric geometry, the evaluated in this interim assessment. Within the NASA High-Speed loads and motions of the two power paths differ. Friction must be Research Program, the Emissions Scenarios Committee provides a considered to property evaluate the balance beam mechanism. For the forum for identifying the required scenarios and evaluating the resulting design studied, the balance beam is not an effective device for load database being developed with the advanced emissions modeling sharing unless the coefficient of friction is less than 0.003. The complete capabilities at the Boeing Company and McDonnell Douglas system stiffness as represented by th stiffness matrix used in this Corporation. DOE

596 MATHEMATICAL AND COMPUTER SCIENCES 15

15 techniques. The benefits of formal methods in requirements driven software development (forward engineering') is well documented. One MATHEMATICAL AND COMPUTER SCIENCES advantage of rigorously engineering software is that formal notations are precise, verifiable, and facilitate automated processing. This paper Includes mathematical and computer sciences (general); computer describes the application of formal methods to reverse engineering, operations and hardware; computer programming and software; com- where formal specifications are developed for a portion of the shuttle on- puter systems; cybernetics; numerical analysis; statistics and probabil- orbit digital autopilot (DAP). Three objectives of the project were to: ity; systems analysis; and theoretical mathematics. demonstrate the use of formal methods on a shuttle application, facilitate the incorporation and validation of new requirements for the system, and verify the safety-critical properties to be exhibited by the A94-61255 software. Author MULTIOBJECTIVE TRAJECTORY OPTIMIZATION BY GOAL PROGRAMMING WITH FUZZY DECISIONS SHINJI SUZUKI Tokyo Univ., Tokyo (Japan) and TAKESHI N94-36498*# Reliable Software Technology Corp., Reston, VA. YOSHIZAWA Journal of Guidance, Control, and Dynamics (ISSN AN EMPIRICAL COMPARISON OF A DYNAMIC SOFTWARE 0731-5090) vol. 17, no. 2 March-April 1994 p. 297-303 refs TESTABILITY METRIC TO STATIC CYCLOMATIC (BTN-94-EIX94381311168) Copyright COMPLEXITY A sequential goal programming approach is considered for not JEFFREY M. VOAS, KEITH W. MILLER, and JEFFREY E. PAYNE only well-defined flight trajectory problems but also ill-defined problems In NASA. Goddard Space Right Center, Proceedings of the Eighteenth that have no feasible solutions satisfying all design requirements due Annual Software Engineering Workshop p 343-365 Nov. 1993 to strict boundary conditions or tight path constraints. By using a time (Contract NAG1-884) integration algorithm, trajectory optimization problems are transformed Avail: CASI HC A03/MF A04 into numerical optimization problems that seek optimal control vari- This paper compares the dynamic testability prediction technique ables at discrete time points to minimize an objective function and termed 'sensitivity analysis' to the static testability technique termed satisfy various design constraints. By defining the target goal values of cydomatic complexity. The application that we chose in this empirical both the constraints and the objective functions and by prioritizing each study is a CASE generated version of a B-737 autoland system. For the goal according to Its significance, the GP formulation modifies ill- B-737 system we analyzed, we isolated those functions that we predict defined problems as multiobjective design problems. Additionally, a are more prone to hide errors during system/reliability testing. We also fuzzy decision making method is applied for those goals that are analyzed the code with several other well-known static metrics. This prioritized, not precisely, but in a fuzzy manner. Numerical applications paper compares and contrasts the results of sensitivity analysis to the for simple ascent trajectory problems show that this method can results of the static metrics. Author efficiently find the trajectories when various kinds of design requirements are imposed for the ill-defined problem. Author (El) N94-36501** National Aeronautics and Space Administration. A94-61260 Goddard Space Right Center, Greenbelt, MD. NEW OUTPUT FEEDBACK DESIGN IN VARIABLE STRUCTURE IMPACT OF ADA IN THE FLIGHT DYNAMICS DIVISION: SYSTEMS EXCITEMENT AND FRUSTRATION WEN-JUNE WANG National Central Univ., Chung LJ (Taiwan, JOHN BAILEY (Software Metrics, Inc., Haymarket, VA.), SHARON Province of China) and YANG-TA FAN Journal of Guidance, Control, WALIGORA (Computer Sciences Corp., Lanham, MD.). and MIKE and Dynamics (ISSN 0731 -5090) vol. 17, no. 2 March-April 1994 STARK In its Proceedings of the Eighteenth Annual Software p. 337-340 refs Engineering Workshop p 422-448 Nov. 1993 (BTN-94-EIX94381311173) Copyright Avail: CASI HC A03/MF A04 This paper proposes an output feedback variable structure control In 1985, NASA Goddard's Right Dynamics Division (FDD) began to stabilize a class of uncertain systems in which the state is unavailable investigating how the Ada language might apply to their software and no estimated state is required. The special sliding hyperplane is development projects. Although they began cautiously using Ada on introduced so that the output of the system is initially on the hyperplane only a few pilot projects, they expected that, if the Ada pilots showed no matter where the initial output is, and the stability of the equivalent promising results, they would fully transition their entire development reduced-order system in the sliding mode is assured under a certain organization from FORTRAN to Ada within 10 years. However, nearly condition. Further, based on the concept of the equivalent motion and 9 years later, the FDD still produces 80 percent of its software in the known bound of the initial state, the constant control gain is derived FORTRAN, despite positive results on Ada projects. This paper reports to guarantee the existence of the sliding mode. Finally, an aircraft model preliminary results of an ongoing study, commissioned by the FDD, to is given to illustrate this design approach. Author (El) quantify the impact of Ada in the FDD, to determine why Ada has not flourished, and to recommend future directions regarding Ada Project trends in both languages are examined as are external factors and N94-36495*# Jet Propulsion Lab., California Insl of Tech., Pasa- cultural issues that affected the infusion of this technology. This paper dena, CA. is the first public report on the Ada assessment study, which will APPLYING FORMAL METHODS AND OBJECT-ORIENTED conclude with a comprehensive final report in mid 1994. ANALYSIS TO EXISTING FLIGHT SOFTWARE Author (revised) BETTY H. C. CHENG (Michigan State Univ., East Lansing, Ml.) and BRENT AUERNHEIMER (California State Univ., Fresno, CA.) In NASA. Goddard Space Right Center, Proceedings of the Eighteenth N94-36628* Universitaet der Bundeswehr Muenchen, Neubiberg Annual Software Engineering Workshop p 274-296 Nov. 1993 (Germany). Fakultaet fuer Luft-und Raumfahrttechnik. (Contract NSF CCR-92-09873) TWO-AXIS CAMERA PLATFORM FOR MACHINE VISION Avail: CASI HC A03/MF ACM J. SCHIEHLEN and E. D. DICKMANNS In AGARD, Pointing and Correctness Is paramount for safety-critical software control Tracking Systems 6 p May 1994 systems. Critical software failures in medical radiation treatment Copyright Avail: CASI HC A02/MF A02 communications, and defense are familiar to the public. The significant Mobile robots operating autonomously have to perceive their quantity of software malfunctions regularly reported to the software environment; many advantages favor using a vision sensor. The engineering community, the laws concerning liability, and a recent NRC concept of dynamic vision is an adequate solution to this problem. The Aeronautics and Space Engineering Board report additionally motivate ability to track moving objects is essential. Therefore, a two axis camera the use of error-reducing and defect detection software development platform is described having several modes of operation, which can be

597 15 MATHEMATICAL AND COMPUTER SCIENCES

mounted on a mobile robot An active vision system is presented, (NASA-CR-196135; NAS 1.26:196135; CMC-TR4.2-92-VOL-2) Avail: including the design of the pan-tilt head and the controller. Problems CASI HC A04/MF A01 arising due to image processing delays, robots' own motion and This report documents the user input and output data require- platform actuator disturbances, e.g. friction, are treated. An aircraft ments for the FEMNAS finite element Navier-Stokes code for real-gas application for vision based autonomous landing is given. Author simulations of external aerodynamics flowfields. This code was developed for the configuration aerodynamics branch of NASA ARC, under SBIR Phase 2 contract NAS2-124568 by Computational Mechanics N94-36633* British Aerospace Defence Ltd., Preston (England). Corporation (COMCO). This report is in two volumes. Volume 1 Military Aircraft Div. contains the theory for the derived finite element algorithm and de- SENSOR DATA FUSION FOR AIR TO AIR SITUATION scribes the test cases used to validate the computer program described AWARENESS BEYOND VISUAL RANGE in the Volume 2 user guide. Author (revised) C. A. NOONAN, M. E. EVERETT, and R. C. FREEMAN In AGARD, Pointing and Tracking Systems 8p May 1994 Copyright Avail: CASI HC A02/MF A02 N94-36962*# Draper (Charles Stark) Lab., Inc., Cambridge, MA. A modem tactical aircraft is faced with ever increasing threats ADVANCED INFORMATION PROCESSING SYSTEM: THE and, to be effective against them, it needs to know what and where they ARMY FAULT-TOLERANT ARCHITECTURE DETAILED are as early as possible during any encounter. It must do this day and DESIGN OVERVIEW Final Report night, in all weather, in hostile countermeasure environments and in the RICHARD E. HARPER, CAROL A. BABIKYAN, BRYAN P. BUTLER, presence of clutter. Tactical aircraft receive large amounts of informa- ROBERT J. CLASEN, CHRIS H. HARRIS, JAYNARAYAN H. LALA, tion from multiple sensors and data communications systems. To allow THOMAS K. MASOTTO, GAIL A. NAGLE, MARK J. PRIZANT, and the crew to manage the aircraft and ensure its mission is fulfilled, the STEVEN TREADWELL Jun. 1994 138 p information must be aligned, correlated, consolidated and presented to (Contract NAS1-18565; RTOP 505-64-52-53) them in a meaningful form. The paper introduces a model of tactical (NASA-CR-194924; NAS 1.26:194924) Avail: CASI HC A07/MF A02 situation awareness processing which comprises sensors, data fusion, The Army Avionics Research and Development Activity (AVRADA) situation assessment and sensor management. The purpose of each is pursuing programs that would enable effective and efficient manage- component of the model and the relationships between them are ment of large amounts of situational data that occurs during tactical discussed. The requirements placed on sensor data fusion by air to air rotorcraft missions. The Computer Aided Low Altitude Night Helicopter sensing are discussed, and so is the way in which they are dominated Right Program has identified automated Terrain Following/Terrain by particular features of the tactical aircraft platform and its mission. The Avoidance, Nap of the Earth (TFfTA, NOE) operation as key enabling influence of these factors on the design of air to air situation awareness technology for advanced tactical rotorcraft to enhance mission surviv- systems is considered. A computer test harness, developed by BAe ability and mission effectiveness. The processing of critical information Defence, Military Aircraft Division, is described, along with built-in toots at low altitudes with short reaction times is life-critical and mission- which calculate test statistics. The harness was developed as part of a critical necessitating an ultra-reliable/high throughput computing plat- program of studies carried out by the Mission Systems group of the Design Quality and R&D team within the Systems Engineering Depart- form for dependable service for flight control, fusion of sensor data, ment at BAe's Warton unit in Lancashire, U.K. Examples of the results route planning, near-field/far-field navigation, and obstacle avoidance operations. To address these needs the Army Fault Tolerant Architec- which were obtained when an air to air sensor data fusion model was ture (AFTA) is being designed and developed. This computer system evaluated are reproduced. These take the form of graphs and diagrams is based upon the Fault Tolerant Parallel Processor (FTPP) developed representing test statistics and offer a means by which different by Charles Stark Draper Labs (CSDL). AFTA is hard real-time, Byzan- solutions to various data fusion problems may be compared under tine, fault-tolerant parallel processor which is programmed in the ADA identical conditions. Author language. This document describes the results of the Detailed Design (Phase 2 and 3 of a 3-year project) of the AFTA development This document contains detailed descriptions of the program objectives, the N94-36914*# Computational Mechanics Co., Knoxville, TN. TF/TA NOE application requirements, architecture, hardware design, AN ARBITRARY GRID CFD ALGORITHM FOR operating systems design, systems performance measurements and CONFIGURATION AERODYNAMICS ANALYSIS. VOLUME 1: analytical models. Author THEORY AND VALIDATIONS Final Report A. J. BAKER, G. S. IANNELLI, PAUL D. MANHARDT, and J. A. ORZECHOWSKI Dec. 1993 179p (Contract NAS2-12568; SBIR-02.07-5494) N94-36970 AirForcelnstofTech.,Wright-PattersonAFB,OH. School (NASA-CR-195918; MAS 1.26:195918; CMC-TR2.1-94-VOL-1) Avail: of Engineering. CASf HC A09/MF A02 A MEAN VALUE ANALYSIS HEURISTIC FOR ANALYSIS OF This report documents the user input and output data require- AIRCRAFT SORTIE GENERATION M.S. Thesis ments for the FEMNAS finite element Navier-Stokes code for real-gas RICHARD C. JENKINS Mar. 1994 91 p Limited Reprodutibility: simulations of external aerodynamics flowfields. This code was devel- More than 20% of this document may be affected by microfiche quality oped for the configuration aerodynamics branch of NASA ARC, under (AD-A278578; AFIT/GOR/ENS/94M-07) Avail: CASI HC A05 SBIR Phase 2 contract NAS2-124568 by Computational Mechanics The primary objective of this study was to develop an analytical Corporation (COMCO). This report is in two volumes. Volume 1 methodology based on the Mean Value Analysis algorithm that approxi- contains the theory for the derived finite element algorithm and de- mates the performance characteristics of a queueing network model scribes the test cases used to validate the computer program described (QNM) containing a fork-join queue with probabilistic branching. These in the Volume 2 user guide. Author (revised) performance characteristics are response time, throughput and queue length at each station. The QNM solved contains the essential features of the aircraft sortie generation process. The sensitivity of the method's N94-36922** Computational Mechanics Co., Knoxville, TN. accuracy to increases in server utilization was determined. The com- AN ARBITRARY GRID CFD ALGORITHM FOR parisons of the results of the MVA heuristic to the outputs of the CONFIGURATION AERODYNAMICS ANALYSIS. VOLUME 2: Logistics Composite Model (LCOM) simulation indicate thattheheuristic's FEMNAS USER GUIDE Final Report accuracy decreased as server utilization increases. When server PAUL D. MANHARDT, J. A. ORZECHOWSKI. and A. J. BAKER utilization was kept in realistic ranges, the results of the heuristic for a Sep. 1992 63 p single fork-join queue were very accurate. For non-maintenance sta- (Contract NAS2-12568; SBIR-02.07-5494) tions, results were within 1 to 2 percent of the LCOM simulation output

598 PHYSICS 16

For stations on the forte-join queue paths, heuristic results were within N94-37344* CAE Electronics Ltd., Saint Laurent (Quebec). 5 percent of the LOOM simulation's output for that portion of the TRAINING AND OPERATIONS SUPPORT SYSTEM (TOPS) network. OTIC GUY LANGLOIS and IAN GORDON In AGARD, International High Speed Networks for Scientific and Technical Information 3 p Feb. 1994 16 Copyright Avail: CASI HC A01/MF A02 This paper describes a potential training and operations support PHYSICS system and discusses the enabling technologies that make it possible - high speed global networks, powerful computers, and an object Includes physics (general); acoustics; atomic and molecular physics; oriented data base management system (OODBMS). It illustrates a real nuclear and high-energy physics; optics; plasma physics; solid-state world example of the system using a scenario involving an aircraft physics; and thermodynamics and statistical physics. maintenance technician. Author A94-61635 COMPUTATION OF SUPERSONIC JET MIXING NOISE FOR AN AXISYMMETRIC CONVERGENT-DIVERGENT NOZZLE ABBAS KHAVARAN Sverdrup Technology, Inc., Cleveland, OH, EUGENE A. KREJSA, and CHAN M. KIM Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 3 May-June 1994 p. 603-609 rets (BTN-94-EIX94401358979) Copyright The turbulent mixing noise of a supersonic jet is calculated for an axisymmetric convergent-divergent nozzle at the design pressure ratio. Aerodynamic computations are performed using the PARC code with a k-epsilon turbulence model. LJghthill's acoustic analogy is adopted. The acoustics solution is based upon the methodology followed in the MGB code. The source correlation function is expressed as a linear combination of second-order tensors (Ribner's assumption). Assuming separable second-order correlations and incorporating Batchelor's isotropic turbulence model, the source term was calculated from the kinetic energy of turbulence. A Gaussian distribution for the time-delay of correlation was introduced. The CFD solution was used to obtain the source strength as well as the characteristic time-delay of correlation. The effect of sound/flow interaction was incorporated using the high frequency asymptotic solution to alley's equation for axisymmetric geometries. Acoustic results include sound pressure level directivity and spectra at different polar angles. The aerodynamic and acoustic results demonstrate favorable agreement with experimental data. Author (El)

A94-61854 SOUND RADIATION AND CAUSTIC FORMATION FROM A POINT SOURCE IN A WALL SHEAR LAYER I. DAVID ABRAHAMS Keele Univ, Staffordshire, United Kingdom, GREGORY A. KRIEGSMANN, and EDWARD L REISS AlAAJoumet (ISSN 0001-1452) vol. 32, no. 6 June 1994 p. 1135-1144 refs (BTN-94-EIX94421374956) Copyright The propagation of acoustic waves from a high-frequency point source in a shear layer flowing over an infinite rigid plate is considered. Stationary and moving sources are analyzed. An infinite sequence of caustic surfaces are created reflection from the wall. The acoustic fields on and off the caustics are obtained. El

N94-36622# GEC-Marconi Avionics Ltd., Basilon, Essex (England). INFRARED SEARCH AND TRACK DEMONSTRATOR PROGRAMME W. D. MCGINN, C. J.TUCKER, andS. NALLANTHIGHAL InAGARD. Pointing and Tracking Systems 10 p May 1994 Copyright Avail: CASI HC A02/MF AO 2 The objective of the infrared search and track (IRST) program is to develop demonstration hardware which will be capable of long range detection and tracking of air targets in an airborne environment This paper describes each of the major subsystems of the IRST equipment which comprises the pointing system, the thermal imaging systems and the signal processing system. The various modes of operation are outlined which provide the capability to search for, detect and track multiple targets; to display imagery of a selected target and to provide passive ranging information. The equipment will be flown in an experimental Tomacto aircraft and the installation and proposed trials are also described. A description of the ground proving equipment is also included. Author

599 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 309) October 1994

Typical Subject Index Listing AEROACOUSTICS AERODYNAMIC INTERFERENCE Computation ol supersonic jet mixing noise for an Numerical investigations on two-dimensional axisymmetric convergent-divergent nozzle canard-wing aerodynamic interference IBTN-94.EIX94401358979I p 599 A94-61635 IBTN-94-EIX94401358989I p 566 A94-61645 SUBJECT HEADING Sound radiation and caustic formation from a point AERODYNAMIC LOADS source in a wall shear layer Unsteady aerodynamic characteristics of a dual-element IBTN-94-EIX94421374956I p 599 A94-61854 airfoil Mixing and noise benefit versus thrust penalty in |BTN-94-EIX94401358968| p 565 A94-61624 ABORTED MISSIONS supersonic jets using impingement tones AERODYNAMIC NOISE — STS-55 pad abort: Engine 2011 oxidizer prebumer INASA-TM-1065831 p 568 N94-36686 Computation ol supersonic jet mixing noise for an augmented spark igniter check valve leak AERODYNAMIC CHARACTERISTICS axisymmetric convergent-divergent nozzle [NASA-CR-193830] p 138 N94-12806 Detailed flow measurements and predictions for a IBTN-94-EIX94401358979I p 599 A94-61635 three-stage transonic fan AERODYNAMIC STABILITY |BTN-94-EIX94311330096| p 587 A94-61062 Stability of skew plates subjected to aerodynamic and REPORT Chine-shaped forebody effects on directional stability in-plane forces NUMBER at high-alpha IBTN-94-EIX94321331202I p 592 A94-61615 IBTN-94-EIX94401358961 | p 579 A94-61617 Evaluation of parameter estimation methods tor unstable Chine-shaped forebody effects on directional stability at high-alpha aircraft IBTN-94-EIX94401358961 | p 579 A94-61617 IBTN-94-EIX94401358965I p 580 A94-61621 Computational study ol the F-5A forebody emphasizing The subject heading is a key to the subject Unique high-alpha roll dynamics of a sharp-edged 65 directional stability content of the document. The title is used to deg delta wing |BTN-94-EIX94401358966| p 571 A94-61622 IBTN-94-EIX94401358962I p 579 A94-61618 provide a description of the subject matter. When Laminar flow studies at Dassault Aviation: Calculations the title is insufficiently descriptive of document Unsteady aerodynamic characteristics of a dual-element and flight tests p 593 N94-3632B content, a title extension is added, separated airfoil Unsteady flow field of large-amplitude pitching airfoils IBTN-94-EIX94401358968I p 565 A94-61624 |AD-A280444| p569 N94-37219 from the title by three hyphens. The accession Preliminary piloted simulation studies of the HL-20 lifting number and the page number are included in AERODYNAMIC STALLING body New airfoil-design concept with improved aerodynamic each entry to assist the user in locating the IBTN-94-EIX94401358972I p 583 A94-61628 characteristics abstract in the abstract section. If applicable, a Wind-tunnel test techniques tor unmanned aerial vehicle IBTN-94-EIX94401372110I p 567 A94-61810 report number is also included as an aid in iden- separation investigations Unsteady flow lield of large-amplitude pitching airfoils tifying the document. Under any one subject IBTN-94-EIX94401358976I p 571 A94-61632 |AD-A280444| p 569 N94-372I9 heading, the accession numbers are arranged in Tipjet 80-inch model rotor hover test: Test no. 1198 AERODYNAMICS IAD-A279680I p 567 N94-36261 Constrained control allocation: Three-moment problem sequence. Technological challenges of High Altitude Long IBTN-94-EIX94381311172I p 579 A94-61259 Endurance unmanned configurations One-equation turbulence model for aerodynamic flows p573 N94-36323 |BTN-94-EIX94401367449| p 563 A94-61782 An aerodynamic and static-stability analysis of the Multidomain method tor several bodies in relative Hypersonic Applied Research Technology (HART) motion missile IBTN-94-EIX94401367452I p 563 A94-61785 |AD-A280631| p 568 N94-36729 Impact of Ada in the Flight Dynamics Division: Excitement and frustration p 597 N94-36501 Unsteady How field of large-amplitude pitching airfoils AEROELASTICITY IAD-A280444 | p 569 N94-37219 Comprehensive model ol anisotropic composite aircraft ABSORPTION COOLING AERODYNAMIC CONFIGURATIONS wings suitable lor aeroelastic analyses Performance and economic enhancement of Chine-shaped forebody effects on directional stability |BTN-94-EIX94401358993| p 572 A94-61649 .regeneration gas turbines through compressor inlet air at high-alpha Alleviation of whirl-flutter on a joined-wing tilt-rotor cooling IBTN-94-EIX94401358961] p 579 A94-61617 aircraft configuration using active controls IBTN-94-EIX94311331069I p 589 A94-61109 Computation of transonic flows around a | NASA-CR-1961031 p 581 N94-36436 ACCURACY wing-plus-fuselage configuration taking viscous effects and AERONAUTICS Numerical investigation of multi-element airfoils a thin separated region into account JPRS report: Central Eurasia. Aviation and | NASA-CR-1945921 p 567 N94-36394 |BTN-94-EIX94401367450| p 563 A94-61783 cosmonautics. No. 5. May 1993 ACOUSTIC PROPAGATION An arbitrary grid CFD algorithm for configuration IJPRS-UAC-94-0041 p583 N94-37000 Sound radiation and caustic formation from a point aerodynamics analysis. Volume 1: Theory and AEROSERVOELASTICITY source in a wall shear layer validations Aeroservoelastic tailoring with piezoelectric materials: IBTN-94-EIX94421374956I p 599 A94-61854 INASA-CR-1959181 p 598 N94-36914 Actuator optimization studies ACTIVE CONTROL An arbitrary grid CFD algorithm for configuration IAD-A278640I p 581 N94-36384 Active stabilization of rotating stall in a three-stage axial aerodynamics analysis. Volume 2: FEMNAS user guide Aeroservoelastic stabilization considerations for pointing compressor INASA-CR-1961351 p 598 N94-36922 and tracking systems p 594 N94-36627 |BTN-94-EIX94311330089| p 591 A94-61130 AERODYNAMIC DRAG AEROSPACE ENGINEERING Active control of wing rock using tangential leading-edge Drag and wake modification of axisymmetric bluff bodies Working group activities of AGARD propulsion and blowing using Coanda blowing energetics panel |BTN-94-EIX94401358987| p 571 A94-61643 IBTN-94-EIX94401358974] p 565 A94-61630 IBTN-94-EIX94311331062I p 589 A94-61116 Whirl-flutter suppression in advanced turboprops and Inlet drag prediction for aircraft conceptual design Possibilities and pitfalls in aerospace applications of propfans by active control techniques |BTN-94-EIX94401358981| p 565 A94-61637 titanium matrix composites p 585 N94-36650 |BTN-94-EIX94401358994| p 578 A94-61650 The case tor surface effect research, platform AEROSPACE INDUSTRY Aeroservoelastic tailoring with piezoelectric materials: applications and technology development opportunities Coping with the defense cutback Actuator optimization studies p5?3 N94-36325 IBTN-94-EIX94401216109I p 563 A94-61788 |AD-A278640| p 581 N94-36384 AEROSPACE VEHICLES AERODYNAMIC FORCES Alleviation of whirl-flutter on a joined-wing tilt-rotor Possibilities and pitfalls in aerospace applications of Stability of skew plates subjected to aerodynamic and aircraft configuration using active controls titanium matrix composites p 585 N94-36650 |NASA-CR-196103| p 581 N94-36436 in-plane torces AEROTHERMODYNAMICS IBTN-94-EIX94321331202I p 592 A94-61615 Multirate flutter suppression system design for the Mainstream ingress suppression in gas turbine disk Benchmark Active Controls Technology Wing Influence of aerodynamic forces in ice shedding cavities INASA-CR-1961121 p 581 N94-36965 | BTN-94-EIX944013589671 p 564 A94-61623 IBTN-94-EIX94311330101) p 586 A94-61057 ACTUATORS Adaptive model architecture and extended Kalman-Bucy AIR BREATHING ENGINES Aeroservoelastic tailoring with piezoelectric materials: filters Nondimensional forms for singular perturbation analyses Actuator optimization studies |BTN-94-EIX94401377806| p 592 A94-61767 • of aircraft energy climbs IAO-A278640I p 581 N94-36384 AERODYNAMIC HEATING |BTN-94-EIX94401358168| p 572 A94-61674 ADA (PROGRAMMING LANGUAGE) Analysis of hjgh speed flow, thermal and structural AIR CARGO Impact of Ada in the Flight Dynamics Division: interactions The future of large capacity/long range multipurpose Excitement and frustration p 597 N94-36501 |NASA-CR-196017| p 593 N94-36420 air cargo fleets p 573 N94-36326

A-1 AIR COOLING SUBJECT INDEX

AIR COOLING Characterisation of Fibre Reinforced Titanium Matrix Propulsion system selection for a High Altitude Long Mainstream ingress suppression in gas turbine disk Composites Endurance aircraft P 578 N94-36333 cavities IAD-A2775206I p 585 N94-36649 The STRATO 2C propulsion system: A low cost |BTN-94-EIX94311330101| p 586 A94-61057 Possibilities and pitfalls in aerospace applications of approach for a High Altitude Long Endurance aircraft Performance and economic enhancement of titanium matrix composites p 585 N94-36650 p 578 N94-36335 Characterisation of Fibre Reinforced Titanium Matrix cogeneration gas turbines through compressor inlet air Applications of Titanium Matrix Composite to large cooling airframe structure p 585 N94-36651 Composites IBTN-94-EIX94311331069I p 589 A94-61109 IAD-A2775206 I P 585 N94-36649 SCS-6 Urn) fiber reinforced titanium AIR DATA SYSTEMS Manufacture and propertfes of Sigma fibre reinforced p 585 N94-36652 Measurement uncertainty and feasibility study of a flush titanium P 585 N94-36655 airdata system lor a hypersonic flight experiment Manufacture and properties of Sigma fibre reinforced Impact of Materials Delects on Engine Structures titanium p 585 N94-36655 |NASA-TM-4627| p 569 N94-37378 Integrity AIR FLOW Defects and their effects on the integrity of nickel based |AGARD-R-790| P 595 N94-37321 Numerical investigation of multi-element airfoils aeroengine discs p 586 N94-37328 History and prognosis ol material discontinuity eflects INASA-CR.194592I p 567 N94.36394 Substantiating powder metal life methodologies for on engine components structural integrity AIR INTAKES engines P 595 N94-37330 p 595 N94-37322 Effect of pressure on second-generation pressurized Predicting defect behaviour p 596 N94-37331 Alternate melting and refining routes fluidized bed combustion plants AIRCRAFT CONTROL p 585 N94-37323 |BTN-94-EIX94311331067| p 589 A94-61I11 Optimum flight trajectory guidance based on total energy Detects and their effects on the integrity of nickel based AIR LAUNCHING control of aircraft aeroengine discs p 586 N94-37328 Wind-tunnel test techniques for unmanned aerial vehicle |BTN-94-EIX94381311167| p 579 A94-61254 Turbine disks: Lifing against defects and materials separation investigations Reduced-order H(INF) compensator design lor an development p 595 N94-37329 IBTN-94-EIX94401358976I p 571 A94-6I632 aircraft control problem Substantiating powder metal life methodologies lor AIR NAVIGATION |BTN-94-EIX94381311174| p 579 A94-61261 engines p 595 N94-37330 Landing of an unmanned helicopter on a moving Some nonmtuitive features in time-efficient attitude Predicting defect behaviour p 596 N94-37331 . platform. High accuracy navigation and tracking maneuvers of combat aircraft Fiber optic (flight quality) sensors for advanced aircraft p 576 N94-36618 IBTN-94-EIX94381311180I p 570 A94-61267 propulsion AIR POLLUTION Experimental design of H(sub infinity) weighting INASA-CR-1911951 p 577 N94-37401 Project report: Aircraft — atmospheric effects of functions for flight control systems AIRCRAFT EQUIPMENT stratospheric aircraft IBTN-94-EIX94401358163I p 580 A94-61669 Laser designation pods optimized concept for day /night |DE94-011759| p596 N94-37155 Nonlinear model-following control application to airplane operations p 594 N94-36620 AIR TO AIR REFUELING control Infrared search and track demonstrator programme EHlOt. A new helicopter capable of long range IBTN-94-EIX94401358166I p 580 A94-61672 p 599 N94-36622 missions p 574 N94.36330 Implementation of a full-envelope controller tor a AIRCRAFT FUELS In-flight refueling. Dassault Aviation research on the high-performance aircraft Advanced thermally stable, coal-derived. iel tuels Rafale aircraft p 574 N94-36341 IBTN-94-EIX94401358167I p 580 A94-61673 development program. Experiment system and model Future tanker considerations and requirements Analysis and control of bifurcation phenomena in aircraft development p 575 N94.36342 flight |AD-A278968| p 584 N94-36505 Aerial refueling interoperability from a receiver flying |BTN-94-EIX94401358169| p 572 A94-61675 AIRCRAFT GUIDANCE qualities perspective p 575 N94.36343 An empirical comparison ol a dynamic software Advanced information processing system: The Army Tanker system and technology requirements definition: testability metric to static cyclomatic complexity Fauft-Toferant Architecture detailed design overview A tanker technology road map p 575 N94.36344 p 597 N94-36498 |NASA-CR-194924| p 598 N94-36962 CC-130H(T) tactical aerial refuelling tanker development Aeroservoelastic stabilization considerations tor pointing AIRCRAFT ICING flight lest programme p 575 N94-36347 and tracking systems p 594 N94-36627 Influence of aerodynamic forces in ice shedding AIR TRAFFIC Design and evaluation of a Stochastic Optimal |BTN-94-EIX94401358967| p 564 A94-6I623 Project report: Aircraft — atmospheric effects of Feed-forward and Feedback Technology (SOFFT) flight AIRCRAFT INSTRUMENTS stratospheric aircraft control architecture Takeoff performance monitoring system display IDE94-011759I p 596 N94-37155 |NASA-TP-3419| p 582 N94-37014 options AIR TRAFFIC CONTROL Predicting the effects of unmodeled dynamics on an IBTN-94-EIX94401358988I p 577 A94-61644 An error-resistant linguistic protocol tor air traffic aircraft flight control system design using eigenspace Experimental design of H(sub infinity) weighting control assignment functions for flight control systems INASA-CR-1960981 p 570 N94-37013 | NASA-TM-45481 p 582 N94-37059 |BTN-94-EIX94401358163| p 580 A94-61669 AIR TRANSPORTATION AIRCRAFT DESIGN AIRCRAFT LANDING Mach 2 and more Inlet drag prediction for aircraft conceptual design Reduction in size and unsteadiness of VTOL ground |BTN-94-EIX94401216108| p 569 A94-61787 |BTN-94-EIX94401358981| p 565 A94-61637 vortices by ground fences The future of large capacity/long range multipurpose New airfoil-design concept with improved aerodynamic IBTN-94-EIX94401358975I p 565 A94-61631 air cargo fleets p 573 N94-36326 characteristics An empirical comparison ol a dynamic software Accomplishments under the Airport Improvement |BTN-94-EIX94401372110| p 567 A94-61810 testability metric to static cyclomatic complexity Program Recent Advances in Long Range and Long Endurance p 597 N94-36498 IAD-A280661I p 583 N94-36763 Operation of Aircraft Landing of an unmanned helicopter on a moving Analysis of vertiport studies funded by the Airport |AGARD-CP-547| p 572 N94-36321 platform. High accuracy navigation and tracking Improvement Program (AIP) High Altitude Long Endurance aircraft design studies p 576 N94.36618 I SCT-93RR-21 I p 583 N94-37424 p 572 N94-36322 AIRBORNE/SPACEBORNE COMPUTERS Laminar flow studies at Dassault Aviation: Calculations Two-axis camera platform for machine vision Advanced information processing system: The Army and flight tests p 593 N94-36328 p 597 N94-36628 Fault-Tolerant Architecture detailed design overview The convertible (helicopter/airplane) EUROFAR: AIRCRAFT MAINTENANCE INASA-CR-1949241 p 598 N94-36962 General considerations on the technical progress and on Fault diagnosis in gas turbines using a model-based AIRCRAFT ACCIDENT INVESTIGATION future advances p 574 N94-36331 technique JPRS report: Central Eurasia. Aviation and Calculations used to optimize the installation of civil |BTN-94-EIX94311331071| p 589 A94-61107 cosmonautics. No. 5. May 1993 aircraft engines p 574 N94-36332 Calculations used to optimize the installation of civil |JPRS-UAC-94-004| p583 N94-37000 Propulsion system technologies for long range and long aircraft engines p 574 N94-36332 AIRCRAFT ACCIDENTS endurance aircraft p 578 N94-36334 Aircraft battle damage repair for the 1990's and JPRS report. Central Eurasia. Aviation and Tanker system and technology requirements definition: beyond cosmonautics. No. 5. May 1993 A tanker technology road map p 575 N94-36344 |AD-A278635| p 576 N94-36465 IJPRS-UAC-94-0041 p583 N94-37000 The KDC-10 programme of the Royal Netherlands Air A mean value analysis heuristic for analysis of aircraft AIRCRAFT COMMUNICATION Force p 575 N94-36346 sortie generation An error-resistant linguistic protocol for air traffic AIRCRAFT ENGINES |AD-A278578| p 598 N94-36970 control Transfer of heat by sell-induced flow in a rotating tube Training and operations support system (TOPS) INASA-CR-1960981 p 570 N94-37013 |BTN-94-EIX94311330098| p 587 A94-61060 p 599 N94-37344 Simulation of the secondary air system of aero AIRCRAFT CONFIGURATIONS Planning German Army helicopter maintenance and Alleviation of whirl-flutter on a joined-wing tilt-rotor engines mission assignment |BTN-94-EIX94311330097| p 587 A94-61061 aircraft configuration using active controls |AD-A280483| p 564 N94-37352 Influence of high rotational speeds on heat transfer and (NASA-CR-1961031 p 581 N94-36436 oil film thickness in aero-engine bearing chambers AIRCRAFT MANEUVERS Automatic procedures lor computing complete IBTN-94-EIX94311331074) p 588 A94-61104 Some basic considerations on angles describing airplane configuration geometry from individual component Materials performance in advanced combustion flight maneuvers IBTN-94-EIX94381311179I p 570 A94-61266 descriptions systems | NASA-TM-4607 | p 568 N94-36942 |BTN-94-EIX94311331065| p 584 A94-61113 Some nonintuitrve features in time-efficient attitude AIRCRAFT CONSTRUCTION MATERIALS Working group activities of AGARD propulsion and maneuvers of combat aircraft Materials performance in advanced combustion energetics panel IBTN-94-EIX94381311180I p 570 A94-61267 systems |BTN-94-EIX94311331062| p 589 A94-61116 Range optimal trajectories for an aircraft flying in the IBTN-94-EIX94311331065I p 584 A94-61113 Stall inception and development in an axial flow vertical plane Optimisation of composite aircraft structures by direct aeroengine |BTN-94-EIX94381311181| p 571 A94-61268 manufacturing approaches p 574 N94-36327 |BTN-94-EIX94311330088| p 591 A94-61131 Significance of the dihedral effect in rapid New developments in aluminum lor aircraft and Calculations used to optimize the installation of civil fuselage-reorientation maneuvers automobiles p 584 N94-36413 aircraft engines p 574 N94-36332 |BTN-94-EIX94401358971| p571 A94-61627

