NASA SP-7037 (308) September 1994
AERONAUTICALENGINEERING
SI 001 SP7037(308 940922 S090569 A NASA CENTER FOR AERGSPACE INFORMATION ACCESSIONING 800 ELKRIDGE LANOING ROAD LINTHICUM HEIGHTS MD 210902934
A CONTINUING BIBLIOGRAPHYWITH INDEXES
(NASA-SP-7037(308)) AERONAUTICAL N95-11371 ENGINEERING: A CONTINUING BIBLIOGRAPHY WITH INDEXES (SUPPLEMENT 308) (NASA) 95 p Unclas
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AERONAUTICALENGINEERING
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 withIndexes(NASA SP-7037) lists 269 reports, joumal articles, and other documents recently announced in the NASA STI Database.
Accession numbers cited in this issue include: Scientificand TechnicalAerospaceReports(STAR) (N-10000 Sedes) N94-34467 m N94-36230 A94-13207 -- A94-61023 Open Literature(A-10000 Sedes)
The coverage includes documents on the engineering and theoretical aspects of design, construc- tion, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and 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 cate- gories 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 joumals.
Seven indexeHubject, 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 sched- ules are located at the back of this issue.
ill
TABLE OF CONTENTS
Category 01 Aeronautics 515
522 Category 02 Aerodynamics Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.
Category 03 Air Transportation end Safety 528 Includes passenger and cargo air transport operations; and aircraft accidents.
Category 04 Aircraft Communications and Navigation NoA. 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 530 Includes aircraft simulation technology.
Category 06 Aircraft Instrumentation 536 Includes cockpit and cabin display devices; and flight instruments.
Category 07 Aircraft Propulsion and Power 537 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 539 Includes aircraft handling qualities; piloting; flight controls; and autopilots.
Category 09 Research and Support Facilities (Air) 541 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.
Category 10 Astronautics 543 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; space communications, spacecraft communications, commend and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft propulsion and power.
Category 11 Chemistry and Materials S46 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.
Category 12 Engineering 547 Includes engineering (general); communications and radar;,electronics and electri- cal engineering; fluid mechanics and heat transfer;,instrumentation and photogra- phy; lasers and masers; mechanical engineering; quality assurance and reliability; and structural mechanics. Category13 Geosclencas 556 Includesgeosciences(general);earthresourcesand remotesensing;energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.
Cateogory 14 Life Sciences N,Ao Includes life sciences (general); aerospace medicine; behavioral sciences; man/ system technology and life support; and space biology.
Category 15 Mathematical and Computer Sciences 557 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 559 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 56O Includes social sciences (general); administration and management; documenta- tion and information science; economics and cost anaylsis; law, political science, and space policy; and urban technology and transportation.
Category 18 Space Sciences NoA. 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 ...... D-1 Contract Number Index ...... E-1 Report Number Index ...... F-1 Accession Number Index ...... G-1 Appendix ...... APP-1 TYPICAL REPORT CITATION AND ABSTRACT
NASA SPONSORED
._N 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 MULTIAXlS THRUST VECTORING CAPABILITY AUTHORS --) FRANCIS J. CAPONE and ALBERTO W. SCHIRMER (George Washington Univ., Hampton, VA.) Washington Jul. 1993 <-- PUBUCATION DATE 272 p CONTRACT NUMBER "_ (Contract RTOP 505-62-30-01) REPORT NUMBERS -") (NASA-TM.4450;L-17163;NAS1.15:4450) Avail: CASI HCA12/_.- AVAILABILITY AND MF A03 PRICE CODE An Investigation was conducted at static conditions In order to determine the Intemal performance characteristics of • multiaxis thrust vectoring single expansion ramp nozzle. Yew vectodng was achieved by deflecting yaw flaps in the nozzle sidewall Into the nozzle exhaust flow. In order to ellminate 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 Indinatlon angle, sidewall containment, geomeVic pitch vector angle, and geometric yaw vector angle were studied. This investigation was conducted in the static-test facility of the Langley 16-fcot Transonic Tunnel at nozzle pressure ratios up to 8.0. Author (revised)
TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT
NASA SPONSORED A ACCESSION NUMBER --_ A94-60042 ° National Aeronautics and Space Administration. <.-- CORPORATE SOURCE Lewis Research Center, Cleveland, OH. TITLE EXPERIMENTAL INVESTIGATION OF COUNTER-ROTATING PROPFAN FLUI"rER AT CRUISE CONDITIONS AUTHORS --) ORAL MEHMED NASA Lewis Research Center, Cleveland, OH and <-- AUTHOR'S AFRUA_ON 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) Copydght This article presents wind-tunnel experimental flutter results, at transonic relative flows, for a 0.62-rn-diam composite propfen 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 apparentiy single- degree-of-freedom instabilities, associated reepact_ely with the first end 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. 308)
September 1994
01 C. R. FULLER, W. F. O'BRIEN, and R. H. CABELL AIAA Journal (ISSN 0001-1452) vol. 32, no. 5 May 1994 p. 1072-1077 refs AERONAUTICS(GENERAL) (BTN-94-EIX94301315989) Copyright The fatigue life of dynamic helicopter components is highly dependent on the history of loads experienced by the components A94-60015 during flight. However, practical methods of monitoring the loads on STRUCTURE OF LOCAL PRESSURE-DRIVEN THREE- indtviduai components during flight have not been developed. Current DIMENSIONAL TRANSIENT BOUNDARY-LAYER maintenance programs are characterized by frequent inspections and SEPARATION sometimes pmrnature mlJrement of safety-cdticai components. This LAURA L. PAULEY Pennsylvania State Univ., Univemity Park AIAA paper proposes using an artificial neural network (ANN) to predict the Jouma/ (ISSN 0001-1452) voL 32, no. 5 May 1994 p. 997-1005 loads in crfficai components based on flight vedable information that refs can be easily measured. The artifidal neural network learns the (BTN-94-EIX94301315979) Copyright relationship between flight variables and component loads through The separatk)n of a flat-plate, laminar boundary layer under exposure to e ciatebaseofflight variable records and corresponding influence of e suddenly Imposed three.dlmenslonai external adverse load hiatodes taken from an _ military helicopter undergo- pressure gradient was studied compute_onaily by tlme-aocumte nu- ing standard manetNem. Eight standard flight variables are used as mericai solution of the incompressible Nav_er-Stokas equations. The inputs for predicting the time-varying mean and oscillatory components separation decay was then investigated by impulsively removing the of the teilboorn bending load and the pitch link load for seven flight pressure gradient. The development and decay of the separation rnaneuvem. The ANN predicts the mean and oscillatory components structure were compared with expedrnentai results reported by other with accuracy renging 1tom 90.7% to 97.7% correct. Author(El) investigators for the same geometTy. The pedodtc vortex shedding of the three-dimensionai separation was described in terms of a Stmuhai number based on the freeslmam velocity and Blasius bound_yer rnomemum _ckness at the Iocatkm where asparation occur¢ The char_-'tedstic Strouhai number of 0.0136 dunng the se_ devel- EXPLICIT KUTTA CONDITION FOR AN UNSTEADY TWO- opment from the computetion compared fiworably with 0.0134 Imm the DIMENSIONAL CONSTANT POTENTIAL PANEL METHOD experiment. When the adverse pressure gradient was impulsively NElL BOSE Memodai Univ. of Newfoundland, Saint Johns AIAA removed, the boundary layer returned to an attached boundary layer Jouma/(ISSN0001-1452) vol.32, no.5 May1994 p. 1078-1080 much faster than the time required for the separalion development. rets Author (El) (BTN-94-EIX94301315990) Copyright Described is an explicit Kutta condition that was implemented in A94-60016 e time-domain constant potential panel method for two dimensionai REATTACHMENT STUDIES OF AN OSCILLATING AIRFOIL airfoils in unsteady motion. To calcuiate thrust and propulsive efficiency DYNAMIC STALL FLOWFIELD from oscillating hydrofoils with chordwise flexibility, this panel method S. AHMEDMCAT Inst., San Jose, CA and M. S. was written. El CHANDRASEKHARA AIAA Journal (ISSN 0001-1452) vol. 32, no. 5 May 1994 p. 1006-1012 refs (BTN-94-EIX94301315980) Copyright The realtachlng flow over an oscillating airfoil executing large- CROSSFLOW TOPOLOGY OF VORTICAL FLOWS ampltbJde sinusoldai _ around a mean angle of attack of 10 dog MIGUEL R. VISBAL Wdght Lab, Wright-Patterson Air Force Base, OH has been studied using the techniques of stroboscopic schliemn, two- andRAYMONDE.GORDNIER AJAAJouma/(ISSN0001-1452) vol. component laser Doppler velocimetnj, and point diflractk)n interferom- 32,no. 5 May1994 p. 1085-1087 refi; city, for e ireeetream Mach number of 0.3 and a reduced frequency of (BTN-94-EIX94301315993) Copyright 0.05. The results show that the dynamically stailed flow reatlachas in The aim of this paper is to demonstrate that a number of distinct ' a process _ begins when the airfoil is very close to the static stall tolx_giasof crmsflow_ are possH_eusing crromt-point angle on its downward stroke and progresses over the airfoil through a theory and compute_onai results for delta wing flows. The present largerange ofanglesofattackas theairfoilangledecreasestoabout results confirm and extend recent experimental findings for the instan- 6 dog. The airfoil suction peak shows a drmne_ dee as the static stall taneous cmasflow _ on pitching delta wings. El engJe Is approached, and the vek)clty proxies devaiop such that the tow near fiNDsurface is accelerated. The process completes through disappearance of e separation bubble that focrns over the airfoil. Author (El) A94-60031 PRECISION REQUIREMENT FOR POTENTIAL-BASED PANEL A94-6002S METHODS ARTIFICIAL NEURAL NETWORKS FOR PREDICTING JAMES K. NATHMAN Analytical Methods Inc., Redmond, WA AIAA NONLINEAR DYNAMIC HELICOPTER LOADS Jouma/(ISSN0001-1452) vol.32, no. 5 May1994 p. 1089-1090 A. B. COOK Virginia Polytechrdc Inst. and State Univ., Blacksburg, refs
515 01 AERONAUTICS (GENERAL)
(BTN-94-EIX94301315995) Copyright (BTN.94-EIX94311330699) Copyright Good numerical results were obtained from a potantJal-based A shock-expanslon theory is applied to a 2-cilmansionaJairfoil strip panel method for very thin wings. But small panel number while to obtain the expressions for vadous aerodynamic cosffidants of a fin recognizing their matdx equation was nearly singular. Through the wi_ the combined effects of the dihedral angle, cant angle, angle of precision of the method then, the diverse behavior cleecdbed can be atteck, rollingrate, and the shape of a fin.Th|s attempt has the fo,owing explained. El major assumpUons: the flow is hypemonlc, the airfoil has sharp leading edge, U_e flow behind the leadJng-odge shock is lho same as an A94-60035 isentmpic Pmncrd-Meyer expansion, and the reflections of the Mech SURFACE INTERFERENCE IN RAYLEIGH SCATTERING wavas from the curved shock and thase frornthe Mm_nlines are weak. MEASUREMENTS NEAR FOREBODIES El ZAIDI B. ZAKARIA Purdue Univ., West Lafayette, IN and STEVEN H. COLLICOTT AIAA Journal (ISSN 0001-1452) vol. A94-60113 32, no. 5 May 1994 p. 1098-1100 refs APPLICATIONS OF COMPUTATIONAL FLUID DYNAMICS TO (BTN-94-EIX94301315999) Copyright THE AERODYNAMICS OF ARMY PROJECTILES Determined is the dosast pro_dmity for use of direct Rayleigh WALTER B. STUREK Army Reseamh Lab, MD, CHARLES J. scattering near representalve aerodynamic k)rebodles. The aim of _is NIETUBICZ, JUBARAJ SAHU, and PAUL WEINACHT Journal of expedmant is to provide data that willserve as guldelinas for asleclon Spacecraft and Rockets (ISSN 0022-4650) vol. 31, no. 2 Mamh- of rxx_n_u,_ d_noat_ methods for expe,mera _ h_ Apdl 1994 p. 186-199 refs ,xebedy now_ El (BTN-94-EIX94311330678) _ght The abltity to predict the complete set of aerodynamic perfor- A94-60037 manos parametem for pro_e configurations is _e goal of the VANE-BLADE INTERACTION IN A TRANSONIC TURBINE. computational aerodynamidsts at the U.S. An_y Research Laboratory. PART 1: AERODYNAMICS To addeve this gold, predictive capabilities _ use Navler-Stokes K. V. RAO Allison Gas Turbine DIv, Indianapolis, IN, R. A. computa_onal technlqoss have been devek)ped and al)lalled to an DELANEY, and M. G. DUNN Journal of Propulsion and Power extensive number of prolec_e conflguratlons. A summary of code (ISSN 07484658) vol. 10, no. 3 May-June 1994 p. 305-311 refs valldetlon efforts and applications fo_ both spth-steblilzed and fin- (BTN-_-BX94321333365) Cop_0ht stebl_ized projectile co_gmalione are dascdbed. Significant progress Part1 ofthisartkdeprasentsrasu#sofa computeUonaJinvesUge- in the predictive ospability for projecffie aerodynamics has been gon ofthe effectsof _ede row _nm_ on the asrodynan_csof a achieved through the mmik_lity of substantial subemomputer re- _msonlc turbine stage. The predictions are obtelned using a two- sources and modem computmlonel techniques. Cummt and future dimansional Unsteady Navler-Stokas code 1oaeedon an exl)llclt Runge. rasearch arses of interest ara dascdbed and _ an i_ of Kutte algodthm and an overlapping O*H gdd system. This code computer rasourcas and code _ needed to conUnue b"m si_ the flow in tlme-acourate fashion using nonrMlectlve slage progrmm in projectile computational aerodynamics. Author (El) _ow and out_w boundary conditlone and phase-kq_ing proosdu_s for modeilng arbltxary airfoll counts Inthe vane and blade rows. The O- H grid provides Ngh spatial raeolu_n of the Ngh gradient regions near A94-60141 Itmalrh:di_ m_I _ _ m|_'_'_i_m of_ I_ aml COMBUSTION SHOCK TUNNEL AND INTERFACE auffiow boundaries. Unsteady and tlme-averaged airfoil surface pros- COMPRESSION TO INCREASE RESERVOIR PRESSURE sure p_ om compared with those Itom en older _ of I_ AND ENTHALPY code based on the expildt hopeco_ algorll_ and an O.gdd symm, M. A. S. MINUCCI Instltuto de Estudos Avancados, Sao Jose dos and experlmen=Jdeteo_ained ina short 516 AERONAUTICS (GENERAL) 01 flows can be performed. The canard effects are significant)ydependent Mamh-Apdl 1994 p. 452-454 refs o_ csnard position. El (BTN-94-EIX94311329142) Cop_ht In _ paper, a preliminary study has been initiated to invest)gate A94-60152 how estimation model may be simplified to reduce 1he number of TAIL LOAD CALCULATIONS FOR LIGHT AIRPLANES unknown parameters, and how are _ resulting parameter estimates E. V. INTONE Univ. of California, Berkeley, CA Jotm_/ofAJrcraft sffec'tml by such apprmdmate models. Given special attention is the (ISSN0021-8669) voi.31,no.2 March-April1994 p.466-469 refs extreme case of using dgid body model Inthe esti_ elgodb'vn, and (BTN-94-EIX94311329146) Copydght isan ana_k_ method to predict approximedons to param- For the typical light airplane, •neady rectangular wing pisnform eter esUmates. El with an aspect ratio A of st least _, very simple relalons csn be developed. In lhis f_per, calcu_lkxts for Cte t_l losd on a typical l_wt A94-60159 elq_me are given. El JOINED-WING MODEL VIBRATIONS USING PC-BASED MODAL TESTING AND FINITE ELEMENT ANALYSIS A94-60153 BENHE QU Auburn Univ., Auburn, AL and MALCOLM A. CUTCHINS WAKE CURVATURE AND AIRFOIL LIFT Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 2 March-April LUCIEN Z. DUMITRESCU Provence Univ., Marsellle, France 1994 p. 449-452 refs Journal of AJrcraft (ISSN 0021-8669) vol. 31, no. 2 March-April (BTN.94-EiX94311329141) Copyright 1994 p. 465-466 refs For _ jolned-wing model, the COMPAQ PORTABLE 386 is the (BTN-94-EIX94311329147) Copydght modal testing system 1hatis convenient to use. Finite element analysis The aim of this paper is to discuss, in lhe ligM of some previous results show good agreement with the test results for the first four restS, lhephyslcsofthephanomena,whichareobscuredbyempha- modes in terms of the frequency values and mode shapes. El els DOnumerics. In fills context, an 8nelngy wflh lhe jst-llep will be put forward. El A94-60162 BOUNDARY-LAYER INFLUENCES ON THE SUBSONIC NEAR- A94-60154 WAKE OF BLUFF BODIES AERODYNAMIC PROPERTIES OF CRESCENT WING COLIN P. BRITCHER Old Dominion Univ., Norfolk, VA and PLANFORMS CHARLES W. ALCORN Journal of Aircraft (ISSN 0021-8669) voi. P. L. ARDONCEAU Ecoie Natlonele Supedeum de Mecanique et 31, no. 2 March-Aprg1994 p. 443-444 mrs d' Aerotechnique, Poitiers, France Journal of AJrcmft(ISSN 0021- (BTN-_-EIX94311329138) 8669) voi. 31, no. 2 March-April 1994 p. 462-465 refs In ffds paper, studied is h'le wake of a hunlly of slanted-base bluff (BTN-S4-EIX94311329146) Copyright bodies. The incoming Ix)undary-layer momentum _ influence To inve_gate the crescent planfom_, and to determine if any 1he base pressure and wake stagnation point Iocstk)ne. El advantage can be drawn for aeronautical purposes, _ aerodynamic properties of four different wing pianforms have been _. These plenformsare analyt_=zflydefinedwith1hesamechord/spanlowon A94..60193" Ndonal Aerarmul_ and Space Administration. Hugh L. Dfydan Right Research Facility, Edwards, CA. each model, and a variable sweep/span law varying from zero sweep BUFFET4NDUCED STRUCTURAL/FLIGHT-CONTROL SYSTEM to a 22.3 deg aerodynamlc mean sweep. El INTERACTION OF THE X-29A AIRCRAFT A94-601S5 DAVID F. VORACEK NASA. Dryden Right Research Facility, SCHEDULED MAINTENANCE OPTIMIZATION SYSTEM Edwards, CAand ROBERT CLARKE Joum_ofA/rcraft (ISSN 0021- RAYMOND J. ANDERSON McDonnell-Douglas Coq)., Saint Louis, 8668) voi.31, no.2 March-April1994 p.441-443 MO Journal of Aircraft (ISSN 0021-8669) voi. 31, no. 2 March- (BTN-94-ED(_11329137) Apdl 1994 p. 459-462 Observed in the lateraJ.dlrectionel rodsof the flight-contxoi system (BTN-S4-EIX94311329146)Cof_ght is an _ interaction during iN) high angle-of.-atlack flight Ongoing development is currentiy being done in an integrated envelope exper_Jon of the X-29A f_ward_ wing aircraft. This interaction consists of stnJcturelrnodes _at result in commands to lhe software package composed of a FMECA modulo, a RCM module, a control surface actuators. El SMID, a SMIC module and an ICT module. These said modules will provide an integrated consolidated process for rapid assessment of previous aircraft scheduled maintenarce requirements, combat turn- A94-S0164 around times, and 1he necssesW toois to IXOVk_ future scheduled DETERMINATION OF TIRE-WHEEL INTERFACE LOADS FOR maintenance requirements and optimum elapsed time for ICT's. El AIRCRAFT WHEELS S. KANDARPA Norm Dame Univ., Notre Dame, IN, B. F. SPENCER, A94-60157" National Aeronautics and Space Administration. JR., and D. J. KIRKNER Jouma/ofAJrcraR(ISSN 0021-8669) vel. LangleyResearchCenter,Hampton,VA. 31,no. 2 March-April1994 p. 433-440 refs EFFECTS OF MODEL SCALE ON FUGHT CHARACTERISTICS (BTN-94-EIX9431132S136) Copyright AND DESIGN PARAMETERS A nunwrical tool is developed for determining the pressure WILLIAM H. PHILLIPS NASA. langley Research Center, Hamp- disMbu_on at the tiro-whool interface of an elrcrs_-whool from exped- ton, VA Jouma/ofAJrcraft(ISSN0021-8669) voi.31,no.2 March- ma_,y o_r_ sm_s. The_ _ ane_symme_ April 1994 p. 454-457 mfs finite element model which is subjected to a general loading. The (eTN-94-BX_311329143) Cop,_n_ht loading is mpresanted as a double Foufler sedes, and _e components P_ in_ paperis ash_plewayofexamini__e effects are detemtned by a leest squares fit using the expedmantelly doter- of scaling on a wide range of perametem. In Ihis analyels, the meln mined strains. A Qnlte elemont code based on linear eles_dty for an variables coneidered are namely, Ihe scaJeand ma_ of 1hevehicle and mm_ wasdevek_aedto perform_ _. Sample ema_,_y o__ _t_rt_. B _mer_ _re_ to _u_ate t_ v_d_, and_ _ of t_e aigor,hm.Rnany,a_e_ltetkx,_ of _ typeof ana_tmare A94-60158 and future di_ are indicated. Au_tor (El) PARAMETER ESTIMATES OF AN AEROELASTIC AIRCRAFT AS AFFECTED BY MODEL SIMPLIFICATIONS A94-601S6 A. K. GHOSH Indian Inst. of Tech., Kanpur, India and S. C. AIRCRAFT FLEET MAINTENANCE BASED ON STRUCTURAL RAISINGHANI JoumalofAircraft(ISSN 0021-8669) voi. 31, no. 2 RELIABILITY ANALYSIS 517 01 AERONAUTICS (GENERAL) J. N. YANG California Univ., Irvtne, CA and S. D. MANNING Jouma/ used, and only slightly larger than the number of modes required for of Aircraft(ISSN 0021-8669) voL 31, no. 2 March-April 1994 p. 419- direct aeroelas_ anaiy_s of a single structural case. Author (El) 425 refs (BTN-94-EIX94311329134) Copyright A94-60171 A _ crack grow_ ana_jl_ methodology, based on the AIRCRAFT ACCIDENT FLIGHT PATH SIMULATION AND Iognormal random vadable model, is described and demonstrated for ANIMATION two practicel aircraft stmcturai maintenance applications. In the first D. E. CALKINS Washington Univ., SestUe, WA Journal of Aircraft sppllcaUon, a reliability centered maintenance analysis for evaluating (ISSN0021-8559) vol.31,no.2 March-April1994 p. 376-386 refs aircraft stnctural maintenance and supportability requirements and (BTN-94-EIX94311329129) Copyright optk_lS in terms of risk or reliability is demonslmted. The sensitivity of Dudng 1987, Northwest Airlines Right 255 crashed in DeVoit inthe initial and reinspec'_on intervals to variations in analysis variables is summer, and Co_nental AJdinesRight 1713 crashed in Denver in the invesUgated using a cutout In an aluminum-lithium cheek harne. The winter. This _ will describe the re(x)l'slnJ¢tkm, simulation, and second application is the maintenance scheduling for a fleet of aircraft animation of the time dependent flight psth for each accident through on a caiandar yaer beels interms of dsk or reliability. The crack growth a process known as forensic enginaedng. Forensic engineering is the life dispemon clue to material, service usage severity, and aircraft applica_on of scientific and engineodng knowledge to legal matters, utlliza6on rate on the fleet maintenance schedule are accounted for. such es aoddent _. The flightpa_s were reconstmctod es Nrcmft fleet tracldng data am used and the sans_vity of fleet mainto- an aid in visualizing the sequence of events and the factom InvoNed in nance requirements to variations in the design stmse isveis and other each accidanL Author (El) vedob_es are inveslJgaicl and presented. Author (El) A94-60173 A94-60168 EFFECTS OF THRUST LINE OFFSET ON NEUTRAL POINT TIME SIMULATION OF FLUTTER WITH LARGE STIFFNESS DETERMINATION IN FLIGHT TESTING CHANGES U. P. SOLIES Tennessee Univ. Space Inst., Tullahoma, TN Jouma/ M. KARPEL Technlon - israel Inst. of Tech., _ israel and C. D. ofAircraft(ISSN0021-8669) voL31,no.2 March-April1994 p.362- WlESEMAN Joumai of Aircraft (ISSN 0021-8669) vol. 31, no. 2 366 refs March-April 1994 p. 404-410 refs (BTN-94-ED<_,311329127) Copyright (BTN-O4-EIX94311329132) Copyright On aircraft with high or low thrust lines, conventJorBI stability flight Time simulation of flutter, involving large local stmctu_ changes, tset maU_o 518 AERONAUTICS (GENERAL) 01 STOLLERYJournal of Aircraft (ISSN 0021-8669) vol. 31, no. 2 date. Changes in lift and pitching moment due to ventral nozzle March-Apdl 1994 p. 322-329 rets operation are smaller at full scale. Author (El) (BTN-94-EIX94311329122) Copyright Low-speed wind-tunnel tests were made on a number of vortex A94-60182 flap and vortex plate configurations at the Cranfietd Institute of Technol- UNSTEADY LIFT OF A FLAPPED AIRFOIL BY INDICIAL ogy. The objectives of the expedrnent are to assess the benefits of CONCEPTS these devices on the lift/drag ratio improvement of delta wings. The J. GORDON LEISHMAN Maryland Univ., College Park, MD Journa/ force 8nd surface pmseum meesumiTmnts were made on a 1.15-m ofA/rcraft(ISSN0021-8669) vol.31,no.2 March-April1994 p.298- span, 60 (:legdella wing model. The results indicate that the vortex flap 297 refs deflection angle, which causes the flow to attach on the flap surface (BTN-94-EIX94311329118) Copyright without any large sapara_on, shows a much higher llft/drag ratlo than A praclical rneth(xI Is described for computing the unsteady lifton the flap deflect;on angle which forms 8 Iseding-edge separation vortex an airfoil due to &m arbltTarymolion of 8 tndling-eclge flap. The result for over the _ surface. The performance of 8 vortex plato protn_ing bonn 1he incornpmesibie cese ISobtained in state-space fo_m by means of the leacing edge of the datum delta wing IS comparable to that of the Duhamal super_ and employing an improved exponentiaJ alp vortex flap. However, when the vortex plate ISused with the vortex flap pm_ to Wagner's indidaJ lift fu_. For subsonic compress- deflected, it showed no benefit in these tests. Author (El) Jble flow, the indidal lilt at small values of §me due to impulsive Ualling-edge flap deflec_on is obtained from linear theory in conjunc_on A94-60179" NaS_lalAemrauticsandSpaceAdminislmtJon. Ames with the aerodynamic redprocal theoren_. These results are used with Research Center, Moffett Reid, CA. expedmental results for the oscillating case to obtain complete expo- VORTEX-WING INTERACTION OF A CLOSE-COUPLED nential approxtmmions for the indlcial response due to iml0uisive flap CANARD CONFIGURATION deflec,Bon. The final result for the unstoady litt due to an _bltmry flap EUGENE L. TU NASA Ames Research Center, Moffett Field, CA motion in subsonic flow is obtained in state-space form. Numerical Joum_ofAJrcraft(ISSN0021-8669) voL31,no.2 Math-April 1994 results and comparisons with experimental deta are shown. p. 314321 refs (El) (BTN-94-EIX94311329121) Copyright The thin-layer Navier-Stokes equations are solved numerically to Jnvestiga_ the effects of canard vertical position on 8 close-coupled, A94-60185" National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. canard-wing-body conflguraJJonat a transonic Mach number of 0.90 PREDICTION OF ICE SHAPES AND THEIR EFFECT ON AIRFOIL and angles of attack ranging from -2 to 12 deg. Canmd-wing Intmac- tJonsare inves_gated for the canard postponed above, =op_,_ wnh, DRAG end below the wing (high-, told- end low-canard poaltlons, respectlvely). JNWON SHIN National AeronaulJce and Space Administration, The computational msub show favorable canard-wing in_ractincm for Cleveland, OH, BRIAN BERKOWITZ, HSUN H. CHEN, and TUNCER the high- and told-canard conflguralJ(x_. The unfavorable Hftand drag CEBECI Joutrm/ofA/rcraft(ISSN0021-8669) vol.31,no.2 March- characteristics for the low-canard configuration are examined by analy- Apd11994 p.263-270 refs ses of the low-canard flowfiald stricture and found to be (lirecUy (BTN-94-EIX94311329115) _ght a11flbuted to the Interaction between the canard vortex and the wing of ice shapes and 1he resulting drag increases are surface. At relalh_y low angles of attack, the low-canard vortex pesess presented for a NACA 0012 airfoil. The calculaUons were made using under 1he wing surface and Induces low pressures on the wing lower a comblna_n of modlfled LEWICE and intemclJve boundanj4ayer surface. As the angle of snack IS ircresesd, the low-canard vortex codes for a wide range of values of parameters such as airspeed and impects the wing surface and IS spilt into two clistlnctvorlk;es. t0mperatum, the droplet size and liquid water content oflhe cloud, and Autho¢ (El) the engle of atlack of the airfoil. Based on expedment_ data, an Improved correlation of equivalent send-grain roughness was devel- oped. CalcuiotIKI ice shapes am in good agreement with experimental A94-60180" NatkxlalAeronautlcsendSpace_. Ames data for dine ice, but some differences are shown between predictions Research Center, Meffett Reid, CA. and experlmentel data for glaze ice. Calculated drag coefficients PROPULSION-INDUCED AERODYNAMIC EFFECTS generally folow trends shown bythe expedrnenlal dala. Authm (El) MEASURED WITH A FULL-SCALE STOVL MODEL BRIAN E. SMITH NASA Ames Research Center, Moffett Reid, CA, WILLIAM A. POPPEN, andJ. DAVID LYE Jouma/ofAJmraft (ISSN A94.601U 0021-8669) vol. 31, no. 2 March-Apdl 1994 p. 306-313 rids COMPUTATIONAL ANALYSIS OF A SINGLE JET (BTN-94-EIX94311329120) Co_ IMPINGEMENT GROUND EFFECT LIFT LOSS Propulsion-induced mrodynamic Inmrference effects are pre- XINZNANG Southamp_n Univ. (England) and DAN N. ING JoumaJ sented for a full-scale, powered, STOVI. flghmr alrcreff model. The of A/mmfl(ISSN0021-8668) voL31,no.2 Mardl-Apd11994 p.256- qector_ thrust conflguraSon, designated the E-TA, was 262 refs tested at low apeed in the 40- by80-ft and the 80- by 120-ft wind tunnels (BTN-94-EIX94311329114) Copyright of the National Full-Scale Aerodynamics Comptex located at NASA A study wes camed out on singie-round-;_)t,ground eftect liftloss. ARC. Aerodynamic effects on vehicle llft, drag, and pitching moment The jet exJl Mach number and velocity were 0.71 and 240 m/s, am presented over a range of effecSve velocities for slmulmneous respectively. The effects of ground height, baffle pJste edge, and jet exit oberation of _l i_ng jets. The jeU_rhwne inte_ for separate turbulent Int_ were assessed, and Navter-Stokes equalJons were operaUon of the lifting ejector system and vectorable ventral nozzle are solved using oomputmlonal fluid dynamics. Turbulence closure was also presented. Ejector and engine inlet momentum effects were fully achieved using a k-epellon model, and the result was compared wtth sirnulated Inthese full-scale, powered tests. The Jetthrust vector engis calculations obtained with a differentialsVese model. Three baffle plate of the ventral nozzle wes varied to slmulate Imnaltlon from hover to edms were tested (rounded, squared, and chamfered), and the 7ound wingbome a_ht modes. When _he rang ,_x_or symm and ventr_ heights vaded from ete = 0.15 to 0.8. Itwes found that now mechenisms nozzle am operated simultaneously, the induced effects on lift de- varied slgniflcen_ with ground heights. A coherent vortex existed cresse es the tl'm,st vector angle of the ventral nozzle approaches the between the barite plate end _ ground at _ low ground heights (eta hodzontel. A negative increment in drag Is produced over 8 narrow less _n 0.25), which suppmseed and/or dalayed separation at the porl_n of the _ speed range when the ejso|o_sand ventral baffle plate edge and induced high lift Ioa. At the high ground heights nozzle are operated together.Aero_ induced effectsof (eta greater than/equivalent to 0_5), the vortex disappeared and ejector system measured at full-scale compsre well wi_ the small-scale sepamtlon at the plate edge played an importsnt part In determining the 519 01 AERONAUTICS (GENERAL) liftloss. The baffle plate edge was found to account for as much as 14% elrbrealhlng first stage and rocket second stage are evaluated for of lhe ground effect llft loss. The stress model was found to improve the staging Mach numbem that range from 5 to 14. 'With advanced accuracy of the prediction. Author (El) technologies, the two-stage systems am heavier than lhe singte stage. Using a rocket on the firststage to accalerate from lhe turboramjat limit of Mach 6-Mach 10 elgrdf_ decreases by weight as compared to A94-60187 the Mach 6 staged system.With currenttechnology, the scmmjet two- QUANTITATIVE LOW-SPEED WAKE SURVEYS stage systems are half the weight of the single stage, but still require G.W.BRUNE Boeing Comrnercial AIrplane Co., Suffie, WA Jounm/ substantial technology development in the areas of Inlets, nozzles, ofAircmft (ISSN 0021-8669) voL 31, no. 2 Mar(h-April 1994 p.249- ramjet propulsion, active cooling, and high-temperature structures. 255 refs El (BTN-g4-EIX94311329113) Copyright Theoradcal and practical aspects of conducUng lhree-diman- elonel wake measurements tn large wind tunnels am reviewed with emphasis on aPl_k:atkxm in low-speed aerodynan_. Such quanma- CHARACTERISTICS OF THE SHU'n'LE ORBITER LEESIDE Uve wake surveys furnish separate vaJues for _ components of drag FLOW DURING A RE-ENTRY CONDITION such as profile drag and induced drag but also rneasum llftwNhout the WILLIAM L. KI.EB National Aeronautlcas and Space Adndnistration, use of a balenca. In addition to global data, detalis of the wako tk_vtield Langley Research Canter, Hampfon, VAand JAMES WEILMUENSTER as well as sparr_se distributions of lift and drag are obtained. This JoumalofSpacacmftandRockats (ISSN 0022-4650) voL 31, no. 1 argo cismonsums the value of this measurement technique using Januaw-February 1994 p. 8-16 refs data from wake measuremants _ on a vadely of low-speed (BTN.94-EIX94311322888) _ght con_um_ons Indudlng the complex high-llft system of a Vansport A study of _a leesk:leflow chsractedstics of _ Shuttle Orbiter is aircraft. Au_or (El) presentod kx a re-antn/_ght condltk_. The flow Is compu_d using a point-implicit, finite.volume scheme known as the Langley •-m_mnodynm_ upwindrelaxa_onelgod_m(LAIRA). LAIRA is a A94-60193 ucond-order-accurate, laminar Navler-Stokes solver incorporating EFFECTS OF THE ROLL ANGLE ON CRUCIFORM WING- flnlte-rme chemistry with • radiative equilibrium wall temperature BODY CONFIGURATIONS AT HIGH INCIDENCES distributionand flnito-rato wall catalysis. The compma_onel results are J. MEYER Israel InsLofTech., Halle(Israel) Jouma/ot,._fl compared wflh measured Inffight surface pressure and surface heating andRockets(ISSN 0022-4650) voL31, no. 1 January-February 1994 from severel ,Shuffle Ofoitsr flights. El p. 113-122 refs (BTN-94-EIX94311322903) Copyrlght Three crudform wings were tested on a body at Ihre rogangles, up to tlree kmgitudinal pcaitlons, and angles of snack of up to alpha = 90 PLANAR KRF LASER-INDUCED OH FLUORESCENCE degin a low-speed w/nd tunnel. The to, angle affects, In a elgnllkant IMAGING IN A SUPERSONIC COMBUSTION TUNNEL manner, h'_e fin normel foce coeflk:im_t The nonnel fome on lhe upper T. M. QUAGLIAROLI UnivofVirginla, Chadottosville, VA, G. LAUFER, fins decreases to zorn, at alpha greater than _) deg, po_ because S. D. HOLLO, R. H. KRAUSS, R. B. WHITEHURST, III, and J. C. JR. vortex breakdown on Ule lower fins induces separated flow over MCDANIEL Jouma/ofPro_andPower(ISSN 0748-4658) voL upper fins. As a consequence, a strong ro_IIngmoment Is Induced at 10, no. 3 May-June1994 p.377-381refs these incidences at asymmeffic roll angles. El (BTN-O4-EIX94321333315) Copydght Plenar fl_ Images of OH were obtained in a contk_uous- now,ek,cV,c_,y heat.d,h_ ar_'_p_, hydromn-=rcombust_tun- A94-60198 nel, using a tunable KrF laser.These images were compared to DRAG REDUCTION FOR TURBULENT FLOW OVER A _ tiuorascanca images produced using a doubled- PROJECTILE, PART 2 dye laser under elmiler ¢orw:litior_.Forb_ede_ conflgural_onused, SHEN-MIN LIANG National Chang Kung Univ., Tainan (Talwan) and the Images of doubisd-dys laser4nducad tkx)rascanca dernorsVated a JAN-KUANG FU Jouma/of Spacecraft and Rockets (ISSN 0022- severn distortionas a result of laser beam absorption and fluoresconce 4650) vol. 31, no. 1 January-February 1994 p. 93-98 rels Yapping. By cormmt, imagee of the fluorescence induced by the (BTN-94-EIX94311322900) Copyright tunable KrF laser retelned ti'_esymmetry properties of the tiow. Based The performance of a secant-og_inder-boattall projectile in on signakfo-nolu redo n_, the yieldoflhe fluorescence _le transonic regime in terms of drag is nurn_ Inve_tKI. To o_lained w,h Ihe doubled-dys laser is conelderal_ larger _an the Improve the projectile perfonnarx:e, a drag reduction method, paulve fluormcanoe yield induced by ti'm KrF taser. The measummant uncar- control of shoc_dayer Interaction on the _I, is appl_d. lalntles In lhe present faclllty of OH fluorescence JRducedby'he KrF The pr_m_ results show thstlhe pesslve control _ _ on the laser were pdmadly controlled by photon-statistical noise. Based on boattell not only can reduce the _I drag but also can reduca lhe hme results, tunable IOF liner systems are recommanded for quart- basedrag,andanadd_kx_7%(approximately)totaldragreductionis OH imaging in facilities where _e product of the op_cel path obtained compared wlth U_atwlU_outU_e paselve control. The passlve length for erd_erfluorescence excitation or coileclk)n and the average control effect on totel drag raduction le lounci to be insanelt_e to OH concentration along that pa_ Is greater than 10(exp 16) cm/cm- Reynolds number. El (exp 3). Au_or (El) A94-60205" National Aarormutlcs and Space Administration. Lang_yResearchCenter,Harnp_m,V_. INJECTION OF BUBBUNG LIQUID JETS FROM MULTIPLE TECHNOLOGY AND STAGING EFFECTS ON TWO-STAGE- INJECTORS INTO A SUPERSONIC STREAM TO-ORBIT SYSTEMS TAKAKAGE ARN Virginle Polytechnic Instand State Unlv, _, _.XN W.WILHn'E Nat_r_/,,rorau,ca andSpece.4_noy,L.ang_ VA and JOSEPH A. SCHE1-Z Jounm/of _ and Power (ISSN Research _r, Hampton, VA, WALTER C. ENGELUND, DOUGLAS 0748-4658) voi. 10, no. 3 Mw-June1994p. 382-386 refs O. STANLEY, CHRISTOPHER MAFTEL, ROGER A. LEPSCH, LANCE (BTN-94-EIX9482133331e) e. BUSH, and KA'T'HI:WNE. BURSTER JoumdofS_and Multipte (12 Injectors) bubbling Ikluidjets (helium microbul0blesIn Rockwts(ISSN0022-4650) voL31,no. 1 Janu_eI)maty1984 p. wator) were In_ Imnwerse to a M = 2.4 sldlow. Panetratlon and 31-38 refs spray plume spreading angle were measured directly using (BTN-94-EiX94311322891) Gopydght nanmhado_ra_hsand_nt.I_h_dp_m, respe_ely. The ex- Horizontal takeoff and landing two-stage systems with an perimentswere pedormed at two conditions, i.e., the constant supply 520 AERONAUTICS (GENERAL) 01 pressureconditionandtheconstantliquidmassflowratecondition.For JOSEPH S. SHANG Journal of Thennophysics and Heat Transfer thecaseofaparallelarrangementof the injector orifices to the airflow, (ISSN 0887-8722) voL 7, no. 4 October-December 1993 p. 668- the penetration of the jet army increased steadily from front to back. The 679 refs last jet (12th jet) has over 5 times the penetration of the firstjet for the (BTN-94-EIX94351142135) Copyright water only case. The usual similarity law for the penebatlon, h varies Hypersonic flows past hemisphere cylindem at zero incidence in directly as q exp -0.5, was approximately valid also for the multiple chemical and thermal nonequilibdt_ are invasSgated for a range of water-only jets. For the bubbling jet case, the penetration of the firstjet Mach numbers from 10 to 18. The numedcel code shows excellent doesn't ch_mge with increasing gas concentration gamma, but the rear comparison for surface pressure and heat tm_er predlcUon w_ jets have lese penetrstlon height than that of Xquid-only jets at the recent experiments conducted in a shock tunnel. The numerical code constant injection pressure condition. F(x the cor,.stant injes_n pres- elso compares well for steg_ point heat flux predictions at altitudes sure _, _ resultingpene_¢ionof_e jetphumedecreased of 22 and 37 krn w_ a eat of earf/er expetfmer_. Numed_ sofu_ons increasing gamma. On _ other hand, for the constant liquid mass flow with _ vibrational equilibrium model are compared wi_ those of rate condition, the pene_ of the multiple bubbling jets increased a multltemperature nonequilibrium. The stagnation point heat transfer is little with increasing ganvna. Straight co_mnt jets just coming out of 10 to 23 percent higher for _ nonequilibdum solutions in _ Mach orifice were obsen_d tot the gamma = 0 ceae. Conicaljat plumas were number range of 12-18. The importance of a multitemperature model for obtained for the bubbling jet case. Themtore, the width of the jet plume accurate predic_on of stagnation properties, particularly the heat increased by using the bubbling jet. The effects of the an_e between transfer, is noted. The variation in computed shock-standoff distance the orifice army and the treeatnmm direction and the sudactent substanUatas_ theMachnumberindependencepdnc_plaapplicable concentrationor,the pemeVat_ and n/xingof muWplebubblingjets to ideal gases does not hold fordlssodatingflows. Over the range of warn also dadfled. Author (El) Mach numbers, ff_enoticeable influence of vibm_ional rel_ on the tempembJm distdbu_ons and mass concenblltions in the vi_nity of A94-60334 ed'toc_ is stream in the present study. Author (El) ORNITHOPTER WING DESIGN JAMES D. DELAURIER Univ. of Toronto CanadanAeronau_csand A94-60429 ,._eCWJOLCr,.a/(ISSNDD08-2821) yoL40, no. 1 Marct)1994 p. 10- DIRECT SIMULATION WITH VIBRATION-DISSOCIATION 18 refs COUPLING (BI"N -94-EIX94331337499) Copyright DAVID B. HAS North Carolina State Univ., Raleigh, NC and H. ,6.. Thephys_ of _p_-_r_ _ hesbeenst.dledin orderto HASSAN Journa/ of Thennophys/cs and /-feat Trans4er(ISSN 0887- gaininsightson howanimals_ andto assessthe poesUityof 8722) vol. 7, no. 4 October-December1993 p. 680-686 rets achieving this with 8 flapplng-wing airplane (omithopter). To this end, (BTN-94-EIX94351142136) Copyright the major foous of this work has been the proof-of-concapt tiight tests In the inYastigat|on of hypersonlc _ flows, It is Important to of 8 remo_ly-piloted, ongJno-poworod omlthopter. The level of sophls- conelder the effects of thennel nonequtHbdumon the dissociation rates. tica_on of the analyses and laboratory experiments, which determined Because the vibra_onal mode requires a finite time to relax, vibrational thedeath changastothe_, wasdrk.enby0_eresdtsfrom energy may not be available for dissocla_on imn'mdlately behind the these flight tests. Ultimately, successful sustained flight required the shock. In this way, the diseoclst_n of the preshock species can be development of a con_rohensive uneteady-aefody_aeroe_ delayed for a elgniflcant portion oflhe hypemonlc shock layer. The ana_ _ .t_ ._nd_,rv_ expert',ram. Aue'_{Sl) of _o_men_ns of _'_ o_rect almu_a_ Monte Carlo (DSMC) method of bird do not account for vlbra_on-diseoclatJon A94-60427 coul_. Haas and Boy_ have proposed the vibra_on_ favored THREE-DIMENSIONAL UPWIND PARABOUZEO NAVIER- diseocla_ (VFO) moc_ to acoom_h _s Wk. Th_ moc_ made use of rneasummen_ of i_ distance to determine model con- STOKES CODE FOR SUPERSONIC COMBUSTION FLOWFIELDS stants. A more general expression has been derived that does not GANESH WADAWADIGI lowa State Univ., Ames, IA, JOHN C. require any experimen_ input. The model is used to calculate one- dimensionel shock waves in nitrogen and ti,te flow peat a lunar transfer TANNEHILL, and PHILIP E. BUELOW Jouma/of 7hemtophysksand vehicle (LTV). For the conditions considered in the simulation, Heat Transfer (ISSN 0887-8722) vol. 7, no. 4 October-December influenoe of _issocla_on coupling on heat blmsfor in the 1993 p. 661-667 refs stagnation region of 1he LTV can be important. Author (El) (BTN-94-EIX94351142134) Copyright A new upwind, pambolized Navlar-Stokas (PNS) code has been devek_=edtocompumthe ewe.d_ _ reactingk_ A94-604,_ NationalAemnautlcsandSpece_. Ames in scramjet (supersonic combustion ramjet) engines. The code is a Research Center, Moffatt Reid, CA. modllk:mionofa_ethree-dmmsto_upwindPNS(UPS)airflowcode CALCULATION OF REAL-GAS EFFECTS ON AIRFOIL whlch has been extlmded in the prasent study to pemlit intemel flow AERODYNAMIC CHARACTERISTICS cak:ulationsw_ hydmgen-alrchemtny.W,hlhseeaddlUons,thenew CHUL PARK NASA. Ames Research Center, Moffatt Reid, CA and codo _ tho _U_ ofconq_.m_ b_ earody_ andpropui_vo SEOKKWAN YOON Jo_rml of Thennophysk_ and Heat Transfer flow_ide. The algorl_m solves the PNS oqua_m using a (ISSN 0887-8722) vol. 7, no. 4 October-December 1993 p. 727- volume, upwind TVD method based on Roe's aplx(zdmate Rien_mn 729 rats solver that hes been modilled to account for nonequil_bdumeffects. The (BTN-_,-BX_3S 1142143) Cow_ght fluid medium is assumed to be a chemically reacting mlxtum of Employing the CENS2H and the CENS2D computer codes, this thermally pedect (but cak_k_ly _ct) gases in thermal eq_ib- technical note cak:_tes the effects of two 521 01 AERONAUTICS (GENERAL) (BTN-94- EIX94361135427) Copyright 02 A systematic computation schema is presented for PAR-WIG AERODYNAMICS cruising pedormance, on a FORTRAN program. It is suitable to be executed on personal computers. Effect of many parameters on the Vansporlatlon efficiency is expfored. Two concepts are presented in Includes aerodynwrfcs of bodies, combinations, wings, rotors, and three views and artist impressions. One is a smallest single-crewman control surfaces; and internal flow in ducts and turbomachlnery. vehicle for expedment, sports or pleesum. The other is a large vehicle for dvlt Vansportation. Both have twin hulls, which are quite suitable to A94-603S4 install 'SMALL.TAIL-WIG' or 'WlG-IoC to establish Iongitudlnai att_ude INCIPIENT TORSIONAL STALL FLUTTER AERODYNAMIC stability. Author (El) EXPERIMENTS ON THREE-DIMENSIONAL WINGS PETER F. LORBER United Technologies Research Center, East Hartford, CT and FRANKLIN O. CARTA Journa/of _ and Power(ISSN 0748-4658) vol. 10. no, 2 Merch-Apri11994p. 217-224 A94-S062S refs STATIC AND DYNAMIC FLIGHT-PATH STABILITY OF (BTN-_-EIXS4341338362)Copy_ght AIRPLANES The aerodynam_ of smail amplilude pitching motions neer stail OSAMU KOBAY_SHI Kawase_d Heavy Indust_s Ltd., G,fu (Japan) have been stuckd experimentsny in order to improve understanding of Tnr_ac_ns of _ ,_ SocietyforAe_ and _ torsional stall flutter. A model wing was oedllsted in plich at several erces(ISSN0549-3811) vol. 36, no. 112 August1993 p. 107-120 smail _ over a wide range of conc_:xm. Unsteady sudace refs pressures were measured and intagmtecl to determine _ aerody. (BTN-94-EIX94361135428) Copyright namic damping et rNe q)anwise stations. _ now damping wes The concept of flight-peth stability, whlch is today in ues, is besed and, for moderate Mach number and frequencies, in good on the characteristics of airplanes in equmbdum,or steady urmccelereted agreement w_ _ airfoil theory. Strong nagstive damping was found flight ooncl_ons, and so can be called 'staUc flight-path stability'. After for moSons centered near static stall for all studied reduced fmquen- stmmadzing the studies on the staUc flight-peth mbility from several des, Mach nun-,b_, and sweep angles. The 30-dagmes swept-beck points of view, the concept of 'dynamic flight-path stability'for accaier- configuration wes found to become negatively clamped over the entire ated/decelerat_ flight conditions is introduced, and the elevator com- span nearly simultaneously, while the unswept model exhibited local pensation necessery to provlde an ai_ane wllh a deslred dynamlc raglons of negative damplng ti'let moved towsn:l the wlngtip es the rnean flight-path st_I,y is obtsC,m. Furthamxxe, Itwough _ study on the angle of attack was Increased. Author (El) time hlsto_ ancl the root-locus charactedstlcs of alrplane's motion, Itis show. thet the airp_ne w_ the _ can stably cont_ the flight-pa_ by b'melevator In the backside region. Aulhor (El) N94-34612# DexseuIt Avia_on, ,_int-Cloud (France). HIGH INCIDENCE FLOW ANALYSIS OVER THE RAFALE A [ANALYSE THEORIGUE DE L'ECOULEMENT AUTOUR D'UN RAFALE A A GRANDE INCIDENCE] JEAN-DENIS MARION In AGARD, Technologies for Highly N94-35394"# National Aeronaulk:s and Space Adm_il_tlon. Ames Aircraft 7 p Mar. 1994 In FRENCH Research Center, Moffett Field, CA. Copyright Ava_: CASI HC A02/MF A03 FLIGHT TESTING OF A LUMINESCENT SURFACE PRESSURE A good high angle of ettack (AoA) behavlor Is a requisite for any SENSOR new combat aircraft. In order to gsin a better knowk)dge of 1ha tfow et B. G. MCLACHLAN, J. H. BELL, J. ESPINA, J. GALLERY, M. high AoA, cempula_n over the 'RAFALE A' has besn conductS. The GOUTERMAN, C. G. N. DEMANOANTE, and L BJAFIKE Oct. 1992 ain:raff is In a full noes down contn_ conliguretion: low speed, low 28p amtude, high AoA, snd large con_ surfec_ denect_. Moreover, (Contract RTOP 537-O3-23) sikleslip is consk:leredso es to eseses the leterai behavio¢ of b'_eaircraft (NASA-TM-103970; A-92175; NAS 1.15:103970) Avail: CASI HC A03/ In _ high AoA mgima. Tha computatior_ domain erot.o:l the com- MF A01 plete aircraft Is discmtized into an u_ mesh and the flow is NASA ARC hes conduct_ flight tests of a new bjpe of mmdy. computed w,h ,, 31:) inv_dd (Eu_) approech in _nite elements. nernic pressure sensor based on a luminescent surface costlog. Flights Aerndynamic coerlk_nts have besn anaiyzed togsthar with tha topol- were conducted at the NASA ARC-Dryden Right Research Facility. ogy of the flow in these high AoA oonflgu_. Results have been Tha luminesser_ pressure senesr is bued on a surlace o_ting which, found to ytaida _ agreement concerning the flow features (Ioes when III_ wl_ ultraviolet light, emits visible lightwith an intessity of weathercock stabilily at high AoA) ai&x:ugh abeolute vaJues of dependent on the k)cai air pnmsure on the lufece. "rhis t_hnique _ ere dl beyond reach of ti'_ bludc mete. In an makes It poesible to oblaln preesum dal over the entire imdece of an attempt to get insight into nonsymmst_ llow es it can be found aircraft, es appoesd to ¢onventlonai _, whlch can only exper_ly et h_h Ao_, a _ of U_eboundary condmons mm, mam._rernentset _ po_n_s.Tha(qect_e ofthe Sg,_t which creete a mx,_e of vorticityhes been Implementsd. This leeds to tests wes to evaiuate the effectiveness and prectk:ailty of a lumlnescent ti'm exlstlmoe oflarge amplitude side fo¢ces agreeing wllh expedments. pressure sensor in the actual flight environment. A luminescent pres- (revised) sure esrmor wes Instailed on a fin, the Right Test Fixture (FTF), thst is attached to _ undemk_ of an 1=-104 ainmdt. The response of one surfacecoatingwas evaluatedat low _pen_r_c Mach N94-34704"# Rice Univ., Houston, TX. numbers (M = 1.0-1.6) in order to _ an Initial e_imate of the ANALYSIS OF WAVELET TECHNOLOGY FOR NASA sensor's capables. This memo descdbes the test approech, the APPLICATION8 Final Report techniques used, and the pressure sensor's behavior under flight R.O.WELLS, JR. 31May1994 19p _. A chct _ betwesndetapmvk:k_bymekm'_r,es- (ContractN_U_) cent pressure sensor and b'_et produced by conven0onal pressure (NASA-CR-195929; NAS 1.26:195929) Avail: CASI HC A03/MF A01 i_tion shows b_at1he lumlmmcent esnsor can provide quaN- The purpoes of thls 9rant wes to intnxlUce a breed gn)up of NASA titetive da_ under flight condi_ons. However, the test results aiec show m_mmher8 and m:kninistmtomto wavelet _hnology 8nd to detemlne thet the sonsor has a number of Ilmltetlons which must be Kldresesd itsfuture mie in mesarch and devaiopmont et NASA JSC. The activities if_s technique is to prove useful in the flight envi_ of several b_ held bet_esn NASA JSC scientists and Rice Author(revVed) Univendty researchers me discussed. An stlachad paper, 'Recent 522 AERODYNAMICS 02 Advances in Wavelet Technology', summarizes some aspects ofthese coding effectiveness. The major conclusion from these studies was briefings. Two proposals submitted to NASA reflect the pdmary areas that the effect of the coding film could be readily dispersed by relalJvely of common interest. They are image analysis and numerical solutions weak incident shocks, so the peak heating in the recompression region of partial differantal equations arising in computational fluid dynamics was not significantly reduced by even the largest levels of film cooling. and smJcturel mechanics. CASI For the case studies in the absence of film cooling, the interaction regions were unseparated. However, adding film cooling resulted in regions of boundary h_er separation induced in the film cooling layer, the size of which regions first increased and than decreased wfh N94-34948"# National Aeronautk:s and Space Administration. Ames increased film cooling. Surprisingly, the size of lhe separated regions Research Center, Moffett Reid, CA. and the magnitude of the reconlpresslon haaUng were not slmngly AN EXAMINATION OF THE AERODYNAMIC MOMENT ON influenced by the thickness of the cooling flm, nor by the point of shock ROTOR BLADE TIPS USING FLIGHT TEST DATA AND impingement relative to _ exit plane of the nozzles. The lip thickness ANALYSIS was found to have litUeeffect on cooling effectiveness. Measurements THOMASH. MAIER and WILLIAM G, BOUSMAN 0ct. 1993 20p wi_ and in the absence of shock interaction were compared with the See also A94-12064 results of eadler expadmentel studies and cormlatsd in terms of the (Contract RTOP 505-59-52) mNor parameters conVolling these flows. Aulhor (NASA-TM-104006; A-93047; NAS 1.15:104006; USAATCOM-TR-92- A-014) Avail: CASI HC A03/MF A01 The aneJysis CAMRAD/JA ts used to model two aircraft, a Puma with a swept-tip blade and a UH-60A Black Hawk. The accurecY of the N94-34965"# Calspan-State Univ. of New York Joint Venture, analysis in predicting the torsion loads is assessed by comparing _e Buffalo, NY. Research Center. predicted loads with measurements from flight tests. The influence of EXPERIMENTAL STUDIES OF TRANSPIRATION COOLING essu_ in the analytic_ modet is examined by verying model WITH SHOCK INTERACTION IN HYPERSONIC FLOW, PART B parameters and comparing the predicted results to baseline values for Final Report the torsion loads. Right test dsta from a research Puma are used to MICHAEL S. HOLDEN May 1994 267 p identify the soume of torsion loads. These data indicate that the (Conlract NAG1-790) aerodyTwnlc sectk_n momant in tha re,on of 1he Uede _ do_nstes (NASA-CR-195958; NAS 1.,-°6:195958) Avail: CASl HC A12/MF A03 torsion loading in high-speed flight. Both the aerodynamic esc_on This report describes the result of experimental studies con- moment st the blade tip and _ I_:h-link loads am characterized by ducted to examine the effec_ of the impingement of an oblique shock _ge poCeve (nine-up) moments in the first quadrant v_h rind on 1ha fowlk_d and surface charactefisl_ of a Uanspiretion-cooled reversal of Ioed so that the momant Is negstJveinlha se(xxxJ quedmnt. wallin tud3ulenthypaalonic fli:)w. The prlndpal objsotlve of Ibis work wes Both the character and magnitude of this loading am missed by to dsterrnine whether the interactlon betwean tha obllque shock and the CAMRAD/JA analysis. Author low-momentum region of the transpi_-cooled boundary layer cre- sted a highly dletorted flow_eld and resulted in a signlfcant reductlon in the cooling effectiveness of the _znspim'don-cooled surface. As a N94-34964"# Calspan-Stste Univ. of New York Joint Venture, part of this program, we also sought to determine the effectivenees of Buffalo, NY. Research Center. banspiratlon coding with ni_ and helium injectante for a wide EXPERIMENTAL STUDIES OF SHOCK-WAVE/WALL-JET range of blowing retes under cort_mnt-I:.'oesure cond_ions in the INTERACTION IN HYPERSONIC FLOW, PART A Final absence of shock interaclon. This _ program was con- Report ducted In the Calspan 48-1nch Shock Tunnel st nominel Mach numbem MICHAEL S. HOLDEN and KATHLEEN RODRIGUEZ May 1994 of 6and 8, fora Reynolds number of 7.5 x 10(exp 6). For these test 226 p conditions, we ob_ned fully turbulant bnundary _/em upstream of the (Contract NAG1-790) interac'd_ regions over _e Inmsplrstlon-coolad segment of _ fiat (NASA-CR-195957; NAS 1.26:195957) Avail: CASI HC A11/MF A03 plate. The expadmantel program was conducted in two phases. In the Expedmantal studies have been conducted to examine slot film fimt phese, we examined tha effecls of _ition lavel and coolard cooling effectNaness and the interaction between the cooling film and properties on the cooling effectiveness of tnmspimtion-cook_ surfaces an incident planar shock wave in turbulent hypersun/¢ /tow. The inthe abesn_ of siv)ck Intersotion. Inthe second phese of 1heprogram, expadmanteJ studies were _ in 1ha 484nch shock tunnel st we exanmed tha effects of obUqua shock impingemant on the fowfield Calspan st a fmestmam Msch ntxnber of close to 6.4 and st a Reynolds and sudace chamctedslice of a Vansptralk)n-cooled surface. The nurnber of 35 x 10(exp 6) besed on 1he length of tha rnodel st lha imxllas were corKlucted fora range of shock strengths wfh nitrogen and helium coolants to exandne how the distribution of heat transfer and injec_on point. The Mach 2.3 planar wall jet was generated from 40 transverse nozzJes (with h_ghte of both 0.O8O kch and 0.120 inch), preesure 8rid the chw'actmtstk:s of the _ inU'_einterec*donregion producing a flim thst extended the full width of 1ha model. Tha nozzlas varied with shock strength and the level of mass addiUon fTorn the were operated st pressures and _ clcee to matching transpired section of "d'mmodel. The effecte of b"mdistribution freestresm, es well es st _ where the nozzle flows were over- of the blowing rate along the interaclion regions were aleo exarrdned for and under-expanded. A two-dimenslonal shock generator was used to a renge ofblo_ng rstes glrough lhe tmn__ panels. The generste oUk_ua shocks thst defiacted the flow through tot= tuminge regions of shodomzv_Ix_mdand layer interaction examined in of 11,16, and21 degrees; the flows impinged downstream of the nozzla studies were induced by oblique shocks generated with a sharp, fiat e.dte. Detailed measurements of heat transfer and pressure were made plate, inclined to the freestmam at angles of 5 degrees, 7.5 degrees, both aheed and downstream of 1he injection stetlon, wl_ the grmmm and 10 degrmm. Itwes found lhak In 1tinabmnce of an inoldent shock, concentration of measurements in the regtone of shock-wa_- transpirstloncoolingwes a yew effec'_ivemelhod forreducingboththe heat Irensferand the sidnfrictionloads on the surface.The helium ary layer Interaction. The _ objectives of Ihese expadmontel studies were to explore the effsoUvaness of flim cooling inthe presance coolant was found to be slgnircangy more effective than nltmgan, because of itelow molaoular weight and high specif¢ haat. The studies of reglons of shock-waveboundary layer inte_ and, morn sPedf" c_h/, to determine how boundary layer separst_n and the kuge of shock-wave/tmnsplrefon-coolad surface Interactk_ demonstrated reco_ heating rotes were modified by film cooling. Detailed b'_ztthe irM_ region between the incident shock and the low- disffibutione ofhest transfer and pressure were obteined intha inck:lent- momentum Ixanspim_ion-cooled boundary layer did not result in a shock/wafl-jst intemctlon region for a sefles of shod( strengths and significant increase in the sizeof attachedor separated interac_on impingement positions for each of the two nozzle heights. Measure- regions, and did not result in significant flow_eld distortions above the ments were also made to examine the effects of nozzle lipthldmees on Interaction region. The increase in heating downstream of the shock- 523 02 AERODYNAMICS impingementpointcouldeasilybereduced to the values without shock layer, the vorlJcitylumps into • vortex and protrudes into the Invledd impingement by a relatively small increase in the transpiration cooling region. This process initiates the separation process. The response of inthis region. Surpdsingly, this increase in cooling rate did not result in airfoils in unsteady free sVeam was investigated based on this vortex a significant increase in size of the region ahead of the incident shock generation and convection concept. This approach enabled us to or create a significantly enlarged interaction region wi_ • resultant understand the complicated unsteady aerodyr_mics from a fundamen- increase in the distortion level in the Invlectd flow. Thus, Vanaplre_on tel point of view. Author cooling appears to be a very effecWe technique to cool the Internal surfaces of scmmjat engines, where shocks Inthe engine would induce N94-34971"# Lehigh Univ., Bethlehem, PA. large local increases In wall heating and create viscous/invledd Inter- CONTROL OF LEADING-EDGE VORTICES ON A DELTA WING actions that couJd signlfican_ disturb the smooth flow through the C. MAGNESS, O. ROBINSON, and D. ROCKWELL In NASA. combustor. However, If hydrogen is used as the coolant, burning Ames Research Center, Physics of Forced Unsteady Separation ups_eam of shock Impingement might result in localized hot spots. p 79-100 Mar. 1992 Sponsored by AFOSR Clearly, further research Is needed in this area. Author Avail: CASI HC A03/MF A03 The unsteady flow stricture of laeding-edga vol_ces on e delta N94-34967"# United Technologies Corp., East Hartford, CT. wing has bean investigated using new types of experimental tech- UNSTEADY SEPARATION EXPERIMENTS ON 2-D AIRFOILS, nk:lueS,in order to provide Insight into _ consequences of vadous 3-D WINGS, AND MODEL HELICOPTER ROTORS forms of active control. These investigations involve global control of PETER F. LORBER and FRANKLIN O. CARTA In NASA. Ames the entire wing and local control applied at crucial _ on or Research Center, Physics of Forced Unsteady Separation p 1-22 adjacent to the wing. Transient control having long and short time- Mar. 1992 scales, rala_'e to _ convective time-ecala C,/U(sub Infinity), allows Avail: CASI HC A03/MF A03 sul_tential _ of the unsteady and t_'mH_ean 1towstmcture. Global conVoJat long time-scale involves pitching the wing at rates an I_ on unsteady separalk_ end dynamic stall is balng obtained from two expadmental programs that have been underway at order of magnitude lower than the _ time-scale C/U(sub United Technologies Research Center since 1984. The firstprogram is Inr_y), but at large amplitudes. The functional form of the pitching designed to obtain detailed sudace pressure and boundary layer maneuver exerts a predominant influence on the tr_ of condition tnforma_on dudng high amplitude pitching oecUlalions of • feedingmwt, the Instentaneousver_:_ dst_b.t_, andthe_an- tenanus ioce_on of vortex Ixeal(down. Global control at short time- large (17.3 In.chord) model wing In a wind tunnel. The second Wogrem Involves the consthJction and testing of e pressure-i_ modal scales of the order of the Inherent frequency of the shear layer helicopter rotor. This pmsanmtion describes some of the results of sapmating from the laading-edga and _ natureJfrequency of vortex experiments, and in particular compares the detailed breakdown shows that 'resonant' response of the excited shear layer- stall inception information obtained from the cedltetlng wing with the vodex breakdown system is attainable. The spectral content of the unsteady separation and reverse flow results measured on the retrea- Induced dlaturbance is preserved not only ecroea the entlre corn of the ting blade side of the model rotor during wind tunnel testing. vortex, but also along the axle of the vortex Into the region of vortex Derived from text breskdown. This unstesdy modification results in tinle-mean alteration of the axial and swid veiocby flalde and the location of vortex break- down. Localized controlat long and short time-scalea _vaNea applice- N94-34969"# RondaAgricultural and Mechanical Univ., Tallehaseea, tk)n of vedous trenstent forms of suction and blowing uslng small probes FL. Coll. of Engineering. upstream and downsthmm of the location of vortex breakdown, M wall UNSTEADY FLOW PAST AN AIRFOIL PITCHED AT CONSTANT es dlstdbuted suction and blowlng along the leadthg-edga of the wlng RATE appikKI In • directiontengantlal to ti'm feeding sheat. Theae local control L. LOURENCO, L. VANDOMMELEN, C. SHIB, and A. KROTHAPALLI techniques can reault In substantial alteration of the location of vortex In NASA. Ames Research Center, Physics of Forced Unsteady breakdown; In some ceses, It le possible to eccomplish Uds without nat Separation p 35-59 Mar. 1992 Sponsored by AFOSR Prepared mass addition to U'm flow field. Derived from text in cooperat_ with Fiodde State Univ., Tallahaesea Avail: CASI HC A03/MF A03 N94-34972"# lUinoisInst. of Tech., Chicago, IL. Ruid Dynamics The unsteady flow past a NACA 0012 alrloil that Is undertaldng a Research Cent_. constant-rate pitching up motion is investigated expadmantelly by the THE UNSTEADY PRESSURE RELD AND VORTICITY PIDV technique in e water towing tank. The Reynolds number is 5000, PRODUCTIION AT THE SUCTION SURFACE OF A beaed upon the alrf¢_rs chord and the frea-strearn vekx_ty. The alrfo, PITCHING AIRFOIL Is pbching imply from 0 to 30 deg. with e dimensionlese pitch rote MUKUND ACHARYA and METWALLY H. METWALLY In NASA. alpha of 0.131. Instantaneous velocity and associated vo_ data Ames Reaear_ Center, Physics of Forced Unsteady Separation have been acquired over the entire flow field. The pdmary vortex p 101-118 Mar. 1992 dorninatea the flow behavior altar itseparates from the leading edga of Avail: CASI HC A03/MF A03 the airfoil. C,(xnpiete stag emerges after this vo_lex detad'ms from the Theoqecttveof_s workistodevek)ptechnklUeaforthecontr¢_ airfoil and _ggere the shedding of a counter-ro_ vortex near the and manegemant of separated flows over alrtotis, particularly under lralUng edge. A parallel computational study using the discrete vortex, unsteady operating _. The results are expected to help random walk appro)dmaUon has also been conducted. In general, achieve the ultimate goal, which is ltow rnanagamant for highly maneu- computational results agree very well with the experiment. Author verabla aircraft. Author N94-34.qT0"# University of Southem California, Los Angeles, CA. N94-34974"# Cincinnati Univ., OH. Dept. of Aerospace Engineadng Dept. of Aerospace Engineering. and Engineering Mechanics. UNSTEADY SEPARATION PROCESS AND VORTICITY CHARACTERIZATION OF DYNAMIC STALL PHENOMENON BALANCE ON UNSTEADY AIRFOILS USING TWO.OIMENSIONAL UNSTEADY NAVIER-$'rOKES CHIH-MING 1tO, ISMET GURSUL, CHIANG SHIH, and HANK UN EQUATIONS InNASA. Amea Reaearch Center, _ of Forced _ K.N.GHIA, U.GHIA, andG.A.OSSWN.D InNASA. AmeaReaeamh Separation p 61-77 Mar. 1992 Centar, lq_dcsofForcedUnsteadyse_ p129-147 Mar.1992 (Contract F49620-88-C-0061) (Contract AF-AFOSR-0074-87; AF-AFOSR-024,9.90) Avail: CASI HC A03/MF A03 AveJl:CASI HC A03/MF A03 Low momentum fluiderupts atthe unsteady separation regionand Among the new signifP..antaspects of the present work are: (1) the forms a local shear layer at the viscous-invtscid interface. At the shear trealment of the far-flald boundary; (2) the use of C-gdd topology, with 524 AERODYNAMICS 02 the branch-cut singularity treated analytically; (3) evalualion of would cause stall to occur in a stationary system. This result appeam effect of the envelope of prevailing Inlt)aistates, and finally;,(4) the abillty to stem from the forrnatJonof a vortex dose to the surface of the airfoil to employ streaidine/pathllne 'visualization' to probe the unsteady which continues to provide lift. It is aiso evident that the onset of features prevailing in vortex-dominated flows. The far-field boundary is dynamic stall depends strongly on the airfoil section, and as a msu_ placed at Infinity, using appropriate grid slmtching. This contributes to great care is required in_ development of a calculation method which the accuracy of the solutions, but raised a number of important issues will accumtaiy predict ff_s behavior. Author (revised) which needed to be resolved; this includes determining the equivalent JJrne-dependentdrculal_on for _e pitchingairfoil. A secondary counter* clockwise vortex erupts from withinthe boundary layer and immediately N94-34979"# Lehigh Univ., Bethlehem, PA. DepL of Mechanical pthches off the energe_c laeding-edge shear layer which then, thrnugh Engineedng and Mechanics. hydrodynamic Instability, rolls up into the dynamic stall vortex. The SOME ASPECTS OF UNSTEADY SEPARATION strealdine_line visualization serves to provide Wonnatlon for in- C.R.SMITHandJ.D.A.WALKER InNASA. Ames Research Center, sight into the I_yaics of the unsteady separated flow. Author PhyaicsofFocedUnst_dySe_ p203-208 Mar. 1992 Avail: CASI HC A02/MF A03 Unstsedy separation can be Iorced in a variety of ways and in this N94-34975°# Arizona Univ., Tucson, AZ. presentation two fundamental means will be considered: (1) the intm- COMPUTED UNSTEADY FLOWS OF AIRFOILS AT HIGH ductlon of convec_d vo,_-ular disturbances Into the flow; and (2) the INCIDENCE influence of a spec_c type of three-_mer,,sionai oeorneW. In both K.-Y. FUNG, JEFFREY CURRIER, and S. O. MAN In NASA. Ames _ a response of the viscous flow near the wail is provoked Resserch Center, Physk:s of Fomed Unsteady Sel)aralton p 149-162 wherein the fluid near the surface ehruplly tocuses into a narrow region Mar. 1992 b_at erupts horn the surface into the mainstream. In two-dimensionel Avail: CASI HC A03/MF A03 flows,lhe enJptk)nlakes _le form of a narrow, explosively-growing The flow over an airfoil at an angle of attack above the static stail rake, while in thrse-dimansionai situa_ons, examples are presented ar_e would ordinarily be rnaseivaiy separated. Under dynamic condi- which indicate that the eruplton is aiong a nerrow zone in the shape of _ns, the onset of stail can be delayed to an angla, depending on the a _nt-ehaped p_ume. The nature of the thme-di_ flow type of unsteadiness, much higher than that for _ stall. The stall near a circular cyllnder, whlch Is mounted nonnai to a flat plate, Is aiso onset mechanisms under dynamic condibons are unclear. Due to examined in this study. Hem the thrse-dimanaionai geomeW induces extreme dMk:utties involved, expedmentai investigations, so far, have complex thrse N94-349_# Am',y Aviation Systems Command, Moffett Field, CA. N94-34977"# Naval Postgraduate School, Montomy, CA. Dept. of Aeronautics and _. Aernfiigh_ma,_csD_re_m. THE QUEST FOR STALL-FREE DYNAMIC LIFT COMPUTATION OF UNSTEADY FLOWS OVER AIRFOILS C. TUNG, K. W. MCAUSTER, LAWRENCE W. CARR, E. DUQUE, and J.A. EKATERINARIS and M. F. PLA1-ZER In NASA. Ames Research R. ZINNER In NASA. Ames Research Center, Physics of Forced Canter, PbysicsofForcedUnstsedy Separation p177-185 Mar. UnsteadySeperat_np 277-29S Mar.J992 1992 Sponsured by Navai Nr Systems Command Arab: CASI HC A03/MF A03 Avail: CASI I-IC A02/MF A03 Durlng the pest decade, numerous major effects have addressed Two methods am described for caicula_ unstsedy flows over the question of how to control or alleviate dynamic stall effects on rapidly pitching airfoils. The first method Is based on an interactive hai_:x3)terrotors, but _e concrete evidance of any significant requc_on sct_me in whlch the invtsc_ flow is obtained by a pen_ method. The of the edverse ctwactedst;cs of _he dynamic stall phenomanon hes boundary layer flow is computed by an interac_ method that makes been demonsUat_. Nevertheless, it is important to remember that the use of _ Hllbert integral to coupla the solu_ons of the thviscld and conV_ of dynem_= n", _, an achmva_e go,,'. Exper_n_,_ perform_ viscous flow equatk)ns. The second method is based on the soluIDionof m the US Army Aerofllght-dynamics Director_e more than a decade the compressible Namer-Stokes equations. The solu_on of ago demonstrated that dynamic slall is notan unavoidable penalty of equat_:XlS is obtained wi_ an appmximataiy factorizednullerlcai high amplitude motion, and that airtoils can Indsed opemto dynamlc_ly algorithm, and wi_ single block or multiple grids which enai_e grid at anglas far above the _1 angle without necesserlly forming a embedding to enhance the resolution At _ now regions. In sllailvomx. These expedmants, one of them f_dudng a aiat that was eddltlon, the a.ached flow region can be computed by the numedcai designed from static aidoil consklara_ns, showed that unsteadiness solution of compressible boundary layer equabons. Unstsedy pressure di_ obtained _¢th both _ are compereq _h availehle can be a very benef¢lal factor in U_ development of hlgh-lift devlces for helicopter roto_ The expedance drawn from these early experiments expedmantoJ data. Derived from text is now being focused on a program for the alleviation of dymm_c-mail effects on be_oplsr rotors. The purpese of thla effort Is to _ N94-3497r# Caiifomla State Univ., Long Beach, CA. DepCof Aero- that rotor stsll can be controllad through an improved understanding of space Engineering. the uneteedy effecls on airfoll stolland to documant the rola of specific PREDICTION OF UNSTEADY AIRFOIL FLOWS AT LARGE means that lead to stall ailavlat[_rl in the throe dimensional unsteady ANGLES OF INCIDENCE endronmont of hailcoptsr rotors Inforward fllghL The flint concept to be TUNCER CEBECI, H. M. JANG, and H. H. CHEN In NASA. Ames addressed in _ program will be a s_atl_l airfoil. A two dimensionai Ftesearch Center, Phyaica of Forced Unstudy Seperation p 187-201 unstsedy Navier-Stokes code hes bean _ to compute the _ow Mar. 1992 around a _ airtoil. Derived from _xt Avail: CASI HC A03/MF A03 Tbe effect of the unstsedy motion of an airfoU on b stail behador is of considerable Interest to many pracUcai appications including the N94-34987"# Illinois Inst. of Tech., Chicago, IL Fluid Dynamics blades of helicopter rotors and of exlal compmsso_ and turbines. Research Caner. Expedmants wnh osdllatlng airfoils, for examp_, have shown _ the MECHANISMS OF FLOW CONTROL WITH THE UNSTEADY flow can remain a_mhed tor angles of atlac_ greator than ffxx_ewhlcfl BLEED TECHNIQUE 525 02 AERODYNAMICS D. R. WILLIAMS, M. ACHARYA, and J. BERNHARDT InNASA. Ames variety of aircraft and nonaircreft models. To support these invesUga- Research Center, Physics of Forced Unsteady Separation p 297-307 tions, a deta acquisition system has been developed that has both static Mar. 1992 and dynamic capabilities. The static data acquisition and reduction (_ F49620.86-C-0133) system is described; the hardware and software of this system me Avail: CASI HC A0,.qVMFA03 explalned. The theory and equatlons used to reduce the dsts obtained The unsteady bleed technique (a.k.a. internal acoustic forcing) in the wind tunnel are presented; the oomputer code is not induded. has bean shown to be an effective method for control of _ on Autl_r low Reynolds number aidoils, blunt-end cylinders aiigned axially with the fk_w, _k_ers aiJgned bemand_u_r to the now, and forebody geometries at high angles of attack. In many of _ese Inventions, the N94-35360# Saddla Nalional labs., Albuquerque, NM. mechanlsm for the control has been st1_buted to anhancement of the A REVIEW AND DEVELOPMENT OF CORRELATIONS FOR BASE PRESSURE AND BASE HEATING IN SUPERSONIC shear layer (Kaivin-Hairnholtz) instability bythe _ component of the forclng. However, this is not the only pouil_ rnechankcn, nor may FLOW it be the domkmnt medm_sm under some cond#lorm. In this work R Is J. PARKER LAMB (Texas Univ., Austin, "IX.) and WIllIAM L. demonstrated that st leMt two other _ for flow conlml are OBERKAMPF Nov. 1993 79p (ConVact DE-AC04-94_J.