Case File C-0-11-5441Y

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AERONAUTICAL KTI1 IKT1 E 1NJI1N EL

A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplement 59

JULY 1975

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION ACCESSION NUMBER RANGES

Accession numbers cited in this Supplement fall within the following ranges:

STAR (N-10000 Series) N75-19126-N75-21218

IAA (A-10000 Series) A75-26156-A75-29188

This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by Informatics Information Systems Company. NASA SP-7031 (59)

AERONAUTICAL ENGINEERING

A Special Bibliography

Supplement 59

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in June 1975 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA).

Scieii:,jje and Technical li/onnaijm, 0//ice fiJ1Y 1975 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION EJ Wa.hiiiginn. D. C This Supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161,for $4.00. For copies mailed to addresses outside the United States, add $2.50 per copy for handling and postage. INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Administra- tion this publication has been prepared by the National Aeronautics and Space Administra- tion 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 Special Bibliograph y ( NASA SP-7037) lists 368 reports, journal articles, and other documents originally announced in June 1975 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IA A). 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, fAA Entries and STAR E,itries,in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in fAA or 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 (A75-10000 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 are available at $5.00 per document up to a maximum of 20 pages. The charge for each additional page is 25 cents. Microfiche"' are available at the rate of $1.50 per microfiche for documents identified by the "i" symbol following the accession number. A number of publications, because of their special characteristics, are available only for reference in the AIAA Technical Information Service Library. Minimum airmail postage to foreign countries is $1.00. Please refer to the accession number. e.g. (A75-10763). when requesting publications.

STAR ENTRIES (N75-10000 Series)

One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. 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 to U.S. customers at the price shown in the citation following the letters HC (hard, paper, or facsimile copy). Customers outside the U.S. should add $2.50 per copy for handling and postage charges to the price shown. (Prices shown in earlier STAR volumes. 1962-1974, have been superseded but may be calculated from the number of pages shown in the citation. The price schedule by page count was given in the last STAR issue of 1974 or may be obtained from NTIS.)

Microfiche' are available at a standard price of $2.25 (plus $1.50 for non-U.S. customers) regardless of age for those accessions followed by a "/" symbol. Accession numbers followed by a " +" sign are not available as microfiche because of size or reproducibility.

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 Unit.

NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followed by the " s" symbol), use the N accession number.

NASA patent applications (only the specifications are offered) should be ordered by the US- Patent-AppI- SN number.

Non-NASA publications (no asterisk) should be ordered by the AD. PEI, 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.

Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. The current price and order number are given following the availability line. (NTIS will fill microfiche requests, at the standard $2.25 price, for those documents identified by a " p " symbol.)

(1) A microfiche is a transparent sheet of film. 105 by 148mm in size containing as many as 60 to 98 pages of information reduced to micro m"as (Not to exceed 26: I reduction). Iv 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.. SW., 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.

Avail: ERDA Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of Energy Research and Development Administration reports, usually in Services available from the microfiche form, are listed in Nuclear Science Abstracts. ERDA and its depositories are described in a booklet. Science Information Available from the Energy Research and Devopment Administration (TID-4550), which may be obtained without charge from the ERDA Technical Information Center.

Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) at $10.00 each and microfilm at $4.00 each regardless of the length of the manuscript. Handling and shipping charges are additional. All requests should cite the author and the Order Number as they appear in the citation.

Avail: USGS. Originals of many reports from the U.S. Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this Introduction. The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction.

Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S. by Pendragon House. Inc. (PHI). Redwood City, California. The U.S. price (including a service and mailing charge) is given, or a conversion table may be obtained from PHI.

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: ZLDI. Sold by the Zentralstelle für Luftfahrtdokumefltation und -Information. Munich. 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 Office. Sold by Commissioner of Patents. U.S. Patent 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.

V GENERAL AVAILABILITY

All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and /AA 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.

SUBSCRIPTION AVAILABILITY

This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplements, excluding the annual cumulative index, is $18.00. All questions relating to subscriptions should be referred to the NTIS.

vi ADDRESSES OF ORGANIZATIONS

American Institute of Aeronautics Pendragon House. Inc. and Astronautics 899 Broadway Avenue Technical Information Service Redwood City, California 94063 750 Third Ave. New York, N.Y. 10017 Superintendent of Documents U.S. Government Printing Office British Library Lending Division, Washington, D.C. 20402 Boston Spa, Wetherby, Yorkshire, England University Microfilms Commissioner of Patents A Xerox Company U.S. Patent Office 300 North Zeeb Road Washington, D.C. 20231 Ann Arbor, Michigan 48106

Energy Research and Development University Microfilms, Ltd. Administration Tylers Green Technical Information Center London, England P.O. Box 62 Oak Ridge, Tennessee 37830

ESRO/ E LDO Space Documentation Service U.S. Geological Survey European Space Research Organization 1033 General Services Administration Bldg. Washington, D.C. 20242 114. ay. Charles de Gaulle 92200 Neuilly-sur-Seine. France

Her Majesty's Stationery Office U.S. Geological Survey P.O. Box 569, S.E. 1 601 E. Cedar Avenue London, England Flagstaff, Arizona 86002

NASA Scientific and Technical Information U.S. Geological Survey Facility 345 Middlefield Road P.O. Box 8757 Menlo Park, California 94025 B.W.I.Airport, Maryland 21240

U.S. Geological Survey Bldg. 25, Denver Federal Center National Aeronautics and Space Denver, Colorado 80225 Administration Scientific and Technical Information Office (KSI) Zentralstelle fur Luftfahrtdoku- Washington. D.C. 20546 mentation und -Information 8 Munchen 86 National Technical Information Service Postfach 880 Springfield, Virginia 22161 Federal Republic of Germany

vii TABLE OF CONTENTS

Page

IAA Entries ...... 243 STAR Entries ...... 261

Subject Index ...... A-i Personal Author Index ...... B-i Contract Number Index ...... C-i

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED AVAILABLE ON DOCUMENT MICROFICHE '3 ______ACCESSION NUMBER-40 N7510005*# Lockheed-Georgia Co.. Marietta. CORPORATE 1—ø'-GROUND EFFECT FOR V/STOL AIRCRAFT CONFIGURA- SOURCE I TIONS AND ITS SIMULATION IN THE WIND TUNNEL. TITLE I PART 3: THE TANGENTIALLY BLOWN GROUND AS AN ALTERNATIVE TO A MOVING GROUND: APPLICA ON PUBLICATION TO THE NASA-AMES 40 BY 80-FOOT WIND TUNNEJ DATE AUTHORS •j—.- J. E. Hackett. E. B. Praytor. and E. 0. Caldwell (1973] ^_9p AVAILABILITY refs SOURCE (Contract NA S2-6690) Avail: NTIS HC $4.25 CSCL O1B CONTRACT...... A set of conceptual drawings showing the application of OR GRANT I slot-blowing boundary layer control to the 40- by 80-foot wind I tunnel is presented. In small scale pilot experiments unswept I slots were used, fed by a below-floor plenum. The model was REPORT sting mounted and its wing was unswept. However, design for NUMBER the Ames tunnel was heavily constrained, both by under floor balance mechanisms and by a large turntable. An over floor supply system was therfore designed. A description of appropriate procedures for using the floor tangential blowing system is given. Though some of the operating graphs are specific to the design for the Ames tunnel, both non-dimensional plots and the approach generally are widely applicable. Author TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED AVAILABLE ON DOCUMENT MICROFICHE

ACCESSION A75-10336 * # Sealing technology for aircraft gas turbine - TITLE NUMBER en in L. P. Ludwig and R. L. Johnson (NASA, Lewis Research Center, Cleveland, Ohio). American Institute of Aeronautics and AUTHORS Astronautics and Society of Automotive Engineers, Propulsion I AUTHORS' Conference, 10th, San Diego, Calif., Oct 2'723, 1974, AIAA Paper AFFILIATION 74-1188. p.23refs.12 I Experimental evaluation under simulated engine conditions TITLE OF revealed that conventional mainshaft seals have disadvantages of high _,_ PERIODICAL gas leakage rates and wear. An advanced seal concept, the self-acting face seal, has a much lower gas leakage rate and greater pressure and PUBLICATION speed capability. In endurance tests (150 hr) to 43,200 rpm the DATE self-acting seal wear was not measurable, indicating that noncontact sealing operation was maintained even at this high rotative speed. A review of published data revealed that the leakage through gas path seals has a significant effect on thrust specific fuel consumption, stall margin, and engine maintenance. Reducing leakages by reducing seal clearances results in rubbing contact, and then the seal thermal response and wear determines the.final seal clearances. (Author)

VIII AERONAUTICAL ENGINEERING

A Spec/al Bibliography (Suppl. 59) J U LY 1975

nozzle, and the analysis concerns in particular the effect of the interior region between the nozzle end and the area where the ring jet comes together to form a single jet on the sound field. This interior region has Certain resonating properties. The analysis is carried out in a linear approximation for both planar and cylindrical models and for the two cases when the disturbanles on opposite sides of the jet are either in phase or antiphase. Expressions are derived for certain characteristic frequencies at which disturbances in the jet and the interior region significantly exceed those in the IAA ENTRIES external field. P.T.H.

A75.26312 Eigenvalue/eigenvector assignment for multivariable systems. S. Srinathkumar and R. P. Rhoten (Oklahoma State University, Stillwater, Okla.). Electronics Letters, vol. 11, Mar. 20, 1975. p. 124, 125. A procedure is described which, through linear state feedback, both assigns pole locations (eigenvalues) and specifies parts of the closed-loop modal (eigenvector) structure. The technique is il- 26195 A non-uniqueness of the hypersonic boundary lustrated by synthesizing a controller for the lateral dynamics of a A75. (Author) layer. S. N. Brown and K. Stewartson (University College, London, high-performance aircraft. England). Quarterly Journal of Mechanics and Applied Mathematics, vol. 28, Feb. 1975, p. 75 .90. 19 refs. Using the tangent-wedge approximation to describe the inviscid A75-z6410 # Nonlinear torsional vibrations of thin-walled portion of the flow field, Neiland (1970) discovered a nonuniqueness beams of open section. C. K. Rao )Andhra University, Waltair, of the solution in the neighborhood of the leading-edge of a flat plate India). ASME, Transactions, Series E - Journal of Applied Mechanics, in free hypersonic flow. The nonuriiqueness is associated with a vol. 42, Mar. 1975, p. 240-242. 10 refs. single eigenvalue and eigenfunction occurring between certain terms An attempt has been made to derive and solve the governing of the power series that expresses the pressure. More accurate differential equation of large amplitude torsional vibrations of simply estimates of the eigenvalue are obtained by using the full inviscid supported doubly symmetric thin-walled beams of open section. equations instead of the tangent-wedge approximation. A unique Graphs indicating the influence of large amplitudes on nonlinear eigensolution is obtained for the hypersonic boundary-layer equa- period of torsional vibrations for various nondimensional beam tions, and the relationship between this eigensolution and the constants are presented. (Author) eigensolutions of the reduced Navier-Stokes equations in the limit is examined. V.P.

A75-26414 # The disappearance of the wake shock behind a A75-26212 * Starting vortex, separation bubbles and stall - cylinder in a supersonic flow at high Reynolds number. M. M. A numerical study of laminar unsteady flow around an airfoil. U. B. Zdravkovich (Salford, University, Salforcl, Lancs., England) and G. L. Mehta (Illinois Institute of Technology, Chicago, Ill.; NASA, Ames Hodge (Hawker Siddeley Aviation, Ltd., Hatfield, Herts., England). Research Center, Computational Fluid Dynamics Branch, Moffett ASME, Transactions, Series / - Journal of Fluids Engineering, vol. 97, Field, Calif.) and Z. Lavan (Illinois Institute of Technology. Chicago, Mar. 1975, p. 120-122.5 refs. Ill.). Journal of Fluid Mechanics. vol. 67. Jan. 28. 1976, p. 227-256. The unexpected disappearance of the wake shock behind a 18 refs. Contract No. F44620-69-C-0022. Project THEM IS. cylinder in supersonic flow at a high Reynolds number was studied in The stalling characteristics of an airfoil in a laminar viscous a supersonic wind tunnel of the intermittent blow-down type. For a incompressible fluid are investigated. The governing equations in flow at a Mach number of 2.4 and a Reynolds number of 377.000 a terms of the vorticity and stream function are solved using an detachable bow wave was found to form in front of a 3/4-in. implicit finite-difference scheme and point successive relaxation diameter cylinder with a subsonic wake, while a wide wake without procedure. The development of the impulsively started flow, the wake shocks formed behind the cylinder. Wake widening was similar initial generation of circulation, and the behavior of the forces at to that observed in the transcritical range at subsonic flow. S.D. large times are studied. Following the impulsive start, the lift is at first very large and then it rapidly drops. The subsequent growth of circulation and lift is associated with the starting vortex. After A75-26463 The generation of sound by aerodynamic incipient separation, the lift increases owing to enlargement of the sources in an inhomogeneous steady flow. M. S. Howe (Cambridge separation bubble and intensification of the flow rotation in it. The University, Cambridge, England). Journal of Fluid Mechanics, vol. extension of this bubble beyond the trailing edge causes it to rupture 67, Feb. 11, 1975, p. 597-610. 19 refs. Research supported by Rolls and brings about the stalling characteristics of the airfoil. Sub- Royce /1971/, Ltd. sequently, new bubbles are formed near the upper surface of the airfoil and are swept away. The behavior of the lift acting on the airfoil is explained in terms of the strength and sense of these bubbles. (Author) A75-26466 The expansion of a hypersonic turbulent boundary layer at a sharp corner. A. W. Bloy (Manchester, Victoria University, Manchester, England). Journal of Fluid Mechanics. vol. 67, Feb. 25. 1975, p. 647-655. 12 refs. A75-26234 # Development of acoustic disturbances in supersonic annular jets (Razvitye akusticheskikh vozmushchenii v A sharp wedge expansion flap was tested in the von Karman sverkhzvukovykh kol'tsevykh struiakh). M. G. Lebedev and G. F. Institute Longshot tunnel at Mach 16 and data on the wall pressure and heat transfer were obtained. Pitot pressure measurements in the Telenin. Moskovskii Gosudarstvennyi Universitet, Institut Mekhaniki, er just ahead of the expansion flap were also made. The Nauchnye Trudy, no. 30, 1973. p. 182-199. In Russian. boundary la y The present work investigates theoretically the interaction of a surface data are compared with predictions from a characteristics supersonic jet issuing from an annular nozzle with an external solution for the boundary-layer expansion and from a simple acoustic field. The sound waves are taken to be traveling towards the heat-transfer theory. (Author) 243 A75-26469

A75-26469 On the viscous flow about the trailing edge of rapid scanning are presented. It is concluded that it is necessary to: a rapidly oscillating plate. S. N. Brown and P. G. Daniels (University (1) assure that the modal characteristics of the fuselage are carefully College. London. England). Journal of Fluid Mechanics. vol. 67. Feb. measured, (2) respect as much as possible the linkage conditions of 25, 1975. p. 743-761. 13 refs. the rotor blades during the wall assay, (3) consider a number of The incompressible laminar flow in the neighborhood of the modes that are sufficient for the subsystems, in particular the trailing edge of an aerofoil undergoing sinusoidal oscillations of high lowest-frequency modes, corresponding to the movements of the frequency and low amplitude in a uniform stream is described in the rigid body, and (4) obtain the generalized masses of the blades with limit as the Reynolds number R tends to infinity. The aerofoil is maximum precision, as well as their masses and inertias. S.J.M. replaced by a flat plate on the assumption that leading-edge stall does not take place. It is shown that, for oscillations of nondimensional frequency O(R to 1/4 power) and amplitude O(R to the negative A75-26480 # Unsteady lift forces on a vibrating cylinder in 9/16 power), a rational description of the flow at the trailing edge is a supercritical flow (Portances instationnaires sur uncyliidréibiiint bated on a subdivision of the boundary layer above the plate into dans un écoulement supercritique). E. Szechenyi and H. Loiseau five distinct regions. Asymptotic analytic solutions are found in four (ONERA, Chétillon-sous-Bagneux, Hauts-de-Seine, France). La Re- of these, whilst in the fifth a linearized solution yields an estimate cherche Aerospatiale, Jan-Feb. 1975, p. 45-57. 11 refs. In French. for the viscous correction to the circulation determined b y the Kutta Results previously obtained on a clamped cylinder are reviewed, condition. (Author) and the vibrating mockup and testing and measurement methods used in the present experiment are described. The present results are interpreted and autoexcitation conditions are deduced from them. It A75.26476 # Experimental and theoretical analysis of three is found by comparison that the lift forces have similar behaviors ass dimensional turbulent boundary layers in a curved supersonic function of reduced frequency in supercritical vs subcritical flows. channel (Analyse expérimentale et théorique des couches limites On the other hand, in a transcritical regime, the quasi-aleatory turbulentes tridimensionnelles dans un canal supersonique courbe). J. turbulent flow is not as clearly coupled to the movements of the Cousteix and R. Michel (Toulouse. Centre d'Etudes et de Re- cylinder. S.J.M. cherches, Toulouse, France). La Recherche Aérospatiale, Jan-Feb. 1975, p. 1-10. In French. Research supported by the Direction des A75-26498 The aircraft accident (Der Flugunfalfl. W. Recherches et Moyens d'Essais. Politt. Braunschweig, Richard Carl Schmidt und Co., 1974. 210 p.22 The developing three-dimensional turbulent boundary layer on refs. In German. $13.65. the side wall of a curved nozzle in supersonic flow is studied. The investigation of aircraft accidents as a responsibility of the Numerous measurements of the mean velocity and of the direction state is considered along with questions regarding the objectives of of the velocity in the boundary layer and surface flow visualizations the investigation of accidents and disturbances. Details concerning constitute the experimental part of the study. A detailed determina- the conduction of the investigation are examined, taking into tion of the wall static pressure field permits the calculation of the account organizational aspects of accident investigations, studies external streamlines by means of Euler's equations. These results are conducted by experts, the equipment employed, and the various compared with those calculated by the method of characteristics. An details which have to be attended to during the investigation. integral prediction method is used to calculate the development of Specific investigative aspects applying in the case of glider accidents the boundary layer. The comparison between the experimental and and military aircraft are discussed along with the determination of theoretical results shows a good level of agreement. An attempt at the causes of accident and regulations and laws related to aviation channeling the boundary layer flow is realized by means of fences. accidents. G. R. (Author)

A75-26499 Air Europe: The policy of cooperation among airline companies of the European Six (Air Europe: La politique de A75-26477 # A method for calculating unsteady forces due cooperation entre les compagnies aériennes de l'Europe des Six). C. to interaction between tail surfaces (Méthode de calcul des forces Delepiere-Nys (Bruxelles, Université Libre, Brussels, Belgium). instationnaires dues a l'interactjon entre derive et empennage Brussels, Editions de l'Université de Bruxelles, 1974. 507 p. 83 refs. horizontal). Y. Akamatsu (ONERA, Chátillon-sous-Bagneux, Hauts- In French. $22.50. de-Seine, France). La Recherche Aérospatiale, Jan-Feb. 1975, p. Difficulties inherent in the present civil aviation company 11-20. In French. transportation system, air transport inside the CEE, air transport in A calculation programme of the unsteady aerodynamic forces areas outside of Europe (such as the U.S.), and perspectives on the on a set of surfaces including an horizontal elevator and a vertical fin, proposed cooperation policy are discussed. It is shown how such a applying the potential method, has been Written. This method differs cooperation would be in the best economic interests of all nations from the classical ones in that the normal velocity is obtained by concerned. The controversy that developed over Article 84 of the numerical derivation of the potential calculated on the lifting Rome agreement is described. Various past cooperational organiza- surfaces and in their immediate proximity. It permits a notable tions, and the technical advances that accrued to them, are simplification of the programming and gain in computation time. considered. S.J.M. The comparison of the results with those obtained by other methods presents a good agreement. (Author) A75-26533 Analysis of wreckage. K. F. Packer (Packer Engineering Associates, Naperville, III.) and C. A. Mono. (Annual Air A75-26479 # Determination of the dynamic characteristics Law Symposium on Products Liability in Aviation Litigation, 8th, of a helicopter by the branch-modes method (Determination des Dallas, Tex., Mar. 14 . 16, 1974.) Journal of Air Law and Commerce. caractéristiques dynamiques d'un hIlicoptere a partir des modes vol. 40, Summer 1974, p. 447458. partiels). H. Loiseau and J.-R. Nicolas (ONERA, Châtillon-sous- The procedures and philosophy of accident investigation are Bagrieux, Hauts.de-Seine, France). La Recherche Aérospatiale, Jan.- discussed, taking into account case studies which illustrate the Feb. 1975, p. 35-44. In French. application of the general approach to be followed in the investiga- Experiments are related allowing an estimation of the precision tion. Recant advances in investigative techniques are examined, required in data recording in order to obtain correct calculation giving attention to the scanning electron microscope, the electron results, and demonstrating the validity limits of the branch-modes microprobe chemical analyzer, and infrared imaging. It is pointed out method as applied to an actual helicopter. The mockup and the that the new techniques and instruments play an important role in testing means used are described, and frequency graphs taken by determining aircraft accident causality. G. R.

244 A75-26697

A75-26553 i Effect of interference between moving blade A75-26671 # Development and experimental evaluation of a rows on cascade flutter. I - Experiment on compressor cascade in numerical method for solving the inverse axisymmetric problem in an flexure mode. H. Kobayashi (National Aerospace Laboratory, axial turbine stage with given velocity (Razrabotka i eksperi. Tokyo, Japan), H. Tanaka. and H. Maruta (Tokyo. University, mental'naia otsenka chislennogo metoda reshenila obratnoi osesim- Tokyo, Japan). .JSME. Bulletin, vol. 18, Feb. 1975, p. 140. 150. 11 metrichnoi zadachi v osevoi turbinnoi stupeni pri zadanii skorosti). refs. A. M. Topunov, B. A. Tikhomirov, and N. P. Nechaev. Akademiia The effects of interference between stationary and moving blade Nauk SSSR, lzvestlla, Energetika i Transport, Jan.-Feb. 1975, p. rows on the nonstall cascade flutter in flexural mode are studied 145-156. 5 refs. In Russian. experimentally under the actual operating conditions of an axial-flow compressor. Specially designed flexible stator vanes and rigid rotor blades were used. The pronounced aerodynamic effect of cascade A75-26672 # Elementary method of graphic replotting of a interference on flutter is demonstrated. It is shown that the flutter characteristic of an uncooled turbocompressor when the intake speed is decreased by the effect of the rotor cascade upstream of the temperature and number of revolutions are varied (Elementarnyi stator and is increased by its effect downstream of the stator. V.P. sposob graficheskogo perestroeniia kharakteristiki neokhlazhdae- mogo turbokompressora pri izmenenii temperatury vsasyvaniia i chisla oborotov). I. E. Rozenshtein. Akademiia Nauk SSSR, lzvestiia, A75-26554 // Lift coefficients on a supercavitating jet- Energetika i Transport. Jan.-Feb. 1975, p. 171-173. In Russian. flapped foil between rigid walls. T. Kida and V. Miyai (Osaka Prefecture. University, Sakai, Japan). JSME, Bulletin, vol. 18, Feb. 1975, p. 151 . 158. 7 refs. A75-26684 The impingement of non-uniform, axisym- The method of matched asymptotic expansions is applied to the metric, supersonic jets on a perpendicular flat plate. J. H. Gummer first-order theory on the flow past a two-dimensional supercavitating (Snowy Mountains Engineering Corp., Australia) and B. L. Hunt jet-flapped foil in a wall tunnel, and a solution (the slope of the jet) (Bristol, University, Bristol, England). (Israel Conference on Me- of the governing integro .differential equation is obtained and chanical Engineering, 8th, Haifa, Israel, Sept. 23, 24, 1974.) Israel represented as the series expansion in ascending powers of delta and Journal of Technology, vol. 12, no. 3-4, 1974, p. 221-235. 16 refs. log delta multiplied by functions of the distance from the trailing The impingement flow produced by directing a supersonic, edge, where delta is a small perturbation quantity proportional to the axisymmetr ic jet of air on to a perpendicular flat plate at small jet momentum coefficient. Moreover, the lift derivatives with respect displacements has been investigated experimentally and theoretically to incidence and jet deflection are obtained as the series expansions for a total of eight different jets from conical nozzles operated in ascending powers of delta and log delta. (Author) underexpanded. Shadowgraph photographs of the impingement region and measured surface pressures are presented. The photographs show that a number of shock wave shapes are possible, A75-26589 * Miniature probes for use in gas turbine testing. depending on the conditions in the free jet. The surface pressure G. E. Glawe and L. N. Krause (NASA, Lewis Research Center, distributions are mostly similar to each other inform, with the plate Cleveland, Ohio). Society of Automotive Engineers, Automotive sonic point lying in the neighborhood of the jet edge. Under some Engineering Congress and Exposition, Detroit, Mich., Feb. 24-28, conditions, a stagnation bubble is found to exist in the shock layer. 1975, Paper 750094. 8 p. 7 refs. A new formulation of the single strip approximation of the method Because of space limitations and system complexity in many of integral relations is given. The results for shock shape and surface applications associated with gas turbine testing, extremely small flow pressure obtained from this method agree quite well with the measuring probes have sometimes been required. This paper presents experimental results in the inner part of the shock layer but the several examples of these miniature probes - null type as well as fixed calculation is less satisfactory in the region outside of the jet shock. position - which have proved useful in aircraft and space power An explanation is given for this discrepancy. (Author) systems component testing and are applicable to automotive gas turbine testing. These probes are used to determine component or system performance from the measurement of gas temperature as A75-26685 Heat transfer in separated and reattached well as total and static pressure, and flow direction. Detailed flows - An annotated review. L. S. Fletcher, D. G. Briggs, and R. H. drawings of the sensors are presented along with experimental data Page (Rutgers University, New Brunswick, N.J.). (Israel Conference covering the flow characteristics over the range of intended use. on Mechanical Engineering, 8th, Haifa, Israel, Sept. 23, 24, 1974.) (Author) Israel Journal of Technology, vol. 12, no. 3-4, 1974. p. 236-261. 275 refs. Contract No. F44520-68-C-001 8. This paper reviews more than 280 references dealing with A75-26591 • Tests of laser metal removal for future flexible theoretical and/or experimental studies of convective heat transfer at rotor balancing in engines. J. M. Tessarzik (Mechanical Technology, solid boundaries adjacent to regions of flow separation, in particular Inc., Latham, N.Y.) and D. P. Fleming (NASA, Lewis Research the base and reattachment surfaces. These studies are divided into Center, Cleveland, Ohio). Society of Automotive Engineers, Auto- four major categories: subsonic, two-dimensional supersonic, axisym- motive Engineering Congress and Exposition. Detroit, Mich., Feb. metric supersonic, and booster base heating, and are further divided 24-28, 1975, Paper 750170. 11 p. 10 refs. Contracts No. into various model geometries. For each category, the theoretical F33614-72-C-1801; No. NAS3-1 4420. studies are summarized and insofar as possible, results of the This paper describes recent developments in the flexible rotor experimental investigations are correlated. Some theories are recom- balancing technology area, with particular emphasis on methods for mended for the prediction of heat transfer, and regions for further the addition and removal of correction weights. The currently investigation are delineated. (Author) existing multiplane-multispeed balancing procedure permits one-step balancing of final shaft-bearing assemblies simultaneously in a number of planes and at a number of speeds. Temporary addition of trial weights to the rotor, and the addition or subtraction of A75-26697 # A problem in supersonic jet theory (0 pro- permanent Corrections, are presently performed manually in the blema de teoria jeturilor supersonice). C. lacob (Bucuresti, balancing process. The addition of a computer-controlled laser device Universitatea, Bucharest, Rumania). Studii si Cercetari Matematice, to the balancing system shows promise of eliminating direct operator vol. 27, no. 1, 1975, p.47-66.8 refs. In Rumanian. contact with the rotor in the balancing process, and thus could Prandtl's problem of a supersonic jet in expansion in an provide a considerable increase in the precision level at a critical step atmosphere at rest is considered, where the pressure at the nozzle in the procedure. (Author) mouth is greater than the atmospheric pressure. The analysis is

245 A75-26700

carried out within the framework of Ackeret's approximate method demonstrations, and the techniques used to record voice and data as of linear supersonic aerody namics. The length of the first wave and well as some preliminary results obtained during the ATC demonstra- the maximum width of the jet are obtained. A formula that relates tions. (Author) wave length and average jet width is proposed, which can replace the formulae of Prandtl and Pack. P.T.H. A75-26724 # An experimental TDMA network for airborne warning and control systems interoperability, demonstrations. F. W. Lightfoot, W. B. Smith (Boeing Aerospace Co., Seattle, Wash.), S. G. A75-26700 # The computation of aerodynamic loads on Wilson (Boeing Commercial Airplane Co., Seattle, Wash.), and A. R. helicopter blades in forward flight, using the method of the Petrino (Mitre Corp., Bedford, Mass.). acceleration potential. T. van Holten. Delft, Technische Hogeschool, American Institute of Aero- nautics and Astronautics, Digital Avionics System Conference, Doctor in de technische Wetenschappen Thesis, 1975. 131 p. 11 refs. Boston, Mass, Apr. 24, 1975, Paper 75-563. The method of the velocity potential is examined and a 11 p. An experimental Time Division Multiple Access (TDMA) Com- description is given of the theory of the acceleration potential. munications System operating on a single communications channel is Attention is given to the calculation of steady, two-dimensional developed for the System Integration Demonstration (SID) phase of aerofoil characteristics with the aid of the linearized pressure the Airborne Warning and Control System (AWACS). The descrip- method, the classical lifting line theory, higher-order lifting line tion covers the SID TDMA network with its airborne and ground theory, the far pressure field of a wing, and the swept wing executing terminals, the AWACS installation, the airborne relay station, and a harmonic pitching motion. The boundary conditions pertaining to the spread spectrum modem. Tests show that the TDMA system is the blade of a helicopter rotor in steady forward flight are discussed highly versatile in the dissemination of airborne and ground together with the solution of the boundary value problem for a surveillance, command and control data in tn-services tactical helicopter blade. G. R. exercises. S.D.

A75-26720 # Digital avionics-overview - Airframe manu- A75-26725 # Flight-critical digital control system evalua- facturer's viewpoint. R. Dunn (Boeing Commercial Airplane Co., tion. L. E. Fairbanks (General Electric Co., Binghamton. N.Y.) and J. Seattle, Wash.). American Institute of Aeronautics and Astronautics, E. Templeman (Boeing Commercial Airplane Co.. Seattle, Wash.). Digital Avionics System Conference, Boston, Mass, Apr. 2-4, 1975, American Institute of Aeronautics and Astronautics, Digital Avionics Paper 75552. 6 P. The system requirements in new aircraft are related to changes System Conference, Boston, Mas&, Apr. 24, 1975, Paper 75-566. 15 regarding the criteria used to rate the worth of an aircraft. Aspects of p. 6 refs. Research sponsored b y the U.S. Department of Transporta- aircraft economics, noise, and ecological considerations have become tion. very important. Better performance at lower costs can be provided The flight controls development study task was developed to by a utilization of advanced digital technology in place of the analog permit technology investigations into selected areas of triple-channel, systems employed in present aircraft. Research and development fail-operat iona l , analog and digital system designs. An application programs conducted in the area of digital technology b y an American model based on a flight-critical control system is considered. A aerospace corporation are discussed. G. R. system description is given, taking into account the laboratory configuration and analog subsystem, the incremental control processor subsystem, and the whole word computer subsystem. Perfor- A75-26721 # Digital avionics - An overview. R. W. Meier- mance comparisons are discussed along with aspects of software (FAA, Systems Research and Development Service, Washington. development and control. Attention is also given to the preflight D.C.) - American Institute of Aeronautics and Astronautics, Digital test/failure mode and effects studies. G. R. Avionics System Conference, Boston, Mass., Apr. 24, 1975, Paper 75-553.4 p. The use of digital systems in ATC operations is considered, A75-26726 # Flight test of a digital guidance and control giving attention to computations performed at far greater precision system in a DC-10 aircraft. S. S. Osder, D. C. Mossman, and B. T. and lower cost than feasible with analog techniques. The introduc- Devlin (Sperry Rand Corp.. Sperry Flight Systems Div., Phoenix, tion of digital systems in avionics is not to be confined to the area of Ariz.). American Institute of Aeronautics and Astronautics. Digital navigation. It is pointed Out that a system management onboard Avionics System Conference, Boston, Mass., Apr. 24, 1975, Paper computer could have avoided a recent accident, in which an aircraft 75-567. 11 p. ran Out of fuel before reaching its destination. G. R. A digital guidance and control system flight tested in a DC-10 aircraft in the summer of 1974 confirmed that system's monitoring techniques, certifiable control law software (including automatic A75-26723 # Air Traffic Control demonstration aspects of landing), and automated maintenance management concepts. It also the Applications Technology Satellite-6. R. J. Hilton (FAA, verified compatibility of the system architecture with the aircraft's Washington, D.C.). American Institute of Aeronautics and Astro- guidance/navigation sensors and redundant electrohydraulic flight nautics, Digital Avionics System Conference, Boston, Mass., Apr. 24, control actuators. System organization, in terms of redundancy and 1975, Paper 75-562. 8 P. software-hardware monitoring is described. Computer memory and Air Traffic Control (ATC) demonstrations were included in the time requirements for the various control modes and other software Applications Technology Satellite-6 (ATS-6) aeronautical experi- functions are summarized. Flight results associated with autoland ments for the purpose of gaining practical knowledge in configuring performance and the system's recognition and responses to inserted and using voice and data links in satellite communications and failures during autoland mode engagement are described. (Author) surveillance for ATC. Demonstrations were performed involving the United States FAA, the European Space Research Organization (ESRO), and Canada. An airborne subsystem, a ground subsystem, A75-26727 # Self-testing digital flight control applications. and the interface necessary to establish the voice and data links R. C. Hendrick and C. D. Hill (Honeywell, Inc., Minneapolis, Minn.). through the satellite and satellite earth terminal were developed. American Institute of Aeronautics and Astronautics. Digital Avionics Demonstration scenarios were developed to provide for voice and System Conference, Boston, Mass., Apr. 24, 1975, Paper 75-568. 10 data communication through the satellite and recording of all P. communication and surveillance data was provided for future Applications are presented where digital computation is used to playback and analysis. This paper will describe the specific configura- achieve self-test functions in flight control systems, generally being tion of the subsystems, the details of the tests used for the applied such that equipment redundancy is minimized. Various levels

246 A75-26744

of fault accommodation are considered, including fail-safe, single-fail- The avionics experimental configuration of the considered operative, and dual-fail-operative. The JA-37 automatic flight control system is briefly reviewed, taking into account the concept of an system uses a single processor to perform continual testing to safely advanced air traffic management system, flight critical and non- disable -faulty equipment. The A-7 multimode development test critical functions, and display system characteristics. Cockpit dis- system uses dual-redundant processors to obtain a degree of plays and the navigation computer are examined. Attention is given continued operation after certain electronic failures. Future to the functions performed in the navigation computer, major fly-by-wire systems may triplicate elements to meet mission re- programs in the navigation computer, and questions of software liability and flight safety criteria. System configurations and related development. G.R. developments are described. (Author)

A75-26734 # Digital flight control systems - Considerations A75-26728 # New horizons in air traffic control. G. A. Scott in implementation and acceptance, W. B. Yopp and J. D. McDonnell (FAA. Washington, D.C.). American Institute of Aeronautics and (Douglas Aircraft Co.. Long Beach, Calif.). American Institute of Astronautics, Digital Avionics System Conference, Boston, Mast., Aeronautics and Astronautics, Digital Avionics System Conference, Apr. 2-4, 1975, Paper 75-569. 7 p. Boston, Mass., Apr. 2-4, 1975, Paper 75-577. 6 p. According to the FAA's latest air traffic forecasts, aviation in The current state-of-the-art with respect to the implementation the United States will continue to grow into the indefinite future. To of digital systems in commercial air transport aircraft is discussed. meet the demands of this continuing growth, the existing air traffic Current activity includes industry flight and laboratory evaluation control (ATC) system must be improved. The goals of the future programs. The more significant potential benefits offered by digital upgraded ATC system are: maintain or improve safety, constrain or flight control are discussed. These include improved computational reduce Costs, and increase and improve performance. These goals will precision, reliability, self-monitoring and integral maintenance moni- be met in part by the following new ATC features . Airport Surface toring as well as reduced component cost and weight and ease of Traffic Control System (ASTC), Discrete Address Beacon System design change implementation. Potential problem areas associated (DABS), Air Traffic Control Automation, Intermittent Positive with the implementation of digital flight control systems are Control (IPC), Area Navigation (RNAV), Microwave Landing System discussed in some detail. These range from a lack of 'intuitive' (MLS), and Wake Vortex Avoidance System (WVAS). (Author) understanding of digital processes to the need for development of fault analysis concepts for digital systems. (Author)

A75-26729 # Digital computer design guidelines for a full authority fly-by-wire flight control system. J. G. Allen (Charles Stark A75-26738 // Application of digital systems to Army Draper Laboratory, Inc., Cambridge, Mass.). American Institute of avionics. J. A. Dasaro, M. J. Fisher, L. J. Youngblood, Jr., and G. G. Aeronautics and Astronautics, Digital Avionics System Conference, Chandler, Jr. (U.S. Army, Avionics Laboratory, Fort Monmouth, Boston, Mass, Apr. 2-4, 1975, Paper 75-570. 12 p. USAF-supported N.J.). American Institute of Aeronautics and Astronautics, Digital research. Avionics System Conference, Boston, Mass., Apr. 24, 1975, Paper The design of a digital computer for a full authority fly-by-wire 75.587. 6 P. flight control system is discuss ed- with particular reference to the Recent trends in the development of digital computer hardware determination of the number of channels and the extent of coverage and their application to Army avionics equipment has forced a required, and the part played by the built-in test equipment (BITE) re-evaluation of the system integration methods used in the in a bit-by-bit voted system. Several baseline assumptions are made development of an Army Avionic package. A review of current data concerning computer definition as well as reliability and operational processing hardware development efforts in the areas of navigation, requirements. The design guidelines derived from the study of the communications, and displays is presented to demonstrate trends in analytical models developed for six different multicomputer systems avionics subsystems. The need for a flexible system integration require a minimum of three channels; the use of four channels would technique, based on the application of digital technology is dis- increase the safety margin beyond two orders of magnitude. It is cussed. Finally, the Army's Digital Modular Avionics Program found that BITE allows an extra fault to be tolerated when recovery (DLMAP) is outlined as a coordinated three phase program to from faults with bit-by-bit voting is not possible. S.D. accomplish the desired objective. (Author)

A75-26732 # What have we learned from applying digital A75-26739 # Digital avionics information system /DAIS/ technology to cabin/passenger multiplex systems. J. Mohr (KLM - integrated test bed development. F. A. Scarpino (USAF. Avionics Royal Dutch Airlines, Amsterdam, Netherlands). American Institute Laboratory, Wright-Patterson AFB, Ohio) and R. Goodstein (Boeing of Aeronautics and Astronautics, Digital Avionics System Con- Aerospace Co., Seattle, Wash.). American Institute of Aeronautics ference, Boston, Mass., Apr. 2-4, 1975, Paper 75-574. 4 p. and Astronautics, Digital Avionics System Conference, Boston, Use of digital time division multiplex systems in wide-body Mass, Apr. 2-4, 1975, Paper 75-588. 7 p. aircraft to provide individual passenger control of reading lights, call The United States Air Force Advanced Development Program functions, and music channels is assessed. A typical MUX system is for low cost, standardized avionics for future aircraft is entitled described, and the reliability and ownership costs of first and second Digital Avionics Information System (DAIS). The analysis and design generation systems are outlined. Cost comparisons are made between of an integrated test bed consisting of prototype hardware and MUX and hand-wired systems, and it is shown that the higher software, to be assembled by the Air Force Avionics Laboratory operational costs of MUX systems are offset b y their lower weight (AFAL), are described. The Status of the program, its basic concepts, penalty costs. F.G.M. and Its design goals are reviewed. Progress towards low cost avionics through standardization modularity, and interchangeability can be achieved with current technology subsystems. (Author) A75-26733 * # Software engineering of a navigation and guidance system for commercial aircraft. S. G. Lachmann and R. G. A75-26744 # Instrumentation displays for future naval air- McKinstry (Boeing Co.. Seattle, Wash.). American Institute of craft, W. G. Mulley (U.S. Naval Material Command, Naval Air Aeronautics and Astronautics, Digital Avionics System Conference, Development Center, Warminster, Pa.). American Institute of Aero- Boston, Mass., Apr. 2-4, 1975, Paper 75-575. 16 p. 5 refs. Contract nautics and Astronautics, Digital Avionics System Conference, No. NAS1 . 1 3267. Boston, Mass., Apr. 2-4, 1975, Paper 75-599. 5 p.

247

A75-26745

-The Advanced Integrated Modular Instrumentation System supersonic sections of the nozzle can be designed separately. The (AIMIS) is described. The functions of the display indicators problem is solved numerically in the hodograph plane. The Dirichlet (status/advisory, horizontal situation, vertical situation, and head-up) problem in a rectangle, one side of which is the sonic line, is and the electronics units (data, signal, and display processors and formulated in the subsonic region of the hodograph plane, and is scan converter/refresh units) are outlined. Other features of the solved for the Chaplygin equation. V.P. system mechanization and improvements in operational effectiveness over present cockpit instrumentation are noted. It is shown that AIMIS will reduce cockpit clutter and provide multifunction display A75.26881 # A method of calculating aerodynamic-nozzle and control, refined information and display interaction for pilot profiles with passage through the sound barrier (Metod rascheta decision making, building-block capability for applying the complete konturov aerodinamicheskikh sopl s perekhodom cherez skorost' system or its components to various weapons systems, and reduction zvuka). A. M. Ovsiannikov and U. G. Pirumov. Akademlia Nauk in logistics support, training, and documentation. F.G.M. SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, Jan-Feb. 1975, p. 68-72. 5 refs. In Russian.

A75-26882 # Supersonic flow past intersecting surfaces A75-26745 # Design of the DAIS control and display core (Obtekanie sverkhzvukovym potokom peresekaiushchikhsia poverkh- element. N. A. Kopchick (USAF, Avionics Laboratory, Wright- nostei). N. F. Vorob'ev and V. P. Fedosov. Akademiia Nauk SSSR, Patterson AFB, Ohio), D. E. Dewey, and W. Willich (Boeing lzvestiia, Mekhanika Zhidkosti I Gaza, Jan-Feb. 1975, p. 73-81. 12 Aerospace Co., Seattle, Wash.). American Institute of Aeronautics refs. In Russian. and Astronautics, Digital Avionics System Conference, Boston, The problem of the supersonic flow past slightly twisted Mass., Apr. 2-4, 1975, Paper 75-600. 11 p. intersecting surfaces, whose tangential planes form at each point The present paper discusses the system configuration, critical small angles with the oncoming flow velocity, is analyzed in linear design tradeoff results, and past task simulation results to date formulation. The problem is reduced to the solution of a wave concerning the advanced development program on digital avionics equation for the velocity potential with boundary conditions information system (DAIS). Two major design tradeoff areas are emphasized: (1) dedicated vs shared processing for the control and prescribed at the fairings and at the characteristic bow surface. The display core element, and (2) electronic map display implementation solution is obtained by the Volterra method. V.P. approaches. Conclusions drawn from various efforts indicate that with minimum technical risk, the control and display core element of the DAIS hot bench can be implemented to meet overall program A75.26888 # Numerical study of heat exchange at the objectives. S.J.M. stagnation point of a sphere situated in a hypersonic stream of carbon dioxide gas (Chislennoe issledovanie teploobmena v kriti. cheskoi tochke sfery, obtekaemoi giperzvuk.vym potokom uglekis- A75-26849 • Ride quality evaluation. I. L. G. Richards and logo gaze). N. E. Afonina and V. G. Gromov (Moskovskii Gosudarst- I. D. Jacobson (Virginia, University, Charlottesville, Va.). Ergo- vennyi Universitet, Moscow, USSR). Akademila Nauk SSSR, nomics. vol. 18,. Mar. 1975. p. 129150. 5 refs. Grant No. lzvestiia, Mekhanika Zhldkosti i Gaza, Jan-Feb. 1975, p. 117-120. 5 NGR-47-005-181. refs. In Russian. As part of a larger effort to assess passenger comfort in aircraft, two questionnaires were administered: one to ground-based respondents, the other to passengers in flight. Respondents indicated A75-26891 # A subsonic axisymmetric wake in a viscous gas the importance of various factors influencing their satisfaction with a (Dozvukovoi osesimmetrichenyi sled v viazkom gaze). B. D. Kovalev trip, the perceived importance of various physical factors in and V. I. Myshenkov, Akademiia Nauk SSSR, lzvestiia, Mekhanika determining their level of comfort, and the ease of time spent Zhidkosti i Gaza, Jan-Feb. 1975, p. 148-151. 5 refs. In Russian. performing activities in flight. The in-flight sample also provided a rating of their level of comfort and of their willingness to fly again. Comfort ratings were examined in relation to (1) type of respondent, A75.26894 (2) type of aircraft, (3) characteristics of the passengers, (4) ease of # Calculation of heat transfer at the lines of flow performing activities, and (5) willingness to fly again. (Author) of a three-dimensional boundary layer in a nonuniform external flow (0 raschete teploobmena na liniiakh rastekaniia trekhmernogo pogranichnogo sloia v neodnorodnom vneshnem potoke). B. A. Zemlianskii. Akademiia Nauk SSSR, lzvestiia, Mekhanika Zhldkosti I A75-26879 # Determination of load factors for the impact Gaza, Jan-Feb. 1975, P. 160-162. 5 refs. In Russian. of a profile against the surface of a liquid (Opredelenie peregruzok A method, based on local substitution of an equivalent uniform pri udare prof ilia o poverkhnost' zhidkosti). G. L. Boiko and V. A. flow for a nonuniform flow, proposed for taking into consideration Eroshin. Akademila Nauk SSSR, Izvestiia, Mekhanika Zhidkosti, the transverse nonuniformity of the external viscous flow on the boundary layer is extended to the lines of flow of a three- Gaza, Jan-Feb. 1975, p. 35-38. 7 refs. In Russian. The two-dimensional problem of the impact of thin-section dimensional boundary layer over a 'cloud' body situated in nonuni- twisted wing against the surface of an ideal incompressible fluid is form inviscid flow. The extended method is applied as an example to discussed, assuming that the leading edge always remains above the (DABS). Air Traffic Control Automation, Intermittent Positive unperturbed free surface. Expressions for calculating the hydro- Control (IPC), Area Navigation (RNAV). Microwave Landing System dynamic forces and load factors for such impacts are derived. The (M LS), and Wake Vortex Avoidance System (WVAS). (Author) analytical results obtained for a flat plate are verified experimentally. V.P.

A75.26880 # A method of profiling short two-dimensional A75'26895 # Cavitating flow past a vibrating thin-section nozzles (Ob odnom metode profilirovaniia korotkikh ploskikh sopi). wing profile (Kavitatsionnoe obtekanie tonkogo kolebliushchegosia N. A. Podsypanina and E. G. Shifrin. Akademiia Nauk SSSR, profile). I. I. Efremov and V. N. Semenenko. Akademiia Nauk SSSR, lzvestiia, Mekhanika Zhidkosti i Gaza, Jan-Feb. 1975, p. 54-58. 12 lzvestiia, Mekhanika Zhidkosti I Gaza, Jan-Feb. 1975, p. 163-166. 8 refs. In Russian. refs. In Russian. A method of profiling wind-tunnel nozzles is proposed. By The potential flow of an imponderable incompressible fluid past choosing a nozzle with a straight sonic line, the subsonic and a thin-section slightly twisted wing is analyzed, assuming that the

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cavern covers the suction side of the wing and that it trails off from composite. In addition, tests were conducted under the presence of the trailing edge. The condition for the solvability of Neumann's CO, and mice were injected intraperitoneally or intramuscularly with external boundary value problem for the velocity potential is taken aqueous solutions containing dissolved effluents from the pyrolysis as the condition for the determination of the cavity length. The of cotton or of chlorinated aromatic polyamide. Results indicate that problem is reduced to the solution of a system of integral equations. unique thermodecomposition products of the polymeric materials V.P. are more toxic to mice than are other products from cotton under similar controlled conditions. S.J.M. A75-26896 # Hypersonic flow past pointed and blunt bodies with a concave generatrix (Obtekanie ostrykh I zatuplennykh tel A75-27178 # Aircraft guidance for automatic collision vognutoi obrazuiushchei giperzvukovym potokom). S. L. Vishnevet- avoidance. J. A. Sorensen, A. W. Merz, T. B. Cline, and J. S. skii and Z. S. Pakhomova. Akademiia Nauk SSSR, lzvestiia. Karmarkar. International Federation of Automatic Control, Sympo- Mekhanika Zhidkosti i Gaza, Jan.-Feb. 1975, 176. 180. 5 refs. In p. sium on Automatic Control in Space, 66, Tsakhkadzor, Armenian Russian, SSR, Aug. 26-31, 1974, Paper. 16 p. U.S. Department of Transporta- tion Contract No. TSC-535. This paper is concerned with the development of the guidance A75-26898 Sound welds in wing boxes assured by three system requirements for automatic prevention of aircraft collisions. techniques. Metal Progress. vol. 107, Apr. 1975. p. 67. 68. Electron-beam welding is used in assembling the wing boxes of The guidance commands can be computed on the ground, as part of the F-14 fighter. The.wing boxes are tested by three nondestructive the air traffic control function, or in the air, by means of an methods: ultrasonic inspection, radiography, and die-penetrant independent airborne collision avoidance system. The general prob- inspection. The strict quality-control methods have cut rejects from lem is divided into three parts: (1) the determination of the most 30% to 15%. A.T.S. effective maneuvers required for avoiding the conflict; (2) the development of computer algorithms to estimate the relative state of a threatening aircraft from noisy measurements, and to generate the A75-26900 A pilot's report concerning the VTOL VAK evasive maneuvers based on these estimates; and (3) the determina- 191 B (Pilot report des Senkrechtstarters VAK 191 B). L. Obermeier. tion of the effect of dynamic and measurement errors on the Apr. 1975, 18-22. In German. Flug Revue/F/ugwelt International, p. performance of the system. (Author) Development and investigative work concerned with an evaluation of the advantages and drawbacks of various configurations of V/STOL aircraft is briefly considered, taking into account investigations in the U.S. and in Western Europe. As a result of the A75-27180 # A ioncept of flight dynamics control. M. evaluations interest was expressed b y the U.S. Navy to continue tests Vukobratovic and D. Stokic. International Federation of Automatic with the VTOL aircraft VAK 191 B, which had been developed by a Control, Symposium on Automatic Control in Space, 6th, Tsakhkad- West German aerospace corporation. A technical description of the zor, Armenian SSR, Aug. 26-31, 1974, Paper. 22 p. 7 refs. VAK 191 B is given and details regarding the flight tests conducted Contrary to hierarchical control systems that are based on with the new aircraft are discussed. G.R. 'algebraic levels', the control concept described is based on the introduction of a 'level of nominal dynamics' (algorithmic level) and an 'adaptation level' (level of perturbed regimes). A novel feature of A75.26948 # Important aspects of international air cargo. the control is the introduction of the concept of 'prescribed artificial R. M. Jackson (Seaboard World Airlines, Inc., Kennedy International synergy', using which the synthesis of nominal dynamic regimes can Airport. N.Y.). Astronautics and Aeronautics, vol. 13. Apr. 1975, p. be greatly simplified. The application of the control under considera- 50-53. tion to the selection of a flight trajectory in the presence of strong Questions of the significance of air-freight operations for the disturbances is demonstrated. V.P. economy are examined, taking into account prospects concerning the development of a new pure-cargo aircraft. Aspects of air-freight

rate-making are considered and proposals are made for improved A75-27182 # Adaptive digital system for aircraft control

international rate-making procedures. The relationship between (Adaptivnaia tsifrovaia sistema upravlenhia samoleta). lu. A. regularly scheduled service rates and charter rates is discussed along Nikolaev, E. D. Teriaev, and B. M. Shamrikov. International

with problems of the intermodal air/truck transport era and the Federation of Automatic Control, Symposium on Automatic Control

effects of increased fuel costs on the economy of air transportation. in Space, 6th, Tsakhkadzor, Armenian SSR, Aug. 26-31, 1974, G. R. Paper. 12 P. 5 refs. In Russian. The problem of designing an ada ptive digital system for A75-27052 Characteristics of pressure fluctuations in dis- steering-wheel control of the longitudinal motion of an aircraft is tributed suction of a turbulent boundary layer. L. M. Liamshev, M. discussed that will ensure prescribed controllability characteristics G. Puzino, and S. A. Salosina (Akademiia Nauk SSSR, Akusticheskii for each of the design modes. Solutions are obtained which help to lnstitut, Moscow, USSR). (AkusticheskllZhurnal. vol. 20, Sept.-Oct. overcome the contradictory plant and control requirements, to use 1974, P. 733-737.) Soviet Physics - Acoustics, vol. 20, Mar.-Apr. effectively the a-priori information on the plant, and to take into consideration the s pecific requirements 1975, p. 444-446. 10 refs. Translation. placed on the type of systems studied. The synthesis of the adaptive control law is outlined. V.P.

A75-27073 • A study of the effects on mice of smoke and A75-27367 Fly-by-wire and control configured vehicles - gases from controlled fires in simulated aircraft cabins. A. P. Moreci, Rewards and risks. B. R. A. Burns (British Aircraft Corp., Ltd., A. Furst (San Francisco, University, San Francisco, Calif.), and J. A. Military Aircraft Div., Preston, Lancs., England). Aeronautical Parker (NASA, Ames Research Center, Moffett Field, Calif.). Journal Journal, vol. 79, Feb. 1975, p. 51-58.6 refs. of Fire and Flammability, Combustion Toxicology Supplement, vol. The fly-by-wire concept implies full authority command of 2, Feb. 1975, p. 34-63.17 refs. aircraft motion by means of electrical control stick/pedal transducers Male Swiss albino mice were exposed to the pyrolysis products whose outputs are summed with the outputs of aircraft-motion of two fire-retardant materials, a chlorinated aromatic polyamide and sensors and electrically connected to the control-surface actuators. A a copolymer of vinylidine fluoride and hexafluoropropene. Com- control configured vehicle utilizes the aerodynamic forces available parison tests were made with cotton and a 50/50 cotton-polyester from its movable surfaces to change or redistribute the overall

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aerodynamic forces in such a way as to improve aerodynamic, A75-27596 The 'definition' of the motorsegler. H. Zacher structural, and operational efficiency. The characteristics of the (Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt, fly-by-wire concept are discussed along with details regarding the Institut für Aerodynamik, Munich, West Germany).Aero-Revue. no. system structure involved, the sensors, problems of signal processing, 8. 1974, p. 479-481. 8 refs. (DFVLR-SONDDR-424) and questions of actuation. Attention is given to the power supplies, A new parameter is suggested for the purpose of distinguishing aspects of artificial longitudinal stability, maneuver load control, motorseglers (auxiliary-powered sailplanes) from light airplanes: W/b automatic configuration management, gust alleviation, aeroelastic squared, or the ratio of weight to the square of span. This parameter mode stabilization, direct force control, active flutter prevention, combines the important characteristics of wing loading and aspect and questions of mission-performance design- G .R - ratio (it is their quotient). Diagrams are given showing that motorseglers fall below a W/b squared value of 3 kg/sq m, while Iightplanes generally have W/b squared equal to or greater than 4. A75-27368 'By the application of power' /21st Cayley S.J.M. Memorial Lecture/. J. L. Edwards (Rolls-Royce /19711, Ltd., Derby. A75-27695 Characterization of advanced composite ma- England). Aeronautical Journal, vol. 79, Feb. 1975, p. 59-84.23 refs. A description is given of the technical development of the terials for structural design. M. E. Waddoups (General Dynamics aircraft engine. Questions concerning the advances made with respect Corp., Convair Aerospace Div., Fort Worth, Tex.). (National Science to reciprocating engines are considered, taking into account the Foundation and Consiglio Nazionale delle Ricerche, United States- period from 1903 to 1918, the time between the two world wars, Italy Cooperative Symposium on Advanced Polymer Mechanics - and the second world war. Attention is given to the use of the gas Composite Materials and Ultra-High-Modulus Fibers, 1st, Santa turbine in aviation, the evolution of the gas producer, bypass and Margherita Ligure, Italy, May 27-31, 1974.) Polymer Engineering and ducted fan engines, approaches to obtain vertical lift, evolution by Science, vol. 15, Mar. 1975, p. 160-166. 21 refs, component, compressors, combustion problems, turbine develop- Composite material strength characteristics are studied with a ments, and aspects of thrust augmentation. Questions related to the view toward obtaining improved aircraft components. The data power plant and supersonics are discussed along with aspects of noise obtained show that the addition of high-modulus fibers into a and noise suppression- Industrial and marine application of gas polymeric matrix produced a physically distinct material with substantial advantage over nonreinforced polymers. Since the proper- turbines are also examined. G. R. ties of composites depend strongly on fiber orientation, two design concepts for quasi-brittle materials are considered. Suffer strips thus developed allow connection in a beam without net section stress A75-27495 # Influence of sound upon separated flow over concentration and without arrestment of dynamic fracture. S.D. wings. F. G. Collins and J. Zelenevitz (Texas, University, Austin, vol. 13. Mar. 1975, 408-410. 11 refs. NSF Tex.). AIAA Journal, p. A75.27777 # On the future of jet propulsion in subsonic Grant No. GK-42133. transport aviation. M. Roy. Periodica Polytechnica, Transportation A description is given of a technique for increasing the lift Engineering, vol.2, no. 1, 1974, p. 49-59. coefficient and stall angle and decreasing the drag coefficient of a Parametric development potential studies on the thermo- wing at moderate Reynolds numbers by radiating the airstream with dynamic cycle of transport aviation turbofan engines show that sound. The sound waves cause premature boundary-layer transition, substantial weight and consumption savings can be obtained, without which reduces separated flow regions and suppresses stall. It is expected that the technique will be most useful at low Reynolds increasing turbine inlet temperatures, from the expected improve- numbers. The magnitude of the effect of the sound depends on the ments in compressor turbine efficiencies. It is shown that improve- sound frequency and the sound pressure level. G. R. ments may be obtained by increasing the dilution to roughly mu = 12, while ejector-induced tertiary flow over special wing-flap combinations may provide short takeoff and landing distances and significant noise reduction. V.P. A75.27496 # Interpretation of merged layer behavior for wedges. J. R. Baron (MIT, Lexington, Mass.). AIAA Journal, vol. 13, A75-27838 # Organization of centralized maintenance of Mar. 1975, p.410-412.7 refs. USAF-sponsored research. aircraft assemblies (Organizatsiia tsentralizovannogo remonta It is pointed out that implicit in the wedge analysis conducted agregatov samoletov), S. N. Malkov. Moscow, lzdatel'stvo Transport, by Shorenstein (1972) is a generalization of the plate behavior 1974. 180 p.30 refs. In Russian. involving an implication that a strong interaction follows always the The present work examines theoretical and practical considera- merged region. The investigation reported is concerned with a tions for setting up a steady production basis and rational organiza- clarification of the considered assumptions, giving attention to the tion for centralized repair operations on aircraft assemblies. Methods specific parameter ranges involved and to general qualitative rela- are set forth for determining repair requirements, optimal production tions. G.R. allocation and program planning, and the implementation of typical technology and complex, mechanized work flow lines for group repair of assemblies. P.T.H. A75-27526 The performance in illuminances up to 80,000 lux of a light emitting diode display having a 3 mm character height. A75.27839 Reliability life cycle of a complex electronic B. Ellis, G. J. Burrell, J. H. Wharf, T. D. F. Hawkins, and D. V. Peters airborne equipment. S. P. Mercurio (General Electric Co., Aerospace (Ro Aircraft Establishment, Space Dept., Farnborough, Hants., ya l Equipment Div., Utica, N.Y.) and J. M. Black (USAF, Aeronautical England). 5/0, Proceedings, vol. 15, 4th Quarter, 1974, p. 150-160. Systems Div., Wright-Patterson AFB, Ohio). IEEE Transactions on 9 refs. Reliability, vol. R .24, Apr. 1975, p. 2-7. A red GaAs/P LED display, designed for use in aircraft cockpits, A good reliability program through design and production has been tested at illuminances up to 80,000 lux. Each of the 371 results in excellent equipment performance in the field. A full life subjects who took part in the experiment read 120 random cycle under controlled failure reporting and analysis procedures is characters. The resuItsarüiiiiéd in terms of the error rates and covered. An excess of 48,000 flight hours over 27,000 missions with omission rates as a function of illuminance level and their depen- dences upon the age, eyesight and sex of the subjects are also 303 failures reported from five reporting maintenance shops con- examined. From the error rates for particular characters some stitutes the field reporting phase. In addition, details and supporting deficiencies of the character found are identified and from the results documentation of the overall reliability program during the design of timed tests some inferences concerning the extent to which the phase, demonstration phase, production phase and field use phase are subjects found the display 'comfortable' are drawn. (Author) presented. (Author)

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A75-27852 // Comparison of airport measurements of ap- reported by Hanson (1973) with results obtained by Zorumski proach noise produced by jet aircraft. D. E. Bishop (Bolt Beranek (1974). Hanson's analysis is briefly examined and a formula is and Newman, Inc., Canoga Park, Calif.). Acoustical Society of derived for the far-field pressure due to a dipole pulse. Questions of America. Meeting, 88th, St. Louis, Mo., Nov. 4-8,1974, Paper. 16 p. transmission and reflection are discussed and attention is given to the 5 refs. radiation from ducted dipoles. G. R. The present paper discusses field noise measurements made at the Detroit Metropolitan Airport in 1971 during an evaluation of A75-27877 High-temperature alloys and the aircraft gas proposed changes in the glide slope intercept altitudes. The Detroit turbine. W. Betteridge (International Nickel, Ltd., London, England), measurements, interpreted in terms of noise level vs distance curves, In: The Nimonic alloys and other nickel-base high-temperature alloys are compared with the so-called 'standard' noise level curves often /2nd edition!. New York, Crane, Russak and Co., used for noise exposure forecast (NEF) and day/night average level Inc., 1974, p. 1-6. 16 refs. (ON L) calculations. The comparison indicates no large or systematic Nimonic and other high-temperature alloys used in aircraft gas underestimation of approach noise using the 'standard' noise level turbines are reviewed. Creep deformation of these alloys at elevated curves. S.J.M. temperatures is discussed along with aircraft let-engine requirements. It is seen that improved materials are presently available to secure A75-27853 * # Noise of model target type thrust reversers for increased output and reliability of aircraft gas-turbine engines. S.D. engine-over-the-wing applications. J. A. Stone and 0. A. Gutierrez (NASA. Lewis Research Center, Cleveland, Ohio). Acoustical Society of America, Meeting, 88th, St. Louis, Mo., Nov. 4-8, 1974, Paper. 23 A75-27912 # Adaptive control system with reference model p. 19 refs. (Adaptivni regulatory s referencnim modelem). Z. Pech and J. Frouz The present work reports on experiments concerning the noise (Ceske Vysoke Uceni Technicke, Prague, Czechoslovakia). Auto- generated by V-gutter and semicylindrical target reversers with matizace, vol. 18. Feb. 1975, p.35-42.9 refs. In Czech. circular and short-aspect-ratio slot nozzles having equivalent diam- The present work describes a general approach to the synthesis eters of about 5 cm. At subsonic jet velocities of interest for of an adaptive control system with reference model by means of engine-over-the-wing (OTW) powered-lift aircraft, the reversers were analog simulation. An initial system with adaptation of all three noisier than the nozzles alone and had a more uniform directional control system coefficients is described, which is evaluated as being distribution and more high-frequency noise. Reverser shape was more impractical on account of its small stability range,iong adaptation important than nozzle shape in determining the reverser noise time, and structural complexity. Therefore, a single-loop adaptive characteristics. An estimate is made of perceived noise level along the controller is proposed, which features adaptive capability only in the 152-rn sideline for a hypothetical OTW powered-lift airplane. S.J.M. gain circuit. Increased stability range and decreased adaptation time were thereby obtained. Further modifications resulted in an adaptive controller with automatic gain control. P.T.H. A75-27854 * # Spinning mode sound propagation in ducts with acoustic treatment, E. J. Rice (NASA, Lewis Research Center, Cleveland, Ohio). Acoustical Society of America. Meeting, 88th, St. A75-27919 Stability analysis of stochastic composite Louis, Mo., Nov. 4-8, 1974, Paper. 35 p. 16 refs. systems. A. N. Michel (Iowa State University of Science and Recent acoustic data have shown larger noise attenuations than Technology, Ames, Iowa). IEEE Transactions on Automatic Control, predicted for acoustically treated aircraft engine inlets without vol. AC-20, Apr. 1975, p. 246-250. 19 refs. Research supported by splitter rings. These data have stimulated a more detailed theoretical the Iowa State University of Science and Technology; NSF Grant study of the acoustic propagation of spinning modes in acoustically No. GK-33739. treated open circular ducts. In addition, the suppressor with splitter New results for asymptotic stability and exponential stability rings was modeled by using the rectangular approximation to the with probability for several classes of continuous parameter and annular duct. The theoretical models were used to determine discrete parameter stochastic composite systems are established. In optimum impedance and maximum attenuation for several spinning all cases the objective is to analyze composite systems in terms of lobe numbers from 0 to 50. It is found that for circular ducts the their lower order subsystems and in terms of their interconnecting maximum possible attenuation and the optimum wall impedance are structure. The results are applied to three specific examples. (Author) strong functions of the lobe number. For annular ducts the attenuation and optimum wall impedance are insensitive to the A75-27926 # Theoretical and experimental studies of dis' spinning lobe number for well cut-on modes. The results help explain crete-tone rotor-stator interaction noise. G. F. Homicz, G. R. why suppressors with splitter rings have been quite effective in spite Ludwig, and J. A. Lordi (Calspan Corp., Buffalo, N.Y.). American of the lack of detailed information on the noise-source modal Institute of Aeronautics and Astronautics, Aero-Acoustics Con- structure. Conversely, effective use of outer-wall treatment alone will ference, 2nd, Hampton, Va., Mar. 24-26, 1975, Paper 75443. 19 p. require expanded knowledge of;fhe noise-source structure. Approxi- 37 refs. Contract No. F33615-73-C-2046. mate solutions are presented to help interpret the more exact A theoretical and experimental study is conducted on the theoretical results. . (Author) discrete-tone noise caused by interaction between rotor and stator blade rows of subsonic axial-flow fans and compressors. A compressible two-dimensional analysis of the generated aerodynamic A75-27859 # Propagation of aircraft noise near airports forces is matched, on a strip-theory basis, to the three-dimensional Effects of hillsides, inversions and source directionality. T. F. W. annular duct acoustic modes. Expressions are derived for both the Embleton and J. E. Piercy (National Research Council, Div. of mean square pressure at any position in the duct, and for the total Physics, Ottawa, Canada). Acoustical Society of America, Meeting, power radiated at harmonics of blade péssage frequency in terms of 88th, St. Louis, Mo., Nov. 4-8, 1974, Paper. 9 p. the fan/compressor operating conditions and geometry. The sound pressure level at the outer wall is calculated theoretically, and the resulting predictions are compared with the acoustic data for two A75.27861 • # Unified analysis of ducted turboinachinery different rotor-stator configurations. The discrepancy between noise. W. E. Zorumski and H. C. Lester (NASA. Langley Research theoretical and experimental findings is discussed in detail. S.D. Center, Hampton, Va.). Acoustical Society of America, Meeting, 880, St. Louis, Mo., Nov. 4-8, 1974, Paper. 26 p. 8 refs. An approach for an analysis of ducted turbomachinery noise is A75-27927 # The role of rotor blade blockage in the developed by combining features of the analysis of fan stator noise propagation of fan noise interaction tones. M. G. Philpot (National

251 A75-27928

Gas Turbine Establishment, Farnborough, Hants., England). A75-27931 # Propulsive-lift noise of an upper surface blown American Institute of Aeronautics and Astronautics. Aero-Acoustics flap configuration. N. N. Reddy (Lockheed-Georgia Co, Marietta, Conference, 2nd, Hampton, Va., Mar. 24-26 , 1975, Paper 75447. 12 Ga.). American Institute of Aeronautics and Astronautics, Aero- . p.15 refs. Acoustics Conference, 2nd, Hampton, Va., Mar. 24 26, 1975, Paper Experimental studies indicate that forward propagation of the 75470. 7 p. 7 refs. tone noise caused by rotor/OGV combinations is inhibited by the The radiated sound and the flow characteristics of a scaled blocking effect of the rotor - in some cases to a considerable extent. model of an upper surface blown-flap configuration are experi- The physics of this mechanism and the available two-dimensional mentally investigated. The acoustic results consist of the radiation theoretical treatments of it are reviewed. To enable fans of low pattern and spectral distribution of radiated sound in two planes. hub/tip ratio to be analyzed, a method, based on strip-theory The two planes considered are the nozzle exit plane and the plane principles, of extending such treatments to three dimensions is perpendicular to the wing surface passing through the jet centerline. outlined. This is used in conjunction with one of the simpler theories The flow measurements include mean flow and the turbulence to predict the blockage effects for four different research fans. intensity distribution on the wing/flap (wall jet) and in the Generally good agreement with experiment is obtained and it is trailing-edge wake. These results indicate that a dominant noise is concluded that the approache forms a viable basis for prediction. The generated in the vicinity of the trailing edge. Radiated sound in the implications of the findings are discussed briefly in the context of direction perpendicular to the flap trailing edge correlates with the trailing-edge velocity raised to the power 5, and the spectra correlate turbofan engine design. (Author) with the wall-jet thickness and velocity at the trailing edge. Turbulence close to the surface is amplified as the flow is convected past the trailing edge, while more distant turbulence is not affected A75-27928 # Radiation of duct noise out through a jet flow. by the surface. (Author) H. E. Plumblee (Lockheed-Georgia Co.. Marietta, Ga.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Con- ference, 2nd, Hampton, Va., Mar. 24-26, 1975, Paper 75457. 16 p. A75-27932 # Effect of forward speed on jet wing/flap 12 refs. Research supported by the Lockheed-Georgia Internal interaction noise. W. V. Bhat (Boeing Commercial Airplane Co., Research and Development Fund. Seattle, Wash.) and D. Gallo Rosso (Aeritalia S.p.A., Naples, Italy). The investigation reported forms the basis for a study of the American Institute of Aeronautics and Astrcnautics, Aero-Acoustics radiation field of an arbitrary acoustic distribution at the termination Conference, 2nd, Hampton, Va., Mar. 24-26, 1975, Paper 75475.8 of an engine inlet or exhaust. A description of a physical model is p. 10 refs. presented and a mathematical model is considered. The theoretical A series of model tests has been conducted to assess the problem relations are based on assumptions introduced in the linearization of of jet wing/flap interaction noise for low-aspect-ratio D.shaped the transport equations. The theoretical investigation is sup- nozzles located on the upper surface of a wing. The measurements plemented by an experimental study. The experiments cover an have been made using far-field and near-field wing-mounted flush extensive range of jet velocity and frequency. The experimental data microphones. A prediction procedure for static interaction noise has G.R. are compared with the theoretical results. been formulated from far-field low-frequency interaction-noise measurements obtained under static conditions. The effect of forward A75-27929 # An investigation of the noise from a scale speed on interaction noise has been investigated experimentally using model of an engine exhaust system. W. D. Bryce and R. C. K. Stevens an open-jet tunnel. These test data show that both far-field noise and (National Gas Turbine Establishment, Farnborough, Hants., the near-field wing trailing-edge pressure fluctuations are reduced by (Author) England). American Institute of Aeronautics and Astronautics, the simulated forward speed. Aero-Acoustics Conference, 2nd, Hampton, Va., Mar. 24-26, 1975, Paper 75-459.16 p. 14 refs. A75-27933 # Developments in jet noise modeling - Theoreti- To assist in the identification and understanding of the noise cal predictions and comparisons with measured data. B. J. Tester sources which contribute to the exhaust noise of aircraft gas-turbine (Lockheed-Georgia Co., Marietta, Ga.) and C. L. Morley (South- engines, controlled experiments have been carried Out to study the ampton, University, Southampton, England). American Institute of noise characteristics of a model turbojet exhaust system. The noise Aeronautics and Astronautics, Aero-Acoustics Conference, 2nd, data have been related to measurements of the aerodynamic Hampton, Va., Mar. 24-26, 1975, Paper 75477. 14 p. 21 refs. conditions in the model and, with the aid of specific diagnostic tests, Contract No. F33615.73-C-2032. the predominant noise mechanisms are considered to have been Spectral information on the sound radiated from turbulent recognized. The noise radiation, above that of the jet, is attributed shock-free jets is now available over a wide range of Strouhal primarily to dipole sources generated by the turbine outlet struts, the numbers, for jet densities ranging from 0.3 to 2 times the ambient transmission of this noise being modified b y duct propagation and density and jet velocities ranging from 0.3 to 2 times the ambient nozzle impedance effects. (Author) sound speed. The unexpected nature of some of the data has led to a fundamental re-examination of aerodynamic sound theory in general. by Lilley (1972) and Morley (1973), and jet-noise modeling in A75-27930 # Subsonic jet noise in flight based on some particular. Two areas of significant progress are described: (1) the recent wind-tunnel tests. B. J. Cocking and W. D. Bryce (National Gas Turbine Establishment, Farnborough, Hants., England). effects of nonuniform density which arise with hot jets, and (2) the effects of high Mach number on the radiation from 'isothermal' jets American Institute of Aeronautics and Astronautics, Aero-Acoustics (density ratio = 1). The jet-noise models presented are based on Conference, 2nd, Hampton, Va., Mar. 24-26, 1975, Paper 75462. 20 solutions to Lilley's equation. (Author) p. 24 refs. The mixing noise produced b y a cold subsonic air let has been measured under simulated flight conditions in a large open-jet wind tunnel which has been modified for acoustic work. At a noise A75-27936 # Supersonic jet noise suppression with multi- emission angle of 90 degrees to the jet axis, the overall sound tube nozzle/ejectors. J. Atvars, C. P. Wright, and C. D. Simcox American Insti- pressure level reduces approximately in proportion to the fifth power (Boeing Commercial Airplane Co., Seattle, Wash.). of the relative jet velocity and the noise reductions in the rear are tute of Aeronautics and Astronautics, Aero-Acoustics Conference, p. 7 refs. U.S. increase steadily as the jet axis is approached. These results are 2nd, Hampton, Va., Mar. 24-26, 1975, Paper 75-501.9 compared with theory, and together with some limited data obtained Department of Transportation Contract No. FA72WA-2893. from a coaxial jet, are used as the basis for a discussion on the An environmentally acceptable SST will have to be able to prediction of jet noise in flight. (Author) achieve noise levels comparable to those of other large commercial

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A75-27981

aircraft operating in the same time period. Recently conducted high Some aspects of far-field measurements of the noise generated velocity jet-noise suppression research has demonstrated that noise by a stationary source are examined. Particular attention is given to reductions of 16 PNdB can be achieved statically for less than 1% the determination of the acoustic power, noise level, and acoustic thrust loss by use of multitube nozzles and acoustically lined pressure level in the individual frequency bends to identify the noise ejectors. The paper describes the acoustic design philosophy behind a characteristics of an engine operating in a specific mode. The set of multitube suppressor nozzles. The results of a model-scale and determination of the directional pattern of an aircraft, involving the full-scale test program are given which demonstrate the latest determination of the maximum noise level, is also studied. V.P. advances in jet-noise suppressor technology. (Author) A75-27978 Deutsche Gesellschaft fir Luft- und Raum- A75-27937 # Some recent developments in supersonic jet fahrt. Yearbook 1973 (Deutsche Gesellschaft für Luft- und noise reduction. D. S. Dosanjh (Syracuse University, Syracuse, N.Y.), Raumfahrt, Jahrbuch 1973). Edited by H. Blank and W. Schulz. K. K. Ahuja, M. R. Bassiouni, and P. K. Bhutiani. American Institute Cologne, Deutsche Gesellschaft für Luft- und Raumfahrt, 1974. 348 of Aeronautics and Astronautics, Aero-Acoustics Conference, 2nd, p. In German and English. $30.40. Hampton, Va., Mar. 24-26, 1975, Paper 75-502. 31 p. 29 refs. U.S. Shock waves are considered along with the Airbus A 300, the Department of Transportation Contract No. OS-20094. development of European aeronautics and astronautics, the solar Attention is given to the results obtained in a new large jet wind and the magnetosphere of the earth, peculiar objects of X-ray facility for a two-nozzle coaxial arrangement. A description is and gamma-ray astronomy, air cushion landing systems for aircraft, presented of some preliminary attempts concerning the development high-speed trains, and the aircraft television system. Other topics of prediction schemes for noise from coaxial jets. The effects of lip explored are related to the flight tests conducted with the V/STOL (base) thickness on the coaxial jet flows and radiated noise are experimental aircraft VAK 191 B, the Alpha Jet program, the considered along with results obtained with a two-nozzle coaxial nonlinear behavior of solar paddle elements, the statical computation arrangement in a case in which an inner convergent-divergent jet of circular cylindrical sandwich-type shells, the bending of sandwich designed for M=1.46 was heated to 850 F and the outer convergent plates, the origin of lift, and gliding processes on the liquid surface. jet was operated cold. G.R. G. R.