A-2 SUBJECT INDEX AXIAL FLOW TURBINES

Analytic solution of the Riccati equation (or the homing Characterisation of Fibre Reinforced Titanium Matrix APPLICATIONS PROGRAMS (COMPUTERS) missile linear-quadratic control problem Composites Simulation of the secondary air system of aero IBTN.94-EIX94401358173I p 583 A94-61679 IAD-A27752061 p 585 N94-36649 engines AIRCRAFT MODELS Applications ol Titanium Matrix Composite to large |BTN-94-EIX94311330097| p 587 A94-61061 Nonlinear model-following control application to airplane airframe structure P 585 N94-36651 Buckling and vibration analysis of laminated panels using control SCS-6 (im) fiber reinforced titanium VICONOPT IBTN-94-EIX9440135B166I p 580 A94-61672 p 585 N94-36652 IBTN-94-EIX94401372105I P 592 A94-61805 Analysis and control of bifurcation phenomena in aircraft AIRLINE OPERATIONS Applying formal methods and object-oriented analysis flight The future of large capacity/long range multipurpose to existing flight software p 597 N94-36495 IBTN-94.EIX94401358169I p 572 A94-61675 air cargo (leets P 573 N94-36326 Earth Observing System/Advanced Microwave A mean value analysis heuristic lor analysis of aircraft AIRPORT PLANNING Sounding Unit-A (EOS/AMSU-A) software management sortie generation Rotorwash analysis handbook. Volume 1: Development plan IAD-A2785781 p 598 N94-36970 and analysis | NASA-CR-1893621 p 596 N94-36919 ISCT-93RR-17-VOL-1] p 567 N94-36466 AIRCRAFT PERFORMANCE APPROACH CONTROL Rotorwash analysis handbook. Volume 2: Appendixes Electric drives on the LV100 gas turbine engine Evaluation ol parameter estimation methods tor unstable ISCT-93RR-I7-VOL-2I p 567 N94-36467 aircralt IBTN-94-EIX943113310771 p 588 A94-61101 Analysis ol vertiport studies funded by the Airport |BTN-94-EIX94401358965| p 580 A94-61621 Improvement Program (AIP) ARCHITECTURE (COMPUTERS) Takeoff perlormance monitoring system display ISCT-93RR-21 | P 583 N94-37424 Advanced information processing system: The Army options AIRPORTS Faull-Tolerant Architecture detailed design overview IBTN-94-EIX94401358988I p 577 A94-61644 Accomplishments under the Airport Improvement |NASA-CR-t94924| p 598 N94-36962 Implementation of a full-envelope controller for a Program ASCENT TRAJECTORIES high-performance aircraft |AD-A280661| P 583 N94-36763 Multiobjective trajectory optimization by goal |BTN-94-EIX94401358167| p 580 A94-61673 ALGORITHMS programming with fuzzy decisions Recent Advances in Long Range and Long Endurance A model-based approach for detection of runways and IBTN-94-EIX94381311168I P 597 A94-6I255 Operation ol Aircraft other objects in image sequences acquired using an ASPECT RATIO IAGARD-CP-547I p 572 N94-36321 on-board camera Leading-edge vortex breakdown for wing planforms with AIRCRAFT RELIABILITY I NASA-CR-196424 | p 594 N94-36812 the same slenderness ratio Possibilities and pitfalls in aerospace applications of An arbitrary grid CFD algorithm for configuration IBTN-94-EIX94401358991 | p 566 A94-61647 titanium matrix composites p 585 N94-36650 aerodynamics analysis. Volume 1: Theory and ASTRONAUTICS AIRCRAFT SAFETY validations JPRS report: Central Eurasia. Aviation and Rotorwash analysis handbook. Volume 1: Development INASA-CR-1959181 p 598 N94-36914 cosmonautics. No. 5. May 1993 and analysis An arbitrary grid CFD algorithm for configuration IJPRS-UAC-94-004I p583 N94-37000 |SCT-93RR-17-VOL-1| p 567 N94-36466 aerodynamics analysis. Volume 2: FEMNAS user guide ATMOSPHERIC EFFECTS Rotorwash analysis handbook. Volume 2: Appendixes INASA-CR-1961351 p 598 N94-36922 Project report: Aircraft — atmospheric effects of ISCT-93RR-I7-VOL-2I p 567 N94-36467 ALUMINUM stratospheric aircraft AIRCRAFT STRUCTURES New developments in aluminum for aircraft and IDE94-011759I p596 N94-37155 Comprehensive model of anisotropic composite aircraft automobiles p 584 N94-36413 ATMOSPHERIC TEMPERATURE wings suitable for aeroelaslic analyses ALUMINUM ALLOYS Performance and economic enhancement of IBTN-94-EIX94401358993I p 572 A94-61649 New developments in aluminum for aircraft and cogeneration gas turbines through compressor inlet air Optimisation of composite aircraft structures by direct automobiles p 584 N94-36413 cooling manufacturing approaches p 574 N94-36327 ANALYSIS (MATHEMATICS) IBTN-94-EIX94311331069I p 589 A94-61109 Correlation of analytical and experimental hot structure Analytic solution of the Riccati equation for the homing Hunting phenomena of the balloon motions observed vibration results missile linear-quadratic control problem over Antarctica INASA-TM-1042691 p 576 N94-36644 IBTN-94-EIX94401358173I p 583 A94-61679 |BTN-94-EIX94401358969| p 571 A94-61625 Applications of Titanium Matrix Composite to large ANEMOMETERS AUTOMATIC CONTROL airframe structure p 585 N94-36651 An automated method for Low Level Windshear Alert Analysis and control of bifurcation phenomena in aircraft Literature review and preliminary studies of fretting and System (LLWAS) data quality analysis flight fretting fatigue including special applications to aircraft |AD-A280313| p 596 N94-37126 IBTN-94-EIX94401358169I p 572 A94-61675 loints ANGLE OF ATTACK An empirical comparison of a dynamic software IAD-A280310I p 594 N94-37125 Chine-shaped forebody effects on directional stability testability metric to static cyclomatic complexity AIRCRAFT SURVIVABILITY at high-alpha p 597 N94-36498 Propulsion system technologies for long range and long | BTN-94-EIX94401358961 I p 579 A94-61617 AUTOMATIC PILOTS endurance aircraft p 578 N94-36334 Computational study of the F-5A forebody emphasizing Implementation of a full-envelope controller lor a AIRFOIL OSCILLATIONS directional stability high-performance aircraft Unsteady aerodynamic characteristics of a dual-element IBTN-94-EIX94401358962I p 579 A94-61618 IBTN-94-EIX94401358167I p 580 A94-61673 airtoil Active control of wing rock using tangential leading-edge AUTOMOBILES IBTN-94-EIX94401358968I p 565 A94-61624 blowing New developments in aluminum for aircraft and Navier-Stokes computations for oscillating control |BTN-94-EIX94401358987| p 571 A94-61643 automobiles p 584 N94-36413 surfaces Leading-edge vortex breakdown for wing planforms with AUTONOMOUS NAVIGATION IBTN-94-EIX94401358983I p 566 A94-61639 the same slenderness ratio Two-axis camera platform for machine vision AIRFOIL PROFILES IBTN-94-EIX9440135B991I p 566 A94-61647 p 597 N94-36628 Design of optimized airtoils in subcritical flow New airfoil-design concept with improved aerodynamic AVIONICS IBTN-94-EIX94401358990I p 566 A94-61646 characteristics Design of a multi-channel true flat fluorescent lamp for AIRFOILS IBTN-94-EIX94401372110I p 567 A94-61810 avionic AM-LCD backlighting Influence of aerodynamic forces in ice shedding Vortex cutting by a blade. Part 1: General theory and |BTN-94-EIX94311330477| p 592 A94-61203 |BTN-94-EIX94401358967| p 564 A94-61623 a simple solution ICAAS piloted simulation results p 593 N94-36617 Unsteady aerodynamic characteristics of a dual-element IBTN-94-EIX94421374957I p 563 A94-61855 Preload release mechanism airfoil Fluctuating wall pressures near separation in highly | NASA-CASE-MSC-22327-1 | p 594 N94-36839 |BTN-94-EIX94401358968| p 565 A94-61624 swept turbulent interactions Advanced information processing system: The Army Lift enhancement of an airfoil using a Gurney flap and | BTN-94-EIX944213749581 p 563 A94-61856 Fault-Tolerant Architecture detailed design overview vortex generators Controlling forebody asymmetries in flight: Experience INASA-CR-1949241 p 598 N94-36962 |STN-94-EIX94401358970| p 565 A94-61626 with boundary layer transition strips AXES (REFERENCE LINES) Design of optimized airfoils in subcritical flow | NASA-TM-45951 p 568 N94-36944 Implementation of a full-envelope controller for a IBTN-94-EIX94401358990I p 566 A94-61646 Unsteady flow field of large-amplitude pitching airfoils high-performance aircraft Multidomain method for several bodies in relative |AD-A280444| p569 N94-37219 |BTN-94-EIX94401358167| p 580 A94-61673 motion AXIAL FLOW ANGLES (GEOMETRY) Vortex cutting by a blade. Part 1: General theory and |BTN-94-EIX94401367452| p 563 A94-61785 Some basic considerations on angles describing airplane New airfoil-design concept with improved aerodynamic a simple solution flight maneuvers characteristics |BTN-94-EIX94381311179| p 570 A94-61266 |BTN-94-EIX94421374957| p 563 A94-61855 |BTN-94-EIX94401372110| p 567 A94-61810 AXIAL FLOW TURBINES Low-dimensional description of the dynamics in ANISOTROPIC PLATES Ingestion into the upstream wheelspace of an axial Buckling and vibration analysis of laminated panels using separated flow past thick airfoils turbine stage VICONOPT |BTN-94-EIX94421374967| p 563 A94-61865 IBTN-94-EIX94311330099I p 587 A94-61059 IBTN-94-EIX94401372105I p 592 A94-61805 Numerical investigation of multi-element airfoils Comments on the development ol the early | NASA-CR-1945921 p 567 N94-36394 ANISOTROPY Westinghouse turbojets. 1941-1946 Unsteady flow field of large-amplitude pitching airfoils Comprehensive model of anisotropic composite aircraft IBTN-94-EIX94311331063I p 577 A94-61115 |AD-A280444| p 569 N94-37219 wings suitable for aeroelastic analyses Stall inception and development in an axial flow Prediction of film cooling on gas turbine airfoils IBTN-94-EIX94401358993I p 572 A94-6I649 aeroengine INASA-TM-1066531 p 579 N94-37448 ANNULAR SUSPENSION AND POINTING SYSTEM |BTN-94-EIX94311330088| p 591 A94-61131 AIRFRAME MATERIALS Large angle magnetic suspension test fixture Spanwise transport in axial-flow turbines. Part 2: High Altitude Long Endurance aircraft design studies | NASA-CR-1961381 p 583 N94-37450 Throughflow calculations including spanwise transport p 572 N94-36322 ANTARCTIC REGIONS IBTN-94-EIX94311330085I p 591 A94-61134 AIRFRAMES Hunting phenomena of the balloon motions observed Spanwise transport in axial-flow turbines. Part 1: The High Altitude Long Endurance aircraft design studies over Antarctica multistage environment p 572 N94-36322 IBTN-94-EIX94401358969I p 571 A94-61625 IBTN-94-EIX94311330084I p 592 A94-61135

A-3 AXISYMMETRIC BODIES SUBJECT INDEX

AXISYMMETRIC BODIES BOUNDARY LAYER TRANSITION Advanced thermally stable, coal-derived, jet fuels Drag and wake modification ol axisymmetric blull bodies Calculation of three-dimensional low Reynolds number development program. Experiment system and model using Coanda blowing flows development |BTN-94.EIX94401358974| p 565 A94-61630 IBTN-94-EIX94401358973I p 565 A94-61629 | AD-A278968 I P 584 N94-36505 Prediclion melhod

A-4 SUBJECT INDEX COOLING SYSTEMS

COMPRESSOR BLADES COMPUTATIONAL GEOMETRY CONTROL STABILITY Inviscid-viscous interaction method lor Automatic procedures for computing complete New output feedback design in variable structure three-dimensional inverse design of centrifugal impellers configuration geometry from individual component systems I8TN-94-EIX94311330094I p 590 A94-61125 descriptions IBTN-94-EIX94381311173I p 597 A94-61260 COMPRESSOR ROTORS | NASA-TM-46071 p 568 N94-36942 Nonlinear model-following control application to airplane Detailed flow measurements and predictions for a COMPUTATIONAL GRIDS control three-stage transonic fan Unstructured mesh quality assessment and upwind Euler IBTN-94-EIX94401358166I p 580 A94-61672 IBTN-94-EIX94311330096I p 587 A94-61062 solution algorithm validation Analysis and control of bifurcation phenomena in aircraft Advanced transonic fan design procedure based on a IBTN-94-EIX94401358985I p 592 A94-61641 flight Navier-Stokes method Two-dimensional Euler zonal method using composite IBTN-94-EIX94401358169I P 572 A94-61675 IBTN.94-EIX94311330095I p 587 A94-61063 structured and unstructured meshes CONTROL SURFACES COMPRESSORS IBTN-94-EIX94401358986I p 566 A94-61642 Constrained control allocation: Three-moment problem Ingestion into the upstream wheelspace of an axial Numerical investigation of multi-element airfoils IBTN-94-EIX94381311172I P 579 A94-61259 turbine stage I NASA-CR-1945921 p 567 N94-36394 Navier-Stokes computations for oscillating control Automatic procedures for computing complete IBTN-94-EIX94311330099I p 587 A94-61059 surfaces configuration geometry from individual component IBTN-94-EIX94401358983I p 566 A94-61639 New high-efficiency heavy-duty combustion turbine descriptions 701F CONTROL SYSTEMS DESIGN | NASA-TM-4607 | p 568 N94-36942 Constrained control allocation: Three-moment problem IBTN-94-EIX94311331073I p 588 A94-61105 Automatic computation of Euler-marching and subsonic |BTN-94-EIX94381311172| p 579 A94-61259 Performance and economic enhancement of grids tor wing-fuselage configurations New output feedback design in variable structure cogeneration gas turbines through compressor inlet air INASA-TM-45731 p 568 N94-36950 systems cooling A method for How simulation about complex geometries IBTN-94-EIX94381311173I p 597 A94-61260 IBTN-94-EIX94311331069I p 589 A94-61109 using both structured and unstructured grids Reduced-order H(INF) compensator design for an COMPUTATIONAL FLUID DYNAMICS |NASA-TM-106633| p 569 N94-372B3 aircraft control problem Inviscid-viscous interaction method lor COMPUTER AIDED DESIGN |BTN-94-EIX94381311174| p 579 A94-61261 three-dimensional inverse design ol centrifugal impellers Design of optimized airfoils in subcritical flow Approximate recovery of H-infinity loop shapes using |BTN-94-EIX94311330094| p 590 A94-61125 IBTN-94-EIX94401358990I p 566 A94-61646 fixed-order dynamic compensation Chine-shaped forebody effects on directional stability An empirical comparison of a dynamic software IBTN-94-EIX9440135B152I p 580 A94-61658 at high-alpha testability metric to static cyclomatic complexity Experimental design of H(sub infinity) weighting |BTN-94-EIX94401358961| p 579 A94-61617 p 597 N94-36498 functions for flight control systems Computational study of the F-5A forebody emphasizing IBTN-94-EIX94401358163I p 580 A94-61669 COMPUTER PROGRAMS directional stability Implementation of a full-envelope controller for a An arbitrary grid CFD algorithm for configuration IBTN-94-EIX94401358962I p 579 A94-61618 high-performance aircraft aerodynamics analysis. Volume 1: Theory and IBTN-94-EIX94401358167I p 580 A94-61673 Unsteady aerodynamic characteristics of a dual-element validations Aeroservoelastic stabilization considerations for pointing airtoil |NASA-CR-1959t8| p 598 N94-36914 and tracking systems p 594 N94-36627 |BTN-94-EIX94401358968| p 565 A94-61624 An arbitrary grid CFD algorithm for configuration Calculation of three-dimensional low Reynolds number Mixed H2/H-inlmity optimization with multiple H infinity aerodynamics analysis. Volume 2: FEMNAS user guide constraints flows INASA-CR-1961351 p 598 N94-36922 IBTN-94-EIX94401358973I p 565 A94-61629 IAD-A280572I p 581 N94-36733 COMPUTER SYSTEMS DESIGN Gain weighted eigenspace assignment Computation of three-dimensional hypersonic flows in Advanced information processing system: The Army (NASA-TM-1091301 p 581 N94-36B20 chemical nonequilibrium Fault-Tolerant Architecture detailed design overview Multirate flutter suppression system design for the |BTN-94-EIX94401358982| p 566 A94-61638 INASA-CR-1949241 p 598 N94-36962 Benchmark Active Controls Technology Wing Navier-Stokes computations for oscillating control COMPUTER TECHNIQUES INASA-CR-1961121 p 581 N94-36965 surfaces World jet airplane inventory at year-end 1993 Design and evaluation of a Stochastic Optimal IBTN-94-EIX94401358983I p 566 A94-61639 I PB94-1649931 p 569 N94-36530 Feed-forward and Feedback Technology (SOFFT) (light Prediction method for unsteady axisymmethc flow over COMPUTER VISION control architecture parachutes Two-axis camera platform for machine vision |NASA-TP-3419| p 582 N94-37014 |BTN-94-EIX94401358984| p 566 A94-61640 p 597 N94-36628 Predicting the ellects of unmodeled dynamics on an Unstructured mesh quality assessment and upwind Euler A model-based approach for detection of runways and aircraft (light control system design using eigenspace solution algorithm validation other objects in image sequences acquired using an assignment IBTN-94-EIX94401358985I p 592 A94-61641 on-board camera INASA-TM-4548I p 582 N94-37059 Two-dimensional Euler zonal method using composite | NASA-CR-196424 I p 594 N94-36812 CONTROL THEORY structured and unstructured meshes COMPUTERIZED SIMULATION New output feedback design in variable structure IBTN-94-EIX94401358986I p 566 A94-61642 Simulation of the secondary air system of aero systems Computation of transonic flows around a engines IBTN-94-EIX94381311173I p 597 A94-61260 wing-plus-fuselage configuration taking viscous effects and |BTN-94-EIX9431l330097| p 587 A94-61061 Predicting the effects of unmodeled dynamics on an a thin separated region into account aircraft flight control system design using eigenspace Models for predicting the performance ol Braylon-cycle IBTN-94-EIX94401367450I p 563 A94-61783 assignment engines Low-dimensional description of the dynamics in INASA-TM-4548I p 582 N94-37059 IBTN-94-EIX94311331072I p 589 A94-61106 separated flow past thick airfoils CONTROLLERS |BTN-94-EIX94421374967| p 563 A94-61865 Rotorwash analysis handbook. Volume 2: Appendixes Experimental design of Hfsub infinity) weighting ISCT-93RR-17-VOL-2I p 567 N94-36467 Sensitivity derivatives for three-dimensional supersonic functions for flight control systems Euler code using incremental iterative strategy Applying formal methods and object-oriented analysis IBTN-94-EIX9440135B163I p 580 A94-61669 IBTN-94-EIX94421374969I p 593 A94-61867 to existing flight software p 597 N94-36495 Implementation of a full-envelope controller for a Analysis of high speed flow, thermal and structural An arbitrary grid CFD algorithm for configuration high-performance aircraft interactions aerodynamics analysis. Volume 1: Theory and |BTN-94-EIX94401358167| p 580 A94-61673 |NASA-CR-196017| p 593 N94-36420 validations Two-axis camera platform for machine vision Experimental investigation of nozzle/plume INASA-CR-1959181 p 598 N94-36914 p 597 N94-36628 aerodynamics at hypersonic speeds An arbitrary grid CFD algorithm for configuration Design and evaluation of a Stochastic Optimal INASA-CR-1958291 p 568 N94-36687 aerodynamics analysis. Volume 2: FEMNAS user guide Feed-forward and Feedback Technology (SOFFT) flight An aerodynamic and static-stability analysis of the |NASA-CR-196135| p 598 N94-36922 control architecture Hypersonic Applied Research Technology (HART) CONFERENCES |NASA-TP-3419| p 582 N94-37014 missile Recent Advances in Long Range and Long Endurance CONVECTION |AD-A280631| p 568 N94-36729 Operation of Aircraft Spanwise transport in axial-flow turbines. Part 2: Turbulence modeling of free shear layers (or high | AGARD-CP-547 | p 572 N94-36321 Throughflow calculations including spanwise transport performance aircraft Characterisation of Fibre Reinforced Titanium Matrix IBTN-94-EIX94311330085I p 591 A94-61134 | NASA-CR-1961371 p 594 N94-36808 Composites Spanwise transport in axial-flow turbines. Part 1: The An arbitrary grid CFD algorithm for configuration |AD-A2775206| p 585 N94-36649 multistage environment aerodynamics analysis. Volume 1: Theory and |BTN-94-EIX94311330084| p 592 A94-61135 CONGRESSIONAL REPORTS CONVERGENT-DIVERGENT NOZZLES validations Accomplishments under the Airport Improvement Computation of supersonic jet mixing noise for an INASA-CR-1959181 p 598 N94-36914 Program An arbitrary grid CFD algorithm for configuration axisymmetric convergent-divergent nozzle | AD-A280661 I p 583 N94-36763 aerodynamics analysis. Volume 2: FEMNAS user guide |BTN-94-EIX94401358979| p 599 A94-61635 | NASA-CR-1961351 p 598 N94-36922 CONTROL EQUIPMENT Mixing and noise benefit versus thrust penalty in Developments in centrifugal compressor surge control: Automatic computation of Euler-marching and subsonic supersonic jets using impingement tones A technology assessment grids for wing-luselage configurations | NASA-TM-1065831 p 568 N94-36686 |BTN-94-EIX94311330090| p 590 A94-61129 INASA-TM-45731 p 568 N94-36950 COOLING Navier-Stokes and potential theory solutions for Constrained control allocation: Three-moment problem Study of rotor cavities and heat transfer in a cooling ahelicopter fuselage and comparison with experiment IBTN-94-EIX94381311172I p 579 A94-61259 process in a gas turbine | NASA-TM-45661 p 569 N94-36966 Experimental design of H(sub infinity) weighting |BTN-94-EIX94311330100| p 587 A94-61058 A fundamental study of hypersonic unstarts functions for flight control systems COOLING SYSTEMS IAD-A280506I p 595 N94-37128 IBTN-94-EIX94401358163I p 580 A94-61669 Performance and economic enhancement of A method for flow simulation about complex geometries Implementation of a full-envelope controller for a cogeneration gas turbines through compressor inlet air using both structured and unstructured grids high-performance aircraft cooling | NASA-TM-106633 I p 569 N94-37283 |BTN-94-EIX94401358167| p 580 A94-61673 IBTN-94-EIX94311331069I p 589 A94-61109

A-5 COPOLYMERS SUBJECT INDEX

COPOLYMERS Predicting defect behaviour p 596 N94-37331 DUCT GEOMETRY Replacement ol silicone polymer A with sihcone polymer DEFLECTION Experimental investigation on selecting the ramp and B and the subsequent characterization o( the new cellular Replacement of silicone polymer A with silicone polymer lip parameters ol a two-dimensional external compression silicone materials B and the subsequent characterization of the new cellular inlet |DE94-010105| p 584 N94-36474 silicone materials |BTN-94-EIX94381353570| p 577 A94-61460 CORRELATION IDE94-010105I p584 N94-36474 Swirl control in an S-duct at high angle of attack IBTN-94-EIX94421374970I p 563 A94-61868 Correlation of analytical and experimental hot structure DEFORMATION vibration results Analysis of high speed (low. thermal and structural DUCTED FLOW INASA-TM-1042691 p 576 N94-36644 interactions Swirl control in an S-duct at high angle ol attack CRACK PROPAGATION INASA-CR-1960171 p 593 N94-36420 |BTN-94-EIX94421374970| p 563 A94-61868 Literature review and preliminary studies of fretting and DYNAMIC CONTROL DEICERS fretting fatigue including special applications to aircraft Active control of wing rock using tangential leading-edge Transfer of heat by self-induced flow in a rotating tube joints blowing IBTN-94-EIX94311330098I p 587 A94-61060 |AD-A280310| p 594 N94.37125 |BTN-94-EIX94401358987| p 571 A94-61643 Defects and their effects on the integrity of nickel based DELTA WINGS DYNAMIC MODELS aeroengine discs p 586 N94-37328 Unique high-alpha roll dynamics of a sharp-edged 65 Predicting the effects of unmodeled dynamics on an Predicting defect behaviour p 596 N94-3733I deg delta wing aircraft flight control system design using eigenspace CRACKS IBTN-94-EIX94401358966I p 571 A94-61622 assignment Literature review and preliminary studies of fretting and Navier-Stokes computations for oscillating control INASA-TM-4548I p 582 N94-37059 fretting fatigue including special applications to aircraft surfaces Dynamics of a split torque helicopter transmission joints IBTN-94-EIX944013589831 p 566 A94-61639 |NASA.TM-106410| p 596 N94-37457 |AD-A280310| p 594 N94.37125 Active control ol wing rock using tangential leading-edge DYNAMIC RESPONSE CREEP STRENGTH blowing Active stabilization of rotating stall in a three-stage axial Substantiating powder metal life methodologies lor |BTN-94-EIX94401358987| p 571 A94-6I643 compressor engines p 595 N94-37330 Leading-edge vonex breakdown for wing planforms with IBTN-94-EIX94311330089I p 591 A94-61130 CROSS FLOW the same slenderness ratio DYNAMIC STABILITY Preliminary analysis lor a Mach 8 crossflow transition IBTN-94-EIX94401358991I p 566 A94-61647 Aeroservoelastic stabilization considerations for pointing experiment on the Pegasus (R) space booster DESIGN ANALYSIS and tracking systems p 594 N94-36627 |NASA-TM-104272| p 564 N94-36648 Experimental design of H(sub infinity) weighting Correlation of analytical and experimental hot structure CRYOGENIC WIND TUNNELS functions for flight control systems vibration results Aerodynamic investigation with locusing Schlieren in a IBTN-94-EIX94401358163I p 580 A94-61669 |NASA-TM-104269| p 576 N94-36644 cryogenic wina tunnel Implementation ol a lull-envelope controller lor a DYNAMIC STRUCTURAL ANALYSIS |BTN-94-EIX94421374975| p 593 A94-61873 high-performance aircraft Survey and comparison of engineering beam theories CYLINDRICAL BODIES IBTN-94-EIX94401358167I p 580 A94-61673 for helicopter rotor blades Transfer of heat by self-induced flow in a rotating tube |STN-94-EIX94401358960| p 571 A94-61616 DIELECTRICS Buckling and vibration analysis ol laminated panels using IBTN-94-EIX94311330098I p 587 A94-61060 Design of a multi-channel true flat fluorescent lamp for Drag and wake modification of axisymmetric bluff bodies VICONOPT avionic AM-LCD backlighting using Coanda blowing IBTN-94-EIX94401372105I p 592 A94.61805 IBTN-94-EIX94311330477I p 592 A94-61203 |BTN-94-EIX94401358974| p 565 A94.61630 Analysis of high speed How. thermal and structural DIESEL ENGINES Investigation ol the pan-load performance of two 1.12 interactions |NASA-CR-196017| p 593 N94-36420 MW regenerative marine gas turbines IBTN-94-EIX94311331078I p 588 A94-61100 Alleviation of whirl-flutter on a jomed-wing tilt-rotor aircraft configuration using active controls DAMAGE DIFFUSERS Turbine disks: Lifing against defects and materials Operational stability of a centrifugal compressor and its INASA-CR-1961031 p 581 N94-36436 development p 595 N94-37329 dependence on the characteristics of the DAMPING subcomponents Active stabilization of rotating stall in a three-stage axial IBTN-94-EIX94311330091 i p 590 A94-61128 compressor DIGITAL SIMULATION IBTN-94-EIX94311330089I p 591 A94-61130 Optimum flight trajectory guidance based on total energy EARTH OBSERVING SYSTEM (EOS) Earth Observing System/Advanced Microwave DASSAULT AIRCRAFT control of aircraft In-flight refueling: Dassault Aviation research on the IBTN-94-EIX94381311167| p 579 A94-61254 Sounding Unit-A (EOS/AMSU-A) sottware management plan Rafale aircraft p 574 N94-36341 DIRECTIONAL SOLIDIFICATION (CRYSTALS) INASA-CR-1893621 p 596 N94-36919 DATA ACQUISITION Process enhancements ol superalloy material Three-dimensional force data acquisition and boundary p 585 N94-37324 ECONOMICS corrections tor the Walter H. Beech Memorial 7x10 loot Performance and economic enhancement of DIRECTIONAL STABILITY low speed wind tunnel cogeneration gas turbines through compressor inlet air Chine-shaped forebody eltects on directional stability IAR93-2I p582 N94-36437 cooling at high-alpha DATA BASE MANAGEMENT SYSTEMS IBTN-94-EIX94311331069I p 589 A94-61109 IBTN-94-EIX94401358961I p 579 A94-61617 TRENDS: A flight test relational database user's guide EDUCATION Computational study of the F-5A forebody emphasizing and reference manual Training and operations support system (TOPS) |NASA-TM-108806| p 564 N94-37332 directional stability p 599 N94-37344 IBTN-94-EIX94401358962I p 579 A94-61618 DATA INTEGRATION EIGENVALUES Sensor data fusion tor air to air situation awareness DISKS Gain weighted eigenspace assignment Defects and their effects on the integrity of nickel based beyond visual range p 598 N94.36633 INASA-TM-1091301 p 581 N94-36820 aeroengine discs p 586 N94-37328 DATA REDUCTION EIGENVECTORS Turbine disks: Lifing against defects and materials Three-dimensional force data acquisition and boundary Gain weighted eigenspace assignment development p 595 N94-37329 corrections for the Walter H. Beech Memorial 7x10 foot |NASA-TM-109130| p 581 N94-36B20 low speed wind tunnel DISPLAY DEVICES EJECTION IAR93-21 p 582 N94-36437 Design ol a multi-channel true Hat fluorescent lamp for Wind-tunnel test techniques lor unmanned aerial vehicle DATA RETRIEVAL avionic AM-LCD backlighting separation investigations TRENDS: A flight test relational database user's guide IBTN-94-EIX9431133O477I p 592 A94-61203 IBTN-94-EIX94401358976I p 571 A94-61632 and reference manual DOWNTIME ELECTRIC CONNECTORS INASA-TM-108806I p 564 N94-37332 Aircraft battle damage repair for the 1990's and DC 10 AIRCRAFT Preload release mechanism beyond INASA-CASE-MSC-22327-11 p 594 N94-36839 The KDC-K) programme of the Royal Netherlands Air IAD-A2786351 p 576 N94-36465 ELECTRIC FIELDS Force p 575 N94-36346 DOWNWASH Design of a multi-channel true flat fluorescent lamp for DECISION MAKING Reduction in size and unsteadiness of VTOL ground Multiobjective trajectory optimization by goal avionic AM-LCD backlighting vortices by ground fences |BTN-94-EIX94311330477| p 592 A94-61203 programming with fuzzy decisions IBTN-94-EIX94401358975I p 565 A94-61631 ELECTRIC MOTOR VEHICLES |BTN-94-EIX94381311168| p 597 A94-61255 Rotorwash analysis handbook. Volume 1: Development DEFECTS Electric drives on the LV100 gas turbine engine and analysis |BTN-94-EIX94311331077| p 588 A94-61101 Impact ol Materials Defects on Engine Structures ISCT-93RR-17-VOL-1I p 567 N94-36466 Integrity Rotorwash analysis handbook. Volume 2: Appendixes ELECTRO-OPTICS |AGARD-R-790| p 595 N94-37321 ISCT-93RR-17-VOL-2I p 567 N94-36467 Fiber optic (flight quality) sensors for advanced aircraft History and prognosis of material discontinuity effects DRAG REDUCTION propulsion on engine components structural integrity Lift enhancement of an airfoil using a Gurney flap and INASA-CR-1911951 p 577 N94-37401 p 595 N94-37322 vortex generators ELECTRONIC CONTROL Alternate melting and refining routes IBTN-94-EIX94401358970I p 565 A94-61626 PT6 engine: 30 years of gas turbine technology p 585 N94-37323 Drag and wake modification of axisymmetric bluff bodies evolution Process enhancements of superalloy material using Coanda blowing IBTN-94-EIX94311331064I p 577 A94-61114 p 585 N94-37324 |BTN-94-EIX94401358974| p 565 A94-61630 On the generalization ol true proportional navigation Defects and their effects on the integrity of nickel based DRONE VEHICLES |BTN-94-EIX94401377808| p 570 A94-61769 aeroengine discs p 586 N94-37328 Landing of an unmanned helicopter on a moving EMBEDDING Turbine disks: Lifing against defects and materials platform. High accuracy navigation and tracking Numerical investigation ol multi-element airfoils development p 595 N94.37329 p 576 N94-36618 |NASA-CR-194592| p 567 N94-36394

A-6 SUBJECT INDEX FINITE ELEMENT METHOD

ENERGY TECHNOLOGY Capture region for true proportional navigation guidance FEASIBILITY ANALYSIS Advanced thermally stable, coal-derived, jet fuels with nonzero miss-distance The KDC-10 programme ol the Royal Netherlands Air development program. Experiment system and model IBTN-94-EIX94401358176I p 570 A94-61682 Force P 575 N94-36346 development ERROR ANALYSIS Measurement uncertainty and feasibility study of a flush IAD-A278968 | p 584 N94-36505 Assessment of weighted-least-squares-based gas path airdata system for a hypersonic flight experiment ENGINE CONTROL analysis | NASA-TM-4627 | p 569 N94-37378 Whirl-flutter suppression in advanced turboprops and IBTN-94-EIX94311331070I p 589 A94-61108 FEEDBACK CONTROL preplans by active control techniques Measurement uncertainty and feasibility study of a flush New output feedback design in variable structure |BTN-94-EIX94401358994| p 578 A94-61650 airdata system tor a hypersonic flight experiment systems Improvement ol endurance performance by periodic INASA-TM-4627 | p 569 N94-37378 IBTN-94-EIX94381311173I P 597 A94-61260 optimal control ol variable camber p 581 N94-36329 ERRORS Reduced-order H(INF) compensator design for an Measurement uncertainty and feasibility study of a flush ENGINE DESIGN aircraft control problem airdata system for a hypersonic flight experiment Advanced transonic (an design procedure based on a |BTN-94-EIX94381311174| p 579 A94-61261 | NASA-TM-4627 | p 569 N94-37378 Navier-Stokes method Approximate recovery ol H-mfinity loop shapes using ESTIMATING |BTN-94-EIX94311330095| p 587 A94-61063 fixed-order dynamic compensation Evaluation of parameter estimation methods for unstable Comments on the development ol the early IBTN-94-EIX94401358152I P 580 A94-61658 aircraft Westmghouse turtaoiets. 1941-1946 IBTN-94-EIX94401358965I P 580 A94-61621 Implementation of a full-envelope controller for a IBTN-94-EIX94311331063I p 577 A94-61115 EULER EQUATIONS OF MOTION high-performance aircraft Working group activities ol AGARD propulsion and Computation of three-dimensional hypersonic Hows in IBTN-94-EIX94401358167I p 580 A94-61673 energetics panel chemical nonequilibnum Analytic solution of the Riccati equation for the homing IBTN-94-EIX94311331062I p 589 A94-61116 IBTN-94-EIX94401358982I P 566 A94-61638 missile linear-quadratic control problem Propulsion system selection lor a High Altitude Long Unstructured mesh quality assessment and upwind Euler IBTN-94-EIX94401358173I p 583 A94-61679 Endurance aircralt p 578 N94-36333 solution algorithm validation Gam weighted eigenspace assignment Propulsion system technologies for long range and long IBTN-94-EIX94401358985I p 592 A94-61641 |NASA-TM-109130| p 581 N94-36820 endurance aircraft p 578 N94-36334 Two-dimensional Euler zonal method using composite Design and evaluation of a Stochastic Optimal The STRATO 2C propulsion system: A low cost structured and unstructured meshes Feed-forward and Feedback Technology (SOFFT) flight approach for a High Altitude Long Endurance aircraft |BTN-94-EIX94401358986| p 566 A94-61642 control architecture p 578 N94-36335 Sensitivity derivatives for three-dimensional supersonic INASA-TP-3419] p582 N94-37014 ENGINE INLETS Euler code using incremental iterative strategy Predicting the effects of unmodeled dynamics on an Research on the engineering application of the anti-swirl IBTN-94-EIX94421374969I p 593 A94-61867 aircraft flight control system design using eigenspace measures in engine/inlet compatibility A fundamental study of hypersonic unstarts assignment |BTN-94-EIX94381353571| p 577 A94-61459 IAD-A280506I p 595 N94-37128 | NASA-TM-4548 I p 582 N94-37059 EUROPEAN AIRBUS Inviscid parametric analysis of three-dimensional inlet FEEDFORWARD CONTROL performance Calculations used to optimize the installation of civil Nonlinear model-following control application to airplane IBTN-94-EIX94401358980I p 578 A94-61636 aircraft engines p 574 N94-36332 control EXHAUST EMISSION (BTN-94-EIX94401358166I p 580 A94-61672 Inlet drag prediction for aircraft conceptual design Project report: Aircraft — atmospheric effects of Design and evaluation ol a Stochastic Optimal |BTN-94-EIX94401358981| p 565 A94-61637 stratospheric aircraft Feed-forward and Feedback Technology (SOFFT) flight A fundamental study of hypersonic unstarfs IDE94-011759I p596 N94-37155 control architecture |AD-A280506| p 595 N94-37128 EXPERIMENT DESIGN INASA-TP-3419 | p 582 N94-37014 ENGINE MONITORING INSTRUMENTS Experimental design of Hlsub infinity) weighting FENCES Fault diagnosis in gas turbines using a model-based functions for flight control systems Reduction in size and unsteadiness of VTOL ground technique IBTN-94-EIX94401358163I p 580 A94-61669 vortices by ground lences IBTN-94-EIX94311331071 | p 589 A94-61107 EXTERNAL STORES IBTN-94-EIX94401358975I p 565 A94-61631 Fiber optic (flight quality) sensors lor advanced aircraft Flight test certification of a 480 gallon composite fuel FIBER COMPOSITES propulsion tankonCF-18 p 574 N94-36340 Characterisation ot Fibre Reinforced Titanium Matrix INASA-CR-1911951 p 577 N94-37401 EXTERNAL TANKS Composites ENGINE NOISE Flight test certification of a 480 gallon composite fuel |AD-A2775206| p 585 N94-36649 Mixing and noise benefit versus thrust penalty in tank on CF-18 p 574 N94-36340 SCS-6 (tm) fiber reinforced titanium supersonic jets using impingement tones p 585 N94-36652 |NASA-TM-106583| p 568 N94-36686 Manufacture and properties of sigma fibre reinforced ENGINE PARTS titanium p 585 N94-36655 Assessment of weighted-least-squares-based gas path FIBER OPTICS analysis F-18 AIRCRAFT Fiber optic (flight quality) sensors for advanced aircraft IBTN-94-EIX94311331070I p 589 A94-61108 Flight test certification of a 480 gallon composite fuel propulsion Wear-resisting oxide films for 900 C tank on CF-18 p 574 N94-36340 INASA-CR-1911951 P 577 N94-37401 IDE94-010093I p584 N94-36306 Controlling forebody asymmetries in flight: Experience FIGHTER AIRCRAFT SCS-6 (tm) fiber reinforced titanium with boundary layer transition strips Some nonmtuitive features in time-efficient attitude p 585 N94-36652 | NASA-TM-45951 p 568 N94-36944 maneuvers of combat aircraft Impact of Materials Defects on Engine Structures Fiber optic (flight quality) sensors for advanced aircraft IBTN-94-EIX94381311180I p 570 A94-61267 Integrity propulsion Nondimensional forms tor singular perturbation analyses IAGARD-R-7901 p 595 N94-37321 INASA-CR-191195] p577 N94-37401 of aircraft energy climbs History and prognosis of material discontinuity effects F-5 AIRCRAFT IBTN-94-EIX94401358168I p 572 A94-61674 on engine components structural integrity Computational study of the F-5A forebody emphasizing In-flight refueling: Dassault Aviation research on the p 595 N94-37322 directional stability Rafale aircraft p 574 N94-36341 Alternate melting and refining routes IBTN-94-EIX9440135B962I p 579 A94-61618 ICAAS piloted simulation results p 593 N94-36617 p585 N94-37323 FAILURE ANALYSIS Aeroservoelastic stabilization considerations for pointing Process enhancements ol superalloy material Fault diagnosis in gas turbines using a model-based and tracking systems p 594 N94-36627 p585 N94-37324 technique Sensor data fusion for air to air situation awareness The control of cleanness in powder metallurgy materials |BTN-94-EIX94311331071| p 589 A94-61107 beyond visual range p 598 N94-36633 for turbine disks p 586 N94-37325 Assessment of weighted-least-squares-based gas path FILAMENT WINDING Maintaining constant standards during the forging analysis Manufacture and properties of sigma fibre reinforced process p 586 N94-37326 |BTN-94-EIX94311331070| p 589 A94-61108 titanium p 585 N94-36655 Defects and their effects on the integrity of nickel based FAN BLADES FILLETS aeroengine discs p 586 N94-37328 Detailed flow measurements and predictions for a Leading-edge vortex breakdown for wing planforms with Turbine disks: Lifing against defects and materials three-stage transonic fan the same slenderness ratio development p 595 N94-37329 IBTN-94-EIX94311330096I p 587 A94-61062 IBTN-94-EIX94401358991 | p 566 A94-61647 Substantiating powder metal life methodologies for Advanced transonic fan design procedure based on a FILM COOLING engines p 595 N94-37330 Navier-Stokes method Prediction ot film cooling on gas turbine airfoils Predicting defect behaviour p 596 N94-37331 IBTN-94-EIX94311330095I p 587 A94-61063 INASA-TM-1066531 p 579 N94-37448 FILM THICKNESS ENGINE TESTS FATIGUE LIFE Influence of high rotational speeds on heat transfer and Influence of high rotational speeds on heat transfer and Literature review and preliminary studies of fretting and oil film thickness in aero-engine bearing chambers oil film thickness in aero-engine bearing chambers fretting fatigue including special applications to aircraft |BTN-94-EIX94311331074| p 588 A94-61104 |BTN-94-EIX94311331074| p 588 A94-61104 joints ENVIRONMENT EFFECTS IAD-A280310I p 594 N94-37125 FINITE DIFFERENCE THEORY Project report: Aircraft — atmospheric effects of Multidomain method for several bodies in relative Delects and their effects on the integrity of nickel based stratospheric aircraft motion aeroengine discs p 586 N94-37328 IDE94-011759I P596 N94-37155 IBTN-94-EIX94401367452I p 563 A94-61785 EQUATIONS OF MOTION Substantiating powder metal life methodologies for FINITE ELEMENT METHOD Range optimal trajectories for an aircraft flying in the engines p 595 N94-37330 Influence of high rotational speeds on heal transfer and vertical plane Predicting defect behaviour p 596 N94-37331 oil fitm thickness in aero-engine bearing chambers IBTN-94-EIX94381311181] p 571 A94-61268 FAULT TOLERANCE |BTN-94-EIX94311331074| p 588 A94-61104 Nondimensional forms for singular perturbation analyses Advanced information processing system: The Army Stability of skew plates subjected to aerodynamic and of aircraft energy climbs Fault-Tolerant Architecture detailed design overview in-plane forces IBTN-94-EIX94401358168I p 572 A94-6I674 INASA-CR-1949241 p 598 N94-36962 IBTN-94-EIX94321331202I p 592 A94-61615