-SS000) preunt, and depending on the location and the amplitude of the forcing, these may have significant impact on the flow behavk)r. Expedmants (SAND93-0280; UC-706) Avail: CASI HC A05/MF A01 were conducted on a right.circular cyinder wi_ a aing_ unstmdy bleed A comprehonldve revlew of oxpedmenlal base _m and base Cot a_Jgnedalong the ads of the cylinder. The effects of forcing heating dam raia_d to supersonic and hypemonic tlight vehicles has fr_uancy, forclng unpatude, and aiot kx:atlon on me azlmuthai pres- been comp(etKI. Par'dcularattenlion was paid to _ree-fllght data as wail sure distdbutlon were studisd. The results suggest that,, strong vorUcai ms wind tunnel data for models _ rear sting support. Using sffiJclure forms near the unstmdy bleed slot whan the aiot locstlon is theoretlcally based corraia_on pammetem, a seriss of Internallyconsls. .p_ew. of the beondmy W/er mpmtk_ po_ The mx_ure is tent, emplrk_ pred_-Uon equaUons was developed for _anar and .nmao_, aince it _ crea_ _ ,_ unready fo_ng. The 'volt L_wmmet_ geomeUm (wedge, conee, and,_ndere). Thue equa- generates s sizeable pressure spike (C(sub p) = -3.0) In the time- Uons anoompmm Um q)eed renge |tom k_wsupereonlc to hyperson|c avemoed prmmm fletd immedimly _ of the aiot. _ addi_n flow and laminar and turbulent fombo_ boundery layers. A wide nmge tothe pressure spike, the boundew layer separation location moves of cone and wedge angles and cone blunthess ratios was included in farther downsUeam when the totting is ac_mlm:l. Delay of the separa- Ihe data ben usecl to devek_ 1he correlatiorm. The present investiga- _n is believed to be a result of enhancing the Kaivin-Helmh¢_ tion mo inclucleclprellminan/studies of the effect of angle of attack and instability. When fordng is applisd In a quisacant wtnd tunnai, a wink q)edfk_ redo of the gas. _ (revVed) low-pressure region forms near _ slot U'Bt is purely the result of the second-o_r streaming effect. Derived from toxt N94-35498"# Eioret Com., Paio Alto, CA. DEVELOPMENT AND APPLICATION OF COMPUTATIONAL N94-34g69"# Michigan Slate Univ., East Lansing, MI. AEROTHERMODYNAMICS FLOWFIELD COMPUTER CODES EFFECT OF INITIAL ACCELERATION ON THE DEVELOPMENT Final Teohnical Report, 1 Sep. 1986 - 31 Jan. 1994 OF THE FLOW FIELD OF AN AIRFOIL PITCHING AT CONSTANT ETHIRAJ VENKATAPATHY 14 Jul. 1994 124 p RATE (_ NCC2-420) M. M. KOOCHESFAHANI, V. SMII.JM4OVSKI, and T. A. BROWN In (NASA-CR-196136; NAS 1.28:196136) AveJh CASI HC A06/MF A02 NASA. Ames Research Centor, Physics of Forced _ Separa- was performedin_ area _i modeling tion p 317-332 Mar. 1992 and application of hypersonic, hlgh-enthalpy, thenno-chemical Avail: CASI HC A03/MF A03 nonequBbd,m now (Ae_cs) proUan.. A number of We present results from a series of experiments whom an airfoil _ _k_ddyn_mc (CFD) codes were dev_oped and app, ed is pltched at constant into from 0 to 60 degrees angle of _tack. Itis wail to m_m _gh amJde roc_t-p_ume, the Aeroamst R_ht _ docurmm_ that the dynam_ stJ behavkx of such an aiddi slmng_, (AI-'E), _ brae fk_wfor p_metmy probes, the aing_ _ depends on the nondtmenaionai pitch rete K = dot-alpha C/(2U(sub ramp model (SERN) connected with the National Aerospace Plane, in_nity)), where C is the chord, dot-aiphs the constant p_h raW, and hypmon_c ¢_ag devk_, hypersonk: ramp nows, b_tc range mod- U(sub h_n_y) the f_e mmm speed, in ferny, the act_ mo_ of _e e, shock _ facZ_y noz_, trar_w_ and study nows _ the air_ deem _nom_e _e,_ remp due to _he _r,_ acce_retk_ and shock tunnai facility, arc-}et flows, thermochemlcai nonequglbrlum dec_re_ perkx_ m_0wd by the demp_ of dr_ sym= and nows aro.nd slmm _ cornp_ beau, a.,_symme_ kx_zed nows respom_e charectedetlcs of the aidoU. It is posail_le ewt me pitch rm of k_tmst to re-envy, unsmdy m_ck induced cormus,o_ ph_nom- alone may not suffice in de_:dbing the now and thst the derails of _e en_ h_ _py pu_d fac_y ¢rn_, and unready m_ck motion _ belore achieving a deaired constant pitch r_e may boundery layer _ in shock '_x,_is. Computational mod_ing aiso affect ll'm processes involved in the dyrmmic stail phenonmrmn. Involved developing sppropdete numedcai schemes for the flows on The effects of accaierdon and deceleration periods are inve_atod by Interest and developing, applying, and vaiid=t]ng appropriate thermo- symrr_.a,y va_ng the accaierdo_ m=w_tude and _= dur_on _ _. As i_ut of improving the _ccur_cy of the numedcai through the li accaieri:n phase to constant pitch reto. The predictions, adaptive odd algorithms were explored, and a user- magnitude and duratk_ of decelemtk_ needed to bdng the airfoil f,_edd_,_f-K_oeveo_e (S_GE)w= _. Amtt_mmdy_w_ motion to rest is aimllady controlled. Dedved from lex_ fk_wsof interest included anergy tmrmfer ckjeto etrong redlation, and a • _n_mt _ of effort wm _o_nt _ _ compu_kx_ codes for caiculallng redkdlon and redlat_on modeling. In addison, computa- N94.35246"# NatlonaJ Aeronautlcs and Space Administration. tlonai tools were developed and 8pplted to predict the redlative heat flux Lang_y Research Center, Hampton, VA. and spectra I_t reach the model surface. Aul_r LANGLEY 14- BY 22-FOOT SUBSONIC TUNNEL TEST ENGINEER'8 DATA ACQUISITION AND REDUCTION MANUAL N94-35529 Lehigh Univ., Bethlehem, PA. Dept. of Mechanical Engi- P. FRANK QUINTO and NETrlE M. ORIE Jun. 1994 63 p nwthg an_ _. (Comract FrTOP S35-03-10-02) UNSTEADY STRUCTURE OF LEADING-EDGE VORTICES ON (NASA-TM-4,563; L-17263; NAS 1.15:4563) Avail: CASI HC A04/MF A DELTA WING FInal Report, 1 Nov. 1990 - 31 Oct. 1992 A01 DONALD O. ROCKWEll 22Mar.1994 8p IJmitKiReproducibli_. The Langley 14- by 22-Foot Subsonic TunneHs used to test a large More than 20% of INs document may be affected by microfiche quality 526 AERODYNAMICS 02 (ContractAF-AFOSR-0005-91) Center, Second Intemstional Symposium on Magnetic Suspension (ADoA,?.78988;AFOSR-94-0269TR)Avail:IssuingActivity(Defense Technology, Part 1 p 291-305 May 1994 TechnicalInformationCenter(DTIC)) Avail: CASI HC A03/MF A04 Theoverallobjectiveofthismssarchprogramwastocharacterize Models featuring the simulation of exhaust jets were developed for theunsteadyflowstructureonwingshavingsweptedges.Wingswere magnetic levitation in a wind tunnel. The exhaust gas was stored subjectedtoglobalcontrol, involving motion of the entire wing and local internally producing a discharge of sufficient duration to allow nominal control, involving perturbations at specified locations on the surface of steady state to be reached. The gas was stored in the form of the wing. New types of experimental facilities and image acquisition and compressed gas or a solid rocket propellant. Testing was performed processing techniques have allowed determination of the instenta- with the levitated models although deficiencies prevented the detection neous vorticity distributions and streamline patterns of the flow. The of jet-induced aerodynamic effects. DifficulUas with date reduc'don led occurrence of vortex breakdown and stall and their phase shiftsmlatlve to the development of a new force calibral_n technique, used in to the wing motion and to control at the leading-edges have been conj_ with an exhaust simulator and also In separate high interpreted in terms of new flow mechanisms. DTIC inddence aerodynamic tests. Author N94-35717 Stanford Univ., CA. Dept. of Aeronautics and N94-35864"# California Univ., San Diego, La Jolla, CA. Dept. of AstroneuUcs. Applied Mechanics and Engineering Sdences. INVESTIGATION OF BURNETT EQUATIONS FOR TWO- ON THE VARIOUS FORMS OF THE ENERGY EQUATION FOR DIMENSIONAL HYPERSONIC FLOW Final Report, 1 Nov. A DILUTE, MONATOMIC MIXTURE OF NONREACTING GASES 1992 - 31 Oct. 1993 Final Report DEAN R. CHAPMAN and ROBERTW. MACCORMACK Apr. 1994 16 CHRISTOPHER A. KENNEDY Jui. 1994 19 p p Limited Reproducibility:. More than 20% of this document may be (Contract NAG1-1193; RTOP 505-59-50-05) affected by microfiche quality (NASA-CR-4612; NAS 1.26:4612) Avail: CASI HC A03/MF A01 (Contract F49620-92-J-0012) In _e case of gas mixtures, the governing equations become (AD-A278942; AFOSR-94-0278TR) Avail: Issuing Activity (Defense rathar fornddabie and a complete listingof the equations intheir various Technical information Center (DTIC)) forms and ms_wxls to evaluate the tnmsport coefficients is difficult to Two separate areas of invastigatbon are explored of two dimen- find. This paper seeks to compile common, as well as less well known, sional flow fields computed from the Burnett and Nevler-Stokes equa- results in a single document. Various ralatJonships between equations tions: evaluation of variousforms of Bumett equations from computetions describing conservation of energy for a dilute, monatornlc, nonmacling of one dimensional hypersonic shock stndCtumand two dimensional gas in local equilibrium are provided. The gas is treated as nonmletiv- flow over a flat plate at zero Incidence, and Invention of the istic, not subject to magnetic or electric fields, or racllative affects. Author inte_ at high altitudes of a hypersonic oblique si'mck impinging on a cowl lip. Among five different formulations of Bumett equations, two were found to exhibit in shock stnJcturea small region of flow wherein N94-35950 Ohio State Univ., Columbus. Dept. of Mechanical the heat flux is physically unreal. Preliminary computations with the Engineering. three other formulations are made for flow over a flat plate. It is found EXPANSION EFFECTS ON SUPERSONIC TURBULENT that the well-known ssvem overhea'dng, due to oblique shock impinge- BOUNDARY LAYERS Final Report, 1 Sep. 1991 - 31 Dec. 1993 ment on a leading edge, decreases sigoificantly as altitude increases STEPHEN A. ARNETTE, MO SAMIMY, and GREGORY S. ELLIOTT disappearing at Knudsen numbers above about 0.1. DTIC Feb. 1994 190p _ Repro(k¢tbitity:. Mom than 20% of this document may be affeclad by microfiche quality N9#35825 Naval Postgraduate School, Monterey, CA. Dept. of (Contract AF-AFOSR-0412-91) Mechanical Engineadng. (AD-A278989; MEMS-94-101; AFOSR-94-0"'o:_'rR) Avail: Issuing DATA REDUCTION, ANALYSIS AND RESULTS OF LACV-30- Ac_ (Defense Technical Informa_ Center (DTIC)) 07 AIR CUSHION VEHICLE TESTS, FORT STORY, VA, The affects of various expansion regions on the large scale AUGUST - SEPTEMBER 1993 structure of a Math 3 fully.deveiol_d-turbulent boundary layer am YOUNG S. SHIN and ERIC HOY Feb. 1994 521 p Limited investigated. Five cases am studied: 7 deg and 14 deg centered Reproducibility:. More than 20% of this document may be affected by expsnskx_, 7 cisg 8nd 14 deg gradual expsnsions, and the flat plate. microfiche quality Multi-goint surface pressure measurements, filtered Flayteigh scatter- (AD-A278859; NPS-ME-94-002) Avail: Issuing Activity (Defense _g v_J_.aUons,anddoub_-p_ssv_suaJ_donswere er_oyed. Technical InfommtJon Center (DTIC)) Plan view images of the fiat plate boundary layer reveal the presence The LACV-30-07 Air Cushion Vehicle was instnJmented and of stn,cturas of a very largo _, and llmlted apanwlse, extent. tested at Fort Story, VA dudng the months of Auguat-Septembar 1993 These stnJctums were found well above the inner layer, nominally at n/ by Ed. Thomas, NSWC-Cardrock Division, Annapolis Detachment, delta = 0.5-1.0. The stnJctures were also found in _e expanded Annapolis, MD. The tests include 27 cuts with vehicle speed ranging boundary_/en,. Ac_s the _, the k.m ecale s_x:turasofthe from 0 to 42 knots and approximate wave height of 0 to 2.5 feet. Two outer leyer un_ an _ in ecale and structure 8ng6e.The small trlaxial eccalerometers, and a pitch and rolltmneducar were installedto scale turbulent motions of the incoming boundary layer are quenched measure axial, transverse and vertical eccelarations and pitch and roll by the expansion, while b_mlarge scale Slmucturas respond more (in degree) of the vehicle. The test results clearly show that the vibration gradually. Convection velocttk_ from the pressure corralations are g-ampiitude is extremely low (fraction of 1-g level) for air cushion vehicle reasonable in the incoming boundary leyar, but unreasonably high in and air ouehion vehicle iteelf is acting as a super-dampar to reduce the the expanded boundary layers. Convection velocities from corralations wave-induced vibration response an_itude. The vibration amplitude in of deuble-pmm images appear reasoneb_. The discrepancy between terms of g-leval may not be the controlling factor, but the combined the two results suggests the rete_or_'dp between I_ large scale vehicle dominant freduoncias, vibration g-level, and duration may be st;ucturas and the convecUng pressure field is severely altered by the definite factors that the superconductor msgnet must persist. exl_ DTIC DTIC N94-35965"# Nationel Aeronautics arid Space Admlrdstmtlon. Ames N94-8585S*# Southampton Univ. (England). Research Center, Moffett Reid, CA. THE SIMULATION OF A PROPULSIVE JET AND FORCE WIND TUNNEL MEASUREMENTS ON A FULL-SCALE FIA-18 MEASUREMENT USING A MAGNETICALLY SUSPENDED WITH A TANGENTIALLY BLOWING SLOT WIND TUNNEL MODEL WENDY R. LANSER In its1993 Techrdcal PaperContastforWomon. K. S. GARBUT'r and M. J. GOODYER In NASA. Langley Research Gear Up 2000: Women in Motion p 27-36 Feb. 1994 527 02 AERODYNAMICS Avail: CASI HC A02/MF A02 03 A full-scaie FIA-18 was tested inthe 80 by 120-Foot 'WindTunnel AIR TRANSPORTATION AND SAFETY at NASA Ames Research Center to measure the effectiveness of a tangentially blowing slot in generating significant yawing moments Includes passenger and cargo air transport operations; and aimraft while minimizing coupling in the pitch end roll axes. Various slot accidents. conliguretJonswere tested to determine the optimum configuration. The test was conducted for engles of atteck from 25 to 50 dog, englas of sideslip from -15 to +15 deg, and freestream velocities from 67 rdsec to 168 ft/sec. By altedng the forebody vortex f,ow, yaw control was N94-34915"# Western Aerospace Labs., Inc., Monte Serene, CA. mainteJned for angles of atteck up to 50 dog. Of particular interest was EFFECTS OF CHECKLIST INTERFACE ON NON-VERBAL the result that blowing very close to the radome apex was not as CREW COMMUNICATIONS effective as blowing siightiy farther aft on the redome, that a 16-inch slot LEON D. SEGAL May 1994 95 p was more efficient, and that yawing moments ware generated without (Contract NCC2-486) inducing significant roiling or pitching moments. Author (NASA-CR-177639; A-94079; NAS 1.26:1 77639) Avail: CASI HC A05/ MF A01 The investiga_on looked at the effects of the spatiai layout and funclkx,dity of cockpit displays and controls on crew communlcatkm. S_ly, the study focused on the inVa-codq_ crew interaction, and N94-35g@1"# Eidatics I_, Inc., Tonance, CA. subsequent task pedormance, of aJdinepilots flying different configu- FIA-18 FOREBODY VORTEX CONTROL. VOLUME 1: STATIC rattons of a new electronic checklist, designed and tested in a high- TESTS simulator at NASA Ames Research Center. The flint part of this BRIAN R. KRAMER, CARLOS J. SUAREZ, GERALD N. MALCOLM, proposal establishes the theoretical background for the assumptions and BERT F. AYERS Mar. 1994 183 p undedylng the research, suggesUngthat in the context of the interaction (Contract NAS2-13383) between • mulU-opemtor crew and a machine, the design and configu- (NASA-CR-4582; A-94056; NAS 1.26:4582) Avail: CASI HC A09/MF ration of the interface will affoct intoract_ between indh(iduai opera- A02 tom and the machine, and subsequen_j, the lnteractk_ between A wind tunnel test was conducted On a aix percent modai of the operators. In view of the latest trends in cockpit Interface design and F/A-18 at the NASA Areas 7 X 10-Foot Low Spesd Wind Tunnai. The Nght.desk technolow, in particular, the cantralizalkm of displays and pdmary objective of tho test was to evaJuato severai forebody vortex controls, the inUoductk_ identffias certain problems associated with control configurations at high angles of atlack in order to datermtne the these modem designe end _ete epactflcdeaign I_._ to which the most e_ method of obtaining well behaved yawing moments, in expected results could be 8ppllad. A detailed research program 8nd preparation for the mtery baiance test. Both menhenlo_ end pneun_tic msthodek_y is ou'dined end the results are described end discuesed. systems worn tested. Single and dual _ nose tip strakJm and a Overall, differences in cockl_ design ware shown to Impact theeacth_ vertical noee strake were teated at different aizes and delkctlons. A wilhin the cockpit, includinginterac'donsbetween pilots and aircraft and series of jet blowing conflguralons ware located at various fuselage the (x)opemtlve intemc-llor_ between pilots. Author stevens, azimuth angles, and pofr_ng angles ranging from straight aft to 60 deg cented Inboa¢l. Slot blowing was inves_igatKI lot several slot lenglhs and fusaioge stations. The effect of blowing rate was tested for both of _,se pneuma_ _. The moat effective conlguretions N94-34991# NatlonelTmns_SafatyBoard, Washington, DC. ware then further tested with a variation of both _dedp _ and O_ca of Research and Englneedng. Reynok:ls number ove¢ e range of aries of atteck from 0 to 60 dog. It ANNUAL REVIEW OF AIRCRAFT ACCIDENT DATA: US GENERAL AVIATION CALENDAR YEAR 1991 was found that a very robust system can be developad that provides yawing moments at angles of attack up to 60 dog that aignific_ 4 Apr. 1994 84 p exceeds that available from 30 dog of RRk_r delkction (F/A-18 (PB94-127982; NTSB/ARG-94/01) AvelI: CASI HC A05R41FA01 rne)dmcrn) at 0 dog angle of attack. Author This mpo,lpmsents a statisticalcompUatlonend review of generai aviation accidents which occurred in 1991 Jn the UnitKI States, its terrbodes and possessions, 8nd in interrBtional waters. The accidents reported 8re aJlthose invoMng U.S. registered aircraft not conducing operelloneunder 14 CFR 121,14 CFR 125,14 CFR 127, or 14 CFR 135. This ropod Jsdivided into five esctlons: all accidents, fatal accidents, N94-35994"# Institute for Computer Applications in Science and sedous injury accklants, property damage escidents, 8nd nddalr colli- Er_nee_ng, Hampton, VA. sion 8ccldents. Several tebles present scck:lent parameters for 1991 A THREE DIMENSIONAL MULTIGRID REYNOLDS-AVERAGED accidents only, and each secllon includes tabulations which present NAVIER-STOKES SOLVER FOR UNSTRUCTURED MESHES ccrnparative _ for 1991 end for the five-year padod 1986-1990. Final Report Author (r_sed) D. J. MAVRIPLIS May 1994 28 p Submitted for publication (Cordmct NAS1-19480; RTOP 505-90-52-01) (NASA-CR-194908; NAS 1.26:194908; ICASE-94-29) Avail: CASI HC A03/MF A01 N94-3S236# Federal AVmtion Administration, Oklahoma City, OK. Alhme-_cP._ _ rne_ Reynok_ Mrapd Navk_- Aeromedicai Inst. Stokes sofver la described. Turbulence la simulated using a single §aid- A REVIEW OF COMPUTER EVACUATION MODELS AND THEIR oquatlon model. Computational ovodload8 are minimized through the DATA NEEDS Final Report use of a single _ date-stricture, and efl_kmt muItlgdd JEFFREY H. MARCUS May 1994 14 p solulon technique, end the use of multl-tesklng On shared memory (DOT/FANAM-94/11) Avail: CASI HC A03/MF A01 mulU-procassors. The accuracy and _ of the code are evaiu- Thls document reviews the history end currant status of computer ated by computing two-di_ 11owsIn three dlmenalons end models of the evacuation of en aidlner cabin. Basle concepts upon comparing with results from a previoue_ velldated two-dlmemlonai which evscuatk_ models 8re based 8re discussed, followed by a code which emp_ the same s_u_n aigorUhm. The fe_bUhy of revlew of the Civil Aeromedlcai Ins_itute'sefforts dudng the 1970's. A computing three-dimensional flows on grk:Isof several mi,lon points in comparison is made of the three models available today (GA Model, less ff_m two hours of wsll clock time is demonstrated. Author AIREVAC, 8nd EXODUS). The report then reviews parameters com- 528 AIR TRANSPORTATION AND SAFETY 03 montoellmodels,anddiscussesliteratureavailableasabasisforthese ing these issues were made to the Federel Aviation Administration, parameters.Finally,thereportbdeflydiscussesvalidationexercisesfor American International Airways, Inc., and the Department of Defense. evacuation models. Author Author N94-35522"# North Caroiina State Univ., Raleigh, NC. Dept. of Marine, N94-35482# Na_onelTransporlation Safety Board, Washington, DC. Earth and Atmospheric Sciences. SAFETY STUDY: A REVIEW OF FLIGHTCREW-INVOLVED, NUMERICAL MODELING STUDIES OF WAKE VORTEX MAJOR ACCIDENTS OF US AIR CARRIERS, 1978 THROUGH TRANSPORT AND EVOLUTION WITHIN THE PLANETARY 1990 BOUNDARY LAYER Semlennu=l Report, FY 1994 Jan. 1994 105p YUH-LANG LIN, S. PAL ARYA, and MICHAEL L. KAPLAN 1994 (PB94-917001; NTSB/SS-94/01) Avail: CASI HC A06/MF A02 17p U.S. air carder operations are extremely safe, and ti'm accident (Contract NCC1-188) rate has declined in recent yearn. However, among the wide array of (NASA-CR-196078; NAS 1.26:196078) Avail: CASI HC A03/MF A01 factors cited by the National Transportation Safety Board as causal or The proposed research involves four tasks. The first of these is conffibuting to airplane accidents, aclk_s or inaclfons bythe flightcrew to simulate accumtoly the turbulent processes in the atmospheric have been cited inthe majority offatal air carrier accidents. Recognizing boundary layer. TASS was odginelly developed to study rnaso-gamme that deficiencies in various aspects of the aviation system may ed- scafe phenomena, such as tomadic storms, microbursts and windshear versaly influence flight crew pedonnarce, the safety board conducted effects in terminal areas. Simulation of wake vortex evolution, however, this study to learn rnom about flight crew performance by evaluating will rely on eppropdate mpmsantat_n of the physical processes in the characteristics of _ operating environments, crew members, and surface layer and mixed layer. This involves two parts. First, a specified errors made in major accidents of U.S. air carriers between 1978 and heat flux boundary cond_on must be implemented at the surface. Using 1990 in which _ flight crew was cited bythe board. Charactedstics of this boundary condition, simutatfon results will be compared to experi- the operating environments and flight crews were k:lan_ed from mantal data and to oltmr model results for velidation. At this point, any information derived from major i_tions of 36 accidents and 1 necessary changes to the model will be implemented. Next, a surface incident (for convenience, referred to as an accident). The errors energy budget pararneteriza_on will be added to the model. This will identified inthe accidents were eveluated inlightof the contexts inwid(_ enable calculation of the surface fluxes by accounting for the radiative they occurred. The safety board aggregated the infom_tion examined heat Vansfer to and from the ground and heat loss to the suil rather than in this study from its records of indivk:lual accident InvestJga_. simple specification of the fluxes. The second task involves running Although the data were not analyzed for the pu_ of determining TASS with prescdbed wake vortices In the inlUal (x>ndition.The vortex bends overtime, the board did identify patterns Inthe clatL Inevaluating models willbe supplied by NASA Langley Research Center. SensilMty the results of the study, the boa_ recognized that major accidents are tests will be performed on different mateorotogicel environments in the ram events and that flightcrew parfommnce dudng accidents is subject atmospheric boundary layer, which include stable, neutnd, and un- to the simultaneous influences of many operationel context variables. stabfe stxatiflcaltons, calm and severn wind conditions, and dry and wet Results of this study need to be viewed from this perspedve. condiUons. Vortex strength may be varied as well. Relevant non- Author (revised) dimensional pemmaters will include the folk)wing: Richardson number or Froude _r, Bowen ratio, and height to length scale ratios. The modal output will be analyzed and vlsuelized to better understand the N94-35496# NationelTrensportationSafetyBomd, Washlngton, IX;. tnmspo_, decay, and growth rates of the wake vorticas. The third task Office of Research and Engineering. involves running simulations using observed data. MIT Lincoln Labs is ANNUAL REVIEW OF AIRCRAFT ACCIDENT DATA. US currently planning field experiments at the Memphis elqoort to measure GENERAL AVIATION, CALENDAR YEAR 1992 both meteorological conditions and wake vortex characteristics. Once 15 Jun. 1994 85 p this data becomes available, it can be used to validate the model for (PB94-181054; NTSB/ARG.94/02) Avail: CASI HC A05/MF A01 vortex behavior under different atmospheric conditions. The fourth task This report presents a statistical compilation and review of general will be to simulate the wake in • more realistic environment covering e aviation accidents which occurred in 1992 In the United States, its wider area. Ttds will Involve grid nesting, since high rasoiu_on will be territories and possessions, and in international waters. The accidents required inthe wake region but a larger total domain will be used. During reported are ell those involving U.S. registered elmmft not conducting the firstallocation year, most of the first task will be accomplished. operations under 14 CFR 121, 14CFR 127, or 14 CFR 135. This report Dedved from text is divided into five seclJons: All Accidents; Fatal Accidents: Serious Ir_ury Accidents; Property Damage Accidents; and Midair Collision N94-36048"# National Aeronautics and Space Administration. Accidents. Several rabies present accident parameters for 1992 acci- Leng_yResearchCamtsr,Hampton,V_ dents only, and each sac_n includes tabulations which presam FINAL-APPROACH SPACING AIDS (FASA) EVALUATION FOR comparative statistics for 1992 and for the five-ysar period 1987-1991. TERMINAL-AREA, TIME-BASED AIR TRAFFIC CONTROL Author LEONARD CREDEUR, WIll IAi_l R. CAPRON, GAI::W W. LOHR, DANIEL J. CRAWFORD, DERSHUEN A. TANG, and WIllIAM G. RODGERS, JR. Dec. 1993 193 p N94-35521# NationelTmnsportation safety Board, Washington, DC. (Contract RTOP 505-64-13-01) AIRCRAFT ACCIDENT REPORT: UNCONTROLLED COLLISION (NASA-TP-3399; L-17260; NAS 1.60:3399) Avail: CASI HC A09/MF WITH TERRAIN, AMERICAN INTERNATIONAL AIRWAYS A03 FLIGHT 808, DOUGLAS DC-8-61, N814CK, US NAVAL AIR A jointly funded (NASA/FAA) real-time simulation study was STATION, GUANTANAMO BAY, CUBA, 18 AUGUST 1993 conducted at NASA Langley Research Center to gather comparative 1994 148 p performance data among _ candidate final-approach spacing aid (PB94-910406; NTSB/AAR-94/04) Avail: CASI HC A07/MF A02 (FASA) display formats. Several objective measures of controller This repo_ explains the crash of American International Airways perfomumca and their display eye-scan behevtor sa well as subjective FUght808, a DC-8-61, about 1/4 mile from the approsch end of nJnwaY workload and rating questionnaires were used. For each of two 10 at Leeward Point Airfield, U.S. Navel Air Station, Guantanamo Bay, mprasentatlve pattern-speed procedures (a 170-1o_ procedure and • Cuba, on August 18, 1993. The safety issues discussed in Ihe report 210-knot procaclum _ speed control aiding), data were gathered, via include flightcmw scheduling, the effects of fatigue on flightcrew twelve FAA controllers, using four final-controller display format condi- performance, training on special airports, and the dissemination of tions (manuel/ARTS 3, graphic marker, DICE countdown, and canterline information about special airports. Safety recommendations concern- slot marker). Measured runway separstJons were more precise with 529 03 AIR TRANSPORTATION AND SAFETY both the graphic marker and DICE countdown formats than with the A94-60211 cerndine slot marker and both (graphic and DICE) Improved precision TACTICAL COCKPITS: THE COMING REVOLUTION relative to the manual/ARTS 3 formal For three separate ratingcnteda, EUGENE C. ADAM McDonnell Aircraft, SL Louis, MO IEEE the subject controllers ranked the FASA formats in the same order:. Aerospace and Electronic Systems Maga_ne(ISSN 0885-8985) voLg, graphic marker, DICE countdown, and cantedine slot marker. The no. 3 March 1994 p. 20.26 increased precision measured with the 210-knot pattern-speed price; (BTN-94-EIX94331335530) Copyright (Jure may Indicate the potential for the apl_ICStlon of spaed-conJml A cockp4trevolution is in the maidng. Many of the much bally- aiding where higher pattern speeds are p_ after the bese-to-final hooed, much promised, but littledeliveredtechnologiesofthe70's and turn. Also presented are key FASA issues, a mtionaJe for the formats 80's will finally come of age in the 90's just in _ms to complement the selected for testing, and their dascdption. Author data explosion coming from sensor and processing advances. Tech- nolog_ such as h_met system, _ fiat panel dtsr_Ys, speech recognition, color graphics, decision aiding, and stereopsis are simul- N94-36184 Air Force Inst. ofTech., Wdght-PattersonAFB, OH. School taneously reaching technology maturities _ promise big payoffs for _rd gqnn_,or_ cockpit and beyond. The nrst ganera_on cocP,p_t of Engineering. AN ANALYSIS OF OPERATIONAL SUITABILITY FOR TEST used round dials to help _ plfot keep the aiq_me flying right elde up. AND EVALUATION OF HIGHLY RELIABLE SYSTEMS M.S. The second ganemtion cockpit used rnultlfunc_ dlsplays and Thesis HUD to intedace the pilot with sensors and weapons. What rnight the JAMES N. SERPA Mar. 1994 52 p Umlted Reproducibility:.More third ganoration cockplt look Hke?How might Itintsgrats many of thees than 20% of this document may bo aftected by mlcroflche quaitty technoiogles to simplify the plfofs Iits? Most of all, what Is the payoff? This paper will examine teclical cockpit problems and the technology (AD-A278573; AFIT/GOR/ENS/94M-13) Avail: Issuing _ (De- fense Technical Information Center (DTIC)) needed to solve them and recommand thres ganeralfons of solu_ons. The purpose of this research wBs to develop a Author (El) measure of operational suitability (OS) and determine Itsappllcability in mak_g the test langth d_elon prior to irdUal Opardonel Test and A94-60214 Evaluation(IOT&E). The currentapproach used by the Air Force ATM AND FIS DATA UNK SERVICES OperationalTestand Evalua_onCenter(AFOTEC) was presentedand CHRISTINA R. BAUHOF Mitre Corp,, McLean, VA IEEE used to establishthe relallonshlpsof the test measures, Itwas Aerospace and Eleclmnic Systems Magazine (ISSN 0885-8985) established thst OS could be represented by a function of operational vol. 9, no. 3 Merch1994 p. 38-42 rots availability (A(sub O)) and built-in test effectiveness (BE). BE was (BTN.84- SIX94331335523) Copydght defined and meesures proposed besed on the rnethod of date collec- The Federal Aviation Administration (FAA) cun'_ has under tion. A proposel for predloUng A(sub O), BE, and OS to determine the development data link services for air Ixaffic management (ATM), flight proper test length and semple size wes analyzed for several exanN_m infonTlldfonservice (FIS), and (_rnmun_, navigation, and survaik of prior Infomtatlon. Muitiplicative and additive utility functions were lance (CNS). These sendcse will be pmvk_ed over the aeronautical proposed as possible ways to calculate OS. Itwas shown thst probebil- telecommu_ network (ATN), a woddwide data network in- itystatemants could be rnede about BE, A(sub O), and OS from the pdor tended to IxoV_le data communications connectivity among mobile information; this analysis revealed _ reliance of the results on the prior aircraft, aidtnes, and civil aviation authorities. The ATM and RS information. DTIC services currently under development are part of an evolutionery procses _t wm begln, for _e rnost part, w_h _ of voice services. In the future, sanctus will faciiitste a common source of date for pilots, convoaem n Night planners, u well es computer-to- 05 computer communication systmns between ground based and air- borne automation systems. These future services will provide benefits AIRCRAFT DESIGN, TESTING AND such es the use of optimum aircraft and flight profiles. Author (El) PERFORMANCE A94-4m336 Includes aircraft simulation techniC. F-16 UNCOMMANDED PITCH OSCILLATION W. A. FLYNN Air Force Flight Test Center, Edwards AFB, CA and K. L. KELLER _ Aerormutics and Space Journal (ISSN A94-60181 0008-2821) vol. 40, no. 1 March 1994 p. 27-31 FOREBODY VORTEX CONTROL FOR WING ROCK (BTN-94- EIX94331337501) Capydght SUPPRESSION The Air Force Right Test Center (AFFTC) oonststantiy uses T. T. NG Toledo Univ., OH, C. J. SUAREZ, B. R. KRAMER, L. Y. m_tk=n p_or _o=rid in coqunctlon with _ght test to kk,_fy _rcraft ONG, B. AYERS, and G. N. MALCOLM JournalofAircral_(ISSN flightcontrol problems and also to davaiop, test, and validate solutions 0021-8669) voL 31, no. 2 March-April 1994 p. 298-305 rets to these problems. This paper discusses how ground simulation was (B1"N-94-EIX94311329119) Copyflght v_ indevelopingan e_ softwaren_ to eliminatea Static and free-to-roll tests were conducted in a water tunnel and pote_lally dangerous aircrldt flight cintra4 _. Through Shlltda- a wind tunnel wtth a cordigurdon that consisted of a highly siandar _on, an in-mght u_ pitch oscillation incident was inves_ fombody and 78 dag-swept clelte wings. The _ govemlng gated and tbe source of the proldem wM idanSflKI. A potantlal solution the wing rock of _ confl_ratkm am the Interactions between the wes tested and v_d,_od by us_ U_ sk.u_mr prkx to a_ht test. foreboby and _he _ng york.. Means of suppresCng w_g rock by Addi6onai benefits were gained due to simulmion studk_. The project controllingthe forebodyvoices using small bfowing jets were ex- _lo_ were able to prantice test maneuvers and emergancy procedures plored. Steady blow_g, tenganlailyaftfrom leewardnozzle=nearthe eseant_ to me tight test Ixogram. The pr_rranaw work, accomp_shed forebody _Ipawes found _o be capable of supprsesing wing rock. The wi_ ground simuia_on, corm_ predicted the eftscthm, r_ of the _ng rock mntlon wes attanuatod _ low blo,,vingratos _-"_dolind_|ed _ esftwam modification and eneured the success of an effictant and vallcl hi_ blowing rate6. _ h|gh blo,wing r=os, howover, o_n_'..ant vortex • ght t_t program. Ault_r (El) esymmeldes were aiso IrckJced.On the other hand, aitsmsting pulsed t:dowingon U'mleft anci dg_t siciesof U'mfombody was _ to A94-80_17 _ly be an e_ means of suppressing wing rock w,hout EVALUATION OF THE DYNAMICS AND HANDUNG QUALITY creating, on a time-average basis, large flow asymmetdes. CHARACTERISTICS OF THE BELL 412 HP HELICOPTER Author (El) STEWART W. BAILLIE Inst. for Aerospace Research, 53O AIRCRAFTDESIGN,TESTINGANDPERFORMANCE 05 STANKERELIUK,J.MURRAY-MORGAN,andKENHUICanad/an inflightsignals collected inorder to predict structural damage by maldng Aeronautics and Space Journal (ISSN 0008-2821) voL 40, no. 1 in flight integrated calculations, considedng influences such as: load March1994 p. 32-46 refs signals precision (frequency of points taken); elimination of low ampli- (BTN -94- EIX94331337502) Copyright tude vedations; and cycle counting methods for the damage calcula- A flight test program to determine If the Bell 412 HP would be tion. Author (revised) suitable for use as NRC's Advanced Systems Research Aircraft (ASRA) is described. As 8 replacement to the NRC Bell 205 Airborne N94,.,3,4594.# Deutsche Aerospace A.G., Munich (Germany). MiJitenj Simulator, the ASRA characteristics should include high conVol power Aircraft Div. and a minimum of control crces-coupling. Using bo_ frequency and THE ROLE OF FATIGUE ANALYSIS FOR DESIGN OF MILITARY time domaJn parameter _ techniques, the Bell 412 HP AIRCRAFT control response was messed. Other charectorlstJce,such as vehicle R. BOCHMANN and D. WEISGERBER InAGARD, An Assessment vib_ and handling ClUaiiUas,both with the stability augmentation of Fatigue Damage and Crack Growth Prediction Techniques 7 p system (SAS) on and off, were also evaluated. From considerations of Mar. 1994 handling quality and the measured values of control response to both Copyright Avail: CASI HC A02/IVlF A03 step and frequency sweep inputs, the Bell 412 HP is shown dearly to A brief overview of the fatigue design method employed at DASA have airborne slmute_on potential far inexcess oftbe current NRC Bell (Deutsche Aerospace AG) for combat aircraft is presented. The eft- 205 Airborne Simulator. Aulhor (El) ciency of the fatigue anaJ_ embedded in the overall design process--ls discussed and compared with full scale taslJng. Further- N94-34591# AeronauUcel Research Inst. of Sweden, Brcmma. more, possible improvements in the method are suggested. FATIGUE MANAGEMENT AND VERIFICATION OF AIRFRAMES Author (revised) A. F. BLOM end HANS ANSELL In AGARD, An Assessment of Fatigue Damage and Crack Growth Prediction Techniques 25 p N94-34S95# Wright Lab., Wdght-Pattemon AFB, OH. Mar. 1994 DAMAGE TOLERANCE MANAGEMENT OF THE X-29 Cop_tght Avail: CASt HC _F A03 VERTICAL TAIL The me_odo4(Oy currently used in Sweden for fatigue manage- J. HARTER In AGARD, An Assessment of Fatigue Damage and ment and vedflcalton of Airframes is dascdbed. Applications from the Crack Growth Prediction Techniques 8 p Mar. 1994 new fighter aircraft JAS39 Gripen are included in order to illustrate the Copyright Avail: CASI HC A02/MF A03 vadous concepts being considered. Additional experience from recent Dudng t_gh eng..of-attack (ena), km than 25 deg, the X-29 work on the older §ghter 37Viggen is also included to highlight certain experienced severn vert_'.,ai tall buffeL Rn tip eccaierometer data differences in _ detail analyses, stemming from rather different exceeded 110 g's at sppro)dmately 16 Hz. The U.S. Air Force Right nominal stress levais in the two aircraft. The pre_mt paper discusses Dynamics Directorate was asked to provkle technicel support to ensure tbe hendling of loed sequences end Icecl specn devaiopment, slxess that the entire X-2g flighttest program could be safely conducted. The analyses and fracture mechanics analyses, fatigue crack growth Right Dynamics Directorate transitioned an in-house developed crack modelling, component and full scale testing, service load monitoring gmw_ llfe prediclk)n program to the X-29 program office and NASA/ regarding both the dedicated test aircraft, which is used to verify basic Dryden as well as e_ technical suppo_ Three dimensional load assumptions, and also the individual load tracking program crack growth analyses were conducted between flight days to back developed for the new tighter. Author poseible damage growth based on actual strain data collected at cri_..aJ areas of _ ver_ai t_. The entire high &ce flight test program was N94.34592# Locld_eed Aeronautical Systems Co., Marietta, GA. completed as plenned using MODGRO to predict damage accumute- RISK ANALYSIS OF THE C-141 WS40S INNER-TO-OUTER ti_n. The clatewas used to menage flightrneneuvers to maximize useful WING JOINT flightdata and minimize stnJcturai risk. A fotiow-on flight test program R. E. ALFORD, R. P. BELL, J. B. COCHRAN, and D. O. HAMMOND was conducted with the x-2g to assass Vortox Flow Control. Repair to In AGARD, An Assessment of Fatigue Damage and Crack Grow_ the tell was recluiredto complete this mission. Anaiym end verification Prediction Techniques 10 p Mar. 1994 Presented at the Stnctural testing of the repair was pedormed by the Right Dynamics Directorate. Integrity Program Conference, San Antonio, TX, 2-5 Dec. 1991; Atthe end of that flight tset program, lass than 10 percent oflhe repair sponsored by USAF life was used. Author (revised) Copyright Avail: CASI HC A02/1MF A03 It is evident that weapon m/stem management benefits greatly N94-34,,_)6# BdtlshAerospece Defence Ltd., Fambomugh (England), from _ use of probabllistlc flsk assessment meCmcls. The C-141 WS 405 inner-to-outer wing joint provides an actual case of how this Military Aircraft Div. HARRIER 2: A COMPARISON OF US AND UK APPROACHES technology was iml_ment_ by Lockheed and USAF engineers to TO FATIGUE CLEARANCE detomnlne _ of inspection and mlmir for the C-141 fleeL Author F. S. PERRY In AGARD, An Assessment of Fatigue Damage and Crack Growth Prediction Techniques 27 p Mar. 1994 Copyright Avail: CASI HC A03/MF A01 N94,.3459_ Dassault-Bmguet Avla_on, Saint Ckx_ (France). ASSESSMENT OF IN-SERVICE AIRCRAFT FATIGUE The different approaches adopted for the fatigue clearance of the Harder 2 in United Statu Madne Corps end RoyaJ Air Fome Ueage are MONITORING PROCESS R. J. CAZES In AGARD, An Assessment of Fatigue Damage and discussed. Brief accounts am given of the impact differing analysis and national airwor_inass requimmer_ have had on Crack Growth Prediction Techniques 8 p Mar. 1994 fetlgue design, test, and monltodng of the airframe. Author (revised) Copydght Avail: CASl HC A02/MF A03 Maintaining the _rai integrity of aircraft depends on the Initial deflnitienof en inspectlon program to _ slnJcturai damage that mey N94-34F,g7# British Aerospace Defence Ltd., Brough (England). occur in sen4ce. Prediction of possible fatigue damage due to the _Un_ applled loeds end condlti(x_ of use encountored In servlce is based on FATIGUE DESIGN, TEST AND IN-SERVICE EXPERIENCE OF THE BAE HAWK an 8neJysJs of the probability of incipient cracks and on an ovaiu81Jon of tho dovok=f)mont o( undotast_le fautts 8ssumed to endst botwoen JOHN OHARA In AGARD, An Assessment of Fatigue Damage two irupectlo_. The velJdJty of ovaius_on modais Jsgenerally demon- end Crack Growth Prediction Techniques 10 p Mar. 1994 strated based on compadeons with rasub obteined en aiementerY tast Copyright Avail: CASl HC A02/MF A03 plecas subjected to pradJcted Iocai Joed condJt;ons Jnservice end used The BAo Hawk family is designed pdrnerlly to UK mgulatkms, to identify the Influence of events such as rare overloads or frequent includingfire safe life S-N fatigue philosophy. S-N data pertinent to key repe_ve small loads. This paper presents the pdnciplas for procomng features was assembled at lhe design stage, and fatigue 531 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE coupon/elementtestswereconductedinconfirmation.TheHawk aim of this symposium was to review Ule vadous technologies, which TMk.1lullscalefatiguetest(FSFT)hascontinuedtoleadtheRAFfleet, combine to give this increased opera_nal capability, and the tech- andthetestloadinghasbeenvalidatedbyamajoroperationalloads nlquas which are available or being developed, to overcome b_e design measurement(OLM)exercise.Incidentsarisingonthe FSFT or in- problems associated with the attainment of _me goals. The sympo- service are handled by several approaches including S-N and hacture sium was divided Into six sessions covedng propulsion and integrated mechanics caicu_tions, testing, statistical anah_s, and modifications flight control, aerodynamics and control at high angles of attack, and/or routlne inspections are introduced when necessary. The devel- post-stall light and control, flying qualities applied criteria, agility and opment of the fatigue life clearances of the BAe Hawk family is simula_on. discussed wi_ particular emphasis on the ¢onfin'natory testing and in- service loads measurement necessary to ensure and maintain fleet aimraft fatigue life clearance. Author N94-34806# Caisppn Corp., Arnold AFS, TN. USAFIAEDC AERODYNAMIC AND PROPULSION GROUND TEST AND EVALUATION TECHNIQUES FOR HIGHLY MANEUVERABLE AIRCRAFT: CAPABILITIES AND N94-34598# National Aerospace Lab., Amsterdam (Netherlands). CHALLENGES REDUCTION OF FATIGUE LOAD EXPERIENCE AS PART OF EDWARD M. KRAFT, GLEN R. LAZALIER, and M. L. LASTER THE FATIGUE MANAGEMENT PROGRAM FOR F-18 AIRCRAFT OF THE RNLAF In AGARD, Technologies for Highly Manoeuvmble Aircraft 15 p Mar. 1994 D. J. SPIEKHOUT In AGARD, An Assessment of Fatigue Damage Copyright Avail: CASI HC AO3/MF A03 and Crack Grow_ Prediction Techniques 11 p Mar. 1994 The simulation of highbj agile aircraft during the development Copyflght Avail: CASI HC A03/MF A03 phase presents a signiticant challenge to aerodynamic and propulsion Loed monitoring of the F.16 Neat of the RNLAF is carfled out by ground test and evaluation megxx_logias. The pdrne_ simul_on NLR using an electronic davlce capable of anaiyTJng _ signal of a chak,ngas are c=.med by U_e _)nt unready, m_ated nelure of strain gage bddge on one of the main carry through bulkheeds. Thls Is the flow phenomena ruN.dated wflh maneuvering aircraft that cause done on a sampla of the fleet. By maidng uas of 1he infommtion stored dynamic effects on the airframe and engine. In general, ground test in a large centralized data base system. 'individual airplane Inciting' is techniques are quasi-steady and transient effects are repmsanted by done. Six tirnas per year, the fatigue danmge experience of lhe fleet is Unearized supemo_on of steady-state data and unsteady sm_l mpodod to Ihe air staff, expresead inthe so called 'crack severity Indax.' disturbances. Cummt trends in the design of tecticai fighter aircraft From the measummante It Is Imown that the RNLAF is pperdng Ite F- mqun does coupl_g betwasn _e ,,_rframe, a_onk=, and propu_ 16 flast In e very darneging wsy. For thls reason, Itwas deddad to systems. In addition, the extreme attiludas and high angular rate i_the poaslbill_as of how to decrasas the asvedty of flylng. In _ of _ new bread of vehk:lacausas a sUong nonlinear coupling this prograrnmuch attention has bean gh_ento the 'stress per G' relation between components. In lhe current paper, several aerodynamic and dudng a flight. In pa_cular the influence of flying _ favodte take Off store configurations has been studied. Author (revised) ground test =nd ev_uetk_n melhodo_ ap_aUe to mmeuvedng aircraft are m,mmadzed, chailangas auodatod with cun'ont tl_hnkluas are identir_l, and an emerging integrated test and ev_.a_on =ncept that can sign_can,y _=e= the que,ty, time, and N94-34599# _ Corp., Fort Worth, TX. cost of davelpplng a new flight vehicte is Introduced. Author AN OVERVIEW OF THE F-1E SERVICE UFE APPROACH J. W. MORROW and G. T. HERRICK In AGARD, An Assessment of Fatigue Damage and Crack Growth Prediction Techniques 9 p BdtishAerospace Defence Ltd., War_ (England]. Aaro- Mar. 1994 dynan_ Dept. Copyright Avail: CASI HC A02/MF A06 DESIGN OF INTEGRATED FLIGHT AND POWERPLAHT The F-16 airframe was designed accocding to the latest USAF CONTROL SYSTEMS philosppby adapted inthe 1970s. It has a modular structural arrange- C. RELDING In AGARD, Technologies for Highly Manoeuvrable mant and maximum uee has been rnada of aiumlnum. It was dasigned Aircraft 12 p Mar. 1994 wffhfracture requtremonte in rnindfrom itsirception. Prasanted in view- Copyright Avail: CASI HC A03/MF A03 graph format are 1=-16requirements for airframe stncturai durability This paper da_dlxm the work being undartak_ by Brrdsh Aero- and safety, F-16 design approach, metals crack growth analysis space on bolh of hme projecla, as a continual;on of the flight control rr_. _,_m bulkhead web an_. rest p_ oom- and hx:hnok_y demormratk_ research m=cas_u0_ o0m_eted on _. fatigue and fracture conVol plan. F-16 tome management earlier projects such as the Jaguar Fly-By-Wlre and the Experimental approach, I=-16 fleet management recording systems, and lessons Aircraft I_rogramme (EAP). Derived from text laamed. CASI N94-34811# Wdght Lab., Wdght-Pattemon AFB, OH. N94-3460_ AdvismyGroupforAan:xlpaceRaseamhand Develop- RESULTS FROM THE STOL AND MANEUVER TECHNOLOGY merit, NeuBy-Sur-Saine (France). Right Mechanics Panel. DEMONSTRATION PROGRAM TECHNOLOGIES FOR HIGHLY MANOEUVRABLE DAVID J. MOORHOUeE In AGARD, Technologies for Highly AIRCRAFT [LES TECHNOLOGIES POUR LES AERONEFS A ManOetMableAircraft 8p Mar. 1994 HAUTE MANOEUVRABlUTE] _)p_ght Avail: CASl HC A02_MF A03 Mar. 1994 339 p In ENGLISH and FRENCH Symposium held The S/MTD ixogmm has generated flightt|mt date to vaiidate four in Annapolie, MD, 18-21 Oct. 1993 specific tm:hnok)gkm: 2-0 lhruet vectoring & revereing nozzle; inte- (AGARD-CP-548; ISBN-92-835-0740-1) Copyright Avail: CASI HC A15/MF A03 _ aumr_no_ _ng g.Uance; and rou_ _k_h_h _ rm The new genaraS0n of combat aircraft kKx_xm signmcant landing gear. These tochnologtes have bean integrafad into an F.15B advances inmaneuver capabU#y, espedaily Insuch area= as post-stell to providemlmon banel_tsscro_ the complete flightenvelope from on- control and sustained supersonic maneuver. These tK_nok_glaS ex- beard gnklance to a I_KI wea_'_ershort landk_g, through _gnifcantiy pend the operatlonai capabilltias, and are assantlal for m'vlvai in a enhanced maneuvering benefits to supersonic pedormance. These sophlstlcated threat scanado, and aiso to obtain favorabla exchange technologies are either _ng on to other aircraft, or can be ratios against an opponent using _ currentgeneration of fighters. The considered _)la design qXions for h_tureaircraft. Dedved _m text 532 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE 05 N94-34614#InetitutdeMecaniquedesFIuidesdeMarseille(France). augmented, basically unstable aircraft. Its Stability and P__,orttr_System TECHNIQUESFORAERODYNAMICCHARACTERIZATION (FCS) is of a much higher comple)dty than that used tn earlier aircraft, ANDPERFORMANCEEVALUATIONATHIGHANGLEOF e.g., the Tornado. To ensure that safe opamtion and optimum perfor- ATTACK[OUTILSPOURLACARACTERISATION mance are not degraded due to possible handling quality deflclendes, AERODYNAMIQUEETL'EVALUATIONDES new methods had to be used for both _e development and PERFORMANCESAHAUTEINCIDENCE] essessment oflhe aircrafL This paper describes the s_Uons and O.RENIERIn AGARD, Technologies for Highly Manoeuvrable the methods used in customer assessment pdor to nrst flight. An Aircraft 13 p Mar. 1994 In FRENCH overview of lhese meU'xxis is pmv_led. Author (revised) Copyright Avail: CASI HC A03/MF A03 ONERA-IMFL develops techniques for high AOA maneuvering N94-34622# Naval Air Warfare Center, W_rmineter, PA. Air Vehicle aircraft behavior studies. Specific wtnd.tunnais test coning and oecilis- and Crew Systems Technok)gy Dept. tory coning mo_ons, and cortstant pitch rate tests provide irflorma_on APPLICATION OF CURRENT DEPARTURE RESISTANCE .beut ready _d unready, k)w epesd aerodynam_. Spec_ soft- CRITERIA TO THE POST-STALL MANOEUVERING were facilitates data analysis and aerodynamic modeling. Application ENVELOPE of nonlinear dynamic systems analysis techniques allows stebill_es ROBERT M. SELTZER and JEFFREY F. CALVERT In AGARD, caicuIeUons and performance evaluation. For some maneuvers, be- Technologies for Highly Manoeuvmble Aircraft 17 p Mar. 1994 I"m_or predictions can be validated _ model flight tests in _o"_cal Copyright Avail: CASI HC A03/MF A03 wind-_ or in labem_on/. These ted'rdques have been used for This paper presents an anaiysis of current departure resistance fofai0ody yaw _ stucN_. _ of _ otf¢iery_y to _rcmft and high angle of attack (HAOA) flying quality parameters _ respect dynen_¢ molic,n_;w=,_ measured in "wlnd-turm_)l fecii_. Model flight to applicability and uUlity in the design and assessment of todays tests confirm expected behaviors. Author (revised) enhanced maneuverability aircraft. Modem fighter/atteck aircraft pos- sess exlmmaiy nonlinear aerodynamic databases and highly complex flightcontrol systems. In addition, b'_se aircraft require both departure N94-34617# TsentndrdAarogldrodinen_m_ Inst., Moecow (USSR). resistance and mission effective HAOA rn_neuvedng capabiflty. The AERODYNAMIC DESIGN OF SUPER MANEUVERABLE H_ of using traditional departure s_ility parameters such AIRCRAFT as C(sub n(bete (sub DYN))) and LCDP to address departure resLs- R. D. IRODOV and A. V. PETROV In AGARD, Technologies for tence and agility design and analysis issues are analyzed and pre- Highly Manoeuvrable Aircraft 6 p Mar. 1994 sented herein. Discussion Includes the)design phlkxK)l_t./ar_:l tnl_ Cepyflght Av_l: CASl HC A02/MF A0_ of Inqxovtng _ versus o'ynmTdCdopaftum reaistence. In _¢k:lltion, The main peculiarities of aerodynamic design of higtCymeneuvar- the _lltyofopen or _ departure parameters de_,ed from ai)le aircraft am examined. The po_ii_es of improving the aerody- linear and/or deco_ equatk=ns of mobon rep_ highly nonlin- namic characteristics of aircraft at high angkls of attack by use of ear aircraft is addressed. Finally, 8 general methoddiogy outlining the _h-,ft devices and powares_m systems (boundary _,yer control application and velidlty of current depalture susceptibility parameters blowlng over wlng, englne lhrust vectoring) are shown. The condltlo_ to the modem airoraft HAOA flight regime is provided with recom- of contn_able maneuver at high post-mailed angles of attack (alpha is mendations. Author (revised) less U'mnor equai to 90 degraes) are esteblished. Resulteofexperknen- tel _ on the influence of wing plenfo_m and locations of N94-34823# Wdght Lab., Wdght-Pattemon AFB, OH. Flight aircraft cumponente (wing, empennage) on b_e Iongitudinaistebmtyand Dynamics D_reeorm. conVollabil,y at high angles of attack are presented. A c(_paraiJve FLYING QUALITIES EVALUATION MANEUVERS analysis of aerodynamic and _er pedormance of aimrafl of THOMAS J. CORD, DAVID B. LEGGETI', DAVID J. WILSON, various conRguratfom (conventional, three-surface, canard) is per- DAVID R. RILEY, and KEVIN D. CITURS In AGARD, Technolo- formed. A.U_)r (revised) gies for Highly Manoeuvrable Aimmft 8 p Mar. 1994 Copy_ Avail: CASI HC A02/MF A03 An initiaiut of aircraft meneuvers hae peen defined to augment N94-34620# Naval Air Warfare Center, Patuxent River, MD. SMke the evaluation melhode currently used by the flying qualities and flight Aircndt Test Dtrectomm. test communith)s. Thaee meneuvers aro maent to employ the foll range X-31 TACTICAL UTILITY: INITIAL RESULTS of evailable aircrsft dynamics and to be 8pplied over _ lullAircraft flight DAVID E. CANTER and ALLEN W. GROVES In AGARD, envelepe. They indude severai dosed-kx_ taeks 8rid are the start of Technologies for Highly Manoeuvrable Nrcmft 15 p Mar. 1994 a sat of demonmnd_on meneuvem (o4_e typa now umd in Ihe rotorcmft Copyflght Avail: CASI HC A03/MF A0c3 flyingquality epecBcati_) for aircraft requirements. A pdrnary goal wes The X-31 is 8 research airoraft built to explore Ihe tacticai benefits to esteblish 8 tis petwesn deaign pammatem, aircreft atlY_JteS, and the of the emanced r_hter rnaneuverabmty U_atis poWble mrough me use oparatlonai usage environment while maintaining control of the evelu- of _rust vectoring. This paper gives background Information on the 8tldn procees. The epproech wae to corx:er_nde on aircraft dynsmics program and on Ihe aircraft. The high angle of attack envelope whk:h occur Indaily operstlons end to create pilot tesks whlch use those expansion phese is cuvered. Th|s aect_on detelis aircraft modiflca_ons conditionsto relate to important aircraft characteristics. E)_s'tlngevelu- that were required. The tactical ufliity phase of teetlng, inducing a'donme'dlodS concentrste on comparing quenffiatlve date to charte in simulation end Night testing, is discussed. Helmet mounted dleplay end MIL-Stendards which predict flying qualities. The maneuvem dis- supemon_ thrust vectoring teste planned for the near fubJream bdeny cussed hare direclly maesure the abilityof lhe pilot to pedmm Ihe tesks discussed. Aumor (reUse) of interest end at the mene time mainteJn• tie to the design cummunity. A.,_or (r_sed) N94-34621# Deutsct_ Fo_ fuer Luft- und P,aund_rt, N94-34624# /why Aviation Systems Command, Moffett Field, CA. Brumw_ (Germany). Inst. of Right Mechanics. STUDY FINDINGS ON THE INFLUENCE OF EFA FLYING QUALITIES SPECIFICATION AND ITS MANEUVERABlUTY AND AGILITY ON HEUCOPTER UTILISATION HANDLING QUALmES M. MARCHAND, R. KOEHLER, H. DUDA, E. BUCHACKER, and K. MAT(HEW S. WHALLEY In AGARD, Techn_ogles for Highly ELBEL InAGARD, Technologies for Highly Manoeuvrable Aircraft ManoeuvrabMAin:mft 10p Mar. 1994 18 p Mar. 1994 Copyright Avail: CASI HC A02/MF A03 Copyright Avail: CASI HC A03/MF A03 Three piloted slmulatlon studiss were performed bythe U.S. Amny The European Fighter Aircraft (EFA) was designed as 8 highly Aero_igh_ Directorate to examine the influence of maneuver- 533 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE abilityandagilityonhelicopterhandlingqual_asandtoprovidean specifications and requirements willneed tobe prepared in a different expandedbasisforthedynamicresponserequirementsinAeronautical way from U_atUad,_onally used. Author (revised) DesignStandard33(3,HandlingQualiUasRequirementsfor Military Rotorcraft. The expedments focused on aggressive tasks such as Air. to-aircombat and targetacquisitionand backing.The first expedmant N94-34626# AIania, Turin (Italy). focused on yaw agility requirements In the fown of attllude quickness OPERATIONAL AGILITY ASSESSMENT WITH THE AM-X lind _. The second experiment focueed on pitch and rollagility AIRCRAFT and maneuverability requirements in the form of bandwid_, angular RENZO BAVA, UGO ROSSI, and SERGIO PALONI In AGARD, rate, and attitude quickness. The third experiment focused on Tecl_as for Highly _e Nrcmft 19 p Mar. 1994 verabillty requirements inthe form of normal and Iong_llnal load Copydght Avail: CASI HC A03/MF A03 envelope for both convent_nal and compound helicnptem. Findings Raldng to lhe sotivitiss performed byWG 19 a common area of from the throe studies are presented in 5_e form of Cooper-Harper interest was individuated by Aem_ccht, Alanta, and the Flight Test handling qualltiss ratings, pilot commentary, and task performance. Center of the Italian Air Force to Investigate the application of the agility Author concept to conventional aircraft. Agility metdcs and maneuvers have been developed to evaluate _ operal_onal offoctJvenas8 of a modem flghtorin the new combat scenarlos that evolved following the introduc- of advanced technok_las. Agility metrics and maneuvens, how- N94-34628# British Aerospace Defence Ltd., Preston (England). over, may be effectively adopted to evaluate also operational OPERATIONAL AGILITY: AN OVERVIEW OF AGARD effec_venassofa co_wer_ aircraftsincethose metricshave been WORKING GROUP 19 devaloped to reproducesyr_he_b/the new operationalscenark_. K. MCKAY In AGARD, Technok_as for Highly ManueuwaMe Nrcmft The AM-X ground attack aircraft was hence chosen as a tss'd)_ to 11p Mar. 1994 vert_ the applicability of the agil_ corcep_ to conventional aircraft Copydght Avail: CASI PIG A03/MF A03 to assess the possible benallts for opemlk_nal tminlng. The research The environment in which a fighter pilot is required to operate is act_ty is balng cemod out by sknuiator and mght tasts to compare subject to continual c_. This change arises from advances in simulator cueing _ against the roal A/C and to inve_gate technok_/and the aaodng wodd pd,k_d sauaUon.The ordypredk:Uon simulator effectiveness for agility IminJng. Single ax_ agility rnaneuvem that can bo made wtth any conlkisnco is that this chenge process is pe_ by o_m.a_or _l be _ideted _ upcoming n_ht tests. bound to continue w_l an unpredictable rate. In dealing with change, Results from _ sottvity will be used to plan and perform lurther it is easy to prascdbe a procass but exlmmely difficultto implernent lhe simuiaUon to= with complex muitJaxis dosed loop agility tasks.This process with success. Success requires antldpa_pn, reaction, reevalu- sorry proved U',st agnJty me_ and _ m epp,cabis a_so ation and rnodiflcatlon of tactics and procassas. The nasd for change to conventior_ NC as woll, and are effective in evaluating it within a must be recognized and socornmodeted. Such an approach, whether highly dynamic con/)at environment. Operational agility may be Im- applied to fighter airplanes or any field of human endeavor, translates proved wi_ edequate pilot training and simulator may be used as an to agility. In undertaking this work, the group encountered many effective tool for IL Anyway, par_oJlar _ter_on must be paid tothe deflniUons of agility, some of which represented widely differing view- definition of 1he training program to overcome shortcomings of points. Often, in _ past, protagonists of the ver_ng ideas have fallen simulator cuing mn_ Au_or (revised) into heated arguments as to who is dQht. Fortunately, wi_lin the group, we have l_en able to stand back and sxamkw Itm argumm'_s with a dlspas_onam approach which has enabled us to understand the N94-34628# Defence Research Agency, Bedford (England). arguments and see the common gm_md, m_r than THE INFLUENCE OF FLYING QUALITIES ON OPERATIONAL clHfemncas. From our dJ_ra_o_ and disoussk)ns, the answer hes AGILITY _nerged that no one was wrong, 'dlat Ell were r_ht, at Immt in parL GARETH D. PADFIELD and JOHN HODGKINSON In AGARD, However, few had taken _ time to stand back and take an all Technologies for Highly Manoeuvrable Aimmft 14 p Mar. 1994 embracing view. Had they done so, than the message that all were Copyright Avail: CASI HC A03/MF A03 Wlng to put forward mlght have hed a widor and mon) sympathetlc Flying quellt_s standards are fomlalh/set to ensom ia_ flight audiance. All of the agility ooncepts lhat have been put fonva_ here and therefore to reflect minimum, rather than optimum, requirements. some medt. What was requlred was a way to relate the ideas and be A_Ityis a llylng quallty but rolates to opomllons at hlgh, If not magnum, able to apply Ihem Ina manner that is bolh reasonaMe m_l logicalfrom perloltnance. While the quelity metrics and test procedures for flying, both _ viewpoints of _e designer/supplier of almrafl and the cus- as covered for example inMIL-STD-1797 or ADS33, may provide sn tomer/user of lhe vshidas Ihat rasulL In deflnlng a weapon system, it is assentlal to exandne the component psrls and U_alrinteractlon, whether flight_ Ngh perfomtance. A currentconcem in both fire fixed and rotery lhis be aldmme, propulsion system, asnsom, codq_ and avionk_ (x wing mmmunitiss isthe al_ance of substantlat_ agility ariteda and the lhe weapcm lhermalvas and as_bUsh balance and wnergisllc In_- poesible conflicts between flying qualities and high perfomlance, i.e., oration betwean sHof the componente apprnprlste to the intsnded role more mi_ not always be betl. TI_ paper addmasas these concerns and ndsskms of the alrcralt. It Is the nasd to ashleve balance and and suggests an a_Ity hwtor lhat quantl_ l)_k),msnc_ margins in integration that is tho pdrne ddvor for undenindk_ opofa_ agility _ng qus_as _ms. The atUtude quk:io_, from _ klst rotaw- as a sot of concoplz, soppc_ted by moVlcs whlch • into a genomllzed wing handlingmquimmants, provtdas an kleal agility measure and links hamowork, capa_e of ovsk_ng a co_p_,x co.t,,t alrc_t c_n w,h handling wilh agility. A new perameter, based on maneuver accalem- a view to maximizing Ihe effectivene_ of that design wt_ln affordal_ Uon, is Introduced as a poterv_l candidate for defining upper limits to cost Iknits.The asltv_tias of _e group have produced such a fr'=mewod(, Oytng quelltlos. Thaso concepts aro introduced within a fr_ derived from the various flight mechanics based concepts, but which aimed at unif_ng Oy_ngquall_m and pe_ roqutrornords. R- would appear to be generalizable to cover Ihe olher syslems, et_heras ndy, a probablllsllc soalysis of pllot handling qualitlas ratinge is individual systems, or as a total we_qx)n syst_ There is lurlher work presented that sogges_ a powerfulrelatiomi_p between inherent required to conliwn _ this framewod( will stand, but our initial _rh.amo nyin0 q.alm_ and npor=_ a_i,y. A.mor (re_) investigeUons are very promisi_. Thls polite _heway fon_ f_r lucre _ aurroutes _o he _.dled, ova_Bd, and woOT.d again= oash N94-34629# Aerospace __ Test Establishment, Cold Lake oe_r, togeh')er w_h lhe oost Irn_k:allons, to d_srmine U1e ol_n',um (/Uber=). solutions. This may imply sionW_ant compromises If the roles and AN AGILITY METRIC STRUCTURE FOR OPERATIONAL perceived throats are too diverse. A consequance is that future deslgn AGILITY 534 . AIRCRAFT DESIGN, TESTING AND PERFORMANCE 05 ANDREW REIF In AGARD, Technologies for Highly Menoeuvrable M. S. CHANDRASEKHARA, LAWRENCE W. CARR, and S. AHMED Aircraft 15 p Mar. 1994 In NASA. Ames Research Center, Physics of Forced Unsteady Sepa- Copyright Avail: CASI HC A03/MF A03 ration p23-34 Mar. 1992 This paper summarizes how an agility metric organizational Avail: CASI HC A03/MF A03 sln_"turewas developed bythe Right Mechanics Panel Working Group Dynamic stall of an airfoil is a ck_ssic case of forced unsteady 19. The MnJCtUm was developed from existing concepts and was separated flow. Flow sepamUon is brought about by large incidences generalized for appllcat_n to both fixed and rotery wing aircraft. The tnVoduced bytho large amplitude unsteady pitchlng rno'donof an airfoil. approach was based on time domain analysis concepts focusing on the One of the parameters that affects _te dynamic stall process is the '_me to complete' 8 specific opemUonai task as 'die pdmmy metric. history of the unsteady motion. In addition, Ihe problem is complicated From this meblc a hierarchy of smaller time scale _ were by the effects of compressibility that rapidly appear over the airfoil even developed to emphasize the desired transient response dependent on at low Mach numbers at moderately high angles of attack. Conse- the mission. The metric slmcture was developed for organizing the quent, It ts of interest toknow theeffects of pitch rote history on the concepts of airframe agility as these were the most mature. The meVic dynamic stall process. This abslmct compares the results of a flow scheme is comprised oftransient, exbedmentai, and oberatl(xW meVtcs. visuai_ study of _e problem with two different pitch rate histories, The transient metrics were defined as those time dependent param- nard, osdHating airfoil motion and a linear change tn the angle of eters 1hat characterize instantaneous airframe state changes. Experi- attack due toa transient pitching motion. Derived from text mental metrics were defined by discrete small task elements wi_ compound properties that were optimized for evaluation purposes but were not necessarily recognizai_e as a mission related maneuver. N94-34988"# C,ok:xado Univ., Boulder, CO. Operational metrics were defined as _m_ete mission task elements CONCEPTS AND APPLICATION OF DYNAMIC SEPARATION including the total vehicle response inmultiple degrees of frasdem. The FOR AGILITY AND SUPER-MANEUVERABILITY OF AIRCRAFT: sJn_ure was also found to be al_ICehle to other aspects of agility AN ASSESSMENT through the evoMng concept of operaUo_ agility. This ent_ the PETER FREYMUTH In NASA. Ames Research Center, Phys_s of ,nVted study of po_Ue systems, p_kXNeh_ k_erface, and weapon Forced Unsteady Separation p 309-316 Mar. 1992 system time based agility metrics. Rnally, the working group idenned Avail: CASl HC A02JMF A03 areas which required further study. Author (revised) Aims for Improvement of fighter aircrMt pursued bythe unsteady flow community are high agility (the abiflty of the aircraft to make close turns in a low-speed regime) and super maneuverability (the ability of N94-34703"# NaUonal Ae_ and Space Admlnlstmtion. Hugh the aircraft to operate at high anglos of attack in a post atall regime L. Dryden R_t Research Fadl,y, Edwards, CA. o_Jringquick maneuvers in a more extended speed range). High nglliL_r DEVELOPING AND FLIGHT TESTING THE HL-10 UFTING roquh'as high lift coefad,'qmtsat lew speeds in ,, dyr_m_'c situaUon end BODY: A PRECURSOR TO THE SPACE SHUTTLE this requirement can be met by d_ly fomed separation or by ROBERT W. KEMPEL (PRC Kenlmn, Inc., Edwards, CA.), WENETH quaslstatlc stall oontmL The competing me_ods will be assessed D. PAINTER (National Test Pilot School, Mojave, CA,), and MILTON O. based on the known physics. Ivlarmuvedng into the post stall regime THOMPSON Apr. 1994 56 p also InvoNas dynamic sepam_on but because even fast maneuvers (Contract RTOP S0S-56-S0) involving the entire aircraft are 'aerodynamically slow' the resulting (NASA-RP-1332; H-1942; NAS 1.61:1332) Avail: CASI HC A04/MF dynamic vortex structures should be considered 'elicited' rather ,6,01 'forcecl.'More work seoms to be nasded inthle area of elidted dynamic The odglns of U_e IHfng-bedy Idse are raced beck to f_e mid- separa_n. Derived from text 1950's, when tm concept of a manned setsllite reentedng 'ereEarth's atmosphere In Ihe _rm of a winglass lifting body was firstproposed. The ao'varm_as of k_w rasntTy decelera_on k,_ds, renge capa_my, and horizontal landing of a tiffingreenb'y vehicle (as compared with the high N94-35241"# NatlonaiAeronau1_:s and SpaceAdmlnislmlkm. Hugh L. Dryden Right Research Fadlity, Edwards, CA. decelerabon loads and parachute landing of a capsule) are presented. EVALUATING THE DYNAMIC RESPONSE OF IN-FLIGHT The evolution of the hypersonlc HL-10 IItting body Is reviewed horn the THRUST CALCULATION TECHNIQUES DURING THROTTLE lheoretlcal daslgn and development procass to Its selecaon as one of TRANSIENTS two low-speed flight vehicles for fabrication and piloted flight tse_g. RONALDJ. RAY Jun. 1994 27p Prasentedatthe7thBienniai The design, development, and flight tMtlng of the low-speed, air- launched, rockat-powered HL-10 was part of an unprecedented NASA Right Test Conference, Colorado Spdngs, CO, 20-23 Jun. 1994 (Contract RTOP 505-68-00) end contractor efforL NASA Langley _ Center concelved and (NASA-TM-4591; H-1990; NAS 1.15:4591; AIAA PAPER 94-2115) developed the yet'dale shape and conducted numerous Ibeoreticai, Copyright Avail: CASI HC A03/MF A01 exbedmentai, and wind-tunnai studies. NASA Right Re_mmh Center New flighttest meneuvem and ana_#ds technlquas for evaluaUng (now NASA Dryden Right Research Center) was ruponaible for final the dynamk: response of in-mghtmruat mode_ dudng throme trans_nts _w-spa_ (P,_ch numbers _s men 2.0) as_ w._/m, pro)ted have heen developed and validated. The sppmech is based On the si_, contmg lew devaiopment, end fllgm tasis. The l_me con- aircraft and engine performance mlatlonehip between _mat and drag. tractor, Normrop Corp., was rasponaib_ for hardwere design, labrlca- Uon, and integration. Interasting and unusuai events in lhe fight tasting Two alight tast _, a throttle step and a _rotlJe frequency sweep, were developed and used in the study. Qraphicai ana_sis are prasented w#h a review of significant problems encountered in fl_e techniques, includinga frequency domain analysis method, were also firstfli0ht and how lhey were solved. Iml_rassionsby the pSotswho Ilew developed and evaluated. They provide quantitative and qualita_ve the HL-10 are included. The HL-10 completed a successful 37-fli0ht results. Four _rust _ melhode were used to demonstrate and program, achieved the highast Mach number and affitude of lhls class validate the tast t_. Right test applications on two high- vehicle, and contributed m theetschnologybase used todevelopthe perfomamce aircraft confirmed the tast methods as vaitd end accurate. space shuffle and future generaUons of lilting bodies. Author Thase meneuvers Ond enalym t_hniquas were easy to iml_ment end use. Rlght tast rasuits Indicate the enalyais techniquas can identify the combined effects of model error and I_ response N94-34968"# Naval Poatgraduate School, Monterey, CA, Dept. of _ On lho caiaJlatod thrust veJue. Tho rnethode developed In Aemnautk_ end Astlonautk_ this report provide an sccurate approach for eveludng, validating, or COMPARISON OF PITCH RATE HISTORY EFFECTS ON comparing thrust calculation meU'mde for dynamic fight applications. DYNAMIC STALL Author 535 05 AIRCRAFTDESIGN,TESTINGANDPERFORMANCE N94-35969"#NationalAeronauticsandSpaceAdministration.Hugh 31, no. 2 March-Apfll 1994 p. 367-375 mrs L DrydenRightResearchFacility,Edwards,CA. (BTN-94-EIX94311329128) Copyright IN-FLIGHTSIMULATIONSTUDIESATTHENASADRYDEN In 1971, the U.S. Army first _ the development of FLIGHTRESEARCHFACILITY computer code KRASH to model the Impact dynamlce and _ MARYF.SHAFERIn NASA. Ames Research Center, 1993Technical of airframes. The Federal Avla_n Administration continued _ sup- Paper Contest for Women. Gear Up 2000: Women in Motion p 77-97 port in 1975. Many enhencements have been added to the initialcode, Feb. 1994 and the cun'ent official mlaase version is KRASH 85. The next step In Avail: CASI I-IC A03/MF A02 the ongoing advancement of KRASH includes urcerteintles in model- Since the late 1950's the NaUonal Aeronautics and Space ing capabilities, which is the (xxddbub_ of this work. In _, a Aclmlrd_'s Dryden Right Research Facility has found in-flight Monte Cado simulation framework has been utilized here to parmti the si_ to be an invaluable tool. In-flight sirnuis_on has been used input of parameter uncerlalntlos, and thus allow the output variables to to addreu a wide varlety of flying qualitiss questlons, includinglow llft- be bound with a degree of statisticaicor_dence. An airframe model was to-drag ratio approach characts_ for vehicles like the )(-15, the selected and pmliminmy sensitivity tests wore performed on four lifting bodies, and the space shuffle; the effects of time delays on parameters, spedflca_ _ Impact surlace coemdant of dynamic conUollablMtyof aircraft w,h digital flight control systems; the causes _ctlon, the Internal beam damping constant, the external crushing and cures of pilot-induced ceci_ in a variety of aircraft; and flight spdng damping ratio, and 1he material properties, including yield control systems for such diverse aircraft as the )(-15 and the X-29. In- stnmm. Resulte from these praltminary taste ebowed the model was IV_ghtCnajlatlon has aiso been used to ar_cipate problems, avoid them, to _ Inthe first throe _rs, while it was insensi- end solve problams once they appear. This papar presents en account 5ve to chengss in the material proparllas. AccelaraUons and impuises of the V_,0ht ¢mu_k_ atthe D_yd_ Right Reuar_ Fac_ and were i_oned for two of the masses in _ model. The mNns and some discussion. An extensive bibliography is included. Author stenden:l_ at each time step were celculated and incorporated me plots. Finally, vedl_n whether the simulation yielded mtlslic_ly sionll_ant r_ub, and oonfldance bounds for resulW wtih large uncorteinty are presented. The te(:hnktuen outlined hem am O6 coml_etely _ to M general a KRASH rnodeJas deaimd. AIRCRAFT INSTRUMENTATION Author (El) Includes cockpit and cabin display devices; and flight inslmmenW. A94-60174" National Aeronautics and Space Administration. Langley Research Canter, Hampton, VA ALLEVIATION OF SIDE FORCE ON TANGENT-OGIVE A94.80180 FOREBODIES USING PASSIVE POROSITY AIRCRAFT LANDING GEAR POSITIONING CONCERNING ABNORMAL LANDING CASES STEVEN X. S. BAUER NASA, Langley Research Center, Hampton, HSING-,JUIN LEE Na_nai Ghung Hsing Univ., Taichung, Tahven VAend MICHAELJ. HEMSCH Jouma/ofA/rcraft(ISSN 0021-8669) and CHENG-YI CHIOU Jouma/ofA/rcraft(ISSN 0021-8669) vol. 31, vol. 31,no.2 IVlarch-AprH1994 p. 354-361 reis no. 2 March-April 1994 p. 446-449 refs (BTN-94-EIX94311329126) Copyright (BTN-94-EIX94311329140) Copyright expe_ l_ation to determkm the o_ of Addrmmed In this papar is the search for dynamically supedor pm_o i_metty for ellavle_ng _lde f_ on forebodl_ _ cc_- pcettioning of aircraft landing geam. For assessing _e amount of In the NASA _ Research _ter 7-ft by l_ft higl_-spm_d ldnidngenergy absod:)edby ncee isndlng gear for nomlai and ebnomlal _ lumnel._, moment, and mzi_ I_rO dma worn _ isndtng cas_, the parcumon Ux)ofy and lumpin0 man concept are on ooN_ a_ p_ (_ po_an,y, O.C_>On.hola Ulam) tenmnt-o_ve gor_ of g_ _ _.5 _ S.O. Tho _ forebo_ wore merged. El wlhaut tnm_ion gritto _mulate free 1tension comm:m. The extent A94-60170 of porcelty on the kxebodkm wu varlad to determine the extent of ANALYSIS OF AERODYNAMICS OF AIRFOILS MOVING OVER porceity nuded to aila_late xide forces. Stetic Iongtiudlnai end lateral- A WAVY WALL drectionai _sbllity and m prmsum date were obteined _t Mach KYOKO NITTA Nagoya Univ, Aichi, Japan Journal of AJrcrWt nurmem of 0_?.,0.5. end 0.8, ,,,_las of atteck from -5 to 4S deg, end ro, (ISSN 0021-8669) vol. 31, no. 2 March-April 1994 p. 387-395 mrs engla_ from -90 to 180 deg. The solid forebodiss exhibited large (BTN-94-EIX94311329130) Copyright asymmetric lU_e_ure Ioeds at moderate to high angles of attack The -erodynamic charactedstice end the motion of a two-dlmen- ceuaing kuge side forcea end _ momente; the b'ans#ion gm had slonai flat plate airfi:dl flying over a wavy wail sudace are calculated. The _ effect on the mymmelflc charactedsllce, but had a large oflact used computalonal scheme is a tinite diflarence method (ADI K:heme), on the Iongitudlnai chamcte_ The porous forebodlas exhiblted no which wu developed to improve the Ames code LTRAN2 and to slgnlf_mt slde Ion:es or yawlng moments at any angla of aUack tested. expand the cornp.te_ red.ced ,eqwncy re21on .p to 0.e. k_x,sce- Aulhor (El) ,ons of _e g_ W...mJng system is the mmr po_t _ sp_,ng the LTRAN2 vemion to _ current rm_em. Weak compmmNity (M(sub A94-80183 x) = 0.1-0.3) is conslderod, but nordineadty is neglected in current DRAG REDUCTION OF AIRPLANE FUSELAGES THROUGH ceiculations. Numedcai oomputetions include cases of a Ratplate flying SHAPING BY THE INVERSE METHOD over a flat solid wd In mldiUon to the cues of a moving wavy wall. The flat plate is fixed in the fmestmam at flint, and xlter some mmmn:h of M. F. ZEDAN King Saud Univ, Riyadh (Saudl Arabia), A. A, SELF, ila aerodynamic _lmctmtslice. mroalastlc enaiym is addeb allow|ng and S. AL-MOUFADI Jouma/ofAJrcraft (ISSN 0021-8669) vol. 31, 3 DOFs. The _ resulte are oompamd w,h Ihcee ot_neb by no. 2 March-April 1994 p. 279-287 refs the rang surface theory. The agrumant is sa, s_ac_y. P_'_or (B) (BTN-94-EIX94311329117) Copyright The ax_ m0.W,y m._on forthe ax_ymma_ _._e p_em was oxtendod to utilize doublet elements with linear Intenslty distrlbu- A94-8017"J tlon. "rhoamlution convorgos faster _m tho mource-basod mothod and INVESTIGATION OF MONTE CARLO SIMULATION IN FAA is U'mrefomquite _. A pmcedure based on _ _olution was PROGRAM KRASH used to deslgn low-drag laminar fuselage shapes for small aircraft HOWARD J. FLEISHER Galaxy Scientific Corp., Plaasantville, NJ appllcations wl_ a volumetrlc Reynok:isnumber range of I0-30 mllllon. and HAYM BENAROYA Jouma/ofAJrcraft(ISSN 0021-8669) voL A proffie wflh a fineness ratloof 6, Vansltlon at 40% of body isnglh, and 536 AIRCRAFT PROPULSION AND POWER 07 volumetricdragcoefficient of 0.012 at e nominal R(sub qq) of 15 million, sioned by system designam at the date of this document Is of the order was developed. The present inverse procedure was shown to be 8 of 2500 feet. The term 'altitude' shall be defined for the purposes of this powerful alternative to optimization me_ods. Several transition criteria document 8s height or distance from the terrain to the allimeter were investigated in the course of the study. The Crebtree cdtedon antennas. Compliance with _ese standards is recommended as 8 appears to be the most consistent. Expedmentel transition data for means of essudng that the equipment will sa_factodly perform its a._dsymmetdc bodies at high (flight) Reynolds numbers are urgently intended functions over all conditions normally encountered in routine needed. Author (El) ae_ operations. Inasmuch 8s measured values of mdlo equip merit pedormance chamcte_ may he a funclk)n of the method of measummant, standard test conditions and methods of tests 8re also A94-60623 recommended. Dedved from text EFFECTS OF PROPELLER ON THE TURNING OF OLD FIGHTERS TADASHI SATe Iwate Univ., Modoka (Japan), HIROBUMI OHTA, 07 SHOKICHI KANNO, and TATSUO CHUBACHI Transactiona ofthe AIRCRAFT PROPULSION AND POWER Japan Society for Aeronautical and Space Sciences (ISSN 0549- 3811) vol. 36, no. 112 August 1993 p. 72-91 refs (BTN-94- EIX94361136426) Copyright Includes pdme propulsion systems and systems _, e.g., gas This paper ISconcerned with the effects of propaller on the tumlng turbine engines and compressors; and on-board auxiliary power plants for almraft. flight of old fighters. The effects of propeller are composed of three alements. One of them Is the aerodynamic moments Induced bythe vorto)c The second is the gym moments and the third Is the torque A64-60426 _ due to propeller. The oBrves of trailingvortices are spiral. Exact NUMERICAL METHOD FOR SIMULATING FLUID-DYNAMIC analysis ISvery difficuILTherefore the vor_lce6are decomposed into the AND HEAT-TRANSFER CHANGES IN JET-ENGINE INJECTOR wdal and circumferential components In this paper. The letter gives almostnoeffect.Appro_Irnateanalysesofaerodynamicmomentsand FEED-ARM DUE TO FOUUNG V. R. KAI"rA Systems Research Laboratories, Inc., Dayton, OH and stability dedvstNes were pedonned. The results were applied to the W. M. ROQUEMORE Journal of Themmphys_ and Heat Transfer si_ of turning Nght of old flghtem. Consk:lereble effects am (ISSN0887-8722) vol.7,nc.4 October-December1993 p.651-660 shown in the figures. Author (El) (BTN-94-EIX94351142133) A _ method lor intngmtlng fluld_ sirnui_lons and heat-transfer calculations in different segments of solid boundaries N94-35055"# Pannaytvanle State Univ., Univendty Park, PA. Dept. of has been developad to predictdepos_on ins_e tubes. The fu_ Computer Science and Englnaedng. the._mde_ mechanism Is _eated ._a_c_h/ using a ACCURATE ESTIMATION OF OBJECT LOCATION IN AN IMAGE four-step global-chemletry modal. Deposits m aJlowed to grow on the SEQUENCE USING HELICOPTER FLIGHT DATA wall surlace, and the resulting Ifuid-dynan_ and heat-tnmsfer changes YUAN-LIANG TANG and RANGACHAR KASTURI In NASA. 8re implicitiycon_ using a time-d_t formula_on. Turbulent- Goddard Space Flight Center, The 1994 Goddard Conference on Ifow simulations for the fuel flow boLmded by the fuel-deposit thterface Sp==ceApplicetions of Artlflclal Intelligence p 147-157 May 1994 am mede on a body-oflantlKI coordinate system. The induclJonpedod, (ContractNAG1-1371) whlch ISasaedated with the siower depoaltlon dudng the Initialhoum of Avail: CASI HC A03/MF A03 expo_re, is modeled by introdudng a wall-raec_on-typa rnochenism In autonomous navigation, It is essential to obtain a three- for the sudaee stlcldng phenomenon. CaJculations 8re made for full- dimensional (3D) descdptlon of the sta_ environment tn which the scale and helf-scele gas-turbine injector faed-an'n dgs. The tempera- vehicle IS traveling. For 8 rotorcrafl conducting Iow-laffiude flight, this turn at the delX_it-tube interface is found toIncrease with deposition. de_ ISpartiodady useful for obemde datestlon and avoidance. Computed escumulamd dapceit welght and changes inthe fube-innar- In this paper, we addreu the problem of 3D poslJk)nestimetion for statlc wall temperature wi_ time me compared with the expedmental data. objects from a monocular sequence of images captured from a law- The effects of foullng on heat Imnsfer and bfockage to the fuel flow are letltude flying helicopter. Since the environment ISstatic, It ISweft known discussed. _ (El) thet the optk_ flow in the image will produce a radiating pattern from 1he focus of expansk)n. We propcee a mo_Ion anaJysis system which utilizes the epipolar _ to accurataly eefimate 3D _ of A94-60447 m objects ina real world image sequance taken from a low-attitude EXPERIMENTAL INVESTIGATION ON SUPERSONIC flying helk:opter. Raeuits show that tds approach gives goodae_mat_ COMBUSTION (2) of _lect positionsnearthe rotocr_s intendedNoht-pa_. XING_-IOU UU The 31st Reaeamh Inst., Minisby of Ae_ and (reUsed) Astronauts, Beiilng (China), JINGHUA UU, YUREN WANG, YUNQI GE, UXING YANG, and YUU HU Jouma/of_ Tec/mo/ogy (ISSN 1001-4055) no. 4 August 1993 p. 1-7 In CHINESE rels N94-35344# Radio Technical Commission for Aeronautics, (BTN-94- BX943S 1144_85) Weshington, DC. An _ IrMm_i_ was c_,'ded out on two rm:x:lal MINIMUM PERFORMANCE STANDARDS: AIRBORNE LOW- m.