A75-27938 # Noise generation and transmission in duet A75-27980 Airbus A 300 - Comparison of the flight test combustors. D. W. Lindley and H. A. Hassan (North Carolina State results with the flight performance and flight characteristics deter- University, Raleigh, N.C.). American Institute of Aeronautics and mined on the basis of theory and wind tunnel tests (Airbus A 300. Astronautics, Aero-Acoustics Conference, 2nd, Hampton, Va., Mar. Vergleich der durch Theorie und Windkanalversuche ermittelten 24-26, 1975, Paper 75-527. 15 p. 16 refs. U.S. Department of Flugleistungen und Flugeigenschaften mit den Ergebnissen der Transportation Contract No. 05-40056. Flugerprobung). R. Beteille (Airbus Industrie, Paris, France). In: Using a well-stirred reactor model to describe the combustion of Deutsche Gesellschaft für Luft- und Raumfahrt, Yearbook 1973. a propane-air mixture, the effect of flow nonuniformities on the Cologne, Deutsche Gesellschaft für Luft- und transmission of noise from hard and lined ducted combustion Raumfahrt, 1974, p. 41-52. In German. systems is considered. It is shown that for the range of Mach The airbus is a two-engine short-haul and medium-range aircraft. numbers, pressures, and temperatures considered, flow non- The number of passengers carried by the aircraft will be in the range uniformities have little influence on the frequency that characterizes from 240 to 345, depending on the comfort provided. The combustion noise in ducted combustors. On the other hand, for the aerodynamic investigations were conducted in close cooperation end impedence employed, the duct length has the greatest influence between British, French. and German aerospace firms. The flight on the characteristic frequency. The characteristic frequencies range of the aircraft under various conditions is discussed and the predicted by the theory are in good agreement with available aircraft flight characteristics at low speeds are examined. Attention is experiment. (Author) given to devices for increasing the lift, the maximum lift coefficients, and takeoff and landing characteristics. The flight performance and flight characteristics at high flight speeds are also considered. It is A75-27939 # The use of Hartmann generators as sources of found that the performance shown by the aircraft in the flight tests high intensity sound in a large absorption flow duct facility. D. L. is even slightly better than expected on the basis of theoretical, Martlew (National Gas Turbine Establishment, Farnborough, Hants., calculations and wind tunnel tests. G. R. England). American Institute of Aeronautics and Astronautics. Aero-Acoustics Conference, 2nd, Hampton, Va., Mar. 24-26, 1975, Paper 75-529. 10 p. 5 refs. The new, large scale. Noise Test Facility, consisting of a large A75-27981 European aeronautics and astronautics at the anechoic chamber and a flow duct for absorber testing, has been crossroads (Die europäische Luft- und Raumfahrt am Scheideweg). commissioned in support of an aircraft-engine noise-reduction L. Bblkow (Messerschmitt-Bölkow-Blohm GmbH, Ottobrunn, West program. Extensive experience has been gained in the use of groups Germany). (Deutsche Gesel/schaft für Luft- und Raumfahrt, Jahres- of Hartmann generators as sources of high intensity sound for the tagung. 6th, and Osterreichische Gesellschaft für Weltraumforschung flow duct. The development of these sources and their performance und Flugkorpertechnik, Jahrestagung, 11th, Innsbruck, Austria, are described. This type of noise generator has a tonal spectrum, and Sept. 25-28, 1973.) In: Deutsche Gesellechaft für Luff- und methods of testing and analyzing data are outlined which take this Raumfahrt, Yearbook 1973. Cologne, Deutsche into account. It is concluded that, where suitable air supplies are Gesellschaft für Luft- und Raumfahrt, 1974, p. 53-63. In German. available, the Hartmann generator is a convenient noise source with A brief historical review of the development of aviation and the which accurate measurements of absorption can be obtained. aerospace industry is presented, taking into account new develop- (Author) ments in aviation and the current technological and economical situation in this field. Difficulties of the European aerospace industry compared to the conditions existing for the U.S. in the field of A75-27943 # Classification problems of aircraft noise (Klas- aviation are examined along with approaches for the European sifizierungsprobleme des Fluglarmes). V. Chalupova. Hungarian industry to overcome problems arising from the current lack of Optical, Acoustical and Filmtechnical Society, Conference on Noise specialization of aerospace firms in specific areas. Long-term plan- Abatement, 2nd, Budapest, Hungary, May 6-10, 1974, Paper. 7 p. In ning required for developments in aviation make it imperative for the German. European countries involved to make now a decision concerning

253 A75-27983 their policy with respect to the development of new aircraft in friction effects. The second old investigation considered has been Europe. Such a decision should take into account the strength reported by Wagner in 1932. The justification of objections made represented by the creativity of European research and development against certain aspects of this investigation is discussed. G.R. personnel which made it possible to develop weapons systems at one third of the price which would have been required for such developments in the U.S. G. R. A75-28095 Critical analysis and improvement of the source-panel method. V. Losito and L. G. Napolitano (Napoli, Università, Naples, Italy). L'Aerotecnica - Missili e Spazio, vol. 54, A75-27983 Air cushion landing systems for aircraft. B. H. Feb. 1975. p. 5-12. Consiglio Nazionale delle Ricerche Contract No. Goethert (Tennessee, University, Tullahoma, Tenn.). (Deutsche 73,00339,07. Gesellschaft für Luft- und Raumfahrt, Jahrestagung, 6th. and The source-panel (SP) method developed by Smith and co- Osterreichische Gesel/schaft für Weltraumforschung und Flug. workers (1958, 1962, 1967) for the evaluation of two-dimensional körperrechnik, Jahrestagung, 1 7th, Innsbruck, Austria, Sept. 25.28, potential flow fields about arbitrary bodies is critically analyzed to 1973.) In: Deutsche Gesellschaft für Luft- und Raumfahrt, Yearbook find ways of improving its lift prediction capability. Numerical 1973. - Cologne, Deutsche Gesellschaft für Luff- experiments are carried Out to reveal the possible causes of error in und Raumfahrt, 1974, p. 85-101. 14 refs. the evaluation of the lift coefficient by the SP method. An improved Difficulties which in the case of large aircraft are related to the source-panel (ISP) method is proposed on the basis of the results small support area of the wheels of conventional landing gears can be obtained. It is shown that the ISP method yields highly accurate eliminated by making use of an air cushion system. In an values for the lift coefficient even with a comparatively small number experimental design a normal ground clearance of about one quarter of panels. S.D. of an inch was obtained with the aid of such a system. Basic principles of operation of an air cushion system are discussed along with questions of system design, the various types of feasible air A75-28096 Survey on two calculation methods in tran- cushion landing systems, problems of shock absorption during sonic regime. R. Marazzi (Aeronautica Macchi S.p.A., Milan, Italy). landing impact, handling on the ground, the weight ofconventional L'Aerotecnica - Miss/lie Spazio, vol. 54, Feb. 1975, p. 13-23. 11 refs. and air cushion landing systems, and the design goals for demonstra- The flow about a nonlifting airfoil and the flow in De Laval's tion aircraft with air cushion landing system. G.R. nozzle are solved using two different computational methods. Murman's (1972) method solves the transonic small-disturbance equation. The finite-difference scheme changes in type if the flow is A75.27985 Flight tests with the V/STOL experimental locally subsonic or supersonic. The notion of parabolic discretization aircraft VAK 191 B (Erprobung des V/STOL-Experimentalflugzeugs is introduced in order to properly represent the flow crossing the VAK 191 B). R. Riccius (Vereinigte Flugtechnische Werke-Fokker upstream branch of the sonic line. A change of coordinates is made GmbH, Bremen, West Germany). (Deutsche Gese/lschaft für Luft- in order to have a smaller integration step near the airfoil. The und Raumfahrt, Jahrestagung, 6th, and Osterreichische Gesel/schaft solution is obtained by successive approximations. Euler's equations für Weltraumforschung und Flugkörpertechnik, Jahrestagung, 11th, are solved in the nozzle problem. A change of coordinates is made Innsbruck, Austria. Sept. 25-28, 1973). In: Deutsche Gesellschaft für and the integration domain is transformed in a rectangular one. The Luff- und Raumfahrt, Yearbook 1973. Cologne, numerical calculation is carried out in this new nonphysical Deutsche Gesellschaft für Luft- und Rumfahrt, 1974, p. 125-146. coordinate system. A third-order explicit scheme, like Riethmyer's 11 refs. In German. two-step scheme, is used. No artificial viscosity is needed to damp Three VAK 191 B experimental aircraft were built in connec- the nonlinear instability. Iterations are needed to reach a steady tion with plans for the development of a German-Italian military state. (Author) aircraft for the high subsonic speed range and low flight altitudes. The VAK 191 B is a single-seat aircraft for a wide spectrum of combat missions including reconnaissance operations. A technical A75-28194 Extension of the lifting line model for the description of the aircraft is given, taking into account its VTOL helicopter rotor (Erweiterung des Traglinienmodells beim Hubsch- capability, questions of aircraft control and stabilization, the rauberrotor). R. Hille (Hamburg, Universität, Hamburg, West bleed-air system, and the fly-by-wire principle used. The aircraft Germany). Zeitschrift für Flugwissenschaften, vol. 23, Mar. 1975, p. development test program is considered along with the flight test 77-95. 12 refs. In German. Research supported by the Deutsche program. Attention is given to the range of the aircraft, dynamical Forschungsgemeinschaft. characteristics of longitudinal and lateral control, hover and vertical The lifting line model of the propeller in asymmetrical flow is flight characteristics, and the transition from VTOL to conventional- extended for the helicopter rotor in forward flight by taking the flight operation. G. R. wing flapping motion and the nonconstant flow rate through the rotor plane into account. Using measurement results for the 5 58 helicopter, investigations are conducted on the problem whether the A75-27990 The range ofvalidity in the case of two old computations of thrust and circulation can be improved in this way. investigations. I -The origin of lift. II - Collision and gliding processes Such improvements can be observed, though the agreement of on the liquid surface (Ober den GUltigkeitsbereich zweier alter computation results and measurement results is not yet fully Arbeiten. I - Auftriebsentstehung. II - Stow- und Gleitvorgãnge an satisfying. Finally, a correction term for the consideration of the der Flüssigkeitsoberflächen). H. Wagner. (Deutsche Gesellschaft für compressibility effect at the rotor in forward flight is calculated. Lull- und Raumlahrt, Jahrestagung, 6th. and Osterreichische Gesell- (Author) schaft Air Weltraumforschung and F/ugkärpertechnik, Jahrestagung, 11th, Innsbruck, Austria, Sept. 25-28, 1973.) In: Deutsche Gesell- schaft für Luff- und Raumfahrt, Yearbook 1973. A75-28201 # Estimates of the stability derivatives of a Cologne, Deutsche Gesellschaft für Luft- und Raumfahrt, 1974, p. helicopter and a V/STOL aircraft from flight data. D. G. Gould and 250-260. 17 refs. In German. W. S. Hindson (National Aeronautical Establishment, Flight Research The analysis regarding the origin of circulation around a wing in Laboratory, Ottawa, Canada). (NATO, AGARD, Specialists Meeting a frictionless liquid conducted by Wagner (1925) is considered, giving on Aircraft State and Parameter Identification Techniques, NASA attention to objections raised by other investigators who point out Langley Research Center, Hampton, Va., Nov. 5-8, 1974.) Canada, the importance of friction in the investigated process. It is shown National Research Council, Division of Mechanical Engineering and that the problem studied belongs to a case in which the flow outside National Aeronautical Establishment, Quarterly Bulletin, no. 4, the thin boundary layers can be computed without regard for 1974, p. 1-20. 10 refs.

254

A75-28349

Stability derivatives for the Bell 205 helicopter have been The present paper discusses the chemical and noise pollution derived from flight data using a least squares quasilinearization produced by aircraft and the implications of environmental con- technique. The aircraft model, which included a first order rep- siderations for the future of commercial aviation. The levels of resentation of rotor response characteristics was based on funda- carbon monoxide, unburned hydrocarbons, oxides of nitrogen, and mental parameters descriptive of the particular design. A con- smoke emitted by present aircraft engines are tabulated, and it is glomerate analysis procedure which produced estimates based on noted that none of the engines meets the 1979 standards set by the data from several similar manoeuvres was used to increase the Environmental Protection Agency. Operational and technological confidence in the results obtained. Data from the CL-84 V/STOL methods for reducing engine emissions are discussed. The considera- aircraft were also analyzed, indicating the validity of certain a priori tion of aircraft noise includes an explanation of the relevant longitudinal stability derivatives for the aircraft, and yielding regulations contained in FAR Part 36. The noise produced by estimates of others. The results indicate the need to use a more aircraft engines is a complex mixture of various types of fan, jet, elaborate modelling technique, such as was used for the Bell 205, tailpipe, and turbine noise. Changes in landing, takeoff, and ground which takes into account the particular complexities of the aircraft. operations are being considered to reduce noise near airports. (Author) Possible changes in engine design, including the use of external noise suppressors, sound-absorbent linings, and above-the-wing engine A75-28222 # Problem of aircraft noise in the vicinity of mourcts, are discussed. A.T.S. airports (Sul problema del rumore degli aeroplani nei dintorni degli aw-oporti). D. Priolo. Istituto Internazionale delle Comunicazioni, A75-28236 Con vegno Internazionale del/a Comunicazioni, 22nd, Genoa, Italy, Stress intensity factors for some through- Oct. 7-12, 1974, Paper. 35 p. 16 refs. In Italian. cracked fastener .holes. A. F. Gran dt, Jr. (USAF. Materials The present paper considers problems involved in airport Laboratory, Wright-Patterson AFB, Ohio). International Journal of planning, including the relationship of the airport to its surroundings, Fracture, vol.11, Apr. 1975, p.283-294.23 refs. especially with regard to the protection of the neighboring area from A stress intensity factor solution is developed for a large plate the harmful effects of noise. A basic introduction is given to the containing radial hole cracks loaded with arbitrary crack face problem of measuring noise and sonic disturbance. The factors pressure. When the pressure is defined as the unflawed hoop stress affecting sound intensity and propagation, the units used to measure surrounding a mechanical fastener, stress intensity factor calibrations sound quantity and quality, and the evaluation of disturbance, as are readily computed by the linear superposition principle. Results distinct from sound, are considered. The West German law on noise, obtained in this manner agree well with previous solutions deter- which took effect in 1971, is discussed. Various noise standards are mined for open holes loaded in remote tension. The potential applied in different zones in relation to the airport. Noise can be usefulness of the present analysis is further demonstrated with controlled by regulating the flight maneuvers and trajectories of application to specific fastener configurations, including interference aircraft near airports. The contributions of the terrain and passive fit fasteners, pin-loaded plates, and cold-worked holes. (Author) measures to noise suppression are considered, A.T.S. A75-28348 • # An experimental study of the structure and A75-28223 # Noise certification of aircraft (Certificazione acoustic field of a jet in a cross stream. I. Camelier (Instituto acustica degli aeromobili). V. Fiorini (Registro Aeronautico Italiano, Tecnologico de Aeronáutica, São José dos Campos, São Paulo, Rome, Italy). Istituto Intemazionale del/a Comunicazioni, Convegno Brazil), K. Karamcheti, and B. Hodder (Stanford University. Intemazionale delle Comunicazioni, 22nd, Genoa, Italy, Oct. 7-12, Stanford, Calif.). American Institute of Aeronautics and Aàtro- 1974, Paper. 16 p. 9 refs. In Italian. nautics, Aero-Acoustics Conference, 2nd, Hampton, Va., Mar. 24-26, The criteria involved in aircraft noise certification are discussed. 1975, Paper 75460. 37 p. 16 refs. Grants No. NGR-05-020-526; No. Special attention is given to Annex 16 of the ICAO convention on NsG-2007. civilian aviation and the conflicts between its noise standards and The investigation reported is related to studies of the noise those of FAR 36. The future prospects of noise regulation are generated by a lifting jet in forward motion such as in the case of a considered. A.T.S. V/STOL aircraft. The investigation involved experiments in a subsonic wind tunnel. The two-microphone cross-correlation method A75-28227 # Jet noise suppressors for turbojet engines. M. used for measuring the acoustic intensity provides data concerning Marini (Fiat S.p.A., Turin, Italy). Istituto Internazionale de/le the noise directly radiated from the source, practically free from any Comunicazioni, Convegno Internazionale della Comunicazioni, 22nd, reflection effects. The theoretical basis of the two-microphone Genoa, Italy, Oct. 7-12, 1974, Paper. 33 p. 8 refs. In Italian. method is discussed along with the experimental apparatus, the The present paper considers the problems involved in noise characteristics of the flow inside the jet, and the features of the suppression, for the purposes of certification, in low- and medium- acoustic field. G. R. power turbojet engines, whose acoustic characteristics are dominated by exhaust-jet noise. This is a broad group, including the engines used in executive jets and transports such as the Boeing 707. The A75-28349 • # Effects of friction and heat conduction on design of a noise-suppression device must take into account the sound propagation in ducts. P. Huerre and K. Karamcheti (Stanford structure of a typical exhaust jet, which comprises the central core, University, Stanford, Calif.). American Institute of Aeronautics and the mixing region, and a region of fully developed turbulent flux Astronautics, Aero-Acoustics Conference, 2nd, Hampton, Va., Mar. downstream of the mixing region. The methods of reducing jet noise 24-26, 1975, Paper 75-520. 35 p. 23 refs. Grants No. include reducing the length of the mixing region and diminishing the NGR-05-020-526; No. NsG-2007. exhaust velocity. General considerations concerning the geometry of A theoretical formulation of the propagation of sound in a lobed silencers and the tosses they entail are outlined. An 8-lobed viscous and heat conducting medium is presented. The problem is silencer designed by Fiat is described. The unit was tested successful- reduced to the determination of two scalar potentials related to ly on a twin-engine HS. 125 aircraft. A.T.S. pressure and entropy fluctuations respectively, and a vector potential related to vorticity fluctuations. The particular case of a two- dimensional duct of constant width is thoroughly investigated in the A75-28228 # Development of air transport and environ- low, high, and very high frequency ranges. It is shown that three mental requirements (Lo sviluppo delle comunicazioni aeree e le distinct families of modes may propagate along the duct axis, esigenze ambientali). G. Maoli (Fiat S.p.A., Turin, Italy). Istituto namely, pressure, entropy, and vorticity dominated modes. Perturba- Intemazionale del/e, Comunicazioni, Convegno Internazionale delle tion methods are used to study the variations of attenuation rates, Comunica.zioni, 22nd, Genoa, Italy, Oct. 7-12, 1974, Paper. 77 p. 33 phase velocities, and mode shapes, as a function of frequency and refs. In Italian. duct width. (Author)

255 A75-28400

A75-28400 Ratio of peak frequencies of jet self and shear A75-28470 # F-15 computational subsystem. T. V. McTigue American Institute of noise spectra. J. R. McCartney (Ulster. New University, Coleraine, (McDonnell Aircraft Co., St. Louis, Mo.). 39. Mar. 22. Aeronautics and Astronautics, Digital Avionics System Conference, Northern Ireland). Journal of Sound and Vibration, vol. 269-272. 7 refs. National Research Council of Canada Grant Boston, Mass, Apr. 2-4, 1975, Paper 75-590. 8 p. 1975. p. A description is given of the computational subsystem used in No. A-2003. the F-15 weapon system. The consolidated computational design approach is discussed in which the mission-oriented computations are A75-28432 Design of a digital-stability augmentation and performed in a single central computer, and the sensor-oriented control system with gust alleviation and modal suppression. M. computations are carried out in special processors in various sensor Healey and H. M. S. Al-Bahrani (University College. Cardiff, Wales). and display equipment. Major characteristics of the central computer Institution of Electrical Engineers, Proceedings, vol. 122, Apr. 1975. hardware and software design are described. Finally, the multiplex p. 437-440. 8 refs. communications system between the central computer and the A stochastic, discrete, implicit model-following control law is interfacing peripheral avionics equipment is outlined. S.D. developed for a stability augmentation and control system for the pitch axis of a flexible-bodied aircraft. Particular attention is paid to the choice of weighting matrices in the quadratic i.p. so as to give a A75-28472 # The U.S. Candidate Microwave Landing Sys- compromise between handling, gust alleviation and modal sup- tem - A new generation of avionics/ground equipment. J. R. Sebring pression. (Author) (Bendix Corp., Communications Div., Baltimore, Md.). American Institute of Aeronautics and Astronautics, Digital Avionics System Conference, Boston, Mass., Apr. 24, 1975, Paper 75-607. 7 p. # Digital avionics from the viewpoint of ATA. F. A75-28466 A scanning beam system which uses a time reference signal C. White (Air Transport Association of America, Washington, D.C.). format is considered. Basic requirements for the new microwave American Institute of Aeronautics and Astronautics, Digital Avionics landing system (MLS) are discussed along with the MLS signal format 5 System Conference, Boston, Mass., Apr. 24, 1975, Paper 75-551. and the installation on a typical runway. A description is given of the p. 6 refs. airborne equipment involved, taking into account the envelope The application of digital technology to air-ground communica- processor, the angle processor, aspects of angle function acquisition, tions is considered, taking into account the supporting role of an the time gate tracker, and time gate acquisition logic. G. R. automation data base. A system approach to civil aircraft navigation using digital technology is discussed along with digital flight control systems considerations related to implementation and acceptance. # The aerodynamic characteristics and trailing Aspects of software engineering of a navigation and guidance system A75-28522 vortex wake of propeller V/STOL configurations. A. H. Wickens for commercial aircraft are examined and a possible airline point of (National Aeronautical Establishment, Ottawa, Canada). Canadian view is presented. G. R. Aeronautics and Space Journal, vol. 21, Mar. 1975, p. 81-98. 11 refs. This paper describes the aerodynamic characteristics of lifting # Interaction of military/civil position location propellers and wing-propeller configurations, with particular refer- A75-28467 ence to the concept of a powered-lift system, and its complex flows and reporting systems. H. Gumbel (Philco-Ford Corp., Palo Alto, American Institute of Aeronautics and Astronautics, Digital downstream in the wake. The propeller, when inclined to large Calif.). angles, and at high advance ratios, is a singular example of a Avionics System Conference, Boston, Mass., Apr. 24, 1975, Paper powered-lift system in which lift is derived partly by deflecting and 75-561. 10 P. energizing a stream tube of air, and in part, by a wing-like vortex This paper presents a comparative analysis of civil navigation flow in which the propeller disc can be thought of as a low aspect and air traffic control systems and corresponding military systems. ratio wing of circular plan form. The trailing wake is characterized by Very different requirements have led to independent developments by the DoD and the FAA in their respective spheres of responsibili- mixed regions of propulsive and vortex flow in which concentrations of vorticity may induce downwash and sidewash velocities of ties. These developments could result in the implementation of considerable magnitude in the surrounding fluid. The propulsive systems incompatible on a hardware level. The cost of redundant use of both systems could be prohibitively costly to the military, not to stream tube, or slipstream, is an integral part of this wake, and speak of cockpit crowding and electronic complications. Civil deforms with it, ultimately rolling up with the trailing vortices. (Author) systems under consideration include ATCRBS, DABS, and IPC and military systems reviewed include AIMS, SEEK BUS, LORAN and GPS. The paper presents an approach to an integrated system which Metallurgical factors affecting high strength would satisfy the requirements of civil air traffic control for military A75-28529 (Author) aluminum alloy production. D. S. Thompson (Reynolds Metals Co., users in peace time. Richmond, Va.). (Symposium on Advances in the Physical Metal- lurgy of Aluminum Alloys, Philadelphia, Pa., May 29-June 1, 1973.) SEEK BUS - A time division multiple access A75-28468 // Metallurgical Transactions A - Physical Metallurgy and Materials system. D. D. Neuman (Mitre Corp., Bedford, Mass.). American Science, vol. 6A, Apr. 1975, p. 671-683. 73 refs. Contracts No. Institute of Aeronautics and Astronautics, Digital Avionics System F33615-72-C-1202; No. F33615-71 -C-1 805. Conference, Boston, Mass., Apr. 24, 1975, Paper 75-564. 5 p. With the advent of' linear elastic fracture mechanics, the detailed The system SEEK BUS is being developed for the U.S. Air Force effects of processing and microstructure on toughness can be as an aid in improving the effectiveness of its air operations. In evaluated. The effect of microstructure on plane stress and plane aircraft, SEEK BUS provides the data required for operations related strain fracture toughness is considered in detail together with to collision avoidance, station-keeping, rendezvous, air-to-air co- strength, fatigue behavior and corrosion resistance. It is concluded ordination, identificatiora, navigation, and instrument landing. The that second phase particles in all size ranges can influence toughness. network architecture is considered along with questions of system Increasing the size and amount of particles or decreasing precipitate feasibility, aircraft position determination, system performance, coherency all lead to decreases in toughness. Grain structure is also system capacity, and questions of signal structure. G.R. shown to play a prominent role in determining plane stress fracture # System approach to civil aircraft navigation toughness; at a given strength level, a fibrous grain structure and the A75-28469 prevention of recrystallization are desirable. Thermomechanical using digital technology. T. A. Ellison (United Air Lines, Inc., San processing is considered to offer a possible route to achieving a Francisco, Calif.). American Institute of Aeronautics and Astro- nautics, Digital Avionics System Conference, Boston, Mass., Apr. 24, desirable balance of toughness, strength and corrosion resistance. (Author) 1975, Paper 75-572. 7 p. 14 refs.

256 A75-28671

A7548626 Aeroacoustics: Fan, STOL, and boundary A75-28653 # Hypersonic, viscous gas flow around a wing of layer noise; sonic boom; aeroacoustic instrumentation. Edited by H. small aspect ratio (Giperzvukovoe viazkoe techenie gaze okolo kryla T. Nagamatsu (GE Research and Development Center, Schenectady, malogo udlineniia). A. I. Ruban and V. V. Sychev. TsAGI, Uchenye N.Y.). New York, American Institute of Aeronautics and Astro- Zap/ski, vol. 4, no. 5, 1973, p. 18-25. In Russian. nautics, Inc. (Progress in Astronautics and Aeronautics Series. The critical stage of a hypersonic flow around a slightly Volume 38); Cambridge, Mass., MIT Press, 1975. 524 p. Members, elongated plate at high Reynolds number is investigated. A class of $19.; nonmembers, $30. self-similar solutions is found, and it is shown that perturbations in Fan, STOL, and boundary layer origins of aircraft noise the symmetry plane of the wing propagate along the boundary layer pollution are considered, as well as certain sonic boom problems, and up to the leading edge. The nature of this propagation is investigated some means of measuring noise pollution are discussed. Topics numerically. P.T.H. covered include broadband noise generation by airfoils and axial flow fans, inlet geometry and axial Mach number effects on fan noise A75-28654 # The three-dimensional character of a cross propagation, source noise suppression of subsonic tip speed fans, flow around a circular cylinder (0 trekhmernom kharaktere surface pressure fluctuations in hypersonic turbulent boundary poperechnogo obtekaniia krugovogo tsilindra). A. I. Korotkin. layers, distortion of weak shock waves by turbulence in a stratified TsAGI, Uchenye Zap/ski, vol. 4, no. 5, 1973, p. 26-33. 6 refs. In still atmosphere, and hypersonic flow velocity measurements using Russian. the laser velocimeter. Results of wind tunnel investigations of the three-dimensional flow around the surface of a circular cylinder in the region of flow S.J.M separation at Reynolds numbers corresponding to subcritical and supercritical flow regimes are presented. The characteristic size of the cell structure of the flow along the cylinder generatrix in the A75-28629 Aeroacoustjcs: Jet and combustion noise; duct separation zone is compared with known experimental data for the acoustics. Edited by H. T. Wagamatsu (GE Research and Develop- corresponding size in the wake behind the cylinder. P.T.H. ment Center, Schenectady, N.Y.). New York, American Institute of Aeronautics and Astronautics, Inc. (Progress in Astronautics and A75-28658 Aeronautics Series. Volume 37): Cambridge, Mass., MIT Press, 1975. # Study of two hypersonic, axisymmetric, shaped nozzles with smooth contour (Issledovanie dvukh giper- 556 p. Members, $19.; nonmembers, $30. Jet and combustion sources of aircraft noise pollution are zvukovykh osesimmetrichnykh profilirovannykh sopl s gladkim investigated, and some aspects of duct acoustics are examined. konturom). N. V. Denisova, I. I. Mezhirov, and lu. I. Chistov. TsAGI, Uchenye Subjects studied include the relationship between acoustic energy Zap/ski, vol.4, no. 5, 1973, p.56-64.7 refs. In Russian. density flux near the jet axis and far-field acoustic intensity, the The present work describes the aerodynamic design and experi- effect of temperature on supersonic jet noise, jet noise suppression mental investigation of two hypersonic, axisymmetric nozzles, by swirling the jet flow, noise generation by ducted combustion calculated with account for the effect of viscosity on the establish- systems, core engine noise, sound interaction with a ducted helical ment of a nearly uniform flow at Mach numbers 13.45 and 15.45. flow, use of a relaxation technique in nozzle wave propagation The isentropic Contours of the nozzles have Continuous derivatives problems, and a theoretical and experimental study of sound up to the third, inclusively. The experimental nozzles secured a flow close to that calculated, with variations within the limits of plus or attenuation in an annular duct. S.J.M. minum 1%. Smooth flow buildup was obtained without significant Mach number perturbations along the axis. P.T.H. A75-28650 # Part load specific fuel consumption of gas turbines. J. Jerie (Ceske Vysoke Uceni Technicke, Prague, Czecho- A75-28665 # Interaction between a sonic boom N-wave and slovakia). ASME, Transactions, Series A - Journal of Engineering for an obstacle near corner points (Vzaimodeistvie N-volny zvukovogo Power, vol. 97, Apr. 1975, p. 303, 304. udara $ prepiatstviem v okrestnosti uglovykh tochek). K. B. Sokolov. An analysis is made of the effect of various thermodynamic and TsAGI, Uchenye Zap/ski, vol. 4, no. 5, 1973, p. 104-109. 9 refs. In design conditions on the feasibility of improving the part Iced Russian. specific fuel consumption (PLSFC) of gas turbines. It is shown that A conical shock tube is used to study the impact of a appropriate control of compressor and turbine characteristics is sonic-boom wave on the upper portion of a model structure important in practically all developments of gas turbines aimed at (parallelepiped) to determine the time-behavior of the pressure acting improving the PLSFC. A.T.S. on a building. The effects of diffraction and reflection of the N-wave at the corners and roof of the model are taken into consideration. The effect of the low-pressure wave arising at an upper corner of the A75-28651 # Theory of transonic flow around a profile (K building on the pressure distribution over the wall exposed to the teorii transzvukovykh techenhi okolo profilia). lu. B. Lifshits. TsAGI, shock wave is evaluated. The pressure on the building near the apex Uchenye Zapiski, vol.4, no. 5, 1973, p. 1-8.8 refs. In Russian. of a triangular corner is plotted against time. The characteristics of transonic flow of an ideal gas around three S.D. different wing profiles are investigated. The change in flow parameters is studied during the transition from a computational regime A75-28668 # Influence of fuselage flexibility on the stress characterized by isentropic compression in the local supersonic zone strain state of the wing (0 vliianii podatlivosti fiuzeliazha na to a flow with a shock wave. The location and form of the shock napriazhenno-deformirovannoe sostoianie kryla). V. A. Belous. waves are analyzed. P.T.H. TsAGI, (Jchenye Zap/ski, vol.4, no. 5,1973, p. 119-124. In Russian. Some aspects of the calculation of the stresses and strains in a A75-28652 # Calculation of the flow around blunted, non- wing, in the case where the middle surface of the wing is arbitrarily symmetric cones with large aperture angle (Raschet obtekaniia spaced from the neutral line of the fuselage. A panel/girder scheme zatuplennykh nesimmetrichnykh konusov s bol'shim uglom rast- for the solution of the problem is proposed, and is applied to wing vora). A. P. Bazzhin and S. V. Pirogova. TsAGI, Uchenye Zapiski, stress calculations for low-wing, midwing, and high-wing monoplane. vol.4, no. 5, 1973, p.9-17.6 refs. In Russian. The stresses caused by plane deformation of the wing middle surface A finite difference method is used to compute the supersonic are compared to stresses arising due to wing twist. V.P. flow across blunt axisymmetric and nonaxisymmetric bodies formed from a 120-degree cone by spherically blunting the nose section and A75-28671 # Nonlinear problem of the unsteady flow past rounding off the side edge. Various mixed gas flows are calculated, an airfoil lattice (Nelineinaia zadacha o nestatsionarnom obtekanii differing in Mach number, body geometry, gas properties, and angle reshetki profilei). V. P. Riabehenko. TsAGI, Uchenye Zap/ski, vol.4, of attack. P.T.H. no. 6, 1973, p. 8-16. 7 refs. In Russian.

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A numerical method is proposed for solving the nonlinear A75-28770 # A specialised recording system for the mea- problem for an airfoil lattice which, starting from rest, performs surement of helicopter rotor blade performance in flight. F. B. arbitrary motions in ideal incompressible potential flow. The Moulang (Royal Aircraft Establishment, Bedford, Hants., England). solution is obtained in time steps, at each of which the problem In: International Aerospace Instrumentation Symposium, 8th, Cran- becomes a linear one. The method is essentially an extension of a field, Beds., England, Mar. 24-27, 1975, Proceedings. method proposed by Riabchenko and Saren (1972) for the linear London, Royal Aeronautical Society, 1975. 12p. problem of the flow past a vibrating lattice of arbitrary airfoils. As an Flight measurements of the detailed aerodynamic performance example, the method is applied to the synchronous harmonic of helicopter aerofoil sections have been made at the Royal Aircraft in-phase and out-of-phase vibrations of airfoils. V.P. Establishment, Bedford as part of a continuing program to increase overall helicopter rotor performance. This paper describes a complete system designed for the acquisition and analysis of large numbers of A75-28676 # Qualitative analysis of a family of extrenluflls in a problem involving optimal control of aircraft motion (Kachest. blade surface pressures. The large amount of data involved in these vennoe issledovanie semeistva ekstremalei v odnoi zadache optimal'- measurements demands an automatic processing method. The data is nogo upravienila dvizheniem samoleta). V. F. lllarionov and V. T. therefore recorded on magnetic tape and is processed via a complex Pashintsev. TsAGI, Uchenye Zap/ski, vol. 4, no. 6, 1973, p. 58-65. In hybrid computing installation to give a final output in the form of Russian. graphic displays (which may be hard copy) and tabulated coeffi- An energy method is applied to the problem of optimizing flight cients. (Author) control for minimum fuel consumption over a prescribed range. A procedure is proposed for determining, in the altitude-velocit y plane, A75-28771 # Application of a new slip-ringless propeller the loci of points corresponding to moments at which instantaneous blade measurement system. M. J. Walker (National Aviation Facilities steady optimum-trust modes are realized and for establishing the Experimental Center, Atlantic City, N.J.). In: International Aero- direction in which the phase point moves. V.P. space Instrumentation Symposium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, Proceedings. London, Royal Aeronautical Society, 1975. 10 p. A75-28680 // An example of boundary layer flow with two A propeller-mounted blade vibration data system has been used instability regions (Primer techenila v pogranichnom sloe s dvumia for the acquisition of propeller-operating stress data for single and oblastiami neustoichivosti). V. M. Lytovinov. TsAGI, Uchenye twin engine general aviation aircraft in flight. The system overcomes Zap/ski, vol.4. no. 6. 1973. p. 88-93. 8 refs. In Russian. the difficulties of traditional slip-ring and brush assemblies. Tests The stability of the boundary layer flow on a wing is analyzed in have proven it to be highly accurate, and results obtained with it a direction normal to the mainstream for the case where S-shaped have been reproducible. S.J.M. velocity profiles with two points of inflection may occur beyond the line of minimum pressure. Numerical calculations indicate that for A75-28774 * # A new flight test data system for NASA such velocity profiles, the region of instability is bounded by two aeronautical flight research. K. C. Sanderson (NASA, Flight Research intersecting neutral curves. It is shown that the phase velocity of the Center, Edwards, Calif.). In:. International Aerospace Instrumenta- disturbances near the critical Reynolds number is close to the tion Symposium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, velocity at the point of inflection situated nearer to the wall. The Proceedings. London, Royal Aeronautical So- minimum Reynolds number along a second neutral curve is found to ciety, 1975. 17 p. 10 refs. be noncritical. S.D. The airborne integrated flight test data system (AIFTDS) is described. This system integrates an airborne digital computer with a high-bit-rate pulse code modulation system. Its design was influenced A75-28887 # Allowance for the elastic deformation of the by in-house technical experience with similar modules and b y the wing in its own plane in the calculation of the skewsymmetric multiproject environment in which it was expected to operate. The vibrations of an aircraft with a small-aspect-ratio wing (Uchet present work describes events leading to the development of the uprugoi deformatsii kryla v svoei ploskosti pri raschete antisim- system, reviews factors that influenced the objectives for the system metrichnykh kolebanii samoleta $ krylom malogo udlineniia). V. A. and the resulting design, and describes the elements themselves. Mosunov. TAGI, Uchenye Zap/ski, vol. 4, no. 6, 1973, p. 131-137. Block diagrams supplement the text. S.J.M. In Russian.

A75-28778 # Development of an R.F. telemetry system. H. A75-28717 * New evidence of the mechanisms of noise W. Redhead. In: International Aerospace Instrumentation Sym- generation and radiation of a subsonic 'et. L. Maestrello and S. P. Pao posium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, Proceed- (NASA, Langley Research Center, Hampton, Va.). Acoustical So- London, Royal Aeronautical Society, 1975. vol. 57, Apr. 1975. p. 959, 960. ings. ciety of America, Journal, p. A multi-channel miniature telemetry system designed to obtain dynamic stress and temperature data from engine rotors is described. Data recording and analysis, system Construction, the module test A75-28769 # Take-off instrument for assessing achieved sequence, system build, engine installation, running experience, and performance during take-off and a take-off accident analysed in system development are discussed. Emphasis in design was placed on context. J. H. H. Grover (Miles-Phoenix, Ltd.). In: International presentation of th data in a form readily assimilable b y the engineer. Aerospace Instrumentation Symposium, 8th, Cranfield, Beds., S.J.M. England, Mar. 24-27, 1975, Proceedings. London, Royal Aeronautical Society, 1975. 12 p. Criteria defining adequate aircraft performance during takeoff A75-28781 # Wide bandwidth optical telemetry link for are assessed, and the Miles-Phoenix runway distance indicator (RD I) ground testing of equipment in high EMI environments. C. G. is recommended as a highly effective safety measure. This instrument Wildey, J. M. Ley, and J. S. Mitchell (Electro Optic Developments, shows aircraft speed and runway distance remaining in relation to a Ltd., Brentwood, Essex, England). In: International Aerospace decision point, at which takeoff (good performance) or deceleration Instrumentation Symposium, 8th, Cranfield, Beds., England, Mar. (poor performance) courses can bo. chosen. It is suggested that an 24-27, 1975, Proceedings. London, Royal Aero- accident occurring at Anchorage, ,Alaska in 1970 could have been nautical Society, 1975.9 p.7 refs. Research supported by the Royal averted if this equipment had been in use. U.M. Aircraft Establishment.

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The present work describes a wide-bandwidth (approximately examined: pilot's display (presentation), accuracy and performance, 100 MHz) laser telemetry link developed to provide a telemetry reliability, and operating principle. It is concluded that no great facility in intense electromagnetic pulse environments. The equip- change is foreseen in the display presentation of altimeters (that the ment was intended for ground testing of aircraft subsystems counter/pointer type will become almost universal); that servo subjected to electrically simulated nuclear environments. The optical altimeters will gradually replace mechanical ones; that baro altitude system discussed has important advantages over microwave trans- will continue to be the main altitude reference up to altitudes of at mitters for this purpose. S.J.M. least 50,000 feet; and that radio altimeters will expand their role of providing accurate landing references. S.J.M.

A75-28785 # A new centralised warning display for aircraft. S. Beddoe (Plessey Co.. Ltd., Titchfield, Hants., England). In: A75-28790 # Airborne equipment for use with the micro- International Aerospace Instrumentation Symposium, 8th, Cranfield, wave landing system. J. P. Birchenough and K. Lawson (Plessey Co., Beds., England, Mar. 24-27, 1975, Proceedings. Ltd., Ilford, Essex, England). In: International Aerospace Instrumen- London, Royal Aeronautical Society, 1975.9 p. Research supported tation Symposium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, by the Ministry of Defence (Procurement Executive). Proceedings. London, Royal Aeronautical The present work outlines the development of a new improved Society, 1975. 11 p. central warning display for aircraft. The project was undertaken Several proposed alternatives to the instrument landing system because it was considered that significant improvements in both (ILS) presently in use, which fall under the heading 'microwave performance and reliability could be achieved over existing designs. landing system' (MLS), are reviewed. Disadvantages of the ILS, The new design uses an assembly of miniature electromagnetic general requirements for the MLS, the Doppler MLS design, ground indicators of improved construction in association with an original guidance installations, the 'ILS replacement' airborne receiver, the process of low-level lighting. Various tests were carried out to assist comprehensive modular receiver, and airborne equipment integrity in making the decision to employ electromagnetic indicators rather are considered. S.J.M. than the more common semiconductor interface displays. S.J.M.

A75-28791 # Characteristics of MIS signals and their effect A75-28786 # Integrated avionics - Controls and displays for on flight control systems. G. McConville (Smiths Industries, Ltd., helicopter IFR operation. F. J. Winter, Jr. (USAF. Flight Dynamics Wembley, Middx., England). In: International Aerospace Instrumen- Laboratory, Wright-Patterson AFB, Ohio). In: International Aero- tation Symposium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, space Instrumentation Symposium, 8th, Cranfield, Beds., England, Proceedings. London, Royal Aeronautical Mar. 24-27, 1975, Proceedings. London, Royal Society, 1975. 11 p. Aeronautical Society, 1975. 11 p. A three-part study was undertaken to assess MLS performance. A flight research effort has been established to investigate all The study simulated maneuvers executed to exercise the aircraft/ aspects of helicopter instrument flight rule (IFR) operations ranging autopilot combination in the appropriate modes. The elevation 1 from lift-off through transition to cruise and approach to hover and MLS model assumed the aircraft to be initially flying at a constant landing. The basic purpose is to evaluate recent developments in height of 2000 ft.; the azimuth study had the plane initially flying in rotary wing instrument flight capability. These developments center heading steering mode to give a 45 deg intercept with the ILS radial; around vehicle controllability through both control/display and and the elevation 2 MLS model supposed that the aircraft was stability augmentation systems. The configuration to be first initially established on a 3 deg glide path. Means by which the evaluated was designed from the results documented by actual pilot integrity of an AFCS can be influenced by the MLS are discussed. performance during typical rotary wing IFR maneuvers. The S.J.M. maneuver profiles were designed and flown to record pilot activity and aircraft attitude. Several subject pilots flew the designed profiles to establish in what areas improvements were required. Each pilot's A75-28792 # The range of airborne processing available to performance was then computerized to create a 'mean' value of pilot the future user of the Doppler MLS. P. Barton, F. G. Overbury, and ability to perform prescribed tasks. The analysis of the data gathered P. K. Blair (Standard Telecommunication Laboratories, Ltd., Harlow, determined in what areas pilot performance could most likely be Essex, England). In: International Aerospace InstrumentatiOn improved through refined helicopter controls and displays. (Author) Symposium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, Proceedings. London, Royal Aeronautical A75-28787 A new J band pulsed radar altimeter. W. P. Society, 1975. 12 p. Northen (Plessey Co, Ltd., Ilford, Essex, England) and I. D. The Doppler MLS operational parameters and range of applica- Longstaff (Royal Radar Establishment, Malvern, Worcs., England). tion are considered. The principles of Doppler scanning signal In: International Aerospace Instrumentation Symposium, 8th, generation, the basis of airborne processing, narrow-band filtering, Cranfield, Beds., England, Mar. 24-27, 1975, Proceedings. time gating and tracking methods, the fixed-course discriminator, the London, Royal Aeronautical Society, 1975. 12 p. selectable course discriminator, the sine-cosine tracker for wide A new pulsed radar altimeter has been developed for small coverage azimuth or elevation 1 systems and the high-performance helicopter and light aircraft applications. A number of improvements elevation processor for low-angle coverage are discussed and on current altimeters have been possible through the choice of a high described. S.J.M. resolution system operating at J band. The aerials have been combined into the same box as the T/R Unit. High resolution has allowed the use of a simplified leading edge tracker. A technique of continuous reference tracking has been adopted to improve accuracy A75-28793 # Astrolabe - A synthetic circular aperture sys- and integrity. Flight testing has shown that the system performance tem for landing and navigation. J. Dorey and G. Gamier (ONERA. is suited to many low level applications. (Author) Ctiãtillon-sous-Bagneux, Hauts-de-Seine, France). In: International Aerospace Instrumentation Symposium, 8th, Cranfield, Beds., A75-28788 # Altimeters - The way ahead. A. N. Du Feu England, Mar. 24-27, 1975, Proceedings. (Smiths Industries, Ltd., Wembley, Middx., England). In: Interna- London, Royal Aeronautical Society, 1975.14 p. tional Aerospace Instrumentation Symposium, 8th, Cranfield, Beds., The new Astrolabe MLS is described in terms of its theoretical England, Mar. 24-27, 1975, Proceedings. properties and preliminary reexperimental results. In this system, the London, Royal Aeronautical Society, 1975. 14 p. 12 refs. two angular coordinates (elevation and azimuth) are obtained by Four key features responsible for the present form of the two-dimensional phase modulation of a microwave carrier induced altimeter and determining its future course of development are by the continuously rotating motion of an isotropic antenna. It is

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explained how, by using quasi-holographic techniques in signal processing, it is possible to obtain a multifunctional system for both the air-derived and ground-derived configurations. This multifunctional system combines (1) takeoff, approach and landing aid. (2) display of the external situation for navigational aids, and (3) zone navigation. S.J.M.

A75-28797 # The development of a serial P.C.M. instrumentation system. M. J. Taylor (Hawker Siddeley Aviation, Ltd., Woodford, Essex, England). In: International Aerospace Instrumen- tation Symposium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, Proceedings. London, Royal Aeronautical Society, 1975. 14 p. The current work covers progress from specification to test work on a PCM instrumentation system. It also describes some of the experiences and results from its use during 70 hours of development flying for the Victor K.Mk.2 tanker aircraft. Photographs and diagrams supplement the text. Specifications include large input capacity, flexible sampling rate, and computerized data recovery. S.J.M.

A75-28801 # The benefits of real time computer analysis of experimental aircraft flight test data. R. P. LeCann (Grumman Data Systems Corp., Bethpage, N.Y.). In: International Aerospace Instru- mentation Symposium. 8th, Cranfield, Beds., England, Mar. 24-27, 1975, Proceedings. London, Royal Aeronautical Society, 1975. 12p. The process of multidiscipline or integrated testing used in conjunction with real-time computer analysis is described, and its benefits to flight testing are indicated. Its effect is most noticeable during the initial development phase of envelope expansion. Flying qualities testing, a flight loads program, performance testing, propulsion testing, and limit checking with this process are considered. SJ.M.

A75-28802 # Testing the MIS Doppler concept. A. E. Brindley and L. C. Calhoun (I IT Research Institute, Chicago, III.). In: International Aerospace Instrumentation Symposium, 8th, Cranfield, Beds., England, Mar. 24-27, 1975, Proceedings. London, Royal Aeronautical Society, 1975. 12 p. The present paper describes an experimental program conducted to develop and MLS to replace existing ILS equipment in the 1980s. The program is deemed to have been successful, and it selected the Doppler technique rather than the scanning beam method for further testing. Instrumentation design, data reduction, data acquisition, field tests, results of a concept validation program, and a multipath investigation are described. The following features of the flexibly designed data collection and reduction system made for simplicity in programming: (1) standard variable names, (2) standard input, output, and conversion program, and (3) use of FORTRAN IV and a standard plotting language. S.J.M.

A75-28866 # Fatigue strength of D16T Duralumin at normal and elevated temperatures as a function of the cycling rate (Soprotivlenie duraliumina D16T ustalostnomu razrusheniiu pri normal'noi i povyshennoi temperaturakh V zavisimosti ot skorosti tsiklicheskogo nagruzheniia). A. V. Karlashov, V. V. Sazonov. and V. P. Tokarev (Kievskii Institut Inzhenerov Grazhdanskoi Aviatsii, Kiev, Ukrainian SSR). Problemy Prochnosti, Feb. 1975, p.84-87.9 refs. In Russian.

260 N75-19134

sub 0 - alpha), while in the later, substantial improvements (reduced tracking error (55%). decreased maximum altitude variations (67%), and decreased speed variations (43%)), were obtained using the tactual display. It appears that such a display offers considerable potential for inflight use. Author

STAR ENTRIES N7519132* Bolt, Beranek, and Newman, Inc., Cambridge, Mass EVALUATION OF TACTUAL DISPLAYS FOR FLIGHT CONTROL William H. Levison, Robert B. Tanner. and Thomas J. Triggs In MIT Proc. of the 9th Ann. Conf. on Manual Control 1973 p 55-71 refs Sponsored in part by ARPA N75-19127 Michigan Univ.. Ann Arbor. Dept. of Aerospace Engineering. (Contract N00014-73-C-0031) EFFECTS OF VISUAL FLIGHT DISPLAY DYNAMICS ON CSCL O1C ALTITUDE TRACKING PERFORMANCE IN A FLIGHT Manual tracking experiments were conducted to determine SIMULATOR the suitability of tactual displays for presenting flight-control E. F. Weener, A. M. Howe., and A. W. Pew In MIT Proc. of information in multitask situations. Although tracking error scores the 9th Ann. Conf. on Manual Cntrol 1973 p 3-8 are considerably greater than scores obtained with a continuous visual display, preliminary results indicate that inter-task interfer- CSCL 05E ence effects are substantially less with the tactual display in The effects were studied of visual display dynamics on pilot situations that impose high visual scanning workloads. The tracking performance in a simulator. The tracking task consisted single-task performance degradation found with the tactual display of maintaining the piloted aircraft at the same altitude as two appears to be a result of the coding scheme rather than the aircraft positioned three-hundred feet ahead; as would be required use of the tactual sensory mode per Se. Analysis with the in level formation flying. The two leading aircraft were represented state-variable pilot/vehicle model shows that reliable predictions symbolically along with the horizon on a CAT display. Vertical of tracking errors can be obtained for wide-band tracking systems position of these aircraft with respect to the horizon indicated once the pilot-related model parameters have been adjusted to the altitude of the subject's aircraft, which was disturbed by reflect the pilot-display interaction. Author atmospheric turbulence. Various bandwidths of second-order dynamics were interposed between the true aircraft altitude and N7519133* Air Force Inst. of Tech.. Wright-Patterson AFB, the displayed altitude, whereas no dynamics were interposed in Ohio. the attitude display. Experiments were run using two experienced PITCH PAPER PILOT REVISITED pilots and two substantually different longitudinal dynamics for John D. Arnold, Robert B. Johnson, and James D. Dillow In the piloted aircraft. Preliminary results indicate a significant MIT Proc. of the 9th Ann. Conf. on Manual Cnntrnl 1973 decrease in altitude tracking performance for display dynamics p 75-81 refs with natural frequencies below ten radians per second. Author CSCL O1C Two methods are described for predicting the handling qualities of an aircraft in pitch. Both methods are based on N7519128* National Aeronautics and Space Administration. minimizing a pilot rating expression with respect to free pilot Ames Research Center, Moffett Field. Calif. parameters. In one case the pilot rating expression was developed A STUDY ON AIRCRAFT MAP DISPLAY LOCATION AND from a set of moving base simulation data. In the other case, ORIENTATION the pilot rating expression was developed from a set of fixed D. L. Baty. T. E. Wempe. and E. M. Huff In MIT Proc. of the base simulation data. In both cases pilot rating is primarily a 9th Ann. Conf. on Manual Control 1973 p 9-24 refs function of pitch attitude and pitch rate; however, in the moving base case, the pilot rating is more sensitive to pitch rate than CSCL 010 in the fixed base case. For each method. predicted pilot ratings Six airline pilots participated in a fixed-base simulator study and performance measures agree well with the measured data to determine the effects of two Horizontal Situation Display corresponding to that case. Both methods are used to predict (HSD/map) panel locations relative to the Vertical Situation pilot ratings for a set of flight test configurations and the results Display (VSD), and of three map orientations on manual of the two methods agree to within one half a rating unit. The piloting performance. Pilot comments and opinions were formally predicted ratings in both cases correlate well with the actual obtained. Significant performance differences were found between pilot ratings from the flight tests. Author wind conditions, and among pilots, but not between map locations and orientations. The results also illustrate the potential tracking N75-19134 Air Force Inst. of Tech.. Wright-Patterson AFB, accuracy of such a display. Recommendations concerning display Ohio. location and map orientation are made. Author ROLL PAPER PILOT Flynoy R. Naylor, James D. Dillow. and Russell A. Hannan In MIT Proc. of the 9th Ann. Conf. on Manual Control 1973 N75-19131 * Ohio State Univ., Columbus. Dept. of Aviation. p 83-92 refs A TACTUAL PILOT AID FOR THE APPROACH-AND- CSCL O1C LANDING TASK: INFLIGHT STUDIES A mathematical model for predicting the pilot rating of an Richard D. Gilson and Robert E. Fenton In MIT Proc. of the aircraft in a roll task is described. The model includes: (i) the 9th Ann. Conf. on Manual Control 1973 p 49-53 refs lateral-directional aircraft equations of motion; (2) a stochastic gust model; (3) a pilot model with two free parameters; and CSCL 01 (4) a pilot rating expression that is a function of rms roll angle A pilot aid -- a kinesthetic-tactual compensatQry display -- and the pilot lead time constant. The pilot gain and lead time for assisting novice pilots in various inflight situations has constant are selected to minimize the pilot rating expression. undergone preliminary inflight testing. The efficacy of this display, The pilot parameters are then adjusted to provide a 20% stability as compared with two types of-visual displays, was evaluated margin and the adjusted pilot parameters are used to compute in both a highly structured approach-and-landing task and a less a roll paper pilot rating of the aircraft/gust configuration. The structured test involving tight turns about a point. In both roll paper pilot rating was computed for 25 aircraft/gust situations, the displayed quantity was the deviation (alpha sub configurations. A range of actual ratings from 2 to 9 were 0 - alpha) in angle at attack from a desired value alpha sub 0. encountered and the roll paper pilot ratings agree quite well In the former, the performance with the tactual display was with the actual ratings. In addition there is good correlation comparable with that obtained using a visual display of (alpha between predicted and measured rms roll angle. Author

261 N75-19135

N7519135* Air Force Flight Dynamics Lab., Wright-Patterson parameters in terms of allowable path deviations and pilot AFB, Ohio. workload levels, a Set of director laws is achieved which allows PAPER PILOT PONDERS SUPERSONIC TRANSPORTS improved system performance at reduced workload levels. The pilot acts essentially as a proportional controller with regard to John A. Stone In MIT Proc. of the 9th Ann. Conf. on Manual the director signals, and control motions are compatible with Control 1973 p 95-101 refs those appropriate to status-only displays. Author CSCL O1C N75-19141 * Deutsche Forschungs- und Versuchsanstalt fuer The application is described of the digital program Pitch Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). Paper Pilot to a presimulation analysis of a large delta wing IMPROVEMENTS IN PILOT/AIRCRAFT-INTEGRATION BY aircraft similar to the Concorde supersonic transport. Pilot ADVANCED CONTACT ANALOG DISPLAYS acceptance (in terms of Cooper-Harper ratings), pilot model V. Wilckens In MIT Proc. of the 9th Ann. Conf. on Manual parameters, and pilot-vehicle performance were predicted by Paper Control 1973 p 175-192 refs Pilot and compared to actual inflight measures. Results are good and illustrate the value of using the Paper Pilot concept CSCL 01 during the planning stages of simulation. Author Several expert statements selected from literature and concerning the qualities of modern information displays lead to the definition of a number of requirements which should be N75.19137* Bolt. Beranek, and Newman, Inc., Cambridge, Mass. covered by the displays of the future. It is shown that abstract A DISPLAY EVALUATION METHODOLOGY APPLIED TO displays principally cannot fulfill all these demands and that simply VERTICAL SITUATION DISPLAYS superimposing abstract symbols with the natural view of the Sheldon Baron and William H. Levison In MIT Proc. of the outside world or with it's artificial equivalent will not result in 9th Ann. Conf. on Manual Control 1973 p 121-132 refs an optimum solution. Some test results are shown for confirma- tion of the concept; Special and general problems are touched. (Contract NAS2-6652) Author CSCL OlD An approach to display evaluation based on the optimal- N75-19165 Polish Academy of Sciences. Warsaw. control or state-variable model of the human operator is described. COMPUTATION OF AIRFOIL DRAG PROFILES [OS- The approach evolved over the past several years, and is believed LICZENIA OPORU PROFILOW LOTNICZYCH] to have significant advantages for display evaluation. The Zenon Nowak 1974 39 p refs In POLISH foundations of the methodology are briefly described, and results )Rept-35 /1974) Avail: Issuing Activity are presented of its application to the analysis of vertical situation An algorithm is described for the automatic calculation of displays for STOL approach. This analysis includes the effects the drag coefficients of airfoil profiles at an angle of attack of both status and command displays on pilot workload and value not greater than a few degrees, a given value :of the system performance. Author Reynolds number, and the value of the Mach number near zero. The computation also supports the classical theory of boundary N7519138* McDonnell-Douglas Corp.. Long Beach, Calif. layers. A computer program is presented in ALGOL 1204 language A CONFORMAL HEAD-UP DISPLAY FOR THE VISUAL together with a description of its usage. Transl. by M.J.S. APPROACH J. M. Naish In MIT Proc. of the 9th Ann. Conf. on Manual N75-19166 Stanford Univ., Calif. Control 1973 p 133-145 refs FLAPPING RESPONSE CHARACTERISTICS OF HINGELESS ROTOR BLADES BY A GENERALIZED HARMONIC BAL- CSCL 010 ANCE METHOD Ph.D. Thesis The degree of conformity used in matching a superimposed David Allen Peters 1974 175 p display to its visual background is considered in relation to the Avail: Univ. Mièrofilms Order No. 74-27083 information available for vertical guidance and control during a Linearized equations of motion for the flapping response of purely visual approach. The information may be represented by flexible rotor blades in forward flight are derived in terms of individual symbols or combined in a single symbol, and the relative generalized modal coordinates using the Rayleigh-Ritz method. merits of these methods are discussed. A fully conformal display The equations are sufficiently general to apply to hingeless or format is developed for the purpose of showing both the articulated rotors (with hinge offset and root spring restraint), position and direction of the flight path, with provision for the including variable section properties and pitch-flap coupling. The effects of disturbances, ILS compatibility, and control needs. The aerodynamic model includes the reversed flow region, compressi- field of view needed for all conditions and phases of the visual bility, and radial and azimuthal variations in the lift-curve slope. approach with a fully conformal display is studied in relation to The basic physical characteristics of hingeless rotor response the limitations of conventional collimator systems. Methods are derivatives are examined. First, approximate expressions for certain discussed which depend on deviation of the sight line, and on rotor derivatives are obtained (with some simplifications and windshield reflection of the uncollimated image of a simple pointer. assumptions) to gain direct insight into hingeless rotor response Limited flight tests show some promise for the uncollimated mechanisms. Second, numerical results are presented to illustrate method. Author the relationships between basic rotor parameters and rotor response characteristics. Rotor response derivatives are then N7519140* Bolt, Beranek, and Newman, Inc., CambridQe, Mass. calculated using a variety of mathematical modeling assumptions A MODEL BASED TECHNIQUE FOR THE DESIGN OF to determine the sensitivity of the results to modeling approxima- FLIGHT DIRECTORS tions. Dissert. Abstr. William H. Levison In MIT Proc. of the 9th Ann. Conf. on Manual Control 1973 p 163-172 refs N75-19167 Stanford Univ., Calif. ROTATION IN VIBRATION, OPTIMIZATION. AND AERO- (Contract NAS2-6652) ELASTIC STABILITY PROBLEMS Ph.D. Thesis CSCL O1C Krishna Rao Venkata Kaza 1974 193 p A new technique for designing flight directors is discussed. Avail: Univ. Microfilms Order No. 74-27045 This technique uses the optimal-control pilot/vehicle model to The governing equations of motion for the study of vibra- determine the appropriate control strategy. The dynamics of this tion and dynamic stability of a rapidly rotating deformable body control strategy are then incorporated into the director control are developed starting from the nonlinear theory of elasticity. laws, thereby enabling the pilot to operate at a significantly Vibration frequencies in perpendicular planes of a rotating uniform lower workload. A preliminary design of a control director for beam inclined at an arbitrary angle of the axis of rotation are maintaining a STOL vehicle on the approach path in the presence calculated. A stability analysis of this beam is performed with of random air turbulence is evaluated. By selecting model the angle of inclination and rotational speed as parameters.

