Aeronautical Engineering

NASA SP-7037 (305) June 1994

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

(NASA-SP-7037(305)) AERONAUTICAL N94-34688 ENGINEERING: A CONTINUING BIBLIOGRAPHY WITH INDEXES (SUPPLEMENT 305) (NASA) 95 p Unclas

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AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

National Aeronautics and Space Administration Scientific and Technical Information Program Washington. DC 1994 This publication was prepared by the NASA Center for AeroSpace Information, 800 Elkridge Landing Road, Linthicum Heights, MD 21090-2934, (301) 621-0390. INTRODUCTION

This issue of Aeronautical Engineering—A Continuing Bibliography with /nctexesfNASA SP-7037) lists 239 reports, journal articles, and other documents recently announced in the NASA STI Database.

Accession numbers cited in this issue include: Scientific and Technical Aerospace Papon's (STAR) (N-10000 Series) N94-28399 — N94-30424 Open Literature (A-10000 Series) None in this issue

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

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

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

A cumulative index for 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.

iii TABLE OF CONTENTS

Category 01 Aeronautics 373

Category 02 Aerodynamics 374 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 382 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 383 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 390 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 394 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 395 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 400 Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 401 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

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

Category 11 Chemistry and Materials 403 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.

Category 12 Engineering 408 Includes engineering (general); communications and radar; electronics and electrical engineering; fluid mechanics and heat transfer; instrumentation and photography; lasers and masers; mechanical engineering; quality assurance and reliability; and structural mechanics. Category 13 Geosciences 414 Includes geosciences (general); earth resources and remote sensing; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography. ...

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

Category 15 Mathematical and Computer Sciences 415 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 416 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics.

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

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

Category 19 General N.A.

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

vi TYPICAL REPORT CITATION AND ABSTRACT

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

vii AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 305) June 1994

01 N94-28743# Air Force Inst of Tech., Wright-Patterson AFB. OH. School of Logistics and Acquisition Management AERONAUTICS (GENERAL) DEMONSTRATION OF IMPROVED SOFTWARE SUPPORT LABOR ESTIMATION FOR AIR FORCE OPERATIONAL FLIGHT PROGRAMS THROUGH FUNCTIONAL ORIENTATION M.S. Thesis N94-28666* Naval Aviation Logistics Center. Patuxent River. RONALD R. WARNER. JR. and DARREL L. WRIGHT Dec. 1993 MD. Maintenance Office. 251 p AIRCRAFT AGE IMPACTS ON MAINTENANCE (AD-A275789; AFIT/GSS/LAS/93D-7) Avail: CASI HC A12/MF A03 REQUIREMENTS This study demonstrated two approaches to improve current JOHN JOHNSON Sep. 1993 21 p software support effort estimation models for aircraft software. Both (AD-A275701) Avail: CASI HC A03/MF A01 approaches involved a functional orientation not used by existing Under the current defense environment decreasing economic models. The first approach demonstrated how to orient a model to resources limit new aircraft acquisition programs. As a consequence reflect the block change cycle modification process and how to repre- the Services will be forced to operate aging aircraft without replacement sent support effort changes over time in order to improve effort for many critical missions. The impact of this average age increase estimation accuracy- Current software models do not reflect the support upon future Operating and Support (O&S) costs must be assessed environment or the temporal characteristics of aircraft software sup- properly if the Department of Defense decision makers are to make port The second approach demonstrated how to calibrate a model by properly informed downsizing decisions. The Naval Aviation Mainte- property selecting source data in order to increase accuracy. Support nance Office, Logistics Engineering Department, Resource Analysis calibration is not addressed by current models. A literature search Division, has developed methodology, techniques and procedures for affirmed the validity of both approaches and the methodology. In evaluating potential relationships between the age of in service aircraft addition, a standard description of the block change cycle was devel- and their O&S costs using existing data bases. The incidence of verified oped and validated. A prototype estimation model was derived from the material failures (VF) and the Direct Maintenance Manhours (DMH) COCOMO model and included a unique support calibration. Data was expended to correct them are correlated to the aircraft's age during its obtained from Air Force Software Support Centers but was unusable, in-service operational life and are potential indicators of increased O&S so data was generated from the prototype for the demonstration. A Costs. The Naval Aviation Logistics Data Analysis (NALDA) data bases method that was developed to compare the prototype with current for Navy and Marine Corp aircraft contain historical operations and models demonstrated that the prototype is an acceptable model. maintenance data which can serve as age indicators. DTIC DTIC

N94-29090 Aeronautical Research Labs., Melbourne (Australia). FISHERMANS BEND: A CENTRE OF AUSTRALIAN AVIATION N94-28732* Naval Aviation Logistics Center. Patuxent River, MD. J.LKEPERT Sep. 1993 75 p Limited Reprodudbility. More than 20% Maintenance Office. of this document may be affected by microfiche quality AIRCRAFT AGE IMPACT ON INDIVIDUAL OPERATING AND (AD-A274981; ARL-GD-39; DODA-AR-008-377) Avail: CASI HC ACM SUPPORT COST ELEMENTS Since 1919, Fishermens Bend, Victoria, has been a major center LAURENCE STOLL and STAN DAVIS Sep. 1993 40 p of Australian aviation. Many of Australia's great aviation achievements (AD-A275739) Avail: CASI HC A03/MF A01 were bom there. From its formation in 1939, the Aeronautical Research This study develops methodology, techniques and procedures Laboratory, situated astride this activity at the Bend, has provided for evaluation of age related cost trends associated with major catego- scientific and technical support to numerous aeronautical endeavors ries of Operating and Support cost Data sources including Naval occurring in Its surrounds. This report summarizes the many activities Aviation Logistics Data Analysis (NALDA) history, Chief of Naval at the Bend from the first flight of an S11 Shorthorn from the Carey Operations Flying Hour Projection System Budget Analysis Reports, Airfield in 1919 to the production to the last indigenously built aircraft, Visibility and Management of Operating and Support Cost Maintenance the Nomad, in 1984. The aerodromes have long gone, the roar of aero- Subsystem and Total Support System reports, and Naval Depot engines are contained within test cells, but the strong tradition of Production Performance Reports (PPR's) were used to evaluate cost Australian aviation still lives on at the Bend today. DTIC trends over the most recent ten years of cost data Detailed data was collected on ten major Type Model Series aircraft including the P-3C, N94-29160 Sumitomo Heavy Industries Ltd., Tokyo (Japan). S-3A, F/A-18A/B, F-14A, CH-53E, SH-60B, E-2C, SH-3H, CH-46E and STUDY OF BRIDGE DESIGN AND TECHNOLOGY A-6E Evaluations of age related trends and recommendations for 1993 89 p In JAPANESE changes in current estimating processes when appropriate have been (PB94-137916) Copyright Avail: Issuing Actrvity (National Technical developed forthe following cost categories; (1) Oil Level Consumables/ Information Service (NTIS)) Repair Parts (2) AVDLR's; (3) Aircraft Overhaul/Support (4) Engine Contents: Study of Super Long-span Bridge; ATMD System for Overhaul/Support; (5) Petroleum, Oil. Lubricants (POL); (6) O and I Vibration Suppression on Bridge Tower Effects of Turbulence Flow on level labor requirements. Results of this study dearly demonstrate age Aerodynamic Characteristics of Box Girder Bridges; Aerodynamic related trends of increasing costs linked to aircraft service life fleet age' Stability of Bridge Tower; Fabrication of 780N/mm2 Class High Tensile for most of the categories under examination. DTIC Steels Made Truss Member Chord; Structural Analysis System of Long

373 01 AERODYNAMICS (GENERAL)

Span Bridge; Design of Akashikaikyoohashi Bridge; Design and 02 Vibration Control of Tsurumi Fairway Bridge; Fabrication, Erection and Cable Vibration Control of Kemi 1 -gousen Bridge; Repair Work of Girder AERODYNAMICS on Hanshin Expressway Accidentally Damaged by Falling Heavy Load; Countermeasure for Infra-sound and Erection of Dodairazawabashi Includes aerodynamics of bodies, combinations, wings, rotors, and Bridge; Design, Fabrication, and Laying Down of 4A Steel Caisson for control surfaces; and internal flow in ducts and turbomachinery. Kurushima-ohashi Bridge. NTIS . . ( N94-28658*# National Aeronautics and Space Administration. Lan- gley Research Center, Hampton, VA. STEADY PRESSURE MEASUREMENTS ON AN AEROELASTIC RESEARCH WING (ARW-2) N94-29463* Aerospatiale, Paris (France). MAYNARD C. SANDFORD, DAVID A. SEIDEL, and CLINTON V. A TIME REASONING SYSTEM BASED ON THE EVENT ECKSTROM Feb. 1994 537 p CALCULUS FOR SCHEDULING IN AERONAUTIC (Contract RTOP 505-63-50-15) MAINTENANCE Ph.D. Thesis - Toulouse Univ. [UN (NASA-TM-109046; NAS 1.15:109046) Avail: CASI HC A23/MF A04 SYSTEME DE RAISONNEMENT TEMPOREL BASE SUR LE Transonic steady and unsteady pressure tests have been con- CALCUL D'EVENEMENTS POUR L'ORDONNANCEMENT EN ducted in the Langley transonic dynamics tunnel on a large elastic wing MAINTENANCE AERONAUTIQUE] known as the DAST ARW-2. The wing has a supercritical airfoil, an DENYS BERNARD 1993 214 p In FRENCH aspect ratio of 10.3, a leading-edge sweep back angle of 28.8 degrees, (REPT-932-710-101; ETN-94-95487) Avail: CASI HC A10/MF A03 and two inboard and one outboard trailing-edge control surfaces. Only Problems specific to the planning and scheduling of aircraft the outboard control surface was deflected to generate steady and maintenance work sites are addressed. Methods presently employed unsteady flow over the wing during this study. Only the steady surface and their associated problems are considered. The event calculus of pressure, control-surface hinge moment, wing-tip deflection, and wing- Kowaslki and Sergot is introduced. Its adaptation to the domain of root bending moment measurements are presented. The results from aircraft maintenance is considered, together with the associated infer- ence rules. This permits an appropriate representation of the whole of this elastic wing test are in tabulated form to assist in calibrating the actions which are treated in a particular problem. A description of all advanced computational fluid dynamics (CFD) algorithms. the axioms characterizing the different types of situation for which a plan Author (revised) is to be prescribed is given. This presupposes that the scheduling takes out or prevents intervention of tugs' which could constrain the time N94-28674# Naval Postgraduate School, Monterey, CA. organization of the actions. The sequencing processed by the com- AERODYNAMIC DESIGN USING PARALLEL PROCESSORS puter architecture is considered. The organization of the system is Ph.D. Thesis explained. The last program tested is presented. ESA STEPHEN C. BRAWLEY Sep. 1993 152p (AD-A275470) Avail: CASI HC A08/MF A02 An airfoil design technique has been developed which decreases the computational processing time by more than an order of magnitude when optimizing aerodynamic performance. The practicality of airfoil design using parallel processors and Navier-Stokes flow solvers has N94-29842# Lawrence Livermore National Lab., CA. been demonstrated. Typically, an airfoil is designed to meet certain DUAL-BAND INFRARED (DBIR) IMAGING INSPECTIONS OF criteria based upon its aerodynamic performance at set flight condi- BOEING 737 AND KC-135 AIRCRAFT PANELS tions. If an optimization technique is used for airfoil design, the shape N. K. DELGRANDE, K. W. DOLAN, P. F. DURBIN, M. R. GORVAD, and of the airfoil is varied, and the aerodynamic performance of numerous A. B. SHAPIRO 27 Aug. 1993 55 p airfoil geometries are evaluated using computational fluid dynamics. (Contract W-7405-ENG-48) Multiple aerodynamic performance evaluations require the vast major- (DE94-005700; UCRL-CR-115237) Avail: CASI HC A04/MF A01 ity of computational processing time used in airfoil design optimization. We apply dual-band infrared (DBIR) imaging as a dynamic DTIC thermal tomography tool for wide area inspection of a Boeing 737 aircraft and several Boeing KC-135 aircraft panels. Our analyses are discussed in this report. After flash-heating the aircraft skin, we record N94-28899* Polytechnic Univ., Brooklyn, NY. Dept of Aerospace synchronized DBIR images every 40 ms, from onset to 8 seconds after Engineering. the heat flash. We analyze selective DBIR image ratios which enhance EXPERIMENTAL INVESTIGATION OF THREE-DIMENSIONAL surface temperature contrast and remove surface-emisstvity clutter VORTEX-AIRFOIL INTERACTION IN A SUPERSONIC STREAM (from dirt, dents, tape, markings, ink, sealants, uneven paint, paint Final Report, 15 Oct. 1992-14 Oct. 1993 stripper, exposed metal, and roughness variations). The Boeing 737 IRAJ M. KALKHORAN Dec. 1993 30 p and KC-135 aircraft fuselage panels have varying percent thickness (Contract F49620-93-1-0009) losses from corrosion. We established the correlation of percent (AD-A275107; POLY-AE-93-8; AFOSR-94-0027TR) Avail: CASI HC thickness loss with surface temperature rise (above ambient) for a A03/MF A01 partially corroded F-18 wing box structure and several aluminum An experimental study involving interaction between streamwise reference panels. Based on this correlation, lap splice temperatures wing-tip vortices and a two-dimensional lifting surface in a supersonic rise 1C per 24 +/- 5 % material loss at 0.4 s after the heat flash. We show stream was conducted. The experiments were designed to simulate tables, charts and temperature maps of typical lap splice material interaction of supersonic vortices with aerodynamic surfaces of high- losses for the riveted (and bonded) Boeing 737 and the riveted (but speed aircraft and missiles. The experimental scheme involves posi- unbonded) Boeing KC-135. We map the fuselage composite thermal tioning an instrumented two-dimensional wedge downstream of a inertia, based on the (inverse) slope of the surface temperature versus semi-span wing so that the trailing tip-vortex from the wing interacts with inverse square root of time. Composite thermal inertia maps character- the aerodynamic surface. Experimental results indicate that the inter- ize shallow skin defects within the lap splice at early times (less than 0.3 action strongly depends on the vortex strength and vortex proximity to s) and deeper skin defects within the lap splice at late times (greater the wedge leading edge. In their most organized form, distortion of than 0.4 s). Late time composite thermal inertia maps depict where streamwise vortices upon interacting with the wedge was found to result corrosion-related thickness losses occur. Lap splice sites on a typical in formation of symmetric detached shock fronts far upstream of the Boeing KC-135 panel with low composite thermal inertia values had wedge leading edge followed by an apparent slip surface separating a high skin-thickness losses from corrosion. DOE subsonic region from a supersonic zone. Interaction of vortices with

374 AERODYNAMICS 02

oblique shock wave over the wedge section indicates that interaction of N94-28954* Tohoku Univ., Sendai (Japan). Div. of Engineering. a relatively weak vortex with a moderate strength oblique shock does HIGHER-ORDER ACCURATE NUMERICAL SIMULATION OF not lead to significant changes in the vortex structure. On the other 3D SUPERSONIC MIXING LAYERS [SANJIGEN CHOONSOKU hand, interaction of a moderate strength vortex with a strong oblique KONGOSO NO KOJI SEIDO SUCHI SHIMYURESHON] shock results in the formation of a detached shock wave upstream of KOICHIISHIZAKA, SATORU YAMAMOTO, and HISAAKIDAIGUJI In the oblique shock front D TIC NAL, Proceedings of the 10th NAL Symposium on Aircraft Computa- tional Aerodynamics p 39-44 Dec. 1992 In JAPANESE Avail: CASI HC A02/MF A03 : N94-28946# National Aerospace Lab., Tokyo (Japan). The purpose of the present paper is to perform direct numerical PROCEEDINGS OFTHE10TH NAL SYMPOSIUM ON AIRCRAFT simulations of the time-developing subsonic and supersonic mixing COMPUTATIONAL AERODYNAMICS [DAI 10 KAI KOKUKI layers. In order to simulate unsteady shock-vortex interactions accu- KEISAN KUKI RIKIGAKU SHINPOJIUM U RONBUNSHU] rately, a fourth-order accurate shock capturing scheme is used. This Dec. 1992 268 p In ENGLISH and JAPANESE Symposium held in scheme is based on the third-order accurate upwind finite-difference Tokyo, Japan, 10-12 Jun. 1992 scheme and the accuracy can be extended to fourth(fifth)-order by (ISSN 0289-260X) (NAL-SP-19; JTN-94-80612) Avail: CASI HC A12/ adopting additional compact terms into the schemes. The resolution is MFA03 higher than the existing scheme and the algorithm is simpler than the The following topics were discussed: Monte Carlo simulation ENO (Essentially Non-Oscillatory) scheme. Finally, some numerical using variable soft sphere model, numerical simulation of shock wave, results of subsonic and supersonic mixing layers are shown and the airfoil design using Navier-Stokes code, numerical analysis of super- reliability is discussed in comparison with the ordinary numerical sonic flow, numerical simulation of three dimensional shear flow, and scheme. Author (NASDA) programming and interface for numerical wind tunnel. Author (NASDA) N94-28955* National Aerospace Lab., Tokyo (Japan). NUMERICAL SIMULATION OF AEROTHERMODYNAMIC HEATING OF HYPERSONIC SPACE TRANSPORTATION N94-28952* Kyushu Univ., Fukuoka (Japan). Dept. Aeronautics and VEHICLES [CHOKOSOKU HIKOTAI NO KURIKI KANETSU: Astronautics. CFD TO FUDOSHIKEN] NUMERICAL SIMULATION OF UNSTEADY AERODYNAMIC YUKIMITU YAMAMOTO In its Proceedings of the 10th NAL Sympo- HEATING INDUCED BY SHOCK REFLECTIONS [SHOGEKIHA sium on Aircraft Computational Aerodynamics p 45-50 Dec. 1992 In Nl YUKISARETA HITEIJO KURIKI KANETSU GENSHO NO JAPANESE SUCHI SHIMYURESHON] Avail: CASI HC A02/MF A03 SHIGERU ASO, KENICHI OHYAMA. and MASANORI HAYASHI In Numerical hypersonic aerodynamic studies of space planes, H-2 NAL, Proceedings of the 10th NAL Symposium on Aircraft Computa- Orbiting Plane (HOPE), and OREX (Orbital Re-entry Experiment) have tional Aerodynamics p 27-32 Dec. 1992 In JAPANESE been conducted for several years. In this paper, the analysis of the Avail: CASI HC A02/MF A03 aerodynamic heating and real gas effects is described. Numerical Numerical simulations on unsteady shock reflections by a ramp results are compared with the heat transfer data obtained have been conducted in order to investigate unsteady aerodynamic by various experimental techniques. Author (NASDA) heating due to shock reflection processes at higher incident shock Mach number. The two-dimensional Navier-Stokes equations with thin layer approximation are solved numerically by a TVD (Total Variation N94-28958# Mitsubishi Heavy Industries Ltd., Tokyo (Japan). Diminishing) scheme. The effect of mesh refinement to the calculated NUMERICAL ANALYSIS OF AIRFOIL FOR HELICOPTER results is investigated carefully. The results show the smaller mesh size BLADE AT HIGH ANGLE OF ATTACK USING NAVIER-STOKES is necessary for calculating precise aerodynamic heating loads and CODE [NABIE SUTOKUSU KAISEKI NIYORU HER! BUREDO capturing the fine structure of the shock reflection patterns. YOKUGATA NO KOGYOKAKU TOKUSEI SUISAN NO Author (NASDA) KOKOROMI] NAOHITO ADACHI, MITSUOISHIGURO, MASAHIRO NAKAO, NAOKI HIROSE, and MAMORU SATOU In NAL, Proceedings of the 10th NAL N94-28953* National Aerospace Lab., Kakuda (Japan). Symposium on Aircraft Computational Aerodynamics p 63-68 Dec. NUMERICAL SIMULATION OF STEADY MACH REFLECTION 1992 In JAPANESE BY SHOCK CAPTURING SCHEMES [SHOGEKIHA HOKAKUHO Avail: CASI HC A02/MF A03 NIYORU TEIJO MAHHA HANSHA NO SUCHI SHIMYURESHON] Numerical analysis using an Navier-Stokes code is conducted in TAKESHI KAN DA, KATSUHIRO ITO, KOUICHIRO TANI, and order to develop a method to simulate flow fields around helicopter MASAHIRO TAKAHASHI In its Proceedings of the 10th NAL Sympo- airfoils at high angle of attack. The results are compared with experi- sium on Aircraft Computational Aerodynamics p 33-37 Dec. 1992 In mental data to investigate the subject for the simulation of the flow fields JAPANESE at high angle of attack. Based on the investigation, the effect of the grid Avail: CASI HC A01/MF A03 system is examined. It is shown that the concentration of the grid at the Modem shock capturing schemes, i.e., solution adaptive trailing edge is important Author (NASDA) irrterpolatory schemes, supply beautiful solutions, so they are used generally even in the industrial world. There is a problem in shock N94-28959# Fuji Heavy Industries Ltd., Tokyo (Japan). capturing schemes, however, when there are plural shocks within the NUMERICAL ANALYSIS OF SUPERSONIC TRANSPORT grid points constructing a numerical flux. In order to stabilize a numeri- WINGS [CHOONSOKU YUSOKI SHUYOKU KEIJO NO SUCHI cal solution in such a scheme, the accuracy must be degenerated. Such KAISEKI] a situation can be often seen in two dimensional flow field, and steady TETSUO YAMAZAKI and TAKASHI UCHIDA In NAL, Proceedings of Mach reflection is a typical example of the plural shock flow. An the 10th NAL Symposium on Aircraft Computational Aerodynamics p analytical solution of the steady Mach reflection was shown, and an 69-74 Dec. 1992 In JAPANESE investigation of shock capturing scheme performance by comparing it Avail: CASI HC A02/MF A03 with present analysis was proposed. In this report, a newly developed Numerical analysis of supersonic transport wings was carried out scheme was also used to investigate the characteristics of the shock The drag reduction obtained by using the warped wing design technique capturing schemes, and the performances of TVD (Total Variation is from 0.0006 to 0.0010 in supersonic cruise condition. It is also clarified Diminishing) scheme and of the new scheme were compared. Car- that the drag reduction by use of Euler analysis is less than that by the buncle phenomena and entropy layer on the wall were also discussed. linear method, because the flow mechanism in supersonic region is Author (NASDA) essentially non-linear. Finally it is shown that the cranked arrow wing-

375 02 AERODYNAMICS

body configuration has the best lift to drag ratio in supersonic cruise MUSCL-type (Monotonic Upstream Centered Schemes for Conser- condition in comparison with delta or ogee wing-body configuration. vation Laws) TVD (Total Variation Diminishing) scheme based on Author (NASDA) Roe-type flux splitting for convective terms. Shock location of both numerical results and experimental data are compared and good agreement is obtained in the wide range of Mach numbers up to N94-28961# Ishikawajima-Harima Heavy Industries Co. Ltd., Tokyo M(sub infinity) =16. Shock capturing capability is good enough to .(Japan). describe very strong discontinuity with no more than three grid points. NUMERICAL SIMULATION OF SUPERSONIC FLOW AROUND Author (NASDA) SPACE PLANE WITH ENGINE INSTALLED [ENJIN TSUKI SUPESPUREN ZENKIKEIJO MAWARI NO NAGARE NO SUCHI SHIMYURESHON] N94-28965# National Aerospace Lab., Tokyo (Japan). SHINICHI KURODAand KOZO FUJI! In NAL, Proceedings of the 10th NUMERICAL SOLUTION OF INVERSE PROBLEM IN NAL Symposium on Aircraft Computational Aerodynamics p 81-86 AERODYNAMICS [KOKU RIKIGAKU NIOKERU Dec. 1992 In JAPANESE GYAKUMONDAI TO SONO KAIHO] Avail: CASI HC A02/MF A03 SUSUMUTAKANASHI In its Proceedings of the 10th NAL Symposium Airframe-engine integration is one of the most important prob- on Aircraft Computational Aerodynamics p 105-108 Dec. 1992 In lems in the area of supersonic inlet technologies. In the present paper JAPANESE the flow around an airframe-engjne integration model is numerically Avail: CASI HC A01/MF A03 simulated. Because of the geometrical complexity, the overlaid com- One of the most important inverse problems in aerodynamics is posite grid approach, based on the Fortified Solution Algorithm (FSA) defined as the problem of finding the wing section contour given the concept, is used for the discretization strategy. In the present compu- desired surface pressure distribution for a fixed wing planform. This tation, the composite grid consists of four component grids. The primary problem can be solved by the 'residual-correction' method based on the grid is constructed with respect to the airframe, and the subsidiary grids ' transonic integral equations. In this paper, some of the recent applica- are generated about the nacelle, duct, and diverter. The minor grids are tions of the integral equation method using various analysis codes used to resolve the features of the engine geometry and are overlaid on including Navier-Stokes codes are presented. Author (NASDA) the main grid. The inviscid flow field is solved for this configuration at a Mach number of 2.75 and zero deg angle of attack. Although the overall flow features are successfully simulated by this preliminary computation, further improvement of the solution quality by grid enrichment and N94-28966* Mitsubishi Heavy Industries Ltd., Tokyo (Japan). the discussion about the flow field are left as future work. CODE DEVELOPMENT FOR HYPERSONIC REAL-GAS FLOW Author (NASDA) SIMULATIONS TOWARD THE DESIGN OF SPACE VEHICLES, PART 2 [KURIKI SEKKEI TSURU TOSHITE NO GOKU CHOONSOKURYU KEISANN KODO NO KAIHATSU. SONO 2] N94-28962* Osaka Prefecture Univ., Sakai (Japan). Graduate School. MASAHIRO NAKAO and KOZO FUJII In NAL, Proceedings of the 10th NUMERICAL ANALYSIS OF SONIC BOOM IN THE NEAR FIELD NAL Symposium on Aircraft Computational Aerodynamics p 109-114 [KINOBA NIOKERU SONNIKKU BUMU NO SUCHI KAISEKI] Dec. 1992 In JAPANESE AKIHIKO YOSHIDA, KAZUHIRO NAKAHASHI, and SHOICHI FUJII Avail: CASI HC A02/MF A03 tn NAL, Proceedings of the 10th NAL Symposium on Aircraft Compu- A hypersonic flow simulation system is under development A flow tational Aerodynamics p 87-92 Dec. 1992 In JAPANESE analysis code, an adaptive grid generation code, and a computation Avail: CASI HC A02/MF A03 code of equilibrium chemical composition as a post process routine Numerical solutions of 3-D Euler equations are obtained for have been developed. The flow analysis code that is based on 3-D supersonic flows in order to investigate the sonic boom pressure upwind flux splitting scheme using the VEG (Variable Equivalent signatures in the near field. The models used in the calculations are a Gamma) method has been improved in order to simulate heat transfer body of revolution and two wing-body configurations. The results for the distributions. Numerical simulations are conducted for flow fields body of revolution indicate good agreement with the experimental data. around HOPE (H-2 Orbiting Plane). Flow conditions are Mach number A solution-adaptive-grid method which uses tension and torsion spring of 15 and angle of attack of 30 degrees. Computed heat transfer ratio analogies is applied. The results show that this method improves the distributions are obtained. Results are compared with experimental accuracy of solutions, and that sharper pressure signatures can be data and good agreement is shown along a body symmetrical line of the calculated than those in the initial grid. Author (NASDA) tower surface. Author (NASDA)

N94-28967* Shirrdzu Corp. (Japan). N94-289638 Mitsubishi Electric Corp., Kamakura (Japan). THREE DIMENSIONAL SIMULATION OF COMPRESSIBLE NUMERICAL ANALYSIS OF TWO DIMENSIONAL/ FLOW INDUCED BY A HIGH-SPEED TRAIN MOVING INTO A AXISYMMETRIC NON-EQUILIBRIUM HYPERSONIC FLOW TUNNEL [TONNERU Nl TOTSUNYUSURU KOSOKU [NIJIGEN/JIKU TAISHO GOKU CHOONSOKU HIHEIKORYU SHARYO NIYOTTE YUKISARERU NAGAREBA NO SUCHI NO SUCHI KAISEKI] SHIMYURESHON] TAKUJIKUROTAKI In NAL, Proceedings of the 10th NAL Symposium TAKANOBUOGAWA. KOZO FUJII, and YOSHIAKITAMURA In NAL. on Aircraft Computational Aerodynamics p 93-98 Dec. 1992 In Proceedings of the 10th NAL Symposium on Aircraft Computational JAPANESE Aerodynamics p 115-120 Dec. 1992 In JAPANESE Avail: CASI HC A02/MF A03 Avail: CASI HC A02/MF A03 Numerical analysis of chemically and thermally non-equilibrium A three dimensional compressible flow induced by a practical hypersonic flow around a sphere are carried out Two-dimensional and high-speed train moving into a tunnel is numerically simulated. The flow axisymmetric full Navier-Stokes equations which have chemical and field is decomposed with the zonal method and the Fortified Solution thermal non-equilibrium effects are considered by using Park's two- Algorithm (FSA) is used as an interface scheme. The result indicates temperature model and the Landau-Tefler vibrational relaxation model. that the algorithm is efficient to handle the moving boundary configura- An efficient numerical algorithm is constructed which consists of the tions which include a complicated geometry. The flow features, such as combination of LU-SGS (Lower Upper-Symmetric Gauss-Seidel) a compression wave and an expansion wave created by the train and schemes and the implicit diagonal method for a source Jacobian matrix an increment of drag force acting on the train are clarified. for the time integration of an implicit finite difference method and Author (NASDA)

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N94-28969* Ishikawajima-Harima Heavy Industries Co. Ltd., Tokyo noise. The good agreement of numerical results with experiments for (Japan). surface pressures, wake trajectory, thrust, power, Figure of Merit, and UNSTEADY AERODYNAMIC COMPUTATIONS AROUND acoustic wave forms indicate the accuracy and suitability of the NACA0012 AT HIGH ANGLES OF ATTACK [NACA0012 numerical method. It is demonstrated that both aerodynamics and YOKUGATA MAWARI NO KOGYOKAKU NIOKERU HITEIJO acoustics information can be obtained in a single solution of the KUKIRYOKU NO KEISAN] governing equations. In Part II, the unsteady flowfield results of a two- KAZUHITO MIYATA, JIRO NAKAMICHI, and RINICHI MURAO In dimensional oscillating wing are presented for five widely used turbu- NAL. Proceedings of the 10th NAL Symposium on Aircraft Computa- lence models and compared with experiments. The accuracy and tional Aerodynamics p 127-132 Dec. 1992 In JAPANESE suitability of turbulence models for unsteady separated flow are dis- Avail: CASI HC A02/MF A03 cussed. DTIC In the present study, periodic flows are simulated around NACA 0012 airfoil at high angle of attack to validate the unsteady Navier- N94-29306# Washington State Univ., Pullman. Stokes code. Thin-layer approximated unsteady Navier-Stokes equa- AN EXPERIMENTAL STUDY OF WING TIP VORTEX IN THE tions are integrated in a time-dependent manner with Baldwin-Lomax NEAR WAKE OF A RECTANGULAR WING Interim Report, 1 turbulence model. With Mach number, 0.3 and Reynolds number, 6 x Feb. 1991 - 31 May 1993 10(exp 6), characteristics of lift, drag and moment coefficients are YOUXIN ZHENG and B. R. RAMAPRIAN Jun. 1993 209 p investigated at a variety of angles of attack. The simulated flows are (Contract DAAL03-91-G-0026) compared qualitatively with experimental results obtained by flow (AD-A275389; MME-TF-93-1; ARO-28159.6-EG) Avail: CASI HC visualization conducted in a low-speed tunnel at higher angles of A10/MF A03 attack than that at which 'stall' occurs. The similar periodicity of An experimental study of the tip vortex behind a NACA 0015 the flows is found in the experimental result. Author (NAS DA) rectangular wing of aspect ratio 4 was carried out to understand the structure and evolution of the vortex in the near-wake region. The N94-2B975* Tokyo Univ. (Japan). Graduate School. results of these experimental studies are presented in this report. These STUDY ON MIXING AND INJECTION OF HYDROGEN INTO A measurements were made nonintrusively using three-component la- SUPERSONIC FLOW [CHOONSOKURYU CHU END SUISO NO ser-Doppler velocimetry (LOV). The experiments were carried out at a FUKIDASHI TO KONGO NIKANSURU KENKYU] Reynolds number of about 180,000 in a low-speed wind tunnel. Two KAZUHIKO YOKOTA and SHOJIRO KAJI In NAL, Proceedings of the cases were studied, namely: (1) stationary wing, and (2) wing oscillating 10th NAL Symposium on Aircraft Computational Aerodynamics p 157- in pitch sinusoidally about its quarter-chord axis. The flow properties 162 Dec. 1992 In JAPANESE measured were the three components of the instantaneous velocity. Avail: CASI HC A02/MF A03 These data were processed to obtain time-mean and phase-locked flow The effects of the injection methods on mixing of hydrogen in the properties such as velocity, vorticity and turbulence. The data were free stream are investigated. The numerical simulations are performed obtained at several locations at 0.15 - 3.0 chord lengths downstream by solving the full two-dimensional Navier-Stokes equations using the from the trailing edge. The typical distributions of mean velocity, explicit symmetric total variation diminishing (TVD) scheme. As for the vorticity, circulation and turbulent intensity in the near wake are injection methods, single injection, tandem injection, and parallel presented and discussed for the stationary wing. In the case of the injection are examined. The injected hydrogen mass flow is constant in oscillating wing, the phase-locked velocity, vorticity and turbulence all cases. Injection methods are evaluated by the correlation between data show details of the evolution of the unsteady tip vortex downstream the mixing efficiency and the mass flow averaged total pressure loss at from the trailing edge. The results also show that the flow is strongly the outlet boundary of the computational region. First, the injection non-quasi-steady at the oscillation frequency studied. The results are angle is varied in case of single injection. The results show that the more fully archived on tape and are available to any interested reader. These forward the injection angle is leaned, the more deeply hydrogen can be used as database in the development of wake models for the penetrates into the free stream. Second case is tandem injection, and finite wing, and in studies of three-dimensional wing aerodynamics. the distance between or mass flow ratio of two injections is varied. The DTIC results show that the upstream injection blocks the main stream, so the barrel shock of the downstream injection becomes larger and dominant N94-29443** National Aeronautics and Space Administration. in mixing in tandem injection. Last is parallel injection, and the distance Langley Research Center, Hampton, VA. from the wall to the injection is varied. The results show that parallel LOW-SPEED LONGITUDINAL AERODYNAMIC injected hydrogen can be mixed in the free stream in spite of the fact that CHARACTERISTICS OF A FLAT-PLATE PLANFORM MODEL it has no momentum perpendicular to the free stream. The correlations OF AN ADVANCED FIGHTER CONFIGURATION between the mixing efficiency and the total pressure loss in all BRIAN E. MCGRATH (Lockheed Engineering and Sciences Co., cases show that the mixing efficiency in the parallel injection is Hampton, VA.), DAN H. NEUHART (Lockheed Engineering and Sci- two times as much as in other methods of injection. ences Co., Hampton, VA.), GREGORY M. GATLIN, and PAT ONEIL Author (NASDA) Mar. 1994 36 p Original contains color illustrations (Contract RTOP 505-68-70-05) N94-29197 JAI Associates, Inc., Mountain View, CA. (NASA-TM-109045; NAS 1.15:109045) Avail: CASI HC A03/MF A01; A FREE-WAKE EULER AND NAVIER-STOKES CFD METHOD 8 functional color pages AND ITS APPLICATION TO HELICOPTER ROTORS INCLUDING A flat-plate wind tunnel model of an advanced fighter configura- DYNAMIC STALL Final Report, 1 May 1990 - 30 Sep. 1993 tion was tested in the NASA LaRC Subsonic Basic Research Tunnel GANAPATHIR. SRINIVASAN Nov. 1993 127 p Limited Reproduc- and the 16- by 24-inch Water Tunnel. The test objectives were to obtain ibility: More than 20% of this document may be affected by microfiche and evaluate the low-speed longitudinal aerodynamic characteristics of quality a candidate configuration for the integration of several new innovative (Contract DAAL03-90-C-0013) wing designs. The flat plate test allowed for the initial evaluation of the (AD-A275416; TR-93-01; ARO-27752.8-EG-S) Avail: CASI HC A07 candidate planform and was designated as the baseline planform for This report summarizes the results of the research in two parts. the innovative wing design study. Low-speed longitudinal aerodynamic Part I describes the development and application of a free-wake Euler data were obtained over a range of freestream dynamic pressures from and Navier-Stokes computational fluid dynamics method, called 7.5 psf to 30 psf (M = 0.07 to M = 0.14) and angles-of-attack from 0 to TURNS', for helicopter applications. This finite-difference, implicit, 40 deg. The aerodynamic data are presented in coefficient form for the upwind numerical method uses structured grids, and has been used for lift, induced drag, and pitching moment. Row-visualization results calculating the viscous, three-dimensional flow-fields of rotors in hover, obtained were photographs of the flow pattern over the flat plate model forward flight, blade-vortex interactions, and high speed impulsive in the water tunnel for angles-of-attack from 10 to 40 deg. The force and

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moment coefficients and the flow-visualization photographs showed The effect of a simulated glaze ice accretion on the flowfield of a the linear and nonlinear aerodynamic characteristics due to attached semispan, reflection-plane, rectangular wing at Re = 1.5 million and M flow and vortical flow over the flat plate model. Comparison between = 0.12 was investigated. A laser Doppler velocimeter was used to map experiment and linear theory showed good agreement for the lift and the flowfield on the upper surface of the model in both the dean and iced induced drag; however, the agreement was poor for the pitching configurations at alpha = 0,4, and 8 degrees angle of attack. At low moment Author (revised) angles of attack, the massive separation bubble aft of the leading edge ice horn behaved in a manner similar to laminar separation bubbles. At alpha = 0 and 4 deg, the locations of transition and reattachment as N94-29473*# National Aeronautics and Space Administration. deduced from momentum thickness distributions, were in good agree- Langley Research Center, Hampton, VA. ment with transition and reattachment locations in laminar separation AN EXPERIMENTAL AND THEORETICAL STUDY OF THE bubbles. These values at y/b = 0.470, the certteriine measurement AERODYNAMIC CHARACTERISTICS OF SOME GENERIC location, matched well with data obtained on a similar but two dimen- MISSILE CONCEPTS AT MACH NUMBERS FROM 2 TO 6.8 sional model. The measured velocity profiles on the iced wing com- M. LEROY SPEARMAN and DOROTHY O. BRASWELL Apr. 1994 pared reasonably with the predicted profiles from Navier-Stokes 31 p computations. The iced-induced separation bubble also had features (Contract RTOP 505-69-20-01) similar to the retirculating region aft of rearward-facing steps. At alpha (NASA-TM-109110; NAS 1.15:109110) Avail: CASI HC A03/MFA01 = 0 and 4 deg, reverse flow magnitudes and turbulence intensity levels A study has been made of the experimental and theoretical were typical of those found in the recirculating region aft of rearward- aerodynamic characteristics for some generic high-speed missile facing steps. The calculated separation streamline aft of the ice hom at concepts at Mach numbers from 2 to 6.8. The basic body for this study alpha = 4 deg, y/b = 0.470, coincided with the locus of the maximum had a length-to-diameter ratio of 10 with the forward half being a Reynolds normal stress. The maximum Reynolds normal stress peaked modified blunted ogive and the rear half being a cylinder. Modifications at two locations along the separation streamline. The location of the first made to the basic body included the addition of an after body flare, the peak-value coincided with the transition location, as deduced from the addition of highly swept cruciform wings and the addition of highly swept momentum thickness distributions. The location of the second peak aft tails. The effects of some controls were also investigated with all- was just upstream of reattachment, in good agreement with measure- moving wing controls on the flared body and trailing-edge flap controls ments of flows over similar obstacles. The intermrttency factor in the on the winged body. The results indicated that the addition of a flare, vicinity of reattachment at alpha = 4 deg, y/b=0.470, revealed the time- wings, or tails to the basic body all provided static longitudinal stability dependent nature of the reattachment process. The size and extent of with varying amounts of increased axial force. The control arrange- the separation bubble were a function of angle of attack and spanwise ments were effective in producing increments of normal-force and location. Three dimensional effects were strongest at alpha = 8 deg. pitching-moment at the lower Mach numbers. At the highest Mach The calculated separation and stagnation streamlines varied little with number, the flap control on the winged body was ineffective in producing spanwise location at alpha = 0 deg. The calculated separation stream- normal-force or pitching-moment but the all-moving wing control on the lines at alpha = 4 deg revealed that the bubble was largest near the flared body, while losing pitch effectiveness, still provided normal-force centeriine measurement plane, whereas the tip-induced vortex flow increments. Calculated results obtained through the use of hypersonic and the model root-tunnel wall boundary layer interaction reduced the impact theory were in generally good agreement with experiment at the size of the bubble. These effects were most dramatic at alpha = 8 deg. higher Mach numbers but were not accurate at the lower Mach Dissert Abstr. numbers. Author (revised)

N94-29760*# Stanford Univ., CA. Dept of Aeronautics and Astro- N94-29545*# National Aeronautics and Space Administration. nautics. Langley Research Center, Hampton, VA. NUMERICAL STUDY OF THE TRAILING VORTEX OF A WING EXPERIMENTAL STUDIES OFTRANSONIC FLOW FIELD NEAR WITH WING-TIP BLOWING A LONGITUDINALLY SLOTTED WIND TUNNEL WALL Ph.D. HOCK-BIN UM Mar. 1994 136 p Sponsored by NASA. Ames Thesis • George Washington Univ., 1988 Research Center JOEL L. EVERHART and PERCY J. BOBBITT Apr. 1994 73 p (NASA-CR-195803; NAS 1.26:195803; JIAA-TR-112) Avail: CASI HC (Contract RTOP 506-40-41-01) A07/MF A02 (NASA-TP-3392; L-16423; NAS 1.60:3392) Avail: CASI HC A04/MF Trailing vortices generated by lifting surfaces such as helicopter A01 rotor blades, ship propellers, fixed wings, and canard control surfaces The results of detailed parametric experiments are presented for are known to be the source of noise, vibration, cavitation, degradation the near-wall flow field of a longitudinally slotted transonic wind tunnel. of performance, and other hazardous problems. Controlling these Existing data are reevaluated and new data obtained in the Langley 6- vortices is, therefore, of practical interest. The formation and behavior by 19-inch Transonic Wind Tunnel are presented and analyzed. In the of the trailing vortices are studied in the present research. In addition, experiments, researchers systematically investigate many pertinent wing-tip blowing concepts employing axial blowing and spanwise wall-geometry variables such as the wall openness and the number of blowing are studied to determine their effectiveness in controlling these slots along with the free stream Mach number and model angle of vortices and their effects on the performance of the wing. The 3D, attack. Row field surveys on the plane passing through the centertine unsteady, thin-layer compressible Navier-Stokes equations are solved of the slot were conducted and are presented. The effects of viscosity using a time-accurate, implicit finite difference scheme that employs on the slot flow are considered in the analysis. The present experi- LU-ADI factorization. The wing-tip blowing is simulated using the ments, combined with those of previous investigations, give a more actuator plane concept thereby, not requiring resolution of the jet slot complete physical characterization of the flow near and through the geometry. Furthermore, the solution blanking feature of the chimera slotted wall of a transonic wind tunnel. Author (revised) scheme is used to simplify the parametric study procedure for the wing- tip blowing. Computed results are shown to compare favorably with experimental measurements. It is found that axial wing-tip blowing, N94-29674 Illinois Univ., Urbana-Champaign. although delaying the rofling-up of the trailing vortices and the near-field AN EXPERIMENTAL STUDY OF THE FLOWFIELD ON A behavior of the flowfield, does not dissipate the circulation strength of SEMISPAN RECTANGULAR WING WITH A SIMULATED GLAZE the trailing vortex farther downstream. Spanwise wing-tip blowing has ICE ACCRETION Ph.D. Thesis the effect of displacing the trailing vortices outboard and upward. The ABDOLLAH KHODADOUST 1993 252 p increased "wing-span' due to the spanwise wing-tip blowing has the Avail: Univ. Microfilms Order No. DA9314893 effect of lift augmentation on the wing and the strengthening of the

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trailing vortices. Secondary trailing vortices are created at high span wise tube problem. The computed results are shown to be of high spatial wing-tip blowing intensities. Author (revised) accuracy, primarily in that shock waves are sharply captured. Dissert. Abstr. N94-29826 Maryland Univ., College Park. AN ANALYTICAL STUDY OF UNSTEADY ROTOR/FUSELAGE N94-29879 Kansas Univ., Lawrence. INTERACTION IN HOVER AND FORWARD FLIGHT Ph.D. Thesis UNSTEADY TRANSONIC AERODYNAMICS IN FREQUENCY GILBERT LEWIS GROUSE, JR. 1992 265 p DOMAIN FOR FLUTTER ANALYSIS Ph.D. Thesis Avail: Univ. Microfilms Order No. DA9315626 TAI-HSING TOM SUN 1992 100 p An analytical study of the coupled rotor/fuselage aerodynamic Avail: Univ. Microfilms Order No. DA9313180 environment is presented. Results from the analysis are used to help A finite difference method for calculating the three dimensional understand the nature of interactional phenomena on helicopters. Two nonlinear transonic flow in the frequency domain is presented for the analytical methods have been developed, and results from these solution of unsteady pressure distribution. The averaging technique is models are compared with experimental measurements on a represen- employed to separate the governing equation into the in-phase and the tative rotor/body model. The first method is a simplified analysis that out-of-phase equations. These two equations are then solved simulta- treats the fuselage asaplanarsurface.This model is very computationally neously with the finite difference scheme adopted in an existing steady efficient and is particularly useful for studying the pressure on the upper code. The modified code is verified by comparing the calculated results surface of the fuselage induced by the rotor and its wake. The second, with experimental data and existing computational method fora uniform and more comprehensive, model is the MURFI (Maryland Unsteady rectangular wing with NACA 64A010A airfoil, ONERA M6 wing, a Rotor/Fuselage Interaction) model and consists of an unsteady source uniform rectangular wing with symmetrical circular arc airfoil in pitching panel representation of the fuselage coupled with a lifting line rotor or structural bending oscillations. The results are shown in good model and several different wake models. This analysis is more agreement in most cases. The effects on the unsteady characteristics computationally expensive than the simplified model, but is capable of of grid number and convergence criterion are discussed. A new studying the entire coupled rotor/fuselage flowfield. In addition, the methodology for solving the nonlinear flutter condition is also dis- latter model is also used for the prediction of the effects of the fuselage cussed. The formulations using the Beecham-Titchner method shows on the rotor flowfield. A new helicopter free-wake methodology is also that the flutter conditions can be easily determined. Dissert Abstr. presented. The new model overcomes the well known instability of traditional free-wake methods in hover and in low-speed flight. In N94-29893'* Eloret Corp., Palo Alto, CA. addition, the new method achieves this capability without an appre- PARTICLE KINETIC SIMULATION OF HIGH ALTITUDE ciable increase In computational effort. This model is particularly useful HYPERVELOCITY FLIGHT Final Technical Report, 1 Jan. for interactional aerodynamics since the most severe wake/fuselage 1989-31Jan. 1994 interactions occur in the hover and low-speed flight regime. Using these IAIN BO YD and BRIAN L HAAS 19 Apr. 1994 17 p analytical models, results are shown that clearly demonstrate the (Contract NCC2-582) capability of potential flow analyses to predict interactional effects, (NASA-CR-194535; NAS 1.26:194535) Avail: CASI HC A03/MF A01 provided that all of the pertinent unsteady terms are included in the Rarefied flows about hypersonic vehicles entering the upper analysis. In particular, it is shown that the unsteady terms due to the atmosphere or through nozzles expanding into a near vacuum may only time-rate-of-change of the surface source elements are very important be simulated accurately with a direct simulation Monte Carlo (DSMC) to prediction of the surface pressure response. The analysis has also method. Under this grant, researchers enhanced the models employed provided an improved understanding of the effects of the fuselage on in the DSMC method and performed simulations in support of existing the rotor loads and performance. Dissert Abstr. NASA projects or missions. DSMC models were developed and validated for simulating rotational, vibrational, and chemical relaxation N94-29877 Purdue Univ., West Lafayette, IN. in high-temperature flows, including effects of quantized enharmonic TIME-MARCHING AEROELASTIC AND SPATIAL ADAPTATION oscillators and temperature-dependent relaxation rates. State-of-the- PROCEDURES ON TRIANGULAR AND TETRAHEDRAL art advancements were made in simulating coupled vibration-dissocia- MESHES USING AN UNSTRUCTURED-GRID EULER METHOD tion recombination for post-shock flows. Models were also developed Ph.D. Thesis to compute vehicle surface temperatures directly in the code rather than RUSS DAVID RAUSCH 1992 301 p requiring isothermal estimates. These codes were instrumental in Avail: Univ. Microfilms Order No. DA9314067 simulating aerobraking of NASA's Magellan spacecraft during orbital Two-and three-dimensional, unstructured-grid, upwind-type Euler maneuvers to assess heat transfer and aerodynamic properties of the codes were modified to include time-marching aeroelastic and spatial delicate satellite. NASA also depended upon simulations of entry of the adaptation procedures on triangular and tetrahedral meshes. The Galileo probe into the atmosphere of Jupiter to provide drag and flow modifications tor the time-marching aeroelastic procedures involve the field information essential for accurate interpretation of an onboard addition of the structural equations of motion tor their simultaneous time experiment Finally, the codes have been used extensively to simulate integration with the governing flow equations. A detailed description of expanding nozzle flows in low-power thrusters in support of propulsion the time-marching aeroelastic procedures is presented along with activities at NASA-Lewis. Detailed comparisons between continuum comparisons of computed results with experimental data to assess the calculations and DSMC results helped to quantify the limitations of accuracy of the capability. Flutter results are shown for both two and continuum CFD codes in rarefied applications. Author three-dimensional configurations including a NACA 0012 airfoil, an isolated 45 deg swept-back wing, and a supersonic transport configu- N94-29920*# Princeton Univ., NJ. Dept of Mechanical and Aero- ration with a fuselage, clipped delta wing, and two identical rearward- space Engineering. mounted engine nacelles. The spatial adaptation procedures involve WALL PRESSURE FLUCTUATIONS IN THE REATTACHMENT mesh enrichment and mesh coarsening to either add points in high REGION OF A SUPERSONIC FREE SHEAR LAYER Final gradient regions of the flow or remove points where they are not needed, Technical Report, 1 Jan. 1991 - 30 Jun. 1991 respectively, in order to produce time-accurate solutions of high spatial ALEXANDER J. SMITS 14 Apr. 1994 10 p accuracy at minimal computational cost A detailed description of the (Contract NAG1-1072) enrichment and coarsening procedures is presented along with com- (NASA-CR-195790; NAS 1.26:195790) Avail: CASI HC A02/MF A01 parisons of computed results with experimental data to assess the The primary aim of this research program was to investigate the accuracy of the capability. Steady results using the spatial adaptation mechanisms which cause the unsteady wall-pressure fluctuations in procedures are shown for a NACA 0012 airfoil, an F-5 fighter wing, and shock wave turbulent shear layer interactions. The secondary aim was an ONERA M6 wing. Unsteady results are shown for a NACA 0012 to find means to reduce the magnitude of the fluctuating pressure loads airfoil and a three dimensional simulation of a one-dimensional shock by controlling the unsteady shock motion. The particular flow under

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study is the unsteady shock wave interaction formed in the reattach- moment coefficient versus ground height is also compared with data for ment zone of a separated supersonic flow. Similar flows are encoun- the wing-body configuration. It also shows a good agreement in trend. tered in many practical situations, and they are associated with high However, the magnitude of the suck-down effect is under predicted. levels of fluctuating wall pressure. The free shear layer is formed by the The discrepancy between the computational results and the experi- flow over a backward facing step, using an existing model, with the base mental data is most likely due to a lack of an accurate simulation of pressure on the step adjusted so that there is no pressure discontinuity turbulence effect a fine enough grid system, an accurate specified at the lip. The shear layer therefore develops in a zero pressure vorticity distribution at the jet exit, or unknown experimental errors. The gradient The primary advantage of this flow configuration is that the calculated flow field of ^roll-up jets is also presented. The flow patterns reattachment process can be studied in the absence of a separation of a 90 degree jet impinging on the ground without the free stream effect shock. The mean flow data, and some preliminary hot-wire measure- has a stagnation point on the ground and symmetric with respect to the ments of the mass-flux fluctuations were made by Baca and Settles, jet core. Due to the effect of the free stream, the stagnation point occurs Baca, Williams and Bogdonoff, who showed that the shear layer ahead of the jet core, and the flow pattern is no longer symmetric. For became self-similar at about 17 delta(sub 0) downstream of the lip, and deflected jets with any deflection angle other than 90 degrees, the that it grew at a rate typical of the observed Mach number difference vortex roll-up is stronger in the direction of the jet deflection, and the (about 1/3rd the incompressible growth rate). The turbulence measure- vortex shape is deformed. With a free stream combined with deflected ments were later extended by Hayakawa, Smits and Bogdon off under jet, the flow pattern becomes more complicated. The jet core is NASA Headquarters support Derived from text deformed and the vortex roll-up is obvious. For lower ground height the vortex becomes flatter. In summary, the flow patterns are affected by jet velocity, free stream velocity, deflected angles and ground height Dissert. Abstr. N94-29937*# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. AERODYNAMIC CHARACTERISTICS OF A PROPELLER- N94-30124** Illinois Univ., Urbana-Champaign. Dept of Aeronauti- POWERED HIGH-LIFT SEMISPAN WING cal and Astronautical Engineering. GARL L GENTRY. JR., M. A. TAKALLU, and ZACHARY T. APPLIN THE 3-D LDV MEASUREMENTS ON A 30-DEGREE SWEPT Apr. 1994 70 p WING WITH A SIMULATED ICE ACCRETION Final Report (Contract RTOP 535-03-10-02) MICHAEL B. BRAGG and MICHAEL K. KERHO Apr. 1994 63 p (NASA-TM-4541;L-17259;NAS 1.15:4541) Avail: CASI HC A04/MF (Contract NAG3-1134; RTOP 505-68-10) A01 (NASA-CR-195327; E-8778; NAS1.26:195327) Avail: CASI HC A04/ A small-scale semispan high-lift wing-flap system equipped MFA01 under the wing with a turboprop engine assembly was tested in the Three dimensional flowfield measurements have been obtained LaRC 14- by 22-Foot Subsonic Tunnel. Experimental data were for a semispan 30-degree swept wing with a simulated glaze ice obtained for various propeller rotational speeds, nacelle locations, and accretion. The model tested has a NACA 0012 section perpendicular nacelle inclinations. To isolate the effects of the high lift system, data to the leading edge. Measurements were made using a two-component were obtained with and without the flaps and leading-edge device. The laser Doppler velocimeter (LDV) system. Mean velocity measurements effects of the propeller slipstream on the overall longitudinal aerody- were obtained for all three velocity components. Streamwise turbu- namic characteristics of the wing-propeller assembly were examined. lence intensities were also obtained. All measurements were taken in Test results indicated that the lift coefficient of the wing could be the University of Illinois 3 by 4 foot subsonic wind tunnel at a Reynolds increased by the propeller slipstream when the rotational speed was number of 1 million and 8 degrees angle of attack. The data is presented increased and high-lift devices were deployed. Decreasing the nacelle in tabular form. Author (revised) inclination (increased pitch down) enhanced the lift performance of the system much more than varying the vertical or horizontal location of the nacelle. Furthermore, decreasing the nacelle inclination led to higher lift N94-3015r# National Aeronautics and Space Administration. Ames curve slope values, which indicated that the powered wing could Research Center, Moffett Field, CA. sustain higher angles of attack near maximum lift performance. Any lift COMPUTATION OF WIND TUNNEL WALL EFFECTS FOR augmentation was accompanied by a drag penalty due to the increased COMPLEX MODELS USING A LOW-ORDER PANEL METHOD wing lift Author (revised) DALE L. ASHBY and SCOTT H. HARRIS Feb. 1994 19 p (Contract RTOP 505-59-53) (NASA-TM-104019;A-93077;NAS1.15:104019) Avail: CASI HCA03/ MFA01 N94-29973 Kansas Univ., Lawrence. A technique for determining wind tunnel wall effects for complex AIRCRAFT AERODYNAMICS WITH DEFLECTED JETS IN models using the low-order, three dimensional panel method PMARC GROUND EFFECT Ph.D. Thesis (Panel Method Ames Research Center) has been developed. Initial CHYUAN-HSYAN PAUL LIAW 1992 116p validation of the technique was performed using lift-coefficient data in Avail: Univ. Microfilms Order No. DA9313133 the linear lift range from tests of a large-scale STOVL fighter model in A computational method by combining a potential flow approach the National FuM-Scale Aerodynamics Complex (NFAC) facility. The with a Navier-Stokes solver is developed to analyze the flow field and data from these tests served as an ideal database for validating the predict the aerodynamics for three-dimensional configurations with technique because the same model was tested in two wind tunnel test deflected jet in ground effect The potential flow method, PMARC/ sections with widely different dimensions. The lift-coefficient data VSAERO, is a low-order panel code solving the potential flow over obtained for the same model configuration in the two test sections were three-dimensional geometries. The Navier-Stokes code (NS3D) is different, indicating a significant influence of the presence of the tunnel based on the vorticity transport equation and the Poisson equation for walls and mounting hardware on the lift coefficient in at least one of the the vector velocity potential in viscous, incompressible flow. Calcula- two test sections. The wind tunnel wall effects were computed using tions for a rectangular flat plate and a wing-body combination with a PMARC and then subtracted from the measured data to yield corrected single normal-deflected jet in ground effect with and without free stream lift-coefficient versus angle-of-attack curves. The corrected lift-coeffi- are conducted. The computed results indicate that due to the induced cient curves from the two wind tunnel test sections matched very well. velocity of a constant-thrust jet, the suck-down force (-L) is increased Detailed pressure distributions computed by PMARC on the wing lower when the ground height (h) decreases. Calculated results for a 90 surface helped identify the source of large strut interference effects in degree lifting jet issuing from a flat plate and for a wing-body configu- one of the wind tunnel test sections. Extension of the technique to ration show good agreement in trend with available data. The computed analysis of wind tunnel wall effects on the lift coefficient in the nonlinear

380 AERODYNAMICS 02

lift range and on drag coefficient will require the addition of boundary- geometric shapes of aerodynamic curves and surfaces are pre- layer and separated-flow models to PMARC. Author sented hat may be used for several tasks in CFD work (geometric modeling of surface, refacing of aerodynamic configuration surfaces). Muttiblock grid generation is simplified by allowing grid lines to be only C(sup 0)- continuous over block faces. Block coupling algorithms for N94-30152*# Illinois Univ., Urbana-Champaign. Dept. of Aeronauti- the flow solvers are discussed, that prevent accuracy loss due to the cal and Astronautical Engineering. . -.;!. .; nonsmoothness of the grid over block faces. ESA AN EXPERIMENTAL STUDY OF THE AERODYNAMICS OF A SWEPT AND UNSWEPT SEMISPAN WING WITH A SIMULATED GLAZE ICE ACCRETION Final Report MICHAEL B. BRAGG May 1994 232 p N94-30388 NationalAerospace Lab.,Amsterdam (Netherlands). Fluid (Contract NAG3-1134; NAG3-28; RTOP 505-68-10) . Dynamics/Informatics Div. (NASA-CR-195330; E-8813; NAS 1.26:195330) Avail: CASIHC A11/ NUMERICAL INVESTIGATION INTO HIGH-ANGLE-OF-ATTACK MFA03 LEADING-EDGE VORTEX FLOW Two semispan wings, one with a rectangular planform and one J. I. VANDENBERG, H. W. M. HOEIJMAKERS, and H. A. SYTSMA 26 with 30 degrees of leading edge sweep were tested. Both had a NACA May 1992 29 p Presented at the AIAA 10th Applied Aerodynamics 0012 airfoil section, and both were tested dean and with simulated Conference, Palo Alto, CA, 22-24 Jun. 1992 See also N92-45477 glaze ice shapes on their leading edges. Several surface roughness Sponsored by Netherlands Agency for Aerospace Programs Limited were tested. Each model geometry is documented and each surface Reproducibility: More than 20% of this document may be affected by roughness is explained. Aerodynamic performance of the wing in the microfiche quality form of sectional lift and integrated three-dimensional lift is documented (PB94-125564; NLR-TP-92248-U; AIAA PAPER 92-2600-CP; ETN- through pressure measurements obtained from rows of surface pres- 94-95584) Avail: CASI HC A03 sure taps placed at five span locations on the wing. For the rectangular A Euler method is applied to the steady subsonic (M(infinity) = wing, sectional drag near the midspan is obtained from wake total 0.50) leading edge vortex flow about a 65 deg sharp edged cropped pressure profiles. The data is presented in tabular and graphical form delta wing at incidences close to the incidence at which vortex and is also available on computer disk. Author breakdown is observed in wind tunnel experiments. Above a critical value of the incidence the pseudo time dependent numerical procedure fails to attain a steady state solution. This occurrence of 'solution breakdown' indicates the limits of the domain of applicability of the N94-30176** National Aeronautics and Space Administration. steady flow Euler method for the case of subsonic leading edge vortex Langley Research Center, Hampton, VA. flow. Analysis of the converged solution at incidences just below the USER'S MANUAL FOR THE MODEL INTERFACE AND critical value reveals that above the aft part of the wing the velocity and PLUGBOARD CABINETS IN THE 14- BY 22-FOOT SUBSONIC vortcity distribution within the vortex core undergo a remarkable TUNNEL change. ESA ROBERT B. ASKEW and P. FRANK QUINTO Apr. 1994 55 p (Contract RTOP 505-59-10-13) (NASA-TM-109062; NAS 1.15:109062) Avail: CASI HC A04/MF A01 The primary method of connection between the wind tunnel model N94-30389 National Aerospace Lab., Emmeloord (Netherlands). instrumentation and the data acquisition system in the 14- by 22-Foot Aerodynamics Div. Subsonic Tunnel is through the Model Interface (MIF) and Plugboard EXPERIMENTS AND THEORETICAL CONSIDERATIONS cabinets. The MIF and Plugboard cabinets allow versatility in the REGARDING THE ALLOWABLE ROUGHNESS HEIGHT IN connection of the instrumentation to the different data systems in the LAMINAR FLOW facility. The User's Manual describes the components inside the MIF A.C. DEBRUIN 15 Jun. 1992 12 p Presented at the 1st European cabinet, the input and output of the MIF, and the MIF patchboard, and Forum on Laminar Row Technology, Hamburg, Germany, 16-18 Mar. the Plugboard cabinets. There are examples of standard connections 1992 Limited Reproducibility: More than 20% of this document may be for most of the instrumentation used in the facility. Author (revised) affected by microfiche quality (Contract NIVR-01506N) (PB94-125556; NLR-TP-92252-U; ETN-94-95585) Avail: Issuing Activity (European Space Agency (ESA)) N94-30387 National Aerospace Lab., Amsterdam (Netherlands). The results of detailed experiments with single cylindrical rough- Informatics Div. ness elements in a favorable pressure gradient laminar boundary layer THE DESIGN OF A SYSTEM OF CODES FOR INDUSTRIAL are described. Based on these results, the allowable roughness height CALCULATIONS OF FLOWS AROUND AIRCRAFT AND OTHER is analyzed for a family of similarity type laminar boundary layers. COMPLEX AERODYNAMIC CONFIGURATIONS Subsequently, the problem of optimum airfoil shape with maximum J. W. BOERSTOEL (Technische Univ., Delft, Netherlands.), S. P. resistance against surface roughness is addressed. The scaling laws SPEKREIJSE, and P. L. VITAGLIANO 9 Apr. 1992 16 p Presented for allowable roughness height are also discussed from a more global at the 10th AIAA Applied Aerodynamics Conference, Palo Alto, CA, 22- viewpoint ESA 24Jun. 1992 See also N92-45492 Limited Reproducibility: More than 20% of this document may be affected by microfiche quality (Contract NIVR-01604N) (PB94-125598; NLR-TP-92190-UP; AIAA PAPER 92-2619-CP; N94-30401 National Aerospace Lab., Amsterdam (Netherlands). ALENIA-TR-57X92054; CIRA-DLC-EST-271; ETN-94-95581) Avail: Aerodynamics Div. CASI HC A03 CALCULUS OF VARIATIONS APPLIED TO 2D MULTI-POINT For industrial calculations of three dimensional flows around AIRFOIL DESIGN transport aircraft, a system of Computational Fluid Dynamics (CFD) T. E. LABRUJERE and J. VANDERVOOREN 1 Sep. 1992 32 p codes for flow calculations is developed. This system includes codes Presented at the 1st European Computational Fluid Dynamics Confer- for aerodynamic geometry modeling in block decomposition work, ence. Brussels, Belgium, 7-11 Sep. 1992 Limited Reproducibility: muttiblock grid generation, Euler and Navier-Stokes flow calculations, More than 20% of this document may be affected by microfiche quality and flow visualization. The codes are tuned to each other. Two (PB94-125457; NLR-TP-92361-U; ETN-94-95594) Avail: CASI examples of this tuning are discussed. Analytic representations for HCA03

381 03 AIR TRANSPORTATION AND SAFETY

Aspects of a residual correction method to solve the multipoint divided into five sections: All Accidents; Fatal Accidents; Serious Injury airfoil design problem for subsonic and transonic conditions are dis- Accidents; Property Damage Accidents and Midair Collision Accidents. cussed. The method is based on full potential theory and minimizes a Several tables present accident parameters for 1990 accidents only, cost function weighting the deviations from specified target pressure and each section includes tabulations which present comparative distributions for each design condition in a least squares sense. statistics for 1990 and for the five-year period 1985-1989. NTIS Deviations from specified target pressure distributions (residuals) are translated into airfoil geometry corrections, using an approximate inverse method derived from solving an equivalent incompressible N94-29402S National Transportation Safety Board, Washington, DC. multipoint airfoil design problem using calculus of variations and AIRCRAFT ACCIDENT/INCIDENT SUMMARY REPORT: IN- numerical optimization. The feasibility of introducing the equivalent FLIGHT LOSS OF CONTROL, LEADING TO FORCED LANDING incompressible multipoint design problem is demonstrated for a two AND RUNWAY OVERRUN, CONTINENTAL EXPRESS, INC., point reconstruction test case. First results of a two point example N24706 EMBRAER EMB-120 RT, PINE BLUFF, ARKANSAS, 29 design are presented. ESA APRIL 1993 29 Apr. 1993 51 p (PB94-910404; NTSB/AAR-94/02/SUM) Avail: CASIHC A04/MF A01 This report explains the in-flight loss of control of N24706, leading to a forced landing and runway overrun at Pine Bluff, Arkansas, on 29 03 April 1993. The safety issues discussed in the report are flight crew AIR TRANSPORTATION AND SAFETY professionalism, inattentiveness, and fatigue. A recommendation concerning fatigue was made to the Federal Aviation Administration. Author (revised) Includes passenger and cargo air transport operations; and aircraft accidents.

N94-29862* Systems Control Technology, Inc., Arlington, VA. POTENTIAL HAZARDS OF MAGNETIC RESONANCE IMAGERS N94-28799* Arizona State Univ., Tempe. Dept of Mechanical and TO EMERGENCY MEDICAL SERVICE HELICOPTER Aerospace Engineering. OPERATIONS Final Report CRASHWORTHINESS ANALYSIS OF COMMUTER AIRCRAFT ROBERT B. NEWMAN Jan. 1993 56 p SEATS Technical Note (Contract DTFA01-87-C-00014) DAVID H. LAANANEN Nov. 1993 20 p (DOT/FAA/RD-92/15; SCT-92RR-14) Avail: CASI HC A04/MF A01 (Contract DTFA03-90-P-00447) In recent years, there have been several incidents with helicopters (AD-A275889; CR-R-91012; DOT/FAA/CT-TN-91/28) Avail: CASI HC where magnetic resonance imagers (MRl's) have interfered with the A03/MF A01 operation of magnetic sensors such as compasses and directional During the past several years, the Federal Aviation Regulations gyroscopes. The magnetic fields generated by the MRI magnet causes (FAR) were significantly modified with respect to seat/restraint system magnetic sensors to give aberrant readings. This report documents the strength, attachment of seats to the aircraft structure, and the means characteristics of MIR's and how they operate. It discusses relevant by which they are to be evaluated. Aircraft accident data, human federal regulations of MRI and all magnetic effects and hazards tolerance levels, and aircraft structural characteristics have been involved with operating helicopters in a strong static magnetic field for considered in the development of these new standards. Dynamic both personnel and equipment Finally, the report makes recommenda- testing is now required for seats to be installed in general aviation tions for safe helicopter operations in and around MRl's. Author aircraft, transport category aircraft, and rotorcraft Performance criteria are similar to those specified by the Federal Motor Vehicle Safety Standards for automobiles but also include a limit on pelvic force, in order to prevent spinal injuries which may be caused by the vertical N94-30144 Manitoba Univ.. Winnipeg. Dept of Actuarial and Man- component of impact force. A category of aircraft that has not as yet agement Science. been affected by the rule modifications is the commuter type aircraft, A CAPACITY PLANNING MODEL FOR CANADIAN MILITARY which seats 10 to 19 passengers. Since this airplane is closer in size AIRLIFT REQUESTS M.S. Thesis to general aviation aircraft than to large transports, it is also covered by BARRY ANTHONY STANNARD Aug. 1993 150 p FAR Part 23. The Federal Aviation Administration is currently involved (ISBN-0-315-86079-0; CTN-94-61178) Copyright Avail: Micromedia in the conduct of a test program addressing commuter aircraft occupant Ltd., Technical Information Centre, 240 Catherine Street, Suite 305, crash safety. In support of this effort, a research program the includes Ottawa, Ontario, K2P 2G8, Canada HC/MF full-scale aircraft drop tests, sled tests of seats, and computer simula- The problem of the constrained assignment of n variable length tions is being conducted. This report describes the use of the SOM-LA tasks (missions), integrating many airlift requests from 13 users with (Seat/Occupant Model-Light Aircraft) program in modeling three com- eight priorities, to m parallel machines (CC130 Hercules airframes) is muter aircraft seats. The predicted response of the seats to a potential presented. A general mathematical model was developed which is set of test conditions is described. DTIC suitable for assisting airlift planners in deciding which airlift mission requests to accept The model can be implemented on a microcom- puter and is essentially a computational subroutine for a larger decision support system. A high quality airlift capacity plan resulted from the N94-29185 National Transportation Safety Board. Washington, DC. application of a group of management science techniques. Analytic NATIONAL TRANSPORTATION SAFETY BOARD ANNUAL hierarchy process was used to quantify each mission request A REVIEW OF AIRCRAFT ACCIDENT DATA. US GENERAL sequential linear programming model proved to be a computationally AVIATION, 1990 efficient approach for producing an automated planning aid to assist the 17 Dec. 1993 84 p Limited Reproducttriiity: More than 20% of this airlift capacity planners. The model is flexible, computationally fast and document may be affected by microfiche quality accurate. It handles linked missions, either as a pair or as a minimum (PB94-126869; NTSB/ARG-93/02) Avail: CASI HC A05 out of an optimal number. User hour and fleet flying hour constraints are The report presents a statistical compilation and review of general modelled and missions can be added, deleted, or modified. While the aviation accidents which occurred in 1990 in the United States, its model was developed for the Canadian Forces, it can be adapted for territories and possessions, and in international waters. The report is other similar military and civilian situations. Author (CIST1)

382 AIRCRAFT COMMUNICATIONS AND NAVIGATION 04

04 such efforts were the Adaptive Tactical Navigation (ATM) System and the Autonomous Rxtaking Management (AFM) system, which were AIRCRAFT COMMUNICATIONS AND NAVIGATION both awarded to The Analytic Sciences Corporation (TASC). An intelligent system to aid the pilot with navigation functions was devel- Includes digital and voice communication with aircraft; air navigation oped under the ATN program. This system incorporated real-time systems (satellite and ground based); and air traffic control. knowledge base software to manage the tactical navigation moding, fault tolerance, and pilot aiding to provide a robust navigation prototype for the next generation fighter aircraft. The ATN program highlighted the aircraft weapons officer's heavy workload associated with the location N94-28744* Air Force Inst of Tech., Wright-Patterson AFB, OH. and identification of fixpoints to update and verify the accuracy of the School of Logistics and Acquisition Management navigation system. With this problem in mind, it was determined that an EVALUATION OF ACCESS/NAVIGATIONAL FEATURES OF A intelligent system was needed to automatically locate, image, and GRAPHICAL-USER INTERFACE INSTALLED ON A PORTABLE identify fixpoints and update the navigation solution. The AFM System MAINTENANCE AID M.S. Thesis was developed to prove the feasibility of automated navigation updates USA A. CARNEY and ROGER A. QUINTO Sep. 1993 146 p using tactical sensors and existing mission data processing systems. (AD-A275791; AFIT/GLM/LAL/93S-9) Avail: CASI HC A07/MF A02 Several technologies developed under ATN were incorporated into the Portable maintenance aids (PMA's) are being developed to AFM system including a proven simulation of the navigation sensors, access and store electronic technical information on the fiightline. The controllers, and mission planning and management software. Automa- prototype PMA designed by Armstrong Laboratory personnel has tion of human fix taking activity required integration of several emerging redundant access/navigational features. Redundancy increases soft- technologies including a real-time data fusion architecture, neural ware memory usage and adds unnecessary weight to the PMA. The network and heuristic automatic recognition algorithms, and associa- purpose of this research was to determine the best access/navigational tive memories to retrieve fix points from on-board databases. Integra- feature installed on the PMA. The best feature is the feature that tion of these diverse technologies was simplified by the employment of provides the highest degree of user satisfaction. An experiment was an object-oriented software development approach and real-time con- conducted to evaluate the following features for screen and menu trol system. Derived from text access and navigation, respectively: dedicated/hardware keys, programmable soft keys, and push button keys, and number keys, cursor control keys, and programmable soft keys. Modified computer screens from the prototype PMA were used on a laptop personal computer, N94-29445* Federal Aviation Administration, Washington, DC. which simulated the PMA, to evaluate each feature, one at a time. THE 1993 FEDERAL AVIATION ADMINISTRATION AVIATION Twenty-eight maintenance technicians rated and ranked each access/ SYSTEM CAPITAL INVESTMENT PLAN navigational feature. The results indicated that the best feature for Dec. 1993 304 p screen access and navigation was the dedicated/hardware keys and Avail: CASI HC A14/MF A03 the best feature for menu access and navigation was the number keys. Based on a total system approach, the Aviation System Capital OTIC Investment Plan (CIP) relates user community needs to technical opportunities, human factors, and operational considerations. The systematic implementation of the projects defined in this CIP will result in improved safety and efficiency, while accommodating spiraling N94-28914# Federal Aviation Administration, Atlantic City, NJ. Tech- demands at constrained cost. It supports a more complex system and nical Center. creates a foundation for continued evolution that uses modem tech- LOS ANGELES INTERNATIONAL AIRPORT INSTRUMENT nologies and capabilities. The CIP also recognizes that continuing LANDING SYSTEM APPROACH DATA COLLECTION AND upgrades and enhancements are necessary to meet evolving national REDUCTION, PHASE 1 Final Repoort, Nov. 1991 - Apr. 1992 airspace system (MAS) user needs. It includes the following: Original J. THOMAS, D. TIMOTEO, and P. HOANG Nov. 1993 72 p MAS Plan (Chapter 2)—Preservation of the original NAS Plan projects; (AD-A275115; DOT/FAA/CT-TN93/12) Avail: CASI HC A04/MF A01 Growth (Chapter 3>—Projects that expand, relocate, or consolidate Position data on aircraft flying Instrument Landing System (ILS) existing facilities/capabilities in response to changing demand on the approaches from 40 nautical miles (nmi) down to runway threshold system. Each potential metroplex control facility (MCF) is identified in were collected at Los Angeles International Airport (LAX) between this chapter; Infrastructure Replenishment (Chapter 4)—Projects iden- November 26, 1991 and April 25, 1992. The purpose of the data tified since the original NAS Plan that refurbish structures, replace collection was to provide an accurate database of navigational perfor- obsolete equipment, or relocate facilities to maintain service, improve mance of aircraft frying ILS approaches at distances between 10 nmi effectiveness, and/or reduce cost; Supportability (Chapter 5)—Capital and 32 nmi. Aircraft position data were collected using the in-place LAX improvement projects that support logistics, provide spares, train surveillance primary and secondary radars. The data were reduced and personnel, and manage the human resource aspect of modernizing the analyzed at the Federal Aviation Administration (FAA) Technical Cen- NAS; and New Capabilities (Chapter 6}—Projects identified since the ter by ACD-340 personnel. The discussion in this Final Report concerns original NAS Plan which, if implemented, are expected to add significant the accuracy of the collected position data and possible sources of error new capabilities to the system. The new TRACON Automation System in the data collection. OTIC project is contained in this chapter. Author (revised)

N94-29323* Wright Lab., Wright-Patterson AFB, OH. N94-29558# Advisory Group for Aerospace Research and Develop- OBJECT ORIENTED DESIGN OF THE AUTONOMOUS ment, Neuilly-Sur-Seine (France). Guidance and Control Panel. FIXTAKING MANAGEMENT SYSTEM MACHINE INTELLIGENCE IN AIR TRAFFIC MANAGEMENT JOSEPH DIEMUNSCH and JOHN HANCOCK In AGARD, Aerospace [L'INTELLIGENCE ARTIFICIELLE DANS LA GESTION DU Software Engineering for Advanced Systems Architectures 14 p Nov. TRAFIC AERIEN] 1993 ANDRE BENOrt, ed. (European Organization for the Safety of Air Copyright Avail: CASI HC A03/MF A03 Navigation, Brussels, Belgium.) Oct 1993 400 p In ENGLISH and The Air Force Avionics Laboratory has sponsored several efforts FRENCH The 56th Symposium was held in Berlin, Germany, 11-14 to increase the accuracy of aircraft navigation functions while decreas- May 1993 ing crew workload through the application of intelligent systems. Two (AGARD-CP-538; ISBN-92-835-0724-X) Copyright Avail: CASI

383 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

HCA17/MFA04 art in Air Traffic Control (ATC) research. This prototype is also an This volume contains the Technical Evaluation Report and the 30 example of multiple hardware and software technologies being har- papers, presented at the Guidance and Control Panel Symposium held nessed to develop a solution to a problem initially thought to be too in Berlin, Germany from 11th to 14th May 1993. The papers were complex for automation. The paper then presents the future direction of presented covering the following headings: Air Traffic Processes; research at CES and then closes with the issues which have been Novel Approaches; Transition to Operation; Human/Machine Relation- raised by our work that need addressing before an automated system ship; Air/Ground Integration; PHARE; and Ground Movements Control. will be practical. Author

N94-29559* Mitre Corp., McLean. VA. Center for Advanced Aviation N94-29561S Centre d'Etudes de la Navigation Aerienne, Toulouse Systems Development (France). ADVANCES IN DEVELOPMENT CAPABILITIES FOR USE OF ADVANCED TECHNOLOGIES IN ATM (AIR TRAFFIC INTELLIGENT AIR TRAFFIC MANAGEMENT SYSTEMS MANAGEMENT) DOMAIN KERRY M. LEVIN and JOHN J. FEARNSIDES In AGARD, Machine P. PLANCHON and M. BONNARD In AGARD, Machine Intelligence Intelligence in Air Traffic Management 18 p Oct. 1993 in Air Traffic Management 11 p Oct 1993 Copyright Avail: CASI HC A03/MF A04 Copyright Avail: CASI HC A03/MF A04 Visual presentation is a major source of information for air traffic The CENA is in charge of studies related to Air Traffic Manage- control. Significant advances in computers, display technology, and the ment and therefore to some of the communication, navigation, and tools used by developers of intelligent air traffic management (ATM) surveillance means. The work is carried out to support French and systems pose challenges for the development of computer-human European ATC (air traffic control) in an international cooperation. It interfaces (CHI's) associated with the new automation. The CHI must encompasses studies and experimental development aiming at opera- be designed to be both usable and suitable. This paper reviews three tional implementation within the CAUTRA 5 program. The different capabilities available to developers of intelligent ATM systems: case- CENA projects are integrated in an experimental simulator frame based reasoning system design, rule-based system design, and indi- named ADER. This test-bed will support one of the demonstrations vidually tailored CHI. It recommends that any intelligent ATM system be within PHARE, a joint European experimental program. The CENA examined early in its development cycle in a laboratory environment, organization is based upon a technical directorate in charge of the where it can be tested in concert with other elements of the ATM horizontal projects as previously described and 10 divisions located system. Author either at Atnis-Mons (near Paris) or in Toulouse. One of these divisions, called COA (Control Organization and Automation), deals mainly with studies aiming at providing ATM (air traffic management) operators with N94-29560* CompEngServ Ltd., Ottawa (Ontario). helpful decision tools, using advanced methods and technologies. In INTELLIGENT SYSTEMS FOR AIR SPACE CONTROL AND this paper, it can be found a short description of COA division activities MANAGEMENT and a more precise analysis of one of the projects, called GOETHE, DAVID BOWEN and ANDRZEJ HLIBOW1CKI In AGARD, Machine aiming to provide ATFM (Air Traffic Row Management) regulators with Intelligence in Air Traffic Management 11 p Oct 1993 Sponsored by a more user-friendly tool. Derived from text Transportation Development Centre Copyright Avail: CASI HC A03/MF A04 Complete automation of an air traffic control system requires the N94-29562# Princeton Univ., NJ. Dept of Mechanical and Aero- identification of functions and their allocation to a distributed system, space Engineering. part of which is on the ground and part of which flies. The evolution of AIR TRAFFIC MANAGEMENT AS PRINCIPLED NEGOTIATION current systems appears to be taking place with ill-defined visions of BETWEEN INTELLIGENT AGENTS what the final system will or should look like. In some cases this fuzzy ROBERT STENGEL and JOHN WANGERMANN In AGARD, Machine view of the future is purposely carried because of the implications of Intelligence in Air Traffic Management 10 p Oct 1993 proposing a view which antagonizes various groups or associations (Contract DT-FA01-92-G-0011) representing those already engaged in the process. Yeti each step Copyright Avail: CASI HC A02/MF A04 along the way implies explicitly or implicitly some final target system. As The major challenge facing the world's aircraft/airspace system each year goes by, we move toward a system which may be a long way (AAS) today is the need to provide increased capacity, whilst reducing from what is really desirable in the next century. It seems reasonable delays, increasing the efficiency of flight operations, and improving that some versions of the ideal future system should be understood safety. Technologies are emerging that should improve the perfor- within the community. At least one of these options should be what is mance of the system, but which could also introduce uncertainty, technically feasible. From this, an acceptable system can be negoti- disputes, and inefficiency if not properly implemented. The aim of our ated. The first step in this process is to determine the desired function- research is to apply techniques from intelligent control theory and ality without regard to any other factors. From this, technical feasibility decision-making theory to define an Intelligent Aircraft/Airspace Sys- can be determined and/or predicted; and finally, the allocation of the tem (IAAS) for the year 2025. The I AAS would make effective use of the functions to humans or machines can be debated. The management of technical capabilities of all parts of the system to meet the demand for a dense cluttered air space requires a set of skills and capabilities on increased capacity with improved performance. Author the part of an air traffic control team which, in some of their functions, cannot be represented algorithmically. Successful automated air traffic management systems will necessarily emulate the intuitive portions of N94-29563# Shape Technical Center. The Hague (Netherlands). the human management capability using various technologies drawn USE OF GPS IN AUTOMATED AIR TRAFFIC CONTROL from the broad field of artificial intelligence. Indeed portions of the HERMANN F. HEGELS and WILLEM E. HOEKSTRA In AGARD, overall management system have been the subject of research and Machine Intelligence in Air Traffic Management 26 p Oct 1993 development efforts in many laboratories around the world. The integra- Copyright Avail: CASI HC A03/MF A04 tion of these fragments into an overaD scheme is often left as an The Global Positioning System NAVSTAR is rapidly becoming the implicitly understood architecture. This paper begins by presenting world standard for navigation and timing. Although primarily designed CompEngServ (CES) Ltd.'s view of an automated airspace manage- to be a military system, the civil user community is expanding at a ment system. The paper then presents an overview of the prototype of breathtaking pace. After an introduction to the general GPS policies and an advanced controller workstation developed by CES (under contract the technical fundamentals this paper presents an idea on how to use to Transport Canada) which prototypes various portions of this architec- GPS NAVSTAR to improve Air Traffic Control. Existing selective ture for Airspace Management This system represents the state of the identification features will form the key to a G PS-based position.