A-7 FINITE VOLUME METHOD SUBJECT INDEX

Influence of aerodynamic forces in ice shedding Design and evaluation of a Stochastic Optimal Chine-shaped lorebody effects on directional stability . |BTN-94-ElX94401358967| p 564 A94-61623 Feed-forward and Feedback Technology (SOFFT) flight at high-alpha Buckling and vibration analysis of laminated panels using control architecture IBTN-94-EIX94401358961 I P 579 A94-61617 VICONOPT INASA-TP-34191 p582 N94-37014 Computational study of the F-5A forebody emphasizing IBTN-94-EIX94401372105J p 59? A94-61805 Predicting the effects of unmodeled dynamics on an directional stability Analysis of high speed flow, thermal and structural aircraft flight control system design using eigenspace IBTN-94-EIX94401358962I p 579 A94-61618 interactions assignment Prediction method for unsteady axisymmetnc flow over |NASA-CR-196017| p 593 N94-36420 | NASA-TM-4548 | p 582 N94-37059 parachutes |BTN-94-EIX94401358984| p 566 A94-61640 Correlation of analytical and experimental hot structure FLIGHT HAZARDS vibration results An automated method for Low Level Windshear Alert Numerical simulation of vortex-wedge interaction IBTN-94-EIX94421374955I p 592 A94-61853 |NASA-TM-104269| p 576 N94-36644 System (LLWAS) data quality analysis An arbitrary grid CFD algorithm for configuration |AD-A280313| p 596 N94-37126 Numerical investigation of multi-element airfoils INASA-CR-1945921 P 567 N94-36394 aerodynamics analysis. Volume 1: Theory and FLIGHT INSTRUMENTS validations An arbitrary grid CFD algorithm for configuration Takeoff performance monitoring system display INASA-CR-1959181 p 598 N94-36914 aerodynamics analysis. Volume 1: Theory and options An arbitrary grid CFD algorithm for configuration IBTN-94-EIX94401358988I p 577 A94-61644 validations aerodynamics analysis Volume 2: FEMNAS user guide INASA-CR-1959181 P 598 N94-36914 FLIGHT MECHANICS |NASA-CR-196135| p 598 N94-36922 An arbitrary grid CFD algorithm for configuration Some nonintuitive features in time-efficient attitude FINITE VOLUME METHOD aerodynamics analysis. Volume 2: FEMNAS user guide maneuvers of combat aircraft Two-dimensional Euler zonal method using composite INASA-CR-1961351 p 598 N94-36922 IBTN-94-EIX94381311180I p 570 A94-61267 structured and unstructured meshes Unsteady flow field of large-amplitude pitching airfoils |BTN-94.EIX94401358986| p 566 A94-61642 Range optimal trajectories for an aircraft flying in the |AD-A280444| p569 N94-37219 FINNED BODIES vertical plane FLOW MEASUREMENT Selection criteria for plain and segmented linned tubes |BTN-94-EIX9438131118t| p 571 A94-61268 Detailed flow measurements and predictions for a for heat recovery systems FLIGHT PATHS three-stage transonic Ian |BTN-94-ElX94311331076| p 588 A94-61102 Optimum flight trajectory guidance based on total energy IBTN-94-EIX94311330096I p 587 A94-61062 FINS control of aircraft Rotating laser-Doppler anemometry system for unsteady Selection criteria for plain and segmented finned tubes |BTN-94-EIX94381311167| p 579 A94-61254 relative flow measurements in model centrifugal for heat recovery systems Multiobjective trajectory optimization by goal impellers IBTN-94-EIX943113310761 p 588 A94-61102 programming with fuzzy decisions IBTN-94-EIX94311330092I p 590 A94-61127 fluctuating wall pressures near separation in highly IBTN-94-EIX94381311168I p 597 A94-61255 FLOW REGULATORS swept turbulent interactions Implementation of a full-envelope controller lor a Developments in centrifugal compressor surge control: |BTN-94-ElX9442137495B| p 563 A94-61856 high-performance aircraft A technology assessment An aerodynamic and static-stability analysis of the |BTN-94-EIX94401358167| p 580 A94-61673 IBTN-94-EIX94311330090I p 590 A94-61129 Hypersonic Applied Research Technology (HART) FLIGHT SAFETY FLOW STABILITY missile An automated method for Low Level Windshear Alert Stall inception and development in an axial flow |AD-A280631| p568 N94-36729 System (LLWAS) data quality analysis aeroengine FIRE CONTROL IAD-A280313I p 596 N94-37126 IBTN-94-EIX94311330088I p 591 A94-61131 Review of nonsteady flow models for compressor ICAAS piloted simulation results p 593 N94-36617 FLIGHT SIMULATION stability Aeroservoelastic stabilization considerations for pointing Preliminary piloted simulation studies of the HL-20 lifting and tracking systems p 594 N94-36627 |BTN-94-EIX94311330087| p 591 A94-61132 body FIXTURES Unstable behavior of tow and high-speed compressors IBTN-94-EIX9440135B972I p 583 A94-6162B Large angle magnetic suspension test fixture |BTN-94-EIX94311330086| p 591 A94-61133 Applying formal methods and object-oriented analysis INASA-CR-1961381 p 583 N94-37450 FLOW VELOCITY to existing flight software p 597 N94-36495 FLAPPING Mainstream ingress suppression in gas turbine disk ICAAS piloted simulation results p 593 N94-36617 Numerical investigation of multi-element airloils cavities INASA-CR-1945921 p 567 N94-36394 FLIGHT TESTS | BTN-94-EIX94311330101 I p 586 A94-61057 FLAPS (CONTROL SURFACES) Laminar flow studies at Dassault Aviation: Calculations Ingestton into the upstream wheelspace of an axial Lift enhancement of an airtorl using a Gurney Hap and and flight tests p 593 N94-36328 turbine stage vortex generators Flight test certification of a 480 gallon composite fuel IBTN-94-EIX94311330099I p 587 A94-61059 IBTN-94-EIX94401358970I p 565 A94-61626 tank on CF-18 p 574 N94-36340 Experimental investigation of the steady and unsteady FLAT PLATES CC-130H(T) tactical aerial refuelling tanker development relative flow in a model centrifugal impeller passage Buckling and vibration analysis of laminated panels using flight test programme p 575 N94-36347 IBTN-94-EIX94311330093I p 590 A94-61126 VICONOPT The reduction of takeoff ground roll by the application Operational stability of a centrifugal compressor and its IBTN-94-E.IX94401372105I p 592 A94-61805 of a nose gear jump strut dependence on the characteristics ol the FLIGHT CHARACTERISTICS |NASA-TM-108822| p 576 N94-36380 subcomponents Preliminary piloted simulation studies of the HL-20 fitting Controlling forebody asymmetries in flight: Experience | BTN-94-EIX94311330091 I p 590 A94-61128 body with boundary layer transition strips IBTN-94-EIX94401358972] p 583 A94-61628 | NASA-TM-45951 p 568 N94-36944 FLOW VISUALIZATION Mainstream ingress suppression in gas turbine disk Recent Advances in Long Range and Long Endurance TRENDS: A flight test relational database user's guide Operation of Aircraft and reference manual cavities IAGARD-CP-547I p 572 N94.36321 |NASA-TM-108806| p 564 N94-37332 |BTN-94-EIX94311330t01| p 586 A94-61057 In-flight refueling: Dassault Aviation research on the FLIGHT TIME Detailed flow measurements and predictions for a Rafale aircraft p 574 N94-36341 Technological challenges of High Altitude Long three-stage transonic fan Aerial refueling interoperability from a receiver Hying Endurance unmanned configurations IBTN-94-EIX94311330096I p 587 A94-61062 qualities perspective p 575 N94-36343 p 573 N94-36323 Aerodynamic investigation with focusing Schlieren in a Controlling forebody asymmetries in flight: Experience Future supersonic commercial transport aircraft: A cryogenic wind tunnel with boundary layer transition strips technological challenge for long haul traffic (BTN-94-EIX94421374975I p 593 A94-61873 I NASA-TM-45951 p 568 N94-36944 p 573 N94-36324 FLUID DYNAMICS FLIGHT CONTROL FLOW CHAMBERS Simulation of the secondary air system of aero Constrained control allocation: Three-moment problem Influence of high rotational speeds on heat transfer and engines |BTN-94-ElX94381311172| p 579 A94-61259 oil film thickness in aero-engine bearing chambers |BTN-94-EIX94311330097| p 587 A94-61061 Reduced-order H(INF) compensator design for an |BTN-94-EIX94311331074| p 588 A94-61104 One-equation turbulence model for aerodynamic Hows aircraft control problem FLOW CHARACTERISTICS IBTN-94-EIX94401367449I p 563 A94-61782 |BTN-94-ElX94381311174| p 579 A94-61261 An aerodynamic and static-stability analysis of the Vortex cutting by a blade. Part 1: General theory and Some nonintuitive features in time-efficient attitude Hypersonic Applied Research Technology (HART) a simple solution maneuvers of combat aircraft missile (BTN-94-EIX94421374957I p 563 A94-6I855 |BTN-94-ElX94381311180| p 570 A94-61267 |AD-A280631| p 568 N94-36729 FLUID FLOW Range optimal trajectories for an aircraft flying in the Navier-Stokes and potential theory solutions for Study of rotor cavities and heat transfer in a cooling vertical plane ahelicopter fuselage and comparison with experiment process in a gas turbine IBTN-94-EIX94381311181 | p 571 A94-61268 | NASA-TM-45661 p 569 IM94-36966 |BTN-94-EIX94311330100| p 587 A94-61058 Approximate recovery of H-infinity loop shapes using Prediction of film cooling on gas turbine airloils fixed-order dynamic compensation |NASA-TM-106653| p 579 N94-37448 Transfer ol heat by sell-induced How in a rotating tube |BTN-94-EIX943l1330098| p 587 A94-61060 IBTN-94-EIX94401358152I p 580 A94-61658 FLOW DISTRIBUTION Experimental design of H(sub infinity) weighting Study of rotor cavities and heat transfer in a cooling Computation ol transonic flows around a functions for flight control systems process in a gas turbine wing-plus-fuselage configuration taking viscous effects and |BTN-94-EIX94401358163| p 580 A94-61669 IBTN-94-EIX94311330100I p 587 A94-61058 a thin separated region into account Analysis and control of bifurcation phenomena in aircraft Experimental investigation of the steady and unsteady |BTN-94-EIX94401367450| p 563 A94-61783 Hight relative flow in a model centrifugal impeller passage FLUIDIZED BED PROCESSORS |BTN-94-ElX94401358169| p 572 A94-61675 IBTN-94-EIX94311330093I p 590 A94-61126 Effect of pressure on second-generation pressurized Improvement of endurance performance by periodic Review ol nonsteady flow models tor compressor Huidized bed combustion plants optimal control of variable camber p 581 N94-36329 stability |BTN-94-EIX94311331067| p 589 A94-61111 ICAAS piloted simulation results p 593 N94-36617 |BTN-94-ElX94311330087| p 591 A94-61132 FLUORESCENCE Advanced information processing system: The Army .Spanwise transport in axial-flow turbines. Part 1: The Design of a multi-channel true flat fluorescent lamp tor Fault-Tolerant Architecture detailed design overview multistage environment avionic AM-LCD backlighting INASA-CR-1949241 p 598 N94-36962 (BTN-94-EIX94311330084I p 592 A94-61135 |BTN-94-EIX94311330477| p 592 A94-61203

A-8 SUBJECT INDEX HEAT RESISTANT ALLOYS

FLUTTER GAS PATH ANALYSIS Dynamics ol a split torque helicopter transmission Whirl-duller suppression in advanced turboprops and Assessment of weighted-least-squares-based gas path |NASA-TM-106410| P 596 N94-37457 preplans by active control techniques analysis GOAL THEORY IBTN-94-EIX94401358994I p 578 A94-61650 IBTN-94-EIX94311331070I p 589 A94-61108 Multiobjective trajectory optimization by goal Multidomain method (or several bodies in relative GAS TURBINE ENGINES programming with tuzzy decisions motion Advanced transonic Ian design procedure based on a IBTN-94.EIX94381311168I P 597 A94-61255 IBTN-94-EIX94401367452I p 563 A94-61785 Navier-Stokes method GRAMMARS Mullirate flutter suppression system design lor the IBTN-94-EIX94311330095I p 587 A94-61063 An error-resistanl linguistic protocol lor air traflic Benchmark Active Controls Technology Wing Increased use of gas turbines as commercial marine control INASA.CR-1961121 p 581 N94-36965 engines INASA-CR-1960981 P 570 N94-37013 |BTN-94-EIX94311331080| p 588 A94-61098 FLYING PLATFORMS GRID GENERATION (MATHEMATICS) Mashproekt scientific and production association: A The case lor surface ellect research, platform Unstructured mesh quality assessment and upwind Euler designer of gas turbines for marine and industrial applications and technology development opportunities solution algorithm validation applications p 573 N94-36325 IBTN-94-EIX9440135B985I p 592 A94-61641 IBTN-94-EIX94311331079I p 588 A94-61099 Two-dimensional Euler zonal method using composite FOREBOOIES Investigation of the part-load performance of two 1.12 Chine-shaped lorebody effects on directional stability structured and unstructured meshes MW regenerative manne gas turbines |BTN-94-EIX94401358986| p 566 A94-61642 at high-alpha IBTN-94-EIX94311331078I p 588 A94-61100 IBTN-94-EIX94401358961I p 579 A94-61617 Automatic procedures lor computing complete Electric drives on the LV100 gas turbine engine configuration geometry from individual component Computational study of the F-5A lorebody emphasizing IBTN-94-EIX94311331077I p 588 A94-61101 descriptions directional stability Fault diagnosis in gas turbines using a model-based IBTN-94-EIX94401358962I p 579 A94-61618 | NASA-TM-46071 p 568 N94-36942 technique Automatic computation of Euler-marching and subsonic Eflects ol nozzle exit geometry on lorebody vortex | BTN-94-EIX94311331071 | p 589 A94-61107 grids for wing-fuselage configurations control using blowing PT6 engine: 30 years of gas turbine technology INASA-TM-45731 p 568 N94-36950 |BTN-94-EIX94401358964| p 564 A94-61620 evolution A method for How simulation about complex geometries Controlling lorebody asymmetries in Ilight: Experience |BTN-94-EIX94311331064| p 577 A94-61114 using both structured and unstructured grids with boundary layer transition strips Working group activities of AGARD propulsion and |NASA-TM-106633| p 569 N94-37283 INASA-TM-45951 p 568 N94-36944 energetics panel GROUND EFFECT (AERODYNAMICS) FORGING IBTN-94-EIX94311331062I p 589 A94-61116 The case lor surface effect research, platform Maintaining constant standards during the forging Defects and their effects on the integnty of nickel based applications and technology development opportunities process p 586 N94-37326 aeroengine discs p 586 N94-37328 p 573 N94-36325 FORMALISM Turbine disks: Lifing against delects and materials Rotorwash analysis handbook. Volume 1: Development Applying formal methods and object-oriented analysis development p 595 N94-37329 and analysis to existing flight software p 597 N94-36495 Substantiating powder metal lite methodologies lor ISCT-93RFt-17-VOL.il p 567 N94-36466 engines p 595 N94-37330 FRACTURE MECHANICS Rotorwash analysis handbook Volume 2: Appendixes Detects and their effects on the integrity of nickel based GAS TURBINES ISCT-93RR-17-VOL-2I p 567 N94-36467 Mainstream ingress suppression in gas turbine disk aeroengine discs p 586 N94-37328 GROUND SUPPORT SYSTEMS cavities Planning German Army helicopter maintenance and Predicting detect behaviour p 596 N94-37331 IBTN-94-EIX94311330101 I p 586 A94-61057 FRACTURE STRENGTH mission assignment Study of rotor cavities and heat transfer in a cooling |AD-A280483| p 564 N94-37352 Substantiating powder metal lite methodologies for process in a gas turbine engines p 595 N94-37330 GUIDANCE (MOTION) IBTN-94-EIX94311330100I p 587 A94-61058 Capture region for true proportional navigation guidance FRETTING Ingestion into the upstream wheelspace of an axial with nonzero miss-distance Literature review and preliminary studies of fretting and turbine stage IBTN-94-EIX94401358176I p 570 A94-61682 fretting fatigue including special applications to aircraft IBTN-94-EIX94311330099I p 587 A94-61059 On the generalization of true proportional navigation joints Increased use of gas turbines as commercial marine |BTN-94-EIX94401377808| p 570 A94-61769 IAD-A2803IOI p 594 N94-37125 engines FRICTION |BTN-94-EIX94311331080| p 588 A94-61098 Dynamics of a split torque helicopter transmission Mashproekt scientific and production association: A H INASA-TM-1064101 p 596 N94-37457 designer ol gas turbines lor marine and industrial FUEL CELLS applications H-INFINITY CONTROL Propulsion system selection lor a High Altitude Long IBTIM-94-EIX94311331079I p 588 A94-61099 Reduced-order H(INF) compensator design lor an Endurance aircraft p 578 N94-36333 Investigation of the part-load performance of two 1.12 aircraft control problem FUEL COMBUSTION MW regenerative marine gas turbines |BTN-94-EIX94381311174| p 579 A94-61261 Effect of pressure on second-generation pressurized | BTN-94-EIX943113310781 p 588 A94-61100 Approximate recovery of H-infinity loop shapes using fluidized bed combustion plants Electric drives on the LV100 gas turbine engine fixed-order dynamic compensation |BTN-94-EIX94311331067| p 589 A94-61111 |BTN-94-EIX94311331077| p 588 A94-61101 IBTN-94-EIX94401358152I p 580 A94-61656 New high-efficiency heavy-duty combustion turbine Materials perlormance in advanced combustion Experimental design of H(sub infinity) weighting systems 701F functions for flight control systems IBTN-94-EIX94311331065I p 584 A94-61113 IBTN-94-EIX94311331073I p 588 A94-61105 IBTN-94-EIX94401358163I p 580 A94-61669 FUEL CONSUMPTION Models for predicting the performance of Brayton-cycle Mixed H2/H-inlmiiy optimization with multiple H inlmity PT6 engine: 30 years ol gas turbine technology engines constraints evolution IBTN-94-EIX94311331072I p 589 A94-61106 IAD-A280572I P 581 N94-36733 |BTN-94-EIX9431133!064| p 577 A94-61114 Assessment of weighted-least-squares-based gas path HANDBOOKS FUEL INJECTION analysis Rotorwash analysis handbook. Volume 1: Development |BTN-94-EIX94311331070| p 589 A94-61108 Comments on the development of the early and analysis Westinghouse turbojels. 1941-1946 Perlormance and economic enhancement of ISCT-93RR-17-VOL-1 | p 567 N94-36466 [BTN-94-EIX94311331063I p 577 A94-61115 cogeneration gas turbines through compressor inlet air Rotorwash analysis handbook. Volume 2: Appendixes cooling FUNCTIONAL DESIGN SPECIFICATIONS |SCT-93HR-17-VOL-2| p 567 N94-36467 |BTN-94-EIX94311331069| p 589 A94-61109 Experimental design of H(sub infinity) weighting HARMONICS functions for flight control systems Ellect of pressure on second-generation pressurized Active stabilization of rotating stall in a three-stage axial fluidized bed combustion plants IBTN-94-EIX94401358163I p 580 A94-61669 compressor |BTN-94-EIX94311331067| p 589 A94-61111 FUSELAGES IBTN-94-EIX94311330089I p 591 A94-61130 PT6 engine: 30 years ol gas turbine technology Computation of transonic flows around a HASTELLOY (TRADEMARK) evolution wing-plus-tuselage configuration taking viscous effects and Analysis ol high speed flow, thermal and structural |BTN-94-EIX94311331064| p 577 A94-61114 a thin separated region into account interactions Working group activities of AGARD propulsion and |BTN-94-EIX94401367450| p 563 A94-61783 |NASA-CR-196017| p 593 N94-36420 energetics panel Navier-Stokes and potential theory solutions for HEAD-UP DISPLAYS IBTN-94-EIX94311331062] p 589 A94-61116 ahelicopter fuselage and comparison with experiment Takeolf performance monitoring system display Prediction of film cooling on gas turbine airfoils |NASA-TM-4566| p 569 N94-36966 options INASA-TM-1066531 p 579 N94-37448 FUZZY SYSTEMS IBTN-94-EIX94401358988] p 577 A94-61644 GAS-SOLID INTERACTIONS Multiobjective trajectory optimization by goal HEAT EXCHANGERS Numerical simulation of vortex-wedge interaction programming with fuzzy decisions Selection criteria tor plain and segmented finned tubes IBTN-94-EIX94421374955I p 592 A94-61853 IBTN-94-EIX94381311168I p 597 A94-61255 for heat recovery systems GEAR TEETH IBTN-94-EIX94311331076I p 588 A94-61102 Window functions for the calculation of the time domain HEAT FLUX averages ol the vibration of the individual planet gears Selection criteria for plain and segmented tinned tubes and sun gear in an epicyclic gearbox for heat recovery systems GAS COMPOSITION |BTN-94-EIX94311331047| p 586 A94-61050 IBTN-94-EIX94311331076I p 588 A94-61102 Ingestion into the upstream wheelspace of an axial Dynamics of a split torque helicopter transmission HEAT RESISTANT ALLOYS turbine stage |NASA-TM-106410| p 596 N94-37457 Alternate melting and refining routes |BTN-94-EIX94311330099| p 587 A94-61059 GEARS p 585 N94-37323 GAS DYNAMICS Window functions for the calculation of the time domain Process enhancements of superalloy material Ingestion into the upstream wheelspace ol an axial averages of the vibration of the individual planet gears pSBS N94-37324 turbine stage and sun gear in an epicyclic gearbox Maintaining constant standards during the forging |BTN-94-EIX94311330099| p 587 A94-61059 IBTN-94-EIX94311331047I p 586 A94-61050 process P 586 N94-37326

A-9 HEAT STORAGE SUBJECT INDEX

Substantiating powder metal life methodologies for HOLLOW CATHODES INERTIAL NAVIGATION engines p 595 N94-37330 Design of a multi-channel true flat fluorescent lamp for Landing of an unmanned helicopter on a moving HEAT STORAGE avionic AM-LCD backlighting platform High accuracy navigation and tracking Performance and economic enhancement of IBTN-94-EIX94311330477I p 592 A94-61203 p 576 N94-36618 cogeneration gas turbines through compressor inlet air HOLOGRAPHY INFORMATION SYSTEMS cooling Detailed flow measurements and predictions for a Advanced information processing system: The Army IBTN-94-EIX94311331069I p 589 A94-61109 three-stage transonic tan Fault-Tolerant Architecture detailed design overview HEAT TRANSFER IBTN-94-EIX94311330096I p 587 A94-61062 |NASA-CR-194924| p 598 N94-36962 Training and operations support system (TOPS) Study of rotor cavities and heat transfer in a cooling HOMING DEVICES p 599 N94-37344 process in a gas turbine Analytic solution of the Riccati equation for the homing IBTN-94-EIX94311330100I p 587 A94-61058 missile linear-quadratic control problem INFRARED IMAGERY Infrared search and track demonstrator programme Transfer of heat by self-induced flow in a rotating tube IBTN-94-EIX94401358173I p 583 A94-61679 p599 N94-36622 IBTN-94-EIX94311330098I p 587 A94-61060 HOT ISOSTATIC PRESSING INFRARED TRACKING Influence of high rotational speeds on heat transfer and Manufacture and properties of Sigma fibre reinforced Inlrared search and track demonstrator programme oil film thickness in aero-engine bearing chambers titanium p 585 N94-36655 |8TN-94-EIX94311331074| p 588 A94-61104 p 599 N94-36622 Analysis of high speed flow, thermal and structural HOVERING INLET FLOW Reduction in size and unsteadiness of VTOL ground interactions Research on the engineering application of the anti-swirl |NASA-CR-196017| p 593 N94-36420 vortices by ground fences measures in engme/mlei compatibility IBTN-94-EIX94401358975I p 565 A94-61631 Preliminary analysis for a Mach 8 crossflow transition |BTN-94-EIX94381353571| p 577 A94-61459 experiment on the Pegasus (R) space booster Tipiet 80-inch model rotor hover test: Test no. 1198 Experimental investigation on selecting the ramp and INASA-TM-1042721 p 564 N94-36648 IAD-A279680I p 567 N94-36261 lip parameters of a two-dimensional external compression Prediction of film cooling on gas turbine airfoils HYPERPLANES inlet INASA-TM-1066531 p 579 N94-37448 New output feedback design in variable structure IBTN-94-EIX94381353570I P 577 A94-61460 HEAT TRANSFER COEFFICIENTS systems Inviscid parametric analysis of three-dimensional inlet Selection criteria for plain and segmented finned tubes IBTN-94-EIX94381311173I P 597 A94-61260 performance for heat recovery systems HYPERSONIC FLIGHT |BTN-94-EIX94401358980| p 578 A94-61636 IBTN-94-EIX94311331076I p 588 A94-61102 Measurement uncertainty and feasibility study of a Hush Inlet drag prediction lor aircraft conceptual design HEAT TRANSMISSION airdata system for a hypersonic flight experiment IBTN-94-EIX94401358981 | p 565 A94-61637 Transfer of heat by self-induced flow in a rotating tube I NASA-TM-4627 | p 569 N94-37378 Boundary conditions tor unsteady supersonic inlet IBTN-94-EIX9431133009BI p 587 A94-61060 HYPERSONIC FLOW analyses HELICOPTER CONTROL Computation of three-dimensional hypersonic flows in |BTN-94-EIX94421374964| p 593 A94-61862 Landing of an unmanned helicopter on a moving chemical nonequilibrium Swirl control in an S-ducI at high angle of attack platform. High accuracy navigation and tracking IBTN-94-EIX944013589B2I p 566 A94-61638 |BTN-94-EIX94421374970| p 563 A94-61868 p576 N94-36618 Fluctuating wall pressures near separation in highly INLET PRESSURE HELICOPTER DESIGN swept turbulent interactions Experimental investigation on selecting the ramp and EH101: A new helicopter capable of long range IBTN-94-EIX94421374958I p 563 A94-61856 lip parameters of a two-dimensional external compression missions p 574 N94-36330 inlet A fundamental study of hypersonic unstarts IBTN-94-EIX94381353570I p 577 A94-61460 HELICOPTER PROPELLER DRIVE IAD-A280506I p 595 N94-37128 Dynamics of a split torque helicopter transmission INLET TEMPERATURE HYPERSONIC INLETS INASA-TM-1064101 p 596 N94-37457 Effect of pressure on second-generation pressurized A fundamental study of hypersonic unstarts HELICOPTER WAKES fluidized bed combustion plants IAD-A280506I p 595 N94-37128 Rotorwash analysis handbook. Volume 1: Development |BTN-94-EIX94311331067| p 589 A94-61111 and analysis HYPERSONIC SPEED Preliminary analysis for a Mach 8 crossflow transition INSTALLING ISCT-93RR-17-VOL-1 | p 567 N94-36466 Calculations used to optimize the installation of civil experiment on the Pegasus (R) space booster Rotorwash analysis handbook. Volume 2: Appendixes aircraft engines p 574 N94-36332 INASA-TM-1042721 p 564 N94-36648 ISCT-93RR-17-VOL-2I p 567 N94-36467 INTAKE SYSTEMS An aerodynamic and static-stability analysis of the HELICOPTERS Swirl control in an S-duct at high angle of attack Window functions for the calculation of the time domain Hypersonic Applied Research Technology (HART) IBTN-94-EIX94421374970I p 563 A94-61868 averages of the vibration of the individual planet gears missile and sun gear in an epicycltc gearbox IAD-A280631I p 568 N94-36729 INTERACTIONAL AERODYNAMICS Numerical simulation of vortex-wedge interaction | BTN-94-EIX94311331047| p 586 A94-61050 HYPERSONIC VEHICLES |BTN-94-EIX94421374955| p 592 A94-61853 EH101: A new helicopter capable of long range Applications of Titanium Matrix Composite to large missions p 574 N94-36330 airframe structure p 585 N94-36651 Fluctuating wall pressures near separation in highly swept turbulent interactions Navier-Stokes and potential theory solutions for HYPERSONICS ahelicopter fuselage and comparison with experiment Nondimensional forms for singular perturbation analyses |BTN-94-EIX94421374958| p 563 A94-61856 INASA-TM-45661 p 569 N94-36966 of aircraft energy climbs INTERNAL COMBUSTION ENGINES HELIPORTS IBTN-94-EIX94401358168I p 572 A94-61674 Propulsion system selection for a High Altitude Long Rotorwash analysis handbook. Volume 1: Development Experimental investigation of nozzle/plume Endurance aircraft p 578 N94-36333 and analysis aerodynamics at hypersonic speeds INVENTORIES ISCT-93RR-17-VOL-1] p 567 N94-36466 INASA-CR-1958291 p 568 N94-36687 World jet airplane inventory at year-end 1993 Rotorwash analysis handbook. Volume 2: Appendixes |PB94-164993| p569 N94-36530 ISCT-93RR-17-VOL-2I p 567 N94-36467 INVISCID FLOW Analysis of vertiport studies funded by the Airport Advanced transonic fan design procedure based on a Improvement Program (AIP) Navier-Stokes method ISCT-93RR-21I p 583 N94-37424 ICE IBTN-94-EIX94311330095I p 587 A94-61063 HEURISTIC METHODS Influence of aerodynamic forces in ice shedding Inviscid parametnc analysis of three-dimensional inlet A mean value analysis heuristic (or analysis of aircraft IBTN-94-EIX94401358967I p 564 A94-61623 performance sortie generation ICE PREVENTION IBTN-94-EIX94401358980I p 578 A94-61636 IAD-A2785781 p 598 N94-36970 Transfer of heat by self-induced flow in a rotating tube One-equation turbulence model for aerodynamic flows HIGH ALTITUDE IBTN-94-EIX94311330098I p 587 A94-61060 IBTN-94-EIX94401367449I p 563 A94-61782 High Altitude Long Endurance aircraft design studies IMAGE ANALYSIS Computation of transonic flows around a p 572 N94-36322 A model-based approach tor detection of runways and wing-plus-fuselage configuration taking viscous effects and Technological challenges of High Altitude Long other objects in image sequences acquired using an a thin separated region into account Endurance unmanned configurations on-board camera |BTN-94-EIX94401367450| p 563 A94.61783 p 573 N94-36323 INASA-CR-1964241 p 594 N94-36812 ITERATIVE SOLUTION HIGH STRENGTH ALLOYS IMPELLERS Substantiating powder metal file methodologies for Inviscid-viscous interaction method for Sensitivity derivatives for three-dimensional supersonic engines p 595 N94-37330 three-dimensional inverse design of centrifugal impellers Euler code using incremental iterative strategy HIGH TEMPERATURE |BTN-94-EIX94311330094| p 590 A94-61125 |BTN-94-EIX94421374969| p 593 A94-61867 Performance and economic enhancement of Operational stability of a centrifugal compressor and its cogeneration gas turbines through compressor inlet air dependence on the charactenstics of the cooling subcomponents |BTN-94-EIX94311331069| p 589 A94-61109 IBTN-94-EIX94311330091 | p 590 A94-61128 Wear-resisting oxide films tor 900 C IMPINGEMENT JET AIRCRAFT IDE94-010093I P584 N94-36306 Numerical simulation of vortex-wedge interaction World jet airplane inventory at year-end 1993 Correlation of analytical and experimental hot structure IBTN-94-EIX94421374955I p 592 A94-61853 |PB94-164993| p 569 N94-36530 vibration results INCLUSIONS JET ENGINE FUELS INASA-TM-1042691 p 576 N94-36644 The control of cleanness in powder metallurgy materials Advanced thermally stable, coal-derived, jet fuels HIGH TEMPERATURE GASES for turbine disks P 586 N94-37325 development program. Experiment system and model Mainstream ingress suppression in gas turbine disk INCOMPRESSIBLE FLOW development cavities Low-dimensional description of the dynamics in IAD-A278968I p 584 N94-36505 I BTN-94-EIX94311330101 I p 586 A94-61057 separated flow past thick airfoils JET ENGINES Effect of pressure on second-generation pressurized I8TN-94-EIX94421374967I p 563 A94-61865 Assessment of weighted-least-squares-based gas path fluidized bed combustion plants Numerical investigation of multi-element airfoils analysis |BTN-94.EIX94311331067| p 589 A94-61111 INASA-CR-1945921 p 567 N94-36394 |BTN-94-EIX943l1331070| p 589 A94-61108