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Optimum depth and the optimum mass distribution of a rotating fleet. The computer predictions indicate that relatively large aircraft beam with a fundamental flapping frequency and rotational speed (light jet transport) can experience unacceptable vortex-induced is calculated using a numerical iterative method to solve the roll excursions. Dissert. Abstr. resulting two-point nonlinear boundary-value problem. The effect of steady coning angle and internal damping at the blade flapping P375-19171 Arizona Univ., Tucson. hinge on whirl flutter stability in prop-rotors is investigated. The UNSTEADY VISCOUS FLOW PAST A LIFTING PLATE Ph.D. developed mathematical equations and their analyses are applied Thesis to wind tunnel models. The results indicate that these new Robert Anthony Schmall 1974 200 p parameters have a marked influence on stability, and that they Avail: Univ. Microfilms Order No. 74-28305 change the critical flutter mode. The destabilizing effect of damping A technique for the analysis of unsteady viscous fluid flows at the blade flapping hinge is discovered to be analogous to past aerodynamic shapes is reported. The utility of this tech- the effects of internal damping in gyroscopic systems. nique, called the vorticity source method, is demonstrated by Dissert. Abstr. application to the two-dimensional, constant property flow created by a finite chord flat plate that is impulsively accelerated from N75-19168 Cincinnati Univ.. Ohio. rest to a Constant velocity. The plate is maintained at a constant ANALYSIS OF THICK TURBULENT JET FLOWING ROUND: angle of attack alpha, as measured between the plate chord A CIRCULAR CYLINDER Ph.D. Thesis and the velocity vector of the plate. The flow field development SulaimanOwolabi Talabi 1974 123 p with time is calculated, using numerical solutions to the vorticity Avail: Univ. Microfilms Order No. 74-27147 transport equation. The fluid far from the plate is at rest. Adopting Analytical and experimental investigations of the flow of a elements of inviscid aerodynamic theory, the velocity field is thick, turbulent, and incompressible jet over a circular cylinder related to the vorticity field through the Biot-Savart Law. The are carried Out. A mathematical model which uses the concept method also allows the numerical computations to be confined of equivalent uniform velocity profile is constructed. Based on to the region of non-zero vorticity near the plate. This latter this model, radial and surface pressure distributions over the consideration is an advantage not found in conventional surface of the cylinder are predicted. Fekete and Guitton's empirical approaches based on the stream function. - Dissert. Abstr. relation of the growth rate of turbulent jets flowing over curved surfaces is used in conjunction with some of the present N75-19172 *# Iowa State Water Resources Research Inst., Ames. experimental data to propose an analytical relation between the Engineering Research Inst. exit jet height and the angle of separation. Properties of the jet IPdVISCID TO TURBULENT TRANSITION OF TRAILING are studied and are graphically illustrated. Data on the separation VORTICES angles for large ratios of exit jet height to radius of cylinder are James D. Iversen Nov. 1974 30 p refs also presented. Experimental data show that, at high Reynolds Grant NsG-2040; ERI Proj. 1146-5) numbers, the separation angle is very sensitive to the ratio of (NASA-CR-142298; ISU-ERI-Ames-74241( Avail: NTIS exit height to cylinder radius when that ratio is about 0.33. HC $3.75 CSCL 01A Dissert. Abstr. The characteristics of the plateau region in the vortex system which trails from a lifting wing are discussed. The decay of the vortex due to viscous or turbulent shear is very slow in the N75-19139 Tennessee Univ., Knoxville. plateau so that the maximum tangential speed in the vortices STUDY OF TRANSONIC FLOW OVER VARIOUS BODIES remains nearly constant for some distance downstream of roll-up Ph.D. Thesis and then begins to decrease, becoming inversely proportional to Heinz Hermann Venghaus 1974 - 121 p the square root of the distance downstream. Mathematical models Avail: Univ. Microfilms Order No. 74-27245 are developed to analyze the structure of the plateau area. Several inviscid transonic flow problems were analyzed and Solutions are obtained for both constant and variable eddy viscosity solved, by utilizing the high speed computer. The inviscid transonic models. Author flow over various frontbody-cylinder configu.tions. including small angles of attack, was calculated by the nonlinear-linear stretching PJ7519173 *# Mac Neal -Schwendler Corp.. Los Angeles, Calif. scheme. A transonic flow theory for a conical flare was IMPROVEMENTS TO THE SADSAM COMPUTER PROGRAM developed to determine the flow over a flared part of a body FOR AEROELASTICITY ANALYSIS configuration in the lower transonic regime. The inviscid transonic Robert G. Schwendler Mar. 1975 29 p refs flow field over a long cavity was calculated by a mixed finite (Contract NAS1-12017) difference scheme. An inverse computation method was applied (NASA-CR-132617) Avail: NTIS HC $3.75 CSCL 01A to a compressible subsonic flow over a long cavity, to calculate A computer program for calculating the elastic element forces the inviscid streamline to a given experimental surface pressure and strain energy distribution for normal mode shapes is presented. distribution. The method of characteristics was applied to an The subjects discussed are: (1) revised aerodynamic force under-expanded jet exhaust flow for the determination of the representation, (2) flap aerodynamics, (3) chordwise motions and plume boundary. Dissert. Abstr. aerodynamic forces. (4) wing-tail interaction, and (5) gust analysis. An aircraft configuration used in sample gust analysis is N75-19170 Pennsylvania State Univ., University Park. included. Author THE DYNAMIC RESPONSE OF AIRCRAFT ENCOUNTERING AIRCRAFT WAKE TURBULENCE Ph.D. Thesis N75-19114# National Aerospace Lab., Tokyo (Japan). Robert Charles Nelson 1974 170 p A METHOD FOR PREDICTING UNSTEADY AERODYNAMIC Avail: Univ. Microfilms Order No. 74-28974 FORCES ON OSCILLATING WINGS WITH THICKNESS IN This investigation deals with the dynamic behavior of an TRANSONIC FLOW NEAR MACH NUMBER 1. PART 1: airplane encountering aircraft wake turbulence. A digital computer TWO-DIMENSIONAL THEORY. PART 2: RECTANGULAR simulation was developed to study the response of an aircraft WINGS flying into a trailing vortex wake. The simulation includes the Koji Isogal Jun. 1974 35 p refs complete six degree of freedom equations of motion, a description (NA L-TR-368T-Pt- 1; NAL-TR-368T-Pt-2) Avail: NTIS of the vortex velocity field, unsteady aerodynamics, and pilot HC $3.75 control input. The parameters, varied in this simulation, include An approximate method for predicting aerodynamic loadings the penetration angle, separation distance, aircraft size (for both on circular-arc airfoils oscillating in two-dimensional transonic the penetrating and generating aircraft), and pilot control input flow at Mach number 1 or very near 1 is presented. Employing (single- or multi-axes). Predicted vortex induced motions are an idea analogous to the local linearization concept, a linear presented for a variety of probe aircraft. The probe aircraft partial differential equation with variable coefficients for an selected are representative of general aviation, business, and unsteady small disturbance velocity potential is transformed into light jet transport type aircraft. The aircraft used to generate an approximate integral equation, which relates an unknown the vortex wakes are representative of the commercial transport load distribution to a normalwash condition. A method for solving

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the integral equation is discussed and its working form is given concerning accuracy and identifiability are also discussed. A together with appropriate forms of the kernel functions for general computing algorithm is developed covering all estima- numerical evaluation. Aerodynamic forces on circular-arc airfoils tion techniques described. It is applicable to linear as well as oscillating at Mach number 1 are calculated for several values nonlinear systems and is flexible enough for the solution of various of thickness to chord ratio and compared with those predicted identifiability problems. Using this algorithm the computing by the sonic theory. A considerable effect of the airfoil thickness program has been compiled in general terms to enable the user on both the magnitudes and phase angles of the aerodynamic to achieve the objectives mentioned. As examples, the results forces is found, especially in the reduced frequency range from of the identification of aircraft parameters and aerodynamic o to 0.2, where flutter usually occurs. Aerodynamic forces derivatives for four different aircraft are presented. They include predicted by the present method are applied to a flutter the analysis of flight data from the Basset variable stability aircraft calculation of a rectangular wing, and the effects of airfoil thickness and the simulated data for a nonlinear model of the F-100 on the flutter speed, which were observed in the experiment, aircraft, and the flight data from the longitudinal motion of the are well predicted by the present method. Author HP-115 slender delta-wing research aircraft. Author

N7519178 *# TRW Systems, Redondo Beach, Calif. Applied N75-19175# Cranfield Inst. of Technology (England). Coll. of Mechanics Dept. Aeronautics. TRW VORTEX-LATTICE METHOD SUBSONIC AERODY- LONGITUDINAL AERODYNAMIC DERIVATIVES OF A NAMIC ANALYSIS FOR MULTIPLE-LIFTING-SURFACES (N. SLENDER DELTA WING RESEARCH AIRCRAFT EX- SURFACE) TRW PROGRAM NUMBER HAO10B TRACTED FROM FLIGHT DATA Antulio V. Gomez 1 Sep. 1972 266 p refs V. Klein Jul. 1974 85 p refs (Contract NAS9- 12330) (Cranfield-Aero-27) Avail: NTIS HC $4.75 (NASA-CR- 128588; TRW-20029-1 1 11 0-R0-00) Avail: N TI S The Maximum Likelihood parameter-estimation algorithm was HC $8.50 CSCL 01A used to extract the longitudinal aerodynamics derivative from The program was designed to provide solutions of engineering flight data for the Handley Page HP 115 slender delta-wing accuracy for determining the aerodynamic loads on single- or research aircraft. The responses in the rate of pitch and vertical multiple-lifting-surface configurations that represent vehicles in acceleration were excited from the horizontal steady-state flights subsonic flight, e.g., wings, wing-tail, wing-canard, lifting bodies, at different air speeds by the elevon deflection. In some cases etc. The preparation is described of the input data, associated the measured time histories were converted into frequency input arrangement, and the output format for the program data, response curves, from which the unknown parameters were including specification of the various operational details of the estimated. For the low angle of attack measurements the linear program such as array sizes, tape numbers utilized, and program model of the aircraft was adequate, whereas for the runs dumps. A full description of the underlying theory used in the measured at high angle of attacks the non-linear model had to program development and a review of the program qualification be used. Some indentifiability problems were met because of tests are included. Author the limited number of measured outputs and incorrect design of the experiment. The non-dimensional aerodynamic derivatives N75-19179 5# Kanner (Leo) Associates, Redwood City, Calif. extracted were compared with those from wind-tunnel tests and DYNAMICS OF THE MOTION OF A BODY WITH ALLOW- steady-state measurements. A reasonable degree of consistency ANCE FOR THE UNSTEADY STATE OF THE FLOW ABOUT between the various sets of results was obtained. Author IT S. M. Belotserkovskiy, Yu. A. Kochetkov. and V. K. Tomshin N75-19176# National Aerospace Lab.. Tokyo (Japan). Washington NASA Feb. 1975 17 p refs Transl. into ENGLISH AN EXACT SOLUTION FOR TRANSONIC POTENTIAL FLOW from Izv. Akad. Nauk SSSR, Mekh. Tverd. Tela (USSR). May-Jun. PAST AEROFOIL SECTIONS 1974 p 35-43 Susumu Takanashi Aug. 1974 31 p refs In JAPANESE; (Contract NASw-2481 ENGLISH summary (NASA-TT-F-16133) Avail: NTIS HC $3.25 CSCL 01A (NAL-TR-383) Avail: NTIS HC $3.75 A numerical method and an approximate method based on A hodograph method is developed for obtaining exact solutions the approximation of transient aerodynamic functions by of transonic potential flow around lifting airfoils. The procedure exponential curves are proposed for the solution of the integrodif- of constructing compressible flows from incompressible flows is ferential equations to which some dynamics problems reduce. based on those of Lighthill and Nieuwland. In the present theory, The approximate method leads to systems of ordinary differential however, the complex hodograph potential representing the equations with constant coefficients. The methods are applied starting incompressible flow is divided into two parts: one is a to solving three problems in flight dynamics. Solutions of exact simple function which has the desired singularity of dipole and equations are analyzed. Author vortex at the point corresponding to infinity in the physical plane, and the other is chosen to be a regular function so that the N7519180*# total function represents a flow around a pseudo-elliptical body. National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. This splitting of the solution has many advantages from the INTEGRATION OF AFT-FUSELAGE-MOUNTED FLOW mathematical and computational points of view. The geometrical THROUGH ENGINE NACELLES ON AN ADVANCED and aerodynamical characteristics of the resulting airfoils in the TRANSPORT CONFIGURATION AT MACH NUMBERS compressible flow are controlled by a number of parameters. A FROM 0.6 TO 1.0 family of practically interesting transonic shock-free airfoils has Bernard J. Blaha Washington Mar. 1975 72 been computed by changing the values of these parameters. An p refs (NASA-TM-X-3178) Avail: NTIS HG $4.25 CSCL 01 airfoil of this family was tested in the wind tunnel to compare An approximately 1/30th-scale model of a CTOL aircraft with the theoretical prediction. Author designed for efficient cruise between Mach 0.9 and 0.98 was tested in the Lewis Research Center's 8- by 6-Foot Supersonic N75-19177# Cranfield Inst. of Technology (England). Coll. of Wind Tunnel. Aft-fuselage axial force and pressure were measured Aeronautics. for a series of locally area-ruled engine installations. Two PARAMETER IDENTIFICATION APPLIED TO AIRCRAFT flow-through nacelles with different exit diameters which simulated V. Klein [1974] 153 p refs inlet mass flow ratios of 0.46 and 0.6 (based on maximum (Cranfield-Aero-26) Avail: NTIS HG $6.25 nacelle cross-sectional) area were investigated. Both an NACA-1 All three steps in the identification, namely characterization, cowl and a blunter supercritical cowl were tested with these parameter estimation and verification are considered and applied nacelles. Variations in the amount of local area ruling were to the determination of aircraft parameters from flight data. The investigated and an aft fuselage without nacelles was tested for estimation procedure includes the equation error method and reference. Results observed with flow-through nacelles indicate the output error method with the weighted least squares, maximum that efficient cruise may be obtained on this type of aircraft likelihood and Bayesian estimation technique. The problems with aft-fuselage-mounted engine nacelles. Author

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N75-19186

N75-19181 National Aeronautics and Space Administration. from fluidic signals. Recommendations are made to optimize the Ames Research Center, Moffett Field, Calif. design of the fluidic amplifier and to characterize its dynamic EXPERIMENTAL AERODYNAMIC CHARACTERISTICS FOR response in support of further analytical studies. Author A CYLINDRICAL BODY OF REVOLUTION WITH SIDE STRAKES AND VARIOUS NOSES AT ANGLES OF ATTACK N76-19184# Boeing Commercial Airplane Co.. Seattle, Wash. FROM 0 DEGREES TO 58 DEGREES AND MACH NUMBERS LOW SPEED AND ANGLE OF ATTACK EFFECTS ON SONIC FROM 0.6 TO 2.0 AND NEAR-SONIC INLETS Leland H. Jorgensen and Edgar A. Nelson Washington Mar. T. E. Hickcox, A. L Lawrence, J. Syberg. and D. R. Wiley Mar. 1975 88 refs p 1975 207 p refs (NASA-TM-X-3130; A-5759) Avail: NTIS HC $4.75 CSCL (Contract NAS3- 18035) O1A (NASA-CR-134778; D6-42392) Avail: NTIS HC $7.25 CSCL For a body of revolution with afterbody side strakes. an 01A experimental investigation was conducted in the Ames 6- by Tests of the Quiet. Clean Short-Haul Experimental Engine 6-Foot Wind Tunnel to determine the effects on the aerodynam- (QCSEE) were conducted to determine the effects of forward ic characteristics of forebody geometry, nose strakes, body side velocity and angle of attack on sonic and near-sonic inlet strakes, Reynolds number, Mach number, and angle of attack. aerodynamic performance penalties and acoustic suppression Aerodynamic force and moment characteristics were measured characteristics. The tests demonstrate that translating centerbody for the straked cylindrical afterbody (cylinder fineness ratio of 7) and radial vane sonic inlets, and QCSEE high throat Mach with tangent ogive noses of fineness ratio 2.5 to 5.0. In addition, number inlets, can be designed to operate effectively at forward the straked cylinder afterbody was tested with an ogive nose speed and moderate angle of attack with good performance having a rounded tip and an ogive nose with two different nose and noise suppression capability. The test equipment and strake arrangements. The data demonstrate that the aerodynamic procedures used in conducting the evaluation are described. characteristics for a body of revolution with side strakes can be Results of the tests are presented in tabular form. Author significantly affected by changes in nose fineness ratio, nose bluntness. Reynolds number. Mach number, and, of course, angle of attack. Removing the strakes from the cylindrical aftersection greatly decreased the lift, but this removal hardly changed the N75-19185# Cambridge Univ. (England). Dept. of Engineer- ing. maximum magnitudes of the undesirable side forces that developed at angles of attack greater than about 25 deg for LIFTING SURFACE THEORY FOR A ROTATING SUBSONIC subsonic Mach numbers. Author OR TRANSONIC BLADE ROW M. Namba London ARC 1974 77 p refs Supersedes ARC-34126; ARC-34127 Sponsored in part by the Roy. Soc. N7519182*# Linguistic Systems, Inc.. Cambridge, Mass. of London MECHANICS OF OPTIMUM THREE-DIMENSIONAL (ARC-fl /M-3740; ARC-34126; ARC-34127) Avail: NTIS MOTION OF AIRCRAFT IN THE ATMOSPHERE HC $4.75; HMSO £2.95; PHI $11.55 L. M. Shkadov, A. S. Bukhanova, V. F. Illarionov, and V. P. A lifting-surface method is presented for calculating the Plokhikh Washington NASA Mar. 1975 288 p refs Transl. disturbance velocity and pressure fields as well as the aerodynamic into ENGLISH of the book "Mekhanika optimalnogo pro- lift distributions for a rotating thin blade row in a cylindrical stranstvennogo dvizheniya Ietatelnykh apparatov v atmosfere" duct at subsonic or transonic relative Mach numbers on the Moscow, Mashinostroyeniye Press, 1972 240 p basis of an inviscid, isentropic, small disturbance three-dimensional (Contract NASw-2482) flow theory. The most significant features of the method stem (NASA-TT-F-777) Avail: NTIS HC $8.75 CSCL 01 from a new mathematical treatment of the Fourier-Bessel double The theoretical bases are presented for the method of investi- series, which consists of re-expanding radial eigenfunctions. i.e.. gating an optimum three-dimensional maneuver of a hypersonic Bessel functions, of an arbitrary circumferential order in terms aircraft with the use of aerodynamic forces in motion in the atmos- of a set of radial eigenfunctions of the zero-th order in the phere of a planet. The application of the method is illustrated by the same family. This permits the separation of the singular parts solution of a number of specific problems associated with the and the treatment of essentially a finite number of unknown maneuver: maximization of lateral range (slant range) in the parameters in solving the off-design problem. Some numerical launching of an orbiting craft (missiles) (in the absence and in examples of solutions of the off-design problem of a subsonic the presence of limitations with respect to the heating temperature lifting blade row are presented, and the validity of the two- of the structure); rotation of the plane of the orbit by means of dimensional blade element concept, as well as the importance aerodynamic forces, and landing at a given point on the earth's of various three-dimensional factors, are discussed. The analysis surface. Author is also given for a transonic lifting blade row in which the relative Mach numbers at the blade tip exceed unity. The new mathemati- N75-19183 *# . Franklin Inst. Research Labs., Philadelphia, Pa. cal treatment has turned Out to be powerful in discriminating WIND TUNNEL TESTS OF A SYMMETRICAL AIRFOIL WITH the supersonic singular parts from the subsonic ones. Numerical SCOOP FED SLOTS results are presented, which illustrate the comparison between Charles A. Belsterling Nov. 1974 55 p ref the present lifting-surface theory and the strip theory and (Contract NAS1- 12451) demonstrate the special features of the flows in transonic and (NASA-CR-132568; FIRL-C-3741-2) Avail: NTIS HC $4.25 supersonic axial compressors. It is found that the three- CSCL O1A dimensional effects, i.e., the departure from the strip theory is The design and wind tunnel test of a model vertical tail fin greatest near the sonic radius. Author (ESRO) is described in this report. The model is designed to provide the aerodynamic forces necessary for lateral stabilization without N75-19186fl East Anglia Univ., Norwich (England). School moving parts or a separate source of power. It employs scoop-fed of Mathematics and Physics. slots on both surfaces of the symmetrical airfoil. They are to be FLOW PAST CONICALLY-CAMBERED SLENDER DELTA controlled differentially by means of a fluidic amplifier to implement WINGS WITH LEADING-EDGE SEPARATION an automatic fulltime lateral stabilization system. The results of J. E. Barsby London ARC 1974 50 p refs Supersedes tests show that the control of forces is stable and quite linear RAE-TR-72179; ARC-34435 Monitored by RAE. Famnborough, in various modes of operation. Significant forces were produced Engl. that can be increased as necessary by increasing slot size and (ARC-R/M-3748; RAE-TR-72179; ARC-34435) Avail: NTIS scoop size. Slots can be located ahead of the conventional rudder HC $3.75; HMSO £1.95; PHI $7.65 and the scoop can be at the base of the vertical tail fin to The vortex sheet model of leading edge separation previously avoid the need for major changes in conventional aircraft applied to uncambered delta wings was applied to thin, conically design. The first phase of the work demonstrated the feasibility cambered delta wings whose cross sections are circular arcs. of no-moving-parts aircraft control. The second phase established The simplifications introduced by the use of slender body theory that a practical fluidic amplifier can be built to control slot flows and an asymptotic treatment for the core of the vortex were

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retained. Solutions were found showing a gradual growth of the fluctuates appreciably but is for the most part between 30% leading edge vortex above the upper surface at incidences above and 80% of the turbulence boundary layer thickness for all Mach that for attached flow for wings between the flat plate and the numbers up to 2.2. The root mean square boundary layer pressure semi-circular cone. Variations of the shape and strength of the reduced with Mach number from about 0.01 times the free vortex sheet, the pressure distribution on the wing, and the lift stream dynamic pressure at M = 1 to about 0.003 at and drag of the wing with camber and incidence are displayed. M = 2.2. the front station tending to be slightly the higher at An attempt is made to relate the lifting efficiency of the wing each Mach number. Author (ESRO) to both the distribution of pressure over its surface and to the vorticity shed from its edges. The results support the choice of an attachment lift coefficient approximately half that at which N75-19191# Imperial Coil, of Science and Technology. London the best performance is desired. Author (ESRO) (England). Dept. of Aeronautics. CALCULATION OF TWO-DIMENSIONAL AND AXISYM- N75-19187# Royal Aircraft Establishment. Farnborough METRIC BLUFF BODY POTENTIAL FLOW (England). Structures Dept. P. W. Bearman and J. E. Fackrell Oct. 1974 44 p refs CALCULATIONS OF GENERALISED AIRFORCES ON TWO Sponsored partly by a Donald Campbell Res. Fellowship PARALLEL LIFTING SURFACES OSCILLATING HARMONIC- (IC-Aero-74-07) Avail: NTIS HG $3.75 ALLY IN SUBSONIC FLOW A numerical method for calculating the incompressible D. E. Davies London Aeron. Res. Council 1974 86 p refs potential flow external to a bluff body and its wake is presented. Supersedes RAE-TR-72 180; ARC-34466 The effect of the wake is modeled by placing sources on the (AR C-R /M-3749; RAE-TR-72 180; ARC-34466) Avail: NTIS rear of the wetted surface of the body. The body shapes that HC $4.75; HSMO £3.35; PHI $12.95 can be treated are not limited by the restrictions imposed by Two flat parallel surfaces, oscillating harmonically about a the use of conformal transformation. The wetted surface of the mean configuration were immersed in a uniform subsonic main body is represented by a distribution of discrete vortices. Good stream in a direction parallel to the surfaces. The linearized agreement was found between the pressure distributions predicted equations of potential flow were assumed to be valid, so that by the numerical method and the analytic expressions of Parkinson the upwash on the surfaces could be related to the loading on and Jandali for a two-dimensional circular cylinder, flat plate the surfaces by means of a pair of integral equations. This pair and ellipse. The method was extended to axisymmetric bluff of integral equations was solved, by collocation, for approximations bodies and the results show good agreement with measured to the loadings in terms of given upwashes and these approxima- pressure distributions on a circular disc and a sphere. tions were used to ovaluate generalized airforces. The results Author (ESRO) were compared with some results obtained by other numerical procedures and with some experimental results. Author (ESRO) N75-19192// Imperial Coll. of Science and .Technology, London (England). Dept. of Aeronautics. N75-19188// Royal Aircraft Establishment. Farnborough A WAKE SOURCE MODEL FOR AN INCLINED FLAT PLATE (England). Aerodynamic Dept. IN A UNIFORM STREAM NOTES ON THE APPROXIMATE SOLUTION OF LIFTING- M. E. Davies Sep. 1974 14 p refs Sponsored by Sci. Res. SURFACE THEORY USED IN THE RAE STANDARD Council METHOD (IC-Aero-74-08) Avail: NTIS HG $3.25 J. Weber London ARC 1974 71 p refs Supersedes The wake-source potential flow model for bluff bodies, RAE-TR-73044; ARC-34766 suggested by Parkinson and Jandali, was extended to the (ARC-R/M-3752; RAE-TR-73044; ARC-34766) Avail: NTIS nonsymmetric case of an inclined flat plate in a uniform stream. HG $4.25; HMSO £2.80; PHI $11.00 For angles of inclination up to 60 or 70 degrees, the theory The downwash induced by planar vorticity distributions was predicts th&surface pressure distribution to a reasonable degree computed by exact linear theory andby the RAE Standard Method of accuracy (normal flat plate alpha 0). Author (ESRO) to examine the accuracy of the approximate method. The results on wings of infinite span with load distributions which are uniform N75-19193# Technion - Israel Inst. of Tech.. Haifa. Dept. of across the span were used to derive a modification of the Aeronautical Engineering. downwash equation of the approximate method. It is shown ON THE CALCULATION OF NON-LINEAR AERODYNAMIC that this modification can explain some of the difference between CHARACTERISTICS AND THE NEAR VORTEX WAKE the exact and the approximate results for the spanwise lift Josef Rom, Carlos Zorea. and Rachel Gordon Aug. 1974 18 p coefficient distribution of a plane wing of infinite span at an refs Presented at the 9th Proc. of Congr. Intern. Council of angle of incidence. The downwash distributions on finite wings Aeron. Sd., Haifa, Israel, 25-30 Aug. 1974 of constant chord, unswept and sweptback by 45 degrees, with (Grant AF-AFOSR-2145-71; AF Proj. 9781) given load distributions, computed by the exact and the (AD-A002 161; AFOSR-74-1 766TR; ICAS-Paper-74-27( Avail: approximate method are compared. The lift distribution for wings NTIS CSCL01/1 of given shape derived by the approximate method is also This investigation presents methods for the calculation of compared with more accurate results. Author (ESRO) the distribution of vortices on the wing planform and on the trailing vortex wake by iterative procedures based on the application of the vortex lattice method concepts. In the case N75-19189# Royal Aircraft Establishment. Farnborough when the trailing vortices are taken to leave the wing at the (England). Structures Dept. trailing edge only the calculation results in determining the linear BOUNDARY-LAYER PRESSURE FLUCTUATIONS Al HIGH aerodynamic characteristics and the shape of a rolled up wake. REYNOLDS NUMBERS ON A SECOND FREE-FLIGHT TEST The present investigation considers the cases when the vortices VEHICLE from each cell are allowed to leave the wing planform at a D. R. Roberts London Aeron. Res. Council Feb. 1974 103 p fixed angle. and the case when the vortex Shedding can be refs Supersedes RAE-TR-74029; ARC-35404 limited to the planform edges only. In these cases non-linear (ARC-CP-1 302; RAE-TR-74029; ARC-35404) Avail: N TI S aerodynamic characteristics are evaluated. The corresponding HC $5.25; HMSO £1.70; PHI $6.75 trailing vortex wakes were first calculated by using discrete ideal Measurements were made of the boundary layer pressure vortices. It is now proposed to use a finite core vortex model fluctuations at two positions on the body of a free flight thereby eliminating some of the numerical problems associated aerodynamic test vehicle powered by a solid fuel rocket motor. with the use of the ideal vortices. GRA The vehicle reached a maximum Mach number of 2.2 with a maximum Reynolds number of about 118 millions at the front N75-19194# Army Aviation Systems Test Activity, Edwards measuring station and 207 millions at the rear. Pressure spectra AFB, Calif. were deduced, and were found to compare reasonably with a NATURAL ICING TESTS. UH . 1H HELICOPTER Final theoretical spectrum. The scale of the boundary layer turbulence Report

266 N75-19203

Warren E. Griffith, II, Marvin L Hanks. Carl F. Mittag. and James conditions of fog is essentially independent of wavelength, no laser wavelength that also falls within an absorption-free S. Reid Jun. 1974 36 p refs (AD-A002077; USAASTA-74-31) Avail: NTIS CSCL 01/2 'window', appears to be significantly better than any other A limited evaluation of the capability of a modified UH-1 H wavelength as far as penetration in fog is concerned. The results helicopter to fly in a natural icing environment was conducted of our evaluation of lasers as visual cues or optical guidance at Fort Lewis. Washington. from 5 February through 23 February systems are based primarily on the performance characteristics 1974. Testing was performed by the United States Army Aviation of optical lasers under operationally important low-visibility Systems Test Activity and consisted of 1.7 hours in icing conditions. Author conditions. During this test, four enhancing features, one deficiency, and one shortcoming were noted. There were four N75-19199# Princeton Univ., N.J. Dept. of Aerospace and enhancing features associated with special equipment. The Mechanical Science. deficiency is the inability to maintain autorotational rotor speed GENERAL AVIATION AIRCRAFT SAFETY within operational limits with main rotor ice accumulation. The Oct. 1974 150 p Presented at Princeton Univ. Conf. Meeting striking of the tail rotor by the oscillating iced FM antenna is a no. 119. Princeton, N. J., 24-25 Oct. 1973 Sponsored by FAA shortcoming. Based on these tests, artificial icing characteristics (AD-AO03124; FAA-RD-74-154) Avail: NTIS HC $6.25 observed in previous UH-1H icing tests are representative of The proceedings of a conference on General Aviation Aircraft natural icing characteristics. The UH-1H helicopter does not Safety are presented. Emphasis was placed on current research possess the capability to operate safely in an icing environment. and development efforts in the areas of airworthiness and G RA crashworthiness. The cost and regulatory implications of increased safety were examined. The general aviation accident record was 19195# Summa Corp.. Culver City, Calif. Hughes Helicopter reviewed to show accident patterns and pilot error influences. N75. The prospects for improved safety records were discussed to Div. DYNAMIC LOADS AND STRUCTURAL CRITERIA STUDY show the contributions which can be made by the manufacturers. Final Report, Dec. 1973 - May 1974 For individual titles, see N75-19200 through N75-19207. K. A. Spreuer. S. J. Snackenburg. and G. D. Roeck Sep. 1974 131 p refs N75-19200 National Transportation Safety Board, Washington, (Contract DAAJ02-74-C-001 8; DA Proj. 1 Fl -62208-AH-90) D. C. Bureau of Aviation Safety. (AD-A001739; HI-4-74-124; USAAMRD L-TR-74-74) Avail: ANALYSIS OF GENERAL AVIATION ACCIDENT RECORDS NTIS CSCLO1/3 Charles 0. Miller In Princeton Univ. Gen. Aviation Aircraft This report presents the results of a 6-month technical effort Safety Oct. 1974 p 5-11 to develop a realistic mission profile for each of six helicopter types in Current and future Army inventories: observation, The system for investigating aircraft accidents involving utility, utility /tactical assault, attack, crane, and transport. The general aviation aircraft is discussed. The functions of the National profiles included in this report are the product of operational Transportation Safety Board are defined. The procedures for data gathered over two decades, starting with early NACA efforts processing data pertaining to general aviation aircraft are examined and including extensive studies conducted by the Army Air Mobility to show the manner in which the information is used to improve A and D Laboratory and private enterprise. GRA flight safety. Data are tabulated to show the rank and percentage of general aviation aircraft during 1970, 1971, and 1973 based on accidents caused by: (1) personnel, (2) weather, (3) power N75-19197 Stanford Univ., Calif. ANALYSIS OF IN-FLIGHT DISINTEGRATION ACCIDENTS plant. (4) terrain, and (5) airframe. Author Ph.D. Thesis Frederick Harold Matteson 1974 316 p Avail: Univ. Microfilms Order No. 74-27058 Patterns of wreckage resulting from the disintegration of N75-19201 Federal Aviation Administration, Washington, D.C. aircraft in flight have been studied to aid in accident investigations. GENERAL AVIATION ACCIDENT PATTERNS Emphasis has been given to general aviation accidents where Donald E. Kemp In Princeton Univ. Geri. Aviation Aircraft economic losses are highest and showing little improvement. Safety Oct. 1974 p 12-16 and where flight recorders are seldom used. Idealized wreckage The importance of aircraft design and standardization to the patterns were generated by solution of ballistic trajectory equations education and prevention of aircraft accidents is discussed. for bodies with differing terminal velocities. Effects of changes Several examples of aircraft accidents resulting from lack of in initial flight and wind variables on simultaneous distinteg rations in atmospheres with uniform winds were shown by means of standardization of aircraft controls are presented. The importance easily comprehended diagrams. The technique was then extended of education and training for flying personnel as an accident to progressive breakups and to the effects of altitudinal variations prevention measure are stressed. Author in the wind speed and direction, using wind profiles based on meteorological records. Dissert. Abstr. N75-19202 Ohio State Univ., Columbus. Dept. of Aviation. THE ACCIDENT RECORD IN TERMS OF THE PILOT N75-19198# Stanford Research Inst., Menlo Park. Calif. Jack J. Eggspuehler In Princeton Univ. Gen. Aviation Aircraft FEASIBILITY OF LASER SYSTEMS FOR AIRCRAFT Safety Oct. 1974 p 17-36 LANDING OPERATIONS UNDER LOW VISIBILITY CONDI- TIONS Final Report General aviation aircraft accidents are reviewed from the William Viezee, John Oblanas. and Myron Glaser 11 Oct. 1974 standpoint of pilot performance and pilot error. The importance of adequate pilot education and training to prevent aircraft 116 p refs (Contract DOT-FA73WA-3214; SRI Proj. 2831) accidents is stressed. Several examples of aircraft accidents which (AD-A005637; FAA-RD-74-190) Avail: NTIS HG $5.25 resulted from incorrect pilot decisions and actions are pre- The effects of currently recommended eye-safety standards sented. Author and of atmospheric scattering on the potential application of lasers to the low-visibility aircraft approach and landing operational N75-19203 Federal Aviation Administration, Washington, D.C. environment are assessed. It is concluded that these two criteria CRASH SURVIVABIUTY are serious handicaps in any proposed development of a laser P. Frank Castellon In Princeton Univ. Gen. Aviation Aircraft landing guidance system. The two criteria are interrelated: the Safety Oct. 1974 p 37-45 application of high power, narrow beam lasers to overcome the large attenuation in dense fog increases the eye-safety hazard, A research project to improve the crash survivability of general whereas a lowering of laser power to guarantee eye-safety aviation aircraft is discussed. Structural design criteria for aircraft drastically reduces the distance over which the laser beam can components which will aid in crash survival are described. Various be used effectively. Since the scattering coefficient during restraint mechanisms such as seat belts, shoulder harnesses, air

267 N75-19204 bags, and combinations of these devices are examined. Test each year involve carburetor finduction system icing as a probable equipment for conducting full scale drop and impact tests of cause/factor. Under conditions conducive to carburetor /induction aircraft to evaluate restraint equipment is proposed. Author icing, between 50 and 70 percent of engine malfunction /failure accidents (exclusive of those due to fuel exhaustion) are due to carburetor/induction system icing. Since the evidence of such N75-19204 Princeton Univ., N.J. Dept. of Aerospace and icing may not remain long after an accident, it is probable that Mechanical Sciences. the frequency of occurrence of such accidents is underestimated; GENERAL AVIATION HANDLING QUALITIES RESEARCH therefore, some extrapolation of the data was conducted. The David R. Ellis In its Gen. Aviation Aircraft Safety Oct. 1974 problem of carburetor /induction system icing is particularly acute p 46-58 for pilots with less than 1000 hours of total flying time. The Research projects to reduce the accident rate for general severity of such accidents is about the same as any accident aviation aircraft by improving aircraft control and handling qualities resulting from a forced landing or precautionary landing. About are discussed. Various items of aircraft equipment which are 144 persons, on the average, are exposed to death and injury designed to provide solutions to control problems are described. each year in accidents involving carburetor /induction icing as a Flight tests of specific aerodynamic configurations to determine probable cause/factor. Author the effectiveness of modifications to control surfaces are reported. Efforts to improve the landing safety of aircraft under adverse N75-19209# Royal Aircraft Establishment. Farnborough conditions are reported. Author (England). THE STRADA FLIGHT PATH TRACKING SYSTEM N75.19205* National Aeronautics and Space Administration. J. P. Marvillet and J. L Jouzeau Jan. 1975 29 p refs Transl. Ames Research Center, Moffett Field, Calif. into ENGLISH from Aeronaut. Astronaut (Paris), v. 35, no. 3, DESIGN CONSIDERATIONS FOR STALL/SPIN AVOID- 1972 p 19-29 ANCE )RAE-Lib-Trans-1813; BR46822) Avail: NTIS HC $3.75 Seth B. Anderson In Princeton Univ. Gen. Aviation Aircraft A summary of the required performance and a general Safety Oct. 1974 p 59-76 description of the STRADA system is given along with a detailed study of the LIDAR components. The problems related to system The paper discusses three aspects of the stall/spin problem: reliability and to propagation in the atmospheric medium are (1) aerodynamic effects, (2) stall warning, and (3) stall limiting. solved. The performance and the fields of application of the The results show that the stall/spin problem could be alleviated optimized test facility as regards cost, efficiency, and ease of by good handling qualities up to and beyond the stall, careful operation are considered. Author selection of aerodynamic parameters which promote spin- resistance, adequate stall warning methods and stall margins, and an acceptable form of limiting elevator effectiveness near the maximum coefficient of lift. Author N75-19210// Air Force Special Weapons Center, Kirtland AFB, N.Mex. N75-19206 Federal Aviation Administration, Washington, D.C. TIEDOWN TESTS FOR AIR TRANSPORT OF THE XM542 ECONOMICS: GENERAL AVIATION COST FACTORS SPRINT CONTAINER Final Report. Apr. - May 1974 Gene S. Mercer In Princeton Univ. Gen. Aviation Aircraft Safety Grant W. Gray Oct. 1974 25 p ref Oct. 1974 p 94-100 (AF Proj. 921C) A study to determine the economic factors which influence )AD-AO01844; AFSWC-TR-74-27) Avail: NTIS CSCL 15/5 the growth of general aviation was conducted. Emphasis was Aircraft tiedown configurations for transport of the XM542 placed on the costs arising from changes in theFederal regulatory Sprint container in the C-5A. C-130, and C-141 aircraft were environment and higher Federal aviation user chatges. The study designed and tested by the Air Force Special Weapons Center developed a data base of ownership and operating costs in each (AFSWC). The developed tiedown configurations, test procedures, segment of general aviation. Regression equations were developed test data, and test observations are presented. GRA which related the demand for aircraft and flight hours to the appropriate cost categories. Charts are included to show the various ,factors in aircraft operation which have an economic N75-19211# Cincinnati Univ.. Ohio. impact. Author USERS MANUAL FOR UCIN VEHICLE OCCUPANT CRASH STUDY MODEL VERSION Technical Report, 1 Jun. - N75-19207 General Aviation Manufacturers Association, 1 Dec. 1974 Washington, D.C. Chris E. Passerello, Ronald L Huston, and Mark W. Harlow MANUFACTURER'S OVERVIEW 2 Dec. 1974 34 p refs Edward W. Stimpson In Princston Univ. Gen. Aviation Aircraft (Contract N00014-72-A-0027-0002; NR Proj. 122-303) (AD-AO01801; UC-EA-120174-3) Avail: NTIS CSCL 01/2 Safety Oct. 1974 p 117-120 The manual briefly describes the model and the range of applicability of the program. it provides detailed instructions The contribution of aircraft manufacturers to improved safety regarding the card coding of input data. It discusses the of general aviation aircraft is discussed. An analysis of the interpretation of the out-put results. A sample listing of input overall accident rate for general aviation aircraft is presented. GRA Federal and state programs to provide better navigation aids data is also provided. ' and terminal facilities are reported. Research projects conducted by aircraft manufacturers to provide increased aircraft reliability are reported. Author N75-19212# EDMAC Associates, Inc., East Rochester, N.Y. TACAN/DME DIGITAL DATA BROADCAST DESIGN PLAN. N7519208*# Manned Systems Sciences, Inc., Northridge, Calif. VOLUME 5: FLIGHT TEST PROGRAM Final Report A STUDY OF CARBURETOR /INDUCTION SYSTEM ICING Sep. 1974 33 p IN GENERAL AVIATION ACCIDENTS Final Report (Contract DOT-FA72WA-3080) Richard W. Obermayer and William T. Roe Mar. 1975 47 p (AD-AO01405/0: FAA-RD-74-161-5) Avail: NTIS HC $3.75 refs The digital data broadcasting design plan implements the (Contract NAS4-2191) system engineering process for the purpose of defining ground/ (NASA-CR-143835) Avail: NTIS HC $3.75 CSCL 018 airborne equipment configuration and flight test program. This An assessment of the frequency and severity of carburetor/ plan documents an approach to verify the operational significance induction icing in general-aviation accidents was performed. The and technical feasibility of utilizing existing DME and TACAN to available literature and accident data from the National Transporta- provide the function of broadcasting data to aircraft for use in tion Safety Board were collected. A computer analysis of the support of area navigation in addition to its normal function. accident data was performed. Between 65 and 90 accidents Author

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N75-19220# Naval Air Development Center, Warminster, Pa. N75-19213# EDMAC Associates. Inc.. East Rochester. N.Y. TACAN/DME DIGITAL DATA BROADCAST DESIGN PLAN. FLIGHT TEST EVALUATION OF SECANT VECAS COLLISION VOLUME 1: OPERATIONAL ANALYSIS Final Report AVOIDANCE SYSTEM Final Report Michael Raditz, Oscar Shames, James Hinds, and Patrick Finnegan Sep. 1974 79 p (Contract DOT-FA72WA-3080) Nov. 1974 262 p refs (AD-A001403/5; FAA-RD-74-161-1) Avail: NTIS HC $4.75 )AD-AO02281: NADC-74207-60) Avail: NTIS CSCL 17/7 SECANT (Separation and Control of Aircraft using nonsyn- chronous techniques) is a candidate for a national standard collision avoidance system. The VEGAS (Vertical Escape Collision N75-19214# Mitre Corp.. McLean. Va. MULTI-SITE INTERMITTENT POSITIVE CONTROL ALGO- Avoidance System) version was evaluated for ability to communi- RITHMS FOR THE DISCRETE ADDRESS BEACON SYS- cate accurately and with sufficient distance to provide timely and correct advisories and maneuver commands in simulated TEM GRA A. L. McFarland 30 Sep. 1974 267 p refs high traffic density. (Contract DOT-FA70WA-2448) (AD-A001 112/2: MTR-6742: FAA-EM-74-4) Avail: NTIS N75-19221 Stanford Univ., Calif. NC $8.50 CSCL 17/7 AERODYNAMIC DESIGN OF A ROTOR BLADE FOR Complete detailed computer algorithms for implementing MINIMUM NOISE RADIATION Ph.D. Thesis Intermittent Positive Control within a multi-site Discrete Address Yung Hoon Yu 1974 87 p Beacon System network are presented. Author Avail: Univ. Microfilms Order No. 74-27141 An analysis of the aerodynamic design of a hovering rotor blade for obtaining minimum aerodynamic rotor noise has been N75-19216# Lincoln Lab.. Mass. Inst. of Tech.. Lexington. carried Out. Attention is given only to rotational noise due to PROVISIONAL MESSAGE FORMATS FOR THE DABS/NAS pressure fluctuations on blade surfaces. A functional relation INTERFACE (REVISION 1) between the pressure distribution along the blade span and the D. Reiner and H. F. Vandevenne 10 Oct. 1974 46 p refs radiated noise is developed. From this relation, along with Supersedes FAA-RD-74-63 Revised constraint equations concerning given levels of aerodynamic (Contracts DOT-FA72WAI-261: F19628-73-C-0002: FAA Proj. performance such as given total lift and drag. one may deduce, 034-241-012) by utilizing the variational method, an optimum shape of the lift (FAA-RD-74-63-A: ATC-33-Rev- 1: FAA-RD-74-63) Avail: distribution. Results are presented to show that the noise field NTIS HG $3.75 is considerably affected by the shape of the lift distribution Formats for message are defined which are to be transmitted along the blade and that noise reduction of about 5 db may be between DABS and NAS facilities (en route or terminal). These obtained by designing the rotor blade to yield minimum noise. messages include one way surveillance reports to NAS and two Dissert. Abstr. way communications messages. The latter support data link functions between NAS and DABS equipped aircraft, as well as N75.19222*# Bolt. Beranek. and Newman. Inc., Cambridge, aiding in the monitoring and control of DABS sensors. Author Mass. ACOUSTIC TRANSMISSION THROUGH A FUSELAGE SIDEWALL J. F. Wilby and T. D. Scharton [19741 79 p refs (Contract NAS1-1 1839) N75-19217# Royal Aircraft Establishment. Farnborough (NASA-CR-132602: BBN-2742) Avail: NTIS HG $4.75 CSCL (England). 2OA HELICOPTER ROTOR-PRODUCED MODULATION AND A study was conducted to define an idealized fuselage sidewall AERIAL FIELD DISTRIBUTION IN THE BAND 30 TO structure and to construct a simplified analytical model for 76 MHz determining acoustikal transmission from exterior to interior of W. W. Langrish and D. P. L. May Jul. 1974 200 p the fuselage. The structural model chosen for the study consists )RAE-TR-74032: BR42417( Avail: NTIS HG $7.00 of a double wall system connected by line supports. The double A comprehensive investigation into the cause and effect of wall has curvature in one direction but is assumed to be infinite rotor produced modulation was made in order to assess its in extent in the other direction. Diffuse acoustic plane waves consequences in the performance of frequency modulated systems are used as a representation of the excitation field. The of communication. The investigation included detailed measure- transmission of acoustical energy through the sidewall is ments of the polar field patterns of two airborne antennas of a considered in terms of resonant and non-resonant response. The similar type, one mounted above and the other below the helicopter analytical model is used to estimate the noise levels expected fuselage. The investigation was carried out in connection with a in an aircraft with a high lift pruIsion system. Author particular communications project, but the results described are applicable to a wide range of airborne systems of future design N75.19223*# Kanner (Leo) Associates, Redwood City, Calif. since the general case can be predicted from the information. PROBLEMS OF DESIGNING PASSENGER AIRCRAFT Author (ESRO) V. M. Sheynin and V. I. Kozlovskiy Washington NASA Mar. 1975 306 p refs Transl. into ENGLISH of the book "Problemy proyektirovaniya passazhirskikh samoletov" Moscow. Mashino- N75-19219# Michigan Univ., Ann Arbor. Radiation Lab. stroyeniye Press, 1972 308 p DUAL BAND AIRBORNE ANTENNA STUDY Final Report, (Contract NASw-2481) 30 Jun. 1973 - 28 Feb. 1974 (NASA-Tr-F-808) Avail: NTIS HG $9.25 CSCL 01 Joseph E. Ferris Oct. 1974 110 p Problems of passenger aircraft design, tracing tendencies (Contract DAAB0773-C-0337( from the past through the present, and presenting forecasts for (AD-AO02043: UMICH-012126-1-F: ECOM-73-0337-F) Avail: the future are examined. Problems are approached primarily from NTIS CSCL 09/5 the standpoint of increasing economic effectiveness, with a goal The design and fabrication of two antenna systems is of improving passenger-cargo mixes, operating expenses and described and experimental results are presented. Each includes thresholds of profitability. The work goes into problems of two antennas, one of which operates in the C band and the different configurations with respect to engine placement, other operates at Ku band. Both antennas in the first system advantages of different types of engines, empennage configuration. are vertically polarized while those in the second system are layout of passenger and cargo space and thrust- and lift-to-weight- horizontally polarized. The antenna systems are designed for ratios. The most attention is paid to standard jet passenger airborne use and they are interchangeable with respect to the airplanes and air-buses, but Short Takeoff and Landing (STOL( physical mounting arrangements. Extensive data is given on and Vertical Takeoff and Landing (VTOL) airplanes are also pattern characteristics, on interband isolation, on gain and on discussed with respect to their use in relatively undeveloped the input VSWR. GRA areas. Author

269 N75-19224

N75-19224 5# Boeing Commercial Airplane Co.. Seattle, Wash. level-crossing counting procedures. The frequency distributions FUEL CONSERVATION POSSIBILITIES FOR TERMINAL obtained are then used to find fatigue life ratios using the AREA COMPATIBLE AIRCRAFT Final Report Miner-Palmgren hypothesis of cumulative damage. Results show Mar. 1975 234 p refs that those methods which consider every level crossed or every (Contract NAS1-12018) peak encountered give shorter life estimates than those which (NASA-CR-132608; D6-22421) Avail: NTIS HC $7.50 CSCL disregard all minor intermediate load fluctuations. Those which 01C depend upon threshold conditions occupy an intermediate position. Design features and operational procedures are identified, Correlation and spectral analyses are also conducted for each which would reduce fuel consumption of future transport aircraft. flight. Author (ESRO) The fuel-saving potential can be realized during the last decade of this century only if the necessary research and technology N75-19228# General Dynamics/Fort Worth, Tex. Convair programs are implemented in the areas of composite primary Aerospace Div. structure, airfoil/wing design. and stability augmentation systems. ENVIRONMENTAL AND OPERATING REQUIREMENTS FOR The necessary individual R and T programs are defined. The FIRE EXTINGUISHING SYSTEMS ON ADVANCED AIR- sensitivity to fuel usage of several design parameters (wing CRAFT Final Report, 25 Jun. 1973 - 25 Jan. 1974 geometry, cruise speed, propulsion) is investigated, and the results J. D. McClure and A. J. Springer Sep. 1974 161 p refs applied to a candidate 18, 140-kg (40.000-Ib) payload. 5556-km (Contract F33615-73-C-2071) (3000-nmi) transportdesign. Technical and economic comparisons (AD-A001 640; JTCG /AS-74-T-002; AFAPL-TR-73- 122) Avail: are made with current commercial aircraft and other advanced NTIS CSCLO1/3 designs. Author Fire extinguishing systems for the advanced aircraft to 1980 will be required to operate efficiently over a wider range of environmental conditions than ever before. To determine what these environmental conditions will be for engine nacelles and N75-19225# Sydney Univ. (Australia). Dept. of Aeronautical adjacent compartments, a study was performed using an existing Engineering. high performance aircraft. Using this aircraft, its operational SHEAR LAG ANALYSIS OF THICK SKIN AIRCRAFT parameters were extrapolated Out to the advanced aircraft STRUCTURES environment. This study defines the environment in which the Grant P. Steven Sep. 1974 36 p refs fire extinguishing system will be required to operate. primary (ATN-7404) Avail: NTIS HC $3.75 and secondary fire zones, ignition sources, combustibles, and With the increasing thickness of the stiffened skin panels in fire extinguishing agent requirements. GRA aircraft structures it is found that the traditional method of diffusion analysis for concentrated loads is inadequate. A closed form theory is developed which allows the skin to take up its direct N75-19230# Army Aviation Systems Command, St. Louis, Mo. stress stiffness in a more natural manner rather than lumping it MAJOR ITEM SPECIAL STUDY (MISS), U H-iC TAIL ROTOR in with the longitudinal stiffeners. The results of this solution BLADE Final Report, Jan. 1964 - Dec. 1973 are compared with experimental and finite element results and Nov. 1974 22 p it is found to offer significant improvements both in predicting (AD-A001 714; USAAVSCOM-TR-74-47( Avail: NTIS CSCL the diffusion and the maximum shear stress in the skin panel. 01/3 This latter aspect is of importance when the buckling strength Major Item Special Study (MISS) reports are performed on of the skin panel in shear is under consideration. Author DA Form 2410 reportable components. These are time change items and certain condition change items selected because of high cost or need for intensive management. Basically, the N75-19226 5# National Aeronautics and Space Administration. MISS reports are concerned with analyzing reported removal Langley Research Center, Langley Station, Va. data presented in the Major Item Removal Frequency (MIRF) LOW-SPEED WIND-TUNNEL TESTS OF A 1/10-SCALE report. The failure modes reported for each removal are examined MODEL OF A BLENDED ARROW ADVANCED SUPERSONIC and grouped into categories which are intended to clarify the TRANSPORT An Early Domestic Dissemination Report intent of the data reporting. From this data, removal distribution H. Clyde McLemore and Lysle P. Partett Mar. 1975 70 p can be plotted and an MTR (mean time to removal) can be refs calculated. The MISS reports then investigate possible cost (Proj. FEDD) savings based on total elimination of seleàted failure modes. (NASA-TM-X-72671) Avail: NASA Industrial Applications These modes are chosen because of the percentage of failures Centers only to U.S. Requesters: HC $4.25/MF $2.25 CSCL they represent and/or because they appear to be feasible Product 01C Improvement Program (PIP) areas. GRA Tests were conducted in the Langley full-scale tunnel to determine the low-speed aerodynamic characteristics of a 1/10-scale model of a blended-arrow advanced supersonic N75-19231# Army Aviation Systems Test Activity, Edwards transport. Tests were made for the clean configuration and a AFB, Calif. high-lift configuration with several combinations of leading and VIBRATION AND TEMPERATURE SURVEY PRODUCTION trailing-edge flaps deflected for providing improved lift and AH-1G HELICOPTER Final Report, 12 Sep. - 29 Nov. 1973 longitudinal stability in the landing and takeoff modes. The tests Emmett J. Laing and Arnold E. Weand, Jr. Mar. 1974 370 p were conducted for a range of angles of attack from -6 deg to refs 30 deg, sideslip angles from -5 deg to 10 deg, and for Reynolds (AD-A002063; USAASTA-70-15-5) Avail: NTIS CSCL 01/3 numbers from 6.780.000 to 13.850.000 corresponding to test The objective of the entire environmental test project is to velocities of 41 knots to 85 knots. Author determine quantitative vibration and temperature environment data for all present-day Army helicopters. The objective of the AH-1G environmental survey was to determine the vibration and N75-19227# Royal Aircraft Establishment, Farnborough temperature environment of the AH-1G instruments, avionics, (England). Structures Dept. selected components, and the crew stations under all normal A COMPARISON OF FLIGHT LOADS COUNTING METHODS operating conditions. GRA AND THEIR EFFECTS ON FATIGUE LIFE ESTIMATES USING DATA FROM CONCORDE N75-19232# Army Aviation Systems Command, St. Louis, Mo. Ann G. Goodwillie London Aeron. Res. Council 1974 66 p CH-47A ASSESSMENT AND COMPARATIVE FLEET refs Supersedes RAE-TR-73200; ARC-35297 EVALUATION: EXECUTIVE SUMMARY REPORT Final (ARC-CP-1304; RAE-TR-73200; ARC-35297) Avail: NTIS Report HC $4.25: HMSO £1.15; PHI $4.90 Nov. 1974 168 p Four load-time histories of turbulence encountered by (AD-A002057; USAAVSCOM-TR-74-46) Avail: NTIS CSCL Concorde are analyzed by six different peak-counting and 01/3

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The purpose of the executive summary is to provide an N75-19237# Grumman Aerospace Corp.. Bethpage. N.Y. overview and summarization of the CH-47A assessment. The AN IMPROVED AUTOMATED STRUCTURAL OPTIMIZA- parameters presented provide management perspective of the TION PROGRAM Final Report, 27 Mar. 1973 - 30 Aug. CH-47A fleet, in addition to comparative fleet evaluations. 1974 Various presentations of reliability and maintainability related Walter J. Dyer. Sep. 1974 158 p refs parameters give the present system posture of the CH-47A fleet. (Contract F33615-73-C-3086; AF Proj. 1467) Model designation series assessment and comparative fleet (AD-AO02688; AFFDL-TR-74-96) Avail: NTIS CSCL 01/3 evaluations are covered in this report. Quality and command This volume presents the results of an effort to modify, program assessments and the command statistics and problem expand and improve the usefulness of ASOP (Automated summary are the other reports which make up the total executive Structural Optimization Program), originally documented in AFFDL summary for the CH-47A. GRA TR-70-1 18. The new version of the program is named ASOP-2. GRA N75-19234# California Univ.. Los Angeles. Dept. of System Sciences. AN AIRCRAFT APPLICATION OF SYSTEM IDENTIFICA- TION IN THE PRESENCE OF STATE NOISE N75-19238# Army Materiel Command, Alexandria. Va. Kenneth W. Iliff 1974 16 p refs Presented at NATO Advan. ENGINEERING DESIGN HANDBOOK. HELICOPTER Study Inst., New Direc. in Signal Process, in Commun. and Control. ENGINEERING, PART 1: PRELIMINARY DESIGN Darlington, England. 5-17 Aug. 1974 30 Aug. 1974 876 p refs (Grant AF-AFOSR-2492-73; AF Proj. 9769) (AD-AO02007: AMCP-706-201-Pt-1) Avail: NTIS CSCL 01/3 (AD-A001936: AFOSR-74-1756TR) Avail: NTIS CSCL 01/2 This handbook discusses the design requirements applicable A maximum likelihood estimator for a linear system with to Army helicopters for all missions under visual flight rule IVFRI state and observation noise is developed to determine unknown operation, day or night. As such, the scope of this document aircraft coefficients from flight data in the presence of turbulence has been limited to cover the basic aerial vehicles. Design (state noise). The formulation of the algorithm is presented briefly. requirements for mission-essential equipment--e.g., weapons. The linear equations for an aircraft in atmospheric turbulence sensors, cargo-handling equipment--are beyond this scope and are defined. The effectiveness and accuracy of the technique are not discussed, although the helicopter-integral interface are assessed by first applying it to simulated flight data, in requirements for such equipment are included. The design of which the true parameter values are known, then to actual flight power plants, batteries, generators or alternators, and similar data obtained in turbulence. A complete set of aircraft coef- components, are also beyond the scope of the handbook. GRA ficients is obtained as well as an estimate of the turbulence time history. The validity of the estimated state noise and of the estimated coefficients is tested. The feasibility of using the N75-19239# Advanced Technology Labs., Inc., Westbury, N.Y. algorithm for defining an adaptive control law to alleviate the MULTI-SLOT FILM COOLING OF SUPERSONIC AIRCRAFT effects of turbulence on the aircraft is discussed. GRA USING AIR AS A COOLANT Final Technical Report, 4 Jun. 1973 - 3 May 1974 N75-19235# United Aircraft Corp., Stratford. Conn. Sikorsky John I. Erdos and John D. Ranlet Jul. 1974 96 p refs Aircraft Div. (Contract F33615-73-C-3132: AF Proj. 1366) DESIGN AND FATIGUE TESTING OF INTEGRAL ARMORED (AD-AO02673: ALT-TR-202; AFFDL-TR-74-85( Avail: NTIS SERVO ACTUATOR MODIFIED TRUNNION Final Report CSCL 01/3 K. Wood and L. Moriarty Oct. 1974. 38 p The study evaluates multi-slot film cooling using air as an (Contract DAAJ02-74-C-0013; DA Proj. 1F2-62205-AH-88) active coolant for thermal protection of aircraft surfaces under (AD-A002069; SER-64383; USAAMRD L-TR -74-80) Avail: conditions of steady-state (cruise) operation at supersonic speeds NTIS CSCL01/3 and low to moderate altitudes. In-flight refrigeration of captured The program summarized by this report was conducted to atmospheric air using a turbocooler. as described, is assumed design and establish the structural strength of a modified trunnion to be the only practical means of providing the required continuous design for the integral armored servo actuator. The originally supply of cold air. Therefore the properties of the coolant have designed trunnion was found to have a fatigue strength below been described in terms of the vehicle flight conditions and the the mean strength level of comparable CH-54B parts as reported efficiency of a turbocooler. A computer program has been in USAAMRDL Technical Report 73-25. The design analysis and developed based on the described analysis which determines fatigue test data show that the modified trunnion is comparable the slot locations necessary to protect a surface to a specified in strength to the mean strength levels of the equivalent maximum adiabatic wall temperature at a given set of primary components on the production CH-54B helicopter. GRA flow conditions. GRA

N75-19236// Technology, Inc.. Dayton, Ohio. OPERATIONAL USE OF THE UH-1 H HELICOPTERS IN ARCTIC ENVIRONMENT Final Report, 16 Oct. 1972 - N75-19241# Instrument Flight Center, Randolph AFB, Tex. 15 Feb. 1974 HAROWE ALTITUDE WARNING SYSTEM EVALUATION Raymond B. Johnson, Jr. and Ruth E. Meyers Aug. 1974 Final Report 465 p refs Edwin G. Webb, Jr. and Gabriel P. Intano Nov. 1974 15 p (Contract DAAJ02-73-C-00 14: DA Proj. 1 Fl -62208-AH-90) refs (AD-A002603; U5AAMRDL-TR-74-65) Avail: NTIS CSCL (AD-AO02583; IFC-TR-74-7) Avail: NTIS CSCL 01/2 01/3 A pilot factors evaluation of the Harowe altitude warning For the continued study of Army helicopter operations, a system was conducted to determine its acceptability for use in multichannel operational usage data program was conducted on Air Force aircraft. The system has the primary function of assisting two UH-1H helicopters flying assorted missions in the arctic pilots in attaining and maintaining assigned or desired command environment from December 1972 to April 1973. During this altitudes. A secondary function, decision height mode, was period, 88 hours of valid in-flight data were recorded and processed incorporated in the AWS to examine the concept of altitude for each of 15 time-related parameters. These parameters were warning during landing approaches. Ten sorties were flown in a selected to reflect the operational usage of the helicopters. Two North American T-39 Sabreliner. Pilots were selected from the zechniques. the Four Mission Segment and the Flight Condition IFC and instrument pilot instructor school student population. Recognition (FCR) methods, were used in processing and The normal mode , of operation was found acceptable for aiding analyzing the data. The ultimate objective was to improve the pilots in leveling at and maintaining desired altitudes. The accuracy fatigue analyst's understanding of the operational flight spectrum of the normal mode was acceptable and with further development of U.S. Army helicopters and its effect in defining reliable design of the decision height mode. the Harowe system would be criteria for helicopters. GRA acceptable for installation in Air Force aircraft. GRA

271 N75-19243

N75-19243# Avco Lycoming Div., Stratford, Conn. Acoustic shielding benefits for CTOL over-the-wing (01W) DEVELOPMENT OF SELF-ACTING SEALS FOR HELICOPTER applications were obtained experimentally with various multitube ENGINES nozzles using a simple board to represent a wing. Eight nozzles Peter Lynwander Oct. 1974 72 p refs consisting of three to thirteen 2.36-cm diameter tubes were (Contract NAS3-16823) tested. The nozzles included single and double rings of tubes. (NASA-CR-134739; LYC-74-55) Avail: NTIS HC $4.25 CSCL Shielding surface lengths of 15.0 to 54.4 cm were used with 11A each nozzle. Far-field noise data were obtained at 90 deg from An experimental evaluation of a NASA-designed self-acting the jet axis and with a nominal jet exhaust velocity of 200 m/sec. face seal for use in advanced gas turbine main shaft positions The jet noise shielding benefits for the nozzles with double rows was conducted. The seal incorporated Rayleigh step pads of tubes, in terms of sound pressure level spectra, are correlated (self-acting geometry) for lift augmentation. Satisfactory perform- successfully as a function of an earlier developed parameter for ance of the gas film seal was demonstrated in a 500-hour nozzles with a single ring of tubes that includes consideration endurance test at speeds to 183 m/s (600 ft/sec. 54.000 rpm) of the number of tubes and the local peak velocity in the flow and air pressure differential of 137 newtons per squaie cèntimete field at the trailing edge of the shielding surface. Author (198.7 psi). Carbon wear was minor. Tests were also conducted with seal seat runout greater than that expected in engine operation and in a severe sand and dust environment. Seal N75.19247*# National Aeronautics and Space Administration. operation was satisfactory in both these detrimental modes of Lewis Research Center. Cleveland, Ohio. operation. Author COMPARISON OF PARAMETRIC DUCT-BURNING TUR- BOFAN AND NON-AFTERBURNING TURBOJET ENGINES N7519244*# National Aeronautics and Space Administration. IN A MACH 2.7 TRANSPORT Lewis Research Center, Cleveland, Ohio. John B. Whitlow, Jr. Mar. 1975 73 p refs PRELIMINARY EVALUATION OF TURBOFAN CYCLE (NASA-TM-X-71679; E-8269) Avail: NTIS HC $4.25 CSCL PARAMETERS AND ACOUSTICAL SUPPRESSION ON THE 21E NOISE AND DIRECT OPERATING COST OF A COM- A parametric study was made of duct-burning turbofan and MERCIAL MACH 0.85 TRANSPORT suppressed dry turbojet engines installed in a supersonic transport. J. D. Eisenberg Feb. 1975 48 p refs A range of fan pressure ratios was considered for the separate- (NASA-TM-X-71664: E-8239) Avail: NTIS HC $3.75 CSCL flow-fan engines. The turbofan engines were studied both with 20A and without jet noise suppressors. Single- as well as dual-stream A study was made of the effects of turbofan cycle parameters suppression was considered. Attention was concentrated on and the use of acoustic noise suppression material to quiet 200 designs yielding sideline noises of FAR 36 (108 EPNdB) and passenger, Mach 0.85 trijets having design ranges of 2778. below. Trades were made between thrust and wing area for a 4630. and 9260 kilometers (1500, 2500, and 5000 n. mi). constant takeoff field length. The turbofans produced lower Aircraft gross weight and direct operating cost, which varied airplane gross weights than the turbojets at FAR 36 and below. with amount of suppression and cycle selection, are presented The advantage for the turbofans increased as the sideline noise as functions of both EPNdB traded and 90 EPNdB contour limit was reduced. Jet noise suppression, especially for the duct footprint area. Noise levels 10.9 EPNdB below FAR 36 require- stream, was very beneficial for the turbofan engines as long as ments result in a 5 percent increase in DOC for an aircraft duct burning was permitted during takeoff. The maximum dry designed for a range of 9260 kilometers (5000 n. mi.). An unsuppressed takeoff mode, however, yielded better results at aircraft designed for a 2778 kilometer (1500 n. mi.) range would extremely low noise levels. Noise levels as low as FAR 36-11 have an EPNdB level 14 below FAR 36 for this same economic EPNdB were obtained with a turbofan in this takeoff mode, but penalty. In this range of noise level, fan-machinery noise is the at a considerable gross weight penalty relative to the best FAR principal source. Author 36 results. Author

N7519245*# National Aeronautics and Space Administration. N75-19248# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. Langley Research Center, Langley Station, Va. METAL MATRIX COMPOSITES FOR AIRCRAFT PROPUL- INTERIOR NOISE CONSIDERATIONS FOR POWERED-LIFT SION SYSTEMS STOL AIRCRAFT Robert A. Signorelli 1975 24 p refs Presented at Intern. C. Kearney Barton Apr. 1975 19 p refs Conf. on Composite Mater., Geneva, 7-11 Apr. 1975 and Boston. (NASA-TM-X-72675) Avail: NTIS HC $3.25 CSCL 01 14-18 Apr. 1975 Powered-jet configuration which are under development for (NASA-TM-X-71685; E-8280) Avail: NTIS HC $3.25 CSCL use on STOL aircraft involve impingement of the jet engine 21E exhaust onto wing and flap surfaces. The impinging jet produces Studies of advanced aircraft propulsion systems have higher noise levels at lower frequencies than does the jet alone. indicated that performance gains and operating costs are possible These higher levels, together with the close proximity of the through the application of metal matrix composites. Compressor engine and flap noise sources to the fuselage sidewall, suggest fan blades and turbine blades have been identified as components that the noise levels in these aircraft may be high enough to with high payoff potential as a result of these studies. This interfere with passenger comfort. To investigate this possibility, paper will present the current status of development of five interior noise levels were estimated for both an upper surface candidate materials for such applications. Boron fiber/aluminum, blown and an externally blown flap configuration. This paper boron fiber/titanium, and silicon carbide fiber/titanium composites describes the procedure used to estimate the interior noise levels are considered for lightweight compressor fan blades. Di- is described these levels are compared with levels on existing rectionally solidified eutectic superalloy and tungsten wire/ jet aircraft and on ground transportation vehicles. These estimates superalloy composites are considered for application to turbine indicate high levels in the STOL aircraft; therefore, areas of blades for use temperatures to 1100 C (2000 F). Author possible improvements in technology for control of STOL interior noise are also discussed. Author

N7519246*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. N75-19249# Goodyear Tire and Rubber Co.. Akron, Ohio. INFLUENCE OF MULTITUBE MIXER NOZZLE GEOMETRY INVESTIGATION OF 14.5mm API SELF-SEALING! ON CTOL-OTW JET NOISE SHIELDING CRASHWORTHY FUEL TANK MATERIAL Final Report, Jun. U. VonGlahn and D. Groesbeck 1975 21 p refs Presented 1973 - Jun. 1974 at 89th Meeting of the Acoust. Soc. of Am.. Austin, Tex., E. J. Koski and H. F. Villemain Sep. 1974 30 p refs 8-11 Apr. 1975 (Contract DAAJ02-73-C-0099) )NASA-TM-X-71681; E-8275) Avail: NTIS HC $3.25 CSCL (AD-A001752; GTR-19-927; USAAMRDL-TR-74-78) Avail: 20A NTIS CSCL 13/4

272 N75-19259

This final report describes the results of a program for a The analysis of data from flight tests of a Fiat G.91-T3 crashworthy. 14.5mm AN tolerant fuel cell construction developed aircraft is discussed. A survey is presented of possible evaluation and subjected to qualification testing. GRA methods of which five methods were selected. A description is given of the procedures adopted. ESRO N75-19250# General Motors Corp., Indianapolis, Ind. Detroit Diesel Allison Div. INVESTIGATION OF AIRCRAFT COMBUSTOR NOISE Final N75-19256 European Space Research Organization, Paris Report, Jun. 1973 - Apr. 1974 (France). W. R. Semrau and D. E. Frye, Jr. Sep. 1974 413 p refs MANUAL EVALUATION OF SPECIAL FLYING MANEUVERS (Contract DAAJ02-73-C-0088; DA Proj. 1G1-72207-AA-110) FOR THE DETERMINATION OF FLIGHT-MECHANICAL (AD-AO01 737; DDA-EDR-8225; USAAMRDL-TR-74-73) Avail: COEFFICIENTS AND DERIVATIVES FROM FLIGHT TESTS NTIS CSCL21/5 U. VonMejer In its Determination of Aircraft Characteristics Current combustor design technology depends primarily upon from Flight Test (ESRO-TT-104( Nov. 1974 p 17-32 refs empirical correlation and past experimental experience of the Transl. into ENGLISH of "Bestimmung von Flugzeugkenndaten designers. There is a continuing need for knowledge of the aus Flugversuchen", DGLR, Cologne, DLR-Mitt-73-25. 1973 p combustion process and how the different design and performance 29-50 parameters are related. The objective of this program was to Manual data analysis procedures of G.91-T3 aerodynamic investigate the feasibility of measuring combustor noise and then characteristics are described. The aircraft was fitted with relating the noise levels by correlation curves to other pertinent equipment designed to measure the derivatives in non-steady performance parameters, such as combustor efficiency, and mass flight, consisting of measurement units, a recording system and emissions. GRA a data conversion unit. The measurement of the dynamic longitudinal stability is discussed. The method used for evaluation N75-19251# Avco Lycoming Div., Stratford, Conn. of the lateral motion is described. A simplified evaluation of PLT 27 GAS TURBINE ENGINE EXHAUST EMISSION AND special flying maneuvers is considered. ESRO NOISE MEASUREMENTS Final Report, 21 May . 31 Dec. 1973 Phillip M. Rubins, Edward Auerbach, and Jochen A. Daman Sep. 1974 111p refs N75-19257 European Space Research Organization. Paris (Contract DAAJ02-73-C-0068; DA Proj. 1 G 1 -62204-AA-7 1 (France). (AD-A001 728; LYC-74-7; USAAMRDL-TR-62204-AA-7 1) Avail: DETERMINATION OF AERODYNAMIC DERIVATIVES OF NTIS CSCL21/5 THE FIAT G-91 T3 AIRCRAFT FROM FLIGHT TESTS BY The results of the exhaust gas emission analysis show that MEANS OF MANUAL ANALOG MODEL MATCHING the exhaust gases have a low content of unburned combustion A. Pietrass In its Determination of Aircraft Characteristics from products, i.e., hydrocarbons and carbon monoxide, down to idle Flight Test (ESRO-TT-104) Nov. 1974 p 58-87 refs Transi. power due to the high combustion efficiency of this engine. The into ENGLISH of "Bestimmung von Flugzeugkenndaten aus combustion efficiency is 99.5 percent at idle and 99.9 percent Flugversuchen". DGLR, Cologne. DLR-Mitt-73-25. 1973 above 10 percent of maximum-rated power. The smoke numbers P 81.110 of the PLT 27 engine are extremely low. No visible smoke was Aerodynamic derivatives of the FIAT G-91 T3 aircraft were produced at any power setting with any of the injector systems determined by evaluating the results of flight tests in accordance tested. The PLT 27 engine meets the exhaust gas emission with the method of the manual variation of the model parameters standards set by the EPA for 1979 for fixed-wing aircraft. GRA in the analog computer (analog model matching). The test flights were carried Out at an altitude of 20.000 ft and at Mach numbers of 0.4 and 0.8. The results often deviate significantly from the N75-19252# European Space Research Organization. Paris values deduced from the manufacturer's data, this being (France(. particularly true as regards the lateral motion. Author (ESRO) DETERMINATION OF AIRCRAFT CHARACTERISTICS FROM FLIGHT TESTS Nov. 1974 260 p refs Transl. into ENGLISH of "Bestimmung N75-19258 European Space Research Organization. Paris von Flugze ugkenndaten aus Flugversuchen", DG LR. Cologne. (France). DLR-Mitt-73-25, 1973 295 p Proc. of Joint Session of DGLR EVALUATION OF FLIGHT TEST OF THE FIAT G .91 T3 BY Specialist Comm. "Flight Characteristics and Flight Test Tech.", MEANS OF THE METHOD OF FORCED OSCILLATIONS Brunswick. 10-12 Oct. 1972 H. J. Munser In its Determination of Aircraft Characteristics (ESRO-TT-104; DLR-Mitt-73-25( Avail: NTIS HC $8.50; ZLDI. from Flight Test (ESRO-TT-104) Nov. 1974 p 88-106 ref Munich 61.95 DM Transl. into ENGLISH of "Bestimmung von Flugzeugkenndaten Different procedures for the analysis of flight test data in aus Flugversuchen", DGLR, Cologne, DLR-Mitt-73-25. 1973 order to obtain stability characteristics are presented. Methods p 111-132 discussed include: time vectors, forced oscillations, analog The G.91-T3 aircraft was actuated to perform harmonic matching, and' regression analysis. Notwithstanding the consider- oscillations, in order to determine its stability characteristics. Sets able difficulties in data measurement, the task of evaluating of equations were derived in order to calculate the stability aircraft characteristics from flight data is indispensable for setting derivatives for each degree of freedom. The method was tested up reliable mathematical models to describe the dynamic behavior with simulated, and flight test data. It is concluded that the of the aircraft. method of forced oscillations is not particularly suitable for fully automatic evaluation. ESRO N75-19259 European Space Research Organization, Paris N75-19254 European Space Research Organization. Paris (France). (France). EVALUATION OF FLIGHT TESTS OF THE FIAT G-91 T3 COMPARISON OF EVALUATION PROCEDURES FOR THE BY MEANS OF REGRESSION ANALYSIS DETERMINATION OF FLIGHT-MECHANICAL COEF- H. Friedrich In its Determination of Aircraft Characteristics from FICIENTS AND DERIVATIVES FROM FLIGHT TESTS Flight Test (ESRO-TT-104) Nov. 1974 p 107-137 ref Transl. H. Friedrich In its Determination of Aircraft Characteristics from into ENGLISH of "Bestimmung von Flugzeugkenndaten aus Flight Test (ESRO-TT-104( Nov. 1974 p 7-16 refs Transl. Flugversuchen". DG LR, Coloane, D LR-Mitt-73-25. 1973 into ENGLISH of "Bestimmung von Flugzeugkenndaten aus p 133-168 Flugversuchen", DGLR, Cologne, DLR-Mitt-73-25, 1973 p 15-28 The experiences made in applying regression analysis are summarized. Regression analysis is a refined mathematical

273 N75-19260 program that undertakes the breakdown of the aerodynamic differential equations is described; the new method is simpler coefficients into the components due to the individual variables than other procedures of this type known at present. and at the same time eliminates any stochastic errors. All the - Author (ESRO) derivations can be obtained on one run. Attempts at practical evaluation are described. ESRO N75-19265 European Space Research Organization. Paris European Space Research Organization. Paris (France). N75-19260 DETERMINATION OF DERIVATIVES BY A MODEL WITH (France). A SAAB-SCANIA DEVELOPED METHOD FOR OBTAINING AUTOMATIC PARAMETER R. Koehler In its Determination of Aircraft Characteristics from STABILITY DERIVATIVES FROM FLIGHT TESTS Flight Test (ESRO-TT-104) Nov. 1974 224-239 Transl. G. Niss In its Determination of Aircraft Characteristics from p Flight Test (ESRO-TT-104) Nov. 1974 p 138-153 ref Transi. into ENGLISH of "Bestimmung von Flugzeugkenndaten aus into ENGLISH of 'Bestimmunng von Flugzeugkenndaten aus Flugversuchen", DG LA, Cologne. D LA-Mitt-73-25. 1973 p 261-278 Flugversuchen" DG LR. Cologne, DLR-Mitt-73-25. 1973 An analog Circuit that continuously adapts the model p 169-184 parameters to the unknown system characteristic values is used The method used is an assembly of procedures from other to determine the derivatives of an aircraft from flight data. The known methods. Parameters needed for the analyses are available results of an evaluation with a linear and a nonlinear model are from onboard analog tape recordings. The tapes are converted Author (ESRO) to digital computer tapes at the same time as all the scaling discussed. and other instructions are fed into the process. The time intervals to be processed are also defined. After corrections have been N75-19266 European Space Research Organization. Paris made the process continues with calculation of forces and (France). moments. Digital simulation in 6 degrees of freedom is used as SELECTED EXAMPLES OF THE EVALUATION OF VAK 191 a validity check. ESRO B FLIGHT TESTS A. Burdorf In its Determination of Aircraft Characteristics from N75-19261 European Space Research Organization, Paris Flight Tests (ESRO-TT-104) Nov. 1974 p 240-254 Transl. (France). into ENGLISH of "Bestimmung von Flugzeugkenndaten aus CHARACTERISTICS OF THE AJ 37 AIRCRAFT: COMPAR- Flugversuchen". DGLR, Cologne, DLR-Mitt-73-25. 1973 p 279 ISON OF THE RESULTS OF WIND TUNNEL AND FLIGHT TESTS A method is described enabling determination of the roll G.Straeng In its Determination of Aircraft Characteristics from control characteristic of the VAK 191 B aircraft from measured Flight Test (ESRO-TT-104) Nov. 1974 p 154-170 Transl. values obtained during hovering flight. The basic magnitude is into ENGLISH of "Bestimmung von Flugzeugkenndaten aus the rotational velocity as measured by the rate gyro, its variations Flugversuchen", DGLR, Cologne, DLR-Mitt-73-25. 1973 in time approximated by means of a polynomial that is then p 185-202 differentiated. The effect of the discretization of the measured Comparison of aerodynamic coefficients obtained from wind values as a result of data transmission is investigated. The tunnel measurements with results of flight tests is possible only rotational acceleration obtained consists of the desired control in individual cases, since wind tunnel models have a rigidity or acceleration and aerodynamic disturbances. The disturbances elasticity not corresponding to that of the aircraft. Elasticity occurring during these flights were estimated with a simulation correction must, therefore, be carried out. The method used for program for the VAK 191 B aircraft, thereby determining the the AJ 37 aircraft is briefly described. A satisfactory agreement control characteristic. ESRO was found between coefficients obtained from flight tests and the ones calculated from corrected wind tunnel tests. ESRO N75-19267# Royal Aircraft Establishment, Bedford (England). Aerodynamics Dept. N75-19262 European Space Research Organization. Paris DETERMINATION OF THE RUDDER POWER AND DIREC- (France). TIONAL STABILITY OF THE FAIREY DELTA 2 AIRCRAFT SOME ASPECTS OF PERFORMANCE MEASUREMENTS IN USING A WINGTIP PARACHUTE NONSTEADY FLIGHT G. Ingle London Aeron. Res. Council 1974 34 p refs J. A. Mulder In its Determination of Aircraft Characteristics Supersedes RAE-TR-73025; ARC-34852 from Flight Test (ESRO-TT-104) Nov. 1974 p 171-190 refs (ARC-CP-1298; RAE-TR-73025; ARC-34852) Avail: NTIS Transl. into ENGLISH of "Bestimrnung von Flugzeugkenndaten HC $3.75; HMSO 65p; PHI $2.75 aus llugversuchen", DGLR. Cologne, DLA-Mitt-73-25. 1973 The wingtip parachute technique was used to extract a rudder p 20-222 power derivative for the Fairey Delta 2 research aircraft. The The principle of determining the angle of attack and the flight tests revealed that the derivative has a considerably smaller rate of climb from measurements in nonsteady flight is described. value than tunnel tests suggested, and it is believed that this is It is shown that small zero-shifts of the inertial transducers would due to the aeroelasticity of the fin and rudder, and possibly to result in unacceptable errors in the calculated angle of attack unrepresentative flow over the '.,r the wind-tunnel model. and in rate of-climb. A-flight path reconstruction technique yielding Once the derivative was obtained, a directional stability derivative estimates of the zero-shifts turns Out to be the keypoint of the was derived on the assumption that the rudder power derivative flight test technique presented. ESAO was small. The values of the directional stability derivative obtained by this technique agree well with those from other flight tests and reasonably well with tunnel test results. Author (ESRO) N75-19263 European Space Research Organization, Paris (France). DETERMINATION OF THE PARAMETERS OF A SYSTEM N75-19268# Army Foreign Science and Technology Center. OF EQUATIONS OF MOTION FROM FLIGHT TEST DATA Charlottesville, Va. HELICOPTER FLIGHT REGIMES H.U. Schaeufele In its Determination of Aircraft Characteristics from Flight Test (ESRO-TT-104) Nov. 1974 p 191-212 refs G. Samoilov 17 Aug. 1974 18 p Transl. into ENGLISH from Transl. into ENGLISH of "Bestimmung von Flugzeugkenndaten Aviatsiya i Kosmonavtika (USSR). no. 11. 1972 p 20-21, aus Flugversuchen". DGLR, Cologne, DLR-Mitt-73-25. 1973 26-27 (AD-AO01220; FSTC-HT-23-299-74) Avail: NTIS CSCL 01/2 p 223-248 The method of least squares can be used for the determination The article deals with steady regimes of helicopter flight. of the parameters of a system of differential equations. It is The first and the second regimes of a steady he ;opter flight shown that good results can be obtained with this method. A are described. Horizontal flights as well as other rectilinear states subsequent iteration aims at improving the parameters calculated such as climbs and engine descent are studied. A significant with the help of the method of least squares. A new procedure part of the article is devoted to steady turns and some unsteady for the iterative determination of the parameters of a system of flight regimes such as acceleration and slowing down. GRA

274 N75-19546

N75-19269# Princeton Univ., N.J. Instrumentation and Control the trainer without these features. The group using the enhanced Lab. trainer took longer and required more problems to satisfy the FLIGHT PATH CONTROL AND PERFORMANCE ANALYSIS. trials-to-criterion logic used in the practice session. All students PHASES 1 AND 2. INTEGRATED DISPLAY, PHASE 3 Final expressed predominantly favorable attitudes toward the trainer. Report Results are discussed, and recommendations are offered. GRA G. J. Born, T. A. Dukes, E. J. Durbin, and P. B. Sun Jul. 1974 114 p refs (Contract DAAB07-72-C-0161) N7519367*# National Aeronautics and Space Administration. (AD-A002014; ECOM-0161-72-F) Avail: NTIS CSCL 01/3 Lewis Research Center, Cleveland, Ohio. The question of symbology superimposed on an image display PROCESSABLE HIGH TEMPERATURE RESISTANT POLY- for low level flying is explored. Three formats of symbology MER MATRIX MATERIALS superimposed on a TV image display have been developed, based Tito T. Serafinj 1975 20 p refs Presented at Intern. Conf. on the ITED (Integrated Trajectory Error Display). A helicopter on Composite Mater., Geneva, 7-11 Apr. 1975 performance and control model developed earlier is reviewed. (NASA-TM-X-71682: E-7324l Avail: NTIS HC $3.25 CSCL A gas turbine engine model is developed, first for the ideal liD turbine, and then modified for a practical engine mounted in a Studies conducted with addition-type polyimides are reviewed helicopter. Three modifications of the SATED (Superimposed with emphasis on the development of the Polymerization of Integrated Trajectory Error Display) are described. These changes Monomer Reactants (PMR) approach, in which PMR occurs on have been made to improve the integration of the symbology the surface of the reinforcing fibers. Author with the image display. The modified display is described in the form of a briefing for simulator test subjects. GRA N15-19413# National Aerospace Lab.. Tokyo (Japan). ON FATIGUE CRACK ARRESTING BY A STOP-HOLE IN N75-19271 Calspan Corp., Buffalo, N.Y. 2024-T3 ALUMINUM ALLOY SHEET SPECIMENS A STUDY FOR ACTIVE CONTROL RESEARCH AND Hiroyuki Terada and Yoshiaki Kakuta 1974 18 p refs In VALIDATION USING THE TOTAL IN-FLIGHT SIMULATOR JAPANESE; ENGLISH summary (TIFS) AIRCRAFT (NAL-TR . 359) Avail: NTIS HC $3.25 Robert T. N. Oien, Hamilton Daughaday. Dominick Andrisani, II, Attempts made to find out the most effective way to arrest Robert D. Till, and Norman C. Weingarten Apr. 1975 164 p the fatigue crack by the stop-hole are reported. The influence of refs the following three parameters on the crack propagation life (Contract NAS1-13329) was studied; the size of the stop-hole, the distance between (NASA-CR-132614; AK-5560-F-1) Avail: NTIS HC$6.25 CSCL the front edge of the stop-hole and the tip of the crack occured, 148 and the crack length at the moment of repair. Single edge notched The results of a feasibility study and preliminary design for sheet specimens of 2024-T3 aluminum alloy were tested under active control research and validation using the Total In-Flight partially tensile fatigue loads with Constant stress amplitudes. Simulator (TIFS) aircraft are documented. Active control functions Conclusions drawn from the study show: (1) repairing fatigue which can be demonstrated on the TIFS aircraft and the Cost of cracks of shorter length is more effective; and (2) the radius of preparing, equipping, and operating the TIFS aircraft for active the stop-hole must be large enough to release the stress near control technology development are determined. It is shown that the crack tip sufficiently. The distance between the front edge the TIFS aircraft is as a suitable test bed for inflight research of the stop-hole and the tip of the fatigue crack occurring must and validation of many ACT concepts. Author be short enough to leave sufficient residual width and to leave an effective residual compressive stress region around the crack tip. Author N75'19274# Royal Aircraft Establishment, Farnborough (England). N75-19414# National Aerospace Lab.. Tokyo (Japan). REAL-TIME SIMULATION OF JET ENGINES WITH A RELATION BETWEEN SCATTER OF FATIGUE LIFE AND DIGITAL COMPUTER(1), FABRICATION AND CHARACTER- S-N CURVE IN AIRCRAFT STRUCTURAL ALUMINIUM ISTICS OF THE SIMULATOR ALLOY 2024-T4 K. Nishio, N. Sugiyama, T. Koshinuma, T. Hashimoto, T. Ohata. Toshiyuki Shimokawa and Yasumasa Hamaguchi Apr. 1974 and H. Ichikawa 18 Sep. 1974 53 p refs Transl. into ENGLISH 10 p refs In JAPANESE; ENGLISH summary from Japanese report (NAL-TR-360( Avail: NTIS HC $3.25 (RAE-Lib-Trans-1768; BR46783; NAL-TR-283( 1972)) Avail: The accumulated effect on fatigue life of the experimental NTIS HC $4.25 conditions, the material properties in its virgin state, and the The fabrication and performances of a real-time jet engine cumulative process of damage in cyclic loading was investigated simulator using a digital computer are reported along with as an error in the applied stress. This concept was applied to simulation test results. Actual engine test data for the lift jet the results of a series of fatigue tests on unnotched sheet engine JR-100H are included. Author specimens of aircraft structural aluminum alloy 2024-T4. Firstly, the S-N curve, where N is the median fatigue life, was determined N75-19278# University of Southern Calif.. Los Angeles. from a series of experimental results. The equivalent stress of Behavioral Technology Labs. each specimen, which is considered to be the sum of the applied FIELD EVALUATION OF MODEL 2 OF THE COMPUTER- stress and its estimated error, was calculated from the S-N BASED, INDIVIDUAL TRAINER FOR THE RADAR IN- curve and the fatigue life of each specimen. The distribution of TERCEPT OFFICER Final Report, 1 Jan. - 31 Dec. 1974 tye equivalent stress is quantitatively evaluated. Secondly, using Joseph W. Rigney, D. Kirk Morrison, Louis A. Williams. and the order statistics and assuming the distribution of the Douglas M. Towne Jul. 1974 58 p refs equivalent stress to be normal, the fatigue life distribution having (Contract N61339-73-C-0065; ARPA Order 2310) the same scatter as that obtained in the experiment was introduced (AD-AO02705; NAVTRAEQUI PCEN-73-C-0O65-2) Avail: NTIS from the S-N curve and the assumed equivalent stress distribution. CSCL 05/9 The interrelation between the scatter of the equivalent stress, Model II of the basic skills intercept trainer for Radar Intercept the S-N curve, and the scatter of fatigue life is discussed. Officers was evaluated in a school environment. Model II Author incorporated different instructional sequencing logic, additional weaponry capability, and additional graphic features from Model N75-19546# Westinghouse Electric Corp.. Lima, Ohio. Aero- I (developed under a previous project). These added features space Electrical Div. were designed to assist the student in understanding the intercept PROGRAM FOR THE DEVELOPMENT OF A SUPER- geometry and in learning to use the B-scan display. One (N-31) CONDUCTING GENERATOR. PART 1: PHASE 1 Report of two random groups practiced on a trainer with these for May 1971 - Jan, 1974 additional graphics, the other group (N-29) used a version of A. D. Blaugher. J. L. McCabria, and James H. Parker, Jr. Oct.

