> Aeronautical NASA SP-7037 (132) Engineering February 1981 A Continuing Tl NASA Bibliography with Indexes

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National Aeronautics Space Administration

SHUTTLE LAUNCH 1981 Aeronautical Engineering Ae ering Aeronautical Engineerjr Kjineering Aeronautical Engir cal Engineering Aeronautical I i itiral Fnaineerina Aeroat {NASA-SP-7037(13^M AEHONAUTICAL ENGINEERING: A CONTINUING BIBLIOGHAPHY, SUPPLEMENT 132 (National Aeronautics and |Space Administration) \\2 p HC 4>5.00 gineering Aeronautical Engin ;al Engineering Aeronautical E lautical Engineering Aeronaut Aeronautical Engineering Aen : ring Aeronautical Engineering Supplement t';i

STAR r\:-H)( NASA SP-7037(132)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 132

A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in January 1981 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA).

Scientific and Technical Information Branch 1981 National Aeronautics and Space Administration Washington, DC This supplement is available as NTISUB/141/093 from the National Technical Information Service (NTIS). Springfield. Virginia 22161 at the price of $5.00 domestic; $10.00 foreign. INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. Since that time, monthly supplements, have been issued. This supplement to Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 342 reports, journal articles, and other documents originally announced in January 1981 in Scientific and Technical Aerospace Reports (STAR) or in International A erospace A bstracts (JAA). 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 bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes -- subject, personal author, and contract number — are included. An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A81 -10000 Series)

All publications abstracted in this Section are available from the Technical Information Service, American Institute of Aeronautics and Astronautics. Inc. (AIAA). as follows: Paper copies of accessions are available at S7.00 per document up to a maximum of 40 pages. The charge for each additional page is $0.25. Microfiche of documents announced in IAA are available at the rate of $3.00 per microfiche on demand, and at the rate of $1.25 per microfiche for standing orders for all IAA microfiche. The price for the IAA microfiche by category is available at the rate of $1.50 per microfiche plus a $1.00 service charge per category per issue. Microfiche of all the current AIAA Meeting Papers are available on a standing order basis at the rate of $1.50 per microfiche.

Minimum air-mail postage to foreign countries is $1.00 and all foreign orders are shipped on payment of pro-forma invoices.

All inquiries and requests should be addressed to AIAA Technical Information Service. Please refer to the accession number when requesting publications.

STAR ENTRIES (N81 -10000 Series)

One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviatiorts are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.

Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code followed by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables on page vii.

Documents on microfiche are designated by a pound sign ($) following the accession number. The pound sign is used without regard to the source or quality of the microfiche.

Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices. For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Section, Springfield. Va. 22161.

NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followed by the * symbol), use the N accession number. NASA patent applications (only the specifications are offered) should be ordered by the U S-Patent-Appl-SN number. Non-NASA publications (no asterisk) should be ordered by the AD, PB. or other report number shown on the last line of the citation, not by the N accession number. It is also advisable to cite the title and other bibliographic identification.

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(1) A microfiche is a transparent sheet of film. 105 by 148 mm in size, containing as many as 60 to 98 pages of information reduced to micro images (not to exceed 26:1 reduction). Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration. Public Documents Room (Room 126). 600 Independence Ave.. S.W.. Washington. D.C. 20546. or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory.

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Avail: BLL (formerly NLL): British Library Lending Division. Boston Spa. Wetherby, Yorkshire. England. Photocopies available from this organization at the price shown. (If none is given, inquiry should be addressed to the BLL.)

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

Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document.

Avail: • U.S. Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks. U.S. Patent and Trademark Office, at the standard price of 50 cents each, postage free.

Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line. GENERAL AVAILABILITY

All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliography user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA documents is included on the inside back cover.

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VI ADDRESSES OF ORGANIZATIONS

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Schedule A STANDARD PAPER COPY PRICE SCHEDULE

(Effective January 1. 19811

Price Pave Range North American Fon»,n Code Price Price A01 Microfiche $ 3 50 S 700 A02 001 025 500 1000 A03 026-050 6.50 1300 ACM 051-075 800 1600 A05 076 100 950 1900 A06 101-125 11 00 2200

A07 126-150 12 50 2500 A08 151 175 1400 2800 A09 176-200 15.50 31 00 A10 201 225 1700 3400 A11 226 250 18.50 3700

A12 251-275 2000 4000 A13 276-300 21 50 4300 A14 301-325 2300 4600 A15 326-350 24.50 4900 A16 351-375 2600 5200

A17 376-400 27 50 5500 A18 401 425 2900 5800 A19 426-450 30.50 6100 A20 451-475 3200 6400 A21 476-500 3350 67 OO

A22 501-525 3500 7000 A23 526-550 3650 7300 A24 551-575 3800 7600 A25 576-600 3950 7900 601-up V

A99 - Write for quote

I/ Add SI.50 for each additional 25 page increment or portion thereof for 601 pages up.

2/ Add S3.00 for each additional 25 page increment or portion thereof for 601 pages and more.

Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche

North American Foraien Price Price) EOl S 5.50 $ 1150 E02 6.50 13 50 E03 8.50 17.50 E04 10.50 21.50 E05 12.50 2550

E06 1450 29.50 E07 1650 3350 EOS 18.SO 37 50 £09 2050 41.50 E10 2250 4550

Ell 2450 49.50 E12 2750 5550 E13 3050 61 50 E14 3350 67.50 E15 3650 73.50

E16 3950 79.50 E17 42.50 85.60 E18 4550 91.50 E19 5050 10050 E20 6050 121.50

E99 - Write for quote N01 TABLE OF CONTENTS IAA Entries 1 STAR Entries 21

Subject Index A-1 Personal Author Index B-1 Contract Number Index C-1

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT -AVAILABLE ON MICROFICHE -*• N81-10636*# FWG Associates. Inc.. Tullahoma. Term.- NASA ACCESSION PILOT-AIRCRAFT SYSTEM REPONSE TO WIND SHEAR NUMBER r Interim Report Barry S. Turkel and Walter Frost Washington NASA Nov - -CORPORATE 1980 98 p refs SOURCE TITLE- (Contract NAS8-33458) , (NASA-CR-3342) Avail: NTIS^ HC A05/MF A01 CSCL04B- The nonlinear aircraft motion and automatic control model is expanded to incorporate the human pilot into simulations of -PUBLICATION AUTHORS- aircraft response to wind to wind shear. The human pilot is DATE described by a constant gains lag filter. Two runs are carried out using pilot transfer functions. Fixed-stick, autopilot, and manned computer simulations are made with an aircraft having CONTRACT -AVAILABILITY characteristics of a small commuter type aircraft flown through OR GRANT - SOURCE longitudinal winds measured by a Doppler radar beamed along the glide slope. Simulations are also made flying an aircraft through sinusoidal head wind and tail wind shears at the phugoid REPORT frequency to evaluate the response of manned aircraft in -COSATI NUMBER- thunderstorm wind environments. S.F. CODE

TYPICAL CITATION AND ABSTRACT FROM IAA

~AVAILABLE ON t MICROFICHE AIAA ACCESSION ' A81-10474 ft ^-The design of blowing-cooled aircraft electrical NUMBER—— machines (Voprosy konstruktsii produvaemykh aviatsionnykh elek- tricheskikh mashin). V. I. Naumenko, O. G. Klochkov. and V. V., 'AUTHORS Bandurin (Akademiia Nauk Ukrainskoi SSR, Institut Elektrodina- TITLE- miki. Kiev, Ukrainian SSR). TekJ>nicheskaia Elektrodinamika, July- Aug. 1980, p. 81-87. In Russian. AUTHOR'S The current status of air-cooled aircraft electrical machines is AFFILIATION reviewed. The possibility of reducing the weight and size of TITLE OF air-cooled machines is discussed, with particular emphasis on the PERIODICAL- design of cooling systems for synchronous ac-generators. B.J. PUBLICATION DATE AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 132)

FEBRUARY 1981

IAA ENTRIES impeller, the blade is of constant small thickness, which is the common practice in centrifugal fan construction. The other impeller has airfoil blading constructed from the standard C4 profile which is commonly used in axial compressors. Results indicate that the characteristics of the airfoil-bladed impellers at design velocity are significantly different when compared with other impellers. Detailed flow measurements were carried out at impeller periphery using a A81-10045 i! Reliability and engineering-economic-charac- hot-wire anemometer and conventional instruments. (Author) teristics of aircraft engines (Naderzhnost' i tekhniko-ekonomicheskie kharakteristiki aviatsionnykh dvigatelei). K. P. Alekseev. Moscow, Izdatel'stvo Transport, 1980. 103 p. 18refs. In Russian. The book deals with methods of evaluating the operational A81-10272 Acoustic structures. C. E. Kimball (Boeing reliability and the safety, regularity, and economy characteristics of Military Airplane Co., Wichita, Kan.). (American Welding Society aircraft engines. A function defining the generalized reliability index and Welding Research Council, International Brazing Conference, of an engine is introduced, and a formula for calculating this index is 11th, Los Angeles, Calif., Apr. 15-17, 1980.) Welding Journal, vol. proposed. The influence of the operational conditions on the 59, Oct. 1980, p. 26-30. reliability, safety, and economy of an engine is examined, and The paper discusses a titanium brazing method for producing maintenance trends for modern transport-aircraft engines are dis- honeycomb acoustic cylinders. Brazing was performed with a 3003 cussed. V.P. aluminum filler metal, using an improved vacuum pumping system and argon purging. A mandrel, a rotisserie door assembly, and a brazing retort were placed into an electric furnace which heated the A81-10096 Design of airfoils in incompressible viscous brazement to 1255 F held for a minimum of 2 min during the flows by numerical optimization. H. N. V. Dutt and A. K. Sreekanth brazing operation. A 36 in. diameter cylinder was brazed within (Indian Institute of Technology, Madras, India). Computer Methods tolerances of + or - 0.010 in.; the brazements show weight advantages in Applied Mechanics and Engineering, vol. 23, Sept. 1980, p. from 20 to 50% over conventional materials. AT. 355-368. lOrefs. A method is outlined for the design of airfoils in incompressible viscous flows by numerical optimization wherein a reduced number A81-10355 Aspect ratio variability in part-through crack of design coordinates are used to define the airfoil shape. The life analysis. R. J. Engle, Jr. (USAF, Flight Dynamics Laboratory, optimization problem is formulated as a nongradient search in a Wright-Patterson AFB, Ohio). In: Part-through crack fatigue life finite constrained parameter space. The approach is to define the prediction. Philadelphia, Pa., American Society airfoil as a linear combination of basic shapes which may be for Testing and Materials, 1979, p. 74-88. 7 refs. analytically or numerically defined. The design problem is to Various analytical solutions currently used in part-through crack determine the participation of each of these basic shapes in defining life prediction are reviewed, including those which account for shape the optimum airfoil. The aerodynamic analysis program is specially change effects as well as constant shape solutions. Comparisons of developed to fit the requirements of the optimization program and is these solutions with constant amplitude experimental data are based on the vortex singularity method for inviscid flow analysis and examined. Results are presented for three different materials: the momentum integral method for boundary layer analysis. Four 2219-T851 aluminum, 6AI-4-V (beta annealed) titanium, and 9Ni- examples have been worked out to illustrate the proposed design 4Co-0.20C steel. (Author) method. In these, modifications to four different airfoil geometries are made to achieve either a minimum drag coefficient or a minimum pitching moment coefficient under prescribed constraints. The A81-10362 Part-through crack problems in aircraft struc- results show that significant drag or pitching moment reduction is tures. J. L. Rudd, H. A. Wood (USAF, Flight Dynamics Laboratory, possible through shape manipulation alone. (Author) Wright-Patterson AFB, Ohio), and T. M. Hsu (Lockheed-Georgia Co., Marietta, Ga.). In: Part-through crack fatigue life prediction. A81-10162 Comparative performance of two centrifugal Philadelphia, Pa., American Society for Testing and fan impellers differing in blade section. M. R. Shaalan and A. M. Materials. 1979. p. 168-194. 15 refs. Shibl (Riyadh, University, Riyadh, Saudi Arabia). In: Heat Transfer The most common types of flaws which exist in aircraft and Fluid Mechanics Institute, Meeting, 27th, Los Angeles, Calif., structures and the test data and analytical criteria needed to predict June 23-25, 1980, Proceedings. Stanford, Calif., their growth are discussed. A number of special analytical and Stanford University Press, 1980, p. 53-63. 6 refs. structural considerations are discussed such as small flaws, cold- Two centrifugal fan impellers, each with backward-curved worked holes, plasticity effects, failure criteria, and multiple flaw blading and constant width, have been tested for overall and for sites. The analytical crack growth and residual strength requirements detailed performance. The two impellers were designed for the same which must be met as well as the initial flaw sizes and shapes which conditions but differ only in the blade section configuration. In one must be assumed in the Air Force damage tolerance design A81 10439

requirements (MIL-A-83444) are presented. Recently developed described. Attention is given to two performance concepts which will stress intensity factor solutions for quarter elliptical corner cracks be studied: one for a European-based figher and the other for a emanating from various types of fastener holes are presented. Middle-East-based fighter. It is shown that emphasis in NASA's Predictions using these current solutions are correlated with other 'supercruise' fighter study will be to obtain industry concepts of approximate solutions as well as experimental test data. (Author) tactical aircraft possessing two or three times the supersonic cruise ranges of existing fighters, allowing the supercruise vehicles to fly efficiently most, if not all, of their takeoff-to-landing mission profiles A81-10439 ff Forced vibrations of a nonlinear system ex- at about Mach 2. Consideration is given to the primary new cited by a centrifugal oscillator with a sloping engine characteristic technologies to be evaluated, such as variable cycle engines and dry (O vynuzhdennykh kolebaniiakh nelineinoi sistemy, vozbuzhdaemoi turbojets, low-aspect-ratio arrow wings, composite materials, and tsentrobezhnym vibratorom, imeiushchim pologuiu kharakteristiku active controls with digital avionics. M.E.P. dvigatelia). N. P. Plakhtienko and N. V. Lysak (Akademiia Nauk Ukrainskoi SSR, Institut Mekhaniki, Kiev, Ukrainian SSR). Priklad- naia Mekhanika, vol. 16, Sept 1980, p. 110-114. 7 refs. In Russian. A81-10632 * The performance of slotted blades in cascade. Centrifugal oscillators, of the type used in dynamic analyses of H. Matsumiya (Mechanical Engineering Laboratory, Sakura, Ibaraki, mechanical systems, are powered by low-power engines. Mounted on Japan) and M. Shirakura (Tokyo, University, Tokyo, Japan). JSME, elastic structures, such engines may give rise to interactions between Bulletin, vol. 23, Aug. 1980, p. 1320-1334. 18 refs. the translational and rotational motions of the vibrator elements, A precise solution of the problem of determining a two- which lead to unsteady mode shapes of vibration and hinder dimensional potential flow of incompressible fluid around arbitrary transition through resonance. In the present paper, these and some shaped slotted blades in cascade was obtained by conformal other associated phenomena are analyzed. V.P. mapping. This solution facilitates precise evaluation of the extremely complicated calculations around the slot even if the slot and the A81-10468 •; Brushless cryogenic ac motors (Beskontaktnye main aerofoil are approximated close to each other. Utilization of a kriogennye etektricheskie mashiny peremennogo toka). Z. K. Sika modified Milne-Thomson's circle theorem together with Milne- (Akademiia Nauk Latviiskoi SSR, Fiziko-Energeticheskii Institut, Thomson's circle theorem, as a means of analysis, gives simple Riga, Latvian SSR). Akademiia Nauk Latviiskoi SSR, Izvestiia, Seriia expressions of mapping function and complex potential function, Fizicheskikh i Tekhnicheskikh Nauk, no. 4, 1980, p. 68-79. 26 refs. suitable for electronic computer calculations. Wind tunnel tests, with In Russian. comparison between slotted and unslotted cascades, were also Basic types of brushless cryogenic equipment and their classifi- conducted. Slight slot effect was obtained in both outer regions of cation system are presented. Development of motors is described, flow inlet angle. However, in the middle region of inlet angle, slot including rotor designs without windings, ferromagnetic rotors effect was insufficient due to the divergent shape of slot employed. without windings, and a cascade type cryogenic machine with a (Author) synchronous motor with windings. A.T.

A81-10633 ft Discrete frequency noise due to irregularity in A81-10474 H The design of blowing-cooled aircraft electrical blade row of axial fan rotor. T. Fukano, Y. Kodama, and Y. machines (Voprosy konstruktsii produvaemykh aviatsionnykh elek- Takamatsu (Kyushu University, Fukuoka, Japan). JSME, Bulletin, tricheskikh mashin). V. I. Naumenko, 0. G. Klochkov, and V. V. vol. 23, Aug. 1980, p. 1335-1343. 12 refs. Bandurin (Akademiia Nauk Ukrainskoi SSR, Institut Elektrodina- It is experimentally made clear in this paper that discrete tones miki, Kiev, Ukrainian SSR). Tekhnicheskaia Elektrodinamika, July- appear in the frequency band lower than the blade passing frequency Aug. 1980, p. 81-87. In Russian. when a rotor has manufacturing errors of stagger angle, pitch, camber The current status of air-cooled aircraft electrical machines is or chord length, which result is at variance with the general reviewed. The possibility of reducing the weight and size of understanding that the frequency of discrete noise corresponds to air-cooled machines is discussed, with particular emphasis on the the blade passing frequency and its harmonics. The relations between design of cooling systems for synchronous ac-generators. B.J. the magnitude of the deviation of the blading parameter from a design value and the induced sound pressure level of discrete tone A81-10499 ft The aircraft in the stratosphere (L'avion dans and the resulting change of fluid dynamic characteristics of the fan la stratosphere). M. Nicolet. Academie Royale de Belgigue, Classe des are also examined. Analytic considerations of measured wave Sciences. Bulletin, vol. 65, no. 12. 1979, p. 681-686. In French. patterns of pressure fluctuation indicate that this type of discrete The effect of combustion gases from supersonic flights upon the noise originates in a distortion of the circumferential distribution of ozone layer has been a major concern since the discovery that skin mean flow rates through the rotor from the uniform distribution and cancer is induced by ultraviolet radiation. An equation for the the consequent circumferential variation of mean pressure level, photochemical equilibrium of oxygen within the ozone layer is arising from the unequal blade loading of each blade of a rotor due presented showing that several processes involving hydrogen, nitro- to the errors in manufacturing. (Author) gen, and halogen oxides are significant in the region's equilibrium. From 25 km and under, a positive effect of NO2 dissociation which A81-10708 H Application of the laser velocimetry technique provides oxygen atoms occurs more often than the direct dissocia- to Langley's 0.3-meter Cryogenic Wind Tunnel. L. R. Gartrell, P. B. tion of 02, while for the region above 25 km (above the maximum Goodrum, W. W. Hunter, Jr., and J. F. Meyers. Supersonic Tunnel concentration of ozone) the N02 dissociation is less significant than Association, Semiannual Meeting, 54th, New York, N.Y., Oct. 9, W, the photodissociation of 02. Therefore, it is believed that supersonic 1980, Paper. 33 p. 6 refs. flights, such as the Concorde, above 25 km could, in sufficient A limited series of laser velocimeter tests were conducted in the numbers, directly affect the equilibrium of the stratospheric ozone Langley 0.3-m Transonic Cryogenic Tunnel. The results demon- layer. However, flights below 25 km will not destroy the ozone, but strated that the laser velocimeter technique could be applied to the rather increase the production of the stratospheric ozone. A.C.W. facility to obtain velocity measurements over a 51-235 m/sec range with at least + or - 1% accuracy. No seeding material was injected during these tests to augment existing Mie scattering material. It is A81-10575 NASA presses fighter gains. C. Covault. Avia- postulated that the scattering material in these tests was liquid tion Week and Space Technology, vol. 113, Oct. 27, 1980, p. 16-18. nitrogen normally injected to control the tunnel conditions. Signal NASA planned contracts early next year on long-range, super- levels obtained during the tests indicated that the average paniculate sonic cruise aircraft in order to gain a new technology base are size was greater than desired, more than 1.0 micron in diameter. A81 10768

Tunnel vibrations were considered a potential problem before the Atlanta's new airport, to be opened in September 1980, will test but no detrimental effects on the optical system were noted. It is include a 500,000-sq ft two-level terminal linked underground to a concluded that the laser velocimeter technique is a viable method for satellite complex of four concourses and three runways; a fourth measuring velocity in the 0.3-m Transonic Cryogenic Tunnel. The runway is scheduled to be added in the early 1980s. Parking will most significant problem is the reduction and control of the size of accommodate 11,500 cars. The airport design features a column- existing scattering particulates. (Author) leveling system to compensate for unequal soils conditions, a unique split-complex plan dictated by the high passenger transfer rate, and the latest available people-mover system with moving sidewalk A81-10709 * # A numerical study of candidate transverse fuel redundancy. V.L. injector configurations in the Langley scramjet engine. J. P. Drummond (NASA, Langley Research Center, Hampton, Va.). Joint A81-10747 Fatigue damage mechanisms in composite Army-Navy-NASA-Air Force Interagency Propulsion Committee, materials - A review. W. W. Stinchcomb and K. L. Reifsnider Combustion Meeting, 17th, Hampton, Va., Sept. 22-26, 1980, Paper. (Virginia Polytechnic Institute and State University, Blacksburg, 27 p. 11 refs. Va.). In: Fatigue mechanisms. Philadelphia, Pa., A computer program has been developed that numerically solves American Society for Testing and Materials, 1979, p. 762-781; the two-dimensional Navier-Stokes and species equations near one or Discussion, p. 782-787. 57 refs. more transverse hydrogen fuel injectors in a scramjet engine. The A review is presented of the current knowledge of fatigue program currently computes the turbulent mixing and reaction of damage mechanisms in fiber-reinforced composite materials covering hydrogen fuel and air, and allows the study of separated regions of damage modes, their interactions, and effects on engineering proper- the flow immediately preceding and following the injectors. The ties. The damage state occurs by various combinations of fiber, complex shock-expansion structure produced by the injectors in this matrix, and interfacial processes; it was shown that damage is region of the engine can also be represented. Results are presented strongly dependent on the material, laminate configuration, geom- that describe the flow field near two opposing transverse fuel etry, stress state, load history, and environment. The mechanisms injectors and two opposing staged (multiple) injectors, and compari- which cause dispersed damage result in higher notch growth sons between the two configurations are made to assess their mixing resistance, while localized damage leads to shorter life and lower and flameholding qualities. (Author) residual strength. It was concluded that compression can cause local buckling and delamination, producing larger degradation than a A81-10711 * ri Flameholding characteristics of a swept-strut tensile stress of equal magnitude. A.T. H2 fuel-injector for scramjet applications.> G. B. Northam, C. A. Trexler, and C. R. McClinton (NASA, Langley Research Center, A81-10749 On understanding environment-enhanced fa- Hampton, Va.). Joint Army-Navy-NASA-Air Force Interagency tigue crack growth - A fundamental approach. R. P. Wei (Lehigh Propulsion Committee, Combustion Meeting, 17th, Hampton, Va., University, Bethlehem, Pa.). In: Fatigue mechanisms. Sept. 22-26, 1980, Paper. 20 p. 12 refs. Philadelphia, Pa., American Society for Testing and A series of direct-connect tests are conducted which simulate Materials, 1979, p. 816-831; Discussion, p. 831-840. 52 refs. the flow around the center swept-strut fuel-injector of a scramjet Contract No. N00014-75-C-0543. NR Project 036-097. engine module. The experimental geometry includes both perpen- A review of fundamentals of environment-enhanced fatigue dicular and parallel fuel injectors which are swept with respect to the crack growth is presented. Corrosion fatigue is taken into considera- upstream flow direction in a manner simulating the flow geometry in tion in aircraft and offshore structures, highway bridges, transmission the combustion region of the scramjet module. Seven different strut lines, and coal conversion systems. Fracture mechanics technology, injector geometries are evaluated for their performance, flamehold- modern surface analysis, and metallurgical techniques such as Auger ing, and inlet-combustor interaction characteristics. The most effi- electron spectroscopy and low energy electron diffraction analysis cient combustion process is exhibited by the configuration having made it possible to quantify environmental fatigue cracking. Types the deepest step with perpendicular injector orifices located 3.5 to of fatigue crack behavior and sequential processes involved in 4.5 step heights downstream from the step. However, long center- embrittlement by gaseous environments are discussed; crack growth body and staged injection configurations perform as equally well as rates in AISI 4340 steel in aqueous media are analyzed. A.T. the deep step configuration when evaluating only the amount of perpendicular fuel injection. Since the staged injection configuration exhibits the lowest ignition and flameholding limit, it is suggested A81-10767 Piloted simulation studies of helicopter agility. that the optimum injection configuration should incorporate a deep B. N. Tomlinson and G. D. Padfield (Royal Aircraft Establishment, step with staged injection in order to improve the low temperature Bedford, England). Vertica, vol. 4, no. 2-4, 1980, p. 79-106. 17 refs. autoignition-flameholding characteristics. A.L.W. The need for helicopters to operate close to the ground and near obstacles has prompted a critical look at design features which affect performance and handling qualities in this environment. Some A81-10718 Airfield pavement demonstration-validation experiments using a ground-based flight simulator have been con-, study. D. M. Arntzen (Department of Public Works, Chicago, III.), E. ducted to investigate this subject and to obtain data on helicopter J. Barenberg (Illinois, University, Urbana, III.), and R. J. Krause agility. These experiments required the development of a general (Wiss, Janney, Elstner and Associates, Inc., Northbrook, III.). ASCE, mathematical model capable of representing helicopter flight, includ- Transportation Engineering Journal, vol. 106, Nov. 1980, p. ing gross maneuvers, from hover to cruise and validation by 721-730. comparison with flight tests. An exacting low level flying course was An instrumentation and testing program is presented which has created on a model ground terrain and formed the primary task for been designed to provide realistic data for pavement designs and to the six pilots involved in the experiments. A set of rotors were validate results from a finite element program developed specifically represented which differed in blade flapping stiffness and inertia to analyze jointed concrete pavements. Preliminary results of design (Lock number). The paper describes these aspects and then goes on and validation tests are briefly discussed. V.L. to describe how the simulated helicopter was flown over the agility course with each rotor to investigate the effects of rotor design. Some of the theoretical consequences of these variations are outlined A81-10719 Atlanta's new central passenger terminal com- and the results of piloted flights in the simulator described. (Author) plex. J. F. Kortan (Stevens and Wilkinson Architects, Engineers, Planners, Inc., Atlanta, Ga.). (American Society of Civil Engineers, Annual Convention and Exposition, Atlanta, Ga., Oct 22-26, 1979.) A81 10768 Helicopter tail configurations to survive tail ASCE, Transportation Engineering Journal, vol. 106, Nov. 1980, rotor loss. A. Brocklehurst (Westland Helicopters, Ltd., Yeovil, p.765-774. Somerset, England) and P. Taylor (Southampton, University, South- A81-10769 ampton, England). Vertica, vol. 4, no. 2-4, 1980, p. 107-119. 5 refs. A four-lobe bearing 25.4 mm in diameter was tested with the Research supported by the Westland Helicopters. load vector 'on pad' and 'off pad'. Static pressures were measured on Recently the US Army have specified that a helicopter must be the center line of the bearing and these experimental data are capable of returning from its mission after suffering a tail rotor loss. compared with two sets of theoretical results. The half-Sommerfeld The helicopter should possess sufficient directional stability to fly at and Reynolds boundary conditions were each used in the theoretical the minimum power speed with a sideslip angle of not more than 20 predictions. Of particular significance is the fact that the experimen- deg. A simple theory, describing the yawing oscillation of a tal data correlate best with the half-Sommerfeld solution. Differences helicopter, has been applied to a typical helicopter in order to between the data and the theoretical solution of the order of 10-35% identify the stability implications on the aerodynamic design of and 15-100% are realized for the half-Sommerfeld and Reynolds meeting the above tail rotor loss criterion. The fin area required, for boundary conditions, respectively. Moreover, the trends of pressure a fin and single tail rotor configuration, to meet both the above versus rotational speed for the experimental data and the theoretical criterion and to ensure adequate lateral stability characteristics was solution are the same for the half-Sommerfeld condition but large even if camber and incidence were used. The same helicopter sometimes differ for the Reynolds condition. (Author) but with twin tail rotors and no fin was investigated. This configuration has additional advantages including the unique ability to land in confined places after the loss of a tail rotor. (Author) A81-10913 Investigation of lateral forces and moments in the case of asymmetric gas flows in nozzles. G. Z. Nikulin, L. V. A81-10769 The aerodynamic characteristics of some new Pchelkina, U. G. Pirumov, and G. S. Rosliakov. (Akademiia Nauk RAE blade sections, and their potential influence on rotor perfor- SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, vol. 15, Mar.-Apr. mance. P. G. Wilby (Royal Aircraft Establishment, Farnborough, 1980, p. 70-85.) Fluid Dynamics, vol. 15, no. 2, Sept. 1980, p. Hants., England). Vertica, vol. 4, no. 2-4, 1980, p. 121-133. 231-244. 19 refs. Translation. The values of maximum lift coefficient and pitching moment Three-dimensional supersonic nozzle flows are analyzed, using coefficient at zero lift, and the drag characteristics, are given for an approach which combines experimental studies with numerical several new RAE profiles and NACA 0012, as measured in steady calculations carried out by the small perturbation and finite- conditions. Results from oscillatory tests are then presented for RAE difference methods. Particular attention is given to lateral forces and 9647 (one of the new sections) and NACA 0012. These show that at moments, generated by asymmetries of the contour of conical or IVI = 0.3, the gain in maximum lift coefficient for the new section shaped nozzles. It is shown how the small perturbation method can relative to NACA 0012 is considerably greater in dynamic conditions be used to greatly simplify the analysis without impairing accuracy. than in steady conditions. Dynamic tests are seen to be necessary for V.P. the full assessment of new profiles. The effect of section characteris- tics on rotor performance is evaluated by means of a rotor performance calculation that incorporates a model of dynamic stall; A81-10916 Flow past a slender profile in a channel with the predicted onset of blade stall providing a criterion for deter- permeable walls. IM. A. Marevtseva. (Akademiia Nauk SSSft, Izvestiia, mining the rotor thrust limits. The new sections are seen to offer a Mekhanika Zhidkosti i Gaza, vol. 15, Mar.-Apr. 1980, p. 111-117.) 35% increase in rotor thrust capability, relative to rotors with the Fluid Dynamics, vol. 15, no. 2, Sept. 1980, p. 265-270. 11 refs. NACA 0012 section. (Author) Translation. An exact solution is obtained to the boundary interference A81-10770 Experimental application of a vibration reduc- problem for the potential flow of an ideal incompressible fluid past a tion technique. W. R. Walker (Royal Aircraft Establishment, Struc- slender wing profile in a channel with slit-shaped perforations tures Dept., rarnborough, Hants., England). Vertica, vol. 4, no. 2-4, transverse to the flow. The degree of perforation of the upper and 1980, p. 135-146. lower walls is assumed to be identical. The wind tunnel is assumed to Attention is drawn to a method of reducing the vibration at be situated in a constant-pressure chamber, the pressure being equal specific points of a structure by means of a relatively simple to that of the unperturbed flow. Use is made of the condition of experimental technique. The method relies on the measurement of proportionality of the longitudinal and normal perturbed-velocity transfer functions, which are used to predict changes in vibratory components. It is shown that under such conditions, transverse response as structural parameters are altered. Of particular concern in ventilation leads to an increase in wall interference. V.P. this paper are the practical difficulties involved in ensuring a reasonable level of accuracy in the response predictions. This is A81-10919 Asymmetric flow of subsonic and sonic jets examined by applying the technique to a helicopter tail cone. over an infinite wedge. N. A. Podsypanina and E. G. Shifrin. (Author) I Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, vol. 15, Mar.-Apr. 1980, p. 137-141.) Fluid Dynamics, vol. 15, no. 2, Sept. 1980, p. 286-289. 6 refs. Translation. A81-10839 An analytical method to calculate misalign- the analysis deals with the subsonic or transonic flow past an ment in the journal bearing of a planetary gear system. P. K. Das and infinite wedge, in the case where the critical line of flow branches at S. S. Gupta (Pratt and Whitney Aircraft of Canada, Ltd., Longueuil, the apex of the wedge. A flow of this type can arise only at a quite Quebec, Canada). Wear, vol. 61, June 2, 1980, p. 143-156. 7 refs. specific relationship of the geometrical parameters. The problem is A computerized method of calculating misalignments in hydro- solved in the hodograph plane by a numerical method proposed by dynamic bearings of a planetary gearbox was developed. The Podsypanina (1975) for profiling Laval nozzles. V.P. program was applied to the misalignment in the bearing of a reduction gearbox in a 850 hp turboprop engine. Carrier rotational stiffness had the strongest effect on the misalignment; the rotational A81 10920 Two methods for calculating the load on the stiffnesses of the ring and the sun gears have a limited influence, but surface of a slender body executing axisymmetric vibrations in a the misalignment can be reduced by flexible ring and sun gears. The sonic gas flow. V. lu. Ol'shanskii. (Akademiia Nauk SSSR, Izvestiia, effects of misalignment on planet bearings was not significant until Mekhanika Zhidkosti i Gaza, vol. 15, Mar.-Apr. 1980, p. 151-154.) the second stage, during which the peak pressure increased by 85% Fluid Dynamics, vol. 15, no. 2, Sept. 1980, p. 300-302. Translation. and the minimum film thickness decreased by 53%. A.T. In the present paper, the low-frequency axisymmetric vibrations of the surface of a slender body situated in sonic flow are analyzed A81-10840 An experimental and theoretical investigation under the assumption of a linear velocity distribution along the of pressures in four-lobe bearings. R. D. Flack, M. E. Leader, and P. body. A nonlinear equation with variable coefficients derived for the E. Allaire (Virginia, University, Charlottesville, Va.). Wear, vol. 61, nonstationary portion of the velocity potential, is solved, first, by June 16, 1980, p. 233-242. 13 refs. Research'supported by the separation of variables and then by the method of superposition of Engineering Foundation; Contract No. EF-76-5-01-2479. sources. The obtained expressions for the nonstationary portion of A81-11338 the velocity potential are shown to be well suited for calculating College of Technology, Paisley. Scotland). Applied Scientific Re- unsteady surface loads for a slender body of revolution in a sonic gas search, vol. 36, no. 2, 1980, p. 93-108. 25 refs. flow. V.P. An experimental investigation has been completed to study several methods of avoiding the jet screech phenomenon due to air A81-11157 High-density avionic power supply. K. K. jet impingement on solid boundaries. Measurements were completed Hedel (General Electric Co., Aircraft Equipment Oiv., Utica, N.Y.). in the Mach number region of M = 0.5 using a 25 mm diameter IEEE Transactions on Aerospace and Electronic Systems, vol. 16, nozzle with the air jet impinging on flat, concave and convex Sept. 1980, p. 615-619. boundaries. Sound pressure levels were recorded in the plane of the The development of a standard 3/4 ATR 5-V, 60-A power nozzle outlet at a distance of 1.46 m from the jet axis. With the air supply is described. This novel converter circuit allows packaging a jet impinging on the flat board normal to its surface a maximum 300-W logic supply at a density of 5.7 W/cu in., thereby taking only sound pressure occurred at a spacing of approximately two nozzle two slots or 10% of the available volume. BJ. diameters producing a distinct screech at a sound level of 20 dB above that of the free jet. Three methods of preventing this screech A81-11158 Radar target detection and map-matching algo- were studied1. (1) inserting disturbances into the shear layer at the rithm studies. L. M. Novak (MIT, Lexington, Mass.). IEEE Trans- nozzle exit; (2) changing the geometry of the boundary shape to actions on Aerospace and Electronic Systems, vol. 16, Sept. 1980, p. improve the jet stability in the impingement region; and (3) 620-625. 11 refs. USAF-Army-DARPA-sponsored research. introducing disturbances at the stagnation region which had the Results of a study of adaptive threshold target detection and effect of displacing the distinct screech to another frequency range. map-matching algorithms are presented. Log threshold processing is (Author) shown to be preferred over linear threshold processing when the clutter data surrounding the target cell is contaminated by other targets, decoy corner reflectors, or bright clutter cells. Whereas A81-11320 # Head-up displays. Ill (Elektroniczno-optyczne previous studies have resorted to extensive Monte-Carlo simulations systemy wskazan projekcyjnych /HUD/. III). E. Malinski (Instytut of log threshold algorithms, the results were obtained using a novel Lotnictwa, Warsaw, Poland). Technika Lotnicza i Astronautyczna, analytical approach based upon Parseval's theorem. (Author) vol. 35, Aug.-Sept. 1980, p. 17-21. 10 refs. In Polish. The development and applications of head-up displays .are reviewed with emphasis on operational functions for typical ground A81-11242 H The 767's flight-management system - A new and air attack missions. Attention is given to systems with electronic generation of airborne avionics. R. A. Peal (Boeing Commercial mixing of symbols and video images which project the terrain or Airplane Co., Renton, Wash.). Astronautics and Aeronautics, vol. 18, external surroundings and the symbolic data display on a common Nov. 1980, p. 37-39. screen. B.J. The procurement specifications for the 767 avionics were necessarily different from those for previous aircraft because the 767 A81-11321 If Reduction of energy consumption in the flight management system uses not a single off-the-shelf item of vibrational shot peening of axial compressor vanes (Obnizenie equipment. Therefore this digital technology system has presented a energochlonnosci wibrokulowania lopatek sprezarki osiowej). M. great challenge to the design product engineers guiding it toward Marciniak (Warszawa, Politechnika, Warsaw, Poland). Technika Lot- certification. This paper describes such developments as the new nicza i Astronautyczna, vol. 35, Aug.-Sept. 1980, p. 23, 24. In interface data base, software configuration control, the applied Polish. technology, the primary flight instruments, and the flight- A system for vibrational shot peening is described and the shot management digital computer system. B.J. peening process is analyzed. A method for reducing the energy consumption in the vibrational shot peening of axial compressor A81-11244 # F/A-18's landing, launch and recovery system. vanes is presented. B.J. D. L. Bourisaw and C. F. Brandenberg (McDonnell Aircraft Co., St. Louis, Mo.). Astronautics and Aeronautics, vol. 18, Nov. 1980, p, 48-52, 63. A81-11322 # Methods of fuel conservation in civil aviation. The F/A-18 Hornet is a carrier-based fighter and attack aircraft I (Metody oszczedzania paliwa w lotnictwie komunikacyjnym. I). M. designed to eventually replace both the F-4 and the A-7 for the U.S. Kawczynski. Technika Lotnicza i Astronautyczna, vol. 35, Aug.- Navy and Marines. It was determined that the landing gear delivery Sept. 1980, p. 36-38. In Polish. leadtimes would be among the longest for any of the procured Several methods for saving fuel in civil aviation are described. equipment. Furthermore, design definition efforts for a carrier- These methods include modifications in aircraft design, operational suitable landing gear that would satisfy the many operational, methods, and aircraft balancing during flight. B.J. structural, and geometric requirements, while still fitting into the small dense airframe, added to the already strained schedule span A81-11324 H Impact damage of aircraft gas turbine engines time. This paper describes the way in which these procurement with axial compressors (Uszkodzenie udarowe w lotniczych silnikach difficulties were overcome. B.J. turbinowych ze sprezarka osiowa). M. Ostapkowicz. Technika Lotnicza i Astronautyczna, vol. 35, Aug.-Sept. 1980, p. 45-47. In A81-11245 # Add fluorescent minitufts to the aerodynami- Polish. cist's bag of tricks. J. P. Crowder (Boeing Commercial Airplane Co., Data on the foreign object damage (FOD) of axial compressors Renton, Wash.). Astronautics and Aeronautics, vol. 18, Nov. 1980, p. of gas turbine engines are reviewed. Methods for improving the FOD 54-56. reliability of axial compressors are discussed. B.J. Recent experience has demonstrated the feasibility of routinely using fluorescent minitufts to visualize low-speed and transonic A81-11338 Design and fabrication of stabilized organic flows. This extension of the traditional yarn technique permits large matrix composites. J. A. Suarez (Grumman Aerospace Corp., numbers of minitufts to be applied to the surfaces of a wind tunnel Bethpage, N.Y.). (American Ceramic Society, Annual Conferences on model, yet produces negligible interference with the flow. Extremely Composites and Advanced Materials, 2nd and 3rd, Cocoa Beach, Fla., thin fluorescent nylon monofilament (diameter as small as 0.0007 Jan. 22-25, 1978 and Jan. 21-24, 1979.1 Ceramic Engineering and in.) forms the tufts. Small drops of lacquer-type adhesive attach the Science Proceedings, vol. 1, July-Aug. 1980, p. 370-385. Contract tufts to the model. Fluorescence photography records the visual No. F33615-76-C-5311. data. B.J. Integrally-stiffened graphite/epoxy compression panels represen- tative of secondary aircraft structure were designed and fabricated. A A81-11302 An experimental investigation of jet screech thermal pressure forming process was developed to manufacture by air jet impingement on solid boundaries. A. M. Petrie (Paisley various panels which were designed for compression loading and A81-11339

analyzed using existing analytical techniques. A structural efficiency induced drag leads to the result that a twisted swept-forward wing is comparison of the integrally-stiffened graphite/epoxy compression equivalent to a twisted swept-back wing with an enlarged aspect- panels and a baseline sandwich panel with graphite/epoxy skins and ratio. (Author) aluminum honeycomb core was performed. (Author) A81-11603 The analysis of fatigue failures. C. J. Peel and A81-11339 Design and test of a graphite-epoxy composite P. J. E. Forsyth (Royal Aircraft Establishment, Farnborough, Hants., A-10 slat. J. Clarke (Fairchild Republic Co., Farmingdale, N.Y.). England). In: International Council of the Aeronautical Sciences, (American Ceramic Society, Annual Conferences on Composites and Congress, 12th, Munich, West Germany, October 12-17, 1980, Advanced Materials, 2nd and 3rd, Cocoa Beach, Fla., Jan. 22-25, Proceedings. New York, American Institute of 1978 and Jan. 21-24, 1979.1 Ceramic Engineering and Science Aeronautics and Astronautics, Inc., 1980, p. 18-29. 31 refs. Proceedings, vol. 1, July-Aug. 1980, p. 386-397. The post failure analysis of fatigue cracking has developed A composite slat has been developed which has a constant cross during the last decade into a quantitative technique vital to both section and consists of a lightweight full-depth corrosion-resistant aircraft structural testing and accident investigations. The quantita- aluminum honeycomb core covered with AS/3501-5 graphite epoxy tive techniques used retrospectively to determine fatigue crack skins. Design policy, materials and process development, and growth rates are explained and compared with complementary programs of structural testing and nondestructive evaluation are predictions based upon linear elastic fracture mechanics taking reviewed. It is shown that advance composites can be cost competi- account of the limitations to both techniques. Examples include tive with metals and used on aircraft to achieve low weight and low detailed analyses of fatigue cracking in undercarriages during cost if applied carefully. V.L. structural testing, cracking from fastener holes in the wing of a military aircraft undergoing testing and the in-service failure of the A81-11441 The aerodynamics of pure subsonic flow /4th tail-plane of a transport aircraft. The analyses consider in particular revised edition/ (Aerodynamik der reinen Unterschallstromung /4th the causes of premature and unexpected fatigue failures with revised edition/). F. Dubs. Basel, Birkhauser Verlag (Flugtechnische reference to current airworthiness philosophies. (Author) Reihe. Volume 1), 1979. 323 p. 131 refs. In German. $15.30. Fundamentals in the aerodynamics of pure subsonic flow are A81-11604 * Numerical optimization - An assessment of.its investigated. Aircraft wing design is examined with emphasis on role in transport aircraft aerodynamic design through a case study. achieving lift with a minimum of resistance. The production of wing M. E. Lores, P. R. Smith (Lockheed-Georgia Co., Marietta, Ga.), and profiles is considered including the determination of profiles based R. A. Large (USAF, Flight Dynamics Laboratory, Wright-Patterson on potential pressure distribution and boundary layer theory. The AFB, Ohio). In: International Council of the Aeronautical Sciences, function of the propeller in propulsion and as an aerodynamic brake Congress, 12th, Munich, West Germany, October 12-17, 1980, is discussed along with the use of tow channels and wind channels in Proceedings. New York, American Institute of aerodynamics investigations. R.C. Aeronautics and Astronautics, Inc., 1980, p. 41-52. 22 refs. NASA-supported research; Contract No. F33615-78-C-3014. A81-11475 Subsequent proof of damage tolerance for a An efficient transonic wing design procedure based upon landing gear component after numerous takeoffs and landings numerical optimization together with three-dimensional transonic (IMachtraglicher Schadenstoleranzbeweis eines Flugzeug- methods has been developed and used to design an advanced Fahrwerksteiles nach zahlreichen Starts und Landungen). E. A. B. de transport wing. The method development included an examination Graaf, P. de Rijk (National Luchtvaartlaboratorium, Emmeloord, of the use of both full potential and extended small disturbance Netherlands), and G. F. J. A. van Gestel (Van Doorne's Automobiel- analysis codes and demonstrated that the former formulation was fabriek, Eindhoven, Netherlands). (Deutsche Gesellschaft fur Zer- more reliable. In either case, the design procedure is economical and storungsfreie Priifung, Jahrestagung, Gottingen, West Germany, May easy to use. Design verification in a unique semi-span test arrange- 12-14, 1980.) Materialprufung, vol. 22, Sept. 1980, p. 369-372. In ment demonstrated that the design method produced a wing which German. satisfied the study design requirements. However, aeroelastic defor- Design philosophies based on the safe-life, fail-safety, and mation of the wing occurred during the wind tunnel test. The damage-tolerance concepts are examined, along with the respective computational methods used in the design procedure were employed inspection intervals and regulations. Four different nondestructive to assess the effect of the aeroelastic deformation. The paper tests with a landing gear component prepared on AISI 4340, concludes with an evaluation of the design procedure and recommen- low-alloy high-strength steels, are described, which revealed the dation for its improvement. (Author) 'subsequent' damage tolerance of the component, in the sense that by the time the tolerance proof became available, the component had been replaced by a new one. V.P. A81-11605 The relevance of the Flex-Hub Prop-Fan for fuel-efficient airliners. K. W. Sambell. In: International Council of the Aeronautical Sciences, Congress, 12th, Munich, West Germany, A81-11602 How to improve the performance of transport October 12-17, 1980, Proceedings. New York, aircraft by variation of wing aspect-ratio and twist /12th Daniel and American Institute of Aeronautics and Astronautics, Inc., 1980, p. Florence Guggenheim International Memorial Lecture/. E. 53-62. 11 refs. Truckenbrodt (Miinchen, Technische Universitat, Munich, West The Flex-Hub Prop-Fan, a variant of the rigid-hub prop-fan, is Germany). In: International Council of the Aeronautical Sciences, predicted to have improved performance and control characteristics Congress, 12th, Munich, West Germany, October 12-17, 1980, for twin-engine M 0.8 airliners. In the one-engine inoperative case at Proceedings. New York, American Institute of take-off, the Flex-Hub Prop-Fan will have a more even thrust Aeronautics and Astronautics, Inc., 1980, p. 1-17. 15 refs. distribution in its tip-path plane and will develop higher propulsive The lecture deals with the influence of the wing aspect-ratio and efficiency and greater propulsive lift. A preliminary analysis, with a twist on the induced drag of transport aircraft. Whereas the fixed engine core-size, compares payload capability of three aircraft: taper-ratio and the sweep of the wing are given, the aspect-ratio and powered by fan-jets, rigid-hub prop-fans, and flex-hub prop-fans. The twist are the two variable parameters. With respect to the critical respective design gross weights were 300,000 Ibs., 320,000 Ibs., and transonic Mach-number a swept-forward wing has similar qualities as 342,000 Ibs. At a range of 2,000 n.m., the passengers carried were a swept-back wing, both at the same angle of sweep. The spanwise 232, 255 and 280. The fuel economy (seat-statute miles per U.S. lift distribution will be discussed with regard to two aspects: elliptic gallon) was 68.7, 76.5 and 79.5. Other unique characteristics of the lift distribution for the design lift coefficient and lift distribution for Flex-Hub Prop-Fan are discussed, including cross-wind control, blade high lift coefficient in the vicinity of stalling. The investigation of de-icing, and wing trailing-vortex interaction. (Author) A81 11613

A81-11606 New concepts for design of fully-optimized defined in the design synthesis. Applications of this multivariate configurations for future supersonic aircraft A. Nastase (Aachen, optimization method are described to illustrate the effects of varying Rheinisch-Westfalische Technische Hochschule, Aachen, West Ger- performance requirements and incorporating technological advances many). In: International Council of the Aeronautical Sciences, in the design. The dependency of the optimum configuration on the Congress, 12th, Munich, West Germany. October 12-17, 1980, particular requirements specified and the need for a thorough Proceedings. New York, American Institute of investigation of the characteristics of the mathematical model that Aeronautics and Astronautics, Inc., 1980, p. 63-74. 22 refs. lead to the optimum configuration are emphasized. It is concluded The drag of a supersonic aircraft can be decreased by replacing that effort should be made to increase the acceptability of the its conventional wing with a design whose geometrical characteristics multivariate optimization techniques in the pre-feasibility stage of are optimized for minimum drag. A graphic-analytical method for design as it offers a potentially valuable guide in selecting configura- solving a variational problem for the drag-functional which contains tions for more detailed consideration. (Author) the wing surface as the unknown and the shape of the wing projection as the unknown boundary is presented. The method was A81-11610 ORAPO - Computer-assisted design and manu- used for designing of an optimized delta wing model and the facturing system. F. Bernard (Avions Marcel Dassault-Breguet Avia- construction of the wing for the Concorde aircraft A.T. tion, Saint-Cloud, Hauts-de-Seine, France). In: International Council of the Aeronautical Sciences, Congress, 12th, Munich, West Ger- A81-11607 Possibilities for the valuation of different many, October 12-17, 1980, Proceedings. New combat aircraft configurations with respect to flight mechanics. P. York, American Institute of Aeronautics and Astronautics, Inc., Mangold and H. Wiinnenberg (Dornier GmbH, Friedrichshafen, West 1980, p. 112-122. Germany). In: International Council of the Aeronautical Sciences, The 'DRAPO' design and manufacturing system uses computer- Congress, 12th, Munich, West Germany, October 12-17. 1980, ized aerodynamic and structural analysis with teleprocessing of Proceedings. New York, American Institute of aircraft component geometries to manufacturing plants. Manual Aeronautics and Astronautics, Inc., 1980, p. 75-81. 5 refs. engineering drawing has been replaced by direct design of frames, Evaluation of various configurations during early design stages wings, and the ribs in three dimensions using an interactive graphic of aircraft is discussed. The weighted sum of all single valuations console. The graphic console is also used to describe the paths of produces the most promising configuration, which is based on machining equipment and monitor their accuracy; applications in criteria for control about the pitch-, roll-, and yaw axis, stability designing the main frame of a military aircraft and its electrical behavior, center of gravity range, and sensitivity to gusts. The critical circuitry are presented. A.T. spin tendency is important in the high angle of attack flight regime of modern fighter aircraft; post-stall control is achieved by enlarge- ment of the horizontal tail or by variations of the center of gravity A81-11611 Computer aided compilation of an electrical position. It is concluded that the summarizing process described here drawing file. j.-P. Pauzat (Societe Nationale Industrielle Aerospatiale, produces a nearly objective numerical design. A.T. Blagnac, Haute-Garonne, France). In: International Council of the Aeronautical Sciences, Congress, 12th, Munich, West Germany, October 12-17, 1980, Proceedings. New York, A81-11608 Advanced combat aircraft wing design. B. American Institute of Aeronautics and Astronautics, Inc., 1980, p. Probert (British Aerospace Aircraft Group, Preston, Lanes., England) 123-128. and D. R. Holt (British Aerospace, Aircraft Group, Brough, A general computer design system called GICE is being set up to Humberside, England). In: International Council of the Aeronautical draw and manage all the documents of an aircraft electrical drawing Sciences, Congress, 12th. Munich, West Germany, October 12-17, file. This system enables optimization of the design-to-cost of all the 1980, Proceedings, New York, American Insti- definitions of this drawing file, from the conception of the electrical tute of Aeronautics and Astronautics, Inc., 1980, p. 82-96. Research data in the design office to its utilization by the production and supported by the Ministry of Defence. product support departments. B.J. The paper considers various means of achieving a typical set of design requirements for a combat aircraft, ranging from variable sweep options to a fixed wing configuration. It is shown that with A81-11612 * Advanced fuel system technology for utilizing the aid of transonic theoretical methods designs can be achieved broadened property aircraft fuels. G. M. Reck (NASA, Lewis Research Center, Cleveland, Ohio). In: International Council of the which give good (L/D) values over a wide range of Mach number and Aeronautical Sciences, Congress, 12th, Munich, West Germany, lift coefficients. Use of variable sweep is a powerful means of achieving a wide range of requirements whilst use of variable camber October 12-17, 1980, Proceedings. New York, devices has a strong influence on reconciling, often conflicting, American Institute of Aeronautics and Astronautics, Inc., 1980, p. geometric requirements especially when aeroelastic effects are taken 129-143. 28 refs. into account. Further improvements at high lift can be achieved with Factors which will determine the future supply and cost of slotted devices. High incidence penetration can be aided with the use aviation turbine fuels are discussed. The most significant fuel of strakes and these can be designed to have only a small drag properties of volatility, fluidity, composition, and thermal stability penalty at low lift coefficients. These points are illustrated by are discussed along with the boiling ranges of gasoline, naphtha jet describing the design of a variable sweep and fixed wing configura- fuels, kerosene, and diesel oil. Tests were made to simulate the low tion and results are described and discussed for both. (Author) temperature of an aircraft fuel tank to determine fuel tank temperatures for a 9100-km flight with and without fuel heating; the A81-11609 Some experiences with numerical optimisation effect of N content in oil-shale derived fuels on the Jet Fuel Thermal in aircraft specification and preliminary design studies. 0. A. Lovell Oxidation Tester breakpoint temperature was measured. Finally, (Royal Aircraft Establishment, Aerodynamics Dept., Farnborough, compatibility of non-metallic gaskets, sealants, and coatings with Hants., England). In: International Council of the Aeronautical increased aromatic content jet fuels was examined. A.T. Sciences, Congress, 12th, Munich, West Germany, October 12-17, 1980, Proceedings. New York, American Insti- A81-11613 Calculation of the flow field around engine- tute of Aeronautics and Astronautics, Inc., 1980, p. 97-111. 20 refs. wing-configurations. C. Haberland, G. Sauer (Berlin Technische The development of preliminary design methods to find the best Universitat, Berlin, West Germany), and E. Code (Gebr. Sulzer AG, configuration is discussed historically. A method for synthesizing a Zurich, Switzerland). In: International Council of the Aeronautical combat aircraft using a large number of design variables, and the Sciences, Congress, 12th, Munich, West Germany, October 12-17, associated analysis procedures, is summarized. This is combined with 1980, Proceedings. New York, American Insti- a numerical optimization method to obtain the minimum value of a tute of Aeronautics and Astronautics, Inc., 1980, p. 144-157. 35 nonlinear objective function subject to many nonlinear constraints refs. Research supported by the Deutsche Forschungsgemeinschaft. A81-11614

A panel method for the determination of the flow field around were found for a given stagnation pressure; the frequencies were not high bypass engines without limitations with respect to geometry, simultaneously present, which indicated an instability in the jet speed and mass flow rate is presented. Within this computation structure. B.J. method any flow inside the engine contour causing an error in mass flow rate and pressure distribution has been eliminated by developing A81-11617 The all-electric aircraft. D. K. Bird (USAF a mathematical model which represents the real physical flow by Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio). In: introducing a controlled distribution of singularities on the surface International Council of the Aeronautical Sciences, Congress, 12th, combined with suitable boundary conditions. Hence, this modified Munich, West Germany, October 12-17, 1980, Proceedings. panel method allows to provide an arbitrary mass flow rate New York, American Institute of Aeronautics and independent of the onset flow velocity satisfying the continuity of Astronautics, Inc., 1980, p. 189-201. 21 refs. the inlet flow. Checking the computation model for several axisym- A review of information on all-electrical aircraft is presented. metric inlets and engine contours, it turns out that the calculated Combining power-by-wire (electrical actuation) and fly-by-wire velocities are physically accurate in the far field as well as near the (electrical signal transmission) will unify the secondary power and engine and compare well with experimental results. To determine the the flight control systems under a single electrical medium. This will spanwise and chordwise interference effects for typical engine eliminate the troublesome hydraulic to electrical interface and positions the axisymmetric engine model as a first step is combined problems of hydraulic fluid equipment: electromechanical actuation with an infinite unswept wing. (Author) is achieved by using rare earth samarium-cobalt permanent magnets. A.T. A81-11614 Engine air intake design support by use of computational methods and comparison of theoretically derived A81-11618 Flying qualities criteria for advanced control technology transports. H. A. Mooij (Nationaal Lucht- en Ruimte- pressure distributions with experimental data A. Eberle and D. M. vaartlaboratorium, Amsterdam, Netherlands). In: International Schmitz (Messerschmitt-Bolkow-Blohm GmbH, Munich, West Ger- Council of the Aeronautical Sciences, Congress, 12th, Munich, West many). In: International Council of the Aeronautical Sciences, Germany, October 12-17, 1980, Proceedings. Congress, 12th, Munich, West Germany, October 12-17, 1980, New York, American Institute of Aeronautics and Astronautics, Inc., Proceedings. New York, American Institute of 1980, p. 202-208. 8 refs. Aeronautics and Astronautics, Inc., 1980, p. 158-172. 9 refs. Two methods based on potential theory and Euler's equations The background behind expected developments concerning primary flight control systems of future active control technology have been used for inviscid flow simulation which can be a useful transports is indicated. A survey of research performed by the tool for the evaluation of the pressure distribution along the air National Aerospace Laboratory to generate the necessary informa- intake walls. The following features of the methods are emphasized: tion to formulate low-speed flying qualities criteria for future the use of a conservative artificial density scheme for the potential transport aircraft employing a certain class of active control variational principle, semiorthogonal grid generation, and the use of a technology is presented. As tools, research flight simulators and characteristic boundary algorithm for Euler's equations. The ele- research aircraft have been used. All evaluations have been performed ments of, the computer program can be extended to three- using a deflection-type side-stick controller. The acceptability of dimensional flows and viscid interaction. V.L. neutral stick force stability for attitude stabilized aircraft is dealt with followed by a comprehensive treatment of criteria for longitudi- A81-11615 A study of the air inlet efficiency of a combat nal and lateral-directional maneuvering characteristics. (Author) aircraft concept with dorsal inlet. K. Widing (Flygtekniska Forsoks- anstalten, Bromma, Sweden). In: International Council of the Aeronautical Sciences, Congress, 12th, Munich, West Germany, A81-11619 Improved flight control performance and fail- October 12-17, 1980, Proceedings. New York, ure tolerance using modern control techniques. H. Berman American Institute of Aeronautics and Astronautics, Inc., 1980, p. (Grumman Aerospace Corp., Bethpage, N.Y.). In: International 173-182. Research sponsored by the Forsvarets Materielverk. Council of the Aeronautical Sciences, Congress, 12th, Munich, West An experimental investigation has been carried out to increase Germany, October 12-17, 1980, Proceedings. the knowledge of the combined effects of the favorable wing flow New York, American Institute of Aeronautics and Astronautics, Inc., and the disturbances from the forebody on the performance of a 1980, p. 209-218. 15 refs. dorsal inlet concept at take off and landing conditions. Wind tunnel Modern control techniques, including linear optimal control and tests were performed with a 1:5 model in FFA's low speed wind estimation theory, have been under investigation for many years. tunnel. At the engine face station, both steady state and fluctuating However, application to the control of aircraft has been limited. The pressure measurements were carried out to establish the inlet advent of practical digital flight control systems in recent years gives new impetus to the use of tnese techniques • particularly with the performance. A number of distortion indices for different engines rapid increase in computational capability of flight-type hardware. have been calculated. Results are presented which indicate that both This paper outlines an organized computer-aided procedure using total pressure losses and distortion indices considered are relatively modern control techniques to design digital Fly-By-Wire flight low and remain low up to moderate angles of attack and side-slip. control systems. The design procedure combines a methodology for (Author) determining sampling requirements, with a direct digital design A81-11616 On screeching jets exhausting from an axi- procedure for control law synthesis, with stochastic estimation as a symmetric supersonic nozzle. G. M. Carlomagno, C. Lanniello, and P. means for sensor analytic redundancy. Applying the procedure Vigo (Napoli, Universita, Naples, Italy). In: International Council of results in facilitating the synthesis step, enhancing control perfor- the Aeronautical Sciences, Congress, 12th, Munich, West Germany, mance, and increasing sensor system reliability and failure tolerance. October 12-17, 1980, Proceedings. New York, This paper describes the theoretical basis of the techniques and their American Institute of Aeronautics and Astronautics, Inc., 1980, p. application to advanced aircraft designs. (Author) 183-188. 14 refs. Research sponsored by the Consiglio Nazionale delle Ricerche. The behavior of screeching jets exhausting from an axisym- ASM 1620 OLGA, a gust alleviation system for improve- metric convergent-divergent nozzle was studied experimentally for ment of passenger comfort of general aviation aircraft. B. Krag, D. several nozzle configurations. Sound peaks behaving as screeches Rohlf (Deutsche Forschungs- und Versuchsanstalt fur Luft- und were detected in the weakly overexpanded and underexpanded Raumfahrt, Institut fur Flugmechanik, Braunschweig, West Ger- regimes. The external nozzle configuration had a marked effect on many), and H. Wiinnenberg (Dornier GmbH, Friedrichshafen, West the screech intensity, but did not influence the screech frequency. In Germany). In: International Council of the Aeronautical Sciences, the weakly overexpanded regime, two different screech frequencies Congress, 12th, Munich. West Germany, October 12-17, 1980, A81-11626

Proceedings. New York, American Institute of This paper describes a concept of aircraft control in which the Aeronautics and Astronautics, Inc., 1980, p. 219-231.8 refs. pilot commands are variables directly related to the aircraft motion A remotely controlled wind tunnel model and computer and not to deflexion angles of control surfaces. It is the airborne simulations have been used to test an open-loop gust alleviation computer which synthesizes and coordinates the commands for the system (OLGA) for a smal civil transport aircraft. The discussion various control surfaces, so that the aircraft reaches the maneuver concentrates on the dynamic response of the model and the effects goa set by the pilot. Two examples of maneuver commands have of measuring accuracy, gust sensor position, control surface rate been considered: The first example corresponds to a common mode limitation, and the dynamic characteristics of the sensors on the of aircraft control whereby the pilot sets the sideslip, roll rate, and performance of the gust allevration system and the handling qualities pitch rate; the control law is briefly described and then evaluated by of the model. V.L. digital simulation in the final phase of an air-to-ground gunfiring; the second example is specific to the air-to-ground gunnery; an approach to designing an Integrated Flight and Fire Control System is A81-11621 Active flutter suppression design and test - A presented whereby the pilot's task is reduced to target designation. joint U.S.-F.R.G. program. T. Noll (USAF, Flight Dynamics Labora- The design of both control systems is based on linear optimal control tory, Wright-Patterson AFB, Ohio), H. Honlinger, O. Sensburg theory with model-following improvement. (Author) (Messerschmitt-Bolkow-Blohm GmbH, Ottobrunn, West Germany), and K. Schmidt (Bundeswehr, Manching, West Germany). In: A81 -11624 Dynamic stability parameters at high angles of International Council of the Aeronautical Sciences. Congress, 12th, attack. K. J. Orlik-Ruckemann and E. S. Hanff (National Aeronauti- Munich, West Germany, October 12-17, 1980, Proceedings. cal Establishment, Unsteady Aerodynamics Laboratory, Ottawa, New York, American Institute of Aeronautics and Canada). In: International Council of the Aeronautical Sciences, Astronautics, Inc., 1980, p. 232-241. 10 refs. Congress, 12th, Munich, West Germany, October 12-17, 1980, A wing/store active flutter suppression system was designed, Proceedings. New York, American Institute of fabricated and installed on the F-4F aircraft to demonstrate and Aeronautics and Astronautics, Inc., 1980, p. 265-277. 21 refs. evaluate the concept in flight. The design used the existing autopilot A review is presented of some of the fluid dynamics phenomena and trailing edge ailerons with improved high-gain actuators. The that are associated with oscillatory flight at high angles of attack, feedback system used outboard wing accelerometers combined in a with particular emphasis on asymmetric shedding of forebody manner defined by optimal control theory. The external stores were vortices, asymmetric breakdown of leading edge vortices, the internally modified and were used as a flutter stopper for flight oscillatory motion of such vortices, and the time lag between the safety during the tests. Identification problems attributed to struc- vortex motion and the causative motion of the aircraft. These tural nonlinearities in the wing pylon-store system were encountered phenomena cause a number of important effects on the dynamic during the ground and flight tests. As a result, high speed flights with stability parameters at high alpha, such as strong non-linearities with the active flutter suppression system operating have not yet been alpha, significant static and dynamic aerodynamic cross coupling, accomplished. To describe the tests completed, open loop diagrams large time-dependent effects and a strong configuration dependence. as well as damping curves for important elastic modes are presented. New wind tunnel testing techniques to determine all the required In addition, recent results of an active flutter suppression design direct, cross and cross-coupling moment derivatives due to oscillation analysis and a transonic wind tunnel test of a lightweight fighter in pitch, yaw and roll as well as in vertical and lateral translation are aircraft configuration with a wing mounted external store are briefly described. (Author) presented. Good correlation between the analyses and test data is shown. Based on these and other investigations, active flutter suppression is now a feasible concept. Following more extensive A81-11625 Investigation of high-manoeuvrability flight design and testing experience in the area of safety and adaptive vehicle dynamics. M. E. Beyers (South African Council for Scientific control, active flutter suppression can be made operational and and Industrial Research, Flight Mechanics Div., Pretoria, Republic of included in the design of future tactical aircraft. (Author) South Africa). In: International Council of the Aeronautical Sci- ences, Congress, 12th. Munich, West Germany, October 12-17, 1980, A81-11622 A stability augmentation system which covers Proceedings. New York, American Institute of the complete flight envelope for a F-4c aircraft without gain Aeronautics and Astronautics, Inc., 1980, p. 278-292. 22 refs. scheduling. G. Kreisselmeier and R. Steinhauser (Deutsche For- The potential role of wind tunnel free-flight experiments in the schungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut fiir flight dynamic analysis of high-performance aircraft and missiles is Dynamik der Flugsysteme, Oberpfaffenhofen, West Germany). In: examined. The usefulness of the approach is seen to be not only International Council of the Aeronautical Sciences, Congress, 12th, contingent on the ability to extract aerodynamic derivatives, but also Munich, West Germany, October 12-17, 1980, Proceedings. lies in the broader objective of aerodynamic data/mathematical New York, American Institute of Aeronautics and model validation. Experimental and analytical techniques were Astronautics, Inc., 1980, p. 242-246. 12 refs. developed to study the generic nonoscillatory motion of high- For a McDonnell-Douglas F-4c aircraft a robust, fixed gain manoeuvrability vehicles in free flight and subsequently investigated controller is designed, which provides satisfying handling qualities of in depth. The stability derivatives of a destabilized, air-to-air missile the longitudinal motion of the aircraft over the complete flight range configuration were determined in free flight at Mach 0.7, revealing without gain scheduling. Robustness is achieved in the sense of highly nonlinear behavior and, in particular, 3 discontinuous dynamic covering large parameter variations and providing good gain and stability characteristic at medium angles of attack. The feasibility of phase margins. Only low control rates and low feedback gains are aircraft model free-flight tests is demonstrated on the basis of involved. The results are obtained by application of a performance simulations and a trajectory validation scheme proposed for the vector optimization design method which allows to take care of a corroboration of free-flight and captive-model dynamic data. great many of different design objectives simultaneously and in a (Author) highly systematic fashion. (Author) A81-11626 Longitudinal motion of low-flying vehicles in A81-11623 Multivariable aircraft control by manoeuvre nonlinear flowfields. R. Staufenbiel and G. Kleineidam (Aachen, commands - An application to air-to-ground gunnery. Mr. Dang Vu Rheinisch-Westfalische Technische Hochschule, Aachen, West Ger- Binh (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, France). In: many). In: International Council of the Aeronautical Sciences, International Council of the Aeronautical Sciences, Congress, 12th, Congress, 12th, Munich, West Germany, October 12-17, 1980. Munich, West Germany, October 12-17, 1980, Proceedings. Proceedings. New York, American Institute of New York, American Institute of Aeronautics and Aeronautics and Astronautics, Inc., 1980, p. 293-308. 8 refs. Astronautics, Inc., 1980, p. 247-256. 8 refs. (ONERA, TP no. The relationship between aerodynamic configuration and longi- 1980-127) tudinal stability in ground effect is investigated. It is shown that A81-11627

longitudinal stability is an important factor affecting the design of motion systems are also discussed. A performance diagram illustrates wing-in-ground (WIG) vehicles. Airfoil characteristics and wing the connection between specifications, such as maximum excursion, shapes are analyzed under static and dynamic height stability, and maximum velocity, maximum acceleration, bandwidth, and the configurations suitable for the design of stable WIGs are proposed. A design parameters. It is shown that in order to eliminate Coulomb- comparison between a conventional configuration and a WIG friction which results in reversal bump, hydrostatic bearings provid- configuration is made by simulating flare maneuvers. V.L. ing a permanent oilfilm between the sliding surfaces inside the actuator are applied. A.C.W. A81-11627 Identification of longitudinal flying character- istics of an aeroplane and the effect of nonstationary aerodynamics. A81-11634 Reduction of the take-off ground run distance V. Kocka (Vyzkumny a Zkusebni Letecky Ustav, Prague, Czechoslo- to a given set of atmospheric condition. D. lonescu (Institutul vakia). In: International Council of the Aeronautical Sciences, National Pentru Creatie Stiintifica si Tehnica, Bucharest, Rumania). Congress, 12th, Munich, West Germany, October 12-17, 1980, In: International Council of the Aeronautical Sciences, Congress, Proceedings. New York, American Institute of 12th, Munich, West Germany, October 12-17, 1980, Proceedings. Aeronautics and Astronautics, Inc., 1980, p. 309-323. 15 refs. New York, American Institute of Aeronautics Identification of aircraft longitudinal flying characteristics and and Astronautics, Inc., 1980, p. 385-390. its mathematical and physical variants was analyzed from a gnoseo- A method which permits to determine the take-off ground run logical viewpoint. A classification of nonstationary aerodynamics is distance for any atmospheric conditions, if the value of this distance presented to facilitate aerodynamic model analysis and to distinguish is available from direct measurement during a single take-off in between the 'path' and 'attitude' changes in the angle of attack. known atmospheric conditions, is presented. Based on classical Comparable expressions were derived for aerodynamic frequency equations which define the movement of the aircraft on the ground, transfers of entire aircraft, comprising normalized dimensionless the effects of the atmospheric factors (pressure and temperature) on transfers of the wing, the tailplane, and the interaction of the wing the take-off velocity and on the thrust of the engines are analyzed and the tailplane. The Strouhal number effect on complex aerody- and finally, a formula allowing to pass from a known distance to namic derivatives was determined; the corresponding weight func- another one obtained under different atmospheric conditions is tions were computed by the frequency spectrum of elevator established. The method may be useful to personnel acting in the deflection and by frequency transfers for responses of the aircraft. field of flight tests to determine the take-off ground run distance A.T. variations produced by changes in atmospheric conditions or by changes of the airport's height where the aircraft operates. (Author) A81-11630 The future cockpit of the next generation of civil aircraft. J. P. Laborie (Societe IMationale Industrielle Aero- A81-11635 The role of flight simulation in the design and spatiale, Division Avions, Toulouse, France). In: International development of the Sea Harrier Nav-Attack System. H. J. Allen Council of the Aeronautical Sciences, Congress, 12th, Munich, West (British Aerospace, Flight Simulation, Hatfield, Herts., England) and Germany, October 12-17, 1980, Proceedings. P. R. Walwyn, In: International Council of the Aeronautical New York, American Institute of Aeronautics and Astronautics, Inc., Sciences, Congress, 12th, Munich, West Germany, October 12-17, 1980, p. 347-352. 1980, Proceedings. New York, American Insti- The next generation of civil aircraft will be equipped with tute of Aeronautics and Astronautics, Inc., 1980, p. 391-400. 6 refs. completely new digital systems. The cockpit itself will be fitted with The introduction of more complex avionic systems into the new equipment which improves the man/machine interface. The single seat Harrier aircraft posed several problems, not the least of information will be displayed to the crew on cathode ray tubes which was the question of whether the pilot workload would be which have a full color capacity. The design of the complete cockpit acceptable. To determine this, and to obtain more detailed informa- is also new and is conceived in a totally integrated concept. This tion on system integration and performance, well in advance of flight paper describes the cockpit of a future aircraft: the Airbus A.310. testing, a maths model was developed on the existing BAe Hatfield (Author) flight simulator. The paper includes a brief description of the facility A81-11631 A theoretical and practical design investigation and of the Sea Harrier model in particular. Numerous investigations of the future military cockpit. J. W. Lyons (British Aerospace, were carried out and a pragmatic system of testing and reporting was Aircraft Group, Brough, Humberside, England). In: International used to ensure the results were incorporated at an early stage. The Council of the Aeronautical Sciences, Congress, 12th, Munich, West areas of study are mentioned and, to illustrate the central theme of Germany, October 12-17, 1980, Proceedings. the paper, the development of the air-to-air interception display is New York, American Institute of Aeronautics and Astronautics, Inc., described fully. The simulation, used at an early stage, has been an 1980, p. 353-359. 6 refs. extremely cost effective tool in eliminating faults in design concep- Trends in the design of future military cockpits are examined tion and developing new ideas. It has a continuing support role with emphasis on ergonomic and mechanical aspects. Specific during flight testing and future planning, and is being used as a problems discussed include seat design, the use of electronic displays, training aid for the first squadron pilots. (Author) ejection techniques, and conditioning systems producing low-noise environments. V.L. A81-11636 Low-speed airfoil section research at Delft University of Technology. J. L. van Ingen, L. M. M. Boermans, and J. A81-11633 Development and application of a moving base J. H. Blom (Delft, Technische Hogeschool, Delft, Netherlands). In: visual flight simulator including the design of hydraulic actuators International Council of the Aeronautical Sciences, Congress, 12th, with hydrostatic bearings. T. J. Viersma and M. Baarspul (Delft, Munich, West Germany, October 12-17, 1980, Proceedings. Technische Hogeschool, Delft, Netherlands). In: International Coun- New York, American Institute of Aeronautics and cil of the Aeronautical Sciences, Congress, 12th, Munich, West Astronautics, Inc.. 1980, p. 401-416. 49 refs. Germany, October 12-17, 1980, Proceedings. A review is given of some theoretical and experimental research New York, American Institute of Aeronautics and Astronautics, Inc., on the aerodynamic characteristics of airfoil sections for low speed 1980, p. 371-384. 20 refs. flows. Computer programs have been developed which combine A survey of current manned flight simulation research at the potential flow calculations with other computational methods to Department of Aerospace Engineering at Delft University of Tech- predict the development of the laminar boundary layer, the nology is presented with emphasis given to the assessment of the occurrence and possibly bursting of laminar separation bubbles, the dynamic characteristics of flight simulator motion systems, resulting position of transition and the development of the turbulent in a uniform measurement and analysis method. The design of boundary layer. Special attention has been given to theoretical and hydraulic actuators with hydrostatic bearings for flight simulator experimental research on the subjects of laminar separation bubbles