384 AIRCRAFT COMMUNICATIONS AND NAVIGATION 04 velocity, and acceleration message. Higher update rates and the vastly and demonstrated during flight trials using a VHF data link for commu- improved information on each aircraft will provide the input for a flight nication. Results of these flight tests will be presented. Author (revised) plan correlation function enabling an automatic air traffic monitoring and control far beyond current standards. Author N94-29567# Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Brunswick (Germany). Inst. of Right Guidance. N94-29564# Raumfahrt Systemtechnik G.m.b.H., Salem (Germany). CONTRIBUTIONS OF DLR TO AIR TRAFFIC CAPACITY GROUND INDEPENDENT LANDING SYSTEM ENHANCEMENT WITHIN A TERMINAL AREA ,. . HANS MARTIN BRAUN and PHILIPP HARTL In AGARD, Machine U. VOELCKERS, U. BROKOF, D. DIPPE, and M. SCHUBERT In Intelligence in Air Traffic Management 6 p Oct. 1993 AGARD, Machine Intelligence in Air Traffic Management 11 p Oct Copyright Avail: CASI HC A02/MF A04 1993 Air traffic in Central Europe is dramatically increasing today. Copyright Avail: CASI HC A03/MF ACM There are some indications that present upgrades of the air traffic Enhancement of air traffic capacity within the TMA cannot be control system might not be efficient and that planned upgrades will not achieved easily. Single solutions and improvements of technical equip- be realized in time due to budgetary restrictions. One key element in air ment, procedures and standards, with automation support for human traffic control is a precise navigation of the aircraft during landing, the operators in isolated areas, e.g. for the management of the airport, most critical part of the flight. It is presently performed by use of the airspace and Air Traffic Control very often will only yield marginal instrument landing system ILS and in some areas already by the capacity increases. Whether it is: new concrete (runways, taxiways, microwave landing system MLS. The latter provides a very high aprons), reduced separation minima, or advanced ATM functions, all navigation performance and allows a high landing sequence under all these measures will only result in significant capacity increases, if they weather conditions. However, it requires extensive ground equipment are designed, developed and implemented in a comprehensive, com- at the airports and hence, only a few airports in Central Europe are bined effort, making use of set of complementary measures and equipped with it today. This paper presents the results of a study on a functions in a well structured, optimized architecture and implementa- new microwave landing system with a spacebome radar transmitter tion strategy. This comprehensive approach is especially true for high and airborne radar receivers. Based on this bistatic radar system, density TMA's/airports, operating dose to capacity limits, where any navigation in landing phase could also be performed independently capacity enhancement measure will directly affect and/or require from weather conditions. However, it does not require any active capacity related issues in other areas. Based upon the specific needs equipment at the landing site. Even taxi way guidance could be of the Frankfurt airport and TMA, DLR is working on a variety of tools performed with this system. It is called 'Ground Independent Landing eind functions, which—combined and implemented in a well designed System' (GILS). Author strategy plan—can yield significant capacity increases without the construction of new runways. Three candidate systems—under development or even already in operation—which mutually depend on and N94-29565# Deutsche Aerospace A.G., Ulm (Germany). complement one another will be presented as examples of an even GPS/GNSS FOR ATM larger capacity enhancement plan for the TMA. Derived from text THOMAS JACOB, JOCHEN MEYER-HILBERG, GERHARD BANTLE, WINIFRED ROESCH, HEINZ-GEORG WIPPICH, and HORST SCHMIDT In AGARD, Machine Intelligence in Air Traffic Management 10 p Oct1993 N94-29568*# National Aeronautics and Space Administration. Ames Copyright Avail: CASI HC A02/MF A04 Research Center, Moffett Reid, CA. The actual implemented Air Traffic Control (ATC) systems have DESIGN OF CENTER-TRACON AUTOMATION SYSTEM radar coverage gaps on the Northern Atlantic and Trans-Siberian HEINZ ERZBERGER, THOMAS J. DAVIS, and STEVEN GREEN In Routes as well as in the Pacific area. This situation results in Insufficient AGARD, Machine Intelligence in Air Traffic Management 12 p Oct air traffic surveillance information in the corresponding control sectors 1993 and larger separation between aircraft on these routes to ensure safe Copyright Avail: CASI HC A03/MF A04 operation. Unfortunately, this procedure reduces the capacity and limits A system for the automated management and control of terminal air traffic flow. These problems can be overcome by the worldwide use area traffic, referred to as the Center-TRACON Automation System of the high accurate position data from Global Navigation Satellite (CTAS), is being developed at NASA Ames Research Center. In a Systems (GNSS) such as the U.S. Global Positioning System (GPS) cooperative program, NASA and FAA have efforts underway to install and the Russian Global Navigation System (GLONASS) aboard the and evaluate the system at the Denver area and Dallas/Ft Worth area aircraft as proposed by the ICAO-FANS plan. In combination with the air traffic control facilities. This paper will review CTAS architecture, and Automatic Dependent Surveillance (ADS) function as specified by automation functions as well as the integration of CTAS into the existing ARINC 745, the onboard computed position and flight path data is operational system. CTAS consists of three types of integrated tools transmitted to the Aeronautical Telecommunication Network (ATN) for that provide computer-generated advisories for both en-route and further use by ATM and ATC. Based on these principles, Deutsche terminal area controllers to guide them in managing and controlling Aerospace AG, Airborne Systems Division has developed a demon- arrival traffic efficiently. One tool, the Traffic Management Advisor strator. This system integrates the precise (Differential) GNSS informa- (TMA), generates runway assignments, landing sequences and land- tion with the data from an Inertia) Measurement Unit (e.g. AHRS) aboard ing times for all arriving aircraft, including those originating from nearby the demonstrator aircraft to fulfill the accuracy and consistency/integrity feeder airports. TMA also assists in runway configuration control and requirements during all phases of flight This system integration has flow management. Another tool, the Descent Advisor (DA), generates been done to ensure integrity of GNSS position information during clearances for the en-route controllers handling arrival flows to metering satellite outages or satellite masking, e.g. during turns. For demonstrat- gates. The DA's clearances ensure fuel-efficient and conflict free ing ADS-functionality, the onboard computed position and flight path descents to the metering gates at specified crossing times. In the velocity is transmitted in combination with flight management informa- terminal area, the Rnal Approach Spacing Tool (FAST) provides tion to the ground system using a data link. In addition to this en-route heading and speed advisories that help controllers produce an accu- ADS function with medium accuracy requirements, a high accuracy rately spaced flow of aircraft on the final approach course. Data bases mode using Differential GNSS data for conflict detection calculations consisting of several hundred aircraft performance models, airline between low separated aircraft has been implemented. The conflict preferred operational procedures, and a three dimensional wind model detection and alert functions are based on a special designed Expert support the operation of CTAS. The first component of CTAS, the Traffic System capable of real time operation. A taxi monitoring function can Management Advisor, is being evaluated at the Denver TRACON and also be performed by the system. All system functions have been tested the Denver Air Route Traffic Control Center. The second component

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the Final Approach Spacing Tool, will be evaluated in several stages at Traffic Control System (ATC) involving both man and machine. The the Dallas/Fort Worth Airport beginning in October 1993. An initial stage present document reports on two examples which typify the man- of the Descent Advisor tool is being prepared for testing at the Denver machine relationships in systems which are partly automated. In one Center in late 1994. Operational evaluations of all three integrated case, the part played by the machine is detrimental to man's involve- CTAS tools are expected to begin at the two field sites in 1995. ment; in the other case, man and machine work together for better Derived from text results. The manner in which this second approach was used during the development of the CENA's ERATO project is described. N94-29569f National Aerospace Lab., Amsterdam (Netherlands). •Transl. by FLS SIMULATION OF FULLY AUTOMATED AIR TRAFRC CONTROL CONCEPTS N94-29572# Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, WIM DENBRAVEN and HANS VANDENBOS In AGARD, Machine Brunswick (Germany). Inst. for Right Guidance. Intelligence in Air Traffic Management 16 p Oct 1993 Sponsored by CONSIDERATIONS ON GRAPHICAL USER INTERFACES FOR Schiphol Airport Authorities INTELLIGENT ATM SUPPORT SYSTEMS Copyright Avail: CASI HC A03/MF A04 R. BEYER In AGARD, Machine Intelligence in Air Traffic Management In order to be able to investigate various aspects of the complex 13 p Oct 1993 Air Traffic Control (ATC) system of the future, a real-time ATC simula- Copyright Avail: CASI HC A03/MF A04 tion facility has been constructed at NLR. The ATC automation environ- Considerations on the design of graphical user interfaces (GUI's) ment 'Of this simulator is provided by CTAS, the Center/TRACON for air traffic controllers are presented in the context of a European Air Automation System, developed by the NASA Ames Research Center. Traffic Management System (EATMS). The fundamental issues dis- For the simulation of air traffic, radar observations, and data link, the cussed include the following: air traffic controller tasks; human informa- NLR ATC Research Simulator (NARSIM) is used. The facility can be tion processing and mental models; and automation strategies with used at various levels of automation, ranging from conventional, respect to the GUI design. The more specific issues of GUI design 'manual' ATC to fully automatic control. For the latter, CTAS has been which are also discussed include the following: GUI programming extended with various decision and control algorithms, dealing with environments and standards; development tools; design principles and taste normally executed by the air traffic controller. In a set of real-time human factors/human engineering standards; and usability testing. simulation experiments different concepts of fully automated ATC are Conclusions are drawn regarding the current background of GUI design investigated, characterized by various combinations of control func- with respect to an EATMS and necessary future developments. tions and different levels of air-ground interaction. Furthermore, the Author (revised) effect of different levels of aircraft navigation performance is studied. The traffic samples are based on single-runway IFR operations for N94-29573# Deutsche Forschungsanstatt fuer Luft- und Raumfahrt, Schiphol Airport with the traffic mix and distribution based on predic- Brunswick (Germany). Inst for Right Guidance. tions for the year 2000. The Dutch airspace is simulated with one overall INTERACTIVE ANALYSIS AND PLANNING TOOLS FOR AIR area control sector, controlling traffic from all directions to the three TRAFFIC AND AIRSPACE MANAGEMENT arrival gates, and one Schiphol approach sector, merging the aircraft S. E. MAHUCH In AGARD, Machine Intelligence in Air Traffic from these gates into a properly spaced sequence on final approach. Management 13 p Oct 1993 For the analysis of the simulations, methods are under development to Copyright Avail: CASI HC A03/MF A04 present overall ATC system performance in terms of safety, flight Since 1989, the Institute for Right Guidance of the German efficiency, capacity, and control performance. The results of the Aerospace Research Establishment (DLR) has been developing proto- simulations are used to determine critical areas in ATC system automa- types of interactive tools in close cooperation with the German Air tion, as well as potential benefits thereof. They can also contribute to an Navigation Services (DFS) in order to achieve gradual improvements optimal distribution of tasks between man and machine in the ATC in the efficiency and productivity of the air traffic control system. The system of the future. Author (revised) paper briefly describes the potential of a selection of analysis and planning tools that have been developed in this framework. After an N94-29570* European Organization for the Safety of Air Navigation, introduction into the 'planning world' of tactical and strategical air traffic Brussels (Belgium). planning, the objectives and potentials of four tools will be demon- DECISION MAKING AIDS (DMA) IN ON-LINE ATC SYSTEMS strated as applied to real traffic scenarios and actual problems of the ANDRE BENOIT, JEAN-MARC POMERET, and SIP SWIERSTRA In current ATM system. Author (revised) AGARD, Machine Intelligence in Air Traffic Management 11 p Oct 1993 N94-29574* Alcatel ISR, Evry (France). Copyright Avail: CASI HC A03/MF A04 DAISY: A DECISION AID FOR AN AIR SITUATION This paper covers the potential of Decision Making Aids to be INTERPRETATION SYSTEM implemented before the year 2000 and, within the time frame consid- N. BICHAT. R. ALLOUCHE, and A. BORIES In AGARD, Machine ered, covers all of the aspects of automated assistance, based on flight Intelligence in Air Traffic Management 8 p Oct 1993 path prediction and monitoring, which help air traffic controllers to Copyright Avail: CASI HC A02/MF ACM establish and assess the predicted traffic situation more efficiently. Due to increases in air traffic volume and the evolution of opera- Problem detection, problem minimization, and 'best next clearance' tional missions, Alcatel ISR has been awarded a contract to analyze the advisories will permit the reduction of the controller's mental workload requirements of military air traffic controllers, especially in the area of without decreasing the level of safety or the controller's situational the air situation interpretation and the implementation of a mock-up. awareness. Author (revised) DAISY is aimed at providing controllers with a decision aid tor an air situation interpretation system. In this context interpretation stands for N94-29571* Centre d'Etudes de la Navigation Aerienne, Toulouse all the rules and combined information which give an operational (France). meaning to the air situation. Abnormal situations are highlighted, a COGNITIVE APPROACH TO SPECIFICATIONS ON AIR diagnosis is given, and a proposal is made for decision. After a TRAFFIC CONTROLLERS' DECISION ASSISTANCE SYSTEMS requirements analysis is conducted, both by experts and controllers [UNE APPROCHE COGNITIVE POUR LA SPECIFICATION during six months, a twelve-month technical feasibility study was led by D'AIDES A LA DECISION POUR LES CONTROLEURS Alcatel ISR, and a mock-up was developed dealing with typical interpre- AERIENS] tation scenario such as trajectory prediction. Author (revised) MARCEL LEROUX In AGARD. Machine Intelligence in Air Traffic Management 10 p Oct 1993 In FRENCH N94-29575# Deutsche Forschungsanstalt fuer Luft-und Raumfahrt, Copyright Avail: CASI HC A02/MF A04 Brunswick (Germany). Inst for Right Guidance. The central problem of this investigation is the creation of an Air DLR'S ATM DEMONSTRATION PROGRAMME

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V. ADAM. E. KLOSTERMANN, and M. SCHUBERT In AGARD, Rapid technological changes are taking place in the aviation Machine Intelligence in Air Traffic Management 12 p Oct 1993 system user facilities - both on the aircraft flight deck and at the Copyright Avail: CASI HC A03/MF A04 aeronautical operational control (AOC), or flight dispatch centers. On The Institute for Right Guidance of DLR is involved in medium and the flight deck, the flight management system (FMS) is bringing long term research and development of concepts, procedures, func- capability for precise three-dimensional guidance, flight path optimizations, and components for a future integrated Air Traffic Management tion, and speed control to meet required time-of-arrival (RTA) con- System. The medium term work concentrates on improvements constraints at key route waypoints. This is enhanced by the precision global cerning the capacity of Frankfurt airport This paper describes a navigation satellite system (GNSS), use of digital datalink for commu- planned demonstration program which is designed to prove concepts nications, and automatic dependent surveillance (ADS). At AOC facili- and tools developed by the Institute in cooperation with the German ties, advancements in flight planning, flight following, weatherinformation ATC Authority (DPS) and the operator of Frankfurt airport (FAG) as well and datalink allow the dispatcher greater flight operations management as with PHARE. The aim of these experiments is to demonstrate the capability over the airline fleet. This is especially significant for oceanic feasibility and merits of integration of onboard avionics with advanced airspace operations. In parallel, the oceanic air traffic management ATC systems on the ground. For this purpose an Air Traffic Manage- (ATM) system is undergoing an evolution in automation that will ment Demonstrator System will be employed, which comprises an air enhance the overall aviation system productivity. Much of the informa- segment and a ground segment connected via an automatic data link tion that each of the three system components - flight deck/FMS, AOC, and voice communication. The demonstration program will be per- and ATM - have would be very useful to the other two components for formed in several phases comprising simulation runs in an air traffic flight efficiency and overall productivity enhancements. Worldwide simulator as well as flight testS'With a real aircraft Author (revised) datalink technology will provide a universal and reliable data communication capability between these components to allow this information N94-29576# Honeywell, Inc., Minneapolis, MN. Systems and Re- sharing. This paper discusses the opportunity to integrate the functions search Center. of the FMS, AOC, and ATM computers by exploiting the capabilities of ADVANCED AIR TRAFFIC CONTROL AND FLIGHT worldwide ground and air data link. First, the outstanding needs of both MANAGEMENT SYSTEM CONCEPTS the oceanic airspace user and traffic management provider are stated. ROBERT L SCHULTZ In AGARD, Machine Intelligence in Air Traffic Then, the emerging technological capabilities of ATM automation, FMS Management 11 p Oct 1993 and AOC are summarized. This is followed by explicit operational Copyright Avail: CASI HC A03/MF A04 applications where the integration of these capabilities can bring A time-based air traffic control (ATC) system where vehicles are incremental benefits to flight efficiency and human productivity. Needs sequenced on desired time of arrival (TOA) has been proposed as one of both the airspace user and air traffic management service provider way that might help increase airport capacity. This paper evaluates are addressed. Operations using today's organized oceanic track three time-based ATC system concepts: (1) ground based (computing system as well as the future free route system are discussed. The trajectories on the ground), (2) aircraft based (computing trajectories on opportunities for FMS-AOC-ATM integration are illustrated by three the aircraft), and (3) ground and air based (generating parametrized scenarios for oceanic operation. These include a mid-oceanic route velocity and acceleration profiles on the aircraft and transmitting them replanning task to respond to weather change, a passing maneuver to to the ground where trajectories are recomputed). The parameters allow more flexibility in flight speed and altitude when flying along a track compared are amount of database, complexity of communications, system, and use of the FMS RTA capability to meet scheduled track computational requirements, autonomy of aircraft, and similarity to entry gate times with precise accuracy. Author (revised) current procedures. The ground-and-air-based approach using parametrized profiles has the best potential for providing a high-landing-rate N94-29578** National Aeronautics and Space Administration. Lan- ATC system with minimal processing and communications require- gley Research Center, Hampton, VA. ments. In this approach, ATC assigns time slots at the metering fix PROFILE NEGOTIATION: AN AIR/GROUND AUTOMATION based on desired time of arrival (TOA) and range-TOA windows INTEGRATION CONCEPT FOR MANAGING ARRIVAL TRAFFIC generated on the aircraft The aircraft sends a simple set of param- DAVID H. WILLIAMS, P. DOUGLAS ARBUCKLE, STEVEN M. GREEN, etrized deceleration and velocity profiles to the ground. The ground and WIM DENBRAVEN In AGARD, Machine Intelligence in Air Traffic processor uses these profiles to generate trajectories and identify Management 11 p Oct 1993 conflicts. The ground processor resolves conflicts by examining nearby Copyright Avail: CASI HC A03/MF A04 trajectories using both the sets of parametrized deceleration and NASA Ames Research Center and NASA Langley Research velocity profiles and the range-TOA windows. The new horizontal plan Center conducted a joint simulation study to evaluate a profile negotia- and the new profile parameters are sent to the aircraft, where the aircraft tion process (PNP) between a time-based air traffic control ATC system flight management system (FMS) regenerates the trajectory and and an airplane equipped with a four dimensional flight management precisely flies it. The advantages of such a system are that it is a natural system (4D FMS). Prototype procedures were developed to support the extension of the current system; it does not require massive ground functional implementation of this process. The PNP was designed to databases of aircraft thrust, drag and FMS models; tt uses a ground provide an arrival trajectory solution that satisfies the separation processor generating simple models to examine and resolve conflicts; requirements of ATC while remaining as dose as possible to the it requires only one air-to-ground interaction; and the aircraft is autono- airplane's preferred trajectory. The Transport Systems Research Ve- mous. A simulation was used to evaluate the concept. The models used hicle cockpit simulator was linked in real-time to the Center/TRACON in the simulation are ATC trajectory generator, aircraft FMS, aircraft Automation System (CTAS) for the experiment. Approximately 30 path controller, and vehicle motion. Multiple-aircraft scenarios, starting hours of simulation testing were conducted over a three week period. in cruise and descent, were examined. Factors examined were sepa- Active airline pilot crews and active Center controller teams participated ration distances between aircraft on different approach trajectories, as test subjects. Results from the experiment indicate the potential for Author successful incorporation of airplane preferred arrival trajectories in the CTAS automation environment. Controllers were able to consistently N94-29577# Federal Aviation Administration, Washington, DC. and effectively negotiate nominally conflict-free trajectories with pilots OPPORTUNITIES FOR INTEGRATING THE AIRCRAFT FMS, flying a 4D-FMS-equipped airplane. The negotiated trajectories were AERONAUTICAL OPERATIONAL CONTROL CENTERS, AND substantially closer to the airplane's preference than would have FUTURE AIR TRAFFIC MANAGEMENT SYSTEMS IN OCEANIC otherwise been possible without the PNP. Airplane fuel savings relative AIRSPACE to baseline CTAS were achieved in the test scenarios. The datalink CLYDE MILLER, BILL BLAKE, JOHN SORENSEN, and JOSEPH procedures and clearances developed for this experiment while pro- MILLER In AGARD, Machine Intelligence in Air Traffic Management viding the necessary functionality, were found to be operationally 10 p Oct 1993 unacceptable to the pilots. Additional pilot control and understanding of Copyright Avail: CASI HC A02/MF A04 the proposed airplane-preferred trajectory and a simplified clearance

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procedure were cited as necessary for operational implementation of The Common Modular Simulator (CMS) project is part of the the concept. From the controllers' perspective, the main concerns were Program for Harmonized ATM Research in Eurocontrol (PHARE). The the ability of the 4D airplane to accurately track the negotiated trajectory main objective of this project is to provide a common integration and the workload required to support thePNP as implemented in this environment which shall allow the creation of a homogeneous infra- study. Author structure in order to facilitate and harmonize the development as well as the evolution of ATM simulators in the different research establish- ments. To meet such an ambitious objective, CMS partners have adopted a system architecture based on a client-server model with N94-29579# European Organization for the Safety of Air Navigation, active servers providing event subscription and event notification Brussels (Belgium). mechanisms. The main advantages of such client-server models are to AIR-GROUND INTEGRATION OF THE ATM SYSTEM IN PHARE offer a very modular system architecture and to provide, through the B. KIRSTETTER and R. D. HUNTER In AGARD, Machine Intelligence associated application programming interface (API), a very powerful in Air Traffic Management 11 p Oct 1993 mechanism of abstraction. This leads to a very flexible, evolutive, open, Copyright Avail: CASI HC A03/MF A04 scalable and adaptable system. CMS will offer an architecture test bed This paper provides a general introduction into the Programme of for future advanced ATM systems. As a consequence, this project Harmonised Air Traffic Management Research in EUROCONTROL should be of great benefit to many other ATM projects. (PHARE). It describes the objectives of the research program and Author (revised) addresses the benefits of the integration of the automated systems onboard the aircraft with those of the ATC systems on the ground using N94-29583# Eurocontrol Experimental Centre, Bretigny (France). a digital air-ground data link. The assumptions on the expected ARC2000: AUTOMATIC RADAR CONTROL infrastructure and environment are explained and the possible automa- XAVIER FRON, BERNARD MAUDRY, JEAN-PIERRE NICOLAON, tion and air-ground negotiation strategies discussed. Finally descrip- and JEAN-CLAUDE TUMELIN In AGARD, Machine Intelligence in Air tions of the experimental facilities available or under development and Traffic Management 14 p Oct 1993 of the planned experiments are provided. Author Copyright Avail: CASI HC A03/MF A04 The 'Studies, Tests, and Applied Research' (STAR) program of the EUROCONTROL Agency is addressing several implementation timescales for air traffic management (ATM) systems and procedures. N94-29580# Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, ARC2000 (automatic radar control 2000) is presently the major long- Brunswick (Germany). Inst for Flight Guidance. term component of the STAR program, for implementation beyond EXPERIMENTAL FLIGHT MANAGEMENT SYSTEM 2015. ARC2000 is addressing the enroute ATC capacity issue, which V. ADAM, G. INGLE, and R. RAWLINGS In AGARD, Machine is severe in Europe, by investigating the limit case where both major Intelligence in Air Traffic Management 21 p Oct 1993 constraints, workload and sectorization, are eliminated. It is often easier Copyright Avail: CASI HC A03/MF A04 to solve a complex problem by first looking at the limit case. ARC2000 The paper reviews the requirements for an Experimental Right could not be implemented as such, but should provide precious Management System (EFMS) and the methods adopted for its devel- information with respect to feasible levels of automation in the long opment. The functionality is described and the future applica- term. There are also significant by-products which will speed up shorter tion of the system is summarized. Author term research. Indeed, ARC2000 provides a 20-30 minute conflict-free planning which is a key feature of the European Air Traffic Management System (EATMS) concept Author (revised)

N94-29581* National Aerospace Lab., Amsterdam (Netherlands). N94-29584* Technische Univ., Brunswick (Germany). Inst of Right THE PHARE ADVANCED TOOLS Guidance and Control. HENK A. P. BLOM, GARF1ELD DEAN, MARC LEGUILLOU, ERIC AUTOMATIC CONTROL STEPS FOR AIRCRAFT TAXI PETRE, and UWE VOELCKERS In AGARD, Machine Intelligence in GUIDANCE Air Traffic Management 8 p Oct 1993 KLAUS MOEHLENKAMP and GUNTHER SCHAENZER In AGARD, Copyright Avail: CASI HC A02/MF A04 Machine Intelligence in Air Traffic Management 5 p Oct 1993 The Programme for Harmonisation of ATM Research in Eurccontrol Sponsored by German Research Society (PHARE) has undertaken to perform the required research work Copyright Avail: CASI HC A01/MF A04 necessary for the introduction of advanced ATM. Within this PHARE Modem high precision navigation systems based on satellite and framework, it is the task of the PHARE Advanced Tools (PATs) group inertia) navigation provide a positioning accuracy that has never been to develop the appropriate automation and communication tools to achieved before, for aircraft enroute as well as during approach and on support the air traffic controller. Although the principles for computation, the airfield. By using such combined accurate positioning systems it is prediction and control of air traffic trajectories are well developed, the possible to guide aircraft on the ground and to perform automatic various future ATM scenarios reflect different views on the way taxiing, which further increases the safety of ground operations. automation and communication technology can best be applied. The Whenever high precision terrestrial navigation is needed, common consequence of this is that PHARE research has to be directed towards aeronautical navigation displays are not able to provide the information, multiple ATM scenarios, and that the PATs to be developed should be which easily can be combined with the pilot's view from the cockpit, to applicable to automation and communication under different ATM deliver the necessary guidance aid. A flexible map display is desired to scenarios. The paper gives an overview of the approach taken by the be shown in the cockpit The new taxi guidance system GtNaS, PATs group in facing this challenge. Author presented in this paper, is based on an integrated navigation system (DGPS/INS) and a digital map using only the standard display and navigation hardware of modem commercial aircraft The system was successfully tested in one of our testbeds, a van. This van can be driven N94-29582* Centre d'Etudes de la Navigation Aerienne, Toulouse automatically by the system as well as by the pilot using the information (France). of the digital map and a drive- director. The accuracy reaches submeter THE COMMON MODULAR SIMULATOR (CMS): AN level. Author (revised) ARCHITECTURE TEST BED FOR FUTURE ADVANCED ATM SYSTEMS N94-29585* Marconi Radar Systems Ltd.. Chelmsford (England). J. R. VELTEN In AGARD, Machine Intelligence in Air Traffic Manage- AIRSIDE GROUND MOVEMENTS SURVEILLANCE ment 8 p Oct 1993 D. R. CORRALL, A. N. CLARK, and A. G. HILL In AGARD, Machine Copyright Avail: CASI HC A02/MF ACM Intelligence in Air Traffic Management 13 p Oct 1993 Sponsored in

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part by Commission of the European Communities of the demonstration program including test criteria and scenarios, Copyright Avail: CASI HC A03/MF A04 controller and pilot/aircraft response times, and risk analysis. Results In the modem world there is an increasing need for surveillance, of the demonstration program on the feasibility of the 3400 ft runway and a consequent need for automatic or semi-automatic methods for spacing standards using PRM are presented. Recommendations on processing dynamic input data and presenting it in a form which is useful radar update rate, accuracy, and display requirements for the PRM to the end user. This paper outlines advanced knowledge-based system are summarized. This paper also describes the follow-on techniques for monitoring such data. The techniques have been applied research activities to investigate further reduction of parallel runway to airport ground traffic applications and demonstrated in particular on spacing standards to below 3400 ft using the PRM system and data from actual turn-round scenarios for stand area servicing of an advanced navigation and landing systems. Applications and extension aircraft as observed by a single camera. Results are output in real-time of research results to triple and quadruple closely spaced parallel as a status report by an integrated system which is designed to handle runways are discussed. Author (revised) the vagaries of real data in respect to incompleteness and uncertainty. The new techniques developed can also be applied to other ground movements surveillance applications which have multiple sensor inputs of the same or different modalities. Author (revised)

N94-30189* Advanced Aviation Concepts, Jupiter, FL. EXTREMELY LOW VISIBILITY IFR ROTORCRAFT APPROACH (ELVIRA) OPERATIONAL CONCEPT DEVELOPMENT. N94-29586* Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, VOLUME 1: EXECUTIVE SUMMARY Final Report Wessling (Germany). Inst. of Radiofrequency Technology. CATHERINE A. ADAMS, RICHARD J. ADAMS, SCOTT A. FONTAINE, A NOVEL NEAR-RANGE RADAR NETWORK FOR AIRPORT and HOWARD A. WHEELER Mar. 1994 51 p SURFACE CONTROL (Contract DTFA01-89-C-00016) K.-H. BETHKE, B. ROEDE. M. SCHNEIDER, and A. SCHROTH In (DOT/FAA/RD-94/1.1) Avail: CASI HC A04/MF A01 AGARD, Machine Intelligence in Air Traffic Management 14 p Oct The Extremely Low Visibility IFR Rotorcraft Approach (ELVIRA) 1993 workshop was the second since 1987 to address the enhancement of Copyright Avail: CASI HC A03/MF A04 safety and reliability of helicopter operations by improving the attrac- This contribution describes a radar network for airport surface tiveness of IFR operations in lieu of special VFR operations. The 1993 movement guidance and control. The network comprises several low workshop was the next logical step in the FAA's Vertical Flight research power radar stations which are organized in modules of four stations and development program since significant, relevant analyses, simula- each. All antennas are staring and illuminating the area continuously. tion and flight test work has been accomplished in the past six years. Moving objects are localized by range profile measurements and a The workshop was held in Santa Fe, New Mexico on August 24-26, subsequent multilateration. Each module runs autonomously. The 1993. The participants were a select group of 59 industry and govern- module computer at the master station calculates the multilaterations ment experts in each of their individual disciplines. The group was and controls the communication with three slave stations. The mea- charged with the task of defining an ELVIRA operational concept in the sured data from these stations are transferred via the radar transmitters areas of: operational needs, infrastructure requirements, procedural to the master station, while the multilateration and imaging results are changes, technology requirements, night tests, and public benefits. sent via data cables to the central computer. There, the information from These experts were asked explicitly to address affordable and practical all modules will be merged and tracks will be constructed; furthermore, near term solutions to issues previously identified through their expe- a classification process on the basis of the images will be executed. rience. The deliberations at the workshop resulted in the identification Author (revised) near term needs of the operator types who would use ELVIRA, activity regions, safety factors and operational improvements. These needs were analyzed and the operational changes responsive to the needs were documented. The proceedings of the workshop culminated with a recommendation of ten IFR enhancements that would eliminate N94-29587# Federal Aviation Administration, Washington, DC. Re- current penalties for using the IFR system. If action is taken to achieve search and Development Service. these changes, safety and mission reliability will be increased through DEVELOPMENT OF PRECISION RUNWAY MONITOR SYSTEM increased flight hours under positive control. Volume 1 summarizes the FOR INCREASING CAPACITY OF PARALLEL RUNWAY activities and contributions of the participants. Volume 2 provides an OPERATIONS overview of the presentations at the workshop. Volume 3 documents GENE A. WONG In AGARD, Machine Intelligence in Air Traffic the perspectives of the participants as recorded by Technical Monitors Management 12 p Oct 1993 and observers. Author Copyright Avail: CASI HC A03/MF A04 This paper describes the results of a research program to investigate the use of advanced radar, display systems, and controller alert automation aid to increase capacity at airports with closely spaced parallel runways. Analysis has indicated that the runway spacing could be reduced without adversely affecting capacity if a surveillance radar N94-30285 Defence Research Establishment Suffield, Medicine Hat of higher update and accuracy and a high resolution color display (Alberta). system with controller alert automation aid are used. This paper first THE USE OF LOW COST DIFFERENTIAL MODE GPS describes a research program to demonstrate the feasibility of using a RECEIVERS IN UNMANNED VEHICLES precision runway monitor (PRM) system for conducting independent THOMAS E. OLLEVIER In its Proceedings of the 3rd Conference on simultaneous approaches to parallel runways spaced at less than 3400 Military Robotic Applications p 81 -85 1991 ft (1035 m) apart A PRM system consists of an improved radar system Avail: Issuing Activity (Defence Research Establishment Suffield, P.O. that provides high azimuth and range accuracy and higher data rates Box 4000, Medicine Hat, AB T1A 8K6 Canada) than the current terminal airport surveillance radar (ASR), a processing A critical component of the guidance and control system of an system that monitors all approaches and generates controller alerts unmanned vehicle is the position and attitude determination system. when an aircraft appears to be blundering, and a high resolution color This system determines the accuracy with which the unmanned vehicle display. Two airports were selected to serve as the demonstration and system can determine the position of the behicle and hence the position test facilities of the PRM system. This paper describes the key elements of the object in the vehicle's sensor field of view. Author (CISTI)

389 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

05 N94-28660# Naval Postgraduate School, Monterey, CA. A MOMENT PLOTTING METHOD FOR CHARACTERIZING AIRCRAFT DESIGN, TESTING AND AIRCRAFT FATIGUE DATA POPULATION DISTRIBUTIONS PERFORMANCE M.S. Thesis ROLF M. LOKENSGARD Sep. 1993 106 p Includes aircraft simulation technology. (AD-A275500) Avail: CASI HC A06/MF A02 A method was developed where, by statistically analyzing samples of aircraft fatigue data from a population, the population's probability distribution function is determined. The method uses plots of a sample's coefficient of variation, and measures of skewness and kurtosis, N94-28647* Battelle Columbus Labs., OH. superimposed on templates of curves created from the moment EFFECTS OF REPAIR ON STRUCTURAL INTEGRITY Final functions of normal, lognormal, Weibull, and exponential distributions. Report, Jan. 1990 - Sep. 1992 The moment functions are derived for each distribution. The plotting R. RICE, R. FRANCINI, S. RAHMAN, M. ROSENFELD, S. RUST, S. technique is combined with a comparison of goodness of fit statistics to SMITH, and D. BROEK Dec. 1993 156p form the complete distribution selection method. The method is first (Contract DTRS57-89-C-00006) tested on random numbers generated from known distributions to see (AD-A275756; DCT-VNTSC-FAA-93-11; DOT/FAA/CT-93/79; PB94- if the correct distributions are selected; then the method is applied to 143336) Avail: CASI HC A08/MF A02 helicopter loads data, fatigue life characterization test data, and count- FAA regulations require commercial aircraft operators to repair ing accelerometer data. DTIC damaged aircraft structures. These repairs must be performed in a timely manner to reduce aircraft downtime and loss of revenue. A guiding principal for such repairs is to restore the structure to the original (or better) static strength and stiffness. However, the repair can also be N94-288ir# California Polytechnic State Univ., San Luis Obispo. designed for adequate fatigue resistance, damage tolerance, and DepL of Aeronautical Engineering. inspectability. Fatigue and damage tolerance (DT) analyses should be MODIFICATION OF ACSYNT AIRCRAFT COMPUTER based on realistic stress histories which, in turn, should be derived from PROGRAM FOR PRELIMINARY DESIGN Semiannual Progress realistic load spectra. Thus, an algorithm for the development of a stress Report, Oct. 1993 - Mar. 1994 history should be included in a comprehensive analysis of repairs. DANIEL J. BIEZAD and RUBEN ROJOS-OVIEDO 31 Mar. 1994 Since many damage repair stations and airlines do have at least basic 13 p computer facilities that can be used for fatigue and damage tolerance (Contract NCC2-834) analysis, one goal has been the development of a relatively simple, yet (NASA-CR-195737; MAS 1.26:195737) Avail: CASI HC A03/MF A01 accurate analytical tool to design aircraft repairs more effectively. The This paper presents the development of a computer simulation of structural analysis and stress spectrum development procedures de- agility flight test techniques. Its purpose is to evaluate the agility of scribed in this report are approximate and, therefore, have certain aircraft configurations early in the preliminary design phase. The limitations. These procedures might be used to qualitatively compare simulation module is integrated into the NASA Ames aircraft synthesis the quality of different repair options with the original structure. design code. Trade studies using the agility module embedded within DTIC the design code to simulate the combat cycle time agility metric are illustrated using a Northrop F-20 aircraft model. Results show that the agility module is effective in analyzing the influence of common parameters such as thrust-to-weight ratio and wing loading on agility criteria. The module can also compare the agility potential between N94-28657* Foster-Miner Associates, Inc., Waitham, MA. different configurations and has the capability to optimize agility perfor- FULL-SCALE TESTING AND ANALYSIS OF CURVED mance early in the design process. Author AIRCRAFT FUSELAGE PANELS Final Report, May 1991 • Mar. 1992 G. SAMAVEDAM, D. HOAOLEY, and D. THOMSON Dec. 1993 58p N94-28837# Naval Postgraduate School. Monterey, CA. (Contract DTRS57-89-D-00009) ACQUISITION, DESIGN MODIFICATION, ASSEMBLY, AND (AD-A275666; DOT-VNTSC-FAA-93-10; DOT/FAA/CT-93/78; PB94- GROUND TEST OF NPS HUMMINGBIRD REMOTELY PILOTED 142551) Avail: CASI HC A04/MF A01 HELICOPTER M.S. Thesis This report presents data on (1) residual strength of aircraft GREGORY J. PICK Sep. 1993 93 p panels containing Multiple-Site Damage (MSD) in tap splices, and (2) (AD-A275546) Avail: CASI HC A05/MF A01 fatigue strength of panels subjected to cyclic pressure loading. The The Hummingbird is a 150-lb. gross weight remotely piloted testing was conducted using the dedicated Aging Aircraft Test Facility helicopter (RPH) with a 50-Ib. payload and a rotor radius of 10.25 ft. It previously built in the Foster-Miller laboratory. A previous report de- is powered by a 25 h.p. air cooled two-cylinder Westiake engine. As scribes the work in the first phase involving the design and operation of such it represents one of the largest RPH's in the world. It was the facility and the test data generated on residual strength of panels purchased from Gorham Model Products in 1992 to provide a suitable with longitudinal midday skin cracks. In the Phase II work presented rotorcraft research flight test platform for the Department of Aeronautics here, several residual strength tests were conducted to develop a and Astronautics at the Naval Postgraduate School. The helicopter was relationship between failure pressure and the lead crack length in the delivered disassembled and was accompanied by an ample supply of critical upper rivet line of the lap joint In some of the panels multiple- replacement and spare parts. Also included was a second helicopter in site damage was also built in the rivet line during fabrication. The a partially assembled condition that had been previously flown. Assem- reduction in the residual strength due to MSD has been experimentally blies provided comprised the chassis, main rotor transmission, rotor quantified. Conditions of crack arrest at tear straps and panel flapping head assembly, and tailboom with tail rotor gear box and rotor. The task were also investigated. Fatigue testing of the panel, with no initial undertaken by this thesis was to fabricate one operable RPH and to damage in the tap splice except an unbonded lap joint area, was design, fabricate, and install whatever new assemblies that were conducted to investigate the crack initiation at multiple sites, crack required for its NPS mission and to make up for deficiencies in the i growth rates and eventual linkup of the ligaments and fracture failure. previous design. The work completed required: (1) design, fabrication, The ultimate life of the panel, and the damage in critical upper and lower and installation of a new skid-type landing gear system; (2) redesign j skin rivet rows was determined. Conclusions of practical interest were and incorporation of a new engine mount system; (3) modification of the drawn from the test data DTIC engine and main rotor transmission coupling; (4) upgrade of the

390 AIRCRAFT DESIGN, TESTING AND PERFORMANCE 05 electrical system and elongation of the nose section; and (5) initial OF ACHIEVABLE PERFORMANCE IN AIRCRAFT DESIGN M.S. engine testing. Recommendations for future modifications to the heli- Thesis copter and laboratory facilities and development of a static hover test MARK F. REIDINGER Dec. 1993 151 p fixture are also included. DTIC (AD-A275359; AFIT/GAE/ENY/93D-23) Avail: CASI HC A08/MF A02 This thesis explores the usefulness of a computer aided control design software package called ODES in determining the limits of N94-28870* Naval Postgraduate School, Monterey, CA. achievable aircraft performance as it relates to controller capability. PROCEDURAL GUIDE FOR MODELLING AND ANALYZING Modem aircraft, particularly fighters, are being designed to be statically THE FLIGHT CHARACTERISTICS OF A HELICOPTER DESIGN unstable to enhance their maneuverability and performance. It is USING FLIGHTLAB M.S. Thesis possible that the aircraft, although physically capable of a certain level GARY P. MCVANEY 23 Sep. 1993 150p of performance due to its engine/airframe combination, may be uncon- (AD-A275077) Avail: CASI HC A07/MF A02 trollable up to this level. This study sought to develop a methodology to This thesis presents one method for modeling and analyzing a use QDES to make a preliminary analysis of an aircraft design to helicopter design using FlightJab. Flighttab is a computer program that determine if there exists a controller that will enable this design to meet provides for engineering design, analysis, and simulation of aircraft its performance goals and, if not, to determine what the limits of using nonlinear dynamic modeling techniques. The procedure to model achievable performance are. DTIC a single main rotor helicopter is outlined using a sample helicopter design. The analysis procedure contains computer program scripts for determining the time response of the helicopter to standard control N94-29042# Logicon, Inc., Dayton. OH. inputs such as a longitudinal impulse, a lateral step, and a pedal BACKSCATTER HAZE DEVICE FOR MEASUREMENT OF HAZE doublet. A linear model of the helicopter can be extracted from the IN AIRCRAFT TRANSPARENCIES Final Report, Jan. 1991 - nonlinear model, and a comparison of the time response to the control Dec. 1992 Inputs based on these two models is presented. The procedure for H. L. TASK (Air Force Systems Command, Wright-Patterson AFB, conducting frequency sweep testing for the linear model is also OH.), RICHARD J. BARTELL, and SHELDON E. LINGER May 1993 discussed. This guide to using Rightiab for aircraft modelling and 36 p analysis is designed to make it easier to use Rightiab for creating (Contract AFPROJ. 7184) additional aircraft models for use in control system analysis and (AD-A275127; AL/CF-TR-1993-0102) Avail: CASI HC A03/MF A01 additional engineering design. DTIC The method currently used throughout the aircraft transparency industry to measure haze is ASTM Test Method D1003. This procedure was originally developed for applications involving small, thin, and flat N94-28957* Fuji Heavy Industries Ltd., Tokyo (Japan). transparent parts. Major limitations of Test Method D1003 include its A DESIGN OF THIRD-GENERATION AIRFOILS FOR restriction to small, flat samples and its requirement for having the HELICOPTER ROTOR BLADES USING NAVIER-STOKES source and detector on opposite sides of the sample under test In order [NABIE SUTOKOSU KAISEKI O MOCHIITA HERIKOPUTA to facilitate field testing of installed aircraft windscreens, a test method ROTA BUREDO YO DAI 3 SEDAI KOUSEINO YOKUGATA NO was developed which overcomes the limitations of Test Method 01003. SEKKEI] The new method determines haze values by measuring the amount of MASAAKINAKADATE and MASAHIRO OBUKATA In NAL, Proceed- light backscattered off the surface of the transparency under test. A ings of the 10th NAL Symposium on Aircraft Computational Aerody- prototype instrument was developed and tested against D1003. The namics p 57-62 Dec. 1992 In JAPANESE results of those tests are presented. The new instrument consists of an Avail: CASI HC A02/MF A03 integrating sphere, a mechanically chopped incandescent light source, Recent progress in the performance of helicopters has been so a silicon detector, and supporting electronics. This report describes the remarkable that maximum speeds of over 200 knot are not uncommon device, which is based on U.S. Patent Number4,687,338, in detail. Use among experimental helicopters. Such high performance owes much of this type of device in the field could provide quantitative data for to the progress in rotor aerodynamics, especially the development of determining when an installed aircraft, windscreen should be replaced advanced airfoils. Additionally, the recent progress in Computational or refinished in place. DTIC Ruid Dynamics (CFD) and supercomputers has been quite remarkable. These improvements make it possible to accurately predict airfoil performance up to and beyond maximum lift, where viscous and vortical N94-29200# Naval Postgraduate School, Monterey, CA. effects prevail. A practical design target was identified. The target was A NON-LINEAR SIMULATION FOR AN AUTONOMOUS to obtain airfoil shapes with comparable performance to that of Boeing UNMANNED AIR VEHICLE M.S. Thesis Helicopter's third-generation airfoils, VR-12 through VR-15. Prior to the DAVID R. KUECHENMEISTER Sep. 1993 123p design, a parametric study on leading edge thickness and camber was (AD-A275062) Avail: CASI HC A06/MF A02 carried out The study depended upon the fact that the maximum lift of Unmanned Air Vehicles have become increasingly important on airfoils is related to leading edge shape. An optimal combination of the modem battlefield. The restrictive requirement for runways and leading edge thickness and camber was decided during the parametric special equipment to take off and land was partially solved by the study. Then, the shape, especially around the leading edge, was vertical take off and landing Airborne Remotely Operated Device, successively refined by relaxing the leading edge pressure peak to AROD. Work done at the Naval Postgraduate School has modified the realize much higher maximum lift without spoiling other performance. AROD to not only land and launch vertically, but to fly horizontally for Finally, off-design and overall characteristics were verified up to the majority of the mission. To realize these capabilities, as well as that transonic Mach numbers. The airfoil U896H thus designed, has a of autonomous flight, an accurate computer model was required of both thickness over chord ratio of 0.10 and has symmetric section shape the AROD and the avionics test bed aircraft. Bluebird, in order to design except for the optimized cambar around the leading edge. Wind tunnel the control and navigation systems. High fidelity, non-linear equations results of the airfoil showed high maximum lift and high drag divergence of motion were derived in matrix form that represented any six degree Mach number as expected and enough to be among third-generation of freedom aircraft model, and they were then tailored for use on specific airfoils. Author (NASDA) aircraft Computer modeling of the resulting equations of motion, as well as the sensors used on the aircraft, was done using SIMULINK and MATLAB software. The resulting computer model provides a non-linear N94-28998# Air Force Inst of Tech., Wright-Patterson AFB, OH. system of equations, which are easily linearized at any desired flight School of Engineering. condition, as required by the proposed control and navigation EXPLORING ODES AS A TOOL FOR DETERMINING LIMITS system design. DTIC

391 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

N94-29391* Aeronautical Systems Div., Wright-Patterson AFB, OH. and forward flight Thus, this research work is an analytical formulation KC-135 COCKPIT MODERNIZATION STUDY AND CREW of an optimum rotor for various pre-defined missions. Dissert Abstr. REDUCTION FEASIBILITY DEMONSTRATION Final Report, 15 Aug. 1992 - 31 Aug. 1993 JOHN E. EHRHART, JR., JORDAN R. KRISS, JANET M. EMERSON, N94-29685*# Lockheed Aircraft Service, Inc., Ontario, CA. and THOMAS C. HUGHES Oct 1993 123 p AIRCRAFT SYSTEM AFT TELESCOPE CAVITY (AD-A275230; ASC-TR-93-5023) Avail: CASI HC A06/MF A02 CONFIGURATION STUDY FOR STRATOSPHERIC Future KC-135 missions will require significant increases in OBSERVATORY FOR INFRARED ASTRONOMY (SOFIA), aircraft flexibility to respond to the Air Force vision of Global Reach, PHASE 2 Final Report 22 Apr. 1994 Global Power. Such flexibility typically translates into advanced avion 171 p Original contains color illustrations ics systems and system capabilities; however, a large percentage of (Contract NAS2-13872) the avionics systems currently installed on the KC-135 are late 1950's (NASA-CR-194266; NAS 1.26:194266; R54045007) Avail: CASI HC and 1960's technology which has degraded the efficiency, reliability, A08; 62 functional color pages color pages maintainability and safety of the KC-135 mission. Strategic Air Com- The SOFIA Aircraft System (AS) Phase 1 Study was a broad- mand (SAC), now Air Mobility Command (AMC) issued a statement of based study which addressed itself to satisfying technical and program- need (SON, 1987) addressing the need to modernize the KC-135 matic requirements by drawing from existing technology and applying cockpit avionics to attend to these problems. This report documents the cost-efficient commercial approaches to the aircraft modification. In this evaluation phase of this program and for the first time directly compares SOFIA AS Phase 2 Study, five critical areas of the aircraft were selected the two-man and three-man cockpit configurations. The validation of for more detailed investigation: forward pressure bulkhead, aft bulk- the reduced crew consisted of a comparison of crew performance head, .free' shell to bulkhead interface, shell cut-out to bulkhead across three distinct missions - Minot Castle and Desert Results interface, and flooring. The in-depth investigation of these areas upon supported the two-person (No Nav) cockpit, given certain modifica- a finite element model (FEM), with a fine grid model in areas of particular tions. Based on these results, the CSEF recommended follow-on flight interest, is discussed. The FEM code used is called 'STRAP' and was test of the KC-135. Recommendations are based upon using the final developed by the engineering firm, Rasmussen and Associates. STRAP design, identical in system capabilities, as developed at the Craw is NASTRAN compatible to within 1%. The loads applied to the model Station Evaluation Facility. The key to the success of this program lies were approximated from known 747 envelope conditions. The areas of in the utilization of the modifications discussed in this report and the investigation, and a section through the fuselage is shown. The thrust proper implementation of those modifications in future KC-135 of this investigation was to develop the design concepts conceived cockpits. OTIC under phase 1 to the point where detailed design could be undertaken with a high level of confidence. Derived from text

N94-29594 Georgia Inst of Tech., Atlanta. HELICOPTER MISSION AND ROTOR PERFORMANCE N94-29854 Purdue Univ., West Lafayette, IN. OPTIMIZATION WITH QUASI-LINEAR INFLOW THEORY Ph.D. INTEGRATED PROPULSION-AIRFRAME DYNAMICS AND Thesis CONTROL Ph.D. Thesis AZHAR MANSUR KHAN 1992 149 p RONALD A. PEREZ 1990 329 p Avail: Univ. Microfilms Order No. DA9315887 Avail: Univ. Microfilms Order No. DA9313941 The enhanced performance envelope of a future generation The development of an integrated control scheme to enhance the rotorcraft is greatly desired by all the designers. This design goal can performance of a generic interconnected muttivariable dynamical sys- be achieved through rotor performance optimization design methodol- tem, consisting of a turbofan engine and an airframe, in the presence ogy, which in simple words is a numerical technique for obtaining the of predominantly destructive dynamical interactions over the flight design goals by satisfying the design requirements. The design goal for envelope is considered in this research. The control scheme consists rotorcraft performance optimization is the reduction of rotor power for of two components: a simple static forward loop or feedback loop a specific weight and mission while the design variables are the rotor precompensator to improve the interactions followed by a forward or chord and twist which define the rotor blade geometry. Constraints are feedback loop controller to improve the performance. System perfor- applied to satisfy certain minimum design requirements. Since optimi- mance specifications dictate zero steady state errors in the engine and zation is a complex numerical iterative procedure, which utilizes a airframe controlled output variables as well as minimal overshoot with considerable amount of computation time, it is desired by all designers rapid and smooth acceleration and deceleration profiles. Furthermore to come up with such an aerodynamic model for helicopter performance the system must be tolerant to soft and hard output sensor failures by calculations which utilizes minimum amount of computer processing means of analytic redundancy only. A control methodology to satisfy time. In view of the above, a steady non-uniform inflow model is used the above specifications is presented here. Necessary and sufficient to calculate the rotor performance for both hover and forward flight The conditions are presented in order to achieve stable closed loop perfor- main emphasis of this research work has been to simplify the inflow mance of the overall system by tuning every loop separately (i.e., model without loss of accuracy since, ultimately, this research work is decentralized stability). This leads to very simple control structures, but going to be a part of the multidisciplinary helicopter design optimization. even for these rather simple control schemes, a significant improve- Therefore, all time dependent terms have been neglected and all ment over previous integration schemes is obtained. Dissert Abstr. pressure functions and power expressions have been time averaged. After neglecting unsteady terms it was required to take care of the blade N94-29878 Georgia Inst of Tech., Atlanta tip loss; for which the PrandtJ's tip loss function has been used. All ROTORCRAFT AIRFRAME STRUCTURAL OPTIMIZATION FOR complex integrals have also been calculated ahead of time and stored VIBRATION AND DYNAMIC STRESS REDUCTION INCLUDING in data files to be used as input to the main program as and when DAMPING TREATMENT Ph.D. Thesis required. The rotor performance code is then modified to a nonlinear ASHISH KUMAR SAREEN 1992 129p constrained optimization problem to be used as input to the optimization Avail: Univ. Microfilms Order No. DA9315910 routine. The updated version of a FORTRAN routine (CONMIN) for This work focuses on the development of finite element based constrained function minimization is used for optimization purpose. methodologies for mass, stiffness, and damping modifications of Finally, the most optimum planform for the rotor is obtained from the practical airframe structures. This preliminary design type of engineer point of view of taper and twist, that requires the least amount of power ing methodology of analysis and optimization allows rapid and accurate for a given thrust for hover, for forward flight, and for certain specified engineering prediction and placement of responses while guiding the missions. The missions to be optimized are a combination of both hover structural designer-dynamicist in determining the location, type and

392 AIRCRAFT DESIGN, TESTING AND PERFORMANCE 05 quantity of structural modifications when the airframe is sustaining fastener holes can be detected easily by acoustic emission without the severe forced vibrations. For new airframe structures, minimum weight removal of fasteners. Acoustic emission monitoring is shown to be structures can be designed with proper placement of airframe natural superior to conventional nondestructive testing in locating fatigue frequencies and subject to constraints on forced response displace- cracks and can be used to determine load conditions leading to crack ments and dynamic stresses by systematic nonlinear programming- growth. Author (CISTI) based modifications of mass, stiffness and damping of the structure. In the case of an existing design, when significant mass and stiffness modifications cannot be affected, the designer can resort to viscoelas- N94-30131# Royal Military Coll. of Canada, Kingston (Ontario). Dept tic type energy-dissipation damping treatments and determine their of Physics. efficacy. Furthermore, should the change of excitation frequency bring ENHANCED FATIGUE CRACK DETECTION IN AGING about modal resonance, damping treatments can control response due AIRCRAFT USING CONTINUOUS ACOUSTIC EMISSION to resonating modes, without resorting to stiffness or mass changes. MONITORING This work focuses on the development of necessary computational STUART L. MCBRIDE, YANHUA HONG, and MICHAEL POLLARD tools for airframe structural optimization and implements the sensitivity Feb. 1993 12 p analysis procedures for the various design constraints encountered in (DREP-93-16; CTN-94-61137) Avail: CASI HC A03/MF A01 vibration and fatigue design of structures. The application of the Acoustic emission measurements were used to detect fatigue optimization procedure is demonstrated using both an elastic-line as cracks in a full-scale aircraft structure during ground durability and welt as a built-up finite element model of the Bell AH-1G helicopter damage tolerance testing. Data are presented for about 3,000 equiva- airframe structure. Dissert. Abstr. lent flying hours of continuous monitoring. Acoustic emission data were acquired via piezoelectric sensors using a 32-channel instrumentation N94-29887 Civil Aviation Authority, London (England). system. The regions of the aircraft structure monitored were located on AIRCRAFT EVACUATIONS: THE EFFECT OF A CABIN WATER the lower wing skin, particularly the 15 percent, 39 percent, and 44 SPRAY SYSTEM UPON EVACUATION RATES AND percent spar regions. Fatigue cycling loads were applied at various BEHAVIOUR loading points to simulate the known flight load spectra measured on D. M. BOTTOMLEY (Cranfield Inst of Tech., Bedford, England.), H. C. flying aircraft. Defects detected by acoustic emission and confirmed by MUIR (Cranfield Inst. of Tech., Bedford, England.), and M. C. LOWER conventional nondestructive methods were of two types: fatigue cracks (Southampton Univ., England.) Mar. 1993 71 p Original contains color in fastener holes repaired at or before 9,754 equivalent flying hours or illustrations new defects occurring principally at the wing skin edge aft of the 44 (CAA-PAPER-93008; ISBN-0-86039-547-2; ETN-94-95514) Copyright percent spar. For a number of defects, acoustic emission detection Avail: Issuing Activity (Civil Aviation Authority, Greville House, 37 preceded conventional detection by about 3,000 equivalent flying Gratton Road, Cheltenham, England, HC) hours. Compared to periodic monitoring, continuous acoustic emission An experiment which investigated the human factors aspects of monitoring increases the number of crack advance events available for water spray systems, proposed as a means of reducing the effects of analysis and enables more secure confirmation of their source. Con- fire occurring in an aircraft cabin, is reported. The potential effects of tinuous monitoring also improves the location of crack advance sources such systems upon evacuation rates and other issues such as visibility and provides a better estimate of distributed structural noise. and audibility within the cabin were investigated. In total, eight full scale Author (CISTI) aircraft evacuations were conducted using a 707 airframe. Each evacuation involved a group of around forty five adults who performed one evacuation only. Four groups evacuated in dry conditions, the N94-30293 Defence Research Establishment Suffield, Ralston remaining four evacuated in the water spray. Video cameras were (Alberta). positioned both inside the aircraft cabin and on the platform outside to HATT-X: A HIGH PERFORMANCE FLYING LABORATORY FOR provide objective measures of evacuation performance. Subjective AUTONOMOUS UNMANNED AIRCRAFT RESEARCH AND accounts were also obtained using post evacuation questionnaires. DEVELOPMENT The results revealed that the evacuation times for the two conditions ALEX B. MARKOV and ROBERT W. HERRING In its Proceedings of were virtually identical, the lack of a statistically significant difference the 3rd Conference on Military Robotic Applications p 136-142 1991 suggesting that the presence of the water spray did not affect evacua- Avail: Issuing Activity (Defence Research Establishment Suffield, P.O. tion rates. Other results are given. ESA Box 4000, Medicine Hat, AB T1A 8K6 Canada) An experimental flight vehicle has been developed by the Cana- N94-30129* Royal Military Coll. of Canada, Kingston (Ontario). Oept dian Forces to serve as a flying platform on which to investigate and of Physics. demonstrate a variety of emerging technologies. This vehicle is the ACOUSTIC EMISSION MONITORING OF AGING AIRCRAFT High-speed Aeronautical Technologies Testbed (HATT-X), a high STRUCTURES subsonic speed rocket powered drone that has evolved from the S. L. MCBRIDE, M. R. VINER, and M. D. POLLARD Mar. 1993 ROBOT-X aerial target drone. HATT-X is a highly maneuverable 13 p platform that is capable of autonomous and semiautonomous flight. It (DREP-93-17; CTN-94-61135) Avail: CASI HC A03/MF A01 is currently being used to investigate a number of drone technologies. Acoustic emission measurements were used to detect fatigue Capabilities that are being pursued include highly agile evasive maneu- cracks in a full-scale aircraft structure during ground durability and vering, the ability to take intelligent actions to counter defensive damage tolerance testing. Measurements were made using a 16- measures, and supersonic flight Current capabilities of HATT-X and channel data acquisition system receiving signals from piezoelectric ongoing research and development are reviewed. Planned enhance- sensor elements. Fatigue cycling loads were applied at various loading ments that will facilitate a number of advanced configurations are also points on the aircraft structure to simulate the known flight load spectra discussed. Author (CISTI) measured in flight Acoustic emission data were recorded for 700 equivalent flying hours and analyzed at intervals. After 700 hours of testing it was dear from the acoustic emission data that significant crack N94-30342 National Aerospace Lab., Amsterdam (Netherlands). Ruid growth was occurring in the starboard wing skin. Fasteners were Dynamics Dtv. removed to inspect fastener holes in the damage area identified by DEVELOPMENT OF A METHOD TO PREDICT TRANSONIC acoustic emission. Fatigue cracks were detected in several holes using LIMIT CYCLE OSCILLATION CHARACTERISTICS OF FIGHTER eddy current only after the structure was loaded to open the cracks. AIRCRAFT (CONTINUED) Acoustic emission data were further analyzed to reconstruct the history JOSJ.MEIJERandATLEEM.CUNNINGHAM,JR. 10Apr. 1992 21 of defect growth and to separate the crack growth emission data from p Presented at the 33rd AIAA/ASME/AHS/ASC Structures, Structural crack face rubbing data. The tests show that cracks originating inside Dynamics and Materials Conference/Dynamics Specialist Conference,

393 06 AIRCRAFT INSTRUMENTATION

Dallas, TX, 16-17 Apr. 1992 Sponsored by USAF; General Dynamics findings of the study lend support to the hypothesis that an attitude Corp.; Ministry of Defence; and National Aerospace Lab. Limited display formed of the integration of ADI and HUD type symbology will Reproducibility: More than 20% of this document may be affected by demonstrate a performance benefit over a pure HUD format DTIC microfiche quality (Contract NIVR-Q7801N) (NLR-TP-92156-U;ETN-94-95576) Copyright Avail: Issuing Activity (European Space Agency (ESA)) N94-29316? Aerospatiale, Toulouse (France). The continued development of a method to predict the transonic HOW TO CONTROL THE INCREASE IN THE COMPLEXITY OF limit cycle oscillation characteristics for a fighter aircraft is reported. An CIVIL AIRCRAFT ON-BOARD SYSTEMS earlier analysis of steady wind tunnel data, obtained for a fighter type P. CHANET and V. CASSIGNEUL In AGARD, Aerospace Software aircraft, indicated that shock induced and trailing edge separation play Engineering for Advanced Systems Architectures 10 p Nov. 1993 a dominant role in the development of Limit Cycle Oscillations (LCD) at Copyright Avail: CASI HC A02/MF A03 transonic speeds. On the basis of these data, a semi-empirical LCD After showing how the complexity of digital systems is doubling prediction method is being developed. Its preliminary version was about every five years, and evoking the difficulties caused by this applied to several configurations and correctly identified those which evolution, a methodological approach is described called the 'Systems have encountered LCO. It showed the potential for application early in Development Workshop' aiming to gain mastery of this evolution. the design process of new aircraft to determine and understand the Among design, production and validation stages, the importance of the nonlinear aeroelastic characteristics. The method has been upgraded design process is emphasized. The most acute problems of system since. It is described in its present form and results of the latest development are generally described, and examples are given of the predictions are used to further assess various parametric effects. The power and benefits that can be expected from computer design tools. ultimate refinements are expected from recent unsteady wind tunnel System architecture design and functional specification are expanded force and pressure measurements of which a few preliminary results somewhat, to show what benefits can be expected from an integrated are analyzed. ESA approach. Through the SAO example, all development stages are evoked. A rough outline of the necessary capacities for a common work environment is drawn. Finally, it is noted that the increasing necessity of international cooperation in civil aviation consolidates the proposed approach. Author 06 AIRCRAFT INSTRUMENTATION N94-29332S Alsys, Inc., Saint Cloud (France). Includes cockpit and cabin display devices; and flight instruments. ADA RUN TIME SYSTEM CERTIFICATION FOR AVIONICS APPLICATIONS JACQUES BRYGIER and MARC RICHARD-FOY In AGARD, Aero- N94-29005* Texas Univ., Arlington. Dept of Industrial Engineering. space Software Engineering for Advanced Systems Architectures 9 p INFORMATION PRESENTATION FOR EXPERT SYSTEMS IN Nov. 1993 FUTURE FIGHTER AIRCRAFT Final Report, Dec. 1992 - Aug. Copyright Avail: CASI HC A02/MF A03 1993 The certification procedures apply to a fully developed system MICA R. ENDSLEY and ESIN O. KIRIS Sep. 1993 31 p including both hardware and software components. The issue is that the (Contract F33616-89-C-0532) equipment supplier must integrate various components coming from (AD-A275126; AL/CF-TR-1993-0164) Avail: CASI HC A03/MF A01 separate sources. In particular, the Ada Run Time System is embedded This study explored the method for presentation of information fn in the equipment like any other application component This leads to two the context of a crew-aiding intelligent associate. Forty-five male Air major requirements: the Ada Run Time System must be a glass box, Force pilots and forty-five male and female students served as subjects and unused run-time services must be eliminated from the embedded in the evaluation of prototype display designs. Categorical information components. The first requirement comes from the civil aviation coding produced the shortest processing and response times for both procedures D0178A, and the second is a consequence of the need to groups of subjects. Confidence in decision making was shown to be proof the system. This can lead to the elimination of some unpredictable affected by both coding schema and subject experience level. or unsafe Ada language features. The criticality of the system consists DTIC of three levels: critical, essential, and non-essential. The report ARINC 613 (from the Airlines Electronic Engineering Committee) surveys the Ada language and provides a list of features not to be used in avionics N94-29048# Logicon, Inc.. Dayton. OH. embedded software, at least for the first two levels. A COMPARISON OF THREE AIRCRAFT ATTITUDE DISPLAY Author (revised) SYMBOLOGY STRUCTURES Interim Report. Dec. 1990 - Dec. 1991 ERIC E. GEISELMAN, ROBERT K. OSGOOD, and DAVID W. BIERS Jun. 1993 106 p Prepared in cooperation with Dayton Univ., OH N94-29334# Alenia, Torino (Italy). (Contract F33615-89-C-0532) ON GROUND SYSTEM INTEGRATION AND TESTING: A (AD-A275172; AL/CF-TR-1993-0134) Avail: CASI HC A06/MF A02 MODERN APPROACH This study evaluated the attitude information conveyance of a new B. DIGIANDOMENICO In AGARD, Aerospace Software Engineering aircraft attitude display concept The new symbology format, called the for Advanced Systems Architectures 7 p Nov. 1993 THETA symbology, was developed by integrating the shape of the Copyright Avail: CASI HC A02/MF A03 conventional ADI and the transparency of the HUD into a single format Modem aircraft, military or civil, incorporate the most up-to-date This research addressed whether or not there was a significant technology from all fields of research and development There is an performance advantage or decrement incurred by the symbology increasing tendency to develop digital control systems to replace integration. The THETA symbology, ADI, and HUD were evaluated analog control systems in all areas: engine control, power generation, during an attitude maintenance task and an attitude recovery task. The fuel control, and environmental control. Digital systems are felt to be results of the study suggest few differences between the THETA and irreplaceable in avionics, and they are quickly approaching this level in ADI formats while performance and training time were better with both flight control systems. Indeed, digital systems are responsible for the the THETA symbology and the ADI than with the HUD format The increased sophistication of modem aircraft and for the success of