A-10 SUBJECT INDEX MARINE PROPULSION

Impact ol Materials Delects on Engine Structures LASER GUIDANCE LINEAR EQUATIONS Integrity Laser designation pods optimized concept for day/night Sensitivity derivatives for three-dimensional supersonic I AGARD.R-7901 p 595 N94-37321 operations p 594 N94-36620 Euler code using incremental iterative strategy History and prognosis ol material discontinuity effects LASER INTERFEROMETRY IBTN-94-EIX94421374969I P 593 A94-61867 on engine components structural integrity Laser interferometer skin-friction measurements of LINEAR PROGRAMMING P 595 N94-37322 crossing-shock-wave/turbulent-boundary-layer Multiobjective trajectory optimization by goal JET IMPINGEMENT ns programming with fuzzy decisions Reduction in size and unsteadiness ol VTOL ground |BTN-94-EIX94421374974| p 593 A94-61872 IBTN-94-EIX94381311168I P 597 A94-61255 vortices by ground fences LASER RANGER/TRACKER LINEAR QUADRATIC GAUSSIAN CONTROL IBTN-94-EIX94401358975I P 565 A94-61631 Landing of an unmanned helicopter on a moving Analytic solution ol the Riccati equation for the homing Mixing and noise benefit versus thrust penalty in platform. High accuracy navigation and tracking missile linear-quadratic control problem supersonic /els using impingement tones p 576 N94-36618 IBTN-94-EIX94401358173I p 583 A94-61679 INASA-TM-1065831 p 568 N94-36686 LASER TARGET DESIGNATORS LINGUISTICS Laser designation pods optimized concept for day/night Turbulence modeling ol Iree sneat layers for high An error-resistant linguistic protocol for air traffic operations p 594 N94-36620 performance aircraft control LATERAL CONTROL INASA-CR-1961371 p 594 N94-36808 INASA-CR-1960981 p 570 N94-37013 Some nonintuttive features in time-efficient attitude JET MIXING FLOW LIQUID CRYSTALS maneuvers of combat aircraft Computation of supersonic iet mixing noise lor an Design ol a multi-channel true flat fluorescent lamp for IBTN-94-EIX94381311180I p 570 A94-61267 avionic AM-LCD backlighting axisymmetric convergent-divergent nozzle Active control of wing rock using tangential leading-edge |BTN-94-EIX94401358979| p 599 A94-61635 |BTN-94-EIX94311330477| p 592 A94-61203 blowing LOADS (FORCES) Mixing and noise benefit versus thrust penalty in |BTN-94-EIX94401358987| p 571 A94-61643 supersonic jets using impingement tones Replacement of silicone polymer A with silicone polymer LATERAL STABILITY B and the subsequent characterization of the new cellular |NASA-TM-106583| p 568 N94-36686 Significance of the dihedral effect in rapid JET NOZZLES silicone materials fuselage-reorientation maneuvers IDE94-010105I p5B4 N94-36474 Tipjet- 80-inch model rotor hover test: Test no. 1198 IBTN-94-EIX94401358971 | p 571 A94-61627 Predicting defect behaviour p 596 N94-37331 IAD-A279680I p 567 N94-36261 LAY-UP JET PROPULSION Dynamics of a split torque helicopter transmission Manufacture and properties of Sigma fibre reinforced INASA-TM-106410) p 596 N94-37457 Comments on the development of the early titanium p 585 N94-36655 Westinghouse turboiets. 1941-1946 LOGISTICS LEADING EDGE SLATS A mean value analysis heuristic for analysis of aircraft IBTN-94-EIX94311331063I p 577 A94-61115 Unsteady aerodynamic characteristics of a dual-element JET THRUST sortie generation airfoil IAD-A278578I p 598 N94-36970 Mixing and noise benefit versus thrust penalty in IBTN-94-EIX94401358968I p 565 A94-61624 supersonic jets using impingement tones LOW REYNOLDS NUMBER LEADING EDGE SWEEP Calculation of three-dimensional low Reynolds number INASA-TM-1065831 p 568 N94-36686 Inviscid parametric analysis of three-dimensional inlet JOINED WINGS flows performance IBTN-94-EIX94401358973I P 565 A94-61629 Alleviation of whirl-flutter on a joined-wing tilt-rotor IBTN-94-EIX94401358980I p 578 A94-61636 aircraft configuration using active controls LOW SPEED WIND TUNNELS LEADING EDGES Three-dimensional force data acquisition and boundary INASA-CR-1961031 p 581 N94-36436 Leading-edge vortex breakdown tor wing planforms with JOINTS (JUNCTIONS) corrections for the Walter H. Beech Memorial 7x10 loot the same slenderness ratio low speed wind tunnel Literature review and preliminary studies of fretting and IBTN-94-EIX94401358991 | p 566 A94-61647 fretting fatigue including special applications to aircraft IAR93-2I p582 N94-36437 LEAST SQUARES METHOD LUBRICATION joints Assessment of weighted-least-squares-based gas path IAD-A280310I p 594 N94-37125 Influence of high rotational speeds on heat transfer and analysis oil film thickness in aero-engine bearing chambers IBTN-94-EIX94311331070I p 589 A94-61108 IBTN-94-EIX94311331074I p 588 A94-61104 K LIAPUNOV FUNCTIONS LUMINAIRES Nonlinear model-following control application to airplane Design of a multi-channel true flat fluorescent lamp tor K-EPSILON TURBULENCE MODEL control avionic AM-LCD backlighting Turbulence modeling of free shear layers lor high |BTN-94-EIX94401358166| p 580 A94-61672 I BTN-94-EIX94311330477 | p 592 A94-61203 performance aircraft LIFE (DURABILITY) LUMINANCE |NASA-CR-196137| p 594 N94-36808 Propulsion system technologies for long range and long Design of a multi-channel true flat fluorescent lamp for KALMAN FILTERS endurance aircraft p 578 N94-36334 avionic AM-LCD backlighting Adaptive model architecture and extended Kalman-Bucy Characterisation of Fibre Reinforced Titanium Matrix |BTN-94-EIX94311330477| p 592 A94-61203 fillers Composites LUMINOSITY |BTN-94-EIX94401377806| p 592 A94-61767 IAD-A2775206I p 585 N94-36649 Design of a multi-channel true flat fluorescent lamp tor LIFT avionic AM-LCD backlighting Lift enhancement of an airfoil using a Gumey flap and |BTN-94-EIX94311330477| p 592 A94-61203 vortex generators LABYRINTH SEALS IBTN-94-EIX94401358970I p 565 A94-61626 M Mainstream ingress suppression in gas turbine disk New airfoil-design concept with improved aerodynamic characteristics cavities MACH NUMBER |BTN-94-EIX94401372110| p 567 A94-61810 |BTN-94-EIX94311330101| p 586 A94-61057 Unsteady blade pressures on a propfan: Predicted and LAMINAR FLOW LIFT DEVICES measured compressibility effects Laminar flow studies at Dassault Aviation: Calculations Lift enhancement of an airfoil using a Gurney flap and |BTN-94-EIX94401358996| p 578 A94-61652 and flight tests p 593 N94-36328 vortex generators Implementation of a full-envelope controller for a LAMINATES IBTN-94-EIX94401358970I p 565 A94-61626 high-performance aircraft Buckling and vibration analysis of laminated panels using Aeroservoelastic tailoring with piezoelectric materials: I BTN-94-EIX94401358167 | p 580 A94-61673 VICONOPT Actuator optimization studies MAGNETIC BEARINGS |BTN-94-EIX94401372105| p 592 A94-61805 IAD-A278640I p 581 N94-36384 Large angle magnetic suspension test fixture Applications of Titanium Matrix Composite to large LIFT DRAG RATIO INASA-CR-1961381 p 583 N94-37450 airframe structure p 585 N94-36651 Design of optimized airfoils in subcritical flow MAGNETIC SUSPENSION LANDING AIDS IBTN-94-EIX94401358990I p 566 A94-61646 Large angle magnetic suspension test fixture An empirical comparison of a dynamic software New airfoil-design concept with improved aerodynamic INASA-CR-1961381 P 583 N94-37450 testability metric to static cyclomatic complexity' characteristics MANAGEMENT PLANNING P 597 N94-36498 |BTN-94-EIX94401372110| p 567 A94-61810 Earth Observing System/Advanced Microwave LASER ANEMOMETERS Improvement of endurance performance by periodic Sounding Unit-A (EOS/AMSU-A) software management Rotating laser-Doppler anemometry system for unsteady optimal control of variable camber p 581 N94-36329 plan relative How measurements in model centrifugal Numerical investigation of multi-element airfoils INASA-CR-1893621 p 596 N94-36919 impellers INASA-CR-1945921 p 567 N94-36394 MANUFACTURING IBTN-94.EIX94311330092I p 590 A94-61127 Optimisation of composite aircraft structures by direct LASER APPLICATIONS LIFTING BODIES manufacturing approaches p 574 N94-36327 Preliminary piloted simulation studies of the HL-20 lifting Mainstream ingress suppression in gas turbine disk Manufacture and properties of Sigma fibre reinforced cavities body titanium p 585 N94-36655 |BTN-94-EIX94311330101| p 586 A94-61057 IBTN-94-EIX94401358972I p 583 A94-61628 The control ol cleanness in powder metallurgy materials Detailed flow measurements and predictions for a LIGHT AIRCRAFT for turbine disks p 586 N94-37325 three-stage transonic fan High Altitude Long Endurance aircraft design studies Maintaining constant standards during the forging |BTN-94-EIX94311330096| p 587 A94-61062 p 572 N94-36322 process p 586 N94-37326 LASER DOPPLER VELOCIMETERS LIGHT GAS GUNS MARINE PROPULSION Detailed flow measurements and predictions for a Experimental investigation ol nozzle/plume Increased use of gas turbines as commercial marine three-stage transonic fan aerodynamics al hypersonic speeds engines |BTN-94-EIX94311330096| p 587 A94-61062 INASA-CR-1958291 p 568 N94-36687 IBTN-94-EIX94311331080I p 588 A94-61098 Rotating laser-Doppler anemometry system for unsteady LIGHT HELICOPTERS Mashproekt scientific and production association: A relative flow measurements in model centrifugal Planning German Army helicopter maintenance and designer of gas turbines for marine and industrial impellers mission assignment applications |BTN-94-EIX94311330092| p 590 A94-61127 | AD-A280483 I p 564 N94-37352 IBTN-94-EIX94311331079I p 588 A94-61099

A-11 MARKETING SUBJECT INDEX

Investigation ol the part-load performance ol two 1.12 MICROWAVE LANDING SYSTEMS Unsteady aerodynamic characteristics of a dual-element MW regenerative marine gas turbines A model-based approach lor detection ol runways and airfoil IBTN-94-EIX9431133I078I p 588 A94-61100 other objects in image sequences acquired using an IBTN-94-EIX94401358968I P 565 A94-61624 Investigation ol Ihe part-load performance ol two 1.12 on-board camera Computation of three-dimensional hypersonic flows in MW regenerative marine gas turbines |NASA-CR-196424| p 594 N94-36812 chemical nonequilibnum |BTN-94-EIX943M33!078| p 588 A94-6IIOO MICROWAVE SOUNDING IBTN-94-EIX94401358982I P 566 A94-61638 MARKETING Earth Observing System/Advanced Microwave Navier-Stokes computations for oscillating control Coping with the defense cutback Sounding Unit-A (EOS/AMSU-A) software management surfaces IBTN-94-EIX94401216109I p 563 A94-61788 plan I8TN-94-EIX94401358983I P 566 A94-61639 World jet airplane inventory at year-end 1993 INASA-CR-1893621 p 596 N94-36919 Numerical investigation of multi-element airfoils |PB94-164993| P569 N94-36530 MILITARY AIRCRAFT INASA-CR-1945921 P 567 N94-36394 MASSIVELY PARALLEL PROCESSORS Aircraft battle damage repair for the 1990's and An aerodynamic and static-stability analysis of the Turbulence modeling of free shear layers tor high beyond Hypersonic Applied Research Technology (HART) performance aircraft IAD-A278635I p 576 N94-36465 missile INASA-CR-1961371 p 594 N94-36808 |AD-A280631| P 568 N94-36729 MILITARY HELICOPTERS An arbitrary grid CFD algorithm lor configuration MATHEMATICAL MODELS Planning German Army helicopter maintenance and Window functions for the calculation of the lime domain aerodynamics analysis. Volume 1: Theory and mission assignment validations averages of the vibration of the individual planet gears | AD-A280483 I p 564 N94-37352 and sun gear en an epicyclic gearbox INASA-CR-1959181 P 598 N94-36914 MILITARY OPERATIONS IBTN-94-EIX94311331047I p 586 A94-61050 An arbitrary grid CFD algorithm for configuration Future tanker considerations and requirements Models for predicting the performance of Brayton-cycle aerodynamics analysis. Volume 2: FEMNAS user guide engines p 575 N94-36342 INASA-CR-196135] P 598 N94-36922 IBTN-94-EIX94311331072I p 589 A94-61106 MILITARY TECHNOLOGY Navier-Stokes and potential theory solutions lor Fault diagnosis in gas turbines using a model-based Investigation of the part-load performance ol two 1.12 ahelicopter fuselage and comparison with experiment technique MW regenerative manne gas turbines INASA-TM-45661 p 569 N94-36966 |BTN-94-EIX94311331071| p 589 A94-61107 IBTN-94-EIX94311331078I P 588 A94-61100 A fundamental study of hypersonic unstarts Comprehensive model ol anisotropic composite aircraft Working group activities of AGARO propulsion and IAD-A280506I p 595 N94-37128 wings suitable for aeroelastic analyses energetics panel Prediction of film cooling on gas turbine airioils IBTN-94-EIX94401358993I p 572 A94-61649 IBTN-94-EIX94311331062I p 589 A94-61116 INASA-TM-106653I P 579 N94-37448 Nonlinear model-following control application to airplane Coping with the delense cutback NAVIGATION control |BTN-94-EIX94401216109| p 563 A94-61788 Capture region lor true proportional navigation guidance |8TN-94-EIX94401358166| p 580 A94-6I672 MIMO (CONTROL SYSTEMS) with nonzero m/ss-dislance Analysis and control of bifurcation phenomena in aircraft Mixed H2/H-inlmity optimization with multiple H inlinity IBTN-94-EIX94401358176I p 570 A94-61682 flight constraints On the generalization of true proportional navigation IBTN-94-EIX94401358169I p 572 A94-61675 |AD-A280572| p 581 N94-36733 IBTN-94-EIX94401377808I P 570 A94-61769 Adaptive model architecture and extended Kalman-Bucy MISS DISTANCE NICKEL ALLOYS filters Capture region for true proportional navigation guidance Process enhancements of superalloy material IBTN-94-EIX94401377806I p 592 A94-61767 with nonzero miss-distance p 585 N94-37324 Equivalent plate structural modeling for wing shape IBTN-94-EIX94401358176I p 570 A94-61682 Maintaining constant standards during the forging optimization including transverse shear process p586 N94-37326 MISSILE CONFIGURATIONS IBTN-94-EIX94421374979I p 564 A94-61877 Defects and their effects on the integrity ot nickel based An aerodynamic and static-stability analysis of the Analysis of high speed flow, thermal and structural aeroengine discs P 586 N94-37328 Hypersonic Applied Research Technology (HART) interactions missile Substantiating powder metal life methodologies for INASA-CR-1960171 p 593 N94-36420 IAD-A280631I p 568 N94-36729 engines P 595 N94-37330 JPRS report: Central Eurasia. Aviation and MISSILE CONTROL NIGHT cosmonautics. No. 5. May 1993 Analytic solution of the Riccati equation lor the homing Laser designation pods optimized concept tor day/night IJPRS-UAC-94-004I p583 N94-37000 missile linear-quadratic control problem operations p 594 N94-36620 Predicting defect behaviour p 596 N94-37331 IBTN-94-EIX94401358173I p 583 A94-61679 NOISE PREDICTION (AIRCRAFT) Dynamics, of a split torque helicopter transmission Capture region for true proportional navigation guidance Computation of supersonic jet mixing noise tor an |NASA-TM-106410| p 596 N94-37457 with nonzero miss-distance axisymmetric convergent-divergent nozzle MECHANICAL DEVICES IBTN-94-EIX94401358176I p 570 A94-61682 |BTN-94-EIX94401358979| p 599 A94-61635 Preload release mechanism MISSILES NOISE REDUCTION I NASA-CASE-MSC-22327-1 | p 594 N94-36839 Analytic solution of the Riccati equation for the homing Forward sweep, low noise rotor blade MECHANICAL DRIVES missile linear-quadratic control problem INASA-CASE-LAR-14569-11 p 576 N94-36767 Electric drives on the LV100 gas turbine engine IBTN-94-EIX94401358173I p 583 A94-61679 NONDESTRUCTIVE TESTS IBTN-94-EIX94311331077I p 588 A94-61101 An aerodynamic and static-stability analysis of the Characterisation of Fibre Reinforced Titanium Matrix MECHANICAL PROPERTIES Hypersonic Applied Research Technology (HART) Composites Characterisation of Fibre Reinforced Titanium Matrix missile IAD-A27752061 p 585 N94-36649 Composites |AD-A280631| p 568 N94-36729 Process enhancements of superalloy material IAD-A2775J061 p 585 N94-36649 MISSION PLANNING p 585 N94-37324 Planning German Army helicopter maintenance and Possibilities and pitfalls in aerospace applications of NONEQUILIBRIUM FLOW titanium matrix composites p 585 N94-36650 mission assignment Experimental investigation ol nozzle/plume Manufacture and properties of sigma fibre reinforced | AD-A280483 I p 564 N94-37352 MULTIGRID METHODS aerodynamics at hypersonic speeds titanium p 585 N94-36655 INASA-CR-1958291 p 568 N94-36687 MELTING Two-dimensional Euler zonal method using composite structured and unstructured meshes NONLINEAR FEEDBACK Alternate melting and refining routes Nonlinear model-following control application to airplane p 585 N94-37323 IBTN-94-EIX94401358986I p 566 A94-61642 A method lor How simulation about complex geometries control Process enhancements of superalloy material using both structured and unstructured grids IBTN-94-EIX94401358166I p 580 A94-61672 p 585 N94-37324 |NASA-TM-106633| p 569 N94-37283 NONLINEAR SYSTEMS METAL MATRIX COMPOSITES Prediction of film cooling on gas turbine airfoils Nonlinear model-following control application to airplane Characterisation of Fibre Reinforced Titanium Matrix |NASA-TM-106653| p 579 N94-37448 control Composites MULTISENSOR APPLICATIONS |BTN-94-EIX94401358166| p 580 A94-61672 IAD-A2775206I p 585 N94-36649 Sensor data fusion for air to air situation awareness Analysis and control ol bilurcation phenomena in aircralt Possibilities and pitfalls in aerospace applications of beyond visual range p 598 N94-36633 High! titanium matrix composites p 585 N94-36650 IBTN-94-EIX94401358169I p 572 A94-61675 Applications of Titanium Matrix Composite to large NOSE TIPS airtrame structure p 585 N94-36651 N An aerodynamic and static-stability analysis ol the SCS-6 (Im) fiber reinforced titanium Hypersonic Applied Research Technology (HART) NAP-OF-THE-EARTH NAVIGATION p 585 N94-36652 missile Advanced information processing system: The Army IAD-A280631I p 568 N94-36729 Manufacture and properties ol sigma fibre reinforced Fault-Tolerant Architecture detailed design overview titanium p 585 N94-36655 |NASA-CR-194924| p 598 N94-36962 NOZZLE FLOW Tipjet 80-inch model rotor hover test: Test no. 1198 METAL POWDER NASA PROGRAMS Substantiating powder metal life methodologies for Impact ol Ada in the Flight Dynamics Division: IAD-A279680I p 567 N94-36261 engines p 595 N94-37330 Excitement and frustration p 597 N94-36501 Experimental investigation of nozzle/plume MICROWAVE EQUIPMENT NATURAL LANGUAGE PROCESSING aerodynamics at hypersonic speeds Earth Observing System/Advanced Microwave An error-resistant linguistic protocol for air traffic I NASA-CR-1958291 p 568 N94-36687 Sounding Unit-A (EOS/AMSU-A) software management control NOZZLE GEOMETRY plan INASA-CR-1960981 p 570 N94-37013 Effects ol nozzle exit geometry on lorebody vortex [NASA-CR-1893621 P 596 N94-36919 NAVIER-STOKES EQUATION control using blowing MICROWAVE IMAGERY Transler of heat by sell-induced (low in a rotating tube |BTN-94-EIX94401358964| p 564 A94-61620 A model-based approach for detection ol runways and IBTN-94-EIX94311330098I p 587 A94-61060 NOZZLE INSERTS other objects in image sequences acquired using an Advanced transonic fan design procedure based on a Mixing and noise benefit versus thrust penalty in on-board camera Navier-Stokes method supersonic jets using impingement tones |NASA-CR-196424| p 594 N94-36812 IBTN-94-EIX94311330095I p 587 A94-61063 INASA-TM-1065831 p 568 N94-36686

A-12 SUBJECT INDEX PROPULSION SYSTEM CONFIGURATIONS

NOZZLES PATTERN RECOGNITION POWDER METALLURGY Ingestion into the upstream wheelspace of an axial A model-based approach for detection of runways and The control of cleanness in powder metallurgy materials turbine stage other objects in image sequences acquired using an tor turbine disks P 586 N94-37325 IBTN-94-EIX9.S31I330099I p 587 A94-61059 on-board camera Delects and their effects on the integrity of nickel based NUCLEATION INASA-CR-1964241 p 594 N94-36812 aeroengine discs P 586 N94-37328 Literature review and preliminary studies ol fretting and PEGASUS AIR-LAUNCHED BOOSTER Substantiating powder metal fife methodologies for (retting fatigue including special applications to aircraft Preliminary analysis for a Mach 6 crossflow transition engines p 595 N94-37330 joints experiment on the Pegasus (R) space booster PRECIPITATION HARDENING IAD-A280310I p 594 N94-37125 INASA-TM-1042721 p 564 N94-36648 Substantiating powder metal life methodologies for NUMERICAL ANALYSIS PERFORMANCE PREDICTION engines p 595 N94-37330 Transler of heat by self-induced flow in a rotating tube Models lor predicting the performance of Brayton-cycle PREDICTION ANALYSIS TECHNIQUES IBTN-94-EIX94311330098I p 587 A94-61060 engines Detailed flow measurements and predictions for a IBTN-94-EIX94311331072I p 589 A94-61106 three-stage transonic Ian PERFORMANCE TESTS |BTN-94-EIX94311330096| p 587 A94-61062 0 Flight test certification of a 480 gallon composite fuel Models lor predicting the performance of Brayton-cycle tankonCF-18 p 574 N94-36340 engines In-thght refueling: Dassault Aviation research on the OBJECT-ORIENTED PROGRAMMING IBTN-94-EIX94311331072I p 589 A94-61106 Rafale aircraft P 574 N94-36341 Impact of Ada in the Flight Dynamics Division: An empirical comparison of a dynamic software Excitement and frustration p 597 N94-36501 CC-130H(T) tactical aerial refuelling tanker development testability metric to static cyclomatic complexity OGIVES flight test programme P 575 N94-36347 p 597 N94-36498 Effects of nozzle exit geometry on lorebody vortex PERTURBATION Characterisation of Fibre Reinforced Titanium Matrix control using blowing Nondimensional forms for singular perturbation analyses Composites |BTN.94-EIX94401358964| p 564 A94-61620 of aircraft energy climbs | AD-A27752061 p 585 N94-36649 OILS IBTN-94-EIX94401358168I p 572 A94-61674 Substantiating powder metal life methodologies for Influence ol high rotational speeds on heat transfer and PIEZOELECTRICITY engines p 595 N94-37330 Aeroservoelastic tailoring with piezoelectric materials: oil film thickness in aero-engme bearing chambers Predicting defect behaviour p 596 N94-37331 IBTN-94.EIX94311331074I p 588 A94-61104 Actuator optimization studies PREFORMS |AD-A278640| p 581 N94-36384 OPERATING COSTS SCS-6 (tm) fiber reinforced titanium p 585 N94-36652 PT6 engine: 30 years of gas turbine technology PILOT PLANTS evolution Effect of pressure on second-generation pressurized PREPROCESSING |BTN-94-EIX94311331064| p 577 A94-61114 fluidized bed combustion plants Optimum flight trajectory guidance based on total energy |BTN-94-EIX943t1331067| p 589 A94-6IH1 Optimum flight trajectory guidance based on total energy control of aircraft control of aircraft PILOTLESS AIRCRAFT |BTN-94-EIX94381311167| p 579 A94-61254 |BTN-94-EIX94381311167| p 579 A94-61254 Wind-tunnel test techniques for unmanned aerial vehicle PRESSURE OPERATIONAL HAZARDS separation investigations Unsteady blade pressures on a preplan: Predicted and |BTN-94-EIX94401358976| p 571 A94-61632 Rotorwash analysis handbook. Volume t: Development measured compressibility effects and analysis Technological challenges of High Altitude Long IBTN-94-EIX94401358996I p 578 A94-61652 ISCT-93HR-17-VOL-1I p 567 N94-36466 Endurance unmanned configurations PRESSURE DISTRIBUTION p 573 N94-36323 Rotorwash analysis handbook. Volume 2: Appendixes Operational stability of a centrifugal compressor and its ISCT-93RR-17-VOL-2I p 567 N94-36467 PISTON ENGINES dependence on the characteristics of the OPTIMAL CONTROL The STRATO 2C propulsion system: A low cost subcomponents Multiobjective trajectory optimization by goal approach for a High Altitude Long Endurance aircraft | BTN-94-EIX94311330091 I p 590 A94-61128 programming with fuzzy decisions p 578 N94-36335 Lift enhancement of an airloil using a Gurney flap and IBTN-94.EIX94381311168I p 597 A94-61255 PITCH (INCLINATION) vortex generators Range optimal trajectories for an aircraft flying in the Some basic considerations on angles describing airplane IBTN-94-EIX94401358970I p 565 A94-61626 vertical plane flight maneuvers Fluctuating wall pressures neat separation in highly |BTN.94-EIX943813111B1| p 571 A94-61268 |BTN-94-EIX94381311179| p 570 A94-61266 swept turbulent interactions Nonlinear model-following control application to airplane PLASTIC DEFORMATION IBTN-94-EIX94421374958I p 563 A94-61856 control Literature review and preliminary studies of fretting and Controlling torebody asymmetries in flight: Experience IBTN.94.EIX94401358166I p 580 A94-61672 fretting fatigue including special applications to aircraft with boundary layer transition stnps Improvement of endurance performance by periodic joints | NASA-TM-45951 p 568 N94-36944 optimal control of variable camber p 581 N94-36329 IAD-A280310I p 594 N94-37125 PRESSURE EFFECTS Mixed H2/H-infinity optimization with multiple H infinity PLATE THEORY Effect of pressure on second-generation pressurized constraints Equivalent plate structural modeling for wing shape fluidized bed combustion plants IAD-A280572I p 581 N94-36733 optimization including transverse shear |BTN-94-EIX94311331067| p 589 A94-61111 OPTIMIZATION |BTN-94-EIX94421374979| p 564 A94-61877 PRESSURE MEASUREMENT Optimisation of composite aircraft structures by direct PLATES (STRUCTURAL MEMBERS) Ingestion into the upstream wheelspace of an axial manufacturing approaches p 574 N94-36327 Stability of skew plates subjected to aerodynamic and turbine stage OSCILLATIONS in-plane forces IBTN-94-EIX94311330099I p 587 A94-61059 Multidomain method for several bodies in relative IBTN-94-EIX94321331202I p 592 A94-61615 Measurement uncertainty and feasibility study ol a Hush motion PLUMES airdata system for a hypersonic flight experiment IBTN-94-EIX94401367452I p 563 A94-61785 Experimental investigation of nozzle/plume | NASA-TM-46271 p 569 N94-37378 OXIDE FILMS aerodynamics at hypersonic speeds PRESSURE RECOVERY Wear-resisting oxide films tor 900 C | NASA-CR-1958291 p 568 N94-36687 Experimental investigation on selecting the ramp and IDE94-010093I p584 N94-36306 PNEUMATIC CONTROL lip parameters of a two-dimensional external compression The reduction of takeoff ground roll by the application inlet of a nose gear jump strut IBTN-94-EIX94381353570I p 577 A94-61460 INASA-TM-108822] p 576 N94-36380 PROCESS CONTROL (INDUSTRY) PNEUMATIC EQUIPMENT Maintaining constant standards during the forging PANEL METHOD (FLUID DYNAMICS) Tipjet 80-inch model rotor hover test: Test no. 1198 process p 586 N94-37326 Navier-Stokes and potential theory solutions for (AD-A279680I p 567 N94-36261 PROGRAM VERIFICATION (COMPUTERS) ahelicopter fuselage and comparison with experiment PODS (EXTERNAL STORES) An arbitrary grid CFD algorithm tor configuration | NASA-TM-45661 p 569 N94-36966 Aerial refueling interoperability from a receiver flying aerodynamics analysis. Volume 1: Theory and PANELS qualities perspective p 575 N94-36343 validations Buckling and vibration analysis of laminated panels using POINT SOURCES |NASA-CR-19591B| p 598 N94-36914 VICONOPT Sound radiation and caustic formation from a point PROPELLANT TESTS IBTN-94-EIX94401372105I p 592 A94-61805 source in a wall shear layer Coating the boron particles to increase the combustion PARACHUTES IBTN-94-EIX94421374956I p 599 A94-61B54 efficiency of boron fuel Prediction method for unsteady axisymmetric flow over |BTN-94-EIX94381353577| p 584 A94-61473 POINTING CONTROL SYSTEMS parachutes PROPELLER FANS Aeroservoelastic stabilization considerations for pointing |BTN-94-EIX94401358984| p 566 A94-61640 Whirl-flutter suppression in advanced turboprops and and tracking systems p 594 N94-36627 PARALLEL COMPUTERS propfans by active control techniques Large angle magnetic suspension test fixture Advanced information processing system: The Army |BTN-94-EIX94401358994| p 578 A94-61650 | NASA-CR-1961381 p 583 N94-37450 Fault-Tolerant Architecture detailed design overview Unsteady blade pressures on a propfan: Predicted and INASA-CR-1949241 p 598 N94-36962 POLYMERS measured compressibility effects PARALLEL PROCESSING (COMPUTERS) Replacement of silicone polymer A with silicone polymer |BTN-94-EIX94401358996| p 578 A94-61652 Turbulence modeling of free shear layers tor high B and the subsequent characterization of the new cellular PROPULSION performance aircraft silicone materials Working group activities of AGARD propulsion and |NASA-CR-196137| p 594 N94-36808 IDE94-010105I p584 N94-36474 energetics panel PARAMETER IDENTIFICATION POSITION (LOCATION) |BTN-94-EIX94311331062| p 589 A94-61116 Evaluation of parameter estimation methods for unstable Aerial refueling interoperability from a receiver flying PROPULSION SYSTEM CONFIGURATIONS aircraft qualities perspective p 575 N94-36343 Technological challenges of High Altitude Long |BTN-94-EIX94401358965| p 580 A94-61621 POTENTIAL THEORY Endurance unmanned configurations Adaptive model architecture and extended Kalman-Bucy Navier-Stokes and potential theory solutions for p 573 N94-36323 filters ahelicopter fuselage and comparison with experiment Propulsion system selection for a High Altitude Long |BTN-94-EIX94401377806| p 592 A94-61767 | NASA-TM-45661 p 569 N94-36966 Endurance aircraft p 578 N94-36333

A-13 PROPULSION SYSTEM PERFORMANCE SUBJECT INDE>

Propulsion system technologies lor long range and long RESEARCH AIRCRAFT ROTOR DYNAMICS endurance aircraft p 578 N94-36334 The reduction of takeoff ground roll by the application Survey and comparison of engineering beam theories The STRATO 2C propulsion system: A low cost of a nose gear jump strut for helicopter rotor blades approach for a High Altitude Long Endurance aircraft INASA-TM.108822I p 576 N94-36380 |BTN-94-EIX94401358960| p 571 A94-61616 p 578 N94-36335 Predicting the effects of unmodeled dynamics on an ROTORS PROPULSION SYSTEM PERFORMANCE aircraft flight control system design using eigenspace Study of rotor cavities and heat transfer in a cooling Models lor predicting the performance ol Brayton-cycle assignment process in a gas turbine engines | NASA.TM-45481 p 582 N94-37059 |BTN-94-EIX94311330100| p 587 A94-61058 IBTN-94-EIX94311331072I p 589 A94-61106 RESEARCH VEHICLES Ingestion into the upstream wheelspace ol an axial Recent Advances in Long Range and Long Endurance The reduction ol takeoff ground roll by the application turbine stage Operation of Aircraft ol a nose gear |ump strut |BTN-94-EIX94311330099| p 587 A94-61059 |AGARD-CP-547| p 572 N94-36321 INASA-TM.108822I P 576 N94-36380 Tipiet 80-inch model rotor hover test: Test no. 1198 Technological challenges of High Altitude Long REVERSE ENGINEERING (AD-A279680I p 567 N94-36261 Endurance unmanned configurations Applying formal methods and object-oriented analysis RUNWAYS p 573 N94-36323 to existing flight software p 597 N94-36495 A model-based approach lor detection ol runways and Possibilities and pitlalls in aerospace applications ol other objects in image sequences acquired using an titanium matrix composites p 585 N94-36650 REYNOLDS NUMBER Mainstream ingress suppression in gas turbine disk on-board camera PROTOCOL (COMPUTERS) |NASA-CR-196424| p 594 N94-36812 An error-resistant linguistic protocol for air traffic cavities control IBTN-94-EIX94311330101I p 586 A94-61057 INASA-CR-1960981 p 570 N94-37013 Numerical investigation ol multi-element airfoils PUMP IMPELLERS INASA-CR-1945921 p 567 N94-36394 Experimental investigation of the steady and unsteady RICCATI EQUATION relative flow in a model centrifugal impeller passage Analytic solution ol the Riccati equation (or the homing SCHEDULING IBTN-94-EIX94311330093I p 590 A94-61126 missile linear-quadratic control problem Planning German Army helicopter maintenance and Rotating laser.Doppler anemometry system lor unsteady IBTN-94-EIX94401358173I p 583 A94-61679 mission assignment relative How measurements in model centrifugal RIGID STRUCTURES IAD-A2804831 p 564 N94-37352 impellers Predicting the elfects of unmodeled dynamics on an SCHLIEREN PHOTOGRAPHY IBTN-94-EIX94311330092I p 590 A94-6I127 aircraft flight control system design using eigenspace Aerodynamic investigation with locusing Schlieren in a PURSUIT TRACKING assignment cryogenic wind tunnel Two-axis camera platform lor machine vision INASA-TM-4548I p 582 N94-37059 |BTN-94-EIX94421374975| p 593 A94-61873 p 597 N94-36628 ROCKET ENGINES SEALERS Comments on the development of the early Mainstream ingress suppression in gas turbine disk Westmghouse turbojets. 1941-1946 cavities Q IBTN-94-EIX94311331063I p 577 A94-61115 |BTN-94-EIX94311330101| p 586 A94-61057 ROLL SEALING QUALITY CONTROL Some basic considerations on angles describing airplane Mainstream ingress suppression in gas turbine disk Unstructured mesh quality assessment and upwind Euler Ilight maneuvers cavities solution algorithm validation IBTN-94-EIX94381311179I p 570 A94-61266 | BTN-94-EIX94311330101 | p 586 A94-61057 IBTN-94-EIX94401358985I p 592 A94-6)641 Unique high-alpha roll dynamics of a sharp-edged 65 Influence of high rotational speeds on heat transfer and Impact of Materials Delects on Engine Structures deg delta wing oil film thickness in aero-engine bearing chambers Integrity IBTN-94-EIX94401358966I p 571 A94-61622 |BTN-94-EIX94311331074| p 588 A94-61104 JAGARD-R-790I p 595 N94-37321 The reduction of takeoff ground roll by the application SEALS (STOPPERS) The control of cleanness in powder metallurgy materials of a nose gear jump strut Wear-resisting oxide lilms lor 900 C for turbine disks p 586 N94-37325 INASA-TM-1088221 p 576 N94-36380 IDE94-010093I p 584 N94.36306 Maintaining constant standards during the forging ROLLING MOMENTS SECONDARY FLOW process p 586 N94-37326 Significance ol the dihedral effect in rapid Unsteady flow field of large-amplitude pitching airloils OUEUEING THEORY tuselage-reorientation maneuvers |AD-A280444| p 569 N94-37219 IBTN-94-EIX94401358971 | p571 A94-61627 A mean value analysis heuristic lor analysis of aircraft SEGMENTS sortie generation ROTARY WING AIRCRAFT Rotorwash analysis handbook. Volume 1: Development Selection criteria for plain and segmented finned tubes IAD-A2785781 p 598 N94-36970 for heat recovery systems and analysis ISCT-93HR-17-VOL-1I p 567 N94-36466 IBTN-94-EIX94311331076I p 588 A94-61102 Rotorwash analysis handbook. Volume 2: Appendixes SELF LUBRICATING MATERIALS ISCT-93RR-17-VOL-2I p 567 N94-36467 Wear-resisting oxide lilms for 900 C TRENDS: A Ilight test relational database user's guide IDE94-010093I p584 N94-36306 RAMJET ENGINES and reference manual SENSITIVITY Comments on the development of the early INASA-TM-1088061 p 564 N94-37332 Sensitivity derivatives for three-dimensional supersonic Westmghouse turbojets. 1941-1946 ROTARY WINGS Euler code using incremental iterative strategy |BTN-94-EIX94311331063| p 577 A94-61115 Survey and comparison ol engineering beam theories |BTN-94-EIX94421374969| p 593 A94.6186T REACTING FLOW lor helicopter rotor blades SEPARATED FLOW Computation ol three-dimensional hypersonic Hows in IBTN-94-EIX94401358960I p 571 A94-61616 Computation of transonic flows around a chemical nonequilibnum Forward sweep, low noise rotor blade wing-plus-fuselage configuration taking viscous effects and IBTN-94-EIX94401358982I p 566 A94-61638 |NASA-CASE-LAR-14569-1| p 576 N94-36767 a thin separated region into account REDUCED ORDER FILTERS ROTATING FLUIDS |BTN-94-EIX94401367450| p 563 A94-61783 Reduced-order H(INF) compensator design lor an Transler ol heat by self-induced How in a rotating tube Fluctuating wall pressures near separation in highly aircraft control problem |BTN-94-EIX94311330098| p 587 A94-61060 swept turbulent interactions |BTN-94-EIX94381311174| p 579 A94-61261 ROTATING STALLS |BTN-94-EIX94421374958| p 563 A94-61856 REENTRY VEHICLES Active stabilization of rotating stall in a three-stage axial Low-dimensional description of the dynamics m Adaptive model architecture and extended Kalman-Bucy compressor separated flow past thick airfoils filters IBTN-94-EIX94311330089I p 591 A94-61130 |BTN-94-EIX94421374967| p 563 A94-61865 IBTN-94-EIX94401377806I p 592 A94-61767 Stall inception and development in an axial flow Unsteady How field ol large-amplitude pitching airioiis. REFINING aeroengine |AD-A280444| p 569 N94-37219 IBTN-94-EIX94311330088I p 591 A94-61131 Alternate melting and refining routes SEPARATION Review of nonsteady flow models for compressor P585 N94-37323 Wind-tunnel test techniques tor unmanned aerial vehicle- REFRACTORY MATERIALS stability IBTN-94-EIX94311330087I p 591 A94-61132 separation investigations Possibilities and pitfalls in aerospace applications ol |BTN-94-EIX94401358976| p 571 A94-61632 titanium matrix composites p 585 N94-36650 Unstable behavior of low and high-speed compressors IBTN-94-EIX94311330086) p 591 A94-61133 SERVICE LIFE REFRIGERATING ROTOR AERODYNAMICS Impact ol Materials Defects on Engine Structures Perlormance and economic enhancement of Inviscid-viscous interaction method lor Integrity cogeneration gas turbines through compressor inlet air three-dimensional inverse design ol centrifugal impellers |AGARD-R-790| p 595 N94-37321 cooling |BTN-94-EIX9431!330094| p 590 A94-61125 |BTN-94-EIX94311331069| p 589 A94-61109 Alternate melting and refining routes Experimental investigation of the steady and unsteady p 585 N94-37323 REINFORCING FIBERS relative flow in a model centrifugal impeller passage SHEAR LAYERS SCS-6 (tin) fiber reinforced titanium |BTN-94-EIX94311330093| p 590 A94-61126 Sound radiation and caustic formation from a point p 585 N94-36652 Whirl-flutter suppression in advanced turboprops and source in a wall shear layer RELIABILITY ANALYSIS preplans by active control techniques |BTN-94-EIX94421374956| p 599 A94-61854 New high-efficiency heavy-duty combustion turbine |BTN-94-EIX94401358994| p 578 A94-61650 701F ROTOR BLADES Turbulence modeling ol Iree shear layers tor high IBTN-94-EIX94311331073I p 588 A94-61105 Ingestion into the upstream wheelspace of an axial performance aircraft Possibilities and pitlalls in aerospace applications ol turbine stage |NASA-CR-196137| p 594 N94-36808 titanium matrix composites p 585 N94-36650 |BTN-94-EIX94311330099| p 587 A94-61059 SHEAR STRAIN RESCUE OPERATIONS Advanced transonic Ian design procedure based on a Equivalent plate structural modeling for wing shape EH 101: A new helicopter capable of long range Navier-Stokes method optimization including transverse shear missions p 574 N94-36330 | BTN-94-EIX94311330095 | p 587 A94-61063 IBTN-94-EIX94421374979] p 564 A94-61877