|l_r,m:mlc coml:_mom of dlffadng Im"_llm. "r'l_ coml_i_ _ RANGE RADAR ALTIMETERS a rearwen_-lacing step and a d_ng duc_ Bo_h ofme_ use 1 Nov. 1974 64 p Supemedae RTCA Paper No. 96-63/130-123 elecldc 8rc-heat_l air 11osimulate the working condi1_ns associated (RTCA-DO-155) wHh Incomthg tk_v that varied hem Ma = 2.1 fo 3.0. Comparisons were Avail: CASI HC A04/MF A01 made between '_e two combumore of different lenglh: each bums Minlmum padornunce starcler_ m Bet forth for thoae ofutractor- kemoeno or _mgen fuo_;and oach hae fue_i_cted oithm-i_n,el or istics of the alrbome Iow-mnge redar altimater which 8re esaemial for perpendicular to the alretraem_ El its opemtlon in appScetlona which provide meaeumd height above tenon forclearanceand_ng data.Thepot_n_ d_er_ ranmof _P.atk_n_ _ th_ eq_prnantpres_d_ _ pred_ ck_lon of the /U)4-60449 term low-range.' It should be recognized that very limited capapilitles COMPUTATION AND DISCUSSION OF A NEARLY CONSTANT may suffice in some installalJons while other installet_onsmay require DEGREE OF REACTION TURBINE STAGE a broader range of altitude (height) data. The maximum range env_ JIYA CUl Beljing Univ. of Aeronautics and Astronautics, Beljlng 537 07 AIRCRAFT PROPULSION AND POWER (China) Joumal of Propulslon Tectmology (ISSN1001-4055) no. 4 N94-34679"# General Motors Corp., Indianapolis, IN. Gas August1993 p. 14-17 In CHINESE refs Turbine Div. (BTN-94-EIX94351144987) Copyright COMPOSITE MATRIX EXPERIMENTAL COMBUSTOR Final The tension spline streamline curvature method was used. The Te¢hnisal Report nozzle vanes' Isadlng edge positive lean angle Is Increased to 18 dog, MARC D. PASKIN Apr. 1994 181 p and their reverse to conventional exit angle twist increased to 22.5 dog. (Contract HA,$3-24226) The variations of main gas dynamic parameters, total pressure loss (NASA-CR-194446; EDR-16346; HAS 1.26:194446; ARL-TR-334) Avei: coefficients, and stage efflclendas elong the blade height were shown CASI HC A09/MF A02 together with the corresponding conventional stage of the same A joint Army/NASA program was conducted to design, fabricate, path for comparison. A reactk_ difference of only 0.032 was achieved; and test an advanced, reverse-flow, small gas turbine combustor however, owing to 8 stage exit pressure that is at its highest at the utili_ a com_ metal/ceramlc (CIVIC) wall cooling concept. The shroud, the nozzla exit pressure is still highest at shroud. It seems objectives of this effort worn to develop 8 design method (basic design apparent that in order to minimize nozzle vane secondary flow and data base and analysis) for the CMC coo,rig technique and then shroud clearance leakage losses, an optimum pressure gradient along demonstrate itsapp(ica_n to an advanced cycle, small, reverse-flow nozzle vane exit is decisive In future study. El combustor with 3000 F burner outlat temperature (BOT). The CMC concept offem significant Improvements in well cooling effsolNenass resulting in a large reduction In cooling air requirements. Therefore more air is available for control of burner outlet temperature pattern in A94-60454 eddNon tothe baneflts of irnproved efflclancy, reduced emissions, and COMBUSTION PERFORMANCE OF DUMP COMBUSTOR IN mnoke levele. Task 1 of the prngmm defined oomponant matedals ancl RAMJET ENGINE USING LIQUID HYDROGEN FUEL localized design of the composite wall structure in conjunction with SHAOQING WANG The 31st Research Inst., Ministxyof Aeronautics development of basic deign models for analysis of flow and heat and Astronautics, Beljlng (China) Journa/of Proptds/on Tech_ transfer hough the wall. Task 2 required imptemontation of the (ISSN1001-4055) no. 4 Auguet1993 p. 42-46 InCHINESE re/s selected matedais and validated design models during combustor (BTN-94-EIX94351144992) _ deign. DatJmdeign of the _ected combustor concept The ramjet charactadat_s aasoc_ with using liquid hydrogen and its refinement with 3-D aorothewnel analysis were completed in were calculated and analyzed. The reaul showed that the ran_t's Task 3. Task 4 covered detail d_, process development and pedormance meat the required demands inthe range of M = 1.50-6.00 fabdcetion, and a series of burner rig tests. Burner rig tests covered and H = 40 km. The _ rasuk for dump and normel (xxnbuetom charactedzatlon of cold flow pressure drop, lean blowout and ignition were compared. At low altitude and smell M number, the rasur,marK)wed mapping steady-state performance throughout the operating range that the parformance of dump combustor is batter than nownelcornbus- including the milestone 3000 F BOT as well as two asdes of simulated tin, i.e. the thrust is increased and the resistance of ovedtow is cyoltcthewnel shock teats at high point BOT condRIons of 2700 F (32 demeased. At higher altitude and higher M number, the differences total cycles) and 3000 F (68 total cycles). Rig test results have between the two are very small. Additionally, the problem of demonsUated the benefits and vlab|llty of the CMC concept, rneet|ng or matching is also partially solved by using dump _. El exceeding _ asmtherrnel performance and liner wall temparatum charactadsttce of similar lower temperature combustom, achieving 0.15 pattern factor at 3000 F BOT while utilizing approxtmetsiy 80 percent loss cooling air than convention_, Nm-cooled combustion N94-34607# Wdght Lab., Wright-Patterson AFB, OH. Turbine systems. Aub"_r Engine Div. PROGRESS AND PURPOSE OF IHPTET PROGRAM RICHARD J. HILL InAGARD, Technologies for Highly Manueuwable Aircraft 8p Mar. 1994 Copyright Avail: CASI PiG A02/MF A03 N94-34993"# Coltec Industries, West Hartford, CT. Control IHPTET is _ Integrated High Performance Turbine Engine Syst=m Dtv. Technolow ini_a_ve. This paper dimmas the pumcee (beckTound HOT GAS INGESTION EFFECTS ON FUEL CONTROL SURGE goals and applications) and the progress of IHPTET. IHPTET is 30 RECOVERY AND AH-1 ROTOR DRIVE TRAIN TORQUE SPIKES percent comptete and achieving significant success in advancing Final Raport, Sap. - Oct. 1992 turbine engine tech_ levels. The future of IHPTET is bdghL FRANK TOKARSKI, MIHIR DESAI, MARTIN BOOKS, and RAYMOND IHPTET deveBopad technologies are being applied to bath mi0tery end ZAGRANSKI Apr. 1994 54p commercial turbine engines _ both new engines and fleet (Contact NAS3-26075; DA PROJ. 1L1-62211-A-47) m(x:lembalk_n's. IHPTET Is the technology base (or ell future militmy (NASA-CIR-191047; E-8638; HAS 1.26:191047; ARL-CR-13) Avail: systems and the springboard for many new commen:lal engines. CASl HC A04/MF A01 Author Tht= report auras the work accomplished through com- purer sknulalion to understand the impact of the h_ turbine assembly ('rA) fuel control on rocket gas Ingestion induced engine surgas on Ihe AH-1 (Cobra) helicoptor. Thase surgas excite the N94-34608# Rolis-Royce Ltd., Bristol (England). lighUydempad tomionel modas of the Cobra rotor ddve trein and can ENGINE CHARACTERISTICS FOR AGILE AIRCRAFT sauas over_ of the tail rotor sheft. The simuidon studlas show K. R. GARWOOD, G. S. HODGES, and H. E. ROGERS In AGARD, the hyd_ TA control has a nogligtblo effect on drive Tectmok@as for Highly ManomJVrJ_ Aircraft 8 p Mar. 1994 Ueln rasonancas becauas lls msponas is eufficlenUyattenuated at the Copyright Avail: CASI HC A02/MF A03 resonant frequencies. However, a digital eisolronic conlrol woddng A number of different factom drive and conslmJnthe devetopmant through _ TA co_'s sspam_, emergency _J_ metedng system of future technolow. This papar looks at the curare pampactlve on the has basn k:len6fled 88 a solution to tho ove_ problem. StaU_ doveJopmant of eO,o eTrcmttWsto.ru -rid morn _nec.k:dy, tho or_ne of-tho-mt software wHhin the elechor_c control can _ aclive characteristics UNlse demand. Having _ the dasirable engine daml_ng of the rotor ddvetraJn to eliminate exneeelve torque spikas due _, _ key tachnok_es required to enable thm_ are to any dlsturi_mcas including anglne sorgeo and aggmaslve hellcq)tar discussed. It le proposed _at _e ol:_mum a_le eircm# system wlg be maneuvem. Modlflcatlone to the axletlng TA hydmmechenlcal control ac_eved glven thase tec_'x_kJglesby cor_dering the bast way Inwhk:h are relatlvely mlnor, and ex_ing angine sansors can be uBlzed by lhe the engine shoukJ be 'rated' to fulfill the operational requirements electronic control. Therefore, Itis concluded that the comblnatlon of full envisaged. Aub_r authority digital eleclmnlc control (FADEC) _ hyd_ 538 AIRCRAFT STABILITY AND CONTROL 08 backupusingtheexistingTAcontrolenhances flight safety, improves The concept of applying suctk_ at the nose of forebodies at high helicopter performance, reduces pilot woddoed, and provides a sub- angles of attack to control the vortex flow was tested in two dynamic stantial payback for very little investmenL Author wind-tunnel experiments on large scale versions of the Defence Research Agency (DRA) High Incidence Research Model (HIRM1) in the DRA 24ft wiod tunnel. The firat experiment with a HIRM 1 wind tunnel model mountgd on a free.to-yaw dg used an analog control system. The N94-3S352"# NatlonalAeronauticsand SpaceAdministratJon. Lewis model was contmged at angles of attack of 28 degrees and 32.5 Research Center, Cleveland, OH. COMPUTATIONAL METHODS FOR HSCT4NLET CONTROLS/ degrees by applying differential suction through small holes near the nose apex to minimize the error between demanded and measured CFD INTERDISCIPLINARY RESEARCH GARY L. COLE, KEVIN J. MELCHER, AMY K. CHICATELU, TOM T. erie of slde_tp. The second experiment used a free-flight version of HIRM1 w_ a digital Departure Prevention System (DPS) which was HARTLEY, and JOONGKEE CHUNG May 1994 13 p Presented at flown successfully in previous expedmants. A nose suction control law, the 30fit Joint Propulsion Conference, Indianapolis, IN, 27-29 Jun. designed to maintain nil about the wind axis, was added to the DPS. 1994; sponsored by AIAA, ASME, SAE, and ASEE The model was mounted on a dgwhich aUowed freedom inyaw, roll, and (Contract N_233; NAG3-1450; RTOP 505-62-52) pitch, the tsilplanes could move symmetrically and differentially, and (NASA-TM-106618; ICOMP-94-10; E-8903; NAS 1.15:106618; AIAA the rudder was used to augment directional stability. The model could PAPER 94-3209) Copyright Avail: CASl HC A03/MF A01 be flown at angiss of attack up to about 30 degrees, wi_ the suc_on A program aimed at facilitating the use of computational fluid cont_l law ac'lNo, but would diverge in yaw and roll ff the suc_on wes dynamics (CFD) simulations by the contmis disciplineis presented. The turnedoff. Author(revised) objective is to reduce the deve_t time and cost for propulsion system controls by using CFD simulations to obtain hlgh-SdeUtysystem modsis forconVol design and es numerlcal teat bede for control syatem N94-34615# Bath Univ. (England). School of Mechanical testing and velida_on. An interdisciplinary team has been formed to Engineedng. developanaMk_ andcomputationaltoolsin threedisdl_ineareas: YAW CONTROL BY TANGENTIAL FOREBODY BLOWING cont_s, CFD, and _ _. 1"he controis effort has N. J. WOOD and W. J. CROWTHER In AGARD, Technologies for focused on spedfying requirements for an interface between the Highly Manceuvrable Aircraft 10 p Mar. 1994 controls speclaJistand CFD simulatkx'_s and a new method f(x exlmct- Copyright Avail: CASl HC A02/MF A03 ing linear, reduced-order control models from CFD simulations. Exist- Aimraft yaw control at high angles of attack by tangential fombody ing CFD codes are being modified to permit time accurate execu_on blowing has been investigated expedmantally. Tests were performed in and provide reaUstic boundmy condltlons for controis studies. Pandlel the University of Bath 2.1 m X 2.5 m low speed wind tumel using an processing and distdbuted computing techniques, aJongwilh existing approxtmete_y 6 percent scale generic combat aircraft model fitted with system intngration software, am being used to reduce CFD exeoJl_n blowing slots in _e nose cone. Six cornpone_ strain gauge balance times and to support the development of an integrated analysis/design force and moment data was measured for angles of attack up to 90 system. This paper describes: fire init_l appiicetkm for the tl_ degrees for various stot geomatdes snd _. The effect of slot being developed, the high speed civil transport (HSCT) inlet control azimuthal location is demonstrated and a slotstall phe_non problem; sctlvities being pursued in each discipline area; and a described.A geomeWdependentforeboW/_ng_)w-S_d coupling prototype_ syatem_ p_cefor_ operat_ and has been identified which can lead to unexpected yaw_g and roiling visualization of a time-accurate HSCT4nlat sirnuldon. momants. The prlmery soume of ym,dng moment is shown to be the enllanced mea of atlached tiow on the blown slde of the forebody rather than direct vortex influence. The optimum slot extent and location N94-35746 Air Force Office of Sclentil_ Research, Boiling AFB, depend on _te angle of at|ack ranga over which control is required. For Washing_n, DC. rngions where ateedy vortes _mymmeW is present, siots neer the apex AFOSR CONTRACTORS PROPULSION MEETING of the fo_body produce severn control reversals at low blowing rates M.A. BIRKANandJ. M.TISHKOFF 20Apr. 1994 338p Meeting which can be minimized by placing _ slots away from _ apex. For held inAtiangc City, NJ, 14-18 Jun. 1993 Umited Reprodudbllity: More control In regions where the flow Is dominated by periodic vortex than 20% of 1his documant may be affected by mlcrofche quality shedding, long s_s offer efficient control to 90 degree angle of attack. (ConVact AF PROJ. 2308) The moat suRablecompromise forwide range controlwould appeer to (AD-A279028; AFOSR-TR-94-0275) Avail: Issuing Activtty (Defense be a shortsk)tplacedaway from lheapex ofthefombody. Technical Infoematlon Center (DTIC)) Author(revised) Abstracts are _ for research in aJrbrea_Ing combustion, rocketpropulsion,anddiagnoatk_inreac_ngmediasupposalby the Air Force Office of SdenUflc Research. DTIC m4-3461s# DefenceResearchAganw,Bedford(_). CONTROL OF LEADING-EDGE SEPARATION ON A CAMBERED DELTA WING 08 P. R. ASHILL and G. L RIDDLE In AGARD, Technologies for Highly Manceuvrab_ Akncraft13 p Mar. 1994 AIRCRAFT STABILITY AND CONTROL Copyright Aveil: CASI HC A03/MF A(X3 Wind tunnsi studies of Ifows over a cembered delta wing of 60 Includes aircraft handling qualities; piloting; flight controls; and c_.ees isading.K_ =,'eep = _, _ceedhavesho,n thatthet_v autopBots. =eperates on a lonverd part of 1he curved upper surface. Aithough not apparent in surlace pressure diatdbutlons, this separa_on strongly ir_uances the _ of the oneet of leading-edga sep_uatton. The N94-34613# Defence Research Agency, Famborough, I-larn_hire prasantpape_ desc,lbesa wind-tunn,dstudy intothe use of sub _). _rody,wn_ andPro_Con boundery-_vo,tex gane,atom,Inthefo.'nofth|n_.'es,tocontn_the DYNAMIC TESTS TO DEMONSTRATE LATERAL CONTROL flowalongand towan_theupper-sudaceseparation"ne.The contn_b USING FOREBODY SUCTION ON LARGE SCALE MODELS IN em_ctivebecewe# shi_ _e p(x_onof the oneatof leedlng-edga THE DRA 24 FOOT WIND TUNNEL mpamiondo.mmmm,ansu_ngincmesedleeding-edgathruat,meir_y GERALDINE F. EDWARDS, A.JEAN ROSS, EDWARD B.JEFFERIES, lhrough a reorganization of the Nparated flow ftall_ downst_mm. The and CHARLES O. OLEARY In AGARD, Technologies for Highly Wow mechanisms are described, as well as the effects of wire number. Manceuvrable Aircraft 14 p Mar. 1994 Multiple wires can I)mVidea reduction of about 16% Inthe lift-deper¢lent Copyright Avail: CASI HC A03/MF AD3 drag factor. The impiicelkms of the study for the subsonic slight 539 08 AIRCRAFT STABILITY AND CONTROL charactedslJcs of supersonic combat aircraft are described and sug- values of the bleed and control power data can be used for sizing the gest that the vortex generators offer genuine improvements in subsonic reac-.Ik_controls fora future short takeoff and vertical lendlng (STOVL) maneuver performance. Author (revised) aircraft Author N94-34618# Deutsche Aerospace A.G., Munich (Germany). Military N94-35258"# National AercnauUcs and Space Administration. Hugh Aircraft Group. L Dryden Right Research Fedllty, Edwards, CA. X-31A CONTROL LAW DESIGN FLIGHT TESTING A PROPULSION-CONTROLLED H. BEH and G. HOFINGER In AGARD, Technologies for Highly AIRCRAFT EMERGENCY FLIGHT CONTROL SYSTEM ON Menoeuwab4e Aircraft 9 p Mar. 1994 AN F-15 AIRPLANE Copyright Avail: CASI HC A02/MF A03 F. W. BURCHAM, JR., JOHN BURKEN, and TRINDEL A. MAINE This paper presents an overview on the X.31A flight control law NASA, Washington Jun. 1994 19 p Presented at the 7th Biennial design philosophy and the technical reaiizalkXl of the design. After an Right Test Conference, Colorado Spdnge, CO, 20-23 Jun. 1994 intmduc_on to the FCS hardware configuration, the basic c0¢R_ law (Contract RTOP 533-O2-34) stnJcture and the method used for feedback gain calculatkm are (NASA-TM-4590; H-1988; NAS 1.15:4590; AIAA PAPER 94-2123) presented. Several elements, such as the feedforward path, gravity Copyright Avail: CASI HC A03/MF A01 effect compensation, Inerl/ai and gymsco_ coupling compensation, Right tests of a propulsion-controlled aircraft (PCA) system on an and the pilotcommand system, are discussed In more _I. Slmplffied F-15 airplane have been conducted at the NASA D_jden Right Re- block diagrams of the basic flight control mode in the longitudinal and surch Center. The airplane was tlown with ail flight control surlaces leterai/diredJonal ads follow. Rnaily, the implementation of the thrust locked both in the menuai throffies-orW mode end in en augmented vectodng system including engagement and disengagement proce- system mode. In the letter mode, pilot thumbwheel commands and dure is shown. Author (revised) airc_/_ were used to pos,lon the thn_les. Right evelua_on remJltsshowed that the PCA system cen be used to land en N94-34619# Deutsche Forschungsanetaft fuer Luft- und Raumlahrt, ai_lenethathas suffereda major ftightconVolsyslernfailuresafely. BnJnswick (Germany). Inst. fuer Rugmechenilc The PCA system was used to renover the F-15 aiq04ene from e severn X-31A SYSTEM IDENTIFICATION APPLIED TO POST-STALL upset cxmdi_on,descend, end land. Pllots from NAS_ U.S. Alr Force, FLIGHT: AERODYNAMICS AND THRUST VECTORING u.s. Navy, and McDorm, Dougm Aerospace evaiumd _ PCA D. ROHLF, E. PLASTSCHKE, and S. WEISS In AGARD, Technolo- and were favoraUy impressed .r_h _ capaU_. Menuai gles for Highly _ Aircraft 12 p Mar. 1994 throBes-only approaches were unsucceuful. 111tspeper deecribes the Copyright Avail: CASI HC A03/MF A03 PCA s_nem ope_k_ end tuSng, it me presem ft_hmst resu.s and Right testing of the X-31A post-stall experimental aimraft started pUot comments. Author in Oct. 1990. By the end of 1992, the X-31A flight regime had been expanded to 70 deg angle of attack, and a significant number of flight tests with dynamic post-stail maneuvem had been performed. Within N94-35796 Air Force Inst. ofTech., Wdght-PattersonAFB, OH. the international 'Combined X-31A Right Test Team,' DLR (the Gem'Bn of _needng. DIRECT REDUCED ORDER MIXED H2/H INFINITY Aerospace Research Establishment) contdl0utss its system identiflca- CONTROL FOR THE SHORT TAKE-OFF AND LANDING/ _on expedence and capabilities to the determination of aerodynamic pemmetars and thrust vector conlml effectlveness from flighttsst dats. MANEUVER TECHNOLOGY DEMONSTRATOR (STOL./MTD) M.S. Thesis Aftsr a brief descdption of the applisd hardware and software, this paper presents recent results from mght test data compa_blUty checking. The WILLIAM C. REIGELSPERGER, JR. Mar. 1994 169 p Limited k:isntircstion modais used for the separstKI evaiustion of Iong_tudinai ReproducibUity:More then 20% of this document may be alfected by i__ _ are Introduced. This emphasizes I_ rn_o_, qua,ty r_one necessary forX_IA Ngh angle ofattack_- (AD-A278675; AFIT/GAE/ENY/94M-3) Avail: Issuing Activity (De- _. I__ resultsof selectedaerodynamic parametersare fenee Technical Infommtlon Center (DTIC)) in_dson to _nd-_ predictions.The _ca_ of One of the conclusiom from the STOL/MTD program was the X-31A thrust vector control e_eness is addressed, and prelimi- need for a multlvadab_ method of deslgnlng controllers of low order. nary results am presented as well. An overview of future identification This research investigated that problem by studying reduced order ac_4tJes with respect to nonllnear/Instalk3rmry effects In the high angle mixed H-two/H-infinity control _ applied to the STOL landing of attack regime is ghten. Author (revised) con§_.mation whk:h empk)ys both thn_ voctodng and #w use of e _._ _ng_wore__n __ rnet hand_ _t_ cn_da and reduced _ _rk_oad _ _ng N94-34994°# Natk)nai Aeronautics and SpaceAdminisUation. Ames __ __._ _were_ Research Center, Moffett Fle_, CA. YAV-SB REACTION CONTROL SYSTEM BLEED AND th_ _inear _ _ _ _ MI _r _ _ CONTROL POWER USAGE IN HOVER AND TRANSITION ____l___re_. _ _ue _ _ _ _ _ were _ed PAUL F. BORCHERS, ERNESTO MORALEZ, III, VERNON K. well. The reduced order method was _ed H-_4nfl_ MERRICK, and MICHAEl. W. STORTZ Apr. 1994 47 p __. A _ order controller that had good performance was (Contract RTOP 533-02-37) found by uslng a pe_ constmlnt, end a fourth order controller (NASA-TM-104021; A-93080; HAS 1.15:104021 ) Avail: CASI HC A03/ that provided good margins wu founcl using a robusmess constraint. MF A01 A_rd order controller was also found with • perfomlance constrak¢ Using • calibrated Rollo-Royce Pegasus engine and e:dstlng Rm¢omnlonda_s for finding a low order controller, with good perfor- ___ _m_,_ _i_ manoe and robuslness are given. DTIC __mm(R_)_ra__n_on a YAV_B _ _ typical_ _, _, hover, landingmeneuvem. R_ th_ _ were _ N94-35873"# National Aeronautics and SplLne Administration. RCS nozzle total pressure measumments, end contml power was Leng_ Reswch _, Hampton, VA. detsrmlned from the moments produced by _tese thrusts and _e FLUTTER SUPPRESSION DIGITAL CONTROL LAW DESIGN aircrafrs momenW of inerUa. Them data doo.xnent the _ AND TESTING FOR THE AFW WIND TUNNEL MODEL of the YAV-88 RCS with its baaic stablUtymJgmentation system (SAS) VIVEK MUK}-IOPADHYAY In its NASA Wed(shop on Disldbutsd engaged. Advanced cont]rol system designs for the YAV-8B can be Parameter Modeling and Control of Rexlble Aerospace Systems compered to the original SAS based on the total bleed use end the p 135-149 Jun. 1994 percentage of available bleed used. In aclditJon,the peak and mean Avail: CASI HC A03/MF A06 54O RESEARCH AND SUPPORT FACILITIES (AIR) 09 Thedesignofacontrollawfor simultaneously suppressing the ttonin the second phase of the study greatly anhanced the aircraft flying symmetric and antisymmetdc flutter modes of a s'dngmounted tixed-ln- qualities. This paper descdbes the simulated tilt-wing aircraft and the roll aeroalasUc wind.tunnal modal is described. The flutter suppression flap control concepts and presents the results of both phases of the control law was designed using linasr quadratic _ ti_ory, and simulation study. Author italso involved control law order reduc_on, a gain root-locusstudy, and use of previous experimental results. A 23 percent increase in the open- loop flutter dynandc pressure was de--ted dudng the wlnd-tunnal N94-35972"# National Aeronautics and Space Administration. Antes test. Rapid roll maneuvem at 11 percent above _ symmstd¢ flutter Research Center, Moffett Reid, CA. boundary were also performed when _ model was in a free-to-roll GROUND VIBRATION TEST OF THE XV-IS TILTROTOR configuration. Author (revised) RESEARCH AIRCRAFT AND PRETEST PREDICTIONS KAREN STUDEBAKER and ANITA ABREGO In its 1993 Technical Paper Contest lor Women. Gear Up 2000: Woman in Motion p 117- N94-35874"# California Univ., Los Angeles, CA. Dept. of Mechani- 123 Feb. 1994 ceJ, Aerospace and Nudasr Englnasdng. Avail: CASI HC A02/MF A02 SELECTED TOPICS ON THE ACTIVE CONTROL OF The firstcomprehensive ground vlbmtlon survey was performed HELICOPTER AEROMECHANICAL AND VIBRATION on the XV-15 TiItrotor Research Aircraft to reassure the vibmtk_n modes PROBLEMS of the airframe end to provide date crtticel fix determining whJd flutter PERETZ P. FRIEDMANN In NASA. Langley Research Canter, NASA stabmtymargins.Theaircraftwassuspencledbythewingswrd_bungas Workshop on Distributed Parameter Modeling and Control of Flexible cords and ceblas. A NASTRAN finite elament modal was used in the Aercepece Systems p 151-177 Jun. 1994 design of _ suspensk_ system to minimize its interference with the (ContractNAG2-477) wing modes. The pdma,,y ot_e_ve of the test was to measure the Avail: CASI HC A03/MF A06 dynanVc charactedstice of the wings and pykx_sfix asroalasUc ste_i_y Thle paper describes Ina concise manner throe eslested topics on analysis. In addlUon, over 130 acc_erometers were placed on the the active conUol of helicopt_ asromectw_cel and vtbrdon IXo_ems. airframe to characterize the fuselage, wing, and tall vlbratk_n. Protest The thras topice are es follows: (1) the active control of hallcopter air- predictions were made _ the NASTRAN model as well as cormla- resonance using an LQG/LTR approach; (2) si_ of higher _ns with the tost data. The resuJtsshowed that the suspension system heffnor_ control (HHC) el)plied to a four blacled hingelaes helicopter provided the isola_on necessary for modal measurements. rotor infixward flight; and (3) vibration suppression in forward flight on Author(revised) a hingalees helicopter rotor using an actively controlled, _ span, trolling edga flap, which ts mounted on the blade. Only a few salected illustrative results are presented. The results obtained claady indicate O9 thattheper_ spemac_valycont_ed _o hascon_em_e pot_m_ for vibrst_ reduction In helicopter rotors. AUtilor (revised) RESEARCH AND SUPPORT FACILITIES (AIR) Inckx:las airports, hangars and runways; aircraft repair and overhaul N94-35875"# Ohio State Univ., Columbus. Dept. of Electdcal fadtillas; wind tunnels; shock tube factlit_s; and engine test blocks. Engineering. ROBUST CONTROL DESIGN TECHNIQUES FOR ACTIVE FLUTTER SUPPRESSION N94-34(_10# Naval Air Warfare Center, Wamdnstar, PA. Flight HITAY OZBAY and GLEN R. BACHMANN In NASA. Langley Dy.am_ and_ Branch. Research Center, NASA Workshop on Distributed Parameter Modeling APPUCATION OF CENTRIFUGE BASED DYNAMIC FLIGHT and Conlml of Rexibie Aerospace Systems p 179-191 Jun. 1994 SIMULATION TO ENHANCED MANEUVERABILITY RDT/E Avail: CASI HC A03/MF A06 J. F.CALVERTand D.A- KIEFER InAGARD, Technologles for Highly In this paper, an active flutter suppression problem is studied for Manoeuwabla Aircraft 16 p Mar. 1994 a thin airfoil In _dy asrodynamics. The _ modal of this Copyright Avail: CASI HC A03/MF A03 system is Infinite dimensional because of Theodomen's function which This paper addresses the strengths of centdfuge simulation to is irrdonal. Several second order appro_irnstlons of Thsodoraan's provide _ unfamiliar and severe _ environment associated with function are compared. A finite dimensional model is obtained from highanglaof attackand post-stanmaneuvedng.The approachto such an approxlmation. We use H Infinity control techniques to llnd a development and testing of centrifuge motion control algodthn_ is robustly stabilizing controller for ac_ve flutter mJppresalon. outilned, including inherent modeling constraints such as three degrees _uthor (revised) of freedom, estimmod human perceptual medals, and the machine- associated _stn_:lur_ conaldera_ons. Difflourdas of alOo- ri_n devalopmant am Blustmted using _e results ofa rece_ f_ng N94-3F,9_P# NationalAeronautk_andSpeceAdministmti_. Ames qu_es expedmantin_atedto studythe effectsof motionon I_k)t Research _mter, Moffett Field, CA. rdnga fix proposed noas-down conlml power guidaline criteria. Uas of PILOTED SIMULATION STUDY OF TWO TILT-WING CONTROL off-llne computer models to tune algodthm performance Is also pre- CONCEPTS sentod. Finally, current capabilities of cenffifugo simulation and a LOURDES G. BIRCKELBAW and LLOYD D. CORUSS In its 1993 discussion of future applications is outlined. Author (revised) Technical Paper Contest forxWomen. Gear Up 2000: Women in Motion p 1-12 Feb. 1994 Avail: CASI HC A03/IVlF A02 N94-34632"# National Aeronautics and Space Administration, A two-phalm piloted simulation _udy was conducted to Investi- wa_n_on, DC. gate alternative wing and flap controls for tilt-wing alrctafL The InitlaJ NATIONAL FACILITIES STUDY. VOLUME 1: FACIMTIES pheas of the study competed the flytng qualltlas of botha convantional INVENTORY (p_) f_o andanVmova,vegaared_o. Theescondphaseof 29 Apr. 1994 49 p thestudyIntroducedanaltemmemethodofpilo¢controlfor_e gaared (NASA-TM-109854; NAS 1.15:109854) Avail: CASI HC A03/MF flapandfurtherstuc,edtheflylnoquai_esoftheprogrammedflap,and A01 two geared flap configurationS. In general, the pilot rating showed little The Inventory actMty was initiated to solve the criticel need fora vamuionbetw_n _ prog_ flapandthegearedflapcont;ol singlasourceofsitespedflcdescriptiveandperametncdataonmajor concepts. Some differences between the two concepts were no_ced public and privately held aeronautics and aerospace related facilities. and am discuesed in this peper. The eddition of pitc_ attitude stebiliza- This a challenging undertaldng due to the scope of the effort and the 541 09 RESEARCH AND SUPPORT FACILITIES (AIR) short lead time inwhich to assemble the inventory and have It available summary view of the 30-year mission forecast and requirements to support the task group study needs. The inventory remains dynamic baseline, an overview of excursions from that baseline that were as sites are being added and &m data Is accessed and refined as studied, and orgenization of _ repod;,Introduction _ provides discus- study progresses. The inventonj activity also included the design and sions of _ me_ used in this anal; Baseline Model B implementation of a computer database and analytical tools to simplify provides the mission and requirements model baseline developed for access to the date. This volume desoribes the steps which were taken Space Opemtlons and Space R&D analyses; Excursions from the to define the data requirements, select sit_, and solicit and acquire baseline -- reviews the details of vedations or 'excursions' that were data from them. A discussion of the Inventory stnJCtUreend analytlcsJ developed to t_t Itw future program prolections csptured In the tools is also provided. Derived from text baseline; and a Glossary of Acronyms. Derived from text N94-34636"# National Aeronautics and Space Administration, N94-34633"# National Aeronautics and Space Administration, Wsshlngton, DC. Washing_n, DC. NATIONAL FACILITIES STUDY. VOLUME 4: SPACE NATIONAL FACILITIES STUDY. VOLUME 2: TASK GROUP OPERATIONS FACILITIES TASK GROUP Final Report ON AERONAUTICAL RESEARCH AND DEVELOPMENT 29 Apr. 1994 590p FACILITIES REPORT (NASA-TM-109858; NAS 1.15:109858) Avail: CASI HC A25/MF A06 29 Apr. 1994 413p The I_ ob_ of the Nat]on_ FadlWes Study (NFS) (NASA-TM-109855; NAS 1.15:109855) Avail: CASI HC A18/MF A04 were to: (1) determine where U.S. facilities do not meet national The Task Group on Ae_ R&D Facilities examined the aerospace needs; (2) _ new facilities required to make U.S. status and requirements for aeronaulics facilities against _ competi- capabilities 'world class' where such improvements am in the nelional tive need. Emphasis was placed on ground-beseq faclllties for sub- interest; (3) define where consolidation and phase-out of exlstlng _c, super=x_c and _ aerodynam_, and propdCon. facilities is appropda_; and (4) develop a fang-term _ plan for Subsonic and transonlc wlnd tumals werejudged to be most _ and wodd-ckm _d,y aeq_s,k)n and shared usage. The Space Opera- of highest pdodty. Rasuits of b_e study ere presented. Facilities Task Group defined discrete tasks to ac_ish the Dedved from text above objectMm wtihtn the scope of the study. An asasssmant of national space operations lm:dlitleswas concluotod to determine the nation's capability to meet the requirements of space opomUons cludng thonext30 yaem. Tho mlsslonmodal uaed inthoal_lytodaflnefacillty N94-34634"# National Aeronautics and Space Administration, requlremormISdaacdbed InVolume 3.eaeed on ti'dsmodal,thernslor Wes_ng_n, DC. focus of the Task Group was to idan_y any substantlve overlap or NATIONAL FACILITIES STUDY. VOLUME 2A: FACILITY STUDY undomtlllzdonofspace operations f'aciii_ and to identify any faclllty OFFICE ON THE NATIONAL WIND TUNNEL COMPLEX Flnal shorthdis b'_ would necsssltem facglty upgredes or new facilas. The Report focus of _ Ini_il study was dlri_ted toward facility moomn_ 29Apr. 1994 864p to consoildal_r_, domJNm, erd'lancsrmmte, and uPOmdes (NASA-TM-109856; NAS 1.15:109856) Avail: CASI HCA99/MFA10 conskh_md nm:_mery to ,_¢iermy end _fentivaly m.,pporttho be_mline The Facility Study Office (FSO) has completed its assigned requirements model..a¢lh_es _ to id_ng facility needs or acth/_es. The results of the FSO efforts, studies, and asasssments ere for enhancing U.S. intomational oompetiffvoness documented. An overview o4the FSO _ as well as a general and achieving wo_d-cless capability, where appropdato, were deferred comparison of all concepts constdared are pmvtch_. Detailed informa- to a sui)seq_mnt study phese. Dedved (torn text l'on is also provided for the salectod concspt, _ D-Option 5. Only findings am presented. The FSO developed recocrannan(:ldonsonly as a consequancs of assumptions for cost and scbeduie essessments. N94-34637"# National Aeronautics and Space Administration, Dedveq from text Washington, DC. NATIONAL FAClMTIES STUDY. VOLUME 5: SPACE RESEARCH AND DEVELOPMENT FACILITIES TASK GROUP Final Report N94-34635"# National Aeronautics and Space Administration, 29 Apr. 1994 211p Washington, DC. (NASA-TM-109859; NAS 1.15:109859) Avail: CASI HC A10/MF A03 NATIONAL FACILITIES STUDY. VOLUME 3: MISSION AND With the beginnings of the U.S. space program, them was a REQUIREMENTS MODEL REPORT Flnal Report pre_ need to devalop tedll_s that couid support the ted_ 29 Apr. 1994 I02p roso..¢h and deve_pmont. _g, and oper_ons of ovoh_g sp_;e (NASA-TM-109857; NAS 1.15:109857) Avail: CASI HC A06/MF A02 syslmm. Redundm_ in facilities that wes oncs and advantage in The Na_onal Fadlity Study (NFS) wee iniUated in 1992 by Daniel providing flexibility and schedule accomrnoda_on is Instead fast be- S. Gogdln,Adndnistmtor of NASA as en _ to devalop a compm- coming a burden on scsrcs resourcss. As a rosult, them is a clear hensive and integrated I°ng'term plan f°r future facililkm"The resulting' pemeplk_ in many secfom that the U.S. hae many space R&D facUlties mul_-agancy NFS consisted of _ Task Groups: Aeronautics, Space that are under-utilized and which are no longer cost-effective to Ope_, and Space Re=arch and Deve_pment (RaD) Task maintain. At the ssme time, It is clear that the U.S. continues to possess Groups. A four_ group, the Englnaedng and Cost Analysis Tesk Group, many spacs R&D fadll_s wt_ch era the best-- or mnong the best-- was subeequentiy added to provide cross-cuffing functions, such as in the world. In order to remain world class in key areas, careful am_t_g consistency in davalop_ an memory of space facmt_ am_mnn_nt of currant capabilities and planning for new fadlit_ is Space facilities decisions requlm an assessment of current and future needed. The NaUof_ F_y Study (NFS) was INUred in 1_2 to needs, l"herefom, me two'mk gmups daallng wi_ spese _ a dave_p a _ and V_ograted _r_-to_ _ for f.ture conalstant modal of future spacs mmlon progrems, operallom and aeroq)acs facll#iss that maets currant and projected govemmant and R&D. The model is a middle ground bsssiine _ for NFS commercial needs. In o_ler to esasm the natlon'e cspablty to support analytical ptapoaes w#h excumions to cover potentk¢ spacs prngrern research and davek)pmmt (I:_D), a Space P.&D Task Group strategies. The modal indudas three major sectors: IX)D, civilian wae formed. Tha Tesk Group wes co.chalmd by NASA and DOD. The govemmant, and commercial space. The model spans the next 30 Task Group formed four major, tect_ly- and hJnction_ly. yaers because of'_e long isad times essocimed w(th facHtes devsiop odentod woddng groups: Human and Machine Operations; Informs- mant and uaege. This documant, Volume 3 of the final NFS report, is tlon and _; Propulsion and Power;, and Materi_s, organized along the following lines: ExecuIk, e Summa_-- provides a Structures, and Right Dynamics. In addition to thase groups, three 542 ASTRONAUTICS 10 suppor'dngworkinggroupswereformed: Systems Engineering and 10 Requirements; Strategy and Policy; and Costing Analysis. The Space ASTRONAUTICS R&D Task Group examined several hundred facilities against the template of a baseline mission and requimrrsnts model (developed in common with the Space Operations Task Group) and a set of excur- Includes astmnau_cs (general); astrodynamics; ground support sys- slons from the baseline. The model and excursions am described in terns and fadlltJes (space); launch vehicles and space vehicles; space Volume 3 of the NFS final report. In addition, as a part of Ihe effort, the VensportatJon; spacecraft communications, command end tmctdng; group examined key strategic issues associated with space R&D spacecraft design, testing and performance; spacecraft instrumenta- facilities p_enningfor the U.S., and these are discussed InSection 4 of tion; and spacecraft propulsion and power. _is volume. Dedved from text A94-60106 CONTROL STRATEGIES FOR SPACE BOOSTERS USING AIR N94-34919"# NationalAeronautics and SpaceAdmini_. Lewis COLLECTION SYSTEMS Research Center, Cleveland, OH. H. G. KAUFFMAN Wright State Univ., Dayton, OH, R. V. FLOW QUALITY STUDIES OF THE NASA LEWIS RESEARCH GRANDHI, W. L. HANKEY, and P. J. BELCHER Journal of CENTER ICING RESEARCH TUNNEL Spacecraft and Rockets (ISSN 0022-4650) vol. 31, no. 2 March- E. ALLEN ARRINGTON (NYMA, Inc., Brook Park, OH.), MARK T. Apd11994 p. 243-248 refs PICKETT, and DAVID W. SHELDON Jun. 1994 44 p Presented (BTN-94- EIX94311330665) Gopyfight at the 18_ Aerospace Ground Testing Conference, Colorado Spdngs, A simple and efficient performance anaiysis method is developed CO, 20-23Jun. 1994; sporsoredbyAIAA for evaluating vehicle pitch and engine throttie controls to minimize (Con_c't NAS3-25266; RTOP 505-62-84) booster fuel required to fillsecond-stege liquid oxygen (LOX) tanks and (NASA-TM.106545; E-8691; NAS 1.15:106545; AIAA PAPER 94- deliver the vehicle to the staging point. An optimization methodology 2590) Avail: CASI HC A03/MF A01 finds a throttle schedule that controls both the air-breathing engine and A sedes of studies have been conducted to determine the flow the LOX (:_llac_on rate. The aitltude-vaioctty profile is dedved from a quality in the NASA Lewis Icing Research Tunnel. The pdrnery purpose caiculus/energy management contouring method. Auto- of ,d-rosestudlas was to document airflow characteristics, Includingtlow rna_ edaplive-gain pitch-rote and throttle controls are developed. anguladty, inthe test section and tunnel loop. A vertically mounted rake Resuits from a parametric study show that colleclJngon the run for en was used to survey total and static pressure end two comp(x_nfs of optimum schedule results in a 17% fuel savings over collection at a flow angle at three axial stations within the test sactJon (test sacton constant Mach number. Author (El) Inlet, test plane, and test section exlt; 15 survey stations total). This information will be used to develop methods of Impr(Mng the eerody- nemic and icing charactedslics within the test sac_on. The data from A94-60110 surveys made in the tunnel loop were used to determine areas where NAVIER-STOKES SOLVER FOR HYPERSONIC FLOW OVER A overall tunnel flow quality and efficiency can be improved. A separate SLENDER CONE report documents similar flow quality surveys conducted inthe diffuser CHANG-SHENG TAI Chung C,heng Irst of Technology, Taoyuan, section of the Idng Research Tunnel. The flow quality studies were Taiwan and AR-FU KAO Journa/of Spacecraft and Rockets (ISSN (x)nducted at several locations around the tunnel loop. Pressure, 0022-4650) vol. 31, no. 2 March-April 1994 p. 215-222 mrs velocity, and now angularity measurements were made by using both (BTN-94-ED(943t1330_1) Cor_ght fixed and Varslatlng probes. Although surveys were made throughout A ful Navlar-Stokas code has been developed for predicting the the tunnel loop, emphasis was placed on lhe test section and tunnel aerodynamic properties of slender cones. This code can simulate an areas directly ¢._lmam ofthe test section (settlingchamber, be,mouth, entire flowflaid of slender cones, such as boundary layer and vortices. and cooler). Row visuai_, by video recording smoke and tuft An explicit upwind flux-difference-split scheme combined witha multi- pattoms, was also used dudng _ase studies. A great deal of flow stagemethedhasbsen imlplarnentedforsolving the steadysxisymrnetric visuaiizatJonwork was conducted tn the area of the drive fan. Informa- fullNavter-St_as equations. Experimental elate are found to be ingood tion gethemcl there will be used to improve the flow quailty upstream end agraement with the code prediclions. This code cen be extended to a ddwnstmam of the fen. Auth(x rnul_dtmersionai program for simulating the three-dimensional practJ- cel prob4em. Author (El) A94-60112 N94-35267"# Sverdrup Technology, Inc., Brook Park, OH. HOT CORROSION TEST FACILITY AT THE NASA LEWIS DETERMINATION OF SLENDER BODY AERODYNAMICS SPECIAL PROJECTS LABORATORY Final Report USING DISCRETE VORTEX METHODS RAYMOND C. ROBINSON and MICHAEL D. CUY May 1994 39 p G. A. GEBERT Utah State Univ, Logan, UT Jouma/of Spacecraft (Contract NAS3-25266; RTOP 537-04-20) and Rockets (ISSN 0022-4650) vol. 31, no. 2 March-April 1994 (NASA-CR-195323; E-8770; NAS 1.26:195323) Avail: CASI HC A03/ p. 200-207 refs MF A01 (BTN-94-EIX94311330679) Copyright The Hot Corrosion Test Facility (HCTF) at the NASA Lewis Speciai Current aerodynamic interest has tumed to the study of Projects Laboratory (SPL) is a high-velocity, pressurized burner dg supenneneuvembla fighters end weapon performance when launched curnmtly used to evaluate the environmenlai durability of advanced in extreme fJJ_11t conditions. The evaiLl_Jton of design missile perfor- ceramic mataflais such as SIC and S13N4. The HCTF uses laboratory rnence requires multiplemrs of six degree-of-freedom (6-DOF) simu- service air which is preheated, mixed with jet fuel, and ignited to lations, analyzing the missile behavior for a variety of launch and flight simuiate the conditio_ of • gas turbine engine. Air, fuel, and water conditions. Before wind-tunnel tests, it is necessary to produce the systems am computor.controllad to maintain test cnodtlkxm which aerodynamic loading of cencMate missiles for 6-DOF analyses. Since Include maximum air flow_ of 250 kg/hr (550 Ibm/hr), pressures of 100- semi-emldricai formulas fall in regions of nonlinear aerodynamics, and 600kPa(1-6arm),andgastemperaturesexceed_g1500C (2732F). solu_ors to the rub Navter-Stokes equations are too coslht and time The HCTF provides a mlatlvely inexpensive, yet sophisticated means consuming, an ai_matJve method of discrete vortex analysis is re- for msearchem to study the high-temperature oxidation of i¢lvanced examined. The present theo_j examines the three.dimensionai nature materials, and the injection of a salt solution provides the added of the shed vor_dty and generaiizes pmvk)us discrete vortex analyses. capability of conducting hot corrosion studies. Aub_r Consequently, the results demorstmte relative user independence in 543 10 ASTRONAUTICS determining all slender-body loading at angles of attack from 0 to 70 successful touchdown conditions would be possible for this low lift-to- deg. The rapid calculations of the discrete vortex method makes it a drag-ratio vehicle (approximately equal to 4), but also the vehicle would pdme candidate for the determinatons of high angle-of-attack aerody- not exceed its design dynamic pressure limit of 400 psf dudng envy. nar_c databases. Author (El) This dynamic pressure constraint limit, coupled _ limited available _ au_odty at low supersonic speeds, restrtcls 1he available A94-60191 maneuvedng capability for gle HL-20 to esquire gle runway. One result SIMPLIFIED METHOD FOR EVALUATING THE FLIGHT of this analym was _at _is resl_ve rnanmJvedng capabil_ rices not STABILITY OF LIQUID-FILLED PROJECTILES allow _ use of a model-fo,owing ablnosphedc enVy-guidance algo- dthm, such as "d_atused bythe Space Shuffle, but instead requires a DANIEL J. WEBER Army Edgewood Arsenal, MD Journal of more edapteble guidance algorithm. Therefore, for this analysis, a Spacecraft and Rockets (ISSN 0022-4650) vol. 31, no. 1 January- predictor-corrector guidance algoriSTn was developad lhat would pro- February 1994 p. 130-134 mfs vide succmdul touchdown conditions whiis not violating 1he Uynamic (BTN-94-EIX94311322905) Copyright pressure constralnL A flight-control system was designed and incomo- This paper describes a modification to the Mcyclic theory to include the effect of a liquid paylcad on the _ and stability of 1he rated, along with the predlctor-correc_r guidance algorithm, into a 81x- projec_e. The influence on the projectile's motion by1he liquid payload dagrse.of-fresdom simulation. This sl_ was tested under many combinations of off-nomlnal almospheric density profiles and winds is similar to the Magnus effect. A computer program has been devel- and showed that lhe HL-20 remained _. This Idmulstion also oped that detenninas the convex pro_e moron using either retcal estimates of Uquld-fill cheracterls_cs or experimental results indicated that _le HL-20 could reach lhe landing site and execute a obtained from a testfixture for nonrigid pa)4oacis. Preliminary stability successful landing under all off-nomir_l conditions simulated. assessments for liquid-filledprojectile can be made rapidly and provide AuIhor (El) 8 means of datennlning the relalve Importance between _e aerody- namic and tk:luld-flilcheractedstics on the projectites flight stability. A94-60397" National Aeronautics and Space Administration. El langley Research Center, Hampton, VA. EFFECT OF UFT-TO-DRAG RATIO IN PILOT RATING OF THE HL-20 LANDING TASK A94-60274 E. BRUCE JACKSON NASA Langley Research Center, Hampton, PRELIMINARY INVESTIGATIONS ON IMPROVING AIR- VA, ROBERT A. RIVERS, and MELVIN L. BAILEY Jouma/ of AUGMENTED ROCKET PERFORMANCE SpacecraffandRockats(ISSN 0022-4650) vol. 30, no. 5 Septem- K. N. ANIL Indian InsL of Tech., Madras, India and K. A. ber-October 1993 p. 543-548 m/s DAMODARAN JoumalofPropulalonandPower(ISSN0748.4558) (B'rN-94-EIX94351137057) Copyright voL 10, no. 3 May-June 1994 p. 432-434 refs A man-ln-ltm-icc_ $t_ Mudy of tl_ h_mclilngqualities of ltm (BTN-94-EIX94321333323) Copyright HL-20 llftlng-bodyvehicle was made in a fixed-bese slmulaton cock:pit Use of the Petal nozzle instead of the conventional conical nozzle at NASA Langley Resserch Center. The purpoes of the sludy wes to as the pdrne_ stream representing fuel-rich gases ex_lng from a rocket identify and sub_ opportunities for improving the origlnel design nozzle has de_ considerable improvement In U_e parfor- of the vehlde from a harding quali_es and landing pedormance rnance of an alr-augmanted rockeL This can be atldbuted to the perspective. Using prellmlne_ wind tunnel data, a subsonic asmdy- improved mbdng of the hot, e_'taust gases conlalnlng unbumt fuel with namlc model of the HL.20 wes developad. This model wes edequate to the surrounding alrslmam, and subsequent heat release. El simulate lhe lest 75-90 e of the approach and landing. A slmpie flight com_ ey=em w_ da_gnea and _amanted. U_ng _ asrody- A94-60395" National Aeronautics and Space Administration. namic modal es a _, visual apprceches and Isndlngs wem mada Langley Research Center, Hampton, VA. at esveral vehicle ilft-to-drag ratios. Pilots ra_d 1he handling character- AERODYNAMIC CHARACTERISTICS OF THE HL-20 _cs ofeach conflguratk)nu_ng a convontk_n_numedc_ p§ot-ra_ng GEORGE M. WARE NASA Langley Research Center, Hampton, VA scale. Results from e_e study showed a high degree of correlation and CHRISTOPHER I. CRUZ Journal of Spacecraft and Rockets betwesn _be _-to-drag rato and pgot r_ng. Level I pilot ratings were (ISSN 0022-4650) voL 30, no. 5 September-October 1993 p. 529- obtekled when the I./13 ratio was W:)pro)dmately3.8 Orhigher. 536 refs A,_'x)r (El) (BTN-94-EIX94351137055) Copyright Wind tunnel tests were made from subsonic to hypersonic speeds A94-60398" National Aeronautics and Space Administration. to define the aerodynamic characteristics of _e HL-20 ilflJng-body Langley Research Center, Hampton, VA. configuration. The date have been assembled into an aerodynamic AERODYNAMIC HEATING ENVIRONMENT DEFINITION/ database for flight analysis of lhls proposed vehicle. The wind tunnel THERMAL PROTECTION SYSTEM SELECTION FOR THE da_ ind_ates that the rnod_ is k_ngr=dn_ly and _rJy ste_e (about HL-20 a center-of-gravity Iocatkm of 0.34 body Isnglh) over Ihe teet range from K. E. WURSTER NASA Langley Reseamh Centar, Hampton, VA Mach 20 to 0.3. At hypamonic speeds, the HL-20 model trknmed at a and H. W. STONE Journal of SpacecmfLand Rockets (ISSN 0022- ilft/drag (I/D) ratio of 1.4. This value gives the vehicle a cmesrange 4650) voL30, no.5 September-October1993 p.549-557 mrs capability similar to that of the space shuffle. At subsonic speeds, Iha (BTN-94-EIX94351137058) Cop_ HL-20 has a Mmmed L/D raUo of about 3.6. Replacing 1he fiat-plate Definitionof _he m)ro_hennal environment is critical to any vehicle outboard tine wilh fins having an airfoil shapa incmesed lhe n'mximum such as _e HL-20 Personnel Launch System that operates wilhin the subsonic Mmmed IJD to 4.2. Aulho((El) hypemonic fliom regim.. ,_ of an approprim U-_rn,mlpro_on system daslgn is highly dapandant on Ihe accuracy of lhe heating- A94-60396" National Aeronautics and Space Administration. environment Ixedic_. It is demonstrated that g_e entry environment Lang_ Research Center, Hampton, VA. datenrdnes the thermal _ system design for t_is vehicle. The SIX-DEGREE-OF-FREEDOM GUIDANCE AND CONTROL- methods used to predict lhe g_mzal envl_ lot the HL-20 ENTRY ANALYSIS OF THE HL-20 Pen,om_ Launch Sy,tem vehide are desc,t_d. Compedeo_ of e,e RICHARD W. POWELL NASA Langley Research Center, Hampton, engln_dng solutions w_ computatlo_ euld dynamlc _, ss VA Joumal of Spacecraft and Rockets (ISSN 0022-4650) vol.30, well as ,_r_d-_-r_r_l test re,tits, show gcod agresment. TI'_ _I/ng no. 5 September-October1993 p. 537-542 refs predictions over esveml cdUcal regions of _ vehlcls, including g_ (BTN-94-EIX94351137056) Copyright stegrmion erms of _e noes and leading edges, windward canterUne The ability of 1he HL-20 lifting body to fly has been evaluated for and wlng surfaces, and leeward surfaces, are discussed. Resul_ of an automated (no pilot inputs) entry from atmosphericInterlaceto predictions based on fire englnsedng me,hods found w_hln the MINI- landing. This evaluatk_ was required to demonstrate that not only VER aerodynamic heating code are used inconjunction wl_ lhe results 544 ASTRONAUTICS 10 ofthe extensive wind-tunnel tests on this configuration to define • flight The reduced mobility experienced while wearing the suits did increase thermal environment. Rnally, the selection of the thermal ixotec- egress times, although they still remained accepteble. The window I/on system based on these predic_ons and current technok3gy is arrangement for pilot viewing was found to be reasonably accepteble, described. Author (El) al_h slight modifications, such as an Increased downward view, is desirable. Author (El) A94-60399" National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. N94-35390"# National Aeronautics and Space Administration, HL-20 COMPUTATIONAL FLUID DYNAMICS ANALYSIS Wash_on, DC. K. JAMES WEILMUENSTER NASA Langley Research Center, AEROSPACE SAFETY ADVISORY PANEL Annual Report Hampton, VA and FRANCIS A. GREENE JoumaJ of Spacecraft and Mar. 1993 82 p Odginal contains color ill_ Rockets (ISSN 0022-4650) vol.30,no.5 September-October1993 (NASA-TM-109840; NAS 1.15:109840) Avail: CASI HC A05/MF A01; p. 558-566 refs 1 functional color page (BTN-94-EIX94351137059) Copyright The Aerospace Safety Advisory Panel (ASAP) provided overnight The sasan_ alemante of a comput_onal auid _ anely- on the safety aspects of many NASA programs. In eddilk_, ASAP sis of the HL-20/pemonnal launch system aeroU_rmal environment at undertook three special studies. At the request of the Administrator, the hypersonic speeds including surface definition, grtd generation, solu- panel assessed the requimmants for an assured crew ratum vehlde tion techniques, and visual representetk_n of results am presented. (ACRV) for _ space ste_n and reviewed _ organiz-tion of the F_xamp_of _uUon technk_uevalUaUonthroughcompar_e w_h safety and mt_don quality func_on within NASA. Atthe behest of data from ground-based facilities are presented, elong with mmJItsfrom Congress, the panel formed an independent, ad hoc woddng group to compute_ atmghtcund_one._ atnightpointeincUcate examine the safety and reliability of the space shuffle main engine. that rsal-gas effects have little or no effect on vehicle aerodynamics _ 2 prasants fmdinge and re(xxTtmendations. Section 3 consists and, at these conditions, results from approximate techniques for of Inlon_kx_ in support of these findings and recommandat_s. datermlning surfecs heaUng are comparable w_h thosa obtelned from AppandJcas A, B, C, and D, raspactlvety, cover the panel membership, Navier-Stokas sokJ_ns. Author (El) • e NASA response to the findings 8nd recommendatk_ns in the March 1992 report, a chronology of the paners asSvitias dudng the mpo_ng A94-60400" National Aeronautics and Space Administration. pedod, and the antim ACRV study mporL Dedved from text Langley Research Center, Hampton, VA. PRELIMINARY STRUCTURAL EVALUATION AND DESIGN OF THE HL-20 N94-35591"# Na_onalAeronaut_andSpaceAdmin_. Lewis Research Conter, Cleveland, OH. LANCE B. BUSH NASA Langley Research Center, Hampton, VA, CHALLENGING THE FUTURE - JOURNEY TO EXCELLENCE. JAMES C. ROBINSON, and DEBORAH M. WAHLS Journal of AEROPROPULSION STRATEGIC PLAN FOR THE 1990'S Spacecraft and Rockets(ISSN 0022.4650) vol. 30, no. 5 SepterrP ber-October 1993 p. 567-572 refe 1990 27p (NASA-TM-109250; NAS 1.15:109250) Avail: CASI HC A03/MF A01 (BTN-94-EIX94351137060) Copyflght Over the past several months, the Lewis AeropropuIsion Man- A lifting body concspt, the HL-20, was designed at NASA Langley agement Councll (AMC) has conducted a _ assas_nent of its Research Center, and a stn_m_ analym of the conjuration with a slrateglc plan. This assessment clearly indlcated a need forchange, cylindrical pressurized crew cabin was presented. Loads Ior the vehide I:x:fdlin the aeropropuisk_ pn)gmm emphaels and in the approash to were asaen_ed from mlsalon loading condltlons such as abort, on- csmAngouttimt program.Customerssanta strongmessagethatthe oroit pressu_, blaet overpmssure, aemdymm'_ maneuwr, and t0Ud'K:kXNn.The cfltlcal Ioeding _ were identified, and resultant i_oOmm n_m't improve U'm tinml_xmssof research and ixnduots _xl aervicss =nd must work morn c_osalyw,h them to develop loads were mapped onto the slnctum in oeder to rev_w the effec_ of and tnmsfer new _l-_oicgy. The s'_rategicplan de_nes AMC's vision the mission loading conditions. The HL-20 structural concept was ¢zedforthemim_n kinds,andthere_mng ¢_ctur_ w_ were for the future and uncle_ying organizational values. It c_ntalns a set of calcutatod. _ (El) broed stmteglas and actions that point the way toward achieving the goals of customer _isfec_on, orgertza_r_ effecUver_, and pro- A94-60405" National Aeronautics and Space Administration. gramma_c excslisncs.Thosa stmtegkm areex_ toformthebasis Leng_yResearchCenter,Hampton,VA _x thedevek_ ofspec_c tec_c_'pkms by Lewis aemeropu_on HUMAN FACTORS EVALUATION OF THE HL-20 FULL-SCALE thrustteams,dh_dons,and branches.To guide_ p_ng ofthe MODEL aeropropuhdon program, _ strategicplan ouffinesthe agency's s_ _rec_onsandk_g-range_ geeb,theaeropropu_on KELLI F. WILLSHIRE NASA langley Research Center, Hampton, a'_m, pro_ctkm of Law_ VA, LISA C. SIMONSEN, and WILLIAM L. WlU.SHIRE, JR. Jouma/ _s and key ot_'_vas _orachi_ng aempropulelon budgets, planned allocs_ons of resources, and the ofSpacecmftandRockets(ISSNO022-4650) voL30,no.5 Septmt. ber-October 1993 p. 606-614 ru4s procssses that will be used to measure su©csss in canying out the strm_ p_n. CAS_ (BTN-94-EIX94351137065) Copyright The human fectors tes_g of the HL-20 partmmml launch eystem full-scale model was conducted in both the ver_cal _cl hodzonlal N94-35605"# National Aeronautics and Space Administration. portions at NASA Langley Research Center. Three main areas of Goddard Space Right Center, Greenbelt, MD. test_ were considered: an anth_ m evalua_on, the ingress FMGHT MECHANICS/ESTIMATION THEORY SYMPOSIUM, and egress ofa 10-pamon crew, and pllot viewing. Tha_, 1994 ranging from the 5th to 95th parcsntile size, hed sufficientclaerancs in KATHY R. HARTMAN, ed. Washington May 1994 533 p themndal,_ the exceptk_nof the laettworowsof Nets andthe Sympo_um held in Greenbelt, MD, 17-19 May 1994 cock_ arae.Adjusteb_eaealhe_hteand/orplasemantof the seats (Contract RTOP 550-00-00) ferther forwwd would _ more headroom. In the hodzordal po_- (NASA-CP-3265; REPT-94B00060; NAS 1.56:3265) Avalh CASI HC ticn,themodeI'eaeatplacsm_ntandalelewldthalbweda quickand A23/MF A04 ordedy10-parsonegressfortheno-k_l (asln_ur_ supportrun_ng This conference publication inckKkm 41 papem and abstracts the_n_h onthealele),S-_.-h_hke_,and12-_.-hi0hk_ _. presented at _ Right Mechanics/E_mation Theory Symposium on Egress llmas were lass than 20 s. For the verllcal posltion, the moders May 17-19, 1994. Sponsoredby the F_t Dynem_ DiV,s_ of long cy#nddcsl m with ffm ladder in b'_ecslUng allowed a quick and Godderd Space Flight Center, this symposium featured technical orderly egress wtth average times less than 30 s. Ingress and egress papers on a wide range of issues related to orbit-attitude predictkm, procedures were demonstrated using shuttle pertlakpreasure suits. determination and control; attitude sensor calibration; attitude deteani- 545 10 ASTRONAUTICS nation error analysis; attitude dynamics; and orbit decay and maneuver A94-65348 strategy. Govemmant, industry, and the academic community pedlci- RAMAN MEASUREMENTS AT THE EXIT OF A COMBUSTOR pated In the preparation and presentstJon of these papers. SECTOR ANIL GULATI General Electric Co., Schenectady, NY Journal of Propulsion and Power(ISSN 0748-4658) vol. 10, no. 2 March-April N94-35880"# Nationel Aeronautics and Space Administration. 1994 p. 169-175 refs (ErrN-_,-BX_.q41338356) Cop_ght Langley Research Center, Hampton, VA. AN OVERVIEW OF RECENT ADVANCES IN SYSTEM Spontaneous Raman diagnostics are applied to the exit plane of IDENTIFICATION an elrcraft ec_ine cocrd_stor see'tothJeledwith both natural gas liquid JER.NAN JUANG In its NASA Workshop on Distributed Parameter fuel (kerosene). ProXies of tanlperatum and major species are obtained Modeling and Control of Rexib_e Aerospace Systems p 279-289 Jun. st the sector exlL The Rarnen mean temperature dsta agrees well with 1994 thence measurements at identical operating conditions. The Avail: CASI HC A03/MF A06 rms proxies show up to 12and 16% fltctuatlons in temperstum at the Thls paper presents an overview of the recent advences in system conte_ne of the burner with natural gas and kerosene, raspec'tMdy. identification for modal testing and control of large _exlble strictures. The mean profiles of major specias show the expected fronds. Upto6% Several techniques are discussed inducing the Obsenmr/Kairnan Filter unbumt oxygen is measured at the centerlina with natural gas. The Idenlfficalk3n, the Observer/Controller IclenlJ_:aJlon,and the Slate- corresponding value with liquidfuel is 8%. Profiles of unburned hydro- Space System Identlfx:a_on in the Frequency Domain. The System/ carbons, carbon_-_de, and hydrogen m the csnte_ne kc_ate ObserverlConVoiler Toolbox developed at NASA Langley Research Incomplete combuslon at the measurement plana as _ evidenced Center is used to show the appllca_ns of these techniques to reai by the vislb_ name emn_ng ¢OnilcanUy beyond the sector e_. aercspace structures such as the Hubble s_ telescope and _e ixoflles of nonnaUzed rms mole fractions of major specias are aiso active fle)dble aircraft wing. Author (revised) presentKl. Finaily, me Raman systsm Is applied m a room t,m_nermum cell at _ preuunm to extend the l_jstem to this regime. The Raman signals increase Xneady with pressure as expected. Author (El) N94-35902"# National Aeronautics and Space Administration. Lang_y Research Center, Hampton, VA A94-608_ SECOND INTERNATIONAL SYMPOSIUM ON MAGNETIC EFFECT OF COARSE SECOND PHASE PARTICLES ON SUSPENSION TECHNOLOGY, PART 2 FATIGUE CRACK PROPAGATION OF AN AL-ZN-MG-CU NELSON J. GROOM, ed. and COLIN P. BRITCHER, ed., May ALLOY 1994 258 p Symposium held In Seattle, WA, 11-13 Aug. 1993 Sponsored by NASA, Washington R. GURBUZ Middle East Technical Univ., Ankara (Turkey) and (Contract RTOP 233-03-01-01) S. P. ALPAY Scrlpta Metallurgica et Materlalia (ISSN 0956-716X) (NASA-CP-3247-PT-2; L-17369-PT-2; NAS 1.55:3247-PT-2) Avail: vol. 30, no. 11 June 1, 1994 p. 1373-1376 refs CASI HC A12/MF A03 (BTN-_-BX94301320144) In order to examine the state of technok_y ofall areas of rnagnatic The elrn of thle work is to dstmmina the role of the rnost_=mmonly suspension and to review related recent developments in sensors and obsewed cname second phase particles namely, AI7Cu2Fe, Mg2Si and _ on the stage 2 fatigue crack propagation of a 7050 tonY, s spproachas, superconducUng magnet technok_j, and de- aiumtmlm alloy, which is widely used in airframe construction. Fe- sign/knplementation practices, the 2nd Inte_ Symposium on Magnetic Suspension Technology was held m the Wse_n Hotel in containing N7Cu2Fe particles de not contribute beneficially to fa_gue Seaffie, WA, on 11-13 Aug. 1993. The symlx_um included 18 techni- life and slmngth of 7050 N-ailoy at the T73651 temper. El cal sessions in which 44 papers were presented. The technical mm- A94-60873 sions covered the areas of bsedngs, bearing mndelling, controls, RETAINED MECHANICAL PROPERTIES OF A NEW AL-LI-CU- vibration isolation, rnicromachines, superconductivity, wind tunnel magnetic suspension systems, magnetJcelly levitated trains (MAGLEV), MG-AG ALLOY AS A FUNCTION OF THERMAL EXPOSURE rotating machinery and energy storage, and applications. A list of TIME AND TEMPERATURE attendees appears at the end of the documonL A. P. REYNOLDS Anaiytical Services and Materials, Hampton, VA and D. M. ROYSTER Scrlpte Metallurgica et Materiafla (ISSN 0956-716X) vol. 30, no. 11 June 1, 1994 p. 1485-1490 refs 11 (BTN-94-EIX94301320164) Co_ght Presented is a cont_ study of the mechanical property CHEMISTRY AND MATERIALS steha_yofa new N-LJ-C_Ag alloy,RX818, a_r long term expo- sureto pmpcsed hlgh speed clvllmmspon servlce tmnpersturse. A 2.3 Includes chemistry and materials(general); composite materisb; inoc- rnm thick sheet In the T(sub 9) condition was used In this study. El genic and physical chemisVy; metallic matedais; nonntetallic materials; and propellants and fuels. A94-60892" National Aeronautics and Space Administration. Langley Research Cenmr, Hampton, VA A94-60275 FIELD DEPLOYABLE NONDESTRUCTIVE IMPACT DAMAGE TURBULENT COMBUSTION REGIMES FOR HYPERSONIC ASSESSMENT METHODOLOGY FOR COMPOSITE PROPULSION EMPLOYING HYDROGEN-AIR DIFFUSION STRUCTURES FLAMES JOSEPH N. ZALAMEDA NASA. Langley Research Center, G. BALAKRISHNAN Celifomia Univ., San Diego, La Jolle, CA and Hampton, VA, GARY L. FARLEY, and BARRY T. SMITH Jouma/ F. A. WILLIAMS Journal of Propulsion and Power (ISSN 0748- of Composites Technology and Research (ISSN 0884-6504) vol. 4658) vol. 10, no. 3 May-June 1994 p. 434-436 refs 16, no. 2 April 1994 p. 161-169 refl (BTN-94-EIX94321333324) Copyright (BTN-94-EIX94301321378) C_ Most designs of supersonic combusllon engines Involve turbulent A Wchnique le being devaioped for rapld in.servk_ detectlon and hydrogen injection into _ supersonic elmtmams in the conbustor quantltication of damage in composite airframe smJctur_ combining whlch leads to nonpremixed combusti_ reprseenta_ve of turbulent thermal and ulbasontc _ evaiua_n {NDE). Thermal flames. The present communication mlxxts the _ of inspeclon technlquas can be used to identify impact damage areas caiculations performed to determine the mg4rnesin which this turbulent because It is fast, inspecte lerge areas, and is noncontacting. Oncs an combustion is likely to occur. El area of concsm is idantifled, characterization of lhe depth and extent of 546 ENGINEERING 12 thedamagecanbedeterminedusingultmsonlcvolumel]'icimaging. Ioca_ons on two different yawed-cone models under venous angle-of- Ultrasonicvolumetricimagingquantifiesthedamagebygivingaply-by- attack conditions in two different experimental facilities and are verified. plyview of the damage. Single-sided measurements were made on two This correlation is only suggested as a tool for preliminary transition types of samples, fiat panels with through-the-thiclmees reinforce- prediction and design in thme-dimensfonaJ boundary layers; once a rnents and a 'Y'-stiffened sldn. These samples were impacted with an prsiiminmy shape is selected, furlhe r linear stabilitytheory or paraboiized aluminum ball at venous valodtJas. The thermal results were compared stability equation calculations am strongly urged. Author (El) with ultrasonic C-scans and the ultrasonic volumeUic results were compared with destructive tests. The thermal images compared well with the C-scan images in bothrelative size and shape. I1was found that A94-60017 SYMMETRY BREAKING IN VORTICAL FLOWS OVER CONES: the ulUasonic volumetric results gave a better indicatfon of damage THEORY AND NUMERICAL EXPERIMENTS than achievable with the dastructJve specimen evaluation method. It has been shown that a multldisoiplinapj approach using thermal and PETER M. HARTWICH Vigyan Research Associates, Inc., ultrasonic NDE techniques is an efficient and informative Inspection Hampton, VA AIAAJouma/(ISSN 0001-1452) vol. 32, no. 5 May method for identifying and quantifying damage. Author (El) 1994 p. 1013-1020 refs (BTN-94-EIX94301315981) Copyright A stability analysis suggests that invisdd incompressible flow, independent from angle of attack and regardless whether attached or N94-3S795 Galaxy Sdantific Co_., PleasanMlle, NJ. separated, over slender cones is only marginally stable in regions of UNLEADED AVGAS PROGRAM Interim Report decelerating clrcumfemn_al flow. Reducing slenderness or surface DAVID A'rWOOD, AUGUSTO FERRARA, and PAULA RINGEBACH curvature Iowem the frequency spectrum of the harmonic perturbations Mar. 1994 38 p Limited Reproducibility: Morn _ 20% of this and, thus, reduces their impact on the overall stability of flows over document may be affected by microfiche quality slender cones. Associating the no,on of instebilit]es in such flows with (AD-A278650; DOT/FAA/CT-93/65) Avail: Issuing Activity (Defense the onset of vortex asymmetries pmvidas a model for expleJning a Technical Infownatlon Center (DTIC)) variety of flow phenomena in Navier-Stolms sirnulalfons of laminar (Re The Federal Aviation Administration (FAA) Technical Center has sub I = 0.6, 1.2, and 2.4 x 10(exp 6); I is body length) incompressible pedormed extensive rasearch toward finding an unleaded flows over three dghtdrcutar cones (cone half-angle (delta) = 2.5, 5, and for the current leaded aviation gasoline for general aviation aimreft. 10 deg) at moderate to high angles of attack (alpha/delta = 1,2, and 3). Described in the report are tes_ng procedures, results to date, and Author (El) future testing plans. The tests include vapor lock behavior, perfor- mance, endurance, detonation analysis, material coaT)atibtlity, storage stability, vo_tility, emissions, water miscibility, and flight tes_ng. The A94-60027 volatility tests include Reid Vapor Pressure, distillation, and vapor to THREE-DIMENSIONAL CLOSURE OF THE PASSAGE- liquid ratio tests. The endurance tests involved periodic checks of AVERAGED VORTICITY-POTENTIAL FORMULATION cytinder wear, partJculady valve seat wear, leak downs to determine XUDONG ZHANG Ecole Polytechnique, Montreel, ANDRE cyflnder compression loss, and oil analysis. DTIC GARON, end RICARDO CAMARERO AIAA Journal (ISSN 0001- 1452) vol. 32, no. 5 May 1994 p. 1080-1083 mrs (BTN-94-EIX94301315991) Copyright Described in this paper is • modified three-dimensional model for 12 simulating the rotor-stetor interac_on flow. Fully three-dlmensional ENGINEERING ffowsare individually computed in the rotor and stetor blade rows of this model. El Includes engineedng (general); communications; electronics and elec- bical engineedng; fluid mechanics and heat transfer;,instnanontetion A94-60034 and photography; lasers and masers; mechanical engineering; quality NUMERICAL INVESTIGATION OF CYLINDER WAKE FLOW assurance and reliability; and stnJcturel mechanics. WITH A REAR STAGNATION JET J.D.MO MamphlsSteteUniv.,TNandM.R.DUKE, JR. AIAAJoumal (ISSN 0001-1452) voi. 32, no. 5 May 1994 p. 1095-1088 refs A94-60004 (BTN-94-EIX94301315998) Copyright TRANSITION CORRELATIONS IN THREE-DIMENSIONAL Wake flow characteristics, being a topic of interest for years now, BOUNDARY LAYERS create • considerable drag and an oscillating lateral force that causes HELEN L. REED Arizona State Univ., Tempe, AZ and TIMOTHY mechanical vt_ in the cylinder. The mechanics of the increasing S. HAYNES AIAA Journal (ISSN 0001-1452) voi. 32, no. 5 May form drag is addressed. El 1994 p. 923-929 refs (BTN-94-EIX94301315968) _ght The stability and 1mnsition characteristics of thme-dknensional A94-60039 boundary-layer flows are examined. Rrst, the flow over a rotating cone LOCALIZATION OF AEROELASTIC MODES IN MISTUNED is considered computationally. An increase of stagnation temperature HIGH-ENERGY TURBINES is found to be only slightly stebiti_ng. Parameter studies on _e simple CHRISTOPHE PIERRE Unlv of Michigan, Ann Arbor, MI, TODD E. rotating-cone geometry provide a large database of three-dimenslonal SMITH, and DURBHAV. MURTHY Journal of Propuision and Power boundary-layer profiles and assodated stability ctwac_dstics. To (ISSN 0748-4658) vol. 10, no. 3 May-June 1994 p. 318-328 rets determine the possibility of con'ala_ng _ Iocagon with param- (BTN-94-EIX94321333307) Copyright stem based purely on basic-state three-dt_ boundary-layer The effects of blade nislunlng on the aoroelastlc vibration char- profile charastedstics, an empirical Uansition kx:atk_ of N - 9 is acterlstics of hlgh-energy turblnas are investigated, ualng the tirst stage assumed. Traneitlon _ dnes not correlate wi_ the tmditional of the oxidizer tudx_xJmp in the Space Shuffle main rocket engine as crossffow Reynolds number. A more appropriate definition forcroasffow an example. A modal aeroelestic analysis procedure is used In concert Reynolds number is found and termed R(sub cf). This new parlm_ter Mth a lineadzad unsteady aerodynamic theory that accounts for the appeam fo correlate for tmr',_on location when plotted agalnet maxl- effects of blade thk::M'mss, camber, and steady loading. High sensitNtty mum croasflow velocity. Then, the flow over • yawed cone is consid- of the dynamic chamcterlelJcs of mistuned rotors is deaKxtslmted. In ered expedmantelly. The correlation results obtained from the parUcular, the aeroelestlc free vibra_on modes become localized to a rotating-cone work are applied to the actual measured tmnaltion few blades, possibly leading to rogue blade failure, and the locus of the 547 12 ENGINEERING aeroelesUc eigenvaJues loses its regular sbucture when smaJlmistuning Blackst_, VA. M. W. HYER, D. COHEN, M. J. SHUART, S. R. (of the order usually present in actual rotors) is I_. Perturbation YN.AMANCHIU, and C. B. PRASAD Jouma/ofSp_ocraflandRocke_s analyses that y(eld physical insights into these phenomena am pre- (ISSN0022-4650) vol.31,no.2 Mard_Apd11994 p.278-284 rets santad. A powerful but easily calcufstod stodlas_ sans_ivJty measure (m'N-94.EIX_43_ _330S_0) Copydght that allows the global prediction of mistunlng effects is develaped. A new numerical procedure for determining load proporlk)ning in Author (El) _r mechanical joints in composite plates is presented. The Jolntaare Ioeded in doul01elap teshion in tension with plns through the holes. The commercial finite element program ABAQUS is used to A94-60040 predict the load pro_ng among fasteners Using two independent AXIAL COMPRESSOR PERFORMANCE DURING SURGE plane stress fln_ element models, one mpresanUng _ composite I.J. DAY UnlvofC, ambridge, Cand)ddge, UnltKIKingdem Jouma/of inner lap and one representing the two steel outer laps, Interacting Propu/s/on and Power (ISSN 0748-4658) vol. 10, no. 3 May-June through rigid clrouku surlaces. The circular surfaces effectively mpm- 1994 p. 329-336 refs Sant dgtd pins. Load ploportl_ is pmdlctad for 8 number of geom- (BTN-94-EiX_2133330e) etries. Excellent comBle_n with expedmentaJ data is obtained. There is iinlitad infomlatl_ available In the Hteratum about Itow Exper_r_mt_and computed surfaces1_,,_nsareaisotound tocompare conditions in a,dal compressors during surge. This article presents well. The assumption of a rediaJcosine distribution of contact stress detailedmeasuremanW _n a k)w-mead tastdg k_urnanted Iopk:k between festaner and hole boundary, often used In these studies, is up detailsof axialand dn:_renUJ Wow disturbances.The results shown to be substantially in errorforsome holes. Author (El) show that surge is irdtleted by rotating stall, and that the etmuing surge c_ isa eaquence of wen ordered c_ evants.The dlflemrces In cycle behavior between 'classic surge' and 'deep surge' A94-_131 am investigated, and it is sho_ that the shape of the _ MEASUREMENT OF DIFFUSION IN FLUID SYSTEMS: charactaris_c determlmm which of _ willoccur. From the results, it APPLICATIONS TO THE SUPERCRITICAL FLUID REGION ts aiso conckxled that some imporlant factom, such as overall pmuure THOMAS J. BRUNO National Inst. of Standards and Technology, rise and size of hymmm k3op,have not roceived sufrclent altm_ Boulder, CO Journal of _ and Heat Transfer (ISSN in existing tacJ'rdques for predicUng the rotating stall/surge boundary. 0887-8722) vol. 8, no. 2 April-June 1994 p. 329-333 rels In line with then findings, an Appendix by E. M. Greitzer presents a (BTN-94-EIX94311330650) Copyright more general version of the 'B Parametar', which takes into account the The expedmantal procedures that am appllcaMe to the measure- irifluanco of compressar desion vedables on the 8tamng behavlor of the mant of diffusion in superarltk:al fluld sulu_ons are reviewed. Thls toplc compressor. AuU'_ (El) is of groat inlpotlance to the proper deign of edvanced alrcraft and turblne fuels, since the lueis on these alrcralt may sumetlmes operato A94-60043 under supercditcal fluid condltlons. More specifically, we will consider DYNAMIC AEROELASTIC STABILITY OF VERTICAL-AXIS measuremants of the blnary intaraction dlffusloncoefllclent D exp 12of WIND TURBINES UNDER CONSTANT WIND VELOCITY a _lute (spedes 1) and the eolvent (species 2). In thls dlscussion, the FRED NITZSCHE DLR-Inst of Aoroelesticlty, Goeffingen, Gor- supemrltlcal fluid is species 2, and the solute, spedes 1, wlll be at a many Journal of Propulsion and Power (ISSN 0748-4658) vol. I0, relaSvely low canclmlmlk)n, sume_Irnes approaching infinite dilution. no. 3 May-June 1994 p. 348-355 refs After 8 brief introduc'_ to h_e concept of diffusion, we will discuss (BTN-94-EIX94321333311) Copy,_ in detail tie use of chromatographic methods, and then bdefly treat The flutter problem associated wi_ the blades of a class of iiOht scattor_, nuc_or maoneUc resonance spectra, and p_ venical-a_s wind turbines called Dertleus Is studied in detail. The _. Author (El) spinning blade is supposed to be initislly curved in a particular m charactadzed by a stata of pure tendon at the blade cro_ esction. From this equilibrium poldtlon a three-dlmansional llnear pertufba_km psIm11 A94.