394 AIRCRAFT PROPULSION AND POWER 07 avionics as it now exists. The net result is that, while in the first unsteady rotor-stator interaction calculation and a steady stage generation of jet planes there were no onboard computers, modem calculation. Author (NASDA) aircraft may have more than twenty—with single or multiple 32 bit microprocessors, multiple megabytes of RAM, and sophisticated real N94-28978# Ishikawajima-Harima Heavy Industries Co. Ltd., Tokyo time operating systems. Author (revised) (Japan). APPLICATION OF FLOW FIELD SIMULATION TO TURBINE N94-29389# Air Univ., Maxwell AFB, AL Airpower Research Inst VANE DESIGN [SUCHI SHIMYURESHON TO TABIN COCKPIT VIDEO: A LOW COST BOA SOURCE YOKURETSU SEKKEI] KEVIN W. SMITH Dec. 1993 96 p KOJI MATSUNAGA, HISAO TAKEUCHI, ATSUSHIGE TANAKA, (AD-A275228; AU-ARI-93-1) Avail: CASI HC A05/MF A01 RURIKO YAMAWAKI, HIROSHI HAMAZAKI, KAZUO KIKUCHI, and This research can not address all the bomb damage assessment OSAMU NOZAKI In NAL, Proceedings of the 10th NAL Symposium (BDA) problems experienced during the Gulf War, as time and classi- on Aircraft Computational Aerodynamics p 175-180 Dec. 1992 In fication would preclude such an analysis. Instead, it will focus on unit JAPANESE level war-fighting interfaces, particularly those to which onboard video Avail: CASI HC A02/MF A03 was a key contributor. DTIC This paper presents an application of the three dimensional Navier-Stokes computations in designing a turbine vane cascade. The accurate prediction of the cascade flow characteristics such as total 07 pressure loss and outlet flow angle is important for aerodynamic AIRCRAFT PROPULSION AND POWER engineers to -evaluate the performance of airfoil contour shapes. Curvilinear leaned and swept stator vanes, adopted to suppress the Includes prime propulsion systems and systems components, e.g., gas secondary flow and reduce the losses, are studied in detail. The turbine engines and compressors; and on-board auxiliary power plants advanced design based on the three dimensional Navier-Stokes computations succeeded in reducing the losses, showing the capa- for aircraft bility of the code as a design tool. Author (NASDA) N94-28960* Tokyo Univ. (Japan). Graduate School. NUMERICAL STUDY ON THE INTERACTION BETWEEN N94-28981* National Aerospace Lab., Tokyo (Japan). Aeroengine SCRAMJET ENGINE MODULES CAUSED BY THERMAL Div. CHOKE [SAMARU CHOKU NITORU SUKUMARA JETTO EN JIN AN ELLIPTIC-HYPERBOLIC GRID GENERATION METHOD AND NO MOJURU KANNO KANSHO] APPLICATION TO COMPRESSOR FLOWS [DAEN- TAKUOONODERAandSHOJIROKAJI In NAL, Proceedings of the SOKYOKUSEN GATA KOSHI SEISEIHO TO ASSHUKUKI 10th NAL Symposium on Aircraft Computational Aerodynamics p 75- NAGARE ENO OYO] 80 Dec. 1992 In JAPANESE KAZUOMIYAMAMOTO In its Proceedings of the 10th NAL Sympo- Avail: CASI HC A02/MF A03 sium on Aircraft Computational Aerodynamics p 193-198 Dec. 1992 Airframe-integrated scramjet engines are now proposed as one In JAPANESE of the most promising propulsion systems for hypersonic transports and Avail: CASI HC A02/MF A03 transatmospheric vehicles for single-stage-to-orbiL Such engines are A three dimensional grid generation method was developed in composed of several modules, each of which consists of an air-intake, which an elliptic grid generation equation can be locally changed into a a combustion chamber, and a nozzle, and these modules are attached simple hyperbolic type to specify exact grid spacings and directions side by side to the bottom surface of the fuselage of a vehicle. In such explicitly. Some simple weighting functions are utilized in order to a configuration, it is considered that when disturbances cause one of change the equation type smoothly. Resultant grids tor several kinds of the modules to be unstated, such influences propagate to the adjoining blade rows show the method's robustness in the convergence charac- modules through the intake and/or the nozzle, and that the normal teristics and its flexibility in application to a variety of complicated operation of the propulsion system should be destroyed. In this study, geometries. Author (NASDA) such interactions between modules of the airframe-integrated scramjet engines are investigated numerically. Shock waves generated by N94-29103*# Sverdrup Technology, Inc., Brook Park, OH. thermal choke in the heating region of the module are used to trigger STRUCTURAL/AERODYNAMIC BLADE ANALYZER (SAB) unstart. The flow field, including the yaw cross section of the modules, USER'S GUIDE, VERSION 1.0 Final Report is approximated. An inviscid compressible flow is assumed, so Euler M. R. MOREL Mar. 1994 112 p equations with heating terms are used as the governing equations. The (Contract NAS3-25266; RTOP 505-63-5B; RTOP 535-03-10; RTOP explicit symmetric TVD (Total Variation Diminishing) scheme is used. 505-62-10) From the two-dimensional calculations, the following conclusions are (NASA-CR-194460; E-8490; NAS1.26:194460) Avail: CASI HC A06/ obtained: (1) when thermal choke occurs in one module of a scramjet MFA02 engine, its influence reaches the adjoining modules through shock The structural/aerodynamic blade (SAB) analyzer provides an wave propagation and they become unstarted; and (2) the transient automated tool for the static-deflection analysis of turbomachinery process from the started condition to unstarted is completed in about 30 blades with aerodynamic and rotational loads. A structural code msec, and the unstarted modules generate not thrust but drag. calculates a deflected blade shape using aerodynamic loads input An Author (NASDA) aerodynamic solver computes aerodynamic loads using deflected blade shape input. The two programs are iterated automatically until N94-28977# National Aerospace Lab., Tokyo (Japan). deflections converge. Currently, SAB version 1.0 is interfaced with NUMERICAL STUDY ON INTERNAL FLOWS OF CENTRIFUGAL MSC/NASTRAN to perform the structural analysis and PROP3D to COMPRESSORS [ENSHIN ASSHUKUKI NO NAIBU NAGARE perform the aerodynamic analysis. This document serves as a guide for NIKANSURU SUCHI KAISEKI] the operation of the SAB system with specific emphasis on its use at TAKASHIYAMANEandTOSHIONAGASHIMA In Ms Proceedings of NASA Lewis Research Center (LeRC). This guide consists of six the 10th NAL Symposium on Aircraft Computational Aerodynamics p chapters: an introduction which gives a summary of SAB; SAB's 169-174 Dec. 1992 In JAPANESE methodology, component files, links, and interfaces; input/output file Avail: CASI HC A02/MF A03 structure; setup and execution of the SAB files on the Cray computers; Numerical calculations have been performed for the analysis of hints and tips to advise the user, and an example problem demonstrat- internal flow structures of centrifugal compressors. Computational ing the SAB process. In addition, four appendices are presented to results reveal the jet and wake structure at the impeller exit The effects define the different computer programs used within the SAB analyzer of the wake against diffuser vanes were also investigated by an and describe the required input decks. Author (revised)

395 07 AIRCRAFT PROPULSION AND POWER

1 N94-29254* Technische Hochschule, Darmstadt (Germany). Inst models with 'consistent macro-volume expressions ('hybrid combustor tuer Energie- und Kraftwerkstechnik. modelling') was proposed. This hybrid modeling approach has been NUMERICAL MODELLING OF TURBINE COMBUSTION calibrated with combustors that include diffusion flame, lean premix/ CHAMBERS prevaporized, or rich-lean types of combustion processes. The hybrid S. MA1DHOF and J. JANICKA In AGARD, Fuels and Combustion modeling technique gives good 'quantitative' agreement with mea- Technology for Advanced Aircraft Engines 10 p Sep. 1993 sured data on gaseous emissions, smoke, combustion efficiency, lean Copyright Avail: CASI HC A02/MF A04 blowout fuel-air ratio, pattern factor, liner wall temperature levels, and This paper focuses on the calculation of the flow and scalar fields gradients of a number of combustors. Author (revised) of axisymmetric gas turbine combustion chambers with non-premixed combustion. Modelling of the turbulent swirling flow is carried out both N94-29257# Pratt and Whitney Aircraft of Canada Ltd., Mississauga by viscosity and Reynolds stress closure. It is our intention to specify (Ontario). the shortcomings as well as the potential of the different schemes with RECENT CFD APPLICATIONS IN SMALL GAS TURBINE regard to prediction capabilities, numerical performance, and economic COMBUSTION SYSTEMS DEVELOPMENT worth. The various aspects of modelling are discussed. A short T. C. J. HU and L. A. PROCIW In AGARD, Fuels and Combustion description of the governing transport equations as well as the turbu- Technology for Advanced Aircraft Engines 12 p Sep. 1993 lence closure is given. An equilibrium chemistry model is compared to Copyright Avail: CASI HC A03/MF AIM a laminar flamelet model, both schemes applied in conjunction with a A typical small gas turbine combustor is modelled using CFD, and probability density formulation for scalar properties. Numerical results the numerical results are compared with laser doppler velocimetry of velocities and temperature in model gas turbine combustion cham- (LDV) measured data. The predicted flow characteristics are in excel- bers are compared with experimental results. Probable reasons for lent agreement with the measurements. Some aspects of CFD applica- deviations are deduced and some prospects for possible future devel- tion in combustor design are discussed. CFD can be used in the opment of numerical simulation of gas turbine combustion are given. following ways: as a tool in studying the flowfield development; in the Author (revised) optimization of location, size, and quantity of flow devices; in monitoring flow performance; and in correlating important design parameters. Use N94-29255* Alfa Romeo S.p A, Naples (Italy). Research and De- of CFD can significantly reduce the lapse time and the development velopment Dept cost of gas turbine combustors. Author NUMERICAL SIMULATION OF AEROTHERMAL CHARACTERISTICS IN GAS TURBINE COMBUSTORS N94-29256# Sotiete Nationals d'Etudeetde Construction de Moteurs WITH COMPLEX GEOMETRIES d'Aviation, Moissy-Cramayel (France). P. DIMARTINO, G. CINQUE, and C. PADUANO In AGARD, Fuels and AEROTHERMOCHEMICAL CALCULATIONS IN Combustion Technology for Advanced Aircraft Engines 14 p Sep. AFTERBURNERS [CALCULS AEROTHERMOCHIMIQUES 1993 DANS LES FOYERS DE RECHAUFFE] Copyright Avail: CASI HC A03/MF A04 C. DEJEU, J. L. SCHULTZ, and S. MEUNIER In AGARD, Fuels and A method is presented for calculating steady three-dimensional Combustion Technology for Advanced Aircraft Engines 8 p Sep. 1993 two-phase turbulent reactive flows with curved irregular boundaries. In FRENCH Original contains color illustrations The gas phase equations are solved in an Eulerian frame of reference Copyright Avail: CASI HC A02/MF A04 by a numerical technique based on the finite volume approach, while The detailed study of the aerodynamics and the thermodynamics the equations describing droplet motion, evaporation, and burning are of systems is an important part in the process of dimensioning and treated in a Lagrangian frame of reference. Turbulent transport is optimizing the afterburning chambers of modem turbojets. In this described by the standard k-epsilon model. The combustion model context, the article presents two examples of geometries and recent utilizes a conserved scalar formulation and an assumed shape prob- results drawn from concrete cases. The aerothermochemical code ability density function to account for chemistry-turbulence interaction. which was used was developed by ONERA within the framework of the The numerical scheme employs structured non-orthogonal grids, a Cooperative Action for Combustion Chambers (A3C). It is based on a node-centered variable arrangement and Cartesian velocity compo- volumes type technique finished with a structured three-dimensional nents. A special interpolation procedure is used to avoid checkerboard mesh adapted to the walls. The model of combustion used of the oscillations due to pressure-velocity coupling, and a tow diffusive and generalized type 'Eddy Break Up' is the subject of a more detailed bounded scheme is introduced to approximate the convective terms in presentation. Author (revised) the transport equations. The capabilities of the numerical procedure are demonstrated by simulating an annular combustion chamber for which N94-29263* General Electric Co., Cincinnati, OH. Advanced Engine experimental results were available. The agreement between calcu- Combustor Aero Design. lation and experiments ranges from fair to good. Author (revised) FUEL INJECTOR DESIGN FOR HIGH TEMPERATURE AIRCRAFT ENGINE N94-29256* General Motors Corp., Indianapolis, IN. Gas Tur- R. W. STICKLES, W. J. DODDS, T. R. KOBLISH, J. SAGER, and S. bine Div. CLOUSER In AGARD, Fuels and Combustion Technology for APPLICATION OF CFD IN COMBUSTOR DESIGN Advanced Aircraft Engines 12 p Sep. 1993 TECHNOLOGY (Contract N00140-87-C-6321) HUKAM C. MONGIA In AGARD, Fuels and Combustion Technology Copyright Avail: CASI HC A03/MF A04 for Advanced Aircraft Engines 18 p Sep. 1993 The objective of the Innovative High Temperature Aircraft Engine Copyright Avail: CASI HC A03/MF A04 Fuel Nozzle Program was to design and evaluate a nozzle capable of Multidimensional computational combustion dynamics has been operating at a combustor inlet air temperature of 1600 F (1144 K) and used over the last twenty years to provide improved insight during gas a fuel temperature of 350 F (450 K). The nozzle was designed to meet turbine combustor design and development processes. The empirical/ the same performance requirements and fit within the size envelope of analytical combustor design methodology that was first demonstrated a current production dual orifice fuel nozzle. The design approach was under the Army sponsored Combustor Design Criteria Validation to use improved thermal protection and fuel passage geometry in program conducted during 1974-1978 has been used in the design and combination with fuel passage surface treatment to minimize coking at demonstration of 15 advanced rigcombustors, four technology demon- these extreme fuel and air temperatures. Heat transfer models of strator engine combustors, three engine combustors, and one small several fuel injector concepts were used to optimize the thermal turbine augmentor. Recognizing the limitations of turbulent combustion protection, while sample tube coking tests were run to evaluate the models, numerics, and the assumptions required to fully specify the effect of surface finish, coatings and tube material on the coking rate. boundary conditions for practical gas turbine combustion systems, a Based on heat transfer analysis, additional air gaps, reduced fuel new technique that combines state-of-the-art turbulent combustion passage flow area and use of ceramic tip components reduced local

396 AIRCRAFT PROPULSION AND POWER 07 fuel wetted wall temperatures by more than 200 F (100 K) when T. J. ROSFJORD and J. M. COHEN In AGARD, Fuels and Combustion compared to a current production fuel nozzle. Sample tube coking test Technology for Advanced Aircraft Engines 10 p Sep. 1993 Sponsored results showed the importance of surface finish on the fuel coking rate. by Pratt and Whitney Aircraft Therefore, a one micro-inch (0.025 micron) roughness was specified for (Contract N00140-87-C-9902) all fuel passage surfaces. A novel flow divider valve in the tip was also Copyright Avail: CASI HC A02/MF ACM employed to reduce weight, allow room for additional thermal protec- A unique test capability has been defined and used at the United tion, and provide back pressure to reduce the risk of fuel vaporization. Technologies Research Center to evaluate the transient response of The fuel nozzle was fabricated and evaluated in a series of high advanced gas turbine combustors. This UTC Transient Combustion temperature coking tests. Initial results of these tests indicate that Facility offers the opportunity to achieve pre-defined time variations of thermal protection and surface treatments were partially successful in the air and fuel flow rates and air temperature delivered to a combustor preventing nozzle fouling, but additional refinement of the internal model. This capability can be used for model scales ranging from multi- flowpath is needed to prevent buildup of coke particles that partially nozzle combustor sectors to smaller setups focusing on one compo- blocked the spin slots which meter the nozzle fuel flow. Author nent or process. A dedicated control computer aids in establishing time profiles for the input parameters and automatically executing the transient test. Among its applications, the facility has been used to study the occurrence of in-nozzle fuel vaporization during Bodie cycles and N94-292644 Pratt and Whitney Aircraft of Canada Ltd., Mississauga to assess the tolerance of a fuel-staged combustor to rapid fuel (Ontario). redistribution. Author DESIGN ASPECTS IN SMALL AIRCRAFT GAS TURBINE FUEL INJECTORS K. MCCALDON, L. A. PROCIW, and P. SAMPATH In AGARD, Fuels and Combustion Technology for Advanced Aircraft Engines 10 p Sep. N94-29270# Fiat Aviazione S.p.A., Turin (Italy). Direzione 1993 Progettazione. Copyright Avail: CASI HC A02/MF A04 TECHNOLOGY RIGS: A TOOL FOR AFTERBURNER The causes of fuel injector spray deterioration and the effects of DEVELOPMENT this deterioration on engine durability and performance are discussed. G. RICCARDI, A. TASSELLI, and A. TROVATI In AGARD, Fuels and Small aircraft gas turbine fuel injectors present special design chal- Combustion Technology for Advanced Aircraft Engines 17 p Sep. lenges due to low fuel flow rates involved and the physical size 1993 limitations. The principal fuel injector performance requirements are Copyright Avail: CASI HC A03/MF A04 discussed in relation to their effect on the hydraulic, aerodynamic, and To develop a component of an advanced aircraft engine, heavy thermal design of aerating fuel injectors. Author experimental activities are necessary. To avoid very long and expensive test campaigns on development engines, tests on the so-called technology rigs are fundamental. Particularly in the case of combustion components, whose analytical simulations by means of computer code N94-29267# Leeds Univ. (England). Dept of Fuel and Energy. are still not completely satisfactory and where very high gas tempera- ULTRA LOW NO(X) ULTRA LEAN GAS TURBINE PRIMARY tures may cause important problems of mechanical integrity, it is ZONES WITH LIQUID FUELS essential to check the behavior of the component on the rig before G. E. ANDREWS, H. S. ALKABIE, U. S. ABDULHUSSAIN, and M. testing on the engine. This paper gives an overview of the test rigs which ABDULAZIZ In AGARD, Fuels and Combustion Technology for are used by RatAvio in the development of the afterburner system for Advanced Aircraft Engines 14 p Sep. 1993 Sponsored in part by an advanced fighter aircraft engine. The tests which are carried out on Science Research Council these rigs are described and some of the most important results are Copyright Avail: CASI HC A03/MF A04 reported, discussing the benefit they have given to the engine develop- Three low NOx gas turbine combustor design concepts, Jet Mix, ment Even if this paper obviously does not cover all the results obtained Grid Mix and radial swirters, which have been demonstrated to give very from rig tests over years of engine development, the few examples low NOx emissions using gaseous fuels have been successfully tested reported clearly show the importance of these rigs and confirm that the on liquid fuels and low NOx emissions demonstrated. The Jet Mix was financial outlay to build and update the rigs, test plants and models is shown to have low NOx emissions at atmospheric pressure and has worthwhile. Author been tested at pressure, with similar low NOx results. Kerosene performance and emissions was very similar to that for propane as the fuel. The scale up of the Jet Mix was found to be possible without increasing the NOx emissions greatly and is a preferable design option N94-29291# Advisory Group for Aerospace Research and Develop- to the use of large numbers of smaller Jet Mix modules. Sector tests at ment, Neuilly-Sur-Seine (France). Propulsion and Energetics Lab. pressure showed the Jet Mix design produced emission reductions RESEARCH AND DEVELOPMENT OF RAM/SCRAMJETS close to the best of the NASA dean combustor results. The Grid Mix low AND TURBORAMJETS IN RUSSIA [LA RECHERCHE ET LE NOx design was shown to be capable of low NOx performance using DEVELOPPEMENT DES STATOREACTEURS, DES kerosene. There was a much wider flame stability than for the Jet Mix STATOREACTEURS A COMBUSTION SUPERSONIQUE ET design and lower NOx emissions were demonstrated. The radial swirier DES TURBOSTATOREACTEURS EN RUSSIE] with vane passage of 76mm wall fuel injection was shown to have ultra Dec. 1993 230 p Lecture series held in Laurel, MD, 1-2 Dec. 1993, low NOx emissions with liquid fuels, only slightly higher than for in Cologen, Germany, 13-14 Jan. 1994, and in Paris, France, 17-18 gaseous fuels. For a high air flow radial swirier it was found that central Jan. 1994 kerosene injection gave lower NOx emissions than for gaseous fuels (AGARD-LS-194;ISBN-92-835-0732-0) Copyright Avail: CASI HC and had the potential to yield a NOx El of below 10 at simulated take off A11/MFA03 conditions. Author Russia has a long tradition of achievement in ramjet research and development The need for new and effective products has led to the establishment of ramjet research as a priority in Russian research and development This Lecture Series will present and discuss the scientific N94-29269* United Technologies Research Center, East Hartford, problems associated with the development of ramjets/scramjets and CT. Aerothermal Technology/Chemical Sciences. turboramjets. Some specific aspects of liquid/solid ramjet develop- EVALUATION OF THE TRANSIENT OPERATION OF ment the concepts of LH2 high efficiency RAM combustors, the results ADVANCED GAS TURBINE COMBUSTORS of full scale turborarnjet testing, scramjet or CFD analyses, and ground

397 07 AIRCRAFT PROPULSION AND POWER

flight tests will be studied. This Lecture Series, endorsed by the Copyright Avail: CASI HC A03/MF A03 Propulsion and Energetics Panel of AGARD, has been implemented by This lecture addresses problems of scramjet propulsion for the Consultant and Exchange program. single-stage aerospace planes. The aerospace plane main objective is acceleration of some payload up to orbital speed. It defines a require- N94-29292# Central Inst. of Aviation Motors, Moscow (Russia). ment for the propulsion system to be frugal in the wide flight speed range INTRODUCTION AND OVERVIEW OF RESEARCH AND under conditions of propulsion mass limitation and thrust compared DEVELOPMENT OF SOLID PROPELLANT RAMROCKETS, with flight vehicle weight In accordance with modem estimations, real LIQUID FUEL RAMJETS AND EXPERIMENTAL HYDROGEN hydrogen fuel scramjet specific impulse may be several times more RAM COMBUSTORS than that of a rocket engine in the wide flight speed range, from Mf=S...6 V. SOSOUNOV In AGARD, Research and Development of Ram/ up to Mf = 15...20. But hydrogen scramjet propulsion requires signifi- Scramjets and Turboramjets in Russia 19 p Dec. 1993 cant air ram connected with high heating of vehicle structure, large Copyright Avail: CASI HC A03/MF A03 hydrogen tanks (and vehicle), and special forms of the flight vehicle. As Ramjets, turboramjets, and scramjets have been studied inten- a result the scramjet advantage, as well as any other air breathing sively as possible propulsion systems for missiles, high velocity planes, engine advantage, over the modem liquid rocket engines is not and aerospace planes, which would use this type of propulsion during doubtless. Nevertheless scramjets can provide good efficiency in the atmospheric acceleration phase. All of these propulsion system aerospace planes if each scramjet element and units are developed configurations have a degree of commonality: ram ducts. This fact is very carefully and have high performances. In another case, scramjet discussed in this section of the Lecture Series. CASI may lose competition with liquid rocket engines and a full scale scramjet will be never created. Theoretical and experimental investigations, N94-29293# Central Inst. of Aviation Motors, Moscow (Russia). ground and flight model tests have demonstrated the possibility of TURBORAMJET ENGINES: TYPES AND PERFORMANCES supersonic combustion ramjet for hypersonic flights. But we must carry M. M. TSKHOVREBOV In AGARD, Research and Development of out serious investigations to obtain high efficiency of scramjet elements Ram/Scramjets and Turboramjets in Russia 22 p Dec. 1993 and scramjet propulsion as a whole to be sure of scramjet success in Copyright Avail: CASI HC A03/MF A03 aerospace plane competition with liquid rocket engine. Author (revised) In this report on turboramjet engines, some of the properties of variable cycle propulsion plants based on a combination of ramjet and N94-29296* Central Inst. of Aviation Motors, Moscow (Russia). various turbine-type engines are considered. Various measures of SCRAMJET CFD METHODS AND ANALYSIS. PART 1: engine thrust performance vs. Mach number are represented. Tur- SCRAMJET CFD METHODS. NUMERICAL SIMULATION OF boramjet engines (TRE) are classified according to their manner of THE FLOW IN SCRAMJET DUCT energy transfer to the ramjet parts. The defining principles of essential V. KOPCHENOV, K. LOMKOV, L MILLER, V. KRJUKOV, I. RULEV, TRE propulsion plant working parameters are considered. TRE's with V. VINOGRADOV, V. STEPANOV, N. ZACHAROV, R. TAGUIROV, various levels of thrust performance are presented. An effectiveness and M. AUKIN In AGARD, Research and Development of Ram/ comparison of various combined propulsion plants for future hyper- Scramjets and Turboramjets in Russia 20 p Dec. 1993 sonic transport planes and a TSTO first stage with LH2 fuel is given. A Copyright Avail: CASI HC A03/MF A03 preference is shown for the turboramjet engine as a universal multi- The computer analysis of scramjet flow became of great impor- mode propulsion plant The optimization of operating modes in re- tance because of the limited possibilities of ground tests and difficulties sponse to changing conditions is adopted as an approach to governing of measurements in high speed/enthalpy flows. This fact is a powerful the operation of a combined engine working process. Author (revised) stimulus in CFD development A short description and examples of applications of the mathematical model for scramjet duct flow devel- N94-29294* Central Inst of Aviation Motors, Moscow (Russia). oped in CIAM are presented in this paper. Derived from text RESEARCHANDDEVELOPMENTOFRAMJETS/HAMROCKETS. PART 1: INTEGRAL SOLID PROPELLANT RAMROCKETS N94-29297* Central Inst of Aviation Motors, Moscow (Russia). V. SOSOUNOV In AGARD, Research and Development of Ram/ RESEARCH AND DEVELOPMENT OF RAMJETS/RAMROCKETS. Scramjets and Turboramjets in Russia 31 p Dec. 1993 PART 2: INTEGRAL LIQUID FUEL RAMJETS Copyright Avail: CASI HC A03/MF A03 V. SOSOUNOV In AGARD, Research and Development of Ram/ Solid propellarrt ramrockets (SPRR) combine the exclusive op- Scramjets and Turboramjets in Russia 23 p Dec. 1993 erational advantages of solid rockets with the higher fuel efficiency of Copyright Avail: CASI HC A03/MF A03 air breathing engines. The specific feature of an SPRR which differs Integral liquid fuel ramjets (LFRJ) have some specific features from a liquid fuel ramjet is the arrangement of the ram combustor in influencing their arrangement and construction. Among such features which the products of the primary burning of the solid propellarrt inside are: a larger size and working duration than solid propellant ramjets the gas generator are injected through nozzles and rebumed. The (SPRR), the necessity of fuel manifolds and flameholders, the wall second feature of the SPRR combustion process is that the gas by- cooling system arrangement in the combustion chamber, and the products of primary gas generator are rebumed in the ram combustor possibility of fuel flow and nozzle position control during flight on as turbulent or quasi-turbulent gas flames. Usually there is no need for different speed/altitude trajectories. This lecture will discuss some special flameholders. These special features can lead to some pecu- items concerning the mentioned LFRJ features: the integration of ram liarities in the inserted booster case and to rather complicated gasified combustor and booster; duct flow instability during the ejection of fuel supply devices. The third special (negative) feature of SPRR is the booster case; fuel supply device and effective combustion in ramjet; constant or programmed fuel supply rate during the flight Hence, the and adaptive control of ramjet on different flight trajectories. problem of SPRR fuel flow rate control arises. This lecture discusses Author (revised) the following topics: integration of SPRR with a booster rocket engine; the energy capabilities of different ramjet solid propellants and their N94-29298* Central Inst of Aviation Motors, Moscow (Russia). application; the effectiveness of secondary fuel combustion in the ram RESEARCH AND DEVELOPMENT OF RAMJETS/RAMROCKETS. combustor, model and full scaled ramrocket ground testing; and fuel PART 3: THE STUDY OF GASEOUS HYDROGEN RAM flowrate control in ramrockets. Author (revised) COMBUSTORS V. A. SOSOUNOV In AGARD. Research and Development of Ram/ N94-29295* Central Inst of Aviation Motors, Moscow (Russia). Scramjets and Turboramjets in Russia 6 p Dec. 1993 SOME PROBLEMS OF SCRAMJET PROPULSION FOR Copyright Avail: CASI HC A02/MF A03 AEROSPACE PLANES. PART 1: SCRAMJET: AIMS AND The peculiarities of H2 ramjet turboramjet high efficiency ram FEATURES combustors are discussed which include some special topics such as: A. ROUDAKOV In AGARD. Research and Development of Ram/ flame stabilization behind the nozzle edge; increase of the number of Scramjets and Turboramjets in Russia 20 p Dec. 1993 nozzles and ram combustor length reduction; separate combustion 398 AIRCRAFT PROPULSION AND POWER 07 without mixing of flames; uniform spread of fuel and air in chamber unducted propfan propulsion systems at angle of attack. The computer section; the experiment on model burner series; and methods of codes resulting from this study are referred to as Advanced Ducted effective H2 combustion in a short combustor. Author (revised) Propfan Analysis Codes (ADPAC). This report is intended to serve as a computer program user's manual for the ADPAC developed under Task 2 of NASA Contract NAS3-25270, Unsteady Ducted Propfan N94-29299# Central Inst of Aviation Motors, Moscow (Russia). Analysis. Aerodynamic calculations were based on a four-stage Runge- CIAM EXPERIMENTAL TURBORAMJETS Kutta time-marching finite volume solution technique with added nu- M. M. TSKHOVREBOV, V. I. SOLONIN, and P. A. K. ADJARDOUZOV merical dissipation. Atime-accurat eimplici t residual smoothing operator In AGARD, Research and Development of Ram/Scramjets and was. utilized for unsteady flow predictions. For unducted propfans, a Turboramjets in Russia 23 p Dec. 1993 single H-type grid was used to discretize each blade passage of the Copyright Avail: CASI HC A03/MF A03 complete propeller. For ducted propfans, a coupled system of five grid In this report some results of the TRE operating process including blocks utilizing an embedded C-grid about the cowl leading edge was those performed on specially developed demonstrator engines are used to discretize each blade passage. Grid systems were generated considered. Essential technical requirements and design features of by a combined algebraic/elliptic algorithm developed specifically for the experimental TRE designed and developed at CIAM for investiga- ducted propfans. Numerical calculations were compared with experi- tory study on a test bench are shown. Test facilities for experimental mental data for both ducted and unducted propfan flows. The solution investigations of TRE in 'connected tube* manner and experimental scheme demonstrated efficiency and accuracy comparable with other work technology features are presented. Some results of the CIAM TRE schemes of this class. Author experimental study included engine parameters on changing to ramjet operation mode variation. Working parameters in the windmilling (ramjet) mode of operation, and flow characteristics in the afterburner- N94-29860-* Eloret Corp., Palo Alto, CA. ramjet combustion chamber are shown. A TRE based on TF parts A STUDY OF LOW EMISSIONS GAS TURBINE COMBUSTIONS characteristics matching on changing to ramjet operation mode and Final Technical Report, 1 Oct. 1990 - 31 Jan. 1994 engine working parameter variations when going to windmilling in the HENRY G. ADELMAN 25 Apr. 1994 11 p ramjet mode are discussed. Author (revised) (Contract NCC2-699) (NASA-CR-195763; NAS 1.26:195763) Avail: CASI HC A03/MF A01 Analytical studies have been conducted to determine the best N94-29300* Central Inst of Aviation Motors, Moscow (Russia). methods of reducing NO(x) emissions from proposed civilian super- SCRAMJET CFD METHODS AND ANALYSIS. PART 2: sonic transports. Modifications to the gas turbine engine combustors SCRAMJET CFD ANALYSIS. NUMERICAL SIMULATION OF and the use of additives were both explored. It was found that SUPERSONIC MIXING AND COMBUSTION APPLIED TO combustors which operated very fuel rich or lean appear to be able to SCRAMJET COMBUSTOR meet future emissions standards. Ammonia additives were also effec- V. KOPCHENOV. K. LOMKOV, S. ZAITSEV. and I. BORISOV In tive in removing NO(x), but residual ammonia remained a problem. AGARD, Research and Development of Ram/Scramjets and Studies of a novel combustor which reduces emissions and improves Turboramjets in Russia 30 p Dec. 1993 performance were initiated. In a related topic, a study was begun on the Copyright Avail: CASI HC A03/MF A03 feasibility of using supersonic aircraft to obtain atmospheric samples. A short description of a mathematical model developed in CIAM The effects of shock heating and compression on sample integrity were for numerical simulation of supersonic mixing and combustion, which modeled. Certain chemical species, including NO2, HNO3, and CIONO2 permits the analysis of the three-dimensional effects, is presented. were found to undergo changes to their composition after they passed Some aspects of mixing and combustion enhancement will also be through shock waves at Mach 2. The use of detonation waves to considered on the base of CIAM experience. Derived from text enhance mixing and combustion in supersonic airflows was also investigated. This research is important to the use of airbreathing propulsion to obtain orbital speeds and access to space. Both steady N94-29301# Central Inst. of Aviation Motors, Moscow (Russia). and pulsed detonation waves were shown to improve engine perfor- SOME PROBLEMS OF SCRAMJET PROPULSION FOR mance. Author (revised) AEROSPACE PLANES. PART 2: SCRAMJET: DEVELOPMENT AND TEST PROBLEMS A. ROUDAKOV In AGARD, Research and Development of Ram/ N94-30013"# Duke Univ., Durham, NC. Dept of Mechanical Engi- Scramjets and Turboramjets in Russia 26 p Dec. 1993 neering and Materials Science. Copyright Avail: CASI HC A03/MF A03 AEROACOUSTIC SENSITIVITY ANALYSIS AND OPTIMAL The topics covered include the following: SCRAMJET develop- AEROACOUSTIC DESIGN OF TURBOMACHINERY BLADES ment strategy; subscaie model SCRAMJET flight tests; hypersonic Status Report, 11 Jul. 1993 -10 Jan. 1994 flying laboratory and experimental double mode SCRAMJET; KENNETH C. HALL 10 Jan. 1994 24 p SCRAMJET operation in flight conditions; and experimental dual (Contract NAG3-1433) model SCRAMJET parameters. Derived from text (NASA-CR-195786; NAS 1.26:195786) Avail: CASI HC A03/MFA01 During the first year of the project we have developed a theoretical analysis - and wrote a computer code based on this analysis - to N94-29438*# General Motors Corp., Indianapolis, IN. Gas Turbine compute the sensitivity of unsteady aerodynamic loads acting on Div. airfoils in cascades due to small changes in airfoil geometry. The steady INVESTIGATION OF ADVANCED COUNTERROTATION BLADE and unsteady flow though a cascade of airfoils is computed using the CONFIGURATION CONCEPTS FOR HIGH SPEED TURBOPROP full potential equation. Once the nominal solutions have been com- SYSTEMS. TASK 2: UNSTEADY DUCTED PROPFAN ANALYSIS puted, one computes the sensitivity. The analysis takes advantage of COMPUTER PROGRAM USERS MANUAL Final Report, Mar. the fact that LU decomposition is used to compute the nominal steady 1990-Mar. 1991 and unsteady flow fields. If the LU factors are saved, then the computer EDWARD J. HALL. ROBERT A. DELANEY. and JAMES L BETTNER time required to compute the sensitivity of both the steady and unsteady May 1991 116p flows to changes in airfoil geometry is quite small. The results to date (Contract NAS3-25270; RTOP 535-03-10) are quite encouraging, and may be summarized as follows: (1) The (NASA-CR-1B7105; NAS 1.26:187105) Avail: CASI HC A06/MF A02 sensitivity procedure has been validated by comparing the results The primary objective of this study was the development of a time- obtained by Unite difference' techniques, that is, computing the flow dependent three-dimensional Euler/Navier-StokesaeradynamicanaJy- using the nominal flow solver for two slightly different airfoils and sis to predict unsteady compressible transonic flows about ducted and differencing the results. The 'analytic' solution computed using the

399 07 AIRCRAFT PROPULSION AND POWER

method developed under this grant and the finite difference results are N94-29317* Societe de Fabrication d'lnstruments de Mesure, Massy found to be in almost perfect agreement (2) The present sensitivity (France). Industries Groupe Avionique. analysis is computationally much more efficient than finite difference PERFORMING SPECIFICATIONS FOR COMPLEX SYSTEMS' techniques. We found that using a 129 by 33 node computational grid, SOFTWARE [SPECIFICATIONS EXECUTABLES DES the present sensitivity analysis can compute the steady flow sensitivity LOGICIELS DES SYSTEMES COMPLEXES] about ten times more efficiently that the finite difference approach. For F. DELHAYE and D. PAQUOT In AGARD, Aerospace Software the unsteady flow problem, the present sensitivity analysis is about two Engineering for Advanced Systems Architectures 14 p Nov. 1993 In and one-half times as fast as the finite difference approach. We expect FRENCH that the relative efficiencies will be even larger for the finer grids which Copyright Avail: CASI HC A03/MF A03 will be used to compute high frequency aeroacoustic solutions. Com- The role played by numerical technologies has increased with putational results show that the sensitivity analysis is valid for small to each generation of flight control systems. Most of the functions of these moderate sized design perturbations. (3) We found that the sensitivity systems are now assumed by integrated software and to industrialize analysis provided important insight into how airfoils should be modified the production of these software systems is rapidly becoming a to improve their aeroelastic stability. Using this insight, we redesigned necessity. The SFIM Industries have created a system which can an aeroelastically unstable cascade to produce a stable cascade. successfully address each phase of the life cycle. Helicopter operating Derived from text is intrinsically complex and any redundancy in the control systems increases this complexity. To create specifications for such systems is difficult but it is critical, as errors in specifications are often detected in N94-301304 Atlantis Scientific Systems Group, Inc., Ottawa (Ontario). the final phases of development, resulting in costly corrections. It is thus RADAR JET ENGINE HEALTH MONITORING PROJECT Final necessary to verify the precision and the justification of the specifica- Report tions as early as possible. Within its Research and Development CATHERINE HARRISON, NICHOLAS WISE, LEONARD LIGHSTONE, activities in avionics, SFIM evaluated the specifications' techniques in and L PHILIP CARR Jun. 1993 47 p the cycle of complex systems' development. Several techniques have (ASSGI-301; CTN-94-61136) Avail: CASI HC A03/MF A01 been studied (structural analysis, synchronized languages, expert Radar returns of aircraft exhibit jet engine modulation (JEM) lines. systems) and two of them were tested in experiments. These tech- The JEM lines are caused by the rotating parts in the turbine engines. niques made it possible to create and validate some of the specifica- The radar returns from the engines suggest that it may be possible to tions, with varying degrees of success. The positive aspect of these monitor the health of the engine, more specifically blade damage and techniques was clearly shown, they are significant elements in the cost possibly blade tip rub, by using radar as a sensor. A feasibility study was management program of complex systems' software. Author conducted using continuous wave K-band and X-band radar on CF-700 and J-85 engines. Results showed that to make realistic JEM measure- N94-29728 Kansas Univ., Lawrence. ments, a radar with two channels (in-phase and quadrature) is required AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF and that there are optimal viewing angles for different fan blade LEADING EDGE EXTENSIONS ON DIRECTIONAL STABILITY configurations. Radars were accordingly modified and tested including AND THE EFFECTIVENESS OF FOREBODY NOSE STRAKES an X-band cross polarization radar for seeing further into the engine and Ph.D. Thesis a X-band dual channel radar. It is not yet known if the radar can see into AN-KUOFU 1992 197p the engine beyond the second compressor stage. Work remains to be Avail: Univ. Microfilms Order No. DA9323014 done in order to decide whether radar as an engine health monitoring Low speed wind tunnel testing was conducted at Aeronautical device would present any advantages over conven tional maintenance Research Laboratory in Taiwan, ROC, using a generic configuration, to methods. Author (CISTI) investigate the effect of leading-edge extensions (LEX) on directional stability and the effectiveness of forebody nose stakes. To help interpret the wind tunnel measurements, flow visualization including 08 dye and laser sheet was also conducted. It was found that for the AIRCRAFT STABILITY AND CONTROL present configuration, the LEX vortices dominated the flow field such that the forebody vortices were depressed to stay dose to the body Includes aircraft handling qualities; piloting; flight controls; and autopi- surface. Because of this, the nose strakes on this configuration were lots. found to be ineffective in reducing directional instability and producing control moment with a single strake. Directional instability for the configuration with the LEX's was mainly caused by the vertical tail. N94-28632# Michigan Univ., Ann Arbor. Dept of Electrical Engineer- However, for the configuration with a single small nose strake at very ing and Computer Science. high angles of attack, the instability was caused by a second forebody CLOSED LOOP VIBRATIONAL CONTROL: THEORY AND vortex formed under the nose strake which stayed dose to the body surface. Using a single large nose strake, effectiveness for yaw control APPLICATIONS Final Report, 1 Jan. 1990 - 30 Sep. 1993 SEMYON M. MEERKOV, PIERRE T. KABAMBA, and ENG-KEE POH was significantly improved. However, for sideslip control, the proper forebody side for its deployment depends on the angle of attack. In 15 Dec. 1993 95 p (Contract DAAL03-90-G-0004) addition, with a pair of large nose strakes, the untrimmed yawing moment was almost eliminated at zero sideslip. A bi-stable condition (AD-A275451; ARO-27510.3-EG) Avail: CASI HC A05/MF A01 was identified for the configuration without the LEX's at alpha=46 deg. In this project, a novel control technique, referred to as Closed in the water tunnel and 48 deg. in the wind tunnel. For the baseline Loop Vibrational Control, is developed and applied to the problem of configuration with the LEX's, a bi-stable condition was also found at fuselage vibrations suppression in helicopter dynamics. This technique alpha = 55 deg. Dissert Abstr. is applicable to systems where the control input enters the open loop dynamics as an amplitude of a periodic, zero average function, and this amplitude can be chosen to depend on the systems outputs. An N94-29850 Wichita State Univ., KS. example of such a system is the helicopter with Higher Harmonic DECOUPLED FLIGHT CONTROL SYSTEM DESIGN USING Control (HHC) where periodic feathering of rotor blades around a fixed THE SINGULAR PERTURBATION METHOD pitch angle is introduced in order to suppress the fuselage vibrations. SUKJUNEPARK 1992 209 p For systems with this structure, a number of control-theoretic problems, Avail: Univ. Microfilms Order No. DA9311976 including stabilizability, pole placement and robustness, have been A new approach is developed to design the high gain output solved, and the results are reported in this document DTIC feedback with proportional plus integral (P-l) controller. The singular

400 RESEARCH AND SUPPORT FACILITIES (AIR) 09

pertuitation theory is utilized for the theoretical development This COUNTERROTATION BLADE CONFIGURATION FOR WIND approach is simpler and more comprehensive than the other methods. TUNNEL TESTING Final Report The controller produces desirable closed-loop response with minimal G. H. NICHOLS 1 Mar. 1994 164 p interaction between outputs. The new design method is applied to the (Contract NAS3-25269) design of decoupling flight control systems for the full aircraft model (NASA-CR-194868; NAS 1.26:194868) Avail: CASI HC A08/MF A02 (i.e., lateral and longitudinal dynamics). The complete process used to Work performed by GE Aircraft on advanced counterrotation obtain a decoupling flight control law is presented. A robustness study blade configuration concepts for high speed turboprop system is is included to test the controller performance with parameter variations. described. Primary emphasis was placed on theoretically and experi- The results show that the controller is robust with respect to varying mentally evaluating the aerodynamic, aeromechanical, and acoustic maneuver commands. Also, this study includes the six degree of performance of GE-defined counterrotating blade concepts. Several freedom nonlinear simulation to validate the design method. The blade design concepts were considered. Feasibility studies were nonlinear simulation results show that output-feedback solutions from conducted to evaluate a forward-swept versus an aft-swept blade the linear case satisfy the required conditions for application to nonlin- application and how the given blade design would affect interaction ear systems. A computer aided design program is developed to assist between rotors. Two blade designs were initially selected. Both designs in the interactive design process. Dissert. Abstr. involved in-depth aerodynamic, aeromechanical, mechanical, and acoustic analyses followed by the fabrication of forward-swept, forward rotor blade sets to be wind tunnel tested with an aft-swept, aft rotor blade set. A third blade set was later produced from a NASA design that was based on wind tunnel test results from the first two blade sets. This blade N94-30204'# National Aeronautics and Space Administration. Lewis set had a stiffer outer ply material added to the original blade design, in Research Center, Cleveland, OH. order to reach the design point operating line. Detailed analyses, A NOVEL APPROACH TO NOISE-FILTERING BASED ON A feasibility studies, and fabrication procedures for all blade sets are GAIN-SCHEDULING NEURAL NETWORK ARCHITECTURE presented. Author (revised) T. TROUDET (Sverdrup Technology, Inc., Brook Park, OH.) and W. MERRILL Apr. 1994 10 p (Contract NAS3-25266; RTOP 584-03-11) (NASA-TM-106563; E-8739; NAS 1.15:106563) Avail: CASIHC A02/ MFA01 N94-28749** National Aeronautics and Space Administration. Lewis A gain-scheduling neural network architecture is proposed to Research Center, Cleveland, OH. enhance the noise-filtering efficiency of feedforward neural networks, THE NOZZLE ACOUSTIC TEST RIG: AN ACOUSTIC AND in terms of both nominal performance and robustness. The synergistic AERODYNAMIC FREE-JET FACILITY benefits of the proposed architecture are demonstrated and discussed RAYMOND S.CASTNER Apr. 1994 12p Presented at the 18th AIAA in the context of the noise-filtering of signals that are typically encoun- Aerospace Ground Testing Conference, Colorado Springs, CO, 20-23 tered in aerospace control systems. The synthesis of such a gain- Jun. 1994; sponsored by AIAA scheduled neurofiltering provides the robustness of linear filtering, (Contract RTOP 505-62-84) while preserving the nominal performance advantage of conventional (NASA-TM-106495; E-8485; NAS 1.15:106495; AIAA PAPER 94- nonlinear neurofiltering. Quantitative performance and robustness 2565) Avail: CASI HC A03/MF A01 evaluations are provided for the signal processing of pitch rate re- The nozzle acoustic test rig (NATR) was built at NASA Lewis sponses to typical pilot command inputs for a modem fighter aircraft Research Center to support the High Speed Research Program. The model. Author (revised) facility is capable of measuring the acoustic and aerodynamic performance of aircraft engine nozzle concepts. Trade-off studies are conducted to compare performance and noise during simulated low-speed flight and takeoff. Located inside an acoustically treated dome with a 62- ft radius, the NATR is a free-jet that has a 53-in. diameter and is driven N94-30284 Combustion Dynamics Ltd., Medicine Hat (Alberta). by an air ejector. This ejector is operated with 125 Ib/s of compressed PAYLOAD CENTRAL CONTROL FOR UNMANNED AIRCRAFT air, at 125 psig, to achieve 375 Ib/s at Mach 0.3. Acoustic and D. R. WEILER, M. G. HENDERS, R. H. CHESNEY, and D. EHMAN In aerodynamic data are collected from test nozzles mounted in the free- Defence Research Establishment Suffield, Proceedings of the 3rd jet flow. The dome serves to protect the surrounding community from Conference on Military Robotic Applications p 74-80 1991 high noise levels generated by the nozzles, and to provide an anechoic Avail: Issuing Activity (Defence Research Establishment Suffield, P.O. environment for acoustic measurements. Information presented in this Box 4000, Medicine Hat, AB T1A 8K6 Canada) report summarizes free-jet performance, fluid support systems, and A control system concept is being developed for use in unmanned data acquisition capabilities of the NATR. Author (revised) surveillance aircraft to control the aircraft automatically in response to the imagin g sensor payload requirement. The implementation of such a control system is discussed and results of simulation tests are presented. Author (CISTI) N94-2895W National Aerospace Lab., Tokyo (Japan). Aerodynam- ics Div. RAREFIED GAS NUMERICAL WIND TUNNEL. PART 8: HOPE 09 [KIHAKU KITAI SUCHI FUDO. 8: HOPE] RESEARCH AND SUPPORT FACILITIES (AIR) KATSUHISA KOURA, MIKINARI TAKAHIRA. and HIROAKI MATSUMOTO In its Proceedings of the 10th NAL Symposium on Includes airports, hangars and runways; aircraft repair and overhaul Aircraft Computational Aerodynamics p 17-20 Dec. 1992 In facilities; wind tunnels; shock tube facilities; and engine test blocks. JAPANESE Avail: CASI HC A01/MF A03 The Rarefied Gas Numerical Wind Tunnel (RGNWT) developed for the simulation of rarefied gas flows around three dimensional whole N94-28510*# General Electric Co., Cincinnati, OH. Advanced Tech- flight bodies is applied to the H-2 Orbiting Plane (HOPE). Some flowfield nology Operations. properties and aerodynamic characteristics are presented. DESIGN AND FABRICATION OF FORWARD-SWEPT Author (NASDA)

401 09 RESEARCH AND SUPPORT FACILITIES (AIR)

N94-28951# National Aerospace Lab., Tokyo (Japan). FIXLER Jun. 1993 61 p NUMERICAL SIMULATION OF ARC HEATED WIND TUNNEL (Contract DTFA01-87-C-00014) FLOW [AKU KANETSU GATA FUDO NO SUCHI KAISEKI] (DOT/FAA/RD-93/2) Avail: CASI HC A04/MF A01 RYOJITAKAKI, YASUHIRO WADA, and YASUO WATANABE In its The research for this project included an in-depth analysis of high- Proceedings of the 10th NAL Symposium on Aircraft Computational rise fire incidents in which helicopters have been used. Following this Aerodynamics p 21 -26 Dec. 1992 In JAPANESE effort, a survey was conducted of building codes that were applicable Avail: CASI HC A02/MF A03 to the construction of heliports and helistops on the roofs of high-rise A numerical analysis of ttiermochemica) nonequilibrium inviscid buildings. These codes were examined to determine common and flow is made for the arc heated wind tunnel at NAL (National Aerospace uncommon elements and to identify strengths and weaknesses. After Laboratory). The calculation is carried out with the Harten-Yee type analyzing this data, the FAA's Heliport Design Advisory Circular (AC) TVD (Total Variation Diminishing) scheme, using finite-rate seven 150/5390-2 was reviewed. This data was then used to develop recom- species chemical reactions and the Park's 2-temperature model in mendations for additions or changes to the AC. Author order to take account of nonequilibrium thermochemistry. Results of numerical simulations for three models (perfect gas model, 1 -temperature model, and 2-temperature model) are presented and are compared N94-30200*# National Aeronautics and Space Administration. Lan- with each other. Author (NASDA) gley Research Center, Hampton, VA. APPLICATION OF FUZZY LOGIC TO THE CONTROL OF WIND TUNNEL SETTLING CHAMBER TEMPERATURE N94-29052** Texas A&M Univ.. College Station. Engineering Ex- DAVID A. GWALTNEY and GREGORY L. HUMPHREYS Mar. 1994 periment Station. 16p WIND TUNNEL TESTING AND RESEARCH Final Report, 25 (Contract RTOP 505-70-59-03) Jan. 1990-12 Mar. 1993 (NASA-TM-109105; NAS 1.15:109105) Avail: CASI HC A03/MF A01 ORAN W.NICKS 15 Nov. 1993 21 p The application of Fuzzy Logic Controllers (FLC's) to the control (Contract NAS9-18261) of nonlinear processes, typically controlled by a human operator, is a (NASA-CR-188273; NAS 1.26:188273) Avail: CASI HC A03/MF A01 topic of much study. Recent application of a microprocessor-based The topics covered include the following: a test of a Space Shuttle FLC to the control of temperature processes in several wind tunnels has model with various base enhancements intended to help reduce the proven to be very successful. The control of temperature processes in drag of the Shuttle in the landing configuration; further tests conducted the wind tunnels requires the ability to monitor temperature feedback using a Shuttle model to explore base drag improvement techniques; from several points and to accommodate varying operating conditions testing of parafoils having different airfoil shapes and line lengths; a in the wind tunnels. The FLC has an intuitive and easily configurable study of ground effects on a Shuttle model; and three dimensional structure which incorporates the flexibility required to have such an velocity profiles in the wake aft of the Space Shuttle were determined ability. The design and implementation of the FLC is presented along to study the effects of wake velocities on the Orbiter drag chute. with process data from the wind tunnels under automatic control. Derived from text Author

N94-29151# Air Force Civil Engineering Center, Tyndall AFB, FL N94-30399 National Aerospace Lab., Amsterdam (Netherlands). Ruid Engineering and Services Lab. Dynamics Div. ASPHALTIC CONCRETE PERFORMANCE UNDER HEAVY CORRECTION OF X HOT-WIRE MEASUREMENTS FOR FIGHTER AIRCRAFT LOADING Final Report, Apr. 1988 - Nov. GRADIENTS NORMAL TO THE PLANE OF THE WIRES 1990 J. H.M.GOODEN 9 Jut. 1992 53 p Limited Reproducibility: More D. A. TIMIAN, S. M. DASS, W. C. DASS, R. H. SUES, and M. B. HARDY than 20% of this document may be affected by microfiche quality Feb. 1993 359 p (PB94-125473; NLR-TP-95592; ETN-94-95592) Avail: CASI HC A04 (AD-A275046; AFCESA/ESL-TR-91-26; XC-AFCESA/ESL) Avail: A gradient correction method, which allows correction of the CASIHCA16/MFA03 results obtained from X hot wire measurements for flow gradients Rutting of asphaltic concrete pavements is rapidly becoming a normal to the plane of the hot wires, is described. The influence of these cause for concern among AF civil engineers. Modem fighter aircraft gradients on the hot wire response is determined from the hot wire often have operating tire pressures well above the capacity of the response equations. A data processing method which allows a correc- existing pavements. To reduce rutting, a mix design technique that tion of the measured data after the measurements have been com- explicitly considers the expected loading was investigated. Pavement pleted is described. The method was applied to hot wire measurements test sections were constructed and trafficked by high pressure tires. of the mean and fluctuating flow velocities in the turbulent wake shed Variations in test sections included mix design (Marshall and gyratory), from a two dimensional wing above a single trailing edge flap. ESA airfield design (4- and 6-inch flexible and rigid composite), and wheel loading (F-15C/D). Pavement loading was monitored throughout trafficking, including dynamic load magnitude, position, and velocity. N94-30423 NationalAerospace Lab..Amsterdam (Netherlands). Ruid Pavement response was measured by taking profilographs before, Dynamics Div. during, and after trafficking. Damage parameters were defined and A MODERNISED HST OF NLR calculated to evaluate test section response and performance. Dam- F.JAARSMA.J. SMITH, and R. K. VANDERDRAAI 31Oct1992 22 age varied significantly between test sections, with the most obvious p Presented at the European Windtunnels and Forum on Windtunnel factors being the mix design and the base layer support The gyratory Test Techniques, Southampton Univ., England, 14-17 Sep. 1992 test sections outperformed their Marshall counterparts with the gyratory Limited Reproducibility: More than 20% of this document may be composite section performing the best This study has shown that affected by microfiche quality pavements can be designed using gyratory methods. However, im- (AD-B179220; NLR-TP-92420-U; ETN-94-95961) Avail: CASI provements in base layer performance are needed to improve the HCA03 overall performance of flexible airfield pavements. DTIC The modernization underway and plans for the future of the High Speed Tunnel (HST) are reported. The improvement comprised three main objectives, namely: improvement of testing capabilities; improve- N94-29754* Systems Control Technology, Inc., Arlington, VA. ment of Reynolds number range; and improvement of productivity. ROOFTOP EMERGENCY HELIPORTS Final Report Because of budget limitations the total plan will be executed in phases. WILLIAM T. SAMPSON, III, SANDRA HENNINGER, and RICHARD S. The first phase, now under full execution, concerns the following more

402 CHEMISTRY AND MATERIALS 11

specific items: extension of test section length to reduce buoyancy distribution of the first failure to occur after proof testing in order to effects; adaptability to two different test section heights (1.6 and 1.8 m) understand the effects of the sustained load and the proof load on fiber allowing extended incidence range; new model support system allow- life. DTIC ing a selection between slender sting support boom with limited incidence range (30 deg), double roll sting boom with moderate incidence range (30 deg in a single sweep) and limited yaw (+ and -10 deg), or articulated sting boom with large incidence range (50 deg) and N94-28823*# National Aeronautics and Space Administration. Lan- large yaw (+ and - 30 deg); automated tunnel operation for improved gley Research Center, Hampton, VA. productivity and improved accuracy; and modernization of the controls PREDICTION OF STRESS-STRAIN RESPONSE OF SCS-6/ of the power plant. Wall and support interference effects were studied TIMETAL-21S SUBJECTED TO A HYPERSONIC FLIGHT in detail in order to arrive at improved mechanical systems and PROFILE correction methods. Further improvements planned in the future in- MASSOUD MIRDAMADI (Analytical Services and Materials, Inc., clude application of adaptive walls and an increase of power to extend Hampton, VA.) and W. STEVEN JOHNSON Feb. 1994 32 p the range in terms of Reynolds number testing. ESA (Contract RTOP 505-63-50-04) (NASA-TM-109026; NAS 1.15:109026) Avail: CASI HC A03/MF A01 Thermomechanical response of a cross-ply SCS-6/Timetal-21 S composite subjected to a generic hypersonic flight profile with the temperature ranging from -130 C to 816 C was evaluated experimen- 11 tally and analytically. A two dimensional micromechanical anlaysis, VISCOPLY, was used to predict the stress-strain response of the CHEMISTRY AND MATERIALS laminate and of the constituents in each ply during thermomechanical loading conditions. In the analysis, the fiber was modeled as elastic with Includes chemistry and materials (general); composite materials; inor- transverse orthotropic and temperature dependent properties and the ganic and physical chemistry; metallic materials; nonmetallic materials; matrix was modeled using a tnermoviscoplastic constitutive relation. and propellants and fuels. The fiber transverse modulus was reduced in the analysis to simulate fiber-matrix interface failure. Reasonable agreement was found between measured and predicted laminate stress-strain response when N94-28654# Naval Postgraduate School, Monterey, CA. fiber-matrix debonding was modeled. Author SERVICE LIFE PREDICTION OF COMPOSITE STRUCTURES THROUGH FIBER TESTING M.S. Thesis GREGORY S. MORIN Sep. 1993 94 p (AD-A275661) Avail: CASI HC A05/MF A01 N94-28830 Aluminum Co. of America, Alcoa Center, PA. Increasing the severity of the stress history of a structure reduces ROLE OF MICROSTRUCTURE ON THE FATIGUE DURABILITY its service life. Feasibility studies to increase the zero fuel weight of the OF ALUMINUM AIRCRAFT ALLOYS Progress Summary P-3 Orion depend heavily on the resulting decrease in service life of the Report, Mar. - Dec. 1993 wing box and airframe. One option of extending the service life of J. R. BROCKENBROUGH, R. J. BUCCI, A. J. HINKLE. P. E. existing aircraft is through the replacement or augmentation of critical MAGNUSEN, and S. M. MIYASATO 29 Dec. 1993 40 p Limited structural members with composite materials. Since structural compos- Reproducibility: More than 20% of this document may be affected by ites do not yet have adequate service life statistics, life predication must microfiche quality be through probability modeling. Such modeling can begin with experi- (Contract N00014-91-C-0128) mental data on accelerated testing of fiber life under several sustained (AD-A275B14) Avail: CASI HC A03 load levels. This data can be the basis for an appropriate strength-life The goal of this program is to provide a framework through which model of the fiber which can in term be related to the strength-life model metallic alloy development programs and aircraft life assessment of the composite by the local-load sharing model. The local-load sharing methodologies may exploit the potentially significant advantages in model captures the physical failure sequence of fiber failure within a performance, weight reduction, and cost savings offered by quality composite. Such a strength-life model, when combined with structural improved materials and processes. The key performance attribute analysis, can be used to predict an airframe's service life under the studied in this investigation is fatigue durability as identified by cracking changed conditions associated with the zero fuel weight increase. which originates from microstructural features and grows to an DTIC inspectable dimension of economic consequences (i.e., a crack requiring diagnostic or corrective action during the operational lifetime of a part). Meeting the program objective consists of the following steps: (1) coupling historical material performance data with new data to formu- N94-28655* Naval Postgraduate School. Monterey, CA. late the opportunity and validate the concept, (2) quantifying the SAFETY ENHANCEMENT OF COMPOSITES VIA PERIODIC relationship between microstructure and performance, (3) synthesizing PROOF TESTING M.S. Thesis and verifying analytical models for predicting statistical fatigue re- JOSEPH H. WOODWARD Sep. 1993 74 p sponse from microstructure data, and (4) developing test/evaluation (AD-A275662) Avail: CASI HC A04/MF A01 protocols to facilitate technology implementation and concept scale-up The development of new composite materials, which lack the to quantify payoff potential. DTIC historical field data base, has led to the need for an accelerated life testing method applicable to composites. Accelerated life testing by increasing the sustained stress levels requires the modeling and validation of a strength-life relation. Proof testing of composite fibers by N94-28901 Allied-Signal Aerospace Co., DBS Plaines, IL. Research over-loading is one step in the understanding of the relationship. It is and Development also important in the reliability and safety assurance in deployment of ADVANCED FUEL PROPERTIES: A COMPUTER PROGRAM composite structures. A parametric study examined the strength-life FOR ESTIMATING PROPERTY VALUES Final Report, Sep. relation of composite fibers and a methodology to analyze the fiber 1987-Jan. 1993 failures after proof testing. The fiber statistical strength was modeled by C. A. PARKER, J. T. DONNER, K. R. SQUIRE, R. J. SCHOFIELD, and a probability of failure model while a deterministic approach was taken K.R.KRIHA May 1993 175p Limited Reproducibility: More than 20% considering individual fibers and the associated life reduction each fiber of this document may be affected by microfiche quality experienced during the proof testing procedure. Also studied was the (Contract F33615-87-C-2709)

403 11 CHEMISTRY AND MATERIALS

(AD-A275248; WL-TR-93-2086) Avail: CASI HC A08 The challenges in designing high performance aircraft combus- The U.S. Air Force has seen that in order to develop fuels needed tion systems have not changed significantly over the years, but the for the high performance aircraft of the future, the ability to design fuels approach has shifted towards a more sophisticated analytical process. based on the satisfaction of a set needed properties is necessary. This Initially an overview of the U.S. Navy's component technology develop- report covers all phases of a project to develop software to accomplish ment procedure is presented to show now technology development is this goal. This report discusses the methods used by the software to still tied into mission requirements. A more technical discussion on obtain the thermochemical properties of organic fuel candidates. combustion technology status and needs will show that the classic Emphasis was placed on describing the methods used to determine the impediments that have hampered progress towards near-stoichiomet- properties of a mixture of compounds, since it is these types of mixtures ric combustion still exist Temperature rise, mixing, liner cooling, that are most likely to befound in fuels. OTIC stability, fuel effects, temperature profile control, and emissions continue to confront the aerodynamic and mechanical designers with a plethora of engineering dilemmas and trade-offs. In addition, new N94-29004f Princeton Univ., NJ. Dept. of Mechanical and Aero- materials such as ceramic matrix composites (CMC) and intermetallics space Engineering. like titanium aluminides (TiAl) are now being incorporated into every FUELS COMBUSTION RESEARCH Annual Technical Report, advanced design. The process of combustion design has taken on a 1 Oct. 1992-30 Sep. 1993 new meaning over the past several years as three dimensional codes IRVIN CLASSMAN and KENNETH BREZINSKY 10 Dec. 1993 24 p and other advanced design and validation tools have finally changed (Contract AF-AFOSR-0431-91) the approach from a 'cut and bum' technique to a much more analytical (AD-A275122;AFOSR-94-0032TR) Avail: CASI HC A03/MF A01 process. All of these new aspects are now integral elements of the new Future Air Force aircraft fuels will contain chemical constituents equation for advanced combustion design that must be fully understood that not only contribute to the propulsion of the aircraft but also to the and utilized. Only then will the operable, high temperature capable temperature control of both the combustor walls and the aircraft body. combustion systems needed for future military aircraft be developed. Temperature control may require the use of new, endothermic fuels Author such as methylcydohexane (MCH). This cydoalkane in the presence of a catalyst dehydrogenates to toluene. The toluene and hydrogen product containing a small amount of unreacted MCH, fuel the com- N94-29249* Rolls-Royce Ltd., Bristol (England). bustor. The burning characteristics of the mixture as well as its COMBUSTION FOR FUTURE SUPERSONIC TRANSPORT temperature stability as it is transferred to the combustor, most likely as PROPULSION a supercritical fluid, are largely unknown. Clarifying the combustion and B. W. LOWRIE In AGARD. Fuels and Combustion Technology for thermal stability characteristics of both gaseous and supercritical fluid Advanced Aircraft Engines 6 p Sep. 1993 mixtures of toluene and methylcydohexane has been the focus of the Copyright Avail: CASI HC A02/MF ACM past year's research. Gas phase flow reactor studies of the pyrolysis Even with ifs marginal performance, Concorde has demon- and oxidation of pure MCH and of the oxidation of mixtures of MCH and strated that supersonic civil aircraft are a practical proposition. A toluene nave revealed the chemical means by which MCH affects the second generation machine will need sufficiently good performance for oxidation chemistry of toluene. Supercritical fluid flow reactor examina- a robust operating system that can provide reliable, frequent service tions of the thermolysis of MCH and toluene mixtures have suggested with competitive economics. Additionally, the propulsion system must chemical routes to deposit formation in the fluid fuels. These results be acceptable environmentally. That is it must create acceptable noise are described in greater detail in this report DTIC levels around airports and have acceptable emissions throughout its mission including cruise. Whatever devices may be used to improve the acceptability at subsonic flight conditions, the high operating tempera- N94-29246* Advisory Group for Aerospace Research and Develop- tures at cruise can create difficult targets for the operation of the ment Neuilly-Sur-Seine (France). Propulsion and Energetics Panel. combustion system both mechanically and in the combustion process FUELS AND COMBUSTION TECHNOLOGY FOR ADVANCED itself. While the driving force is ever better fuel consumption and weight AIRCRAFT ENGINES [LES PROPERGOLS ET LES SYSTEMES to achieve economic viability, a future supersonic transport engine will DE COMBUSTION POUR LES MOTEURS D'AERONEFS] have cycle temperatures limited only by the mechanical integrity of the Sep. 1993 495 p In ENGLISH and FRENCH Symposium held in major components. The environment of the major components in Ruggi, Italy, 10-14 May 1993 Original contains color illustrations modem gas turbine engines is dominated by the air delivered by the (AGARD-CP-536;ISBN-92-835-0719-3) Copyright Avail: CASI HC compressor system. Consequently the maximum compression tem- A21/MF A04 perature is governed by materials available for the turbine and com- The conference proceedings contains 38 papers that cover new pressor discs. The continued improvement of the disc material leads to technologies for low NO(x) combustors and advanced high pressure/ combustion inlet temperatures beyond today's experience and sets high temperature cycle engines. The technical evaluation report and difficult targets for combustion system emissions. This is worsened by the keynote address are included at the beginning, and discussions the requirement being at cruise and therefore maintained for the major follow most papers. The symposium was arranged in the following part of the mission. Problems such as creep and oxidation of metallic sessions: technology overview papers (two papers); modeling: pollut- parts are also considered. Author (revised) ant formation (four); modeling: combustor design (five); high temperature fuels and fuel systems (six); combustion research: performance (six); combustion research: emissions (five); fuel atomization: diagnos- N94-29252S Cranfield Inst of Tech., Bedford (England). School of tics and modeling (five); and combustion research: flowfield and mixing Mechanical Engineering. (four). The last paper is a contribution from Russia not allocated to a FLOWFIELD PREDICTION OF NO(X) AND SMOKE session. PRODUCTION IN AIRCRAFT ENGINES S. AUZADEH and J. B. MOSS In AGARD. Fuels and Combustion Technology for Advanced Aircraft Engines 20 p Sep. 1993 Sponsored N94-29248* Naval Air Warfare Center, Trenton, NJ. Aircraft Div. by Science Research Council COMBUSTION TECHNOLOGY NEEDS FOR ADVANCED HIGH Copyright Avail: CASI HC A03/MF A04 PRESSURE CYCLE ENGINES CFD predictions of nitric oxide and smoke production in a tubular STEPHEN D. CLOUSER and RICHARD A. KAMIN In AGARD, Fuels combustor are described for a range of inlet temperature and pressure and Combustion Technology for Advanced Aircraft Engines 8 p Sep. conditions up to 800 K and 8 bar, chosen to distinguish the effects of 1993 both state properties and turbulence on formation rates. Combustion Copyright Avail: CASI HC A02/MF A04 models based on both laminar flamelet and chemical equilibrium

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representations are contrasted and compared with measurements in and static tests, where the behavior of a fuel is investigated in a wide the literature. While uncertainties persist with respect to the detailed variety of environments. The study of several baseline fuels in these mechanisms, notably for soot formation, a strategy is identified which devices has led to some new insights into the mechanisms of fuel extends the role of mixture fraction in the calculation of the influence of thermal (in)stability. It is becoming dear that a fuel's tendency to oxidize turbulent scalar fluctuations on emissions prediction. Author (revised) (to form peroxides, for example) is often inversely proportional to its ten dency to form insoluble deposits. Author (revised)

N94-29259* Pratt and Whitney Aircraft, West Palm Beach, FL. Fuels and Lubricants Group. N94-29262# Systems Research Labs., Inc., Dayton, OH. HIGH TEMPERATURE FUEL REQUIREMENTS AND PAYOFFS DEVELOPMENT OF GLOBAL/CHEMISTRY MODEL FOR JET- TEDD B. BIDDLE and BENNETT M. CROSWELL In AGARD, Fuels FUEL THERMAL STABILITY BASED ON OBSERVATIONS and Combustion Technology for Advanced Aircraft Engines 12 p Sep. FROM STATIC AND FLOWING EXPERIMENTS 1993 Sponsored by AFWAL and Naval Air Propulsion Test Center V. R. KATTA, E. G. JONES, and W. M. ROQUEMORE In AGARD, Copyright Avail: CASI HC A03/MF A04 Fuels and Combustion Technology for Advanced Aircraft Engines 11 p This paper describes a study performed under contract to Air Sep. 1993 Force Wright Laboratory, Wright-Patterson Air Force Base, Dayton, OH (Contract F33615-90-C-2033) in association with the Naval Air Propulsion Laboratory, Trenton, NJ. Copyright Avail: CASI HC A03/MF A04 The study projected fuel temperature capability requirements for future Two global-chemistry models for oxidative deposition of jet fuels tactical fighter applications and the payoffs that would be realized by are evaluated by integrating them into a Computational Ruid Dynamics achieving these capabilities. The study was approached on the basis with Chemistry (CFDC) code. A previously developed two-step global- of the maximum benefit that might be realized through the use of high chemistry model was found to be insufficient to describe the thermal- temperature fuels, i.e. elimination of the recirculation system. Heat oxidation and -deposition rates associated with a Jet-A fuel. A new toads were projected for different missions spanning IHPTET technol- global-chemistry model has been developed systematically based on ogy phases 1,2. and 3 at different flight conditions. Fuel temperatures observations from flowing and static experiments. The global- across fuel system components were calculated at these heat loads. autoxidation reaction is modified such that the reaction rate becomes Shortfalls of the current 163 C fuel capability were shown, and minimun zeroth-order with respect to the dissolved oxygen concentration. The fuel temperature requirements were defined. The study concluded that generation of deposit-forming precursor is coupled with the autoxidation elimination of the recirculation system is not feasible but shows how reaction by introducing a radical species ROO. A formulation for the high temperature fuel capability can minimize the weight penalty sticking probability has also been developed. Deposition profiles are associated with fuel recirculation. In this way, potential payoffs for high well represented by this new model under a variety of temperature and temperature fuel development were shown in the form of reduced flow conditions. The model correctly predicts the changes in magnitude weight penalties that would normally be encountered as larger and and spatial location of the deposition peak due to changes in flow. The larger recirculation systems are required to accommodate the increas- CFDC model, which is designed for flowing systems, has been ex- ing heat loads projected for advanced aircraft Author (revised) tended to static experiments. The model incorporates a non-depleting species F(sub s) representing all non-oxygen compounds responsible for deposition. Static experiments were found to provide a useful and N94-29260* Institute National de Tecnica Aeroespacial, Madrid inexpensive method for estimating the concentration of F(sub s) in (Spain). Fuels and Lubricants Lab. the fuel. Author HIGH TEMPERATURE RESISTANT JET FUELS LUIS M. PELOCHE and SANTIAGO ASENSIO In AGARD, Fuels and Combustion Technology for Advanced Aircraft Engines 9 p Sep. 1993 N94-29265*# Pennsylvania State Univ., University Park. Dept. of Sponsored by British Petroleum Oil, Inc. Mechanical Engineering. Copyright Avail: CASI HC A02/MF A04 THE EFFECT OF INCOMPLETE FUEL-AIR MIXING ON THE The thermal stability of aviation fuels is evaluated according to the LEAN LIMIT AND EMISSIONS CHARACTERISTICS OF A LEAN ASTM D 2341 method. This characteristic is linked to the presence of PREVAPORIZED PREMIXED (LPP) COMBUSTOR generators of instability, mainly didephins and N and S derivates. The D. A. SANTAVICCA, R. L. STEINBERGER. K. A. GIBBONS, J. V. objectives of the present work are as follows: to obtain, in the laboratory, CITENO, and S. MILLS In AGARD, Fuels and Combustion Technology kerosene which is thermally stable; the isolation and identification of for Advanced Aircraft Engines 12 p Sep. 1993 Sponsored by NASA. generators of instability; and the regeneration of thermally unstable Lewis Research Center and GE kerosenes. Author (revised) Copyright Avail: CASI HC A03/MF A04 Results are presented from an experimental study of the effect of N94-29261* Wright Lab.. Wright-Patterson AFB, OH. incomplete fuel-air mixing on the lean limit and emissions characteris- RESEARCH AND DEVELOPMENT OF HIGH THERMAL tics of a lean, prevaporized, premixed (LPP), coaxial mixing tube STABILITY FUELS combustor. Two-dimensional exciplex fluorescence was used to char- T. EDWARDS, W. M. ROQUEMORE, W. E. HARRISON, and S. D. acterize the degree of fuel vaporization and mixing at the combustor ANDERSON In AGARD, Fuels and Combustion Technology for inlet under non-combusting conditions. These tests were conducted at Advanced Aircraft Engines 19 p Sep. 1993 a pressure of 4 atm., a temperature of 400 C, a mixer tube velocity of Copyright Avail: CASI HC A03/MF A04 100 m/sec and an equivalence ratio of .8, using a mixture of tetradecane, Increases in aircraft performance are leading to increases in the 1 methyl naphthalene and TMPD as a fuel simulant. Fuel-air mixtures thermal stress on the primary aircraft coolant—the fuel. Fuel thermal with two distinct spatial distributions were studied. The exciplex mea- stability limitations may offset future aircraft performance gains. The Air surements showed that there was a significant amount of unvaporized Force's Wright Laboratory is sponsoring several research programs to fuel at the combustor entrance in both cases. One case, however, address this problem. The development of an additive package for JP- exhibited a very non-uniform distribution of fuel liquid and vapor at the 8 to improve its thermal stability is the primary focus of this paper. This combustor entrance, i.e., with most of the fuel in the upper half of the program involves extensive testing of fuels and additives in a variety of combustor tube, while in the other case, both the fuel liquid and vapor test devices, culminating in tests in a fuel system simulator and engine were much more uniformly distributed across the width of the combus- tests. These tests involve Air Force personnel, on-site contractors tor entrance. The lean limit and emissions measurements were all (University of Dayton Research Institute, Systems Research Laborato- made at a pressure of 4 atm. and a mixer tube velocity of 100 m/sec, ries), Pratt and Whitney Aircraft Co., additive manufacturers, and using Jet A fuel and both fuel-air mixture distributions. Contrary to what Sandia National Laboratory. The test devices include several flowing was expected, the better mixed case was found to have a substantially