10 A81-11644

and transition. The paper will review the main results of this analysis code is also described. Finally, a brief review is made of two research. Capabilities of the resulting computer programs will be kinds of facilities; one is the two-dimensional high Reynolds number illustrated through comparison with experimental results for some wind tunnel, and the other is a numerical simulation project. airfoils. (Author) (Author)

A81-11638 Design and tests of an helicopter rotor blade A81-11641 Flow computation around multi-element air- with evolutive profile. J. J. Thibert (ONERA, Chatillon- foils in viscous transonic flow. H. Rosch and K. D. Klevenhusen sous-Bagneux, Hauts-de-Seine, France) and J. M. Pouradier (Societe (Vereinigte Flugtechnische Werke GmbH, Bremen, West Germany). Nationale Industrielle Aerospatiale, Division Helicopteres, Marignane, In: International Council of the Aeronautical Sciences, Congress, Bouches-du-Rhone, France). In: International Council of the Aero- 12th, Munich, West Germany, October 12-17, 1980, Proceedings. nautical Sciences, Congress, 12th, Munich, West Germany, October New York, American Institute of Aeronautics 12-17, 1980, Proceedings. New York, American and Astronautics, Inc., 1980, p. 470-479. 22 refs. Institute of Aeronautics and Astronautics, Inc., 1980, p. 429-443. A new singularity method is applied to multi-element airfoils in (ONERA, TP no. 1980-125) the physical plane for calculating both, the incompressible velocities In 1974 ONERA and Aerospatiale undertook jointly a research and the incompressible potential- and streamfunction along the program to improve helicopter rotor aerodynamics and particularly contour of each element. The values of the preceding computation to design optimized blades for future machines. This paper is a are used to build an orthogonal grid in which the airfoil is mapped to synthesis of the results obtained during the design process of a blade a line in the streamline plane. The computational domain is this with evolutive profile. The design methodology of a new family of streamline plane wherein the full transonic potential equation is airfoil sections covering a range of thickness to chord ratios from 6 solved using a finite difference method. The great influence of to 13 percent is presented and the performances of these airfoils viscous effects has been incorporated using the so-called surface deduced from tests in the S3 Modane wind tunnel are compared with transpiration concept. The representation of the displacement effect those of other known airfoils. The results obtained on model rotors of the boundary layer and wakes is based on the well-known integral and in flight on a SA365 Dauphin helicopter will be presented and method and a trailing edge flow concept, which includes normal analyzed. The use of the OA family gives an improvement of the pressure gradients and wake curvature effects. Comparisons of the rotor performances in hover and advancing flight and a reduction of theory with high Reynolds number experiments show the good the pitch control loads. The flight envelope has also been increased agreement for pressure distribution and lift. (Author) with these new airfoils. All these results will help in the setting up of the specifications of the future airfoil generation. (Author) A81-11642 High lift research and its application to aircraft design. J. R. Wedderspoon (British Aerospace, Aircraft Group, A81-11639 Review of numerical methods for the problem Weybridge, Surrey, England). In: International Council of the of the supersonic flow around bodies at angle of attack. P. I. Aeronautical Sciences, Congress, 12th, Munich, West Germany, Chushkin (Akademiia IMauk SSSR, Vychislitel'nyi Tsentr, Moscow, October 12-17, 1980, Proceedings. New York, USSR) and G. P. Voskresensky (Akademiia Nauk SSSR, Institut American Institute of Aeronautics and Astronautics, Inc., 1980, p. Prikladnoi Matematiki, Moscow, USSR). In: International Council of 480-493. 8 refs. the Aeronautical Sciences, Congress, 12th, Munich, West Germany, The aerodynamic research and development procedures used by October 12-17, 1980, Proceedings. New York, the Weybridge-Bristol Division of British Aerospace to design American Institute of Aeronautics and Astronautics, Inc., 1980, p. efficient high lift devices for advanced civil transport aircraft are 444-454. 70 refs. described, stressing the importance of achieving the correct balance Numerical methods for three-dimensional steady supersonic between theory and experiment. The theoretical methods used are inviscid flow around bodies modelling vehicles and their separate reviewed, and the design of a rigid Kruger slat is discussed. The main parts are reviewed. Three main groups of methods are considered: experimental techniques are described and the importance of the finite-difference net methods, method of characteristics, method of large body of data obtained during a major U.K. research programme integral relations (including method of lines). A number of different the 'National High Lift Programme' is assessed. Some interesting examples with numerical results concerning flow structure and results from this programme are quoted including the effect of aerodynamic properties under various flight conditions are discussed. supercritical section profiles on high lift performance. (Author) In some cases nonequilibrium processes in the air are taken into account. (Author) A81-11643 High-lift investigations on some small aspect ratio wings. H. Korner (Deutsche Forschungs- und Versuchsanstalt A81-11640 Research on transonic wings at the National fur Luft- und Raumfahrt, Institut fur Entwurfs-Aerodynamik, Braun- Aerospace Laboratory, Japan. N. Kamiya and N. Hirose (National schweig, West Germany). In: International Council of the Aeronauti- Aerospace Laboratory, Tokyo, Japan). In: International Council of cal Sciences, Congress, 12th, Munich, West Germany, October 12-17, the Aeronautical Sciences, Congress, 12th, Munich, West Germany, 1980, Proceedings. New York, American Insti- October 12-17, 1980, Proceedings. New York, tute of Aeronautics and Astronautics, Inc., 1980, p. 501-512. 19 American Institute of Aeronautics and Astronautics, Inc., 1980, p. refs. 455-469. 41 refs. An experimental investigation of the flow on some unconven- A brief review is made of the recent research on transonic wings tional small aspect ratio wings at high angle of attack is given. The being conducted at the NAL in Japan with the aim of improving investigation comprises force and flow field measurements as well as transonic performance of aircraft. It consists of two parts. One is the flow visualization by oil-flow, wool tuft in the wake and smoke research on transonic aerodynamics and the other is the research on injections on backward and forward swept and hybrid wings. The the optimization of transonic wings using such aerodynamics as a study shows that a stable flow behavior can be generated for a tool. Firstly, research on aerodynamics is described, which includes number of different planforms. For these cases aerodynamic coeffi- design of shock free airfoils using the hodograph method; numerical cients C(L), C(D), and C(M) are presented. The flow visualization design of shock free airfoils using the method of artificial gas; gives a deeper insight into the phenomenology of the flow. (Author) numerical design of airfoils with a shock wave by use of the relaxation method; two kinds of numerical analyses of unsteady flow A81-11644 Optimizing the fixed leading edge shape of a around airfoils, one using Euler equations and the other using full transonic wing to suit the landing high-lift requirements. M. potential equations; and analysis of flow around three dimensional Ingelman-Sundberg and L.-E. Eriksson (Flygtekniska Forsoks- wings by use of integral equations. Some remarks are also made anstalten, Bromma, Sweden). In: International Council of the about the viscous effect evaluation. Secondly, research on optimiza- Aeronautical Sciences, Congress, 12th, Munich, West Germany, tion of transonic airfoils is described. The evaluation of the airfoil October 12-17, 1980, Proceedings. New York,

1 1 A81-11645

American Institute of Aeronautics and Astronautics, Inc., 1980, p. A systematic experimental program is described which has lead 513-521. 6 refs. Research supported by the Forsvarets Materielverk. to a patented vortex diffuser device for drag reduction. This consists The paper reports the results of low-speed tests conducted as of a winglet-like vane mounted from a boom which trails a wing tip. part of a larger program to optimize a transonic aircraft wing for Under CID-limited conditions on the vanes, it is claimed that the use three flight phases', transonic cruise at Wl = 0.85, maneuvering at M = of an aft location yields greater drag reduction per square foot of 0.5, and landing. The low-speed part of the program was limited to vane area and larger-span vanes may be used effectively. There is droop variations for the leading edge of a basic wing with planform, little interference with the wing tip and adverse effects, such as loss thickness, and twist distribution determined by transonic considera- of aileron power after winglet stall, are avoided. It is pointed out that tions, the objective was to find out if it could be possible to avoid a strong coupling exists between induced drag and wing root bending movable leading edge flaps. The requirement for sufficient Reynolds for near-planar wings. This coupling can be reduced significantly by numbers in tests of this kind is emphasized. V.L. employing nonplanar tips and design flexibility benefits. (Author)

A81-11645 Winglets development at Israel Aircraft Indus- A81-11648* Leading-edge'Vortex Flaps'for enhanced sub- tries. I. Darel, Y. Eliraz, and Y. Barnett (Israel Aircraft Industries, sonic aerodynamics of slender wings. t>. M. Rao (Vigyan Research Ltd., Lod, Israeli. In: International Council of the Aeronautical Associates, Inc., Hampton, Va.). In: International Council of the Sciences, Congress, 12th, Munich, West Germany, October 12-17, Aeronautical Sciences, Congress, 12th, Munich, West Germany, 1980, Proceedings. New York, American Insti- October 12-17, 1980, Proceedings. New York, tute of Aeronautics and Astronautics, Inc., 1980, p. 522-529. American Institute of Aeronautics and Astronautics, Inc., 1980, p. The first wind tunnel tests for the development of winglets at 554-562. NASA-supported research. IAI were conducted on the ARAVA STOL transport aircraft in late The 'Vortex Flap' is a novel concept aimed at reducing the 1974. On this aircraft the aim of the design was to improve the take lift-dependent drag due to leading-edge flow separation on highly off weight limitations with one engine inoperative, without compro- swept, slender wings at high angles of attack. The suction effect of mising cruise performance. The flight tests confirmed the wind coiled vortices generated via controlled separation over leading-edge tunnel results at the design point and a substantial increase in the flap surfaces is utilized to produce an aerodynamic thrust compo- permissable take off weight was achieved. The overall cruise nent. This principle was verified through wind-tunnel experiments on performance was improved as well. Following the successful winglet 74-deg and 60-deg delta wings and a supersonic-cruise slender wing development on the ARAVA, a new program was started in 1978 on aircraft configuration. Adaptation of the vortex-flap for augmenta- the IAI Westwind business jet. This design was special in that the tion of roll-control on the 74-deg delta at high angles of attack also winglets were installed on wing tip tanks. The design aim for the was demonstrated. Selected results are presented in this paper to Westwind was greater fuel efficiency, and take off weight limitations indicate the potential of the vortex flap concept to enhance the gains were a secondary objective. As a result, a new Westwind 2 was low-speed performance, stability and control of slender wing aircraft. tested and received certification, with greater fuel efficiency. This (Author) paper presents details of winglet geometry, wind tunnel and flight tests and performance improvements due to installation of winglets. A81-11649 An experimental investigation of the inter- (Author) action between a glancing shock wave and a turbulent boundary layer. H. Kubota and J. L. Stollery (Cranfield Institute of Technol- A81-11646 * Optimum subsonic, high-angle-of-attack na- ogy, Cranfield, Beds., England). In: International Council of the •celles. R. W. Luidens, N. 0. Stockman, and J. H. Diedrich (NASA, Aeronautical Sciences, Congress, 12th, Munich, West Germany, Lewis Research Center, Cleveland, Ohio). In: International Council October 12-17, 1980, Proceedings. New York, of the Aeronautical Sciences, Congress, 12th, Munich, West Germa- American Institute of Aeronautics and Astronautics, Inc., 1980, p. ny, October 12-17, 1980, Proceedings. New 563-574. 14 refs. USAF-supported research. York, American Institute of Aeronautics and Astronautics, Inc., A variable incidence wedge, mounted from the side of a 1980, p. 530-541. 16 refs. supersonic tunnel, has been used to study 3-D glancing interaction. A Many proposed advanced aircraft - but especially tilt-nacelle, wedge-generated oblique shock-wave interacts with the thick turbu- subsonic-cruise, V/STOL aircraft - require nacelles that operate over lent boundary layer growing along the tunnel side wall. Two related a wide range of aerodynamic conditions. The optimum design of test programs have been completed using a 6 x 6 cm intermittent such nacelles and their inlets is described, including how the inlet tunnel and a 23 x 23 cm continuous tunnel, both operating at a low-speed design conditions are selected, the conditions for which Mach number of approximately 2.5. The experimental results include the various regions of the inlet are designed, and appropriate criteria oil-flow pictures, vapor-screen and smoke photographs, surface of merit. For low-speed operation the optimum internal surface pressure distributions, local heat transfer, liquid crystal pictures of velocity distributions and skin friction distributions are described for surface temperature and viscous layer surveys. The test data show three categories of inlets: those without boundary-layer control that the interaction is complex, with an induced layer which (8LC), those with BLC, and those with blow-in door slots and originates near the root of the wedge, spreading and crossing the path retractable slats. Experimental results are presented that show the of the side wall boundary layer. Separation is defined by the performance of the various types of inlets. At cruise speed the effect appearance of a complete convergence line in the surface-oil-flow of factors that reduce the nacelle external surface area and the local pictures. No separation occurs as long as the surface stream lines are skin friction is illustrated. These factors are cruise Mach number, pliable enough to be bent along the edge of the induced layer, even inlet throat size, fan-face Mach number, and nacelle contour. The when the surface flow deflection exceeds the shock angle. However, interrelation of these cruise-speed factors with the design require- separation does take place when the induced layer forces the surface ments for good low-speed performance is discussed. Finally an inlet stream lines to deflect beyond a maximum permissible angle. A design without BLC and an optimized inlet design with.slots and slats correlation of incipient separation data is given. (Author) are compared to illustrate the possible reductions in nacelle size. A81-11650 Weight optimization of wing structures accord- (Author) ing to the gradient method. D. W. Mathias, H. Rohrle, and J. Artmann (Cornier GmbH, Friedrichshafen, West Germany). In: International Council of the Aeronautical Sciences, Congress, 12th, A81-11647 Vortex drag reduction by aft-mounted diffus- Munich, West Germany, October 12-17, 1980, Proceedings. ing vanes. J. E. Hackett (Lockheed-Georgia Co., Marietta, Ga.). In: New York, American Institute of Aeronautics and International Council of the Aeronautical Sciences, Congress, 12th, Astronautics, Inc., 1980, p. 575-582. Research supported by the Munich. West Germany, October 12-17, 1980, Proceedings. Bundesministerium der Verteidigung. New York, American Institute of Aeronautics and For the design of wing structures with optimal weight the Astronautics, Inc., 1980, p. 542-553. 22 refs. gradient method is applied due to the different constraints (stresses.

12 A81-11659

flutter speed). The theory and the computer program are described. tion is given to transmission-ultrasonic testing (e.g., C-Scan), As an example, an idealized wing consisting of bending/torsion bar reflection-ultrasonic testing, the eddy current technique, radiog- elements is presented for which the stresses as well as the flutter raphy, and holography. The evaluation method which works best for speed are active restrictions. (Author) each type of structure, such as sandwich structures with a Nomex honeycomb core and carbon cladding, or adhesive bonded metal A81-11651 Structural optimization of advanced aircraft joints is examined. A.C.W. structures. G. Schneider, H. Godel, and O.Sensburg (Messerschmitt- Bolkow-Blohm GmbH, Munich, West Germany). In: International A81-11655 Holographic non-destructive testing of materi- Council of the Aeronautical Sciences, Congress, 12th, Munich, West als using pulsed lasers. H. Fagot, F. Albe, P. Smigielski (Institut Germany, October 12-17, 1980, Proceedings. Franco-Allemand de Recherches, Saint-Louis, Haut-Rhin, France), New York, American Institute of Aeronautics and Astronautics, Inc., and J. L. Arnaud (Societe Nationale Industrielle Aerospatiale, 1980, p. 583-595. 13 refs. Laboratoire Central, Suresnes, Hauts-de-Seine, France). In: Interna- The application of a structure optimization program is demon- tional Council of the Aeronautical Sciences, Congress, 12th, Munich, strated for several design studies, including a simplified structure to West Germany, October 12-17, 1980, Proceedings. show the capabilities of the system, aeroelastic efficiency calcula- New York, American Institute of Aeronautics and Astronautics, tions for fin and rudder, and structural layout of a carbon fiber Inc., 1980, p. 626-633. Research supported by the Direction des composite delta wing. The program merges several disciplines, such as Recherches, Etudes et Techniques. static loads, stress and strain calculations by finite elements, The results of in situ and laboratory nondestructive testing unsteady aerodynamics, flutter calculations, static aeroelastics, and experiments are reported in which double exposure holography with weights, which can be used separately and independently. V.L. two pulsed ruby lasers is used to detect various defects in aircraft structures. It is shown that the method is particularly suitable for detecting defective bonding during maintenance or fabrication and A81-11652 Application of weldbonding to A-10 produc- for detecting cracks during fatigue testing. V.L. tion aircraft. A. Shames, R. Rupp, and J. Clarke (Fairchild Republic Co., Farmingdale, N.Y.). In: International Council of the Aeronauti- cal Sciences, Congress, 12th, Munich, West Germany, October 12-17, ASM 1656 Structural flight load testing, calibration and 1980, Proceedings. New York, American Insti- analysis. E. Rauscher (Vereinigte Flugtechnische Werke-Fokker tute of Aeronautics and Astronautics, Inc., 1980, p. 596-603. 5 refs. GmbH, Bremen, West Germany). In: International Council of the The Al weldbonding process combines techniques of adhesive Aeronautical Sciences, Congress, 12th, Munich, West Germany, bonding and resistance welding for the production nacelle cowls, October 12-17, 1980, Proceedings. New York, beaded panels, flaps, and fins in A-10 aircraft. The manufacturing American Institute of Aeronautics and Astronautics, Inc., 1980, p. method consisting of phosphoric acid anodizing, application of the 634-644. 11 refs. weldbond adhesive, and microprocessor controlled resistance welding In this paper structural flight load testing is reported. The are described; after welding, the components are cured at 121 C for 3 calibration procedure including strain gauge bridge selection to hrs. 7075 and 2024 aluminum alloys were bonded and tested in an obtain flight loads is described. There are several evaluation methods environmental chamber simulating ambient and altitude conditions for short and long flight periods to check design loads for static and at 35,000 ft; in addition, X-ray and Fokker bond testers were used to fatigue criteria. The maximum likelihood method is used to detect delamination, lap-shear tests measured the shear strengths, and investigate aerodynamic coefficients. Counting procedures are used static and spectrum fatigue analyses were performed. AT. for statistical purposes. (Author)

A81-11657 Flight simulation environmental fatigue crack A81-11653 Development of the A300 fin in modern propagation in 2024-T3 and 7475-T761 aluminium. R. J. H. Wanhill composite fibre construction. D. Schulz (Messerschmitt-Bolkow- (Nationaal Lucht- en Ruimtevaartlaboratorium, Amsterdam, Nether- Blohm, GmbH, Hamburg, West Germany). In: International Council lands). In: International Council of the Aeronautical Sciences, of the Aeronautical Sciences, Congress, 12th, Munich, West Ger- Congress, 12th, Munich, West Germany, October 12-17, 1980, many, October 12-17, 1980, Proceedings. New Proceedings. New York, American Institute of York, American Institute of Aeronautics and Astronautics, Inc., Aeronautics and Astronautics, Inc., 1980, p. 645-651. 26 refs. 1980, p. 604-618. Flight simulation fatigue crack propagation tests on 2024-T3 On the basis of a research program sponsored by the German and 7475-T761 aluminum alloy sheet were carried out using a gust government development was started on the Airbus fin box in spectrum representative of the load history of an under wing skin in fiber-reinforced plastics in 1978. In 1984 one fin shall be certificated a transport aircraft. The investigation included tests at several design for airworthiness and be tested in airline service. In this paper, stress levels and in environments of laboratory air and air plus water program and design aims are set up. Main results achieved during the spray. The results are discussed with respect to the choice of first development phases are reported. Environmental conditions to structural concepts using 7475 alloy and evaluation of the fatigue be considered permit the use of 120 C-resin systems. As the result of properties of such concepts. (Author) analytical and experimental investigations with respect to weight, production costs, maintenance and reliability, a structure was chosen which is primarily reinforced by open-section stringers. By using a A81-11659 A practical method for predicting flight-by- low-cost production concept the increased composite material cost flight crack growth in fighter type aircraft for damage tolerance can be offset. (Author) assessment. M. Levy, A. S. Kuo, and K. P. Grube (Fairchild Republic Co., Farmingdale, N.Y.). In: International Council of the Aeronauti- cal Sciences, Congress, 12th, Munich, West Germany, October 12-17, A81-11654 Nondestructive evaluation of composite struc- 1980, Proceedings. New York, American Insti- tures (Controle non destructif des pieces en materiaux composites). tute of Aeronautics and Astronautics, Inc., 1980, p. 666-675. 23 M. Treca and J. Odorico (Societe Nationale Industrielle Aerospatiale, refs. Laboratoire Central, Suresnes, Hauts-de-Seine, France). In: Inter- It has been experimentally observed that the flight-by-flight national Council of the Aeronautical Sciences, Congress, 12th, crack growth rate, da/dF, under fighter type spectra, can be uniquely Munich, West Germany, October 12-17, 1980, Proceedings. related to the stress intensity factor per unit stress, alpha, for various New York, American Institute of Aeronautics and forms of 2024-T3 type aluminum alloys. The crack growth analysis Astronautics, Inc., 1980, p. 619-625. In French. method based on this observation is shown to be more effective in Methods for evaluating carbon fiber composite structures are terms of accuracy and computer time than the standard cycle-by-' reviewed including both industrial and research methods. Considera- cycle integration method. This experimental approach was extended

13 A81-11662

to include spectrum variation, stress level differences, various initial the Aeronautical Sciences, Congress, 12th, Munich, West Germany, flaw and geometry configuration, and load transfer effects. In October 12-17, 1980, Proceedings. New York, selected cases, the technique of developing experimental crack American Institute of Aeronautics and Astronautics, Inc., 1980, p. growth curves derived directly from fractographic analysis of 758-772. 35 refs. specimens tested with periodic marker sequence loadings is discussed. Forced singular perturbation technique (FSPT), based on The expansion of the da/dF vs. alpha method is shown as a useful artificial insertion of a 'small' parameter into the equations of and viable tool in performing the fatigue crack growth analyses in motion, has been used to generate approximate feedback solutions in support of the A-10A damage tolerance reassessment task. (Author) several aircraft performance optimization problems. This approach has some inherent limitations, not being exposed in previous works. The paper presents and discusses such limitations revealed by a A81-11662 Operational durability of airframe structures. recent investigation. In spite of the restrictions FSPT provides an R. J. Schliekelmann (Fokker-VFW, Schiphol, Netherlands). In: attractive methodology for a large class of properly formulated International Council of the Aeronautical Sciences, Congress, 12th, problems. This potential is demonstrated by two examples of air Munich, West Germany, October 12-17, 1980, Proceedings. combat performance optimization. (Author) New York, American Institute of Aeronautics and Astronautics, Inc., 1980, p. 702-712. 19 refs. A81-11668 Optimal flight vehicle design and linear vector The concept of the durability of airframe structures and spaces. S. M. Ramachandra (Alfateh University, Tripoli, Libya). In: methods of design for durability are discussed together with the International Council of the Aeronautical Sciences, Congress, 12th, relationship between the operational economy of an aircraft and the Munich, West Germany, October 12-17, 1980, Proceedings. structural characteristics of the airframe. It is shown that sufficient New York, American Institute of Aeronautics and resistance of airframe structures to working loads and environmental Astronautics, Inc., 1980, p. 773-777. 12 refs. factors can be achieved only by a systematic approach which A linear vector space approach to the design and optimization of includes the following phases: definition of structural concepts, flight vehicles is presented. The design space can be explored to selection of primary structural materials and means of their obtain the best performance with the current or anticipated protection against environmental effects, definition of joining meth- technology, and to obtain performance approaching customer ods, and integration. V.L. desired specifications. The sensitivity coefficient is defined for perturbations in the design vector. Parameter uncertainties, especially at the beginning of the design process, are handled with probability A81-11665 Investigation of the stalling characteristics of a measures or through membership functions of the theory of fuzzy general aviation aircraft. R. F. Stengel and W. B. Nixon (Princeton sets. The flight vehicle design of civil and multiple-role military University, Princeton, N.J.). In: International Council of the Aero- aircraft is considered. R.C. nautical Sciences, Congress, 12th, Munich, West Germany, October 12-17, 1980, Proceedings. New York, American A81-11669 Three years of operation of the ONERA Institute of Aeronautics and Astronautics, Inc., 1980, p. 729-743. 32 pressurized subsonic wind tunnel. J.-M. Carrara and A. Masson refs. Research supported by theSchultz Foundation. (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, France). In: Inter- Analytical and numerical estimates of the stalling characteristics national Council of the Aeronautical Sciences, Congress, 12th, of a small, single-engine aircraft are compared with flight test results. Munich, West Germany, October 12-17, 1980, Proceedings. Analyses include nonlinear simulation and linear stability-and-control New York, American Institute of Aeronautics and evaluation using aerodynamic and thrust characteristics obtained Astronautics, Inc., 1980, p. 778-792. 5 refs. (ONERA, TP no. from a full-scale test in the NASA Langley Research Center 30 x 60 1980-129) ft Wind Tunnel as well as subscale model test data. Flight tests Three years after the entry into service of the pressurized include prestall calibration runs, symmetric gradual stalls, and mildly subsonic wind tunnel F1 of ONERA at Le Fauga-Mauzac a first accelerated stalls in the vertical plane. These tests tend to confirm survey of its utilization was presented. After a brief description of predictions based upon wind tunnel results, and they indicate areas the wind tunnel and its instrumentation, the paper describes in which special care must be taken in collecting data for aerodynamic characteristics and performance of the tunnel. The aerodynamic parameter identification. (Author) testing devices of the wind tunnel and some original testing techniques are presented. The variety of the tests performed is illustrated by typical examples. A comparison with flight results of A81-11666 Procedures to improve flight safety in wind those obtained on a model of Mercure makes it possible to globally shear conditions. R. Kbnig and P. Krauspe (Braunschweig, Tech- validate the quality of the wind tunnel. (Author) nische Universitat, Braunschweig, West Germany). In: International Council of the Aeronautical Sciences, Congress, 12th, Munir.h, West Germany, October 12-17, 1980, Proceedings. A81-11670 DFVLR-dynamic model testing in wind tun- New York, American Institute of Aeronautics and Astronautics, Inc., nels for active controls research. K. Wilhelm and B. Gmelin 1980, p. 744-757. 14 refs. Research supported by the Deutsche (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Forschungsgemeinschaft. Institut fur Flugmechanik, Braunschweig, West Germany). In: Inter- Wind shear on take-off and landing may crucially restrict flight national Council of the Aeronautical Sciences, Congress, 12th, safety. After a short description of the meteorological weather Munich, West Germany, October 12-17, 1980, Proceedings. phenomena most closely associated with wind shear, reasons are New York, American Institute of Aeronautics and given for the existing hazards to aircraft operations with the use of Astronautics, Inc., 1980, p. 793-807. 39 refs. conventional cockpit instruments. Different methods to compensate Application of the concepts of Active Control Technology to for wind shear effects are evaluated (open loop wind shear the design of aircraft is discussed with reference to two wind tunnel elimination/total energy display/management of specific energy rate) facilities for dynamic model testing: (1) Installation for Dynamic including today's state of the art as well as an outlook on future Simulation in Wind Tunnels for investigations in the field of instrumentation corresponding to the problem and a comment on fixed-wing aircraft, and (2) Rotor Test Stand for investigations in the groundbased wind siiear warning systems. (Author) field of rotary-wing aircraft. Problems of. transferability of measure- ment data from model to full-scale aircraft are discussed and test results are presented. V.L.

A81-11667 Aircraft performance optimization by forced A81-11671 Adaptable wind tunnel walls for 2D and 3D singular perturbation. J. Shinar (Technion - Israel Institute of model tests. U. Ganzer (Berlin, Technische Universitat, Berlin, West Technology, Haifa, Israel) and A. Merari. In: International Council of Germany). In: International Council of the Aeronautical Sciences,

14 A81-11722

Congress, 12th, Munich, West Germany, October 12-17, 1980, Proceedings. New York, American Institute of Proceedings. New York, American Institute of Aeronautics and Astronautics, Inc., 1980, p. 837-846. 14 refs. Aeronautics and Astronautics, Inc., 1980, p. 808-816. 13 refs. (ONERA, TP no. 1980-126) Research supported by the Bundesministerium fur Forschung und The phenomena of electrostatic charging of aircraft and the Technologie and Deutsche Forschungsgemeinschaft. consequent problem of interference with navigation and communica- Two-dimensional model tests were made in a test section with tion systems are considered in view of the development of a standard flexible top and bottom wall. A conventional NACA 0012 aerofoil ground testing procedure for eliminating static charging hazards. It is and a supercritical CAST 7 aerofoil were used with a tunnel height to proposed that a standard procedure for testing aircraft charging chord ratio of 1.5. It was shown that wall interference effects can be phenomena and various protections, in the laboratory, in the factory, reduced by wall shaping and that transonic blockage can be avoided. and on the field can be realized by efficient and economical ground The same test section was used for 3-component force-measurement test simulations. The test method includes the verification of of a simple swept-wing-body-combination to demonstrate con- bonding between metallic surfaces, surface resistance measurements, vergence of the adaption process for 3D model tests. (Author) the simulation of tribo-electric charging, and the verification of minimal coupling between dischargers and antennas. The application A81-11672 » A system for model access in tunnels with an of the procedure can be achieved with the use of specific instruments unbreathable test medium. R. R. Howel and S. D. Joplin (NASA, which have been designed and implemented at ONERA, and Langley Research Center, Hampton, Va.). In: International Council marketed in France. The performance and application of a bonding of the Aeronautical Sciences, Congress, 12th, Munich, West Ger- verification device as well as an instrument which injects charged many, October 12-17, 1980, Proceedings. New particles for the simulation are discussed in conjunction with the York, American Institute of Aeronautics and Astronautics, Inc., proposed test procedure. A.C.W. 1980, p. 817-822. 7 refs. In many specialty wind tunnels, test gases other than ambient A81-11675 Wind shear detection from PCM-recorded air are used to meet special testing requirements. A typical example MLS-flight data. P. Vorsmann and M. Swolinsky (Braunschweig, is the use of freon as the test gas to achieve a realistic density ratio Technische Universitat, Braunschweig, West Germany). In: Inter- between gas and model for exploring flutter stability boundaries. national Council of the Aeronautical Sciences, Congress, 12th, Another example is the use of pressurized air \o elevate the stream Munich, West Germany, October 12-17, 1980, Proceedings. density and enhance Reynolds number or dynamic pressure simula- New York, American Institute of Aeronautics and tion. Such specialty tunnels require a system of access to the model Astronautics, Inc., 1980, p. 847-855. 9 refs. Research supported by which will allow services and changes to the model without exposing the Deutsche Forschungsgemeinschaft. personnel to the unnatural and perhaps hostile environment or During the test phase of the SET AC microwave landing system, requiring the venting and purging of the entire tunnel circuit. This flight tests were performed for wind determination along the flight paper will describe the plenum and model access systems for the path. Approach profiles were curved in elevation and azimuth. All forthcoming U.S. National Transonic facility where gaseous nitrogen flight parameters were recorded on board in digital form by a (N2) at temperatures between 338 and 78 K and at pressures to 9 PCM-flight data acquisition system. The evaluation of the recorded bars is used as the test medium. The operation at cold temperatures flight data on a digital computer showed that some signals contained imposes some additional requirements which make the access disturbances resulting from sensor dynamics or digital noise due to systems more difficult to design and time consuming to operate than numerical differentiation. Nonrecursive digital filters were applied to for conventional wind tunnels. (Author) eliminate undesired signal properties. The longitudinal wind compo- nent and its power spectrum were computed. Wind shear was detected by the off-line use of nonrecursive digital filters as well. (Author) A81-11673 Wind tunnel wall interference in a test section with ventilated walls. H. Sawada (National Aerospace Laboratory, A81-11676 ECS integration for fuel efficient/low life Tokyo, Japan). In: International Council of the Aeronautical cycle cost design. V. K. Rajpaul (Boeing Military Airplane Co., Sciences, Congress, 12th, Munich, West Germany, October 12-17, Seattle, Wash.). In: International Council of the Aeronautical 1980, Proceedings. . New York, American Insti- Sciences, Congress, 12th, Munich, West Germany, October 12-17, tute of Aeronautic and Astronautics, Inc., 1980, p. 823-836. 18 1980, Proceedings. New York, American Insti- . refs. tute of Aeronautics and Astronautics, Inc., 1980, p. 856-861. An approach to the ventilated wind tunnel wall interference Current technology environmental control systems (ECS) in problem is proposed in which velocity components of flow near the aircraft suffer from deficiencies in two major respects: (1) the fuel walls inside a test section are used as boundary conditions for solving penalty for engine bleed air extraction and ram air drag is high, and a boundary value problem of the flow field. The wall interference on (2) lack of adequate system temperature and moisture controls result a wing model installed in a test section is estimated, since various in excessively high avionic equipment failure rates, thereby adversely quantities related to wall interference can be estimated with affecting life cycle costs. Studies conducted in development of sufficient accuracy if only transversal lower harmonics of the energy efficient, low life cycle cost ECS are discussed with a tactical streamwise distributions are available. The effect of suction from the mission aircraft used for illustrating problems, new concepts and side walls in a two-dimensional wind tunnel is investigated in detail. payoffs. Concepts which significantly reduce fuel consumption, The proposed method for calculating blockage and lift interference thrust and drag penalties to an aircraft are related to reliability of corrections is applied to a two-dimensional test section configuration interfacing systems, in particular the avionics. Relationship to life of a 2m x 2m transonic wind tunnel. The blockage factor ratio and cycle cost of ECS/avionic systems is discussed. (Author) lift interference parameters are shown to be dependent upon the lift coefficient but not significantly sensitive to either uniform Mach A81-11722 The vibration of a multi-bearing rotor. J. L. numbers between 0.6 and 0.8, or to the difference in the tested Nikolajsen and R. Holmes (Sussex, University, Brighton, England). airfoil sections. Therefore, it becomes possible by the use of these Journal of Sound and Vibration, vol. 72, Oct. 8, 1980, p. 343-350. characteristics to make corrections without measuring the pressure Research supported by the Science Research Council and Ministry of distributions near the walls each time. A.C.W. Defence (Procurement Executive). A numerical method based on the use of influence coefficients is A81-11674 Ground testing of aircraft antistatic protec- described for the free and forced vibration analysis of a general tion. J. Taillet (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, rotor/bearing system. The method is found to combine the numerical France). In: International Council of the Aeronautical Sciences, speed of the transfer matrix method with the accuracy and versatility Congress, 12th, Munich, West Germany, October 12-17, 1980, of the finite element method. The paper describes the prediction of

15 A81-11723

the vibration performance of a four-bearing rotor with which Flat free vortex sheets are introduced near the edges beside the experimental results compare satisfactorily. (Author) vortex cores above the wing. The flowfield is assumed to be conical and flow is permitted through the free sheets. Instead of applying the A81 11723 Some thoughts on the effects of flight on jet usual boundary conditions on free vortex sheets an attempt is made noise as observed in actual flight and in wind tunnels. R. G. Hoch to fulfill the suction analogy by prescribing normal force coefficients (SNECMA, Centre d'Essais de Villaroche, Moissy-Cramayel, Seine-et- and taking account of the condition that the whole free vortex Marne, France). Journal of Sound and Vibration, vol. 72, Oct. 8, system should be force-free. This procedure leads to satisfactory 1980, p. 379-389. 17 refs. results for the pressure distributions with small total vortex strength Evidence on differences between flight effects on jet noise as within the free vortex sheets, but for small angle of attack the observed in flight tests and in tests with model jets in anechoicwind normal forces according to Smith's method have to be used instead tunnels is briefly reviewed and discussed. The effects on noise of of those according to leading edge suction analogy. (Author) single stream jets is distinguished from those on noise of coaxial jets. A way of explaining the differences, both between model and engine A81-11778 Calibration of the high speed wind tunnel jets and single stream and coaxial jets is proposed, which involves TVM 150 in the supersonic range (Eichung des Hochgeschwindig- ideas drawn from Ribner's self-noise/shear-noise model, recent results keitewindkanals TVM 150 im Uberschallbereich). W. Weinert on noise amplification of excited jets, and new lines of research. (Darmstadt, Technische Hochschule, Darmstadt, West Germany). (Author) Zeitschrift fur Flugwissenschaften und Weltraumforschung, vol. 4, Sept.-Oct. 1980, p. 280-289. 20 refs. In German. A81-11724 Experiments on effective source locations and The Laval nozzle calibration and its flow quality in the velocity dependence of the broad band noise from a rotating rod. U. test-section of the high speed wind tunnel TVM 150 at the R. Kristiansen (Trondheim, Uniyersitetet, Trondheim, Norway). Aeronautical Institute of the Technical University Darmstadt are Journal of Sound and Vibration, vol. 72, Oct. 8, 1980, p. 403-413. 7 presented. Investigations of Mach number and flow-angle distribu- refs. tions at supersonic Mach numbers were carried out with conventional Effective acoustic source positions (observed from the far field) pilot rakes and a combined calibration rake for measuring flow have been located for the broad band noise from a cylindrical rod angularity. The relative maximum Mach number error increases with rotated about its mid-point by measuring the cross spectral density a decreasing Mach number and increasing radius of nozzle range. function of two microphone signals on the axis of rotation. Local While the flow-angle of attack is directed with increasing distance source position Strouhal numbers could thereby be calculated. On from the tunnel axis against the top and bottom wall, the flow in the the basis of acoustic power measurements it was demonstrated that plane of the sideslip angle is directed against the nozzle axis. Both the noise may be normalized on a rod tip Strouhal number basis, and flow-angle errors show the same Mach number dependent tendency that the velocity exponent is nearly constant when plotted against within the 0.1-degree-range. Along the tunnel axis there are no this parameter. The results indicate that vortex shedding like that for mentioned deviations in the test rhombus. (Author) stationary cylinders in a cross flow (occurring along the outer 1/3 of the rod for a rotational speed of 1000 rpm) is responsible for the A81-11779 Calculation of plane transonic flows using the high levels of broad band noise in a major peak region. Sources integral equation method and shock fitting (Berechnung ebener influenced by harmonics of the rod passing frequency were found for transsonischer Strbmungen nach der Integralgleichungsmethode mit frequencies lower than the vortex shedding ones. At higher frequen- Stossanpassung). R. Voss (Deutsche Forschungs- und Versuchsanstalt cies broad band noise was found to be emitted from the rod tip area. fur Luft- und Raumfahrt, Institut fur Aeroelastik, Gottingen, West (Author) Germany). Zeitschrift fur Flugwissenschaften und Weltraum- A81-11751 Hydrogen - Its technology and implications. forschung, vol. 4, Sept.-Oct. 1980, p. 289-295. 23 refs. In German. Volume 4 - Utilization of hydrogen. Edited by K. E. Cox and K. D. Research supported by the Deutsche Forschungsgemeinschaft Williamson, Jr. (California, University, Los Alamos, N. Mex.l. Boca The present work uses the integral equation method to compute Raton, Fla., CRC Press, Inc., 1979. 252 p. $59.95. approximately two dimensional steady transonic flows with shocks around airfoils at freestream Mach numbers less than 1. Potential This compilation focused on hydrogen fueled surface transporta- flow and small disturbances are assumed. In contrast to other tion, hydrogen-fueled aircraft, domestic uses of hydrogen, industrial methods, integrals over the pressure jump along the shocks are applications, and safety in the handling of H. The volume includes explicitly calculated during the iterative solution of the integral numerous references on H properties, materials of construction for equation. Shocks are fitted to the flow field at each iteration step. its containment, and the design of H equipment; physical properties Shock position and shock strength are calculated by combining the of H and its compounds are tabulated. A.T. normal shock conditions and the condition that shock induced A81-11753 Hydrogen-fueled aircraft. G. D. Brewer profile drag and drag from entropy rise across the shock are equal. (Author) (Lockheed-California Co., Burbank, Calif.). In: Hydrogen: Its tech- nology and implications. Volume 4. Boca Raton, A81-11780 Local properties of three-dimensional separa- Fla., CRC Press, Inc., 1979, p. 79-148. 27 refs. tion lines. E. H. Hirschel (Messerschmitt-Bdlkow-Blohm, GmbH, A review is presented of applications of hydrogen in aircraft and Munich, West Germany) and W. Kordulla (Deutsche Forschungs- und aerospace. The costs of LH2 as fuel in commercial transport aircraft Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Theoretische are outweighed by the low energy requirements of LH2 powered Stromungsmechanik, Gottingen, West Germany). (Deutsche Gesell- vehicles in performing long range missions; a H powered SST can save schaft fur Luft- und Raumfahrt, Symposium fiber Stromungen mit more than 25% of fuel at speeds of Mach 2.7. The NASA flight Ablosung, Munich, West Germany, Sept. 19, 20, 1979, Paper research program and the CL-400 aircraft project are described along 79-063.t Zeitschrift fur Flugwissenschaften und Weltraumforschung, with turbojet engine development and hypersonic aircraft studies. vol. 4. Sept.-Oct. 1980, p. 295-307. 23 refs. Transport aircraft designs including supersonic transport fuels sys- Series expansions are used to examine the local properties of tem, engine characteristics, environmental factors, and aircraft flow in the vicinity of steady vortex-layer separation lines. The performance are discussed. A.T. absolute value for the tau-minimum line and the line of points of A81-11777 Simplified vortex models for slender lifting inflection are assumed to be close to the separation line. Experi- surfaces with leading edge separation (Vereinfachte Wirbelmodelle mental and computed boundary layers on ellipsoids and wings yield a fur schlanke Tragflachen mit Vorderkantenablosung). B. Wagner separation criterion for three dimensional shear flow. The distribu- (Dornier GmbH, Friedrichshafen, West Germany). Zeitschrift fur tion of shear stress components in chordwise direction on a swept Flugwissenschaften und Weltraumforschung, vol. 4, Sept-Oct 1980, tapered wing is discussed along with the compressible turbulent p. 267-279. 16 refs. In German. Bundesministerium fur Verteidigung boundary layer on a swept tapered wing with a break in the trailing Contract No. T/RF-41/80030/81429. edge. R.C.

16 A81-12024

A81-11782 Initial experience with methods to evaluate A81-11822* Status of knowledge of sonic booms. D. J. flight test characteristics with operational flight maneuvers (Erste Maglieri, H. W. Carlson, and H. H. Hubbard (NASA, Langley Erfahrungen mit Methoden zur Bewertungvon Flugeigenschaften inn Research Center, Hampton, Va.). Noise Control Engineering, vol. 15, Flugversuch mit operationellen Flugmanovern). E. Buchacker Sept.-Oct. 1980, p. 57-64. 137 refs. (Bundesamt fur Wehrtechnik und Beschaffung, Manching, West The effects of primary and secondary sonic boom carpets are Germany). Zeitschrift fur F lugwissenschaften und Weltraum- reviewed with reference to waveform characteristics and audibility, forschung. vol. 4, Sept.-Oct. 1980, p. 318-321. 9 refs. In German. role of the atmosphere, source characteristics, carpet measurements A method for evaluating flight test characteristics is presented and predictions, effects of aircraft maneuvers, and sonic boom that utilizes operational maneuvers to obtain quantitative and minimization. It is shown that primary booms which involve only qualitative statements. Frequency and systems analysis are used as propagation in the lower atmosphere are well predicted by means of quantitative methods, including power density spectra of control current methods and are amendable to minimization. V.L. column movement and of aircraft normal acceleration. Bode dia- grams of the transfer function between normal acceleration and ASM 1900 ,-/ Civil aviation safety. Ill - Prospects of im- control column movement are also presented. Clear and repeatabte provement. W. Tye. Aircraft Engineering, vol. 52, Oct. 1980, p. 2-4. qualitative analyses require that test exercises are well-defined by the The constraints on the improvement of aircraft safety levels are test engineer and reviewed with the pilot prior to flight. R.C. of two kinds, technological capability and cost. Both are temporary and tend to limit the rate at which safety improves rather than to set A81 11797 New BBC high-efficiency gas turbines (Neue any barrier. It is noted that the greatest good comes from applying BBC-Gasturbinen grosser Leistung). E.-O. Muller and F. Potz. safety efforts to newer aircraft or to aircraft in the design stage, as Energiewirtschaftliche Tagesfragen, vol. 30, Oct. 1980, p. 775-781. they will carry a increasing proportion of the traffic. B.J. In German. BBC has designed and built more than 450 single-shaft gas turbines of various types and has developed a program for further A81-11920 # Calculation of separated viscous flows on wing developing and improving compressors, combustion chambers, and profiles by a coupling approach (Calcul d'ecoulements visqueux turbines. The present paper deals with two latest developments - the decolles sur profils d'ailes par une approche de couplage). J. C. Le 13E gas turbine and Turbine-17, of 120 MW and 210 MW, Balleur and M. Neron (ONERA, Chatillon-sous-Bagneux, Hauts-de- respectively, and an efficiency of 0.32 and inlet temperature of 1000 Seine, France). (NATO, AGARD, Symposium on Computation of C, each. A distinctive feature of these turbines is the ability to Viscous-lnviscid Interactions, Colorado Springs, Colo., Sept. 29-Oct. operate with low quality fuels, such as crude oils and lean gases. V.P. 1, 1980.) ONERA, TP no. 1980-122, 1980. 16 p. 18 refs. In French. Research supported by the Direction des Recherches, Etudes et Techniques. A81-11818 Noise control design problems on air cushion The computation of viscous incompressible flows over single or vehicles and surface effect ships. M. E. Dvornak (Bell Aerospace multiple airfoils, with or without separation, is achieved using on the Textron, New Orleans, La.). Noise Control Engineering, vol. 14, one hand an inviscid flow calculation, with modified boundary Jan.-Feb. 1980, p. 12-23. 13 refs. conditions, and on the other hand a method providing calculation The acoustic design features, noise criteria, noise source-path- and coupling for boundary layers and wakes, within conditions of receiver interdependencies, and design approaches to noise control in strong viscous interaction. The inviscid flow is calculated with a surface effect ships are reviewed. Specific noise control design method of singularities, the numerics of which has been improved by approaches include low-frequency soft mounts, gas turbine/lift fan using both source and vortex distributions over profiles, associated silencers, air propeller shrouds and special propeller designs, acoustic with regularity conditions for the fictitious flows inside of the transmission loss and absorptive materials, and grouping of noise airfoils. The viscous calculation estimates the difference between sources and compartment relocation. V.L. viscous flow and inviscid interacting flow with a direct or inverse integral method, laminar or turbulent, with or without reverse flow. A81-11820 Prediction of changes in aircraft noise expo- The numerical method for coupling determines iteratively the sure. D. K. Holger (Iowa State University of Science and Technology, boundary conditions for the inviscid flow. For attached viscous layer Ames, Iowa). Noise Control Engineering, vol. 14, May-June 1980, p. regions an underrelaxation is locally calculated to insure stability. 119-126. 10 refs. Grant No. AF-AFOSR-77-3308. For separated or separating regions, a special semi-inverse algorithm The NOISEMAP computer program of the United States Air is used. Comparisons with experiments are presented. (Author) Force for generating contours of noise exposure measured by the day-night equivalent sound level (DNL) is briefly discussed. A method is proposed for approximate manual calculation of changes A81-11956 // Finite element analysis of natural and. forced in contours resulting from changes in operational data. The method flexural vibrations of rotor systems. Z. Dzygadlo. Journal of is limited to cases in which the general shape of the DNL contours at Technical Physics, vol. 21, no. 1, 1980, p. 63-75. 15 refs. a base does not change. For cases involving significant changes in The finite element technique is applied to analyze flexural flight paths or aircraft types, a full-scale base resimulation is vibrations, critical speeds, and forced vibrations of rotors on flexible recommended. V.L. supports. The equations of dynamic equilibrium of a deformable rotor element are derived, and the influence of the shear forces, the rotation of the element and the gyroscopic moments are taken into A81-11821 Community response to noise from a general account. Conditions relating the motion of a rigid element to a aviation airport. S. E. Birnie, F. L. Hall, and S. M. Taylor (McMaster deformable one are determined. An algorithm is presented for a University, Hamilton, Ontario, Canada). Noise Control Engineering, numerical analysis of vibration frequencies and modes, critical speeds vol. 15, July-Aug. 1980, p. 37-45. 6 refs. The paper provides relationships between noise level and and resonance characteristics. S.S. response variables through an analysis of social survey and physical data collected around a small general aviation airport. The responses A81-12024 ,7 Gyrostabilizers for inertial control systems investigated included annoyance, activity interference, health effects, (Girostabilizatory inertsial'nykh sistem upravleniia). L. A. Severov. and non-noise effects of general aviation traffic, such as fear of Leningrad, Izdatel'stvo Leningradskogo Universiteta, 1979. 152 p. 80 crashes, air pollution, aircraft lights, house vibration, and television refs. In Russian. interference. Results indicate a much higher response than that The book deals with gyrostabilizers for noncompensating predicted by Schultz (1978), e.g., at 30 NEF, Schultz predicts inertial control systems of unmanned flight vehicles. Particular approximately 15% highly annoyed, compared with 28% in this attention is given to the analysis and synthesis of the platform study. V.L. stabilization circuit and to the kinematic and dynamic description of'

17 A81-12078

gyrostabilizers with various platform suspension systems and various craft and Powered Lift Aircraft Forum, 5th, Amsterdam, Nether- gyroscope and stabilizing-engine arrangements. An analytical-design lands, Sept. 4-7. 1979. Paper. 28 p. (MBB-UD-277-79-0) solution is obtained for optimal gyrostabilizer regulators. The The paper deals with the design, manufacture, and acceptance possibility of using large amplification factors in the stabilizing testing of carbon fiber composite fan blades for the German-Dutch circuit is analyzed both from the viewpoint of the structural stability wind tunnel. The design, based on well-proven methods used in conditions linear multivariate systems and from the viewpoint of the aircraft and helicopter construction, involves a special blade attach- absolute stability conditions of systems with nonlinear elements. ment concept, precise anisotropic-stress and frequency analysis, and V.P. thermal computations. The overall static and dynamic behavior is verified by finite element calculations. Some aspects of the manu- A81-12078 A simple laser interferometer for wind tunnel facturing process are examined. V.P. flow visualisation. N. Pollock (Department of Defence, Aeronautical Research Laboratories, Melbourne, Australia). Journal of Physics E- A81-12097 Helicopter flight characteristics improvement Scientific Instruments, vol. 13, Oct. 1980, p. 1062-1066. 7 refs. through swept-tip rotor blades. H. Huber (Messerschmitt-Bolkow- A simple interferometer design based on a conventional wind Blohm GmbH, Munich, West Germany). European Rotorcraft and tunnel schlieren system is described. This new interferometer Powered Lift Aircraft Forum, 5th, Amsterdam, Netherlands, Sept. arrangement employs a laser light source, a lens which splits off the 4-7, 1979, Paper. 24 p. 13 refs. (MBB-UD-275-79-0) reference beam after test beam expansion and a lens and Lloyd The paper deals with a theoretical and experimental program mirror to recombine the two beams. The reference beam passes aimed at designing, developing, and flight testing two versions of through the test section but is contracted to a narrow waist and helicopter swept-tip rotor blade, and to verify the theoretically displaced well away from the model location. The design combines a predicted improvements in aerodynamic performance, flight me- number of characteristics which render it particularly useful for wind chanics, and rotor load characteristics. The effect of tip design tunnel tests. These characteristics include: simplicity, optical robust- parameters was studied systematically, using various angles of tip ness, low vibration sensitivity, modest coherence requirements and sweep and various center of mass locations. Flight tests with the BO ease of interferogram analysis. The main disadvantage is that only 105 hingeless-rotor helicopter at speeds of 300 km/h and corre- half the total field of view can be recorded on a single interferogram. sponding advancing tip Mach number of 0.90 confirmed the Test results, confirming the above advantages, are presented from an expected potential of swept-tip design. V.P. interferometer based on the 406 mm aperture schlieren system fitted to the Aeronautical Research Laboratories transonic wind tunnel. (Author) A81-12241 The accident/injury matrix - A tool for aircraft accident investigation. G. K. Brandon (USAF, School of Aerospace Medicine, Brooks AFB, Tex.). Aviation, Space, and Environmental A81-12094 A method of helicopter low airspeed estima- Medicine, vol. 51, Oct. 1980, p. 1147-1149. 9 refs. tion based on measurement of control parameters. A. Faulkner and An accident/injury matrix developed for use in automobile S. Attlfellner (Messerschmitt-Bolkow-Blohm GmbH, Munich, West accidents was modified for use in aviation. The matrix subdivides an Germany). European Rotorcraft and Powered Lift Aircraft Forum, accident into three temporal phases: preaccident, accident, and 5th, Amsterdam, Netherlands, Sept. 4-7, 1979, Paper. 19 p. postaccident. Each temporal phase is then further divided into (MBB-UD-276-79-0) specific factors: human, environmental, aircraft, and life support The pitot-static instrument fails as an indicator of airspeed at equipment. This form of analysis will assist in determining the chain low helicopter flight speeds and hover. Airspeed and side-slip of events in an accident and serve as a logical tool for developing indicators would be welcome to the pilot in these modes of flight. In future preventive strategies. Use of the matrix is explained and the present paper, an alternative indirect method of airspeed examples are given for each cell produced by the subdivisions. estimation is proposed which, based on measurement of control and (Author) some other control-system parameters, is particularly well suited for modern hingeless-rotor helicopters. A simplified mathematical model A81-12348 Airbus Industrie's heavenly twins - A310 and of the helicopter rotor is discussed. Analytical equations for the A300-600. M. Lambert. Interavia, vol. 35, Nov. 1980, p. 1001-1006. longitudinal and transverse aerodynamic velocity components are In engineering terms, the A310 is to be a 200-seater, preserving derived. Some results of a computer simulation are examined. V.P. the useful features of the A300, but introducing the latest technology in aerodynamics, materials, propulsion, and systems to achieve optimum fuel consumption and minimum operating costs. A81-12095 Model tests for an active rotor isolation The A300 fuselage can be relatively simply shortened without losing system. R. Mehlhose, M. Obermayer ((Messerschmitt-Bolkow-Blohm the wide cabin and the good freight capacity. The brand new wing GmbH, Munich, West Germany), and M. Degener (Deutsche For- has sufficiently improved efficiency to justify itself, but has been schungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut fur further refined to produce the present A310 wing. The materials and Aeroelastik, Gbttingen, West Germany). European Rotorcraft and systems improvements of the A310 are to be transferred back to the Powered Lift Aircraft Forum, 5th, Amsterdam, Netherlands, Sept A300-600. V.P. 4-7, 1979, Paper. 30 p. 12 refs. (MBB-278-79-0) The paper deals with an approach to the design of active A81-12349 Computerized flight management for fuel vibration control, where the rotor/transmission system is isolated saving. C. Bulloch. Interavia, vol. 35, Nov. 1980, p. 1010-1012. from the fuselage by special active isolation system with appropriate The efficient flight of an aircraft involves meticulous balancing disturbance rejection controllers: airframe vibration control by notch of weight (gravity), lift, thrust, and drag. All of these vary according insulator feedback of the transmitted isolator forces, and gearbox to the density of the air, and in turn the density depends on the local displacement control by integral feedback. In this concept, the conditions which may change significantly. With the advent of the isolator units are composed of electrohydraulic actuators and parallel ultra-compact airborne computer, it became possible to perform the springs for support of the fuselage and as fail safe devices. Tests power and indicated airspeed adjustments required by the local showed that extremely high vibration reduction can be achieved with conditions and to regulate the thrust settings and the flight control this concept. V.P. surfaces to ensure the most efficient use of fuel. In the present paper, some representative computerized flight management systems are discussed. V.P.

A81-12096 Development of wind tunnel fan blade made of composite materials. P. Wackerle and H. Weiss (Messerschmitt- A81-12350 Aerial survey photography. M. Grangier. Bolkow-Blohm GmbH, Munich, West Germany). European Rotor- Interavia, vol. 35, Nov. 1980, p. 1050-1054.

18 A81-12737

The development of aerial survey photography to its current tion techniques to control the equivalence ratio of the initial burning state is reviewed. The discussion covers such aspects of this field as zone. Lean equivalence ratios are maintained at high power engine aircraft, their equipment, flight techniques, data collecting tech- operating conditions for low NO(x) emissions, while near stoichio- niques (photographic emulsions, IR thermography, multispectral metric conditions are maintained at low power for good efficiency sensors, etc.), photogrammetric plotting, and orthophotomaps. The and low emissions of carbon monoxide and unburned hydrocarbons. uses and perspectives of aerial photography are examined. V.P. The goal of this program was to obtain a low level of N0(x) emissions at stratospheric cruise conditions; additional goals are to achieve the proposed 1984 EPA emission standards over the A81-12367 H An example of the transonic flow past a body landing/take off cycle and performance and operational requirements with a discontinuity in the contour curvature (Primer transzvukovo- typical of advanced aircraft engines. (Author) go obtekaniia tela s razryvom krivizny kontura). V. A. Ivanov and I. A. Chernov. Prikladnaia Matematika i Mekhanika, vol. 44, Sept.-Oct. A81-12619 Excitation of a circular array of cylinders with 1980, p. 950-952. 5 refs. In Russian. longitudinal slits. E. I. Veliev and V. P. Shestopalov (Akademiia The analysis deals with the exact solution of transonic equa- Nauk Ukrainskoi SSR, Institut Radiofiziki i Elektroniki, Kharkov, tions, which constitutes a generalization of the well-known self- Ukrainian SSR). (Radiofizika, vol. 23, no. 2, 1980, p. 202-212.) simulating solution describing the transonic flow past a convex Radiophysics and Quantum Electronics, vol. 23, no. 2, Aug. 1980, p. corner. The lines of flow and the velocity field in the transonic flow 144-151. 11 refs. Translation. past a convex corner are identified. V.P. The paper considers a circular array utilizing hollow circular cylinders with longitudinal slots instead of cylindrical rods. The array is excited by a magnetic current filament. Emphasis is placed on a A81-12476 // The emulsion chamber experiment on super- low-frequency mode of oscillations. Simple equations for the density sonic Concorde /Echos/. J. N. Capdevielle (Bordeaux I, Universite, of a surface current and radiation patterns are derived. V.T. Bordeaux, France), J. Iwai (Waseda University, Tokyo, Japan), T. Ogata, S. Toyoda (Tokyo, University, Tokyo, Japan), I. Ohta (Utsunomiya University, Utsunomiya, Japan), F. Fumuro (Kwansei A81-12703 Linear vortex theories of a profile and wing Gakuin University, Nishinomiya, Japan), R. Ih'ara, Y. Takahashi, and with air intake. V. M. Shurygin. (Akademiia Nauk SSSR, Doklady, T. Yanagita (Osaka University, Toyonaka, Japan). In: International vol. 250, no. 4, 1980, p. 829-833.) Soviet Physics - Doklady, vol. 25, Cosmic Ray Conference, 16th, Kyoto, Japan, August 6-18, 1979, Feb. 1980, p. 91-93. 5 refs. Translation. Conference Papers. Volume 6. Tokyo, University A method previously developed for the construction of a of Tokyo, 1980, p. 324-329. 8 refs. primary vortex sheet in the case of a profile is generalized to the A supersonic flight experiment to observe the energy spectrum construction of the primary vortex surface for a wing of infinite span of cosmic-rays not less than TeV and nuclear interactions above 50 (in particular, a wing with an arbitrary intake line). For the TeV has been carried out with an emulsion chamber. By the total construction of the primary vortex surface it is necessary to let the integrated exposure of about 200 hours at 15 km - 17km, more than shape of the wing in the planform excise from each source-sink on 400 events (gamma-rays and nucleons) with energies exceeding 700 the intake line a part of the vortex sheet corresponding to the GeV are observed, in agreement with existing primary spectrum. A source-sink on a plane, and then to continue the resulting attached preliminary analysis of nuclear events with energies greater than 60 sheet from the edges of the wing as free vortex sheets. B.J. TeV is given. One of them showed high P(T) production with A81-11704 Stable near-resonant states forced by perturba- extraordinarily high densities in the forward rapidity space. The tion heating in a simple baroclinic model. J. O. Roads (California, possibility of the second violation of scaling is brie"-/ discussed. University, La Jolla, Calif.). Journal of the Atmospheric Sciences, (Author) vol. 37, Sept. 1980, p. 1958-1967. 10 refs. NSF Grants No. A81-12608 /; Optimum design of axial flow gas turbine ATM-77-20602; No. OCE-74-24592; No. ATM-78-24003; No. OCE- stage. I - Formulation and analysis of optimization problem. II - 77-2282. The stationary nonlinear response to perturbation heating is Solution of the optimization problem and numerical results. S. S. Rao (Indian Institute of Technology, Kanpur, India) and R. S. Gupta calculated in a highly truncated, two-level baroclinic model. For (Punjab Engineering College, Chandigarh, India). ASME, Trans- certain values of the intrinsic parameters and forcing, multiple actions, Journal of Engineering for Power, vol. 102, Oct. 1980, p. equilibrium states exist. For a specific zonal and meridional wavelength, three equilibrium states are present: two are near a 782-797. 29 refs. resonant point and one is near the zonal forcing equilibrium. Only An attempt is made to optimize the efficiency and weight of an one of these is ever stable, namely, the one where the zonal wind is axial flow gas turbine stage by considering deflection, stress, and vibration aspects along with the aerodynamic requirements. The on the low side of the resonant point; this state has a relatively small zonal wind and relatively large stationary perturbations. The equi- optimization problem, formulated as a nonlinear programming librium point on the high side of resonance is unstable mainly due to problem, is solved by using the interior penalty function method in resonant instability and the equilibrium point near the forcing which the Davidon-Fletcher-Powell variable metric unconstrained equilibrium is unstable mainly due to baroclinic unstability. Differ- minimization technique with cubic interpolation method of one ent equilibria are obtained for each vector wavenumber because the dimensional minimization is employed. Numerical solution of the resonant value of the zonal wind decreases with decreasing wave- problem is presented along with the results of sensitivity analysis length. (Author) conducted about the optimum point. V.L. A81-12737 The status of rotor noise technology. R. P. A81-12609 ,

19 A81-12782

system and the Ogee tip have shown reasonable success in reducing the impulsive noise due to blade vortex interaction. Results obtained during model tests with these systems are also presented. R.C.

A81-12782 " Automation of aircraft gas-turbine power plants (Avtomatika aviatsionnykh gazoturbinnykh silovykh usta- novok). S. A. Gaevskii, F. N. Morozov, and lu. P. Tikhomirov. Moscow, Voenizdat, 1980. 248 p. 12 refs. In Russian. In the present book, extensive use of diagrams and illustrations is made to introduce the reader to the various aspects of aircraft gas-turbine engine automatic control. Some representative automatic control systems of such engines are discussed. V.P.