A-14 SUBJECT INDEX SUPPORT SYSTEMS

SHEAR STRESS SPACE FLIGHT STRUCTURAL DESIGN Laser interferometer skin-friction measurements of Adaptive model architecture and extended Kalman-Bucy Equivalent plate structural modeling lor wing shape crossing-shock-wave/turbulent-boundary-layer filters optimization including transverse shear ns IBTN-94-EIX94401377806I p 592 A94-61767 IBTN-94-EIX94421374979I p 564 A94-61877 |BTN-94-EIX94421374974| p 593 A94-61872 SPACECRAFT CONSTRUCTION MATERIALS High Altitude Long Endurance aircraft design studies SHIPS Possibilities and pitfalls in aerospace applications of p 572 N94-36322 Landing ol an unmanned helicopter on a moving titanium matrix composites p 585 N94-36650 Applications of Titanium Matrix Composite to large plattorm. High accuracy navigation and tracking Applications of Titanium Matrix Composite to large airframe structure P 585 N94-36651 p 576 N94-36618 airframe structure p 585 N94-36651 STRUCTURAL FAILURE SHOCK TUBES SPACECRAFT DESIGN History and prognosis ol material discontinuity effects Experimental investigation ol nozzle/plume Preliminary piloted simulation studies of the HL-20 lifting on engine components structural integrity aerodynamics at hypersonic speeds body p 595 N94-37322 INASA-CR-1958291 p 568 N94-36687 IBTN-94-EIX94401358972I p 583 A94-61628 Turbine disks: Liling against defects and materials SHOCK TUNNELS SPACECRAFT PROPULSION development p 595 N94-37329 Experimental investigation ol nozzle/plume Possibilities and pitlalls in aerospace applications ol STRUCTURAL STABILITY aerodynamics at hypersonic speeds titanium matrix composites P 585 N94-36650 Alleviation of whirl-flutter on a jomed-wing tilt-rotor INASA-CR-1958291 p 568 N94-36687 SPACECRAFT RELIABILITY SHOCK WAVE INTERACTION aircraft configuration using active controls Possibilities and pitfalls in aerospace applications of INASA-CR-1961031 p 581 N94-36436 Inviscid parametric analysis ot three-dimensional inlet titanium matrix composites P 585 N94-36650 performance Correlation of analytical and experimental hot structure SPANWISE BLOWING vibration results IBTN-94-EIX94401358980I p 578 A94-61636 Active control of wing rock using tangential leading-edge Laser interferometer skin-friction measurements of |NASA-TM-104269| p 576 N94-36644 blowing STRUCTURAL VIBRATION crossmg-shock-wave/turbulent-boundary-layer |BTN-94-EIX94401358987| p 571 A94-61643 ns Buckling and vibration analysis of laminated panels using |BTN-94-EIX94421374974| p 593 A94-61872 SPECTRAL METHODS VICONOPT Analysis of high speed flow, thermal and structural Low-dimensional description ol the dynamics in IBTN-94-EIX94401372105I p 592 A94-61805 interactions separated flow past thick airfoils Correlation of analytical and experimental hot structure INASA-CR-1960171 p 593 N94-36420 |BTN-94-EIX94421374967| p 563 A94-61865 vibration results SHOCK WAVES STABILITY TESTS INASA-TM-1042691 P 576 N94-36644 Detailed flow measurements and predictions tor a Nonlinear model-following control application to airplane STRUTS three-stage transonic fan control The reduction ol takeoff ground roll by the application IBTN-94-EIX94311330096) p 587 A94-6I062 IBTN-94-EIX94401358166I p 580 A94-61672 of a nose gear jump strut SHORT HAUL AIRCRAFT STABILIZATION |NASA-TM-108822| p 576 N94-36380 The reduction of takeoff ground roll by the application Active stabilization of rotating stall in a three-stage axial SUBCRITICAL FLOW of a nose gear jump strut compressor Design of optimized airfoils in subcntical flow INASA-TM-1088221 p 576 N94-36380 IBTN-94-EIX94311330089I p 591 A94-61130 IBTN-94-EIX94401358990I p 566 A94-61646 SHORT TAKEOFF AIRCRAFT Analysis and control of bifurcation phenomena in aircraft SUBSONIC FLOW The reduction of takeoff ground roll by the application flight Unsteady blade pressures on a propfan: Predicted and ol a nose gear jump strut IBTN-94-EIX94401358169I p 572 A94-61675 measured compressibility effects INASA-TM-1088221 p 576 N94-36380 STATIC PRESSURE IBTN-94-EIX94401358996I p 578 A94-61652 SHOT PEENING Ingestion into the upstream wheelspace of an axial Automatic computation of Euler-marching and subsonic Literature review and preliminary studies of fretting and turbine stage grids for wing-fuselage configurations fretting fatigue including special applications to aircraft IBTN-94-EIX94311330099I p 587 A94-61059 | NASA-TM-4573 | p 568 N94-36950 lomts STATIC STABILITY SUBSONIC FLUTTER IAD-A280310I p 594 N94-37125 An aerodynamic and static-stability analysis of the Alleviation of whirl-flutter on a |0ined-wmg till-rotor SIDESLIP Hypersonic Applied Research Technology (HART) aircraft configuration using active controls Significance of the dihedral effect in rapid missile |NASA-CR-196103| p 581 N94-36436 fuselage-reonentation maneuvers |AD-A280631| p 568 N94-36729 SUCTION |BTN-94-EIX9440t358971| p 571 A94-61627 Unsteady flow field ol large-amplitude pitching airfoils STATISTICAL ANALYSIS SIGNAL PROCESSING |AD-A280444| p 569 N94-37219 Predicting defect behaviour p 596 N94-37331 Adaptive model architecture and extended Kalman-Bucy SUPERSONIC COMBUSTION RAMJET ENGINES filters STEADY FLOW Inviscid parametric analysis of three-dimensional inlet Experimental investigation of the steady and unsteady IBTN-94-EIX94401377806] p 592 A94-61767 performance SILICONES relative flow in a model centrifugal impeller passage |BTN-94-EIX94401358980| p 578 A94-61636 Replacement of silicone polymer A with silicone polymer IBTN-94-EIX94311330093I p 590 A94-61126 Experimental investigation of nozzle/plume B and the subsequent characterization of the new cellular STEELS aerodynamics at hypersonic speeds silicone materials Alternate melting and refining routes INASA-CR-1958291 P 568 N94-36687 IDE94-010105I p584 N94-36474 p 585 N94-37323 SUPERSONIC FLOW SISO (CONTROL SYSTEMS) STOCHASTIC PROCESSES Sensitivity derivatives for three-dimensional supersonic Mixed H2/H-mfmity optimization with multiple H infinity Design and evaluation of a Stochastic Optimal Euler code using incremental iterative strategy constraints Feed-forward and Feedback Technology (SOFFT) flight IBTN-94-EIX94421374969I p 593 A94-61867 |AD-A280572| p 581 N94-36733 control architecture SUPERSONIC INLETS SKIN FRICTION |NASA-TP-3419| p 582 N94-37014 Research on the engineering application of the anti-swirl Laser interferometer skin-friction measurements of STOCKPILING measures in engine/inlet compatibility crossing-shock-wave/turtulent-boundary-layer Replacement of silicone polymer A with silicone polymer IBTN-94-EIX94381353571 | p 577 A94-61459 ns B and the subsequent characterization of the new cellular Experimental investigation on selecting the ramp and IBTN-94-EIX94421374974] p 593 A94-61872 silicone materials lip parameters ot a two-dimensional external compression SLIDING FRICTION IDE94-010105I p584 N94-36474 inlet Wear-resisting oxide films for 900 C STRATOSPHERE IBTN-94-EIX94381353570I p 577 A94-61460 IDE94-010093I p584 N94-36306 Project report: Aircraft — atmospheric effects of Boundary conditions for unsteady supersonic inlet SOFTWARE ENGINEERING stratospheric aircraft analyses An empirical comparison of a dynamic software IDE94-011759I p596 N94-37155 |BTN-94-EIX94421374964| p 593 A94-61862 testability metric to static cyclomatic complexity STRESS ANALYSIS SUPERSONIC JET FLOW p597 N94-36498 PT6 engine: 30 years of gas turbine technology Computation ol supersonic jet mixing noise tor an Impact of Ada in the Flight Dynamics- Division: evolution axisymmetric convergent-divergent nozzle Excitement and frustration p 597 N94-36501 [ BTN-94-EIX94311331064] p 577 A94-61114 IBTN-94-EIX94401358979I p 599 A94-61635 Earth Observing System/Advanced Microwave Mixing and noise benefit versus thrust penalty in Influence of aerodynamic forces in ice shedding Sounding Unit-A (EOS/AMSU-A) software management |BTN-94-EIX94401358967| p 564 A94-61623 supersonic jets using impingement tones plan | NASA-TM-106583 | p 568 N94-36686 INASA-CR-1893621 p 596 N94-36919 STRESS INTENSITY FACTORS SUPERSONIC SPEED SOFTWARE RELIABILITY Defects and their effects on the integrity of nickel based An aerodynamic and static-stability analysis of the aeroengine discs p 586 N94-37328 Applying formal methods and object-oriented analysis Hypersonic Applied Research Technology (HART) to existing flight software p 597 N94-36495 STRESS MEASUREMENT missile Impact of Ada in the Flight Dynamics Division: Laser interferometer skin-friction measurements of | AD-A280631 | p 568 N94-36729 Excitement and frustration p 597 N94-36501 crossing-shock-wave/turbulent-boundary-layer SUPERSONIC TRANSPORTS SOLID LUBRICANTS ns Mach 2 and more Wear-resisting oxide films lor 900 C |BTN-94-EIX94421374974| p 593 A94-61872 |BTN-94-EIX94401216108| p 569 A94-61787 |DE94-010093| p584 N94-36306 STRESS RELAXATION Future supersonic commercial transport aircraft: A SOLID ROCKET PROPELLANTS Replacement of silicone polymer A with silicone polymer technological challenge for long haul traffic Coating the boron particles to increase the combustion B and the subsequent characterization of the new cellular p 573 N94-36324 efficiency of boron fuel silicone materials Project report: Aircraft — atmospheric effects of |BTN-94-EIX94381353577| p 584 A94-61473 IDE94-010105I p584 N94-36474 stratospheric aircraft SOUND WAVES STRUCTURAL ANALYSIS |DE94-011759| p596 N94-37155 Sound radiation and caustic formation from a point Comprehensive model of anisotropic composite aircraft SUPPORT SYSTEMS source in a wall shear layer wings suitable for aeroelastic analyses Training and operations support system (TOPS) IBTN-94-EIX94421374956I p 599 A94-61854 IBTN-94-EIX94401358993I p 572 A94-61649 p 599 N94-37344

A-15 SURFACE GEOMETRY SUBJECT IND£>.

SURFACE GEOMETRY Correlation of analytical and experimental hot structure TIP SPEED Automatic procedures for computing complete vibration results Tipjet 80-inch model rotor hover test: Test no. 1198 configuration geometry from individual component |NASA-TM-104269| p 576 N94-36644 IAD-A279680I P 567 N94-36261 descriptions Measurement uncertainty and feasibility study of a flush TITANIUM I NASA-TM-4607 | p 568 N94-36942 airdata system for a hypersonic flight experiment Characterisation of Fibre Reinforced Titanium Matrix SURFACE NOISE INTERACTIONS |NASA-TM-4627| p 569 N94-37378 Composites Sound radiation and caustic formation from a point TEMPERATURE MEASUREMENT |AD-A2775206| P 585 N94-36649 source in a wall shear layer Influence ol high rotational speeds on heat transfer and Possibilities and pitfalls in aerospace applications of IBTN-94-EIX94421374956I p 599 A94.61854 oil film thickness in aero-engine bearing chambers titanium matrix composites P 585 N94-36650 SURFACE TEMPERATURE |BTN-94.EIX94311331074| p 588 A94-61104 Applications of Titanium Matrix Composite to large Inlluence ol high rotational speeds on heat transfer and airframe structure P 585 N94-36651 Fiber optic (flight quality) sensors lor advanced aircraft SCS-6 (tm) fiber reinforced titanium oil film thickness in aero-engine bearing chambers propulsion |BTN.94.EIX94311331074| p 588 A94.61104 p 585 N94-36652 INASA-CR-1911951 p 577 N94-37401 Correlation of analytical and experimental hot structure Manufacture and properties of Sigma fibre reinforced vibration results TEMPERATURE SENSORS titanium p 585 N94-36655 |NASA-TM-104269| p 576 N94.36644 Fiber optic (flight quality) sensors for advanced aircraft TITANIUM ALLOYS SURGES propulsion Characterisation ol Fibre Reinforced Titanium Matrix Developments in centrifugal compressor surge control: |NASA-CR-191195| p 577 N94-37401 Composites A technology assessment TERRAIN FOLLOWING AIRCRAFT | AD-A27752061 p 585 N94-36649 |BTN-94.EIX94311330090| p 590 A94-61129 Advanced information processing system: The Army Alternate melting and refining routes Stall inception and development in an axial flow Fault-Tolerant Architecture detailed design overview p585 N94-37323 aeroengine |NASA-CR-194924| p 598 N94-36962 Maintaining constant standards during the forging (BTN.94.EIX94311330088I p 591 A94-61131 THERMAL ANALYSIS process p 586 N94-37326 Unstable behavior of low and high-speed compressors Study of rotor cavities and heat transfer in a cooling TOLERANCES (MECHANICS) |BTN-94-EIX94311330086| p 591 A94-61133 process in a gas turbine Turbine disks: Lifing against detects and materials SWEPT FORWARD WINGS |BTN-94-EIX94311330100| p 587 A94-61058 development p 595 N94-37329 Forward sweep, low noise rotor blade Preliminary analysis for a Mach 8 crossflow transition TORQUE INASA-CASE-LAR-14569-1 I p 576 N94-36767 experiment on the Pegasus (R) space booster Dynamics of a split torque helicopter transmission SWEPT WINGS | NASA-TM-1042721 p 564 N94-36648 |NASA-TM-106410| p 596 N94-37457 Calculation of three-dimensional low Reynolds number THERMAL BUCKLING TOTAL ENERGY SYSTEMS flows Analysis of high speed (low. thermal and structural Optimum flight trajectory guidance based on total energy IBTN-94-EIX94401358973I p 565 A94-61629 interactions control of aircraft Comprehensive model of anisotropic composite aircraft [NASA-CR-1960171 p 593 N94-36420 |BTN-94-EIX94381311167| p 579 A94-61254 wings suitable for aeroelastic analyses THERMAL RESISTANCE TRACKING (POSITION) |BTN-94-EIX94401358993| p 572 A94-61649 Characterisation of Fibre Reinforced Titanium Matrix On the generalization of true proportional navigation The reduction of takeoff ground roll by the application Composites I8TN-94-EIX94401377808I p 570 A94-6I769 of a nose gear jump strut | AD-A27752061 p 585 N94-36649 Landing of an unmanned helicopter on a moving INASA-TM-1088221 p 576 N94-36380 THERMAL STABILITY platform. High accuracy navigation and tracking SWIRLING Advanced thermally stable, coal-derived, jet fuels p 576 N94-36618 Research on the engineering application of the anti-swirl development program. Experiment system and model Aeroservoelastic stabilization considerations for pointing measures in engine/inlet compatibility development and tracking systems p 594 N94-36627 IBTN-94-EIX94381353571I p 577 A94-61459 |AD-A278968| p 584 N94-36505 Sensor data fusion for air to air situation awareness SYSTEMS ANALYSIS THERMAL STRESSES beyond visual range p 598 N94-36633 An automated method for Low Level Windshear Alert Study of rotor cavities and heat transfer in a cooling TRAILING EDGES System (LLWAS) data quality analysis process in a gas turbine Numerical investigation of multi-element airfoils |AD-A280313| p 596 N94-37126 |BTN-94-EIX94311330100| p 587 A94-61058 (NASA-CR-1945921 p 567 N94-36394 SYSTEMS ENGINEERING Advanced thermally stable, coal-derived, jet fuels TRAJECTORIES Detailed flow measurements and predictions for a development program. Experiment system and model Significance of the dihedral effect in rapid three-stage transonic fan development tuselage-reorientation maneuvers IBTN-94-EIX94311330096I p 587 A94-61062 | AD-A2789681 p 584 N94-36505 |BTN-94-EIX94401358971| p 571 A94-61627 SYSTEMS STABILITY Correlation of analytical and experimental hot structure TRAJECTORY ANALYSIS New output feedback design in variable structure vibration results Nonlinear model-following control application to airplane systems |NASA-TM-104269| p 576 N94-36644 control |BTN-94-EIX94381311173| p 597 A94-61260 THERMODYNAMIC EFFICIENCY IBTN-94-EIX94401358166I p 580 A94-61672 New high-efficiency heavy-duty combustion turbine Nondimensional forms for singular perturbation analyses 701F of aircraft energy climbs [BTN-94-EIX94311331073I p 588 A94-61105 IBTN-94-EIX94401358168I p 572 A94-61674 Materials performance in advanced combustion On the generalization of true proportional navigation TABS (CONTROL SURFACES) systems IBTN-94-EIX94401377808I p 570 A94-61769 Numerical investigation of multi-element airfoils |BTN-94-EIX94311331065| p 584 A94-61113 TRAJECTORY CONTROL | NASA-CR-1945921 p 567 N94-36394 THERMOMECHANICAL TREATMENT Optimum flight trajectory guidance based on total energy TAKEOFF Maintaining constant standards during the forging control of aircraft Takeoff performance monitoring system display process p 586 N94-37326 IBTN-94-EIX94381311167I p 579 A94-61254 options THREAT EVALUATION Range optimal trajectories for an aircraft flying m the IBTN-94-EIX94401358988I p 577 A94-61644 Sensor data lusion for air to air situation awareness vertical plane The reduction of takeoff ground roll by the application beyond visual range p 598 N94-36633 IBTN-94-EIX943813111B1 | p 571 A94-6126B of a nose gear jump strut THREE DIMENSIONAL FLOW On the generalization of true proportional navigation |NASA-TM-108822| p 576 N94-363BO Calculation of three-dimensional low Reynolds number IBTN-94-EIX94401377808I p 570 A94-61769 TANKER AIRCRAFT flows TRAJECTORY OPTIMIZATION Future tanker considerations and requirements | BTN-94-EIX944013589731 p 565 A94-61629 Optimum flight trajectory guidance based on total energy p 575 N94-36342 Computation of three-dimensional hypersonic flows in control of aircraft Tanker system and technology requirements definition: chemical nonequilibrium |BTN-94-EIX94381311167| p 579 A94-61254 A tanker technology road map p 575 N94-36344 |BTN-94-EIX94401358982| p 566 A94-61638 Multiobjectrve trajectory optimization by goal The KDC-10 programme of the Royal Netherlands Air THREE DIMENSIONAL MODELS programming with fuzzy decisions Force p 575 N94-36346 Three-dimensional force data acquisition and boundary IBTN-94-EIX94381311168I p 597 A94-61255 corrections for the Walter H. Beech Memorial 7x10 loot CC-130H(T) tactical aerial refuelling tanker development TRANSATMOSPHERIC VEHICLES low speed wind tunnel flight test programme p 575 N94-36347 Nondimensional forms for singular perturbation analyses TARGET ACQUISITION |AR93-2| p582 N94-36437 of aircraft energy climbs THRUST-WEIGHT RATIO Laser designation pods optimized concept for day/night IBTN-94-EIX94401358168I p 572 A94-61674 The reduction ol takeoff ground roll by the application operations p 594 N94-36620 TRANSDUCERS of a nose gear jump strut Infrared search and track demonstrator programme Window functions for the calculation of the time domain |NASA-TM-108822| p 576 N94-36380 p 599 N94-36622 TILT ROTOR AIRCRAFT averages of the vibration of the individual planet gears TECHNOLOGY ASSESSMENT and sun gear in an epicyclic gearbox The convertible (helicopter/airplane) EUROFAR: Developments in centrifugal compressor surge control: |BTN-94-EIX94311331047| p 586 A94-61050 General considerations on the technical progress and on A technology assessment future advances p 574 N94-36331 TRANSMISSIONS (MACHINE ELEMENTS) |BTN-94-EIX94311330090| p 590 A94-61129 Alleviation of whirl-flutter on a joined-wing tilt-rotor Window functions for the calculation of the time domain Tanker system and technology requirements definition: aircraft configuration using active controls averages of the vibration of the individual planet gears A tanker technology road map p 575 N94-36344 |NASA-CR-196103| p 581 N94-36436 and sun gear in an epicyclic gearbox TEMPERATURE EFFECTS Analysis of vertiport studies funded by the Airport |BTN-94-EIX94311331047| p 586 A94-61050 Study of rotor cavities and heat transfer in a cooling Improvement Program (AIP) Dynamics of a split torque helicopter transmission process in a gas turbine |SCT-93RR-21| p 583 N94-37424 |NASA-TM-106410| p 596 N94-37457 |BTN-94-EIX94311330100| p 587 A94-61058 TIME OPTIMAL CONTROL TRANSONIC COMPRESSORS Fault diagnosis in gas turbines using a model-based Significance of the dihedral effect in rapid Detailed flow measurements and predictions lor a technique fuselage-reorientation maneuvers three-stage transonic fan |BTN-94-EIX94311331071| p 589 A94-61107 |BTN-94-EIX94401358971| p 571 A94-61627 |BTN-94-EIX94311330096| p 587 A94-61062

A-16 SUBJECT INDEX VISCOUS FLOW

Advanced transonic tan design procedure based on a Spanwise transport in axial-flow turbines. Part 1: The UPPER SURFACE BLOWING Navier-Slokes method multistage environment The reduction of takeoff ground roll by the application IBTN-94-EIX94311330095I D 587 A94-61063 |BTN-94-EIX94311330084| p 592 A94-61135 of a nose gear jump strut TRANSONIC FLOW TURBULENT FLOW INASA-TM-1088221 P 576 N94-36380 Navier-Stokes computations lor oscillating control One-equation turbulence model lor aerodynamic flows UPSTREAM surfaces IBTN-94-EIX94401367449I p 563 A94-61782 Ingestion into the upstream wheelspace ol an axial I BTN-94-EIX94401358983 | p 566 A94-61639 Preliminary analysis for a Mach 8 crossflow transition turbine stage Numerical investigations on two-dimensional experiment on the Pegasus (R) space booster IBTN-94-EIX94311330099I p 587 A94-61059 canard-wing aerodynamic interference |NASA-TM-104272| p 564 N94-36648 UPWIND SCHEMES (MATHEMATICS) IBTN-94-EIX94401358989I p 566 A94-61645 TURBULENT HEAT TRANSFER Unstructured mesh quality assessment and upwind Euler Computation ot transonic flows around a Study of rotor cavities and heat transfer in a cooling solution algorithm validation wing-plus-fuselage configuration taking viscous ellects and process in a gas turbine |BTN-94-EIX94401358985| p 592 A94-6164t a thin separated region into account IBTN-94-EIX94311330100I p 587 A94-61058 USER MANUALS (COMPUTER PROGRAMS) IBTN-94-EIX94401367450I D 563 A94-61783 TURBULENT MIXING Rotorwash analysis handbook. Volume 2: Appendixes TRANSONIC WIND TUNNELS Computation of supersonic jet mixing noise for an ISCT-93RR-17-VOL-2I p 567 N94-36467 axisymmetnc convergent-divergent nozzle Aerodynamic investigation with focusing Schlieren in a An arbitrary grid CFD algorithm for configuration IBTN-94-EIX94401358979I p 599 A94-61635 cryogenic wind tunnel aerodynamics analysis. Volume 2: FEMNAS user guide One-equation turbulence model for aerodynamic flows IBTN-94-EIX94421374975I p 593 A94-61873 INASA-CR-1961351 p 598 N94-36922 TRANSPORT AIRCRAFT IBTN-94-EIX94401367449I p 563 A94-61782 TRENDS: A flight lest relational database user's guide Nondimensional forms lor singular perturbation analyses TWO DIMENSIONAL FLOW and reference manual of aircraft energy climbs Review of nonsteady flow models lor compressor INASA-TM-1088061 p 564 N94-37332 IBTN-94-EIX94401358168I p 572 A94-61674 stability The future of large capacity/long range multipurpose |BTN-94-EIX94311330087| p 591 A94-61132 air cargo fleets p 573 N94-36326 Two-dimensional Euler zonal method using composite Tanker system and technology requirements definition: structured and unstructured meshes A tanker technology road map p 575 N94-36344 IBTN-94-EIX94401358986I p 566 A94-61642 TRIBOLOQY Numerical investigations on two-dimensional V/STOL AIRCRAFT Wear-resisting oxide films for 900 C canard-wing aerodynamic interference Reduction in size and unsteadiness of VTOL ground IDE94-010093I p 584 N94-36306 IBTN-94-EIX94401358989I p 566 A94-61645 vortices by ground fences TURBINE BLADES A method for flow simulation about complex geometries |BTN-94-EIX94401358975| p 565 A94-61631 Process enhancements of superalloy material using both structured and unstructured grids VAPOR DEPOSITION P 585 N94-37324 |NASA-TM-106633| p 569 N94-37283 SCS-6 (tm) fiber reinforced titanium TURBINE ENGINES TWO DIMENSIONAL MODELS p 585 N94-36652 Propulsion system selection for a High Altitude Long Numerical investigation of multi-element airfoils Manufacture and properties of Sigma fibre reinforced Endurance aircraft p 578 N94-36333 INASA-CR-1945921 p 567 N94-36394 titanium p 585 N94-36655 TURBINE WHEELS TWO PHASE FLOW VARIABLE PITCH PROPELLERS Study of rotor cavities and heat transfer in a cooling Simulation of the secondary air system of aero Investigation ot the part-load performance ol two 1.12 process in a gas turbine engines MW regenerative marine gas turbines IBTN-94-EIX94311330100I p 587 A94-6t058 |BTN-94-EIX94311330097| p 587 A94-61061 IBTN-94-EIX9431133107BI p 588 A94-61100 TURBINES Influence of high rotational speeds on heat transfer and VELOCITY DISTRIBUTION Tipjet 80-inch model rotor hover test: Test no. 1198 oil film thickness in aero-engine bearing chambers Transfer of heat by self-induced flow in a rotating tube IAD-A2796801 p 567 N94-36261 IBTN-94-EIX94311331074 | p 588 A94-61104 |BTN-94-EIX94311330098| p 587 A94-61060 TWO STAGE TURBINES TURBOCOMPRESSORS VELOCITY MEASUREMENT Study of rotor cavities and heat transfer in a cooling Active stabilization of rotating stall in a three-stage axial Rotating laser-Doppler anemometry system for unsteady compressor process in a gas turbine relative flow measurements in model centrifugal IBTN-94-EIX94311330100I p 587 A94-61058 IBTN-94-EIX94311330089I p 591 A94-61130 impellers Review of nonsteady flow models for compressor |BTN-94-EIX94311330092| p 590 A94-61127 stability |BTN-94-EIX94311330087| p 591 A94-61132 u An automated method lor Low Level Wmdshear Alert System (LLWAS) data quality analysis Unstable behavior of low and high-speed compressors IAD-A2803I3I p 596 N94-37126 IBTN-94-EIX94311330086I p 591 A94-61133 UNSTEADY AERODYNAMICS TURBOFAN ENGINES Loading characteristics of finite wings undergoing rapid VERTICAL FLIGHT Fault diagnosis in gas turbines using a model-based unsteady motions: A theoretical treatment Optimum flight trajectory guidance based on total energy technique |BTN-94-EIX94401358963| p 571 A94-61619 control of aircraft | BTN-94.EIX94311331071 | p 589 A94-61107 Unique high-alpha roll dynamics of a sharp-edged 65 |BTN-94-EIX94381311167| p 579 A94-61254 TURBOFANS deg delta wing VERTICAL LANDING Models lor predicting the performance of Brayton-cycle |BTN-94-EIX94401358966| p 571 A94-61622 Reduction in size and unsteadiness of VTOL ground engines Unsteady aerodynamic characteristics of a dual-element vortices by ground fences IBTN-94-EIX94311331072I p 589 A94-61106 airfoil IBTN-94-EIX94401358975I p 565 A94-61631 TURBOJET ENGINES IBTN-94-EIX94401358968I p 565 A94-61624 VERTICAL TAKEOFF AIRCRAFT Models for predicting the performance of Brayton-cycle Numerical investigations on two-dimensional Tipjet 80-inch model rotor hover test: Test no 1198 engines canard-wing aerodynamic interference IAD-A2796801 p 567 N94-36261 IBTN-94.EIX94311331072I p 589 A94-61106 IBTN-94-EIX94401358989I p 566 A94-61645 Analysis of vertiport studies funded by the Airport Comments on the development of the early UNSTEADY FLOW Improvement Program (AIP) Westmghouse turbojets. 1941-1946 Experimental investigation of the steady and unsteady |SCT-93RR-21| P 583 N94-37424 relative flow in a model centrifugal impeller passage |BTN-94-EIX94311331063| p 577 A94-61115 VIBRATION TURBOMACHINE BLADES IBTN-94-EIX94311330093I p 590 A94-61126 Window functions tor the calculation of the time domain Rotating laser-Doppler anemometry system lor unsteady Unsteady blade pressures on a propfan: Predicted and averages of the vibration of the individual planet gears measured compressibility effects relative flow measurements in model centrifugal and sun gear in an epicyclic gearbox IBTN-94.EIX94401358996I p 578 A94-61652 impellers IBTN-94-EIX94311331047] p 586 A94-61050 |BTN-94-EIX94311330092| p 590 A94-61127 Vortex cutting by a blade. Part 1: General theory and VIBRATION DAMPING a simple solution Review of nonsteady flow models for compressor Correlation of analytical and experimental hot structure |BTN-94.EIX94421374957| p 563 A94-61855 stability vibration results |BTN-94-EIX94311330087| p 591 A94-61132 TURBOPROP ENGINES |NASA-TM-104269| p 576 N94-36644 Whirl-flutter suppression in advanced turboprops and Unstable behavior of low and high-speed compressors Multirate flutter suppression system design tor the |BTN-94-EIX94311330086| p 591 A94-61133 propfans by active control techniques Benchmark Active Controls Technology Wing |BTN-94-EIX94401358994| p 578 A94-61650 Prediction method for unsteady axisymmetric flow over INASA-CR-1961121 p 581 N94-36965 TURBULENCE parachutes VIBRATION ISOLATORS |BTN-94-EIX94401358984| p 566 A94-61640 One-equation turbulence model for aerodynamic flows Whirl-flutter suppression in advanced turboprops and Numerical investigations on two-dimensional |BTN-94-EIX94401367449| p 563 A94-61782 preplans by active control techniques TURBULENCE EFFECTS canard-wing aerodynamic interference IBTN-94-EIX94401358994I p 578 A94-616SO IBTN-94-EIX94401358989I p 566 A94-61645 Fluctuating wall pressures near separation in highly VIBRATION MODE swept turbulent interactions Unsteady blade pressures on a propfan: Predicted and Correlation of analytical and experimental hot structure measured compressibility effects |BTN-94.EIX94421374958| p 563 A94-61856 vibration results |BTN-94-EIX94401358996| p 578 A94-61652 TURBULENCE MODELS INASA-TM-1042691 p 576 N94-36644 Boundary conditions for unsteady supersonic inlet One-equation turbulence model for aerodynamic flows VISCOSITY |BTN-94-EIX94401367449| p 563 A94-61782 analyses One-equation turbulence model lor aerodynamic flows |BTN-94-EIX94421374964| p 593 A94-61862 TURBULENT BOUNDARY LAYER |BTN-94-EIX94401367449| p 563 A94-61782 Laser interferometer skin-friction measurements of Low-dimensional description of the dynamics in VISCOUS FLOW crossing-shock-wave/turbulent-boundary.layer separated flow past thick airfoils Computation of transonic flows around a ns |BTN-94-EIX94421374967| p 563 A94-61865 wing-plus-tuselage configuration taking viscous elfects and |BTN-94-EIX94421374974| p 593 A94-61872 Experimental investigation of nozzle/plume a thin separated region into account TURBULENT DIFFUSION aerodynamics at hypersonic speeds IBTN-94-EIX94401367450I p 563 A94-61783 Spanwise transport in axial-flow turbines. Part 2: INASA-CR-1958291 p 568 N94-36687 Low-dimensional description of the dynamics in Throughflow calculations including spanwise transport Unsteady flow field of large-amplitude pitching airfoils separated flow past thick airfoils |BTN-94-EIX94311330085| p 591 A94-61134 |AD-A280444| p 569 N94-37219 |BTN-94-EIX94421374967| p 563 A94-61865