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leaner operating limit The two mixture distributions also unexpectedly HUANG In AGARD, Fuels and Combustion Technology for Advanced resulted in comparable NO(x) emissions, for a given equivalence ratio Aircraft Engines 17 p Sep. 1993 and inlet temperature, however, lower NO(x) emissions were possible Copyright Avail: CASI HC A03/MF A04 in the better mixed case due to its leaner operating limit Author As part of an ongoing program of continuous improvement by control of gaseous emissions from the combustors of gas turbines, a unique fuel-staged annular combustor is being developed for applica- N94-29268# Centra Applicazioni Militari dell'Energia Nucleare, Pisa tion to current and future Pratt & Whitney aircraft engines. The (Italy). configuration advantages of this combustor are outlined, and discus- COMPUTATIONAL AND EXPERIMENTAL RESULTS IN HIGH sions are presented on staging considerations and fuel system im- PRESSURE COMBUSTIONS OF H2/AIR AND H2/O2/H2O pacts. Development of the fuel-staged combustor is described by DINO DINI In AGARD, Fuels and Combustion Technology for reference to supporting mixing experiments and computational fluid Advanced Aircraft Engines 10 p Sep. 1993 dynamic studies, and rig tests at high pressures. Measured results are Copyright Avail: CASI HC A02/MF A04 given appropriate tor the International Aero Engines (IAE) V2500 The first results of a research and development program on engine that show progressive reductions in achieved emissions com- combustion characteristics of gaseous hydrogen fuel in a 'can' type gas pared to the goals established for this program. Author turbine combustor, both in combination with air or with oxygen and water, are here presented. Application of a H2/O2/H2O combustion chamber is suggested for the launch-boost phase of an advanced N94-29274# Defence Research Agency, Famborough (England). turboramjet Experiments have been conducted to determine the THE INFLUENCE OF AIR DISTRIBUTION ON HOMOGENEITY configuration and the operation of the hydrogen-air combustion cham- AND POLLUTANT FORMATION IN THE PRIMARY ZONE OF A ber test facility, to be transferred to two different kinds of small power TUBULAR COMBUSTOR turboshafts. Computations, project details and tests, are presented J. R. TILSTON, M. I. WEDLOCK, and A. D. MARCHMENT In AGARD, regarding high pressure and temperature stoichiornetric H2/O2 com- Fuels and Combustion Technology tor Advanced Aircraft Engines 12 p bustion in which water is gradually injected. Referring to an already Sep. 1993 realized and operated (on behalf of the author) H2/O2/H2O combustor (Contract BRfTE/EURAM-1019) for a water steam closed cycle in a turbine/alternator electrically Copyright Avail: CASI HC A03/MF A04 propelled automobile, a detailed design is developed for a quite higher This paper summarizes the work undertaken by the Defense steam temperature, as required in high performance boost phase of a Research Agency (DRA Pyestock) for the BRITE/EURAM Low Emis- low noxious emission advanced turboramjet, in which H2 and O2 are sions Combustor Technology Project No 1019. The work was jointly Stored in liquid form. Author funded by the CEC (DGXIIH), the UK DTI (CARAD - ATF4) and the UK MOD (DCSA). The gas turbine emissions problem is summarized and the design philosophy of the experimental program is described. The N94-29271*# California Univ., Irvine. Combustion Lab. principal objective was to demonstrate a simultaneous reduction of POLLUTANT EMISSIONS FROM AND WITHIN A MODEL GAS NO(x) and smoke emissions together with acceptable idling emissions TURBINE COMBUSTOR AT ELEVATED PRESSURES AND and stability in an unstaged combustor. A secondary objective was to TEMPERATURES demonstrate the extent to which NO(x) and smoke could be reduced if S. A. DRENNAN, C. O. PETERSON, F. M. KHATIB, W. A. SOWA, and the combustor was to be used as the main stage of a staged combustor G. S. SAMUELSEN In AGARD, Fuels and Combustion Technology for where a poorer idling performance could be accepted. The work Advanced Aircraft Engines 10 p Sep. 1993 Sponsored by Northrop consisted of a parametric investigation of the principal factors control- Corp. ling the emissions produced in the combustor primary zone. Particular (Contract NAG3-1124; F08635-90-C-0100) emphasis was placed on the influence of the distribution, number, and Copyright Avail: CASI HC A02/MF A04 size of air entry holes and of residence time on pollutant formation. The Conventional and advanced gas turbine engines are coming results from the complete experimental program are summarized. under increased scrutiny regarding pollutant emissions. This, in turn, These suggest that NO(x) reductions of about 30-40 percent should be has created a need to obtain in-situ experimental data at practical possible together with excellent smoke and idling performance. The conditions, as well as exhaust data, and to obtain the data in combus- results suggest that NO(x) was formed very dose to stoichiornetric tors that reflect modem designs. The in-situ data are needed to (1) flame temperatures even at very weak combustor mixture strengths assess the effects of design modifications on pollutant formation, and and under well mixed conditions. The reductions that were achieved (Z) develop a detailed data base on combustor performance for the were largely as a result of reductions of residence time. Author development and verification of computer modeling. This paper reports on a novel high pressure, high temperature facility designed to acquire such data under controlled conditions and with access (optical and extractive) for in-situ measurements. To evaluate the utility of the N94-29275* Universidad Politecnica de Madrid (Spain). Dept. de facility, a model gas turbine combustor was selected which features Motopropulsion y Termofluidodinamica. practical hardware design, two rows of jets (primary and dilution) with EFFECTS OF HYDROGEN ADDITION ON POLLUTANT four jets in each row, and advanced wall cooling techniques with laser EMISSIONS IN A GAS TURBINE COMBUSTOR drilled effusive holes. The dome is equipped with a flat-waned swirier J, SALVA and G. LOPEZ In AGARD, Fuels and Combustion with vane angles of 60 degrees. Data are obtained at combustor Technology for Advanced Aircraft Engines 9 p Sep. 1993 pressures ranging from 2 to 10 atmospheres of pressure, levels of air Copyright Avail: CASI HC A02/MF A04 preheat to 427 C, combustor reference velocities from 10.0 to 20.0 nV This paper presents an experimental work on the control of s, and an overall equivalence ratio of 0.3. Exit plane and in-situ pollutants produced in a tubular hydrocarbon fueled combustor, by the measurements are presented for HC. O2, CO2, CO, and NO(x). The injection of hydrogen in small quantities (less than 4 percent of total exit plane emissions of NO(x) correspond to levels reported from fuel). Hydrogen is introduced in the primary zone premixed with the air. practical combustors and the in-situ data demonstrate the utility and Using this technique, with lean primary zone, it is possible to reduce the potential for detailed flow field measurements. Author NO(x) emission level while maintaining CO and HC emission index at normal levels (CO and HC levels are greater without hydrogen injection). Injecting butane, instead of hydrogen, shows that there is no N94-29272# Pratt and Whitney Aircraft, East Hartford, CT. beneficial effect so the influence of hydrogen in CO and HC reduction REDUCTION OF NO(X) BY FUEL-STAGING IN GAS TURBINE is due mainly to factors such as hydrocarbon substitution and chemical ENGINES: A COMMITMENT TO THE FUTURE kinetics. An analysis to estimate the contribution of these factors is also I. SEGALMAN. R. G. MCKINNEY, G. J. STURGESS, and L-M. included. Author 406 CHEMISTRY AND MATERIALS 11

crossflow has been conducted. Temperature distributions, mixing rate, N94-292760 Imperial Coll. of Science and Technology, London (En- and standard deviation were determined for measurements with round gland). Dept. of Mechanical Engineering. jet orifices by parametric variation of flow and geometric conditions. The DUCTED KEROSENE SPRAY FLAMES results show that best mixing strongly depends on an optimum momen- R. M. PEREZ-ORTIZ, S. SIVASEGARAM, and J. H. WHITELAW In tum flux ratio. Too high ratios yield a deterioration of mixing process, AGARD, Fuels and Combustion Technology for Advanced Aircraft due to the mutual impact of opposed entraining jets. Furthermore, over Engines 16 p. Sep. 1993 Sponsored by Rolls-Royce Ltd. a wide range of geometries investigated, inline and staggered configu- (Contract N00014-89-J-1721) rations provide similar mixing rates. An appreciable enhancement of Copyright Avail: CASI HC A03/MF A04 mixing with staggered orifice configurations only occurs for high Reaction progress in premixed methane-airflames in round ducts momentum flux ratios and large spacings. ' ' Author without and with kerosene sprays has been quantified on the basis of species concentration measurements for different fueling arrange- N94-29285* Central Inst. of Aviation Motors, Moscow (Russia). ments of kerosene with equivalence ratio, proportion of liquid to ENDOTHERMIC FUELS FOR HYPERSONIC AVIATION gaseous fuel, duct length and air preheat temperature as variables in LEONID S. IANOVSKI and CLIFFORD MOSES In AGARD, Fuels and smooth and in rough combustion. The intensity of heat release close to Combustion Technology for Advanced Aircraft Engines 8 p Sep. 1993 the flame holder in rough combustion was greater than that in smooth Copyright Avail: CASI HC A02/MF A04 combustion, and the duct length necessary to ensure complete com- The creation of hypersonic vehicles and the use of jet engines with bustion decreased with air preheat temperature and upstream turbu- higher temperature cycles has resulted, in a significant increase in the lence intensity and was weakly dependent on the proportion of methane thermal stresses of the engine elements. In order to use the fuel as the to kerosene in flow arrangements where the kerosene was sprayed coolant for these elements, it is necessary to increase the heat capacity upstream of the flame-holder. The injection of kerosene through the of hydrocarbon fuels. This problem can be solved by taking advantage flame holder at a velocity larger than that of the mean flow past the disk of such high temperature chemical processes as catalytic dehydroge- led to uneven mixing and incomplete combustion. Pulsed injection of nation and thermal cracking or pyrolysis of hydrocarbon fuels, including kerosene through a pintle-type injector also resulted in incomplete the addition of the initiators and catalysts. The chemical heat capacity combustion due to the larger droplet size than in arrangements with a of hydrocarbon fuels can be used for the direct cooling of such elements steady flow of kerosene. Oscillations of large amplitude were induced as combustion chambers, nozzles, and front wing edges; indirect at equivalence ratios usually associated with smooth combustion and cooling of these elements can be accomplished by using a heat- oscillations in rough combustion ameliorated by pulsed injection of transport medium in the fuel/air or fuel/gas heat exchangers. The kerosene comprising around 10 percent of the total fuel. Author gaseous products of the decomposed fuels can be used as a working medium for the drive ofthe equipment of a fuel/feeding system. N94-29277*# National Aeronautics and Space Administration. Lewis Author (revised) Research Center, Cleveland, OH. SPRAY COMBUSTION EXPERIMENTS AND NUMERICAL N94-29356*# National Aeronautics and Space Administration. Lewis PREDICTIONS Research Center, Cleveland, OH. EDWARD J. MULARZ (Army Research Lab., Cleveland, OH.), DANIEL FUEL-RICH CATALYTIC COMBUSTION OF A HIGH DENSITY L. BULZAN, and KUO-HUEY CHEN In AGARD, Fuels and Combus- FUEL tion Technology for Advanced Aircraft Engines 21 p Sep. 1993 Original THEODORE A. BRABBS (Sverdrup Technology, Inc., Brook Park, contains color illustrations OH.) and SYLVIA A. MERRITT Washington Jul. 1993 13 p Copyright Avail: CASI HC A03/MF A04 (Contract RTOP 505-62-52) The next generation of commercial aircraft will include turbofan (NASA-TP-3281; E-7298; NAS 1.60:3281) Avail: CASI HC A03/MF engines with performance levels significantly better than those In the A01 current fleet. Control of paniculate and gaseous emissions will also be Fuel-rich catalytic combustion (ER is greater than 4) of the high an integral part of the engine design criteria. These performance and density fuel exc-tetrahydrocydopentadiene (JP-10) was studied over emission requirements present a technical challenge for the combus- the equivalence ratio range 5.0 to 7.6, which yielded combustion tor control of the fuel and air mixing and control of the local stoichiom- temperatures of 1220 to 1120 K. The process produced soot-free etry will have to be maintained much more rigorously than with gaseous products similar to those obtained with iso-octane and jet-A in combustors in current production. A better understanding of the flow previous studies. The measured combustion temperature agreed well physics of liquid fuel spray combustion is necessary. This paper with that calculated assuming soot was not a combustion product The describes recent experiments on spray combustion where detailed process raised the effective hydrogen/carbon (H/C) ratio from 1.6 to measurements of the spray characteristics were made, including local over 2.0, thus significantly improving the combustion properties of the drop-size distributions and velocities. Also, an advanced combustor fuel. At an equivalence ratio near 5.0, about 80 percent of the initial fuel CFD code has been under development and predictions from this code carbon was in light gaseous products and about 20 percent in larger are compared with experimental results. Studies such as these will condensable molecules. Fuel-rich catalytic combustion has now been provide information to the advanced combustor designer on fuel spray studied for three fuels with H/C ratios of 2.25 (iso-octane), 1.92 (jet-A), quality and mixing effectiveness. Validation of new fast, robust, and and 1.6 (JP-10). A comparison of the product distribution of these fuels efficient CFD codes will also enable the combustor designer to use than shows that in general, the measured concentrations of the combustion as valuable additional design tools for optimization of combustor products were monotonic functions of the H/C ratio with the exception concepts for the next generation of aircraft engines. Author of hydrogen and ethylene. In these cases, data for JP-10 fell between iso-octane and jet-A rather than beyond jet-A. It is suggested that the N94-29281* Technische Hochschule, Darmstadt (Germany). Right ring cross-linking structure of JP-10 may be responsible for this Propulsion. behavior. All the fuels studied showed that the largest amounts of small THE MIXING PROCESS IN THE QUENCHING ZONE OF THE hydrocarbon molecules and the smallest amounts of large condens- RICH-LEAN-COMBUSTION CONCEPT able molecules occurred at the lower equivalence ratios. This corre- TH. DOERR and D. K. HENNECKE In AGARD, Fuels and Combustion sponds to the highest combustion temperatures used in these studies. Technology for Advanced Aircraft Engines 9 p Sep. 1993 Sponsored Although higher temperatures may improve this mix, the temperature by DFG Original contains color illustrations is limited. First, the life of the present catalyst would be greatly Copyright Avail: CASI HC A02/MF A04 shortened when operated at temperatures of 1300 K or greater. The rich bum/quick quench/lean bum (RQL) combustion system Second, fuel-rich catalytic combustion does not produce soot because is a potential concept to reduce both NO(x) and CO, UHC emissions. the combustion temperatures used in the experiments were well below In view of the concept's crucial mixing process, an experimental the threshold temperature (1350 K) for the formation of soot. Increasing investigation of a nonreacting multiple jet mixing with a confined the temperature above this value would remove the soot-free nature of

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the process. Since all the fuels studied show a similar breakdown of the instant of time. This information can then be reconstructed outside the primary fuel into smaller molecular combustion products, this technique wind tunnel for visual analysis and digital processing. This yields can be applied to all hydrocarbon fuels. Author (revised) precise characterizations of aerodynamic phenomena. The reconstruction and subsequent hologram image storage process is discussed, with particular attention paid to the digital image processor and N94-29457* Aerospatiale, Suresnes (France). Dept Materiaux the data reduction technique. DOE FIRE BEHAVIOR OF AERONAUTICAL MATERIALS [COMPORTEMENT AU FEU DES MATERIAUX AERONAUTIQUES] B.COSTES, C. KURAS,andB.CARRIERS 1993 25pin FRENCH N94-28646# Instron Corp., Canton, MA. (REPT-932-600-105; DCR/M-61546/C-92; ETN-94-95484) Avail: DEVELOPMENT OF ALTERNATING CURRENT POTENTIAL CASI HC A03/MF A01 DROP (ACPD) PROCEDURES FOR CRACK DETECTION IN A set of graphics that introduce the aeronautical problems of ALUMINUM AIRCRAFT PANELS Final Report, May - Dec. 1990 tenacity and safety linked to fire in an aircraft and the combustion of D. A. JABLONSKI Dec. 1993 108p aircraft construction materials are presented. Materials currently used, (Contract DTRS57-89-D-00007) their certification, and present solutions to their associated problems, (AD-A275755; DOT-VNTSC-FAA-93-9; DOT/FAA/CT-93/76) Avail: are considered. Previous aircraft accidents and their causes are CASI HC A06/MF A02 addressed as case studies. Combustion tests and environmental The Alternating Current Potential Drop (ACPD) method is inves- constraints are reported. ESA tigated as a means of making measurements in laboratory experiments on the initiation and growth of multiple site damage (MSD) cracks in a common aluminum alloy used for aircraft construction. Procedures for N94-29900 Wichita State Univ., KS. instrumenting MSD test specimens are recommended. The ACPD THE EFFECT OF MECHANICAL PAINT STRIPPING ON THE method is found to be capable of the following: (1) detecting crack FATIGUE AND FRACTURE OF THIN ALUMINUM AIRPLANE initiation at a crack length of the order of 1 mm; (2) monitoring crack SKIN Ph.D. Thesis propagation at a resolution of the order of 5 micrometers; and (3) JOEP.AMRO 1992 150p providing an indirect measurement of crack extension in R-curve type Avail: Univ. Microfilms Order No. DA9311975 tests of fastener hole details. DTIC An experimental investigation has been carried out to evaluate the affects of dry stripping (paint removal by plastic particle blasting) on aluminum aircraft skins (2024-T3). Analytical procedures were carried out for determining changes in fatigue life and relevant fracture resis- N94-28665* Ohio State Univ., Columbus. Dept of Mechanical Engi- tance parameters such as number of cycles required to generate a neering. surface crack of certain length, crack propagation rate, and number of BOUNDARY LAYERS INDUCED BY THREE-DIMENSIONAL cycles to failure while indicating the dependence of these parameters VORTEX LOOPS Final Report, 1 May 1989 • 31 Aug. 1993 on the surface condition (morphology). The surface morphology depen- A. T. CONLISK, H. AFFES, O. R. BURGGRAF, and ZHENHUA XIAO dence on deformation, fracture resistance properties, and defects Dec. 1993 278 p presented on the surface were characterized using scanning electron (Contract DAAL03-89-K-0095) microscopy, optical microscopy, and other modem metallographic (AD-A275678; RF-767440/722045; ARO-26595.7-EG) Avail: CASI techniques. The results indicated that all the parameters of plastic HC A13/MF A03 media blasting had significant effects on the fatigue life of the speci- The flow field generated by a helicopter in flight is extremely mens. Minor changes in the blasting parameters may reveal different complex and it has been recognized that interactions between different results. All fatigue samples were found to exhibit a general decrease in components can significantly affect helicopter performance. In particu- life of 10 to 46 percent after being subjected to four cycles of paint lar, the effects of the interaction between the rotor wake and the removal. The samples were cyclically loaded to 20,000 cycles then helicopter fuselage are extremely difficult to predict and pose a chal- stripped and repainted four times; 20,000 cycles represents approxi- lenging problem for researchers and designers in the rotorcraft area. In mately 5 years of life. The initial stress ratio for loading was 0.1 with the present work, a model for the interaction of a rotor-tip-vortex with the stresses varying from 20 to 65 ksi. Dissert Abstr. airframe of a helicopter is developed. The present report describes the calculation of the motion of the tip-vortex toward the airframe, the calculation of the induced pressure on the airframe, and the calculation of the boundary-layer flow under the vortex during the time period prior 12 to the time when a portion of the tip-vortex collides with the airframe. ENGINEERING DTIC

Includes engineering (general); communications; electronics and electrical engineering; fluid mechanics and heat transfer, instrumentation and photography; lasers and masers; mechanical engineer- N94-28704** Naval Air Warfare Center, Indianapolis, IN. ing; quality assurance and reliability; and structural mechanics. NAVAIR AIRCRAFT WIRING STANDARDIZATION AND QUALIFICATION PROGRAM THOMAS MEINER In NASA. Lewis Research Center, Second NASA Workshop on Wiring for Space Applications p 59-61 Jan. 1994 Avail: CASI HC A01/MF A03; 8 functional color pages N94-28466* Sandia National Labs.. Albuquerque, NM. The topics are presented in viewgraph form and include the HOLOGRAPHIC INTERFEROMETRY: A USER'S GUIDE following: wiring responsibilities; purpose of the program; measure- D. GRIGGS OC11993 31 p ment of program effectiveness; results; and summary. CASI (Contract DE-AC04-94AL-85000) (DE94-003136; SAND-92-2909) Avail: CASI HC A03/MF A01 This manual describes the procedures and components necessary to produce a holographic interferogram of a flow field in the Sandia National Laboratories hypersonic wind tunnel. In contrast to classical N94-28705*# Naval Air Warfare Center, Indianapolis, IN. interferometry, holographic interferometry records the amplitude and ORGANIZED WIRING SYSTEMS phase distribution of a lightwave passing through the flow field at some THOMAS MEINER In NASA. Lewis Research Center, Second NASA

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Workshop on Wiring for Space Applications p 63-77 Jan. 1994 Original (AD-A275362; AFIT/GA/ENY-93D-2) Avail: CASI HC A06/MF A02 contains color illustrations This thesis designed, constructed, and tested a robotic arm for the Avail: CAS) HC A03/MF A03; 8 functional color pages Aerobot (Aerial Robot). The main purpose of the ARM is to enable the The topics are presented in viewgraph form and include the Aerobot to retrieve objects during an annual robotics competition. following: wiring systems, quality control, qualification and standard- Design of the ARM involved synthesizing the characteristics of simplic- ization, and maintenance costs. . CASI ity, weight strength, and size. The result was a three-degree-of- freedom manipulator that uses electric motors, cable linkages, and N94-28724*# Stanford Univ., CA. Joint Inst for Aeronautics and telescoping tubes to access a work space below the Aerobot Forward Acoustics. and inverse kinematics were investigated to enable automation of the A METHOD FOR THE MODELLING OF POROUS AND SOLID ARM. Data was collected from infrared sensors to validate the model. WINDTUNNELWALLSIN COMPUTATIONAL FLUIDDYNAMICS Manipulation of the ARM is presently under open loop control (joy stick) CODES which demonstrates the use of tele-robotics and its capabilities. THOMAS JOHN BEUTNER Dec. 1993 124p OTIC (Contract NCC2-55) (NASA-CR-195699; NAS1.26:195699; JIAA-TR-111) Avail: CASI HC N94-28948# National Aerospace Lab., Tokyo (Japan). A06/MF A02 MONTE CARLO SIMULATION OR NORMAL SHOCK WAVE. Porous wall wind tunnels have been used for several decades PART 2: VHS MODEL AND VSS MODEL [SHOGEKIHA NO and have proven effective in reducing wall interference effects in both MONTE KARURO SHIMYURESHON. 2: VHS MODERU TO VSS low speed and transonic testing. They allow for testing through Mach MODERU] 1, reduce blockage effects and reduce shock wave reflections in the test HIROAKIMATSUMOTO and KATSUHISA KOURA In its Proceedings section. Their usefulness in developing computational fluid dynamics of the 10th NAL Symposium on Aircraft Computational Aerodynamics (CFD) codes has been limited, however, by the difficulties associated p7-10 Dec. 1992 In JAPANESE with modelling the effect of a porous wall in CFD codes. Previous Avail: CASI HC A01/MF A03 approaches to modelling porous wall effects have depended either The validity of the Variable Soft Sphere (VSS) molecular model, upon a simplified linear boundary condition, which has proven inad- which is consistent with both the viscosity and diffusion coefficients of equate, or upon detailed measurements of the normal velocity near the any intermolecular potential, is investigated by the Monte Carlo simu- wall, which require extensive wind tunnel time. The current work was lation of the shock wave structure in binary gas mixtures of Maxwell initiated in an effort to find a simple, accurate method of modelling a molecules. Calculations are made by the null-collision direct-simulation porous wall boundary condition in CFD codes. The development of Monte Carlo method. The VSS model yields the same shock wave such a method would allow data from porous wall wind tunnels to be structures as Maxwell molecules even when the Variable Hard Sphere used more readily in validating CFD codes. This would be beneficial (VHS) molecular model reveals a different structure. The computation when transonic validations are desired, or when large models are used time and simplicity of the VSS model are confirmed to be almost the to achieve high Reynolds numbers in testing. A computational and same as those of the VHS model. The VSS model is, therefore, experimental study was undertaken to investigate a new method of preferable to the VHS model in practical use. Using the reliable values modelling solid and porous wall boundary conditions in CFD codes. The of the VSS parameters, the shock wave structure in He and Xe gas method utilized experimental measurements at the walls to develop a mixtures is investigated to compare with the measured density profiles. flow field solution based on the method of singularities. This flow field The density gradient and separation distance are in reasonable agree- solution was then imposed as a pressure boundary condition in a CFD ment with the experimental results. Author (NASDA) simulation of the internal flow field. The effectiveness of this method in describing the effect of porosity changes on the wall was investigated. N94-28949* National Aerospace Lab., Tokyo (Japan). Aerodynam- Also, the effectiveness of this method when only sparse experimental ics Div. measurements were available has been investigated. The current work VARIABLE SOFT SPHERE MOLECULAR MODEL IN THE demonstrated this approach for low speed flows and compared the MONTE CARLO SIMULATION OF AIR SPECIES [KUKIBUNSHI results with experimental data obtained from a heavily instrumented NO MONTE KARURO SHIMYURESHON NIOKERU VSS BUNSHI variable porosity test section. The approach developed was simple, MODERU] computationally inexpensive, and did not require extensive or intrusive KATSUHISA KOURA, HIROAKI MATSUMOTO, and MIKINARI measurements of the boundary conditions during the wind tunnel test TAKAHIRA In its Proceedings of the 10th NAL Symposium on Aircraft It may be applied to both solid and porous wall wind tunnel tests. Computational Aerodynamics p 11-15 Dec. 1992 In JAPANESE Author Avail: CASI HC A01/MF A03 The Variable Soft Sphere (VSS) molecular model is developed so N94-28815*# Pratt and Whitney Aircraft, East Hartford, CT. that both the viscosity and diffusion coefficients are consistent with THERMAL/STRUCTURAL TAILORING OF ENGINE BLADES those for any intermolecular potential. The values of the VSS cross- (T/SEAEBL). THEORETICAL MANUAL Final Report section parameters are listed for air species together with the viscosity K. W. BROWN and W. B. CLEVENGER Mar. 1994 40 p coefficients, which may be required in the evaluation of the Knudsen (Contract NAS3-22525; RTOP 505-63-5B) number. The VSS model is applied to the 'Rarefied Gas Numerical Wind (NASA-CR-194462; E-8495; NAS 1.26:194462) Avail: CASI HC A03/ Tunnel (RGNWT)1 and some results obtained using the RGNWT are MFA01 presented for the flowfield around the H-2 Orbiting Plane (HOPE). The Thermal/Structural Tailoring of Engine Blades (T/STAEBL) Author (NASDA) system is a family of computer programs executed by a control program. The T/STAEBL system performs design optimizations of N94-2895W National Aerospace Lab.. Amsterdam (Netherlands). cooled, hollow turbine blades and vanes. This manual describes the T/ ENGRID: A GRAPHICAL INTERACTIVE CODE FOR THE STAEBL data block structure and system organization. The approxi- COMPUTATION OF STRUCTURED GRIDS FOR BLOCKED mate analysis and optimization modules are detailed, and a FLOW DOMAINS validation test case is provided. Author S. P. SPEKREUSE In its Proceedings of the 10th NAL Symposium on Aircraft Computational Aerodynamics p 51 -56 Dec. 1992 Prepared N94-28894* Air Force Inst of Tech., Wright-Patterson AFB, OH. in cooperation with Alenia, Rome, Italy Sponsored by Netherlands School of Engineering. Agency for Aerospace Programs, Delft, Netherlands DESIGN AND CONSTRUCTION OF THE AEROBOT ROBOTIC Avail: CASI HC A02/MF A03 MANIPULATOR (ARM) M.S. Thesis The underlying idea of the widely used and accepted multiblock WILLIAM L. COCHRAN Dec. 1993 118 p approach for flow analysis is to subdivide a geometrical complex flow

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domain region into several smaller, more manageable regions, referred Avail: CASI HC A02/MF A03 to as blocks. Typically there are several individual blocks in a given flow A new approach to compute external viscous flows around three domain, each block having three computational coordinates. In the dimensional configurations is proposed. A prismatic grid is used where present approach the grid generation process is divided into two sub- the three dimensional surface is covered by triangles similar to the processes: (1) block decomposition, i.e., the creation of blocked flow unstructured grid. The direction away from the body surface is struc- domains; and (2) grid generation, i.e., the computation of structured tured so as to achieve efficient and accurate computations for high grids in the blocks. The ENQRID code is a general purpose multi-block Reynolds number viscous flows. The prismatic grid is generated by a grid generation code for the computation of Euler or Navier-Stokes newly developed marching-type procedure in which grid spacings are types of grids in flow domains which are already subdivided into blocks. controlled by a variational method. The capability of the method is The two required input files for ENGRID are a topology and a geometry demonstrated by applying it to a viscous flow computation around a file. The topology file defines the topology of a multi-block flow domain. complete aircraft configuration. Author (NASDA) The topology of a blocked flow domain describes how the blocks are connected to each other. The geometry file contains the geometrical information of a multi-block flow domain. The file contains the geometri- N94-2898W Tokyo Inst. of Tech. (Japan). Dept of Energy Sciences. cal definition of all vertices, all non-default elementary edges, and all TRANSONIC EXPANDING FLOW THROUGH AXIALLY non-default elementary faces. Author (NASDA) SYMMETRIC ORIFICES [JIKU TAISHO ORIFISU O TORU SENONSOKU BOCHORYU] YUMINOBUIGARASHI and HISASHIMIKAMI In NAL, Proceedings N94-28964* Kawasaki Heavy Industries Ltd., Gifu (Japan). of the 10th NAL Symposium on Aircraft Computational Aerodynamics ROLE OF COMPUTATIONAL FLUID DYNAMICS IN p 215-220 Dec. 1992 In JAPANESE AERONAUTICAL ENGINEERING. PART 10: NUMERICAL Avail: CASI HC A02/MF A03 ANALYSIS OF FLOW AROUND 2-D MULTI-ELEMENT HLD This paper describes a method of finding the flow pattern of an [SEKKEI NICKERU SUCHI KAISEKI NO KATSUYO NITSUITE. axially symmetric transonic gas jet through a circular orifice. Numerical SONO 10: 2 JIGEN TAYOKUSO MAWARI NAGARE NO SUCHI solutions were obtained by hodograph transformation and the method KAISEKI] of characteristics. The contraction coefficient, velocity profiles and KOICHI EG AMI, EIJI SHIMA. KAN I CHI AMANO. and SHINGO centeriine Mach number distributions were calculated. The numerical NAKAMURA In NAL, Proceedings of the 10th NAL Symposium on results are found to agree with the experimental data by Sherman. Aircraft Computational Aerodynamics p 99-104 Dec. 1992 In Author (NASDA) JAPANESE Avail: CASI HC A02/MF A03 A 2-D Navier-Stokes analysis of flow around multi-element high lift devices was carried out In order to calculate the aerodynamic charac- N94-28986# National Aerospace Lab., Kakuda (Japan). teristics in a wide range of angle of attack, the q-omega 2-equations SIMILARITY BETWEEN TURBULENT FLOWS THROUGH turbulence model was used. Numerical results show ftowfields with CURVED PIPE AND ORTHOGONAL ROTATING PIPE [NUI large viscous wake region without flow separation on the top surface of NAGARE O TOMONAU KANNAI RANRYU NO SOJISEI] the flap at large angle of attack. In high Reynolds number cases, HIROSHIISHIGAKI In its Proceedings of the 10th NAL Symposium on numerical results of decrease in lift coefficient were computed. Aircraft Computational Aerodynamics p 221-224 Dec. 1992 In Author (NASDA) JAPANESE Avail: CASI HC A01/MF A03 The secondary flow due to Coriolis force takes place when viscous N94-28976# Kawasaki Heavy Industries Ltd., Tokyo (Japan). fluid flows through a straight pipe rotating about an axis perpendicular VERIFICATION OF A THREE-DIMENSIONAL VISCOUS FLOW to the pipe axis. This is analogous to the secondary flow due to ANALYSIS FOR A SINGLE STAGE COMPRESSOR [NS KAISEKI centrifugal force in the flow through a stationary curved pipe. The NIYORU TANDAN ASSHUKUKI YOKURETSU NAGARE NO quantitative similarities between the two flows are demonstrated for KENSHO] turbulent flow by the similarity arguments and computational study AKINORI MATSUOKA, KEISUKE HASHIMOTO. OSAMU NOZAKI, using kappa-epsilon turbulence model. It is demonstrated that the KAZUO KIKUCHI, MASAHIRO FUKUDA, and ATSUHIRO TAMURA mutual similarity between two flows is established for friction In NAL, Proceedings of the 10th NAL Symposium on Aircraft Compu- factors and flow patterns. Author (NASDA) tational Aerodynamics p 163-168 Dec. 1992 In JAPANESE Avail: CASI HC A02/MF A03 A transonic flowfield around rotor blades of a highly loaded single N94-29091 Aeronautical Research Labs., Melbourne (Australia). stage axial compressor was numerically analyzed by a three dimen- COLD EXPANSION AND INTERFERENCE FOR EXTENDING sional compressible Navier-Stokes equation code using Chakravarthy THE FATIGUE LIFE OF MULTI-LAYER METAL JOINTS and Osher type total variation diminishing (TVD) scheme. A stage J.M.FINNEY OCL1993 34 p Limited Reproducibility: More than 20% analysis which calculates both flowfields around inlet guide vane (IGV) of this document may be affected by microfiche quality and rotor blades simultaneously was earned out Comparing with (AD-A274982; ARL-RR-17; DODA-AR-008-369) Avail: CASI HC A03 design values and experimental data, computed results show slight The influences of both hole cold expansion and interference-fit difference quantitatively. But the numerical calculation simulates well fasteners for extending the fatigue life of multilayer aluminum alloy joint the pressure rise characteristics of the compressor and its flow pattern specimens under variable amplitude loading have been examined including strong shock surface. Author (NASDA) experimentally. Improvements in fatigue life were markedly dependent on the degree of load transfer in the specimen joint The cold expansion of fastener holes enhanced fatigue life in low load transfer joints but not N94-28979* Osaka Prefecture Univ., Sakai (Japan). Dept of Aero- in 100% load transfer joints. The use of interference-fit fasteners, nautical Engineering. especially at high degrees of interference, was an effective means of life THREE-DIMENSIONAL EXTERNAL FLOW COMPUTATIONS improvement irrespective of proportion of load transfer. Interfacial USING PRISMATIC GRID [PURIZUMU KOSHI NIYORU SAN JIG fretting limited the improvement in fatigue life of low load transfer joints EN GAIBURYU NO SUICHI KEISAN] to a factor of about six, and, although some fretting occurred in 100% KAZUHIRO NAKAHASHI In NAL, Proceedings of the 10th NAL load transfer joints, it was not determinative, and a 40-fold increase in Symposium on Aircraft Computational Aerodynamics p 181 -186 Dec. fatigue life was obtained with a combination of hole cold expansion and 1992 In JAPANESE interference-fit fastener. DTIC

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N94-29104** Sverdrup Technology, Inc., Brook Park, OH. TIME-RESOLVED MEASUREMENTS IN A THREE TURBOMACHINERY FORCED RESPONSE PREDICTION DIMENSIONAL MODEL COMBUSTOR SYSTEM (PREPS): USER'S MANUAL Final Report R. JECKEL and S. WITTIG In AGARD, Fuels and Combustion M. R. MOREL and D. V. MURTHY Mar. 1994 115p Technology for Advanced Aircraft Engines 15 p Sep. 1993 Sponsored (Contract NAS3-25266; NAG3-1669; RTOP 505-63-58; RTOP by Arbeitsgemeinschaft Hochtemperatur Gasturbine and BMFT 232-01-OB) Copyright Avail: CASI HC A03/MF A04 (NASA-CR-194465; E-8518; NAS1.26:194465) Avail: CASI HC A06/ Locally and time-resolved measurements of the velocity, tem- MFA02 perature, and species concentration in a three dimensional jet-stabi- The turbomachinery forced response prediction system (FREPS), lized combustor are presented: The combustor was developed at the version 1.2, is capable of predicting the aeroelastic behavior of axial- Institute for Thermal Turbomachinery, University of Karlsruhe, for flow turbomachinery blades. This document is meant to serve as a extended benchmark experiments. For the present investigation, the guide in the use of the FREPS code with specific emphasis on its use combustor was fired by propane. The profiles of the velocity, tempera- at NASA Lewis Research Center (LeRC). A detailed explanation of the ture, and species distribution were determined at seven planes along aeroelastic analysis and its development is beyond the scope of this the combustor axis. A comparison between the cold flow and the document and may be found in the references. FREPS has been reacting hot gas conditions is given. The time-resolved velocity and developed by the NASA LeRC Structural Dynamics Branch. The temperature measurements were performed by a two component LDA- manual is divided into three major parts: an introduction, the preparation system as well as specially designed and optimized thermocouple of input, and the procedure to execute FREPS. Part 1 includes a brief probes. The time-dependent analysis demonstrates that the velocity background on the necessity of FREPS, a description of the FREPS and turbulence and/or the temperature fluctuations are dramatically system, the steps needed to be taken before FREPS is executed, an increased under hot combusting conditions. Finally, the locally deter- example input file with instructions, presentation of the geometric mined species distributions are compared with the global concentra- conventions used, and the input/output files employed and produced by tions at the exit of the combustor providing a data base for numerical FREPS. Part 2 contains a detailed description of the command names tests. Author (revised) needed to create the primary input file that is required to execute the FREPS code. Also, Part 2 has an example data file to aid the user in creating their own input files. Part 3 explains the procedures required to execute the FREPS code on the Cray Y-MP, a computer system N94-29353** National Aeronautcs and Space Administration. Marshall available at the NASA LeRC. Derived from text Space Right Center, Huntsville, AL TUNED MASS DAMPER FOR INTEGRALLY BLADED TURBINE ROTOR Patent Application N94-29282* Deutsche Forschungs- und Versuchsanstalt fuer Luft- JOHN J. MARRA, inventor (to NASA) (Pratt and Whitney Aircraft, West und Raumfahrt, Cologne (Germany). Inst. for Propulsion Technology. Palm Beach, FL.) 12Oct1993 12 p INVESTIGATION OFTHE TWO-PHASE FLOW IN A RESEARCH (NASA-CASE-MFS-28697-1; NAS 1.71:MFS-28697-1; US-PATENT- COMBUSTOR UNDER REACTING AND NON-REACTING APPL-SN-134443) Avail: CASI HC A03/MF A01 CONDITIONS The invention is directed to a damper ring for damping the natural C. HASSA, A. DEICK, and H. EICKHOFF In AGARD, Fuels and vibration of the rotor blades of an integrally bladed rocket turbine rotor. Combustion Technology for Advanced Aircraft Engines 12 p Sep. 1993 The invention consists of an integral damper ring which is fixed to the Sponsored by TECFLAM underside of the rotor blade platform of a turbine rotor. The damper ring Copyright Avail: CASI HC A03/MF A04 includes integral supports which extend radially outwardly therefrom. The flow resulting from an airblast atomizer with prefilmer and The supports are located adjacent to the base portion and directly under corotating swirl was investigated in a cylindrical combustion chamber. each blade of the rotor. Vibration damping is accomplished by action of Gas and droplet velocities were measured by a phase Doppler an- tuned mass damper beams attached at each end to the supports. emometer and species and gas temperature by gas sampling probes These beams vibrate at a predetermined frequency during operation. respectively, thermoelements at atmospheric conditions and without The vibration of the beams enforce a local node of zero vibratory fuel and air preheat Because of interference with the liquid phase, the amplitude at the interface between the supports and the beam. The species measurements were restricted to a minimum distance of 40 vibration of the beams create forces upon the supports which forces are mm from the atomizer lip. The temperature measurements showed the transmitted through the rotor blade mounting platform to the base of dominating influence of the external redrculation zone on flame stabi- each rotor blade. When these forces attain a predetermined design lization for the investigated nozzle configuration with a small expansion frequency and magnitude and are directed to the base of the rotor angle of the swirling flow. The species concentration fields exhibit blades, vibration of the rotor blades is effectively counteracted. homogeneous radial profiles at an axial distance of 100 mm behind the NASA atomizer, although droplets are observed up to 140 mm. Integrating the measured liquid volume flux density profiles, it was found that the fuel flux at 45 mm behind the atomizer had diminished to 14 percent of the maximum measured value. The axial profile of the liquid flux weighted N94-29448*# National Aeronautics and Space Administration. Lyndon Sauter mean diameter is almost linearly increasing from 22 to 31 B. Johnson Space Center, Houston, TX. micrometers. Systematic experimental errors and losses of the system LANDING GEAR ENERGY ABSORPTION SYSTEM Patent sensitivity, which enter the results partly with opposite signs, have an Application influence on the measured flux densities and moments of the particle CHRISTOPHER P. HANSEN, inventor (to NASA) 1 Dec. 1993 size distribution. The measurement of individual flux density profiles 17 p was reproducible to within 45 percent A comparison between the gas (NASA-CASE-MSC-22277-1; NAS 1.71:MSC-22277-1; US-PATENT- flow in the nearfield of the atomizer under reacting and nonreacting APPL-SN-159606) Avail: CASI HC A03/MF A01 conditions showed a partial suppression of the expansion of the velocity A landing pad system is described for absorbing horizontal and profiles by the hot comer vortex. Together with the combustion induced vertical impact forces upon engagement with a landing surface where axial acceleration, the thus effected reduction of the effective swirl tircumferentiaUy arranged landing struts respectively have a clevis number leads to the breakdown of the recirculation at 29 mm. which receives a slidable rod member and where the upper portion of Author (revised) a slidable rod member is coupled to the clevis by friction washers which are force fit onto the rod member to provide for controlled constant force N94-29283# Karlsruhe Univ. (Germany). Lehrstuhl und Inst fuer energy absorption when the rod member moves relative to the clevis. Thermische Stroemungsmaschinen. The lower end of the friction rod is pivotally attached by a ball and socket

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to a support plate where the support plate is arranged to slide in a will permit a greater reliability of maintenance control. The diagnostic transverse direction relative to a housing which contains an energy performed with this tool would be rapid;: the control of 30,000 rivets on absorption material for absorb-ing energy in a transverse direction. the Airbus fuselage would take approximately 45 minutes. ESA NASA

N94-29534 Cincinnati Univ., OH. N94-29456# Aerospatiale, Cannes (France). Espace et Defense. RNS OPTIMIZATION PROCEDURE FOR THREE-DIMENSIONAL THEORETICAL AND EXPERIMENTAL STUDY OF A COMPOSITE VELOCITY MULTI-BLOCK APPLICATIONS Ph.D. CYLINDRICAL MICROSTRIP ANTENNA Thesis M. MONACO (Nice Univ., France.), G. GHIO (Nice Univ., France.), E. HUSSAIN MOHAMED HASA ALMAHROOS 1992 215 p CAMBIAGGIO (Nice Univ.. France.), J. P. BOISSET, M. SAUVAN, and Avail: Univ. Microfilms Order No. DA9313812 B. BURALLI 1993 5p RNS analysis of the composite velocity formulation has been (REPT-932-440-109; ETN-94-95479) Avail: CASI HC A01/MF A01 applied for three dimensional flows. A consistent coupled strongly A low profile microstrip belt antenna concept was developed and implicit procedure has been used to solve the coupled system of tested. The antenna radiation pattern was optimized. The antenna is equations in general nonorthogonal coordinate system. Different forms suitable for optimal air or space based reception of radio localized of contravariant momentum balances have been examined. A muttiblock signals. The antenna, along with a 3.78 bandwidth, offers ripple within analogy and optimization strategies have been implemented and are W- 2 dB and 98 percent coverage probability. The system was presented. Three dimensional subsonic and transonic, viscous-inviscid conceived to receive the global positioning system radio signals interacting flows over afterbody configurations have been evaluated. beamed from the navigation system by time and range satellite Laminar and turbulent flow solutions, with and without regions of network. The resulting microstrip belt antenna is a low cost, low profile, retirculation and shock wave boundary layer interaction, are pre- low weight and easy integration antenna concept ESA sented. Three dimensional flows over multiple body configurations are also presented. Dissert Abstr.

N94-29460*# High Technology Corp., Hampton, VA. LONG-WAVELENGTH ASYMPTOTICS OF UNSTABLE N94-29552** Kentucky Univ., Lexington. CROSSFLOW MODES, INCLUDING THE EFFECT OF SURFACE EXPERIMENTAL VALIDATION OF FINITE ELEMENT AND CURVATURE BOUNDARY ELEMENT METHODS FOR PREDICTING MEELAN CHOUDHARI Apr. 1994 43 p STRUCTURAL VIBRATION AND RADIATED NOISE Final (Contract NAS1-19299; RTOP 538-05-15-03) Report (NASA-CR-4579; NAS 1.26:4579) Avail: CASI HC A03/MF A01 A. F. SEYBERT, T. W. WU, and X. F. WU Jan. 1994 94 p Original Stationary vortex instabilities with wavelengths significantly larger contains color illustrations than the thickness of the underlying three-dimensional boundary layer (Contract NAG3-912; DAPROJ. 1L1-62211-A-47A; RTOP 505-62-10) are studied with asymptotic methods. The long-wavelength Rayleigh (NASA-CR-4561; ARL-CR-109; E-8264; NAS 1.26:4561) Avail: CASI modes are locally neutral and are aligned with the direction of the local HC A05/MF A01; 3 functional color pages inviscid streamline. For a spanwise wave number Beta much less than This research report is presented in three parts. In the first part, 1, the spatial growth rate of these vortices is O(Beta(exp 3/2)). When acoustical analyses were performed on modes of vibration of the Beta becomes O(R(exp -1/7)), the viscous correction associated with housing of a transmission of a gear test rig developed by NASA. The a thin sublayer near the surface modifies the inviscid growth rate to the modes of vibration of the transmission housing were measured using leading order. As Beta is further decreased through this regime, viscous experimental modal analysis. The boundary element method (BEM) effects assume greater significance and dominate the growth-rate was used to calculate the sound pressure and sound intensity on the behavior. The spatial growth rate becomes comparable to the real part surface of the housing and the radiation efficiency of each mode. The of the wave number when Beta = O(R(exp -1/4)). At this stage, the radiation efficiency of each of the transmission housing modes was disturbance structure becomes fully viscous-inviscid interactive and is then compared to theoretical results tor a finite baffled plate. In the described by the triple-deck theory. For even smaller values of Beta, the second part, analytical and experimental validation of methods to vortex modes become nearly neutral again and align themselves with predict structural vibration and radiated noise are presented. A rectan- the direction of the wall-shear stress. Thus, the study explains the gular box excited by a mechanical shaker was used as a vibrating progression of the crossflow-vortex structure from the inflectional upper structure. Combined finite element method (FEM) and boundary ele- branch mode to nearly neutral long-wavelength modes that are aligned ment method (BEM) models of the apparatus were used to predict the with the wall-shear direction. Author noise level radiated from the box. The FEM was used to predict the vibration, while the BEM was used to predict the sound intensity and total radiated sound power using surface vibration as the input data, N94-29474* Aerospatiale, Suresnes (France). Centre Commun de vibration predicted by the FEM model was validated by experimental Recherches Louis-Bleriot modal analysis; noise predicted by the BEM was validated by measure- AUTOMATION OF THE NOT DIAGNOSTIC USING NEURAL ments of sound intensity. Three types of results are presented tor the NETS. APPLICATION: INSPECTION OF AIRBUS total radiated sound power sound power predicted by the BEM model LONGITUDINAL JOINTS DURING MAINTENANCE using vibration data measured on the surface of the box; sound power [AUTOMATISATION DU DIAGNOSTIC EN CND PAR predicted by the FEM/BEM model; and sound power measured by an L'UTILISATION DE RESEAUX NEURONAUX. APPLICATION: acoustic intensity scan. In the third part, the structure used in part two INSPECTION EN MAINTENANCE DES LIAISONS was modified. A rib was attached to the top plate of the structure. The LONGITUDINALES AIRBUS] FEM and BEM were then used to predict structural vibration and CHRISTINE BROUSSET and GILLES BAUDRILLARD1993 11 p In radiated noise respectively. The predicted vibration and radiated noise FRENCH were then validated through experimentation. Author (revised) (REPT-932-600-104; ETN-94-95483) Avail: CASI HC A03/MF A01 A neural network tool was developed to automate the Non Destructive Testing (NOT) of aeronautical structures carried out with N94-29566* Shape Technical Center, The Hague (Netherlands). the SIAM system. The SIAM system is used to reveal splits in ACCS SURVEILLANCE EXPLORATORY PROTOTYPE (ASEP) longitudinal metal joints on the Airbus fuselage. The integration of the K. GAEBLER In AGARD, Machine Intelligence in Air Traffic Manage- neural net tool within the SIAM control system is considered possible. ment 18 p Oct 1993 The automatic diagnostic should provide the operator with an aid which Copyright Avail: CASI HC A03/MF A04

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The increasing sophistication of surveillance systems, both civil- Models are presented which represent both microscopic and macro- ian and military, has generated a great deal of interest in techniques of scopic processes. At the microscopic level, the N-state approximation mufti-target tracking and sensor integration. To help SHAPE and the of Rapp and coworkers is extended to compute velocity dependent NATO Air Command and Control System (ACCS) Management Agency inelastic and dissociative transition probabilities for atom-diatom and (NACMA) to specify and implement the ACCS surveillance subsystem, diatom-diatom collisions. Nitrogen atoms and diatoms are considered in particular in the areas of data fusion and identification, the SHAPE in this part of the study and an enharmonic model of the diatom is used. Technical Center (STC) is currently developing an ACCS Surveillance Dissociated product states are modeled by dividing the continuum into Exploratory Prototype (ASEP) as an element of its new integrated discrete states. The acceleration scheme of Secrest is applied to the N- testbed. The purpose of the ASEP is to demonstrate the feasibility and state method and preliminary calculations on the simpler H2-He operational benefits of future air picture generation systems. The collision system show order of magnitude increases in efficiency. The significant difference between this advanced system and currently N-state approximation is seen to be more accurate than currently used available systems is that ASEP will provide better tracking continuity, first order theories. At the macroscopic level, master equation simula- more accurate estimates of track positions, velocity, acceleration, and tions are performed. A new model for the state-specific dissociative rate additional information on targets. The provision of this information on air coefficient is presented and validated. The present results are com- targets is also of great importance for civil ATC systems, especially in pared to published dissociative cross sections for the para-H2-Ar view of growing requirements for ATC planning, conflict alert and collision system as computed by the quasiclassical trajectory (QCT) conflict resolution. The use of multiple sensors and sources requires the technique. In order to make the comparison consistent, all inelastic rate fusion of different types of data, including sensor reports containing coefficients used in the master equation are scaled to published measured attributes such as the target type and other target features. inelastic QCT results. The present model is seen to reproduce the more Since advanced fusion algorithms are using kinematic data as well as sophisticated dissociative QCT cross sections to within a factor of two attribute data for the identification process, the majority of all air targets in general. The master equation results also indicate that the most can be identified automatically. This paper gives an overview of the significant contribution to the average dissociative rate coefficient following components that are implemented in the ACCS Surveillance comes from the low-to-mid vibrational levels. Similar results have been Exploratory Prototype at STC: scenario generation and sensor simula- obtained by other researchers from more expensive detailed computation; real-time multi-sensor tracking; real-time radar data integration; tions. Dissert Abstr. external track and flight plan data integration; and air picture presentation on a Surveillance Workstation using new human-computer interface (HCI) techniques. Derived from text N94-29726* National Aeronautics and SpaceAdministration. Goddard Space Right Center, Greenbeft, MO. SIX-DEGREE-OF-FREEDOM PARALLEL MINIMANIPULATOR N94-29647** National Aeronautics and Space Administration. WITH THREE INEXTENSIBLE LIMBS Patent Langley Research Center, Hampton, VA. FARHAD TAHMASEBI, inventor (to NASA) and LUNG-WEN TSAI, MINIATURE LINEAR-TO-ROTARY MOTION ACTUATOR inventor (to NASA) 18 Jan. 1994 13 p Filed 20 Jut. 1992 MICHAEL R. SOROKACH, JR. In NASA. Ames Research Center, The (NASA-CASE-GSC-13485-1; US-PATENT-5,279,176; US-PATENT- 27th Aerospace Mechanisms Symposium p 299-314 May 1993 APPL-SN-915567; US-PATENT-CLASS-74-479B; US-PATENT- Avail: CASI HC A03/MF A03 CLASS-74-479PF; US-PATENT-CLASS-901-14; US-PATENT-CLASS- A miniature hydraulic actuation system capable of converting 901-19; INT-PATENT-CLASS-G05G-11/00; INT-PATENT-CLASS- linear actuator motion to control surface rotary motion has been B25J-11/00) Avail: US Patent and Trademark Office designed for application to active controls on dynamic wind tunnel A Six-Degree-of-Freedom Parallel-Manipulator having three models. Due to space constraints and the torque requirements of an inextensible limbs for manipulating a platform is described. The three oscillating control surface at frequencies up to 50 Hertz, a new actuation inextensible limbs are attached via universal joints to the platform at system was developed to meet research objectives. This new actuation non-collinear points. Each of the inextensible limbs is also attached via system was designed and developed to overcome the output torque universal joints to a two-degree-of-freedom parallel driver such as a limitations and fluid loss/sealing difficulties associated with an existing five-bar linkage, a pantograph, or a bidirectional linear stepper motor. vane type actuator. Static control surface deflections and dynamic The drivers move the lower ends of the limbs parallel to a fixed base and control surface oscillations through a given angle are provided by the thereby provide manipulation of the platform. The actuators are mounted actuation system. The actuator design has been incorporated into a on the fixed base without using any power transmission devices such transonic flutter model with an active trailing edge flap and two active as gears or belts. spoilers. The model is scheduled for testing in the LaRC 16 Foot Official Gazette of the U.S. Patent and Trademark Office Transonic Dynamics Tunnel during Summer 1993. This paper will discuss the actuation system, its design, development difficulties, test results, and application to aerospace vehicles. Author N94-29740* National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. METHOD FOR CANCELLING EXPANSION WAVES IN A WAVE N94-29675 Texas Univ., Austin. ROTOR Patent MODELS FOR VIBRATION-DISSOCIATION COUPLING IN DANIEL E. PAXSON, inventor (to NASA) 29 Mar. 199410 p Red 6 HIGH-TEMPERATURE GASES Ph.D. Thesis Jul. 1993 Division of US-Patent-Appl-SN-889003, filed 26 May 1992 DAVID ALBERT GONZALES 1993 199 p (NASA-CASE-LEW-15218-2; US-PATENT-5,297.384; US-PATENT- Avail: Univ. Microfilms Order No. DA9323408 APPL-SN-086581; US-PATENT-APPL-SN-889003; US-PATENT- Nonequilibrium conditions are expected in the flowfields about CLASS-60-39.02; INT-PATENT-CLASS-F02C-3/02) Avail: US Patent high speed, high altitude research vehicles. These conditions may be and Trademark Office found in regions of rapid compression and rapid expansion in the A wave rotor system includes a wave rotor coupled to first and flowfield. The impact of nonequilibrium effects on such quantities as second end plates. Special ports are provided, one in each of the first heat transfer rate and pressure distribution is not dear. This is due in and second end plates, to cancel expansion waves generated by the part to the lack of reliable theoretical models with which to predict release of working fluid from the wave rotor. One of the expansion nonequilibrium processes in high temperature gases. Accurate compu- waves is reflected in the wave rotor from a reflecting portion, and tational chemistry techniques cannot be used for engineering analyses provided to the special port in the second end plate. Fluid present at the because they are prohibitively expensive. The focus of this research is special port in the second end plate has a stagnation pressure and on the development of engineering models that suitably reproduce the mass flow which is substantially the same as that of the cells of the wave elaborate computational chemistry results with far greater efficiency. rotor communicating with such special port. This allows for cancellation

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of the expansion wave generated by the release of working fluid from enhance ENSAERO in both algorithm and geometric capabilities. the wave rotor. The special port in the second end plate has a first end During the last five years, the algorithms of the code have been corresponding substantially to the head of the expansion wave, and a enhanced extensively by using high-resolution upwind algorithms and second end corresponding substantially to the tail of the expansion efficient implicit solvers. The zonal capability of the code has been wave. Also, the special port is configured to continually change along extended from a one-to-one grid interface to a mismatching unsteady the circumference of the second end plate to affect expansion wave zonal interface. The geometric capability of the code has been ex- cancellation. An expansion wave generated by a second release of tended from a single oscillating wing case to a full-span wing-body working fluid from the wave rotor is cancelled in a similar manner to that configuration with oscillating control surfaces. Each time a new capa- described above using a special port in the first end plate. Preferably the bility was added, a proper validation case was simulated, and the cycle of operation of the wave rotor system is designed so that the capability of the code was demonstrated. Author (revised) stagnation pressure and mass flow of the fluid present at the special ports is the same so that the special ports may be connected by a common duct Official Gazette of the U.S. Patent and Trademark Office 13 GEOSCIENCES N94-29839 Missouri Univ., Rolla LIQUID ATOMIZATION IN SUPERSONIC FLOWS Ph.D. Thesis Includes geosciences (general); earth resources; energy production AZZEDINE MISSOUM 1993 138 p and conversion; environment pollution; geophysics; meteorology and Avail: Univ. Microfilms Order No. DA9326598 climatology; and oceanography. An experimental investigation of the atomization of a round liquid jet by coaxial, costream injection into a supersonic, Mach 1.5 air flow is reported. Extensive flow visualization was conducted using schlieren/ N94-28600** Washington State Univ., Pullman. Dept. of Civil and shadowgraph, flash photography, and short duration (ns) laser imag- Environmental Engineering. ing. The finer details of the jet were revealed when viewed under high THE RADIOCARBON HYDROXYL TECHNIQUE Abstract Only magnification with the help of a microscope. The liquid and air pressures MALCOLM J. CAMPBELL and JOHN C. SHEPPARD In SRI Interna- were varied individually. Photographic evidence indicates the presence tional Corp., Local Measurement of TroposphericHO(x) 1 p Feb. 1994 of three regions within the liquid jet a primary region enclosed by the Avail: CASI HC A01/MF A01 first shock cell where the primary breakup occurs, a secondary region The Radiocarbon Technique depends upon measuring the rate of in which the jet is totally broken because of its interaction with the oxidation of CO in an essentially unperturbed sample of air. The supersonic wave structure, and a third, subsonic region further down- airborne technique is slightly different. Hydroxyl concentrations can be stream. It was found that the breakup mechanism of liquid jets in calculated directly; peroxyl concentrations can be obtained by supersonic airstreams is quite complex. The breakup seems to be NO doping. Author initiated by the growth of the turbulent structure on the liquid surface and the subsequent detachment of the three-dimensional structure as fine droplets by the intense shear at the liquid-gas interface. This seems to N94-29247# Deutsche Forschungsanstalt fuer Uift- und Raumfahrt, confirm the boundary layer stripping mechanism. The liquid jet expands Oberpfaffenhofen (Germany). Inst. fuer Physik der Atmosphaere. into a bubble like formation as it interacts with the first set of waves. ON THE EFFECT OF EMISSIONS FROM AIRCRAFT ENGINES Higher liquid injection pressures resulted in higher initial spray angles. ON THE STATE OF THE ATMOSPHERE The liquid jet displayed a geometry strongly dependent on the pressure U. SCHUMANN In AGARD, Fuels and Combustion Technology for distribution resulting from the wave structure present in the supersonic Advanced Aircraft Engines 19 p Sep. 1993 Sponsored by DFG; BMFT; jet Droplet size and velocity distributions were measured by the P/DPA and Commision of the European Communities (Phase/Doppler Particle Analyzer) system. The Sauter Mean Diameter Copyright Avail: CASI HC A03/MF A04 (SMD) was measured at several axial and radial locations at various Emissions from aircraft engines include carbon dioxide, water liquid and air pressures. The SMD shows a decrease with increase in vapor, nitrogen oxides, sulphur components, and various other gases both the air-to-liquid mass flow ratio and the Weber number. The drop and particles. Such emissions from high-flying global civil subsonic size decreased towards the outer edges of the jet The results lead one aircraft contribute to anthropogenic climate changes by increase of to conclude that the coaxial, coflowing configuration is very attractive for ozone and cloudiness in the upper troposphere, and by enhanced atomizing scramjet liquid fuels. Dissert Abstr. greenhouse effect The absolute emissions by air traffic are small (a few percent of total) in comparison to surface emissions. However, the greenhouse effect of emitted water and of nitrogen oxides at cruise N94-29942*# MCAT Inst, San Jose, CA. altitude is large in comparison to that of the same emissions near the ALGORITHM AND CODE DEVELOPMENT FOR UNSTEADY earth's surface because of relatively large residence times at flight THREE-DIMENSIONAL NAVIER-STOKES EQUATIONS altitudes, low background concentrations, low temperature, and large SHIGERU OBAYASHI Apr. 1994 6p radiative efficiency. At present it appears that the emissions of nitrogen (Contract NCC2-605) oxides have changed the background concentration in the upper (NASA-CR-195774; MAS 1.26:195774; MCAT-94-002) Avail: CASI troposphere in between 40 deg N and 60 deg N by 100 percent, causing HC A02/MF A01 an increase of ozone by about 20 percent Regionally the observed Aeroelastic tests require extensive cost and risk. An aeroelastic annual mean change in cloudiness is of order 0.4 percent The resultant wind-tunnel experiment is an order of magnitude more expensive than greenhouse effect of changes in ozone and thin cirrus cloud cover a parallel experiment involving only aerodynamics. By complementing causes a climatic surface temperature change of the order 0.01 to 0.1 the wind-tunnel experiments with numerical simulations, the overall K. These temperature changes are small in comparison to the natural cost of the development of aircraft can be considerably reduced. In variability. Recent research indicates that the emissions at cruise order to accurately compute aeroelastic phenomenon it is necessary to altitude may increase the amount of stratospheric aerosols and polar solve the unsteady Euler/Navier-Stokes equations simultaneously with stratospheric clouds and thereby may have an impact on the atmo- the structural equations of motion. These equations accurately de- sphere environment to a yet unknown degree. Air traffic is increasing scribe the flow phenomena for aeroelastic applications. At ARC a code, by about five to six percent per yean fuel consumption grows by about ENSAERO, is being developed for computing the unsteady aerody- three percent per year. Moreover, the climatic changes due to air traffic namics and aeroelasticity of aircraft, and it solves the Euler/Navier- enhance other environmental problems originating, e.g., from anthro- Stokes equations. The purpose of this cooperative agreement was to pogenic carbon dioxide or methane emissions. Hence, air traffic

414 MATHEMATICAL AND COMPUTER SCIENCES 15

induced emissions are of growing importance. This calls for the MASAKOTSUCHIYA, KAZUYO SUEMATSU, SHUNJl SUEMATSU, development of efficient and low-emission propulsion systems and HARUO HATAMA, HIROSHI MORISHIGE, YASUSHI YAMAGUCHI, other means to reduce the emissions. This paper surveys the state of and YUKIHIRO KARUBE In its Proceedings of the 10th NAL knowledge and describes several items of results from recent and Symposium on Aircraft Computational Aerodynamics p 259-264 Dec. ongoing research. Author (revised) 1992 In JAPANESE Avail: CASI HC A02/MF A03 Numerical Wind Tunnel (NWT) is a CFD (Computational Fluid 15 Dynamics)-oriented parallel computer system with distributed memory, and the operating system of NWT is UNIX. In order to provide users MATHEMATICAL AND COMPUTER SCIENCES much convenience and to maintain efficient functions of management on 'MSP' operating system, it is preferable to use NWT with user Includes mathematical and computer sciences (general); computer interface of MSP which is the operating system up to this time. In this operations and hardware; computer programming and software; com- paper the procedure how to construct user interface of MSP for NWT puter systems; cybernetics; numerical analysis; statistics and probabil- is presented. Author (NASDA) ity; systems analysis; and theoretical mathematics. N94-29315* Advisory Group for Aerospace Research and Develop- N94-28947# National Aerospace Lab., Amsterdam (Netherlands). ment, Neuilly-Sur-Seine (France). Avionics Panel. ENGINEERING OF SYSTEMS FOR APPLICATION OF AEROSPACE SOFTWARE ENGINEERING FOR ADVANCED SCIENTIFIC COMPUTING IN INDUSTRY SYSTEMS ARCHITECTURES [L'INGENIERIE DES W. LOEVE In NAL, Proceedings of the 10th NAL Symposium on LOGICIELS POUR LES ARCHITECTURES DES SYSTEMES Aircraft Computational Aerodynamics p 1-5 Dec. 1992 AEROSPATIAUX] Avail: CASI HC A01/MF A03 Nov. 1993 333 p In ENGLISH and FRENCH Symposium held in Paris, Mathematics software is of growing importance for computer France, 10-13 May 1993 simulation in industrial computer aided engineering. To be applicable in (AGARD-CP-545; ISBN-92-835-0725-8) Copyright Avail: CASI HC industry, the mathematics software and supporting software must be A15/MF A03 structured in such a way that functions and performance can be maintained easily. In the present paper, a method is described for During the past decade, many avionics functions which have development of mathematics software in such a way that this traditionally been accomplished with analogue hardware technology requirement can be met Author (NASDA) are now being accomplished by software residing in digital computers. The purpose of this Symposium was to bring together military aero- N94-28980# Kyoto Univ., Sakyoku (Japan). space software experts from all NATO countries to share the results of APPLICATION OF DIGITAL CONTROL THEORY TO ADAPTIVE their software research and development and virtually every aspect of GRID GENERATION [SAITEKI SEIGYO O MOCHIITA TEKIO software was considered with the following representing a partial set of KOSHI SEISEIHO] topics: Aerospace Electronics Software Specification, Software De- MAKOTO KOBAYAKAWA and EITARO YAMADA In NAL, Proceed- sign, Programming Practices and Techniques, Software Validation and ings of the 10th NAL Symposium on Aircraft Computational Aerody- Testing, Software Management and Software Environments. namics p 187-192 Dec. 1992 In JAPANESE Avail: CASI HC A02/MF A03 N94-29320# Dassault-Breguet Aviation, Saint Cloud (France). Div. New methods for adaptive grid generation through optimal regu- des Etudes Avancees. lator of digital control are presented. The performance index of linear FLIGHT COMMAND SOFTWARE DEVELOPMENT: RAFALE optimal regulator problem has a strong relation to the characteristics of STUDIES [LE DEVELOPPEMENT DES LOGICIELS DE adaptive grid generation. Paying attention to this point, one and two COMMANDES DE VOL, L'EXPERIENCE RAFALE] dimensional Poisson equations are transformed into the state-space D. BEURRIER, F. VERGNOL, and PH. BOURDAIS In AGARD. form. The numerical examples of NACA-0012 airfoil flow field and Aerospace Software Engineering for Advanced Systems Architectures supersonic flow around comers show strong clustering of grid lines at 13 p Nov. 1993 In FRENCH shock waves through these two kinds of adaptation. Author (NASDA) Copyright Avail: CASI HC A03/MF A03 After the introduction of the RAFALE'S Right Command System N94-28992* National Aerospace Lab., Tokyo (Japan). (Systeme de Commande de Vol: SCV). DASSAULT Aviation presents PERFORMANCE EVALUATION OFTHE NWT WITH PARALLEL its studies on software applications to critical safety systems, with an FORTRAN [NWT HEIRETSU FORTRAN Nl MOTODUKU emphasis on the following: (1) The methodology used in the develop- HEIRETSU HYOKA] ment It includes a phase for the formalization of the software specifi- TAKASHINAKAMURA. MASAHIROYOSHIDA, MASAHIROFUKUDA, cations, its objective being to improve on the dialogue between two SHUICHI NAKAMURA, TAKEOMURASE,andTATSUYAMATSUZAKI distinct entities: the automaticians on one hand and the computer In its Proceedings of the 10th NAL Symposium on Aircraft Computa- programmers on the other hand. (2) The key support systems used in tional Aerodynamics p 253-258 Dec. 1992 In JAPANESE Prepared this methodology: GISELE: specification tool using a formal language in cooperation with Fujitsu Ltd., Tokyo, Japan whose testing and automatic prototype potential guarantee a descrip- Avail: CASI HC A02/MF A03 tive quality, and VALIRAF: validation tool which automatically com- The Numerical Wind Tunnel (NWT) is under research and devel- pares the results of the system to the models obtained during the opment by NAL-Fujitsu joint activity. It is a parallel computer system of studies on specifications. It manages the testing process and evaluates distributed memory architecture composed of vector processors. In this its level of reliability. An assessment of the results and a presentation paper, the performance on the desk of two application programs that of future programs of study are also included. Author (revised) were parallelized by current parallel language processor is shown. The performance using network simulator and evaluation software VTAP' N94-29325* Electronic System G.m.b.H., Munich (Germany). which is based on VP400 performance analysis is evaluated. The Elektroniksystem-und Logistik. estimation that the present machine performs CFD (Computational EXPERIENCES WITH THE HOOD DESIGN METHOD ON Fluid Dynamics) simulation about 100 times faster than Fujitsu VP400 AVIONICS SOFTWARE DEVELOPMENT is presented. Author (NASDA) W. MALA and E. GRAND! In AGARD, Aerospace Software Engineer- ing for Advanced Systems Architectures 12 p Nov. 1993 N94-28993* National Aerospace Lab., Tokyo (Japan). Copyright Avail: CASI HC A03/MF A03 A METHOD OF USER INTERFACE FOR NWT [NWT NO YUZA HOOD represents one of the most interesting approaches of the INTAFEISU JITSUGEN HOSHIKI] recent years to support an object oriented SW design for large

415 15 MATHEMATICAL AND COMPUTER SCIENCES

embedded systems written in Ada. This paper reports about experi- This paper discusses the impact DOD development standards ences gained by the authors in the context of a current large European and Integrated Product Teams have had on influencing F-22 cockpil avionic development project, where the Ada SW design has been Controls and Displays software test and evaluation. Authoi performed using HOOD Version 3.0. A simplified example describes the approach taken in the project for SW architectural design. A critical evaluation of the HOOD method follows, where advantages and N94-29344# British Aerospace Defence Ltd., Preston (England). disadvantages are discussed and some hints are given to overcome Military Aircraft Div. some identified weak areas. The paper concludes with the recognition SDE'S FOR THE YEAR 2000 AND BEYOND: AN EF of HOOD as a promising approach and encourages further discussion PERSPECTIVE to remove the weak areas. Derived from text D. J. GOODWIN In AGARD, Aerospace Software Engineering for Advanced Systems Architectures 8 p Nov. 1993 Copyright Avail: CASI HC A02/MF A03 The process of selecting a software development environment for N94-29337* Wright Lab., Wright-Patterson AFB, OH. Avionics Lo- the embedded software of a large, complex military aircraft project can gistics Branch. be long and costly. The process adopted on the European Rghter TESTING OPERATIONAL FLIGHT PROGRAMS (OFPS) Aircraft (EFA) project by British Aerospace (BAe) is described, from the CHARLES P. SATTERTHWAITE In AGARD. Aerospace Software initial research and prototyping exercises performed in the seventies to Engineering for Advanced Systems Architectures 10 p Nov. 1993 the demonstration of the technology on the experimental aircraft project Copyright Avail: CASI HC A02/MF A03 and finally leading to the collaboration with the Eurofighter partner The ability to accurately test a system is a highly desirable feature companies (EPC's), building on European software experience to in the engineering design process. The ability to model your system's specify, procure, and release the EFA software development environ- environment and to exercise your system, in that environment, is also ment (EFA SDE). Issues arising within the EF forum that could influence highly desirable. Operational Flight Programs are the software pro- the development of SDE's for future military aircraft projects are grams of avionics embedded computer systems. Not only is it desirable described. Author (revised) to be able to test and model Operational Right Programs, it is essential. The consequences of not performing accurate Operational Right Program testing can be devastating. Some of these include premature N94-29727** National Aeronautics and Space Administration. weapons release, erroneous flight instrument displays, and complete Goddard Space Right Center, Greenbelt, MD. system failure. In order to test Operational Right Programs, there are SOFTWARE MANAGEMENT ENVIRONMENT (SME) several things one must know about the Operational Right Program, its CONCEPTS AND ARCHITECTURE, REVISION 1 weapons system host, its support environment and how to generate ROBERT HENDRICK (Computer Sciences Corp., Beltsville, MD.), and perform its test This paper will address these issues as it develops DAVID KISTLER (Computer Sciences Corp., Beltsville. MD.), and JON a strategy to test an Operational Right Program. Author (revised) VALETT Sep. 1992 84 p (NASA-CR-189293; NAS 1.26:189293; SEL-89-103-REV-1) Avail: CASI HC A05/MF A01 This document presents the concepts and architecture of the N94-29338# TA Consultancy Services Ltd., Famham (England). Software Management Environment (SME), developed for the Soft- INTEGRATED FORMAL VERIFICATION AND VALIDATION OF ware Engineering Branch of the Right Dynamic Division (FDD) of SAFETY CRITICAL SOFTWARE GSFC. The SME provides an integrated set of experience-based N. J. WARD In AGARD, Aerospace Software Engineering tor management tools that can assist software development managers in Advanced Systems Architectures 11 p Nov. 1993 managing and planning flight dynamics software development projects. Copyright Avail: CASI HC A03/MF A03 This document provides a high-level description of the types of informa- Embedded software providing the functionality for a flight vehicle tion required to implement such an automated management tool. self destruct system was judged to be safety critical and required the Author (revised) highest level of assurance in its correctness. In order to achieve this a program of independent verification and validation was initiated which involved the definition of a formal specification of the software combined with static analysis and dynamic testing. The formal specification, 16 written in an Object Oriented form of 2, was used to clarify the requirements and to provide a definition against which the code could PHYSICS be formally verified. A range of static analyses were performed culminating in Compliance analysis which effectively provided a proof of the Includes physics (general); acoustics; atomic and molecular physics; code against low level mathematical specifications that were refined nuclear and high-energy physics; optics; plasma physics; solid-state down from the Z specification. The dynamic test sets were chosen physics; and thermodynamics and statistical physics. partly from the requirements specification and party from the static analysis results so that complete path coverage through every module was achieved. The work revealed a number of errors within the code N94-29175# Swedish Inst. for Materials Testing, Boras. and its specifications, which were corrected. Through its rigor and the DETERMINATION OF SOUND POWER LEVELS OF AIR identification of errors, the analysis has given a very high degree of TERMINAL UNITS ACCORDING TO ISO 5135-NORDIC INTER- confidence in the correctness of the software. Author (revised) LABORATORY TESTS, NORDTEST PROJECT NO. 968-91 Technical Report No. 214 G. ANDRESEN and H. G. JONASSON 1993 46 p (PB94-137411; SP-RAPP-1993-43) Avail: CASI HC A03/MF A01 N94-29339# Air Force Systems Command, Wright-Patterson AFB, An inter-laboratory test program to determine the sound power OH. level of air terminal units was carried out The measurements were A DISCIPLINED APPROACH TO SOFTWARE TEST AND performed in accordance with ISO 5135. Four laboratories participated, EVALUATION each carrying out measurements on six test objects: two non-adjust- J. LEA GORDON In AGARD, Aerospace Software Engineering for able air terminal units, two adjustable air terminal units and two Advanced Systems Architectures 8 p Nov. 1993 dampers. The diameters of the chosen units were 125 and 250 mm. The Copyright Avail: CASI HC A02/MF A03 statistical basis for firm conclusions has not been satisfactory. One of

416 PHYSICS 16

the participating laboratories was unable to measure on such low flow noise metrics, only Perceived Level completely accounted for the rates as those used for the test objects chosen for this investigation and effects of wave shape, rise time, and peak overpressure. Neither metric two of the test objects were damaged during the transportation between fully accounted for the effect of duration. However, the magnitude of the the participating laboratories. NTIS duration effect was small over the very wide range of durations considered. Author

N94-29362*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field, CA. N94-29856** National Aeronautics and Space Administration. BOUNDARY LAYER CONTROL DEVICE FOR DUCT Langley Research Center, Hampton, VA. SILENCERS Patent Application DYNAMIC FRACTURE MECHANICS ANALYSIS FOR AN EDGE FREDRIC H. SCHMITZ, inventor (to NASA) and PAULT. SODERMAN, DELAMINATION CRACK inventor (to NASA) 15 Nov. 1993 12 p STEPHEN A. RIZZI and JAMES F.DOYLE Apr. 1994 13 p Proposed (NASA-CASE-ARC-12030-1; NAS 1.71:ARC-12030-1; US-PATENT- for presentation at the Fifth International Conference on Recent APPL-SN-151690) Avail: CASI HC A03/MF A01 Advances in Structural Dynamics, Southampton, England, 18-21 Jul. A boundary layer control device includes a porous cover plate, an 1994 acoustic absorber disposed under the porous cover plate, and a porous (Contract RTOP 505-63-50-10) flow resistive membrane interposed between the porous cover plate (NASA-TM-109106; NAS 1.15:109106) Avail: CASI HC A03/MF A01 and the acoustic absorber. The porous flow resistive membrane has a A global/local analysis is applied to the problem of a panel with an flow resistance low enough to permit sound to enter the acoustic edge delamination crack subject to an impulse loading to ascertain the absorber and high enough to damp unsteady flow oscillations. NASA dynamic J integral. The approach uses the spectral element method to obtain the global dynamic response and local resultants to obtain the J integral. The variation of J integral along the crack front is shown. The N94-2940r# Old Dominion Univ., Norfolk, VA. crack behavior is mixed mode (Mode 2 and Mode 3), but is dominated REVIEW OF SONIC FATIGUE TECHNOLOGY by the Mode 2 behavior. Author B. L CLARKSON (University Coll. of Swansea, Wales.) Apr. 1994 75 p (Contract NAG1-363; RTOP 763-23-45-70) (NASA-CR-4587; NAS 1.26:4587) Avail: CASI HC A04/MF A01 From the earty-1960s until the mid-1980s, there was very little theoretical development for sonic fatigue prediction. Design nomographs based on simple theoretical models and results of specially designed tests were developed for most common aircraft structures. The use of advanced composites in the 1980s, however, generated an increased interest in development of more sophisticated theoretical models because of the possibilities fora much wider range of structural designs. The purpose of this report is to review sonic fatigue technology and, in particular, to assess recent developments. It also suggests a plan for a coordinated program of theoretical and experimental work to meet the anticipated needs of future aerospace vehicles. Author