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N75-19878// Air Force Weapons Lab., Kirtland AFB, N.Mex. 1974 243 p refs (Contract F33615-71-C-1591; AF Proj. 3145) USAF AIRCRAFT TAKEOFF LENGTH DISTANCES AND (AD-A001649; AFAPLTR-74-84-Pt-1) Avail: NTIS CSCL CLIMBOUT PROFILES Final Report, 1 Jun. 1973 - 15 Sep. 10/21 1974 The work included the preliminary studies and design of a David F. Menicucci Oct. 1974 35 p ref 12.000 RPM. 5 MVA. 400 Hz generator with a rotating field. It (AD-AO01826; AFWL-TR-74-279) Avail: NTIS CSCL 13/2 also includes the individual tests of the most critical components, The Air Force Weapons Laboratory in cooperation with the i.e.. the dynamic cryogenic seals, power leads, interconnections Argonne National Laboratory has developed a computerized Air of the SC coils. SC field windings, and construction and test of Quality Assessment Model (AQAM) which will be used to assess a complete rotor. The cold rotor tests (at 4.2K) were conducted the impact of airbase activity on Ambient Air Quality within the up to the overspeed value of 13.200 rpm. Full excitation of the airbase and in surrounding areas. The AQAM has the capability field (equivalent to 5.32 MVA) was obtained at the operating of precisely simulating the aerial and ground operating cycle of each active USAF aircraft. An important component of this speed of 12.000 rpm. GRA operating cycle is the takeoff runway roll distance. The runway roll is associated with high engine power settings and cor- N75-19557# Army Foreign Science and Technology Center, respondingly high pollution emissions. This report outlines the Charlottesville, Va. procedure for utilizing least-squares curve fitting techniques to ANTENNAS, A COLLECTION, ISSUE 15 develop equations to accurately define the runway roll distance L Sopin, L. Bazelyan. G. lnyutin. V. Narbut. and V. Zamyatin for each USAF aircraft in given meteorological conditions. GRA 15 Jun. 1974 128 p refs Transl. into ENGLISH from Antenny (Moscow), no. 15. 1972 N75-20209 European Space Research Organization. Paris (AD-A002646; FSTC-HT-23-718-74) Avail: NTIS CSCL 09/5 (France). Contents: The theory of two-dimensional arrays with random THE COEXISTENCE OF TWO SUPERSONIC PLANE FLOWS arrangement of the radiators; Experience in the development of IN THE PRESENCE OF A LONGITUDINAL PRESSURE two-dimensional antenna arrays with random arrangement of the GRADIENT c02 radiators; On the three-dimensional structure of cross- Jacques Paulon, Xavier Garonne et al In its La Rech. Aerospatiale, polarization radiation of axisymmetrical parabolic antennas; On Bi-monthly Bull. No. 1974-2(ESRO-TT-113( Dec: 1974 p 15-34 the problem of reducing directive gain and dispersion of the refs Transl. into ENGLISH from La Rech. Aerospatiale, Bull. direction of the principal maximum of the radiation pattern of a Bimestriel (Paris), no. 1974-2. Mar.-Apr. 1974 p 75-82 sectionalized antenna of a traveling wave; On the problem of the statistics of a field of focussed systems; Directive gain and A study of two supersonic, plane, parallel Vows at different input impedence of a flat radiator located close to a boundary Mach numbers, but at the same pressure, is used to contribute surface; Analysis of the properties of coupled structures; An to the understanding of the complex stratified flows encountered evaluation of aircraft capacitor medium wavelength folded- in supersonic compressors with shocks. In particular, it sheds GRA dipole antennas for their efficiency. some light on the shape of de-energization shock waves and allows the verification of the correlation formulas used for N75-19585# Advisory Group for Aerospace Research and calculating flow separations at the walls. Author (ESRO) Development. Paris (France). TECHNICAL EVALUATION REPORT ON FLUID DYNAMICS PANEL SYMPOSIUM ON V/STOL AERODYNAMICS N75-20212 European Space Research Organization. Paris refs (France). B. M. Spee (Natl. Aerospace Lab.) Feb. 1975 13 p SOME NOTES ON THE THERMODYNAMICS OF THRUST Symp. held at Delft. Netherlands, 24-26 Apr. 1974 REVERSAL IN FLIGHT c77 (AGARD-AR-78) Avail: NTIS HC $3.25 Pierre Garriere In its La Rech. Aerospatiale, Bi-monthly Bull. Papers presented at the Fluid Dynamics Panel Symposium No. 1974-2 (ESRO-TT- 113) Dec. 1974 86-88 Transl. into are reviewed along with the Current situation in V/STOL p ENGLISH from La Rech. Aerospatiale, Bull. Bimestriel (Paris(, aerodynamics research. The following areas were discussed; no. 1974-2. Mar.-Apr. 1974 107 powered high-lift systems; mechanical high-lift systems and jet p lift. It is concluded that the direct operating Cost of V/STOL It is shown that, in order to obtain a maximum braking must be decreased through optimization of aerodynamic effect in flight, the thrust reversal should take place in a characteristics in order to compete with conventional aircraft. Author manner leading to the greatest possible irreversibility through interaction of the jet with the external free flow. Thrust reversers should be tested, not on a test bench. but in a wind tunnel McDonnell-Douglas Astronautics Co.. St. Louis, N75-19586 t# only. Author (ESRO) Mo. ANALYTICAL COMPARISON OF HYPERSONIC FLIGHT AND WIND TUNNEL VISCOUS/INVISCID FLOW FIELDS Final N75-20213 European Space Research Organization. Paris Report (France). H. J. Fivel, R. V. Masek. and L. J. Mockapetris Washington DETERMINATION BY MEANS OF HYDRAULIC ANALOGY NASA Feb. 1975 124 p refs OF THE TRANSONIC FLOW IN A BLADE CASCADE c02 (Contract NAS1-1 1728) Emilien Robert, Lucien Reding et al In its La Rech. Aerospatiale, (NASA-CR-2489( Avail: NTIS HC $5.25 CSCL 20D 81-monthly Bull. No. 1974-2 (ESRO-U-113) Dec. 1974 Flow fields were computed about blunted, 0.524 and 0.698 p 89-101 refs Trans 1. into ENGLISH from La Rech. Aerospatiale, radians, cone configurations to assess the effects of nonequilibrium Bull. Bimestriel (Paris). no. 1974-2. Mar-Apr. 1974 p 108-112 chemistry on the flow field geometry, boundary layer edge conditions, boundary layer profiles, and heat transfer and skin A technique is described for studying the flow through the friction. Analyses were conducted at typical space shuttle entry interblade channels of a transonic cascade and for determining conditions for both laminar and turbulent boundary layer flow. the position of the flow isobars. The use of injected powder In these calculations, a wall temperature of 1365 K (2000 F) particles and motion picture photography reveals the flow velocity was assumed. The viscous computer program used in this and direction along the isobars. Author (ESRO) investigation was a modification of the Blottner non-similar viscous code which incorporated a turbulent eddy viscosity model after Cebeci. The results were compared with equivalent calculations N75-20221 # National Aeronautics and Space Administration. for similar (scaled) configurations at typical wind tunnel conditions. Flight Research Center, Edwards, Calif. Wind tunnel test gases included air, nitrogen. CF4 and helium. A FLIGHT TEST INVESTIGATION OF THE ROLLING The viscous computer program used for wind tunnel conditions MOMENTS INDUCED ON A T-376 AIRPLANE IN THE WAKE was the Cebeci turbulent non-similar computer code. Author OF A B.747 AIRPLANE

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Harriet J. Smith Apr. 1975 23 p refs Flight vehicles are characterized according to their manner (NASA-TM-X-56031) Avail: NTIS HC $3.25 CSCL O1C of operation and type of propulsion system: and their associated A flight test investigation of the B-747 vortex wake sources of noise are identified. Available noise reduction characteristics was conducted using a T-37B as a probe aircraft. technology as it relates to engine cycle design and to powerplant The primary purpose of the program was the validation of the component design is summarized. Such components as exhaust results of B-747 model tests which predicted significant alleviation jets, fans, propellers, rotors, blown flaps, and reciprocating- of the vortex strength when only the inboard flaps were deflected. engine exhausts are discussed, along with their noise reduction Measurements of the vortex-induced rolling moments of the probe potentials. Significant aircraft noise reductions are noted to have aircraft showed that the predicted alleviation did occur. The effect been accomplished by the application of available technology in of landing gear extension, increased lift coefficient, idle thrust, support of noise certification rules. Further noise reductions to and sideslip were investigated, and all had an adverse effect on meet more stringent future noise regulations will require the alleviated condition as evidenced by increased Induced rolling substantial additional technology developments. Improved moments of the T-37B probe aircraft. Idle thrust also increased analytical prediction methods, and well-controlled validation the strength of the 6-747 wake vortexes with both inboard and experiments supported by advanced-design aeroacoustic facilities, outboard flaps, extended. Author are required as a basis for an effective integrated systems approach to aircraft noise control. Author N7520222*# Kansas Univ., Lawrence. THE FUTURE OF AERONAUTICS N75-20231 * National Aeronautics and Space Administration. 1974 419 p refs Presented at NASA/Univ. Conf. on Aeron., Ames Research Center, Moffett Field, Calif. Lawrence, Kans., 23-24 Oct. 1974 Sponsored in part by ON WAKE VORTEX ALLEVIATION - NASA Leonard Roberts In Kans. Univ. The Future of Aeron. 1974 (NASA-CR-142559) Avail: NTIS HC $10.50 CSCL 01 p 139-167 refs The proceedings of a conference on the future of aeronau- CSCL O1A tics are presented. The subjects discussed include the following: Research within NASA relating to the nature of lift-induced (1) aeronautics and the education of the engineer, (2) technical vortex wakes behind large aircraft and the means whereby the trends in aeronautics, and (3) the role of the university in hazard they represent to smaller aircraft can be alleviated is aeronautics. The technical trends in aeronautics are concerned reviewed. The research, carried Out in ground based facilities with aircraft noise control, the effect of the aircraft on the and in flight shows that more rapid dispersion of the wake can environment, airborne electronics for automated flight, and trends be effected by several means and that the modification of in aircraft design. span-loading by appropriate flap deflection holds promise of early practical application. Author

N7520223* National Aeronautics and Space Administration, N7520232* National Aeronautics and Space Administration. Washington. D.C. Langley Research Center, Langley Station, Va. AERONAUTICS IN THE AMERICAN SOCIETY AIRBORNE ELECTRONICS FOR AUTOMATED FLIGHT James C. Fletcher In Kans. Univ. The Future of Aeron. 1974 SYSTEMS P 1-10 George B. Graves, Jr. In Kans. Univ. The Future of Aeron. CSCLO1B 1974 p 168-181 refs The trends in aeronautics and aeronautical education are CSCL OlD discussed with respect to the roles of industry, government, and The increasing importance of airborne electronics for use in the universities. The importance of the aviation industry to the automated flight systems is briefly reviewed with attention to economy of the country is examined. The impact of reduced both basic aircraft control functions and flight management enrollment of aeronautical engineering students in the universities systems for operational use. The requirements for high levels of on the future of the aeronautical industry is stressed. It is stated systems reliability are recognized. Design techniques are discussed that the role of the government should be to sponsor and conduct and the areas of control systems, computing and communica- basic research and advanced technology programs for civil and tions are considered in terms of key technical problems and military aviation, and the specification, development, procure- trends for their solution. Author ment, and operation of military aircraft. Recommendations are made for approaches which may be taken to influence more N7520235* qualified students to enter the field of aeronautics. Author National Aeronautics and Space Administration. Langley Research Center. Langley Station, Va. SOME TRENDS IN AIRCRAFT DESIGN: STRUCTURE N7520228* Lockheed Aircraft Corp., Sunnyvale, Calif. THE NEXT FORTY YEARS IN AVIATION George W. Brooks In Kans. Univ. The Future of Aeron. 1974 Willis M. Hawkins In Kans. Univ. The Future of Aeron. 1974 p 212-270 refs p 58-95 CSCL O1C CSCLO1B - Trends and programs currently underway on the national A prediction of the status of various types of aviation scene to improve the structural interface in the aircraft design activities whióh may be expected in twenty years is presented. process are discussed. The National Aeronautics and Space The basic assumptions are that the population of the nation will Administration shares a partnership with the educational and continue to grow at more than 7 percent and that the need for industrial community in the development of the tools, the criteria, air transportation of passengers and cargo will increase according- and the data base essential to produce high-performance and ly. Various predictions are also made for the developments in cost-effective vehicles. Several thrusts to build the technology vertical takeoff aircraft, short haul airline operations, general in materials, structural concepts, analytical programs, and aviation, and military aircraft. Areas of improvement are integrated design procedures essential for performing the trade-offs indicated for air navigation, air traffic control, night vision, quiet required to fashion competitive vehicles are presented. The aircraft, and the use of hydrogen as a fuel. Author application of advanced fibrous composites, improved methods for structural analysis, and continued attention to important peripheral problems of aeroelastic and thermal stability are N7520229* National Aeronautics and Space Administration. among the topics considered. Author Langley Research Center, Langley Station, Va. TRENDS IN AIRCRAFT NOISE CONTROL N75,20236* National Aeronautics and Space Administration. Harvey H. Hubbard and Earl W. Conrad In Kans. Univ. The Flight Research Center, Edwards, Calif. Future of Aeron. 1974 p 96-122 refs STATUS AND TRENDS IN ACTIVE CONTROL TECHNOL- OGY CSCLO1C - Herman A. Rediess and Kenneth J. Szalai In Kans. Univ. The

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Future of Aeron. 1974 p 271-320 refs TO MACH 2.01 Donald L Maiden Washington Apr. 1975 77 p refs CSCL O1C (NASA-TN-D-7906: L-9976) Avail: NTIS HC $4.25 CSCL The emergence of highly reliable fly-by-wire flight control 01A systems makes it possible to consider a strong reliance on A wind-tunnel investigation was conducted to determine the automatic control systems in the design optimization of future aeropropulsion performance (thrust-minus-drag) of a single-engine, aircraft. This design philosophy has been referred to as the control variable-geometry, two-dimensional (2-D) wedge nozzle with configured vehicle approach or the application of active control simulated translating-shroud and collapsing-wedge mechanisms. technology. Several studies and flight tests sponsored by the The investigation was conducted statically and at Mach numbers Air Force and NASA have demonstrated the potential benefits from 0.60 to 2.01 at an angle of attack of 0 deg and at varied of control configured vehicles and active control technology. The jet total-pressure ratios up to 21, depending on the Mach present status and trends of active control technology are reviewed number. The results indicate that the isolated aeropropulsion and the impact it will have on aircraft designs, design techniques, performance of a variable-geometry two-dimensional wedge nozzle and the designer is predicted. Author is competitive with axisymmetric nozzles at transonic and supersonic speeds, but the isolated performance is slightly inferior for static take-off and low subsonic speeds. With the use of a N75-20237 * National Aeronautics and Space Administration. simple tertiary-air ejector, the static take-off performance was Langley Research Center, Langley Station, Va. increased. Author OPPORTUNITIES FOR AERODYNAMIC-DRAG REDUC- TION N7520248*# National Aeronautics and Space Administration. Robert E. Bower In Kans. Univ. The Future of Aeron. 1974 Lewis Research Center, Cleveland, Ohio. p 321-350 reis AN EXPERIMENTAL INVESTIGATION OF COMPRESSOR Methods for reducing aerodynamic drag to improve aircraft STALL USING AN ON-LINE DISTORTION INDICATOR AND performance and reduce fuel consumption are discussed. The SIGNAL CONDITIONER techniques considered are: (1) pressure drag reduction, (2) William G. Costakis and Leon M. Wenzel Washington Apr. supercritital airfoils. (3) subcritical airfoils. (4) induced drag 1975 33 p refs reduction by over-the-wing blowing and increased aspect ratio. (NASA-TM-X-3182; E-8120) Avail: NTIS HC $3.75 CSCL and (5) friction drag reduction by laminar flow control and slot O1A injection. It is stated that a 50 percent reduction from current The relation of the steady-state and dynamic distortions and drag values is expected through the application of these the stall margin of a J85-13 turbojet engine was investigated. techniques. Author A distortion indicator capable of computing two distortion indices was used. A special purpose signal conditioner was also used N75-20241 * National Aeronautics and Space Administration. as an interface between transducer signals and distortion indicator. Langley Research Center, Langley Station, Va. A good correlation of steady-state distortion and stall margin UNIVERSITY RESEARCH IN AERONAUTICS was established. The prediction of stall by using the indices as John E. Duberg In Kans. Univ. The Future of Aeron. 1974 instantaneous distortion indicators was not successful. A p 371-373 sensitivity factor that related the loss of stall margin to the CSCL 01 turbulence level was found. Author The contributions which universities can make to aeronautical research projects are discussed. The activities of several N75-20249# National Research Council of Canada, Ottawa facilities are presented to show the effectiveness of the educational (Ontario). and research programs. Reference is made to the Intergovernmen- QUARTERLY BULLETIN OF THE DIVISION OF MECHANI- tal Personnel Act of 1970 which permits an exchange of Federal CAL ENGINEERING AND THE NATIONAL AERONAUTICAL agency personnel with state and local governments and with ESTABLISHMENT, 1 OCTOBER - 31 DECEMBER 1974 public and private higher education schools. Author 31 Dec. 1974 102 p refs (DME/NAE-1974(4)) Avail: NTIS HC $5.25 N7520242* Cessna Aircraft Co., Wichita, Kans. Research data on estimates of stability derivatives of the GENERAL AVIATION'S FUTURE NEED FOR RESEARCH Bell 205 helicopter and V/STOL aircraft, air cushion vehicle Malcolm Harned In Kans. Univ. The Future of Aeron. 1974 transportation in Canada. and thermodynamic efficiency of the p 374-375 Otto and Carnot cycles are summarized. CSCLO,1B The research requirements for general aviation aircraft are presented. Emphasis is placed on improving the performance of N75-20260 National Aeronautical Establishment. Ottawa airfoils, propellers, and engines. Additional requirements are (Ontario). Flight Research Lab. expressed with respect to external noise reduction, internal noise ESTIMATES OF THE STABILITY DERIVATIVES OF A reduction, and exhaust emission control. The requirement for HELICOPTER AND A V/STOL AIRCRAFT FROM FLIGHT anti-icing developments to create improved flight safety is DATA discussed. Author D. G. Gould and W. S. Hindson In NRC Quart. Bull, of the Div. of Mech. Eng. and the NatI. Aeron. Estab. 31 Dec. 1974 N7520243* Stanford Univ., Calif. p 1-20 refs Presented at the Specialists Meeting on Aircraft UNIVERSITY RESEARCH IN AERONAUTICS State and Parameter Identification Tech., Hampton, Va., 5-8 Nov. Holt Ashley In Kans. Univ. The Future of Aeron. 1974 1974 p 376-381 Stability derivatives for the Bell 205 helicopter have been CSCLO1B derived from flight data using a least squares quasilinearizetion The types of aeronautical research projects which universities technique. The aircraft model, which included a first order should and should not accept for Government and industry are representation of rotor response characteristics was based on discussed. Specific examples of suitable and unsuitable research fundamental parameters descriptive of the particular design. A projects are presented. The author recommends two modes by conglomerate analysis procedure which produced estimates based which universities can be of assistance to other organizations in on data from several similar manoeuvres was used to increase aeronautical research. Author the confidence in the results obtained. Data from the CL-84 V/STOL aircraft were also analyzed, indicating the validity of N75-20247 *# National Aeronautics and Space Administration. certain a priori longitudinal stability derivatives for the aircraft, Langley Research Center, Langley Station, Va. and yielding estimates of others. The results indicate the need PERFORMANCE OF AN ISOLATED TWO-DIMENSIONAL to use a more elaborate modelling technique, such as was used VARIABLE-GEOMETRY WEDGE NOZZLE WITH TRANSLAT- for the Bell 205, which takes into account the particular ING SHROUD AND COLLAPSING WEDGE AT SPEEDS UP complexities of the aircraft. Author

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N75-20281 Division of Mechanical Engineering. Ottawa (Ontario). the measured pressure distributions. The experimental results are Engine Lab. compared with the results of inviscid theory to gain an appreciation SOME AIR CUSHION TECHNOLOGY RESEARCH IN of the magnitude of shock wave-boundary layer interaction effects. CANADA The results have indicated that inviscid theory shows reasonable H. S. Fowler In NRC Quart. Bull, of the Div. of Mech. Eng. agreement with the experimental results where the length of and the NatI. Aeron. Estab. 31 Dec. 1974 p 21-31 rats (For the interaction region is short compared with the flare length. availability see N75-20249 12-01) Author Details are given of hovercraft use for transport of heavy loads over poor roads on off-road terrain which varies with the N76-20258# Cranfield Inst. of Technology (England). Coll. of season. Special attention was given to: (1) low temperature Aeronautics. operation of ACV5, (2) the use of ACVs as icebreakers. (3) field LONGITUDINAL AERODYNAMIC DERIVATIVES OF A trials of hoverbarges. and (4) the use of mobile laboratory vehicles. SLENDER DELTA-WING RESEARCH AIRCRAFT EXTRAC- Project CASPAR, for studying performance and skirt-terrain TED FROM FLIGHT DATA interaction of various skirt problems. Author V. Klein [1975] 85 p refs (Cranfield-Aero-27) Avail: NTIS HC $4.75 The Maximum Likelihood parameter-estimation algorithm was Air Force Inst. of Tech.. Wright-Patterson AFB, N75-20263# used to extract the longitudinal aerodynamic derivatives from Ohio. School of Engineering. flight data for the Handley Page HP 115 slender delta-wing COMPUTER SIMULATION OF MAINTENANCE FOR research aircraft. The responses in the rate of pitch and vertical MULTI-MISSION RPV'S M.S. Theóia acceleration were excited from the horizontal steady-state flights refs Paul R. Sheridan Dec. 1974 104 p at different airspeeds by the elevon deflection. In some cases (AD-A003351; GSA/SM/74D-8) Avail: NTIS CSCL 01/3 the measured time histories were converted into frequency The purpose of this research project was to develop a response curves. from which the unknown parameters were computer simulation model of maintenance for a multi-mission estimated. For the low angle of attack measurements the linear RPV. The model is developed with as much flexibility as possible model of the aircraft was adequate, whereas for the runs measured consistent with the expressed desires of the RPV SPO at at high angle of attacks the non-linear model had to be used. Wright-Patterson AFB. Ohio. A method of analyzing the output Some identifiability problems were met because of the limited of the simulation to determine trade-offs between the use of number of measured outputs and incorrect design of the manpower and vehicles is also developed and a numerical example experiment. The non-dimensional aerodynamic derivatives is presented. The greatest value of this research is the potential extracted were compared with those from wind-tunnel tests for use in various areas of study concerning RPV maintenance. and steady-state measurements. A reasonable degree of This report does not address questions of operational effectiveness consistency between the various sets of results was obtained. of MMRPVs in the target area. GRA Author N75-20253 4l National Aeronautics and Space Administration. Lewis Resbarch Center, Cleveland, Ohio. N75-20259# Cranfield Inst. of Technology (England). Coll. of EVALUATION OF SOME CONTROL-VOLUME TECHNIQUES Aeronautics. FOR ANALYSIS OF SHOCK-BOUNDARY LAYER INTERAC- PARAMETER IDENTIFICATION APPLIED TO AIRCRAFT TIONS IN SUPERSONIC INLETS V. Klein [1975) 153 p refs Warren R. Hingst Washington Apr. 1975 15 p refs (Cranfield-Aero-26) Avail: NTIS HC $8.25 (NASA-TM-X-3186; E-7866) Avail: NTIS HC $3.25 CSCL All three steps in the identification as follows: (1) characteriza- 200 tion, (2) parameter estimation and (3) verification are considered Various control-volume models used to analyze the shock and applied to the determination of aircraft parameters from boundary layer bleed interaction were investigated. The bleed flight data. The estimation procedure includes the equation error assumptions of the models and their influence on the analytical method and the output error method with the weighted least solutions are discussed. The results of the analysis using these squares, maximum likelihood and Bayesian estimation technique. models are compared with experimental boundary-layer data taken The problems concerning accuracy and identifiability are also in a supersonic inlet. The experimental Mach number upstream discussed. A general computing algorithm is developed covering of the interaction Was 1.66, and the oblique-shock pressure ratio all estimation techniques described. It is applicable to linear as was 1.33. The boundary layer data included bleed flow rates up well as nonlinear systems and is flexible enough for the solution to approximately 0.6 of the upstream boundary layer mass flow of various identifiability problems. Using this algorithm the rate. The first model assumed the bleed was removed from the computing program has been compiled in general terms to enable control volume with a momentum that was characterized by a the user to achieve the Objectives mentioned. As examples, the pressure termediate between the upstream and downstream results of the identification of aircraft parameters and aerodynamic pressures. The second model assumed the control volume was derivatives for four different aircraft are presented. Author bounded by a streamline dividing the bleed and residual flows and eliminated the need to specify the momentum of the bleed flow. Comparison of the results using the models showed that N7520260*# Boeing Co., Seattle, Wash. specifying the bleed pressure in one model was equivalent to SIDESLIP OF WING-BODY COMBINATIONS refs specifying the pressure along the dividing streamline in the Paul E. Rubbert Oct. 1972 55 p (Contract NAS2-5006) other. Author (NASA-CR-114716; 06-60160) Avail: NTIS HC $4.25 CSCL O1A N75-20257// Weapons Research Establishment. Salisbury A small-disturbance theory is developed for predicting the (Australia). aerodynamics of an airplane in sideslip. Second-order terms BOUNDARY LAYER EFFECTS IN SUPERSONIC FLOW OVER involving the interaction between sideslip angle and angle of CYLINDER-FLARE BODIES attack. sideslip angle and wing camber, etc.. are retained. It is M. L Robinson Jul. 1974 54 p refs found that the second-order terms can produce the dominant (WRE-Rept-1238(WR/D)) Avail: NTIS HC $4.25 sideslip effects when the dihedral, of the li fting surfaces is small. The effects of shock wave-boundary layer interaction on the Numerical implementation of the theory requires a solution forces acting on cylinder-flare bodies have been investigated procedure capable of producing accurate velocity gradients in experimentally at a Mach number of 2.8. Detailed pressure the first-order solution. Author measurements have been made on two axisymmetric bodies with 15 deg semi-angle flare afterbodies in the incidence range 0 deg to 10 deg. The Reynolds numbers of the tests based on the N75-20262# Royal Aircraft Establishment. Farnborough distance from the nose to the cylinder-flare junction varied between (England). Aerodynamics Dept. 0.8 million and 2.5 million. Force distributions and total forces COMPUTATION OF THE VELOCITY FIELD INDUCED BY A and centre-of-pressure positions were obtained by integration of PLANAR SOURCE DISTRIBUTION APPROXIMATING A

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SYMMETRICAL NON-LIFTING WING IN SUBSONIC FLOW superposition of two waves traveling downstream, namely, the J. A. Ledger London Aeron. Res. Council 1974 41 p refs exciting sound wave and the excited instability wave. Supersedes RAE-TR-72176; ARC-34383 Author (ESRO) (ARC-R /M-3751; RAE-TR-72 176; ARC-34383) Avail: NTIS HC $3.75; HMSO £1.65; PHI $6.75 N75-20271# Douglas Aircraft Co.. Inc., Long Beach, Calif. The singular double integrals which arise in the calculation A THEORETICAL METHOD FOR CALCULATING THE of the components of perturbation velocity due to a swept wing AERODYNAMIC CHARACTERISTICS OR ARBITRARY with given thickness distribution by linearized theory, were EJECTOR-JET-FLAPPED WING: THEORETICAL ANALYSIS evaluated by a numerical method. Two computer programs were Final Report written, one for points on the wing planform and one for points Michael L. Lopez and Norman F. Wasson Jun. 1974 142 p off. Following the techniques adopted by Sells, the integral over refs the wing was constructed from the sum of analytic spanwise (Contract F33615-73-C-3127) integrals taken along lines of local sweep. The resuts obtained (AD -AOO23 19; MDC-J6063: AFFDL-TR-74-72( Avail: NTIS were tested against calculations by Freestone for points on the CSCLO1/1 wing planform for both sheared and tapered wings. Further A theoretical method has been developed to determine the comparisons for points on the wing surface were made with aerodynamic characteristics of ejector-jet-flapped wings in results by the method of A. M. 0. Smith. Author (ESRO) incompressible flow. The ejector-jet-flap is a high-lift concept conceived as a means of generating lift by using the jet-flap principle. The ejector, which consists of a primary jet directed N75-20263// City Univ., London (England). in the gap formed by the upper and lower sections of the flap, SOME REMARKS ON THE INDUCED VELOCITY FIELD OF provides, as the result of the entrainment of a secondary fluid, A LIFTING ROTOR AND ON GLAUERT'S FORMULA a trailing edge jet momentum normally in excess of that of the A. R. S. Bramwell London Aeron. Res. Council 1974 35 p primary jet. In the present method the ejector system inside the refs Supersedes ARC-34822 flap is considered as an internal mechanism and the total HC $3.75; (ARC-CP-1301; ARC-34822) Avail: NTIS momentum at the trailing edge is considered as a single thin HMSO 65p; PHI $2.75 jet of known momentum flux. Thus, the external aerodynamics The induced velocity field of a lifting rotor is discussed in of the ejector-jet-flap wing is similar to that of a wing with a relation to the pressure field rather than the vortex wake in an jet-augmented flap with a suction or sink effect in the region of attempt to obtain a clearer understanding of the relationship the flap hinge. GRA between the induced velocity and rotor forces. A number of results are derived and, where appropriate, are compared with N75-20272# Virginia Polytechnic Inst. and State Univ., those obtained from the theory of the vortex wake. An investigation Blacksburg. Dept. of Aerospace and Ocean Engineering. into the validity of Glauert's formula indicates that it appears to WIND TUNNEL STUDIES OF THE TURBJLENT WAKE be true for all rotor loadings for the linearized, high speed. case. BEHIND SELF PROPELLED SLENDER BODIES Final Calculations of the induced power show that for typic-al rotor Report loadings the power in hovering flight is about 10 per cent J. A. Schetz and A. K. Jakubowski Jun. 1974 18 p refs greater than the ideal induced power, rising to about 15 to (Contract N00014-72-A-0136-0004) 20 per cent greater in forward (light. Author (ESRO( (AD-A002396; VPI-AERO-014( Avail: NTIS CSCL 20/4 This report presents a summary of the data obtained for N75-20264# Imperial Coll. of Science and Technology, London self-propelled. slender (10 x 1) bodies in a six-foot square, low (England). Dept. of Aeronautics. turbulence wind tunnel. One model was propelled by axial air THE PREDICTION OF TURBULENT HEAT TRANSFER TO injection through a peripheral slot, and the other was propelled WEDGE COMPRESSION CORNERS AND CYLINDER-FLARE by a three-bladed, high pitch propeller. The tests were conducted BODIES AT HYPERSONIC SPEEDS at (Re sub Dl equals approximately 600.000. Data for the mean Cohn Osborne Mar. 1973 38 p refs flow, turbulence intensities and Reynolds stresses were obtained (Contract AT/2037 /057) at five axial stations in the range greater than 2 and less than (lC-Aero-73-03) Avail: NTIS NC $3.75 40. GRA A number of calculation methods were used to predict the heat transfer from hypersonic turbulent boundary layers on wedge N75-20273# National Aviation Facilities Experimental Center, compression corners and cylinder flare bodies. Only attached Atlantic City, N.J. flows were considered. The results were compared with recent data of Coleman and Stollery (1972) and Coleman (1973). The DEVELOPMENT OF A SCIENTIFIC BASIS FOR ANALYSIS prediction methods giving the best agreement with the data are OF AIRCRAFT SEATING SYSTEMS Final Report, Aug. the Gibson and Spalding (1971) method and the simplified Walker 1972 - Apr. 1974 refs method. Author (ESRO) David H. Leananen Jan. 1975 216 p (Contract DOT-FA72WA-3101) (AD-AO04306; FAA-NA-74-175; FAA-RD-74-130) Avail; N75-20267# European Space Research Organization. Paris NTIS HC $7.50 CSCLO1/3 A three-dimensional mathematical model of an aircraft seat, (France). ON THE INSTABILITY OF A SOUND-INFLUENCED FREE occupant. and restraint system has been developed as an aid to JET the development of crashworthy seats and restraint systems for general aviation aircraft. The occupant model consists of eleven Eberhard Pfizenmaier Jan. 1975 157 refs Transi. into p rigid mass segments whose dimensions and inertial properties ENGLISH of "Zur lnstabilitaet des Schallbeeinflussten Freistrahls', have been determined from studies of human body anthropometry DFVLR, Berlin Report DLR-FB-73-69. 14 May 1973 Original and kinematics. The seat model is made up of beam and membrane German report available from DFVLR. Porz, West Ger. 48. elements with provision for simulating plastic behavior by the 10 DM introduction of plastic hinges in the beams. A user-oriented (ESRO-TT-122; DLR-FB-73-69) Avail: NTIS HC $6.25 computer program called Seat Occupant Model-Light Aircraft The reaction of an axisymmetric free jet to disturbances (SOM-LA) based on the three-dimensional model has been excited by a sound field was investigated. The exciting sound developed for use by engineers concerned with design and analysis field was used as a diagnostic tool in order to synchronize of general aviation seats and restraint systems in that detailed disturbances in the free jet to a single Strouhal number. If the descriptions of both are used as input. The response of the seat Strouhal number is small, disturbances are amplified exponentially. and occupant, restraint system loads, and various injury criteria If the Strouhal number is high, the experiments no longer reveal Author exponential amplification, but standing wave patterns and even are predicted for any given set of crash conditions. damped amplitudes. In this case agreement between stability theory and experimental results fails. The structure of the N75.20274# National Transportation Safety Board, Washington, disturbances found experimentally can be interpreted as a D.C. Bureau of Aviation Safety.

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AIRCRAFT ACCIDENT REPORT. EASTERN AIR LINES, INC. operating but apparently was not used by the crew to monitor MCDONNELL-DOUGLAS DC 9-31, N8967E AKRON- the approach. GRA CONTON REGIONAL AIRPORT, NORTH CANTON, OHIO, 27 NOV. 1973 N75-20278// National Transportation Safety Board. Washington, 5 Nov. 1974 54 p D.C. (PB-238637/3; NTSB-AAR-74-12; File-1-0029) Avail: NTIS DELTA AIR LINES INCORPORATED MCDONNELL DOUG- HC$4.25 CSCL01B LAS DC-9-32, N3323L, CHATTANOOGA MUNICIPAL An Eastern Air Lines McDonnell-Douglas DC-931 crashed AIRPORT, CHATTANOOGA, TENNESSEE Aircraft Accident at Akron-Canton Regional Airport, North Canton. Ohio. on Report November 27, 1973. at 2129 e.s.t. The aircraft ran off the end 27 Nov. 1974 45 p of runway 01 after completing a precision approach and (PB-238479/0: NTSB-AAR-74-13) Avail: NTIS HC$3.75 CSCL landing, traversed 110 feet of unpaved ground, and plunged 01B over a 38-foot embankment. The aircraft was damaged About 1851 e.s.t. on November 27, 1973, Delta Air Lines substantially by the impact, but there was no fire. The 21 Flight 516, a McDonnell Douglas DC-9-32. N3323L, crashed passengers and 5 crewmembers sustained various injuries. The while making an ILS approach to runway 20 at Chattanooga National Transportation Safety Board determines that the probable Municipal Airport, Chattanooga, Tennessee. Seventy-four cause of the accident was the captain's decision to complete passengers and five crewmembers were aboard the aircraft. the lending at an excessive airspeed and at a distance too far Thirty-eight passengers and four crewmembers were injured: there down a wet runway to permit the safe stopping of the aircraft. were no fatalities. The aircraft was destroyed. The National Factors which contributed to the accident were: (1) lack of airspeed Transportation Safety Board determines the probable cause of awareness during the final portion of the approach, (2) an the accident was that the pilot did not recognize the need to erroneous indication of the speed command indicator, and (3) correct an excessive rate of descent after the aircraft had passed hydroplaning. GRA decision height. GRA

N75-20276# National Transportation Safety Board, Washington, N75-20286# Pan American World Airways, Inc., New York, D. C. Bureau of Aviation Safety. OCEANIC AIR ROUTE NAVIGATION WITH ENVELOPE SPECIAL STUDY: SAFETY ASPECTS OF EMERGENCY MATCH LORAN-C Final Report, Dec. 1974 EVACUATIONS FROM AIR CARRIER AIRCRAFT Patrick A. J. Reynolds Dec. 1974 117 p 13 Nov. 1974 45 p (Contract DOT-FA74WA-3388) (PB-238269/5: NTSB-AAS-74-3) Avail: NTIS HC$3.75 CSCL (AD-A003800: FAA-AD-74-205) Avail: NTIS HC $5.75 CSCL 018 17/7 Recent U.S. air carrier accidents in which an emergency A Loran-C envelope matching receiver (Edo Model 800T) evaculation occurred are examined. These accidents exemplify was evaluated as a potential replacement for Loran-A. The unit the factors most commonly identified as influencing evacuation was installed on a Boeing 707 aircraft and data were collected success. The factors identified and discussed include the following: primarily on North Atlantic routes. Results of this program weather, terrain, aircraft attitude, fire and smoke, evacuation slides, indicate that where Loran-C coverage exists in adequate availability emergency lighting, emergency communications equipment, and geometry it may be considered a conditionally acceptable obstructions to egress, passenger preparedness, crewmember substitute for Loran-A as a pilot-operated updating reference for training, and crewmember procedures. Safety recommendations Doppler navigation systems on oceanic air routes. Author regarding improvements in evacuation slides, megaphones, public address systems, passenger briefings, emergency lighting, and crewmember training are included. GRA N75-20289 + Engineering Sciences Data Unit. London (England). NON-DIMENSIONAL METHODS FOR THE MEASUREMENT N75-20276# National Transportation Safety Board, Washington, OF LEVEL FLIGHT PERFORMANCE OF TURBINE ENGINED D. C. Bureau of Aviation Safety. HELICOPTERS ANNUAL REVIEWS OF AIRCRAFT ACCIDENT DATA US Nov. 1974 22 p Sponsored by Roy. Aeron. Soc. AIR CARRIER OPERATIONS, 1973 (ESDU-74042) Avail: NTIS HC $74.50 24 Oct. 1974 93 p Methods are described for measuring and presenting the (P8-238281/0: NTSB-ARC-74-2) Avail: NTIS HC $4.75 CSCL steady level-flight performance of turbine-engined helicopters in 018 terms of nondimensional parameters. The three test methods The record of aviation accidents which occurred in all described are distinguished by the atmospheric parameters operations of the U.S. Air Carriers for calendar year 1973 is used: density alone, density and temperature, and pressure and temperature. presented. It includes an analysis by classes of carriers, causes F.O.S. and related factors, types of accidents, and phases of operation. Statistical tables which summarize the accidents, fatalities, and N75-20290*# Scientific Translation Service, Santa Barbara, Calif. accident rates along with causal tables and the briefs of accidents LIFTING SURFACE FOR AIRCRAFT are presented in the appendices. GRA Charles Fauvel and Henri Coltel Washington NASA Apr. 1975 22 p Transl. into ENGLISH from German patent no. 677527. N75-20277# National Transportation Safety Board, Washington, class 62b. group 4 os. examiner's copy. div. 22. F79596 XI/62b, D. C. 29 Jun. 1935 PAN AMERICAN WORLD AIRWAYS, INCORPORATED (Contract NA5w-2483( BOEING 707-3218. N454PA, PAGO PAGO. AMERICAN (NASA-TT-F-16241) Avail: NTIS HC $3.25 CSCL 01C SAMOA, 30 JANUARY 1974 Aircraft Accident Report A pre-World War 2 German patent is described for an airplane 8 Nov. 1974 32 p wing whose profile is automatically changed as a function of (PB-238478/2: NTSB-AAR-74-15) Avail: NTIS HC$3.75 CSCL the flight parameters (velocity, angle of attack, etc.) in such a 01B manner that the center of pressure always remains approximately About 2341, American Samoa standard time, on January 30, at the same place. The patent includes an automatic steering 1974, Pan American World Airways, Flight 806. crashed 3.865 device for aircraft. Conventional and wing-only aircraft are feet short of runway 5 at Pago Pago International Airport. The considered. Author flight was making an ILS approach at night. Of the 101 persons aboard the aircraft, only 5 survived the accident. One survivor N75-20291 // Lockheed Aircraft Corp.. Sunnyvale, Calif. died of injuries 9 days after the accident. The aircraft was destroyed EVALUATION OF ADVANCED LIFT CONCEPTS AND FUEL by Impact and fire. The National Transportation Safety Board CONSERVATIVE SHORT-HAUL AIRCRAFT, VOLUME 1 Final Report determines that the probable cause of the accident was the failure of the pilot to correct an excessive rate of descent after J. H. Renshaw, M. K. Bowden, C. W. Narucki. J. A. Bennett, P. the aircraft had passed decision height. VASI was available and R. Smith, R. S. Ferrill, C. C. Randall, J. G. Tibbetts, A. W.

281 N75-20292

Patterson, A. T. Meyer et al Jun. 1974 312 p refs 2 Vol. (Contract DOT-FA72WA-3 134) (contract NAS2-6995) (AD-A003799; FAA-AD-74-194) Avail: NTIS HC $4.75 CSCL (NASA-CR-137525) Avail: NTIS HC $9.25 CSCL 01 01/3 The performance and economics of a twin-engine augmentor A liquid nitrogen fuel tank inerting system has been certifi- wing airplane were evaluated in two phases. Design aspects of cated and is in operation in a DC-9 jet transport. This system the over-the-wing/internally blown flap hybrid, augrnentor wing, reduces the fuel tank ullage space and vent system oxygen and mechanical flap aircraft were investigated for 910 m. field concentration to a non-combustible level by dilution with nitrogen length with parametric extension to other field lengths. Fuel which is stored aboard the airplane in a liquid state. The objective savings achievable by application of advanced lift concepts to of this contractual effort was to investigate whether the new short-haul aircraft were evaluated and the effect of different concept of on-board nitrogen generation by separating nitrogen field lengths, cruise requirements, and noise levels on fuel from engine bleed air using ultrathin semi-permeable membranes consumption and airplane economics at higher fuel prices were will eliminate the requirement to carry liquid nitrogen in the determined. Conclusions and recommendations are presented. airplane and thus reduce the logistics requirements of nitrogen Author inerting systems. The function of the inerting system is to reduce the oxygen concentration in the fuel tank vapor spaces and vent lines to a level below which combustion and thus explosion N75,20292*# Lockheed Aircraft Corp.. Sunnyvale. Calif. cannot occur, regardless of the presence of an ignition source. EVALUATION OF ADVANCED LIFT CONCEPTS AND FUEL This is accomplished by replacing the oxygen' in the tank ullage CONSERVATIVE SHORT-HAUL AIRCRAFT, VOLUME 2 Final and vent system with nitrogen so that the oxygen concentration Report will always be nine percent or less by volume under all flight J. H. Renshaw, M K. Bowden, C. W. Narucki, J. A. Bennett, P. and ground conditions. Author A. Smith, A. S. Ferrill, C. C. Randall, J. G. Tibbetts, R. W. Patterson, R. T. Meyer et al Jun. 1974 367 p refs 2 Vol. N75-20296# Tennessee Univ. Space Inst., Tullahoma. (Contract NAS2-6995) AIR CUSHION LANDING SYSTEMS FOR AIRCRAFT (NASA-CR-137526l Avail: NTIS HC $10.00 CSCL 01C B. H. Goethert [1974] 29 p refs For abstract, see N75-20291. Avail: NTIS HC $3.75 A brief summary of the current state-of-the-art of air cushion N75.20293*# National Aeronautics and Space Administration. landing systems for aircraft is presented. Aircraft equipped with Flight Research Center, Edwards. Calif. such novel landing systems have the unique capability of operating DEVELOPMENT OF A REMOTE DIGITAL AUGMENTATION on a variety of prepared and unprepared surfaces, such as hard SYSTEM AND APPLICATION TO A REMOTELY PILOTED runways, water, swamps, slush and loose snow without RESEARCH VEHICLE necessitating any changes of the landing system. Detailed John W. Edwards and Dwain A. Deets Washington Apr. 1975 descriptions of the special technical features are given, such as 54 p refs the design of the inflatable trunks, the flexible material with (NASA-TN-D-7941; H-854) Avail: NTIS HC $4.25 CSCL differential-directional stiffness, auxiliary cushion air compressor 01C system, control system for ground operation. etc. The feasibility A cost-effective approach to flight testing advanced control of this system was demonstrated in extensive tests with a concepts with remotely piloted vehicles is described. The approach single-engine LA-4 aircraft. The success of these demonstration utilizes a ground based digital computer coupled to the remotely tests resulted in installing an air cushion landing system in an piloted vehicle's motion sensors and control surface actuators operational two-engine aircraft in the 50.000 pound class. through telemetry links to provide high bandwidth feedback Author control. The system was applied to the control of an unmanned 3/8-scale model of the F-15 airplane. The model was remotely N75-20297# Royal Aircraft Establishment. Farnborough augmented; that is, the F- i 5 mechanical and control augmentation (England). Structures Dept. flight control systems were simulated by the ground-based THE VARIABILITY OF FATIGUE DAMAGE FROM FLIGHT computer, rather than being in the vehicle itself. The results of TO FLIGHT flight tests of the model at high angles of attack are discussed. N. I. Bullen London Aeron. Res. Council 1974 28 p refs Author Supersedes RAE-TR-73046; ARC-34723 (ARC-CP-1297; RAE-TA-73046; ARC-34723l Avail: NTIS N75.20294*# National Aeronautics and Space Administration. HC $3.75; HMSO 55p; PHI $2.35 Langley Research Center. Langley Station, Va. The variability of fatigue damage from flight to flight is WIND TUNNEL INVESTIGATION OF HELICOPTER ROTOR examined for a fleet of aircraft, both within aircraft and between WAKE EFFECTS ON THREE HELICOPTER FUSELAGE aircraft. A method is described of modifying the standard analysis MODELS of variance technique to take account of correlation between John C. Wilson and Raymond E. Mineck [1974] 140 p Prepared consecutive flights and an example is given. It is then shown in cooperation with Army Air Mobility A and D Lab., Hampton, how to use the estimates of variance so obtained in the derivation Va. of factors for damage prediction, both on a short term basis for (NASA-TM-X-3185-Suppl) Avail: NTIS HC $5.75 CSCL O1C a few unmetered flights and also for complete life estimation. The effects of rotor downwash on helicopter fuselage Author (ESRO) aerodynamic characteristics were investigated. A rotor model for generating the downwash was mounted close to each of three N75-20298# Royal Aircraft Establishment. Bedford (England). fuselage models. The main report presents the force and moment Aerodynamics Dept. data in both graphical and tabular form and the pressure data FLIGHT SIMULATION OF A WESSEX HELICOPTER: A in graphical form. This supplement presents the pressure data VALIDATION EXERCISE in tabular form. Each run or parameter sweep is identified by a T. Wilcock and Ann C. Thorpe London Aeron. Res. Council unique run number. The data points in each run are identified 1974 61 p refs Supersedes RAE-TR-73096; ARC-35005 by a point number. The pressure data can be matched to the (ARC-CP-1299; RAE-TA-73096; ARC-35005) Avail: NTIS force data by matching the run and point number. Author HC $4.25; HMSO £1; PHI $3.90 A piloted flight simulation of the Westland Wessex helicopter N75-20295# General Electric Co.. Lynn, Mass. Aircraft which was intended to investigate the validity of simulation for Equipment Div. the representation of flight handling behavior is described. Two FEASIBILITY OF ADAPTING A THIN FILM PERMEABLE areas were of concern: the representation of the Wessex within MEMBRANE TO JET TRANSPORT FUEL TANK INERTING a limited computational capacity, and the suitable simulation of SYSTEM Final Report the flying environment so that handling characteristics were Warella Browall, John W. Harrison. and Robert M. Salemme presented correctly to the pilots. By limiting the scope of the Jan. 1975 76 D simulation to the normal flying regime of the helicopter, an

282 N75-20306 adequate representation of the Wessex was possible. Presentation programs operating within 100.000 octal units were also of handling behavior was satisfactory in pitch and roll: some developed to provide optional data sources for SWEEP. These difficulties were experienced in the representation of yawing include the flexible airloads program to assess the effects of behavior and of height control near the hover, and were attributed flexibility on lifting surface airloads, and the flutter optimization to inadequate motion capability of the simulator. The results of program to optimize the stiffness distribution required for lifting this simulation were used to give confidence in the interpretation surface flutter prevention. This volume. Volume I, summarizes of future helicopter simulation. Author (ESRO) the program and its capabilities. GRA

N75-20299# Battelle Columbus Labs.. Ohio. N76-20302# Rockwell International Corp.. Los Angeles, Calif. FATIGUE-CRACK GROWTH BEHAVIOR OF C-5A WING Aircraft Div. CONTROL POINTS Interim Report, 20 Oct. 1972 - 20 Oct. A STRUCTURAL WEIGHT ESTIMATION PROGRAM 1973 (SWEEP) FOR AIRCRAFT. VOLUME 2: PROGRAM Samuel H. Smith May 1974 52 p refs INTEGRATION AND DATA MANAGEMENT MODULE. (Contract F33657-73-C-0281) PART 1: PROGRAM INTEGRATION (AD-A002553: ASD-TR-74-18) Avail: NTIS CSCL 01/3 G. Hayase, A. Hiyama. C. Martindale. and H. Rockwell Jun. .An extensive fatigue-crack-growth analysis was conducted 1974 224 p to evaluate the flight-by-flight crack-growth behavior of the C-5A (Contract F33615-71-C-1922) wing structure control points. Fourteen missions of flight stress (AD-A002852; ASD/)(R-74 . 10-VoI.2-Pt-1) Avail: NTIS CSCL spectra and several mission mixes were considered in the analysis. 01/3 Both linear and retarded (nonlinear) concepts of fatigue-crack The methodology, program description, and users informa- growth were analyzed with the AFFDL CRACKS II computer tion for the SWEEP control program are presented along with program with the Willenborg effective stress retardation model. the input data processing module, final output module, and the The model was found to adequately predict laboratory flight-by- data management module. GRA flight test data. Fatigue-crack-growth behavior was found to be sensitive to stress increments as derived from a Constant N75-20303# Rockwell International Corp., Los Angeles, Calif. exceedance curve, mission severity, and stress sequence. The Aircraft Div. results of the flight-by-flight analysis for each of the wing structure A STRUCUTRAL WEIGHT ESTIMATION PROGRAM control points defined the most critical locations for inspection (SWEEP) FOR AIRCRAFT. VOLUME 2: PROGRAM purposes. In addition, fatigue-crack behavior was found to be INTEGRATION AND DATA MANAGEMENT MODULE. very sensitive to mission stress spectra and mission mix. GRA PART 2: DATA MANAGEMENT MODULE G. Hayase, A. Hiyama, C. Martindále, and H. Rockwell Jun. N75-20300# Army Materials and Mechanics Research Center, 1974 285 p Watertown, Mass. (Contract F33815-71-C-1922) DEVELOPMENT OF SCRATCH AND SPALL RESISTANT (AD-A002853; ASD/XR-74'10-VoI-2 . Pt.2) Avail: NTIS CSCL WINDSHIELDS Final Report 01/3 John R. Plumer Aug. 1974 22 p refs Presented at Proc. of Conf. on Transparent Aircraft Enclosures. Las Vegas, Nev.. 5-8 Feb. 1973 N75-20304# Rockwell International Corp.. Los Angeles, Calif. (DA Proj. 1728005) Aircraft Div. (AD-AO02513; AMMRC-TR-74-19) Avail: NTIS CSCL 01/3 A STRUCTURAL WEIGHT ESTIMATION PROGRAM Studies were performed to evaluate possible ways of (SWEEP) FOR AtRCRAFT, VOLUME 2: PROGRAM improving the primary weaknesses in existing Army helicopter INTEGRATION AND DATA MANAGEMENT MODULE, windshields, namely, scratching and spalling. Three experimental APPENDIX A: DATA MANAGEMENT MODULE FLOW windshield material configurations offering a potential solution CHARTS AND FORTRAN LISTS were fabricated for test and evaluation. The spall problem was G. Heysse, R. Hlyama, C. Martindale, and H. Rockwell Jun. approached by using polycarboriate as a backup material and 1974 330 p refs was incorporated into each design. The scratch problem was (Contract F33815-71-C-1922) approached by employing either (i) a hard surface coating. (2) (AD-A00285 1; ASD/XR-74- 1 OVoI-2-App-A) Avail: NTIS CSCL an acrylic cladding, or (3) a thin glass cladding to the polycarbonate 01/3 backup material. Commercially available materials and abrasion- resistant coatings were evaluated utilizing a windshield wiper apparatus, while spall performance was studied by ballistic testing N71-20305# Rockwell International Corp., Los Angeles, Calif. and high-speed photography of each of three test configura- Aircraft Dlv, tions. GRA A STRUCTURAL WEIGHT ESTIMATION PROGRAM (SWEEP) FOR AIRCRAFT. VOLUME 3: AIRLOADS N75-20301# Rockwell International Corp.. Los Angeles. Calif. ESTIMATION MODULE Aircraft Div. P. Wildermuth, G. Rothammar, and P. Hiyema Jun. 1974 A STRUCTURAL WEIGHT ESTIMATION PROGRAM 279 p refs (SWEEP) FOR AIRCRAFT. VOLUME 1: EXECUTIVE (Contract F33615-71-C-1922) SUMMARY (AD-A002854; ASD/)(R-74- 1 O-Vol-3) Avail: NTIS CSCL L. Ascani Jun. 1974 36 p refs 01/3 (Contract F33615-71-C-1922) The methodology, program description, and user's informa- (AD-A002850; ASD /)(R-74- 10-Vol-i) Avail: NTIS CSCL tion for the airload module of SWEEP are presented. 01/3 G PA Three computer programs were written with the objective of predicting the structural weight of aircraft through analytical methods. The first program, the structural weight estimation N75-20305# Rockwell International Corp.. Los Angeles, Calif. program (SWEEP), is a completely integrated program including Aircraft Div. routines for airloads, loads, spectra, skin temperatures, material A STRUCTURAL WEIGHT ESTIMATION PROGRAM properties, flutter stiffness requirements, fatigue life, structural (SWEEP) FOR AIRCRAFT. VOLUME 3: AIRLOADS sizing, and for weight estimation of each of the major aircraft ESTIMATION MODULE. APPENDIX A: MODULE FLOW structural components. The program produces first-order weight CHARTS AND FORTRAN LISTS. APPENDIX B: SAMPLE estimates and indicates trends when parameters are varied. OUTPUT Fighters, bombers, and cargo aircraft can be analyzed by the P. Wildermuth, G. Rothammer, and A. Hlyama Jun. 1974 program. The program operates within 100,000 octal units on 190 the Control Data Corporation 6600 computer. Two stand-alone (Contract F33815-71-C-1922)

283 N75-20307

(AD-A002855; ASD(R-74-10-Vol-3-App-A/8) Avail: NTIS A STRUCTURAL WEIGHT ESTIMATION PROGRAM CSCL 01/3 (SWEEP) FOR AIRCRAFT. VOLUME 8: WING AND EMPENNAGE MODULE. BOOK 3: TECHNICAL DISCUS- SION, SECTION 6 N75-20307# Rockwell International Corp.. Los Angeles. Calif. G. Hayase Jun. 1974 357 p refs Aircraft Div. (Contract F33615-71-C-1922) A STRUCTURAL WEIGHT ESTIMATION PROGRAM (AD-A002866: ASD/)(R-74-10-Vol-6-Bk-3( Avail: NTIS CSCL (SWEEP) FOR AIRCRAFT. VOLUME 4: MATERIAL 01/3 PROPERTIES, STRUCTURE TEMPERATURE, FLUTTER AND FATIGUE H. Haroldson, C. Hodson, S. Mellin. H. Rockwell, and S. Tejani N75-20313// Rockwell International Corp., Los Angeles, Calif. Jun. 1974 408 p refs Aircraft Div. (Contract F3361 5-71-C-1 A STRUCTURAL WEIGHT ESTIMATION PROGRAM (AD-A002856: ASD(R-74-10-Vol-4) Avail: NTIS CSCL (SWEEP) FOR AIRCRAFT. VOLUME 6: WING AND 01/3 EMPENNAGE MODULE. APPENDIX A: GENERAL The methodology, program description, and user's information INFORMATION FOR MODULE FLOW CHARTS AND are presented for the use of material properties, flutter and LISTINGS. APPENDIX B: PROGRAM FLOW CHARTS, temperature module, and fatigue module of SWEEP. OVERLAYS (8.0). (14,0). (15.0). (16.0) AND (11,0) G RA G. Hayase Jun. 1974 472 p (Contract F33615-71-C1922) N75-20308# Rockwell International Corp., Los Angeles, Calif. (AD-A002859: ASDJ)(R-74- 1 O-Vol-6-App-A /B) Avail: NTIS Aircraft Div. CSCL 01/3 A STRUCTURAL WEIGHT ESTIMATION PROGRAM (SWEEP) FOR AIRCRAFT. VOLUME 5: AIR INDUCTION SYSTEM AND LANDING GEAR MODULES. PART 1: AIR N75-20314# Rockwell International Corp., Los Angeles, Calif. INDUCTION SYSTEM MODULE Aircraft Div. D. Chaloff, R. Hiyama, and C. Martindale Jun. 1974 472 p A STRUCTURAL WEIGHT ESTIMATION PROGRAM refs (SWEEP) FOR AIRCRAFT. VOLUME 6: WING AND (Contract F33615-71-C-1922) EMPENNAGE MODULE. APPENDIX C: PROGRAM FLOW (AD-A002857; ASD,5(R-74-10-V6l-5-Pt-1) Avail: NTIS CSCL CHARTS. OVERLAYS (9,0) AND (10,0) 01/3 G. Hayase Jun. 1974 340 p refs The methodology, program description, and user's informa- (Contract F33615-71-C-1922) tion are presented for the air induction system and landing gear (AD-A002860; ASD/(R-74-10-VoI-6-App-C( Avail: NTIS CSCL modules of SWEEP. GRA 01/3 N76-20309# Rockwell International Corp., Los Angeles, Calif. Aircraft Div. N75.20315# Rockwell International Corp., Los Angeles, Calif. A STRUCTURAL WEIGHT ESTIMATION PROGRAM Aircraft Div. (SWEEP) FOR AIRCRAFT. VOLUME 6: AIR INDUCTION A STRUCTURAL WEIGHT ESTIMATION PROGRAM SYSTEM AND LANDING GEAR MODULES. PART 2: (SWEEP) FOR AIRCRAFT. VOLUME 6: WING AND LANDING GEAR MODULE EMPENNAGE MODULE. APPENDIX D: PROGRAM FLOW D. Chaloff. P. Hlyama, and C. Martindale Jun. 1974 180 p CHARTS, OVERLAY (18.0) refs G. Hayase Jun. 1974 243 p (Contract F33615-71-C-1922) (Contract F33615-71-C-1922) (AD-A002858; ASDmR-74-10-Vol-5-Pt-2) Avail: NTIS CSCL (A0-A00286 1: ASD /XR-74- 1 0-VoI-6-App-D) Avail: NTIS CSCL 01/3 01/3

N76-20310# Rockwell International Corp., Los Angeles, Calif. Aircraft Div. N75-20316# Rockwell International Corp.. Los Angeles, Calif. A STRUCTURAL WEIGHT ESTIMATION PROGRAM Aircraft Div. (SWEEP) FOR AIRCRAFT. VOLUME 8: WINO AND A STRUCTURAL WEIGHT ESTIMATION PROGRAM EMPENNAGE MODULE. BOOK 1: TECHNICAL DISCUS- (SWEEP) FOR AIRCRAFT. VOLUMES: WING AND SION SECTIONS 1 AND 2 EMPENNAGE MODULE. APPENDIX E: PROGRAM G. Hayase Jun, 1974 382 p LISTINGS, OVERLAYS (8.0), (14.0). (15.0). (16.0). AND (Contract F33815-71-C-1922) (17.0) (AD-A002864; ASDmR-74-10-Vol-6-Bk-1) Avail: NIS CSCL G. Hayase Jun. 1974 239 p 01/3 (Contract F33615-71-C-1922) The methods and program description for the wing and (AD-A002862: ASDR-74-10-VoI-6-App-E) Avail: NTIS CSCI empennage module of SWEEP are presented. Pro g ram listings 01/3 and flow charts are Included In the appendix. G PA N76-20317# Rockwell International Corp.. Los Angeles, Calif. N75.20311# Rockwell International Corp., Los Angeles, Calif. Aircraft Div. Aircraft Dlv, A STRUCTURAL WEIGHT ESTIMATION PROGRAM A STRUCTURAL WEIGHT ESTIMATION PROGRAM (SWEEP) FOR AIRCRAFT. VOLUME 6: WING AND (SWEEP) FOR AIRCRAFT. VOLUME 8: WING AND EMPENNAGE MODULE. APPENDIX F: PROGRAM EMPENNAGE MODULE. BOOK 2: TECHNICAL DISCUS- SION, SECTIONS 3 AND 4 LISTINGS, OVERLAYS (9,0), (10,0) AND (18,0) G. Hayase Jun. 1974 353 p G. Hayaee Jun. 1974 261 p (Contract F33615-71-C-1922) (Contract F33615-71-C-1922) (AD-A002863; ASD(R-74-10-Vol-6-App-F) Avail: NTIS CSCL (AD-A002$65; ASD/XR-74-10-Vol . 8-8k-2) Avail: NTIS CSCL 01/3 01/3

N75-20312# Rockwell International Corp., Los Angeles, Calif. N75-20318# Rockwell International Corp., Los Angeles, Calif. Aircraft Dlv, Aircraft Div.