20 N81-10011

and connecting linkages are described as applicable in a 530 by 810 millimeter transonic tunnel. Author

N81-10008# TRW Systems and Energy. Redondo Beach. Calif. Engineering Sciences Lab. HOLOGRAPHIC INVESTIGATION OF SLENDER BODY VORTEX WAKES Final Report, 28 Jul. 1978 - 28 Mar. STAR ENTRIES 1980 F. D. Deffenbaugh and J. L. Jacoby Jul. 1980 79 p refs (Contract F3361 5-78-C-3028; AF Proj. 2307) (AD-A089496: TRW-32399-6002-UT-00: AFWAL-TR-80-3061) Avail. NTIS HC A05/MF A01 CSCL 20/4 N81-10001 Engineering Sciences Data Unit. London (England). The three dimensional vortex flow field behind slender missile DRAG INCREMENT DUE TO REAR FUSELAGE UPSWEEP configurations at high angle of attack was investigated using 1980 10 p laser holography. Holographic interferograms of the flow about (ESDU-80006; ISBN-0-85679-290-X) For information on two ogive cylinder models were recorded for low speed flows. availability of series, sub-series, and other individual data items, M less than .1. at angles of attack from 20 to 50 degrees. write NTIS. Attn: ESDU. Springfield. Va. 22161 Helium injected into the flow above the model was entrained Drag increment due to rear fuselage upsweep is predicted. into the entire vortex structure, and the three dimensional position The results may be applied to the calculation of cruise drag. of the core could not be determined from the interferograms. The research is relevant to military and civil transport aircraft Dual exposure holograms of the flow field seeded with 40- subcritical Mach numbers. ESDU (GRA) 100 micron glass microballoons were recorded using a pulsed ruby laser. Pairs of particles could not be easily identified in the reconstructed image and the three dimensional velocity field could N81-10O04*# National Aeronautics and Space Administration. not be measured. Surface pressures were measured and integrated Langley Research Center, Hampton. Va. to provide load distributions, normal and side force coefficients. ESTIMATION OF WING NONLINEAR AERODYNAMIC Roll angle was varied with angle of attack and tunnel conditions CHARACTERISTICS AT SUPERSONIC SPEEDS constant. Conditions of maximum vortex asymmetry were Harry W. Carlson and Robert J. Mack Nov. 1980 84 p refs determined from the measured pressure distributions. GRA (NASA-TP-1718: L-13589) Avail: NTIS HC A05/MF A01 CSCL 01A A computational system for estimation of nonlinear aerody- namic characteristics of wings at supersonic speeds was developed and was incorporated in a computer program. This corrected N81-10010# Royal Aircraft Establishment. Farnborough linearized theory method accounts for nonlinearities in the variation (England). Aerodynamics Dept. of basic pressure loadings with local surface slopes, predicts AN INVESTIGATION OF SCALE EFFECTS ON THE TRAN- the degree of attainment of theoretical leading edge thrust, and SONIC FLOW OVER SWEPT WINGS. PART 2: MEASURE- provides an estimate of detached leading edge vortex loadings MENTS ON A MODEL OF A VARIABLE-SWEEP STRIKE- that result when the theoretical thrust forces are not fully FIGHTER CONFIGURATION realized. T.M. 0. J. Weeks and J. Hodges London Dec. 1977 127 p tefs Supersedes RAE-TR-77184: ARC-37815 (ARC-R/M-3842-PI-2: BR73152: RAE-TR-77184: ARC-37815) N81-10005*# National Aeronautics and Space Administration. Avail: NTIS HC A07/MF A01: HMSO £14 PHI Langley Research Center, Hampton. Va. Measurements of forces and wing pressures were made on A FAN PRESSURE RATIO CORRELATION IN TERMS OF a wing plus body half-model of a variable sweep strike fighter MACH NUMBER AND REYNOLDS .NUMBER FOR THE configuration at Mach numbers between 0.6 to 0.825 and at LANGLEY 0.3 METER TRANSONIC CRYOGENIC TUNNEL Reynolds numbers in the range 2.3 X 10 to the 6th power to Pierce L. Lawing and Charles L. Ladson Nov. 1980 21 p 19 X 10 to the 6th power. Results were obtained with the refs wings swept at both 25 deg and 40 deg. The data were analyzed (NASA-TP-1752: L-13713) Avail: NTIS HC A02/MF A01 to show the effects of changes in Reynolds number, and in the CSCL 01A location of transition, on the transonic flows over the upper Calibration data for the two dimensional test section of the surface of the wing at high incidence. For the 25 deg sweep Langley 0.3 Meter Transonic Cryogenic Tunnel were used to configuration results are described which are consistent with develop a Mach number-Reynolds number correlation for the those observed on the transport aircraft wing. The 40 deg sweep fan pressure ratio in terms of test section conditions. Well configuration gave examples of scale effect which were essentially established engineering relationships combined to form an three dimensional in nature and which persisted up to full scale equation which is functionally analogous to the correlation. A Reynolds numbers. Author (ESA) geometric loss coefficient which is independent of Reynolds number or Mach number was determined. Present and anticipated N81-10011# Von Karman Inst. for Fluid Dynamics, Rhode-Saint- uses of this concept include improvement of tunnel control Genese (Belgium). schemes, comparison of efficiencies for operationally similar wind ANALYTICAL CHARACTERISTICS METHODS: APPLICA- tunnels, prediction of tunnel test conditions and associated energy TIONS usage, and determination of Reynolds number scaling laws for R. Stuff (DFVLR. Goettingen. West Germany) 1980 57 p refs similar fluid flow systems. T.M. Presented at Von Karman Inst. Lecture Ser. on Mathematical Methods in Fluid Mech.. Rhode Saint Genese. Belgium. 25- N81 1OOO7# Aeronautical Research Labs., Melbourne (Australia). 29 Feb. 1980 Submitted for publication AN INTRODUCTION TO DYNAMIC DERIVATIVES (3) (VKI-Preprint-1980-10) Avail: NTIS HC A04/MF A01 METHODS OF OSCILLATING MODELS IN PITCH AND YAW The prerequisites for application of the analytical characteris- IN A 530 BY 810 MILLIMETRE TRANSONIC WIND tics method include analytical descriptions of the geometry of TUNNEL wave fronts and rays, and analytical solutions of the wave equation G. F. Forsyth Apr. 1979 45 p refs of the potential equation for supersonic flow. The latter are applied (ARL/Aero-Note-390: AR-001-724) Avail: NTIS as initial solutions to the analytical characteristics method. HC A03/MF A01 Examples of application range from unsteady subsonic to steady Mechanisms are considered which allow models to be supersonic flow, from theoretical predictions (o the evaluation oscillated in pitch and yaw during wind tunnel tests to measure of the flow field from near field wind tunnel test data. dynamic derivatives. Types of pivots, motion producing linkages Author (ESA)

21 N81-10012

N81-10012# National Aerospace Lab.. Amsterdam (Netherlands). and a measure of the circulation distribution in the wake of the Flight Div. wing were computed. Author (ESA) IN-FLIGHT MEASUREMENT OF AERODYNAMIC LOADS ON CAPTIVE STORES. EQUIPMENT AND RESULTS N81-10016# Royal Aircraft Establishment, Farnborough G. J. Alders 17 Apr. 1979 12 p refs Presented at AGARD (England). Flight Mech. Panel Symp. on Missile System Flight Dyn.. London. THEORETICAL DETERMINATION OF SUBSONIC OSCIL- 21-24 May 1979 LATORY AIRFORCE COEFFICIENTS FOR FIN-TAILPLANE (NLR-MP-79013-U) Avail: NTIS HC A02/MF A01 CONFIGURATIONS A force balance store was developed, consisting of a D. E. Davies London HMSO Sep. 1979 237 p refs support structure to be mounted on a 14 in. bomb rack, a load (RAE-TR-79125: RAE-Struct-BF/B/0794: BR79125) Avail: measuring balance and a shape representing the store to be NTIS HC A11/MF A01 analyzed. The shape is replaceable. A series of flight tests with Linearized equations of potential flow are solved numerically two different force balance store shapes was carried out with for the loadings for oscillation at general frequency in any an NF-5 aircraft. The store was mounted in the normal captive antisymmetric modes, and the generalized aerodynamic coef- position as well as 0.15 m below. The results of the measurements ficients obtained Approximation to the loadings are taken as are compared with data from other sources, such as wind tunnel linear combinations of basis functions. The condition satisfied results. Predictions, made with the computer model and using by the loadings at the junction of the fin and half tailplanes is the aerodynamic data obtained with the force balance store are imposed on the approximations and the variational principle of compared with actual drop test results. The excellent agreement Flax is applied to get the coefficients in the said linear combina- indicates that in flight measurement of airloads on captive stores tions. The procedure is programmed in ICL 1900 FORTRAN. is a valuable tool for a better determination of the safe release Results obtained using the program on a number of examples envelope of external stores. Author (ESA) are given. Author (ESA)

N81-10O13# Aeronautical Research Inst. of Sweden, Stockholm. N81-10O17# European Space Agency, Paris (France). Aerodynamics Dept. ANALYSIS OF CALCULATED THREE-DIMENSIONAL A COMPREHENSIVE EVALUATION AND ANALYSIS OF INVISCID FLOW FIELDS WITH EMBEDDED SHOCK WAVES TRANSONIC FLOW CALCULATIONS ON THREE RELATED (PRESENTATION OF A FIELD SOLUTION). PART 1 WING-BODY CONFIGURATIONS Claus Weiland and Hans-Juergen Thies Jul. 1979 52 p refs Georg Drougge, N. Agrell, and S. Hedman 1979 40 p refs Transl. into ENGLISH of "Anal. Berechneter Dreidimensionaler (Contract FMV-F-K-82223-76-001-21-001) Reibungsfreier Stroemungsfelder mil Eingebetteten Verichtungs- (FFA-TN-AU-1418-PT-1) Avail: NTIS HC A03/MF A01 stoessen (Darstellung einer Feldoesung) Teil 1", Rept. DFVLR-FB- The design of a wing-body combination where an inverse 78-09 DFVLR. Cologne, Apr. 1978 Original report in GERMAN procedure analysis based on the transonic small disturbance previously announced as N79-30155 theory was studied. Features of aerodynamic interest were found. (ESA-TT-558: DFVLR-FB-78-09) Avail: NTIS HC A04/MF A01: This led to modifications in the use of the numerical method in DFVLR. Cologne DM 27.90 the wing-body design. The modified wing-body combination was Flow fields around a number of different body contours, again tested and the results analyzed further. It was concluded and calculated by means of a finite difference procedure are that the inverse method can be a powerful design tool and that analyzed. The investigated fields are three dimensional in general. in any case for moderate aspect ratios the concept of a wing The analysis is carried out with the air of characteristics, as formed from two dimensional profiles can be replaced by the streamlines, lines of constant static pressure and static density, concept of a wing formed from two surfaces. Author (ESA) and with the velocity vectors at the gridpoints in planes phi = const. Planes z = const lines of constant cross flow Mach number and the velocity vectors of the crossflow at the gridpoints are N81-10014# National Aerospace Lab.. Amsterdam (Netherlands). presented. The interval of freestream Mach number considered Incompressible Aerodynamics Div. is 1.4 M sub infinity < or = M < or = 3. and the range of BOUNDARY LAYER MEASUREMENTS ON A TWO- angle of attack alpha is up to 20 deg. The quality of the finite DIMENSIONAL WING WITH FLAP difference solution used is demonstrated by comparison with B. vandenBerg Jan. 1979 110 p refs experimental data. The accuracy attained especially for the (Contract NIVR-1812) detection of the position and the contour of embedded shocks (NLR-TR-79009-U) Avail: NTIS HC A06/MF A01 is very good. Author (ESA) A wind tunnel experiment was performed on a wing flap configuration designed to prevent flow separations. The measure- ments comprised surface pressure measurements, boundary layer N81-10018# European Space Agency. Paris (France). and wake traverses, and surface flow visualizations. Three angles ANALYTICAL ESTIMATION ON NONLINEAR LONGITU- of attack were applied and two widths of the gap between DINAL CHARACTERISTICS OF WINGS WITH SMALL AND wing and flap, with mixing of wing wake and flap boundary MODERATE ASPECT RATIO BY THE VORTEX LATTICE layer occurring with the smaller gap. The flow phenomena were METHOD IN INCOMPRESSIBLE FLOW sufficiently well described by these measurements to make detail Wolfgang Schroeder Jan. 1980 80 p refs Transl. into ENGLISH comparisons possible with calculation methods for the viscous of 'Berechnung der nichtlinearen Beiwerte von Fluegeln mil flow around multielement airfoils. Author (ESA) kleinem u. mittlerem Seitenverhaeltnis dem Wirdbelleiterverfahren in inkompressibler Stroemung', DFVLR. Brunswick Report N81-10015# Royal Aircraft Establishment. Farnborough DFVLR-FB-78-26. Sept. 1978 Original report in GERMAN (England). previously announced as N79-30161 Original German report FLOW MEASUREMENTS IN THE WAKE OF A WING FITTED available from DFVLR. Cologne DM 31,80 WITH A LEADING-EDGE ROOT EXTENSION (STRAKE) (ESA-TT-585: DFVLR-FB-78-26) Avail: NTIS P. J. Butterworth London HMSO Sep. 1979 40 p refs HC A05/MF A01 (RAE-TR-79120: RAE-Aero-3464: BR72779) Avail: NTIS A nonlinear vortex-lattice method is described applying a HC A03/MF A01 force-free condition to the vortex sheet given the trailing-, side- In a low-speed wind tunnel, measurements were taken of and leading edges, respectively. In extensive test runs various the velocity vector in the flow field behind the wing of a combat influences on the numerical stability of the iterative rolling up aircraft model. The wing was fitted with a leading-edge root process were studied such as the force free condition of the extension (strake) and could have either a plain leading edge or wake, the number of horseshoe vortices, the panel distribution a deployed slat outboard. Four flow investigations were made: along span and chord, the representation of the wakes by chains at three angles of incidence with the plain leading edge and at of straight vortex elements of different length and number, and one angle of incidence with the slat deployed. The distribution the introduction of an artificial friction parameters. Because of of the total head deficit, the streamwise component of vorticity. numerical difficulties the slender delta wing itself could not be

22 N81-10026

treated completely. These numerical difficulties resulting from agencies/departments and industry organizations participating in the singular behavior of line vortices are described and ways of this effort are identified. Program schedule with milestones is overcoming them are suggested. Author (ESA) presented. Program management and funding requirements are also identified. GRA N81-10O19*# Human Resources Research Organization. Alexandria. Va. N81-10023# Battelle Columbus Labs.. Ohio. CIVIL HELICOPTER WIRE STRIKE ASSESSMENT STUDY. EVALUATION OF SAFETY PROGRAMS WITH RESPECT TO VOLUME 2: ACCIDENT ANALYSIS BRIEFS Final Report THE CAUSES OF GENERAL AVIATION ACCIDENTS. Clyde H. Tuomela and Mark F. Brennan Oct. 1980 221 p VOLUME 2: APPENDICES (Contract NAS2-10505) T. M. Connor and C. W. Hamilton May 1980 266 p (NASA-CR-152390: FR-MTRD(CA)-80-13-Vol-2) Avail: NTIS (Contract DOT-FA78WA-4159) HC A10/MF A01 CSCL 01C (AD-A089181: FAA-ASP-80-2A) Avail: NTIS A description and analysis of each of the 208 civil helicopter HC A12/MF A01 CSCL 01/2 wire strike accidents reported to the National Transportation Safety The extent to which the Federal Aviation Administration (FAA) Board (NTSB) for the ten year period 1970-1979 is given. The safety programs wwere aligned with the causes of general aviation accident analysis briefs were based on pilot reports. FAA accidents was determined. The data base used consisted of a investigation reports, and such accident photographs as were total of 30.592 general aviation accident records compiled by made available. Briefs were grouped by year and. within year, the National Transportation Safety Board (NTSB) from by NTSB accident report number. T.M. 1971 through 1977. Analysis of these records was made with respect to NTSB-cited cause/factors. The FAA programs N81-10O20*# Crash Research Inst.. Tempe. Ariz. implemented during the study time period and pertaining to safety SYSTEMS ANALYSIS OF THE INSTALLATION. MOUNTING. were also included in this study. R.C.T. AND ACTIVATION OF EMERGENCY LOCATOR TRANSMIT- TERS IN GENERAL AVIATION AIRCRAFT Final Report David S. Hall 10 Jan. 1980 218 p (Contract NAS5-25444) (NASA-CR-160036: CRI-7846-14) Avail: NTIS N81-10O24# Terrestrial Environmental Specialist, Inc.. Phoenix. HC A10/MF A01 CSCL QIC N.Y. A development program was developed to design and improve HANDBOOK ON BIRD MANAGEMENT AND CONTROL the Emergency Locator Transmitter (ELT) transmitter and to Final Report. Aug. 1977 - Feb. 1979 improve the installation in the aircraft and its activation subsystem. Vincent J. Lucid and Roy S. Slack Mar. 1980 188 p refs There were 1135 general aviation fixed wing aircraft accident (Contract F08635-77-C-0377) files reviewed. A detailed description of the damage to the aircraft (AD-A089009: AFESC/ESL-TR-80-1) Avail: NTIS was produced. The search aspects of these accidents were studied. HC A09/MF A01 CSCL 06/6 As much information as possible about the ELT units in these This handbook was prepared to provide information to Air cases was collected. The data should assist in establishing Force pest managers on hazardous and pest bird control. It installation and mounting criteria, better design standards for discusses bird control in hangars, on airfields, and at other base activation subsystems, and requirements for the new ELT system locations. A systematic approach for surveying and determining design in the area of crashworthiness. T.M. control methods for bird problems is provided and legal aspects of bird control are discussed. Chapters two through eight have N81-I0021*jjl National Aeronautics and Space Administration. review questions to help the pest manager evaluate his proficiency Ames Research Center. Moffett Field. Calif. in each subject area. A slide/tape presentation was prepared NASA AVIATION SAFETY REPORTING SYSTEM Quarterly corresponding with information in this handbook. Copies are Report, 1 Jan. - 31 Mar. 1979 available for loan from Major Command Entomologists and the Apr. 1980 34 p refs Prepared in cooperation with Battelle Air Force Engineering and Services Center. GRA Columbus Labs.. Mountain View. Calif. (NASA-TM-81225: A-8311: QR-11) Avail: NTIS N81-10025# Societe Nationale Industrielle Aerospatiale. Les HC A03/MF A01 CSCL 01 C Mureaux (France). A comprehensive study of near midair collisions in terminal APPLICATIONS OF PYROTECHNIQUES IN AVIATION [DES airspace, derived from the ASRS database is presented. A selection APPLICATIONS DE LA PYROTECHNIE DANS LE DOMAINE of controller and pilot reports on airport perimeter security, AERONAUTIQUE] unauthorized takeoffs and landings, and on winter operations is S. Morlan Paris 1979 6 p In FRENCH Presented at Congr. presented. A sampling of typical Alert Bulletins and their responses on Explosifs et Pyrotech.: Appl. Spatiales. Toulouse. 22-25 Oct. is presented. T.M. 1979 (SNIAS-792-422-103) Avail: NTIS HC A02/MF A01 N81-10022# Federal Aviation Administration. Atlantic City. NJ. The cutting of canopies and windows in aircraft to permit Technical Center. abandonment in emergencies is discussed. The advantages of ENGINEERING AND DEVELOPMENT PROGRAM PLAN pyrotechnic logic circuits are presented. The use of pyrotechnics AIRCRAFT CRASHWORTHINESS for opening cabin windows in a prototype Corvette aircraft is C. A. Caiafa and Lawrence M. Neri Jun. 1980 55 p refs illustrated. Possible applications for assisting in ground evacuations (AD-A089431: FAA-CT-80-166: FAA-EO-18-6) Avail: NTIS in civilian transport aircraft are mentioned. Author (ESA) HC A04/MF A01 CSCL 01/2 The Aircraft Crashworthiness Program^ Plan is designed to reduce or prevent aircraft occupants from incurring serious or N81-10026# National Technical Information Service, Springfield, fatal injuries in a survivable crash impact accident by incorporating Va. crashworthy design features into the initial stages of fixed-wing SEARCH AND RESCUE METHODS AND EQUIPMENT. A and rotary-wing aircraft development. It describes a 5 year BIBLIOGRAPHY WITH ABSTRACTS Progress Report. development program for both airplanes and rotorcraft. It identifies 1964 - Jun. 1980 five major subprogram areas for study and- analysis to ac- Edith Kenton Jul. 1980 269 p Supersedes NTIS/PS-79/0649: complish the programs goals: (1) Airframes: (2) Cabin safety: NTIS/PS-78/0539 (3) Fuel system protection: (4) Emergency evacuation system: (PB80-812837: NTis/PS-79/0649: NTIS/PS-78/0539) Avail: and (5) Standards, criteria, and procedures. The plan emphasizes NTIS HCS30.00/MFS30.00 CSCL06G use of available background data, development of analytical Maritime and aviation search and rescue are evaluated in techniques, validation of analytical techniques, validation of data approximately 262 abstracts. Search and rescue planning, locating to determine feasibility/acceptability and transmittal of appropri- equipment, rescue beacons, communication devices, specialized ate data for consideration as the basis for regulation, standards, aircraft and their components, and searching strategies are etc. The federal aviation administration groups, other government discussed. GRA

23 N81 -10027

N81-1OO27# National Technical Information Service, Springfield. The first section of this report contains statistics on aircraft Va. operations, by user category for 30 airports for selected days in BIRO STRIKES AND AVIATION SAFETY. CITATIONS FROM June. July and August 1978. Using the series of tables and THE NTIS DATA BASE Progress Report. 1964 - Jun. 1980 graphs on Atlanta as an example, the data should be interpreted Guy E. Habercom. Jr. Jul. 1980 117 p Supersedes NTIS/PS-79/ as described in the following paragraphs. First, note that the 0753: NTIS/PS-78/0694 data used for generating the statistics in the table included all (PB80-812944; NTIS/PS-79/0753: NTIS/PS-78/0694) Avail: operations occurring in Atlanta during August 1978. Local time NTIS HC S30.00/MF $30.00 CSCL 01B in this case would be equivalent to eastern daylight time. Hazards to aircraft created by engine ingestion or airplane Aircraft operations occurring between midnight and 1:00 a.m. interception of birds are investigated in these Government are counted in time slot zero. Similarly, activity occurring between sponsored research reports. Bird damage assessment, structural 12:00 noon and 1:00 p.m. is assigned to time slot 12:00. The strengthening, windshield design, and bird tracking and dispersal second part of this report consists of six tables and seven graphs methods are studied. This updated bibliography contains which portray total daily aircraft departures and average hourly 107 citations. 17 of which are new entries to the previous aircraft departures by equipment type for three cities: Kansas edition. GRA City, Missouri: Omaha. Nebraska: and St. Louis, Missouri. This part of the report may be regarded as exploratory in nature. N81-10028# National Transportation Safety Board. Washington. The tables and graphs provide, for the first time, information on D. C. Bureau of Technology. departures by equipment type, by hour of the day. Previously, ANNUAL REVIEW OF AIRCRAFT ACCIDENT DATA, U.S. such information was available for air carrier operations at the GENERAL AVIATION CALENDAR YEAR 1978 Summary top 100 air carrier airports. The information in this section includes Report operations by all user categories. GRA 20 May 1980 209 p (PB80-201916: NTSB-ARG-80-1) Avail: NTIS N81-10O32# Mitre Corp.. McLean. Va. HC A10/MF A01 CSCL01B ANALYSIS OF POTENTIALLY CORRECTABLE LANDING A summary of aircraft accidents which occurred in U.S. DELAYS AT ATLANTA general aviation operations during the calendar year 1978 is Bela P. Collins Nov. 1979 65 p refs given. It includes an analysis of accident data providing an (Contract DOT-FA80WA-4370) overview, types of accidents, accident causal factors, kind of (AD-A089408; MTR-79W00415: FAA-EM-79-23) Avail: NTIS flying, and conclusions: a statistical compilation of accident HC A04/MF A01 CSCL 17/7 information presented in the form of accident and rate tables, The Local Flow Traffic Management order (DOT/FAA analytic tables, injury tables and cause/factor tables. In 1978. 7110.72). dated 15 November 1976. provided for the establish- there were 4,494 total general aviation accidents. 793 of which ment of local procedures, at designated airports (16 initially), were fatal. Included in the total number of accidents are that would assist aircraft operators in minimizing fuel usage. 63 collisions between aircraft. GRA These local procedures would be predicted on the aircraft performing a profile descent in conjunction with en route metering. This report presents the results of a field data collection and N81 1O029# Automation Industries. Inc.. Silver Spring. Md. analysis of arrival traffic flows into the Atlanta-Hartsfield Vitro Labs. Div. International Airport. The purpose of the analysis was to RECOMMENDED SHORT-TERM ATC IMPROVEMENTS FOR quantify the effect of traffic flow on runway utilization and to HELICOPTERS. VOLUME 2: RECOMMENDED HELICOP identify avoidable delays. Recommendations to improve the flow TER ATC TRAINING MATERIAL Final Report. Aug. 1979 - of traffic are also discussed. GRA Apr. 1980 Tirey K. Vickers and D. J. Freund Nov. 1980 82 p N81-10034# IIT Research Inst.. Annapolis. Md. (Contract DOT-FA79WA-4279) THE DISCRETE ADDRESS BEACON SYSTEM/AIR TRAFFIC (AD-A089441: FAA-RD-80-88-Vol-2) Avail: NTIS CONTROL RADAR BEACON SYSTEM/ATCRBS IFF MARK HC A05/MF A01 CSCL 17/7 12 SYSTEM (DABS/ATCRBS/AIMS) PERFORMANCE The recommended Short Term ATC Improvements for PREDICTION MODEL Final Report Helicopters are documented in three volumes. This volume C. Randall Crawford and C. Wayne Ehler Apr. 1980 80 p provides complete training material for helicopter ATC. It contains refs major sections on Helicopter Capabilities and Limitations, on (Contracts F19628-78-C-0006: DOT-FA70WAI-175: AF Proj. Helicopter Navigation and on Helicopter Control Procedures. 649E) GRA (AD-A089440: ECAC-PR-77-061: FAA-RD-79-88) Avail: NTIS HC A05/MF A01 CSCL 17/9 N81 10030$ Automation Industries. Inc.. Silver Spring. Md. The Discrete Address Beacon System (DABS) is to be RECOMMENDED SHORT-TERM ATC IMPROVEMENTS FOR gradually phased into the existing Air Traffic Control Radar Beacon HELICOPTERS. VOLUME 3: OPERATIONAL DESCRIPTION System (ATCRBS) in the 1980's. The DABS selective address OF EXPERIMENTAL LORAN-C FLIGHT FOLLOWING (LOFF) feature is designed to alleviate the ATCRBS problems of IN THE HOUSTON AREA Final Report over-interrogation and synchronous garble. The FAA requested Tirey K. Vickers and D. J. Freund Apr. 1980 32 p that the Electromagnetic Compatibility Analysis Center (ECAC) (Contract DOT-FA79WA-4279) develop a computer model with the capability to predict mutual (AD-A089385: FAA-RD-80-88-Vol-3) Avail: NTIS interference arising in a mixed secondary-surveillance radar HC A03/MF A01 CSCL 17/7 environment. The nature of the DABS interrogation schedule The recommended Short Term ATC Improvements for required that the model be a time-event store simulation. The Helicopters are documented in three volumes. This volume (3) model inputs are selected from the ECAC data base and consist provides the complete Operational Description of the Experimental of the characteristics of a ground and air deployment of sensors Loran Flight Following (LOFF) in the Houston Area. It describes and transponders. Detailed characteristics of a sensor-of-interest both airborne and ground components and states the objectives (So) are among the inputs. The model output is primarily a that are being sought in the experiment. GRA record of the events that were predicted to occur during a simulation period. The performance of each transponder is N81-1O031# Federal Aviation Administration. Washington. D. C. described by its reply history during the time in which the Office of Aviation Policy. equipped aircraft is in the So mainbeam. The fruit rate at the HOURLY AIRPORT ACTIVITY PROFILES: 30 AIRPORTS So is predicted, and the performance of the subject sensor is BY USER. 3 AIRPORTS BY USER AND EQUIPMENT TYPE. represented by the results of DABS transactions and ATCRBS SELECTED DAYS IN JUNE. JULY AND AUGUST. 1978 target evaluations. Other summary outputs are available from 1980 156 p the model, including interrogation rates, sidelobe suppression rates, (AD-A089450: FAA-AVP-80-7) Avail: NTIS and the identity of equipments that cause observable interfer- HC A08/MF A01 CSCL 01/5 ence. GRA

24 N81 10043

N81-10036# Automation Industries, Inc.. Silver Spring, Md. were arranged in the order of ascending cost, to learn as much Vitro Labs. Div. as possible about the subject as quickly as possible and to PROPOSED ATC SYSTEM FOR THE GULF OF MEXICO. weed out or revise impractical solutions before they reach a HELICOPTER OPERATIONS DEVELOPMENT PROGRAM more expensive stage of evaluation or development. A detailed Final Report simulation program was prepared using a modified factorial design D. J. Freund and T. K. Vickers Nov. 1979 48 p in order to isolate the effects of changes in various parameters. (Contract DOT-FA79WA-4279) GRA (AD-A089430: FAA-RD-80-85) Avail: NTIS HC A02/MF A01 CSCL 17/7 N81 10039# NT Research Inst. Chicago. III. A helicopter ATC system for the Gulf of Mexico is set forth. IMPACT OF THE DISCRETE ADDRESS BEACON SYSTEM It embodies a concept of evolutionary growth in four phases: (DABS) ON AIR TRAFFIC CONTROL RADAR BEACON (1) The Present System period of use 1980 - IFR navigation is SYSTEM (ATCRBS) PERFORMANCE IN SELECTED DEPLOY- obtained primarily with LoranC, or VLF/OMEGA. Back up systems MENTS Final Report are ADF and Airborne Weather Radar. VOR/DME is used over T. Keech and G. Fleming Apr. 1980 57 p refs land. ACT is by procedural control ans separation standards (Contract F19628-78-C-0006) because no radar or other surveillance system is available off (AD-A089611: FAA-RD-80-93: ECAC-CR-79-127) Avail: NTIS shore: (2) LOFF Loran c Flight Following Period of Evaluation HC A04/MF A01 CSCL 17/7 1981 - The LOFF system is placed in operation for experimentation A computer analysis was conducted to investigate the effect and evaluation. While ATC is still performed by procedural control. of the proposed Discrete Address Beacon System (DABSI on LOFF will assist ground controllers by reducing workload, the Air Traffic Control Radar Beacon System (ATCRBS) in a improving flexibility, etc. Experiments will also be performed on future (1982) Los Angeles, CA. air traffic environment. The secondary radar systems ATCRBS VLATME to provide surveill- performance of ATCRBS was examined at two sites, both with ance: (3) Augmented LOFF Period of use 1983 and beyond - (a) the existing all-ATCRBS ground environment and (b) a IFR helicopters will be able to fly direct, offset or segmented mixed ATCRBS/DABS ground environment (using various levels RNAV routes. ATC will be essentially equivalent to the NAS. of DABS channel activity). It was observed that, in general. Navigation by Loran C will expand. Surveillance will be by LOFF DABS operations will not affect the ability of ATCRBS interrogators and/or secondary radar. Area of control will be 1.500 to 10.000 to perform their air traffic control function of reliably detecting over entire Gulf, and 4 RNAV Traffic Control Period of use aircraft. GRA 1985 and beyond - IFR helicopters will be able to use any of a number of certified navigation systems. ATC systems will adapt to varying accuracies of these systems. ATC will be based N81-10041# Automation Industries, Inc., Silver Spring, Md. on surveillance provided by aircraft reporting of position informa- Vitro Labs. Div. tion and/or secondary radar. Separation standards will be reduced RECOMMENDED SHORT-TERM ATC IMPROVEMENTS FOR and be equivalent to Northeast Corridor. GRA HELICOPTERS. VOLUME 1: SUMMARY OF SHORT TERM IMPROVEMENTS Final Report N81-10037$ Automation Industries, Inc.. Silver Spring. Md. Tirey K. Vickers and D. J. Freund Aug. 1980 48 p Vitro Labs. Div. (Contract DOT-FA79WA-4279) PRELIMINARY TEST PLANS OF ATC CONCEPTS FOR (AD-A089521: FAA-RD-80-88-1) Avail: NTIS LONGER TERM IMPROVEMENT HELICOPTER DEVELOP- HC A03/MF A01 CSCL 17/7 MENT PROGRAM Final Report A summary report is made of all improvements studied. D. J. Freund and Tirey K. Vickers May 1980 50 p refs Improvements are categorized as to those that can be re- (Contract DOT-FA79WA-4279) commended for immediate operational consideration or use and (AD-A089407: FAA-RD-80-87) HC A03/MF A01 CSCL those that require limited short term simulation or test. The 17/7 recommendations for immediate use include: (1) Helicopter ATC Test and simulation planning is documented for longer-term training material. (2) Operational Description of Loran Offshore improvements in helicopter ATC concepts, which are classified Flight Following (LOFF). (3) Recommendations concerning military into the following categories: (1) Offshore Route Structure in training routes and (4) Survey data for use in Gulf communications the Gulf of Mexico, (2) Secondary Radar, (3) Analysis of Navigation and route structure planning. The recommendations for short Errors in the Gulf. (4) Offshore Surveillance and Communica- term simulation include: (1) Dual waypoint holding patterns. (2) tions to 300 NM Range. (5) Real-Time Reporting of Aircraft- other holding patterns and (3) shortened entry procedures for Derived Position. (6) VHP Communications Study in the CONUS, intercepting final approach path. GRA (7) ATC Implications of Alternate Airports for Helicopters, and (8) Wake Vortex Separation. GRA N81-10O43# Deutsche Forschungs- und Versuchsanstalt fuer N81-10038# Automation Industries. Inc., Silver Spring, Md. Luft- und Raumfahrt, Brunswick (West Germany). Abteilung Vitro Labs. Div. Instrumentierung und Anthropotechnik. RECOMMENDATIONS FOR SHORT-TERM SIMULATION OF ANALYSIS OF THE FUNCTION PRINCIPLE AND OPER- ATC CONCEPTS. HELICOPTER OPERATIONS DEVELOP- ATIONAL ASSESSMENT OF AN ONBOARD GLIDEPATH MENT PROGRAM Final Report GUIDANCE SYSTEM FOR VISUAL APPROACHES (VISUAL D. J. Freund and T. K. Vickers Feb. 1980 44 p APPROACH MONITOR (VAM) (Contract DOT-FA79WA-4279) Josef Thomas and Helmut Stein Oct. 1979 107 p refs In (AD-A089435: FAA-RD-80-86) Avail: NTIS GERMAN: ENGLISH summary Report will also be announced HC A03/MF A01 CSCL 01/5 as translation (ESA-TT-655) A number of recommendations from a previous helicopter (DFVLR-FB-79-38) Avail: NTIS HCA06/MFA01; DFVLR. air traffic control (ATC) study (See Report FAA-RD-78-150) were Cologne DM 20,00 examined. Those which appeared to have potential for early The visual approach monitor. VAM, a head-up display system implementation were selected for further testing. The selected for manual approach was analyzed as regards its functioning recommendations included: (1) dual-fix holding patterns to save principles and associated error characteristics. System simulations airspace; (2) speed control procedures and short approach paths and flight tests were carried out with special emphasis on to save fuel; (3) various methods of reducing separation in order performance and stability studies. Experimental comparisons to increase airport or heliport capacity. Under item 3 above, a between VAM guided and unaided visual approaches revealed rationale for utilizing existing parallel approaches of helicopters no significant advantages for VAM as far as flight path accuracy and CTOL aircraft was presented for consideration. Extensive is concerned. However. VAM performed significantly better with use of flight simulation and ATC simulation was recommended regard to variances and extreme values for nearly all flight guidance in order to reduce the time and cost of evaluating the potential parameters. Its overall performance was found to be comparable improvements. The steps of the recommended simulation program to that of the instrument landing system. Author (ESA)

25 N81-10044

N81-10O44# Royal Aircraft Establishment. Farnborough Robert Hippler May 1980 80 p Sponsored by NASA and (England). NTIS CONTRIBUTIONS TO THE UNITED KINGDOM MI- (NASA-CR-163656; PB80-809072) Avail: NTIS CROWAVE LANDING SYSTEM RESEARCH AND DEVELOP- HC S30.00/MF $30.00 CSCL DID MENT PROGRAM. 1974 TO 1978. VOLUME 1 Head up displays are the subject of this retrospective survey J. M. Jones London HMSO May 1979 250 p refs 3 Vol. of much of the world aerospace literature. Design, fabrication (RAE-TR-79052-Vol-1; RAE-RAD-NAV-Vol-1; BR73155) Avail: and use. and applications to specific aircraft, such as the F-4E, NTIS HC A11/MF A01 Jaguar, Tornado. F-18, Viggin. A-10, AV-8B. Sea Harrier. Space In support of the UK MLS program Doppler Microwave Shuttle, helicopters. KC-135S. and in commercial aircraft, are Landing System (DMLSI equipment operating on both frequency discussed. A look at the future in this field is also presented. division and time division multiplex formats was extensively Contains 70 citations. GRA evaluated by means of analysis, ground and flight tests and hybrid simulation. Results show that the use of the Doppler N81-10050# New England Research Application Center. Storrs. technique leads to simple and reliable equipment with performance Conn. well inside the operational requirements. A full understanding of HEAD UP DISPLAYS. CITATIONS FROM THE NTIS DATA the possible environmental effects on system performance at BASE Progress Report. 1970 - Apr. 1980 5 GHz was obtained. Author (ESA) Robert Hippler May 1980 133 p Sponsored in part by NTIS (PB80-809064) Avail: NTIS HC S30.00/MF $30.00 CSCL 01D N81-10045# Royal Aircraft Establishment. Farnborough Design, fabrication and use, and applications to specific (England). aircraft, such as the F-4E. Jaguar. Tornado. F-18, Viggin, A-10, CONTRIBUTIONS TO THE UNITED KINGDOM MI- AV-8B, Sea Harrier, Space Shuttle, helicopters. KC-1358. and CROWAVE LANDING SYSTEM RESEARCH AND DEVELOP- in commercial aircraft, are discussed. A look at the future in MENT PROGRAM, 1974 TO 1978. VOLUME 2 this field is also presented. GRA J. M. Jones London HMSO May 1979 168 p 3 Vol. (RAE-TR-79052-Vol-2; BR79052) Avail: NTIS HC A08/MF A01 N81-10053 Engineering Sciences Data Unit. London (England). In support of the UK MLS program. Doppler Microwave THE USE OF DATA ITEMS ON AIRCRAFT PERFORMANCE Landing System (DMLS) equipment operating on both frequency MEASUREMENT division and time division multiplex formats was extensively 1980 9 p Supersedes ESDU-75017 evaluated by means of analysts, ground and flight tests and (ESDU-80009: ESDU-75017; ISB N-0-85679-292-6) For hybrid simulation. Charts and figures pertaining to the following information on availability of series, sub-series, and other individual topics are presented: the Doppler MLS technique: basic data data items, write NTIS, Attn: ESDU, Springfield. Va. 22161 collection for ICAO submission: FDM system test results: and The purpose of flight testing and the principles that govern the time division multiplex system. Author (ESA) the methods of processing the data obtained, are explained to show the interrelationship between the various items that treat particular aspects and to indicate how methods not currently N81-10046$ Royal Aircraft Establishment. Farnborough discussed in the items might be applied. The processing of flight (England). test data obtained from aircraft with turbofan. turbojet, turboprop, CONTRIBUTIONS TO THE UNITED KINGDOM MI- or piston engines are described. ESOU (GRA) CROWAVE LANDING SYSTEM RESEARCH AND DEVELOP- MENT PROGRAM. 1974 TO 1978. VOLUME 3 J. M. Jones London HMSO May 1979 237 p 3 Vol. N81-10054*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. (RAE-TR-79052-Vol-3: BR79052) Avail: NTIS HC A11/MF A01 THE XV-1S TILT ROTOR RESEARCH AIRCRAFT In support of the UK MLS program. Doppler Microwave Daniel C. Dugan. Ronald G. Erhart (Bell Helicopter Textron. Fort Landing System (DMLS) equipment operating on both frequency Worth. Tex.), and Laurel G. Schroers (AVRADCOM) Sep. 1980 21 p refs Prepared in cooperation with AVRADCOM division and time division multiplex formats was extensively (NASA-TM-81244; AVRADCOM-TR-80-A-15: A-8343) Avail: evaluated by means of analysis, ground and flight tests and hybrid simulation. Charts and figures pertaining to the following NTIS HC A02/MF A01 CSCL 01C topics are presented: the Doppler simulator and time division The design characteristics of the XV-15 Tilt rotor research multiplex bench measurements: flight trials results of the TDM aircraft are presented. Particular attention is given to the following: system; field trials at operational airports; and a reference-less control system: conversion system; and propulsion system. Flight test results are also reported. R.C.T. system. Author (ESA)

N81 10O55# McDonnell Aircraft Co., St. Louis. Mo. N81-10O48# New England Research Application Center. Storrs. AIRCRAFT HYDRAULIC SYSTEMS DYNAMIC ANALYSIS. Conn. VOLUME 6: STEADY STATE FLOW ANALYSIS SSFAN ADIABATIC GAS FLOW. CITATIONS FROM THE NTIS COMPUTER PROGRAM TECHNICAL DESCRIPTION Final DATA BASE Progress Reoort. 1970 - Aor. 1980 Technical Report. Jun. 1978 - Nov. 1979 Robert Hippler May 1980 167 p Sponsored in part by NTIS Ray Levek and Bob Young Wright-Patterson AFB AFAPL Apr. (PB80-808546) Avail: NTIS HC S30.00/MF $30.00 CSCL 1980 339 p refs Revised (Contract F33615-74-C-2016) 17G Adiabatic gas flows for planetary and stellar atmospheres, (AD-A089240; AFAPL-TR-76-43-VOI-6) Avail: NTIS aerodynamics, heat transfer, nozzles, turbines, and energy systems, HC A15/MF A01 CSCL 01/3 such as magnetohydrodynamics and fusion reactors are discussed SSFAN is a steady state hydraulic flow and pressure analysis in approximately 76 citations. Analytical and modeling techniques, computer program. Its primary purpose is to analyze non-linear characteristics, experimental data, and fundamental principles are resistance aircraft hydraulic systems. The program handles covered. Two and three dimensional, compressible and in- complex flow networks containing flow and/or pressure disconti- compressible gas dynamic flows, for unbounded and bounded, nuities such as unbalanced area actuators and check valves. Solutions for a combination of simultaneously operating sub- stable and unstable conditions are included. • GRA systems are easily obtained. The program is designed using a N81-10O49*# New England Research Application Center. Storrs. building block approach so that new component or element models Conn. may be added with minimum change to the main program. The HEAD UP DISPLAYS. CITATIONS FROM THE INTERNA- solution method is a matrix type, using iteration to obtain a TIONAL AEROSPACE ABSTRACTS DATA BASE Progress final flow and pressure balance. The program internally corrects Report. 1976 - Apr. 1980 viscosities for pressure, determines whether flow is laminar.

26 IMS 1 10062

transition or turbulent for use of appropriate resistance factors N81-10059# Lockheed-Georgia Co.. Marietta. Advanced and corrects reservoir pressure for altitude effects. A quasi- Concepts Dept. transient section has been added to allow multiple steady state DESIGN OPTIONS STUDY. VOLUME 4: DETAILED calculations when simulating subsystem operations. The data is ANALYSES SUPPORTING APPENDICES Final Report stored and can be printed in either tabular form or computer W. T. Mikolowsky. H. J. Abbey. L. A. Adkins. H. A. Bricker. and plot form. The program was written with the aircraft hydraulic E. W. Caldwell Sep. 1980 202 p refs system designer in mind. The terminology and units are commonly (Contract F33615-78-C-0122) used terms such as fluid viscosity in centistokes. temperatures (AD-A089539: LG80ER0009-Vol-4l Avail: NTIS in degrees Fahrenheit and flow in gallons per minute. Conversion HC A10/MF A01 CSCL 01/3 of units for calculation is accomplished internally in the pro- Nonproprietary information and study methods are presented. gram. GRA The baseline aircraft that serves as the basis for the qualitative assessment is described, as well as the computer methods used N81-10056# Lockheed-Georgia Co.. Marietta. Advanced to assist in the redesign of aircraft incorporating each design Concepts Dept. option. GRA DESIGN OPTIONS STUDY. VOLUME 1: EXECUTIVE SUMMARY Final Report N81-10O6O# Naval Postgraduate School. Monterey. Calif. W. T. Mikolowsky. L W. Noggle. H. J. Abbey. L A. Adkins, THE USE OF PARAMETRIC COST ESTIMATING RE- and H. A. Bricker Sep. 1980 27 p LATIONSHIPS AS THEY PERTAIN TO AIRCRAFT AIR- (Contract F33615-78-C-0122) FRAMES: A NEW PERSPECTIVE M.S. Thesis (AD-A089536; LG80ER0006-Vol-1) Avail: NTIS Bruce Robert Bennett Mar. 1980 47 p refs HC A03/MF A01 CSCL 01/3 (AD-A089525) Avail: NTIS HC A03/MF A01 CSCL 14/1 The Advanced Civil/Military Aircraft ACMA is envisioned as The purpose of this thesis was to review cost estimating an advanced technology cargo aircraft with the potential for relationships that have been developed and used for aircraft fulfilling the needs of both military airlift and commercial air airframe costs, to identify existing problems, and where freight in the 1990's and beyond. The ultimate goal of the Design appropriate, to suggest alternatives for the future application of Options Sudy is the development of fundamental information cost estimating relationships to aircraft airframes. Mahalanobis regarding both the military and commercial cost and effective- distance was explored as a means of complementing the more ness implications of the most significant transport aircraft traditional statistical measures for regression analysis. This study functional design features. This volume, the Executive Summary supports the conclusion that cost estimating relationships should of the Design Options Study Final Report, presents an overview be developed for a specific system to be estimated, and that of the requirements of potential users of the ACMA and a brief Mahalanobis distance is a potentially effective tool by which summary of the results of the study. GRA the analyst may address the important issue of analogy between the data base and the proposed system. GRA

N81-10O57# Lockheed-Georgia Co., Marietta. Advanced N81-10061# Army Aviation Engineering Flight Activity, Edwards Concepts Dept. AFB. Calif. DESIGN OPTIONS STUDY. VOLUME 2: APPROACH AND PRELIMINARY AIRWORTHINESS EVALUATION AH-1S SUMMARY RESULTS Final Report HELICOPTER WITH OGEE TIP SHAPE ROTOR BLADES W. T. Mikolowsky. L. W. Noggle. H. J. Abbey, L. A. Adkins. Final Report, Nov. 1979 - Apr. 1980 and H. A. Bricker Sep. 1980 177 p refs Gary L. Bender. Henry Arnaiz, David Ottomeyer. Ralph Woratschek. (Contract F33615-78-C-0122) Larry Higgins, and John S. Tulloch May 1980 40 p rets (AD-A089537: LG80ER0007-Vol-2) Avail: NTIS (AD-A089625: USAAEFA-77-25) Avail: NTIS HC A09/MF A01 CSCL 01/3 HC A03/MF A01 CSCL 01/3 Background information for the requirement for the advanced The United States Army Aviation Engineering Flight Activity civil military aircraft (ACMA) is given and the approach used to conducted a Preliminary Airworthiness Evaluation of the AH-IS investigate transport aircraft design options is described. The helicopter with OGEE tip-shape main rotor blades to determine initial qualitative assessment used to reduce the scope of the if any improvement in performance or handling qualities resulted study and the results of the detailed analyses are summarized. from replacing the K747 blades. Additionally, the acoustics These results include estimates of the effects on aircraft geometry signature of the OGEE blades were measured by the US Army and efficiency, military effectiveness, and both civil and military Research and Technology Laboratories (Aeromechanics Lab). Tests costs for incorporating in the ACMA each of the design options were conducted at Edwards Air Force Base (elevation 2302 feet) identified in the qualitative assessment. GRA and Coyote Flats (elevation 9980 feet). California from 1 November 1979 through 8 April 1980. Forty-five test flights N81-10058# Lockheed-Georgia Co., Marietta. Advanced were flown for a total of 36.6 productive hours (63.2 total Concepts Dept. hours). Both hover and level flight performance were degraded DESIGN OPTIONS STUDY. VOLUME 3: QUALITATIVE by installation of OGEE tip-shape main rotor blades. Low-speed ASSESSMENT Final Report handling qualities were unaffected by the OGEE blades. Other W. T. Mikolowsky. H. J. Abbey. L A. Adkins. H. A. Bricker. and handling qualities tests were not accomplished. Results of E. W. Caldwell Sep. 1980 177 p refs acoustics tests will be reported by the laboratories under a separate (Contract F33615-78-C-0122) cover. GRA (AD-A089538: LG80ER0008-Vol-3) Avail: NTIS HC A09/MF A01 CSCL 01/3 N81-10O62# Deutsche Forschungs- und Versuchsanstalt fuer All functional design features and associated options that Luft- und Raumfahrt. Brunswick (West Germany). Abteilung have a potential impact on military/commercial commonality of Flaechenflugzeuge. the advanced civil military aircraft are qualitatively assessed. AN ANALYTICAL STUDY OF LANDING FLARE Functional areas considered include basic aircraft performance, Guenther Knorr and Knut Wilhelm Sep. 1979 77 p refs In ground interface, airfield compatibility, cargo compartment, inflight GERMAN: ENGLISH summary Report will also be announced refueling, personnel accommodations, and military/civil design as translation (ESA-TT-656) criteria. Based on this assessment, the following features are (DFVLR-FB-79-40) Avail: NTIS HCA05/MFA01: DFVLR. recommended for further analysis: design payload, loading/ Cologne DM 15.20 unloading apertures, planform shape of the cargo compartment, The relation between landing flare and the specific dynamic floor height, takeoff distance/gear flotation, noise characteristics/ characteristics of an aircraft as studied. A simple behavioral law engine-out climb gradient, cargo-envelope maximum height. is used to obtain analytical solutions for state variables. Both passenger provisions, maximum structural payload, service life conventional flare maneuver operations and coupled control specifications, cargo compartment pressurization. and cargo operations are investigated. The effects of wind shear on landing accommodation provisions. GRA flare are also demonstrated. Analytical solutions applicable to a

27 N81-10063

transport aircraft are discussed: these solutions lead to a definition compares these four powerplants types in several general aviation of the time range for flare initiation. Author (ESA) applications are reported. The evaluation consisted of installing each powerplant type in rubberized aircraft which are sized to accomplish fixed missions. The primary evaluation criteria include N81-10O63# Illinois Univ. at Urbana-Champaign. Coordinated projected aircraft cost, total ownership cost, and mission fuel. Science Lab. Author OPTIMIZED COMPUTER SYSTEMS FOR AVIONICS APPLICATIONS Final Technical Report. 1 Feb. - 30 Sep. N81-10068# General Electric Co., Lynn. Mass. Aircraft Engine 1979 Group. R. T. Chien and L. J. Peterson Feb. 1980 175 p refs MARITIME PATROL AIRCRAFT ENGINE STUDY. GENERAL (Contract F33615-78-C-1559: AF Proj. 2003) ELECTRIC DERIVATIVE ENGINES. VOLUME 2: AP- (AD-A089570: AFAL-TR-79-1235) Avail: NTIS PENDIX A. PERFORMANCE DATA - GE27/T3 STUDY A1 HC A08/MF A01 CSCL 09/5 TURBOPROP Final Report. Oct. 1978 - Apr. 1979 The main purpose of this project is to investigate the R. Hirschkron. R. H. Davis, and R. E. Warren 30 Apr. 1979 commonalities among the four subareas of signal processing, 81 p namely, radar, communications, image processing and electronic (Contract N62269-78-C-0414) warfare: and to establish possible common functional descriptions (AD-A089336: R79AEG052-Vol-2: NADC-79133-60-Vol-21 as the basis for a common architecture. An extensive search Avail: NTIS HC A05/MF A01 CSCL 21/5 was made to list all important kernels and algorithms in radar, This study developed data on General Electric common core communications and image processing. These kernels and derivative engines for use in Maritime Patrol Aircraft (MPA) algorithms were carefully analyzed with respect to their computa- concept formulation studies. The study included the screening tional complexity and identification of commonality for architec- of potential General Electric turbofan and turboprop/turboshaft tural purposes. It was discovered that significant commonalities engines and the preparation of technical and planning informa- do exist in many areas. These common areas represent significant tion on three of the most promising engine candidates. Screening overlap and commonality which can be utilized in a common of General Electric derivative candidates was performed utilizing architecture. GRA an analytical MPA model using synthesized mission profiles to rank the candidates in terms of fuel consumption, weight, cost N81-10O64# Deutsche Forschungs- und Versuchsanstalt fuer and complexity. The three turboprop engines selected for further Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer study were as follows: TF34 growth derivative version with boost Flugfuehrung. and new LPT (TF34/T7 Study A1), F404 derivative with booster SYSTEM SIMULATION APPLIED TO THE EVALUATION OF stages and new LPT (F404/T1 Study AD. and GE27 scaled DISPLAYS FOR GUIDANCE AND CONTROL and boosted study engine (GE27/T3 Study A1). Vol- Uwe Teegen (Technische Univ.. Brunswick) Jun. 1979 62 p ume 1 summarizes the screening analysis and contains technical, refs In GERMAN: ENGLISH summary Report will also be planning, installation, cost and development data for the three announced as translation (ESA-TT-659) selected turboprop engines. Volumes 2. 3 and 4 of this report (DFVLR-Mitt-79-10) Avail: NTIS HC A04/MF A01: DFVLR. contain the detailed performance data estimates for the Cologne DM 12.60 GE27/T3 Study A1. TF34/T7 Study A1 and F404/T1 Study The development of displays for monitoring and controlling A1 turboprop engines, respectively. GRA complex technical systems is facilitated by employing a computer simulation of the man-machine system during the theoretical N81-10069# General Electric Co.. Lynn. Mass. Aircraft Engine design phase. A simulation model for the manual control task is Group. described which leads to a method for evaluating displays. The MARITIME PATROL AIRCRAFT ENGINE STUDY. GENERAL capabilities and applications of this simulation model to a pilot ELECTRIC DERIVATIVE ENGINES. VOLUME 3: AP- airplane system restricted to aircraft motion in the vertical plane PENDIX B. PERFORMANCE DATA - TF34/T7 STUDY A1 and a two channel pilot mode are presented. The results obtained TURBOPROP Final Report. Oct. 1978 - Apr. 1979 suggest that the model should be further developed. R. Hirschkron. R. H. Davis, and R. E. Warren 30 Apr. 1979 Author (ESA) 81 p (AD-A089279: R79AEG052-Vol-3: N A D C-79 1 33-60-Vol-3) N81-10O65*# New England Research Application Center. Storrs. Avail: NTIS HC A05/MF A01 CSCL 21/5 Conn. This study developed data on General Electric common core GYROCOMPASSES. CITATIONS FROM THE INTERNA- derivative engines for use in Maritime Patrol Aircraft (MPA) TIONAL AEROSPACE ABSTRACTS DATA BASE Progress concept formulation studies. The study included the screening Report. 1972 - Apr. 1980 of potential General Electric turbofan and turboprop/turboshaft C. Gilbert Young May 1980 165 p Sponsored by NASA and engines and the preparation of technical and planning informa- NTIS tion on three of the most promising engine candidates. Screening (NASA-CR-163675: PB80-809023) Avail: NTIS HCS30.00/MF of General Electric derivative candidates was performed utilizing $30.00 CSCL 17G an analytical MPA model using synthesized mission profiles to Research on gyrocompasses and related areas, such as rank the candidates in terms of fuel consumption, weight, cost navigation, inertial navigation, gyrocompass design and construc- and complexity. The three turboprop engines selected for further tion, and gyrocompass systems is reported. Kalman and other study were as follows: TF34 growth derivative version with boost types of electronic systems used in conjunction with the basic and new LPT (TF34/T7 Study A1). F404 derivative with booster gyrocompass unit are also considered. Strap down systems are stages and new LPT (F404/T1 Study AD. and GE27 scaled discussed. This bibliography contains 186 abstracts. GRA and boosted study engine (GE27/T3 Study A1). Vol- ume 1 summarizes the screening analysis and contains technical, N81-10O67*# National Aeronautics and Space Administration. planning, installation, cost and development data for the three Lewis Research Center. Cleveland. Ohio. selected turboprop engines. Volumes 2. 3 and 4 of this report COMPARISONS OF FOUR ALTERNATIVE POWERPLANT contain the detailed performance data estimates for the TYPES FOR FUTURE GENERAL AVIATION AIRCRAFT GE27/T3 Study A1. TF34/T7 Study A1 and F404/T1 Study T. J. Wickenheiser. G. Knip. R. M. Plencner. and W. C. Strack A1 turboprop engines, respectively. GRA Oct. 1980 50 p refs (NASA-TM-81584: E-561) Avail: NTIS HC A03/MF A01 CSCL N81-1O070# Air Force Inst. of Tech., Wright-Patterson AFB. 21E Ohio. School of Systems and Logistics. Recently completed NASA sponsored conceptual studies were AN ANALYSIS OF AIR FORCE MANAGEMENT OF TURBINE culminated in the identification of promising new technologies ENGINE MONITORING SYSTEMS ITEMS) M.S. Thesis for future spark ignition, diesel. rotary, and turbine engines. The Elbert B. Hubbard. Ill and Gregory A. Swecker Jun. 1980 results of a NASA in-house preliminary assessment study that 118 p refs

28 N81-10077

(AD-A089365: AFIT-LSSR-68-80) Avail: NTIS A residual fatigue life prediction method, suitable for HC A06/MF A01 CSCL 21/5 retirement for cause application, has been developed for two p Turbine Engine Monitoring Systems ITEMS) are engine health WA turbine disks the F100 Ist-stage high pressure turbine disk monitoring and diagnostic tools being developed and tested for and the TF30 10th-stage compressor disk. The method is based use on Air Force engines in order to improve and reduce the upon interaction of fracture mechanics crack propagation modeling cost of engine maintenance and management and to aid in the concepts with laboratory nondestructive evaluation NDE hyper- implementation of On Condition Maintenance. Previous research- bolic sine SIMM model refined during an earlier Air Force Materials ers have described the major features of TEMS. analyzed the Laboratory AFML program. Stress intensity K solution for the results of development and test efforts, and identified problems eingine components were based upon experimental effective K which must be overcome. This study examines the problem of determinations made during full-scale component fatigue tests. fragmentation which exists in the Air Force management of TEMS The NDE techniques developed for disk inspections included development and testing. The authors describe and analyze the acoustic emission AE, eddy current EC, and fluorescent penetrants overall Air Force management of TEMS. Management problems FP. Stress-enhanced penetrant and semi-automated rotating probe were identified and classified into three major areas: structure EC techniques were developed as periodic inspections, while and role problems, information flow and integration problems, the AE time-domain technique was developed as a real-time and leadership and command problems. Four alternative inspection tool. GRA management concepts were analyzed. Based on this analysis, the authors recommend that the management structure be N81-10075# Rolls-Royce Ltd., Derby (England). modified, and a TEMS Task Force be established to more QUANTITATIVE THERMOGRAPHY IN AERO-ENGINE effectively utilize TEMS for Air Force engine maintenance and RESEARCH AND DEVELOPMENT management. GRA M. Hilton 1980 21 p (PNR-90021) Avail: NTIS HC A02/MF A01 N81-10072# AiResearch Mfg. Co.. Phoenix. Ariz. The use of a recording thermograph to study an engine COMPOUND CYCLE TURBOFAN ENGINE (CCTE). exhaust unit which is suspected of having thermal gradients of TASK 9: CARBON-SLURRY FUEL COMBUSTION EVALUA- sufficient severity to cause local distortion is described. Tempera- TION PROGRAM Final Report. Jun. - Sep. 1979 ture measurements obtained from color contoured thermograms T. W. Bruce and H. Mongia Mar. 1980 101 p refs are compared with thermocouples embedded in the exhaust unit. (Contract F33657-77-C-0391) The data processing and analysis techniques are described together IAD-A089451; Rept-21-3365-A: AFWAL-TR-80-2035) Avail: with the problems encountered when correlating the Thermovi- NTIS HC A06/MF A01 CSCL 21/4 sion results with those obtained from the thermocouples. Reasons The carbon slurry fuel evaluation program demonstrated the for the discrepancies are discussed with an assessment of the feasibility of running a currently available carbon slurry fuel in a problem magnitude and possible means of overcoming them in combustion rig and a turbine engine. This program also established future applications. Author (ESA) the preliminary design criteria for operating on carbon slurry fuels. Subcontracts work was performed by Pennsylvania State for fuel droplet measurements and by Suntech, Inc. for fuel development and manufacture. GRA N81-1O076# New England Research Application Center, Storrs, Conn. N81-10073# Detroit Diesel Allison. Indianapolis. Ind. AXIAL FLOW COMPRESSORS. CITATIONS FROM THE FUEL CHARACTER EFFECTS ON CURRENT. HIGH PRES- ENGINEERING INDEX DATA BASE Progress Report, SURE RATIO, CAN-TYPE TURBINE COMBUSTION SYS- 1970 - Apr. 1980 TEMS Final Report. Jun. 1978 - Jun. 1979 Robert Hippler May 1980 140 p Sponsored in part by NTIS Rodney E. Vogel. Dennis L. Troth, and Albert J. Verdouw (PB80-808611I Avail: NTIS HC S30.00/MF $30.00 CSCL Wright-Patterson AFB. Ohio AFAPL Apr. 1980 163 p refs 21E (Contract F33615-78-C-2006: AF Proj. 3048) Axial flow compressors used in jet engines, gas turbines, (AD-A089182: DDA-EDR-9762: AFAPL-TR-79-2072: turbo fans, ultra centrifuges and other turbomachinery are AFESC/ESL-TR-79-29) Avail: NTIS HC A08/MF A01 CSCL discussed in approximately 123 citations. Design, blades and 21/4 rotors, materials, flow measurement, performance and applications The effect of limited fuel property variation on the performance are included. GRA of current, high pressure ratio, can type combustors was evaluated. The TF41 turbofan combustor was employed. This combustor N81-1OO77*# National Aeronautics and Space Administration. has conventional, dual orifice fuel injection and film cooling. The Ames Research Center. Moffett Field. Calif. combustion zone is approximately stoichiometric at takeoff. Twelve A PILOTED SIMULATOR INVESTIGATION OF STATIC experimental fuels, including JP-4 and JP-8. were tested. STABILITY AND STABILITY/CONTROL AUGMENTATION Distillation range, hydrogen content, and aromatic type were varied EFFECTS ON HELICOPTER HANDLING QUALITIES FOR by blending JP-4 and JP-8 fuels with mineral seal oil and two INSTRUMENT APPROACH types of aromatic solvents. Performance tests were accomplished J. V. Lebacqz, R. 0. Forrest, and R. M. Gerdes Sep. 1980 at idle, altitude cruise, dash, and takeoff conditions. Sea level 393 p refs altitude ignition tests were also completed. Fuel fouling and (NASA-TM-81188: FAA-RD-8064: A-8125) Avail: NTIS carboning characteristics were established. Combustor operating HC A17/MF A01 CSCL01C parameters such as linear temperature, pattern factor, ignition A motion base simulator was used to compare the flying fuel/air ratio, lean blow out fuel/air ratio, and exhaust emissions qualities of three generic single rotor helicopters during a full were correlated to fuel properties. The effect of fuel properties attention to flight control task. Terminal area instrument on combustor and turbine hardware durability was assessed approaches were flown with and without turbulence. The analytically. GRA turbulence of helicopter static stability was investigated in terms of the values of cockpit control gradients as specified in the N81-10074# Pratt and Whitney Aircraft. West Palm Beach. existing airworthiness criteria. The effectiveness of several types Fla. Government Products Div. of stability control augmentation systems in improving the DISK RESIDUAL LIFE STUDIES. PART 2: TF30 10TH- instrument flight rules capability of helicopters with reduced static STAGE COMPRESSOR DISK (INCOLOY 901) Final Report. stability was examined. Two levels of static stability in the pitch, 1 Apr. 1976 - 30 Jun. 1979 roll, and yaw axes were examined for a hingeless rotor configura- J. S. Cargill. J. K. Malpani. and Y. W. Cheng Dec. 1979 96 p tion: the variations were stable and neutral static stability in refs pitch and roll, and two levels of stability in yaw. For the lower (Contract F33615-76-C-51 72; AF Proj. 7351) level of static stability, four types of stability and control (AD-A089524: PWA-FR-11878-Pt-2: AFML-TR-79-4173-PI-2) augmentation were examined for helicopters with three rotor Avail: NTIS HC A05/MF A01 CSCL 21/5 types: hingeless, articulated, and teetering. S.F.

29 N81-10078

N81-1OO78# Deutsche Forschungs- und Versuchsanstalt fuer AIRCRAFT ENGINE NACELLE FIRE TEST SIMULATOR. Luft- und Raumfahrt. Brunswick (West Germany). Abt. VOLUME 1: TECHNICAL Final Report. Sep. 1976 - Apr. Flaechenflugzeuge. 1980 FLIGHT TEST RESULTS OF THE HFB 320 MODEL FOLLOW- Karlheinz 0. W. Ball. Dennis B. Burnsides, Rolf D. Hegele. and ING CONTROL SYSTEM FOR THE IN-FLIGHT SIMULATION Paul R Hughes Apr. 1980 81 p OF AIRBUS A 130 (Contract F33615-76-C-2084: AF Proj. 3048) Sep. 1979 76 p refs In GERMAN: ENGLISH summary Report (AD-A089629: AFWAL-TR-80-2055-Vol-1) Avail: NTIS will also be announced as translation (ESA-TT-660) HC A05/MF A01 CSCL 14/2 (DFVLR-Mitt-79-131 Avail: NTIS HC A05/MF A01: DFVLR. This report describes the design, installation, and initial Cologne DM 15.40 checkout of the Aircraft Engine Nacelle Fire Test Simulator. This The programming of the airborne computer is discussed. facility was designed to realistically reproduce the environments The effects on nonlinearities were demonstrated from the results and combustion related phenomena encountered within an engine of ground-based simulation of the test aircraft, model and control nacelle. The facility provides both heating and cooling of the system. The high quality of the A 310 model aircraft simulation inlet air. heating of the engine case, control of air velocity and is confirmed from the flight-test results obtained. Examples are air pressure, and for the injection of fluids, combustibles or presented in which the ground based simulation technique is extinguishants. The report presents the final implementation of used to predict flight test results. Author (ESA) the system and details the hardware installation, the control system, and the software needed to provide integrated control, N81-10079# Naval Construction Battalion Center. Port Hueneme, safety, and data acquisition. Only limited checkout was possible Calif. due to the failure of the air compression and the cleaning and FIBERGLASS-REINFORCED RIGID POLYURETHANE modification efforts required to return the system to a safe EXPEDIENT PAVEMENT SUBJECT TO SIMULATED operating level. GRA F-4 AIRCRAFT TRAFFIC P. S. Springston May 1980 65 p refs (YF53536091) N81-10083# National Technical Information Service, Springfield. (AD-A089266: CEL-TN-1578) Avail: NTIS HC A04/MF A01 Va. CSCL 11/2 AIRFIELD PAVEMENT EVALUATION. CITATIONS FROM A multipurpose expedient paving system is being developed THE NTIS DATA BASE Progress Report. Jul. 1975 - Jun. to enable more rapid construction of expeditionary airfields by 1980 Marine Corps forces engaged in an amphibious landing. Previous GuyE. Habercom.Jr. Jul. 1980 211 p Supersedes NTIS/PS-79/ research has resulted in a conceptual pavement. FIBERMAT. 0754: and NTIS/PS-78/0685 which consists of a facing of fiberglass-reinforced polyester resin (PB80-812860: NTIS/PS-79/0754: NTIS/PS-78/0685) Avail: (FRP) bonded to a core of fiberglass-reinforced rigid polyurethane NTIS HC S30.00/MF $30.00 CSCL01E foam. FIBERMAT has been subjected to a series of laboratory The bibliography contains abstracts of Government sponsored tests to define response to stress fatigue and environmental research reports relative to airfield pavement structures. Durability, cycling. A similar structural sandwich of FRP and rigid polyurethane wear resistance, skid resistance and surface qualities are analyzed foam has been tested and found to meet F-4 aircraft static and evaluated. This updated bibliography contains 202 citations, load, tailhook impact, and engine exhaust blast requirements. 12 of which are new entries to the previous edition. GRA This report documents the results of a traffic test conducted on a section of FIBERMAT having a 5 inch thick fiberglass-reinforced foam core and a 1/4 inch thick FRP facing. Distributed traffic N81-10128# National Bureau of Standards. Washington. D.C. was applied to the test section with a load cart which simulated Center for Fire Research. a main gear of an F-4 aircraft. The cart was equipped with a IGNITION OF A LIQUID FUEL Final Progress Report. 1 May 30-7.7. 18 plyrating tire inflated to 265 psi and loaded to 1978 - 30 Sep. 1979 27.000 pounds. The first failure within the test section was Takashi Kashiwagi. Howard R. Baum. and John A. Rockett Jan. recorded at 136 coverages (1.306 passes) of the load cart, and 1980 78 p refs the entire test section was considered failed at 310 coverages (Grant AF-AFOSR-0006-79: AF Proj. 2308) (2.141 passes). GRA (AD-A089295: AFOSR-80-0476TR) Avail: NTIS HC A05/MF A01 CSCL20/R N81-10080# Battelle Columbus Labs.. Ohio. This report summarizes progress in the study of ignition of POLYMER RESEARCH IN RAPID RUNWAY REPAIR a liquid fuel under high intensity radiation. It describes an MATERIALS Final Report, Jan. - Oct. 1979 experimental study of the key processes during ignition and a Manfred Luttinger, Charles W. Kistler. Jr.. Henry M. Grotta. and theoretical modeling study of part of the phenomena during the Richard G. Sinclair Tyndall AFB. Fla. Air Force Engineering ignition period. The experiments were conducted using a CW and Service Lab. Nov. 1979 93 p refs C02 laser with incident fluxes from 1000 to 5000 W/sq cm (Contract F08635-79-C-0040) and n-decane as the flammable liquid. High speed photographs (AD-A089606: AFESC/ESL-TR-79-43) Avail: NTIS of ignition events showed a periodic depression in the decane HC A05/MF A01 CSCL 11/1 surface, probably caused by the thrust of the strong decane Low viscosity, two-component epoxy resins were formulated vapor flux: radial outward motion of the liquid, probably caused for airless spray application over quartz or dolomite aggregates. by a surface tension, gradient was also observed. The first The formulation selected for full evaluation was based on appearance flame was in the gas phase well above the surface mercaptan curing systems. Trifunctional acrylate monomers were The proposed autoignition mechanism of decane by the C02 used in some formulations as modifiers. The resulting polymer laser is the absorption of the incident laser beam by the vapor concrete set up within 3 to 4 minutes after mixing at temperatures plume. The effect on ignition of the incident angle of the laser around 73 degrees F. Good cures within 1/2 hour of mixing beam with respect to the decane surface was studied from 90 can be obtained in wet environments down to 5 degrees C and to 30 degrees. On reducing the incident angle, the ignition delay in dry environments down to -25 degrees C. Good adhesion to time becomes longer and the minimum incident flux for ignition wet aggregates requires the use of coupling agents, organofunc- increases significantly. A theoretical model describing the flow tional silanes being preferred. Good bonding to asphalt and motion in the gas phase caused by a heated surface was calculated Portland cement concrete and good wear characteristics were numerically and solved analytically. GRA demonstrated. Flexural strength properties are satisfactory after cool down both under dry and wet application conditions. While the polymer concrete is hot due to the exotherm of the curing N81-10152# Boeing Military Airplane Development. Seattle. reaction, flexural strength properties are low. GRA Wash. Advanced Aircraft Branch. CAST ALUMINUM STRUCTURES TECHNOLOGY (CAST). N81-10081$ Systems Research Labs., Inc.. Dayton. Ohio. TECHNOLOGY TRANSFER (PHASE 6) Summary Technical Aerosystems Group. Report

30 N81-10576

James W. Faber Apr. 1980 255 p refs AXIAL FLOW COMPRESSORS. CITATIONS FROM THE (Contract F33615-76-C-3111) NTIS DATA BASE Progress Report. 1974 - Apr. 1980 (AD-A087492; D180-25725-1: AFWAL-TR-80-3020) Avail: Robert Hippler May 1980 217 p Sponsored in part by NTIS NTIS HC A12/MF A01 (PB80-808603) Avail: NTIS HC S30.00/MF $30.00 CSCL Structural and manufacturing technologies, integrity, produci- 13G bility. and viability of cast aluminum primary airframe structures Various axial flow compressors, used in jet engines, gas are discussed. Preliminary design, manufacturing methods, detailed turbines, turbo fans, ultra centrifuges, and in other turbo machinery, design, fabrication of demonstration articles and production are treated in these abstracts. Citations center on design, including hardware, structural test evaluation, and technology transfer are blades and rotors, and materials, measurements of flow, included. S.F. performance, and applications. This bibliography contains 200 citations. GRA N81-10168 Societe Nationals Industrielle Aerospatiale, Suresnes (France). Lab. Central. N81-10446# Air Force Inst. of Tech.. Wright-Patterson AFB. ELASTOMERS USED IN AERONAUTICS INDUSTRY [LES Ohio. School of Systems and Logistics. ELASTOMERES UTILISES DANS L'INDUSTRIE AERONAU- A CONTROLLED EVALUATION OF THE DIFFERENCES TIQUE] BETWEEN TWO APPROACHES TO RELIABILITY INVEST- G Dallemagne Paris 11 Jun. 1980 25 p In FRENCH Presented MENT SCREENING M.S. Thesis at Stage Mater. Nonmetal.. Jun. 1980 Russell M. Genet and John M. Wallace Jun. 1980 73 p refs (SNIAS-801-551-105) Avail: NTIS HC A02 (AD-A087506: AFIT-LSSR-36-80) Avail: NTIS The physicochemical structure of elastomers is briefly HC A04/MF A01 CSCL 14/1 examined. The performance of various elastomers under specific There is a continuing concern about the high aircraft support conditions is given. Their uses in various aircraft components cost and poor availabilities caused by some aeronautical and systems are discussed. Classification and standardization equipments. It is generally accepted that basic research, procedures are exposed together with the testing equipment engineering development, and improvements in fielded equipments employed and the results obtained. Author (ESA) should concentrate on high burner types of equipment. This has been countered by the suggestion that the emphasis would be N81-10436$ National Gas Turbine Establishment. Farnborough better placed on those equipment types with the highest return (England). on investment. An experiment was conducted, using data from A METHOD OF PERFORMANCE PREDICTION FOR over 20,000 aeronautical equipments, to determine if the high CENTRIFUGAL COMPRESSORS. PART 1: ANALYSIS. burner and return on investment approaches really emphasize PART 2: COMPARISON WITH EXPERIMENT different equipment types. It was found that, in fact, different M. V. Herbert London Feb. 1980 175 p refs Supersedes equipment types were emphasized. The high burner approach NGTE-M78029: ARC-38052: NGTE-M78031: ARC-38053 emphasized jet engines, radar sets, etc.. while the return on (ARC-R/M-3843: BR73151: NGTE-M78029: ARC-38052: investment approach emphasized valves and actuators, fuel NGTE-M78031: ARC-38053I Avail. NTIS HC A08/MF A01: gauges, and other mundane but troubelsome equipments. These HMSO £18 PHI research findings suggest that a change in policy might be A method was developed capable of producing reasonably appropriate. GRA accurate stage characteristics, in terms of mass flow, pressure ratio, work input and efficiency, for any centrifugal compressor N81-10454# Politecnico di Milano (Italy). with radial outflow (i.e.. with no axial component of velocity at EVALUATION OF SECTION PROPERTIES FOR HOLLOW outlet), given only overall geometric properties. The analytical COMPOSITE BEAMS treatment and assumptions used are presented along with the Vittorio Giavotto. Marco Borri, Luigi Puccinelli, Vittono Caramaschi results of applying the method to various machines and comparison (Construzioni Aeronautiche Giovanni Agusta S. P. A. Cascina of the predictions with test data. Prediction of choking flow is Costa di Samarate. Italy), and Francesco Mussi (Construzioni generally satisfactory, and the mass flow/pressure ratio character- Aeronautiche Giovanni Agusta S. P. A. Cascina Costa di Samarate. istics produced have substantially correct form, although no general Italy) 7 Sep. 1979 30 p refs Presented at the Fifth European means have been found of predicting the onset of surge. For Rotorcraft and Powered Lift Aircraft Forum. Amsterdam. 4-7 Sep. the cases examined the error in predicted efficiency level is 1979 within 1 to 2 percent at design speed, sometimes more at low (Paper-Nr-35) Avail: NTIS HC A03/MF A01 speed. Author (ESA) The plan for the development and the validation of design procedures for composite beam-like structures and structural N81-10437# Von Karman Inst. for Fluid Dynamics. Rhode-Saint- components is described. Analytical as well as experimental results Genese (Belgium). are reported. The development of the program HA NBA (Hollow INLET FLOW IN CENTRIFUGAL PUMPS AT PARTIAL Anisotropic Beam Analysis) which, based on an original displace- DELIVERIES ment method approach, allows the evaluation of section stiffnesses Mete Sen Jun. 1979 9 p In FRENCH: ENGLISH summary and stresses is presented. The program works on a finite element Presented at Soc. Hydrotech. de France Session 113 on idealization of the beam section and computes the stresses from Comportement Dyn. des Turbomachines Hydrauliques. 20-21 Jun. the resultant forces and moments acting on the particular section, 1979 Submitted for publication as the usual engineer's beam theory. Experimental results mainly (VKI-Preprint-1979-16) Avail: NTIS HC A02/MF A01 concern the identification of elastic properties for composite Pump design parameters influencing swirling reverse flow laminates, at relativevly low stress levels, and the validation of were investigated. Several impellers were developed and tests the results of the program HANBA. Analytical results compare were performed to investigate inlet flow characteristics. An very well with experimental ones, the largest differences in section important parameter is called the Pump's Critical Delivery which stiffenesses so far evaluated being of the order of 1%. The plan corresponds to the onset of swirling reverse flow at the tip of is still going on and future activities are also outlined in the the blade's leading edge. The results showed uniform aerodynamic paper. R.K.G. hub to tip blade loading to be the most important criterion associated with low critical deliveries. High critical deliveries are N81-10576*# National Aeronautics and Space Administration. obtained with a high aerodynamic blade loading at the tip. Head Washington. D. C. stability is not related to swirling reversed flow. A relation does, SURVEY POPULATION RESPONSE TO AIRPLANE NOISE. however, exist between shaft power and reverse flow. PART 1 Author (ESA) C. Bitter and K. W. Schwager May 1980 71 p Transl. into ENGLISH from Enouete Readies Bevolking op Vliegtuiglawaai. (Leiden). Aug. 1964 69 p Transl. by Kanner (Leo) Associates. N81-10441# New England Research Application Center. Storrs. Redwood City. Calif. Original doc. prep, by Institute for Health Conn. Techniques. TNO, Netherlands