(m137 is _rimlx_ to da_o the dynamic ao_c md_Ui_ of the INVERSE DESIGN OF SUPER-ELUPTIC COOLING PASSAGES I_ade in _e i_e_Nx;o of fmo _nd o?oed I_/m_u_ of the Roquot- IN COATED TURBINE BLADE AIRFOILS Lyapunov theory for periodic systems. Author (El) GEORGE S. DUUKRAVICH Pennsylvania State Univ., Unlvemity Park, PA and THOMAS J. MARTIN Jouma/of Thennophys/cs and Heat Transfer (ISSN 0887-8722) vel.8,no.2 April-June1994 p. _4,,,6(X_ t 288-294 rob LOW-NOISE, HIGH-STRENGTH, SPIRAL-BEVEL GEARS FOR HEUCOPTER TRANSMISSIONS (BTN-_-ED(94311330654) Copyr_ DAVID G. LEWlCKI NASA Lewle Research Center, Cleveland, OH, A hlghly accurata and relleble algod_m capable of pedom_Ing ROBERT F. HANDSCHUH, ZACHARY S. HENRY, and FAYDOR L automatk: inveme deign of cooW_ _ow pauam numbem, mabes, slzos, and locations Inside coetad solid objects has been developed. LITVIN Journa/ofP_andPower(ISSN0748.4658) vol. 10, no. 3 May-June 1994 p. 356-361 rids The Use has the freedom to ,q_eclfy arUtmry tan_peratures and heat (BTN-94-EIX94321333312) Copyright fluxes at the polnta on lhe outar sudace of the object, and either twnpemures or heat times on _e surfaces of _e yet unlmown coolent Advanced-deslgn spiral-bevel gears were tested in an OH-58D helicoptsr Imnemisaion using the NASA [email protected] Helk_r Tranmds- flow passages. The runber of passages required could be guessed aion Test Stand. Three different gear designs tasted Included: the and _ algorithm will automdcaHy _iminata the _ pes- agea. The method allom evan inexpedanced designem toachieve an current design of the OH-58D b'atwnluion; 8 hlgher4Uangth design at_maJ con_ura_n of coolant Ixu_ages in a eingle computer run themn'm as lhecurrantIx_tw_h a funWht radiustoreducegeartooth while smis_ng u_r-spedfled manufacturing conmdm that were bendingm (and thus.weight);and a k)wer-noisedesignthe incoq)om_edvie,, barrier func6on meU_. The optlmiza_ algod_ms asthe h_,_ but w,, modmed _ofh mom_sy to reduce _Tan_ arrorand holm. No_. qbr_, and too_ sVa_ tests used In b'dsinvome design code ware breed on gredlent search and on a modred New_n mamh. A Cmp_e method toreecaplngfrom k)c_' were parformed and eigni_J_ gear m and noles _ were achieved. Author (El) n_ has been kq_e,_ that_ofves sw_ betwean two d_ferent_ of_,eot_ve lur,clk_n.11",eo_drn_ vak,eo__he gradient _m_h I_r wu found usino a simple r_ of fl_ing A94-60101 ,_ hiohly -oc:urm op|Ina _rouoh ,_ set of I_s in the onat gunot_n/ ANALYSIS OF MULTIFASTENER COMPOSITE JOINTS search parameter plane, and seaidng out the value 1hat will generate O. H. GRIFFIN, JR. Virginia Polytechnic Inst. and State Univ., minimal error. Author (El) 548 ENGINEERING 12 A94-60139 9, no. 3 March1994 p. 6-11 CONJUGATECONDUCTION-CONVECTIONHEATTRANSFER (BTN-94-EIX94331335528) Copyright WITHAHIGH-SPEEDBOUNDARYLAYER This paper describes the Kaiser Electronics developed WIDE- FREDERICKL.SHOPEArnoldEngineeringDevelopmentCenter, EYE Helmet Mounted Display System that uses a Kaiser unique almmft ArnoldAFS,TN Jouma/of Themtophysics and Heat Transfer (ISSN retained unit/pilot retained unit (ARU/PRU) helmet display unit design. 0887-8722) vol. 8, no. 2 April-June 1994 p. 275-281 refs The overall system block diagram is presented and each major (BTN-94-EIX94311330652) subsystem is described in detail. Extensions to the basic design to add A space-marching boundary-layer program has been extensively full color capability am also described. Author (El) modified to modal conjugate conductfon-convecton heat transfer for the case of co-flowing high-speed gas and liquid coolant. Solid body cond_ is modeled as one-dimensional, constant property heat A94-60210 transfer. "The coolant is modeled empirically as a bulk fluid with FINDER, A SYSTEM PROVIDING COMPLEX DECISION combined forced convection and subcooled nucleate boiling. The flow SUPPORT FOR COMMERCIAL TRANSPORT REPLANNING solver was modified to solve the group of conjugats boundary equations OPERATIONS simultaneously and Implicitly with the exi_ng momentum and energy VINCENT BITrERMANN Commercial Avionics Div., Velizy (France), equations for the gas. The msultlng conjugate conducflon-convec_on GUY DEKER, PIERRE SASSUS, JEAN-CHRISTOPHE MIELNIK, and program has been applied to analysis of failure of a backside watar- JEAN-MARIE JUD IEEE Aerospace and EteclTonic Systems Maga- cooled nozzle for a high enthalpy, supersonic wind tunnel. The compu- ,_ne(ISSN0885-8985) vol. 9, no.3 March1994 p. 12-18 mrs tational results have been used to establish that the primary failure (BTN-94-EIX94331335529) Copyright mode is nudeate-boiling burnout and to propose a numedcal burnout Dedsion-ald systems, likely to appear in future almraft genera- limit applicable to the specific nozzle con_gumtk)n. Author (El) tiuns, could play a central role in the cockpit thanks to the broad spectrum of functhxm_es and decision support facil_es they will offer to the crew. As part of such systems, the exploratory FINDER mock-up A94-60161 is a knowiedge based system (KBS) designed to help crew members IN-FLIGHT VELOCITY MEASUREMENTS USING LASER continually optimize their flight plan by suggesting solutiol_ consider- DOPPLER ANEMOMETRY ing exhaustive into_ related to flight context, either on pilot H. W. JENTINK National Aerospace Lab., Amsten:larn, Ne_x)riands request or upon external information occurrence. The successful Anffiles, M. STIEGLMEIER, and C. TROPEA Jouma/ofAJrcraft(ISSN evaluation by Air France pilots of that first mock-up dedicated to 0021-8669) vol. 31, no. 2 March-Apd11994 p. 444-446 rets divemlon procedure on pilotrequest has led to the current development (BTN-94-EIX94311329139) Copyright of an enhanced system with nominal anroute opemtfone and real-time capabili_es. Nominal enrouts opem_ns concern the op_rniza_on w_ In Ibis study, the newiy designed Laser Doppler anemome_y respect to an evolulh,e constraining of favoring environment (due to (LDA) is used to measure boundary-layer profiles on a twin engine Falrchiid Sweadngen Metro II aircraft in flight. Demonslmted am the weather, trafficor regulated areas, and ETOPS constmlnts). This study potentials of the technique for in-flight appllcatlons. Also described am paves the way for 8 future flight assistant system concept which is the operat_al aspects of the equipmenL El already under inves_gatiun and may take place in SEXTANT Avioniqua's future development steps. Author (El) A94-60175 A94-60256 COMPUTATIONAL ANALYSIS OF OFF-DESIGN WAVERIDERS SHEAR BUCKUNG RESPONSE OF TAILORED COMPOSITE X. HE Oldahoma Univ., Norman, OK and M. L. RASMUSSEN PLATES Jouma/ofAJrcraft(ISSN0021-8669) veL31,no.2 March-Aprll 1994 SHERRILL S. BIGGERS Clemson Unlv, Clemson, SC and p. 345-353 refs STEPHANE S. PAGEAU AIAA Journal (ISSN 0001-1452) vol. (BTN-94-EIX94311329125) Copyright 32, no. 5 May 1994 p. 1100-1103 raft; Comprehensive inviscld and viscous numerical simulations of (BTN-94-EIX94301316000) Copyright hypersonic flow past nonconical _ waverldars are pre- The plecewise-unifonn approach to tailoring as a means of sented. The flowfields and asrodyrwnic forces at off.design conditions improving the shear buckling loads of composite plates is evaluated. are determined inviscidly by a space marching CFD code wilh the initial The pdmery objective is to determine the tailoring patterns and date plane provided by a time marching Naviar-Stokes CFD code. Off- degree of concentral_n of t_ material used. El design conditions include off-design Mach numbers, angles of attack, and rounded leading edges. A wide range of waveddar contig_ is investigated and compared. On-design viscous flows past a waveddar A94-60_P_ with a sherp leading edga at M(sub irdbdty)= 4 and at different Reynolds STRUCTURE AND PENETRATION OF A SUPERCRITICAL numbers and temparatum boundary condilfons am obtained by a time FLUID JET IN SUPERSONIC FLOW marching Navfar-Stokes solver. These calculations show the effects of J. C. HERMANSON United Techndogies Research Cent, East viscous interactions, which are influential near 1he leading edges, and Hartford, CT, United Steres, P. PAPAS, and I. W. KAY Journal of determine the viscous drag. The inviscid _ show that L/D Propu/s/on and Power (ISSN 0748-4658) vol. 10, no. 3 May-June decreases as M(sub infinity)increases (withalpha = 0). At the on-design 1994 p. 387-394 refs Mach numbers, the ma.x_¢_ IJD may occur st slight _ or (BTNo94- EIX94321333317) negative alpha, depending on the sllapa of the wavedder, and zero lift The penetration chamctaris_cs and turbulent stnJctum of trans- occurs at a negative alpha ap_ eClUal to half of the body verse supe_ rdtrogan (and mterenoe subcooled liquid ethanol) thickness. The effects of slight leading-edge blunting produce only local jets worn examined experimentally by the use of spark shadowgraph effects in the flowtiald and small losses in LJD. The dmractem of the imaging. For givan injection and freas_eam stagnation pressures, Ifowtialds in the base plane are illuslmtsd. AuIhor (El) suparcrltical nitrogen jets panetmted slgnif_-.anb'y less into the super- sonic stream than subccoiad ehmol jets. The jet panatratlon furlt_er demeaesd with increases inthe degree of suped'leaL The supemriticel nitrogen jets were charactedzed by large-scele structure not generally WIDE-EYE (TM)/HELMET MOUNTED DISPLAY SYSTEM FOR observed for the case of subcooled ethanol injection. Practical difficul- ROTORCRAFT APPLICATIONS ties inherent in the use of liquid fuel slmulants in unheated supersonic LOGAN R. ZINTSMASTER Kaiser Electmrics, San Jose, CA IEEE flows for the simulation of supersonic combusl_on environments are Aerospace and Electronic Systems Mag_ne (ISSN 0885-8985) vol. discussed. Author (El) 549 12 ENGINEERING A94-60335 ROBERT E. FIELD Northem Illinois University, DeKalb, IL and STRUCTURAL INTEGRITY AND CONTAINMENT ASPECTS OF RAYMOND VISKANTA Joumal of Thennophysics and Heat Transfer SMALL GAS TURBINE ENGINES (ISSN 0887-8722) voL 7, no. 4 October-December 1993 p. 616- S. S. GUPTA Pratt & Whitney Canada and R. GOMUC Canadian 623 refs Aeronautics and Space Journal (ISSN 0008-2821) vol. 40, no. 1 (BTN-94-ED<943S1142128) Cor_ght March 1994 p. 19-26 refs ,S_ materials, such as glass, hava many applica- (BTN-94-EIX94331337500) Copyright tions In Ngh-temperatum environments such as supersonic aircraft Stncturai integrity of rotating components In gas turbine engines canopies and spacecraft windows. At elevated temperatures the is vary crucial since their failure implies hlgt_Impact energy, which, ff energy lmnefer within semitransparent rnatedais Is domlnated by urlcontained, could mean damage to aircraft structures, controls, and radiatlen, maidng both the predlctlon and measurement of Intemai so fodh, and, in the worst scenario, even loss of lives. ThJs final temperatures substantially more difficult than for opaque substances. consequence has led to very stringent airworthimms regula_ns for Expedrnentai meesumment of the dynamic internal temperature disffi- engIne/aircraft carlJflcations. This paper discusses the htModcai ste_- Ix_on in soda-lime glass plates cooling from an initial ten'hperatum of of nonconteinment events intulbofane, turboprops, and turboshafts approximate_ = 550 C has besn perlonned. Tha boun_ry condillo_ and shows how the damage severity varies between different applica- on the plates wem established using the lebomtory mnblent for the front surlaca end emptoying a radmnt haater at the rear surlace. Tha surface tions and how changes to regulatJoneare continuing In order to Improva the rellabUity of aircmft/rotorcraft. The paper also presents design and internal plate temperatures ware measured using thermocouples ch_kmgesre_._ng fromthe ana_ compk.Cyof centekw.mV f.md Inthegins.Thatempenm'edm arecompmdto pred_lons noncontainment event and the way Pratt & Whitney Canada design/ obtsined from the solution of the tnmelent energy equeion wham the internal radiative tmnefer has been accounted for using dgnrous ana_e/teat system caters to all _ requimrnents. The weight and coat impactof possiblechangestocurrentregulaeonearealsoi_m)ntsd. radiative transfer theory. The predicted and measured temperatures, Author (El) expedmentel me1"KJd,procaes uesd to fuse the thennocouples In the test plates, and the fomtulatk_ of the energy _ forsernitmnsper- ent materiels am discussed. Author (El) A94-6035_ NatienaiAe_endSpacaAdmt_. Lewis Research Center, Cleveland, OH. APPROXIMATE SIMILARITY PRINCIPLE FOR A FULL-SCALE A94-60951 STOVL EJECTOR PROCESSING YTTRIUM BARIUM COPPER OXIDE WENDY S. BARANKIEWICZ NASA Lewis Research Center, Cleve- SUPERCONDUCTOR IN NEAR-ZERO GRAVITY land, OH, GAIL P. PERUSEK, and MOUNIR B, IBRAHIM _of DONALD R. PETI'IT Los Alamos Na'd. Lab., Los Alamos, NM, Propu/s/on and Power (ISSN 0748-4658) vol. 10,no.2 _Apdl DEAN E. PETERSON, KIMBERLY A. KUBAT-MARTIN, JOHN J. 1994 p. 198-203 rids PETROVIC, HASKELL SHEINBERG0 YATES COULTER, and (BTN-94-EIX94341338360) Cop_ DELBERT E. DAY Joumal of Crystal Growth (ISSN 0022-0248)vol. Full-scale ejector experiments are expensive end difficu# to 139, no. 3-4 May 2 1994 p. 302-308 refs implement at engine exhaust temperatures. For _ reason the utility (BTN-_4-BXS_,311332378) ofuCng_m,a_y wvx:_, In par_w the Munkendp_mp_nc_e The effects of processing YBa2Cu30(x) (Y123) superconductor for iesnVopic tlow. wes exptored. _ performarce test data for a full- In _e near-zero gravity (0 g) environment provided by the NASA KC- scale thrust augmenting ejector ware analyzed for pdmary flow Win- 135 airptene flying on parabolic Vajectodes were studied. A new sheet pemtum up to 1560 R. At diffenmt pdma_ temperatures, exit premium float zone furnace, designed for this study, enai_ed fast temperature contoum were compared for simiJarity.A norKIbnem_nel flow _ _. Up to en 18 g sample wes prcceesed wilh each parabola. eter is then used to eliminate pdmmy nozzle tmnpemtum dependence Sampkm of Y123 were processed as bulk sheets and and varlfy elrnilKfty betwesn the hot and cold Itow expedmente. Under conteining Ag end Pd. Tha 0 g procesesd samples were mul_ yat the assumption that an appropriate simlk, W prindple can be estsb- retained a localizedY123 etolctl_n_try where a single ground-based lishecl, properly chosen perlormanoe parameters ware found to be (1 g) oxygen anneal at temperatures of 800 C mcovamd nearly 100 similar for both flow and cold flow model tests. Author (El) vol% supe_ng Y123. The 1 g processed control samples remainedmula-pheseafterthe esme_ annealwnhlees A94-60412 than 45 vol% es superconducting Y123. The _g transi- NATURAL CONVECTION IN A CAVITY WITH FINS ATTACHED tion tmnperatum wes 91 Kfor both 0 g end 1 g prccaesed samples. Melt TO BOTH VERTICAL WALLS toxtudng of bulk Y123 In 0 g produced aligned gmJne about a fac'lorof GEORGE N. FACAS Trenton State College, Trenton, NJ JounW of three larger than in analogous 1 g rumples. Trensport-critlcai current ThermophysicsandHeat Transfer(ISSN0e87-8722)voL7, no. 4 denaitles wore at or below 18 A/sq cm, due to the _ of cracks October-December 1993 p. 555-560 refs caused bythe rapid heating rotes required bythe short time at0 g. Author (El) (BTN.94-EIX94351142119) Numerk_ calculatkx_ m presented for two-dimeneion_ naturai _ flow Insk:leen air-filled clwity wlth fl_ - of lenglh 0.1, N94-34581# Adv_ Group for Aerospace Research end Devalop- 0.3,and0.5ofthecavW/w_th-attB:hadekingboththeheatsdandme rmmt, Neuilly-Sur-Saine (France). Sbuctures and Materials Panel cooledOde of the cave. Tha govan_ngeque_0min the m_wn AN ASSESSMENT OF FATIGUE DAMAGE AND CRACK function-vortidtyformula_enaresolvedusingfinitedifferences.The GROWTH PREDICTION TECHNIQUES [L'EVALUATION DE Amkawa differendng scheme is used to repmesnt the conveclk_ L'ENDOMMAGEMENT EN FATIGUE ET LES TECHNIQUES DE terms. Row chamcmdstlca are Invastlgat_ for thres baffle leng_s and PREDICTION DE LA PROPAGATION DES FISSURES] G_ numbem In the range of 9.0 x 10(exp 3) to 1.0 x 10(exp 5). A Mar. 1994 278p 77_MestinghaidinBordeau_,Fmnoe, 29-30 _ flow structure le found to exlet for a be_fle length of 0.1. Sap.1_3 Howevar, when the baffle length is equal to 0.3 or gnmm', the fluid fON (AGARD-R-797; ISBN-e2-835-0734-7) Copyright Avail: CASI HC breaks down into es(xxx_,W ci_ addi_n to the IxtmW A13/MF A03 ci¢,,_ion-.enda_t, InUn, meresinh_harhintnnmr ram acro_ Fatigue is an Important conelderat_n in sthx:tuml design and the two lkles of the cadty. Author(El) rnon_ng of continued alnvorlldmms of militaryaircraft.This Work- titled 'An Aesemm_nt of Fdgue Damage and Crack Growth A94.60421 _ Techniques' pme,tdeda forum for an in-depth _ of MEASUREMENT AND PREDICTION OF DYNAMIC the cun,elatlon betwesn In-esrvlca experience end results frornenaly_ TEMPERATURES IN UNSYMMETRICALLY COOLED GLASS cal _ modais, q_cimen leval tests, co_ teats, end full- WINDOWS scale tests. Additionally, it made possible an examination of 550 ENGINEERING 12 operating standards that different countries adopt with respect to Copyright Avail: CASl HC A03/MF A03 various elements in the design process for assessment of fatigue In this paper the methods used for calculating the fa_gue life of damage. metallic dynamic components in rotorcraft is reviewed. In the past, rotorcraft fatigue design has combined constant amplitude tests of full- scale parts wflh flight loads and usage data in a conservatk, e manner N94-34586# Plea Univ. (Italy). Dept. of Aerospace Engineering. AN ASSESSMENT OF FATIGUE CRACK GROWTH to provide 'safe life' component replacement times. This is in oontrast to other industries, such as the automobile induslw, whore spectnJm PREDICTION MODELS FOR AEROSPACE STRUCTURES loading in fatigue tes19_ is a part of the design procedure. Tredil_lally, A. SALVETI'I, L. LAZZERI, and A. PIERACCI In AGARD, An the linear cumulates damage rule has been used in a deterministic Assessment of Fa_gue Damage and Crack Growth Prediction Tech- manner using a conservative value for fa_gue snngth based on • one niques 17 p Mar. 1994 in a thousand probability of failure. Conservatism on load and usage are Copyright Avail: CASI HC A03/MF A03 also often employed. This procedure will be discussed along with the The current state of crack grow_ prediction models foraerospace cummt U.S. Army fatigue lifespecification for new mtomrafl which ls the 8ppllcs_ns is reviewed with speciel reference to IknitatJons and so-called 'six nines' mliabilily reqt_rement. In order to achieve the six possible improvements. The present work elms at examining the nines reliability requirement the exploration and adop_n of new different crack growth prediction models with mfemncs to effective approaches in design and fleet management may elso be necessary if applicatlon for practical use (i.e. with the objective of identifying the nKluirement is to be met with a minimum impact on sh'ucturaJ experlmantel deta necsssary to apply the model) and at quantlf_ng the welghL To this end a fracture mechanlcs approach to fatigue life design reliability of the different models. Bo_ crack growth predic_ models may be required inorder to provide a morn accurate estimate of damage currency used by aerospace industries and prediction _ under progression. Also reviewed in this paper is a fracture mechanics development w_hin the scientificcommunity are considered. An experi- approach fix calculating tot_ fatigue life which is based on a crack- mental program has been carried out to help achieve the obj. closure small crack considerations. Author (revised) N94-34721°# Washington Univ., Saint Louis, IVlO. N94-34587# McDonnell-Douglas Coq)., Saint Louis, MO. COMBINED LAURA-UPS SOLUTION PROCEDURE FOR A COMBINED APPROACH TO BUFFET RESPONSE ANALYSES CHEMICALLY-REACTING FLOWS M.S. Thesis AND FATIGUE UFE PREDICTION WILLIAMA. WOOD 6Jun. 1994 78p J. H. JACOBS and R. PEREZ In AGARD, An Assessment of Fdgue (NASA-TM-107964; NAS 1.15:107964) Avail: CASI HC A05/MF A01 DamageandCmckGrow_P_Technklues11 p Mar. 1994 A new procsdum seeks to combine the _n-layer Nsvter-Stokes Copydght Avail: CASI HC A03/MF A03 solver LAURA with the paraboltzed Navlsr-Stokes solver UPS for the Expedmental measurement and neural network based preclic_n aerothermodynam_ eolu_n of chemlcaily-reacting air nowltelds. The of wind tunnel model empennage nmdom pressures are discussed. interface protocol is presented and _ meb_:l isapplied to two slender, Arffik_ly generated neural network power spec'tmldensities of sudace blunted shapes. Bo_ ax_ymmat_ and three dimensional sofu_ns pressures are used to augment exlstlng data and than Ioed an elastic are included wi_ surface prossum and heat transfer comparisons finite element model to obtain response speclm. Datells on the use of between the present method and previously published results. The actuel response speclm from flight tsst data are also dlscussed. A caseofMach2Sflowoverana.,dsymmeVicelxdegreesphere-conewt_ random specn latlgue rneU_xl is described which effectively corn- hines buffet and maneuver loads Into a time series based on aircraft a noncstalytic wall is considered to 100 nose mdU. A stebity bound on the man.rig step elzo wss obeorved wflh Uts csse and ls _ to usage data. A peak-valley damage analysis procedure is errcloyed to chemlstW effecls resulting from the noncatalytic well boundew condi- compute the aggregate fatigue llfe of the slnJctum based on five _n. A second case ,.eth Mach 28 now ovor s sphere<:one-_inder- combined load time series infon_tion. ApplicaUons of the mathod as 1hueconfiguration is cumputed at bofh two and rN0 degree sngles of s continual learning tool for buffet response spectra is elaborated. atlack w_ a fully<:atalytic wall. Surlace pressures are seen to be wflhin A._ (revised) fNe percsnt wi_ the present method competed to the baseline LAURA solution and heat lmnsfers me within 10 percent. The effect of grid resolution ls Invest_ated and the nonequilibdum results are compared N94-34588# Deutsche Aerospace A.G., Munich (Germany). Military wflh a perkJct gas 8oiution, showing that while _ surface pressure is Aircraft Div. relatively unchanged by the inclusion of reacting chemistry the NOTCH FATIGUE ASSESSMENT OF AIRCRAFT nonequ_ibdumhea_ngis25 percenthigher.Theproceduredemon- COMPONENTS USING A FRACTURE MECHANICS BASED slrates elgnik:ant, on_er of magnilude reductions in _ time and PARAMETER required memory for the three dimensional case over an 811thln-Jsyer CHR. BOLLER, M. BUDERATH, P. HEULER, and M. VORMWALD In Navler.Stoku suiution. Author AGARD, An Assessment of Fatigue Damage and Crack Growth Pmdicti_ Technlques 16 p Mar. 1994 N94-34722"# National Aeronautics and Space Administration. Copydght Avail: CASI HC A03/MF A03 Lang_yResearchCenter.Hsmp_, V_. Fatigue llfo evaluation has been perfomled fix flight-by-fllght DESIGN ORIENTED STRUCTURAL ANALYSIS loeded coupons and real alrcmft _ components mede of 7075- GARYL. GILES Jun. 1994 12p Proposed for presantation at the 1"/351 using the IocaJstrain approe_ and e hacture mechanlcs based Second International Conference on Compulational SInJctures Tech- parameter. Re_lts show that _s approach can well compete with the nofogy,_, Gamcs,30Aug.- _Sep.lg94 tradltlonaay used nominal stress approach. The advantages are a (Contract RTOP 509-10-11-02) better understm_ing of material's fatigue behavior and a less experl- (NASA-TM-109124; NAS 1,15:109124) Avail: CASI HC A03/MF ,6,01 mental effort required forthe detennlnatlon of besellne deta mal_g the De_rabie characteristics and banatits of design oriented analy_s local strain approedl Interesting also for redeJgn wi_in aircraft told-life methods m desodbed and Hlmlnm_ bypresan_ng a synop_ descdp- mxove_ .pda_ tk_nof the _ and urns of the F.quh_ent _ Pine Solution (ELAPS) computer o0de. ELAPS is a design odent_ slnJC- N94-34,_)_# /umy Vehicle Strictures Lab., Hampton, VA. turid anaJylds msl_ho:l which ls intlmded lot use in the early design of ROTORCRAFT FATIGUE LIFE-PREDICTION: PAST, PRESENT, elrcraft wing structmes. Model ixepera_on ls mlnin/zed by using a few AND FUTURE targeplatoseTnenteto modelthe wingboxstru:Ue.Comp.tmior._ RICHARD A. EVERETT, JR. and W. EI.BER InAGAFID, An Assess- er_-y isachievedbyusing• JJmi_odnumberofglobal chplacemant ment of Fatigue Damage and Crack Growth Predict_ Techniques funclJons that enc(xnpess all sogmants over the wing pter_orm. Cou- 31 p Mar. 1994 Sponsored by NASA. Langley piing wlth o'd'mrcodes is fadlitated since the output quanti_s such as 551 12 ENGINEERING deflections and stmssas am calculated as continuous functions over effects are Included; and to show that spedal trea_nant of the time- the plate segments. Various aspects of _ ELAPS devek:q)n_nt are derivative of the normal velocity is needed to allmtnate the ill-posed discussed including the _ fonTcia_on, veriflcsUonof results by solution behavior, which is observed when small spatial and temporal compmison wlth finite element analysis results, coupling with other step sizes are used. Author (revised) codes, and calculation of sansit_ dedvatlves. The effectiveness of ELAPS for multidisciptinary design application Is i11_ by dascdb- Ing itsuse in design studies of high speed civiltnmsport wing structures. N94-35074" National Aeronautics and Space Administration. Author Langley Research Canter, Hampton, VA. ACTIVE THERMAL ISOLATION FOR TEMPERATURE RESPONSIVE SENSORS Patent N04-34966"# National Aaronautk:s and Space Adrnin_. Ames SCOTT D. MARTINSON, inventor (to NASA), DAVID L. GRAY, Research Center, Moffatt Field, CA. inventor (to NASA), DEBRA L CARRAWAY, inventor (to NASA), PHYSICS OF FORCED UNSTEADY SEPARATION andDANIELC.REDA, Invantor (to NASA) 17Mey1994 8p Rled LAWRENCE W. CARR, ed. Mar. 1992 328 p Wmkshop held in 2 Jan. 1992 Supersedes N92-29954 (30 - 20, p 3446) Moffett Raid, CA; sponsored by AFOSR and ARO (NASA-CASE-LAR-14612-1; US-PATENT-5,311,772; US-PATENT- APPL-SN-820431; US-PATENT-CLASS-73-147; US-PATENT-CLASS- (Contract moP 5o5-59-53) 73-204.18; INT-PATENT-CLASS-G01F-1/68; INT-PATENT-CLASS- (NASA-CP-3144; A-91055; NAS 1.55:3144) Avail: CASI HC A15/MF A03 GO1M-9/11) Avail: US Patent and Trademark OffK_ The detection of IIow tmnsi_on betwasn lamimu and turbulent This report conteins the procsedings of a wod_ held at NASA Ames Research C4mter in April 1990. This workshop was jointly now and of shear slmas or sidn friction of airfoils is important in basic organized by NASA, the Air Force Oflk_ of Sclan_flc Research research for vallde_on of airfoil theory and design. These values are (AFOSR), and the Amly Raseamh Oflk_ (ARO), and was directed convanllonally measured using hot film nickel sensors deposited on a towan:l improved understanding of _ physical prcx:easas that polytmlde sube_te. The substmte electrically insulates the sensor unsteady separation to occur. The proceedings (xx_dn the wrltlen underlying alrfoll but is prevented from thermally isolating _ sensor by cor_but_ns for the workshop, and Indude ealected viewgmphs uud thlctmeas conatndms necessary to avoid flow conteminatlon. Proposed in the various presentations. heating of the model surface is difficult to control, requires significant energy expenditures, and may alter the basic flow state of the airfoil. A temperalum responsive sensor is located in the alrltow over the spedlkKl sudacs of a body and Is mainlined at a constent temperature. N94-3497r# _ Missiles and Space Co., Sunnyvale, CA. An actlve thermal Isolator is located between this temperature raspon- WILL THE REAL DYNAMIC INSTABILITY MECHANISM PLEASE sire sensor and the spedllc sudacs of the body. The totel thlcknass of BE RECOGNIZEDI the Isolator and sensor avoid any contemination of the flow. The L. E. ERICSSON In NASA. Ames Rasasmh Cen_r, Physics of temperature of this isolator is controned to reducs con(3ucthmheat tiow Forced Unsteady Sepemtion p 163-175 Mar. 19g_ from the temperature rasponsNe sanso_to the body. Thls temperature Avail: CASI HC A03/MF A03 control Includes (1) operating the isolator at fire same temperature as There Is a dchnass of tlow mechanisms that csn cause dynamic the constant temperature of the sensor;, and (2) establishing a fixed instability. Only after asking the right questions and carefully consider- boundary temperature which is either less than or equal to, or siighSy ing the answers can the fluid dynamlc sourcs of the obasnmd dynamic greeter _ tho Nneor constant temperature. The present Invention instability be recognized. This is illustrated by two carefully chosen ascordingly thermally Isolates a temperature responsive sensor in an examples. Auger energy effidant, controllable manner while avoiding any contemination of the flow. Ofl_al Gazette of the U.S. Patent and Trademark Office N94-34980"# United Technologies Research Center, East Hartford, CT. DEPARTURE SOLUTIONS OF THE UNSTEADY THIN-LAYER N94-35224"# NYMA, Inc., Brook Park, OH. AND FULL NAVIER-STOKES EQUATIONS SOLVED USING DATA REDUCTION PROCEDURES FOR LASER VELOCIMETER STREAMLINE CURVATURE BASED ITERATION TECHNIQUES MEASUREMENTS IN TURBOMACHINERY ROTORS Final M. BARNETT, D. TURNER, and A. P. ROTHMAYER In NASA. Roport Ames Raseamh Center, Physics of Forced Unsteady Sepemtion JANLEPICOVSKY Jui.1994 11p Prasantedatthe7thlntematlonal p 209-218 Mar. 1992 Sponso_:l in part by NSF Symposium on ApI_ of Laser Techniques to Ruid _, Avail: CASI HC A02/MF A03 Lisbon, Portugal, 11-14 JuI. 1994; sponsored by ADIST, CML, The dev_opment of a thoroughunderaten_ng ofthe ,mcha- CTAMFUTL, Direccao Geral de Turismo, European Research Office, _ foevom_ eru_Dtk_nmhorn viscous layars, which are I)siioved _ be United Stetas Army, Navy and Air Fon:_ Depte., Fta_dasao Calouste associated w_ _ such as dynan_ stell onast and tmnsitk_, Gulbanldan, FLAD, IST, ITEC, JNICT, and TAP - Air Portugal is crucial if accurate models of such phanomana are to be Iormulated. (Contract NAS3-27186; RTOP 505-62-20) •t_ deve0og_mantof such modeis may, in turn, alb_w got tho po_U_y (NASA-CR-195343; E-Sg20; NAS 1.26:195343) Avail: CASI HC A03/ hit suct_elVects _ be accourl_ed gordudng tho design of verious MF A01 aerodynamic devices such as wings, helicopter rotors, and Blade-to-blade velocity distributions baud on laasr valodmeter turbomachinery bladtng and thus lead to designe whlch are stelHras or data acquired in compmsmr or fan rotors are Increasingly uasd as stall resistant and which have be_r stelkmcovery properties. The _ for the vedtica_kx_ and celi_ of Ut)ornadW_ery pmsant Invastlgatk_n _ _ conc_Jctedas I_a-I of .._ _dfort _ devalop con_ n._ dyr_ (CF_) codes. Using _=er Dormer v_ mmlytical taxi numrter_ tools which can be used Io beip improve our moWr (LDW deta kx this puq_, however, must be done csutio_mly. undmtm_ ofthe vor_-anJpt_ m=chan_m =' h_h Rma_ Anldo Ir_ tho s_lhmt lully rasofved i_ of tho soed i_tido rOSl_ numbers. The addWon of Ihe _ equat_n m b_e knc(xnlPlexflmAdlalds,them is an impommt _hamm_ diffs_rancs beLween da_c_ unmedy boundeW4W_r equa_m is m=_ a=ond_ng _o CFD ;ndlctions and LDV blade-to-blade velocity dlstdbutlons. CFD recs.tas_._oec anat.,asofthe_o,tex-e,_ prouem and isa _ codes cslculme velodty flalds for an Idealb,.edre|or peseage. LDV dat_ _ea_.reofthe anm he,no _ by the prasant_. The on the o_er hand, stem hem the astual geon_ of all bledo channels purpose of t_s paper isas follows:to deasr_e departureediut_n ina rofor.The geomelry oflan vedas from _ to channel as a rasult behavior observed when using unsteady, s'a_mn_ne-curv_Jre based of manufacludng tolerances, assembly tolarancas, and incurred opera- solution procedures in which nontdvial transverse preasum gradient _onal damage or changes in 1he rotor individual blades. Author 552 ENGINEERING 12 N94-35226#JointPublicationsResearchSer_ce,Arlington,VA. wave numbem of longitudinal vortices and features of the flow in a JPRSREPORT:SCIENCEANDTECHNOLOGY.CENTRAL supersonic stream; numerical calculation of the three dimeneioneJ EURASIA laminar compressible boundary layer on contoured delta wings with 9Mar.199446p Transl.intoENGLISHfromvariousRussianar6clas supersonic leading edges; eisclm-eroaion machining inaviation engine (JPRS-UST-94-006) Avail: CASI HC A03/MF A01 construction; study of the development of turbulence in the region of a Translated articles cover the following topics: elactrophysicai break above a bianguterwing; opUcai reconslzuctlon of microwave properties of heterogeneous composites in high-frequency region of hoiograms; conetmints on paramatars of ItNmmticaJ rnodel of _ of aiectmmagnetic field; Zont-M helicopter deck landing signal generating Mai bodies in satellite experiment for refining value of gra_ system; ratdevai of geopomntlal and temperature fields by radio constant; eslmgen(k)tlc network at beginning of thin:l millennium; measurement method for model of general circulation of atmosphere: prospects and problems in remote sensing of earth; cltgitelmapping and computation method; global climate observing system; refiectkxn of geoinformatlon systems; new generation of equipment for mateoroiogi- internalwavepacketsfrom planedgldboundary;vorticalsystems caJlab aircraft; and geological factors in global changes: importance of behind cylinder in continuously stratified fluid;_res-dimenaiorml prob- catastrophes and pedodidty of processes. Author lem of flow of multilayar fluid of finite and Infinite depth around source; energy iossas in ra_ of gravity waves accompanying characterb- tics of submerged body;, and anomalous frequency dispersion of N94-35500"# Aubum Univ., AL. Dept. of Mechanical Engineering. internal waves in ocean. Author INFLUENCE OF BACKUP BEARINGS AND SUPPORT STRUCTURE DYNAMICS ON THE BEHAVIOR OF ROTORS WITH ACTIVE SUPPORTS Annual Status Raport N94-35342# Joint Publ_ Research Settee, Adlngton, VA. GEORGET. FLOWERS Jun. 1994 25 p JPRS REPORT: SCIENCE AND TECHNOLOGY. CENTRAL (ContractNA(_-I S07) EURASIA (NASA-CR-196119; NAS 1.25:196119) Avail: CASl HC A03_F A01 10 Feb. 1994 78 p Transl. into ENGLISH from vadous Russian arllcles Progress over _ past year Includes the following: A simplified (JPFIS-UST-94-005) Avail: CASI HC A05/MF A01 rotor modal wi_ a flexibleshaft and backup beadngs has been Translated ar_clas cover the following _cs: optimal rotation a.,ds developed. A aimp(e rotor modai which includes a fie_dbla disk and of satellite "IV receiving antenna; measurement of structural param- bem_gew,hdearencehesbesndevaio_edoralthedynem_ ofb'_e atars of signals, received from identified targets; diagnostics of gallium model investigated. A rotor model based upon the T-501 engine has arsanlde films grown by the atornicdayer epltexy method; acoustic been developed which inctudes bacicJp bearing affects. Parallel simu- diagnostic me_iods in new..genem_ aerospace equipment devalop- lation runs are being conducted using an ANSYS based finite alement ment: anaiysb of cryogenic field heat exchenge_m in aircraft model of the T.501. The magnetic hearing _ rig is currenUy floating gas turbine engines; mass characteristics opti_ of hydrogen and cl_ teste are baing conductod. A paper has been wrlUon that documents the work using the T-501 engine model. Work hydride spacecraft rofdge_ lift-to-drag ratio st supersonic veloci- ties; delta wing in hypersonic viscous gas tiow with Intermediate hes contioued wilh the slmplil_ mocleL The flnito aiement model Is inte_ allowing for wake flow; numericaJ simulation of chemically currenUy being modffied to Include the effects of foundation dynamics. and b__ly nonequilibdum flows at low and Inton'nedlate A llteratum saarch for mntedai on foil beadngs has heen conducted. A Reynolds numbers; measurement of the total content and altitude flnim element model is being developed for a magnetic beadng insades distribution of ozone from the Meteor-3 satellites; comparison of rnod_ wnhafoabackupbeadng. Dedvedfromtex_ profiles of s_itosphere trace species and obesrva_m_ data; and sm._on of r_n0of0es-dustdoudfon_n0d.r_n0k.pactofesteroids and comets. CASI N94=35803 Penneyhmnla State Univ., University Park, PA. Dept. of Engine_ng. THE AERODYNAMIC AND HEAT TRANSFER EFFECTS OF AN ENDWALL BOUNDARY LAYER FENCE IN A 90 DEGREE NDk36385# Joint PublicaSons Research Service, Ading_n, VA. TURNING SQUARE DUCT M.S. Thaela JPRS REPORT: SCIENCE AND TECHNOLOGY. CENTRAL DEANH.RI2ZO May1994 76p UmltedRepr(x:lucibllity:Momthan EURASIA 20% of lhls document may be affectod by mlcmf,che quality 3May1994 62p Transl.intoENGUSHfromvadousRueslanartides (AD-A278903) Avail: Issuing Ac_vity (Defense Technical Information (JPRS-UST-94-010) Avail: CASI HC A04A4F A01 Center (DTIC)) Translated articles covar the following topios: optimal syatems 1o detectand ck_dfy rno_ngoblecis;rnu_p_ekk._.atk_ of op0c_ This experimental study _ the utility of boundary layor fences in turbine passage flow. Boundary layer fences have readings in n'.ddsensor Information and measurement system; been relntmckx'ed es a poesibie methed to achisve favorable effects in of tirstintegrais in synthesis of optimai controi; study of the devaioprnent turbines. Previous studlas have uescl llnear cescades whlch necessar- of turbulence in the region of a break above a triangular wing; llyInVoducea Ix_ vo_toxre_ng from the endwailboundery aiectmerosion machining in aviation engine conethction; and curnula- layar impinging on the blade laeding edge. The present study Uees a tion of a fiet aix)ck wave in a tube by a thin pedetel gas layar of lower cunmd square duct that exhlblts no honmshoe vortex, but does have densily. CASI the characteristicpassage vorticesof a turning/low. The turbine passage is simulated to _Iudy the Interact)on effects of the boundmy layar fence end the paesage fiow dorrmated by the peesage vortices. N94-35387# Joint Publications Research Sen4ce, Arlington, VA. Specifically, a singleboundary layer fence of va_ng dimersions is JPRS REPORT: SCIENCE AND TECHNOLOGY. CENTRAL atlached Io a heated endwall of the duct. The fiow Is tully turbulant at EURASIA theIn_tof meduct.Rve-ho_probeand_iquldoryst_thermography 8 Jun. 1994 98p expedmentai mchnlques are usad to detenr, lrm the chenges in the (JPRS-UST-94-012) Avail: CASI HC A05/MF A02 aerodynamic Oowfield and the heat transfer coefficient of the heated Tmnslated artlclas covar 1he kl)wing _dcs: aiec'dcai conduc- endwail es compared Io the same duct w#h no fence. Hotwim meesum- tivity of CeO2-Ta205 cerandcs in air end ccxnbustiongases; Ol_indza- menis are also pmesntKI for the descrlp_on of the inlat flow field tlon of hypersonic wings; ae_ nozzles of gas dynamic lasers; turbulence. Thls study adds to the currenb'ysmall voiurne of infommtion effect of injector nozzle design parameters for the model combuslJon on fences in pesaage flow in esverai importent aspects. The effect of chamber of a Uquld-propeUant rocket engine on the generation of ti_e fence on the pessage vortex is studied in a known flow conflgum- transverse gas vibrations; new materials and processes: prospects for _on. The increased pressure losses of thicker (wider) fences are development and creation of aviation engineering; spectral profile of Investigated and results show a significant dependence on fence 553 12 ENGINEERING dimensions. Uquid crystal therrnography is used to obtain a high- Avail: CASI HC A03/MF A04 msolu_on map of the endwall heat transfer coefficient for two fence A high speed electric spindle based on active electromagne_c configurations. DTIC suspension technology has been designed, built, and tasted. The main goal of the rasearch wod 554 ENGINEERING 12 loss,improvedreliability,fault-tolerance,andgreatlyextendedbeadng shaft encoders which am photodiodas which measure the rotor re- servlcellfe.Themarriageoftheseadvantageswith innovative struc- sponse. Magnetic levitaUon of _e rotor via reluctance forces has been tural network design and advanced materials utlllzation will permit achieved and has reduced _ctional torque losses to less _ I pement major increases in thrust to weight performance and structural effi- of 1he avaUable torque. The results indicate that high speed limits of ciency for future gas turbine engines. However, obtaining the rna_mum these ac'_ato_ are related to torque ripple. Hysteresis motors payoff requires two key ingredients. The first key ingredient is the use magnelJcbearings am under consideration and willproduce high speed of modem magne_ bearing technologies such as innovative digital rotalonel machines wilh excellent sensor appltcalion potential. Author conVol techniques, high-densHy power e_eclmnics, high-density mag- netic actuators, fault-tolerant system architecture, and electronic (sensorlass) position estimation. This paper describes these technolo- N94-35911"# Sulzer-Escher Wyss Ltd., Zurich (Switzedand). gies. The second key ingredient is to go beyond the simple replacement ROTOR DYNAMIC BEHAVIOUR OF A HIGH-SPEED OIL- of roiling element bearings with magnetic basdngs by incorporating FREE MOTOR COMPRESSOR WITH A RIGID COUPLING magnetic bearings as an Integral part of the overall engine design. This SUPPORTED ON FOUR RADIAL MAGNETIC BEARINGS is analogous to the proper approach to designing with composites, J. SCHMIED and J. C. PRADETTO In NASA. Langley Research whereby the designer tailors Ihe geometry and load carrying functlon of Center, Second Inte_ Symposium on Magnelk: Suspension ti'=eslnJctural system or component for the cor_ instead of simply Techn_, Part 2 p 557-572 May 1994 _ng ca_ ina design originally intended for metal rnete- Avail: CASI HC A03/MF A03 dal. This paper describes methodologias for the design integration of The combination of a hlgh-speed motor, dry gas seals, and magnetic bearings in gas turbine engines. Author magnetic beadngs realized in this unit tecllitetes 1he _i_ti<)n of oil. The motor Is coup_:l wtlh a quill shaft to b'_ecompressor. This yields N94-35905"# NationalAeronautJcs and SpeceAdminisltatlon. Lewis higher netural frequencias of the rotorItmn wflh the use of a diaphragm Research Center, Cleveland, OH. coupling and helps to maJntein a sufficient margin of the rna_rnum ELECTROMECHANICAL SIMULATION AND TEST OF speed to the frequency of bhe second comprassor bending mode. ROTATING SYSTEMS WITH MAGNETIC BEARING OR However, the controller of each bearing then has to take the combined PIEZOELECTRIC ACTUATOR ACTIVE VIBRATION modes of both machines into account. The requirements for CONTROL controller to ensure stebllily and sufficient damping of aJIcrilJcaJspeeds AIAN B. PAI.AZZOLO (Texas A&M Univ., College Station, TX.), are designed and compemd wilh the implernented controller. The PUNAN TANG (Texas A&M Univ., College Ste_n, TX.), CHAESIL KIM calculated closed loop behavior was confirmed experimentally, except (Texas A&M Univ., College Ste_on, TX.), DANIEL MANCHALA (Texas U_e_ny of sume hlgher modes due to =ight f_luency devia_ons of A&M Univ., College Station, TX.), TIM BARRETT (Texas A&M Univ., _e rotor model to lhe acluaJ rotor. The Irdluence of a mechanlcaJ College SteUon, "IX.), ALBERT F. KASCAK (Army Aviation Systems damper as a device to provk_ additional damping to high models is Command, Cleveland, OH.), GERALD BROWN, GERALD demonslrated lheorelk_lly. After all, it was not necessary to installthe MONTAGUE, ELISEO DIRUSSO, STEVE IO.USMAN at aJ. In NASA. damper, since all modes cold be stabilized by _he controller. Langley Research Center, Second Interndo_ Symposium on Mag- (revised) netic Suspension Techn_, Part 2 p 467-478 May 1994 Avail: CASI HC A03/MF A03 N94-35915"# Kanagswa Academy of Science and Technology, This peper conteJns a _ of Ihe experience of Ule aulhors Kaw_ (Japan). infile field of electmmecharlical modeling forroteting _ry - ective MAGNETICALLY SUSPENDED STEPPING MOTORS FOR vibralJon conlml. Piezosiectdc and magnetic bearing actuator based CLEAN ROOM AND VACUUM ENVIRONMENTS control ere discussed. Author TOSHIRO HIGUCHI In NASA. langley Research Center, Second Int_ne_onat Symposium on Magnetic Suspension Technology, Part 2 N94-35907"# Wisconsin Univ., Madison, WI. Center for Applied p 62S-639 May 1994 Mtcroelectronics. Avail: CASI HC A03,'lVlFA03 PLANAR ROTATIONAL MAGNETIC MICROMOTORS WITH To answer _e growing needs for super-clean or contect free INTEGRATED SHAFT ENCODER AND MAGNETIC ROTOR actuators for uses in dean rooms, vacuum chambem, and space, LEVITATION innoveWe actuatom whk:h conte_ the funct_ns of stepl_ng motors HENRY GUCKEI., T. R. CHRISTENSON, K. J. SKROBIS, J. KLEIN, ancl magnetic beadngs in one body were deveiof)_. The roto¢of the and M. KARNOWSKY In NASA. Langley Research Center, Second magnetically suspended stepping motor is suspended llke • magnetic Interne.lionel Symposium on Magne_c SusponCon Technck)W, Part 2 beadng and rotatKl and posltloned Ukea stepp4ngmotor. The Importent p 501-511 May 1994 tndtof_e motor _sthst_ _ nota s_e wdxlureor comd_ne_on of a (Contract N00014-91-J-1876; NSF ECS-91-16566; NSF DMR-88- s_ moor and _ magnet_ bear_, butan ama_ of 21625; SRC-88-MC-507) a 8tepp_g rnof:xand a ma0netk=beadng.Ow_g too_drmd deign ar_ Avail: CASI HC A03/MF A03 fred-back control, a toofhecl stetor and rotor are an mat are neeclecl Deep x-ray lllhography and siectmplating may be combined to strusUewias for steJ)le suq_enskm. More 1hen ten types of motors forma fa_dcatk)ntod for_k:_d devk:asw_ kuge _ such as _near type, h_h accuracy rofary type, two-di_ type, hetghls, to 500 mlcron, and exlmme edge act_as, lass tmn 0.1 micron- asd hlgh wcuum type were built and tested. Thls paper describes the run-out per 100 micron of helght. This procass ooncept which odglneted slnJctum and design of these motors and _leJr performance for such in Germany as LIGA may be further extruded by adding surface appllcations as prec/se positioning rolary teble, linear conveyor eystem, micromechlnlng. "INs extlmslon permits the Mlxication of precision and lhete-zela _r Io¢dean room and high vacuum use. metel Bnd plastic parts whlch mey be asasmbled intolhree-dlmenelon81 Derived from text mk:rumecha_c_ components and systenne.The proce_ng to_ may be used to fabrkmte devlcas frorn ferromagnetlc matedal such as nlckel N94-3591r# Xerad, Inc., Santa Monica, CA. and nlckeHron alloys. These materials when property heat Imated FUTURE ULTRA-SPEED TUBE-FLIGHT Abstract Only e:d_b#a_e rnagnelc_ forcurrentto9uxcor_emk_ and ROBERT M. SALTER In NASA. Langley Research _r, Second mar_neJ behav_ _x pe,manent mamet appa:,,S=_ The teoaand I_ Symposium on Magnetic Suspension Technology, Part 2 mater_d8have been tested_a planar,magnet,c,rotetk)md_ p 66g-670 May 1994 fabr_. Three phase reluctancemecNnee ofb",e6:4conngurdon Awih CASI HC A01/MF A03 w_ 280 mL_on clarneterrotor8have been teetedand anelyzed.Stab_ Future long-link, ullm-speed, sudace transport systems will rotatlonal speeds to 34,000 rpm with output tOn:lUasabove 10 x 10(exp require eteclmmagnetlcally (EM) driven and restrained vehidas oper- -9) N-m have been obtained. The behavior is monitored with integrated ating under reduced.elmosphere invery straight tubes. Such tube-flight 555 12 ENGINEERING balnswillbesafe,energyconseNative, pollution-free, and in a pro- found in advanced aircraft, are l_ghtweight and susceptlbie to critical tected environment. Hypersonic (and oven hyperbellistk:) speeds are vibrations, and consequently dynamic response plays a very important lheoretlcaJlyachievable. Uffimate system choices willrepre_mtlmdeofis role in lhelr analysis. The presence of flaws and cnu:ks can have between amodtlzed capital costs (ACC) and operallng costs. For ca_ consequences. The stress intlmslty factor, K, emerges as exam_e, king coas,ng ,nks might emily aerodynamic ,ft cour_ed a very significant parameter b_at charactedzes the crack behavior. In w_h EM restraint and drag make-up. Optimized, combined EM llft, and analyzlng the clynamlcresponse of panels lhat conteln cracks, the flnlte thrust vectors could reduce energy costs but at Increased ACC. element method is used, 10utbecause Ibis type of problem is inherently (Repulsive levitation can produce lift-over-drag I/d ratios a decade computetionelly intensive, a number of ways of cak:_a_ng K more greater than aerodynamic), Alternatively, vehicle-emanated, Induced- efflclenlly am explored. CASI mirror fields in a conducting (akanlnt_ sheet) road bed could reduce ACC but at sube'mntlalanergy coste. Ulln_spsed tube flightwllldemand fast-acting, high-pmdsion sansom and ¢omputedzed magneUc shim- 13 _ng. This serne conVol system can malntein a magnetic 'guide way' invadant in Iner_d space with inertial dat_-_om Imbedded in tube GEOSCIENCES sUuctums 1osense and correct for earth tremorL Ullm-speed tube flight can complete with aircraft for transit time and can provide even greater Includes geosciences (general); earlh resources; energy production passenger convenience by single-model connectkorm with local sub- and conversion: en_mmont po_n; geophysics: metonrot_gy and ways and Ira)dec Ilnse./¢d'K_h cargo lransp(xt generaBy will not need c_r,a_W: and oceanography. to be performed at ulVa spseds, such spseds rnay well be da_mbie for high b_roughputto optimize channel costs. Thus, 8 largo and e_ N94-35596 Massachusetts InsL of Tech., lexington. pipeline might be replaced wilh small EM-ddven pallets mthigh speeds. THE INFLUENCE OF DATA LINK-PROVIDED GRAPHICAL (revmd) WEATHER ON PILOT DECISION-MAKING ANN-MARIE T. LIND, ADAM DERSHOWITZ, and STEVEN R. BUSSOLARI 6 Apr. 1994 80 p Limited Reproducibility:.More than N94-35945"# National Aerocautlcs and Space AdmkrdsUalk)n. Lewis 20% of lhis document may be affected by _che quality Research Center, Cleveland, OH. (Conlmct DTFA01-93-Z-02012) A SUPERSONIC TUNNEL FOR LASER AND FLOW.SEEDING (AD-A278871; MIT-ATC-215; DOT/FA/VRD-94/9) AveJl: Issuing Ac- TECHNIQUES tMty (_ Technical Infocmatlon Center (DTIC)) ROBERT J. BRUCKNER and JAN LEPICOVSKY Jun. 1994 15 p Th_ report dooume_ U_e _nd_n_ of ,, human fecto_ study Presented at 1he 121h Applisd Aerodynamics Conference, conducted to setimate 1he effects of _ Graphical Wealher SeMce Spdngs, CO, 20-24 Jun. 1994; sponsored by AIAA (GWS) on general av_tlon (GA) aircraft utility, pilot _ua_onal aware- (ConVact NAS3-27186; RTOP 505-62-10) ne_, and _ wea_er dissemination woddoed imposed on ground (NASA-TM-106588; E-8852; NAS 1.15:106588; AI/_ PAPER 94- penmnnel. GWS Is a d_te llnk ap_, being developed at MIT 1825) Avail: CASI HC A03/MF A01 Llnco_ Labomtonj through the sponsorship of Ibe Federal Aviation A supers(x_ wind tunnel with flow conditions of 3 Ibm/s (1.5 kg/ Adndnislmtlon, that will provide near.rsal-_e graphical wsalher infor- s) at a free-strsem Mach number of 2.5 wse designed and tm_d to matlon to the General Avi_on pilot In _e cockpit. Twenty Instrument- ixovtde an arana lot future davetownont work on isser _ rated p_t, par,dpmd _n a_e study. Sublec_ were presented w_h and flow-seeding technique6. The hyt)rld supemonlc nozzle deign _'mt aclual wsalher Information in _e context of a series of was used incorporated the rapU expansion rnee_ of pmpuis_ preflight bdeflngs and acco_ng 'flights'. GWS im- nozzles while Itmainlained the uniform, disturbanc_lrsa flow required sgse were sccessil_ on a Madn_o_h Computer. The study deslgn in eupemonic wtnd tunnels. A vieoous _ wse performed on 1be enebied Ihe anJysis of the effects of GWS m_d tbe detem_inatJonof tunnel to daterrnlne a_e boundary _jer growth characteristics along'_e whether those effects were influenced by the experlance level of the gowpath. Appropriate cormclions were lhon mada Io t_e contour of 1he pUoVuser. Obtective and subjecUve msesures of effectivaness were nozzle. Axisl prewum dlstdbub_ were _ and Mach number cohctKL Results indicate _ GWS had a substen_ effect on disUU)ulk)nswere calculatod based on _ree indapendent dMa reduc- wearer-related dedsk)n-maldng. This was true for pilots wi_ varying tion melh(xis. A compfete uncertelnty analysls was pedorrrmcl on the levels of imtxument experience. Subject cordidence In 1he ability to precision error of each method. Complex #hock-wuve pamm_ were use_ Ihe wsa_'_)r sfluationwas markedly increued when GWS was ganerated in b_e flow field by wedgse mountod rmar lhe roof ancl floor Used. Suqec_ w_ GWS made tewer calls for weal_r informalk)n to of a-m tunnY. The most slable mock structure was _ expe_ weather dissemination ground personnel, thus indicating a potential mentelly by the use of a locuslng schUeran sysWn and a novel, laser de(mue in ground personnel woddoad. Subjects found GWS to be besad clyTmmicuhock positk_nsensor. Thrsa pomngal _ very useful and were onthuslas_ about receiving data rink services in rnglons lot future Isaer and flow-seedng _udkm were cmatod in the • e GA oock_ in 1be tutum. DTIC shock stmcU_: deceleratlon lhrough an oblklUe shock wmve of 50 degrees, strong da_eratlon _rough a normal shock wave, and acceferallon through a supersonic expansion fan containing 25 de- N94-3S720 _ InsL of Tech., L_x_. gmes of flow turning. At.e_ DATA REQUIREMENTS FOR CElUNG AND VISIBILITY PRODUCTS DEVELOPMENT J. LKELLER 13/1_or.1994 41p U_Fleprodudbility:Morelhan N94-35974°# Pun:lue Univ., West Lafeyebe, IN. School of Aeronau- 20% of 1his document may be affected by mlcrorche qualNy Ucs and Astmnau_,cs. (Contract DTFA01-93-Z-02012; F19628-90.C-0002) FREQUENCY DOMAIN ANALYSIS OF THE RANDOM LOADING (AD-A2781)59; ATC-212; DOT/FA/VFID-94/5) Avail: Issuing Activity OF CRACKED PANELS Final Report, 10ot. 1990 - 30 8ep. (Defense Technk:al _ Center (DTIC)) 1993 The Federal Avidon _ (FAA) Ir_grs_ed Tem_al JAMESF. DOYLE 16Jun. 1994 89p Wealhe_ System (ITWS) is lupp_ting lhe davelofxnant of wselher (ConVact NAG1-1173) produc_ _ for air bufflc oonl_i in 'd_ torrnirml aru. Tl_mo (NASA-CR-196021; NAS 1.26:196021) Avail: CASI HC A05/MFN)I woducte wlil teke advantege of new tmminal arse sermors, induding The p_..y _xt concerned _he _ of _t_k_ me_- Terminal Doppler WeaU'w Radar (TDWR), Next Generation We_er ods for the accurate predlctlon of the _ of _ loedlng on 8 panel Radar (NEXRAD), and the Meteorologk:al Data Collection and Report- wllh a crock. Of particular concern wse lhe Influance of fmquoncy on lhe Ing System (MDCRS). Some of these ITWS products willallow air tndflc strsas intensity _ behavior. Many modem sUucturu, such m 1hose manngem to _ significant short-term changes in ceiling and 556 MATHEMATICAL AND COMPUTER SCIENCES 15 visibility.Thisreportfocuseson_e scientific data requirements for they approach lower altitudes. This is padJculady exacting in Iow- supporting prototype modai-system development and diagnostics. el_tude helicopter missions, where aggressive terrain hugging maneu- Model diag_ can include case studies to determine the most vering create minimal horizontal and vertical clearances and demand important physical processes that were responsible for a particular precise terrain poslUoning. Sole reliance on airborne precision navige- ceiling and visibility event, providing the insight necessary for the tJon and stored terrain elevetion data for above.round-level (AGL) development of effec'_ve ceiling and visibility product aigodthn_. In positioning severely limits the operatk)nai altitude of such systems. A time such case study diagnostics could also Indude careful off-line Kalman filter is presented which blends radar aitlmater returns, preci- failure analyses that may effect the design of the opem_onai system. sion navigetion, and stored terrain elevat_n data for AGL positioning. General ceiling and visibility test beds am discussed. Updated reports The filter is evaluated using low-altitude hellcuptar flight test data will be released periodically as the ITWS ceiling and visibility project acquired over moderately rugged terrain. The proposed Kalrnan filter is proceeds. DTIC found to remove large disparities in predicted AGL altitude (i.e., from airborne navigation and termln elevation data) in the presence of N94-35807 Massachusetts Inst. of Tech., Lexington. measurement imomaiias and dropouts. Previous work suggested a TERMINAL DOPPLER WEATHER RADAR (TDWR) LOW LEVEL minimum clearance affitude of 220-ft AGL for a near-tanain guidance WIND SHEAR ALERT SYSTEM 3 (LLWAS 3) INTEGRATION system; integration of a radar altimeter suggests operation of that STUDIES AT ORLANDO INTERNATIONAL AIRPORT Project system to 50 ft, subject to obetacle-avoldance limitations. Report, 1991 - 1992 Author (El) RODNEY E. COLE and RUSSELL F. TODD 20 Apr. 1994 55 p Umited Reprodudblllty: More than 20% of this document may be affected by microfiche quality A94.60197 DRAG REDUCTION OF TURBULENT FLOW OVER A (Contract DTFA01-93-Z-02012; FI9628-90-C-0(X_) (AD-A279957; ATC-216; DOT/FANRD-94/12) Avail: Issuing Acthdty PROIJECTILE, PART 1 (Defense Technical informat_n Center (DTIC)) JAN-KAUNG FU Chinese Air Force Academy, _g ('l'alwan) In 1993 the Federal Aviation Administration (FAA) began deploy- and SHEN-MIN UANG Jouma/of Spacecraft and Rocke/s (ISSN ing two new wind shear detection systems: the Terminal Doppler 0022-4650) vol. 31, no. 1 Januim/-FebnJary 1994 p. 85-92 refs Wsether Redar (TDWR) and the thlrd-generation Low Levai Windshear (BTN-94-EaX94311322899)Cop_ght Alert System (U.WAS 3). Cummtly, nine airports am scheduled to A numedcai study is rnade to anaiyze the drag parformanoe of • receNe both e TDWR and an LLWAS 3. Thle number may eventuaily secant.ogive.cyllnder-boatmil projectile in the tmneonic Mach number incmese to as high as 45. When co-located the systl)ms will be regime belween 0.91 and 1.20. To improve the projectile's perfor- integratedto providea singlesetof windshearaiertsandinwove mance, two drag reduction methods, boattalling and base bleed, are system performance. The TDWR production schedule required one of spplled. The effectiveness of each rnethod and the comblnation of both throe intagrat;on algorithms to be chosen for specifk:atlon by fail 1991. methods m studied by va_lng the values of parametem such as The thrse aigedthrns are the prototype intag_ aigodthm dev_ boa_aJl angle, bleed quantity, and bleed area. The computed disffibu- at the National Center for A_n_sphedc Research (NCAR) and _ two tions of surface pressure coefl_ont of _ projectile with different algorithms developed at MIT Lincoln Laboratory (MIT LL). To assess beatlail angles are in dose agreement with expedmental data. El the performanoe of the throe aigodthms, MIT LL pedonned a study of intagra_on, TDWR, and LLWAS 3 aigodthms at Orlando Intamationai A94-60212 Airport (MCO) inthe summer of 1991. Based on the msuits of this study, SYNTHETIC VISION FOR ENHANCING POOR VISIBILITY MIT LL and NCAR issued a joint recommenda_n that the FAA procure FLIGHT OPERATIONS one of the integration algorithms dav_ at MIT I.L Thle ai_ was dernomtmtsd xt the Odando I_ Nrport in the lmmrner of H. MOLLER Tachnleche Univ, Munich (Germany) and G. SACHS 1992. Rasuits of the 1991 comparative stody and a follow-up study of IEEE Aerospace and Electronic Systems Magazine (ISSN 0885- TDWR, LLWAS 3, and Message Level integration aigorflhrns at 8985) vol. 9, no. 3 March 1994 p. 27-33 refs Odando in 1992 are dlecuseed. NI the elgodthms mat the requirement (BTN-94-EIX94331335531) Copyright of datecting 90 percent of mlcrobumt level wind shear with loas events. The present paper is concerned _ computer generated vision LLWAS 3, Build 5 TDWR, and the MIT LL Integration aigodthnw with as • fufdler technique provk:llng visual OLmSfor the pilot. C(x13xJ_r Build 5 TDWR ail mat the requirement that less th=n 10 percent of wind genemted vleion may be used in combination w#h the afommantioned shear alerts be false. DTIC sensor based technkluee. Thus, it is pol_ble to compensate for limitation8 which senior based vilud sy_erns have in providing visibility range or in generi_n 0 • non'nai Iooldng image. In eddmon,compu_generatedVna0en/hasthepote_ai forproving 15 eddl_onal Inlormation to the plot for cuntrolling the flight path or for MATHEMATICAL AND COMPUTER SCIENCES warning purposes. This potantlal can yield improved and/or more _ as curnpared Mth the natural view when loddng out of the cockpit wind(_. El includes _ and computer .sciences (general); computer operatior_ and hardware; computer programming and software; com- puter systems; cybemelcs; nurnedcai analysis; statistics and probabtl- N94-34921"# National Aeronautics and Space Administration. _. systam=amaym;and_eoretk:= mathema_. Goddan_ Space Right Cenlr, Greenbelt, MD. ADA DEVELOPERS' SUPPLEMENT TO THE RECOMMENDED A94.60176" NationalABonamlcsandSpace_. Ames APPROACH Research Center, Moffetl Field, CA. RUSH KESTER (Computer Sciences Corp., Greenbelt, MD.) and DESIGN AND ANALYSIS OF A KALMAN FILTER FOR TERRAIN- LINDA LANDIS (Computer Sclencee Corp., Greenbelt, MD.) Nov. REFERENCED POSITIONING AND GUIDANCE 1993 36p RICHARD E. ZELENKA NASA. Ames Research Center, Moffatt (Contract RTOP 552-OO-OO) Field, CA Journal of Aircraft (ISSN 0021-8669) vol. 31, no. 2 (NASA-CR-189345; SEL-81-305SPI; NAS 1.26:189345) Avail: CASI March-April 1994 p. 339.344 refs HC N)3AAF A01 (BTN-94-ELX9431132S124) document is a coaec_on ofguidelines for progranrnem and Avionic systems that depend on digitized terrain elevation data tot managers who are responsible for the development of flight dynamics guidance generation or navlgetk_nel reference require accurate abso- applications in Ads. It is intended to be used in conjunc_on with the lute and relative distance rneasumrnents to the terrain, espaclaily as Recommended Approach to Software Development (SEL-81-305), 557 15 MATHEMATICAL AND COMPUTER SCIENCES which descdbes the software development lifo cyck), its products, N94-35071"# Durham Univ. (England). _ intelligence Systems reviews, me_'lods, toois, and measures. The Ade Devegopers' Supple- Research Group. merit provides addifJonaldetail on such topics as reuse, ot_ect-orlented ENGINEERING LARGE-SCALE AGENT-BASED SYSTEMS analysis, and object-odentad design. Au_or WITH CONSENSUS A. BOKMA, A. SLADE, S. KERRIDGE, and K. JOHNSON In NASA. Gock:la_ Space Right Center, The 1994 Godderd Conference on Space Apl)licatior_ of ArlJficlalIntelligence p 343-356 May 1994 N94-35063"# NatlonaJAeronautk:s and SpaceAdrnintstrstlon. Lyndon Avail: CASI HC A03/MF A03 B. Johnson Space Center, Houston, "IX. The paper presents the consensus me_hod for _ devei_ VISTA GOES ONUNE: DECISION-ANALYTIC SYSTEMS FOR of large.sc_e agent-based systams. Systems can be developed as REAL-TIME DECISION-MAKING IN MISSION CONTROL networks of knowledge based agents (KBA) which engage ina collabo- MATTHEW BARRY, ERIC HORVITZ, CORINNE RUOKANGAS, and rativo problem solving effort. The method provides a comprehensive SAMPATH SRINIVAS In NASA. Godderd Space Right Center, The and intagmtad approach to U'_edevek)prnent of this type of system. This 1994 Goddard Conference on Space Applications of Arb_dal Intelli- includes a systerna_c analym of user requirements as well as a gence p 241-252 May 1994 nuctumd approach to generating a system design which exhibits Ihe Ave,: CASI HC A03/MF A03 desired functionality. There is a direst correspondence betwesn system TI_ Vista project has centered on 1be use of ckv,'a_kx_theoretic requirements and design components. The benefits of Ihis approach approaches for n-armging the display of cd_cal information relevant to are _'_atrequirements are traceabge Imo design compononts and code reaPtirne operations dedsiorB. The _ste.I project originallydeveloped thus facilitdng vedtk:ation. Tbe use of 1he corNnsus rnethod wffh two a protOtyl_eof U_ese ap_ for managing §ight con's_ di_ in major test applications d_owed it to be succass/ui and also provided lhe Space Shuttle Mission _ Center (MCC). The follow-on Vista- v_.aUe _r_ght into pro_ems _c_ _soc_tad wrd__he deve0op- II pro_ integmlod these approachas In i workMatlon program whlch merit of large systams. Author (revised) cuwentiy le being certlRed for ues in the MCC. To our Imowledge, Ibis wm be the first ap_ of automated dec_on-tbeoretic rmmo_ng tac_ for real-Ume spacecraft operaUorm. We shall describe 1be development and capabilifJas of g_e Vista-II systmn, and proMde an N94-35240"# Institute for Computer Applications in Science and overview of em uas of decision-lheorolc re_ tacl_ to 1be Engmemg, Hampton. VA. problems of managing the complexJty of night conU_lk, dismays. We RUNTIME SUPPORT FOR DATA PARALLEL TASKS Final discu. U_erolevence of the Vista _ w_n the MCC desiCon- Report making environment, focusing on the problems of detecting and MATTHEW HAINES, BRYAN HESS, PIYUSH MEHROTRA, JOHN dl_ng spacecmft e_cUonmc_amk:al subsystems component fail- VANROSENDALE, and HANS ZIMA Apr. 1994 23 p Submitted for ures with limited _, and tm problem of determining what pub,k:aUon oontrol sc_(x'w sta:ukJ be taken in high-stakes, time.odtical situations in (Contract NAS1-19480; RTOP 505-90-52-01) responas _ ,, dlagno_s performed under uncertainty. Flna_, we shall (NASA-CR-194904; NAS 1.26:194,904; ICASE-94-26) Avell: CASI HC outline our current research directions for follow-on projects. Ault_r A03/MF A01 We have recer_ introduced a set of Fortran language extm'edons tr=t e,,ow for ir,t_m_ =4_rt of mk e,nd dm pam_ism, m:_ N94-36064"# Natlonal_ and SpaceAdrrdnistration. Lymlon provide for shared data ol0stmctkxm (SDA's) es a melhod for commu- nicdons and i1_ among _ tasks. In _ paper we B. Johnesn Space Cenmr, Houston, TX. MISSION EVALUATION ROOM INTELLIGENT DIAGNOSTIC discun Ihe deign and impismentalion isaues of "_e rurdlme system AND ANALYSIS SYSTEM (MIDAS) neceua_ to _q_x_t tbeas ex_enskms, and d_cuas the under_ng GINGER L. PACK. JANE FALGOUT, JOSEPH BARCIO, STEVE roq_mments for s.c_ a system. To _t,_e fees_,ty of this approach, SHNURER, DAVID WADSWORTH, and LOUIS FLORES In NASA. we implemont a prototype of tbe mntime systom and use _ls to supp(xt an abstract muRUsdpUnary optimization (MOO) problem for aircraft Godde¢l Space Flight Center, The 1994 Godderd Conference on design. We give Ini_ai results and discuss future plans. _r Space Applica_0rm of _al Intelligence p 253-267 May 1994 Avail: CASI HC A03/MF A03 The role of Mbmion Evaluation Room (MER) engineers is to provUe en_nesdng .mpo_ dumg Space Sh.tSe mlmom, _ Space Shunle systerns. These er_nesm are c(xcemed wilh ensuring Iht lhe N94-35256"# Nattomd Aeronautics and Space Administration. mme f(x whlch Ihey are ruponsible function ndiably, and es Godda_ Space Right Center, Greenbelt, MD. intanded. "rheMER is a central f,kdlily from which englnesm mmywork, COST AND SCHEDULE ESTIMATION STUDY REPORT In fuMing lhls daub. Enginesm peNicipato in reahtlme moni_ STEVECONDON (Compm_SdencesCorp.,Gresnl_t, MD.),MYRNA of ,_utue taW.eW cUta and provide a ver_y of ana_es esesc_ted REGARDIE (Computer Sciences Corp., Greenbelt, MD.), MIKE STARK. wi_ h'_eoperation of _e shuffle. The Johnson Space Cemsr's Automn- and SHARON WALIGORA Nov. 1993 133 p _n and _ Division is woddng to Inmsfer advences in intMiigent (Contract RTOP S52-00-(X)) synm_ tocrmology to NASA'e operaUonaJ environment. Spec,k:a,y, (NASA-CR-189344; SEL-93-002; NAS 1.26:189344) Avail: CASI HC b"mMER Intelligent Diagnostic and Analysis Systm_ (MIDAS) project A07/MF A52 provides MER englnesre wtlh software to aasist them wilh _ng, Thls report dasodbas 1he analysts bedormed and _e findings of flltedng and analyzing Shutlle telemetry deta, dudng and Mtar Shuttle a study of b_e software developnmnt cost and schedule estimation missions. MIDAS off4oade to oomputors and software, _te tesks of data mode_ ._d by tbe F_ht _ D_v_x)n (FDD), Godde_d Space g_, vlris,,ing, _ _, end prov_es _he onglnesrs w_ Flight Center. The study analyzes typical FDD projects, locusing Irdon'mdion which Is in a moro conctee and uesble fo_n nesded to pmwlly on those developed _ince 10e2. The _udy mconlirms _e m_o_t desisk_ _ _d engineering ev_._'on. Engineers are sW_dard SEL effort mtlon model lhst is beesd on s/ze ad}ustad for hm able to concentnm on morn difficultwobloms es thoy m_,es.This reuse; however, _ lot U_eproduc_ and growlh parametam paper describes oome, but not an of the appncations 1hat have besn in Itm _ effort model huve been upda_:l. The study aiso developed for MER engineers, under the MIDAS Project. The sampling produced a schedule pmdictlon model besed on empldcal deta that de_odbed berewith wae eslected to _0w 1he range of taaks 1hat vades dependlng on sp_ type. Models for tbe dlstdbu_on of englnesm must pedom_ for n_uion euppo¢ and to ohow me vedous e_ort m:_ =:mdune by ,ee.cym phase =r,= mo prmm_, mr_ny, e= levels of _ "d_athave been applied to essist lhelr effort¢ rq)ort ex_ how to use _"mas models to plan SEL pro_ects. Author Author 558 PHYSICS 16 N94-35958#NavalSurfaceWarfareCenter,Dal'dgmn,VA.Weapons ROBERT A. MITCHELTREE, and PETER A. GNOFFO Journal of SystemsDepL Thermophysics and Heat Transfer (ISSN 0887-8722) vol. 8, no. 2 USER'SGUIDEFORANINTERACTIVEPERSONAL April-June 1994 p. 244-250 mfs COMPUTERINTERFACEFORTHEAEROPREDICTION (BTN-94-EIX94311330648) Copyright CODE Lunar and Mars mtum cotclitions are examined using the Langley THOMASC.HYMER,FRANKG.MOORE,andCORNELLDOWNS aemthennodynernic upwind relaxation algorithm fiowfield code and the Jun.1994101p Langley optimized radiative nonequillbrium radiation code to assess (NSWCDD/TR-94/107)Avail:CASIHCA06/MFA02 the effect of radiative coupling on exJsymmetdc thermochemical Tnisreportdeecdbesinteractive,user-ffiendly,preprocessingand nonequilibflum flows. Coupling of the two codes is achieved iteratively. post-processingPCmodulesdesignedtooperatewiththe latest Special trealment required to couple radiation in a shock-capturing version of the NSWC Aeropredic_on Code (AP93). As part of the method is discussed. Results indicate that while coupling effects are preprocessing input module, geomet_ Inputs are now automated by generally the same as occur in equilibrium flows, under certain condi- giving the user many o_. By using this new software, a set of tk_s redtetion can modify the chemical Idne_cs of a nonequilibdum aerodynamic coefficients can be obtained on most weapon configura- flow, end thus alter relaxation processes. C,oupling effects are found to lk)ns in less than 15 minutes from time of inil_ setup to computer be small for all cases considered, except for a 5 m diem eerobrake outputs, compared to 2 to 4 hours for the AP93 computer mainframe returning from Mars at 13.6 Io'n/s. Author (El) version. While the computer cost savings am modest (the AP93 executes on a large computer in less than a second), the manpower A94-60349 savings and producth_y enhancements can be significant. The user's COMPARISON OF OPTICAL MEASUREMENT TECHNIQUES guide attempts to aid users of the AP93 by correlating AP93 PC FOR TURBOMACHINERY FLOWFIELDS interface data inputs and the corresponding source code variable JOHN R. FAGAN Purdue Univ, West Lafayette, IN and SANFORD names. "rnis crcss-referoncing information is given in italics in the FLEETER Joumal of Propulsion and Power (ISSN 0746-4658) vol. discussion. Author (revised) 10, no. 2 March-April1994 p. 176-182 refs (BTN-94- EIX94341338357) Copyright A preliminary set of measurements were made of the flowfi(dd in 16 the Purdue Reseamh Centrifugal Compressor using e laser two-focus (L2F) velocimater and a laser Doppler veioclmater (LDV). After a review PHYSICS of the preliminary results, the LDV system was chosen to con_nue this research due to the advantages it demonstrated over _ L2F system Includes physics (general); acoustics; atomic and molecular physics; in making measurements in this flowfleld. The 1.2F date are compared nuclear and high-energy physics; opgcs; plasma physics; sclid-stete and contrasted to the LDV data. While this comparison is not to physk:s;andthe_cs andst_s.c_ phys.;. insinuate the local features of the LDV date are universally correct, an evaluation ofthe global features of the compressor flowfieid based upon the LDV measurements demonstrate consistency, i.e. measurements at vedous plenas in the tiowlteld demonstrate cunse_ of mess and A94-80009 NEW MULTIGRID APPROACH FOR THREE-DIMENSIONAL a reasonable dlstflbution of work in the compressor. In addition, meffgxlologies to determine the effect of the measurement volume UNSTRUCTURED, ADAPTIVE GRIDS VIJAYAN PARTHASARATHY Univ. of Texas, Austin and Y. geometry for the two systems are presented. Finally, the edventeges end disadvantages of using the L2F system fortud)omechtnery tiowflelds KALLINDERIS AIAAJoumaJ(ISSN0001-1452) voL32, no. 5 May Is discussed Interms of measurement accuracy, applicability to general 1994 p. 956-963 rofs turbomachinery fk)wllelds, and the capability to make meaeu mrnents in (BTN-94-EIX94301315973) Copyright regions of high noise due to stray refleclfons. Specific examples based A new multigrid method wtth adaptive unstnJctumd gdds is upon this expedmentel work am presented. Author (El) presented. The three-dimensional Euler equations are solved on tetrahedral grids that are adaptively refined or coarsened locally. The rnuffigdd method is employed to propagate the fine grid correcJJons A94-60361 morn rapidly by redistributing the changes-ln-time of the solutionfrom FEASIBILITY STUDY OF A CONTAINED PULSED NUCLEAR the fine grid to the coarser grids to accelerate convergence. A new PROPULSION ENGINE approach is employed that uses the parent cells of the fine gdd cells in ALEXANDER G. PARLOS Texas A&M Univ., College Station, TX an adapted mesh to generate successively coarser levels of multigrid. and JOHN D. METZGER Journal of Propulsion and Power (ISSN Thle obviatesthe need tor the genemtlen of a sequoncs of ind_t_ 0746-4658) vol. 10, no. 2 March-Apdl 1994 p. 269-278 refs nonovedapplng grids as well as the relatively complicated operaUons (BTN-94-BX9434133_) that need to be perfoffned to inteq:)date the solution and the residuals The result of a feasibility analysis of a contained puleed nuclear between the Independent gdds. The solver is an explicit, vertex-besed, propulsion (CPNP) engine concept utilizing the enormously dense finite vo4ume scheme that employs edge-besed data stxuctums and energy generated by small nuclear detonations is presented in this operations. Spatial discretlzation is of centmJ-diffemncing type com- arficle.This concept was initiallyproposed and studied in the 1950s and _ned withspsc_ up_nd4ikssmoo_ng opera_rs._opUcat_ncases 1960s under the program name HELLOS. The current feasibility of the include adaptive solulfons obtained wi_ _dd acceleration for concept is based upon materials technoiogy that has advanced to a supersonic 8nd subsonic flow over a bump in a channel, as weft as state that allows the design of pressure vase, s required to contain the transonic flow around the ONERA M6 wing. Two levels of multigrid blast associated with smelt nuclear detonations. The impulsive nature msuited in reduction in the number of iterations by a factor of 5. of the energy source provides the means for drcumventing the mate- Au_x)r (El) rials then_si barriers that am inherent in steady-state nuclear propul- sion concepts. The rapidenergy h'anster to the propellent results Inhigh thrust leveis for times less than 1 s following the detonation. The A94-60143" National Aeronautics and Space Administration. preliminary feasibility analysis using off-the-shed materials technology Langley Research Center, Hampton, VA. appears to indicate that the CPNP concept can have thrust-to-weight COUPLED RADIATION EFFECTS IN THERMOCHEMICAL ratios on the order of I or greater. Though the specific impulse is not e NONEQUlLIBRIUM SHOCK-CAPTURING FLOWFIELD good indicator for in_ engines, an operating-cycle averaged CALCULATIONS specific impulse of approximately 1000 or greater seconds was UN C. HARTUNG NASA. Langley Research Center, Hampton, VA, calculated. Author (El) 559 16 PHYSICS A94-69410 (Contract NAS2-13721) THREE-DIMENSIONAL THERMAL ANALYSIS FOR LASER- (NASA-CR-196132; NAS 1.26:196132; RIACS-TR-94-06) Avail: CASI STRUCTURAL INTERACTIONS HC A03/MF A01 HARTMUT H. LEGNER Physical Sciences, Inc., Andovar, MA" This paper prasants a new rcethod for computing acoustic signals ALBERT W. BAILEY, and MICHAEL F. HINDS Journal of from helicopter rotors In fonNerd flight. The aerodynamic and acoustic Thermophyslcs and Heat Transfer(ISSN 0887-8722) vol. 7, no. 4 solu_ons inthe ce_ flaid m (xxnputed with a flnits-dt_ranoe solver _or October-December 1993 p. 545-546 refs the Euler equations. A _ cylindrical _rchhoff surface is then (BTN-94-EIX94351142117) Copyright placed around the entire rotor system. This K]rchhoff sudace moves A three-dlmenelonel thermal anely_s method with direct applica- subesnlcaily w,h the rotorinforwaml flight. The flnlte-dlfferance solullon tion to laser-sbIJc_rel Interacllons has been developed. This robust, is Inteq_ofated onto thls cyllnddcel surface at each time step and a implicit finite-volume technique solves _ enthaiplc form of the heat Ki_dd_}ff IntagroSon is uesd to ceny the ocoustic elgnai _o the _ tield. condition eduaUon for laser mdiatlon Interacting Mth thrae.dimanslonel Computed values for high-speed impulsive noise show excellent aerospace structures. It utilizes finite dements derived from _ slnJC- agreement wflh model-rotor and flight-test expedrnantel data. Results tural analysis and accommodates arbitrary beam profiles to compute from the new method offer high accuracy with reasonable _r the ablative material response. Computed results for a compceite hat- resource recl_mmants. Author sUffened panel are illustrated. This method has also Veatecl laser- structural problems Involving oblique beam Incidence, complex structures, multiple matedais, and beam slewing. El 17 A94-60430 SOCIAL SCIENCES NEW TWO-TEMPERATURE DISSOCIATION MODEL FOR REACTING FLOWS Includes social sciences (general); administration and management DAVID P. OLYNICK North Carolina State Univ., Raleigh, NC documentation and Informationscience; econo_cs and cost analysis; and H. A. HASSAN Journal of Thermophystcs and Heat Transfer law and political science; and urban technology and thmsporlal_n. (ISSN 0887-8722) voL 7, no. 4 October-December 1993 p. 687-696 refs (B'TN-94-EIX94351142137) Cowright N94.34730"# National Aeronautics and Space Administration. A new two-temperature dlssoclatk_nmodel for _e coupled vibm- Lang_ Rmwch Cer_r, Hampton, VA. Uon.dlssoda_n prncess le dedved from Idnatlc theory. It is applied for NASNDOD AEROSPACE KNOWLEDGE DIFFUSION flows undergoing compression. The model minindzes uncemdntles RESEARCH PROJECT. PAPER 42: AN ANALYSIS OF THE aesnciated wilh the two-temparatum rnod_ of Perk. The efl_ts of the TRANSFER OF SCIENTIFIC AND TECHNICAL model on AOTV-type flowfielde are examined and compared with the park model. Caiculaticns are carded out for tiows wflh and wflhout INFORMATION (STI) IN THE US AEROSPACE INDUSTRY JOHN M. KENNEDY (indiana Univ., Bloomington, IN.), THOMAS _. When coneldedng flows with ionization, a four-temperature E. PINELLI, LAURA F. HECHT, and REBECCA O. BARCLAY 1994 rnodel is emrdoysd. For Rre II ¢ondMons, tho essump_ of oquINbdurn 17 p Presented at the Annual Meeting of the Amedcen Sociological between the vibrational and electron-electronic temperatura8 is some- Aesoc_tion, Los Angeles, CA, 5-9 Aug. 1994 what poor. A similar statement holde lot the translak_onsiand rotationel (Contract NAGW-1682) temperatures. These trande am consistent with results obtained using (NASA-TM-109863; NAS 1.15:10Q863) Avail: CASI HC A03/MF A01 direct simulation Monte Carlo (DSMC) method. Author (El) The U.S. aemepace Induslryhes a long hleto_ Offederal support for rasearch raiatsd to lWneeds. Slnce the establlstm_e_ of the Natlonai N94-35863"# National Aaronaut_s and Space _. Hugh Adv_ Coma2ttes for Ae_ (NACA) In 1915, _ federal L. Dryden Right Research Facility, Edwards, CA. Oovemmo_ hes ixovtded conUnuous