284 N75-20330

A STRUCTURAL WEIGHT ESTIMATION PROGRAM N75-20324# Rockwell International Corp.. Los Angeles, Calif. (SWEEP) FOR AIRCRAFT. VOLUME 7: FUSELAGE Aircraft Div. MODULE A STRUCTURAL WEIGHT ESTIMATION PROGRAM R. Hiyama Jun. 1974 439 p refs (SWEEP) FOR AIRCRAFT. VOLUME 11: FLEXIBLE (Contract F33615-71-C-1922) AIRLOADS STAND .ALON€ PROGRAM (AD-A002867: ASD (R-74-1 0-Vol-i) Avail: NTIS CSCL P. Wildermuth, G. Rothammer. and T. Byer Jun. 1974 274 p 01/3 refs The methodology, program description, and user's information (Contract F33615-71-C-1922) are presented for the fuselage module of SWEEP. (AD-A002873; ASDmR-74-1 0-Vol-i 1) Avail: NTIS CSCL G RA 01/3 The methodology, program description, and user's information N75-20319# Rockwell International Corp.. Los Angeles, Calif. are presented for the flexible loads stand-alone program of SWEEP. Aircraft Div. GRA A STRUCTURAL WEIGHT ESTIMATION PROGRAM (SWEEP) FOR AIRCRAFT. VOLUME 7: FUSELAGE N75-20325# Army Aviation Systems Command, St. Louis. Mo. MODULE. APPENDIX A: MODULE FLOW CHARTS AND MAJOR ITEM SPECIAL STUDY (MISS). UH-1 H TAIL ROTOR FORTRAN LISTS. APPENDIX B: FUSELAGE MODULE HANGERS Interim Technical Report, Jan. 1964 - Dec. SAMPLE OUTPUT 1973 R. Hiyama 'Jun. 1975 450 p Dec. 1974 24 p (Contract F33615-71-C-1922) (AD-A003263; USAAVSCOM-TR-74-52) Avail: NTIS CSCL (AD -A002868; ASD fl(R-74- 10-Vol-i-App-A/B) Avail: NTIS 01/3 CSCL 01/3 Major Item Special Study (MISS) reports are performed on DA Form 2410 reportable components. These are time change items and certain condition change items selected because of N75-20320# Rockwell International Corp., Los Angeles, Calif. high cost or need for intensive management. Basically, the Aircraft Div. MISS reports are concerned with analyzing reported removal A STRUCTURAL WEIGHT ESTIMATION PROGRAM data presented in the Major Item Removal Frequency (MIRF) (SWEEP) FOR AIRCRAFT. VOLUMES: PROGRAMMER'S report. The failure modes reported for each removal are examined MANUAL and grouped into categories which are intended to clarify the C. Martindale, H. Rockwell, G. Hayase. and R. Hiyama Jun. intent of the data reporting. From this data, removal distribution 1974 81 p can be plotted and an MTR (mean time to removal( can be (Contract F33615-71-C-1922( calculated. The MISS reports then investigate possible cost (AD-A002869: ASD/XR-74-10-Vol-8( Avail: NTIS CSCL savings based on total elimination of selected failure modes. 01/3 These modes are chosen because of the percentage of failures The program structure and operation of SWEEP is described. they represent and/or because they appear to be feasible Product Information is given for modifying and debugging the program. Improvement Program (PIP) areas. GRA GRA N75-20329 National Aeronautics and Space Administration. Flight Research Center, Edwards, Calif. N75-20321# Rockwell International Corp.. Los Angeles, Calif. Aircraft Div. EXPLORATORY WIND TUNNEL TESTS OF A SHOCK- A STRUCTURAL WEIGHT ESTIMATION PROGRAM SWALLOWING AIR DATA SENSOR AT A MACH NUMBER (SWEEP) FOR AIRCRAFT. VOLUME 9: USER'S MANUAL OF APPROXIMATELY 1.83 R. AlIen, D. Chaloff, G. Hayase, A. Hiyama. and C. Martindale Jack Nugent, Lana M. Couch, and Lannie D. Webb Mar. 1975 42 p refs Jun. 1974 373 p refs (Contract F33615-71-C-1922) (NASA-TM-X-56030( Avail: NTIS HC $3.75 CSCL 010 (A0-A002870; ASD/)(R-74-10-Vol-9) Avail: NTIS CSCL The test probe was designed to measure free-stream Mach number and could be incorporated into a conventional airspeed 01/3 The instructions and input descriptions are presented for nose boom installation. Tests were conducted in the Langley the integrated SWEEP program. 4-by 4-foot supersonic pressure tunnel with an approximate angle 3RA of attack test range of -5 deg to 15 deg and an approximate angle of sideslip test range of + or - 4 deg. The probe incorporated a variable exit area which permitted internal flow. The internal 20322# Rockwell International Corp.. Los Angeles, Calif. N75. flow caused the bow shock to be swallowed. Mach number Aircraft Div. was determined with a small axially movable internal total pressure A STRUCTURAL WEIGHT ESTIMATION PROGRAM tube and a series of fixed internal Static pressure orifices. Mach (SWEEP) FOR AIRCRAFT. VOLUME 9: USER'S MANUAL number error was at a minimum when the total pressure tube APPENDIX A was close to the probe tip. For four of the five tips tested, the R. Allen, D. Chal6ff, G. Hayase. R. Hiyama. and C. Martindale Mach number error derived by averaging two static pressures Jun. 1974 299 p measured at horizontally opposed positions near the probe (Contract F33615-71-C-1922) entrance were least sensitive to angle of attack changes. The (AD-A002871: ASD/XR-74-10-Vol-9 .App-A) Avail: NTIS CSCL same orifices were also used to derive parameters that gave 01/3 indications of flow direction. Author

N75-20330// Air Force Flight Dynamics Lab., Wright-Patterson N75-20323# Rockwell International Corp.. Los Angeles, Calif. AFB, Ohio. Aircraft Div. C-141 ALL WEATHER LANDING SYSTEM (AWLS) FLIGHT A STRUCTURAL WEIGHT ESTIMATION PROGRAM TEST REPORT: OPTIMIZATION AND PRE-EXPERIMENTAL (SWEEP) FOR AIRCRAFT. VOLUME 10: FLUTTER PHASES Final Report, 1 Nov. 1972 - 19 Feb. 1974 OPTIMATION STAND-ALONE PROGRAM Robert J. Hovde Apr. 1974 142 p S. Siegel Jun. 1974 271 p (Contract DOT-FA70WAI-173) (Contract F33615-71-C-1922) (AD-A003952; AFFDL-TM-74-109-FG SA; FAA-RD-74-192) (AD -A002872: ASDp(R-74-1 0-Vol-i 0) Avail: NTIS CSCL Avail: NTIS HC $5.75 CSCL 01/4 01/3 A chronological description of C-141 aircraft flight tests and The methodology. program description, and user's information aircraft modification since Nov. 1. 1972, is given. The present are presented for the flutter optimization standalone program aircraft (NC-1414, 61-2775) and All Weather Landing System of SWEEP. GRA (AWLS) configurations are described along with the pilot

285 N15-2O331

procedures to be used initially in the Experimental Phase of the Dec1974 316 p - program. Individual mission reports are presented in Appen- (Contract F33615-71-C-1625; AF Proj. 3066) dix A. Diagrams of each baseline approach are presented in (AD-A002543; Rept-7-3-2 10173-Pt-i; Appendix 8. The primary conclusion is that the aircraft is ready AFAPL-TR-74-109-Pt-1) Avail: NTIS CSCL 21/5 for Category Ill Weather Flight Testing. Some discussion is Part I of this report documents the analysis, design, and rig presented on equipment specifications for CAT Ill landings. Two tests conducted in Phases 1 and 2. Part 2 reports the engine areas are identified that need further developmental work: (1) work and sea-level tests completed in Phase 3. Parts 3A and For short runway operations and stop and go operations, an 38 document the altitude tests conducted in Phase 4. This accurate Runway Distance Remaining Display is needed. (2) For program was conducted to determine the impact of variable zero visibility landings. the pilot requires some positive indication geometry compressor, turbine, and exhaust-nozzle components that the aircraft is almost stopped: otherwise the pilot tends to on turbofan engine performance. GRA stop too abruptly, causing the aircraft to lurch violently at the moment of final stopping. Author N75-20338// AiResearch Mfg. Co.. Phoenix, Ariz. IMPACT OF TURBINE MODULATION ON VARIABLE-CYCLE N75-20331# E-A Industrial Corp., Chamblee, Ga. ENGINE PERFORMANCE. PHASE 3: ENGINE MODIFICA- INSTRUMENT SYSTEM TEST. ELLIOTT HELICOPTER AIR TION AND SEA LEVEL TEST. PART 2 Final Technical DATA SYSTEM Final Report Report, May 1971 - 31 Dec. 1974 I. John Carter 30 Oct. 1974 30 p refs W. R. Davenport. G. J. Dixon. A. Fischer, K. R. Fledderjohn, J. (Contract N00014-73-C-0291; NR Proj. 213-114) R. Shearer, M. A. Steele, D. W. Stephenson. and F. Weber (AD-A002332; EA-01-0032-A-11) Avail: NTIS CSCL 01/3 Dec. 1974 245 p During 1973-1974, evaluation of a helicopter lift margin (Contract F33615-71-C-1625; AF Proj. 3066) system was conducted on a NUH-1M helicopter. In order to (AD-A002544; Rept-73-210173-Pt-2; AFAPL-TR-74-109-Pt-2) provide air data references to the pilot and for assessment of Avail: NTIS CSCL 21/5 the effects of airspeed and vertical speed variations on System An AiResearch Model TFE731-2 Turbofan Engine was accuracies an air data subsystem was supplied, consisting of a modified to incorporate production-type variable-geometry two- axis helicopter airspeed sensing equipment. Findings are hardware and tested to determine the effects of turbine modulation reported and discussed. GRA at both sea-level static and simulated high-altitude flight conditions at subsonic and supersonic flight Mach numbers. GRA N75-20332# Boeing Vertol Co.. Philadelphia, Pa. VISUAL AUGMENTATION SYSTEM WAS) LABORATORY DEMONSTRATION AND TEST RESULTS Technology N75-20339# AiResearch Mfg. Co.. Phoenix, Ariz. Development Report IMPACT OF TURBINE MODULATION ON VARIABLE-CYCLE L. F. Simpson Oct. 1974 36 p ENGINE PERFORMANCE. PHASE 4: ADDITIONAL (Contract DAAJ01-71-C-0840) HARDWARE DESIGN AND FABRICATION. ENGINE (AD-A003323; USAAMRDL-TR-74-68) Avail: NTIS CSCL MODIFICATION, AND ALTITUDE TEST, PART 3A Final 01/3 Technical Report, 17 May 1971 - 31 Dec. 1974 This document describes the laboratory demonstration of the W. A. Davenport, G. J. Dixon. A. Fischer. K. A. Fledderjohn, J. Visual Augmentation System (VAS) and components, later A. Shearer, M. A. Steele, D. W. Stephenson. and F. Weber installed in the Model 347 helicopter, and the results of tests Dec. 1974 306 p of operational parameters pertinent to the performance and (Contract F33615-71-C-1625; AF Proj. 3066) suitability for in-flight evaluation; i.e.. TV camera functions and (AD-A002545; Rept-73-210173-Pt-3A; Optical characteristics such as focus, field of view, sensitivity, AFAPL-TR-74-109-Pt-3A) Avail: NTIS CSCL 21/5 linearity resolution and vibration, electromagnetic compatibility The Variable-Cycle TFE731 Turbofan Engine utilized in the environmental tolerance. Based on the results of the tests and altitude performance test is the same engine that was used in demonstrations, it was concluded that the VAS was suitable for the Phase Ill sea-level test program. The engine description is use in the flight evaluation test program. GRA presented in 3.1.1. The test engine. Part 3069600, Serial No. 7399, Build 2. was assembled with new hardware and instrumentation as required, and incorporated variable primary N75-20336# Oxford Univ. (England). Dept. of Engineering and fan exhaust nozzles. The variable compressor stator and Science. LP turbine stator actuation systems were identical with those INTERNAL-COMBUSTION ENGINE/VAPOUR CYCLE used during the Phase Ill test program. GRA COMBINATION Ph.D. Thesis M. S. Radwan Sep. 1974 406 p refs Sponsored in part by Inst. of Mech. Engineers, Sci. Res. Council, and CAV Ltd.. N75-20340# AiResearch Mfg. Co.. Phoenix, Ariz. London IMPACT OF TURBINE MODULATION ON VARIABLE-CYCLE (OUEL-1097174) Avail: NTIS HC $10.50 ENGINE PERFORMANCE. PHASE 4: ADDITIONAL The possibility of using the heat rejected both in the cooling HARDWARE DESIGN AND FABRICATION, ENGINE system and in the exhaust of an internal combustion engine for MODIFICATION, AND ALTITUDE TEST, PART 36 Final a vapor power cycle to increase the power production and the Technical Report, 17 May 1971 - 31 Dec. 1974 thermal efficiency of the combination is discussed. Heat transfer W. R. Davenport. G. J. Dixon, A. Fischer, K. A. Fledderjohn, J. characteristics from cast iron and steel in distilled water and R. Shearer, M. A. Steele, D. Stephenson. and F. Weber Dec. monochlorobenzene are presented, and the effect of nucleate 1974 275 p refs boiling of the two liquids on the surface heat transfer properties (Contract F33615-71-C-1625) of the two metals is dealt with. Diesel engine performance at (AD-A002546; Rept-73-210173-Pt-3B; elevated jacket temperatures with water and monochlorobenzene AFAPL-TR-74-109-Pt-3B) Avail: NTIS CSCL 21/5 was determined. The performance to be expected at full and The objective of this series of tests was to demonstrate part load of a 1500 H.P. diesel engine with a water or that the net thrust and airflow of the TFE731 Engine may be monochlorobenzene vapor power cycle is compared. ESRO increased at Mach 0.6. 20,000 feet, standard atmosphere with the use of variable geometry that tends to increase the low pressure rotor speed or the engine airflow at a constant LP N75-20337# AiResearch Mfg. Co.. Phoenix, Ariz. rotor speed. G RA IMPACT OF TURBINE MODULATION ON VARIABLE-CYCLE ENGINE PERFORMANCE. PHASE 1 AND 2: DESIGN FABRICATION AND RIG TEST, PART 1 Final Technical N75-20341# Bell Helicopter Co., Fort Worth, Tex. Report, 17 May 1971 - 31 Dec. 1974 OH-68A PROPULSION SYSTEM VIBRATION INVESTIGA- W. R. Davenport, G. J. Dixon, A. Fischer, K. R. Fledderjohn, J. TION Final Report R. Shearer, M. A. Steele, D. W. Stephenson, and F. Weber James A. White Aug. 1974 190 p refs

286 N75-20349

(Contract DAAJ02-73-C-001 7; DA Proj. 1 G2-62207-AH-89) CRITERIA FOR LARGE ADVANCED SUPERSONIC AIR- (AD-A002672; USAAMRDL-TR-74-67) Avail: NTIS CSCL CRAFT Final Report 21/5 Robert W. Sudderth, Jeff G. Bohn, Martin A. Caniff, and Gregory The report presents the results of an investigation of the R. Bennett Mar. 1975 212 p refs OH-58A helicopter and Allison T-63 engine vibration characteris- (Contract NAS2-7966) tics. The investigation was directed toward the determination of (NASA-CR-137635) Avail: NTIS HC$7.25 CSCL O1C engine response using impedance /mobility methods and NAsa STructural ANalysis (NASTRAN). The results of these studies Longitudinal handling qualities criteria in terms of airplane response characteristics were developed. The criteria cover high are compared with each other, with results from independent speed cruise maneuvering, landing approach, and stall recovery. vibration tests of the airframe and engine, and with engine vibration Data substantiating the study results are reported. levels measured during flight testing of the OH-58A helicopter. Author The objective was to determine the parameters defining the vibratory interaction and to provide a common language for engine/airframe interface analysis and for preparation of engine/airframe specifications. GRA N78-20347# European Space Research Organization. Paris (France). EXTRACTION OF FLIGHT MECHANIC DERIVATIVES FROM N75-20342# Air Force Flight Dynamics Lab.. Wright-Patterson FLIGHT DATA BY A MANUAL ANALOG MATCHING AFB, Ohio. TECHNIQUE ROTATING ENGINE DESIGN AND CYCLE ANALYSIS Alfred Platrass Dec. 1974 82 p refs Trasl. into ENGLISH PROGRAM of Ermittlung von flug mocha nlschen Derivativen aus Flugmes- I. A. Carnegis Oct. 1974 55 p refs sungen durch manuelle Variation der Modellparameter am (AF Proj. 8224) Analogrechner, DLR-FB-73-1 11. DFVLR, 8 Sep. 1973 Original (AD-A002314; AFFDL-TR-74-128) Avail: NTIS CSCL 21/5 German report available from DFVLR. Porz, West Ger. This report describes a computer program titled 'Rotating 27.90DM Engine Design and Cycle Analysis Program'. The program is (ESRO-TT-1 18; DLR-FB-73-1 11) Avail: NTIS HC $4.75 capable of analyzing turbojets, two spool turbofans (both front Starting from linearized equations of motion of conventional and aft fans), turboprops, turboshafts, and subsonic burning jet aircraft, relations are established between single derivatives ramjets. This program was developed with emphasis on high or groups of derivatives and characteristics of the transient motion speed computation for cycle analysis and for propulsion /flight In measured responses. An Iterative procedure Is given for control sensor analysis. It is capable of computation time in parameter identification by manual analog model matching. Some the order of a few milliseconds per cycle case. The report parameters extracted from flight measurements of a business includes a description of the program's capabilities and limitations, lot aircraft differ considerably from predicted values. Beyond the special features, complete listing, sample input data, and widely used linear equations with constant aerodynamic derIve- corresponding sample output data. GRA tivee, parameters were identified of nonlinear Increase of drag with incremental angle of attack, and nonstatlonary flap N75-20343# Pennsylvania State Univ., University Park. Applied effectiveness, Author (ESRO) Research Lab. MEASUREMENT AND ANALYSIS OF THE UNSTEADY N79.20349# Honeywell, Inc., Minneapolis, Minn. Systems NORMAL FORCE AND PITCHING MOMENT ON AN AXIAL and Research Center. FLOW FAN ROTOR BLADE ELEMENT DIGITAL FLIGHT CONTROL SYSTEM FOR TACTICAL Edgar P. Bruce 3 May 1974 22 p refs Presented at the FIGHTER. VOLUME 1 DIGITAL FLIGHT CONTROL SYSTEM 2nd Interagency Symp. on Univ. Res. in Transportation Noise, ANALYSIS InterIm Report, Fob. 1872 - Jun. 1973 Rayleigh, N. C., 5-7 Jun. 1974 A. Ferit Konar, J. K. Mahesh, and B. KIzilos Jun. 1974 353 p (Contract N00014-67-A-0226-0005) refs (AD-A002739; TM-74-124) Avail: NTIS CSCL 20/1 (Contract F33615-72-C-1058; AF Proj. 1987) In recent years, the radiated noise problem has emerged as (AD-A002320; FOl 31 -IR 1 'Vol . 1; Honeywell-08001 -Vol- 1; one of the most serious problems associated with the design of AFFDL-TR-73 . 119-VoI-1) Avail: NTIS CSCL 01/3 axial flow turbomachines. Prediction of the noise radiated from The Digital Flight Control Systems for Tactical Fighters a turbomachine is dependent upon a knowledge of the fluctuating Program is a development program which defines the technology forces on the blades. The ARL axial flow research fan (AFRF) necessary to apply digital flight control techniques to the three-axis, was designed specifically to provide a capability for detailed multiple flight control configuration demands of advanced research which will define the response of axial flow tur- fighter aircraft. Analysis efforts to date have defined powerful bomachinery blade elements and/or blade rows to subsonic computer program tools which permit determination of flight incompressible unsteady flow of the type encountered in practice. control system performance as a function of computational The purpose of the memo is to describe this facility and the parameters word length, sample rate, and computational delays. specialized equipment that has been developed for use in it, An exercise of the programs using the F-4 as a model indicates and to present some preliminary unsteady force data. GRA 100 iterations per second as satisfactory for the longitudinal axis. . GRA N7520344 e # Lockheed Aircraft Corp., Burbank. Calif. N75-20349# Honeywell, Inc., Minneapolis, Minn. Systems EVALUATION OF ACTIVE CONTROL TECHNOLOGY FOR and Research Center. SHORT HAUL AIRCRAFT Final Report DIGITAL FLIGHT CONTROL SYSTEMS FOR TACTICAL J. H. Renshaw, J. A. Bennett, 0. C. Harris, J. F. Honrath, and FIGHTERS. VOLUME 2: DOCUMENTATION OF THE A. W. Patterson Feb. 1975 156 p refs (Contract NAS2-6995) DIGITAL CONTROL ANALYSIS SOFTWARE (DIGIKON) Interim Report, Feb. 1972 Oct. 1973 (NASA-CR-137634; LG75ER0029) Avail: NTIS HC$6.25 CSCL O1C A. F. Konar, B. Kizilos, J. Gayl, J. K. Mahesh. and M. Borow Jun. 1974 478 refs An evaluation of the economics of short-haul aircraft designed p (Contract F33615-72 . with active controls technology and low wing-loading to achieve C-1058; AF Proj. 1987) (AD-A002327; FOl 31 -IR1 -V0I-2; Honeywell-08001-Vol-2; short field performance with good ride quality is presented. Results AFFDL-TR-73-1 19-VoI . 2) Avail: NTIS CSCL 01/3 indicate that for such a system incorporating gust load alleviation The computer programs which implement the mathematical and augmented stability the direct operating cost is better than analyses and models developed in Volume I are described. The for aircraft without active controls. J.M.S. programs are developed in Fortran IV language. Extensive use of subroutines is made to provide programming flexibility when N75.20345*# Boeing Commercial Airplane Co.. Seattle, Wash. considering alternate airframe/dynamics/control points/ DEVELOPMENT OF LONGITUDINAL HANDLING QUALITIES measurement systems /controllers effect on control system

287 N75-20350

performance. A demonstration example is included in Volume I When an airframe component breaks suddenly, under to illustrate how these programs are used and how the conditions well within the design envelope, the occurrence is computational requirements are derived. GRA usually termed brittle fracture. This report uses an analytical scheme which combines data from several different sources in order to provide diagrams of fracture resistance versus thickness N75-20350# National Aeronautics and Space Administration. for a number of standard yield strength levels. By using such Ames Research Center, Moffett Field, Calif. diagrams, limited data on a new alloy or heat treatment may SHAKE TEST OF ROTOR TEST APPARATUS IN THE 40- be compared. and the impact on designs where fracture resistance BY 80-FOOT WIND TUNNEL is important may be assessed. The data background employed Wayne Johnson (Army Air Mobility R and D Lab.. Moffett 'Field. in the analysis consisted of both iron- and aluminum-base airframe Calif.) and James C. Biggers Feb. 1975 74 p materials. However, this report focuses largely on the 7000- (NASA-TM-X-62418; A-5973( Avail: NTIS HC $4.25 CSCL series aluminum alloys. Minimum expected behavior has been 14B developed for this series of aluminum alloys by examining fracture A shake test was conducted to determine the dynamic toughness, yield strength, and thickness effect in accordance characteristics of a rotor test apparatus on strut systems. The with the analytical scheme described. GRA rotor-off hub transfer function (acceleration per unit force as a function of frequency) was measured in the longitudinal and N75-20554# Boeing Commercial Airplane Co.. Seattle, Wash. lateral directions, using a combination of broadband and discrete DEVELOPMENT OF STATISTICAL FATIGUE FAILURE frequency excitation techniques. The dynamic data is summarized CHARACTERISTICS OF 0.125 INCH 2024-T3 ALUMINUM for the configurations tested, giving the following properties for UNDER SIMULATED FLIGHT-BY-FLIGHT LOADING Final each mode identified: the natural frequency, the hub response Report, Aug. 1972 - Mar. 1974 at resonance, and the fixed system damping. The complete transfer J. P. Butler and D. A. Rees Jul. 1974 186 p refs functions are presented, and the detailed test results are (Contract F33615-72-C-2003: AF Proj. 7351) included as an appendix. Data analysis techniques developed to (AD-A002310: AFML-TR-74-124( Avail: NTIS CSCL 11/6 obtain on-line measurements of the system modal properties, Thirty-two unique multidetail specimens were tested to including the damping coefficient and the damping ratio are develop a data base for investigating the statistical materials/ discussed. Author structures fatigue failure characteristics of 2024-T3 aluminum alloy in the form of 0.225-in-thick sheet. The test loading was a random-load, flight-by-flight loading block spectrum repeated N75-20352# Boeing Commercial Airplane Co., Seattle, Wash. to obtain crack initiation. Six different basic spectra, representative WIND MODELS FOR FLIGHT SIMULATOR CERTIFICATION of cargo/transport or gust load flights, were applied to the OF LANDING AND APPROACH GUIDANCE AND CONTROL specimens. Fatigue crack initiation was detected and controlled SYSTEMS Final Report to a nominal crack length of about 0.04 in. from the edge of Neal M. Barr, Dagfinn Gangaas. and Dwight R. Schaeffer Dec. the hole by a painted crack detection circuit system. After detection 1974 623 p refs of crack initiation, each hole was restored to an undamaged (Contract DOT-FA72WA-2934) state by oversiziog and coldworking. A statistical analysis of (AD-A003801; FAA-RD-74-206( Avail: NTIS HC$15.25 CSCL the data by previously developed maximum likelihood methods 17/7 is presented for both scale and shape parameters of the log-normal Analytic and probabilistic descriptions of low-altitude mean and two-parameter Weibull distributions. GRA wind and turbulence are investigated and described. The effects of wind and turbulence on aerodynamics and aircraft motion AiResearch Mfg. Co., Phoenix, Ariz. are analyzed. A model of wind and turbulence, suitable for the N75-20676// certification of landing and approach guidance and control systems EVALUATION PROGRAM ON USING COMPRESSOR BLEED by flight simulations, is developed, and consideration given to AIR AS A SOURCE OF PNEUMATIC POWER FOR FLUIDIC Final Report, Oct. 1972 - Oct. 1973 implementation. Author CIRCUITS R. S. McCarty 5 Oct. 1973 75 p (Contract N62269-73-C-0476( N75-20353# National Aviation Facilities Experimental Center, (AD -A002483; AuResearch-73-41 0307) Avail: NTIS CSCL Atlantic City, N.J. 13/7 EVALUATION OF THE RUBINO PROCEDURE FOR RADIO The program activities encompassed study and analysis of TELEMETRIC THEODOLITE POSITIONING Final Report, Oct. the characteristics of compressor bleed air as it is affected by 1974 engine power settings, engine age, location of the extraction D. S. Lamer Jan. 1975 46 p Revised point, inlet ingestion, and how the contamination of all of these (Contract DOT-FA74NA-1027( affect fluidic components. . GRA (AD-A0043 17: FAA-NA-74-177-Rev; FAA-EM-74-17) Avail: NTIS HC$3.75 CSCLO1/5 An evaluation of a procedure described in the Working Paper N75-20777# Battelle Columbus Labs., Ohio. on Radio Telemetric Theodolite (RTT) Positioning was conducted. FRACTURE MECHANICS OF TINY CRACKS NEAR An analysis and evaluation was conducted by gathering informa- FASTENERS tion about the present glide slope system, difficulties that had William E. Anderson Jun. 1974 61 p refs been encountered, and changes that had been implemented. The (Contract E33657-73-C-0281( analysis performed indicates that all factors affecting the glidepath (AD-A002554; ASD-TR-74-24) Avail: NTIS CSCL 11/6 are separated by the RU placement into path structure (indicated This report deals with the question of how tiny a crack by the flight recording), and the threshold crossing height might be in aluminum alloys of high strength and still be (which is incorporated into the RTT placement). This study analytically treated by the methods of linear elastic fracture evaluation concludes that because of this separation the procedure mechanics (LEFM(. These techniques are used to obtain estimates is better because it provides a better description of the glidepath of the expected rate of crack extension. Under simple cyclic in space. Author loadings. LEFM-based predictions are usually within a factor of two from measured experimental results. GRA

N75-20548# Battelle Columbus Labs., Ohio. DESIGN AND PURCHASE EXPECTATIONS FOR FRACTURE RESISTANCE OF 700-SERIES ALUMINUM AIRFRAME ALLOYS Interim Report, Oct. 1972 - Sep. 1973 William E. Anderson Jan. 1974 38 p refs (Contract F33657-73-C-0281) (AD-AO02552: ASD-TR-74-16) Avail: NTIS CSCL 11/6

288 SUBJECT INDEX

AERONAUTICAL ENGINEERING 1A Special Bibliography (Suppl. 59) JULY 1975

Typical Subject Index Listing

SUBJECT TIT LE I EXTENSION Comparison of parametric duct-burning turbofan and CYCLIC LOADS ri non-afterburning turbojet engines in a Mach 2.7 f-Low cycle high temperature fatigue in aircraft transport I jet engines: conference proceedings [NASA-TM-X-71679] . 875-19247 I (AGABD-CP-155) N75-10487 ACOUSTIC NOZZLES Supersonic jet noise suppression with multitube nozzle/ejectors [AIAA PAPER 75-501] 575-27936 E REPORT TITL UMBER [.^U MBERSIO ACOUSTIC PROPERTIES Classification problems of aircraft noise --- far field measurements A75-279143 Low speed and angle of attack effects on sonic and The title is used to provide a description of the subject matter. When the title is near-sonic inlets insufficiently descriptive of the document content, a title extension is added. [NASA-CR-134778] 875-19184 separated from the title by three hyphens The NASA or AIAA accession number Preliminary evaluation of turbofan cycle is included in each entry to assist the user in locating the abstract in the abstract parameters and acoustical suppression on the section of this supplement. If applicable, a report number is also included as an noise and direct operating cost of a commercial Mach 0.85 transport aid in identifying the document. [N&SA-TM-X-71664) N75-192444 Trends in aircraft noise control N75-20229 ACOUSTIC VELOCITY A method of calculating aerodynamic-nozzle ABSORBERS (MATERIALS) profiles with passage through the sound barrier The use of Hartmann generators as sources of high A75-26881 intensity sound in a large absorption flow duct Low speed and angle of attack effects on sonic and facility near-sonic inlets IAIAX PAPER 75-529] A75-27939 [NASA-CR-134778] 875-19184 AC GENERATORS ADAPTIVE CONTROL Program for the development of a superconducting Adaptive digital system for aircraft control generator. Part 1: Phase 1 --- including A75-27182 critical component tests Adaptive control system with reference model [AD-5001649] 875-19546 application to automatic pilots ACCELERATION (PHYSICS) A75-27912 The computation of aerodynamic loads on helicopter Digital flight control system for tactical blades in forward flight, using the method of fighter. Volume 1: Digital flight control the acceleration potential Book system analysis [AD-A002320] 875-20348 ACCIDENT PREVENTION Digital flight control systems for tactical General Aviation Aircraft Safety fighters. Volume 2: Documentation of the [AD-5003124] 875-19199 digital control analysis software (DIGIKON) ACOUSTIC DUCTS [AD-A002321] N75-20349 Spinning mode sound propagation in ducts with AERIAL RUDDERS acoustic treatment Flight determination of the rudder power and 575-27854 directional stability of the Fairey Delta 2 Unified analysis of ducted turbomachinery noisy aircraft using a wingtip parachute A75-27861 [ARC-CP-1298] 875-19267 Radiation of duct noise out through a jet flow AERODYNAMIC BRAKES acoustic field model for aircraft engine Some notes on the thermodynamics of thrust (AIRS PAPER 75457] A75-27928 reversal in flight Noise generation and transmission in duct combustors N75-20212 15155 PAPER 75-527] A75-27938 AERODYNAMIC CHARACTERISTICS The use of Hartmann generators as sources of high A method of calculating aerodynamic-nozzle intensity sound in a large absorption flow duct profiles with passage through the sound barrier facility A75-26881 [BIAS PAPER 75-529] 575-27939 The aerodynamic characteristics and trailing Effects of friction and heat conduction on sound vortex wake of propeller V/STOL configurations propagation in ducts A75-28522 [AlAS PAPER 75-520] A75-28349 Study of two hypersonic, amisymmetric, shaped Aeroacoustics: Jet and combustion noise; duct nozzles with smooth contour acoustics --- Book A75-2865B 575-28629 An exact solution for transonic potential flow ACOUSTIC INSTABILITY past aerofoil sections Development of acoustic disturbances in supersonic 1 NAt-TR-383J N75-19176 annular lets Parameter identification applied to aircraft A75-26234 [CRANFIELD-AERO-26 ] N75-19177 ACOUSTIC MEASUREMENTS On the calculation of non-linear aerodynamic Aeroacoustics: Fan, SlOt, and boundary layer characteristics and the near vortex wake noise; sonic boom; aeroacoustic instrumentation [AD-A002161] N75-19193 Book Technical evaluation report on Fluid Dynamics 575-28625 Panel Symposium on V/STOL Aerodynamics [AGARD-AR-78] N75-19585

A-i AERODYNAMIC COEFFICIENTS SUBJECT INDEX

AERODYNAMIC COEFFICIENTS A structural weight estimation program (SWEEP) for Lift coefficients on a supercavitating jet-flapped aircraft. Volume 11: Flexible airloads foil between rigid walls stand-alone program A75-26554 [AD-A002873] 875-20324 Critical analysis and improvement of the AERODYNAMIC NOISE source-panel method - for lift prediction Development of acoustic disturbances in supersonic A75-28095 annular jets Computation of airfoil DRAG profiles A75-26234 CREPT-35/1974] 875-19165 The generation of sound by aerodynamic sources in Dynamics of the motion of a body with allowance an inhomogeneous steady flow for the unsteady state of the flow about it A75-26463 (NASA-TT-F-16133] 875-19179 'Theoretical and experimental studies of AERODYNAMIC CONFIGURATIONS discrete-tone rotor-stator interaction noise Unsteady viscous flow past alifting plate [AIAA PAPER 75-1143] A75-27926 N75-19171 Radiation of duct noise out through a jet flow Experimental aerodynamic characteristics for a acoustic field model for aircraft engine cylindrical body of revolution with side strakes [AIAA PAPER 75-457] A75-27928 and various noses at angles of attack from 0 Developments in jet noise modeling - Theoretical degrees to 58 degrees and Bach numbers from 0.6 predictions and comparisons with measured data to 2.0 [AIAA PAPER 75-417] A75-27933 [NASA-TM-X-3130] N75-19181 Some recent developments in supersonic jet noise Problems of designing passenger aircraft reduction [NASA-TT-F-808] 875-19223 [AIAA PAPER 75-502] A75-27937 Fuel conservation possibilities for terminal area Ratio of peak frequencies of jet self and shear compatible aircraft noise spectra [NASA-CR-132608] 875-19224 A15-28400 AERODYNAMIC DRAG Aeroacoustics: Fan, STOL, and boundary layer The range of validity in the case of two old noise; sonic boom; aeroacoustic instrumentation investigations. I - The origin of lift. II - Bck Collision and gliding processes on the liquid A75-28626 surface Aeroacoustics: Jet and combustion noise; duct A75-27990 acoustics --- Book Opportunities for aerodynamic-drag reduction A75-28629 N75-20237 Trends in aircraft noise control AERODYNAMIC FORCES S75-20229 A method for calculating unsteady forces due to AERODYNAMIC STABILITY interaction between tail surfaces Rotation in vibration, optimization, and A75-26477 aeroelastic stability problems Unsteady lift forces on a vibrating cylinder in a N75-19167 supercritical flow Low-speed wind-tunnel tests of a 1/10-scale model A75-26480 of a blended arrow advanced supersonic transport Improvements to the SADSAM computer program for aerodynamic control and stability aeroelasticity analysis [NASA-TM-X-72671] 875-19226 [NASA-CR-132617] 875-19173 Determination of aircraft characteristics from A method for predicting unsteady aerodynamic flight tests forces on oscillating wings with thickness in [ESRO-TT-104] 875-19252 transonic flow near Mach number 1. Part 1: Comparison of evaluation procedures for the Two-dimensional theory. Part 2: Rectangular determination of flight-mechanical coefficients wings and derivatives from flight tests --- Fiat G-91 [NAL-TR-368T-PT-1] 875-19174 P3 aircraft Integration of aft-fuselage-mounted flow through N75-19254 engine nacelles on an advanced transport Determination of aerodynamic derivatives of the configuration at Mach numbers from 0.6 to 1.0 FIAT G-91 P3 aircraft from flight tests by means [NASA-TM-X-3178] 875-19180 of manual analog model matching Some remarks on the induced velocity field of a N75-19257 lifting rotor and on Glauert's formula Evaluation of flight test of the FIAT G-91 T3 by [ARC-CP-1301 ] 875-20263 means of the method of forced oscillations AERODYNAMIC INTERFERENCE 875-19258 Effect of interference between moving blade rows Evaluation of flight tests of the FIAT 0-91 P3 by on cascade flutter. I - Experiment on compressor means of regression analysis cascade in flexure mode 875-19259 A75-26553 A SAAB-SCANIA developed method for obtaining Theoretical and experimental studies of stability derivatives from flight tests discrete-tone rotor-stator interaction noise 875-19260 [AIAA PAPER 75-443] A75-27926 Characteristics of the AJ 31 aircraft: Comparison Wind tunnel investigation of helicopter rotor wake of the results of wind tunnel and flight tests effects on three helicopter fuselage models noting elasticity correction for wind tunnel (NASA-TM-X-3185-SUPPL] N75-202911 model AERODYNAMIC LOADS N75-19261 The computation of aerodynamic loads on helicopter Determination of derivatives by a model with blades in forward flight, using the method of automatic parameter --- analog circuit the acceleration potential --- Rook N75-19265 A75-26700 Extraction of flight mechanic derivatives from TRW vortex-lattice method subsonic aerodynamic flight data by a manual analog matching technique analysis for multiple-lifting-surfaces (N. [ESRO-TT-118] 875-20347 surface) TRW program number HAO108 AERODYNAMIC STALLING (NASA-CR-128588) 875-19178 Starting vortex, separation bubbles and stall - A Calculations of generalised airforces on two numerical study of laminar unsteady flow around parallel lifting surfaces oscillating an airfoil harmonically in subsonic flow A75-26212 [ARC-R/11-3749] 875-19187 Design considerations for stall/spin avoidance A structural weight estimation program (SWEEP) for 875-19205 aircraft. Volume 3: Airloads estimation module AERODYNAMICS (AD-A002854] 875-20305 A problem in supersonic jet theory A structural weight estimation program (SWEEP) for A75-26697 aircraft. Volume 3: Airloads estimation module. Appendix A: Module flow charts and FORTRAN lists. Appendix B: Sample output [AD-A002855] 875-20306

A-2

SUBJECT INDEX AIRBORNE/SPACEBORNE COMPUTERS

AEROELASTICITY - USAF aircraft takeoff length distances and Allowance for the elastic deformation of the wing climbout profiles in its own plane in the calculation of the [AD-A001826] 1175-19878 skewsymmetric vibrations of an aircraft with a AIR TRAFFIC CONTROL snail-aspect-ratio wing Digital avionics - An overview --- Air Traffic A75-28687 Control Radar Beacon System Rotation in vibration, optimization, and [AIAA PAPER 75-553] A15-26721 aeroelastic stability problems Air Traffic Control demonstration aspects of the M75-19167 Applications Technology Satellite-6 Improvements to the SADSAM computer program for (AIAA PAPER 75-562] A75-26723 aeroelasticity analysis New horizons in air traffic control [NASA-CR-132617] N75-19173 [AIAA PAPER 75-569] A75-26728 AERONAUTICAL ENGINEERING Software engineering of a navigation and guidance The future of aeronautics system for commercial aircraft (NASA-CR-142559] N75-20222 [AIAA PAPER 75-575] A75-26733 Aeronautics in the American society Interaction of military/civil position location N75-20223 and reporting systems --- of.ATC University research in aeronautics [AIAA PAPER 15-561] A75-28467 N75-20241 SEEK BUS - A time division multiple access system General aviation's future need for research ATC applications N75-20242 [AIAA PAPER 75-564] A75-28468 University research in aeronautics TACAN/DNE digital data broadcast design plan. N75-20243 Volume 1: Operational analysis AERONAUTICAL SATELLITES [AD-A001403/5] 1115-19213 Air Traffic Control demonstration aspects of the Multi-site intermittent positive control Applications Technology Satellite-6 algorithms for the discrete address beacon system (AIAA PAPER 75-562) A75-26723 [AD-A001112/2] 1175-19214 AEROSPACE INDUSTRY Provisional message formats for the DABS/NAS Deutsche Gesellschaft fuer Luft- und Raumfahrt, interface (revision 1) Yearbook 1973 --- German book (FAA-RD-74-63-A] 1115-19216 A75-27978 Plight test evaluation of SECANT VECAS collision European aeronautics and astronautics at the avoidance system crossroads [AD-A002281] 1175-19220 A75-27981 AIR TRANSPORTATION AEROTHERNODYNAMICS The aircraft accident --- German book Some motes on the thermodynamics of thrust A75-26498 reversal in flight Air Europe: The policy of cooperation among N75-20212 airline companies of the European Six --- French AFTERBODIES book Experimental aerodynamic characteristics for a A75-26499 cylindrical body of revolution with side strakes Ride quality evaluation. I --- aircraft passenger and various noses at angles of attack from 0 comfort assessment degrees to 58 degrees and Mach numbers from 0.6 A75-26849 to 2.0 Tiedown tests for air transport of the IM542 (NASA-TM-X-3130] N75-19181 sprint container Boundary layer effects in supersonic flow over [AD-A001844) 1175-19210 cylinder-flare bodies The next forty years in aviation (WEE-REPT-1238 (WE/U) 3 N75-20257 1175-20228 AIR CARGO AIRBORNE EQUIPMENT Important aspects of international air cargo An experimental TDNA network for airborne warning rate structure, container handling and fuel and control systems inter-operability costs effects demonstrations A75-269'48 [AIAA PAPER 15-563] A15-26724 AIR FLOW Reliability life cycle of a complex electronic Multi-slot film cooling of supersonic aircraft airborne equipment using air as a coolant A75-27839 [AD-A002673] N75-19239 Airborne equipment for use with the microwave Wind tunnel studies of the turbulent wake behind landing system self propelled slender bodies A75-28790 (AD-A002396] 1175-20212 The range of airborne processing available to the AIR INTAKES future user of the Doppler MLS --- Microwave A structural weight estimation program (SWEEP) for Landing Systems aircraft. Volume 5: Air induction system and A75-28792 landing gear nodules. Part 1: Air induction The development of a serial P.C.M. instrumentation system module system [AD-A002857] 1175-20308 A75-28797 AIR JETS AIRBORNE/SPACEBORNE COMPUTERS Subsonic jet noise in flight based on some recent Flight test of a digital guidance and control wind-tunnel tests system in a DC-10 aircraft [AIAA PAPER 75-462] A75-27930 [AIAA PAPER 75-567] A75-26726 AIR NAVIGATION Software engineering of a navigation and guidance Software engineering of a navigation and guidance system for commercial aircraft system for commercial aircraft [AIAA PAPER 75-515] A15-26733 [AIAA PAPER 75-575] A75-26733 Digital flight control systems - Considerations in System approach to civil aircraft navigation using implementation and acceptance digital technology. [AIAA PAPER 75-577] A75-26734 [AIAA PAPER 75-572] A75-28469 Application of digital systems to Army avionics TACAN/DME digital data broadcast design plan. (AIAA PAPER 75-587] A75-26738 Volume 1: Operational analysis P-iS computational subsystem --- computer systems [AD-A001403/5] 1175-19213 design Oceanic air route navigation with envelope match [AIAA PAPER 75-590] A75-28470 Loran-C The U.S. Candidate Microwave Landing System - A [AD-A003800] 1175-20286 new generation of avionics/ground equipment AIR POLLUTION (AIAA PAPER 75-607] A75-28472 Development of air transport and environmental A new flight test data system for NASA requirements --- for air and noise pollution aeronautical flight research reduction A75-28174 A75-28228

A-3

AIRCRAFT SUBJECT INDEX

AIRCRAFT Stability analysis of stochastic composite systems Quarterly bulletin of the Division of Mechanical application to control of aircraft and Engineering and the National Aeronautical nonlinear systems Establishment, 1 October - 31 December 1974 A75-27919 [DME/NAE-1974(4) ] 875-20249 Qualitative analysis of a family of extremums in a AIRCRAFT ACCIDENT INVESTIGATION problem involving optimal control of aircraft The aircraft accident --- German book motion A75-26498 A75-28676 Analysis of wreckage --- aircraft accident A model based technique for the design of flight investigation directors --- optimal control models A75-26533 N75-19140 Take-off instrument for assessing achieved Status and trends in active control technology performance during take-off and a take-off 875-20236 accident analysed in context Development of a remote digital augmentation 615-28769 system and application to a remotely piloted Aircraft accident report. Eastern Air Lines, Inc. research vehicle McDonnell-Douglas DC 9-31, N8961E Akron-Conton [NASA-TN-D-7941] 875-20293 Regional Airport, North Canton, Ohio, 27 Nov. 1973 Evaluation of active control technology for short (P8-238637/33 875-20274 haul aircraft --- cost effectiveness Special study: Safety aspects of emergency (NASA-CR-137634] 875-20344 evacuations from air carrier aircraft AIRCRAFT DESIGN [P8-238269/5] 875-20275 Digital avionics-overview - Airframe AIRCRAFT ACCIDENTS manufacturer's viewpoint Analysis of in-flight disintegration accidents [AIAA PAPER 75-552] A75-26720 N75-19197 A pilot's report concerning the VTOL VAR 191 B General Aviation Aircraft Safety A75-26900 [AD-A003124] 875-19199 Deutsche Gesellschaft fuer Luft- und Raumfahrt, Analysis of general aviation accident records Yearbook 1973 --- German book N75-19200 A75-21978 General aviation accident patterns Airbus A 300 - Comparison of the flight test N75-19201 results with the flight performance and flight The accident record in terms of the pilot characteristics determined on the basis of N75-19202 theory and wind tunnel tests Crash survivability 675-21980 N75-19203 Air cushion landing systems for aircraft General aviation handling qualities research A75-27983 875-19204 Flight tests with the V/STOL experimental aircraft A study of carburetor/induction system icing in VAR 191 B general aviation accidents A75-27985 [NASA-CR-143835] 875-19208 General aviation accident patterns Environmental and operating requirements for fire N75-19201 extinguishing systems on advanced aircraft General aviation handling qualities research [AD-A001640] 875-19228 N75-19204 Annual reviews of aircraft accident data US Air Design considerations for stall/spin avoidance Carrier operations, 1973 N75-19205 [P8-238281/0] N75-20276 Problems of designing passenger aircraft Pan American World Airways, Incorporated Boeing [NASA-TT-F-808] N75-19223 707-3218, N454PA, Pago Pago, American Samoa, 30 Fuel conservation possibilities for terminal area January 1974 compatible aircraft (PB-238478/2] N75-20277 [NASA-CR-132608] N75-19224 Delta Air Lines Incorporated McDonnell Douglas Engineering design handbook. Helicopter DC-9-32, N3323L, Chattanooga Municipal Airport, engineering, part 1: Preliminary design --- for Chattanooga, Tennessee VFR operation [P8-238479/0] 875-20278 [AD-A002007] 875-19238 AIRCRAFT ANTENNAS The future of aeronautics Dual band airborne antenna study [NASA-CR-142559] N75-20222 [AD-A002043] N15-19219 Aeronautics in the American society AIRCRAFT COMMUNICATION N75-20223 SEEK BUS - A time division multiple access system Some trends in aircraft design: Structure ATC applications N75-20235 [AIAA PAPER 75-564] A75-28468 Status and trends in active control technology Multi-site intermittent positive control N75-20236 algorithms for the discrete address beacon system Lifting surface for aircraft --- wing profiles [AD-A001112/2] N75-19214 (NASA-TT-F-16241] N75-20290 AIRCRAFT COMPARTMENTS Air cushion landing systems for aircraft What have we learned from applying digital N75-20296 technology to cabin/passenger multiplex systems AIRCRAFT ENGINES cost and weight analysis 'By the application of power' /21st Cayley [AIAA PAPER 75-574] A75-26732 Memorial Lecture/ --- technical survey of AIRCRAFT CONFIGURATIONS aircraft engines Integration of aft-fuselage-mounted flow through A75-27368 engine nacelles on an advanced transport High-temperature alloys and the aircraft gas turbine configuration at Mach numbers from 0.6 to 1.0 A75-27877 (NASA-TM-X-3178] 875-19180 Development of an R.F. telemetry system --- for AIRCRAFT CONTROL aircraft engine stress and temperature data Digital flight control systems - Considerations in A75-28778 implementation and acceptance Low speed and angle of attack effects on sonic and [AIAA PAPER 75-577] A75-26734 near-sonic inlets Design of the DAIS control and display core element [NASA-CR-134778] 875-19184 Digital Avionics Information System Metal matrix composites for aircraft propulsion [AIAA PAPER 75-600] A75-26745 systems A concept of flight dynamics control --- for [NASA-TM-X-71685] N75-19245 aircraft PLT 21 gas turbine engine exhaust emission and A75-27180 noise measurements Adaptive digital system for aircraft control (AD-A001728] 875-19251 A75-27182 AIRCRAFT EQUIPMENT Ply-by-wire and control configured vehicles - Wide bandwidth optical telemetry link for ground Rewards and risks testing of equipment in high EMI environments A75-27367 A75-28781

A-l4

SUBJECT INDEX AIRCRAFT PERFORMANCE

General aviation accident patterns Air cushion landing systems for aircraft 875-19201 N75-20296 Airborne electronics for automated flight systems AIRCRAFT MAINTENANCE N75-20232 Organization of centralized maintenance of General aviation's future need for research aircraft assemblies --- Russian book 875-20242 A75-27838 Development of a scientific basis for analysis of CH-47A assessment and comparative fleet - aircraft seating systems evaluation: Executive summary report [AD-A004306] 875-20273 [AD-A002057] 875-19232 Instrument system test. Elliott helicopter air Computer simulation of maintenance for data system multi-mission NPV 5 [AD-A002332] N75-20331 (AD-A003351] N75-20253 AIRCRAFT FUEL SYSTEMS AIRCRAFT MANEUVERS Investigation of 14.5mm API Aircraft guidance for automatic collision avoidance self- sealing/crashworthy fuel tank material A75-27178 [AD-A001752] N75-19249 Manual evaluation of special flying maneuvers for Feasibility of adapting a thin film permeable the determination of flight-mechanical membrane to jet transport fuel tank inerting coefficients and derivatives from flight tests system longitudinal and lateral stability of [AD-A003799] N75-20295 G-91-T3 aircraft AIRCRAFT GUIDANCE N75-19255 Software engineering of a navigation and guidance AIRCRAFT MODELS system for commercial aircraft Developments in jet noise modeling - Theoretical (AIAA PAPER 75-575) A75-26733 predictions and comparisons with measured data Aircraft guidance for automatic collision avoidance [AIAA PAPER 75-477] A75-27933 A75-27178 Extension of the lifting line model for the Wind models for flight simulator certification of helicopter rotor landing and approach guidance and control systems A75-28194 [AD-A003801] N75-20352 Estimates of the stability derivatives of a AIRCRAFT HAZARDS helicopter and a V/STOL aircraft from flight data A study of the effects on mice of smoke and gases A75-28201 from controlled fires in simulated aircraft cabins AIRCRAFT NOISE A75-27073 Spinning mode sound propagation in ducts with AIRCRAFT INDUSTRY acoustic treatment Digital avionics-overview - Airframe A75-27854 manufacturer's viewpoint The use of Hartmann generators as sources of high (AIAA PAPER 75-552] A75-26720 intensity sound in a large absorption flow duct Manufacturer's overview facility 875-19207 [AIAA PAPER 75-529] A75-27939 AIRCRAFT INSTRUMENTS Classification problems of aircraft noise --- far Application of digital systems to Army avionics field measurements [AIAA PAPER 75-587] A75-26738 A75-27943 Digital avionics information system /DAIS/ Problem of aircraft noise in the vicinity of integrated test bed development airports [AIAA PAPER 75-588] A75-26739 A75-28222 The performance in illuminances up to 80,000 lux Noise certification of aircraft of a light emitting diode display having a 3 mm A75-28223 character height Development of air transport and environmental A75-27526 requirements --- for air and noise pollution A new centralised warning display for aircraft reduction A75-28785 A75-28228 A new 3 band pulsed radar altimeter Aeroacoustics: Fan, STOL, and boundary layer A75-28787 noise; sonic boom; aeroacoustic instrumentation Altimeters - The way ahead Book A75-28788 A15-28626 A display evaluation methodology applied to Preliminary evaluation of turbofan cycle vertical situation displays parameters and acoustical suppression on the N75-19137 noise and direct operating cost of a commercial Improvements in pilot/aircraft-integration by Mach 0.85 transport advanced contact analog displays [NASA-TM-X-71664] 875-19244 875-19141 Influence of multitube mixer nozzle geometry on C-141 All Weather Landing System (AWLS) flight CTOL-OTW jet noise shielding test report: Optimization and pre-experimental (NASA-TM-X-71681] N75-19246 phases Trends in aircraft noise control [AD-A003952] 875-20330 815-20229 AIRCRAFT LANDING AIRCRAFT PERFORMANCE New horizons in air traffic control A pilot's report concerning the VIOL VAK 191 B [AIAA PAPER 75-569] A75-26728 A75-26900 Air cushion landing systems for aircraft The 'definition' of the motorsegler A75-27983 [DFVLR-SONDDR-424] A15-27596 The U.S. Candidate Microwave Landing System - A Roll paper pilot --- mathematical model for new generation of avionics/ground equipment predicting pilot rating of aircraft in roll task [AIAA PAPER 75-607] A75-28472 N75-19134 A tactual pilot aid for the approach-and-landing Parameter identification applied to aircraft task: Inflight studies (CRANFIELD-AERO-26] 875-19177 N75-19131 General aviation handling qualities research Feasibility of laser systems for aircraft landing N75-19204 operations under low visibility conditions Problems of designing passenger aircraft [AD-A005637] 875-19198 (NASA-TT-F-808] 875-19223 Rarowe altitude warning system evaluation An aircraft application of system identification [AD-A002583] N75-19241 in the presence of state noise Pan American World Airways, Incorporated Boeing [AD-A001936] 875-19234 707-3218, N454PA, Pago Pago, American Samoa, 30 Some aspects of performance measurements in January 1979 nonsteady flight --- angle of attack and rate of (P8-238478/2] 875-20217 climb Delta Air Lines Incorporated McDonnell Douglas N75-19262 DC-9-32, N3323L, Chattanooga Municipal Airport, Parameter identification applied to aircraft Chattanooga, Tennessee (CRANFIELD-AERO-26] N75-20259 (PB-238479/0] N75-20278

A-5

AIRCRAFT RELIABILITY SUBJECT INDEX

Sideslip of wing-body combinations --- disturbance A structural weight estimation program (SWEEP) for theory for predicting aerodynamics of aircraft aircraft. Volume 5: Air induction system and in sideslip landing gear modules. Part 1: Air induction (NASA-CR-1114716) 075-20260 system module Won-dimensional methods for the measurement of [AD-A002857] 075-20308 • level flight performance of turbine engined A structural weight estimation program (SWEEP) for helicopters aircraft. Volume 5: Air induction system and (ESDU-74042] 075-20289 landing gear modules. Part 2: Landing gear Air cushion landing systems for aircraft module 075-20296 [AD-A002858] 075-20309 Development of longitudinal handling qualities A structural weight estimation program (SWEEP) for criteria for large advanced supersonic aircraft aircraft. Volume 6: Wing and empennage module. [NASA-CR-1376351 075-203145 Book 1: Technical discussion sections 1 and 2 AIRCRAFT RELIABILITY [AD-A002864] 075-20310 Flight-critical digital control system evaluation A structural weight estimation program (SWEEP) for [AIAA PAPER 75-566] A75-26725 aircraft. Volume 6: Wing and empennage nodule. General Aviation Aircraft Safety Rook 2: Technical discussion, Sections 3 and 4 (AD-A0031241 075-19199 [AD-A002865] N75-20311 AIRCRAFT STABILITY A structural weight estimation program (SWEEP) for Fly-by-wire and control configured vehicles - aircraft. Volume 6: Wing and empennage module. Rewards and risks Book 3: Technical discussion, section 5 A75-27367 [AD-A002866] N75-20312 Adaptive control system with reference model A structural weight estimation program (SWEEP) for application to automatic pilots aircraft. Volume 6: Wing and empennage module. A75-27912 Appendix A: General information for module flow Estimates of the stability derivatives of a charts and listings. Appendix B: Program flow helicopter and a V/STOL aircraft from flight data charts, overlays (8,0), (14,0), (15,0), (16,0) A75-28201 and (17,0) Design df a digital-stability augmentation and [AD-A002859] 075-20313 control system with gust alleviation and modal A structural weight estimation program (SWEEP) for suppression aircraft. Volume 6: Wing and empennage module. A75-28432 Appendix C: Program flow charts, overlays (9,0) Allowance for the elastic deformation of the wing and (10,0) in its own plane in the calculation of the (AD-A002860) 075-20314 skewsymmetric vibrations of an aircraft with a A structural weight estimation program (SWEEP) for small-aspect-ratio wing aircraft. Volume 6: Wing and empennage module. A75-28687 Appendix D: Program flow charts, overlay (18,0) The dynamic response of aircraft encountering [AD-A002861] N75-20315 aircraft wake turbulence A structural weight estimation program (SWEEP) for N75-19170 aircraft. Volume 6: Wing and empennage module. AIRCRAFT STRUCTURES Appendix B: Program listings, overlays (8,0), Characterization of advanced composite materials (14,0), (15,0), (16,0), and (17,0) for structural design --- of aircraft [AD-A002862] N75-20316 A75-27695 A structural weight estimation program (SWEEP) for Stress intensity factors for some through-cracked aircraft. Volume 6: Wing and empennage module. fastener holes Appendix F: Program listings, overlays (9,0), A75-28236 (10,0) and (18,0) Shear lag analysis of thick skin aircraft structures (AD-A002863] 075-20317 (ATN-7404] 075-19225 A structural weight estimation program (SWEEP) for An improved automated structural optimization aircraft. Volume 7: Fuselage module program [AD-A002867] 075-20318 [AD-A002688) 075-19237 A structural weight estimation program (SWEEP) for Relation between scatter of fatigue life and S-N aircraft. Volume 7: Fuselage module. Appendix curve in aircraft structural aluminium alloy A: Module flow charts and FORTRAN lists. 2024-T4 Appendix B: Fuselage module sample output (NAL-TR-360) 075-191414 (AD-A002868] N75-20319 The variability of fatigue damage from flight to A structural weight estimation program (SWEEP) for flight aircraft. Volume 8: Programmer's manual (ARC-CP-1297] 075-20297 (AD-A002869) 075-20320 A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 1: Executive summary aircraft. Volume 9: User's manual (AD-A002850] 075-20301 [AD-A002870] 075-20321 A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 2: Program integration and aircraft. Volume 9: User's manual, appendix A data management module. Part 1: Program [AD-A002871] 075-20322 integration A structural weight estimation program (SWEEP) for [AD-A002852] 075-20302 aircraft. Volume 10: Flutter optimnation A strucutral weight estimation program (SWEEP) for stand-alone program aircraft. Volume 2: Program integration and (AD-A002872] N75-20323 data management module. Part 2: Data A structural weight estimation program (SWEEP) for management module aircraft. Volume 11: Flexible airloads [AD-A002853] 075-20303 stand-alone program A structural weight estimation program (SWEEP) for (AD-A002873] 075-20324 aircraft. Volume 2: Program integration and AIRCRAFT WAKES data management module. Appendix A: Data The aerodynamic characteristics and trailing management module flow charts and FORTRAN lists vortex wake of propeller V/STOL configurations [AD-A002851) 075-203014 A75-28522 A structural weight estimation program (SWEEP) for The dynamic response of aircraft encountering aircraft. Volume 3: Airloads estimation module aircraft wake turbulence [AD-A002854] 075-20305 N75-19170 A structural weight estimation program (SWEEP) for Inviscid to turbulent transition of trailing aircraft. Volume 3: Airloads estimation vortices module. Appendix A: Module flow charts and (NASA-CR-142298] N75-19172 FORTRAN lists. Appendix B: Sample output A flight test investigation of the rolling moments [AD-A002855] 075-20306 induced on a T-37B airplane in the wake of a A structural weight estimation program (SWEEP) for 8-747 airplane aircraft. Volume 4: Material properties, [NASA-TM-X-56031] N75-20221 structure temperature, flutter and fatigue On wake vortex alleviation [AD-A002856] N75-20307 N75-20231

A-6

SUBJECT INDEX APPROACH CONTROL

AIRFOIL PROFILES ALTIMETERS Nonlinear problem of the unsteady flow past an Altimeters - The way ahead airfoil lattice A75-28788 A75-28671 Harowe altitude warning system evaluation Computation of airfoil DRAG profiles [AD-A002583] N75-19241 CREPT-35/1974] N75-19165 ALTITUDE A method for predicting unsteady aerodynamic Harowe altitude warning system evaluation forces on oscillating wings with thickness in [AD-A002583] N75-19241 transonic flow near Mach number 1. Part 1: ALTITUDE CONTROL Two-dimensional theory. Part 2: Rectangular Effects of visual flight display dynamics on wings altitude tracking performance in a flight (NAL-TR-368T-PT-1] N75-19174 simulator An exact solution for transonic potential flow N75-i9 127 past aerofoil sections ALUMINUM ALLOYS (NAL-TE--383] N75-19176 Metallurgical factors affecting high strength AIRFOILS aluminum alloy production Starting vortex, separation bubbles and stall - A A75-28529 numerical study of laminar unsteady flow around Fatigue strength of D16T Duralumin at normal and an airfoil elevated temperatures as a function of the A75-26212 cycling rate Critical analysis and improvement of the A75-28866 source-panel method --- for lift prediction On fatigue crack arresting by a stop-hole in 05-28095 2024-T3 aluminum alloy sheet specimens Survey on two calculation methods in transonic (NAL-TR-359] N75-19413 regime Relation between scatter of fatigue life and S-N A75-28096 curve in aircraft structural aluminium alloy Wind tunnel tests of a symmetrical airfoil with 2021-TI scoop fed slots (NAL-TR-360) N75-19414 [NASA-CR-132568] N75-19183 Design and purchase expectations for fracture AIRFRAMES resistance of 700-series aluminum airframe alloys Digital avionics-overview - Airframe [AD-A002552] N75-20548 manufacturers viewpoint Development of statistical fatigue failure (AIAA PAPER 75-552] A75-26720 characteristics of 0.125 inch 202 14-T3 aluminum Operational use of the OH-i H helicopters in under simulated flight-by-flight loading Arctic environment [AD-A002310] N75-20554 [AD-A002603] N75-19236 Fracture mechanics of tiny cracks near fasteners AIRLINE OPERATIONS in high strength aluminum alloys Ride quality evaluation. I --- aircraft passenger [AD-A002554] N75-20777 comfort assessment AMPLITUDE MODULATION A75-26849 Helicopter rotor-produced modulation and aerial Important aspects of international air cargo field distribution in the band 30 to 76 MHz rate structure, container handling and fuel (RAE-TR-71032] N75-19217 costs effects ANALOG CIRCUITS A75-26948 Determination of derivatives by a model with The next forty years in aviation automatic parameter --- analog circuit N75-20228 N75-i9265 Annual reviews of aircraft accident data US Air ANALOG COMPUTERS Carrier operations, 1973 Determination of aerodynamic derivatives of the (PB-238281/0] N75-20276 FIAT G-91 T3 aircraft from flight tests by means AIRPORT PLANNING of manual analog model matching Propagation of aircraft noise near airports - N75-19257 Effects of hillsides, inversions and source Extraction of flight mechanic derivatives from directionality flight datd by a manual analog matching technique A75-27859 [ESRO-TT-118] N75-20317 Problem of aircraft noise in the vicinity of ANALOG SIMULATION airports Adaptive control system with reference model A75-28222 application to automatic pilots AIRPORT SURFACE DETECTION EQUIPMENT A75-27912 New horizons in air traffic control ANALYSIS OF VARIANCE [AIAA PAPER 75-569] A75-26728 The variability of fatigue damage from flight to AIRPORTS flight Comparison of airport measurements of approach [ARC-CP1297] N75-20297 noise produced by jet aircraft ANECHOIC CHAMBERS A75-27852 The use of Hartmann generators as sources of high AIRSPEED intensity sound in a large absorption flow duct Exploratory wind tunnel tests of a facility shock-swallowing air data sensor at a Mach [AIAA PAPER 75-529] A75-27939 number of approximately 1.83 ANGLE OF ATTACK [NASA-TM-X-56030] N75-20329 Some aspects of performance measurements in Instrument system test. Elliott helicopter air nonsteady flight --- angle of attack and rate of data system climb [AD-A002332] N75-20331 N75-19262 ALGORITHMS ANNULAR NOZZLES Computation of airfoil DRAG profiles Development of acoustic disturbances in supersonic CREPT-35/1974] N75-19165 annular jets Multi-site intermittent positive control A75-26234 algorithms for the discrete address beacon system ANTENNA RADIATION PATTERNS fAD-A001112/2] N75-19214 Helicopter rotor-produced modulation and aerial ALL-WEATHER AIR NAVIGATION field distribution in the band 30 to 76 MHz C-ill All Weather Landing System (AWLS) flight [RAE-TR-74032] N75-19217 test report: Optimization and pre-experimental Antennas, a collection, issue 15 phases [AD-A002646] N75-19551 (AD-A003952] N75-20330 ANTENNAS ALPHANUMERIC CHARACTERS Antennas, a collection, issue 15 The performance in illuminances up to 80,000 lax [AD-A0026 146] N75-19557 of a light emitting diode display having a 3 mm APPROACH CONTROL character height Comparison of airport measurements of approach A75-27526 noise produced by jet aircraft A75-27852

A-i

APPROACH INDICATORS SUBJECT INDEX

Wind models for flight simulator certification of Digital avionics from the viewpoint of ATA --- Air landing and approach guidance and control systems Transport Association of America [AD-A003801 ] N75-20352 [AIAA PAPER 75-551] A75-281$66 APPROACH INDICATORS F-is computational subsystem --- computer systems Evaluation of the Rubinoprocedure for radio design telemetric theodolite positioning [AIAA PAPER 75-590] A75-28470 [AD-A004317] N75-20353 The U.S. Candidate Microwave Landing System - A APPROXIMATION new generation of avionics/ground equipment Notes on the approximate solution of [AIRA PAPER 75-607] A75-28472 lifting-surface theory used in the RAE standard Integrated avionics - Controls and displays for method helicopter IPR operation (ARC-R/M-3752) li75-19188 A75-28786 ARCTIC REGIONS Vibration and temperature survey production Ali-1G Operational use of the UH-1 H helicopters in helicopter Arctic environment [AD-A002063] N75-19231 [AD-A002603] N75-19236 AXIAL FLOW TURBINES AREA NAVIGATION Development and experimental evaluation of a New horizons in air traffic control numerical method for solving the inverse (AIAA PAPER 75-569] A75-26728 axisymmetric problem in an axial turbine stage System approach to civil aircraft navigation using with given velocity digital technology A75-26671 [AIAA PAPER 75-572] A75-28469 Measurement and analysis of the unsteady normal ASPECT RATIO force and pitching moment on an axial flow fan The definition of the motorsegler rotor blade element [DFVLR-SONDDR-424] A75-27596 [AD-A002739] N75-20343 ATS 6 AIIS!MMETRIC FLOW Air Traffic Control demonstration aspects of the Development and experimental evaluation of a Applications Technology Satellite-6 numerical method for solving the inverse (AIAA PAPER 75-562] A75-26723 axisymmetric problem in an axial turbine stage AUTOMATIC FLIGHT CONTROL with given velocity Self-testing digital flight control applications A75-26671 (AIAA PAPER 75-568) A75-26727 A subsonic axisymmetric wake in a viscous gas Digital flight control systems - Considerations in A75-26891 implementation and acceptance Calculation of two-dimensional and axisymmetric [AIAA PAPER 75-577] A75-267314 bluff body potential flow Aircraft guidance for automatic collision avoidance [IC-AEBO-74-07] N75-19191 A75-27178 A concept of flight dynamics control --- for aircraft B A75-27180 BALANCING Adaptive digital system for aircraft control Tests of laser metal removal for future flexible A75-27182 rotor balancing in engines Adaptive control system with reference model [SAE PAPER 750170] A75-26591 application to automatic pilots BEAMS (SUPPORTS) A75-27912 Nonlinear torsional vibrations of thin-walled Digital avionics from the viewpoint of ATA --- Air beams of open section Transport Association of America A75-26'410 [AIAA PAPER 75-551] A75-28866 BELL AIRCRAFT Characteristics of MLS signals and their effect on Estimates of the stability derivatives of a flight control systems . --- Microwave Landing helicopter and a V/STOL aircraft from flight data Systems N75-20250 A75-28791 BENDING MOMENTS Airborne electronics for automated flight systems Influence of fuselage flexibility on the N75- 20232 stress-strain state of the wing Status and trends in active control technology A75-28668 N75-20236 BIBLIOGRAPHIES AUTOMATIC PILOTS Heat transfer in separated and reattached flows - Plight test of a digital guidance and control An annotated review system in a DC-10 aircraft A75-26685 (AIAA PAPER 75-567] A75-26726 BIRDS Adaptive control system with reference model Development of scratch and spall resistant application to automatic pilots windshields - A75-27912 [AD-A002513] N15-20300 Characteristics of ELS signals and their effect on BLOCKING flight control systems --- Microwave Landing The role of rotor blade blockage in the Systems propagation of fan noise interaction tones A75-28791 (AIAA PAPER 15-447] 835-27921 AVIONICS BLOWDOWN WIND TUNNELS Digital avionics-overview - Airframe The disappearance of the wake shock behind a manufacturers viewpoint cylinder in a supersonic flow at high Reynolds [AIAA PAPER 75-552] A75-26720 number Digital avionics - An overview --- Air Traffic 835-26414 Control Radar Beacon System BLUFF BODIES [AIAA PAPER 75-553] A75-26721 Calculation of two-dimensional and azisymmetric Plight-critical digital control system evaluation bluff body potential flow (AIAA PAPER 75-566] A75-26725 (IC-AERO-74-07] N75-19191 Application of digital systems to Army avionics BLUNT BODIES (AIAA PAPER 75-587] 835-26738 Hypersonic flow past pointed and blunt bodies with Digital avionics information system /DAIS/ a concave generatrix integrated test bed development A15-26896 (AIAA PAPER 75-588] A75-26739 Calculation of the flow around blunted, Design of the DAIS control and display core element nonsymmetric cones with large aperture angle Digital Avionics Information System A15-28652 (AIAA PAPER 75-600] A75-26745 Reliability life cycle of a complex electronic airborne equipment A75-27839

A-8

SUBJECT INDEX COCKPITS

BODIES OF REVOLUTION C-i ll 1 AIRCRAFT Experimental aerodynamic characteristics for a C-141 All Weather Landing System (AWLS) flight cylindrical body of revolution with side strakes test report: Optimization and pre-experimental and various noses at angles of attack from 0 phases degrees to 58 degrees and Bach numbers from 0.6 [AD-A003952] N75-20330 to 2.0 CANADA (NASA-TN-X-3130] N75-19181 Quarterly bulletin of the Division of Mechanical BODY-WING CONFIGURATIONS Engineering and the National Aeronautical Noise of model target type thrust reversers for Establishment, 1 October - 31 December 1974 engine-over-the-wing applications (DME/NAE-1974(4) ] N75-20249 A75-27853 Some air cushion technology research in Canada BOEING 707 AIRCRAFT N15-20251 Pan American World Airways, Incorporated Boeing CARBON DIOXIDE 701-3218, N454PA, Pago Pago, American Samoa, 30 Numerical study of heat exchange at the stagnation January 19711 point of a sphere situated in a hypersonic (P8-238478/2) N75-20277 stream of carbon dioxide gas Oceanic air route navigation with envelope match A75-26888 Loran-C CARBURETORS [AD-AGO 3800] N75-20286 A study of carburetor/induction system icing in BOEING 747 AIRCRAFT general aviation accidents A flight test investigation of the rolling moments (NASA-CR-1 143835] 1175-19208 induced on a T-37B airplane in the wake of .a CARGO AIRCRAFT B-747 airplane Important aspects of international air cargo [NASA-TM-X-56031] N75-20221 rate structure, container handling and fuel BOUNDARY LAYER CONTROL costs effects Opportunities for aerodynamic-drag reduction 135-26948 N75-20237 CASCADE FLOW Evaluation of some control-volume techniques for Effect of interference between moving blade rows analysis of shock-boundary layer interactions in on cascade flutter. I - Experiment on compressor supersonic inlets cascade in flexure node (NASA-TM-X-3186] N75-20256 A75-26553 BOUNDARY LAYER EQUATIONS Determination by means of hydraulic analogy of the Hypersonic, viscous gas flow around a wing of transonic flow in a blade cascade small aspect ratio N75-20213 A75-28653 CAVITATION FLOW BOUNDARY LAYER FLOW Cavitating flow past a vibrating thin-section wing Beat transfer in separated and reattached flows - profile An annotated review A75-26895 A75-26685 CERTIFICATION Interpretation of merged layer behavior for wedges Noise certification of aircraft A75-27496 A75-28223 An example of boundary layer flow with two CH-47 HELICOPTER instability regions CH-47A assessment and comparative fleet A75-28680 evaluation: Executive summary report BOUNDARY LATER SEPARATION [AD-A002057] 1115-19232 An experimental investigation of compressor stall CHANNELS (DATA TRANSMISSION) using an on-line distortion indicator and signal An experimental TOHA network for airborne warning conditioner and control systems interoperability (NASA-TM-X-31823 N75-20248 demonstrations BOUNDARY LAYER TRANSITION (AIAA PAPER 15-563) 135-26724 Influence of sound upon separated flow over wings CIRCULAR CYLINDERS A75-27495 The disappearance of the wake shock behind a BOUNDARY LAYERS cylinder in a supersonic flow at high Reynolds Boundary-layer pressure fluctuations at high number Reynolds numbers on a second free-flight test A75-26414 vehicle The three-dimensional character of a cross flow [ABC-CP-1302] 1175-19189 around a circular cylinder Evaluation of some control-volume techniques for A75-28654 analysis of shock-boundary layer interactions in Analysis of thick turbulent jet flowing round: A supersonic inlets circular cylinder [NASA-TN-X-3186] N75-20256 N15-19168 Boundary layer effects in supersonic flow over CIVIL AVIATION cylinder-flare bodies Air Europe: The policy of cooperation among [WRE-REPT-1238 (WR/D) ] 1175-20257 airline companies of the European Six --- French BROADCASTING book TACAN/OME digital data broadcast design plan. 835-26499 Volume 5: Flight test program New horizons in air traffic control (AD-A001 1405/0) 1175-19212 [AIAA PAPER 15-569] A15-26728 TACAN/DBE digital data broadcast design plan. Digital avionics from the viewpoint of ATA --- Air Volume 1: Operational analysis Transport Association of America [AD-A001403/5] 1175-19213 [AIAA PAPER 15-551] A75-28466 BUBBLES Interaction of military/civil position location Starting vortex, separation bubbles and stall - A and reporting systems --- of ATC numerical study of laminar unsteady flow around [AIAA PAPER 75-561] 835-28461 an airfoil System approach to civil aircraft navigation using A75-26212 digital technology [AIAA PAPER 75-572] 835-28469 CLIMBING FLIGHT L. Some aspects of performance measurements in C BAND nonsteady flight --- angle of attack and rate of Dual band airborne antenna study climb (AD-A002043] N75-19219 1175-19262 C-S AIRCRAFT COCKPITS Fatigue-crack growth behavior of C-5A wing control Instrumentation displays for future naval aircraft points [AIAA PAPER 75-599] A75-261414 (AD-A002553] N75-20299 Users manual for 0dB vehicle occupant crash study model, version 2 [AD-A001801) N15-19211