N94-29464** National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. SUBJECTIVE RESPONSE TO SONIC BOOMS HAVING DIFFERENT SHAPES, RISE TIMES, AND DURATIONS DAVID A. MCCURDY Mar. 1994 44 p (Contract RTOP 537-03-21-03) (NASA-TM-109090; NAS 1.15:109090) Avail: CASI HC A03/MF A01 Two laboratory experiments were conducted to quantify the subjective response of people to simulated outdoor sonic booms having different pressure signatures. The specific objectives of the experiments were to compare subjective response to sonic booms when described in terms of loudness' and 'annoyance'; to determine the ability of various noise metrics to predict subjective response to sonic booms; to determine the effects on subjective response of rise time, duration, and level; and to compare the subjective response to 'N-wave' sonic boom signatures with the subjective response to 'minimized' sonic boom signatures. The experiments were conducted in a computer-controlled, man-rated sonic boom simulator capable of reproduc- ing user-specified pressure signatures for a wide range of sonic boom parameters. One hundred and fifty sonic booms representing different combinations of two wave shapes, four rise times, seven durations, and three peak overpressures were presented to 36 test subjects in each experiment The test subjects in the first experiment made judgments of 'loudness' while the test subjects in the second experiment judged 'annoyance.' Subjective response to sonic booms was the same whether expressed in terms of loudness or in terms of annoyance. Analyses of several different noise metrics indicated that A-weighted sound exposure level and Perceived Level were the best predictors of subjective response. Further analyses indicated that, of these two

417 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 305) June 1994

Acoustic emission monitoring ot aging aircraft Aeroacoustic sensitivity analysis and optimal Typical Subject Index Listing seroacoustic design of turbornechmery blades IDREP-93-17] p 393 N94-30129 [NASA-CF1-195786] p 399 N94-30013 Enhanced fatigue crack detection in aging aircraft using A modernised HST of NLR continuous acoustic emission monitoring IAD-B179220] P402 N94-30423 I SUBJECT HEADING I [DREP-93-161 P393 N94-30131 AERODYNAMIC NOISE ACTIVE CONTROL Determination of sound power levels of air terminal units Miniature knesr-to-fotary motion actuator according to ISO 5135-Nordic inter-laboratory tests. p413 N94-29647 Nordtest proiect no. 968-91 ABORTED MISSIONS ACTUATORS [PB94-137411] p416 N94-29175 — STS-SS pad abort Engine 2011 oxtdizsr prebumer Mnaure triev-to-rotary motion actuator AERODYNAMIC STABILITY augmented spark Igniter check valve teak p413 N94-29647 Closed loop vibrabonal control: Theory and 1NASA-CR-1936301 p 138 N94-12806 ADA (PROGRAMMING LANGUAGE) Tpplicntions Ada run time system certification tor avionics IAO-A275451] P400 N94-2B632 applications p394 N94-29332 Exploring ODES as a tool for determining limits of ADAPTIVE CONTROL acrwjvable performance in aiuafl design Application of digital control theory to adaptive grid (AD-A275359) p 391 N94-28998 generation p415 N94-28980 Study of bridge ueBJgn and technology ADDITIVES (P894-137916) p373 N94-29160 Research and development of high thermal stability fuels p405 N94-29261 AERODYNAMIC STAUJNC The subject heading is a key to the subject A tree-wake Euler and Navier-Stokes CFD method and AERIAL RECONNAISSANCE content of the document. The title Is used to its •pr**^1*1** to hslicopter lolors axrudng dyrujmc staD Cockpit video: A tow coat BOA source (AIXA275416) p377 N94-29197 provide a description of the subject matter. When [AD-A275228] p395 N94-293S9 AERODYNAMICS the title is insufficiently descriptive of document Paytoad central control tor unmanned aircraft p401 N94-302M Aerodynamic design using parallel processors content, a title extension Is added, separated [AD-A275470] p374 N94-2B674 AEROACOUSnCS from the title by three hyphens. The accession Experimental in»eitigation of thieo dimensiuiial Aeroacoustic eensitivtty analysis and optimal number and the page number are Included In vortex-airfoil interaction in a supersonic stream aaresceustic design of mrbomachJnerY blades each entry to assist the user in locating the (NASA-Cn-195786) p399 N94O0013 [A&A2751071 P374 N94-2B899 ProOsMOinys of tho 10tn NAL Sympovuni on Ajrcrsft abstract In the abstract section. If applicable, a AEROBRAKMO report number Is also Included as an aid in iden- Parade fcnetc simulation el high altitude hypervatocity Computational Aerodynames (NAL-SP-19] p375 N94-2B946 tifying the document. Under any one subject ENGRID: A graphical interactive code for the [NASA^R.194535] p379 N94-29B93 heading, the accession numbers are arranged In compulation of structured grids for blocked flow dornsins sequence. P409 N94-28956 Holographic (nterterometry. A user's guide AemUmiiiuUieiiiLal calculations in afterburners (DE94-003138] p40B N94-28486 Exploring GOES as a tool tor determining limits of ^_ p396 N94-29258 Algorithm and code devetopmenf for unsteady achievable perfomianos in aircraft design [AD-A27S3S9] ^ p391 three itnieniiunal Navier-Stokes equations Study of bridQB dk»>i p400 N94-29728 Computational Aerodynamics ACCIDENTS The design of a system of codas tor industrial I NAL-SP-19) p375 N94-26946 Aircraft accident/incident summary report In-flight toes calculations of flows around aircraft and other complex Engineering of systems tor application of scientific of control, leading to forced landing and runway overrun. aerodynamic configurations computing in industry p 415 N94-28947 Continental Express. Inc.. N24706 Embraer EMB-120 RT, [PB94-12S596] p381 N94-30387 Monte Carlo simulation or normal shock wave. Part 2: Pine Bkiff. Arkansas, 29 April 1993 Ctitaihji ot vwtions cpplied to 3D nwltH*o»nt VMS model and VSS model p409 N94-28948 (PB94-910404J P382 N94-29402 Variable soft sphere molecular model in the Monte Carlo ACOUSTIC EMISSION [PB94-12S4S7I P381 N9«-30«01 sanitation of air species p409 N94-26M9 Enhanced fatigue crack detection in aging aircraft using Rarefied gas numerical wind tunnel. Part 8: HOPE AERODYNAMIC DRAG continuous acoustic emission mouumig p401 N94-2B9SO Unsteady aerodynamic computations around (DREP-93-161 393 N94-30131 Numerical emulation of arc heated wind tunnel now P NACA0012 at Ngh angles of attack p377 N94-28969 ACOUSTIC FATIGUE P402 N94-2B9S1 Aerodynainc characteristics of a propeller-powered Numerical simulation of unsteady aerodynamic heating Review of sonic fatigue technology Mgh-Mt aernispan wing [NAS^CR-4587] 417 N94-2B407 induced by shock reflections p375 N94-2B952 P [NASA-TVM541) p380 N94-29937 Numerical simulation of steady Maeh reflection by shock ACOUSTIC MEASUREMENT AERODYNAMIC INTERFERENCE capturing schemes P375 N94-28953 The nozzle acoustic lest rip; An acoustic and Experimental studies of transonic flow netd near a Higher-order accurate numerical simulation of 3D aerodynamic tree-jet taciHy tongrtixknaDy slotted wind tunnel wan supersonic mixing layers p375 N94-28954 (NASA-TM-106495) p 401 N94-28749 (NASA-TP^392) P 378 N94-29S45 Numerical simulation of aerothermodynamic heating ot n ot eound Dower levels el n terminal uniti AERODYNAMIC LOADS hypersonic space transportation vehicles according to ISO 5135-Nordic inter-latioratory tests. Structural/aerodynamic blade analyzer (SAB) user's p375 N94-2B9S5 Nordteit proiect no. 968-81 gude. version 1.0 Transonic expanding flow through anally symrinUiL [PB94-137411] P416 N94-29175 [NASA-CW-194460] p395 N94-29103 P410 N94-28985

A-1 SUBJECTINDEX AEROSPACE ENGINEERING

Ground independent landing system Testing Operational Flight Programs (OFPs) Similarity between turbulent flows through curved pipe p416 N94-29337 and orthogonal rotating pipe p 4tO N94-2B986 p 385 N94-29564 Fishermans Bend: A centre of Australian aviation GPS/GNSS for ATM P 385 NS4-29565 AIRCRAFT ACCIDENT INVESTIGATION Aircraft accident/incident summary report In-flight loss (AD-A274981) p 373 N94-29090 Contributions of OLR to air traffic capacity enhancement AEROSPACE ENGINEERING within a terminal area P 385 N94-29567 of control, leading to forced landing and runway overrun, Aerospace Software Engineering for Advanced Systems Simulation of fully automated air traffic control Continental Express. Inc.. N24706 Embraer EMB-120 RT. Architectures concepts P386 N94-295S9 Pine Bluff. Arkansas. 29 April 1993 |AGARr>CP-545] p415 N94-29315 DLR's ATM demonstration programme IPB94-910404) p382 N94-29402 AEROSPACE PLANES p386 N94-29575 AIRCRAFT ACCIDENTS Numerical sanitation of supersonic flow around space AIR TRAFFIC CONTROL Crashworthiness analysis of commuter aircraft seats plane with engine installed p 376 N94-2B9B1 Machine Intelligence in Air Traffic Management [AD-A275889J P 382 N94-2B799 Some problems of scramjet propulsion tor aerospace (AGARf>CP.S38] P383 N94-29558 National Transportation Safety Board annual review of planes. Part 1: Scramjet: Aims and features Advances in development capabilities for intelligent air aircraft accident data. US general aviation. 1990 p398 N94-29295 traffic management systems p 384 N94-29559 [PB94-126869) p 382 N94-29185 Some problems of scramjet propulsion tor aerospace Intelligent systems for air space control and Fire behavior of aeronautical materials planes. Part 2: Scramjet Development and test management P 384 N94-29560 fREPT-932-600-105] P 408 N94-294S7 problems p399 N94-29301 Use of advanced technologies in ATM (air traffic AIRCRAFT APPROACH SPACING Contributions of DLR to air traffic capacity enhancement AEROSPACE VEHICLES management) domain p 384 N94-29561 Variable soft sphere molecular model in the Monte Carto Air traffic management as principled negotiation within a terminal area P 385 N94-29567 simulation of air species p 409 N94-28949 between intelligent agents p 384 N94-29562 Design of Center-TRACON Automation System Rarefied gas numerical wind tunnel. Pan B: HOPE Use of GPS in automated air traffic control p385 N94-29568 p 401 N94-28950 p384 N94-29563 Profile negotiation: An air/ground automation integration Numerical simulation of aerothermodynarnc heating of Ground independent landing system concept tor managing arrival traffic p 387 N94-29S78 hypersonic space transportation vehdes p385 N94-29564 ARC2000: Automatic radar control p375 N94-28955 GPS/GNSS for ATM p 385 N94-29565 p388 N94-29583 Code development for hypersonic real-gas flow ACCS Surveillance Exploratory Prototype (ASEP) Development of precision runway monitor system tor simulations toward the design of space vehicles, part 2 p412 N94-29566 increasing capacity of parallel runway operations' p376 N94-28966 Contributions of DLR to air traffic capacityenhancement p389 N94-29587 Review of sonic fatigue technology within a terminal area P 385 N94-29567 AIRCRAFT COMPARTMENTS fNASA-CR-4587] p4t7 N94-29407 Design of Center-TRACON Automation System Aircraft evacuations: The effect of a cabin water spray AEROTHERMOCHEMISTRY p385 N94-29568 system upon evacuation rates and behaviour Numerical simulation of arc heated wind tunnel flow Simulation of fully automated air traffic control [CAA-PAPER-93008] p 393 N94-29887 p 402 N94-28951 concepts p386 N94-29569 AIRCRAFT CONFIGURATIONS Aerothennochemical calculations in afterburners Decision Making Aids (DMA) in on-line ATC systems Three-dimensional external flow computations using p396 N94-29258 p386 N94-29570 prismatic grid p410 N94-28979 Models for vibration-dissociation coupling in Cognitive approach to specifications on air traffic AIRCRAFT CONSTRUCTION MATERIALS high-temperature gases p 413 N94-2967S controllers'Decision assistance systems Service life prediction of composite structures through A study of tow emissions gas turbine combustions p386 N94-29571 [NASA-CR-195763] p 399 N94-29860 Considerations on graphical user interfaces for intelligent (AD-A27S661) p 403 N94-2B654 AEROTHERMODYNAMICS ATM support systems p386 N94-29572 Fun-scale testing and analysis of curved aircraft fuselage Ducted kerosene spray flames p 407 N94-29276 Interactive analysis and planning toots for air traffic and AFTERBURNING airspace management p386 N94-29573 IAD-A275666] p 390 N94-28657 Aerothermochemical calculations in afterburners DAISY: A decision aid tor an air situation interpretation NAVAIR aircraft wiring standardization and qualification p396 N94-29258 system p386 N94-29574 program p408 N94-28704 Tochnotogy ftys'. A tool for •ftortoumof dovotopnwH DLR's ATM demonstration programme Role ot microstructure on the fatigue durability of p 397 N94-29270 p386 N94-29575 aluminum aircraft alloys AQING (MATERIALS) Advanced air traffic control and flight management (AD-A275814) p 403 N94-28830 Aircraft age impacts on maintenance requirements system concepts P 387 N94-29576 Fire behavior of aeronautical materials IAD-A275701] p373 N94-28666 Opportunities for integrating the aircraft FMS. (REPT-932-600-105) p 408 N94-29457 AIR BREATHING ENGINES aeronautical operational control centers, and future air AIRCRAFT CONTROL Research and development of ramjets/ramrockets. Pan traffic management systems in oceanic airspace An experimental and theoretical study of the 1: Integral solid propellent ramrockets p 387 N94-29577 aerodynamic characteristics of some generic missile p398 N94-29294 Profile negotiation: An air/ground automation integration concept) at Mach numbers from 2 to 6.8 AIR COOLING concept for managing arrival traffic p387 N94-29578 (NASA-TM-109110) p 378 N94-29473 Acquisition, desiyn modification, assembly, and ground Air-ground intonation of the ATM system in PHARE Opportunities for •itegraliny the aiuafl FMS, test of NPS Hummingbird remotely piloted heficoptar p388 N94-29579 aeronautical operational control centers, and future air (AD-A275S46J p390 N94-28837 Experimental flight management system traffic management systems in oceanic airspace AIRFLOW P388 N94-295BO p387 N94-29577 Evaluation of the transient operation of advanced gas The PHARE advanced tools p388 N94-29581 Decoupled flight control system design using the singular turbine combustors p 397 N94-29269 The Common Modular Simulator (CMS): An architecture perturbation method p400 N94-29850 The mfluence of air distribution on homogeneity and test bed for future advanced ATM systems Paytaad central control tor unmanned aircraft pollutant formation in the primary zone of a tubular p388 N94-29582 p 401 N94-30284 combustor p406 N94-29274 ARC2000: Automatic radar control AIRCRAFT DESIGN AIR JETS p388 N94-29583 Organized wiring systems p 408 N94-28705 The mixing process in the quenching zone of the A novel near-range radar network tor airport surface Modification of ACSYNT aircraft computer uiuuiam tor nch-tearvcombustJori concept p 407 N94-29281 control p389 N94-29586 AIR NAVIGATION Development of pieusieii runway monitor system tor (NASA-CR-195737) p390 N94-2S817 Object oriented design of the autonomous fixiaking increasing capacity ot parallel runway operations Exploring ODES as a tool tor determining limits of management system p 383 N94-29323 p389 N94-295B7 achievable performance in aircraft design Ground independent landing system AIR TRAFFIC CONTROLLERS (PERSONNEL) (AD-A275359) p 391 N94-2B998 p385 N94-29564 Decision Making Aids (DMA) in on-line ATC systems Information presentation tor expert systems in future GPS/GNSS for ATM p385 N94-29565 p386 N94-29570 fighlBf aircraft Sonulfltiort of fully flutomfltod 4vr tr&fHc control Cognitive approach to specifications on air traffic fAD-A275126) p394 N94-29005 concepts p386 N94-29569 controllers'decision assistance systems Spray combustion experiments and numerical Interactive analysis and planning tools for air traffic and p386 N94-29571 predictions p407 N94-29277 airspace management p 386 N94-29573 Considerations on graphical user menaces for intelligent Low-speed longitudinal aerodynamic characteristics of ARC2000: Automatic radar control ATM support systems p386 N94-29572 a flat-plate plantorm model of an advanced fighter p388 N94-29583 Interactive analysis and planning tools for air traffic and cuufiyuiatiun AIR POLLUTION airspace management p 386 N94-29573 [NASA-TM-109045J p 377 N94-29443 On the effect of emissions from strut aft engines on the DAISY: A decision aid for an air situation interpretation AIRCRAFT ENGINES state of the atmosphere p 414 N94-29247 system p386 N94-29574 Fuels and Combustion Technology tor Advanced Aircraft Pollutant emissions from and within a model gaa turbine AIR TRANSPORTATION Engines combustor at elevated pressures and temperatures National Transportation Safety Board annual review of IAGARD-CP-536) p 404 NS4-29246 p406 N94-29271 aircraft accident data. US general aviation. 1990 On the effect of emi-mma from aircraft engines on the Reduction of NO'x) by fuel-staging in gas turbine [PS94-126869J P382 N94-2918S state of the annualnae p 414 N94-29247 eitojiies: A cutiuniuiieiil to the future A capacity planning model for Canadian miBlary aHft p406 N94-29272 Combustion technology needs tor advanced high requests pressure cyde engines p 404 N94-29248 The influence of air distribution on homogeneity and IISBM-0-315-86079-0] p 382 N94-30144 Combustion tor future supersonic transport propulsion pottutant formation in the primary zone of a tubular AIRBORNE RADAR combustor p406 N94-29Z74 Ground independent landing system p 404 N94-29249 AIR SAMPLING p385 N94-29564 Ftowfiek) prediction of NO(x) and smoke production in A study of low Gftu&sions QSS turbine combustions AIRBORNE/SPACEBORNE COMPUTERS anratt engines p 404 N94-29252 I NASA-CR-195763] p 399 N94-29860 Ada run time system certification for avionics High temperature fuel requirements and payoffs AIR TRAFFIC applications p394 N94-29332 p405 N94-29259 Machine Intelligence in Air Traffic Management On ground system integration and testing: A modem Design aspects in small aircraft gas turbine fuel (AGARD-CP.538) p383 N94-29558 approach p394 N94-29334 in/actors p397 N94-29264

A-2 SUBJECTINDEX APPLICATIONS PROGRAMS (COMPUTERS)

Technology rigs: A tool tor afterburner development AIRCRAFT NOISE Proceedings of the 10th NAL Symposium on Aircraft p 397 N94-29270 Experimental validation of finite element and boundary Computational Aerodynamics INAL-SP-19) P375 N94-28946 Reduction of NO(«) by fuel-staging in gas turbine element methods for predicting structural vibration and engines: A commitment to the future radiated noise Application of flow field simulation to turbine vane p406 N94-29272 [NASA-CR-4561) p412 N94-295S2 design P 395 N94-28978 The influence of air distribution on homogeneity and AIRCRAFT PERFORMANCE Time-marching aeroelastic and spatial adaptation pollutant formation in the primary zone of a tubular Exploring ODES as a tool tor determining limits of procedures on triangular and tetrahedral meshes using combustor p406 N94-29274 achievable performance in aircraft design an unstructured-grid Euler method p 379 N94-29877 Effects of hydrogen addition on pollutant emissions in IAT>A275359] p 391 N94-28998 Calculus of variations applied to 2D multi-point airfoil a gas turbine combustor p 406 N94-29275 AIRCRAFT PILOTS design •_•• 't. Ducted kerosene spray flames p 407 N94-29276 Effects of repair on structural integrity (PB94- 125457) p 381 N94-30401 (AD-A275756] p 390 N94-28647 . -.HYSpray combustion experiments and numerical AIRFRAMES •'• AIRCRAFT PRODUCTION predictions p 407 N94-29277 An analytical study of unsteady rotor/fuselage Fishermans Bend: A centre of Australian aviation Some problems of scramjet propulsion tor aerospace interaction in hover and forward flight [AD-A274981] P373 N94-29090 planes. Part 2: Seramjet: Development and test p 379 N94-29826 problems p399 N94-29301 AIRCRAFT SAFETY Fun-scale testing and analysis of curved aircraft fuselage Integrated proputsion-airframe dynamics and control AIRCRAFT EQUIPMENT p 392 N94-29854 Cockpit video: A low cost BDA source panels Rotorcraft airtrame structural optimization for vibration [AD-A275228J p 395 N94-29389 [AD-A275666] p 390 N94-28657 and dynamic stress reductjon including damping AIRCRAFT FUELS Crashworthmess analysis of commuter aircraft seats treatment p 392 N94-29878 Advanced fuel properties: A computer program for [AD-A275889] P 382 N94-28799 estimating property values National Transportation Safety Board annual review of AIRLINE OPERATIONS [AD-A275248] p 403 N94-28901 aircraft accident data. US general aviation, 1990 Effects of repair on structural integrity Fuots combustion r^sosrch [PB94-126869] p 382 N94-29185 (AD-A275756) p 390 N94-28647 [AD-A275122) p 404 N94-29004 Fre behavior of aeronautical materials Design of Center-TH ACON Automation System Fuels and Combustion Technology for Advanced Aircraft (REPT-932-600-105) p 408 N94-29457 p385 N94-29568 Engines Aircraft evacuations: The effect of a cabin water spray DLR's ATM demonstration programme [AGARD-CP-536] p 404 N94-29246 system upon evacuation rates and behaviour p 386 N94-29575 High temperature resistant jet fuels [CAA-PAPER-93008] p 393 N94-29887 AIRPORTS p405 N94-29260 AIRCRAFT STRUCTURES Los Angeles international airport instrument landing AIRCRAFT GUIDANCE Development of Alternating Current Potential Drop system approach data collection and reduction, phase 1 Opportunities tor integrating the aircraft FMS. (ACPD) procedures tor crack detection in aluminum aircraft [AD-A275115] p 383 N94-28914 aeronautical operational control centers, and future air panels Contributions of DLR to air traffic capacity enhancement traffic management systems in oceanic airspace (AD-A275755J p 408 N94-28646 within a terminal area p 385 N94-29567 p387 N94-29577 Effects of repair on structural integrity Design of Center-TRACON Automation System Profile negotiation: An air/ground automation integration (AD-A275766) p 390 N94-28647 p385 N94-29568 concept tor managing arrival traffic p 387 N94-29578 Full-scale testing and analysis of curved aircraft fuselage DLR's ATM demonstration programme Air-ground integration of the ATM system in PHARE panels p386 N94-29575 p388 N94-2957S [AD-A275666] p 390 N94-2S657 Development of precision njnway monitor system for Experimental flight management system A moment plotting method tor characterizing aircratl increasing capacity of parallel runway operations P3B8 N94-29580 fatigue data population distributions p389 N94-295B7 The PHARE advanced tools p 388 N94-29581 (AD-A275500) p 390 N94-28660 AIRSPACE Automatic control steps for aircraft taxi guidance Crashworthiness analysis of commuter aircraft seats Contributions of DLR to air traffic capacity enhancement p388 N94-29S84 f AD-A275889) p 382 N94-28799 wrthm a terminal area p385 N94-29567 A novel near-range radar network tor airport surface Fuels combustion research Interactive analysis and planning tools for air traffic and control p389 N94-29586 [AD-A275122] p 404 N94-29004 airspace management p 386 N94-29573 Development of precision runway monitor system tor Backscatter haze device for measurement of haze in ALGORITHMS increasing capacity of parallel runway operations aircraft transparencies Algorithm and code development tor unsteady p389 N94-29587 [AD-A275127] p 391 N94-29042 three-dimensional Navier-Stokes equations AIRCRAFT ICING Cold expansion and interference tor extending the [NASA-CR-195774] p 414 N94-29942 An experimental study of the ftowfield on a semtspan fatigue lite of multi-layer metal joints ALTERNATING CURRENT rectangular wing with a simulated glaze ice accretion [AD-A274982] p 410 N94-29091 Development of Alternating Current Potential Drop p378 N94-29674 Review of sonic fatigue technology (ACPD) procedures for crack detection in aluminum aircraft The 3-D LDV measurements on a 30-degree swept wing [NASA-CR-4587] p417 NB4-29407 with a simulated ice accretion Automation of the NOT diagnostic using neural nets. [ AD-A275755] p 408 N94-28646 [NASA-CR-195327] p 380 N94-30124 Application: fnspadion of Airbus tonujtuduial joints during ALTERNATING DIRECTION IMPLICIT METHODS An experimental study of the aerodynamics of a swept Unsteady aerodynamic computations around andunswepl semispan wing with a simulated glaze ice [REPT-932-600-104] p412 N94-29474 NACA0012 at high angles of attack p 377 N94-28969 accretion Dual-Band Infrared (DBIR) imaging inspections of Boeing ALUMINUM ALLOYS (NASA-CR-195330) p381 N94-301S2 737 and KC-135 aircraft panels Development of Alternating Current Potential Drop AIRCRAFT INDUSTRY [DE94-005700] p 374 N94-29842 (ACPD) procedures for crack detection in aluminum aircraft Fishermans Bend: A centre of Australian aviation Dynamic fracture mechanics analysis for an edge panels [AD-A274981] p 373 N94-29090 delamiiiauon crack ( AD-A275755J p 408 N94-28646 AIRCRAFT INSTRUMENTS [NASA-TM-108106) p417 N94-29856 Role of microstructure on the fatigue durability of GPS/GNSS for ATM p 385 N94-29565 Rotorcraft ajrframe structural optimization for vtoration aluminum aircraft alloys AIRCRAFT MAINTENANCE and dynamc Aliv^i reduction Eicludiriy damping (AD-A275814) p 403 NB4-28830 Effects of repair on structural integrity treatment p392 N94-29878 Cow expansion and interference for extending the (AD-A275756] p390 N94-28647 Acoustic omission nxxutcfuig of Afpng Aircraft fatigue lite of multi-layer metal joints Aircraft age impacts on maintenance requirements structurtts [AD-A274982] p 410 N94-29091 [AO-A275701] p 373 N94-28666 [DREP-93-17] p393 N94-30129 The effect of mechanical paint sliiupiiiu on the fatigue Organized wiring systems p 408 N94-28705 EnnAncod fatiQUB cr&cK detection tn SQIOQ Aircraft USIHQ and fracture of thin aluminum airplane skin Aircraft age impact on individual operating and support continuous acoustic emission monitoring p408 N94-29900 cost elements [DREP-93-16] p393 N94-30131 AMMONIA (AD-A275739) p 373 N94-28732 AIRFIELD SURFACE MOVEMENTS A study of low 0 missions 0ss turbine combustions Evaluation of access/navigational features of a Automatic control steps for aircraft taxi guidance (NASA-Cfl-195763) p 399 N84-29860 graphical-user interface installed on a portable p388 N94-28584 ANGLE OF ATTACK maintenance aid Aireide ground movements surveillance Numerical analysis of airfoil for helicopter Made at high IAD-A275791] p383 N94-28744 p388 N94-29585 angle of attack using Navier-Stokes code Role of microstructure on the fatigue durability of A novel near-range radar network for airport surface p375 N94-28958 aluminum aircraft alloys control P389 N94-29586 An experimental study of the ftowfield on a semtspan [AD-A27S814] P403 N94-28830 AIRFOIL PROFILES rectangular wing with a simulated glaze ice accretion A time reasoning system based on the event calculus A design of third-generation airfoils for helicopter rotor p37B N94-29674 for scheduling in aeronautic maintenance blades using Navier-Stokes p 391 N94-28957 Aerodynamic characteristics of a propeller-powered (REPT-932-710-101] p 374 N94-29463 high-lift semispan wing Numerical analysis of airfoil for helicopter Hade at high (NASA-TM-4541) p 380 N94-29937 The affect of mechanical paint stiipping on the fatigue angle of attack using Navier-Stokes code and fracture of thin aluminum airplane skin ANTENNA DESIGN p375 N94-28958 p408 N94-29900 Theoretical and experimental study of a cylindrical Unsteady aerodynamic computations around AIRCRAFT MODELS rrocrostnp antenna NACA0012 at high angles of attack p377 N94-28969 Modification of ACSYNT aircraft computer program for IREPT-932-440-109] p 412 N94-29456 preliminary design Application of digital control theory to adaptive grid ANTENNA RADIATION PATTERNS [NASA-CR-195737] p 390 N94-28817 generation p41S N94-28980 Theoretical and experimental study of a cylindrical A non-linear simulation for an autonomous unmanned Helicopter mission and rotor performance optimization mcrostnp antenna air vehicle with quasi-linear inflow theory p 392 NS4-29594 [REPT-932-440-109] p 412 N94-2S456 I AD-A275062] p 391 N94-29200 AIRFOILS APPLICATIONS PROGRAMS (COMPUTERS) Miniature knear-to-rotary motion actuator Aerodynamic design using parallel processors Flight command software development: RAFALE p413 N94-29647 [AD-A27S470] p374 N94-2B674 p415 N94-29320

A-3 SUBJECTINDEX APPROACH

Considerations on graphical user interfaces for intelligent AUTONOMOUS NAVIGATION ATM support systems p 386 N94-29572 Object oriented design of the autonomous fixtaking APPROACH management system p 383 N94-29323 C-135 AIRCRAFT Los Angeles international airport instrument landing AVIATION PSYCHOLOGY KC-135 cockpit modernization study and crew reduction system approach data collection and reduction, phase 1 Information presentation for expert systems in future feasibility demonstration (AD-A275115) P3B3 N94-28914 fighter aircraft (AD-A275230] P 392 N94-2939I Extremely Low Visibility IFR Rotorcraft Approach (AD-A275126) p394 N94-29005 Dual-Band Infrared (DBIR) imaging inspections of Boeing 737 and KC-135 aircraft panels (ELVIRA) operational concept development Volume 1: AVIONICS Executive Summary Aerospace Software Engineering for Advanced Systems [DE94-005700] P 374 N94-29842 [DOT/FAA/RD-94/1,1] p 389 N94-30189 Architectures CALCULUS APPROACH CONTROL [AGARD-CP-545] P415 N94-29315 A time reasoning system based on the event calculus tor scheduling in aeronautic maintenance Advanced air traffic umiiol and flight management Experiences with the HOOD design method on avionics fREPT-932-710-101] P 374 N94-29463 system cmicepu p 387 N94-28576 software development p41S N94-29325 Profile negotiation: An air/ground automation integration CANCELLATION Ada run time system certification for avionics Method for cancelling expansion waves in a wave concern tor managing arrival traffic p 387 N94-29578 applications p394 N94-29332 Experimental flight management system rotor On ground system integration and testing: A modem P388 N94-29580 (NASA-CASE-LEW-15218-2) p413 N94-29740 approach p 394 N94-29334 Extremely Low Visibility IFR Rotorcraft Approach CARBON MONOXIDE (ELVIRA) operational concept development. Volume 1: Testing Operational Flight Programs (OFPs) The radiocarbon hydroxyl technique Executive Summary p416 N94-29337 p 414 N94-28600 [DOT/FAA/RD-94/1.1] p 389 N94-30189 KC-135 cockpit modernization study and crew reduction CARBON-CARBON COMPOSITES ARC HEATING feasibility demonstration Dynamic fracture mechanics analysis for an edge Numerical simulation of arc heated wind tunnel flow [AD-A275230] p 392 N94-29391 delamination crack P402 N94-28951 DLR's ATM demonstration programme | NASA-TM-109106] p417 N94-29856 ARCHITECTURE (COMPUTERS) p386 N94-29575 CASCADE FLOW How to control the increase in the complexity ol civil Application of flow field simulation to turbine vane aircraft on-board systems P 394 N94-29316 design P 395 N94-2B976 Software Management Environment (SME) unicepts B An elliptic-hyperbolic grid generation method and and architecture, revision 1 application to compressor flows P 395 N94-28981 [NASA-CR- 189293] P 416 1494-29727 BACKSCATTERING CATALYSIS ARTIFICIAL INTELLIGENCE Backscaner haze device for measurement of haze in Fuel-nch catalytic combustion of a high density fuel Information presentation for expert systems in future aircraft transparencies [NASA-TP-3281J p 407 N94-29356 fighter aircraft [AD-A275127] p 391 N94-29042 CENTRIFUGAL COMPRESSORS Numerical study on internal flows of centrifugal (AD-A275126) P394 N94-29005 BLOWING compressors p 395 N94-2B977 Object oriented design of the autonomous fbrtaking Numerical study of the trailing vortex of a wing with CERTIFICATION management system p 383 N94-29323 wing-tip blowing Ada run lirne system certification for avionics Machine Intelligence in Air Traffic Management [NASA-CR-195803] p 378 N94-29760 [AGARD-CP-538] P383 N94-295S8 applications p394 N94-29332 BODY-WING CONFIGURATIONS Advances in development capabilities for intelligent air CF-700 ENGINE NufftGfical analysis of sonic boocn m tho nov fioU traffic management systems p 384 N94-29559 Radar jet engine health monitoring project p376 N94-28962 Intelligent systems for air space control and fASSGI-301] p400 N94-30130 management p 384 N94-29560 Three-dimensional external flow computations using CHASSIS ASPHALT prismatic grid p410 N94-2B979 Acquisition, design modification, assembly, and ground Asphaltic concrete performance under heavy fighter Aircraft aerodynamics with deflected jets in ground test of NPS Hummingbird remotely piloted helicopter aircraft loading effect p380 N94-29973 (AD-A27S546] p390 NB4-28837 (AD-A27S046] p 402 N94-29151 BOEING 737 AIRCRAFT CIVIL AVIATION ASYMPTOTIC METHODS Dual-Band Infrared (DBIR) imaging inspections of Boeing Effects of repair on structural integrity Long-wavelength asymptotics of unstable crossflow 737 and KC-135 aircraft panels [AD-A2757S6] p 390 N94-2B647 modes, including the effect of surface curvature [DE94-005700] p 374 N94-29842 How to control the increase in the complexity of civil [NASA-CR-4579] P412 N94-29460 BOMBS (ORDNANCE) aircraft on-board systems p 394 N94-29316 ATMOSPHERIC COMPOSITION Cockpit video: A low cost BOA source Ada run ame system certification for avionics Tho t&diocdrbon hydroxyl toctimpuo [AD-A275228) p395 N94-293B9 applications P394 N94-29332 P414 N94-28600 BOUNDARY CONDITIONS CLIMATE CHANGE On the effect of emissions from aircraft engines on the A niethud tor the modelling of porous and solid wind On the effect of emissions from aircraft engines on the state of the atmosphere p 414 N94-2B247 tunnel walls vi *'JM"|iftft*l^?'*f iflui ddynamic s cff^?? state of the atmosphere P414 N94-29247 ATMOSPHERIC MODELS [NASA-CR-195699] p409 N94-28724 COCKPITS Monte Carlo simulation or normal shock wave. Part 2: BOUNDARY ELEMENT METHOD KC-135 cockpit modernization study and crew reduction VMS model and VSS model P4O9 N94-28948 rinerimflntil validation of finite element and boundary feasibility demonstration Variable soft sphere molecular model in the Monte Carlo •lament methods for predicting structural vibration and (AD-A275230J p 392 N94-29391 simulation of air species P4O9 N94-28949 COLD WORKING [NASA-CR-4561] p412 N94-29552 Cold expansion and interference for extending the Rarefied gas numerical wind tunnel. Pan 8: HOPE BOUNDARY LAYER FLOW fatigue lite of mum-layer metal joints p 401 N94-289SO Boundary layers induced by thiee dlnieiuiuiial vortex (AD-A274982) p410 N94-29091 ATOMIZERS loops COMBUSTIBLE FLOW Investigation of the two-phase flow in a research [AT>A27S676] p 408 N94-28685 Ftowfiekt piediction of NO(x) and smoke production in combustor under reacting and non-reacting conditions long-wavelength asymptolics of unstable crossflow aircraft engines p 404 N94-29252 P411 N94-29282 modes, Mtcluitiiy the effect of surface curvature Time-resolved measurements in a three dimensional ATTITUDE INDICATORS (NASA-CR-4579] p412 N94-29460 model combustor p411 N94-29283 A comparison of three aircraft attitude display symbotogy BOUNDARY LAYER SEPARATION Scramjet CFD methods and analysis. Part 1: Scramjet structures Boundary layers induced by three dimensional vortex CFD methods. Numerical simulation of the flow in scramjet | AD-A275172) p 394 N94-29O48 loops duct p398 N94-29296 AUDITORY PERCEPTION [AD-A275678] p408 N94-28665 COMBUSTION Subjective response to some booms having different An ajtparifnsntal study of tho flownoU on 8 somispan Fuels combustxjn research shapes, rise times, and durations rectangular wing with a snnutatad glaze ice accretion [AD-A275122) p404 N94-29004 I NASA-TM- 109090) p 417 N94-29464 p376 N94-29674 Numerical simulation of aerothermal characteristics in AUTOMATED RADAR TERMINAL SYSTEM BOUNDARY LAYER TRANSITION gas turbine cmnbuslois with complex geometries Machine Intelligence in Air Traffic Management An ejiperiiiieiilal study of the flownold on a semispan P396 N94-29255 [AGARD-CP-538] p383 N94-295SB rectangular wing with a simulated glaze ice accretion Recent CFD applications in smalI gas turbine combustion AUTOMATIC CONTROL p378 N94-29674 systems development p 396 N94-29257 Automation of the NOT diagnostic using neural nets. EjtpuJiiiienls and theoretKal consider atmf is regarding Aerotherrnocherrocal calculations in afterburners Application: Inspection of Airbus longitudinal joints during the allowable roughness height in laminar flow p396 N94-29258 maintenance [PB94-125556] p 381 N94-30389 COMBUSTION CHAMBERS (REPT-932-6OO-104) P412 N94-29474 BRIOOES (STRUCTURES) Numerical study on the interaction between scramjet engine modules caused by thermal choke Intflftigent systems for air if*af.'»t cuiuul and Study of bridge design and tschnolOQy P395 N94-28960 management P384 N94-29560 [PB94-137916] p373 N94-29160 BUILDINGS Fuels combustion research Use of GPS in automated air tiaffic conuul Rooftop emergency hefiports (AD-A275122) p 404 N94-29004 P384 N94-29563 (DOT/FAA/RD-93/2) p402 N94-29754 Numerical modelling of turbine combustion chambers Design of Center-TRACON Automation System BULKHEADS P396 N94-29254 P38S N94-2956B Aircraft system aft telescope cavity configuiatxxi study Numerical simulatjon of acromermal characteristics in Simulation of fuOy automated air traffic cmitjol for Stratospheric Observatory for Infrared Astronomy gas turbine combustors with complex geometries concepts P386 N94-29569 (SOFIA), phase 2 p396 N94-29255 ARC2000: Automatic radar control [NASA-CR-194266) p 392 N94-29685 Application of CFD in combustor design technology P388 N94-29583 BUTANES ^___ P396 N94-29256 Automate! mtrol steps for aircraft taxi guidance Effects of hydrogen addition on poQutam emssions in Recent CFD applications in small gas turbine combustion P388 N94-29584 a gas turbine combustor p 406 N94-29275 systems development p396 N94-29257

A-4 SUBJECTINDEX COMPUTER AIDED DESIGN

Aerotherrnochemical calculations in afterburners COMBUSTION STABILITY Unsteady aerodynamic computations around P396 N94-29256 The influence of air distribution on homogeneity and NACA0012 at high angles of attack p 377 N94-28969 Fuel injector design tor high temperature aircraft pollutant formation in the primary zone of a tubular Study on mixing and injection of hydrogen into a engine P 396 N94-29263 combustor p 406 N94-29274 supersonic flow p 377 N94-28975 The effect of incomplete fuel-air mixing on the lean limit Ducted kerosene spray flames p 407 N94-29276 Verification of a three-dimensional viscous flow analysis and emissions characteristics of a Lean Prevaporized COMBUSTION TEMPERATURE tor a single stage compressor p 410 N94-28976 Premixed (LPP) combustor p405 N94-29265 Combustion for future supersonic transport propulsion Numerical study on internal flows of centrifugal P404 N94-29249 Ultra low NO(x) ultra lean gas turbine primary zones compressors p 395 N94-28977 with bqukj fuels P397 N94-29267 COMMAND AND CONTROL Application of flow field simulation to turbine vane ACCS Surveillance Exploratory Prototype (ASEP) design p395 N94-28978 Computational and experimental results in high pressure p4t2 N94-29S66 combustions of H2/air and H2/O2/H2O COMMERCIAL AIRCRAFT Three-dimensional external flow computations using P406 N94-29268 Effects of repair on structural integrity prismatic grid p410 N94-28979 Evaluation of the transient operation of advanced gas [AD-A275756J P 390 N94-28S47 Application of digital control theory to adaptive grid turbine combustors p397 N94-29269 Ada run time system certification for avionics generation p 415 N94-28980 Pollutant emissions from and within a model gas turbine applications P 394 N 94-29332 An elliptic-hyperbolic grid generation method and combustor at elevated pressures and temperatures COMMUNICATION NETWORKS application to compressor flows p 395 N94-28981 p406 N94-29271 DLR'S ATM demonstration programme Transonic expanding flow through axialry symmetric Reduction of NO(x) by fuel-staging in gas turbine P386 N94-29S75 orifices p410 N94-28985 engines: A commitment to the future COMMUTER AIRCRAFT Similarity between turbulent flows through curved pipe P406 N94-29272 CrashworMness analysis of commuter aircraft seats and orthogonal rotating pipe p 410 N94-28986 The influence of air distribution on homogeneity and [AD-A275889] p 382 N94-28799 Performance evaluation of the NWT with parallel pollutant formation in the primary zone of a tubular COMPLEX SYSTEMS Fortran p415 N94-28992 combustor P406 N94-29274 Performing specifications for complex systems' software P400 N94-29317 A method of user interface for NWT _ .Effects of hydrogen addition on pollutant emissions in p415 N94-2B993 a gas turbine combustor p406 N94-29275 COMPONENT RELIABILITY NAVAIR aircraft wiring standardization and qualification A free-wake Euter and Navier-Stokes CFD method and Spray combustion experiments and numerical program p 408 N94-28704 its application to helicopter rotors including dynamic stall predictions p 407 N94-29277 COMPOSITE MATERIALS [AD-A27S416] p377 N94-29197 Investigation of the two-phase flow in a research Safety enhancement of composites via periodic proof Ftowlield prediction of NO(x) and smoke production in combustor under reacting and non-reacting conditions testing aircraft engines p 404 N94-29252 P411 N94-292B2 [AD-A275662] p 403 N94-28655 Application of CFD in combustor design technology Time-resolved measurements in a three dimensional COMPOSITE STRUCTURES p396 N94-29256 model combustor p411 N94-292B3 Safety enhancement of composites via periodic proof Development of global/chemistry model for jet-fuel Research and Development of Ham/Scram|ets and tosting thermal stability based on observations from static and Turboramjets in Russia [AD-A27S662] p403 N94-28655 flowing experiments p 405 N94-29262 (AGARD-LS-194) p397 N94-29291 Review of sonic fatigue technology Spray combustion experiments and numerical Research and development of lamjets/ramiocHets. Part (NASA-CR-45B7] p417 N94-29407 predictions p407 N94-29277 t; Integral solid propettant ramrockets Dynamic fracture mechanics analysis for an edge Scramjet CFD methods and analysis. Pan 1: Scramjet p398 N94-29294 CFD melnuds. Numerical simulation of the flow in scramjet CIAM experimental turboramjets P399 N94-29299 (NASA-TM-109106) p417 N94-298S6 duct p 398 N94-29296 COMBUSTION CHEMISTRY COMPRESSIBLE FLOW _ jjerarnjet CFD methods and analysis. Part 2: Scramjet Fuels combustion research Three dimensional simulation of compressible flow CFD analysis. Numerical simulation of supersonic mixing [AD-A275122] p 404 N94-29004 induced by a high-speed train moving into a tunnel and combustion applied to scramjet combustor Fuels and Combustion Technology tor Advanced Aircraft p376 N94-28967 p 399 N94-29300 Engines COMPRESSOR ROTORS Investigation of advanced counterrotation Made [AGARD-CP-536] p 404 NB4-29246 Verification of a three-dimensional viscous flow analysis configuration concepts for high speed turboprop systems. Flowfiek) prediction of NCHx) and smoke production in for a single stage compressor p410 N94-28976 Task 2: Unsteady ducted proptan analysis computer aircraft engines p 404 N94-29252 An elliptic-hyperbolic grid generation method and program users manual The effect of incomplete fuel-air mixing on the lean Bmit application to compressor flows p 395 N94-28981 [NASA-CR-187105] p 399 N94-29438 and emissions characteristics of a Lean Prevaporized COMPUTATIONAL FLUID DYNAMICS RNS optimization procedure for three-dimensional Premixed (LPP) combustor p40S N94-29265 Aerodynamic design using parallel processors composite velocity multi-block applications Computational and experimental results in high pressure [AD-A275470] p374 N94-28674 P412 N94-29534 combustions of H2/air and H2/O2/H2O A method for the modelling of porous and solid wind Tine-marching aeroelastic and spatial adaptation P406 N94-29268 tunnel walls In c^j^^jjutatiofMl fluid dynamics codon procedures on triangular and tetrahedral meshes using COMBUSTION CONTROL (NASA-CR-195699] p409 N94-28724 an unstructured-grid Euter method p379 N94-29877 Evaluation of the transient operation of advanced gas Proceedings of the 10th NAL Symposium on Atfcraft Aircraft aerodynamics with deflected jets in ground turbine combustors p397 N94-29269 Computational Aerodynamics effect P380 N94-29973 Fuel-rich catalytic combustion of a high density fuel (NAL-SP-19) p375 N94-2B946 Aeroaccustic sensitivity analysis and optimal (NASA-TP-32B1) p407 N94-29356 Engineering of systems for application of scientific aeroacousHc design of turbomachinery blades COMBUSTION PHYSICS computing in industry p41S N94-28947 [NASA-CR-195786] p 399 N94-30013 NumGnc&l fnodotung of turfairw cofflbustioo ctiflrnbofB Monte Carlo simulation or normal shock wave. Part 2: The design of a system of codes for industrial P396 N94-29254 VMS model and VSS model p409 N94-28948 calculations of flows around aircraft and other complex Numerical simulation of aerothermal characteristics in Variable soft sphere molecular model in the Monte Carto aerodynamic configurations gas turbine combustors with complex geometries simulation of air species p4O9 N94-28949 (PB94-125598J p 381 N94-30387 p396 N94-2925S Rarefied gas numerical wind tunnel. Part 8: HOPE Numerical investigation into high-angte-ot-attack Application of CFD in combustor design technology p 401 N94-28950 leading-edge vortex flow p396 N94-29256 Numerical simulation of arc heated wind tunnel flow [PB94-125564) p 381 N94-303B8 COMBUSTION PRODUCTS p402 N94-289S1 COMPUTATIONAL GRIDS Fuels and Combustion Technology for Advanced Aircraft Numerical simulation of unsteady aerodynamic heating Numeral simulation of steady Mach reflection by shock Engines induced by shock reflections p375 N94-28952 capturing schemes p 375 N94-289S3 (AGARD-CP-536] p 404 N94-2S246 Numerical simulation of steady Mach reflection by shock ENGRID: A graphical interactive code for the Ftowfield prediction of NO(x) and smoke production in capturing schemes p 375 N94-28953 computation of structured grids for blocked flow domains aircraft engines p404 N94-29252 Higher-order accurate numerical simulation of 3D p409 N94-289S6 The effect of incomplete fuel-air nixing oh the lean limit supersonic mixing layers p375 N94-28954 Numerical analysis of airfoil tor helicopter blade at high and emissions characteristics of a Lean Prevaporized Numerical simulation of aerotherrnodynamic heating of angle of attack using Navier-Stokes code Premixed (LPP) combustor p405 N94-29265 hypi sot »transportation vehicles p375 N94-28958 Ultra low NOW ultra lean gas turbine primary zones p375 N94-28955 Numerical simulation of supersonic Row around space with liquid fuels p 397 N94-29267 ENGRID: A graphical interactive code for the plane with engine installed p 376 N94-28961 Technology rigs: A tool for afterburner development computation of structured grids for blocked flow domains Numerical analysis of sonic boom in the near field P397 N94-29270 p409 N94-28956 p376 N94-28962 Pollutant emissions from and within a model gas turbine Numerical simulation of supersonic flow around space Three dimensional external flow computations using combustor at elevated pressures and temperatures plane with engine installed p376 N94-28961 prismatic grid p 410 N94-28979 p406 N94-29271 Numerical analysis of sonic boom in the near field Application of digital control theory to adaptive grid The nfluence of air dtttribubon on ftomcoenefly and p376 N94-28962 generation p415 N94-28980 pollutant formation in the primary zone of a tubular Role of computational fluid dynamics in aeronautical An elliptic-hyperbolic grid generation method and combustor p406 N94-29274 engineering. Part 10: Numerical analysis of flow around application to compressor flows p395 N94-28981 Research and development of ramjets/ramrockets. Part 2-O multielement HID p410 N94-28964 Time-marching aeroelastic and spatial adaptation 1: Integral solid propeOant ramrockets Numerical solution of inverse problem in procedures on triangular and tetrahedral meshes using p398 N94-29294 aerodynamics p376 N94-2896S an unstructured-grid Euter method p 379 N94-29877 Fuel-rich catalytic combustion of a high density fuel Code development tor hypersonic real-gas flow COMPUTER AIDED DESIGN [NASA-TP-3281J p 407 N94-29356 simulations toward the design of space vehicles, part 2 Aerodynamic design using parallel processors Fire behavior of aeronautical materials p376 N94-28966 [AD-A275470] p 374 N94-28674 (REPT-932-600-105] p 408 N94-28457 Three dimensional simulation of compressible flow Thermal/structural tailoring of engine blades A study of tow emissions gas turbine combustions induced by a high-speed train moving into a tunnel (T/SEAEBL). Theoretical manual [NASA-CR-195763] p 399 N94-29860 p376 N94-2B967 [NASA-CH-194462] p 409 N94-28815

A-5 COMPUTER DESIGN SUBJECTINDE

Modification of ACSYNT aircraft computer program for CONSTRUCTION Acoustic emission monitoring of aging ajrcra preliminary design Study of bridge design and technology structures [NASA-CR-195737] p 390 N94-28817 [PB94-137916] P373 N94-29160 [DREP-93-17] P 393 N94-3012 Procedural guide for modelling and analyzing the flight Rooftop GffiGrQfincy heliports Enhanced fatigue crack detection in aging aircraft usir characteristics of a helicopter design using flightlab [DOT/FAA/RD-93/2] p 402 N94-29754 continuous acoustic emission monitoring [DHEP-93-16] P393 N94-3013 [AD-A275077] p 391 N94-2B870 CONTINUOUS WAVE RADAR Application ol flow field simulation to turbine vane Radar jet engine health monitoring project CRACKING (FRACTURING) Full-scale testing and analysis ol curved aircraft fuselag design p395 N94-2897B [ASSGI-301) p400 N94-30130 panels Exploring ODES as a tool for determining limits of CONTRAROTATING PROPELLERS [AD-A275666] P 390 N94-2865 achievable performance in aircraft design Investigation of advanced counterrotation blade CRACKS (AD-A275359) p 391 N94-28998 configuration concepts for high speed turboprop systems. Development of Alternating Current Potential Oro Calculus.of variations applied to 2D multi-point airfoil Task 2: Unsteady ducted preplan analysis computer (ACPD) procedures for crack detection in aluminum aircrai program users manual [P894-125457] p 381 N94-30401 (NASA-CR-187105] p 399 N94-29438 COMPUTER DESIGN [AD-A275755] P 408 N94-2864 CONTROL SIMULATION How to control the increase in the complexity of civil Dynamic fracture mechanics analysis tor an eag Procedural guide for modelling and analyzing the flight aircraft co-board systems P 394 N94-29316 delamination crack characteristics of a helicopter design using flightlab COMPUTER NETWORKS [NASA-TM-109106] p417 N94-298S [AD-A275077] p 391 N94-28870 The Common Modular Simulator (CMS): An architecture CRASHWORTHINESS test bed tor future advanced ATM systems Simulation of fully automated air traffic control Crashworthiness analysis of commuter aircraft seat p388 N94-29582 concepts P386 N94-29569 [AD-A275B89] P 382 N94-2879 COMPUTER PROGRAMS CONTROL SURFACES CROSS FLOW Modification of ACSYNT aircraft computer program for Experimental investigation of three-dimensional The mixing process in the quenching zone of thi pFBiinunsiy do sign vortex-airfoil interaction in a supersonic stream rich-lean-combustion concept P 407 N94-2928 [NASA-CR-195737] p 390 N94-28817 [AD-A275107] p374 N94-28899 Long-wavelength asymptote of unstable crossflot Advanced fuel properties: A computer program for Numerical study of the trailing vortex of a wing with modes, including the effect of surface curvature estimating property values wing-tip blowing [NASA-CR-4579] P412 N94-294S [AD-A275248) p 403 N94-28901 (NASA-CR-195803] p 378 N94-29760 CURVED PANELS Investigation of advanced counterrotafon blade CONTROL SYSTEMS DESIGN Full-scale testing and analysis of curved aircraft tuselagi configuration concepts for high speed turboprop systems. Intelligent systems for air space control and panels Task 2: Unsteady ducted preplan analysis computer management p384 N94-29560 (AD-A275666) p 390 N94-28651 program users manual Decoupled flight control system design using me singular CYLINDRICAL ANTENNAS [NASA-CR-187105] p 399 N94-29438 perturbation method p400 N94-29B50 Theoretical and experimental study of a cytindrica miciosliip antenna Software Management Environment (SME) concepts CONTROL THEORY [REPT-932-440-109] P 412 N94-29456 and architecture, revision 1 Application of digital control theory to adaptive grid [NASA-CR-1B9293J p416 N94-29727 generation p415 N94-28980 Aeroacoustic sensitivity analysis and optimal Air traffic mflnsgenient AS pnooipled mt^oUflbOft aeroacousfic design of turbomachinefy blades between intelligent agents p384 N94-29562 [NASA-CR-195786) p 399 N94-30013 The design of a system of codes for industrial Decoupled fbghl control system dosign using the smguter calculations of flows around aircraft and other complex perturbation method p400 N94-28850 Full-scale testing and analysis of curved aircraft fuselage aerodynamic configurations CONTROLLABILITY panels (AD-A275666) p 390 N94-28657 (PB94-125S98] P381 N94-30387 Exploring ODES as a tool for determining limits of COMPUTER SYSTEMS PROGRAMS achievable performance in aircraft design Asphattc concrete performance under heavy tightei specifications for complex systems' [AD-A275359] p 391 N94-28998 aircraft loading p400 N94-29317 CONTROLLERS [AD-A275046] p 402 N94-29151 Ada run time system certification tor avionics Exploring ODES as a tool for detaiiming limits of DAMAGE ASSESSMENT applications p39« N94-29332 achievable performance in aircraft design Cockpit video: A low cost BOA source Integrated formal verification and validation of safety [AD-A275359] p 391 N94-28998 [AD-A275228] p 395 N94-2938S critical software p416 N94-29338 Integrated proputsion-airfrarne dynamics and control DATA ACQUISITION COMPUTER VISION p392 N94-29854 Los Angeles international airport instrument landing Airside ground movements surveillance Application of fusy logK to the Mjuliiil of wind tunnel system approach data collection and reduction, phase 1 p 388 N94-29585 settling chamber temperature [AD-A275115] p 383 N94-28914 COMPUTERIZED SIMULATION [NASA-TM-109105] p 402 N94-30200 User's manual for the model interface and plugboard Modification of ACSYNT aircraft computer program (or COOLANTS cabinets in the 14- by 22-foot subsonic tunnel prsbnviBfy design Research and dovekjpiiienl of high thermal stability [NASA-TM-109062] p 381 N94-30176 [NASA-CR-195737] p 390 N94-28817 fuels p405 N94-29261 DATABASES A non-*near simulation tor an autonomous unmanned COOLING SYSTEMS Los Angeles ilia national airport instrument landing air vehicle Endothermc fuels tor hypersonic aviation 'system approach data collection and reduction, phase 1 [AD-A275062] p 391 N94-29200 P407 N94-292B5 [AD-A275115] p383 N94-28914 Ted.TOlogy rigs: A tool for afterburner development CORIOUS EFFECT DATA INTEGRATION p397 N94-29270 Strnti&nty between turbulent flows through curved pipe ACCS Surveillance Explo tory Prototype (ASEP) Pollutant emissions from and within a model gas turbine and orthogonal rotating pipe P410 N94-28986 p412 N94-29566 combustor at elevated pressures and temperatures CORROSION DATA LINKS P406 N94-29271 Dual-Band Infrared (DBIR) imaging inspections of Boeing Simulation of tuDy automated air CUflUUl Scramjet CFD methods and analysis. Part 2: Scramiet 737 and KC-135 aircraft panels concepts p 386 N94-29569 CFD analysis. Numerical simulation of supersonic mixing (DE94-005700) p 374 N94-29842 DATA RECORDING and combustion applied to scramjet combustor COST ANALYSIS Cockpit video: A low cost 6DA source p399 N94-29300 Aircraft age impact on individual operating and support [AD-A275228] p 395 N94-29389 Testing Operational Flight Programs (OFPs) cost elements DATA REDUCTION p416 N94-29337 [AD-A275739] p 373 N94-28732 Los Angeles international airport instrument landing Simulation of fully automated air traffic control COST ESTIMATES system approach data collection and reduction, phase 1 concepts p386 N94-29569 Demonstration of improved software support labor [AD-A275115] p 383 N94-28914 Numerical study of the trailing vortex of a wing with estimation for Air Force operational fliylil programs through Correction of X hot-wire measurements tor gradients wing-tip blowing functional orientation normal to the plane of the wires [NASA-CR-195803] p 378 N94-29760 [AD-A275789] p373 N94-28743 [PB94-125473] p402 N94-30399 CONCRETES COUNTERROTATION DATA SYSTEMS AsphalDc concrete performance under heavy fighter Design and fabrication of forward swept counter? otam i User's manual for the model interface and plugboard aircraft loading blade configuration tor wind tunnel testing cabinets in the 14- by 22-foot subsonic tunnel [AD-A275046] p 402 N94-29151 [NASA-CR-194868] p 401 N94-28510 (NASA-TM-109062) p 381 N94-30176 CRACK INITIATION Cot in ibulions of BLR to air traffic capacity enhancement DECISION MAKING Development of Alternating Current Potential Drop within a terminal area p385 N94-29567 tntormation presentation for expert systems in future (ACPD) procedures for crack detection in aluminum aircraft CONFERENCES fighter auuall [AD-A275126] p 394 N94-29005 Fuels and Combustion Technology tor Advanced Aircraft (ADA275755] p408 N94-28646 Advances in development capabilities for intelligent air Engines CRACK PROPAGATION traffic management systems p 384 N94-29559 [AGARO-CP-538] p4O4 N94-29246 Development of Alternating Current Potential Drop Aerospace Software Engineering tor Advanced Systems (ACPD) procedures for crack detection in aluminum aircraft Air traffic management as principled negotiation Architectures between intelligent agents p 384 N94-29562 [AGARD-CP-54S] p415 N94-2931S (AOA275755) P 408 N94-28646 Decision Making Aids (DMA) in on-line ATC systems Machine Intelbgence in Air Traffic Management Putt-scale testing and analysis of curved aircraft fuselage p386 N94-29570 (AGARD-CP-538J P383 N94-29558 panels Cognitive approach to specifications on air traffic CONFIGURATION INTERACTION (AD-A275666) P 390 N94-28657 controllers' dnci*uon assistance systems Numerical study on the interaction between ccramjet Dynamic fracture mechanics analysis for an edge P386 N94-29571 engne modules caused by thermal choke delamination crack DAISY: A decision aid for an air situation interpretation p395 N94-28960 [NASA-TM-109106] p417 N94-29856 system p386 N94-29574

A-6 ERRORS SUBJECTINDEX

DEFLECTION DISPLAY DEVICES Potential hazards of magnetic resonance tmagers to Structural/aerodynamic Made analyzer (SAB) user's Information presentation tor expert systems in future emergency medical sen/ice helicopter operations guide, version 1.0 fighter aircraft [DOT/FAA/RD-92/15] P 382 N94-29882 [NASA-CR-194460] p395 N94-29103 [AD-A275126] P 394 N94-29005 ENDOTHERMIC FUELS DEGREES OF FREEDOM A comparison of three aircraft attitude display symbology Fuels combustion research A non-linear simulation lor an autonomous unmanned structures IAD-A275122] P 404 N94-29004 air vehicle [AD-A275172] P 394 N94-29048 Endothermic fuels for hypersonic aviation [AD-A275062] p 391 N94-29200 DRAG REDUCTION p 407 N94-29285 Six-degree-ol-freedom parallel minimanipulator with Numerical analysis of supersonic transport wings ENERGY ABSORPTION p375 N94-28959 three inextenstble ftmbs Landing gear energy absorption system INASA-CASE-GSC-13485-1] p413 N94-29726 DRONE AIRCRAFT INASA-CASE-MSC-22277-1] p411 N94-29448 HATT-X: A high performance flying laboratory tor ENERGY DISSIPATION DEHVDROGENATION autonomous unmanned aircraft research and Study on mixing and injection of hydrogen into a Endothermic fuels for hypersonic aviation development P 393 N94-30293 p407 N94-29285 supersonic now p377 N94-28975 DROPS (LIQUIDS) DELAHINATING Numerical simulation of aei other mal characteristics in ENERGY TRANSFER Dynamic fracture mechanics analysis tor an edge gas turbine combustors with complex geometries Turboramjet engines: Types and performances delamtnaoon crack p 396 N94-292S5 p 398 N94-29293 [NASA-TM-109106] p 417 N94-29856 DUCTED FANS ENGINE AIRFRAME INTEGRATION DELTA WINGS Investigation of advanced counterrotation blade Numerical study on the interaction between scramjet Numerical investigation into Mgh-angle-of-attack configuration concepts lor high speed turboprop systems. engine modules caused by thermal choke leading-edge vortex flow Task 2: Unsteady ducted propfan analysis computer p395 N94-28960 [PB94-125564J p381 N94-30388 program users manual Numerical simulation of supersonic flow around space DEPOSITION [NASA-CR.187105] p 399 N94-29438 plane with engine installed p376 N94-2B961 Development of global/chemistry model for Jet-fuel DUCTED FLOW ENGINE CONTROL thermal stability based on observations from static and Ducted kerosene spray flames p 407 N94-29276 Research and development of ramjets/ramrockets. Part flowing experiments p 405 N94-29262 Scramjet CFD methods and analysis. Part 1: Scramjet 2: Integral liquid fuel ramjets p 398 N94-29297 DESCENT TRAJECTORIES CFD methods. Numerical simulation of the flow in scramjet ENGINE COOLANTS Advanced air traffic control and flight management duct p398 N94-29296 Endothermic fuels tor hypersonic aviation system concepts p 387 N94-29576 DUCTS p407 N94-29285 DESIGN ANALYSIS Introduction and overview of research and development ENGINE DESIGN A design of third-generation airfoils lor helicopter rotor of solid propellent ramrockets. liquid fuel ramjets and Fuels and Combustion Technology for Advanced Aircraft blades using Navier-Stokes p 391 N94-28957 experimental hydrogen ram combustors Engines Recent CFD applications in small gas turbine combustion p398 N94-29292 [AGARD-CP-536] p 404 N94-29246 systems development p396 N94-29257 DURABILITY Combustion technology needs tor advanced high DETECTION Rote of rricrostructure on the fatigue durability of pressure cycte engines p404 N94-29248 aluminum aircraft alloys Development of Alternating Current Potential Drop High temperature fuel requirements and payoffs (AD-A275B14] p 403 N94-28830 (ACPD) procedures for crack detection in aluminum aircraft p405 N94-29259 panels DYNAMIC CONTROL Design aspects in small aircraft gas turbine fuel [AD-A275755] p 408 N94-28646 Integrated proputsion-airtrame dynamics and control injectors p397 N94-29264 p392 N94-29854 DETERIORATION Technology rigs: A tool for afterburner development DYNAMIC LOADS p397 NM-29270 Design aspects in small aircraft gas turbine fuel Asphaltic concrete performance under heavy fighter injectors p 397 N94-29264 Pollutant emissions from and within a model gas turbine aircraft loading combustor at elevated pressures and temperatures DIFFERENTIAL EQUATIONS (AD-A275046] p 402 N94-29151 p 406 N94-29271 A free-wake Euter and Navier-Stokes CFD method and DYNAMIC MODELS Reduction of NO(x) by fuel-staging in gas turbine . its application to helicopter rotors including dynamic stall Miniature ttnear-to-rotary motion actuator engines: A comratment to the future (AD-A27S416) p 377 N94-29197 p413 N94-29647 p406 N94-29272 DIFFRACTION DYNAMIC PRESSURE Spray combustion experiments and numerical Backscatter haze device for measurement of haze in Low-speed longitudinal aerodynamic characteristics of predictions p407 N94-29277 aircraft transparencies a flat-plate plantorm model of an advanced tighter The mixing process in the quenching zone of the (AD-A275127) p 391 N94-29042 configuration rich-tean-combustion concept p 407 N94-29281 DIGITAL NAVIGATION [NASA-TM-109045] p377 N94-29443 QAM experimental turboramjets p399 N94-29299 Automatic control steps tor aircraft taxi guidance DYNAMIC RESPONSE Scramjet CFD methods and analysis. Part 2: Scramjet p388 N94-29584 Turtaomachinery forced response prediction system CFD analysis. Numerical simulation of supersonic mixing DIGITAL SIMULATION (FREPS): User's manual and combustion applied to scramjet combustor Proceedings of the 10th NAL Symposium on Aircraft [NASA-CR-194465J p 411 N94-29104 p399 N94-29300 Computational Aerodynamics DYNAMIC STRUCTURAL ANALYSIS ENGINE INLETS (NAL-SP-19) p375 N94-28946 Turbomachinery forced response prediction system Introduction and overview of research and development Engineering of systems lor application of scientific (FHEPS): User's manual of sottd propellent ramrockets. liquid fuel ramjets and computing in industry p41S N94-2B947 [NASA-CR-194465] p411 N94-2S104 experimental hydrogen ram combustors Monte Carlo simulation or normal shock wave. Pan 2: Experimental validation of finite element and boundary p398 N94-29292 VMS model and VSS model p409 N94-28948 element methods tor uieOctiiiy structural vibration and Turboramjet engines: Types and performances Variable son sphere molecular model in the Monte Carlo radiated noise p398 N94-29293 simulation of air species p 409 N94-28949 [NASA-CR-4561] p412 N94-29S52 ENGINE TESTING LABORATORIES Rarefied gas numerical winct tunnel. Part 8: HOPE Dynamic fracture mechanics analysis for an edge The nozzle acoustic test rig: An acoustic and p 401 N94-289SO delamination crack aerodynamic tree-jet facility Numerical simulation of arc heated wind tunnel flow [NASA-TM-109106] p417 N94-29856 (NASA-TM-106495) p 401 N94-28749 p402 N94-28951 DYNAMIC TESTS ENGINE TESTS Numerical simulation of unsteady aerodynamic heating Crashworfhness analysts of commuter aircraft seats Research and development of high thermal stability induced by shock reflections p375 N94-2B952 [AD-A275889] p 382 N94-28799 fuels p405 N94-29261 Numerical simulation of steady Mach reflection by shock Technology rigs: A tool for afterburner development capturing schemes p 375 N94-28953 p397 N94-29270 Higher-order accurate numerical simulation of 3D QAM experimental turboramjets p 399 N94-29299 supersonic mixing layers p 375 N94-28954 Some problems of scramjet propulsion tor aerospace Numerical simulation of aenjthermodynamic heating of ELASTIC WAVES planes. Part 2: Scramjet Development and test hypersonic space transportation vehicles Method for cancelling expansion waves in a wave problems p399 N94-29301 p375 N94-2B955 rotor ENTRANCES Transonic expanding now through anally symmetric [NASA-CASE-LEW-1521B-2] P 413 N94-29740 Three dimensional simulation of compressible flow orifices p410 N94-2B985 ELECTRIC WIRE induced by a high-speed train moving mto a tunnel Similarity between turbulent flows through curved pipe NAVAIR aircraft wiring standardization and qualification p376 N94-28967 and orthogonal rotating pipe p4lO N94-28986 program p408 N94-26704 ENVIRONMENT EFFECTS Performance evaluation of the NWT with parallel Organized wiring systems p 408 N94-28705 On the effect of emissions from aircraft engines on the Fortran p415 N94-28992 state of the atmosphere p 414 N94-29247 ELECTROMAGNETIC FIELDS A method of user interface tor NWT EQUATIONS OF MOTION Potential hazards of magnetic resonance tmagers to p415 N94-28993 A non-linear simulation for an autonomous unmanned Ktcal service helicopter operations DIGITAL SYSTEMS air vehicle [DOT/FAA/HD-92/15] p382 N94-29862 How to control the increase in the complexity of cnnl [AD-A275062] p 391 N94-29200 •reran on-board systems p394 N94-29316 EMBEDDED COMPUTER SYSTEMS ERROR ANALYSIS On ground system integration and testing: A modem Experiences with the HOOD design method on avionics Los Angeles international airport instrument landing approach p394 N94-29334 software development p415 N94-29325 system approach data collection and reduction, phase 1 DIRECTIONAL STABILITY Integrated formal verification and validation of safety [AD-A275115] p 383 N94-28914 An experimental investigation of the effect of leading critical software p416 N94-29338 ERRORS edge extensions on directional stability and the EMERGENCIES Los Angeles international airport instrument landing effectiveness of torebody nose strakes Rooftop emergency heUports system approach data collection and reduction, phase 1 p400 N94-29728 [DOT/FAA/RD-93/2] p 402 N94-29754 (AD-A275115) p383 N94-2B914

A-7 SUBJECTINDEX ESTIMATING

ESTIMATING FATIGUE (MATERIALS) FLARED BODIES Advanced fuel properties: A computer program tor Effects of repair on structural integrity An experimental and theoretical study of the estimating property values [AD-A275756] p 390 N94-28647 aerodynamic characteristics of some generic missile [AD-A275248J p 403 N94-28901 A moment plotting method for characterizing aircraft concepts at Mach numbers from 2 to 6.8 EULER EQUATIONS OF MOTION fatigue data population distributions (NASA-TM-109110] P378 N94-29473 ENGRID: A graphical interactive code for the IAD-A275500J p 390 N94-28660 FLAT PLATES Low-speed longitudinal aerodynamic characteristics of computation of structured grids tor blocked flow domains FATIGUE LIFE p409 N94-28956 A moment plotting method for characterizing aircraft a flat-plate planform model of an advanced fighter Numerical analysis of supersonic transport wings fatigue data population distributions configuration p375 N94-289S9 [AD-A275500] . . ,. . p 390 N94-28660 [NASA-TM-109045] p 377 N94-29443 FLEXIBLE WINGS Numerical analysts of sonic boom in the near field Cold expansion and interference for extending the Steady pressure measurements on an Aeroelastic p376 N94-2S962 fatigue life of mufti-layer metal joints Research Wing (ARW-2) Investigation of advanced counterrotation blade [AD-A274982) P 410 N94-29091 [NASA-TM-109046] P 374 N94-28658 configuration concepts for high speed turboprop systems. The effect of mechanical paint stripping on the fatigue Task 2: Unsteady ducted pro plan analysis computer FLIGHT CONDITIONS and fracture of thin aluminum airplane skin A non-linear simulation tor an autonomous unmanned program users manual P408 N94-29900 (NASA-CR-187105) p399 N94-29438 air vehicle Time-marching aeroelastic and spatial adaptation FATIGUE TESTS (AD-A275062J p 391 N94-29200 Cold expansion and interference for extending the procedures on triangular and tetrahedral meshes using Extremely Low Visibility IFR Rotorcraft Approach an unstructured-grid Euler method p 379 N94-29877 fatigue life of multi-layer metal joints (ELVIRA) operational concept development. Volume 1: (AD-A274982) p 410 N94-29091 Numerical investigation into high-angle-of-attack Executive Summary leading-edge vortex flow FEASIBILITY ANALYSIS (DOT/FAA/RD-94/1.IJ p 389 N94-30189 [PB94-125564) p381 N94-30388 KC-135 cockpit modernization study and crew reduction FLIGHT CONTROL EVACUATING (TRANSPORTATION) feasibility demonstration Exploring ODES as a tool for determining limits of Aircraft evacuations: The effect of a cabin water spray [AD-A275230) p 392 N94-29391 achievable performance in aircraft desiyn system upon evacuation rates and behaviour FEEDBACK " ' ' (AD-A275359) p 391 N94-28998 [CAA-PAPER-93008] p 393 N94-29887 Integrated proputston-eirframe dynamics and control Flight command software development: RAFALE EVALUATION P392 N94-29854 studies p 415 N94-29320 NAVAIH aircraft wiring standardization and qualification FEEDBACK CONTROL On ground system integration and testing: A modem program p 408 N94-28704 Closed loop vibrational control: Theory and approach p 394 N94-29334 EXHAUST EMISSION applications Decoupled flight control system design using the singular On the effect of emissions from aircraft engines on the (AD-A275451) p400 N94-28632 perturbation method P 400 N94-29850 state of the atmosphere p 414 N94-29247 Decoupled flight control system design using the singular A novel approach to noise-filtering based on a Ultra tow NO(x) ultra lean gas turbine primary zones perturbation method p400 N94-29850 gam-scheduling neural network architecture with liquid fuels p 397 N94-29267 tntBor&tod propuJsKxvfliilrflnw dynflnucs &nd control [NASA-TM-106563) p 401 N94-30204 Pollutant emissions fiuni and withm a model gas turbine P392 N94-29854 FLIGHT ENVELOPES combustor at elevated pressures and temperatures FIBER COMPOSITES Integrated piopulsion-atffitfim dynamics and control p406 N94-28271 SorviOB bto prediction of oornposrto structures through p392 N94-29854 Reduction of NO(x) by fuel-staging in gas turbine fiber tsstinQ FLIGHT HAZARDS engines: A commitment to the futue [AD-A275661] p 403 1494-28654 Potential hazards of magnetic resonance frnaoers to p406 N94-29272 Prediction of stress-strain response of emergency medical service helicopter operations The influence of air distribution on homogeneity and SCS-6/Timetal-21S subjected to a hypersonic flight [DOT/FAA/RD-92/15] p 382 N94-29862 pollutant formation in the primary zone of a tubular profile FLIGHT MANAGEMENT SYSTEMS combustor p 406 N94-29274 [NASA-TM-109026] p 403 N94-2B823 Machine Intelligence in Air Traffic Management Effects of hydrogen addition on pollutant emissions in FIBER STRENGTH (AGAROCP-538) p 383 N94-29558 a gas turbine combustor p 406 N94-29275 Sflfety cohflncemcnt of composrtBS vis periodic proof Advances in development capabilities for intelligent air Spray combustion enpeiimems and numerical testing traffic management systems p 384 N94-29559 predictions p 407 N94-29277 (AD-A275662) p 403 N94-2865S Intelligent systems for air space control and EXHAUST GASES FKtHTER AIRCRAFT management p 384 N94-29560 Ultra low NCXx) ultra lean gas turbine primary zones Inloiiiiation presentation for expert systems in future Use of advanced technologies in ATM (air traffic with liquid fuels p397 N94-29267 fiylilei aircraft management) domain p 384 N94-29561 [AD-A275126] p 394 N94-29005 Reduction of NO(>) by fuel-staging in gas turbine Air traffic management as principled negotiation Asphaltic concrete performance under heavy fighter engines: A commitment to the future between inteUigenl agents p 384 N94-29562 p406 N94-29272 aircratl loading [AD-A275048] p402 N94-29151 GPS/GNSS tor ATM p385 N94-29565 Effects of hydrogen addition on pollutant emissions in Contributions of BLR to air traffic capacity enhancement a gas turbine combustor p 406 N94-29275 Low-speed longitudinal aerodynamic characteristics of a flat-plate planform model of an advanced fighter within a terminal area p 385 N94-29567 Sprsy combustion fixpcu in'ionts end nurnonc&l configuration Design of Center-TRACON Automation System predictions p407 N94-29277 (NASA-TM-109045) p 377 N94-29443 P385 N94-29568 A study of low 6fra&sions Q&S turbino combustions Development of a method to predict transonic limit cycle Advanced air traffic control and flight management (NASA-CR-195763) p 399 N94-29860 oscillation characteristics of fighter aircraft (continued) system concepUi p 387 N94-29576 EXHAUST NOZZLES [NLR-TP-921S6-U] p393 N94-30342 Opportunities for ntegrattng the aiiuaft FMS, The nozzle acoustic test rig: An acoustic and FINITE DIFFERENCE THEORY aeronautical operational control centers, and future air aerodynamic tree-fet facility Numerical study of the trailing vortex of a wing with traffic management systems in oceanic airspace (NASA-TM-106495] p 401 N94-28749 wing-tip blowing P387 N94-29577 EXPERT SYSTEMS [NASA-CO-195803] p 378 N94-29760 Profile negotiation: An air/ground automation integration Information presentation tor expert systems in future Unsteady transonic aerodynamics in frequency domain concept for managing arrival traffic p 387 N94-29578 fighter aircraft tor flutter analysis p379 N94-29879 Air-ground integration of the ATM system in PHARE (AD-A275126] p 394 N94-29005 Aeroacoustic sensitivity analysts and optimal P388 N94-29579 GPS/GNSS for ATM p385 N94-29565 •nirmi LKintM design of tuitionlachuiory blades [NASA-CR-195786] p 399 N94-30013 Expaimental flight management system DAISY: A decision aid for an air situation interpretation P388 N94-29580 system p 386 N94-29574 FINITE ELEMENT METHOD Experimental validation of finite element and boundary The PHARE advanced tools p388 N94-29581 element methods tor predicting structural vibration and FUGHT PATHS Decision Making Aids (DMA) in on-line ATC systems (NASA-CR-4561] p412 N94-29SS2 P386 N94-29570 Aircraft system aft telescope cavity configuration study F-22 AIRCRAFT Advanced air traffic control and flight management for Stratospheric Observatory tor Infrared Astronomy A disciplined i ch to software test and evaluation system concepts p387 N94-29576 (SOFIA), phase 2 p416 N94-29339 Profile negotiation: An air/ground automation integration [NASA-CR-194266] p 392 N94-29685 FABRICATION concept for managing arrival traffic p 387 N94-29578 Dynamic fracture mechanics analysis for an edge Air-ground integration of the ATM system in PHARE Design and fabrication of forward-B wopt counterrotation delanitnatKK i crack p 388 N94-29579 blade configuration for wind tunnel testing (NASA-TM-109106) p417 N94-29856 The PHARE advanced tools p 388 N94-29581 [NASA-CR-194868] p 401 N94-2S510 Rotorcrafl airframe structural optimization for vibration FALKNER-SKAN EQUATION and dynamc suuss reduction ndudng damping FUGHT PLANS Experiments and theoretical considerations legarduig treatment p392 N94-29878 ACCS Surveillance Exploratory Prototype (ASEP) the allowable roughness height in laminar flow FIRE EXTINGUISHERS P412 N94-29566 [PB84-12S556] p38t N94-30389 Aircratl evacuations: The effect of a cabin water spray Opportunities tor integrating the aircraft FMS. FASTENERS system upon evacuation rates and behaviour aeronautical operational control centers, and future air Development of Alternating Current Potential Drop (CAA-PAPER-93008] p 393 N94-29887 traffic management systems in oceanic airspace (ACPD) procojuro G for crack detection in aluminum avcraft FIRES P387 IM94-29577 Rooftop emergency heCporo FUGHT SAFETY (AO-A275755] p 408 N94-28646 (DOT/FAA/RD-93/2] p402 N94-29754 Crashworthiness analysis of commuter aircraft seats Cold expansion and interference for extending the FLAME STABILITY [AD-A2758SSJ p 382 N94-28799 fatigue ife of multi-layer metal joints Ultra low NO(x) ultra lean gas turbine primary zones Integrated formal verification and validation of safety [AD-A274982] p410 N94-29091 with liquid fuels p397 N94-29267 critical software p 416 N94-29338