A-17 VORTEX BREAKDOWN SUBJECT INDEX

VORTEX BREAKDOWN Lift enhancement ol an airfoil using a Gurney flap and Leading-edge vortex breakdown for wing planlorms with vortex generators the same slenderness ratio |BTN-94-EIX94401358970| p 565 A94-61626 | BTN-94-EIX94401358991 I p 566 A94-61647 Wind-tunnel test techniques for unmanned aerial vehicle VORTEX FILAMENTS separation investigations Vortex cutting by a blade. Part 1: General theory and |BTN-94-EIX9440t358976| p 571 A94-61632 a simple solution Active control of wing rock using tangential leading-edge |BTN-94-EIX94421374957| p 563 A94-61855 blowing VORTEX GENERATORS |BTN-94-EIX94401358987| p 571 A94-61643 Lilt enhancement ol an airloil using a Gurney Map and WIND VELOCITY vortex generators An automated method for Low Level Windshear Alert |BTN-94-EIX94401358970| p 565 A94-61626 System (LLWAS) data quality analysis VORTICES |AD-A280313| P 596 N94-37126 Simulation ol the secondary air system ol aero WING LOADING engines Loading characteristics ol finite wings undergoing rapid IBTN-94-EIX94311330097I p 587 A94-61061 unsteady motions: A theoretical treatment Experimental investigation ol the steady and unsteady IBTN-94-EIX94401358963I P 571 A94-61619 relative How in a model centrifugal impeller passage The reduction of takeoff ground roll by the application IBTN-94-EIX9431I330093I p 590 A94-61126 of a nose gear jump strut Effects ol nozzle exit geometry on forebody vortex | NASA-TM-1088221 p 576 N94-36380 control using blowing WING OSCILLATIONS |BTN.94-EIX9440I358964| p 564 A94-6I620 Loading characteristics of finite wings undergoing rapid Reduction in size and unsteadiness of VTOL ground unsteady motions: A theoretical treatment vortices by ground fences |BTN-94-EIX94401358963| p 571 A94-61619 I8TN-94.EIX94401358975I p 565 A94-61631 Multirate flutter suppression system design for the Multidomam method for several bodies in relative Benchmark Active Controls Technology Wing motion INASA-CR-1961121 P 581 N94-36965 IBTN-94-EIX94401367452I p 563 A94-61785 WING PROFILES Numerical simulation ol vortex-wedge interaction Equivalent plate structural modeling for wing shape IBTN-94-EIX94421374955I p 592 A94-61853 optimization including transverse shear Vonex cutting by a blade. Part 1: General theory and |BTN-94-EIX94421374979| p 564 A94-61877 a simple solution WING TANKS |BTN-94-EIX94421374957| p 563 A94-61855 Flight test certification of a 480 gallon composite fuel tankonCF-18 p 574 N94-36340 WINGS w Loading characteristics of finite wings undergoing rapid unsteady motions: A theoretical treatment WAKES |BTN-94-EIX94401358963| p 571 A94-61619 Drag and wake modification of axisymmetnc bluff bodies Computation ol transonic flows around a using Coanda blowing wing-plus-fuselage configuration taking viscous effects and IBTN-94-EIX9440135B974I p 565 A94-61630 a thin separated region into account One-equation turbulence model lor aerodynamic Hows |BTN-94-EIX94401367450| p 563 A94-61783 |BTN-94-EIX94401367449| p 563 A94-61782 Aeroservoelastic tailoring with piezoelectric materials: Multidomam method lor several bodies in relative Actuator optimization studies motion |AD-A278640| p 581 N94-36384 |BTN-94-EIX9440t367452| p 563 A94-61785 WALL PRESSURE Fluctuating wall pressures near separation in highly swept turbulent interactions IBTN-94-EIX94421374958I p 563 A94-61856 X-31 AIRCRAFT WARNING SYSTEMS Controlling forebody asymmetries in flight: Experience An automated method (or Low Level Windshear Alert with boundary layer transition strips System (LLWAS) data quality analysis INASA-TM-4595I p 568 N94-36944 |AD-A280313| p 595 N94-37126 WASTE ENERGY UTILIZATION Selection criteria for plain and segmented tinned tubes for heat recovery systems IBTN-94-EIX94311331076I p 588 A94-61102 YAW WEAR RESISTANCE Some basic considerations on angles describing airplane Wear-resisting oxide films lor 900 C flight maneuvers IDE94-010093I p584 N94.36306 |BTN-94-EIX94381311179| p 570 A94-61266 WEDGES YAWING MOMENTS Numerical simulation ol vortex-wedge interaction Controlling forebody asymmetries in flight: Expenence IBTN-94-EIX94421374955I p 592 A94-61853 with boundary layer transition strips WEIGHTING FUNCTIONS | NASA-TM-45951 p 568 N94-36944 Experimental design of Hlsub infinity) weighting functions for flight control systems |BTN-94-EIX94401358163| p 580 A94-61669 WIND MEASUREMENT An automated method lor Low Level Windshear Alert System (LLWAS) data quality analysis |AD-A280313| p 596 N94-37126 WIND SHEAR An automated method for Low Level Windshear Alert System (LLWAS) data quality analysis IAD-A280313] p 596 N94-37126 WIND TUNNEL APPARATUS Three-dimensional force data acquisition and boundary corrections for the Walter H. Beech Memorial 7x10 loot low speed wind tunnel IAR93-21 p 582 N94-36437 WIND TUNNEL CALIBRATION Three-dimensional force data acquisition and boundary corrections lor the Walter H. Beech Memorial 7x10 loot low speed wind tunnel IAR93-2I p582 N94-36437 WIND TUNNEL MODELS Three-dimensional force data acquisition and boundary corrections for the Walter H. Beech Memorial 7x10 foot low speed wind tunnel (AH93-2J p582 N94-36437 WIND TUNNEL TESTS Experimental investigation on selecting the ramp and lip parameters of a two-dimensional external compression inlet IBTN-94-EIX94381353570I p 577 A94-61460

A-18 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 309) October 1994

Typical Personal Author Index Listing ANANTHASWAMY. V. BEIER. K. J. Influence ol aerodynamic forces in ice shedding Investigation of the pan-load performance of two 1.12 |BTN-94-EIX94401358967| p 564 A94-61623 MW regenerative marine gas turbines I PERSONAL AUTHOR | ANDERSON. MELVIN S. | BTN-94-EIX94311331078 I p 588 A94-61100 Buckling and vibration analysis of laminated panels using BERARDO. STEPHEN V. VICONOPT Analysis ol vertiporl studies funded by the Airport IBTN-94-EIX94401372105I p 592 A94-61805 Improvement Program (AIP) ANDRISANI, DOMINICK, II ANDRISANI, DOMINICK. II ISCT-93RR-21 | p 583 N94-37424 Gain weighted eigenspace assignment BERCHTOLD. G. — A feasibility study regarding the addition of a fifth control |NASA-TM-109130| P 581 N94-36820 Optimisation of composite aircraft structures by direct to a rotorcraft in-flight simulator AOKI. S. manufacturing approaches p 574 N94-36327 [NASA-CR-193240] pi 12 N94-10895 New high-efliciency heavy-duty combustion turbine BERG. MARTIN C. 701F Multirate flutter suppression system design for the REPORT |BTN-94-EIX94311331073| p 588 A94-61105 Benchmark Active Controls Technology Wing J TITLE NUMBER AOYAMA, K. INASA-CR-1961121 p 581 N94-36965 New high-efficiency heavy-duty combustion turbine BERGMANN. J. W. 701F Predicting defect behaviour p 596 N94-37331 IBTN-94-EIX94311331073I p 588 A94-61105 BERRY. JOHN D. ARNAL, 0. Navier-Stokes and potential theory solutions for Listings in this Index are arranged alphabetically Laminar How studies at Dassault Aviation: Calculations ahehcopter fuselage and companson with experiment by personal author. The title of the document and flight tests p 593 N94-36328 |NASA-TM-4566| p 569 N94-36966 is used to provide a brief description of the AUERNHEIMER, BRENT BHAVNANI, S. H. Applying formal methods and object-oriented analysis Mainstream ingress suppression in gas turbine disk subject matter. The report number helps to to existing flight software p 597 N94-3649S cavities indicate the type of document (e.g., NASA |BTN-94-EIX94311330101| P 586 A94-61057 report, translation, NASA contractor report). The BIEDERMAN, B. P. page and accession numbers are located B Advanced transonic fan design procedure based on a beneath and to the right of the title. Under any Navier-Stokes method one author's name the accession numbers are BABIKYAN, CAROL A. IBTN-94-EIX94311330095I p 587 A94-61063 Advanced information processing system: The Army BILLET, M. L. arranged in sequence. Fault-Tolerant Architecture detailed design overview Reduction in size and unsteadiness of VTOL ground | NASA-CR-194924 | p 598 N94-36962 vortices by ground fences BADGER, M. IBTN-94-EIX94401358975I p 565 A94-61631 PT6 engine: 30 years of gas turbine technology BJORKMAN, W. S. evolution TRENDS: A flight test relational database user's guide |BTN-94-EIX94311331064| p 577 A94-61114 and reference manual BAILEY, JOHN |NASA-TM-108806| p 564 N94.37332 BOCVAROV, SPIRO ABRAHAMS, I. DAVID Impact of Ada in the Flight Dynamics Division: Sound radiation and caustic formation from a point Excitement and frustration p 597 N94-3650I Some nonintuitive features in time-efficient attitude source in a wall shear layer maneuvers of combat aircraft BAKER, A. J. |BTN-94-EIX94381311180| p 570 A94-61267 |BTN-94-EIX94421374956| p 599 A94-61854 An arbitrary grid CFD algorithm for configuration Significance of the dihedral effect in rapid ABRAMIAN, M. aerodynamics analysis. Volume 1: Theory and tuselage-reorientation maneuvers Experimental investigation of the steady and unsteady validations IBTN-94-EIX94401358971] p 571 A94.61627 relative flow in a model centrifugal impeller passage INASA-CR-1959181 p 598 N94-36914 BOGDANOFF, DAVID W. |BTN-94-EIX94311330093| p 590 A94-61126 An arbitrary grid CFD algorithm for configuration Experimental investigation ot nozzle/plume Rotating laser-Doppler anemometry system for unsteady aerodynamics analysis. Volume 2: FEMNAS user guide aerodynamics at hypersonic speeds relative flow measurements in model centrifugal INASA-CR-1961351 p 598 N94-36922 INASA-CR-195829I p 568 N94.36687 impellers BANDA, SIVA S. BOND), M. J. |BTN-94-EIX94311330092| p 590 A94-61127 Reduced-order H(INF) compensator design for an TRENDS: A flight test relational database user's guide ADAMS. MARY S. aircraft control problem and reference manual Automatic procedures for computing complete |BTN-94-EIX94381311174| p 579 A94-6126t INASA-TM-1088061 p 564 N94-37332 configuration geometry from individual component Implementation of a full-envelope controller lor a BONK, D. descriptions high-performance aircraft Effect ot pressure on second-generation pressurized | NASA-TM-4607 | p 568 N94-36942 IBTN-94-EIX94401358167I p 580 A94-61673 lluidized bed combustion plants Automatic computation of Euler-marching and subsonic BARGER, RAYMOND L. |BTN-94-EIX94311331067| p 589 A94.61111 grids lor wing-fuselage configurations Automatic procedures for computing complete BOTROS, K. K. | NASA-TM-45731 p 568 N94-36950 configuration geometry from individual component Developments in centrifugal compressor surge control ADAMS, RICHARD J. descriptions A technology assessment Reduced-order H(INF) compensator design for an | NASA-TM-46071 p 568 N94-36942 IBTN-94-EIX94311330090I p 590 A94-61129 aircraft control problem Automatic computation of Euler-marching and subsonic BRADY, C. 0. |BTN-94-EIX94381311174| p 579 A94-61261 grids lor wing-fuselage configurations Increased use of gas turbines as commercial marine Implementation of a full-envelope controller for a I NASA-TM-4573 I p 568 N94-36950 engines high-performance aircraft BARGETTO, R. IBTN-94-EIX943D331080I p 588 A94-6I098 |BTN-94-EIX94401358167| p 580 A94-61673 Technological challenges of High Altitude Long BRAGDON, CLIFFORD R. Analysis of vertiport studies funded by the Airport ADIBNAZARI. SAEED Endurance unmanned configurations p573 N94-36323 Improvement Program (AIP) Literature review and preliminary studies of fretting and | SCT-93RR-21 | p 583 N94-374J4 fretting fatigue including special applications to aircraft BARLAS, M. REMZI BRINKGREVE, PAUL R. joints Nonlinear model-following control application to airplane The KDC-10 programme of the Royal Netherlands Air | AD-A2803101 P594N94-37125 control Force p 575 N94-36346 ALLMARAS. S. R. IBTN-94-EIX94401358166I p 580 A94-61672 BRITCHER. COLIN P. One-equation turbulence model for aerodynamic flows BATINA, JOHN T. Large angle magnetic suspension test fixture |BTN-94-EIX94401367449| p 563 A94-61782 Unstructured mesh quality assessment and upwind Euler | NASA-CR-1961381 p 583 N94-37450 AMANO. R. S. solution algorithm validation BRONCONI, R. Study of rotor cavities and heat transfer in a cooling IBTN-94-EIX94401358985I p 592 A94-61641 Performance and economic enhancement of process in a gas turbine BATTISSON, C. J. cogeneration gas turbines through compressor inlet air |BTN-94-EIX94311330100| p 587 A94-61058 EH101: A new helicopter capable of long range cooling ANANDAN, MUNISAMY missions P 574 N94-36330 |BTN-94-EIX94311331069| p 589 A94-61109 Design ol a multi-channel true flat fluorescent lamp for BAUGHCUM, STEVE BROOKS, THOMAS F. avionic AM-LCD backlighting Project report: Aircraft Forward sweep, low noise rotor blade |BTN-94-EIX94311330477| p 592 A94-61203 IDE94-011759I p596 N94-37155 |NASA-CASE-LAR-14569-1| p 576 N94-36767 B-1 BROWN, EUGENE F. PERSONAL AUTHOR INDEX

BROWN. EUGENE F. CHU. M. L. DOEL. D. L. Inlet drag prediction for aircraft conceptual design Influence of aerodynamic forces in ice shedding Assessment ol weighted-least-squares-based gas path IBTN-94-EIX94401358981 | p 565 A94-61637 IBTN-94-EIX94401358967] p 564 A94-61623 analysis BUFFINGTON. JAMES M. CIMBALA. J. M. IBTN-94-EIX94311331070I P 589 A94-61108 Implementation of a full-envelope controller for a Reduction in size and unsteadiness of VTOL ground DOMAS. P. A. hign-performance aircraft vortices by ground fences Substantiating powder metal life methodologies for IBTN-94-EIX94401358167I p 580 A94-61673 IBTN-94-EIX94401358975I p 565 A94-61631 engines P 595 N94-37330 BULGUBURE, C. CLARK. DAVID A. DURHAM. WAYNE C. Laminar flow studies at Dassault Aviation: Calculations An automated method for Low Level Wmdshear Alert Constrained control allocation: Three-moment problem IBTN-94-EIX94381311172I p 579 A94-61259 and flight tests p 593 N94-36328 System (LLWAS) data quality analysis Nonlinear model-fotfowing control application to airplane BUTLER. BRYAN P. IAD-A280313I p 596 N94-37I26 Advanced information processing system: The Army control CLASEN. ROBERT J. Fault-Tolerant Architecture detailed design overview IBTN-94-EIX94401358166I p 580 A94-61672 Advanced information processing system: The Army |NASA-CR-194924| p 593 N94-36962 DYER. JOHN C. Fault-Tolerant Architecture detailed design overview BYRNS. EDWARD V. JR. Coping with the defense cutback |NASA-CR-194924| p 598 N94-36962 Approximate recovery of H-mfimty loop shapes using IBTN-94-EIX94401216109I p 563 A94-61788 fixed-order dynamic compensation CLIFF. EUGENE M. DYMENT, RICHARD J. Some nonintuitive features in time-efficient attitude IBTN-94-EIX94401358152I p 580 A94-61658 Analysis ot vertiport studies funded by the Airport maneuvers of combat aircraft Improvement Program (AIP) IBTN-94-EIX943B1311180I p 570 A94-61267 ISCT-93RR-21I P583 N94-37424 Range optimal trajectories tor an aircraft Hying in the vertical plane CAUSE, A. J. IBTN-94-EIX94381311181I p571 A94-61268 Nondimensional forms for singular perturbation analyses Significance of the dihedral eflect in rapid of aircraft energy climbs fuselage-reorientation maneuvers ENGELBERT, HANS-PETER IBTN-94-EIX94401358168I p 572 A94-61674 IBTN-94-EIX94401358971 | p 571 A94-61627 Landing of an unmanned helicopter on a moving CALISE. ANTHONY J. COBLEIGH. BRENT R. platform. High accuracy navigation and tracking Approximate recovery of H-infmity loop shapes using Controlling lorebody asymmetries in flight: Experience p 576 N94-36618 fixed-order dynamic compensation with boundary layer transition strips EPPEL, JOSEPH C. IBTN-94-EIX944013581S2I p 580 A94-61658 I NASA-TM-4595 I p 568 N94-36944 The reduction of takeoff ground roll by the application CALVERT, W. J. of a nose gear jump strut COLIN, PH. INASA-TM-1088221 p 576 N94-36380 Detailed (low measurements and predictions for a Calculations used to optimize the installation of civil three-stage transonic fan aircraft engines p 574 N94-36332 EPSTEIN, A. H. | BTN-94-EIX94311330096] p 587 A94-61062 Active stabilization of rotating stall in a three-stage axial COSTA. PETER J. compressor CAMBIER, JEAN-LUC Adaptive model architecture and extended Kalman-Bucy IBTN-94-EIX94311330089I p 591 A94-61130 Expenmental investigation of nozzle/plume filters aerodynamics at hypersonic speeds |BTN-94-EIX94401377806| p 592 A94-61767 ERICSSON. l_ E. INASA-CR-1958291 p 568 N94-36687 Unique high-alpha roll dynamics of a sharp-edged 65 COURTY, J. C. deg delta wing CAMPO. E. Laminar flow studies at Dassault Aviation: Calculations IBTN-94-EIX94401358966I p 571 A94-61622 Turbine disks: tiling against detects and materials and flight tests p 593 N94-36328 development p 595 N94-37329 CROSS, J. L, ESAY. BILL CARALP. M. TRENDS: A flight test relational database user's guide Analysis and control of bifurcation phenomena in aircraft Maintaining constant standards during the forging and reference manual flight process p 586 N94-37326 INASA-TM-1088061 p 564 N94-37332 IBTN-94-EIX94401358169I p 572 A94-61675 CARNEVALE, E. CUMMINGS, RUSSELL M. ETLINGER. HANK Performance and economic enhancement of Numerical investigation of multi-element airfoils Design of a multi-channel true flat fluorescent lamp for cogeneration gas turbines through compressor inlet air INASA-CR-1945921 p 567 N94-36394 avionic AM-LCD backlighting cooling CUSHING, STEVEN |BTN-94-EIX94311330477| p 592 A94-61203 IBTN-94-EIX94311331069I p 589 A94-61109 An error-resistant linguistic protocol for air traffic EVERETT. M. E. CARR. WILLIAM control Sensor data fusion for air to air situation awareness Design of a multi-channel true flat fluorescent lamp for INASA-CR-1960981 p 570 N94-37013 beyond visual range p 598 N94-36633 avionic AM-LCD backlighting CYRUS, JOHN D. |BTN-94-EIX94311330477| p 592 A94-61203 Propulsion system selection for a High Altitude Long CEBECI, TUNCER Endurance aircraft p 578 N94-36333 Calculation of three-dimensional low Reynolds number flows FAN, YANG-TA |BTN-94-EIX94401358973| p 565 A94-61629 New output feedback design in variable structure CHAFFIN, MARK S. systems DAVIDSON, JOHN B. IBTN-94-EIX94381311173I p 597 A94-61260 Navier-Stokes and potential theory solutions for Gain weighted eigenspace assignment aheficopter fuselage and comparison with experiment INASA-TM-1091301 p 581 N94-36820 FERGUSON. SAMUEL W. Rotorwash analysis handbook. Volume 1: Development | NASA-TM-45661 p 569 N94-36966 Predicting the effects of unmodeled dynamics on an CHEN. F. Y. aircraft flight control system design using eigenspace and analysis Stability of skew plates subjected to aerodynamic and assignment ISCT-93RR-17-VOL-1 | p 567 N94-36466 in-plane forces INASA-TM-4548] p 582 N94-37059 Rotorwash analysis handbook. Volume 2: Appendixes IBTN-94-EIX94321331202I p 592 A94-61615 DAY, I. J. ISCT-93RR-17-VOL-2I p 567 N94-36467 CHEN. HSUN H. Unstable behavior of low and high-speed compressors Analysis of vertiport studies funded by the Airport Calculation of three-dimensional low Reynolds number IBTN-94-EIX94311330086I p 591 A94-61133 Improvement Program (AIP) flows DEANE, ANIL E. ISCT-93RR-21I p 583 N94-37424 IBTN-94-EIX94401358973I p 565 A94-61629 Low-dimensional description of the dynamics in FERTIS, DEMETER G. CHEN. L, T. separated flow past thick airfoils New airfoil-design concept with improved aerodynamic Two-dimensional Euler zonal method using composite |BTN-94-EIX94421374967| p 563 A94-61865 characteristics structured and unstructured meshes DEATON, VIVIAN C. IBTN-94-EIX94401372110I p 567 A94-61810 |BTN-94-EIX94401358986| p 566 A94-61642 Correlation of analytical and experimental hot structure FISHER. DAVID F. CHENG, BETTY H. C. vibration results Controlling forebody asymmetries in flight: Experience Applying formal methods and object-oriented analysis INASA-TM-1042691 p 576 N94-36644 with boundary layer transition strips to existing (light software p 597 N94-36495 DEBONIS, JAMES R. | NASA-TM-45951 p 568 N94-36944 A method for flow simulation about complex geometries CHENG. PETER Y. FLETCHER, A. R., JR. Aeroservoelastic stabilization considerations lor pointing using both structured and unstructured grids Electric drives on the LVIOO gas turbine engine and tracking systems p 594 N94-36627 INASA-TM-1066331 p 569 N94-37283 |BTN-94-EIX94311331077| p 588 A94-61101 DEFREVILLE, CHARLES FRANZ. JOSEPH CHEVET, F. In-flight refueling: Dassault Aviation research on the Propulsion system selection for a High Altitude Long Maintaining constant standards during the forging Rafale aircraft p 574 N94-36341 Endurance aircraft p 578 N94-36333 process p 586 N94-37326 • DELUCIA, M. CHIN. V. Performance and economic enhancement of FREDIANI, ALOO Two-dimensional Euler zonal method using composite cogeneration gas turbines through compressor inlet air Turbine disks: Lifing against defects and materials development p 59S N94-37329 structured and unstructured meshes cooling |BTN-94-EIX94401358986| p 566 A94-61642 IBTN-94-EIX94311331069I p 589 A94-61109 FREEMAN, C. CHIN, VAN-SHIN DEVADIGA, SADASHIVA Stall inception and development in an axial flow Numerical investigations on two-dimensional A model-based approach for detection ol runways and aeroengine canard-wing aerodynamic interference other objects in image sequences acquired using an IBTN-94-EIX94311330088I p 591 A94-61131 |BTN-94-EIX94401358989| p 566 A94-61645 on-board camera Unstable behavior of low and high-speed compressors CHOKANI, NDAONA INASA-CR-1964241 p 594 N94-36812 |BTN-94-EIX94311330086| p 591 A94-61133 Edects of nozzle exit geometry on forebody vortex DICKMANNS, E. D. FREEMAN. R. C. control using blowing Two-axis camera platform for machine vision Sensor data fusion for air to air situation awareness |BTN-94-EIX94401358964| p 564 A94-61620 p 597 N94-3662B beyond visual range p 598 N94-36633

B-2 PERSONAL AUTHOR INDEX KATO, OSAMU

FREUND. J. B. H HUGUENIN. YVES Drag and wake modification ot axisymmetnc bluff bodies Laser designation pods optimized concept for day/night using Coanda blowing HALSKI, P. J. operations P 594 N94-36620 |BTN-94-EIX9440I35B974| p 565 A94-61630 ICAAS piloted simulation results p 593 N94-36617 HUNZIKER, R. FUKUE. I. HANFF. f.. S. Operational stability of a centrifugal compressor and its New high-elficiency heavy.duly combustion turbine Unique high-alpha roll dynamics ol a sharp-edged 65 dependence on the characteristics ol the 701F deg delta wing subcomponents |BTN-94-EIX94311331073| p 588 A94-61105 IBTN-94-EIX94401358966I P 571 A94-61622 IBTN-94-EIX943I1330091] P 590 A94-61128 HARMAN. T. B. Reduction m size and unsteadiness of VTOL ground vortices by ground fences IBTN-94-EIX94401358975I p 565 A94-61631 HARPER. RICHARD E. IANNELLI, G. S. GALATOLO. ROBERTO Advanced information processing system: The Army An arbitrary grid CFD algorithm for configuration Turbine disks: Lifing against defects and materials Fault-Tolerant Architecture detailed design overview aerodynamics analysis. Volume 1: Theory and development p 595 N94-37329 |NASA-CR-194924| p 598 N94-36962 validations INASA-CR-1959181 p 598 N94-36914 GALVANI. J.-L. HARRIS. CHRIS H. IVEY. P. C. Future supersonic commercial transDort aircraft: A Advanced information processing system: The Army Transfer of heat by self-induced flow m a rotating tube technological challenge for long haul traffic Fault-Tolerant Architecture detailed design overview IBTN-94-EIX94311330098I p 587 A94-61060 p 573 N94-36324 |NASA-CR-194924| p 598 N94-36962 GARG. VIJAY K. HARRISON. G. f. Prediction of film cooling on gas turbine airfoils Defects and their effects on the integrity of nickel based aeroengine discs p 586 N94-37328 INASA-TM-1066531 p 579 N94-37448 HAYNES, J. M. GARRISON. T. J. JACKSON, E. BRUCE Active stabilization of rotating stall in a three-stage axial Laser interferometer skin-friction measurements of Preliminary piloted simulation studies ol the HL-20 lifting compressor body crossmg-shock-wave/lurbulenl-boundary-iayer IBTN-94-EIX94311330089I p 591 A94-61130 ns IBTN-94-EIX94401358972I P 583 A94-61628 HEFAZI, H. |BTN-94-£IX94421374974| p 593 A94-61872 JANG, CORY S. Two-dimensional Euler zonal method using composite Lift enhancement of an airfoil using a Gurney flap and GARTENBERG. EHUD structured and unstructured meshes Aerodynamic investigation with focusing Schlieren in a vortex generators IBTN-94-EIX94401358986I p 566 A94-61642 IBTN-94-EIX94401358970I p 565 A94-61626 cryogenic wind tunnel HEMSCH, MICHAEL J. IBTN-94-EIX94421374975I p 593 A94-61873 JATEGAONKAR. R. V. Leading-edge vortex breakdown for wing planlorms with Evaluation of parameter estimation methods for unstable GARWOOD, K. R. the same slenderness ratio Propulsion system technologies for long range and long aircraft IBTN-94-EIX94401358991 | p 566 A94-61647 IBTN-94-EIX94401358965I P 580 A94-61621 endurance aircraft p 578 N94-36334 HENDERSON, J. F. JENKINS, RICHARD C. GAUGLER. RAYMOND E. Developments in centrifugal compressor surge control: A mean value analysis heuristic for analysis of aircraft Prediction of film cooling on gas turbine airfoils A technology assessment sortie generation |NASA-TM-106653| p 579 N94-37448 |BTN-94-EIX94311330090| p 590 A94-61129 IAD-A2785781 p 598 N94-36970 GENEROLI, ROBERT M. HENDRICKS, G. J. JOHNSON. BONNIE L Preload release mechanism Active stabilization of rotating stall in a three-stage axial Three-dimensional force data acquisition and boundary INASA-CASE-MSC-22327.il p 594 N94-36839 compressor corrections tor the Walter H. Beech Memorial 7 x 10 foot GHOSE. D. |BTN-94-EIX94311330089| p 591 A94-61130 low speed wind tunnel On the generalization of true proportional navigation HENSHAW, JIM IAR93-2I p582 N94-36437 IBTN-94.EIX94401377B08I p 570 A94-61769 SCS-6 (tm) fiber reinforced titanium JOHNSON. ERIC N. GHOSE, DEBASHISH p 585 N94-36652 Predicting the effects of unmodeled dynamics on an Capture region for true proportional navigation guidance HIMMELSBACH, J. aircraft flight control system design using eigenspace with nonzero miss-distance Influence of high rotational speeds on heat transfer and assignment IBTN-94-EIX94401358176I p 570 A94-61682 oil film thickness in aero-engine bearing chambers INASA-TM-4548I p 582 N94-37059 |BTN-94-EIX94311331074| p 588 A94-61104 GILHAM, S. JONES. HENRY E. HOBBS, D. E. Transfer of heat by sell-induced flow in a rotating tube Sensitivity derivatives for three-dimensional supersonic Advanced transonic fan design procedure based on a IBTN-94-EIX94311330098I p 587 A94-61060 Euler code using incremental iterative strategy Navier-Stokes method IBTN-94-EIX94421374969I p 593 A94-61867 GITTNER, NATHAN M. |BTN-94-EIX94311330095| p 587 A94-61063 JONES, J. WAYNE Eflecls of nozzle exit geometry on forebody vortex HOEPPNER, DAVID control using blowing Possibilities and pitfalls in aerospace applications ol Literature review and preliminary studies of fretting and titanium matrix composites p 585 N94-36650 |BTN-94-EIX94401358964| p 564 A94-61620 fretting fatigue including special applications to aircraft JONES, W. D. GLAHN. A. joints Influence of high rotational speeds on heat transfer and Electric drives on the LV100 gas turbine engine IAD-A280310I p 594 N94-37125 |BTN-94-EIX9431t331077| p 588 A94-61101 oil film thickness in aero-engine bearing chambers HOEPPNER, DAVID W. |BTN-94-EIX94311331074| p 588 A94-61104 JORDAN, LA VON History and prognosis of material discontinuity effects Future tanker considerations and requirements GONG, LESLIE on engine components structural integrity p 575 N94-36342 Preliminary analysis lor a Mach 8 crossflow transition p595 N94-37322 JU. HANN-SHING experiment on the Pegasus (Ft) space booster HOLCOMB. DARRELL H. Experimental design ol H(sub infinity) weighting |NASA-TM-104272| p 564 N94-36648 Aircraft battle damage repair for the 1990's and functions for flight control systems CODDLING. J. S. beyond |BTN-94-EIX9440t358163| p 580 A94-61669 Mainstream ingress suppression in gas turbine disk IAD-A278635I p 576 N94-36465 JULIEN. A. cavities HOLLAND, SCOTT D. PT6 engine: 30 years of gas turbine technology | BTN-94-EIX94311330101 | p 586 A94-61057 Inviscid parametric analysis of three-dimensional inlet evolution GORDON, IAN performance |BTN-94-EIX94311331064| p 577 A94-61114 Training and operations support system (TOPS) IBTN-94-EIX94401358980I p 578 A94-61636 JUMPER, ERIC J. p599 N94-37344 HOU, GENE W. Loading characteristics of finite wings undergoing rapid GRABOWSKI, L. Sensitivity derivatives lor three-dimensional supersonic unsteady motions: A theoretical treatment Defects and their effects on the integrity of nickel based Euler code using incremental iterative strategy IBTN-94-EIX94401358963] p 571 A94-61619 aeroengine discs p 586 N94-37328 IBTN-94-EIX94421374969I p 593 A94-61867 GREEN, T. HOWARD, J. H. G. Ingestion into the upstream wheelspace of an axial Experimental investigation of the steady and unsteady K turbine stage relative flow in a model centrifugal impeller passage |BTN-94-EIX94311330099| p 587 A94-61059 IBTN-94-EIX94311330093I p 590 A94-61126 KARAS. O. V. Computation of transonic flows around a Rotating laser-Doppleranemometry system for unsteady QUO. R. W. wing-plus-fuselage configuration taking viscous effects and Swirl control in an S-duct at high angle of attack relative flow measurements in model centrifugal a thin separated region into account |BTN-94-EIX94421374970| p 563 A94-61868 impellers |BTN-94-EIX94401367450| p 563 A94-61783 QUO, SUO-FENG |BTN-94-EIX94311330092| p 590 A94-61127 KARPOUZIAN, G. Optimum flight trajectory guidance based on total energy HSU, CHIN S. Comprehensive model of anisotropic composite aircraft control of aircraft Reduced-order H(INF) compensator design for an wings suitable tor aeroelastic analyses |BTN-94-EIX94381311167| p 579 A94-61254 aircraft control problem IBTN-94-EIX94401358993I p 572 A94-61649 GURUSWAMY, GURU P. |BTN-94-EIX943813t1174| p 579 A94-61261 KASTURI, RANGACHAR Navier-Stokes computations lor oscillating control HUBERSON, S. A model-based approach for detection of runways and surfaces Multidomain method for several bodies in relative other objects in image sequences acquired using an |BTN-94-EIX94401358983| p S66 A94-61639 motion on-board camera GYARMATHY, G. IBTN-94-EIX94401367452I p 563 A94-61785 |NASA-CR-196424| p 594 N94-36812 Operational stability of a centrifugal compressor and its HUGO. RONALD J. KATO. OSAMU dependence on the characteristics ol the Loading characteristics of finite wings undergoing rapid Some basic considerations on angles describing airplane subcomponents unsteady motions: A theoretical treatment flight maneuvers IBTN-94-EIX94311330091 | p 590 A94-61128 IBTN-94-EIX94401358963I p 571 A94-61619 |BTN-94-EIX94381311179| p 570 A94-61266

B-3 KEHOE, MICHAEL W. PERSONAL AUTHOR INDEX

KEHOE. MICHAEL W. LUCK. D. L. Correlation ol analytical and experimental hot structure Increased use ol gas turbines as commercial marine viDration results LABELLE. LINDA J. engines |NASA-TM-104269| p 576 N94-36644 Analysis of vertiport studies funded by the Airport IBTN-94-EIX94311331080I p 588 A94-61098 KENNEDY. DAVID Improvement Program (AIP) LUDDERS. J. RICHARD Buckling and vibration analysis ol laminated panels using ISCT-93RR-21 I p 583 N94-37424 Analysis ol vertiport studies lunded by the Airport VICONOPT LAGRANGE. MARIO B. J. Improvement Program (AIP) |BTN-94-EIX94401372l05| p 592 A94-61805 Flight test certification of a 480 gallon composite fuel |SCT-93RR-21| p583 N94-37424 KETCHUM, DOUGLAS tank on CF-18 p 574 N94-36340 LUDWIG. D. J. Design ol a multi-channel true llal lluoresceni lamp lor LALA. JAYNARAYAN H. Aerial relueling interoperability from a receiver llymg avionic AM-LCD backlighting Advanced information processing system: The Army qualities perspective p 575 N94-36343 |BTN-94-EIX94311330477| p 592 A94-61203 Faull-Tolerant Architecture detailed design overview LUTZE. FREDERICK H. KHAVARAN. ABBAS (NASA-CR-1949241 p 598 N94-36962 Some nonintuitive features in iime-eflicient attitude Computation ol supersonic jet mixing noise lor an LAMBERT. RALPH E. maneuvers ol combat aircraft axisyrnmetnc convergent-divergent nozzle Aeroservoelastic stabilization considerations lor pointing IBTN-94-EIX94381311180I P 570 A94-61267 IBTN-94-EIX94401358979I p 599 A94-61635 and tracking systems p 594 N94-36627 Significance of the dihedral effect in rapid KHILNANI. V. I. LANDY. H. J. fuselage-reonentation maneuvers Mainstream ingress suppression in gas turbine disk ICAAS piloted simulation results p 593 N94-36617 IBTN-94-EIX9440135B971I p 571 A94-61627 cavities LANGLOIS. GUY Nonlinear model-following control application to airplane | BTN-94-EIX94311330101 I p 586 A94-6I057 Training and operations support system (TOPS) control KHODADADI, J. M. p 599 N94-37344 (BTN-94-EIX9440I358I66I P 580 A94-61672 Mainstream ingress suppression in gas turbine disk LARK. KRISTINE A. LYRINTZIS. A. S. cavities Process enhancements ol superalloy material Design of optimized airfoils in subcntical flow I BTN-94.EIX94311330101 | p 586 A94-6I057 p 585 N94-37324 |BTN-94-EIX94401358990| p 566 A94-61646 KIM. CHAN M. LARSEN. JAMES M. Computation ol supersonic jet mixing noise lor an Possibilities and pitfalls in aerospace applications of axisymmetnc convergent-divergent nozzle titanium matrix composites p 585 N94-36650 M IBTN-94-EIX94401358979I p 599 A94-61635 LEBLANC. A. D. MAISEL. MARTIN D. KIRKER. ROBERT PT6 engine: 30 years of gas turbine technology The reduction ol takeolf ground roll by the application Design of a multi-channel true flat lluorescent lamp tor evolution ol a nose gear jump strut avionic AM-LCD backlighting |BTN-94-EIX94311331064| p 577 A94-61114 |NASA-TM-108822| p 576 N94-36380 |BTN-94-EIX943l1330477| p 592 A94-61203 LEE. BENG P. MALAN, PAUL KLAVETTER, E. A. Calculation of three-dimensional low Reynolds number Inlet drag prediction lor aircraft conceptual design Advanced thermally stable, coal-derived. |et fuels flows IBTN-94-EIX94401358981 I p 565 A94-61637 development program. Experiment system and model |BTN-94-EIX94401358973| p 565 A94-61629 MANHARDT, PAUL D. development LEE. DUCK JOO An arbitrary grid CFD algorithm for configuration IAD-A278968I p 584 N94-36505 Numerical simulation of vortex-wedge interaction aerodynamics analysis. Volume I: Theory and KLENNER. J. IBTN-94-EIX94421374955I p 592 A94-61B53 validations Optimisation ol composite aircraft structures by direct LEE, EDWIN E. INASA-CR-1959I8I p 598 N94-36914 manufacturing approaches p 574 N94-36327 Aerodynamic investigation with focusing Schlieren in a An arbitrary grid CFD algorithm lor conliguration KNIGHT. D. D. cryogenic wind tunnel aerodynamics analysis. Volume 2: FEMNAS user guide Laser interferometer skin-friction measurements of IBTN-94-EIX94421374975I p 593 A94-61873 INASA-CR-1961351 p 598 N94-36922 crossing-shock-wave/turbulent-boundary-layer LEIGH, JAMES E. ns Three-dimensional lorce data acquisition and boundary MARKOPOULOS, N. Nondimensional lorms (or singular perturbation analyses |BTN-94.EIX94421374974| p 593 A94-6I872 corrections lor the Waller H. Beech Memorial 7 x 10 fool of aircraft energy climbs KOENIG. G. W. low speed wind tunnel IBTN-94-EIX94401358168] p 572 A94-61674 Predicting defect behaviour p 596 N94-37331 IAR93-2I p582 N94-36437 MARSHALL, J. S. KOOCHESFAHANI. MANOOCHEHR M. LEJAMBRE. C. R. Vortex cutting by a blade. Part 1: General theory and Unsteady flow field of large-ampfitude pitching airfoils AoVanced transonic fan design procedure based on a a simple solution |AO-A280444| pseg N94-37219 Navier-Stokes method |BTN-94-EIX94421374957| p 563 A94-61855 KORAKIANITIS. T. IBTN-94-EIX94311330095I p 587 A94-61063 MARTIN. S. J. Investigation ol the part-load performance ol two 1.12 LEWIS, K. L. Advanced thermally stable, coal-derived, jet fuels MW regenerative marine gas turbines Spanwise transport in axial-How turbines. Part 2: development program. Experiment system and model IBTN-94-EIX94311331078I p 588 A94-61100 Throughllow calculations including spanwise transport development Models lor predicting the performance ol Brayton-cycle IBTN-94-EIX94311330085I p 591 A94-61134 | AD-A2789681 p 584 N94-36505 engines Spanwise transport in axial-How turbines. Part 1: The IBTN-94-EIX94311331072) p 589 A94-61106 multistage environmenl MARTINI, A. KORIAGIN, JOHN |BTN-94-EIX94311330084| p 592 A94-61135 The convertible (helicopter/airplane) EUROFAR: Tanker system and technology requirements delinition: LEWIS. MARK J. General considerations on the technical progress and on A tanker technology road map p 575 N94-36344 A fundamental study of hypersonic unstarts future advances p 574 N94-36331 KORIVI, VAMSHI MOHAN IAD-A280506I p 595 N94-37128 MASON, GREGORY S. Sensitivity derivatives tor three-dimensional supersonic LI, CHENFANG Multirate flutter suppression system design lor the Euler code using incremental iterative strategy Coating the boron particles to increase the combustion Benchmark Active Controls Technology Wing |BTN-94-EIX94421374969| p 593 A94-61867 etficiency ol boron (uel INASA-CR-1961121 p 581 N94-36965 KOVALEV, V. E. IBTN-94-EIX94381353577; p 584 A94-61473 MASON, WILLIAM H. Computation ol transonic Hows around a LI, S. Z. Chine-shaped lorebody ellects on directional stability wing-plus-fuselage configuration taking viscous effects and Wear-resisting oxide films lor 900 C at high-alpha a thin separated region into account IDE94-010093I p584 N94-36306 |BTN-94-EIX94401358961| p 579 A94-61617 IBTN-94-EIX94401367450I p 563 A94-61783 LIBRESCU, L. Computational study of Ihe F-5A lorebody emphasizing KRANTZ, TIMOTHY l_ Comprehensive model of anisotropic composite aircraft directional stability Dynamics of a split torque helicopter transmission wings suitable for aeroelastic analyses IBTN-94-EIX94401358962I p 579 A94-61618 |NASA-TM-106410| p 596 N94-37457 IBTN-94-EIX94401358993I p 572 A94-61649 MASOTTO, THOMAS K. KREJSA, EUGENE A. LIN. SAN-YIH Advanced information processing system: The Army Computation ol supersonic jet mixing noise lor an Numerical investigations on two-dimensional Fault-Tolerant Architecture detailed design overview axisymmetric convergent-divergent nozzle canard-wing aerodynamic interference I NASA-CR-194924 | p 598 N94-36962 IBTN-94-EIX94401358979] p 599 A94-61635 IBTN-94-EIX94401358989I p 566 A94-61645 MAVRIPLIS, CATHERINE LIU. SHIN-WHAR KRIEGSMANN. GREGORY A. Low-dimensional description of the dynamics in Experimental design ol Hlsub inlinity) weighting Sound radiation and caustic lormation from a point separated flow past thick airfoils source in a wall shear layer lunctions lor (light control systems |BTN-94-EIX94421374967| p 563 A94-61865 IBTN-94-EIX94401358163I p 580 A94-61669 |BTN-94-EIX94421374956| p 599 A94-61854 MAYER. DAVID W. LIVNE, ELI KRIMMER. MICHAEL Equivalent plate structural modeling lor wing shape Boundary conditions for unsteady supersonic inlet Future tanker considerations and requirements optimization including transverse shear analyses p 575 N94-36342 IBTN-94-EIX94421374979] p 564 A94-61877 IBTN-94-EIX94421374964I p 593 A94-61862 KRISHNAN. RAMKI R. LONGLEY, J. P. MCCLAIN, J. GREER Automatic computation ol Euler-marching and subsonic Review of nonsteady flow models for compressor The reduction of takeoff ground roll by the application grids lor wing-luselage configurations stability ol a nose gear jump strut |NASA-TM-4573| p 568 N94-36950 |BTN-94-EIX94311330087| p 591 A94-61132 INASA-TM-1088221 p 576 N94-36380 KUNZ, DONALD L. LOVEREN, NEDELJKO MCFADDEN, P. D. Survey and comparison ol engineering beam theones Analytic solution ol the Riccati equation for the homing Window functions lor the calculation ol the time domain lor helicopter rotor blades missile linear-quadratic control problem averages ol the vibration ol the individual planet gears |BTN-94-EIX94401358960| p 571 A94-61616 IBTN-94-EIX94401358173I p 583 A94-61679 and sun gear in an epicyclic gearbox KUTZ, K. J. LUCE. W. |BTN-94-EIX94311331047| p 586 A94-61050 Simulation ol the secondary air system ol aero The reduction ol takeoll ground roll by the application MCGINN. W. D. engines of a nose gear jump strut tnlrared search and track demonstrator programme |BTN-94-EIX94311330097| p 587 A94-61061 INASA-TM-1088221 p 576 N94-36380 p 599 N94-36622