mes_ch sup_ rai_ed _ mo_ ENGINE EXHAUST CHARACTERISTICS EVALUATION IN and aimmft dUgn. Thle nH_ch hes con_buted to the IntmTmticnel SUPPORT OF AIRCRAFT ACOUSTIC TESTING praandnsnce ofthe U.S. aercxqpaco Industp/. In _ pBper, we presant KIMBERLY A. ENNIX In NASA. Ames Research Caner, 1993 a esck_ ana_/,dsofaercepaceengn,ecs and sdant_taand how Technicel Papar Contest for Woman. Gear Up 2000: Woman in Moton _r atl_udesand behavkxs br_pactthefk_wofsolant_cand technlcel p 13-20 Feb. 1994 (SLY).We use a _ framewo,k to explainthe Avail: CASI HC A02JMF A02 Spofty dlueminatlon of federally funded aerospace research. Our NASA Dryden Right Research Fadllty and NASA Langley Re- raeserch is aimed towarde providing fedarel polioymakem wflh a clearer search Center completed a joint acoustic flight test pn)omm. Test undemtand_g Of how n wben tedaraNy _unded aerospace reseamh ob_c_ were (1) to quanUfy and evakmm subamic dlmb-mo-cru_ is used. This understanding will help policymakera design improved nolse and (2) to obteln a quality noise datebese for ues In validating the Informatk)n Inu'_fer systems that wig aid the compat_vaness of the AJmraftNoise Prediction Program. These tests were oonducted uJng U.S. aerospace industry. Author (revised) aircraft with engines that represent the high nozzle _m ra_o of future transport designs. Test flights wera _ at subsonic speeds that exceeded Mach 0.3 using F-18 and F-16XL aircrafL This N94.35899°# National Aeronautics and Space Administration, papar describes the efforts of NASA D_jden Fllght Reesan:h FadUly In Washington, DC. this flight test program. Topics dlscmaed includethe rest elrcraft, estup, BUDGET ESTIMATES, FISCAL YEAR 1995. VOLUME 1: and matrix. In addition, the engine modeling codes and nozzle exhaust AGENCY SUMMARY, HUMAN SPACE FLIGHT, AND charsctarlslics are described. Author SCIENCE, AERONAUTICS AND TECHNOLOGY 1994 340p N94-360Q1"# Research Inst. IorAdvanoed Computer Science, Moflett (NASA-TM-109791; NAS 1.15:109791) Avail: CASI HC A15/MF A03; SOOHC Field, CA. COMPUTATION OF HEUCOPTER ROTOR ACOUSTICS IN The NASA budget raquest hu baen _ In FY 1995 Inlo FORWARD FLIGHT four _opropr_tions: human space flight; science, _, ROGER STRAWN (Army Aviation Systems Command, Moffatt t_hno_gy;, mi_on _ppoe; and Inmm_ ganer_. The tu'cen m Field, CA.) and RUPAK BISWAS Mar. 1994 11 p Presented flight appropriations provides funding for NASA's human space flight at the 19th Army Science Conference, Orlando, Ft., 20-24 Jun. 1994 actlv_m. This includes the on-orblt i_ra (space sta_on and Subm_ed for publication Spacaieb), tr_r_tat_ cepa_,ty (space shuU_ program, ,n_._ng 560 SOCIAL SCIENCES 17 operations,programsupport,andperformanceandsafetyupgrades), Women (ACW) sponsored the second ACW Technical paper Contest andtheRussiancooperationprogram,whichIncludestheflightactivi- for Ames women in order to increase the visibility of, and to encourage tiesassociatedwiththe cooperative research flights to the Russian Mir wr_ng for publication by Ames women sdentists, engineers, and space station. These activities are funded in the following budget line technicians. The topics of the contest paper mirrored inthe topics of the items: space station, Russian cooperation, space shuffle, and payload 1993 Society for Wornen Engineers (SWE) National Convention, which utilization and operations. The science, aeronautics, and technology included technological, workplace, global, and family issues. appropriations provides funding for the research and development activities of NASA. This includes funds to extend our knowledge of the N94.36117"# NationaiAe_ and SpaceAdministmtk)n. Ames earth, its space environment, and the universe and to invest in new Research Center, Moffett Field, CA. technologies, particularly in aeronautics, to ensure the future competi- RESEARCH AND TECHNOLOGY, 1993 tivanees of the nat_n. These objectives am achieved through the May 1994 306 p Odginai contains color illustrations following elements: space science, life and mlcrogravity sciences and (NASA-TM-108816;A-94041; HAS 1.15:108816) Avail: CASI HC A14/ applications, mission to planet aerlh, aeroneuticeJ research and tech- MF A03; 12 functional color pages nology, advanced concepts and technology, launch services, mission Selected research and technology activities at Ames Research communication services, and academic programs. CASI Center, includingthe Moffett Field site and the Dryden Flight Research Facility, am summarized. These activities exemplify the center's varied N94-35262# Federal A_al_n AdministrstJon,Washington, DC. and produclwe research efforts for 1993. This year's report presents THE FEDERAL AVIATION ADMINISTRATION PLAN FOR some of the challenging work recently acoompIIshscl In the areas of RESEARCH, ENGINEERING AND DEVELOPMENT aerospace systems, flight opera_ons and msaarch, aerophysics, and May 1994 190 p Odginel contains color illus'cations space research. Author (mv4sad) Avail: CASI HC A09/MF A02; 1 functional color page The Federal Aviation Admlnistmtion (FAA) manages and opar. ates the National Airspace System (NAS), a significant national re- source. However, the demands on this system am continuously growing, and changing technologies provide the opportunity to improve system effectiveness and efficiency. To this end, the FAA's research, engineering, and development program is an investment in the future that will sustain the United States preeminence in avla_on throughout the world. Without this investment, the United States leadership would erode. Thus, the importance of avist_n to the netion mandates a comprehensive research, engineering, and development program to ensure both the safety of public air tmn_ and the fuffillment of national prlodUes and policy goals. Derived from text N94-35070"# NationaiAaronautics and SpaceAdmlnistratlon. Ames Research Center, Moffett Field, CA. DIRECTOR'S DISCRETIONARY FUND Report, FY 1992 May 1993 133p (Contract RTOP 307-51-50) (NASA-TM-103997; A-93031; NAS 1.15:103997) Avail: CASI HC A071 MF A02 This technical memorandum contains bdef technical papam de- scribing msaarch and technolngy development programs sponsored bythe ARC Director's Discretionary Fund dudng rmcaiyear 1992 (Oct. 1991 through Sep. 1992). An appendix provides administrative Infor- mation for each of the 45 sponsored research programs. Author N94-35444# Advisory Group for Aerospace Research and Develop- merit, Neuilly-Sur-Seine (France). AGARD HIGHLIGHTS 93/2 Sep. 1993 47 p Odginai contains cokx illustrations (AQARD-HIGHLIGHTS-93/2) Copyright Avail: CASI HCA03/MFA01 Highlights of the _ and accomplishments of the Advisory Group for Aerospace Research and Development (AGARD) dudng the second quarter of 1993 am discussed. Topics covered include technol- ogy cooperation with Russia, including aircraft flight safety;, the von Karman Medal and the Sclermc Achievement Award for 1993; two arises on a visit to Zhukovsky, including discussion on fluid dynamics related to helicopters; intemationai air traffic handling cooperation; and the European Transonic Wind Tunnel (ETW). CASI N94-35961"# National Aaronautics and Space Administration. Ames Research Canter, Moffett Field, CA. 1993 TECHNICAL PAPER CONTEST FOR WOMEN. GEAR UP 2000: WOMEN IN MOTION ROBIN ORANS, ed., SOPHIE DUCKETT, ed., and SUSAN WHITE, ed. Feb. 1994 131p ContestheldlnMoffettF'mld, CA, 1993 (NASA-CP-10134; A-93034; NAS 1.50:10134) Avail: CASI HC A07/ MF A02 The NASA Ames Research Center Advisory Comm_ae for 561 SUBJECT INDEX AERONAUTICAL ENGINEERING / A Continuing Bibfiography (Supplement 308) September 1994 Typical Subject Index Listing ADAPTIVE CONTROL AERODYNAMIC INTERFERENCE Six.degree-of-freedom guidance and control-entry Propulsion-induced aerodynamic effects measured with analys_s of the HL-20 a full-scale STOVL model IBTN-94-EIX94351137056J p 544 A94-60396 [BTN-94-EIX943113291201 p 519 A94-60180 AEROACOUSTICS I SUBJECT HEADING I AEROOYNAMIC LOADS Computer=on of helicopter rotor acoustics in forward Artificial neural networks for predicting nonlinear flight dynamic helicopter loads I [NASA.CR.196132] p 560 N94.36031 IBTN-94-EIX9430t3159891 p 515 A94-60025 AERODYNAMIC CHARACTERISTICS ABORTED MISSIONS Determination of slender body aerodynamics using Navzer-Stokes solver for hyperson0c flow over e slender discrete vortex methods STS-55 pad abort: Engine 2011 oxldlzlr prebumer cone ugmented spark igniter check valve leek [ BTN-94-EIX943113306791 p543 A94-60112 [ BTN-94-EIX94311330681 J p543 A94-60110 Pressure measurements on • forwerd-swept Determination of slender body aerodynamics using w_g-canard configuration discrete vortex methods IBTN-94-EIX94311329149J p 516 A94-60151 [ BTN.94-EIX943 t 1330679 ] p543 A94-60112 R-193830)_ _A_RON IP 138 N94-12806 Tail load calculebons for light awplanes Applications of computational fluio dynamos to the [BTN-94-EIX94311329148] p 517 A94-60152 aerodynamics of Army projectiles [BTN-94-EIX94311330678] p 516 A94-60113 Alleviation of side force on tangent-ogwe forebodies Aerodynamic properbes of crescent wing planforms using passNe p A-1 AERODYNAMICS SUBJECT INDEX AERODYNAMICS AEROSPACE INDUSTRY AIR TRAFFIC CONTROL Crossflow topology of vortical flows NASA/DaD Aerospace Knowledge Diffusion Research Final-Approach Spacing Aids (FASA) evaluation for I BTN-94-EIX9430 t 315993 J p515 A94-60029 Project Paper 42: An analysis of the transfer of Scientific terminal-area, time-based air traffic control Determination of slender body aerodynamics using and Technical Information (STI) in the US aerospace INASA'TP-3399] p 529 N94-36048 discrete vortex methods industry AIR TRANSPORTATION IBTN-94-EtX943113306791 p 543 A94-601t2 INASA-TM-109863] p 560 N94-34730 The Federal Aviabon Administration plan for research, engineering and development p 561 N94.35262 Applications of computational fluid dynamics to the AEROSPACE SAFETY AIRBORNE EQUIPMENT aerodynamics of Army projectiles Aerospace Safety Advisory Panel IBTN-94-EIX943113306781 p 516 A94-60113 [NASA-TM-109840} p 545 N94-35390 Minimum performance standards: Airborne low.range radar altimeters Analysis of aerodynamics of airfoils moving over a wavy AEROSPACE SCIENCES wall Director's discretionary fund IRTCA-DO-1551 p 537 N94-35344 AIRBORNE RADAR IBTN-94-EIX94311329130] p 536 A94-60170 [NASA.TM.1039971 p 561 N94-35370 Minimum performance standardsl Airborne low-range AEROSPACE SYSTEMS Aerodynamic design of super maneuverable aircraft radar altimeters p 533 N94-34617 Aerospace applicabons of magnebc boanngs [RTCA-DO-155] p 537 N94-35344 p 554 N94-35837 Flight Mechamcs/Estimation Theory Symposium, 1994 AIRCRAFT ACCIDENT INVESTIGATION AEROSPACE TECHNOLOGY TRANSFER INASA-CP-3265] p 545 N94-35605 Safety study: A review of fllghtcrew-involved, meier Control of maglev vehicles with aerodynamic and NASA/DaD Aerospace Knowledge Diffusion Research acc_ents of US air careers, 1978 through 1990 g_daway disturbances p 554 N94-35842 Project. Paper 42: An analysis of the transfer of Scientific [PB94-917001] p 529 N94-35482 and Technical Information (STI) in the US aerospace Future ultra-speed tube-flight p 555 N94-35918 Aircraft accident report: Uncontrolled collision with industry Research and technology, 1993 terrsin, American Internabonal Airways Flight 808, Douglas [NASA-TM-t09863| p 560 N94-34730 INASA-TM-1088161 p 561 N94-36117 DC-8-61, N814CK, US Naval Air Stabon. Guantanamo Bay, AGARD highlights 93/2 AEROELASTICITY Cuba. 18 August 1993 [AGARD-HIGHLIGHTS-9312] p 561 N94.35444 Localizabon of aeroelasbc modes in mistuned [PB94-910406] p 529 N94-35521 Challenging the Future - Journey to Excellence AIRCRAFT ACCIDENTS hlgl'Penergy turbines Aeroproput_on stretag,c plan for the 1990's [STN-94-EIX94321333307] p 547 A94-60039 Aircraft accident flight path simulation and animation (NASA-TM-109250] p 545 N94-35591 [ BTN-94-EIX943113291291 p518 A94-60171 Dynamic aeroelastic stability of vertical.axis wind AEROTHERMODYNAMICS Structural integrity and containment aspects of small turbines under constant wind velocity Charactensbca of the Shuttle Od_ter leeside flow during gas turbine engines IBTN-94-EIX94321333311 ] p 548 A94-60043 a re-enlrf condltk)n { BTNo94-EIX94331337500 ] p 550 A94-60335 Parameter estimates of an aeroelastic airoraft as [BTN-g4-EIX94311322888] p 520 A94-60208 Annual review of aircraft accident data: US general affected by model ,,JmplifP..ations Aerodynamic beabng anvironmeat definition/thermal arm|ion calender year 1991 [BTN-94-EIX94311329142] p 517 A94-60158 protection system selecbon for the HL-20 [PB94-t27982] p 528 N94.3499t Time sirnu_etion of flutter wdh large stiffness changes [ BTN-94-EIX94351137058 ] p 544 A94-60398 Safety study: A rew, ew of flightcrew-involved, major IBTN-94-EIX94311329132] p 518 A94.60168 HL-20 computabonai fluid dymzrmcs analysis accidents of US sir namers. 1978 through 1990 Modal coordinates for aaroelestic anaiy_as with large [ BTN.94-EIX94351137059 ] p545 A94-60399 [ PB94-917001J p 529 N94-35482 local structural variations Three-dimansa_nal thermal anaiyms for taser-elructurel Annual review of aircraft accident data. US general ISTN-94.EIX94311329131] p 518 A94-60169 interactions aviabon, c=dender year 1992 Will the reel dynamic instability mechanism please be [BTN-94-EIX9435tt42117] p 580 A94-60410 [PB94-181054] p 529 N94-35496 recognized! p 552 N94-34976 Natural convection in a cavity with fins attached to both Aircraft accident report: Uncontrolled collision with Rutter supwesmon digital control law deign and tesbng vertical walls terrain, American In|area|lot, el Airways Flight 808, Douglas for the AFW wind tunnel model p 540 N94.35873 [BTN-94-EIX94351142119] p 550 A94-60412 DC-8-61, N814CK, US Naval Air Station, Guantanamo Bay, AERONAUTICAL ENGINEERING Combined LAURA.UPS solution procedure for Cuba, 18 August 1993 National facilities study. Volume 2: Task group on che_ly_eac_og gows 1PB94-910406] p 529 N94.35521 aeronautical re_)erch and development facilities reporl [NASA-TM-107964] p 551 N94-34721 AIRCRAFT APPROACH SPACING [ NASA-TM- t09855 ] p542 N94-34633 Dev_opment end application of computabonal Final-Approach Spacing Aids (FASA) evaluation for terminal-area, bme4_aerJ air traffic control Nabocml tacilibes study, Volume 2A: Facility Study Office aemthermodynamics flowheld computer codes on the Nabonel Wind Tunnel Complex [NASA-CR-196136] p 526 N94-35498 tNASAoTP-3399] p 529 N94.36048 AIRCRAFT COMMUNICATION [NASA-TM.109856} p 542 N94-34634 AGING (MATERIALS) Effect of coarse second phase particles on fatigue crack ATM and FIS data Link s_s Aerospace Safety Advisory Panel |BTN-94-EIX94331335533] p 530 A94-602t4 [NASA-TM-109840] p 545 N94-35390 p¢opagetion of an Al-Zn-Mg-Cu alloy [BTN-94-EIX94301320144] p 546 A94-60853 AIRCRAFT COMPARTMENTS Challenging the Future . Journey to Excellence AI4-1G HEUCOWrER A revmw of computer evacuation models and their data Aeropro_sion strstegzc plan for the 1990's Hot gas ingestion effects on fuel control surge recovery needs [ NASA-TM- t 09280 ] p545 N94-35591 ind AH-1 rotor dnve train torque spikes [DOTIFAAIAM-94/11] p 528 N94-35236 AERONAUTICS [NASA-CR-191047] p 538 N94-34993 AIRCRAFT CONFIGURATIONS National taci_les study. Volume 1: Facilities inventory AIR BREATHING BOOSTERS Joined*wing model vibrations using PC-based modal [NASA-TM-t09854J p 541 N94-34632 Control strategies for space boosters using air collectmn testing and finite element analy_ds National facilibes study. Volume 2: Task group on systems [BTN-94-EIX94311329141] p 517 A94-60159 aeroneutmal research and development facilities repot [BTN.94.EIX84311330685| p 543 A94-60106 AIRCRAFT CONSTRUCTION MATERIALS [NASA-TM-109855] p 542 N94.34633 AIR BREATHING ENGINES Allevmtion of side torce on tangent-ogNe iorebod0es AGARD highlights 93/2 Co_rol strsteg0es for space boosters using sir collection using pass,re porosity I AGARD-HIGHLIGHTS-93/2| p 561 N94.35444 systems [ BTN-94-EIX94311329126 ] p536 A94-60174 Research and technofogy, 1993 [BTN-94-EIX94311330685 ] p543 A94-60106 Superso_c transport wing minimum weight design I NASA-TM.1088t 6 J p561 N94-36117 Tectmelugy and staging effects on two-stage-to-orbit integrating aerodynar_cs and structures AEROSPACE ENGINEERING systems [BTN-94-EIX94311329123] p 518 A94-60177 Retained mechanical propertms of a new AI-Li-Cu-Mg-Ag An assessment of fatigue crack growth prediCbO_ [ BTN-94-EIX94311322891 ] p520 A94-60205 models for aarotN_ce structures p 551 N94.34586 AFOSR Contractors Propulsion Meeting alloy as a function of thermal exposure brae and lAD-A279028| p 539 N94.35746 temperature NatiOnal facilities study. Volume 1: Facilities irNeotory AIR FLOW [BTN-94-EIX94301320164J p 546 A94-60873 [NASA-TM-109854J p 541 N94-34632 In_mlxxl of 10ubOling liquid jets from multiple injectors AIRCRAFT CONTROL National facilities study. Volume 3: Mlesion and into a supersonic stream Design of integrated flight and powerplent controf requirements model report [BTNo94-EIX94321333316| p 520 A94-60267 systems p 532 N94-34609 [NASA-TM-109657] p 542 N94-34635 Prskminary kwsebgetions on improving air-augmented Yaw control by tangential forebody blowing National tacitibes study. Volume 4: Space operabons rocket performance p 539 N94-346t5 facilities task group IBTN-94-EIX94321333323] p 544 A94-60274 X-31A control law de_ p 540 N94-34618 iNASA-TM*1098581 p 542 Ng4-34636 Espenmantal inveabgetion on supersonic combustion YAV-SB reaction control system bleed end control power Nabonal facilities study. Volume 5: Space research and (2) usage m hover end tran_ben development fecilitms task group IBTN'94"EIX94351144985 ] p 537 A94-60447 |NASA-TM-t04021] p 540 N94-34994 INASA-TM-t09859| p 542 N94-34637 Flow quality studies of the NASA Lewis Research Center Flight testing a propuis4on.controfled aircraft emergency NASA/DaD Aerospace Knowledge Dfffumon Reich Ic,ng Research Tunnel flight control system on an F-15 mrplene Project. Paper 42: An analysis Of the transfer of Scientific INASA.TM-106545] p 543 N94.34919 {NASA-TM-4590| p 540 N94-35258 and Technical Inlormebon (STI) in the US aerospace Active thermal isolation for temperature responmve Piloted simulebon study of two blt-w_ng control senecrs p 541 N94-35962 [NASA-TM-109863i p 560 N94.34730 [ NASA-CASE-LAR- 14612-1 ] p552 N94-35074 F/A-18 Iorebody voctox cortt_ol. Volume 1: Static tests JPRS report: Science and teshnology, Central Eureka HOt Corrosion Test FecLih'y at the NASA Lewis Speci_ [NASA-CR-451M?.] p 528 N94-35991 IJPRS.UST-94-O05] p 553 N94-35342 ProjectsLaboratory [NASA-CR-195323| p 543 N94-35267 AIRCRAFT DESIGN JPRS report: SOerlce and technology. Central Euras_ Measurement of dlffumon m fluid systems: ApplP..abons [JPRS-UST.94-0t0] p 553 N94-35385 AIR NAVIGATION to the supercdtical fluid region JPRS report: Science and technology. Central Eurawa Design and analysis of a Kalman filter for ten_n..referenced posibo_ng and gu_danoe [BTN-94-EIX94311330660) p 548 A94-60131 [JPRS-UST-94-012] p 553 N94-35387 [ BTN-94-EIX94311329124 ] p557 A94-60176 The role o! fatigue analysis for design of military AGARD P4ghl_lhta 9312 AIR POLLUTION mroraft p 531 N94-34594 [AGARD-HIGHLIGHTS-9312] p 56t N94-35444 Raman measurements at the exit of a combustor USAF/AEDC aerodynamic and propuismn ground test Research end technology, 1993 seclor and evaluation techniques for highly maneuverable aircraft: INASA-TM-108816] p 561 N94-36117 I BTN.94-EIX94341338356] p 546 A94-60348 Capabilities end challenges p 532 N94-34606 A-2 SUBJECT INDEX ALUMINUM ALLOYS Design of integrated flight and powerplant control Parameter estimates of an aeroelastic aircraft as AIRCRAFT WAKES systems p 532 N94-34609 affected by model s_mplificat:ons Wake curvature and airfoil lift Aerodynamic design of super maneuverable aircrah IBTN-94-EIX94311329142J p 517 A94.60158 IETN-94-EIX94311329147J p 517 A94-60153 p 533 N94-34617 Supersonic transport wing minimum wmght design Numerical modeling studies of wake vortex transport Operational agility: An overview of AGARD Working integrating aerodynamics end structures end evolution w_thin the planetary boundary layer Group 19 p 534 N94-34625 IBTN-94-EIX94311329123} p 518 A94-60177 INASA-CR't 96078] p 529 N94-35522 Design oriented structural analysis Ornithopter wing design AIRFOIL OSCILLATIONS [BTN-94-EIX943313374991 p 521 A94-60334 INASA-TM-109124J p 551 N94-34722 Reattachment studies of an oscillating aidoil dynamic AIRCRAFT ENGINES Yaw control by tangential forebody blowing stall flowfield p 539 N94-34615 Raman measurements at the exit of a combustor [BTN-94-EIX943013159801 p 515 A94.60016 AIRCRAFT NOISE sector Unsteedy lift of a flapped airfoil by indicter concepts Low-no_se, I_gh-strength, spiral-bevel gears for I BTN-94-EIX94341338356 J p .546 A94-60348 IBTN-94-EIX94311329118J p 519 A94-60182 helicoc.ter transmissions Approximate sJmilenty penciple for a full-scale STOVL Companson of p_tch rate history effects on dynamic [BTN-94-EIX94321333312J p 548 A94-60044 elector stall p 535 N94-34968 1993 Technical Paper Contest for Woman Gear Up [BTN-94-EIX94341338360} p 550 A94-60352 2000: Women in Motion AIRFOIL PROFILES Pred_ctien of unsteady alrfotl flows el large angles of Progress and purpose of IHPTET program [NASA-CP-10134} p 561 N94-35961 incK:ience p 525 N94.34978 p 538 N94-34607 Engine exhaust characteristics evaluation in supporf of Engine charactecstics for agile sircraff aircraft acoustic testing p 560 N94-35963 Some aspects of unsteady separation p 538 N94-34608 AIRCRAFT PARTS p 525 N94-34979 National facilities study. Volume 2: Task group on Determination of tire-wheel interface loads for aJrcraff AIRFOILS aeronautical research and development facilities report wheels Reettachment studies of an osciflating airfoil dynamic INASA-TM-t09855) p 542 N94-34633 ISTN-94-EIX94311329136] p 517 A94-60164 stall flowfleld Challenging the Future - Journey 1o Excellence Aerospace applications of magnebc beanngs IBTN-94-EIX94301315980J p 515 A94-60016 Aeropmpulsion sti'ategic plan for the 1990's p 554 N94.35837 Explicd Kufta cono_tion for an unsteady two-dtmensional INASA-TM-t09250J p 545 N94-3559t AIRCRAFT PERFORMANCE constant potential panel method Engine exhaust characteristics evaluation in support of X-31 tactical utility: Initial results p 533 N94.34620 [BTN-94-EIX94301315990J p 515 A94-60026 aircraft acoustic testing p 560 N94-35963 EFA flying qualitms specification end its utilisation Inverse design of super-elliotic cooling passages in AIRCRAFT FUELS p 533 N94-34621 coated turbine blade airfoils Measurement of ¢kffus_n in fluid systems: Applications The influence of flying qualities on operational agility [ BTN.94-EIX943113306541 p548 A94-60137 to lt_e supercntical fluid regien p 534 N94-34628 Wake curvature end _utfoillift [STN-94-EIX94311330660J p 548 A94-60131 An agility metric structure for oporetional agility [BTN-94-EIX94311329147] p 517 A94-60153 Unleaded AVGAS program p 534 N94-34629 Analysis of aerodynan_cs of aJrfods moving over a wavy IAD-A278650J p 547 N94-35795 Evaluabng the dynamic response of in-flight thrust wall AIRCRAFT GUIDANCE caJculetien techn_ues during throttle transmnts IBTN-94-EIX94311329130} p 536 A94-60170 Results from the STOL end Maneuver Technology [NASA-TM-4591 ] p 535 N94-35241 Unsteady lift of a flapped eidoil by indic=el concepts Demonstration program p 532 N94-34611 Piloted simtdabon study of two tilt-welg control JBTN-94-EIX94311329118 ] p519 A94-60182 AIRCRAFT ICING concepts p 541 N94-35962 Pred_cbon of ice shapes and their effect on airfoil drag Prediction of ice shapes and their effect on airfoil drag AIRCRAFT PILOTS {BTN-94-EIX94311329115] p 519 A94-60185 [BTN-94-EIX94311329115] p 519 A94-60185 The influence O4 data link-provided graphical weather Calc_abon of real-gas effects on airfoil aerodynamic AIRCRAFT INSTRUMENTS on pilot decismn-making characteristics Wide-Eye (fm)/helmet mounted display system for [AD-A278871] p 556 N94-35596 {BTN-94.EIX94351142143J p 521 A94-6043S rotorcrafl applicetmns AIRCRAFT REMABIUTY Unsteady flow past an ak'toil pitched at constant rate I BTN-94-EIX94331335528 ) p549 A94-60209 Structural integnty end containment aspects of small p 524 N94-34969 Tactmal cockpits: The coming revolution gas turbine engines The unsteady pressure field end vortieity productiion at [ BTN-94-EIX94331335530 ] p530 A94-60211 J BTN-94.EIX94331337500] p 550 A94-60335 the suction st=dace of a I_tcblng airtoil AIRCRAFT LANDING An Assessment Of Fetigue Damage and Crack Growth p 524 N94-34972 Aircraft landing gear positioning co¢_errNng abnormal Predictld¢_ Techniques Characterization of dynamic stall phenomenon using landing cases JAGARD-R-797] p 550 N94-34581 two-dimensonal unsteady Nav)er-Stokes equetions lBTN-94-EIX94311329140] p 536 A94-60160 Him'mr 2: A companson of US and UK approaches to p 524 N94-34974 Synthetic vision for enhancing poor visibility flight fatigue clearance p 531 N94.34596 Con_ed unsteady flows of sirfods at high incidence operations Fatigue design, lest and in-se_ice experience of the p 525 N94-34975 [BTN-94-EIX94331335531 ] p 557 A94-60212 BAe Hawk p 531 N94-34597 Coml_tatlen of unsteady flows over a_loils AIRCRAFT LAUNCHING DEVICES AIRCRAFT I_dUrETY p 525 N94-34977 Technology and staging effects on two-stage-to-odoit Annual review o1 am_raff ecc_ent data: US general Prediction o4 unsteady airfoil flows at large angles of systems eviebon calendar year 1991 inodence p 525 N94-34978 { BTN-94-EIX94311322891 ] p520 A94-60205 {PB94-127982] p 528 N94-34991 Effect of initial acceleration on the _nt of the AIRCRAFT MAINTENANCE A revmw oi computer evacuabo_ models and thor data flow fiek:l of an akfoil pltcblng at constant rate Artificial neural networks for predicting nonlinear needs p 526 N94-34989 dynamic hetmopter loads [DOTIFAAIAM.94111| p 528 N94-35236 Active thermal isolation for temperature responsive IBTN-94-EIX94301315989} p 515 A94-60025 AIRCRAFT SPECIFICATIONS sensors Scheduled maintenance optimization system EFA flying qualities specHication and _ts utilmetion [NASA-CASE-LAR-14612-t ] p 552 N94-35074 [BTN-94-EIX94311329145] p 517 A94-60155 p 533 N94-34621 AIRFRAMES Aircraft fleet maintenance based on structural rellebility AIRCRAFT STABILITY Investigabon of Monte Carlo simulation in FAA program analysis Static and dyrmm,c flight-path stability o4 mrplanes KRASH {BTN-94-EIX94311329134] p 517 A94-60166 [BTN-94-EIX94361135428} p 522 A94-60625 [BTN-94-EIX94311329128] p 536 A94-60172 Risk analysis of the C-141 WS405 inner.to-outer wing EFA flying qualities spectticetK)n and its utilisation Effect of coarse second phase particles on tat=gue crack Joint p 531 N94-34592 p 533 N94-34621 propagation of an Al-Zn-Mg-Cu alloy The role of fatigue analysis for design of military AIRCRAFT STRUCTURES | BTN-94-EIX94301320144 ] p 546 A94-60853 aircraft p 531 N94.34594 Arcraft fleet maintenance based on stnJCtUml rJabilh'y Field de_oyable nondestructive impact damage AIRCRAFT MANEUVERS enalys_ assessment methodology for composite structures Determination O4 slender body aerodynamics using [BTN-94-EIX94311329134) p 517 A94-60166 [BTN-94-EIX94301321378] p 546 A94-60892 discrete vortex methods Tbree-d_mens_nal thermal analysis for leser-struc'mral Fat_ue menagement and verification of mrtrames [BTN-94-EIX94311330679] p 543 A94-60112 interactions p 531 N94-34591 USAF/AEDC aerodynamic and PrOpulsion ground test |BTN-94-EIX94351142117] p 560 A94-60410 Hamer 2: A comparison of US end UK approaches to and evaluation techniques for highly maneuverable aircraft: Measurement and predictldn O4 _'nany, c temperatures fatigue clearance p 531 N94-34596 Capebilitms and challenges p 532 N94-34606 in unsymmeb'ically cooled glass windows An ov_rv_mw of the F-16 sennce Ide approach Results from the STOL and Maneuver Technology { BTN-94-EIX94351142126 ] p550 ,6,94-60421 p 532 N94-34599 Demonstration p¢ogram p 532 N94-34611 Field deployable nondestrucltve impact damage Ground vibrebon test of the XV-15 Ti_rotor Research X.31 tactical utility: Initial results p 533 N94-34620 assessment methodology for conga structures Amcraft and pretest pcedicbons p 541 N94-35972 Flying qualities evaluation maneuvers [ BTN-94-EIX94301321378 ] p 546 A94-60892 AIRUNE OPERATIONS p 533 N94-34623 An Assessment of Fatigue Damage and Crack Growth Safety study: A revmw of fl_ghtcrew-involved, m&lor The influence of flying qualdies on op_atienal agdity Prediction Techniques accidents of US air can'iers, 1978 tl','o_gh 1990 p 534 N94.34628 [AGARD-R-797] p 550 N94-34581 [PB94-917001] p 529 N94-35482 An agility metnc structure for o_eretienal agility An assessment of fatigue crack growth prediction ALGORrrHMS p 534 N94-34629 mod_s for aerospace sltuctures p 551 N94-34586 A three dimensional multigrld Reynolds-averaged Application of centhfuge based dynamic fti_It fMmuletion Notch fatigue assessment 04 aJreraft components mung Na,,qer.Stokes solver for unaUuctL_ed meshes to enhanced maneuverability RDT/E a fracture mechanics based l_U_m_or INASA-CR-194906} p 528 N94-35994 p 541 N94-34630 p 551 N94.34588 ALUMINUM ALLOYS Concepts end applcatien of dynar_c separation for Design prorated sUuctuml anaty_s Effect of coarse second phase particles on fatKjue crack agility and super-maneuverability of aircraft: An iNASA-TM-109124] p 551 N94.34722 _ooagabon of an Al-Zn-Mg-Cu alloy assessment p 535 N94-34988 An oveneew of recent advances in system [BTN-94-EIX94301320144] p 546 A94-60853 AIRCRAFT MODELS identificabon p 546 N94-35880 Ret_uned mechan¢.al propertms of a new AI-Li-Cu-Mg-Ag Effects of model scala on flight charectenstics end Frequency domain analysis of the random loading of alloy as a function of themlel exposure t,me and design parameters cracked panels temperature IBTN-94-EIX94311329143J p 517 A94-60157 INASA-CR-1960211 p 556 N94-35974 [BTN-94-EIX94301320164J p 546 A94-60873 A-3 SUBJECT INDEX ANGLE OF ATTACK ANGLE OF AI"rACK AUTONOMOUS NAVIGATION BOUNDARY LAYER CONTROL Reattachment studies of an oscillating airfoil dynamic Accurate estimation of obiect location m an image Aerodyrmmic design of super maneuverable aircraft stall flowheld sequence using helicopter flight data p 533 N94-34617 IBTN-94-EIX94301315980] p 515 A94-60016 p 537 N94-35055 The quest for stall-free dynamic lift p 525 N94-34986 Incipient torsional stall flutter aerodynamic expenments AVIATION METEOROLOGY Mechanisms of flow control with the unsteady bleed on t_ee-dimensional w=ngs The influence of data liok-provided graphm..al weather IBTN-94.EIX94341338362 t p522 A94-60354 on pilot decision-making technique p 525 N94-34987 Damage tolerance management of the X-29 ve_cal lAD-A278871| p 556 N94-35596 Concepts and application of dynamic separation for agility and super-maneuverability of aircraft: An tad p 531 N94-34595 Data requ_remanta for calling and walbilify products assessment p 535 N94.34988 High incidence flew analysis over the Rafale A development The aerodynamic and heat transfer effects of an endwall p 522 N94-34612 lAD-A278959| p 556 N94-35720 boundary layer fence in a 90 degree turmng square duct Dynamic tests to demonstrate lateral control using Terminal Doppler Weather Radar (TDWR) Low Level lAD-A2789031 p 553 N94-35803 torebody suction on large scale models in the DRA 24 Wind Shear Alert System 3 (LLWAS 3) integration studies foot wind tunnel p 539 N94-34613 BOUNDARY LAYER FLOW at Orlando international Airport Structure of local pressure-driven three-dimensional Techniques for aerodynamic characterization and IAD-A278957J p 557 N94.35807 transient boundary-layer separation performance evaluation at high angle 04 attack AXIAL FLOW p 533 N94.34614 tBTN-94-EIX9430t3159791 p 515 A94-60015 Axial compressor performance duhng surge Computation of unsteady 1lows over airfoils Yaw control by tangential fcrebody I_owmg [ BTN-94-EIX94321333308] p 548 A94-60040 p 525 N94-34977 p 539 N94-34615 AXIAL FLOW TURBINES Some aspects of unsteady separation Aerodynamic design of super maneuverable aircraft Prodicbon of unsteady airfelt flows at large angles of p 525 N94-34979 p 533 N94-34617 incidence p 525 N94.34978 X-31A system identification applied to post-stall fkght: BOUNDARY LAYER SEPARATION Aerodynamcs and thrust vectonng p 540 N94-34619 Structure of local pressure-drrven three-dimensional Application of cun'ent departure resistance criteria to B transmm boundary-layer separation the post-stall manoeuvenng envelope [ BTNo94-EIX943013159791 p 515 A94-60015 p 533 N94.34622 BAFFLES Control of leading-edge separation on a cambered delta wing p 539 N94-34616 Compenscn of oitch rate histonf effects on dynamic Computational analysis of a single _et impingement stall p 535 N94-34968 ground effect lift loss Experimental studies of shock-wave/wall-let interaction [BTN-94-EIX94311329114] p 519 A94-60186 in hypersonic flow. part A Computed unsteady flows of airlolts at high incidence Natural convection in a cavity with fins attached to both | NASA-CR-195957] p 523 N94-34964 p 525 N94-3,4975 vertical walls Physics of Forced Unsteady Separation Effect of initial accaierabon on the devalppmant of the [BTN-94-EIX94351142119] p 550 A94-60412 INASA-CP-31441 p 552 N94.34966 flow field of an airfoil pitching st constant rate BARIUM OXIDES Unsteady separation exbenmanta on 2-D airfoils, 3-D p 526 N94-34989 Processing ytthum barium copper oxide superconductor wings, and model hehcopter rotors p 524 N94.34967 Wind tunnel measurements on a lull-scale F/A-18 with in near-zero gqlvlty Unsteady separation process and vor1_ balance on s tangentially blowing slot --- conducted in the Ames 80 IBTN-94-EIX943f1332378] p 550 A94-60951 unsteady aMoils p 524 N94-34970 by 120 foot wind tunnel p 527 N94-35965 BASE FLOW Control of leschng-edge vorl_es on a delta wing F/A-18 forebody vortex control. Volume 1: Static tests Drag reduction for turbulent flow over a prOleCtile, pert p 524 N94-34971 I NASA-CR-4582 ] p 528 N94-35991 2 Computed unsteady flows of turfolls at high inodence ANGLES (GEOMETRY) | BTN-94-EIX94311322900 ] p520 A94-60196 p 525 N94-34975 Effects of the roll angle on cruciform wing-boo'y BASE HEATING Will the real dynamic instability mechanism please be configurations at high incidences A rewew and develof)ment of correlations for base recognized! p 552 N94-34976 IBTN-94-EIX94311322903] p 520 A94-60193 pressure and bass heating in super'sonic flow Prediction of unsteady airfoil flows at large angles of ANNEAUNO |SAND93-0280] p 526 N94-35360 incidence p 525 N94-34978 Processing yttrium banum copper oxide superconductcr BASE PRESSURE Mechamsms of flow contro( with the unsteady bleed in near-zero grsvfly A review and development of correlations fo( base technique p 525 Ng4-34987 [BTN-94-EIX9431 t332378] p 550 A94-60951 pressure and base heating in su_mm_c flow Concepts and application of dynamic separation for APPROACH CONTROL |SAND93-0280] p 526 N94-35360 agility and super-maneuverability of aircraft: An Final-Approach Spacing Aids (FASA) evaluation for BELL AIRCRAFT assessment p 535 N94-34988 terr_nsl-eree, time-based air Uaffic control Evaluation of the dynamics and handling quality Effect of initial accelerabon on the development of the I NASA-TP-3399 ] p 529 N94.36048 characteristics of the Bell 412 HP he_icopta¢ flow field of an airfoil pitching at constant rate p 526 N94-34989 APPROPRIATIONS [BTN-94-EIX94331337502] p 530 A94-60337 BENDING FATIGUE BOUNDARY LAYER STABILITY Budget estimates, fiscal year 1995. VokJme 1: A9ermy Transition correlebons in three-dimensional bounden/ summary, human space flight, and science, seror_autics Low-nolss, high-strength, spiral-bevel gears fcr layers and technology helicopter transmissions [BTN.94-EIX94301315968] p 547 A94-60004 {NASA.TM.t09791| p 560 N94-35899 [BTN-94-EIX94321333312] p 548 A94-60044 BLAIDE mJl_ NOffiE BOUNDARY LAYER TRAN_q'ION ARC JET ENGINES Computation of helicoptar rotor acoustics in fonNard Transition correlations in three-dimens_:¢0st boundsry AFOSR Contractors Propulsion Meeting flight layers I AD-A279028 ] p 539 N94-35746 (NASA-CR.196132J p 560 N94-36031 [BTN-94.EIX94301315968] p 547 A94.60004 ASIA BLADE TIPS Will the real dynamic instability mechanism please be JPRS report: Science and technology Central Eurasia Experimental investigation of counter-rotating prppfan recognized! p 552 N94-34976 [JPRS-UST-94-O05] p 553 N94-35342 flutter at cnese conditions BOUNDARY LAYERS JPRS report: Science and technology. Central Eurasia ISTN-94-EIX94321333310] p 516 A94-60042 Surface interference in Rayletgh scattering IJPRS-UST-94-0101 p 553 Ng4-35385 An exan_nation of the aerodynam_ moment on rotor measurements near foretxxEes JPRS report: Science and technology Central Eura=a blade bps using flight test data and anely"s [STN-94.EIX94301315999] p 516 A94..60035 IJPRS-UST-94-012] p 553 N94-35387 INASA-TM-104006] p 523 N94.34948 In-flight velocity measurements us_g laser Doppler ATMOSPHERIC BOUNDARY LAYER BLOCK DIAGRAMS anemomatry Numerical modeling studms of wake vortex transport X-31A control taw design p 540 N94.34616 [ BTN-94-EIX94311329139] p549 A94-60161 and w,'olution within the planetary boundery layer BLOWING Boundary-layer influences on the subsonic near-wake [NASA-CR-t_6078] p 529 N94-35522 Yaw control by tangential torabody bio_ng of bluff bodies ATMOSPHERIC TURBULENCE p 539 N94-34615 [BTN-94-EIX943113291381 p 517 A94-60162 Numerical rnodeling studies of wake vortex transport Wind tunnel measurements on a tuft-scale F/A-18 with Prediction of ice shapes and their effect on lurloil drag and evolution within the planetary boundary layer a tangentially blowing slot -- conducted in the Ames 80 [BTN-94-EIX94311329115J p 519 A94-60185 lNASA-CR-1960781 p 529 N94o35522 by 120 fOOt wind tunnel p 527 N94-35965 Computed unsteady fk:m_ of airfoils at high incidence ATTACK AIRCRAFT FIA-18 iorebody vortex control. V04uma 1: Stabc tests p 525 N94-34975 [NASA-CR-45821 p 528 N94-35991 Operational agility assessment with the AM.X aircraft Departure solutions of the unsteady thin-layer and full BLUFF BODIES p 534 N94-34626 Newer-Stokes equations solved u=angstreamline curvstme Boundary.layer influences on the subsonic near-wake AI"rrruDE (INCUNATION) based iteration tachn_ues p 552 N94-34980 ot bluff podlas Study f_dings on the influence Of maneuverability and A supersonic tunnel for laser and ftow-seedmg [ BTN-94-EIX94311329138 ] p517 A94-60162 technmuas agility on helicopter handling q_tiities BOATTAILS p 533 N94-34624 [NASA.TM-106588] p 556 N94-35945 Drag reduction for turbulent flow over a protectile, part BUBBLES ATnTUDE CONTROL 2 Dynarmc testa to demonstrate lateral control using Injection of bubbling liquid jets hem multiple injectors [BTN-94-EIX94311322900] p 520 A94-60196 to¢ebody suction on large scale models in the DRA 24 into a IM_erson_ _l'olm Drag reduction of turbulent flow over I _, part foot wind tunnel p 539 N94.34613 1 [BTN-94-EIX9432t333316] p 520 A94-60267 Piluted sm_dation study of two tilt-wing control [BTN-94-EIX943113226991 p 557 A94-60197 BUCKMNG concepts p 541 N94.35962 BODY-WING CONFIGURATIONS Sheer buckling response of tailored composite plates AUTOMATIC CONTROL Effects of the roll angle on cruciform wing-body [BTN-94-EIX94301316000] p 549 A94-60256 BUFFETING An oven_ew ot recent advances in system coctfig_ahona at high incidences [lentifiuabon p 546 N94.35880 [BTN-94-EIX94311322903| p 520 A94-60193 Buffet-induced sVu,ctural/flight-control system AUTOMATIC PILOTS BOOSTER ROCKET ENGINES interaction of the X-29A aircraft Six-degree-of-freedom guidance and control-entry Control strategies for space boosters using air collection IBTN-94-EIX94311329137] p 517 A94-60163 analyeJs ol the HL-20 systems A oornbined approach to buffet response analyses and I BTN-94-EIX943511370561 p 544 A94-EO396 [ BTN-94-EIX943113306851 p543 A94-60106 fatigue lile predict=on p 551 N94.34587 A-4 SUBJECT INDEX COMPUTERS Damage tolerance management of the X-29 vertical Combustion performance of dump combustor in ramjet Numerical method for simulating fluid-dynamic and tail p 531 N94-34595 engine using liquid hydrogen fuel heat-transfer changes in jet-eogioe iniector feed-arm due BURNERS I BTN-94-EIX94351144992 J p538 A94-60454 to fouhng Hot Corrosion Tesl Facility at the NASA Lewis Special COMBUSTION CHAMBERS [ BTN.94-EIX94351142133 J p537 A94-60426 Projects Laboratory Preliminary investigations on improwng air-augmented Computation of noneduilibrium hypersonic flowfields INASA-CR-1953231 p 543 N94-35267 rocket performance around hemisphere cylinders BTN-94-EIX943213333231 p 544 A94-60274 IBTN-94-EIX94351142135J p 521 A94-60428 C Turbulent combustion regimes for hypersonic propuis,on High incidence flow enalys=s OVer the Rafale A empldymg hydrogen-air diffusion flames p 522 N94-34612 [ BTN-94-EIX94321333324 J p546 A94-60275 Analysis of wavelet technology for NASA applications C-141 AIRCRAFT Raman measurements at the exit of a combustor JNASA-CR-195929 ] p 522 N94-34704 Risk analysis of the C-141 WS405 inner-to-outer wing sector Combined LAURA-UPS sofubon procedure for toint p 531 N94-34592 I BTN-94-EIX94341338356J p 546 A94-60348 chemically-reacting flows CAMBERED WINGS Expenmentel investcJation on supersonK: COmbustion [NASA-TM-107964] p 551 N94-34721 Control of leading-edge separation on a cambered delta (2) wing p 539 N94-34616 [ BTN-94-ElXg4351144985 ] p 537 A94-60447 Physics of Forced Unsteady Separatm.n CANARD CONFIGURATIONS Combustion performance of dump combustor in ramjet INASA-CP-3144] p 552 N94-34966 Pressure measurements on a forward-swept engine using liquid hydrogen fuel Computational methods foe HSCT-inlet controls/CFD w,ng-canard conf_juration I BTN-94-EIX94351144992 J p538 A94-60454 interdis_plinary research fBTN-94-ElXg43113291491 p 516 A94-60151 Compo.s_te matrix expenmentel combustor lNASA-TM-106618J p 539 N94-35352 Vortex.wing interaction ot a close-coupled canard JNASA-CR-194446J p 538 N94.34679 A three dimensional multigrid Reynolds-averaged configuration COMBUSTION EFFICIENCY Nawer-Slokes sofver for unstructured meshes IBTN-94-EIX94311329121] p 519 A94-60179 Combusbon performance of dump combustor in ramjet JNASA.CR-lg4908] p 526 Ng4-35994 Aerodynamic design of super maneuverable aircraft engine using liouid hy0rogen Iuel COMPUTATIONAL GRIDS p 533 N94-34617 IBTN-94-EIX94351144992] p 538 Ag4Jo0454 New multignd approach for three-dimens_onal Direct reducod order mixed H2/H infinity control for the COMBUSTION PRODUCTS unstructured, ad&otive grids Short Take.Oft and Landing/Maneuver Technology Raman measurements at the exit of a combustor [BTN-94-EIX94301315973] p 559 A94-60009 Demonstrator (STOL/MTD) secto¢ Charactenzation of dynamic stall phenomenon using lAD-A278675) p 540 N94-35796 [BTN-g4-EIX94341338356] P 546 A94-E0348 two-dimensional unsteady Nawer-Stokes equations CASCADE FLOW COMFORT p 524 N94-34974 TIlree-dimensional closure of the passage.averaged Control o1 meglev vehicles with aerodynamic and ComputalK)n of unsteady flows over airfoils vorbcity-potentiel formulation guideway disturbances p 554 N94-35842 p 525 N94-34977 COMMUNICATING I BTN-94-EIX94301315991 J p 547 A94-60027 A three dimensional muffigrid Reynolds-averaged CAVITIES Effects of checklist interface on non-verbal crew Navier-Stokes solver for unstructured meet'ms Natural convecbon in a cavity wtth tins attached to both communications [NASA-CR-194908] p 528 N94-35994 vertical wails INASA-CR.177639J p 528 N94-34915 COMPUTER AIDED DESIGN [BTN-94-EIX94351142119) p 550 A94-60412 COMMUNICATION NETWORKS Inverse design of super-elliptic cooliog passages in CEILINGS (METEOROLOGY) ATM and FIS data link Sef_nces coated turbine blade airfoils Data requirements fo¢ ceiling and wsd0ildy products ( BTN-94-EIX943313355331 p53 A94-60214 [BTN-94-EIX94311330654| p 548 A94-60137 develdpmant COMPENSATORS COMPUTER ANIMATION lAD-A278959] p 556 N94-35720 Third order LPF type compensator for flexible rotor Aircraff accident fkght path simulation and animation CENTRIFUGAL COMPRESSORS suspens_n p 554 N94-35863 I BTN-94-EIX94311329129 ] p518 A94-60171 Comparison of Optical measurement techniques for COMPLEX SYSTEMS COMPUTER GRAPHICS turbomachinefy flow'fields Application of current departure rselstance criteria to Synthetic vision for enhancing poor visibility flight [BTN-94.EIX94341338357] p 559 A94.60349 the post-stall manoeuvenng envelope operations CERAMIC MATRIX COMPOSITES p 533 N94-34622 [BTN-94-EIX94331335531] p 557 A94-60212 Composite matrix experimental combustor COMPONENT REUABIUTY The influence of data link-prOVided graphical weather NASA-CR-1944461 p 538 N94-34679 Artificial neural networks for predicting nonlinear on pdot decismn-making CERAMICS dyflar_c helico_er kinds lAD-A278871 ] p 556 N94-35596 Hot Corrosion Test Facility at the NASA Lewls Specie| I BTN-94-EIX94301315989 ] p 515 A94-60025 COMPUTER NETWONKS Projects Laboratory An analysis of operational suitability for test and Engineering large-scale agent-based systems with [NASA-CR-195323 ] p 543 N94-35267 evaluation of highly reliable systems consensus p 558 N94-35071 CHEMICAL ENGINEERING lAD-A278573 ] p 530 N94-36184 COMPUTER PROGRAMS JPRS report: Scmnce and technology. Central Eurasia COMPOSITE MATERIALS Techniques for aerodynemic characterization and IJPRS-UST-94.010] p 553 N94-35385 JPRS report: Scmnce and technology. Central Eurasia performance evaluation al high angle of attack JPRS report: Science and technology. Central Eurasia IJPRS-UST-94-012] p 553 N94-35387 p 533 N94-34614 IJPRS-UST-94-012] p 553 N94-35387 COMPO_TE STRUCTURES Design oriented structural anatyms CHROMATOGRAPHY Thcee-dimans_0nal thermal analysis for ieser-structural INASA-TM-109124] p 551 N94-34722 interactions Measurement of diffusion in fluid systems: Applications Runtime supcx_rt for data parallel tasks to the supercntioal fluid regmn [BTN-94-EIX94351142117} p 560 A94-60410 INASA-CR-1949041 p 558 N94-35240 IBTN-94-EIXg4311330660] p .548 A94-60131 Field deployable nondestructive impact damage Development and appi_ation of computational CIRCULAR CONES assessment motnddology for composite structures aero_namics f_d computer codes Symmetry breaking in vortmal flows OVer cones: Theory |BTN-94-EIX94301321378| p 546 A94-60892 INASA-CR-196136_ p 526 N94-35.498 and numerical expenmenta COMPRESSIBLE BOUNDARY LAYER COMPUTER SYSTEMS DESIGN {BTN.94-EIX94301315981 ] p 547 A94.60017 Computation of unsteady flows over ak'foils National facilities study Volume 1: Facilitms inventory CIRCULAR CYLINDERS p 525 N94-34977 |NASA-TM-109854| p 541 N94-34632 Some aspects of unsteady separabon Expansion effects on supersonic turbulent boundary Engineering large-scats agent.based systems with p 525 N94.34979 layers consensus p 558 N94-35071 CIVIL AVIATION lAD-A278989| p 527 N94-35950 COMPUTER VISION COMPRESSIBLE FLOW Annual review of aircrah accident data: US general Synthetic vision for enhancing poor visibility flight avmtien calendar year 1991 Unsteady lift of a fl_ e_oil by indic_l concepts operations [PB94-127982] p 528 N94-34991 [BTN-94-EIX94311329118] p 51g A94-60182 IBTN-9,I-EIX94331335531 ] p 557 A94-60212 CLEAN ROOMS COMPRESSORS COMPUTERIZED SIMULATION Magnatcally suspended stepl_ng motors for clean room Rotor dynamic behewour of a high-speed oil-free motor Cornt)ustion shock tunnel and interface compress=on to and vacuum environments p 555 N94-35915 comp¢sesor with a ng_d cor_ling supported on four radial increase rese_o_ pressure and enthalpy CLIMATOLOGY magnetic beanngs p 555 N94-35911 [BTN-94-EIX94311330650] p 516 A94-60141 JPRS report: Science and technology Central Eurasia COMPUTATIONAL FLUID DYNAMICS Joioed-wmg model v_brations using PC-based modal [JPRS-UST-94-006J p 553 N94-35226 New muttigrid apprnach for three-dmlensJ_onal testing and finite element analysis COATINGS unstructured, adaWn_e grids BTN.94-EIX94311329141 | p 517 A94-60159 [BTN-94-EIX94301315973] p 559 A94-60009 Flight testing of a luminescent surface pressure Investigation of Monte C_do simulation in FAA program sensor Structure of ldcat pressure-dnven three-dimensional KRASH [NASA-TM-103970] p 522 N94-35394 transient boundary-layer Separation BTN-94-EIX94311329128] p 536 A94-60172 COCKPITS [BTN-94-EIX94301315979] p 515 A94-60015 A review of ¢ompuler evacuation rnoOels and their data Tactical cOCkl_ta: The coming revolubon Symmetry breaking m vortical flows over cones: Theory needs [BTN-94-EIX94331335530 J p 530 A94-60211 end numerical exT)ecmlents DOT/FAA/AM-94/11] p 528 N94-35236 Effects of checklist interface on non-verbal crew IBTN-94.EIX94301315981] p 547 A94-60017 _b_al methods for HSCT-inlet contro_s/CFD Vane-blade _ntoractldn in a transOmC tud0ina. Pml I: commonicabons interdiecipiimuy research INASA-CR-177639] p 528 N94-34915 Aerodynamics NASA-TM-106618] p 539 N94-35352 COLD FLOW TESTS [BTN-94-EIX94321333305] p 516 A94-60037 Deve_ and application of computational Approximate sirmlanty pnnciple for a full-scale STOVL Applications of computatk0nal fluid dynamics to the eerothe_nam_cs fldwfield computer codes elector eemdynemx:s of Army projectiles NASA-CR-196136] p 526 N94-35498 IBTN-94-EIX94341338360J p 550 A94-60352 [BTN.94.EIX94311330678] p 816 A94-60113 COMPUTERS COMBUSTION Computational analysis of off-Oe_gn waven¢lers JPRS report: Science and technology Central Euras=a Combustion shock tunnel and interface compression to IBTN-94-EIX94311329125] p 549 A94-60175 JPRS-UST-94-0101 p 553 N94-35385 increase reseP_o_r pressure and enthalpy HL-20 cort'_outatldnel fluid dynamics analysis JPRS report: Science and technology Central Eurasm I BTN-94-EIX94311330650 J p516 A94-60141 [BTN-94-EIX943511370591 p 545 A94-60399 IJPRS-UST-94-0121 p 553 N94-35387 A-5 CONDUCTIVE HEAT TRANSFER SUBJECT INDEX CONDUCTIVE HEAT TRANSFER Integration of magnetic bearings in the design of CRASHWORTHINESS COnlugate conduction-convection heat transfer with a advanced gas turbine engines p 554 N94-35903 investigation of Monte Cado slmulation in FAA program high-speed boundary layer Rotor dynamic behaviour of a h*gh*speed oil-tree motor KRASH I BTN-94.EIX94311330652 ] p549 A94-60139 compressor with a ngid coupling supported on four radial [ BTN-94-EIX94311329128 ] p536 A94-60172 CONFERENCES magnetic bearings p 555 N94.359t 1 CRITICAL VELOCITY Technologies for Highly Manoeuwabie Aircraft CONVECTIVE FLOW Dee=gn, construction, end testing of a five active axes IAGARD-CP-548 ] p 532 N94.34605 magnetic beanng system p 554 N94-35846 Natural conveclion in • cavity with fins attached to both Physics of Forced Unsteady Separat,on vertical walls CROSS FLOW [NASA-CP.3144J p 552 N94-34966 [BTN.94-EIX94351142119] p 550 A94-60412 Crossflow topology of vortical flows Flight Mechanics/Esbmabon Theo_ Symposium, 1994 CONVECTIVE HEAT TRANSFER [BTN.94.EIX94301315993] p 515 A94-60029 INASA-CP-32651 p 545 N94.35605 CRUCIFORM WINGS Conjugate conduction-convecl=on heat transfer with a AFOSR Contractors Propulsion Meeting Effects of the roll angle on crucdorm wing-body high.speed boundary layer {AD.A279028 ] p 539 N94-35746 configuratPons at high incidences [STN-94-EIX94311330652 ] p549 A94-60139 Second International Symposium on Magnetic [BTN-94-ElX94311322903J p 520 A94.60193 The aerodynamic and heat transfer effects of an endwetl Suspens*on Technology. part 2 CRUISING FLIGHT boundary layer fence in a 90 degree turning square duct INASA-CP-3247-PT-2} p 546 N94-35902 Systemat¢ computation schema of PAR-WIG crursing IAD-A278903 J p 553 N94.35803 CONICAL BODIES per/offnance COOLANTS Symmetry breaking in vorbcal flows over cones: Theory {BTN.94-EIXg43611354271 p 521 A94.60624 and numerical expenments Conjugate conduction-convect*on heat transfer with a CUMULATIVE DAMAGE IBTN-94.EIX943013159811 p 547 A94.60017 high-speed bogndery layer Reduction of fatigue load experience as part of the Techniques for aerodynamic characterizabon and [ BTN-94.EIX94311330652 p549 A94.60139 fatigue management program for F-16 aircraft of the performance evaluabo_ at high angle of attack COOLING RNLAF p 532 N94.34598 p 533 N94-34614 Measurement and predicbon of dynamic temperatures CURRENT DENSITY CONICAL NOZZLES in unaymmetrically cooled [ass windows Procee_og yttrium bandm copper oxide sup_conductor Preliminary investigetmns on .'rip,roving air-augmented I BTN-94-EIX94351142128 p550 A94-60421 in near-zero gravity rocket per/ormance COOUNG SYSTEMS [ BTN-94-EIX94311332378 | p 550 A94-60951 IBTN-94-EIX94321333323] p 544 A94-60274 Inverse design of super-elliptic cooling passages in CYUNDRICAL BODIES CONSTRUCTION coated turbine blade air/oils Numerical investigation of cylinder wake flow with a rear Design, consUuction, and testing of • five sctNa axes [ BTN-94-EIX94311330654 p548 A94-60137 stagnation jet magnetic bearing system p 554 N94-35846 COPPER ALLOYS [ BTN-94-EIX94301315998 ] p 547 A94.60034 CONTROL EQUIPMENT Effect of coarse second phase particles on fatigue crack Mechar.sms of flow control with the unsteady bleed Design. construction, end testing of a five active axes propagation of an AI-Zn-M I-Cu alloy technique p 525 N94-34987 magnetic beanng system p 554 N94-35846 [BTN-94-EIX94301320144 p 546 A94-60853 CONTROL SIMULATION Retained mecheok?JiI properlies ol a new AI-Li-Cu-Mg-Ag D In-flKJht simulation studies el the NASA Dryden Flight alloy Is • function of thermal exposure time and Research Facility p 536 N94.35969 temperature CONTROL STABILITY DAMAGE [ BTN.94.EIX94301320164 p546 A94-60873 Vortex.wing interaction of a close.coupled canard Assessment of in-sennce aircraft fatigue monitoring COPPER OXIDES conf_bon process p 531 N94-34593 Proceesmg yttrium barium copper oxide superconductor [BTN-94-EIX94311329121] p 519 A94.60179 Damage tolorence management of the X-29 vertical CONTROL SURFACES in rmar-zero gravity tail p 531 N94.34595 [ BTN-94.EIX94311332378 p550 A94.60951 Buffet-induced structurst / flight .controt system DAMAGE ASSESSMENT interaction of the X-29A airorsft CORROSION TESTS Fiekl dep4oyablo nondestructive impact damage IBTN-94-EIX94311329137] p 517 A94.60163 Hot Corros_n Test Fecilay st the NASA Lena Special assessment methodology for compes_te structures Projects Laboratory Experimental studies of vortex flaps end vortex plates | BTN-94-EIX94301321378 | p 546 A94-60892 [NASA-CR-195323] p 543 N94.35267 [BTN-94-EIX94311329122J p 518 A94.60178 An Assessment o! Fatigue Damage end Crack Growth C06T ANALYSIS Vortex-wing interaction of • close-coupled canard Predictmn Techniques configuration Nebonst facilities study. Volume 2A: Facility Study Office [AGARD-R-797] p 550 N94-34581 [ BTN-94-EIX94311329121 ] p519 A94-60179 on the National Wind Tunnel Compk_ A combined approach to buffet response analyses and Damage tolerance management of the X-29 vertical [NASA-TM-109856] p 542 N94-34634 fatigue life prediction p 551 N94-34587 tail p 531 N94-34595 COST ESTIMATES DAMPING High incidence flow analysis over the Refale A Co_ and schedu_ estimation study report Third order LPF type compensator for flexible rotor p 522 N94.34612 [NASA-CR-189344] p 558 N94-35256 suspenemn p 554 N94-35863 DATA ACQUiSITiON Control of maglev vehicles with eerodymim=c and Budget estimates, fiscal yler 1995. Volume 1: Agency guidewsy disturbances p 554 N94-35842 summery, human Ikoace flight, and _nce, eeroNwtics Mission Evaluation Room Intelligent Dmgnoetic and CONTROL SYSTEMS DESIGN end tachnolow Analysis System (MIDAS) p 558 N94.35064 F-16 uncommanded pitch osoHation [NASA.TM-1097g1 ] p 560 N94-35899 Langley 14. by 22-foot subsonic tunnel test engineer's data ecquisition and reduction manual [ BTN-94-EIX94331337501 ] p530 A94-60336 COST REDUCTION [NASA-TM-4563J p 526 N94.35246 Deign of integrated flight and powerpfant control Future unra-apeed tube-fl*ght p 555 N94-35918 Data requirements for catting end visibility products systems p 532 1'494-34609 COUNTER ROTATION development Results from the STOL end Maneuver Technology Expqmmentai invesbgatk_n of counter-rotstieg propfan (AD-A278959] p 556 N94-35720 Demonstration program p 532 N94-34611 flutter st crume co_lltlohe DATA BASES X-3tA control law design p 540 N94-34618 [BTN.94.EIX94321333310] p 516 A94-60042 Robust control deslgn techniques for active flutter National facilities study. Volume 1 : Facilitlae inventory COUPLING suppresl.o_ p 541 N94-35875 [NASA-TM-109854] p 541 N94-34632 Direct simulation with vibration-diesocfation coul_ing CONTROL THEORY DATA COMPRESSION [BTN-94-EIX94351142138] p 521 A94-60429 X-31A control law design p 540 N94-34618 CRACK PROPAGATION Analyws of wavelet technology for NASA applications Dk'ect reduced order mixed H21H infinity cordrol for the [NASA-CR-195929] p 522 N94-34704 Effect Of coanm saco_l pillsa perticfas on fal_ue oreck Short Take-Oft end Landing/Maneuver Technology DATA LINKS propagation of an AkZn-Mg-Cu alloy Demonstrator (STOL/MTD) ATM and FIS data link ImP,_ces [BTN.94-EIX94301320144} p 546 A94-60853 lAD-A278675| p 540 N94-35796 [BTN-94-EIX94331335533] p 530 A94.60214 Flutter suppr_ digital control law design Mid testing An Assessment of Fatigue Damage and Cnlck G_wth l:h'ediotion Techmques The influence of data link-provided graphical weather for the AFW wind tunnel model p 540 N94-35873 on pilot deci=aon-meking CONTROLLABILITY [AGARD-R-797] p 550 N94.34581 [AD-A278871 | p 556 N94.35596 An assessment of fatigue crack growth pmd_ion Evaluation of the dynamics and hendting quality DATA PROC_NG characteristics Of the Bell 4t2 HP helicopter models for aernepeca structures p 551 N94-34586 Mission Evaluation Room intolltgent Diagnostic end [BTN-94.EIX94331337502] p 530 A94.60337 Fatigue manl_ and vedfloalKm of airframes Analysis System (MIDAS) p 558 N94.35064 Effect of lift-to-drag ratio in pilot rating of Ihe HL.20 p 531 N94-34591 DATA REDUCTION landing task Dernege tolerance management of the X.29 vertical Data rebuction procedures for laser veloclmeter [ BTN-94-EIX94351137057 ] p544 A94-60397 tail p 531 N94.34595 mea.._ements in turbomachine_/rotors X-31A system identifP._ltion applied to post-ststl flight: CRACKS [NASA-CR-195343] p 552 N94-35224 Aerodynamcs and thrust vectoring p 540 N94.34619 Risk analy_s of the C-141 WS405 inner-to-outer wing Study fk'x_ngs on the influence of maneuverability and ioinl p 531 N94-34592 Langdey 14- by 22-toot subsonic tunnel test ongmeer's data acquisition and reduction manual agility on helicopter handling qualities Frequency domain analysis of the random loading of [NASA.TM4563J p 526 N94.35246 p 533 N94-34624 cracked panels The iofkJenceof flyingqu_itieson operal_ agility [NASA-CR-19e021] p 556 N94-35g74 Dets reduction, analysis and results of LACV.30-07 p 534 N94-34628 CRASH INJURIES vehicle fasts, Fort Story, VA, August. Septemb_ Direct reduced order mixed H2/H infinity control for the Annual review of akcraft eccidenl dats: US general 1993 Short Take-Off end Landing/Maneuver Technology arraign calendar year 1991 [AD-A27885g] p 527 N94.35_26 Demonstrator (STOL/MTD) |PB94-127982] p 528 N94.34991 DATA STRUCTURES |AD-A278675] p 540 N94.35796 CRASHES Runfime support for data parallel tasks CONTROLLERS Aircraft accident report: Uncontrolled collision with {NASA-CR.194904] p 558 N94-35240 Direct reduced order mixed H21H infinity control for Ihe terrain, Amencan International Airways Flight 808, Douglas DECAY RATES Short Take-Off and Landing/Maneuver Technology DC-8-61, N814CK, US Naval Air Station, Guantanemo Bay, Numerical modeling studies of wake vortex transport Demonstrator (STOL/MTD) Cuba, 18 August 1993 and evolution w_'_n the planetary boundary layer lAD-A278675| p 540 N94-35796 [PB94-910406} p 529 N94-35521 [NASA-CR-t960781 p 529 N94-35522 A-6 SUBJECT INDEX EVACUATING _RANSPORTATION) DECISION MAKING DRAG REDUCTION ELECTRONIC EQUIPMENT TESTS FINDER, A system providing complex decision supporf Drag reduction of airplane fuselages through shaping Minimum performance standards: Airborne low-range for commercial transport replannlng operations by the inverse method radar allimetars I BTN-94*EIX94331335529 J p 549 A94-60210 [BTN-94-EIX94311329tt7) p 536 A94-60183 RTCA-DO-155 J p 537 N94-35344 Vista goes online: Decision.analytic systems for real.time Drag reduction for turbulent flow over a proiestiio, part ELECTROPHYSICS decis=on-making in m*ss_on control p 558 N94-35063 2 JPRS report: Scmnce and techr_ology Central Eurasia Mission Eveluabon Room Intelkgent Diagnostic and 18TN-94-EIX94311322900] p 520 A94-60196 JJPRS-UST-94-006 J p 553 N94-35226 Analysis System |MIDAS) p 558 N94-35064 Drag reduction of turbulent flow over a protjecble, part ELECTROPLATING 1 The influence of data link-provided grsphmal weather Planar rotational magnetic micromotors wrth integrated on pilot decision.making I BTN-94-EIX94311322899 ] p557 A94.60197 shaft encoder and magnetic rotor levitation DRDIP' SIZE lAD-A2788711 p 556 N94.35596 p 555 N94-35907 DECISION THEORY PredK:bon of ice shapes and their effect on airfoil drag EMERGENCIES IBTN-94-EIX94311329115J p 519 A94-60185 Vista goes online: Decmon-analybc systems for real-time Flight testing a propels_on-cOntrolied aircrafl emergency DUCTED FLOW deciszon-making in rmssion control p 558 N94-35063 flight control system on an F-15 a*rl_ane The serodynamic and heat transfer effects of an endwall DELTA WINGS INASA-TM-4590J p 540 N94-35258 boundary layer fence in a 90 degree turning sduare duct Crossflow topology of vortical flows ENERGY CONSERVATION [ AD-A2789031 p 553 N94-35803 (STN-94-EIX943013159931 p 515 A94-60029 DUCTS On the VerK)us forms of the energy equation for a dilute, rnonatom_c mixture of oonreacting gases Expenmental studies of vortex flaps and vortex plates The aerodynamic and heat transfer effects of sn endwall [NASA-CR-4612J p 527 N94-35864 lBTN-94-EIX94311329122] p 518 A94-60178 boundary layer fence in a 90 degree turning square duct ENERGY TRANSFER Forebody vortex control for wing rock suppresszon IAD_A278903 ] p 553 N94-35803 (BTN-94-EIX94311329119] p 530 A94-60181 DUMP COMBUSTORS Measurement and predictzon of dynamic temperatures Control of leading-edge separation on a cambererl delta Combustion performance of dump combustor in ramjet in unsymmetrcally coolad glass windows wing p 539 N94-34616 engine _ liquid hydrogen fuel [BTN.94-EIX94351142128} p 550 A94-60421 Control of leading-edge vortices on a delta wing |BTN-94-EIX94351144992 t p538 A94-60454 ENGINE CONTROL p 524 N94.34971 DYNAMIC CHARACTERISTICS Control stratagms for space boosters using sir co_lechon Localizabon of seroelasbc modes in mistunod systems Unsteady structure of leading-edge vortices On a delta wing high-energy turbines [BTN-94-EIX943113306851 p 543 A94-60t06 ENGINE DESIGN lAD-A278988) p 526 N94-35529 [ BTN-94.EIX94321333307 ] p 547 A94-60039 DESIGN ANALYSIS Rotor dynamic behaviour of s high-speed oil.free motor Progress and purpose of IHPTET program compressor with s ngid coupling supported on four radial p 538 N94.34607 Effects of model scale on flight characteristics and design parameters magnetic bearings p 555 N94-35911 Engine charactarlatics for agile aircraft DYNAMIC CONTROL [BTN-94-EIX94311329143] p 517 A94-60157 p 538 N94.34608 An overview of recent advances in system Technologies for Highly Manoeuvrable Aircraft Influence of backup beanngs snd support structure identifk:stio_ p 546 N94-35880 [AGARD-CP-548) p 532 N94-34605 dynermcs on the behavior of rotors wrth active suppocts DYNAMIC PRESSURE [NASA-CR-196t19] p 553 N94-35500 Developing and flight tesbng the HL-10 lifting body: A Computation and dlscusston of a nearly constant degree Integration of msgnetic bearings in the design of precursor to the Space Shuttle of reacti_l turbms stsga advanced gas tur_ne engines p 554 N94-35903 [NASA-RP-1332) p 535 N94-34703 [BTN-94-EIX94351144987 ] p537 A94-6044g ENGINE FAILURE Design oriented structural analysis DYNAMIC RESPONSE Structural integrity and containment aspects of small |NASA-TM-109124| p 551 N94-34722 Study findings on the influence of maneuverability and gas turbtne engines DESTRUCTIVE TESTS agility Do hekcopter handling quelib_s IBTN.94.EIX94331337500] p 550 A94-60335 Field deployable nondestructive impact damage p 533 N94-34624 ENGINE NOISE assessment methodology for composite structures Evaluating the dynamic response Of in-flight thrust Eog_ne exhaust charectenatcs evaluation in support of [BTN-94-EIX94301321378] p 546 A94-60892 calculation techns_ues during throttle transgress aircraft acoustic testing p 560 N94-35963 DIFFUSION |NASA-TM-4591] p 535 N94.35241 ENGINE TESTS Measurement of diffusion in fluid systems." Applications DYNAMIC STRUCTURAL ANALYSIS National facilities study. Volume 2: Task group on to the supercritical fluid regK)n Frequency domain analysis of the random loading of aeronautical research and development tacilitms report lBTN-94-EIX94311330660] p 548 A94-60131 cracked panels |NASA-TM-109855J p 542 N94-34633 DIFFUSION COEFFICIENT |NASA-CR-196021] p 556 N94-35974 Evaluating the dynamic response of in-flight thrust DYNAMIC TESTS Measurement of d_umon in fluid systems: Al_cabons calculation technKlues dunng throttle transmnts to the superchtmal fluid region Dynam¢ tests to demonstrate lateral control using [NASA-TM-4591] p 535 N94-35241 [ BTN-94-EIX94311330660 ] p548 A94-60131 forebody _ on large scale models in the DRA 24 HOt CorrosaDn Test Facildy st the NASA Lamas Spec_l DIFFUSION FLAMES foot wind tunnel p 539 N94-34613 ProlectsLabucatory Turbulent combustion regimes for hyperso_c prOl_Jl_ [NASA-CR-195323] p 543 N94-35267 employmg hydrogen-ak diffusion flames E ENGINEERS [ BTN-94-EIX94321333324 ) p 546 A94-60275 NASA/DOD Aerospace Knowledge Diffusion Research DIGITAL SYSTEMS Prolecl Paper 42: An anelysm of the transfer of Soentihc EARTH SCIENCES Dynamic tests to demonstrate lateral control using and Technical Information (STI) in the US aerospace JPRS report: Science and technology. Central Eurasm forebody suction on large scale models in tlm DRA 24 industry [JPRS-UST-94-006] p 553 N94-35226 foot wind tunnel p 539 N94-34613 [NASA-TM-109863] p 560 N94-34730 JPRS report: Scmnoa and teehootoW. Central Euresm Flutter suppression d0gital control law desdgn and testing Mil_io_ Evaluabon Room Intelligent Diegnostic and [JPRS-UST-94-O05] p 553 N94-35342 for the AF'W wind tunnel model p 540 N94-35873 Analy_s System |MIDAS) p 558 N94-35064 DILUTION JPRS report: Science snd technology Central Eureem ENTHALPY [JPRS-UST-94-012] p 553 N94-35387 Measurement of diffusion in fluid systems: Appticabons Combustion srmck tunnel and interface compression to Research and technology, 1 to the supercritical fluid region increase r_r pressure and enthalpy IBTN-94-EIX9431133066OI p 548 A94-60131 |NASA-TM-108816] p 561 N94-36117 EGRE_ [BTN-94-EtX94311330650] p 516 A94-60141 DIRECTIONAL CONTROL ENTRAINMENT YAV-aB reaction control system bleed and control power Human factors evaluation of the HL-20 full-scale rnodet Propulsion-induced aerodynamic effects measured w_th usage m hover and transition a fulktm.Jlle STOVL model [ BTN-94-EIX94351137065 ] p545 A94-60405 [NASA-TM-fO4021 J p 540 N94.34994 [BTN-94-EIX94311329120] p 519 A94-60180 EJECTORS Wind tunnel measurements On s fulkscala F/A-18 with EQUATIONS OF MOTION a tangentially blowing slot -. conducted k_ the Ames 80 Approxn'mZta _ ponciple for a full-scale STOVL eieetor Modal coordinates for aeroelastic snalyszs with large by 120 foot wind tunnel p 527 N94-35965 lOcal structural vanations [BTN-94-ElXgu1341338360] p 550 A94-60352 DIRECTIONAL STABIUTY [BTN-94-EIX9431132913t ] p 518 A94-60169 ELECTRICAL ENGINEERING Dynamic tests to demonstrate lateral co_Vol using ETHYL ALCOHOL forebody suction on large scale models in the DRA 24 JPRS report: Science SOd technology. Central Eurama [JPRS-UST-94-005] p 553 N94-35342 Structure and penetration of s Sup_rcr_..st fluid let in foot wtnd tunnel p 539 N94-34613 w,Jberao_c flow JPRS reporl: Sconce and technology. Central Eurasm DISPLAY DEVICES [BTN-94-EIX94321333317] p 549 A94-60268 [JPRS-UST-94-010] p 553 N94-35385 Tactcal cockl_ts: The coming revolutio_ EULER EQUATIONS OF MOTION JPRS report: Science sod technology. Central Eurasia [ BTN-94-EIX9433 t 335530 ] p530 A94-60211 New mulbgnd approach for three-¢limens_ooal Effects of checklist interface on non-verbal crew [JPRS-UST-94-012] p 553 N94-35387 ELECTROMECHANICS unstructured, adapbve grids commur_',abons (BTN-94-EIX943013tSg73] p 559 A94-60009 Design, construction, and tesbng of s five active axes [NASA-CR-177639] p 528 N94-34915 H_gh Incidence flow analys_s over the Rstsle A DISSOCIATION magnetic bearing system p 554 N94-35846 p 522 N94-34612 Direct simulabon with v_xat_.d_bon coupling Elactromechanical simulation snd test of rotating EURO_PIE systems with magnetic beanng or ptezoelacthc actuator [STN-94-EIX94351142136] p 521 A94.60429 JPRS repert: SOerx:e and technology. Central Eurasia New two-temperature dissociation model for reacting active viprebon control p 555 N94-35905 (JPRS-UST-94-005| p 553 N94-3,5342 flows ELECTRONIC CONTROL JPRS report: Science and technology. Central Eurasia IBTN-94-EIX943511421371 p 560 A94-60430 Hot gas ingestion effects On fuel control wJrge recovery |JPRS-UST.94-010) p 553 N94-35385 DISTRIBUTED PROCESSING and AH-1 rotor dr_e train terbue s,o_kes JPRS report: Soence and technology, Central Eurasia [NASA-CR-191047] p 538 N94-34993 Eng_'H_nng large-scale agent-based systems with [JPRS-UST-94-012| p 553 N94-35387 consensus p 558 N94-35071 ELECTRONIC EQUIPMENT EVACUATING (TRANSPORTATION) DRAG An analysis of operational suitability for test and A rev',ew of computer evscuabon models and their data Control of iesding-edge separation on s cambered delta evaluabon of highly reliable systems needs wing p 539 N94-34616 |AD-A2785731 p 530 N94.36184 [DOT/FAA/AM-94/11 ] p 528 N94-35236 A-7 EXHAUST GASES SUBJECT INDEX EXHAUST GASES An overview of the F-16 service life approach FLAT PLATES Preliminary investigations on improving air-augmented p 532 N94-34599 Analysis of aerodynamics of aidolls moving over a wavy rocket performance FATIGUE TESTS wall I BTN-94-EIX94321333323 J p 544 A94-60274 Harrier 2: A companson of US and UK approaches to [BTN.94-EIX94311329130J p 536 A94-60f70 The s_mulation of a propulsive jet and force fatigue clearance p 531 N94.34596 Some aspects of unsteady separation measurement using a magnetically suspended wind tunnel p 525 N94-34979 Fatigue design, test and in-service experience of the model p 527 N94-35855 BAe Hawk p 531 N94-34597 Expansion effects on supersonic turbulent boundary EXHAUST SYSTEMS layers FEASIBILITY ANALYSIS lAD-A278989] p 527 N94-35950 Engine exhaust charactenstms evsluatmn in support of F easibllity study of a contained pulsed nuclear prppulsion aircraft acoust¢ testing p 560 N94-35963 FLEXIBLE BODIES oogine EXTERNAL STORES An overview of recent advances in system ( BTN-94-EIX94341338369 ] p 559 A94-60361 Reduction of fat_Jue load experience as part of the identification p 546 N94-35880 FEDERAL BUDGETS fatigue management program for F-16 aircraft of the FLIGHT CHARACTERISTICS RNLAF p 532 N94-34598 Budget estimates, fiscal year 1995. Volume 1: Agency Effects at model scale on flight characteristics and summary, human space flight, and science, aeronautzcs design parameters and technology IBTN-94-EIXg4311329143J p 517 A94-60157 F [NASA-TM-t09791 J p 560 N94-35899 Parameter estimates of an aeroslastic aircraft as FEEOGACK affected by model simpliftcabons F-15 AIRCRAFT X-31A control law design p 540 N94-34618 [ BTN.94.EIX94311329142 ] p517 A94-60158 Flight testing a propulsion-controlled aircraft emergency FEEl)BACK CONTROL Suffet-induced structoral/flight-control system flight control system on an F-15 airplane Application of current departure resistance critena to interact=on of the X-29A aircraft [NASA.TM-4590] p 540 N94.35258 the post.stall manoeuvering envelope I BTN-94-EIX94311329137 ] p517 A94-60163 F-18 AIRCRAFT p 533 N94-34622 Aircraft accldanl flight path simulation and animation F-16 uncomman(led pitch oscillation Modelling and control of a rotor supported by magnetic [STN-94-EIX94311329129] p 5f8 A94-60171 [BTN-94-EIX94331337501 ] p 530 A94-60336 bearings p 554 N94-35858 Evaluation of the dynamics and handling quality ReductK)n of fatigue load experience as part of the FEEDFONWARD CONTROL characteristics of the Bell 412 HP helicopter fatigue management wogram for F-t6 aircraft 0t the X-31A control law design p 540 N94-34618 [ BTN-94-EIX94331337502 ] p 530 A94-60337 RNLAF p 532 N94-34598 FENCES (BARRIERS) Systematic computation scheme of PAR-WIG cruising An overview of the F-16 service life approach The aerodynamic and heat transfer effects of an ondwall performance p 532 N94-34599 IBTN'94-EIX943611354271 p 521 A94-60624 F-11 AIRCRAFT boundary layer fence in a 90 degree turning square duct Technologies for Highly Manoeuvreble Aircraft Wind tunnel measurements on a full-scale F/A-18 with lAD-A278903 ] p 553 N94.35803 I AGARD-CP.5481 p 532 N94-34605 FIGHTER AIRCRAFT a tangent=ally blowing slot -- conducted in the Ames 60 Engine characteristics for agile aircraft Forebody vortex control for wing rock suppressmn by 120 foot wind tunnel p 527 N94-35965 p 538 N94-34608 I BTN-94-EIX94311329119 ] p530 A94-60181 F/A. 18 forebody vortex control Volume 1: Static tests Control of leading-edge separation on a cambered delta Effects of propeller on the turning of old fighters [ NASA-CR.45821 p 528 N94-3599t wing p 539 N94.34616 FABRICATION I BTN-g4-EIX94361135426 ] p537 A94-60623 EFA flying qualities specifh3ation and its utilisation Planer rotational magnetic r_crometors with integrated The role of fatigue analysis for design of mihtary p 533 N94-34621 shaft encoder and magnetic rotor levitation mrcraft p 531 N94-34594 Application of current departure resistance crdena to p 555 N94-35907 Techno_ for Highly Manoeuvraole Aircraft the post-stall manoeuvenng envelope FAILURE ANALYSIS IAGARD-CP-5481 p 532 N94-34605 p 533 N94-34622 Structural mtegnty and containment aspects of small USAF/AEDC aerodynamic and propulsion ground test Flying qualifies evaluation maneuvers gas turbine engines and evaluation tachnlquas for highly maneuverable aircraft: p 533 N94-34623 [BTN-94-EIX94331337500] p 550 A94-60335 Capabilities and challenges p 532 N94.34606 The influence of flying quelitms on operabonal agihty An Assessment of Fatigue Damage and Crack Growth Design of integrated flight and powerptant control p 534 N94-34628 Prediction Tech_ques systems p 532 N94-34609 In-flight simulation studies at the NASA Dryden Flight IAGARD'R-797) p 550 N94-34581 High incidence flow analysis over the Rafale A Reseamh Facility p 536 N94-35969 FAR FIELDS p 522 N94-34612 FLIGHT CONDITIONS Charectanzation of dynamic stall phenomenon using EFA flying qualities specification and its u_iselJon Static and dynamic flK:Jht-path stability of airplanes two-dimensional unsteady Navier.Sfokes equations p 533 N94.34621 [BTN-94-EIX94361135428] p 522 A94-60625 p 524 N94-34974 Application of current departure resistance criteria to Flight testing of a luminescent sudace pressure ComputatK)n of helicppter rotor acoustics in forward the post-stall manoeuvenng envelope serlsor fbght p 533 N94-34622 I'NASA-TM-103970] p 522 N94-35394 [NASA-CR-196132} p 560 N94-36031 Operational igility: An ovennew of AGARD Working FUGHT CONTROL FATIGUE (MATERIALS) Group 19 p 534 N94-34625 Aircraft landing gear positioning concerning abnormal Effecl of coarse second phase particles on fatigue crack Concepts and application of dynamic separation for landing cases propagation of an Al-Zn-Mg-Cu alloy agility and super-maneuverability Of aircraft: An [ ETN-94-EIX94311329140 ] p536 A94-60160 [BTN-94-EIX94301320144] p 546 A94-60853 assessment p 535 N94-34988 Buffet-induced structural/flight-control system An Assessment ot Fatigue Damage and Crack Growth FILM COOUNG interaction of the X-29A IirCreh Prediction Techniques Expenmental studies of shock-wave/well-jet interaction [STN-94-EIX94311329137] p 517 A94-60163 IAGARD-R-Tg7J p 550 N94-3458t in hy_ flOW, part A F-16 ur',commended pitch oscillebon An assessment of fatigue crack growth predc'bon INASA-CR-195957] p 523 N94-34964 [STN-94-EIX94331337501 ] p 530 A94-60336 models for aerospace sVLctores p 551 N94-34586 FINANCIAL MANAGEMENT Six-dngree-of-freedorn guidance and control-entry Notch fatigue assessment of aircraft components using Budget estimates, fiscal year 1995. Volume 1: Agency analysis of the HL-20 a fracture mechenics based parameter summery, human space f_ht, and soence, aeronautrs [ BTN-94-EIX9435 t t 37056 | p 544 A94-60396 p 551 N94-34588 and technology Technologies for Highly Manoeuvrable Aircraft Rotorcraft fatigue life-prediction: Past, present, and INASA-TM-1097gf ] p 560 N94-35899 [AGARD-CP.548] p 532 N94-34605 future p 551 N94-34590 FINENESS RATIO Dynamic tests to demonstrate lateral control using Fatigue management and verifcation of airframes Drag reduction of airl_ana tu_dages through shaping tocebody suction on large scale m(xlels in the DRA 24 p 531 N94-34591 by the _werse method toot wind tunnel p 539 N94-34613 Assessment of in-sennce aircraft fatigue monitoring |BTN.94-EIX94311329117] p 5.36 A94-60183 X-31A system identification applied to pest-stall flight: process p 531 N94.34593 FINITE DIFFERENCE THEORY Aerodynamics and thrust vectonng p 540 N94.34619 Hamer 2: A comparison of US and UK approaches to Natural cortvection in a cav_y with tins attached to both X-31 tactical utility: Ir_tiel results p 533 N94-34620 fatigue clearance p 531 N94-34596 ve_Jcal wells ApplP...ation of current departure resistance criteria to FATIGUE LIFE [ BTN-94-EIX94351142119 ] p550 A94-60412 the post-steal menoeuvenng envelope Artificial neural networks for predicting nonlinear FiNiTE ELEMENT METHOD p 533 N94-34622 dynamic helicopter loads Analysis of muttJfestoner composite joints YAV-8B reaction control system bleed and control power I BTN-94-EIX94,301315989 J p516 A94-60025 [BTN.94.EIX94311330690] p 548 A94-60101 usage in hover and transit,on Effect of coarse second phase perticles on fatigue crack Three-dimensional thermal analysis for laser-structural {NASA-TM-104021 ] p 540 N94.34994 interw=tione propagabo_ of an At-Zn-Mg-C,u alloy Vista goes online: Decision-analytic systems for real-time I BTN-94-EtX94301320144 J p546 A94-60853 [STN.94.EIX94351142117] p 560 A94-60410 decision-making in misemn control p 558 N94.35063 A comblnad approach to buffet response analyses and A combined approach to buffet response analyses and Flight testing a propulsaon-controlled aircraft emergency fatigue life prediction p 551 N94-34587 fatigue life prediction p 551 N94-34587 flight control system on an F-f5 a,'ptana Hi_ incidence flow analysis over the Rafale A Notch tatN_ue assessment of aircraft components using [NASA.TM-4590| p 540 N94-35258 p 522 N94-34612 a fracture mecher_cs based p_irameter FINS in-flight mm,,_atmn studies at the NASA Dryden Flight p 551 N94-34588 Hyprmmn_rm eerodynemics Research Facility p 536 N94.35969 Rotorcraft fatigue life-predlction: Pest, present, and [BTN-94-EIX94311330699] p 516 A94-60092 FLIGHT CREWS future p 551 N94-34590 Effects of checklist interface on non-verbal crew Natural convection in a cavity with fins attached to both The role of fatigue analysis for design of military vertical walls commumcations aircraft p 531 N94-34594 [BTN-94.EIX94351142119] p 550 A94-60412 INASA-CR-177639] p 528 N94.34915 Fatigue design, test and in-service experience of the FLAPPtNG Safety study: A rev_w of flighfcrew-involved, maior BAe Hawk p 531 N94-34597 Unsteady llft of a flel_)ed airfoil by indiciel concepts accidents of US air camera, 1978 through 1990 Reduction of fatigue load experience as part of the |BTN-94-EIX943113291t8} p 519 A94-60182 [PB94-917001 I p 529 N94-35482 fatigue management program for F-16 aircraft of the Orndhopler wing design FMGHT ENVELOPES RNLAF p 532 N94-34598 |BTN-94-EIX94331337499] p 521 A94-60334 X-31 tactical utility: Initial results p 533 N94-34620 A-8 SUBJECT INDEX FRACTURE MECHANICS Application of current departure resistance criteria to Evaluating the dynamic response ol in-flight thrust Characterization of dynamic stall phenomenon using the post-stall manoeuvering envelope calculation techniques during throtlle transients two.dimene,onat unsleady Navier-Slokes equations p 524 N94-34974 p 533 N94-34622 I NASA-TM-4591 J p 535 N94-35241 Flying qualities evaluation maneuvers Flight testing a prOpulsmn-controlled aircraft emergency Computed unsteady flows of airfoils al high incidence p 525 N94-34975 p 533 N94-34623 flight control system on an F-15 airplane FLIGHT FATIGUE INASA'TM-4590J p 540 N94-35258 Will the real dynamic instability mecbanism please be Aircraft acc,denl report: Uncontrolled collision with Flight testing ot a luminescent surtace pressure recognized! p 552 N94-34976 sensor terrain, American International Airways Flight 808, Douglas FLOW VELOCITY [NASA-TM-103970] p 522 N94-35394 DC.8-61, N814CK, US Naval Air Station, Guantanamo Bay, Comparison of optical measurement techniques Ior Unleaded AVGAS program Cuba, 18 August 1993 turbomachinery flowhelds J PB94-910406 J p529 N94-35521 IAD-A278650J p 547 N94-35795 lBTN.g4-EIX94341338357J p 559 A94-60349 Engine exhausl characteristics evaluation in supOo¢t of FLIGHT INSTRUMENTS FLOW VISUALIZATION aircraft acoustic testing p 560 N94-35963 Tachcal cockpits: The coming revolution Flow quality studies of the NASA Lewis Research Center In-flight simulebon studies at the NASA Dryden FIKjht J BTN-g4-EIX943313355301 p 530 A94.60211 Icing Research Tunnel Research Facikty p 536 N94-35969 FLIGHT MANAGEMENT SYSTEMS [NASA-TM-106545] p 543 N94-34919 FLIGHT TRAINING FINDER, A System providing complex decision support Co_panson of prtch rate history effects on dynamic Operational agility assessment with the AM-X aircraft stall p 535 N94-34968 for commercial transport reptann_ng operebons p 534 N94.34626 [BTN-94-EIX94331335529J p 549 A94-60210 FLOAT ZONES A supersonic tunnel for laser end flow°seeding techniques Tactical cockpits: The coming revolution Processing yttnum banum copper oxide super_uctor [ NASA-TM-1065881 p 556 N94-35945 I BTN-94-EIX94331335530 J p530 A94-E0211 in near-zero gravity FLIGHT MECHANICS [BTN-g4-ElXg4311332378J p 550 A94-60951 FLUID DYNAMICS Ornithopter wing design FLOQUET THEOREM Will the real dynamic instability mechanism please be lBTN-94-EIX94331337499] p 521 A94-60334 Dynamic aeroelastic stability of vertical.axis wind recognize(If p 552 N94-34976 An agildy memc structure for operational agility turbines under conslant wind velocdy Computatm, n of unsteady flows over airfoils p 534 N94-34629 ]BTN-94-EIX94321333311] p 548 A94-60043 p 525 N94-34977 FLIGHT PATHS FLOW CHARACTERISTICS FLUID FLOW Aircraft a_t flight path simulebon and animation Numencal investigation of cylinder wake flow with e rear Natural convection in a cavity with fins attached to both IBTN-94-EIX94311329129} p 518 A94-60171 stagnatK)n jet vertical walls IBTN.94-EIX94301315998J p 547 A94-60034 ISTN-94-EIX94351142119J p 550 A94-60412 Static and dynamic flight.path stability of airplanes Characteristics of the Sbuttle Orbiter _ flow dunng FLUID JETS JBTN-94-EtX94361135428) p 522 A94-60625 a re-entry condition Numerical investKJahon of cylinder wake flow with a rear FLIGHT PLANS [ BTN.g4-EIX94311322888 ] p 520 A94-60208 stagnation jet FINDER, A system providing complex decision support Natural convection m a cavity with fins attached to both [BTN.94.EIX943013159981 p 547 A94-60034 for commercial transport replanning operabons vertical walls Injecbon of babbling liquid lets from multiple infectors [BTN-94-EIX94331335529J p 549 A94-60210 [BTN-94-EIX94351142119] p 550 A94-60412 into a supersonic stream FLIGHT RECORDERS FLOW DISTRIBUTION [BTN-94-EIX94321333316] p 520 A94-60267 Reduction of fatKjue load experience as part of the Reattachment sludies of en oscillating airfoil dynarmc Structure and ponetratic, n of a supercribcal fluid let m fatigue management program for F-16 aircraft of the stall flowfleld suoersonic flow RNLAF p 532 N94.34598 [BTN-94-EIX94301315980] p 515 A94-60016 JBTN-94-EIX943213333171 p549 A94-60268 FLIGHT SAFETY Crossflow topology of vorlicel flows FLUTTER Safety study: A review ol fiightcrew-involved, malor [BTN.94-EIX94301315993] p 515 A94-60029 Loca_zat_3n of aeroeiast_c modes in m_stgned accidents of US air careers. 