A-9

COLLISION AVOIDANCE SUBJECT INDEX

COLLISION AVOIDANCE A structural weight estimation program (SWEEP) for Aircraft guidance for automatic collision avoidance aircraft. Volume 2: Program integration and A75-27178 data management module. Part 1: Program Flight test evaluation of SECANT VECAS collision integration avoidance system [AD-A002852] N75-20302 [AD-A002281] N75-19220 A strucutral weight estimation program (SWEEP) for COMBUSTION CHAMBERS aircraft. Volume 2: Program integration and Noise generation and transmission in duct combustors data management module. Part 2: Data [AIAA PAPER 75-527] A75-27938 management module Investigation of aircraft combustor noise (AD-A002853] N75-20303 [AD-A0017371 N75-19250 A structural weight estimation program (SWEEP) for COMBUSTION PHYSICS aircraft. Volume 2: Program integration and Aeroacoustics: Jet and combustion noise; duct data management module. Appendix A: Data acoustics --- Book - management module flow charts and FORTRAN lists A75-28629 [AD-A002851] W75-20304 COMBUSTION PRODUCTS A structural weight estimation program (SWEEP) for A study of the effects on mice of smoke and gases aircraft. Volume 3: Airloads estimation module from controlled fires in simulated aircraft cabins [AD-A002854] N75-20305 A75-27073 A structural weight estimation program (SWEEP) for COMFORT aircraft. Volume 3: Airloads estimation Ride quality evaluation. I --- aircraft passenger module. Appendix A: Nodule flow charts and comfort assessment FORTRAN lists. Appendix B: Sample output A75-26849 [AD-A002855] N75-20306 COMMAND AND CONTROL A structural weight estimation program (SWEEP) for An experimental TDNA network for airborne warning aircraft. Volume 4: Material properties, and control systems interoperability structure temperature, flutter and fatigue demonstrations [AD-A002856] N75-20307 [&IAA PAPER 75-563] P.75-26724 A structural weight estimation program (SWEEP) for CONNERCIA9 AIRCRAFT aircraft.. Volume 5: Air induction system and Development of air transport and environmental landing gear modules. Part 1: Air induction requirements --- for air and noise pollution system module reduction [ADA002857] N7520308 A75-28228 A structural weight estimation program (SWEEP) for Annual reviews of aircraft accident data US Air aircraft. Volume 5: Air induction system and carrier operations, 1973 landing gear modules. Part 2: Landing gear [PB-238281/0] N75-20216 module COMPLEX SYSTEMS [AD-A002858] N75-20309 Stability analysis of stochastic composite systems A structural weight estimation program (SWEEP) for application to control of aircraft and aircraft. Volume 6: Wing and empennage module. nonlinear systems Book 1: Technical discussion sections 1 and 2 A75-27919 [AD-A002864] N75-20310 COMPOSITE MATERIALS A structural weight estimation program (SWEEP) for Characterization of advanced composite materials aircraft. Volume 6: Wing and empennage module. for structural design --- of aircraft Book 2: Technical discussion, sections 3 and 4 A75-27695 [AD-A002865] N75-20311 Some trends in aircraft design: Structure A structural weight estimation program (SWEEP) for N75-20235 aircraft. Volume 6: Wing and empennage nodule. COMPRESSIBLE FLOW Book 3: Technical discussion, section 5 The prediction of turbulent heat transfer to wedge [AD-A002866] N75-20312 compression corners and cylinder-flare bodies at A structural weight estimation program (SWEEP) for hypersonic speeds aircraft. Volume 6: wing and empennage module. (IC-AERO-73-03] N75-20264 Appendix A: General information for nodule flow COMPRESSOR BLADES . charts and listings. Appendix B: Program flow Theoretical and experimental studies of charts, overlays (8,0), (14.0), (15,0), (16.0) discrete-tone rotor-stator interaction noise and (17,0) [AIAA PAPER 75-443] A75-27926 [AD-A002859] N75-20313 COMPRESSOR ROTORS A structural weight estimation program (SWEEP) for Impact of turbine modulation on variable-cycle aircraft. Volume 6: Wing and empennage module. engine performance. Phase 1 and 2: Design Appendix C: Program flow charts, overlays (9,0) fabrication and rig test, part 1 and (10,0) [AD-A002543] N75-20337 (AD-A002860] N75-203114 Impact of turbine modulation on variable-cycle A structural weight estimation program (SWEEP) for engine performance. Phase 3: Engine aircraft. Volume 6: Wing and empennage module. modification and sea level test, part 2 Appendix D: Program flow charts, overlay (18,0) [AD-A002544] N75-20338 [AD-A002861] N75-20315 Impact of turbine modulation on variable-cycle A structural weight estimation program (SWEEP) for engine performance. p hase 4: Additional aircraft. Volume 6: Wing and empennage module. hardware design and fabrication, engine Appendix E: Program listings, overlays (8,0), modification, and altitude test, part 3A (14,0), (15,0), (16,0), and (17,0) [AD-A002545] N75-20339 [AD-A002862] N75-20316 Impact of turbine modulation on variable-cycle A structural weight estimation program (SWEEP) for engine performance. Phase 4: Additional aircraft. Volume 6: Wing and empennage module. hardware design and fabrication, engine Appendix F: Program listings, overlays (9,0), modification, and altitude test, part 38 (10,0) and (18,0) [AD-A002546] N75-20340 [AD-A002863] N75-20317 Evaluation program on using compressor bleed air A structural weight estimation program (SWEEP) for as a source of pneumatic power for fluidic aircraft. Volume 7: Fuselage module circuits [AD-A002867] N75-20318 [AD-A002483) N75-20616 A structural weight estimation program (SWEEP) for COMPUTER ASSISTED INSTRUCTION aircraft. Volume 7: Fuselage module. Appendix Field evaluation of model 2 of the computer-based, A: Nodule flow charts and FORTRAN lists. individual trainer for the radar intercept officer Appendix B: Fuselage module sample output [AD-A002705] N75-19278 [AD-A002868] N75-20319 COMPUTER PROGRAMMING & structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 8: Programmer's manual aircraft. Volume 1: Executive summary [AD-A002869] N75-20320 [AD-A002850] N75-20301 A structural weight estimation program (SWEEP) for aircraft. Volume 9: User's manual [AD-A002870] N75-20321

A-1O

SUBJECT INDEX CORNER FLOE

A structural weight estimation program (SWEEP) for Technical evaluation report on Fluid Dynamics aircraft. Volume 9: User's manual, appendix A Panel Symposium on V/STOL Aerodynamics [AD-A002871] N75-20322 [AGARD-AR-78] N75-19585 A structural weight estimation program (SWEEP) for The future of aeronautics aircraft. Volume 10: Flutter optimation [NASA-CR-142559] N75-20222 stand-alone program CONICAL CAMBER [AD-A002872] N75-20323 Flow past conically-cambered slender delta wings A structural weight estimation program (SWEEP) for with leading-edge separation aircraft. Volume 11: Flexible airloads (ARC-R/11-3748) N75-19186 stand-alone program CONICAL FLOW [AD-A002873] N75-20324 Calculation of heat transfer at the lines of flow COMPUTER PROGRAMS of a three-dimensional boundary layer in a Software engineering of a navigation and guidance nonuniform external flow system for commercial aircraft A75-26894 [AIAA PAPER 75-575] A75-26733 Calculation of the flow around blunted, Improvements to the SADSAN computer program for nonsymmetric cones with large aperture angle aeroelasticity analysis A75-28652 (NASA-CR-132617] N75-19173 CONICAL NOZZLES TRW vortex-lattice method subsonic aerodynamic The impingement of non-uniform, axisymmetric, analysis for multiple-lifting-surfaces (N. supersonic lets on a perpendicular flat plate surface) TRW program number HAO10B A75-26684 [NASA-CR-128588] N75-19178 CONSTRUCTION MATERIALS An improved automated structural optimization Some trends in aircraft design: Structure program N75-20235 (AD-A002688] N75-19237 CONTROL BOARDS OH-58A propulsion system vibration investigation A model based technique for the design of flight [AD-A002672] N75-20341 directors --- optimal control models Digital flight control systems for tactical N75-19140 fighters. Volume 2: Documentation of the CONTROL CONFIGURED VEHICLES digital control analysis software (DIGIKON) Fly-by-wire and control configured vehicles - [AD-A002327] N75-203149 Rewards and risks COMPUTER SYSTEMS DESIGN A75-27367 Digital computer design guidelines for a full CONTROL SIMULATION authority fly-by-wire flight control system Adaptive control system with reference model (AIAA PAPER 75-570) A75-26729 application to automatic pilots Digital avionics information system /DAIS/ A75-21912 integrated test bed development A study for active control research and validation [AIRA PAPER 75-588] A75-26739 using the Total In-Flight Simulator (TIFS) F-15 computational subsystem --- computer systems aircraft design [NASA-CR-132614] N75-19271 [AIAA PAPER 75-590] A75-281470 CONTROL STABILITY A new flight test data system for NASA Low-speed wind-tunnel tests of a 1/10-scale model aeronautical flight research of a blended arrow advanced supersonic transport A75-28774 aerodynamic control and stability The development of a serial P.C.H. instrumentation (NASA-TM-X-72671] N75-19226 system CONTROL SURFACES A75-28797 Wind tunnel tests of a symmetrical airfoil with COMPUTER TECHNIQUES scoop fed slots Development and experimental evaluation of a [NASA-CR-132568] N75-19183 numerical method for solving the inverse CONTROL THEORY axisyminetric problem in an axial turbine stage A concept of flight dynamics control --- for with given velocity aircraft - A75-26671 A75-27180 The benefits of real time computer analysis of CONTROLLABILITY experimental aircraft flight test data General aviation handling qualities research A75-28801 N75-19204 COMPUTERIZED DESIGN Flight simulation of a Wessex helicopter: A Rotating engine design and cycle analysis program validation exercise [AD-A0023114] N75-2032 [ARC-CP-1299] N75-20298 COMPUTERIZED SIMULATION CONVECTIVE HEAT TRANSFER Paper pilot ponders supersonic transports Heat transfer in separated and reattached flows - H75-19135 An annotated review Real-time simulation of let engines with a digital A75-26685 computer(1), fabrication and characteristics of CONVERGENT-DIVERGENT NOZZLES the simulator A method of profiling short two-dimensional nozzles [RAE-LIB-TRANS-1768] N75-19274 for transonic wind tunnels Computer simulation of maintenance for A75-26880 multi-mission RPV's Some recent developments in supersonic jet noise [AD-A003351] N75-20253 reduction CONCAVITY [AIAA PAPER 15-502] A15-21937 Hypersonic flow past pointed and blunt bodies with Survey on two calculation methods in transonic a concave generatrix regime A75-26896 Al5-28096 CONCORDE AIRCRAFT COOLING SYSTEMS A comparison of flight loads counting methods and Multi-slot film cooling of supersonic aircraft their effects on fatigue life estimates using using air as a coolant data from Concorde [AD-A002673] N15-19239 [ARC-CP-1304] N75-19227 Internal-combustion engine/vapour cycle combination CONDUCTIVE HEAT TRANSFER [OUEL-1091/74] N75-20336 Effects of friction and heat conduction on sound CORE STORAGE propagation in ducts Design of the DAIS control and display core element [AIAA PAPER 75-520] A75-28349 Digital Avionics Information System CONFERENCES [AIAA PAPER 15-600] A15-26745 General Aviation Aircraft Safety CORNER FLOW [AD-A003124] N75-19199 The expansion of a hypersonic turbulent boundary Determination of aircraft characteristics from layer at a sharp corner flight tests A15-26466 [ESRO-TT-104] N75-19252

)I]

COST ANALYSIS SUBJECT INDEX

COST ANALYSIS DATA PROCESSING Economics: General aviation cost factors The benefits of real time computer analysis of N75-19206 experimental aircraft flight test data COST EFFECTIVENESS 875-28801 What have we learned from applying digital Testing the MLS Doppler concept technology to cabin/passenger multiplex systems A75-28802 cost and weight analysis Parameter identification applied to aircraft [8186 PAPER 75-574] A75-26732 [CRANFIELD-AERO-26] N75-19177 Important aspects of international air cargo An aircraft application of system identification rate structure, container handling and fuel in the presence of state noise costs effects [AD-8001936] N75-19234 675-26948 Determination of the parameters of a system of Evaluation of active control technology for short equations of motion from flight test data haul aircraft --- cost effectiveness least squares method [NASA-CR-137634] N75-20344 N75-19263 CRACK PROPAGATION DATA RECORDING On fatigue crack arresting by a stop-hole in A specialised recording system for the measurement 2024-T3 aluminum alloy sheet specimens of helicopter rotor blade performance in flight [NAL-TR-359) N75-19413 875-28770 Fatigue-crack growth behavior of C-58 wing control The development of a serial P.C.M. instrumentation points system [60-6002553] N75-20299 A75-28797 Fracture mechanics of tiny cracks near fasteners DATA SYSTEMS in high strength aluminum alloys A new flight test data system for NASA [AD-A002554] N75-20777 aeronautical flight research CRACKING (FRACTURING) A75-28774 Stress intensity factors for some through-cracked DATA TRANSMISSION fastener holes SEEK BUS - A time division multiple access system A75-28236 ATC applications CRASH INJURIES [8166 PAPER 75-564] A75-28468 Users manual for UCIN vehicle occupant crash study TACAN/DRE digital data broadcast design plan. model, version 2 Volume 1: Operational analysis [60-8001801] N75-19211 [60-6001403/5] N75-19213 CRASH LANDING Flight test evaluation of SECANT PECkS collision Analysis of wreckage --- aircraft accident avoidance system investigation [AD-A002281 J N75-19220 675-26533 DC 9 AIRCRAFT CRASHES Aircraft accident report. Eastern Air Lines, Inc. The aircraft accident --- German book McDonnell-Douglas DC 9-31, N8967E Akron-Conton 675-26498 Regional Airport, North Canton, Ohio, 27 Nov. 1973 CREEP PROPERTIES [P8-238637/3] N75-20274 High-temperature alloys and the aircraft gas turbine Delta Air Lines Incorporated McDonnell Douglas A75-27877 DC-9-32, N3323L, Chattanooga Municipal Airport, CROSS FLOW Chattanooga, Tennessee An experimental study of the structure and [P0-238479/0] N75-20278 acoustic field of a jet in a cross stream Feasibility of adapting a thin film permeable (6188 PAPER 75-460] 875-28348 membrane to jet transport fuel tank meEting The three-dimensional character of a cross flow system around a circular cylinder [80-8003799] N75-20295 675-28654 DC 10 AIRCRAFT CYCLIC LOADS Flight test of a digital guidance and control Fatigue strength of D16T Duralumin at normal and system in a DC-10 aircraft elevated temperatures as a function of the [AIAA PAPER 75-567) A75-26726 cycling rate DELTA WINGS A75-28866 Longitudinal aerodynamic derivatives of a slender delta wing research aircraft extracted from flight data D [CRANFIELD-AERO-27] N75-19175 DATA ACQUISITION Flow past conically-cambered slender delta wings Analysis of general aviation accident records with leading-edge separation N75-19200 [ARC-R/M-3748] N75-19186 An aircraft application of system identification Longitudinal aerodynamic derivatives of a slender in the presence of state noise delta-wing research aircraft extracted from [AD-A001936] N75-19234 flight data Computer simulation of maintenance for [CRANFIELD-AERO-27] N75-20258 multi-mission RPV5 DESIGN ANALYSIS (80-8003351] N75-20253 Digital computer design guidelines for a full Exploratory wind tunnel tests of a authority fly-by-wire flight control system shock-swallowing air data sensor at a Mach [AIAA PAPER 75-570] A75-26729 number of approximately 1.83 DIFFERENTIAL EQUATIONS [NASA-TM-X-56030] N75-20329 Dynamics of the motion of a body with allowance DATA LINKS for the unsteady state of the flow about it SEEK BUS - A time division multiple access system [NASA-TT-F-16133] N75-19179 ATC applications DIGITAL COMMAND SYSTEMS [AIAA PAPER 75-564] 875-28468 Development of a remote digital augmentation Provisional message formats for the DABS/NAS system and application to a remotely piloted interface (revision 1) research vehicle (FAA-RD-74-63-A] N75-1)216 [NASA-TN-D-7941] N75-20293 DATA MANAGEMENT DIGITAL COMPUTERS A strucutral weight estimation program (SWEEP) for Digital computer design guidelines for a full aircraft. Volume 2: Program integration and authority fly-by-wire flight control system data management module. Part 2: Data [8186 PAPER 75-570] 875-26729 management module Paper pilot ponders supersonic transports (AD-A002853] N75-20303 H75-19135 A structural weight estimation program (SWEEP) for Real-time simulation of jet engines with a digital aircraft. Volume 2: Program integration and computer (1), fabrication and characteristics of data management module. Appendix A: Data the simulator management module flow charts and FORTRAN lists [RAE-LIB-TRANS-1768] N75-19274 [AD-A002851 ] N75-20304

A-12 SUBJECT INDEX ECONOMIC FACTORS

DIGITAL NAVIGATION A study on aircraft map display location and System approach to civil aircraft navigation using Orientation --- effects of map display location digital technology on manual piloting performance (AIAA PAPER 75-572] A75-28469 N75-19128 DIGITAL SYSTEMS A tactual pilot aid for the approach-and-landing Flight-critical digital control System evaluation task: Inflight studies [AIAA PAPER 75-566] A75-26725 N75-19131 Self-testing digital flight control applications Evaluation of tactual displays for flight control [AIAA PAPER 75-568] A75-26727 N75-19132 Digital flight control systems - Considerations in A display evaluation methodology applied to implementation and acceptance Vertical situation displays [AIAA PAPER 75-577] 135-26734 N75-19137 Application of digital systems to Army avionics Improvements in pilot/aircraft-integration by (AIAR PAPER 75-587] A75-26738 advanced Contact analog displays Digital avionics information system /DAIS/ N75-19141 integrated test bed development Flight path control and performance analysis, (AIAA PAPER 75-5881 A75-26739 phases 1 and 2. Integrated display, phase 3 Design of the DAIS control and display core element [AD-A002014] N75-19269 Digital Avionics Information System DISTANCE MEASURING EQUIPMENT [AIAA PAPER 75-600] A75-26745 Take-off instrument for assessing achieved Adaptive digital system for aircraft control performance during take-off and a take-off A75-27182 accident analysed in context Design of a digital-stability augmentation and A75-28769 control system with gust alleviation and modal DOPPLER NAVIGATION suppression Airborne equipment for use with the microwave A75-28432 landing system Digital avionics from the viewpoint of ATA --- Air A75-28790 Transport Association of America The range of airborne processing available to the (AIAA PAPER 75-551] A75-28466 future user of the Doppler MLS --- Microwave TACAN,'DNE digital data broadcast design plan. Landing Systems Volume 5: Flight test program A75-28792 (AD-A001405/0] 875-19212 Testing the MLS Doppler concept TACAN/DRE digital data broadcast design plan. A75-28802 Volume 1: Operational analysis DOWN WASH (AD-A001403/5] N75-19213 Notes on the approximate solution of Digital flight control system for tactical lifting-surface theory used in the RAE standard fighter. Volume 1: Digital flight control method system analysis [ARC-R/M-3752] N75-19188 (AD-A002320] 875-20348 DRAG Digital flight control systems for tactical Computation of airfoil DRAG profiles fighters. Volume 2: Documentation of the [REPT-35/1974] 875-19165 digital control analysis software (DIGIKON) DRAG REDUCTION [AD-A002327] 875-20349 Opportunities for aerodynamic-drag reduction DIGITAL TECHNIQUES N75-20237 Digital avionics-overview - Airframe DUCTED FAN ENGINES manufacturers viewpoint Unified analysis of ducted turbomachinery noise (AIAA PAPER 75-552] A75-26720 A75-27861 Digital avionics - An overview --- Air Traffic DUCTED FLOW Control Radar Beacon System Noise generation and transmission in duct combustors [AIAA PAPER 75-553] A75-26721 [AIAA PAPER 75-527] A75-27938 What have we learned from applying digital DYNAMIC CHARACTERISTICS technology to cabin/passenger multiplex systems Determination of the dynamic characteristics of a cost and weight analysis helicopter by the branch-nodes method [AIAA PAPER 75-574] A75-26732 A75-26479 DIRECTIONAL CONTROL Shake test of rotor test apparatus in the 40- by Integrated avionics - Controls and displays for 80-foot wind tunnel helicopter IFR operation (NASA-TM-X-62418] N75-20350 A75-28786 DYNAMIC CONTROL Major Item Special Study (MISS), OH-1C tail rotor A concept of flight dynamics control --- for blade aircraft (AD-A001714] 875-19230 A75-27180 DIRECTIONAL STABILITY DYNAMIC LOADS Flight determination of the rudder power and Dynamic loads and structural criteria study directional stability of the Pairey Delta 2 military helicopters aircraft using a wingtip parachute (AD-A001739] 875-19195 (ARC-CP-1298) N75-19267 DYNAMIC STRUCTURAL ANALYSIS DISPLAY DEVICES Rotation in vibration, optimization, and Software engineering of a navigation and guidance aeroelastic stability problems system for commercial aircraft N75-19167 [AIAA PAPER 75-575] A75-26733 Dynamic loads and structural criteria study Instrumentation displays for future naval aircraft military helicopters (AIAA PAPER 75-599] A75-26744 (AD-A001739] N75-19195 Design of the DAIS control and display core element Digital Avionics Information System (AIAA PAPER 75-600] A75-26745 E The performance in illuminances up to 80,000 lux ECONOMIC ANALYSIS of a light emitting diode display having a 3 mm Air Europe: The policy of cooperation among character height airline companies of the European Six --- French A75-27526 book A new centralised warning display for aircraft A75-26499 A75-28785 ECONOMIC FACTORS Integrated avionics - Controls and displays for Important aspects of international air cargo helicopter IFR operation rate structure, container handling and fuel A75-28786 costs effects Altimeters - The way ahead A75-26948 A75-28788 Economics: General aviation cost factors N75-19206 Problems of designing passenger aircraft (NASA-TT-F-808] N75-19223

A-13

EDUCATION SUBJECT INDEX

EDUCATION ENGINE INLETS Aeronautics in the American society Elementary method of graphic replotting of a 975-20223 characteristic of an uncooled turbocompressor EIGEI VALUES when the intake temperature and number of Eigenvalue/'eigenvectOr assignment for revolutions are varied multivariable systems --- linear state feedback A75-26672 control Low speed and angle of attack effects on sonic and A75-26312 near-sonic inlets BIGEN VECTORS (NASA-cR-134778] 875-19184 Eigenvalue/eigenvectOr assignment for ENGINE NOISE multivariable systems --- linear state feedback Spinning mode sound propagation in ducts with control acoustic treatment A75-26312 A75-27854 ELASTIC DEFORMATION Unified analysis of ducted turbomachinery noise Allowance for the elastic deformation of the wing 175-27861 in its own plane in the calculation of the Radiation of duct noise out through a jet flow skewsymmetric vibrations of an aircraft with a acoustic field model for aircraft engine small-aspect-ratio wing (AIAA PAPER 75-457] A75-27928 A75-28687 An investigation of the noise from a scale model ELECTRIC EQUIPMENT of an engine exhaust system --- turbojet noise Airborne electronics for automated flight systems measurement 875-20232 [ALIA PAPER 75-459] 175-27929 ELECTRO-OPTICS Noise generation and transmission in duct combustors Astrolabe - A synthetic circular aperture system (AIAA PAPER 75-527] A75-27938 for landing and navigation The use of Hartmann generators as sources of high A75-28793 intensity sound in a large absorption flow duct ELECTROMAGNETIC PULSES facility Wide bandwidth optical telemetry link for ground [AIAA PAPER 75-529] 175-27939 testng of equipment in high EMI environments Classification problems of aircraft noise --- far A75-28781 field measurements ELECTRON BEAM WELDING A75-27943 Sound welds in wing boxes assured by three Jet noise suppressors for turbojet engines techniques A75-28227 175-26898 AeroacousticS: Jet and combustion noise; duct ELECTRONIC COUNTERMEASURES acoustics --- Book Reliability life cycle of a complex electronic A75-28629 airborne equipment Influence of multitube mixer nozzle geometry on A75-27839 CTOL-OTW jet noise shielding ELECTRONIC EQUIPMENT TESTS [NASA-TM-X-71681] 875-19246 Reliability life cycle of a complex electronic Comparison of parametric duct-burning turbofan and airborne equipment non-afterburning turbojet engines in a Mach 2.7 A75-27839 transport ELEVATORS (CONTROL SURFACES) [NASA-TM-I-71679] 875-19247 A method for calculating unsteady forces due to ENGINE TESTS interaction between tail surfaces Miniature probes for use in gas turbine testing A75-26477 [SAE PAPER 750094] 175-26589 ENERGY METHODS Development of an R. F. telemetry system --- for Qualitative analysis of a family of extremuins in a aircraft engine stress and temperature data problem involving optimal control of aircraft A75-28778 notion Performance of an isolated two-dimensional A75-28676 variable-geometry wedge nozzle with translating ENGINE DESIGN shroud and collapsing wedge at speeds up to Mach By the application of power /21st Cayley 2.01 Memorial Lecture/ --- technical survey of [NASA-TN-D-7906] 875-20247 aircraft engines ENVIRONMENT SIMULATION A75-27368 Wind models for flight simulator certification of The role of rotor blade blockage in the landing and approach guidance and control systems propagation of fan noise interaction tones (AD-A003801] 875-20352 [lIlA PAPER 75-447] 175-27927 ENVIRONMENTAL MONITORING Part load specific fuel consumption of gas turbines USA? aircraft takeoff length distances and A75-28650 clinibout profiles Metal matrix composites for aircraft propulsion (AD-A001826] 875-19878 systems ENVIRONMENTAL TESTS (NASA-TM-X-71685] 875-19245 Vibration and temperature survey production 18-10 Impact of turbine modulation on variable-cycle helicopter engine performance. Phase 1 and 2: Design [AD-A002063] 875-19231 fabrication and rig test, part 1 EQUATIONS OF MOTION (AD-A002543] N75-20337 Determination of the parameters of a system of Impact of turbine modulation on variable-cycle equations of motion from flight test data engine performance. Phase 3: Engine least squares method modification and sea level test, part 2 N75-19263 (AD-A002544] 875-20338 EUROPEAN AIRBUS Impact of turbine modulation on variable-cycle Airbus A 300 - Comparison of the flight test engine performance. Phase 4: Additional results with the flight performance and flight hardware design and fabrication, engine characteristics determined on the basis of modification, and altitude test, part 3A theory and wind tunnel tests [AD-A002545] 875-20339 A75-27980 Impact of turbine modulation on variable-cycle EUROPEAN SPACE PROGRAMS engine performance. Phase 4: Additional European aeronautics and astronautics at the hardware design and fabrication, engine crossroads modification, and altitude test, part 3B A75-27981 [AD-A002546] 875-20340 EVALUATION Rotating engine design and cycle analysis program Comparison of evaluation procedures for the (AD-A002314] 875-20342 determination of flight-mechanical coefficients and derivatives from flight tests --- Fiat G-91 T3 aircraft N75-19254

A-14

SUBJECT INDEX FLIGHT CONTROL

EXHAUST GASES FEEDBACK CONTROL PLT 27 gas turbine engine exhaust emission and Eigenvalue/eigenvector assignment for noise measurements multivariable systems --- linear state feedback [AD-A001728] 875-1 9251 control USAF aircraft takeoff length distances and A75-26312 climbout profiles FIGHTER AIRCRAFT [AD-A001826] 875-1 9878 Digital flight control system for tactical EXHAUST NOZZLES fighter. Volume 1: Digital flight control Supersonic jet noise suppression with multitube system analysis nozzle/ejectors [AD-A002320] N75-20348 [AIAA PAPER 75-501] A75-2 7936 Digital flight control systems for tactical EXHAUST SYSTEMS fighters. Volume 2: Documentation of the An investigation of the noise from a scale model digital control analysis software (DIGIKON) of an engine exhaust system --- turbojet noise (AD-A002327] 875-20349 measurement FINITE DIFFERENCE THEORY [AIAA PAPER 75-459) A75-2 7929 Survey on two calculation methods in transonic Internal-combustion engine/vapour cycle combinat ion regime [OUEL-1097/74) 875-2 0336 A75-28096 EXTERNALLY BLOWN FLAPS Calculation of the flow around blunted, Propulsive-lift noise of an upper surface blown nonsymmetric cones with large aperture angle flap configuration A75-28652 [AIAA PAPER 75-470] A75-2 7931 FINITE ELEMENT METHOD EXTEEMUM VALUES A theoretical method for calculating the Qualitative analysis of a family of extremulas in aerodynamic characteristics or arbitrary problem involving optimal control of aircraft ejector-jet-flapped wing: Theoretical analysis motion [AD-A002319] 875-20271 A75-28676 FIRE EXTIRGUISERS Environmental and operating requirements for fire extinguishing systems on advanced aircraft F [AD-A001640] 875-19228 F-14 AIRCRAFT FIRES Sound welds in wing boxes assured by three A study of the effects on mice of smoke and gases techniques from controlled fires in simulated aircraft cabins A75-26898 A75-27073 F-iS AIRCRAFT FLAME RETARDANTS F-iS computational subsystem --- computer systems A study of the effects on mice of smoke and gases design from controlled fires in simulated aircraft cabins [AIAA PAPER 75-590] A75-28470 A75-27073 F-100 AIRCRAFT FLAT PLATES Parameter identification applied to aircraft A non-uniqueness of the hypersonic boundary layer [CHANFIELD-AERO- 26) 875-20259 A75-26195 FAILURE ANALYSIS On the viscous flow about the trailing edge of a Reliability life cycle of a complex electronic rapidly oscillating plate airborne equipment A75-26469 A75-27839 The impingement of non-uniform, azisymmetric, FASTENERS supersonic jets on a perpendicular flat plate Stress intensity factors for some through-cracked A75-26684 fastener holes Interpretation of merged layer behavior for wedges A75-28236 A75-27496 FATIGUE (MATERIALS) A wake source model for an inclined flat plate in on fatigue crack arresting by a stop-hole in a uniform stream 2024-73 aluminum alloy sheet specimens [XC-AERO-74708) 875-19192 (NAL-TR-359) 875-19413 FLEXIBLE BODIES Fatigue-crack growth behavior of C-SA wing control Influence of fuselage flexibility on the points stress-strain state of the wing (AD-A002553) 875-20299 A75-28668 FATIGUE LIFE FLIGHT ALTITUDE A comparison of flight loads counting methods and A new J band pulsed radar altimeter their effects on fatigue life estimates using A75-28787 data from Concorde Altimeters - The way ahead [ARC-CP-1304] N75-19221 A75-28788 Relation between scatter of fatigue life and S-N FLIGHT CHARACTERISTICS curve in aircraft structural aluminium alloy Pitch paper pilot revisited --- methods for 2024-74 predicting handling qualities of aircraft in pitch [NAL-TR-360] 875-19414 N75-19133 The variability of fatigue damage from flight to Helicopter flight regimes flight [AD-A001220] 875-19268 [ARC-CP-1297] 875-20297 Parameter identification applied to aircraft A structural weight estimation program (SWEEP) for (CRANFIELD-AEEO-26) 875-20259 aircraft. Volume 4: Material properties, Flight simulation of a Wessex helicopter: A structure temperature, flutter and fatigue validation exercise [AD-A002856] N75-20307 [ARC-CP-1299] 875-20298 Development of statistical fatigue failure Extraction of flight mechanic derivatives from characteristics of 0.125 inch 2024-73 aluminum flight data by a manual analog matching technique under simulated flight-by-flight loading [ESEO-TT-118] 875-20347 [AD-A002310] 875-20554 FLIGHT CONTROL FATIGUE TESTS Flight-critical digital control system evaluation Fatigue strength of D16T Duralumin at normal and (AIAA PAP2R 75-566] A75-26725 elevated temperatures as a function of the Digital computer design guidelines for a full cycling rate authority fly-by-wire flight control system A75-28866 [AIAA PAPER 75-510] A75-26729 Design and fatigue testing of integral armored Qualitative analysis of a family of extremums in a servo actuator modified trunnion problem involving optimal control of aircraft (AD-A002069] N75-19235 motion FD 2 AIRCRAFT A75-28676 Flight determination of the rudder power and Evaluation of tactual displays for flight control directional stability of the Fairey Delta 2 N75-19132 aircraft using a wingtip parachute [ARC-CP-1298] 875-19267

A-15

PLIGHT HAZARDS SUBJECT INDEX

Mechanics of optimum three-dimensional notion of Development of statistical fatigue failure aircraft in the atmosphere characteristics of 0.125 inch 2024-T3 aluminum (NASA-TT-P-777) N75-19182 under simulated flight-by-flight loading Flight path control and performance analysis, (AD-A002310] 1175-20554 phases 1 and 2. Integrated display, phase 3 FLIGHT SIMULATORS (AD-A002014) N75-19269 Effects of visual flight display dynamics on N study for active control research and validation altitude tracking performance in a flight using the Total In-Flight Simulator (TIPS) simulator aircraft N75-19127 [NASA-CR-132614] N75-19271 A study for active control research and validation Status and trends in active control technology using the Total In-Flight Simulator (TIPS) N75-20236 aircraft Digital flight control system for tactical [NASA-CR-132614] N75-19271 fighter. Volume 1: Digital flight control Real-time simulation of jet engines with a digital system analysis computer(1), fabrication and characteristics of (AD-A002320] N75-20348 the simulator Digital flight control systems for tactical [RAE-LIB-TRANS-1768] 1175-19274 fighters. Volume 2: Documentation of the Wind models for flight simulator certification of digital control analysis software (DIGIKON) landing and approach guidance and control systems [AD-A002327] N75-20349 (AD-A003801] 1175-20352 PLIGHT HAZARDS FLIGHT STABILITY TESTS The dynamic response of aircraft encountering Estimates of the stability derivatives of a aircraft wake turbulence helicopter and a V/STOL aircraft from flight data N75-19170 A75-28201 Analysis of general aviation accident records FLIGHT TEST VEHICLES N75-19200 Boundary-layer pressure fluctuations at high Development of scratch and spall resistant Reynolds numbers on a second free-flight test windshields vehicle (AD-A002513] N75-20300 [ARC-CP-1302] N75-19189 FLIGHT INSTRUMENTS FLIGHT TESTS Instrumentation displays for future naval aircraft Plight test of a digital guidance and control [AIAA PAPER 75-599] A75-26744 system in a DC-10 aircraft Effects of visual flight display dynamics on [AIAA PAPER 75-567] A75-26726 altitude tracking performance in a flight A pilots report concerning the VIOL VAK 191 8 simulator A75-26900 N75-19127 Airbus A 300 - Comparison of the flight test A study on aircraft map display location and results with the flight performance and flight orientation --- effects of map display location characteristics determined on the basis of on manual piloting performance theory and wind tunnel tests N75-19128 A75-27980 A tactual pilot aid for the approach-and-landing Flight tests with the V/STOL experimental aircraft task: Inflight studies VAK 191 B N75-19131 A75-27985 A conformal head-up display for the visual approach A specialised recording system for the measurement N75-19138 of helicopter rotor blade performance in flight C-141 All Weather Landing System (AWLS) flight A75-28770 test report: Optimization and pre-experimental Application of a new slip-ringless propeller blade phases measurement system [AD-A003952] N75-20330 A75-28771 Instrument system test. Elliott helicopter air A new flight test data system for NASA data system aeronautical flight research [AD-A002332] N75-20331 A75-28774 FLIGHT MECHANICS Astrolabe - A synthetic circular aperture system A concept of flight dynamics control --- for for landing and navigation aircraft A75-28793 A75-27180 The development of a serial P.C.H. instrumentation Extraction of flight mechanic derivatives from system flight data by a manual analog matching technique A75-28797 [ESRO-TT-118] 1175-20347 The benefits of real time computer analysis of FLIGHT PATHS experimental aircraft flight test data Take-off instrument for assessing achieved A75-28801 performance during take-off and a take-off A tactual pilot aid for the approach-and-landing accident analysed in context task: Inflight studies A75-28769 N75-19131 The STRADA flight path tracking system Parameter identification applied to aircraft [RAE-LIB-TRANS-1813] N75-19209 (CRANFIELD-AERO-26) N15-19117 FLIGHT SAFETY Natural icing tests. OH-1H helicopter Self-testing digital flight control applications [AD-A002077] N75-19194 (AIAA PAPER 75-568] A75-26727 TACAN/DME digital data broadcast design plan. Natural icing tests. UH-1H helicopter Volume 5: Flight test program (AD-A002077] N75-19194 (AD-A001405/0] 1175-19212 Design considerations for stall/spin avoidance An aircraft application of system identification N75-19205 in the presence of state noise Economics: General aviation cost factors [AD-A001936] 1175-19234 1175-19206 Determination of aircraft characteristics from Manufacturers overview flight tests H75-19207 [ESRO-TT-104] 1175-19252 PLIGHT SIMULATION Comparison of evaluation procedures for the Paper pilot ponders supersonic transports determination of flight-mechanical coefficients M75-19135 and derivatives from flight tests --- Fiat G-91 An aircraft application of system identification 13 aircraft in the presence of state noise 1175-19254 [AD-A001936) R75-19234 Manual evaluation of special flying maneuvers for Flight simulation of a Wessex helicopter: A the determination of flight-mechanical validation exercise coefficients and derivatives from flight tests [ARC-CP-1299] 1175-20298 longitudinal and lateral stability of 0-91-13 aircraft N75-19255

A-16

SUBJECT INDEX FORTRAN

Determination of aerodynamic derivatives of the P1.0W MEASUREMENT FIAT G-91 13 aircraft from flight tests by means Experimental and theoretical analysis of three of manual analog model matching dimensional turbulent boundary layers in a B75-1-9257 curved supersonic channel Evaluation of flight test of the FIAT G-91 13 by A75-26476 means of the method of forced oscillations Miniature probes for use in gas turbine testing N75-19258 [SAE PAPER 750094] A75-26589 Evaluation of flight tests of the FIAT G-91 13 by Determination by means of hydraulic analogy of the means of regression analysis transonic flow in a blade cascade N75-19259 375-20213 A SAAB-SCANIA developed method for obtaining FLOW STABILITY stability derivatives from flight tests An example of boundary layer flow with two m75-19260 instability regions Characteristics of the AJ 37 aircraft: Comparison A75-28680 of the results of wind tunnel and flight tests FLOW VELOCITY noting elasticity correction for wind tunnel An example of boundary layer flow with two model instability regions N75-19261 A75-28680 Some aspects of performance measurements in FLOW VISUALIZATION nonsteady flight --- angle of attack and rate of The aerodynamic characteristics and trailing climb vortex wake of propeller V/STOL configurations N75-19262 A75-28522 Determination of the parameters of a system of FLUID DYNAMICS equations of motion from flight test data Technical evaluation report on Fluid Dynamics least squares method Panel Symposium on V/STOL Aerodynamics N75-19263 [AGARD-AR-18] N15-19585 Determination of derivatives by a model with FLUIDIC CIRCUI'S automatic parameter --- analog circuit Wind tunnel tests of a symmetrical airfoil with N75-19265 scoop fed slots Selected examples of the evaluation of VAK 191 B [NASA-CR-132568) N75-19183 flight tests -- roll control characteristic in Evaluation program on using compressor bleed air hovering flight as a source of pneumatic power for fluidic N75-19266 circuits A flight test investigation of the rolling moments [AD-A002483] N75-20676 induced on a 1-378 airplane in the wake of a FLUTTER 8-797 airplane A structural weight estimation program (SWEEP) for [NASA-TM-X-56031] N75-20221 aircraft. Volume 4: Material properties, FLIGHT TRAINING structure temperature, flutter and fatigue Field evaluation of model 2 of the computer-based, [AD-A002856] N15-20301 individual trainer for the radar intercept officer A structural weight estimation program (SWEEP) for [AD-A002705] N75-19278 aircraft. Volume 10: Flutter optimation FLOW CHARACTERISTICS stand-alone program Study of transonic flow over various bodies (AD-A002872] N15-20323 N75-19169 FLUTTER ANALYSIS Inviscid to turbulent transition of trailing Effect of interference between moving blade rows vortices on cascade flutter. I - Experiment on compressor [NASA-CR-142298] N75-19172 cascade in flexure node On wake vortex alleviation A75-26553 N75-20231 FLY BY WIRE CONTROL FLOW CHARTS Self-testing digital flight control applications A structural weight estimation program (SWEEP) for (AIAA PAPER 15-568) A75-26727 aircraft. Volume 2: Program integration and Digital computer design guidelines for a full data management module. Appendix A: Data authority fly-by-wire flight control system management module flow charts and FORTRAN lists [AIAA PAPER 75-570] A75-26129 [AD-A00 2851] N75-20304 Fly-by-wire and control configured vehicles - A structural weight estimation program (SWEEP) for Rewards and risks aircraft. Volume 6: Wing and empennage module. A15-21361 Appendix A: General information for module flow Status and trends in active control technology charts and listings. Appendix B: Program flow N15-20236 charts, overlays (8,0), (19,0), (15,0), (16,0) FORCE DISTRIBUTION and (17,0) Lifting surface theory for a rotating subsonic or (AD-A002859] N75-20313 transonic blade row A structural weight estimation program (SWEEP) for [ARC-R/11-3140) N75-19185 aircraft. Volume 6: Wing and empennage module. Notes on the approximate solution of Appendix C: Program flow charts, overlays (9,0) lifting-surface theory used in the RAE standard and (10,0) method (AD-A002860] N75-20314 [ARC-R/M-3152] N15-19188 A structural weight estimation program (SWEEP) for FORCED VIBRATION aircraft. Volume 6: Wing and empennage module. Evaluation of flight test of the FIAT G-91 13 by Appendix D: Program flow charts, overlay (18,0) means of the method of forced oscillations (AD-A002861] N75-20315 N15-19258 FLOW DISTORTION FORTRAN The generation of sound by aerodynamic sources in A structural weight estimation program (SWEEP) for an inhomogeneous steady flow aircraft. Volume 2: Program integration and A75-26463 data management module. Appendix A: Data An experimental investigation of compressor stall management module flow charts and FORTRAN lists using an on-line distortion indicator and signal (AD-AUO2851] N15-20304 conditioner A structural weight estimation program (SWEEP) for [NASA-TM-X-3182] N75-20248 aircraft. Volume 3: Airloads estimation FLOW DISTRIBUTION module. Appendix A: Module flow charts and Study of transonic flow over various bodies FORTRAN lists. Appendix B: Sample output N75-19169 (AD-A002855] N75-20306 Analytical comparison of hypersonic flight and A structural Weight estimation program (SWEEP) for wind tunnel viscous/inviscid flow fields aircraft. Volume 6: Wing and empennage module. (NASA-CR-2489] N75-19586 Appendix E: Program listings, overlays (8,0), (14,0), (15,0), (16,0) , and (11,0) [AD-A002862] N75-20316

A-li

FRACTURE MECHANICS SUBJECT INDEX

A structural weight estimation program (SWEEP) for aircraft. Volume 6: wing and empennage module. Appendix F: Program listings, overlays (9,0) (10,0) and (18,0) G-91 AIRCRAFT (AD-A002863] N75-20317 Manual evaluation of special flying maneuvers for FRACTURE MECHANICS the determination of flight-mechanical Design and purchase expectations for fracture coefficients and derivatives from flight tests resistance of 700-series aluminum airframe alloys longitudinal and lateral stability of [AD-A002552] N75-20548 G-91-T3 aircraft Fracture mechanics of tiny cracks near fasteners N75-19255 in high strength aluminum alloys Determination of aerodynamic derivatives of the - [AD-A002554] N75-20777 FIAT 0-91 T3 aircraft from flight tests by means FRACTURE STRENGTH of manual analog model matching Metallurgical factors affecting high strength N75-19257 aluminum alloy production Evaluation of flight test of the FIAT G-91 T3 by A75-28529 means of the method of forced oscillations FREE FLIGHT N75-19258 Boundary-layer pressure fluctuations at high Evaluation of flight tests of the FIAT 0-91 T3 by Reynolds numbers on a second free-flight test means of regression analysis vehicle N75-19259 (ARC-CP-1302] N75-19189 GALLIUM ARSENIDES FREE FLOE The performance in illuminances up to 80,000 lux A non-uniqueness of the hypersonic boundary layer of a light emitting diode display having a 3 mm A75-26195 character height FREE JETS A75-27526 The impingement of non-uniform, axisymmetric, GAS EXPANSION supersonic jets on a perpendicular flat plate The expansion of a hypersonic turbulent boundary A75-26684 layer at a sharp corner Effect of forward speed on jet wing/flap A75-26466 interaction noise A problem in supersonic jet theory [AIAA PAPER 75-475] A75-27932 A75-26697 On the instability of a sound-influenced free jet GAS FLOW [ESRO-TT-122] - N75-20267 A subsonic axisymmetric wake in a viscous gas FREQUENCY MODULATION A75-26891 Helicopter rotor-produced modulation and aerial Theory of transonic flow around a profile field distribution in the band 30 to 76 MHz A75-28651 [RAE-TR-74032] N75-19217 Hypersonic, viscous gas.f low around a wing of FRICTION FACTOR small aspect ratio Effects of friction and heat conduction on sound A75-28653 propagation in ducts GAS TEMPERATURE [AIAA PAPER 75-520] A75-28349 Elementary method of graphic replotting of a FRICTIONLESS ENVIRONMENTS characteristic of an uncooled turbocompressor The range of validity in the case of two old when the intake temperature and number of investigations. I - The origin of lift. II - revolutions are varied Collision and gliding processes on the liquid A75-26672 surface GAS TURBINE ENGINES A75-27990 Miniature probes for use in gas turbine testing FUEL CONSUMPTION (SAN PAPER 750094] A75-26589 Part load specific fuel consumption of gas turbines Tests of laser metal removal for future flexible A75728650 rotor balancing in engines Qualitative analysis of a family of extremums in a (SAN PAPER 750170) A75-26591 problem involving optimal control of aircraft High-temperature alloys and the aircraft gas turbine notion A75-27877 A75-28676 Part load specific fuel consumption of gas turbines Fuel conservation possibilities for terminal area A75-28650 compatible aircraft Development of self-acting seals for helicopter (NASA-cR-132608] N75-19224 engines Evaluation of advanced lift concepts and fuel (NASA-CR-134739] N75-19243 conservative short-haul aircraft, volume 1 PLT 27 gas turbine engine exhaust emission and (NASA-CR-137525] N75-20291 noise measurements Evaluation of advanced lift concepts and fuel [AD-A001728] N75-19251 conservative short-haul aircraft, volume 2 Rotating engine design and cycle analysis program (NASA-CR-137526] N75-20292 [AD-A00231 14] N75-20342 FUEL TANKS GENERAL AVIATION AIRCRAFT Investigation of 14.5mm API Application of a new slip-ringless propeller blade self-sealing/crashworthy fuel tank material measurement system [AD-A001752] N75-19249 A75-28771 Feasibility of adapting a thin film permeable Analysis of in-flight disintegration accidents membrane to jet transport fuel tank inerting N75-19197 system General Aviation Aircraft Safety [AD-A003799] N75-20295 [AD-A003124] N75-19199 FUSELAGES Analysis of general aviation accident records Influence of fuselage flexibility on the N75-19200 stress-strain state of the wing General aviation accident patterns A75-28668 N75-19201 A structural weight estimation program (SWEEP) for The accident record in terms of the pilot aircraft. Volume 7: Fuselage module N75-19202 (AD-A002867] N75-20318 Crash survivability A structural weight estimation program (SWEEP) for N15-19203 aircraft. Volume 7: Fuselage module. Appendix General aviation handling qualities research A: Module flow charts and FORTRAN lists. N15-19204 Appendix B: Fuselage module sample output Design considerations for stall/spin avoidance (AD-A002868] N75-20319 N75-19205 Economics: General aviation cost factors N75-19206 Manufacturers overview N75-19207 The next forty years in aviation N75-20228

A-18

SUBJECT INDEX HOVERING STABILITY

General aviation's future need for research HELICOPTER CONTROL N75-20242 Integrated avionics - Controls and displays for Development of a scientific basis for analysis of helicopter IFR operation aircraft seating systems A75-28786 [AD-A004306] 1175-20273 Major Item Special Study (MISS), OH-1C tail rotor GLIDE LANDINGS blade Comparison of airport measurements of approach [AD-A001714] 1175-19230 noise produced by jet aircraft HELICOPTER DESIGN A75-27852 Determination of the dynamic characteristics of a GLIDE PATHS helicopter by the branch-modes method Evaluation of the Rubino procedure for radio A75-26479 telemetric theodolite positioning Design and fatigue testing of integral armored [AD-A00 14317] 1175-20353 servo actuator modified trunnion GLIDERS [AD-A002069] 1175-19235 The -definition- of the motorsegler Major Item Special Study (MISS), 011-18 tail rotor [DFVLR-SONDDR-424] A75-27596 hangers GOVERNMENT PROCUREMENT [AD-A003263] 1175-20325 Aeronautics in the American society HELICOPTER ENGINES N75-20223 Development of self-acting seals for helicopter GRAPHS (CHARTS) engines Elementary method of graphic replotting of a (NASA-CR-134739] 1175-19243 characteristic of an uncooled turbocompressor HELICOPTER PERFORMANCE when the intake temperature and number of Estimates of the stability derivatives of a revolutions are varied helicopter and a V/STOL aircraft from flight data A75-26672 A75-28201 GROUND EFFECT MACHINES A specialised recording system for the measurement Air cushion landing systems for aircraft of helicopter rotor blade performance in flight A75-27983 A75-28770 Quarterly bulletin of the Division of Mechanical Helicopter flight regimes Engineering and the National Aeronautical [AD-A001220] 1175-19268 Establishment, 1 October - 31 December 1974 Flight simulation of a Wessex helicopter: A [DME/NAE-1974(4) 3 1175-20249 validation exercise Some air cushion technology research in Canada [ARC-CP-1299] N75-20298 N75-20251 HELICOPTER PROPELLER DRIVE Air cushion landing systems for aircraft Extension of the lifting line model for the 1175-20296 helicopter rotor GROUND STATIONS A75-28194 The U.S. Candidate Microwave Landing System - A HELICOPTERS new generation of avionics/ground equipment The computation of aerodynamic loads on helicopter [AIAA PAPER 75-607] A75-28472 blades in forward flight, using the method of GROUND TESTS the acceleration potential --- Book wide bandwidth optical telemetry link for ground A75-26700 testing of equipment in high EMI environments Helicopter rotor-produced modulation and aerial A75-28781 field distribution in the baud 30 to 76 MHz GUIDANCE SENSORS [EAE-TB-740321 1175-19217 Feasibility of laser systems for aircraft landing Flight path control and performance analysis, operations under low visibility conditions phases 1 and 2. Integrated display, phase 3 [AD-A005637] 1175-19198 [AD-A002014] 1175-19269 GUST ALLEVIATORS Non-dimensional methods for the measurement of Design of a digital-stability augmentation and level flight performance of turbine engined control system with gust alleviation and modal helicopters suppression (ESDU-74042] N75-20289 A75-28432 Development of scratch and spall resistant Status and trends in active control technology windshields N75-20236 [AD-A002513] 1175-20300 GUST LOADS Instrument system test. Elliott helicopter air Improvements to the SADSAM computer program for data system aeroelasticity analysis [AD-A002332] N75-20331 [NASA-CR-132617] N75-19173 Visual Augmentation System (VAS) laboratory demonstration and test results --- onboard helicopter - [AD-A003323] N75-20332 HARMONIC OSCILLATION OH-58A propulsion system vibration investigation Calculations of generalised airforces on two [AD-A002672] N75-20341 parallel lifting surfaces oscillating HIGH STRENGTH ALLOYS harmonically in subsonic flow Metallurgical factors affecting high strength [ARC-R/M-3749] 1175-19187 aluminum alloy production HARNESSES A75-28529 Crash survivability Fracture mechanics of tiny cracks near fasteners N75-19203 in high strength aluminum alloys HEAD-UP DISPLAYS [AD-1002554] 1175-20777 A conformal head-up display for the visual approach HODOGRAPHS - N75-19138 An exact solution for transonic potential flow HEAT TRANSFER past aerofoil sections Calculation of heat transfer at the lines of flow [NAL-TR-383] N75-19176 of a three-dimensional boundary layer in a HORIZONTAL TAIL SURFACES nonuniform external flow Calculations of generalised airforces on two A75-26894 parallel lifting surfaces oscillating Internal-combustion engine/vapour cycle combination harmonically in subsonic flow (O0EL-1097/74] N75-20336 [ARC-R/9-3749] 1175-19187 BRAT TRANSFER COEFFICIENTS HOVERING Numerical study of heat exchange at the stagnation Aerodynamic design of a rotor blade for minimum point of a sphere situated in a hypersonic noise radiation stream of carbon dioxide gas N75-19221 A75-26888 HOVERING STABILITY Interpretation of merged layer behavior for wedges Selected examples of the evaluation of YAK 191 B A75-27496 flight tests --- roll control characteristic in hovering flight N75-19266

A-19

HP-115 AIRCRAFT SUBJECT INDEX

RP-115 AIRCRAFT ILLUMINANCE Longitudinal aerodynamic derivatives of a slender The performance in illuminances up to 80,000 lux delta wing research aircraft extracted from of a light emitting diode display having a 3 mm flight data character height [CRANflELD-AERO-27J 1175-19175 A75-27526 Longitudinal aerodynamic derivatives of a slender IMPACT LOADS delta-wing research aircraft extracted from Determination of load factors for the impact of a flight data profile against the surface of a liquid [CRANFIELD-AERO-27] 1175-20258 A75-26819 Parameter identification applied to aircraft IMPACT TESTS [CRANFIELD-AERO- 26] N75-20259 Development of scratch and spall resistant HUMAN FACTORS ENGINEERING windshields What have we learned from applying digital [AD-A002513] 1115-20300 technology to cabin/passenger multiplex systems 15-FLIGHT MONITORING cost and weight analysis Self-testing digital flight control applications [AIAA PAPER 75-514] A75-26132 [AIAA PAPER 75-568) A75-26721 Crash survivability A specialised recording system for the measurement 1175-19203 of helicopter rotor blade performance in flight Users manual for UCIN vehicle occupant crash study A75-28770 model, version 2 Application of a new slip-ringless propeller blade [AD-A001801] 1175-19211 measurement system Preliminary evaluation of turbofan cycle A75-28771 parameters and acoustical suppression on the The development of a serial P.C.M. instrumentation noise and direct operating cost of a commercial system Each 0.85 transport A15-28191 (NASA-TM-X-71664) 1175-19244 INCOMPRESSIBLE FLOW Development of a scientific basis for analysis of On the viscous flow about the trailing edge of a aircraft seating systems rapidly oscillating plate [AD-A004306] 1175-20273 A75-26469 HYDRAULIC ANALOGIES INERT ATMOSPHERE Determination by means of hydraulic analogy of the Feasibility of adapting a thin film permeable transonic flow in a blade cascade membrane to jet transport fuel tank inerting N75-20213 system HYDROFOIL OSCILLATIONS [AD-A003199] 1175-20295 Determination of load factors for the impact of a INFORMATION SYSTEMS profile against the surface of a liquid Digital avionics information system /DAIS/ A75-26879 integrated test bed development HYPERSONIC BOUNDARY LAYER [AIAA PAPER 75-588] A75-26739 A non-uniqueness of the hypersonic boundary layer INLET FLOW A75-26195 Low speed and angle of attack effects on sonic and The expansion of a hypersonic turbulent boundary near-sonic inlets layer at a sharp corner (NASA-CR-13 14778] 1175-19184 A75-26466 INSTRUMENT APPROACH The prediction of turbulent heat transfer to wedge Pan American World Airways, Incorporated Boeing compression corners and cylinder-flare bodies at 707-321B, N454PA, Pago Pago, American Samoa, 30 hypersonic speeds January 1974 [IC-AERO-73-03] 1175-20264 [PB-238478/2] 1115-20217 HYPERSONIC FLIGHT Delta Air Lines Incorporated McDonnell Douglas Analytical comparison of hypersonic flight and DC-9-32, N3323L, Chattanooga Municipal Airport, wind tunnel viscous/inviscid flow fields Chattanooga, Tennessee (NASA-CR-2489] 1175-19586 [PB-238479/0] N75-20278 HYPERSONIC FLOW INSTRUMENT FLIGHT RULES Numerical study of heat exchange at the stagnation Integrated avionics - Controls and displays for point of a sphere situated in a hypersonic helicopter IFR operation stream of carbon dioxide gas A75-28186 A75-26888 INSTRUMENT LARDING SYSTEMS Hypersonic flow past pointed and blunt bodies with C-141 All Weather Landing System (AWLS) flight a concave generatrix test report: Optimization and pre-experimental A75-26896 phases - Hypersonic, viscous gas flow around a wing of [AD-A003952] 1175-20330 small aspect ratio Evaluation of the Rubino procedure for radio A75-28653 telemetric theodolite positioning HYPERSONIC HEAT TRANSFER [AD-A004311] 1115-20353 The expansion of a hypersonic turbulent boundary INTAKE SYSTEMS layer at a sharp corner A study of carburetor/induction system icing in A75-26466 general aviation accidents HYPERSONIC NOZZLES [NASA-CR-11e3835] N75-19208 Study of two hypersonic, axisymmetric, shaped INTERNAL COMBUSTION ENGINES nozzles with smooth contour Internal-combustion engine/vapour cycle combination A75-28658 [OUEL-1097/74] N15-20336 INTERNATIONAL COOPERATION Air Europe: The policy of cooperation among airline companies of the European Six --- French ICE FORMATION book Natural icing tests. UH-1H helicopter Al5-26499 [AD-A002077] N75-19194 European aeronautics and astronautics at the A study of carburetor/induction system icing in crossroads general aviation accidents A75-27981 [NASA-CR-143835] 1175-19208 INVISCID FLOW ICE PREVENTION Calculation of heat transfer at the lines of flow Natural icing tests. UH-1H helicopter of a three-dimensional boundary layer in a (AD-A002071] 1175-19194 nonuniform external flow IDEAL GAS A75-26894 Theory of transonic flow around a profile Study of transonic flow over various bodies A75-28651 N15-19169 Analytical comparison of hypersonic flight and wind tunnel viscous/inviscjd flow fields [NASA-CR-2489] N15-19586

A-20

SUBJECT INDEX LIFT

IRON ALLOTS JET FLOE Design and purchase expectations for fracture Analysis of thick turbulent jet flowing round: A resistance of 700-series aluminum airframe alloys circular cylinder [AD-A002552] N15-20548 N75-19168 JET INPINGENENT The impingement of non-uniform, axisymmetric, J supersonic jets on a perpendicular flat plate J-85 ENGINE A75-26684 An experimental investigation of compressor stall JET NIXING FLOE using an on-line distortion indicator and signal Some notes on the thermodynamics of thrust conditioner reversal in flight [NASA-TN-X-3182] N15-20248 N75-20212 JET AIRCRAFT JET PROPULSION Environmental and operating requirements for fire On the future of jet propulsion in subsonic extinguishing systems on advanced aircraft transport aviation [AD-A001640] N75-19228 A75-27777 Influence of nultitube mixer nozzle geometry on CYOL-OTE let noise shielding [NASA-TE-X-71681 ] N75-19246 L Interior noise considerations for powered-lift LARINAR FLOE STOL aircraft Starting vortex, separation bubbles and stall - A (NASA-TM-X-72675) N75-19248 numerical study of laminar unsteady flow around USA? aircraft takeoff length distances and an airfoil climbout profiles A75-26212 [AD-A00186] N75-19818 On the viscous flow about the trailing edge of a JET AIRCRAFT NOISE rapidly oscillating plate Comparison of airport measurements of approach A75-26469 noise produced by jet aircraft LANDING AIDS A75-27852 A conformal head-up display for the visual approach Noise of model target type thrust reversers for N15-19138 engine-over-the-wing applications Feasibility of laser systems for aircraft landing A75-27853 operations under low visibility conditions Propagation of aircraft noise near airports - [AD-A005631] N75-19198 Effects of hillsides, inversions and source LANDING GEAR directionality Air cushion landing systems for aircraft A75-27859 A75-27983 Radiation of duct noise out through a jet flow A structural weight estimation program (SWEEP) for acoustic field model for aircraft engine aircraft. Volume 5: Air induction system and [AIAA PAPER 75-457] A75-27928 landing gear modules. Part 2: Landing gear An investigation of the noisefrom a scale model module of an engine exhaust system --- turbojet noise (AD-A002858] N75-20309 measurement LASER APPLICATIONS (AIAA PAPER 75-459] 835-27929 Wide bandwidth optical telemetry link for ground Subsonic jet noise in flight based on some recent testing of equipment in high EMI environments wind-tunnel tests A75-28781 [AIAA PAPER 75-462] A75-27930 LASER BEATING Effect of forward speed on jet wing/flap Tests of laser metal removal for future flexible interaction noise rotor balancing in engines [AIAAPAPER 75-475] A75-27932 (SAE PAPER 150170] A75-26591 Developments in jet noise modeling - Theoretical LASER OUTPUTS predictions and comparisons with measured data Feasibility of laser systems for aircraft landing (AIAA PAPER 75-477] A15-27933 operations under low visibility conditions Supersonic jet noise suppression with multitube [AD-A005637] 915-19198 nozzle/ejectors LATERAL CONTROL (kILL PAPER 75-501] A75-27936 Selected examples of the evaluation of VAK 191 B Jet noise suppressors for turbojet engines flight tests --- roll control characteristic in A75-28227 hovering flight An experimental study of the structure and P75-19266 acoustic field of a jet in a cross stream LATERAL STABILITY [AIAA PAPER 75-460] A75-28348 Manual evaluation of special flying maneuvers for Aeroacoustics: Jet and combustion noise; duct the determination of flight-mechanical acoustics --- Book coefficients and derivatives from flight tests A75-28629 longitudinal and lateral stability of Interaction between a sonic boom N-wave and an G-91-T3 aircraft obstacle near corner points P15-19255 A75-28665 LEADING EDGES New evidence of the mechanisms of noise generation A non-uniqueness of the hypersonic boundary layer and radiation of a subsonic jet Al5-2695 A75-28717 Interpretation of merged layer behavior for wedges Investigation of aircraft combustor noise A75-27496 (AD-A001737] N75-19250 Flow past conically-cambered slender delta wings JET ENGINES with leading-edge separation Real-time simulation of jet engines with a digital [ARC-R/8-3748] N75-19186 computer(1), fabrication and characteristics of LEAST SQUARES METHOD the simulator Determination of the parameters of a system of (RAE-LIB-TRANS-1768] P75-19274 equations of motion from flight test data JET FLAPS least squares method Lift coefficients on a supercavitating jet-flapped N75-19263 foil between rigid walls Estimates of the stability derivatives of a A75-26554 helicopter and a V/STOL aircraft from flight data Propulsive-lift noise of an upper surface blown N75-20250 flap configuration LIFT [AIAA PAPER 75-470] A75-27931 Unsteady lift forces on a vibrating cylinder in a A theoretical method for calculating the supercritical flow aerodynamic characteristics or arbitrary - A75-26480 ejector-jet-flapped wing: Theoretical analysis Lift coefficients on a supercavitating jet-flapped [AD-A002319] N75-20271 foil between rigid walls A15-26554

A-21

LIFT AUGMENTATION SUBJECT INDEX

The range of validity in the case of two old CH-47A assessment and comparative fleet investigations. I - The origin of lift. II - evaluation: Executive summary report Collision and gliding processes on the liquid (AD-A002057] 875-19232 surface - LONGITUDINAL CONTROL A75-27990 Adaptive digital system for aircraft control Critical analysis and improvement of the A75-27182 source-panel method --- for lift prediction Pitch paper pilot revisited --- methods for A75-28095 predicting handling qualities of aircraft in pitch Lifting surface theory for a rotating subsonic or 975-19133 transonic blade row LONGITUDINAL STABILITY [ARC-R/9-3740] 875-19185 Longitudinal aerodynamic derivatives of a slender LIFT AUGMENTATION delta wing research aircraft extracted from Noise of model target type thrust reversers for flight data engine-over-the-wing applications [CRANFIELD-AERO-27] N75-19175 A75-27853 Manual evaluation of special flying maneuvers for Evaluation of advanced lift concepts and fuel the determination of flight-mechanical conservative short-haul aircraft, volume 1 coefficients and derivatives from flight tests (NASA-CR-137525) 875-20291 longitudinal and lateral stability of Evaluation of advanced lift concepts and fuel G-91-T3 aircraft conservative short-haul aircraft, volume 2 875-19255 [NASA-CR-137526] 875-20292 Longitudinal aerodynamic derivatives of a slender LIFT DEVICES delta-wing research aircraft extracted from Propulsive-lift noise of an upper surface blown flight data flap configuration [CEANFIELD-AERO-27] N75-20258 (AIAA PAPER 75-470) A75-27931 Development of longitudinal handling qualities LIFTING BODIES criteria for large advanced supersonic aircraft Unsteady viscous flow past a lifting plate (NASA-CH-137635] 875-20345 N75-19171 LORAN C TRW vortex-lattice method subsonic aerodynamic Oceanic air route navigation with envelope match analysis for multiple-lifting-surfaces (N. Loran-C surface) TRW program number HAO10B [AD-A003800] 875-20286 [NASA-CR-128588] 875-19178 LOW ASPECT RATIO WINGS A theoretical method for calculating the Hypersonic, viscous gas flow around a wing of aerodynamic characteristics or arbitrary small aspect ratio ejector-jet-flapped wing: Theoretical analysis A75-28653 [AD-A002319] 875-20271 Allowance for the elastic deformation of the wing Lifting surface for aircraft --- wing profiles in its own plane in the calculation of the (NASA-TT-F-16241] 875-20290 skewsymnetric vibrations of an aircraft with a LIFTING ROTORS small-aspect-ratio wing Extension of the lifting line model for the A75-28687 helicopter rotor A75-28194 Some remarks on the induced velocity field of a lifting rotor and on Glauerts formula MACH NUMBER [ARC-CP-1301 ] 875-20263 Exploratory wind tunnel tests of a LIGHT EMITTING DIODES shock-swallowing air data sensor at a Mach The performance in illuminances up to 80,000 lax number of approximately 1.83 of a light emitting diode display having a 3 mm [NASA-TM-X-56030] 875-20329 character height MACHINING A75-27526 Tests of laser metal removal for future flexible LINEAR PREDICTION rotor balancing in engines Notes on the approximate solution of [SAE PAPER 750170] A75-26591 lifting-surface theory used in the RAE standard MAN MACHINE SYSTEMS method Instrumentation displays for future naval aircraft (ARC-R/M-3752] 875-19188 [AIAA PAPER 75-599] A75-26744 LINEAR SYSTEMS MANEUVERABILITY Eigenvalue/eigen vector assignment for Helicopter flight regimes multivariable systems --- linear state feedback [AD-A001220] 875-19268 control MATHEMATICAL MODELS A75-26312 Unified analysis of ducted turbomachinery noise LIQUID NITROGEN A75-27861 Feasibility of adapting a thin film permeable Roll paper pilot --- mathematical model for membrane to jet transport fuel tank inerting predicting pilot rating of aircraft in roll task system N75-19134 [AD-A003799] 875-20295 Extraction of flight mechanic derivatives from LIQUID SURFACES flight data by a manual analog matching technique Determination of load factors for the impact of a [ESRO-TT-118] N75-20347 profile against the surface of a liquid MAXIMUM LIKELIHOOD ESTIMATES A75-26879 Longitudinal aerodynamic derivatives of a slender The range of validity in the case of two old delta-wing research aircraft extracted from investigations. I - The origin of lift. II - flight data Collision and gliding processes on the liquid (CRANFIELD-AERO-27 1 875-20258 surface MEASURE AND INTEGRATION A75-27990 Computation of the velocity field induced by a LOADS (FORCES) planar source distribution approximating a A comparison of flight loads counting methods and symmetrical non-lifting wing in subsonic flow their effects on fatigue life estimates using [ANC-R/N-3751] 875-20262 data from Concorde MEASURING INSTRUMENTS [ARC-CP-1304] N75-19227 Analysis of wreckage --- aircraft accident Some air cushion technology research in Canada investigation N75-20251 A75-26533 Development of statistical fatigue failure MECHANICAL PROPERTIES characteristics of 0.125 inch 2024-T3 aluminum Characterization of advanced composite materials under simulated flight-by-flight loading for structural design --- of aircraft (AD-A002310] 875-20554 A75-27695 LOGISTICS MANAGEMENT Major Item Special Study (MISS) , UH-1C tail rotor blade (AD-A001714] 875-19230

A-22

SUBJECT INDEX NOISE MEASUREMENT

MEMBRANE STRUCTURES MILITARY TECHNOLOGY Feasibility of adapting a thin film permeable Application of digital systems to Army avionics membrane to jet transport fuel tank inerting [AIAA PAPER 75-587] A75-26138 system MINIATURE ELECTRONIC EQUIPMENT [AD-A003799] 975-20295 Miniature probes for use in gas turbine testing MERIDIONAL FLOW [SAE PAPER 750094] A75-26589 Development and experimental evaluation of a NODAL RESPONSE numerical method for solving the inverse Determination of the dynamic characteristics of a axisymmetric problem in an axial turbine stage helicopter by the branch-modes method with given velocity A75-26479 A75-26671 METAL FATIGUE Fatigue strength of D16T Duralumin at normal and IT" elevated temperatures as a function of the NACELLES cycling rate Integration of aft-fuselage-mounted flow through A75-28866 engine nacelles on an advanced transport METAL MATRIX COMPOSITES configuration at Mach numbers from 0.6 to 1.0 Metal matrix composites for aircraft propulsion (RASA-TM-I-3178) 875-19180 systems NASA PROGRAMS (NASA-TM-X-71685] 875-19245 A new flight test data system for NASA Processable high temperature resistant polymer aeronautical flight research matrix materials A75-287114 [NASA-TM-X-71682] 875-19367 NAVIGATION AIDS METEOROLOGICAL PARAMETERS Airborne equipment for use with the microwave USAF aircraft takeoff length distances and landing system cliobout profiles A75-28790 [AD-A001826] 875-19878 Characterist..cs of ELS signals and their effect on MICROSTRUCTURE flight control systems --- Microwave Landing Metallurgical factors affecting high strength Systems aluminum alloy production A75-28791 A75-28529 Astrolabe - A synthetic circular aperture system MICROWAVE ANTENNAS for landing and navigation Astrolabe - A synthetic circular aperture system A75-28793 for landing and navigation Oceanic air route navigation with envelope match A75-28793 Loran-C Dual band airborne antenna study [AD-A003800] 875-20286 [AD-A002043] N75-19219 NEAR WAKES MICROWAVE LANDING SYSTEMS A subsonic axisymmetric wake in a viscous gas The U.S. Candidate Microwave Landing System - A A75-26891 new generation of avionics/ground equipment NEUMANN PROBLEM (AIAA PAPER 75-607) A75-28472 Cavitating flow past a vibrating thin-section wing Airborne equipment for use with the microwave profile landing system A75-26895 A75-28790 NIGHT VISION Characteristics of NLS signals and their effect on Visual Augmentation System (VAS) laboratory flight control systems --- Microwave Landing demonstration and test results --- onboard Systems helicopter A75-28791 (AD-A003323] N15-20332 The range of airborne processing available to the NIMONIC ALLOYS future user of the Doppler MLS --- Microwave High-temperature alloys and the aircraft gas turbine Landing Systems A75-27877 A75-28792 NOISE (SOUND) Astrolabe - A synthetic circular aperture system Measurement and analysis of the unsteady normal for landing and navigation force and pitching moment on an axial flow fan A75-28793 rotor blade element Testing the MLS Doppler concept [AD-A002739] 875-20343 A75-28802 NOISE GENERATORS MIDAIR COLLISIONS 8oise generation and transmission in duct combustors Aircraft guidance for automatic collision avoidance [AIAA PAPER 75-527] A75-21938 A75-27178 New evidence of the mechanisms of noise generation MILITARY AIRCRAFT and radiation of a subsonic jet Instrumentation displays for future naval aircraft Al5-28717 [AIAA PAPER 75-599] A75-26744 NOISE INTENSITY Flight tests with the V/STOL experimental aircraft Comparison of airport measurements of approach YAK 191 B noise produced by jet aircraft A75-27985 A75-21852 Aeronautics in the American society NOISE MEASUREMENT N75-20223 Comparison of airport measurements of approach The next forty years in aviation noise produced by jet aircraft N75-20228 A15-21852 MILITARY AVIATION An investigation of the noise from a scale model Interaction of military/civil position location of an engine exhaust system --- turbojet noise and reporting systems --- of ATC measurement [AIAA PAPER 75-561] A75-28467 (AIAA PAPER 75-459] A75-21929 MILITARY HELICOPTERS Propulsive-lift noise of an upper surface blown Dynamic loads and structural criteria study flap configuration military helicopters (AIAA PAPER 75-410] A75-21931 (AD-A001739] N75-19195 Classification problems of aircraft noise --- far Vibration and temperature survey production AR-1G field measurements helicopter A75-21943 [AD-AUO2063] N75-19231 Aeroacoustics: Fan, STOL, and boundary layer CH-47A assessment and comparative fleet noise; sonic boon; aeroacoustic instrumentation evaluation: Executive summary report Book [AD-A002057] N75-19232 A15-28626 Engineering design handbook. Helicopter Interior noise considerations for powered-lift engineering, part 1: Preliminary design --- for STOL aircraft VFR operation (NASA-TM-1-72675] 875-19248 [AD-A002007] 875-19238