B-4 PERSONAL AUTHOR INDEX REIF, ANDREW

MEHLHORN. R. NALLANTHIGHAL. S. PAYNTER, GERALD C. improvement of endurance performance by periodic Infrared search and track demonstrator programme Boundary conditions lor unsteady supersonic inlet optimal control ol variable camber p 581 N94-36329 p 599 N94-36622 analyses MENNE. S. NALLASAMY. M. |BTN-94-EIX94421374964| p 593 A94-61862 Computation ol three-dimensional hypersonic Hows in Unsteady blade pressures on a propfan: Predicted and PEISEN. DEBORAH J. chemical nonequilibnum measured compressibility effects Analysis of vertiport studies funded by the Airport IBTN-94-EIX94401358982I p 566 A94-61638 IBTN-94-EIX94401358996I p 578 A94-61652 Improvement Program (AIP) MEROLA. A. NARAYANSWAMI. N. ISCT-93RR-21 | P 583 N94-37424 New high-elticiency heavy-duty combustion turbine Laser interferometer skm-lriclion measurements of PERKINS. JOHN N. 701F crossmg-shock-wave/turbulent-boundary-layer Inviscid parametric analysis of three-dimensional inlet IBTN-94.EIX94311331073I p 588 A94-61105 ns performance |BTN-94-EIX94421374974| p 593 A94-61872 MERRINGTON, G. L. IBTN-94-EIX94401358980I p 578 A94-61636 NATESAN. K. Fault diagnosis in gas turbines using a model-based PERSON. LEE H.. JR. Materials performance in advanced combustion technique Takeoff performance monitoring system display I BTN-94-EIX94311331071 | p 589 A94-61107 systems options IBTN-94-EIX94311331065I p 584 A94-61113 METWALLY. MUNIR IBTN-94-EIX94401358988J p 577 A94-61644 NEWMAN. PARRY A. PETERSON, M. B. Proiecl report: Aircraft Sensitivity derivatives tor three-dimensional supersonic Wear-resisting oxide films for 900 C IDE94-01I759I p596 N94-37155 Euler code using incremental iterative strategy I DE94-010093 | p 584 N94-36306 MEYER. R. P. IBTN-94-EIX94421374969I p 593 A94-61867 ICAAS piloted simulation results p 593 N94-36617 NISHIMURA. JUN PETIT. JOCELYN I. MIDDLETON. DAVID B. Hunting phenomena of the balloon motions observed New developments in aluminum for aircraft and automobiles P 584 N94-36413 Takeoff performance monitonng system display over Antarctica options |BTN-94-EIX94401358969| p 571 A94-61625 PFITZNER, M. IBTN-94.EIX94401358988I p 577 A94-61644 NITZSCHE. F. Computation of three-dimensional hypersonic flows in MILLER. KEITH W. Whirl-flutter suppression in advanced turboprops and chemical nonequilibnum An empirical comparison of a dynamic software propfans by active control techniques |BTN-94-EIX94401358982| p 566 A94-61638 testability metric to static cyclomalic complexity |BTN-94-EIX944013S8994| p 578 A94-61650 PIELLISCH. RICHARD p 597 N94-36498 NOCETO, M. Mach 2 and more MITCHELL. ALEC New high-efficiency heavy-duty combustion turbine IBTN-94-EIX94401216108I p 569 A94-61787 Alternate melting and refining routes 701F PINSKY. MARK A. p 585 N94-37323 IBTN-94.EIX94311331073] p 588 A94-61105 Analysis and control of bifurcation phenomena in aircraft MOES. TIMOTHY R. NOONAN, C. A. flight Measurement uncertainty and feasibility study of a flush Sensor data fusion for air to air situation awareness IBTN-94-EIX94401358169I p 572 A94-61675 airdata system for a hypersonic flight experiment beyond visual range p 598 N94-36633 POISSON-OUINTON, PHILIPPE I NASA-TM-46271 p 569 N94-37378 The future of large capacity/long range multipurpose MOESSER. MARK W. air cargo fleets p 573 N94-36326 Literature review and preliminary studies of fretting and POPPEL, GARY L. fretting fatigue including special applications to aircraft OBAYASHI. SHIGERU Fiber optic (flight quality) sensors for advanced aircraft joints Navier-Stokes computations for oscillating control propulsion IAD-A280310I p 594 N94-37125 surfaces |NASA-CR-191195| p 577 N94-37401 MOGILKA. PH. IBTN-94-EIX94401358983I p 566 A94-61639 PRABHU. A. Calculations used to optimize the installation of civil OHERN. T. J. PT6 engine: 30 years of gas turbine technology aircraft engines p 574 N94-36332 Advanced thermally stable, coal-derived, jet fuels evolution MOLBAY-ARSAN. A. development program. Experiment system and model |BTN-94-EIX94311331064| p 577 A94-61114 Calculations used to optimize the installation of civil development PRIZANT. MARK J. aircraft engines p 574 N94-36332 IAD-A278968I p 584 N94-36505 Advanced information processing system: The Army MONAGHAN. RICHARD C. OLEJNICZAK, J. Fault-Tolerant Architecture detailed design overview Preliminary analysis for a Mach 8 crossflow transition Design of optimized airfoils in subcritical flow INASA-CR-194924) p 598 N94.36962 experiment on the Pegasus (R) space booster IBTN-94-EIX94401358990I p 566 A94-61646 PROFFITT, MELISSA S. |NASA-TM-104272| p 564 N94-36648 ORZECHOWSKI, J. A. Design and evaluation of a Stochastic Optimal MONTHUS, X. An arbitrary grid CFD algorithm for configuration Feed-forward and Feedback Technology (SOFFT) flight Calculations used to optimize the installation of civil aerodynamics analysis. Volume 1: Theory and control architecture aircraft engines p 574 N94-36332 validations |NASA-TP-3419| p582 N94-37014 MOORE, KEVIN A. INASA-CR-1959181 p 598 N94-36914 Three-dimensional force data acquisition and boundary An arbitrary grid CFD algorithm for configuration corrections for the Walter H. Beech Memorial 7x10 foot aerodynamics analysis. Volume 2: FEMNAS user guide Q low speed wind tunnel INASA-CR-1961351 p 598 N94-36922 IAR93-2I P582 N94-36437 OSBORNE, ROBERT C. MORAN. KENNETH J. OUINN. ROBERT D. Reduced-order H(INF) compensator design for an Preliminary analysis for a Mach 6 crossflow transition An aerodynamic and static-stability analysis of the aircraft control problem experiment on the Pegasus (R) space booster Hypersonic Applied Research Technology (HART) |BTN-94-EIX94381311174| p 579 A94-61261 |NASA-TM-104272| p 564 N94-36648 missile OSTROFF, AARON J. |AO-A280631| p 568 N94-36729 Design and evaluation of a Stochastic Optimal MOUSTAPHA. S. H. Feed-forward and Feedback Technology (SOFFT) flight PT6 engine: 30 years of gas turbine technology control architecture evolution |NASA-TP-3419| p 582 N94-37014 RAGSDALE. W. A. |BTN-94-EIX94311331064| p 577 A94-61114 OWEN, J. M. MOVER, S. A. Preliminary piloted simulation studies of the HL-20 lifting Transfer of heat by self-induced flow in a rotating tube body Wind-tunnel test techniques for unmanned aerial vehicle IBTN-94-EIX94311330098I p 587 A94-61060 separation investigations IBTN-94-EIX94401358972I p 583 A94-61628 |BTN-94-EIX94401358976| p 571 A94-61632 RAISSON. G. MUNGAL, M. G. The control of cleanness in powder metallurgy materials Drag and wake modification of axisymmetric bluff bodies for turbine disks p 586 N94-37325 using Coanda blowing PAPADOPOULOS. PERIKLES RAMAN, GANESH IBTN-94-EIX94401358974I p 565 A94-61630 Experimental investigation of nozzle/plume Mixing and noise benefit versus thrust penalty in MUNRO, BRUCE C. aerodynamics at hypersonic speeds supersonic jets using impingement tones Nonlinear model-following control application to airplane INASA-CR-1958291 p 568 N94-36687 |NASA-TM.106583| p 568 N94-36686 RAVI. R. control PARILLE, DONALD R. Chine-shaped forebody effects on directional stability IBTN-94-EIX94401358166I p 580 A94-61672 Process enhancements of superalloy material MURPHY, PATRICK C. p 585 N94-37324 at high-alpha Predicting the effects of unmodeled dynamics on an |BTN-94-EIX9440135896t| p 579 A94-61617 PARK, JIN-HO Computational study of the F-5A forebody emphasizing aircraft flight control system design using eigenspace Numerical simulation of vortex-wedge interaction assignment directional stability IBTN-94-EIX94421374955I p 592 A94-61853 |BTN-94-EIX94401358962| p 579 A94-61618 INASA-TM-4548I p 582 N94-37059 PASOUERO, G. MURRAY, S. F. REEVES, J. M. L Turbine disks: Lifing against defects and materials The case for surface effect research, platform Wear-resisting oxide films for 900 C development p 595 N94-37329 IDE94-010093I p584 N94-36306 applications and technology development opportunities PAVELIC. V. p 573 N94-36325 Study of rotor cavities and heat transfer in a cooling REID. D. R. N process in a gas turbine Selection criteria for plain and segmented finned tubes IBTN-94-EIX94311330100] p 587 A94-61058 for heat recovery systems NAGLE, GAIL A. PAYNE, JEFFREY E. |BTN-94-EIX94311331076| p 588 A94-61102 Advanced information processing system: The Army An empirical comparison ol a dynamic software REIF, ANDREW Fault-Tolerant Architecture detailed design overview testability metric to static cyclomatic complexity CC-130H(T) tactical aerial refuelling tanker development |NASA-CR-194924| p 598 N94-36962 p 597 N94-36498 flight test programme p 575 N94-36347

B-5 REISS, EDWARD L. PERSONAL AUTHOR INDEX

REISS. EDWARD U SCHNEIDER. J. W. TALBOT. M. D. Sound radiation and caustic formation from a point Replacement of silicone polymer A with silicone polymer Wind-tunnel test techniques for unmanned aerial vehicle source in a wall shear layer B and the subsequent characterization of the new cellular separation investigations IBTN-94-EIX94421374956I p 599 A94-61854 silicone materials IBTN-94-EIX94401358976I P 57t A94-61632 RENAUD. J. IDE94-010105I P 584 N94-36474 TANG. YUAN-LIANG The convertible (helicopter/airplane) EUROFAR- SCHROEDER. JOHANNES A model-based approach for detection of runways and General considerations on the technical progress and on Landing of an unmanned helicopter on a moving other objects in image sequences acquired using an luture advances p 574 N94-36331 platform. High accuracy navigation and tracking on-board camera RHIE. C. M. p576 N94-36618 |NASA-CR-196424| p 594 N94-36812 Advanced transonic tan design procedure based on a SCHWANTJE. ROBERT TATTON-BROWN. H. E. Navier-Stokes method Earth Observing System/Advanced Microwave EH101: A new helicopter capable of long range missions P 574 N94-36330 IBTN-94-EIX94311330095I p 587 A94-61063 Sounding Unit-A (EOS/AMSU-A) software management RICE. EDWARD J. Plan TAYLOR. ARTHUR C. Sensitivity derivatives for three-dimensional supersonic Mixing and noise benefit versus thrust penalty in INASA-CR-1893621 P 596 N94.36919 supersonic jets using impingement tones Euler code using incremental iterative strategy SCHWARTZ. ALAN W. INASA-TM-1065831 p 568 N94-36686 |BTN-94-EIX94421374969| p 593 A94.61867 Tipiet 80-cnch model rotor hover test: Test no. 1198 RICHARDS. W. LANCE THIELECKE. F. IAD-A279680I P 567 N94.36261 Preliminary analysis for a Mach 8 crossflow transition Evaluation of parameter estimation methods for unstable experiment on the Pegasus (R) space booster SEALS. ROBERT aircraft INASA-TM-1042721 p 564 N94-36648 Project report: Aircraft IBTN-94-EIX94401358965I P 580 A94-61621 RIVERS. ROBERT A. IDE94-011759I P596 N94-37I55 THORNTON. EARL A. Preliminary piloted simulation studies of the HL-20 lifting SETTLES, G. S. Analysis of high speed flow, thermal and structural body Laser interferometer skin-friction measurements of interactions IBTN-94-EIX94401358972I p 583 A94.61628 crossing- shock-wave/turbulent-boundary-layer INASA-CR-1960171 p 593 N94-36420 ROBERTS. L. ns TISCHLER, V. A. Active control ol wing rock using tangential leading-edge IBTN-94-EIX94421374974I p 593 A94-61872 High Altitude Long Endurance aircraft design studies blowing SEYWALD. HANS p 572 N94-36322 IBTN-94-EIX94401358987I p 571 A94-6I643 Range optimal trajectories for an aircraft flying in the TOENSKOETTER. H. ROBERTSON. A. vertical plane The STRATO 2C propulsion system: A low cost Effect of pressure on second-generation pressurized IBTN-94-EIX94381311181 I p 571 A94-61268 approach for a High Altitude Long Endurance aircraft fluidized bed combustion plants SGASLIK. ACHIM p 578 N94-36335 |BTN-94-EIX94311331067| p 589 A94-61111 Planning German Army helicopter maintenance and TOMIC. MILOS ROBERTSON. J. G. mission assignment Analytic solution of the Riccati equation for the homing Manufacture and properties of sigma fibre reinforced IAD-A280483I P 564 N94-37352 missile linear-quadratic control problem titanium p 585 N94-36655 SHEN. WEN-ZHONG IBTN-94-EIX9440I358173I p 583 A94-61679 ROCK. S. M. Multidomain method for several bodies in relative TRANTER. P. H. Active control of wing rock using tangential leading-edge motion Detects and their effects on the integrity of nickel based blowing IBTN-94-EIX94401367452I p 563 A94-61785 aeroengine discs p 586 N94-37328 IBTN-94-EIX94401358987I p 571 A94-61643 SMAILYS, A. A. TREADWELU STEVEN ROMANOV. V. I. PT6 engine: 30 years of gas turbine technology Advanced information processing system. The Army Mashproekt scientific and production association: A evolution Fault-Tolerant Architecture detailed design overview designer of gas turbines for marine and industrial IBTN-94-EIX94311331064I p 577 A94-61114 INASA-CR-1949241 p 598 N94-36962 TREMBLAY. MARC applications SONDAK. DOUGLAS CC-130H(T) tactical aerial refuelling tanker development IBTN-94-EIX94311331079I p 588 A94-61099 Turbulence modeling of free shear layers for high flight test programme p 575 N94-36347 ROSSO. M. performance aircraft TROTT. W. New high-efficiency heavy-duty combustion turbine INASA-CR-1961371 p 594 N94-36808 Advanced thermally stable, coal-derived, jet fuels 701F SPALART. P. R. development program. Experiment system and model IBTN-94-EIX94311331073) p 588 A94-61105 One-equation turbulence model for aerodynamic flows development ROTEA. MARIO A. IBTN-94-EIX94401367449I p 563 A94-61782 IAD-A278968I p 584 N94-36505 Aeroservoelastic tailoring with piezoelectric matenals: SPEAR. D. A. TSAI, L. C. Actuator optimization studies Advanced transonic fan design procedure based on a Mainstream ingress suppression in gas turbine disk |AD-A278640| p 581 N94-36384 Navier-Stokes method cavities IBTN-94-EIX94311330095I p 587 A94-61063 RUND, BERTON B. | BTN-94-EIX94311330101 I p 586 A94-61057 SPEER, T. M. Tanker system and technology requirements definition: TUCKER, C. J. Simulation of the secondary air system of aero A tanker technology road map p 575 N94-36344 Infrared search and track demonstrator programme engines RUSS. STEPHAN M. p 599 N94-36622 IBTN-94-EIX94311330097I p 587 A94-61061 Possibilities and pitfalls in aerospace applications of TUNCER. ISMAIL H. SPEZZAFERRO. R. titanium matrix composites p 585 N94-36650 Unsteady aerodynamic characteristics of a dual-element Technological challenges of High Altitude Long Endurance unmanned configurations airfoil I BTN-94-EIX94401358968 I p 565 A94 -61624 p573 N94-36323 SRIVATSAN. RAGHAVACHARI TURNER. A. B. Ingestion into the upstream wheelspace of an axial Takeoff performance monitoring system display SACHS. G. turbine stage options Improvement of endurance performance by periodic IBTN-94-EIX94311330099I p 587 A94-61059 IBTN-94-EIX94401358988I p 577 A94-61644 optimal control of variable camber p 581 N94-36329 STAPLETON, A. W. SALKELD. RICHARD W. Detailed flow measurements and predictions for a U Process enhancements of superalloy material three-stage transonic tan p 585 N94-37324 IBTN-94-EIX94311330096I p 587 A94-61062 UCER, A. S. SAMPSON. WILLIAM T. STARK, MIKE Working group activities of AGARD propulsion and Analysis of vertiport studies funded by the Airport Impact of Ada in the Flight Dynamics Division: energetics panel Improvement Program (AIP) Excitement and frustration p 597 N94-36501 IBTN-94-EIX94311331062I p 589 A94-61116 | SCT-93RR-21 I p 583 N94-37424 STORMS, BRUCE L. ULLAURI. JULIO C. SANKAR. LAKSHMI N. Lift enhancement of an airfoil using a Gurney flap and Mixed H2/H-mfinity optimization with multiple H infinity Unsteady aerodynamic characteristics of a dual-element vortex generators constraints airfoil IBTN-94-EIX944013589701 p 565 A94-61626 IAD-A280572I p 581 N94-36733 IBTN-94-EIX94401358968I p 565 A94-61624 STRAKA, WILLIAM A. UMEMURA, S. SARATHV, K. P. Leading-edge vortex breakdown for wing planforms with New high-efficiency heavy-duty combustion turbine Advanced transonic fan design procedure based on a the same slenderness ratio 701F Navier-Stokes method IBTN-94-EIX94401358991I p 566 A94-61647 IBTN-94-EIX94311331073I p 588 A94-61105 [BTN-94-EIX94311330095I p 587 A94-61063 STRICKLAND. J. H. SAWYER. BRIAN M. Prediction method for unsteady axisymmetric flow over Analysis of vertiport studies funded by the Airport parachutes Improvement Program (AIP) |BTN-94-EIX94401358984| p 566 A94-61640 |SCT-93RR-21| p583 N94-37424 SUZUKI, SHINJI VANAKEN, JOHANNES M. MulUobjective trajectory optimization by goal SCAVUZZO. R. J. Alleviation of whirl-flutter on a joined-wing tilt-rotor programming with fuzzy decisions Influence of aerodynamic forces in ice shedding aircraft configuration using active controls IBTN-94-EIX94381311168I p 597 A94-61255 |BTN-94-EIX94401358967| p 564 A94-61623 INASA-CR-1961031 p 581 N94-36436 SCHIEHLEN, J. VENKAYYA, V. B. Two-axis camera platform for machine vision High Altitude Long Endurance aircraft design studies p 597 N94-36628 p 572 N94-36322 SCHMISSEUR, J. D. TABOREK, J. VOAS, JEFFREY M. Fluctuating wall pressures near separation in highly Selection criteria tor plain and segmented finned tubes An empirical comparison of a dynamic software swept turbulent interactions for heat recovery systems testability metric to static cyclomatic complexity IBTN-94-EIX94421374958I p 563 A94-61856 IBTN-94-EIX94311331076I p 588 A94-6tt02 p 597 N94-36498

B-6 PERSONAL AUTHOR INDEX ZHANG, XUELIANG

VUKELICH. SHARON WU, SHU-FAN Process enhancements of superatloy material Optimum (light trajectory guidance based on total energy p 585 N94-37324 control of aircraft |BTN-94-EIX94381311t67| p 579 A94-61254 WUEBBLES. DONALD J. w Project report: Aircraft IDE94-011759I p 596 N94.37155 WAGGOTT, J. Mainstream ingress suppression in gas turbine disk cavities I BTN-94-EIX94311330101 I p 586 A94-61057 YANG. CIANN-DONG WALIGORA. SHARON Experimental design of H(sub infinity) weighting Impact ol Ada in the Flight Dynamics Division: functions for flight control systems Excitement and frustration p 597 N94-36501 IBTN-94-EIX94401358163I p 580 A94-61669 WANG. K. D. YANG. GUOCAI Study of rotor cavities and heat transfer in a cooling Research on the engineering application of the anti-swirl process in a gas turbine measures in engine/inlet compatibility IBTN.94-EIX9431I330100I p 587 A94-61058 IBTN-94-EIX94381353571 | p 577 A94-61459 WANG, WEN-JUNE YANG, HENRY T. Y. New output feedback design in variable structure Unstructured mesh quality assessment and upwind Euler systems solution algorithm validation IBTN-94.EIX94381311173I p 597 A94-61260 IBTN-94-EIX9440135B985I p 592 A94-61641 WANG. YUH-YING YOSHIZAWA. TAKESHI Numerical investigations on two-dimensional Multiobjectrve trajectory optimization by goal canard-wing aerodynamic interference programming with fuzzy decisions IBTN-94-EIX94401358989I p 566 A94-61645 IBTN-94-EIX94381311168I p 597 A94-61255 WAY. S. YOUNG. HARRY J. Comments on the development of the early Preload release mechanism Westinghouse turbojets. 1941-1946 I NASA-CASE-MSC-22327-11 p 594 N94-36839 IBTN-94-EIX94311331063I p 577 A94-61115 YOUNG. T. H. WEILAND. C. Stability of skew plates subjected to aerodynamic and Computation of three-dimensional hypersonic flows in in-plane forces chemical nonequilibrium IBTN-94-EIX94321331202I p 592 A94-61615 |BTN-94-EIX94401358982| p 566 A94-61638 WEINSTEIN, LEONARD M. Aerodynamic investigation with focusing Schlieren in a cryogenic wind tunnel ZACHARIAS, R. M. IBTN-94-EIX94421374975I p 593 A94-61873 Advanced transonic fan design procedure based on a WEISSHAAR, TERRENCE A. Navier-Stokes method Aeroservoelastic tailoring with piezoelectric materials: IBTN-94-EIX94311330095I p 587 A94-61063 Actuator optimization studies ZANGENEH, M. IAD-A278640I p 581 N94-363B4 Inviscid-viscous interaction method tor WELL. KLAUS H. three-dimensional inverse design of centrifugal impellers Range optimal trajectories lor an aircraft flying in the |BTN-94-EIX94311330094| p 590 A94-61125 vertical plane ZHANG, XUELIANG |BTN-94-EIX9438131118t| p 571 A94-61268 Experimental investigation on selecting the ramp and WENG, P. f. lip parameters of a two-dimensional external compression Swirl control in an S-duct at high angle of attack inlet |BTN-94-EIX94421374970| p 563 A94-61868 IBTN-94-EIX94381353570I p 577 A94-61460 WHITMORE. STEPHEN A. Measurement uncertainty and feasibility study of a flush airdata system for a hypersonic flight experiment | NASA-TM-46271 p 569 N94-37378 WILLIAMS. FRED W. Buckling and vibration analysis of laminated panels using VICONOPT |BTN-94-EIX94401372105| p 592 A94-61805 WILLIAMS. RONALD H. Process enhancements of superalloy material p585 N94-37324 WILSON. A. G. Stall inception and development in an axial flow aeroengine IBTN-94-EIX94311330088I p 591 A94-61131 WILSON, D. G. Models for predicting the performance of Brayton-cycle engines |BTN-94-EIX94311331072| p 589 A94-61106 WILSON, F. W. An automated method lor Low Level Windshear Alert System (LLWAS) data quality analysis (AD-A280313I p 596 N94-37126 WILSON, TIMOTHY M. Applications of Titanium Matrix Composite to large airframe structure p 585 N94-36651 WINICK, ROBERT M. Analysis ol vertiport studies funded by the Airport Improvement Program (AIP) ISCT-93RR-21 | p583 N94-37424 WITTIG, S. Influence of high rotational speeds on heat transfer and oil film thickness in aero-engine bearing chambers |BTN-94-EIX94311331074| p 588 A94-61104 WONG, G. S. Active control ol wing rock using tangential leading-edge blowing IBTN-94-EIX94401358987I p 571 A94-61643 WOOD, N. J. Active control of wing rock using tangential leading-edge blowing |BTN-94-EIX94401358987| p 571 A94-61643 WOODARD, PAUL R. Unstructured mesh quality assessment and upwind Euler solution algorithm validation IBTN-94-EIX94401358985I p 592 A94-61641

B-7 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 309) October 1994

Air Univ., Maxwell AFB, Al_ Draper (Charles Stark) Lab., Inc., Cambridge, MA. Aircraft battle damage repair for the 1990's and Advanced information processing system: The Army beyond Fault-Tolerant Architecture detailed design overview Typical Corporate Source |AD-A278635| P 576 N94-36465 |NASA-CR-194924| p 598 N94-36962 Alenia Aeronautica, Turin (Italy). Index Listing Technological challenges of High Altitude Long Endurance unmanned configurations p573 N94-36323 Eloret Corp., Palo Alto, CA. Allied-Signal Aerospace Co, Kansas City, MO. Experimental investigation of nozzle/plume | CORPORATE SOURCE; Replacement of silicone polymer A with silicons polymer aerodynamics at hypersonic speeds B and the subsequent characterization of the new cellular INASA-CR-1958291 p 568 N94-36687 silicone materials EMA, Mansfield, TX. |DE94-010105| p584 N94-36474 Rotorwash analysis handbook. Volume 1: Development Adaptive Research Corp* Huntsvllla, Al_ Aluminum Co. of America, Alcoa Center, PA. and analysis — Structured finite volume modeling of US Navy aircraft New developments in aluminum for aircraft and |SCT-93RR-17-VOL-1| p 567 N94-36466 engine test cells. Task 1: Turboshatt engine, volume 1 automobiles P 584 N94-36413 Rotorwash analysis handbook. Volume 2: Appendixes [AD-A2681761 p 135 N94-17432 Argonne National Lab., IL. ISCT-93RR-17-VOL-2I p 567 N94-36467 Weaf-resisting oxide films for 900 C Eurocopter France, Marignane (France). 1 IOE94-010093I p584 N94-36306 REPORT] The convertible (helicopter/airplane) EUROFAR: Army Aviation Systems Command, Hampton, VA. I- TITLE NUMBER General considerations on the technical progress and on Navier-Stokes and potential theory solutions for future advances p 574 N94-36331 ahelicoptec fuselage and comparison with experiment INASA-TM-4566] p 569 N94-36966

Listings in this index are arranged alphabetically B Federal Aviation Administration, Washington, DC. by corporate source. The title of the document is Accomplishments under the Airport Improvement used to provide a brief description of the subject Boeing Commercial Airplane Co., Seattle, WA. Program matter. The page number and the accession World jet airplane inventory at year-end 1993 IAD-A280661I p 583 N94-36763 IPB94-1649931 p 569 N94-36530 Flat Aviazione 8-p.A., Turin (Italy). number are included in each entry to assist Boston Univ., MA. the user in locating the abstract in the abstract Turbine disks: Liling against defects and materials An error-resistant linguistic protocol for air traffic development p 595 N94-37329 section. If applicable, a report number is also control Forge Soclete National* d'Etude et de Construction de included as an aid in identifying the document. INASA-CR-196098] p 570 N94-37013 Moteurs d'Aviation, Genrmvilliers (France). British Aerospace Defence Ltd, Preston (England). Maintaining constant standards during the forging Sensor data fusion tor air to air situation awareness process p 586 N94-37326 beyond visual range p 598 N94-36633 Frontier Technology, Inc., Beavercreek, OH. British Columbia Univ., Vancouver. Future tanker considerations and requirements Alternate melting and refining routes p 575 N94-36342 p585 N94-37323 British Petroleum Co. Ltd., Sunbury-on-Thames (England). Manufacture and properties of Sigma fibre reinforced Advisory Group for Aerospace Research and titanium p 585 N94-36655 GEC-Marconi Avionics Ltd., BasUon, Essex (England). Development, Neullly-Sur-Selne (France). Infrared search and track demonstrator programme Recent Advances in Long Range and Long Endurance p 599 N94-36622 Operation of Aircraft General Electric Co., Cincinnati, OH. IAGARD-CP-5471 P572 N94-36321 Substantiating powder metal life methodologies for Characterisation ol Fibre Reinforced Titanium Matrix CAE Electronics Ltd, Saint Laurent (Quebec). engines p 595 N94-37330 Composites Training and operations support system (TOPS) Fiber optic (flight quality) sensors for advanced aircraft IAD-A277S206I p 585 N94-36649 p599 N94-37344 propulsion Impact of Materials Defects on Engine Structures California Polytechnic State Univ., San Luis Obtspo, (NASA-CR-1911951 p 577 N94-37401 Integrity CA. IAGARD-R-790] p 595 N94-37321 Numerical investigation of multi-element airfoils Aerotet Delft Corp., Anna, CA. INASA-CR-194592] p 567 N94-36394 Earth Observing System/Advanced Microwave Computational Mechanics Co, Knoxvllte, TN. Sounding Unit-A (EOS/AMSU-A) software management An arbitrary grid CFO algorithm for configuration Imphy S.A, Imphy (France). plan aerodynamics analysis. Volume 1: Theory and The control of cleanness in powder metallurgy materials |NASA-CR-189362| p 596 N94-36919 validations for turbine disks p 586 N94-37325 Aerospace Engineering Test Establishment, CoM Lake INASA-CR-195918] p 598 N94-36914 Industrieanlagen-Betriebsgesellsehaft m.b.H, (Alberta). An arbitrary grid CFD algorithm for configuration Ottobninn (Germany). Flight test certification of a 480 gallon composite fuel aerodynamics analysis. Volume 2: FEMNAS user guide The STRATO 2C propulsion system: A low cost tank on CF-18 p 574 N94-36340 INASA-CR-196135) p 598 N94-36922 approach tor a High Altitude Long Endurance aircraft CC-130H(T) tactical aerial refuelling tanker development p 578 N94-36335 flight test programme p 575 N94-36347 Aerospatiale, Toulouse (France). Future supersonic commercial transport aircraft: A Dassault Aviation, Saint-Cloud (France). technological challenge for long haul traffic Laminar flow studies at Dassault Aviation: Calculations Jet Propulsion Lab, California Inst. of Tech, p573 N94-36324 and flight tests p 593 N94-36328 Pasadena, CA. Calculations used to optimize the installation of civil In-flight refueling: Dassault Aviation research on the Applying formal methods and object-oriented analysis aircraft engines p 574 N94-36332 Rafale aircraft p574 N94-36341 to existing flight software p 597 N94-36495 Air Force Inst of TecrL, Wright-Patterson AFB, OH. Defence Research Agency, Famborough, Hampshire Joint Publications Research Service, Arlington, VA. An aerodynamic and static-stability analysis of the (England). JPRS report: Central Eurasia. Aviation and Hypersonic Applied Research Technology (HART) Defects and their effects on me integrity of nickel based cosmonautics. No. 5. May 1993 missile aeroengine discs P 586 N94-37328 [JPRS-UAC-94-004] p583 N94-37000 IAD-A280631) p 568 N94-36729 Deutsche Aerospace A.G, Munich (Germany). Mixed H2/H-infinity optimization with multiple H infinity Optimisation of composite aircraft structures by direct constraints manufacturing approaches p 574 N94-36327 IAD-A280572I p 581 N94-36733 Domier-Werke Om.b.H, Friedrichshaten (Germany). A mean value analysis heuristic for analysis of aircraft Landing of an unmanned helicopter on a moving Lawrence Uverrnore National Lab, Uvermore, CA. sortie generation platform. High accuracy navigation and tracking Project report: Aircraft IAD-A278578I p 598 N94-36970 p576 N94-36618 [DE94-011759I p 596 N94-37155