1978 through 1990 Ne,,ner-Stokes solver for hypersonic flow over a slender high-energy turbines f PB94-917001 ] p 529 N94-35482 cone [BTN-94-EIX94321333307) p 547 A94-60039 Aircraft accident report: Uncontrolled collision with [BTN-94-EIX94311330681 } p 543 A94-60110 Experimental investigabon ot counter-rotatm Fatigue management and verification of airframes Progress and purpose of IHPTET program HEAT RESISTANT ALLOYS Reta,ned mec ha nw.,al propertms of a new AI-Li-Cu-Mg-Ag p 531 N94-34591 p 538 N94-34607 alloy es a function Of thermal exposure time and Frequency domain analysis of the random loading of Integration of magnetic bearings in the design of temperature cracked panels advanced gas turbine engines p 554 N94-35903 INASA-CR-196021 I p 556 N94-35974 GAS TURBINES [BTN-94-EIX943013201641 p 546 A94-60873 HEAT TRANSFER FREE CONVECTION Structural integrity and containment aspects of small Preliminary investigations on improving air.augmenled Natural convection in a cavity w_th fins attached to both gas turbine engines vertical walls rocket performance [BTN.94.EIX943313375001 p 550 A94.60335 I BTN-94-EIX94351142119 j p550 A94-60412 IBTN-94-EIX94321333323J p 544 A94.60274 Composite matrix expenmental combusfor FREE FLIGHT Natural convection in a cavity with fins attached to both INASA-CR.194446) p 538 N94-34679 A review and development of corretebons for base vertcal walls The aerodynamic and heat transfer effects of an endwsli pressure and base heating in supersonic flow ISTN-94-EIX943511421t9] p 550 A94-60412 boundary layer fence in a 90 degree turning square duct [ SAND93.02801 p 526 N94.35360 Numerical method for simulating fiuKI-dynamic and FREE FLOW I AD-A278903 } p 553 N94-35803 heat-trensfar changes in/at-engine injector faed-arm due GASOLINE Structure and penetration of a supercntical fluid jet in to fouling supersonic flow Unleaded AVGAS program IBTN.94-EIX943511421331 p 537 A94.60426 IAD'A2786501 p 547 N94-35795 [STN-94-EIX943213333171 p 549 A94-60268 Composate matrix expenmental combostor FREQUENCIES GEAR TEETH INASA-CR-1944461 p 538 N94-34679 An overview of recent advances in system Low-noiss, high.strength, spiral.bevel gears for HEUCOPTER CONTROL identifK:ation p 546 N94-35880 helicopter trensmissmns Evetuat_n of the dynamics end handling quality FUEL COMBUSTION IBTN-94-EIX94321333312} p 548 A94-60044 cheracterrstics of the Bell 412 HP helicopter Raman measurements at the exit of a combustor GEARS [ BTN.94.EIX94331337502 ] p530 A94.60337 sector Low-noise, high-strength, s_ral-bevel gears for Study findings on the influence of maneuverability end { BTN-94-EIX94341338356 _ p546 A94-60348 bahcopter transmissions agility on helicopter handling qualities FUEL CONTROL {BTN-94-EIX94321333312] p 548 A94-60044 p 533 N94-34624 Hot gas ingestion effects on fuel control surge recovery GENERAL AVIATION AIRCRAFT HELICOPTER PERFORMANCE end AH-1 rotor drive train torque slakes Annual rev_ of aircraft accident dais: US general Evaluation of the dynamics and hendting quality [NASA-CR-191047J p 538 N94-34993 aviation calendar year 1991 charactenstcs of the Bell 412 HP hebcopter FUEL INJECTION [PB94-127982] p 528 N94.34991 IBTN.94.EIX94331337502| p 530 A94-60337 Study tindiegs o_ the influence of maneuverability end Turbulent combustPon regimes for hypersonic proOutsion Annual review of =urcreft accident data US general employing hydrogen-sir diffus_n flames aviabon, calendar year 1992 agility on helicopter handling qualitms p 533 N94-34624 [BTN-94-EIX94321333324] p 546 A94-60275 [PB94.1810541 p 529 N94.35496 The influence of flying qualities on operational agility Numerical method for simulating fluid.o'ynamic end The influence of data link.provided graph¢.al weather p 534 N9,1-34628 heat-transfer changes in jet-engine injector teed-arm due on pilot decismn-meking HEUCOPTIER PROPELLER DRIVE to fouling lAD-A278871 ] p 556 N94-35596 [BTN-94-EIX94351142133} p 537 A94-60426 Low-norse. high-strength, soiral-bevel gears for Unleaded AVGAS Program Experimental investigatK>n on supersonic combustion rmkcoptar transmissions lAD-A278650) p 547 N94-35795 [ BTN.94-EIX94321333312 J p 548 A94-60044 (2) GEOPOTENTIAL IBTN-94-EIX94351144985] p 537 A94-60447 Hot gas ingestion effects on fuel control surge recovery JPRS report: Science end technology. Central Eurssm FULL SCALE TESTS end AH-1 rotor drive train torque sp*kss [JPRS-UST-94-O06] p 553 N94-35226 Approximate similarity pnnople for a full-scale STOVL [NASA..CR-191047] p 538 N94-34993 HEUCOPTERS elector Measurement and prediction of dynamic temporetures [ BTN-94-EIX94341338360 ] p 550 A94-60352 Evskmtion of the dynarmcs and handling quality in unsymmetrkcally cooled gtass windows cheractenstics of the Bell 412 HP helicopter An Assessment of Fe_jue Damage end Crack Growth I BTN-94-EIX94351142128 ] p550 A94-60421 Predict=on Techmques [BTN.94-EIX94331337502| p 530 A94-60337 GOVERNMENT PROCUREMENT [AGARD-R-797] p 550 N94-34581 Accurate estimation of object location in an image Budget ssbnmtss, fiscal year 1995. Volume 1: Agency Fatigue desKjn, test and in-service experience of the summ4m/, human space lt=ght, and sc=ence, aeronautics sequence using helicopter flight data BAe Hawk p 531 N94-34597 p 537 N94-35055 and technology FURNACES INASA-TM-109791 ] p 560 N94-35899 Selected topics on the active control of helicopter Processing yttrium barium copper oxide superconductor GRAPHICAL USER INTERFACE eeromechenicaJ snd vibrat0on problems in near-zero gravity User's guide for en interactive personal computer p 541 N94-35874 { BTN-94-EIX94311332378 ] p550 A94_0951 intedaco lor the aeropredicl_ code HEUUM FUSELAGES [NSWCDD/TR-94/107] p 559 N94.35958 injection Of bubbling liquid jets from multiple inlectors Drag reduction of airplane fi_elages through shaping GRAVITATION into a su_c stream by the inverse method ProceSsslg yttrium barium _ oxide superconductor [STN-94-EIX94321333316] p 520 A94-60267 IBTN-94-EIX94311329117] p 536 A94-60183 in near.zoro gravity HELMET MOUNTED DISPLAYS Ground vibration test Of the XV-15 Tlitrofor Research [ STN-94-EIX94311332378 ] p550 A94-60951 Wide-Eye (tm)/baimet mounted display system for A_rcrafl and pretest predictions p 541 N94-35972 GRAVITY WAVES rotorctaft appiicatinns JPRS re_co_: Science and technology. Central Eurasm [BTN.94-EIX94331335528 p 549 A94-60209 G IJPRS-UST-94-006] p 553 N94-35226 HIGH REYNOI.JD_ NUMBER GRID GENERATION (MATHEMATICS) Drag reduction of awplane fuselages through shaping GALERKIN METHOD Characterization of dynam¢ stall phenOmenOn usleg by the inverse method A three dimensional multigrid Reynolds-averaged two..din_m_onal unsteady Never-Stokes equations [ BTN-94-EIX94311329117 p 536 Ag4-60183 Newer-Stokes solver for unstructured meshes p 524 N94-34974 HIGH STRENGTH INASA-CR-194908J p 528 N94-35994 GROUND EFFECT (AERODYNAMICS) Low-nolss, high-strength, sp=rel-bevel gears for GAS COOLING Compulational analysis of • single jet impingement helJcoptar transmissions Inverse design of super-elliptic cooling passages in ground effect lift loss IBTN-94-EIX94321333312 p 548 A94-60044 |BTN-94-EIX94311329114] p 5t9 A94-60186 coated turhine blade aMoils HIGH TEMPERATURE GROUND EFFECT MACHINES IBTN-94-EIX94311330654] p 548 A94-60137 Measurement end prediction Of dynamic temperatures Data _, imllysis and results Of LACV-30-07 sir GAS GENERATORS in unsymmethcally cooled g_sss windows vehicle taele. Fort Story, VA, August - September The simulation Of a propulsive jet end force [BTN-94.EIX94351142128 p 550 A94-60421 1993 measurement ue=ng a magnetically suspended wind tunnel HiGH TEMPERATURE ENVIRONMENTS model p 527 N94-35855 |AD-A27885g} p 527 N94-35826 Measurement end prediction of dynamic temperatures GAS JETS GROUND SUPPORT SYSTEMS in unsymmethcally cooled _ass windows Mission Evaluation Room Intell_ent Diagnostic and Structure and penetmbon ots supefchtical fluid jet in [ BTN-94-EIX94351142128 p 550 A94-60421 suoorsonic flow Analyeis System (MIDAS) p 558 N94-35064 GROUND HIGH TEMPERATURE GASES I BTN-g4-EIX94321333317 ] p549 Ag4-60268 Preliminary invest_tions on improving air-augmented The simulation of a pr'opuisive jet and force USAF/AEDC aerodynamic and prof)ulsion ground test rocket performance measurement using a magnetically su_koended wind tunnel end evaluation techniques for highly maneuverable aircraft: {BTN-94-EIX94321333323 p 544 A94-60274 model p 527 N94-35855 CapsiZe end challenges p 532 N94.34606 GAS MIXTURES Ground Wbretion test of the XV-15 Tiltrotor Research Hot gas ingestion effects on fuel control surge recovmy Aircraft end pretest predictions p 541 N94-35972 and AH-1 rotor drive train torque spikes On the venous forms Of the energy equation for a dilute, |NASA-CR-191047| p 538 N94.34993 monatorrsc mixture Of nonreacting gases HIGHLY MANEUVERABLE AIRCRAFT [NASA-CR-4612] p 527 N94-35864 H GAS STREAMS Technologies for Highly Manoeuvrable Aircraft IAGARD-CP-548] p 532 N94-34605 Inlection of bubbling kqu¢l jets from multiple injectors HARMONIC CONTROL USAF/AEDC aeredynam,c and propr_lw_n ground tael into • supersonic stream Selected top*cs on the active control of helicopter end _tiort techniques for highly menetNarable _iroraft: [BTN-94-EIX94321333316) p 520 A94-60287 aen_arscal end vibration problems GAS TURBINE ENGINES p 541 N94-35874 Capabilities end challenges p 532 N94-34606 Measurement of diflusmn in fluid systems: Apfdmations HARRIER AIRCRAFT Aerodynamic design of super maneuverable aircraft p 533 N94-34617 to the su_oarcribcal fluid region Hsmar 2: A companson of US and UK lkowo&ches tO { BTN-94-EIX94311330660 | p548 A94.60131 fatigue clearance p 531 N94.34596 Flying qualities evsluebon maneuvers Structural integrity end containment aspects of smell YAV-aB reaction control ayetem bleed and control power p 533 N94-34623 gas turbine engines usage in hovel and transition Operational agility: An overview ot AGARD Working IBTN-94-EIX943313375001 p 550 A94-60335 I NASA-TM-104021] p 540 N94-34994 Group 19 P 534 N94-3462.5 A-10 SUBJECT INDEX IONIZATION The unsteady pressure field and vort,'city productiion at Experimental studies of shock-wave/wall-jet interaction INCOMPRESSIBLE FLOW the suction surface of a pitching airfoil in hypersonic flow. part A Symmetry breaking in vorbcel flows over cones: Theory p 524 N94-34972 I NASA-CR-195957] p 523 Ng4-34964 and numencsl experiments HISTORIES Expanmental studies of transpiration cooling with shock [BTN-g4-EIX94301315981 ) p 547 A94-60017 In-flight simulation studies at the NASA Dryden Flight interaction in hypersonic flow. part B INDICATING INSTRUMENTS Research Facdity p 536 N94-35969 INASA-CR-195958] p 523 N94-34965 Wide-Eye (tm)/helmet mounted display system for HLolO REENTRY VEHICLE A review and development of correlations for base rotorcraff applications Developing and fhght testing the HL-t0 lifting body: A pressure and base heating in supersonic flow (BTN-g4-EIX94331335528] p 549 A94-60209 precursor to the Space Shuttle J SAND93.0280 J p 526 N94-35360 INDUCED DRAG [NASA-RP.1332] p 535 N94-34703 Development and application of computatK)nel Ouantitative low-speed wake surveys HORIZONTAL FLIGHT aerothermodynamics flowheld computer copes J BTN-94-EIX94311329113 J p520 Ag4-60187 INASA-CR-196136] p 526 N94-35498 Computation Of helicopter rotor acoustics in forward INFORMATION DISSEMINATION flight Investigation of Burnetl equations for two-dlmenmonel NASA/DaD Aerospace Know_dge DiffuSiOn Research hypersonic flow INASA-CR-1961321 p 560 N94-36031 Prolect Paper 42: An analysis of the transfer of Sc:entific HORIZONTAL SPACECRAFT LANDING IAD-A278942J p 527 N94-35717 HYPERSONIC HEAT TRANSFER and Technical loforrnat,on (STI) in the US aerospace Effect of litt-to-drag ratio in pilot rating of the HL-20 industry Aerodynamic heating environment 0efinltion/thermal landing task I NASA-TM-1098631 p 560 N94-34730 protection system selection for the HL-20 IBTN-94-EIX94351137057J p 544 A94-60397 INFORMATION SYSTEMS HOT CORROSION [BTN-94-EIX94351137058J p 544 A94.60398 Combined LAURA-UPS solution procedure Ior National tacdihes study Volume I: Facilihes inventory Hot Corrosmn Test Facility at the NASA Lewis Specml chemicallyoreacting flows INASA-TM-1098541 p 541 N94-34632 Projects Laboratory INASA-TM-1079641 p 55t N94-34721 INGESTION (ENGINES) I NASA.CR.195323 J p 543 N94-35267 HYPERSONIC SHOCK Hot gas ingestion effects on fuel control surge recovery HOVERING Invesl_jat_on of Bumett eguabons for lwo-dimens_onel and AH-1 rotor dove train torque spikes YAV-aB reaction control system bleed and control power hypersonic flow |NASA-CR-1910471 p 538 N94-34993 usage in hover and transitK)n IAD-A278942J p 527 N94-35717 INGRESS (SPACECRAFT PASSAGEWAY) INASA-TM-104021 J p 540 N94.34994 HYPERSONIC SPEED Human factors evaluation of the HL-20 full-scale HUMAN CENTRIFUGES Technology and staging effects on two-stage.to-orbit model Application of centrifuge based dynam0c flight simulation systems IBTN-94.EIX943511370651 p 545 A94-60405 to enhanced maneuverability RDT/E lBTN-94.EIX94311322891] p 520 A94-60205 INJECTION p 541 N94-34630 Aerodynamic characteristics of the HL-20 Injection of bubbhng IKIU_I jets from multiple injectors HUMAN FACTORS ENGINEERING J BTN-94.EIX94351137055 ] p 544 A94-60395 into a supersonic stream Human factors evaluation of the HL-20 full-scale Future ultra-speed tube-flight p 555 N94-35918 IBTN-94-EIX94321333316] p 520 A94-60267 model HYPERSONIC VEHICLES Structure and penetratm.n of a supercritical fluid jet in {STN-94-EIX94351137065] p 545 A94-60405 Develop0ng and flight testrng the HL-10 lifting body: A suparsonJc flow Effects of checklist interface on non-verbal crew precursor to the Space Shuttle |BTN-94-EIX94321333317J p 549 A94-60268 communicabons (NASA-RP.13321 p 535 N94-34703 INJECTORS INASA-CR.177639] p 528 N94-34915 A review and development of correlations for base InjecUon of bubbling IKluld jets from multiple inlectors The influence of data link-provided grsp_cal weather pressure and base heating in supersonK: fk_v into a supersonic stream O_ pilot decision-making ISAND93-0280] p 526 N94-35360 JBTN-94-EIX94321333316 ] p 520 A94-60267 lAD-A278871] p 556 N94-35596 HYPERSONIC WIND TUNNELS INLET FLOW Final-Approach Spacing ARIa (FASA) evaluation for Combustion shock tunnel and interface compression to Computational methods for HSCT-intet controls/CFD terminal.area, time-based air traffic contrO_ increase reservolr pressure and enthalpy interdisciplinary research I NASA-TP-3399] p 529 N94-36048 [BTN-g4-EIX94311330650] p 516 A94-60141 {NASA-TM-1066181 p 539 N94,-35352 HUMAN-COMPUTER INTERFACE National facilities study. Volume 2: Task group on INSPECTION The influence of data link-provided graphical weather aeronaubcel research and development facilities report Assessment of in-service aircraft fatigue menitoring on pilot decis_n-maklog INASA-TM-109855] p 542 N94-34633 process p 531 N94-34593 lAD-A278871] p 556 N94-35596 HYPERSONICS The role of fatigue analysis for design of military HYDRODYNAMICS Hypersonic fm aerodynam,cs airorafl p 531 N94-34594 INTERACTIONAL AERODYNAMICS Expliat Kutta condition for an unsteady two-dimensional [BTN-94.EIX94311330699] p 516 A94-60092 constant potenbal panel method HL-20 computational fluid dynamics anelyms Three-dimens_onel closure of the passage-averaged [BTN-94-EIX94301315990J p 515 A94-60026 [BTN-94-EIX94351137059] p 545 A94-60399 vorticity-potentlal formulabon HYDROFOIL OSCILLATIONS Investigation of Bumett equations for two-dimens_onal [BTN-94-EIX94301315991 J p 547 A94-6(X)27 Vane-blade interaction in a transomc turbine. Part 1: Expiloit Kutta condition for an unsteady two-drmens_nel hy_rscnk_ fk_ Aerodynamcs constant potential panel method {AD-A278942J p 527 N94-35717 [BTN-94-EIX94321333305] p 516 A94-60037 [ BTN-94-EIX94301315990 ] p515 A94-60026 Superlmmc transport wing minimum weight design HYDROFOILS integrating aerodynamrs and structures Explicit Kutta condition for an unsteady two-dimensional [STN-94-EIX94311329123J p 518 A94-60177 constant potential panel method ICE Vortex-wing interaction at a close-coupled canard |BTN-94-EIX94301315990] p 515 A94-60026 configuration HYDROGEN FUELS Prediction at ice shapes and their effect on airfoil drag [BTN-94-EIX94311329121] p 519 A94-60179 Turf_Jlerd propuls_,n [BTN-94-EIX94311329115] p 519 Ag4-60185 combustion regimes for hypersonic Forebod_ vorlex control for w_ng rock suppression employing hydrogen-air diffuslon flames IMAGE ANALYSIS [ BTN-94-EIX94311329119 ] p530 A94-60181 JBTN-94-EIX94321333324 ] p546 A94*60275 Analysis of wavelet technology for NASA app_.atioris INTERFACIAL TENSION Combustion performance of dump combustor in ramlet [NASA-CR-195929] p 522 N94.34704 Detarmznabon of tire-wheel interface loads for aircraft engine using liquid hydrogen fuel IMAGE PROCESSING wheels IBTN-94-EIX94351144992J p 538 A94-60454 Accurate estimation of object location in an image [BTN-94-EIX94311329136_ p 517 A94-60164 HYDROXYL RADICALS sequence uam_ helicopter fl_lht data INTERNAL WAVES Planar KrF laser-induced OH fluorescence imaging in p 537 N94-35055 JPRS report: Science and techr!ology Central Euresm a supersonic combusbon tunnel Unsteady structure of leadlog-edge vorlres on a darts lJPRS-UST-94-O06| p 553 N94-35226 [BTN-94-EIX94321333315] p 520 A94-60266 w_ng INTERNATIONAL COOPERATION HYPERSONIC FUGHT [AD-A278968} p 526 N94-35529 AGARD highlights 93/2 Turbulent combustion regimes for hyperscmc pfopulsmn IMAGING TECHNIQUES [AGARD-HIGHLIGHTS-93/2] p 561 N94-35444 employing hydrogen-air diffusion flames Planar KrF laser-induced OH fluorescence imaging in INVENTORIES JBTN-94-EIXg4321333324 ] p546 A94-60275 a supersonic combust_,n tunnel Nabonel facilitms StUdy. Volume 1: Facilities inventory HYPERSONIC FLOW [BTN-94-EIX94321333315] p 520 A94-60266 [NASA-TM-1098541 p 541 N94-34632 Naviar-Sto_es solver for hyperson¢ flow over a slender INVlSClD FLOW cone F0eld daployabla nonpes_'_--twe impact damage Symmetry breaking in vortral flows over cones: Theon/ ( BTN-94.EIX9431133068t ] p543 A9.4-60110 aseesement metho_ for composite structures and numencal expenments Combustion shock tunnel and interlace compres,mon Io [BTN-94-EIX94301321378] p 546 A94-60892 IMPACT DAMAGE [BTN-94-EIX943013159811 p 547 A94-60017 increase reservoir pressure and enthaipy High incidence flow analy_s over the Rafele A IBTN-94.EIX94311330650J p 516 A94-60141 Field deployable nondestructive impact damage p 522 N94-34612 Computational analysis Of off-des_gn waveriders assessment methodology for _te structures Unsteady separation process and vorticity balance on {BTN-94-EIX94311329125] p 549 A94-60175 [BTN-94-EIX94301321378] p 546 A94-60892 unsteady airfoils p 524 N94-34970 Computabon of nonequilionum hypersonic flowfields Annual revmw of aircraft accident data: US general Computation of unsteady flows over a_oils around I'_m_ol'_e cylinders aviabon calendar year 1991 p 525 N94-34977 |PB94-127982.] p 528 N94.34991 I BTN-94-EIX94351142135 ] p521 A94-60428 Some aspects of unsteady separabon Direct simulation with vibration-dissociation causing IMPINGEMENT p 525 N94-34979 [BTN-94-EIX94351142136] p 521 A94-60429 Expenmentel studies Of transp_ation cookng with shock ION ENGINES Cek:utation of mat-gas effects on aelo_l aerodynamic interaction in hyperSOnK: flow, part B AFOSR Contractors Propuls,,on Meeting characteristics lNASA'CR'195958] p 523 N94-34965 IAD-A279028_ p 539 N94-35746 IBTN-94-ElXg4351142143] p 521 A94-80436 IN-FLIGHT MONITORING IONIZATION Cor_oined LAURA-UPS solution procedure for In-flight velocity measurements using laser Doppler New two-temperature dissociation model for reacting cher'mcally-reacting flows anememe_ flows [NASA-TM-1079641 p 551 N94-34721 [BTN-94-EIX94311329139J p 549 A94-60161 I BTN-94-EIX94351142137 ] p560 A94-60430 A-11 SUBJECT INDEX ISOLATORS LIFT AUGMENTATION ISOLATORS LAMINAR FLOW Concepts and application of dynamic separation for Active thermal isolation for temperature responsive Active thermal isolation tor temperature responsive sensors sensors agility and super-maneuverability of wrcraft: An assessment p 535 N94-34988 INASA-CASE-LAR-14612-t } p 552 N94-35074 INASA-CASE-LAR-14612-1 J p 552 N94-35074 LIFT DRAG RATIO Unsteady structure o1 leading-edge vortices on a delta Effect of lift.to-drag ratio in pilot rating of the HL-20 wing J lAD-A278988) p 526 N94-35529 landing task LAMINATES {BTN-94-EIX94351137057} p 544 A94-60397 JET AIRCRAFT MFTING BODIES Shear buckling response of tailored composite plates Aerodynamic cheractenstics of the HL.20 Fatigue design, test and in-se_tce experience of the IBTN.94.EIX94301316000} p 549 A94-60256 BAe Hawk p 531 N94-34597 IBTN-94-EIX9435t137055J p 544 A94-60395 DesKJn Oriented structural analysis JET ENGINE FUELS [NASA-TM-1091241 p 551 Ng4-34722 Six.degree-of-freedom guidance and control-entw Hot Corrosion Test Facility at the NASA Lewis Special LANDING GEAR analysis of the HL-20 [BTN-94-EIX94351137056] p 544 A94.60396 Projects Laboratory Aircraft landing gear posJtioning concermng abnormal [NASA-CR-195323 ) p543 N94-35267 Effect of lift-to-drag ratio in pilot rating of the HL-20 landing cases JET ENGINES IBTN-94-EIX94311329140] p 536 A94-60160 landing task Approximate similarity principle for a full-scale STOVL LANDING SIMULATION [BTN-94-EIX94351137057 ] p 544 A94-60397 elector Effect of lift-to-drag retio in pilot rating of the HL-20 Aerodynam*c heating environment definition/thermal |BTN.94.EIX94341338360) p 550 A94.60352 protection system selection for the HL.20 lending task Numerical method for simulating flu_l,-dynam0c end IBTN-94.EIX94351137058 ] p544 A94-60398 {BTN.94.EIX94351137057] p 544 A94-60397 heat.transfer changes in let-engine inlector feed-arm due LASER ANEMOMETERS HL-20 computational fluid dynarn0cs analysm to fouling {STN.94-EIX94351137059 ] p545 A94-60399 In-flight velocity measurements using laser Doppler IBTN*94.EIX94351142133J p 537 A94.60426 Preliminary structural evaluation and design of the anemometry JET FLOW {BTN-94-EIX94311329139] p 549 A94-60161 HL-20 Structure and penetration of a sup_critcel fhJid _1 in LASER APPLICATIONS [BTN-94-EIX94351137060 ] p545 A94-60400 Human factors evaluation of the HL-20 full.scale su0erson¢ flow A supersonic tunnel for laser and flow-seeding [ BTN-g4-EIX94321333317 ] p 549 A94-60268 model techniques Development and application of computational [NASA.TM-106588] p 556 N94-35945 I BTN-94-EIX94351137065 ] p545 A94-60405 UFTING REENTRY VEHICLES aerothermodyrmmics flowfleld computer codes LASER BEAMS [NASA-CR-196136) p 526 Ng4-35498 Three-d_man_el thermal analysis for laser-structural Aerodyrmrn_c cheractermtics of the HL-20 JET IMPINGEMENT interactions ISTN-94"EIX94351137055] p 544 A94-60395 Computational analysis of a single iet impingement ISTN*94-EIX94351142117| p 560 A94-60410 Six.degree-of-freedom guidance and control-entry ground effect lift loss LASER DOPPLER VELOCIMETERS analysis of the HL-20 IBTN-94-EIX94311329114] p 519 A94-60186 |BTN.94-EIX94351137056] p 544 A94-60396 In-flight velOcity measurements using laser Doppler JET PROPULSION Effect of lift-to-d_ag ratio in pilot rating of the HL-20 snemometry ProputsK_-induced aerodynamic effects measured w_h [BTN.94.EIX94311329139 } p54g A94-60161 landing task a (uli-ecale STOVL model Comparison of optical measurement tachmques for [BTN-94-EIX94351137057] p 544 A94-60397 IBTN-94-EIX94311329120] p 51g A94-60180 turbomechinery ftowfielda Aerodynamic heating enveonment definition/thermal Challenging the Future - Journey to Excellence. [STN-94-EIX94341338357] p 559 A94-60349 protecboa system selection for tim HL-20 [BTN-94-EIX94351137058] p 544 A94-60398 Aero_roputsKDrl strategic plan for the 1990's Data reduction procedures to( laser velocimeter HL-20 computational fluid dynamics analysis INASA-TM-109250] p 545 N94-35591 measurements in turboma_ rotors JOINED WINGS [ BTN-94-EIX94351137059 J p545 A94-60399 |NASA-C,R-195343] p 552 N94-35224 Joined-wing model wbrations using PC-based modal LASER INDUCED FLUORESCENCE Preliminary structural evaluation end des*gn 0t the testing and finile element analys_s Planar KrF laser-induced OH fluorescence nnaging in HL-20 {BTN-94-EIX94311329141 ] p517 A94-60159 [BTN-94-EIX94351137060] p 545 A94-60400 • supermon*c combustion tunnol Human factors evaluation of the HL-20 full-scale JOINTS (JUNCTIONS) [BTN-94-EIX94321333315J p 520 A94-60266 Analy_s of multifastarmr composite joints LATERAL CONTROL model JSTN-94-EIX94311330690] p 548 A94-80101 {BTN-94-EIX94351137065] p 545 A94-60405 Dynamic tests to demonstrate lateral control using Risk analysis of the C-141 WS405 inner-to-outer wing forebody suction on large scale models in the DRA 24 LIGHT AIRCRAFT _:_nt p 531 N94-34592 foot wind tunnel p 539 N94-34613 Tail load calculations for light airplanes LEADING EDGE SLATS [BTN-94-EIX94311329148| p 517 A94-60152 UGHT SCATTERING The quest for stldl-groe dyrmrmc lift K p 525 N94-34986 Surface interference in Reylelgh scattanng LEADING EDGE SWEEP measurements near forebodms [STN-94-EIX94301315999] p 516 A94-60035 K-EPSlLON TURBULENCE MODEL Contr_ of ing-edge eaperation on a cambered detm Measurement of diffusion in fluid systems: Appi¢,a_ons Computatk:x_l analysis of • single jet impingement wing p 539 N94-34616 ground effect lilt loss LEADING EDGE THRUST to the supercnbcal fluid region [BTN-94-EIX94311330660] p 548 A94-60131 [BTN-94-EIX94311329114} p 519 A94-60186 Control of leaoing-edge seperation on a cambered delta LININGS KALMAN FILTERS wing p 539 N94-34616 Compomta metnx expenmantal combeato_ Dean and analysis of a Kalman filter for LEADING EDGES ten'sin-referenced po_tiomng and guidance Computation and diecus._on of a needy constant degree [NASA-CR-194446] p 538 N94.34679 | BTN-94-EIX94311329124 ] p 557 A94-60176 of _ turbkle stage MOULD FILLED SHELLS KELVIN-NELMHOLTZ INSTABILITY [BTN.94-EIX94351144987 | p537 A94-60449 S_mpMhod method for evaluabng the flight stability of iK_id-filled pro_octJ_es Mechanisms of flow control with the unsteady bleed Control of leading-edge separation on a cambered delta [ BTN-94-EIX94311322905 ] p544 A94-60101 technique p 525 N94-34987 var_ p 539 N94-34616 UOUID FLOW KEROSENE Control of feeding-edge vOrtices on a darts wing Remen measurements et the exit of a combustor p 524 N94-34971 Injection of bubbling li_ jets from multiple inlectors eact(x Unsteady sUucture of leedmg-edge vortices on i delta into • _ic stream [STN-94-EIX943213333t6] p 520 A94-60267 [BTN-94-EIX94341338356] p 546 A94-60348 w_ng LIQUID HYDROGEN KNOWLEDGE BASED SYSTEMS lAD-A278988] p 526 N94-35529 LEVITATION Combustion performance of dump combustor in ramjet FINDER, A system providing complex decision support for _c0al transport reptanning operations Future ultra-speed tube-flight p 555 N94-35918 en_ne umng I_ hydrogen fuel [ BTN-94-EIX94351144992 ] p 538 A94-60454 IBTN-94-EIX94331335529} p 549 A94-60210 LIFE (DURABILITY) Rotorcrsft fatigue life-prediction: Pest, prenmnt, end LIQUID PROPELLANT ROCKET ENGINES Engineering large-scale agent-based systems tuture p 551 N94-34590 AFOSR Contrectors Proputmo_ Meeting consensus p 558 N94:35071 Dimage tolerance management of the X-29 vertical lAD-A279028] p 539 N94-35746 KNUOSEN FLOW tail p 531 N94-34595 LITHIUM ALLOYS Investigation of Bumett equations for two-dimen_onal UFE BCIENCES Retained mechamcsl propertms of S new AI-U-Cu-Mg-Ag tVpar_n¢ "ow JPRS report: Science and technology, Central Eurama alloy as a function of thermal exposure time and lAD-A278942] p 527 N94-35717 [JPRS-UST.94-005] p 553 N94-35342 temperature KRYPTON FLUORIDE LASERS Dm3ctods diecratiomm//und [STN-94-EIX94301320164] p 546 A94-60873 Planar KrF laser-reduced OH tiuoreececme imaging in INASA-TM-103997] p 561 N94-35370 LITHOGRAPHY a superso_c combustion tunnel JPRS report: Scmnce and technology. Central Eura_,a PIimar rotatkDnal magnetic micromotors with integrated [BTN-94-EIX94321333315] p 520 A94-60266 [JPRS-UST.94-010] p 553 N94-35385 shah en¢oder and magnetic rotor tavltabon KuI"rA,,JOUKOWSKI CONDITION JPRS report: Science and technology. CenVel Eormm p 555 N94-35907 Explicit Kutta condibofl for an unsteady two-dinlmlsmnal [JPRS-UST-94-012| p 553 N94-35387 LONGITUDINAL STABILITY constant potential panel method Research and technology, 1993 Aerodynamc design of super manouver_le awcreff IBTN-94.EIX94301315990} p 515 A94-60026 [NASA.TM*108816] p 561 N94-36117 p 533 N94.34617 UFT Wake cu_ature and mrfo_ lilt LOW ALTITUDE Accurate estimation of object locebon in an image L [BTN-94-EIX94311329147J p 517 A94-60153 Vortex-wing interaction of a close-coupled canard sequence ulMng hel¢opter flight data p 537 N94-35055 LAMINAR BOUNDARY LAYER configuration Minimum performance standards: A_rborne low-range Structure of local wessure-dhven three-dimensional [BTN-g4-EIX94311329121 ) p519 A94-6017g radar aHimeters transient boundary-layer separatk:_ Unstesdy lift of a tiepped airfoil by ind_'_el concepts IRTCA-DO.155] p 537 N94-35344 IBTN-94-EIX94301315979} p 515 A94-60015 IBTN-94-EIX94311329118] p 519 A94,-60182 A-12 SUBJECT INDEX NASAPROGRAMS LOW NOISE MANAGEMENT METHODS MICROBURSTS (METEOROLOGY) Low-noise, high-strength, spiral-bevel gears for Control strategies for space boosters using air collection Terminal Doppler Weather Radar (TDWR) Low Level helicopter transmissions systems Wind Shear Alert System 3 (LLWAS 3) integration stud,as IBTN-94-EIX94321333312J p 548 A94-6C,044 [BTN-94-EIX94311330685] p 543 A94-60106 at Orlando International Airport LOW PASS FILTERS MANAGEMENT PLANNING lAD*A2789571 p 557 N94-35807 Third order LPF type compensator for flexible rotor National facilities study Volume 5: Space research and MICROGRAVITY APPLICATIONS suspension p 554 N94-35863 development facilities task group Processing yttnum banum copper oxide supercOnductor LOW SPEED INASA-TM-1098591 p 542 N94.34637 in near-zero gravity Quantitative low-speed wake surveys The Federal Aviation Administratfon plan for research, I BTN-94-EIX94311332378J p 550 A94-60951 I BTN-94-EIX94311329113 ] p520 A94-60187 engineering and development p 561 N94-35262 MICROMECHANICS MANEUVERABILITY LOW VISIBILITY Planar rotabonat magnetic rmcromotors with integrated Technologies for Highly Manoeuvreb/e Aircraft Synthetic vision for enhancing poor visibility flight shaft encoder and magnetic rotor levitation operations IAGARD-CP-548) p 532 N94-34605 p 555 N94-35907 fBTN-94-EIX94331335531 ] p 557 A94-60212 Engine characteristics for agde aircraft MICROMOTORS LUMINESCENCE p 538 N94-34608 Planar rotational magnetic micromotors with integrated A_rodynamic design of super maneuverable aircraft Flight testing of a luminescent surface pressure shaft encOder and magnetic rotor levitabon p 533 N94-34617 sensor p 555 N94-35907 INASA-TM-103970i p 522 N94-35394 AppiicatH>n of current departure resistance critena to MICROWAVE LANDING SYSTEMS the post-stall manneuvenng envelope An analysis of operational suitability for test and p 533 N94-34622 M evaluation of highly reliable systems Study findings on the influence of maneuverabihty and lAD-A2785731 p 530 N94-36184 agility on helicopter handling qualities MIDAIR COLLISIONS MACH NUMBER p 533 N94-34624 Annual review of aircraft accident data: US general Technology and staging effects on two-stage-to-orbit Operational agility: An ov_ of AGARD Working avtabon calendar year 1991 systems Group 19 p 534 N94-34625 |PB94-127982) p 528 N94-34991 Operational agility assessment with the AM-X a_'crafl {BTN-94-EIX94311322891] p 520 A94-60205 MILITARY HEUCOPTERS Incip_enl torsional stall flutter aerodynamic expenments p 534 N94-34626 Artihclal neural networks for predicting nonlinear on three-dlmens,onal wings The influence of flying qualibes on operational agility dynamic hekcopter loads IBTN-94-EIX94341338362J p 522 A94-60354 p 534 N94-34628 [STN-94-EIX94301315989J p 515 A94-60025 MAGNESIUM ALLOYS An agility metric structure for operational agility Study findiegs on the influence of maneuverability and Effect of coarse second phase parbcles on fet_ue crack p 534 N94.34629 agility on hekcopter handling quaiibes propagation of an AI-Zn-Mg-Cu alloy Appiicabo_ of centrifuge based dynamic fhght s=muiation p 533 N94-34624 (BTN-94-EIX94301320144] p 546 A94-60853 to enhanced maneuverability RDT/E MISSILE CONFIGURATIONS Retained rnecharacal properties O1 a new Ai.L,-Co-Mg-Ag p 541 N94-34630 User's gu_e for an interacftve personal computer alloy as a function of thermal exposure ftme and Concepts and epplicabon of dynamic separation for interface for the aeroprodiction code temperature agdity and super-maneuverability of aircraft: An |NSWCDD/TR-94/107J p 559 N94-35958 [BTN-94-EIX94301320164] p 546 A94-60873 assessment p 535 N94.34988 MISSILES MAGNETIC BEARINGS MANNED SPACE FUGHT Determination of slender body aerodynamics using Influence of backup bearings end support structure Budget estimates, fiscal year 1995. Volume 1: Agency discrete vo*lex methOdS dynamics on the behawor of rotors with active supoorts summary, human space flight, end science, aeronautics lBTN-94-EIX94311330679] p 543 A94-60112 INASA-CR-196119J p 553 N94-35500 and technok>gy MOBILE COMMUNICATION SYSTEMS |NASA-TM-109791] p 560 N94-35899 Aerospace apphcations of magnetic beanngs ATM and FIS data link services p 554 N94-35837 MASS FLOW RATE IBTN-94-EIX94331335533J p 530 A94-60214 Deragn, construction, and testing of a five achve axes In_eclK_n of bubbling liquid jets from multiple injectors MOISTURE CONTENT magnetic bearing system p 554 N94-35846 into a supersonic stream Predicbon of me sr_oes and their effect on airfoil drag Modelling and control of s rotor supported by magnetic [BTN-94-EIX94321333316] p 520 A94-60267 ]BTN-94-EIX94311329115) p 519 A94-60185 beanngs p 554 N94-35858 MATHEMATICAL MODELS MONATOMIC GASES Third order LPF type compensator for flexible rotor Axial COml_eesor performance dunng surge On the venous fonms of the energy eQuatN3n for a dilute. suspens=on p 554 N94-35863 [BTN-94-EIX94321333308] p 548 A94-60040 monatomic mixture of rlonroacting gases Second Intarnabonal Symposium on Magnetic New two-tompe_ature dissociation model for reacting |NASA-CR-4612) p 527 N94-35864 flows Suspension Technology, part 2 MONTE CARLO METHOD INASA-CP-3247-PT-2J p 546 N94-35902 [BTN-94.EIX94351142137] p 560 A94-60430 thveebgation of Monte Carlo aimuiat_n in FAA program Integration of magnetic bearings in the design of An assessment of fatigue crack growth prediction KRASH advanced gas turbine engtnes p 554 N94-35903 models for aorospace structures p 551 N94-34586 [BTN-94-EIX94311329128] p 536 A94-60172 Electromechanicsl simulation and test of rotabng Cost and schedule estimabon study repo_ MOTION SIMULATION systems with magnetic bearing or pmzoek_'thc actuator [NASA-CR-189344] p 558 N94-35256 Application of centhfu0e based dynamic flight _muletion active vibration control p 555 N94-35905 Influence of backup bearings and supporf structure to enhanced maneuverability RDTIE Planar rotational magnetic micromotors with integrated dynamics on the behavior of rotors with active sup_oorls p 541 N94-34630 [NASA-CR-196119] p 553 N94.35500 shaft encoder and magnetJC rotor levitabon MOTION STABILITY p 555 N94-35907 N_I modeling studms of wake vortex transport Simpl_ied method for evatueting the flight stability of Rotor dynamic behaviour of a high-speed oil-free motor and evolution within the planetary boundary layer Ik:luid-filled prolectiles INASA-CR-196078] p 529 N94-35522 compressor with a rigid coupling supported on four radial |BTN-94-EIX94311322905] p 544 A94-60191 magnetic bearings p 555 N94-35911 A three dimensional multigrid Reynolds-averaged MULTIGRID METHODS Magnetically suspended stepping motors for clean room Nevler-Stokes solver for unstnJctureO meshes New multigrid aplxoach fOr three-dimensional and vacuum enwronments p 555 N94-35915 [NASA-CR-194908) p 528 N94-35994 unstructured, adaptive grids MAGNETIC CONTROL MATRICES (MATHEMATICS) [BTN.94.EIX94301315973] p 559 A94-60009 Modelling and control of a rotor supported by magnetic Modelling and control of e rotor supported by magnetic A three dimensional multigrid Reynolds-averaged bearings p 554 N94-35858 beanngs p 554 N94-35858 Navmr-Stokes solver for unstructured meshes MAGNETIC LEVITATION VEHICLES MECHANICAL PROPERTIES INASA-CR-194908] p 528 N94-35994 Control of maglev vehicles with aerodynamic and Three-dimensK;¢ml thermal analyses for taser-sVucturel gu,deway disturbances p 554 N94-35842 interactions Second International Symposium on Magnet¢ [BTN-94-EIX94351142117] p 560 A94-60410 N SuspensJon Technology. part 2 Retmned mechan_.al propertms of a new AI-Li-Cu-Mg-Ag [NASA-CP-3247-PT-2] p 546 N94-35902 alloy as a funolJon of thermal exposure time and NAP-OF-THE-EARTH NAVIGATION Future ultra-speed tube-flight p 555 N94-35918 temperature Accurate estimation of ob_t locaben in an image MAGNETIC SUSPENSION [BTN-94-EIX94301320164} p 546 A94-60873 sequence using helicopte¢ flight data Aerospace applicatmns of magnetic beenngs METAL FATIGUE p 537 N94-35055 p 554 N94-35837 NASA PROGRAMS Risk analyms of the C-141 WS405 inrm¢-to-outer wtng The simulabon of a propulsNe jet and force joint p 531 N94-34592 NASAIDOD Aerospace Knowledge D_ffus_on Research measurement using a magnetically suspended wind tunnel Project. Paper 42: An analysis of the transfer of Scientific The role of fatigue analysis for design of military model p 527 N94.35855 aircraft p 531 N94-34594 and Technical Information (STI) in the US aerospace Third order LPF type compensator fOr flexible rotOr industry An overvmw of the F-16 serwce lile approach suspension p 554 N94-35863 [NASA-TM-109863| p 560 N94-34730 p 532 N94-34599 Second Internabonal Symposium on Magnetic D_rector's discretionary fund METEOROLOGICAL RADAR Suspension Technology, part 2 [NASA-TM-103997J p 561 N94-35370 Terrmnal Doppler Weather Rsdar (TDWR) Low Level [ NASA-CP-3247-PT-2 ] p 546 N94-35902 Aerosp_os Safety Advisory PaneJ Planar rotational magnetic mmromotors with integrated Wind Shear AkH1 System 3 (LLWAS 3) integration studms |NASA-TM-t09840] p 545 N94-35390 at Orlando Internetmnel Airport shaft encoder and magnetic rotor levitabo_ Challenging the Future - Journey to Excellence IAD-A278957| p 557 N94-35807 p 555 N94-35907 Aeropropolsion strategic plan fOr the 1990's Magnetmally suspended stepping motors for clean room METEOROLOGICAL SERVICES INASA-TM-109250| p 545 N94.35591 and vacuum environments p 555 ND4-35915 The influence of data link.provided graphical weather Budget estimates, fiscal year 1995. Volume 1: Agency Future ultra-speed tube-flight p 555 N9.4-35918 on pilot decision-making summary, human space flight, and science, aeronautics MAN MACHINE SYSTEMS [AD-A278871] p 556 N94.35596 end technology Effects of checklist interface on non-verbal crew Data redu_rements for ceiling and wsibility products INASA-TM-109791 ) p 560 N94-35899 communications deveiepment Research and technology. 1993 INASA-CR-1776391 p 528 N94-34915 lAD-A278959} p 556 N94-35720 INASA-TM-108816] p 561 N94-361t7 A-13 NATIONAL AIRSPACE SYSTEM SUBJECT INDEX NATIONAL AIRSPACE SYSTEM NOZZLE FLOW P The Federal Aviation Administration plan for research, Computabon and discussion of a needy constant degree engineering and development p 561 N94.35262 of reaction turbme stage PANEL METHOD (FLUID DYNAMICS) NATURAL GAS I BTN-94-EIX94351144987 J p537 A94-60449 Explicit Kutta condition for an unsteady two-dimensional Raman measurements at the exit of a combustor NOZZLES constant potential panel method sector Propulsion-induced aerodynamic effects measured with IBTN.94.EIX94301315990] p 515 A94-60026 IBTN-94*EIX943413383661 p 546 A94-60348 a full-scale STOVL model Precmmn requiremenl for potential.based panel NAVIER-STOKES EQUATION methods [BTN-94-EIX94311329120J p 519 A94.60180 Structure of local pressure-driven three-dimensional IBTN-94-EIX94301315995J p 515 A94-60031 Forebody vortex control for wing rock suppression transient boundary-layer separation Computation of unsteady flows over airfoils [BTN-94-EIX94311329t191 p 530 A94.60181 J BTN-g4-EIX94301315979 ] p 515 A94-60015 p 525 N94-34977 Vane.blade interaction in a transonic turbine. Part 1: NUCLEAR ENERGY PANELS Aerodynamics JPRS report: Science and technology. Central Eurasia Field deployable nondestructive impact damage {BTN-94-EIX94321333305J p 516 A94-60037 {JPRS.UST.94-005] p 553 N94-35342 assessmenl methodology for composite structures Navmr-Stokes SOlver for hyperSOnic flow over a slender NUCLEAR EXPLOSIONS IBTN-94-EIX94301321378J p 546 Ag4-60892 cone Feasibility study of a contained pulsed nuclear propulsion Frequency domain analysis of the random loading of [BTN-94-EIX94311330681 J p 543 A94-60110 engine cracked panels Applications of computational fluid dynamics to the [BTN.94.EIX943413383691 p 559 A94-60361 INASA.CR-196021J p 556 N94.35974 aerodynamics of Army projectiles NUCLEAR MAGNETIC RESONANCE PARALLEL PROCESSING (COMPUTERS) [BTN-94-EIX943113306781 p 516 A94-60113 Runtime support for data parallel tasks Measurement of diffusion in fluid systems: Applications {NASA-CR-194904] p 558 N94.35240 Combmed LAURA.UPS solution procedure for to the suparcntiual fluid regJo_ PARTIAL DIFFERENTIAL EQUATIONS chemically-reacting flows JSTN-94-EIX94311330660) p 548 A94-60t31 INASA-TM-107964} p 551 N94-34721 Aneiys_s o1 wavelet technology for NASA applications NUCLEAR PROPULSION [NASA-CR-195929J p 522 N94.34704 Charactanzet_n of dynarmc stall phenomenon using Feasibitity study of a contained pulsed nuclear propulsion PARTICLE IMAGE VELOClMETRY two-dimensional unsteady Nevler-Stokes equations art_ne Unsteady flow past an airfoil pitched et constant rate p 524 N94-34974 JBTN-94-EIX94341338369] p 559 A94-60361 p 524 N94-34969 Computation of unsteady flows over a_oils NUCLEATE BOILING Dets reductK)n procedures for laser velocimeter p 525 N94-34977 Conjugate conduction.convection heat transfer with • measurements in turbomachine_ rotors Departure solutions of the unsteady thin-layer and full high-lkneed boundary layer [ NASA.CR- 195343 J p552 N94.35224 Newer-Stokes equations solved using streamline curvature J BTN-94-EIX943113306521 p549 A94-60139 PASSENGER AIRCRAFT based iteration techn_ues p 552 N94-34980 NUMERICAL ANALYSIS A review of computer evacuation models and their data A three dimensional multigrid Reynolds-averaged needs Navmar-Stokes solver for unstructured meshes Analysis of wavelet technology for NASA applications [ NASA-CR-195929] p522 N94-34704 |DOT/FAAIAM.94111] p 528 N94-35236 INASA-CR-1949081 p 528 N94-35994 PASSENGERS NEAR WAKES NUMERICAL CONTROL Future ultra-speed tube-flight p 555 N94-35918 Bourldary.leyer influences on the subso_c near-wake Computational methods 1or HSCT-mlet contnNs/CFD PENETRATION of bluff bodms interdtscipiinary research Structure and peneUation of a soparcntm..al fluid jet in [NASA-TM-106618J p 539 N94-35352 IBTN-94-EIX94311329138] p 517 A94-60162 superso_c flow NEURAL NETS NUMERICAL FLOW VISUALIZATION [BTN-94-EIX943213333t7] p 549 A94-60268 Artificial neural networks for predicting nonlinear Charsctartzabon of dynamic stall phenomenon using PERFORMANCE PREDICTION dynamic heiicoptar loads two-dmlenslonal unsteady Nawar-Stokes equations Axial compressor performance dunng surge [BTN-94-EIX94301315989] p 515 A94-60025 p 524 N94-34974 IBTN-94-EIX94321333308 ] p 548 A94-60040 A combined approach to buffet response analyses end PERFORMANCE TESTS tatigue life prediction p 551 N94-34587 Techniques for aerodynamic characterization an0 NOISE PREDICTION (AIRCRAFT) O performance evaluation et high angle of attack Engine exhaust charectenstios evaluation in support of p 533 N94-34614 errcratl acoustic tesbng p 560 N94-35963 OgJECT-ORIENTED PROGRAMMING PILOT ERROR NOISE PROPAGATION Ads developers' supplement to the recommended Safety study: A revmw of thghtcrew.involved, major Computation of helicopter rotor acoustics in forward approach accidents of US air cernars, 1978 through 1990 flight [ NASA-CR-189345J p557 N94-34921 [ PB94-917001 } p 529 N94-35482 INASA-CR-196132] p 560 N94-36031 O6LIOUE SHOCK WAVES Aircraft accident report: Uncontrolled collision with terrain, American International Airways Flight 808, Douglas NOISE REDUCTION Experimental studma of transplrstio¢_ co(ding with shock DC-8-61, N814CK, US Naval Air Station, Guantanamo Bay, Low.noise, high-strength, spiral-bevel gears for interection in I_ flow, part B Cuba, 18 August 1993 helicopter transmissions I NASA-CR-lg5958 ] p523 N94-34965 JPB94-910406] p 529 N94-35521 [BTN-94-EIX943213333121 p 548 A94-60044 inveatigation of Bumett equebona for two-drmans_nai PILOT PERFORMANCE NONDESTRUCTIVE TESTS h_ic flow Effects of checklist interface on non-verbal crew [AD-A278942] p 527 N94-35717 Field deployable nondestructive rrnpact damage commumcations assessment methodology for composite structmes A superso_c tunnel for laser and flow-seeding INASA-CR-177639| p 525 N94-34915 techniques [BTN-94-EIX94301321378] p 546 A94-60892 Safety study: A review of ftightcrew-involved, major NONEQUIMBRIUM CONDITIONS [NASA-TM-106588] p 556 Ng4-35945 accidents of US air cen'mrs, 1978 through 1990 Computabon of nonequilibnum hypersonic flowlields OBSTACLE AVOIDANCE [PB94-917001 ] p 529 N94-35482 around hemlspt'mre cylinders Accurate estimation of object location in an image A_n_nlft accident report: Uncontrolled collision with [BTN-94-EIX94351142135] p 521 A94-60426 sequ6nce using hehcopter flight data torrain, American International Ah'ways Fkght 808, Douglas NONEQUILIBRIUM FLOW p 537 N94-35055 DC-8-61, N814CK, US Naval Air Station, Guantaname Bey, Coul_ed radletmn effects in thermochemmal ON-MNE 8YtR'EM$ Cuba, 18 August 1993 nor,equilibrium shock-captunng flowfleld calculations Vista goes on_ine: Deci_.enalytio systems for real-time {P694-910406| p 529 N94.35521 [ BTN-94-EIX94311330648 ] p559 A94-60143 decision-maktng in mission control p 558 N94-35063 PILOT TRAINING Development and application of computational OPERATING Oprlrational agilityassessment with the AM-X aircraft aerothermodynamrs flowfieid computer codes Future ultra-speed tube-flight p 555 N94.35918 p 534 N94.34626 INASA-CR-t96136J p 526 N94-35498 OPERATIONS RESEARCH PISTON ENGINES NONEQUIUBRIUM RADIATION Nelionai facilities study. Volume 3; Mlemon and UNeadeO AVGAS program COUpled radmtlon effects in thermochemicai requirements model report [AD'A2786501 p 547 N94-35795 nonequi_ibrium shock-captunng flow/told calculebons INASA-TM-109857] p 542 N94-34635 PITCH (INCLINATION) J BTN-9,I-EIX94311330648 J p559 A94-60143 National facilities study. Volume 4: Space operations Comparison of pitch rate history effects on dynamic NONINTRUSIVE MEASUREMENT facilities task _'oup stall p 535 N94-34968 Effect of i_tial accelerabon on the development of the Surface interference in Raylaigh scattarmg [NASA-TM-109658] p 542 N94-34636 flow field of an airfoit pitching it constant rate meesuremartts near forebodies Netlo¢_l fadlitws study. Volume 5: Space research end p 526 N94-34989 [STN.94.EIX94301315999] p 516 A94-60035 clot facNities task group Data reduction, analysis and results of LACV-30-07 air NONLINEAR SYSTEMS [NASA-TM-109859] p 542 N94.34637 OPTICAL MF.AII'_REMENT cushion vehicle tests, Fort Story. VA, August - September Techniques for aerodynamic characterization and 1993 performance evaluation at high angle of attack Comparison of optical measurement tachniques for [AD-A278859] p 527 N94-35826 p 533 N94.34614 tuYoomachinery flowfle_de PITCHING MOMENTS NORMAL SHOCK WAVES I BTN-94-ElXg434t338357) p 559 A94-60349 Effects of thrust line offset on neutral point detarminatmn A suparsor_c tunnel for laser and flow-lmedmg OFqlMAL CONTROL *nf_ tas_n_ tecflniquea Magnetically suspended stepping mo4or'l for clean room [ STN-94-EIX94311329127 ] p518 A94-60173 [NASA.TM-106688] p 556 N94-35945 and vacuum environments p 555 N94-359t5 An examination of the amodynemio moment on rotor NORTH ATLANTIC TREATY ORGANIZATION (NATO) ORBIT CALCULATION btade t_ using flight test data end anah/ais AGARD highlights 93/2 Flight Mednlnk:slEstimebon Theory Sympomum, 1994 [NASA-TM-t04006] p 523 N94-34948 [AGARD-HIGHLIGHTS-93/2] p 561 N94-35444 [ NASA-CP.3265J p 545 N94.35605 Comparison of pitch rate history effects on dynamic NOWCASTING OSCILLATIONS stall p 535 N94.34968 Data requirements for ceiling end visibility products Techniques for aerodynamic characterization and The unsteady pressure field end vortioity productiion at development pedow_ance evaluation at high angle ol attack the suction surface of a pitching airfoil lAD-A278959] p 556 N94-35720 p 533 N94.34614 p 524 N94-34972 A-14 SUBJECT INDEX RESEARCH AIRCRAFT PLATES (STRUCTURAL MEMBERS) PRESSURE MEASUREMENT R Analys,s of muflifastener composite joints Pressure measurements on a forward-swept I BTN-94-EIX94311330690 J p548 A94-60101 wig-canard configuration RADAR DETECTION Shear buckling response of tailored composite plates (BTN-94-EIX94311329149} p 516 A94-60151 Terminal Doppler Weather Radar (TDWR) Low Level IBTN-94-EIX94301316000] p 549 A94-60256 Flow quality studies of the NASA Lewis Research Center Wind Shear Alert System 3 (LLWAS 3) ,ntegration studies Design oriented structural analysis Icing Research Tunnel at Orlando International Airport INASA-TM-1091241 p 551 N94-34722 INASA-TM.106545J p 543 N94.34919 lAD-A278957] p 557 N94-35807 POROSITY Flight testing of a luminescent surface pressure RADAR RECEIVERS sensor Allevsation of s=de force on tangent-ogive forebixlles An analysis of operational suitability for test end using passive porosdy I NASA-TM-103970] p522 N94-35394 evaluation of mghly reliable systems PRESSURE RATIO I BTN-94-EIX94311329126 } p536 A94-60174 lAD-A278573] p 530 Ng4-36184 POROUS MATERIALS Computation and discus,_on of a nearly constant degree RADARSCOPES of reaction lud_ne stage Alleviation of side force on tangent.ogive forebodies Final-Approach Spacing Aids (FASA) evaluation for [ BTN-94.EIX94351144987 ] p 537 A94-60449 using passNe porosity mrmioal-area, t_ne-based air traft=c control PRESSURE SENSORS IBTN-94-EIX94311329126J p 536 A94-60174 [NASA-TP-3399] p 529 N94.36048 FltJht testing of a luminescent surface pressure RADIAT.ION EFFECTS POSITION (LOCATION) sensor Localization of aeroelastic modes in mistuned Coupled radmtion effects in _hen',cel INASA.TM.103970J p 522 N94-35394 mgh-energy turbines PRESSURE VESSELS nor'_q_liOnum shock-captunng flow6eld calculations IBTN-94-EIX94321333307} p 547 A94-60039 [BTN-94-EIX94311330648] p 559 A94-60143 Feasibility study of a contained pulsed nuclear propulsion POSITION SENSING RADIO ALTIMETERS engine Integration o! magnetic bearings in the design of [BTN-94-EIX94341338369] p 559 A94-60361 Minimum performance standards: Airborne low-range advanced gas turbine eng,nes p 554 N94-35903 PROBABILITY THEORY radar altimeters [RTCA-DO-155J p 537 N94-35344 POSITIONING Assessment of lo-serwce mrcrafl fatigue monitoring Aircrah landing gear positioning concerning abnormal process p 531 N94-34593 RADIO EOUIPMENT landing cases PROCUREMENT MANAGEMENT Minimum performance standards: Airborne low-range {BTN.94.EIX94311329140] p 536 A94-60160 Budget estimates, fiscal year 1995 Volume 1: Agency redar altimeters Design and analysis of a Kalman filter for summary, human space fkght, end soence, aeronautms [RTCA.DO-155] p 537 N94-35344 terrain-referenced positioning and guidance and technology RAIL TRANSPORTATION {BTN-94-EIX943113291241 p 557 A94-60176 [NASA-TM-1097911 p 560 N94-35899 Control of mauler vehicles with eerodynarmc and Magneticelty suspended step_ng motors for clean room PROGRAM VERIFICATION (COMPUTERS) guidewey disturbances p 554 N94-35842 and vacuum envkonmonts p 555 N94-35915 F.16 uncommande¢l pitch osoliation RAMAN SPECTRA POTENTIAL THEORY IBTN-94-EIX94331337501) p 530 A94-60336 Raman measurements at the exit of a combustor PROJECT MANAGEMENT Precision requirement for potential.based panel sector methods Netionel tacilibes study Volume 2A: Facdity Study Office (BTN-94-EIX943413383561 p 546 A94-60348 IBTN-94-EIX94301315995) p 515 A94-60031 on the National Wind Tunnel Complex RAMJET ENGINES PRECISION INASA-TM-109856] p 542 N94-34634 Comt)usbon performance of dump combustor m ramjet PROJECT PLANNING Preci._on requirement for potential-based panel entj_ne using liqu4d hydrogen fuel methods Cost and schedule esbmation study repod [ BTN-94-EIX94351144992 ] p538 A94-60454 [NASA-CR.189344] p 558 N94-35256 [BTN-94-EIX94301315995] p 515 A94-60031 RANDOM LOADS PROJECTILES PREDICTION ANALYSIS TECHNIQUES Frequency domain anelysis of the random loading of Applw.atione of computafionel fluid dynamics 1o the Artit,cial neural networks for predicting nonlinear cracked panels dynamic helicopter loads aerodynamics of Army proiectiles [NASA-CR-196021 ] p 556 N94-35974 [BTN-94-EIX943113306781 p 516 A94-60113 IBTN-94-EIX94301315989] p 515 A94-60025 RAYLEiGN SCATTERING S_mplified method for evaluating the flight stability of Axial compressor performance during surge Surfece interferertce in Reyleigh scattering I_d-fitled protectiles IBTN-94-EIX94321333308] p 548 A94-60040 measurements near forebodms | BTN-94-EIX94311322905] p544 A94-60191 Navler.Stokes solver for hypersonic flow over a slender [BTN-94-EIX94301315999] p 516 A94-60035 cone Drag reduction for turbulent flow over • proffmtile, part REACTING FLOW 2 [BTN-94-EIX94311330681 ) p 543 A94-60110 New two-temperatore dissociation model for reacting [STN-94-EIX94311322900] p 520 A94-60196 flows Measurement end pred_cbon of dynarmc temperatures Drag reduc0on of turboient flow over • proijecfile, part in unsymmetrically cooled glass widows IBTN-94-EIX9435t142137] p 560 A94-60430 1 [BTN-94-EIX94351142128] p 550 A94-60421 Combined LAURA-UPS sofubon procedure for [BTN-g4-EIX94311322899] p 557 A94-60197 chem_.AMly-reacting flows An Assessment of Fat_gee Damage and Crack Growlh PROP.FAN TECHNOLOGY Prediction Techniques [NASA-TM-1079641 p 551 N94-34721 Experimental mvesfigetlo_ of counter-rotating propfen REAL GASES IAGARD-R-797] p 550 N94.34581 flutter at cruise condibons Calculefion of real-ges effects on aalorl aerodynamic An assessment of fatigue crack growth prediction [BTN-94-EIX94321333310] p 516 A94-60042 models for aecospace structures p 551 N94-34586 cheracteitsbcs PROPELLANT COMBUSTION {BTN-94.EIX94351142143] p 521 A94-60436 A combined approach to buffet response analyses and Preliminary invest_gabons On m_rowng air-augmented REAL TIME OPERATION tatKJue life prediction p 551 N94-34587 rocket performance PREMIXlNG Vista goes online: Decm_on-anaiy',Jc systems for real.time [BTNo94-EIX94321333323] p 544 A94-60274 decia*on-meking in miss_n control p 558 N94-35063 Turbulent combustion regimes for hypersorNc proIo_SKz, n Turbulent combustion re,rhea for _nic Wopulmon REAI"TACHED FLOW employing hydrogen-air diffumon flames employmg hydroge_mr diffusion flames Reattachmont studies of en oscdleting eirloil dynamic [BTN-94-EIX94321333324J p 546 A94-60275 [BTN.94-EIX94321333324] p 546 A94-60275 stall fiowfleld PRESSURE DISTRIBUTION PROPIELLER FANS IBTN.94.EIX94301315980] p 515 A94-60016 Determination of fire-wheel interface loads for aircraft Ex_mentel investigation of counter*rotating prof)len RECTANGULAR WINGS wheels flutter at cruree cond_or_ Tail load celcuiations for light airp4enes I BTN-94-EIX94311329136 ] p517 A94-60164 [BTN.94.EIX94321333310] p 516 A94-6(X)42 IBTN-94-EIX943t1329148] p 517 A94-60152 Control of leading-edge separation Do a cambered deita PROPELLERS REENTRY wig p 539 N94-34616 Effects of prop_ler on the turning of old fighters Charlctar_tics of the Shuttle Orbiter leeside flow du_ng Combmed LAURA-UPS solution procedure for [ BTN-94-EIX94361135426 ] p537 A94-60623 • re-entry condition chermcally*reecting flows PROPULSION |BTN-94-EIX94311322888] p 520 A94-60208 INASA-TM-107964] p 551 N94-34721 AFOSR Contractors Propulsion Meeting HL-20 cornputabonal fluid dynamms analysis The unsteady pressure field and vorticity productiion at [AD-A279028] p 539 N94.35746 IBTN-94-EIX94351137059 ] p 545 A94-60399 the suction sucface of a I:_tching airfoil REENTRY GUIDANCE PROP_LBION SYSTEM CONFIGURATIONS p 524 N94-34972 Propol=K:*'_-inducod eerodyoam¢ effects measured with S_x-Oegree-of-freedom guidance end control-entry Mechamsms of flow control with the unsteady btaed a full-scale STOVL model enelysis of the HL-20 techmque p 525 N94-34987 [STN.94-EIX94351137056) p 544 A94-60396 [BTN.94.EIX94311329120] p 519 A94-601B0 A supersonic tunnel for laser end flow-seeding REENTRY SHIELDING PROPULSION SYSTEM PERFORMANCE techn_ues Aerodynemlc heating environment definition/thermal PreliminaP/ investlgabons on improving elf-augmented I NASA-TM-t 06588 ] p 556 N94-35945 protection system selection for the HL-20 rocket performance Expansion effects on supersonic turb_ent boundary [BTN-9.4-EIX94351137058] p 544 A94-60398 layers [BTN.94.EIX94321333323] p 544 A94-60274 REFRACTORY COATINGS I AD-A278989] p 527 N94-35950 USAFIAEDC aemdynam*c and propolmon ground test COmpOsde matrix experimental combustor PRESSURE DRAG and eveluafion tachmques for highly manmNerable aircraft: [NASA-CR-194446) p 538 N94-34679 Nurnermil investigation of cylinder wake flow with a rear Capabilities and chellengea p 532 N94-34606 REUABIUTY ANALYSIS stagnation jet Engme charactanefics for =gile airorafl Airoreft fleet maintenance based on structural reliability [BTN-94-EIX94301315998] p 547 A94-60034 p 538 N94-34608 analyais PRESSURE GRADIENTS [BTN-94-EIX94311329134] p 517 A94-60166 Structure of local preseure-driven three-dimensionel REMOTELY PILOTED VENICUES transient boundary-leyer soparation Q _ter w_g dee_n [BTN-94-EIX943013159791 p 515 A94-60015 [BTN-94-EIX94331337499] p 521 A94-60334 Computation and d_scusmon of a nearly constant degree QUATERNIONS RESEARCH AIRCRAFT of reaction turbine stage Modelling and control of a rotor supported by magnetic Ground vibration test of the XV-15 Tiitrotor Research I BTN-94-EIX943511449871 p 537 A94-60449 beenngs p 554 N94-35858 Aircraft and pretest predictions p 541 N94-35972 A-15 RESEARCH AND DEVELOPMENT SUBJECT INDEX RESEARCH AND DEVELOPMENT ROLLING MOMENTS S National facilibes study Volume 2: Task group on Forebody vortex control for wing rock suppression aeronautical research and development facilities report IBTN-94-EIX94311329119] p 530 A94*6018t SAFETY MANAGEMENT INASA-TM-109555] p 542 N94-34633 Effects of the roll angle on cruciform wing-body Aerospace Safety Advisory Panel National facilities study. Volume 3: Miss=on and configurations at high incidences [NASA.TM-109840J p 545 N94-35390 requ=rements model reporl I BTN-94-EIX94311322903 } p520 A94-60193 SATELLITE ORIENTATION Flight Mechanics/Estimation Theory Symposium, 1994 [NASA.TM.109857) p 542 Ng4.34635 Yaw control by tangential forebody biowmg INASA-CP'32651 p 545 N94.35605 National facilities study. Volume 4: Space operations p 539 N94-34615 facihties task group SATELLITE TRACKING ROTARY WING AIRCRAFT INASA-TM-f09858] p 542 Ng4-34636 Flight Mechanics/Estimation Theory Symposium, 1994 Rotorcraft fatigue lite-pred.iction: Past, present, and National facilitms study. Volume 5: Space research end J NASA-CP-3265 | p 545 N94-35605 future p 551 N94-34590 development facilities task group SCALE MODELS ROTARY WINGS l NASA-TM-109859 J p 542 N94-34637 Yaw control by tangential torebody blowing An examination of the aerodynamic moment on rotor NASA/DOD Aerospace Knowledge Diffusion Research p 539 N94-34615 blade tips usmg flight test data and analysis Project Paper 42: An analysis of the transfer of Scientific SCHEDUUNG |NASA-TM.104006J p 523 N94.34948 and TechnK:al Inlormation (STI) in the US aerospace Scheduled maintenance optirr.zalton system industry Unsteady separation experiments on 2-D airfoils, 3-D [ BTN*94-EIX94311329145 ] p517 A94-60155 I NASA-TM-t 09863 ) p 560 N94-34730 wings, end model helicopter rotors p 524 N94.34967 Cost and schedule estimation study report The Federal Avmtion Administration plan for research. Prediction of unsteady aidoll flows st large angles of INASA-CR-1893441 p 555 N94-35256 engmeenng and development p 561 N94.35262 incidence p 525 N94.34978 SCHLIEREN PHOTOGRAPHY JPRS report: Science and technology. Central Eurasia Departure SOlUIK)ns of the unsteady thin-layer and full A supersonic tunnel for laser and flow.seeding IJPRS-UST-94-0051 p 553 N94-35342 Navlar-Stokes equations solved usmg slreamlme curvature techmques D_rector's discretions W fund based iteration technioues p 552 N94-34980 INASA-TM-106588] p 556 N94-35945 INASA-TM-103997J p 561 N94-35370 The quest for stall-free dynamic lift SCIENTISTS JPRS report: Science and technology. Central Eoras_a p 525 N94-34986 NASA/DOD Aerospace Knowledge Diffusion Research Pro_ct. Paper 42: An anelys_s of the transfer of Sc_enMic IJPRS-UST-94-0t01 p 553 N94-35385 Selected topics on the active control of helicopter and Technical InformatK)n (STI) in the US aerospace JPRS report: Sc*ence and technology. Central E_asia aeromechanical and vibration problems industry I JPRS-UST-94-012J p 553 N94-35387 p 541 N94-35874 AGARD h_lhkghts 93/2 [NASA-TM-109863J p 560 N94-34730 Computation of helicopter rotor acoustics in forward IAGARD-HIGHLIGHTS-g3/2] p 561 N94-35444 SEALS (STOPPERS) flight Challenging the Future - Journey to Excellence. Rotor dynarmc behaviour of e high-speed oil-free motor INASA-CR-196132] p 560 N94-36031 Aeropropulsion strategic plan for the 1990's compresso¢ with 8 ngid coupling supported on four radial ROTATING FLUIDS I NASA.TM.t 09250| p545 N94-35591 magnetic beam'bgs p 555 N94-35911 Axial compressor performance during sucge Budget esbmates, fiscal year 1995, Volume 1: Agency SECONDARY FLOW [ BTN-94-EIX94321333308 | p 548 A94-60040 summary, human space flight, and scmnce, aeronautics Computalion and discussion of a nearly constant degree ROTATING SHAFTS and technology of reaction turbne stage I NASA-TM-109791 _ p560 N94-35899 Planer rotational magnetic m_cromotors with integrated I BTN-94-EIX94351t44987] p 537 A94-60449 Research and technology, 1993 shaft encoder and magnetic rotor levitation The aerodynamic and heat transfer effects of an endwell NASA-TM-1088161 p 561 N94-36117 p 555 N94-35907 boundary layer lance in a 90 degree turning square duct RESEARCH FACILITIES ROTATING STALLS lAD-A278903 ] p 553 N94-35503 National tacilitms study. Volume 1: Facilities inventory Axial compressor performance dunng surge SEPARATED FLOW NASA-TM-109854 J p 54t N94.34632 [BTN-94-EIX94321333308 ] p 548 A94-60040 Crossflow topology of vortm81 flows National facilities study Volume 2: Task group on ROTATION |BTN-94-EIX94301315993] p 515 A94-60029 aeronautical research and development taolibes report Modelling and control of a rotor supportad by magnetic Effects of the roll angle on cruciform wing-body NASA-TM-109555] p 542 N94-34633 bearings p 554 N94.35858 configurabons st high incidences National facilities study Volume 3: Mis.._on end ROTOR AERODYNAMICS J BTN-94-EIX94311322903 | p 520 A94-60193 requirements model reporl Three-dimensional closure of the passage-.avorsged Control of laaolng-edge separabo_ on s cambered delta rNASA-TM-t09557] p 542 N94-34635 vort_-potenbal formulation wing p 539 N94-34616 National facilities study Volume 4: Space operations [STN.94.EIX94301315991] p 547 A94-60027 Physcs of Forced Unsteady Separation facihties task group An exsminetion of the 8erodyrmmic moment on rotor [NASA-CP-3144| p 552 N94-34966 NASA-TM-1098581 p542 N94-34636 b_ade tips u=ng flight test data and analysis Unsteady separation expenments on 2-D 8idoits, 3-D Nabonal facihties study. Volume 5: Space research and [NASA.TM-104006] p 523 N94-34948 tWngs, and model helicopter rotors p 524 N94.34967 development facilities task group Ground vibration test of the XV-15 Tiitrotor Research Comparison of pitch rate history effects on dynamic NASA-TM-109859} p 542 N94-34637 Aircraft and pretest predictions p 541 N94-35972 stall p 535 N94-34968 RESEARCH MANAGEMENT Computation of helicopter rotor acoustics in forward Unsteady flow past an aidoil pitched at constant rate National tacilitms study. Volume 5: Space research and flight p 524 Ng4-34969 development facititms task group [NASA-CR-196132] p 560 N94-36031 Unsteady separation process and vorticity balance on INASA-TM-109559) p 542 N94.34637 ROTOR DYNAMICS unsteB:ly lwfoiis p 524 N94-34970 The Federal Aviation Administration plan for research, Rotor dynamic behawour of a high-speed old-free motor The unstse_y pressure field sad vort_ty gropucti_on at engineenng and development p 561 N94.35262 compcessor with a rigid coupling supporled on four radial the suction surface Of 8 pitching sirfoll RESEARCH PROJECTS magnetic bearings p 555 N94.35911 p 524 N94-34972 Director's dmcrebonary lund ROTOR LIFT Characterization of dynamic stall phenomenon using [NASA-TM-1039971 p 561 N94-35370 The quest for stall-fi'ee dynamic lift two-dtmons.,onal unsteady Nsvier-Stokes equations RESONANT FREQUENCIES p 525 N94-34986 p 524 N94-34974 Rotor dynamic behawour of a h*gh-speeO oil-free motor ROTORS Will the real dynam*c inetaollity mechanism please be combreseor w;th s rig_l coupling supporled on tour radial Three-dimene_onal closure of the pase=ge-avaraged recognized! p 552 N94-34976 magnebc beanngs p555 N94-35911 vorlicity-potentlal formulation SERVICE UFE RETIREMENT FOR CAUSE [ BTN-94-EIX94301315991 ] p547 A94-60027 The role of fatigue analysis for design of military Artificial neural networks for predicting nonlinear Data reduction procedures for laser velocimotar aircraft p 531 N94-34594 dynamK: helcopter toe(Is measurements in turbomachinary rotors An oven_ew of the F.16 servics life approach {BTN-94-EIX9430131598g] p 515 A94-60025 [NASA-CR-195343] p 552 N94-352.24 p 532 N94-34599 RIDING QUAUTY Influence of backup beanngs and support structure SHADOWGRAPH PHOTOGRAPHY Control of maglev vehicles with aerodynamic and dynamics on the behavior of rotors with sctNe supports Sb'ucture and penetration of a supercritical fluid jet in g*.Bleway disturbances p 554 N94.35842 (NASA-CR-196119] p 553 N94-35500 _erson,c _ow RISK Design, consfruchon, and testing of a five active axes [BTN.94.EIX94321333317] p 549 A94-60268 Risk anelys_s of the C-141 WS405 inner-to.outer w_ng magnetic bearing system p 554 N94-35846 SHAFTS (MACHINE ELEMENTS) jomt p 531 N94.34592 Third order LPF type compensator for flexible rotor Rotor dynamic behaviour of a high-s_eed oil-free motor ROCKET ENGINES suspenmon p 554 N94-35863 compressor with S rigid coupling supporled on tour radial Locahzabon of aeroelastic modes in mlatuned Electromechanical simulation end test o! rotating mlgnet_ b_lulngs p 555 N94-355t 1 high-energy turbines systems with magnate be_ or piezoelectric _tuator SHEAR LAYERS JBTN-94-EIX94321333307 ] p 547 A94-60039 active vibration control p 555 N94.35905 Control of leaoing-edge vortices o_ a delta wing Prelirmnary invostigabons on imwoving air-su_mentad Plarmr rotatM_nel magnetic micromotors with integrated p 524 N94.34971 rocket performance shaft encoder and magnetic rotor levi_tion Characterization of dynamic stall phenomenon usmg I BTN-94-EIX94321333323 ] p 544 A94-60274 p 555 N94-35907 twc-dimens_nel unsteady Newer.Stokes equations ROCKET NOZZLES Rotor dynamic behaviour of a high-speed oil-free motor p 524 N94-34974 Pre_irmnary mvesbgat)ons on improwng ei¢-sugmentad corn_xeseor with a rigid coupling supportad on four SHEAR STRENGTH rocket performance magne_c bearings p 555 N94-35g11 Shear buckling response of tailored _e plates i BTN-94-EIX94321333323] p 544 A94-60274 Magnetically suspended steppgng motors for clean room [BTN-94-EIX9430t316000] p 549 A94-60256 ROLL and vacuum environments p 555 N94-35915 SHEAR STRESS Study findings on the influence of maneuvar_ih'y and RUN TIME (COMPUTERS) Active thermal isolation for temperature responsive Sgddy on heticopter handling qualities Runtime supporl for data parallel tasks imnsors p 533 N94-34624 |NASA-CR-194904| p 558 N94-35240 JNASA-CASE.LAR.14612.1} p 552 N94-35074 Data reduction, analysis and results of LACV.30-07 air RUNGE-KU'I_A METHOD SHOCK TUNNELS cushion vehicle tests, Fort Story, VA. August - Septemt_r Verm-blacle interaction in a transonic turbine. Part 1: Combustion shock tunnel and interface compression lo 1993 Aerodynamics increase reservoir pressure and enthalpy JAD-A278859 J p 527 N94-35826 IBTN-94-EIX94321333305) p 516 A94-60037 IBTN-94-EIX94311330650} p 516 A94-60141 A-16 SUBJECT INDEX STRUCTURAL DESIGN SHOCK WAVE INTERACTION SPACE SHUTTLES STATIC STABILITY Experimental studies of shock-wave/wall-let interaction Aerodynamic characteristics of the HL-20 Static and dynamic flight-path stability of airplanes in hypersonic flow, part A IBTN-94-EIX94351137055 J p 544 A94-60395 IBTN-94-EIX9436113,5428 ] p 522 A94-60625 I NASA-CR-T95957] p 523 N94-34964 Six-degree-of-freedom guidance and control-entry STATIC TESTS Experimental stud=as of transpiration cooling with shock analysis of the HL-20 Approximate similarity prlnc=ple for a full-scale STOVL interaction in hypersonic flow, part B l BTN.94.EIX943511370561 p 544 A94-60396 elector INASA-CR-t95958} p 523 N94-34965 Effect of lift-to-drag ratio in pilot rating of the HL-20 [BTN-94-EIX9434t338360] p 550 A94-60352 Investigation of Burnett equations for two-dimensional landing task STATORS hypersonic flow IBTN-94.EIX94351137057J p 544 A94-60397 Three-dimens_onal closure of the passage-averaged IAD-A278942J p 527 N94-35717 Aerodynamic heating environment definition/thermal vocticity-potential formulation SHOCK WAVES protection system selection for the HL-20 IBTN-94-EIX94301315991 I p 547 A94-6(_27 Expenmental studies of shock-wave/wall.jet interaction I BTN-94-EIX9435t 137058 ] p 544 A94-60398 STEPPING MOTORS HL-20 computational fluid dynamics analysis in hypersonic flow, part A Magnetically suspended stepping motors for clean room [BTN-94-EIX94351137059] p 545 A94-60399 (NASA-CR-1959571 p 523 N94-34964 and vacuum enwronments p 555 N94-35915 SHORT TAKEOFF AIRCRAFT Preliminary structural evaluation and design of the HL-20 STIFFNESS Results from the STOL and Maneuver Technology Time simuistion of flutter with large stiffness changes Demonstration program p 532 N94-3461 t {BTN-94-EIX94351137060] p 545 A94-60400 Human factors evaluation of the HL-20 full-scale IBTN-94-EIX94311329132) p 518 A94-60168 Direct reduced order mixed H2/H infinity control tot the model STOCHASTIC PROCESSES Short Take-Off and Landing/Maneuver Technology |BTN-94-EIX943511370651 p 545 A94-60405 Localization of aeroetastic modes in mistuned Demonstrator (STOL/MTD) Measurement and brechction of dynamic temperatures h_gh-energy turbines I AD-A278675] p 540 N94.35796 in unsyrnmethcally cooled glass windews [BTN-94-EIX94321333307J p 547 A94-60039 SHROUDS IBTN-94-EIX94351142128] p 550 A94-60421 STORAGE STABILITY Computabon and d_scuss_on of a needy constant degree Aerospace Safety AdvisoP/Panel Unleaded AVGAS program of reaction tucbrne stage INASA-TM-109840] p 545 N94-35390 [AD-A278650] p 547 N94-35795 IBTN-94-EIX9435tt44987J p 537 A94-60449 SPACE STATION FREEDOM STOVL AIRCRAFT SlDESUP Aerospace Safety Ao'vmory Panel YAV-aB reacbon control system bleed and control power Wind tunnel measurements on a full-scale F/A-18 wdh (NASA-TM-1098401 p 545 N94-35390 usage in hover and transition a tangentially olowing slot -- conducted in the Ames 80 SPACECRAFT CABINS I NASA-TM-104021 J p 540 N94-34994 by 120 foot wind tunnel p 527 N94.35965 Human factors evaluation of the HL-20 full-scale STRAIN DISTRIBUTION SILVER ALLOYS model Notch fatigue assessment of aircraft components using Retained mechanm.al properties of a new AI-Li-Cu-Mg-Ag [ BTN-94-EIX94351137065 ] p545 A94-60405 a fracture mecharNcs based parameter alloy as • function of thermal exposure time end SPACECRAFT COMPONENTS p 551 N94.34588 temperature Aerospace applications of magnetic beenngs STRAIN MEASUREMENT IBTN-94-EIX94301320164J p 546 A94-60873 p 554 N94-35837 Notch fatigue assessment of aircraft components using SITE SELECTION SPACECRAFT CONSTRUCTION MATERIALS a fracture mechan*cs based parameter Nabonal facilities study Volume 2A: Facility Study Office Measuren'mnt and prediction of (_ttmamic temperatures p 551 N94.34588 on the National Wind Tunnel Complex in uosymmetncally cooled glass windows STRAKES [NASA-TM-109856] p 542 N94-34634 ( BTN-94-EIX94351142128 ] p550 A94-60421 F/A-18 forebody vortex control Volume 1: Static tests SKIN FRICTION SPACECRAFT CONTROL [NASA-CR-4582J p 528 N94-35991 Active thermal isolation for temperature respcnsNe Vista goes online: Docis=on-anelytic systems for reel-time STRATIFIED FLOW sensors decismn-making in mission control p 558 N94-35063 JPRS report: Science and technology_ Central Eurasia [NASA-CASE-LAR.14612-1] p 552 N94-35074 SPACECRAFT DESIGN [JPRS-UST.94-006) p 553 N94-35226 SLENDER BOglES I:_'el_mmery structural evaluation and design of the STRESS ANALYSIS Determination of slender body aerodynamics using HL-20 Analysis of muttifestener composite joints discrete vortex methods IBTN-94-EIX94351137060} p 545 A94-60400 {BTN-94-EIX94311330690] p 545 A94-60101 [ BTN-94-EIX94311330679 ] p543 A94-60112 SPACECRAFT MODELS An Assessment of Fatigue Damage and