31 N81-10577

(Contract NASw-3199) Harvey J. Clewell. Ill Mar. 1980 186 p refs 2 Vol. (NASA-TM-75790: Rept-D-19) Avail: NTIS (AF Proj. 1900) HC A04/MF A01 CSCL 13B (AD-A089076: AFESC/ESL-TR-80-17-Vol-2) Avail: NTIS A questionnaire concerning aircraft noise is presented. The HC A09/MF A01 CSCL 13/2 tabulated responses to it are also presented. T.M. An analysis of 3 1/2 years of data on fuel jettisoning by US Air Force aircraft was performed to provide the basis for an N81-10577*# National Aeronautics and Space Administration. accurate assessment of the environmental effects associated with Washington. D. C. this practice. This volume contains complete listings of all ANNOYANCE FROM LIGHT AIRCRAFT INVESTIGATION reported fuel dumps by Air Force aircraft for the period 1 Jan CARRIED OUT AROUND FOUR AIRPORTS NEAR PARIS 75 through 30 Jun 78. sorted by Air Force command and by Apr. 1980 55 p refs Transl. into ENGLISH of La gene causee aircraft. A third section presents the distribution of fuel jettisoning par laviation legere-enquete effectuee autour de quatre aerodromes by latitude and longitude coordinates. GRA de la region parisienne Transl. by Kanner (Leo) Associates, Redwood City. Calif. Original doc. prep, by Centre Ketudes et de Recherches Pyschologiques Air and Analyse, Recherche et N81 10636*# FWG Associates. Inc.. Tullahoma. Tenn. Conseil en Marketing et Communication (Paris) PILOT-AIRCRAFT SYSTEM REPONSE TO WIND SHEAR (Contract NASw-3199) Interim Report (NASA-TM-75823) Avail: NTIS HC A04/MF A01 CSCL Barry S. Turkel and Walter Frost Washington NASA Nov. 13B 1980 98 p refs An opinion survey was carried out on residents living near (Contract NAS8-33458) four airports in the Paris, France area. An evaluation of their (NASA-CR-3342) Avail. NTIS HC A05/MF A01 CSCL 04B responses concerning noise pollution and possible expansion of The nonlinear aircraft motion and automatic control model airport activity is presented. L.F.M. is expanded to incorporate the human pilot into simulations of aircraft response to wind to wind shear. The human pilot is N81-10578# Committee on Public Works and Transportation described by a constant gains lag filter. Two runs are carried (U. S. House). out using pilot transfer functions. Fixed-stick, autopilot, and AVIATION SAFETY AND NOISE ABATEMENT manned computer simulations are made with an aircraft having Washington GPO 1979 448 p refs Hearings on H. R. characteristics of a small commuter type aircraft flown through 2458. H. R. 3547 and H. R. 3596 Before the Subcomm. on longitudinal winds measured by a Doppler radar beamed along Aviation of the Comm. on Public Works and Transportation, 96th the glide slope. Simulations are also made flying an aircraft Congr.. 1st Sess.. 24 Apr. and 1 May 1979 through sinusoidal head wind and tail wind shears at the phugoid (GPO-50-923) Avail: Subcommittee on Aviation frequency to evaluate the response of manned aircraft in The 1979 hearings before the House subcommittee on thunderstorm wind environments. S.F. aviation considering legislation to establish noise reduction and N81-10807*# National Aeronautics and Space Administration. safety programs are presented. Three bills are introduced and Lewis Research Center. Cleveland. Ohio. examined, the general proposal of each being to provide Federal NEW INTERPRETATIONS OF SHOCK-ASSOCIATED NOISE assistance to airport operators to prepare and carry out noise WITH AND WITHOUT SCREECH compatibility programs and to provide assistance to assure U. vonGlahn 21 Nov. 1980 25 p refs To be presented at continued safety in aviation. Both indirect methods of noise the 100th Meeting of the ASA. Los Angeles, 17-21 Nov. 1980 abatement involving land use and flight pattern control and direct (NASA-TM-81590: E-569) Avail: NTIS HC A02/MF A01 CSCL aircraft engineering investigations are addressed. M.G. 20A Anomalous trends in present convergent nozzle (Mach 1) shock associated noise analyses and predictions, with particular emphasis on the roles of screech and jet temperature, are N81-10580# Air Force Engineering and Services Center. Tyndall discussed. Experimentally measured values of shock associated AFB. Fla. Environics Div. noise are used to reassess data trends, including both frequen- FUEL JETTISONING BY U.S. AIR FORCE AIRCRAFT. cy and sound pressure level. The data used includes model-scale VOLUME 1: SUMMARY AND ANALYSIS Final Technical nozzles, varying in nominal diameter from 5 cm to 13 cm. and Report. Feb. 1972 - Dec. 1979 full scale engine nozzles up to 48 cm. All data were obtained Harvey J. Clewell. Ill Mar. 1980 60 p refs at static conditions. From this reassessment of the measured (AF Proj. 1900) data, new empirical methods for the prediction of shock associated (AD-A089010: AFESC/ESL-TR-80-17-Vol-1) Avail: NTIS noise are developed. Separate procedures are presented for HC A04/MF A01 CSCL 13/2 screech free and screech contaminated shock associated noise. An analysis of 3 1/2 years of data on fuel jettisoning by In the present approach, shock associated noise spectra are US Air Force aircraft was performed to provide the basis for an developed from considerations that include the peak sound accurate assessment of the environmental effects associated with pressure level and its frequency, the low frequency sound pressure this practice. The nature and extent of US Air Force jettisoning level slope, and the high frequency sound pressure level slope was examined, and the principal commands, aircraft, locations, or roll-off; the latter is shown to vary with directivity angle. altitudes, and quantities were identified. The reasons for fuel Author jettisoning were also investigated, and the relative importance N81-11013*# Kentron International. Inc.. Hampton. Va. of fuel jettisoning as a source of hydrocarbon pollution was PRELIMINARY DESIGN CHARACTERISTICS OF A SUB- estimated, considering both the possibility of ground contamination SONIC BUSINESS JET CONCEPT EMPLOYING AN ASPECT by liquid fuel, and the potential for production of photochemical RATIO 25 STRUT BRACED WING oxidant pollution from the vapors. The analysis indicates that R. V. Turriziani, W. A. Lovell. G. L. Martin. J. E. Price. E. E. current Air Force policies concerning fuel jettisoning are adequate Swanson. and G. F. Washburn Oct. 1980 101 p refs to minimize any negative environmental consequences, and that (Contract NAS1-16000) Air Force operational practices are in keeping with these policies. (NASA-CR-159361) Avail: NTIS HC A06/MF A01 CSCL Fuel jettisoning as carried out by Air Force aircraft does not 0!A appear to produce any serious environmental consequences. The advantages of replacing the conventional wing on a GRA transatlantic business jet with a larger, strut braced wing of aspect ratio 25 were evaluated. The lifting struts reduce both N81-10581$ Air Force Engineering and Services Center. Tyndall the induced drag and structural weight of the heavier, high aspect AFB. Fla. Environics Div. ratio wing. Compared to the conventional airplane, the strut braced FUEL JETTISONING BY U.S. AIR FORCE AIRCRAFT. wing design offers significantly higher lift to drag ratios achieved VOLUME 2: FUEL DUMP LISTINGS Final Technical Report. at higher lift coefficients and. consequently, a combination of Feb. 1972 - Dec. 1979 lower speeds and higher altitudes. The strut braced wing airplane

32 N81-11022 provides fuel savings with an attendant increase in construction N81-11019/JI Advisory Group for Aerospace Research and costs. Author Development. Neuilly-Sur-Seine (France). COMPARISON OF UNSTEADY PRESSURE FIELDS COM- N81-11014*# Boeing Vertol Co.. Philadelphia. Pa. PUTED AND MEASURED ON THE ZKP MODEL FULL SCALE WIND TUNNEL INVESTIGATION OF A M. Couston. J. J. Angelini. and J. P. Meurzec Aug. 1980 21 p BEARINGLESS MAIN HELICOPTER ROTOR Final Report refs In FRENCH; ENGLISH summary Presented at the 50th 10 Oct. 1980 608 p refs Conf. of the Commission on Structures and Materials, Athens, (Contract NAS2-10333) Apr. 1980 (NASA-CR-152373: D210-11659-1) Avail: NTIS (AGARD-R-688: ISBN-92-835-2107-2) Avail: NTIS HC A99/MF A01 CSCL 01A HC A02/MF A01 A stability test program was conducted to determine the The unsteady pressure fields prediction for a supercritical wing effects of airspeed, collective pitch, rotor speed and shaft angle is considered from a bidimensional nonlinear method corrected on stability and loads at speeds beyond that attained in the for tridimensional interactions between strips using an asymptotic BMR/BO-105 flight test program. Loads and performance data approximation. This approximation is derived for a wing with were gathered at forward speeds up to 165 knots. The effect large aspect ratio and low sweep angle. An application of this of cyclic pitch perturbations on rotor response was investigated method to a real case is described. Oscillation of the control- at simulated level flight conditions. Two configuration variations surface on a rigid model in a transonic wind tunnel is consid- were tested for their effect on stability. One variable was the ered. M.G. control system stiffness. An axially softer pitch link was installed in place of the standard BO-105 pitch link. The second variation was the addition of efastomeric damper strips to increase the N81-11020# Toronto Univ. (Ontario). Inst. for Aerospace structural damping. The BMR was stable at all conditions tested. Studies. At fixed collective pitch, shaft angle and rotor speed, damping THE TURBULENT WIND AND ITS EFFECT ON FLIGHT generally increased between hover and 60 knots, remained Bernard Etkin Aug. 1980 93 p refs relatively constant from 60 to 90 knots, then decreased above (UTIAS-Review-44: CN-ISSN-0082-5247) Avail: NTIS 90 knots. Analytical predictions are in good agreement with HC A05/MF A01 test data up to 90 knots, but the trend of decreasing damping An overview of the problems posed for aviation by turbulent above 90 knots is contrary to the theory. A.R.H. winds is presented. The technical issues, especially for design, simulation and certification, are delineated and commented upon. The present state of knowledge of turbulence at altitude and of N81-11016# ARO, Inc.. Arnold Air Force Station. Tenn. the wind and turbulence near the ground are reviewed. The WIND TUNNEL INVESTIGATION OF THE AERODYNAMIC input/response problem is discussed in depth, with special HYSTERESIS PHENOMENON ON THE F-4 AIRCRAFT AND attention to the requirement for unsteady aerodynamics and how ITS EFFECTS ON AIRCRAFT MOTION Final Report. 1 Oct. it can be fulfilled. The four point model of the airplane is introduced 1978 - 31 Oct. 1979 and developed, and an extension made to the existing spectral J. F. Herman and E. S. Washington AEDC Sep. 1980 96 p theory of response to two dimensional inputs. Passenger comfort, refs Sponsored by Air Force gust alleviation, and representation of turbulence in piloted flight (AD-A089851: AEDC-TR-80-10) Avail: NTIS simulators are discussed. S.F. HC A05/MF A01 CSCL 20/4 A wind tunnel test program and an analytical study were N81-11021# RANN. Inc., Palo Alto. Calif. conducted to investigate aerodynamic hysteresis phenomena on EXPLORATORY STUDY OF HAZARD MITIGATION AND the F-4 aircraft. The wind tunnel test was conducted in the RESEARCH IN THE AIR TRANSPORT SYSTEM Final Arnold Engineering Development Center (AEDC) Aerodynamic Report Wind Tunnel (4T) to investigate the source of aerodynamic R. L. Bisplinghoff, P. G. Dembling. A. J. Eggers. Jr., C. W. Harper, hysteresis in static aerodynamic data. The wind tunnel test also and J. D. Young 31 Mar. 1980 99 p refs provided data that were used in a motion simulation study of (AD-A089204: EMW-00432) Avail: NTIS HC A05/MF A01 the effect of hysteresis on predicted aircraft motion. Static CSCL 13/12 longitudinal lateral directional force and moment data and wing The study examines a series of principles that may effectively pressure data were obtained on a 0.5 scale model (without mitigate technological hazards within the Air Transport System. pylons or external stores) with various simulated leading-edge These principles are: precise design criteria and verification of slats. These data include the effects of Mach number, angle of the standards which relate to an airplane:s operating environment: attack, model movement, and time dependence on the aerodynam- quality control in manufacturing with high levels of performance ic hysteresis characteristics. Data are presented for the Mach in design, construction, inspection, and maintenance of the system: number range from 0.7 to 0.95 at angles of attack from -4 to periodic testing and evaluation of equipment and human elements 24 deg at zero deg sideslip angle and for sideslip angles from to meet performance standards: training and education of key -12 to 12 deg at angles of attack of 5, 10. 15, and 20 deg. managers and operators in emergency procedures with emphasis Six degrees of freedom motion simulation studies were used to in new systems and multi-problem hazards: establish communica- assess the effect of hysteresis in the rolling-moment coefficient tion modes linking key elements with institutions in the system on the prediction of aircraft motion. Simulations of various flight to mitigate, respond, and recover from emergencies: a system maneuvers were conducted both with and without hysteresis in of reporting incident and accident investigations in a prompt the aerodynamic data. GRA manner to allow for a coordinated recovery: and the system must be regulated, audited, and demonstrated frequently to protect N81-11017# Naval Surface Weapons Center, White Oak. Md. public interest, including proper liability. These principles are then Research and Technology Dept. analyzed in three areas in which successful hazard mitigation A COMPARISON OF NEWTON-LIKE METHODS FOR THE will reduce the effects of increased technological applications. TRANSONIC SMALL DISTURBANCE EQUATION These topic areas include: design, construction, inspection, and A. B. Stephens and A. G. Werschulz 24 Jun. 1980 20 p maintenance: system development and operation: and liability refs and regulation. The study concludes that with the rapid (AD-A090270: NSWC/TR-80-271) Avail: NTIS development in high technology and with its subsequent rapid HC A02/MF A01 CSCL 20/4 application to our national capability, technological hazards We investigate the efficiency of Newton's method and two converge onto a wide variety of societies' activities. The report variants of Newton's method for the numerical solution of the suggests that successful mitigation of technological hazards can small disturbance equation of non-lifting transonic flow past a be achieved through utilizing the previously outlined principles parabolic airfoil. In particular, it is shown that the efficiency of within the total air transport system environment. GRA Newton's method can be substantially improved with respect to both storage and computational time if the Jacobian matrix is N81-11022# Federal Aviation Administration. Atlantic City. N.J. suitably altered. GRA SUMMARY OF FEDERAL AVIATION ADMINISTRATION

33 N81-11023

RESPONSES TO NATIONAL TRANSPORTATION SAFETY his traffic. The work effort addressed the relocation of operational BOARD SAFETY RECOMMENDATIONS Quarterly Report, positions from their usual peripheral sites in the tower cab to a Apr. - Jun. 1980 unique four-winged central console with each wing having its J. R. Harrison et al Jul. 1980 167 p own instrumentation. This console housed two Local Control (AD-A089971: FAA-ASF-80-2: ASF-300) Avail: NTIS and two Airport Surveillance Radar (ASR) positions on one side HC A08/MF A01 CSCL 01/2 of the console and a Ground Control position on the opposite This report contains NTSB recommendations and all FAA side with identical instrumentation. These five positions were responses to Board recommendations that were delivered to the endowed with a 'flip/flop' capability as traffic dictated. The other Board during the applicable quarter. In addition, the report includes two positions. Clearance Delivery/Flight Data and Watch NTSB requests and FAA responses concerning reconsiderations, Supervisor, remained constant at each end of the console, status reports, and followup actions. The table of contents for regardless of traffic flow. While the four-winged central console this report reflects only those NTSB recommendations which solved the Local Controller's instrumentation availability, it are still open pending FAA action (i.e., those that have not reflected two problems. Limited room on the console caused been designated as 'closed' by the NTSB as a result of acceptable overcrowding and resultant overheating of the operational action). Accordingly, the table of contents may reflect a number equipment. Local Control perambulation was restricted due to of multiple recommendations (example: A-80-5 through 7). but the two ASR controllers and tower peripheral boundaries. Since background material is included only for those recommendations few airports require the 'flip/flop' design necessary by a tower which remain in an 'open' status. Background information for located between dual runways, it was concluded that no further those recommendations which have been closed is available in evaluation of this console concept would be made. GRA FAA headquarters files. GRA N81-11026$ Federal Aviation Administration. Atlantic City. N.J. N81-11023# Civil Aeronautics Board. Washington. DC. Office of Systems Engineering Management. Financial and Traffic Data Section. ATARS IMPLEMENTATION TRADEOFF AIRPORT ACTIVITY STATISTICS OF CERTIFICATED ROUTE Robert W. Sittler and Karl Seller, III Jul. 1980 108 p refs AIR CARRIERS. CALENDAR YEAR 1979 (AD-A089977: FAA-EM-80-10: AEM-200) Avail: NTIS 31 Dec. 1979 357 p Prepared in cooperation with FAA, HC A06/MF A01 CSCL 01/2 Washington. D.C. The study is a comparative analysis of the costs and benefits (AD-A089748) Avail: NTIS HC A16/MF A01 CSCL 01/2 from competing distributed and centralized ATARS architectures. This report furnishes airport activity of the Certificated Route The current DABS/ATARS structure is a distributed one: a new Air Carriers. Included in the data contained in Table 6 are architecture is postulated for deployment as a centralized ATARS passenger enplanements. tons of enplaned freight, express, and system. Distributed and centralized ATARS are compared as to mail. Both scheduled and non-scheduled service, and domestic performance, cost, reliability, maintainability, vulnerability and and international operations are included. These data are shown growth potential. Performance and reliability are treated as by airport and carrier. Table 7 includes departures by airport, constraints to be met equally by all architectures. Maintainability carrier and type of operation, and type of aircraft. GRA is included in cost. The cost analysis including cost sensitivities forms the bulk of the study. It is found that centralization of N81-11024# Federal Aviation Administration, Atlantic City. N.J. most sites is more costly than a distributed deployment and Technical Center. that the individual sites which contribute most to a cost advantage PROCEEDINGS OF THE 1979 SEMINAR ON AIR TRAFFIC for centralization lie in high density terminal areas. A most CONTROL. TERMINAL RADAR APPROACH CONTROL significant finding is that centralized ATARS is inferior to (TRACON) FACILITY SUPERVISORY DESK COMPLEX distributed ATARS in vulnerability. The options are about equal Progress Report. Nov. 1979 - Feb. 1980 in growth potential. GRA Paul Zito. John Goodwin. Felix Hierbaum. Michael Massimino. and Tom E. Zurinskas Aug. 1980 107 p Seminar held at N81-11028| Lincoln Lab., Mass. Inst. of Tech.. Lexington. Atlantic City. N.J. FORMATS FOR DABS DATA LINK APPLICATIONS (FAA Proj. 219-151-140) J. L Leeper and R. S. Kennedy 30 Jul. 1980 34 p refs (AD-A089914: FAA-CT-80-170: FAA-RD-80-105) Avail: NTIS (Contract F19628-80-C-0002: DOT-FA78WAI-895) HC A06/MF A01 CSCL 17/7 (AD-A089963: ATC-96: FAA-RD-80-81) Avail: NTIS With the planned construction of new control tower and HC A03/MF A01 CSCL 01/2 TRACON facilities, the Federal Aviation Administration (FAA) has The purpose of this paper is to describe formats developed established a need for standardized supervisory desk complexes. for transmitting aviation-related messages over the Discrete The Air Traffic Control (ATC) Systems Applications Branch Address Beacon System (DABS) data link. Initial data link (ACT-210) at the Federal Aviation Administration (FAA) Technical applications include: Minimum Safe Altitude Warning (MSAW) Center conducted a study of selected field facilities. In addition, alerts (Terminal Area): Takeoff Clearance Confirmation: Altitude a seminar was held at the Technical Center which resulted in Assignment Clearance Confirmation (Enroute): Weather Reports: recommending several different supervisor's desk designs for Enhanced Terminal Information Service (ETIS): Downlink of future implementation at new facilities or as useful, functional, Airborne Measurements. The formats described in this paper cover and efficient replacements for existing TRACON installations. the DABS communications formats for uplink messages from GRA the DABS sensor to the airborne data link system, and the downlink messages from the aircraft. Downlink messages include NB1-11025# Federal Aviation Administration. Atlantic City, N.J. pilot requests for routine weather information and ETIS service, NEW TERMINAL RADAR APPROACH CONTROL IN TOWER pilot acknowledgements for uplink tactical messages, and airborne CAB CONCEPT FOR LOVE FIELD. DALLAS. TEXAS Final measurements. GRA Report, Mar. - May 1980 Donald Bottomley, Edward G. Ezekiel, and Thomas Zurinskas N81-11030 Michigan Univ.. Ann Arbor. Aug. 1980 17 p IMPROVED AIRCRAFT CRUISE BY PERIODIC CONTROL (AD-A089996: FAA-CT-80-40: FAA-RD-80-79) Avail: NTIS Ph.D. Thesis HC A02/MF A01 CSCL 17/7 Daniel Thomas Lyons 1980 302 p This study was accomplished in response to a request from Avail: Univ. Microfilms Order No. 8025721 Air Traffic Service (AAT-100), for development of a mockup to The possibility of improving aircraft cruise by periodic motion evaluate a centrally positioned terminal radar approach control was investigated for subsonic aircraft with jet engines. Three in a tower cab (TRACAB) console. Presently, the Local Control cruise problems were studied: maximum range, maximum position at Love Field, Dallas, Texas, generally faces both southeast endurance, and peak altitude. Normal steady state cruise was runways, with all the attendant instrumentation in front of the compared with periodic cruise in which the controls and state controller. However, when conditions dictate a northwest variables were time-dependent periodic functions. Periodic cruise operation, the Local Controller must turn away to see and sequence results in improved performance under certain circumstances.

34 N81-11037

Periodic cruise gives greater peak altitudes than are possible N81-11035# Army Research Inst. for the Behavioral and Social with steady state cruise. A state inequality constraint which limits Sciences. Alexandria. Va. Manpower and Educational Systems the peak altitude is required to retain dynamic pressure for Technical Area. aerodynamic control at the peak altitude. A large energy height HELICOPTER ELECTRO-OPTICAL SYSTEM DISPLAY is desirable for maximum peak altitude. However, the period REQUIREMENTS. 1. THE EFFECTS OF CRT DISPLAY increases rapidly as the energy height approaches the maximum SIZE, SYSTEM GAMMA FUNCTION, AND TERRAIN TYPE energy height for steady cruise. Dissert. Abstr. ON PILOTS REQUIRED DISPLAY LUMINANCE Aaron Hyman. Richard M. Johnson, and Paul A. Gade Mar. N81-11032*# National Aeronautics and Space Administration. 1980 29 p refs Langley Research Center. Hampton. Va. (DA Proj. 2Q1-62722-A-765) BIBLIOGRAPHY ON AERODYNAMICS OF AIRFRAME/ (AD-A089755: ARI-TR-441) Avail: NTIS HC A03/MF A01 ENGINE INTEGRATION OF HIGH-SPEED TURBINE- CSCL 05/8 POWERED AIRCRAFT, VOLUME 1 Twenty-four Army helicopter pilots viewed videotaped Mark R. Nichols Nov. 1980 92 p refs segments of low-level and nap-of-the-Earth (NOE) helicopter flights (NASA-TM-81814; L-13251-Vol-1) Avail: NTIS as presented on television monitors designed to simulate an HC A05/MF A01 CSCL 01C airborne low-light-level television cockpit display system. While This bibliography was developed as a first step in the viewing these displays in an environment having no additional preparation of a monograph on the subject of the aerodynamics ambient illumination, these pilots were asked to set cockpit monitor of airframe/engine integration of high speed turbine powered luminance at the lowest level that they judged would permit aircraft. It lists 1535 unclassified documents published mainly successful flight control over the terrain being overflown. Each in the period from 1955 to 1980. Primary emphasis was devoted pilot adjusted luminance levels for eight different display conditions to aerodynamic problems and interferences encountered in the formed by the factorial combination of display size, type of terrain, integration process: however, extensive coverage also was given and object-luminance to display-luminance transfer function to the characteristics and problems of the isolated propulsion (system gamma function). Results show that pilots used lower system elements. A detailed topic breakdown structure is used. luminance settings when viewing the larger of the two display The primary contents of the individual documents are indicated sizes presented. They also used significantly lower luminance by the combination of the document's title and its location settings when viewing wooded terrain, with the system gamma within the framework of the bibliography. T.M. function modified to provide 'enhanced' contrast in the luminance range of interest, as against an unmodified system gamma function. The pilot's subjective impressions agreed with their N81-11033# Army Research and Technology Labs.. Moffett measured settings. This report discusses the impact of these Field. Calif. Aeromechanics Lab. results on the specifications of display requirements for a low EXPERIMENTAL AND ANALYTICAL STUDIES OF A MODEL light-level television system for aiding night NOE flight. GRA HELICOPTER ROTOR IN HOVER F. X. Caradonna and C. Tung 1980 20 p refs Presented at N81-11036# Aircraft Research and Development Unit. Edinburg the European Rotorcraft and Powered Lift Aircraft Forum. Bristol. (Australia). England. 16-19 Sep. 1980 FITMENT OF TAMAM STANDBY ATTITUDE INDICATORS (AD-A089780; Rept-25) Avail: NTIS HC A02/MF A01 CSCL TO MACCHI AIRCRAFT Engineering Report 20/4 D. K. King Aug. 1980 17 p The present study is a benchmark test to aid the development (AD-A089378: TI-683) Avail: NTIS HC A02/MF A01 CSCL of various rotor performance codes. The study involves simultane- 01/4 ous blade pressure measurements and tip vortex surveys. The Aircraft Research and Development Unit reworked Macchi Measurements were made for a wide range of tip Mach numbers MB 326H Draft Modification Order No 365 to install the'TAMAM' including the transonic flow regima. The measured tip vortex Standby Attitude Indicator (SAI) in the front and rear instrument strength and geometry permit effective blade loading predictions panels of Macchi aircraft. Modifications were also developed to when used as input to a prescribed wake lifting surface code. It provide independent switching and circuit protection for each is also shown that with proper inflow and boundary layer modeling, SAI on the existing FIRE/OVERHEAT panel in the Right hand the supercritical flow regime can be accurately predicted. GRA console of the front cockpit. RPM indicator lighting control was transferred from its individual rheostat to the panel lighting control and protection circuit. The modification was successfully test flown with particular emphasis on instrument readability, lack of N81-11034# Martin Marietta Corp.. Baltimore, Md. conflict with the flight controls and ease of operation. Residual CONTAINER LIFE ADAPTER-HELICOPTER (CLAH) OPERA- errors noted in the SAIs after maneuvers were large but were TIONAL PROTOTYPE (PREPRODUCTION) MILITARIZED immediately cancelled by operation of the caging knob. Trial UNITS FOR FLIGHT EVALUATION AND OPERATIONAL flying of the installation showed the modification to be operation- TESTING Final Report. Sop. 1978 - Apr. 1980 ally acceptable and fleet wide installation was recommended. Edgar G. Ball Aug. 1980 76 p GRA (Contract DAAK51-78-C-0026: DA Proj. 1L1-62209-AH-76) (AD-A089794; ER-15047: USAAVRADCOM-TR-80-D-20) Avail: NTIS HC A05/MF A01 CSCL 01/3 N81-11037*# National Aeronautics and Space Administration. This report covers the efforts required to manufacture and Lewis Research Center. Cleveland, Ohio. test two operational preproduction militarized CLAHs for Army LOW-SPEED AERODYNAMIC PERFORMANCE OF 50.8- flight evaluation and operational suitability. The CLAH is an CENTIMETER-DIAMETER NOISE-SUPPRESSING INLETS external load-carrying device that is suspended under a cargo FOR THE QUIET. CLEAN. SHORT-HAUL EXPERIMENTAL helicopter and enables the helicopter flight crew to automatically ENGINE (QCSEE) align with, engage, lock on. pick up, transport, and deposit an 8 John M. Abbott. James H. Diedrich. and Robert C. Williams x 8 x 20 foot MILVAN or commercial container without assistance Aug. 1978 37 p refs of ground crew. This production prototype CLAH design has (NASA-TP-1178: E-9542) Avail: NTIS HC A03/MF A01 CSCL evolved from a series of contracts involving research, study, 21E development, and testing of experimental container lifting devices. Two basic inlet concepts, a high throat Mach number (0.79) The design change per this contract included eliminating the design and a low throat Mach number (0.60) design, were tested retractable guide system and the pyrotechnic emergency jettison with four diffuser acoustical treatment designs that had face system. Reliability, maintainability, logistic and cost analyses sheet porosity ranging from 0 to 24 percent for the high Mach were conducted, and orientation/training sessions were provided number inlet and 0 to 28 percent for the low Mach number to enable Government personnel to operate, maintain, repair, inlet. The tests were conducted in a low speed wind tunnel at and provide logistic support for the CLAH field test program. free stream velocities of 0. 41, and 62 m/sec and angles of GRA attack to 50 deg. Inlet throat Mach number was varied about

35 N81 11038 the design value. Increasing the inlet diffuser face sheet porosity conditions with high total pressure fluctuation (turbulence). It is resulted in an increase in total pressure loss in the boundary recommended that improvements continue to be made in the layer for both the high and low Mach number inlet designs, statistical methods, particularly adjustments for high turbulence however, the overall effect on inlet total pressure recovery of conditions, and that the Melick method be used as an on-line 0.991 at the design throat Mach number, a free stream velocity distortion analysis tool for inlet performance tests. GRA of 41 m/sec, and an angle of attack of 50 deg; Inlet flow separation at an angle of attack of 50 deg was encountered N81-11041jj/ Pratt and Whitney Aircraft, West Palm Beach, with only one inlet configuration the high Mach number design Fla. Government Products Div. with the highest diffuser face sheet porosity (24 percent). A.R.H. DISK RESIDUAL LIFE STUDIES. PARTI: FIDO 1ST-STAGE TURBINE DISK (IN100) J. S. Cargill, J. K. Malpani. and Y. W. Cheng Dec. 1979 N81-11038*# National Aeronautics and Space Administration. 108 p refs Lewis Research Center, Cleveland, Ohio. Propulsion Lab. (Contract F33615-77-C-5172; AF Proj. 7351) OFF-DESIGN PERFORMANCE LOSS MODEL FOR RADIAL (AD-A089791: PWA-FR-11878-Vol-1; AFML-TR-79-4173-P1-1) TURBINES WITH PIVOTING, VARIABLE-AREA STATORS Avail: NTIS HC A06/MF A01 CSCL 21/5 Peter L. Meitner and Arthur J. Classman Nov. 1980 15 p A residual fatigue life prediction method, suitable for refs Retirement-for-Cause application, has been developed for two P (NASA-TP-1708: AVRADCOM-TR-80-C-13: E-455) Avail: WA turbine disks: the F100 1st-stage high pressure turbine disk NTIS HC A02/MF A01 CSCL21E and the TF30 10th-stage compressor disk. The method is based An off-design performance loss model was developed for upon interaction of fracture mechanics crack propagation modeling variable stator (pivoted vane), radial turbines through analytical concepts with laboratory nondestructive evaluation (NDE) modeling and experimental data analysis. Stator loss is determined techniques. Fracture mechanics life models were developed using by a viscous loss model-: stator vane end-clearance leakage effects the GPD hyperbolic sine (SINH) model refined during an earlier are determined by a clearance flow model. Rotor loss coefficient Air Force Materials Laboratory (AFML) program. Stress intensity were obtained by analyzing the experimental data from a turbine (K) solutions for the engine components were based upon rotor previously tested with six stators having throat areas from experimental effective K determinations made during full-scale 20 to 144 percent of design area and were correlated with component fatigue tests. The NDE techniques developed for.disk stator-to-rotor throat area ratio. An incidence loss model was inspections included acoustic emission (AE), eddy current (EC), selected to obtain best agreement with experimental results. and fluorescent penetrants (FP). Stress-enhanced penetrant and Predicted turbine performance is compared with experimental semi-automated rotating probe EC techniques were developed results for the design rotor as well as with results for extended as periodic inspections, while the AE time-domain technique was and cutback versions of the rotor. Sample calculations were developed as a real-time inspection tool. GRA made to show the effects of stator vane end-clearance leakage. Author NB1-11042# RAND Corp., Santa Monica. Calif. AIRCRAFT TURBINE ENGINE MONITORING EXPERIENCE. AN OVERVIEW AND LESSONS LEARNED FROM SELECTED N81 11039*# National Aeronautics and Space Administration. CASE STUDIES Interim Report Lewis Research Center, Cleveland, Ohio. John L Birkler and J. R. Nelson Aug. 1980 115 p refs SURFACE PYROMETRY IN PRESENCE OF RADIATION (Contract F49620-77-C-0023) FROM OTHER SOURCES WITH APPLICATION TO TURBINE (AD-A089752: RAND/R-2440-AF) Avail: NTIS BLADE TEMPERATURE MEASUREMENT HC A06/MF A01 CSCL 21/5 Donald R. Buchele Nov. 1980 19 p refs Two approaches have evolved in attempts to improve engine (NASA-TP-1754: E-396) Avail: NTIS HC A02/MF A01 CSCL operations, maintenance, and management while reducing support 21E costs. The first concentrates on short-term practices (inflight data Surface pyrometry is feasible even when the amount of surface are recorded in a snapshot mode). The second approach focuses radiation is exceeded by radiation from surrounding sources. To on long-term benefits through improved knowledge of the measure and correct for this interfering radiation, several methods operating environment. (Data must be recorded continuously on that use multiple wavelength pyrometry were compared by an at least a few aircraft.) Engine duty-cycle research by the military error analysis. For a specific application to turbine blade services has demonstrated that neither the sen/ices nor the temperature measurement in a turbofan engine, a two wavelength manufactures have a clear idea of power requirements and frequent method was best. Auxiliary measurements at the same wave- throttle movements during operational sorties in fighter aircraft lengths substantially improve the accuracy of the method. S.F. and have generally overestimated engine parts life and underex- pected life-cycle costs. The narrow concept of cost savings over N81 11040# ARO, Inc., Arnold Air Force Station. Tenn. the short term should not be the sole criterion on which monitoring AN EVALUATION OF STATISTICAL METHODS FOR THE systems are judged. Monitoring systems for recent and future PREDICTION OF MAXIMUM TIME-VARIANT INLET TOTAL engines should include continuously recorded data now that PRESSURE DISTORTION Final Report, 1 Oct. 1978-24 Sep. reliability, durability, and cost issues are almost on an equal footing with performance. GRA 1979 Marvin E. Sanders and Richard E. Christenson AEDC Sep. 1980 56 p refs Sponsored by Air Force N81-11043*# National Aeronautics and Space Administration. (AD-A089817: AEDC-TR-79-77) Avail: NTIS Ames Research Center. Moffett Field. Calif. HC A04/MF A01 CSCL 21/5 SIMULATING STUDY OF THE INTERACTION BETWEEN An analysis was conducted to determine the accuracies and THE PROPULSION AND FLIGHT CONTROL SYSTEMS OF limitations of three statistical methods used to predict engine-face A SUBSONIC LIFT FAN VTOL maximum time-variant total pressure distortion. The statistical Bruce E. Tinling and Gary L. Cole Nov. 1980 50 p refs methods have all been proposed as low-cost alternatives to the (NASA-TM-81239: A-8346) Avail: NTIS HC A03/MF A01 time-consuming and costly deterministic method generally used CSCL 01 C for reducing engine-face time-variant total pressure data. The The possibility of interactions between the propulsion and statistical methods are evaluated by comparing their predicted flight control systems of a three-fan subsonic VTOL aircraft was distortion values and patterns to those measured with the studied using nonreal time simulation. Time histories of critical deterministic method. Data comparisons from tests of four different internal engine parameters were obtained and possible deleter- inlet models, covering a wide range of Mach numbers, mass ious effects of engine dynamics on flight control were identified flow ratios, model attitudes, and distortion factors, were used and analyzed. No deleterious effects, with the exception of the during the analysis. The results show good agreement between effects of the fan actuator deadband, were found. A method of the measured and predicted values for all three statistical methods. alleviating these effects through feedback of the actuator output The distortion pattern predictions, however, were inadequate at to the flight controller was developed. T.M.

36 N81-11058

N81-11044*# National Aeronautics and Space Administration. N81-11047# Systems Research Labs.. Inc.. Dayton, Ohio. Ames Research Center. Moffett Field. Calif. A MULTIVARIATE APPROACH TO HANDLING QUALITIES FLIGHT EVALUATION OF STABILIZATION AND COMMAND RATING SCALE DEVELOPMENT Final Report. 1 Jun. - AUGMENTATION SYSTEM CONCEPTS AND COCKPIT 30 Sep. 1979 DISPLAYS DURING APPROACH AND LANDING OF Ralph H. Smith and Warren S. Torgenson Jan. 1980 186 p POWERED-LIFT STOL AIRCRAFT refs James A. Franklin. Robert C. Innis. and Gordon H. Hardy Nov. (Contract F49620-79-C-0158: AF Proj. 2313) 1980 94 p refs (AD-A089825: AFOSR-80-0876TR) Avail: NTIS (NASA-TP-1551: A-7968) Avail: NTIS HC A05/MF A01 CSCL HC A09/MF A01 CSCL 01/3 QIC Recent advances in aircraft handling qualities indicate the A flight research program was conducted to assess the possibility that a small number of physical dimensions can be effectiveness of manual control concepts and various cockpit used for handling qualities quantification. Several candidate displays in improving altitude (pitch, roll, and yaw) and longitudinal metrics for handling qualities now exist which form a portion of path control during short takeoff aircraft approaches and landings. the set required. An exploratory study was conducted to evaluate Satisfactory flying qualities were demonstrared to minimum the use of multivariate analysis techniques for identification of decision heights of 30 m (100 ft) for selected stabilization and the necessary physical dimensions of handling qualities. It is command augmentation systems and flight director combinations. concluded that the Cooper-Harper scale can be considered a Precise landings at low touchdown sink rates were achieved direction in the space defined by the first few principal compo- with a gentle flare maneuver. . S.F. nents of the experimental variance-covariance matrix. A simulation experiment is proposed which should permit development of a N81-11045/J Range Commanders Council. White Sands Missile set of nonadjectival rating scales which will complement the Range. N. Mex. Range Safety Group. Cooper-Harper scale, reduce the variability of pilot rating data, FLIGHT TERMINATION RECEIVER/DECODERS DESIGN. and better support the flight test identification of handling PERFORMANCE AND CERTIFICATION Final Report deficiencies. GRA 1980 20 p Supersedes RSG-313-72 (AD-A089746: RSG-313-80: RSG-313-72) Avail: NTIS N81-11049$ Southampton Univ. (England). Dept. of Aeronautics HC A02/MF A01 CSCL 16/1 and Astronautics. This document contains design, performance, and certification THE PRINCIPLES AND APPLICATIONS OF CRYOGENIC test requirements for range safety flight termination system WIND TUNNELS command destruct receiver/decoders. It replaces Range Com- M. J. Goodyer In AGARD Cryogenic Wind Tunnels Jul. 1980 manders Council (RCC) Range Safety Group (RSG) Document 6 p refs 313-72. Flight termination is an emergency action taken by Range Avail: NTIS HC A12/MF A01 Safety for the protection of life and property when a vehicle The background to the emergencies of the cryogenic wind violates established safety criteria. This action circumvents the tunnel is described and its advantages compared with other means vehicle's normal control modes and ends its power and/or for raising the values of test Reynolds number to full scale are controlled flight. Flight termination procedures may include any discussed. The basic aero and thermodynamics of wind tunnel one or a combination of the following: (a) Complete vehicle testing is introduced and the advantages of low temperature in destruction by explosive means: (b) Aerodynamic disruption of low speed and in transonic testing are quantified. Attention is the flight mechanism: (c) Deployment of high drag devices: drawn to secondary advantages unique to this tunnel, and to (d) Fuel cut-off to the combustion chambers of ignited motors: the potentials of unconventional test gases. Descriptions of current (e) Inhibit ignition of unburned motors: and (f) Other special types and applications of cyrogenic wind tunnels are included. actions dictated by the vehicle configuration or special problems. R.K.G. These actions may be activated by manual, computerized and/or automated modes. GRA N81-11057*# National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. MODEL DESIGN AND INSTRUMENTATION EXPERIENCES N81-11046# Purdue Univ., Lafayette. Ind. School of Aeronautics WITH CONTINUOUS-FLOW CRYOGENIC TUNNELS and Astronautics. Robert A. Kilgore In AGARD Cryogenic Wind Tunnels Jul. MULTIVARIABLE CLOSED-LOOP ANALYSIS AND FLIGHT 1980 22 p refs CONTROL SYNTHESIS FOR AIR-TO-AIR TRACKING Final Avail: NTIS HC A12/MF A01 CSCL 148 Report. 1 Jan. - 31 Dec. 1979 The development of wind tunnels that can be operated at David K. Schmidt 18 Jun. 1980 105 p refs cryogenic temperatures has placed several new demands on the (Grant AF-AFOSR-0042-79: AF Proj. 2313) ability to build and instrument wind tunnel models. The experiences (AD-A090050: AFOSR-80-0961TR) Avail: NTIS at the NASA Langley Research Center relative to the design HC A06/MF A01 CSCU 05/8 and instrumentation of models for continuous flow cryogenic A synthesis method based on optimal control techniques, wind tunnels are reviewed. R.K.G. closed-loop task-oriented design objectives, and an optimal control model of the human pilot was applied to augment the system dynamics in the air-to-air tracking task. Single and multi-axis N81-11058# Douglas Aircraft Co.. Inc.. Long Beach. Calif. analyses were performed. Single axis results, obtained for Aerodynamics Subdiv. longitudinal pitch tracking with different sets of active sight display MODEL DESIGN AND INSTRUMENTATION FOR INTERMIT- dynamics, indicate the optimum system dynamics were affected TENT CRYOGENIC WIND TUNNELS by numerator (or display) dynamics. Improved tracking perfor- J. D. Cadwell In AGARD Cryogenic Wind Tunnels Jul. 1980 mance was predicted, and the trends in augmented system 8 p refs dynamics (eigenvalues) were shown to agree with previous results. Avail: NTIS HC A12/MF A01 Moving-base simulation results obtained for a highly-banked flight The design and instrumentation of a model for an intermittent condition were also used to establish a new multi-axis pilot cryogenic wind tunnel is discussed. The model requirements model. This model is considered suitable for simultaneous control including tolerances and data accuracy are noted. The mechanical of the dynamically interacting longitudinal and lateral-directional design of the wing, the considerations for material to be used, axes of the vehicle/display system. The system augmentation, and the instrumentation that is to be installed in the wing are based on this model, again was predicted to significantly improve discussed. The design of the fuselage center section, the six performance. The trends in system eigenvalues for various component balance installation with heaters, and the heater for augmentation levels showed good agreement with the above the balance-to-sting adapter is reviewed. The design and the aft longitudinal results. However, the lateral-directional axis was found fuselage and empennage, and the fuselage nose including the to be much more important, and significant modification of the instrumentation package to be housed in the fuselage nose dynamics were predicted to lead to system improvements. GRA compartment is shown. The model conditioning that is required

37 N81-11060

to obtain acceptable data: prevent frost buildup on the model (AD-A089750; AEDC-TR-80-11) Avail: NTIS after it is cooled, and reheating the model to make model HC A06/MF A01 CSCL 16/2 configuration changes is also discussed. R.K.G. A dynamic derivative sensitivity study was conducted to demonstrate the importance of dynamic derivatives in missile motion simulation studies. Generalized bank-to-turn and yaw-to- N81-11060# Douglas Aircraft Co.. Inc., Long Beach, Calif. turn missile configurations were used with a six degree of Aerodynamics Subdiv. freedom linearized stability program. The effects of various dynamic CALIBRATION OF A B LOWD OWN-TO-ATMOSPHERE derivatives on missile stability were investigated in both level CRYOGENIC WIND TUNNEL and turning flight for several Mach numbers and altitude J. D. Cadwell In AGARD Cryogenic Wind Tunnels Jul. 1980 conditions. GRA 9 p refs Avail: NTIS HC A12/MF A01 N81-11113*# National Aeronautics and Space Administration. Calibration of short duration cryogenic wind tunnels pose Langley Research Center. Hampton, Va. difficulties and requirements beyond those already present in A PROBABILISTIC ANALYSIS OF ELECTRICAL EQUIPMENT the calibration either of conventional short run time facilities or VULNERABILITY TO CARBON FIBERS of cryogenic continuous tunnels. The requirements and instrumen- Wolf Elber Oct. 1980 31 p refs tation for calibration of a transonic blowdown to atmosphere (NASA-TM-80217) Avail: NTIS HC A03/MF A01 CSCL cryogenic wind tunnel are described, with emphasis on those 110 aspects differing from the calibration of similar non-cryogenic The statistical problems of airborne carbon fibers falling onto tunnels. Reference is made of the literature for detailed descriptions electrical circuits were idealized and analyzed. The probability of. of conventional calibration practices which remain applicable for making contact between randomly oriented finite length fibers cryogenic blowdown tunnels. Author and sets of parallel conductors with various spacings and lengths N81-11063# Douglas Aircraft Co.. Inc., Long Beach. Calif. was developed theoretically. The probability of multiple fibers Aerodynamics Subdiv. joining to bridge a single gap between conductors, or forming THE CONTROL OF PRESSURE. TEMPERATURE AND MACH continuous networks is included. From these theoretical considera- NUMBER IN A BLOWDOWN-TO-ATMOSPHERE CRYO- tions, practical statistical analyses to assess the likelihood of GENIC WIND TUNNEL causing electrical malfunctions was produced. The statistics J. D. Cadwell In AGARD Cryogenic Wind Tunnels Jul. 1980 obtained were confirmed by comparison with results of control- 8 p ref led experiments. A.R.H. Avail: NTIS HC A12/MF A01 The control system that used in a four foot blowdown wind N81-11116# General Dynamics/ Convair. San Diego. Calif. tunnel prior to the modification of the facility to a cryogenic DEVELOPMENT OF ADVANCED INTERCEPTOR SUB- operation is reviewed. The control requirements for a cryogenic STRUCTURAL MATERIAL blowdown tunnel and the Mach and Reynolds number controls Julius Hertz and Norman R. Adsit Aug. 1980 163 p refs are discussed. The proposed method to be used to control the (Contract DAAG46-78-C-0056: DA Proj. 1W1-62113-A-661) temperature in the cryogenic tunnel is shown. The start of a (AD-A090127: AMMRC-TR-80-44) Avail: NTIS blow sequence in a cryogenic blowdown tunnel and the detrimental HC A08/MF A01 CSCL 1 1/4 effect that it has on a pre cooled model is considered. A transient This report is aimed at the development of ultra-high modulus protection system, to be evaluated in a one foot pilot tunnel graphite/epoxy structures for use in future advanced terminal that will shield the model during the start of a run is shown. interceptors. The work has produced a preliminary full-scale design The conventional method of measuring model attitude by and demonstrated, experimentally and analytically, that the design correcting the pod angle for sting and balance deflections is will carry the loads. More study needs to be conducted and shown to be inadequate in a cryogenic blowdown tunnel and some further experimental work is recommended before a full-scale alternate methods that can be used are discussed. Author article is tested The present work has concentrated on testing the aft joint and an intermediate ring for holding an equipment N81-11064# National Aerospace Lab.. Amsterdam (Netherlands). package in the frustra. GRA THE EUROPEAN TRANSONIC WIND TUNNEL ETW J. P. Hartzuiker and R. J. North In AGARD Cryogenic Wind Tunnels Jul. 1980 17 p refs N81-11117*# Naval Surface Weapons Center. Dahlgren. Va. Environmental Test Chamber. Avail: NTIS HC A12/MF A01 FIBER RELEASE FROM IMPACTED GRAPHITE REIN- A high Reynolds number transonic tunnel is described on FORCED EPOXY COMPOSITES Final Report the basis of preliminary design results. The construction of a T. C. Babinsky Jun. 1980 71 p Sponsored by NASA cryogenic pilot tunnel and supporting programs on model design (NASA-CR-163684; AD-A090112: NSWC/TR-80-216) Avail: and instrumentation are discussed. S.F. NTIS HC A04/MF A01 CSCL 11D Carbon fibers released from composites by aircraft fires and crashes can cause electrical shorts and consequent equipment N81-11065*# National Aeronautics and Space Administration. damage. This report investigates less vigorous release mechanisms Langley Research Center. Hampton, Va. than that previously simulated by explosive burn/blast tests. When CHARACTERISTICS AND STATUS OF THE US NATIONAL AS/3501-6 composites are impacted by various head and weight TRANSONIC FACILITY configurations of a pendulum impactor, less than 0.2 percent by William 0. Igoe In AGARD Cryogenic Wind Tunnels Jul. weight of the original sample is released as single fibers. Other 1980 11 P refs fiber release mechanisms studied were air blasts, constant Avail: NTIS HC A12/MF A01 CSCL 14B airflow, torsion, flexural. and vibration of composite samples. A major application of the cryogenic wind tunnel concept is The full significance of the low single fiber release rates found discussed- A closed return fan driven circuit with a 2.5 meter here is to be evaluated by NASA in their aircraft vulnerability square slotted test section, pressurized up to 8.85 atmospheres, studies. GRA and providing chord Reynolds numbers of 120 million based on a chord Of 0.25 meter at transonic speeds using cold nitrogen as the test gas is described. S.F. N81-11118# Aerospace Corp.. El Segundo. Calif. Materials Sciences Lab. MICROCRACKING IN GRAPHITE-EPOXY COMPOSITES N81-11093# ARO. Inc., Arnold Air Force Station, Tenn. Interim Report MISSILE MOTION SENSITIVITY TO DYNAMIC STABILITY Ernest G. Wolff 1 Sep. 1980 34 p refs DERIVATIVES Final Report. 1 Oct. 1978 - 30 Sep. 1979 (Contract F04701-79-C-0080) T. F. Langham AEDC Sep. 1980 111 p refs Sponsored by (AD-A089894: TR-0080-5950-01-1: SD-TR-80-65) Avail: Air Force NTIS HC A03/MF A01 CSCL 11/4

38 N81-11134

Microcracking in composite materials is commonly caused The changes in conditioning procedure which have taken place by ply stiffness variations in crossply layup during application of are outlined along with the factors which have influenced these applied stress, and by differential thermal expansion coefficients changes. Author of the fiber and the matrix during thermal excursions. It is responsible for changes in macro- and micrornechanical properties, N81-11130# Toronto Univ.. Downsview (Ontario). Inst. for permeability to gases, and dimensional instability. Theories, Aerospace Studies. experimental techniques, and effects of microcracking are EFFECT OF VARIOUS ENVIRONMENTAL CONDITIONS ON reviewed. The coefficient of cracking expansion is defined, and POLYMER MATRIX COMPOSITES procedures for reducing deleterious effects of microcracking on R. C. Tennyson In AGARD Effect of Serv. Environ, on Composite composite structures are presented. GRA Mater. Aug. 1980 21 p refs

N81-11120# Naval Air Development Center. Warminster. Pa. Avail: NTIS HC A15/MF A01 Aircraft and Crew Systems Technology Directorate. Experimental results obtained on the short and long term COMPATIBILITY OF AIRCRAFT OPERATIONAL FLUIDS behavior of polymer matrix composites subjected to various WITH A GRAPHITE/EPOXY COMPOSITE: DEVELOPMENT environmental conditions are given. Changes in mechanical OF AN EXTERIOR COATING SYSTEM AND REMOVER Final stiffness, strength and coefficient of thermal expansion were Report measured under ambient pressure and thermal vacuum conditions. K. G. Clark 26 Jun. 1980 43 p refs In all tests involving the vacuum environment, measurements (ZF54502001) were made in-situ, necessitating the use of mechanical loading (AD-A090049; NADC-80046-60) Avail: NTIS fixtures acting through flexible bellows to provide stiffness and HC A03/MF A01 CSCL 11/4 strength data. Results are given on the effects of varying some The objective of this investigation is the identification of fabrication parameters (length of post-cure time and rate of aircraft operational and specialty chemical which are potentially cool-down in autoclave) on the changes observed in strength detrimental to the integrity of organic matrix composites. In this and stiffness. The materials investigated include: graphite/epoxy. report, results of several studies made with the graphite/epoxy boron/epoxy. PRD-49/epoxy and E glass/epoxy. S.F. Hercules AS/3501-6 are disclosed. Several alternatives to the problem of paint removal are discussed. It is concluded that N81-11131# Deutsche Forschungs- und Versuchsanstalt fuer water and maintenance fluids containing water produce significant Luft- und Raumfahrt. Brunswick (West Germany). Inst. for plasticization of graphite/epoxy, while most solvents, oils, Structural Mechanics. hydraulic fluids, and fuel cause no significant mechanical losses. PREDICTABILITY OF MOISTURE ABSORPTION IN Paint removal was found to be a significant problem due to the GRAPHITE/EPOXY SANDWICH PANELS activity of chemical removers. Removal is complicated by the H. W. Bergmann and P. Nitsch In AGARD Effect of Serv. fact that stripping thermoset coatings from graphite/epoxy is Environ, on Composite Mater. Aug. 1980 11 p refs more difficult than stripping from aluminum. A 'weak link' coating system using a nitrocellulose primer is. thus far. the best strippable Avail: NTIS HC A15/MF A01 composite coating if used with the simple methylene chloride Graphite/epoxy materials tend, to degrade in hot and moist remover designated 4-70-1. It is recommended that confirmational environments. The high dependence of the strength loss on the testing with tensile, flexure, compression, fatigue and dynamic moisture content demands an assessment of the amount and mechanical specimens of graphite/epoxy and possibly some distribution of absorbed moisture, particularly in the case of adhesive, be made. Following these tests, the nitrocellulose/ lightweight sandwich panels. The reliability of such predictions polyurethane coating system should be field tested on graphite/ hinges on the formulation of theoretical considerations, the epoxy aircraft substrates. GRA accuracy of numerical processes, the definition of material constants and a proper interpretation of the environmental conditions. The impact of errors in these parameters on predicted N81-11128# Advisory Group for Aerospace Research and moisture contents, and comparisons of analytical forecasts with Development, Neuilly-Sur-Seine (France). experimentally determined values, are the topics of this paper. EFFECT OF SERVICE ENVIRONMENT ON COMPOSITE S.F. MATERIALS N81-11133# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich Aug. 1980 326 p refs In ENGLISH; partly in FRENCH Presented (West Germany). at the 50th Meeting of the AGARD Struct, and Mater. Panel. CONSTANT-AMPLITUDE AND FLIGHT-BY FLIGHT TESTS Athens. 14-17 April 1980 ON CFRP SPECIMENS (AGARD-CP-288: ISBN-92-835-0273-6) Avail: NTIS F. J. Arendts, K. O. Sippel, and D. Weisgerber In AGARD HC A15/MF A01 Effects of Serv. Environ, on Composite Mater. Aug. 1980 12 p The effects of environmental and mechanical stress on the refs Sponsored in part by Ministry of Defense composite materials of aircraft structures are described. Graphite- epoxy and carbon fiber reinforced plastics are tested for fatigue Avail: NTIS HC A15/MF A01 and tensile creep. Effects of environmental temperature and Constant amplitude and flight by flight tests with five different moisture (humidity) are emphasized. Applications for aerodynamic load spectra were done with unnotched carbon fiber reinforced and aerospace engineering are included. plastic specimens. The influence of overloads was investigated. The test results were compared with fatigue life predictions based on 'miner's rule' applied for different conditions. Overloads in all N81-11129# British Aerospace Aircraft Group. Preston (England). cases cause a significant reduction of the fatigue life. Fatigue Advanced Structural Applications Dept. life estimations based on 'miner's rule' are on the unsafe side THE IMPLICATIONS OF LABORATORY ACCELERATED in some cases by more than a factor 10. getting a big scatter CONDITIONING OF CARBON FIBRE COMPOSITES among the cases investigated. S.F. E. C. Edge In AGARD Effect of Serv. Environ, on Composite Mater. Aug. 1980 17 p refs N81-11134| Laboratorium fuer Betriebsfestigkeit. Darmstadt Avail: NTIS HC A15/MF A01 (West Germany). The evidence on the effects of long term natural weathering FATIGUE STRENGTH OF CFRP UNDER COMBINED of carbon fiber composites is examined and its implications with FLIGHT-BY FLIGHT LOADING AND FLIGHT-BY-FLIG HT regard to the conditioning of test specimens discussed. The effects TEMPERATURE CHANGES of laboratory accelerated tests on the properties of some composite J. J. Gerharz and D. Schuetz In AGARD Effect of Serv. Environ. materials are considered in conjunction with the relevance of on Composite Mater. Aug. 1980 24 p refs data thus acquired to real life situations and the need to generate the data with reasonable speed for design considerations. Avail: NTIS HC A15/MF A01

39 N81-11135

Influence of environment on the fatigue of carbon fiber Helicopter rotors are subjected to a certain number of reinforced plastics unnotched, notched and bolted specimens is aggressions associated with the environment in which they rotate. studied. The specimens are simultaneously subjected to load and The use of new materials such as carbon and glass epoxy environmental histories. A flight by flight load and environment composites requires the manufacturer to conduct specific sequence typical for the wing root of a fighter airplane is applied. qualification research programs for each of these aggressions. Tests with simplified simulation of environment, allowing high The modes of degradation from rain and sand erosion and from loading frequencies, are run. The admissibility of the simplifications civil and military impacts on blades made of composite materials is evaluated by comparing the results of each simplified test are presented. Research on erosion enabled selection of the most with the results from long time quasi real time test with effective protective materials. Experience in the use of blades temperatures accompanying the loads in each flight. The 'quasi as well as results from firing and impact tests show an excellent real time' flight by flight program includes temperature cycles fatigue behavior after shocks and impact, due in a large measure and a humidity cycle. The specimens are heated and cooled by to the fail-safe character of composite materials. This good preconditioned air forced through the test chamber. The results behavior, associated with the possibility of very extensive repairs, of room temperature fatigue tests and of static tests at various is an important factor to the superiority of composite blades environmental conditions are available. For a constant fatigue over metal blades. Transl. by A.R.H. stress level residual strength and stiffness data demonstrate the damage growth made apparent by ultrasonic scan records. S.F. N81-11139*$ National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. N81-11135# Royal Netherlands Aircraft Factories Fokker. GRAPHITE-EPOXY PANEL COMPRESSION STRENGTH Rijswijk. REDUCTION DUE TO LOCAL IMPACT FATIGUE TEST RESULTS OF CARBON FIBER REINFORCED Michael F. Card and Marvin D. Rhodes In AGARD Effect of PLASTIC F28 AIRCRAFT COMPONENT AND ITS STRUC- Serv. Environ, on Composite Mater. Aug. 1980 13 p refs TURAL DETAILS J. A. A. M. Dijns In AGARD Effect of Serv. Environ, on Avail: NTIS HC A15/MF A01 CSCL 11D Composite Mater. Aug. 1980 5 p The effects of low velocity impact on the compressive strength of graphite/epoxy structures are reviewed. Extensive tests were Avail: NTIS HC A15/MF A01 conducted on sandwich beams, laminated plates and stiffened As a part of the development program on the structural panels. Conditions for failures were investigated by impact tests application of carbon fiber reinforced plastic composites in aircraft on statically loaded test specimens. Lightly loaded graphite structures, a speedbrake was designed and built in carbon fiber structures (such as aircraft secondary structure) were insensitive reinforced plastics and aramide fiber composites. Different to impact damage. In more heavily loaded structures, (such as configurations were studied and one was selected for a detailed wing panels), appreciable reductions in compressive strength design in the form of a schematic model. Test were carried out occurred. The implications of the tests for structural design are on structural details and two schematic speedbrake models were discussed by comparing panel masses for designs where ultimate fabricated for full scale static and dynamic load tests. One strains were reduced due to impact considerations with the masses speedbrake was produced for flight testing on an operational of designs with higher ultimate strains. Preliminary test data are aircraft. The tests resulted in a design of the speedbrake in presented to show the possibility of improvements in damage which no metal parts were used and in which all joints were to tolerance achievable by using an alternate matrix material. bonded with 120 C and room temperature curing adhesives. R.K.G. without the use of additional fasteners. The first model speedbrake was successfully tested to ultimate load without failure or any N81-11141# Centre d'Essai Aeronautique. Toulouse (France). plastic deformation. The second model speedbrake was tested ASSESSING THE BEHAVIOR OF HIGH MODULUS COM- at a maximum fatigue load equal to 65 percent of the ultimate POSITE MATERIALS IN LIGHTNING [EVALUATION DU load. The full size CFRP speedbrake showed a weight saving of COMPORTEMENT A LA FOUDRE DE STRUCTURES EN 25 percent when compared with the Al alloy design. S.F. MATERIAUX COMPOSITES HAUT MODULE] J. Rouchon and D. Gall In AGARD Effect of Serv. Environ, N81-11137# Royal Aircraft Establishment. Farnborough on Composite Mater. Aug. 1980 14 p In FRENCH (England). Materials Dept. RELATIONSHIPS BETWEEN IMPACT RESISTANCE AND Avail: NTIS HC A15/MF A01 FRACTURE TOUGHNESS IN ADVANCED COMPOSITE Lightning strikes of aircraft in flight are relatively frequent MATERIALS and result in damage and even destruction to both equipment G. Dorey In AGARD Effects of Serv. Environ, on Composite and structures, particularly those made of composite materials. Mater. Aug. 1980 11 p refs Generalities about lightning are reviewed and methods for measuring it during flight and simulating it on the ground are Avail: NTIS HC A15/MF A01 described. Results are presented for laboratory tests on carbon- A variety of CFRP laminates and one GRP laminate were epoxy monolithic and boron-epoxy coated sandwich specimens, subjected to impact by steel balls, over a range of incident and on the elements of real structures. Associated control energies, and residual strengths were measured. Superimposed processes are also considered. Transl. by A.R.H. static load during impact substantially altered the residual strength curves. The laminates were also tested with machined notches and analyzed in terms of fracture toughness. Results of impact N81-111420 Boeing Co., Seattle, Wash. performance both during impact and in subsequent residual LIGHTNING PROTECTION CONSIDERATIONS FOR strength tests were compared, with the aim of correlating service GRAPHITE/EPOXY AIRCRAFT STRUCTURE performance with laboratory toughness tests. Effects of materials S. D. Schneider In AGARD Effect of Serv. Environ, on Composite and geometric variables are discussed together with possibilities Mater. Aug. 1980 6 p refs for improvements. R.K.G. Avail: NTIS HC A15/MF A01 When advanced composites such as graphite/epoxy were N81-11138# Societe Nationale Industrielle Aerospatiale. first being considered for aircraft structure, a common belief Marignane (France.) Div. Helicopteres. was that lightning would heavily damage the structure. This belief EROSION AND IMPACTS ON COMPOSITE HELICOPTER has since proven to be false. Advanced composites react to BLADES [EROSION ET IMPACTS SUR LES PALES lightning strikes in a manner different from aluminum, but the D'HELICOPTERES EN COMPOSITES] resultant damage is by no means alarming. Two basic types of M. Torres In AGARD Effect of Serv. Environ, on Composite lightning damage to which aircraft structures are subjected, are Mater. Aug. 1980 10 p In FRENCH discussed. Known, documented techniques and design philoso- phies for protection against lightning caused structural damage Avail: NTIS HC A15/MF A01 are reviewed for classical aluminum aircraft structure fabricated

40 N81-11233

with metal fasteners, and the impact of graphite/epoxy on these technology program to reduce fuel consumption of commercial classical approaches is addressed. Detailed lightning test criteria, transport aircraft through the use of advanced composites is test techniques, and criteria are also given and related to graphite described, including preliminary results. Ground and flight structures. R.K.G. environmental effects on the composite materials used in the flight service programs are also discussed. J.M.S. N81-11143*# National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. N81-11148# Air Force Wright Aeronautical Labs., Wright- THE POTENTIAL FOR DAMAGE FROM THE ACCIDENTAL Patterson AFB. Ohio. Systems Support Div. RELEASE OF CONDUCTIVE CARBON FIBERS FROM AIR FORCE APPLICATIONS AND IN-SERVICE EXPERIENCE AIRCRAFT COMPOSITES WITH COMPOSITE STRUCTURES Vernon L. Bell In AGARD Effect of Serv. Environ, on Composite Frank J. Fechek In AGARD Effect of Serv. Environ, on Composite Mater. Aug. 1980 21 p refs Mater. Aug. 1980 10 p

Avail: NTIS HC A15/MF A01 CSCL 11D Avail: NTIS HC A15/MF A01 Carbon and graphite fibers are known to be electrically Advanced composite development programs which contribute conductive. The rapidly accelerating use of carbon fibers as the to the capability to use these materials in primary and secondary reinforcement in filamentary composite materials brought up the structures on high performance military aircraft are described. possibility of accidental release of carbon fibers from the burning Emphasis is placed on a systematic, periodic nondestructive of crashed commercial airliners with carbon composite parts. evaluation of selected composite structures in operational service. Such release could conceivably cause widespread damage to Visual and X-radiographic inspection techniques are shown to electrical and electronic equipment. The experimental and be quite usable on composite strucutres in the field. However, analytical results of a comprehensive investigation of the various inefficiencies using available, portable ultrasonic inspection elements necessary to assess the extent of such potential damage equipment in the field environment accentuate the need for the in terms of annual expected costs and maximum losses at low development of a semi-automated, ultrasonic inspection system probabilities of occurrence are presented. A review of NASA specifically designed to be compatible with current, production materials research program to provide alternate or modified composite aircraft structures. A system satisfying these needs is composite materials to overcome any electrical hazards from shown to be feasible. J.M.S. the use of carbon composites in aircraft structures is described. R.K.G. N81-11149# Naval Air Systems Command. Washington. D. C. N81-11145# Westland Helicopters Ltd.. Yeovil (England). US NAVY SERVICE EXPERIENCE WITH ADVANCED FATIGUE AND DAMAGE PROPAGATION IN COMPOSITE COMPOSITES ROTOR BLADES A. Somoroff, M. Dubberly, J. M. McGinn. M. Tarricone. and A. A. J. Barnard In AGARD Effect of Serv. Environ, on Composite Manno (Naval Air Development Center. Warminster. Pa.) In Mater. Aug. 1980 17 p Sponsored by Ministry of Defense. AGARD Effect of Serv. Environ, on Composite Mater. Aug. England 1980 16 p refs Avail: NTIS HC A15/MF A01 Avail: NTIS HC A15/MF A01 The development and flight evaluation of carbon/glass fiber Lifetime durability information encompassing laboratory reinforced plastic rotor blades is considered. Results are presented programs, exposure of ground specimens and observation of flight from tests undertaken on tail and main blades. The excellent structures is presented. The specific structures discussed include fatigue and damage propagation characteristics of the composite the F-14 horizontal stabilizer and the H-46 rotor blade which blades are emphasized. The rig and flight tests demonstrated are in production, and the YAV-8B wing developed for production unlimited fatigue lives for the composite blades and the structural of the AV-8B. Also discussed are S-3 spoilers and F-4 access element tests indicated low material scatter factors in both static doors which were developed exclusively to acquire service data. and fatigue cases. Test results also indicate improved safety It is noted that the F-18 aircraft makes extensive use of through the use of composite blades. J.M.S. graphite-epoxy composites in primary wing, horizontal stabilizer, and vertical stabilizer skin structure. As of the end of February N81-11146# Messerschmitt-Boelkow-Blohm G.m.b.H.. Munich 1980. eleven F-18 development aircraft are engaged in flight (West Germany). test evaluation. A cumulative total of more than 900 flight hours SERVICE EXPERIENCE WITH GRC HELICOPTER BLADES have been accumulated with the highest number of flight hours I BO-105) for an individual aircraft being 214 and the longest calendar K. Brunsch In AGARD Effect of Serv. Environ, on Composite service time for an individual aircraft being 18 months. During Mater. Aug. 1980 17 p refs this period the graphite-epoxy structure has performed well and without incident. J.M.S. Avail: NTIS HC A15/MF A01 The service experience of light helicopters (BO-105) both for civil and military operations is discussed with emphasis on N81-11233# Aerospace Medical Research Labs.. Wright- data accumulated on composite (GRC) rotor blades. Full scale Patterson AFB. Ohio. fatigue test results with new blades and blades after 4000 hours TOXICITY OF SYNTHETIC HIGH DENSITY AND CONVEN- of flight are compared as are coupons cut out of blades before TIONAL HYDROCARBON JET FUELS TO A SOIL BACTERI- and after thousands of service hours. Impact strength and UM Technical Report, Sep. 1978 - Sep. 1979 erosion-corrosion problems are among the factors considered. Sheldon A. London and Charlie R. Mantel Aug. 1980 22 p J.M.S. refs (AF Proj. 6302) N81-11147*$ National Aeronautics and Space Administration. (AD-A089527: AFAMRL-TR-80-105) Avail: NTIS Langley Research Center. Hampton. Va. HC A02/MF A01 CSCL 06/20 COMPOSITE COMPONENTS ON COMMERCIAL AIR- The effects of selected high density and conventional jet CRAFT fuels on the growth kinetics of a soil microorganism were H. Benson Dexter In AGARD Effect of Serv. Environ, on determined. A culture of Enterobacter clocacae isolated from Composite Mater. Aug. 1980 22 p refs soil was exposed to various concentrations of each fuel in a mineral salts medium and bacterial growth was monitored Avail: NTIS HCA15/MFA01 CSCL11D turbidimetrically and by viable count techniques. Effects were Flight experience gained with numerous composite aircraft indicated by observing changes in maximum bacterial growth, structures is discussed. Both commercial transports and helicopters growth rate, lag time, and death rate. The majority of the fuels are included. Design concepts with significant mass savings and studied manifested their effects by decreasing the number of appropriate inspection and maintenance procedures are among viable organisms during the stationary growth period. Stable the factors considered. Also, a major NASA/U.S. industry emulsion formation resulted in erroneous turbidimetric determina-

41 N81 11269 tions. The applicability of bacterial systems as indicators of toxicity trends in sensor and computer technology to formulate a candidate of water insoluble jet propellents was discussed. GRA for a flutter mode control implementation. E.D.K. N81-11273# Saab-Scania, Linkoping (Sweden). Aerospace N81-11269| Saab-Scania, Linkoping (Sweden). Aerospace Div. Div. FAILURE MANAGEMENT FOR THE SAAB VIGGEN COMPUTER BASED IN-FLIGHT MONITORING JA37 AIRCRAFT Kjell Folkesson In AGARD Fault Tolerance Design and Kjell Folkesson In AGARD Fault Tolerance Design and Redundancy Management Tech. Sep. 1980 23 p Redundancy Management Tech. Sep. 1980 21 p ref