A-23

NOISE POLLUTION SUBJECT INDEX

PLT 27 gas turbine engine exhaust emission and NONUNIFORM FLOW noise measurements Calculation of heat transfer at the lines of flow [AD-A001728] N75-19251 of a three-dimensional boundary layer in a NOISE POLLUTION nonuniform external flow Problem of aircraft noise in the vicinity of A75-26894 airports NOSE FINS A75-28222 Experimental aerodynamic characteristics for a Noise certification of aircraft cylindrical body of revolution with side strakes A75-28223 and various noses at angles of attack from 0 Development of air transport and environmental degrees to 58 degrees and Each numbers from 0.6 requirements --- for air and noise pollution to 2.0 reduction (NASA-TM-X-3130) 875-19181 A75-28228 NOZZLE DESIGN Aeroacoustics Jet and combustion noise; duct A method of profiling short two-dimensional nozzles acoustics --- Book for transonic wind tunnels A75-28629 A75-2688O NOISE PROPAGATION A method of calculating aerodynamic-nozzle The role of rotor blade blockage in the profiles with passage through the sound barrier propagation of fan noise interaction tones A75-26881 [AIAA PAPER 75-447] A75-27927 Some recent developments in supersonic jet noise Interaction between a sonic boon N-wave and an reduction obstacle near corner points [AIAA PAPER 75-502) A75-27937 A75-28665 Study of two hypersonic, axisyrnmetric, shaped New evidence of the mechanisms of noise generation nozzles with smooth contour and radiation of a subsonic jet A75-28658 A75-28717 Impact of turbine modulation on variable-cycle NOISE REDUCTION engine performance. Phase 1 and 2: Design Spinning mode sound propagation in ducts with fabrication and rig test, part 1 acoustic treatment [AD-A002543] 875-20337 A75-27854 Impact of turbine modulation on variable-cycle Propagation of aircraft noise near airports - engine performance. Phase 3: Engine Effects of hillsides, inversions and source modification and sea level test, part 2 directionality [AD-A002544] 875-20338 A75-27859 Impact of turbine modulation on variable-cycle Effect of forward speed on jet wing/flap engine performance. Phase 4: Additional interaction noise hardware design and fabrication, engine [AIAA PAPER 75-1175] A75-27932 modification, and altitude test, part 3A Supersonic jet noise suppression with multitube [AD-A002545] 875-20339 nozzle/electors Impact of turbine modulation on variable-cycle [AIAA PAPER 75-501] A75-27936 engine performance. Phase 4: Additional Some recent developments in supersonic jet noise hardware design and fabrication, engine reduction modification, and altitude test, part 38 [AIAA PAPER 75-502] A75-27937 (AD-A002546) 875-20340 Jet noise suppressors for turbojet engines NOZZLE FLOW A75-28227 Influence of multitube mixer nozzle geometry on Aerodynamic design of a rotor blade for minimum CTOL-OTW jet noise shielding noise radiation (NASA-TM-X-716813 875-19246 875-19221 Impact of turbine modulation on variable-cycle Preliminary evaluation of turbofan cycle engine performance. Phase 1 and 2: Design parameters and acoustical suppression on the fabrication and rig test, part 1 noise and direct operating cost of a commercial [AD-A002543] N75-20337 Each 0.85 transport Impact of turbine modulation on variable-cycle (NASA-TM-X-71664 ] 875-19244 engine performance. Phase 3: Engine Influence of multitube mixer nozzle geometry on modification and sea level test, part 2 CTOL-OTV jet noise shielding [AD-A002544] 875-20338 [NASA-TE-I-71681 ] 875-19246 Impact of turbine modulation on variable-cycle Trends in aircraft noise control engine performance. Phase 4: Additional N75-20229 hardware design and fabrication, engine NOISE SPECTRA modification, and altitude test, part 3A Noise of model target type thrust reversers for [AD-A002 5115] 875-20339 engine-over-the-wing applications Impact of turbine modulation on variable-cycle A75-27853 engine performance. Phase 4: Additional Unified analysis of ducted turbomachinery noise hardware design and fabrication, engine A75-27861 modification, and altitude test, part 3B Developments in jet noise modeling - Theoretical [AD-A002546] 875-203110 predictions and comparisons with measured data NOZZLE GEOMETRY [AIAA PAPER 75-477] A75-27933 Study of two hypersonic, axisymmetric, shaped Ratio of peak frequencies of jet self and shear nozzles with smooth contour noise spectra A75-28658 A75-28400 Performance of an isolated two-dimensional NONDESTRUCTIVE TESTS variable-geometry wedge nozzle with translating Sound welds in wing boxes assured by three shroud and collapsing wedge at speeds up to Each techniques 2.01 A75-26898 [NASA-TN-D-7906] 875-20247 NONLINEAR EQUATIONS NUMERICAL ANALYSIS Nonlinear problem of the unsteady flow past an Development and experimental evaluation of a airfoil lattice numerical method for solving the inverse A75-28671 axisymmetric problem in an axial turbine stage NONLINEAR SISTERS with given velocity Stability analysis of stochastic composite systems A75-26671 application to control of aircraft and Nonlinear problem of the unsteady flow past an nonlinear systems airfoil lattice A75-27919 A75-28611 NONLINEARITY Dynamics of the motion of a body with allowance Nonlinear torsional vibrations of thin-walled for the unsteady state of the flow about it beams of open section [NASA-TT-F-16133) 875-19119 A75-26410

A-24 SUBJECT INDEX PITCHING MOMENTS

Computation of the velocity field induced by a Preliminary evaluation of turbofan cycle planar source distribution approximating a parameters and acoustical suppression on the symmetrical non-lifting wing in subsonic flow noise and direct operating cost of a commercial [ARC-R/H-3751] N75-20262 Each 0.85 transport NUMERICAL CONTROL [NASA-TE-X-71664] N75-19244 Adaptive digital system for aircraft control Development of a scientific basis for analysis of A75-27182 aircraft seating systems Design of a digital-stability augmentation and [AD-A004306] 375-20273 control system with gust alleviation and modal PASSENGERS suppression What have we learned from applying digital A75-28432 technology to cabin/passenger multiplex systems cost and weight analysis [AIAA PAPER 75-574] A75-26732 Ride quality evaluation. I --- aircraft passenger 0010 0 comfort assessment Aircraft accident report. Eastern Air Lines, Inc. 175-26849 McDonell-Douglas DC 9-31, N8967E Akron-Conton PERFORATED PLATES Regional Airport, North Canton, Ohio, 27 Nov. 1973 Stress intensity factors for some through-cracked [P0-238637/3] N75-20274 fastener holes OPTICAL COMMUNICATION A75-28236 Wide bandwidth optical telemetry link for ground PERFORMANCE PREDICTION testing of equipment in high EMI environments The role of rotor blade blockage in the A75-28781 propagation of fan noise interaction tones OPTICAL PATHS [AIAA PAPER 75-447] 175-27927 Feasibility of laser systems for aircraft landing Pitch paper pilot revisited --- methods for operations under low visibility conditions predicting handling qualities of aircraft in pitch [AD-A005637] N75-19198 N75-19133 OPTICAL PROPERTIES Field evaluation of model 2 of the computer-based, A new centralised warning display for aircraft individual trainer for the radar intercept officer A75-28785 [AD-1002705] N75-19278 OPTICAL TRACKING Sideslip of wing-body combinations --- disturbance Effects of visual flight display dynamics on theory for predicting aerodynamics of aircraft altitude tracking performance in a flight in sideslip simulator [NASA-CR-114716] 875-20260 N75-19127 PERFORMANCE TESTS OPTIMAL CONTROL Take-off instrument for assessing achieved Design of a digital-stability augmentation and performance during take-off and a take-off control system with gust alleviation and modal accident analysed in context suppression A75-28769 175-28432 Characteristics of MLS signals and their effect on Qualitative analysis of a family of extremums in a flight control systems --- Microwave Landing problem involving optimal control of aircraft Systems motion A75-28791 A75-28676 Testing the ELS Doppler concept A model based technique for the design of flight 175-28802 directors --- optimal control models Development of self-acting seals for helicopter N75-19140 engines Mechanics of optimum three-dimensional motion of [NASA-CR-134739] N75-19243 aircraft in the atmosphere Some aspects of performance measurements in [NASA-TT-F-777] N75-19182 nonsteady flight --- angle of attack and rate of OPTIMIZATION climb An improved automated structural optimization N75-19262 program Oceanic air route navigation with envelope match [10-1002688] N75-19237 Loran-C OSCILLATING CYLINDERS [10-1003800] N75-20286 Unsteady lift forces on a vibrating cylinder in a PERSONNEL DEVELOPMENT supercritical flow Aeronautics in the American society A75-26480 075-20223 OSCILLATING FLOW PERTURBATION A method for predicting unsteady aerodynamic On the instability of a sound-influenced free jet forces on oscillating wings with thickness in (ESRO-TT-122) N75-20267 transonic flow near Each number 1. Part 1: PERTURBATION THEORY Two-dimensional theory. Part 2: Rectangular Sideslip of wing-body combinations --- disturbance wings theory for predicting aerodynamics of aircraft (NAL-TR-368T-PT-1J N75-19174 in sideslip [NASA-CR-114716] N75-20260 PILOT ERROR r The accident record in terms of the pilot PICKINGS (SEALS) N75-19202 Development of self-acting seals for helicopter PILOT PERFORMANCE engines Integrated avionics - Controls and displays for [NASA-CR-134739] N75-19243 helicopter IFR operation PARACHUTES A75-28786 Flight determination of the rudder power and A study on aircraft map display location and directional stability of the Fairey Delta 2 orientation --- effects of map display location aircraft using a wingtip parachute on manual piloting performance (ARC-CP-1298] N75-19267 875-19128 PARALLEL FLOW PILOT TRAINING The coexistence of two supersonic plane flows in The accident record in terms of the pilot the presence of a longitudinal pressure gradient N75-19202 N75-20209 PITCHING MOMENTS PARTICLE SIZE DISTRIBUTION Measurement and analysis of the unsteady normal Metallurgical factors affecting high strength force and pitching moment on an axial flow fan aluminum alloy production rotor blade element A75-28529 [10-1002739] 875-20343 PASSENGER AIRCRAFT Problems of designing passenger aircraft [NASA-TT-F-808] N75-19223

A-25

PNEUMATIC CONTROL SUBJECT INDEX

PNEUMATIC CONTROL PRODUCTION PLANNING Evaluation program on using compressor bleed air Organization of centralized maintenance of as a source of pneumatic power for fluidic aircraft assemblies --- Russian book circuits 175-27838 (AD-A002483) 875-20676 PROJECT MANAGEMENT POLLUTION CONTROL General aviation's future need for research Development of air transport and environmental 875-20242 requirements --- for air and noise pollution University research in aeronautics reduction 875-20243 175-28228 PROPELLER BLADES POLTIMIDE RESINS Application of a new slip-ringless propeller blade Processable high temperature resistant polymer measurement system matrix materials A75-28771 [NASA-TM-X-71682] 875-19367 PROPELLER DRIVE POSITIONING DEVICES (MACHINERY) The aerodynamic characteristics and trailing Tiedown tests for air transport of the XM542 vortex wake of propeller V/SFOL configurations sprint container A75-28522 [AD-A001844] 875-19210 PROPULSION SYSTEM CONFIGURATIONS POTENTIAL FLOW By the application of power' /21st Cayley Cavitating flow past a vibrating thin-section wing Memorial Lecture/ --- technical survey of profile aircraft engines 175-26895 A75-27368 Critical analysis and improvement of the On the future of jet propulsion in subsonic source-panel method --- for lift prediction transport aviation A75-28095 A75-27777 Nonlinear problem of the unsteady flow past an Propulsive-lift noise of an upper surface blown airfoil lattice flap configuration - 175-28671 (AIAA PAPER 75-470] 175-27931 Calculation of two-dimensional and axisymmetric PROPULSION SYSTEM PERFORMANCE bluff body potential flow 05-58A propulsion system vibration investigation [IC-AERO-74-07] N75-19191 [AD-A002672] N75-20341 A wake source model for an inclined flat plate in PULSE CODE MODULATION a uniform stream The development of a serial P.C.M. instrumentation [IC-AERO-74-08] 875-19192 system POTENTIAL THEORY A75-28797 A method for calculating unsteady forces due to PULSE RADAR interaction between tail surfaces A new .J band pulsed radar altimeter A75-26477 A75-28787 PREDICTION ANALYSIS TECHNIQUES PYROLYSIS Critical analysis and improvement of the A study of the effects on mice of smoke and gases source-panel method --- for lift prediction from controlled fires in simulated aircraft cabins 175-28095 A75-27073 PRESSURE DISTRIBUTION Integration of aft-fuselage-mounted flow through engine nacelles on an advanced transport configuration at Mach numbers from 0.6 to 1.0 QUALITY CONTROL [NASA-TM-X-3178] 875-19180 Major Item Special Study (MISS) , OH-ill tail rotor Lifting surface theory for a rotating subsonic or hangers transonic blade row [AD-A003263] N75-20325 (ARC-R/M-3740) 875-19185 QUIET ENGINE PROGRAM A wake source model for an inclined flat plate in Low speed and angle of attack effects on sonic and a uniform stream - near-sonic inlets (IC-AERO-74-08] 875-19192 [NASA-Cs-134778] 875-19184 Boundary layer effects in supersonic flow over cylinder-flare bodies [WBE-REPT-1238(WR/D) ] 875-20257 R Some remarks on the induced velocity field of a RADAR BEACONS lifting rotor and on Glauert's formula Digital avionics - An overview --- Air Traffic (ARC-CP-1301] 875-20263 Control Radar Beacon System Wind tunnel studies of the turbulent wake behind [AIAA PAPER 75-553] A75-26721 self propelled slender bodies Multi-site intermittent positive control [AD-A002396] 875-20272 algorithms for the discrete address beacon system PRESSURE DRAG [AD-A001112/2] 875-19214 Opportunities for aerodynamic-drag reduction RADAR TRACKING N75-20237 The STRADA flight path tracking system PRESSURE GRADIENTS [RAE-LIB-TRANS-1813] 875-19209 The coexistence of two supersonic plane flows in Field evaluation of model 2 of the computer-based, the presence of a longitudinal pressure gradient individual trainer for the radar intercept officer N75-20209 (AD-1002705] 875-19278 PRESSURE MEASUREMENTS RADIO ALTIMETERS A specialised recording system for the measurement A new J band pulsed radar altimeter of helicopter rotor blade performance in flight 175-28787 A75-28770 RADIO TELEMETRY Boundary-layer pressure fluctuations at high Evaluation of the Rubino procedure for radio Reynolds numbers on a second free-flight test telemetric theodolite positioning vehicle [AD-A004317] 875-20353 [ARC-CP-1302] 875-19189 RAYLEIGH-RITZ METHOD PRESSURE OSCILLATIONS Flapping response characteristics of hingeless Characteristics of pressure fluctuations in rotor blades by a generalized harmonic balance distributed suction of a turbulent boundary layer method 175-27052 875-19166 PRESSURE REDUCTION REAL TIME OPERATION Evaluation program on using compressor bleed air The benefits of real time computer analysis of as a source of pneumatic power for fluidic experimental aircraft flight test data circuits A75-2880i [AD-A002483] 875-20676 REATTACHED FLOW Heat transfer in separated and reattached flows - An annotated review A75-26685

A-26

SUBJECT INDEX SCALE MODELS

RECIPROCAL THEOREMS A specialized recording system for the measurement The generation of sound by aerodynamic sources in of helicopter rotor blade performance in flight an inhomogeneous steady flow A75-28770 A75-26463 Helicopter rotor-produced modulation and aerial RECONNAISSANCE AIRCRAFT field distribution in the band 30 to 76 MHz Flight tests with the V/STOL experimental aircraft [RAE-TR-74032] N75-19217 YAK 191 B Wind tunnel investigation of helicopter rotor wake A75-27985 effects on three helicopter fuselage models REDUNDANT COMPONENTS [NASA-TN-X-3185-SUPPL] N75-20294 Flight-critical digital control system 'valuation Major Item Special Study (MISS), UN-1H tail rotor [AIAA PAPER 75-566] A75-26725 hangers REGRESSION ANALYSIS [AD-A003263] 1175-20325 Evaluation of flight tests of the FIAT G-91 T3 by ROTATING BODIES means of regression analysis Rotation in vibration, optimization, and N75-19259 aeroelastic stability problems RELIABILITY ANALYSIS N75-19167 Airborne electronics for automated flight systems ROTOR AERODYNAMICS N75-20232 Flapping response characteristics of hingeless RELIABILITY ENGINEERING rotor blades by a generalized harmonic balance Reliability life cycle of a complex electronic method airborne equipment N75-19166 A75-27839 Wind tunnel investigation of helicopter rotor wake REMOTE CONTROL effects on three helicopter fuselage models Development of a remote digital augmentation [NASA-TM-I-3185-SUPPL] N75-20294 system and application to a remotely piloted ROTOR BLADES research vehicle Aerodynamic design of a rotor blade for minimum [NASA-TN-D-794 1] N75-20293 noise radiation REMOTELY PILOTED VEHICLES 1175-19221 Computer simulation of maintenance for ROTOR BLADES (TURBOMACHINERY) multi-mission RPV5 Effect of interference between moving blade rows (AD-A003351] N75-20253 on cascade flutter. I - Experiment on compressor RESEARCH AIRCRAFT cascade in flexure mode Development of a remote digital augmentation A75-26553 system and application to a remotely piloted The role of rotor blade blockage in the research vehicle propagation of fan noise interaction tones (NASA-TN-D-7941] N75-20293 (AIAA PAPER 75-447] A75-27927 RESEARCH FACILITIES ROTORS University research in aeronautics Tests of laser metal removal for future flexible N75-20241 rotor balancing in engines RESEARCH PROJECTS (SAE PAPER 750170] A75-26591 Manufacturer's overview Shake test of rotor test apparatus in the 40- by 1175-19207 80-foot wind tunnel University research in aeronautics (NASA-TM-X-62 1418] 1175-20350 1175-20241 General aviations future need for research N75-20242 University research in aeronautics S WAVES N75-20243 Ratio of peak frequencies of jet self and shear Quarterly bulletin of the Division of Mechanical noise spectra Engineering and the National Aeronautical A75-281$00 Establishment, 1 October - 31 December 1971$ S-N DIAGRAMS (DME/NAE-1974(4) ) 1175-202119 Relation between scatter of fatigue life and S-N RETARDING curve in aircraft structural aluminium alloy On fatigue crack arresting by a stop-hole in 2024-T4 2024-T3 aluminum alloy sheet specimens [NAL-TR-360] N75-19414 [NAL-TR-359] N75-191$13 SAAB AIRCRAFT REYNOLDS NUMBER A SAAB-SCANIA developed method for obtaining The disappearance of the wake shock behind a stability derivatives from flight tests cylinder in a supersonic flow at high Reynolds N75-19260 number SAAB 37 AIRCRAFT A75-26414 Characteristics of the AJ 37 aircraft: Comparison RIGID ROTORS of the results of wind tunnel and flight tests Flapping response characteristics of hingeless noting elasticity correction for wind tunnel rotor blades by a generalized harmonic balance model method N75-19261 N75-19166 SAFETY DEVICES ROLL Flight test evaluation of SECANT VECAS collision Roll paper pilot --- mathematical model for avoidance system predicting pilot rating of aircraft in roll task [AD-A002281] N75-19220 N75-19134 SAFETY FACTORS Selected examples of the evaluation of VAK 191 B Development of a scientific basis for analysis of flight tests --- roll control characteristic in aircraft seating systems hovering flight [AD-A004306] N75-20273 1175-19266 Development of scratch and spall resistant ROLLING MOMENTS windshields A flight test investigation of the rolling moments [AD-A002513] N75-20300 induced on a T-37B' airplane in the wake of a SAMOA B-747 airplane Pan American World Airways, Incorporated Boeing [NASA-TM-X-56031] 1175-20221 707-321B, N454PA, Pago Pago, American Samoa, 30 ROTARY WINGS January 1974 The computation of aerodynamic loads on helicopter (PB-238478/2] N75-20277 blades in forward flight, using the method of SCALE MODELS the acceleration potential --- Book An investigation of the noise from a scale model A75-26700 of an engine exhaust system --- turbojet noise Extension of the lifting line model for the measurement helicopter rotor [AIAA PAPER 75-459] A75-27929 A75-28194 Propulsive-lift noise of an upper surface blown flap configuration (AIAA PAPER 75-470] A75-27931

A-27

SCOOPS SUBJECT INDEX

SCOOPS SHORT TAKEOFF AIRCRAFT Wind tunnel tests of a symmetrical airfoil with Interior noise considerations for powered-lift scoop fed slots STOL aircraft (NASA-CE-132568] N75-19183 [NASA-TM-X-72675] N75-192148 SEAT BELTS A theoretical method for calculating the Crash survivability aerodynamic characteristics or arbitrary N75-19203 ejector-jet-flapped wing: Theoretical analysis SEATS [AD-A002319] N75-20271 Development of a scientific basis for analysis of SIDE INLETS aircraft seating systems Wind tunnel tests of a symmetrical airfoil with (AD-A004306] N75-20273 scoop fed slots SELF ADAPTIVE CONTROL SYSTEMS (NASA-CR-132568) N75-19183 Self-testing digital flight control applications SIDESLIP (AIAA PAPER 75-568) A75-26727 Sideslip of wing-body combinations --- disturbance SELF OSCILLATION theory for predicting aerodynamics of aircraft Ratio of peak frequencies of jet self and shear in sideslip noise spectra [NASA-CR-114716] N75-20260 175-28400 SIGNAL ANALYSIS SEPARATED FLOW Characteristics of HLS signals and their effect on Starting vortex, separation bubbles and stall - A flight control systems --- Microwave Landing numerical study of laminar unsteady flow around Systems an airfoil A75-28791 175-26212 SIGNAL PROCESSING Beat transfer in separated and reattached flows - The range of airborne processing available to the An annotated review future user of the Doppler ELS --- Microwave A75-26685 Landing Systems Influence of sound upon separated flow over wings 175-28792 A75-27495 Astrolabe - A synthetic circular aperture system The three-dimensional character of a cross flow for landing and navigation around a circular cylinder k75-28793 A75-28654 SKIN (STRUCTURAL MEMBER) The coexistence of two supersonic plane flows in Shear lag analysis of thick skin aircraft structures the presence of a longitudinal pressure gradient (ATN-7404) N75-19225 N75-20209 SLENDER BODIES SERVOMECHANISMS Wind tunnel studies of the turbulent wake behind Design and fatigue testing of integral armored self propelled slender bodies servo actuator modified trunnion (AD-A002396) N75-20272 [AD-A002069] N75-19235 SLENDER CONES SHARP LEADING EDGES Calculation of heat transfer at the lines of flow Hypersonic flow past pointed and blunt bodies with of a three-dimensional boundary layer in a a concave generatrix nonuniform external flow A75-26896 A75-26894 SHEAR FLOW SLENDER WINGS Developments in jet noise modeling - Theoretical Longitudinal aerodynamic derivatives of a slender predictions and comparisons with measured data delta-wing research aircraft extracted from [AIAA PAPER 75-417] A75-27933 flight data SHEAR STRESS [CRANFIELD-AERO-27] N75-20258 Shear lag analysis of thick skin aircraft structures SMALL PERTURBATION FLOW [ATN-7404) N75-19225 The computation of aerodynamic loads on helicopter SHOCK WAVE GENERATORS blades in forward flight, using the method of The disappearance of the wake shock behind a the acceleration potential --- Book cylinder in a supersonic flow at high Reynolds A75-26700 number SONIC BOOMS A75-26414 Aeroacoustics: Fan, STOL, and boundary layer SHOCK WAVE INTERACTION noise; sonic boom; aeroacoustic instrumentation Interaction between a sonic boom N-wave and an Book obstacle near corner points 175-28626 A75-28665 Interaction between a sonic boom N-wave and an Evaluation of some control-volume techniques for obstacle near corner points analysis of shock-boundary layer interactions in A75-28665 supersonic inlets SOUND FIELDS [NASA-TM-X-3186] N75-20256 Development of acoustic disturbances in supersonic Boundary layer effects in supersonic flow over annular jets cylinder-flare bodies A75-26234 (WEE-REPT-1238 (WR/D) ] N75-20257 Radiation of duct noise out through a jet flow SHOCK WAVE PROFILES acoustic field model for aircraft engine Hypersonic flow past pointed and blunt bodies with (AIAA PAPER 75-457) 175-27928 a concave generatrix An experimental study of the structure and A75-26896 acoustic field of a jet in a cross stream SHOCK NAVE PROPAGATION (AIAA PAPER 75-460] A75-28348 Theory of transonic flow around a profile On the instability of a sound-influenced free jet A75-28651 (ESEO-TT-122] N75-20267 SHOCK WAVES SOUND GENERATORS Boundary layer effects in supersonic flow over The generation of sound by aerodynamic sources in cylinder-flare bodies an inhomogeneous steady flow (WEE-REPT-1238(WR/D) ] N75-20257 A75-26463 SHORT HAUL AIRCRAFT The use of Hartmann generators as sources of high Evaluation of advanced lift concepts and fuel intensity sound in a large absorption flow duct conservative short-haul aircraft, volume 1 facility [NASA-CR-137525] N75-20291 [1111 PAPER 75-529] A75-27939 Evaluation of advanced lift concepts and fuel SOUND PRESSURE conservative short-haul aircraft, volume 2 New evidence of the mechanisms of noise generation [NASA-CR-137526] N75-20292 and radiation of a subsonic jet Evaluation of active control technology for short A75-28717 haul aircraft --- cost effectiveness SOUND PROPAGATION (NASA-CR-137634] N75-20344 Influence of sound upon separated flow over wings A75-27495

A-28 SUBJECT INDEX STRUCTURAL WEIGHT

Spinning mode sound propagation in ducts with Influence of fuselage flexibility on the acoustic treatment stress-strain state of the wing A75-27854 A7 5-28668 Propagation of aircraft noise near airports - STRESS MEASUREMENT Effects of hillsides, inversions and source Development of an R.F. telemetry system --- for directionality aircraft engine stress and temperature data A75-27859 A75-28778 Effects of friction and heat conduction on sound STRUCTURAL ANALYSIS propagation in ducts OH-58A propulsion system vibration investigation (AIAA PAPER 75-520] A75-28349 (AD-A002672) 1175-20341 SOUND TRANSMISSION STRUCTURAL DESIGN Noise generation and transmission in duct combustors Characterization of advanced composite materials (AIAA PAPER 75-527] A75-27938 for structural design --- of aircraft SPACECRAFT COMMUNICATION A75-27695 Air Traffic Control demonstration aspects of the STRUCTURAL DESIGN CRITERIA Applications Technology Satellite-6 Aerodynamic design of a rotor blade for minimum [AIAA PAPER 75-562] A75-26723 noise radiation SPHERES 875-19221 Numerical study of heat exchange at the stagnation Operational use of the US-i H helicopters in point of a sphere situated in a hypersonic Arctic environment stream of carbon dioxide gas [AD-A002603] 875-19236 A75-26888 Some trends in aircraft design: Structure SPRINT MISSILE N75-20235 Tiedown tests for air transport of the X8542 STRUCTURAL ENGINEERING sprint container An improved automated structural optimization [AD-A001844] N75-19210 program STABILITY DERIVATIVES [AD-A002688] N75-19237 Estimates of the stability derivatives of a The future of aeronautics helicopter and a V,'STOL aircraft from flight data [NASA-CR-142559] 875-20222 A75-28201 STRUCTURAL FAILURE Longitudinal aerodynamic derivatives of a slender Analysis of in-flight disintegration accidents delta wing research aircraft extracted from N75-19197 flight data STRUCTURAL BERBERS (CRANFIELD-AERO-27] 875-19175 A structural weight estimation program (SWEEP) for Determination of aircraft characteristics from aircraft. Volume 1: Executive summary flight tests (AD-A002850] 875-20301 (BSRO-TT-104] N75-19252 A structural weight estimation program (SWEEP) for A SAAB-SCANIA developed method for obtaining aircraft, volume 2: Program integration and stability derivatives from flight tests data management module. Part 1: Program N75-19260 integration Determination of derivatives by a model with [AD-A002852] 875-20302 automatic parameter --- analog circuit A strucutral weight estimation program (SWEEP) for N75-19265 aircraft. Volume 2: Program integration and Estimates of the stability derivatives of a data management module, part 2: Data helicopter and a V/STOL aircraft from flight data management module N75-20250 [AD-A002853] 875-20303 Longitudinal aerodynamic derivatives of a slender STRUCTURAL VIBRATION delta-wing research aircraft extracted from On the viscous flow about the trailing edge of a flight data rapidly oscillating plate [CRANFIELD-AERO-27] 1175-20258 A75-26469 STAGNATION POINT Determination of the dynamic characteristics of a Numerical study of heat exchange at the stagnation helicopter by the branch-modes method point of a sphere situated in a hypersonic A75-26479 stream of carbon dioxide gas STRUCTURAL WEIGHT A75-26888 A structural weight estimation program (SWEEP) for STATE VECTORS aircraft. Volume 1: Executive summary Eigenvalue/eigenvector assignment for [AD-A002850] N75-20301 multivariable systems --- linear state feedback A structural weight estimation program (SWEEP) for control aircraft. Volume 2: Program integration and A75-26312 data management module. Part 1: Program STATISTICAL ANALYSIS integration Annual reviews of aircraft accident data US Air [AD-A002852] 1175-20302 Carrier operations, 1973 A strucutral weight estimation program (SWEEP) for [PB-238281/0] 1175-20276 aircraft. Volume 2: Program integration and STEADY FLOW data management module. Part 2: Data The generation of sound by aerodynamic sources in management module an inhomogeneous steady flow [AD-A002853] 875-20303 A75-26463 A structural weight estimation program (SWEEP) for STOCHASTIC PROCESSES aircraft. Volume 2: Program integration and Stability analysis of stochastic composite systems data management module. Appendix A: Data application to control of aircraft and management module flow charts and FORTRAN lists nonlinear systems (AD-A002851] N75-20304 A75-27919 A structural weight estimation program (SWEEP) for Design of a digital-stability augmentation and aircraft. Volume 3: Airloads estimation module control system with gust alleviation and modal (AD-A002854] N75-20305 suppression A structural weight estimation program (SWEEP) for A75-28432 aircraft. Volume 3: Airloads estimation STRATIFIED FLOW module. Appendix A: Module flow charts and The coexistence of two supersonic plane flows in FORTRAN lists. Appendix B: Sample output the presence of a longitudinal pressure gradient (AD-A002655] N75-20306 875-20209 A structural weight estimation program (SWEEP) for STRESS ANALYSIS aircraft. Volume 4: Material properties, Shear lag analysis of thick skin aircraft structures structure temperature, flutter and fatigue [ATN-7404] 1175-19225 (AD-A002856) 1175-20307 STRESS CONCENTRATION A structural weight estimation program (SWEEP) for Stress intensity factors for some through-cracked aircraft. Volume 5: Air induction system and fastener holes landing gear modules. Part 1: Air induction A75-28236 system nodule (AD-A002857] 1175-20308

A-29

SUBSONIC AIRCRAFT SUBJECT INDEX

A structural weight estimation program (SWEEP) for SUBSONIC SPEED aircraft. Volume 5: Air induction system and Experimental aerodynamic characteristics for a landing gear modules. Part 2: Landing gear cylindrical body of revolution with side strakes module and various noses at angles of attack from 0 [AD-A00 2858] N75-20309 degrees to 58 degrees and Bach numbers from 0.6 A structural weight estimation program (SWEEP) for to 2.0 aircraft. Volume 6: wing and empennage module. (NASA-TN-X-3130] 4475-19181 Book 1: Technical discussion sections 1 and 2 SUBSONIC WIND TUNNELS [AD-A002864] N75-20310 An experimental study of the structure and A structural weight estimation program (SWEEP) for acoustic field of a jet in a cross stream aircraft. Volume 6: wing and empennage module. (AIAA PAPER 75-1460] A75-28348 Book 2: Technical discussion, sections 3 and 4 SUCTION [AD-A002865] N75-20311 Characteristics of pressure fluctuations in A structural weight estimation program (SWEEP) for distributed suction of a turbulent boundary layer aircraft. Volume 6: wing and empennage module. A75-27052 Book 3: Technical discussion, section 5 SUPERCAVITATING FLOW [AD-A002866] 4475-20312 Lift coefficients on a supercavitating jet-flapped A structural weight estimation program (SWEEP) for foil between rigid walls aircraft. Volume 6: Wing and empennage module. A75-26554 Appendix A: General information for nodule flow SUPERCONDUCTIVITY charts and listings. Appendix B: Program flow Program for the development of a superconducting charts, overlays (8,0), (14,0), (15,0), (16,0) generator. Part 1: Phase 1 --- including and (17,0) critical component tests [AD-A002859] N75-20313 [AD-A001649] N75-19546 A structural weight estimation program (SWEEP) for SUPERCRITICAL FLOW aircraft. Volume 6: Wing and empennage module. Unsteady lift forces on a vibrating cylinder in a Appendix C: Program flow charts, overlays (9,0) supercritical flow and (10,0) A75-26480 [AD-A002860] 4475-20314 SUPERCRITICAL WINGS A structural weight estimation program (SWEEP) for Opportunities for aerodynamic-drag reduction aircraft. Volume 6: Wing and empennage module. H75-20237 Appendix D: Program flow charts, overlay (18,0) SUPERHIGB FREQUENCIES [AD-A002861] N75-20315 Dual band airborne antenna study A structural weight estimation program (SWEEP) for (AD-A002043] 4475-19219 aircraft. Volume 6: Wing and empennage module. SUPERSONIC AIRCRAFT Appendix 5: Program listings, overlays (8,0), multi-slot film cooling of supersonic aircraft (14,0), (15,0), (16,0), and (17,0) using air as a coolant (AO-A002862] 4475-20316 (AD-A002673] 4475-19239 A structural weight estimation program (SWEEP) for Development of longitudinal handling qualities aircraft. Volume 6: Wing and empennage module. criteria for large advanced supersonic aircraft Appendix F: Program listings, overlays (9,0), [NASA-CR-137635] 4475-20345 (10,0) and (18,0) SUPERSONIC COMPRESSORS [AD-A002863] N75-20317 The coexistence of two supersonic plane flows in A structural weight estimation program (SWEEP) for the presence of a longitudinal pressure gradient aircraft. Volume 7: Fuselage module N75-20209 (AD-A002867) 4475-20318 SUPERSONIC FLOW A structural weight estimation program (SWEEP) for The disappearance of the wake shock behind a aircraft. Volume 7: Fuselage module. Appendix cylinder in a supersonic flow at high Reynolds A: Nodule flow charts and FORTRAN lists. number - Appendix B: Fuselage module sample output A75-26414 (AD-A002868] 4475-20319 Supersonic flow past intersecting surfaces --- wings A structural weight estimation program (SWEEP) for A75-26882 aircraft. Volume 8: Programmer's manual The coexistence of two supersonic plane flows in [AD-A002869] 4475-20320 the presence of a longitudinal pressure gradient A structural weight estimation program (SWEEP) for 4475-20209 aircraft. Volume 9: User's manual SUPERSONIC INLETS [AD-A002870] N75-20321 Evaluation of some control-volume techniques for A structural weight estimation program (SWEEP) for analysis of shock-boundary layer interactions in aircraft. Volume 9: User's manual, appendix A supersonic inlets [AD-A002871] 4475-20322 (NASA-TN-5-3186) 4415-20256 A structural weight estimation program (SWEEP) for SUPERSONIC JET FLOW aircraft. Volume 10: Flutter optimation Development of acoustic disturbances in supersonic stand-alone program annular jets [AD-A002872] N75-20323 A75-26234 A structural weight estimation program (SWEEP) for The impingement of non-uniform, axisymmetric, aircraft. Volume 11: Flexible airloads supersonic jets on a perpendicular flat plate stand-alone program A75-26684 (AD-A002873] N75-20324 A problem in supersonic jet theory SUBSONIC AIRCRAFT A75-26697 On the future of jet propulsion in subsonic Supersonic jet noise suppression with multitube transport aviation nozzle/ejectors A75-27777 [AIAA PAPER 75-501] A75-27936 New evidence of the mechanisms of noise generation Some recent developments in supersonic jet noise and radiation of a subsonic jet reduction [AIAA PAPER 75-502] A75-27937 SUBSONIC FLOW SUPERSONIC NOZZLES A subsonic axisymmetric wake in a viscous gas - Experimental and theoretical analysis of three A75-26891 dimensional turbulent boundary layers in a Theoretical and experimental studies of curved supersonic channel discrete-tone rotor-stator interaction noise A15-26476 (AjAR PAPER 75-443) A75-27926 A method of calculating aerodynamic-nozzle Subsonic jet noise in flight based on some recent profiles with passage through the sound barrier wind-tunnel tests A75-26881 [AIRA PAPER 75-462] A75-27930 Some recent developments in supersonic jet noise reduction [AIAA PAPER 75-502) A75-27937 SUPERSONIC TRANSPORTS Flight-critical digital control system evaluation [AIAA PAPER 75-566) A75-26125

A-30 SUBJECT INDEX TEST EQUIPMENT

Paper pilot ponders supersonic transports A structural weight estimation program (SWEEP) for N75-19135 aircraft. Volume 6: Wing and empennage nodule. Low-speed wind-tunnel tests of a 1/10-scale model Appendix C: Program flow charts, overlays (9,0) of a blended arrow advanced supersonic transport and (10,0) aerodynamic control and stability [AD-A002860] N75-20314 (NASA-TM-X-72671] 875-19226 A structural weight estimation program (SWEEP) for Comparison of parametric duct-bursing turbofan and aircraft. Volume 6: Wing and empennage module. non-afterburning turbojet engines in a Each 2.7 Appendix 0: Program flow charts, overlay (18,0) transport [AD-A002861] 875-20315 (NASA-TM-X-71679) 875-19247 A structural weight estimation program (SWEEP) for SUPERSONIC WAKES aircraft. Volume 6: Wing and empennage module. The disappearance of the wake shock behind a Appendix E: Program listings, overlays (8,0), cylinder in a supersonic flow at high Reynolds (14,0), (15,0), (16,0), and (17,0) number [AD-A002862] 875-20316 A75-26414 A structural weight estimation program (SWEEP) for SURFACE PROPERTIES aircraft. Volume 6: Wing and empennage module. Supersonic flow past intersecting surfaces --- wings Appendix F: Program listings, overlays (9,0), A75-26882 (10,0) and (18,0) SURVEILLANCE RADAR [AD-A002863] N75-20317 Multi-site intermittent positive control Major Item Special Study (MISS), 011-18 tail rotor algorithms for the discrete address beacon system hangers (AD-A001112/2] 875-19214 (AD-A003263] 875-20325 Provisional message formats for the DABS/NAS TAIL SURFACES interface (revision 1) A method for calculating unsteady forces due to (FAA-RD-74-63-A] 875-19216 interaction between tail surfaces SWEPT WINGS A75-26477 An example of boundary layer flow with two TAKEOFF EONS instability regions Take-off instrument for assessing achieved A75-28680 performance during take-off and a take-off SYSTEMS ENGINEERING accident analysed in context An experimental TDNA network for airborne warning A75-28769 and control systems interoperability TECHNOLOGICAL FORECASTING demonstrations New horizons in air traffic control [AIAA PAPER 75-563] A75-26724 (AIAA PAPER 75-569] A75-26728 Application of digital systems to Army avionics On the future of jet propulsion in subsonic [AIAA PAPER 75-587] A75-26738 transport aviation Interaction of military/civil position location A75-27777 and reporting systems --- of ATC The next forty years in aviation [AIAA PAPER 75-561] A75-28467 N75-20228 System approach to civil aircraft navigation using TECHNOLOGY ASSESSMENT digital technology Digital avionics - An overview --- Air Traffic [AIAA PAPER 75-572] A75-28469 Control Radar Beacon System Development of an R.F. telemetry system --- for (AIAA PAPER 75-553] A75-26721 aircraft engine stress and temperature data Digital flight control systems - Considerations in A75-28778 implementation and acceptance A structural weight estimation program (SWEEP) for [AIAA PAPER 75-577] A75-26734 aircraft. Volume 1: Executive summary Fly-by-wire and control configured vehicles - [AD-A002850] 875-20301 Rewards and risks A structural weight estimation program (SWEEP) for A75-27367 aircraft. Volume 2: Program integration and 'By the application of power' /21st Cayley data management module. Part 1: Program Memorial Lecture/ --- technical survey of integration aircraft engines [AD-A002852] 875-20302 A75-27368 SISTERS STABILITY Deutsche Gesellschaft fuer tuft- und Raumfahrt, Stability analysis of stochastic composite systems Yearbook 1973 --- German book application to control of aircraft and A75-27978 nonlinear systems European aeronautics and astronautics at the A75-27919 crossroads A75-27981 TECHNOLOGY TRANSFER T Tests of laser metal removal for future flexible TA CA N rotor balancing in engines TACAN/DEE digital data broadcast design plan. [SAE PAPER 750170] 175-26591 Volume 1: Operational analysis TELEMETRY (AD-A001403/5] 875-19213 Development of an R.F. telemetry system --- for TAIL ASSEMBLIES aircraft engine stress and temperature data Wind tunnel tests of a symmetrical airfoil with A75-28718 scoop fed slots Wide bandwidth optical telemetry link for ground [NASA-CR-132568] 875-19183 testing of equipment in high EMI environments A structural weight estimation program (SWEEP) for A75-28781 aircraft. Volume 6: Wing and empennage module. Provisional message formats for the DABS/WAS Book 1: Technical discussion sections 1 and 2 interface (revision 1) [AD-A002864] 875-20310 [FAA-RD-74-63-A] 875-19216 A structural weight estimation program (SWEEP) for TEMPERATURE MEASURING INSTRUMENTS. aircraft. Volume 6:. Wing and empennage module. Development of an B.?. telemetry system --- for Book 2: Technical discussion, sections 3 and 14 aircraft engine stress and temperature data [AD-A002865] 875-20311 175-28718 A structural weight estimation program (SWEEP) for TENNESSEE aircraft. Volume 6: Wing and empennage module. Delta Air Lines Incorporated McDonnell Douglas Book 3: Technical discussion, section 5 DC-9-32, N3323L, Chattanooga Municipal Airport, [AD-A002866] 875-20312 Chattanooga, Tennessee A structural weight estimation program (SWEEP) for (PB-2381479/0] 875-20278 aircraft. Volume 6: Wing and empennage nodule. TEST EQUIPMENT Appendix A: General information for module flow Digital avionics information system /DAIS/ charts and listings. Appendix B: Program flow integrated test bed development charts, overlays (8,0), (14,0), (15,0), (16,0) (AIAA PAPER 75-588] A75-26739 and (17,0) [AD-A002859] 875-20313

A-31

THEODOLITES SUBJECT INDEX

THEODOLITES TORSIONAL VIBRATION Evaluation of the Rubino procedure for radio Nonlinear torsional vibrations of thin-walled telemetric theodolite positioning beams of open section [AD-A004317] N75-20353 A75-26410 THERMAL INSULATION TOXIC HAZARDS Multi-slot film cooling of supersonic aircraft A study of the effects on mice of smoke and gases using air as a coolant from controlled fires in simulated aircraft cabins (AD-A002673] N75-19239 A75-27073 THERMAL RESISTANCE TRACKING (POSITION) Processable high temperature resistant polymer The STRADA flight path tracking system matrix materials (RAE-LIB-TRANS-1813] N75-19209 [NASA-TN-171682] N15-19367 TRAILING EDGES THERMODYNAMIC CYCLES On the viscous flow about the trailing edge of a On the future of let propulsion in subsonic rapidly oscillating plate transport aviation A75-26469 A75-27777 Inviscid to turbulent transition of trailing Part load specific fuel consumption of gas turbines vortices A75-28650 [NASA-CH-1142298] N75-19172 THERMODYNAMIC EFFICIENCY TRAJECTORY ANALYSIS Part load specific fuel consumption of gas turbines Analysis of in-flight disintegration accidents A75-28650 N75-19197 Quarterly bulletin of the Division of Mechanical TRAJECTORY CONTROL Engineering and the National Aeronautical A concept of flight dynamics control --- for Establishment, 1 October - 31 December 1974 aircraft [DME/NAE-1974(4) ] N75-20249 A75-27180 THIN AIRFOILS TRANSONIC FLOW Cavitating flow past a vibrating thin-section wing Survey on two calculation methods in transonic profile regime A75-26895 035-28096 THIN FILMS Theory of transonic flow around a profile Feasibility of adapting a thin film permeable A75-28651 membrane to let transport fuel tank inerting Study of transonic flow over various bodies system N75-19169 (AD-A003799] N75-20295 A method for predicting unsteady aerodynamic THIN WALLS forces on oscillating wings with thickness in Nonlinear torsional vibrations of thin-walled transonic flow near Mach number 1. Part 1: beams of open section Two-dimensional theory. Part.2: Rectangular A75-26410 wings THREE DIMENSIONAL BOUNDARY LAYER [NAL-TR-368T-PT-1] N75-19174 Experimental and theoretical analysis of three An exact solution for transonic potential flow dimensional turbulent boundary layers in a past aerofoil sections curved supersonic channel (NAL-TR-383] N75-19176 A75-26476 Determination by means of hydraulic analogy of the Calculation of heat transfer at the lines of flow transonic flow in a blade cascade of a three-dimensional boundary layer in a N75-20213 nonuniform external flow TRANSONIC NOZZLES A75-26894 A method of profiling short two-dimensional nozzles THREE DIMENSIONAL FLOW for transonic wind tunnels Calculation of the flow around blunted, A75-26880 nonsyminetric cones with large aperture angle TRANSONIC SPEED A75-28652 Experimental aerodynamic characteristics for a The three-dimensional character of a Cross flow cylindrical body of revolution with side strakes around a circular cylinder and various noses at angles of attack from 0 A75-28654 degrees to 58 degrees and Mach numbers from 0.6 THREE DIMENSIONAL MOTION to 2.0 Mechanics of optimum three-dimensional motion of [NASA-TM-X-3130] N75-19181 aircraft in the atmosphere TRANSONIC WIND TUNNELS [NASA-TT-F-777] N75-19182 A method of profiling short two-dimensional nozzles THRUST REVERSAL for transonic wind tunnels Noise of model target type thrust reversers for A75-26880 engine-over-the-wing applications TRANSPORT AIRCRAFT A75-27853 Digital flight control systems - Considerations in Some notes on the thermodynamics of thrust implementation and acceptance reversal in flight [AIAA PAPER 75-517] 035-26134 N75-20212 Integration of aft-fuselage- mounted flow through Performance of an isolated two-dimensional engine nacelles on an advanced transport variable-geometry wedge nozzle with translating configuration at Mach numbers from 0.6 to 1.0 shroud and collapsing wedge at speeds up to Mach [NASA-TM-X-3178] N75-19180 2.01 Fuel conservation possibilities for terminal area [NASA-TN-D-7906] N75-20247 compatible aircraft TINE DIVISION MULTIPLEXING [NASA-CR-132608] N15-19224 An experimental TDMA network for airborne warning Special study: Safety aspects of emergency and control systems interoperability evacuations from air carrier aircraft demonstrations (PB-238269/5] N75-20275 [AIAA PAPER 75-563] A15-26724 TRANSPORTATION What have we learned from applying digital Some air cushion technology research in Canada technology to cabin/passenger multiplex systems N75-20251 cost and weight analysis TURBINE BLADES [AIAA PAPER 75-574] A75-26732 High-temperature alloys and the aircraft gas turbine SEEK BUS - A time division multiple access system A75-27877 ATC applications Metal matrix composites for aircraft propulsion [AIAA PAPER 75-564] A75-28468 systems TIME SIGNALS [NASA-TM-X-11685] N15-19245 The U.S. Candidate Microwave Landing System - A Determination by means of hydraulic analogy of the new generation of avionics/ground equipment transonic flow in a blade cascade (AIAA PAPER 75-607] A75-28472 N75-20213

A-32

SUBJECT INDEX UNSTEADY FLOW

Measurement and analysis of the unsteady normal TURBULENT PLOW force and pitching moment on an axial flow fan Analysis of thick turbulent jet flowing round: A rotor blade element circular cylinder [AD-A002739] N75-20343 N75-19168 TURBINE ENGINES TURBULENT HEAT TRANSFER Non-dimensional methods for the measurement of The prediction of turbulent heat transfer to wedge level flight performance of turbine engined compression corners and cylinder-flare bodies at helicopters hypersonic speeds [ESDU-74042] 1175-20289 (IC7AERO-73-03) 1175-202614 TO RB OC 0 MPR ES SOB S TURBULENT JETS Effect of interference between moving blade rows Developments in jet noise modeling - Theoretical on cascade flutter. I - Experiment on compressor predictions and comparisons with measured data cascade in flexure mode [AIAA PAPER 75-477] A75-27933 A75-26553 Ratio of peak frequencies of jet self and shear Elementary method of graphic replotting of a noise spectra characteristic of an uncooled turbocoapressor A75-28400 when the intake temperature and number of TURBULENT WAKES revolutions are varied The three-dimensional character of a cross flow A75-26672 around a circular cylinder Theoretical and experimental studies of A75-28654 discrete-tone rotor-stator interaction noise The dynamic response of aircraft encountering (AIAA PAPER 75-443] A75-27926 aircraft wake turbulence TURBOFAN ENGINES N75-19170 On the future of let propulsion in subsonic Inviscid to turbulent transition of trailing transport aviation vortices A75-27777 [NASA-CR-142298] 1175-19172 Radiation of duct noise out through a jet flow On wake vortex alleviation acoustic field model for aircraft engine N75-20231 [AIAA PAPER 75-1157] A75-27928 Wind tunnel studies of the turbulent wake behind Comparison of parametric duct-burning turbofan and self propelled slender bodies non-afterburning turbojet engines in a Mach 2.7 [AD-A002396] 1175-20272 transport Wind tunnel investigation of helicopter rotor wake [NASA-TM-I-71679] N75-19247 effects on three helicopter fuselage models Impact of turbine modulation on variable-cycle [NASA-TM-X-3185-SUPPL] N75-20294 engine performance. Phase 1 and 2: Design TWISTED WINGS fabrication and rig test, part 1 Determination of load factors for the impact of a (AD-A002543) N75-20337 profile against the surface of a liquid Impact of turbine modulation on variable-cycle A75-26879 engine performance. Phase 3: Engine TWO DIMENSIONAL FLOW modification and sea level test, part 2 Heat transfer in separated and reattached flows - [AD-A002544] 1175-20338 An annotated review Impact of turbine modulation on variable-cycle A75-26685 engine performance. Phase 4: Additional A method for predicting unsteady aerodynamic hardware design and fabrication, engine forces on oscillating wings with thickness in modification, and altitude test, part 3A transonic flow near Mach number 1. Part 1: [AD-A002545] 1175-20339 Two-dimensional theory. Part 2: Rectangular Impact of turbine modulation on variable-Cycle wings engine performance. Phase 4: Additional [NAL-TR-368T-PT-1] 1175-19174 hardware design and fabrication, engine Calculation of two-dimensional and axisymmetric modification, and altitude test, part 3B bluff body potential flow [AD-A0025 116] 1175-20340 (IC-AERO-74-07] 1175-19191 TURBOFANS TWO DIMENSIONAL JETS Theoretical and experimental studies of A problem in supersonic jet theory discrete-tone rotor-stator interaction noise A75-26697 [AIAA PAPER 75-443] A75-27926 The role of rotor blade blockage in the propagation of fan noise interaction tones U [AIAA PAPER 75-447] A75-27927 OH-i HELICOPTER TURBOJET ENGINES Natural icing tests. UH-1H helicopter An investigation of the noise from a scale model [AD-A002077] 1175-19194 of an engine exhaust system --- turbojet noise Major Item Special Study (MISS) , OH-1C tail rotor measurement blade [AIAA PAPER 75-459] A75-27929 [AD-A001714] 1175-19230 .Jet noise suppressors for turbojet engines Operational use of the OH-i 11 helicopters in A75-28227 Arctic environment Rotating engine design and cycle analysis program [AD-A002603] 1175-19236 [AD-A002314] 1175-20342 UNIVERSITIES TURBOMACHINE BLADES University research in aeronautics Lifting surface theory for a rotating subsonic or 1115-20241 transonic blade row General aviation's future need for research [ARC-R/N-3740] N75-19185 1175-20242 TURBOMACHIEERY University research in aeronautics Unified analysis of ducted turbomachinery noise 1175-202113 A15-27861 UNSTEADY FLOW TURBULENCE EFFECTS Starting vortex, separation bubbles and stall - A Analysis of thick turbulent jet flowing round: A numerical study of laminar unsteady flow around circular cylinder an airfoil N75-19168 A75-26212 TURBULENT BOUNDARY LAYER A method for calculating unsteady forces due to The expansion of a hypersonic turbulent boundary interaction between tail surfaces layer at a sharp corner A75-26477 A75-26466 Nonlinear problem of the unsteady flow past an Experimental and theoretical analysis of three airfoil lattice dimensional turbulent boundary layers in a A75-28671 curved supersonic channel Unsteady viscous flow past a lifting plate A75-26476 N75-19171 Characteristics of pressure fluctuations in distributed suction of a turbulent boundary layer A75-27052

A-33 USER MANUALS (COMPUTER PROGRAMS) SUBJECT INDEX

USER NANUALS (COMPUTER PROGRAMS) VISCOUS FLUIDS Users manual for UCIN vehicle occupant crash study Unsteady viscous flow past a lifting plate model, version 2 975-19171 (AD-A001801] 975-19211 VISUAL CONTROL A structural weight estimation program (SWEEP) for A conformal head-up display for the visual approach aircraft. Volume 8: Programmer's manual 875-19138 [AD-A002869] 975-20320 VISUAL FLIGHT RULES A structural weight estimation program (SWEEP) for Engineering design handbook. Helicopter aircraft. Volume 9: User's manual engineering, part 1: Preliminary design --- for [AD-A002870] 975-20321 VFR operation A structural weight estimation program (SWEEP) for (AD-A002007] 875-19238 aircraft. Volume 9: User's manual, appendix A VISUAL TASKS [AD-A002871] 975-20322 Effects of visual flight display dynamics on altitude tracking performance in a flight simulator N75-19127 Y/STOL AIRCRAFT Evaluation of tactual displays for flight control A pilot's report concerning the VTOL YAK 191 B 875-19132 A75-26900 VOLTERRA EQUATIONS Flight tests with the V/STOL experimental aircraft Supersonic flow past intersecting surfaces --- wings YAK 191 B A75-26882 A75-27985 VORTEX SHEETS Estimates of the stability derivatives of a The range of validity in the case of two old helicopter and a Y/STOL aircraft from flight data investigations. I - The origin of lift. II - A75-28201 Collision and gliding processes on the liquid An experimental study of the structure and surface acoustic field of a jet in a cross stream A75-27990 [AIAA PAPER 75-460] A75-28348 Flow past conically-cambered slender delta wings The aerodynamic characteristics and trailing with leading-edge separation vortex wake of propeller Y/STOL configurations [ARC-R/9-3748] 875-19186 A75-28522 VORTICES Technical evaluation report on Fluid Dynamics The aerodynamic characteristics and trailing Panel Symposium on V/STOL Aerodynamics vortex wake of propeller V/STOL configurations [AGARD-AR-78] 875-19585 A75-28522 Estimates of the stability derivatives of a The dynamic response of aircraft encountering helicopter and a V/STOL aircraft from flight data aircraft wake turbulence H75-20250 N75-19170 VAPORS Inviscid to turbulent transition of trailing Internal-combustion engine/vapour cycle combination vortices (OUEL-1097/74] 875-20336 [NASA-CR-142298] 875-19172 VELOCITY DISTRIBUTION On the calculation of non-linear aerodynamic Computation of the velocity field induced by a characteristics and the near vortex wake planar sou'ce distribution approximating a [AD-A002161] 875-19193 symmetrical non-lifting wing in subsonic flow On wake vortex alleviation [ARC-R/I-3751] 875-20262 815-20231 Some rem'rks on the induced velocity field of a YORTICITI EQUATIONS lifting rotor and on Glauert's formula Starting vortex, separation bubbles and stall - A [AR-CP-1301] N75-20263 numerical study of laminar unsteady flow around VERTICA PERCEPTION an airfoil A display evaluation methodology applied to A75-26212 vertical situation displays -- VERTICAL TAKEOFF AIRCRAFT MA A theoretical method for calculating the WAKES aerodynamic characteristics or arbitrary A wake source model for an inclined flat plate in ejector-jet-flapped wing: Theoretical analysis a uniform stream [AD-A002319] N75-20271 (IC-AERO-74-08) 875-19192 VIBRATION On the calculation of non-linear aerodynamic.- Rotation in vibration, optimization, and characteristics and the near vortex wake aeroelastic stability problems - [AD-A002161] 875-19193 WALL FLOW VIBRATION EFFECTS Experimental and theoretical analysis of three Vibration and temperature survey production AH-1G dimensional turbulent boundary l&yers in a helicopter curved supersonic channel [AD-A002063] 875-19231 - A75-26476 VIBRATION METERS WALL PRESSURE Application of a new slip-ringless propeller blade Characteristics of pressure fluctuations in measurement system distributed suction of a turbulent boundary layer A75-28771 A75-27052 VIBRATION TESTS WARNING SYSTEMS OH-58A propulsion system vibration investigation An experimental TDMA network for airborne warning [AD-A002672] 875-20341 and control systems interoperability Shake test of rotor test apparatus in the 40- by demonstrations 80-foot wind tunnel (AIAA PAPER 75-563) A75-26724 [NASA-TN-X-62418] 975-20350 A new centralised warning display for aircraft A75-28785 VISCOUS FLOW A non-uniqueness of the hypersonic boundary layer Barowe altitude warning system evaluation A75-26195 (AD-A002583] N75-19241 On the viscous flow about the trailing edge of a WAVE DIFFRACTION rapidly oscillating plate Supersonic flow past intersecting surfaces --- wings A75-26469 - A75-26882 A subsonic axisymnetric wake in a viscous gas WEAPON SYSTEMS A75-26891 F-15 computational subsystem --- computer systems Hypersonic, viscous gas flow around a wing of design small aspect ratio (AIAA PAPER 75-590] A75-28470 A75-28653 WEDGE FLOW Analytical comparison of hypersonic flight and The expansion of a hypersonic turbulent boundary wind tunnel viscous/inviscid flow fields layer at a sharp corner (NASA-CH-2489] 875-19586 A75-26466 SUBJECT INDEX 1-15 AIRCRAFT

Interpretation of merged layer behavior for wedges Allowance for the elastic deformation of the wing A75-27496 in its own plane in the calculation of the WEDGES skewsymmetric vibrations of an aircraft with a The prediction of turbulent heat transfer to wedge small-aspect-ratio wing compression corners and cylinder-flare bodies at A75-28687 hypersonic speeds WING PROFILES [IC-AERO-73-03] N75-20264 Cavitating flow past a vibrating thin-section wing WELD TESTS profile Sound welds in wing boxes assured by three A75-26895 techniques Theory of transonic flow around a profile A75-26898 A75-28651 VESTLAND AIRCRAFT Lifting surface for aircraft --- wing profiles Flight simulation of a Wessex helicopter: A (NASA-TT-F-16241) N75-20290 validation exercise WING TIPS [ARC-CP-1299] N75-20298 Flight determination of the rudder power and WIND PROFILES directional stability of the Fairey Delta 2 wind models for flight simulator certification of aircraft using a wingtip parachute landing and approach guidance and control systems (ARC-CP-1298] N75-19267 [AD-A003801] N75-20352 WINGS WIND TUNNEL RODELS Supersonic flow past intersecting surfaces --- wings Integration of aft-fuselage-mounted flow through A75-26882 engine nacelles on an advanced transport Sound welds in wing boxes assured by three configuration at Each numbers from 0.6 to 1.0 techniques (NASA-TN-X-3118] N75-19180 A75-26898 WIND TUNNEL TESTS Influence of sound upon separated flow over wings Subsonic jet noise in flight based on some recent A75-27495 wind-tunnel tests The range of validity in the case of two old [AIAA PAPER 75-862] A75-27930 investigations. I - The origin of lift. II - Effect of forward speed on jet wing/flap Collision and gliding processes on the liquid interaction noise surface [AIAA PAPER 75-475] A75-21932 A75-2l990 Airbus A 300 - Comparison of the flight test Calculations of generalised airforces on two results with the flight performance and flight parallel lifting surfaces oscillating characteristics determined on the basis of harmonically in subsonic flow theory and wind tunnel tests [ARC-R/N-3749] N75-19187 A75-21980 On the calculation of non-linear aerodynamic An experimental study of the structure and characteristics and the near vortex wake acoustic field of a jet in a cross stream [AD-A002161] N15-19193 [AIAA PAPER 75-460] A15-28348 Fatigue-crack growth behavior of C-5A wing control Low-speed wind-tunnel tests of a 1/10-scale model points of a blended arrow advanced supersonic transport [AD-A002553] N75-20299 aerodynamic control and stability A structural weight estimation program (SWEEP) for (NASA-TM-X-72671] N75-19226 aircraft. Volume 6: Wing and empennage module. Characteristics of the Al 31 aircraft: Comparison Book 1: Technical discussion sections 1 and 2 of the results of wind tunnel and flight tests (AD-A002864] N15-20310 noting elasticity correction for wind tunnel A structural weight estimation program (SWEEP) for model aircraft. Volume 6: Wing and empennage nodule. N75-19261 Book 2: Technical discussion,.sections 3 and 4 Wind tunnel investigation of helicopter rotor wake (AD-A002865) N75-20311 effects on three helicopter fuselage models A structural weight estimation program (SWEEP) for [NASA-TN-X-3185-SUPPL] N75-20294 aircraft. VoluEe 6: Wing and empennage module. Exploratory wind tunnel tests of a Book 3: Technical discussion, section 5 shock-swallowing air data sensor at a Bach [AD-A002866] N75-20312 number of approximately 1.83 A structural weight estimation program (SWEEP) for (NASA-TN-X-56030] N75-20329 aircraft. Volume 6: Wing and empennage module. Shake test of rotor test apparatus in the 40- by Appendix A: General information for module flow 80-foot wind tunnel charts and listings. Appendix B: Program flow (NASA-TM-X-62418] N75-20350 charts, overlays (8,0), (14,0), (15,0), (16,0) WIND TUNNELS and (17,0) Analytical comparison of hypersonic flight and [AD-A002859] N75-20313 wind tunnel viscous/inviscid flow fields A structural weight estimation program (SWEEP) for [NASA-CR-2489] N75-19586 aircraft. Volume 6: Wing and empennage module. WINDSHIELDS Appendix C: Program flow charts, overlays (9,0) Development of scratch and spall resistant and (10,0) windshields [AD-A002860] N75-20314 [AD-A002513] N15-20300 A structural weight estimation program (SWEEP) for WING FLAPS aircraft. Volume 6: Wing and empennage nodule. Effect of forward speed on jet wing/flap Appendix D: Program flow charts, overlay (18,0) interaction noise [AD-A002861] N75-20315 [AIAA PAPER 75-475] A75-27932 A structural weight estimation program (SWEEP) for WING LOADING aircraft. Volume 6: Wing and empennage module. Determination of load factors for the impact of a Appendix E: Program listings, overlays (8,0), profile against the surface of a liquid (14,0), (15,0), (16,0), and (17,0) A75-26819 [AD-A002862] N75-20316 Characteristics of pressure fluctuations in A structural weight estimation program (SWEEP) for distributed suctionof a turbulent boundary layer aircraft. Volume 6: Wing and empennage module. Al5-27052 Appendix F: Program listings, overlays (9,0), The 'definition of the motorsegler (10,0) and (18,0) (DFVLR-SONDDR-424] A75-27596 [AD-A002863] N75-20317 Influence of fuselage flexibility on the stress-strain state of the wing A75-28668 X WING OSCILLATIONS I-iS AIRCRAFT Cavitating flow past a vibrating thin-section wing A new flight test data system for NASA profile aeronautical flight research A75-26895 Al5-28l74 Nonlinear problem of the unsteady flow past an airfoil lattice A75-28611

A-35 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING /A Special. Bibliography (Suppl. 59) JULY 1975

Typical Personal Author Index Listing

ASHLEY, H. CIVINSKAS, K. C.__NAUTHE1 University research in aeronautics rA comparison of optimum JP and 182 turbofan N15-202f43 ,-1 engines designed for two subsonic transport ATYARS, J. L missions Supersonic jet noise suppression with multitube I [NASA-TN-X 71622) 875-10945 nozzle/ejectors [AIAA PAPER 75-501] A75-27936 AUERBACH, 8. - NISA PLY 27 gas turbine engine exhaust emission and Li EPORI I ACCESSION I noise measurements NUMBER NUMBER (AD-A001728] R75-19251 B Listings in this index are arranged alphabetically by personal author. The title BARON, J. . N. of the document provides the user with a brief description of the subject matter. Interpretation of merged layer behavior for wedges The report number helps to indicate the type of document cited (e.g.. NASA A75-27t496 report. translation. NASA contractor report). The accession number is located BARON, S. A display evaluation methodology applied to beneath and to the right of the title, e.g. N75- 10945. Under any one authors vertical situation displays name the accession numbers are arranged in sequence with the /AA accession N75-19137 numbers appearing first BARR, N. N. Windmodels for flight simulator certification of A landing and approach guidance and control systems AFONINA, N. L. [AD-A003801] 875-20352 Numerical study of heat exchange at the stagnation BARSBT, J. B. point of a sphere situated in a hypersonic Flow past conically-cambered slender delta wings stream of carbon dioxide gas with leading-edge separation A75-26888 [ARC-R/N-37 118] 875-19186 ARUJA, F_ K. BARTON, C. K. Some recent developments in supersonic jet noise Interior noise considerations for powered-lift reduction STOL aircraft [AIAA PAPER 75-502] . 575-27937 (NASA-TM-X-72675) 875-19248 AKANATSU, Y. BARTON, P. A method for calculating unsteady forces due to The range of airborne processing available to the interaction between tail surfaces future user of the Doppler NLS A75-26477 A75-28792 AL-BABRANI, H. N. . S. BASSIOUNI, N, R. Design of a digital-stability augmentation and Some recent developments in supersonic jet noise control system with gust alleviation and modal reduction suppression (AIAA PAPER 75-502] A75-27937 A75-28432 BAT!, D. . L. ALLEN, J. G.G. & study on aircraft nap display location and Digital computer design guidelines for a full orientation authority fly-by-wire flight control system N75-19128 (AIAA PAPER 75-570) A75-26729 BAZELTAN, L. ALLEN, B. Antennas, a collection, issue 15 A structural weight estimation program (SWEEP) for [AD-A0026 116) 875-19557 aircraft. Volume 9: User's manual BAZZBIN, A. P. [AD-A002870] 875-20321 Calculation of the flow around blunted, A structural weight estimation program (SWEEP) for nonsymuetric cones with large aperture angle aircraft. Volume 9: User's manual, appendix A A75-28652 [AD-A002871] 875-20322 BEARNAN, P. V. ANDERSON, S. B. Calculation of two-dimensional and axisymmetric Design considerations for stall/spin avoidance bluff body potential flow N75-19205 [IC-AERO-714-07] 875-19191 ANDERSON, N. N. BE000B, S. Design and purchase expectations for fracture A new centralised Warning display for aircraft resistance of 700-series aluminum airframe alloys A75-28785 [AD-A002552] N75-20548 BELOTSERKOYSKI!, S. N. Fracture mechanics of tiny cracks near fasteners Dynamics of the motion of a body with allowance (AD-A002554) 875-20777 for the unsteady state of the flow about it ANDRISANI, 0., H [NASA-TT-F-16133) 815-19179 A study for active control research and validation BELOUS, V. A. using the Total In-Flight Simulator (TIPS) Influence of fuselage flexibility on the aircraft stress-strain state of the wing [NASA-CR-132614] 875-19271 A15-28668 ARNOLD, J. D. BBLSTERLING, C. A. Pitch paper pilot revisited Wind tunnel tests of a symmetrical airfoil with N75-19133 scoop fed slots ASCANI, L. [NASA-CR-132568] 875-19183 A structural weight estimation program (SWEEP) for BENNETT, U. R. aircraft. Volume 1: Executive summary Development of longitudinal handling qualities [AD-A002850) N75-20301 criteria for large advanced supersonic aircraft (NASA-CR-137635) 875-20345

B-i BENNETT, J. A. PERSONAL AUTHOR INDEX

BENNETT, J. A. Evaluation of advanced lift concepts and fuel Evaluation of advanced lift concepts and fuel conservative short-haul aircraft, volume 2 conservative short-haul aircraft, volume 1 (NASA-CR-137526] 875-20292 [NASA-CR-137525] N75-20291 BONER, R.-R. Evaluation of advanced lift concepts and fuel opportunities for aerodynamic-drag reduction conservative short-haul aircraft, volume 2 N75-20237 (NASA-CR-137526] N75-20292 BRARWELL, A. B. S.. Evaluation of active control technology for short Some remarks on the induced velocity field of a haul aircraft lifting rotor and on Glauert's formula (NASA-CR-137634] 875-20344 [ARC-CP-1301] 875-20263 BETEILLE, B. BRIGGS, 0. . G. Airbus A 300 - Comparison of the flight test Heat transfer in separated and reattached flows - results with the flight performance and flight An annotated review characteristics determined on the basis of A75-26685 • theory and rind tunnel tests BRINDLE!, A. B. A75-27980 resting the ELS Doppler concept BETTERIDGE, N. A75-28802 High-temperature alloys and the aircraft gas turbine BROOKS, G. V..N. 675-21811 Some trends in aircraft design: Structure 875-20235 HEAT, N. V. Effect of forward speed on jet ring/flap BRONALL, N. interaction noise Feasibility of adapting a thin film permeable [6166 PAPER 75-4751 675-27932 membrane to jet transport fuel tank inerting BRUTIANI, P. K. system Some recent developments in supersonic let noise [60-6003799] 875-20295 reduction BROWN, S. N. [6166 PAPER 75-502] 675-27937 A non-uniqueness of the hypersonic boundary layer BIGGERS, J. C. - A75-26195 Shake test of rotor test apparatus in the 40- by On the viscous flow about the trailing edge of a 80-foot wind tunnel rapidly oscillating plate (NASA-TM-X-62418] 875-20350 A75-26469 BIRCHEN000H, J. P. BRUCE, B. . P. Airborne equipment for use with the microwave Measurement and analysis of the unsteady normal landing system force and pitching moment on an axial flow fan 675-28790 rotor blade element BISHOP, D. E. (60-6002739] 875-20343 Comparison of airport measurements of approach BRYCE, N. 0. noise produced by jet aircraft An investigation of the noise from a scale model A75-27852 of an engine exhaust system BLACK, J. B. [AIAA PAPER 75-459] 675-27929 Reliability life cycle of a complex electronic Subsonic jet noise in flight based on some recent airborne equipment wind-tunnel tests 675-27839 [6166 PAPER 15-462] 675-27930 BLAHA, B. J. BUKBANOVA, N. S. Integration of aft-fuselage-mounted flow through Mechanics of optimum three-dimensional motion of engine nacelles on an advanced transport aircraft in the atmosphere configuration at Bach numbers from 0.6 to 1.0 [NASA-TT-F-777] 875-19182 (NASA-TN-X-31781 875-19180 BULLEN, N. I. BLAIR, P. K. The variability of fatigue damage from flight to The range of airborne processing available to the flight future user of the Doppler MIS [ARC-CP-1297] 875-20297 A75-28792 BURDOEF, B. BLAUGHER, R. D. Selected examples of the evaluation of VAK 191 B Program for the development of a superconducting flight tests generator. Part 1: phase 1 875-19266 [60-6001649] N75-19546 BURNS, B. . B. A. BLENK, H. Fly-by-wire and control configured vehicles - Deutsche Gesellschaft fuer Luft- and Raumfahrt, Rewards and risks Yearbook 1973 675-27367 675-27978 BURRELL, G. J. BLOT, A. N. The performance in illuminances up to 80,000 lux The expansion of a hypersonic turbulent boundary of a light emitting diode display having a 3 mm layer at a sharp corner character height 675-26466 615-27526 BOELKOW, L. BUTLER, 3. P. E'Iropean aeronautics and astronautics at the Development of statistical fatigue failure crossroads characteristics of 0.125 inch 2024-T3 aluminum 675-27981 under simulated flight-by-flight loading BOHR, J. G. (AD-A002310] 875-20554 Development of longitudinal handling qualities BYAR, T. criteria for large advanced supersonic aircraft A structural weight estimation program (SWEEP) for [NASA-CR-137635] 875-20385 aircraft. Volume 11: Flexible airloads BOIKO, G. L. stand-alone program Determination of load factors for the impact of a [AD-A002813] N75-20324 profile against the surface of a liquid A75-26879 BORN, G. J. Flight path control and performance analysis, CALHOUN, L. C. phases 1 and 2. Integrated display, phase 3 Testing the MLS Doppler concept fAD-6002014] 875-19269 675-28802 BORON, B. CANELIER, I. Digital flight control systems for tactical An experimental study of the structure and • fighters. Volume 2: Documentation of the acoustic field of a jet in a cross stream digital control analysis software (DIGIKON) [6166 PAPER 75-460] 675-28348 [AD-6002327] 875-20349 CANT??, B. A. BONDER, B. K. Development of longitudinal handling qualities Evaluation of advanced lift concepts and fuel criteria for large advanced supersonic aircraft conservative short-haul aircraft, volume 1 [NASA-CR-137635] N75-20345 [NASA-CR-137525] 875-20291

B-2 PERSONAL AUTHOR INDEX DO LEO, A. N.