Crack Growth SLENDER CONES Human lectors evaluation of the HL.20 full-acale Predicbon Techr_lues Symmetry breaking in vortical flows over cones: Theory model [AGARD-R-797J p 550 N94-34581 and numermal expenments ( BTN-94-EIX94351137065 ] p545 A94-60405 Fatigue management and verifioabon of airframes [BTN-94-EIX94301315981] p 547 A94-60017 SPACECRAFT REENTRY p 53t N94-34591 Nevier.Stokes solver for hypersonic flow over • siend_ _l'lRrr.s_ CORROSION CRACKING cone Charectenstcs of the Shutde Od_ter _ flow dur_ a rHntry condition Effect of coarse second phase barbcles on fatigue crack [BTN-94-EIX94311330681] p 543 A94-60110 propagation of an AI-Zn-Mg-Cu alloy SLOTS [ BTN-94-EIX94311322888 ] p 520 A94.60208 {BTN-94-EIX94301320144J p 546 A94-60853 Six-de_ee.of-freedom guidance end control-entry Mechanisms of flow control with the ur_teedy bleed STRESS INTENSITY FACTORS technique p 525 N94.34987 analysis of tile HL-20 Frequency domain analysis of the random loading of SOCIOLOGY (BTN-94-EIX94351137056 ] p544 A94-60396 cracked panels SPACECRAFT STRUCTURES NASA/DOD Aerosoece Knowledge Diffusion Research |NASA-CR-19602t ] p 556 N94-35974 Prelect. Paper 42: An enaly_s of the transfer of Scmntific _t and predtclk)n of clynan'Nc temporatures STRUCTURAL ANALYSIS in unsymmetrically cooled gtass windows and TechniCal Information (STI) in the US aerospace hJ_tysls of multifastener composite joints industw [ BTN-94-EIX94351142128 ] p550 A94-60421 [STN-94-EIX9431t330690| p 548 A94-6010t SPECTROSCOPIC ANALYSIS ( NASA-TM-109863 ] p 560 N94-34730 Effects of model scale on flight characteristics and SOFTWARE ENGINEERING Raman measurements at the exit of a combustor des_ge parameters sector Engineering large-scale agent.based systems wilh [BTN-94-EIX94311329143| p 5t7 A94-60157 consensus p 558 N94-35071 |STN-94-EIX94341338356] p 546 A94-60348 Joined-wing model vtbrat._ons us=ng PC-based modal Cost and schedule eetimatmn study report SPECTRUM ANALYSIS testing end finde element analys=s [ NASA-CR.189344 ] p 558 N94-35256 A corn_ned approach to buffet response analyses and [BTN-94-EIX94311329t41| p 517 A94-60159 SOFTWARE REUSE fetKjue life bredictio_ p 551 N94-34587 Mo0bl coordinates for aeroetastic analys_s with large Ada developers' supplement to the recommended SPINDLES local sVuctural venations approach Desert, construction, end testing of • five active axes [BTN-94-EIX9431t32913t) p 518 A94-60169 (NASA-CR-189345J p 557 N94-34921 megnebc beanng system p 554 N94-35846 Prelimina_ structural evaluation end design o! the SOUO PROPELLANT COMBUSTION SPUNES HL-20 AFOSR Contractors Propulsion Meeting Computation end discuss4on of a needy constant degree [BTN-94-EIX94351137060] p 545 A94-60400 IAD-A279028J p 539 N9,4-35746 of react/on tod_ne stage Three-dimemaonal thermal analysis tor tasor-stn_tural SOLID PROPELLANT ROCKET ENGINES [BTN-94-EIX94351144987] p 537 A94-60449 interactions AFOSR Contractors Propulss)n Meeting SPRAYERS _BTN-94-EIX94351142117] p 560 A94-60410 IAD-A279028J p 539 N94-35746 Notch fatH_ue assessment of aircraft components using SPACE MISSIONS Irl_ of bubb4ing liquid lets from mult_o_ inpectors into a superaonic stream a fracture mechanics based parameter Vista goes online: Decismn-analytlc systems for reel-time [BTN-94-EIX94321333316] p 520 A94-60267 p 55t N94-34588 deoslon-making in mission control p 558 N94-35063 Analys_s ot wavelet technology for NASA appIK;:atK_ns SPACE PROCESSING STABILITY AUGMENTATION |NASA-CR-195929] p 522 N94-34704 1993 TechnPcal Paper Contest for Women. Gear Up YAV-aS reaclJon corm'ol system bteed and control power usage in hover and bansi_ Deign oriented structural enalys_s 2000: Women in Motion INASA-TM-109t24J p 551 N94.34722 [NASA-TM-104021 ] p 540 N94-34994 [NASA-CP-10134] p 561 N94-35961 STRUCTURAL DESIGN SPACE SHUI"rLE MAIN ENGINE STABILITY DERIVATIVES Am_raf_ fleet maintenance based on structural reliabddy Localization of aeroetastic modes in m_tuned Effects of bropallor on the turning of old fighter,& ana_ |BTN-94-EIX94361135426] p 537 A94-60623 high-ermrgy turbrnes |BTN-94-EIX94311329t34| p 517 A94-60166 STAGNATION PRESSURE [BTN-94-EIX94321333307] p 547 A94-60039 Preliminary structural evakJation and design of the SPACE SHUTTLE MISSIONS Structure and permtrat_,n of a JRioerordical fluid jet in HL-20 Mms_on Evaluation Room Intelhgent Diagnostic and mnmnlC flow [STN-94-EIX94351137060| p 545 A94-60400 Analysis System (MIDAS) p 558 N94-35064 [BTN-94-EIX94321333317] p 549 A94-60268 An Assessment of Fatigue Damage and Crack Growth SPACE SHUTTLE ORBITERS STANDARDS Prediction Techniques Characteristics of the Shuttle Orolter leeside flow dunng Mimmum performance standards: Aidoome low.range [AGARD-R-797] p 550 Ng4-3458t a re-ent_" condition radar altimeters Hern_ 2: A comparison of US and UK approaches to |BTN-94-EIX94311322888) p 520 A94-60208 [ RTCA-DO- 155) p 537 N94-3534,4 fatigue clearance p 531 N94-34596 A-17 STRUCTURAL FAILURE SUBJECTINDEX Fatigue design, lest and in-service experience of the Experimental invest_ation on supersonic combustion SYSTEM EFFECTIVENESS BAe Hawk p 531 N94-34597 (2) The Federel Aviation AdmintstratK)n plan for research, STRUCTURAL FAILURE IBTN-94-EIX94351144985} p 537 A94-60447 engineering and development p 561 N94-35262 An analysis of operational suitability for test and Assessment of in-service aircraft fatigue monitoring AFOSR Contractors Propulsion, Meeting process p 531 N94-34593 [AD-A279028} p 539 N94.35746 evatuabon of highly reliable systems STRUCTURAL RELIABILITY SUPERSONIC COMBUSTION RAMJET ENGINES lAD.A278573| p 530 N94-36t84 Aircraft fleet maintenance based on structural reliability SYSTEM FAILURES Technology and staging effects on two-stage-to-orbit analys_s Flight testing a propulsion-controlled aircraft emergency systems flight control system on an F-15 airplane IBTN-94-EIX943113291341 p 517 A94.60166 [BTN-94-EIX94311322891J p 520 A94-60205 INASA-TM-4590] p 540 N94.35258 An Assessment of Fatigue Damage and Crack Growth SUPERSONIC FLOW Prediction Techniques SYSTEM IDENTIFICATION Supersonictransport wing minimum weight design IAGARD-R-797J p 550 N94-34581 X-31A system iclentlfK:ation apPlmd to post-stall flight: integrabng aeredynam_cs and structures Rotorcraft fatigue life.predicbon: Past, wesent, and Aerodynamics and thrusl vectonng p 540 N94-34619 [BTN-94-EIX94311329123 t p 518 A94-60177 future p 551 N94-34590 An overvmw of recent advances in system STRUCTURAL VIBRATION Injection of bctbbting liquid jets from mulbple injectors identification p 546 N94-35880 into a supersonic stream Joined.wing model vibrations using PC-based modal SYSTEMS ANALYSIS IBTN-94-EIX94321333316] p 520 A94-60267 testing and finite element analysis Techniques for aerodynamic characterization and JBTN-94-EIX94311329141 ] p 517 A94-60159 Structure and penetration of a supercritical fluid jet in pedormance evaluation at high angle of atteck Modal coordinates for aeroelest¢ analysis with large supersonic flow p 533 N94-34614 local structural venations I BTN-94-EIX94321333317 } p 549 A94-60268 SYSTEMS INTEGRATION [BTN-94-EIX94311329131 ) p 518 A94-60169 Three-dimensa0rml upwind parabolized Navlar-siokes Terminal Doppler Weather Radar (TDWR) Low Level Frequency domain analysis of the random loading of code foe supersonic combustion flowfialds Wind Shear Alert System 3 (LLWAS 3) integration studies cracked panels tBTN.94.EIX94351142134] p 521 Ag4-60427 at Orlando International Airport {NASA-CR-196021] p 556 N94-35974 Expodmental investigetion on supersonic combustion lAD-A278957| p 557 N94-35807 SUBSONIC FLOW (2) Unsteady lift of a flapped airfoil by indicial concepts [BTN-94-EIX94351144985] p 537 A94-60447 T [RTN-94-EIX94311329118} p 519 A94-60182 A review and development of correlations tar base SUBSONIC SPEED pressure and base heating in supersonic flow T-53 ENGINE Aeredynarr, c characteristics of the HL-20 [ SAND93-0280] p 526 N94-35360 Hot gas ingestion effects on luel control surge recovery [ BTN-94-EIX94351137055 J p 544 A94-60395 A supersonic tunnel for laser and flow-seeding and AH-1 rotor drive train torque spikes Wind tunrmt measurements on a lull-scale F/A.18 with technK:lues [NASA-CR.19t047J p 538 N94-34993 a tangentially blowing slot -. conducted in the Ames 80 [NASA-TM-106588] p 556 N94-35945 by 120 foot wind tunnel p 527 N94.35965 TAIL ASSEMBUES SUPERSONIC INLETS SUBSONIC WIND TUNNELS A combined approech to buffet response analyses and Computational methods for HSCT-inlet controls/CFD National facilities study Volume 2: Task group on fatigue life pred_cbon p 551 N94-34587 inlordlsc_plinary research aeronautical research and development facWitias report Damage tolerance management of the X.29 vertical lNASA-TM-106618] p 539 N94-35352 [NASA-TM.109855] p 542 N94.34633 tail p 531 N94-34595 SUPERSONIC NO2ZLES Flow quality studms of the NASA Lewis Research Center Aerodynamic des_jn of super maneuverable a_rcraft A supersonic tunnel for leser and flow-seeding Icilxj Research Tunnel p 533 N94-34617 techniques TAIL SURFACES [NASA-TM-t06545} p 543 N94-34919 (NASA-TM-t06588] p 556 N94-35945 T_I load calculations for kght e_arms Langley 14- by 22-foot subsonic tunnel test engineer's SUPERSONIC SPEED beta acquisition and reduction manual [BTN-94-EIX943t1329148] p 517 A94-60152 TAKEOFF I NASA.TM-45631 p 526 N94-35246 Aerodynarmc cheractehstics of the HL-20 SUCTION {BTN-94-EIX94351137055] p 544 A94-60395 Direct reduced order mixed H2/H infinity control for the Expansion effects on supersonic turbulent boundary Short Take-Off and Landing/Maneuver Technology Dynamic tests lo demonstrate lateral control using layers Demonstrator (STOL/MTD) forebody suction on large scale models in the DRA 24 [AD-A278989] p 527 N94.35950 lAD-A278675| p 540 N94-35796 foot wind tunnel p 539 N94-34613 SUPERSONIC TRANSPORTS TECHNOLOGIES The unsteady pressure field and vortc_ty productik)n at Computational methods for HSCT-intet controls/CFD JPRS report: Science and technology Central Eurasia the sucbon surface of a pitching airfoil interdisciplinary research [JPRS-UST-94-006| p 553 N94-35226 p 524 N94-34972 { NASA-TM-106618 ] p539 N94-35352 JPRS report: Scm_'e and technology. Central Eurasia SUPERCONDUCTING MAGNETS SUPERSONIC TURBINES [JPRS-UST-94-005] p 553 Ng4.35342 Second International Sympo_um on Magnetic Vane-blade interaction in a transonic turbine. Part 1: JPRS report: Science and technology. Central Eurasia Suspons_on Technology, parl 2 Aemdynemics [JPRS-UST-94-010] p 553 N94.35385 [ NASA-CP-3247-PT-2 ] p 546 N94-35902 JPRS repi)rt: Scmnce and technology. Central Eurasm SUPERCONDUCTIVITY [ BTN-94-EIX94321333305] p 515 A94-60037 SUPERSONIC WIND TUNNELS [JPRS-UST-94-012} p 553 N94-35387 ProcessBng yttnum banum copper oxKle superconductor TECHNOLOGY ASSESSMENT Coniugete condoct_n-so_wection heat transfer with • in near-zero grawty high-speed boundary layer Tactical cockpds: The coming revolution ( STN-94-EIX94311332378 ] p550 A9,4-60951 lBTN-94-EIX94331335530} p 530 A94-60211 [ BTN-94-EIX94311330652 ] p549 A94-60139 SUPERCONDUCTORS TELEMETRY A _q_mmnio lunnel for _ end flow-soIKling Missio_ Evaluation Room Intelbgent Diagnostic and Processing yttrium barium copper oxide superconductor technKlues Analy_s System (MIDAS) p 558 N94-35064 in near-zero gravity INASA-TM-106588] p 556 N94-35945 TEMPERATURE CONTROL [ BTN-94-EIX94311332378 | p550 A94-60951 SUPPORT SYSTEMS Active thermal isolation for temperature responsNe Data reduct_n, analysis and results of LACV-30-07 e_r FINOER, A system Ixoviding complex decision support soneof$ cush_on vehicle tests, Fort Story, VA, August -Septernber for commercial transport repianning operations [ NASA-CASE-LAR- 14612-1 } p552 N94-35074 1993 {BTN-94-EIX94331335529] p 549 Ag4-60210 TEMPERATURE DEPENDENCE IAD-A278859J p 527 Ng4-35826 SURFACE ROUGHNESS Aplxoximata sm_larity I_naple for a _ull-scale STOVL SUPERCRITICAL FLUIDS Prediction of ice shapes and their effect on airfoil drag Measurement of diffus0on in fluid systems: Applications I BTN-94oEIX94311329115 ] p519 A94-60185 e_ector to the supercritcal fluid region SURGES [BTN-94-EIX94341338360} p 550 A94-60352 TEMPERATURE DISTRIBUTION [BTN.94.EIX94311330660] p 548 A94-60131 Hot gas ingestion effects on fuel control surge recovery Cbaracleristcs of the Shuttle Orb_e_ leeside flow during Structure and penetration of a supeccritcal fluid jet in and AH-1 rotor drNe train torque spikes a re-entry condition supersonic flow [NASA-CR-191047| p 538 N94-34glY3 SURVEYS [BTN-94-EIX94311322888] p 520 A94-60208 [BTN-94-EIX94321333317} p 549 A94-60268 TEMPERATURE MEASUREMENT Quantitative low.speed wake surveys SUPERSONIC AIRCRAFT Raman measurements at the exit of a combustor [ BTN.94.EIX94311329113) p520 A94-60187 Measurement and predictio_ of dynamic temperatures esctor SUSPENS_DN SYSTEMS (VEHICLES) in uneymmetrically cooled glass windows [BTN-94-EIX94341338356] p 546 A94-60348 Control of meglev vehicles with aerodynamic and [BTN-94-EIX94351142128J p 550 A94-60421 Meluluremertt and prediction of dynamK: temperatures SUPERSONIC BOUNDARY LAYERS guideway disturbances p 554 N94-35842 SWEAT COOLING in unsymmethcally cooled glass windows Conjugate conducbon-convection heat transfer with a [ BTN-94-EIX94351142128 ] p550 A94_60421 _I studies of trans_raban cooling with shock _gh-speed boundarylayer TEMPERATURE SENSORS interaction in hypersonic flow, part B [BTN-94-EIX94311330652) p 549 A94-60139 Active thermal isolatio_ for temperature responsNe [NASA-CR-195g58] p 523 N94-34965 Expansion effects on supersonic turbalenl boundary SWEPT FORWARD WINGS 14Bnsors layers | NASA-CASE-LAR-14612-1 ] p552 N94-35074 Pressure melmurements on a forward-swept [AD-A278989J p 527 N94-35950 wmg-camud configuration TERRAIN ANALYSIS SUPERSONIC COMBUSTION [BTN-g4-EIX94311329149] p 516 A94-60151 Design and analysis of a Kalmen lifter for Planar KrF ialer-induced OH fluorescence _naging tn SWEPT WINGS terram--roferlmced poctioning and gu_daoce a supersonio combustion tunnel torla0nal stall flutter a_rodynemio experintents [ BTN-94-EIX94311329124 | p557 A94-60176 [BTN-94-EIX943213333151 p 520 A94-60266 on threa,dimensior_ _nge TEST CHAMBERS Turbulent combustK_n regimes for hyperson¢ pcopulwon [BTN-94-EIX94341338362] p 522 A94-60354 Combuation shock tunnel and interface compres._on to eml_oylng hydrogen-tur diffusion flames Will the real dynamic instabilk'y mectlenism _eesa be increase mNn_olr pressure and enthalpy [BTN-94-EIX94321333324] p 546 A94-60275 recognized! p 552 N94-34976 [BTN-94-ElX943113306501 p 516 A94.60141 Three-dimensional upwind parepolized Navler-Stokes SYNCHRONISIII TEST FACILITIES code for aupersor.c combustion flowtields Runtime support tar data parallel tasks Natioflal facilitms study, Volume 1: Facilities inventory IBTN-94-EIX94351142134] p 521 A94-60427 [NASA-CR-194904J p 558 N94-35240 [NASA-TM-109854} p 541 N94-34632 A-18 SUBJECT INDEX UNSTEADY AERODYNAMICS National facilities study Volume 2: Task group on TOLERANCES (MECHANICS) TURBORAMJET ENGINES aeronautical research and development facilities repod Damage tolerance management of the X-29 vertical Technology and staging effects on two-stage-to-orbit INASA-TM-1098551 p 542 N94-34633 tail p 531 N94-34595 systems THERMAL ANALYSIS TORQUE |BTN-94-EIX94311322891 ] p 520 A94-60205 Three-dimens)onal thermal analysis for laser-structural Effects of propeller on the turning of old fighters TURBULENCE interactions [BTN-g4-EIX943611354261 p 537 A94-60623 Alleviation of side force on tangent-ogNe forebodtes {BTN-94-EIX94351142117} p 560 A94-60410 Hot gas ingest)on effects on fuel control surge recovery using passNe porosity New two-temperature dissociation model for reacting and AH-t rotor drive train torque spikes [BTN-94-EIX94311329126J p 536 A94-60174 flows I NASA.CR.191047 J p538 N94-34993 Expans0on effects on supersonic turbulent boundary IBTN-94-EIX94351142137) p 560 A94-60430 TORSION layers THERMAL CONDUCTIVITY An examinabon of 1he aerodynamic moment on rotor lAD-A278989} p 527 N94-35950 Three-dimensional thermal analysis for laser-structural blade tips using fl_jht test data and analysis TURBULENCE MODELS interactions INASA-TM-t04006J p 523 N94-34948 Prediction of unsteady airfoil flows at large angles of TRAILING EDGE FLAPS l BTN-g4-EIX94351 t42117 J p560 A94-60410 incidence p 525 N94-34978 Unsteady Idl of a flapped a_oil by ind)olal concepts THERMAL PROTECTION TURBULENT BOUNDARY LAYER IBTN.94.EIX94311329118] p 519 A94-60182 Aerodynamic heating enwonment defindion/thermaf Computat*onal analysis of a single jet impingement Selected topics on the active corltrol ol helicopter protection system selection for the HL-20 ground effect lift loss aeromechan_cal and vibration problems [ BTN-94.EIX94351137058 J p 544 A94-60398 [BTN-94-EIX94311329114] p 519 A94-.60186 p 541 N94-35874 THERMAL RADIATION A review and development of correlations tar base TRAINING AIRCRAFT Coupled radmtion effects in thermochemlcal Fat_ue design, test and in-se_qce experience of the pressure and base heating in supersonic flow nonequilibnum shock-capturing flowfield calculations BAe Hawk p 531 N94-34597 ISAND93"0280] p 526 N94-35360 I BTN-94-EIX94311330648 ] p559 A94-60143 TRAJECTORY ANALYSIS The aerodynamic and heat transfer effects of an endwall THERMAL STABILITY Six-degree-of-freedom guidance and control-entry boundary layer fence in a 90 degree turning square duct Retained mechan)oal prOperties of a new AI-Li-Cu.Mg-Ag analysis ol the HL-20 [AD-A278903 ] p 553 N94-35803 alloy as a lunction of thermal exposure time and IBTN-94.EIX94351137056] p 544 A94-60396 Expansion effects on supersomc turbulent boundary temperature TRAJECTORY CONTROL layers {BTN-94-EIX94301320164] p 546 A94.60873 Yaw control by tangential forebody blowing IAD-A278989J p 527 N94-35950 THERMOCOUPLES p 539 N94.34615 TURBULENT COMBUSTION Measurement and predichon of dynamic temperatures TRANSITION FUGHT Turbulenl combust)on regimes for hypersonic prOpulSion in unsymmetncally cooled glass windows YAV-8S react|on control system bleed end control power eml_oylng hydrogen-mr diffusion flames ( BTN-94-EIX94351142128} p 550 A94-60421 usage in hover and transit,on {BTN-94-EIX94321333324| p 546 A94-60275 THERMOGRAPHY INASA-TM-104021] p 540 N94-34994 AFOSR Contractors Propulsion Meeting Field deployable nondestructive impact damage TRANSITION TEMPERATURE IAD'A279028) p 539 N94-35746 assessment methodology for composite structures Processing yttrium banum copper oxide superco¢_uctor TURBULENT DIFFUSION in near-zero gravity {BTN-94-EIX94301321378] p 546 A94-60892 Turbulent combusbon reg*mes for hypersor_ic proputs)on {STN-94-EIX94311332378} p 550 A94-60951 THIN AIRFOILS employing hydrogen-mr cliff us)on flames TRANSMISSIONS (MACHINE ELEMENTS) Robust control design techniques for active flutter [BTN-94-EIX94321333324 J p 546 A94o60275 Low-name, high-strength, spcal-bevel gears for suppressmn p 541 N94-35875 TURBULENT FLOW helicopter transmms)ons THIN WINGS Drag reduction for turbuionf flow over a projectile, part |STN-94-EIX94321333312} p 548 A94-60044 PreciS)on requirement for potential-based panel 2 TRANSONIC FLOW methods [ BTN-94-EIX94311322900 ] p 520 A94-60196 Expe_mentel investigation of counferorotating propfan [ BTN-g4-EIX94301315995 J p515 A94-60031 flutter at cruise conditions Drag reduction of turbulent flow over a proqectile, part THREE DIMENSIONAL BOUNDARY LAYER 1 |STN-94-EIX94321333310] p 516 A94-60042 Transition correlations in three-dimensional boundary TRANSONIC SPEED [ BTN-94-EIX94311322899 J p 557 A94-60197 layers Drag reduction of turbulent flOw OVer a Wold'tHe, pert Structure and penetration of a superordical fluid let ,n IBTN-94-EIX94301315968J p 547 A94-60004 1 supersonic now THREE DIMENSIONAL FLOW ISTN-94-EIX94311322899| p 557 A94-60197 [BTN-94-EIX943213333171 p 549 A94-60268 New multigrio aPproach for thcee-dimens.,onal TRANSONIC WIND TUNNELS Experimental studies of shock-wave/wall-jet interaction unstructured, adaptive grids National facilities study. Volume 2: Task group on in hypersemc flew, part A I BTN-94-EIX94301315973 ] p559 A94-60009 aeronaut)oat research and development facilities report [NASA-CR-f95957] p 523 N94-34964 Three-dimenemnal closure of the passage-averaged INASA-TM-109855) p 542 N94-34633 Exprmmental studies of transpiration cooling wtth shock vortlcity.potentlal formulation TRANSPORT AIRCRAFT interaction in hypersonic flow, part B |BTN-94-EIX94301315991 ] p 547 A94-60027 Quantitative low.speed wake surveys [NASA-CR-195958) p 523 N94-34965 Three-dimens)onal upend parabolized Newer-Stokes [STN-94-EIX94311329113 ) p 520 A94-60187 Active _1 isolation for temperature responsive PROPERTIES code for supersonic combustion flewfields TRANSPORT een_ocs IBTN-94-EIX94351142134} p 521 A94-60427 On the various forms o4 the energy e(:lUal_on for a dilute, [NASA-CASE-LAR-14612-1] p 552 N94-35074 menaton'.c mixture o1 nonreecting gases Some aspects of unsteady separation A three dimensional multigrid Reynolds-averaged p 525 N94-34979 INASA-CR-4612] p 527 N94-35864 Nevier-Sto_as sblver for unstructured meshes TRANSPORTATION A three dimensional multigrid Reynolds-averaged [ NASA-CR-194908 ) p 528 N94-35994 Navmr-Stokes solver for unstructured meshes Future ultrs-speed tube-flight p 555 N94-35918 TURNING FLIGHT INASA-CR-1949081 p 528 N94-35994 TUNING Effects of Wopeller on the turning of old fighters THROTTLING Locellzation of eeroelasbc modes in rmstuned [ BTN-94-EIX943611354261 p 537 A94-60623 Flight testing a proPptseon-controlled aircrafl emergency high-energy turbines TWO DIMENSIONAL FLOW fl_lht control system on an F-15 iurplene lBTN-94-EIX94321333307] p 547 A94-60039 Explicit Kutta cond_t)on for an tmsteady two-dimens_al I NASA.TM-45901 p 540 N94-35258 TURBINE BLADES constant pptentlal panel method THRUST Locahzation of aeroelastic rno0es in mistuned [BTN.94.EIX94301315990| p 515 A94-60026 Effects of thrust hne ofset on neutral point determination high-energy turbin_ in flight testing [BTN-94-EIX94321333307] p 547 A94-60039 Natural co_wecltc_ in a cavity wdh fins attached to both [ BTN.94.EIX94311329127) p518 A94-60173 Experimental investigation of counter-rotating prop/an vertic_ wails Evaluating the dynamic response of in-fligtlt thrust flutter at or_se conditions [BTN-94-EIX94351142119] p 550 A94-60412 calculation techniques during throttte transients [STN-94-EIX94321333310] p 516 A94-60042 Irwestigation of Bumett equabo_s for two-dimenmonel [ NASA-TM-4591 J p 535 N94-35241 Dynamic aeroelastic stability of vertical-axis wind hypersonic flow THRUST VECTOR CONTROL turbines under constant wind velocity [AD-A278942} p 527 N94-35717 Results from the STOL and Maneuver Technology [BTN-94-EIX94321333311 | p 548 A94-60043 Demonstration program p 532 N94-34611 Inverse design o1 super-olliptic cooling passages in Aerodynamic design o1 super maneuverable aircraft coated turbine blade aidblls U p 533 N94.34617 [ BTN-94-EIX94311330654 ] p 548 A94-60137 X-31A control law design p 540 N94-34618 TURBINE PUMPS ULTRASONIC TESTS X-31A system identification applied to post-stall flight: Localization of aeroelastic modes m mmtunecl Field deployable nondestructive Impact damage AerodynarrHcs and tt_Jst vectoring p 540 N94-34619 high-energy turbines assessment methodology for composite structures X-31 tactical utility: Inibal results p 533 N94-34620 [BTN-94-EIX94321333307| p 547 A94-60039 [BTN-94-EIX94301321378] p 546 A94-60892 Direct reduced order rmxed H2/H infinity control for the TURBINES UNSTEADY AERODYNAMICS Short Take-Oft and Landing/Maneuver Technology Comw_mtion and discuss)on of a n_ constant pe_'ee Localization ol aeroetastic modes in mistuned Demonstrator (STOL/MTD) of maction tuYo_ sta_ high-energyturbines [ AD-A278675 } p 540 N94-35796 [ BTN-94-EIX94351144987 ] p537 A94-60449 [STN-94-EIX94321333307] p 547 A94-60039 TILT WING AIRCRAFT TURBOCOMPRESSORS Orn_thepterw_g design 1993 Technical Paper Contest for Women. Gear Up Axial compressor perlormance duong surge [BTN-94-EIX94331337499] p 521 A94-60334 2000: Women in Motion [ BTN-94-EIX94321333306 ] p 548 A94-60040 Techmques for aerodynamic characterization and [NASA-CP-10134} p 561 N94-35961 Prediction of unsteady airfoil flows at large angtes of perlorrnance evaluation at hlgh angle of attack Piloted simulation study of two tiff-wing control incidence p 525 N94-34978 p 533 N94-34614 concepts p 541 N94-35962 TURBOMACHINERY Unsteady separation process and vorticity balance on TIME SERIES ANALYSIS Departure solutions of the unsteady thin-layer and furl unsteady aidods p 524 N94-34970 A combined approach to buffet response analyses and Naviet-Stokes eduat)ons solved using streamline curvature Robust control design technK:lues for active flutter fatigue life prediction p 551 N94-34587 based iteratK)n techniques p 552 N94-34980 suppressmn p 541 N94-35875 A-19 UNSTEADY FLOW SUBJECT INDEX UNSTEADY FLOW Flutter suppression digital control law design and tesbng Unsteady flow past an airfoil pitched at constant rate p 524 N94-34969 Explicit Kutta condition for an unsteady two-dimens,onal for the AFW trend tunnel model p 540 N94-35873 constant potential panel method Selected topics on the active control of helicopter Unsteady separation process and vorticdy balance on I BTN-94-EIX94301315990 J p515 A94-60026 aeromechanical and vibration problems unsteady airfoils p 524 N94-34970 Unsteady separation expenments on 2-D airfoils. 3-D p 54t N94-35874 Control of leading-edge voices on a delta wing p 524 N94-34971 wings, and model helicopter rotors p 524 N94-34967 Robust control design techniques for active flutter Comparison of Pitch rate history effects on dynamic suppression p 54t N94-35875 Charactenzation of dynamic stall phenomenon using stall p 53.5 N94-34968 Electromechanical simulation and test of rotating two-dimensional unsteady Navidr-Stokes equations p 524 N94-34974 Unsteady flow past an airfoil _tched at constant rate systems with magnetic beanng or pmzoelectnc actuator p 524 N94-34969 active vibration control p 555 N94-35905 Prediction of unsteady airfoil flows at large angles of incidence p 525 N94-34978 Unsteady separation process and vorticlty balance on VIBRATION MODE unsteady airfoils p 524 N94-34970 Local_.ation of aeroelestic modes in mistuned Departure solutions of the unsteady thin-layer and full Navier-Stokes equabons solved using streamline curvature Control of leading-edge vortK:es on a delta wing high-energy turbines p 524 N94-3497t [BTN-94-EIX94321333307t p 547 A94-60039 based ileration techniques p 552 N94-34980 Unsteady structure of leading-edge vorbces on a delta The unsteady Pressure field and vorticity Productiion at Experimental investigation of counter-rotating Propfan the suction surface of a pitching airfoil flutter at cruise conditions wing p 524 N94-34972 [BTN-94-EIX9432t333310} p 5t6 A94-60042 lAD-A278988| p 526 N94-35529 Charactenzation of dynamic stall phenomenon using Time simulation of flutter with large stiffness changes F/A-18 lorebody vortax control Volume 1: Static tests two-dimens_onal unsteady Navier.Stokes equations [BTN-94-EIX943113291321 p 518 A94-60168 INASA-CR-4582} p 528 N94.35991 p 524 N94.34974 Modal coordinates for aeroelestic analysis with large VORTICITY Computed unsteady flows of airfoils at high incidence local structural venations Expenmental studms of vortex flaps and vortex plates p 525 N94-34975 IBTN-94-EIX94311329t3t | p 518 A94-60169 IBTN-94.EIX943113291221 p 518 A94-60178 Computation of unsteady flows over airfoils Ground vibration test of the XV.15 Tiltrotor Research Unsteady flow past an agrfoil Pitched at constant rate p 525 N94-34977 Aircraft and pretest predictions p 541 N94-35972 p 524 N94-34969 Prediction of unsteady airfoil flows at large angles of VIBRATION TESTS The unsteady Pressure field and re.city Productilon at incidence p 525 N94-34978 Low-no0se, high.strength, s_ral-bevst gears for the suction sudace of a oitching airfoil The quest for stall-free dynamic lift helicoptar transmissions p 524 N94-34972 p 525 N94-34986 I BTN.94-EIX943213333121 p 548 A94-60044 Unsteady structure of leading-edge vortres on a delta Mechanisms of flow control with the unsteady bleed Ground vibi'abon test of the XV-15 Tiitrotor Research wing technique p 525 N94-34987 Aircraft and pretest Predictiorts p 541 N94-35972 lAD-A278988| p 526 N94-35529 Concepts end _m_.,ation of dynamic separation for VISCOUS FLOW agility and super-maneuverability of aircraft: An Computation of unsteady flows over airfoils W assessment p 535 N94-34988 p 525 N94-34977 Unsteady structure of leading-edge vortices on a delta Some aspects of unsteady separation WAKES wing p 525 N94.34979 Numencal investigation of cylinder wake flow with a rear [AD-A278988J p 526 N94-35529 VISIBILITY stagnation jet UNSWEPT WINGS Data requirements for ceiling and visibility Products [ BTN-94-EIX94301315998 ] p 547 A94-60034 Incipient torsional stall flutter aerodynamic experiments devek_ment Quantitative low-speed wake surveys on three.dimensional wmgs lAD-A278959| p 556 N94-35720 |BTN-94-EIX94311329113| p 520 A94-60187 |BTN-94-EIX94341338362] p 522 A94-60354 VISIJAL CONTROL WALL FLOW USER MANUALS (COMPUTER PROGRAMS) Effect of lift-to-drag ratio in I_lOt rating of the HL-20 Experimental studies of transpiration cooling with shock Langley 14- by 22-foot subsonic tunnel test engineer's landing task interaction in hypersenic flow, part B data acquisition end reducbon manual [BTN-94-EIX94351137057 | p 544 A94-60397 INASA-CR-195958| p 523 N94-34965 I NASA.TM-4563 ] p 526 N94-35246 VISUAL SIGNALS The aerodynamic and heat transfer effects of an end'wall User's gutde for an interactive personal computer Synthetic vision for enhancing poor visibility flight interface for the aeropredcbon code boundery layer fence in a 90 0egrae turning square duct operations lAD-A278903) p 553 N94-35803 INSWCDD/TR-94/1071 p 559 N94-35958 l BTN-94-EIX94331335531 ] p557 A94-60212 WALL JETS VORTEX BREAKDOWN Expenmental stu0ies of shock-wave/wall.jet interaction Effects of the roll angle on cruciform wing-body V in hypersonic flow. part A configurations at high incidences INASA-CR-195957| p 523 N94-34964 [BTN-94-EIX94311322903| p 520 A94-60193 VISTOL AIRCRAFT WALL TEMPERATURE Con_ol of le_Klmg-edge vortices on = delta wing Propulsson-induced aerodyr_mlc effects measured with Cheractensbcs of the Shuttle Orbder leesida flow dunng p 524 N94-34971 a tun-scale STOVL model a re-entry condition Unsteady structure of leading-edge vortices oe a delta [STN-94-EIX943113291201 p 519 A94-60180 [BTN-94-EIX94311322888| p 520 A94-60208 wing Compomte matrix experimental combustor Approxmlata similarity principle for a full-scale STOVL lAD-A278988| p 526 N94-35529 INASA-CR-194446] p 538 N94-34679 ejector VORTEX FLAPS WALLS [ BTN-94.EIX94341338360 ] p550 A94-60352 Sxpeemental studws of vortex flaps and vortex plates VANES Natural convectmn in a cavity with fins attached to both [BTN-94-EIX94311329122] p 518 A94-60178 Computation and dmcuss_on of a nearly constant degree vertical walls VORTEX GENERATORS of react_n turbine stage [ BTN-94.EIX94351t 421f 9 ] p550 A94-60412 Control of leading-edge separation on a uambered d_ta I BTN-94-EIX9435 t 144987 ] p 537 A94.60449 wing p 539 N94-34616 Some aspects of unsteady separation VAPOR PRESSURE VORTEX SI'IEDDING p 525 N94-34979 Unleaded AVGAS program Yaw control by tangential forebody blo_ng WARNING SYSTEMS IAD-A2786501 p 547 N94-35795 p 539 N94.346t5 Terminal Defiler Weather Radar (TDWR) Low Level VAPORS Unsteady flow past an aidoil pitched at constant rate Wind Shear Alert System 3 (LLWAS 3) integrabon studies Unleaded AVGAS Program p 524 N94.34969 at Orlando Internabonal/_rport lAD-A2786501 p 547 N94-35795 VORTICES lAD-A278957| p 557 N94-35807 VELOCITY DISTRIBUTION Symmetry breaking in vortical flows over corms: Theory WATER Data reduction Procedures for laser vstoometer and numerical experiments I_ectio_ Of bubbling liquid jets from multiple inlectors measurements in tud)omachmery rotors [ BTN-94-EIX943013 t 5981 ] p547 A94-60017 into a su_oeraomc stream [NASA-CR-195343| p 552 N94-35224 CrnsMlow topology of vortical flows |BTN-94-EIX9432t333316] p 520 A94-60267 VELOCIT_ MEASUREMENT [BTN-94-EIX94301315993] p 515 A94-60029 WATER TUNNEL TESTS In-flight velocity measurements using laser Doppler Nav=_-Sto_es _Ner for hyperson_ flow over • slender Effect of initial accelerabon on the development of the anemomethj cone flow field of an aidoil pitching at constant rate [BTN-94-EIX94311329139] p 549 A94-60161 [BTN-94-EIX943f1330681] p 543 A94-60110 p 526 N94-34989 Determination Of slender body aerodynamics u_ng Comparison of optical measurement techniques for WAVE PACKETS discrete vortax methods turbomachinew tiowfields JPRS report: Science and technology. Central Eurasia [ BTN-94-EIX94341338357 ] p 559 A94-60349 { BTN-94-EIX94311330679 ] p543 A94-60112 [JPRS-USTo94-006) p 553 N94-35226 Experimental studms of relax flaps and vortex plates Flow quality studms of the NASA Lew_s Research Center WAVELET ANALYSIS [BTN-94-EIX94311329122] p 510 A94-60t78 Icing Research Tunnel Analysis of wlvstat technology for NASA applications Vortex.wing interaction of a close-coupled canard [NASA-TM-106545] p 543 N94-34919 |NASA-CR-195929] p 522 N94-34704 co_lion WAVERIDERS VIBRATION [BTN-94-EIX94311329121] p 519 A94-60179 Computational analys,s of oft-deign waveriders Time slmuletion of flutter with large stiffness changes Forlbody vortex control for wing rock suPl_raasion [BTN-94-EIX94311329125| p 549 A94-60175 |BTN-94-EIX94311329132] p 518 A94-60168 [BTN-94-EIX94311329119] p 530 A94-60181 WEAPON SYSTEM MANAGEMENT Dkect simulation with vibration-diasocmtidn coupling Computational analysis el a single jet impingement I BTN-94-EIX94351142136 ] p521 A94-60429 ground effect lift Risk analysis of _ C-141 WS405 inner-to-outer wing Selected topics on the active control of heScoptor IBTN.94.EIX94311329114| p 519 A94-60186 joint p 531 N94-34592 WEAPONS DEVELOPMENT aeromechancal sod vibrat_n prol_ms Effect= Of Ixopellor on the turning of old fighters p 541 N94-35874 [BTN-9,I.EIX94361135426] p 537 A94-60623 Operational a_lily: An overview of AGARD Working VIBRATION DAMPING Dynamic tests to demonstrate lateral control using Group 19 p 534 N94-34625 Data reducbon, anah/sm and results of LACV.30-07 air forebody sucbon on large scale models in the DRA 24 WHEELS cush,on vehicle tests, Fort Story, VA, August - September foot w_d tunnel p 539 N94-34613 Determination of t_re-wheel interlace loads for a_,rcraft 1993 Yaw control by tangential furebody blowing whets I AD-A2788591 p 527 N94-35826 p 539 N94.34615 [BTN-94-EIX94311329136] p 517 A94-60164 A-20 SUBJECT INDEX ZINC ALLOYS WIND SHEAR WING OSCILLATIONS Terminal Doppler Weather Radar (TDWR) Low Level Forebody vortex control for wing rock suppress_n Wind Shear Alert System 3 (LLWAS 3) integration studies IBTN-94-EIX94311329119_ p 530 A94-60181 at Orlando International AJrporf Unsteady lift of a flapped airfoil by indic=al concepts IAD-A278957J p 557 N94-35807 IBTN-94-EIX94311329118} p 519 A94-60182 WIND TUNNEL APPARATUS Incipient torsional stall flutter aerodynamic experiments Langley 14- by 22-foot subsonic tunnel lest engineer's on three-dimensional wings data acquisition and reduction manual I BTN-94-EIX94341338362 J p 522 A94-60354 INASA-TM-4563 ] p 526 N94-35246 Unsteady separation experiments on 2-D airfoils. 3-D WIND TUNNEL CALIBRATION wings, and model helicopter rotors p 524 N94-34967 Flow quality studies of the NASA Lewfs Research Center WING PLANFORMS Icing Research Tunnel Tail load calculations for light airplanes {NASA-TM-106545J p 543 N94-34g19 {BTN-94-EIX94311329148] p 517 A94-60152 WIND TUNNEL MODELS Aerodynamic properties of crescent wing pianforms A comoined approach to buffet response analyses and [ BTN-94-EIX943113291461 p517 A94-60154 tatigue life prediction p 551 N94-34587 Aerodynam,c design of super maneuverable aircraft p 533 N94-34617 Dynamic tests to demonstrate lateral control using WING TIP VORTICES forebody suction on large scale models in the DRA 24 Numerical modeling stud;es of wake vortex transport foot wind tunnel p 539 N94-34613 and evolution within the planetary boundary layer The sumulatlon of a propulsive jel and force INASA-CR-1960781 p 529 N94-35522 measurement using s magnetically suspenOeO wind tunnel WINGS model p 527 N94-35855 Supersomc transport wing minimum weight design Flutter suppress, on digital control law design and testing integrating aerodynamics and structures for the AFW wind tunnel model p 540 N94-35873 IBTN-94-EIX94311329123) p 518 A94-60177 WIND TUNNEL NOZZLES Vortex-wing interaction of a close-coupled canard Coniugate conduction-convect,on heat transfer with a configuration high-speed boundary layer (STN-94-EIX94311329121 } p 519 A94-60179 I BTN-94-EIX94311330652 J p549 A94-60139 Omithopter wing design A supersonic tunnel for laser and flow.seeding {BTN-94-EIX94331337499} p 521 A94-60334 techniques Risk analysis of the C-141 WS405 inner-to-outer w_ng [NASA-TM-106588} p 556 N94-35945 Ioint p 531 N94-34592 WIND TUNNEL TESTS Design oriented structural analysis Experimental investigation of counter-rotating propfan {NASA-TM-109124J p 551 N94-34722 flutter at cruise conditions Ground vibrabon test of the XV-15 Tiftrotor Research JBTN-94-EIX94321333310J p 516 A94-60042 Aircraft end pretest predictions p 541 N94-35972 Alleviation of side force on tangent-ogive forebodies WORKLOADS (PSYCHOPHYSIOLOGY) using passive porosity The influence of data Iink-prov_ed graphical weather I BTN-94-EIX94311329126 } p 536 A94-60174 on pilot decision-making Proouls,on-induced aerodynamic effects measured wTth [AD-A278871} p 556 N94-35596 s full-scale STOVL model Direct reduced otder mixed H2/H infinity control fo¢ the { BTN-94-EIX94311329120 J p519 A94-60180 Shorf Take-Off and Landing/Maneuver Technology Quantitative low-speed wake surveys Demonstralor (STOL/MTD) I BTN-94-EIX943113291131 p520 A94-60187 {AD-A2786751 p 540 N94-35796 Incipient torsional stall flutter aerodynamic expenmenta Final-Approach Spacing Aids (FASA) evaluation for on three-dirnenslonal wings tarminal-erea, time-_ air traffic control IBTN-g4-EIX94341338362} p 522 A94-60354 { NASA-TP-33991 p 529 N94-36048 Aerodynamic characteristics of the HL-20 {BTN-g4-EIX94351137055} p 544 A94-60395 A combined approach to buftet response analyses and X fatigue life Wedict_on p 551 N94-34587 X-29 AIRCRAFT Dynamic tests 10 demonstrate lateral control using forebody suction on large scale models in the DRA 24 Buffet-induced structurellflight-controi system interaction of the X-29A iurcreft foot wind tunnel p 539 N94.34613 Flow quality studies of the NASA Lewts Research Center ISTN-94-EIX94311329137] p 517 A94-60163 Icing Research Tunnel Damage toferance management of the X-29 vertical [NASA.TM-106,545J p 543 N94.34919 tail p 531 N94-34595 X-31 AIRCRAFT Unsteady separation experiments on 2-D airfoils. 3-D wings, and model helicopter rotors p 524 N94.34967 X-31A system identification app_iad to post-stall flight: Mechanisms of flow control with the unsteady bleed Aeroo*ynamms and thrust vectonng p 540 N94-34619 technique p 525 N94-34987 X-31 tactical utility: Initial results p 533 N94-34620 The aerodynamic and heat transfer effecls of an endwall XV-15 AIRCRAFT Ground vibre_on test of the XV.15 Tiltrotor Research boundary layer fence in a 90 degree turning square duct lAD-A278903} p 553 N94-35803 AirQ'att and pretest predictions p 541 N94-35972 The simulation of s prOpulsNe let and force measurement using a magnetically susqended wind tunnel Y model p 527 N94-35855 Flutter suppression digital control law design and tasting YAW for the AFW wind tunnel model p 540 N94-35873 Yew control by tangential fo_ebody blowing Wind tunnel measurements on s full-scale F/A-18 with p 539 N94.34615 a tangentially blowing slot -- conducted in the Ames 80 Study findings on the influence of maneuverability end by 120 IDOl wind tunnel p 527 N94-35965 agility on helloopter handling qualihes F/A-t 8 forebody vortex control. Volume 1: Stalin tests p 533 N94-34624 (NASA-CR-4582} p 525 Ng4-35991 YAWING MOMENTS WIND TUNNELS Yaw control by tangential forebody blowing Control ol leading-edge separation on a cambered delta p 539 N94-34615 wing p 539 N94,34616 Wind tunnel measurements on s full-scale F/A-18 with Nahonal facilitms study Volume 2A: Facility Study Office a tangentially blowing slot -. conducted in the Ames 80 on the Natlooal Wind Tunnel Complox by 120 foot wind tunnel p 527 N94-35965 INASA-TM-1098561 p 542 N94-34634 Y'n'RIUM OXIDES WIND TURBINES Processing yttrium bahum copper oxide superconductor Dynamic eeroelastic stability of vertical-axis wind in near-zero gravity turbines under constant wind velocity [BTN-94-EIX94311332375 } p 550 A94-60951 {BTN-94-EIX94321333311 } p 548 A94-60043 WIND VELOCITY Dynamic aeroelestic stability of vertical-axis wind Z turbines under constant wind velocity |STN-94-EIX94321333311] p 548 A94.60043 ZINC ALLOYS WINDOWS Effect of coarse second phase pemcJes on fatigue creck Measurement and prediction of dynamic temperatures propagation ot an AI-Zn-Mg-Cu alloy in unsymmetncally cooled glass windows { BTN-94-EIX94301320144 } p 546 A94-60853 {BTN-94-EIX94351142128} p 550 A94-60421 WINDSHIELDS Human factors evaluation of the HL-20 full-scale model {BTN-94-EIX94351137065} p 545 A94-60405 A-21 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING / A Continuing Bib/iography (Supplement 308) September 1994 Typical Personal Author Index Listing ANIL, K. N. BARRY, MATTHEW Preliminary investigations on improving art-augmented Vista goes online: Decision-anelytic systems for real-time rocket performance decision-making in mission control p 558 N94-35063 [BTN-94-EIX94321333323] p 544 A94o60274 BARTHELEMY, J.-F. M. JPERSONAL AUTHOR J ANSELL, HANS Supersomc transporl wing m,nimum weight design Fatigue management and venficabon of airframes integrating aerodynambcs and structures p 531 N94-34591 [STN-94-EIX94311329123} p 518 A94-60177 ARAI, TAKAKAGE BAUER, STEVEN X. S. ANDRISANI, DOMINICK, II Injection of bubbling liquid jets from multiple inJectcrs Alleviation of side force on tangent-oglve focebodies A feasibility study regarding the ack:litiortof a fifth control into a supersonic stream using passNe porosdy s roforcrafl in-flight simulator [BTN-94-EIX94321333316] p 520 A94-60267 (BTN-94-EIX94311329126J p 536 A94-60174 ARDONCEAU, P. L BAUHOF, CHRISTINA R. ATM and FIS data link services A-CR- 193240] p112 _,.._ Aerodynamic properties of crescent wing pianforms {BTN-g4-EIX94311329146] p 517 A94-60154 IBTN-94-EIX94331335533] p 530 A94-60214 ARNETTE, STEPHEN A. BAVA, RENZO INUMBERI (NUMBER I I NUMBER { Expansion effects on supersonic turbulent boundary Operationsl agility assessment with the AM.X aircraft layers p 534 N94-34626 I AD-A2789891 p 527 N94-35950 BEH, H. ARRINGTON, E. ALLEN X-31A control law design p 540 N94-34618 Listings in this index are arranged alphabetically Flow quality studies of the NASA Lewis Research Center BELCHER, P. J. Control strategies for space boosters using aw collection by personal author. The title of the document Icing Research Tunnel [NASA-TM-106545] p 543 N94o34919 systems is used to provide a brief description of the ARYA, S. PAL IBTN-94-EIX94311330685J p 543 A94-60106 subject matter. The report number helps to Numencal modeling studies of wake vortex transport BELL, J. H. indicate the type of document (e.g., NASA and evolution within the planetary boundary layer Fhght tesbng of a luminescent surface pressure sensor report, translation, NASA contractor report). The INASA-CR. 196078 ] p529 N94.35522 (NASA-TM-103970] p 522 N94-35394 page and accession numbers are located ASHILL, P. R. Control of leading-edge separation on a cambered delta BELL, R. P. beneath and to the right of the title. Under any wing p 539 N94-34616 R_,k enatys=s of the C-141 WS405 inner-to-outer tmng one author's name the accession numbers are ATWOOD, DAVID Joint p 531 N94-34592 arranged in sequence. Unleaded AVGAS program BENAROYA, HAYM lAD-A278650] p 547 N94-35795 Invesbgetion of Monte Carlo simulation in FAA program AYERS, B. KRASH Forebody vortex control for wing rock suppression [BTN-94-EIX9431t329128J p 536 A94-60172 { BTN_g4-EIX94311329119 ] p530 A94-60181 BERKOWITZ, BRIAN A AYERS, BERT F. Prediction of ice shapes and their effect on air/oil drag F/A-18 forebody vortex control. Volume 1: Static tests [RTN-94-EIX94311329115 ] p519 A94-60185 ABREGO, ANITA (NASA-CR-4582] p 528 N94-35991 BERNHARDT, J. Ground vibration test of the XV-15 Tiltrotor Research Mechanisms of flow control w_th the unsteady bleed Aircraft and I_etest predictinfts p 541 N94-35972 B technique p 525 N94-34987 ACHARYA, M. BIGGERS, SHERRILL B. Shear 10tcklieg response of tailored composite plates Mechanisms of flow control with th,e unsteady bleed BACHMANN, GLEN R. (BTN-94-EIX94301316000J p 549 A94-60256 technique p 525 N94.34987 Robusl control des_n techniques for active flutter BIRCKELBAW, LOURD(S G. ACHARYA, MUKUND suppres_on p 541 N94-35875 Piloted s_mulabon study of two tilt-wing control The unsteady pressure field and vorticity productiien at BAILEY, ALBERT W. concepts p 541 N94-35962 the sucbon surface of a pdching airfod Thrae-o_mens,,onal thermal ermlyl,s for laser-structural BIRKAN, M. A. p 524 N94-34972 interactions AFOSR Contractors Propula_K)nMeeting ADAM, EUGENE C. [BTN-94-EIX94351142117 ] p560 A94-60410 JAD-A279028 ) p 539 N94-35746 Tactical cockpits: The coming revolution BAILEY, MELVIN L BISWAS, RUPAK [BTN-g4.EIX94331335530] p 530 A94-60211 Effect of HI-to-drag ratio in pilot rating of the HL-20 Computabon of helicopter roter aCOUStiCs in forward landing task AHMED, S. flight {BTN-94-EIX94351137057] p 544 A94-60397 [NASA-CR-196132} p 560 N94-36031 ReaHachment studies of an oscillating airfoil dynan_c stall llowfield BAli.LIE, STEWART W. BITTERMANN, VINCENT [BTN-94-EIX94301315980] p 515 A94-60016 Evak_tion of the dynem, cs and handling quality FINDER, A system providing comp4ex decismn support characteristics of the Bell 412 HP hel_er for o0mmercml transpoct replann{ng operations Comparison of pitch rate I',story effects On dynamic (BTN.94-EIX94331337502 ] p530 A94-60337 [BTN-94-EIX94331335529| p 549 A94-60210 stall p 535 N94-34968 BALAKRISHNAN, G. BJARKE, I.. AL-MOUFADI, S. Tudoukmt combustion regimes for hyperson¢ propulaie_ Fkght testing of a luminescent surface pressure Drag reduction of airplane fuselages through shaping employmg hydrogen-eir diffusion flames serieor by the inverse method [BTN-94-EIX94321333324| p 546 A94-60275 [NASA-TM-103970] p 522 N94-35394 IBTN-94-EIX94311329117] p 536 A94-60183 BARANKIEWlCZ, WENDY S. BLOM, A. F. ALCORN, CHARLES W. Approximate simdanty pnncipie for a full-scale STOVL Fabgue management and venfcabon ol airframes Boundary-layer influences on the subso¢_ic near-wake electer p 531 N94.34591 of bluff bodies [BTN-94.EIX94341338360] p 550 A94-60352 BOCHMANN, R. BARCIO, JOSEPH JBTN-94-EIX94311329138 ] p517 A94-60162 The role of fatigue analysis for design of military Mission Evaluation Room Intelligent Dmgnost)c end aircraft p 531 N94-34594 ALFORD, R. E. Analysis System (MIDAS) p 558 N94-35064 BOKMA, A. Risk analys_s of the C-141 WS405 inner-to-outer wing BARCLAY, REBECCA O. Engineering large-scale agent-based systems with joint p 531 N94-34592 NASA/DOD Aerospace Knowledge Diffusion Research consensus p 558 N94-35071 ALPAY, S. P. Protect. Paper 42: An enahtsis of the transfer of Sc_mtif¢ BOLLER, CHR. Effect of coarse second phase perlJclos on fatigue crack and Tecrncst Inlormabon (STI) in the US aerospace NOtCh fabgue assessment of iwcraff components umng pro_oagabon of an AI-Zn-Mg-Cu alloy industry a fracture mechamcs based parameter [BTN-94-EIX94301320144 ] p 546 A94-60653 (NASA.TM-109863J p 560 N94-34730 p 551 N94-34588 BARNETT, M. BOOKs, MARTIN ANDERSON, RAYMOND J. Departure sokJtions of the unsteady thin-layer and full Hot gas ingestion effects on fuel control surge recoven/ Scheduled maintenance optimization system Navier-Stokes equations solved using strearvdine curvature end AH-I rotor drive tr_n torque s_kes {BTN-g4-EIX94311329145] p 517 A94-60155 based iteration technKlueS p 552 N94-34980 INASA-CR-191047] p 538 N94-34993 ANDO, SHIGENORI BARRETT, TIM BORCHERS, PAUL F. Systematic computation scheme of PAR.WIG cruising Electromechanical simuletion and test of rotating YAV-aB reaction control system bleed and control power performance systems with magnetic beanng or piezoelectric ectuato( usage in hover end transition {STN-g4-EIX94361135427 ] p521 A94-60624 actlve vibration control p 555 N94-35905 [NASA-TM-104021 ] p 540 N94-34994 B-1 PERSONAL AUTHOR INDEX BOSE, NElL BOSE, NElL CAPRON, WILLIAM R. COLLICOTT, STEVEN H. Explicit Kutta condition for an unsteady two-dimensional Final-Approach Spacing Aids (FASA) evaluation for Surface interference in Rayleigh scattenng constant potential panel method terminal-area, time-based air traffic control measurements near forebodles IBTN-94-EIX94301315990J p 515 A94-60026 INASA'TP'33ggJ p 529 N94-36048 IBTN-94-EIX943013f59991 p 516 A94-60035 BOUSMAH, WILLIAM G. CARABELU, STEFANO COHDON, STEVE An examination of the aerodynamic moment on rotor Design, construction, and testing of a five ectwe axes Cost and schedule estimation study report blade tips using flight test data and analysis magnetic hearing system p 554 N94-35846 INASA.CR.189344 j p 558 N94-35256 INASA.TM.f04006] p 523 N94.34948 CARR, LAWRENCE W. COOK, A. B. BRITCHER, COLIN P. Physics of Forced Unsteady Separation Artificial neural networks for predicting nonlinear Boundary-layer influences on the subsonic near-wake INASA.CP.3144} p 552 Ng4-34966 dynamic helicopter loads of bluff bodies Comparison of pitch rate history effects on dynamic [BTN.94-EIX94301315989] p 515 A94-60025 IBTN-94-EIX94311329138) p 517 A94-60162 stall p 535 N94-34968 CORD, THOMAS J. The quest for stall-free dynamic lift Second Internabonal Symposzum on Magnetic Flying qualities evaiuabon maneuvers p 525 N94.34986 p 533 N94-34623 Suspension TechnOlogy, part 2 CARRAWAY, DEBRA L fNASA-CP-3247-PT-2) p 546 N94-35902 CORLISS, LLOYD D. Active thermal isoiabon for temperature responsive BROWN, GERALD Piloted s_muletion study of two tilt-wing control sensor. Electromechanioal simulation and test of rotating concepts p 541 N94-35962 INASA.CASE.LAR.14612-1J p 552 N94.35074 systems with magnetic hearing or piezoelectric actuator COULTER, YATES CARTA, FRANKLIN O. active wbcatK)n control p 555 N94-35905 Processing yttrium barium copper oxide superconductor Incipient torsmnel stall flutler aerodynan_c experiments in near-zero gravity BROWN, T. A. on three-climens_Dnal wings [ BTN-94-EIX94311332378 ] p550 A94-60951 Effect of lndiel acceleration on the development of the IBTN.94-EIX94341338362 ] p 522 A94-60354 flow field of an airfod pitching st constant rate Unsteady separation experiments on 2-D airfoils, 3-D CRAWFORD, DANIEL J. p 526 N94.34989 wings, and model helicopter rotors p 524 N94-34967 Final.Approach Spacing Aids (FASA) evaluation for terminal-area, time-based air traffic control BRUCKNER, ROBERT J. CASWELL, RUTH A supersonic tunnel for laser and flow-seeding Control of maglev vehicles with aerodynamic and [NASA-TP-3399] p 529 N94-36048 techniques guidewsy disturbances p 554 N94.35842 CREDEUR, LEONARD INASA-TM-106588J p 556 N94.35945 CAZES, R. J. Final-Approach Spacing Aids (FASA) evaluation for BRUNE, G. W. Assessment of in-servtce aircraft fatigue monitoring terminal-area, time-based air traffic control QuanMative low-speed wake surveys ;xocess p 531 N94.34593 |NASA-TP-339g ] p 529 N94-36048 [BTN-94-EIX94311329113J p 520 A94-60187 CEBECl, TUNCER CROWTHER, W. J. BRUNO, THOMAS J. Predmboa of ice shapes and their effect on aidoll drag Yaw control by tangential forebody blowing Measurement of diffusion in fluid systems: Aoplmabons [BTN.94-EIX943t1329t15] p 519 A94-60185 p 539 N94-34615 to the supercritical fluid reg00n Prediction of unsteady airfoil flows at large angles of CRUZ, CHRISTOPHER I. [BTN-94-EIX94311330660 ] p 548 A94-60131 incidence p 525 N94.34975 Aerodynamic characteristics of the HL-20 BUCHACKER, E. CHANORASEKHARA, M. S. [BTN-94-EIX943511370551 p 544 A94-60395 EFA flying qualibes specification and Its utiliution Reattac_t studms of an oscillating airfoi_ dynamic CUI, JIVA stall ftowtiald p 5,33 N94-34621 Computation and discussion of a needy constant degree [ BTN-94-EIX94301315980 ] p515 A94-60016 BUDERATH, M. of reaction turbine stage Comparison of i_tch rata history effects on dynamic Notch fatigue assessment of akoraft components using [BTN.94-EIX94351144987] p 537 A94-60449 stall p 535 1'494-34968 a fracture mechanics based parameter CURRIER, JEFFFIEV CHAPMAN, DEAN R. p 551 N94-34588 Computed unsteady flows of airfofls at tugh incidence Investigabon of Bumett equabons for two-dimena_onal BUELOW, PHIUP E. p 525 N94-34975 hypersonic flow Three-dimensional upwind parabofized Navmr-Stokes CUTCHINS, MALCOLM A. lAD-A278942] p 527 N94-35717 Joined-wing model vipratk_'ts using PC-based modal code for supersonic combustion ltowhelds CNENo H. N. testing and finde element analysis IBTN-94-EIX94351142134] p 521 A94-60427 Prediction of unsteady airfoil flows at large angles of [BTN-94-EIX94311329141] p 517 A94-60159 BURCHAM, F. W., JR. incidence p 525 N94.34978 CUY, MICHAEL D. Flight testing a Wopulsion-controllad aircraft emergency CHEN, HSUN H. Hot Corrosion Test Facility at the NASA Lewis Specml flight control system on an F-15 airplane Prediction of ce shapes and their oftect on airfoil drag Protects Laboratory INASA-TM-4590] p 540 N94.35258 |BTN-94-EIX94311329115] p 519 A94-60185 [NASA-CR.195323] p 543 N94.35267 BURKEN, JOHN CHICATEUJ, AMY K. Fhght testing a propulsion-controlled aircraft emergency Computational methods for HSCT-inlet controfs/CFD flight control system on an F-15 lurplane interdisciplinary research D [NASA-TM.4590] p 540 N94-35258 [NASA-TM-106618) p 539 N94-35352 BURSTER, KATHRYN E. CHiOU, CHENG-YI DAMODARAN, K. A. Technology and staging effects on two-stage-to-orbit Aircraft landing 9ear po=dtionmg concerning Bbnownal Pretiminary investigations on impro'wng air-4ugmentad systarP_ landing cases rocket performance IBTN-94-EIX94311322891 ] p520 A94-60205 IBTN-94-EIX94311329140] p 536 A94-60160 [BTN-94-EIX94321333323] p 544 A94-60274 BUSH, LANCE B. CHRISTENSON, T. R. DAY, DELBERT E. Technology and staging effects on two-stage-to-od_ Planar rotational magnetic mioromotors with integrated Processing yttrium barium copper oxide superconductor systems =d'_ft ancod_ and magnetic rotor levitation in near-zero gravity [ BTN-94-EIX94311322891 } p520 A94-60205 p 555 N94-35907 IBTN-94-EIX94311332378] p 550 A94-60951 CHUBACHI, TATSUO Preliminary structural evaluation and design of the DAY, I. J. HL-20 Effects of propeller on the turning of old fighters Axial compressor per'formance during surge [BTN.94.EIX94361135426) p 537 A94-60623 [ BTN-g4-EIX94351137060 ] p 545 A94-60400 |BTN-94-EIX94321333308] p 548 A94-60040 CHUNG, JOONGKEE DEKER, GUY BUSSOLARI, STEVEN R. Computationll methods for HSCT-intet contr_slCFD FINDER, A system providing complex decision support The influence of data 5nk-provided graphical weather inte_qis_plinery research for commarcleJ transport replanning operabone on I_lOt decismn-making [NASA-TM-t06618] p 539 N94-35352 |AD-A278871 ] p 556 N94-35596 [BTN-94-EIX94331335529] p 549 A94-60210 CITURS, KEVIN D. DELANEY, R. A. Flying qualities evaluation maneuvers Vine-blade interaction in e transonic turbine. Parl 1: C p 533 N94.34623 Aerody_m,cs CLARKE, ROBERT [BTN-94-EIX94321333305] p 516 A94-60037 Buffat-inckJCed sthJcturel / ftight-control system DELAURIER, JAMES D. CABEI.L, R. H. interaction of the X-29A aircraft Ornithopter wing destgn Artificial neural networks for predicting nonlinear [BTN-94-EIX94311329137] p 517 A94-60163 [BTN-94-EIX9433t337499) p 521 A94-60334 dynamo heFioopter loads COCHRAN, J. IL DELPRETE, CRISTIANA [BTN-94-EIX94301315989 ] p515 A94-60025 RiSk analy_s of the C-141 WS405 innar-to-outar wing Deugn, construction, and testing of a live active axes CALKINS, D. E. joint p 531 N94-34592 magnati¢ bearing system p 554 N94-35846 Aimraft accident flight bath simu_tion and animation COEN, P. G. DEMANDANTE, C. G. N. [BTN-94-EIXB4311329129 ] p518 A94-60171 Supersonic transport wing minimum weight design Flight testing of a luminescent surface pressure CALVERT, J. F. integrating esrodynan'ncs and structures SerlSOr Apptmabon of centrifuge based dynamic fl0ghtsimulation [ BTN-94-EIX94311329123 ) p518 A94-60177 [NASA.TM-103970] p 522 N94.35394 to enhanced maneuverability ROT/E COHEN, D. 0ERSHOWrrz, ADAM p 541 N94-34630 Analysis of muftifestener costa joints The influence of data link-provKled grspr_'.sl weather CALVERT, JEFFREY F. [ BTN-G4-EIX94311330690 ] p548 A94-60101 on pilot dacmlon-making Aoplmation of current dopart_'e r_kbtanoe criteria to COLE, GARY L [AD-A278871] p 556 N94-35596 the pOSt-stall menoetJv/mng envelope ComqutaiJonal methods for HSCT.inlet controfs/CFD DE,S_, MIHIR p 533 N94-34622 inter¢li_plirmry research Hot gas ingestion effects on tuet control surge recovery CAMARERO, RICARDO [NASA-TM-106618] p 539 N94-35352 and AH-1 rotor drive train torque slakes Three--dimen_l closure of the passage-averaged COLE, RODNEY F- _NASA-CR.191047] p 538 N94-34993 vorticdy.potent=al formulation Teresnel Doppler Weather Radar (TDWR) Low Level DIRUSSO, ELBEO [BTN-94-EIX94301315991] p 547 A94.60027 Wind Shear Alert System 3 (LLWAS 3) integration studies Electromechsnical simulation and test Of rotating CARTER, DAVID E. at Odando Intarnabonal Airport systems with magnetic bearing or pmzoelectnc actuator X-31 tactm.al utility: Initial results p 533 N94-34620 [AD-A,278957 ) p 557 N94-35807 active vibration control p 555 N94-35905 B-2 PERSONAL AUTHOR INDEX HANKEY, W.L. DOVI, A. R. FARLEY, GARY L GHOSH0 A. K. Supersonic transport wmg ms=mum weJght design Field deployable nondestructive impact damage Parameter estimates of an aeroelastic aircraft as integrating aerodynamics and structures assessment methodology for composite structures affected by model szmplificat=ons IBTN-94-EIX94311329123] p 518 A94-60177 I BTN-94-EIX94301321378 ] p 546 A94-60892 IBTN-94-EIX94311329142J p 517 A94-60158 DOWNER, JAMES FERRARAo AUGUSTO GILES, GARY L Aerospace applications of magnetic hearings Unleaded AVGAS program Design ormented structural analysis p 554 N94-35837 lAD-A278650} p 547 N94-35795 {NASA.TM-109124] p 551 N94-34722 DOWNS, CORNELL FIELD, ROBERT E. GNOFFO, PETER A. User's guide lot an interactive personal computer Measurement and prediction of dynamic temperatures Coupled radiation effects in thermochemtcal inter'lace for the aeroprechct_on code nonequilibnum shock-captunng flowfmld calculations in unsymmetrically cooled glass wmdows { NSWCDD/TR.94/107 ] p559 N94-35958 [BTN-94-EIX943511421281 p 550 A94-60421 I BTN.94-EIX943113306481 p559 A94-60143 DOYLE, JAMES F. GOLDIE, JAMES FIELDING, C. Aerospace applications of megnel¢ hearings Frequency domain analysis of the random loading of Design of integrated flight and powerplant control p 554 N94-35837 cracked panels systems p 532 N94.34609 t NASA-CR-196021 I p 556 N94-35974 FLEETER, SANFORD GOMUC, R, Structural integnty and containmenl aspects of small DUCKEI"F, SOPHIE Comparison of optical measurement techniques for gas turbine engines 1993 Techmcal Paper Contest for Women. Gear Up turbomachinery flowfietds [BTN-94-EIX94331337500] p 550 A94-60335 2000: Women in Mormon IBTN-94-EIX94341338357J p 559 Ag4-60349 GONDHALEKAR, VIJAY {NASA-CP-10134] p 561 N94-35961 FLEISNER, HOWARD J. Aerospace epphcatlons of magnetic bearings DUDA, H. Invesbgabon of Monte Carlo simulation in FAA program p 554 N94.35837 EFA flying qualities specification and its uttlis_ilJon KRASH GOODYER, M. J. p 533 N94-34621 [BTN-94.EIX94311329128] p 536 A94-60172 The simulation of a propulsive jet end force DUKE, M. R., JR. FLORES, LOUIS measurement uSmg a magnetically suspended wind tunnel Numencal invesbgat=on of cylinder wake flow with a rear Mission Evaluation Room Intelligent Diagnostic and model p 527 N94-35855 stagnation jet AnalySis System (MIDAS) p 558 N94-35064 GORDRIER, RAYMOND E. [BTN-94-EIX943013159981 p 547 A94-60034 FLOWERS, GEORGE T. Crossflow t01_ology Of vorbcal flows DULIKRAVlCH, GEORGE S. Influence of backup hearings and support structure [BTN-94-EIX94301315993] p 515 A94-60029 dynamics on the hehawor of rotors with acbve supports Inverse design of SUl:_r-elliotic cooling passages in GOUTERMAN0 M. coated turbine blade aJrtods INASA.CR.196119) p 553 N94-35500 FLUECKIGER, KARL Fkght tasbng of a luminescent surface pressure IBTN-94-EIX94311330654 J p 548 A94-60137 sensor Control of maglev vehicles with aerodynam¢ and DUMITRESCU, LUClEN Z. g_deway disturbances p 554 N94-35842 [NASA-TM-103970] p 522 N94-35394 Wake curvature and airfoil lift FLYNN, W. A. GRANDHI, R. V. [BTN-94-EIX94311329147J p 517 A94-60153 F.16 uncommended pitch oscillation Control strategies for space boosters using air collection DUNN, M. G. systems [BTN-94-EIX94331337501] p 530 A94-60336 Vane-blede interaction in a transonic turbine. Pert 1: FREYMUTH, PETER [BTN-94-EIX94311330685J p 543 A94-60106 Aerodynamics GRAY, DAVID L Concepts and application of dynamic separation for I BTN-94-EIX94321333305 ] p516 A94-60037 egikty and super-meneuverabildy of aircraft: An Active thermal isolation for temperature responsNe DUQUE, E. sensors assessment p 535 N94-34988 [NASA-CASE-LAR-14612-1 J p 552 N94-35074 The quest for stall-free dynamic lilt FRIEDMANN, PERETZ P. p 525 N94-34986 Selected topics on the active control of helicooter GREENE, FRANCIS A. eeromechanical and vibrabon problems HL-20 compt,tatK_nal fluid dynamics enalys*s p 541 N94-35874 {BTN.94-EtX94351137059J p 545 A94-60399 GRIFFIN, O. H. JR. E FU, JAN.KAUNG Drag reduc:tJon of turbulent flow over a proiiecble, part Ana_s of multffaslener composde joints EDWARDS, GERALDINE F. 1 I BTN-94-EIX94311330690 ] p 548 A94-60101 GROOM, NELSON J. Dynamic tests to demonstrate lateral control using [ BTN-94-EIX94311322899 ) p 557 A94-60197 torebo<:ly SUCtK)n on large scale models in the DRA 24 FU, JAN-KUANG Second IntamatK)nal Symposium on Magnetic Su_oert_won Technology, part 2 fool wmd tunnel p 539 NS4-34613 Drag reducbon for turbulent flow over a pro_Bc'tile, part EKATERINARIS, J. 2 |NASA-CP.3247.PT-2} p 548 N94-35902 GROVES, ALLEN W. Computation of unsteady flows over airfoils IBTN-94-EIX94311322900] p 520 A94-60196 X-31 tactical ulility: Initial results p 533 N94-34620 p 525 N94-34977 FULLER, C. R. GUCKEL, HENRY ELBEL K. Artificial neural networks for predicting nonlinear Planar rotational magnetic mK_romotors with integrated EFA flying qualities speciticatK)n end its utilisation dynamo helioopter loads shaft encoder and megnebc rotor levftation p 533 N94-34621 IBTN.94.EIX94301315989] p 515 A94-60025 p 555 N94-35907 ELRER, W. FUNG, K.-Y. GULATI, ANIL Computed tmstaady flows of airfoils at high incidence Rotorcraft fatigue lite-prediction: Past. present, and Ramen measurements at the exit of a combustor p 525 N94-34975 future p 551 N94-34590 nactor ELUOTT, GREGORY S. [BTN-94-EIX943413383561 p 546 A94-60348 Expansion effects on supersonic turbulent boundary G GUPTA, S. S. layers Structural integrity end cont_lunment aspects Of smell lAD-A278989] p 527 N94-35950 GALLERY, J. gas turbine engmes ENGELUND, WALTER C. Flight testing o1 a luminescent surface pressure [ BTN-94-EIX943313375001 p 550 A94-60335 Technology and staging effects on two-stage-to-orbit sensor GURBUZ, R. systems [NASA-TM-103970) p 522 N94-35394 Effect of coarse second phase particles on fabgue crack IBTN-94-EIX943113228911 p 520 A94-ro0205 GARBUTT, K. S. propagation of an AI-Zn-Mg-Cu alloy ENNIX, KIMBERLY A. The swnutation of a propui_ave let and force [BTN-94-EIX94301320144] p 546 A94-60853 Engine exhaust characteristics evaluation in support of measurement using a magnetically suspended wind tunnel GURSUL iSMIET aircraft acoustK:; tesbng p 560 N94-35963 model p 527 N94-35855 Unsteady separation process and vortmity balance on ERICSSON, L E. GARON, ANDRE unsteady air/oils p 524 N94-34970 GURUMOORTHY, R. Will the real dynamic instability mechanism please be Three-dimens, onal closure of the passage-averaged recognized! p 552 N94-34978 vortcity-botantial formuletion Modelling end control of a rotor supported by magnetic {BTN.94-EIX94301315991 ] p 547 A94-60027 hearings p 554 N94-35858 E_'INA, J. GARWOOD, K. R. Fkght testing of a luminescent surface pressure sensor Engme characteristics for agile a_'craft H I NASA-TM- 103970 } p 522 N94-35394 p 538 N94-34608 GE, YUNOI EVERETT, RICHARD A., JR. HAINES, MATTHEW Experimental investigation on supersor_c combustion Rotorcraft fatigue lite*predictlon: Past, present, and (2) Runtime _ for data parellel tasks future p 551 N94-34590 IBTN-94-EIX94351144985} p 537 A94-60447 [NASA-CR-194904] p 558 N94-35240 HALL, L E. GEBERT, G./L Supersonic transporl wing ms=mum weight desKjn F Determination of slender body eerodynam*ce usiog discrete vortex methods intagralmg aerodynamics and structures [BTN-94-EIX94311330679] p 543 A94-60112 [BTN-94-EIX94311329123] p 518 A94-60177 FACAS, GEORGE N. GENTA, GIANCARLO HAMMOND, D. O. Natural convection in a cavity with fins attached to both Deign, consth_tion, and tasting of a f_e acthm axes Risk analysis of the C-141 WS405 inner-to-outer wing vertical walls magnetic bearing system p 554 N94-35846 joint p 531 N94-34592 [BTN.94.EIX94351142119] p 550 A94-60412 GHIA, K. N. HANDSCHUH, ROBERT F. FAGAN, JOHN R. Ct_ractenzation of dynemic stall phenomenon using Low-no*se, high-strength, s_rel-bevel gem for Comparison ol optical measurement techncques for two*dimensonai unsta=K_'y Navmr-Stokes equations hel¢optar transmissions turbomachiner_ flowflelds p 524 N94-34974 [BTN-B4-EIX94321333312] p 548 A94-60044 [ BTN-94-EIX94341338357 ] p 559 A94-60349 GHIA, U. HANKEY, W, L FALGOUT, JANE Charscterizabon of dynamic stall phenomenon using Control stratagies for space boosters using air collection Mission Evaluation Room Ictelhgent Diagnostic and two-dimenePonai unsteady Nevler-Stokes equations systems Analysis System (MIDAS) p 558 N94-35064 p 524 N94-34974 [BTN-94-EIX943113306851 p 543 A94.60106 B-3 HARTER, J. PERSONAL AUTHOR INDEX HARTER, J. HOLLO, S. D. KAPLAN, MICHAEL L. Damage tolerance management of the X.29 vertical Planar KrF laser.induced OH fluorescence imaging in Numencal modeling studies of wake vortex transport tail p 531 N94-34595 a supersonic combustion tunnel and evolution w_thin the planetary boundary layer HARTLEY, TOM T. [BTN-94-EIX94321333315J p 520 A94-60266 INASA.CR-196078J p 529 N94-35522 Computational methods for HSCT-iniet controis/CFD HORVITZ, ERIC KARNOWSKY, M. interdisciplinary research Vista goes online: Decision-analytic systems for real-time Planar rotational magnetic micromotors with integrated fNASA-TM-1066181 p 539 N94-35352 decisaon-meking in mission control p 558 N94-35063 shaft encoder and magnetic rotor levhation HARTMAN, KATHY R. HOY, ERIC p 555 N94-35907 Flight Mechamcs/EstimatPon Theory Symposium, 1994 Data reduction, analysis and results Of LACV-30-07 air KARPEL, M. INASA-CP-3265} p 545 N94-35605 cushion vehicle tests. For't Story, VA, August - September Time simulation of fluher with large stiffness changes 1993 HARTUNG, UN C. |BTN-94.ElXg4311329132) p 518 A94-60168 I AD-A278859 ] p 527 N94-35826 Coupled radiation effects in thermochemical Modal coordinates for aeroetastic analysis with large HU, YUU nonequdibnum shock-capturing flowfietd calcuisbons local structural variations Expenmental investigation on supersonic combustion T BTN-94-EIX94311330648 J p559 A94-60143 {BTN.94.EIX94311329131 J p 518 A94-60169 (2) HARTWICH, PETER M. KASCAK, ALBERT F. I BTN-94-EIX94351144985 ] p537 A94-60447 Symmetry breaking in vortical flows over cones: Theory Electromechanical simulation and tesl of rotating HUI, KEN and numerical experiments systems with magnetic beanng or pmzoe_ectnc actuator Evaluation of the dynamics and handling quality IBTN-94-ElXg4301315981J p 547 A94-60017 active vibrabon control p 555 N94-35905 characteristics of the Bell 412 HP helicopter HAS, DAVID B. [BTN.94.EIX94331337502J p 530 A94-60337 KASTURI, RANGACHAR Accurate estimation of obiect location in an image Direct slmuiatlen with vibration-dissociation coupling HYER, M. W. I BTN-94-EIX943511421361 p521 A94-60429 Analys_s of multifastaner composite joints sequence using helicopter flight data p 537 N94-35055 HASSAN, H. A. (BTN.g4.EIX94311330690] p 548 A94-60101 D_rect simulation with vibration-dissociation coupling HYMER, THOMAS C. KAI"rA, V. R. IBTN-94-EIX94351142136] p 521 A94-60429 User's guide for an interactive personal computer Numerical method for s,mulcting fluid-dynamic and New two-temperature dissocistio_ model for reacting interfaca for the aero_>redictJon code heel-transfer changes in jet-engine ini,ector feed-arm due flows [NSWCDD/TR-94/107] p 559 N94-35958 to fouling IBTN-94-EIX94351142137] p 560 A94-60430 [BTN.94.EIX94351142133] p 537 A94.60426 HAYNES, TIMOTHY S. I KAUFFMAN, H. G. Transition correlations m three-dimenszorml boundary Control strategms for space boosters using ak collection layers systems IBRAHIM, MOUNIR B. IRTN-94-EIX943013159681 p 547 A94-60004 IBTN-94-EIX943113306851 p 543 A94-60106 Apl_oximate similarity pnncipie for a full-scale STOVL HE, X. KAY, I. W. ejector Computational analysis of off-de_gn wavehders Structure and penetration of a supercntical fluid let in I BTN.94.EIX94341338360 ] p 550 A94-60352 IBTN-94-EIX94311329125] p 549 A94-60175 supersonic flow ING, DAN N. HECHT, LAURA F. IBTN-94-EIX94321333317] p 549 A94-60268 Computational analysis of a single jet impingement KEU..ER, J. L NASA/DOD Aerospace Knowledge Diffu,_on Research ground effect lilt less Project. Paper 42: An analysis of the transfer of Scientific [ BTN.94-EIX94311329114 | p519 A94-60186 Data requirements for ceiling and visibility products and Technical Information (STI) in the US aerospace IROOOV, R. D. developmenl industry Aerodynamic design of super maneuverable amcmft I AD-A2789591 p 556 N94-35720 INASA-TM-109863] p 560 N94-34730 p 533 N94-34617 KELLER, K. L NEMSCH, MICHAEL J. F.16 uncommanded pifch oscillation Alieviabon of s0de force on tangent-ogNe forebodles IBTN-94-EIX94331337501] p 530 A94-60336 using passive porosity J KEMPEL, ROBERT W. IBTN-94-EIX94311329126] p 536 A94-60174 Developing and flight testing the HL-10 lifting body: A HENRY, ZACHARY S. JACKSON, E. BRUCE precursor tO the Space Shuttle Low-norse, hKJh-strength, s;xral-bevel gears for Effect of lift-to-drag ratio in pilot rating of the HL.20 INASA-RP-t332] p 535 N94-34703 helicopter transmissions iand,ng t_k KENNEDY, CHRISTOPHER A. IBTN-94-EIX94321333312] p 548 A94-60044 IBTN-94-EIX94351137057] p 544 A94-60397 On the venous forms of the energy equation lora dilute, JACOBS, J. H. HERMANSON, J. C. monatomic m_xture of nonreacting gases Structure and penetration of a supe_cfitleal fluid jet in A comoined splxoach to buffet response analyses and [NASA-CR-4612] p 527 N94-35864 fatigue life I_ediotion p 551 N94-34587 supersonc flow KENNEDY, JOHN M. JANG, H. M. [ BTN-94-EIX94321333317 } p549 A94-60268 NASA/DOD Aerospace Knowledge DiflUSK)n Research HERRICK, G. T. Prediction of unsteady airfoil flows el large angles of Project. Paper 42: An anatyms of the transfer of Scientific incidence p 525 N94.34978 An overview of the F-16 service life approach and Technical Information (STI) in the US aerospace JEFFERIES, EDWARD B. p 532 N94-34599 industry Dynamic tests to demonstrate lateral control using HESS, BRYAN |NASA-TM-109863} p 560 N94-34730 forebody m_..'tion on large scale models in the DRA 24 Runtime support for data parallel 1asks KEREUUK, STAN foot wind tunnel p 539 N94-34613 NASAoCR.194904 ] p 558 N94-35240 Evaluation of the dynamcs and handling quality JENTINK, H. W. cheractermtics of the Bell 412 HP helicopter HEULER, P. In-flight veio¢ify measurements using laser Doppler Notch fatigue asseeement of aircraft components using anemometry [BTN-94-EIX94331337502| p 530 A94-60337 a fracture mechanics based barameter IBTN-94-EIX94311329139} p 549 A94-60161 KERRIDGE, S. p 551 N94-34588 JOHNSON, K. Engineering lerge-scale agent-based systems with HIGUCHI, TOSHIRO Engineering large-scats agent.based systems with consensus p 558 Ng4.3.5071 Magnetically suspended stepping metom for clean room consensus p 558 N94-35071 KESTER, RUSH and vacuum environments p 555 N94-35915 JO6YULA, ESWAR Ada developers' supplement to the recommended HILL RICHARD J. Computabon of nonerlUilibrium hypersonic ftowfields approach [NASA-CR-189345] p 557 N94-34921 Progress and purpose of IHPTET program around hemisphere cylinders KIEFER, D. p 538 N94-34607 |BTN-94-EIX94351142135] p 521 A94-60428 Application of centrifuge based dynam=c flight slmuletion HINDS, MICHAEL F. JUANG, JER-NAN tO enhanced meneuverabilify RDT/E Three-dimensional thermal analysis for laser-structural An overvmw of recent erlvences in IP/atem p 54t N94.34630 interactions identification p 546 N94.35880 KIM, CHAESIL I BTN-94-EIX943511421t 7] p560 A94-60410 JUD, JEAN-MARIE Electromechenical simulation and test of rotating NO, CHIH-MING FINDER, A system providing complex decision suppod for commercial transport replanning operations systems with magnetic bearing or piezoelectric actuator Unsteady separation process and vorticity balance on IBTN-94-EIX94331335529] p 549 A94-60210 active vilxation control p 555 N94-35g05 unsteady airfoils p 524 N94-34970 KIRKNER, D. J. HOCKNEY, RICHARD Determ0nation of tire-wheel interlace loads for a_creft Aerospace applications of magnetic bearings K wheels p 554 N94-35837 |BTN-94.EIX94311329136J p 517 A94-60164 HOOGES, G. S. KALLINDERIS, Y. KLEB, WILLIAM L En_ne cheractenstica for agile aircraft New muftigrid app¢oach for three-dimens*onal Chersctertstics of the Shuttle Od_ter kJeside flow during p 538 Ng4-34608 unstructm'ad, adaptive grids a rHntry condition HOOGKINSON, JOHN [BTN-94-EIX94301315973| p 559 A94-_0009 IBTN-94-EIX94311322888| p 520 A94-60208 The influence of flying qualities on operational agility KANDARPA, $. KLEIN, J. p534 N94-34628 Dqma-minatJon of tim-wheel interlace loads for mrcrafl Planer rotational magnetic mcmmoto_ with integcated HOFINGER, G. shaft encodar and magnetic rotor levitation X-31A control law des.,gn p 540 N94-34618 [ BTN-94-EIX94311329138 | p517 A94-60184 p 555 N94-35907 HOLDEN, MICHAEL S. KANNO, SHOKiCHI KLUSMAN, STEVE Expenmental studms of shock-wave/wall-jet interaction Effects Of prooeiler on the tucrNng Of Ofd fighters Electromechenical simulation and test of rotating in hyperso_c flow, part A |BTN-94-EIX94361135426] p 537 A94-60623 systems with magnetic beanng or pmzoetoctnc actuator INASA-CR-195957] p 523 N94-34964 KAO, AR-FU active vibration cOntrol p 555 N94-35905 Expenmental studies of transp4ratmn cooling with shock N4vler-Stokes solver for hyperson_ flew over a slender KOBAYASHI, OSAMU interact=0n in hypersonic flow, part B cone Static and dynamic fXght-path stability of awpienas [NASA-CR-t959581 p 523 N94-34965 [BTN-94-EIX94311330681 ) p 543 A94-60110 [BTN-94-EIX94361t35428) p 522 A94-60625 B-4 PERSONAL AUTHOR INDEX MONTAGUE, GERALD KOEHLER, R. UANG, SHEN-MIN MARCHAND, M. EFA flying qualities specification and its utilisation Drag reduction for turbulent flow over a protectile, part EFA flying qualities specitication and its utilisst_on p 533 N94-34621 2 p 533 N94-34621 KOOCHESFAHANI, M. M. IBTN-94-EIX94311322900J p 520 A94-60196 MARCUS, JEFFREY H. Effect of initial acceleration on the development of the Drag reduction of turbulent flow over a proijectile, part A review of computer evacuation models and their data flow held of an airfoil pitching at constant rate 1 needs p 526 N94-34989 [ STN-94-EIX94311322899 ] p557 A94-60197 { DOT/FAA/AM-94/11 I p 528 N94-35236 KRAFT, EDWARD M. LIN, HANK MARION, JEAN-DENIS USAF/AEDC aerodynamic and propulsion ground test Unsteady separation process and vorticity balance on High incidence flow analysis Over the Rafale A and evaluation techniques for highly maneuverable aircraft: unsteady airfoils p 524 N94-34970 p 522 N94.3-4612 Capabihlies and challenges p 532 N94.34606 MARK, STEVE KRAMER, B. R. UN, YUH-LANG Control of maglev vehicles with aerodynamic and Numencai modeling studies of wake vortex transport Forebody vortex control for wag rock suppression guKleway disturbances p 554 N94-35842 and evolution within the planetary boundary layer f BTN-94-EIX94311329119 J p830 A94.60181 MARTIN, THOMAS J. KRAMER, BRIAN R. I NASA.CR-196078J p 529 N94-35522 Inverse desagn of super-elliptic cooting passages in LIND, ANN-MARIE T. F/A-18 Iorebody vortex control Volume 1: Static tests coated turbine blade mrfods The influence of data link-provided graphical weather INASA-CR-4582J p 528 N94-35991 IBTN-94-EIX9431133065,41 p 548 A94-60137 KRAUSS, R. H. on pilot decismn-meking MARTINSON, SCOTT D. (AD-A278871] p 556 N94-35596 Planar KrF laser.induced OH fluorescence imaging in Actwe thermal isolation for temperature responsive a supersonic combustion funnel MTVlN, FAYDOR L sensors f BTN-94-EIX94321333318 ] p 520 A94.60266 Low-noise, high-strength, spiral.bevel gears for [NASA-CASE-LAR-14612-1 ] p 552 N94-35074 KROTHAPALU, A. helicopter transmissions MATSUSHITA, OSAMI Unsteady flow past an airfoil pitched at constant rate BTN-94-EIX94321333312) p 548 A94-60044 Third order LPF type compensator for flexible rotor p 524 N94-34969 LIU, JINGHUA suspens0o_ p 554 N94-35863 KUBAT-MARTIN, KIMBERLY A. Expenmentai investDgation on supersonic combustion MAVRIPLIS, D. J. Processmg yttrium banum copper oxide superconductor (2) A three dimensional muttigrid Reynolds-averaged in near-zero grawty BTN-94-EIX94351144985 ] p537 A94-60447 Navmr-Stokes solver for unstructured meshes IBTN-94-EIX94311332378] p 550 A94-60951 LIU, XINGZHOU INASA-CR-194908) p 528 N94-35994 KURKOV, ANATOLIE P. Expenmental investigation on supersonic combustion MCAUSTER, K. W. Expenmental investigation of counter-rotating propfan (2) The quest for stan-free dynamic lift flutter at cruise condflions BTN-94-EIX94351144985 ] p537 A94-60447 p 525 N94-34986 [BTN-94-EIX94321333310] p 516 A94-60042 LOHR, GARY W. MCCALLUM, DUNCAN FinaloApproach Spacing Aids (FASA) evaluation for Control of maglev vehicles with aerodynam.K: and L terminal-area, time-bassd air traffic control guKJeway disturbances p 554 N94-35842 NASA-TP-3399 ] p 529 N94-36048 MCDANIEL, J. C. JR. LOMBARDI, GIOVANNI Planar KrF leser-*nduced OH fluorescence imaging in LAITONE" F- V. Pressure measurements on a forward-swept a supersontc combustion tunnel Tail load calculations for light airplanes wag-canard configuration [ BTN-94-EIX94321333315 } p 520 A94.60266 (BTN-94-EIX943113291481 p 517 A94-60152 BTN-94-EIX94311329149] p 516 A94-60151 MCKAY, K. LAMB, J. PARKER LORBER, PETER F. OperatiOnal agility: An overvmw of AGARD Working A r_ and development Of correlations for base Group 19 p 534 N94-34625 Inc:ipmnt tomonal stall flutter aerodynamic experiments pressure and bass heating in superso_c flow on thme-dimenaJonel rungs MCLACHLAH, B. G. [SAND93-0280) p 526 N94-35360 BTN-94-EIX94341338362] p 522 A94-60354 Ftight testing of a luminescent surface pressure LANDIS, LINDA seneor Unsteady separation experiments on 2-D aidods. 