A-8 SUBJECTINDEX GAS TURBINES

Aircraft accident/incident summary report In-flight loss FLOW MEASUREMENT The effect of incomplete fuel-air mixing on the lean limit of control, leading to forced landing and runway overrun. Correction of X hot-wire measurements tor gradients and emissions characteristics of a Lean Prevaporized Continental Express. Inc.. N24706 Embraer EMB-120 RT. normal to the plane of the wires Premixed (LPP) combustor p 405 N94-29265 Pine Bluff. Arkansas. 29 April 1993 (PB94-125473] p402 N94-30399 Evaluation of the transient operation of advanced gas (PB94-910404] p 382 N94-29402 FLOW STABILITY turbine combustors p 397 N94-29269 The 1993 Federal Aviation Administration Aviation Long-wavelength asymptotjcs of unstable crossflow FUEL INJECTION System Capital Investment Plan p 383 N94-29445 modes, including the effect of surface curvature Fuel injector design tor high temperature aircraft Interactive analysis and planning tools for air traffic and [NASA-CR-4579] p 412 N94-29460 engine p 396 N94-29263 airspace management p 386 N94-29573 FLOW VELOCITY Design aspects in small aircraft gas turbine fuel DAISY: A decision aid for an air situation interpretation Correction of X hot-wire measurements for gradients injectors p397 N94-29264 system p386 N94-29574 normal to the plane of the wires Effects of hydrogen addition on pollutant emiss^ifii in [PB94-125473] P402 N94-30399 Development of precision runway monitor system tor a gas turbine combustor p 406 N94-29275 FLOW VISUALIZATION increasing capacity of parallel runway operations Ducted kerosene spray flames p 407 N94-29276 p389 N94-2958T Holographic interterometry: A user's guide Investigation of the two-phase flow in a research Extremely Low Visibility IPR Rotorcraft Approach [DE94-O03136] p 408 N94-28466 combustor under reacting and non-reacting conditions (ELVIRA) operational concept development Volume 1: An experimental investigation of the effect of leading p411 N94-29282 Executive Summary edge extensions on directional stability and the IDOT/FAA/RD-94/1.1] p 389 N94-30189 effectiveness of torebody nose strakes FUEL SPRAYS FLIGHT SIMULATION p 400 N94-29728 Ducted kerosene spray flames p 407 N94-29276 Modification of ACSYNT aircraft computer program for Wall pressure fluctuations in the reattachment region Spray combustion experiments and numerical protirntnsry dcsiQn of a supersonic tree shear layer predictions p407 N94-29277 (NASA-CR-195737) p 390 N94-28817 (NASA-CR-195790) p 379 N94-29920 FUEL SYSTEMS Procedural guide tor modelling and analyzing the flight FLUID FLOW High temperature fuel requirements and payoffs characteristics of a helicopter design using fligmiab Holographic interterometry: A user's guide P405 N94-29259 [AD-A27S077] p 391 N94-28870 (DE94-003136) p 408 N94-28466 Research and development of high thermal stability A non-linear simulation for an autonomous unmanned FLUID JETS fuels p 405 N94-29261 air vehicle Liquid atomization in supersonic flows Reduction of NO(x) by fuel-staging in gas turbine p 414 N94-29839 (AD-A275062J p 391 N94-29200 engines: A commitment to the future Particle kinetic simulation of high altitude hypervetocity FLUTTER ANALYSIS p406 N94-29272 Unsteady transonic aerodynamics in frequency domain flight FUNCTIONAL ANALYSIS tor flutter analysis p 379 N94-29879 (NASA-CR-194535) p 379 N94-29893 Engineering of systems for application of scientific Development of a method to predict transonic limit cycle FLIGHT SIMULATORS computing in industry p415 N94-28947 oscillation characteristics of fighter aircraft (continued) Six-degree-ot-treedom parallel minimanipulator with FUNCTIONAL DESIGN SPECIFICATIONS (NLR-TP-92156-U) p393 N94-30342 three inextensible Bmbs Engineering of systems tor application of scientific | NASA-CASE-GSC-13485-1] p413 N94-29726 FORCED VIBRATION computing in industry P415 N94-28947 Turbomacnmery forced response prediction system FLIGHT TESTS How to control the increase in the complexity of civil (FREPS): User's manual Acquisition, design modification, assembly, and ground aircraft 00-board systems P394 N94-29316 [NASA-CR-194465] p411 N94-29104 test of NPS Hummingbird remotely piloted helicopter FUSELAGES FORMALISM [AD-A275546] p 390 N94-28837 Closed loop vibrational control: Theory and Some problems of scratnjet propulsion for aerospace Flight command software development: RAFALE Studies p 415 N94-29320 planes. Part 2: Scramjet: Development and test [AD-A27S451] P400 N94-28632 FORTRAN problems p399 N94-29301 An analytical study of unsteady rotor/fuselage Performance evaluation of the NWT with parallel Testing Operational Flight Programs (OFPs) interaction in hover and forward flight Fortran p 415 N94-2B992 p416 N94-29337 P379 N94-29826 FRACTURE MECHANICS FLOW CHARACTERISTICS FUZZY SYSTEMS Role of microstructure on the fatigue durability of Study of bridge design and technology Application of fuzzy logic to the control of wind tunnel aluminum aircraft alloys IPB94-137916] p373 N94-29160 settling chamber temperature (AD-A27SB14) p 403 N94-28830 Recent CFD applications in small gas turbine combustion [NASA-TM-109105] p 402 N94-30200 systems development p396 N94-29257 Dynamic fracture mechanics analysis for an edge An experimental study of wing tip vortex in the near delamination crack wake of a rectangular wing [NASA-TM-109106] p 417 N94-29856 [AD-A275389] p 377 N94-29306 FRACTURE STRENGTH FLOW DISTRIBUTION Effects of repair on structural integrity GAS DISSOCIATION Code development for hypersonic real-gas flow (AD-A275756) p390 N94-28647 Models for vibration-dissociation coupling in simulations toward the design of apace vehicles, part 2 The effect of mechanical paint stripping on the fatigue high-temperature gases p4l3 N94-29675 p376 N94-28966 and fracture of ttwi aluminum airplane skin GAS GENERATORS Three dimensional simulation of compressible flow p408 N94-29900 Research and development of ramjets/ramrockets. Part induced by a high-speed train moving into a tunnel FREEFLOW 1: Integral aoUd propellant ramrockets p376 N94-28967 Low-speed longitudinal aerodynamic characteristics of P398 N94-29294 Transonic expanding flow through axially symmetric a flat-plate planform model of an advanced fighter GAS INJECTION orifices p410 N94-2898S configuration Study on mixing and injection ol hydrogen into a A free-wake Euter and Navier-Stokes CFD method and [NASA-TM-109045] p 377 N94-29443 supersonic flow P377 N94-28975 its application to helicopter rotors including dynamic stall FREE JETS Effects of hydrogen addition on pollutant emissions in (AD-A275416) p377 N94-29197 The nozzle acoustic test rig: An acoustic and a gas turbine combustor p 406 N94-29275 Flowfield prediction of NO(x) and smoke production in aerodynamic free-jet facility The mixing process in the quenching zone of the aircraft engines p404 N94-29252 [NASA-TM-106495] p 401 N94-28749 rich-lean-combustion concept p 407 N94-29281 Numerical modelling of turbine combustion chambers FUEL COMBUSTION GAS TURBINE ENGINES p3% N94-29254 Fuels combustion research Combustion technology needs for advanced high Pollutant emissions from and within a model gas turbine [AD-A275122] p 404 N94-29O04 pressure cycle engines p 404 N94-29248 combustor at elevated pressures and temperatures High temperature fuel requirements and payoffs p406 N94-29271 Fuels and Combustion Technology for Advanced Aircraft Engines p 405 N94-29259 The influence of air distribution on homogeneity and Design aspects in small aircraft gas turbine fuel (AGARD-CP-536] p404 N94-29246 pollutant formation in the primary zone of a tubular injectors p 397 N94-29264 combustor p406 N94-29274 Combustion technology needs for advanced high Pollutant emissions from and within a model gas turbine Time-resolved measurements in a three dimensional pressure cycle engines p 404 N94-29248 combustor at elevated pressures and temperatures model combustor p411 N94-29283 Computational and experimental results in high pressure P406 N94-29271 An experimental study of the flowfield on a semispan combustions of H2/air and H2/O2/H2O Reduction of NO(x) by fuel-staging in gas turbine rectangular wing with a simulated glaze ice accretion p406 N94-29268 engines: A commitment to trie future p378 N94-29674 Ducted kerosene spray flames p407 N94-29276 P406 N94-29272 An analytical study of unsteady rotor/fuselage Spray combustion experiments and numerical The influence of air distribution on homogeneity and interaction in hover and forward flight predictions p 407 N94-29277 pollutant formation in the primary zone of a tubular p379 N94-29826 Time-resolved measurements in a three dimensional combustor P406 N94-29274 Aircraft aerodynamics with deflected jets in ground model combustor p41l N94-29283 Effects of hydrogen addition on pollutant emissions in effect p380 N94-29973 Endothermic fuels tor hypersonic aviation a gas turbine combustor p 406 N94-29275 The 3-D LDV measurements on a 30-oegree swept wmg p407 N94-29285 A study of tow emissions gas turbine combustions with a simulated ice accretion [NASA-CR.195763] p 399 N94-Z9860 Research and development of ramjets/ramrockets. Part [NASA-CR-195327] p 380 N94-30124 GAS TURBINES 1: Integral solid propellant ramrockets The design of a system of codes for industrial Numerical modelling ol turbine combustion chambers p398 N94-29294 calculations of flows around aircraft and other complex P396 N94-29254 aerodynamic configurations Fuel-rich catalytic combustion of a high density fuel Numerical simulation of aerothermal characteristics in [PB94-12S598] p381 N94-30387 (NASA-TP-3281) p407 N94-29356 gas turbine combustors with complex geometries FLOW EQUATIONS A study of low emissions gas turbine combustions P396 N94-29255 The design of a system of codes for industrial [NASA-Cn-195763) p399 N94-29860 Application of CFD in combustor design technology calculations of flows around aircraft and other complex FUEL FLOW P396 N94-29256 aerodynamic configuratjons Fuel injector design tor high temperature aircraft Recent CFD applications in small gas turbine combustion (PB94-125598) p 381 N94-30387 engine p396 N94-29263 systems development p 396 N94-29257

A-9 GAS-LIQUID INTERACTIONS SUBJECTINDEX

Ultra low NOW ultra lean gas turbine primary zones HAZE HOLOGRAPHIC INTERFEROMETRY with liquid fuels p 39? N94-29267 Backscatter haze device tor measurement of haze in Holographic interferometry: A user's guide Computational and experimental results in nigh pressure aircraft transparencies IDE94-003136) P408 N94-28466 combustions of H2/air and H2/O2/H2O [AD-A275127] p 391 N94-29042 HOLOGRAPHY p406 N94-29268 HEAT TRANSFER Holographic interferometry: A user's guide Evaluation of me transient operation of advanced gas Code development for hypersonic real-gas flow fDE94O03136J P408 N94-28466 turbine combustore p 397 N94-29269 simulations toward the design of space vehicles, part 2 HORIZONTAL FLIGHT Pollutant emissions from and within a model gas turtxne p376 N94-28966 An analytical study of unsteady rotor/fuselage oombustor at elevated pressures and temperatures Particle kinetic simulation of high attitude nypervelocrty interaction in hover and forward flight p379 N94-29826 p406 N94-29271 fbp/nt A study of low emissions gas turbine combustions (NASA-Cfl-194535] P 379 N94-29893 HOT-WIRE FLOWMETERS Correction of X hot-wire measurements tor gradients >NASA-Cfl-195763) p 399 N94-29860 HELICOPTER DESIGN normal to the plane of the wires GAS-UOUID INTERACTIONS Procedural guide tor modelling and analyzing the flight [PB94-125473J P402 N94-30399 Liquid atomiZBtion in supersonic flows characteristics of a helicopter design using flightlab HOVERING p414 N94-29839 (AD-A275077] p 391 M94-28870 An analytical study of unsteady rotor/fuselage GENERAL AVIATION AIRCRAFT Helicopter mission and rotor performance optimization National Transportation Safety Board annual review of mtBractx^n in hover and forward flight with quasi-linear inflow theory p 392 N94-29594 aircraft accident data. US general aviation. 1990 p 379 N94-29826 [PB94-126869] p 382 N94-291B5 Rotorcraft euliame structural optimization for vibration HUMAN FACTORS ENGINEERING and dynamic stress reduction including damping GENERAL OVERVIEWS Information presentation tor expert systems in future treatment p392 N94-29878 Review of sonic fatigue technology fighter aircraft (NASA-CR-4587) p 417 N94-29407 HELICOPTER PERFORMANCE [AD-A275126] p 394 N94-2900S GIRDERS Closed loop wbrational control: Theory and A comparison of three aircraft attitude display symbotogy •Study of bridge design and technology applications structures [PB94-137916] p373 N94-29160 (AD-A275451) p400 N94-28632 [AD-A275172] p 394 N94-29O48 The 1993 Federal Aviation Administration Aviation GLOBAL POSITIONING SYSTEM Boundary layers induced by three-dimensional vortex Theoretical and experimental study of a cylindrical loops System Capital Investment Plan p 383 N94-2944S IIHUW&UII^ antenna (AD-A27567B) p408 N94-2B665 Aircratt evacuations: The effect of a cabin water spray system upon evacuation rates and behaviour (REPT-932-440-1091 p412 N94-29456 Procedural guide for modelling and analyzing the Right (CAA-PAPER-930081 p 393 N94-29887 Use of GPS in automated air traffic control characteristics of a helicopter design using ffightiab HUMAN PERFORMANCE p384 N94-29563 (AD-A27S077) p 391 N94-28870 Helicopter mission and rotor performance optimization Cognitive approach to specifications on air traffic GPS/GNSS for ATM p 385 N94-29565 with quasi-linear inflow theory p392 N94-29594 controllers' decision assistance systems The use of low cost differential mode GPS receivers HELICOPTER PROPELLER DRIVE p386 N94-29571 in unmanned vehicles p389 N94-30285 Experimental validation of finite element and boundary HUMAN TOLERANCES GOODNESS OF FIT element methods tor piudicling structural vibration and Crashworthiness analysis of commuter aircraft seats A moment plotting method for characterizing aircratt radiated noise (AD-A275889) p 382 N94-28799 tatjgue data population distributions [NASA-CR-4561] p412 N94-295K HUMAN-COMPUTER INTERFACE [AD-A275500) p 390 K94-28660 HELICOPTERS Evaluation of access/navigational features of a GRAPHICAL USER INTERFACE Ctosed loop vibrational control: Theory and graphical-user interface installed on a portable Evaluation of access/navigationaf features of a applications maintenance aid graphical-user interface installed on a portable (AD-A275451) p 400 N94-28632 [AD-A275791] p383 N94-2B744 maintenance aid Acquisition, design modification, assembly, and ground A method of user interface for NWT [AO-A27S791] p383 N94-28744 test of NPS Hummingbird remotely piloted helicopter P41S N94-28993 Considerations on graphical user interfaces for inteHigem [AD-A275546] p 390 N94-28837 Information pfestfcftlation for enpert systems in future ATM support systems p 386 N94-29572 Procedural guide tor modelling and analyzing the flight fighter aircraft GRID GENERATION (MATHEMATICS) characteristics of a helicopter design using flightJab IAD-A27S126) p394 N94-29005 ENGRID: A graphical interactive code for the [AD-A275077] p 391 N94-28870 Advances in development capabilities tor intelligent air computation of structured grids tor blocked flow domains Rooftop emergency heliports traffic management systems p 384 N94-29559 p409 N94-28956 [DCT/FAA/RD-93/2) p 402 NS4-297S4 Intelligent systems for air space control and Numerical analysis of airfoil for helicopter blade at high An analytical study of unsteady rotor/fuselage management p384 N94-29560 angle of attack using Navier-Stokes code intBucliofi •"! novor end fofwsrd (L^Til Use of advanced technologies in ATM (air traffic p375 N94-28958 P379 N94-29826 management) domain p 384 N94-29561 Three-dimensional external flow computations using Potential hszvos of mAQnotic rosonsnco imAQflrs to ACCS Surveillance Exploratory Prototype (ASEP) prismatic grid p410 N94-28979 emergency medical service helicopter operations p412 N94-29S66 IDOT/FAA/RD-92/1S) p 382 N94-29862 Application of digital control theory to adaptive grid Decision Making Aids (DMA) in on-line ATC systems Extremely Low Visibility IFR Rotorcraft Approach generation p415 N94-28980 p386 N94-29570 (ELVIRA) operaticnal concept development Volume 1: An elliptic-hyperbolic grid generation method and ConsidOfBtionB on QTBphic&l usor mtBrt&oss tor mtBtbQont Executive Summary ATM support systems p3B6 N94-29572 application to compressor flows p 395 N94-28981 (DOT/FAA/RD-94/1.1] p 389 N94-30189 HYDRAULIC EQUIPMENT Time-marching aeroelastic and spatial adaptation HELIPORTS Miniature knear-to-rotary motion actuator procedures on triangular and tetrahedral meshes using Rooftop omcrponcy nonpons p413 N94-29647 an uiistructured-grid Eufer method p 379 N94-29877 (DOT/FAA/RD-93/2] p402 N94-29754 The design of a system of codes for ndustml HIGH ALTITUDE HYDROCARBON COMBUSTION calculations of flows around aircraft and other complex Particle kinetic simulation of high attitude hypervetocrty Time-resolved measurements in a three dimensional aerodynamc configurations flight model combustor p411 N94-29283 IPB94-125S98] p 381 N94-30387 (NASA-CR.194535) p379 N94-29893 Fuel-rich catalytic combustion of a nigh density fuel GROUND BASED CONTROL HIGH PRESSURE (NASA-TP-32B1) p407 N94-293S6 Design of Center-TRACON Automation System Combustion technology needs for advanced high HYDROCARBON FUELS p385 N94-29568 pressure cycle engines p 404 N94-29248 Fuel-rich catalytic combustion of a high density fuel ARC2000: Automatic radar control Computational and experimental results in high pressure (NASA-TP-3281) p407 N94-293S6 p388 N94-29583 combustions of H2/

A-10 LIQUID ATOMIZATION SUBJECTINDEX

Particle kinetic simulation of high altitude nypervelocity INTERFERENCE FIT L flight Cold expansion and interference for extending the (NASA-CR.19453S] P 379 N94-29893 fatigue life of multi-layer metal joints LAMINAR BOUNDARY LAYER (AD-A274982J p4tO N94-29091 Experiments and theoretical considerations regarding HYPERSONIC FLOW Numerical analysis of two dimensional/axisymmetric INVERSE KINEMATICS the allowable roughness height in laminar flow non-equilibrium hypersonic flow p 376 N94-28963 Design and construction of the Aerobot Robotic (P894-125556J P 381 N94-30389 Manipulator (ARM) Code development (or hypersonic real-gas flow LAMINATES [AD-A275362] p 409 N94-28894 simulations toward the design of space vehicles, part 2 Prediction of stress-strain response of P376 N94-28966 INVISCID FLOW SCS-6/Timetal-21S subjected to a hypersonic flight Numerical simulation of supersonic flow around space Particle kinetic simulation of high altitude hypervelocity profile plane with engine installed p 376 N94-28961 [ NASA-TV-1090261 p 403 N94-28823 flight ITERATIVE SOLUTION LANDING GEAR [NASA-CR-194535] P 379 N94-29893 Calculus of variations applied to 2D multi-point airfoil HYPERSONIC WIND TUNNELS Landing gear energy absorption system design INASA-CASE-MSC-22277-1] p411 N94-29448 Holographic interterometry: A user's guide [PB94-125457] p 381 N94-30401 fDE94-003136] P 408 N94-2B466 LANDING LOADS HYPERSONICS Landing gear energy absorption system Some problems of scramjet propulsion for aerospace (NASA-CASE-MSC-22277-1] p411 N94-29448 planes. Part 2: Scramjet Development and test LAP JOINTS problems P 399 N94-29301 J INTEGRAL Full-scale testing and analysis of curved aircraft fuselage Models for vibration-dissociation coupling in Dynamic fracture mechanics analysis for an edge panels high-temperature gases p413 N94-29675 delamination crack IAD-A275666] p 390 N94-28657 [NASA-TM-109106] p417 N94-29856 LEADING EDGES J45 ENGINE Experimental investigation of three-dimensional I Radar jet engine health monitoring project vortex-airfoil interaction in a supersonic stream I ASSGI-301] p400 N94-30130 [AD-A275107] p374 N94-28899 ILL-POSED PROBLEMS (MATHEMATICS) JET AIRCRAFT An experimental investigation of the effect of leading Numerical solution of inverse problem in Information presentation tor expert systems in future aerodynamics P 376 N94-2B965 edge extensions on directional stability and the tighter aircraft effectiveness of torebody nose strakes IMAGE PROCESSING (AD-A275126I p 394 N94-29005 Amide ground movements surveillance p400 N94-29728 JET ENGINE FUELS P388 N94-295B5 An experimental study of the aerodynamics of a swept High temperature fuel requirements and payoffs and unswept semispan wing with a simulated glaze ice IMAGING TECHNIQUES p405 N94-29259 Potential hazards of magnetic resonance imagers to accretion High temperature resistant jet fuels emergency medical service helicopter operations [NASA-CR-195330] p 381 N94-30152 p405 N94-29260 [DOT/FAA/RD-92/15J p 382 N94-29862 LECTURES Research and development of high thermal stability IMPACT DAMAGE Research and Development of Ram/Scramjets and fuels p 405 N94-29261 Cockptt video: A low cost BDA source Turboramjets in Russia Development of global/chemistry model for jet-fuel [AO-A27522BJ P 395 N94-29389 [AGARD-LS-194] p397 N94-29291 thermal stability based on observations from static and IMPELLERS Introduction and overview of research and development flowing experiments p405 N94-29262 Numerical study on internal flows of centrifugal of solid propellant ramrockets. liquid fuel ramjets and The effect of incomplete fuel-air mixing on the lean limit compressors P 395 N94-28977 oxpGfiflftontBl hydroQon fAfrv comt>ust0'6 and emissions characteristics of a Lean Prevaponzed INFORMATION SYSTEMS p398 N94-29292 Premixed (LPP) combustor p 405 N94-29265 A comparison of three aircraft attitude display symbotogy LIFE (DURABILITY) structures Endothermic fuels for hypersonic aviation Sorvicd W0 prediction of cornpostts structures ttirouQti [AO-A275172] p 394 N94-29048 p407 N94-292B5 fiber testing INFRARED IMAGERY Liquid summation in supersonic flows (AD-A275661] p 403 N94-2B654 Dual-Band Infrared (DBIR) imaging inspections of Boeing p414 N94-29839 LIFE CYCLE COSTS 737 and KC-135 aircran panels JET ENGINES Aircraft age impact on individual operating and support [DE94-005700] P 374 N94-29842 Combustion for future supersonic transport propulsion coat elements INJECTORS p404 N94-29249 [AD-A275739] P373 N94-28732 Ducted kerosene spray flames p407 N94-29276 JET FLOW Demonstration of improved software support labor INLET AIRFRAME CONFIGURATIONS Transonic expanding flow through axially symmetric estimation for Air Force operational flight programs through Numerical study on the interaction between scramjet orifices p410 N94-28985 functional orientation engine modules caused by thermal choke JET IMPINGEMENT (AD-A275789J p 373 N94-28743 p395 N94-28960 Aircraft aerodynamics with deflected jets In ground LIFT INLET FLOW effect p380 N94-29973 Unstosdy AorDdyn&fiuc coffiputetions tvound Scramjet CFD methods and analysis. Part 1: Scramjet JET MIXING FLOW NACA0012 at high angles of attack p377 N94-28969 CFD methods Numerical simulation of the flow in scramjet Study on mixing and injection of hydrogen into a Aerodynamic characteristics of a propeller-powered duct P398 N94-29296 supersonic flow p377 N94-2B975 high-lift semispan wing INSPECTION (NASA-TM-4541] p 380 N94-29937 The mixing process in the quenching zone of the Radar jet engine health monitoring project Computation of wind tunnel wall effects tor complex rich-lean-combustion concept p 407 N94-29281 [ASSGI-301] p400 N94-30130 models using a low-order panel method INSTRUMENT ERRORS Scramjet CFD methods and analysis. Part 2: Scramjet [NASA-TM-104019] p 380 N94-30151 Correction of X hot-wire measurements for gradients CFD analysis. Numerical simulation of supersonic mixing LIFT AUGMENTATION nufnial to the plane of the wires and combustion applied to scramjet combustor Numerical study of the trailing vortex of a wing with (PB94-125473) p402 N94-30399 p399 N94-29300 wing-tip blowing INSTRUMENT FLIGHT RULES JET PROPULSION [NASA-Cfl-195803] p 378 N94-29760 Extremely Low Visibility IFR Rotorcraft Approach Combustion for future supersonic transport propulsion Aerodynamic characteristics of a propeller-powered (ELVIRA) operational concept development. Volume 1: p404 N94-29249 high-tin semispan wing Executive Summary JP4 JET FUEL (NASA-TM-4541] p 380 N94-29937 [DOT/FAA/RD-94/1.1] p 389 N94-30189 Research and development of high thermal stability LIFT DEVICES INSTRUMENT LANDING SYSTEMS fuels P405 N94-29261 Role of computational fluid dynamics in aeronautical Los Angeles international airport instrument landing JUDGMENTS engineering. Part 10: Numerical analysis of flow around system approach data collection and reduction, phase 1 Subjective response to sonic booms having different 2-0 mufti-element HLD p 410 N94-28964 [AD-A2751151 P 383 . N94-28914 shapes, rise times, and durations LIFT DRAG RATIO Ground independent landing system [NASA-TM-109090] p417 N94-29464 Numerical analysis of supersonic transport wings p385 N94-29564 p375 N94-28959 INTEGRAL EQUATIONS LIFTING ROTORS Numerical solution of inverse problem in A design of third-generation airfoils for helicopter rotor aerodynamics P 376 N94-28965 blades using Navier-Stokes p 391 N94-2B957 INTEGRAL ROCKET RAMJETS K-EPSILON TURBULENCE MODEL LIGHT SCATTERING Research and development of ramjets/ramrockets. Part Numerical simulation of aerothermal characteristics in Backscatter haze device for measurement of haze in 2: Integral liquid fuel ramjets p 398 N94-29297 gas turbine combustors with complOK geometries aircraft transparencies Research and development of rarnjets/ramrockets. Part p396 N94-292S5 [AD-A275127] p 391 N94-29042 3: The study of gaseous hydrogen ram combustore KEROSENE LIGHT SOURCES p398 N94-29298 High temperature resistant jet fuels Backscitter haze device for measurement of haze in INTERACTIONAL AERODYNAMICS p405 N94-29260 aircraft transparencies Experimental investigation of three-dimensional IAD-A275127] p 391 N94-29042 Ducted kerosene spray flames p407 N94-29276 vortex-airfoil interaction in a supersonic stream LINEAR FILTERS (AD-A275107) P374 N94-28899 KNOWLEDGE BASED SYSTEMS A novel approach to noise-nrtering based on a RNS optimization procedure tor three-dimensional Object oriented design of the autonomous fixtaking gain-scheduling neural network architecture composite velocity multi-block applications management system p383 N94-29323 (NASA-TM-106563) p 401 N94-302O4 p412 N94-29534 Advances in development capabilities for intelligent air LIQUID ATOMIZATION An analytical study of unsteady rotor/fuselage traffic management systems p 384 N94-29559 Investigation of the two-phase flow in a research interaction in hover and forward flight Airside ground movements surveillance combustor under reacting and non-reacting conditions p379 N94-29826 p388 N94-29585 P411 N94-29282

A-11 SUBJECTINDEX LIQUID FUELS

Liquid atomization in supersonic flows MATHEMATICAL MODELS Particle kinetic simulation of high altitude hypervelocity p 414 N94-29839 Flowfield prediction of NO(x) and smoke production in flight [NASA-CR-194535] P379 N94-29893 UQUID FUELS aircraft engines P 404 N94-29252 Ultra low NO(x) ultra lean gas turbine primary zones Numerical modelling of turbine combustion chambers MULTIGRID METHODS with liquid fuels p 397 N94-29267 p396 N94-29254 ENGRID: A graphical interactive code for the Research and development of ramjets/ramrockets. Part Scramjet CFD methods and analysis. Part 2: Scramjet computation of structured grids tor blocked flow domains 1: Integral solid propellant ramrockets CFD analysis. Numerical simulation of supersonic mixing P409 N94-28956 p398 N94-29294 and combustion applied to scramjet combustor An elliptic-hyperbolic grid generation method and UQUID INJECTION p399 N94-29300 application to compressor flows p 395 N94-28981 Investigation of the two-phase flow in a research Models tor vibration-dissociation coupling in RNS optimization procedure for three-dimensional combustor under reacting and non-reacting conditions high-temperature gases P 413 N94-29675 composite velocity mufti-block applications p411 N94-29282 An analytical study of unsteady rotor/fuselage p412 N94-29534 liquid atomization in supersonic flows interaction in hover and forward flight MULTISENSOR APPLICATIONS p414 N94-29839 p379 N94-29826 ACCS Surveillance Exploratory Prototype (ASEP) UOUID ROCKET PROPELLANTS P412 N94-29566 Introduction and overview of research and development MEASURING INSTRUMENTS User's manual for the model interface and plugboard of solid propellant ramrockets, liquid fuel ramjets and experimental hydrogen ram combustons cabinets in the 14- by 22-foot subsonic tunnel p 398 N94-29292 [NASA-TM-109062] P 381 N94-30176 N Research and development of ramjets/ramrockets. Part MEDICAL SERVICES NATIONAL AIRSPACE SYSTEM 2: Integral liquid fuel ramjets p 398 N94-29297 Potential hazards of magnetic resonance imagers to The 1993 Federal Aviation Administration Aviation UOUID SURFACES emergency medical service helicopter operations System Capital Investment Plan p 383 N94-29445 Liquid atomization in supersonic flows (DOT/FAA/RD-92/15] p382 N94-29862 p414 M94-29839 METAL FATIGUE NAVIEH-STOKES EQUATION LIQUID-VAPOR INTERFACES Role of microsmicture on the fatigue durability of Numerical simulation of unsteady aerodynamic heating Liquid atomization in supersonic flows aluminum aircraft alloys induced by shock reflections p37S N94-28952 p414 N94-29839 (AD-A275814) p 403 N94-28830 ENGRID: A graphical interactive code for the Looisncs Cold expansion and interference tor extending the computation of structured grids tor blocked flow domains The 1993 Federal Aviation Administration Aviation fatigue life of multi-layer metal joints P409 N94-28956 System Capital Investment Plan p383 N94-29445 [AD-A274982] P*10 N94-29091 A design of mini-generation airfoils for helicopter rotor LONGITUDINAL STABILITY The effect of mechanical paint stripping on the fatigue Hades using Navier-Stokes p 391 N94-28957 An experimental and theoretical study of the and fracture of thin aluminum airplane skin Unsteady aerodynamic computations around aerodynamic characteristics of some generic missile p408 N94-29900 NACA0012 at high angles of attack P377 N94-28969 concepts at Mach numbers from 2 to 6.8 METAL JOINTS A free-wake Euler and Navier-Stokes CFD method and INASA-TM-109110] p37B N94-29473 Cold expansion and interference tor extending the its application to helicopter rotors including dynamic stall LOUDNESS fatigue Me of multi-layer metal joints [AD-A275416J P 377 N94-29197 Subjective response to sonic booms having efferent [AD-A274982] P 410 N94-29091 Investigation of advanced counterrotation blade shapes, rise times, and durations configuration concepts for high speed turboprop systems. [NASA-TM-109090] p417 N94-29464 Automation of the NOT diagnostic using neural nets. Task 2: Unsteady ducted propfan analysis computer LOW VTSIBIUTY Application: Inspection of Avbus longrtudinal ^>iJUb during Extremely Low Visibility IFR Rotorcraft Approach maintenance program users manual [REPT-932-600-104] p412 N94-29474 INASA-CR-187105) p 399 N94-29438 (ELVIRA) operational concept development Volume 1: Executive Summary METAL MATRIX COMPOSITES RNS optimization procedure tor three-dimensional IOOT/FAA/RD-94/1.I] p 389 N94-30189 Prediction of stress-strain response of composite velocity multi-block applications SCS-6/Timetal-2lS subjected to a hypersonic flight P412 N94-29534 profile Numerical study of the trailing vortex of a wing with M FNASA-TM-109026] p 403 N94-28823 wing-tip blowing METHOD OF CHARACTERISTICS (NASA-CR-195803) p 378 N94-29760 MAGNETIC EFFECTS Transonic expanding flow through axially symmetric Algorithm and code development for unsteady Potential hazards of magnetic resonance imagers to orifices p410 N94-28985 three-dimensional Navier-Stokes equations emergency medical service helicopter operations MICROMECHANICS (NASA-CR-195774) p 414 N94-29942 [DOT/FAA/RD-92/15] p 382 N94-29862 Prediction of stress-strain response of Aircraft aerodynamics with deflected jets in ground MAGNETIC FIELDS SCS-6/Timetal-21S subjected to a hypersonic flight effect p380 N94-29973 Potential hazards of magnetic resonance Knagere to profile NAVIGATION AIDS emergency medical service helicopter operations [NASA-TM-109026] p403 N94-28823 (DOT/FAA/RD-92/15] p382 N94-29862 Ground independent landing system MICROPROCESSORS MAGNETIC RESONANCE p3B5 N94-29564 On ground system ntegration and testing: A modem GPS/GNSS for ATM p 385 N94-29S65 Potential hazards ol magnetic resonance ntagers to p394 N94-29334 emergency medical service helicopter operations NAVIGATION SATELLITES > ANTENNAS [DOT/FAA/RD-92/15) p 382 N94-29862 GPS/GNSS for ATM p 385 N94-29565 Theoretical and experimental study of • cylindrical MAN MACHINE SYSTEMS rmcrostnp antenna NEAR WAKES Engineering of systems tor application of scientific [REPT-932-440-109] P412 N94-29456 An experimental study of wing tip vortex in the near computing in industry p415 N94-28947 wake of a rectangular wing MICROSTRUCTURE Cognitive approach to specifications on air traffic Role of microstrucuire on the fatigue durability of (AD-A275389] p 377 N94-29306 controllers' decision assistance systems aluminum ajrcratt alloys NEURAL NETS p386 N94-2S571 [AD-A275814] p403 N94-28830 Automation of the NOT diagnostic using neural nets. MANAGEMENT PLANNING MICROWAVE LANDING SYSTEMS Application: Inspection of Airbus longitudinal joints during Software Management Environment (SME) concepts Ground independent landing system maintenance ana architecture, revision 1 p385 N94-29564 {REPT-932-600-104} p412 N94-29474 (NASA-CR-189293) p416 N94-29727 MILITARY TECHNOLOGY A novel approach to noise-filtering based on a MANAGEMENT SYSTEMS A disciplined approach to software test and evaluation gain-scheduling neural network architecture Object oriented design of the autonomous tbctaking p416 N94-29339 [NASA-TM-106563] p 401 N94-30204 management system p 383 N94-29323 MISSILE DESIGN NITRIC OXIDE DLR's ATM denim Btiabon programme An experimental and theoretical study of the FtowheW prediction of NOW and smoke production in p386 N94-29S75 aerodynamic characteristics of some generic missile aircraft engines p 404 N94-292S2 ARC2000: Automatic radar control concepts at Mach numbers from 2 to 6.8 NITROGEN OXIDES p388 N94-29563 [NASA-TM-109110] p 378 N94-29473 Fuels and Combustion Technology for Advanced Aircraft Software Management Environment (SME) concepts MISSILES Engines Experimental investigation of throe dimensional and architecture, revision 1 (AGARD-CP-S36] p 4O4 N94-29246 vortex-airfoil interaction in a supersonic stream (NASA-CR-189293] p416 N94-29727 On the effect of emissions from aircraft engines on the [AD-A275107] p374 N94-28899 state of the atmosphere p 414 N94-29247 MANEUVERABILITY MISSION PLANNING Ultra low NCHx) ultra lean gas turbine primary zones Exploring ODES as a tool tor determining limits of A capacity planning model for Canadian military artft achievable performance in aircraft design with bqiid fuels p 397 N94-29267 requests [AD-A275359] p 391 N94-28998 [ISBN-O-315-8607B-0) p 382 N94-30144 Reduction of NO(x) by fuel-staging in gas turbine MANIPULATORS MOLECULAR INTERACTIONS engines: A commitment to the future Omtiyn and construction of the Aerobot Robotic Monte Carlo simulation or normal shock wave. Part 2: P406 N94-29272 Manipulator (ARM) VMS model and VSS model p409 N94-28948 The influence of air distribution on homogeneity and IAD-A275362] p409 N94-28894 MONTE CARLO METHOD pollutant formation in the primary zone of a tubular Sn-dogroo of-freedom parallel minimanipulator with Pioceedings of the 10th NAL Symposium on Aircraft combustor p 406 N94-29274 uinie mextensAle hmbs Computational Aerodynamics Effects of hydrogen addition on pollutant emissions in (NASA-CASE-GSC-13485-1) p 413 N94-29726 [NAL-SP-19] P375 N94-28946 a gas turbine combustor p 406 N94-29275 MANUALS Monte Carlo simulation or normal shock wave. Part 2: NOISE INTENSITY User's manual tor the model interface and plugboard VMS model and VSS model p409 N94-2B948 Subjective response to sonic booms having different cabinets in the 14- by 22-toot subsonic tunnel Variable soft sphere molecular model in the Monte Carlo stvspGS, rise brnos. find durations (NASA-TM-109062] p 381 N94-30176 simulation of air species p409 N94-28949 (NASA-TM-109090] p417 N94-29464

A-12 PROP-FAN TECHNOLOGY SUBJECT INDEX

Low-speed longitudinal aerodynamic characteristics of NOISE PREDICTION (AIRCRAFT) OPTIMAL CONTROL Experimental validation of finite element and boundary Application of digital control theory to adaptive grid a flat-plate planform model of an advanced fighter element methods for predicting structural vibration and generation p415 N94-28980 configuration radiated noise Calculus of variations applied to 2D multi-point airfoil [NASA-TM-109045] p 377 N94-29443 [NASA-CH-4561 ] P 412 N94-29552 design PLANNING NOISE REDUCTION (PB94-125457J p381 N94-30401 A time reasoning system based on the event calculus Boundary layer control device for duct silencers OPTIMIZATION for scheduling in aeronautic maintenance [NASA-CASE-ARC-12030-1J P 417 N94-29362 Aerodynamic design using parallel processors (REFT-932-710-101] p 374 N94-29463 A novel approach to noise-filtering based on a [AD-A275470J p 374 N94-28674 Interactive analysis and planning tools for air traffic and gain-scheduling neural network architecture Thermal/structural tailoring of engine blades airspace management p 386 N94-29573 [NASA-TM-106563] p 401 N94-30204 (T/SEAEBL). Theoretical manual POLLUTION CONTROL INASA-CR.194462] p 409 N94-28815 Reduction of NO(x) by fuel-staging in gas turbine NONDESTRUCTIVE TESTS ORGANIC COMPOUNDS Automation of the NOT diagnostic using neural nets. engines: A commitment to the future Advanced fuel properties: A computer program for p 406 N94-29272 Application: Inspection of Airbus longitudinal joints during estimating property values A study of tow emissions gas turbine combustions maintenance (AO-A2752481 p 403 N94-28901 [REPT-932-600-104] p412 N94-29474 [ NASA-CR-195763] p 399 N94-29860 ORIFICE FLOW Radar jet engine health monitoring project Transonic expanding flow through axially symmetric POROUS BOUNDARY LAYER CONTROL IASSGI-301] p400 N94-30130 orifices p410 N94-28985 Boundary layer control device for duct silencers (NASA-CASE-ARC-12030-1) p417 N94-29362 NONEOUIUBRIUU CONDITIONS OSCILLATION DAMPERS Models for vibration-dissociation coupling in Tuned mass damper for integrally bladed turbine rotor POROUS PLATES high-temperature gases p413 N94-2967S [NASA-CASE-MFS-2B697-1] p411 N94-29353 Boundary layer control device for duct silencers NONEOUIUBRIUM FLOW [NASA-CASE-ARC-12030-1] p417 N94-29362 Numerical analysis of two dimensional/airisymrnetrie POROUS WALLS non-equilibrium hypersonic flow p 376 N94-28963 A method tor the modelling of porous and solid wind Models for vibration-dissociation coupling in tunnel walls in computational fluid dynamics codes high-temperature gases P 413 N94-29675 PAINTS [NASA-CR-195699] p 409 N94-28724 The effect of mechanical paint stripping on the fatigue NONLINEAR EQUATIONS PORTABLE EQUIPMENT and fracture of thin aluminum airplane skin A non-linear simulation for an autonomous unmanned Evaluation of access/navigational features of a p408 N94-29900 air vehicle graphical-user interface installed on a portable PANEL METHOD (FLUID DYNAMICS) [AD-A2750621 p391 N94-29200 maintenance aid Aircraft aerodynamics with deflected jets in around (AD-A275791) p 383 N94-28744 NONLINEAR FILTERS effect p380 N94-29973 A novel approach to noise-filtering based on a PREDICTION ANALYSIS TECHNIQUES Computation of wind tunnel wall effects for complex Role ol microstructure on the fatigue durability of gam-scheduling neural network architecture models using a low-order panel method (NASA-TM-106563) p401 N94-30204 aluminum aircraft alloys (NASA-TM-104019) p 380 N94-30151 [AD-A275814] p 403 N94-28830 NONUNEARITY PANELS A non-linear simulation tar an autonomous unmanned Spray combustion experiments and numerical Development of Alternating Current Potential Drop predictions p407 N94-29277 air vehicle (ACPD) procedures for crack detection in aluminum aircraft [AD-A275062] p391 N94-29200 Development of a method to predict transonic hmit cycle oscillation characteristics of fighter aircraft (continued) NOSES (FOREBODIES) [AD-A275755] p408 N94-28646 [NLR-TP-92156-U] p 393 N94-3O342 An experimental investigation of the effect of leading Dual-Band Infrared (DBIR) imag inspections of Boeing edge extensions on directional stability and the PREMIXED FLAMES 737 and KC-135 aircraft panels Ducted kerosene spray flames p 407 N94-29276 effectiveness of forebody nose strakes [DE94-O05700] p 374 N94-29842 p400 N94-29728 PREMIXING PARALLEL PROCESSING (COMPUTERS) The effect of incomplete fuel-air mixing on the lean limit NOZZLE DESIGN Aerodynamic design using parallel processors and emissions characteristics of a Lean Prevaporized Fuel injector design for high temperature aircraft [AD-A275470] p 374 N94-28674 Prerruxed (LPP) combusttr p 405 N94-29265 engine p396 N94-29263 Performance evaluation of the NWT with parallel Effects of hydrogen addition on pollutant emissions in Fortran p415 N94-28992 NOZZLE FLOW a gas turbine combustor p 406 N94-29275 Fuel injector design for high temperature aircraft A method of user interface tor NWT PRESSURE DISTRIBUTION p415 N94-28993 engine p396 N94-29263 Wall pressure fluctuations in the reattacnment region PAVEMENTS Scramjet CFD methods and analysis. Pan 1: Scramjet of a supersonic tree shear layer CFD methods. Numerical simulation of the flow in scramjet Asphaltic concrete performance under heavy fighter (NASA-CR-195790] p 379 N94-29920 aircraft loading duct p398 N94-29296 Computation (ft wind tunnel wall effects for cornplox Particle kinetic simulation of high attitude hypervekxsty (AD-A275046] p402 N94-291S1 models using a low-order panel method flight PERFORMANCE PREDICTION (NASA-TM-104019] p380 N94-30151 Roto of rncrostructure on the fatigue durability of (NASA-CR-194535) p 379 N94-29893 Calculus of variations applied to 2D multi-point airfoil aluminum arcraft alloys NUMERICAL ANALYSIS design IAD-A27S814] p403 N94-28830 Numerical analysis of airfoil for helicopter Wade at high [PB94-12S457] p 381 N94-30401 PERFORMANCE TESTS angle of attack using Navier-Stokes code PRESSURE EFFECTS Some problems of scramjet propulsion for aerospace Pollutant omissions from and will m i a model gas turbine p375 N94-28958 planes. Part 2: Scramjet Development and test combustor at elevated pressures and temperatures NUMERICAL CONTROL problems p399 N94-29301 Application of fuzzy logic to the control of wind tunnel p406 N94-29271 A disciplined approach to software test and evaluation PRESSURE MEASUREMENT settling chamber temperature p 416 N94-29339 Steady pressure measurements on an Aeroelastic INASA-TM-109105] p 402 N94-30200 PERSONAL COMPUTERS Research Wing (ARW-2) Evaluation of access/navigational features of a [NASA-TM-109046] p 374 N94-28658 graphical-user interface installed on a portable PRESSURE OSCILLATIONS (Yi8int0n8nc6 Bid Wall pressure fluctuations in the reattachment region [AD-A275791J p383 N94-28744 OBJECT-ORIENTED PROGRAMMING of a supersonic free shear layer PERTURBATION THEORY Aerospace Software Engineering toe Advanced Systems f NASA-CR-195790) p 379 N94-29920 Decoupled flight control system design using the singular Architectures PROBABILITY DISTRIBUTION FUNCTIONS perturbation method p400 N94-298SO (AGARD-CP-545) p41S N94-29315 A moment plotting method for characterizing aircraft PILOT PERFORMANCE Object oriented design of the autonomous fixtaking fatigue data population distributions : Information presentation for expert systems in future management system p 383 N94-29323 (AD-A275SOO) p 390 N94-2B660 fighter aircraft OBLIQUE SHOCK WAVES PROGRAM VERIFICATION (COMPUTERS) (AD-A275126) p394 N94-29005 Experimental investigation of three-dimensional Integrated formal verification and validation of safety Aircraft accident/incident summary report In-flight toss vortex-airfoil interaction in a supersonic stream critical software p416 N94-29338 of control, loading to forced landing and runway overrun. IAD-A275107] p374 N94-2B899 PROGRAMMING ENVIRONMENTS Continental Express. Inc., N24706 Embraer EMB-120 RT. ON-LINE SYSTEMS SDE's tor the year 2000 and beyond: An EF Pine Bluff. Arkansas. 29 April 1993 Decision Making Aids (DMA) in on-line ATC systems perspective p 416 N94-29344 [PB94-910404] p382 N94-29402 p386 N94-29570 Considerations on graphical user interfaces for intelligent PILOTLESS AIRCRAFT ONBOARD DATA PROCESSING ATM support systems p386 N94-29572 Payload central control for unmanned aircraft GPS/GNSS tor ATM p 385 N94-29565 PROJECT MANAGEMENT p401 N94-30284 OPERATING COSTS NAVAIR aircraft wiring standardization and qualification Aircraft age impacts on nuintenanc* reQUtTBments PIPES (TUBES) program p408 N94-2B704 IAD-A275701) p373 N94-28666 Similarity between turbulent Rows through curved pipe SIDE'S tor the year 2000 and beyond: An EF Aircraft age impact on individual operating and support and orthogonal rotating pipe p410 N94-28986 perspective p 416 N94-29344 cost elements PITCHING MOMENTS The 1993 Federal Aviation Administration Aviation (AD-A275739] p 373 N94-28732 An experimental and theoretical study of the System Capital Investment Plan p 383 N94-29445 The 1993 Federal Aviation Administration Aviation aerodynamic characteristics of some generic missile PROP-FAN TECHNOLOGY System Capital Investment Plan p383 N94-29445 concepts at Mach numbers from 2 to 6.6 Investigation of advanced eounterrotation blade OPERATIONS RESEARCH [NASA-TM-109110] P378 N94-29473 configuration concepts for high speed turboprop systems. A capacity planning model for Canadian military airlift PLANFORMS Task 2: Unsteady ducted propfan analysis computer requests Numerical solution of inverse problem in program users manual f ISBN-O-31546079-0 J p 382 N94-30144 aerodynamics p376 N94-28965 [NASA-CR-187105J p 399 N94-29438

A-13 SUBJECTINDEX PROPELLANT ADDITIVES

PROPELLANT ADDITIVES RADIATION DETECTORS RESIDUAL STRENGTH A study of low emissions gas turbine combustions BacKscatter haze device tor measurement of haze in Full-scale testing and analysis of curved aircraft fuselage (NASA-CR-195763) P 399 N94-29860 aircraft transparencies panels PROPELLANT CHEMISTRY (AD-A275127J P 391 N94-29042 (AD-A275666] P 390 N94-28657 Fuels combustion research RADIO NAVIGATION RESIDUAL STRESS [AD-A275122J p 404 N94-28004 The use of low cost differential mode GPS receivers Prediction of stress-strain response of PROPELLANT COMBUSTION in unmanned vehicles p 389 N94-30285 SCS-6/Timetal-2lS subjected to a hypersonic flight Fuel-rich catalytic combustion ol a high density fuel RADIO RECEIVERS profile [NASA-TP-3281J p407 N94-29356 The use of tow cost differential mode GPS receivers [NASA-TM-109026J P 403 N94-2B823 PROPELLANT PROPERTIES in unmanned vehicles p 389 N94-302B5 REYNOLDS NUMBER A modernised HST of NLR Advanced fuel properties: A computer program tor RAMJET ENGINES [AD-B179220] P 402 N94-30423 estimating property values Research and development of ramjets/ramrockets. Part RIGID ROTOR HELICOPTERS IAD-A275248) p 403 N94-28901 1: Integral solid propellent ramrockets Numerical analysis of airfoil tor helicopter blade at high PROPELLER SLIPSTREAMS p 398 N94-29294 Aerodynamic characteristics ol a propeller-powered angle of attack using Navier-Stokes code Research and development of ramjets/ramrockets. Part htgh-tifl semispan wing p375 N94-28958 2: Integral bawd fuel ramjets p 398 N94-29297 (NASA-TM-4S41] p 380 N94-29937 RIVETS Research and development of ramjets/ramrockets. Part PROPELLERS Full-scale testing and analysis of curved aircraft fuselage Aerodynamic characteristics of a propeller-powered 3: The study of gaseous hydrogen ram combustors panels p398 N94-29298 high-lift semispan wing (AD-A275666) p 390 N94-28657 (NASA-TM-4541) p 380 N94-29937 QAM experimental turboramjets p 399 N94-29299 ROBOT ARMS PROPULSION SYSTEM CONFIGURATIONS RAMPS (STRUCTURES) Design and construction of the Aerobot Robotic Research and Development of Ham/Scramjets and Numerical simulation of unsteady aerodynamic heating Manipulator (ARM) Turboramjets in Russia induced by shock reflections p 375 N94-28952 IAD-A275362J p 409 N94-28894 (AGARO-LS-194) p 397 N94-2S291 RANGEFINDING ROBOTICS Turboramjet engines: Types and performances Simulation of tuUy automated air traffic control Design and construction of the Aerobot Robotic p398 N94-29293 concepts p386 N94-29569 Manipulator (ARM) PROPULSION SYSTEM PERFORMANCE RAREFIED GASES (AD-A2753621 p 409 N94-28894 Fuels combustion research Monte Carlo simulation or normal shock wave. Part 2: ROOFS [AD-A275122I p 404 N94-29004 VMS model and VSS model p409 N94-28948 Rooftop emergency heliports (DOT/FAA/RD-93/2) P402 N94-29754 Combustion for future supersonic transport propulsion REACTION KINETICS ROTARY WINGS p404 N94-29249 High temperature resistant jet fuels Boundary layers induced by three-dimensional vortex Research and Development of Ram/Scramjets and p405 N94-29260 Turboramjets in Russia loops Development of global/chemistry model tor jet-fuel [AGARD-LS-194] p397 N94-29291 [AO-A275678] p 408 N94-28665 thermal stability based on observations from static and Turboramjet engines: Types and performances A free-wake Euler and Navier-Stokes CFD method and flowing enpaiiiients p 405 N94-29262 p398 N94-29293 its application to helicopter rotors including dynamic stall Some problems of scramjet propulsion tor aerospace REAL TIME OPERATION (AD-A275416) p377 N94-29197 planes. Part 1: Scramjet Aims and features Information presentation for expert systems in future Hofacoptor mission And rotor poffofrnancc optinuzstion p398 N94-29295 fighter aircraft with quasi-linear inflow theory p392 N94-29594 DAM experimental turboramjets p 399 N94-29299 [AD-A275126] p 394 N94-29005 Numerical study of the trailing vortex of a wing with Some problems of scramjet propulsion for aerospace GPS/GNSS for ATM p385 N94-29565 wing-tip blowing planes. Part 2: Scramjet Development and test ACCS Surveillance Exploratory Prototype (ASEP) [NASA-CR-195803] p 378 N94-29760 problems p 399 N94-29301 p 412 N94-29566 ROTATION psYCHOAcousncs REATTACHED FLOW Similarity between turbulent flows through curved pipe Subjective response to sonic booms having different An expel ii i Kintal study of the flowfioJd on a semispan and orthogonal rotating pipe p 410 N94-28986 shapes, rise times, and durations rectangular wing with a simulated glaze ce accretion ROTOR AERODYNAMICS (NASA-TM-109090] p417 N94-29464 p378 N94-29674 A design of third-generation airfoils for helicopter rotor PYROLYSIS RECIRCULATIVE FLUID FLOW blades using Navier-Stokes p 391 N94-28957 Endothermic fuels for hypersonic aviation An experimental study of the ftowfieM on a semispan Numerical analysis of airfoil for helicopter blade at high p407 N94-292S5 rectangular wing with a simulated glaze ice accretion angle of attack using Navier-Stokes code p378 N94-29674 P375 N94-28958 Q RECTANGULAR WINGS Verification of a three-dimensional viscous flow analysis An experimental study of wing tip vortex in the near tor a single stage compressor p410 N94-28976 ROTOR BLADES QUALIFICATIONS wake of a rectangular wing (AD-A275389J p 377 N94-29306 Numerical study of the trailing vortex of a wing with NAVAIR Bircr&ft wirinQ stAndflftfizstion snd wing-dp blowing program p408 N94-28704 An expoiimental study of the flowfield on a semispan [NASA-CR-195803) p 378 N94-29760 rectangular wing with a Stfnulatsd Qtaze too accretion Organized wiring systems p 408 N94-2870S ROTOR BLADES (TURBOMACHINERV) Fire behavior of aeronautical materials p378 N94-29674 Verification of a three-dimensional viscous flow analysis [REPT-932-600-105] p 408 N94-294S7 REFLECTED WAVES for a single stage compiessor p 410 N94-28976 QUALITY CONTROL Method tor cancelling expansion waves in a wave Tuned mass damper for integrally bladed turbine rotor NAVAIR aircraft wiring standardization and qualification (NASA-CASE-MFS-28697-1) p411 N94-29353 program p408 N94-28704 [NASA-CASE-LEW-15218-2] p413 N94-29740 ROTOR BODY INTERACTIONS Organized wiring systems p 408 N94-28705 REGULATIONS An analytical study of unsteady rotor/fuselage Effects of repair on structural integrity nteractjon in hover and forward flight [AD-A2757S6] p 390 N94-28647 P379 N94-29826 Crashworthiness analysis of commuter aircraft seats ROTOR LIFT [AJXA275689] p382 N94-28799 A design of third-generation airfoils for helicopter rotor RADAR APPROACH CONTROL RELAXATION METHOD (MATHEMATICS) blades using Navier-Stokes p 391 N94-28957 Design ol Center-TRACON Automation System Numerical analysis of two dimenskmal/axisymineiric p385 N94-29568 ROTORS non-equilibrium hypersonic flow p376 N94-28963 Acquisition, design modification, assembly, and ground Development of precision runway monitor system for REMOTELY PILOTED VEHICLES test of NPS Hummingbird remotely piloted helicopter increasing capacity of parallel runway operations Acquisrtion, design mudincatjon, assembly, and ground [AD-A275546) p 390 N94-28837 p389 N94-29587 test of NPS Hufiimiiiulxid remotely piloted helicopter Method for cancelling expansion waves in a wave (AD-A275546) p390 N94-28837 RADAR NAVIGATION rotor Ground indepondont torvferiQ system A noo-foi8flr sunul&tion for &n Autonomous unm&rtnod (MASA-CASE-LEW-1521B-2) p 413 N94-29740 p385 N94-29564 air vehicle (AD-A275062) p 391 N94-29200 RUNWAYS ARC2OOO: Automatic radar control Contributions of DLR to air traffic capacity enhancement p388 N94-29S83 The use of low cost differential mode GPS receivers in unmanned vehicles p389 N94-30285 within a terminal area p 385 N94-29567 RADAR NETWORKS HATT-X: A high performance flying laboratory for RUSSIAN FEDERATION A novel neaMange radar nettouffc for aiport surface autonomous unmanned auciatt research and Research and Development ol Ram/Scramjets and control p389 N94-29586 development p393 N94-30293 Turboramjets in Russia RADAR RECEIVERS RESEARCH AIRCRAFT (AGARMS-194) 0397 N94-29291 Ground independent landing system The radiocafbon hydroxyl technique p385 N94-29564 p414 N94-28600 RADAR SIGNATURES Design and construction of the Aerobot Robotic Radar jet engine health monitoring project Manipulator (ARM) IASSGI-301) P400 N94-30130 (AD-A275362] P409 N94-28894 SAFETY RADAR TRACKING HATT-X: A high performance frying laboratory tor Safety enhancement of composites via periodic proof StnHJtstiofi ol fuOy Butorrusted wx ti&ffic control autonomous unmanned aircraft research and concepts p386 N94-29569 development p393 M94-30293 [AT>A275662] p 403 N94-28655 RADAR TRANSMITTERS RESEARCH FACILITIES SATELLITE NAVIGATION SYSTEMS Ground independent landing system Fishermans Bend: A centre of Australian aviation Use of GPS in automated air traffic control p38S N94-29564 (AD-A274981J p 373 N94-29090 P384 N94-29563

A-14 STRUCTURAL VIBRATION SUBJECTINDEX

SCALARS SMOKE SPACECRAFT REENTRY Numerical modelling of turbine combustion chambers Flowfield prediction of NO(x) and smoke production in Numerical simulation of aerothermodynamic heating of p 396 N94-29254 aircraft engines p 404 N94-292S2 hypersonic space transportation vehicles p 375 N94-28955 SCAUNG LAWS The influence of air distribution on homogeneity and Experiments and theoretical considerations regarding pollutant formation in the primary zone of a tubular SPANW1SE BLOWING the allowable roughness height in laminar flow combustor P 406 N94-29274 Numerical study of the trailing vortex of a wing with (P894-125556] P 381 N94-30389 SOFIA (AIRBORNE OBSERVATORY) wing-tip blowing SCHEDULING Aircraft system aft telescope cavity configuration study [NASA-CR-195803] p 378 N94-29760 A time reasoning system based on the event calculus for Stratospheric Observatory for Infrared Astronomy SPECIFIC HEAT tor scheduling in aeronautic maintenance (SOFIA), phase 2 Endothermic fuels for hypersonic aviation [REPT-932-710-t01J p 374 N94-29463 fNASA-CR-194266) p 392 N94-29685 p 407 N94-292B5 SEAT BELTS SOFTWARE ENGINEERING SPRAYERS Crashworthiness analysts of commuter aircraft seats Demonstration of improved software support labor Ducted kerosene spray flames p 407 N94-29276 estimation for Air Force operational flight programs through [AD-A275889] P 382 N94-28799 Spray combustion experiments and numerical functional orientation SEATS predictions p 407 N94-29277 Crashworthiness analysis of commuter aircraft seats [AD-A275789] P 373 N94-2B743 Aerospace Software Engineering for Advanced Systems Aircraft evacuations: The effect of a cabin water spray [AD-A27S889] p 382 N94-28799 system upon evacuation rates and behaviour Architectures SEPARATED FLOW ICAA-PAPER-93008) p 393 N94-29887 Rote of computational fluid dynamics in aeronautical IAGARD-CP-S45) P41S N94-2931S SPRAYING engineering. Part 10: Numerical analysis of flow around Experiences with the HOOD design method on avionics Investigation of the two-phase flow in a research 2-D multi-element HID p410 N94-28964 software development p 415 N94-29325 combustor under reacting and non-reacting conditions SEQUENCING Testing Operational Flight Programs (OFPs) p411 N94-29282 A time reasoning system based on the event calculus p416 N94-29337 for scheduling in aeronautic maintenance Integrated formal verification and validation of safety STANDARDIZATION [REPT-932-710-101] p 374 N94-29463 critical software p 416 N94-29338 NAVAIR aircraft wiring standardization and qualification SERVICE LIFE A disciplined approach to software test and evaluation program p 408 N94-28704 Service life prediction of composite structures through p 416 N94-29339 Organized wiring systems p 408 N94-28705 fiber testing SDE's tor the year 2000 and beyond: An EF STANDARDS [AD-A275661] p 403 N94-2B654 perspective p416 N94-29344 NAVAIR aircraft wiring standardization and qualification Aircraft age impacts on maintenance requirements Software Management Environment (SME) concepts program p 408 N94-28704 [AD-A275701] P373 N94-28666 and architecture, revision 1 STATIC STABILITY (NASA-CR-189293] p 416 N94-29727 Aircraft age impact on individual operating and support An experimental and theoretical study of the cost elements SOFTWARE RELIABILITY aerodynamic characteristics of some generic missile Demonstration of improved software support labor [AD-A275739] p 373 N94-2B732 concepts at Macri numbers from 2 to 6.8 SHARP LEADING EDGES estimation for Air Force operational flight programs through (NASA-TM-109110] p378 N94-29473 Numerical investigation into high-angle-of-attack functional orientation [AD-A275789] p 373 N94-28743 STATISTICAL TESTS leading-edge vortex flow A moment plotting method for characterizing aircraft SOFTWARE TOOLS [PB94-125564I p381 N94-30388 fatigue data population distributions SDE'8 for the year 2000 and beyond: An EF SHEAR LAYERS [AO-A2755OO] p 390 N94-2B660 Wall pressure fluctuations in the reattachment region perspective P416 N94-29344 of a supersonic free shear layer SOLID PROPELLANT ROCKET ENGINES STATORS (NASA-CR-195790) p 379 N94-29920 Research and development of ramjets/ramrockets. Part Numerical study on internal flows of centrifugal SHOCK ABSORBERS 1: Integral solid propellant ramrockets compressors p 395 N94-28977 Lflruling QOST onorQy flbsyplton system p398 N94-29294 STEADY FLOW [NASA-CASE-MSC-22277-1J p411 N94-29448 SOLID ROCKET PROPELLANTS Steady pressure measurements on an Aeroelastic SHOCK FRONTS Introduction Bnd overview of research and development Research Wing (ARW-2) Experimental investigation of three-dimensional of solid propellant ramrockets, liquid fuel ramjets and [NASA-TM-109046] p 374 N94-28658 vortex-airfoil interaction in a supersonic stream experimental nydroQen ram combustors Aeroacoustic sensitivity analysis and optimal IAD-A275107) p 374 N94-28899 p398 N94-29292 eeroacoustic design of turbomachmery blades SHOCK HEATING Research and development of ramjets/ramrockets. Part (NASA-CR-195786] p 399 N94-30013 Numerical simulation of unsteady aerodynamic heating 1: Integral solid propellant ramrockets STRAKES induced by shock reflections p375 N94-289S2 p398 N94-29294 An experimental investigation of the effect of leading A study of tow emissions gas turbine combustions SONIC BOOMS edge extensions on directional stability and the [NASA-CR-195763] p 399 N94-29860 Nurnencal analysis of sorac boom in the near field effectiveness of forebody nose strakes SHOCK WAVE INTERACTION p376 N94-28962 p400 N94-29728 Wall pressure fluctuations in the reattacnment region Subjective response to tonic booms having different STRESS-STRAIN RELATIONSHIPS of a supersonic tree shear layer shapes, rise times, and durations Prediction of stress-strain response of [NASA-Cfl-195790] p379 N94-29920 [NASA-TM-109090) p417 N94-29464 SCS-6/Timetal-21S subjected to a hypersonic flight SHOCK WAVE PROFILES SOUND INTENSITY profile Numerical simulation of unsteady aerodynamic heating Subjective response to sonic booms having different [NASA-TM-1090261 p 403 N94-2B823 induced by shock reflections p 375 N94-28952 shapes, rise tames, and durations STRUCTURAL ANALYSIS Numerical simulation of steady Mach reflection by shock (NASA-TM-109090) p 417 N94-29464 Effects of repair on structural integrity capturing schemes p375 N94-28953 SOUND PRESSURE (AD-A275756) p 390 N94-28647 SHOCK WAVE PROPAGATION Determination of sound power levels of air terminal units Service life prediction of composite structures through Numerical simulation of steady Mach reflection by shock according to ISO 5135-Nordic inter-laboratory tests, fiber testing capturing schemes p 375 N94-28953 Nordtest project no. 966-91 [AD-A275661] p 403 N94-2B654 SHOCK WAVES [PB94-137411] p416 N94-29175 Thermal/structural tailoring of engine blades Wall pressure fluctuations in the reattachment region SPACE BASED RADAR (T/SEAEBL). Theoretical manual of a supersonic free shear layer Ground independent landing system [NASA-CR-194462] p 409 N94-2B615 [NASA-CR-195790] p379 N94-29920 p38S N94-29564 Structural/aerodynamic blade analyzer (SAB) user's SIGNAL PROCESSING SPACE SHUTTLES guide, version 1.0 Backscafler haze device tor measurement of haze in Wind tunnel testing and research [NASA-CR-194460] p395 N94-29103 aircraft transparencies (NASA-CR-188273] p 402 N94-290S2 Study of bridge design and technology [AD-A275127] p 391 N94-29042 SPACECRAFT DESIGN [PB94-137916] p 373 N94-29160 A novel approach to noise-filtering based on a Code development for hypersonc real-gas flow PerfofnunQ specifications for complex systems' gain-scheduling neural network architecture simulations toward the design of space vehicles, part 2 software p400 N94-29317 [NASA-TM-106563] p 401 N94-30204 p376 N94-28966 STRUCTURAL DESIGN SILENCERS SPACECRAFT LANDING Study of bridge design and technology Boundary layer control device for duct silencers Landing gear energy absorption system [PB94-137916] p373 N94-29160 INASA-CASE-ARC-12030-1] p417 N94-29362 (NASA-CASE-MSC-22277-1] p411 N94-29448 Review of sonic fatigue technology [NASA-CR-4587] 0417 N94-29407 SIMULATORS SPACECRAFT MODELS Simulation of fully automated air traffic control Wind tunnel testing and research Dynamic fracture mechanics analysis for an edge concepts p386 N94-29569 delamination crack [NASA-CR-188273] p402 N94-29052 The Common Modular Simulator (CMS): An architecture [NASA-TM-109106] p 417 N94-29856 SPACECRAFT PROPULSION test bad for future advanced ATM systems Rotorcraft airrrame structural optimization for vibration Some pioUoms of scramjet ^J^PJMOCI for aerospace p386 N94-29582 and dynamic stress reduction including damping planes. Part 1: Scramjet Aims and features SKID LANDINGS treatment p392 N94-29878 p398 N94-2929S Aircraft accident/incident summary report In-flight toss STRUCTURAL FAILURE of control, leading to forced landing and runway overrun. Research and development of ramjets/ramrockets. Part Effects of repair on structural integrity Continental Express. Inc.. N24706 Embraer EMB-120 RT, fc Integral liquid fuel ramjets p 398 N94-29297 (AD-A275756) p 390 N94-28647 Pine Bluff. Arkansas. 29 April 1993 Research and development of ramjets/ramrockets. Pan STRUCTURAL STABILITY [PB94.910404] p382 N94-29402 3: The study of gaseous hydrogen ram combustors Study of bridge design and technology SLOTTED WIND TUNNELS p 398 N94-29298 [PB94-137916) p373 N94-29160 Experimental studies of transonic flow field near a Some problems of scramjet propulsion for aerospace STRUCTURAL VIBRATION longitudinally slotted wind tunnel wall planes. Part 2: Scramjet Development and test Study of bridge design and technology [NASA-TP-3392] P378 N94-29S45 problems p399 N94-29301 [PB94-137916] p373 N94-29160