CARNEGIS, I. A. DAVENPORT, V. R. Rotating engine design and cycle analysis program Impact of turbine modulation on variable-cycle [AD-A002314] N75-20342 engine performance. Phase 1 and 2: Design CARTER, I. J. fabrication and rig test, part 1 Instrument system test. Elliott helicopter air [0.0-0.002543] 1175-20337 data system Impact of turbine modulation on variable-cycle [AD-A002332] 1175-20331 engine performance. Phase 3: Engine CASTELLON, P. F. modification and sea level test, part 2 Crash survivability [AD-A002544] 1175-20338 1175-19203 Impact of turbine modulation on variable-cycle CHALOFF, D. engine performance. Phase 4: Additional A structural weight estimation program (SWEEP) for hardware design and fabrication, engine aircraft. Volume 5: Air induction system and modification, and altitude test, part 30. landing gear nodules. Part 1: Air induction [AD-A002545] 1175-20339 system nodule Impact of turbine modulation on variable-cycle [AD-A002857] 1175-20308 engine performance. Phase 4: Additional A structural weight estimation program (SWEEP) for hardware design and fabrication, engine aircraft. Volume 5: Air induction system and modification, and altitude test, part 38 landing gear modules, part 2: Landing gear [AD-A002546] 1175-20340 nodule DAVIES, D. B. (AD-A002858] 1175-20309 Calculations of generalised airforces on two A structural weight estimation program (SWEEP) for parallel lifting surfaces oscillating aircraft. Volume 9: User's manual harmonically in subsonic flow (AD-A002870] 1175-20321 [ARC-R/H-3749] 1175-19187 A structural weight estimation program (SWEEP) for DAVIES, N. B. aircraft. Volume 9: User's manual, appendix A A wake source model for an inclined flat plate in [ AD-A002871] N75-20322 a uniform stream CHALUPOVA, V. (IC-AERO-4-08] 1175-19192 Classification problems of aircraft noise DEBTS, D. A.A. A75-27943 Development of a remote digital augmentation CHANDLER, G. S., JR. system and application to a remotely piloted Application of digital systems to Army avionics research vehicle [AIAA PAPER 75-587] A75-26738 [NASA-TN-D-7941] 1175-20293 CR1111, R. T. N. DELEPIERE-NYS, C. A study for active control research and validation Air Europe: The policy of cooperation among using the Total In-Plight Simulator (TIPS) airline companies of the European Six aircraft 0.75-26499 (NASA-CR-132614] 1175-19271 DENAN, 3. 0.. CHISTOY, 10. I. PLT 27 gas turbine engine exhaust emission and Study of two hypersonic, azisymmetric, shaped noise measurements nozzles with smooth contour [0.0-0.001728] 1175-19251 A75-28658 DENISOVA, N. V. CLIME, T. B. Study of two hypersonic, axisymmetric, shaped Aircraft guidance for automatic collision avoidance nozzles with smooth contour A75-27178 A75-28658 COCKING, B. J. DEYLIN, B. Y. Subsonic jet noise in flight based on some recent Flight test of a digital guidance and control wind-tunnel tests system in a DC-10 aircraft (AIAA PAPER 75-462] 0.75-27930 [AIAA PAPER 75-567] 0.75-26726 COLLINS, F. S. DEWEY, D. E. Influence of sound upon separated flow over wings Design of the DAIS control and display core element A75-27495 (AIAA PAPER 75-6001 0.75-26745 COLTEL, B. DILLON, J. D. Lifting surface for aircraft Pitch paper pilot revisited (NASA-TT-F-16241] N75-20290 N75-19133 CONRAD, E. V. Roll paper pilot Trends in aircraft noise control N75-19134 1175-20229 DIXON, G.. 3. COSTAKIS, V. G. Impact of turbine modulation on variable-cycle An experimental investigation of compressor stall engine performance. Phase 1 and 2: Design using an on-line distortion indicator and signal fabrication and rig test, part 1 conditioner [AD-A002543] 1175-20337 (NASA-TN-I-3182] 1175-20248 Impact of turbine modulation on variable-cycle COUCH, L. N. engine performance. Phase 3: Engine Exploratory wind tunnel tests of a modification and sea level test, part 2 shock-swallowing air data sensor at a Mach [AD-A002544] 1175-20338 number of approximately 1.83 Impact of turbine modulation on variable-cycle [NASA-TM-X-56030) 1175-20329 engine performance. Phase 4: Additional COUSTEIX, J. hardware design and fabrication, engine Experimental and theoretical analysis of three modification, and altitude test, part 3A dimensional turbulent boundary layers in a [AD-A002545] 1175-20339 curved supersonic channel Impact of turbine modulation on variable-cycle A75-26476 engine performance. Phase 4: Additional hardware design and fabrication, engine modification, and altitude test, part 38 D [AD-A002546] N75-20340 DANIELS, P. G. DONE!, J. On the viscous flow about the trailing edge of a Astrolabe - A synthetic circular aperture system rapidly oscillating plate for landing and navigation A75-26469 A75-28793 DASARO, J. A. DOSANJH, D. S. Application of digital systems to Army avionics Some recent developments in supersonic jet noise (AIAA PAPER 75-587] A75-26738 reduction DAUGHADAY, H. [AIAA PAPER 75-502] A75-27937 A study for active control research and validation DO LEO, A. N._ using the Total In-Flight Simulator (TIPS) Altimeters - The way ahead aircraft A75-28788 (NASA-CR-132614] 1175-19271

B-3 DUBERG, J. E. PERSONAL AUTHOR INDEX

DUBERG, J. E. FERRILL, R. S. University research in aeronautics Evaluation of advanced lift concepts and fuel N75-20241 conservative short-haul aircraft, volume 1 DUKES, T. A. (NASA-CR-137525) N75-20291 Plight path control and performance analysis, Evaluation of advanced lift concepts and fuel phases 1 and 2. Integrated display, phase 3 conservative short-haul aircraft, volume 2 [AD-A002014] N75-19269 (NASA-CR-137526] N75-20292 DUNN, K. FERRIS, J. B. Digital avionics-overview - Airframe Dual hand airborne antenna study manufacturer's viewpoint [AD-A002043] N75-19219 [AIAA PAPER 75-552] A75-26720 FINNEGAN, P. DUEBIN, B. J. Flight test evaluation of SECANT VECAS collision Flight path control and performance analysis, avoidance system phases 1 and 2. Integrated display, phase 3 [AD-A002281 ] N75-19220 [AD-A002014] N75-19269 FIORINI, V. DYER, V. J. Noise certification of aircraft An improved automated structural optimization A75-28223 program FISCHER, A. [AD-A002688] N75-19237 Impact of turbine modulation on variable-cycle engine performance. Phase 1 and 2: Design fabrication and rig test, part 1 E [AD-A002543] N75-20337 EDWARDS, J. L. Impact of turbine modulation on variable-cycle 'By the application of power' /21st Cayley engine performance. Phase 3: Engine Memorial Lecture! modification and sea level test, part 2 A75-27368 [AD-A002544] N75-20338 EDWARDS. J. V. Impact of turbine modulation on variable-cycle Development of a remote digital augmentation engine performance. Phase 4: Additional system and application to a remotely piloted hardware design and fabrication, engine research vehicle modification, and altitude test, part 3A (NASA-TN-D-7941] N75-20293 (AD-A002545] N75-20339 EFRBNOV, I. I. Impact of turbine modulation on variable-cycle Cavitating flow past a vibrating thin-section wing engine performance. Phase 4: Additional profile hardware design and fabrication, engine A75-26895 modification, and altitude test, part 3B EGGSPUEHLER, J. J. [AD-A002546] N75-20340 The accident record in terms of the pilot FISHER, N. .3. N75-19202 Application of digital systems to Army avionics EISENBENG, J. D. [AIAA PAPER 75-587] A75-26738 Preliminary evaluation of turbofan cycle FIVEL, H.. .3. parameters and acoustical suppression on the Analytical comparison of hypersonic flight and noise and direct operating cost of a commercial wind tunnel viscous/inviscid flow fields Mach 0.85 transport [NASA-CR-2489] N75-19586 [NASA-TM-X-71664] N75-19244 FLEDDERJOHN, K. N. ELLIS, B. Impact of turbine modulation on variable-cycle The performance in illuminances up to 80,000 1LIX engine performance. Phase 1 an 2: Design of a light emitting diode display having a 3 mm fabrication and rig test, part 1 character height [AD-A002543] N75-20337 A75-27526 Impact of turbine modulation on variable-cycle ELLIS, D. R. engine performance. Phase 3: Engine General aviation handling qualities research modification and sea level test, part 2 N75-19204 (AD-A002544] N75-20338 ELLISON, T. A. Impact of turbine modulation on variable-cycle System approach to civil aircraft navigation using engine performance. Phase 4: Additional digital technology hardware design and fabrication, engine [AIAA PAPER 75-572] A75-28469 modification, and altitude test, part 3A EMBLETON, T. F. V. [AD-A002545] N75-20339 Propagation of aircraft noise near airports - Impact of turbine modulation on variable-cycle Effects of hillsides, inversions and source engine performance. Phase 4: Additional directionality hardware design and fabrication, engine A75-27859 modification, and altitude test, part 38 EROOS, J. I. [AD-A002546] N75-20340 Multi-slot film cooling of supersonic aircraft FLEMING, D. P. using air as a coolant Tests of laser metal removal for future flexible [AD-A002673] N15-19239 rotor balancing in engines EROSHIN, V. A. [SAM PAPER 7501701 A75-26591 Determination of load factors for the impact of a FLETCHER, J. C. profile against the surface of a liquid Aeronautics in the American society A75-26879 N75-20223 FLETCRER, L. S. Beat transfer in separated and reattached flows - F An annotated review PACKRELL, J. E. A7 5-26685 Calculation of two-dimensional and axisymmetric FOWLER, H. S. bluff body potential flow Some air cushion technology research in Canada [IC-AERO-74-07 N75-19191 N75-20251 FAIRBANKS, L. E. I FRIEDRICH, H. Flight-critical digital control system evaluation Comparison of evaluation procedures for the (AIAA PAPER 75-566] P.75-26725 determination of flight-mechanical coefficients FAUVEL, C. and derivatives from flight tests Lifting surface for aircraft N75-19254 (NASA-TT-F-16241] N75-20290 Evaluation of flight tests of the FIAT G-91 T3 by FEDOSOY, V. P. means of regression analysis Supersonic flow past intersecting surfaces N75-19259 A75-26882 FROUZ, J. FENTON, N. N. Adaptive control system with reference model A tactual pilot aid for the approach-and-landing A7 5-27912 task: Inflight studies N75-19131

B-4

PERSONAL AUTHOR INDEX BATASE, C.

FRYE, D. B., JR. GRIFFITH, B. E., IX Investigation of aircraft combustor noise Natural icing tests. 08-111 helicopter [AD-A001737] N75-19250 (AD-A002077] N75-19194 FURS?, A. GROESBECK, 0. A study of the effects on mice of smoke and gases Influence of multitube mixer nozzle geometry on from controlled fires in simulated aircraft cabins CTOL-OTW jet noise shielding A75-27073 [NASA-TM-X-71681] N75-19246 GROMOY, V. G. Numerical study of heat exchange at the stagnation G point of a sphere situated in a hypersonic GALLO ROSSO, D. stream of carbon dioxide gas Effect of forward speed on jet wing/flap A75-26888 interaction noise GROVER, .7. 11. B. [AIAA PAPER 75-475] A75-27932 Take-off instrument for assessing achieved GANGAIS, D. performance during take-off and a take-off Wind models for flight simulator certification of accident analysed in context landing and approach guidance and control systems A75-28769 [AD-A003801] N75-20352 GUMBEL, H. GABBIER, G. Interaction of military/civil position location Astrolabe - A synthetic circular aperture system and reporting systems for landing and navigation [AIAA PAPER 75-561] A75-28467 A75-28793 GUNNER, J. H. GARONRE, I. The impingement of non-uniform, axisymmetric, The coexistence of two supersonic plane flows in supersonic jets on a perpendicular flat plate the presence of a longitudinal pressure gradient A75-26684 N75-20209 GUTIERREZ, 0. A. GARRIERE, P. Noise of mo'el target type thrust reversers for Some notes on the thermodynamics of thrust engine-over-the-wing applications reversal in flight A75-27853 N75-20212 GAYL, J. -w Digital flight control systems for tactical fighters. Volume 2: Documentation of the HARAGUCHI, Y. digital control analysis software (DIGIK9N) Relation between scatter of fatigue life and S-N (AD-A002327] N75-20349 curve in aircraft structural aluminium alloy GILSON, R. U. 2024-T4 A tactual pilot aid for the approach-and-landing (NAL-TR-360] N75-19414 task: Inflight studies BANKS, H. L. N75- 19131 Natural icing tests. UH-1H helicopter GLASER, H. (AD-A002077] N75-19194 Feasibility of laser systems for aircraft landing BANNEN, K. A. operations under low visibility conditions Roll paper pilot (AD-A005637] N75-19198 N75-19134 GLUE, G. E. HARLOW, H. N. Miniature probes for use in gas turbine testing Users manual for UCIN vehicle occupant crash study (SAE PAPER 750094] A75-26589 model, version 2 GOETHERT, B. H. (AD-A001801] N75-19211 Air cushion landing systems for aircraft HARMED, H. 1.75-27983 General aviation's future need for research Air cushion landing systems for aircraft N75-20242 N75-20296 HAROLDSON, B.. GO!EZ, A. V. A structural weight estimation program (SWEEP) for TRW vortex-lattice method subsonic aerodynamic aircraft. Volume 4: Material properties, analysis for multiple-lifting-surfaces (N. structure temperature, flutter and fatigue surface) TRW program number HAO10B (AD-A002856] N75-20307 [NASA-CR-128588] N75-19178 HARRIS, 0. C. GOODSTEIN, B. Evaluation of active control technology for short Digital avionics information system /DAIS/ haul aircraft integrated test bed development [NASA-cR-131634] N75-20344 (AIAA PAPER 75-588] A75-26739 HARRISON, .7. V. 000DWILLIE, A. G. Feasibility of adapting a thin film permeable A comparison of flight loads counting methods and membrane to jet transport fuel tank inerting their effects on fatigue life estimates using system data from Concorde [AD-A003799] N75-20295 [ARC-CP-1304] N75-19227 BASHIMOYO, T. GORDON, K. Real-time simulation of jet engines with a digital On the calculation of non-linear aerodynamic computer(1), fabrication and characteristics of characteristics and the near vortex wake the simulator [AD-A002161] N75-19193 (RAE-LIB-TRANS-1768] N75-19274 GOULD, D. G. BASSAN, B. A. Estimates of the stability derivatives of a Noise generation and transmission in duct combustors helicopter and a V/STOL aircraft from flight data [AIAA PAPER 75-521] A75-27938 A75-28201 HAWKINS, T. D. F. Estimates of the stability derivatives of a The performance in illuminances up to 80,000 lux helicopter and a V/STOL aircraft from flight data of a light emitting diode display having a 3 mm N75-20250 character height GRANDY, A. F., JR. A15-21526 Stress intensity factors for some through-cracked HAWKINS, W. H. fastener holes The next forty years in aviation A75-28236 X75-20228 GRAVES, G. B., JR. BATASE, G. Airborne electronics for automated flight systems A structural weight estimation program (SWEEP) for N75-20232 aircraft. Volume 2: Program integration and GRAY, G. W. data management module. Part 1: Program Tiedown tests for air transport of the 1M542 integration sprint container [AD-A002852] N75-20302 [AD-A001844] N75-19210

8-5

BElLE!, M. PERSONAL AUTHOR INDEX

& strucutral weight estimation program (SWEEP) for Estimates of the stability derivatives of a aircraft. Volume 2: Program integration and helicopter and a V/STOL aircraft from flight data data management module. Part 2: Data - - N75-20250 management module BINUST, W. H. (AD-&002853] N75-20303 Evaluation of some control-volume techniques for A structural weight estimation program (SWEEP) for analysis of shock-boundary layer interactions in aircraft. Volume 2: Program integration and supersonic inlets data management module. Appendix A: Data [NASA-TN-1-3186] N75-20256 management module flow charts and FORTRAN lists BITANA, H. [AD-A002851] N75-20304 A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 2: Program integration and aircraft. Volume 6: Wing and empennage module. data management module. Part 1: Program Book 1: Technical discussion sections 1 and 2 integration [AD-A002864] N75-20310 [AD-A002852] N75-20302 A structural weight estimation program (SWEEP) for A strucutral weight estimation program (SWEEP) for aircraft. Volume 6: Wing and empennage module. aircraft. Volume 2: Program integration and Book 2: Technical discussion, sections 3 and 4 data management module. Part 2: Data [AD-A002865] N75-20311 management module A structural weight estimation program (SWEEP) for [AD-A002853] N75-20303 aircraft. Volume 6: Wing and empennage module. A structural weight estimation program (SWEEP) for Book 3: Technical discussion, section 5 aircraft. Volume 2: Program integration and [AD-A002866] N75-20312 data management nodule. Appendix A: Data A structural weight estimation program (SWEEP) for management module flow charts and FORTRAN lists aircraft. Volume 6: Wing and empennage module. [AD-A002851] N75-20304 Appendix A: General information for module flow A structural weight estimation program (SWEEP) for charts and listings. Appendix 8: Program flow aircraft. Volume 3: Airloads estimation module charts,overlays (8,0), (14,0), (15,0), (16,0) [AD-A002854] N75-20305 and (17,0) A structural weight estimation program (SWEEP) for (.AD-A002859] N75-20313 aircraft. Volume 3: Airloads estimation A struttural weight estimation program (SWEEP) for module. Appendix A: Nodule flow charts and aircraft. Volume 6: Wing and empennage module. FORTRAN lists. Appendix B: Sample output Appendix C: Program flow charts, overlays (9,0) [AD-A002855] •, N75-20306 and (10,0) A structural weight estimation program . (SWEEP) for [AD-A002860] N75-20314 aircraft. Volume 5: Air induction system and A structural weight estimation program (SWEEP) for landing gear modules. Part 1: Air induction aircraft. Volume 6: Wing and empennage module. system module Appendix D: Program flow charts, overlay (18,0) [AD-A002857] N75-20308 [AD-A002861] N75-20315 A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 5: Air induction system and aircraft. Volume 6: Wing and empennage module. landing gear nodules. Part 2: Landing gear Appendix E: Program listings, overlays (8,0) nodule (14,0), (15,0) (16,0) , and (17,0) [AD-A002858] R75-20309 [AD-A002862] N75-20316 A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 7: Fuselage module aircraft. Volume 6: Wing and empennage module. [AD-A002867] N75-20318 Appendix F: Program listings, overlays (9,0) A structural weight estimation program (SWEEP),for (10,0) and (18,0) aircraft. Volume 7: Fuselage module. Appendix [AD-A002863] N75-20317 A: Nodule flow charts and FORTRAN lists. A structural weight estimation program (SWEEP) for Appendix B: Fuselage module sample output aircraft. Volume 8: Programmer's manual - [AD-A002868] N75-20319 [AD-A002869] N75-20320 A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 8: Programmers manual aircraft. Volume 9: User's manual (AD-A002869] N75-20320 [AD-A002870] N75-20321 A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 9: User's manual aircraft. Volume 9: User's manual, appendix A (AD-A002870] N75-20321 (AD-A002871] N75-20322 A structural weight estimation program (SWEEP) for BEALE!, N. aircraft. Volume 9: User's manual, appendix A Design of a digital-stability augmentation and [AD-A002871] N75-20322 control system with gust alleviation and nodal HODDER, B. • suppression An experimental study of the structure and A75-28432 acoustic field of a jet in a cross stream BRNDRICK, B. C. [AIAA PAPER 75-460] A75-28348 Self-testing digital flight control applications UODGE, U. L. [AIAA PAPER 75-568] A75-26727 The disappearance of the wake shock behind a BICKCOX, T. N. cylinder in a supersonic flow at high Reynolds Low speed and angle of attack effects on sonic and number • near-sonic inlets A75-26414 (NASA-CR-134778] N75-19184 HODSON,. C. BILL, C. D. A structural weight estimation program (SWEEP) for Self-testing digital flight control applications aircraft. Volume 4: Material properties, [AIAA PAPER 75-568] A75-26727 structure temperature, flutter and fatigue HILLE, B. [AD-A002856] N75-20307 Extension of the lifting line model for the HONICZ, U. F. helicopter rotor Theoretical and experimental studies of A75-28194 discrete-tone rotor-stator interaction noise HILTON, H. J. '- [AIAA PAPER 75-443] A75-27926 Air Traffic Control demonstration aspects of the HONBATH, J. F. Applications Technology Satellite-6 Evaluation of active control technology for short (AIAA PAPER 75-5621 A75-26723 haul aircraft HINDS, J. [NASA-CH-137634] N75-20344 Flight test evaluation of SECANT VECAS collision HOVDR, B. .3. avoidance system C-141 All Weather Landing System (AWLS) flight [AD-A002281 ] N75-19220 test report: Optimization and pre-experimental HINDSON, W. S. phases Estimates of the stability derivatives of a [AD-A003952] N75-20330 helicopter and a V/STOL aircraft from flight data A75-28201

5-6 PERSONAL AUTHOR INDEX KOEHLEE, E.

HOVE, N. S. JOHNSON, N. B. The generation of Sound by aerodynamic sources in Pitch paper pilot revisited an inhowogeneous steady flow N75-19133 A75-26463 JOHNSON, B. B., JR. HOVE, B. N. Operational use of the OH-i U helicopters in Effects of visual flight display dynamics on Arctic environment altitude tracking performance in a flight [AD-A002603] N75-19236 simulator JOHNSON, V. N75-19127 Shake test of rotor test apparatus in the 40- by HUBBARD, H. H. 80-foot wind tunnel Trends in aircraft noise control [NASA-TN--X-62418] 875-20350 N75-20229 JORGENSEN, L. B. RUBBER, P. Experimental aerodynamic characteristics for a Effects of friction and heat conduction on sound cylindrical body of revolution with side strakes propagation in ducts and various noses at angles of attack from 0 [AIAA PAPER 75-520] A75-28349 degrees to 58 degrees and Mach numbers from 0.6 HUFF, H. N. to 2.0 A study on aircraft map display location and (NASA-TM-X-3130] 875-19181 orientation JOUZEAU, J. L. N75-19128 The STRADA flight path tracking system BUNT, B. L. [RAE-LIB-TRANS-1813] 875-19209 The impingement of non-uniform, axisymmetric, supersonic jets on a perpendicular flat plate A75-26684 HUSTON, B. L. KAKUTA, Y. K Users manual for UCIN vehicle occupant crash study On fatigue crack arresting by a stop-hole in model, version 2 2024-T3 aluminum alloy sheet specimens [AD-A001801] N75-19211 (NAL-TR-359] 875-19413 KARANCHETI, K. An experimental study of the structure and acoustic field of a jet in a cross stream IACOB, C. [AIAA PAPER 75-460] A75-28348 A problem in supersonic jet theory Effects of friction and heat conduction on sound A75-26697 propagation in ducts ICHIKAWA, H. [AIAA PAPER 75-520] A75-28349 Real-tine simulation of jet engines with a digital KARLASHOV, A. V. computer(1) , fabrication and characteristics of Fatigue strength of D16T Duralumin at normal and the simulator elevated temperatures as a function of the [RAE-LIB-TRANS-1768) N75-19274 cycling rate ILIFF, K. V. A75-28866 An aircraft application of system identification KARNANKAR, J. S. in the presence of state noise Aircraft guidance for automatic collision avoidance [AD-A001936] 875-19234 A75-27178 ILLABIONOY, V. F. KAZA, K. B. V. Qualitative analysis of a family of extremums in a Rotation in vibration, optimization, and problem involving optimal control of aircraft aeroelastic stability problems motion 875-19167 A75-28676 KEEP, D. H. Mechanics of optimum three-dimensional motion of General aviation accident patterns aircraft in the atmosphere N75-19201 (NASA-TT-F-777] N75-19182 KIDA, T. INGLE, G. Lift coefficients on a supercavitating jet-flapped Flight determination of the rudder power and foil between rigid walls directional stability of the Fairey Delta 2 A75-26554 aircraft using a wingtip parachute KIZILOS, B. (ABC-CP-1298] N75-19267 Digital flight control system for tactical INTANO, G. P. fighter. Volume 1: Digital flight control Harowe altitude warning system evaluation system analysis (AD-A002583] 875-19241 [AD-A002320] 875-20348 INTUTIN, G. Digital flight control systems for tactical Antennas, a collection, issue 15 fighters. Volume 2: Documentation of the (AD-A002646] N75-19557 digital control analysis software (DIGIKON) ISOGAI, K. [AD-A002327] N75-20349 A method for predicting unsteady aerodynamic KLEIN, V. forces on oscillating wings with thickness in Longitudinal aerodynamic derivatives of a slender transonic flow near Mach number 1. part 1: delta wing research aircraft extracted from Two-dimensional theory. Part 2: Rectangular flight data wings [CRANFIELD-&EB0-27] N75-19175 (NAL-TR-368T-PT-1J 875-19174 Parameter identification applied to aircraft IVERSEN, J. U. (CRANFIELD-AERO-26] 875-19177 Inviscid to turbulent transition of trailing Longitudinal aerodynamic derivatives of a slender vortices delta-wing research aircraft extracted from (NASA-CR-142298] N75-19172 flight data [CRANFIELD-AERO-27] N75-20258 Parameter identification aplied to aircraft [CRANFIELD-AERO-26] N75-20259 JACKSON, B. N. - KOBATASHI, H. Important aspects of international air cargo Effect of interference between moving blade rows A75-26948 on cascade flutter. I - Experiment on compressor JACOBSON, I. D. cascade in flexure mode Ride quality evaluation. I A75-26553 A75-26849 KOCHETKOV, V. A. JAKUBONSKI, A. K. Dynamics of the motion of a body with allowance Wind tunnel studies of the turbulent wake behind for the unsteady state of the flow about it self propelled slender bodies [NASA-TT-F-16133) 875-19179 [AD-A002396] 075-20272 KOEHLER, B. JERIE, J. Determination of derivatives by a model with Part load specific fuel consumption of gas turbines automatic parameter A75-28650 V75-19265

B-i KONAR, A. F. PERSONAL AUTHOR INDEX

KONAR, A. F. A display evaluation methodology applied to Digital flight control system for tactical vertical situation displays fighter. Volume 1: Digital flight control N75-19137 system analysis A model based technique for the design of flight [AD-A002320] N75-20348 directors Digital flight control systems for tactical N75-19140 fighters. Volume 2: Documentation of the LET, J. E. digital control analysis software (DIGIKON) Wide bandwidth optical telemetry link for ground (AD-A002327] 875-20349 testing of equipment in high EMI environments KOPCHICK, N. A. A75-28181 Design of the DAIS control and display core element LIARSHEY, L. N. (AIAA PAPER 75-600] A75-26745 Characteristics of pressure fluctuations in KOROTKIN, A. I. distributed suction of a turbulent boundary layer The three-dimensional character of a cross flow 835-27052 around a circular cylinder LIPSEITS, TO. - B. 835-28654 Theory of transonic flow around a profile KOSHINUMA, I. A75-28651 Real-time simulation of jet engines with a digital LIGBTFOOT, F. V. computer(1) , fabrication and characteristics of An experimental TUNA network for airborne warning the simulator and control systems interoperability [RAE-LIB-TRANS-1768] 875-19274 demonstrations KOSKI, E. J. [AIAA PAPER 75-563] A75-26724 Investigation of 14.5mm API LINDLET, D. V. self-sealing/crashworthy fuel tank material Noise generation and transmission in duct combustors [AD-A001752] 875-19249 (AIAA PAPER 75-521] A75-27938 KOVALEV, B. D. LOISEAU, B. A subsonic axisysmetric wake in a viscous gas Determination of the dynamic characteristics of a A75-26891 helicopter by the branch-nodes method KOZLOVSKIT, V. I. A75-26479 Problems of designing passenger aircraft Unsteady lift forces on a vibrating cylinder in a (NASA-TT-F-808] 875-19223 supercritical flow KRAUSE, L. N. A75-26480 Miniature probes for use in gas turbine testing LONGSTAFF, I. D. [SAE PAPER 750094) A75-26589 A new J band pulsed radar altimeter A15-28781 LOPEZ, N. L. A theoretical method for calculating the I aerodynamic characteristics or arbitrary L&ANANEN, D. H. Development of a scientific basis for analysis of ejector-jet-flapped wing: Theoretical •analysis aircraft seating systems [AD-A002319] 875-20271 [AD-A004306] 875-20273 LORDI, 3. A. LACBMANN, S. G. Theoretical and experimental studies of Software engineering of a navigation and guidance discrete-tone rotor-stator interaction noise system for commercial aircraft [AIAA PAPER 75-443] A75-27926 (AIAA PAPER 75-575) A75-26733 LOSITO, V. LAING, K. J. Critical analysis and improvement of the Vibration and temperature survey production AR-1G source-panel method helicopter 875-28095 [AD-A002063] 875-19231 LUDWIG, G. B. LANGRISH, V. V. Theoretical and experimental studies of Helicopter rotor-produced modulation and aerial discrete-tone rotor-stator interaction noise field distribution in the band 30 to 76 MHz [AIAA PAPER 75-443] A75-27926 [RAE-TR-74032) 1175-19217 LYNWANDER, P. LAVA!, Z. Development of self-acting seals for helicopter Starting vortex, separation bubbles and stall - A engines numerical study of laminar unsteady flow around (NASA-CR-134739] 875-19243 an airfoil LYTOVINOY, V. N. A75-26212 An example of boundary layer flow with two LAWRENCE, B. L. instability regions Low speed and angle of attack effects on sonic and A75-28680 near-sonic inlets [NASA-CR-134778] N75-19184 LAWSON, K. ILI Airborne equipment for use with the microwave NAESTRELLO, L. landing system New evidence of the mechanisms of noise generation A75-28790 and radiation of a subsonic jet LEBEDEY, N. G. A15-28717 Development of acoustic disturbances in supersonic NAHESH, J. K. annular jets Digital flight control system for tactical A75-26234 fighter. Volume 1: Digital flight control LECAWN, B. P. system analysis The benefits of real time computer analysis of [AD-A002320] 875-20348 experimental aircraft flight test data Digital flight control systems for tactical 835-28801 fighters. Volume 2: Documentation of the LEDGER, J. A. digital control analysis software (DIGIKON) Computation of the velocity field induced by a (AD-A002327] 875-20349 planar source distribution approximating a MAIDEN, D. L. symmetrical non-lifting wing in subsonic flow Performance of an isolated two-dimensional (ABC-R/M-3751] 1175-20262 variable-geometry wedge nozzle with translating LERNEB, D. S. shroud and collapsing wedge at speeds up to Each Evaluation of the Rubino procedure for radio 2.01 telemetric theodolite positioning [NASA-TN-D-7906] 815-20247 [AD-A004317] 875-20353 RALKOY, S. N. LESTER, H. C. Organization of centralized maintenance of Unified analysis of ducted turbomachinery noise aircraft assemblies A15-27861 A75-27838 LEVISON, N. H. Evaluation of tactual displays for flight control 875-19132

B-B PERSONAL AUTHOR INDEX MITTAG, C F.

RADII, C. NCCONVILLE, C. Development of air transport and environmental Characteristics of MLS signals and their effect on requirements flight control systems A75-28228 A75-28791 MARAZZI, N. MCDONNELL, 5. 0. Survey on two calculation methods in transonic Digital flight control systems - Considerations in regime implementation and acceptance A75-28096 [AIAA PAPER 75-577] A75-26734 MARINI, N. MCFARLAND, A. L. Jet noise suppressors for turbojet engines Multi-site intermittent positive control A75-28227 algorithms for the discrete address beacon system MARTINDALE, C. [AD-A00111212] 875-19214 A structural weight estimation program (SWEEP) for NCKINSTRY, N. C. aircraft. Volume 2: Program integration and Software engineering of a navigation and guidance data management module. Part 1: Program system for commercial aircraft integration [AIAA PAPER 75-575] A75-26733 [AD-A002852] 875-20302 ACLEMORE, H. C. A strucutral weight estimation program (SWEEP) for Low-speed wind-tunnel tests of a 1/10-scale model aircraft. Volume 2: Program integration and of a blended arrow advanced supersonic transport data management module. Part 2: Data (NASA-TE-1-72671] 875-19226 management module MCTICUE, T. .V. [AD-A002853] 875-20303 F-is computational subsystem A structural weight estimation program (SWEEP) for [AIAA PAPER 75-590) A75-28470 aircraft. Volume 2: Program integration and MEHTA. U. B.B. data management module. Appendix A: Data Starting vortex, separation bubbles and stall - A management nodule flow charts and FORTRAN lists numerical study of laminar unsteady flow around [AD-A002851] 875-20304 an Pair foil A structural weight estimation program (SWEEP) for A75-26212 aircraft. Volume 5: Air induction system and MEYER, R_ W.W. landing gear modules. Part 1: Air induction Digital avionics - An overview system module [AIAA PAPER 75-553] A75-26721 [AD-A002857] 875-20308 MELLIW, S. A structural weight estimation program (SWEEP) for A structural weight estimation program (SWEEP) for aircraft. Volume 5: Air induction system and aircraft. Volume 4: Material properties, landing gear modules. Part 2: Landing gear structure temperature, flutter and fatigue module [AD-A002856] N75-20307 (AD-AO02858] 875-20309 MENICUCCI, D. F. A structural weight estimation program (SWEEP) for USA? aircraft takeoff length distances and aircraft. Volume 8: Programmer's manual climbout profiles [AD-A002869] 875-20320 [AD-A001826] 875-19878 A structural weight estimation program (SWEEP) for MERCER, G. . S. aircraft. Volume 9: User's manual Economics: General aviation cost factors [AD-A002870] N75-20321 875-19206 A structural weight estimation program (SWEEP) for MERCURIO, S. P. aircraft. Volume 9: User's manual, appendix A Reliability life cycle of a complex electronic [AD-A002871] N75-20322 airborne equipment MARTLEW, D. L. A7 5-27839 The use of Hartmann generators as sources of high MERZ, A. W. intensity sound in a large absorption flow duct Aircraft guidance for automatic collision avoidance facility A75-27178 (AIAA PAPER 75-529) A75-27939 MEYER, R. T. MARUTA, H. Evaluation of advanced lift concepts and fuel Effect of interference between moving blade rows conservative short-haul aircraft, volume 1 on cascade flutter. I - Experiment on compressor [WASA-CR-137525] 875-20291 cascade in flexure mode Evaluation of advanced lift concepts and fuel A75-26553 conservative short-haul aircraft, volume 2 MARYILLET, J. P. [NASA-CR-137526] 875-20292 The STRADA flight path tracking system MEYERS, N. A. [RAE-LIB-TRANS-1813] 875-19209 Operational use of the OH-i H helicopters in MASEK, R. V. Arctic environment Analytical comparison of hypersonic flight and (AD-A002603] 875-19236 wind tunnel viscous/invj scjd flow fields MEZHIROV, I. I. (NASA-CR-2489] 875-1-9586 Study of two hypersonic, axisymnetric, shaped MATTESON, F. H. nozzles with smooth contour Analysis of in-flight disintegration accidents A75-28658 N75-19197 MICHEL, A. N. MAY, D. P. L. Stability analysis of stochastic composite systems Helicopter rotor-produced modulation and aerial A75-27919 field distribution in the band 30 to 76 MHz MICHEL, N. [RAE-TR-74032] 875-19217 Experimental and theoretical analysis of three MCCABRIA, J. L. dimensional turbulent boundary layers in a Program for the development of a superconducting curved supersonic channel generator. Part 1: Phase 1 - A75-26476 [AD-A001649] 875-19546 MILLER, C. 0. MCCARTNEY, J. B. Analysis of general aviation accident records Ratio of peak frequencies of jet self and shear - 875-19200 noise spectra MINECK, R. E. A75-28400 Wind tunnel investigation of helicopter rotor wake MCCARTY, N. S. effects on three helicopter fuselage models Evaluation program on using compressor bleed air (NASA-TN-E-3185-SIJPPL] 875-20294 as a source of pneumatic power for fluidic MITCHELL, J. S. circuits - Wide bandwidth optical telemetry link for ground [AD-A002483] 875-20676 testing of equipment in high EMI environments MCCLURE, J. D. A75-28781 Environmental and operating requirements for fire MITTAG,C. F. extinguishing systems on advanced aircraft Natural icing tests.. Uil-1H helicopter [AD-A001640] 875-19228 [AD-A002077] 875-19194

3-9

HITAI, Y. PERSONAL AUTHOR INDEX

Huh, Y. NATLOR, F. R. Lift coefficients on a supercavitating jet-flapped Roll paper pilot foil between rigid walls 975-19134 A75-26554 NECBAEV, N. P. kOCKAPETRIS, L. J. Development and experimental evaluation of a Analytical comparison of hypersonic flight and numerical method for solving the inverse wind tunnel vious/inviscid flow fields axisymmetric problem in an axial turbine stage (NASA-CR-2489] 975-19586 with given velocity HBR, J. A75-26671 What have we learned from applying digital NELSON, E.-R. technology to cabin/passenger multiplex systems Experimental aerodynamic characteristics for a [AIAA PAPER 75-574] A75-26732 cylindrical body of revolution with side strakes HORECI, A. P. and various noses at angles of attack from 0 A study of the effects on mice of smoke and gases degrees to 58 degrees and Each numbers from 0.6 from controlled fires in simulated aircraft cabins to 2.0 A75-27073 [NASA-TH-X-3130] 4475-19181 HORFET, C. I. NELSON, R. C.. Developments in jet noise modeling - Theoretical The dynamic response of aircraft encountering predictions and comparisons with measured data aircraft wake turbulence (AIAA PAPER 75-477] A75-27933 N7 5-19170 HORIARTY, L. NEOHAN, D. D. Design and fatigue testing of integral armored SEEK BUS - A time division multiple access system servo actuator modified trunnion [AIAA PAPER 15-56 44] A75-281468 (AD-A002069) N75-19235 NICOLAS, 3.-N. NORIN, C. N. Determination of the dynamic characteristics of a Analysis of wreckage helicopter by the branch-modes method A75-26533 A75-26479 HORNISON, D. K. NIKOLAEV, ID. A. Field gvaluation of model 2 of the computer-based, Adaptive digital system for aircraft control individual trainer for the radar intercept officer A75-27182 [AD-A002705] N75-19278 NISHIO, K. HOSSHAN, D. C. Real-time simulation of jet engines with a digital Flight test of a digital guidance and control computer(1), fabrication and characteristics of system in a Dc-10 aircraft the simulator [AIAA PAPER 75-567] A75-26726 (RAE-LIB-TBANS-1768] 4475-19274 AOSUNOV, V. A. MISS, G. Allowance for the elastic deformation of the wing A SAAB-SCANIA developed method for obtaining in its own plane in the calculation of the stability derivatives from flight tests skewsymmetric vibrations of an aircraft with a 4475-19260 small-aspect-ratio wing NORTHEN, V. P. A75-28687 A new .3 band pulsed radar altimeter HOULANG, F. B. A75-28787 A specialised recording system for the measurement NOVAK, K. of helicopter rotor blade performance in flight Computation of airfoil DRAG profiles A75-28770 CREPT-35/1974] 4475-19165 HOLDER, J. A. NUGEN?, J. Some aspects of performance measurements in Exploratory wind tunnel tests of a nonsteady flight shock-swallowing air data sensor at a Mach N75-19262 number of approximately 1.83 NULLEY, N. U. [NASA-TM-X-56030] N75-20329 Instrumentation displays for future naval aircraft [AIAA PAPER 75-5991 A75-26744 HUNSEN, H. J. Evaluation of flight test of the FIAT G-91 T3 by OBERHATER, N. V. means of the method of forced oscillations A study of carburetor/induction system icing in N75-19258 general aviation accidents NTSHENKOV, V. I. [NASA-CR-143835] 4475-19208 A subsonic axisymmetric wake in a viscous gas OBBRHEINR, L. A75-26891 A pilot's report concerning the VTOL VAK 191 B A75-26900 OBLANAS, 1. Feasibility of laser systems for aircraft landing NAGARATSO, H. T. operations under low visibility conditions Aeroacoustics: Fan, STOL, and boundary layer [AD-A005631] 4475-19198 noise; sonic boom; aeroacoustic instrumentation OHATA, F. A75-28626 Real-time simulation of jet engines with a digital WAlSH, J. H. computer(1), fabrication and characteristics of A conformal head-up display for the visual approach the simulator N75-19138 [RAE-LIB-TRANS-1768] 4415-19274 NAHBA, H. OSBORNE, C. Lifting surface theory for a rotating subsonic or The prediction of turbulent heat transfer to wedge transonic blade row compression corners and cylinder-flare bodies at (ARC-R/N-37 140] N75-19185 hypersonic speeds NAPOLITINO, L. U. (IC-AERO-73-03] 4415-20264 Critical analysis and improvement of the OSDEN, S. S. source-panel method Flight test of a digital guidance and control A75-28095 system in a DC-10 aircraft NARBUT, V. [AIAA PAPER 75-567] A75-26726 Antennas, a collection, issue 15 OVERBURT, F. U. [AD-A0026 146] N75-19557 The range of airborne processing.available to the NARUCKI, C. V. future user of the Doppler ELS Evaluation of advanced lift concepts and fuel A15-28192 conservative short-haul aircraft, volume 1 OVSIANNIKOV, AH. [NASA-cR-137525] N75-20291 A method of calculating aerodynamic-nozzle Evaluation of advanced lift concepts and fuel profiles with passage through the sound barrier conservative short-haul aircraft, volume 2 A75-26881 (NASA-cR-137526] 4475-20292

B-iD

PERSONAL AUTHOR INDEX REID, J. S.

PIETRASS, A. Determination of aerodynamic derivatives of the P FIAT 0-91 T3 aircraft from flight tests by means PACKER, K. F. of manual analog model matching Analysis of wreckage 875-19257 A75-26533 Extraction of flight mechanic derivatives from PAGE, R. H. flight data by a manual analog matching technique Heat transfer in separated and reattached flows - [ESRO-TT-118] 875-20347 An annotated review PIR000VA, S. V. A75-26685 Calculation of the flow around blunted, PAKHOEOVA, Z. S. nonsymnetric cones with large aperture angle Hypersonic flow past pointed and blunt bodies with A75-28652 a concave generatrix PIRUNOV, U. G. A75-26896 A method of calculating aerodynamic-nozzle PLO, S. P. profiles with passage through the sound barrier New evidence of the mechanisms of noise generation A75-26881 and radiation of a subsonic jet PLOKHIKH, V. P. A75-28717 Mechanics of optimum three-dimensional motion of PARKER, J. A. aircraft in the atmosphere A study of the effects on nice of smoke and gases [NASA-TT-F-777] 875-19182 from controlled fires in simulated aircraft cabins PLUEBLEE, H. B. A75-27073 Radiation of duct noise out through a jet flow PARKER, J. H., JR. [AIAA PAPER 75-457] A75-27928 Program for the development of a superconducting PLUMER, J. B. generator. Part 1: phase i Development of scratch and spall resistant (AD-A001649] 875-19586 windshields PARLETI, L. P. [AD-A002513] 875-20300 Low-speed wind-tunnel tests of a 1/10-scale model PODSYPANINA, N. A. of a blended arrow advanced supersonic transport A method of profiling short two-dimensional nozzles [NASA-TM-X-72671) 875-19226 A75-26880 PASHIETSEY, V. T. POLITT, V. Qualitative analysis of a family of extremums in a The aircraft accident problem involving optimal control of aircraft A7 5-26498 motion PRIOLO, D. 835-28676 Problem of aircraft noise in the vicinity of PASSERELLO, C. B. airports Users manual for UCIN vehicle occupant crash study A7 5-28222 model, version 2 PUZINO, N. G. [AD-A001801] 875-19211 Characteristics of pressure fluctuations in PATTERSON, R. V. distributed suction of a turbulent boundary layer Evaluation of advanced lift concepts and fuel A75-27052 conservative short-haul aircraft, volume 1 [RASA-CR-137525] N75-20291 Evaluation of advanced lift concepts and fuel R conservative short-haul aircraft, volume 2 RADITZ, N. (NASA-CR-137526] 875-20292 Flight test evaluation of SECANT VECAS collision Evaluation of active control technology for short avoidance system haul aircraft - [AD-A002281] 875-19220 (NASA-CR-137634] 875-20344 RADWAN, N. S. PAULON, J. Internal-combustion engine/vapour cycle combination The coexistence of two supersonic plane flows in [OUEL-1097/74] 875-20336 the presence of a longitudinal pressure gradient RANDALL, C. C. N75-20209 Evaluation of -advanced lift concepts and fuel PECH, Z. conservative short-haul aircraft, volume 1 Adaptive control system with reference model (NASA-CR-137525] 875-20291 A75-27912 Evaluation of advanced lift concepts and fuel PETERS, D. A. conservative short-haul aircraft, volume 2 Flapping response characteristics of hingeless [NASA-CR-137526] 875-20292 rotor blades by a generalized harmonic balance RANLET, J. D. method Multi-slot film cooling of supersonic aircraft 875-19166 using air as a coolant PETERS, D. V. [AD-A002673] 875-19239 The performance in illuminances up to 80,000 lux RAO, C. K. of a light emitting diode display having a 3 mm Nonlinear torsional vibrations of thin-walled character height beams of open section A75-27526 A7 5-26410 PETRINO, A. B. REDDY, N. N. An experimental TDMA network for airborne warning Propulsive-lift noise of an upper surface blown and control systems interoperability flap configuration demonstrations [LILA PAPER 75-410] A75-21931 [AIAA PAPER 75-5631 A75-26724 REDHEAD, H. V. PEW, B. V. Development of an R.F. telemetry system Effects of visual flight display dynamics on A7 5-28778 altitude tracking performance in . a flight EEDIESS, H. A. simulator Status and trends in active dontrol technology N75-19127 N75-20236 PFIZENNLIER, B. REDING, L. On the instability of a sound-influenced free jet Determinaticn by means of hydraulic analogy of the [ESRO-TT-122] 875-20267 transonic flow in a blade cascade PHILPOT, B. G. N15-20213 The role of rotor blade blockage in the REES, D. A. propagation of fan noise interaction tones Development of statistical fatigue failure [LILA PAPER 75-447] A75-27927 characteristics of 0.125 inch 20244-T3 aluminum PIERCI, J. R. under simulated flight-by-flight loading Propagation of aircraft noise near airports - [AD-A002310] 875-205514 Effects of hillsides, inversions and source REID, J. S. directionality Natural icing tests. UN-1H helicopter A75-27859 (AD-A002077] . N75-191914

B-il REINEB, D. PERSONAL AUTHOR INDEX

REINER, D. EON, J. Provisional message formats for the DABS/NAS On the calculation of non-linear aerodynamic interface (revision 1) characteristics and the near vortex wake (FAA-RD-74-63-A) 875-19216 [AD-A002161] 875-19193 RENSHAW, J. H. ROTHAMEER, G. Evaluation of advanced lift concepts and fuel A structural weight estimation program (SWEEP) for conservative short-haul aircraft, volume 1 aircraft. Volume 3: Airloads estimation module (NASA-CH-137525] N75-20291 [AD-A002854] 875-20305 Evaluation of advanced lift concepts and fuel A structural weight estimation program (SWEEP) for conservative short-haul aircraft, volume 2 aircraft. Volume 3: Airloads estimation [NASA-CB-137526] 875-20292 nodule. Appendix A: Nodule flow charts and Evaluation of active control technology for short FORTRAN lists. Appendix 8: Sample output haul aircraft [AD-A002855] 875-20306 [NASA-CR-13763 14]. N75-20344 A structural weight estimation program (SWEEP) for REYNOLDS, P. H. J. aircraft. Volume 11: Flexible airloads Oceanic air route navigation with envelope match stand-alone program Loran-C [AD-A002873] 875-20324 [AD-A003800] 875-20286 ROY, N. EMOTES, R. P. On the future of let propulsion in subsonic Eigenvalue/eigenvector assignment for transport aviation multivariable systems A75-27777 A75-26312 EOZENSHTEIN, I. N. RIABCHENKO, V. P. Elementary method of graphic replotting of a Nonlinear problem of the unsteady flow past an characteristic of an uncooled turbocompressor airfoil lattice when the intake temperature and number of A75-28671 revolutions are varied RICCIUS, B. A75-26672 Plight tests with the V/STOL experimental aircraft RUBAN, A. I. VAK 191 B Hypersonic, viscous gas flow around a wing of A75-27985 small aspect ratio RICE, N. J. A75-28653 Spinning mode sound propagation in ducts with RUBBERY, P. B. acoustic treatment Sideslip of wing-body combinations A75-27854 [NASA-CR-114716] 875-20260 RICHARDS, L. G. ROBINS, P. N. Bide quality evaluation. I PLT 27 gas turbine engine exhaust emission and A75-26849 noise measurements RIGNET, J. V. [AD-A001728) 875-19251 Field evaluation of model 2 of the computer-based, individual trainer for the radar intercept officer [AD-A002705] 875-19278 S ROBERT, B. SALENHE, N. H. Determination by means of hydraulic analogy of the Feasibility of adapting a thin film permeable transonic flow in a blade cascade membrane to jet transport fuel tank inerting 875-20213 system ROBERTS, D. R. [AD-A003799] 875-20295 Boundary-layer pressure fluctuations at high SALOSINA, S. A. Reynolds numbers on a second free-flight test Characteristics of pressure fluctuations in vehicle distributed suction of a turbulent boundary layer [ARC-CP-1302] 875-19189 A75-27052 ROBERTS, L. SAHOILOY, C. On wake vortex alleviation Helicopter flight regimes N75-20231 [AD-A001220] 875-19268 ROBINSON, H. L. SANDERSON, K. C. Boundary. layer effects in supersonic flow over A new flight test data system for NASA cylinder-flare bodies aeronautical flight research [WRE-REPT-1238 (WR/D) ] 875-20257 A75-28774 ROCKWELL, H. SAZONOV, V. V. A structural weight estimation program (SWEEP) for Fatigue strength of D16T Duralumin at normal and aircraft. Volume 2: Program integration and elevated temperatures as a function of the data management module. Part 1: Program cycling rate integration A75-28866 [AD-A002852) 875-20302 SCARPINO, F. A. A strucutral weight estimation program (SWEEP) for Digital avionics information system /DAIS/ aircraft. Volume 2: Program integration and integrated test bed development data management module. Part 2: Data [AIAA PAPER 75-588) A75-26739 management module SCHAEFFER, 0. H. (AD-A002853) 875-20303 Wind models for flight simulator certification of A structural weight estimation program (SWEEP) for landing and approach guidance and control systems aircraft. Volume 2: Program integration and [AD-A003801] N75-20352 data management module. Appendix A: Data SCHAEUPELE, B. U. management module flow charts and FORTRAN lists Determination of the parameters of a system of [AD-A00 2851] . 875-20304 equations of motion from flight test data A structural weight estimation program (SWEEP) for 875-19263 aircraft. Volume 4: Material properties, SCHETZ, J. A. structure temperature, flutter and fatigue Wind tunnel studies of the turbulent wake behind [AD-4002856] 875-20307 self propelled slender bodies A structural weight estimation program (SWEEP) for [AD-A002396] 875-20272 aircraft. Volume 8: Programmer's manual SCHRALL, B. A. [AD-A002869] 875-20320 Unsteady viscous flow past a lifting plate BOB, V. T. N75-19171 A study of carburetor/induction system icing in SCHULZ, V. general aviation accidents Deutsche Gesellschaft fuer Luf t- und Eaumfahrt, (NASA-CR-143835) 875-19208 Yearbook 1973 ROECK, G. D. A75-27978 Dynamic loads and structural criteria study SCHEENDLER, H. C. [AD-A001739] 875-19195 Improvements to the SADSAH computer program for aeroelasticity analysis [NASA-CR-132617] 875-19173

B-12

PERSONAL AUTHOR INDEX STEV&RTSON, K.

SCOTT, G. A. Evaluation of advanced lift concepts and fuel New horizons in air traffic control conservative short-haul aircraft, volume 2 [AIAA PAPER 75-569] A75-26728 [NASA-CB-137526] N75-20292 SEBRING, J. N. SMITH, S.-H. The U.S. Candidate Microwave Landing System - A Fatigue-crack growth behavior of C-5A wing control new generation of avionics/ground equipment points [AflA PAPER 75-607] A75-28472 [.AD-A002553] N75-20299 SEMENENKO, V. N. SMITH, V. B. Cavitating flow past a vibrating thin-section wing An experimental TDNA network for airborne warning profile and control systems interoperability A75-26895 demonstrations SEMRAU, N. R. [AIAA PAPER 75-563] A75-26724 Investigation of aircraft combustor noise SNACKENBURG, S. J. [AD-A001737] N75-19250 Dynamic loads and structural criteria study SHRAFINI, T. V. (AD-A001739] N75-19195 Processable high temperature resistant polymer SOKOLOV, K. B. matrix materials Interaction between a sonic boom N-wave and an [NASA-TN-1-71682] N75-19367 obstacle near corner points SHAMES, 0. A75-28665 Plight test evaluation of SECANT VECAS collision SOPIN, L. avoidance system Antennas, a collection, issue 15 (AD-A002281] N75-19220 [AD-A0026 146] N75-19557 SHAMRIKOV, B. N. SORENSEN, J. A. Adaptive digital system for aircraft control Aircraft guidance for automatic collision avoidance A75-27182 A75-27178 SHEARER, J. N. SPEE, B. N. Impact of turbine modulation on variable-cycle Technical er. aluation report on Fluid Dynamics engine performance. Phase 1 and 2: Design Panel Symposium on V/STOL Aerodynamics fabrication and rig test, part 1 [AGARD-AR-78] N75-19585 [AD-1002543] N75-20337 SPEEDER, K. R. Impact of turbine modulation on variable-cycle Dynamic loads and structural criteria study engine performance. Phase 3: Engine [AD-A001739] N75-19195 modification and sea level test, part 2 SPRINGER, B. J. [AD-A002544] N75-20338 Environmental and operating requirements for fire Impact of turbine modulation on variable-cycle extinguishing systems on advanced aircraft engine performance. Phase 4: Additional [AD-A001640] N75-19228 hardware design and fabrication, engine SRINATHKUMAR, S. modification, and altitude test, part 3A Eigenvalue/eigenvector assignment for [AD-A002545] N75-20339 multivariable systems Impact of turbine modulation on variable-cycle A75-26312 engine performance. Phase 4: Additional STEELE, M. A. hardware design and fabrication, engine Impact of turbine modulation on variable-cycle modification, and altitude test, part 3B engine performance. Phase 1 and 2: Design [AD-A002546] N75-20340 fabrication and rig test, part 1 SHERIDAN, P. R. [AD-A002543] N75-20337 Computer simulation of maintenance for Impact of turbine modulation on variable-cycle multi-mission RPV's engine performance. Phase 3: Engine [ AD-A003351] N75-20253 modification and sea level test, part 2 SHETNIN, V. N. [AD-A002544] N75-20338 Problems of designing passenger aircraft Impact of turbine modulation on variable-cycle (NASA-TT-F-808] N75-19223 engine performance. Phase 4: Additional SHIFRIN, B. C. hardware design and fabrication, engine A method of profiling short two-dimensional nozzles modification, and altitude test, part 3A A75-26880 (AD-A002545] N15-20339 SHIMOKAVA, T. Impact of turbine modulation on variable-cycle Relation between scatter of fatigue life and S-N engine performance. Phase 4: Additional curve in aircraft structural aluminium alloy hardware design and fabrication, engine 2024-T4 modification, and altitude test, part 3B [NAL-TR-360] N75-191414 [AD-A002546] N75-20340 SHKADOV, L. N. STEPHENSON, D. Mechanics of optimum three-dimensional motion of Impact of turbine modulation on variable-cycle aircraft in the atmosphere engine performance. Phase 4: Additional (NASA-TT-F-777) N75-19182 hardware design and fabrication, engine SIEGEL, S. modification, and altitude test, part 38 A structural weight estimation program (SWEEP) for (AD-A002546] 1115-20340 aircraft. Volume 10: Flutter optination STEPHENSON, D. V. stand-alone program Impact of turbine modulation on variable-cycle [AD-A002872] N7520323 engine performance. Phase 1 and 2: Design SIGNORELLI, H. A. fabrication and rig test, part 1 Metal matrix composites for aircraft propulsion [AD-A002543] 1175-20337 systems Impact of turbine modulation on variable-cycle [NASA-TM-X-71685] N75-19245 engine performance. Phase 3: Engine SIMCOI, C. D. modification and sea level test, part 2 Supersonic jet noise suppression with multitube [AD-A002544] 1475-20338 nozzle/ejectors Impact of turbine modulation on variable-cycle [AIAA PAPER 75-501] A75-27936 engine performance. Phase 4: Additional SIMPSON, L. F. hardware design and fabrication, engine Visual Augmentation System (VAS) laboratory modification, and altitude test, part 3A demonstration and test results (AD-A002545) 4475-20339 [AD-A003323] N75-20332 STEVEN, C. P. SMITH, H. J. Shear lag analysis of thick skin aircraft structures A flight test investigation of the rolling moments [ATN-7409] 1175-19225 induced on a T-375 airplane in the wake of a STEVENS, H. C. K. 8-747 airplane An investigation of the noise from a scale model (NASA-TM-X-56031) N75-20221 of an engine exhaust system SMITH, P. B. [AIAA PAPER 75-459] A75-27929 Evaluation of advanced lift concepts and fuel STEIARTSON, K. conservative short-haul aircraft, volume 1 A non-uniqueness of the hypersonic boundary layer [NASA-CR-137525] N75-20291 A75-26195

8-13 STIHPSOJ, N. N. PERSONAL AUTHOR INDEX

STIHPSON, N. V. TESSARZIK, .3. .1. Manufacturer's overview Tests of laser metal removal for future flexible 575-19207 rotor balancing in engines STOKIC, D. [SAE PAPER 750170] A75-26591 A concept of flight dynamics control TESTER, B. J. A75-27180 Developments in jet noise modeling - Theoretical STONE, J. R. predictions and comparisons with measured data Noise of model target type thrust reversers for [AIAA PAPER 75-477] 4.75-27933 engine-over-the-wing applications THOIPSON, D. S.. A75-27853 Metallurgical factors affecting high strength Paper pilot ponders supersonic transports aluminum alloy production - 875-19135 A75-28529 STRAEIG, G. THORPE, A. C. Characteristics of the AJ 37 aircraft: Comparison Flight simulation of a Wessex helicopter: A of the results of vied tunnel and flight tests validation exercise 875-19261 [ARC-CP-1299] 875-20298 SUDDERTB, B. V. TIBBBTTS, .3. G. Development of longitudinal handling qualities Evaluation of advanced lift concepts and fuel criteria for large advanced supersonic aircraft conservative short-haul aircraft, volume 1 [NASA-CR-137635] 875-203145 (NASA-CR-137525] N75-20291 SUGITAHA, N. Evaluation of advanced lift concepts and fuel Real-time simulation of jet engines with a digital conservative short-haul aircraft, volume 2 computer(1), fabrication and characteristics of NASA-CR-137526] 875-20292 the simulator TIKEOMIROY, B. A. (RAE-LIB-TRANS-1768] N75-192711 Development and experimental evaluation of a SUN, P. B. numerical method for solving the inverse Flight path control and performance analysis, axisynmetric problem in an axial turbine stage phases 1 and 2. Integrated display, phase 3 with given velocity. (AD-A002014] 875-19269 A75-26671 SIBERO, J.. TILL, B. D. Low speed and angle of attack effects on sonic and A study for active control research and validation near-sonic inlets using the Total In-Flight Simulator (TIFS) (NASA-CR-134778] 875-19184 aircraft SYCUNV, V. V. [NASA-CR-132614] 875-19271 Hypersonic, viscous gas flow around a wing of TOKAEEV, V. P. small aspect ratio Fatigue strength of D16T Duralumin at normal and A75-28653 elevated temperatures as a function of the SZALAI, K. J. cycling rate Status and trends in active control technology A75-28866 N75-20236 TOESHIN, V. K. SZECBBNYI, E. Dynamics of the motion of a body with allowance Unsteady lift forces on a vibrating cylinder in a for the unsteady state of the flow about it supercritical flow (NASA-TT-F-16133] 875-19119 A75-26480 TOPUNOY, A. N. Development and experimental evaluation of a numerical method for solving the inverse T azisymmetric problem in an axial turbine stage TAKANASHI, S. with given velocity An exact solution for transonic potential flow A75-26611 past aerofoil sections TOWNE, D. H. [NAL-TR-383] 875-19176 Field evaluation of model 2 of the computer-based, TALABI, S. 0. individual trainer for the radar intercept officer Analysis of thick turbulent jet flowing round: A (AD-A002705] 875-19278 circular cylinder TRIOGS, T. J. 875-19168 Evaluation of tactual displays for flight control N75-19132 TANAKA, H. Effect of interference between moving blade rows on cascade flutter. I - Experiment on compressor cascade in flexure mode 4.75-26553 VAN BOLTER, T. TANNER, R. B. The computation of aerodynamic loads on helicopter Evaluation of tactual displays for flight control blades in forward flight, using the method of N75-19132 the acceleration potential A75-26700 TAYLOR, N. J. The development of a serial P.C.M. instrumentation VANDEVENNE, H. F. system Provisional message formats for the DABS/HAS A75-28797 interface (revision 1) 875-19216 TEJANI, S. (FAA-RD-74-63-A] A structural weight estimation program (SWEEP) for VENGHAUS, H. H. aircraft. Volume 4: Material properties, Study of transonic flow over various bodies structure temperature, flutter and fatigue N75-19169 [AD-A002856] 875-20307 VIEZEE, V. TELENIN, G. F. Feasibility of laser systems for aircraft landing Development of acoustic disturbances in supersonic operations under low visibility conditions annular jets [AD-A005637] 875-19198 A75-26234 VILLEMAIN, H. F. TEEPLENAN, J. N. Investigation of 14.5mm API Flight-critical digital control system evaluation self-sealing/crashworthy fuel tank material [AIAA PAPER 75-566] 4.75-26725 (AD-A001752] 875-19249 TERADA, H. VISBNEVETSKII, S. L. On fatigue crack arresting by a stop-hole in Hypersonic flow past pointed and blunt bodies with 2024-T3 aluminum alloy sheet specimens a concave generatrix [NAL-TR-359] 875-19413 A15-26896 TERIAEV, N. D. VONGLAHN, U. Adaptive digital system for aircraft control Influence of multitube mixer nozzle geometry on A75-27182 CTOL-OTW jet noise shielding [NASA-TM-X-71681] 875-19246

B-14 PERSONAL AUTHOR INDEX YOPP, N. B.

VONNETER, U. WENZEL, L. N. Manual evaluation of special flying maneuvers for An experimental investigation of compressor stall the determination of flight-mechanical using an on-line distortion indicator and signal coefficients and derivatives from flight tests conditioner N75-19255 [NASA-TN-X-3182] N75-20248 VOROBEV, N. F. WHARF, J. H. Supersonic flow past intersecting surfaces The performance in illuminances up to 80,000 lux A75-26882 of a light emitting diode display having a 3 mm VUKOBRATOVIC, N. character height A concept of flight dynamics control A75-27526 A75-27180 WHITE, F. C. Digital avionics from the viewpoint of ATA (AIAA PAPER 75-551) A75-28466 WHITE, J. A. WADDOUPS, N. E. OH-58A propulsion system vibration investigation Characterization of advanced composite materials [AD-A002672] 875-20341 for structural design WHITLOW, J. B., JR. A75-27695 Comparison of parametric duct-burning turbofan and WAGANATSU, H. T. non-afterburning turbojet engines in a Mach 2.7 Aeroacoustics: Jet and combustion noise; duct transport acoustics [NASA-TM-X-71679] N75-19247 A75-28629 VICKERS , N. H. WAGNER, H. The aerodynamic characteristics and trailing The range of validity in the case of two old vortex wake of propeller V/STOL configurations investigations. I - The origin of lift. II - A75-28522 Collision and gliding processes on the liquid WILCKRNS, V. surface Improvements in pilot/aircraft-integration by A75-27990 advanced contact analog displays WALKER, N. J. 875-19141 Application of a new slip-ringless propeller blade WILCOCK, T. measurement system Flight simulation of a Wessex helicopter: A A75-28771 validation exercise WASSON, N. F. (ARC-CP-1299) 875-20298 A theoretical method for calculating the WILDERNUTH, P. aerodynamic characteristics or arbitrary A structural weight estimation program (SWEEP) for ejector-jet-flapped wing: Theoretical analysis aircraft. Volume 3: Airloads estimation module [AD-A002319) N75-20271 [AD-A002854) 875-20305 WEAND, A. E., JR. A structural weight estimation program (SWEEP) for Vibration and temperature survey production AH-1G aircraft. Volume 3: Airloads estimation helicopter module. Appendix A: Nodule flow charts and (AD-A002063) 875-19231 FORTRAN lists. Appendix B: Sample output WEBB, N. U., JR. [AD-A002855) N75-20306 Harove altitude warning system evaluation A structural weight estimation program (SWEEP) for (AD-A002583] 1475-19241 aircraft. Volume 11: Flexible airloads WEBB, L. D. stand-alone program Exploratory wind tunnel tests of a [AD-A002873] 875-20324 shock-swallowing air data sensor at a Hach WILDEY, C. U. number of approximately 1.83 Wide bandwidth optical telemetry link for ground (NASA-TM-X-56030] N75-20329 testing of equipment in high EMI environments WEBER, F. A75-28781 Impact of turbine modulation on variable-cycle RILEY, D. R. engine performance. Phase 1 and 2: Design Low speed and angle of attack effects on sonic and fabrication and rig test, part 1 near-sonic inlets [AD-A002543] 875-20337 [NASA-CR-134778J 875-19184 Impact of turbine modulation on variable-cycle WILLIAMS, L. A. engine performance. Phase 3: Engine Field evaluation of model 2 of the computer-based, modification and sea level test, part 2 individual trainer for the radar intercept officer (AD-A002544) 875-20338 [AD-A002705] 875-19278 Impact of turbine modulation on variable-cycle WILLICH, W. engine performance. Phase 1: Additional Design of the DAIS control and display core element hardware design and fabrication, engine (AIAA PAPER 75-600] A75-26745 modification, and altitude test, part 3A WILSON, J. C. [AD-A002545] 875-20339 Wind tunnel investigation of helicopter rotor wake Impact of turbine modulation on variable-cycle effects on three helicopter fuselage models engine performance. Phase 4: Additional [NASA-TN-X-3185-SIJpPL] 1475-20294 hardware design and fabrication, engine WILSON, S. U. modification, and altitude test, part 38 An experimental TUNA network for airborne warning [AD-A002546] 1475-20340 and control systems interoperability WEBER, J. demonstrations Notes on the approximate solution of [AIAA PAPER 75-563) A75-26724 lifting-surface theory used in the RAE standard WINER, F. 3., JR. method Integrated avionics - Controls and displays for [ARC-R/N-3752] N75-19188 helicopter IFs operation VENEER, N. F. A75-28786 Effects of visual flight display dynamics on WOOD, K. altitude tracking performance in a flight Design and fatigue testing of integral armored simulator servoactuator modified trunnion 875-19127 [AD-A002069] 875-19235 WEINGARTEN, N. C. WRIGHT, C. P. A study for active control research and validation Supersonic jet noise suppression with multitube using the Total In-Flight Simulator (TIFS) nozzle/ejectors aircraft [AIAA PAPER 75-501] A75-27936 (NASA-CR-132614) 875-19271 WENPE, T. B. A study on aircraft map display location and orientation YOPP, V. B. Y N75-19128 Digital flight control systems - Considerations in implementation and acceptance [AIAA PAPER 75-5771 A75-26734

B-15

!OIJNGBLOOD, L. J., JR. PERSONAL AUTHOR INDEX

YOURGBL000, L. J., JR. Application of digital systems to Army avionics [AIAA PAPER 75-5871 A75-26738 Tn, T. H. Aerodynamic design of a rotor blade for minimum noise radiation N75-19221

z ZACEER, B. The definition of the notorsegler (DFVLR-SONDDR-424] A75-27596 ZABTATIN, T. Antennas, a collection, issue 15 [AD-A002646] N75-19557 ZDRATKOVICH, H. H. The disappearance of the wake shock behind a cylinder in a supersonic flow at high Reynolds number A75-26414 ZELENEVITZ, J. Influence of sound upon separated flow over wings 835-27495 ZEMLIANSKII, B. A. Calculation of heat transfer at the lines of flow of a three-dimensional boundary layer in a nonuniform external flow A75-26894 ZOREA, C. On the calculation of non-linear aerodynamic characteristics and the near vortex wake (AD-A002161) N75-19193 ZOBUNSEI, N. H. Unified analysis of ducted turbomachinery noise A75-27861

B-16 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING 1A Special Bibliography(Supp/. 59) JULY 1975

Typical Contract Number Index Listing PROJECT THEnIS 4175-26212 N75-20322 SRI PROJ. 2831 775-20323 NASW-2483 N75-10036 4475-19198 4475-20324 505-04 975-20256 F33615-72—C-1058 505-04-11-31 N75-20247 4175-203148 CONTRACT I 505-05 4415-20246 INASA ACCESStON 975-20349 NUMBER NUMBER 505-06-23 4475-20329 L ?33615-72-c-1202 505-06-81 775-19161 A75-28529 505-10-21 4475-20350 F33615-72-C-2003 51 11-52-01 975-20221 Listings in this rrrdeu are arranged alphanumerically by contract number. 975-20554 743-04-12-02 R75-19226 Under each contract number, the accession numbers denoting documents F33615-13-C-2032 743-05-01-01-00 4175-27933 that have been produced as a result of research done under that contract 4475-20260 F33615-73-C-2046 160-67-05 715-20293 are arranged in ascending order with the /AA accession numbers appearing 675-27926 501024 4475-19180 first. The accession number denotes the number by which the citation is F33615-73-C-2071 identified ineithefthe IAA0r srARsecton. N75-19228 F33615-73-C-3086 AF PROJ. 921C 03-t'O0a-2448 975-19237 975-19210 4475-19214 F33615-73-c-3127 Al' PROJ. 1366 DOT-FA70WAI-173 975-20271 N75-19239 975-20330 733615-73-C-3132 AF PROJ. 1467 DOT-FA729A-2893 975-19239 975-19237 475-27936 P33657-73-C-0281 A? PROJ. 1987 DOT-F6728A-2934 975-20299 975-20348 975-20352 975-20548 975-20349 DOT-FA72WA-3080 975-20777 A? PROJ. 3066 975-19212 F144520'-68-C-0018 975-20337 975-19213 675-26685 975-20338 DOT-FA72146-31 01 F44620_69_C0022 975-20339 N75-20273 475-26212 N? PROJ. 3145 DOT-FA72I1A-3134 NASW-2481 975-19179 975-19546 975-20295 975-19223 AF PROJ. 7351 DOT-FA72WAI-261 76844-21482 975-19182 975-20554 975-19216 96814-2483 975-20290 A? PROJ. 8224 DOT-FA73WA-3214 11881-11728 975-19586 N75-20342 N75-19198 9681-12017 N75-19173 A? PROJ. 9769 POT-PA71484-1027 9681-12018 975-19224 975-19234 975-20353 9651-12451 975-19183 A? .PROJ. 9781 DOT-rA747A-3388 NAS1-13267 675-26733 975-19193 975-20286 NAS1-13329 975-19271 AF-AFOSI1-2145-71 001-PH-1 1-7570 8A82-5006 975-20260 975-19193 975-14136 NAS2-6652 975-19137 AF-AFOSR-2492-73 001-08-20094 675-27937 975-19140 975-192314 DOF-TSC-535 475-27178 NAS2-6995 975-20291 ARPA ORDER 2310 001-05-40056 675-27938 975-20292 975-19278 FRI PROJ. 1146-8 975-20344 61/2037/057 975-20264 4475-19172 I1AS2-7966 975-20345 CNR-73,00339,07 FAA PROJ. 034-241-012 NAS3-14420 675-26591 675-28095 975-19216 NAS3-16823 975-19243 04 PROJ. 1F1-62208-AH-90 F19628-73-c-0002 NAS3-18035 915-19184 975-19195 975-19216 NAS4-2191 975-19208 975-19236 F336114-72-C-1801 9489-12330 875-19178 ON PROJ. 172-62205-618-88 675-26591 708-05-020-526 975-19235 F33615-71-C-1591 675-28348 ON PROJ. 101-62204-66-71 4475-19546 675-28349 975-19251 F33615-71-C-1625 NGR-47-005-181 04 PROJ. 1G1-72207-NA-110 975-20337 675-26849 975-19250 4475-20338 98 PROJ. 122-303 ON PROJ. 1G2-62207-Aff-89 975-20339 4475-19211 775-20341 975-20340 4444 PROJ. 213-114 DA PROJ. 1728005 F33615-71-c-1805 4475-20331 975-20300 675-28529 NRC 6-2003 675-28400 DNAB07-72-C-0161 F33615-71-c-1922 NSF GK-33739 675-27919 975-19269 975-20301 NSFGK-42133 675-27495 046807-73-C- 0337 975-20302 NS 3-2007 675-283148 975-19219 4175-20303 675-28349 DANJO1-71-C-0840 975-20304 NSG-2040 4475-19172 975-20332 975-20305 900014-67-6-0226-0005 DAA302-73-C-00 14 975-20305 975-20343 975-19236 N75-20307 N00014-72-A-0027-0002 OANJ02-73-C-0017 975-20303 975-19211 4475-20341 975-20309 4400014-72-A-0136-0004 DAAJ02-73-C-0068 4475-20310 975-20272 975-19251 975-20311 J N00014-73-C-0031 046302-73-C-0088 975-20312 4475-19132 975-19250 4475-20313 3000 14-73-C-0291 DNAJ02-73-C-0099 4475-20314 4475-20331 4475-19249 975-20315 361339-73-2-0065 DAAJ02-74-c-0013 N75-20316 975-19278 775-19235 975-20317 962269-73-2-0476 DNAJ02-74-C-0018 4475-20318 N75-20676 775-19195 975-20319 P803. FEOD 975-19226

NASA-Langley, 1975 C-i 1. Report No. 2. Government Accession No. 3. Recipients Catalog No. NASA_SP-7037(59) 4. Title and Subtitle 5. Report Date AERONAUTICAL ENGINEERING July 1975

A Special Bibliography (SupplementSupplement 59,i 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 ii. Contractor Grant No. Washington, DC 20546

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 368 reports, articles, and other documents introduced into the NASA scientific and technical information system in June 1975.

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

19. Security Oassif. (of this report) 20 . Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified Unclassified 110 $4.00 HC

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NASA CONTINUING BIBLIOGRAPHY SERIES

NUMBER TITLE FREQUENCY NASA SP--7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine, space medicine, and space biology NASA SP--7037 AERONAUTICAL ENGINEERING Monthly Engineering, design, and operation of aircraft and aircraft components NASA SP -7039 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and applications for patent NASA SP--7041 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft NASA SP -7043 ENERGY Quarterly Energy sources, solar energy, energy conversion, transport, and storage NASA SP-7500 MANAGEMENT Annually Program, contract, and personnel management, and management techniques

Details on the availability of these publications may be obtained from: SCIENTIFIC AND TECHNICAL INFORMATION OFFICE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D.C. 20546