3-D Ada developers' supplement to the recommended INASA-TM.103970] p 522 N94-35394 wings, and model helicopter rotors p 524 N94.34967 approach MEHMED, ORAL LOURENCO, L INASA-CR-189345] p 557 N94.34921 Experimental investKJation of cOunter-rotating propfan Unsteady flow past en a_oil pitched at constant rate LANSER, WENDY R. flutter af cruise conditions Wind tunnel measurements on a full.scale F/A-18 with p 524 N94-34969 |BTN-94-EIX94321333310] p 516 A94-60042 LYE, J. DAVID a tangentially blowing slot p 527 N94-35965 MEHROTRA, PIYUSH Proputsk)n-inducecl aerodynamic effects measured with LASTER, M. L Runtime support for data parallel tasks a full-scale STOVL model USAF/AEDC aerodynamic and propulsion grOund test INASA.CR-194904] p 558 N94-35240 [BTN-94-EIX94311329120] p 519 A94-60180 and evaluation techniques for highly maneuverable aircraft: MELCHER, KEVIN J. LYONS, JAMES P. Capabilities and challenges p 532 N94.34606 Computat_,_al me_ for HSCT-inlet controls/CFD Integration of magnetic bearings in the deign of LAUFER, G. interduu:_nary research advanced gas turbine en_rms p 554 N94-35903 [NASA-TM-106618] p 539 N94-35352 Planar KrF laser.induced OH fluorescence imaging in MERRICK, VERNON K. a supersonic combust=on tunnel YAV-8B reaction control system _ and control power |BTN-94-EIX94321333315] p 520 A94-60266 M usage m hover end trens_bon LAZAUER, GLEN R. ]NASA-TM.104021 ] p 540 N94-34994 USAF/AEDC aerodynamic and propulsion ground test MACCORMACK, ROBERT W. METWALLY, METWALLY H. end evaiuetx)n tachn_ues for highly maneuverable aircraft: Investigation of Bumett equations for lwo-dlmens4ch'ml The unste_y pressure held and vorticity productiion et Capabilities end challenges p 532 N94-34606 _nic flow the suction surface of a pitching airfoil LAZZERI, L. lAD-A278942] p 527 N94-35717 p 524 N94-34972 An assessment of fatigue crack growth prediction MAFTEL., CHRISTOI_IER METZGER, JOHN D. models for aerospace structures p 551 N94-345,86 Technology end stag=ng effects on two-stage-to-gall)it Feasibility study of a contained pulsed nuclear propulston LEE, NSING-JUIN systems engine Aircraft landing gear pes_t_onmg concerting abnormal [ BTN-94-EIX94311322891 ] p520 A94-60205 [BTN-94-EIX94341338369] p 559 A94-6036t landing cases MAGNESS, C. METER, J. [BTN-94-EIX94311329140] p 5:36 A94-60160 Control of leading-edge vorlJces on a delta wing Effects of the roit angle on crucifcrm wing-body LEGGETr, DAVID B. p 524 N94-34971 cantharis at high incidences Flymg quaiitms evaluation maneuvers MAIER, THOMAS N. [ BTN-94-EIX94311322903 } p520 A94-60193 p 533 N94-34623 An exemmation Of the aerod_c montent on rotor MIELNIK, JF.AN-CHRI_rOPtlE LEC._IER, HARTMLrr H. blade t_s usmg flight test data and analysis FINDER, A system provid0ng corn_olex decismn support Three-dimensional thermal analysis for testa-structural [NASA-TM-104006] p 523 N94-34948 for commerc;al tran$_oort rel_er'_ning operabons interacbons MAINE, TRINDEL A. (BTN-94-EIX94331335529) p 549 A94-60210 [BTN-94-EIX94351142117J p 560 A94-60410 Flight testing a propulmon-controtied mrcreft emergency MINUCCI, M. A. S. LEISHMAN, J. GORDON flight control system on an F-15 axplane Combustion shock tunnel and interface compress=on to Unsteady lift of a ftappecl airfoil by indiclel cormepts [NASA-TM-4590] p 540 N94-35258 increase reserv_ pressure and enthalpy IBTN-94-EIX94311329118] p 519 A94-60182 MALCOLM, O,. N. IBTN.g4-EIXg43113306S0] p 516 A94-60141 LEPICOVSKY, JAN Forebody vortex control for wing rock suq0premon MITCHELTREE" ROQERT A. iBTN-94-EIX94311329119] p 530 A94-60181 Coupled radmtion effects in t_hemical Data roducbon procedures for laser velocimetar MALCOLM, GERALD N. nom_uHlorium shock-capturing flewfmld calculebons measurements in turbomachmery rotors F/A-18 foret_ody vortex control. Volume 1: Static tests JBTN-94-EIX94311330648] p 559 A94-60143 [NASA-CR-1953.43] p 552 N94-35224 [NASA-CR4S82] p 528 N94.35991 MO, J. D. A supersonic tunnel for laser end flow-seeding MAN, S. O. Numerical kwestigabo_ of cylinder wake flow with a rear tachrNques Computed unsteady flows of anloils at high moidence stagnation [NASA-TM-106588] p 556 N94-35g,45 p 525 N94-34g75 IBTN.94-EIX94301315998] p 547 A94-60034 LEPSCH, ROGER A. MANCHAI..A, DANIEL MOLLER, H. Technology and staging effects on two-stage.to.orbit Electromechanicel simulation and test of rotating Synthetic viSiOn for enhancing poor visibility flight systems systems with magnetic bearing or pmznelectrJc actuator o_eretlone [BTN-94.EIX94311322891] p 520 A94.60205 active vibration control p 555 N94-35905 IBTN-94-EIX94331335531 ) p 557 A94-60212 LEWICKI, DAVID G. MANNING, S. D. MONTAGUE, GERALD Low-noise, high-strength, _ral-bevel gears for Aarcrafl fleet maintenance based on structural reliability Electromechenical simulation and test of rotatmg helicopter transmiss4ons anelym systems wtth magnetic beanng or p_ezoelectnc actuator (BTN-94-EIX943213333121 p 548 A94-60044 IBTN-94-EIX94311329134] p 517 A94-60166 ectwe vibration control p 555 N94-35905 B-5 MOORE, FRANK G. PERSONAL AUTHOR INDEX MOORE, FRANK G. ORIE, NETTLE M. PIERRE, CHRISTOPHE User's gu_e for an interactive personal compuler Langley 14- by 22-foot subsonic tunnel test engineer's Localization of aeroelestic modes in mistuneq interface for the aeropredictlon code data acqumition and reduction manual high-energy turbines FNSWCDD/TR-94/107 } p 559 N94-35958 |NASA-TM.45631 p 526 N94-35246 [BTN-94-EIX94321333307] p 547 A94-60039 MOORHOUSE, DAVID J. OSSWALD, G. A. PINELLI, THOMAS E. Results from the STOL and Maneuver Technology Characterization of dynamic stall phenomenon using NASA/DOD Aerospace Knov_edge Ddfusion Research Demonstrabon program p 532 N94-34611 two-dimensional unsteady Navler-Stokes equa_ons Proiect Paper 42: An analysis of the transfer of Scientific MORALEZ, ERNESTO, III p 524 N94.34974 and Technical Information (STI) in the US aerospace YAV-8B reaction control system bleed and control power OZBAY, HITAY industry usage in hover and transdK>n Robust control design techniques for active flutter [NASA-TM-109863] p 560 N94-34730 [NASA-TM-104021 ] p 540 N94-34994 suppression p 541 N94.35875 PLASTSCHKE, E. MORELLI, MAURO X-31A system identification applied to post-staff flight: Pressure measurements on a forward-swept P Aerodynamics and thrust vectonng p 540 N94-34619 wing-canard configurat=on PLATZER, M. F. Computation ot unsteady flows over airfoils IBTN-94-EIX9431132914g] p 516 A94-60151 PACK, GINGER L p 525 N94.34977 MORROW, J. W. Mission EvaluatK)n Room intelligent Dmgnosbc and An ovennew of the F-16 sennce life approach Analysis System |MIDAS) p 558 N94-35064 POPPEH, WILLIAM A. p 532 N94.34599 PAl)FIELD, GARETH D. Proputsion-mdv, cad aerodynamic effects measured with MUKHOPADHYAY, VIVEK The influence of flying qualities on operational agility a lull-scale STOVL model Flutter suppression dKj_al control law de=gn and testing p 534 N94-34628 IBTN.94-EIX94311329120] p 519 A94.60180 for the AFW wind tunnel model p 540 N94-35873 PAGEAU, STEPHANE S. POWELL, RICHARD W. MURRAY-MORGAN, J. Shear buckkng response of tailored composde plates Six-degree-of-freedom guidance and control-entry Evaluabon of the dynamics and handling qoalfly [BTN.94.EIX94301316000] p 549 A94.60256 analysis of the HL-20 charactenstics of the Bell 412 HP helicopter PAINTER, WENETH D. I BTN.94.EIX94351137056 ] p 544 A94-60396 [BTN-94-EIX94331337502] p 530 A94-60337 Developing and flight testing the HL-10 lifting body: A PRADEEP, A. K. MURTHY, DURBHA V. precursor to the Space Shuttle Modelling and control of a rotor supported by magnetic Localization of aeroetast¢ modes in mistuned [NASA-RP.1332J p 535 N94.34703 beanngs p 554 N94-35858 h_h-energy tucbmes PAL.AZZOLO, ALAN B. PRADE1"rO, J. C. IBTN-94-EIX943213333071 p 547 A94-60039 Electromechanical simulation and test of rotating Rotor dynamic behawour of a high-speed oil-free motor MYRABO, L N. systems w_th magnetic beanng or piezoelectric actuator compressor with a rig=d coupling supported on four radial CombustK)n shock tunnel and interlace corrkor_ to acbve vibration control p 555 N94-35905 magnetic bearings p 555 N94-35911 increase rese_o=r pressure and enthalpy PALONI, SERGIO PRASAD, C. B. IBTN-94-EIX943113306501 p 516 A94-60141 Operational agility assessment with the AM-X aircraft Analysis of multifastener composite Iomts p 534 N94-34626 [BTN-94-EIX94311330690] p 548 A94-60101 PAPAS, P. PRESTON, MARK A. Structure and penetrat_l_n of a su¢_rcritical fluid jet in N Integration of magnetic bearings in the design of s_0ersorac flow advanced gas turbine engines p 554 N94-35903 NAGAMATSUo H. T. [BTN-94-EIX94321333317] p 549 A94-60268 Combustion shock tunnel and interface compression to PARK, CHUL increase reservoir pressure and enthaipy Calculation of real-gas effects on aidoil aerodynamic Q [BTN-94.EIX94311330650] p 516 A94-60141 cheraclermtics NATHMAN, JAMES K. [BTN-94-EIX94351142143] p 521 A94-60436 QU, BENHE Precision requirement for potential-based panel PARLOS, ALEXAHDER G. Joined-wing model Wbcaticns uamg PC-based modal methods FeaaiblXty study of a contained pulsed nuclear propulsion testing and finite element analysis [BTN-94-EIX94301315995] p 515 A94-60031 engine IBTN-94-EIX94311329141] p 517 A94-60159 NG, T. T. [ BTN-94.EIX94341338369 ] p559 A94-60361 OUAGLIAROLI, To M. Fcrepody vortex control for wing rock supprese_on PARTHASARATHY, VMAYAN Planar KrF laser-induced OH fleocesuence imaging in IBTN-94-EIX94311329119} p 530 A94-60181 New multignd approach for three.oirmmsaonal a supersonic combustion tunnel NlrrUBICZ, CHARLES J. unstructured, adaptive grids [BTN-94-EIX94321333315) p 520 A94.60266 Apf)licabons of computational fluid dynamics to the [ BTN-94-EIX94301315973 ] p559 A94-.60009 QUINTO, P. FRANK aerodynamics of Army projectiles PASKIN, MARC D. Langley 14- by 22-foot subsonic tunnel test engineer's IBTN-94-EIX94311330678] p 516 A94-60113 Composite matnx experimental combustor pats aC(l_SdJon and reductK_n manual NITTA, K¥OKO [NASA.CR.194446] p 538 N94-34679 [NASA-TM-4563J p 526 N94-35246 Analy_s ol serodynamcs of airfoils moving over • wavy PAULEY, LAURA L wall Structure of local pressure-drwen three-dimensional R [BTN-94-EIX94311329130] p 536 A94-60170 transmnt boundary-layer separabon [BTN-94-EIX94301315979] p 515 A94-600t5 NITZSCHE, FRED RAISINGHANI, S. C. Dynamic aeroelastic stability of vertical.axis wind PEREZ, R. Parameter estimates of an aeroelaslic aircraft as A combined 8pwoach to buffet response ermlyses and turbines under constant wind velocity affected by model simplificabons [BTN-94-EIX94321333311] p 548 A94-60043 fatigue He predCtion p 551 N94-34587 |BTN-94-EIX94311329142] p 517 A94-60158 PERRY, F. S. RAO, K. V. O Harrier 2: A compansen of US and UK approaches to Vane-blade interacto') in a transonic turbine Part 1: fatigue c0earsnce p 531 N94-34596 Aerodynam_s PERUSEK, GAlL P. |BTN-94-EIX94321333305] p 516 A94-60037 O'BRIEN, W. F. Approximate similarity principle for a full-scale STOVL RASMUSSEN, M. L. Artificial neural networks for predicting nonlinear elector Computational analyms of off-des_n wavenders dynarmc helicopter loads [BTN-g4.EIX94341338360| p 550 A94-60352 IBTN-94-EIX94311329t25] p 549 A94-60175 [BTN-94-EIX94301315989} p 515 A94-60025 PETERSO_ DEAN E. NAY, RONALD J. OBERKAMPF, WILUAM L Prooaseang yttrium barium copper oxide lupercorKluofor Evaluating the dynamic response of in-f_ght thrust A review and development of correlations for base in noar-zoro gravity calculation tactm_ms during &woftle tmnsmnta pressure and base basting in supersorvc flow [BTN-94-EIX94311332378] p 550 A94-60951 INASA-TM-459t ] p 535 N94-35241 ISAND93-0280] p 526 N94-35360 PETROV, ,_ V. REDA, DANIEL C. OHARA, JOHN Aerodynamic design of super maneuverable smcraft Acbve thermal isolation for temperature responsive Fatigue design, test and in-eanm_ experience of the p 533 N94-34617 _sors [NASA-CASE-LAR-14612-1] p 552 N94-35074 BAe Hawk p 531 N94-34597 PETROVlC, JOHN J. REED, HELEN L ONTA, HIROBUMI Processing ytthum barium copper oxide superconductor Effects of prop_ler on the turrdng of old fighters in near-zero gravity Trans_Jon corralabons in three-dimens_ml boundary hlyers [ BTN-94-EIX94361135426 ] p537 A94-60623 [BTN-94-EIX943113323781 p 550 A94-60951 [STN-94-EIX94301315968] p 547 A94-60004 OLEARY, CHARLES O. PEI"rlT, DONALD R. REGARDIE, MYRNA Dynamic tests to demonstrate lateral control using Procesmng yttrium bar_Jm co_p_ oxide superconductor Cost and schedule estimatio_ study rel_,rl fcrebody suction on large scale models in the DRA 24 in near-zero gravity [NASA-CR-189344] p 558 N94-35256 toot wind tunnel p 539 N94.34613 [ BTN-94-EIX94311332378 ] p550 A94-.60951 REIF, _W OLYNICK, DAVID P. PHILUPS, WILUAM H. An agility metric structure for opan_onal agil_ New two-temperalure dissocmtion model for reacting Effects of model scale on flight characteristics and p 534 N94-34629 flows design parameters REIGEI.SPERGER, WILLIAM C., JR. [ BTN-94-EIX94351142137 ] p560 A94-60430 |BTN-94-EIX94311329143] p 517 A94.60157 D#e¢t reduced Order m_ed H21H infinity control for the ONG, L Y. PICKLrI"r, MARK T. Short Take-Off and Lending/Maneuver Technology Fcrebody vortex control for _ rock st4Rxession Flew quality studies of the NASA Lewis Research Center Demonstrator (STOL/MTD) [ BTN-94-EIX94311329119 ] p530 A94-60181 Icing Research Tunnel lAD-A278675] p 540 N94-35796 ORAl/S, RORIN [NASA.TM.106545] p 543 N94-3491g RENIER, O. 1993 Techncal Paper Conies1 for Women. Gear Up PIERACCI, A. Techniques for aerodynamic charscterizatPon and 2000: Women in Motion An assessment of fatigue crack growth prediction performance evaluation at high angle of attack INASA.CP-t0134} p 561 N94-35961 models for aerospace structures p 551 N94-34586 p 533 N94-34614 B-6 PERSONAL AUTHOR INDEX TANG, PUNAN REYNOLDS, A. P. SALVE3-rl, A. SMITH, BRIAN E. Retained mechanical propertms of a new AI-LJ-Cu-Mg-Ag An assessment of fatigue crack growth prediction Propulsion-reduced aerodynamic effects measured with alloy as a function of thermal exposure time and models for aerospace structures p 551 N94-34586 a full-scale STOVL model temperature SAMIMY, MO IBTNo94-EIX94311329120] p 519 A94-60180 JBTN-94-EIX94301320164r p 546 A94-60873 Expansion effects on supersonic turbulent boundary SMITH, C. R. RIDDLE, G. L layers Some aspects of unsteady separation Control of leading.edge separation on a cambered delta lAD-A278989] p 527 N94-35950 p 525 N94-34979 wing p 539 N94-34616 SASSUS, PIERRE SMITH, TODD E. RILEY, DAVID R. FINDER, A system provKling complex decision support Localization of aeroeiastic modes in mistuned Flying quaiibes evaluation maneuvers for commercial transport replanning operations high-energy turbines p 533 N94-34623 IBTN-94-EIX94331335529) p 549 A94-60210 [BTN-94-EIX94321333307] p 547 A94-60039 RINGEBACH, PAUL& SATO, TADASHI SOLIES, U. P. Unleaded AVGAS program Effects of Propeller on the turning of old fighters Effects of thrust line offset on neutral point determination lAD-A278650] p 547 N94-35795 ( BTN.94.EIX94361135426] p 537 A94-60623 in fhght testing RINOIE, K. SCHETZ, JOSEPH A. IBTN-94-EIX943f13291271 p 518 A94.6qt73 Experimental studies of vortex flaps and vortex plates Inlection of bubbling I¢luid _ets from multil:de injectors SOOD, DEVENDRA K. IBTN-94-EIX94311329122J p 518 A94-60178 into a supersonic stream Integration of magnetic bearings in the des_n of RIVERS, ROBERT A. I BTN-94-EIX94321333316 ] p 520 A94-60267 advanced gas turbine engines p 554 N94-35903 Effect of lift-to-drag ratio in pilot rating of the HL-20 SCHMIED, J. SPENCER, B. F., JR. landing task Rotor dynamic behawour of a hKjh-speed oil.free motor Determination of tire-wheel interface loads for aircraft IBTN-94-EIX94351137057] p 544 A94-60397 compressor with a rigid coupling supported on four radial wheels RlZZO, DEAN H. magnetic beanngs p 555 N94-35911 iBTN-94-EIX94311329136J p 517 A94-60164 The aerodynamPc and heat transfer effects of an endwafl SEGAL, LEON D. SPIEKHOUT, D. J. boundary layer fence in a 90 degree turning square duct Effects of checklist interface on non-verbal crew Reduction of fatigue load experience as part of the lAD-A278903] p 553 N94-35803 communications fatigue management program for F-16 aircraft of the ROBINSON, JAMES C. [NASA-CR.177639] p 528 N94-34915 RNLAF p 532 N94-34598 Preliminary structural evaluation and design of the SELF, A. A. SRINIVAS, SAMPATH HL-20 Drag reduction of airplane fuselages through shaping IBTN-94-EIX943511370601 p 545 A94-60400 by the rnverse method Vista goes online: Decis_n-analytic systems fcr real-time decision-making in rmssK)n control p 558 N94-35063 ROBINSON, O. IBTN-94-EIX94311329117] p 536 A94-60183 Control of leading-edge vortices on a delta w=og SELTZER, ROBERT M. STANLEY, DOUGLAS O. p 524 N94-34971 Application of current departure ms=stance criteria to Technology and staging effecls on two-stage-to.odod ROBINSON, RAYMOND C. the post-stall manoeuvenng envelope Systems Hot Con'osK)n Test Facility at the NASA Lew_s Special p 533 N94-34622 [BTN-94-EIX94311322891 ) p 520 A94-60205 Projects Laboratory SERPA, JAMES N. STARK, MIKE INASA-CR-195323 ] p 543 N94-35267 An analysis of operational suitability for test and Cost and schedule estimation study rel:)ort ROCKWELL, D. evaluation of highly reliable systems INASA-CR'189344J p 558 N94-35256 Control of leading-edge vortices on • delta wing [ AD-A2.78573J p 530 N94-36184 STIEGLMEIER, M. p 524 N94.34971 SHAFER, MARY F. In-flight velocity measurements using laser Doppler ROCKWELL, DONALD O. In-flight simulation studms at the NASA Dryden Fkght enemomem/ Unsteady structure of leading-edge vortmes on a delta Research Facility p 536 N94-35969 {BTN-94-EIX94311329139] p 549 A94-60161 wing SHANG, JOSEPH S. STOLLERY, J. L I AD-A2789881 p 526 N94-35529 Computation of nonequ=librium hypersonic flowfields Expenmental stodles of vcrlex flaps and vortex plates ROOGERS, WILLIAM G, JR. around hemisphere cylinders [BTN-94-EIX94311329122J p 518 A94-60178 Final-Approach Spacing Aids (FASA) evaluation for [BTN-94-EIXg4351142135] p 521 A94-60428 STONE, H. W. terminal-area, time-based sir traffic control SHEINBERG, HASKELL Aerodynamic heetiog enwronment definition/thermal [NASA-TP-3399] p 529 N94-36048 Processing yttrium barium copper oxide superconductor RODRIGUEZ, KATHLEEN Protection system selection for the HL-20 in near-zero gravity [ BTN-94-EIX9435f 137058 i p 544 A94-60398 Experimental studies of shock-wave/wail-jet interaction I BTN-94-EIX94311332378] p 550 A94-60951 STORACE, ALBERT F. in hypersonic flow, part A SHELDON, DAVID W. Integration o! magnetic bearings in the design of (NASA-CR-195957 J p 523 N94-34964 Flow quality studies of the NASA Lewis Research Center advanced gas turbine engines p 554 N94.35903 ROGERS, H. E. Icing Research Tunnel Engine characteristics for agile aircraft [NASA-TM-106545] p 543 N94-34919 rroRTZ, MICHAEL W. p 538 N94-34608 SHIB, C. YAV..aB reaction control system bleed and control power ROHLF, D. Unsteady flow past an airfoil pitched at constant rate usage m hover and transition [NASA-TM-104021) p 540 N94-34994 X-31A system ldentifc.ation applied to post-stall flight: p 524 N94-34969 Aerodynamics and thrust vectoring p 540 N94-34619 SHIH, CHIANG STRAWN, ROGER ROGUEMORE, W. M. Unsteady separation process and vorticity balance on Computabon of helicopter rotor acoustics in forward flight Numerical method for simulating fluid-dynamic and unsteady aidoils p 524 N94-34970 [NASA-CR-196132J p 560 N94-36031 heat-transfer changes in jet-engine injector feed*arm due SHIN, JAIWON to fouling Prediction Of ice shapes and _ effect on airfoil drag STUDEBAKER, KAREN I BTN-94-EIX94351142133) p537 A94-60426 [BTN-94-EIX94311329115] p 519 A94-60185 Ground vibration test Of the XV-15 Tiltrotor Research ROSS, A. JEAN SHIN, YOUNG S. Aircraft end Pretest Predictions p 541 N94-35972 Dynamic tests to demonstrate lateral control using Data reduction, analysis and resufts of LACV-30-07 air STUREK, WALTER B. forebody suction on large scale models in the DRA 24 cusl'_on vehicle tests, Fort StoP/, VA, August - September Applications of compt,labonal fluid dynamics to the foot wind tunnel p 539 N94-34613 1993 aerodynart_-s of Army profectiles ROSSl, UGO tAD-A278859] p 527 N94-35826 [BTN-94-EIX94311330678] p 5f6 A94-60113 Operational agility assessment with the AM.X aircraft SHNURER, STEVE SUAREZ, C. J. p 534 N94-34626 Mission Evaluation Roo_ Intelkgent Diagnostic and Forebody vortex control for ,sang rock suppress=on ROTHMAYER, A. P. Analysis System (MIDAS) p 558 N94-35064 [BTN-94-EIX94311329119] p 530 A94-60181 Departure solutions of the unsteady thin-layer and full SHOPE, FREDERICK L. SUAREZ, CARLOS J. Nav:er-Stokes equations solved using streamline curvature Conlugate co " heat transfer with a F/A-18 foret:)ody vortex control Volume 1: Static tests based iteration techn_luaS p 552 N94-34980 high-speed boundary layer [NASA-CR-4582] p 528 N94-35991 ROYSTER, D. M. [ BTN-94.EIX94311330652 ] p549 A94-80139 SHUART, M. J. Retained mechanical p¢operties of a new AI-Li-C,u-Mg-Ag alloy as a funcbon of thermal exposure time and Analysis of multifastar_' composite joints T [BTN-94-EIX94311330690] p 548 A94-60101 temperature SIMONSEN, USA C. IBTN-94-EIX94301320164] p 546 A94-60873 TAI, CHANG-SHENG Human factors evaluation of the HL-20 full-scale RUOKANGAS, CORINNE Nav',er-Stokes solver for hypersonK: flow over a slender model Vista goes online: Deosmn-analytic systems for real-time cone [ BTN-94.EIX94351137065 ] p545 A94-60405 decision-making in m,salon control p 558 N94-35063 [BTN-94-EIX94311330681 ] p 543 A94-60110 SKROBIS, K. J. TAKAGI, MICHIVUKI Planer rotabonal magnetic m_romotora with integrated Third order LPF lype compensator for flexible rotor S shaft encoder and magnetic rotor levitati(m p 555 N94-35907 suspensmn p 554 N94-35863 SLADE, A. TAKAHASHI, NAOHIKO SAcHs, G. Engineering llu'ge-scele agent-based systems with Third order LPF type compensator for flexible rotor Synthetic vision for enhancing poor visibility flight Consensus p 558 N94-35071 suspartsmn p 554 N94-35863 operations SMILJANOVSKI, V. TANG, DERSHUEN A. [ BTN-94-EIX94331335531 ] p557 A94-60212 Effect Of initial scceleration on the development Of the Final-Approach Spacing Aids (FASA) evaluation for SANg, JUBARAJ flow held of an airfoil pdchiog at constant rate terminal-area, tmle-based ak traffic control Applications of computational fluid dynamics to the p 526 N94-34989 [NASA-TP.3399] p 529 N94-36048 aerodynamics of Army projectiles SMITH, BARRY T. TANG, PUNAN IBTN-94-EIX94311330678] p 516 A94-601t3 Field deployable nondestructive imOact damage Etactromechenicel simulation end test of rotating SALTER, ROBERT M. assessment methodology for composite structures systems with magnetic beenng or p_ezoelectnc actuator Future ultra-speed tube-flight p 555 Ng4-35918 [BTN-94-EIX94301321378] p 546 A94-60892 ectrve vibrabon control p 555 N94-35905 B-7 PERSONAL AUTHOR INDEX TANG, YUAN-LIANG WANG, YUREN YANG, J. N. TANG, YUAN-LIANG Aircrah fleet maintenance based on structural relial_lity Accurate estimation of object locafion in an image Experimental investigation on supersonic combustion analysts sequence using helicopter flight data (2) [ BTN-94.EIX94311329134 I p517 A94-60166 p 537 N94-35055 [ BTN-94-EtX94351144985i p 537 A94-60447 YANG, LIXING TANNEHILL, JOHN C. WARE, GEORGE M. Expenmental investigation on supersonic combustion Three-dimenszonal upwind paraboiized Navior-Stokes Aerodynamac characteristics of the HL.20 (2) code for supersonic combustion flowfields [BTN.94-EIX943511370551 p 544 A94-60395 IBTN-94"EIX943511449851 p 537 A94.60447 IBTN-g4-EIX94351142134] p 521 A94-60427 WEBER, DANIEL J. Simplifmd method for evaluating the flight stability of YANG, R.-J. THOMPSON, MILTON O. Hypersonic fin aerodynamics IKluid-filiod projectiles Developing and flight testing the HL-10 lilting body: A IBTN-94.EIX943f1330699] p 516 A94.60092 [ BTN.94-EIX9431 t 322905) p,544 A94-60f 91 precursor to the Space Shuttle WEILMUENSTER, JAMES YOON, SEOKKWAN INASA-RP.1332) p 535 N94-34703 Calcutst=on of real-gas effects on airfo*l aerodynamic Cherectenstics of the Shuffle OYoiter ioeside flow dunng TISHKOFF, J. M. characteristics a re-entry condition AFOSR Contractors Propulsion Meebng IBTN-94-EIX94351142143] p 521 A94-60436 I BTN-94-EIX94311322888 } p 520 A94-60208 IAD-A279028 ] p539 N94-35746 WEILMUENSTER, K. JAMES TODD, RUSSELL F. HL-20 computational fluid dynamics analysis Z Terminal Doppler Weather Radar (TDWR) Low Level IBTN.94.EIX94351t 37059 ] p545 A94-60399 Wind Shear Alert System 3 (LLWAS 3) integration studios ZAGRANSKI, RAYMOND at Odando International Airport WEINACHT, PAUL [AD-A278957 ] p 557 N94-35807 Applications of computational fluid dynamics to the Hot gas ingestion effects on fuel control surge recovery aerodynamics of Army projectiles and AH-1 rotor dnve train torque spikes TOKARSKI, FRANK {BTN-94-EIX94311330678] p 516 A94-60113 INASA-CR-191047_ p 538 N94-34993 HOt gas ingestion effects on fuel control surge recovery WEISGERBER, 0. ZAKARIA, ZAIDI B. end AH-1 rotor drive tram torque sp*kes Sudece interference in Rayldtgh scattering INASA-CR.1910471 p 538 N94-34993 The role of fatigue analysis for design of military aircraft p 531 N94.34594 measurements near forebodios TROPEA, C. WEISS, S. [BTN-94-EIX94301315999 p 516 A94-60035 In-flight velocity measurements ustng laser Doppler X-31A system identifiation applied to post-stell flight: ZALAMEDA, JOSEPH N. enemomet_ Fluid deployable nondesfructNe impact damage {BTN-94-EIX94311329139] p 549 A94-60161 Aerodynamics and thrust vectonng p 540 N94-34619 assessment methodology for compo_te structures WELLS, R. O., JR. TU, EUGENE L [BTN-94-EIX94301321378 p 546 A94-60892 Vortex-wing interaction of • close-coupled canard Analysis of wavelel technofogy for NASA applications INASA-CR-195929] p 522 N94-34704 ZlEDAN, M. F. configurahon Drag reduction of airplane fuselages through shai_ng IBTN-94-EIX94311329121 ] p519 A94-60179 WHALLEY, MATTHEW S. by the inverse method Study findings on the influence of maneuverability and TUNG, C. IBTN.94.EIX94311329117 p 536 A94-60183 agility o_ helicopter handling qualitms The quest for stall-free dyr_rmc lift ZELENKA, RICHARD E. p 533 N94-34624 p 525 N94-34986 Design end analysis of a Kalman filter for TURNER, D. WHITE, SUSAN terrain-referenced po_boning and gmdance 1993 TechnP-..al Paper Contest for Womerl. Gear Up Departure solutions Of the unsteady thin-layer end full [BTN-94.EIX94311329124 p 557 A94-60176 2000: Women in Mof_fl Navior-Stokes equations solved using streamline curvature ZHANG, XIN based itoratmn techniques p 552 N94-34980 [NASA-CP.10134] p 561 N94-35961 Computebonal analysis of a stogie jet impingement WHITEHUFIST, R. B., III ground effect tiff loss I=lanar KrF laser-induced OH fluorescence imaging in iBTN-94.EIX94311329f14 p 519 A94-60186 V a supersonic combustion tunnel ZHANG, XUDONG ISTN-94-EIX94321333315] p 520 A94-60266 Three-dimenmonal closure of the passage-averaged VANDOMMELEN, L WIESEMAN, C. O. vortiody-potential formulation Unsteady flow past an airfoil pitched at constant rate Time simulation of flutter with large stiffness changes IBTN.94-EIX9430131599f p 547 A94-60027 p 524 N94-34969 [ BTN-94-EIX94311323132 J p518 A94-60168 ZIM/_ HANS VANROSENDALE, JOHN Modal coordinates for aeroelastic analysis with large Runfime support for data parallel tasks Runtime support for data parallel tasks local structural variations _NASA-CR.194904} p 558 N94-35240 [ NASA.CR.194904 ] p 558 N94.35240 [BTN-94-EIX94311329131} p 518 A94-60163 ZINNER, R. VENKATAPATHY, ETHIRAJ WILHITE, ALAN W. The quest for stall-tree dynamic lift Devoiopment and applmation of co--lionel Technology end staging effects on two*stage-to-oroit p 525 N94-34986 aarof#_ermodyr_mics fk:_41_ld computer cOdeS systems ZINTSMASTER, LOGAN R. INASA-CR-196136] p 526 N94.35498 IBTN-94-EIX94311322891 ] p 520 A94-60205 Wide-Eye (tm)/hoimet mounted display system for rotorcraft applications VISBAL, MIGUEL R. WILLIAMS, D. R. | BTN-94-EIX94331335528 ] p 549 A94-60209 Crossfldw topology of vortical flows Mechanisms of flow control with the unsteady bleed IBTN.94-EIX94301315993] p 515 A94-60029 technmNe p 525 N94.34987 VISKANTA, RAYMOND WILLIAMS, F. A. Measurement and predmbon of dynamic temperatures Turbuiont combustion regimes for hypersonic prop_lsdon in unsymmemcally cooled glass windows hydrogen-sir diffusion flemes [STN-94-EIX94351142128] p 550 A94-60421 [BTN-94-EIX94321333324] p 546 A94-80275 VORACEK, DAVID F. WlLLSHIRE, KEUJ F. Buffet-induced structural/flight-control system Human factors evaluation of the HL-20 full-scaio interaction of the X.29A aircraft model [ BTN-94-EIX94311329t 37 ] p517 A94-60183 [STN-94.EIX94351137065] p 545 A94-60405 VORMWALD, M. WILLSHIRE, WILLIAM L, JR. Human factors evaluation of the HL-2O full-scale Notch fatigue assessment of aircraft components using a fracture mechemce based parameter model p 551 N94-34588 [BTN-94.EIX94351137065 ] p545 A94-60405 WILSON, DAVID J. Flying qualities evaluat_n maneuvers W p 533 N94-34623 WOOD, N. J. WADAWADIOI, GANESH Yaw control by tongentml forebody b_owsng Three-dimensional upwind parabolized Newer-Stokes p 539 N94-34615 code for supersonic combustion fiowfiolds WOOD, WILLIAM A. [BTN.94-EIX94351142134] p 521 A94-60427 Com_nad LAURA-UPS solution procedure for WADSWORTH, DAVID chemically,.rsecting flows Miss=on Evaluation Room Intelbgent Diagnostic and [NASA-TM-t07964 } p 551 N94-34721 Analyszs System (MIDAS) p 558 N94-35064 WRENN, G. A. WAHLS, OEBORAH M. Supersonic transporl wing minimum weight design Preliminary structural evaluation and demgn of the inte_ratm 9 aerodyTtr_ce and structures HL-20 [BTN-94-EIX94311329123] p 518 A94-60177 | BTN*94.EIX94351137060 ] p545 A94-60400 WURS'rER, K. E. WAUGORA, SHARON AModymlmlc heating enwrorymerd definition/thermal Cost and schedule estimation study report protection system seioctldn for the HL.20 i NASA.CR.189344 ] p588 N94-35256 [BTN-94-EIX94351137058] p 544 A94-60398 WALKER, J. D. A. Some aspects of unsteady separation p 525 N94-34979 Y WANG, _d.IAOQING Combustion performance of dump combustor in ramjet YALAMANCHILI, S. R. engine using liquid hydrogen fuel Analysis of multHestener composite jemts A94-60101 I BTN-94-EIX94351144992 ] p538 A94-60454 IBTN.94.EIX94311330690 } p 548 B-8 CORPORATE SOURCE INDEX AERONAUTICAL ENGINEERING / A Continuing Bib/iography (Supplement 308) September 1994 The quest for stall-free dynamic lift Defence Research Agency, Farnborough, Hampshire Typical Corporate Source p 525 N94-34986 (England). Index Listing Army Vehicle Structures Lab., Hampton, VA. Dynamic tests to demonstrate lateral control using Rotorcraft fatigue lite-lxed_ction: Pest, present, and torebody suction on large scale models in the DRA 24 future p 551 N94-34590 foot wmd tunnel p 539 N94-34613 Auburn Unlv., AL Deutsche Aero41pace e.G., Munich (_ny). Influence of backup beanngs and support structure I CORPORATE SOURCE I Notch fatigue assessment of mrcraft components usmg dynamics on the behavior of rotors with active supports a fracture mechanics based parameter [NASA-CR-196119] p 553 N94-35500 p 551 N94-34588 The role of fatigue analysis for design of military Adaptive Fieeearch Corp. Huntsville, AL B aircraft p 531 Ng4-34594 Structured finite volume modeling of US Navy aircraft X-31A control law design p 540 N94-34618 Ina test cells, Task 1: Turbosheft engine, volume 1 Bath Univ. (England). Deutsche Forachungnnstaft fuer Lufl- und Reumfahrt. A268176] p 135 N94-17432 Yaw control by tangential forebody blowing Brunswick (Gevmany). p 539 N94-34615 X-31A system _dentihcation app_md to post-stall flKJht: British Aerospace Defence Ltd., Brough (England). Aeroo'yrmmics and thrust vector_g p 540 N94.346t 9 Fabgue des=gn, test and in-service expermnce of the BAe Hawk p 531 N94.34597 EFA flymg qualitms specifm.abon end ds utilisebon British Aerospace Defence Ltd., Fernborough p 533 N94-34621 (England). Draper (Charles Stark) Lab., Inc, Cembrkige, MA. Harne( 2: A companson of US end UK approaches to Control of meglev vehicles with aerodynarmc and Listings in this Index are arranged alphabetically fatigue clearance p 531 N94-34596 guideway disturbances p 554 N94-35842 British Aeroepace Defence Ltd., Preston (England). by corporate source. The title of the document is Durham UNv. (England). Operational agility: An overview of AGARD Worlung Engineenng large-scale agent.based systems with used to provide a bdef description of the subject Group 19 p 534 N94-34625 consensus p 558 N94-3.5071 matter. The page number and the accession British Aerospace Defence Ltd., Warren (England). number are included in each entry to assist Design of inte_'ated flight end powerplent control the user In locating the abstract In the abstract systems p 532 N94.34609 E section. If applicable, a report number is also Eidetlt_ tntematlonal, Inc., Torrance, CA. included as an aid in identifying the document. C F/A-18 forebody vortex control Volume 1: Static tests [NASA-CR-4582} p 528 N94-35991 California State Univ. Long Beach. CA. Prediction of unsteady airfoil fk3ws at large angFes of Eloret Corp., Pldo Alto, CA. incidence p 525 N94-34978 Development end applicabon Of computational California Univ. Los Angeles, CA. aerothermodyrmmics flow/mid computer codes Selected topics on the active control of hatN_pter [NASA-CR-196136] p 526 N94-35498 eeromechancal end vibcation fxo01ems p 541 N94-35874 F California Univ. San Diego, La Jeff, CA. A On the venous forms of the energy equation for a dilute, monato_c rmxture of nonmacbng gases Federal Aviation Admlnlstrabh_l, _ City, OK. {NASA-CR-4612] p 527 N94-35864 A rewew of compute( evacuation models and thetr data Advisory Group fo¢ Aerospace Research end Cadspan Corp. Arnold AFS, TN. needs Development. Neuitly-Sur-Se_ne (France). USAF/AEDC aerodynamic end p¢opulmon ground test |DOTIFAAIAM.94111] p 528 N94.35236 An Assessment of Fatigue Damage and Crack Growth and evaluation technques tor h0ghly msne_Nereble aircraft: Federel Aviation Administration, Washington, IX:. Predicbon Techniques Capabllit=es and challenges p 532 N94-34606 The Federal Awabon AdmnstrabOn plan for research, [AGARD-Ro797] p 550 N94-34581 Ceiepan-Stste Univ. of New York Joint Venture, angineenng end development p 561 N94-35262 Technologies for Highly Menoeuvrabla Awcreft Buffalo, NY. Florida Agricunurel and Mechanlcel Univ., Teliehassee, [AGARD-CP-548] p 532 N94-34605 Expenmental studms of shock-weve/wel6jet interaction FL AGARD highhghts 93/2 in h_ flow. part A Unsteady flow past en airfoil I_tched at constant rate |AGARD-HIGHLIGHTS*93/2t p 561 N94-35444 {NASA-CR-t95957] p 523 N94-34964 p 524 N94-34969 Aeronautical Research InsL of Sweden, Bromma. Experimental studies of transpiration coo_ing w_ shock Florida State Univ. Teliehaesee, FL Fetmgue management end venficeho, of mdremes interacben in hyperson0c flow, bert B Unsteady flow past en airfoil I_tched at constant rate [NASA-CR-195958J p 523 N94-34965 p 531 N94-34591 p 524 N94-34969 Aerospace Engineering Test EstabllMlment. Cold Lake Cincinnati Univ. OH. (_aberta). Charactenzabon of dynamic stall phenomenon using An agility metric structure for ogeretional agility two-d_mensionel unsteady Navle(-Stokes eduatio_'Ds G p 534 N94-34629 p 524 N94-34974 Cok)reck) Univ. Boulder, CO. Air Force Inst. of Tech., Wright-Patterson AFB, OH. Galaxy SckmUfl¢ Cocp., Piemntvilie, NJ. Concepts and applcation of dynamic ss_arebon for D_rect reduced order mixed H2/H infinity control for the Unleaded AVGAS program sgility and super-maneuverability of aircraft: An Short Take-Off and Landing/Maneuver Technology IAD-A2786501 p 547 N94-35795 Demonstrator (STOL/MTD) assessment p 535 N94-34988 Coltm: induetries. West Hartford, CT. Gemw_ Electric Co., Lyon, MA. I AD-A278675] p 540 N94-35796 Integration of magnetic bearings in the design of HOt gas Ingestion effects on fuel control surge recoveqf An analysis of operational suitability for test end and AH-1 rotor drive train torque spikes advanced 9es turbine engines p 554 N94-35903 evaluation of highly reliable systems |NASA.CR.191047] p 538 N94-34993 Eiectrtc Co., Sctt4rmctecly, NY. lAD-A278573] p 530 N94-36184 Modelling end control of • rotor supported by rnagnebc Air Force Office of Scientific Reesaroft, BoBng AFB, D beanngs p 554 N94.35858 Washington, DC. Motors Corp., Indianapolis, IN. AFOSR Contractors Propulsion Meeting Composite methx expenrmmtsl COrN_JStor lAD-A279028 ] p 539 N94-35746 Oammuit A_ Salnt.CIoud (Frence). [NASA-CR-194446] p 538 N94.34679 Aienie, Turin (Ita0y). High incidence flow analysis over the Rafsle A Operational sgdity assessment with the AM-X aircraft p 522 N94-34612 p 534 N94-34626 Desesult-Breguet Aviation, Salt Cloud (France). Arizona Univ. Tucson, AZ. Assessment of in-sennce aecreft fatigue monitoring Computed unsteady flows of aidoits at high inoidence i_ocess p 531 N94.34593 Illinois mnsL of Tnch. Chicago, IL p 525 N94-34975 Defence Research Agency, Bedford (England). The unsteady pressure field and vo*licdy producbion at Army Aviation Syefem Command, Moffett FieM, CA. Control of leading-edge separation 0(1 a cambered delta the suction surlece of a p_tching a_oil Study findings on the influence of maneuverability and wmg p 539 N94-34616 p 524 N94-34972 agility on helicopter handling qualities The influence of flymg qualities on operational agility Mechanisms of flow control with the unsteady oleed p 533 N94-34624 p 534 N94°34628 technique p 525 N94-34987 C-1 CORPORA TE SOURCE Instltut de Mecanlque des Fluides de Marseilie InsUtut de Macanlque des Ftutdes de Marselite National facilities study. Volume 5: Space research and Technology and staging effects on two-stage-to-orbit (France). development facilities task group systems Techniques for aerodynamic characterization and [NASA-TM-109859] p 542 N94-34637 IBTN-94-EfX9431132289tl p 520 A94-60205 performance eveluabon at high angle of attack Aerospace Safety Advisory Panel Aerodynamic characteristics of the HL-20 p 533 N94.34614 INASA-TM-109840] p 545 N94-35390 IBTN'94-EIX94351137055] p 544 A94_60395 S_x-degree-of-freedom guidance and control-entry Institute for Computer Applications in Science and Budget estimates, fiscal year 1995. Volume 1: Agency analysis ot the HL.20 Engineering, Hampton, VA. summary, human space flight, and sc=ence, aeronautics I BTN-94-EIX94351137056] p 544 A94.60396 Runtime support for data parallel tasks and technology Effect of lift-to-drag ratio in pilot rating of the HL-20 INASA-CR'194904J p 558 N94-35240 1NASA-TM-109791 ] p560 N94.35899 landing task A three dimensional multigrid Reynolds.averaged National Aeronautics end Space Administration. Ames Newer-Stokes solver for unstructured meshes IBTN-94-EIX94351137057] p 544 A94-60397 Research Center, Moffett Fiakl, CA. [ NASA-CR-1949081 p 528 N94-35994 Aerodynamic heeling environment definition/thermal DesK3n and anatys_s of a Kalman filter for protection system selection for the HL-20 terrain-referenced posihoning and guidance IBTN-94"EIX94351137058 ) p 544 A94.60398 J [BTN-94-EIX943113291241 p 557 A94-60176 HL.20 computatm_al fluid dynamics enalys=s Vortex.wmg interaction of a close-coupled canard I BTN.94-EIX943511370561 p 545 A94-60399 Joint Publications Research Service, Arlh_lton , VA. conflgurabon Preliminary structural evaluation end design of the JPRS report: Science and technology. Central Eurasia [BTN-94-EIX943tt329121 I p 519 A94-60179 HL-20 IJPRS-UST-94-006] p 553 N94-35226 PropulsKm.induced aerodynamic effects measured with lBTN-94.EIX94351137060] p 545 A94-60400 JPRS report: Science and tachnciogy. Central Eurasia a full-scale STOVL model Human lectors evaluation of the HL-20 full-scale IJPRS-UST-94-005] p 553 N94-35342 [BTN-94-EIX943113291201 p 519 A94-60180 model JPRS report: Science and technology. Central Eurasia Calculation of real-gas effects on Jdrfoil aerodynamic {BTN-94-EIX94351137065 ] p545 A94-60405 IJPRS-UST-94-0101 p 553 N94.35385 characteristics Fiald _ployal_e nondestructive impact damage JPRS report: Soence and technology. Central Eurasia [BTN-94-EIX94351142143] p 521 A94-60436 assessment methodology for composite structures [JPRS-UST-94-0121 p 553 N94.35387 An examination of the aerodynamic moment on rotor [ BTN.94-EIX94301321378 ] p5.46 A94-60892 blade tips using flight test data and analy_s Das_gn oriented structural analyms K {NASA.TM-104006} p 523 N94.34948 [NASA-TM-109124J p 551 N94-34722 NASA/DOD Aerospace Kno_e_ge Diffusion Research Physics of Forced Unsteady Separation [ NASA-CP-31441 p 552 N94-34966 Prolect. Paper 42: An analysis of the transfer of Scientific Kenagawa Academy of Science and Techno_gy, end Technical lnfotmation (STI) in the US aerospace Kawmlaki (JalNm). YAV-aB reaction control system bleed end control power industry usage in hover and transition Magnebc_lly suspended stepprng motors for clean room |NASA-TM-109863] p 560 N94-34730 [NASA-TM-104021 ] p 540 N94.34994 and vacuum environments p 555 N94-35915 Active thermal isolation for temperature responsive Director's dismetionary fund sensors [NASA-TM-103997] p 561 N94.35370 L INASA-CASE-LAR.t4612.1] p 552 N94-35074 Flight testing of a luminescent surface pressure Langley 14- by 22-foot subsonic tunnel test engineer's sensor Univ., Sethinhlm, PA. data 8cqu=_tion end reducbo_ manual [NASA-TM-103970) p 522 N94.35394 Control of leading-edge votticas on a delta wing [NASA-TM-4563) p 526 N94-35246 1993 Technical Paper Contest for Women. Gea r Up p 524 N94.34971 Flutter suplxessmn digital control law des_ln and testing 2000: Women in Mobon Some aspects of urtstesdy seperatio_ for the AFW wind tunnel model p 540 N94-35873 [NASA-CP-10134] p 561 N94-35961 p 525 N94-34979 An OVerview of recent advances in system Unsteady structure of leading-edge vortices on a delta Piintad slmoiation study of two tiit-wmg oontrol identification p 546 N94-35880 wing concepts p 541 N94-35962 Second International Sympo_um on Magnetic lAD-A278988) p 526 N94-35529 Wind tunnel measurements on a tulksce, le F/A-18 with Suspen_on Technoio,gy, part 2 Lockheed Aeronautical System Co., Marietta, GA. a tangentially blowmg slot p 527 N94-35965 |NASA-CP-3247-PT-2] p 546 N94-35902 Risk analysis of the C-141 WS405 inner-to-outer Ground vibration test of the XV-15 Tdb'otor Research Final.Approach Specmg Aids (FASA) evaluation for )bint p 531 N94-34592 Airoraft and pretest predictions p 541 N94-35972 termmsl-area, time*based air traffic control Lockheed Corp., Fort Worth, TX. Rasear'ch end tachnolegy, 1993 {NASA-TP-3399] p 529 N94-36048 An overview of the F-16 service life approach [NASA-TM-t08816] p 561 N94-36117 Natlonll Aeronautics and Space Administration. Lewis p 532 N94-34599 National Aeronautics and Speoa A_. Research Center, Cleveland, OH. Lockheed Missiles and ,_e COo, S_, CA. Goddard Space Flight Center, Greeni_dt, MD. Expenmontal lovesbgation of counter-rotating propfan Will the real dynamic instability mechanism please be Ade developers' supplement to the recommended flutler et Chase conditions recognized! p 552 N94-34976 approach IBTN.94-EIX94321333310] p 516 A94-60042 [NASA-CR-189345] p 557 N94-34921 Prediction of ice shapes and their effect on airfoil drog Cost end schedule estiwmtiot_ study report |BTN-94-EIX943t1329115) p 519 A94-60185 M [NASA-CR-189344] p 558 N94-35256 Approxm_te similarity principle for a tull-ecale STOVL Flight Mechen_.-'s/E_tion Theory SympomJm, 1994 ejector M_tta InsL of TIc'h, Lexington. [NASA-CP-3265] p 545 N94-35605 |BTN-94-EIX9434133e360] p 550 A94-60352 The influence of data link-provcled graphical weather Netinnai Aeronautics and Space Administration. Hug_ Flow quality studies of the NASA Lew_s Research Center on I_Ot dec_._on-making L Dryden Flight Reasa_h Facility, Edwards, CA. Icing Research Tunnel lAD-A278871 ] p 556 N94-35596 Buftet-induced structurol/flight -control system [NASA-TM-106545] p 543 N94-34919 Data req_rements for ceiling and visibility products interaction of the X-29A =drorafl Computational methods for HSCT-intat controis/CFD development [BTN-94-EIX94311329137] p 517 A94-60163 interdisciplinary research [AD-A,?.78959] p 556 N94-35720 DeveioPm9 and flight testing the HL-10 lifting body:, A [NASA-TM-lO66t8] p 539 N94-35352 Terminal Doppier Weather Radar ('TDWR) Low Level precursor to the Space Shuttle Challenging the Future - Journey to Excetinnce. Wind Shear Alert System 3 (LLWAS 3) integration studms [NASA-RP-1332] p 535 N94-34703 Aeropropuis_on stratag_c plan for the 1990'S st Orlando IntematK_zal Airport Evaluating the dynamic response Of in-flight thrust {NASA-TM-109250) p 545 N94-35591 {AD-A278957] p 557 N94.35807 calculation techniques during throttle transemta Eiactromechenicat simulation end test of rotating McDonnelkOouglas Corp., Saint Louis, MO. lNASA-TM-4591 ) p 535 N94-35241 systems with magnetic beanng _ i_ezoetectnc ectueter active vib_bon corttro_ p 555 N94-35905 A combined al:_rcach to buffet response analyses and Right testing • pro_JIsion-controlled eircroff emergency A _,_aerso_c tunnel for taser and tlow-esedmg fatigue life prediction p 551 N94-34587 flight control syatern on I_ F-15 IBrp4ene [NASA-TM-4590} p 540 N94-35258 techniques Michigan State Univ., East Lansing, MI. |NASA-TM-106588] p 556 N94-35945 Effect of initial accelerotiorn on the deveinpmenl of the Engine exhaust charoct(mstics evaluation in support of aJ'croft ecousbc testing p 560 N94-35963 National Aerospace Lab. Amsterdam (Netherlands). flow field of an airfoil i_tching at constant rote Reduction of fatigue load expemmce as part of the p 526 N94-34989 In-flight _rmdafion studms at the NASA Dryden Right Research Feclilty p 538 N94-35966 fatigue management program for F-16 aircraft of the Natkmal Aeronsuti¢= and Space AdmlnMtratinq. RNLAF p 532 N94-34598 N Lyn¢inn B. Joitnson Space Center, Houllon, TX. National Oefence Academy, Tokyo (Japan). Vista goes online: Deasmn.-analy_c systems for reel-time Third order LPF type compensator for flexible rotor decision-tasking in mluion control p 558 N94-35063 suspension p 554 N94-35863 HaUona_ Aeronautics amcl Space A¢lmlnletraUon, Mles_on Evaluation Room Intelligent Diagnostic and NMtimal Trens_ Safety Born'd, Washington, Wagon. De. Analysis System (MIDAS) p 558 N94-35064 DC. National fec_lities study. Volume 1: Fac_fies inventory NaUon#mi J_mronlmtins and _ A_ti_n. Annual rev_w of mrcrofl accident data: US general |NASA-TM-1098541 p 541 N94-34632 Longley Research Center, Hmpton, VA. aviation calef, der year 1991 National facilities study Volume 2: Task group on Coupled radiation effects in thermochemical [PB94-127982| p 528 N94-34991 aeronautical rermarch and development fecititms report nomKluWibrium shock-captunng _Id calculations Safely study: A review Of flightorew-iovo4ved, max;," iNASA-TM-109855] p 542 N94-34633 [BTN-94-EIX94311330648J p 559 A94-60143 ac¢identa of US air camera, 1978 through 1990 Natiertal fl(_lit_ study. Vo_uflll_ 2A: Facility Study Office Effects of model _..4de on flight chera¢_ and [P894-917001 ] p 529 N94-35482 on ine Nationel Wind Tunnel Coml:4ex dean p=remelero Annual review of aircraft accident data. US general [NASA-TM-109856) p 542 N94.34634 [BTN-94-EIX94311329143] p 517 A94-80157 aviation, calendlt year 1992 National facditms study. Volumo 3: Miss=0n end Alinviation of _ force on taogent-ogNe forebocties [PB94.181054] p 529 N94.35496 requirements model report usm9 pesewa poro_ty Aircraft accident report: Uncontrolled collision with INASA-TM-109657| p 542 N94-34635 [ BTN-94-EIX94311329126 ] p536 A94-60174 terroin, American International Airways Flight 808, Douglas National tacitities study. Volume 4: Space operations Supersonic transport wing minimum weight design DC-8-61, N814CK, US Naval Air Station, Guantansmo Bay, facilities task group integrating aerodynsm_ca end structures Cuba, 18 August 1993 [NASA-TM.109858) p 542 N94-34636 [ BTN-94-EIX94311329123 ] p518 A94-60177 [PB94-910406J p 529 N94-35521 C-2 CORPORA TE SOURCE Xerad, inc. Naval Air Warfare Center, Patuxent River, MD. Stanford Unlv., CA. X-31 tachcal utility: Initial results p 533 N94-34620 Investigation of Burnett eduat;ons Ior two-d,mensionat Naval AIr Warfare Center, Wermlnster, PA. hypersonic flow Apphcation ot current departure resistance criteria tO AD-A278942_ p 527 N94-35717 the post-stall manoeuvermg envelope Sulzer-4Escher Wyee Ltd., Zurich (Switzerland). p 533 N94-34622 Rotor dynamic behaviour of a high-speed oil-free motor Application of centnfuge based dynamic flight s=mulation compressor with a rigid coupling supported on tour radial to enhanced maneuverability RDT/E magnetic bearings p 555 N94-35911 p 541 N94-34630 Sverdrup Technology, Inc., Brook Park, OH. Hot Corrosion Test Facility at the NASA Lewis Special Naval Postgraduate School, Monterey, CA. Pro_ects Laborato_' Companson of pitch rate history effects on dynamic INASA-CR-tg5323_ p ,543 N94-35267 stall p 535 N94-34968 Computation of unsteady flows over airfoils p 525 N94-34977 T Data reduction, analy_s and results of LACV-30-07 air cushion vehicle tests, Fort Story, VA, August - September Tokyo Univ. (Japan). 1993 Magnetically suspended stepping motors for clean room IAD-A278859} p 527 N94-35826 and vacuum environments p 555 N94-35915 Naval Sudace Warfare Center, Dahigren, VA. Tsentrelnl Aerogldrodinamicheskli inst., Moscow User's guide for an interactive personal computer (USSR). interface for the aeroprediohon code Aerodynamic design of super maneuverable aircraft _ NSWCDD/TR-94/1071 p559 N94-35955 p 533 N94-34617 North Carolina State Univ., Raleigh, NC. Numencal modeling studies of wake vortex transport U end evolution within the planetary boundary layer INASA-CR-196078] p 529 N94-35522 United Technologies Corp., East Hartford, CT. NYMA, Inc., Brook Park, OH. Unsteady separabon expenments on 2-D airfoils. 3-D Data reduction procedures for laser velocimeter wings, and model helicopter rotors p 524 N94-34967 measurements in turbomachinery rotors United Technologies Research Center, East Hartford, INASA'CR-195343 ) p 552 N94-35224 CT. Departure solubons of the unsteady thin-layer and full 0 Navier-Stokes equations so_ved using streamline cuntature based iteration tachnRlues p 552 N94.34980 UnhiereJty of Southern California, Los Angeles, CA. Ohio Slate Univ., Columbus. Unsteady soparat_on process and vort_city batance on Robust control design techniques for active flutter unsteady airfoils p 524 N94-34970 Suppression p 541 N94-35875 Expansion effects on supersonic turb_ent boundary layers W lAD-A278989] p 527 N94-35950 Wmlhington Univ. Saint Louis. MO. P Coml:_neq LAURA-UPS solution procedure for chem:c.any-reacting flows INASA-TM-1079641 p 551 N94-34721 Pennsylvania State Univ., University Park, PA. Western AIm0q:)ace Labs_ Inc., Monte Sere/to, CA. Accurate estimabon of obiect location in an image Effects ot checklist interface on non.verbal crew sequence using helicopter flKJftt data comrr_nications p 537 N94-35055 INASA-CR-177639} p 528 N94-34915 The aerodynamic and heat transfer effects of an end'wall Wla¢om=ln Univ., Ma¢l_mn, Wt. boundary layer fence in a 90 degree turning square duct Planar rotational magnetic mloromotors with integrated [AD-A278903J p 553 N94-35803 shaft encoder and magnetic rotor levitation Pm_ uni_. fltaly). p 555 N94-35907 An assessment of fatigue crack growth prediction Wright Lab. Wrig_t-Patterlmn AFB, OH. models for aerospace structures p 551 N94-34586 Damage tolererce management of the x-2g vertical PoIttacnico dl Tortno (italy). tail p 531 N94-34595 Design. construction, and testing of a five actNe axes Pro_'ees and purpose of IHPTET program magnetic beanng system p 554 N94-35846 p 538 N94-34607 Purdue Univ., West Lafayette, IN. Results from the STOL and Maneuver Technology Frequency 0omain analysis of the random Io_ding of Demonstration prng_'am p 532 N94-34611 crocked panels Fty_ng qualibas evaluation maneuvers [NASA-CR-196021 J p 556 Ng4-35974 p 533 N94-34623 R X Radio Technical Commtaldon lor Aeroftaotlctk Xered, Inc., Santa Monlca, CA. Weehlngton, IX:. Future ultra-speed tt..Oe-flight p 5=;5 N94-35g18 Minimum pertormance standards: Airf)orne low-range radar altimeters [RTCAoDO-155} p 537 N94.35344 Research Inst. for Advanced Compotar ScNmce, Moffett Field, CA. Computation of helicopter rotor aCOuStics in forward fKgt_t INASA°CR-196132) p 560 N94-36031 Rice Univ., Houston, TX. Analysis of wave_et technology lor NASA appiicatK)ns [NASA-CR-t95929] p 522 N94-34704 Rolls-Royce Ltd., Bristol (England). Engine charactenstics for agile aircraft p 538 N94-34608 S Slndll NltlOnll LI_ Al_lNIfque, NM. A revmw and development of _orrelations for base p_eesure and base heating _ supe_r_ flow |SANDg3-0280] p 526 N94-35360 Satcon Technology Corp., C_nbrk_e, MA. Aerospace apol_at_ons of magnetic peer)ngs p 554 N94-35837 Southampton Univ. (England). The simulabon of a propulsive rat and force measurement using a magnebcatly suspended wind tunnel model p 527 N94-35655 C-3 FOREIGN TECHNOLOGY INDEX AERONAUTICAL ENGINEERING I A Continuing Bibliography (Supplement 308) September 1994 F Effects of propeller on the turning of old fighters Typical Foreign Technology (BTN-94-EIX943611354261 p 537 A94-60623 Index Listing FRANCE Systematic computation scrmme of PAR-WIG cruising Wake curvature and airfoil lit1 f_t_lormarlce IBTN-94+EIX94311329147 ] p517 A94-60153 [BTN-94-EIX94361135427] p 521 A94.60624 Static and dynamic flight-path stability of airplanes Aerodynamic properbes of crescent wing planforms [ BTN-94-EIX94361135428 } p 522 A94-60625 IBTN-94-EIX94311329146} p 517 A94-60154 ICOUNTRY OF INTELLECTUAL ORIGIN I Third order LPF type compensator for flexible rotor FINDER, A system providing complex decision suppo_ suf_oension p 554 N94-35863 tor commercial transport replanning operations Magnebcally suspended stepP+og motors for clean room |BTN-94-EIX9433_3355291 p 549 A94_o0210 and vacuum environments p 555 N94-35915 CHE_ An Assessment of Fatigue Damage and Crack Growth The present situation _ future devatopmlml ot Chinese Prediction Techniques vielion relillbility end mllinlllinllbillty engineering IAGARD-R-7971 p 550 N94-34581 N Assessment of in-sennce aircraft fatigue monitoring p153 _ process p 531 N94-34593 NETHERLANDS [-'_-_--'_I ACCESSION I Technologies for Highly Manoeuwabie Aircraft Reducbon of lat_jue load expermnce as part of the IAGARD-CP-54S } p 532 N94-34605 fatigue management program tar F+16 a_m'aft of the I NUMBERI High incmlence flow analysis Over 1he Ratale A RNLAF p 532 N94-34598 p 522 N94-34612 NETHERLANDS ANTILLES Techniques for aerodynamic characlerizabon and In-flight velocdy measurements using laser Doppler performance evaluabon at high angle of attack anomometry Listings tn this index are arranged alphabetically p 533 N94-34614 (BTN-94-EIX94311329139] p 549 A94-60161 by country of Intellectual origin. The title of the AGARD h*ghlights 93/2 document is used to provide a brief description [AGARD-HtGHUGHTS-93/2} p 561 N94-35444 R of the subject matter. The page number and accession number ere Included in each entry G RUSSIA to assist the user in locating the abstract In JPRS report: Science and technology. Central Eurasia the abstract section. If applicable, a report num- GERMANY IJPRS-UST.94-006J p 553 N94-35226 ber is also included as an aid in identifying Dynamic aeroelastic stability of vertical-axis wind JPRS report: Soence and technology. Central Eurasia turt_nes under constant wind velocity the document. iJPRS-UST-94-O051 p 553 N94-35342 [BTN-94-EIX94321333311] p 548 A94-60043 JPRS report: Scmnce and technology Central Eurasia Synthetic vision for enhancing poor visibility fhght [JPRS-UST.94-010J p 553 N94-35385 ope¢atJons JPRS report: Science and technology, CenUal Eurama IBTN-94-EIX94331335531 i p 557 A94-60212 IJPRS-US'r -94-012 ] p 553 N94-35387 Notch fabgue assessment o1 aircraft corntx)nents u_og a fracture mechanics based peram_er p 551 N94-3.45e8 S The role of fatigue analysis for design of military aircraft p 5.31 N94-34594 SAUDI ARABIA X-31A conlJ'ol law design p 540 N94-34618 Drag reducbon of airplano fuselages through shaping X-31A sysmm t<:kmtiftcetion appl_d to post-start It+ght: by the reverse method B Aerodynamics and thrust vectonog p 540 N94-34619 [BTN-94-EIX94311329117 ] p536 A94-60183 EFA flying qualities iq_eoificabon and its ublisetion SWEDEN BRAZIL p 533 N94-34621 Fabgue management and venticabon of alr/rames p 531 N94-34591 Combustion shock tunnel and interface compross_n to SWlTZIERLAND increase reservo+r pressure and Imthalpy I Rotor dynamic pellaVlour of a h*gh+speed oit-fTee motor IBTN-94-EIX94311330650] p 516 A94-60141 cornpr_ wrth a rlg_ coupling sup_30_ed on to,dr redml INDIA magnetK: beanngs p 555 N94-35911 Parameter estimates of an aeroelastic aircraft as C affected by model _nplifcatmm IBTN.94-EIX94311329142} p 517 A94-60158 T CANADA Preliminary mveatigetons on improvzng air-_Jgmented Explicit Kutta condition/or an unsteady two-dimen_l rocket performance TAIWAN, PROVINCE OF CHINA constant potential panel method IBTN-94-EIX94321333323] p 544 A94-60274 Navmr.SIokes solver for hypersonic flow over a slender {BTN.94-EIX943013159901 p 515 A94-60026 ISRAEL cone Time s_muietion of flutter with large stiffness changes IBTN-94-EIX94311330681 } p 543 A94-S0110 Three-dimenSional closure of 1he passage.averaged [BTN-94-EIX94311329132] p 518 A94-60168 Aircraft landing gear positioning concorr_ng abnormal vorticity-potentiel formulation Modal coordinates for seroe(estic ar_lysis wdh targe _r_g cases IBTN-94-EIX94301315991] p 547 A94.60027 local slnJctural vanatiens ISTN.94-EIX94311329140} p 536 A94.60160 Ornithopter wing design {BTN-94-EIX943113291311 p 518 A94-60169 Drag reducbon for turbulent flow over a projec_e, part [BTN.94-EIX943313374991 p 521 A94.60334 Effects of the roll angle on crucitorm wing-body 2 Structural integrity and containment aspects of small configurations at h*gh incidences IBTN.94-EIX94311322900] p 520 A94-60196 gas turb4ne engines ( BTN-94-EIX94311322903 ] p520 A94-60193 Drag reckJcbon of turbulent flow over a pro_lectite, pert IBTN-94-EIX94331337500] p 550 A94-60335 ITALY 1 Preesure measucemanta on • forwm'd-swepr {BTN-94-EIX94311322899] p 557 A94-60197 Evatuabon o1 the dynamics and handling quality TURKEY cheractanslics of the Bell 412 HP heimopter wmg-canerd configeration Effect of coarse second phase particles on fatigue crack [BTN.94-EIX94331337502] p 530 A94-60337 IBTN-94-EIX9431132914g] p 516 A94-60151 An assessment of fatigue crack growlh prediction Wopagabon of an AI-Zn-Mg-Cu alloy An agility melric structure for operatior_l agility models for aerospace structures p 551 N94.34586 IBTN.94-EIX94301320144) p 546 A_4-60853 p 534 N94-34629 Operational agility assessment with the AM.X ak'oraft CHINA p 534 N9,1-34626 U Exporumental invest_getion on superson¢ _stion Dew,gn, construction, and testing of a five sc_ve axes (2) magnebc bearmg system p 554 N94-35846 UNITED KINGDOM IBTN.94-EIX943511449e51 p 537 A94-60447 Axial compressor performance dunng surge Computabon and discussmn of a needy constant degroe J IBTN-94-EIX94321333308} p 548 A94-60040 of reaction tutt)ine stage Expenrrmntal atudms of vortex flaps and vortex plates IBTN.94-EIX94351144987] p 537 A94.60449 JAPAN I STN-94-EIX94311329122 } p518 A94-60178 Combustion performance of dump combuslor in ramjet Analys_s of aerodynamK:s of air/oils mowng over a wavy Computational anatys=s of a single let impingement engme usmg liquid hydrogen fuel wall grOUnd effect lift loss I BTN-94-EIX94351144992] p 538 A94.60454 {BTN-94-EIX94311329130] p 536 A94-60170 [BTN+94-EIX94311329114 ] p519 A94-60186 D-1 USSR FOREIGN TECHNOLOGY INDEX Harrier 2: A comparrson of US and UK approaches to fat_jue clearance p 531 N94-34596 Fatigue desKjn, test and in-se_/_oa expermnce of the BAe Hawk p 531 N94-34597 Engine characteristics for agile aircraft p 538 N94-34608 Design of integrated flight and powerplant control systems p 532 N94-34609 Dynamic tests to demonstrate lateral control using foreboOy suction on large scale models in the DRA 24 toot wind tunnel p 539 N94-34613 Yaw control by tangential forebody blowing p 539 N94-34615 Control of leading-edge separation on a cambered delta wing p 539 N94-34616 Operational aglUty: An overview of AGARD Working Group 19 p 534 N94-34625 The influerc-e of flying qoalitms on operational eg/lily p 534 N94-34628 Engineering large-scale agent-based systems with consensus p 558 N94-35071 The simulation of a propulsive pet end force rrmasurernent using a magnetcally suspended wfnd tunnel model p 527 N94-35855 USaR Aerodynamic design ol super maneuverable alrcrafl p 533 N94-34617 I).2 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 308) September 1994 Typical Contract Number RTOP 505-62-84 ...... p 543 N94-34919 RTOP 505-64-13-01 ...... p 529 N94-36048 Index Listing RTOP 505-68-00 ...... p 535 N94-35241 RTOP 505-68-50 ...... p 535 N94-34703 RTOP 505-90-52-01 ...... p 558 N94-35240 p 528 N94-35994 RTOP 509-10-11o02 ...... p 551 N94-34722 RTOP 533-02-34 ...... p 540 N94-35258 AF PROJ. 2404 ...... p 44 N94-17461 RTOP 533-02-37 ...... p 540 N94-34994 F--- RTOP 535-03-10-02 ...... p 526 N94-35246 RTOP 537-03-23 ...... p 522 N94-35394 CONTRACTI ACCESS O. RTOP 537-04-20 ...... p 543 N94-35267 NUMBER INUMBER J I NUMBER RTOP 550-00-00 ...... p 545 N94-35605 RTOP 552-00-00 ...... p 557 N94-34921 p 558 N94-35256 SRC-88-MC-507 ...... p 555 N94-35907 Listings In this index ere arranged alphanumeri- cally by contract number. Under each contract number the accession numbers denoting docu- ments that have been produced as a result of research done under the contractare 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. 2308 ...... 539 N94-35746 AF-AFOSR-O005-91 ...... 526 N94-35529 AF-AFOSR-0074-87 ...... 524 N94-34974 AF-AFOSR-0249-90 ...... 524 N94-34974 AF-AFOSR -0412-91 ...... 527 N94-35950 DA PRO J, 1 L1-62211 -A-47 ...... 538 N94.34993 DAAJ02-92-C-0055 ...... 554 N94-35903 DE-AC04-94AL-85000 ...... 526 N94-35360 DTFA01-93-Z-02012 ...... 556 N94-35596 p 556 N94-35720 p 557 N94-35807 F 19628-90-C-0002 ...... p 556 N94-35720 557 N94-35807 F49620-86-0-0133 ...... 525 N94-34987 F49620-88-C-0061 ...... 524 N94-34970 F49620-92-J-0012 ...... 527 N94-35717 NAGW-1682 ...... 560 N94-34730 NAG1-1173 ...... 556 N94-35974 NAG1-1193 ...... 527 N94-35864 NAG1-1371 ...... 537 N94-35055 NAGI-790 ...... 523 N94-34964 523 N94-34965 NAG2-477 ...... 541 N94-35874 NAG3-1450 ...... 539 N94-35352 NAG3-1507 ...... 553 N94-35500 NAG9-681 ...... 522 N94-34704 N AS 1 - 19480 ...... 558 N94-35240 528 N94-35994 NAS2-13383 ...... 528 N94-35991 NAS2-13721 ...... 560 N94-36031 NAS3-24226 ...... 538 N94-34679 NAS3-25266 ...... 543 N94-34919 543 N94-35267 NAS3-26075 ...... :J538 N94-34993 NAS3-27186 ...... 552 N94-35224 :=556 N94-35945 NCC1-188 ...... 529 N94-35522 NCC2-420 ...... :J526 N94-35498 NCC2-486 ...... 528 N94-34915 NC03-233 ...... 539 N94-35352 NSF DMR-88-21625 ...... 555 N94-35907 NSF EOS-91-16566 ...... 555 N94-35907 N00014-91-J-1876 ...... 555 N94-35907 RTOP 233-03-01-O1 ...... p 546 N94-35902 RTOP 307-51-50 ...... 561 N94-35370 RTOP 505-59-50-05 ...... 527 N94-35864 RTOP 505-59-52 ...... 523 N94-34948 RTOP 505-59-53 ...... 552 N94-34966 RTOP 505-62-10 ...... p 556 N94-35945 RTOP 505-62-20 ...... ) 552 N94-35224 RTOP 505-62-52 ...... 539 N94-35352 E-1 REPORT NUMBER INDEX AERONAUTICAL ENGINEERING / A Continuing Bibfiography (Supplement 308) September 1994 BTN-94-EIX94301315980 ...... p 515 A94-60016 BTN-94-EIX94331337502 ...... p 530 A94-60337 Typical Report Number BTN-94-EIX94301315981 ...... :) 547 A94-60017 BTN-94-EIX94341338356 ...... p ,546 A94-60348 Index Listing BTN-94-EIX94301315989 ...... ,515 A94-60025 BTN-94*EIX94341338357 ...... p 559 A94-60349 BTN-94-EIX94301315990 ...... 515 A94-60026 BTN-94-EIX94341338360 ...... p 550 A94-60352 " BTN-94-EIX94341338362 ...... p 522 A94-60354 BTN-94-EIX94301315991 ...... 547 A94-60027 BTN-94-EIX94341338369 ...... p 559 A94-60361 BTN-94-EIX94301315993 ...... 515 A94-60029 ON BTN-94-EIX94351137055 ...... p 544 A94-60395 " BTN-94-EIX94301315995 ...... 515 A94-60031 SPONSOREDNASA IMICROFICHEJ BTN-94-EIX94351137056 ...... p 544 A94..60396 " BTN-94-EIX94301315998 ...... 547 A94-60034 BTN-94-EIX94351137057 ...... p 544 A94-60397 ° BTN-94-EIX94301315999 ...... 516 A94-60035 BTN-94-EIX94351137058 ...... p 544 A94,-60398 " BTN-94-EIX94301316000 ...... 549 A94-60256 NASA-CR-167690 ...... p 139 N94-12810 " # BTN-94-EIX94351137059 ...... p 545 A94-60399 " BTN-94-EIX94301320144 ...... 546 A94-60853 BTN-94-EIX94351137060 ...... p 545 A94-60400 " --V-- BTN-94-EIX94301320164 ...... 546 A94-60873 BTN-94-EIX94351137065 ...... p 545 A94-60405 * REPORTI _ ACCESS,ONI BTN-94-EIX94301321378 ...... 546 A94-60892" BTN-94-EIX94351142117 ...... p 560 A94-60410 NUMBER INUMBERI I NUMBER I BTN-94-EIX94311322888 ...... 520 A94-60208 " BTN-94-EIX94351142119 ...... p 550 A94-60412 BTN-94-EIX94311322891 ...... 520 A94-60205 " BTN-94-EIX94351142128 ...... p 550 A94*80421 BTN-94-EIX94311322899 ...... 557 A94-60197 BTN-94-EIX94351142133 ...... p 537 A94-60426 Listings In this Index are arranged alphanumeri- BTN-94-EIX94311322900 ...... 520 A94-60196 BTN-94-EIX94351142134 ...... p 521 A94-60427 cally by report number. The page number BTN-94-EIX94311322903 ...... ) 520 A94-60193 BTN-94-EIX94351142135 ...... p 521 A94-60428 BTN-94-EtX94311322905 ...... 544 A94-60191 indicates the page on which the citation Is BTN-94-EIX94351142136 ...... p 521 A94-60429 BTN-94-EIX94311329113 ...... ) 520 A94-60187 located. The accession number denotes the num- BTN-94-EIX94351142137 ...... p 560 A94-60430 BTN-94-EIX94311329114 ...... ) 519 A94-60186 BTN-94-EIX94351142143 ...... p 521 A94-60436 " ber by which the citation is Identified. An aster- BTN-94-EIX94311329115 ...... ) 519 A94-60185 ° BTN-94-EIX94351144985 ...... p 537 A94-60447 Isk (*) Indicates that the item Is a NASA report. BTN-94-EIX94311329117 ...... 536 A94.60183 BTN-94-EIX94351144987 ...... p 537 A94--60449 A pound sign (#) Indicates that the Item Is avail- BTN-94-EIX94311329118 ...... p 519 A94-60182 BTN-94-EIX94351144992 ...... p 538 A94-60454 able on microfiche. BTN-94-EIX94311329119 ...... 530 A94-60181 BTN-94-EIX94361135426 ...... p 537 A94-60623 BTN-94-EIX94311329120 ...... p 519 A94-60180 " BTN-94-EIX94361135427 ...... p 521 A94-60624 BTN-94-EIX94311329121 ...... 519 A94-60179 ° BTN-94-EIX94361135428 ...... p 522 A94-60625 A-91055 ...... p 552 N94-34966 " # BTN-94-EIX94311329122 ...... 5t8 A94-60178 A-92175 ...... p 522 N94-35394 " # BTN-94-EIX94311329123 ...... 518 A94-60177 ° DOT/FAA/AM-94/11 ...... p528 N94-35236 # A-93031 ...... p 561 N94-35370 " # BTN-94-EIX94311329124 ...... 557 A94-60176 " A-93034 ...... p 561 N94-35961 " # BTN-94-EIX94311329125 ...... 549 A94-60175 DOTIFAAICT-93165 ...... p 547 N94-35795 A-93047 ...... p 523 N94-34948 " # BTN-94-EIX94311329126 ...... p 536 A94-60174 ° A-93080 ...... p 540 N94-34994 " # BTN-94-EIX94311329127 ...... 518 A94-60173 DOT/FAA/RD-94/12 ...... p 557 N94-35807 A-94041 ...... p561 N94-36117 " # BTN-94-EIX94311329128 ...... 536 A94-60172 DOTIFAAIR[:)-9415 ...... p 556 N94-35720 BTN-94-EIX94311329129 ...... 518 A94-60171 A-94056 ...... p 528 N94-35991 " # DOTIFAAIRD.9419 ...... p 556 N94-35596 A-94079 ...... p528 N94-34915 " # BTN-94-EIX94311329130 ...... 3 536 A94-60170 BTN-94-EIX94311329131 ...... 518 A94-60169 E-8638 ...... p 538 N94-34993 ° # BTN-94-EIX94311329132 ...... 518 A94-60168 AD-A278573 ...... p 530 N94-36184 E-8691 ...... p 543 N94-34919 * # BTN-94-EIX94311329134 ...... 517 A94-60166 AD-A278650 ...... p 547 N94-35795 E-8770 ...... p 543 N94-35267 " # BTN-94-EIX94311328136 ...... 517 A94-60164 AD-A278675 ...... p 540 N94-35796 E-8852 ...... p 556 N94-35945 " # BTN-94-EIX94311329137 ...... 517 A94-60163 " AD-A278859 ...... p 527 N94-35826 E-8903 ...... p 539 N94-35352 " # BTN-94-EIX94311329138 ...... ) 517 A94-60162 AD-A2.78871 ...... p 556 N94-35596 E-8920 ...... p 552 N94-35224 " # AD-A278903 ...... p 553 N94-35803 BTN-94-EIX94311329139 ...... 549 A94-60161 BTN-94-EIX94311329140 ...... ) 536 A94-60160 AD-A278942 ...... p 527 N94-35717 EDR-16346 ...... p 538 N94-34679 " # AD-A278957 ...... p 557 N94-35e07 BTN-94-EIX94311329141 ...... ) 517 A94-60159 AD-A278959 ...... p 556 N94-3572CI BTN-94-EIX94311329142 ...... ) 517 A94-60158 H-1942 ...... p 535 N94-34703 ° # AD-A278988 ...... p 526 N94-35529 BTN-94-EIX94311329143 ...... ) 517 A94-60157 " H-1988 ...... p 540 N94-35258 ° # BTN-94-EIX94311329145 ...... 517 A94-60155 AD-A278989 ...... p 527 N94-35950 H-1990 ...... p 535 N94-35241 " # AD-A279028 ...... p 539 N94-35746 BTN-94-EIX94311329146 ...... 517 A94-00154 BTN-94*EIX94311329147 ...... ) 517 A94-60153 ICASE-94-26 ...... p 558 N94-35240 " # BTN-94-EIX94311329148 ...... 517 A94-60152 AFIT/GAE/ENY/94M-3 ...... p 540 N94-35796 ICASE-94-29 ...... p 528 N94-35994 " # BTN-94-EIX94311329149 ...... 516 A94-60151 BTN-94-EIX94311330648 ...... 559 A94-60143 ° AFIT/GOR/ENS/94M-13 ...... p 530 N94-36184 ICOMP-94-10 ...... p 539 N94-35352 " # BTN-94-EIX94311330650 ...... 516 A94-60141 BTN-94-EIX94311330652 ...... 548 A94-60139 AFOSR-TR-94-0275 ...... p 539 N94-35746 INT-PATENT-CLASS-G01F-1/68 . p 552 N94-35074 " BTN-94-EIX94311330654 ...... 548 A94-60137 INT-PATENT-CLASS-G01M-9/11 p 552 N94-35074 ° AFOSR-94-O268TR ...... p 527 N94-35950 BTN-94-EIX94311330660 ...... 548 A94..60131 BTN-94-EIX94311330678 ...... 516 A94-60113 AFOSR-94-0269TR ...... p 526 N94-35529 ISBN-92-835-0734-7 ...... p 550 N94-34581 # BTN-94-EIX94311330679 ...... 543 A94-60112 AFOSR-94-0278TR ...... p 527 N94-35717 ISBN-92-835-0740-1 ...... p 532 N94-34605 # BTN-94-EIX94311330681 ...... 543 A94-60110 BTN-94-EIX94311330685 ...... 543 A94-60106 AGARD-CP-548 ...... p 532 N94-34605 # JPRS-UST-94--005 ...... p 553 N94-35342 # BTN-94-EIX94311330690 ...... 548 A94-60101 JPRS-UST-94-006 ...... p 553 N94-35226 # AGARD-HIGHLIGHTS-93/2 ...... p 561 N94-35444 # BTN-94.EIX94311330699 ...... 516 A94-60092 JPRS-UST-94-010 ...... p 553 N94-35385 # BTN-94-EIX94311332378 ...... 550 A94-60951 BTN-94-EIX94321333305 ...... JPRS-UST-94-012 ...... p 553 N94-35387 # AGARD-R-797 ...... p 550 N94-34581 # 516 A94-60037 BTN-94-EIX94321333307 ...... 547 A94-60039 L-17260 ...... p 529 N94-36048 " # BTN-94-EIX94321333308 ...... 548 A94-_040 AIAA PAPER 94-1825 ...... p 556 N94-35945 ° # L-17263 ...... p 526 N94-35246 ° # BTN-94-EIX94321333310 ...... 518 A94-60042 • AIAA PAPER 94o2115 ...... p 535 N94-35241 " # L-17369-PT-2 ...... p 546 N94-35902 * # AIAA PAPER 94-2123 ...... p 540 N94-35258 " # BTN-94-EIX94321333311 ...... 548 A94-60043 BTN-94-EIX94321333312 ...... 548 A94-60044 o AIAA PAPER 94-2590 ...... p 543 N94-34919 " # MEMS-94-101 ...... p 527 N94-35950 AIAA PAPER 94-3209 ...... p 539 N94-35352 ° # BTN-94-EIX94321333315 ...... 52O A94-60266 BTN-94-EIX94321333316 ...... Ag4_0267 MIT-ATC-215 ...... p 556 N94-35596 ARL-CR-13 ...... p 538 N94.34993 " # BTN-94-EIX94321333317 ...... 549 A94-e0288 BTN-94-EIX94321333323 ...... 544 A94-80274 NAS 1.15:103970 ...... p 522 N94°35394 " # BTN-94-EIX94321333324 ...... 546 A94-60275 ARL-TR-334 ...... p 538 N94-34679 " # NAS 1.15:103997 ...... p 561 N94-35370 ° # BTN-94-EIX94331335528 ...... 549 A94-60209 NAS 1.15:104006 ...... p 523 N94-34948 " # BTN-94-EIX94331335529 ...... $49 A94-60210 ATC-212 ...... p 556 N94-35720 NAS 1.15:104021 ...... p 540 NS4-34994 " # BTN-94-EIX94331335530 ...... 530 A94-60211 ATC-216 ...... p 557 N94-35807 NAS 1.15:106545 ...... p 543 N94-34919 ° # BTN-94-EIX94331335531 ...... 557 A94-60212 BTN*94-EIX94331335533 ...... 530 A94-60214 NAS 1.15:106588 ...... g 556 N94-35945 " # BTN-94-EIX94301315968 ...... p 547 A94-60004 BTN-94-EIX94331337499 ...... 521 A94-60334 NAS 1.15:106618 ...... p 539 N94-35352 " # BTN-94-EIX94301315973 ...... p 559 A94-60009 BTN-94-EIX94331337500 ...... 550 A94-60335 NAS 1.15:107964 ...... p 551 N94-34721 " # BTN-94-EIX94301315979 ...... p 515 A94-60015 BTN-94-EIX94331337501 ...... 530 A94-60336 NAS 1.15:108816 ...... p 561 N94-36117 " # F-1 NAS 1.15:109124 REPORT NUMBER INDEX NAS 1 15:109124 ...... p 551 N94-34722 * # NSWCDD/TR-94/107 ...... p 559 N94-35958 # NAS 1.15:109250 ...... p 545 N94-35591 " # NAS 1.15:109791 ...... p 560 N94.35899 ° # NTSB/AAR.94/04 ...... p 529 N94-35521 # NAS 1.15:109840 ...... p 545 N94.35390 ° # NAS 1.15:109854 ...... p 541 N94-34632 " # NTSB/ARG-94/01 ...... p 528 N94-34991 # NAS 1.15:109855 ...... p 542 N94-34633 ° # NTSB/ARG-94/02 ...... p 529 N94-35496 # NAS 1.15:109856 ...... p 542 N94-34634 " # NAS 1.15:109857 ...... p 542 N94-34635 ° # NTSB/SS-94/01 ...... p 529 N94-35482 # NAS 1.15:109858 ...... p 542 N94.34636 " # NAS 1.15:109859 ...... p 542 N94.34637 # PB94-127982 ...... p 528 N94-34991 # NAS 1.15:109863 ...... p 560 N94.34730 # PB94-181054 ...... p 529 N94-35496 # NAS 1.15:4563 ...... p 526 N94.35246 # PB94-910406 ...... p 529 N94-35521 # NAS 1,15:4590 ...... p 540 N94.35258 # PB94-917001 ...... p 529 N94-35482 # NAS 1.15:4591 ...... p 535 N94.35241 # NAS 1.26:177639 ...... p 528 N94-34915 # REPT-94BO0060 ...... p 545 N94-35605 " # NAS 1.26:189344 ...... p 558 N94-35256 # NAS 1,26:189345 ...... p 557 N94-34921 # RIACS-TR-94-06 ...... p 560 N94-36031 ° # NAS 1.26:191047 ...... p 538 N94.34993 # NAS 1.26:194445 ...... p 538 N94-34679 " # RTCA-DC_155 ...... p 537 N94-35344 # NAS 1.26:194904 ...... p 558 N94-35240 " # NAS 1.26:194908 ...... p 528 N94-35994 o # SAND93_280 ...... p 526 N94-35360 # NAS 1.26:195323 ...... p 543 N94-35267 " # NAS 1.26:195343 ...... p 552 N94-35224 * # SEL-81-305SP1 ...... p 557 N94-34921 " # NAS 1.26:195929 ...... p 522 N94.34704 * # SEL-93-002 ...... p 558 N94-35256 * # NAS 1.26:195957 ...... p 523 N94-34964 " # NAS 1.26:195958 ...... p 523 N94-34965 * # UC-706 ...... p 526 N94-35360 # NAS 1,26:196021 ...... p 556 N94-35974 " # NAS 1.26:196078 ...... p 529 N94-35522 * # US-PATENT-APPL-SN-820431 ..... p 552 N94-35074 " NAS 1.26:196119 ...... 1o 553 N94-35500 " # NAS 1.26:196132 ...... p 560 N94-36031 " # US-PATENT-CLASS-73-147 ...... p 552 N94-35074 * NAS 1.26:196136 ...... IO 526 N94-35498 * # US-PATENT-CLASS-73-204.18 .... p 552 N94-35074 " NAS 1.26:4582 ...... IO 528 N94-35991 " # NAS 1.26:4612 ...... p 527 N94-35864 " # US-PATENT-5.311,772 ...... p 552 N94-35074 * NAS 135:10134 ...... p 561 N94-35961 * # NAS 1.55:3144 ...... p 552 N94-34966 " # USAATCOM-TR-92-A-014 ...... p 523 N94-34948 * # NAS 1.55:3247-PT-2 ...... p 546 N94-35902 " # NAS 1.55:3265 ...... p 545 N94-35605 " # NAS 1.60:3399 ...... p 529 N94-36048 * # NAS 1.61:1332 ...... p 535 N94-34703 " # NASA-CASE-LAR-14612-1 ...... p 552 N94-35074 ° NASA_P-10134 ...... p 561 N94-35961 * # NASA-CP-3144 ...... p 552 N94-34966 " # NASA-CP-3247-PT-2 ...... p 546 N94-35902 * # NASA-CP-3265 ...... p 545 N94-35605 " # NASA-CR-177639 ...... p 528 N94-34915 * # NASA-CR- 189344 ...... p 558 N94-35256 " # NASA-CR-189345 ...... p 557 N94-34921 " # NASA-CR-191047 ...... p 538 N94-34993 " # NASA-CR-194446 ...... p 538 N94-34679 * # NASA'CR-194904 ...... p 558 N94-35240 * # NASA-CR-19490e ...... p 528 N94-35994 * # NASA-CR-195323 ...... p 543 N94-35267 " # NASA-CR-195343 ...... p 552 N94-35224 o # NASA-CR- 195929 ...... p 522 N94-34704 * # NASA-CR-195957 ...... p 523 N94-34964 * # NASA_,,R- 195958 ...... p 523 N94-34965 " # NASA-CR-196021 ...... p 556 N94-35974 " # NASA-CR-196078 ...... p 529 N94-35522 " # NASA-CR-196119 ...... p 553 N94-35500 ° # NASA-CR-196132 ...... p 560 N94-36031 * # NASA-CR-196136 ...... p 526 N94-35498 " # NASA-CR-4582 ...... p 528 N94-35991 * # NASA-CR--4612 ...... p 527 N94.35864 " # NASAoRP-1332 ...... p 535 N94-34703 * # NASA-TM- 103970 ...... p 522 N94-35394 * # NASA-TM-103997 ...... p 561 N94.35370 ° # NASA-TM-104006 ...... p 523 N94-34948 * # NASA-TM-104021 ...... p 540 N94.34994 * # NASA-TM-106545 ...... p 543 N94-34919 * # NASA-TM-106588 ...... p 556 N94-35945 " # NASA-TM-108618 ...... p 539 N94-35362 " # NASA-TM-107964 ...... p 551 N94-3472t # NASA-TM-108816 ...... p 561 N94-36117 # NASA-TM-109124 ...... p 551 N94-34722 # NASA-TM-109250 ...... p 545 N94-35591 # NASA-TM-109791 ...... p 560 N94-35899 # NASA-TM-109840 ...... p 545 N94-35390 # NASA-TM-109854 ...... p 541 N94-34632 # NASA-TM-109855 ...... p 542 N94-34633 # NASA-TM-109856 ...... p 542 N94-34634 # NASA-TM-109857 ...... p 542 N94-34835 # NASA-'rM-109858 ...... p 542 N94-34636 # NASA-TM-109859 ...... p 542 N94-34637 # NASA-TMoI09863 ...... p 560 N94-34730 # NASA.TM,,4563 ...... p 526 N94-35246 # NASA-TM-4590 ...... p 540 N94-35258 # NASA-TM-4591 ...... p 535 N94-35241 # NASA-TP-3399 ...... p 529 N94-36048 ° # NPS-ME-94-O02 ...... p 527 N94-35826 F-2 ACCESSION NUMBER INDEX AERONAUTICAL ENGINEERING I A Continuing Bibliography (Supp/ement 308) September 1994 Typical Accession Number A94-60853 p 546 N94-35063 " # p 558 A94-60873 p 546 N94-35064 " # p 558 Index Listing A94-60892 " p 546 N94-35071 " # p 558 A94-60951 p 550 N94-35074 " p 552 N94-35224 " # p 552 N94.34581 # 55O N94-35226 # p 553 ON N94-34586 # 551 N94-35236 # p 528 SPONSOREDNASA IMICROFICHEI N94-34587 # 551 N94-35240 * # p 558 = ,I N94-34588 # 551 N94-35241 ° # p 535 N94-35246 " # p 526 A94-10717 " # p 71 N94-34590 " # 551 N94-34591 # 531 N94-35256 ° # p 558 N94-34592 # 531 N94-35258 " # p 540 ACCESSION N94-34593 # ) 531 N94-35262 # p 561 NUMSERI N94-34594 # } 531 N94 35267 " # p 543 N94-34595 # 531 N94-35342 # p 553 N94-34596 # 531 N94-35344 # p 537 N94-34597 # 531 N94-35352 " # p 539 Listings in this Index are arranged alphanumericefly N94-34598 # 532 N94-35360 # p 526 by accession number. The page number indicates the N94-34599 # 532 N94-35370 " # p 561 page on which the citation is located. The accession N94-34605 # 532 N94-35385 # p 553 N94-35387 # p 553 number denotes the number by which the citation is N94.34606 # 532 N94.34607 # 538 N94-35390 " # p 545 identified. An astedsk (') indicates that the item is a N94-34608 # 536 N94-35394 ° # p 522 NASA report. A pound sign (#) indicates that the Item N94-34609 # 532 N94.35444 # p 561 is available on microfiche. 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