C-1 Maryland Univ. CORPORA T£ SOURCE

M Design and evaluation of a Stochastic Optimal Analysis of vertiport studies funded by the Airport Feed-forward and Feedback Technology (SOFFT) flight Improvement Program (AIP) Maryland Univ., College Park. MO. control architecture |SCT-93RR-21| p 583 N94-37424 A fundamental study of hypersonic unstarts |NASA-TP-34t9| p582 N94-370I4 IAD-A280506I p 595 N94-37128 Predicting the effects of unmodeled dynamics on an Massachusetts Inst. of Tech., Cambridge. aircraft flight control system design using eigenspace An automated method for Low Level Windshear Alert assignment | NASA-TM-45481 p 582 N94-37059 Technische Univ., Munich (Germany). System (LLWAS) data quality analysis Improvement of endurance performance by periodic |AD-A280313| p 596 N94-37126 National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. optimal control of variable camber p 581 N94-36329 MCAT InsL, San Jose, CA. Textron Specialty Materials, Lowell, MA. Turbulence modeling of free shear layers for high Mixing and noise benefit versus thrust penalty in supersonic jets using impingement tones SCS-6 (tm) fiber reinforced titanium performance aircraft p 585 N94-36652 I NASA-CR-1961371 p 594 N94-36808 | NASA-TM-106583 | p 568 N94-36686 A method for flow simulation about complex geometries Thomson-TRT Defense, Guyancourt (France). McDonnell-Douglas Aerospace, Long Beach, CA. using both structured and unstructured grids Laser designation pods optimized concept for day/night Tanker system and technology requirements definition: operations p 594 N94-36620 A tanker technology road map p 575 N94-36344 | NASA-TM-1066331 p 569 N94-37283 McDonnell-Douglas Aerospace, Saint Louis, MO. Prediction of film cooling on gas turbine airfoils ICAAS piloted simulation results p 593 N94-36617 |NASA-TM-106653| p 579 N94-37448 Dynamics of a split torque helicopter transmission u Aeroservoelastic stabilization considerations for pointing and tracking systems p 594 N94-36627 |NASA-TM-106410| p 596 N94-37457 Universltaet der Bundeswehr Muenchen, Neublberg Naval Air Warfare Center, Patuxent River, MD. McDonnell-Douglas Corp, Saint Louis, MO. (Germany). Aerial refueling interoperability from a receiver flying Applications of Titanium Matrix Composite to large Two-axis camera platform for machine vision airtrame structure p 585 N94-36651 qualities perspective p 575 N94-36343 p597 N94-36628 Michigan State Univ., East Lansing, Ml. Naval Air Warfare Center, Warminster, PA. Utah State Univ., Logan, UT. The case for surface effect research, platform Unsteady How field of large-amplitude pitching airfoils Literature review and preliminary studies of fretting and |AD-A280444| p 569 N94-37219 applications and technology development opportunities fretting fatigue including special applications to aircraft p 573 N94-36325 Motoren- und Turtoinen-Unlon Muenchen G.m.b.H., joints Munich (Germany). Propulsion system selection for a High Altitude Long IAD-A280310] p 594 N94-37125 Predicting defect behaviour p 596 N94-37331 Endurance aircraft p 578 N94-36333 Utah Univ., Salt Lake City, UT. Naval Postgraduate School, Monterey, CA. History and prognosis of material discontinuity effects Planning German Army helicopter maintenance and on engine components structural integrity N mission assignment p595 N94-37322 IAD-A280483I P564 N94-37352 National Aeronautics and Space Administration. Ames Naval Surface Warfare Center, Bethesda. MD. Research Center, Moffett Field, CA. Tipjet 80-inch model rotor hover test: Test no. 1198 Navier-Stokes computations for oscillating control IAD-A2796BO] p 567 N94-36261 surfaces Virginia Unrv, Chariottesville, VA. (BTN-94-EIX94401358983I p 566 A94-61639 Analysis of high speed flow, thermal and structural The reduction of takeoff ground roll by the application interactions of a nose gear jump strut | NASA-CR-1 9601 7 1 p593 N94-36420 |NASA-TM-108822| p 576 N94-36380 Office National d'Etudes et de Recherche* TRENDS: A flight test relational database user's guide Aerospatiale*. Paris (France). and reference manual The future of large capacity/long range multipurpose w INASA-TM-1088061 p 564 N94-37332 air cargo fleets p 573 N94-36326 National Aeronautics and Space Administration. Old Dominion Univ., Norfolk. VA. Washington Univ., Seattle, WA. Goddard Space Flight Center, Greenbelt, MD. Large angle magnetic suspension test fixture Multirate flutter suppression system design for the Low-dimensional description of the dynamics in INASA-CR-1961381 p 583 N94-37450 Benchmark Active Controls Technology Wing separated flow past thick airfoils INASA-CR-1961121 P581 N94-36965 |BTN-94-EIX9442t374967| p 563 A94-61665 Westland Helicopters Ltd., Yeovll (England). Impact of Ada in the Flight Dynamics Division: EH101: A new helicopter capable of long range missions p 574 N94-36330 Excitement and frustration p 597 N94-36501 Pennsylvania State Univ., University Park, PA. Wichita State Univ., KS. National Aeronautics and Space Administration. Hugh A model-based approach for detection of runways and Three-dimensional force data acquisition and boundary L, Dryden Flight Research Center, Edwards, CA. other objects in image sequences acquired using an corrections for the Walter H. Beech Memorial 7x10 foot Controlling torebody asymmetries in flight: Experience on-board camera low speed wind tunnel with boundary layer transition strips |NASA-CR-196424| p 594 N94-36812 IAR93-2I p582 N94-36437 |NASA-TM-4595| p 568 N94-36944 Purdue Univ., West Lafayette, IN. Wright Lab, Wright-Patterson AFB, OH. Measurement uncertainty and feasibility study of a flush Aeroservoelastic tailoring with piezoelectric materials: High Altitude Long Endurance aircraft design studies airdata system tor a hypersonic flight experiment Actuator optimization studies p 572 N94-36322 INASA-TM-4627) p 569 N94-37378 | AD-A278640 ] p 581 N94-36384 National Aeronautics and Space Administration. Hugh Possibilities and pitfalls in aerospace applications of L. Dryden Flight Research Facility, Edwards, CA. titanium matrix composites p 585 N94-36650 Correlation of analytical and experimental hot structure Process enhancements of superalloy material vibration results pS85 N94-37324 | NASA-TM-1042691 p 576 N94-36644 Reliable Software Technology Corp., Reston, VA. Preliminary analysis for a Mach 8 crossflow transition An empirical comparison of a dynamic software experiment on the Pegasus (R) space booster testability metric to static cyclomatic complexity |NASA.TM-104272| p 564 N94-36648 p 597 N94-36498 National Aeronautics and Space Administration. Rolis-ftoyce Ltd, Bristol (England). Lyndon B. Johnson Space Center, Houston, TX. Propulsion system technologies for long range and long Preload release mechanism endurance aircraft p 578 N94-36334 INASA-CASE.MSC-22327.il p 594 N94-36839 Royal Netherlands Air Force, The Hague. National Aeronautics and Space Administration. The KDC-10 programme of the Royal Netherlands Air Langley Research Center, Hampton, VA. Force p575 N94-36346 Preliminary piloted simulation studies of the HL-20 lifting body IBTN-94-EIX94401358972) p 583 A94-61628 Invisod parametric analysis of three-dimenstonai inlet performance Sandia National Labs, Albuquerque, NM. |BTN-94-EIX9440135B980| p 578 A94-61636 Advanced thermally stable, coal-derived, jet fuels Takeoff performance monitoring system display development program. Experiment system and model options development IBTN-94-EIX94401358988I p 577 A94-61644 |AD-A278968| p 584 N94-36505 Forward sweep, low noise rotor blade Sterling Software, Inc., Moffett Field, CA. INASA-CASE-LAR-14569-11 p 576 N94-36767 Alleviation of whirl-flutter on a joimd-wing tilt-rotor Gain weighted eigenspace assignment aircraft configuration using active controls |NASA.TM-109130| p 581 N94-36820 [NASA-CR-196103) p581 N94-36436 Automatic procedures for computing complete Stonehtn CoO, North Easton, MA. configuration geometry from individual component An error-resistant linguistic protocol for air traffic descriptions control INASA-TM-46071 p 568 N94-36942 | NASA-CR-196098] p 570 N94-37013 Automatic computation of Euler.marching and subsonic Systems Control Technology, Inc., Arlington, VA. grids for wing-fuselage configurations Rotorwash analysis handbook. Volume 1: Development | NASA-TM-45731 p 568 N94-36950 and analysis Navier-Stokes and potential theory solutions for ISCT-93RR-17-VOL-1) p 567 N94-36466 aheticopter fuselage and comparison with experiment Rotorwash analysis handbook. Volume 2: Appendixes [NASA.TM-4566] p 569 N94-36966 ISCT-93RR-17-VOL-2I p 567 N94-36467

C-2 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 309) October 1994

Typical Foreign Technology Swirl control in an S-duct at high angle of attack ITALY |BTN-94-EIX94421374970| p 563 A94-61868 Performance and economic enhancement of Index Listing cogeneration gas turbines through compressor inlet air cooling IBTN-94-EIX94311331069I P 589 A94-61109 Technological challenges of High Altitude Long [COUNTRY OF INTELLECTUAL ORIGIN) FRANCE Endurance unmanned configurations Multidomain method for several bodies in relative p 573 N94-36323 motion Turbine disks: Lifing against defects and materials IBTN-94-EIX944013674521 p 563 A94-61785 development p 595 N94-37329 Recent Advances in Long Range and Long Endurance CHINA Operation of Aircraft |— The present situation and future development of Chinese IAGARD-CP-547I p572 N94-36321 aviation reliability and maintainability engineering Future supersonic commercial transport aircraft: A 153 A94-10101 technological challenge for long haul traffic p573 N94-36324 JAPAN The future of large capacity/long range multipurpose New high-efficiency heavy-duty combustion turbine air cargo fleets p 573 N94-36326 701F Laminar flow studies at Dassault Aviation: Calculations | BTN-94-EIX94311331073] p 588 A94-61105 and flight tests p 593 N94-36328 Multiobjective trajectory optimization by goal The convertible (helicopter/airplane) EUROFAR. programming with fuzzy decisions Listings in this index are arranged alphabetically General considerations on the technical progress and on |BTN-94-EIX94381311168| p 597 A94-61255 by country of intellectual origin. The title of the future advances p 574 N94-36331 Some basic considerations on angles describing airplane document Is used to provide a brief description Calculations used to optimize the installation of civil flight maneuvers aircraft engines p 574 N94-36332 of the subject matter. The page number and IBTN-94-EIX94381311179) p 570 A94-61266 In-flight refueling: Dassault Aviation research on the Hunting phenomena of the balloon motions observed accession number are included in each entry Rafale aircraft P 574 N94-36341 over Antarctica to assist the user in locating the abstract in Laser designation pods optimized concept for day/night | BTN-94-EIX944013589691 p 571 A94-61625 the abstract section. If applicable, a report num- operations P 594 N94-36620 ber is also included as an aid in Identifying Characterisation of Fibre Reinforced Titanium Matrix the document. Composites K IAD-A2775206I p 585 N94-36649 Impact of Materials Defects on Engine Structures KOREA, REPUBLIC OF Integrity Numerical simulation of vortex-wedge interaction IAGARD-R-790I p595 N94-37321 IBTN-94-EIX94421374955) p 592 A94-61853 The control of cleanness in powder metallurgy materials for turbine disks p 586 N94-37325 Maintaining constant standards dunng the forging N process p 586 N94-37326 NETHERLANDS The KDC-10 programme of the Royal Netherlands Air Force p 575 N94-36346

GERMANY Simulation of the secondary air system of aero AUSTRALIA engines Fault diagnosis in gas turbines using a model-based I8TN-94-EIX94311330097) p 587 A94-61061 RUSSIA technique Influence of high rotational speeds on heat transfer and Computation of transonic flows around a IBTN-94-EIX94311331071) p 589 A94-61107 oil film thickness in aero-engine bearing chambers wing-plus-fuselage configuration taking viscous effects and [BTN-94-EIX943t 13310741 p 588 A94-61104 a thin separated region into account Evaluation of parameter estimation methods for unstable |BTN-94-EIX94401367450| p 563 A94-61783 aircraft JPRS report: Central Eurasia. Aviation and IBTN-94-EIX94401358965I p 580 A94-61621 cosmonautics. No. 5, May 1993 CANADA Computation of three-dimensional hypersonic flows in IJPRS-UAC-94-0041 p 583 N94-37000 PT6 engine: 30 years ot gas turbine technology chemical nonequilibrium evolution [BTN-94-EIX944013589821 p 566 A94-61638 IBTN-94-EIX94311331064I p 577 A94-61114 Whirl-flutter suppression in advanced turboprops and Developments in centrifugal compressor surge control: preplans by active control techniques SWITZERLAND A technology assessment IBTN-94-EIX94401358994) p 578 A94-61650 Operational stability of a centrifugal compressor and its |BTN-94-EIX94311330090| p 590 A94-61129 Optimisation of composite aircraft structures by direct dependence on the characteristics of the Flight test certification of a 480 gallon composite fuel manufacturing approaches p 574 N94-36327 subcomponents tank on CF-18 p 574 N94-36340 Improvement of endurance performance by periodic IBTN-94-EIX943113300911 p 590 A94-61128 CC-130H(T) tactical aerial refuelling tanker development optimal control of variable camber p 581 N94-36329 flight test programme p 575 N94-36347 The STRATO 2C propulsion system: A low cost Alternate melting and refining routes approach for a High Altitude Long Endurance aircraft P585 N94-37323 p57B N94-36335 Training and operations support system (TOPS) Landing of an unmanned helicopter on a moving TAIWAN, PROVINCE OF CHINA p 599 N94-37344 platform. High accuracy navigation and tracking New output feedback design in variable structure systems CHINA p576 N94-36618 |BTN-94-EIX9438131t173| p 597 A94-61260 Optimum flight trajectory guidance based on total energy Two-axis camera platform for machine vision Stability of skew plates subjected to aerodynamic and control of aircraft p597 N94-36628 in-plane forces IBTN-94-EIX94381311167) p 579 A94-61254 Predicting defect behaviour p596 N94-37331 (BTN-94-EIX94321331202I p 592 A94-61615 Research on the engineering application of the anti-swirl Numerical investigations on two-dimensional measures in engine/inlet compatibility canard-wing aerodynamic interference (BTN-94-EIX94381353571I p 577 A94-61459 IBTN-94-EIX94401358989] p 566 A94-61645 Experimental investigation on selecting the ramp and Experimental design of H(sub infinity) weighting lip parameters of a two-dimensional external compression INDIA functions for flight control systems inlet Capture region for true proportional navigation guidance IBTN-94-EIX94401358163I p 580 A94-61669 [BTN-94-EIX94381353570I p 577 A94-61460 with nonzero miss-distance TURKEY Coating the boron particles to increase the combustion IBTN-94-EIX94401358176) p 570 A94-61682 Working group activities of AGARD propulsion and efficiency of boron fuel On the generalization of true proportional navigation energetics panel IBTN-94-EIX943813S3577I p 584 A94-61473 IBTN-94-EIX94401377808I p 570 A94-61769 IBTN-94-EIX94311331062I p 589 A94-61116

D-1 UKRAINE FOREIGN TECHNOLOGY INDEX u UKRAINE Mashproekt scientific and production association: A designer of gas turbines for marine and industrial applications |BTN-94-EIX94311331079| p 588 A94-61099 UNITED KINGDOM Window functions for the calculation of the time domain averages of the vibration of the individual planet gears and sun gear in an epicyclic gearbox |BTN-94-EIX94311331047| p 586 A94-61050 Ingestion into the upstream wheelspace ol an axial turbine stage IBTN-94.EIX94311330099I p 587 A94-61059 Transfer ot heat by self-induced flow in a rotating tube IBTN-94-EIX94311330098I p 587 A94-61060 Detailed flow measurements and predictions for a three-stage transonic fan IBTN-94-EIX94311330096I p 587 A94-61062 Inviscid-viscous interaction method for three-dimensional inverse design of centrifugal impellers |BTN-94-EIX94311330094| p 590 A94-61125 Stall inception and development in an axial flow aeroengine |BTN-94-EIX94311330088| p 591 A94-61131 Review of nonsteady flow models for compressor stability |BTN-94-EIX94311330087| p 591 A94-61132 Unstable behavior of low and high-speed compressors IBTN-94.EIX94311330086I p 591 A94-61133 Spanwise transport in axial-How turbines. Par! 2: Throughflow calculations including spanwise transport IBTN-94-EIX94311330085I p 591 A94-61134 Spanwise transport in axial-flow turbines. Part 1: The multistage environment |BTN-94-EIX94311330084| p 592 A94-61135 Buckling and vibration analysis of laminated panels using VICONOPT |BTN-94-EIX94401372105| p 592 A94-61805 Sound radiation and caustic formation from a point source in a wall shear layer IBTN-94-EIX94421374956! p 599 A94-61854 EH 101: A new helicopter capable of long range missions p 574 N94-36330 Propulsion system technologies for long range and long endurance aircraft p 578 N94-36334 Infrared search and track demonstrator programme p 599 N94-36622 Sensor data fusion for air to air situation awareness beyond visual range p 598 N94-36633 Manufacture and properties of Sigma fibre reinforced titanium p 585 N94-36655 Defects and their effects on the integrity of nickel based aeroengine discs p 586 N94-37328

YUGOSLAVIA Analytic solution of the Riccati equation for the homing missile linear-quadratic control problem |BTN-94-EIX94401358173| p 583 A94-61679

D-2 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 309) October 1994

Typical Contract Number SBIR-02.07-5494 p 598 N94-36914 p598 N94-36922 Index Listing W-31-109-ENG-38 p 584 N94-36306 W-7405-ENG-48 .... P596 N94-37155

AF PRO). 2404 p 44 N94-17461

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 PROJ. 2302 p 585 N94-36650 AF-AFOSR-0386-91 p 581 N94-36384 AF-AFOSR-0417-89 p 569 N94-37219 DA PROJ. 111-62211-A-47-A p 596 N94-37457 OA PROJ. 3048 p 584 N94-36505 DE-AC04-76DP-00613 p 584 N94-36474 DE-AC04-94AL-85000 p 584 N94-36505 DTFA01-87-C-00014 p 567 N94-36466 P567 N94-36467 DTFA01-91-Z-02036 p 596 N94-37126 DTFA01-93-C-00030 p 583 N94-37424 F49620-92-J-0006 p 595 N94-37128 NAG1-1013 p 593 N94-36420 NAG1-1056 P583 N94-37450 NAG1-1371 p 594 N94-36812 NAG1-884 p597 N94-36498 NAG2-564 p 570 N94-37013 NAS1-18565 P598 N94-36962 NAS1-19672 P569 N94-36966 NAS2-12568 p 598 N94-36914 p 598 N94-36922 NAS3-25805 p 577 N94-37401 NAS3-27186 p 568 N94-366B6 NAS5-32314 p596 N94-36919 NCC1-156 p581 N94-36965 NCC2-417 p 581 N94-36436 NCC2-487 p 568 N94-36687 NCC2-663 p 594 N94-36808 NCC2-761 p 567 N94-36394 NSF CCR-92-09873 p 597 N94-36495 PROJ. RR22-M59 P 567 N94-36261 RTOP 023-10-01-01 P569 N94-36966 RTOP 422-00-00 p 596 N94-36919 RTOP 505-59-36-01 p 569 N94-36966 RTOP 505-59-38 p 576 N94-36380 p 564 N94-37332 RTOP 505-6J-10 P596 N94-37457 RTOP 505-62-50 P 577 N94-37401 RTOP 505-62-52 P 579 N94-37448 RTOP 505-63-50 p 576 N94-36644 RTOP 505-64-30-01 p 581 N94-36820 P582 N94-37014 RTOP 505-64-52-01 p 582 N94-37059 RTOP 505-64-52-53 P 598 N94-36962 RTOP 505-66-40 p 569 N94-3737B RTOP 505-68-71 p 568 N94-36944 RTOP 505-70-91 P 564 N94-36648 RTOP 509-10-11-01 P56B N94-36942 p 568 N94-36950 RTOP 537-02-22 P 568 N94-36686 RTOP 537-02-23 P 569 N94-37283

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 309) October 1994

BTN-94-EIX94311330088 p 591 A94-61131 BTN-94-EIX94401358991 P 566 A94-61647 Typical Report Number BTN-94-EIX94311330089 p 591 A94-61130 BTN-94-EIX94401358993 P 572 A94-61649 Index Listing BTN-94-EIX94311330090 p 590 A94-61129 BTN-94-EIX94401358994 p 578 A94-61650 BTN-94-EIX94311330091 p 590 A94-61128 BTN-94-EIX94401358996 p 578 A94-61652 BTN-94-EIX94311330092 p 590 A94-61127 BTN-94-EIX94401367449 p 563 A94-61782 BTN-94-EIX94311330093 p 590 A94-61126 BTN-94-EIX94401367450 P 563 A94-61783 NASA ON BTN-94-EIX94311330094 p 590 A94-61125 BTN-94-EIX94401367452 p 563 A94-61785 SPONSORED MICROFICHE BTN-94-EIX94311330095 p 587 A94-61063 BTN-94-EIX94401372105 P 592 A94-61805 BTN-94-EIX94311330096 p 587 A94-61062 L BTN-94-EIX94401372110 P 567 A94-61810 I I BTN-94-EIX94311330097 p 587 A94-61061 BTN-94-EIX94401377806 P 592 A94-61767 NASA-CR-167690 p 139 N94-12810 ' # BTN-94-EIX94311330098 p 587 A94-61060 BTN-94-EIX94401377808 P 570 A94-61769 BTN-94-EIX94311330099 p 587 A94-61059 BTN-94-EIX94421374955 P 592 A94-61853 BTN-94-EIX94311330100 p 587 A94-61058 REPORT PAGE I ACCESSION BTN-94-EIX94421374956 P 599 A94-61854 BTN-94-EIX94311330101 p 586 A94-61057 NUMBER NUMBER I NUMBER BTN-94-EIX94421374957 p 563 A94-61855 BTN-94-EIX94311330477 p 592 A94-61203 BTN-94-EIX94421374958 P 563 A94-618S6 BTN-94-EIX94311331047 p 586 A94-61050 BTN-94-EIX94421374964 p 593 A94-61862 BTN-94-EIX94311331062 p 589 A94-61116 Listings in this index are arranged alphanumeri- BTN-94-EIX94421374967 p 563 A94-61865 ' BTN-94-EIX94311331063 p 577 A94-61115 cally by report number. The page number BTN-94-EIX94421374969 p 593 A94-61867 BTN-94-EIX94311331064 p 577 A94-61114 indicates the page on which the citation is BTN-94-EIX94421374970 p 563 A94-61868 BTN-94-E1X94311331065 p 584 A94-61113 BTN-94-EIX94421374974 p 593 A94-61872 located. The accession number denotes the num- BTN-94-EIX94311331067 p 589 A94-61111 BTN-94-EIX94421374975 P 593 A94-61873 ber by which the citation is identified. An aster- BTN-94-EIX94311331069 p 589 A94-61109 BTN-94-EIX94421374979 p 564 A94-61877 isk (•) indicates that the item is a NASA report. BTN-94-EIX94311331070 p 589 A94-61108 BTN-94-EIX94311331071 p 589 A94-61107 A pound sign (ft) indicates that the item is avail- CORKNSWC/SSD-93/54 p 567 N94-36261 tt able on microfiche. BTN-94-EIX94311331072 p 589 A94-61106 BTN-94-EIX94311331073 p 588 A94-61105 CDRL-008 p 596 N94-36919 ' tt BTN-94-EIX94311331074 p 588 A94-61104 BTN-94-EIX94311331076 p 588 A94-61102 CMC-TR2.1-94-VOL-1 P 598 N94-36914 • # A-94042 p 564 N94-37332 ' # BTN-94-EIX94311331077 p 588 A94-61101 CMC-TR4.2-92-VOL-2 P 598 N94-36922 ' tt A-94082 p 576 N94-36380 ' tt BTN-94-EIX94311331078 p 588 A94-61100 BTN-94-EIX94311331079 p 588 A94-61099 CONF-9311208-1 p596 N94-37155 tt AD-A2775206 p 585 N94-36649 it BTN-94-EIX94311331080 p 588 A94-61098 BTN-94-EIX94321331202 p 592 A94-61615 AD-A278578 p 598 N94-36970 DE94-010093 P 584 N94-36306 BTN-94-EIX94381311167 p 579 A94-61254 AD-A278635 p 576 N94-36465 DE94-010105 p 584 N94-36474 tt BTN-94-EIX94381311168 p 597 A94-61255 AD-A278640 p 581 N94-36384 DE94-011759 p596 N94-37155 # BTN-94-EIX94381311172 p 579 A94-61259 AD-A278968 p 584 N94-36505 BTN-94-EIX94381311173 p 597 A94-61260 AD-A279680 p 567 N94-36261 # DOT/FAA/CT-93/2 P 594 N94-37125 BTN-94-EIX94381311174 p 579 A94-61261 AD-A280310 p594 N94-37125 BTN-94-EIX94381311179 p 570 A94-61266 AD-A280313 p 596 N94-37126 DOT/FAA/PP-94-2 P 583 N94-36763 tt BTN-94-EIX94381311180 p 570 A94-61267 AD-A280444 p 569 N94-37219 BTN-94-EIX94381311181 p 571 A94-61268 AD-A280483 p 564 N94-37352 DOT/FAA/RD-93-31-VOL-1 p567 N94-36466 tt BTN-94-EIX94381353570 p 577 A94-61460 AD-A280506 p 595 N94-37128 DOT/FAA/RD-93-31-VOL-2 p567 N94-36467 tt BTN-94-EIX94381353571 p 577 A94-614S9 AD-A280572 p 581 N94-36733 tt DOT/FAA/RD-93/37 p583 N94-37424 tt BTN-94-EIX94381353577 p 584 A94-61473 AD-A280631 p 568 N94-36729 tt BTN-94-EIX94401216108 p 569 A94-61787 AD-A280661 p 583 N94-36763 tt E-7881 P 596 N94-37457 • tt BTN-94-EIX94401216109 p 563 A94-61788 E-8844 p 568 N94-36686 ' # BTN-94-EIX94401358152 p 580 A94-61658 AERO-3 p 581 N94-36384 E-8955 p 569 N94-37283 • tt BTN-94-EIX94401358163 p 580 A94-61669 E-8965 P 579 N94-37448 • tt BTN-94-EIX94401358166 p 580 A94-61672 AFIT/DS/AA/94-3 p 568 N94-36729 It BTN-94-EIX94401358167 p 580 A94-61673 H-1943 P 576 N94-36644 * tt BTN-94-EIX94401358168 p 572 A94-61674 H-1954 p 564 N94-36648 • tt AFIT/GAE/ENY/94J-Q4 p 581 N94-36733 tt BTN-94-EIX94401358169 p 572 A94-61675 H-1992 P 568 N94-36944 • tt BTN-94-EIX94401358173 p 583 A94-61679 H-2010 P 569 N94-37378 • tt AFIT/GOR/ENS/94M-07 p 598 N94-36970 BTN-94-EIX9440135B176 p 570 A94-616B2 BTN-94-EIX9440135B960 p 571 A94-61616 AFOSR-94-0263TR p 581 N94-36384 ISBN-92-835-0711-8 P 595 N94-37321 tt BTN-94-EIX94401358961 p 579 A94-61617 AFOSR-94-0355TR p 569 N94-37219 ISBN-92-835-0726-6 P 572 N94-36321 tt BTN-94-EIX94401358962 p 579 A94-61618 AFOSH-94-0362TR p 595 N94-37128 ISBN-92-835-0735-5 P 585 N94-36649 # BTN-94-EIX94401358963 p 571 A94-61619 BTN-94-EIX94401358964 p 564 A94-61620 JPRS-UAC-94-004 p 583 N94-37000 tt AGARD-CP-547 ; p 572 N94-36321 tt BTN-94-EIX94401358965 p 580 A94-61621 BTN-94-EIX94401358966 p 571 A94-61622 KCP-613-5266 p 564 N94-36474 tt AGARD-R-790 p 595 N94-37321 tt BTN-94-EIX94401358967 p 564 A94-61623 AGARD-R-796 p 585 N94-36649 tt BTN-94-EIX94401358968 p 565 A94-61624 L-17273 p582 N94-37014 • tt BTN-94-EIX94401358969 p 571 A94-61625 L-17325 P 569 N94-36966 ' tl AIAA PAPER 94-1826 p 568 N94-36944 • tt BTN-94-EIX94401358970 p 565 A94-61626 AIAA PAPER 94-1930 p 569 N94-37378 ' # BTN-94-EIX94401358971 p 571 A94-61627 L-17333 P 582 N94-37059 • tt L-17364 p 568 N94-36950 • # AIAA PAPER 94-2955 p 568 N94-36686 • * BTN-94-EIX94401358972 p 583 A94-61628 ' L-17395 P 568 N94-36942 ' tt BTN-94-EIX94401358973 p 565 A94-61629 ANL/OTM/CR-5 p 584 N94-36306 BTN-94-EIX94401358974 p 565 A94-61630 MCAT-94-12 P 594 N94-36808 • tt BTN-94-EIX94401358975 p 565 A94-61631 ARL-TR-291 p 596 N94-37457 • tt BTN-94-EIX94401358976 p 571 A94-61632 NAS 1.15:104269 p 576 N94-36644 • tt BTN-94-EIX94401358979 p 599 A94-61635 NAS 1.15:104272 p 564 N94-36648 * # AR93-2 p582 N94-36437 # BTN-94-EIX94401358980 p 578 A94-61636 • NAS 1.15:106410 p 596 N94-37457 • tt BTN-94-EIX94401358981 p 565 A94-61637 NAS 1.15:106583 p 568 N94-36686 • tt ATC-207 p596 N94-37126 BTN-94-EIX94401358982 p 566 A94-61638 NAS 1.15:106633 p 569 N94-372B3 BTN-94-EIX94401358983 p 566 A94-61639 • NAS 1.15:106653 p 579 N94-37448 ATCOM-TR-94-A-013 p 569 N94-36966 • » BTN-94-EIX94401358984 p 566 A94-61640 NAS 1.15:108806 p 564 N94-37332 BTN-94-EIX94401358985 p 592 A94-61641 NAS 1.15:108822 p 576 N 94-36380 AU-ARI-93-4 p576 N94-36465 BTN-94-EIX94401358986 p 566 A94-61642 NAS 1.15:109130 p 581 N 94-368 20 BTN-94-EIX94401358987 p 571 A94-61643 BTN-94-E1X94311330084 p 592 A94-61135 NAS 1.15:4548 p 582 N94-37059 BTN-94-EIX94401358988 p 577 A94-61644 ' BTN-94-EIX94311330085 p 591 A94-61134 NAS 1.15:4566 p 569 N94-36966 BTN-94-EIX94311330086 p 591 A94-61133 BTN-94-EIX94401358989 p 566 A94-61645 NAS 1.15:4573 p 568 N94-36950 BTN-94-EIX94311330087 p 591 A94-61132 BTN-94-EIX94401358990 p 566 A94-61646 NAS 1.15:4595 p 568 N 94-36944

F-1 NAS 1.15:4607 RE POP T NUMBER INDEX

NAS 1.15:4607 p 568 N94-36942 ' # NAS 1.15:4627 p 569 N94-37378 * tt NAS 1.26:189362 p 596 N94-36919 ' It NAS 1.26:191195 p 577 N94-37401 ' » NAS 1.26:194592 p 567 N94-36394 • # NAS 1.26:194924 p 598 N94-36962 ' tt NAS 1.26:195829 p 568 N94-36687 ' # NAS 1.26:195918 p 598 N94-36914 • # NAS 1.26:196017 p 593 N94-36420 ' if NAS 1.26:196098 p 570 N94-37013 " tt NAS 1.26:196103 p 581 N94-36436 • H NAS 1.26:196112 p 581 N94-36965 ' # NAS 1.26:196135 p 598 N94-36922 * tt NAS 1.26:196137 p 594 N94-36808 • tt NAS 1.26:196138 p 583 N94-37450 ' tt NAS 1.26:196424 p 594 N94-36812 * # NAS 1.60:3419 p 582 N94-37014 • tt NAS 1.71:LAR-14569-1 p 576 N94-36767 • tt NAS 1.71 :MSC-22327-1 p 594 N94-36839 ' tt

NASA-CASE-LAR-14S69-1 p 576 N94-36767 • tt

NASA-CASE-MSC-22327-1 p 594 N94-36839 ' tt

NASA-CR-1B9362 p 596 N94-36919 " tt NASA-CR-191195 p577 N94-37401 * tt NASA-CR-194592 p 567 N94-36394 ' tt NASA-CR-194924 p 598 N94-36962 • tt NASA-CR-195829 p 568 N94-36687 ' tt NASA-CR-195918 p 598 N94-36914 ' tt NASA-CR-196017 p 593 N94-36420 ' # NASA-CR-196098 p 570 N94-37013 ' tt NASA-CR-196103 p 581 N94-36436 ' tt NASA-CR-196112 p581 N94-36965 ' # NASA-CR-196135 p 598 N94-36922 • tt NASA-CR-196137 p 594 N94-36808 ' tt NASA-CR-196138 p 583 N94-37450 ' t> NASA-CR-196424 p 594 N94-36812 ' tt

NASA-TM-104269 p 576 N94-36644 • tt NASA-TM-104272 p 564 N94-36648 ' tt NASA-TM-106410 p 596 N94-37457 • tt NASA-TM-106583 p 568 N94-36686 ' tt NASA-TM-106633 p 569 N94-37283 " tt NASA-TM-106653 p 579 N94-37448 * tt NASA-TM-108806 p 564 N94-37332 " tt NASA-TM-108822 p 576 N94-36380 • tt NASA-TM-109130 p 581 N94-36820 • tt NASA-TM-4548 p 582 N94-37059 ' tt NASA-TM-4566 p 569 N94-36966 " 0 NASA-TM-4573 p 568 N94-36950 * # NASA-TM-4595 p 568 N94-36944 ' 0 NASA-TM-4607 p 568 N94-36942 ' # NASA-TM-4627 p 569 N94-37378 ' tt

NASA-TP-3419 p 582 N94-37014 ' tt

PB94-164993 p 569 N94-36530

REPT-10339 p 596 N94-36919 ' tt REPT-9803-1 p 596 N94-36919 • tt

R94AEB175 p577 N94-37401 ' tt

SCT-93RR-17-VOL-1 p567 N94-36466 tt SCT-93RR-17-VOL-2 p 567 N94-36467 tt SCT-93RR-21 p583 N94-37424 tt

UCRL-JC-116530 p596 N94-37155 tt

US-PATENT-APPL-SN-230571 p 594 N94-36839 ' tt US-PATENT-APPL-SN-238044 p 576 N94-36767 ' tt

UVA/528308/MANE94/101 p 593 N94-36420 • tt

WL-TR-94-2003 p 584 N94-36505

F-2 ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 309) October 1994

Typical Accession Number N94-36261 # pS67 N94-37283 ' # P569 Index Listing N94-36306 p584 N94-37321 # pS95 N94-36321 tt pS72 N94-37322 # p595 N94-36322 tt p572 N94-37323 tt p585 N94-36323 # p573 N94-37324 tt p585 NNAS; A ON N94-36324 tt p573 N94-37325 tt pS86 ISPONISOREOI l MICROFICHE N94-36325 tt p573 N94-37326 tt pS86 N94-36326 » pS73 N94-37328 # p586 N94-36327 tt pS74 N94-37329 tt p595 A94-10717 • t p71 N94-36328 tt pS93 N94-37330 tt P595 N94-36329 » p581 N94-37331 tt p596 N94-36330 tt pS74 N94-37332 • « P564 ACCESSION I PAGE pS74 N94-37344 # pS99 NUMBER | NUMBER N94-36331 » N94-36332 # p574 N94-37352 p564 N94-36333 tt pS78 N94-37378 • tt p569 N94-36334 # p578 N94-37401 •# p577 Listings in this index are arranged alphanumerically N94-36335 # p578 N94-37424 tt PS83 N94-36340 tt P574 N94-37448 ' * p579 by accession number. The page number indicates the N94-36341 # p574 N94-37450 ' # p583 page on which the citation is located. The accession N94-36342 # p575 N94-37457 ' tt pS96 number denotes the number by which the citation is N94-36343 tt p 575 identified. An asterisk (•) indicates that the Item is a N94-36344 » p575 NASA report. A pound sign (#) indicates that the item N94-36346 # p575 is available on microfiche. N94-36347 # p575 N94-36380 * # pS76 N94-36384 p 581 N94-36394 • # pS67 N94-36413 ' tt p584 p586 A94-61623 P564 N94-36420 " # p593 p586 A94-61624 PS65 N94-36436 * # p 581 A94-61058 P587 A94-61625 P571 N94-36437 # p582 A94 -61059 P587 A94-61626 p565 N 94-36465 p576 A94-61060 pS87 p567 A94-61627 p571 N94-36466 tt A94-61061 p587 N94-36467 # P567 p587 p583 N94-36474 # pS84 A 94-61063 pS87 A94-61629 p565 N94-36495 " # p597 p 588 A94-61630 p565 N94-36498 * tt p597 A94-61099 p588 pS65 N94-36501 '# p597 A94-61100 p588 A94-61632 p571 N 94.36505 P584 A94-61101 p588 A94-61635 p599 N 94.36530 p569 A94-61102 p588 A94-61636 ' p578 N94-36617 # p593 A94-61104 P588 N94-36618 tt pS76 A94-61637 p565 A94-61105 p588 N94-36620 # p594 A94-61638 p566 p589 N94-36622 # p599 A94-61639 ' p589 p566 N94-36627 # pS94 A94-61640 p589 pS66 N94-36628 ft p597 A 94-61109 p589 p592 N94-36633 tt p598 A 94-61642 A94-61111 p589 p566 N94-36644 • tt pS76 A94-61113 P584 p571 N94-36648 • tt P564 p577 A94-61114 p577 N94-36649 # P585 A94-61115 p577 pS66 N94-36650 # p585 p566 p589 N94-366S1 # P58S A94-61647 P590 p566 N94-36652 # pSSS pS72 A94-61126 pS90 N94-366S5 # pses p578 A94-61127 p590 A94-61650 N94-36686 ' # pS68 A94-61652 p578 A94-61128 PS90 N94-36687 • tt p568 A94-61129 p590 A94-61658 p580 N94-36729 # pS68 A94-61669 A94-61130 P591 pSSO N94-36733 # p581 A94-61131 P591 A94-61672 pSSO N94-36763 # p583 A94-61673 A94-61132 p591 pSSO N94-36767 ' tt p576 A94-61674 A94-61133 pS91 p572 N94-36808 • # p594 A94-61675 A94-61134 P591 p572 N94-36812 ' # p594 p583 A94-61135 P592 A94-61679 N94-36820 ' ft pS81 A94-61203 p592 A94-61682 p570 N94-36839 • # pS94 A94-61767 A 94-61254 p579 p592 N94-36914 ' tt p598 A94-61769 p597 p570 N94-36919 '# p596 A94-61259 p579 A94-61782 p563 N94-36922 ' # p598 A94-617B3 A94-61260 p597 p563 N94-36942 ' tt pS68 p579 A94-61785 p563 N94-36944 ' # pS68 A94-61266 p570 A94-61787 p569 N94-369SO ' # P568 A94-61267 pS70 A94-61788 pS63 N94-36962 ' # p598 A94-61268 p571 A94-61805 p592 N94-36965 ' # p581 A94-61459 pS77 A94-61810 p567 N94-36966 * # p569 A 94-61460 p577 A94-61853 p592 N94-36970 p598 A94-61473 PS84 A94-61854 pS99 N94-37000 # p583 A94-61615 P592 A94-61855 pS63 N94-37013 ' » p570 A 94-61616 p571 A94-61856 p563 N94-37014 ' # p582 A 94-61617 p579 A94-61862 p593 N94-37059 ' tt p582 A94-61865 ' pS63 A94-61618 p579 N 94-37 125 pS94 A94-61867 p593 N 94-371 26 p596 A94-61619 p571 p563 A94-61620 P564 p593 N 94-37 128 p595 A94-61621 pseo A94-61873 p593 N94-371S5 tt p596 A94-61622 p571 pS64 N94-37219 pS69 G-1 AVAILABILITY OF CITED PUBLICATIONS

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4. Title and Subtitle 5. Report Date Aeronautical Engineering October 1994 A Continuing Bibliography (Supplement 309) 6. Performing Organization Code JTT 7. Author(s) 8. Performing Organization Report No.

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15. Supplementary Notes

16. Abstract This report lists 212 reports, articles and other documents recently announced in the NASA STI Database.

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

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