A-15 SUBJECTINDEX SUBSONIC FLOW

Experimental validation of finite element and boundary SUPERSONIC TRANSPORTS TARGET ACQUISITION element methods tor predicting structural vibration and Combustion for future supersonic transport propulsion ACCS Surveillance Exploratory Prototype (ASEP) p412 N94-29566 radiated noise p 404 N94-29249 [NASA-CR-4561] p412 N94-29552 A study of low emissions gas turbine combustions TARGET RECOGNITION Rotorcraft airframe structural optimization tor vibration (NASA-CR-195763] p 399 N94-29860 ACCS Surveillance Exploratory Prototype (ASEP) p412 N94-29566 and dynamic stress reduction including damping SUPERSONIC WAKES treatment p 392 N94-29876 Numerical study on internal flows of centrifugal TASKS Cognitive approach to specifications on air traffic SUBSONIC FLOW compressors P 395 N94-28977 The 3-D LDV measurements on a 30-degree swept wing controllers' decision assistance systems SUPPORT SYSTEMS p386 N94-29571 with a simulated ice accretion Flight command software development: RAFALE Considerations on graphical user interlaces for intelligent INASA-CR-195327] p 380 N94-30124 studies p415 N94-29320 ATM support systems p 386 N94-29572 Numerical investigation into rngh-angle-ol-anack SURFACE NAVIGATION TAXIING leading-edge vortex flow Automatic control steps for aircraft taxi guidance Automatic control steps for aircraft taxi guidance [PB94-125S64] p 381 N94-30388 p388 N94-29584 p 388 N94-295B4 SUBSONIC WIND TUNNELS SURFACE ROUGHNESS Airside ground movements surveillance The nozzle acoustic test rig: An acoustic and An experimental study of the aerodynamics of a swept p 388 N94-29585 aerodynamic free-jet facility and unswept semispan wing with a simulated glaze ice A novel near-range radar network tor airport surface INASA-TM-106495] p 401 N94-28749 accretion control p389 N94-29586 User's manual tor the model interface and plugboard [NASA-CR-195330) P 381 N94-30152 TECHNOLOGY ASSESSMENT cabinets in the 14- by 22-foot subsonic tunnel Experiments and theoretical considerations regarding Combustion technology needs lor advanced high (NASA-TM-109062) p 381 N94-30176 the allowable roughness height in laminar flow pressure cycle engines p 404 N94-29248 SUPERCOMPUTERS [PB94-125556] P 381 N94-30389 TELESCOPES A method of user interface for NWT SURFACE TEMPERATURE Aircraft system aft telescope cavity configuration study p41S N94-28993 Dual-Band Infrared (DBIR) imaging inspections of Boeing for Stratospheric Observatory lor Infrared Astronomy SUPERCRITICAL AIRFOILS 737 and KC-135 aircraft panels (SOFIA), phase 2 Steady pressure measurements on an Aeroelastic (DE94-005700) p374 N94-29842 INASA-CR. 194266] p 392 N94-2968S Research Wing (ARW-2) SURFACE TREATMENT TEMPERATURE CONTROL (NASA-TM-109046) p 374 N94-28658 Fuel injector design for high temperature aircraft Fuels combustion research SUPERSONIC AIRCRAFT engine p396 N94-29263 IAD-A275122] p 404 N94-29004 Advanced fuel properties: A computer program tor The effect of mechanical paint stripping on the fatigue Application of fuzzy logic to the control of wind tunnel estimating property values and fracture of thin aluminum airplane stoi settling chamber temperature IAD-A275248) p 403 N94-28901 p408 N94-29900 Numerical analysis of supersonic transport wings (NASA-TM-109105) p 402 N94-30200 SURFACE VEHICLES TEMPERATURE DEPENDENCE p375 N94-28959 Three dimensional simulation of compressible flow SUPERSONIC COMBUSTION Particle kinetic simulation of high altitude hypervetoeity induced by a high-speed train moving into a tunnel Scramjet CFD methods and analysis. Part 2: Scramjet p376 N94-28967 flight CFD analysis. Numerical simulation of supersonic mixing (NASA-CR-194535] p 379 N94-29893 SURVEILLANCE and comrnistion applind to scrarnjet uufiiuustor TEMPERATURE DISTRIBUTION Cockpit video: A low cost BDA source p399 N94-29300 The mixing process in the quenching zone of the (AD-A275228] P 395 N94-28389 Fuel-nch catalytic combusuuri of a high density fuel rich-lean-combustion concept p407 N94-29281 ACCS Surveillance Exploratory Prototype (ASEP) (NASA-TP-3281) p 407 N94-29356 TEMPERATURE EFFECTS p412 N94-29566 SUPERSONIC COMBUSTION RAMJET ENGINES Pollutant emissions from and witluii a model gas turbine Arade ground movements surveillanee Numerical study on the interaction between scrarnjet p388 N94-295B5 combustor at elevated pressures and temperatures engine modules caused by thermal choke p406 N94-29271 SURVEILLANCE RAOAR p39S N94-28960 GPS/GNSS for ATM p 385 N94-29565 TEST CHAMBERS Research and Development of Ram/Scramjets and Development of precision runway monitor system for A modernised HST of NLR Turboramjets in Russia inu aasii m capacity of parallel runway operations (AD-B179220) p402 N94-30423 IAGARD-LS-194] p 397 N94-29291 p 389 N94-29587 TEST FACILITIES Introduction and overview of research and development SWEPT WINGS OAM experimental turboramjets p 399 N94-29299 of solid propellent ramrockets. liquid fuel ramjets and Steady pressure measurements on an Aeroelastic TEST STANDS experimental hydrogen ram combustors Research Wing (ARW-2) Technology rigs: A tool for afterburner development p398 N94-29292 [NASA-TM-109046] p 374 N94-2865S p397 N94-29270 Some problems of scramjet propulsion for aerospace The 3-D LDV measurements on a 30-degree swept wing THERMAL ANALYSIS planes. Part 1: Scramjet Aims and features with • simulated ice accretion Thermal/structural tailoring of engine blades p398 N94-29295 (NASA-CR-195327) p380 N94-30124 (T/SEAEBL). Theoretical manual Scramjet CFD methods and analysis. Part 1: Scramjet An experimental study of the i jrodynamcs of a swept [NASA-Cfi-194462] p409 N94-28815 CFD methods. Numerical simulation of the flow in scramjet and unswept semispan wing with a simulated glaze ice THERMAL ENERGY duct p3S8 N94-29296 Accretion Development of global/chemistry model tor jet-fuel Scramjet CFD methods and analysis. Part 2: Scramjet (NASA-CR-195330] p381 N94-30152 thermal fttfllrii'^y bofiod on observatxjns from static and CFD analysis. Numerical simulation of supersonic mixing SWEPTBACK WINGS flowing experiments p 405 N94-29262 and CfOnrtJujiliGfk Bff"*** to scramjet cmnuustm Design end tabncation of forw8rd*sw6pi counterrot&tion THERMAL PROTECTION p399 N94-29300 blade configuration for wind tunnel testing. Fuel injector design for high temperature aircraft (NASA-CR-194868] p 401 N94-28510 Socno problems of scfAnifet propulsion fof •orospftOB engine p 396 N94-29263 SYMBOLS planes. Part 2: Scramjet Development and test THERMAL STABILITY problems p 399 N94-2S301 Aujuipaiisonof three ayciaft attitude Display symbology •tnictures High temperature resistant jet fuels Liquid atomization in supersonic flows p405 N94-29260 p414 N94-29839 IAD-A275172] p 394 N94-29048 SYSTEMS ENGINEERING Research and development of high thermal stability SUPERSONIC FLIGHT On ground system integration and testing: A modem fuels p 405 N94-29261 Experimental investigation of three-dimensional approach p394 N94-29334 Development ol global/chemistry model lor jet-fuel vortex-airfoil interaction in a supersonic stream A disciplined approach to software test and evaluation thermal stability based on observations from static and (AD-A27S107) p374 N94-28899 p416 N94-29339 flowing experiments p 405 N94-29262 SUPERSONIC FLOW The Common Modular Simulator (CMS): An architecture THERMAL STRESSES Experimental investigation of three Uimuiisiuiial test bed for future advanced ATM systems Prediction ol stress-strain response of vortex-airfoil inter action in a supersonic stream p388 N94-295B2 SCS-6/Timetal-21S subjected to a hypersonic flight | AD-A275107] p 374 N94-28E99 SYSTEMS INTEGRATION profile Higher-order accurate numerical simulation of 3D On Qround system mtsQrfition end testing; A modern [NASA-TM-109026J p403 N94-288T3 supersonic mixing layers p 375 N94-289S4 approach p394 N94-29334 Research and development of high thermal stability Numerical simulation of supersonic flow around space Automation of the NDT Diagnostic using neural nets. fuels p40S N94-29261 plane with engine installed p376 N94-28961 Application: Inspection of Airbus longitudinal joints during THERMOCHEMICAL PROPERTIES Study on mixing and injection of hydrogen into a maintenance Advanced fuel properties: A computer program tor [REPT-932-600-104] p 412 N94-29474 supersonic now p 377 N94-28975 estimating property values Air-ground inlegi alien of the ATM system in PHAHE Scramiet CFD methods and analysis. Pan 2: Scramjet (AD4275248] p 403 N94-28901 p388 N94-29579 . CFD analysis. Numerical simulation of supersonic mixing THERMODYNAMIC PROPERTIES 1 SYSTEMS SIMULATION and combustion apf *'^ to scramjet cuHtaistor Particle kinetic simulation ol high attitude hypervetocity The Common Modular Simulator (CMS): An architecture p399 N94-29300 flight tnt bed for future advanced ATM systems Liyarl atomization in supersonc flows |NASA-C«-194535] p 379 N94-29893 p388 N94-295B2 p414 N94-29839 THERMOGRAPHV SUPERSONIC HEAT TRANSFER Dual-Band infrared (DBIR) imaging inspections of Boeing Numerical simutation of •erotnermodynamic heating of 737 and KC-135 aircraft panels hypersonic space transportation vehicles (DE94-005700) p 374 N94-29842 p375 N94-26955 TAIL ROTORS THICKNESS SUPERSONIC JET FLOW Acquisition, design modification, assembly, and ground Dual-Band Infrared (DB1H) imaging inspections of Boeing fltomizfition in supersonic flows test of NPS HuiiuiiijiybuU itifihOwy ftttoted helicopter 737 and KC-135 aircraft panels p414 N94-29839 [AD-A275546] p390 N94-28837 (DE94-005700) p374 N94-29842

A-16 UNSTEADY FLOW SUBJECTINDEX

THREE DIMENSIONAL BOUNDARY LAYER Experimental flight management system TURBOPROP ENGINES Long-wavelength asymptotics of unstable crossflow p388 N94-29580 Aerodynamic characteristics of a propeller-powered modes, including the effect of surface curvature The PHARE advanced tools p 388 N94-29581 high-lift semispan wing [NASA-CR-4579] P 412 N94-29460 TRANSATMOSPHERIC VEHICLES [NASA-TM-4541] P 380 N94-29937 THREE DIMENSIONAL FLOW Numerical study on the interaction between scramjel TURBORAMJET ENGINES Boundary layers induced by three-dimensional vortex engine modules caused by thermal choke Research and Development of Ram/Scramjets and loops p395 N94-28960 Turboramjets in Russia [AD-A275678] P 408 N94-28665 TRANSIENT RESPONSE [ AGARD-LS-I&4] p 397 N94-29291 Proceedings ol the 10th NAL Symposium on Aircraft Evaluation of the transient operation of advanced gas Introduction and overview of research and development turbine combustors P 397 N94-29269 Computational Aerodynamics of solid propellent ramrockets, liquid fuel ramjets and (NAL-SP-19] P375 N94-28946 TRANSITION FLOW experimental hydrogen ram combustors Long-wavelength asymptotics of unstable crossflow p 398 N94-29292 Verification of a three-dimensional viscous flow analysts modes, including the effect of surface curvature tor a single stage compressor P 410 N94-28976 Turboramjet engines: Types and performances (NASA-CR-4579) p412 N94-29460 p 398 N94-29293 Application of flow field simulation to turbine vane TRANSMISSIONS (MACHINE ELEMENTS) design P 395 N94-28978 Research and development of ramjets /ramrockets. Part Experimental validation of finite element and boundary 3: The study of gaseous hydrogen ram combustors Three-dimensional external flow computations using element methods tor predicting structural vibration and p 398 N94-29298 prismatic grid P 410 N94-28979 radiated noise TURBULENCE An elliptic-hyperbolic grid generation method and (NASA-CR-4561) p412 N94-29552 Correction of X hot-wire measurements for gradients application to compressor flows p 395 N94-28981 TRANSMITTER RECEIVERS normal to the plane of the wires A free-wake Euter and Navier-Stokes CFD method and Ground independent landing system [PB94-125473] p 402 N94-30399 p385 N94-29564 its application to helicopter rotors including dynamic stall TURBULENCE EFFECTS [AD-A275416] P 377 N94-29197 TRANSOCEANIC FLIGHT Study of bridge design and technology Numerical simulation of aerothermal characteristics in Opportunities for integrating the aircraft FMS. [PB94-137916] p373 N94-29160 gas turbine combustors with complex geometries aeronautical operational control centers, and future air TURBULENT FLOW P396 N94-29255 traffic management systems in oceanic airspace Similarity between turbulent flows through curved pipe Time-resolved measurements in a three dimensional p387 N94-29577 and orthogonal rotating pipe p 410 N94-28986 model eombustor p411 N94-292B3 TRANSONIC FLOW Numerical modelling ot turbine combustion chambers RNS optimization procedure for three-dimensional Steady pressure measurements on an Aeroelastic p396 N94-29254 composite velocity multi-block applications Research Wing (ARW-2) Numerical simulation of aerothermal characteristics in p412 N94-29534 (NASA-TM-109046] p 374 N94-286S8 gas turbine combustors with complex geometries Unsteady transonic aerodynamics in frequency domain Numerical solution of inverse problem in p396 N94-29255 tor flutter analysis P 379 N94-29879 aerodynamics p 376 N94-28965 Time-resolved measurements in a three dimensional The 3-0 LDV measurements on a 30-degree swept wing Verification of a three-dimensional viscous flow analysis model eombustor p 411 N94-29283 with a simulated ice accretion for a tingle stage compressor p410 N94-28976 Wall pressure fluctuations in the reattachment region [NASA-CR-195327] p 380 N94-30124 Investigation of advanced counterrotabon blade of a supersonic free shear layer The design of a system of codes tor industrial configuration concepts for high speed turboprop systems. [NASA-CR-195790] p 379 N94-29920 calculations of flows around aircraft and other complex Task 2: Unsteady ducted preplan analysis computer TURBULENT MIXING aerodynamic configurations program users manual Higher-order accurate numerical simulation of 3D [PB94-125598] p 381 N94-30387 [NASA-CR-187105] p 399 N94-29438 supersonic mixing layers p375 N94-28954 THREE DIMENSIONAL MODELS Experimental studies of transonic flow field near a Study on mixing and injection of hydrogen into a Higher-order accurate numerical simulation of 3D supersonic flow p 377 N94-28975 supersonic mixing layers p 375 N94-28954 longitudinally slotted wind tunnel wall [NASA-TP-3392] p 378 N94-29545 TVD SCHEMES Three dimensional simulation of compressible flow A design of third-generation airfoils tor helicopter rotor Unsteady transonic aerodynamics in frequency domain induced by a high-speed train moving into a tunnel blades using Navier-Stokes p 391 N94-28957 for flutter analysis p379 N94-29879 p376 N94-2B967 Numerical analysis of sonic boom in the near field TIME Development of a method to predict transonic limit cycle p376 N94-28962 A time reasoning system based on the event calculus oscillation characteristics of fighter aircraft (continued) Numerical analysis of two dimensional/axisymrnetric for scheduling in aeronautic maintenance [NLR-TP-S2156-UJ p 393 N94-30342 non-equilibrium hypersonic flow p 376 N94-28963 [REPT-932-710-101] p 374 N94-29463 TRANSONIC WIND TUNNELS Role ol computational fluid dynamics in aeronautical TIME LAG Experimental studies of transonic flow field near a engineering. Part 10: Numerical analysis of flow around Development of a method to predict transonicfim Ncycl e longitudinally slotted wind tunnel wall 2-D multi-element HLD p410 N94-28964 oscillation characteristics of fighter aircraft (continued) [NASA-TP-3392] p 378 N94-29545 TWO DIMENSIONAL FLOW [NLR-TP-92156-U] p 393 N94-30342 A modernised HST of NLH Calculus of variations applied to 20 multi-point airfoil TIME MARCHING [AD-B179220] p402 N94-30423 design Time-marching aeroelastic and spatial adaptation TRANSPARENCE [PB94-125457] p 381 N94-30401 procedures on triangular and tetrahedral meshes using Back scatter haze device for mn^m *mf*r*r*t of haze in TWO DIMENSIONAL MODELS an unstructured-grid Euler method p 379 N94-29877 aircraft transparencies Role of computational fluid dynamics in aeronautical TIRES [AD-A275127] p 391 N94-29042 engineering. Part 10: Numerical analysis of flow around Asphaltoc concrete performance under heavy fighter TRANSPORT AIRCRAFT 2-D multielement HLD p410 N94-28964 aircraft loading Numerical analysis of supersonic transport wings TWO PHASE FLOW [AD-A275046J p402 N94-29151 p375 N94-28959 Numerical simulation of aerothermal characteristics in TOLUENE gas turbine combustors with complex geometries Fuels combustion research TUNNELS Three dimensional simulation of compressible flow p396 N94-29255 [AD-A275122] p404 N94-29004 Investigation of the two-phase flow in a research TOMOGRAPHY induced by a high-speed train moving into a tunnel p376 N94-28967 eombustor under reacting and non-reacting conditions Dual-Band Infrared (DBIR) imaging inspections of Boeing p411 N94-29282 737 and KC-135 aircraft panels TURBINE BLADES IDE94-005700) p374 N94-29842 Design and fabrication of forward-swept countemnatjon TOWERS blade configuration tor wind tunnel testing u Study of bridge design and technology (NASA-CR-194B68) p 401 N94-28510 [PB94-137916] p373 N94-29160 Thermal/structural tailoring of engine blades UNITED STATES Toxtcrrv AND SAFETY HAZARD (T/SEAEBL). Theoretical manual National Transportation Safety Board annual review of Fire behavior ol aeronautical materials INASA-CR-194462] p 409 N94-28815 aircraft accident data. US general aviation. 1990 [REPT-932-600-105] p 408 N94-29457 Application of flow field simulation to turbine vane [PB94-126869] p 382 N94-29185 TRACKING (POSITION) design p395 N94-28978 UNSTEADY AERODYNAMICS ACCS Surveillance Exploratory Prototype (ASEP) TURBOFAN ENGINES Numerical study on the interaction between scramjet p412 N94-29566 Spffly combustion experiments and numerical engine modules caused by thermal choke TRAILING EDGES predictions p407 N94-29277 p395 N94-28960 Numerical analysis of airfoil for helicopter Made at high Integrated propulsion-Airfranie dynamics and control Unsteady aerodynamic computations around angle of attack using Navier-Stokes code p392 N94-29854 NACA0012 at high angles of attack p 377 N94.28969 p375 N94-2B958 TURBOJET ENGINES Unsteady transonic aerodynamics in frequency domain for flutter analysis p 379 N94-29879 TRAJECTORY ANALYSIS Aerolheiriocfiemical calculatiens in afterburners Advanced air traffic control and flight management P396 N94-29258 Algorithm and code development for unsteady system concepts p387 N94-29576 three-dimensional Navier-Stokes equations CIAM experimental turboramjets p399 N94-29299 Experimental flight management system [NASA-CR-195774J p 414 N94-29942 P388 N94-29S80 TURBOMACHINE BLADES Aeroacoustic sensitivity analysis and optimal TRAJECTORY CONTROL Structural/aerodynamic blade analyzer (SAB) user's aeroacoustic design of turbomachinery blades Profile negotiation: An air/ground automation integration guide, version 1.0 (NASA-Cfl-195786] p 399 N94-30013 concept for managing arrival traffic p 387 N94-2957B (NASA-CR-194460) P 395 N94-29103 Development of a method to predict transonic limit cycle TRAJECTORY OPTIMIZATION Turbomachinery forced response prediction system oscillation characteristics of fighter aircraft (continued) Profile negotiation: An air/ground automation integration (PREPS): User's manual [NLR-TP-92156-U] p 393 N94-30342 concept tor managing arrival traffic p 387 N94-29578 [NASA-CR-194465] p411 N94-29104 UNSTEADY FLOW TRAJECTORY PLANNING Aeroacoustic sensitivity analysis and optimal Boundary layers induced by three-dimensional vortex Air-ground integration of the ATM system in PHARE aeroacoustc design of turbomacftmery blades loops p388 N94-29579 (NASA-CR-195786J p 399 N94-30013 IAD-A275678] p 408 N94-28665

A-17 SUBJECTINDEX UNSWEPT WINGS

An experimental study of wing tip vortex in the near VISCOPLASnclTY Low-speed longitudinal aerodynamic characteristics of wake of a rectangular wing Prediction of stress-strain response of a flat-plate planform model of an advanced fighter [AD-A27S389J P 377 N94-29306 SCS-6/Timetal-21S subjected to a hypersonic flight configuration [NASA-TM-109045] P 377 N94-29443 Investigation of advanced counterrotation Made profile configuration concepts for high speed turboprop systems. (NASA-TM-109026) P 403 N94-2B823 Miniature linear-to-rotary motion actuator p 413 N94-29647 Task 2: Unsteady ducted preplan analysis computer VISCOSITY program users manual Numerical modelling of turbine combustion chambers WIND TUNNEL TESTS Design and fabrication of forward-swept counterrotation (NASA-CR-187105) P 399 N94-29438 p396 N94-29254 blade configuration for wind tunnel testing AeroacoustJc sensitivity analysis and optimal VISCOUS FLOW [NASA-CR-194868] P401 N94-28510 aeroacoustx design of turbomachmery blades Verification of a three-dimensional viscous flow analysis Steady pressure measurements on an Aeroelastic (NASA-CR-195786) p 399 N94-30013 for a single stage compressor p 410 N94-28976 Research Wing (ARW-2) Three-dtmenstona! external flow computations using UMSWEPT WINGS (NASA-TM-109046J p 374 N94-28658 prismatic grid p410 N94-28979 An experimental study of the aerodynamics of a swept A method tor the modelling of porous and solid wind and unswept aemrepan wing with a simulated glaze ice VISUAL ACUITY tunnel walls in computational fluid dynamics codes accretion Bacfcscatter naze device tor measurement of haze in [NASA-CR-195699] p 409 N94-28724 [NASA-CR-195330J P 381 N94-301S2 aircraft transparenoes Wind tunnel testing and research UPSTREAM (AD-A275127] - p391 N94-29042 (NASA-CR-188273) p 402 N94-29052 Experimental investigation of three-dimensional VORTEX BREAKDOWN An experimental study of wing tip vortex in the near vortex-airfoil interaction in a supersonic stream Numerical investigation into high-angie-of-attack wake of a rectangular wing (AD-A275107] p 374 N94-28899 leading-edge vortex flow (AD-A275389) p 377 N94-29306 UPWIND SCHEMES (MATHEMATICS) [PB94-125S64] p 381 N94-30388 Experimental studies of transonic flow field near a Code development for hypersonic real-gas flow VORTICES longitudinally slotted wind tunnel wall simulations toward the design of space vehicles, part 2 Boundary layers induced by three-dimensional vortex (NASA-TP-3392] p378 N94-29545 p376 N94-2896S loops An experimental study of the flowfwld on a semispan Time-marching aeroelastic and spatial adaptation IAD-A275678) p 408 N94-28665 rectangular wing with a simulated glaze ice accretion procedures on triangular and tetrahedral meshes using Experimental investigation of three-dimensional p378 N94-29674 an unstructured-grid Euler method p 379 N94-29877 vortex-airtocl interaction in a supersonic stream An experimental investigation of the effect of leading USER MANUALS (COMPUTER PROGRAMS) [AD-A275107] p374 N94-28899 edge extensions on directional stability and the Thermal/structural tailoring of engine blades Long-wavelength asymptotics of unstable crossflow effectiveness of torebody nose strakes (T/SEAEBL). Theoretical manual modes, including the effect of surface curvature p400 N94-29728 (NASA-CR-194462) p 409 NB4-28815 (NASA-CR-4579) p 412 N94-29460 Algorithm and code development tor unsteady Procedural guide for modelling and analyzing the flight An experimental investigation of the effect of leading three-dimensional Navier-Stokes equations ctuuACtensliLS of a helicopter design using fbghUab edge extensions on directional stability and the [NASA-CR-195774] p 414 N94-29942 (AD-A27S077) p 391 N94-28870 effectiveness of forebody nose strakes The 3-0 LDV measurements on a 30-degree swept wing Structural/aerodynamic Wade analyzer (SAB) user's p400 N94-29728 with a simulated ice accretion [NASA-CR-195327] p 380 N94-30124 guide, version 1.0 Numerical study of the trailing vortex of a wing with Computation of wind tunnel wall effects tor complex [NASA-CR-194460] p395 N94-29103 wing-tip blowing models using a low-order panel method Turbomachmery forced response prediction system fNASA-Cn-195603] p 378 N94-29760 [NASA-TM-104019) p 380 N94-30151 (FHEPS): User's manual Numerical investigation Mo higtvangte-of-attack WIND TUNNEL WALLS [NASA-CR-194465] p411 N94-29104 leading-edge vortex flow A method tor the modelling of porous and solid wind USER REQUIREMENTS (P894-125564) p 381 N94-30388 tunnel watts in computational fluid dynamics codes Use of advanced technologies in ATM (air traffic [NASA-CR-19S699J p 409 N94-28724 management) domain p 384 N94-29561 Computation of wind tunnel wall effects for complex w models using a low-order panel method [NASA-TM-104019] p380 N94-30151 WAKES WIND TUNNELS Boundary layers induced by threo dimensional vortex Holographic interterometry: A user's guide V-23 AIRCRAFT loops [DE94-003136] p 408 N94-28466 Organized wiring systems p408 N94-28705 (AD-A275678J p 408 N94-28665 Performance evaluation of the NWT with parallel V/STOL AIRCRAFT WALL FLOW Fortran p415 N94-28992 Computation of wind tunnel wall effects for complex A ntothod for the mooolunQ of porous end ttotid wind Application of fuzzy logic to the control of wind tunnel models using a tow order panel method tunnel walls in computational ftud dynamics codes settling chamber temperature (NASA-TM-104019) P380 N94-30151 [NASA-CR-195699] p 409 N94-2B724 [NASA-TM-109105] p 402 N94-30200 VANES Experimental studies of transonic flow field near • WINDSHIELDS Thermal/structural tailoring of engine blades longitudinally slotted wind tunnel wall Backscatter haze device for measurement of haze in (T/SEAEBL). Theoretical manual (NASA-TP-3392) p378 N94-29545 •icraft transparencies (NASA-CR-194462) p 409 N94-28815 WALL PRESSURE [AD-A275127] p 391 N94-29042 VAPOR PHASES Wall pressure fluctuations in the raattaehment region WING OSCILLATIONS Numerical simulation of aerothermal characteristics h of a supersonic free shear layer Development of a method to predict transonic limit cycle gas turbine combusuifs with complex goon Millies [NASA-CR-195790] p 379 N94-29920 oscJUation characteristics of fighter aircraft (continued) p396 N94-2925S WATER TUNNEL TESTS [NLR-TP-92156-U] p 393 N94-30342 VECTOR PROCESSING (COMPUTERS) Low-speed longitudinal aerodynamic characteristics of WING PROFILES Performance evaluation of the NWT with parallel a flat-plate planlorm model of an advanced fighter Numerical analysis of supersonic transport wings Fortran p415 N94-28992 p375 N94-28959 A method of user intertace for NWT [NASA-TM-109045] p 377 N94-29443 Numerical solution of inverse problem in p415 N94-28993 WATER VAPOR aerodynamics p376 N94-28965 WING TIP VORTICES VENTILATORS On me affect of emissions from aircraft engines on the Experimental investigation of three-dimensional Determination of sound power levels of air terminal units state of me atmosphere p 414 N94-29247 voitex-airfoQ interaction in a supersonic stream accenting to ISO 5135-Nordic imer-lataoratory tests, WAVE ATTENUATION [AD-A275107] 374 N94-28899 Nordtest proiect no. 968-91 Method for cancelling expansion waves in a wave P An experimental study of wing tip vortex in the near (PB94-137411] p416 N94-29175 rotor wake of a rectangular wing (NASA-CASE-LEW-15218-2) p413 N94-29740 VIBRATION . . [AD-A275389] p 377 N94-29306 Closed loop vibrationa! contra): Theory and WEAPON SYSTEMS WING TIPS applications Testing Operational Flight Piograms (OFP») Experimental investigation of three-dimensional [AD-A275451] p400 N94-28632 p416 N94-29337 vortex-eirfoB Biter action in a supersonic stream VIBRATION DAMPING A disciplined approach to software test and evaluation (AD-A275107J P374 N94-28899 Closed loop vocational controls Theory and p416 N94-2S339 WINGS applications WIND TUNNEL CALIBRATION Experimental investigation of three-dimensional (AD-A275451) p400 N94-2B632 Experimental studies of transonic flow field near a vortex-airfoil nteractjon in a supersonic stream Study of biidge design and technology longitudinally slotted wind tunnel waD (AD-A275107J p37« N94-28899 (PB94-137916J p373 N94-29160 [NASA-TP-3392] p 378 N94-2954S Numerical study of the trailing vortex of a wing with Tuned mass damper for integrally Haded turbine rotor WIND TUNNEL MODELS wng-tjp blowing (NASA-CASE-MFS-28697-1) p411 N94-29353 Variable suit sphere molecular model in me Monte Carlo {NASAOH95803J p 378 N94-29760 simulation of air species p409 N94-28949 Aerodynamic characteristics of a propeller-powered VIBRATION ISOLATORS Rarefied gas numerical wind tunnel Pan 8: HOPE Tuned mass damper for integraDy Haded turbine rotor p401 N94-289SO |NASA-TM-«541J p 3BO N94-29937 (NASA-CASE-MFS-28697-tj ' p411 N94-29353 Numerical simulation of arc heated wind tunnel flow WIRING VIBRATIONAL STATES p 402 N94-2B9S1 NAVAIR iicraft wiri ion and qualification Models for violation-dissociation coupling in Numerical simulation of aeiothermodynamic heating of program p<08 N94-28704 high-temperature gases p4t3 N94-29675 hypersonic space transportation vehicles Organized wiring systems p 408 N94-28705 VIDEO TAPE RECORDERS p375 N94-289S5 WORK FUNCTIONS Cockpit video: A low cost BOA source Wind tunnel testing and research Engineering of systems for application of scientific (AD-A275228J p 395 N94-28389 [NASA-CR-188273] p402 N94-29052 computing m industry p 415 N94-28947

A-18 SUBJECTINDEX WORKSTATIONS

WORKING FLUIDS Method for cancelling expansion waves in a wave rotor (NASA-CASE-LEW.15218-21 p 413 N94-29740 WORKLOADS (PSYCHOPHYSIOLOQV) Information presentation for expert systems in future fighter aircraft [AD-A275126] p 394 N94-2900S WORKSTATIONS ACCS Surveillance Exploratory Prototype (ASEP) p412 N94-29566

A-19 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 305) June 1994

ALMAHROOS. HUSSAIN MOHAMED HASAN BEURRIER, D. Typical Personal Author RNS optimization procedure tor three-dimensional Flight command software development RAFALE Index Listing composite velocity mufb-bloek applications studws P415 N94-29320 p412 N94-29534 BEUTNER THOMAS JOHN AUANO, KANICHI A method tor me moOeUtng ol porous and solid wind Role ot computational fluid dynamics in aeronautical tunnel walls in computational fluid dynamics codes engineering. Pan 10: Numerical analysis ot flow around (NASA-CR-195699] p409 N94-28724 [ PERSONAL AUTHOR | 2-O mum-element MLD p410 N94-28964 BEYER R. ^ AMRO. JOE P. Coosidorstions on prttphic«aJ usor intwtitcos for «iilwJQ6nt The effect of mechanical paint stripping on the fatigue ATM support systems p386 N94-29572 and fracture ot thin aluminum airplane skin BICHAT. N. ANDMSAN1. DOMINJCK, U p406 N94-29900 I— Ate«sl^s»udyreg*rc*>gthead*tionofaftfthcomrol DAISY: A decision aid for an air situation ANDERSON, S. D. system p386 N94-29574 to • fotorcraft in-flight simulator Research and development of high thermal stability BIDDLE. TEOD B. [NASA-CR-193240] p 112 N94-1089S fuels p405 N94-29261 High temperature fuel requirements and payoffs ANDRESEN.O. p405 N94-292S9 Determination ot sound power levels of air terminal units -TTTLE according to ISO 5135-Nordic inter-laboratory tests. BIERS, DAVID W. Nordtest protect no. 968-91 A comparison of three au Liaft attitude display s [PB94-137411] p416 N94-29175 structures ANDREWS, at [AOA275172] p394 N94-29046 Uttra low NO(x) uttra lean gas turbine primary zones BtEZAD. DANIEL J. Listings In this index are arranged alphabetically with squid fuels p397 N94-29267 Modification ol ACSYNT anraft computer program for APPUN, ZACHAHY T. pra»minary design by personal author. The tide of the document [NASA-CR-195737] p390 N94-28817 is used to provide a brief description of the Aerodynamic characteristics of a propeller-powered Ngh-ift semispan wing BLAKE. BOi. subject matter. The report number helps to (NASA-TM-4541) p380 N94-2M37 Opportunities tof IntoQrBtinQ the ufcfein FMS, indicate the type of document (e.g.. NASA ARBUCKLE, P. DOUGLAS aeronautical operational control centers, and future air report, translation, NASA contractor report). The Prose negotiation: An air/ground automation integration traffic m nt systems in page and accession numbers are located concept tor managing arrival traffic p 387 N94-2957B p387 N94-29577 beneath and to the right of the title. Under any ASENStO, SANTIAOO BLOM, HENK A. P. one author's name the accession numbers are High leiiajeiame reiiitant tot fuels The PHARE advanosd tools p388 N94-29561 p405 N94-29260 BO68TTT, PERCY J. arranged in sequence. ASHBT.DALEL. Experimental studies ot transonic flow field near a Computation of wind tunnel wan effects tor complex lon^tudtriiilly stottod wind tunnrt wsll models using a tow-order panel method (NASA-TP-3392J p 378 N94-29545 (NASA-TM-104019] p380 N94-30151 BOERSTOEL.J.W. ABDULAZJZ.M. ASKEW. ROBERTS. The design of a system of codes tor industrial Ultra low NOW ultra teen gas turbine primary zones user's manual tor the model interface and plugboard eatoutaltons of flows around aircraft and other complex with liquid fuels p397 N94-29267 cabinets n the 14- by 22-foot subsonic tunnel ABDULHUSSAIN, U. S. fNASA-TM.109082] p38f N94-30176 [PB94-125598] p381 N94-30387 ASO, SHMEW Ultra tow NO(x) uftra lean gas turbine primary zones BOtSSET,J.P. with liquid fuels p397 N94-29267 Numerical simulation of unsteady aerodynamic heating induced by shock reflections p37S N94-28952 Theoretical and experimental study ot a cylindrical ADACHL NAOHITO AUKIM.it rnknetrip antenna Numerical analysis of airfoil for helicopter Hade at high Scrwnjtt CFD nwthods md aWlyBtt. Pvt 1: Scnunfst [REPT-S32-440-109] p412 N94-294S6 angle of attack using Navier-Stokes code CFD fnMnodv. MuffMncd BJinueBtron of itwflowin vcrBfnjot BONNARD.M. p375 N94-2B958 duct p39B N94-2929B Use of advanced technologies in ATM (air traffic ADAM.V. management) domain p384 N94-29S61 DLR's ATM demonstration piegrarmne BORtES,A p386 N04-2B575 B DAISY: A decision aid for an arsituat irpreta Experimental flight management system p386 N94-29574 p 388 N94-29500 BANTLE, OERHARD ADAMS, CATHERINE A. 8PS/6NSS tor ATM p38S N94.29565 Scramjet CFD methods and anatysn. Part 2: Scramjet Extremely Low Visibility IFR Rotorcratt Approach BARTEU, RICHARD J. CFD analysis. Numerical simulatxxi of supersonic moong (ELVIRA) operational concept development Volume 1: Baekscatter haze device for mi jnment ot haze in and combustion appliad to seramjel eombustor Executive Summary aircraft transparencies p399 N94-29300 IDOT/FAA/RD-94/1.1] p 389 N94-30189 fAD-A275127) p391 N94-29042 BOTTOMLET.D.M. ADAMS. RICHARD J. ARD.GILLES Aircraft evscusoons: The effect of a cabin water spray Extremely Low Visibility IFR Rotorcratt Approach Automation ot the NOT diagnostic using neural nets. system upon evacuation rates and behaviour (ELVIRA) operational concept development. Volume 1: ApjieKJUurt Inspection ot Avbus tongrtudmel joints during [CAA-PAPER-93008) p393 N94-298B7 Executive Summary BOURDAIS.PH. (DOT/FAA/RD-M/1,1] p389 NM-30189 [REPT-e32-600-104] p412 N94-29474 Flight command software development: RAFALE ADELMAN, HENRY & BENOfT. ANDRE studies p41S N94-29320 A study ot tow emissions gas turbine combustions MtBCnin0 InteuiQonov w\ Air T rifnc wunttQCfnont BOWEN, DAVID (NASA-CR-195763) p399 N94-29860 (AOARD-CP-538] p383 N94-2BS56 for air spare control and ADJARDOUZOV P. A. K. P384 N94-29S60 Decision Making Aids (DMA) in on-line ATC systems BO YD, IAIN QAM experimental turboramjets p399 NM-29299 p386 NS4-29570 Ptrtde kinetic simutstion of high altitude hypenntoctty AFFES.H. BERNARD, DENTS fight Boundary layers induced by tr»ee dimeniional vortex A time reasoning system based on the event calculus (NASA-CR-19453S] p379 N94-29893 toops for scnodubnQ in aMfonaUitic neBntonttnc0 BRABBS, THEODORE A. IADA275678] p4O8 N94-2866S (REFT-a32-710-101] p374 N94-29463 Fuel-rich catalytic combustion of a Ngh density fuel AUZADEH.8. BETHKE.K.-H. (NASA-TP-3281) p407 N94-29356 FtowhsW prediction of NOW end smoke production in A novel near-range radar network tor airport surface BRAOO, MICHAEL B. aircraft engines p404 NS4-292S2 control p 389 N94>29566 The 3-0 LDV measurements on a 30-degrea swept wing AUCABIE.H.8. BETTNER. JAMES L. with s s&nulsted ce accretion Uttra tow NO(x) ultra lean gas turbine primary zones (nvMDQBteon of etdvv«C9o oountwrotettjon oisOit (NASA-CR-f95327) p 380 N94-30124 with liquid fuels p397 N94-2B267 configuration concepts for high speed turboprop systems. An experimental study of the aerodynarncs of a swept ALLOUCHE.R. Task 2: Unsteady ducted proptan analysis compulei and uiujwepl semispan wing with a simulated glaze ice DAISY: A decision aid tor an air situation iiilarui elation UIUUJBIII usen manual system p386 N94-29574 [NASA-CR-187105] p 399 N94-29438 INASA-CR-195330] p381 N94-301S2 B-1 PERSONAL AUTHOR INDEX BRASWELL, DOROTHY O.

BRASWELL, DOROTHY O. CINQUE, G. DELORANDE, N. K. An experimental and theoretical study of the Numerical simulation of aerothermal characteristics in Dual-Band Infrared (DBIR) imaging inspections of Boeing aerodynamic characteristics of some generic missile gas turbine combustors with complex geometries 737 and KC-135 aircraft panels concepts at Maori numbers from 2 to 6.6 p 396 NS4-29255 [DE94-005700J P 374 N94-29842 (NASA-TM-109110J p378 N94-29473 CTTENO, J. V. DELHAYE.F. BRAUN. HANS MARTIN The effect of incomplete fuel-air mixing on the lean limit Performing specifications for complex systems' Ground independent landing system and emissions characteristics of a Lean Prevaporized software P400 N94-29317 p385 N94-29564 Premixed (LPP) combustor p 405 N94-29265 DENBRAVEN. W1M Simulation of fully automated air traffic control BRAWLEY, STEPHEN C. CLARK, A. N. concepts P386 N94-29569 ^'Aerodynamic design using parallel processors Airside ground movements surveillance (AD-A27S470] p374 N94-28674 p388 N94-29585 Profile negotiation: An air/ground automation integration concept for managing arrival traffic p 387 N94-29578 BREZINSKY, KENNETH CLARKSON, B. l_ DIEMUNSCH, JOSEPH Fuots combustion resfi&fch Review of sonic fatigue technology Object oriented design of the autonomous fixtaking (AOA275122J p404 N94-29004 [NASA-CR-4587] P417 N94-29407 management system p 363 N94-29323 BROCXENBROUQH, J. R. CLEVENGER, W. B. Role of microstructure on the fatigue durability of DIGIANDOMENICO, B. Thermal/structural tailoring of engine blades On ground systfifn urtogrflOcn &nd testing; A modem aluminum aircraft alloys (T/SEAEBL). Theoretical manual approach p 394 N94-29334 [AD-A275814] p 403 N94-28830 (NASA-CR-194462) P 409 N94-2B815 DIMARTINO, P. BROEK.D. CLOUSER.S. Numerical simulation of aerothermal characteristics in Effects of repair on structural integrity Fuel injector design for high temperature aircraft gas Untune combustors with complex geometries (AD-A275756) p390 N94-28647 engine p396 N94-29263 P396 N94-29255 BROKOF. U. CLOUSER, STEPHEN D. DINI, DINO Contributions of DLR to air traffic miMCity enhancement Combustion technology needs for advanced high Computational and experimental results in high pressure within a terminal area p 385 N94-29567 pressure cycle engines P 404 N94-2924B combustions.erf H2/air and H2/O2/H2O BROUSSET. CHRISTINE COCHRAN, WILLIAM L p406 N94-29268 Automation of the NOT diagnostic using neural nets. Design and construction of the Aerobot Robotic DIPPE.D. Application: Inspection of Airbus longitudinal joints during Manipulator (ARM) Contributions of DLR to air traffic capacity enhancement maintenance IAD-A275362] p409 N94-28894 within a terminal area P 385 N94-29S67 (REPT-932-600-104] p412 N94-29474 COHEN. J. M. DODOS, W. J. BROWN, K. W. Evaluation of the transient operation of advanced gas Fuel injector design tor high temperature aircraft Thermal/structural tailoring of engine blades turbine combustors p 397 N94-29269 engine p396 N94-29263 (T/SEAEBL) Theoretical manual CONUSK.A.T. DOERR, TH (NASA-CR-194462) p 409 N94-28815 Boundary layers induced by three-dimensional vortex The mixing process in the quenching zone of the BRVGIER, JACQUES loops rich-lean-oxnbustion concept p 407 N94-29281 Ada run tame system certification for avionics {AD-A275678J P 408 N94-28665 DOLAN.K.W. applications p394 N94-29332 CORRALL.D. R. Dual-Band infrared (DBIR) imaging inspections ol Boeing 737 and KC-135 aircraft panels BUCCI.R.J. Anide ground movements surveillance Role of microstructure on the fatigue durability of p388 N94-29S85 [DE94-005700] p 374 N94-29842 DONNERJ.T. aluminum aircraft alloys COSTES.B. [AD-A275B14] p 403 N94-28830 Advanced fuel properties: A computer program for Fire behavior of aeronautical materials estimating property values BULZAN. DANIEL L. (REPT-932-600-105J p406 N94-29457 Spray combustion experiments and numerical (AD-A275248) p403 N94-2B901 CROSWELU BENNETT M. predictions p 407 N94-29277 DOYLE. JAMES F. High temperature fuel reoumnents and payoffs Dynamic fracture mechanics analysis for an edge BURALU. B. p40S N94-29259 Theoretical and experimental study of a cylindrical delamRiation crack GROUSE, GILBERT LEWIS, JR. mitiusbip antenna f NASA-TM-109106J p 417 N94-298S6 An analytical study of unsteady rotor/fuselage [REPT-932-440-109] p 412 N94-29456 DRENNAN, & A. interaction in hovor and forward flight Pollutant emissions from and within a model gas turbine BURGGRAF, O. R. P379 N94-29826 combustor at elevated pressures and temperatures Boundary layers induced by three-dimensional vortex CUNNINGHAM, ATLEE M, JR. p406 N94-29271 loops Development of a method to predict transonic limit cycle DUBBIN, P. F. IAD-A275678] p 408 N94-28665 oscillation characteristics of fighter aircraft (continued) Dual-Band Infrared (DBIR) imaging inspections of Boeing [NLR-TP-921564J] p393 N94-30342 737 and KC-135 aircraft panels [DE94-005700] p374 N94-29842

CAMBIAGGIO. E. Theoretical and experimental study of a cylindrical DAIOUJI, HISAAKI mictusliip antenna Higher-order accurate numerical simulation of 3D ECKSTROM, CLINTON V. [REPT-932-440-109] p 412 N94-29456 supersonic mixing layers p 375 N94-2B954 Steady pressure measurements on an Aeroelastic CAMPBELL. MALCOLM J. Research Wing (ARW-2) DASS.S.M. Th o fBffMXrn *\^f* T hydioxyt tocnnojuo [NASA-TM-109046] p 374 N94-2865B Asphaltc eonaele pertormince under heavy fighter p 414 N94-2B600 EDWARDS, T. affcraft loading Research and development of high thermal stability CARNEY. USA A. (AD-A275046) P402 N94-29151 Evaluation of access/navigational features of a fuels p40S N94-29261 DASS.W.C. graphical-user nterface installed on a poilable EQAMI, KCHCHI Asphaltic concrete performance under heavy lighter maintenance aid Role of computational fluid dynamics in aeronautical IAD-A275791) p 383 N94-28744 engineering. Part 10: Numerical analysis of flow around (AO-A27S046] p402 N94-29151 CARR, L. PHILIP 2-D multi-element HLD p 410 N94-2B964 DA VIS. STAN EHMAN.D. Radar jet engine health m Aircraft tge impact on vKfividual oporatng end tuppoft IASSGI-301] p400 N94-30130 Paytoad central control for unmanned aircraft CARRIERS, B. p 401 N94-302B4 [AD-A275739] p373 N94-28732 EHRHART, JOHN E, JR. Fire behavior of aeronautical matenals DAVIS, THOMAS J. KC-135 cockpit modernization study and crew reduction [REPT-932-600-105] p 408 N94-29457 Design of Center-TRACON Automation System feasibility demonstration CASSKSNEUL, V. p385 N94-29568 [AD-A275230] p 392 N94-29391 How to control tho mcrB&BO in tho cornptoxity of civil DEAN, GARFIELD EICKHOFF, H. aircraft on-board systems p 394 N94-29316 The PHARE advanced foots p388 N94-29581 Investigation of the two-phase flow in a research CASTNER. RAYMOND S. PEBHUTN.A.C. combustor under reacting and non-reacting conditions Thfi fKJiZte ftCOUAbC tBSt riQZ An ECTT^IStlC V)d Experiments and ttieuioucal consideretions reuaiUuig P411 N94-292B2 aerodynamic free-jet factory the allowable roughness height in laminar flow EMERSON. JANET M. [NASA-TM-106495] p 401 N94-28749 (P894-125556) p 381 N94-30389 KC-135 cockpit modernization study end crew reduction CHANET.P. DDCK.A. feasibility'demonstration How to ciwilJij ittB (Hcnm*) fi tti0 coRipiGJuty of CIVH Investigation of the two-phase flow in a research [AD-A275230] p 392 N94-29391 aircraft on-board systems 394 N94-2B316 P combustor under reacting and norKMCtJng concfilima ENDSLEY, MICA R. CHEN. KUO-HUEY p411 N94-292B2 Infcrmation presentation for expert systems in future Sony combustion oxpttrimonts And nLvnsnct) DEJEU.C. fiufilef aver aft prexictiora p407 N94-29Z77 Aerathermochemica! calculations in afterburners (AD-A275126) p 394 N94-29005 CHESNEY, R.H. p396 N94-29258 ERZBERGER. HEINZ PaykMd central control for unmanned aircraft OELANEV. ROBERT A. Design of Center-TRACON Automation System p401 N94-30284 Investigation of advanced counterrotation blade P385 N94-29568 CHOUDHARI, MEELAN configuration concepts for high speed turboprop systems. EVERHART, JOEL L. Long-wavelength asymptotics of unstable crossflow Task 2: Unsteady ducted proptan analysis computer Experimental studies of transonic flow field near a modes, including the effect of surface curvature program users manual longitudinally slotted wind tunnel wan (NASA-Cfi-4579) P412 N94-29460 (NASA-CR-187105) P 399 N94-29438 (NASA-TP-3392) p 378 N94-29545 B-2 JACOB, THOMAS PERSONAL AUTHOR INDEX

F GORVAD, M. R. HERRING, ROBERT W. Dual-Band Infrared (DBIR) imaging inspections of Boeing HATT-X: A high performance frying laboratory tor autonomous unmanned aircraft research and FEARNSIDES. JOHN J. 737 and KC-135 aircraft panels development p393 N94-30293 Advances in development capabilities tor intelligent air [DE94-OOS700] p374 N94-29842 traffic management systems P 384 N94-29559 GRAND), E. HILL, A. G. Experiences with the HOOD design method on avionics Airside ground movements surveillance PICK, GREGORY J. p388 N94-29S85 Acquisition, design modification, assembly, and ground software development p41S N94-29325 test of NPS Hummingbird remotely piloted helicopter GREEN, STEVEN HINKLE, A. J. (AD-A275546) p 390 N94-28837 Design of Center-TRACON Automation System Role ol microstructure on the fatigue durability of p385 N94-29568 aluminum aircraft alloys FtNNEY, J. M. GREEN, STEVEN M. COM expansion and interference tor extending the [AD-A27S614) p403 N94-28830 Profile negotiation: An air/ground automation integration HIROSE, NAOKI fatigue fife of multi-layer metal (twits concept tor managing arrival traffic p 387 N94-29S78 [AD-A274982) P 410 N94-28091 Numerical analysis ot airfoil for helicopter blade at high GRIGGS. D. angle of attack using Navier-Stokes code FIXLER, RICHARD & Holographic interim ume try A user's guide p 375 N94-2B958 Rooftop emergency heliports (OE94-003136J p408 N94-28466 [DOT/FAA/RD-93/2] p 402 N94-29754 HUBOWICKI, ANDRZEJ GWALTNEY, DAVID A. Intelligent systems tor air space control and FONTAINE, SCOTT A. Application of fuzzy logic to the control of wind tunnel Extremely Low Visibility IFR Rotorcraft Approach management p384 N94-29560 settling chamber temperature HOADLEY. D. (ELVIRA) operational concept development Volume 1: [NASA-TM-109105] P 402 N94-30200 Executive Summary Full-scale testing and analysis of curved aircraft fuselage [DOT/FAA/RD-94/1.1] p 389 N94-30189 panels FRANCINI, R. H [AD-A275666] p 390 N94-28657 Effects of repair on structural integrity HOANG, P. IAD-A275756) p 390 N94-28647 Los Angeles international airport instrument landing HAAS, BRIAN L. FRON, XAVIER system approach data collection and reduction, phase 1 Partde kinetic simulation of high altitude hypervelocity (AD-A275115) p383 N94-28914 ARC2000: Automatic radar control flight HOEUMAKERS, H. W. M. p388 N94-29583 (NASA-CR-194535] P379 N94-29893 Numerical investigation into high-angle-of-attack FU, AN-KUO HALL, EDWARD J. An experimental investigation of the effect of leading leading-edge vortex flow Investigation of advanced counterrotation blade [PB94-125564J p 381 N94-303B8 edge extensions on directional stability and the configuration concepts for high speed turboprop systems. HOEKSTRA, WILLEM E. effectiveness of forebody nose strokes Task 2: Unsteady ducted preplan analysis computer Use of GPS in automated air traffic control p400 N94-2972B program users manual p384 N94-29563 FUJI), KOZO (NASA-CR-187105] p399 N94-29438 HONG, YANHUA Numerical simulation of supersonic flow around space HALL. KENNETH C. Enhanced fatigue crack detection in aging aircraft using plane with engine installed p376 N94-28961 Aeroacoustjc sensitivity analysis and optimal continuous acoustic emission monitoring Code development tor hypersonic real-gas flow BOroscoustic dosifln ot turboniflchjnofy btodos [DREP-93-16] P393 N94-30131 simulations toward the design of space vehicles, part 2 (NASA-CR-195786] p 399 N94-30013 p 376 N94-28966 HAMAZAKI, HIROSHI HU, T. C. J. Recent CFD applications in small gas turbine combustion Three dimensional simulation of compressible flow Application of flow field simulation to turbine vane systems development p 396 N94-29257 induced by a high-speed train moving into a tunnel design p39S N94-28978 p376 N94-28967 HUANG, L.-M. HANCOCK, JOHN Reduction of NO(x) by fuel-staging in gas turbine FUJI), SHOICHI Object oriented design of the autonomous fixtaking Numerical analysis of sonic boom in the near field management system p 383 N94-29323 engines: A commitment to the future p406 N94-29272 P376 N94-2B962 HANSEN, CHRISTOPHER P. FUKUDA, MASAHIRO LsndtnQ QB&T onofQy *h*^^*faftH system HUGHES. THOMAS C. Verification ol a three-dimensional viscous flow analysis (NASA-CASE-MSC-22277-1) p411 N94-29448 KC-135 cockpit modernization study and crew reduction tor a single stage compressor p 410 N94-28976 feasibility demonstration HARDY, M, a [AD-A275230] p 392 N94-29391 Performance evaluation of the NWT with parallel Asphaltic concrete performance under heavy fighter Fortran p415 N94-28992 HUMPHREYS. GREGORY L avcraft loading Application of fuzzy logic to the control of wind tunnel (AD-A275046) p402 N94-29151 settling chamber temperature HARRIS, SCOTT H. [NASA-TM-109105] p 402 N94-30200 Computation of wind tunnel wall effects for complex HUNTER. R. D. models using a tow-order panel method Air-ground integration of the ATM system in PHARE GAEBLER. K. (NASA-TM-104019] p 380 M94-30151 ACCS Surveillance Exploratory Prototype (ASEP) p388 N94-29579 HARRISON, CATHERINE p412 N94-29566 Radar jet engine health monitoring protect GATUN, GREGORY H. [ASSGI-301) p400 N94-30130 Low-speed longitudinal aerodynamic characteristics of HARRISON, W. E. a flat-plate planform model of an advanced fighter Research and development of high thermal stability IANOVSKI, LEONID & configuration fuels p405 N94-29261 Endothermc fuets tor hypersonic aviation [NASA-TM-10904S] p 377 N94-29443 HARTL, PHIUPP p407 N94-29285 GEISELMAN, ERIC E. Ground independent landing system KURASHI. YUMINOBU A comparison of three auciaft attitude display symbotogy p385 N94-29S64 Transonic expanding flow through axially symmetric structures orifices p410 N94-28985 HASHIMOTO. KEISUKE (AD-A275172] p 394 N94-29048 INGLE. G. Verification of a three dimensional viscous flow analysis GENTRY, GARL l_ JR. Experimental flight management system tor a single stage compressor p 410 N94-28976 Aerodynamic characteristics of a propeller-powered p 388 N94-29580 high-lift semispan wing HASSA.C. (SHIOAKI, HIROSHI [NASA-TM-4541] p 380 N94-29937 Investigation ol the two-phase flow in a research Similarity between turbulent flows through curved pipe combustor under reacting and non-reacting conditions and orthogonal rotating pipe p 410 N94-28986 OHIO, G. p411 N94-29282 Theoretical and experimental study of a cylindrical ISHIQURO, MITSUO HATAMA, HARUO nvcroslnp antenna . . Numerical analysis ol airfoil tor helicopter blade at high A method of user interface for NWT (REPT-932-440-109) p 412 N94-29456 angle ot attack using Navier-Stokes code p415 N94-28993 GIBBONS, K. A. p375 N94-28958 HAYASHI, UASANORI ISHUAKA, KOICHI The effect of incomplete fuel-air mixing on the lean limit Nunwnc&l simulation of unstosdy ftorodynAnuc nofltmQ and emissions characteristics of a Lean Prevaporized Higher-order accurate numerical simulation of 3D induced by shock reflections p375 N94-289S2 supersonic mixing layers p 375 N94-289S4 Promoted (LPP) combustor p 405 N94-29265 rro, KATSUHIRO CLASSMAN, IRVIN HEGELS. HERMANN F. Use of GPS in automated air traffic control Numerical simulation of steady Mach reflection by shock Fuols cofittwstion rosofirch p384 N94-29563 capturing schemes P375 N94-28953 (AD-A275122) p404 N94-29004 MENDERS. M.G. GONZALES, DAVID ALBERT Paytoad central control tor unmanned aircraft Models for vibration-dissociation coupling in p 401 N94-30284 high-temperature gases p413 N94-29675 OOODEN. J. H. M. HENDRICK, ROBERT JAARSMA, F. ' Correctnn of X hot-wire measurements tor gradients Software Management Environment (SME) concepts A modernised HST of NLR normal to me plane of the wires and architecture, revision 1 (AD-B179220] p402 N94-30423 [PB94-12S473) p402 N94-30399 [NASA-CO-189293 ] p416 N94-29727 JABLONSKI, D. A. GOODWIN, 0. J. HENNECKE, D. K. Development of Alternating Current Potential Drop SOE's for the year 2000 and beyond: An EF The mixing process in the quenching zone of the (AGPO) procedures tor crack detection in aluminum aircraft perspective p 416 N94-29344 nch-tean-combustxxi concept p 407 N94-29281 panels GORDON, J. LEA HENNINGER. SANDRA (AD-A275755) p 408 N94-2B646 A disciplined approach to software test and evaluation Rooftop emergency heliports JACOB, THOMAS p416 N94-29339 [DOT/FAA/RD-93/2] P 402 N94-297S4 GPS/GNSS for ATM p 385 N94-29565

B-3 PERSONAL AUTHOR INDEX JANICKA, J.

JANICKA, J. KOBUSH, T. R. LOWHIE. B. W. Numerical modelling ol turbine combustion chambers Fuel injector design for high temperature aircraft Combustion for future supersonic transport propulsion p 396 N94-29254 engine p 396 N94-29263 p 404 N94-29249 JECKEL, H. KOPCHENOV, V. Time-resolved measurements in a three dimensional Scramjet CFD methods and analysis. Pan 1: Scramjet model combustor p411 N94-29283 CFD methods. Numerical simulation of the flow in scramjet M JOHNSON, JOHN duct P398 N94-29296 MAGNUSEN, P. E. Au craft age impacts on maintenance requirements Scramjet CFD methods and analysis. Part 2: Scramjet Role of microstructure on the fatigue durability of (AD-A275701) p373 N94-28666 CFD analysis. Numerical simulation of supersonic mixing aluminum aircraft alloys JOHNSON. W. STEVEN and combustion applied to scramjet combustor [AD-A275814) p403 N94-28830 Prediction ol stress-strain response of p399 N94-29300 MAHUCH.S.E. SCS-6/Timetal-21S subjected to a hypersonic flight KOURA, KATSUHISA Interactive analysis and planning tools for air traffic and profile Monte Carlo simulation or normal shock wave. Part 2: airspace management p 386 N94-29573 [NASA-TM-109026] p 403 N94-28823 VHS model and VSS model p409 N94-28948 MAIDHOF. S. JONASSON.KG. Variable soft sphere molecular model in the Monte Carlo Numerical modelling of turbine combustion chambers Determination ol sound power levels of air terminal units simulation of air species p 409 N94-28949 p396 N94-29254 according to ISO 5135-Nordic inter-laboratory tests. Rarefied gas numerical wind tunnel. Part B: HOPE MALA.W. Nordtest protect no. 968-91 p 401 N94-28950 Experiences with the HOOD design method on avionics [PB94-137411J p416 N94-29175 software development p415 N94-29325 JONES. E.G. KRIHA. K. R. MARCHMENT, A. D. Development of global/chemistry model for jet-fuel Advanced fuel properties: A computer program for The influence of air distribution on homogeneity and thermal stability based on observations from static and estimating property values pollutant formation in the primary zone of a tubular flowing experiments p 405 N94-2S262 [AD-A27S248] p403 N94-28901 KRISS, JORDAN R. combustor p406 N94-29274 KC-135 cockpil modenuzation study and crew reduclxxi MARKOV, ALEX B. feasibility demonstration HATT-X: A high performance flying laboratory for IAD-A275230) P392 N94-29391 autonomous unmanned aircraft research and development p393 N94-30293 KABAMBA. PIERRE T. KRJUKOV, V. MARRA. JOHN J. Closed loop vibrational control: Theory and Scramjet CFD methods and analysis. Part 1: Scramjet Tuned mass damper tor integrally btaded turbine rotor applications CFD methods. Numerical simulation of the flow in scramjet [ NASA-CASE-MFS-28697-1J p 411 N94-29353 (AD-A27S451) p400 N94-28632 duct p398 N94-29296 KAJI, SHOJIRO MATSUMOTO, HIROAKI KUECHENMEISTER, DAVID R Numerical study on the interaction between scramjet Monte Carlo simulation or normal shock wave. Part 2: A non-linear simulation for an autonomous unmanned engine modules caused by thermal choke VMS model and VSS model p409 N94-28948 air vehicle p395 N94-28960 Variable soft sphere molecular model in the Monte Carlo [AD-A275062] p 391 N94-29200 Study on mixing and injection of hydrogen into a simulation of air species p409 N94-28949 supersonic flow p 377 N94-2B975 KURAS.C. Rarefied gas numerical wind tunnel. Pan 8: HOPE KALKHORAN, I RAJ M. Fire behavior of aeronautical materials p 401 N94-28950 [REPT-932-600-105J p 408 N94-29457 Experimental investigation of three-dimensional MATSUNAGA, KOJI KURODA. SHINICHI vortex-airfoil interaction in a supersonic stream Application of flow field simulation to turbine vane Numerical simulation of supersonic flow around ypftfl** [AO-A275107] p 374 N94-28899 design p395 N94-28978 plane with engine installed p 376 N94-28961 KAMIN, RICHARD A. KUROTAKL TAKUJI MATSUOKA. AKINORI Combustion technology needs tor advanced high Numerical analysis of two dimensional/axisymmetric Verification of a three-dimensional viscous flow analysis pressure cycle engines p 404 N94-29248 non-equilibrium hypersonic flow p376 N94-28963 for a single stage compressor p 410 N94-28976 KANDA, TAKESHI MATSUZAKI, TATSUYA Numerical simulation of steady Mach reflection by shock Performance evaluation of the NWT with parallel capturing schemes p 375 N94-28953 Fortran p 415 N94-28992 KARUBE, YUKIHIRO MAUDRY, BERNARD A method of user interface tor NWT LAANANEN, DAVID H. ARC2000: Automatic radar control p415 N94-28993 Crashworthmess analysis of commuter aircraft seats P388 N94-29583 [AD-A275889] p382 N94-28799 KATTA. V. R. MC8RIDE.S.L. Development of global/chemistry model for jet-fuel LABRUJERE, T. E. Acoustic emission nxxvtonng of aging aircraft thermal stability based on observations from static and Calculus of variations applied to 2D multi-point airfoil structures flowing experimenU) p 405 N94-28262 [DREP-03-17J P393 N94-30129 KEPERT.J. 1_ [PB94-125457] p381 N94-30401 LEOUILLOU, MARC MCBR1DE. STUART L Fishermans Bend: A tentie of Australian aviatjon Enhanced fatigue crack detection in aging aircraft using (AD-A274981] p 373 N94-29090 The PHARE advanced tools p388 N94-295B1 LEROUX, MARCEL continuous acouAbc emssion monitonng KERHO. MICHAEL K. Cognitive approach to specifications on air traffic [DREP-93-16] p393 N94-30131 The 3-D LDV measurements on a 30-degree swept wing controllers' decision assistance systems MCCALDON.K. with B simulated ice Accretion P386 N94-29S71 Design aspects in small aircraft gas turbine fuel (NASA-Cfl-195327) P380 N94-30124 LEVIN. KERRY M. injectors p397 N94-29264 KHAN, AZHAR MANSUR Advances in development capabilities for ntefljyoiil air MCCURDY, DAVID A. Helicopter mission and fOUw perform traffic management systems p 384 N94-29559 Subjective response to sonic booms having different with quasMinear inflow theory p392 N94-29594 UAW, CHYUAN-HSYAN PAUL shapes, rise times, and durations KHATIB, F. M. Aircraft aerodynamics with deflected jets in ground (NASA-TM-109090] p417 N94-29464 Pollutant ernssions from and within a model Qas turbine effect p380 N94-29973 MCGRATH, BRIAN E. combustor at elevated pressures and temperatures UGHSTONE, LEONARD Low-speed longitudinal aerodynamic characteristics of p406 N94-29271 Radar jet engine health monitoring project a flat-plate planform model of an advanced fighter KHODADOUST, ABDOLLAH (ASSGI-301] p400 N94-30130 An experimental study of the flowfield on a semispart UM, HOCK-BIN (NASA-TM-109045) p 377 N94-29443 rectangular wing with a simulated glaze ice accretion Numerical study of the traffing vortex of a wing with MCKINNEY. R. G. p376 N94-29674 wing-tip blowing Reduction of NO(x) by fuel-staging in gas turbine KIKUCHL KAZUO [MASA-CR-195803] p 378 N94-29760 engines: A commitment to the future Verification of a throe dimensional viscous flow analysis LOEVE.W. p406 N94-29272 for a single stage compressor p 410 N94-28976 Engineering of systems for application of scientific MCVANEY, GARY P. Application of flow field simulation to turbine vane computing m industry p 415 N94-28947 Procedural guide for modelling and analyzing the flight design p395 N94-28978 LOKENSQARO. ROLF M. characteristics of a helicopter design using ffightlab A moment plotting method for characterizing aircraft KIRS. ESIN O. | AD-A275077] p 391 N94-28870 0 fatigue data population distributions Information p^so ^*^ for expert systems in future MEERKOV, SEMYON M. [AD-A275500J p390 N94-28660 fighter aircraft Closed loop vibrational control: Theory and LOMKOV, K. IAD-A275126] p394 N94-29005 applications Scramjet CFD methods and analysis. Part 1: Scramjet (AD-A275451J p 400 N94-28632 KIRSTETTER, B. uf*u ineUimls. Numerical suinjlaTmiof the flown scramiei Air-ground integration of the ATM system in PHARE duct p398 N94-29296 MEUER.JOSJ. p388 N94-29S79 Scram|et i^r*i/ methods and analysis. Part 2: Scramjet Development ol a method to predict transonic limit cycle KISTLER DAVID CFD analysis. Numerical simulation of supersonic mixing escalation characteristics of tighter aircraft (continued) Software Management Environment (SME) cu«.«uu and combustxjn apnliod to scramjet miiKjbStiw [NLR-TP-92156-U) p 393 N94-30342 and architecture, revision 1 p399 N94-29300 MEINER. THOMAS (NASA-CR-189293) p 416 M94-29727 LOPEZ. G. NAVAIR aircraft wiring standardization and qualification KLOSTERMANN, E. Effects of hydrogen addrbon on poDutant emisiiuns in program p 408 N94-28704 DLR's ATM demonslialiei'i piogramme a gas turbine combustor p 406 N94-29275 Organized wiring systems p 408 N94-28705 p386 N94-29575 LOWER, M.C. MERRILL, W. KOBAYAKAWA, MAKOTO Affcraft evacuations: The effect of a catxn water spray A novel approach to noise-filtering based on a Application of digital control theory to adaptive grid system upon evacuation rai8& and bettav>our gain-scheduling neural network architecture p415 N94-28980 [CAA-PAPER-93008) p 393 N94-29887 (NASA-TM-106563) p 401 N94-30204

B-4 PERSONAL AUTHOR INDEX RICCARDI, G.

MERRITT. SYLVIA A. N Fuel-rich catalytic combustion ol a high density luel INASA-TP-3281) P407 N94-29356 NAGASHIMA, TOSHIO PADUANO, C. Numerical simulation of aerothermal characteristics in MEUNIER. S. Numerical study on internal flows of centrifugal Aerothermochemical calculations in afterburners compressors p 395 N94-28977 gas turbine combustors with complex geometries p396 N94-29255 p396 N94-29258 NAKADATE, MASAAKI PAOUOT, D. MEYER-HILBERG, JOCHEN A design of third-generation airfoils for helicopter rotor Performing specifications for complex systems' GPS/GNSS tor ATM p 385 N94-29S65 blades using Navier-Stokes p 391 N94-28957 NAKAHASHI, KAZUHIRO software p400 N94-29317 MIKAMI, H1SASHI Numerical analysis of sonic boom in the near field PARK, SUKJUNE Transonic expanding flow through axially symmetric p376 N94-28962 Decoupled flight control system design using the singular orifices P410 N94-28985 Three-dimensional external flow computations using perturbation method p 400 N94-29850 MILLER, CLYDE prismatic grid p 410 N94-28979 PARKER, C. A. Opportunities for integrating the aircraft FMS. NAKAMICHI, JIRO Advanced fuel properties: A computer program for aeronautical operational control centers, and future air Unsteady aerodynamic computations around estimating property values traffic management systems in oceanic airspace NACA0012 at high angles of attack p 377 N94-28969 IAD-A275248) p 403 N94-26901 p387 N94-29577 NAKAMURA, SHINQO PAXSON, DANIEL E. MILLER. JOSEPH Role of computational fluid dynamics in aeronautical Method tor cancelling expansion waves in a wave Opportunities for integrating the aircraft FMS, engineering. Part 10: Numerical analysis of flow around rotor aeronautical operational control centers, and future air 2-D murb-elemem HLD p 410 N94-28964 INASA-CASE-LEW-15218-2] p413 N94-29740 traffic management systems in oceanic airspace NAKAMURA, SHUICHI PELOCHE, LUIS M. p 387 N94-29577 Performance evaluation of the NWT with parallel High temperature resistant jet fuels MILLER. L. Fortran p415 N94-28992 p405 N94-29260 Scramjet CFD methods and analysis. Part 1: Scramjet NAKAMURA, TAKASHI PEREZ-ORTIZ. R. M. CFO methods. Numerical simulation of the flow in scramjet Performance evaluation of the NWT with parallel Ducted kerosene spray flames p 407 N94-29276 duct p398 N94-29296 Fortran p 415 N94-28992 PEREZ, RONALD A. MILLS, S. NAKAO. MASAHIRO Integrated propulsion-airframe dynamics and control The effect of incomplete fuel-air mixing on the lean limit Numerical analysis of airfoil tor helicopter Made at high p 392 N94-29854 and emissions characteristics of a Lean Prevaporized angle of attack using Navier-Stokes code PETERSON, C. 0. Premixed (LPP) comtaustor p405 N94-29265 p375 N94-28958 Pollutant emissions from and within a model gas turbine MIRDAMADI. MASSOUO Code development for hypersonic real-gas flow combustor at elevated pressures and temperatures Prediction of stress-strain response of simulations toward the design of space vehicles, part 2 p 406 N94-29271 SCS-6/Timetal-21S subjected to a hypersonic flight P376 N94-28966 PETRE, ERIC profile NEUHART. DAN H. The PHARE advanced toots p 388 N94-29581 [NASA-TM-109026] p 403 N94-28823 Low-speed longitudinal aorodynamc characteristics of PLANCHON, P. MISSOUM, AZZEDINE a flat-plate planform model of an advanced fighter Use of advanced technologies in ATM (air traffic Liquid atomization in supersonic flows configufation management) domain p384 N94-29561 p414 N94-29839 [NASA-TM-109045] p 377 N94-29443 POH.ENG-KEE MIYASATO, S. M. NEWMAN. ROBERT & Closed loop vrbraoonal control: Theory and Role of rmcrostructure on the fatigue durability of Potential hazards of magnetic resonance imagers to applications aluminum aircraft alloys emergency medical service helicopter operations [AD-A275451] p 400 N94-28632 [AD-A275814) p 403 N94-28830 [OOT/FAA/RD-92/15] p 382 N94-29862 POLLARD. M. D. MIYATA. KAZUHITO NICHOLS. G. H. Acoustic emission monitoring of aging aircraft Unsteady aerodynamic computations around Design and fabrication of forward-swept counterrotation structures NACA0012 at high angles ol attack p 377 N94-28969 Made configuration tor wind tunnel testing [DREP-93-17] p393 N94-30129 POLLARD, MICHAEL MOEHLENKAMP, KLAUS (NASA-CFM94868) p 401 N94-28510 Enhanced fatigue crack detection in aging aircraft using Automatic control steps tor aircraft taxi guidance NICKS. ORAN W. continuous acoustic emission monitoring p388 N94-29584 Wind tunnel testing and research (DREP-93-16] p 393 N94-30131 MONACO. M. [NASA-CR-188273] p402 N94-29052 NICOLAON, JEAN-PIERRE POMERET, JEAN-MARC Theoretical and experimental study of a cylindrical Decision Making Aids (DMA) in on-line ATC systems mtcrostrtp antenna ARC2000: Automatic radar control p388 N94-29563 p386 N94-2957O [REPT-932-440-109) p412 N94-294S6 PROCIW, L. A. NOZAKLOSAMU MONGIA, HUKAM C. Recent CFD applications in small gas turbine combustion Verificatirxi of a threo dimensional viscous flow analysis Application of CFD in combustor design technology systems development p396 N94-292S7 tar a single stage compressor p410 1494-28976 p396 N94-29256 Design aspects in small aircraft gas turbine luel MOREL, M. R. Application of flow field simulation to turbine vane injectors p 397 N94-29264 Structural/aerodynamic Made analyzer (SAB) user's design p395 N94-28978 guide, version 1.0 [NASA-Cfi-194460] p 395 N94-29103 Turbomachinery forced response prediction system (FREPS): User's manual OUINTO, P. FRANK [NASA-CR-194465] p411 N94-29104 User's manual for the model interface and plugboard OBAYASHI, SHIGERU cabinets in the 14- by 22-foot subsonic tunnel MORIN, GREGORY S. Algorithm and code development tor unsteady Sofvico Wo prediction of composrto structures ttvouQti [NASA-TM-109062J p38t N94-30176 tnree-drmensional Navier-Stokes equations QUINTO, ROGER A. fibGr tBSttRQ [NASA-CR-195774) p414 N94-29942 [AD-A275661] p 403 N94-28654 Evaluation of access/navigational features of a OBUKATA. MASAHIRO graphical-user interface installed on a portable MORISHIGE, HIROSHI A design of third-generation airfoils for helicopter rotor maintenance aid A method of user interface for NWT blades using Navier-Stokes p 391 N94-28957 [ AD-A275791) p 383 N94-28744 p415 N94-28993 OGAWA, TAKANOBU MOSES, CLIFFORD Three dimensional simulation of compressible flow Endotherrrac fuels tor hypersonic aviation induced by a high-speed train moving into a tunnel p407 N94-29285 P376 N94-28967 MOSS, J. B. RAHMAN, S. Flowfietd prediction of NO(x) and smoke production in OHYAMA. KENICHI Effects of repair on structural integrity aircraft engines p 404 N94-29252 Numerical simulation of unsteady aerodynamic heating [AD-A275756] p 390 N94-28647 MUIR. H. c. induced by shock reflections p375 N94-28952 RAMAPRIAN. B. R. Aircraft evacuations: The effect of a cabin water spray OLLEVIER. THOMAS E. An experimental study of wing tip vortex in the near system upon evacuation rates and behaviour The use of low cost differential mode GPS receivers wake of a rectangular wing (CAA-PAPER-93008] p 393 N94-29887 in unmanned vehicles p 389 N94-30285 [ AD-A275389] p 377 N94-29306 RAUSCH, RUSS DAVID MULARZ. EDWARD J. ONEIL.PAT Time-marching aeroelastic and spatial adaptation Spuy cofflbustjon flxpoofnonts And nunwnctv Low-speed longitudinal aerodynamic characteristics of procedures on triangular and tetrahedral meshes using predictions p407 N94-29277 a flat-plate planform model of an advanced fighter an unstructured-grid Euter method p 379 N94-29877 MURAO, RINICHI UN (figuration (NASA-TM-109045] p 377 N94-29443 RAWUNGS.R. Unsteady aerodynamic computations around Experimental flight management system NACA0012 at high angles of attack p377 N94-28969 ONODERA, TAKUO P388 N94-29580 MUtUSE, TAKEO Numerical study on the interaction between scramiel REIOINGER, MARK F. Performance evaluation of the NWT with parallel engine modules caused by thermal choke Exploring ODES as a tool tor determining limits of Fortran p415 N94-28992 p395 N94-28960 Bcniovsbte pflnorni&noo in circrsft (tesiQn MURTHY. D. V. OSGOOD, ROBERT K. [ AD-A275359) p 391 N94-28998 Turbomachinery forced response prediction system A comparison of ttiieu aircraft Altitude display symbology RICCARDI. G. (FREPS): User's manual structures Technology rigs: A tool tor afterburner development [NASA-CR-194465] p411 N94-29104 [AD-A275172] p 394 N94-29048 p 397 N94-29270