Avail: NTIS HC A08/MF A01 Avail: NTIS HC A08/MF A01 Various computer techniques used to monitor flight safety The JA-37 Viggen is the first military aircraft in series critical flight control systems components such as sensors, servos, production and field-service equipped with a digital automatic and the FSC computer itself are described. Flight safety critical flight control system. The JA-37 Digital Automatic Flight Control FCS sensors and usually redundant. The degree of redundancy System has high control authority and is a flight safety critical is a function of the control authority of the sensors, the stability system. It has duplex sensors, a single channel digital computer, of the aircraft, and existing back-up arrangements. The digital and simple secondary servos. The digital computer performs FCS computer can be used for servo monitoring in many different control-law calculation and sensor and servo monitoring, as well ways. The servo configuration usually determines the best monitor as extensive self test on ground and during flight. The sensors solution. In redundant servo configurations, various signals, such are monitored by comparison. The servos are monitored by as electrical current, differential pressure, velocity, or servo comparing the output from a software model with the servo position, can be provided to the digital comptuer and monitored output. E.D.K. for failure detection. The FCS digital computer is usually a flight safety critical element and must be closely monitored. Failures must be detected and isolated with very high confidence. In N81-11274*$ National Aeronautics and Space Administration. redundant digital FCS computers, both computer self test and Hugh L. Dry den Flight Research Center. Edwards. Calif. monitoring of the computer outputs are used to detect computer FLIGHT EXPERIENCE WITH FLIGHT CONTROL RE- failures. The monitoring can be relized in software or in external DUNDANCY MANAGEMENT hardware. E.D.K. Kenneth J. Szalai, Richard R. Larson, and Richard D. Glover In AGARD Fault Tolerance Design and Redundancy Management Tech. Sep. 1980 27 p refs N81-11270# Oepartement d'Etudes et de Recherches en Technologie Spatiale, Toulouse (France). Avail: NTIS HCA08/MFA01 CSCL01C DETECTING THE FAILURE OF AIRCRAFT SENSORS USING Flight experience with both current and advanced re- ANALYTICAL REDUNDANCY (DETECTION DE PANNE DE dundancy management schemes was gained in recent flight CAPTEURS D'AVION PAR UTILISATION DE LA REDOND- research programs using the F-8 digital fly by wire aircraft. The ANCE ANALYTIQUE] flight performance of fault detection, isolation, and reconfiguration Marc Labarrere In AGARD Fault Tolerance Design and (FDIR) methods for sensors, computers, and actuators is reviewed. Redundancy Management Tech. Sep. 1980 17 p refs In Results of induced failures as well as of actual random failures FRENCH; ENGLISH summary are discussed. Deficiencies in modeling and implementation techniques are also discussed. The paper also presents comparison Avail: NTIS HC A08/MF A01 off multisensor tracking in smooth air, in turbulence, during large Failure detection techniques implemented on-board aircraft maneuvers, and during maneuvers typical of those of large must be simple and robust. By replacing a triplex vital system commercial transport aircraft. The results of flight tests of an with a duplex system associated with analytical redundancy, the advanced analytic redundancy management algorithm are problem is reduced to isolating the failed sensor. Estimation compared with the performance of a contemporary algorithm in techniques are well suited here because of the atmospheric terms of time to detection, false alarms, and missed alarms. turbulence factor. Different techniques have been used according The performance of computer redundancy management in both to whether the nature of the analytical redundancy is stochastic, iron bird and flight tests is also presented. E.D.K. deterministic, static, or dynamic. Various estimation algorithms used include: (1) mixed observations: (2) estimation by observers or Kalman filters, using one or several quations and one or N81-11275# Deutsche Forschungs- und Versuchsanstalt fuer several measurements: and (3) autoadaptive techniques by luft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst. identifying the flight configuration. A solution based on the choice for Flight System Dynamics. and use of deterministic redundancy relations which are ROBUST CONTROL SYSTEM DESIGN independent of atmospheric disturbances is presented and J. Ackermann In AGARD Fault Tolerance Design and Redundancy applied to the records of real flights. Transl. by A.R.H. Management Tech. Sep. 1980 14 p refs Avail: NTIS HC A08/MF A01 The short period longitudinal mode of an F 4-E with horizontal canards is instable in subsonic flight and unsufficiently N81-11272# Honeywell Systems and Research Center. damped at supersonic speed. The control system has to provide Minneapolis, Minn. acceptable pole locations according to military specifications for FAILURE MANAGEMENT TECHNIQUES FOR HIGH flying qualities. A fixed gain controller using three paralleled SURVIVABILITY Thomas B. Cunningham In AGARD Fault Tolerance Design gyros is designed, such that the pole region requirements in four typical flight conditions are robust with respect to gain and Redundancy Management Tech. Sep. 1980 25 p refs reduction to one third. Thus nothing bad happens immediately after one or two gyro failures. Failure detection and redundancy Avail: NTIS HC A08/MF A01 management may be performed at a higher hierarchical level, Survivability of aircraft can be greatly enhanced by employing which does not have to be extremely fast. The use of accelerometers a number of considerations and techniques in design and or air data sensors for angle of attack or dynamic pressure is placement of avionics components. The initial sizing and location totally avoided in this concept and no gain scheduling is of surfaces should include the impact of survivability. Avionics necessary. The design for robustness with respect to different hardware sharing offers cost reductions and can provide high flight conditions and sensor failures is performed by a novel performance if reliability and survivability issues are successfully parameter space design tool. E.D.K. addressed. Observers offer a structure for seeking solutions to surivability problems. Observers for in the loop sensor reconstruc- N81-11290# Federal Aviation Administration, Atlantic City, N.J. tion often require stability margin enhancement. Techniques for Technical Center. examining this problem and improving stability exist. These TEST AND EVALUATION OF THE AIRPORT SURVEILLANCE considerations are discussed in detail and are combined with RADAR (ASR) 8 WIND SHEAR DETECTION SYSTEM

42 N81-11492

(PHASE 2), REVISION Interim Report. Apr. - Dec. 1979 N81-11415# National Aerospace Lab.. Amsterdam (Netherlands). D. L. Offi. W. Lewis. T. Lee. and A. DeLaMarche Aug. 1980 FLIGHT SIMULATION ENVIRONMENTAL FATIGUE CRACK 40 p refs Revised PROPAGATION IN 2024-T3 AND 747S-T761 ALUMINUM (FAA Pro). 022-242-830) R. J. H. Wanhill Jan. 1980 10 p refs Presented at the 12th (AD-A090111: FAA-CT-80-17-A-Rev: FAA-RD-80-21-A-Rev) I CAS Congr., Munich. 12-17 Oct. 1980 Avail: NTIS HC A03/MF A01 CSCL 17/9 (NLR-MP-80003-U: ICAF-1168) Avail: NTIS A wind shear detection system developed by the Wave HC A02/MF A01 Propagation Laboratory (WPL) to operate with the Federal Aviation A gust spectrum representative of the load history of an Administration (FAA) Airport Surveillance Radar (ASR)-8 was under wing skin in a transport aircraft was used in flight simulation installed and is being tested at the FAA technical Center. Initial fatigue crack propagation tests on 2024-T3 and 7475-T761 efforts, previously reported in Report NA-78-59-LR. were directed aluminum alloy sheet. Tests were conducted at several design toward hardware and software shakedown and feasibility stress levels and in environments of air and air plus water spray. determination. Second phase tests compared radar with aircraft Results show that the fatigue crack propagation resistance of and tower winds, evaluated the wind shear measurement capability 2024-T3 sheet under gust spectrum loading is generally superior under various weather conditions, and investigated the effective- to that of 7475-T761 sheet, and that this superiority is mainly ness of a simple two-azimuth pointing strategy and system due to a greater amount of crack growth retardation during the capabilities and limitations. Results showed the system to be less severe loads and flights that follow the peak loads in severe compatible with and to operate satisfactorily with the ASR-8. flights. The straightforward use of 7475 alloy in tension-critical The processing and spectral display of clear air and precipitation structures like the under wing skin of a transport aircraft would returns is feasible. The accuracy of agreement between radar- result in decreased crack propagation resistance. In order to measured winds and components of the aircraft-measured winds utilize the higher static structural efficiency and fracture toughness in both radially oriented flights and runway offset flights, using of 7475 alloy (in relation to 2024-T3). it may be possible to a two-azimuth pointing technique, was examined. Radar versus improve the relative performance by selecting an adhesive bonded tower wind agreement was also examined. Potentially dangerous laminated sheet or sandwich panel concepts. A.R.H. wind shears associated with weather during these tests were detectable. Certain system limitations also have been defined and considered. It is recommended that tests continue to complete N81-11422*# National Aeronautics and Space Administration. definition of and demonstrate capabilities in all weather situations, Langley Research Center, Hampton, Va. to optimize performance, and to provide information to specify AN ANALYTICAL TECHNIQUE FOR APPROXIMATING system design for possible development of a prototype model. UNSTEADY AERODYNAMICS IN THE TIME DOMAIN GRA H. J. Dunn Nov. 1980 31 p refs (NASA-TP-1738: L-13255) Avail: NTIS HC A03/MF A01 N81-11364# Aeronautical Research Labs.. Melbourne (Australia). CSCL 20K A SIX-CHANNEL QUICK-LOOK UNIT FOR THE AODYNAM- An analytical technique is presented for approximating ICS DIVISION MKI AIRBORNE DATA ACQUISITION unsteady aerodynamic forces in the time domain. The order of PACKAGE elements of a matrix Pade approximation was postulated, and A. J. Farrell. S. H. Creed. I. M. Kerton. and P. Ferrarotto Feb. the resulting polynomial coefficients were determined through a 1980 31 p refs combination of least squares estimates for the numerator (AD-A089975; ARL/AERO-TM-319) Avail: NTIS coefficients and a constrained gradient search for the denominator HC A03/MF A01 CSCL 09/5 coefficients which insures stable approximating functions. The A ground-based unit is described which, when connected to number of differential equations required to represent the a chart recorder, provides a post-flight analogue record of up to aerodynamic forces to a given accuracy tends to be smaller six channels simultaneously of data recorded on the Aerodynamics than that employed in certain existing techniques where the Division MKI Airborne Data Acquisition Package. GRA denominator coefficients are chosen a priori. Results are shown for an aeroelastic. cantilevered. semispan wing which indicate a N81-11365# Aeronautical Research Labs.. Melbourne (Australia). good fit to the aerodynamic forces for oscillatory motion can be TRANSDUCER INSTALLATION FOR THE SEA KING MK achieved with a matrix Pade approximation having fourth order 50 MATHEMATICAL MODEL VALIDATION FLIGHT TESTS numerator and second order denominator polynomials. Author D. T. Hourigan Mar. 1980 24 p refs (AD-A089924: ARL/AERO-TM-322: AR-001-806) Avail: NTIS N81-11448*# National Aeronautics and Space Administration. HC A02/MF A01 CSCL 01/3 Lewis Research Center, Cleveland. Ohio. The installation of transducers in a R.A.N. Sea King MK 50 PERFORMANCE OF A STEEL SPAR WIND TURBINE BLADE helicopter is described. These transducers were used to obtain ON THE MOD 0 100 kW EXPERIMENTAL WIND TURBINE flight trials data for validating a mathematical model of the Final Report aircraft. GRA Theo G. Keith, Jr. (Toledo Univ.), Timothy L Sullivan, and Larry A. Viterna Sep. 1980 24 p refs N81-11412*# National Aeronautics and Space Administration. (Contract EX-76-1-01-1028) Lewis Research Center. Cleveland. Ohio. (NASA-TM-81588: DOE/NASA/1028-27; E-567) Avail: NTIS SUPERHYBRID COMPOSITE BLADE IMPACT STUDIES HC A02/MF A01 CSCL 10B C. C. Chamis. R. F. Lark, and J. H. Sinclair [1980] 16 p refs The performance and loading of a large wind rotor. 38.4 m Proposed for presentation at the 26th Ann. Intern. Gas Turbine in diameter and composed of two low-cost steel spar blades Conf.. Houston. Tex.. 9-12 Mar. 1981 were examined. Two blades were fabricated at Lewis Research (NASA-TM-81597: E-580) Avail: NTIS HC A02/MF A01 CSCL Center and successfully operated on the Mod-0 wind turbine at 20K Plum Brook. The blades were operated on a tower on which The feasibility of superhybrid composite blades for meeting the natural bending frequency were altered by placing the tower the mechanical design and impact resistance requirements of on a leaf-spring apparatus. It was found that neither blade large fan blades for aircraft turbine engine applications was performance nor loading were affected significantly by this tower investigated. Two design concepts were evaluated: leading edge softening technique. Rotor performance exceeded prediction spar (TiCom) and center spar (TiCore). both with superhybrid while blade loads were found to be in reasonable agreement composite shells. The investigation was both analytical and with those predicted. Seventy-five hours of operation over a experimental. The results obtained show promise that superhybrid five month period resulted in no deterioration in the blade. composites can be used to make light weight, high quality, large Author fan blades with good structural integrity. The blades tested N81-11492| AeroVironment. Inc.. Pasadena, Calif. Aerosciences successfully demonstrated their ability to meet steady state Group. operating conditions, overspeed. and small bird impact require- DEFINITIVE GENERIC STUDY FOR THE EFFECT OF HIGH ments. A.R.H. LIFT AIRFOILS ON WIND TURBINE EFFECTIVENESS.

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EXECUTIVE SUMMARY Final Report The microcomputer array system is discussed with specific Peter B. S. Lissaman. Robert E. Wilson. R. W. Thresher, and attention given to its electronic warware applications. Several Stel N. Walker May 1979 93 p refs aspects of the system architecture are described as well as some (Contract EG-77-C-01-4042) of its distinctive characteristics. R.C.T. (SERI/TR-98003-2) Avail: NTIS HC A05/MF A01 The effect of high lift airfoils on the cost effectiveness of N81-11688*# National Aeronautics and Space Administration. HAWT and VAWT (horizontal and vertical axis wind turbine) Lewis Research Center, Cleveland. Ohio. machines is studied. The scope involved first studying modern AN AUTOMATED PROCEDURE FOR DEVELOPING HYBRID two dimensional airfoils, and developing a generalized formulation COMPUTER SIMULATIONS OF TURBOFAN ENGINES for their performance in terms of lift. drag, and thickness at John R. Szuch and Susan M. Krosel 1980 19 p refs Proposed appropriate Reynolds numbers. Single element, multi-element, for presentation at the 14th Ann. Simulation Symp.. Tampa, symmetrical, extra thick airfoils and jet flap airfoils were analyzed. Fla.. 18-20 Mar. 1981 The jet flap airfoils were considered to be unacceptable because (NASA-TM-81605; E-598) Avail: NTIS HC A02/MF A01 CSCL of excessive power requirements. Then the effect of using the 098 above airfoils on the rotors of a variety of wind turbines was A systematic, computer-aided, self-documenting methodology made. Qualitative representation of the type of airfoils studied for developing hybrid computer simulations of turbofan engines is given. DOE is presented. The methodology makes use of a host program that can run on a large digital computer and a machine-dependent target (hybrid) program. The host program performs all of the N81-11600# Exxon Research and Engineering Co.. Linden, N.J. calculations and date manipulations needed to transform Government Research Labs. user-supplied engine design information to a form suitable for ALTERNATIVE ENERGY SOURCES FOR NON-HIGHWAY the hybrid computer. The host program also trims the self TRANSPORTATION, APPENDICES contained engine model to match specified design point E. N. Cart, Jr.. ed. Jun. 1980 560 p information. A test case is described and comparisons between (Contract DE-AC05-77CS-05438) hybrid simulation and specified engine performance data are (DOE/CS-05438/T1-Vol-3) Avail: NTIS HC A24/MF A01 presented. S.F. A planning study was made for DOE on alternate fuels for nonhighway transportation (aircraft, rail, marine, and pipeline). N81-11769*# National Aeronautics and Space Administration. DOE is provided with a recommendation of what alternate fuels Lewis Research Center. Cleveland. Ohio. Fluid Mechanics and may be of interest to nonhighway transportation users from now Acoustics Div. through 2025 and the research and development needed to CORE NOISE MEASUREMENTS FROM A SMALL. GENERAL allow nonpetroleum derived fuels to be used in nonhighway AVIATION TURBOFAN ENGINE transportation. DOE Meyer Reshotko and Allen Karchmer 21 Nov. 1980 28 p refs Presented at the 100th Meeting of the Acoust. Soc. of Am.. Los Angeles, 17-21 Nov. 1980 N81-11513# Exxon Research and Engineering Co.. Linden. NJ. (NASA-TM-81610: E-607) Avail: NTIS HC A03/MF A01 CSCL Government Research Labs. 20A ALTERNATIVE ENERGY SOURCES FOR NON-HIGHWAY As part of a program to investigate combustor and other TRANSPORTATION. VOLUME 1 core noises, simultaneous measurements of internal fluctuating E. N. Cart. Jr.. ed. Jun. 1980 26 p refs pressure and far field noise were made with a JT15D turbofan (Contract DE-AC05-77CS-55438) engine Acoustic waveguide probes, located in the engine at the (DOE/CS-05438/TI-Vol-D Avail: NTIS HC A03/MF A01 combustor, at the turbine exit and in the core nozzle wall, were Alternate fuels for nonhighway transportation (aircraft, rail, used to measure internal fluctuating pressures. Low frequency marine, and pipeline) were investigated. A recommendation of acoustic power determined at the core nozzle exit corresponds what alternate fuels may be of interest to nonhighway transporta- in level to the far field acoustic power at engine speeds below tion users from now through 2025 is made. The research and 65% of maximum, the approach condition. At engine speeds development needed to allow nonpetroleum derived fuels to be above 65% of maximum, the jet noise dominates in the far used in nonhighway transportation is discussed. In the near term field, greatly exceeding that of the core. From coherence (present-1985), there is unlikely to be any major change in the measurements, it is shown that the combustor is the dominant fuels used in any of the four modes of transportation except source of the low frequency core noise. The results obtained that the average quality of the marine fuel is likely to get worse. from the JT15D engine were compared with those obtained In the midterm period (1985-2000). there will be a transition previously from a YF102 engine, both engines having reverse to nonpetroleum fuels, based primarily on shale oil derived liquids flow annular combustors and being in the same size class. assuming a shale oil industry is started during this time. DOE Author

N81-11770*# National Aeronautics and Space Administration. N81-11658*# Goodyear Aerospace Corp.. Akron. Ohio. Lewis Research Center. Cleveland. Ohio. MICROPROCESSOR SOFTWARE APPLICATIONS FOR EFFECT OF A SEMI-ANNULAR THERMAL ACOUSTIC FLIGHT TRAINING SIMULATORS SHIELD ON JET EXHAUST NOISE Wayne P. Leavy In NASA. Goddard Space Flight Center J. Goodykoontz 21 Nov. 1980 21 p refs Presented at the Aerospace Appl. of Microprocessors 1980 p 103-111 100th Meeting of the Acoust. Soc. of Am.. Los Angeles. 17-21 Nov. 1980 Avail: NTIS HC A12/MF A01 CSCL 098 (NASA-TM-81615: E-616) Avail: NTIS HC A02/MF A01 CSCL The g cueing system software design and implementation 20A in the dual microprocessor system of the F-15 operational flight Reductions in jet exhaust noise obtained by the use of an training simulator g cueing system is presented. The software is annular thermal acoustic shield consisting of a high temperature, structured in the two microcomputers such that one serves as low velocity gas stream surrounding a high velocity central jet a controller performing all logical functions and interface with exhaust appear to be limited by multiple reflections. The effect the host computer system while the other serves as an arithmetic of a semi-annular shield on jet exhaust noise was investigted unit performing all mathematical functions. M.G. with the rationale that such a configuration would eliminate or reduce the multiple reflection mechanism. Noise measurements N81-11673*| Goodyear Aerospace Corp., Akron. Ohio. for a 10 cm conical nozzle with a semi-annular acoustic shield MICROCOMPUTER ARRAY PROCESSOR SYSTEM are presented in terms of lossless free field data at various Kenneth D. Slezak In NASA. Goddard Space Flight Center angular locations with respect to the nozzle. Measurements were Aerospace Appl. of Microprocessors 1980 p 259-274 made on both the shielded and unshielded sides of the nozzle. The results are presented parametrically. showing the effects of Avail: NTIS HC A12/MF A01 CSCL 098 various shield and central system velocities and temperatures.

44 N81-11909

Selected results are scaled up to a typical full scale engine size The changing economic environment and the developing to determine the perceived noise level reductions. A.R.H. requirement to put increased emphasis on downstream activities in the early phases of a weapon system program are discussed. N81-11774# State Univ. of New York at Buffalo. Amherst. A possible approach to calculating the magnitude and spread of Faculty of Engineering and Applied Sciences. cost reducing investments is considered and applications of life COOPERATIVE INVESTIGATION OF THE NOISE PRODUC- cycle cost analysis in strategic decision making, the design ING REGION OF AN AXISYMMETRIC JET Final Report process, and as a sales aid are mentioned. E.D.K. W. K. George. R. E. A. Arndt. and H. M. Nagib Jul. 1980 34 p refs N81-11905# Army Aviation Research and Development (Contract F49620-78-C-0047) Command. St. Louis. Mo. (AD-A089692: AFOSR-80-0754TR) Avail: NTIS US ARMY DESIGN-TO-COST EXPERIENCE HC A03/MF A01 Richard B. Lewis, II. Edward P. Laughlin. and Francis E. Spring The objectives of this three-university effort are: to determine In AGARD Design to Cost and Life Cycle Cost Jul. 1980 whether or not large scale structures exist in the mixing layer 11 p of an axisymmetric jet: to determine whether or not these large Avail: NTIS HC A15/MF A01 scale structures (if they exist) contribute to the radiated noise: Design-to-Cost procedures were included in all major U.S. and to quantify the above conclusions so that the results can Army aviation procurements since 1972, Experience was gained be used for evaluation of jet noise theories and for prediction of during design, development, procurement and initial fielding of radiated noise. This is a report on the initial phase of the work several major systems. The ownership cost of this equipment is in which the primary emphasis has been on the construction of considered during development. Production and operational phases the experimental facilities, the acquisition and assembly of the and techniques for cost control are discussed. Lessons learned measurement hardware and the development of computer as a result of joint Government-Industry Design-To-Unit- software. Noteworthy advances include an analysis and extension Production-Cost programs are presented. Techniques which were of the burst-mode LDA. and the continued development of digitally effective in cost management on utility and attack helicopters sampled flow visualization techniques. Experiments on various and turbine engine programs are listed. Producibility engineering nozzle shapes at low Reynolds number indicate that nozzle shape planning, initial production tooling, and facilitization to reduce plays an important role in determining the vortex pairing in the production costs are discussed. The role of warranties in controlling mixing layer and the radiated noise. This does not appear to be operating and support costs is illustrated. It is concluded that the case at high Reynolds numbers. The preliminary conclusion Design-To-Unit-Production-Cost techniques were effective in is that the pairing and turbulence structures observed at low achieving lower production costs, but that additional work is Reynolds numbers have little to do with jet noise. GRA necessary to better control operating and support costs and thereby achieve optimal life cycle costs. E.D.K. N81-11778# Rockwell International Corp.. El Segundo. Calif. North American Aircraft Oiv. N81-11906# Advisory Group for Aerospace Research and WEAPON BAY CAVITY NOISE ENVIRONMENTS. DATA Development. Neuilly-Sur-Seine (France). CORRELATION AND PREDICTION FOR THE B-1 AIRCRAFT A REVIEW AND ASSESSMENT OF SYSTEM COST REDUC- Final Report. Feb. 1979 - May 1980 A. G. Tipton Wright-Patterson AFB. Ohio AFFDL Jun. 1980 TION ACTIVITIES W. E. Lamar In its Design to Cost and Life Cycle Cost Jul. 239 p refs 1980 38 p refs (Contract F33615-79-C-3208: AF Proj. 2401) Avail: NTIS HC A15/MF A01 (AD-A089770: NA-80-247: AFWAL-TR-80-3050) Avail: NTIS A review of the evolution of cost reduction concepts over HC A11/MF A01 CSCL 20/1 the past decade to current design to life cycle cost (DTLCC) During development of the B-1 aircraft, an extensive cavity efforts is presented. Emphasis is given to progress achieved and noise measurement and noise reduction program using wind tunnel basic problems and issues which have confronted successful models and evaluation on a flight-test aircraft was conducted. application of these concepts. The review addresses the Substantial cavity noise reduction was achieved with retrofitted importance of top management action, consideration of costs in spoilers for a Mach 0.6 to 1 range for the weapon bay cavity the early phase, and a credible data base. Progress in developing of L/D = 2.2. A substantial amount of cavity unsuppressed cost prediction and analysis methods, technologies to reduce and suppressed data were acquired from wind tunnel models development, acquisition, operations and support costs, the and the full-scale aircraft. Data for weapon bay cavities with institutionalization of design to cost and design to life cycle internal stores and multiple open cavities was also obtained. cost methods, and remaining challenges are discussed. E.D.K. The data acquired during development of B-1 cavity noise suppressors are correlated and compared with previously published data. The data are correlated with existing prediction techniques N81 11907# Boeing Aerospace Co.. Seattle, Wash. and modifications to the current prediction techniques, and DESIGN TO LIFE CYCLE COST RESEARCH guidelines are recommended. GRA Fred T. Carlson In AGARD Design to Cost and Life Cycle Cost Jul. 1980 15 p N81-11902# Advisory Group for Aerospace Research and Avail: NTIS HC A15/MF A01 Development. Neuilly-Sur-Seine (France). Design to life cycle cost research applied to the area of DESIGN TO COST AND LIFE CYCLE COST logistics systems is discussed with a look at history data for Jul. 1980 333 p refs In ENGLISH and FRENCH Symp. typical aircraft systems. Deficiencies in systems operations and held in Amsterdam. 19-22 May 1980 support are identified and described. Methods of assessing the (AGARD-CP-289: ISBN-92-835-0268-X) Avail: NTIS cost, risk, and program application are discussed. Areas of HC A15/MF A01 emphasis, cost drivers, and their impacts are shown. It is Life cycle costs (LCC) methodology and its relation to ' determined that many deficiencies in the ownership of systems specifications and requirements are discussed. Other topics include do not relate to program plans. Resolution by future technology the impact of LCC analysis on total system design, cost control advances must be aimed toward elimination of manpower, of operations and support, and LCC of subsystems and compo- material, and program causative factors through research of nents. logistics subsystems, i.e.. inspections, material distribution, people use, and logistics networks. E.D.K. N81-11903# British Aerospace Aircraft Group. Preston (England). LIFE CYCLE COST ANALYSIS (LCCA) IN MILITARY N81-11909$ British Aerospace Aircraft Group. Preston (England). AIRCRAFT PROCUREMENT EVOLUTION OF TECHNIQUES FOR LCC ANALYSIS R. Chisholm In AGARD Design to Cost and Life Cycle Cost J. M. Jones In AGARD Design to Cost and Life Cycle Cost Jul. 1980 8 p refs Jul. 1980 13 p Avail: NTIS HC A15/MF A01 Avail: NTIS HC A15/MF A01

45 N81-11910

The need to control aircraft operating and support costs into the design on a large scale. With respect to structures, starting with a coordinated approach to life cycle cost (LCC) carbon-epoxy composite technology is one of the most remarkable. analysis during the conceptual design stage is identified. Its introduction at the design stage results in reduction of mass Experiences in the development and use of LCC models are and cost, first on the elements to which it is applied, and then discussed. The limitations of existing systems together with by the amplifying effect on the assembly of the structure and examples of current work on this subject are presented. E.O.K. the rest of the aircraft: engine, equipment, and fuel. Such a process supposes that the technology to be applied has attained a degree of maturation which permits prediction of performance N81-11910# McDonnell Aircraft Co.. St. Louis. Mo. and cost with certitude. Transl. by A.R.H. THE HORNET PROGRAM: A DESIGN TO LIFE CYCLE COST CASE STUDY Robert D. Dighton In AGARD Design to Cost and Life Cycle N81-11914# Societe Nationale Industrielle Aerospatiale, Paris Cost Jul. 1980 12 p (France). Aircraft Div. ORGANIZING A DESIGN-TO-COST PROGRAM Avail: NTIS HC A15/MF A01 Robert Tassinari In AGARD Design to Cost and Life Cycle A primary requirement of the Hornet program is significant Cost Jul. 1980 14 p reduction in life cycle cost (LCC). The design and management techniques used to develop a new fighter/attack system at an Avail: NTIS HC A15/MF A01 affordable LCC are described. The designer must consider key Total cost control at all development and production stages elements of LCC such as reliability, maintainability, unit production is a prerequisite to any significant design-to-cost (DTC) program. cost, and logistics support cost elements in parallel with traditional Design to life cycle cost (DTLCC) methods further require intimate concerns of weight and performance when designing life cycle knowledge of operational and maintenance costs. Specialists in costs. Examples of trade studies resulting in relatively large LCC this cost management method are aware of these two principles. avoidances are summarized. E.D.K. Less obvious, perhaps are the great advantages to be derived through an organization specifically trained in the application of N81-11911# General Dynamics/Fort Worth, Tex. F-16 Systems DTC and DTLC principles. A specialized organization and Engineering Management. methods for integrating costs into all phases of new programs DESIGN TO COST AND THE F-16 MULTIROLE FIGHTER was created much in the way that weights were calculated into W. M. Rowell In AGARD Design to Cost and Life Cycle Cost programs in the past. To keep pace with this reorganization in Jul. 1980 14 p refs development, emphasis was placed on training personnel in value analysis and DTC methods. Results of these efforts first became Avail: NTIS HC A15/MF A01 apparent in 1977, during development of the A 200. Today, The low cost of the F-16 Fighter Aircraft is the result of a the same principles are being applied in development of the selected balance of innovative technologies, available low cost A 310. E.D.K. material and equipment, and cost reducing configuration options. This was implemented through the application of design to cost concepts from the beginning of the program. The F-16 full scale N81-11915$ American Airlines, Inc., Tulsa. Okla. development contract contained several clauses which provided A NEW METHOD FOR ESTIMATING TRANSPORT AIR- downstream cost control including control of both acquisition CRAFT DIRECT OPERATING COSTS and operations. A key part of this plan was the identification Keith Grayson In AGARD Design to Cost and Life Cycle Cost and close tracking of a few cost drivers which comprise over Jul. 1980 20 p refs 50% of the air vehicle cost. A number of specific contract provisions are aimed at control of operating and support costs. These Avail: NTIS HC A15/MF A01 provisions provide financial incentives and penalties for considera- A means of estimating aircraft direct operating costs for tion of reliability and other logistic support parameters. Other comparative purposes was developed which was able to recognize control provisions require cost considerations in trade studies, and include the potential benefits to be gained from technology engineering change proposals, and in vendor selections. E.O.K. and design innovation when applied to commercial transport aircraft. The work performed on this subject is reviewed. The validity of the developed methods and how they can be used in N81-11912# Messerschmitt-Boelkow-Blohm G.m.b.H.. Munich the evaluation of aircraft for an airline's fleet is also demon- (West Germany). Aircraft Div. strated. E.D.K. STRUCTURAL INTEGRATION AS A MEANS OF COST REDUCTION N81-11916# Societe Nationale Industrielle Aerospatiale. P. E. Siebert In AGARD Design to Cost and Life Cycle Cost Marignane (France.) Jul. 1980 17 p DESIGN-TO-COST APPLIED TO THE AS360 HELICOPTER Avail: NTIS HC A15/MF A01 [LE DESIGN TO COST APPLIQUE A L'HELICOPTERE Through some components of the Tornado fighter aircraft it AS350] is demonstrated how costs can be reduced by structural Rene Mouille In AGARD Design to Cost and Life Cycle Cost integration. The components are two flat panels, the wing carry Jul. 1980 18 p In FRENCH through box and the Taileron. Cost savings could be achieved from 15% to a maximum of 68%. E.D.K. Avail: NTIS HC A15/MF A01 In order to remain competitive on the international market, cost reduction studies were undertaken at Aerospatiale and were N81-11913# Avions Marcel Dassault, Saint-Cloud (France). concretized in the design of the AS350 helicopter after two DESIGN-TO-COST AND NEW TECHNOLOQIES [DESIGN- years' effort by a small experimental research group. The TO-COST ET TECHNOLOGIES NOUVELLES] development of this helicopter, which is definitely more economical Francois Cordie In AGARD Design to Cost and Life Cycle than the Alouette 2 or the Gazelle, has followed the same cost Cost Jul. 1980 8 p In FRENCH reduction spirit as was used in its design. The method is classic N81-11902 02-81) and is based on (1) analysis of the value of functions and of Avail: NTIS HC A15/MF A01 the parts assuring these functions; (2) criticism of the solution: Modern combat aircraft design can no longer be undertaken (3) search for new solutions: and (4) choice of compromises. without giving equal consideration to mission cost and perform- The experience of the participants permitted rapid elimination of ance when making compromises which lead to the choice of an the most expensive choice as well as those with least performance. aircraft formula. These compromises are based on technologies The benefits to be obtained from proceeding correctly from the which can be used from the beginning of production. Usually design stage can be very important with regards to both acquisition they are new technologies which have passed the laboratory and utilization costs. This is of interest to both civil and military stage and applied to existing aircraft before being integrated users. Transl. by A.R.H.

46 IM81-11927

N81-11917# United Air Lines. Inc., San Francisco, Calif. applied to two international collaborative military aircraft are RELIABILITY-CENTERED MAINTENANCE considered and some of the lessons and problems encountered F. S. Nowlan In AGARD Design to Cost and Life Cycle Cost are addressed. R.C.T. Jul. 1980 13 p refs

Avail: NTIS HC A15/MF A01 N81-11922# Vereinigte Flugtechnische Werke G.m.b.H.. Bremen The use of reliability centered maintenance principles are (West Germany). discussed with respect to aircraft component life cycle costs. ESTIMATION OF RELATIVE TOTAL COST FOR AIRCRAFT The following inherent reliability characteristics are emphasized: SYSTEMS failure consequences, judged by the effect of loss of function J. Bollmann and H. Lankenau In AGARD Design to Cost and on safety, mission capability and operational readiness: failure Life Cycle Cost Jul. 1980 9 p refs modes which lead to an item's loss of function: exposure to secondary damage that results from certain failure modes: visibility Avail: NTIS HC A15/MF A01 of the failure process and a mechanic's ability to discover potential A suitable method for determining the relative total costs failures and thereby prevent functional failures: evidence by which (fixed and operating costs) is described. It is shown that during the operating crew can realize that a functional failure has the operating phase a clear statistical comparison must contin- occurred, exposure to the consequences of multiple failures: and uously be accomplished between the target and the actual values failure rates. R.C.T. in order to ensure that any deviations and the causes of such deviations can be detected and eliminated. The need to have an agreed procedure between operator, aircraft manufacturer and N81-11918# British Aerospace Aircraft Group. Preston (England). equipment supplier is emphasized. R.C.T. SOME ENGINEERING ASPECTS OF LIFE CYCLE COST- ING G. W. Bleasdale In AGARD Design to Cost and Life Cycle N81-11923# Messier-Hispano-Bugatti S.A.. Montrouge (France). Cost Jul. 1980 9 p refs USING COST REDUCTION CONCEPTS AT MESSIER- HISPANO-BUGATTI [MISE EN OEVRE DES CONCEPTS Avail: NTIS HC A15/MF A01 DE REDUCTION DES COUTS CHEZ MESSIER-HISPANO- The constituents that are common to most life cycle cost BUGATTI] methods are identified. Ways in which some of the engineering M. Eslinger In AGARD Design to Cost and Life Cycle Cost costs can be minimized are discussed. It is shown that the Jul. 1980 11 p In FRENCH extra cost of better engineering design may increase the acquisition cost but this will be more than offset by the large reduction in Avail: NTIS HC A15/MF A01 support costs complemented by the increase in reliability and Industrialization, value analysis, production cost objective, and aircraft availability. Examples are given showing typical contribu- life cycle cost objective are four concepts used at M-H-B to tions to high support costs of mechanical components. R.C.T. reduce the cost of products such as landing gear, hydraulic equipment, wheels, and brakes. Each of these concepts is N81-11919* Northrop Corp., Hawthorne. Calif. Aircraft examined, and the means necessary for their implementation Group. are indicated. Results of using these techniques are described. BALANCED DESIGN: MINIMUM COST SOLUTION Transl. by A.R.H. E. Huie and H. F. Harris In AGARD Design to Cost and Life Cycle Cost Jul. 1980 8 p N81-11924# Gabelman (Irving J.) Technical Associates, Rome. Avail: NTIS HC A15/MF A01 N.Y. The application of life cycle cost analysis is discussed and SUMMARY OF AGARD LECTURE SERIES 100: METHOD- the techniques used to assessed life cycle costs during the different OLOGY FOR CONTROL OF LIFE CYCLE COSTS FOR phases of weapon system development are described. An AVIONICS SYSTEMS illustrative case study showing the benefits of the application of Irving J. Gabelman In AGARD Design to Cost and Life Cycle life cycle costing on availability, sustained sorties, and requirements Cost Jul. 1980 8 p Lecture held in Bonn. 7-8 May 1979 are presented. R.C.T. and in Athens. 10-11 May 1979

N81-11920# Industrieanlagen-Betriebsgesellschaft m.b.H., Avail: NTIS HC A15/MF A01 Ottobrunn (West Germany). The continually increasing cost of avionics and weapons systems between aquisition and their lifetime operation are DESIGN TO COST AND SYSTEMS. LCC discussed. Specific emphasis is given to the following: elements Klaus Wickel In AGARD Design to Cost and Life Cycle Cost of life cycle costs: parametric cost analysis: and life cycle cost Jul. 1980 9 p methodology. R.C.T. Avail: NTIS HC A15/MF A01 Different aspects of the design to costs approach are N81-11926$ Ministry of Defence. London (England). addressed with special attention given to their operational and SUMMARY OF AGARD LECTURE SERIES 107: THE maintenance cost and methodological implications. Three major APPLICATION OF DESIGN TO COSTAND LIFE CYCLE COST subtasks of the design to cost task are examined: design to TO AIRCRAFT ENGINES financial feasibility: design to personnel feasibility: and design E. J. Jones In AGARD Design to Cost and Life Cycle Cost to system's life cycle costs. It is shown that design to cost is Jul. 1980 5 p Lecture held in Saint Louis. France 12-13 May indisputably an absolutely essential approach to tackling the cost 1980 and in London. 15-16 May 1980 problems as long as the objective does not degenerate to mere design to financial feasibility. R.C.T. Avail: NTIS HC A15/MF A01 The latest methodologies of cost/performance comparison N81-11921# British Aerospace Aircraft Group. Preston (England). and trade offs for aircraft engines are examined. Information IMPACT OF MAINTAINABILITY OF LIFE CYCLE COSTS includes data collection, analysis, modelling and estimating all G. R. Thornber In AGARD Design to Cost and Life Cycle Cost development and operations costs. R.C.T. Jul. 1980 11 p Avail: NTIS HC A15/MF A01 The interpretation of the definitions of the varied parameters used in assessing maintainability with respect to their significant N81-11927# Air Force Wright Aeronautical Labs.. Wright- effect on the quantification of the effect on life cycle cost. One Patterson AFB. Ohio. Aero Propulsion Lab. possible interpretation is considered and the results obtained THE ROLE OF ADVANCED TECHNOLOGY OF TURBINE using this are indicated. Methods of assessing maintainability as ENGINE LIFE CYCLE COST

47 N81-11928

Robert F. Panella. Michael A. Barga. and Richard G. McNally In AGARD Design to Cost and Life Cycle Cost Jul. 1980 13 p refs Avail: NTIS HC A15/MF A01 The advanced technology of the turbine engine and its impact on life cycle costs (LCC) is addressed. To adequately assess this advanced technology, LCC techniques are to be developed which are sensitive to performance, structural design, manufactur- ing processes, reliability and maintainability. These techniques are then used to determine the performance/life/cost trade-offs of the advanced technology. An overview of current efforts in LCC techniques, and trade-offs is given. R.C.T.

N81-11928# Lucas Aerospace Ltd., Birmingham (England). Engine Management Div. COST CONSIDERATIONS OF ENGINE FUEL CONTROL SYSTEMS A. J. Eccleston In AGARD Design to Cost and Life Cycle Cost Jul. 1980 14 p

Avail: NTIS HC A15/MF A01 The manufacture of hydromechanical systems is discussed. It is shown that by applying well tried principles a value engineering team can identify considerable potential savings, particularly in the case of new designs. While lower life cycle costs are frequently only achieved at the expense of increased first cost this is not invariably so. R.C.T.

N81-11953*# AiResearch Mfg. Co.. Phoenix, Ariz COST/BENEFIT ANALYSIS OF ADVANCED MATERIALS TECHNOLOGY CANDIDATES FOR THE 1980'S. PART 2 Final Report R. E. Dennis and H. F. Maertins Aug. 1980 106 p refs (Contract NAS3-20073) (NASA-CR-165176: AIRESEARCH-21-3663-PT-2) Avail: NTIS HC A06/MF A01 CSCL 05A Cost/benefit analyses to evaluate advanced material technol- ogies projects considered for general aviation and turboprop commuter aircraft through estimated life-cycle costs, direct operating costs, and development costs are discussed. Specifically addressed is the selection of technologies to be evaluated: development of property goals: assessment of candidate technologies on typical engines and aircraft: sensitivity analysis of the changes in property goals on performance and economics, cost, and risk analysis for each technology: and ranking of each technology by relative value. The cost/benefit analysis was applied to a domestic, nonrevenue producing, business-type jet aircraft configured with two TFE731-3 turbofan engines, and to a domestic, nonrevenue producing, business type turboprop aircraft configured with two TPE331-10 turboprop engines In addition, a cost/benefit analysis was applied to a commercial turboprop aircraft configured with a growth version of the TPE331-10. M.G.

N81-12010# Air Force Materials Lab.. Wright-Patterson AFB. Ohio. AIR FORCE TECHNICAL OBJECTIVE DOCUMENT FY 1981 Sidney 0. Davis Dec. 1979 30 p Supersedes AFML-TR-78- 195 (AD-A089709: AFML-TR-79-4222: AFML-TR-78-195) Avail: NTIS HC A03/MF A01 CSCL 15/3 This technical objective document was prepared by the Materials Laboratory and describes the materials technology areas for meeting future Air Force operational needs. The six technology areas encompass the full spectrum of materials capabilities required for future aircraft, missile, space, and electronic systems: thermal protection materials: aerospace structural materials: aerospace propulsion materials, fluid, lubricant, and elastomeric materials: protective coatings and materials, and electromagnetic windows and electronics. Presented for each TA is the general objective, specific goals, technical approaches, and a Laboratory TA focal point who can facilitate face-to-face discussions with Laboratory engineers and scientists. GRA

48 SUBJECT INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 132) FEBRUARY 1981

Typical Subject Index Listing

SUBJECT HEADING IIBFB1HES J-L ACOUSTIC PBOPAGATIOB rDevelopment of advanced interceptor substrnctnzal Analytical characteristics methods: Ipplications •aterial graphite epozv lissile structures [VKI-PBEPBI&T-1980-10] B81-10011 [1D-A090127] H81-11116 1COOSIIC VELOCITY Two methods for calculating the load on the surface of a slender body executing axisymmetric vibrations in a sonic gas flow REPORT TITIE 181-10920 NUMBER ACTIVE COHTBOI DFVLB-dynamic model testing in wind tunnels for active controls research 181-11670 The title is used to provide a description of the subject matter. When the title is ACTOATOBS insufficiently descriptive of the document content, a title extension is added, Development and application of a moving base separated from the title by three hyphens. The NASA or AIAA accession number visual flight simulator including the design of is included in each entry to assist the user in locating the abstract in the abstract hydraulic actuators with hydrostatic bearings 181-11633 section of this supplement. If applicable, a report number is also included as an ADBESIVE BOBDIHG aid in identifying the document. Application of weldbonding to 1-10 production aircraft 181-11652 1DBESIVES Polymer research in rapid runway repair materials [1D-1089606] B81-10080 1-10 AIBCBAPI ADIABATIC FLOI Design and test of a graphite-epoxy composite 1-10 Adiabatic gas flow, citations from the NTIS data slat base 181-11339 [PB80-808516] H81-10048 Ipplication of weldbonding to 1-10 production AEBIAL PBOIOGBAPHI aircraft Aerial survey photography 181-11652 181-12350 1-300 AIBCBlfT AEEOACODSTICS Development of the 1300 fin in modern composite An experimental investigation of jet screech by fibre construction air jet impingement on solid boundaries 181-11653 181-11302 Airbus Industrie's heavenly twins - 1310 and Some thoughts on the effects of flight on jet 1300-600 noise as observed in actual flight and in wind 181-12318 tunnels 1BSOBBEBS (H1IEBI11S) 181-11723 Icoustic structures titanium brazing method AEBODISAHIC CflABlCTEBISIICS for producing honeycomb structures for jet Comparative performance of two centrifugal fan engine noise reduction impellers differing in blade section 181-10272 181-10162 1CCBIEB1TED HIE TESTS Belicopter tail configurations to survive tail The implications of laboratory accelerated rotor loss conditioning of carbon fibre composites 181-10768 H81-11129 The aerodynamic characteristics of some new BAE 1CCIDEHT IHVESTIGATIOB blade sections, and their potential influence on Evaluation of safety programs with respect to the rotor performance causes of general aviation accidents. Volume 2: 181-10769 Ippendices Numerical optimization - In assessment of its role [1D-1089181] 1181-10023 in transport aircraft aerodynamic design through Inuual reviev of aircraft accident data, O.S. a case study General aviation calendar year 1978 181-11601 [PB80-201916] H81-10028 Idvanced combat aircraft wing design ACCIDEBT SBETEHTIOH 181-11608 Evaluation of safety programs with respect to the A study of the air inlet efficiency of a combat causes of general aviation accidents. Volume 2: aircraft concept with dorsal inlet Ippendices 181-11615 [1D-1089181] S81-10023 Dynamic stability parameters at high angles of 1COOSIIC DOCIS attack Icoustic structures titanium brazing method 181-11621 for producing honeycomb structures for jet Identification of longitudinal flying engine noise reduction characteristics of an aeroplane and the effect 181-10272 of nonstationary aerodynamics ICOOSIIC IflPEDlHCE 181-1.1627 Effect of a semi-annular thermal acoustic shield low-speed airfoil section research at Delft on jet exhaust noise University of Technology [H1S1-TB-81615] B81-11770 181-11636 ICOUSTIC HEISUBEMEHIS Design and tests of an helicopter rotor blade with Experiments on effective source locations and evolutive profile velocity dependence cf the broad band noise from [OBEB1. TP SO. 1980-125] 181-11638 a rotating rod Estimation of wing nonlinear aerodynamic 181-11721 characteristics at supersonic speeds [H1S1-TP-1718] B81-10001

1-1 4EBODYBAHIC COEPFICIZSTS SUBJECT IHDBI

Comparison of Unsteady Pressure Fields Computed AZBODTBAMIC STABILITY and Measured on the ZKP model Investigation of high-manoeuvrability flight [AGABD-B-688] N81-11019 vehicle dynamics The turbulent wind and its effect on flight .481-11625 [ UTIAS-BEVIEW-44 ] N81-11020 Longitudinal notion of low-flying vehicles in Low-speed aerodynamic performance of nonlinear flowfields 50.8-centimeter-diameter noise-suppressing A81-11626 inlets for the Quiet, Clean, Short-haul An analytical study of landing flare Experimental Engine (QCSEE) Lewis 9- by [DFVLB-FB-79-40] B81-10062 15-foot low speed wind tunnel tests Full scale wind tunnel investigation of a [MASA-TP-1178] N81-11037 bearingless main helicopter rotor Ames 10 by ABBODISAflIC COEFFICIBB1S 80 foot wind tunnel test using the BO-105 Theoretical determination of subsonic oscillatory helicopter airforce coefficients for fin-tailplane [HAS1-C8-152373] B81-11014 configurations Hind tunnel investigation of the aerodynamic [BAI-TB-79125] N81-10016 hysteresis phenomenon on the 1-1 aircraft and Flight evaluation of stabilization and command its effects 00 aircraft motion augmentation system concepts and cockpit [AD-J089851] B81-11016 displays daring approach and landing of Flight evaluation of stabilization and command powered-lift STOL aircraft augmentation system concepts and cockpit [JIASA-TJ-1551 ] 881-11044 displays during approach and landing of AEBODYNAUC CONFIGOBAIIOHS powered-lift STOL aircraft Longitudinal motion of low-flying vehicles in [KASA-TP-1551] B81-11044 nonlinear flowfields Hissile notion sensitivity to dynamic stability A81-11626 derivatives High lift research and its application to aircraft [AD-A089750] H81-11093 design AEIODIBJHIC STALLIHS A81-11642 Investigation of the stalling characteristics of a High-lift investigations on some small aspect general aviation aircraft ratio wings 481-11665 A81-11643 AEBGDSBABICS Optimizing the fixed leading edge shape of a The aerodynamics of pure subsonic flow /4th transonic wing to suit the landing high-lift revised edition/ German book requirements A81-11441 AS 1-11644 High-lift investigations on some small aspect Noise control design problems on air cushion ratio wings vehicles and surface effect ships A81-11643 A81-11818 Linear vortex theories of a profile and wing with Theoretical determination of subsonic oscillatory air intake airforce coefficients for fin-tailplane A81-12703 configurations Adiatatic gas flow. Citations from the NTIS data [BAF.-TB-79125] 881-10016 base AEBOEYBAHIC DBAG [PB80-808546] 881-10048 Drag increment due to rear fuselage upsweep Pilot-aircraft system reponse to wind shear [ESDU-80006] B81-10001 [BASi-CB-3342] H81-10636 ABBODXBAUC IOECES The principles and applications of cryogenic wind Investigation of lateral forces and moments in the tunnels case of asymmetric gas flows in nozzles N81-11049 A81-10S13 Model design and instrumentation experiences with An analytical technique for approximating unsteady continuous-flow cryogenic tunnels aerodynamics in the tine domain K81-11057 [NASA-TP-1738] H81-11422 The European Transonic Hind tunnel ETH AEBODIBAHIC IBTEBFEBBHCE H81-11064 wind tunnel wall interference in a test section Characteristics and status of the DS National with ventilated walls Transonic Facility A81-11673 M81-11065 AEBODYNABIC LOADS AEBOELASTICITI Two methods for calculating the load on the Full scale wind tunnel investigation of a surface of a slender body executing axisymmetric bearingless main helicopter rotor Ames 40 by vibrations in a sonic gas flow 80 foot wind tunnel test using the BO-105 A81-10920 .helicopter Structural flight load testing, calibration and [NASA-CB-152373] N81-11014 analysis An analytical technique for approximating unsteady A81-11656 aerodynamics in the time domain Procedures to improve flight safety in wind shear IHASA-TP-1738] B81-11422 conditions AEBOHAOTICA1 EBGIHJBSIHG A81-11666 Fatigue test results of carbon fiber reinforced AEBODJBABIC BOISE plastic F28 aircraft component and its Discrete frequency noise due to irregularity in structural details blade row of axial fan rotor N81-11135 A81-10633 AIB COOIJIG On screeching jets exhausting from an axisymmetric The design of blowing-cooled aircraft electrical supersonic nozzle machines A81-11616 AS 1-10474 Experiments on effective source locations and AIB IH1AKZS velocity dependence of the broad band noise from Engine air intake design support by use of a rotating rod computational methods and comparison of 181-11724 theoretically derived pressure distributions Noise control design problems on air cushion with experimental data vehicles and surface effect ships A81-11614 A81-11818 A study of the air inlet efficiency of a combat The status of rotor noise technology aircraft concept with dorsal inlet A81-12737 A81-11615 Beapon bay cavity noise environments, data Linear vortex theories of a profile and wing with correlation and prediction for the B-1 aircraft air intake [AD-A089770] B81-11778 A81-12703

A-2 SUBJECT IHDBI AIBCBAF1 DESIG1

AIB 1AVIGATIOS Test and evaluation of the Airport Surveillance Recommended short-teem A1C improvements for Radar (ASRJ-8 wind shear detection system (phase helicopters. Volume 3: Operational description 2), revision of experimental 10BAH-C flight following (LOFF) [AC-A090111] N81-11290 in the Houston area AIB TBAHSPOB1ATIOH [AD-A089385] H81-10030 Airbus Industrie's heavenly twins - A310 and AIB POLLOTIOS A300-600 The aircraft in the stratosphere effects on A81-12348 ozone layer equilibrium Airport activity statistics of certificated route A81-10499 air carriers, calendar year 1979 Fuel jettisoning by U.S. Air Force aircraft. [AD-A089748] N81-11023 Volume 1: Summary and analysis Alternative energy sources for non-highway [AD-A089010] N81-10580 transportation, appendices Fuel jettisoning by U.S. Air Force aircraft. [DOE/CS-05438/T1-VOL-3] N81-11500 Volume 2: Fuel dump listings AIBBOB1E/SPACBBOBSE COSPOTEiS [AD-A089076] 881-10581 The 767 "s flight-management system - i new AIB TBAFFIC generation of airborne avionics Hourly airport activity profiles: 30 Airports by A81-11242 user, 3 airports by user and equipment type, AIBCBAFT ACCIDENT IBVESTIGATIOB selected days in June, July and August, 1978 The accident/injury matrix - A tool for aircraft [AD-A089450] S81-10031 accident investigation Airport activity statistics of certificated route A81-12241 air carriers, calendar year 1979 AIBCBAFT ACCIDEITS [AD-A089748] N81-11023 Helicopter tail configurations to survive tail AIB IBAFFIC COB1BOL rotor loss NASA Aviation Safety Beporting System A81-10768 [NASA-Tn-81225] H81-10021 civil aviation safety. Ill - Prospects of Recommended short-term A1C improvements for improvement helicopters. Volume 2: Recommended helicopter A81-11900 AIC training material Annual review of aircraft accident data, O.S. [AD-A089441] N81-10029 General aviation calendar year 1978 Recommended short-term ATC improvements for [EB80-201916] B81-10028 helicopters. Volume 3: Operational description AIBCBAFT COBFISOBATIOBS of experimental LORAN-C flight following (LOFF) New concepts for design of fully-optimized in the Houston area configurations for future supersonic aircraft [AD-A089385] N81-10030 A81-11606 Analysis of potentially correctable landing delays Some experiences with numerical optimisation in at Atlanta aircraft specification and preliminary design [AD-A089408] N81-10032 studies The Discrete Address Beacon System/Air Traffic A81-11609 Control Hadar Beacon System/ATCBBS IFF Hark 12 Bibliography on aerodynamics of airframe/engine system (DABS/ATCBBS/AIMS) performance prediction integration of high-speed turbine-powered model aircraft, volume 1 [AD-A089440] N81-10034 [NASA-TH-81814] N81-11032 Proposed ATC system for the Gulf of Hexico: AIBCBAFT COHSTBDCTIOB HATEIIALS Helicopter operations development program Acoustic structures titanium brazing method [AD-A089430] N81-10036 for producing honeycomb structures for jet Preliminary test plans of ATC concepts for longer engine noise reduction term improvement helicopter development program A81-10272 [AD-A089407] N81-10037 A practical method for predicting flight-by-flight Recommendations for short-term simulation of ATC crack growth in fighter type aircraft for damage concepts. Helicopter operations development tolerance assessment program A81-11659 [AD-A089435] N81-10038 Composite components on commercial aircraft Impact of the discrete Address Beacon System B81-11147 (DABS) on Air Traffic Control Badar Beacon Air Force applications and in-service experience System (ATCBBS) performance in selected with composite structures deployments S81-11148 [AD-A089611] N81-10039 Cost/benefit analysis of advanced materials Recommended short-term ATC improvements for technology candidates for the 1980's, part 2 helicopters. Volume 1: Summary of short term [BAS4-CB-165176] B81-11953 improvements AIBCBAFT C011BOI [AD-A089521] N81-100U1 The all-electric aircraft Contributions to the United Kingdom microwave A81-11617 landing system research and development program, Improved flight control performance and failure 1974 to 1978. Volume 1 tolerance'using modern control techniques £BAE-TR-79052-VOI-1] N81-10044 A81-11619 Contributions to the United Kingdom microwave DFVLB-dynamic model testing in wind tunnels for landing system research and development program, active controls research 1974 to 1978. Volume 2 A81-11670 [BAE-TB-79052-VOL-2] N81-10045 System simulation applied to the evaluation of Contributions to the United Kingdom microwave displays for guidance and control landing system research and development program, [DFVIB-DITT-79-10] B81-10064 1974 to 1978. Volume 3 AIBCBAFT DESIGB [BAE-TB-79052-VOI-3] N81-10046 The aerodynamics of pure subsonic flow /4th Proceedings of the 1979 Seminar on Air Traffic revised edition/ German book Control. Terminal Radar Approach Control A81-11441 (TBACON) facility supervisory desk complex How to improve the performance of transport [AD-A089914] N81-11024 aircraft by variation of wing aspect-ratio and New terminal radar approach control in tower cab twist /12th Daniel and Florence Guggenheim concept for Love Field, Dallas, Texas International Memorial Lecture/ [AD-A089996] N81-11025 AS 1-11602 ATABS implementation tradeoff Numerical optimization - An assessment of its role [AD-A089977] 1181-11026 in transport aircraft aerodynamic design through Formats for DABS data link applications a case study [AD-A089963] H81-11028 A81-11604 The relevance of the Flex-Hub Prop-Fan for fuel-efficient airliners A81-11605

A-3 AIHCB4FT DETECIIOB SUBJECT IBDEI

New concepts for design of fully-optimized Calculation of the flow field around configurations fee future supersonic aircraft engine-wing-configurations A81-11606 481-11613 Advanced combat aircraft uing design Hydrogen-fueled aircraft 481-11608 481-11753 Some experiences with numerical optimisation in Variable geometry, lean, premixed, prevaporized aircraft specification and preliminary design fuel combustor conceptual design study studies [ASHE P4PEB 80-GT-16] 481-12609 A81-11609 4utomation of aircraft gas-turbine power plants DBAFO - Computer-assisted design and manufacturing Bussian book system 481-12782 A81-11610 Comparisons of four alternative powerplant types Computer aided compilation of an electrical for future general aviation aircraft drawing file [NASA-TB-81584] H81-10067 A81-11611 4ircraft engine nacelle fire test simulator. The all-electric aircraft Volume 1: Technical A81-11617 [AD-4089629] S81-10081 Active flutter suppression design and test - A Summary of AGABD Lecture Series 107: The joint U.S.-F.B.G. program Application of Design to Cost and Life Cycle A81-11621 Cost to Aircraft Engines A stability augmentation system which covers the 1181-11926 complete flight envelope for a F-4c aircraft Cost/benefit analysis of advanced materials without gain scheduling technology candidates for the 1980's, part 2 481-11622 [HAS4-CB-165176] N81-11953 The future cockpit of the next generation of civil AIBCBJFT EflOIPflBBT aircraft The design of blowing-cooled aircraft electrical A81-11630 machines A theoretical and practical design investigation 481-10471 of the future military cockpit Head up displays. Citations from the A81-11631 International Aerospace Abstracts data base Research on transonic wings at the National [N4S4-CB-163656] H81-10049 Aerospace Laboratory, Japan Aircraft hydraulic systems dynamic analysis. A81-11640 Volume 6: Steady state flow analysis SSFAB High lift research and its application to aircraft computer program technical description design [AD-A089240] 1181-10055 A81-11642 A controlled evaluation of the differences between Hinglets development at Israel Aircraft Industries two approaches to reliability investment screening 481-11645 [AD-A087506] 1181-10446 Optimum subsonic, high-angle—of-attack nacelles Detecting the failure of aircraft sensors using 481-11646 analytical redundancy Structural optimization of advanced aircraft N81-11270 structures Transducer installation for the Sea King UK 50 A81-11651 mathematical model validation flight tests Optimal flight vehicle design and linear vector [AD-A089924] N81-11365 spaces Balanced design: Minimum cost solution A81-11668 N81-11919 Hydrogen-fueled aircraft AIECBAFT FOEl SYSTEMS 481-11753 Engineering and development program plan aircraft Engineering and development program plan aircraft crashworthiness crashworthiness [AD-4089431] 1181-10022 [AD-A089431] H81-10022 4IBCBAFT FUELS The IV-15 tilt rotor research aircraft Advanced fuel system technology for utilizing [HASA-TH-81244] N81-10054 broadened property aircraft fuels Design options study. Volume 1: Executive summary 181-11612 user reguirements for the advanced civil ECS integration for fuel efficient/low life cycle military aircraft cost design Environmental Control Systems in [AD-A089536] . 1181-10056 aircraft Design options study. Volume 2: Approach and 481-11676 summary results advanced civil military Computerized flight management for fuel saving aircraft: cost estimates 481-12349 [AD-A089537] N81-10057 AIBCBAFT GOIDABCE Design options study. Volume 3: Qualitative Analysis of the function principle and operational assessment advanced civil military aircraft assessment of an onboard glidepath guidance [AD-A089538] 1181-10058 system for visual approaches (Visual Approach Preliminary design characteristics of a subsonic Honitor (VAn) business jet concept employing an aspect ratio [DFVLB-FB-79-38] 881-10043 25 strut braced ving System simulation applied to the evaluation of [NASA-CE-159361] 1181-11013 displays for guidance and control Evolution of techniques for ICC analysis j [DFVLB-HITT-79-10] H81-10064 N81-11909 Gyrocompasses. Citations from the International The Hornet program: A design to life cycle cost Aerospace Abstracts data base case study [HASA-CB-163675] 1181-10065 881-11910 AIBCBAFT BAZ1BDS Design-to-cost and new technologies Civil helicopter wire strike assessment study. N81-11913 Volume 2: Accident analysis briefs AIBCEAFT DETECTION [BASA-CB-152390] 881-10019 Systems analysis of the installation, mounting, Aircraft engine nacelle fire test simulator. and activation of emergency locator transmitters Volume 1: Technical in general aviation aircraft [AD-A089629] 881-10081 [NASA-CB-160036] N81-10020 Assessing the behavior of high modulus composite AIBCBAFT EHGISES materials in lightning Beliability and engineering-economic 1181-11141 characteristics of aircraft engines Bussian The potential for damage from the accidental book release of conductive carbon fibers from A81-10045 aircraft composites Impact damage of aircraft gas turbine engines with S8 1-11143 axial compressors 481-11324

4-4 SUBJECT IIDBI AIBCBAFI SAFETY

AIBCB4FI HIDB4ULIC SISTBHS Aircraft performance optimization by forced Development and application of a moving base singular perturbation visual flight sinulator including the design of 481-11667 hydraulic actuators with hydrostatic bearings Optimal flight vehicle design and linear vector A81-11633 spaces AIBCBAPT IBDOSTBZ 481-11668 A reviev and assessment of system cost reduction DFVLB-dynamic model testing in wind tunnels for activities active controls research H81-11906 A81-11670 Osing cost reduction concepts at The use of data items on aircraft performance Hessier-Hispano-Bugatti measurement H81-11923 [ESDO-80009] S81-10053 AIBCBAFT ISSTBOBEETS The XV-15 tilt rotor research aircraft Head-up displays. Ill [BASi-Ta-812411] 1181-10054 A81-11320 Improved aircraft cruise by periodic control Hind shear detection from Ecu-recorded Mis-flight 881-11030 data AIECBAFT flLOTS A81-11675 Bultivariable closed-loop analysis and flight AIBCBAFT LABDI5S control synthesis for air-to-air tracking F/A-18's landing, launch and recovery system [AD-A090050] 1181-11046 A81-11244 AIBCBAF1 EBODUCTJOB Optimizing the fixed leading edge shape of a DB4PO - Computer-assisted design and manufacturing transonic wing to suit the landing high-lift system requirements 481-11610 AS 1-11644 Application of weldbonding to 4-10 production An analytical study of landing flare aircraft [DFV1B-FB-79-40] 1181-10062 481-11652 Airport activity statistics of certificated route AIBCBAFT EBODOC1IOI COSTS air carriers, calendar year 1979 Design to Cost and Life Cycle Cost [AD-A089748] N81-11023 [4GABE-CP-289] H81-11902 AiaCBAFI LAOBCHISG DEVICES The Hornet program: A design to life cycle cost F/A-18's landing, launch and recovery system case study A81-11244 B81-11910 AIBCBAFT BillTEIUCE Design to cost and the F-16 multirole fighter Compatibility of aircraft operational fluids Kith N81-11911 a graphite/epoxy composite: Development of an Structural integration as a means of cost reduction exterior coating system and remover 1181-11912 [AD-A090049] 1181-11120 Design-to-cost and new technologies fieliability-centered maintenance K81-11913 H81-11917 Organizing a design-to-cost program Impact of maintainability of life cycle costs N81-11914 H81-11921 A new method for estimating transport aircraft AIBCBAFT HANEOJBBS direct operating costs Piloted simulation studies of helicopter agility N81-11915 A81-10767 Design-to-cost applied to the AS350 helicopter 11 ultivariable aircraft control by manoeuvre 1181-11916 commands - An application to air-to-ground gunnery Estimation of relative total cost for aircraft [ONEBA, TP NO. 1980-127] A81-11623 systems Initial experience with methods to evaluate flight N81-11922 test characteristics with operational flight Using cost reduction concepts at maneuvers Messier-Hispano-Bugatti A81-11782 H81-11923 A multivariate approach to handling gualities AIBCBAFT BELIABI1ITI rating scale development Beliability and engineering-economic [AD-A089825] 881-11047 characteristics of aircraft engines Bussian AIBCBAPT flODElS book Model tests for an active rotor isolation system A81-10045 C8BB-278-79-0] A81-12095 Subseguent proof of damage tolerance for a landing Sodel design and instrumentation for intermittent gear component after numerous takeoffs and ccyogenic wind tunnels landings 1181-11058 481-11475 AIBCBAFT NOISE A piloted simulator investigation of static Prediction of changes in aircraft noise exposure stability and stability/control augmentation A81-11820 effects on helicopter handling gualities for Community response to noise from a general instrument approach aviation airport [BASi-TB-81188] S81-10077 AS 1-11821 Exploratory study of hazard mitigation and The status of rotor noise technology research in the air transport system A81-12737 [AD-A089204] 1181-11021 Survey population response to airplane noise, part 1 Summary of. Federal Aviation Administration [SASA-TM-75790] N81-10576 responses to National Transportation Safety 4IBCEAFT PABTS Board safety recommendations Structural integration as a means of cost reduction [AD-A089971] N81-11022 N81-11S12 Some engineering aspects of life cycle costing UBCBAFI SEBFOBBAHCE 1181-11918 Bow to improve the performance of transport AIBCBAFI SAFETY aircraft by variation of Ming aspect-ratio and Ground testing of aircraft antistatic protection twist /12th Daniel and Florence Guggenheim [ONEBA. TP NO. 1980-126] A81-11674 International Memorial lecture/ Civil aviation safety. Ill - Prospects of A81-11602 improvement Possibilities for the valuation of different A81-11900 combat aircraft configurations with respect to HAS4 Aviation Safety Eeporting System flight mechanics {HASA-TH-81225J N81-10021 A81-11607 Engineering and development program plan aircraft Identification of longitudinal flying crash worthiness characteristics of an aeroplane and the effect [4D-4089431] B81-10022 of nonstationary aerodynamics A81-11627

A-5 AIBCBAFT SPECIJICiflOBS SOBJECT IHDEX

Evaluation of safety programs vith respect to the AIBCBAFT SOBIIVABILITY causes of general aviation accidents. Volume 2: Helicopter tail configurations to survive tail Appendices rotor loss [AD-A089181] N81-10023 A81-10768 Handbook on bird management and control The analysis of fatigue failures [AD-A08S009] H81-10024 481-11603 Applications of pyrotechnigues in aviation Failure management techniques for high survivability [SNIAS-792-422-103] N81-10025 H81-11272 Search and rescue methods and eguipment. A ilBFIILO SOBFACE MOVEMENTS bibliography vith abstracts NASA Aviation Safety Eeporting system [PB8G-812837] N81-10026 [NAS4-TB-81225] N81-10021 Bird strikes and aviation safety. Citations from AIBFOIL PBOFILBS the Mils data base Design of airfoils in incompressible viscous flovs [PB80-812944] B81-10027 by numerical optimization Exploratory study of hazard mitigation and 481-10096 research in the air transport system The performance of slotted blades in cascade [AD-A089204] N81-11021 481-10632 Summary of Federal Aviation Administration Lov-speed airfoil section research at Delft responses to National Transportation Safety University of Technology Board safety recommendations 481-11636 [AD-4089971] N81-11022 Design and tests of an helicopter rotor blade vith ATAK5 implementation tradeoff evolutive profile [AD-A089977] N81-11026 [ONEBA, IP NO. 1980-125] A81-11638 AIBCBAFT SPECIFICATIONS Calculation of separated viscous flovs on wing Some experiences vith numerical optimisation in profiles by a coupling approach aircraft specification and preliminary design [ONEBA, TP SO. 1980-122] 481-11920 studies Linear vortex theories of a profile and ving vith A81-11609 air intake AIBCEAPT STABILITY A81-12703 A stability augmentation system which covers the AIBFOI1S complete flight envelope for a F-lc aircraft The aerodynamic characteristics of some nev HAI vithout gain scheduling blade sections, and their potential influence on A81-11622 rotor performance Dynamic stability parameters at high angles of A81-10769 attack Flov computation around multi-element airfoils in A81-11621 viscous transonic flov Model tests for an active rotor isolation system A81-11641 [MBB-278-79-0] A81-12095 A comparison of Nevton-like methods for the AIBCBAF1 S5BUCIOBBS transonic small disturbance equation Aspect ratio variability in part-through crack [4D-4090270] N81-11017 life analysis Definitive generic study for the effect of high A81-10355 lift airfoils on vind turbine effectiveness, Part-through crack problems in aircraft structures executive summary A81-10362 [SEBI/TB-98003-2] 1181-11192 Experimental application of a vibration reduction AIBFBABE HATBBIALS technique Flight simulation environmental fatigue crack A81-10770 propagation in 2024-T3 and 7475-T761 aluminium Design and test of a graphite-epoxy composite A-10 481-11657 slat Operational durability of airframe structures 481-11339 481-11662 The analysis of fatigue failures Cast Aluminum structures Technology (CAST). A81-11603 Technology transfer (phase 6) Height optimization of ving structures according [AD-A087492] 1181-10152 to the gradient method Exploratory study of hazard mitigation and A81-11650 research in the air transport system Structural optimization of advanced aircraft [AD-A089201] H81-11021 structures Air Force technical objective document FY 1981 481-11651 [AD-A089709] B81-12010 Development of the A300 fin in modern composite AIBFBAHES fibre construction The use of parametrj.c cost estimating A81-11653 relationships as they pertain to aircraft Nondestructive evaluation of composite structures airframes: 4 nev perspective 481-11651 [AD-A089525] B81-10060 Holographic non-destructive testing of materials Bibliography on aerodynamics of airframe/engine using pulsed lasers for aircraft structures integration of high-speed turbine-powered A81-11655 aircraft, volume 1 Structural flight load testing, calibration and [NASA-TM-81814] H81-11032 analysis Development of advanced interceptor substructural 481-11656 material graphite epoxy missile structures Operational durability of airframe structures [AD-A090127] N81-11116 481-11662 AIBLIHE OPEBATI01S Ground testing of aircraft antistatic protection Methods of fuel conservation in civil aviation. I [ONEBA, IF NO. 1980-126] A81-11671 A81-11322 Elastomers used in aeronautics industry Hourly airport activity profiles: 30 Airports by [SHIAS-801-551-105] H81-10168 user, 3 airports by user and eguipment type, Evaluation of secticn properties for hollov selected days in June, July and August, 1978 composite beams [AC-A089150] B81-10031 [PAFEB-HB-35] 881-101151 A nev method for estimating transport aircraft Lightning protection considerations for direct operating costs graphite/epoxy aircraft structure N81-11915 N81-11112 AIBPOBT SLABBING Air Force applications and in-service experience Airfield pavement demonstration-validation study uith composite structures 481-10718 N81-11118 Atlanta's nev central passenger terminal complex OS Havy service experience vith advanced composites 481-10719 in aircraft composite structures Reduction of the take-off ground run distance to a 1181-11149 given set of atmospheric condition 481-11631

i-6 SUBJECT IBDBI

Prediction cf changes in aircraft noise exposure 4PPBOACH IBDICATOBS A81-11820 Proceedings of the 1979 Seminar on Air Traffic ATABS implementation tradeoff Control. Terminal fiadar Approach Control [AD-A089977] H81-11026 (TBACOK) facility supervisory desk complex AIBPOBT lOiEBS [AD-A089910] B81-1102<4 Sew terminal radar approach control in toner cab ABCBITECTOBE (COHPOTEBS) concept for Love Field, Dallas, Texas Optimized computer systems for avionics applications [AD-A089996] N81-11025 [AD-A089570] B81-10063 Test and evaluation of the Airport Surveillance Hicrocomputer array processor system design Badar (ASBJ-8 vind shear detection system (phase for electronic warfare 2), revision 881-11673 [AD-A090111] N81-11290 ABBBSTIB6 GEAB AIBPOBTS F/A-18's landing, launch and recovery system Commanity response to noise from a general A81-112UI) aviation airport ASPECT BATIO A81-11821 Aspect ratio variability in part-through crack NASA Aviation Safety Beporting System life analysis [HASA-TH-81225] N81-10021 A81-10355 Sourly airport activity profiles: 30 Airports by Bov to improve the performance of transport user, 3 airports by user and equipment type, aircraft by variation of wing aspect-ratio and selected days in June, July and August, 1978 twist /12th Daniel and Florence Guggenheim [AD-A089t50] H81-10031 International Hemorial Lecture/ Analysis of potentially correctable landing delays A81-11602 at Atlanta ASPHALT [AD-A089U08] N81-10032 Polymer research in rapid runway repair materials Airfield pavement evaluation. Citations from the [AD-A089606] N81-10080 Oils data base ATLAITA (61) [PB80-812860] N81-10083 Atlanta's new central passenger terminal complex Annoyance from light aircraft investigation A81-10719 carried out around four airports near Paris ATHOSPHEBIC EFFECTS [BASA-TH-75823] N81-10577 The aircraft in the stratosphere effects on Airport activity statistics of certificated route ozcne layer equilibrium air carriers, calendar year 1979 A81-10199 [AD-A089718] N81-11023 Reduction of the take-off ground run distance to a AIRSPEED given set of atmospheric condition A method of helicopter low airspeed estimation A81-11634 based on measurement of control parameters ATBOSPBEBIC HODEIS [BBB-UD-276-79-0] A81-1209<4 The turbulent wind and its effect on flight ALGOBITBHS [UTIAS-BEVIIH-41 ] S81-11020 Badar target detection and map-matching algorithm ATTITUDE COBTB01 studies Flight evaluation of stabilization and command A81-11158 augmentation system concepts and cockpit ALTEBBATIKG COBBEHT displays during approach and landing of Brushless cryogenic ac motors powered-lift STOL aircraft A81-10I168 £BASA-TP-1551] B81-11011 ALDBIBDH ATTITUDE IBDICATOBS Cast Aluminum Structures Technology (CAST). Fitment of TA8AI) standby attitude indicators to Technology transfer (phase 6) Hacchi aircraft £AB-A087192] H81-10152 [AD-A089378] B81-11036 lightning protection considerations for AOTOBATIC COBTBOI graphite/epcxy aircraft structure Automation of aircraft gas-turbine power plants 881-111U2 Bussian book ALDHIBDH ALLOYS A81-12782 Flight simulation environmental fatigue crack Improved aircraft cruise by periodic control propagation in 2024-T3 and 7175-1761 aluminium B81-11030 A81-11657 Container Life Adapter-Helicopter (CLAH) Flight simulation environmental fatigue crack operational prototype (preprodnction) propagation in 202H-T3 and 7175-T761 aluminum militarized units for flight evaluation and ving panels for transport aircraft operational testing [BLB-HP-80003-U] N81-11115 [AD-A08979U] B81-11031 ABGLB OF ATTACK AUTOMATIC FLIGHT COBTBOL Dynamic stability parameters at high angles of Failure management for the SAAB Viggen JA37 aircraft attack H81-11273 A81-11621 AVIONICS Beviev of numerical methods for the problem of the The design of blowing-cooled aircraft electrical supersonic flow around bodies at angle of attack machines A81-11639 A81-1017I) Optimum subsonic, high-angle-of-attack nacelles High-density avionic power supply A81-116U6 A81-11157 ABTEHBA ABBAIS The 767"s flight-management system - A new Excitation of a circular array of cylinders Kith generation of airborne avionics longitudinal slits in radio antennas A81-11212 481-12619 The rcle of flight simulation in the design and ABTEB8A BADIATIOS PAITBBBS development of the Sea Harrier Bav-Attack System Excitation of a circular array of cylinders with A81-11635 longitudinal slits in radio antennas Becommended short-term ATC improvements for A81-12619 helicopters. Volume 2: Becommended helicopter APPBOACfl AID LASBISS TESTS (STS) ATC training naterial Flight evaluation of stabilization and command £AD-A089««1] B81-10029 augnentation system concepts and cockpit Head up displays. Citations from the BUS data base displays during approach and landing of £PB80-809064] 881-10050 powered-lift STOL aircraft Optimized computer systems for avionics applications [HASA-TP-1551] B81-110U4 [AD-A089570] B81-10063 APPBOACH COBTBOL Summary of Federal Aviation Administration Analysis of the function principle and operational responses to Bational Transportation Safety assessment of an onboard glidepath guidance Beard safety recommendations system for visual approaches (Visual Approach £AD-A089971] H81-11022 Monitor (VAH) Failure management techniques for high survivability [DFVLB-IB-79-38] H81-10013 B81-11272

A-7 AIIAL PLOB TDBBINES SUBJECT IBDBI

Hicrocomputer array processor system design The control of pressure, temperature and Mach for electronic warfare number in a blowdown-to-atmosphere cryogenic B81-11673 wind tunnel Estimation of relative total cost for aircraft B81-11063 systems BO-105 BELICOPTEB S81-11922 Full scale wind tunnel investigation of a Summary of AGABD Lecture Series 100: Methodology bearingless main helicopter rotor Ames 40 by for control of life cycle costs for avionics 80 foot wind tunnel test using the EO-105 systems helicopter B81-11924 [BASA-CB-152373] B81-11014 The role of advanced technology of turbine engine BODI-IIBG ABD TAIL COBEIGOBATIOBS life cycle cost Possibilities for the valuation of different 881-11927 combat aircraft configurations with respect to AXIAL FLCi XOBBINES flight mechanics Optimum design of axial flow gas turbine stage. I A81-11607 - Formulation and analysis of optimization BOBI-1IBS COHPIGOBATIOBS problem. II - Solution of the optimization A comprehensive evaluation and analysis of problem and numerical results transonic flow calculations on three related A81-12608 wing-body configurations [FFA-TN-AU-1418-PT-1] B81-10013 BOEING 767 AIBCBAJT B The 767's flight-management system - A new B-1 AIBCB4FT generation of airborne avionics Heapon bay cavity noise environments, data A81-11242 correlation and prediction for the B-1 aircraft BOBOI-BEOXT COHPOOBDS £AD-A08977G] N81-11778 Effect of various environmental conditions on BATS (STEDC10BAL ONUS) polymer matrix composites Weapon bay cavity noise environments, data N81-11130 correlation and prediction for the B-1 aircraft BOOHDABI LAIEB FLO! [AD-A089770] H81-11778 Low-speed airfoil section research at Delft BEAMS (SOPPOBTS) University of Technology Evaluation of section properties for hollow A81-11636 composite beams BOONDABJ JALDE PBOBLEBS [PAPEB-NB-35] B81-10454 An experimental and theoretical investigation of BEABISGLESS BOTOBS pressures in four-lobe bearings Pull scale Kind tunnel investigation of a A81-10840 tearingless main helicopter rotor Ames 40 by BHiZIBG 80 foot wind tunnel test using the BO-105 Acoustic structures titanium brazing method helicopter for producing honeycomb structures for jet [BASA-CB-152373] 1181-11014 engine noise reduction BEABIBGS A81-10272 The vibration of a multi-bearing rotor BBOADBAKD A81-11722 Experiments on effective source locations and BEBDIHG VIBBATIOB velocity dependence of the broad band noise from Finite element analysis of natural and forced a rotating rod flexural vibrations of rotor systems A81-11724 A81-11956 BBOSBES (ElECTBICAI COSTACTS) BIBLIOGBAPHIES Brushless cryogenic ac motors Search and rescue methods and equipment. A A81-10468 bibliography with abstracts [PB80-812837] B81-10026 Bird strikes and aviation safety. Citations from the N1IS data base CALIBBATIBG [PB80-812944] B81-10027 Structural flight load testing, calibration and Adiabatic gas flow. Citations from the BUS data analysis base A81-11656 [PB80-808546] B81-10048 Calibration of a blowdown-to-atmosphere cryogenic Head up displays. Citations from the wind tunnel International Aerospace Abstracts data tase S81-11060 [NASA-CB-163656] K81-10049 CABBON Gyrocompasses. Citations from the International Compound Cycle Turbofan Engine (CCTB). Task 9: Aercspace Abstracts data base Carbon-slurry Fuel Combustion Evaluation Program [BAEA-CB-163675] B81-10065 [AD-A089451] H81-10072 Axial flow compressors, citations from the CABBOB DIOIIDE LASBBS Engineering Index data base Ignition of a liguid fuel [PB80-808611 ] 1181-10076 [AD-A089295] B81-10128 Airfield pavement evaluation. Citations from the CABB08 FIBEB BEIBFOBCED PLASTICS K1IS data base Effect of service environment on composite materials [PB80-812860] B81-10083 [AGABD-CP-288] B81-11128 Axial flow compressors. Citations from the BUS Constant-amplitude and flight-by-flight tests on data base CFBP specimens [PB80-808603] B81-10441 H81-11133 Bibliography on aerodynamics of airframe/engine Fatigue strength of CFBP under combined integration of high-speed turbine-powered flight-by-flight loading and flight-by-flight aircraft, volume 1 temperature changes [BASA-1H-81814] B81-11032 N81-11134 BIBD-*IBCBAFf COLLISICHS Fatigue test results of carbon fiber reinforced Bird strikes and aviation safety. Citations from plastic F28 aircraft component and its the Nils data base structural details [PB80-812944] H81-10027 H81-11135 BIBDS The potential for damage from the accidental Handbook on bird management and control release of conductive carbon fibers from £AD-A089009] B81-10024 aircraft composites BLOiDOHB USD TDBBELS H81-11143 Calibration of a blowdown-to-atmosphere cryogenic Design-to-cost and new technologies wind tunnel H81-11913 B81-11060

A-8 SUBJECT I8DEI COMPOSITE BiTIBIAIS

CABBOB FIBEBS Systems analysis of the installation, mounting, A probabilistic analysis of electrical equipment and activation of emergency locator transmitters vulnerability to carbon fibers in general aviation aircraft * [8ASA-TB-80217] B81-11113 [BASA-CB-160036] 881-10020 Fiber release from impacted graphite reinforced NASA Aviation Safety Beporting System epoxy composites [NASA-TB-81225] H81-10021 [BASA-CE-16368U] 881-11117 Summary of Federal Aviation Administration The implications of laboratory accelerated responses to Bational Transportation Safety conditioning of carbon fibre composites Board safety recommendations H81-11129 [AD-A089971] 881-11022 CAHGO Proceedings of the 1979 Seminar on Air Traffic Container life Adapter-Helicopter (CLAH) Control. Terminal Radar Approach Control operational prototype (preproduction) (IfiACON) facility supervisory desk complex militarized units for flight evaluation and [AD-A089914] 881-11021 operational testing COATIBGS [AD-A089794] 881-11034 Compatibility of aircraft operational fluids vith CAB60 AIBCBAF1 a graphite/epoxy composite: Development of an Design options study. Volume 1: Executive summary exterior coating system and remover user requirements for the advanced civil [AD-A090049] 881-11120 military aircraft COCKPIT S1BULATOBS [AD-A089536] B81-10056 Piloted simulation studies of helicopter agility Design options study. Volume 2: Approach and A81-10767 summary results advanced civil military COCKPITS aircraft: cost estimates The future cockpit of the next generation of civil [AD-A089537] B81-10C57 aircraft Design options study. Volume 3: Qualitative A81-11630 assessment advanced civil military aircraft A theoretical and practical design investigation [AD-A089538] 881-10058 of the future military cockpit Design options study. Volume 1: Detailed A81-11631 analyses supporting appendices advanced COLLISIOBS civil military aircraft Civil helicopter wire strike assessment study. [AD-A089539] H81-10059 Volume 2: Accident analysis briefs CASCADE PIOI [BASA-CB-152390] 881-10019 The performance of slotted blades in cascade COBBOSTIOB CHAiBMS A81-10632 Variable geometry, lean, premixed, prevaporized CAS1 ALLOTS fuel combustor conceptual design study Cast Aluminum structures Technology (CAST). [ASHE PAPEB 80-GT-16] A81-12609 Technology transfer (phase 6) Fuel character effects on current, high pressure [AD-A087492] 1181-10152 ratio, can-type turbine combustion systems CAVITIES [AD-A089182] H81-10073 Heapon bay cavity noise environments, data COBBOS1IOS EFFICIBSCY correlation and prediction for the B-1 aircraft Flameholding characteristics of a svept-strut H2 [AD-A089770] H81-11778 fuel-injector for scraajet applications CEHEBTS A81-10711 Polymer research in rapid runway repair materials Variable geometry, lean, premixed, prevaporized [AD-A089606] H81-10080 fuel combustor conceptual design study CEHTBIFOGAL COHIBBSSOBS [ASHE PAPEB 80-GT-16] A81-12609 Comparative performance of two centrifugal fan COBHABI AID COITBOL impellers differing in blade section Bultivariable aircraft control by manoeuvre A81-10162 commands - An application to air-to-ground gunnery A method of performance prediction for centrifugal [OBEBA, TP NO. 1980-127] A81-11623 compressors. Part 1: Analysis. Part 2: COBHEBCIAL AIBCBAFT Comparison vith experiment The future cockpit of the next generation of civil [ABC-B/B-3843] B81-10436 aircraft CEBTBIFOGAL 8UBPS A81-11630 Inlet flow in centrifugal pumps at partial Design options study. Volume 1: Executive summary deliveries user requirements for the advanced civil [VKI-PBEPBIHT-1979-16] H81-10137 military aircraft CEBTBIFOSES [AE-A089536] S81-10056 Axial flov compressors. Citations from the Design options study. Volume 2: Approach and Engineering Index data base summary results advanced civil military [PB80-808611] H81-10076 aircraft: cost estimates CBBTIflCAlIOI [AD-A089537] H81-10057 Flight termination receiver/decoders design, Design options study. Volume 3: Qualitative performance and certification assessment advanced civil military aircraft [AD-A089746] B81-11045 [AD-A089538] H81-10058 CBABBEI FLOS Design options study. Volume 4: Detailed Flov past a slender profile in a channel vith analyses supporting appendices advanced permeable nails civil military aircraft A81-10916 [AD-A089539] B81-10059 CHEMICAL EO.OILIBBIOB Composite components on commercial aircraft The aircraft in the stratosphere effects on 881-111*7 ozone layer equilibrium COBPAIIBILITI A81-10499 Compatibility of aircraft operational fluids vith CIBCDI1 DIAGBAflS a graphite/epoxy composite: Development of an Characteristics and status of the OS Bational exterior coating system and remover Transonic Facility [AD-AO90049] B81-11120 881-11065 COBPOSEBT BELIABIJ.III CIVIL AVIATIOB A controlled evaluation of the differences tetveen Methods of fuel conservation in civil aviation. I tvo approaches to reliability investment screening A81-11322 [AD-A087506] B81-10446 OIGA, a gust alleviation system for improvement of COBPOSITE BATBBIALS passenger comfort of general aviation aircraft Evaluation of section properties for hollow A81-11620 composite beams Civil aviation safety. Ill - Prospects of CfAPEB-BB-35] B81-10454 improvement Effect of service environment on composite materials A81-11SOO [AGABD-CP-288] B81-11128

A-9 COBPOSITE STBOCTOBBS SUBJECT IBDEX

The implications of laboratory accelerated Aircraft hydraulic systems dynamic analysis. conditioning of carbon fifcre composites Volume 6: Steady state flow analysis SSFAN H81-11129 computer program technical description Relationships between impact resistance and [AC-A089240] N81-10055 fracture toughness in advanced composite materials COHPOTEB SIS1EBS DESIGB N81-11137 DRAPO - Computer-assisted design and manufacturing Assessing the behavior of high modulus composite system materials in lightning 481-11610 H81-11141 COaPOTEB TECHBIQOES Composite components on commercial aircraft Computerized flight management for fuel saving B81-11147 A81-12349 Air Force applications and in-service experience Computer based in-flight monitoring with composite structures N81-11269 1181-11148 COHPOTBHIZBD DESIGN COBPOSITE STBOC1DBES Numerical optimization - An assessment of its role Design and test of a graphite-epoxy composite A-10 ' in transport aircraft aerodynamic design through slat a case study A81-11339 A81-11601 Structural optimization of advanced aircraft DRAPO - Computer-assisted design and manufacturing structures system A81-1U51 481-11610 Development of the 4300 fin in modern composite Computer aided compilation of an electrical fibre construction drawing file J81-116S3 A81-11611 Nondestructive evaluation of composite structures Engine air intake design support by use of 481-11651 computational methods and comparison of Development of uind tunnel fan blade made of theoretically derived pressure distributions composite materials with experimental data [MBB-UD-277-79-0] 481-12096 481-11614 Development of advanced interceptor substructural Optimum design of axial flow gas turbine stage. I material graphite epoxy missile structures - Formulation and analysis of optimization [AD-A090127] N81-11116 problem. II - Solution of the optimization Erosion and impacts on composite helicopter blades problem and numerical results N81-11138 481-12608 Fatigue and damage propagation in composite rotor Design options study. Volume 4: Detailed blades analyses supporting appendices advanced N81-11145 civil military aircraft Composite components on commercial aircraft [AD-A089539] N81-10059 N81-11147 COnPOTEBIZBD SIHOUTIGB Air Force applications and in-service experience Prediction of changes in aircraft noise exposure Kith composite structures 481-11820 N81-11148 A comprehensive evaluation and analysis of US Havy service experience with advanced composites transonic flow calculations on three related in aircraft composite structures wing-body configurations N81-11149 [IT4-TN-AD-1418-PT-1] N81-10013 COHPBESSIOH LOADS System simulation applied to the evaluation of Design and fabrication of stabilized organic displays for guidance and control matrix composites [DFVLB-BI1T-79-10] H81-10064 481-11338 Bissile motion sensitivity to dynamic stability COMPRESSOR BLADES derivatives Reduction of energy consumption in the vitrational [AD-A089750] N81-11093 shot peer,ing of axial compressor vanes An automated procedure for developing hybrid A81-11321- computer simulations of turbofan engines Disk residual life studies. Part 2: TI30 [BASA-TB-81605] N81-11688 10th-stage compressor disk (INCOIOY 901) CONCRETE SXBDCTOBES [AD-A089524] . N81-10074 Airfield pavement demonstration-validation study COMPBESSOB EfFICIEICI 481-10718 A method of performance prediction for centrifugal COHCBETES compressors. Part 1: Analysis. Part 2: Polymer research in rapid runway repair materials Comparison with experiment [AD-A089606] S81-10080 [ABC-B/B-3843] N81-10436 COHFEBEBCBS COBPUTATIOSiL F101D DJBABICS Effect of service environment on composite materials Calculation of the flow field around [4GABD-CP-288] 881-11128 engine-wing-configurations COBFOBBAL BAPPIB6 A81-11613 The performance of slotted blades in cascade Engine air intake design support by use of A81-10632 computational methods and comparison of CO1GBESSIOBAL BEPOBIS theoretically derived pressure distributions Aviation safety and noise abatement with experimental data [GFC-50-923] H81-10578 481-11614 COBSOLES Beview of numerical methods for the problem of the Proceedings of the 1979 Seminar on Air Traffic supersonic flow around bodies at angle of attack Control. Terminal Badar 4pproach Control A81-11639 (TRACON) facility supervisory desk complex Besearch on transonic wings at the National [AD-A089914] B81-11024 Aerospace laboratory, Japan New terminal radar approach control in tower cab A81-11640 concept for Love Field, Dallas, Texas Flow computation around multi-element airfoils in [AD-A089996] B81-11025 viscous transonic flow COBTBOL BOiBDS A81-11641 New terminal radar approach control in tower cab Calculation of plane transonic flows using the concept for Love Field, Dallas, Texas integral equation method and shock fitting [AD-A089996] B81-11025 A81-11779 C08TBOL COBFISDBED VEHICLES Calculation of separated viscous flows on wing Flying gualities criteria for advanced control profiles by a coupling approach technology transports [ONEBA, IP NO. 1980-122] A81-11920 A81-11618 COMPDTEB PBOGEAHS Multivariable aircraft control by manoeuvre Estimation of wing nonlinear aerodynamic commands - An application to air-to-ground gunnery characteristics at supersonic speeds [ONERS, IP NO. 1980-127] A81-11623 [NASA-TP-1718] B81-10004

4-10 SUBJECT IHDBI CBYOGEIIC BIHD TOIIEIS

COSTEOL STABILIIT Design-to-cost and nev technologies A stability augmentation system vhich covers the M8 1-11913 complete flight envelope for a P-Uc aircraft Design-to-cost applied to the AS350 helicopter vithout gain scheduling 881-11916 481-11622 Using cost reduction concepts at COSTBOL TBEOEY Bessier-flispano-Bugatti Improved flight control performance and failure 881-11923 tolerance using modern control techniques CBACK IBITI4TIOI A81-11619 Fatigue damage mechanisns in composite materials - COBTSOLLABI11II A reviev Piloted simulation studies of helicopter agility AS 1-10717 A81-10767 CBACK PBOEAGATIOB The control of pressure, temperature and Mach Aspect ratio variability in part-through crack number in a blovdovn-to-atmosphere cryogenic life analysis vind tunnel 481-10355 S81-11063 Fart-through crack problems in aircraft structures COHVEBGEIT BOZZIBS A81-10362 8ev interpretations of shock-associated noise vitb Fatigue damage mechanisms in composite materials - and vithout screech 4 reviev [BAS4-TH-81590] 881-10E07 A81-10747 COBTESSEHT-D1VEBGBBI BOZZIES On understanding environnent-enhanced fatigue On screeching jets exhausting from an axisymaetric crack grovth - 4 fundamental approach supersonic nozzle 481-10719 A81-11616 Flight simulation environmental fatigue crack Calibration of the high speed vind tunnel TVD 150 propagation in 2021-13 and 7175-T761 aluminium in the supersonic range 481-11657 481-11778 4 practical method for predicting flight-by-flight COSH1C BATS crack grovth in fighter type aircraft for damage The emulsion chamber experiment on supec-sonic tolerance assessment Concorde /Echos/ A81-11659 481-12176 Disk residual life studies. Part 1: F100 COST AB4LISIS 1st-stage turbine disk (IN100) ATABS implementation tradeoff [AD-A089791] N81-11011 £40-4089977] H81-11026 Flight simulation environmental fatigue crack Life Cycle Cost Analysis (ICCA) in military propagation in 2021-13 and 7175-T761 aluminum aircraft procurement ving panels for transport aircraft B81-11903 [HLB-HP-80003-U] N81-11115 Evolution of technigues for ICC analysis CBACKIBG (FBACTUBIBG) N81-11909 The analysis of fatigue failures Cost/benefit analysis of advanced materials 481-11603 technology candidates for the 1980's, part 2 CBASBES [SASA-CB-165176] 881-11953 Systems analysis of the installation, mounting, COST BIFBC1IVEHESS and activation of emergency locator transmitters Definitive generic study for the effect of high in general aviation aircraft lift airfoils on uind turbine effectiveness, [BASA-CB-160036] B81-10020 executive summary Engineering•and development program plan aircraft [SEBI/TB-98003-2] B81-11192 crashvorthiness Cost considerations of engine fuel control systems [AD-A089131] N81-10022 N81-11S28 CHITICAI FLOS COSI BSTIBATBS Inlet flov in centrifugal pumps at partial Design options study. Volume 2: Approach and deliveries summary results advanced civil military £VKI-EBEPBIBT-1979-16] B81-10137 aircraft: cost estimates CBOISINe FLIGBT [AD-&089537] H81-10057 Improved aircraft cruise by periodic control The use of parametric cost estimating B81-11030 relationships as they pertain to aircraft CBYOGEBIC EfiOIPHElT airfraffles: A nev perspective Brushless cryogenic ac motors [AD-A089525] " B81-10060 A81-10168 Maritime patrol aircraft engine study. General CBI06EBIC IIBD TOB1ELS Electric derivative engines. Volume 2: A system for model access in tunnels vith an Appendix A. Performance data - GE27/T3 study a1 unbreathable test medium turboprop 481-11672 [4D-A089336] B81-10068 A fan pressure ratio correlation in terms of fiach Maritime patrol aircraft engine study. General number and Reynolds number for the Langley 0.3 Electric derivative engines. Volume 3; meter transonic cryogenic tunnel Appendix B. Performance data - TF31/T7 study A1 (NAS4-TP-1752] 881-10005 turboprop The principles and applications of cryogenic vind [AD-A089279] 881-10069 tunnels The potential for damage from the accidental N81-11019 release of conductive carbon fibers from Hodel design and instrumentation experiences vith aircraft composites continuous-flov cryogenic tunnels 881-11113 S81-11057 OS Army design-to-cost experience Hodel design and instrumentation for intermittent B81-11905 cryogenic vind tunnels A reviev and assessment of system cost reduction S81-11058 activities Calibration of a blovdovn-to-atmosphere cryogenic 881-11906 vind tunnel Design to life cycle ccst research S81-11060 H 81-11907 The control of pressure, temperature and Hach i nev method for estimating transport aircraft number in a blovdovn-to-atmosphere cryogenic direct operating costs vind tunnel 881-11915 B81-11063 COSI BEDOCIIOI Characteristics and status of the US Rational Design to Cost and life Cycle Cost Transonic Facility [AGABE-CP-289] 881-11902 B81-11065 The Hornet program: A design to life cycle cost case study 881-11910

4-11 CDHOLATIVE DASAGB SUBJECT IBDEZ

CUMULATIVE DAHAGE Reliability-centered maintenance A practical method for predicting flight-by-flight B81-11917 crack growth in fighter type aircraft for damage Design to cost and systems, LCC tolerance assessment H81-11920 481-11659 Summary of AGABE Lecture Series 107: The CUTTING Application of Design to Cost and Life Cycle Applications of pyrotechnigues in aviation Cost to Aircraft Engines [SNIAS-792-U22-103] H81-10025 N81-11926 CYCLIC LOADS DIESEL ENGINES On understanding environment-enhanced fatigue Comparisons of four alternative powerplant types crack growth - I fundamental approach for future general aviation aircraft A81-107U9 [BASA-TH-8158U] B81-10067 CILIBDBICAL ANIEHHAS DIFFERENCE EQUATIONS Excitation of a circular array of cylinders with A comparison of Newton-like methods for the longitudinal slits in radio antennas transonic small disturbance equation A81-12619 [AD-A090270J 881-11017 DIFFDSEBS Vortex drag reduction by aft-mounted diffusing vanes A81-11617 DAMAGE DIGITAL COBEDTBBS The potential for damage from the accidental Failure management for the SAAB Viggen JA37 aircraft release of conductive carbon fibers frcm 081-11273 aircraft composites DIGITAL 10 ANALOG COBVEETEBS 881-11113 A six-channel guick-look unit for the aerodynamics DAMAGE ASSBSSBBiT division MKI airborne data acquisition package A practical method for predicting f light-by-flight [AC-A089975] N81-11361 crack growth in fighter type aircraft for damage DIBECtlONAL STABILITI tolerance assessment Helicopter tail configurations to survive tail A8 1-11659 rotor loss Assessing the behavior of high modulus composite A81-10768 materials in lightning DISCBETE ADDBESS BEACOJ SYSTEM N81-11111 The Discrete Address Beacon System/Air Traffic Fatigue and damage propagation in composite rotor Control Badar Beacon system/ATCBBS IFF Bark 12 llades system (DAES/ATCBBS/AIHS) performance prediction model DATA ACQDISITIOB [AD-A0891UO] B81-10031 Hind shear detection from ice-recorded HLS-flight Impact of the discrete Address Beacon System data (CABS) on Air Traffic Control Badar Beacon A81-11675 System (ATCBBS) performance in selected A six~channel guick-look unit for the aerodynamics deployments division MKI airtorne data acquisition package CAD-A089611] B81-10039 [AD~A089975] B81-11361 Formats for DABS data link applications DATA COBSELATICB CAD-A089963] B81-11028 Weapon bay cavity noise environments, data DISKS (SBAIES) correlation and prediction for the B- 1 aircraft Disk residual life studies. Part 2: TF30 [AD-A089770] N81-11778 10th-stage compressor disk (INCOLOJ 901) DATA LINKS tAD-A089524] H81-1007U Formats for DABS data link applications DISPLAY DEUCES [AD-A089963] N81-11028 The future cockpit of the next generation of civil DATA SBOCESSIBG aircraft The use of data items on aircraft performance A81-11630 measurement A theoretical ajid practical design investigation [ESDU-80009] N81-10053 of the future military cockpit DECISION HAKIBG A81-11631 Balanced design: Minimum cost solution Head up displays. Citations from the 081-11919 International Aerospace Abstracts data base Design to ccst and systems, LCC [BASA-CB-163656] N81-10049 H81-11920 System simulation applied to the evaluation of DECISION TBEOEI displays for guidance and control Estimation of relative total cost for aircraft [DFVLB-MITT-79-10] B81-10061 systems Proceedings of the 1979 Seminar on Air Traffic N81-11922 Control. Terminal Badar Approach Control DEFENSE INDOSTBI (TBACON) facility supervisory desk complex Air Force technical objective document !J 1981 [AD-A089914] N81-1102"! [AD-A08S709] N81-12010 Helicopter electro-optical system display DESIGN ANALYSIS requirements. 1. The effects of CBT display Design of airfoils in incompressible viscous flows size, system ganma function, and terrain type on by numerical optimization pilots required display luminance A81-10096 [AD-A089755J N81-11035 Possibilities for the valuation of different DISTANCE combat aircraft configurations with respect to Beduction of the take-off ground run distance to a flight mechanics given set of ataospheric condition A81-11607 A81-116311 Airbus Industrie's heavenly twins - A310 and DISTORTION A30C-600 An evaluation of statistical methods for the A81-123t8 prediction of maxioum time-variant inlet total Evaluation of section properties for hollow pressure distortion composite teams [AD-A089817] B81-110UO [PAPEB-NB-35] B81-10H5Q DOCDHENT STOBAGE A1ABS implementation tradeoff Computer aided compilation of an electrical [SD-A089977 J 881-11026 drawing file The European Transonic Nind tunnel ETH A81-11611 1181-11061 DOBESTIC EHEBGI The implications of laboratory accelerated Hydrogen - Its technology and implications. Volume conditioning of carbon fibre composites <4 - Utilization of hydrogen Book B81-11129 A81-11751 Design to Cost and life Cycle Cost [AGAHD-CP-289] H81-11902

A-12 SUBJECT ISDBX BHGISE DESIGB

DOPPiBB BADAB ELECTRIC BBTIOBKS Contributions to the Doited Kingdom microwave Computer aided compilation of an electrical landing system research and development program/ drawing file 1971 to 1978. Volume 1 481-11611 [BAE-TE-79052-Y01-1] H81-10011 BLECTBIC POiBB SUPPLIES Contributions to the Dnited Kingdom microwave High-density avionic power supply landing system research and development program, 481-11157 19711 to 1978. Volume 2 ELECTEJCAi PBOPEBTIE3 [BAE-TR-79052-VOL-2] 881-10015 Assessing the behavior of high modulus composite Contributions to the United Kingdom microuave materials in lightning landing system research and development program, 881-11111 1971 to 1978. Volume 3 BLEC1BOB OPTICS [BAE-TB-79052-VC1-3] H81-10016 tiead-up displays. Ill lest and evaluation of the Airport Surveillance 481-11320 Badar (ASB)-8 wind shear detection system (pbase BLBCIBOSTATIC CBABSE 2), revision Ground testing of aircraft antistatic protection [4D-4090111J B81-11290 (OBEBA, IP NO. 1980-126] A81-11671 DRAFTING (DB4BIBG) EBEB6I COBSBBVATIOB Computer aided compilation of an electrical Beduction of energy consumption in the vibrational drawing file shot peening of axial compressor vanes 481-11611 A81-11321 DBA6 BEASOBBBBHT Methods of fuel conservation in civil aviation. I Drag increment due to rear fuselage upsweep A81-11322 [ESDD-80006] H81-10001 The relevance of the Flex-Hub Prop-Fan for DRAG BEDUCTICB fuel-efficient airliners Vortex drag reduction by aft-mounted diffusing vanes A81-11605 481-11617 B8EB6Y COSSDHPII01 Leading-edge 'Vortex Flaps1 for enhanced subsonic Characteristics and status of the OS national aerodynamics of slender wings Transonic Facility A81-11618 B81-11065 DOBABHITY EBEBGI COSVBBSIO! EFFICIEHCY Operational durability of airframe structures New BBC high-efficiency gas turbines 481-11662 481-11797 Aircraft turbine engine monitoring experience. An EBEBGI POLICY. overview and lessons learned from selected case Definitive generic study for the effect of high studies lift airfoils on wind turbine effectiveness, [4D-&089752] S81-11012 executive summary DYB4BIC CBABACTEBISTICS [SEBI/TB-98003-2] B81-11192 Development and application of a moving base Alternative energy sources for non-highway visual flight simulator including the design of transportation, appendices hydraulic actuators with hydrostatic bearings [DOE/CS-05138/T1-VOL-3] 881-11500 A81-11633 EBEB6I SPECTB4 Plow measurements in the wake of a wing fitted The emulsion chamber experiment on super-sonic with.a leading-edge root extension (strake) Concorde /Echos/ £B4E-IB-79120] B81-10015 481-12176 DYHABIC BODE1S EBEB6I TBCBBOLOGY DFVLB-dynamic model testing in wind tunnels for Hydrogen - Its technology and implications. Volune active controls research 1 - Utilization of hydrogen Book 481-11670 481-11751 DYSABIC BESPOBSE EBGIBE COUTBOl Hissile motion sensitivity to dynamic stability The all-electric aircraft derivatives 481-11617 [AD-A089750J B81-11093 Computerized flight management for fuel saving DO A HIC STABILITY 481-12319 Dynamic stability parameters at high angles of EiGISE DESIGI attack 4 numerical study of candidate transverse fuel A81-11621 injector configurations in the Langley scramjet DYBABIC STBOC1DEA1 ABA1YSIS engine The vibration of a multi-bearing rotor 481-10709 481-11722 Engine air intake design support by use of computational methods and comparison of theoretically derived pressure distributions with experimental data ECOBOflIC F4CIOBS 481-11611 Beliability and engineering-economic Hydrogen-fueled aircraft characteristics of aircraft engines Bussian 481-11753 took Optimum design of axial flow gas turbine stage. I 481-10015 - Formulation and analysis of optimization EDDI COBEEBfS problem. II - solution of the optimization Disk residual life studies. Part 1: F100 problem and numerical results 1st-stage turbine disk (IB100) 481-12608 £40-4089791] B81-11011 Variable geometry, lean, premixed, prevaporized BIASTOHEBS fuel coabustor conceptual design study Elastomers used in aeronautics industry [4SBE P4PEB 80-GT-16] 481-12609 [SBI4S-801-551-105J S81-10168 Autonation of aircraft gas-turbine power plants BLECTBIC COBIiOl Bussian book The all-electric aircraft 481-12782 481-11617 Maritime patrol aircraft engine study. General ELECTHIC EQOIPflEBI Electric derivative engines. Volume 2: A probabilistic analysis of electrical equipment Appendix 4. Performance data - GE27/T3 study al vulnerability to carbon filers turboprop [H4SA-TH-80217] 1181-11113 [40-4089336] H81-10068 ElECTBIC BOfOBS Maritime patrol aircraft engine study. General Brushless cryogenic ac motors Electric derivative engines. Volume 3: 481-10168 4ppendix B. Performance data - TF31/T7 study 41 The all-electric aircraft turboprop A81-11617 [AD-A089279] BS1-10069

4-13 ESGIHB FAILOBE SOBJBCI IBDBX

Cost/benefit analysis of advanced materials ESCAPE SIS1EBS technology candidates for the 1980's, part 2 Engineering and development program plan aircraft [NASA-CB-165176] 1181-11953 crashworthiness EHGIHB FAILOBE IAD-A089U31} H81-10022 Impact damage of aircraft gas turbine engines with BDBOPBAI AIBBOS axial compressors Airbus Industrie's heavenly twins - A310 and A81-11321 A300-600 EHGIBB INLETS A81-12318 Engine air intake design support by use of EVACOAIIiG (TBAiSPOBTATIOB) computational methods and comparison of Applications of pyrotechniques in aviation theoretically derived pressure distributions ISNIAS-792-422-103] H81-10025 Kith experimental data EITEBHAL S10BES A81-11611 In-flight measurement of aerodynamic loads on Optimum subsonic, high-angle-of-attack nacelles captive stores. Equipment and results A81-11616 [HLB-HP-79013-U] B81-10012 Lou-speed aerodynamic performance of 50.8-centimeter-diameter noise-suppressing inlets for tie Quiet, Clean, Short-haul Experimental Engine (QCSEE) Lewis 9- iy F-U AIBCBAFI 15-foot Ion speed Hind tunnel tests Active flutter suppression design and test - A [BASA-TP-1178] H81-11037 joint O.S.-F.B.G. program EBGIBE NOISE A81-11621 Acoustic structures titanium brazing method A stability augmentation system which covers the for producing honeycomb structures for jet complete flight envelope for a F-lc aircraft engine noise reduction without gain scheduling A81-10272 A81-11622 Core noise measurements from a small, general Fiberglass-reinforced rigid polyurethane expedient aviation turhofan engine pavement subject to simulated f-t aircraft traffic [HASA-TM-81610] 881-11769 [AD-A089266] M81-10079 EIGISE TBSTIJG LABOBATOBIBS Nind tunnel investigation of the aerodynamic Quantitative thermography in aero-engine research hysteresis phenomenon on the F-1 aircraft and and development its effects on aircraft motion [PBB-90021] 881-10075 [AD-A089851] B81-11016 EHGIBE TESTS Bobust control system design Beliaiility and engineering-economic B81-11275 characteristics of aircraft engines Bassian ?-8 AIBCBAFT book Flight experience with flight control redundancy A81-10015 management Forced vibrations of a nonlinear system excited by K81-11271 a centrifugal oscillator with a sloping engine F-16 AIBCBAFI characteristic Design to cost and the F-16 multirole fighter 481-10139 S81-11911 Aircraft turbine engine monitoring experience. 4n F-18 AIBCBAPI overview and lessons learned from selected case F/A-18's landing, launch and recovery system studies A81-1121I) [AD-A089752] B81-11012 PABBICATIOB EH?IBOBHBBT BABAGBHEB1 Design and fabrication of stabilized organic Handbook on bird management and control matrix composites [AD-A08S009J sai-10024 481-11338 EBYIBOHHEBT SIHOLATIOB Development of advanced interceptor substructural Prediction of changes in aircraft noise exposure material graphite epoxy missile structures AS 1-11820 [AD-A090127] 881-11116 EHVIBOBHEBTiL COBTBOL FAIL-SAFE SYSTBBS ECS integration for fuel efficient/low life cycle Improved flight control performance and failure cost design Environmental Control Systems in tolerance using modern control techniques aircraft A81-116J9 A81-11676 fAILOBE EB?IBOHHENT»L TESTS Detecting the failure of aircraft sensors using Effect of service environment on composite materials analytical redundancy [AGABB-CP-288] 881-11128 B81-11270 Effect of various environmental conditions on FAILOBE ABJLYSIS polymer matrix composites The analysis of fatigue failures S81-11130 481-11603 Fatigue strength of CFBP under combined Computer based in-flight monitoring flight-by-flight loading and flight-by-flight N81-11269 temperature changes Failure management techniques for high survivability 881-11134 (181-11272 Flight simulation environmental fatigue crack Failure management for the SAAB Viggen JS37 aircraft propagation in 2021-13 and 7175-1761 aluminum H81-11273 ifing panels for transport aircraft Flight experience with flight control redundancy [KLB-MP-80003-0] S81-11115 management EPOII BESISS B81-1127I1 Microcracking in graphite-epoxy composites FAB BLADES [AD-A089891] 881-11118 Discrete frequency noise due to irregularity in EQOATIOHS OF HOTIOB blade row of axial fan rotor An exact solution of the problem of the motion of A81-10633 a gyroscope in a Cardan suspension Development of wind tunnel fan blade made of A81-12701 composite materials EBOSIOI [HBB-UD-277-79-0] A81-12096 Erosion and impacts on composite helicopter blades Superhybrid composite blade impact studies 881-11138 [BASA-TH-81597] B81-11112 EBBOB AHALYSIS FATIGDB (BA1BBIALS) Predictability of moisture absorption in Cast Aluminum Structures Technology (CAST). graphite/epoxy sandwich panels Technology transfer (phase 6) N81-11131 [AD-A087192] B81-10152 ESCAPE (ABABDOiflBBI) Fatigue and damage propagation in composite rotor Applications of pyrotechnigues in aviation blades [SBIAS-792-122-1C3] N81-10025 B81-11115

A-11 SUBJECT IBDEI FLIGHT COBTBOL

FATIGOB HIS Fatigue strength of CFBP under combined Aspect ratio variability iD part-through crack flight-by-flight loading and flight-by-flight life analysis temperature changes A81-10355 N81-1113Q Fatigue damage mechanisms in composite materials - Fatigue test results of carbon fiber reinforced A review plastic F28 aircraft component and its A81-107U7 structural details The analysis of fatigue failures 1181-11135 A81-11603 FILE HAISTBNANCB (COHEOIEBS) Disk residual life studies, fart 2: TF30 Computer aided compilation of an electrical lOth-stage compressor disk (ISCOLOY 901) draving file [AD-A089524] B81-10C71I A81-11611 Airfield pavement evaluation. Citations from the FINANCIAL SiBAGEHBBT NIIS data base Evolution of techniques for LCC analysis [PB80-812860] H81-10083 B81-11909 Disk residual life studies. Part 1: F100 FINITE DIFFBBBNCB TBEOBt 1st-stage turbine disk (IK 100) Beviev of numerical methods for the problem of the [AD-A089791] B81-11011 supersonic flov arcund bodies at angle of attack Constant-amplitude and flight-by-flight tests on A81-11639 CFRP specimens FINITE ELEHEBT HETHOD H81-11133 Flov computation around multi-element airfoils in FATIGOE 1ES1S viscous transonic flov Flight simulation environmental fatigue crack A81-11611 propagation in 2024-T3 and 7475-1761 aluminium Finite element analysis of natural and forced A81-11657 flezural vibrations of rotor systems Fatigue strength of CFBP under combined A81-11956 flight-by-flight loading and flight-by-flight FISHED BODIES temperature changes Theoretical determination of subsonic oscillatory B81-11134 airforce coefficients for fin-tailplane Fatigue test results of carbon fiber reinforced configurations plastic F28 aircraft component and its [BAE-TB-79125] 1181-10016 structural details FINS N81-11135 Development of the A300 fin in modern composite FADLI TOLEBAHCB fibre construction Computer based in-flight monitoring A81-11653 1181-11269 FIBE COBTEOL Failure management techniques for high survivability Hultivariable aircraft control by manoeuvre B81-11272 commands - An application to air-to-ground gunnery Flight experience with flight control redundancy [ONEBA, TP BO. 1980-127] A81-11623 management FIBE PBEVEBTIOB N81-11274 Aircraft engine nacelle fire test simulator. Bobust control system design Volume 1: Technical N81-11275 [AD-A089629] 1181-10081 FEEDBACK COBT801 FIIBD ilBGS Nultivariable closed-loop analysis and flight Engineering and development program plan aircraft control synthesis for air-to-air tracking crashvorthiness (AD-A090050] H81-11016 [AD-A089431] N81-10022 FIBEE COMPOSITES FLAflE BOLDEBS Fatigue and damage propagation in composite rotor Flameholding characteristics of a svept-strut H2 blades fuel-injector for scramjet applications B81-11145 A81-10711 FIBEB BEIEASE FLEIIN6 A probabilistic analysis of electrical equipment Finite element analysis of natural and forced vulnerability to carbon fibers flexural vibrations of rotor systems [HASA-TH-80217] H81-11113 A81-11956 Fiber release from impacted graphite reinforced FLI6BT CHABACTEBISTICS epoiy composites Identification of longitudinal flying [HASA-CB-163684] H81-11117 characteristics of an aeroplane and the effect The potential for damage from the accidental of nonstationary aerodynamics release of conductive carbon fibers from S81-11627 aircraft composites Development and application of a moving base S81-11143 visual flight simulator including the design of FIELD TBEOBI (PHISICS) hydraulic actuators vith hydrostatic bearings Analysis of calculated three-dimensional inviscid A81-11633 flov fields vith embedded shock naves Helicopter flight characteristics improvement (presentation of a field solution), part 1 through svept-tip rotor blades [ESA-TT-558] B81-10017 [HBB-OD-275-79-0] A81-12097 FIGHIBB ilBCBAFT Improved aircraft cruise by periodic control NASA presses fighter gains long-range S81-11030 supersonic cruise aircraft A multivariate approach to handling qualities A81-10575 rating scale development Possibilities for the valuation of different [AD-A089825] N81-11017 combat aircraft configurations vith respect to FLI6BI COITBOI flight mechanics The 767's flight-management system - A new A81-11607 generation of airborne avionics Advanced combat aircraft ving design A81-11212 A81-11608 Flying qualities criteria for advanced control A study of the air inlet efficiency of a combat technology transports aircraft concept vith dorsal inlet A81-11616 A81-11615 Improved flight control performance and failure A practical method for predicting flight-by-flight tolerance using modern control techniques crack grovth in fighter type aircraft for damage A81-11619 tolerance assessment Hnltivariable aircraft control by manoeuvre A81-11659 commands - An application to air-to-ground gunnery Constant-amplitude and flight-by-flight tests on [OBEBA, TP HO. 1980-127] A81-11623 CFBP specimens DFVLB-dynaoic model testing in wind tunnels for H81-11133 active controls research A81-11670

A-15 FLIfiBT HAZABDS SUBJECT IHDBZ

4 method of helicopter Ion airspeed estimation Becommendations for short-term simulation of ATC based on measurement of control parameters concepts. Helicopter operations development [HBB-OD-276-79-0] 481-12091 program Computerized flight management for fuel saving [AD-A089435] 881-10038 481-123149 A piloted simulator investigation of static Secom mended short-term ATC improvements for stability and stability/control augmentation helicopters. Volume 3: Operational description effects on helicopter handling qualities for of experimental IOBAN-C flight following (LOFF) instruaent approach in the Houston area [NASA-TB-81188] 881-10077 [AD-A089385] H81-10030 Pilot-aircraft system reponse to wind shear Fitment of TANAH standby attitude indicators to [N8SA-CB-3342] B81-10636 Macchi aircraft Flight simulation environmental fatigue cracX [AD-A089378] 881-11036 propagation in 2024-T3 and 7475-T761 aluminum Simulating study of the interaction between the King panels for transport aircraft propulsion and flight control systems of a [m.B-ME-80003-0] H81-11115 subsonic lift fan VIOL FLIGHT SIBOLATOBS [NASA-TH-81239] M81-110Q3 Development and application of a moving base flight termination receiver/decoders design, visual flight simulator including the design of performance and certification hydraulic actuators vith hydrostatic bearings [AD-A089746] H81-11045 AS 1-11633 Kulti variable closed-loop analysis and flight The turbulent wind and its effect on flight control synthesis for air-to-air tracking [01IAS-BEVIEH-44] N81-11020 [AD-A090050] 1181-11046 Microprocessor software applications for flight Computer based in-flight monitoring training simulators N8 1-11269 B81-11658 Detecting the failure of aircraft sensors using FLIGHT STABILITY TESTS analytical redundancy Missile motion sensitivity to dynamic stability S81-11270 derivatives robust control system design [AD-A089750] 1181-11093 H81-1127S FLIGHT S1BBSS FLIGHT HiZiBDS Flight simulation environmental fatigue crack Bird strikes and aviation safety. Citations from propagation in 2024-T3 and 7475-T761 aluminium the NTIS data base A81-11657 [PB80-812944] N81-10027 FLIGBI TESTS FLIGHT IBSIBOHEHTS Active flutter suppression design and test - A Head up displays. Citations from the BUS data base joint U.S.-F.fi.G. program [EB80-809064] N81-10050 481-11621 PLIGBI HECBAHICS Beduction of the take-off ground run distance to a The aerodynamics of pure subsonic flow /4th given set of atmospheric condition revised edition/ --- German book A81-1163II Design and tests of an helicopter rotor blade vith possibilities for the valuation of different evolutive profile combat aircraft configurations with respect to [OHEBA, IP NO. 1980-125] 481-11638 flight mechanics Structural flight load testing, calibration and 481-11607 analysis Aircraft performance optimization by forced A81-11656 singular perturbation Investigation of the stalling characteristics of a 481-11667 general aviation aircraft FLIGBT P4TH3 A81-11665 Recommended short-term 4TC improvements for Initial experience with methods to evaluate flight helicopters. Volume 3: Operational description test characteristics with operational flight of experimental IOBAN-C flight following (I.CFF) maneuvers in the Houston area 481-11782 [AD-A089385]' 1181-10030 Helicopter flight characteristics improvement FLIGHT HECOBDEiS through swept-tip rotor blades A six-channel quick-look unit for the aerodynamics [BBB-OD-275-79-0] 481-12097 division MKI airborne data acguisition package In-flight measurement of aerodynamic loads on [AD-A089975] N81-11364 captive stores* Equipment and results FLIGHT BOIES [MLB-BP-79013-D] N81-10012 Summary of Federal Aviation Administration The use of data items on aircraft performance responses to National Transportation Safety measurement Board safety recommendations [ESCO-80009] N81-10053 [AD-A089971] N81-11022 Flight test results of the BFB 320 model following FLIGHT SAFBTI control system for the in-flight simulaticn of procedures to improve flight safety in wind shear Airbus A 130 conditions [DFVLB-HIIT-79-13] B81-10078 A81-11666 Aircraft turbine engine monitoring experience. An Ground testing of aircraft antistatic protection overview and lessons learned from selected case [OHEBA, T5 NO. 1980-126] 481-11674 studies Civil aviation safety. Ill - Prospects of [AD-A089752] B81-11042 improvement Constant-amplitude and flight-by-flight tests on A81-11900 CIEP specimens NASA Aviation Safety Beporting System N81-11133 [NASA-TH-81225] N81-10021 FLIGHT TB4IIIIG Aviation safety and noise abatement Becommended short-term AXC improvements for CGPO-50-9233 N81-10578 helicopters. Volume 2: Recommended helicopter Failure management for the SAAB Viggen JA37 aircraft ATC training material N81-11273 (AD-A089441] N81-10029 FLIGBI SIHULATION Fitment of TAMAB standby attitude indicators to piloted simulation studies of helicopter agility Hacchi aircraft A81-10767 [AD-A089378] K81-11036 Identification of longitudinal flying FLIGHT VEHICLES characteristics of an aeroplane and the effect Investigation of high-manceuvraiility flight of nonstationary aerodynamics vehicle dynamics A81-11627 A81-11625 The role of flight simulation in the design and Optimal flight vehicle design and linear vector development of the Sea Harrier Nav-Attack System spaces 481-11635 A81-11668

A-16 SUBJECT IHDEI GAS DYiAHICS

Gyrostabilizers for inertial control systems FBACTOBE STBEIGTB Russian book fielationships between impact resistance and A81-12024 fracture toughness in advanced composite materials PLOi CHABACIZBISTICS N81-11137 Analytical estimation on nonlinear longitudinal FBASCB characteristics of vings with small and moderate Annoyance from light aircraft investigation aspect ratio by the vortex lattice method in carried out around four airports near Paris incompressible flow [HASA-TM-75823] B81-10577 [ESA-TT-585] H81-10018 JBBB FLIGHT The European Transonic iind tunnel ETI Investigation of high-manoeuvrability flight H81-11064 vehicle dynamics FLO! DISTOBTIOH A81-11625 Flow past a slender profile in a channel with FBEE VIBHATIOI permeable walls The vibration of a multi-bearing rotor A81-10916 A81-11722 FLO! DISTBIBOTIOB Finite element analysis of natural and forced Calculation of the flow field around flexural vibrations of rotor systems engine-wing-configurations A81-11S56 481-11613 FUEL COflBDSTIOS Analysis of calculated three-dimensional inviscid Compound Cycle Turbofan Engine (CCTE). Task 9: flow fields with embedded shock waves Carbon-Slurry Fuel Combustion Evaluation Program (presentation of a field solution), part 1 [AD-A089451] B81-10072 [ESA-TT-558] H81-10017 Alternative energy sources for non-highway FLO! GEOBBTBY transportation, volume 1 Asymmetric flow of subsonic and sonic jets over an [DOE/CS-OS438/T1-VOL-1] H8 1-11513 infinite wedge FUEL COHSUHPTIOI A81-10919 Methods of fuel conservation in civil aviation. I An example of the transonic flow past a tod; with A81-11322 a discontinuity in the contour curvature The relevance of tne Flex-Hub Prop-Fan for A81-12367 fuel-efficient airliners FLO! BEASDBEBESI AS 1-11605 High-lift investigations on some small aspect Advanced fuel system technology for utilizing ratio wings broadened property aircraft fuels A81-11643 A81-11612 FLOH VELOCITY ECS integration for fuel efficient/low life cycle Calculation of the flow field around cost design Environmental Control Systems in engine-wing-configurations aircraft A81-11613 A81-11676 FLO! VISUALIZATION Computerized flight management for fuel saving Add fluorescent minitufts to the aerodynamicist's A81-12349 bag of tricks Maritime patrol aircraft engine study. General A81-11245 Electric derivative engines. Volume 2: High-lift investigations on some small aspect Appendix A. Performance data - GE27/T3 study al ratio wings turboprop A81-11643 [AD-A089336] 1181-10066 A simple laser interferometer for wind tunnel flow Maritime patrol aircraft engine study. General visualisation Electric derivative engines. Volume 3: A81-12078 Appendix B. Performance data - IF34/T7 study A1 Holographic investigation of slender body vortex turboprop wakes [AD-A089279] H81-10069 [AD-A089496] B81-10008 FDEL COHTBOL FLUID BOUSDABJES ECS integration for fuel efficient/low life cycle An experimental investigation of jet screech by cost design Environmental Control Systems in air jet impingement on solid boundaries aircraft A81-11302 J81-11676 FLQT1BB Cost considerations of engine fuel control systems Active flutter suppression design and test - A B81-11928 joint U.S.-F.B.G. program FUEL IBJECTIOB A81-11621 A numerical study of candidate transverse fuel til BY ilBB COI1BOI injector configurations in the Langley scramjet Improved flight control performance and failure engine tolerance using modern control technigues A81-10709 A81-11C19 Flameholding characteristics of a swept-strut B2 Flight experience with flight control redundancy fuel-injector for scramjet applications management A81-10711 H81-11274 FUEL SYSTEMS FOBCIO VIBBATIOB Advanced fuel system technology for utilizing Forced vibrations of a nonlinear system excited by broadened property aircraft fuels a centrifugal oscillator with a sloping engine A81-11612 characteristic FDEL TESTS A81-10439 Advanced fuel system technology for utilizing The vibration of a multi-bearing rotor broadened property aircraft fuels A81-11722 A81-11612 Finite element analysis of natural and forced FOICTIOBAL DESIGI SPECIFICATION flexural vibrations of rotor systems Design options study. Volume 3: Qualitative A31-11956 assessment advanced civil military aircraft FOBMAT [AD-A089538] M81-10058 Formats for DABS data link applications FUSELAGES CAD-A089963] H81-11028 Drag increment due to rear fuselage upsweep FBACfOBE BECHABICS [ESDO-80006] B81-10001 Fatigue damage mechanisms in composite materials - A review A81-10747 On understanding environment-enhanced fatigue GAS DYBAHICS crack growth - A fundamental approach Adiacatic gas flow. Citations froa the NTIS data A81-10749 base Disk residual life studies. Fart 1: F100 £FB80-808546] H81-10048 1st-stage turbine disk (1H100) [AD-A089791] H81-11041

A-17 GAS FLOi SUBJECT IBDBX

6AS FLOi Predictability of moisture absorption in Investigation cf lateral forces and moments in the graphite/epoxy sandwich panels case of asymmetric gas flows in nozzles 881-11131 A81-10S13 Graphite-epoxy panel compression strength GAS STBBAHS reduction due to local impact Two methods foe calculating the lead on the 881-11139 surface of a slender bod; executing axisymmetric lightning protection considerations for vibrations in a sonic gas flow graphite/epoxy aircraft structure A81-10S20 N81-11142 Effect of a semi-annular thermal acoustic shield US Navy service experience with advanced composites on jet exhaust noise in aircraft composite structures [BASA-TM-81615] H81-11770 881-11149 GAS 10EBIHE EHGIHES GBOUHD EFFECT (AEBODINIHICS) Impact damage of aircraft gas turbine engines vith Longitudinal motion of low-flying vehicles in axial compressors nonlinear flowfields A81-11324 481-11626 Optimum design of axial flow gas tarbine stage. I GBOOBD EFFECT BACBIBBS - Formulation and analysis of optimization Noise control design problems on air cushion problem. II - Solution of the optimization vehicles and surface effect ships problem and numerical results A81-11818 A81-12608 GBOOBD TESTS Automation of aircraft gas-turbine pover plants Ground testing of aircraft antistatic protection Russian book IONZBA, IP 80. 1980-126] A81-11674 A81-12782 GOLF OF MEXICO Comparisons of four alternative poverplant types Proposed ATC system for the Gulf of Mexico: for future general aviation aircraft Helicopter operations development program [NASA-T»-8158a] H81-10067 [4D-A089Q30] 881-10036 An analysis of Air Force management of Turbine GUST ALLEVIATOBS Engine Monitoring Systems (THUS) OLGA, a gust alleviation system for improvement of [AD-A089365] S81-10070 passenger comfort of general aviation aircraft GAS 10BBIBES A81-11620 New BBC high-efficiency gas turbines GOSI LOADS A81-11797 Kind shear detection from ECM-recorded MLS-flight Axial flou compressors. Citations from the data Engineering Index data base 481-11675 [PB80-808611 ] 881-10076 GUSTS Axial flow compressors. Citations from the BTIS The turbulent wind and its effect on flight data base [DTIAS-BEVIEH-44] • H81-11020 [PB80-808603] 881-101(41 GIBOCOBfASSES 6EABS Gyrocompasses. Citations from the International An analytical method to calculate misalignment in Aerospace Abstracts data base the journal bearing of a planetary gear system [NASA-CB-163675] 881-10065 A81-10839 GIBOSTABILIZEBS GEBEBAL AVIATIOH AIBCBAF* Gyrostabilizers for inertial control systems OLGA, a gust alleviation system for improvement of Bussian book passenger comfort of general aviation aircraft A81-1202i( A81-11620 Investigation of the stalling characteristics of a general aviation aircraft H 481-11665 BABBIEB AIBCBAFT Annual review of aircraft accident data, U.S. The role of flight simulation in the design and . General aviation calendar year 1S78 development of the Sea Barrier Bav-Attack System [PB80-201916] B81-10028 481-11635 GLASS FIBEB BEIBFOBCED PLASTICS BiZABDS Fatigue damage mechanisms in composite materials - A probabilistic analysis of electrical equipment A review vulnerability to carbon fibers A81-107<(7 [NASA-TH-80217] 881-11113 Fiberglass-reinforced rigid polyurethane expedient BEAD-DC DISPLAYS pavement subject to simulated F-4 aircraft traffic Head-up displays. Ill [AD-A089266] H81-10079 481-11320 GLIDE FilBS Head up displays. Citations from the HTIS data base An analytical study of landing flare [PB80-80906U] N81-10050 [DFVLB-FB-79-40] S81-10062 BEAT TBASSFEB GBAPBITE-ECOXI COMPOSITE BA5EBIALS Adiabatic gas flow. citations from the NTIS data Design and fabrication of stabilized organic base matrix composites [PB80-8085U6] 881-100U8 A81-11338 BEAWI LIFT BELICOP1BBS Design and test of a graphite-epoxy composite A-10 Container Life Adapter-Helicopter (CLAB) slat operational prototype (preproduction) 481-11339 militarized units for flight evaluation and Development of advanced interceptor substructural operational testing material graphite epcxy missile structures [AD-4089794] H81-11034 [AD-A090127] B81-11116 BBLICOPIEB COBTBOL Fiber release from impacted graphite reinforced A method of helicopter lov airspeed estimation epoxy composites based on measurement cf control parameters [8ASA-CB-163684] H81-11117 [BBB-DD-276-79-0] A81-12094 Hicrocracking in graphite-epoxy composites Becommended short-term ATC improvements for [AD-A089894] B81-11118 helicopters. Volume 3: Operational description Compatibility of aircraft operational fluids with of experimental LOBA8-C flight following (LOFF) a graphite/epoxy composite: Development of an in the Houston area exterior coating system and remover [AD-A089385] B81-10030 [AD-A0900U9] 881-11120 Container Life Adapter-Helicopter (CL4B) Effect of service environment on composite materials operational prototype (preproduction) [AGABD-CP-288] B81-11128 militarized units for flight evaluation and Effect of various environmental conditions on operational testing polymer matrix composites [AD-A08979U] B81-11034 881-11130

A-18 SUBJECT INDEI IHPiCI CABAGE

HE1ICOPIEB DESIGH BOVEBIHG Design and tests of an helicopter rotor blade «ith Experimental and analytical studies of a model evolutive profile helicopter rotor in hover [OSEBA. IP NO. 1980-125] . A81-11638 [AD-A089780] B81-11033 Model tests for an active rotor isolation system BUNAS FACTOBS EB6ISBEBIBG [HBB-278-79-0] A81-12095 A theoretical and practical design investigation Helicopter flight characteristics improvement of the future military cockpit through swept-tip rotor blades AS 1-11631 [HBB-OD-275-79-0] 481-12097 BDBAB BBACTIOBS Oesign-to-cost applied to the AS350 helicopter Community response to noise from a general S81-11S16 aviation airport HELICOPTEB PEBFOEiAHCE 481-11821 Piloted simulation studies of helicopter agility Survey population response to airplane noise, part 1 481-10767 [NASA-IB-75790] B81-10576 Helicopter flight characteristics improveoent BIBBID COHPUTEBS through s«ept-tip rotor blades An automated procedure for developing hybrid [MBB-UD-275-79-0 ] 481-12097 computer simulations of turbofan engines Experimental and analytical studies of a model [NASA-TU-81605] H81-11688 helicopter rotor in hover BIBBID STBOC10BES £40-4089780] B81-11033 Superhybrid composite blade impact studies HELICOPTBB TAIL BOIOBS [NASA-TH-81597] M81-11412 Helicopter tail configurations to survive tail HTDBADLIC EQOIPHEST rotor loss Aircraft hydraulic systems dynamic analysis. 481-10768 Volume 6: Steady state flou analysis SSFJN BELICOPIBB IAKES computer program technical description Recomneeded short-term ATC improvements for [AD-A089240] B81-10055 helicopters. Volume 2: Becomiaended helicopter BIDBOCABBOBS ATC training material Toxicity of synthetic high density and [4D-4089111 ] 1181-10029 conventional hydrocarbon jet fuels to a soil HELICOPTEBS bacterium The aerodynamic characteristics of some ne« BAE [AD-A089527] B81-11233 blade sections, and their potential influence on HTDBOGEB FUELS rotor performance A numerical study of candidate transverse fuel A81-10769 injector configurations in the Langley scramjet Experimental application of a vibration reduction engine technique A81-10709 A81-10770 Flameholding characteristics of a swept-strut H2 The status of rotor Boise technology fuel-injector for scramjet applications A81-12737 A81-10711 Civil helicopter dire strike assessment study. Hydrogen - Its technology and implications. Volume Volume 2: Accident analysis briefs 4 - Utilization of hydrogen Book [NASA-CB-152390] H81-10019 481-11751 Recommended short-term ATC improvements for Hydrogen-fueled aircraft helicopters. Volume 2: Recommended helicopter AS 1-11753 ATC training material BIDBOGEN-BASED BBEBGI [AD-A089141] B81-10029 Hydrogen - Its technology and implications. Volume Proposed ATC system for the Gulf of Mexico: >i - Utilization of hydrogen Book Helicopter operations development program 481-11751 [AD-A089130] N81-10036 BIDBOHECHABICS Preliminary test plans of ATC concepts for longer Cost considerations of engine fuel control systems term improvement helicopter development program B81-11928 [AD-A089407] N81-10037 HIPEBSOBIC SHOCK Recommendations for short-term simulation of ATC Analysis of calculated three-dimensional inviscid concepts. Helicopter operations development flow fields Kith embedded shock naves program (presentation of a field solution) , part 1 [AD-AC89435] B81-10038 [ES4-TT-558] 1181-10017 Becommended short-term ATC improvements for BYSTEBBSIS helicopters. Volume 1: Summary of short term Hind tunnel investigation of the aerodynamic improvements hysteresis phenomenon on the F-4 aircraft and £AD-4089521] S81-10041 its effects on aircraft motion Helicopter electro-optical system display [AD-A089851] K81-11016 requirements. 1. The effects of CBT display size, system gamma function, and terrain type on pilots reguired display luminance [AD-A089755] B31-11035 IGUTIOH Erosion and impacts on composite helicopter blades Ignition of a liquid fuel B81-11138 [AD-4089295] B81-10128 Transducer installation for the Sea King UK 50 IHAGE PBOCESSI1G mathematical model validation flight tests Badar target detection and map-matching algorithm [AD-A089921] H81-11365 studies HIGB ASPECT BATIO 481-11158 Preliminary design characteristics of a subsonic Optimized computer systems for avionics applications business jet concept employing an aspect ratio [AD-A089570] B81-10063 25 strut braced ving IBAGE TUBES [HASA-CB-159361 ] B81-11013 Head up displays. Citations from the BTIS data base BIGH EBEBGI IBTEBACTIOIS [EB80-809064] B81-10050 The emulsion chamber experiment on super-sonic IHPACT D4H4SB Concorde /Echos/ Impact damage of aircraft gas turbine engines vith 481-121176 axial compressors HOlOGBAPflIC IHTEBFEBOHEtBI 481-11324 Holographic non-destructive testing of materials Belationships between impact resistance and using pulsed lasers for aircraft structures fracture toughness in advanced composite materials 481-11655 B81-11137 Holographic investigation of slender body vortex Graphite-epoxy panel compression strength uakes reduction due to local impact [AD-A089496] £81-10008 B81-11139

A-19 IHFACT BESISIASCE SUBJECT IBDEI

IBPACT BESISTAHCE IBTEBFEBOHETEBS Belationships between impact resistance and 4 simple laser interferometer for wind tunnel flow fracture toughness in advanced composite materials visualisation N81-11137 481-12078 Erosion and impacts on composite helicopter blades IBTBBGBAHDLAB COBBOSIOH B81-11138 On understanding environment-enhanced fatigue Superhybrid composite blade impact studies crack growth - A fundamental approach [MAS4-TH-81597] H81-11412 A81-10149 IMPACT TESTS IBVESTBE§TS Fiber release from impacted graphite reinforced 4 controlled evaluation of the differences tetween epoxy composites two approaches to reliability investment screening [N4S4-CE-163684] M81-11117 £40-4087506] B81-10446 Graphite-epoxy panel compression strength IBVISCID F10I reduction due to local impact Analysis of calculated three-dimensional inviscid H81-11139 flow fields with embedded shock vaves IHPEILEBS (presentation of a field solution), part 1 Comparative performance of two centrifugal fan [ES4-1T-558] B81-10017 impellers differing in blade section 481-10162 IN-FLIGHT HOBITOBIBG In-flight measurement of aerodynamic loads on JET AIBCBAFT captive stores. Eguipmect and results Preliminary design characteristics of a subsonic [HLB-BP-79013-U] ' N81-10012 business jet concept employing an aspect ratio Flight test results of the BFB 320 model following 25 strut braced wing control system for the in-flight simulation of [NASA-CB-159361] B81-11013 Airbus A 130 Fitment of TABAM standby attitude indicators to [DFVLB-BITT-79-13] 1181-10078 Macchi aircraft Aircraft turbine engine monitoring experience. An [AD-4039378] B81-11036 overview and lessons learned from selected case JET AIBCBAFT BOISE studies An experimental investigation of jet screech by [AD-A089752] H81-11042 air jet impingement on solid boundaries IUCOHBBBSSIBIE FLOI 481-11302 Design of airfoils in incompressible viscous flows Some thoughts on the effects of flight on jet by numerical optimization noise as observed in actual flight and in wind A81-10096 tunnels Flow past a slender profile in a channel with A81-11723 permeable walls Status of knowledge of sonic booms A81-10916 481-11822 Flow computation around multi-element airfoils in Aviation safety and noise abatement viscous transonic flow [GPO-50-923] B81-10578 481-11641 New interpretations of shock-associated noise with INDICATING IHSTBUflEKTS and without screech Systems analysis of the installation, mounting, [NASA-TM-81590] B81-10807 and activation of emergency locator transmitters Core noise measurements from a small, general in general aviation aircraft aviation turbofan engine [SAS4-CE-160036] M81-10020 [NASA-TB-81610] B81-11769 UDDSTBIAI EBEBGY Effect of a semi-annular thermal acoustic shield Hydrogen - Its technology and implications. Volume on jet exhaust noise 4 - Utilization of hydrogen Book [NASA-TM-81615] B81-11770 A81-11751 Cooperative investigation of the noise producing IHEBTIA FBIHCISLE region of an axisynmetric jet An exact solution of the problem of the motion of [AD-A089692] B81-11774 a gyroscope in a Cardan suspension JET EBGIHE FOE1S 481-12704 Fuel character effects on current, high pressure I8EBTIAL SAVIGATION ratio, can-type turbine combustion systems Gyrostabilizers for inertial control systems [AD-4089182] B81-10073 Bussian beck Ignition of a liquid fuel 481-12024 [AD-A089295] H81-10128 Gyrocompasses. Citations from the International Fuel jettisoning by U.S. Air force aircraft. Aerospace 4bstracts data base Volume 1: Summary and analysis [8ASA-CB-163675] K81-10065 [AE-A089010] 1181-10580 IHJDBIES Fuel jettisoning by U.S. Air Force aircraft. The accident/injury matrix - 4 tool for aircraft Volume 2: Fuel dump listings accident investigation [AD-A089076] B81-10581 481-12241 Toxicity of synthetic high density and IHLET FLOS conventional hydrocarbon jet fuels to a soil A study of the air inlet efficiency of a combat bacterium aircraft concept with dorsal inlet [AD-4089527] B81-11233 A81-11615 JET BSGIBES IHLE1 CBESSOBE Quantitative thermography in aero-engine research An evaluation of statistical methods for the and development prediction of maximum time-variant inlet total [PHB-90021] B81-10075 pressure distortion Axial flow compressors. Citations from the [AD-A089817] K81-11040 Engineering Index data base INSTBDBEBT AEPBOACH [EB80-808611] B81-10076 A piloted simulator investigation of static 4xial flow compressors. Citations from the NTIS stability and stability/control augmentation data base effects on helicopter handling qualities for [PB80-808603] B81-10441 instrument approach JET BXBAOSI [ SASA-TB-81188] B81-10077 On screeching jets exhausting from an axisymmetric INTEGBAL EQOATIOHS supersonic nozzle Calculation of plane transonic flows using the A81-11616 integral eguatlon method and shock fitting JET PIOS 481-11779 Effect of a semi-annular thermal acoustic shield IHTEGBATED CIBCDITS on jet exhaust noise High-density avionic power supply [NASA-TB-81615] B81-11770 481-11157