B-5 RICE, R. PERSONAL AUTHOR INDEX

RICE, R. SCHMIDT. HORST SOWA, W. A. Effects of repair on structural integrity GPS/GNSS for ATM p385 N94-29565 Pollutant emissions from and within a model gas turbine (AD-A275756J p 390 N94-28647 SCHMITZ. FREDRIC H. combustor at elevated pressures and temperatures RICHARD-FOY. MARC Boundary layer control device for duct silencers p406 N94-29271 Ada run time system certification for avionics (NASA-CASE-ARC-12030-1] P 417 N94-29362 SPEARMAN. M. LEROY An experimental and theoretical study of the applications p 394 N94-29332 SCHNEIDER. M. RfZZI, STEPHEN A. A novel near-range radar network tor airport surface aerodynamic characteristics of some generic missile Dynamic fracture mechanics analysis tor an edge control P389 N94-29586 concepts at Mach numbers from 2 to 6.8 (NASA-TM-109110) p 378 N94-29473 delamination crack SCHOFIELD, R. J. SPEKREUSE, S. P. (NASA-TM-109106) p417 N94-29656 Advanced fuel properties: A computer program for ENGRIO: A graphical interactive code for the ROEOE.B. estimating property values computation of structured grids for blocked flow domains A novel near-range radar network tor airport surface [AD-A275248] p 403 N94-28901 control p389 N94-29586 p409 N94-28956 SCHROTHA. ROESCH. WINIFRED The design of a system of codes for industrial A novel near-range radar network tor airport surface GPS/GNSS for ATM p 385 N94-29565 calculations of flows around aircraft and other complex control P389 N94-29586 ROJOS-OVIEOO, RUBEN aerodynamic configurations Modification of ACSYNT aircraft computer program for SCHUBERT. M. [PB94-125598] p 381 N94-30387 preliminary design Contributions of DLR to air traffic capacity enhancement SQUIRE, K. R. [NASA-CFM 95737] p 390 N94-28817 within a terminal area p 385 N94-29567 Advanced fuel properties: A computer program for ROOUEMORE. W. U. DLR's ATM demonstration umgiariinie estimating property values Research and development of high thermal stability p386 N94-29S75 [AD-A275248) p403 N94-28901 fuels p405 N94-29261 SCHULTZ, J. L SRINIVASAN, GANAPATHI R. Development of global/chemistry model for jet-fuel Aerothermochemical calculations in afterburners A free-wake Euler and Navier-Stokes CFD method and thermal stability based on observations from static and p396 N94-29258 its application to helicopter rotors including dynamic stall flowing experiments p405 N94-29262 SCHULTZ. ROBERT L. (AD-A275416) p 377 N94-29197 ROSENFELD, M. Advanced air traffic control and flight management STANNARD, BARRY ANTHONY Effects of repair on structural integrity system concepts p 387. N94-29576 A capacity planning model tor Canadian military airtift [AD-A275756J p 390 N94-28647 SCHUMANN, U. requests ROSFJORD. T. J. On the effect of emissions from aircraft engines on the (ISBN-0-315-86079-0) p 382 N94-30144 Evaluation of the transient operation of advanced gas state of the atmosphere p 414 N94-29247 STEINBERGER. R. L. turbine combustors p397 N94-29269 SEOALMAN, L The effect of incomplete fuel-air mixing on the lean limit ROUOAKOV, A. Reduction of NO(x) by fuel-staging in gas turbine and emissions characteristics of a Lean Prevaporized Some problems of scramjet propulsion tor aerospace engines: A commitment to the future Promoted (LPP) combustor p405 N94-29265 planes. Pan 1: Scramiet Aims and features p406 N94-29272 STENGEL. ROBERT p398 N94-29295 SEIDEU DAVID A. Air traffic management as principled negotiation Some probteim of scramjet propulsion tor aerospace Steady pressure measurements on an Aeroelastic between intelligent agents p 384 N94-29562 planes. Pan z. Scramjet Development and fast Research Wing (ARW-2) STEPANOV, V. problems p 399 N94-29301 [NASA-TM-109046] p 374 N94-28658 Scramjet CFD methods and analysis. Pan 1: Scramjet RULEV, L SEYBERT. A.F. \jr\j iiNjUiods. Numerical simutatiori of the flow in scramjet Scramiet CFD methods and analysis. Part 1: Scramjet Experimental validation of finite element and boundary duct p398 N94-29296 CFD methods. Numerical simulation of the flow in scramjet element methods for predicting structural vibration and STICKLES. R. W. duct P398 N94-29296 radiated noise Fuel injector design for high temperature aircraft RUST. S. [NASA-CR-4561] p 412 N94-29S52 engine p396 N94-29263 Effects of repair on structural integrity SHAPIRO, A. B. STOLL, LAURENCE [AOA275756] p 390 N94-28647 Dual-Band Infrared (DBIR) imaging inspections of Boeing AMuaft age impact on individual operating and ^ypf* 737 and KC-135 aircraft panels cost elements [DE94-005700] p374 N94-29842 (AD-A275739) p 373 N94-28732 SHEPPARD, JOHN C. STURGESS, G. J. The radwcarbon hydroxyl techniQue SAGER. J. Reduction of N0(x) by fuel-staging in gas turbine P414 N94-28600 Fuel injector design tor high temperature aircraft engines: A commitment to the future SHIMA.EUI engine p396 N94-29263 p406 N94-29272 Role ol computational fluid dynamics in aeronautical SALVA.J. SUEMATSU. KAZUYO engineering. Pan 10: Numerical analysis of flow around Ettects ol hydrogen addition on pollutant emaiiona in A rnottiod of UBOT intoffcoo for NWT 2-D multi-element HLD p410 N94-28964 a gas turbine combustor p 406 N94-29275 p415 N94-28993 STVASEGARAM. S. SAMAVEDAM.G. Ducted kerosene spray flames p407 N94-29276 SUEMATSU. SHUNJI Full-scale testing and analysis of curved aircraft fuselage A method of user interlace tor NWT panels SMITH J- A modernised HST of NLR p415 N94-28993 IAD-A275666] p 390 N94-28657 [AD-B179220] p402 N94-30423 SUES.R.H SAMPATH P. SMITH, KEVIN W. Asphaltic concrete performance under heavy fighter Design aspects in small aircraft gas turbine fuel Cockpit video: A low cost BDA source avcraft loading injectors p 397 N94-29264 (AD-A27522B) p 395 N94-29389 [AD-A275046] p402 N94-29151 SAMPSON. WILLIAM T. Ill SMITHS. SUN, TAI-HSING TOM Rooftop emergency heliports Effects of iBpai on structural ntegrtty Unsteady transonic aorodyiiainicii in frequency domain (DOT/FAA/RD-93/2J P402 N94-29754 [AOA275756] p390 N94-2B647 for flutter analysis p379 N94-29879 SAMUELSEH G. S. SHITS, ALEXANDER J. SWIERSTRA. SIP Pollutant emissions from and within a model gas turbine WaD pressure fluctuations in the reattachment region Decision Making Aids (DMA) in on-line ATC systems combustor at elevated pressures and temperatures of a supersonic tree shear layer p386 N94-29570 p406 N94-2927t [NASA-CR-195790] p379 N94-29920 SYTSMA.H.A. SANOFORD. MAVNARD C. SODERUAN, PAULT. Numerical investigation into Ngh-angje-of-attack Steady pressure measurements on an Aeroelastic Boundvy teyor control oovico for ouct sttenofirs leadiiiu-edge vortex flow Research Wing (ARW-2) [NASA-CASE-ARC-12030-1] p417 N94-29362 [PB94-125564] p381 N94-30388 (NASA-TM-109046) p 374 N94-2865B SOLONIN.V.L SANTA VICCA. D. A. CUM experimental turboramjels p399 N94-29299 The effect of incomplete tuel-air mixing on the lean Brntt SORENSEN, JOHN and emissions characteristics of a Lean Prevaporized Oppomjnties for tfttegrating the aiciafl FMS. Premoced (LPP) combustor p 405 N94-29265 aeronautical operational control centers, and future air TAGUIROV, R. SAREEM, ASHISH KUMAR traffic management systems in oceanic avspace Scramjet CFD methods and analysis. Pan 1: Scramjet Rotorcraft airtrame structural optimization for vibration P387 N94-29577 CFD methods. Numerical simulation of the flow in scramjet and dynamic stress reduction including damping SOROKACH MICHAEL R, JR duct p398 N94-29296 MinjflturotaiBW-to-rotBr ymotio n tctmtof treatment p392 N94-29878 TAHMASEBI. FARHAD P413 N94-29647 SATOU. MAMORU Sa-degree-ol-freedom parallel minimanipulator with SOSOUNOV. V. three inextensMe bmbs Numerical analysis of ajrfoa for helicopter blade at high fnlitj^hivtivft and ovorviow of research and |^n**?*pi_l

B-6 PERSONAL AUTHOR INDEX ZHENG, YOUXIN

TAKALLU. M. A. VANOENBOS. NANS WU, T. W. Aerodynamic characteristics of a propeller-powered Simulation of fully automated air traffic control Experimental validation of finite element and boundary high-fin serraspan wing concepts p 386 N94-29569 element methods for predicting structural vibration and [NASA-TM-4541] p 380 N94-29937 VANDERDRAAI, R. K. radiated noise INASA-CR-4561] P412 N94-29S52 TAKANASHI. SUSUUU A modernised HST of NLR Numerical solution of inverse problem in (AD-B179220] p402 N94-30423 WU. X.F. aerodynamics p376 N94-28965 VANDERVOOREN, J. Experimental validation of finite element and boundary element methods tor predicting structural vibration and TAKEUCHI, H1SAO Calculus of variations applied to 2D multi-point airfoil radiated noise Application ol now field simulation to turbine vane design f NASA-OM561) P412 N94-29552 design P 395 N94-28978 [PB94-125457J p 381 N94-30401 VELTEN, J. R TAMURA, ATSUHIRO The Common Modular Simulator (CMS): An architecture Verification of a three-dimensional viscous flow analysis test bed for future advanced ATM systems for a single stage compressor p 410 N94-28976 p388 N94-29582 XIAO, ZHENHUA TAMURA, VOSHIAKI VERGNOU F. Three dimensional simulation of compressible flow Flight command software development: RAFALE Boundary layers induced by three-dimensional vortex induced by a high-speed train moving into a tunnel studies p415 N94-29320 loops p376 N94-28967 VINER, M. R [AD-A27567B] p 408 N94-28665 TANAKA, ATSUSHIGE Acoustic emission monitoring of aging aircraft Application of flow field simulation to turbine vane structures design p 395 N94-2B978 [DREP-93-17] p393 N94-30129 TAHI, KOUtCHIRO VINOGRADOV, V. YAMADA. EITARO Numerical simulation of steady Mach reflection by shock Scramjet CFD methods and analysis. Part 1: Scramjet Application of digital control theory to adaptive grid capturing schemes p 375 N94-28953 CFD methods. Numerical simulation of the flow in scramjet generation p415 N94-28980 TASK.H.L. duct p398 N94-29296 YAMAGUCH1. YASUSHI Backscaner haze device for measurement of haze in VTTAGUANO. P. L. A method of user interlace tor NWT aircraft transparencies The design ol a system of codes tor industrial p415 N94-28993 (AD-A275127J p 391 N94-29042 calculations of flows around aircraft and other complex YAMAMOTO, KAZUOMI TASSELU, A. aerodynamic configurations An elliptic-hyperbolic grid generation method and Technology rigs: A tool for anerbumer development [PB94-125598] p381 N94-30387 application to compressor flows p 395 N94-28981 p397 N94-29270 VOELCKERS, U. YAMAMOTO, SATORU THOMAS, J. Contributions of OLR to air traffic capacity enhancement Higher-order accurate numerical simulation of 3D Los Angeles international airport instrument landing within a terminal area p 385 N94-29567 supersonic mixing layers p 375 N94-28954 system approach data collection and reduction, phase 1 VOELCKERS, UWE YAMAMOTO. YUKIMITU [AO-A275115] p3S3 1494-28914 The PHARE advanced tools p388 N94-29581 Numerical simulation of aerothei nioUynamic heating of THOMSON, O. hypersonic apace transportation vehicles Full-scale testing and analysis of curved aircraft fuselage p375 N94-2B955 panels w YAMANE, TAKASHI [AD-A275666] p 390 N94-28657 Numencal study on vitemal flows of centrifugal WAOA. YASUHIRO 77LSTON, J. H. compressors p 395 N04-28S77 Nufnoncftl stmulAtion of vc hsflted wind tunnot flow The influence of air distribution on homogeneity and YAMAWAKI, RURIKO p402 N94-2B9S1 pollutant formation in the primary zone of a tubular Application of flow field simulation to turbine vane combustor p406 N94-29274 WANQERMANN.JOHN design p 395 N94-2B97B Air traffic management as principled negotiation TIMIAN, D. A. YAMAZAKI, TETSUO between intelligent agents p384 N94-29S62 Asphaltic concrete performance under heavy fighter Numerical analysis of supersonic transport wings aircraft loading WARD, N. J. p375 N94-28959 [AD-A275046] p 402 N94-29151 Integrated formal verification and validation of safety YOKOTA, KAZUHIKO critical software p416 N94-2S338 T1MOTEO, O. Study on mixing and injection of hydrogen into a Los Angeles international airport instrument landing WARNER, RONALD R, JR. supersonic flow p377 N94-2897S system approach data collection and reduction, phase 1 Demonstration of improved software support labor YOSHIDA, AKIHIKO [AD-A275115] p383 N94-28914 estimation for Air Force operational flight programs through Numerical analysis of sonic boom in the near held functional orientation p376 N94-28962 TROUDET, T. [AD-A275789) p373 N94-28743 YOSHIDA, MASAHIRO A novel approach to noise-filtering based on a Performance evaluation of the NWT with parallel gain-scheduling neural network architecture WATANABE, VASUO p415 N94-28992 INASA-TM-106563] p 401 N94-30204 Numerical simulation of arc heated wind tunnel flow P402 N94-2B951 TROVATI, A. Tocfinotofly ri0s.' A toot tof •fteftounwr dovslopfnont WEDLOCK, ILL p397 N94-29270 The influence of air distribution on homogeneity and pollutant formation in the primary zone ot a tubular TSAL LUNG-WEN ZACHAROV.N. combustor p406 N94-2S274 Si»-degree-of-freedom parallel mrnimantpulator with Scramjet CFD methods and analysis. Part 1: Scramjet three ^extensible tmtas WEILER, 0. R. CFD methods. Numencal simulation of the flow in scramjet [NASA-CASE-GSC-13485-1] p413 N94-29726 Paytoad central control for unmanned aircraft duct p398 N94-29298 p401 N94-30284 TSKHOVREBOV, M. M. ZATTSEV.S. Turboramjet engines: Types and performances WHEELER, HOWARD A. Soramjet CFD methods and analysis. Part 2: Scramjet p398 N94-29293 Extremely Low Visibility IFR Rotorcratt Approach CFD analysis. Numerical simulation of supersonic mixing (ELVIRA) operational concept development Volume 1: CIAM experimental turbommjets p399 N94-29299 and combustion applied to scramjet combustor Executive Summary p399 N94-29300 TSUCHIYA. MASAKO (DOT/FAA/RD-94/1,1) p 389 N94-301B9 ZHENG. YOUXIN A method of user interlace tor NWT WHITELAW, J. H. An experimental study of wing tip vortex in the near p415 N94-28993 Ducted kerosene spray Ramos p407 N94-29276 wake of a rectangular wing TUMEUN. JEAN-CLAUDE [AD-A275389] p 377 N94-29306 ARC2000: Automatic radar control WILLIAMS, DAVID H. p388 N94-29583 Profile negotiation: An air/ground automation integration concept for managing arrival traffic p 387 N94-29578 WIPPICH, HEINZ-OEORG U GPS/GNSS for ATM p385 N94-29565 WISE, NICHOLAS UCHIDA, TAKASHI Radar jel engine health monitoring project Numenca) analysis ot supersonic tiAns^jort wings [ASSGI-301] p400 N94-30130 p375 N94-28959 wrmas. UNGER, SHELDON E. Time-resolved measurements in a three dimensional Bacfcscatler haze device for measurement of haze in model combustor p41l N94-292B3 aircraft transparencies WONG, GENE A. (AD-A275127J p 391 N94-29042 Development of precision runway monitor system for increasing capacity ot parallel runway operations p389 N94-295B7 WOODWARD, JOSEPH H. VALETT, JON Safety enhancement of composites via periodic proof Software Management Environment (SME) concepts and architecture, revision 1 (AD-A275662) P403 N94-28655 (NASA-CR. 189293] p418 N94-29727 WRIGHT, DARREL L. VANOENBERG, J. L Demonstration of improved software support labor Numerical investigation into high-angle-of-attack estimation for Air Force operational flight programs through leading-edge vortex flow functional orientation (PB94-125564] p381 N94-303BB (AD-A275789) p 373 N94-28743

B-7 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 305) June 1994

AutORVBtion of the NOT ctagnostic usinQ nowJ n0ts. CaHfof iHa Urav, Irvine. Application: Inspection of Airbus longitudinal pints during Pollutant emulsions from and witrMn a modal gas turbine combustor at elevated pressures and temperatures Typical Corporate Source r.REPT.932-600-104] p 412 N94-29474 p406 M94-29271 Aerospatiale, Toutouee (Franc*). Central mat of Aviation Motors, Moscow (Russia). Index Listing How to couijuf the inrrTasri in ONI cun^ilexily of ovii Endotherrnc fuels tor hypersonic aviation aircraft c«-board systems p394 N94-29316 p407 N94-29285 Air Fore* CM) Engineering Center, Tyndafl AFB, FL. liiliuuuLUuii and overview of research and development Asphaltic concrete performance under heavy fighter of solid propellant ramrockets. liquid fuel ramjets and [CORPORATE SOURCE| experimental hydrogen ram eombustors (AOA275046) p402 N94-29151 p398 N94-29J92 Air Force but of Tech, Wi lulu-Pallet sun AFB, OH. Turboramjet engines: Types and pertormanoes Demonstration of improved software support labor P398 NB4-29293 Adaptive Research Corp, Huntsvtll*. AL, estimation for Air Force operational flight programs through Hosttvcn end oovAlopfipsnt of rvrijots/rvTvocitots. PaVt |— Structured finite volume modeling of US Navy aircraft functional orientation 1: integral solid propellant ramrockets engine MM calls. Tuk 1: Turboshatt engine. volutM 1 (AO-A2757B9) p 373 N94-28743 P398 N94-29294 [AD-A268176] p 135 NM-17432 Evaluation of access/navigational features of a graphical-user interlace installed on a portable Some problems of scramiet propulsion tor aerospace maintenance aid planes. Part 1: Scramjet Aims and features [AO-A275791] p383 N94-28744 P398 N94-2S295 Design and cumuucuun of the Aerobot Robotic Scramiet CFD methods and analysis. Part 1: Scramjel Manipulator (ARM) CFD methods. Numerical simulation of the flow in scramjet [AD-A275362J p409 N94-288M duct p398 N94-29296 Exploring ODES as a tool tor determining limits of Research and development of ramjets/ramrockets. Part achievable pertormance In aircraft design a Integral liquid fuel ramjets p398 N94-292S7 Ustings in this index are arranged alphabetically (AD-A275359] p 391 N94-289M Research and development of ramjets/mmrockets. Part by corporate source. The title o) the document Is Command. WilgM-PaHtaieen AFB, 3: The study of gaseous hydrogen ram eombustors used to provide a brief description of the subject OH. p398 N94-29298 matter. The page number and the accession Ac to software lest and evaluation QAM experimental turboramjets p399 N94-29299 number are included in each entry to assist P416 N94-29339 Scramjet CFD methods and analysis. Part 2: Scrarr^et Air IMv, MaxweB AFB. Al_ CFD analysis. Numerical emulation of supersonic mmng the user in locating the abstract In the abstract Cockpit video: A low cost BDA source and combustion applied to acramjet combustor section. If applicable, a report number Is also (AD-A27S228) p395 N94-293B9 p399 N94-Z0300 included as an aid In Identifying the document. Alcatel BR. Evry (France). Some problems of scramjet propulsion tor aerospace DAISY: A decision aid tor an air situation Inlerpielalion planes. Par) 2: Scramjet: Development and tot system p386 N94-29574 problems p399 N94-29301 Atom*. Torino (Italy) . Centre cTEtudea de la Navigation Aartenr On ground system integration and testing: A modem approach p394 N94-29334 Use of advanced technologies in ATM (air traffic Atonta Spazto S»A, Rom* (Italy). management) domain p 384 N94-29561 ENGRID: A graphical iitaractive code for the Cognitive approach to specifications on air traffic computation of structured grids for blocked flow domains contiDttw dtonon ssustmos syvtoms P409 N94-28956 p386 N94-29571 AovBnoo Avutton Conovpts* *Jupitcrv FL AM Romeo EpA. Naples (Italy). The Common Modular Simulator (CMS): An architecture Extremely Low Visibility IFR Rotorcraft Approach Numerical simulation el aarothermal ctiaracteristies In teat bad tor future advanced ATM systems (ELVIRA) operational concept de»eloprnant Volume 1: gas turbine eombustors wHh eomple» geometries p388 N94-29562 Executive Summary P396 N94-292S5 Santo AppBcsilonl MOtarl detTEnerguj Nucknr*. Plea [DOT/FAA/RD-94/1.1] p389 N94-30189 AMed^lgnel AOTospao* Co, Des Flames, U- (nary). Advleory Group for At Advanced fuel properties: A computer program tor v/oftiput»rttonatl twd vxpc air utts in high pressure NeuWy-l • (France). estimating property values combustions of H2/ar and H2/O2/H2O fi^rtCQmbMtol9ChnQ^torM*VK*6Hmn (ADAZ7S248] P403 N94-28901 P406 N94-29266 Enojnos Atoya, toe, BaM Ctoud (Franco). Ctndnnat) Unhr, OH. [AGARD-CP-536] P404 N94-29246 Ada run erne system ueriilKaliuii tor avionics RNS optmizatxjn procedure for three-dimensional Research and Development of Ram/Scrainjets and appicalions p394 N94-29332 composae velocity mutlKbloek appucabons Turtaoramjets in Russia Aluminum Co. of America, Alcoa Center, PA. p412 N94-29534 IAGARD-LS-194] P397 N94-28291 Role of mcroitructure on the fatigue durability of CM Aviation Authority, London (England). Aerospace Software Engineer* ig tor Advanced Systems aluminum aircraft alloys Aircraft evacuations: The effect of a cabin water spray Architectures (AD-A275B14] p. 403 N94-2S830 system upon evacuation rates and behaviour IAGARD-CP-S45) p41S N94-2931S Arizona State Unto, Temp*. [CAA-PAPER-93006] p 393 N94-29887 Machine Intelligence in Air Traffic Management Craahwonhinass anelyais of commuter aircraft Mats Combuatton Dynamic* Ltd, Medicine Hat (Alberta). (AGAHD-CP-538] p383 N94-2BS5B (AD-A275aB9) P382 N94-2B799 Paytoad central control tor unmanned amafl Atlemts Sdentmc Syetame Croup, toe, Ottawa Aeronautical Reeearch Labs, Metooume (Australia). P401 N94-30284 (Ontario). Fjshermans Bend: A centre of Australian aviation CompEngSarv Ltd, Ottawa (Ontario). Radar )el engine hearth mentoring protect Inteuigent systems tor air apace control and (AD-A274981) P373 NM-29090 Cold exnerriiuii and interference tor extending the (ASSGI-301J p400 N94-30130 management p384 NB4-29S60 fatigue lite of multi-layer metal joints CranfWd met of Tech, Bedford (England). FtowfieM prediction of NCXx) and smoke production in [AEM274982] P410 N94-29091 B Aeronautical Systems Dr., Wright-Patterson AFB, OH. aircraft engines p404 N94-29252 KC-135 cockpit modernization study and crew reduction Bane** Columbus Lab*, OH. feasibility demonstration Effects of repair on structural integrity (AD4275230] p392 N9449391 (AD-A27S756) p390 N94-28647 Aeroapatiato. Cannaa (France). ItrtlUti nsrnipsri rtstanra I 111. rrastrm fTnrjIaiwI) Dasaault-Braguet Avkttton, Saint Ctoud (France). Theoretical and experimental study of a cylindrical SOT* tor the year 2000 and beyond: An EF Flight command software development: RAFALE microstnp antenna P416 •tuxes P415 N94-29320 (REPT-932-440-109) p412 N94.294SC Defence Research Agency. Famborough (England). Aerospatiale, Parts (France). The influence of air distribution on homogeneity and A time roasoring system baaed on the event calculus pollutant formation in the primary zone of a tubular tor scheduling in aeronautic maintenance combustor p406 N94-29274 IREPT-S32-710-101) p374 NM-2B463 CaMombj Polylaelmk. State UoK, San LuteOMspo. AerospeUat*. Suraene* (France). Modmeation of ACSYMT aircrafl computer program tor Hat (AJbarta). Fire behavior of oemnamtil materials The use of tow cost mode GPS reeeimis fREPT-932-600-105] p4OB N94-294S7 [NASA-CR-16S737] p390 N94-28817 inunmanr P389 N94-3028S

C-1 Defence Research Establishment Suffield CORPORA TE SOURCE

Defence Research Establishment Suffield, Ralaton Kawasaki Heavy Industries Ltd, Tokyo (Japan). (Albert*). Verification of a three-dimensional viscous flow analysis HATT.X: A high performance flying laboratory lor General Electric Co, Cincinnati, OH, tor a single stage compressor p 410 N94-28976 autonomous unmanned aircraft research and Design and fabrication of forward-swept counterrotation Kentucky Urdv, Lexington. development p 393 N94-30293 blade configuration tor wind tunnel testing Experimental validation of finite element and boundary element methods for predicting structural vibration and Deutsche Aerospace A.G, Ulm (Germany). (NASA-CR-194868) p 401 N94-28S10 GPS/GNSS tor ATM p385 N94-29565 Fuel injector design for high temperature aircraft radiated noise [NASA-CR-4561] p412 N94-29552 Deutsche Forechungs- und Versuchsanstatt fuer Luft- engine p396 N94-29263 Kyoto Unhr, Sakyoku (Japan). und Raumfahrt, Cologne (Germany). General Motors Corp, Indianapolis, IN. Application of digital control theory to adaptive grid Application ol CFD in combustor design technology Investigation ol the two-phase How in a research generation p415 N94-28980 combustor under reacting and non-reacting conditions p396 N94-29256 Kyushu Unhr, Fukuoka (Japan). p411 N94-29282 Investigation of advanced counterrotation blade Numerical simulation of unsteady aerodynamic healing Deutsche Fonchungsanstatt fuer Luft- und Raumtahrt, configuration concepts for high speed turboprop systems. induced by shock reflections p 375 N94-28952 Brunswick (Germany). Task 2: Unsteady ducted preplan analysis computer Contributions of DLR to air traffic capacity enhancement program users manual within a terminal area P 385 N94-29567 [NASA-CR-1B7105] p399 N94-29438 Considerations on graphical user interlaces for intelligent Georgia InsL of Tech, Atlanta. ATM support systems p386 N94-29572 Helicopter mission and rotor performance optimization Lawrence Uvermore National Lab, CA. Interactive analysis and planning tools tor air traffic and with quasHinear inflow theory p 392 N94-29594 Dual-Band Infrared (DBIR) imaging inspections of Boeing airspace management p 386 N94-29573 Rotorcraft airframe structural optimization tor vibration 737 and KC-135 aircraft panels DLH's ATM demonstration programme and dynamic stress reduction including damping [DE94-005700] p374 N94-29842 p366 N94-29575 treatment p392 N94-29878 Leeds Unhr. (England). Ultra low NCHx) ultra lean gas turbine primary zones Experimental flight management system with liquid fuels p 397 N94-29267 p3S8 N94-295BO Lockheed Aircraft Service, me, Ontario, CA. Deutsche Forachungsanstatt fuer Luft- und Raumfahrt, H Aircraft system an telescope cavity configuration study Oberpfaffenhofen (Germany). High Technology Corp, Hampton, VA. for Stratospheric Observatory for Infrared Astronomy On the effect ol emissions from aircraft engines on the (SOFIA), phase 2 state ol the atmosphere P414 N94-29247 Long-wavelength asymptotics of unstable crossflow modes, including the effect of surface curvature (N ASA-CR. 194 266) p 392 N94-29685 Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Logjcon, me, Dayton, OH. Wessllng (Germany). [NASA-Cfl-4579] p412 N94-29460 Honeywell, me, Minneapolis, MN. Backscatter haze device for measurement of haze in A novel near-range radar network lor airport surface aircraft transparencies control p389 N94-29586 Advanced air traffic control and flight management system concepts p 387 N94-29576 (AD-A275127] p 391 N94-29042 Duke Urav, Durham, NC. A comparison of three aircratt attitude display symbotogy Aeroacousbc sensitivity analysis and optimal structures aeroacoustic design ol turbomachinery blades I (AD-A275172) p 394 N94-29048 [NASA-CR-195786] P 399 N94-30013 Knots Unhr, Urbana-Champalgn. An experimental study of the nowfteM on a serrispan M rectangular wing with a simulated glaze ice accretion p378 N94-29674 Manitoba Onr», Winnipeg. Electronic System OrrLbJt, Munich (Germany). The 3-D LOV measurements on a 30-degree swept wing A capacity planning model for Canadian military aJrtffi Experiences with the HOOD design method on avionics with a simulated ice accretion requests software development p 415 N94-29325 (NASA-CR-195327] p 380 N94-30124 [ISBN-0-315-86079-0) p 382 N94-30144 Etoret Corp, Palo Alto. CA. An experimental study of the aerodynamics of a swept Marconi Radar Systems Ltd, Chetmstord (England). A study ol low emissions gas turbine combustions and unswept semispan wing with a simulated glaze ice Airside ground movements surveillance [NASA-CR-195763] p 399 N94-29860 accretion p388 N94-29585 Particle kinetic simulation of high altitude hyperveiocity INASA-CR-195330] p 381 N94-301S2 Maryland Untv, CoDege Park. flight Imperial CoO. of Science and Technology, London An analytical study of unsteady rotor/fuselage INASA-CR-194535] p 379 N94-29893 (England). interaction in hover and forward flight p379 N94-29826 Eurocontrol Experimental Centre, Bretigny (France). Ducted kerosene spray flames p407 N94-29276 MCATmst, Stn Jose, CA. ARC2000: Automatic radar control Inallluto Mactona ld e Tccnlca Aefoaspaftal, Madrid Atgorithm and code development for unsteady p3B8 N94-29583 (Spam). High tofnpGTBtm resistant Jet fuels three-dimensional Navier-Stokes equations European Organization lor the Safety of Air [NASA-CR-195774] p 414 N94-29942 Navigation, Brussels (Belgium). p405 N94-29260 liisliuii Corp, Canton, MA. Michigan Unhr, Aim Arbor. Decision Making Aids (DMA) in on-line ATC systems Closed loop vibrational control: Theory and p3B6 N94-29570 Development of Alternating Current Potential Drop (ACPD) procedures for crack detection in aluminum aircraft Air-ground integration of the ATM system in PHARE [AD-A275451] p 400 N94-28632 p3B8 N94-29579 [AD-A275755] p 408 N94-28646 Missouri Unhr, Rotta. IslHkawamia-Hartma Haavy Industries Co. Ltd, Tokyo Uqud atomization in supersonic flows (Japan). p 414 N94-29839 Numerical simulation of supersonic flow around space Mttre Corp, McLean, VA. plane with engine installed p376 N94-28961 Advances in development capabilities for intelligent air Federal Aviation AdmliilsUaUon. Atlantic City, MJ. Unstsfloy •orooynsnuc coiT*piitstiorts sround traffic management systems p 384 N94-29559 Los Angeles international airport instrument landing NACA0012 at high angles of attack p377 N94-28969 Mitsubishi Electric Corp, Kamakura (Japan). system approach data collection and reduction, phase 1 Application of flow field simulation to turbine vane Numerical analysis of two diineiisiuiial/anisyiiiiiieliic [AD-A275115] p 383 N94-28914 design p395 N94-28978 non-equilibrium hypersonic flow p 376 N94-28963 Mitsubishi Heavy Industries Ltd, Tokyo (Japan). Federal Aviation Administration. Washington, DC. Numerical analysis of airfoil tor helicopter Made at high The 1993 Federal Aviation Administration Aviation angle ol attack using Navier-Stokes code System Capital Investment Plan p 383 N94-29445 P375 N94-289S8 Opportunities for integrating the aircraft FMS. JAI Associates, me. Mountain View, CA. Code development tor hypersonic real-gas now aeronautical operational control centers, and future air A free-wake Euter and Navier-Stokes CFD method and simulations toward the design of space vehicles, pan 2 traffic management systems in oceanic airspace its applicatjon to helicopter rotors including dynamic stall p376 N94-28966 p387 N94-29S77 [AD-A275416J p 377 N94-29197 Development of precision runway monitor system for increasing capacity of parallel runway operations N p389 N94-29S67 National Aeronautics and Space Administration. Ames Flat Avtaxione S*.A, Turin (Italy). Kansas Unhr, Lawrence. Research Center, Moffett FMd. CA. Technology rigs: A tool for afterburner development An experimental vivestigstjon of the effect of leading Boundary layer control device tor duct silencers p397 N94-29270 edge extensions on directional stability and the (NASA-CASE-ARC-12030-1] p 417 N94-29362 Foster-Miner Associate, me, Wattham. MA. effectiveness of torebody nose strakes Design of Centsr-TRACON Automation System Full-scale testing and analysis of curved aircraft fuselage p400 N94-29728 P385 N94-29S68 panels Unsteady transonic aerodynamics in frequency domain Computation of wind tunnel wan effects for complex [AD-A275666] p 390 N94-28657 for flutter analysis p379 N94-29879 models using a tow order panel method Aircraft aerodynamics with deflected jets in ground Full Heavy Industries Ltd, Tokyo (Japan). [NASA-TM-104019] p 380 N94-30151 effect P380 N94-29973 A design of third-generation airfoils for neBcopter rotor national Aeronautics and Space AdmlnlsliaUon. Kartsruhe Unhr. (Germany). blades using Navier-Stokes p 391 N94-289S7 Ooddard Space FUght Center. Greenbett, MO. Time-resolved measurements in a three diriieiiaiuiiBl Six-degree-ot-treedom parallel mcrarnarapuJaUx with Numerical analysis of supersonic transport wings model combustor p411 N94-29283 uw*6 mextensftle kmbs p37S N94-28959 Kawasaki Heavy Industries Ltd, Grfu (Japan). [NASA-CASE-GSC-13485-1) p413 N94-29726 Fujitsu Ltd, Tokyo (Japan). Role ol computational fluid dynamics in aeronautical Software Management Environment (SME) concepts Performance evaluation ol the NWT with parallel engineering. Pan 10; Numerical analysis of flow around and architecture, revision 1 Fortran p41S N94-28992 2-O mutt-element HLJD p410 N94-28964 (NASA-CR-189293) p416 N94-29727

C-2 Sverdrup Technology, Inc. CORPORATE SOURCE

National Aeronautic* and Spaea Administration. Similarity between turbulent flows through curved pipe P Lyndon B. Johnaon Space Center, Houston, TX. and orthogonal rotating pipe P 410 N94-28986 Landing gear energy absorption system National Aerospace Lab, Tokyo (Japan). Pennsylvania State Unrv, University Park. [NASA-CASE-MSC-22277-1] p411 N94-29448 Proceedings of the 10th NAL Symposium on Aircraft The effect of incomplete fuel-air mixing on the lean limit National AeronautJca and Space Administration. Computational Aerodynamics and emissions characteristics of a Lean Prevaporaed LangJey Research Center. Hampton, VA. [NAL-SP-19J P375 N94-28946 Premixed (LPP) combustor p 405 N94-2926S Steady pressure measurements on an Aeroelastic Monte Carlo simulation or normal shock wave. Part 2: Polytechnic Unrv, Brooklyn, NY. Research Wing (ARW-2) VMS model and VSS model p409 N94-28948 Experimental investigation of three-dimensional [NASA-TM-109046] p 374 N94-28658 Variable soft sphere molecular model in the Monte Carlo vortex-airfoil interaction in a supersonic stream Prediction of stress-strain response of simulation of air species p 409 N94-28949 [AD-A275107] p 374 N94-28899 SCS-6/Ttmetal-21 S subjected to a hypersonic flight Rarefied gas numerical wind tunnel. Part 8: HOPE Pratt and Whitney Aircraft, East Hartford. CT. profile p 401 N94-28950 Thermal/structural tailoring of engine blades [NASA-TM-109026] P 403 N94-28823 Numerical simulation of arc heated wind tunnel flow (T/SEAEBL). Theoretical manual Low-speed longitudinal aerodynamic characteristics of p402 N94-28951 [NASA-Cfl-194462] P 409 N94-2B815 a flat-plate plantorm model of an advanced fighter Numerical simulation of aerothermodynamic heating of Reduction of NO(x) by fuel-staging in gas turbine configuration engines: A commitment to the future (NASA-TM-109045] P 377 N94-29443 hypersonic space transportation vehicles p375 N94-28955 p406 N94-29272 Subjective response to sonic booms having different Pratt and Whitney Aircraft, West Patm Beach, Fl_ shapes, rise times, and durations Numerical solution of inverse problem in aerodynamics P 376 N94-28965 High temperature fuel requirements and payoffs (NASA-TM-109090] p417 N94-29464 p405 N94-29259 An experimental and theoretical study of the Numerical study on internal flows of centrifugal Pratt and Whitney Aircraft of Canada Ltd, Mlsatasauga aerodynamic characteristics of some generic missile compressors p395 N94-28977 (Ontario). concepts at Mach numbers from 2 to 6.6 An elliptic-hypertaolic grid generation method and Recent CFD applications in small gas turbine combustion (NASA-TM-1091101 p378 N94-29473 application to compressor flows p 395 N94-28981 systems development p396 N94-29257 Experimental studies of transonic flow field near a Performance evaluation of the NWT with parallel Design aspects in small aircraft gas turbine fuel longitudinally slotted wind tunnel wall Fortran p415 N94-28992 injectors p397 N94-29264 (NASA.TP-3392] p37B N94-2954S A method of user interface tor NWT Princeton Unrv, NJ. Profile negotiation: An air/ground automation integration p415 N94-28993 concept tor managing arrival traffic p 387 N94-29578 Fuels combustion research National Transportation Safety Board, Washington, Miniature Imear-to-rotary motion actuator (AO-A275122) p 404 N94-29004 DC. p413 N94-29647 Air traffic management as principled negotiation National Transportation Safety Board annual review of Dynamic fracture mechanics analysis tor an edge between intelligent agents p3B4 N94-29562 aircraft accident data. US general aviation. 1990 delamination crack (PB94-126B69] p 382 N94-2918S Wall pressure fluctuations in the reattachment region [NASA-TM-109106] p417 N94-29856 of a supersonic free shear layer Aircraft accident/incident summary report In-flight toss Aerodynamic characteristics of a propeller-powered INASA-CR-195790] p 379 N94-29920 of control, leading to forced landing and runway overrun. high-Kit semispan wing Purdue Unhr, Wed Lafayette, IN. (NASA-TM-4S41J p 380 N94-29937 Continental Express. Inc.. N24706 Embreer EMB-120 RT, Pine Bluff. Arkansas. 29 April 1993 Integrated propulsion*ain>ame dynamics and control User's manual tor the model interlace and plugboard p392 N94-29854 cabinets in the 14- by 22-foot subsonic tunnel [PB94-910404] p382 N94-29402 Time-marching aeroelastic and spatial adaptation [NASA-TM-109062) p 381 N94-30176 Maval Air Warfare Center, Indianapolis, IK procedures on triangular and tetrahedral meshes using Application of fuzzy logic to the control of wind tunnel NAVAIR aircran wiring standardization and qualification an unstructured-grid Euler method p379 N94-29877 settling chamber temperature program p408 N94-28704 (NASA-TM-109105) p 402 N94-30200 Organized wiring systems p 408 N94-2B70S National Aeronautics and Space Administration. Lewis Naval Air Warfare Canter, Trenton, NJ. Research Center, Cleveland. OR Combustion technology needs lor advanced high The nozzle acoustic test rig: An acoustic and pressure cyde engines p404 N94-29248 Raumtahrt Systemlechnlk Oirub-R, Salem (Germany). aerodynamic tree-rat facility Naval Aviation Logistics Center, PMuzent Rrv«r, MO. Ground independent landing system [NASA-TM-106495] p 401 N94-28749 Aircraft age impacts on maintenance requirements p385 N94-29S64 Spray combustion experiments and numerical (AD-A275701) p 373 N94-2B666 RoUa-floyce Ltd, Bristol (England). predictions p407 N94-29277 Ararat! age impact on individual operating and support Combustion for future supersonic transport propulsion Fuel-rich catalytic combustion of a high density fuel p404 N94-29249 [NASA.TP-32811 p407 N94-29356 cost elements (AD-A275739J p373 N94-2B732 Royal Military CoO. of Canada. Kingston (Ontario). Method for cancelling expansion waves in a wave Acoustic emission monitonng of aging rotor Naval Postgraduate School, Monterey, CA. Service Wo prediction of composite structures through stnjctures [NASA-CASE-LEW-15218-2] p413 N94-29740 (DREP-93-17) p393 N 94-30129 A novel approach to noise-fittering based on a fiber testing [AD-A275661] p403 N94-28654 Enhanced fatigue crack detection in aging an craft using gain-scheduling neural network architecture continuous acoustic emission monitoring Safety enhancement of compotiles via periodic proof [NASA-TM-106563) p 401 N94-30204 (DREP-93-16) p393 N94-30131 National Aeronautics and Space Administration. testing Marshall Space Flight Center, HuntsvfUe. Al_ [AD-A2756S2] p 403 N94-286SS Tuned mass damper for integrally Maded turbine rotor A moment plotting method tor characterizing aircraft (NASA-CASE-MFS-28697-1) p411 N94-29353 fatigue data population distributions National Aerospace Lab, Amsterdam (Netherlands). (AD-A275500J p390 N94-2B660 Sanaa National Labs, Albuquerque, NM. Engineering of systems tor application of scientific Aerodynamic design using pai processors Holographic interterometry: A user's guide computing in industry p415 N94-28947 [AD-A275470] p374 N94-28674 (OE94-003136) p408 N94-28466 ENGRID: A graphical interactive code tor trie Acquisition, design modrficabc \ assembly, Shape Technical Center, The Hague (Netherlands). computation of structured grids tor blocked flow domains test of NPS HummingDvd remotely piloted helicopter Use of QPS in automated air traffic control p409 N94-28956 [AD-A27S546] p 390 N94-28837 p384 N94-29563 Simulation of fully automated air traffic control Procedural guide for modelling and analyzing the flight ACCS Surveillance Exploratory Prototype (ASEP) concepts p386 N94-29S69 characteristics of a helicopter design using ftighttab p412 N94-29566 The PHARE advanced toots p388 N94-29581 [AD-A275077] p 391 N94-2B870 uluiiuxu Col p. (Japan). Development of a method to predict transonic limit cycle A nonlinear simulation for an autonomous unmanned Three dimensional simulation of compressible flow oscillation characteristics of fighter aircraft (continued) air vehicle induced by a high-speed train moving into a tunnel [NLR-TP-92156-U] p 393 N94-30342 (AD-A275062) p 391 N94-29200 p376 N94-28967 The design of a system of codes tor industrial Sodett de Fabrication d'lnstruments de Meaure, ettrertantfs AQency for Aerospace Programs, Delft. calculations of flows around aircraft and other complex Massy (France). ENGRID: A graphical interactive code tor the aerodynamic configurations Performing specifications tor complex systems' computation of structured grids for blocked flow domains (PB94-12S598) p 381 N94-30387 software p400 N94-29317 Numerical investigation into Ngh-angte-ol-attack p409 N94-28956 Sodete Nationale d'Etude et de Construction de leading-edge vortex flow Motaurs d-Aviation. Motasy-Cnmayal (France). [PB94-125564] p 381 N94-30388 Aerothermochemical calculations in afterburners Correction of X hot-wire measurements for gradients p396 N94-29258 normal to the plane of the wires Stanford Unrv, CA. (PB94-125473) p402 N94-30399 Onto State Unrv, Columbus. A method tor the modelling of porous and solid wind Calculus of variations applied to 2D mufti-point airfoil Boundary layers induced by three-dimensional vertex tunnel walls in computational fluid dynamics codes loops (NASA-CR-195699) p 409 N94-2B724 (PB94-125457) p381 N94-30401 (AD-A275678] p408 N94-28665 Numerical study of the (raffing vortex of a wing with A modernised HST of NLR OM DomMon Unrv, Norfolk, VA. wing-tip blowing IAD-B179220) p402 N94-30423 Review of some fatigue technology INASA-CR-195803] p 378 N94-29760 elherlafiQSL [NASA-CR-4587] p417 N94-29407 Sumitomo Heavy Industrie* Ltd, Tokyo (Japan). Experiments and theoretical considerations regarding Study of bridge design and technology the allowable roughness height in laminar flow Oaaka Prafecture Unrv, Sakal (Japan). [PB94-137916] p373 N94-29160 (PB94-12SSS6) p 381 N94-30389 Numerical analysis of sonic boom in the near field Sverdrup Technology, me. Brook Park. OH. National Aerospace Lib, Kakuda (Japan). p376 N94-28962 Structural/aerodynamic blade analyzer (SAB) user's Numerical simulation of steady Mach reflection by shock Three-dimensional external flow computations using guide, version 1.0 capturing schemes p375 N94-28953 prismatic grid P 410 N94-28979 [NASA-CR-194460] p395 N94-29103

C-3 Swedish Inst for Materials Testing CORPORATE SOURCE

Turbomachinery forced response prediction system (FREPS): User's manual [NASA-CR-194465] p411 N94-29104 Swedish Inst. for Materials Testing, Boras. Determination of sound power levels of air terminal units according to ISO 5135-Nordic inter-laboratory tests, Nordtest project no. 968-91 [PB94-137411] p416 N94-29175 Systems Control Technology, me, Arlington, VA. Rooftop emergency heliports (DOT/FAA/RD-93/2) p402 N94-29754 Potential hazards of magnetic resonance imagers to emergency medical service helicopter operations IDOT/FAA/RD-92/15] p 382 N94-29862 Systems Reseat eh Labs, Inc, Dayton, OH. Development of global/chemistry model tor jet-fuel thermal stability based on observations from static and flowing experiments p405 N94-292S2 T

TA Consultancy Services Ltd, Famham (England). Integrated formal verification and validation of safety critical software p 416 N94-29338 Technlsehe Hochsehukt. Darmstadt (Germany). Numencflf rnodGlbrtQ of turbine cornbustion cfiflrnoGrs p396 N94-29254 The mixing process in the quenching zone of the rieh-tearvcombustion concept p 407 N94-29281 Technlsehe Unhr, Brunswick (Germany). Automatic control steps lor aircraft taxi guidance p388 N94-29564 Tans MM Unhr, College Station. Wind tunnel testing and research [NASA-CR-188273) p 402 N94-29052 Texas Unhr, Arlington. liifuiillation pr^nitfMatifT** for export systems BI future figfiter aiuafl (A0-A275126J p394 N94-2BOOS Texas Unhr, Austin. Models for viorafjorxfasoaation coupling in high-temperature gases p 413 N94-29675 Tohoku Unhr, Sendal (Japan). Higher-order accurate numerical simulation of 3D supersonic mixing layers p 375 N94-28954 Tokyo Inst of Tech. (Japan). Transonic expanding flow through anally symmetric orifices p410 N94-28965 Tokyo Unhr. (Japan). Numerical study on the interaction between scramjet engine modules caused by thermal choke p395 N94-28960 Study on mixing and injection of hydrogen into a supersonic flow p 377 N94-28975 u Unltto TtcfafiotoQitfl RvMCeVCtt Center, Esct ttertfocd, CT. Evolustion of tho trsnsiGnt opGfBtion of ftOVsncBd Q*ts turbine combustors p397 N94-29269 UnrMrsMad PoUtecracs da Madrid (Spain). Effects of hydrogen addition on pollutant envssions in a gas turbine combustor p 406 N94-29275 w Washington State Unhr, Pullman. The rfttftor»«'^ffrt hydfojcyl toctvuQUG p414 N94-28600 An ftniwfif^^nuii study of wing tip vofteji in the near wake of a rectangular wing [AD-A275389] P 377 N94-29306 Wichita State Unhr, KS. DnroiiplnrHligtucoiiUul system design using the singular perturbation method p 400 N94-298SO The effect of mechanical paint snipping on the fatigue and fracture of thin aluminiirn av plane skin p40B N94-29900 Wright Lab, Wright-Patterson AFB, OH. Research and development of high thermal stabiity fuels P405 N94-29261 Object oriented design of the autonomous fixtakmo management system p383 N94-2S323 Tesong Operational FSght Programs (OFPs) P416 N94-29337

C-4 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 305) June 1994

The we el tow cost differential mode OPS receivers DLR's ATM demonstration pioaramme *\ unmanned vehicles P389 N94-30285 p386 N94-29575 HATT-X: A high performance flying laboratory tor Experimental flight managernont systern autonomous unmanned aircraft research and p388 N94-295BO Typical Foreign Technology development P 393 N94-30293 Automatic control (taps for aircraft tan guidance p388 N94-29S84 Index Listing A novel neaMange radar network tor airport turtace control P389 N84-29586

[COUNTRY Of INTELLECTUAL ORIGIN) FRANCE Fuels and Combustion Technology for Advanced Aircraft Engines ITALY [AGARD-CP-536] P«04 N94-29246 Numerical simulation of aeiothermal characteristics in _L AeiullieiiiiuUieiiiLal calcubrtons in afterbumeni CHMA gas turbine eombustors with complex geometries — Th» prnsnt situation and future development of Chines* p396 N94-292S6 p396 N94-292S5 aviation refctbuity and mainutnaoUity engmeering Research and Development of Ram/Scramjets and Computational and experimental results in high pressure 1S3 A94-10101 Turboramiets in Russia combustions of H2/air and H2/O2/H2O [AGARD-LS-194] P397 N94-29291 p406 N94-29266 Aerospace Software Engineering for Advanced Systems T0cnnolo0y nQS* A tool for ifiorounior oovotopcncnl Architectures p397 N94-29270 [AGAROCP-M51 P*1S N94-29315 On ground systen) ffitoprction Ano testing A modem How to control the increase in the compkuity of civil p394 N94-29334 aircraft on-board systems P 394 N94-29316 Listings In this Index are arranged alphabetically Peifuniiiiu specifications for complex systems by country of Intellectual origin. The title of the software p400 N94-2S317 Flight command software development: RAFALE document Is used to provide a brief description p415 N94-29320 JAPAN Proceedings of the 10th NAL Symposium on Aircraft of the subject matter. The page number and run feme system cavlifiLason for avioncs accession number are Included In each entry p394 N94-29332 Computational Aerodynaiiics INAL-SP-19] p375 N94-28946 Theoretical and experimental study of a cylindrical to assist the user In locating the abstract In Monte Carto simulation or normsl shock wave. Part 2: the abstract section. If applicable, a report num- irteiusliip antenna [REPT-83Z-440-109) P412 N94-2B4S6 VHS model and VSS model p409 N94-2B948 ber is also included as an aid In Identifying Fire behavior of aeronautical materials Variable soft sphere molecular model in the Monte Carto simulation of air specie* p409 N94-28949 the document. (REPT-932-600.105] P406 N94-29457 A time i i based on the event calculus Rarefied gas numerical wind tunnel. Part 6: HOPE tor scheduhng in aeronautic iiiaMitenance p 401 N94-2S950 [REPT-932-710-101} p374 N94-29463 Numerical simulation of arc heated wind tunnel flow Automation of the NOT diagnostic using neural nets. p402 N94-28951 Numerical simulation of unsteady aerodynamic heating Application: Inspection el Airbus tongjuidinal taints during induced by shock reflections p375 N94-289S2 (REPT-932-600-t04] p412 N94-29474 Numerical simulation of steady Mach reflection by shock Machine Inteuoence In Air Traffic Management capturing schemes p375 N94-26953 [AGART>CP-538] p383 N94-29558 Higher-order accurate numerical simulation of 3D supersonic mixing layers p375 N94-28954 AUSTRALIA Use of advanced technologies in ATM (air traffic Numerical simulation of aeiullieiiiiudvtiimc heating of Ftthermans Bend: A centre of Australian aviation management) domain p384 N94-29S01 hypersonic space transportation verities IAD-A274981] p 373 N94-29000 Cognitive approach to specifications on air traffic Cold expansion and interference tor extending the p37S N94-28955 A design el ttwd-genemimi airfoils tor heitoopter rotor f«igue lite of mulWayer metal torts p3S6 N94-29S71 Hades using Navier-Stokes p391 N94-28957 IAOA274982] p410 N94-29091 DAISY: A decision aklto ra n w i p3B8 N94-29574 Numerical analysis of airfoil tor heecopter Made at Ngh The Common Modular Simulator (CMS): An architecture angle of attack using Navier-Stokes code B last bad tor future advanced ATM systems p375 p388 N94-28582 Numerical analysis of supersonic transport wings ARC2000: Automatic radar control p375 N94-2B959 Decision Making Aids (DMA) in on-line ATC systems p388 N94-29S83 Numerical study on the intaraclio b p 386 N94-29570 •ngiiie modules caused by thermal choke Air-ground integration of the ATM system in PHARE p395 N94-28960 p388 N94-28S7S Numerical simulation of supersonic flow around space plane with engine installed p 376 N94-28961 QERMANY Numerical analysis of sonic boom in the near field On ttk0 cfnct of •nwonft front •wciftn •nojnss on Ino p376 N94-28962 state of the atmosphere p4l4 N94-29247 Numerical analysis of two dimensional/axisymmetric Numerical modelling of turbine combustion chambers non-equatrium hypersonic flow P376 N94-2B963 BeoantCFD applications in small gas turbine combustion p396 N94-29254 Role of computational fluid dynamics in aeronautical system!development page N94-29257 The nixing process in the quenching zone of the engineering. Part 10: Numerical analysis of flow around Design atpects In small aircraft gas turbine fuel ncMesn-combustxxi concept p407 N94-2928t 2-D muttMlement HLD p410 N94-28964 injectors p397 N94-29264 Investigation of the two-phase flow in a research Numerical solution of inverse problem it Intelligent systems for air space control and eombuator under reacting and non-reacting conditions •erodynamies p376 N94-2B965 management p384 N94-29560 p4t1 N94-2B2K Code development for hypersonic real-gas Mow Acoustic emission montoring of aging aircratt TknaH or* nts in a three dimensional simulations toward the design of space vehicles, part 2 etmcturts model oombustor P411 N94-29283 p376 N94-28966 [DREP-03-17] P393 N04-3012S Experiences with the HOOD ov gn method on avionics Three Omemimial simulation of compressible flow Radar jet engine health monitoring project p41S N94-2932S induced by a high-spssu train moving Into a tunnel (ASSGl-301i p400 N94-30130 Ground independent landing system P376 N94-28967 Enhanced fatigue crack detection in aging aircraft using p385 N94-29S64 Unsteady aerodynamic computations around continuous •cmittjc emission monitoring GPS/GNSStorATM P3S5 N94-29565 NACA0012 at high angles of attack p377 N94-2896B [DREP-fr3-iej p383 N94-30131 Contributions of DLR to air traffic capacity enhancement Study on mixing and infection of hydrogen into a A capacity planning model for Canadian nvlitary ajrwi with*atamwialana P38S N94-29567 supersoncnow p377 N94-2B975 Considerations on graphical user interfaces for intelligent Varificalionofarhiee diiiieiiiiuiisl viscous flow analysis (ISBN-041546079-0] p382 N94-30144 ATM support systems p386 N94-29572 for a single stage compressor p410 N94-28976 Paytoad central control tor unmanned aircraft Interactive analysis and planning tods tor air traffic and Numerical study on internal flows of centntugaf p401 N94302B4 aitpace management p3S6 N94-29573 p39S N94-2S977

D-1 FOREIGN TECHNOLOGY INDEX NETHERLANDS

Application ol flow field simulation to turbine vane design p 395 N94-28978 Three-dimensional external flow computations using SPAIN prismatic grid p 410 N94-28979 High temperature resistant jet fuels P405 N94-29260 Application of digital control theory to adaptive grid Effects of hydrogen addition on podutant emissions in generation p415 N94-26980 a gas turbine combustor p 406 N94-29275 An elliptic-hyperbolic grid generation method and SWEDEN application to compressor flows p 395 N94-28981 Determination of sound power levels of air terminal units Transonic expanding flow through anally symmetric according to ISO 5135-Nordic inter-laboratory tests. orifices p410 N94-28985 Nordtest project no. 968-91 Similarity between turbulent flows through curved pipe [PB94-137411] p416 N94-29175 and orthogonal rotating pipe p4!0 N94-28986 Performance evaluation of the NVvT with parallel u Fortran p41S N94-28992 A method of user interface for NWT UNITEO KINGDOM P415 N94-28993 Conibustion for futunj supersonic trflnsport propulsion Study of bridge design and technology P404 N94-29249 (PB94-137916) p373 N94-29160 Rowfield prediction of NOW and smoke production in aircraft engines p 404 N94-29252 Ultra low NO(x) ultra lean gas turbine primary zones N with liquid fuels P397 N94-29267 The influence of air di&uiuution on humuyenorry and NETHERLANOS pollutant formation in the primary zone of a tubular Engineering of systems for application of scientific combustor p406 N94-29274 computing in industry . p415 N94-28947 Ducted kerosene spray flames p 407 N94-29276 ENGRID: A graphical interactive code for the Integrated formal verification and validation ol safety computation of structured grids tor blocked flow domains critical software p416 N94-29338 p409 N94-2B9S6 SOE's for the year 2000 and beyond: An EF perspective p 416 N94-29344 Uae of GPS in automated air traffic control Airaide ground movements surveillance p384 N94-29S63 P388 N94-2958S ACCS Surveillance Exploratory Prototype (ASEP) Aircratt evacuations: The effect of a cabin water spray P412 N94-29566 system upon evacuation rates and behaviour Simulation of fully automated air tiaffic coiiliul (CAA-PAPER-93008] p 393 N94-28887 concepts p386 N94-29569 The PHARE advanced tools p388 N94-29581 Davetopmeni of a method to predict transonic limit cycle oscillation characteristics of fighter aircraft (continued) (NLR-TP-921S6-U] p 393 N94-30342 The design of a system of codes for industrial calculations of flows around aircraft and other complex aerodynamic configurations [PB94-125598] p 381 N94-30387 Numerical investigation into higlvangle-of-atlack leading-edge vortex flow [PB94-125564] p 381 N94-303B8 Expel in mills and theoretical considerations regarding the allowable roughness height in laminar flow [PB94-12S5S6] p381 N94-30389 Correction of X hot-wire measurements tor gradients normal to the plane of me wires [PB94-12S473] p402 N94-30399 Calculus of variations applied to 2D mum-point ajrtol design (P6S4-1254S7] p 381 N94-30401 A rnodemoed HST of NLR IAD-B179220) p402 N94-3O423

RUSSIA Enrjotherrrac fuels for hyperaorac aviation p407 N94-2928S Introduction and overview of research and development of solid propellam ramrockets, liquid fuel ramjets and oxpotintontav nyoroQon rent cornbustors p398 N94-2BZ92 Turboramjet engines: Types and performances p398 N94-29293 HGso&rcfi And dovolopfflont of unijots/fjUin'ookcts. Psrt 1: Integral solid propeUant ramrockets P398 N94-29294 Sofns prootofTts of flCfdrnjol propulsion for 80fospcc0 planes. Part 1: Scramjet Aims and features p3S8 N94-2929S Sctanijot U^LJ iiwttwds And ftnslysts. Psrt 1; Scrvnfot CFD methods. Numerical simulation of the flow in seramjet duct p338 N94-29296 Research and development el ramjets/iamroclmls. Part 2: integral Bquid fuel ramjets p 398 N94-29297 Raseaich and devetopment of ramjets/ramrockets. Part 3: The study of ffmw hydrogen ram combustora p398 N94-29298 CtAM experimental turboramiets p399 N94-29299 Scramjel CFD method* and analysis. Part 2: Scramjet CFD analysis. Numerical stmutaton of supersonic mining and cofiAjb&ljOfh appfir<1 to scrarniet uonajuslm p399 N94-29300 Some problems of aciaiiiiet propulsion for aerospace planes. Part 2: Scramjet Development and test p399 N94-2S301

D-2 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 305) June 1994

N0014O-87-C-6321 _ p396 N94-29263 N0014O-87-C-9902 _ p397 N94-29269 RTOP 232-01-06 — p411 N94-29104 RTOP 505-59-10-13 p381 N94-30176 Typical Contract Number RTOP 505-59-53 — p380 N94-301S1 Index Listing RTOP 505-62-10 p395 N 94-29103 p412 N94-2BS52 RTOP 505-62-52 . P407 N 94-29356 RTOP 505-62-84 . p401 N94-28749 RTOP 505-63-5B p409 N94-26815 pM5 N94-29103 AF PROJ. 2404 p 44 N94-17461 RTOP 505-63-50-04 . p403 N94-28823 RTOP 5050-50-10 . p417 N94-29856 RTOP 505-63-50-15 . p374 N94-28658 RTOP 505*3-58 — P411 N94-29104 RTOP 505-68-10 — p380 N94-30124 p381 N94-30152 RTOP SOS-W-7O-05 p377 N94-29443 RTOP 505*9-20-01 p378 N 94-294 73 Listings In this index are arranged alphanumeri- RTOP 505-70-59-03 . p402 N94-30200 RTOP 506-40-41-01 p378 N94-29545 cally by contract number. Under each contract RTOP 535-03-10*2 p380 N94-29937 number the accession numbers denoting docu- RTOP 53503-10 — p395 N94-29103 ments that have been produced as a result ol P399 N94-29438 research done under the contract are shown. The RTOP 537-03-21-03 p417 N94-29464 accession number denotes the number by which RTOP 538-05-15-03 p412 N94-29480 RTOP 584-03-11 — p401 NS4-30204 the citation is identified In the abstract section. RTOP 783-23-45-70 . p417 N94-29407 Preceding the accession number Is the page W-7405-ENG-4B — p374 N94-29842 number on which the citation may be found.

AFPROJ. 7184 _. AF-AFOSfl-0431-91 BRITE/EURAM-1019 DA PROJ. 1L1-62211-A-47A DAAL03-89-K-0095 OAAL03-90-C-0013 DAA103-90-G-0004 OAAL03-91-G-0026 DE-AC04-94A1.-85000 0T-FA01-92-G-0011 DTFA01-87-CO0014

DTFA01-89-C-00016 DTFA03-BO-P-00447 DTRS57-89-C-00006 DTRS57-89-O-O0007 DTRS57-69-D-00009 FO863S-90-C-0100 F3361S47-C-2709 F33615-89-C-0532 F3361S-90-C-2033 F336lfr«9-C-O532 F49620-93-1-0009 NAGl-1072 h4AG 1-363 NAG3-1124 NAG3-1134

NAG3-1433 NAG3-1669 NAG3-28 NAG3-912 NASl-19299 NAS2-13872 NAS3-22525 NAS3-25266

NAS3-2S269 NAS3-2S270 NAS9-18261 NCC2-55 NCCZ-SB2 NCC2-«05 NCCZ499 NCC3434 NIVRO1506N NIVR-01604N NIVR47801N N000l4-89s»-1721 NO0014-91-C-012S

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 305) June 1994

p397 N94-29291 t p381 N94-30387 p 381 N94^0388 AIAA PAPER 92-2600CP P 381 N94^0388 p381 N84-30389 Typical Report Number AIAA PAPER 92-2619-CP P 381 N94^30387 p402 N94-3039S Index Listing AIAA PAPER 94-2565 P 401 N94-28749 ' p381 N94-30401 ETN-94-95961 p402 N94^0423 AL/CF-TH-1993*102 P 391 N94-29042 AL/CF.TH-1993-0134 P 394 N94-29048 AL/CF.TR-1993*164 P 394 N94-29005 INT.PATENT.CLASS-B25J-11/00 p413 N94-29726 •

ALENIA.TR-57X92054 INT-PATENTCLASS-F02C-3/02 . p413 N94-29740 •

INT-PATENTCLASS-G05Q.il/00 p413 N94-29726 •

ISBN^-315-86079* .... p382 N94-30144 ISBMV86039-S47-2 .... p393 N94-29887 ISBN-924350719-3 .... P404 N94-29246 ISBN-92-835-0724-X .... p383 N94-295S8 Ustings in this Index are arranged alphanumeri- .... p415 N94-29315 cally by report number. The page number .... p397 N94-29291 indicates the page on which the citation Is located. The accession number denotes the num- JIAA-TR.111 ... p 409 N94-28724 • ber by which the citation is identified. An aster- JIAA-TR-112 _. p 378 N94-29760 * isk (*) indicates that the item Is a NASA report. p375 N94-26946 A pound sign (*) Indicates that the Item Is available on microfiche. _„ p 378 N94-29545 ' A-93077 p 380 N9440151 • * _ p380 N94-29937' ... p 414 N94-29942 ' AT>A274981 p373 N94-29090 AD-A274882 p4lO N94-29091 ... p377 N94-29306 AB4275046 p402 N94-29151 * AT>A275Q62 p391 N94-29200 * NAL^P-19 ... p375 N94-28946 AD-A27S077 N94-28870 ff AD-A275107 p374 N94-28899 * NAS 1.15:104019 . p380 N94-30151 ' AD-A275115 ..... P3B3 N94-28914 ff NAS 1.15:106495 . p401 N94-28749 A0^275122 _.. P404 N94-29004 IT NAS 1.15:106563 . p401 AD-A275126 _.. P394 N94-29005 * NAS 1.15:109026 . p403 N94-2B823- N94-29042 * NAS 1.15:109045 . p377 N94-29443 ' AD-A275127 _ p391 DCR/M-6154Q/C-92 AD-A275172 . p394 N94-29048 ff NAS 1.1! p374 N94-28658 • AD-A275228 . P395 NS4-29389 * p381 p417 N94-29464- . p374 N94-2BB42 N94-2B9O1 NAS 1.15:109105 P402 N94-30200* NB4.2BMH NAS 1.15:109106 . p417 N94-29B56* , p410 NAS 1.15:109110 p378 N94-29473 * DOOA-AR-006-377 . p373 NAS 1.15:4541 _ p380 N94-29937- N94-29197 NAS 1.26:187105 N94-29438' DOT-VNTS&FAA-93-10 . NAS 1.26:188273 N94-29052 AD-A275451 p400 N94-28832 ff OOT-VNTSC-FAA-03.il . p374 N94-2B674 f N94-297Z7 AD-A275470 DOT-VNTSC-FAA434 - NAS 1.26:189293 AD-A275SOO p390 N94-28660 ff NAS 1.26:194266 N94-296B5 ~ N94-28837 » NAS 1^6:194460 N94-29103 AT>A275546 DOT/FAA/CT-TN41/2B . p382 N94-28815 N94-291 OOT/FAA/CT-TN93/12 p383 N94-28914 AD-A27S666 ... p 390 N94-286S7 ff N94-298S3 N94-28510' AO-A275678 ,_. P40B N94-28665 * DOT/FAA/CT-93/76 . p4O8 N94-28646 AD-A275701 .. p373 N94-28666 # N94-30124 • DOT/FAA/CT-83/78 . p390 N94-28657 AD-A275739 ... p 373 N94-28732 f OOT/FAA/CT43/79 N94-30152 * _ p408 N94-28846 ff N94-28724- NAS 1^6:195737 N94-28817 • AD-A275756 _. p390 N94-2B647 0 DOT/FAA/RW2/15 ... p382 NAS 1.26:195763 N94-29660' AD-A275789 ... p 373 N94-28743 ff DOT/FAA/RD-93/2 _ -. p402 N94-29754 AOA275791 ._ " N94-28744 ff DOT/FAA/HD-94/1.1 NAS 1^6:195774 . p414 N94-29942* N94-28830 NAS 1.26:1*5786 N94-30013* NAS 1^6:195790 p379 N94-29920* N94-287B9 ff DREP-63-16 N94-30131 NAS 1^6:195603 DREP-93-17 p378 N94-29760* AD4179220 ... P402 N94-30423 NAS 1.26:4561 ... p412 N94-29SS2' . p412 N94-29460* . p407 N94-29356 AFCESA/ESL-TH-91-26 _. p402 N94-2B151 f PJUXU p417 N94-29407* NAS1.60-J281 p407 N94-293S6- N94-29545* E-8490 — p378 NAS 1.71:ARC-12030-1 — p417 N94-29362' E-6495 NAS 1.7l:MFS-28697-1 — P411 N94-29353* AFrr/GAE/ENY/B3O-23 . p 301 N94-28998 t E-8518 . p411 NAS 1.71*ISC-22277-1 p411 N94-29448* . p401 N9M0204 AFIT/GLM/LAL/93S4 - p 383 N94-28744 ff E-8778 P380 NASACAS£WkRC-12030-1 _ p417 N94-29362*ff p381 AFTT/GSS/LAS/93D-7 _ p373 N94^B743 ff ... p 413 N94-29726 * . p412 N94-29456 NASA32TR ETN-94-95484 p4oe N94-29457 . p374 N94-29463 ff AGART>CP.S36 . p404 N94-29246 ff FITWM-95487 NASACASE-MFS-28697-1 ... p411 N94-29353-* N94-29887 P383 N94-29S5B ff AGAR&CP-S45 ~ . P415 N94^931S ff FTN-94-9S576 p393 N94^0342 NASA-CASE-MSC-22277.1 _ p411 N94-29448* #

F-1 REPORT NUMBER INDEX NASA-CR-187105

NASA-CR-187105 p399 N94-29438 # US-PATENT-CLASS-901-19 p 413 N94-29726 • NASA-CR-188273 p402 N94-29052 # NASA-Cft-1 89293 p416 N94-29727 # US-PATENT-5^79,176 p 413 N94-29726 • NASA-Cft-194266 p392 N 94-29685 US-PATENT-5i97.384 p413 N94-29740' NASA-CR-1 94460 p395 N94-29103 NASA-CR-1 94462 p409 N 94-2881 5 WL-TH-93-2086 -. p403 N94-28901 NASA-CR-194465 p411 N 94-29104 NASA-CR-1 94535 p379 N 94-29893 XC-AFCESA/ESL p402 N94-29151 # NASA-CR-1 94868 p401 N94-28510 NASA-CR-1 95327 p380 N94-30124 NASA-CR-1 95330 p381 N94-30152 NASA-CR-1 95699 — p409 N94-28724 NASA-CR-1 95737 p390 N94-28817 NASA-CR-1 95763 p 399 N94-29860 NASA-CR-195774 p414 N 94-29942 NASA-CR-1 95786 p399 N94-30013 NASA-CR-1 95790 p379 N94-29920 NASA-CR-1 95803 p378 N94-29760 NASA-CR-4561 p412 N94-29S52 NASA-CFU579 p412 N94-29460 NASA-CR-4587 p417 N94-29407

NASA-TU-10""0 p380 N94-30151 MA5A-TU-1WW> -— - p401 N94-28749 NASA.TU.1 PfiSfi.1 p401 N94-30204 NASA-TM-109026 p403 N 94-28823 NASA-TM-10904S p377 N94-29443 NASA-TM-109046 p374 N94-28658 NASA-TM-109062 p381 N94-30176 NASA-TM-109090 p417 N 94-29464 NASA-TM-109105 p402 N94-30200 NASA-TM-109106 p417 N94-29856 NAfiA-TU-inaiin p 378 N 94-294 73 NASA-TM-4541 . p380 N94-29937

MA$A-TP-32ft1 p407 N94-2B356 NASA-TP-3392 . . ._ P378 N94-29545

NLR-TP-92156-U _ p393 N94-30342 NLR-TP-82190-UP p 381 N94-30387 NLR-TP-92248-U p 381 N94-30388 NLR-TP-92252-U . p381 N94-30389 NLR-TP-92361-U . p 381 N94-30401 NLR-TP-924ZO-U . p402 N94-30423 NLR-TP-95592 _ . p402 N94-30399

NTSB/AAR-94/02/SUM ... p 382 N94-29402 f

NTSB/ARG-93/02 ... p382 N94-29185

PB94-125457 p381 N94-30401 PB94-125473 P402 N94-30399 PB94-125556 — N94-30389 PB94-125564 p381 N94-30388 PB94-125598 p381 N94-30387 P894-126869 p382 N94-29185 PB94-137411 p416 N94-29175 f PB94-137916 . p373 N94-29160 PB94-142551 . p390 N94-28657 # PB94-143336 p390 N94-28647 t PB94-910404 p382 N94-29402 t

POLY-AE-93-8 p 374 N94-28899 *

REPT-932-440-109 P412 N94-29456 * REPT-932-600-104 _. p412 N94-29474 t REPT-932.600-105 _ p4O8 N94-29457 t REPT-932-710-101 . _. p374 N94-29463 #

RF-767440/722045 . p408 N94-28665 »

R54045007 ... p392 N94-2968S'#

SAND-92-2909 P408 N94-28486 t

SCT42RH-14 . . p382 N94-29862 t

SEL-89-103-REV-1 . p416 N94-29727-*

SP-HAPP-1993-43 . . p416 N94-29175 t

TR-93-01 . p377 N94-29197

UCRL-CR-115237 p374 N94-29842 §

US-PATENT-APPL-SN486S81 . p413 N94-29740 US^ATENT-APPL-SN-134443 . p411 N94-2S353 US-PATENT-APPL-SN-151690 . p417 N94-29362 US-PATENT-APPL-SN-1S9606 . p411 N94-29448 US-PATENT-APP1.-SN-889003 . p413 N94-29740 US-PATENT-APPL-SN-915567 . p413 N94-29726

US-PATENT-CLASS-60-39.02 _ . p413 N94-29740 US-PATENT-CLASS-74-479B _ . p413 N94-29726 US-PATENT-CLASS-74-479PF . p413 N94-29726 US-PATEMT-CLASS-901-14 _ . p413 N94-29726

F-2 ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 305) June 1994

N94-29282 p411 N94-29726* P413 Typical Accession Number N94-28283 p411 N94-29727 * # p416 Index Listing N94-29285 P407 N94-2872S P400 N94-29740 * P413 p397 N 94-29291 N94-29754 * p402 N94-29292 p398 N94-29760 • «l p378 P398 NASA ON N94-29293 N94-29826 p378 PONSOREO MICROFICHE N94-29294 P3S8 N94-29839 p414 k N94-29295 p398 N94-29842 H p374 N94-28296 N94-2S850 p400 A94-10717 • t p71 N94-29297 N94-2S854 p392 N94-29298 P398 NS4-28856** p417 N94-29299 p399 N94-29880-* P399 ACCESSION I PAGE N94-29300 NUMBER NUMBER N94-2B862 # P382 N94-29301 p399 N94-29877 p378 N94-29306 p377 N94-29878 P392 N94-28315 p41S N94-29879 p379 N94-29316 P394 N94-29887 p393 Listings in this index are arranged alphanumerically N94-29317 P400 by accession number. The page number Indicates the N94-29893'f P379 N94-2B320 P41S N9*-?9900 P408 page on which the citation Is located. The accession N94-29323 P383 N94-29920** p379 number denotes the number by which the citation is N94-29325 P415 N94-29937-* p380 identified. An asterisk (•) indicates that the Item is a N94-28332 p3«4 N94-29942'* P414 p3»4 NASA report. A pound sign («) Indicates that the Item N94-29334 N94-29973 p360 N94-29337 P416 is available on microfiche. N94-300t3 ' p399 N94-29338 p416 NM-30124* p380 N94-29339 p416 N94-30129 p393 N94-28344 p416 N94-30130 p411 p400 M94-28466 P408 N94-2B975 p377 NM-29353* N94-30131 P393 M94-2S356 * p407 N94-28510* p401 N94-28976 p410 N84-30144 P382 N94-29362- p417 N94-28600* p414 N94-26977 p395 N94-30151 * P380 N94-28978 N94-29389 P395 N94-28632 p400 P39S N94-30152- P381 N94-28979 p410 N94-28391 p392 M94-28646 P40B NS4-30176* P381 N94-28960 p415 N94-29402 P382 N94-30t89 p389 N 94-28847 P390 N94-28S81 p395 N94-2S407- p417 N94-30200' P402 N94-28654 P403 N94-2B965 p410 N94-29438* N94-30204 * p401 N94-28855 p403 N94-2B966 p410 N94-29443- p377 N94-30284 N94-2B657 p401 p390 N94-28992 p415 N94-2B44S N94-302B5 p374 M94-28658 • N94-2B993 p415 N94-2S448 • p411 N94-30293 N94-28660 p390 p412 N94-2S996 p391 N94-294S6 N94-30342 p393 p406 N94.2B665 N84-29004 p404 N94-294S7 NB4-30387 p381 N94-2B666 p373 N94-2B005 P3S4 N94-29480* p412 NB4-3038B p381 N94-28674 P374 p374 N94-Z9O42 p391 N94 28463 MX-30389 P381 N94-2B704 • P408 N94-2B464- p417 N94-29048 P384 p402 N94-28705* p406 N94-2S473' p378 N94-29052* p402 NB4-30401 p381 N94-26724 • p409 N94-29MO p373 N94-29474 p412 NM-30423 p402 N94-28732 p373 NV4-2S091 p410 NM-29534 p412 N94-28743 p373 N94-29103* P39S N84-28S45* p378 N94-2B744 P383 N84-29104- p411 NS4-2BSS2* P412 N94-28749 ' p401 N94-291S1 P402 N9< 20888 P3S3 N94-28799 P382 N94-2S160 p373 N84-28S59 N94-2SB1S * p409 N94-2917S p4ie NM 29860 p384 N94-26817 * p380 N94-29185 P382 N94-28561 P384 N94-28823' p403 N94-29197 p377 NB4-29502 P384 N94-28830 p403 N94-29200 p391 N94-29S63 p384 N94-26837 p390 N84-2B246 P404 N94-29S64 P38S N94-28870 p391 N94-29247 p414 N94-29M5 p38S N94-28894 p409 N94-Z8248 P404 NS4-29S66 P412 N94-28899 p374 N94-ZB249 P404 N94-29567 N94-2B901 p403 N94-292S2 p404 N94-29568 P385 N94-28914 p383 N94-2B254 P3S6 N94-29S69 N94-26946 p37S N94-2B255 P39B N94-28570 N94-2BB47 p415 N94-292S6 p396 N94-28571 N94-28948 p409 N94-29257 p3S6 N94-29572 p386 N94-26949 p409 N94-292S6 p396 N94-20573 p386 N94-28950 p401 N94-292S9 P405 N94-29574 N94-28951 p402 N94-29260 p40S N94-29575 p386 N94-289S2 p375 N84-Z8261 P40S N94-29576 p387 N94.2B953 p37S N94-2S262 P40S N84-29577 p387 N94-28954 p37S N84-28263 p396 N94-29578 P387 N94-28955 p37S N84-28284 P387 N94-2857B N84-28956 p409 N944B285* p405 N94-29S80 p388 N94.28957 p391 NS4-29267 p3S7 N94-29861 p388 N94-2B9S8 • p37S N94-Z92«e p406 N94-28562 p3M NM-2B959 p375 NB4-2B2SB p387 N94-29863 p388 N94-28960 p38S N84.29270 p397 N94-29564 p38> N94-28961 p376 N94-2B271 • P406 N94-29865 p388 N94-2S962 p376 N»4-28272 P406 N94-29SB6 p389 p389 N94-28963 p376 N94-29274 406 N94-28S87 N94-2B964 P N94-28S94 p392 p410 40S N94-2B965 p376 N94-2927S P N84-29647 ' 0 p413 N94-28966 p376 N94-29276 p407 N94-29674 p378 N94-28967 p376 N94-29277' p407 N94-29675 p413 N94-28969 p377 N94-2S2B1 p407 NB« 20685 '» p3S2 G-1 AVAILABILITY OF CITED PUBLICATIONS

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Rev. 2/94 APP-5 REPORT DOCUMENT PAGE 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (305)

4. Title and Subtitle 5. Report Date Aeronautical Engineering June 1994 A Continuing Bibliography (Supplement 305) 6. Performing Organization Code JTT 7. Authors) 8. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Address

NASA Scientific and Technical Information Program 11. Contract or Grant No.

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

15. Supplementary Notes

16. Abstract This report lists 239 reports, articles and other documents recently announced in the NASA STI Database.

7. Key Words (Suggested by Authors)) 16. Distribution Ststtsmsnt Aeronautical Engineering Unclassified - Unlimited Aeronautics Subject Category - 01 Bibliographies

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