A-20 SUBJECT IHDEI LIFTIBG BODIES

JBT IBPIBGEBEBT LATTICES (BATHEBATICS) An experimental investigation of jet screech by Analytical estimation on nonlinear longitudinal air jet impingement on sclid boundaries characteristics of vings with small and moderate 481-11302 aspect ratio by the vortex lattice method in JET BIIIBG FlOi incompressible flov Cooperative investigation of the noise producing [ESA-TI-585] 881-10018 region of an axisymmetric jet LEADIIG EDGE FLAPS [AD-A089692] 881-11774 Leading-edge 'Vortex Flaps' for enhanced subsonic JET BOZZ1ES aerodynamics of slender wings On screeching jets exhausting from an axisymmetric A81-11648 supersonic nozzle LEADING EDGE SLATS A81-11616 Design and test of a graphite-epoxy composite A-10 JET fBOPOLSIOI slat Simulating study of the interaction between the A81-11339 propulsion and flight control systems of a LEADIHG EDGES subsonic lift fan VTOI Optimizing the fixed leading edge shape of a CBASA-TM-81239] H81-11Q143 transonic wing to suit the landing high-lift JETTISOHIBG requirements Fuel jettisoning by U.S. Air Force aircraft. A81-11644 Volume 1: Summary and analysis Simplified vortex models for slender lifting [AD-A089010] N81-10580 surfaces with leading edge separation Fuel jettisoning by O.S. Air Force aircraft. A81-11777 Volume 2: Fuel dump listings LEAST SQOABES BETBOD [AD-A089076] H81-10581 An analytical technigue for approximating unsteady JOIBtS (JOSCIIOiS) aerodynamics in the time domain Blastonters used in aeronautics industry [SASA-1B-1738] H81-11U22 [SBIAS-801-551-105] N81-10168 LIFE CICLE COSTS JOOBB1L BEABIHSS ECS integration for fuel efficient/low life cycle An analytical method to calculate misalignment in cost design Environmental Control Systems in the journal bearing of a planetary gear system aircraft A81-10839 A81-11676 An experimental and theoretical investigation of Aircraft turbine engine monitoring experience. An pressures in four-lobe bearings overview and lessons learned from selected case A81-10840 studies [AD-A0897S2] 881-11042 Design to Cost and Life Cycle Cost K [AGABD-CP-289] 881-11902 KABBAH VOBTEi STBEET Life Cycle Cost Analysis (LCCA) in military AD example of the transonic flow past a body with aircraft procurement a discontinuity in the ccntour curvature 881-11903 A81-12367 OS Army design-to-cost experience B81-11905 A review and assessment of system cost redaction activities IABIBAB BODBDAil LAIEB N81-11906 Boundary layer measurements on a two-dimensional Design to life cycle cost research •ing with flap 881-11907 [BLE-TB-79009-D] 881-10014 Evolution of techniques for LCC analysis LABIBATBS 881-11909 Predictability of moisture absorption in The Hornet program: A design to life cycle cost graphite/epoxy sandwich panels case study B81-11131 881-11910 Belationships between impact resistance and Design to cost and the F-16 multirole fighter fracture toughness in advanced composite materials 881-11911 B81-11137 Organizing a design-to-cost program LABDIBG AIDS H81-1191U Procedures to improve flight safety in Hind shear Some engineering aspects of life cycle costing conditions B81-11918 481-11666 Balanced design: Binimum cost solution Analysis of the function principle and operational 881-11919 assessment of an onboard glidepath guidance Design to cost and systems, LCC system for visual approaches (Visual Approach 881-11920 Monitor (VAH) Impact of maintainability of life cycle costs [DFVLB-PB-79-38] 881-10043 B81-11921 LABDIBG GEAS Using cost reduction concepts at Subseguent proof of damage tolerance for a landing Bessier-flispano-Bugatti gear component after numerous takeoffs and 881-11923 landings Summary of AGABE Lecture Series 100: Methodology AS 1-11475 for control of life cycle costs for avionics LABDIBG BAIS systems Fiberglass-reinforced rigid polynrethane expedient B81-11924 pavement subject to simulated F-4 aircraft traffic Summary of AGABD Lecture Series 107: The [AD-A089266] B81-10079 Application of Design to Cost and Life Cycle LABDIBG SlaOLAUOB Cost to Aircraft Engines Analysis of the function principle and operational 881-11926 assessment of an onboard glidepath guidance the roie of advanced technology of turbine engine system for visual approaches (Visual Approach life cycle cost HOBitor (TAB) B81-11927 [DFVLB-IB-79-38] B81-10043 LIFT DEVICES IASEB APPLICATION High lift research and its application to aircraft A simple laser interferometer for wind tunnel flow design visualisation A81-11612 A81-12078 LIFTIBG BODIES IATBBAL STABILITY Simplified vortex models for slender lifting Investigation of lateral forces and moments in the surfaces with leading edge separation case of asymmetric gas flows in nozzles AS 1-11777 A81-10913

A-21 LIGBT AISCH4FT SUBJECT ISDEI

LIGHT AIBCBAFT HAGNBTOBIDBODIHABICS Annoyance from light aircraft investigation Adiatatic gas flow. Citations from the NTIS data carried out around four airports near Paris base [HASA-TB-75823] M81-10577 f IB80-8085II6] B81-10048 Preliminary design characteristics of a subsonic BAIHIBBAJCB business jet concept employing an aspect ratio Polymer research in rapid runway repair materials 25 strut braced ving [AB-A089606] H81-10080 [NASA-CB-159361J H81-11013 The potential for damage from the accidental LIGBTHIHS release of conductive carbon fibers from Assessing the behavior of high modulus composite aircraft composites materials in lightning B81-11143 H81-111U1 A new method for estimating transport aircraft Lightning protection considerations for direct operating costs grapnite/epoxy aircraft structure 881-11915 N81-111U2 BAB HACBI8B SYSTEBS LIQUID FUELS Head-up displays. Ill Ignition of a liquid fuel A81-11320 [AD-A089295] N81-10128 The future cockpit of the next generation of civil LOiD TESTS aircraft Structural flight load testing, calibration and A81-11630 analysis The role of flight simulation in the design and A81-11656 development of the Sea Harrier Hav-Attack System LOGISTICS A81-11635 Container Life Adapter-Helicopter (CLAH) Initial experience with methods to evaluate flight operational prototype (preprodaction) test characteristics with operational flight militarized units for flight evaluation and maneuvers operational testing A81-11782 [AD-A089794] H81-11034 System simulation applied to the evaluation of Design to life cycle cost research displays for guidance and control N81-11907 [EFVLB-BITT-79-10] B81-10064 LOGISTICS HAHAGEHENT BiBAGEHEBT ABALTSIS An analysis of Air force management of Turbine An analysis of Air Force management of Turbine Engine Monitoring Systems (IEBS) Engine Bonitoring Systems (TENS) [AD-A089365] S81-10070 [AD-A089365] 1181-10070 LOHGITODIHAL CCHTIOL MABA6EBEST BETHODS A stability augmentation system vhich covers the Using cost reduction concepts at complete flight envelope for a F-4c aircraft Hessier-Hispano-Bugatti Hithout gain scheduling H81-11923 A81-11622 Summary of AGABD Lecture Series 100: Methodology LONGITUDINAL STABILITY for control of life cycle costs for avionics Longitudinal motion of low-flying vehicles in systems nonlinear flowfields S81-11924 A81-11626 BABAGEBEBT PLABBIBG LOB AS Air Force technical objective document FI 1981 Becommended short-term ATC improvements for [AD-A089709] N81-12010 helicopters. Volume 3: Operational description BABEOVBBABILITY of experimental LOHAN-C flight following (LOFP) Investigation of high-manoeuvrability flight in the Houston area vehicle dynamics [AD-A089385] N81-10030 A81-11625 Proposed ATC system for the Gulf of Mexico: A multivariate approach to handling gualities Helicopter operations development program rating scale development [AD-A089U30] 1181-10036 [AD-A089825] B81-11047 Preliminary test plans of ATC concepts for longer BAHUFACTOBIIG term improvement helicopter development prograa DBAPO - Computer-assisted design and manufacturing [AD-A089407] N81-10037 system LOU ASPECT B«IO A81-11610 High-lift investigations on some small aspect Cast Aluminum Structures Technology (CAST) . ratio wings Technology transfer (phase 6) A81-11643 [AD-A087492] 1181-10152 LOR ASPECT SATIO (INGS 1AF BATCHISG GOIDASCB Analytical estimation on nonlinear longitudinal Badar target detection and map-matching algorithm characteristics of wings with small and moderate studies aspect ratio by the vortex lattice method in AS 1-11158 incompressible flow BATHEBATICAL MODELS [ESA-TT-585] 1181-10018 The use of parametric cost estimating LOi COST relationships as they pertain to aircraft ECS integration for fuel efficient/low life cycle airframes: A new perspective cost design Environmental Control Systems in [AD-A089525] 881-10060 aircraft Disk residual life studies. Part 2: TF30 A81-11676 lOth-stage compressor disk (IBCOLOY 901) LOB SPEED ST1BIIIII [AD-A089524] K81-10074 A method of helicopter low airspeed estimation A method of performance prediction for centrifugal based on measurement of control parameters compressors. Eart 1: Analysis. Part 2: [MBB-UD-276-79-0] A81-12091 Comparison with experiment LOI SPEED IIBO TUHHEIS [ABC-B/B-3843] B81-10M36 Low-speed airfoil section research at Delft Predictability of moisture absorption in University of Technology graphite/epoxy sandwich panels A81-11636 B81-11131 High-lift investigations on some small aspect Transducer installation for the Sea King BK 50 ratio wings mathematical model validation flight tests A81-11643 [AD-A089924] 1181-11365 An analytical technique for approximating unsteady aerodynamics in the time domain M [NASA-IP-1738] B81-11422 •ACS BOHBBB BATBII HATBBIAI.S A fan pressure ratio correlation in terms of Bach Effect of service environment on composite materials number and Beynolds number for the Langley 0.3 [ AGABC-CP-288] B81-11128 meter transonic cryogenic tunnel [HASA-TP-1752] 1181-10005

A-22 SOBJECT IBDBI BASA EBOGBABS

Effect of various environmental conditions on Design options study. Volume 1: Executive summary polymer matrix composites user reguirements for the advanced civil 1181-11130 military aircraft MECHANICAL EHGIBBEBIBG [AB-A089536] 881-10056 An analytical method to calculate misalignment in Design options study. Volume 2: Approach and the journal bearing of a planetary gear system summary results advanced civil military A81-10839 aircraft: cost estimates BBCBABICA1 OSCIlLAIOBS [4D-4089537] 881-10057 Forced vibrations of a nonlinear system excited by Design options study. Volume 3: Qualitative a centrifugal oscillator with a sloping engine assessment advanced civil military aircraft characteristic [AD-A089538] 881-10058 A8 1-101)39 Design options study. Volume 1: Detailed MESSAGE EBOCESSIBG analyses supporting appendices advanced Formats for DIBS data link applications civil military aircraft [AD-A089963] 881-11028 [4D-A089539] 1181-10059 METAL FATIGOE life Cycle Cost Analysis (LCCA) in military On understanding environment-enhanced fatigue aircraft procurement crack growth - A fundamental approach B81-11903 481-10719 Impact of maintainability of life cycle costs Flight simulation environmental fatigue crack S81-11921 propagation in 2024-13 and 7175-T761 aluminium BJLITABI BELICOPTBBS A81-11657 Helicopter tail configurations to survive tail Flight simulation environmental fatigue crack rotor loss propagation in 2021-13 and 7175-1761 aluminum A81-10768 wing panels for transport aircraft Preliminary airworthiness evaluation 4H-1S [BLB-MP-80003-U ] 881-11415 helicopter with ogee tip shape rotor tlades SETA! BATBII COMCOSI1ES [AD-4089625] 881-10061 Superhybrid composite blade impact studies Service experience with GBC helicopter blades [B4SA-TB-81597] S81-11412 (BO-105) METAL-ME1AL BOBD1BG 881-11116 Application of veldbonding to A-10 production HILITABI TECB8010GI aircraft Bead-up displays. Ill 481-11652 481-11320 BETEOBOLOGICAL P4BAMBIEBS US Army design-to-cost experience Seduction of the take-off ground run distance to a N81-11905 given set of atnospheric condition Air Force technical objective document FY 1981 481-11631 [AD-A089709] B81-12010 MBTEOBOLOGICAL SAD4B MISALIGHMEIT Test and evaluation of the Airport Surveillance An analytical method to calculate misalignment in Badar (4SB)-8 wind shear detection system (phase the journal bearing of a planetary gear system 2), revision 481-10839 [AD-A090111] ' 1181-11290 MISSILE COBTBOL flETHOD Of CHAB4CIBBISIICS Bissile motion sensitivity to dynamic stability Review of numerical methods for the problem of the derivatives supersonic flow around bodies at angle of attack [AD-A089750] 881-11093 481-11639 MISSILE SIBDCIOBES Analytical characteristics methods: Applications Development of advanced interceptor substructural [VKI-IBEPBIBT-1980-10] N81-10011 material graphite epoxy missile structures BICBCCOBIOIBBS [AD-A090127] 881-11116 Microcomputer array processor system design BOISTOBE COSIEST for electronic warfare Predictability of moisture absorption in S81-11673 graphite/epoxy sandwich panels BICHOCB4CKS 881-11131 Hicrocracking in graphite-epoxy composites MBCA AIBCBAFT [AD-A089894] 1181-11118 Structural integration as a means of cost reduction BICBOPBOCESSOBS 881-11912 Microprocessor software applications for flight BULTIEBOCESSIBG (COHE01EBS) training simulators A six-channel quick-look unit for the aerodynamics B81-11658 division OKI airborne data acquisition package BICBOPBOGBABBIBG CAD-A089975] 1181-11361 Microprocessor software applications for flight Microcomputer array processor system design training simulators for electronic warfare 1181-11658 881-11673 BICROiAVE LAIDI1G SISIEMS BOLTIVABIATE SlAflSIICAL A1ALYSIS Kind shear detection from PCM-recorded MIS-flight Some experiences with numerical optimisation in data aircraft specification and preliminary design A81-11675 studies Contributions to the Onited Kingdom microwave A81-11609 landing system research and development program, Multivariable closed-loop analysis and flight 1971 to 1978. Volume 1 control synthesis for air-to-air tracking [BAE.-1B-79052-VOL-1 ] 881-10011 [AD-A090050] S81-11016 Contributions to the Onited Kingdom microwave 4 maltivariate approach to handling qualities landing system research and development program, rating scale development 1971 to 1978. Volume 2 [AD-A089825] 881-11017 [BAI-TB-79052-VOI-2] H81-10015 Contributions to the United Kingdom microwave landing system research and development program, N 1971 to 1978. Volume 3 BACELLBS [BAF.-TB-79052-V01-3] S81-10016 Optimum subsonic, high-angle-of-attack nacelles BIDAIB C01LISIO§S 481-11646 HASA Aviation Safety Beporting System iircraft engine nacelle fire test simulator. tBASA-TH-81225] 881-10021 Volume 1: Technical MILITABI AIBCBAFI [AD-A089629] 881-10081 A theoretical and practical design investigation BAS4 PBOSBABS of the future military cockpit 8ASA presses fighter gains long-range 481-11631 supersonic cruise aircraft A81-10575

A-23 H1TIOS»L 4»I»TIOB SISHH SUBJECT IHDEX

BATIOBA1 AVIAIION SISTBH Aviation safety and noise abatement Suinmarj of Federal Aviation Administration [GEO-50-923] B81-10578 responses to National Transportation Safety Lou-speed aerodynamic performance of Board safety recommendations 50.8-centimeter-diameter noise-suppressing CSD-A089971] S81-11022 inlets for the Quiet, Clean, Short-haul BA»IG»TIOB AIDS Experimental Engine (QCSEE) Lewis 9- by Gyrostabilizers for inertial control systems 15-foot low speed wind tunnel tests Russian bcok [SASA-TE-1178] 881-11037 A81-12024 Effect of a semi-annular thermal acoustic shield NAVIGATION IBSTBOHEHIS on jet exhaust noise Preliminary test plans of ATC concepts for longer [MASA-TH-81615] B81-11770 term improvement helicopter development program BOBDESIBOCIIVE IES1S [AD-A089407J 1181-10037 Nondestructive evaluation of composite structures NAVY A81-11654 OS Navy service experience with advanced composites Holographic non-destructive testing of materials -— in aircraft ccaposite structures using pulsed lasers for aircraft structures B81-11149 A81-11655 NBBTO»-B4BHSOB HETBOD BOBLISBAH PBOGBABMBG A comparison of Newton-like methods for the Optimum design of axial flow gas turbine stage. I transonic small disturbance equation - Formulation and analysis of optimization [AD-A090270] N81-11017 problem. II - Solution of the optimization BIGHT FLIGHTS (AIBCBAFT) problem and numerical results Helicopter electro-optical system display A81-12608 requirements. 1. The effects of CBT display BOH1IBEAB SISTERS size, system gamma function, and terrain type on Forced vibrations of a nonlinear system excited by pilots required display luminance a centrifugal oscillator with a sloping engine [AD-A089755J H81-11035 characteristic BIGHT ?ISIOB A81-10439 Helicopter electro-optical system display Analytical estimation on nonlinear longitudinal . requirements. 1. The effects of CBT display characteristics of wings with small and moderate size, system gamma function, and terrain type on aspect ratio by the vortex lattice method in pilots required display luminance incompressible flow [AD-A089755] B81-11035 [ESA-TT-585] 881-10018 BITBOGEB BOHLIBBABITS A system for model access in tunnels with an Estimation of wing nonlinear aerodynamic unbreathable test medium characteristics at supersonic speeds A81-11672 [BASA-TJ-1718] 881-10004 SITBOSEH OXIDES HOZXLE FLO! Variable geometry, lean, premized, prevaporized Investigation of lateral forces and moments in the fuel combustor conceptual design study case of asymmetric gas flows in nozzles [ASME PAPEB 80-G1-16] A81-12609 A81-10913 BOISE GESEBATOBS An experimental investigation of jet screech by Experiments on effective source locations and air jet impingement on solid boundaries velocity dependence of the broad band noise from A81-11302 a rotating rod Calibration of the high speed wind tunnel TVfl 150 A81-11724 in the supersonic range Status of knowledge of sonic booms A81-11778 A81-11822 Adiatatic gas flow. Citations from the NTIS data The status of rotor noise technology base A81-12737 [FB80-808546] 881-10048 Cooperative investigation of the noise producing BOZZLE GEOflETBI region of an axisymmetric jet Cooperative investigation of the noise producing [AD-A089692] N81-11774 region of an axisymmetric jet BOISE IHTEBSITI [AD-A089692] 881-11774 Community response to noise from a general 8DCIEAB EHDISIOIS aviation airport The emulsion chamber experiment on super-sonic A81-11621 Concorde /Echos/ BOISE BE1SOHEB.EBI A81-12476 Core noise measurements from a small, general HDC1BAB ISTEBACTIOBS aviation turbofan engine The emulsion chamber experiment on super-sonic [NASA-TH-81610] N81-11769 Concorde /Echos/ BOISE POIiOTIOB A81-12476 Community response to noise from a general BOBEBICAL ABALJSIS aviation airport A comparison of Newton-like methods for the A81-11821 transonic small disturbance equation Survey population response to airplane noise, part 1 [AD-A090270] B81-11017 [NASA-TH-75790] B81-10576 BUBEBICAL COBTBOL Annoyance from light aircraft investigation Computerized flight management for fuel saving carried out around four airports near Earis A81-12349 [NASA-TH-75823] N81-10577 BOBEBICAX FLOI tlSDALIZAtlOB BOISE EBBDICTIOS (AIECBAFT) Engine air intake design support by use of Some thoughts on the effects of flight on jet computational methods and comparison of noise as observed in actual flight and in wind theoretically derived pressure distributions tunnels with experimental data A81-11723 S81-11614 The status of rotor noise technology Eesearch on transonic wings at the National A81-12737 Aerospace Laboratory, Japan Weapon bay cavity noise environments, data A81-11640 correlation and prediction for the B-1 aircraft [AD-A089770] N81-11778 BOISE BECOCTIOH Acoustic structures titanium brazing method OBLIQUE SHOCK BATES for producing honeycomb structures for jet An experimental investigation of the interaction engine noise reduction between a glancing shock wave and a turbulent A81-10272 boundary layer Boise control design problems on air cushion A81-11649 vehicles and surface effect ships A81-11818 SOBJECT IIOBZ PITCHING BOBEIIS

OHEGA BAVIGAIIOB STSIEB PASSBBGEB AIBCBAFt Proposed ATC systei for the Gulf of fiexico: The relevance of the Flex-Hub Prop-Fan for Helicopter operations development program fuel-efficient airliners [AD-A089430] B81-10036 A81-11605 OiBOABD BQOIPBBBT OLGA, a gust alleviation system for improvement of Bead up displays. Citations from the passenger comfort of general aviation aircraft International Aerospace Abstracts data tase A81-11620 [NASA-CB-163656] 881-10019 EAVEHBB1S Fuel jettisoning by D.S. Air Force aircraft. Airfield pavement demonstration-validation study Volume 2: Fuel dump listings A81-10718 [AD-A089076] 881-10581 Fiberglass-reinforced rigid polyurethane expedient OPBBATIOBAL HAZ1BDS pavement subject to simulated F-1 aircraft traffic Exploratory study of hazard mitigation and [AD-A089266] 881-10079 research in the air transport system Airfield pavement evaluation. Citations frcm the [AD-A089204] 881-11021 BUS data tase OPBBATIOBS BBSEABCB [EB80-812860] 881-10083 Becomoended short-term ATC improvements for PEBFOBBAiCE SBBDICIIOB helicopters. Volume 1: Summary of short term A method of performance prediction for centrifugal improvements compressors. Part 1: Analysis. Part 2: [AD-A089521] H81-10011 Comparison vith experiment Aa analysis of Air Force management of Turbine [ABC-B/B-3813] 881-10136 Engine Bonitoring Systems (TEMS) Definitive generic study for the effect of high [AD-A089365] B81-10070 lift aixfoils on wind turbine effectiveness, OPEBAIOB PEBFOBBABCE executive summary Sew terminal radar approach control in toner can [SEBI/1B-98003-2] 881-11192 concept for Love Field, Dallas, Texas PBBFOBBAHCB ItSIS [AD-A089996] H81-11025 Comparative performance of two centrifugal fan OPTIBAL CO1I10L impellers differing in Hade section Improved flight control performance and failure AS 1-10162 tolerance using modern control technigues Airfield pavement demonstration-validation study A81-11619 A81-10718 Aircraft performance optimization by forced Bodel tests for an active rotor isolation system singular perturbation [HBB-278-79-0] A8T-12095 A81-11667 Performance of a steel spar wind turbine blade on Bultivariable closed-loop analysis and flight the Bod-0 100 kR experimental vind turbine control synthesis for air-to-air tracking [HASA-Tfl-81588] 881-11118 [AD-A090050] 881-11016 PEBIODIC ?ABJATIOBS OPTIBIXAHOfl Improved aircraft cruise by periodic control Design of airfoils in incompressible viscous flovs 881-11030 by numerical optimization PEBTUBBATIOI THBOBI A81-10096 Aircraft performance optinization by forced Some experiences with numerical optimisation in singular perturbation aircraft specification and preliminary design A81-11667 studies Analytical characteristics methods: Applications A81-11609 [VKI-PBEPBIKT-1980-10] 881-10011 Structural optimization of advanced aircraft PHOT06BAPBIC EQOUBEII structures Aerial survey photography A81-11651 A81-12350 Optimal flight vehicle design and linear vector PHOTOBAPPIIG spaces Aerial survey photography A81-11668 A81-12350 Optimum design of axial flov gas turbine stage. I PILOT EBBOB - Formulation and analysis of optimization Civil helicopter wire strike assessment study. problem. II - Solution of the optimization Volume 2: Accident analysis briefs problem and numerical results [UASA-CB-152390] S81-10019 A81-12608 PILOT PBBFOBBAJCB OSCIltATIOBS Pilot-aircraft systei reponse to Hind shear An introduction to dynamic derivatives (3) methods [SASA-CB-3312] 1181-10636 of oscillating models in pitch and yaw in a 530 A multivariate approach to handling qualities by 810 millimetre transonic Hind tunnel rating scale development [ABl/AEEO-BOTE-390] B81-10007 [AD-A089825] 881-11047 OZOBOSPHEBB PILOTLESS AIBCBAFI The aircraft in the stratosphere effects on Gyrostabilizers for inertial control systems ozone layer egnilibrinm Russian book A8i-ioi99 481-12021 PIPELIBBS Alternative energy sources for non-highway transportation, volume 1 PACKIIG DEBSHY [DOE/CS-05438/T1-VOL-1] B81-11513 High-density avionic power supply PIPES (IOBBS) A81-11157 Elastomers used in aeronautics industry PADS APPBOIIBATIOB [SBIAS-801-551-105] 881-10168 An analytical technique for approximating unsteady PIS10B EI6IIES aerodynamics in the time domain Comparisons of four alternative poverplant types [HASA-TP-1738] B81-11122 for future general aviation aircraft PABELS [BASA-TH-815811] B81-10067 Design and fabrication of stabilized organic PITCHIB6 BOBEIIS matrix composites An introduction to dynamic derivatives (3) methods A81-11338 of oscillating models in pitch and yaw in a 530 PABABOLIC BODIES by 810 millimetre transonic vind tunnel A comparison of 8evton-like methods for the CABL/AEBO-BOTE-390] 881-10007 transonic small disturbance eguation A piloted simulator investigation of static [AD-A090270] H81-11017 stability and stability/control augmentation PiBABETEB IDEITIFICAIIOB effects on helicopter handling gualities for Simulating study of the interaction between the instrument approach propulsion and flight control systems of a [BASA-TB-81188] B81-10077 subsonic lift fan VTOL [BASA-TB-81239] 881-11013

A-25 POLIUTIOB COHtBOl SUBJECT IHDEX

POLIOTIOB COHTBOL fIBOTECHHICS Variable geometry, lean, premixed, prevaporized Applications of pyrotechnigues in aviation fuel combustor conceptual design study [SNIAS-792-422-103] 1181-10025 [ASNE PAPEB 80-G1-16] 481-12609 POLYOBETBiBE F04H Fiberglass-reinforced rigid polyurethane expedient Q pavement subject to simulated F-4 aircraft traffic QD4I1II COBTBOI [AD-4089266] H81-10079 Bondestructive evaluation of composite structures POTES1IAL FLOS 481-11651 Flow past a slender profile in a channel Kith QUIET EB6IKB PBOGBAS permeable walls Low-speed aerodynamic performance of 481-10916 50.8-centimeter-diameter noise-suppressing POIEB COBDITIOBIBG inlets for the Quiet, Clean, Short-haul High-density avionic power supply Experimental Engine (QCSEE) Lewis 9- by 481-11157 15-foot low speed wind tunnel tests PBEDICTIOB ABALJSIS TECBBIQOES [HASA-TP-1178] B81-11037 Prediction of changes in aircraft noise exposure 481-11620 An evaluation of statistical methods for the prediction of maximum time-variant inlet total B4D4B BEACOBS pressure distortion The Discrete Address Beacon System/Air Traffic [40-4089817] N81-11040 Control Badar Beacon System/AlCBBS IFF Hark 12 PBESSOBE DISIBIBOIIOH system (DABS/ATCRBS/AIHS) performance prediction Engine air intake design support by use of model ; computational methods and comparison of [4D-4089440] S81-10031 theoretically derived pressure distributions Impact of the discrete Address Beacon System with experimental data (DABS) on Air Traffic Control Badar Beacon 481-11611 System (ATCBBS) performance in selected An investigation of scale effects on the transonic deployments flow over swept wings. Part 2: Measurements on [AD-A089611] N81-10039 a model of a variable-sweep strike-fighter BADAB DETECT108 configuration Badar target detection and map-matching algorithm [ABC-B/B-3842-PT-2] 1181-10010 studies Comparison of unsteady Pressure Fields Computed A81-11158 and Measured on the ZKP model BADAB EflOIPBEBT [AGAED-B-688] B81-11019 Optimized computer systems for avionics applications PBESSOBB HIASOBEBEHTS CAD-A089570] N81-10063 An experimental and theoretical investigation of BADAB BAPS pressures in four-lobe bearings Radar target detection and map-matching algorithm 481-10840 studies PBESSOBE BAUD AS 1-11158 Fuel character effects on current, high pressure BADAB NAVIGATJOI ratio, can-type turbine combustion systems Proposed 4IC system for the Gulf of Hexico: [AD-A089182] 1181-10073 Helicopter operations development program PBOCDBEMEBT H4BAGEHEBT [AD-A089430] H81-10036 Design to cost and systems, ICC BADABSCOPES N81-11920 Proceedings of the 1979 Seminar on Air Traffic PBODUCIICB EBG1BEEBIBG Control. Terminal Badar Approach Control Seduction of energy consumption in the vibrational (TB4CON) facility supervisory desk complex shot peening of axial compressor vanes [AE-A089911] S81-11024 AS 1-11321 BADIABT BElTIIfi OS Army design-to-cost experience Ignition of a liquid fuel B81-11905 [AD-4089295] B81-10128 PBODOCT10B P1ABBIBG BADIATIOS PYBOHETEBS 4 review and assessment of system cost reduction Surface pyrometry in presence of radiation from activities other sources with application to turbine blade H81-11906 temperature measurement Design to life cycle cost research [NASA-IP-1751] N81-11039 N81-11907 BADIO AJIESBAS Organizing a design-to-cost program Excitation of a circular array of cylinders with S81-1191U longitudinal slits in radio antennas PEOPELLEB JABS 481-12619 The relevance of the Flex-Hub Prop-Fan for BADIO BgOIPBEBT fuel-efficient airliners Preliminary test plans of 4TC concepts for longer 481-11605 term improvement helicopter development program PBOPOLSIOB SJSTE1I COBFIGOBAIIOHS [AD-4089107] 881-10037 Bibliography on aerodynamics of airframe/engine BAIL TBASSPOBIATIOB integration of high-speed turbine-powered Alternative energy sources for non-highway aircraft, volume 1 transportation, appendices [NASA-TH-81814] H81-11032 [DOE/CS-05438/T1-VOI-3] N81-11500 Simulating study of the interaction between the BAHGE SAFBTX propulsion and flight control systems of a Flight termination receiver/decoders design, subsonic lift fan VIOL performance and certification [NASA-TM-81239] N81-11043 [AD-4089746] 1181-11045 PStCBOACODSTICS BE1L TIDE OPEBATIOB Survey population response to airplane noise, part 1 ATABS implementation tradeoff [NASA-TH-75790] H81-10576 [AD-A089977] N81-11026 POISE CODE HODD1ATIOB BBCOSiAISSABCB AIBCB4FT iind shear detection from pea-recorded Hls-flight Maritime patrol aircraft engine study. General data Electric derivative engines. Volume 2: A81-11675 Appendix A. Performance data - GE27/T3 study al POISED L4SEBS turboprop Holographic non-destructive testing of materials [AD-&089336] H81-10068 using pulsed lasers for aircraft structures Haritime patrol aircraft engine study. General A81-11655 Electric derivative engines. Volume 3: PDflP IHPELLEBS Appendix B. Performance data - TF34/T7 study A1 Inlet flow in centrifugal pumps at partial turboprop deliveries [AD-A089279] H81-10069 [ VKI-PBEPBINT-1979-16] H81-10137

A-26 SUBJECT IBDBI BOTOB BLADES (TOBBOHACHIIEBI)

BECOHDIBG IHSTBOHEBIS BOLLIHG HOBEIfS Hind shear detection from Ecu-recorded MLS-flight A piloted simulator investigation of static data stability and stability/control augmentation A81-11675 effects on helicopter handling qualities for Quantitative thermograph; in aero-engine research instrument approach and development CNASA-1H-81188] 881-10077 [PBB-90021] B81-10075 B01ABI SIBOSCOPES BEDOCTIOB An exact solution of the problem of the motion of Design to cost and the F-16 mnltirole fighter a gyroscope in a Cardan suspension 881-11911 A81-12704 BEDUIDABCI BOTABI STABILITY. Detecting the failure of aircraft sensors using Finite element analysis of natural and forced analytical redundancy flexural vibrations of rotor systems B81-11270 A81-11956 BEDOBDABCI BBCODIBG BOTABI ilBG AIBCBAFT Computer based in-flight monitoring Engineering and development program plan aircraft 1181-11269 crashworthiness Flight experience with flight control redundancy [AD-A089131] B81-10022 management A piloted simulator investigation of static B81-11274 stability and stability/control augmentation Eobust control system design effects on helicopter handling gualities for 881-11275 instrument approach BEIHFOBC1D PLASTICS [BASA-IS-81188] B81-10077 Development of the 4300 fin in modern composite BOIABI IISGS fibre construction The aerodynamic characteristics of sone new B4E A81-11653 blade sections, and their potential influence on BEIHFOBCIBG FIBEBS rotor performance Development of the A300 fin in modern composite A81-10769 fibre construction Design and tests of an helicopter rotor blade with A81-11653 evolutive profile BEtlABJLII! ANALYSIS [OBEBA, 11 BO. 1980-125] A81-11638 Beliability and engineering-economic A method of helicopter low airspeed estimation characteristics of aircraft engines --- Bussian based on measurement of control parameters book [BBB-OD-276-79-0] A81-12094 A81-10045 Model tests for an active rotor isolation system BELIABILITI EHGIBBBBIBG [flBB-278-79-0] A81-12095 Beliatility-centered maintenance The status of rotor noise technology H81-11917 A81-12737 BESCUE OPEB4TIOBS Civil helicopter wire strike assessment study. Systems analysis of the installation, mounting, Volume 2: Accident analysis briefs and activation of emergency locator transmitters ISiSA-CB-152390] 881-10019 in general aviation aircraft Preliminary airworthiness evaluation AB-1S [BASA-CB-160036J 881-10020 helicopter with ogee tip shape rotor blades Search and rescue methods and equipment. A [AD-A089625] B81-10061 bibliography with abstracts Full scale wind tunnel investigation of a [PB80-812837] 881-10026 bearingless main helicopter rotor Ames 40 by BESBABCH AIBCBAFT 80 foot wind tunnel test using the BO-105 Hydrogen-fueled aircraft helicopter A81-11753 [KASA-CB-152373] N81-11014 BESEABCB ABO DEVELOPHBIT Experimental and analytical studies of a model Contributions to the Dnited Kingdom microwave helicopter rotor in hover landing system research and development program, [AD-A089780] 881-11033 1971 to 1978. Volume 1 Erosion and impacts on composite helicopter tlades [BAE-TB-79052-V01-1] 881-10044 B81-11138 Contributions to the Dnited Kingdom microwave Fatigue and damage propagation in composite rotor landing system research and development program, blades 1971 to 1978. Volume 2 B81-1T145 [BAE-TR-79052-VOI-2] S81-10045 Service experience with GBC helicopter blades Contributions to the Dnited Kingdom microwave (BO-105) landing system research and development program, N81-11146 1971 to 1978. Volume 3 BOTATIHG CILIHDEBS [BAE-TB-79052-VOI-3J N81-100U6 Experiments on effective source locations and BESIDBHTIAL ABEAS velocity dependence of the broad band noise fron Community response to noise from a general a rotating rod aviation airport A81-11724 A81-11821 BO1OB AEBODIIABXCS BBSII HATBIX COBEOSIIES An experimental and theoretical investigation of Fatigue strength of CFBP under combined pressures in four-lobe bearings flight-by-flight loading and flight-by-flight 481-10840 temperature changes Experimental and analytical studies of a model helicopter rotor in hover Superhybrid composite blade impact studies [AD-A089780] H81-11033 [BASA-TH-81597] B81-11412 BOTOB BLADES BBIBOLDS IOBBEB Helicopter flight characteristics improvement A fan pressure ratio correlation in terms of Bach through swept-tip rotor blades Dumber and Beynolds number for the langley 0.3 [HBB-DD-275-79-0] A81-12097 meter transonic cryogenic tunnel BOTOB BLADES (IOHBOBACHIBEBT) [BASA-TP-1752] 881-10005 Comparative performance of two centrifugal fan The principles and applications of cryogenic wind impellers differing in blade section tunnels A81-10162 B81-11049 Discrete frequency noise due to irregularity in BIGID B010BS blade row of axial fan rotor An exact solution of the problem of the lotion of A81-10633 a gyroscope in a Cardan suspension Preliminary airworthiness evaluation AH-1S A81-12704 helicopter with ogee tip shape rotor blades BIGID STBOCTOBES [AD-A089625] 881-10061 Design and fabrication of stabilized organic Fatigue and damage propagation in composite rotor matrix composites blades A81-11338 881-11145

A-27 E01OBS SUBJECT IHDEI

£01085 OS Bavy service experience with advanced composites The vibration of a multi-bearing rotor in aircraft composite structures 481-11722 1181-11119 Finite element analysis of natural and forced SBALE Oil flexural vibrations of rotor systems Alternative energy sources for non-highway 481-11956 transportation, volume 1 Performance of a steel spar wind turbine blade on [ DOE/CS-05438/T1-VOL-1J 881-11513 the Bod-0 100 kR experimental wind turbine SHIPS [HASA-TB-81588] B81-11M8 Alternative energy sources for non-highway BOB! LASF.BS transportation, appendices Holographic non-destructive testing of materials [DOE/CS-05438/T1-VOL-3] 881-11500 using pulsed lasers for aircraft structures SHOCK IATE IBTEBACTIOB 481-11655 An experimental investigation of the interaction BDH8AIS between a glancing shock wave and a turbulent Analysis of potentially correctable landing delays boundary layer at Atlanta A81-11649 [AD-AC89408] 1181-10032 SHOCK IAVE PEOFILES Polymer research in rapid runway repair materials Calculation of plane transonic flows using the [AD-A089606] 881-10080 integral equation method and shock fitting Airfield pavement evaluation. Citations from the AB1-11779 Nils data base SHOCK IAVES [PB80-812860 ] B81-10083 Mew interpretations of shock-associated noise with and without screech [BAS4-TB-81590] 1181-10807 SHOBI HADl AXBCBAFT SAAB 37 AISC1AFI Low-speed aerodynamic performance of Failure management for the SAAB Viggen JA37 aircraft 50.8-centimeter-dianeter noise-suppressing N81-11273 inlets for the Quiet, Clean, Short-haul SAFETI DEVICES Experimental Engine (QCSEE) Lewis 9- by Summary of Federal Aviation Administration 15-foot low speed wind tunnel tests responses to National Transportation Safety [BASA-TP-1178] B81-11037 Board safety recommendations SHOBT TiBEOFF AIBCBAFT [AD-A089971] 881-11022 Optimum subsonic, high-angle-of-attack nacelles SAFEII FACTORS 481-11646 Search and rescue methods and equipment. A Flight evaluation of stabilization and command bibliography vith abstracts augmentation system concepts and cockpit [PB80-812837] N81-10026 displays during approach and landing of SAFETY HABAGEBEBT powered-lift STOL aircraft The accident/injury matrix - A tool for aircraft [BASA-TP-1551] . 881-11044 accident investigation SHOT PEE1IBG A81-12241 Eeduction of energy consumption in the vibrational SAHDilCB SIBDCTOEES shot peening of axial compressor vanes Predictability of moisture absorption in 481-11321 graphite/epoxy sanduich panels SI6HAL DETBCTOBS N81-11131 Systems analysis of the installation, mounting, SCALE EFFECT and activation of emergency locator transmitters An investigation of scale effects on the transonic in general aviation aircraft flow over svept wings. Part 2: Measurements on [BASA-CB-160036] B81-10020 a model of a variable-sweep strike-fighter SIGNAL PBOCBSSI1G configuration Optimized computer systems for avionics applications [ABC-B/M-3842-PT-2] 881-10010 [AD-A089570] 881-10063 SCALISG LAIS SIBOLATIOB A fan pressure ratio correlation in terms of Bach Flight test results of the HFB 320 model following number and Reynolds number for the Langley 0.3 control system for the in-flight simulation of meter transonic cryogenic tunnel Airbus A 130 [BASA-TP-1752] H81-10005 [DFVLH-BITT-79-13] B81-10078 SCHLIEBEB PHOTOGBAPHJ SKIB FEICTIOS A simple laser interferometer for wind tunnel flow Local properties of three-dimensional separation visualisation lines in vortex layers 481-12078 [DGLB PAPEB 79-063] 481-11780 SEABCB BAOAB SLEBDEB BODIES Search and rescue methods and equipment. A Two methods for calculating the load on the bibliography with abstracts surface of a slender body executing axisymnetric [PB80-812837] B81-10026 vibrations in a sonic gas flow SEABCBIBG 481-10920 Systems analysis of the installation, mounting, Holographic investigation of slender body vortex and activation of emergency locator transmitters wakes in general aviation aircraft [AD-A089496] B81-10008 [BASA-CB-160036] B81-10020 SLEBDEB HUBS SENSITIVITY Flow past a slender profile in a channel with Bissile motion sensitivity to dynamic stability permeable walls derivatives 481-10916 [AD-A089750] B81-11093 Leading-edge 'Vortex Flaps' for enhanced subsonic SBPABATEO FLOS aerodynamics of slender wings Simplified vortex models for slender lifting A81-11648 surfaces with leading edge separation Simplified vortex models for slender lifting A81-11777 surfaces vith leading edge separation Local properties of three-dimensional separation A81-11777 lines in vortex layers Preliminary design characteristics of a subsonic [DG1B PAEEE 79-063] A81-11780 business jet concept employing an aspect ratio Calculation of separated viscous flows on wing 25 strut braced wing profiles by a coupling approach [BASA-CB-159361] 881-11013 [OBEBA, TP NO. 1980-122] A81-11920 SLOT AHTEBiAS SB1VICE LIFE Excitation of a circular array of cylinders with Operational durability of airfraae structures longitudinal slits in radio antennas A81-11662 A81-12619 Service experience with GBC helicopter blades (BO-105) B81-11146

A-28 SUBJECT ISDEI SOPBBSOBIC AIBCBAFT

SLOBBI PBOPBLLABTS STBOCTOBAl AIAHSIS Compound Cycle Tucbofan Engine (CCTE) . Task 9: Design options study. Volume 4: Detailed Carbon-Slurry Fuel Combustion Evaluation Program analyses supporting appendices advanced [AD-A089451] B81-10072 civil military aircraft SHAH PBBTOBBATIOB FL01 [AD-A089539] H81-10059 A comprehensive evaluation and analysis of STBOCTOBAl DBSIGI transonic flow calculations on three related Airfield pavement demonstration-validation study wing-body configurations A81-10718 [FFA-TH-AO-1418-PT-1] B81-10013 Atlanta's new central passenger terminal complex SO LIE SOBFACBS A81-10719 Two methods for calculating the load on the Design and fabrication of stabilized organic surface of a slender body executing azisymaetric matrix composites vibrations in a sonic gas flow A81-11338 A81-10920 Design and test of a graphite-epoxy composite A-10 An experimental investigation of jet screech by slat air jet impingement on solid boundaries A81-11339 A81-11302 Structural optimization of advanced aircraft SOLVBIIS structures Compatibility of aircraft operational fluids with A81-11651 a giaphite/epoij composite: Development of an Cast Aluminum Structures Technology (CAST). exterior coating system and remover Technology transfer (phase 6) [AD-A090049J H81-11120 [AD-A087492] 1181-10152 SOHIC BOOBS STBDCTDBAL DBSI6I CBITEBIA Status of knowledge of sonic boons Operational durability of airfraoe structures A81-11C22 A81-11662 SOOHD PBESSDBB Exploratory study of hazard mitigation and New interpretations of shock-associated noise vith research in the air transport system and without screech [AD-A089204] H81-11021 [HASA-TH-81590] B81-10807 STBOCTOBAL BIGIBEBBISG SPACECBAH IIStBOBEBTS Structural integration as a means of cost reduction Gyrocompasses. Citations from the International 881-11912 Aerospace Abstracts data base SIBOCTOBAL FAIltJHE [HASA-CB-163675] H81-10065 The analysis of fatigue failures STABILITI AOGHEBTATIOS A81-11603 A stability augmentation system which covers the Lightning protection considerations for complete flight envelope for a F-4c aircraft graphite/epoxy aircraft structure without gain scheduling H81-11142 A81-11622 STBOCTOBAL BE1IABILITI STABILIZED CLAIFOBHS Part-through crack problems in aircraft structures Gyrostabilizers for inertial control systems A81-10362 Bussian book Subseguent proof of damage tolerance for a landing A81-12024 gear component after numerous takeoffs and STATIC LOADS landings Cast Aluminum Structures Technology (CAST). A81-11475 Technology transfer (phase 6) STBOCTOBAL SIBAIi [AD-A087492] N81-10152 Fatigue damage mechanisms in composite materials - Graphite-epoxy panel compression strength A review reduction due to local impact A81-10747 H81-11139 STRUCTURAL VIBB&tlOH STATIC PBESSDBB Two methods for calculating the load on the An experimental and theoretical investigation of surface of a slender body executing axisymmetric pressures in four-lobe bearings vibrations in a sonic gas flow A81-108I40 A81-10920 STATISTICAL ASALYSIS STBOCTOBAL iEIGBT An evaluation of statistical methods for the Height optimization of wing structures according prediction of maximum time-variant inlet total to the gradient method pressure distortion 481-11650 [AC-A089817] H81-11040 STBOTS A probabilistic analysis of electrical eguipment Preliminary design characteristics of a subsonic vulnerability to carbon fibers business jet concept employing an aspect ratio [SASA-TB-80217] H81-11113 25 strut braced wing STATOB BLADES [HASA-CB-159361] 1181-11013 Off-design performance loss model for radial SOBSO«IC FLOI turbines with pivoting, variable-area stators Asymmetric flow of subsonic and sonic jets over an [HASA-TP-1708] 881-11038 infinite wedge STBABES A81-10919 Flow measurements in the wake of a wing fitted The aerodynamics of pure subsonic flow /4th with a leading-edge root extension (strake) revised edition/ German book [BAE-TB-79120J H81-10015 A81-11441 STRAPDOiB IHBBTIAL GUICiBCB Theoretical determination of subsonic oscillatory Gyrocompasses. Citations from the International airforce coefficients for fin-tailplane Aerospace Abstracts data base configurations [HASA-CB-163675] K81-10065 (BAE-TB-79125] 881-10016 STBATOSPBEBB SOBSOHIC HIBD TQIIBLS The aircraft in the stratosphere effects on Three years of operation of the OHEBA pressurized ozone layer egnilibrinn subsonic wind tunnel A81-10499 [OBEBA, TP HO. 1980-129) A81-11669 SXBESS ABALYSIS SOPEBCBITICAL HISS A practical method for predicting flight-by-flight Comparison of Unsteady Pressure Fields Computed crack growth in fighter type aircraft for damage and Beasured on the ZKP model tolerance assessment [AGABD-B-688] 1181-11019 A81-116S9 SOPEBSOBIC AIBCBAFT SIBESS COBBOSIOB CBACKIHG Bew concepts for design of fully-optimized On understanding environment-enhanced fatigue configurations for future supersonic aircraft crack growth - A fundamental approach 481-11606 A81-10749 Optimizing the fixed leading edge shape of a Flight simulation environmental fatigue crack transonic wing to suit the landing high-lift propagation in 2021-T3 and 7475-1761 aluminium reguirements A81-11657 A81-11644

A-29 SOPEHSOBIC COBBOSIIOB BABJF.T EBGIBES SUBJECT IBDBX

Status of knowledge of sonic boons The role of flight simulation in the design and A81-11822 development of the Sea Harrier Nav-Attack System SOPEBSONIC CCBBDSTIOH B1HJET EHGINES A81-11635 A numerical study of candidate transverse fuel Evolution of technigues for LCC analysis injector configurations in the Langley scramjet 881-11909 engine The Hornet program: A design to life cycle cost A81-10709 case study Flameholding characteristics of a swept-strut H2 081-11910 fuel-injector for scramjet applications Design to cost and the F-16 mnltirole fighter A81-10711 881-11911 SDPEBSOBIC CBOISE AIBCBiFT BESEABCB Some engineering aspects of life cycle costing NASA presses fighter gains long-range H81-11918 supersonic cruise aircraft SISTEHS BABAGBflBIT A81-10575 An analysis of Air Force management of Turbine SDPEBSOBIC FLIGHT Engine Honitoring Systems (TEHS) The emulsion chamber experiment on super-sonic [AD-A089365] H81-10070 Concorde /Echos/ A81-12476 SDPEBSOHIC FI01 Investigation of lateral forces and moments in the TABLES (DAIA) case of asymmetric gas fleas in nozzles Annual review of aircraft accident data, U.S. A81-10913 General aviation calendar year 1978 Beview of numerical methods for the problem of the CPB80-201916] B81-10028 supersonic flow around bodies at angle of attack TAIL BOIOBS A81-11639 Fatigue and damage propagation in composite rotor Analytical characteristics methods: Applications blades [TKI-BEEPHIKT-1980-10] H81-10011 N81-11U5 SDPEBSOHIC BOZZLES Service experience with GEC helicopter blades On screeching jets exhausting from an axisyumetric (BO-105) supersonic nozzle B81-11146 A81-11616 TAIL SOBFACES SOPBBSOBIC SPEEDS Theoretical determination of subsonic oscillatory Estimation of wing nonlinear aerodynamic airforce coefficients for fin-tailplane characteristics at supersonic speeds configurations [NASA-TJ-1718] N81-10004 [BAE-TB-79125] S81-10016 SOPEBSOBIC TBANSPOBIS TAKEOFF The aircraft in the stratosphere effects on Airport activity statistics of certificated route ozone layer equilibrium air carriers, calendar year 1979 A81-10499 [AE-A089748] S81-11023 SDPEBSOBIC HDD TUNNELS TAKEOFF BDIS Calibration of the high speed wind tunnel TVH 150 fieduction of the take-off ground run distance to a in the supersonic range given set of atmospheric condition A81-11778 A81-11634 SOPPBESSOBS TABES (COB1AI1EBS) Active flutter suppression design and test - A Elastomers used in aeronautics industry joint U.S.-F.B.G. program [SNIAS-801-551-105] H81-10168 A81-11621 TABGET BECOGBITIOH SOBFACE EJFECI SHIPS Badar target detection and map-matching algorithm Noise control design problems on air cushion studies vehicles and surface effect ships A81-11158 A81-11818 TECHBOLOGICAL FOiECASTIHG SOBFACE FINISHING NASA presses fighter gains long-range Compatibility of aircraft operational fluids with supersonic cruise aircraft a graphite/epoxy composite: Development of an A81-10575 exterior coating system and remover New concepts for design of fully-optimized [AD-A090049] N81-11120 configurations for future supersonic aircraft SDBFACE BAVIGATION A81-11606 Search and rescue methods and equipment. A The all-electric aircraft bibliography with abstracts A81-11617 [EB80-812837] H81-10026 Flying qualities criteria for advanced control SOBVEILLANCE BADAB technology transports Hew terminal radar approach control in tower cab 181-11618 concept for Love Field, Dallas, Texas The.future cockpit of the next generation of civil [AD-A089996] N81-11025 aircraft Test and evaluation of the Airport Surveillance A81-11630 Badar (ASB)-8 wind shear detection system (phase Air Force technical objective document FY 1981 2), revision [AD-A089709] . B81-12010 [AD-A090111] N81-11290 TECHNOLOei ASSBSSHEBT I SOBVEIS New BBC high-efficiency gas turbines Survey population response to airplane noise, part 1 481-11797 £NASA-TS-75790] H81-10576 Comparisons of four alternative powerplant types SHEET FOB1ABD RINGS for future general aviation aircraft Bow to improve the performance of transport [BASA-TH-81584] B81-10067 aircraft by variation of wing aspect-ratio and The role of advanced technology of turbine engine twist /12th Daniel and Florence Guggenheim life cycle cost International Memorial Lecture/ S81-11927 A81-11602 TECBBOLOGY OTILIZATIOS SIIIHETIC FOELS Advanced fuel system technology for utilizing Toxicity of synthetic high density and broadened property aircraft fuels conventicnal hydrocarbon jet fuels to a soil A81-11612 bacterium Airbus Industrie's heavenly twins - A310 and [AD-A089527] H81-11233 A3QO-600 Alternative energy sources for non-highway A81-12348 transportation, volume 1 TEHFBBATDBB COBTBOL [DOE/CS-05438/T1-VOL-1} N81-11513 The control of pressure, temperature and Hach SISTEKS EKGIIEEBING number in a blowdown-to-atmosphere cryogenic The design of blowing-cooled aircraft electrical wind tunnel machines N81-11063 A81-10171

4-30 SUBJECT IBDEI TBAHSPOBT AIBCBAFI

TEBPEHATDBE BB1SDBIBG IHS1BOBEBIS TBABSDOCEBS Quantitative thermography in aero-engine research Transducer installation for the Sea King HK 50 and development mathematical model validation flight tests [PSB-90021J H81-10075 [AD-A089921] H81-11365 TEHSILE SEOPBETIBS TBANSBISSIO1 B2FICIEBC1 Bicrocracking in graphite-epoxy composites A six-channel quick-look unit for the aerodynamics [AD-A089891] H81-11118 division OKI airborne data acquisition package TBHSI1B STBBBGTB [AD-A089975] 881-11361 Effect of various environmental conditions on TBABSHISS10BS (BACBIBE ELEBBITS) polymer matrix composites An analytical method to calculate misalignment in H81-11130 the journal bearing of a planetary gear system TBBSIBAL FACILITIES A81-10839 Atlanta's new central passenger terminal complex TBASSOBIC PLIGHT A81-10719 Research on transonic wings at the national TBBBIBAL GOIDABCB Aerospace Laboratory, Japan Procedures to improve flight safety in wind shear A81-11610 conditions TBAHSOBIC FI01 A81-11666 Asymmetric flow of subsonic and sonic jets over an Flight termination receiver/decoders design, infinite wedge performance and certification A81-10919 [AD-A089716] 881-11045 Flow computation around multi-element airfoils in TBEBBAI BIPAHSIOB viscous transonic flow Effect of various environmental conditions on A81-11611 polymer matrix composites Calculation of plane transonic flows using the N81-11130 integral egnation method and shock fitting TBEBBAL VACOOB TESTS A81-11779 Effect of various environmental conditions on An example of the transonic flow past a body with polymer matrix composites a discontinuity in the contour curvature H81-11130 A81-12367 THEBBOCOOPLE PYBOBETBBS An investigation of scale effects on the transonic Surface pyrometry in presence of radiation from flow over swept wings. Part 2: Measurements on other sources with application to turbine blade a model of a variable-sweep strike-fighter temperature measurement configuration [HASA-TP-1751] 881-11039 [ABC-B/M-3812-PT-2] 1181-10010 THIS 1IBGS A comprehensive evaluation and analysis of Flow past a slender profile in a channel with transonic flow calculations on three related permeable vails wing-body configurations A81-10916 [FFA-TH-Aa-1IU8-PT-1 J B81-10013 TBBBE DIBBBSIOBA1 BOOBBABI LAIBB A comparison of Bewton-like methods for the Local properties of three-dimensional separation transonic small disturbance eguation lines in vortex layers [AD-A090270] B81-11017 [DGIB PAPEE 79-063] A81-11780 TBABSOHIC SPEED IHBEE DIBBBSIOBAL PlOi Calibration of a bloudown-to-atmosphere cryogenic Investigation of lateral forces and moments in the wind tunnel case of asymmetric gas flows in nozzles H81-11060 A81-10913 Characteristics and status of the OS Bational Review of numerical methods for the problem of the Transonic Facility supersonic flow around bodies at angle of attack B81-11065 A81-11639 TBABSOHIC iIBB TDBBELS Analysis of calculated three-dimensional inviscid A system for model access in tunnels with an flow fields with embedded shock waves unbreathable test medium (presentation of a field solution), part 1 A81-11672 [ESA-TT-5S8] B81-10017 A simple laser interferometer for wind tunnel flow TITABIOB visualisation Acoustic structures titanium brazing method A81-12078 for producing honeycomb structures for jet A fan pressure ratio correlation in terns of Bach engine noise reduction number and Reynolds number for the Langley 0.3 A81-10272 meter transonic cryogenic tunnel TOX1CITI [BASA-TP-1752] H81-10005 Toxicity of synthetic high density and An introduction to dynamic derivatives (3) methods conventional hydrocarbon jet fuels to a soil of oscillating models in pitch and yaw in a 530 bacterium by 810 millimetre transonic wind tunnel [AD-A089527] B81-11233 [ABL/AEBO-80TE-390] H81-10007 IBACKIIG (POSITIOB) The European Transonic Rind tunnel ETI Multivariable closed-loop analysis and flight B81-11061 control synthesis for air-to-air tracking TBABSPOBT A1BCBAFT [AO-A090050] B81-11016 Bow to improve the performance of transport TBADEOFFS aircraft by variation of wing aspect-ratio and A1ABS implementation tradeoff twist /12th Daniel and Florence Guggenheim [AD-A089977] B81-11026 International Memorial Lecture/ TBAIUBG-BDGE F1AES A81-11602 Boundary layer measurements on a two-dimensional Numerical optimization - An assessment of its role wing with flap in transport aircraft aerodynamic design through [BLB-TB-79009-U] B81-1001U a case study TBAIBIBG SIBOLATOBS A81-11601 Bicroprocessor software applications for flight Flying qualities criteria for advanced control training simulators technology transports B81-116S8 A8 1-11618 IBAJECIOSI COBtBOI An analytical study of landing flare Flight termination receiver/decoders design, [DFVLB-EB-79-10] H81-10062 performance and certification Exploratory study of hazard mitigation and [AD-A089716] 881-11015 research in the air transport system TBAJECTOBJ OFTIBIZATICB £AD-A08920«] B81-11021 Aircraft performance optimization by forced Container Life Adapter-Helicopter (CLAB) singular perturbation operational prototype (preproduction) A81-11667 militarized units for flight evaluation and operational testing [AD-A089791] B81-1103<4

A-31 TBABSPOBTATIOi EHEBGY SUBJECT INDEX

IBAHSEOBIAIIOB BHBBGI Core noise measurements from a small, general Hydrogen - Its technology and implications. Volume aviation turbofan engine 4 - Utilization of hydrogen Book [BASA-TH-81610] 1181-11769 A81-11751 10BBOFABS Alternative energy sources for non-highvay Axial flov compressors. Citations from the transportation, appendices Engineering Index data base [DOE/CS-05I438/T1-VOL-3J B81-11500 [PB80-808611] H81-10076 Alternative energy sources for non-highvay TOBBOGB8EBATOBS transportation, volume 1 Bev BBC high-efficiency gas turbines [DOE/CS-05438/T1-VOL-1] B81-11513 A81-11797 TDBBIBB GIAOES TOEBOJET EBGIBB COSTBOL Surface pyrometry in presence of radiation from Automation of aircraft gas-turbine pover plants other sources with application to turbine blade Bussian book temperature measurement A81-12782 [NASA-TP-1751J B81-11039 IDBBOJET EB6IBES Performance of a steel spar vind turbine blade on Bibliography on aerodynamics of airframe/engine the Hod-0 100 ks experimental vind turbine integration of high-speed turbine-povered [NASA-TB-81588] B81-11<|i|8 aircraft, volume 1 Definitive generic study for the effect of high [BASA-TM-81811] B81-11032 lift airfoils on uind turbine effectiveness, 10BBOHACHIIEBI executive summary Axial flov compressors. Citations from the [SEBI/TB-98003-2] B81-11492 Engineering Index data base TOBBIIB EBGIBBS [EB80-808611] N81-10076 Fuel character effects on current, high pressure TDBBOPBOP BHGIBES ratio, can-type turbine combustion systems flaritime patrol aircraft engine study. General [AD-A089182] B81-10C73 Electric derivative engines. Volume 2: Off-design performance loss model for radial Appendix A. Performance data - GE27/T3 study a1 turbines with pivoting, variable-area stators turboprop [NASA-TP-1708] N81-11038 IAD-A089336] B81-10068 Snperhybrid composite blade impact studies flaritime patrol aircraft engine study. General [NASA-TH-81597 ] B81-11412 Electric derivative engines. Volume 3: The role of advanced technology of turbine engine Appendix B. Performance data - TF31/T7 study A1 life cycle cost turboprop B81-11927 [AD-A089279] B81-10069 Cost/benefit analysis of advanced materials TOBBDLEBT BODBDABY LAIEB technology candidates for the 1980's, part 2 An experimental investigation of the interaction [BASA-CB-165176] B81-11S53 between a glancing shock vave and a turbulent IDHB1BB IBSTBOBEB1S boundary layer Disk residual life studies. Part 1: F10Q A81-11649 1st-stage turbine disk (IN100) TilSlED ilBGS [AD-A089791] B81-11041 How to improve the performance of transport TUBBIBES aircraft by variation of ving aspect-ratio and Adiabatic gas flow, citations from the BUS data tvist /12th Daniel and Florence Guggenheim base International Memorial Lecture/ [EB80-8085M6] B81-10018 A81-11602 Performance of a steel spar vind turbine blade on TIO DIHBBSIOBAI BOUHDABY LAYBB the Hod-0 100 kN experimental vind turbine Boundary layer measurements on a tvo-dimensional [BASA-TH-81588] S81-11fl

A-32 SUBJECT IIDEI HIBD TUNNEL AfPiBATUS

Using cost reduction concepts at Analytical estimation on nonlinear longitudinal Messier-Hispano-Eugatti characteristics of wings with small and moderate H81-11923 aspect ratio by the vortex lattice method in VAHBS incompressible flow Vortei drag reduction by aft-mounted diffusing vanes [ES4-TT-S85] B81-10018 481-11617 VOBTICES VABIABLB GEOHETIY SIBOCIDBSS Holographic investigation of slender body vortex Variable geometry, lean, premized, prevaporized wakes fuel combustor conceptual design study [AD-A089196] 881-10008 [ASBE PAPEB 80-GT-16] 481-12609 VOLBEBABILITI Off-design performance loss model for radial A probabilistic analysis of electrical equipment turbines vitb pivoting, variable-area stators vulnerability to carbon fibers [8ASA-TF-1708] H81-11038 [BASA-TM-80217] B81-11113 VABIABLE SHEEP 1IHGS in investigation of scale effects on the transonic flow over swept wings. Part 2: Measurements on w a model of a variable-sweep strike-fighter IAKES configuration Holographic investigation of slender body vortex [ABC-B/H-3812-PT-2] 881-10010 wakes VBCTOB SPACES [AD-A089196] B81-10008 Optimal flight vehicle design and linear vector •ALL FLOI spaces Local properties of three-dimensional separation 481-11668 lines in vortex layers VELOCITY DISTBIBUTIOB [DGLB PAEEE 79-063] A81-11780 Flow measurements in the Hake of a wing fitted IALL PBBSSOBE with a leading-edge root eitension (strake) Hind tunnel wall interference in a test section [8AZ-TB-79120] H81-10015 with ventilated walls VEiTH4TIOB 481-11673 Hind tunnel vail interference in a test section H4BBIB6 SIS1EBS with ventilated walls Head up displays. Citations from the Mils data base 481-11673 [PB80-809061] 881-10050 VEEI RIGB FBEO.OEHCIBS HAVELESfiTHS Preliminary test plans of 4TC concepts for longer Surface pyrometry in presence of radiation from tera improvement helicopter development program other sources with application to turbine blade [4D-4089407] 881-10037 temperature measurement VIBB4TIOB DAMCI1G I NASA-IP-1751] 881-11039 Experimental application of a vibration reduction iEAPOS SIS1B8S technique Life Cycle Cost Analysis (LCCA) in military 481-10770 aircraft procurement Active flutter suppression design and test - A B81-11903 joint O.S.-F.B.G. program Summary of AGABD Lecture Series 100: Methodology A81-11621 for control of life cycle costs for avionics VIBBA1IOJ ISOLATOBS systems Model tests for an active rotor isolation system 881-11921 [MBB-278-79-0] 481-12095 HEAPOBS ISDUSTB! VIBBATIOI SIBOL1TOBS A review and assessment of system cost reduction Forced vibrations of a nonlinear system excited by activities a centrifugal oscillator vitb a sloping engine 881-11906 characteristic 1BATBEB1B6 481-10139 Erosion and impacts on composite helicopter blades VISCOUS P10H B8 1-11138 Design of airfoils in incompressible viscous flows HEDGE FLOI by numerical optimization Asymmetric flow of subsonic and sonic jets over an 481-10096 infinite wedge Flov computation around multi-element airfoils in 481-10919 viscous transonic flov HEIGHT IBDICATOBS 481-11611 In-flight measurement of aerodynamic loads on Calculation of separated viscous flows on wing captive stores. Equipment and results profiles by a coupling approach [HLB-HP-79013-U] B81-10012 [OHEB4, IP HO. 1980-122] 481-11920 HEIGHT BEDOCTIOB VISU41 CCBTBOL Height optimization of wing structures according 4nalysis of the function principle and operational to the gradient method assessment of an onboard glidepath guidance 481-11650 system for visual approaches (Visual 4pproach iELDIRG Monitor (VAM) 4pplicatioo of veldbonding to 4-10 production [DFVLB-JE-79-38] 881-10013 aircraft VOBIEI 4ILEVIATI08 481-11652 Vortei drag reduction by aft-mounted diffusing vanes HIHD EFFECTS A81-11617 The turbulent wind and its effect on flight VOBTEI 4VOIDABCB [OTIAS-BEVIEH-11] H81-11020 Preliminary test plans of A1C concepts for longer IIBD SHEAB term improvement helicopter development program Procedures to improve flight safety in wind shear [AD-A089107] B81-10037 conditions VOBTEI FLAPS 481-11666 Vortex drag reduction by aft-mounted diffusing vanes Hind shear detection from PCH-recorded HLS-flight A81-11617 data Leading-edge 'Vortex Flaps' for enhanced subsonic A81-11675 aerodynamics of slender wings Pilot-aircraft system reponse to wind shear 481-11618 [NASA-CB-3312] 881-10636 VOBZBI SBEBTS Test and evaluation of the Airport surveillance Simplified vortex models for slender lifting Badar (4SB)-8 wind shear detection system (phase surfaces with leading edge separation 2), revision A81-11777 [AD-A090111] 881-11290 Local properties of three-dimensional separation HIBD TOBSEL APP4BATUS lines in vortex layers Add fluorescent minitufts to the aerodynamicist1s [DGLB PAPES 79-063] A81-11780 bag of tricks Linear vortex theories of a profile and wing with 481-11215 air intake 481-12703

A-33 IIHD TOBBEL CALIBBATIOB SDBJECI IHBEI

Three years of operation of the ONERA pressurized Hind tunnel investigation of the aerodynamic subsonic Mind tunnel hysteresis phenomenon on the F-4 aircraft and [ONEBA, IE NO. 1980-129] A81-11669 its effects on aircraft motion A system for model access in tunnels with an [AD-A089851] N81-11016 unbreathable test medium Low-speed aerodynamic performance of A81-11672 50.8-centimeter-diameter noise—suppressing TUBBBL CALIBBAIIOB inlets for the Quiet, Clean, Short-haul Calibration of the high speed wind tunnel TVH 150 Experimental Engine (CCSEE) lewis 9- by in the supersonic range 15-foot low speed wind tunnel tests 481-11778 [NASA-IP-1178] ' N81-11037 A fan pressure ratio correlation in terms of'Mach Calibration of a blowdown-to-atmosphere cryogenic number and Reynolds number for the Langley 0.3 wind tunnel meter transonic cryogenic tunnel B81-11060 [NASA-TP-1752] 1181-10005 HIBD TONNE! RAILS illD TOBBBL DBIVES Adaptable wind tunnel walls for 2D and 3D model Development of wind tunnel fan blade made of tests composite materials A81-11671 [MBE-UD-277-79-0] A81-12096 Hind tunnel wall interference in a test section UNO TONBEL BODELS with ventilated walls High-lift investigations on some small aspect A81-11673 ratio wings BIBDPOiBBBD 6EBEBAIOBS A81-11643 Performance of a steel spar wind turbine blade on Adaptable wind tunnel walls for 2D and 3D model the Hod-0 100 kH experimental wind turbine tests [NASA-TH-81588] B81-11448 A81-11671 Definitive generic study for the effect of high A system for model access in tunnels with an lift airfoils on wind turbine effectiveness, unbreathable test medium executive sumi&ary A81-11672 [SEBI/TB-98003-2] N81-11II92 Hodel design and instrumentation experiences with BUG FLAPS continuous-flow cryogenic tunnels Leading-edge 'Vortex Flaps' for enhanced subsonic N81-11057 aerodynamics of slender wings Model design and instrumentation for intermittent A81-11648 cryogenic wind tunnels ilBG FLOI HBTBOD TESIS 1181-11058 Add fluorescent minitufts to the aerodynamicist's The European Transonic Hind tunnel ETH bag of tricks N81-11064 A81-11245 81HD TOBBBL TESTS High-lift investigations on some small aspect Investigation of hig-h-manoeuvrability flight ratio wings vehicle dynamics A81-11643 A81-11625 Ringlets development at Israel Aircraft Industries An experimental investigation of the interaction A81-11645 between a glancing shock wave and a turbulent Adaptable wind tunnel walls for 2D and 3D model boundary layer tests A81-11649 A81-11671 Investigation of the stalling characteristics of a BIBG LOADING general aviation aircraft Height optimization of wing structures according A81-11665 to the gradient method Three years of operation of the ONEGA pressurized A81-11650 subsonic wind tunnel Estimation of wing nonlinear aerodynamic [ONEBA, TI NO. 1980-129] A81-11669 characteristics at supersonic speeds DPVLR-dynamic model testing in wind tunnels for [NASA-TP-1718] N81-10004 active controls research An analytical technique for approximating unsteady A81-11670 aerodynamics in the tine domain Adaptable wind tunnel, walls for 2E and 3D model [NASA-TP-1738] B81-11422 tests BIBG NACELLE COIFIGDUIIOBS A81-11671 Calculation of the flow field around Some thoughts on the effects of flight on jet engine-wing-configurations noise as observed in actual flight and in wind A81-11613 tunnels BIBG OSCILLAIIOBS A81-11723 Active flutter suppression design and test - A A simple laser interferometer for wind tunnel flow joint O.S.-F.B.G. program visualisation A81-11621 A81-12078 BIBG PANELS An introduction to dynamic derivatives (3) methods Flight simulation environmental fatigue crack of oscillating models in pitch and yaw in a 530 propagation in 202U-T3 and 7475-T761 aluminum by 810 millimetre transonic wind tunnel wing panels for transport aircraft [ABL/AEBO-BOTE-390] H81-10007 [NLB-MP-80003-OJ 1181-11415 Holographic investigation of slender body vortex BIBG PBOFILES wakes New concepts for design of fully-optimized [AD-A089496] B81-10008 configurations for future supersonic aircraft An investigation of scale effects on the transonic A81-11606 flow over swept wings. Part 2: Measurements on Longitudinal motion of low-flying vehicles in a model of a variable-sweep strike-fighter nonlinear flowfields configuration A81-11626 [AHC-R/H-3842-PT-2] H81-10010 Research on transonic wings at the National Boundary layer measurements on a two-dimensional Aerospace Laboratory, Japan wing with flap A81-11640 [NLB-TB-79009-D] N81-10014 Optimizing the fixed leading edge shape of a Flow measurements in the wake of a wing fitted transonic wing to suit the landing high-lift with a leading-edge root extension (strake) requirements [BAE-IB-79120] N81-10015 A81-11641 Pull scale wind tunnel investigation of a BIBG SLOTS bearingless main helicopter rotor Ames 10 by The performance of slotted blades in cascade 80 foot wind tunnel test using the BO-105 A81-10632 helicopter BIBGLETS [NASA-CB-152373] N81-11014 Kinglets development at Israel Aircraft Industries A81-11645

A-34 SUBJECT IBDBX 1ABIIG BOBESTS iIHGS Numerical optimization - An assessment of its cole in transport aircraft aerodynamic design through a case study 181-11604 Advanced combat aircraft King design 481-11608 Linear vortex theories of a profile and ving vith air intake 481-12703 Nodel design and instrumentation for intermittent cryogenic wind tunnels N81-11058 USE Civil helicopter vire strike assessment study. Volume 2: Accident analysis briefs [NASA-CB-152390] B81-10019

XV- 15 4 I DC BAFT The IV- 15 tilt rotor research aircraft [HASA-TB-8 121)4] H81-10054

HOHEBIS An introduction to dynamic derivatives (3) methods of oscillating models in pitch and yav in a 530 by 810 millimetre transonic vind tunnel [ABl/AEBC-HOTE-390] S81-10007 A piloted simulator investigation of static stability and stability/control augmentation effects on helicopter handling qualities for instrument approach [NASA-Id-81188] B81-10077

A-35 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 132) FEBRUARY 1981

Typical Personal Author Index Listing

PERSONALAUTHOR COIB, 6. I. ' I Simulating study of the interaction between the ALEKSEEV, B. F. propulsion and flight control systeas of a Reliability and engineering-economic subsonic lift fan VIOL characteristics of aircraft engines [«AS4-Ia-ei239] B81-11043 A81-10045 ALLAIBE. P. B. I An experimental and theoretical investigation of I pressures in four-lobe bearings NASA 481-10840 REPORT TITLE ACCESSION NUMBER NUMBER The role of flight simulation in the design and development of the Sea Harrier Nav-Attack System 481-11635 AHGELIBI, J. J. Listings in this index are arranged alphabetically by personal author. The title Comparison of Unsteady Pressure Fields Computed of the document provides the user with a brief description of the subject matter. and Measured on the ZKP model The report number helps to indicate the type of document cited (e.g.. NASA . [AGAED-E-688] N81-11019 report, translation. NASA contractor report). The accession number is located ABEBDTS, F. J, beneath and to the right of the title, e.g. N81 -11043. Under any one author's Constant-amplitude and flight-by-flight tests on name the accession numbers are arranged in sequence with the IAA accession CFHP specimens 881-11133 numbers appearing first. ABHAIZ. B. Preliminary airworthiness evaluation AH-1S helicopter with ogee tip shape rotor blades CAD-A089625J H81-10061 ABBEI. B. J. ABHADD, J. L. Design options study. Volume 1: Executive summary Holographic non-destructive testing of materials [AD-A089536] 1181-10056 using pulsed lasers Design options study. Volume 2: Approach and A81-11655 summary results ABHDT, B. E. A. [AD-A089537] H81-10057 Cooperative investigation of the noise producing Design options study. Volume 3; Qualitative region of an axisymmetric jet assessment [AD-A089692] 881-11774 [AD-A089538J N81-10058 ABNTZBB, 0. B. Design options study. Volume 4: Detailed Airfield pavement demonstration-validation study analyses supporting appendices A81-10718 [AD-A089539] S81-10059 ABTHABB, J. ABBOTT, J. H. Weight optimization of wing structures according Low-speed aerodynamic performance of to the gradient method 50. 8-centimeter-diameter noise-suppressing 481-11650 inlets for the Quiet, Clean, Short-haul ATTLFELLBEB, S. Experimental Engine (QCSEE) 4 method of helicopter low airspeed estimation [B4SA-TP-1178] H81-11037 based on measurement of control parameters ACKEBHABB, 3. [HBB-UD-276-79-0] A81-12094 Bobust control system design 881-11275 ADKIBS, I. 1. B Design options study. Volume 1: Executive summary BAABSPDL, 0. [AD-A089536] N81-10056 Development and application of a moving base Design options study. Volume 2: Approach and visual flight simulator including the design of summary results hydraulic actuators with hydrostatic bearings [AD-A089537] H81-10057 481-11633 Design options study. Volume 3: Qualitative BABIHSKI, 1. C. assessment Fiber release from impacted graphite reinforced [AD-A089538] 881-10058 epoxy composites Design options study. Volume 4: Detailed [BASA-CB-163681] 881-11117 analyses supporting appendices BALL, E. €. [AD-A089539] H81-10059 Container Life Adapter-Helicopter (CLAQ) ADSIT. E. B. operational prototype (preproduction) Development of advanced interceptor substructural militarized units for flight evaluation and material operational testing [AD-A090127] S81-11116 [AD-A089791I] 881-11031 AGBELL. B. BALL, K. O. i. A comprehensive evaluation and analysis of Aircraft engine nacelle fire test sinulator. transonic flow calculations on three related Volume 1: Technical wing-body configurations [AD-A089629] S81-10081 [FF4-TB-40-1118-PT-1] H81-10013 BABDDBIB, V. V. AlBE, F. The design of blowing-cooled aircraft electrical Holographic non-destructive testing of materials machines using pulsed lasers 481-10174 A81-11655 BABEBBBB6. E. J. ALDBBS, 6. J. Airfield pavement denonstration-validation study Xn-flight measurement of aerodynamic loads on 481-10718 captive stores. Equipment and results [BLE-HP-79013-0] 881-10012

B-1 BAB6A. fl. A. PBBSOBAL AOTHOB INDEX

BABGA, H. A. BBAHDEHBBBG, C. F. The role of advanced technology of turbine engine F/A-18's landing, launch and recovery system life cycle cost A81-11244 H81-11927 BEANDOB. G. K. BABIABD, A. J. The accident/injury matrix - A tool for aircraft Fatigue and damage propagation in composite rotor accident investigation blades A8 1-12241 H81-111I45 BHEHBAH. H. F« BAEHETT. Y. Civil helicopter wire strike assessment study. linglets development at Israel Aircraft Industries Volume 2: Accident analysis briefs A81-116U5 [HASA-CB-152390] B81-10019 BADS, B. B. BBEHEB, G. 0. Ignition of a liquid fuel Hydrogen-fueled aircraft [AD-A089295] H81-10128 A81-11753 BELL, ?. L. BBICKEB, B. A. The potential for damage from the accidental Design options study. Volume 1: Executive summary release of conductive carbon fibers from [AD-A089536] D81-10056 aircraft composites Design options study. Volume 2: Approach and 1181-11143 summary results BEHDBB, G. L. [AD-A089537] H81-10057 Preliminary airworthiness evaluation AH-IS Design options study. Volume 3: Qualitative helicopter vitb ogee tip shape rotor blades assessment [AD-A089625] 881-10061 [AD-A089538] H81-10058 BEHIBTT, B. B. Design options study. Volume 4: Detailed The use of parametric cost estimating analyses supporting appendices relationships as they pertain to aircraft [AD-A089539] 1181-10059 airframes: A nev- perspective BBOCK1EBOBST, A. [AD-A089525] H81-10060 Helicopter tail configurations to survive tail BEBGSAHB. B. I. rotor loss Predictability of moisture absorption in A81-10768 graphite/epoxy sandwich panels BBOCE, 1. I. H81-11131 Compound Cycle Turbofan Engine (CCTE). Task 9: BEBHAS, B. Carbon-Slurry Fuel Combustion Evaluation Program Improved flight control performance and failure [AD-A089451] B81-10072 tolerance using modern control techniques BBDISCH, K. A81-11619 Service experience with GBC helicopter blades BEBBAHD, t. (BO-105) OBAPO - Computer-assisted design and manufacturing N81-111II6 system BOCBACKEB, E. A81-11610 Initial experience with methods to evaluate flight BEYEBS, a. S. test characteristics with operational flight Investigation of high-manoeuvrability flight maneuvers vehicle dynamics A81-11782 A81-11625 BOCHBLE, D. B. BIBD, 0. K. Surface pyronetry in presence of radiation from The all-electric aircraft other sources with application to turbine blade A81-11617 temperature measurement BIBKLEB, J. L. [NASA-IP-1754] 1181-11039 Aircraft turbine engine monitoring experience. An BDLLOCB, C. overview and lessons learned from selected case Computerized flight management for fuel saving studies AS 1-12349 [AD-A089752] 1181-11042 BDBISIOES. 0. B. BIBBIE, S. E. Aircraft engine nacelle fire test simulator. Community response to noise from a general Volume 1: Technical aviation airport [AD-A089629] 1181-10081 A81-11821 BDTTBBiOBTH, P. J. BISP1IIGHOFF. B. L. Flow measurements in the wake of a wing fitted Exploratory study of hazard mitigation and with a leading-edge root extension (strake) research in the air transport system [BAE-TB-79120] 1181-10015 [AD-A089204] N81-11021 BITTBH, C. Survey population response to airplane noise, part 1 [HASA-TB-75790] -- -• • H81-10576 CADiELl, J. D. • - - - - . _ .. . B1EASDALB, G. I. Hodel design and instrumentation for intermittent Some engineering aspects of life cycle costing cryogenic wind tunnels N81-11918 1181-11058 BLOB, J. J. B. Calibration of a blowdown-to-atmosphere cryogenic Low-speed airfoil section research at Delft wind tunnel University of Technology 1181-11060 A81-11636 The control of pressure, temperature and Bach BOBBHABS. L. B. H. number in a blowdown-to-atmosphere cryogenic Low-speed airfoil section research at Delft wind tunnel University of Technology B81-11063 AS 1-11636 CAIAFA, C. A. BOLLBABH, J. Engineering and development program plan aircraft Estimation of relative total cost for aircraft crashMOrthiness systens [AD-A089431] H81-10022 H81-11922 CALDBEL1, B. fl. BOBBI, fl. Design options study. Volume 3: Qualitative Evaluation of section properties for hollow assessment composite beams [AD-A089538] B81-10058 [PAPEB-HB-35] H81-10454 Design options study. Volume 4: Detailed BOTTOHLEY. D. analyses supporting appendices New terminal radar approach control in tower cab [AD-A089539] B81-10059 concept for Love field, Dallas, Texas CAPDEVIBLLB, J. I. [AD-A089996] N81-11025 The emulsion chamber experiment on super-sonic BOOBISAi, D. L. Concorde /Echos/ F/A-18's landing, launch and recovery system A81-12476 A81-11244

B-2 PEBSOBAL AOTBOB IBDBI DB GBAAF. E. A. B.

CABADO1BA, F. X. Fuel jettisoning by D.S. Air Force aircraft. Experimental and analytical studies of a model Volume 2: Fuel dump listings helicopter rotor in hover [AD-A089076] B81-10581 [AD-A089780] N81-11033 COLE, G. L. CABABASCBI, ». Simulating study of the interaction between the Evaluation ot section properties for hollow propulsion and flight control systems of a composite beams subsonic lift fan VIOL [PAPBB-HB-35] H81-10454 [BASA-TB-81239] B81-11043 CARD, B. F. COLLIBS, B. F. Graphite-epoxy panel compression strength Analysis of potentially correctable landing delays redaction due to local impact at Atlanta N81-11139 [AD-A089408] H81-10032 CAHGILL, J. S. COBBOB. I. fl. Disk residual life studies. Part 2: IF30 Evaluation of safety programs with respect to the lOth-stage compressor disk (IHCOLOJ 901) causes of general aviation accidents. Volume 2: [AD-A089524] 881-10074 Appendices Disk residual life studies. Part 1: F100 [AD-A089181] H81-10023 1st-stage turbine disk (IU100) COBDIE, F. [AD-A089791] H81-11041 Design-to-cost and new technologies CABLOBAGBO, G. B. B81-11913 On screeching jets exhausting from an axisymmetric CODSIOH, B. supersonic nozzle Comparison of Unsteady Pressure Fields Computed A81-11616 and Measured on the ZKP model CABLSOB, F. I. (AGABD-B-688] 881-11019 Design to life cycle cost research COVAOLT. C. N81-11907 NASA presses fighter gains CABLSOB, a. 9. A81-10575 Status of knowledge of sonic booms COX, E. E. AS 1-11822 Hydrogen - Its technology and implications. Volume Estimation of wing nonlinear aerodynamic 4 - Utilization of hydrogen characteristics at supersonic speeds A81-11751 [HASA-TJ-1718] B81-10004 CEAiFOBD, C. B. CAHBABA, J.-fl. The Discrete Address Beacon Systea/Air Traffic Three years of operation of the ONEBA pressurized Control Badar Beacon System/ATCBBS IFF Hark 12 subsonic wind tunnel system (DABS/ATCBBS/AIMS) performance prediction [OHEBA, IP BO. 1980-129] A81-11669 model CABI, B. B., JB. [AD-A089440] B81-10034 Alternative energy sources for non-highway CflEBD, S. B. transportation/ appendices A six-channel quick-look unit for the aerodynamics [DOE/CS-05438/T1-VOL-3] B81-11500 division SKI airborne data acquisition package Alternative energy sources for non-highway [AD-A089975] S81-11364 transportation, volume 1 CBOIOEB, J. F. [DOE/CS-05438/T1-VOL-1] N81-11513 Add fluorescent minitufts to the aerodyoamicist's CBABIS, C. C. bag of tricks Superhybrid composite blade impact studies A81-11245 [HASA-TH-81597] N81-11412 COB8IB6HAB, I0 B. CHENG, I. i. Failure management techniques for high survivability Disk residual life studies. Part 2: TF30 H81-11272 10th-stage compressor disk (IBCOIOY 901) [AD-A089524] B81-10074 Disk residual life studies. Part 1: F100 1st-stage turbine disk (IH100) DALLEBiGIE, G. [AD-A089791] H81-11041 Elastomers used in aeronautics industry CHEBHOV, I. A. [SBIAS-801-551-105] B81-10168 An example of the transonic flow past a body with DAHG VO BIBB, BB. a discontinuity in the contour curvature Bultivariable aircraft control by manoeuvre A81-12367 commands - An application to air-to-ground gunnery CHIEH, B. 1. [OBEBA, IP BO. 1980-127] A81-11623 Optimized computer systems for avionics applications DABEL, I. £AD-A089570] N81-10063 Ringlets development at Israel Aircraft Industries CHISB01B, B. A81-11645 Life Cycle Cost Analysis (LCCA) in military DAS, C. K. aircraft procurement An analytical method to calculate misalignment in H81-11903 the journal bearing of a planetary gear system CHB1SIEBSOS, B. E. A81-10839 An evaluation of statistical methods for the DAVIES, 0. E. prediction of maximum time-variant inlet total Theoretical determination of subsonic oscillatory pressure distortion airforce coefficients for fin-tailplane [AD-A089817] B81-11040 configurations CHOSHKIB, F. I. [BAE-IB-79125] B81-10016 Beview of numerical methods for the problem of the DAVIS, B. B. supersonic flov around bodies at angle of attack Haritime patrol aircraft engine study. General A81-11639 Electric derivative engines. Volume 2: CLABK, K. G. Appendix A. Performance data - GE27/T3 study a1 Compatibility of aircraft operational fluids with turboprop a graphite/epoxy composite: Development of an [AD-A089336] B81-10068 exterior coating system and remover Baritioe patrol aircraft engine study. General [AD-A090049] H81-11120 Electric derivative engines. Volume 3: CLABKE, J. Appendix B. Performance data - TF34/T7 study A1 Design and test of a graphite-epoxy composite A-10 turboprop slat [AD-A089279] H81-10069 A81-11339 DAVIS, S. 0. Application of weldbonding to A-10 production Air Force technical objective document Ft 1981 aircraft [AD-A089709] B81-12010 A81-11652 OE GSAAF, E. 1. B. CLEIELL, B. J., Ill Subsequent proof of damage tolerance for a landing Fuel jettisoning by D.S. Air Force aircraft. gear component after numerous takeoffs and Volume 1: Soanary and analysis landings [AD-A089010] B81-10580 A81-11475

B-3 DB BIJE, P. PEBSOIAL AOIBOB IBDEI

DZ BIJK, P. Subsequent proof of damage tolerance foe a landing gear component after numerous takeoffs and landings EBEBLB, A. A81-11475 Engine air intake design support by use of DEPFBHBAUGH, ?. D. computational methods and comparison of Holographic investigation of slender body vortex theoretically derived pressure distributions takes with eiperioeotai data [AD-A089496] H81-10008 A81-11614 DEGEBEE, H. BCCLBSTOH, A. J. Hodel tests for an active rotor isolation system Cost considerations of engine fuel control systems [BBB-278-79-0] A81-12095 N81-11928 DBLABABCHE, i. EDGE, B. C. Test and evaluation of the Airport Surveillance The implications of laboratory accelerated Badar (ASB)-8 wind shear detection system (phase conditioning of carbon fibre composites 2), revision N81-11129 [AD-A090111] N81-11290 EG6EBS. A. J., JB. DEHBLIHG, P. G. Exploratory study of hazard mitigation and Exploratory study of hazard mitigation and research in the air transport system cesearch in the air transport system CAD-A089204] H81-11021 [AD-A089204] N81-11021 EBJ.EB, C. •„ DEBRIS, B. B. The Discrete Address Beacon System/Air Traffic Cost/benefit analysis of advanced materials Control Badar Beacon System/ATCBBS IFF Hark 12 technology candidates for the 1980's, part 2 system (DABS/ATCBBS/AIBS) performance prediction [SASA-CB-165176] N81-11953 model DEITEB, B. B. [AD-A089440] N81-10034 Composite components on commercial aircraft ELBEB, B. S81-11147 A probabilistic analysis of electrical equipment DIEDBICH, J. B. vulnerability to carbon fibers Optimum subsonic, high-angle-of-attack nacelles [NASA-TH-80217] H81-11113 A81-11646 ELIBiZ, I. Low-speed aerodynamic performance of Kinglets development at Israel Aircraft Industries 50.8-centimeter-diameter noise-suppressing A81-11645 inlets for the Quiet, Clean, Short-haul BUGLE, B. J.. JB, Experimental Engine (QCSEE) Aspect ratio variability in part-through crack [NASA-IP-1178] N81-11037 life analysis DIGSTOB. B. 0. A81-10355 The Hornet program: i design to life cycle cost EBB1BT, B. G. case study The XV-15 tilt rotor research aircraft H81-11910 [NASA-TB-81244] S81-10054 DUBS, J. A. A. B. EBIKSSON, L.-E. Fatigue test results of carbon fiber reinforced Optimizing the fixed leading edge shape of a plastic F28 aircraft component and its transonic wing to suit the landing high-lift structural details requirements N81-11135 A81-11644 DOBET, G. ESUHGEB, B. Belationsbips between impact resistance and Using cost reduction concepts at fracture toughness in advanced composite materials Hessier-Hispano-Bngatti H81-11137 H81-11923 DBOOGGB, G. ETKIS, B. A comprehensive evaluation and analysis of The turbulent wind and its effect on flight transonic flow calculations on three related [DTIAS-BEVIEH-44] N81-11020 wing-body configurations BZBKIEL. E. G, [FFA-TH-AB-1418-PT-1] N81-10013 New terminal radar approach control in tower cab DBOBflOHD, J. P. concept for Love Field, Dallas, Texas A numerical study of candidate transverse fuel [AD-A089996] B81-11025 injector configurations in the Langley scramjet engine A81-10709 DDBBEBLI. B. F4BEB, J. I. DS Navy service experience with advanced composites Cast Aluminum Structures Technology (CAST) . N81-11149 Technology transfer (phase 6) DOBS. I. [AD-i087

FLACK, B. D. GALL. D. An experimental and theoretical investigation of Assessing the behavior of high nodulus composite pressures in four-lobe bearings materials in lightning A81-10E10 N81-111Q1 FIBBIBG, G. GiBZBB, 0. Impact of the discrete Address Beacon System Adaptable wind tunnel walls for 2D and 30 model (DABS) on Air Traffic Control Badar Beacon tests System (AICBBS) performance in selected A81-11671 deployments GEHBT. B. B. [AD-A089611 ] H81-10039 A controlled evaluation of the differences retween FOLKBSSOB, K. two approaches to reliability investment screening Computer based in-flight monitoring [AD-A087506] 881-10416 881-11269 GEOBGE, I. K. Failure management for the SAAB Viggen JA37 aircraft Cooperative investigation of the noise producing H81-11273 region of an axisymmetric jet FOBBBST, B. 0. [AD-A089692] 881-11771 A piloted simulator investigation of static GBBDBS. B. H. stability and stability/control augmentation A piloted simulator investigation of static effects on helicopter handling gualities for stability and stability/control augmentation instrument approach effects on helicopter handling gualities for [NASA-TB-81188] N81-10077 instrument approach FOBSI1B. G. f. [HASA-TH-81188] 881-10077 An introduction to dynamic derivatives (3) methods 6EBHABZ, J. J. of oscillating models in pitch and yaw in a 530 Fatigue strength of CFBP under combined by 810 millimetre transonic wind tunnel flight-by-flight loading and flight-by-flight [ABL/AEBO-HOTB-390] 881-10007 temperature changes FOBSYTH, P. J. B. 881-11131 The analysis of fatigue failures GIAVOTTO. V. A81-11603 Evaluation of section properties for hollow FBAHKLIH, J. A. composite beams Flight evaluation of stabilization and command [PAPEB-8B-35] 881-10154 augmentation system concepts and cockpit GLASSBAI, A. J, displays during approach and landing of Off-design performance loss model for radial powered-lift STOL aircraft turbines with pivoting, variable-area stators [HASA-TE-1551] B81-11044 [NASA-IP-1708] S81-11038 FEEDHD. D. J. GLOVBB, B. D. Becommended short-term ATC improvements for Flight experience with flight control redundancy helicopters. Volume 2: Becommended helicopter management ATC training material 881-11274 [AD-A089441] 881-10029 6HELIB, B. Becommended short-term ATC improvements for DFVLB-dynamic model testing in wind tunnels for helicopters. Volume 3: Operational description active controls research of experimental lOBAN-C flight following (LOFF) A8 1-11670 in the Houston area GOEDB, E. [AD-A089385] 881-10030 Calculation of the flow field around • Proposed ATC system for the Gulf of Mexico: engine-wing-configurations Helicopter operations development program A81-11613 [AD-A089U30] N81-10036 GOBDEL, B. Preliminary test plans of ATC concepts for longer Structural optimization of advanced aircraft term improvement helicopter development program structures [AD-A089407] N81-10037 A81-11651 Becommendations for short-term simulation of ATC GOODilH. J. concepts. Helicopter operations development Proceedings of the 1979 Seminar on Air Traffic program Control. Terminal Badar Approach Control [AD-A089U35] 881-10038 (TBACON) facility supervisory desk complex Becommended short-term ATC improvements for [AD-A08991U] 881-11024 helicopters. Volume 1: Summary of short term GOODIES, B. J. improvements The principles and applications of cryogenic wind [AD-A089521] N81-100U1 tunnels FBOS1. i. B81-11049 Pilot-aircraft system reponse to wind shear GOODIKOOBIZ, J. CSASA-CB-3312;] N81-10636 Effect of a semi-annular thermal acoustic shield FOKABO, I. on jet exhaust noise Discrete frequency noise due to irregularity in [HASA-TB-81615] 881-11770 blade row of axial fan rotor GBABGIEB, B. A81-10633 Aerial survey photography FOHUBO. I. A81-12350 The emulsion chamber experiment on snper-sonic GHAISOB, K. Concorde /Echos/ A new method for estimating transport aircraft AS 1-12176 direct operating costs 881-11915 6BBBBE, 1. Variable geometry, lean, premised, prevaporized GABBLHAH. I. J. fuel combustor conceptual design study Summary of AGABD lecture Series 100: Hethodology [ASHE PAPEB 80-GT-16J A81-12609 for control of life cycle costs for avionics 6BOTIA, B. B. systems Polymer research in rapid runway repair materials B81-1192a CAD-A089606] H81-10080 GADB, P. A. GBDBE. K. P. Helicopter electro-optical system display A practical method for predicting flight-by-flight requirements. 1. The effects of CBT display crack growth in fighter type aircraft for damage size, system gamma function, and terrain type on tolerance assessnent pilots required display luminance A81-11659 [AD-A089755] H81-11035 GOPTA, B. S. GAEVSKII, S. A. Optimum design of axial flow gas turbine stage. I Automation of aircraft gas-turbine power plants - Formulation and analysis of optimization A81-12782 problem. II - Solution of the optimization problem and numerical results A81-12608

B-5 GOPTA. S. S. PEBSOSAL ADTflOB IBDBX

GOPTA. S. S. BIEBBAOfl. F. An analytical method to calculate misalignment in Proceedings of the 1979 Seminar on Air Traffic the journal bearing of a planetary gear system Control. Terminal Badar Approach Control A81-10839 (1BACON) facility supervisory desk complex [AD-A089914] N8 1-11024 BIGGIHS, I. H Preliminary airworthiness evaluation AH-1S HABEBCOM. G. E., JB. helicopter with ogee tip shape rotor blades Bird strikes and aviation safety. Citations from [AD-A089625] B81-10061 the NTIS data base BILTOB, fl. [PB80-8 12944] H81-10027 Quantitative thermography in aero-engine research Airfield pavement evaluation. Citations from the and development HTIS data base [PHB-90021] H81-10075 [PB80-812860] 1181-10083 BIPPLEB, B. HABEBIASD, C. Adiatatic gas flow. Citations from the NTIS data Calculation of the flow field around base engine-wing-configurations t PB80-808516] 1181-10048 A81-11613 Bead up displays. Citations from the BACKBIT, J. E. International Aerospace Abstracts data base Vortex drag reduction by aft-mounted diffusing vanes CNASA-CB-163656] N81-10049 i81-11647 Head up displays. Citations from the NIIS data base HAIL, D. S. [PB80-809064] N81-10050 Systems analysis of the installation, mounting, Axial flow compressors. Citations from the and activation of emergency locator transmitters Engineering Index data base in general aviation aircraft [FB80-808611 ] N81-10076 [ NASA-CB-160036] N81-10020 Axial flow compressors. Citations from the NTIS BALI. F. L. data base Community response to noise from a general [FB80-808603] N81-10441 aviation airport HIBOSB, «„ A81-11821 fiesearch on transonic wings at the National HAHILIOH, C. I. Aerospace Laboratory, Japan Evaluation of safety programs with respect to the A81-11640 causes of general aviation accidents. Volume 2: HIBSCBE1, I. B. Appendices Local properties of three-dimensional separation [AD-A089181] B81-10023 lines HAHFP, B. S. [DGLB PAPEB 79-063] A81-11780 Dynamic stability parameters at high angles of BIBSCBEBOB, B. attack Maritime patrol aircraft engine study. General A81-11624 Electric derivative engines. Volume 2: HABOY, G. B. Appendix A. Performance data - GE27/T3 study a1 Flight evaluation of stabilization and command turboprop augmentation systea concepts and cockpit [AD-A089336] H81-10068 displays during approach and landing of Maritime patrol aircraft engine study. General powered-lift STOL aircraft Electric derivative engines. Volume 3: [HASA-TP-1551] H81-11044 Appendix B. Performance data - IF34/T7 study A1 BABPEB. C. R. turboprop Exploratory study of hazard mitigation and [AD-A089279] K81-10069 research in the air transport system BOCB. B. G. [AD-A089204] N81-11021 Some thoughts on the effects of flight on jet BABBIS, B. F. noise as observed in actual flight and in wind Balanced design: Minimum cost solution tunnels 1181-11919 A81-11723 HiHBISOB, J. B. HODGES. J. Summary of Federal Aviation Administration An investigation of scale effects on the transonic responses to National Transportation Safety flow over swept wings. Part 2: Measurements on Board safety recommendations a model of a variable-sweep strike-fighter [AD-A089971] 881-11022 configuration BABTZDIKEB, J. P. [ABC-B/M-3842-PT-2] N81-10010 The European Transonic iind tunnel ETH HOEHLIHGBB, B. H81-11064 Active flutter suppression design and test - A BEDEL, K. K. joint D.S.-F.B.G. program High-density avionic power supply A81-11621 A81-11157 BOLGEB, D. K. BBDBAB, S. Prediction of changes in aircraft noise exposure A comprehensive evaluation and analysis of A81-11820 transonic flow calculations on three related BOLBES, B. wing-body configurations The vibration of a multi-bearing rotor [FFA-TB-10-1418-PT-1] B81-10013 A81-11722 BEGELE. B. 0. BOLT. D. B. Aircraft engine nacelle fire test simulator. Advanced combat aircraft wing design Volume 1: Technical 481-11608 [AD-A089629] H81-10081 BOOBIGAB. 0. T. BEBBEBI, H. V. Transducer installation for the Sea King HE SO A method of performance prediction for centrifugal oatheaatical model validation flight tests compressors. Cart 1: Analysis. Part 2: [AD-A089924] 881-11365 Comparison with experiment BOiEl, B. B. [ABC-B/H-3843] N81-10436 A system for model access in tunnels with an HEBHAH, J. t. unbreathable test medium Hind tunnel investigation of the aerodynamic A81-11672 hysteresis phenomenon on the F-4 aircraft and BSD, T. B. its effects on aircraft notion part-through crack problems in aircraft structures [AD-A089851] N81-11016 A81-10362 BEBIZ, J. HDBBABD. B. B.. Ill Development of advanced interceptor substructural An analysis of Air force management of Turbine material Engine Honitoring Systems (TEoS) [AD-A090127] 1181-11116 [AD-A089365] 881-10070 BOBBABD. B. B. Status of knowledge of sonic booms A81-11822

B-6 EBBSOHU AOTBOB IIOEX KODABA. I.

HDBSB, 8. Helicopter flight characteristics improvement through svept-tip rotor klades K [HBB-UD-275-79-0] A81-12097 KAHIIA. H. BUGBBS, P. B. Besearch on transonic wings at the National Aircraft engine nacelle fire test simulator. Aerospace Laboratory, Japan Volume 1: Technical A81-11640 [AD-A089629] B81-10081 KABCBHBB, A. HDIE, B. Core noise measurements from a snail, general Balanced design: ninimuni cost solution aviation turbofan engine N81-11919 [BASA-TB-81610J 881-11769 BTBAB. 1. KASBIiAGI, I. Belicopter electro-optical system display Ignition of a liquid fuel requirements. 1. The effects of CBT display [AD-A089295] N81-10128 size, system gamma function, and terrain type on KA1CZTHSKI, B. pilots required display luminance Methods of fuel conservation in civil aviation. I [AD-A089755] S81-11035 A81-11322 KEECH, I. Impact of the discrete Address Beacon System (DABS) on Air Traffic Control Badar Beacon IGOE, I. B. System (ATCBBS) performance in selected Characteristics and status of the US National deployments Transonic Facility [AD-AQ89611] H81-10Q39 N81-11065 KEITB. I. G., JB. IBABA. B. Performance of a steel spar wind turbine blade on The emulsion chamber experiment on super-sonic the flod-0 100 kB experimental wind turbine Concorde /Echos/ [BASA-TH-81588] M81-11448 A81-12476 KEHBBDT. B. S. IMGBLBAB-SOHDBEBG, H. formats for DABS data link applications Optimizing the fixed leading edge shape of a IAD-A089963] B81-11028 transonic King to suit the landing high-lift KEHTOB, B, requirements Search and rescue methods and equipment. A A81-11644 bibliography with abstracts 1BBIS. B. C. [PB80-812837] H81-10026 Flight evaluation of stabilization and command KEBIOH, I. B. augmentation system concepts and cockpit A six-channel quick-look unit for the aerodynamics displays dnring approach and landing of division OKI airborne data acquisition package powered-lift STOI aircraft fAD-A089975] H81-11364 [NASA-TP-1551] N81-11044 KBABLAMOV, B. P. IOHESCU. 0. An exact solution of the problem of the motion of Seduction of the take-off ground run distance to a a gyroscope in a Cardan suspension given set of atmospheric condition A81-12704 A81-11634 KIL60BE, B. 1. IVAHOV, V. A. Kodel design and instrumentation experiences with An example of the transonic flow past a body with continuous-flow cryogenic tunnels a discontinuity in the contour curvature B81-11057 A81-12367 KID. J. C. liAI, J. Variable geometry, lean, premized, prevaporized The emulsion chamber experiment on super-sonic fuel combustor conceptual design study Concorde /Echos/ [ASBE PAPEB 80-GT-16] A81-12609 A81-12476 KIBBA1L, C. B. Acoustic structures A8 1-10272 KIHG, D. I. JACOB!. J. L. Fitment of I4HAM standby attitude indicators to Holographic investigation of slender body vortex nacchi aircraft wakes [AD-A089378] B81-11036 [AD-A089496] N81-10008 KISTIEB, C. I., JB. JOB8SOB, B. B. Polymer research in rapid runway repair materials Belicopter electro-optical system display [AD-A089606] N81-10080 requirements. 1. The effects of CBT display KLBIBEIDAB, 6. size, system gamma function, and terrain type on Longitudinal motion of low-flying vehicles in pilcts required display luminance nonlinear flowfields [AD-A089755] S81-11035 A81-11626 JOKES, B. J. KLEVEHBOSEB, E. D. Summary of AGABD Lecture Series 107: The Flow computation around multi-element airfoils in Application of Design to Cost and Life Cycle viscous transonic flow Cost to Aircraft Engines A81-116U1 N81-11926 KLOCHKOV, O. G. JOBES, J. B. The design of blowing-cooled aircraft electrical Contributions to the Doited Kingdom microwave machines landing system research and development program, AS 1-10474 1974 to 1978. Volume 1 KHIP, 6. [BAE-TB-79052-VOL-1] H81-10044 Comparisons of four alternative powerplant types Contributions to the United Kingdom micrcvave for future general aviation aircraft landing system research and development program, [HASA-TB-81584] S81-10067 1974 to 1978. Volume 2 RBOBB, G. [BAE-TB-79052-VOL-2] H81-10045 An analytical study of landing flare Contributions to the Dnited Kingdom microwave [DFVLB-FB-79-40] B81-10062 landing system research and development program, ROCK A, 7. 1974 to 197B. Volume 3 Identification of longitudinal flying [BAE-TE-79052-VOL-3] H81-10046 characteristics of an aeroplane and the effect Evolution of techniques for LCC analysis of nonstationary aerodynamics H81-11909 A81-11627 JOPLIB, S. D. KODAHA, I. A system for model access in tunnels with an Discrete fregnency noise due to irregularity in unbreathable test medium blade row of axial fan rotor A81-11672 AS 1-10633

B-7 KOEHIG, B. PBBSOIAL 40THOB IBDBI

KOEHIG. B. LABGE. B. A. Procedures to improve flight safetj in wind shear Numerical optimization - An assessment of its role conditions in transport aircraft aerodynamic design through £81-11666 a case study KOEBSBB. B. A81-11604 High-lift investigations on some soall aspect LABI. B. F. ratio wings Superhybrid composite blade impact studies 481-11643 [SASA-TM-81597] H81-11412 KOBDDILA. I. LABSOB. B. B. Local properties of three-dimensional separation Flight experience with flight control redundancy lines management [DG1B PAPEB 79-063] A81-11780 B81-11274 KOBT4B, J. F. LAOGHLIH. B. P. Atlanta's new central passenger terminal complex OS Army design-to-cost experience 481-10719 881-11905 KE4G. B. L&1IBG. E. I. OLGA, a gust alleviation system for improvement of A fan pressure ratio correlation in terms of Hach passenger comfort of general aviation aircraft number and Beynolds nnnber for the Langley 0.3 A81-11620 meter transonic cryogenic tunnel KBAdSB, B. J. [BASA-TP-1752] H8 1-10005 Airfield pavement demonstration-validation study LE BALLEOB, J. C. 481-10718 Calculation of separated viscous flows on wing KBADSEB. C. profiles by a coupling approach Procedures to improve flight safety in Hind shear [OBEBA. IP NO. 1980-122] A81-11920 conditions LEAOEB, H. £„ A81-11666 An experimental and theoretical investigation of KBEISSELBE1BB, G. pressures in four-lobe bearings A stability augmentation system which covers the A81-10840 complete flight envelope for a P-lc aircraft LEAVI, 1. P. without gain scheduling Hicroprocessor software applications for flight A81-11622 training simulators KBISTIABSES. 0. B. B81-116S8 Experiments on effective source locations and LEBACQ3. J. T. velocity dependence of the broad band noise from A piloted simulator investigation of static a rotating rod stability and stability/control augmentation A81-11724 effects on helicopter handling qualities for KBOSBL, S. H. instrument approach An automated procedure for developing hybrid [NASA-TH-81188] H81-10077 computer simulations of turbofan engines LEE, I. [NASA'TB-81605] B81-11688 Test and evaluation of the Airport Surveillance KOBOTA, Bo Badar (ASB)-8 wind shear detection system (phase An experimental investigation of the interaction 2), revision between a glancing shock wave and a turbulent [AD-A090111] B81-11290 boundary layer LEBEBB, J. U A81-11649 Formats for DABS data link applications KOO, A. S. [AD-A089963] N81-11028 A practical method for predicting flight-by-flight LEVEK, B. crack growth in fighter type aircraft for damage Aircraft hydraulic systems dynamic analysis. tolerance assessment Volume 6: Steady state flow analysis SSFAN A81-11659 computer program technical description [AD-A089240] H81-10055 LEVI, B. A practical method for predicting flight-by-flight LABABBBBB, H. crack growth in fighter type aircraft for damage Detecting the failure of aircraft sensors using tolerance assessment analytical redundancy 481-11659 H81-11270 LEBIS. B. B.. II LABOilB, J, F. OS Army design-to-cost experience The future cockpit of the next generation of civil S81-11905 aircraft LEIIS. 1. A81-11630 Test and evaluation of the Airport Surveillance LADSOB, C. L. Badar (ASBJ-8 wind shear detection system (phase A fan pressure ratio correlation in terms of Hach 2), revision number and Beynolds number for the Langley 0.3 [AD-A090111] S81-11290 meter transonic cryogenic tunnel LISSAB41. P. B. S. [HASA-TP-1752] N81-10005 Definitive generic study for the effect of high LAHAB, »„ £. lift airfoils on wind turbine effectiveness, A review and assessment of system cost reduction executive summary activities [SEB1/TB-98003-2] 881-11492 N81-11906 LOSDOH, S. A. LAHBEBT, H, Toxicity of synthetic high density and Airbus Industrie's heavenly twins - A310 and conventional hydrocarbon jet fuels to a soil 4300-600 bacterium A8 1-123148 [AD-A089527] 881-11233 LAHGBAB, 1, F. LOBES, B. E. Missile motion sensitivity to dynamic stability Numerical optimization - An assessment of its role derivatives in transport aircraft aerodynamic design through [AD-A089750] H81-11093 a case study UBKEBAD, 8. 481-11604 Estimation of relative total cost for aircraft LOVELL. 0. A. systeos Some experiences with numerical optimisation in N81-11922 aircraft specification and preliminary design LABBIELLO, C. studies On screeching jets exhausting from an axisymmetric 481-11609 supersonic nozzle LOfELL. I. A. A81-11616 Preliminary design characteristics of a subsonic 'business jet concept employing an aspect ratio 25 strut braced wing [NASA-CB-159361] N81-11013

B-8 PEBSOBAL A01BOB IHDEI BELSOB, J. B.

LUCID. 7. J. BCCLIBTOB, C. B. Handbook on bird management and control Flameholding characteristics of a swept-strut 32 [AD-A089009] H81-1002H fuel-injector for scramjet applications LDIDB8S, B. I. A81-10711 Optimum subsonic, high-angle-of-attack nacelles BCGIBB, J. B, A81-11646 US Navy service experience with advanced composites LOTTIBGEB, B. Polyner research in rapid runvay repair materials HCBALLI, B. 6. [AD-A089606] N81-10C80 The role of advanced technology of turbine engine LIOBS, 0. 1. life cycle cost Improved aircraft cruise by periodic control H81-11927 N81-11030 BEBIHOSE, B. LIOHS, J. I. (lodel tests for an active rotor isolation system A theoretical and practical design investigation [HBB-278-79-0] A81-12095 of the future military cockpit BEITHEB. C. L. A81-11631 Off-design performance loss model for radial LISAK, 1. V. turbines vith pivoting, variable-area stators Forced vibrations of a nonlinear system excited by [HASA-TP-1708] B81-11038 a centrifugal oscillator uith a sloping engine BEBABI, A. characteristic Aircraft performance optimization by forced A81-10U39 singular perturbation A8 1-11667 BEUBZEC, J. S, M Comparison of Unsteady Pressure Fields Computed HACK, B. J. and Measured on the ZKP model Estimation of ving nonlinear aerodynamic [ AGABD-B-688] B81-11019 characteristics at supersonic speeds HIKOLOISKI, I. T. [NASA-TP-1718J N81-1000« Design options study. Volume 1: Executive summary BAEBTIBS, B. f. [AD-A089536] 881-10056 Cost/benefit analysis of advanced materials Design options study. Volume 2: Approach and technology candidates for the 1980's, part 2 summary results [NASA-CE-165176] N81-11953 [AD-A089537] B81-10057 SAGtlEfll, 0. J. Design options study. Volume 3: Qualitative Status of knowledge of sonic booms assessment A81-11822 [AD-A089538] B81-10058 HALISSKI, E. Design options study. Volume 4: Detailed Head-up displays. Ill analyses supporting appendices A81-11320 [AO-A089539] S81-10059 BAI.P1HI, J. R. 8OSGIA. B. Disk residual life studies. Part 2: TF30 Compound Cycle Turbof an Engine (CCTE) . Task 9: lOth-stage compressor disk (IHCOLOI 901) Carbon-Slurry Fuel Combustion Evaluation Program [AD-A08952II] H81-10074 [AD-A089151] B81-10072 Disk residual life studies. Part 1: F100 BOOIJ, B. A. 1st-stage turbine disk (111100) Flying qualities criteria for advanced control [AD-A089791] N81-11041 technology transports HAUS01D, P. A81-1U18 • Possibilities for the valuation of different BOBLAB, S. combat aircraft configurations with respect to Applications of pyrotechnigues in aviation flight mechanics [SNIAS-792-«22-103] B81-10025 A81-11607 BOBOZOV, !„ B. BABBO, A. Automation of aircraft gas-turbine pover plants US Navy service experience with advanced composites A8 1-12782 N81-11149 BOOJLLE, B. BAHTEL, C. B. Design-to-cost applied to the AS350 helicopter Toxicity of synthetic high density and N81-11916 conventional hydrocarbon jet fuels to a soil BUELIBE. E.-O. bacterium Beu BBC high-efficiency gas turbines [AD-A089527] N81-11233 AS 1-11797 BABCIHIAK, B. BULABZ. E. J<, Reduction of energy consumption in the vibrational Variable geometry, lean, premised, prevaporized shot peening of axial compressor vanes fuel combustor conceptual design study A81-11321 [ASHE PAPEB 80-GT-16] A81-12609 HABEVISEVA, 8. A. BUSSI, r. Flow past a slender profile in a channel with Evaluation of section properties for hollow permeable vails composite beams A81-10916 CPAPEB-BH-35] H81-10U51 BABTIB, e. L. Preliminary design characteristics of a subsonic business jet concept employing an aspect ratio N 25 strut braced ving BAGIB. B. B. [ HASA-CB-159361 ] 1181-11013 Cooperative investigation of the noise producing BASSIBIHO, B. region of an axisymmetric jet Proceedings of the 1979 Seminar on Air Traffic [AD-A089692] H81-11771 Control. Teroinal Badar Approach Control BASTASE, A. (TBACOD) facility supervisory desk complex Bev concepts for design of folly-optimized £AD-A08991

B-9 HBBI, L. B. PEBSOBAL AOIBOB IBDEI

HEEI. I. H. OSTAPKOIIC2, B. Engineering and development program plan aircraft Impact damage of aircraft gas turbine engines with crashworthiness axial compressors [AD-A089431] 1181-10022 A81-11324 HEBOB, a. OTTOBEIEB. 0. Calculation of separated viscous flows on wing Preliminary airworthiness evaluation AB-1S profiles by a coupling approach helicopter with ogee tip shape rotor blades [OHEBA, IE HO. 1980-122] A81-11920 [AD-A089625] 881-10061 HICHOLS, 8. B. Bibliography on aerodynamics of airfcame/engine integration of high-speed turbine-powered aircraft, volume 1 PADFIELD, G. Do [NASA-TH-81814] H81-11032 Piloted simulation studies of helicopter agility IIIC01ET, H. 481-10767 The aircraft in the stratosphere PABELL4. B. I. A81-10499 The role of advanced technology of turbine engine HIKOLAJSBH, J. I. life cycle cost The vibration of a multi-bearing rotor N81-11927 A81-11722 PAOZAT. J.-P. HIKUIIB, G. Z. Computer aided compilation of an electrical Investigation of lateral forces and moments in the drawing file case of asymmetric gas flows in nozzles 481-11611 A81-10S13 PCHBLKIHA. L. »- 1ITSCB. P. Investigation of lateral forces and moments in the Predictability of moisture absorption in case of asymmetric gas flows in nozzles graphite/epoxy sandwich panels 481-10913 H81-11131 PEAL. B. A. HIXOB, i. B. The 767's flight-management system - A new Investigation of the stalling characteristics of a generation of airborne avionics general aviation aircraft 481-11242 A81-11665 PEEL. C. J. HOGG1E. L. I. The analysis of fatigue failures Design options study. Volume 1: Executive summary A81-11603 [AD-A089536] 1181-10056 PETEBSOB. L. J- Design options study. volume 2: Approach and Optimized computer systems for avionics applications summary results [AD-A089570] B81-10063 [AD-A089537] 1181-10057 PBTBIE, A. B. BOLL. T. 4n experimental investigation of jet screech by Active flutter suppression design and test - A air jet impingement on solid boundaries joint D.S.-I.B.G. program 481-11302 A81-11621 PIBOBO?. D. Go HOBTH, B. J. Investigation of lateral forces and moments in the The European Transonic Hind tunnel ETH case of asymmetric gas flows in nozzles 1181-11064 481-10913 HOBTfiAH, G. B. PL4KBTIEHKO, H. P= Flameholding characteristics of a swept-strut H2 Forced vibrations of a nonlinear system excited by fuel-injector for scramjet applications a centrifugal oscillator with a sloping engine A81-10111 characteristic NOVAK. L. H. 481-10439 Badar target detection and map-matching algorithm PLEHCiSB, B. B. studies Comparisons of four alternative poverplant types A81-11158 for future general aviation aircraft HO1LAI. P. S. [HASA-TH-81584] 1181-10067 Beliatility-centered maintenance PODSIPABIHA. B. A. 1181-11917 Asymmetric flow of subsonic and sonic jets over an infinite wedge A81-10919 POETS, t. OBEBBAIBB, H. New BBC high-efficiency gas turbines Hodel tests for an active rotor isolation system 481-11797 [HBB-278-79-0] 481-12095 POLLOCK, H. ODOBICO, J. 4 simple laser interferometer for wind tunnel flow Nondestructive evaluation of composite structures visualisation 481-11654 481-12078 OffI, 0. L. PODBADIEB. J. B. Test and evaluation of the Airport Surveillance Design and tests of an helicopter rotor blade with Badar (4SB)-8 wind shear detection system (phase evolutive profile 2), revision [OBEBA, IP NO. 1980-125] A81-11638 [AD-A090111] N81-11290 PBICB, J. E. OGATA. T. Preliminary design characteristics of a subsonic The emulsion chamber experiment on super-sonic business jet concept employing an aspect ratio Concorde /Echos/ 25 strut braced wing A81-12476 [HASA-CB-159361] B81-11013 OHTA, I. PBOBEBI. B. The emulsion chamber experiment on super-sonic Advanced combat aircraft wing design Concorde /Echos/ A81-11608 481-121176 PDCCIHELLI, t~ OLSBAISEII. T. 10. Evaluation of section properties for hollow Two methods for calculating the load on the composite beams surface of a slender body executing axisymmetric [P4PEB-SB-35] S81-10454 vibrations in a sonic gas flow A81-10920 OBUK-BOECKEBAfiB, B. J. Dynamic stability parameters at high angles of BAJPAOL, V. K. attack ECS integration for fuel efficient/low life cycle A81-11621 cost design A81-11676

B-10 IEBSOHAI AOTBOB IHDEX SHISAE, J.

BABACBABDBA, S. B. SCBLIBKELHASS, B. J. Optimal flight vehicle design and linear vector Operational durability of airframe structures spaces 481-11662 A81-11668 SCHBIDI, Do E. BAD, D. 8. Nultivariable closed-loop analysis and flight Leading-edge "Vortex Flaps' for enhanced subsonic control synthesis for air-to-air tracking aerodynamics of slender vings £40-4090050] H81-11046 481-11648 SCHBIDI, K. BAG. S. S. Active flutter suppression design and test - A Optimum design of axial flow gas turbine stage. I joint n.S.-F.B.G. program - Formulation and analysis of optimization 481-11621 problem. II - Solution of the optimization SCBHITZ, D. B., problem and numerical results Engine air intake design support by use of A81-12608 computational methods and comparison of B40SCBEH. E. theoretically derived pressure distributions Structural flight load testing, calibration and with experimental data analysis 481-11614 A81-11656 SCBHEIOEB, G. BECK, G. K. Structural optimization of advanced aircraft Advanced fuel system technology for utilizing structures broadened property aircraft fuels A81-11651 A81-11612 SCHSEIDEB. S. D. BEIFSSIDEB, K. I. Lightning protection considerations for Fatigue damage mechanisms in composite materials - graphite/epoxy aircraft structure A review 1181-11142 481-10747 SCBBOEDEB, I. BBSBOXKO, H. Analytical estimation on nonlinear longitudinal Core noise erasuremeats from a small, general characteristics of vings with small and acderate aviation turbofan engine aspect ratio by the vortex lattice method in [HAS4-TM-81610] H81-11769 incompressible flow RHODES, B. 0. [ESA-TT-585] B81-10016 Graphite-epoicy panel compression strength SCBBOEBS, 1. 6. reduction due to local impact The XV-15 tilt rotor research aircraft 881-11139 [B4S4-TH-81244J N81-10054 BOCKETT, J. A. SCBDETZ, D. Ignition of a liguia fuel Fatigue strength of CFBP under combined [4D-4089295] S81-10128 flight-by-flight loading and flight-by-flight BOEHB1E, B. temperature changes Height optimization of wing structures according S81-11134 to the gradient method SCHOLZ, 0. A81-11650 Development of the 4300 fin in modern composite BOBLF, D. fibre construction OLGA, a gust alleviation system for improvement of 481-11653 passenger comfort of general aviation aircraft SCHI4GEB, K. I. 481-11620 Survey population response to airplane noise, part 1 BOSCB, B. [NASA-TM-75790] N81-10576 Flow computation around multi-element airfoils in SEILEB, K., III viscous transonic flow A1ABS implementation tradeoff 481-11641 [AD-4089977] N81-11026 BOSLIAKOV, G. S, SEB, B. Investigation of lateral forces and moments in the Inlet flow in centrifugal pumps at partial case of asymmetric gas flows in nozzles deliveries A81-10913 [VKI-EBEPBIBT-1979-16] N81-10437 BOOCB01, J. SEBSBOBG, O. Assessing the behavior of high modulus composite Active flutter suppression design and test - 4 materials in lightning joint O.S.-F.B.G. program H81-11141 A81-11621 BOBEll, i. B. Structural optimization of advanced 'aircraft Design to cost and the F-16 multirole fighter structures H81-11911 481-11651 BDDD, J. L. SEVEBOV, L. A. Part-through crack problems in aircraft structures Gyrostabilizers for inertial control systems A81-10362 481-12024 BOPP. B. SHAALAH, H. B. Application of weldbonding to A-10 production Comparative performance of two centrifugal fan aircraft impellers differing in blade section 481-11652 481-10162 SBAHBS, A. Application of weldbooding to 4-10 production aircraft SABBE1L, K. I. 481-11652 The relevance of the Flex-Hub Prop-Fan for SBESfOEALOY, V. S. fuel-efficient airliners Excitation of a circular array of cylinders with A81-11605 longitudinal slits SABDEBS, B. E. 481-12619 An evaluation of statistical methods for the SHIBL, A. B. prediction of maximum time-variant inlet total Comparative performance of two centrifugal fan pressure distortion impellers differing in blade section [AD-A089817] H81-11040 481-10162 SADEB, G. SBIFBIH, E. G. Calculation of the flow field around Asymnetric flow of subsonic and sonic jets over an engine-wing-configurations infinite wedge A81-11613 481-10919 SA1ADA, B. SBIBAB, J. wind tunnel wall interference in a test section 4ircraft performance optimization by forced with ventilated walls singular perturbation 481-11673 481-11667 SBIBAKOBA, B. PBBSOBAL ADTBOB IBDEI

SHIBAKOBA. B. SIOLLBBI, J. I., The performance of slotted blades in cascade In experimental investigation of the interaction 481-10632 between a glancing shock wave and a turbulent SBOBIGIB, ?. B. boundary layer linear vortex theories of a profile and Ming with 681-116149 air intake SIB4CE, 1. C. 481-12703 Comparisons of four alternative powerplant types SIBBEBT, E. E. for future general aviation aircraft Structural integration as a means of cost reduction [8AS4-TB-81584] N81-10067 B81-11912 STUFF. B. SIKA. Z. K. Analytical characteristics methods: Applications Brushless cryogenic ac motors [VKI-PBEPBIBT-1980-10] 881-10011 481-101(68 SUAEEZ, J. A. SIHCLAIB, J. H. Design and fabrication of stabilized organic Superhybrid composite blade impact studies matrix composites [BASA-TB-81597] • N81-11li12 A81-11338 SIHCLAIB. B. G. SDLLUAB, t. L. Polymer research in rapid runway repair materials Performance of a steel spar wind turbine blade on [4D-A089606] S81-10080 the Hod-0 100 k« experimental wind turbine SIPPE1. K. 0. [BASA-TB-81588] N81-11I4U8 Constant-amplitude and flight-by-flight tests on SBABSOH, B. B. CFBE specimens Preliminary design characteristics of a subsonic H81-11133 business jet concept employing an aspect ratio SITILEB, B. I. 25 strut braced wing ATABS implementation tradeoff [HASA-CB-159J61] B81-11013 [4D-A089977] 881-11026 SiECKBB, G. A,. SLACK. B. S. An analysis of Air Force management of Turbine Handbook on bird management and control Engine Monitoring Systems (TEMS) [AD-A089009] N81-10024 [AD-A089365] • B81-10070 SLEZAK. K. 0. SiOLIBSKI. B. Microcomputer array processor system Hind shear detection from PCM-recorded HIS-flight N81-11673 data SBIGIBLSKI. f. 481-11675 Holographic non-destructive testing of materials SKALAI. K. J. using pulsed lasers Flight experience with flight control redundancy 481-11655 management SBITB, P. B. N81-11271 Numerical optimization - An assessment of its role SZDCB, J. B. in transport aircraft aerodynamic design through An automated procedure for developing hybrid a case study computer simulations of turbofan engines A81-1160U [NASA-TB-81605] N81-11688 SBITB, B. B. A multivariate approach to handling qualities rating scale development [AD-4089825] N81-11047 . J. SOBOBOFF, 4. Ground testing of aircraft antistatic protection US Jlavy service experience with advanced composites CONEBA, IP BO. 1980-126] A81-11674 N81-11149 TAKABASBI, U SPBIIG, F. E. The emulsion chamber experiment on super-sonic US Army design-to-cost experience Concorde /Echos/ N81-11905 481-12H76 SFHIBSSTOH, F. S. TAKA1IATSO, I. Fiberglass-reinforced rigid polyurethane expedient Discrete freguency noise due to irregularity in pavement subject to simulated f-1 aircraft traffic blade row of axial fan rotor [4D-A089266] N81-10079 481-10633 SBEBKABTB, 4. K. TABBICOHE, B. Design of airfoils in incompressible viscous flows US Navy service experience with advanced composites by numerical optimization B81-111U9 A81-10096 T4SSIH4BI, Bo SXAUFE1BIBL, B. Organizing a design-to-cost program Longitudinal motion of low-flying vehicles in N81-11914 nonlinear flowfields TAILOB, F. 481-11626 Helicopter tail configurations to survive tail STBIH. B. rotor loss Analysis of the function principle and operational 481-10768 assessment of an onboard glidepath guidance TAILOB. S. B. system for visual approaches (Visual Approach Community response to noise from a general Monitor (VAB) aviation airport [DFVLB-FB-79-38] N81-10043 481-11821 STBIBB&OSBH, B. TBEGBN. 0. A stability augmentation system which covers the System simulation applied to the evaluation of complete flight envelope for a P-Uc aircraft displays for guidance and control without gain scheduling [DFV1B-BITT-79-10] B81-1006U 481-11622 TEBH1SOS. B. C. STEBGBL, B. t. Effect of various environmental conditions on Investigation of the stalling characteristics of a polymer matrix composites general aviation aircraft B81-11130 481-11665 taiBIBT. j. j. STEPHENS, A. B. Design and tests of an helicopter rotor blade with A comparison of Newton-like methods for the evolutive profile transonic small disturbance equation [OSEB4, TP NO. 1980-125] 481-11638 [AD-A090270] 881-11017 1HIES, B. 3, STIBCBCOHB, I. i. Analysis of calculated three-dimensional inviscid Fatigue damage mechanisms in composite materials - flow fields with embedded shock waves A review (presentation of a field solution), part 1 481-10747 [ESi-TT-558] B81-10017 STOCBBAB, H. O. Optimum subsonic, high-angle-of-attack nacelles A81-116U6

B-12 PBBSOHAL AOTBOB IBDEI IALKEB. S. 1.

THOHAS, J. IAB IBGEB, J, I. Analysis of the function principle and operational Low-speed airfoil section research at Delft assessment of an onboard glidepath guidance University of Technology system for visual approaches (Visual Approach A81-11636 Honitor (VAS) VAHDEBBBBG, B. [DFVLB-FB-79-38] B81-10043 Boundary layer measurements on a two-dimensional TBOBBBBB, 6. B. wing with flap Impact of maintainability of life cycle costs [NLB-TB-79009-D] N81-10014 Da 1-11921 VELIEV. B. I. TBBESBBB, B. I. Excitation of a circular array of cylinders with Definitive generic study for the effect of high longitudinal slits lift airfoils on wind turbine effectiveness, A81-12619 executive summary VEBDOOI, A. J. [SEBI/TB-98003-2] H81-11192 Fuel character effects on current, high pressure TISBOBIBOV, 10. P. ratio, can-type turbine combustion systems Automation of aircraft gas-turbine poner plants [AD-A089182] N81-10073 A81-12782 VICKEBS, T. K. TIBLIBG, B. E. Becommended short-term ATC improvements for Simulating study of the interaction between the helicopters. Volume 2: Becommended helicopter propulsion and flight control systems of a ATC training material subsonic lift fan VIOL [AD-A039441] N81-10029 [NASA-TH-81239] B81-11043 Becommended short-term ATC improvements for TIPTOB, A. G. helicopters. Volume 3: Operational description Heapon bay cavity noise environments, data of experimental LOSAN-C flight following (LOFF) correlation and prediction for the B-1 aircraft in the Bouston area [AD-A089770] H81-11778 [AD-AQ89385] S81-10030 TOSLIBSOfl. B. 8. Proposed ATC system for the Gulf of Mexico: Piloted simulation studies of helicopter agility Helicopter operations development program A81-10767 [AD-A089430] B81-10036 TOESEBSOB, 1. S. Preliminary test plans of ATC concepts for longer A multivariate approach to handling gualities term improvement helicopter development program rating scale development [4D-1089H07] . H81-10037 [AD-A089825] H81-11047 Becommendations for short-term simulation of ATC TOBEBS, B. concepts. Helicopter operations development Erosion and impacts on composite helicopter blades program H81-11138 [AD-A089H35] H81-10038 TOYODA, S. Becommended short-term ATC improvements for The emulsion chamber experiment on super-sonic helicopters. Volume 1: Summary of short tern Concorde /Echos/ improvements A81-12176 [AD-A089521] N81-100U1 IBECA, H. VIEBSHA, I. J. Nondestructive evaluation of composite structures Development and application of a moving base A81-11654 visual flight simulator including the design of TBEXLBB, C. A. hydraulic actuators with hydrostatic bearings Flameholding characteristics of a strept-strut H2 A81-11633 fuel-injector for scramjet applications VIGO, C. A81-10711 On screeching jets exhausting from an axisymmetric TBOTB, D. L. supersonic nozzle Fuel character effects on current, high pressure A81-11616 ratio, can-type turbine combustion systems VITBBBA, L. A. [AD-A089182] 881-10073 Performance of a steel spar wind turbine blade on TBOCKEUBBODT. B. the Hod-0 100 XH experimental wind turbine Bow to improve the performance of transport [BASA-Ta-81588] 881-111(18 aircraft by variation of wing aspect-ratio and VOEBSflABB, E. twist /12th Daniel and Florence Guggenheim Hind shear detection from Pen-recorded BLS-flight International Hemorial Lecture/ data A81-11602 A81-11675 TOLLOCH, J. S. VOSEL, B. E. Preliminary airworthiness evaluation AH-IS Fuel character effects on current, high pressure helicopter with ogee tip shape rotor blades ratio, can-type turbine combustion systems [AD-A089625] S81-10C61 [AD-A089182] H81-10073 TD8G, C. VOBGLABB, 0. Experimental and analytical studies of a model Bev interpretations of shock-associated noise with helicopter rotor in hover and without screech [AD-AC8S780] N81-11033 [BASA-lfl-81590] H81-10807 TOOHELA, C. B. VOSKBESBBSKI. G. C. Civil helicopter wire strike assessment study. Beview of numerical methods for the problea of the Volume 2: Accident analysis briefs supersonic flow around bodies at angle of attack [NASA-CS-152390] N81-10019 A81-11639 TOBKE1, B. S. VOSS, B. Pilot-aircraft system reponse to wind shear Calculation of plane transonic flows using the (BASA-CB-33112] H81-10636 integral equation method and shock fitting TOBBIZIABI, B. V. A81-11779 Preliminary design characteristics of a subsonic business jet concept employing an aspect ratio 25 strut braced wing w [NASA-CB-159361] H81-11013 liCKBBLE, C. TIE, I. Development of wind tunnel fan blade made of Civil aviation safety. Ill - Prospects of composite materials improvement tBBB-OD-277-79-0] A81-12096 A81-11900 IAGBEB. B. Simplified vortex models for slender lifting surfaces with leading edge separation A81-11777 VAI GESTEL, G. F. J. A. BALKBB, S. B. Subsequent proof of damage tolerance for a landing Definitive generic study for the effect of high gear component after numerous takeoffs and lift airfoils on wind turbine effectiveness, landings executive samoary A81-11175 £SEBI/TB-98003-2] H81-11192

B-13 BALKEH, I. B. PEES01AL AOIHOB IHDEI

BALKEB, I. B. BILB1. C. G. Experimental application of a vibration reduction The aerodynamic characteristics of some new BAE technique blade sections, and their potential influence on A81-10170 rotor performance RAILAGE, J- B. A81-10769 A controlled evaluation of the differences between RILHELB. K. two approaches to reliability investment screening DFVLB-dynamic model testing in wind tunnels for IAD-A087506] 881-10446 active controls research HALRYI, P. B. A81-11670 The role of flight simulation in the design and An analytical study of landing flare development of the Sea Harrier Nav-Attack Systen [DFVLB-FB-79-40] 881-10062 A81-11635 BIILIABS, B. C. RAJH1LL, B. J. B. Low-speed aerodynamic performance of Flight simulation environmental fatigue crack 50.8-centimeter-diaoeter noise-suppressing propagation in 2024-T3 and 7475-T761 aluminium inlets for the Quiet, Clean, Short-haul A81-11657 Experimental Engine (QCSEE) Flight simulation environmental fatigue crack [NASA-IP-1178] B81-11037 propagation in 2024-T3 and 7475-T761 aluminum BILLIABSOH. E. D., JB. [NLB-HP-80003-0] 881-11415 Hydrogen - Its technology and implications. Volume BABBEB. B. E. 4 - Utilization of hydrogen Maritime patrol aircraft engine study. General A81-11751 Electric derivative engines. Volume 2: IILSOB. B. E, Appendix A. Performance data - GE27/13 study al Definitive generic study for the effect of high turboprop lift airfoils on wind turbine effectiveness, [AD-A089336] H81-10068 executive summary Haritime patrol aircraft engine study. General [SEBI/TB-98003-2] H81-11492 Electric derivative engines. Volume 3: IOLFF. E. G. Appendix B. Performance data - IF34/T7 study A1 Microcracking in graphite-epoxy composites turboprop [AD-A089894] N81-11118 [AD-A089279] U81-10069 ROOD, B. A. HASHBOBH, G. F. Fart-through crack problems in aircraft structures Preliminary design characteristics of a subsonic A81-10362 business jet concept employing an aspect ratio ROBAISCBEK, B. 25 strut braced ving Preliminary airworthiness evaluation AH-1S [NASA-CB-159361] 881-11013 helicopter with ogee tip shape rotor blades BASHIBGTOH. E. S. [AD-A089625] 881-10061 Hind tunnel investigation of the aerodynamic IDEHIBBBEBG, B. hysteresis phenomenon on the F-4 aircraft and Possibilities for the valuation of different its effects on aircraft motion combat aircraft configurations with respect to [AD-A089851] H81-11016 flight mechanics BEDDEBSPOOB, J. E. A81-11607 High lift research and its application to aircraft OLGAr a gust alleviation system for improvement of design passenger comfort of general aviation aircraft A81-11642 A81-11620 REEKS, 0. J. An investigation of scale effects on the transonic flow over swept wings. Part 2: Measurements on a model of a variable-sweep strike-fighter IABAGIIA, 1. configuration The emulsion chamber experiment on super-sonic [ABC-B/B-3842-PT-2] H81-10010 Concorde /Echos/ REI, B. P. A81-12176 On understanding environment-enhanced fatigue IOOHG, B. crack grovth - A fundamental approach Aircraft hydraulic systems dynamic analysis. A81-10719 Volume 6: Steady state flow analysis SSFAN BEILABD. C. computer program technical description Analysis of calculated three-dimensional inviscid £AD-A089240] H81-10055 flow fields vith embedded shock vaves IOOHG, C. G. (presentation of a field solution), part 1 Gyrocompasses. Citations from the International [ESA-TT-558] 881-10017 Aerospace Abstracts data base RBINBBT, I. [BASA-CB-163675] N81-10065 Calibration of the high speed wind tunnel TVH 150 IODBG, J. D. in the supersonic range Exploratory study of hazard mitigation and - - A81-11778 research in the air transport system REISGBBBEB, D. [AD-A089201] S81-11021 Constant-amplitude and flight-by-flight tests on CFBI specimens 881-11133 IBISS, B. ZISO, P. Development of wind tunnel fan blade made of Proceedings of the 1979 Seminar on Air Traffic composite materials Control. Terminal Badar Approach Control [MBB-OD-277-79-0] A81-12096 (1BACON) facility supervisory desk complex BEBSCBOLZ. A. G. [AD-A089914] 881-11024 A comparison of Hewton-like methods for the ZOBXBSKAS. 1. transonic small disturbance equation Hew terminal radar approach control in tower cab [AD-A090270] 881-11017 ccncept for love Field, Dallas, Texas BBIIB, B. P., JE. [AD-A089996] N81-11025 The status of rotor noise technology ZOBIHSKAS. T. E. A81-12737 Proceedings of the 1979 Seminar on Air Traffic RICKBL, I. Control. Terminal fiadar Approach Control Design to cost and systems, LCC (TBACON) facility supervisory desk complex H81-11920 [AD-A089914] H81-11024 BICKEHBEISEB. 1. J. Comparisons of four alternative powerplant types for future general aviation aircraft [NASA-TB-81584J S81-10067 BIDIBG, K. A study of the air inlet efficiency of a combat aircraft concept with dorsal inlet A81-11615

B-14 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 132) FEBRUARY 1981

Typical Contract Number Index Listing

B00014-75-C-0543 SASl-16000 N81-11013 A81-10719 862269-78-00114 N81 10068 NASA ACCESSION YF53536091 881- 10079 NUMBER ZE54502001 881- 11120 505-01 881- 11039 505-05 881- 11037 Listings in this index are arranged alphanumerically by contract number. 505-31-13-01 B81 10004 505-31-53-01 H81 10005 Under each contract number, the accession numbers denoting documents 505-31-33-02 H81 11422 that have been produced as a result of research done under that contract 505-42-21 881- 10077 are arranged in ascending order with the IAA accession numbers appearing 505-42-71 881- 11043 first. The accession number denotes the number by which the citation is 505-13-23-01 881- 11032 identified in either the tAAor SWff section. 512-55-11 881-10021 530-01-13-01 881- 11013 532-02-11 881- 11044 532-04-11 881- 10054 534-03-23-01 881-11113 AP PBOJ. 649E EX-76-I-01-1028 881-10034 881-11(1118 AF PfiOJ. 1900 FAA PBOJ. 022-242-830 H81-10580 881-11290 N81-10581 FAA PBOJ. 219-151-110 AP PBOJ. 2003 N81-11021 881-10063 FBV-F-K-82223-76-001-21-001 AF PBOJ. 2307 H81-10013 881-10008 F04701-79-C-0080 AF PBOJ. 2308 H81-11118 881-10128 F08635-77-C-0377 AF PBOJ. 2313 U81-10024 081-11016 F08635-79-C-0010 B81-11047 H81-10080 AF PBOJ. 2401 F19628-78-C-0006 H81-11778 M81-10034 AF PBOJ. 3018 S81-10039 S81-10073 F19628-80-C-0002 H81-10081 B81-11028 AP PBOJ. 6302 F33615-71-C-2016 N81-11233 1181-10055 AF PBOJ. 7351 F33615-76-C-2081 H81-100714 N81-10081 881-11041 P33615-76-C-3111 AF-AFOSB-77-3308 B81-10152 A81-11820 P33615-76-C-5172 AP-AFOSB-0006-79 N81-10071 N81-10128 F33615-76-C-5311 AF-AIOSB-0042-79 A81-11338 B81-110U6 F33615-77-C-5172 BHVG-T/BF-41/80030/81429 S81-11041 A81-11777 F33615-78-C-0122 DA PBOJ. U1-62209-AH-76 1181-10056 881-11031 H81-10057 DA PBOJ. 1S1-62113-A-661 881-10058 B81-11116 H81-10059 DA PBOJ. 2Q1-62722-A-765 F33615-78-C-1559 H81-11035 H81-10063 DAAG46-78-C-0056 F33615-78-C-2006 H81-11116 H81-10073 DAAK51-78-C-0026 P33615-78-C-3011 B81-11034 A81-11601 DE-AC05-77CS-05438 F33615-78-C-3028 H81-11500 H81-10008 DE-AC05-77CS-55438 P33615-79-C-3208 H81-11513 H81-11778 DOT-FA70iAI-175 F33657-77-C-0391 H81-10034 881-10072 DOT-FA788A-4159 P49620-77-C-0023 H81-10023 881-11012 DOT-FA78iAI-895 P49620-78-C-0047 881-11028 881-11771 DOT-FA79RA-4279 F49620-79-C-0158 S81-10029 H81-110I17 881-10030 BASi-3199 881-10576 881-10036 881-10577 881-10037 BAS1-16000 881-11013 H81-10038 SAS2-10333 881-11014 881-10041 BAS2-10505 881-10019 POI-PA80iA-a370 8AS3-20073 881-11953 H81-10032 BAS5-25114 881-10020 EF-76-5-01-2479 8AS8-33158 881-10636 A81-10810 BIVB-1812 881-10014 EG-77-C-01-1042 BB PBOJEC1 036-097 881-11192 A81-10749

C-1 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037(132^ 4. Title and Subtitle 5. Report Date AERONAUTICAL ENGINEERING February 1981 A Continuing Bibliography (Supplement 132) 6. Performing Organization Code

7. Author(s) 8. Performing Organization Report No.

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

National Aeronautics and Space Administration 11. Contract or Grant No. Washington, D.C. 205^6

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

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

This bibliography lists 3^2 reports, articles, and other documents introduced into the NASA scientific and technical information system in January 1981.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement

Aerodynamics Aeronautical Engineering Unclassified - Unlimited Aeronautics Bibliographies

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price* Unclassi fied Unclass ified 112 $5.00 HC

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